A 320 Simulator Malfunctions

A320 SIMULATOR MANUAL SIMULATOR

A320 SIMULATED MALFUNCTIONS DESCRIPTION

This document must be used for training purpose only.

Under no circumstances should this document be used as a reference.

It will not be updated.

All rights reserved. No part of this manual may be reproduced in any form, by photostat, microfilm, retrieval system, or any other means, without the prior written permission of Airbus Industrie.

_ A320 SIMULATOR MANUAL SIMULATOR

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A320 SIMULATED MALFUNCTIONS DESCRIPTION

TABLE OF CONTENTS

Page

Chapter 1 - ADIRS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Chapter 2 - Air Bleed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 Chapter 3 - Air Conditioning/Ventilation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 Chapter 4 - Anti-Ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 47 Chapter 5 - APU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57 Chapter 6 - Attendant/Maint. Computer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 65 Chapter 7 - Cabin Pressure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 73 Chapter 8 - DMC/FWC/SDAC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 83 Chapter 9 - Doors . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 101 Chapter 10 - EIS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 107 Chapter 11 - Electrical Power 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 117 Chapter 12 - Electrical Power 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 131 Chapter 13 - Engine CFM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 149 Chapter 14 - Engine Parameters CFM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 199 Chapter 15 - FAC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 221 Chapter 16 - FADEC CFM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 231 Chapter 17 - Fire Protection/Smoke . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 241 Chapter 18 - Flight Computer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 251 Chapter 19 - FMGC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 259 Chapter 20 - Fuel A320 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 287 Chapter 21 - Hydraulic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 301

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Chapter 22 - Instruments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 325 Chapter 23 - Landing Gear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 333 Chapter 24 - Pitch Control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 349 Chapter 25 - Roll Control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 375

_ DATE : NOV 1998

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_ A320 SIMULATOR MANUAL SIMULATOR

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A320 SIMULATED MALFUNCTIONS DESCRIPTION

TABLE OF CONTENTS

Page

Chapter 26 - Radio NAV . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 387 Chapter 27 - Tires/Brakes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 403 Chapter 28 - Yaw Control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 419 Chapter 29 - Engine IAE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 423 Chapter 30 - Engines Parameters IAE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 473

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Chapter 31 - FADEC IAE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 499

_ DATE : NOV 1998

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION ADIRS

CHAPTER 1 - ADIRS CONTENTS: IR 1 FAULT IR 2 FAULT IR 3 FAULT ADIRS 1 FAULT ADIRS 2 FAULT ADIRS 3 FAULT ADR 1 FAULT ADR 2 FAULT ADR 3 FAULT IR 1 PITCH + 5 DEG IR 1 HDG + 5 DEG IR 1 HDG + 15 DEG IR 2 ROLL + 5 DEG AIRSPEED CHANNEL ADR 1 FAULT AIRSPEED CHANNEL ADR 2 FAULT ALTITUDE CHANNEL ADR 1 FAULT ALTITUDE CHANNEL ADR 2 FAULT

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ALPHA CHANNEL ADR 1&2 FAULT

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ADIRS

CHAPTER 1: ADIRS MALFUNCTION

: IR 1 FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: IR1 FAILURE (OUTPUT ELECTRONICS: 3 High Speed ARINC Bus fail)

CONSEQUENCE

:

- All output data from IR1 will have a Signal Status Matrix (SSM) in failure warning - If the ATT/HDG switching is in neutral position, the appropriate flags appear on concerned displays: • 1. CAPT’s PFD doesn’t show the attitudes: ATT flag • -

2. CAPT’s ND doesn’t show the heading: HDG flag If the ATT/HDG switching is in CAPT/3 position, CAPT PFD and ND normal operations are restored ADIRS CDU ANNUNCIATOR of IR1 indicator “IR FAULT” comes on steady light Blank display when SYSTEM DISPLAY rotary switch is set to the inactive channel of IR1

- In Flight phases 1,2,3,6,9,10: • ECAM WARNING: NAV IR1 FAULT (see sheet FWC 34260) • LIGHT WARNING: Master Caution lights are on • Audio warning: single chime • It is impossible to have CAT 3 DUAL capability After successive action on “CLR” P/B (Ecam Control Panel), the STATUS page appears on the SYS CRT. Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). Cancelling malfunction restores normal operation. Set all switching in neutral position.

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DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ADIRS

CHAPTER 1: ADIRS MALFUNCTION

: IR 2 FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: IR 2 FAILURE (OUTPUT ELECTRONICS: 3 High Speed ARINC Bus fail)

CONSEQUENCE

:

- All output data from IR2 will have a Signal Status Matrix (SSM) in Failure Warning - If the ATT/HDG switching is in neutral position, the appropriate flags appear on concerned displays: • 1. F/O’s PFD doesn’t show the attitudes: ATT flag • -

2. F/O’s ND doesn’t show the heading: HDG flag If the ATT/HDG switching is in F/O/3 position, F/O PFD and ND normal operations are restored. ADIRS CDU ANNUNCIATOR of IR2 indicator “IR FAULT” comes on steady light Blank display when SYSTEM DISPLAY rotary switch is set to the inactive channel of IR2

- In Flight phases 1,2,3,6,9,10: • ECAM WARNING: NAV IR2 FAULT (see sheet 34270) • LIGHT WARNING: Master Caution lights are on • AUDIO WARNING: Single Chime • It is impossible to have CAT 3 DUAL capability After successive actions on “CRL” P/B (Ecam Control Panel) the STATUS page appears on the SYS CRT. Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). Cancelling malfunction restores normal operation Set all switching in neutral position.

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DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ADIRS

CHAPTER 1: ADIRS MALFUNCTION

: IR 3 FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: IR 3 FAILURE (OUTPUT ELECTRONICS: 3 High Speed ARINC Bus fail)

CONSEQUENCE

:

- All output data from IR3 will have a Signal Status Matrix (SSM) in Failure Warning - Local warnings on ADIRS CDU: • 1 - IR3 ANNUNCIATIOR “IR FAULT” comes on steady light • 2 - Blank display when SYSTEM DISPLAY rotary switch is set to the inactive channel of IR3 - If the ATT/HDG switching is set to CAPT/3 • 1. CAPT’s PFD doesn’t show the attitudes: ATT flag • 2. CAPT’s ND doesn’t show the heading: HDG flag - If the ATT/HDG switching is set to F/O/3 the same flags appear on PFD’s F/O & ND’s - In Flight phases 1,2,3,6,9,10 and ATT/HDG switching not on NORM position: • ECAM WARNING: NAV IR3 FAULT (see sheet 34290) • LIGHT WARNING: MASTER CAUTION light are on • AUDIO WARNING: SINGLE CHIME • It is impossible to have CAT 3 DUAL capability - After successive actions on “CLR” P/B (Ecam Control Panel), the STATUS page appears on the SYS CRT. - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

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- Cancelling malfunction restores normal operation. - Set all switching in neutral position.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ADIRS

CHAPTER 1: ADIRS MALFUNCTION

: ADIRS 1 FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: POWER SUPPLY FAILURES

CONSEQUENCE

:

- No ARINC emission from IR1 and ADR1 - If the ATT/HDG switching is in neutral position and the Air Data switching is in neutral position, the appropriate flags appear: • CAPT’s PFD and CAPT’s ND do not show all ADIRS 1 information • Flag HDG on VOR/DME RMI - If the ATT/HDG switching and the AIR DATA switching are in CAPT/3 position, CAPT PFD and ND normal operations are restored - All ADIRS CDU Annunciators from channel 1 are OFF - Blank display when SYSTEM DISPLAY rotary switch is set to the inactive channel of ADIRS 1 - In Flight phases 2,3,5,6,7,9: • ECAM WARNING: NAV ADR 1 FAULT (see sheet 34200) • LIGHT WARNING: MASTER CAUTION lights are on • AUDIO WARNING: Single Chime • It is impossible to have CAT 3 DUAL capability -

After successive actions on “CLR” P/B (Ecam Control Panel) The STATUS page appears on the SYS CRT. Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). Cancelling malfunction then setting INSTANTANEOUS ALIGN on instruction station restores normal operation.

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- Set all switching in neutral position.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ADIRS

CHAPTER 1: ADIRS MALFUNCTION

: ADIRS 2 FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: POWER SUPPLY FAILURES

CONSEQUENCE

:

- No ARINC emission from IR2 and ADR2 - If the ATT/HDG switching is in neutral position and the Air Data switching is in neutral position, the appropriate flags appear: • F/O’s PFD and F/O’s ND do not show all ADIRS 2 information • All ADIRS CDU Annunciators from channel 2 are OFF • -

Blank display when SYSTEM DISPLAY rotary switch is set to the inactive channel of ADIRS 2 ECAM WARNING: NAV ADR 2 FAULT (see sheet 34210) LIGHT WARNING: MASTER CAUTION lights are on AUDIO WARNING: Single chime

- It is impossible to have CAT 3 DUAL capability

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- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction then setting INSTANTANEOUS ALIGN on instruction station restores normal operation - Set all switching in neutral position.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ADIRS

CHAPTER 1: ADIRS MALFUNCTION

: ADIRS 3 FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: POWER SUPPLY FAILURES

CONSEQUENCE

:

- No ARINC emission from IR3 and ADR3 - All ADIRS CDU Annunciators from ADIRU3 are off - Blank display when SYSTEM DISPLAY rotary switch is set to the inactive channel of ADIRS3 - If the ATT/HDG switching is set to CAPT/3, the appropriate flags appear: • The CAPT’s PFD doesn’t not show the attitude and the anemometric information (ATT flag) • The CAPT’s ND doesn’t not show the heading and wind information (HDG flag) • HDG flag appears on VOR/DME RMI • ECAM WARNING: NAV ADR 3 FAULT (see sheet 34240) • LIGHT WARNING: MASTER CAUTION lights are on AUDIO WARNING: Single Chime It is impossible to have CAT 3 DUAL capability Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). Cancelling malfunction then setting INSTANTANEOUS ALIGN on instructor station restores normal operation. Set all switching in neutral position.

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DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ADIRS

CHAPTER 1: ADIRS MALFUNCTION

: ADR 1 FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: ADR 1 INTERNAL FAILURE

CONSEQUENCE

:

- If AIR DATA SWITCHING is in neutral position: • All outputs data are in failure warning • On CAPT PFD appropriate flags disable AIRSPEED AND ALTITUDE information - On CAPT ND: TAS is not displayed - If ECAM/ND XFR switching is on CAPT position: • SAT and TAT are not displayed on SYS CRT. - If AIR DATA SWITCHING is in CAPT/3 position, CAPT PFD and ND normal operations are restored. With ECAM/ND XFR swicthing in neutral position, SAT and TAT are normally displayed on SYS CRT. - On ADIRS CDU FAULT ANN of ADR1 is ON - In flight phases 2,3,5,6,7,9: • ECAM warning: NAV ADR 1 FAULT (see sheet 34200) • LIGHT warning: MASTER CAUTION lights are ON • AUDIO warning: SINGLE CHIME - After successive actions on “CLR” P/B (Ecam Control Panel). - The STATUS page appears on the SYS CRT. - The GPWS is no more operative: after approximately 4 seconds delay, the GPWS “FAULT” light comes on. • Alarms generated by ECAM: report to FWC board 34610 - It is impossible to have CAT 3 DUAL capability - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

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- Cancelling malfunction restores normal operation - Set all switching in neutral position

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ADIRS

CHAPTER 1: ADIRS MALFUNCTION

: ADR 2 FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: ADR 2 INTERNAL FAILURE

CONSEQUENCE

:

- If AIR DATA SWITCHING is in neutral position • All outputs data are in failure warning • On F/O PFD appropriate flags disable AIRSPEED and ALTITUDE information • On F/O ND: TAS is not displayed • On ADIRS CDU FAULT ANN of ADR2 is ON • SAT and TAT are not displayed on SYS CRT - If AIR DATA SWITCHING is in F/O/3 position, F/O PFD and ND normal operations are restored. SAT and TAT are displayed on SYS CRT. - In flight phases 2,3,5,6,7,9: • ECAM warning: NAV ADR 2 FAULT (see sheet 34210) • LIGHT warning: MASTER CAUTION light is ON AUDIO warning: SINGLE CHIME It is impossible to have CAT 3 DUAL capability After successive actions on “CLR” P/B (Ecam control Panel), the STATUS page appears on the SYS CRT. Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). Cancelling malfunction restores normal operation Set all switching in neutral position

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DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ADIRS

CHAPTER 1: ADIRS MALFUNCTION

: ADR 3 FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: ADR 3 INTERNAL FAILURE

CONSEQUENCE

:

- If AIR DATA SWITCHING is in neutral position • On ADIRS CDU FAULT ANN of ADR3 is ON • ECAM warning: NAV ADR3 FAULT - If AIR DATA SWITCHING is on CAPT/3 • On left PFD - AIRSPEED & ALTITUDE FLAGS • On left ND: TAS is not displayed • On ADIRS CDU FAULT ANN of ADR3 is ON - In flight phases 2,3,6,9 : • ECAM warning: NAV ADR3 FAULT (see sheet 34240) • LIGHT warning: MASTER CAUTION lights are ON • Audio warning: SINGLE CHIME - If AIR DATA SWITCHING is on F/O/3 • On right PFD - AIRSPEED & ALTITUDE FLAGS • On right ND: TAS is not displayed • On ADIRS CDU FAULT ANN of ADR3 is ON - In flight phases 2,3,6,9 : • ECAM warning: NAV ADR3 FAULT • LIGHT warning: MASTER CAUTION lights are ON • AUDIO warning: SINGLE CHIME - It is impossible to have CAT 3 DUAL capability - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

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- Cancelling malfunction restores normal operation - Set all switching in neutral position

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ADIRS

CHAPTER 1: ADIRS MALFUNCTION

: IR 1 PITCH + 5 DEG

MALFUNCTION DESCRIPTION

:

CAUSE

: IR 1 INTERNAL DRIFT

CONSEQUENCE

:

- If the ATT/HDG switching is in neutral position, the pitch displayed data on Captain’s PFD increases of 5 DEG (in 1 second) - The “CHECK ATT” message appears on both PFDs - ECAM WARNING: NAV ATT DISCREPANCY (see sheet 34330) - LIGHT WARNING: Master Caution lights are on - AUDIO WARNING: Single Chime

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- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction on ATT/HDG switching setting on CAPT/3 restores the valid pitch displayed on CAPT’s PFD and the “CHECK ATT” message disappears on both PFD

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ADIRS

CHAPTER 1: ADIRS MALFUNCTION

: IR 1 HDG + 5 DEG

MALFUNCTION DESCRIPTION

:

CAUSE

: IR 1 INTERNAL DRIFT

CONSEQUENCE

:

- If the ATT/HDG switching is in neutral position, the displayed heading data on Captain’s PFD and ND increases of 5 DEG (in 1 sec) - The “CHECK HDG” flag appears on both PFDs and NDs - In Flight phases 1,2,3,5,6,7,9,10 : • ECAM WARNING: NAV HDG DISCREPANCY (see sheet 34300) • LIGHT WARNING: Master Caution lights are on

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• AUDIO WARNING: Single Chime - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction ATT/HDG switching setting on CAPT/3 restores the valid heading displayed on CAPT’s PFD and ND “CHECK HDG” message disappears on both PFDs and NDs.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ADIRS

CHAPTER 1: ADIRS MALFUNCTION

: IR 1 HDG + 15 DEG

MALFUNCTION DESCRIPTION

:

CAUSE

: IR 1 INTERNAL DRIFT

CONSEQUENCE

:

- If the ATT/HDG switching is in neutral position, the displayed heading data on Captain’s ND increases of 15 DEG (in 3 sec) - The “CHECK HDG” flag appears on both PFDs and NDs - In Flight phases 1,2,3,5,6,7,9,10 : • ECAM WARNING: NAV HDG DISCREPANCY (see sheet 34300) • LIGHT WARNING: Master Caution lights are on

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• AUDIO WARNING: Single Chime - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenace option selected). - Cancelling malfunction or ATT/HDG switching setting on CAPT/3 restores the valid heading displayed on CAPT’s ND and “CHECK HDG” message disappears on both ND

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ADIRS

CHAPTER 1: ADIRS MALFUNCTION

: IR 2 ROLL + 5 DEG

MALFUNCTION DESCRIPTION

:

CAUSE

: IR 2 INTERNAL DRIFT

CONSEQUENCE

:

- If the ATT/HDG switching is in neutral position, the roll displayed data on F/O’s ND increases of 5 DEG (in 1 second) - The “CHECK ATT” message appears on both PFDs - ECAM WARNING: NAV ATT DISCREPANCY (see sheet 34330) - LIGHT WARNING: Master Caution lights are on - AUDIO WARNING: Single Chime

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- Appropriate messages will be available on MCDU (CFDS function) - (when CFDS maintenance option selected) - Cancelling malfunction or ATT/HDG switching setting on F/O/3 restores the valid roll displayed on F/O’s PFD and the “CHECK ATT” message disappears on both PFD

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ADIRS

CHAPTER 1: ADIRS MALFUNCTION

: AIRSPEED CHANNEL ADR 1 FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: Octal label 206 computed airspeed: BAD TRANSMISSION

CONSEQUENCE

:

- If AIR DATA SWITCHING is in neutral position • On left PFD Airspeed scale is not displayed and red flag SPD appears • On left ND TAS is displayed • The GPWS is no more operative: after approximately 4 seconds delay, the GPWS “FAULT” light comes on. Alarms generated by ECAM: report to FWC boards 34440 & 34610 If AIR DATA SWITCHING is in CAPT/3 position, CAPT PFD normal operation is restored ECAM warning: NO WARNING Cancelling malfunction restores normal operation Set all switching in neutral position.

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DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ADIRS

CHAPTER 1: ADIRS MALFUNCTION

: AIRSPEED CHANNEL ADR 2 FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: Octal label 206 (computed airspeed) BAD TRANSMISSION

CONSEQUENCE

:

- If AIR DATA SWITCHING is in neutral position • On right PFD Airspeed scale is not displayed and red SPD flag appears On right ND, TAS is displayed If AIR DATA SWITCHING is in F/O/3 position, F/O PFD normal operation is restored ECAM warning: NO WARNING Cancelling malfunction restores normal operation Set all switching in neutral position.

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DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ADIRS

CHAPTER 1: ADIRS MALFUNCTION

: ALTITUDE CHANNEL ADR 1 FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: Octal labels 203,204,220 (Altitude, BARO COR ALT 1 & 2): BAD TRANSMISSION

CONSEQUENCE

:

- If AIR DATA SWITCHING is in neutral position - In STD selection: • On left PFD ALT flag appears - In BARO SELECTION: • On left PFD ALT flag appears - The GPWS is no more operative (Mk III only): after approximately 4 seconds delay, the GPWS “FAULT” light comes on. • Alarms generated by ECAM: report to FWC boards 34440 and 34610 If AIR DATA SWITCHING is in CAPT/3 position, CAPT PFD normal operation is restored. ECAM warning: NO WARNING Cancelling malfunction restores normal operation Set all switching in neutral position.

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DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ADIRS

CHAPTER 1: ADIRS MALFUNCTION

: ALTITUDE CHANNEL ADR 2 FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: Octals labels 203,204,220 (Altitude, BARO COR, ALT 1 & 2) BAD TRANSMISSION

CONSEQUENCE

:

- If AIR DATA SWITCHING is in neutral position • In STD selection - On right PFD ALTITUDE FLAG • -

In Baro selection On right PFD ALTITUDE FLAG If AIR DATA SWITCHING is in F/O/3 position F/O PFD normal operation is restored ECAM warning: NO WARNING

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- Cancelling malfunction restores normal operation - Set all switching in neutral position

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ADIRS

CHAPTER 1: ADIRS MALFUNCTION

: ALPHA CHANNEL ADR 1 & 2 FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: RESOLVER NOT SCALED

CONSEQUENCE

:

- Stall warning information is wrong on ADR1 & ADR2 output buses • ECAM warning: NO MESSAGE • LIGHT warning: NO WARNING • Audio warning: NO WARNING - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

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- Cancelling malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ADIRS

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DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION AIR BLEED

CHAPTER 2 - AIR BLEED CONTENTS: ENG 1 BLEED FAULT (HP VALVE) ENG 2 BLEED FAULT (IP VALVE) ENG 1 BLEED LEAK OXYGEN PRESS INC/DEC (psi) R WING BLEED LEAK APU BLEED LEAK

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X BLEED FAULT

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION AIR BLEED

CHAPTER 2: AIR BLEED MALFUNCTION

: ENG 1 BLEED FAULT (HP VALVE)

MALFUNCTION DESCRIPTION

:

CAUSE

: HP VALVE ENG1 stuck open or going to open position (4000HA1)

CONSEQUENCE

:

- If ENG1 BLEED P/B is on (panel 30VU) • Temp outlet precooler increases (function of N2 ENG1) - Then if temp outlet precooler 257degC, after delay: • Bleed valve 1 closes and BLEED 1 FAULT light comes on - If the aircraft is in flight phases 2, 6, 9 : - Then: • Single chime sounds • Master caution light comes on • Associated warning message appears on E/W CRT • “Bleed” page appears on the SYS CRT - When “ENG1 BLEED” P/B is switched OFF: • “ENG 1 BLEED FAULT” light remains on as long as the failure is present • “ENG1 BLEED OFF” light comes on • The action is fed back on the E/W & SYS CRT - After successive “CLR” (Ecam control panel)

U6KSC00

• The appropriate STATUS page appears on the SYS CRT - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION AIR BLEED

CHAPTER 2: AIR BLEED MALFUNCTION

: ENG 2 BLEED FAULT (IP VALVE)

MALFUNCTION DESCRIPTION

:

CAUSE

: Press regulating valve stuck in position

CONSEQUENCE

:

- If ENG 2 BLEED P/B is on (panel 30VU), -

If engine 2 N2 increase Then: PRV outlet press 2 increases Then if PRV outlet pressure 57psi, after delay: “Bleed 2 valve Fault”light comes on If the aircraft is in flight phases 2, 6, 9:

- Then: • Single chime sounds • Master caution light comes on • Associated warning message appears on E/W CRT • “Bleed” page appears on the SYS CRT - When “ENG2 BLEED” P/B is switched OFF: • “ENG 2 BLEED FAULT” light remains on as long as the failure is present • “ENG2 BLEED OFF” light comes on - The action is fed back on the E/W & SYS CRT - After successive “CLR” (Ecam control panel) - The appropriate STATUS page appears on the SYS CRT

U6KSC00

- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION AIR BLEED

CHAPTER 2: AIR BLEED MALFUNCTION

: ENG 1 BLEED LEAK

MALFUNCTION DESCRIPTION

:

CAUSE

: PYLON DUCT LEAK (LH)

CONSEQUENCE

:

- If ENG1 BLEED P/B is on (panel 30VU) - Then: Bleed valve 1, LH WING ANTI-ICE, X BLEED AND APU BLEED close and BLEED 1 FAULT light comes on - If the aircraft is in flight phases 1, 2, 6, 9, 10: - Then: • Single chime sounds • Master caution light comes on • Associated warning message appears on E/W CRT • “Bleed” page appears on the SYS CRT - When “ENG1 BLEED” P/B is switched OFF: • “ENG 1 BLEED FAULT” light remains on as long as the failure is present • “ENG1 BLEED OFF” light comes on • The action is fed back on the E/W and SYS CRT - After successive “CLR” (Ecam control panel) - The appropriate STATUS page appears on the SYS CRT

U6KSC00

- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION AIR BLEED

CHAPTER 2: AIR BLEED MALFUNCTION

: OXYGEN PRESS INC/DEC (psi)

PARAMETER

: CREW OXYGEN CYLINDER PRESSURE

MIN VALUE

: 1 psi MAX VALUE: 2500 psi CHANGE RATE: 300 psi/s

MALFUNCTION DESCRIPTION

:

CAUSE

: INC → FILLING OF THE OXYGEN CYLINDER

CONSEQUENCE

:

- INC: Pressure in the crew oxygen cylinder increases up to the value selected by the instructor. - DEC: Pressure in the crew oxygen cylinder decreases up to the value slected by the instructor. - The ECAM page displays: - 1 - OXYGEN HIGH PRESSURE INDICATION: • Green: When pressure is > 400 psi • Amber: When pressure is < 400 psi • An amber half frame appears when oxygen pressure is < 1500 psi. - 2 - REGUL LO PR INDICATION: • Appears amber in case of oxygen low pressure < 50 psi, detected on the low pressure circuit, if high pressure is < 50 psi, and at least one mask operated

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• When the pressure in the cylinder reaches 1 psi then there is no more air supply in mask after some breathings. - Cancelling the malfunction restores normal operation of the system. - The pressure in the cylinder remains at its value at the time of cancellation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION AIR BLEED

CHAPTER 2: AIR BLEED MALFUNCTION

: R WING BLEED LEAK

MALFUNCTION DESCRIPTION

:

CAUSE

: WING DUCT LEAK (RH)

CONSEQUENCE

:

- If ENG2 BLEED P/B is on (panel 30VU) - Then: BLEED valve 2, RH WING ANTI-ICE, X BLEED and APU BLEED close and BLEED 2 FAULT light comes on - If the aircraft is in flight phases 1, 2, 6, 9, 10: - Then: • Single chime sounds • Master caution light comes on • Associated warning message appears on E/W CRT • “Bleed” page appears on the SYS CRT - When “ENG2 BLEED” P/B is switched OFF • “ENG2 BLEED FAULT” light remains on as long as the failure is present • “ENG2 BLEED OFF” light comes on • The action is fed back on the E/W and SYS CRT - After successive “CLR” (Ecam Control Panel)

U6KSC00

• The appropriate STATUS page appears on the SYS CRT - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION AIR BLEED

CHAPTER 2: AIR BLEED MALFUNCTION

: APU BLEED

MALFUNCTION DESCRIPTION

:

CAUSE

: APU DUCT LEAK

CONSEQUENCE

:

- If APU BLEED P/B is on (panel 30VU) - Then: “APU BLEED VALVE” closes and “APU BLEED FAULT” light comes on - If the aircraft is in flight phases 1, 2, 6, 9, 10: - Then: • Single chime sounds • Master caution light comes on • Associated warning message appears on E/W CRT • “Air Bleed” page appears on the SYS CRT - When “APU BLEED” P/B is switched OFF • “APU BLEED FAULT” light remains on until the failure disappears • “APU BLEED ON” light goes out • The action is fed back on the E/W and SYS CRT - After successive “CLR” (Ecam Control Panel)

U6KSC00

• The appropriate STATUS page appears on the SYS CRT - Cancelling the malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION AIR BLEED

CHAPTER 2: AIR BLEED MALFUNCTION

: X BLEED FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: X Feed stuck closed (auto control motor failure)

CONSEQUENCE

:

- If APU BLEED on and X FEED sel sw on “AUTO” position - Then: • Cross feed valve stuck closed • Engine 2 starting not possible - After delay: • Appropriate message appears on E/W CRT • Single chime sounds • Master caution light comes on • “AIR BLEED” page appears on E/W CRT. - If X FEED sel sw on “OPEN” position - Then:

U6KSC00

• Cross feed valve opens - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION AIR CONDITIONING/VENTILATION

CHAPTER 3 - AIR CONDITIONING/VENTILATION CONTENTS: PACK 1 FAULT (OVERHEAT) PACK 2 FAULT (OVERHEAT) PACK 1 TEMP CONTROLER FAILS PACK 2 AUTO SHUT DOWN INOP FOR STARTING VENT BLOWERS LOW FLOW VENT EXTRACT LOW FLOW OVBD VENT EXTRACT VALVE OPEN COCKPIT HOT AIR OVERHEAT FWD CARGO ISOL VALVES FAULT AFT CARGO ISOL VALVES FAULT FWD CARGO COM EXTRACT FAN FAIL AFT CARGO HOT AIR FAULT AUTO REGULATOR FAIL (ZONE CNTRL FAIL) GRND COOL FAULT CAB FANS FAULT

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VALVE SKIN/HEAT EXCHANGER STUCK CLOSE

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION AIR CONDITIONING/VENTILATION

CHAPTER 3: AIR CONDITIONING/VENTILATION MALFUNCTION

: PACK 1 FAULT (OVERHEAT)

MALFUNCTION DESCRIPTION

:

CAUSE

: Pack 1 compressor sensor overheat (T > 260degC)

CONSEQUENCE

:

- If pack 1 P/B is on (panel 30VU) - then: • Compressor 1 outlet temperature increases • -

“PACK VALVE 1 FAULT” light comes on (after delay) When compressor outlet temp is higher then 230 C, temp becomes amber (advisory mode) If the aircraft is in flight phases 1, 2, 6, 9, 10: Then:

• Single chime sounds • Master caution light comes on • Associated warning message appears on E/W CRT • “AIR BLEED” page appears on the SYS CRT - When PACK 1 P/B is switched off: • “PACK VALVE 1 FAULT” light stays on and “PACK VALVE 1 OFF” light comes on • The action is fed back on the E/W and SYS CRT • When temperature below 250 degC, PACK VALVE 1 FAULT light goes out • Select pack valve 1 on • If fault comes on again • Select pack valve off - After successive “CLR” (Ecam Control Panel), the appropriate status page appears on the SYS CRT • PACK 1 PB switched off

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- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION AIR CONDITIONING/VENTILATION

CHAPTER 3: AIR CONDITIONING/VENTILATION MALFUNCTION

: PACK 2 FAULT (OVERHEAT)

MALFUNCTION DESCRIPTION

:

CAUSE

: Pack 2 compressor sensor overheat (T > 260degC)

CONSEQUENCE

:

- If pack 2 P/B is on (panel 30VU) - Then: • When compressor outlet temp is higher than 230 degC, temp becomes amber, (advisory mode) • Compressor 2 outlet temperature increase after delay: • “PACK VALVE 2 FAULT” light comes on - If the aircraft is in flight phases 1, 2, 6, 9, 10: - Then: • Single chime sounds • Master caution light comes on • Associated warning message appears on E/W CRT • “AIR BLEED” page appears on the SYS CRT - When PACK 1 P/B is switched off: • “PACK VALVE 2 FAULT” light remains on and • “PACK VALVE 2 OFF” light comes on • The action is fed back on the E/W and SYS CRT • When temperature below 250 degC • PACK VALVE 2 FAULT light goes out • Select pack valve 2 on • If fault comes on again • Select pack valve off - After successive “CLR” (Ecam Control Panel) - The appropriate STATUS page appears on the SYS CRT - PACK 1 PB switched off

U6KSC00

- Appropriate messages will be available on MCDU (CFDS function) - (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION AIR CONDITIONING/VENTILATION

CHAPTER 3: AIR CONDITIONING/VENTILATION MALFUNCTION

: PACK 1 TEMP CONTRLER FAILS

MALFUNCTION DESCRIPTION

:

CAUSE

: Pack 1 controller internal failure

CONSEQUENCE

:

- If PACK 1 is on (panel 30VU) - Then: • Pack 1 temperature is set at 15degC - If the aircraft is in flight phases 1, 2, 6, 9, 10 : - Then: • Associated warning message appears on E/W CRT

U6KSC00

• “AIR BLEED” page appears on the SYS CRT - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION AIR CONDITIONING/VENTILATION

CHAPTER 3: AIR CONDITIONING/VENTILATION MALFUNCTION

: PACK 2 AUTO SHUT DOWN INOP FOR STARTING

MALFUNCTION DESCRIPTION

:

CAUSE

: Failure of close relay 12 HB of the flow control valve RH “FCV” remain open

CONSEQUENCE

:

Aircraft on ground - Electrical power supply connected -

Engines stopped APU on and APU BLEED VALVE PB on Pack 1 & 2 P/B on Start engine 2 Pack 1 valve closes Pack 2 valve remains open

- After delay: • “PACK VALVE 2 FAULT” light comes on - Set pack 2 valve PB SW off • “PACK VALVE 2 FAULT” light remains on

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• “PACK VALVE 2 OFF” light comes on - When ditching is selected, pack 2 valve remains open.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION AIR CONDITIONING/VENTILATION

CHAPTER 3: AIR CONDITIONING/VENTILATION MALFUNCTION

: VENT BLOWERS LOW FLOW

MALFUNCTION DESCRIPTION

:

CAUSE

: BLOWER FAN FAULT (20HQ)

CONSEQUENCE

:

- If “BLOWER” P/B is on “AUTO” position (22VU) - Then: “BLOWER FAULT” light comes on - If the aircraft is in flight phase 1, 2, 6, 10: - Then: • Maintenance horn sounds (except phase 6) • Single chime sounds • Master caution light comes on • Associated warning message appears on E/W CRT • “PRESS” page appears on the SYS CRT - When “BLOWER FAN” P/B is switched OVRD • “BLOWER FAULT” light goes out and • “BLOWER OVRD” light comes on • The action is fed back on the E/W and SYS CRT - After successive “CLR” (Ecam Control Panel)

U6KSC00

• The appropriate STATUS page appears on the SYS CRT - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling the malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION AIR CONDITIONING/VENTILATION

CHAPTER 3: AIR CONDITIONING/VENTILATION MALFUNCTION

: VENT EXTRACT LOW FLOW

MALFUNCTION DESCRIPTION

:

CAUSE

: EXTRACT FAN FAULT (18HQ)

CONSEQUENCE

:

- If “Extract Fan” P/B is on “Auto” position (panel 22VU) - Then: “EXTRACT FAULT” light comes on - If the aircraft is in flight phases 1, 2, 6, 9, 10: - Then: • Maintenance horn sounds (except phase 6) • Single chime sounds • Master caution light comes on • Associated warning message appears on E/W CRT • “PRESS” page appears on the SYS CRT - When “Extract Fan” P/B is switched OVRD • “EXTRACT FAULT” light goes out and • “EXTRACT OVRD” light comes on • The action is fed back on the E/W AND sys crt - After successive “CLR” (Ecam Control Panel)

U6KSC00

• The appropriate STATUS page appears on the SYS CRT - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION AIR CONDITIONING/VENTILATION

CHAPTER 3: AIR CONDITIONING/VENTILATION MALFUNCTION

: OVBD VENT EXTRACT VALVE OPEN

MALFUNCTION DESCRIPTION

:

CAUSE

: Skin air outlet valve stuck open (22HQ)

CONSEQUENCE

:

- Aircraft in flight - If the aircraft is in flight phases 2, 3, 6, 9, 10: - Then: • Extract valve stuck open • Single chime sounds • Master caution light comes on • Associated warning message appears on E/W CRT

U6KSC00

• “PRESS” page appears on the SYS CRT - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected) - Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION AIR CONDITIONING/VENTILATION

CHAPTER 3: AIR CONDITIONING/VENTILATION MALFUNCTION

: COCKPIT HOT AIR OVERHEAT

MALFUNCTION DESCRIPTION

:

CAUSE

: Excessive trim air open position order

CONSEQUENCE

:

- If PACK 1 & 2 P/B are on (panel 30VU) - If HOT AIR P/B is on (panel 30VU) - Then: • Cockpit trim air valve go to full heat • -

Cockpit and duct temp increase When cockpit duct temp reaches 88 degC If the aircraft is in flight phases 1, 2, 6, 9, 10: Then:

• HOT AIR FAULT light comes on • HOT AIR VALVE closes • Single chime sounds • Master caution light comes on • Associated warning message appears on E/W CRT • “AIR COND” page appears on the SYS CRT - When temperature < 70 degC to reset the system • Select HOT AIR Pb OFF • HOT AIR FAULT light goes out • HOT AIR OFF light comes on - After successive “CLR” (Ecam Control Panel) - The appropriate STATUS page appears on the SYS CRT - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation - If HOT AIR PB is switched on: • HOT AIR FAULT light remains extinguished

U6KSC00

• HOT AIR OFF light goes out

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION AIR CONDITIONING/VENTILATION

CHAPTER 3: AIR CONDITIONING/VENTILATION MALFUNCTION

: FWD CARGO ISOL VALVES FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: Valve position disagree

CONSEQUENCE

:

• “FWD CARGO ISOL VALVES FAULT” light comes on - If the aircraft is in flight phases 1, 2, 6, 9, 10: - Then: • -

Warning message appears on the E/W CRT When “FWD CARGO ISOL VALVES” P/B is switched OFF: “FWD CARGO ISOL VALVES FAULT” light goes out After successive “CLR” (Ecam Control Panel)

U6KSC00

• The appropriate STATUS page appears on the SYS CRT - Cancelling the malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION AIR CONDITIONING/VENTILATION

CHAPTER 3: AIR CONDITIONING/VENTILATION MALFUNCTION

: AFT CARGO ISOL VALVES FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: Valve position disagree

CONSEQUENCE

:

• “AFT CARGO ISOL VALVES FAULT” light comes on - If the aircraft is in flight phases 1, 2, 6, 9, 10: - Then: • Associated warning message appears on the E/W CRT - When “AFT CARGO ISOL VALVES” P/B is switched OFF: • “AFT CARGO ISOL VALVES FAULT” light goes out • “AFT CARGO ISOL VALVES OFF” light comes on - After successive “CLR” (Ecam Control Panel)

U6KSC00

• The appropriate STATUS page appears on the SYS CRT - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling the malfunction restores normal position

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION AIR CONDITIONING/VENTILATION

CHAPTER 3: AIR CONDITIONING/VENTILATION MALFUNCTION

: FWD CARGO COM EXTRACT FAN FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: F/W FAN OVHT

CONSEQUENCE

:

- ON GROUND or if P < 1psi - If the aircraft is in flight phases 1, 2, 6, 9, 10: • Warning message appears on E/W CRT - After successive “CLR” (Ecam Control Panel) The appropriate STATUS page appears on the SYS CRT (FWD CRG VENT) Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). Clear failure Trip then reset circuit breaker 1HN restores normal operation

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• -

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION AIR CONDITIONING/VENTILATION

CHAPTER 3: AIR CONDITIONING/VENTILATION MALFUNCTION

: AFT CARGO HOT AIR FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: Valve position disagrees (AFT)

CONSEQUENCE

:

- If PACK 1 & 2 P/B are on (panel 30VU) - If HOT AIR (CARGO HEAT) P/B is on (panel 22VU) - Then: • -

HOT AIR CARGO FAULT light comes on After STATUS page selection (Ecam Control Panel) The appropriate STATUS page appears on the SYS CRT Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

- Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION AIR CONDITIONING/VENTILATION

CHAPTER 3: AIR CONDITIONING/VENTILATION MALFUNCTION

: AUTO REGULATOR FAIL (ZONE CNTRL FAIL)

MALFUNCTION DESCRIPTION

:

CAUSE

: Internal ZONE CNTRL PRIMARY CH fail

CONSEQUENCE

:

- In flight phases No 1, 2, 6, 9, 10 - If PACK 1 and 2 on (panel 30VU) - Then: • All ZONE temperature is set to 24 degC • Associated messages appear on E/W CRT • “AIR COND” page appears on DU-ECAM lower

U6KSC00

• Zone trim valve close on real time. - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION AIR CONDITIONING/VENTILATION

CHAPTER 3: AIR CONDITIONING/VENTILATION MALFUNCTION

: GRND COOL FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: Ground cool valve stuck open

CONSEQUENCE

:

U6KSC00

- TBD. Lack of data

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION AIR CONDITIONING/VENTILATION

CHAPTER 3: AIR CONDITIONING/VENTILATION MALFUNCTION

: CAB FANS FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: Failure of the left fan motor stator (15HG)

CONSEQUENCE

:

- If “CABIN RECIRCULATION FAN” P/B is on (22VU) and for flight phases 1, 2, 6, 9, 10 - Then: • “FAN” appears on air cond page (if aircond page selected) - When “CABIN RECIRCULATION FAN” P/B is switched off “Cabin recirculation fan off” light comes on Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). Cancelling malfunction restores normal operation Manual recycling of the corresponding CB is requird to reset this malfunction

U6KSC00

• -

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION AIR CONDITIONING/VENTILATION

CHAPTER 3: AIR CONDITIONING/VENTILATION MALFUNCTION

: VALVE SKIN/HEAT EXCHANGER STUCK CLOSE

MALFUNCTION DESCRIPTION

:

CAUSE

: AUX ISOL VALVE STUCK CLOSED (VALVE D)

CONSEQUENCE

:

- AIRCRAFT IN FLIGHT - If EXTRACT & BLOWER P/B SWS on “AUTO” position (22VU) then: • EXTRACT & BLOWER FAULT light comes on - If the aircraft is in flight phases 1, 2, 6, 9, 10: - Then after delay: • Single chime sounds • Master caution light comes on • Associated warning message appears on E/W CRT • “PRESS” page appears on the SYS CRT - After successive “CLR” (Ecam Control Panel)

U6KSC00

• The appropriate STATUS page appears on the SYS CRT - Cancelling the malfunction restores normal operation

DATE: SEP 1998

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U6KSC00

THIS PAGE INTENTIONALLY LEFT BLANK

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ANTI ICE

CHAPTER 4 - ANTI ICE CONTENTS: CAPT PITOT PROBE FAULT F/O PITOT PROBE FAULT CAPT TAT PROBE FAULT L WINDOW HEAT COMPUTER FAULT WING ANTI-ICE FAULT WING SUPPLY LO PRESSURE ICE DETECTION OVERHEAT

U6KSC00

ENG 2 NACELLE VALVE FAULT

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ANTI ICE

CHAPTER 4: ANTI ICE MALFUNCTION

: CAPT PITOT PROBE FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: Short circuit (detected by P.H.C)

CONSEQUENCE

:

If the Probes/window P/B ON The aircraft is in flight phases 1, 2, 6, 9, 10: Or if the Probes/window P/B OFF and ENG running the aircraft is in flight phases 2, 6, 9: Then: no local warning But: • Single chime sounds • Master caution lights on • Associated anti-ice messages appear on E/W CRT • “ANTI-ICE CAPT PITOT” If ADC3 avail: • Then message “AIR DATA SWITCHING... CAPT” appear on E/W CRT Cancel anti-ice Then after successive “CLR” • Status messages appear • “INOPS SYS • CAPT PITOT" Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ANTI ICE

CHAPTER 4: ANTI ICE MALFUNCTION

: F/O PITOT PROBE FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: Open circuit (detected by P.H.C.)

CONSEQUENCE

:

- If the probes/window P/B ON the aircraft is in flight phases 1, 2, 6, 9, 10 - Or the probes/window P/B OFF and ENG running the aircraft is in flight phases 2, 6, Then: no local warning But: • Single chime sounds • Master caution lights on • Associated anti-ice messages appear on E/W CRT • “ANTI-ICE CAPT PITOT” If ADC3 avail: • Then message “AIR DATA SWITCHING... CAPT” appear on E/W CRT - Cancel anti-ice Then after successive “CLR” • Status messages appear - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

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- Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ANTI ICE

CHAPTER 4: ANTI ICE MALFUNCTION

: CAPT TAT PROBE FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: Open circuit (detected by P.H.C.)

CONSEQUENCE

:

- If the aircraft is in flight phase 6: Then: no local warning But: • Single chime sounds • Master caution lights on • Associated anti-ice messages appear on E/W CRT • No SYS page called - Cancel anti-ice Then after successive “CLR”

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• Status messages appear - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ANTI ICE

CHAPTER 4: ANTI ICE MALFUNCTION

: L WINDOW HEAT COMPUTER FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: Loss of ventilation around the computer in hot temperature configuration causing an overheat

CONSEQUENCE

:

LOSS OF WINDOW HEAT COMPUTER - If the aircraft is in flight phases 1, 2, 6, 9, 10: • The single chime sounds • “CAUT” light illuminates

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• A messages appears on DU-ECAM upper - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ANTI ICE

CHAPTER 4: ANTI ICE MALFUNCTION

: WING ANTI-ICE FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: Left valve blocked in open position

CONSEQUENCE

:

Initial conditions - Wing Anti-ice valve full open (Wings Anti-ice SW to ON) Insert malfunction and set the wing Anti-ice SW to OFF. (If A/C on ground, set anti-ice SW to on and wait 35 s) Check that: • “FAULT” light comes on, on 25VU • If aircraft is in flight phase 1, 2, 3, 6, 9 or 10. Then, after a delay: • Single chime sounds • Master caution light comes on • Appropriate messages appear on E/W CRT • BLEED page appears on SYS CRT - After successive “CLR” - STATUS page appears with appropriate anti-ice messages - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

- Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ANTI ICE

CHAPTER 4: ANTI ICE MALFUNCTION

: WING SUPPLY LO PRESSURE

MALFUNCTION DESCRIPTION

:

CAUSE

: Right wing Anti-ice valve fault

CONSEQUENCE

:

IF BLEED VALVE AND/OR X FEED OPEN Then If wing anti-ice selected on: And aircraft in flight phases 1, 2, 6, 9 or 10 Then : • “FAULT” comes on, on 25vu • Single chime sounds • Master caution light comes on • Associated messages appear on E/W CRT Or: If bleed valve and X FEED valve shut and wing anti-ice on and aircraft in phases 1, 2, 6, 9, 10 Then • Appropriate message appears on E/W CRT • Fault comes on on 25VU • Single chime and master caution are triggered - After successive “CLR” - STATUS messages appear

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- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ANTI ICE

CHAPTER 4: ANTI ICE MALFUNCTION

: ICE DETECTION OVERHEAT

MALFUNCTION DESCRIPTION

:

CAUSE

: NOT POSSIBLE

CONSEQUENCE

:

(Ce système est prévu pour n’être monté que sur l’avion d’essais en vol).

U6KSC00

En outre nous ne disposons d’aucune information).

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ANTI ICE

CHAPTER 4: ANTI ICE MALFUNCTION

: ENG 2 NACELLE VALVE FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: Disagree between valve position and position selected

CONSEQUENCE

:

- When Eng 2 P/B is selected on Then: • Eng 2 anti-ice FAULT light comes on - If the aircraft is in flight phases 1, 2, 6, 9, 10: - Then after a delay: • Single chime sounds • Master caution light comes on • Associated warning message appears on E/W CRT - When Eng 2 P/B is switched off Then: • Eng 2 anti-ice FAULT light goes out • The action in fed back on the E/W CRT - After successive CLR (Ecam Control Panel) - The appropriate STATUS page appears on SYS CRT

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- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ANTI ICE

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THIS PAGE INTENTIONALLY LEFT BLANK

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION APU

CHAPTER 5 - APU CONTENTS: EXTINGUISHABLE FIRE UNEXTINGUISHABLE FIRE APU FAULT APU FAILS TO START (CONTACTOR STUCK OIL QTY INC/DEC (1) APU FLAP FAULT

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APU FUEL ISOL VALVE STUCK

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION APU

CHAPTER 5: APU MALFUNCTION

: EXTINGUISHABLE FIRE

MALFUNCTION DESCRIPTION

:

CAUSE

: FIRE IN APU COMPARTMENT

CONSEQUENCE

:

• “APU FIRE” light illuminates on “FIRE” panel, - On ground: • Automatic APU shut-down occurs, • “APU” fire extinguisher is automatically discharged, • “FAULT” light illuminates on “APU” panel, • “AVAIL” light goes out, • Mechanical horn sounds - For all Flight phases: • Audio CRC sounds, • Red “WARN” lights illuminate on glareshield, • Appropriate messages (nature of failure and actions to be performed) appear on E/W CRT, • “APU” page appears on SYS CRT. - “APU” Fire goes out: • “APU FIRE” light goes out,

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• Audio CRC is stopped. - External consequences: Electrical, Air conditioning, Fuel.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION APU

CHAPTER 5: APU MALFUNCTION

: UNEXTINGUISHABLE FIRE

MALFUNCTION DESCRIPTION

:

CAUSE

: FIRE IN APU COMPARTMENT

CONSEQUENCE

:

• “APU FIRE” light illuminates on “FIRE” panel, - On ground: • Automatic APU shut-down occurs, • After 3s APU fire extinguisher is automatically discharged, • “FAULT” light illuminates on “APU” panel, • “AVAIL” light goes out, • Mechanical horn sounds. - For all Flight phases: • Audio CRC sounds, • Red “WARN” lights illuminate on glareshield, • Appropriate messages (nature of failure and actions to be performed) appear on E/W CRT, • “APU” page appears on SYS CRT. - APU Fire doesn’t go out: • “APU FIRE” light remains ON, • Audio CRC goes out when APU FIRE P/B pressed, • Red “WARN” light remains on. - External consequences: Electrical, Air conditioning, Fuel. - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

- Cancelling malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION APU

CHAPTER 5: APU MALFUNCTION

: APU FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: FUEL SOLENOID FAILED SHORT-SHUT DOWN FROM E.C.B.

CONSEQUENCE

:

- If APU is running: • “FAULT” light illuminates on APU panel, • Shut down occurs. - If aircraft is in flight phases 1, 2, 6, 9, 10: • Audio single chime sounds, • Amber “Master Caution” lights flash on glareshield, • Appropriate messages (nature of failure and action to be performed) appear on E/W CRT, • “APU” page appears SYS CRT. - When MASTER SW P/B is selected OFF: • Action to be performed disappears on E/W CRT. - If APU is not running and normal starting procedure carried out: • Starting is impossible.

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• “FAULT” light illuminates on APU panel. - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION APU

CHAPTER 5: APU MALFUNCTION

: APU FAILS TO START (CONTACTOR STUCK)

MALFUNCTION DESCRIPTION

:

CAUSE

: START CONTACTOR 5KA STUCK OPEN

CONSEQUENCE

:

- If APU is not running and normal starting procedure is carried out: • After approximately 30 seconds “slow start” is detected, • “FAULT” light illuminates on APU panel, • Shut-down occurs. - If aircraft is in flight phases 1, 2, 6, 9, 10: • Audio single chime sounds, • amber “Master Caution” lights flash on glareshied, • Appropriate messages (nature of failure and action to be performed) appear on E/W CRT, • “APU” page appears on SYS CRT. - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

- Cancelling malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION APU

CHAPTER 5: APU MALFUNCTION

: OIL QTY INC/DEC (1)

PARAMETER

: OIL QTY

MIN VALUE

: 01 MAX VALUE: 5.7 1 CHANGE RATE: 1 1/S

MALFUNCTION DESCRIPTION

:

CAUSE

: Decrease in oil quantity due to a leak in oil circuit

CONSEQUENCE

:

- Oil level in tank reaches value selected by the instructor. If oil low level then: • Appropriate indication appears on SYS CRT - Oil temp increases: (if APU running) • “Fault” light illuminates on APU panel, • Shut down occurs. - If aircraft is in flight phases 1, 2, 6, 9, 10 then: (if APU running) • Audio single chime sounds, • Amber “Caution” lights flash on glareshield, • Appropriate messages (nature of failure and action to be performed) appear on E/W CRT,

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• “APU” page appears on SYS CRT. - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION APU

CHAPTER 5: APU MALFUNCTION

: APU FLAP FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: INLET FLAP LOCKED IN POSITION

CONSEQUENCE

:

- If APU is not running, normal starting procedure is carried out and inlet flap remains closed: • “FAULT” light illuminates on APU panel, • Shut down occurs after 30 seconds. • “FLAP OPEN” message doesn’t appear. If aircraft is in flight phases 1, 2, 6, 9, 10: • Audio single chime sounds, • Amber “Master Caution” lights flash on glareshield, • Appropriate messages (nature of failure and action to be performed) appear on E/W CRT, • “APU” page appears on SYS CRT. Cancelling malfunction restores normal operation - If APU is running, when the MASTER switch is switched OFF: • NORMAL APU SHUT-DOWN occurs but “FLAP OPEN” flashes approximately • 3 mn after MASTER SW OFF.

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- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION APU

CHAPTER 5: APU MALFUNCTION

: APU FUEL ISOL VALVE STUCK

MALFUNCTION DESCRIPTION

:

CAUSE

: LOSS OF C/B1QF AND C/B2QF

CONSEQUENCE

:

- If APU is running, APU Fire P/B switched ON and APU Fuel isol valve stuck in open position: If aircraft is in flight phases 1, 2, 6, 9, 10: • Audio single chime sounds, • Amber “Master caution” lights flash on glareshield, • Appropriate message (nature of failure) appears on E/W CRT. • FUEL page appears on SYS CRT. • EMERGENCY APU SHUT-DOWN Occurs (because of APU FIRE P/B ON) Cancelling malfunction restores normal operation. - If APU is not running, normal starting procedure is carried out and APU Fuel isol valve stuck in closed position:

U6KSC00

• Automatic SHUT-DOWN occurs 15 seconds after speed > 7 %. - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ATTENDANT/MAINT. COMPUTER

CHAPTER 6 - ATTENDANT/MAINT. COMPUTER CONTENTS: ACARS FAIL CIDS FAIL CFDIU FAULT DFDR FAULT QAR FAULT

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DMU FAULT

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ATTENDANT/MAINT. COMPUTER

CHAPTER 6: ATTENDANT/MAINT. COMPUTER MALFUNCTION

: ACARS FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Loss of ACARS MU electrical power

CONSEQUENCE

:

- Messages sent to A/C by the ground are not acknowledged ACARS menus on MCDU are not available ECAM warning and messages are conformed to ’23060’ referenced independent failure Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). Cancelling the malfunction restores normal operation

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-

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ATTENDANT/MAINT. COMPUTER

CHAPTER 6: ATTENDANT/MAINT. COMPUTER MALFUNCTION

: CIDS FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Directors 1 and 2 power failure (CB140RH, CB150RH and CB151RH)

CONSEQUENCE

:

-

The Passenger address system is inoperative. The cabin and flight crew interphone system is inoperative (FWD, AFT and EMER CALLS). The Passenger lighted signs are inoperative (NO SMOKING and FASTEN SEAT BELT). The service interphone system is inoperative.

- The emergency evacuation signalling system is inoperative. Consequences on ECAM: Report to FWC boards 23030 and 23080. - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

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ACTION: NIL - Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ATTENDANT/MAINT. COMPUTER

CHAPTER 6: ATTENDANT/MAINT. COMPUTER MALFUNCTION

: CFDIU FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: Loss of normal power supply

CONSEQUENCE

:

CFDIU IN BACK UP MODE Check that: On ground, engines OFF or ON: CFDS BACK UP MODE 80%: N1, N2, EGT & fuel flow move erractically lower or upper than in normal operation • Engine 1 virbrations increase • No warning • If throttle 1 is reduced so that N1 < 60%, normal operation is restored

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• Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS ENGINE DESCRIPTION CFM

CHAPTER 13: ENGINE CFM MALFUNCTION

: COMPRESSOR STALL # 2

MALFUNCTION DESCRIPTION

:

CAUSE

: Compressor stall

CONSEQUENCE

:

- If N1 > 80%: N1, N2, EGT & Fuel Flow move erratically lower or upper than in normal operation Engine 2 vibrations increase No warning If throttle 2 is reduced so that N1 < 60%, normal operation is restored Cancelling malfunction restores normal operation

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-

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS ENGINE DESCRIPTION CFM

CHAPTER 13: ENGINE CFM MALFUNCTION

: N2 ACCESSORY DRIVE LOST #1

MALFUNCTION DESCRIPTION

:

CAUSE

: Engine 1 N2 accessory shaft breaking

CONSEQUENCE

:

- The following equipments are no longer driven: • Lubrification unit • Hydraulic pump • Fuel and oil pumps • IDG • FADEC alternator - N2 indication drops to zero very quickly - Oil pressure drops to minimum value - Engine 1 stops • Single chime sounds • Master caution light comes on

U6KSC00

• Appropriate messages appear on the E/W CRT (LA77240) - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS ENGINE DESCRIPTION CFM

CHAPTER 13: ENGINE CFM MALFUNCTION

: N2 ACCESSORY DRIVE LOST #2

MALFUNCTION DESCRIPTION

:

CAUSE

: Engine 2 N2 accessory drive lost

CONSEQUENCE

:

- The following equipments are no longer driven: • Lubrification unit • Hydraulic pump • Fuel and oil pumps • IDG • FADEC alternator - N2 indication drops to zero very quickly - Oil pressure drops to minimum value - Engine 2 stops • Single chime sounds • Master caution light comes on • Appropriate messages appear on the E/W CRT (LA77250) • “ENGINE” page appears on the SYS CRT

U6KSC00

- When CFDS is operating in MENU mode and BITE TSD (Trouble Shooting Data) function is selected, the snapshot data corresponding to malfunction are displayed on the MCDU. (when BITE TSD maintenance option selected) - Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS ENGINE DESCRIPTION CFM

CHAPTER 13: ENGINE CFM MALFUNCTION

: HOT START #1

MALFUNCTION DESCRIPTION

:

CAUSE

: Faulty starter

CONSEQUENCE

:

- During start sequence: • N2 acceleration is slower than normal • EGT acceleration is higher than normal - As soon as too high EGT variation vs time is detected by FADEC, and if flight phase 1, 2, 6, 9 or 10: • Single chime sounds • Master Caution light comes on • Appropriate message appears on the E/W CRT (LA77080) • “ENGINE” page appears on the SYS CRT • Fuel HP shut off valve is closed for 6 seconds - The FADEC attempts to restart three more times by alternately opening the fuel HP valve, and closing it for 6 seconds as soon as start failure is detected: Appropriate message appears on the E/W CRT Start procedure is then aborted and the engine 1 “FAULT” light comes on. Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). Cancelling malfunction restores normal operation

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• -

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS ENGINE DESCRIPTION CFM

CHAPTER 13: ENGINE CFM MALFUNCTION

: HOT START #2

MALFUNCTION DESCRIPTION

:

CAUSE

: Higher initial fuel flow

CONSEQUENCE

:

- During start sequence: • Fuel flow is higher than normal • N2 acceleration is slower than normal • EGT acceleration is higher than normal. - As soon as a too high EGT variation vs time is detected by FADEC, and if flight phase 1,2,6,9 or 10: • Single chime sounds • Master Caution light comes on • Appropriate message appears on the E/W CRT (LA77090) • “ENGINE” page appears on the SYS CRT. • Fuel HP shut off valve is closed for 6 seconds - The FADEC attempts to restart three more times by altenately opening the fuel HP valve, and closing it for 6 seconds as soon as start failure is detected: • Appropriate message appears on the E/W CRT

U6KSC00

- Start procedure is then aborted and the engine 2 “FAULT” light comes on. - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS ENGINE DESCRIPTION CFM

CHAPTER 13: ENGINE CFM MALFUNCTION

: REVERSER STUCK #1

MALFUNCTION DESCRIPTION

:

CAUSE

: Failure of the reverser system

CONSEQUENCE

:

1 - If the malfunction is inserted with reverse retracted, they can’t be deployed. If not flight phase 3,4,5: Appropriate messages appear on the E/W CRT. (LA77500) 2 - If the malfunction is inserted with reverse deployed, they can’t be retracted. If not flight phase 3,4,5: Appropriate message appears on the E/W CRT (LA77500) 3 - If the Malfunction is inserted during reverse deployment, Amber REV indication remain in view at N1 indication. If not flight phase 3, 4, 5: Appropriate message appears on the E/W CRT (LA77500) Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS ENGINE DESCRIPTION CFM

CHAPTER 13: ENGINE CFM MALFUNCTION

: BOTH ENGINES FLAME OUT

MALFUNCTION DESCRIPTION

:

CAUSE

: Failure of the reverser system

CONSEQUENCE

:

1 - If the malfunction is inserted with reverse retracted, they can’t be deployed. If not flight phase 3,4,5: Appropriate messages appear on the E/W CRT (LA77510) 2 - If the malfunction is inserted with reverse deployed, they can’t be retracted. If not flight phase 3,4,5: Appropriate messages appear on the E/W CRT (LA77510) 3 - If the malfunction is inserted during deployment, Amber REV indication remain in view at N1 indication. If not flight phase 3, 4, 5: Appropriate message appears on the E/W CRT (LA77510) Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected)

U6KSC00

Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS ENGINE DESCRIPTION CFM

CHAPTER 13: ENGINE CFM MALFUNCTION

: HUNG START #1

MALFUNCTION DESCRIPTION

:

CAUSE

: FUEL FLOW CONTROL FAILURE

CONSEQUENCE

:

- During start sequence: • N2 increases then remains below 50 % • N1 increases then remains below 30 % • Starter valve doesn’t close - If starter valve has opened for more than 2 minutes during automatic start sequence: If flight phases 1, 2, 6, 9, or 10: • Single chime sounds • Master caution light comes on • Appropriate messages appear on the E/W CRT (LA77180)

U6KSC00

- Appropriate messages will be available on MCDU (CFDS function) when CFDS maintenance option selected. - Cancelling malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS ENGINE DESCRIPTION CFM

CHAPTER 13: ENGINE CFM MALFUNCTION

: HUNG START #2

MALFUNCTION DESCRIPTION

:

CAUSE

: Faulty starter

CONSEQUENCE

:

- During start sequence: • N2 increases then remains below 50% • N1 increases then remains below 30% • Starter valve doesn’t close - If starter valve has opened for more than 2 minutes during automatic start sequence: If flight phases 1, 2, 6, 9, or 10: • Single chime sounds • Master caution light comes on • Appropriate messages appear on E/W CRT (LA77185)

U6KSC00

- Appropriate messages will be available on MCDU (CFDS function) when CFDS maintenance option selected. - Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS ENGINE DESCRIPTION CFM

CHAPTER 13: ENGINE CFM MALFUNCTION

: N1 ROTOR SEIZED #1

MALFUNCTION DESCRIPTION

:

CAUSE

: N1 rotor seized during start up

CONSEQUENCE

:

- Engine 1 N1 speed remains at zero - Other parameter increase normally - If flight phases 2, 3: • Single chime sounds • Master caution light comes on • Appropriate messages appear on the E/W CRT (LA77170)

U6KSC00

• “ENGINE” page appears on the SYS CRT - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS ENGINE DESCRIPTION CFM

CHAPTER 13: ENGINE CFM MALFUNCTION

: N1 ROTOR SEIZED # 2

MALFUNCTION DESCRIPTION

:

CAUSE

: N1 rotor seized during start up

CONSEQUENCE

:

- Engine 2 N1 speed remains at zero - Other parameters increase normally - If flight phases 2, 3: • Single chime sounds • Master caution light comes on • Appropriate messages appear on E/W CRT (LA77175)

U6KSC00

• “ENGINE” page appears on SYS CRT - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS ENGINE DESCRIPTION CFM

CHAPTER 13: ENGINE CFM MALFUNCTION

: START VALVE STUCK #1

MALFUNCTION DESCRIPTION

:

CAUSE

: Start valve stuck in position

CONSEQUENCE

:

1 - Insert failure before start procedure • all engine 1 indications remain unchanged • Whatever the start sequence is: If flight phases 1, 2, 6, 9 or 10: • Single chime sounds • Master caution light comes on • Appropriate messages appear on the E/W CRT (LA77005) • “ENGINE” page appears on the SYS CRT 2 - Insert failure during start procedure • Start sequence is normally proceeded until N2 reaches 50% • The start valve remains opened • Whatever the start sequence is: If flight phases 1, 2, 6, 9, or 10: • Single chime sounds • Master caution light comes on • Appropriate messages appear on the E/W CRT (LA77020) • “ENGINE” page appears on the SYS CRT - Manual operation of the start valve can be carried out through Maintenance Service Panel (if MSP option selected).

U6KSC00

- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation.

DATE: SEP 1998

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CHAPTER 13: ENGINE CFM MALFUNCTION

: START VALVE STUCK #2

MALFUNCTION DESCRIPTION

:

CAUSE

: Start valve stuck in position

CONSEQUENCE

:

1 - Insert failure before start procedure • All Engine 2 indications remain unchanged • Whatever the start sequence is: If flight phases 1, 2, 6, 9 or 10: • Single chime sounds • Master caution light comes on • Appropriate messages appear on E/W CRT (LA77010) • “ENGINE” page appears on SYS CRT 2 - Insert failure during start procedure • Start sequence is normally proceeded until N2 reaches 50% • The start valve remains opened • Whatever the start sequence is: If flight phases 1, 2, 6, 9 or 10 • Single chime sounds • Master caution light comes on • Appropriate messages appear on the E/W CRT (LA77030) • “ENGINE” page appears on the SYS CRT - Manual operation of the start valve can be carried out through Maintenance Service Panel (If MSP option selected)

U6KSC00

- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation

DATE: SEP 1998

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CHAPTER 13: ENGINE CFM MALFUNCTION

: OIL FILTER CLOGGED (ENGINE 1) #1

MALFUNCTION DESCRIPTION

:

CAUSE

: Clogging of oil filter

CONSEQUENCE

:

If the aircraft isn’t in flight phases 4, 5, 7, 8, • Appropriate messages appear on the E/W CRT (LA77310) • “ENGINE” page appears on the SYS CRT • Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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CHAPTER 13: ENGINE CFM MALFUNCTION

: IGNITION FAIL #1

MALFUNCTION DESCRIPTION

:

CAUSE

: Loss of electrical supply for system ignitor plugs

CONSEQUENCE

:

If automatic start sequence, FADEC 1 tries to start engine 1 according to the following sequence: - Take a top (TOP1) on the on-board clock as soon as starter valve is open. - When N2 > 16 %, igniters A or B (alternative selection) are on, • -

Appropriate message appears on the E/W CRT, (LA77850 or LA77852) Take a top (TOP2) on the on-board clock as soon as fuel is on (N2=22%). At (TOP2 +10s), igniters are off, and automatic dry crank is performed, At (TOP2 +25s) and if flight phase 1,2,6,9 or 10:

• Single chime sounds, • Master caution comes on, • Appropriate message appears E/W CRT, (LA77100) • ENGINE page appears on the SYS CRT (if applying). - At (TOP2 +35s), igniters systems A and B are on. If flight phase 1,2,6,9 or 10: • Single chime sounds, • Master caution comes on • Appropriate message appears E/W CRT, (LA77860) • ENGINE page appears on the SYS CRT (if applying). - At (TOP2 +40s), a new start attempt is performed, • Appropriate message appears on E/W CRT, - At (TOP2 +50s), igniters systems A and B are off, and automatic dry crank is performed, • appropriate message appears on E/W CRT, - At (TOP 2 +1mn15s), igniters systems A and B are on. If flight phase 1,2,6,9 or 10: • Single chime sounds, U6KSC00

• Master caution comes on • Appropriate message appears E/W CRT, (LA77860) • ENGINE page appears on the SYS CRT (if applying).

DATE: SEP 1998

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CHAPTER 13: ENGINE CFM - At (TOP 2+1mn20s), a new start attempt is performed, • Appropriate message appears on E/W CRT, - At (TOP2 +1mn30s), a new start attempt is performed, • Appropriate message appears on E/W CRT - At (TOP2 +2mn) or (TOP2 +1mn55s), engine FAULT light comes on and start valve is closed, • Appropriate message appears on the E/W CRT. - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation N.B. Failure on, engine 1 can’t be started This procedure only applies for ground start - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation

U6KSC00

N.B. Failure on, engine 1 can’t be started

DATE: SEP 1998

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CHAPTER 13: ENGINE CFM MALFUNCTION

: REVERSER UNLOCKED #1

MALFUNCTION DESCRIPTION

:

CAUSE

: Faulty switch operation

CONSEQUENCE

:

- On ground: • The amber REV indication comes on • Engine 1 performances are set to idle - In flight: • The amber REV indication comes on flashing for 9 seconds then remains steady. - If flight phases No 3, 6 or 7 • Single chime sounds • Master caution light comes on - Appropriate messages appear on the E/W CRT (LA77370) • Engine 1 performances are set to idle

U6KSC00

• Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation.

DATE: SEP 1998

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CHAPTER 13: ENGINE CFM MALFUNCTION

: SERIOUS ENG DAMAGE WITH EXTINGUIS. FIRE #1

MALFUNCTION DESCRIPTION

:

CAUSE

: Compressor stall + engine 1 fire

CONSEQUENCE

:

As soon as the failure is inserted, N1, N2, EGT & Fuel flow move erratically lower or upper than in normal operation 3 seconds later: - Engine 1 Fire - On fire panel, “ENG 1 FIRE” light comes on - On central pedestal (115 VU), master ENG 1 “FIRE” light comes on - Nacelle temperature increases until fire stops Ecam displays consequences Whatever the flight phase is: • Audio CRC sounds • Master “Warn” light comes on • Appropriate messages (nature of failure and actions to be performed) appear on E/W CRT • “ENGINE” page appears on SYS CRT Actions Push the ENGINE 1 FIRE P/B (FIRE PANEL) • After a few seconds, engine 1 shuts down • On fire panel, AGENTS ENG 1 “SQUIB” lights come on • All warnings remain on • CRC stops Push the AGENT1 ENG1 push button (FIRE PANEL) • After 3 seconds, AGENT1 “DISH” light comes on

U6KSC00

• After 10 seconds, all fire warnings remain on

DATE: SEP 1998

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CHAPTER 13: ENGINE CFM

Push the AGENT2 ENG1 push button (FIRE PANEL) • After 3 seconds, AGENT2 “DISH” light comes on • After 10 seconds, all fire warnings disappear If activated • Master “Warn” light goes out

U6KSC00

In order to recover normal operation: - Cancel malfunction - Release the “ENG1 FIRE” pushbutton (FIRE PANEL) - On instructor station set the AGENT FIRE RESET

DATE: SEP 1998

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CHAPTER 13: ENGINE CFM MALFUNCTION

: SERIOUS ENG DAMAGE WITH EXTINGUIS. FIRE #2

MALFUNCTION DESCRIPTION

:

CAUSE

: Compressor stall + Engine 2 fire

CONSEQUENCE

:

As soon as the failure is inserted, N1, N2, EGT & Fuel flow move erratically lower or upper than in normal operation 3 seconds later: - Engine 2 Fire - On fire panel, “ENG 2 FIRE” light comes on - On central pedestal (115 VU), master ENG 2 “FIRE” light comes on - Nacelle temperature increases until fire stops Ecam displays consequences Whateve the flight phase is: • Audio CRC sounds • Master “Warn” light comes on • Appropriate messages (nature of failure and actions to be performed) appear on E/W CRT • “ENGINE” page appears on SYS CRT Actions Push the ENGINE 2 FIRE P/B (FIRE PANEL) • After a few seconds, engine 2 shuts down • On fire panel, AGENTS ENG 2 “SQUIB” lights come on • All warnings remain on • CRC stops Push the AGENT1 ENG2 push button (FIRE PANEL) • After 3 seconds, AGENT1 “DISH” light comes on

U6KSC00

• After 10 seconds, all fire warnings remain on

DATE: SEP 1998

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CHAPTER 13: ENGINE CFM

Push the AGENT2 ENG2 push button (FIRE PANEL) • After 3 seconds, AGENT2 “DISH” light comes on • After 10 seconds, all fire warnings disappear If activated • Master “Warn” light goes out

U6KSC00

In order to recover normal operation: - Cancel malfunction - Release the “ENG2 FIRE” pushbutton (FIRE PANEL) - On instructor station set the AGENT FIRE RESET

DATE: SEP 1998

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CHAPTER 13: ENGINE CFM MALFUNCTION

: SERIOUS ENG DAMAGE WITH UNEXTING FIRE #1

MALFUNCTION DESCRIPTION

:

CAUSE

: Compressor stall + engine 1 fire

CONSEQUENCE

:

As soon as the failure is inserted, N1, N2, EGT & Fuel Flow move erratically 3 seconds later:

Engine 1 flame out Engine 1 fire

See failure “Engine 1 flame out” Then failure “Engine 1 unextinguishable fire” for consequences. - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

Cancelling malfunction restores normal operation.

DATE: SEP 1998

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CHAPTER 13: ENGINE CFM MALFUNCTION

: SERIOUS ENG DAMAGE WITH UNEXTING FIRE 2

MALFUNCTION DESCRIPTION

:

CAUSE

: Compressor stall + engine 2 fire

CONSEQUENCE

:

As soon as the failure is inserted, N1, N2, EGT & Fuel Flow move erratically lower or upper than in normal operation 3 seconds later: Engine 2 fire - See failure “UNEXTINGUISHABLE FIRE #2" for consequences. - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

Cancelling malfunction restores normal operation.

DATE: SEP 1998

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CHAPTER 13: ENGINE CFM MALFUNCTION

: SERIOUS ENG DAMAGE WITH PARTIAL PWR LOSS #1

MALFUNCTION DESCRIPTION

:

CAUSE

: Compressor stall

CONSEQUENCE

:

- As soon as the failure is inserted, N1, N2, EGT & 1 fuel flow move erratically lower or upper than in normal operation. - Engine 1 vibrations increase - No warning - Sound effects - 3 seconds later: • Compressor stall disappears

U6KSC00

• Engine performances remain lower than in normal operation - If throttle 1 is reduced, normal vibrations value is restored. - Cancelling malfunction restors normal operation.

DATE: SEP 1998

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CHAPTER 13: ENGINE CFM MALFUNCTION

: SERIOUS ENG DAMAGE WITH PARTIAL PWR LOSS #2

MALFUNCTION DESCRIPTION

:

CAUSE

: Compressor stall

CONSEQUENCE

:

-

As soon as the failure is inserted, N1, N2, EGT & Fuel Flow move erratically Engine 2 vibrations increase No warning Sound effects

- 3 seconds later:

U6KSC00

• Compressor stall disappears - If throttle 2 is reduced, normal vibrations value is restored - Cancelling malfunction restores normal operation

DATE: SEP 1998

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CHAPTER 13: ENGINE CFM MALFUNCTION

: THROTTLE INOPERATIVE (POWER STUCK) #1

MALFUNCTION DESCRIPTION

:

CAUSE

: TLA signal frozen

CONSEQUENCE

:

Engine 1 performances remain constant (at the values reached when the failure is inserted), whatever the throttle position is. • No warning

U6KSC00

Cancelling malfunction restores normal operation.

DATE: SEP 1998

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CHAPTER 13: ENGINE CFM MALFUNCTION

: THROTTLE INOPERATIVE (POWER STUCK) #2

MALFUNCTION DESCRIPTION

:

CAUSE

: TLA signal frozen

CONSEQUENCE

:

Engine 2 performances remain constant (at the values reached when the failure is inserted), whatever the throttle position is. • No warning

U6KSC00

Cancelling malfunction restores normal operation.

DATE: SEP 1998

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CHAPTER 13: ENGINE CFM MALFUNCTION

: ENGINE DETACHED #1

MALFUNCTION DESCRIPTION

:

CAUSE

: Engine 1 detached

CONSEQUENCE

:

N1 and N2 vibrations increase then flash (green) on the “CRUISE” or “ENGINE” page (if selected on the SYS CRT) A few seconds later: - All engine 1 indications become invalid on the upper Ecam display unit - Engine 1 oil quantity and oil pressure drop to zero on the lower Ecam display unit - Engine 1 oil temperature and nacelle temperature are replaced by amber crosses on the lower ECAM display unit. - Aerodynamic, Fuel, Elec, Hydraulic effects - If flight phases No 2, 3, 4, 5, 6, 7, 8 or 9: • Continuous repetitive chime sounds • Master warning light comes on • Appropriate messages appear on the E/W CRT (LA26010 and LA77240) • “ENGINE” page appears on the SYS CRT

U6KSC00

- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation.

DATE: SEP 1998

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CHAPTER 13: ENGINE CFM MALFUNCTION

: ENGINE DETACHED # 2

MALFUNCTION DESCRIPTION

:

CAUSE

: Engine 2 detached

CONSEQUENCE

:

- N1 and N2 vibrations increase then flash (green) on the “CRUISE” or “ENGINE” page (if selected on the SYS CRT). A few seconds later: - All engine 2 indications become invalid on the upper Ecam display unit. - Engine 2 oil quantity and oil pressure drop to zero on the lower ecam display unit - Engine 2 oil temperature and nacelle temperature are replaced by amber crosses on the lower ecam display unit. Aerodynamic, Fuel, Elec, Hydraulic effects - If flight phases 2, 3, 4, 5, 6, 7, 8 or 9: • Audio CRC sounds • Master warning light comes on • Appropriate messages appear on the E/W CRT (LA26020 and 77250) • “ENGINE” page appears on the SYS CRT

U6KSC00

- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation.

DATE: SEP 1998

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CHAPTER 13: ENGINE CFM MALFUNCTION

: FUEL HP VALVE INOPERATIVE # 2

MALFUNCTION DESCRIPTION

:

CAUSE

: HP valve locked

CONSEQUENCE

:

- During start sequence: If automatic start, engine 2 “FAULT” light comes on as soon as N2 reaches 22%. If manual start, engine 2 “FAULT” light comes on as soon as master lever 2 is selected on. - Whatever the start sequence is: If flight phases 1, 2, 6, 9 or 10: • Single chime sounds • Master caution light comes on • Appropriate messages appear on the E/W CRT (LA77050)

U6KSC00

• “ENGINE” page appears on the SYS CRT - Appropriate message will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation

DATE: SEP 1998

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CHAPTER 13: ENGINE CFM MALFUNCTION

: E.I.U. FAIL #2

MALFUNCTION DESCRIPTION

:

CAUSE

: EIU 2 failure

CONSEQUENCE

:

- Engine 2 can not be started if not running -

A/THR is desactivated if previously on Engine 2 reverser sequence can not be proceeded Continuous relight is selected on engine 2 Only flight idle can be obtained on engine 2 If flight idle can be obtained on engine 2

- If flight phases 2, 6 or 9: • Single chime sounds • Master caution light comes on • Appropriate messages appear on E/W CRT (LA77530) • Engine 2 oil temperature and nacelle temperature are replaced by amber crosses on the “ENGINE” page

U6KSC00

- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - When CFDS is operating in MENU mode and BITE TSD (Trouble Shooting Data) function is selected, the snapshot data corresponding to malfunction are displayed on the MCDU. (when BITE TSD maintenance option selected) - Cancelling malfunction restores normal operation

DATE: SEP 1998

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CHAPTER 13: ENGINE CFM MALFUNCTION

: FUEL FILTER CLOGGING #1

MALFUNCTION DESCRIPTION

:

CAUSE

: Clogging of fuel filter

CONSEQUENCE

:

If the aircraft isn’t in flight phases 4, 5, 7, 8 • Appropriate messages appear on the E/W CRT (LA77330) • “ENGINE” page appears on the SYS CRT Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

Cancelling malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS ENGINE DESCRIPTION CFM

CHAPTER 13: ENGINE CFM MALFUNCTION

: IDLE CONTROL FAIL #1

MALFUNCTION DESCRIPTION

:

CAUSE

: EIU 1 failure

CONSEQUENCE

:

- Only flight idle can be obtained on engine 1

U6KSC00

- No warning - Cancelling malfunction restores normal operation

DATE: SEP 1998

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CHAPTER 13: ENGINE CFM MALFUNCTION

: TLA RESOLVER INEQUALITY #1

MALFUNCTION DESCRIPTION

:

CAUSE

: TLA resolver failure

CONSEQUENCE

:

On ground, whatever the throttle position is: • Engine 1 performances are set to idle • Reverse is commanded to restow if previously deployed In flight: • In FLEX-TO or TO/GA modes, engine 1 performances don’t change. • In other modes, MAX CONT mode is selected • If A/THR is selected, thrust is managed between IDLE & MCT On ground or in flight: • Engine 2 stays in normal operating mode: • Single chime sounds • Master caution light comes on • Appropriate messages appear on the E/W CRT (LA77535 or 77540) Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). When CFDS is operating in MENU mode and BITE TSD (Trouble Shooting Data) function is selected, the snapshot data corresponding to malfunction are displayed on the MCDU. (when BITE TSD maintenance option selected)

U6KSC00

Cancelling malfunction restores normal operation.

DATE: SEP 1998

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CHAPTER 13: ENGINE CFM MALFUNCTION

: MAN START FAULT #1

MALFUNCTION DESCRIPTION

:

CAUSE

: Disagree between Master Switch position and HPSOV position

CONSEQUENCE

:

- During start sequence: If automatic start, engine 1 “FAULT” light comes on as soon as N2 reaches 22%. If manual start, engine 1 “FAULT” light comes on as soon as master lever 1 is selected on. - Whatever the start sequence is: If flight phases No 1, 2, 6, 9, 10: • Single chime sounds • Master caution light comes on • Appropriate messages appear on the E/W CRT (LA77040) • “ENGINE” page appears on the SYS crt - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation.

U6KSC00

N.B. cf IGNITION A+B FAULT if FWC requests are not proceeded

DATE: SEP 1998

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CHAPTER 13: ENGINE CFM MALFUNCTION

: REVERSER DEPLOYED #1

MALFUNCTION DESCRIPTION

:

CAUSE

: Reverser failure

CONSEQUENCE

:

- On ground: Engine 1 performances are set to idle • If the A/C is in flight phase 3: Appropriate messages appear on the E/W CRT (LA77370) If throttle lever angle value is lower than zero, normal engine 1 reverser sequence is proceeded. - In flight: • The amber REV indication comes on flashing for 9 seconds then remains steady Engine 1 performances are set to idle If flight phases 6 or 7 • Single chime sounds • Master caution light comes on • Appropriate messages appear on the E/W CRT (LA77370) - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

- Cancelling malfunction restores normal operation.

DATE: SEP 1998

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U6KSC00

THIS PAGE INTENTIONALLY LEFT BLANK

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINE PARAMETERS CFM

CHAPTER 14 - ENGINE PARAMETERS CFM CONTENTS: OIL PRESS INC/DEC # 1 (psi) OIL PRESS INC/DEC # 2 (psi) OIL QUANTITY INC/DEC # 1 (qt) OIL QUANTITY INC/DEC # 2 (qt) E G T INC/DEC # 1 (degC) E G T INC/DEC # 2 (degC) N 1 INC/DEC # 1 (%) N 1 INC/DEC # 2 (%) N 2 INC/DEC # 1 (%) N 2 INC/DEC # 2 (%) N 1 INDICATION FAULT # 1 N 2 INDICATION FAULT # 2 OIL TEMP INC/DEC # 1 (degC) FUEL FLOW INC/DEC # 1 (kg/h) NACELLE TEMP INC/DEC # 1 (degC) VIBRATIONS N1 INC/DEC # 1 (U) VIBRATIONS N2 INC/DEC # 2 (U) VIBRATIONS N1 PEAK (# 1 (%/U)) VIBRATIONS N1 PEAK (# 2 (%/U)) VIBRATIONS N2 PEAK (# 1 (%/U))

U6KSC00

VIBRATIONS N2 PEAK (# 2 (%/U))

DATE: SEP 1998

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CHAPTER 14: ENGINE PARAMETERS CFM MALFUNCTION

: OIL PRESS INC/DEC # 1 (psi)

PARAMETER

: ENGINE 1 OIL PRESSURE

MIN VALUE

: PSI MAX VALUE: 100 psi CHANGE RATE: 2 psi/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Oil pump failure or oiljet clogging

CONSEQUENCE

:

- Oil pressure indication is normally green - As soon as oil pressure reaches 90 psi, oil pressure indication flashes (green) on the “ENGINE” page. - Oil pressure advisory reset is possible if oil pressure decreases below 85 psi. -

As soon as oil pressure drops down 16 psi, oil pressure indication flashes (green) on the “ENGINE” page. Oil pressure advisory reset is possible if oil pressure increases above 18 psi. As soon as engine oil pressure drops down 13 psi, oil pressure indication turns red. If flight phases 2, 3, 4, 5, 6, 7, 8 or 9:

• Audio CRC sounds • Master warning light comes on • Appropriate messages appear on the E/W CRT (LA77290) • “ENGINE” page appear on the SYS CRT - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

- Cancelling malfunction and/or engine oil pressure greater than 18 psi restore normal operation

DATE: SEP 1998

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CHAPTER 14: ENGINE PARAMETERS CFM MALFUNCTION

: OIL PRESS INC/DEC # 2 (psi)

PARAMETER

: ENGINE 2 OIL PRESSURE

MIN VALUE

: 0 psi MAX VALUE: 100 psi CHANGE RATE: 2 psi/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Oil pump failure or oiljet clogging

CONSEQUENCE

:

- Oil pressure indication is normally green -

As soon as oil pressure reaches 90 psi, oil pressure indication flashes (green) on the “ENGINE” page. Oil pressure advisory reset is possible if oil pressure decreases below 85 psi. As soon oil pressure drops down 16 psi, oil pressure indication flashes (green) on the “ENGINE” page. Oil pressure advisory reset is possible if oil pressure increases above 18 psi. As soon as engine oil pressure drops down 13 psi, oil pressure indication turns red

- If flight phases 2, 3, 4, 5, 6, 7, 8 or 9: • Continuous repetitive chime sounds • Master Warning light comes on • Appropriate messages appear on E/W CRT (LA77300) • “ENGINE” page appear on SYS CRT

U6KSC00

- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction and/or engine oil pressure greater than 18 psi restore normal operation

DATE: SEP 1998

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CHAPTER 14: ENGINE PARAMETERS CFM MALFUNCTION

: OIL QUANTITY INC/DEC # 1 (qt)

PARAMETER

: ENGINE 1 OIL QUANTITY

MIN VALUE

: 0 qt MAX VALUE: 22.5 qt CHANGE RATE: 0.5 qt/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Leak in oil circuit

CONSEQUENCE

:

- Oil quantity indication is normally green - As soon as engine oil quantity drops down 4 qt, oil quantity indication flashes (green) on the “ENGINE” page. - Oil quantity advisory reset is possible if oil quantity increases above 6 qt • Oil pressure decreases • Oil temperature increases - If oil pressure and/or oil temperature thresholds are reached: • See corresponding failures - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation.

U6KSC00

N.B. Oil quantity maximum values is limited to initial quantity.

DATE: SEP 1998

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CHAPTER 14: ENGINE PARAMETERS CFM MALFUNCTION

: OIL QUANTITY INC/DEC # 2 (qt)

PARAMETER

: ENGINE 2 OIL QUANTITY

MIN VALUE

: 0 qt MAX VALUE: 22.5 qt CHANGE RATE: 0.5 qt/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Leak in oil circuit

CONSEQUENCE

:

- Oil quantity indication is normally green - As soon as engine oil quantity drops down 4 QT, oil quantity indication flashes (green) on the “ENGINE” page. - Oil quantity advisory reset is possible if oil quantity increases above 6 QT • Oil pressure decreases • Oil temperature increases - If oil pressure and/or oil temperature thresholds are reached: • See corresponding failures - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation

U6KSC00

N.B. Oil quantity maximum value is limited to initial quantity.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINE PARAMETERS CFM

CHAPTER 14: ENGINE PARAMETERS CFM MALFUNCTION

: E G T INC/DEC # 1 (degC)

PARAMETER

: ENGINE 1 EXHAUST GAS TEMPERATURE

MIN VALUE

: 0 degC MAX VALUE: 1000 degC CHANGE RATE: 10 degC/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Incorrect engine operation

CONSEQUENCE

:

- EGT indication is normally green - If flight phases 1, 2, 3, 5, 6, 7, 9 or 10: - When 855 degC < EGT < 890 degC: • The indication becomes amber - If EGT > 890 degC: • The indication becomes red • Single chime sounds • Master caution light comes on • Appropriate messages appear on the E/W CRT (LA77430) - EGT maximum value is memorized and a small red line is positioned at that value on the indicator. - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation.

U6KSC00

N.B. EGT minimum value is limited to static air temperature.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINE PARAMETERS CFM

CHAPTER 14: ENGINE PARAMETERS CFM MALFUNCTION

: E G T INC/DEC # 2 (degC)

PARAMETER

: ENGINE 2 EXHAUST GAS TEMPERATURE

MIN VALUE

: 0 degC MAX VALUE: 1000 degC CHANGE RATE: 10 degC/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Incorrect engine operation

CONSEQUENCE

:

- EGT indication is normally green - If flight phases 1, 2, 3, 5, 6, 7, 9 or 10 : - When 855 degC < EGT < 890 degC: • The indication becomes amber - If EGT > 890 degC: • The indication becomes red • Single chime sounds • Master caution light comes on • Appropriate messages appear on E/W CRT (LA77440) - EGT maximum value is memorized and a small red line is positioned at that value on the indicator - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation

U6KSC00

N.B. EGT minimum value is limited to static air temperature.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINE PARAMETERS CFM

CHAPTER 14: ENGINE PARAMETERS CFM MALFUNCTION

: N 1 INC/DEC # 1 (%)

PARAMETER

: ENGINE 1 LOW TURBINE SPEED RATEE

MIN VALUE

: 0 % MAX VALUE: 120 % CHANGE RATE: 10 %/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Incorrect indication

CONSEQUENCE

:

- N1 indication is normally green - If flight phases 1, 2, 3, 5, 6, 7, 9 or 10 : - When N1LIM+1% < 1 < N1MAX+1%: • The analog indication becomes amber - If N1 > N1MAX+1%: • The analog § digital indications become red - If N1 > 102%: • All indications stay red • Single chime sounds • Master caution light comes on • Appropriate messages appear on the E/W CRT (LA77390)

U6KSC00

- If N1 has overriden 102 %, N1 maximum value is memorized and a small red line is positioned at that value on the indicator. - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINE PARAMETERS CFM

CHAPTER 14: ENGINE PARAMETERS CFM MALFUNCTION

: N 1 INC/DEC # 2 (%)

PARAMETER

: ENGINE 2 LOW TURBINE SPEED

MIN VALUE

: 0 % MAX VALUE: 120 % CHANGE RATE: 10 %/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Incorrect indication

CONSEQUENCE

:

- N1 indication is normally green - If flight phases 1, 2, 3, 5, 6, 7, 9 or 10 : - When N1LIM+1 < N1 < N1MAX+ 1%: • The analog indication becomes amber - If N1 > N1MAX+ 1 % • The analog § digital indications become red - If N1 > 102 %: • All indication stay red • Single chime sounds • Master caution light comes on • Appropriate messages appear on E/W CRT (LA77400)

U6KSC00

- If N1 has overridden 102 % , N1 maximum value is memorized and a small red line is positioned at that value on the indicator - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINE PARAMETERS CFM

CHAPTER 14: ENGINE PARAMETERS CFM MALFUNCTION

: N 2 INC/DEC # 1 (%)

PARAMETER

: ENGINE 1 HIGH TURBINE SPEED RATE

MIN VALUE

: 0 % MAX VALUE: 120 % CHANGE RATE: 10 %/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Incorrect indication

CONSEQUENCE

:

- N2 indication is normally green - If flight phases 1, 2, 3, 5, 6, 7, 9 or 10 - When N2 >105 %: • The indication becomes red • Single chime sounds • Master caution light comes on • Appropriate messages appear on the E/W CRT (LA77410) - If N2 has overridden 105 %, a red cross appears near the N2 indication and remains all the flight.

U6KSC00

- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINE PARAMETERS CFM

CHAPTER 14: ENGINE PARAMETERS CFM MALFUNCTION

: N 2 INC/DEC # 2 (%)

PARAMETER

: ENGINE 2 HIGH TURBINE SPEED

MIN VALUE

: 0 % MAX VALUE: 120 % CHANGE RATE: 10 %/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Incorrect indication

CONSEQUENCE

:

- N2 indication is normally green - If flight phases 1, 2, 3, 5, 6, 7, 9 or 10: - When N2 >105 %: • The indication becomes red • Single chime sounds • Master caution light comes on • Appropriate messages appear on E/W CRT (LA77420) - If N2 has overridden 105%, a red cross appears near the N2 indication and remains all the flight

U6KSC00

- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINE PARAMETERS CFM

CHAPTER 14: ENGINE PARAMETERS CFM MALFUNCTION

: N1 INDICATION FAULT # 1

MALFUNCTION DESCRIPTION

:

CAUSE

: Analog and Digital signals of N1 lost by ECAM

CONSEQUENCE

:

- Engine 1 N1 analog indications are replaced by amber circles on the E/W CRT.

U6KSC00

- Engine 1 N1 numerical indication is replaced by amber crosses on the E/W CRT. - Cancelling the malfunction restors normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINE PARAMETERS CFM

CHAPTER 14: ENGINE PARAMETERS CFM MALFUNCTION

: N2 INDICATION FAULT # 2

MALFUNCTION DESCRIPTION

:

CAUSE

: Digital signal of N2 lost by ECAM

CONSEQUENCE

:

- Engine 2 N2 numerical indication is replaced by two amber crosses on the E/W CRT

U6KSC00

- Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINE PARAMETERS CFM

CHAPTER 14: ENGINE PARAMETERS CFM MALFUNCTION

: OIL TEMP INC/DEC # 1 (degC)

PARAMETER

: ENGINE 1 OIL TEMPERATURE

MIN VALUE

: -56 degC MAX VALUE: 200 degC CHANGE RATE: 2 degC/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Incorrect engine operation

CONSEQUENCE

:

- Oil temperature indication is normally green - As soon as engine oil temperature reaches 140degC, oil temperature indication flashes (green) on the “ENGINE” page - Oil temperature advisory reset is possible if oil temperature decreases below 135 degC. - If engine oil temperature advisory lasts more than 900 s (1/4 h) or if engine oil temperature exceeds 155 degC: Oil indicaion becomes amber, if flight phases 1, 2, 3, 6, 9 or 10: • Single chime sounds • Master caution light comes on • Appropriate messages appear on the E/W CRT (LA77480) • “ENGINE” page appears on the SYS CRT - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - When CFDS is operating in MENU mode and BITE TSD (Trouble Shooting Data) function is selected, the snapshot data corresponding to malfunction are displayed on the MCDU. (when BITE TSD maintenance option selected). - Cancelling malfunction restores normal operation

U6KSC00

N.B. Oil temperature minimum value is limited to static air temperature

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINE PARAMETERS CFM

CHAPTER 14: ENGINE PARAMETERS CFM MALFUNCTION

: FUEL FLOW INC/DEC#1 (kg/h)

PARAMETER

: ENGINE 1 FUEL FLOW

MIN VALUE

: 0 kg/h MAX VALUE: 5000 kg/h CHANGE RATE: 500 kg/h.s

MALFUNCTION DESCRIPTION

:

CAUSE

: Incorrect engine operation

CONSEQUENCE

:

If fuel flow increases, all engine 1 parameters increase too

U6KSC00

If fuel flow decreases, all engine 1 parameters decrease too - Cancelling malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINE PARAMETERS CFM

CHAPTER 14: ENGINE PARAMETERS CFM MALFUNCTION

: NACELLE TEMP INC/DEC # 1 (degC)

PARAMETER

: NACELLE TEMPERATURE

MIN VALUE

: SAT MAX VALUE: 250 degC CHANGE RATE: 5 degC/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Incorrect engine operation

CONSEQUENCE

:

- Nacelle temperature is indicated only when value exceeds advisory threshold (240°C) - Cancelling malfunction restores normal operation

U6KSC00

Complementary data: NACELLE TEMP minimum value is limited to SAT value.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINE PARAMETERS CFM

CHAPTER 14: ENGINE PARAMETERS CFM MALFUNCTION

: VIBRATIONS N1 INC/DEC # 1 (U)

PARAMETER

: ENGINE 1 LOW TURBINE SPEED VIBRATIONS

MIN VALUE

: 0 U MAX VALUE: 10 U CHANGE RATE: 0.5 U/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Incorrect engine operation

CONSEQUENCE

:

- N1 vibrations indication is normally green If N1 vibrations advisory level is reached: - N1 vibrations indication flashes (green) on the “ENGINE” or “CRUISE” page if selected on the SYS CRT - Cancelling malfunction restores normal operation.

U6KSC00

N.B. N1 vibrations advisory level depends on N1 actual value and EVMU initial values.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINE PARAMETERS CFM

CHAPTER 14: ENGINE PARAMETERS CFM MALFUNCTION

: VIBRATIONS N2 INC/DEC # 2 (U)

PARAMETER

: ENGINE 2 HIGH TURBINE SPEED VIBRATIONS

MIN VALUE

: 0 U MAX VALUE: 10 U CHANGE RATE: 0.5 U/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Incorrect engine operation

CONSEQUENCE

:

- N2 vibrations indication is normally green If N2 vibrations advisory level is reached: - N2 vibrations indication flashes (green) on the “ENGINE” or “CRUISE” page if selected on SYS CRT - Cancelling malfunction restores normal operation

U6KSC00

N.B. N2 vibrations advisory level depends on N2 actual value and EVMU initial values.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINE PARAMETERS CFM

CHAPTER 14: ENGINE PARAMETERS CFM MALFUNCTION

: N1 VIBRATION PEAK ENGINE 1

PARAMETER/VALUES

: SELECTED SPEED N1(%): 0 to 110% : VIBRATION PEAK LEVEL: 0 to 10 cockpits units

MALFUNCTION DESCRIPTION

:

CAUSE

: Unbalanced LP rotor due to normal or abnormal engine degradation

CONSEQUENCE

:

- An altered vibration profile on sensed LP vibration level is introduced. - The degraded engine shows new vibration levels which include a vibration peak reaching the selected vibration value (cockpits units) at the selected speed (%). - The unbalanced vibration signature appears only if the selected values allow the vibration signature to overshoot the vibration level of balanced engine. - N1 vibrations indication is normally green. If N1 vibrations advisory level is reached: (5U) - N1 vibrations indication flashes (green) on the "ENGINE" or "CRUISE" page if selected on the SYS CRT. Cancelling malfunction restores normal operation

U6KSC00

N.B. All advisories are always functionnal but there is no real correlation with bite unbalance functions (if available on simulators).

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINE PARAMETERS CFM

CHAPTER 14: ENGINE PARAMETERS CFM MALFUNCTION

: N1 VIBRATION PEAK ENGINE 2

PARAMETER/VALUES

: SELECTED SPEED N1(%): 0 to 110% : VIBRATION PEAK LEVEL: 0 to 10 cockpits units

MALFUNCTION DESCRIPTION

:

CAUSE

: Unbalanced LP rotor due to normal or abnormal engine degradation

CONSEQUENCE

:

- An altered vibration profile on sensed LP vibration level is introduced. - The degraded engine shows new vibration levels which include a vibration peak reaching the selected vibration value (cockpits units) at the selected speed (%). - The unbalanced vibration signature appears only if the selected values allow the vibration signature to overshoot the vibration level of balanced engine. - N1 vibrations indication is normally green. If N1 vibrations advisory level is reached: (5U) - N1 vibrations indication flashes (green) on the "ENGINE" or "CRUISE" page if selected on the SYS CRT. Cancelling malfunction restores normal operation

U6KSC00

N.B.: All advisories are always functionnal but there is no real correlation with bite unbalance functions (if available on simulators).

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINE PARAMETERS CFM

CHAPTER 14: ENGINE PARAMETERS CFM MALFUNCTION

: N2 VIBRATION PEAK ENGINE 1

PARAMETER/VALUES

: SELECTED SPEED N2(%): 0 to 110% : VIBRATION PEAK LEVEL: 0 to 10 cockpits units

MALFUNCTION DESCRIPTION

:

CAUSE

: Unbalanced HP rotor due to normal or abnormal engine degradation

CONSEQUENCE

:

- An altered vibration profile on sensed HP vibration level is introduced. - The degraded engine shows new vibration levels which include a vibration peak reaching the selected vibration value (cockpits units) at the selected speed (%). - The unbalanced vibration signature appears only if the selected values allow the vibration signature to overshoot the vibration level of balanced engine. - N1 vibrations indication is normally green. If N1 vibrations advisory level is reached: (5U) - N1 vibrations indication flashes (green) on the "ENGINE" or "CRUISE" page if selected on the SYS CRT. Cancelling malfunction restores normal operation

U6KSC00

N.B.: All advisories are always functionnal but there is no real correlation with bite unbalance functions (if available on simulators).

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINE PARAMETERS CFM

CHAPTER 14: ENGINE PARAMETERS CFM MALFUNCTION

: N2 VIBRATION PEAK ENGINE 2

PARAMETER/VALUES

: SELECTED SPEED N2(%): 0 to 110% : VIBRATION PEAK LEVEL: 0 to 10 cockpits units

MALFUNCTION DESCRIPTION

:

CAUSE

: Unbalanced HP rotor due to normal or abnormal engine degradation

CONSEQUENCE

:

- An altered vibration profile on sensed HP vibration level is introduced. - The degraded engine shows new vibration levels which include a vibration peak reaching the selected vibration value (cockpits units) at the selected speed (%). - The unbalanced vibration signature appears only if the selected values allow the vibration signature to overshoot the vibration level of balanced engine. - N1 vibrations indication is normally green. If N1 vibrations advisory level is reached: (5U) - N1 vibrations indication flashes (green) on the "ENGINE" or "CRUISE" page if selected on the SYS CRT. Cancelling malfunction restores normal operation

U6KSC00

N.B.: All advisories are always functionnal but there is no real correlation with bite unbalance functions (if available on simulators).

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FAC

CHAPTER 15 - FAC CONTENTS: YAW DAMPER SYS 1 FAULT YAW DAMPER SYS 2 FAULT RUDDER TRIM SYS 1 FAULT RUDDER TRIM SYS 2 FAULT RUDDER TRAVEL SYS 1 FAULT RUDDER TRAVEL SYS 2 FAULT FAC 1 FAIL FAC 2 FAIL

U6KSC00

RUDDER TRIMS RESET INOPERATIVE

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FAC

CHAPTER 15: FAC MALFUNCTION

: YAW DAMPER SYS 1 FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: Electrical power failure of Actuator 1 (detected by FAC1)

CONSEQUENCE

:

1 - If FAC 1 is not engaged No consequence on the YAW DAMPER function 2 - If FAC 1 is engaged and FAC 2 not engaged The YAW DAMPER function is inoperative Alarm description: • - aural warning • - MASTER CAUTION light • - Appropriate messages appears on the ECAM display (See sheets FWC A22420, A22430) • - CAT 1 only is displayed 3 - If FAC 1 and FAC 2 are engaged No consequence on the YAW DAMPER function It is impossible to have CAT 3 DUAL capability Alarm description: • Appropriate messages appear on the ECAM display (See sheets FWC A22400, A22410)

U6KSC00

- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FAC

CHAPTER 15: FAC MALFUNCTION

: YAW DAMPER SYS 2 FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: The fault corresponds to a failure in the FAC 2

CONSEQUENCE

:

1 - If FAC 2 is not engaged No consequence on the YAW DAMPER function 2 - If FAC 2 is engaged and FAC 1 not engaged The YAW DAMPER function is inoperative Alarm description: • - Aural warning • - MASTER CAUTION light • - Appropriate messages appear on the ECAM display (See sheets FWC A22420, A22430) • - CAT 1 only is displayed 3 - If FAC 1 and FAC 2 are engaged No consequence on the YAW DAMPER function It is impossible to have CAT 3 DUAL capability Alarm description:

U6KSC00

• Appropriate messages appear on the ECAM display (See sheets FWC A22410, A22427) - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FAC

CHAPTER 15: FAC MALFUNCTION

: RUDDER TRIM SYS 1 FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: Electrical power supply failure of side 1 motor (detected by FAC1)

CONSEQUENCE

:

1 - If FAC 1 is not engaged No consequence on the FAC functions 2 - If FAC 1 was engaged and FAC 2 not engaged Rudder trim is inoperative, it remains to the rudder trim position indicated on the RUDDER TRIM control indicator Manual rudder trim and reset and inoperative AP1 or AP2 will disengage if it was engaged Alarm description: • - Aural warning • - MASTER CAUTION light • - Appropriate message appears on the ECAM display (See sheets FWC A22460, A22470) • - CAT 1 only is displayed 3 - If FAC 1 was engaged and FAC 2 was engaged No consequence on the FAC functions It is impossible to have CAT3 DUAL capability Alarm description: • Appropriate messages appear on the ECAM display (See sheets FWC A22440, A22465)

U6KSC00

- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FAC

CHAPTER 15: FAC MALFUNCTION

: RUDDER TRIM SYS 2 FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: Failure of the rudder trim function in FAC 2

CONSEQUENCE

:

1 - If FAC 2 is not engaged No consequence on the FAC functions 2 - If FAC 2 was engaged and FAC 1 not engaged Rudder trim is inoperative, it remains to the rudder trim position indicated on the RUDDER TRIM control indicator Manual rudder trim and reset are inoperative AP1 ou AP2 will disengage if it was engaged Alarm description: • - Aural warning • - MASTER CAUTION light • - Appropriate messages appear on the ECAM display (See sheets FWC A22460, A22470) • - CAT 1 only is displayed 3 - If FAC 1 was engaged and FAC 2 was engaged No consequence on the FAC functions It is impossible to have CAT3 DUAL capability Alarm description: • Appropriate messages appear on the ECAM display (See sheets FWC A22450, A22467)

U6KSC00

- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FAC

CHAPTER 15: FAC MALFUNCTION

: RUDDER TRAVEL SYS 1 FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: Electrical power supply failure of side 1 motor (detected by FAC1)

CONSEQUENCE

:

1 - If FAC 1 is not engaged No consequence on the FAC functions 2 - If FAC 1 is engaged and FAC 2 not engaged Pedals rudder deflection limitations are no more function of flight conditions Rudder travel system returns to low speed position if we are in approach configuration (SLAT OUT) within 30s Alarm description: • - Aural warning • - MASTER CAUTION light • - Appropriate messages appear on the ECAM display (See sheets FWC A22510, A22520) 3 - If FAC 1 and FAC 2 are engaged No consequence on the pedal rudder deflection limitations Alarm description:

U6KSC00

• Appropriate messages appear on the ECAM display (See sheets FWC A22490, A22515) - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - When CFDS is operating in MENU mode and BITE TSD (Trouble Shooting Data) function is selected, the snapshot data corresponding to malfunction are displayed on the MCDU (when BITE TSD maintenance option selected) - Cancelling malfunction restores normal operation on ground but in flight a reset by ON/OFF pushbutton FAC 1 is necessary

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FAC

CHAPTER 15: FAC MALFUNCTION

: RUDDER TRAVEL SYS 2 FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: The fault corresponds to a failure in the FAC 2

CONSEQUENCE

:

1 - If FAC 2 is not engaged No consequence on the FAC functions 2 - If FAC 2 is engaged and FAC 1 not engaged Pedals rudder deflection limitations are no more function of flight conditions Rudder travel system returns to low speed position if we are in approach configuration (SLAT OUT) within 30s Alarm description: • - Aural warning • - MASTER CAUTION light • - Appropriate messages appears on the ECAM display (See sheets FWC A22510, A22520) 3 - If FAC 1 and FAC 2 are engaged No consequence on the pedal rudder deflection limitations Alarm description: • Appropriate messages appear on the ECAM display (See sheets FWC A22500,A22517)

- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

- Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FAC

CHAPTER 15: FAC MALFUNCTION

: FAC 1 FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: This fault corresponds to a detected failure in the Flight Augmentation computer 1

CONSEQUENCE

:

1 - If FAC 1 is not engaged FAC 1 can’t be engaged 2 - If FAC 1 was engaged and FAC 2 not engaged Yaw damper, rudder trim, rudder travel system are inoperative Manual rudder trim is inoperative Rudder travel system returns to low speed position if we are in approach configuration (SLAT OUT) FAULT light on the FAC 1 pushbutton appears AP1 or AP2 will disengage if it was engaged Alarm description: • - Aural warning • - MASTER CAUTION light • - Appropriate messages appear on the engines warning display (See sheets FWC A22390, A22392, A22397, A22420, A22430, A22460, A22470, A22510, A22520) FAULT light on the FAC 1 pushbutton disappears when FAC 1 is OFF 3 - If FAC 1 and FAC 2 were engaged FAULT light on the FAC 1 pushbutton appears It is impossible to have CAT3 DUAL capability Alarm description: • Appropriate messages appear on the engines warning display (See sheets FWC A22390, A22392, A22397)

U6KSC00

FAULT light on the FAC 1 pushbutton disappears when FAC 1 is OFF

• FIDS function is not active for centralized maintenance system (CFDIU) Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). • Cancelling malfunction restores normal operation on ground but in flight a reset by ON/OFF pushbutton FAC 1 is necessary

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FAC

CHAPTER 15: FAC MALFUNCTION

: FAC 2 FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: This fault corresponds to an internal hardware failure in the Flight Augmentation Computer 2

CONSEQUENCE

:

1 - If FAC 2 is not engaged FAC 2 can’t be engaged 2 - If FAC 2 was engaged and FAC 1 not engaged Yaw damper, rudder trim, rudder travel system are inoperative Manual rudder trim is inoperative Rudder travel system returns to low speed position if we are in approach configuration (SLAT OUT) Alarm description: • - Aural warning • - Master caution light • - Appropriate messages appear on the engines warning display (see sheets FWC A22393, A22395, A22397, A22420, A22430, A22460, A22470, A22510, A22520) FAULT light on the FAC 2 pushbutton disappears when FAC 2 is OFF 3 - If FAC 1 and FAC 2 were engaged FAULT light on the FAC 2 pushbutton appears It is impossible to have CAT3 DUAL capability Alarm description: • Appropriate messages appear on the ECAM display (See sheets FWC A22393, A22395, A22397)

U6KSC00

FAULT light on the FAC 2 pushbutton disappears when FAC 2 is OFF

- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation on ground but in flight a reset by ON/OFF pushbutton FAC 1 is necessary

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FAC

CHAPTER 15: FAC MALFUNCTION

: RUDDER TRIMS RESET INOPERATIVE

MALFUNCTION DESCRIPTION

:

CAUSE

: This fault corresponds to an electrical cut between the reset switch and the FAC

CONSEQUENCE

:

1 - If one of the two FAC is engaged or if the two FAC are engaged The reset is inoperative Manual rudder trim is still operative Alarm description: • Rudder trim indicator on F/CTL page remains cyan - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - When CFDS is operating in MENU mode and BITE TSD (Trouble Shooting Data) function is selected, the snapshot data corresponding to malfunction are displayed on the MCDU. (when BITE TSD maintenance option selected)

U6KSC00

2 - Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FADEC CFM

CHAPTER 16 - FADEC CFM CONTENTS: THROTTLE 1 INOP (IDLE POWER) THROTTLE 2 INOP (IDLE POWER) REVERSER CONTROL 1 FAIL REVERSER CONTROL 2 FAIL FADEC 1 FAIL FADEC 2 FAIL INCORR REV PWR ENG 1 (LOW) INCORR REV PWR ENG 2 (HIGH)

U6KSC00

THR TARGET NEEDLE FAIL

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FADEC CFM

CHAPTER 16: FADEC CFM MALFUNCTION

: THROTTLE 1 INOP (IDLE POWER)

MALFUNCTION DESCRIPTION

:

CAUSE

: Loss of FADEC fuel schedule

CONSEQUENCE

:

- Engine 1 performances are set to idle whatever the throttle position is.

U6KSC00

- Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FADEC CFM

CHAPTER 16: FADEC CFM MALFUNCTION

: THROTTLE 2 INOP (IDLE POWER)

MALFUNCTION DESCRIPTION

:

CAUSE

: Loss of FADEC fuel schedule

CONSEQUENCE

:

- Engine 2 performances are set to idle whatever the throttle position is.

U6KSC00

- Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FADEC CFM

CHAPTER 16: FADEC CFM MALFUNCTION

: REVERSER CONTROL 1 FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Reverser control failure

CONSEQUENCE

:

- Reverser 1 can’t be deployed - If flight phases 1,2,6,7,8,9 or 10 • Appropriate messages appear on E/W CRT (LA77500) - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - When CFDS is operating in MENU mode and BITE TSD (Trouble Shooting Data) function is selected, the snapshot data corresponding to malfunction are displayed on the MCD. (when BITE TSD maintenance option selected)

U6KSC00

- Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FADEC CFM

CHAPTER 16: FADEC CFM MALFUNCTION

: REVERSER CONTROL 2 FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Reverser control failure

CONSEQUENCE

:

- Reverser 2 can’t be deployed - If flight phases 1,2,6,7,8,9 or 10

U6KSC00

• Appropriate messages appear on E/W CRT (LA77510) - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FADEC CFM

CHAPTER 16: FADEC CFM MALFUNCTION

: FADEC 1 FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Power supply lost

CONSEQUENCE

:

- All engine 1 indications become invalid on the upper ecam display unit. - Engine 1 stops - If flight phases 1,2,3,6,9 or 10: • Single chime sounds • Master caution light comes on • Appropriate messages appear on E/W CRT (LA77980 and 77240)

U6KSC00

• “ENGINE” page appears on SYS CRT - Failure on, engine 1 can’t be restarted - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - When CFDS is operating in MENU mode and BITE TSD (Trouble Shooting Data) function is selected, the snapshot data corresponding to malfunction are displayed on the MCDU. (when BITE TSD maintenance option selected) - Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FADEC CFM

CHAPTER 16: FADEC CFM MALFUNCTION

: FADEC 2 FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Power supply lost

CONSEQUENCE

:

- All engine 2 indications become invalid on the upper ecam display unit. - engine 2 stops - If flight phases 1,2,3,6,9 or 10 : • Single chime sounds • Master caution light comes on • Appropriate messages appear on E/W CRT (LA77985 and 77250)

U6KSC00

• “ENGINE” page appears on SYS CRT - Failure on, engine 2 can’t be restarted - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FADEC CFM

CHAPTER 16: FADEC CFM MALFUNCTION

: INCORR REV PWR ENG 1 (LOW)

MALFUNCTION DESCRIPTION

:

CAUSE

: Sensors failure

CONSEQUENCE

:

U6KSC00

- Engine 1 Reverse extends normally but engine 1 performances remain at low power during the whole reverse phase whatever the throttle 1 position is. - Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FADEC CFM

CHAPTER 16: FADEC CFM MALFUNCTION

: INCORR REV PWR ENG 2 (HIGH)

MALFUNCTION DESCRIPTION

:

CAUSE

: Sensors failure

CONSEQUENCE

:

U6KSC00

- Engine 2 reverse extends normally but engine 2 performances reached then remain at high power during the whole reverse phase whatever the throttle 2 position is. - Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FADEC CFM

CHAPTER 16: FADEC CFM MALFUNCTION

: THR TARGET NEEDLE FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Loss of N1 TARGET signal by ecam

CONSEQUENCE

:

- No more indication of engine 1 N1 TARGET

U6KSC00

- Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FIRE PROTECTION/SMOKE

CHAPTER 17 - FIRE PROTECTION/SMOKE CONTENTS: ENG 1 LOOP A FAULT ENG 1 LOOP B FAULT APU LOOP A FAULT APU LOOP B FAULT AIR CONDITIONING SMOKE AVIONIC SMOKE FWD CARGO SMOKE

U6KSC00

AFT CARGO SMOKE

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FIRE PROTECTION/SMOKE

CHAPTER 17: FIRE PROTECTION/SMOKE MALFUNCTION

: ENG 1 LOOP A FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: LOW PRESSURE IN THE LOOP A DETECTOR

CONSEQUENCE

:

- On ground with batteries only connected Press and hold the “ENG 1 FIRE TEST” push button, check that: • The “ENG 1 FIRE” LIGHT (FIRE PANEL) is out • The AGENT 1 ENG 1 lights come on Release the push button, check that: • -

All fire panel lights are out On ground with external power On ground with engines running In flight

Ecam displays consequences - In flight phases 1, 2, 6, 9, 10 Associated warning messages appear on the E/W CRT Test consequences - Press and hold the ENG 1 FIRE TEST P/B (FIRE PANEL), check that: • The “ENG 1 FIRE” light (FIRE PANEL) is on • The AGENT 1 ENG1 “DISH” and “SQUIB” lights come on • The AGENT 2 ENG1 “DISH” and “SQUIB” lights come on • FIRE messages appear on E/W CRT • CRC is triggered • Master “WARN” light comes on - Release the push button, check that: • All fire panel lights are out • FIRE messages on E/W CRT disappear

U6KSC00

• CRC stops • Master “WARN” light goes out - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FIRE PROTECTION/SMOKE

CHAPTER 17: FIRE PROTECTION/SMOKE MALFUNCTION

: ENG 1 LOOP B FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: LOW PRESSURE IN THE LOOP B DETECTOR

CONSEQUENCE

:

- On ground with batteries only connected Press and hold the “ENG 1 FIRE TEST” push button, check that: • Half of “ENG 1 FIRE” lights are out (FIRE PANEL) • The AGENT 1 ENG 1 lights come on • ENG MASTER 1 “FIRE” light (115VU) comes on Release the push button • All fire panel lights are out • -

ENG MASTER 1 “FIRE” light is out On ground with external power On ground with external running In flight

Ecam displays consequences - In flight phases 1, 2, 6, 9, 10 Associated warning messages appear on the E/W CRT Test consequences - Press and hold the ENG 1 FIRE TEST P/B (FIRE PANEL), check that: • The “ENG1 FIRE” light (FIRE PANEL) is on • The AGENT 1 ENG1 “DISH” and “SQUIB” lights come on • The AGENT 2 ENG1 “DISH” and “SQUIB” lights come on • FIRE messages appear on E/W CRT • CRC is triggered

U6KSC00

• Master “WARN” light comes on

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FIRE PROTECTION/SMOKE

CHAPTER 17: FIRE PROTECTION/SMOKE - Release the push button, check that: • All fire panel lights are out • FIRE messages on E/W CRT disappear • CRC stops • Master “WARN” light goes out Appropriate messages will be available on MCDU (CFDS function)

U6KSC00

(when CFDS maintenance option selected). - Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FIRE PROTECTION/SMOKE

CHAPTER 17: FIRE PROTECTION/SMOKE MALFUNCTION

: APU LOOP A FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: APU LOOP A FAIL

CONSEQUENCE

:

- On ground with batteries only connected Press and hold the “APU FIRE TEST” push button, check that: • Half of “APU FIRE” light (FIRE PANEL) is ON • The AGENT APU lights “DISH” and “SQUIB” come on Release the push button, check that: • -

All fire panel lights are out On ground with external power On ground with engines running In flight

Ecam displayed consequences - In flight phases 1, 2, 6, 9, 10 Associated warning messages appear on the E/W CRT Test consequences - Press and hold the APU FIRE TEST P/B (FIRE PANEL), check that: • The “APU FIRE” light (FIRE PANEL) is on • The AGENT “DISH” and “SQUIB” lights come on • FIRE messages appear on E/W CRT • CRC is triggered • Master “WARN” light comes on - Release the push button, check that: • All fire panel lights are out • FIRE messages on E/W CRT disappear

U6KSC00

• CRC stops • Master “WARN” light goes out - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FIRE PROTECTION/SMOKE

CHAPTER 17: FIRE PROTECTION/SMOKE MALFUNCTION

: APU LOOP B FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: APU LOOP B FAIL

CONSEQUENCE

:

- On ground with batteries connected - Press and hold the “APU FIRE TEST” push button, check that: • Half of “APU FIRE” lights (FIRE PANEL) are out • The AGENT APU lights “DISH” and “SQUIB” come on - Release the push button, check that: • All fire panel lights are out - On ground with external power - On ground with engines running - In flight Ecam displayed consequences - In flight phases 1, 2, 6, 9, 10 • Associated warning messages appear on the E/W CRT Test consequences - Press and hold the APU FIRE TEST P/B (FIRE PANEL), check that: • The “APU FIRE” light (FIRE PANEL) is on • The AGENT “DISH” and “SQUIB” lights come on • FIRE messages appear on E/W CRT • CRC is triggered • Master “WARN” light comes on - Release the push button, check that: • All fire panel lights are out • FIRE messages on E/W CRT disappear • CRC stops

U6KSC00

• Master “WARN” light goes out - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FIRE PROTECTION/SMOKE

CHAPTER 17: FIRE PROTECTION/SMOKE MALFUNCTION

: AIR CONDITIONING SMOKE

MALFUNCTION DESCRIPTION

:

CAUSE

: A fire was started in pack 1

CONSEQUENCE

:

- No warning - Cockpit smoke generation (smoke generator is ready) if the pack 1 valve flow is on, smoke generation is activated • On instructor station inhibite smoke generation: smoke is not generated • On instructor station activate smoke generator: smoke appears by the air conditioning outlets • On instructor station inhibite smoke generation or cancell malfunction: • smoke generation stops

U6KSC00

• smoke is extracted automatically (about 2 min). - Cancelling malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FIRE PROTECTION/SMOKE

CHAPTER 17: FIRE PROTECTION/SMOKE MALFUNCTION

: AVIONIC SMOKE

MALFUNCTION DESCRIPTION

:

CAUSE

: EIS/PFD CAPT GENERATE SMOKE

CONSEQUENCE

:

- Warnings consequences: With blower FAN A or Extract FAN B active • The GEN 1 LINE P/B (EMER ELEC PLUR 21VU) “SMOKE” light comes on • The BLOWER AND EXTRACT (AUTO) P/B (22VU, VENTILATION PANEL) “FAULT” light comes on - In flight phases 1, 2, 3, 6, 9, 10 • SC • Master “CAUT” light comes on • Associated warning messages appear on the E/W CRT • “ELEC” page appears on SYS CRT - Smoke generation: (smoke generator is ready) On instructor station inhibit smoke generation • Smoke is not generated On instructor station activate smoke generation • Smoke appears by the FLIGHT DECK FLOOR OUTLET On instructor station inhibit smoke generation or cancel malfunction • Smoke generation stops • Smoke is extracted automatically (about 2 min). Avionics smoke warning disappears a few seconds after the defective instrument is no longer powered (circuit breaker EIS PFD CAPT (49VU). • Smoke extraction goes on as long as extraction is required - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

- Cancelling malfunction restores normal operation - The E/W CRT smoke warning is resetted in flight phase 10

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FIRE PROTECTION/SMOKE

CHAPTER 17: FIRE PROTECTION/SMOKE MALFUNCTION

: FWD CARGO SMOKE

MALFUNCTION DESCRIPTION

:

CAUSE

: Fire in FWD cargo compartment

CONSEQUENCE

:

If FWD lower cargo smoke detection option valid (modif No 20067) - On ground with external power - On ground with engines running - In flight • CARGO FWD “SMOKE” (22VU, cargo smoke panel) light comes on • ECAM displays consequences (in flight phases 1, 2, 3, 6, 9, 10) • CRC is triggered • MASTER “WARN” light comes • Associated warning messae appears on the E/W CRT • The AIR COND page appears on the SYS CRT - Actions: • Push the FWD CARGO SMOKE DISCH P/B (22VU, cargo smoke panel) • After 3 s, FWD/AFT CARGO SMOKE “DISH” • Lights come on

U6KSC00

• After 10 s all warnings disappear ("Fire is extinguished") - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation. - On instructor station, set the AGENT FIRE RESET, if it is installed the “DISH” lights go out.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FIRE PROTECTION/SMOKE

CHAPTER 17: FIRE PROTECTION/SMOKE MALFUNCTION

: AFT CARGO SMOKE

MALFUNCTION DESCRIPTION

:

CAUSE

: Fire in AFT cargo compartment

CONSEQUENCE

:

If AFT lower cargo smoke detection option valid (modif No 20069) - On ground with external power - On ground with engines running - In flight • CARGO AFT “SMOKE” (22VU, cargo smoke panel) light comes on • The 2 isolation valves of the cargo compartment heating and ventilation are shut off • Ecam displays consequences (in flight phases 1, 2, 3, 6, 9, 10) • CRC is triggered • MASTER “WARN” light comes on • Associated warning message appears on the E/W CRT • The AIR COND page appears on the SYS CRT - Actions: • Push the AFT CARGO SMOKE P/B (22VU, cargo smoke panel) • After 3s, FWD/AFT CARGO SMOKE “DISH” Lights come on • After 10 s all warnings disappear ("Fire is extinguished") - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation

U6KSC00

- On instructor station, set the AGENT FIRE RESET, if it is installed the “DISH” lights go out

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS FLIGHTDESCRIPTION COMPUTER

CHAPTER 18 - FLIGHT COMPUTER CONTENTS: SEC 1 FAIL SEC 2 FAIL SEC 3 FAIL ELAC 1 FAIL ELAC 2 FAIL

U6KSC00

FCDC 2 FAIL

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS FLIGHTDESCRIPTION COMPUTER

CHAPTER 18: FLIGHT COMPUTER MALFUNCTION

: SEC 1 FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Failure of the SEC 1

CONSEQUENCE

:

1) The FAULT light of the SEC 1 push button is illuminated on the overhead panel. 2) If flight phase 1, 2, 6, 9, 10: • Single chime sounds • Amber master caution light comes on • Appropriate messages appear on the Engines Warning Display (see sheet FWC A27310) 3) On the SYSTEM PAGES CRT: F/CTL page: • SPLR 3,R amber • SEC 1 becomes amber • LAF DEGRADED appears STATUS page: • Appropriate messages appear (see sheets FWC A27848,A27675) 4) ENGINES WARNINGS action requests: when the SEC 1 push button on the overhead panel is set to OFF position, the FAULT light disappears and the OFF light is illuminated. 5) Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

6) Cancelling the malfunction restores normal operation after reset of SEC 1 computer.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS FLIGHTDESCRIPTION COMPUTER

CHAPTER 18: FLIGHT COMPUTER MALFUNCTION

: SEC 2 FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Failure of the SEC 2

CONSEQUENCE

:

1) The FAULT light of the SEC 2 push button is illuminated on the overhead panel. 2) If flight phase 1, 2, 6, 9, 10: • Single chime sounds • Amber master caution light comes on • Appropriate messages appear on the Engines Warning Display (see sheet FWC A27320) 3) On the SYSTEM PAGES CRT: F/CTL page: • SPLR 5 amber • SEC 2 becomes amber • LAF DEGRADED appears STATUS page: • Appropriate messages appear (see sheets FWC A27840,A27680) 4) ENGINES WARNINGS action requests: when the SEC 2 push button on the overhead panel is set to OFF position, the FAULT light disappears and the OFF light is illuminated. 5) Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

6) Cancelling the malfunction restores normal operation after reset of SEC 2 computer.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS FLIGHTDESCRIPTION COMPUTER

CHAPTER 18: FLIGHT COMPUTER MALFUNCTION

: SEC3 FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Failure of the SEC 3

CONSEQUENCE

:

1) The FAULT light of the SEC 3 push button is illuminated on the overhead panel. 2) If flight phase 1, 2, 6, 9, 10: • Single chime sounds • Amber master caution light comes on • Appropriate messages appear on the Engines Warning Display (see sheet FWC A27330) 3) On the SYSTEM PAGES CRT: F/CTL page: • SPLR 1 amber • SPLR 2 amber • SEC 3 becomes amber • Appropriate messages appear (see sheets FWC A27841,A27685) 4) ENGINES WARNINGS action requests: When the SEC 3 push button on the overhead panel is set to OFF position, the FAULT light disappears and the OFF light is illuminated. 5) Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

6) Cancelling the malfunction restores normal operation after reset of SEC 3 computer.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS FLIGHTDESCRIPTION COMPUTER

CHAPTER 18: FLIGHT COMPUTER MALFUNCTION

: ELAC 1 FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Failure of the ELAC 1

CONSEQUENCE

:

1) The FAULT light of the ELAC 1 push button is illuminated on the overhead panel. 2) If flight phase 1, 2, 6, 9, 10: • Single chime sounds • Amber master caution light comes on • Appropriate messages appear on the Engines Warning Display (see sheet FWC A27200) 3) On the SYSTEM PAGES CRT: F/CTL page: • B.L AIL are amber boxed • G.R AIL • ELAC 1 becomes amber • LAF DEGRADED appears STATUS page: • Appropriate message appears (see sheet FWC A27620) 4) ENGINE WARNINGS action requests: when the ELAC 1 push button on the overhead panel is set to OFF position, the FAULT light disappears and the OFF light is illuminated. 5) Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

6) Cancelling the malfunction restores normal operation after reset of ELAC 1 computer.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS FLIGHTDESCRIPTION COMPUTER

CHAPTER 18: FLIGHT COMPUTER MALFUNCTION

: ELAC 2 FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Failure of the ELAC 2

CONSEQUENCE

:

1) The FAULT light of the ELAC 2 push button is illuminated on the overhead panel. 2) If flight phase 1, 2, 6, 9, 10: • Single chime sounds • Amber master caution light comes on • Appropriate messages appear on the Engines Warning Display (see sheet FWC A27210) 3) On the SYSTEM PAGES CRT: F/CTL page: • G.L AIL are amber boxed • B.R AIL • ELAC 2 becomes amber • LAF DEGRADED appears STATUS page: • Appropriate message appears (see sheet FWC A27625) 4) ENGINES WARNINGS action requests: when the ELAC 2 push button on the overhead panel is set to OFF position, the FAULT light disappears and the OFF light is illuminated. 5) Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

6) Cancelling the malfunction restores normal operation after reset of ELAC 2 computer.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS FLIGHTDESCRIPTION COMPUTER

CHAPTER 18: FLIGHT COMPUTER MALFUNCTION

: FCDC 2 FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Failure of the FCDC 2

CONSEQUENCE

:

1) Data concentration is still achieved par FCDC 1 2) On the ENGINES WARNINGS CRT: • Appropriate message appears (see that FWC A27557) 3) On the SYSTEM PAGES CRT: STATUS page • Appropriate message appears (see sheet FWC A27559) 4) If FCDC 1 is not supplied, F/CTL page shows no information

U6KSC00

5) Cancelling the malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS FLIGHTDESCRIPTION COMPUTER

U6KSC00

THIS PAGE INTENTIONALLY LEFT BLANK

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FMGC

CHAPTER 19 - FMGC CONTENTS: AP1 DISENGAGED (FD1 AVAILABLE) AP2 DISENGAGED (FD2 AVAILABLE) AP1 LOC CAPTURE FAIL AP2 LOC CAPTURE FAIL AP1 GLIDE CAPTURE FAIL AP2 GLIDE CAPTURE FAIL AP1 ALIGN FAIL AP2 ALIGN FAIL ATHR1 FAIL ATHR2 FAIL NO FLARE LONG FLARE DRIFT LOC BEAM (AUTOLAND) LAND CAPABILITY CHANGE RADIO ALTI DISCREPANCY (AUTOLAND) LOC CAPT STUCK LOC CAPT DRIFT HUD COMPUTER FAIL PVI FAIL FMGC 1 FAIL FMGC 2 FAIL MCDU 1 FAIL FLIGHT MANAGEMENT 1 FAIL FCU SPEED SYNCHRO FAIL FCU REDONDANCY LOST

U6KSC00

FCU FAIL

DATE: SEP 1998

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FMGC

CHAPTER 19: FMGC MALFUNCTION

: AP1 DISENGAGED (FD1 AVAILABLE)

MALFUNCTION DESCRIPTION

:

CAUSE

: Cut between AP INSTINCTIVE DISCONNET switch and FMGC1

CONSEQUENCE

:

1 - If AP1 was not engaged: • AP1 can’t be engaged - If AP1 only was engaged: • AP1 will disengage • Alarm signalled to the pilot • AP1 can’t be reengaged - If AP1 and AP2 were engaged: • AP1 will disengage • AP2 remains engaged • AP1 can’t reengaged • No alarm 2 - Alarm description • The cavalry aural warning sounds during 3 s • The red MASTER WARN light comes on the glareshield during 3 s • Red message “AP OFF” appears on the ENGINES WARNING display during 9 s Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

3 - Cancelling malfunction restores normal operation AP1 can be reengaged by pilot action on AP1 pushbutton.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FMGC

CHAPTER 19: FMGC MALFUNCTION

: AP2 DISENGAGED (FD2 AVAILABLE)

MALFUNCTION DESCRIPTION

:

CAUSE

: Cut between AP INSTINCTIVE DISCONNECT switch and FMGC2.

CONSEQUENCE

:

1 - If AP2 was not engaged: • AP2 can’t be engaged - If AP2 only was engaged: • AP2 will disengage • Alarm signalled to the pilot • AP2 can’t be reengaged - If AP1 and AP2 were engaged: • AP2 will disengage • AP1 remains engaged • AP2 can’t reengaged • No alarm 2 - Alarm description • The cavalry aural warning sounds during 3 s • The red MASTER WARN light comes on the glareshield during 3 s • Red message “AP OFF” appears on the ENGINES WARNING display during 9 s Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

3 - Cancelling malfunction restores normal operation AP1 can be reengaged by pilot action on AP2 pushbutton.

DATE: SEP 1998

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FMGC

CHAPTER 19: FMGC MALFUNCTION

: AP1 LOC CAPTURE FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: LOC deviation sent by ILS1 and ILS2 to FMGC1 is fixed to a value of 250 microA.

CONSEQUENCE

:

1 - If AP1 was engaged or FD1 without AP2 engaged, LOC CAPT MODE can be engaged but AP1 doesn’t follow LOC beam 2 - Alarm description • No alarm - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). 3 - Cancelling malfunction restores normal operation

U6KSC00

LOC deviation value is no more fixed.

DATE: SEP 1998

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FMGC

CHAPTER 19: FMGC MALFUNCTION

: AP2 LOC CAPTURE FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: LOC deviation sent by ILS1 and ILS2 to FMGC2 is fixed to a value of 250 microA.

CONSEQUENCE

:

1 - If AP2 was engaged and AP1 or FD2 engaged without AP1 and FD1 engaged, LOC CAPT MODE can be engaged but AP2 doesn’t follow LOC beam 2 - Alarm description • No alarm - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). 3 - Cancelling malfunction restores normal operation

U6KSC00

LOC deviation value is no more fixed.

DATE: SEP 1998

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FMGC

CHAPTER 19: FMGC MALFUNCTION

: AP1 GLIDE CAPTURE FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: GLIDE deviation sent by ILS1 and ILS2 to FMGC1 is fixed to a value of 80 microA.

CONSEQUENCE

:

1 - If G/S CAPT MODE (G/S * green on FMA) wasn’t engaged • If AP1 was engaged or FD1 without AP2 engaged, G/S CAPT MODE doesn’t engage in FMGC1, while conditions are satisfied. AP1 or FD1 remains in G/S ARM mode (G/S blue on FMA). - If G/S * green was on the FMA • G/S CAPT MODE remains engaged but AP1 doesn’t follow GLIDE beam 2 - Alarm description • No alarm - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

3 - Cancelling malfunction restores normal operation GLIDE deviation value is no more fixed.

DATE: SEP 1998

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FMGC

CHAPTER 19: FMGC MALFUNCTION

: AP2 GLIDE CAPTURE FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: GLIDE deviation sent by ILS1 and ILS2 to FMGC2 is fixed to a value of 80 microA.

CONSEQUENCE

:

1 - IF G/S CAPT MODE (G/S * green on FMA) wasn’t engaged: • IF AP2 was engaged and AP1 not engaged or FD2 engaged without AP1 and FD1 engaged, GLIDE CAPT MODE doesn’t engage in FMGC2 while conditions are satisfied. AP2 or FD2 remains in G/S ARM (G/S blue on FMA). - If G/S CAPT MODE was engaged: • it remains engaged but AP2 doesn’t follow the Glide beam. 2 - Alarm description • No alarm - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). 3 - Cancelling malfunction restores normal operation

U6KSC00

Glide deviation value is no more fixed.

DATE: SEP 1998

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FMGC

CHAPTER 19: FMGC MALFUNCTION

: AP1 ALIGN FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Error on FMGC1 output sent to Flight controls: Body yaw rate orders are fixed during all ALIGN phase.

CONSEQUENCE

:

1 - If AP1 is not engaged • No effect - If AP1 is not in ALIGN landing phase • No effect - If AP1 is in ALIGN landing phase: • With crosswind the drift angle is not set to zero • FD indicates the error on yaw order • No alarm 2 - Alarm description • No purpose 3 - Engines warning action requests • No purpose 4 - Engines warning action display • No purpose

U6KSC00

5 - Cancelling malfunction or ALIGN SUBMODE disengagement (loss of LAND TRACK MODE, AP1 disengagement, ROLL OUT SUBMODE engagement). restores normal operation - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

DATE: SEP 1998

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FMGC

CHAPTER 19: FMGC MALFUNCTION

: AP2 ALIGN FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Error on FMGC2 output sent to Flight controls: Body yaw rate orders are fixed during all ALIGN phase.

CONSEQUENCE

:

1 - If AP2 is not engaged: • No effect - If AP2 is engaged • No effect if AP2 is not in ALIGN landing phase - If AP2 is in ALIGN landing phase • With crosswind the drift angle is not set to zero • FD indicates the error on yaw order • No alarm 2 - Alarm description • No purpose 3 - Engines warning action requests • No purpose 4 - Engines warning action display • No purpose

U6KSC00

5 - Cancelling malfunction or ALIGN SUBMODE disengagement (loss of LAND TRACK MODE, AP2 disengage, ROLL OUT SUBMODE engagement) restores normal operation - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

DATE: SEP 1998

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FMGC

CHAPTER 19: FMGC MALFUNCTION

: ATHR1 FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Cut of A/THR Bus information between FMGC1 and EIU.

CONSEQUENCE

:

1 - IF ATHR1 was not engaged: • ATHR1 can’t be engaged 2 - IF ATHR1 was engaged: • ATHR will disengage • MASTER CAUTION light illuminates • Single chime sounds • Amber message ’THR LK’ blinking on the FMA • Amber message ’AUTO FLT A/THR OFF’ appears on the ENGINE WARNING display • Amber message ’ENG THRUST LOCKED’ appears every 5 s on the Engine Warning Display • Amber message ’EO CLR’ appears on MCDU • A/THR appears on the ’INOP SYS’ colum on the ’STATUS’ page

U6KSC00

3 - Cancelling malfunction restores normal operation ATHR1 can be reengaged by pilot action on ATHR pushbutton

DATE: SEP 1998

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FMGC

CHAPTER 19: FMGC MALFUNCTION

: ATHR2 FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Cut of A/THR Bus information between FMGC2 and EIU.

CONSEQUENCE

:

1 - IF ATHR2 was not engaged: • ATHR2 can’t be engaged 2 - IF ATHR2 was engaged: • ATHR will disengage • MASTER CAUTION light illuminates • Single chime sounds • Amber message ’THR LK’ on the FMA • Amber message ’AUTO FLT A/THR OFF’ appears on the ENGINE WARNING display • Amber message ’ENG THRUST LOCKED’ appears every 5 s on the Engine Warning Display • Amber message ’EO CLR’ appears on MCDU • A/THR appears on the ’INOP SYS’ colum on the ’STATUS’ page

U6KSC00

3 - Cancelling malfunction restores normal operation ATHR2 can be reengaged by pilot action on ATHR pushbutton

DATE: SEP 1998

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FMGC

CHAPTER 19: FMGC MALFUNCTION

: NO FLARE

MALFUNCTION DESCRIPTION

:

CAUSE

: Error in the radio altitude transmitted by the Radio altimeter 1 and 2 to FMGC1 and FMGC2 (RA1 = RA2 = RAtrue + 55 ft).

CONSEQUENCE

:

1 - The aircraft lands without flare phase (Neither Align, nor Roll Out modes are available). • No alarm signalled to the pilot. 2 - Alarm description • No alarm - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

3 - Cancelling malfunction restores normal operation FMGC1 and FMGC2 receive the true radio altitude.

DATE: SEP 1998

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FMGC

CHAPTER 19: FMGC MALFUNCTION

: LONG FLARE

MALFUNCTION DESCRIPTION

:

CAUSE

: Error in the radio altitude transmitted by the Radio altimeter 1 and 2 to FMGC1 and FMGC2 (RA1 = RA2 = RAtrue - 25 Ft)

CONSEQUENCE

:

1 - The aircraft remains at 25 ft above the runway • FLARE indication appears on FMA 2 - Alarm description • No purpose - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

3 - Cancelling malfunction restores normal operation

DATE: SEP 1998

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FMGC

CHAPTER 19: FMGC MALFUNCTION

: DRIFT LOC BEAM (AUTOLAND)

MALFUNCTION DESCRIPTION

:

CAUSE

: LOC Deviation sent by ILS1 and ILS2 to FMGC1 and FMGC2 has a drift of 20 microA/s.

CONSEQUENCE

:

1 - AP/FD doesn’t follow the localizer beam • If Radio alti 200 ft, the FWC signalled an alarm as soon as loc deviation become greater than 20 microA. 2 - Alarm description • AUTOLAND WARNING light flashes on the pilot and copilot’s glareshied • Alarm can be cancelled by engagement of GO AROUND MODE - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). 3 - Cancelling malfunction restores normal operation

U6KSC00

FMGC1 and FMGC2 receive the true loc deviation

DATE: SEP 1998

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FMGC

CHAPTER 19: FMGC MALFUNCTION

: LAND CAPABILITY CHANGE

MALFUNCTION DESCRIPTION

:

CAUSE

: Error on the signal “Power supply split” (input of FMGC1)

CONSEQUENCE

:

1 - If both FMGC were already in CAT3 (CAT3 DUAL on both PFD’s) • Alarm is sent to the pilot 2 - Alarm description • Three click sound • CAT3 SINGLE ONLY appears on FMA - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

3 - Cancelling malfunction restores normal operation

DATE: SEP 1998

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FMGC

CHAPTER 19: FMGC MALFUNCTION

: RADIO ALTI DISCREPANCY (AUTOLAND)

MALFUNCTION DESCRIPTION

:

CAUSE

: Radio altitudes delivered by RA1 and RA2 present a difference of 15 ft (RA2 delivers a wrong value = RA1 value + 15 ft)

CONSEQUENCE

:

The radio altitude displayed on PFD2 is 15 ft greater than that on PFD1 When AP1, or AP1 and AP2 engaged, the FMGS uses radio altitude from transceiver RA1. When only AP2 engaged, the FMGS uses radio altitude from transceiver RA2

U6KSC00

Cancelling the malfunction restores normal operation

DATE: SEP 1998

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FMGC

CHAPTER 19: FMGC MALFUNCTION

: LOC CAPT STUCK

MALFUNCTION DESCRIPTION

:

CAUSE

: Bad coupling of the LOC antenna on the LOC receiver part of the ILS 1 receiver

CONSEQUENCE

:

- On the CAPT PFD screen, if the CAPT ILS pushbutton of the CAPT EFIS control panel is pressed, the LOC index remains stuck to the position it had at the time of the malfunction’s insertion. - The erroneous LOC information is also sent to FWC1, FWC2, GPWS, FMGC1, FMGC2 and CFDIU. - The ILS1 call sign is still received. ACTION: NIL - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FMGC

CHAPTER 19: FMGC MALFUNCTION

: LOC CAPT DRIFT

MALFUNCTION DESCRIPTION

:

CAUSE

: Bad coupling of the LOC antenna on the LOC receiver part of the ILS 1 receiver

CONSEQUENCE

:

- On the CAPT PFD screen, if the CAPT ILS pushbutton of the CAPT EFIS control panel is pressed, the LOC index drifts at 2 dots per minute and then remains stuck at the end of the scale. - Likewise, on the F/O ND screen, in ROSE-ILS mode, the LOC deviation bar drifts at 2 dots per minute and then remains stuck at the end of the scale. - The erroneous LOC information is also sent to FWC1, FWC2, GPWS, FMGC1, FMGC2 and CFDIU. - The ILS 1 test is still valid. - The ILS 1 call sign is still received. ACTION: NIL - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maitenance option selected).

U6KSC00

Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FMGC

CHAPTER 19: FMGC MALFUNCTION

: HUD COMPUTER FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Loss of power supply to the HUD computer

CONSEQUENCE

:

HUD computer is no more operational. The Optical Head Unit displays a TBD picture.

U6KSC00

Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FMGC

CHAPTER 19: FMGC MALFUNCTION

: PVI FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Loss of power supply to the PVI

CONSEQUENCE

:

U6KSC00

PVI is no more operational and shows no information.

DATE: SEP 1998

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FMGC

CHAPTER 19: FMGC MALFUNCTION

: FMGC 1 FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Circuit breaker 10 CA1 28VDC trips.

CONSEQUENCE

:

1 - Loss of power to FMGC1 -

AP1 and FD1 disengage if they were engaged AP1 can’t be reengaged Both PFD use FD2 If AP2 wasn’t engaged:

• Alarm is sent to the pilot • AP2 can be engaged 2 - Alarm description • The cavalry aural warning sounds • The red MASTER WARN light comes on the glareshield • The red message ’AUTO FLIGHT AP OFF’ appears • On the ENGINES WARNING display

U6KSC00

3 - Cancelling the malfunction and resetting circuit breaker restore normal operation

DATE: SEP 1998

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FMGC

CHAPTER 19: FMGC MALFUNCTION

: FMGC 2 FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Loss of power supply 28VDC to the FMGC2.

CONSEQUENCE

:

1 - Loss of power to FMGC2 -

AP2 and FD2 disengage if they were engaged AP2 can’t be reengaged Both PFD use FD1 If AP1 wasn’t engaged:

• Alarm is sent to the pilot • AP1 can be engaged 2 - Alarm description • The cavalry aural warning sounds • The red MASTER WARN light comes on the glareshield • Red message ’AUTO FLT AP OFF’ appears • On the ENGINES WARNING display - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

3 - Cancelling malfunction restores normal operation

DATE: SEP 1998

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FMGC

CHAPTER 19: FMGC MALFUNCTION

: MCDU 1 FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Loss of power supply 115VAC to MCDU1.

CONSEQUENCE

:

MCDU1 is no more illuminated and its display shows no information. • Any action on the MCDU1 has no effect.

U6KSC00

- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

DATE: SEP 1998

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FMGC

CHAPTER 19: FMGC MALFUNCTION

: FLIGHT MANAGEMENT 1 FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: NOT POSSIBLE

CONSEQUENCE

:

U6KSC00

NOT POSSIBLE

DATE: SEP 1998

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FMGC

CHAPTER 19: FMGC MALFUNCTION

: FCU SPEED SYNCHRO FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: NO TRANSMISSION OF THE SPEED FROM THE FCU TO THE FMGC1 AND 2.

CONSEQUENCE

:

Using speed knob on the FCU, in Speed Manual control, new selected speed on the FCU is not displayed on both PFD’s. ATS function does not follow new FCU speed selection and keeps as target the selected speed valid when malfunction breakdown. - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

Cancelling the malfunction on instructor station restores normal operation.

DATE: SEP 1998

Page Page 283 25

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FMGC

CHAPTER 19: FMGC MALFUNCTION

: FCU REDONDANCY LOST

MALFUNCTION DESCRIPTION

:

CAUSE

: Cut between FCU and FMGC1 and FMGC2 of the signal FCU1 HEALTHTY.

CONSEQUENCE

:

- Message “AUTO FLT FCU1 FAULT • BARO REF... CHECK" appears on the ENGINES WARNING Display - Message “FCU1" as inoperative system appears on the Status page - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

Cancelling the malfunction restores normal operation

DATE: SEP 1998

Page Page 284 26

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FMGC

CHAPTER 19: FMGC MALFUNCTION

: FCU FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Loss of power supply to FCU1 and 2.

CONSEQUENCE

:

1 - FCU is no more illuminated • Displays show no information • If they were engaged, ATHR1 and ATHR2 disengaged, they can’t be reengaged • If AP1 or AP2 were in GO AROUND MODE or LAND TRACK MODE: • AP and FD remain engaged • If AP1 and AP2 were not in GO AROUND MODE or LAND TRACK MODE, AP and FD disengaged they can’t be reengaged alarm AP OFF 2 - Alarm description • Amber message ’THR LK’ blinking on FMA. • Cavalry aural warning sounds • Red MASTER WARN light comes on the glareshield • Red message ’AUTO FLT AP OFF’ appears • on the ENGINES WARNING display • Amber MASTER CAUTION light comes on the glareshield • Message ’AUTO FLT FCU 1+2 FAULT’ PFD BARO REF: STD ONLY’ appears on the ENGINES WARNING Display - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). 3 - Malfunction disengagement On Instructor action 4 - Operational consequences

U6KSC00

Normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FMGC

U6KSC00

THIS PAGE INTENTIONALLY LEFT BLANK

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FUEL A320

CHAPTER 20 - FUEL A320 CONTENTS: LEFT TANK PUMP 1 LO PR CENTER TANK PUMP 1 LO PR RIGHT TANK PUMP 1 LO PR LEFT TANK PUMP 2 LO PR CENTER TANK PUMP 2 LO PR RIGHT TANK PUMP 2 LO PR LEFT FUEL QTY INDIC INC/DEC (1) RIGHT FUEL QTY INDIC INC/DEC (1) LEFT TANK FUEL LEAK RIGHT WING QTY PROBE FAILED FUEL QTY INDICATION FAIL X-FEED VALVE STUCK

U6KSC00

REFUELLING FAIL

DATE: SEP 1998

Page Page287 1

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FUEL A320

CHAPTER 20: FUEL A320 MALFUNCTION

: LEFT TANK PUMP 1 LO PR

MALFUNCTION DESCRIPTION

:

CAUSE

: PUMP 21QA MECHANICALLY FAILED

CONSEQUENCE

:

- “FAULT” light comes on FUEL panel, - If aircraft is in flight phases 1, 2, 6, 9, 10: • Appropriate messages (nature of the failure and action to be performed) appear on E/W CRT, • “FUEL” page appears on SYS CRT. - When pump is switched off: • “FAULT” light goes out and “OFF” light comes on FUEL panel • Action to be performed disappears on E/W CRT - After pressing CLR P/B switch (CAPT or F/O):

U6KSC00

• Appropriate STATUS page appears on SYS CRT. - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation.

DATE: SEP 1998

Page Page288 2

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FUEL A320

CHAPTER 20: FUEL A320 MALFUNCTION

: CENTER TANK PUMP 1 LO PR

MALFUNCTION DESCRIPTION

:

CAUSE

: PUMP 37QA MECHANICALLY FAILED

CONSEQUENCE

:

- If pump is running: • FAULT LIGHT comes on. - If aircraft is in flight phase 1, 2, 6, 9, 10: • SC sounds + MASTER CAUTION. • Appropriate messages appear on E/WD CRT • “FUEL” page appears on SYS CRT - When pump is switched off: • “FAULT” light remains out and “OFF” light comes on • Action to be performed disappears on E/WD CRT - After pressing CLEAR P/B switch:

U6KSC00

• Appropriate STATUS page appears on SYS CRT - Cancelling malfunction restores normal operation.

DATE: SEP 1998

Page Page289 3

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FUEL A320

CHAPTER 20: FUEL A320 MALFUNCTION

: RIGHT TANK PUMP 1 LO PR

MALFUNCTION DESCRIPTION

:

CAUSE

: PUMP 22QA MECHANICALLY FAILED

CONSEQUENCE

:

- “FAULT” light comes on FUEL panel, - If aircraft is in flight phases 1,2, 6, 9, 10: • Appropriate messages (nature of the failure and action to be performed) appear on E/W CRT, • “FUEL” page appears on SYS CRT. - When pump is switched off: • “FAULT” light goes out and “OFF” light comes on FUEL panel, • Action to be performed disappears on E/W CRT - After pressing CLR P/B switch (CAPT or F/O):

U6KSC00

• Appropriate STATUS page appears on SYS CRT. - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation.

DATE: SEP 1998

Page Page290 4

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FUEL A320

CHAPTER 20: FUEL A320 MALFUNCTION

: LEFT TANK PUMP 2 LO PR

MALFUNCTION DESCRIPTION

:

CAUSE

: PUMP 25QA MECHANICALLY FAILED

CONSEQUENCE

:

- “FAULT” light comes on FUEL panel, - If aircraft is in flight phases 1, 2, 6, 9, 10: • Appropriate messages (nature of the failure and action to be performed) appear on E/W CRT, • “FUEL” page appears on SYS CRT. - When pump is switched off: • “FAULT” light goes out and “OFF” light comes on FUEL panel, • Action to be performed disappears on E/W CRT - After pressing CLR P/B switch (CAPT or F/O):

U6KSC00

• Appropriate STATUS page appears on SYS CRT. - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation.

DATE: SEP 1998

Page Page291 5

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FUEL A320

CHAPTER 20: FUEL A320 MALFUNCTION

: CENTER TANK PUMP 2 LO PR

MALFUNCTION DESCRIPTION

:

CAUSE

: PUMP 38QA MECHANICALLY FAILED

CONSEQUENCE

:

- In flight,CTR TK Feeding and Slats retracted - If aircraft is in flight phase 1, 2, 6, 9, 10: • Audio single chime sounds • “Master Caution” amber light flash on glareshield • Appropriate messages (nature of the failure and action to be performed) appear on E/W CRT • “FUEL” page appears on SYS CRT - When pump is switched off: • “FAULT” light remains out and “OFF” light comes on FUEL panel • Action to be performed disappears on E/W CRT - After pressing CLR P/B switch (CAPT or F/O):

U6KSC00

• Appropriate STATUS page appears on SYS CRT - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FUEL A320

CHAPTER 20: FUEL A320 MALFUNCTION

: RIGHT TANK PUMP 2 LO PR

MALFUNCTION DESCRIPTION

:

CAUSE

: PUMP 26QA MECHANICALLY FAILED

CONSEQUENCE

:

- “FAULT” light comes on FUEL panel, - If aircraft is in flight phases 1, 2, 6, 9, 10: • Appropriate messages (nature of the failure and action to be performed) appear on E/W CRT, • “FUEL” page appears on SYS CRT. - When pump is switched off: • “FAULT” light goes out and “OFF light comes on FUEL panel, • Action to be performed disappears on E/W CRT - After pressing CLR P/B switch (CAPT or F/O):

U6KSC00

• Appropriate STATUS page appears on SYS CRT. - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FUEL A320

CHAPTER 20: FUEL A320 MALFUNCTION

: LEFT FUEL QTY INDIC INC/DEC (1)

PARAMETERS

: LEFT FUEL QUANTITY

MIN VALUE

: 0 kg MAX VALUE: 5532 kg CHANGE RATE: 20 kg/s

MALFUNCTION DESCRIPTION

:

CAUSE

: PROBE value is wrong (24QT1) and LABEL 257 is affected

CONSEQUENCE

:

- For all flight phases:

U6KSC00

• Left inner cell fuel quatity displayed by ECAM varies in accordance with the quantity selected by the instructor and total fuel quantity displayed by ECAM is also affected. - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation.

DATE: SEP 1998

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CHAPTER 20: FUEL A320 MALFUNCTION

: RIGHT FUEL QTY INDIC INC/DEC (1)

PARAMETERS

: RIGHT FUEL QUANTITY

MIN VALUE

: 0 kg MAX VALUE: 5532 kg CHANGE RATE: 20 kg/s

MALFUNCTION DESCRIPTION

:

CAUSE

: PROBE value is wrong (24QT2) and LABEL 261 is affected

CONSEQUENCE

:

- For all flight phases:

U6KSC00

• Right inner cell fuel quantity displayed by ECAM varies in accordance with the quantity selected by the instructor and total fuel quantity displayed by ECAM is also affected. - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FUEL A320

CHAPTER 20: FUEL A320 MALFUNCTION

: LEFT TANK FUEL LEAK

MALFUNCTION DESCRIPTION

:

CAUSE

: BREAK IN LH INNER CELL

CONSEQUENCE

:

Left inner can fuel quantity decreases quickly. When left inner cell quantity approximately falls below 750 kg (1650 lb). Check that: - Left intercell transfer valves open, - Consequently, left outer cell fuel quantity decreases and left inner cell fuel quantity is affected. - If left wing fuel LO level is detected during at least 30 seconds and if aircraft is in flight phases 1, 2, 6, 10 then: • Audio single chime sounds, • “Master caution” amber lights flash or glareshield, • Appropriate message (nature of failure) appears on E/W CRT. • “FUEL” page appears on SYS CRT. - After pressing CLR/B switch (CAPT or F/O):

U6KSC00

• Appropriate STATUS page appears on SYS CRT - Appropriate messages will be available on MCDU (MENU MODE, CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FUEL A320

CHAPTER 20: FUEL A320 MALFUNCTION

: RIGHT WING QTY PROBE FAILED

MALFUNCTION DESCRIPTION

:

CAUSE

: PROBE 21QT2 and 33QT2 failed

CONSEQUENCE

:

- For all flight phases:

U6KSC00

• Right outer cell Fuel quantity and total fuel quantity displayed by ECAM are downgraded (the two least significant digits of the indication are forced to zero with an amber line across). - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FUEL A320

CHAPTER 20: FUEL A320 MALFUNCTION

: FUEL QTY INDICATION FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: F.Q.I. COMPUTER FAILED

CONSEQUENCE

:

- For all flight phases: • Fuel quantities and fuel temperature indications displayed by ECAM are replaced by amber XX. • On MCDUs, on FUEL PRED page, cyan FQ indication disappears.

U6KSC00

- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FUEL A320

CHAPTER 20: FUEL A320 MALFUNCTION

: X-FEED VALVE STUCK

MALFUNCTION DESCRIPTION

:

CAUSE

: VALVE STUCK IN POSITION

CONSEQUENCE

:

- Whether X-FEED P/B pressed “ON” and X-FEED valve is stuck in close position or X-FEED P/B released “OFF” and X-FEED valve is stuck in open position, then: - If aircraft is in flight phases 1, 2, 6, 9, 10: • Appropriate message (nature of failure) appears on E/W CRT, • “FUEL” page appears on SYS CRT. - After pressing CLR P/B switch (CAPT or F/O):

U6KSC00

• Appropriate STATUS page appears on SYS CRT. - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION FUEL A320

CHAPTER 20: FUEL A320 MALFUNCTION

: REFUELING FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: LOSS OF D.C. POWER SUPPLY AFTER C/B 2QU

CONSEQUENCE

:

- If refuel is in progress: • Refuel operation aborts, • Indicator light AUTO REFUEL “END” flashes on the refueling control panel - If refuel is not running and starting procedure is being carried out: • Refuel is impossible.

U6KSC00

- Cancelling malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION HYDRAULIC POWER

CHAPTER 21 - HYDRAULIC POWER CONTENTS: RSVR FLUID QTY INC/DEC # G (1) RSVR FLUID QTY INC/DEC # B (1) RSVR FLUID QTY INC/DEC # Y (1) RSVR OVERHEAT # G RSVR OVERHEAT # B RSVR OVERHEAT # Y RSVR LO AIR PRESS # G RSVR LO AIR PRESS # B 22 PSI RSVR LO AIR PRESS # B 35 PSI RSVR LO AIR PRESS # Y HYD PRESS INC/DEC # G (psi) HYD PRESS INC/DEC # B (psi) HYD PRESS INC/DEC # Y (psi) ELEC PUMP FAIL # B ELEC PUMP FAIL # Y PUMP FAIL # G PTU FAIL # Y RAT PUMP FAIL # B

U6KSC00

RAT NO AUTOMATIC EXTENSION # B

DATE: SEP 1998

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CHAPTER 21: HYDRAULIC POWER MALFUNCTION

: RSVR FLUID QTY INC/DEC # G (1)

PARAMETERS

: Green reservoir quantity

MIN VALUE

: 01 MAX VALUE: 18 1 CHANGE RATE l/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Green reservoir quantity varies according to the quantity selected by the instructor.

CONSEQUENCE

:

- If tank level is below 31(0.8 gal) • If green Eng 1 pump P/B (40 VU) is on, its “FAULT” light comes on. • If PTU (AUTO) P/B (40 VU) is on, its “FAULT” light comes on - In flight phases 1, 2, 3, 6, 9, 10 and in normal hydraulic conditions Then • Single chime sounds • Master caution light comes on • Associated warning message appears on E/W CRT (29090) • HYD page appears on the SYS CRT - When green Eng 1 pump P/B is switched off • Green system pressure decreases (except if PTU comes on) • The Eng 1 pump “FAULT” light goes off • The Eng 1 pump “OFF” light comes on • The action is fed back on the E/W and SYS CRT’s - When PTU (AUTO) P/B is switched off • Green system pressure decreases down to 0 psi • The PTU (AUTO) P/B “FAULT” light goes off • The PTU (AUTO) P/B “OFF” light comes on

U6KSC00

• The action is fed back on the E/W and SYS CRT’s - After successive actions on “CLR” P/B (Ecam Control Panel), the STATUS page appears on the SYS CRT

DATE: SEP 1998

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CHAPTER 21: HYDRAULIC POWER

EXTERNAL CONSEQUENCES: - When green system pressure decreases, if active, following hydraulic users are affected: • YAW DAMPER, PITCH TRIM, ENGINE 1 REVERSE, SPOILER 1, RUDDER, ELEVATOR, AILERONS, SPOILER 5, NORMAL BRAKES • NOSE WHEEL STEERING, LANDING GEARS, SLATS, FLAPS - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

- Cancelling malfunction restores normal operations.

DATE: SEP 1998

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CHAPTER 21: HYDRAULIC POWER MALFUNCTION

: RSVR FLUID QTY INC/DEC # B (1)

PARAMETERS

: Blue reservoir quantity

MIN VALUE

: 01 MAX VALUE: 8 1 CHANGE RATE: 1 l/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Blue reservoir quantity varies according to the quantity selected by the instructor

CONSEQUENCE

:

If tank level is below 21(0.5 gal). - If blue elec. pump P/B (40 VU) is in normal AUTO configuration its “FAULT” light comes on. - If the aircraft is in flight phases 1, 2, 3, 6, 9, 10 in normal hydraulic conditions. Then • Single chime sounds • Master caution light comes on • Associated warning message appears on the E/W CRT (29110) • HYD page appears on the SYS CRT - When blue elec. pump P/B is switched OFF • Blue sys. pressure decreases (except if RAT supplies the blue sys.) • The blue elec. pump P/B “FAULT” light goes off • The blue elec. pump P/B “OFF” light comes on • The action is fed back on the E/W and SYS CRT’s (HYD and STATUS pages) - After successive actions on CLR" P/B (Ecam Control Panel), the STATUS page appears on the SYS CRT. EXTERNAL CONSEQUENCES: When blue system pressure decreases, if active, following hydraulic users are affected:

U6KSC00

• SPOILER 3, ELEVATOR, AILERONS, RUDDER • EMERGENCY GENERATOR, SLATS - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operations.

DATE: SEP 1998

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CHAPTER 21: HYDRAULIC POWER MALFUNCTION

: RSVR FLUID QTY INC/DEC # Y (1)

PARAMETERS

: Yellow reservoir quantity

MIN VALUE

: 01 MAX VALUE: 18 l CHANGE RATE: 2 l/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Yellow reservoir quantity varies according to the quantity selected by the instructor.

CONSEQUENCE

:

If tank level is below 31(0.8 gal). -

If yellow ENG 2 pump P/B is on, its “FAULT” light comes on If PTU (AUTO) P/B is on, its “FAULT” light comes on If yellow Elec. pump P/B is on, its “FAULT” light comes on If the aircraft is in flight phases 1, 2, 3, 6, 9, 10 in normal hydraulic conditions.

Then • Single chime sounds • Master caution light comes on • Associated warning message appears on E/W CRT (29100) • HYD page appears on the SYS CRT - When yellow Eng 2 pump P/B is switched off • Yellow system pressure decreases except if PTU or Elec pump comes on • The Eng 2 pump P/B “FAULT” light goes off • The Eng 2 pump P/B “OFF” light comes on • The action is fed back on the E/W and SYS CRT’s (HYD and STATUS pages) - When PTU (Auto) P/B is switched off • PTU is not supplie by Fluid, then it is inactive • The PTU (Auto) P/B “FAULT” light goes off • The PTU (Auto) P/B “OFF” light comes on

U6KSC00

• The action is fed back on the E/W and SYS CRT’s (HYD and status pages)

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION HYDRAULIC POWER

CHAPTER 21: HYDRAULIC POWER - When yellow elec. pump P/B is switched off • Yellow system pressure decreases down to O psi • Yellow elec. pump P/B “FAULT” light goes off • Yellow elec. pump P/B “ON” light goes off • The action is fed back on the E/W and SYS CRT units (HYD and STATUS pages) - After successive actions on “CLR” P/B (Ecam Control Panel) the STATUS page appears on the SYS CRT EXTERNAL CONSEQUENCES: When Yellow system pressure decreases, if active, following hydraulic users are affected • YAW DAMPER, PITCH TRIM, ENGINE 2 REVERSE, SPOILER 2, RUDDER, ELEVATOR, SPOILER 4 • FLAPS - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

- Cancelling malfunction restores normal operations.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION HYDRAULIC POWER

CHAPTER 21: HYDRAULIC POWER MALFUNCTION

: RSVR OVERHEAT # G

MALFUNCTION DESCRIPTION

:

CAUSE

: Temp switch failed (Green reservoir temp > 95degC)

CONSEQUENCE

:

- Whatever the Green Eng 1 pump P/B (40 VU) position, its “FAULT” light comes on, and remains on until overheat disappears - Whatever the PTU (AUTO) P/B (40 VU) position, its “FAULT” light comes on, and remains on until overheat disappears - If the aircraft is in flight phases 1, 2, 6, 9, 10 in normal hydraulic conditions. Then • Single chime sounds • Master caution light comes on • Associated warning message appears on the E/W CRT and SYS CRT • HYD’s page appears on the SYS CRT - When green Eng 1 pump P/B is switched off • Green system pressure decreases (except if PTU comes on) • The Eng 1 pump “FAULT” light remains on • The eng 1 pump “OFF” light comes on • The action is fed back on the E/W and SYS CRT’s - When PTU (AUTO) P/B (40 VU) is switched off • Green system pressure decreases down to 0 psi • The PTU (AUTO) P/B “FAULT” light remains on • The PTU (AUTO) P/B “OFF” light comes on

U6KSC00

• The action is fed back on the E/W and SYS CRT’s unit (HYD’s AND STATUS page) - After successive actions on “CLR” P/B (Ecam Control Panel) the STATUS page appears on the SYS CRT - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operations.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION HYDRAULIC POWER

CHAPTER 21: HYDRAULIC POWER MALFUNCTION

: RSVR OVERHEAT # B

MALFUNCTION DESCRIPTION

:

CAUSE

: Temp switch failed (blue reservoir temp > 95degC)

CONSEQUENCE

:

- Whatever the blue elec. pump P/B (40VU) position is, its “FAULT” light comes on, and remains on as long as the malfunction is active. - If the aircraft is in flight phases 1, 2, 6, 9, 10 in normal hydraulic conditions. Then: • Single chime sounds • Master caution light comes on • Associated warning message appears on the E/W CRT and SYS CRT • HYD’s page appears on the SYS CRT - When blue elec. pump P/B is switched off. • Blue elec. pump pressure decreases • Blue sys. pressure decreases (except if RAT supplies the blue sys.) • The blue elec. pump P/B “FAULT” remains on • The blue elec. pump P/B “OFF” light comes on.

U6KSC00

• The action is fed back on the E/W and SYS CRT’s (HYD’s and status pages) - After successive actions on “CLR” P/B (Ecam Control Panel) the STATUS page appears on the SYS CRT - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operations.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION HYDRAULIC POWER

CHAPTER 21: HYDRAULIC POWER MALFUNCTION

: RSVR OVERHEAT # Y

MALFUNCTION DESCRIPTION

:

CAUSE

: Temp switch failed (reservoir temp > 95degC)

CONSEQUENCE

:

- Whatever the yellow Eng 2 pump P/B (40VU) position, its “FAULT” light comes on, and remains on until OVERHEAT disappears - Whatever the PTU (AUTO) P/B (40 VU) position, its “FAULT” light comes on, and remains until overheat disappears - Whatever the yellow elec. pump P/B (40 VU) position, its “FAULT” light comes on, and remains on until OVERHEAT disappears - If the aircraft is in flight phases 1, 2, 6, 9, 10 in normal hydraulic conditions. Then • Single chime sounds • Master caution light comes on • Associated warning message appears on E/W CRT and SYS CRT • HYD’s page appears on the SYS CRT - When yellow Eng 2 pump P/B is switched off • Yellow system pressure decreases except if PTU or Elec pump comes on • The Eng 2 pump P/B “FAULT” light remains on, until overheat disappears • The eng 2 pump P/B “OFF” light comes on • The action is fed back on the E/W and SYS CRT’s UNIT (HYD’s and STATUS pages) - When PTU (AUTO) P/B is switched off • PTU is not supplied by fluid, so it is inactive • The PTU (AUTO) P/B “FAULT” light remains on, until overheat disappears • The PTU (AUTO) P/B “OFF” light comes on

U6KSC00

• The action is fed back on the E/W and SYS CRT’s unit (HYD’s and STATUS pages)

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION HYDRAULIC POWER

CHAPTER 21: HYDRAULIC POWER - When yellow elec. pump P/B is switched off • Yellow system pressure decreases to 0 psi • Yellow elec. pump P/B “FAULT” light remains on, until overheat disappears • Yellow elec. pump P/B “On” light goes off • The action is fed back on the E/W and SYS CRT’s unit (HYD’s and STATUS pages)

U6KSC00

- After successive actions on “CLR” P/B (Ecam Control Panel) the STATUS page appears on the SYS CRT - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operations.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION HYDRAULIC POWER

CHAPTER 21: HYDRAULIC POWER MALFUNCTION

: RSVR LO AIR PRESS # G

MALFUNCTION DESCRIPTION

:

CAUSE

: Air pressure in green reservoir lower than 22 psi

CONSEQUENCE

:

- If the Green Eng 1 Pump P/B is on, its “FAULT” light comes on - If the PTU (Auto) P/B is on, its “FAULT” light comes on - If the aircraft is in flight phases 1, 2, 6, 9, 10 in normal hydraulic conditions Then • Single chime sounds • Master Caution light comes on • Associated warning message appears on E/W and SYS CRT’s (29010) • HYD page appears on the SYS CRT - When Green Eng 1 Pump P/B is switched OFF • Green system pressure decreases (except if PTU comes on) • Eng 1 pump “OFF” light comes on • The Eng 1 pump “FAULT” light goes off • The action is fed back on the E/W and SYS CRT’s (HYD and status pages) (29120) - WHEN PTU (auto) P/B is switched OFF • Green system pressure decreases down to 0 psi • PTU (AUTO) “OFF” light comes on • The PTU (AUTO) “FAULT” light goes off

U6KSC00

• The action is fed back on the E/W and SYS CRT’s (HYD and status pages) (29170) - After successive actions on “CLR” P/B (Ecam Control Panel) the STATUS page appears on the SYS CRT - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling the malfunction restores normal operations.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION HYDRAULIC POWER

CHAPTER 21: HYDRAULIC POWER MALFUNCTION

: RSVR LO AIR PRESS # B 22 PSI

MALFUNCTION DESCRIPTION

:

CAUSE

: Air pressure in blue reservoir lower than 22 psi

CONSEQUENCE

:

- If Blue Elec Pump P/B (40 VU) is in normal “Auto” configuration its “FAULT” light comes on - If the aircraft is in flight phases 1, 2, 6, 9, 10 in normal hydraulic conditions Then: • Single chime sounds • Master Caution light comes on • Associated warning message appears on E/W CRT and SYS CRT • “HYD” page appears on the SYS CRT (29030) - When Blue Elec Pump P/B is switched OFF • Blue system pressure decreases (except if RAT supplies the blue sys.) • The “FAULT” light goes off • “OFF” Blue Elec Pump P/B light comes on

U6KSC00

• The action is fed back on the E/W and SYS CRT (HYD’s and status pages) (29190) - After successive actions on “CLR” P/B (Ecam Control Panel) the STATUS page appears on the SYS CRT - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling the malfunction restores normal operations

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION HYDRAULIC POWER

CHAPTER 21: HYDRAULIC POWER MALFUNCTION

: BLUE RSVR LO AIR PRESS # B 35 PSI

MALFUNCTION DESCRIPTION

:

CAUSE

: Air pressure in blue reservoir lower than 45 psi (35 psi)

CONSEQUENCE

:

- If the aircraft is in flight phases 5, 6, 7 in normal hydraulic conditions Then: • Low pressure detection memorized • No alarm appears • Alarms display after landing below 80 kts (phases 8, 9, 10) - After memorisation of this failure you can delete the failure - If the aircraft is in flight phases 1, 2, 3, 4 in normal hydraulic conditions Then: • No detection and warning - When the aircraft arrive in flight phases 8, 9, 10 (after landing/below 80 kts) Then: • Single chime sounds • Master Caution light comes on • Associated warning message appears on E/W CRT and SYS CRT • “HYD” page appears on the SYS CRT - When Blue Elec Pump P/B is switched OFF • Blue system pressure decreases (except if RAT supplies the blue sys.) • The “FAULT” light goes off “OFF” Blue Elec Pump P/B light comes on - If the failure deleted • The action is fed back on the E/W CRTand SYS CRT - When Blue Elec Pump P/B is switched ON

U6KSC00

• Blue system pressure increases until 3000 psi • Message and warning reappear on SYS CRT but not on E/W CRT

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION HYDRAULIC POWER

CHAPTER 21: HYDRAULIC POWER - It’s impossible to reset message on SYS CRT.The only solution is to lose busbar 1PP e.g. losing electrical power. - If the failure did not delete - When Blue Elec Pump P/B is switched ON • Blue system pressure increases until 3000 psi

U6KSC00

• Message and warning reappear on SYS CRT and E/W CRT - To delete message you must lose electrical power

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION HYDRAULIC POWER

CHAPTER 21: HYDRAULIC POWER MALFUNCTION

: RSVR LO AIR PRESS # Y

MALFUNCTION DESCRIPTION

:

CAUSE

: Air pressure in yellow reservoir lower than 22 psi

CONSEQUENCE

:

- If the Yellow Eng 2 Pump P/B is on, its “FAULT” light comes on - If the PTU (Auto) P/B is on, its “FAULT” light comes on - If the Yellow Elec Pump P/B is on, its “FAULT” light comes on - If the aircraft is in flight phases 1, 2, 6, 9, 10 in normal hydraulic conditions. Then • Single chime sound • Master Caution light comes on • Associated warning message appears on E/W and SYS CRT’s (29020) • HYD page appears on the SYS CRT - When Yellow Eng 2 Pump P/B is switched off • Yellow system pressure decreases except if PTU or Elec Pump comes on • The Eng 2 pump P/B “FAULT” light goes off • The Eng 2 pump “OFF” light comes on • The action is fed back on the E/W and SYS CRT’s (HYD and status pages) (29130) - When PTU (Auto) P/B is switched off • PTU is not supplied by Fluid, so it is inactivated • The PTU (Auto) P/B “FAULT” light goes off • The PTU (Auto) P/B “OFF” light comes on • The action is fed back on the E/W and SYS CRT’s (HYD and status pages) (29180) - When Yellow Elec Pump P/B is switched off • Yellow system pressure decreases down to 0 psi • Yellow Elec Pump P/B “FAULT” light goes off

U6KSC00

• Yellow Elec Pump P/B “ON” light goes off • The action is fed back on the E/W and SYS CRT’s Units (HYD and status pages) - After successive actions on “CLR” P/B (Ecam Control Panel) the STATUS page appears on the SYS CRT - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling the malfunction restores normal operations.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION HYDRAULIC POWER

CHAPTER 21: HYDRAULIC POWER MALFUNCTION

: HYD PRESS INC/DEC # G (psi)

PARAMETERS

: Green system pressure (psi)

MIN VALUE

: 0 MAX VALUE: 3600 psi CHANGE RATE: 200 psi/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Green system pressure switch and transmitter are failed

CONSEQUENCE

:

- Pressure indicated on the HYD page (SYS CRT) and low pressure detected by the switch (system) are according to the value generated by the indicator. - But the real system pressure is not changed and the system working is correct, so no physical consequences but only warning consequences. NOTE: The system pressure value is constantly refreshed on the HYD page and to the ELAC (elevator and aileron computer) - The system pressure warnings don’t affect any “FAULT” light - When pressure decreases and goes down below 1450 psi • If Eng 1 running and aircraft is in flight phases 1, 2, 3, 6, 9, 10 Then • Single chime sounds • Master caution light comes on • Associated warning message appears on E/W CRT (29170) • HYD page appears on the SYS CRT - When pressure increases up to 1750 psi the next sequence is erased. EXTERNAL CONSEQUENCES: When green system pressure decreases, if active, following hydraulic users are affected:

U6KSC00

• YAW DAMPER, PITCH TRIM, ENGINE 1 REVERSE, SPOILER 1, RUDDER, ELEVATOR, AILERONS, SPOILER 5, NORMAL BRAKES • NOSE WHEEL STEERING, LANDING GEARS, SLATS, FLAPS - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operations.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION HYDRAULIC POWER

CHAPTER 21: HYDRAULIC POWER MALFUNCTION

: HYD PRESS INC/DEC # B (psi)

PARAMETERS

: Blue system pressure (psi)

MIN VALUE

: 0 psi MAX VALUE: 3600 psi CHANGE RATE: 200 psi/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Blue elec. pump regulation failed

CONSEQUENCE

:

Blue elec. pump pressure value varies according to the pressure selected by the instructor. - When blue elec. pump pressure decreases and reaches 1450 psi • In flight or on ground with one engine running if the blue elec pump P/B (40 VU) is in normal auto configuration its “FAULT” light comes on. • On ground with both engines stopped and with blue pump OVRD P/B (50 VU) in ON position and the blue elec. • pump P/B (40 VU) in normal “AUTO” configuration, then the same “FAULT” light comes on. • If the aircraft is in flight phases 2, 3, 6, 9 and the AC BUS supplying the blue elec. pump is on. Then • Single chime sounds • Master caution light comes on • Associated warning message appears on the E/W CRT (29140, 29190) • HYD’s page appears on the SYS CRT - When blue elec. pump P/B is switched OFF • The blue elec. pump P/B “FAULT” light goes off • The blue elec. pump P/B “OFF” light comes on • The blue elec. pump shuts down • On HYD’s page, blue system pressure decreases down to blue tank pressure (except if RAT supplies the blue system)

U6KSC00

- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operations.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION HYDRAULIC POWER

CHAPTER 21: HYDRAULIC POWER MALFUNCTION

: HYD PRESS INC/DEC # Y (psi)

PARAMETERS

: Yellow system pressure (psi)

MIN VALUE

: 0 psi MAX VALUE: 3600 psi CHANGE RATE: 200 psi/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Yellow system pressure switch and transmitter are failed

CONSEQUENCE

:

- Pressure indicated on the HYD’s page (SYS CRT) and low pressure detected by the switch (system) are according to the value generated by the instructor. - But the real system pressure is not changed and the system working is correct, so no physical but only warning consequences. NOTE: The system pressure value is constantly refreshed on the HYD page and to the ELAC (elevator and aileron computer) - The system pressure warnings don’t affect any “FAULT” light - When pressure decreases and goes down below 1450 psi • If Eng 2 is running and aircraft is in flight phases 1, 2, 3, 6, 9, 10 Then • Single chime sounds • Master caution light comes on • Associated warning message appears on E/W CRT (29130,29180) • HYD page appears on the SYS CRT - When pressure increases up to 1750 psi the next sequence is erased. EXTERNAL CONSEQUENCES: When yellow system pressure decreases, if active, following hydraulic users are affected • YAW DAMPER, PITCH TRIM, ENGINE 2 REVERSE , SPOILER 2, RUDDER, ELEVATOR, U6KSC00

• SPOILER 4 • FLAPS - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operations.

DATE: SEP 1998

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CHAPTER 21: HYDRAULIC POWER MALFUNCTION

: ELEC PUMP FAIL # B

MALFUNCTION DESCRIPTION

:

CAUSE

: The three-phases AC bus control unit is failed, and deenergizes the blue elec. pump actuator relay.

CONSEQUENCE

:

- Blue elec. pump goes off, and its pressure decreases down to 0 psi - Blue system pressure decreases except if RAT is extended and running - If pump pressure goes below 1450 psi • On ground with one engine running or in flight if the blue elec. pump P/B (40 VU) is in normal AUTO configuration its “FAULT” light comes on. • On ground with both of the engines stopped and with blue pump OVRD P/B (50 VU) in ON position and the blue elec. pump P/B (40 VU) in normal “AUTO” configuration. Then the same “FAULT” light comes on. • If the aircraft is in flight phases 2, 3, 6, 9 in normal hydraulic conditions. Then • Single chime sounds • Master caution light comes on • Associated warning message appears on the E/W CRT (29140) • HYD’s page appears on the SYS CRT - When blue elec. pump P/B is switched off • The blue elec. pump P/B “FAULT” light goes off • The blue elec. pump P/B “OFF” light comes on • The action is fed back on the E/W and SYS CRT’s - If blue system pressure goes below 1450 psi with one engine running (on ground) in flight phases 1, 2, 3, 6, 9, 10 • Single chime sounds • Master caution light comes on • Associated warning message appears on the E/W CRT (29190)

U6KSC00

• HYD’s page appears on the SYS CRT - After successive actions on the “CLR” (Ecam Control Panel) the STATUS page appears on the SYS CRT - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION HYDRAULIC POWER

CHAPTER 21: HYDRAULIC POWER MALFUNCTION

: ELEC PUMP FAIL # Y

MALFUNCTION DESCRIPTION

:

CAUSE

: The three phases AC bus control unit is failed and deenergizes the yellow elec. pump actuator relay.

CONSEQUENCE

:

- Yellow elec. pump remains ON - Yellow system pressure decreases, except if PTU transfers the green hydraulic power or yellow engine pump is operating - If decreasing, yellow system pressure goes down 1450 psi - With eng 2 running, in flight phases 1, 2, 3, 6, 9, 10 Then • Single chime sounds • Master caution light comes on • Associated warning message appears on E/W CRT (29180) • HYD’s page appears on the SYS CRT • With yellow elec. pump ’ON’ light on • Yellow elec. pump “FAULT” light comes on

U6KSC00

- After successive actions on “CLR” P/B (Ecam Control Panel) the STATUS page appears on the SYS CRT - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION HYDRAULIC POWER

CHAPTER 21: HYDRAULIC POWER MALFUNCTION

: PUMP FAIL #G

MALFUNCTION DESCRIPTION

:

CAUSE

: Pump stuck

CONSEQUENCE

:

- Green system pressure decreases, and increases when PTU comes active. - When decreasing ENG 1 pump pressure goes below 1750 psi • In flight or on ground with engine 1 running, green ENG 1 PUMP P/B (40VU) “FAULT” light comes on • If ENG 1 RUNNING, in flight phases 1, 2, 3, 6, 9, 10 Then • Single chime sounds • Master caution light comes on • Associated warning message appears on E/W CRT (29120) • HYD’s page appears on the SYS CRT - If green system pressure decreases ang goes below 1450 psi and Eng 1 running - In flight phases 1, 2, 3, 6, 9, 10 Then • Single chime sounds • Master caution light comes on • Associated warning message appears on E/W CRT (29170) • HYD’s page appears on the SYS CRT REM: • If PTU be comes active then pressure increases • If green pressure increasing reaches 1750 psi, then these warnings disappear. - When Green Eng 1 pump P/B (40 VU) is switched off • Its “FAULT” light disappears

U6KSC00

• Its “OFF” light comes on - After successive actions on “CLR” P/B (Ecam Control Panel) the STATUS page appears on the SYS CRT - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maitenance option selected). - Cancelling malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION HYDRAULIC POWER

CHAPTER 21: HYDRAULIC POWER MALFUNCTION

: PTU FAIL #Y

MALFUNCTION DESCRIPTION

:

CAUSE

: One PTU cylinder is stuck

CONSEQUENCE

:

- If PTU is inhibited (aircraft on ground and parking brake on and engine master levers 1 and 2 not in same positions): • no consequences • on HYD page, PTU is not armed - If green and yellow systems are in normal hydraulic conditions, and PTU is not inhibited: • no consequences • on HYD page, PTU is armed - If pressure difference between yellow and green system goes above 500 psi, PTU doesn’t pressurise the low system (PTU not inhibited). • On HYD page, PTU is shown active if the low system has a pressure greater than 1450 psi, else PTU is shown armed. - If green and yellow systems pressure difference goes above 650 psi, only one engine is running, park brake on, ENG’s PUMPS P/B on, PTU (auto) P/B on and aircraft in flight phases 1, 2 Start the second engine, then check that: • Single chime sounds • Master caution light comes on • Associated warning message appears on E/W CRT (29230) • HYD’s page appears on the SYS CRT In order to reset these warnings, check that yellow elec pump is off and the two engines master levers are off, and change one of these conditions.

U6KSC00

- After successive actions on “CLR” P/B (Ecam Control Panel), the STATUS page appears on the SYS CRT - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operations

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION HYDRAULIC POWER

CHAPTER 21: HYDRAULIC POWER MALFUNCTION

: RAT PUMP FAIL #B

MALFUNCTION DESCRIPTION

:

CAUSE

: Rat pump is broken

CONSEQUENCE

:

Rat pump is extended, locked and running with A/C speed greater than 146 Kts - If blue elec. pump is off: • RAT pump and blue system pressure decrease down to 0 psi If blue system pressure goes below 1450 psi and one engine running (on ground) In flight phases 1, 2, 3, 6, 9, 10 • Single chime sounds • Master caution light comes on • Associated warning message appears on the E/W CRT (29190)

U6KSC00

• HYD’s page appears on the SYS CRT - After successive actions on “CLR” P/B (Ecam Control Panel) the STATUS page appears on the SYS CRT - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling malfunction restores normal operations.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION HYDRAULIC POWER

CHAPTER 21: HYDRAULIC POWER MALFUNCTION

: RAT NO AUTOMATIC EXTENSION #B

MALFUNCTION DESCRIPTION

:

CAUSE

: Rat deployement solenoid 1 failed

CONSEQUENCE

:

RAT can only be extended by electrical deployment system

U6KSC00

- Cancelling malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONSINSTRUMENTS DESCRIPTION

CHAPTER 22 - INSTRUMENTS CONTENTS: STAND BY ASI FAIL STAND BY HORIZON FAIL STAND BY ALTI FAIL VOR/DME RMI FAIL ADF RMI FAIL

U6KSC00

PRINTER FAIL

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONSINSTRUMENTS DESCRIPTION

CHAPTER 22: INSTRUMENTS MALFUNCTION

: STAND BY ASI FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Mechanical failure

CONSEQUENCE

:

• The airspeed indication is frozen on stand by air speed indicator ACTION: NIL

U6KSC00

- Cancelling the malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONSINSTRUMENTS DESCRIPTION

CHAPTER 22: INSTRUMENTS MALFUNCTION

: STAND BY HORIZON FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Power loss

CONSEQUENCE

:

- Red flag on the stand by horizon. - During 5 minutes, all the indications are normal. - After 5 minutes, roll and pitch drift slowly but follow the evolutions of the aircraft. - Roll and pitch indications are fixed 10 minutes after inserting the malfunction.

U6KSC00

Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONSINSTRUMENTS DESCRIPTION

CHAPTER 22: INSTRUMENTS MALFUNCTION

: STAND BY ALTI FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Mechanical failure

CONSEQUENCE

:

• The altitude indication is frozen on stand by altimeter. ACTION: NIL

U6KSC00

- Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONSINSTRUMENTS DESCRIPTION

CHAPTER 22: INSTRUMENTS MALFUNCTION

: VOR/DME RMI FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: VOR/DME RMI power supply failure

CONSEQUENCE

:

On VOR/DME RMI: -

Heading flag appears VOR 1 and VOR 2 flag appears Heading information remains fixed VOR 1 and VOR 2 bearing needles remain fixed DME 1 and DME 2 distances disappear from windows.

U6KSC00

ACTION: NIL - Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONSINSTRUMENTS DESCRIPTION

CHAPTER 22: INSTRUMENTS MALFUNCTION

: ADF RMI FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: ADF RMI power supply failure

CONSEQUENCE

:

On RMI ADF: -

Heading flag appears ADF 1 and ADF 2 flags appear Heading information remains fixed ADF 1 and ADF 2 bearing needles remain fixed.

ACTION: NIL

U6KSC00

- Cancelling the malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONSINSTRUMENTS DESCRIPTION

CHAPTER 22: INSTRUMENTS MALFUNCTION

: PRINTER FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Printer power failure

CONSEQUENCE

:

- The printer is inactive. If a document was just being printed, the listing operating stops.

U6KSC00

- The printer pushbutton control (SLEW) is not illuminated and is inactive. - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling the malfunction restores normal operation, after 30 seconds of printer initialization. But, if a document was just being printed, before the malfunction, the listing is lost.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONSINSTRUMENTS DESCRIPTION

U6KSC00

THIS PAGE INTENTIONALLY LEFT BLANK

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION LANDING GEAR

CHAPTER 23 - LANDING GEAR CONTENTS: LEFT L/G NOT DOWN LOCKED RIGHT L/G NOT DOWN LOCKED NOSE L/G DEFINITIVELY RETRACTED RIGHT L/G DEFINITIVELY RETRACTED L/G DEFINITIVELY RETRACTED L/G LEVER LOCKED NOSE L/G NOT UP LOCKED L/G SYSTEMS FAULT (LGCIU 1 + 2) L/G SYSTEM 1 FAULT (LGCI 1) LEFT L/G MAIN DOOR STAYS OPEN L/G PANEL INDICATOR FAIL ABNORMAL VIBRATION FROM NOSE L/G (DOWN) CAPT NOSE WHEEL STEERING FAIL

U6KSC00

RUDDER STEERING FAIL

DATE: SEP 1998

Page Page333 1

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A320 SIMULATED MALFUNCTIONS DESCRIPTION LANDING GEAR

CHAPTER 23: LANDING GEAR MALFUNCTION

: LEFT L/G NOT DOWN LOCKED

MALFUNCTION DESCRIPTION

:

CAUSE

: LH gear does not lock in down position LH gear down lock inoperative Nota: Malfunction is active only when set before L/G is locked down

CONSEQUENCE

:

- During gear extension sequence, the LH gear red light remains illuminated and the LH gear green light does not illuminate. All doors remain open. - The WHEEL page with amber doors and the red arrow on LH gear appears on the ECAM lower D.U. - If gravity extension is performed, the LH gear red light goes out, the LH gear green light illuminates, otherwise LH gear retract at landing.

U6KSC00

- ECAM warning and messages are conformed to ’32245’ referenced primary failure. - Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION LANDING GEAR

CHAPTER 23: LANDING GEAR MALFUNCTION

: RIGHT L/G NOT DOWN LOCKED

MALFUNCTION DESCRIPTION

:

CAUSE

: RH gear does not lock in down position RH gear down lock inoperative Nota: malfunction is active only when set before L/G is locked down

CONSEQUENCE

:

- During gear extension sequence, the RH gear red light remains illuminated and, the RH gear green light does not illuminate. All doors remain open. - The WHEEL page with amber doors and the red arrow on RH gear appears on the ECAM lower D.U. - If gravity extension is performed, the RH gear red light goes out, the RH gear green light illuminates, otherwise RH gear retract at landing.

U6KSC00

- ECAM warning and messages are conformed to ’32245’ referenced primary failure. - Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION LANDING GEAR

CHAPTER 23: LANDING GEAR MALFUNCTION

: NOSE L/G DEFINITIVELY RETRACTED

MALFUNCTION DESCRIPTION

:

CAUSE

: Gear actuator does not operate: mechanically stuck gear locking actuator Nota: Malfunction is active only when set before L/G unlocked in UP position

CONSEQUENCE

:

The nose gear does not extend in normal or in emergency mode. All doors remain open. During extension operation the nose gear red light remains illuminated and the green light remains out. The WHEEL page with amber doors and red arrow on nose gear appears on the ECAM lower D.U. ECAM warning and messages are conformed to ’32245’ referenced primary failure. Cancelling the malfunction restores normal operation.

U6KSC00

-

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION LANDING GEAR

CHAPTER 23: LANDING GEAR MALFUNCTION

: RIGHT L/G DEFINITIVELY RETRACTED

MALFUNCTION DESCRIPTION

:

CAUSE

: Gear actuator does not operate: mechanically stuck gear locking actuator Nota: Malfunction is active only when set before L/G unlocked in UP position

CONSEQUENCE

:

The RH gear does not extend in normal or in emergency mode. All doors remain open. During extension operation the RH gear red light remains illuminated and the green light remains out. The WHEEL page with amber doors and red arrow on RH gear appears on the ECAM lower D.U. ECAM warning and messages are conformed to ’32245’ referenced primary failure. Cancelling the malfunction restores normal operation.

U6KSC00

-

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION LANDING GEAR

CHAPTER 23: LANDING GEAR MALFUNCTION

: L/G DEFINITIVELY RETRACTED

MALFUNCTION DESCRIPTION

:

CAUSE

: The 3 gear actuators do not operate: Mechanically stuck gear locking actuators Nota: Malfunction is active when set before L/G unlocked in UP position

CONSEQUENCE

:

The LG gear does not extend in normal or in emergency mode. All doors remain open. During operation the 3 red lights remain illuminated and the 3 green lights remain out. The WHEEL page with amber doors and red arrows on each gear appears on the ECAM lower D.U. ECAM warning and messages are conformed to ’32245’ referenced primary failure. Cancelling the malfunction restores normal operation.

U6KSC00

-

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION LANDING GEAR

CHAPTER 23: LANDING GEAR MALFUNCTION

: L/G LEVER LOCKED

MALFUNCTION DESCRIPTION

:

CAUSE

: Internal interlock prevents to set landing gear lever to up position, on system 1 and 2.

CONSEQUENCE

:

U6KSC00

- L/G cannot be retracted. - Motion vibrations will increase rapidly above 240 knots. - Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION LANDING GEAR

CHAPTER 23: LANDING GEAR MALFUNCTION

: NOSE L/G NOT UP LOCKED

MALFUNCTION DESCRIPTION

:

CAUSE

: Nose L/G does not lock in up position, Nose L/G up lock inoperative Nota: Malfunction is active only when set before L/G is locked up

CONSEQUENCE

:

During gear retraction sequence, the Nose gear red light remains illuminated, all doors remain open. Motion vibrations increase rapidly above 250 knots. The WHEEL page with amber doors and the red arrow on nose gear appears on the ECAM lower D.U. ECAM warning and messages are conformed to ’32235’ referenced independent failure. Cancelling the malfunction restores normal operation.

U6KSC00

-

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION LANDING GEAR

CHAPTER 23: LANDING GEAR MALFUNCTION

: L/G SYSTEMS FAULT (LGCIU 1 + 2)

MALFUNCTION DESCRIPTION

:

CAUSE

: Failure of both LGCIU

CONSEQUENCE

:

- The L/G selector lever is inoperative and locked if in down position.

U6KSC00

- It is impossible to use landing gear by selector lever, gravity extension is only possible but without any indicator light. - ECAM WHEEL page information: All gears and doors indicators are amber crosses. - ECAM warning and messages are conformed to ’32450’ and ’32460’ referenced independent failures. - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION LANDING GEAR

CHAPTER 23: LANDING GEAR MALFUNCTION

: L/G SYSTEM 1 FAULT (LGCIU 1)

MALFUNCTION DESCRIPTION

:

CAUSE

: Failure of LGCIU1

CONSEQUENCE

:

- The L/G indicator lights remain off, whatever is the state of the landing gear. -

LGCIU2 keeps or takes the control of landing gear operation. ECAM WHEEL page information: All gears indicators from system 1 are amber crosses. ECAM warning and messages are conformed to ’32450’ referenced independent failure. Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

- Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION LANDING GEAR

CHAPTER 23: LANDING GEAR MALFUNCTION

: LEFT L/G MAIN DOOR STAYS OPEN

MALFUNCTION DESCRIPTION

:

CAUSE

: LH door actuator jams in open position (during retraction or extension)

CONSEQUENCE

:

Motion vibrations will rapidly increase above 240 knots. The WHEEL page with LH amber door appears on the ECAM lower D.U. ECAM warning and messages are conformed to ’32210’ referenced independent failure. Cancelling the malfunction restores normal operation.

U6KSC00

-

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION LANDING GEAR

CHAPTER 23: LANDING GEAR MALFUNCTION

: L/G PANEL INDICATOR FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Circuit breaker 1GA trips

CONSEQUENCE

:

U6KSC00

- The indicator lights and the control lever down arrow light remain off, whatever is the state of the landing gear. The light test remains operative.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION LANDING GEAR

CHAPTER 23: LANDING GEAR MALFUNCTION

: ABNORMAL VIBRATION FROM NOSE L/G (DOWN)

MALFUNCTION DESCRIPTION

:

CAUSE

: Tire retread of nose L/G unsticks

CONSEQUENCE

:

U6KSC00

- Vibration of the cabin during taxi-ing (motion, visual effect on visual according to approved data). - With A/C speed increasing, vibrations disappear 15s after nose wheel lift off. - Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION LANDING GEAR

CHAPTER 23: LANDING GEAR MALFUNCTION

: CAPT NOSE WHEEL STEERING FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Failure coming from the signal in the BSCU

CONSEQUENCE

:

- It is impossible to use nose wheel steering function by the captain’s nose wheel tiller. - ECAM warning and messages are conformed to ’32070’ referenced independent failure if only one BSCU system is valid. - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected) if nose wheel steering arming conditions are available when malfunction occurs.

U6KSC00

- Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION LANDING GEAR

CHAPTER 23: LANDING GEAR MALFUNCTION

: RUDDER STEERING FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: The order coming from the pedals fails before coming in the BSCU

CONSEQUENCE

:

U6KSC00

- It is impossible to use nose wheel steering function by the pedals. - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION LANDING GEAR

U6KSC00

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DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION PITCH CONTROL

CHAPTER 24 - PITCH CONTROL CONTENTS: CAPT SIDE STICK PITCH FAIL F/O SIDE STICK PITCH FAIL CAPT SIDE STICK INOP F/O SIDE STICK INOP ERRONEOUS CAPT PITCH UP ORDER ERRONEOUS F/O PITCH UP ORDER ERRONEOUS CAPT PITCH DOWN ORDER ERRONEOUS F/O PITCH DOWN ORDER PITCH TRIM RWY UP (FAST) PITCH TRIM RWY DOWN (SLOW) STABILIZER JAM SLATS/FLAPS HANDLE INOP SLATS STUCK BY TIP BRAKE FLAPS STUCK BY TIP BRAKE STAB YELLOW SERVO JAM LEFT ELEVATOR GREEN SERVO JAM LEFT ELEVATOR BLOCKED RIGHT ELEVATOR BLOCKED FLAPS & SLATS POS NCD SLATS FAULT FLAPS FAULT THS MOTOR 1 FAIL THS MOTOR 2 FAIL

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THS MOTOR 3 FAIL

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION PITCH CONTROL

CHAPTER 24: PITCH CONTROL MALFUNCTION

: CAPT SIDE STICK PITCH FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Failure in the transducer box used for Pitch Control (Potentiometers associated to ELACS and SECs)

CONSEQUENCE

:

1) The CAPT side-stick pitch order remains frozen. 2) No message on the ENGINES WARNINGS display.

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3) Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION PITCH CONTROL

CHAPTER 24: PITCH CONTROL MALFUNCTION

: F/O SIDE STICK PITCH FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Failure in the transducer box used for Pitch Control (Potentiometers associated to ELACS and SECs)

CONSEQUENCE

:

1) The F/O side-stick pitch order remains frozen. 2) No message on the ENGINES WARNINGS display.

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3) Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION PITCH CONTROL

CHAPTER 24: PITCH CONTROL MALFUNCTION

: CAPT SIDE STICK INOP

MALFUNCTION DESCRIPTION

:

CAUSE

: CAPT side stick wiring is disconnected (pitch and roll axis)

CONSEQUENCE

:

1) CAPT side stick pitch and roll orders remain frozen 2) If flight phase 1, 2, 3, 6, 9, 10: • Single chime sounds • Amber master caution light comes on • Appropriate messages appear on the Engines Warning Display (see sheets FWC A27198, A25795, A27200, A27210) 3) On PFD: Green symbols ’=’ are replaced by ’x’ amber symbols 4) On the SYSTEM PAGES CRT: F/CTL page: LAF DEGRADED appears STATUS page: - Appropriate messages appear (see sheets FWC A27817, A27819, A27821, A27823, A27825, A27645, A27640, A27815) 5) Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

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6) Cancelling the malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION PITCH CONTROL

CHAPTER 24: PITCH CONTROL MALFUNCTION

: F/O SIDE STICK INOP

MALFUNCTION DESCRIPTION

:

CAUSE

: F/O side stick wiring is disconnected (pitch and roll axis)

CONSEQUENCE

:

1) F/O side stick pitch and roll order remain frozen 2) If flight phase 1, 2, 3, 6, 9, 10: • Single chime sounds • Amber master caution light comes on • Appropriate messages appear on the Engines Warning Display (see sheets FWC A27197,A27595,A27200,A27210) 3) On PFD: Green symbols ’=’ are replaced by ’x’ amber symbols 4) On the SYSTEM PAGES CRT: F/CTL page: LAF DEGRADED appears STATUS page: - Appropriate messages appear (see sheets FWC A27817, A27819, A27821, A27823, A27825, A27645, A27640, A27815) 5) Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

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6) Cancelling the malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION PITCH CONTROL

CHAPTER 24: PITCH CONTROL MALFUNCTION

: ERRONEOUS CAPT PITCH UP ORDER

MALFUNCTION DESCRIPTION

:

CAUSE

: Erroneous potentiometers order in Pitch to ELACs and SECs

CONSEQUENCE

:

1) The CAPT side stick Pitch order is blocked to up deflection 2) No message on the ENGINES WARNINGS display.

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3) Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION PITCH CONTROL

CHAPTER 24: PITCH CONTROL MALFUNCTION

: ERRONEOUS F/O PITCH UP ORDER

MALFUNCTION DESCRIPTION

:

CAUSE

: Erroneous potentiometers order in Pitch to ELACs and SECs

CONSEQUENCE

:

1) The F/O side stick Pitch order is blocked to up deflection. 2) No message on the ENGINES WARNINGS display.

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3) Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION PITCH CONTROL

CHAPTER 24: PITCH CONTROL MALFUNCTION

: ERRONEOUS CAPT PITCH DOWN ORDER

MALFUNCTION DESCRIPTION

:

CAUSE

: Erroneous potentiometers order in Pitch to ELACs and SECs

CONSEQUENCE

:

1) The CAPT side stick Pitch order is blocked to down deflection. 2) No message on the ENGINES WARNINGS display.

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3) Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION PITCH CONTROL

CHAPTER 24: PITCH CONTROL MALFUNCTION

: ERRONEOUS F/O PITCH DOWN ORDER

MALFUNCTION DESCRIPTION

:

CAUSE

: Erroneous potentiometers order in Pitch to ELACs and SECs

CONSEQUENCE

:

1) The F/O side stick Pitch order is blocked to down deflection. 2) No message on the ENGINES WARNINGS display.

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3) Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION PITCH CONTROL

CHAPTER 24: PITCH CONTROL MALFUNCTION

: PITCH TRIM RWY UP (FAST)

MALFUNCTION DESCRIPTION

:

CAUSE

: THS RUNAWAY UP

CONSEQUENCE

:

1) THS and control wheel runway up at speed of 0.225deg/s 2) ELAC 2, then ELAC 1 then SEC2 detect the runaway and stop the THS. If flight phase 1, 2, 6, 9, 10: • Single chime sounds • Amber master caution light comes on Appropriate messages appear on the Engines Warning Display (see sheets FWC A27550,A27540 for a short time, replaced after by sheets FWC A27480, A27595) On the PFD, the pitch and roll attitude limit green lines change to amber crosses 3) On the SYSTEM PAGES CRT: F/ CTL page: PITCH TRIM message amber STATUS page: - Appropriate messages appear (see sheets FWC A27817, A27819, A27821, A27823, A27825, A27815) 4) Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

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5) Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION PITCH CONTROL

CHAPTER 24: PITCH CONTROL MALFUNCTION

: PITCH TRIM RWY DOWN (SLOW)

MALFUNCTION DESCRIPTION

:

CAUSE

: THS RUNAWAY DOWN

CONSEQUENCE

:

1) THS and control wheel runaway down at speed of 0.1125deg/s 2) ELAC 2, then ELAC 1, then SEC 2 detect the runaway and stop the THS. If flight phase 1, 2, 6, 9, 10: • Single chime sounds • Amber master caution light comes on Appropriate messages appear on the Engines Warning Display (see sheets FWC A27550, A27540 for a short time, replaced after by sheets FWC A27480, A27595) On the PFD, the pitch and roll attitude limit green lines change to amber crosses 3) On the SYSTEM PAGES CRT: F/CTL page: PITCH TRIM message amber STATUS page: - Appropriate messages appear (see sheets FWC A27817, A27819, A27821, A27823, A27825, A27815) 4) Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

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5) Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION PITCH CONTROL

CHAPTER 24: PITCH CONTROL MALFUNCTION

: STABILIZER JAM

MALFUNCTION DESCRIPTION

:

CAUSE

: THS screw jack blocked

CONSEQUENCE

:

1) THS remains blocked THS is no more controlled by ELAC 2, ELAC 1, SEC 1, SEC 2 computers Manual trim wheel is blocked 2) After a large pitch demand, using side stick: If flight phase 1, 2, 6, 9, 10: • Single chime sounds • Amber master caution light comes on • Appropriate messages appear on the Engines Warning Display (see sheets FWC A27550, A27540, A27595) • 15 seconds after, A27480 message replace A27550 and A27540 messages On the PFD, the pitch and roll attitude limit green lines change to amber crosses 3) On the SYSTEM PAGES CRT: F/CTL page: PITCH TRIM amber STATUS page: - Appropriate messages appear (see sheets FWC A27817, A27819, A27821, A27823, A27825, A27815) 4) Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

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5) Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION PITCH CONTROL

CHAPTER 24: PITCH CONTROL MALFUNCTION

: SLATS/FLAPS HANDLE INOP

MALFUNCTION DESCRIPTION

:

CAUSE

: Slat/flap handle order fails before coming to the SFCCs (failure of the transducer box)

CONSEQUENCE

:

1) It is impossible to move slats and flaps, they remain frozen in position 2) If flight phase 1, 2, 3, 6, 7, 9, 10: • Single chime sounds • Amber master caution light comes on • Appropriate messages appear on the engines Warning Display (see sheets FWC A27050, A27060) 3) On the ECAM upper display: • S FLAP F indications become amber • Actual positions become amber 4) On the SYSTEM PAGES CRT: STATUS page: - Appropriate messages appear (see sheets FWC A27140, A27130) 5) Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). When CFDS is operating in MENU mode and BITE TSD (Trouble Shooting Data) function is selected, the snapshot data corresponding to malfunction are displayed on the MCDU. (when BITE TSD maintenance option selected).

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6) Cancelling the malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION PITCH CONTROL

CHAPTER 24: PITCH CONTROL MALFUNCTION

: SLATS STUCK BY TIP BRAKE

MALFUNCTION DESCRIPTION

:

CAUSE

: The SFCCs detect asymmetric slats movement after control handle order

CONSEQUENCE

:

1) Slats are blocked immediately after control handle order 2) If flight phase 1, 2, 3, 6, 7, 9, 10: • Single chime sounds • Amber master caution light comes on • Appropriate message appears on the Engines Warning Display (see sheet FWC A27070) 3) On the ECAM upper display: • S FLAP indications become amber • S LOCKED amber message appears • Actual position becomes amber 4) On the SYSTEM PAGES CRT: STATUS page: - Appropriate message appears (see sheet FWC A27130) 5) Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

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6) Cancelling the malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION PITCH CONTROL

CHAPTER 24: PITCH CONTROL MALFUNCTION

: FLAPS STUCK BY TIP BRAKE

MALFUNCTION DESCRIPTION

:

CAUSE

: The SFCCs detect asymmetric flaps movement after control handle order

CONSEQUENCE

:

1) Flaps are blocked immediately after control handle order 2) If flight phase 1, 2, 3, 6, 7, 9, 10: • Single chime sounds • Amber master caution light comes on • Appropriate message appears on the Engines Warning Display (see sheet FWC A27080) 3) On the ECAM upper display • FLAP F indications become amber • F LOCKED amber message appears • Actual position becomes amber 4) On the SYSTEM PAGES CRT: STATUS page: - Appropriate message appears (see sheet FWC A27140) 5) Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). When CFDS is operating in MENU mode and BITE TSD (Trouble Shooting Data) function is selected, the snapshot data corresponding to malfunction are displayed on the MCDU. (when BITE TSD maintenance option selected)

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6) Cancelling the malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION PITCH CONTROL

CHAPTER 24: PITCH CONTROL MALFUNCTION

: STAB YELLOW SERVO JAM

MALFUNCTION DESCRIPTION

:

CAUSE

: Jamming of the THS yellow hydraulic motor control valve in neutral position

CONSEQUENCE

:

1) THS is no more controlled by ELAC 2, ELAC 1, SEC 1, SEC 2 computers 2) After a large pitch demand, using side stick: • If flight phase 1, 2, 6, 9, 10: • Single chime sounds • Amber master caution light comes on • Appropriate messages appear on the Engines Warning Display (see sheets FWC A27550,A27540,A27595) • 15 seconds after, A27480 message replace A27550 and A27540 messages On the PFD, the pitch and roll attitude limit green lines change to ambe crosses 3) On the SYSTEM PAGES CRT: F/CTL page: PITCH TRIM amber STATUS page: - Appropriate messages appear (see sheets FWC A27817, A27819, A27821, A27823, A27825, A27815) 4) Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

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5) Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION PITCH CONTROL

CHAPTER 24: PITCH CONTROL MALFUNCTION

: LEFT ELEVATOR GREEN SERVO JAM

MALFUNCTION DESCRIPTION

:

CAUSE

: Jamming of a slide in the left elevator servo fed by the green hydraulic circuit.

CONSEQUENCE

:

1) According to the flight phase: If flight phase 1, 2, 6, 7, 8, 9, 10: • Appropriate messages appear on the Engines Warning Display (see sheet FWC A27430) 2) Control laws remain normal 3) On the SYSTEM PAGES CRT: F/CTL page: G.L ELEV ! becomes amber boxed 4) Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

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5) Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION PITCH CONTROL

CHAPTER 24: PITCH CONTROL MALFUNCTION

: LEFT ELEVATOR BLOCKED

MALFUNCTION DESCRIPTION

:

CAUSE

: Jamming of left elevator.

CONSEQUENCE

:

1) The left elevator remains blocked in position and can’t be actionned by side sticks or by FMGCs orders. 2) After a large pitch demand, using side stick If flight phase 1, 2, 3, 6, 7, 8, 9, 10: • Single chime sounds • Amber master caution light comes on • Appropriate messages appear on the Engines Warning Display (see sheet FWC A27540,A27550,A27595) On the PFD, the pitch and roll altitude limit green line change to amber crosses 3) After another large pitch demand, using side stick • Appropriate messages appear on the Engines Warning Display (see sheet FWC A27380) 4) On the SYSTEM PAGES CRT: F/CTL page: B.L ELEV! becomes amber boxed G.L ELEV! Left ELEV index becomes amber STATUS page: - Appropriate messages appear (see sheets FWC A27817, A27819, A27821, A27823, A27825, A27730, A27815) 5) Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

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6) Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION PITCH CONTROL

CHAPTER 24: PITCH CONTROL MALFUNCTION

: RIGHT ELEVATOR BLOCKED

MALFUNCTION DESCRIPTION

:

CAUSE

: Jamming of right elevator

CONSEQUENCE

:

1) The right elevator remains blocked in position and can’t be actionned by side sticks or by FMGCs orders? 2) After a large pitch demand, using side stick If flight phase 1, 2, 3, 6, 7, 8, 9, 10: • Single chime sounds • Amber master caution light comes on • Appropriate messages appear on the Engines Warning Display (see sheet FWC A27540, A27550, A27595) On the PFD, the pitch and roll attitude limit green lines change to amber crosses 3) After a other large pitch demand, using side stick • Appropriate messages appear on the Engines Warning Display (see sheet FWC A27390) 4) On the SYSTEM PAGES CRT: F/CTL page: Y.R ELEV! becomes amber boxed B.R ELEV! Right ELEV index becomes amber STATUS page: • Appropriate messages appear (see sheets FWC A27817, A27819, A27821, A27823, A27825, A27831, A27815) 5) Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

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6) Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION PITCH CONTROL

CHAPTER 24: PITCH CONTROL MALFUNCTION

: FLAPS & SLATS POS NCD

MALFUNCTION DESCRIPTION

:

CAUSE

: Loss of power supply to IPPUs

CONSEQUENCE

:

1) The slats and flaps are still operating normally - but the position informations are no more received by the FWC. 2) Slat/flap positions are no more displayed on the ECAM upper display

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3) Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION PITCH CONTROL

CHAPTER 24: PITCH CONTROL MALFUNCTION

: SLATS FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: Failure of the slats channel in the SFCC 1

CONSEQUENCE

:

1) The slats speed is half the nominal speed. 2) If flight phase 1, 2, 6, 9, 10: • No aural warning • No master caution light • Appropriate message appears on the Engines Warning display (see sheet FWC A27030) 3) On the SYSTEM PAGES CRT: STATUS page: - Appropriate message appears (see sheet FWC A27120) 4) Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). When CFDS is operating in MENU mode and BITE TSD (Trouble Shooting Data) function is selected, the snapshot data corresponding to malfunction are displayed on the MCDU.(when BITE TSD maintenance option selected)

U6KSC00

5) Cancelling the malfunction restores normal operation

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION PITCH CONTROL

CHAPTER 24: PITCH CONTROL MALFUNCTION

: FLAPS FAULT

MALFUNCTION DESCRIPTION

:

CAUSE

: Failure of the flaps channel in the SFCC 2

CONSEQUENCE

:

1) The flaps speed is half the nominal speed 2) If flight phase 1, 2, 6, 9, 10: • No aural warning • No master caution light • Appropriate message appears on the Engines Warning Display (see sheet FWC A27020) 3) On the SYSTEM PAGES CRT: STATUS page: - Appropriate message appears (see sheet FWC A27110) 4) Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

5) Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION PITCH CONTROL

CHAPTER 24: PITCH CONTROL MALFUNCTION

: THS MOTOR 1 FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Failure of the electric trim motor 1

CONSEQUENCE

:

1) THS is no more controlled by ELAC 2 via the No 1 electrical motor 2) After a large pitch demand, using side stick If flight phase 1, 2, 6, 9, 10: • Appropriate message appear on the Engines Warning Display (see sheet FWC A27550) 3) Automatic pitch trim is still available (controlled by ELAC 1 on THS motor 2) 4) Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

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5) Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION PITCH CONTROL

CHAPTER 24: PITCH CONTROL MALFUNCTION

: THS MOTOR 2 FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Failure of the electric trim motor 2

CONSEQUENCE

:

1) THS is no more controlled by the ELAC 1 and SEC 1 via the No 2 electrical motor 2) Set ELAC 2 in off position: If flight phase 1, 2, 6, 9, 10: • Single chime sounds • Amber master caution light comes on • Appropriate messages appear on the Engines Warning Display (see sheet FWC A27210) 3) On the SYSTEM PAGES CRT: F/CTL page: ELAC 2 becomes amber G.L AIL becomes amber boxed B.R AIL becomes amber boxed LAF DEGRADED appears in amber 4) After a large pitch demand, using side stick: Alarm description - Appropriate messages appear on the Engines Warning Display (see sheets FWC A27540, A27595) On the PFD, the pitch and roll attitude limit green lines change to amber crosses 5) On the SYSTEM PAGES CRT: STATUS page: - Appropriate messages appear (see sheets FWC A27817, A27819, A27821, A27823, A27825, A27625, A27815) 6) Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). 7) Set SEC 2 OFF and check that THS does not move anymore

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8) Cancelling the malfunction and resetting circuit breaker restore normal operation after reset of ELAC 2 computer.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION PITCH CONTROL

CHAPTER 24: PITCH CONTROL MALFUNCTION

: THS MOTOR 3 FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Failure of the electric trim motor 3

CONSEQUENCE

:

1) THS is no more controlled by the SEC 2 via the No 3 Electrical motor. 2) Set ELAC 1 and ELAC 2 in off position: • THS does not move anymore. If flight phase 1, 2, 6, 9, 10: • Single chime sounds • Amber master caution light comes on • Appropriate messages appear on the Engines Warning Display (see sheets FWC A27200, A27210, A27480, A27595) On the PFD, the pitch and roll attitude limit green lines change to amber crosses 3) On the SYSTEM PAGES CRT: F/CTL page: ELAC 1 and 2 become amber B.L AIL and G.L AIL become amber boxed G.R AIL and B.R AIL become amber boxed Right and Left AIL index become amber cross and LAF DEGRADED appears in amber STATUS page: - Appropriate messages appear (see sheets FWC A27817, A27819, A27821, A27823, A27825, A27645, A27640, A27815) 4) On the SYSTEM PAGES CRT: F/CTL page: PITCH TRIM message becomes amber 5) Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

6) Cancelling the malfunction restores normal operation after reset of ELAC 1 and ELAC 2 computers.

DATE: SEP 1998

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DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ROLL CONTROL

CHAPTER 25 - ROLL CONTROL CONTENTS: CAPT SIDE STICK ROLL FAIL F/O SIDE STICK ROLL FAIL ERRONEOUS CAPT ROLL LEFT ORDER ERRONEOUS F/O ROLL LEFT ORDER ERRONEOUS CAPT ROLL RIGHT ORDER ERRONEOUS F/O ROLL RIGHT ORDER LEFT SPOILER 5 RUNAWAY RIGHT SPOILER 3 RUNAWAY LEFT SPEED BRAKE 3 NOT RETRACTED RIGHT SPEED BRAKE 2 & 3 NOT RETRACTED

U6KSC00

LEFT AILERON BLUE SERVO JAM

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ROLL CONTROL

CHAPTER 25: ROLL CONTROL MALFUNCTION

: CAPT SIDE STICK ROLL FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Failure in the transducer box used for Roll control (Potentiometers associated to ELACs and SECs)

CONSEQUENCE

:

1) The CAPT side stick roll order remains frozen. 2) No message on the ENGINES WARNINGS display.

U6KSC00

3) Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ROLL CONTROL

CHAPTER 25: ROLL CONTROL MALFUNCTION

: F/O SIDE STICK ROLL FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Failure in the transducer box used for Roll control (Potentiometers associated to ELACs and SECs)

CONSEQUENCE

:

1) The F/O side stick roll order remains frozen. 2) No message on the ENGINES WARNINGS display.

U6KSC00

3) Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ROLL CONTROL

CHAPTER 25: ROLL CONTROL MALFUNCTION

: ERRONEOUS CAPT ROLL LEFT ORDER

MALFUNCTION DESCRIPTION

:

CAUSE

: Erroneous potentiometers order in Roll to ELACs and SECs

CONSEQUENCE

:

1) The CAPT side stick roll order is blocked to left deflection. 2) No message on the ENGINES WARNINGS display.

U6KSC00

3) Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION ROLL CONTROL

CHAPTER 25: ROLL CONTROL MALFUNCTION

: ERRONEOUS F/O ROLL LEFT ORDER

MALFUNCTION DESCRIPTION

:

CAUSE

: Erroneous potentiometers order in Roll to ELACs and SECs

CONSEQUENCE

:

1) The F/O side stick Roll order is blocked to left deflection. 2) No message on the ENGINES WARNINGS display.

U6KSC00

3) Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ROLL CONTROL

CHAPTER 25: ROLL CONTROL MALFUNCTION

: ERRONEOUS CAPT ROLL RIGHT ORDER

MALFUNCTION DESCRIPTION

:

CAUSE

: Erroneous potentiometers order in Roll to ELACs and SECs

CONSEQUENCE

:

1) The CAPT side stick roll order is blocked to right deflection. 2) No message on the ENGINES WARNINGS display.

U6KSC00

3) Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ROLL CONTROL

CHAPTER 25: ROLL CONTROL MALFUNCTION

: ERRONEOUS F/O ROLL RIGHT ORDER

MALFUNCTION DESCRIPTION

:

CAUSE

: Erroneous potentiometers order in Roll to ELACs and SECs

CONSEQUENCE

:

1) The F/O side stick roll order is blocked to right deflection. 2) No message on the ENGINES WARNINGS display.

U6KSC00

3) Cancelling the malfunction restores normal operation.

DATE: SEP 1998

Page Page381 7

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ROLL CONTROL

CHAPTER 25: ROLL CONTROL MALFUNCTION

: LEFT SPOILER 5 RUNAWAY

MALFUNCTION DESCRIPTION

:

CAUSE

: Left spoiler 5 runaway

CONSEQUENCE

:

1) Left spoiler 5 runaways then stops 2) If flight phase 1, 2, 6, 8, 9, 10: • Single chime sounds • Amber master caution light comes on • Appropriate message appears on the Engines Warning Display (see sheet FWC A27415) 3) On the SYSTEM PAGES CRT: F/CTL page: • left spoiler 5:5 becomes amber (with arrow) • right spoiler 5:5 becomes amber • LAF DEGRADED appears STATUS page: • Appropriate message appears (see sheet FWC A27840) 4) Appropriate messages will be available on MDCU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

5) Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION ROLL CONTROL

CHAPTER 25: ROLL CONTROL MALFUNCTION

: RIGHT SPOILER 3 RUNAWAY

MALFUNCTION DESCRIPTION

:

CAUSE

: Right spoiler 3 runaway

CONSEQUENCE

:

1) Right spoiler 3 runaways then stops 2) If flight phase 1, 2, 6, 8, 9, 10: • Single chime sounds • Amber master caution light comes on • Appropriate message appears on the Engines Warning Display (see sheet FWC A27415) 3) On the SYSTEM PAGES CRT: FLT/CTL page: • left spoiler 3:3 becomes amber • right spoiler 3:3 becomes amber (with arrow) STATUS page: • Appropriate message appears (see sheet FWC A27838) 4) Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

5) Cancelling the malfunction restores normal operation.

DATE: SEP 1998

Page Page383 9

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ROLL CONTROL

CHAPTER 25: ROLL CONTROL MALFUNCTION

: LEFT SPEED BRAKE 3 NOT RETRACTED

MALFUNCTION DESCRIPTION

:

CAUSE

: The left speed brake 3 fails to retract for mechanical reasons

CONSEQUENCE

:

1) The left speed brake 3 can extend but not retract. 2) If flight phase 1, 2, 6, 8, 9, 10: • Single chime sounds • Amber master caution light comes on • Appropriate message appears on the Engines Warning Display (see sheet FWC A27415) 3) On the SYSTEM PAGES CRT: FLT/CTL page: • left speed brake 3:3 becomes amber (with arrow) • right speed brake 3:3 becomes amber STATUS page: • Appropriate message appears (see sheet FWC A27838) 4) Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

5) Cancelling the malfunction restores normal operation.

DATE: SEP 1998

Page Page 384 10

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION ROLL CONTROL

CHAPTER 25: ROLL CONTROL MALFUNCTION

: RIGHT SPEED BRAKE 2 & 3 NOT RETRACTED

MALFUNCTION DESCRIPTION

:

CAUSE

: The right speed brakes 2 & 3 fail to rectract for mechanical reasons

CONSEQUENCE

:

1) The right speed brakes can extend but not retract 2) If flight phase 1, 2, 6, 8, 9, 10: • Single chime sounds • Amber master caution light comes on • Appropriate message appears on the Engines Warning Display (see sheet FWC A27415) 3) On the SYSTEM PAGES CRT: F/CTL page: • left SPLR 2:2 becomes amber • right SPLR 2:2 becomes amber (with arrow) • left SPLR 3:3 becomes amber • right SPLR 3:3 becomes amber (with arrow) STATUS page: • Appropriate message appears (see sheet FWC A27843) 4) Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

5) Cancelling the malfunction restores normal operation.

DATE: SEP 1998

Page Page 385 11

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION ROLL CONTROL

CHAPTER 25: ROLL CONTROL MALFUNCTION

: LEFT AILERON BLUE SERVO JAM

MALFUNCTION DESCRIPTION

:

CAUSE

: Jamming of a slide in the left aileron servo fed by the blue hydraulic circuit

CONSEQUENCE

:

1) Left aileron is blocked 2) If flight phase 1, 2, 6, 9, 10: • No aural warning • No master caution light • Appropriate message appears on the Engines Warning Display (see sheet FWC A27240) 3) On the SYSTEM PAGES CRT: F/CTL page: • B.L AIL amber boxed • LAF DEGRADED appears 4) Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

5) Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION RADIO NAV

CHAPTER 26 - RADIO NAV CONTENTS: DME 1 RECEIVER FAIL DME 2 RECEIVER FAIL ILS 1 RECEIVER FAIL ILS 2 RECEIVER FAIL VOR 1 RECEIVER FAIL VOR 2 RECEIVER FAIL R/A 1 FAIL R/A 2 FAIL ADF 1 RECEIVER FAIL ADF 2 RECEIVER FAIL MLS 1 RECEIVER FAIL MLS 2 RECEIVER FAIL RMP 1 FAIL

U6KSC00

RMP 2 FAIL

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION RADIO NAV

CHAPTER 26: RADIO NAV MALFUNCTION

: DME 1 RECEIVER FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: DME 1 receiver power supply failure

CONSEQUENCE

:

- On VOR/DME RMI, DME 1 displayed data is cleared. - DME 1 call signs are no longer received. - In the case of ILS/DME on the CAPT PFD screen, if the CAPT ILS push button of the CAPT EFIS control panel is pressed, a DME1 red message is displayed. - In the case of VOR/DME or DME alone, if the AFD1-OFF-VOR1 switch is in VOR1 position, a DME red message is displayed in the LH lower corner of the CAPT and F/O ND screens.

U6KSC00

ACTION: NIL - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION RADIO NAV

CHAPTER 26: RADIO NAV MALFUNCTION

: DME 2 RECEIVER FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: DME 2 receiver power supply failure

CONSEQUENCE

:

- On VOR/DME RMI, DME 2 displayed data is cleared. - DME 2 call signs are no longer received. - In the case of ILS/DME on the F/O PFD screen, if the F/O ILS push button of the F/O EFIS control panel is pressed, a DME2 red message is displayed. - In the case of ILS/DME on the F/O PFD screen, if the F/O ILS push button of the F/O EFIS control panel is pressed, a DME2 red message is displayed. - In the case of VOR/DME or DME alone, of the ADF2-OFF-VOR2 switch is in VOR2 position, a DME2 red message is displayed in the RH lower corner of the CAPT and F/O ND screens.

U6KSC00

ACTION: NIL - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling the malfunction restores normal operation.

DATE: SEP 1998

Page Page389 3

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A320 SIMULATED MALFUNCTIONS DESCRIPTION RADIO NAV

CHAPTER 26: RADIO NAV MALFUNCTION

: ILS 1 RECEIVER FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: ILS 1 receiver power supply failure

CONSEQUENCE

:

- On the CAPT PFD screen, if the CAPT ILS push button of the CAPT EFIS control panel is pressed, all the ILS 1 informations disappear and an ILS 1 red message is displayed. - On the F/O ND screen, in ROSE-ILS mode, all the ILS 1 informations disappear and G/S and LOC red messages are displayed. - ILS 1 call signs are no longer received - If the GPWS is in use, mode 5 warning messages are inhibited. - On the PFD, in the FMA part, the message CAT 1 is displayed. - If the aircraft is in flight phase 1,6 or 7, and if an upper level landing capability is engaged (i.e. CAT3 dual or CAT3 single or CAT2 or LAND green), 3 clicks sound to announce the change of category. - Indications and warning symbols/messages generated by ECAM: report to FWC boards 34340 + 34570. - GPWS (only on ground MARK V) is no more operative: • the GPWS fault light comes on • Alarms generated by ECAM: report to FWC board 34610 ACTION: NIL

U6KSC00

- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION RADIO NAV

CHAPTER 26: RADIO NAV MALFUNCTION

: ILS 2 RECEIVER FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: ILS 2 receiver power supply failure

CONSEQUENCE

:

- On the F/O PFD screen, if the F/O ILS push-button of the F/O EFIS control panel is pressed, all the ILS 2 informations disappear and an ILS 2 red message is displayed. - On the CAP ND screen, in ROSE-ILS mode, all the ILS 2 informations disappear and G/S and LOC red messages are displayed. - ILS 2 call signs are no longer received. - On the PFD, in the FMA part, the message CAT 1 is displayed. - If the aircraft is in flight phase 1, 6 or 7, and if an upper level landing capability is engaged (i.e. CAT3 dual or CAT3 single or CAT2 or LAND green), 3 clicks sound to announce the change of category. - Indications and warning symbols/messages generated by ECAM: report to FWC boards 34350 + 34580. ACTION: NIL - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

- Cancelling the malfunction restores normal operation.

DATE: SEP 1998

Page Page391 5

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A320 SIMULATED MALFUNCTIONS DESCRIPTION RADIO NAV

CHAPTER 26: RADIO NAV MALFUNCTION

: VOR 1 RECEIVER FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: VOR 1 receiver power supply failure

CONSEQUENCE

:

- On VOR/DME RMI • VOR 1 flag appears • VOR 1 bearing needle shows a bearing of 90x. - VOR 1 and MKR call signs are no longer received. - Marker informations are no longer displayed when the aircraft overflies the beacons. - If the CAPT and F/O ADF1/OFF/VOR1 switches are on VOR 1 position, on both ND screens, in ROSE-ILS, ROSE-VOR, ROSE-NAV or ARC mode, the VOR 1 informations displayed in the left lower corner and the associated pointers disappear and a VOR 1 red message is showing. - On the CAPT ND screen, in ROSE-VOR mode, all the VOR 1 informations disappear and a VOR red message is showing above the A/C symbol.

U6KSC00

ACTION: NIL - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION RADIO NAV

CHAPTER 26: RADIO NAV MALFUNCTION

: VOR 2 RECEIVER FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: VOR 2 receiver power supply failure

CONSEQUENCE

:

- On VOR/DME RMI • VOR 2 flag appears • VOR 2 bearing needle shows a bearing of 90deg - VOR 2 call signs are no longer received. - If the CAPT and F/O ADF2/OFF/VOR2 switches are on VOR 2 position, on both ND screens, in ROSE-ILS, ROSE-VOR, ROSE-NAV or ARC mode, the VOR 2 informations displayed in the right lower corner and the associated pointers disapper and a VOR 2 red message is showing. - On the F/O ND screen, in ROSE-VOR mode, all the VOR 2 informations disappear and a VOR red message is showing above the A/C symbol.

U6KSC00

ACTION: NIL - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling the malfunction restores normal operation.

DATE: SEP 1998

Page Page393 7

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A320 SIMULATED MALFUNCTIONS DESCRIPTION RADIO NAV

CHAPTER 26: RADIO NAV MALFUNCTION

: R/A 1 FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: R/A 1 receiver power supply failure

CONSEQUENCE

:

- The radio height information (RA2) is still showing on CAPT and F/O PFD screens. - If the GPWS is in use, all the warning messages stop and the FAULT light illuminates. - On the PFD, in the FMA part, the message CAT 2 is displayed. - If the aircraft is in flight phase 1, 6 or 7, if the category 3 is engaged, 3 clicks sound to announce the change of category. - Indications and warning symbols/messages generated by ECAM: report to FWC boards 34360 + 34590.

U6KSC00

ACTION: NIL - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling the malfunction restores normal operation.

DATE: SEP 1998

Page Page394 8

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A320 SIMULATED MALFUNCTIONS DESCRIPTION RADIO NAV

CHAPTER 26: RADIO NAV MALFUNCTION

: R/A 2 FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: R/A 2 receiver power supply failure

CONSEQUENCE

:

- The radio height information (RA1) is still showing on CAPT and F/O PFD screens. - On the PFD, in the FMA part, the message CAT 2 is displayed. - If the aircraft is in flight phase 1, 6 or 7, if the category 3 is engaged, 3 clicks sound to announce the change of category. - Indications and warning symbols/messages generated by ECAM: report to FWC board 34370 + 34600. ACTION: NIL

U6KSC00

- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - Cancelling the malfunction restores normal operation.

DATE: SEP 1998

Page Page395 9

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A320 SIMULATED MALFUNCTIONS DESCRIPTION RADIO NAV

CHAPTER 26: RADIO NAV MALFUNCTION

: ADF 1 RECEIVER FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: ADF 1 receiver power supply failure

CONSEQUENCE

:

- If the ADF RMI optional equipment is installed, on ADF RMI: • ADF1 flag appears • ADF1 bearing needle shows a bearing of 90 deg - ADF 1 call signs are no longer received - If the CAPT and F/O ADF 1/OFF/VOR 1 switches are on ADF 1 position, on both ND screens, in ROSE-ILS, ROSE-VOR, ROSE-NAV or ARC mode, the ADF 1 informations displayed in the left lower corner and the associated pointers disappear and an ADF 1 red message is showing. ACTION: NIL - Appropriate messages will be available on MDCU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

- Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION RADIO NAV

CHAPTER 26: RADIO NAV MALFUNCTION

: ADF 2 RECEIVER FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: ADF 2 receiver power supply failure

CONSEQUENCE

:

- If the ADF RMI optional equipment is installed, on ADF RMI: • ADF2 flag appears • ADF2 bearing needle shows a bearing of 90 deg - ADF 2 call signs are no longer received - If the CAPT and F/O ADF 2/OFF/VOR 2 switches are on ADF 2 position, on both ND screens, in ROSE-ILS, ROSE-VOR, ROSE-NAV or ARC mode, the ADF 2 informations displayed in the left lower corner and the associated pointer disappear and an ADF 2 red message is showing. ACTION: NIL - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

- Cancelling the malfunction restores normal operation.

DATE: SEP 1998

Page Page 397 11

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A320 SIMULATED MALFUNCTIONS DESCRIPTION RADIO NAV

CHAPTER 26: RADIO NAV MALFUNCTION

: MLS 1 RECEIVER FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: OPTION

CONSEQUENCE

:

U6KSC00

OPTION

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION RADIO NAV

CHAPTER 26: RADIO NAV MALFUNCTION

: MLS 2 RECEIVER FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: OPTION

CONSEQUENCE

:

U6KSC00

OPTION

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION RADIO NAV

CHAPTER 26: RADIO NAV MALFUNCTION

: RMP 1 FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: RMP 1 power supply failure

CONSEQUENCE

:

- The displayed frequencies disappear from RMP 1. - Radionavigation: • In normal operation, there is no consequence: frequencies are always selected by FMGC 1. • If “ON NAV” is selected.the frequencies are now selected by the FMGC1 if it works or by FMGC2 if the FMCG1 is also failed. - Radiocommunication: - When RMP3 is applicable: • If RMP 3 is switched ON, VHF 1, VHF 3 and HF 1 frequencies are selected by RMP 3. • If RMP 3 is switched OFF, VHF 1, VHF 3 and HF 1 frequencies are selected by RMP 2. ACTION: NIL - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

- Cancelling the malfunction restores normal operation.

DATE: SEP 1998

Page Page 400 14

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A320 SIMULATED MALFUNCTIONS DESCRIPTION RADIO NAV

CHAPTER 26: RADIO NAV MALFUNCTION

: RMP 2 FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: RMP 2 power supply failure

CONSEQUENCE

:

- The displayed frequencies disappear from RMP 2. - Radionavigation: • In normal operation, there is no consequence: frequencies are always selected by FMGC 2. • If “ON NAV” is selected, the frequencies are now selected by the FMGC2 if it works or by the FMGC1 if the FMGC2 is failed. - Radiocommunication: - When RMP3 is applicable: • If RMP 3 is switched ON, VHF 2 and HF 2 frequencies are selected by RMP 3. • If RMP 3 is switched OFF, VHF 2 and HF 2 frequencies are selected by RMP 1. ACTION: NIL - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

- Cancelling the malfunction restores normal operation.

DATE: SEP 1998

Page Page 401 15

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A320 SIMULATED MALFUNCTIONS DESCRIPTION RADIO NAV

U6KSC00

THIS PAGE INTENTIONALY LEFT BLANK

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONSTIRES/BRAKES DESCRIPTION

CHAPTER 27 - TIRES/BRAKES CONTENTS: BRAKE EXCESSIVE TEMP (WHEEL 3) BRAKES EXCESSIVE TEMP (WHEELS 1,2,4) ALL LEFT TIRES BLOWN ON GROUND ALL RIGHT TIRES BLOWN ON GROUND TIRE 1 PRESS LOW TIRE 1 BLOWN TIRE 2 BLOWN ON GROUND PARTIAL ANTI SKID FAIL (BSCU SYS 1) BSCU SYSTEM 2 FAIL ANTI SKID FAIL AUTO BRAKE FAIL ACCU PRESS INDICATOR FAILURE BRAKES EXCESSIVE TEMP (WHEEL 8)

U6KSC00

BRAKES FAN INOP

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONSTIRES/BRAKES DESCRIPTION

CHAPTER 27: TIRES/BRAKES MALFUNCTION

: BRAKE EXCESSIVE TEMP (WHEEL 3)

MALFUNCTION DESCRIPTION

:

CAUSE

: Brake dragging on wheel 3

CONSEQUENCE

:

- The wheel 3 brake temperature increases according to speed, gross weight and time. - If the temperature of the wheel 3 is greater than 300degC the BRK HOT light comes on. - The WHEEL page appears with the wheel 3 temperature in amber. - ECAM warning and messages are conformed to ’32020’ referenced independant failure. Cancelling the malfunction restores normal operation.

U6KSC00

Wheel 3 temperature returns immediately to the coldest wheel value.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONSTIRES/BRAKES DESCRIPTION

CHAPTER 27: TIRES/BRAKES MALFUNCTION

: BRAKES EXCESSIVE TEMP (WHEELS 1,2,4)

MALFUNCTION DESCRIPTION

:

CAUSE

: Brake dragging on wheels 1, 2 and 4

CONSEQUENCE

:

- The wheels 1, 2, 4 brake temperatures increase according to speed, gross weight and time. - If the temperature of the wheels 1, 2, 4 is greater than 300degC the BRK HOT light comes on. - The WHEEL page appears with the wheels 1, 2, 4 temperature in amber. - ECAM warning and messages are conformed to ’32020’ referenced independent failure. Cancelling the malfunction restores normal operation.

U6KSC00

Wheel 1, 2, 4 temperatures return immediately to the coldest wheel value.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONSTIRES/BRAKES DESCRIPTION

CHAPTER 27: TIRES/BRAKES MALFUNCTION

: ALL LEFT TIRES BLOWN ON GROUND

MALFUNCTION DESCRIPTION

:

CAUSE

: At touch down, the wheel’s tires on left L/G burst

CONSEQUENCE

:

- Rolling in abnormal configuration will induce all secondary effects concerning motion, braking. If Tire Pressure Indicating System option is available: When tire pressures become lower than 74% nominal value: ECAM warning and messages are conformed to ’32030’ referenced independent failure. The WHEEL page appears on ECAM lower D.U. with tire 1 and 2 indications in amber. Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONSTIRES/BRAKES DESCRIPTION

CHAPTER 27: TIRES/BRAKES MALFUNCTION

: ALL RIGHT TIRES BLOWN ON GROUND

MALFUNCTION DESCRIPTION

:

CAUSE

: At touch down, the wheel’s tires on right L/G burst

CONSEQUENCE

:

- Rolling in abnormal configuration will induce all secondary effects concerning motion, braking. If Tire Pressure Indicating System option is available: When tire pressures become lower than 74% nominal value: ECAM warning and messages are conformed to ’32030’ referenced independent failure. The WHEEL page appears on ECAM lower D.U. with the tire 3 and 4 indications in amber. Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONSTIRES/BRAKES DESCRIPTION

CHAPTER 27: TIRES/BRAKES MALFUNCTION

: TIRE 1 PRESS LOW

MALFUNCTION DESCRIPTION

:

CAUSE

: Wheel 1 tire puncture

CONSEQUENCE

:

- Rolling in abnormal configuration will induce all secondary effects concerning motion, braking. - Wheel 1 tire will deflate slowly. If Tire Pressure Indicating System option is available: When WHEEL 1 pressure becomes lower than 79% WHEEL 2 pressure: ECAM warning and messages are conformed to ’32030’ referenced independent failure. The WHEEL page appears on ECAM lower D.U. with tire 1 indication in amber. Appropriate message will be available on MCDU (CFDS fonction) (when CFDS maintenance option selected).

U6KSC00

Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONSTIRES/BRAKES DESCRIPTION

CHAPTER 27: TIRES/BRAKES MALFUNCTION

: TIRE 1 BLOWN

MALFUNCTION DESCRIPTION

:

CAUSE

: The wheel tire No 1 bursts

CONSEQUENCE

:

- Rolling in abnormal configuration will induce all secondary effects concerning motion, braking. If tire pressure indicating system option is available: When tire 1 pressure becomes lower than 74% nominal value: ECAM warning and messages are conformed to ’32030’ referenced independent failure. The WHEEL page appears on ECAM lower D.U. with tire 1 indication in amber. Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONSTIRES/BRAKES DESCRIPTION

CHAPTER 27: TIRES/BRAKES MALFUNCTION

: TIRE 2 BLOWN ON GROUND

MALFUNCTION DESCRIPTION

:

CAUSE

: At touch down, the wheel’s tire 2 bursts

CONSEQUENCE

:

- Rolling in abnormal configuration will induce all secondary effects concerning motion, braking. If Tire Pressure Indication System option is available: When tire 2 pressure becomes lower than 74% nominal value: ECAM warning and messages are conformed to ’32030’ referenced independent failure. The WHEEL page appears on ECAM lower D.U. with tire 2 indication in amber. Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONSTIRES/BRAKES DESCRIPTION

CHAPTER 27: TIRES/BRAKES MALFUNCTION

: PARTIAL ANTI SKID FAIL (BSCU SYS 1)

MALFUNCTION DESCRIPTION

:

CAUSE

: Failure of BSCU sys. 1

CONSEQUENCE

:

- All the functions of BSCU sys. 1 are taken by BSCU sys. 2 and there is no system lost. Appropriate messages will be available on MCDU (CFDS function) (When CFDS maintenance option selected).

U6KSC00

Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONSTIRES/BRAKES DESCRIPTION

CHAPTER 27: TIRES/BRAKES MALFUNCTION

: BSCU SYSTEM 2 FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Power supply of BSCU sys. 2 is lost

CONSEQUENCE

:

- All the functions of BSCU sys. 2 are taken by BSCU sys. 1 and there is no system lost. Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONSTIRES/BRAKES DESCRIPTION

CHAPTER 27: TIRES/BRAKES MALFUNCTION

: ANTI SKID FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Failure of antiskid switch, it is forced to OFF position

CONSEQUENCE

:

- Antiskid function is completely lost. - The braking mode is alternate braking without antiskid. - Nose wheel steering is inoperative. - The WHEEL page appears on the ECAM lower DU with ANTISKID, STEERING, AUTO BRK and ALTN BRK indications displayed. - ECAM warning and messages are conformed to ’32060’ referenced independent failure. Appropriate messages will be available on MCDU (CFDS function) (When CFDS maintenance option selected)

U6KSC00

Cancelling the malfunction restores normal operation.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONSTIRES/BRAKES DESCRIPTION

CHAPTER 27: TIRES/BRAKES MALFUNCTION

: AUTO BRAKE FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Failure of Normal selector valve which remains in closed position

CONSEQUENCE

:

- Autobrake and normal brake is lost. - The AUTO BRK amber and ALTN BRK green indications appear on the WHEEL page of the ECAM lower DU, if L/G is downlocked. - ECAM warning and messages are conformed to ’32050’ and ’32125’ referenced independent failures. Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

Cancelling the malfunction restores normal operation.

DATE: SEP 1998

Page Page 414 12

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONSTIRES/BRAKES DESCRIPTION

CHAPTER 27: TIRES/BRAKES MALFUNCTION

: ACCU PRESS INDICATOR FAILURE

MALFUNCTION DESCRIPTION

:

CAUSE

: Failure of ACCU PRESS indicator circuit

CONSEQUENCE

:

- The ACCU PRESS indication is 0 Psi. - Braking is always available in normal or alternate mode according to hydraulic conditions and A/SKID switch.

U6KSC00

Cancelling the malfunction restores normal operation.

DATE: SEP 1998

Page Page 415 13

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A320 SIMULATED MALFUNCTIONSTIRES/BRAKES DESCRIPTION

CHAPTER 27: TIRES/BRAKES MALFUNCTION

: BRAKES EXCESSIVE TEMP (WHEEL 8)

MALFUNCTION DESCRIPTION

:

CAUSE

: Brake dragging on wheel 8

CONSEQUENCE

:

(only if boggie versus is simulated) -

The wheel 8 brake temperature increases according to speed, gross weight and time. If the temperature of the wheel 8 is greater than 300 degC, the BRK HOT light comes on. The WHEEL system page appears with the wheel 8 temperature in amber. ECAM warning and messages are conformed to ’32020’ referenced independent failure.

U6KSC00

Cancelling the malfunction restores normal operation. Wheel 8 temperature return immediately to the coldest wheel value.

DATE: SEP 1998

Page Page 416 14

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A320 SIMULATED MALFUNCTIONSTIRES/BRAKES DESCRIPTION

CHAPTER 27: TIRES/BRAKES MALFUNCTION

: BRAKES FAN INOP

MALFUNCTION DESCRIPTION

:

CAUSE

: Brake fan P/B 4 GS is inoperative

CONSEQUENCE

:

- Brake fan relays 5GS and 6GS are not energized. - Brakes are not ventilated. - If brake fan P/B was ON, the "ON" light disapears.

U6KSC00

Cancelling the malfunction restores normal operation.

DATE: SEP 1998

Page Page 417 15

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A320 SIMULATED MALFUNCTIONSTIRES/BRAKES DESCRIPTION

U6KSC00

THIS PAGE INTENTIONALY LEFT BLANK

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION YAW CONTROL

CHAPTER 28 - YAW CONTROL CONTENTS: RUDDER PEDALS BLOCKED

U6KSC00

RUDDER GREEN SERVO JAM

DATE: SEP 1998

Page Page419 1

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION YAW CONTROL

CHAPTER 28: YAW CONTROL MALFUNCTION

: RUDDER PEDALS BLOCKED

MALFUNCTION DESCRIPTION

:

CAUSE

: Jamming of the rudder control channel

CONSEQUENCE

:

1) CAPT and F/O pedals are blocked (within the maximum force of the simulator servo jack: 100 daN).

U6KSC00

2) Cancelling the malfunction restores normal operation.

DATE: SEP 1998

Page Page420 2

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION YAW CONTROL

CHAPTER 28: YAW CONTROL MALFUNCTION

: RUDDER GREEN SERVO JAM

MALFUNCTION DESCRIPTION

:

CAUSE

: Jamming of a slide in the rudder servo fed by the green hydraulic circuit

CONSEQUENCE

:

1) An additional force is felt on the rudder pedals

U6KSC00

2) Cancelling the malfunction restores normal operation.

DATE: SEP 1998

Page Page421 3

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION YAW CONTROL

U6KSC00

THIS PAGE INTENTIONALLY LEFT BLANK

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS ENGINES DESCRIPTION IAE

CHAPTER 29 - ENGINES IAE CONTENTS: BOTH ENGINES FLAME OUT FLAME OUT # 1 FLAME OUT # 2 EXTINGUISHABLE FIRE # 1 EXTINGUISHABLE FIRE # 2 UNEXTINGUISHABLE FIRE # 1 UNEXTINGUISHABLE FIRE # 2 COMPRESSOR STALL # 1 COMPRESSOR STALL # 2 N2 ACCESSORY DRIVE LOST # 1 N2 ACCESSORY DRIVE LOST # 2 HOT START # 1 HOT START # 2 REVERSER STUCK # 1 REVERSER STUCK # 2 HUNG START # 1 HUNG START # 2 N1 ROTOR SEIZED # 1 N1 ROTOR SEIZED # 2 START VALVE STUCK # 1 START VALVE STUCK # 2 OIL FILTER CLOGGED (ENGINE 1) # 1 IGNITION FAIL # 1 REVERSER UNLOCKED # 1 SERIOUS ENG DAMAGE WITH EXTINGUIS. FIRE # 1 SERIOUS ENG DAMAGE WITH EXTINGUIS. FIRE # 2 SERIOUS ENG DAMAGE WITH UNEXTING FIRE # 1 U6KSC00

SERIOUS ENG DAMAGE WITH UNEXTING FIRE # 2 SERIOUS ENG DAMAGE WITH PARTIAL PWR LOSS # 1 SERIOUS ENG DAMAGE WITH PARTIAL PWR LOSS # 2 THROTTLE INOPERATIVE (POWER STUCK) # 1

DATE: SEP 1998

Page Page423 1

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A320 SIMULATED MALFUNCTIONS ENGINES DESCRIPTION IAE

ENGINE DETACHED # 1 ENGINE DETACHED # 2 FUEL HP VALVE INOPERATIVE # 2 E.I.U. FAIL # 2 FUEL FILTER CLOGGING # 1 IDLE CONTROL FAIL # 1 TLA RESOLVER INEQUALITY # 1 MAN START FAULT # 1 REVERSER DEPLOYED # 1 AUTOMATIC REVERSION TO N1 RATED MODE # 1

U6KSC00

AUTOMATIC REVERSION TO N1 UNRATED MODE # 2

DATE: SEP 1998

Page Page424 2

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A320 SIMULATED MALFUNCTIONS ENGINES DESCRIPTION IAE

CHAPTER 29: ENGINES IAE MALFUNCTION

: BOTH ENGINES FLAME OUT

MALFUNCTION DESCRIPTION

:

CAUSE

: Engines 1 & 2 flame out

CONSEQUENCE

:

As soon as engines 1 & 2 N2 are lower than 50% and if in flight, FADEC 1 & 2 try to restart engines 1 & 2 energizing both ignitors. Engines 1 & 2 stop. On ground: • Complete loss of electrical supply (if APU not available and GROUND elec not connected). If ELEC power available (APU, EXTERNAL GROUND): • Single chime sounds. • Master caution light comes on. • Corresponding messages appear on the E/W CRT. In flight: • CRC sounds. • Master warning light comes on. • Corresponding messages appear on the E/W CRT

U6KSC00

Cancelling malfunction restores normal operation.

DATE: SEP 1998

Page Page425 3

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A320 SIMULATED MALFUNCTIONS ENGINES DESCRIPTION IAE

CHAPTER 29: ENGINES IAE MALFUNCTION

: FLAME OUT # 1

MALFUNCTION DESCRIPTION

:

CAUSE

: Combustion stopped

CONSEQUENCE

:

- As soon as N2 is lower than 50% and if in flight, FADEC 1 tries to restart engine 1, energizing both ignitors. -

Engine 1 stops. Single chime sounds. Master caution light comes on. Appropriate messages appear on the E/W CRT. Failure on, engine 1 can’t be restarted.

U6KSC00

- Cancelling malfunction restores normal operation.

DATE: SEP 1998

Page Page426 4

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A320 SIMULATED MALFUNCTIONS ENGINES DESCRIPTION IAE

CHAPTER 29: ENGINES IAE MALFUNCTION

: FLAME OUT # 2

MALFUNCTION DESCRIPTION

:

CAUSE

: Combustion stopped

CONSEQUENCE

:

- As soon as N2 is lower than 50% and if in flight, FADEC 2 tries to restart engine 2, energizing both ignitors. -

Engine 2 stops Single chime sounds Master caution light comes on Appropriate messages appear on E/W CRT Failure on, engine 2 can’t be restarted

U6KSC00

- Cancelling malfunction restores normal operation.

DATE: SEP 1998

Page Page427 5

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A320 SIMULATED MALFUNCTIONS ENGINES DESCRIPTION IAE

CHAPTER 29: ENGINES IAE MALFUNCTION

: EXTINGUISHABLE FIRE # 1

MALFUNCTION DESCRIPTION

:

CAUSE

: Engine 1 fire

CONSEQUENCE

:

On ground with external power or in flight • On fire panel “ENG 1 FIRE” light comes on - On central pedestal (115VU), Master ENG 1 “FIRE” light comes on • Nacelle temperature increases until fire stops. • Ecam displays consequences Whatever the flight phase is: • Audio CRC sounds • Master “Warn” light comes on • Appropriate messages (nature of failure and actions to be performed) appear on E/W CRT • “ENGINE” page appears on SYS CRT. Actions Push the ENGINE 1 FIRE P/B (FIRE PANEL) • After a few seconds, engine 1 shuts down • On fire panel, AGENTS ENG “SQUIB” lights come on • All warnings remain on • CRC stops. Push the AGENT 1 ENG 1 push button (FIRE PANEL) • After 3 seconds, AGENT 1 “DISH” light comes on. • After 10 seconds, all fire warnings disappear. • Engine 1 is stopped. • If activated: Master “Warn” light comes on. Cancelling malfunction restores normal operation: - Release the “ENG 1 FIRE” push button (FIRE PANEL).

U6KSC00

• On fire panel, ENG 1 AGENTS “SQUIB” lights go out. - On instructor station set the AGENT FIRE RESET. • On fire panel, ENG 1 AGENT 1 “DISH” light goes out.

DATE: SEP 1998

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS ENGINES DESCRIPTION IAE

CHAPTER 29: ENGINES IAE MALFUNCTION

: EXTINGUISHABLE FIRE # 2

MALFUNCTION DESCRIPTION

:

CAUSE

: Engine 2 fire

CONSEQUENCE

:

On ground with external power or in flight • On fire panel, “ENG 2 FIRE” light comes on • On central pedestal (115VU), Master ENG2 “FIRE” light comes on • Nacelle temperature increases until fire stops Ecam displays consequences Whatever the flight phase is: • Audio CRC sounds • Master “Warn” light comes on • Appropriate messages (nature of failure and actions to be performed) appear on E/W CRT • “ENGINE” page appears on SYS CRT Actions Push the ENGINE 2 FIRE P/B (FIRE PANEL) • After a few seconds, engine 2 shuts down • On fire panel, AGENTS ENG 2 “SQUIB” lights come on • All warnings remain on • CRC stops Push the AGENT1 ENG2 push button (FIRE PANEL) • After 3 seconds, AGENT1 “DISH” light comes on • After 10 seconds, all fire warnings remain on • Engine 2 is stopped Push the AGENT2 ENG2 push button (FIRE PANEL) • After 3 seconds, AGENT2 “DISH” light comes on • After 10 seconds, all fire warnings disappear U6KSC00

• If activated: Master “Warn” light goes out

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS ENGINES DESCRIPTION IAE

CHAPTER 29: ENGINES IAE

In order to recover normal operation: - Cancel malfunction - Realease the “ENG2 FIRE” push button (FIRE PANEL)

U6KSC00

• On fire panel, ENG 2 AGENTS “SQUIB” lights goes out - On instructor station set the AGENT FIRE RESET - On fire panel ENG 2 AGENT 1 and 2 “DISH” lights goes out

DATE: SEP 1998

Page Page430 8

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS ENGINES DESCRIPTION IAE

CHAPTER 29: ENGINES IAE MALFUNCTION

: UNEXTINGUISHABLE FIRE # 1

MALFUNCTION DESCRIPTION

:

CAUSE

: Engine 1 fire

CONSEQUENCE

:

On ground with external power or in flight • On fire panel, “ENG1 FIRE” light comes on • On central pedestal (115VU), Master ENG 1 “FIRE” light comes on • Nacelle temperature increases until fire stops. Ecam displays consequences Whatever the flight phase is: • Audio CRC sounds • Master “Warn” light comes on • Appropriate messages (nature of failure and actions to be performed) appear on E/W CRT • ENGINE page appears on SYS CRT. Actions Push the ENGINE 1 FIRE push button (FIRE PANEL) • After a few seconds, engine 1 shuts down • On fire panel, AGENTS ENG “SQUIB” lights come on • All warnings remain on • CRC stops. Push the AGENT 1 ENG 1 push button (FIRE PANEL) • After 3 seconds, AGENT 1 “DISH” light comes on • After 10 seconds, all fire warnings remain on • Engine 1 is stopped Push the AGENT 2 ENG 1 push button (FIRE PANEL) • After 3 seconds, AGENT 2 “DISH” light comes on • After 10 seconds, all fire warnings remain on U6KSC00

• Engine 1 is stopped

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS ENGINES DESCRIPTION IAE

CHAPTER 29: ENGINES IAE

Cancelling malfunction restores normal operation - Release the “ENG 1 FIRE” push button (FIRE PANEL) • On fire panel, ENG 1 AGENTS “SQUIB” lights go out - On instructor station set the AGENT FIRE

U6KSC00

• On fire panel ENG 1 AGENT 1 and 2 “DISH” light goes out

DATE: SEP 1998

Page Page 432 10

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS ENGINES DESCRIPTION IAE

CHAPTER 29: ENGINES IAE MALFUNCTION

: UNEXTINGUISHABLE FIRE # 2

MALFUNCTION DESCRIPTION

:

CAUSE

: Engine 2 fire

CONSEQUENCE

:

On ground with external power or in flight • On fire panel, “ENG 2 FIRE” light comes on • On central pedestal (115VU), Master ENG 2 “FIRE” light comes on • Nacelle temperature increases until fire stops. Ecam displays consequences Whatever the flight phase is: • Audio CRC sounds • Master “Warn” light comes on • Appropriate messages (nature of failure and actions to be performed) appear E/W CRT • “ENGINE” page appears on SYS CRT Actions: Push the ENGINE 2 FIRE push button (FIRE PANEL) • After a few seconds, engine 2 shuts down • On fire panel, AGENTS ENG “SQUIB” lights come on • All warnings remain on • CRC stops. Push the AGENT 1 ENG 2 push button (FIRE PANEL) • After 3 seconds, AGENT 1 “DISH” light comes on. • After 10 seconds, all fire warnings remain on. • Engine 2 is stopped. Push the AGENT 2 ENG 2 push button (FIRE PANEL) • After 3 seconds, AGENT 2 “DISH” light comes on. • After 10 seconds, all fire warnings remain on. U6KSC00

• Engine 2 is stopped.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS ENGINES DESCRIPTION IAE

CHAPTER 29: ENGINES IAE

Cancelling malfunction restore normal operation: - Release the “ENG 2 FIRE” push button (FIRE PANEL) • On fire panel, ENG 2 AGENTS “SQUIB” lights go out - On instructor station set the AGENT FIRE RESET

U6KSC00

• On fire panel, ENG 2 AGENTS 1 and 2 “DISH” lights go out.

DATE: SEP 1998

Page Page 434 12

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS ENGINES DESCRIPTION IAE

CHAPTER 29: ENGINES IAE MALFUNCTION

: COMPRESSOR STALL # 1

MALFUNCTION DESCRIPTION

:

CAUSE

: Compressor stall

CONSEQUENCE

:

- If N1 > 80%: EPR, N1, N2 EGT & fuel flow move erraticall lower or upper than in normal operation - Engine 1 vibrations increase - No warning - If throttle 1 is reduced so that N1 < 60%, normal operation is restored

U6KSC00

Cancelling malfunction restores normal operation.

DATE: SEP 1998

Page Page 435 13

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A320 SIMULATED MALFUNCTIONS ENGINES DESCRIPTION IAE

CHAPTER 29: ENGINES IAE MALFUNCTION

: COMPRESSOR STALL # 2

MALFUNCTION DESCRIPTION

:

CAUSE

: Compressor stall

CONSEQUENCE

:

- If N1 > 80%: EPR, N1, N2 EGT & Fuel Flow move erratically lower or upper than in normal operation - Engine 2 vibrations increase - No warning - If throttle 2 is reduced so that N1 < 60%, normal operation is restored

U6KSC00

Cancelling malfunction restores normal operation.

DATE: SEP 1998

Page Page 436 14

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A320 SIMULATED MALFUNCTIONS ENGINES DESCRIPTION IAE

CHAPTER 29: ENGINES IAE MALFUNCTION

: N2 ACCESSORY DRIVE LOST # 1

MALFUNCTION DESCRIPTION

:

CAUSE

: Engine 1 N2 accessory shaft breaking

CONSEQUENCE

:

Engine 1 is previously running.After malfunction activation: - The following equipments are no longer driven: • Lubrification unit • Hydraulic pump • Fuel and oil pumps • IDG • FADEC alternator - N2 indication drops to zero very quickly - Oil pressure drops to minimum value - Engine 1 stops • Single chime sounds • Master caution light comes on • Appropriate message appear on the E/W CRT

U6KSC00

Cancelling malfunction restores normal operation

DATE: SEP 1998

Page Page 437 15

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A320 SIMULATED MALFUNCTIONS ENGINES DESCRIPTION IAE

CHAPTER 29: ENGINES IAE MALFUNCTION

: N2 ACCESSORY DRIVE LOST # 2

MALFUNCTION DESCRIPTION

:

CAUSE

: Engine 2 N2 accessory drive lost

CONSEQUENCE

:

Engine 2 is previously running. After malfunction activation: - The following equipments are no longer driven: • Lubrification unit • Hydraulic pump • Fuel and oil pumps • IDG • FADEC alternator - N2 indication drops to zero very quickly - Oil pressure drops to minimum value - Engine 2 stops • Single chime sounds • Master caution light comes on • Appropriate messages appear on the E/W CRT

U6KSC00

Cancelling malfunction restores normal operation.

DATE: SEP 1998

Page Page 438 16

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS ENGINES DESCRIPTION IAE

CHAPTER 29: ENGINES IAE MALFUNCTION

: HOT START # 1

MALFUNCTION DESCRIPTION

:

CAUSE

: Faulty starter

CONSEQUENCE

:

- During start sequence: • N2 acceleration is slower than normal • EGT acceleration is higher than normal - As soon as a too high EGT variation vs time is detected by FADEC, and if flight phase 1, 2, 6, 9 or 10: • Single chime sounds • Master caution light comes on • Appropriate message appears on the E/W CRT • “ENGINE” page appears on the SYS CRT - Engine “FAULT” light comes on - FADEC automatically shuts-off the HP fuel valve and stops ignition. - FADEC starts a dry crank on engine 1 for 45 seconds, then aborts start procedure.

U6KSC00

Cancelling malfunction restore normal operation.

DATE: SEP 1998

Page Page 439 17

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A320 SIMULATED MALFUNCTIONS ENGINES DESCRIPTION IAE

CHAPTER 29: ENGINES IAE MALFUNCTION

: HOT START # 2

MALFUNCTION DESCRIPTION

:

CAUSE

: Higher initial fuel flow

CONSEQUENCE

:

- During start sequence: • Fuel flow is higher than normal • N2 acceleration is slower than normal • EGT acceleration is higher than normal - As soon as a too high EGT variation vs time is detected by FADEC, and if flight phase 1,2,6,9 or 10: • Single chime sounds • Master Caution light comes on • Appropriate message appears on the E/W CRT • “ENGINE” page appears on the SYS CRT. - Engine “FAULT” light comes on. - FADEC automatically shuts-off the HP fuel valve and stops ignition. - FADEC starts a dry crank on engine 2 for 45 seconds, then aborts start procedure.

U6KSC00

Cancelling malfunction restores normal operation.

DATE: SEP 1998

Page Page 440 18

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A320 SIMULATED MALFUNCTIONS ENGINES DESCRIPTION IAE

CHAPTER 29: ENGINES IAE MALFUNCTION

: REVERSER STUCK # 1

MALFUNCTION DESCRIPTION

:

CAUSE

: Failure of the reverser system

CONSEQUENCE

:

1 - If the malfunction is inserted with reverse retracted, they can’t be deployed. If not flight phase 3, 4, 5: • Appropriate messages appear on the E/W CRT. • Engine is set automatically to reverse idle. 2 - If the malfunction is inserted with reverse deployed, they can’t be retracted. If not flight phase 3, 4, 5: • Appropriate messages appear on the E/W CRT. • Engine is set automatically to reverse idle. 3 - If the malfunction is inserted during reverse deployment Amber REV indication remain in view at EPR indication. If not flight phase 3, 4, 5: • Appropriate message appears on the E/W CRT. - Engine stays to reverse idle.

U6KSC00

Cancelling malfunction restores normal operation.

DATE: SEP 1998

Page Page 441 19

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A320 SIMULATED MALFUNCTIONS ENGINES DESCRIPTION IAE

CHAPTER 29: ENGINES IAE MALFUNCTION

: REVERSER STUCK # 2

MALFUNCTION DESCRIPTION

:

CAUSE

: Failure of the reverser system

CONSEQUENCE

:

1 - If the malfunction is inserted with reverse retracted, they can’t be deployed. If not flight phase 3,4,5: • Appropriate messages appear on the E/W CRT • Engine is set automatically to reverse idle. 2 - If the malfunction is inserted with reverse deployed, they can’t be retracted. If not flight phases 3, 4 or 5: • Appropriate messages appear on the E/W CRT • Engine is set automatically to reverse idle. 3 - If the malfunction is inserted during deployment, amber REV indication remain in view at EPR indication. If not flight phase 3, 4 or 5: • Appropriate messages appear on the E/W CRT - Engine stays at reverse idle.

U6KSC00

Cancelling malfunction restores normal operation.

DATE: SEP 1998

Page Page 442 20

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A320 SIMULATED MALFUNCTIONS ENGINES DESCRIPTION IAE

CHAPTER 29: ENGINES IAE MALFUNCTION

: HUNG START # 1

MALFUNCTION DESCRIPTION

:

CAUSE

: Fuel flow control failure

CONSEQUENCE

:

- During start sequence: • As soon as engine is ignited (EGT increasing), FADEC checks dN2/dt value and detects a hung start when this value is considered as insufficient to insure a correct start. - Whatever the start sequence is: If flight phases 1, 2, 6, 9 or 10: • Single chime sounds • Master caution light comes on • Appropriate messages appear on the E/W CRT • “ENGINE” page appears on the SYS CRT • Ignition is stopped, HP fuel valve is closed and engine “FAULT” light is lit on. • Then a dry crank is performed during 45 seconds, and at last starter valve is closed.

U6KSC00

Cancelling malfunction restores normal operation.

DATE: SEP 1998

Page Page 443 21

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A320 SIMULATED MALFUNCTIONS ENGINES DESCRIPTION IAE

CHAPTER 29: ENGINES IAE MALFUNCTION

: HUNG START # 2

MALFUNCTION DESCRIPTION

:

CAUSE

: Faulty starter

CONSEQUENCE

:

- During start sequence: • As soon as engine is ignited (EGT increasing), FADEC checks dN2/dt value and detects a hung start when this value is considered as insufficient to insure a correct start. - Whatever the start sequence is: If flight phases 1, 2, 6, 9 or 10: • Single chime sounds • Master caution light comes on • Appropriate messages appear on the E/W CRT • “ENGINE” page appears on the SYS CRT • Ignition is stopped, HP fuel valve is closed and engine “FAULT” light is lit on. • Then a dry crank is performed during 45 seconds, and last starter valve is closed.

U6KSC00

Cancelling malfunction restores normal operation.

DATE: SEP 1998

Page Page 444 22

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A320 SIMULATED MALFUNCTIONS ENGINES DESCRIPTION IAE

CHAPTER 29: ENGINES IAE MALFUNCTION

: N1 ROTOR SEIZED # 1

MALFUNCTION DESCRIPTION

:

CAUSE

: N1 rotor seized during start up

CONSEQUENCE

:

- Engine 1 N1 speed remains at zero - Other parameter increase normally. - Engine “FAULT” light comes on when N2 > 33%. - If flight phases 2, 3, 6: • Single chime sounds • Master caution light comes on. • Appropriate messages appear on the E/W CRT • “ENGINE” page appears on the SYS CRT - Dry crank is automatically performed during 45 seconds, then starter valve is closed.

U6KSC00

Cancelling malfunction restores normal operation.

DATE: SEP 1998

Page Page 445 23

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS ENGINES DESCRIPTION IAE

CHAPTER 29: ENGINES IAE MALFUNCTION

: N1 ROTOR SEIZED # 2

MALFUNCTION DESCRIPTION

:

CAUSE

: N1 rotor seized during start up

CONSEQUENCE

:

- Engine 2 N1 speed remains at zero - Other parameters increase normally. - Engine “FAULT” light comes on when N2 > 33%. - If flight phase 2, 3, 6: • Single chime sounds. • Master caution light comes on. • Appropriate messages appear on the E/W CRT. • “ENGINE” page appears on the SYS CRT. - Dry crank is automatically performed during 45 seconds, then starter valve is closed.

U6KSC00

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DATE: SEP 1998

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CHAPTER 29: ENGINES IAE MALFUNCTION

: START VALVE STUCK # 1

MALFUNCTION DESCRIPTION

:

CAUSE

: Start valve stuck in position

CONSEQUENCE

:

1 - Insert failure before start procedure • All engine 1 indications remain unchanged • Whatever the start sequence is: If flight phases 1, 2, 6, 9 or 10: • Single chime sounds • Master caution light comes on • Appropriate messages appear on the E/W CRT • “ENGINE” page appears on the SYS CRT 2 - Insert failure during start procedure Start sequence is normally proceeded until N2 reaches 43% • The start valve remains opened • Whatever the start sequence is: If flight phases 1, 2, 6, 9 or 10: • Single chime sounds • Master caution light comes on. • Appropriate messages appear on the E/W CRT. • “ENGINE” page appears on the SYS CRT.

U6KSC00

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CHAPTER 29: ENGINES IAE MALFUNCTION

: START VALVE STUCK # 2

MALFUNCTION DESCRIPTION

:

CAUSE

: Start valve stuck in position

CONSEQUENCE

:

1 - Insert failure before start procedure • All Engine 2 indications remain unchanged • Whatever the start sequence is: If flight phases 1, 2, 6, 9 or 10: • Single chime sounds • Master caution light comes on • Appropriate messages appear on E/W CRT • “ENGINE” page appears on SYS CRT 2 - Insert failure during start procedure Start sequence is normally proceeded until N2 reaches 43%. • The start valve remains opened. • Whatever the start sequence is: If flight phases 1, 2, 6, 9 or 10: • Single chime sounds • Master caution light comes on • Appropriate messages appear on E/W CRT • “ENGINE” page appears on SYS CRT

U6KSC00

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DATE: SEP 1998

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CHAPTER 29: ENGINES IAE MALFUNCTION

: OIL FILTER CLOGGED (ENGINE 1) # 1

MALFUNCTION DESCRIPTION

:

CAUSE

: Clogging of oil filter

CONSEQUENCE

:

If the aircraft isn’t in flight phases 4, 5, 7, 8: - Appropriate messages appear on the E/W CRT. - “ENGINE” page appears on the SYS CRT. - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

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DATE: SEP 1998

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CHAPTER 29: ENGINES IAE MALFUNCTION

: IGNITION FAIL # 1

MALFUNCTION DESCRIPTION

:

CAUSE

: Loss of electrical supply for system ignitor plugs

CONSEQUENCE

:

If automatic start sequence, FADEC 1 tries to start engine 1 according to the following sequence: - Igniter indication A or B (alternate selection) comes on the ENGINE page when N2 = > 15%. (A TOP is to be taken on the on board clock when N2=15%). - At (top + 20 sec): (*) • Engine 1 “FAULT” light comes on ; dry crank is started. • If flight phases 1, 2, 6, 9 or 10: • Single chime sounds • Master caution light comes on • Appropriate messages appear on E/W CRT • “ENGINE” page appears on SYS CRT - At (TOP + 65 sec), dry crank stops. (**) Cancelling malfunction restores normal operation. N.B. Failure on, engine 1 can’t be started. (*) TOP + 30 sec in flight.

U6KSC00

(**) TOP + 75 sec in flight.

DATE: SEP 1998

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CHAPTER 29: ENGINES IAE MALFUNCTION

: REVERSER UNLOCKED # 1

MALFUNCTION DESCRIPTION

:

CAUSE

: Faulty switch operation

CONSEQUENCE

:

- On ground: • The amber REV indication comes on - In flight: • The amber REV indication comes on flashing for 9 seconds then remains steady. - If flight phases NO 2, 3, 4, 5, 6 or 7: • Single chime sounds • Master caution light comes on • Appropriate messages appear on the E/W CRT

U6KSC00

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DATE: SEP 1998

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CHAPTER 29: ENGINES IAE MALFUNCTION

: SERIOUS ENG DAMAGE WITH EXTINGUIS. FIRE # 1

MALFUNCTION DESCRIPTION

:

CAUSE

: Compressor stall + engine 1 fire

CONSEQUENCE

:

As soon as the failure is inserted, EPR, N1, N2, EGT & Fuel flow move erratically lower or upper than in normal operation 3 seconds later: • Engine 1 Fire • Engine flame out. - On fire panel, “ENG 1 FIRE” light comes on - On central pedestal (115 VU), master ENG 1 “FIRE” light comes on - Nacelle temperature increases until fire stops Ecam displays consequences Whatever the flight phase is: • Audio CRC sounds • Master “Warn” light comes on • Appropriate messages (nature of failure and actions to be performed) appear on E/W CRT • “ENGINE” page appears on SYS CRT Actions Push the ENGINE 1 FIRE P/B (FIRE PANEL) • After a few seconds, engine 1 shuts down • On fire panel, AGENTS ENG 1 “SQUIB” lights come on • All warnings remain on • CRC stops Push the AGENT1 ENG1 push button (FIRE PANEL) • After 3 seconds, AGENT1 “DISH” light comes on

U6KSC00

• After 10 seconds, all fire warnings remain on

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CHAPTER 29: ENGINES IAE

Push the AGENT2 ENG1 push button (FIRE PANEL) • After 3 seconds, AGENT2 “DISH” light comes on • After 10 seconds, all fire warnings disappear • If activated: Master “Warn” light goes out In order to recover normal operation: - Cancel malfuntion - Release the “ENG1 FIRE” pushbutton (FIRE PANEL)

U6KSC00

On instructor station set the AGENT FIRE RESET

DATE: SEP 1998

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CHAPTER 29: ENGINES IAE MALFUNCTION

: SERIOUS ENG DAMAGE WITH EXTINGUIS. FIRE #2

MALFUNCTION DESCRIPTION

:

CAUSE

: Compressor stall + Engine 2 fire

CONSEQUENCE

:

As soon as the failure is inserted, EPR, N1, N2, EGT & Fuel flow move erratically lower or upper than in normal operation 3 seconds later: • Engine 2 Fire • Engine flame out. - On fire panel, “ENG 2 FIRE” light comes on - On central pedestal (115 VU), master ENG 2 “FIRE” light comes on - Nacelle temperature increases until fire stops Ecam displays consequences Whatever the flight phase is: • Audio CRC sounds • Master “Warn” light comes on • Appropriate messages (nature of failure and actions to be performed) appear on E/W CRT • “ENGINE” page appears on SYS CRT Actions Push the ENGINE 2 FIRE P/B (FIRE PANEL) • After a few seconds, engine 2 shuts down • On fire panel, AGENTS ENG 2 “SQUIB” lights come on • All warnings remain on • CRC stops Push the AGENT1 ENG2 push button (FIRE PANEL) • After 3 seconds, AGENT1 “DISH” light comes on

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• After 10 seconds, all fire warnings remain on

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CHAPTER 29: ENGINES IAE

Push the AGENT1 ENG2 push button (FIRE PANEL) • After 3 seconds, AGENT1 “DISH” light comes on • After 10 seconds, all fire warnings remain on • If activated: Master “Warn” light goes out. In order to recover normal operation: - Cancel malfunction - Release the ENG2 FIRE" pushbutton (FIRE PANEL)

U6KSC00

On instructor station set the AGENT FIRE RESET

DATE: SEP 1998

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CHAPTER 29: ENGINES IAE MALFUNCTION

: SERIOUS ENG DAMAGE WITH UNEXTING FIRE # 1

MALFUNCTION DESCRIPTION

:

CAUSE

: Compressor stall + engine 1 fire

CONSEQUENCE

:

As soon as the failure is inserted, EPR, N1, N2, EGT & Fuel Flow move erratically 3 seconds later: • Engine 1 flame out • Engine 1 fire - See failure “Engine 1 flame out” - Then failure “Engine 1 unextinguishable fire” for consequences.

U6KSC00

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DATE: SEP 1998

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CHAPTER 29: ENGINES IAE MALFUNCTION

: SERIOUS ENG DAMAGE WITH UNEXTING FIRE # 2

MALFUNCTION DESCRIPTION

:

CAUSE

: Compressor stall + engine 2 fire

CONSEQUENCE

:

As soon as the failure is inserted, N1, N2, EGT & Fuel Flow move erratically lower or upper than in normal operation 3 seconds later: • Engine 2 fire - See failure “UNEXTINGUISHABLE FIRE # 2" for consequences.

U6KSC00

Cancelling malfunction restores normal operation.

DATE: SEP 1998

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CHAPTER 29: ENGINES IAE MALFUNCTION

: SERIOUS ENG DAMAGE WITH PARTIAL PWR LOSS # 1

MALFUNCTION DESCRIPTION

:

CAUSE

: Compressor stall

CONSEQUENCE

:

As soon as the failure is inserted, EPR, N1, N2, EGT & fuel flow move erratically lower or upper than in normal operation. • Engine 1 vibrations increase. • No warning • Sound effects. 3 seconds later: • Compressor stall disappears. • Engine performances remain lower than in normal operation. - If throttle 1 is reduced, normal vibrations value is restored.

U6KSC00

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CHAPTER 29: ENGINES IAE MALFUNCTION

: SERIOUS ENG DAMAGE WITH PARTIAL PWR LOSS # 2

MALFUNCTION DESCRIPTION

:

CAUSE

: Compressor stall

CONSEQUENCE

:

As soon as the failure is inserted, EPR, N1, N2, EGT & Fuel Flow move erratically • Engine 2 vibrations increase • No warning • Sound effects 3 seconds later: • Compressor stall disappears. - If throttle 2 is reduced, normal vibrations value is restored.

U6KSC00

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DATE: SEP 1998

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CHAPTER 29: ENGINES IAE MALFUNCTION

: THROTTLE INOPERATIVE (POWER STUCK) # 1

MALFUNCTION DESCRIPTION

:

CAUSE

: TLA signal frozen

CONSEQUENCE

:

Engine 1 performances remain constant (at the values reached when the failure is inserted), whatever the throttle position is. • No warning.

U6KSC00

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CHAPTER 29: ENGINES IAE MALFUNCTION

: ENGINE DETACHED # 1

MALFUNCTION DESCRIPTION

:

CAUSE

: Engine 1 detached

CONSEQUENCE

:

N1 and N2 vibrations increase then flash (green) on the “CRUISE” or “ENGINE” page (if selected on the SYS CRT) A few seconds later: • All engine 1 indications become invalid on the upper Ecam display unit • Engine 1 oil quantity and oil pressure drop to zero on the lower Ecam display unit • Engine 1 oil temperature and nacelle temperature are replaced by amber crosses on the lower Ecam display unit. • Aerodynamic, Fuel, Elec, Hydraulic effects. If flight phases 2, 3, 4, 5, 6, 7, 8 or 9: • Continuous repetitive chime sounds • Master warning light comes on • Appropriate messages appear on the E/W CRT • “ENGINE” page appears on the SYS CRT - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected)

U6KSC00

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DATE: SEP 1998

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CHAPTER 29: ENGINES IAE MALFUNCTION

: ENGINE DETACHED # 2

MALFUNCTION DESCRIPTION

:

CAUSE

: Engine 2 detached

CONSEQUENCE

:

N1 and N2 vibrations increase then flash (green) on the “CRUISE” or “ENGINE” page (if selected on the SYS CRT). A few seconds later: • All engine 2 indications become invalid on the upper Ecam display unit. • Engine 2 oil quantity and oil pressure drop to zero on the lower ecam display unit • Engine 2 oil temperature and nacelle temperature are replaced by amber crosses on the lower ecam display unit.Aerodynamic, Fuel, Elec, Hydraulic effects If flight phases 2, 3, 4, 5, 6, 7, 8 or 9: • Audio CRC sounds • Master warning light comes on • Appropriate messages appear on the E/W CRT • “ENGINE” page appears on the SYS CRT - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).

U6KSC00

Cancelling malfunction restores normal operation.

DATE: SEP 1998

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CHAPTER 29: ENGINES IAE MALFUNCTION

: FUEL HP VALVE INOPERATIVE # 2

MALFUNCTION DESCRIPTION

:

CAUSE

: HP valve locked

CONSEQUENCE

:

- During start sequence: If automatic start, engine 2 “FAULT” light comes on 2 seconds after N2 reaches 15%. If manual start, engine 2 “FAULT” light comes on as soon as master lever 2 is selected on. - Whatever the start sequence is: If flight phases 1, 2, 6, 9 or 10: • Single chime sounds • Master caution light comes on • Appropriate messages appear on the E/W CRT • “ENGINE” page appears on the SYS CRT

U6KSC00

Cancelling malfunction restores normal operation.

DATE: SEP 1998

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CHAPTER 29: ENGINES IAE MALFUNCTION

: EIU FAIL # 2

MALFUNCTION DESCRIPTION

:

CAUSE

: EIU 2 failure

CONSEQUENCE

:

- Engine 2 can not be started if not running -

A/THR is desactivated if previously on Engine 2 reverser sequence can not be proceeded Continuous relight is selected on engine 2 if mach 0.18 Only flight idle can be obtained on engine 2

If flight phase 2, 6 or 9: • Single chime sounds • Master caution light comes on • Appropriate messages appear on the E/W CRT • Engine 2 oil temperature and nacelle temperature are replaced by amber crosses on the “ENGINE” one

U6KSC00

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DATE: SEP 1998

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CHAPTER 29: ENGINES IAE MALFUNCTION

: FUEL FILTER CLOGGING # 1

MALFUNCTION DESCRIPTION

:

CAUSE

: Clogging of fuel filter

CONSEQUENCE

:

If the aircraft isn’t in flight phases 4, 5, 7, 8 • Appropriate messages appear on the E/W CRT • “ENGINE” page appears on the SYS CRT

U6KSC00

Cancelling malfunction restores normal operation.

DATE: SEP 1998

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CHAPTER 29: ENGINES IAE MALFUNCTION

: IDLE CONTROL FAIL # 1

MALFUNCTION DESCRIPTION

:

CAUSE

: EIU 1 failure

CONSEQUENCE

:

- Only flight idle can be obtained on engine 1 - No warning

U6KSC00

Cancelling malfunction restores normal operation

DATE: SEP 1998

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CHAPTER 29: ENGINES IAE MALFUNCTION

: TLA RESOLVER INEQUALITY # 1

MALFUNCTION DESCRIPTION

:

CAUSE

: TLA resolver failure

CONSEQUENCE

:

On ground, whatever the throttle position is: • Engine 1 performances are set to idle • Reverse is commanded to restow if previously deployed In flight: • In FLEX-TO or TO/GA modes, engine 1 performances don’t change. • In other modes, MAX CONT mode is selected • If A/THR is selected, thrust is managed between IDLE & MCT On ground or in flight and if flight phase 1, 2, 3, 6, 7, 9 or 10: • Engine 2 stays in normal operating mode. • Single chime sounds • Master caution light comes on • Appropriate messages appear on the E/W CRT

U6KSC00

Cancelling malfunction restores normal operation.

DATE: SEP 1998

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CHAPTER 29: ENGINES IAE MALFUNCTION

: MAN START FAULT # 1

MALFUNCTION DESCRIPTION

:

CAUSE

: Disagree between Master Switch position and HPSOV position

CONSEQUENCE

:

During start sequence: If automatic start, engine 1 “FAULT” light comes on 2 seconds after N2 reaches 15 %. If manual start, engine 1 “FAULT” light comes on as soon as master lever 1 is selected on. Whatever the start sequence is: If flight phases 1, 2, 6, 9, 10: • Single chime sounds • Master caution light comes on • Appropriate messages appear on the E/W CRT • “ENGINE” page appears on the SYS CRT.

U6KSC00

Cancelling malfunction restores normal operation.

DATE: SEP 1998

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CHAPTER 29: ENGINES IAE MALFUNCTION

: REVERSER DEPLOYED # 1

MALFUNCTION DESCRIPTION

:

CAUSE

: Reverser failure

CONSEQUENCE

:

- On ground: Engine 1 performances are set to idle • If the A/C is in flight phase 3 or 4: • Appropriate messages appear on the E/W CRT • If throttle lever angle value is lower than zero, normal engine 1 reverser sequence is proceeded. In flight: • The amber REV indication comes on flashing for 9 seconds then remains steady. • Engine 1 performances are set to idle. If flight phases 5, 6 or 7: • Single chime sounds • Master caution light comes on • Appropriate message appear on the E/W CRT

U6KSC00

Cancelling malfunction restores normal operation.

DATE: SEP 1998

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CHAPTER 29: ENGINES IAE MALFUNCTION

: AUTOMATIC REVERSION TO N1 RATED MODE # 1

MALFUNCTION DESCRIPTION

:

CAUSE

: FADEC loss of P2 information

CONSEQUENCE

:

- On the E/W CRT: • All ENG 1 EPR indications are lost • N1 MAX and N1 TLA indications come on ENG 1 N1 indicator • N1 limit is available on THR limit indicator - A/THR functions are lost. - Alpha floor protection is lost. - Flexible take off is no more allowed. - If the aircraft is in flight phase 1, 2, 3, 6, 7, 8, 9 or 10: • Audio single chime sounds • Master caution light illuminates • Appropriate message appears on the E/W CRT (refer to FWC sheet)

U6KSC00

- Cancelling the malfunction restores normal operation providing ENG 1 N1 MODE P/B has been depressed on the overhead panel. - Appropriate messages will be available on MCDU (CMC function when CMC maintenance option selected).

DATE: SEP 1998

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CHAPTER 29: ENGINES IAE MALFUNCTION

: AUTOMATIC REVERSION TO N1 UNRATED MODE # 2

MALFUNCTION DESCRIPTION

:

CAUSE

: FADEC loss of P2 and T2 informations.

CONSEQUENCE

:

- On the E/W CRT: • All ENG 2 EPR indications are lost • N1 MAX and N1 TLA indications doesn’t come ENG 2 N1 indicator • N1 limit is available on THR limit indicator (ENG 1 still valid or operating in N1 rated mode) - A/THR functions are lost. - Alpha floor protection is lost. - Flexible take off is no more allowed. - If the aircraft is in flight phase 1, 2, 3, 6, 7, 8, 9 or 10: • Audio single chime sounds • Master caution light illuminates • Appropriate message appears on the E/W CRT(refer to FWC sheet)

U6KSC00

- Cancelling the malfunction restores normal operation providing ENG 2 N1 MODE P/B has been depressed on the overhead panel. - Appropriate messages will be available on MCDU (CMC function when CMC maintenance option selected).

DATE: SEP 1998

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U6KSC00

THIS PAGE INTENTIONALLY LEFT BLANK

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINES PARAMETERS IAE

CHAPTER 30 - ENGINES PARAMETERS IAE CONTENTS: OIL PRESS (INC/DEC # 1 (psi)) OIL PRESS (INC/DEC # 2 (psi)) OIL QUANTITY (INC/DEC # 1 (qt)) OIL QUANTITY (INC/DEC # 2 (qt)) E G T (INC/DEC # 1 (degC)) E G T (INC/DEC # 2 (degC)) N 1 (INC/DEC # 1 (%)) N 1 (INC/DEC # 2 (%)) N 2 (INC/DEC # 1 (%)) N2 (INC/DEC # 2 (%)) N1 (INDICATION FAULT # 1) N2 (INDICATION FAULT # 2) OIL TEMP (INC/DEC # 1 (degC)) FUEL FLOW (INC/DEC # 1 (kg/h)) NACELLE TEMP (INC/DEC # 1 (degC)) E P R (INDICATION FAULT # 1) E P R (INDICATION FAULT # 2) E P R (INC/DEC # 1) E P R (INC/DEC # 2) VIBRATIONS N1 (INC/DEC # 1 (U)) VIBRATIONS N2 (INC/DEC # 2 (U)) VIBRATIONS N1 PEAK (# 1 (%/U)) VIBRATIONS N1 PEAK (# 2 (%/U)) VIBRATIONS N2 PEAK (# 1 (%/U))

U6KSC00

VIBRATIONS N2 PEAK (# 2 (%/U))

DATE: SEP 1998

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CHAPTER 30: ENGINES PARAMETERS IAE MALFUNCTION

: OIL PRESS INC/DEC # 1 (psi)

PARAMETER

: PARAMETER: ENGINE 1 OIL PRESSURE

MIN VALUE

: MIN VALUE: 0 psi MAX VALUE: 400 psi CHANGE RATE: 10 psi/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Oil pump failure or oiljet clogging

CONSEQUENCE

:

- Oil pressure indication is normally green -

As soon as oil pressure reaches 390 psi, oil pressure indication flashes (green) on the “ENGINE” page. Oil pressure advisory reset is possible if oil pressure decreases below 385 psi. As soon as oil pressure drops down 80 psi, oil pressure indication turns on the “ENGINE” page. Oil pressure advisory reset is possible if oil pressure increases above 85 psi. As soon as engine oil pressure drops down 60 psi, oil pressure indication turns red.

- If flight phases 2, 3, 4, 5, 6, 7, 8 or 9: • Audio CRC sounds • Master warning light comes on • Appropriate messages appear on the E/W CRT • “ENGINE” page appear on the SYS CRT

U6KSC00

Cancelling malfunction and/or engine oil pressure greater than 85 psi restore normal operation

DATE: SEP 1998

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CHAPTER 30: ENGINES PARAMETERS IAE MALFUNCTION

: OIL PRESS INC/DEC # 2 (psi)

PARAMETER

: PARAMETER: ENGINE 2 OIL PRESSURE

MIN VALUE

: MIN VALUE: 0 psi MAW VALUE: 400 psi CHANGE RATE: 10 psi/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Oil pump failure or oiljet clogging

CONSEQUENCE

:

- Oil pressure indication is normally green -

As soon as oil pressure reaches 390 psi, oil pressure indication flashes (green) on the “ENGINE” page. Oil pressure advisory reset is possible if oil pressure decreases below 385 psi. As soon as oil pressure drops down 80 psi, oil pressure indication turns (amber) on the “ENGINE” page. Oil pressure advisory reset is possible if oil pressure increases above 85 psi. As soon as engine oil pressure drops down 60 psi, oil pressure indication turns red

If flight phases 2, 3, 4, 5, 6, 7, 8 or 9: • Continuous repetitive chime sounds • Master Warning light comes on • Appropriate messages appear on E/W CRT • “ENGINE” page appear on SYS CRT

U6KSC00

Cancelling malfunction and/or engine oil pressure greater than 85 psi restore normal operation

DATE: SEP 1998

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CHAPTER 30: ENGINES PARAMETERS IAE MALFUNCTION

: OIL QUANTITY INC/DEC # 1 (qt)

PARAMETER

: PARAMETER: engine 1 OIL QUANTITY

MIN VALUE

: MIN VALUE: 0 qt MAX VALUE: 23.5 qt CHANGE RATE: 0.5 qt/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Leak in oil circuit

CONSEQUENCE

:

- Oil quantity indication is normally green - As soon as engine oil quantity drops down 5 qt, oil quantity indication flashes (green) on the “ENGINE” page. • Oil pressure decreases • Oil temperature increases - Oil quantity advisory reset is possible if oil quantity increases above 7 qt - If oil pressure and/or oil temperature thresholds are reached: • See corresponding failures Cancelling malfunction restores normal operation.

U6KSC00

N.B. Oil quantity maximum values is limited to initial quantity.

DATE: SEP 1998

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CHAPTER 30: ENGINES PARAMETERS IAE MALFUNCTION

: OIL QUANTITY INC/DEC # 2 (qt)

PARAMETER

: PARAMETER: ENGINE 2 OIL QUANTITY

MIN VALUE

: MIN VALUE: 0 qt MAX VALUE: 23.5 qt CHANGE RATE: 0.5 qt/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Leak in oil circuit

CONSEQUENCE

:

- Oil quantity indication is normally green - As soon as engine oil quantity drops down 5 QT, oil quantity indication flashes (green) on the “ENGINE” page. • Oil pressure decreases • Oil temperature increases - Oil quantity advisory reset is possible if oil quantity increases above 7 QT - If oil pressure and/or oil temperature thresholds are reached: • See corresponding failures Cancelling malfunction restores normal operation

U6KSC00

N.B. Oil quantity maximum value is limited to initial quantity.

DATE: SEP 1998

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINES PARAMETERS IAE

CHAPTER 30: ENGINES PARAMETERS IAE MALFUNCTION

: E G T INC/DEC # 1 (degC)

PARAMETER

: ENGINE 1 EXHAUST GAS TEMPERATURE

MIN VALUE

: SAT MAX VALUE: 1000 degC CHANGE RATE: 10 degC/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Incorrect engine operation

CONSEQUENCE

:

- EGT indication is normally green - If flight phases 1, 2, 3, 5, 6, 7, 9 or 10: - When 610 °C < EGT < 635 °C: • The indication becomes amber - If EGT > 635 C°: • The indication becomes red • Single chime sounds • Master caution light comes on • Appropriate messages appear on the E/W CRT - EGT maximum value is memorized and a small red line is positioned at that value on the indicator. Cancelling malfunction restores normal operation.

U6KSC00

N.B. EGT minimum value is limited to static air temperature.

DATE: SEP 1998

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINES PARAMETERS IAE

CHAPTER 30: ENGINES PARAMETERS IAE MALFUNCTION

: E G T INC/DEC # 2 (degC)

PARAMETER

: ENGINE 2 EXHAUST GAS TEMPERATURE

MIN VALUE

: SAT MAX VALUE: 1000 degC CHANGE RATE: 10 degC/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Incorrect engine operation

CONSEQUENCE

:

- EGT indication is normally green - If flight phases 1, 2, 3, 5, 6, 7, 9 or 10: - When 610 °C < EGT < 635 °C: • The indication becomes amber - If EGT > 635 C°: • The indication becomes red • Single chime sounds • Master caution light comes on • Appropriate messages appear on E/W CRT - EGT maximum value is memorized and a small red line is positioned at that value on the indicator Cancelling malfunction restores normal operation

U6KSC00

N.B. EGT minimum value is limited to static air temperature.

DATE: SEP 1998

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINES PARAMETERS IAE

CHAPTER 30: ENGINES PARAMETERS IAE MALFUNCTION

: N 1 INC/DEC # 1 (%)

PARAMETER

: ENGINE 1 LOW TURBINE SPEED RATEE

MIN VALUE

: 0 % MAX VALUE: 120 % CHANGE RATE: 10%

MALFUNCTION DESCRIPTION

:

CAUSE

: Incorrect indication

CONSEQUENCE

:

- N1 indication is normally green - If flight phases 1, 2, 3, 5, 6, 7, 9 or 10: - When N1LIM+1% < N1< 100% and if N1 backup mode (rated) is active: • The analog indication becomes amber - If N1 > 100%, whatever the mode is (EPR or N1): • The analog & digital indications become red - If N1 > 100 %: • All indications stay red • Single chime sounds • Master caution light comes on • Appropriate messages appear on the E/W CRT - If N1 overrides 100 %, N1 maximum value is memorized and a small red line is positioned at that value on the indicator.

U6KSC00

Cancelling malfunction restores normal operation.

DATE: SEP 1998

Page Page480 8

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINES PARAMETERS IAE

CHAPTER 30: ENGINES PARAMETERS IAE MALFUNCTION

: N 1 INC/DEC # 2 (%)

PARAMETER

: ENGINE 2 LOW TURBINE SPEED

MIN VALUE

: 0 % MAX VALUE: 120 % CHANGE RATE: 10%/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Incorrect indication

CONSEQUENCE

:

- N1 indication is normally green - If flight phases 1, 2, 3, 5, 6, 7, 9 or 10: - when N1LIM+1% < N1 100%, whatever the mode is (EPR or N1): • The analog & digital indications become red - If N1 > 100%: • All indication stay red • Single chime sounds • Master caution light comes on • Appropriate messages appear on E/W CRT - If N1 overrides 100%, N1 maximum value is memorized and a small red line is positioned at that value on the indicator

U6KSC00

Cancelling malfunction restores normal operation

DATE: SEP 1998

Page Page481 9

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINES PARAMETERS IAE

CHAPTER 30: ENGINES PARAMETERS IAE MALFUNCTION

: N 2 INC/DEC # 1 (%)

PARAMETER

: ENGINE 1 HIGH TURNBINE SPEED RATE

MIN VALUE

: 0 % MAX VALUE: 120 % CHANGE RATE: 10%/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Incorrect indication

CONSEQUENCE

:

- N2 indication is normally green - If flight phases 1, 2, 3, 5, 6, 7, 9 or 10 - When N2 >100 %: • The indication becomes red • Single chime sounds • Master caution light comes on • Appropriate messages appear on the E/W CRT - If N2 has overridden 100%, a red cross appears near the N2 indication and remains all the flight.

U6KSC00

Cancelling malfunction restores normal operation.

DATE: SEP 1998

Page Page 482 10

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINES PARAMETERS IAE

CHAPTER 30: ENGINES PARAMETERS IAE MALFUNCTION

: N 2 INC/DEC # 2 (%)

PARAMETER

: ENGINE 2 HIGH TURBINE SPEED

MIN VALUE

: 0 % MAX VALUE: 120 % CHANGE RATE: 10%/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Incorrect indication

CONSEQUENCE

:

- N2 indication is normally green - If flight phases 1, 2, 3, 5, 6, 7, 9 or 10: - When N2 > 100%: • The indication becomes red • Single chime sounds • Master caution light comes on • Appropriate messages appear on E/W CRT - If N2 has overridden 100%, a red cross appears near the N2 indication and remains all the flight

U6KSC00

Cancelling malfunction restores normal operation

DATE: SEP 1998

Page Page 483 11

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINES PARAMETERS IAE

CHAPTER 30: ENGINES PARAMETERS IAE MALFUNCTION

: N1 INDICATION FAULT # 1

MALFUNCTION DESCRIPTION

:

CAUSE

: Analog and Digital signals of N1 lost by ECAM

CONSEQUENCE

:

- Engine 1 N1 analog indications are replaced by amber circles on the E/W CRT. - Engine 1 N1 digital indication is replaced by amber crosses on the E/W CRT.

U6KSC00

Cancelling the malfunction restores normal operation.

DATE: SEP 1998

Page Page 484 12

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINES PARAMETERS IAE

CHAPTER 30: ENGINES PARAMETERS IAE MALFUNCTION

: N2 INDICATION FAULT # 2

MALFUNCTION DESCRIPTION

:

CAUSE

: Digital signal of N2 lost by ECAM

CONSEQUENCE

:

- Engine 2 N2 digital indication is replaced by two amber crosses on the E/W CRT.

U6KSC00

Cancelling malfunction restores normal operation.

DATE: SEP 1998

Page Page 485 13

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINES PARAMETERS IAE

CHAPTER 30: ENGINES PARAMETERS IAE MALFUNCTION

: OIL TEMP INC/DEC # 1 (degC)

PARAMETER

: ENGINE 1 OIL TEMPERATURE

MIN VALUE

: SAT MAX VALUE: 200 degC CHANGE RATE: 2 degC/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Incorrect engine operation

CONSEQUENCE

:

- Oil temperature indication is normally green -

As soon as engine oil temperature reaches 156 °C, oil temperature indication flashes (green) on the “ENGINE” page Oil temperature advisory reset is possible if oil temperature decreases below 150 °C. If engine oil temperature advisory lasts more than 900 s (1/4 h) or if engine oil temperature exceeds 170 °C: Oil indication becomes amber,

If flight phases 1, 2, 3, 6, 9 or 10: • Single chime sounds • Master caution light comes on • Appropriate messages appear on the E/W CRT • “ENGINE” page appears on the SYS CRT - Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected). - When CFDS is operating in MENU mode and BITE TSD (Trouble Shooting Data) function is selected, the snapshot data corresponding to malfunction are displayed on the MCDU. (when BITE TSD maintenance option selected) Cancelling malfunction restores normal operation

U6KSC00

N.B. Oil temperature minimum value is limited to static air temperature

DATE: SEP 1998

Page Page 486 14

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINES PARAMETERS IAE

CHAPTER 30: ENGINES PARAMETERS IAE MALFUNCTION

: FUEL FLOW INC/DEC # 1 (kg/h)

PARAMETER

: ENGINE 1 FUEL FLOW

MIN VALUE

: 0 kg/h MAX VALUE: 5000 kg/h CHANGE RATE: 500 kg/h/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Incorrect engine operation

CONSEQUENCE

:

If fuel flow increases, all engine 1 parameters increase too If fuel flow decreases, all engine 1 parameters decrease too

U6KSC00

Cancelling malfunction restores normal operation.

DATE: SEP 1998

Page Page 487 15

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINES PARAMETERS IAE

CHAPTER 30: ENGINES PARAMETERS IAE MALFUNCTION

: NACELLE TEMP INC/DEC # 1 (degC)

PARAMETER

: NACELLE TEMPERATURE

MIN VALUE

: SAT MAX VALUE: 320 degC CHANGE RATE: 5 degC/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Incorrect engine operation

CONSEQUENCE

:

- Nacelle temperature is indicated only when value exceeds advisory thresold (320°C) Cancelling malfunction restores normal operation

U6KSC00

Complementary data: NACELLE TEMP minimum value is limited to SAT value.

DATE: SEP 1998

Page Page 488 16

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINES PARAMETERS IAE

CHAPTER 30: ENGINES PARAMETERS IAE MALFUNCTION

: E P R INDICATION FAULT # 1

MALFUNCTION DESCRIPTION

:

CAUSE

: Analog and Digital signals of EPR lost by ECAM

CONSEQUENCE

:

- Engine 1 EPR analog indications are replace by amber circle on the E/W CRT - Engine 1 EPR numerical indication is replaced by amber crosses on the E/W CRT Cancelling malfunction restores normal operation

U6KSC00

N.B. This malfunction have no effect when the N1 backup mode is selected.

DATE: SEP 1998

Page Page 489 17

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINES PARAMETERS IAE

CHAPTER 30: ENGINES PARAMETERS IAE MALFUNCTION

: E P R INDICATION FAULT # 2

MALFUNCTION DESCRIPTION

:

CAUSE

: Analog and digital signals of EPR lost by ECAM

CONSEQUENCE

:

- Engine 2 EPR analog indications are replaced by amber circle on the E/W CRT - Engine 2 EPR numerical indication is replaced by amber crosses on the E/W CRT Cancelling the malfunction restores normal operation

U6KSC00

N.B. This malfunction have no effect when the N1 backup mode is selected.

DATE: SEP 1998

Page Page 490 18

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINES PARAMETERS IAE

CHAPTER 30: ENGINES PARAMETERS IAE MALFUNCTION

: E P R INC/DEC # 1

PARAMETER

: ENGINE 1 PRESSURE RATIO

MIN VALUE

: 0.6 MAX VALUE: 1.8 CHANGE RATE: 0.1/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Incorrect indication

CONSEQUENCE

:

- EPR indication is always green, and limited to 1.65 (high) 0.95 (low) Cancelling malfunction restores normal operation

U6KSC00

N.B. This malfunction have no effect when N1 backup mode is selected.

DATE: SEP 1998

Page Page 491 19

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINES PARAMETERS IAE

CHAPTER 30: ENGINES PARAMETERS IAE MALFUNCTION

: E P R INC/DEC # 2

PARAMETER

: ENGINE 2 PRESSURE RATIO

MIN VALUE

: 0.6 MAX VALUE: 1.8 CHANGE RATE: 0.1/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Incorrect indication

CONSEQUENCE

:

- EPR indication is always green and limited to 1.65 (high) 0.95 (low) Cancelling malfunction restores normal operation

U6KSC00

N.B. This malfunction have no effect when the N1 backup mode is selected.

DATE: SEP 1998

Page Page 492 20

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINES PARAMETERS IAE

CHAPTER 30: ENGINES PARAMETERS IAE MALFUNCTION

: VIBRATIONS N1 INC/DEC # 1 (U)

PARAMETER

: ENGINE 1 LOW TURBINE SPEED VIBRATIONS

MIN VALUE

: 0 U MAX VALUE: 10 U CHANGE RATE: 0.5 U/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Incorrect engine operation

CONSEQUENCE

:

- N1 vibrations indication is normally green If N1 vibrations advisory level is reached:(5U) - N1 vibrations indication flashes (green) on the “ENGINE” or “CRUISE” page if selected on the SYS CRT Cancelling malfunction restores normal operation.

U6KSC00

N.B. N1 vibrations advisory level depends on N1 actual value and EVMU initial values.

DATE: SEP 1998

Page Page 493 21

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A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINES PARAMETERS IAE

CHAPTER 30: ENGINES PARAMETERS IAE MALFUNCTION

: VIBRATIONS N2 INC/DEC # 2 (U)

PARAMETER

: ENGINE 1 LOW TURBINE SPEED VIBRATIONS

MIN VALUE

: 0 U MAX VALUE: 10 U CHANGE RATE: 0.5 U/s

MALFUNCTION DESCRIPTION

:

CAUSE

: Incorrect engine operation

CONSEQUENCE

:

- N2 vibrations indication is normally green If N2 vibrations advisory level is reached: (5U) - N2 vibrations indication flashes (green) on the “ENGINE” or “CRUISE” page if selected on the SYS CRT Cancelling malfunction restores normal operation.

U6KSC00

N.B. N2 vibrations advisory level depends on N2 actual value and EVMU initial values.

DATE: SEP 1998

Page Page 494 22

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINES PARAMETERS IAE

CHAPTER 14: ENGINE PARAMETERS CFM MALFUNCTION

: N1 VIBRATION PEAK ENGINE 1

PARAMETER/VALUES

: SELECTED SPEED N1(%): 0 to 110% : VIBRATION PEAK LEVEL: 0 to 10 cockpits units

MALFUNCTION DESCRIPTION

:

CAUSE

: Unbalanced LP rotor due to normal or abnormal engine degradation

CONSEQUENCE

:

- An altered vibration profile on sensed LP vibration level is introduced. - The degraded engine shows new vibration levels which include a vibration peak reaching the selected vibration value (cockpits units) at the selected speed (%). - The unbalanced vibration signature appears only if the selected values allow the vibration signature to overshoot the vibration level of balanced engine. - N1 vibrations indication is normally green. If N1 vibrations advisory level is reached: (5U) - N1 vibrations indication flashes (green) on the "ENGINE" or "CRUISE" page if selected on the SYS CRT. Cancelling malfunction restores normal operation

U6KSC00

N.B.: All advisories are always functionnal but there is no real correlation with bite unbalance functions (if available on simulators).

DATE: SEP 1998

Page Page 495 23

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINES PARAMETERS IAE

CHAPTER 14: ENGINE PARAMETERS CFM MALFUNCTION

: N1 VIBRATION PEAK ENGINE 2

PARAMETER/VALUES

: SELECTED SPEED N1(%): 0 to 110% : VIBRATION PEAK LEVEL: 0 to 10 cockpits units

MALFUNCTION DESCRIPTION

:

CAUSE

: Unbalanced LP rotor due to normal or abnormal engine degradation

CONSEQUENCE

:

- An altered vibration profile on sensed LP vibration level is introduced. - The degraded engine shows new vibration levels which include a vibration peak reaching the selected vibration value (cockpits units) at the selected speed (%). - The unbalanced vibration signature appears only if the selected values allow the vibration signature to overshoot the vibration level of balanced engine. - N1 vibrations indication is normally green. If N1 vibrations advisory level is reached: (5U) - N1 vibrations indication flashes (green) on the "ENGINE" or "CRUISE" page if selected on the SYS CRT. Cancelling malfunction restores normal operation

U6KSC00

N.B.: All advisories are always functionnal but there is no real correlation with bite unbalance functions (if available on simulators).

DATE: SEP 1998

Page Page 496 24

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINES PARAMETERS IAE

CHAPTER 14: ENGINE PARAMETERS CFM MALFUNCTION

: N2 VIBRATION PEAK ENGINE 1

PARAMETER/VALUES

: SELECTED SPEED N2(%): 0 to 110% : VIBRATION PEAK LEVEL: 0 to 10 cockpits units

MALFUNCTION DESCRIPTION

:

CAUSE

: Unbalanced HP rotor due to normal or abnormal engine degradation

CONSEQUENCE

:

- An altered vibration profile on sensed HP vibration level is introduced. - The degraded engine shows new vibration levels which include a vibration peak reaching the selected vibration value (cockpits units) at the selected speed (%). - The unbalanced vibration signature appears only if the selected values allow the vibration signature to overshoot the vibration level of balanced engine. - N1 vibrations indication is normally green. If N1 vibrations advisory level is reached: (5U) - N1 vibrations indication flashes (green) on the "ENGINE" or "CRUISE" page if selected on the SYS CRT. Cancelling malfunction restores normal operation

U6KSC00

N.B.: All advisories are always functionnal but there is no real correlation with bite unbalance functions (if available on simulators).

DATE: SEP 1998

Page Page 497 25

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION ENGINES PARAMETERS IAE

CHAPTER 14: ENGINE PARAMETERS CFM MALFUNCTION

: N2 VIBRATION PEAK ENGINE 2

PARAMETER/VALUES

: SELECTED SPEED N2(%): 0 to 110% : VIBRATION PEAK LEVEL: 0 to 10 cockpits units

MALFUNCTION DESCRIPTION

:

CAUSE

: Unbalanced HP rotor due to normal or abnormal engine degradation

CONSEQUENCE

:

- An altered vibration profile on sensed HP vibration level is introduced. - The degraded engine shows new vibration levels which include a vibration peak reaching the selected vibration value (cockpits units) at the selected speed (%). - The unbalanced vibration signature appears only if the selected values allow the vibration signature to overshoot the vibration level of balanced engine. - N1 vibrations indication is normally green. If N1 vibrations advisory level is reached: (5U) - N1 vibrations indication flashes (green) on the "ENGINE" or "CRUISE" page if selected on the SYS CRT. Cancelling malfunction restores normal operation

U6KSC00

N.B.: All advisories are always functionnal but there is no real correlation with bite unbalance functions (if available on simulators).

DATE: SEP 1998

Page Page 498 26

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FADEC IAE

CHAPTER 31 - FADEC IAE CONTENTS: THROTTLE 1 INOP (IDLE POWER) THROTTLE 2 INOP (IDLE POWER) REVERSER CONTROL 1 FAIL REVERSER CONTROL 2 FAIL FADEC 1 FAIL FADEC 2 FAIL INCORR REV PWR ENG 1 (LOW) INCORR REV PWR ENG 2 (HIGH)

U6KSC00

THR TARGET NEEDLE FAIL

DATE: SEP 1998

Page Page499 1

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FADEC IAE

CHAPTER 31: FADEC IAE MALFUNCTION

: THROTTLE 1 INOP (IDLE POWER)

MALFUNCTION DESCRIPTION

:

CAUSE

: Loss of FADEC fuel schedule

CONSEQUENCE

:

- Engine 1 performances are set to idle whatever the throttle position is.

U6KSC00

Cancelling malfunction restores normal operation

DATE: SEP 1998

Page Page500 2

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FADEC IAE

CHAPTER 31: FADEC IAE MALFUNCTION

: THROTTLE 2 INOP (IDLE POWER)

MALFUNCTION DESCRIPTION

:

CAUSE

: Loss of FADEC fuel schedule

CONSEQUENCE

:

- Engine 2 performances are set to idle whatever the throttle position is.

U6KSC00

Cancelling malfunction restores normal operation

DATE: SEP 1998

Page Page501 3

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FADEC IAE

CHAPTER 31: FADEC IAE MALFUNCTION

: REVERSER CONTROL 1 FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Reverser control failure

CONSEQUENCE

:

- Reverser 1 can’t be deployed If flight phases 1,2,6,7,8,9 or 10 • Appropriate messages appear on E/W CRT

U6KSC00

Cancelling malfunction restores normal operation

DATE: SEP 1998

Page Page502 4

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FADEC IAE

CHAPTER 31: FADEC IAE MALFUNCTION

: REVERSER CONTROL 2 FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Reverser control failure

CONSEQUENCE

:

- Reverser 2 can’t be deployed If flight phases 1, 2, 6, 7, 8, 9 or 10 • Appropriate messages appear on E/W CRT

U6KSC00

Cancelling malfunction restores normal operation

DATE: SEP 1998

Page Page503 5

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FADEC IAE

CHAPTER 31: FADEC IAE MALFUNCTION

: FADEC 1 FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Power supply lost

CONSEQUENCE

:

- All engine 1 indications become invalid on the upper ecam display unit. • Engine 1 stops If flight phases 1,2,3,6,9 or 10: • Single chime sounds • Master caution light comes on • Appropriate messages appear on E/W CRT • “ENGINE” page appears on SYS CRT - Failure on, engine 1 can’t be restarted

U6KSC00

Cancelling malfunction restores normal operation

DATE: SEP 1998

Page Page504 6

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FADEC IAE

CHAPTER 31: FADEC IAE MALFUNCTION

: FADEC 2 FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Power supply lost

CONSEQUENCE

:

- All engine 2 indications become invalid on the upper ecam display unit. • Engine 2 stops If flight phases 1,2,3,6,9 or 10: • Single chime sounds • Master caution light comes on • Appropriate messages appear on E/W CRT • “ENGINE” page appears on SYS CRT - Failure on, engine 2 can’t be restarted

U6KSC00

Cancelling malfunction restores normal operation.

DATE: SEP 1998

Page Page505 7

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FADEC IAE

CHAPTER 31: FADEC IAE MALFUNCTION

: INCORR REV PWR ENG 1 (LOW)

MALFUNCTION DESCRIPTION

:

CAUSE

: Sensors failure

CONSEQUENCE

:

- Engine 1 Reverse extends normally but engine 1 performances remain at low power during the whole reverse phase whatever the throttle 1 position is.

U6KSC00

Cancelling malfunction restores normal operation

DATE: SEP 1998

Page Page506 8

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FADEC IAE

CHAPTER 31: FADEC IAE MALFUNCTION

: INCORR REV PWR ENG 2 (HIGH)

MALFUNCTION DESCRIPTION

:

CAUSE

: Sensors failure

CONSEQUENCE

:

- Engine 2 revese extends normally but engine 2 performances reached then remain at high power during the whole reverse phase whatever the throttle 2 position is.

U6KSC00

Cancelling malfunction restores normal operation

DATE: SEP 1998

Page Page507 9

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_ A320 SIMULATOR MANUAL SIMULATOR SIMULATOR A320 SIMULATED MALFUNCTIONS DESCRIPTION

A320 SIMULATED MALFUNCTIONS DESCRIPTION FADEC IAE

CHAPTER 31: FADEC IAE MALFUNCTION

: THR TARGET NEEDLE FAIL

MALFUNCTION DESCRIPTION

:

CAUSE

: Loss of EPR TARGET signal by ecam

CONSEQUENCE

:

- No more indication of engine 1 EPR TARGET

U6KSC00

Cancelling malfunction restores normal operation

DATE: SEP 1998

Page Page 508 10

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