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A 320 SIM, FAILURES AND THEIR FLIGHT DECK EFFECTS EXPLANATIONS
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A320SIMULATOR MANUAL
SIMULATOR
A320 SIMULATED MALFUNCTIONS DESCRIPTION
This document must be usedfor training purpose only.
Under no circumstancesshould 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.
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..........................................................
Chapter 22 - Instruments 325........................................................
Chapter 23 - Landing Gear 333......................................................
Chapter 24 - Pitch Control 349......................................................
Chapter 25 - Roll Control 375.......................................................
_A320 SIMULATOR MANUAL
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A320 SIMULATED MALFUNCTIONS DESCRIPTION
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U6KSC00 TABLE OF CONTENTS Page
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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............................................
Chapter 31 - FADEC IAE 499.......................................................
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U6KSC00 TABLE OF CONTENTS Page
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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
ALPHA CHANNEL ADR 1&2 FAULT
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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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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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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).
- Cancelling malfunction restores normal operation.
- Set all switching in neutral position.
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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 appropriateflags 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 normaloperations 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.
- Set all switching in neutral position.
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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 appropriateflags 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
- 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.
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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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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. WithECAM/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).
- Cancelling malfunction restores normal operation
- Set all switching in neutral position
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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 TATare 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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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).
- Cancelling malfunction restores normal operation
- Set all switching in neutral position
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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 (in1 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
- 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’sPFD and the “CHECK ATT” message disappears on both PFD
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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 of5 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
• 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’sPFD and ND “CHECK HDG” message disappears on both PFDs and NDs.
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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
• 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’sND and “CHECK HDG” message disappears on both ND
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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 (in1 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
- 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 andthe “CHECK ATT” message disappears on both PFD
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CHAPTER 1: ADIRS
MALFUNCTION : AIRSPEED CHANNEL ADR 1 FAULT
MALFUNCTION DESCRIPTION :
CAUSE : Octal label 206 computed airspeed: BADTRANSMISSION
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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CHAPTER 1: ADIRS
MALFUNCTION : AIRSPEED CHANNEL ADR 2 FAULT
MALFUNCTION DESCRIPTION :
CAUSE : Octal label 206 (computed airspeed) BADTRANSMISSION
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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CHAPTER 1: ADIRS
MALFUNCTION : ALTITUDE CHANNEL ADR 1 FAULT
MALFUNCTION DESCRIPTION :
CAUSE : Octal labels 203,204,220 (Altitude, BARO CORALT 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” lightcomes 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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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
- Cancelling malfunction restores normal operation
- Set all switching in neutral position
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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).
- Cancelling malfunction restores normal operation.
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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
X BLEED FAULT
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CHAPTER 2: AIR BLEED
MALFUNCTION : ENG 1 BLEED FAULT (HP VALVE)
MALFUNCTION DESCRIPTION :
CAUSE : HP VALVE ENG1 stuck open or going to openposition (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)
• 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.
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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
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Cancelling the malfunction restores normal operation.
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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 comeson
- 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
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Cancelling the malfunction restores normal operation.
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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
• 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.
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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 lightcomes 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)
• 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.
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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)
• The appropriate STATUS page appears on the SYS CRT
- Cancelling the malfunction restores normal operation
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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:
• Cross feed valve opens
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Cancelling malfunction restores normal operation.
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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
VALVE SKIN/HEAT EXCHANGER STUCK CLOSE
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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
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Cancelling malfunction restores normal operation
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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
- Appropriate messages will be available on MCDU (CFDS function)
- (when CFDS maintenance option selected).
- Cancelling malfunction restores normal operation
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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
• “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
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CHAPTER 3: AIR CONDITIONING/VENTILATION
MALFUNCTION : PACK 2 AUTO SHUT DOWN INOP FORSTARTING
MALFUNCTION DESCRIPTION :
CAUSE : Failure of close relay 12 HB of the flow control valveRH “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
• “PACK VALVE 2 OFF” light comes on
- When ditching is selected, pack 2 valve remains open.
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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)
• 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
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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)
• 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.
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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
• “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
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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
• HOT AIR OFF light goes out
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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)
• The appropriate STATUS page appears on the SYS CRT
- Cancelling the malfunction restores normal operation
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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)
• 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
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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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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).
- Cancelling malfunction restores normal operation
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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
• 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.
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CHAPTER 3: AIR CONDITIONING/VENTILATION
MALFUNCTION : GRND COOL FAULT
MALFUNCTION DESCRIPTION :
CAUSE : Ground cool valve stuck open
CONSEQUENCE :
- TBD. Lack of data
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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
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CHAPTER 3: AIR CONDITIONING/VENTILATION
MALFUNCTION : VALVE SKIN/HEAT EXCHANGER STUCKCLOSE
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)
• The appropriate STATUS page appears on the SYS CRT
- Cancelling the malfunction restores normal operation
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THIS PAGE INTENTIONALLY LEFT BLANK
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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
ENG 2 NACELLE VALVE FAULT
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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).
Cancelling malfunction restores normal operation
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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).
- Cancelling malfunction restores normal operation
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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”
• Status messages appear
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Cancelling malfunction restores normal operation
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CHAPTER 4: ANTI ICE
MALFUNCTION : L WINDOW HEAT COMPUTER FAULT
MALFUNCTION DESCRIPTION :
CAUSE : Loss of ventilation around the computer in hottemperature 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
• 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
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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).
- Cancelling malfunction restores normal operation
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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
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Cancelling malfunction restores normal operation
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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).
En outre nous ne disposons d’aucune information).
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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
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Cancelling malfunction restores normal operation
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CHAPTER 5 - APU
CONTENTS:
EXTINGUISHABLE FIRE
UNEXTINGUISHABLE FIRE
APU FAULT
APU FAILS TO START (CONTACTOR STUCK
OIL QTY INC/DEC (1)
APU FLAP FAULT
APU FUEL ISOL VALVE STUCK
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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,
• Audio CRC is stopped.
- External consequences: Electrical, Air conditioning, Fuel.
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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).
- Cancelling malfunction restores normal operation.
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CHAPTER 5: APU
MALFUNCTION : APU FAULT
MALFUNCTION DESCRIPTION :
CAUSE : FUEL SOLENOID FAILED SHORT-SHUT DOWNFROM 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.
• “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.
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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).
- Cancelling malfunction restores normal operation.
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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,
• “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.
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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.
- Appropriate messages will be available on MCDU (CFDS function)(when CFDS maintenance option selected).
- Cancelling malfunction restores normal operation.
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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:
• 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.
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CHAPTER 6 - ATTENDANT/MAINT. COMPUTER
CONTENTS:
ACARS FAIL
CIDS FAIL
CFDIU FAULT
DFDR FAULT
QAR FAULT
DMU FAULT
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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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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).
ACTION: NIL
- Cancelling the malfunction restores normal operation.
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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
<SYSTEM REPORT/TEST
Access to “SYSTEM REPORT/TEST” item is possible through both MCDUs
In flight:
On both MCDUs, the “ CFDS” item is not displayed om MCDU MENU
Clear malfunction
Trip CFDIU supply breaker (CB 2TW - J18)
Trip CFDUY backup breaker (CB 8TW - J17)
After 1 sec reset CFDIU supply breaker (CB 2TW - J18) and CFDIU backup breaker (CB 8TW - J17)
CFDIU is fully operative after a delay (about 30 s)
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CHAPTER 6: ATTENDANT/MAINT. COMPUTER
MALFUNCTION : CFDR FAULT
MALFUNCTION DESCRIPTION :
CAUSE : INTERNAL POWER FAILURE
CONSEQUENCE :
1 Automatic mode:
ECAM: (TBD)
2 Ground manual mode:
Engagement logic not affected
ECAM: (TBD)
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CHAPTER 6: ATTENDANT/MAINT. COMPUTER
MALFUNCTION : QAR FAULT
MALFUNCTION DESCRIPTION :
CAUSE : Non traitee: Option
CONSEQUENCE :
Non traitee: Option
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CHAPTER 6: ATTENDANT/MAINT. COMPUTER
MALFUNCTION : DMU FAULT
MALFUNCTION DESCRIPTION :
CAUSE : Non traitee: Option
CONSEQUENCE :
Non traitee: Option
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CHAPTER 7 - CABIN PRESSURE
CONTENTS:
CAB PRESS REGULATOR 1 FAULT
CAB PRESS REGULATOR 2 FAULT
STRUCTURE DAMAGE
EXCESSIVE ALTITUDE
CAB PRESS SYS 1 28V DC
CAB PRESS SYS 1 5V AC
NEGATIVE LO DP
REG VALVE STUCK
LDG ELEV ROTACTOR FAIL
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CHAPTER 7: CABIN PRESSURE
MALFUNCTION : CAB PRESS REGULATOR 1 FAULT
MALFUNCTION DESCRIPTION :
CAUSE : Computer fail
CONSEQUENCE :
- If system 1 is selected
Then:
• Cabin pressure system switches to sys 2
- If the aircraft is in flight phases 1,2,6,9,10
Then:
• Associated warning messages appear on E/W crt
• Cab press page appears on the SYS CRT
Sys 1 is not displayed
Sys 2 is green
- 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
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CHAPTER 7: CABIN PRESSURE
MALFUNCTION : CAB PRESS REGULATOR 2 FAULT
MALFUNCTION DESCRIPTION :
CAUSE : Computer fail
CONSEQUENCE :
- If system 2 is selected
Then:
• Cabin pressure system switches to sys 1
• Sys 2 becomes amber on pressu page
- If the aircraft is in flight phases 1, 2, 6, 9, 10
Then:
• Associated warning messages appear on E/W CRT
• Cabin press page appears on the SYS CRT
Sys 2 is amber
Sys 1 is green
- 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
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CHAPTER 7: CABIN PRESSURE
MALFUNCTION : STRUCTURE DAMAGE
MALFUNCTION DESCRIPTION :
CAUSE : Explosive decompression
CONSEQUENCE :
- If the aircraft is above 10000 ft
Then:
• The outflow valve moves to close
• High cabin vertical speed (about 12000 ft/min)
• dp decreases
• Cabin altitude increases
- If the aircraft is in flight phase 1, 6
• When cabin altitude reaches 9550 ft
Then:
• Continuous repetitive chime sounds
• Master warning light comes on
• Associated message appears on E/W CRT
• CABIN PRESS page appears on SYS CRT
- If cabin altitude reaches 11300ft then CIDS on MSP CRT operates Passenger Signs.
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- After cancelling malfunction when cabin altitude decreases below 9550 ft, normal operation is restored.
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CHAPTER 7: CABIN PRESSURE
MALFUNCTION : EXCESSIVE ALTITUDE
MALFUNCTION DESCRIPTION :
CAUSE : Leakage rate of section
CONSEQUENCE :
- If the aircraft is above 10000 ft
Then
• The outflow valve attempts to regulate
• Cabin vertical speed increases (about 6000 ft/min)
• Dp decreases
• Cabin altitude increases
- If the aircraft is in flight phase 1, 6
When cabin altitude reaches 9550 ft
Then:
• Continuous repetitive chime sounds
• Master warning light comes on
• Associated message appears on E/W CRT
• CABIN PRESS page appears on SYS CRT
- If cabin altitude reaches 11300ft then CIDS on MSP CRT operates Passenger Signs.
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- After cancelling malfunction, when cabin altitude is below 9550 ft normal operation is restored.
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CHAPTER 7: CABIN PRESSURE
MALFUNCTION : CAB PRESS SYS 1 28V DC
MALFUNCTION DESCRIPTION :
CAUSE : Loss of 28 V DC
CONSEQUENCE :
- If system 1 is selected
Then:
• Cabin pressure system switches to sys 2
- If the A/C is in flight phases 1,2,6,9,10
Then:
• associated message appears on E/W CRT
• “CABIN PRESS” page appears on SYS CRT
Sys 1 is not displayed
Sys 2 is green
- After successive “CLR” (ECAM control panel)
• Appropriated 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
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CHAPTER 7: CABIN PRESSURE
MALFUNCTION : CAB PRESS SYS 1 5V AC
MALFUNCTION DESCRIPTION :
CAUSE : Loss of 5V ACRelay box 7 LP - Connecteur A - pin 18
CONSEQUENCE :
- If light test SW on
Then:
• FAULT light stays off
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Cancelling malfunction restores normal operation
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CHAPTER 7: CABIN PRESSURE
MALFUNCTION : NEGATIVE LO DP
MALFUNCTION DESCRIPTION :
CAUSE : False warning (threshold offset)
CONSEQUENCE :
- If system 1 or 2 is selected and if the aircraft is in flight phases 1, 6
Then:
• Single stroke chime sounds
• Master caution light comes on
• Associated warning message appears on E/W CRT
• Cab 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.
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CHAPTER 7: CABIN PRESSURE
MALFUNCTION : REG VALVE STUCK
MALFUNCTION DESCRIPTION :
CAUSE : Outflow valve flap mechanical stuck in position
CONSEQUENCE :
- If aircraft on ground and flight phase 9, 10
- If outflow valve not open ( < 5 %)
Then:
• 180s after: Single stroke chime sounds
• Master caution light comes on
• Associated message appears on E/W CRT
• Cab press page appears on SYS CRT
- If flight phases 3, 6
- If system 1 selected
- If vertical speed less than (-2211 ft/min) and valve position less than 5ÿ%, or vertical speed greater than 2211 ft/minand valve position greater than 5 %.
Then:
• Cabin pressure switches to sys 2
• Cabin press fault light comes on
• Associated messages appear on E/W CRT
• Cab press page appears on SYS CRT
- If mode sel P.B. on MAN position
- If man V/S CTL SW on UP or DN position
Then:
• Outflow valve always stuck in position
- After successive CLR (Ecam Control Panel)
• The appropriate status page appears on CRT
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Cancelling malfunction restores normal operation
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CHAPTER 7: CABIN PRESSURE
MALFUNCTION : LDG ELEV ROTACTOR FAIL
MALFUNCTION DESCRIPTION :
CAUSE : LDG ELEV ROTACTOR FAILURE
CONSEQUENCE :
• Set the A/C altitude to 35 000 ft
The selector position read by the CPC becomes wrong. Control of landing elevation switches from auto to manual modeand the CPC takes 14500 ft as landing elevation selection.
Cabin altitude varies according to a 14500 ft elevation selection.
If cabin altitude overrides 9500 ft and if aircraft is in flight phase 1, 6
Then:
• Continuous repetitive chime sounds
• Master warning light comes on
• Associated message appears on E/W CRT.
• CABIN PRESS page appears on SYS CRT
Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
Cancelling the malfunction restores normal operation.
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CONTENTS:
DMC 1 FAULT
DMC 2 FAULT
DMC 3 FAULT
DMC 1 PITCH INC/DEC (DEG/S)
DMC 2 PITCH INC/DEC (DEG/S)
DMC 1 ROLL INC/DEC (DEG/S)
DMC 2 ROLL INC/DEC (DEG/S)
DMC 1 SPEED INC/DEC (KT/S)
DMC 2 SPEED INC/DEC (KT/S)
FWC 1 FAULT (ACQUISITION)
FWC 2 FAULT (ACQUISITION)
SDAC 1 FAULT
SDAC 2 FAULT
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MALFUNCTION : DMC 1 FAULT
MALFUNCTION DESCRIPTION :
CAUSE : Power supply failure (115V AC CB 10WT1)
CONSEQUENCE :
- The display units driven by DMC1 (captain PFD and ND and upper ECAM DU) display a diagonal line.
- The Engine/Warning image is automatically displayed on the lower ECAM DU instead of the system page or statusmessage ("Mono" display configuration).
- Indications and warning symbols/messages generated by ECAM.
Report to FWC boards 31040 and 31090.
ACTION:
The Captain can switch over to DMC 3 by mean of the EIS DMC selector (CAPT/3 position).
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Cancelling the malfunction restores normal operation.
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MALFUNCTION : DMC 2 FAULT
MALFUNCTION DESCRIPTION :
CAUSE : Power supply failure (115V AC CB 10WT2)
CONSEQUENCE :
- The display units driven by DMC2 (F/O PFD and ND and lower ECAM DU) display a diagonal line.
- Indications and warning symbols/messages generated by ECAM.
Report to FWC boards 31050 and 31100.
ACTION:
The first Officer can switch over to DMC3 by mean of the EIS DMC selector (F/O/3 position).
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Cancelling the malfunction restores normal operation.
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MALFUNCTION : DMC 3 FAULT
MALFUNCTION DESCRIPTION :
CAUSE : Power supply failure (115V AC CB 10WT3 andCB 14WT1)
CONSEQUENCE :
- In normal operation, no change in present display configuration.
- If the DMC 1 and 2 are not simultaneously failed, the message DMC 3 appears on status page in section reserved formaintenance information.
- If Captain is switched over DMC3.
• Capt PFD, ND and upper ECAM DU display a diagonal line
• E/W is automatically displayed on the lower ECAM DU instead of the system page or status message.
- If F/O is switched over DMC3.
• F/O PFD, ND and lower ECAM DU display a diagonal line.
ACTION: NIL
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Cancelling the malfunction restores normal operation.
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MALFUNCTION : DMC 1 PITCH INC/DEC (DEG/S)
PARAMETER : Drift rate of Pitch angle (Label 324 from ADIRS1)
MIN VALUE : 0.5 deg/s MAX VALUE: 20 deg/s CHANGE RATE:variable
MALFUNCTION DESCRIPTION :
CAUSE : VARIABLE PITCH DATA COMPUTED BYADIRS 1
CONSEQUENCE :
A drift is added to the true pitch angle
- If the ATT/HDG switching is in neutral position, the pitch data displayed on CAPT’s PFD is wrong
- When the discrepancy between the CAPT’s PFD pitch and F/O’s PFD pitch becomes greater than 5 ; the “CHECKATT” message appears
- In Flight phases 1,2,5,6,7,9,10:
• ECAM warning: NAV ATT DISCREPANCY
• LIGHT warning: MASTER CAUTION light are on
• AUDIO warning: Single Chime Sounds
- If the ATT/HDG switching is in CAPT/3 position, CAPT’s PFD normal operation is restored, the “CHECK ATT”flag and warnings disappear.
(If the drift becomes lower than 5, the “CHECK ATT” flag disappears and warnings disappear)
- 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.
Complementary data: the pitch data will be limited to +/- 30 deg.
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MALFUNCTION : DMC 2 PITCH INC/DEC (DEG/S)
PARAMETER : Drift rate of Pitch angle (Label 324 from ADIRS2)
MIN VALUE : 0.5 deg/s MAX VALUE: 20 deg/s CHANGE RATE:variable
MALFUNCTION DESCRIPTION :
CAUSE : VARIABLE PITCH DATA COMPUTED BYADIRS 2
CONSEQUENCE :
A drift is added to the true pitch angle
- If the ATT/HDG switching is in neutral position, the pitch data displayed on F/O’s PFD is wrong
- When the discrepancy between the CAPT’s PFD pitch and F/O’s PFD pitch becomes grater than 5, the “CHECKATT” message appears
- In Flight phases 1,2,5,6,7,9,10:
• ECAM warning: NAV ATT DISCREPANCY
• LIGHT warning: MASTER CAUTION lights are on
• AUDIO warning: Single Chime Sounds
- If the ATT/HDG switching is in F/O/3 position, F/O’s PFD normal operation is restored, the “CHECK ATT” flagand warnings disappear.
(If the drift becomes lower than 5 the “CHECK ATT” flag disappears and warnings dispappear)
- 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.
Complementary data: the pitch data will be limited to +/- 30 deg.
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MALFUNCTION : DMC 1 ROLL INC/DEC (DEG/S)
PARAMETER : Drift rate of Roll angle (Label 325 from ADIRS1)
MIN VALUE : 0.5 deg/s MAX VALUE: 20 deg/s CHANGE RATE:variable
MALFUNCTION DESCRIPTION :
CAUSE : VARIABLE ROLL DATA COMPUTED BYADIRS 1
CONSEQUENCE :
A drift is added to the true roll angle
- If the ATT/HDG switching is in neutral position, the roll data displayed on CAPT’s PFD is wrong
- When the discrepancy between the CAPT’s PFD roll and F/O’s PFD roll becomes greater than 5, the ’CHECK ATT’message appears
- In flight phases 1, 2, 5, 6, 7, 9, 10:
• ECAM warning: NAV ATT DISCREPANCY
• LIGHT warning: MASTER CAUTION lights are on
• AUDIO warning: Single Chime Sounds
- If the ATT/HDG switching is in CAPT/3 position, CAPT’s PFD normal operation is restored, the “CHECK ATT”flag and warnings disappear.
(If the drift becomes lower than 5, the ’CHECK ATT’ flag dispappears and warnings disappear)
- 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.
Complementary data: the roll data will be limited to +/- 60 deg.
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MALFUNCTION : DMC 2 ROLL INC/DEC (DEG/S)
PARAMETER : Drift rate of Roll angle (Label 325 from ADIRS2)
MIN VALUE : 0.5 deg/s MAX VALUE: 20 deg/s CHANGE RATE:variable
MALFUNCTION DESCRIPTION :
CAUSE : VARIABLE ROLL DATA COMPUTED BYADIRS 2
CONSEQUENCE :
A drift is added to the true roll angle
- If the ATT/HDG switching is in neutral position, the roll data displayed on F/O’s PFD is wrong
- When the discrepancy between the CAPT’s PFD roll and F/O’s PFD roll becomes greater than 5, the “CHECKATT” message appears
- In Flight phases 1, 2, 5, 6, 7, 9, 10:
• ECAM warning: NAV ATT DISCREPANCY
• LIGHT warning: MASTER CAUTION lights are on
• AUDIO warning: Single Chime Sounds
- If the ATT/HDG switching is in F/O/3 position, F/O’s PFD normal operation is restored, the “CHECK ATT” flagand warnings disappear.
(If the drift becomes lower than 5, the “CHECK ATT” flag disappears and warnings disappear)
- 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.
Complementary data: the roll data will be limited to +/- 60 deg.
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MALFUNCTION : DMC 1 SPEED INC/DEC (KT/S)
PARAMETER : Drift rate of Computed airspeed (from ADIRS)
MIN VALUE : 1kt/s MAX VALUE: 15 kt/s CHANGE RATE:variable
MALFUNCTION DESCRIPTION :
CAUSE : VARIABLE WRONG DATA SENT BY ADIRS 1
CONSEQUENCE :
A drift adjustable by the I.S. is added to the normal computed airspeed on arinc output parameter
- If AIR DATA switching is in neutral position on CAPT PFD, speed information is wrong, MACH and TASinformations are not modified
- If AIR DATA switching is in CAPT/3 position, CAPT’s PFD normal operation is restored.
- On ADIRS CDU: no warning
- ECAM warning: no warning
- Cancelling failure restores normal operation
- Set all switching in neutral position
Complementary data: the CAS data will be limited to 0/450 kt.
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MALFUNCTION : DMC 2 SPEED INC/DEC (KT/S)
PARAMETER : Drift rate of Computed airspeed (from ADIRS2)
MIN VALUE : 1 kt/s MAX VALUE: 15 kt/s CHANGE RATE:variable
MALFUNCTION DESCRIPTION :
CAUSE : VARIABLE WRONG DATA SENT BY ADIRS 2
CONSEQUENCE :
A drift adjustable by the I.S is added to the normal computed airspeed on arinc output parameter
- If AIR DATA switching is in neutral position on F/O PFD, speed information is wrong, MACH and TASinformations are not modified
- If AIR DATA switching is in F/O/3 position, F/O’s PFD normal operation is restored.
- On ADIRS CDU: no warning
- ECAM WARNING: no warning
- Cancelling failure restores normal operation
- Set all switching in neutral position.
Complementary data: the CAS data will be limited to 0/450 kt.
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MALFUNCTION : FWC 1 FAULT (ACQUISITION)
MALFUNCTION DESCRIPTION :
CAUSE : COMPUTER TOTAL FAILURE
CONSEQUENCE :
NOTE: The consequences described hereafter apply ONLY to a:“NO-OTHER-MALFUNCTION-INSERTED-A/C-CONFIGURATION”.
The consequences description of this malfunction’s introduction while (an) other malfunction (s) is(are) already present,should be derived from the combination of the other malfunction consequences description with the following one.
FFS/FBS/MTS:
If A/C is in flight phase 1 2 6 9 or 10
or
if A/C is in flight phase 3 4 5 7 or 8 and an action on ECP/RCL
switch has been performed to cancel automatic-flight-phase-inhibition, the following INDEPENDANT warning(s)appears on EW DU:
FWS FWC 1 FAULT
Clear (all) warning(s) presented on EW DU until STATUS page can be displayed on any ECAM - available DU(S, EW,... according to A/C configuration),
the following INOPERATIVE SYSTEM status is(are) displayed on STATUS page:
FWC 1
MTS (only):
The following ECAM message:
- 31 - 00 FWS FWC 1 FAULT
is registered by CFDIU, with adequate GMT and FLIGHT PHASE NUMBER, and displayed in LAST/CURRENTLEG ECAM REPORT item of CFDS MAIN MENU.
The following CFDS message:
NO DATA FROM FWC 1
is registered by CFDIU, with adequate GMT and ATA NUMBER, and displayed in LAST/CURRENT LEG REPORTitem of CFDS MAIN MENU.
It can also be displayed in AVIONICS STATUS item of CFDS MAIN MENU, if malfunction is still present at the timeof selection of this item.
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The following FWC 2 BITE message:
- 31-53-34 FWC 2: NO DATA FROM OPPOSITE FWC
class II internal fault
is registered by FWC 2 BITE, with adequate GMT, and displayed in LAST LEG REPORT item of FWC 2 BITEMENU.
It can also be displayed, if reported by FWC 2 and registered by CFDIU, in LAST/CURRENT LEG REPORT of CFDSMAIN MENU.
The following CFDIU BITE message:
- NO DATA FROM FWC 1
external fault
is registered by CFDIU BITE, with adequate GMT, and displayed in LAST LEG REPORT item of CFDIU BITEMENU.
It can also be displayed in GROUND SCANNING item of CFDIU BITE MENU, if malfunction is still present at thetime of selection of this item.
FFS/FBS.MTS:
Cancelling the malfunction restores FWC 1 NORMAL OPERATION AND ECAM messages disappear from associatedDU.
MTS (only):
- but CFDIU or BITE memorized MAINTENANCE messages do NOT disappear.
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MALFUNCTION : FWC 2 FAULT (ACQUISITION)
MALFUNCTION DESCRIPTION :
CAUSE : COMPUTER TOTAL FAILURE
CONSEQUENCE :
NOTE: The consequences described hereafter apply ONLY to a:“NO-OTHER-MALFUNCTION-INSERTED-A/C-CONFIGURATION”.
The consequences description of this malfunction’s introduction while (an) other malfunction(s) is(are) already present,should be derived from the combination of the other malfunction consequences description with the following one.
FFS/FBS/MTS:
If A/C is in flight phase 1 2 6 9 or 10
or
If A/C is in flight phase 3 4 5 7 or 8 and an action on ECP/RCL switch has been performed to cancelautomatic-flight-phase-inhibition, the following INDEPENDANT warning(s) appear(s) on EW DU
FWS FWC 2 FAULT
Clear (all) warning(s) presented on EW DU until STATUS page can be displayed on any ECAM-available DU(S, EW,... according to A/C configuration),
The following INOPERATIVE SYSTEM status is (are) displayed on STATUS page:
FWC 2
MTS (only):
- The following ECAM message:
31-00 FWS FWC 2 FAULT
is registered by CFDIU, with adequate GMT and FLIGHT PHASE NUMBER, and displayed in LAST/CURRENTLEG ECAM REPORT item of CFDS MAIN MENU.
The following CFDS message:
NO DATA FROM FWC 2
- Is registered by CFDIU, with adequate GMT and ATA NUMBER, and displayed in LAST/CURRENT LEGREPORT item of CFDS MAIN MENU.
- It can also be displayed in AVIONICS STATUS item of CFDS MAIN MENU.
If malfunction is still present at the time of selection of this item.
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The following FWC 1 BITE message:
31-53-34 FWC 1: NO DATA FROM OPPOSITE FWC
Class II internal fault
- Is registered by FWC 1 BITE, with adequate GMT, and displayed in LAST LEG REPORT item of FWC 1 BITEMENU.
It can also be displayed, if reported by FWC 1 and registered by CFDIU, in LAST/CURRENT LEG REPORT of CFDSMAIN MENU.
The following CFDIU BITE message:
NO DATA FROM FWC 2
External fault
Is registered by CFDIU BITE, with adequate GMT, and displayed in LAST LEG REPORT item of CFDIU BITEMENU.
It can also be displayed in GROUND SCANNING item of CFDIU BITE MENU.
If malfunction is still present at the time of selection of this item.
FFS/FBS/MTS:
Cancelling the malfunction restores FWC 2 normal operation and ECAM messages disappear from associated DU,MTS (only)
But CFDIU or BITE memorized MAINTENANCE messages do NOT disappear.
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MALFUNCTION : SDAC 1 FAULT
MALFUNCTION DESCRIPTION :
CAUSE : COMPUTER TOTAL FAILURE
CONSEQUENCE :
CONSEQUENCES:
NOTE: The consequences described her(eafter apply ONLY to a:“NO-OTHER-MALFUNCTION-INSERTED-A/C-CONFIGURATION”.
The consequences description of this malfunction’s introduction while (an) other malfunction(s) is(are) already present,should be derived from the combination of the other malfunction consequences description with the following one.
FFS/FBS/MTS:
If A/C is in flight phase 1 2 6 9 or 10
Or
If A/C is in flight phase 3 4 5 7 or 8 and an action on ECP/RCL
Switch has been performed to cancel automatic-flight-phase-inhibition, the following INDEPENDANT warning(s)appear(s) on EW-DU:
FWS SDAC 1 FAULT
Clear (all) warning(s) presented on EW DU until STATUS page can be displayed on any ECAM-available DU(S, EW,... according to A/C configuration),
The following INOPERATIVE SYSTEM status is (are) displayed on STATUS page:
SDAC 1
MTS (only):
- The following ECAM message:
31-00 FWS SDAC 1 FAULT
is registered by CFDIU, with adequate GMT and FLIGHT PHASE NUMBER, and displayed in LAST/CURRENTLEG ECAM REPORT item of CFDS MAIN MENU.
The following FWC 1 (and FWC 2 respectively) BITE message:
31-55-34 FWC 1 (2 resp.): NO DATA FROM SDAC 1
class II internal fault
is registered by FWC (2 resp.) BITE, with adequate GMT, and displayed in LAST LEG REPORT item of FWC (2 resp.) BITE MENU.
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It can also be displayed, if reported by FWC 1 (2 resp.) and registered by CFDIU, in LAST/CURRENT LEG REPORTof CFDS MAIN MENU.
FFS/FBS/MTS:
Cancelling the malfunction restores SDAC 1 normal operation and ECAM messages disappear from associated DU,MTS (only):
but CFDIU or BITE memorized MAINTENANCE messages do NOT disappear.
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MALFUNCTION : SDAC 2 FAULT
MALFUNCTION DESCRIPTION :
CAUSE : COMPUTER TOTAL FAILURE
CONSEQUENCE :
NOTE: The consequences described hereafter apply ONLY TO A /"NO-OTHER-MALFUNCTION-INSERTED-A/C-CONFIGURATION".
The consequences description of this malfunction’s introduction while (an) other malfunction(s) is (are) already present,should be derived from the combination of the other malfunction consequences description with the following one.
FFS/FBS/MTS:
If A/C is in flight phase 1 2 6 9 or 10
Or
If A/C is in flight phase 3 4 5 7 or 8 and an action on ECP/RCL
Switch has been performed to cancel automatic-flight-phase-inhibition, the following INDEPENDANT warning(s)appear(s) on EW DU:
FWS SDAC 2 FAULT
Clear (all) warning(s) presented on EW DU until STATUS page can be displayed on any ECAM-available DU(S, EW,... according to A/C configuration),
The following INOPERATIVE SYSTEM status is (are) displayed on STATUS page:
SDAC 2
MTS (only) :
The following ECAM message:
- 31-00 FWS SDAC 2 FAULT
Is registered by CFDIU, with adequate GMT and FLIGHT PHASE NUMBER, and displayed in LAST/CURRENTLEG ECAM REPORT item of CFDS MAIN MENU.
The following FWC: (and FWC 2 respectively) BITE message:
31-55-34 FWC 1 (2 resp.): NO DATA FROM SDAC 2
Class II internal fault
Is registered by FWC 1 (2 resp.) BITE, with adequate GMT, and displayed in LAST LEG REPORT item of FWC 1(2 resp.) BITE MENU.
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It can also be displayed, if reported by FWC 1 (2 resp.) and registered by CFDIU, in LAST/CURRENT LEG REPORTof CFDS MAIN MENU.
FFS/FBS/MTS:
Cancelling the malfunction restores SDAC 2 normal operation and ECAM messages disappear from associated DU,
MTS (only):
But CFDIU or BITE memorized MAINTENANCE messages do NOT disappear.
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CHAPTER 9 - DOORS
CONTENTS:
L FWD CABIN DOOR NOT CLOSED
FWD CARGO SWITCH FAULT
AFT CARGO DOOR NOT CLOSED
R AFT CABIN SLIDE AUTO/MAN
AFT EMERG EXIT OPEN
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MALFUNCTION : L FWD CABIN DOOR NOT CLOSED
MALFUNCTION DESCRIPTION :
CAUSE : Door detected not closed - SW
CONSEQUENCE :
- If the aircraft is in flight phases 2, 3, 6, 9
Then:
• Single stroke chime sounds
• Master caution light comes on
• Associated warning message appears on E/W CRT
• LH FWD cab door open on SYS CRT
• VZ cabin increases (in flight)
- Appropriate messages will be available on MCDU (CFDS function)
(when CFDS maintenance option selected).
- Cancelling malfunction restores normal operation
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MALFUNCTION : FWD CARGO SWITCH FAULT
MALFUNCTION DESCRIPTION :
CAUSE : SW faulty
CONSEQUENCE :
- If the aircraft is in flight phases 2, 3, 6, 9
Then:
• Single stroke chime sounds
• Master caution light comes on
• Associated warning message appears on E/W CRT
• FWD cargo door open on SYS CRT
• No action on Vz cabin
- Appropriate messages will be available on MCDU (CFDS function)
(when CFDS maintenance option selected).
- Cancelling malfunction restores normal operation
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MALFUNCTION : AFT CARGO DOOR NOT CLOSED
MALFUNCTION DESCRIPTION :
CAUSE : Door detected not closed - SW
CONSEQUENCE :
- If the aircraft is in flight phases 2, 3, 6, 9
Then:
• Single stroke chime sounds
• Master caution light comes on
• Associated warning message appears on E/W CRT
• VZ cabin increases (in flight)
- Appropriate messages will be available on MCDU (CFDS function)
(when CFDS maintenance option selected).
- Cancelling malfunction restores normal operation
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MALFUNCTION : R AFT CABIN SLIDE AUTO/MAN
MALFUNCTION DESCRIPTION :
CAUSE : Slide disarm
CONSEQUENCE :
- In all flight phases:
• Symbol “SLIDE” of RH aft cabin door disappears on SYS CRT
- Cancelling malfunction restores normal operation
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MALFUNCTION : AFT EMERG EXIT OPEN
MALFUNCTION DESCRIPTION :
CAUSE : Door detected not closed - SW
CONSEQUENCE :
- If the aircraft is in flight phases 2, 3, 6, 9
Then:
• Single stroke chime sounds
• Master caution light comes on
• Associated warning message appears on E/W CRT
• After emerg exit door open on SYS CRT
• VZ cabin increases
- Appropriate messages will be available on MCDU (CFDS function)
(when CFDS maintenance option selected).
- Cancelling malfunction restores normal operation.
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CHAPTER 10 - EIS
CONTENTS:
CAPT PFD FAULT
F/O PFD FAULT
CAPT ND FAULT
F/O ND FAULT
CAPT PFD COLOR FAULT
F/O ND COLOR FAULT
ENG/WARNING DISPLAY FAIL
SYS/STATUS DISPLAY FAIL
SYS/STATUS COLOR FAULT
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CHAPTER 10: EIS
MALFUNCTION : CAPT PFD FAULT
MALFUNCTION DESCRIPTION :
CAUSE : Power supply failure (115V AC CB 11WT1)
CONSEQUENCE :
- Captain PFD screen blank
- There is an automatic transfert of the PFD image on the Captain’s display unit normally showing an ND image.
ACTION:
- Use Captain PFD/ND XFR push-button to select PFD or ND display on the Captain ND screen.
- Appropriate messages will be available on MCDU (CFDS function)
(when CFDS maintenance option selected).
- Cancelling the malfunction restores normal operation.
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CHAPTER 10: EIS
MALFUNCTION : F/O PFD FAULT
MALFUNCTION DESCRIPTION :
CAUSE : Power supply failure (115V AC CB 11WT2)
CONSEQUENCE :
- F/O PFD screen blank
- There is an automatic transfert of the PFD image on the F/O’s display unit normally showing an ND image.
ACTION:
- Use F/O PFD/ND XFR push-button to select PFD or ND display on the F/O ND screen.
- Appropriate messages will be available on MCDU (CFDS function)
(when CFDS maintenance option selected).
- Cancelling the malfunction restores normal operation.
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MALFUNCTION : CAPT ND FAULT
MALFUNCTION DESCRIPTION :
CAUSE : Power supply failure (115V AC CB 12WT1)
CONSEQUENCE :
- Captain ND screen blank.
ACTION:
- Use Captain PFD/ND XFR push-button to select PFD or ND display on the Captain’s PFD screen.
- Appropriate messages will be available on MCDU (CFDS function)
(when CFDS maintenance option selected).
- Cancelling the malfunction restores normal operation.
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CHAPTER 10: EIS
MALFUNCTION : F/O ND FAULT
MALFUNCTION DESCRIPTION :
CAUSE : Power supply failure (115V AC CB 12WT2)
CONSEQUENCE :
- F/O ND screen blank.
ACTION:
- Use F/O PFD/ND XFR push-button to select PFD or ND display on the F/O’s PFD screen.
- Appropriate messages will be available on MCDU (CFDS function)
(when CFDS maintenance option selected).
- Cancelling the malfunction restores normal operation.
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CHAPTER 10: EIS
MALFUNCTION : CAPT PFD COLOR FAULT
MALFUNCTION DESCRIPTION :
CAUSE : Red channel inhibit (connector pin 53 to ground)
CONSEQUENCE :
- Red colour missing on Captain’s PFD screen.
ACTION: NIL
- Cancelling the malfunction restores normal operation.
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MALFUNCTION : F/O ND COLOR FAULT
MALFUNCTION DESCRIPTION :
CAUSE : Red channel inhibit (connector pin 53 to ground)
CONSEQUENCE :
- Red colour missing on F/O’s ND screen.
ACTION: NIL
- Cancelling the malfunction restores normal operation.
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MALFUNCTION : ENG/WARNING DISPLAY FAIL
MALFUNCTION DESCRIPTION :
CAUSE : Power supply failure (115V AC CB 13 WT1)
CONSEQUENCE :
- Upper ECAM DU screen blank,
- The Engine/Warning image is automatically displayed on the lower ECAM DU instead of the system page or statusmessage ("Mono" display configuration).
ACTION:
- By means of the ECAM/ND XFR selector (position CAPT or F/O), each pilot can call on his “ND” DU an A/Csystem or status image instead of the ND image.
- The Engine/Warning image can be temporarily replaced by any A/C SYSTEM page or by the STATUS page, as longas the corresponding push-button switch is maintained pressed on the ECAM Control Panel.
- Appropriate messages will be available on MCDU (CFDS function)
(when CFDS maintenance option selected).
- Cancelling the malfunction restores normal operation.
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MALFUNCTION : SYS/STATUS DISPLAY FAIL
MALFUNCTION DESCRIPTION :
CAUSE : Power supply failure (115V AC CB 13WT2)
CONSEQUENCE :
- Lower ECAM DU screen blank.
ACTION:
- By means of the ECAM/ND XFR selector (position CAPT or F/O), each pilot can call on his “ND” DU an A/Csystem or status image, or Engine/Warning image if both ECAM DUs are inoperative, instead of the ND image.
- The Engine/Warning image can be temporarily replaced by any A/C SYSTEM page or by the STATUS page, as longas the corresponding push-button switch is maintained pressed on the ECAM Control Panel.
- Appropriate messages will be available on MCDU (CFDS function)
(when CFDS maintenance option selected).
- Cancelling the malfunction restores normal operation.
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MALFUNCTION : SYS/STATUS COLOR FAULT
MALFUNCTION DESCRIPTION :
CAUSE : Red channel inhibit (connector pin 53 to ground)
CONSEQUENCE :
- Red colour missing on SYS/STATUS screen.
ACTION: NIL
- Cancelling the malfunction restores normal operation.
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CHAPTER 11 - ELECTRICAL POWER 1
CONTENTS:
GEN 1 EXCITATION FAIL
GEN 2 EXCITATION FAIL
IDG 1 OIL OVERHEAT
IDG 2 OIL PRESS LO
GEN 2 VOLTAGE INC/DEC
APU GEN EXCITATION FAIL
APU GEN VOLTAGE INC/DEC
DUAL GEN FAIL
GEN 1 TRANSFER CONTACTOR OPEN
GEN 1 FREQUENCY INC/DEC
AC BUS TIE CONTACTOR 1 OPEN
GALLEY LOADS INC/DEC
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CHAPTER 11: ELECTRICAL POWER 1
MALFUNCTION : GEN 1 EXCITATION FAIL
MALFUNCTION DESCRIPTION :
CAUSE : GENERATOR 1 EXCITATION CIRCUIT FAIL
CONSEQUENCE :
- GEN 1 “FAULT” light indicator illuminates.
- If the aircraft is in flight phase 2, 3, 6, 9:
• The single chime sounds
• “CAUT” light illuminates,
• ELEC PAGE appears on DU-ECAM lower,
• A message appears on DU-ECAM upper. (LA24000F)
• Voltage and Frequency become zero.
- When GEN 1 push-button is switched off:
• “FAULT” light goes out,
• “OFF” light comes on.
- After successive “CLR” (Ecam Control Panel)
• The 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.
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CHAPTER 11: ELECTRICAL POWER 1
MALFUNCTION : GEN 2 EXCITATION FAIL
MALFUNCTION DESCRIPTION :
CAUSE : GENERATOR 2 EXCITATION CIRCUIT FAILS
CONSEQUENCE :
- GEN 2 “FAULT” light illuminates.
- If the aircraft is in flight phase 2, 3, 6, 9:
• The single chime sounds,
• “CAUT” light illuminates,
• ELEC page appears on DU-ECAM lower,
• A message appears on DU-ECAM upper. (LA24010F)
• Voltage and Frequency become zero.
- When GEN 2 push-button is switched off:
• “FAULT” light goes out,
• “OFF” light comes on.
- After successive “CLR” (ECAM Control Panel):
• The appropriate status page appears on SYS CRT.
- Appropriate messages will be available on MCDU (CFDS function)
(when CFDS maintenance option selected).
- Cancelling the malfunction restores normal operation.
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CHAPTER 11: ELECTRICAL POWER 1
MALFUNCTION : IDG 1 OIL OVERHEAT
MALFUNCTION DESCRIPTION :
CAUSE : Abnormal friction in IDG 1 constant speed drivemechanism
CONSEQUENCE :
When IDG 1 oil temperature is over 185 deg:
- IDG 1 “FAULT” light indicator illuminates.
- If the aircraft is in flight phase 1, 2, 3, 6, 9, 10:
• The single chime sounds,
• “CAUT” light illuminates,
• ELEC PAGE APPEARS ON DU-ECAM lower,
• A message appears on DU-ECAM upper.(LA24022C)
- After depressing IDG 1 push-button:
• “DISC” indication appears on ELEC ECAM page.
• when oil temperature is under 185deg “FAULT” light goes out.
- After successive “CLR” (Ecam Control Panel)
• The appropriate status page appears on SYS CRT.
- Appropriate messages will be available on MCDU (CFDS function)
(when CFDS maintenance option selected).
- Normal operation is restored by cancelling fault and depressing “IDG reconnect” ("ISD reset") or “MASTERRESET” on Instructor’s Station.
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CHAPTER 11: ELECTRICAL POWER 1
MALFUNCTION : IDG 2 OIL PRESS LO
MALFUNCTION DESCRIPTION :
CAUSE : CSD 2 faulty oil pressure switch
CONSEQUENCE :
- IDG 2 “FAULT” light illuminates.
- If the aircraft is in flight phase 2, 3, 6, 9:
• The single chime sounds,
• “CAUT” light illuminates,
• ELEC page appears on DU-ECAM lower,
• A message appears on DU-ECAM upper. (LA24030D)
- When IDG 2 push-button is depressed:
• “DISC” information appears on ELEC ECAM page
• “FAULT” light goes out.
- After successive “CLR” (ECAM Control Panel):
• The appropriate status page appears on SYS CRT.
- Appropriate messages will be available on MCDU (CFDS function)
(when CFDS maintenance option selected).
- Normal operation is restored by cancelling fault and depressing “ISD reset” or “MASTER RESET”.
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CHAPTER 11: ELECTRICAL POWER 1
MALFUNCTION : GEN 2 VOLTAGE INC/DEC
PARAMETER : GEN 2 VOLTAGE
MIN VALUE : 60 V MAX VALUE: 180 V CHANGE RATE: 6 V/s
MALFUNCTION DESCRIPTION :
CAUSE : Faulty GEN 2 excitation
CONSEQUENCE :
- Over 130 V or under 100 V after 4 seconds:
• GEN 2 “FAULT” light illuminates.
- If the aircraft is in flight phase 1, 2, 3, 6, 9, 10:
• The single chime sounds,
• “CAUT” light illuminates,
• ELEC page appears on DU-ECAM lower,
• A message appears on DU-ECAM upper (LA24010F)
- When GEN 2 push-button is switched off:
• “FAULT” light goes out,
• “OFF” light comes on.
- After successive “CLR” (ECAM Control Panel):
• The appropriate status page appears on SYS CRT.
- Appropriate messages will be available on MCDU (CFDS function)
(when CFDS maintenance option selected).
- Cancelling the malfunction restores normal operation
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CHAPTER 11: ELECTRICAL POWER 1
MALFUNCTION : APU GEN EXCITATION FAIL
MALFUNCTION DESCRIPTION :
CAUSE : Generator APU excitation circuit fails
CONSEQUENCE :
- APU GEN “FAULT” light illuminates.
- If the aircraft is in flight phase 1, 2, 3, 6, 9, 10:
• The single chime sounds,
• “CAUT” light illuminates,
• ELEC page appears on DU-ECAM lower,
• A message appears on DU-ECAM upper. (LA24040D1)
- When APU GEN push-button is switched off:
• “FAULT” light goes out,
• “OFF” light comes on.
- After successive “CLR” (ECAM Control Panel):
• The appropriate status page appears on SYS CRT.
- Appropriate messages will be available on MCDU (CFDS function)
(when CFDS maintenance option selected).
- Cancelling the malfunction restores normal operation.
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CHAPTER 11: ELECTRICAL POWER 1
MALFUNCTION : APU GEN VOLTAGE INC/DEC
PARAMETER : APU GEN VOLTAGE
MIN VALUE : 60 V MAX VALUE: 180 V CHANGE RATE: 6V/s
MALFUNCTION DESCRIPTION :
CAUSE : Faulty APU GEN excitation circuit
CONSEQUENCE :
- Over 130 V or under 100 V after 4 seconds:
• APU GEN “FAULT” light illuminates.
- If the aircraft is in flight phase 1, 2, 3, 6, 9, 10:
• The single chime sounds,
• “CAUT” light illuminates,
• ELEC page appears on DU-ECAM lower,
• A message appears on DU-ECAM upper.(LA24040D1)
- When APU GEN push-button is switched off:
• “FAULT” light goes out,
• “OFF” light comes on.
- After successive “CLR” (ECAM Control Panel):
• The appropriate status page appears on SYS CRT.
- Appropriate messages will be available on MCDU (CFDS function)
(when CFDS maintenance option selected).
- Cancelling the malfunction restores normal operation.
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CHAPTER 11: ELECTRICAL POWER 1
MALFUNCTION : DUAL GEN FAIL
MALFUNCTION DESCRIPTION :
CAUSE : Simultaneous failure of GEN 1 and GEN 2 excitationfailure
CONSEQUENCE :
- If APU is not running, main AC BUS BARS are lost, automatic extension of RAT. During few seconds no ACpower available except AC static inverter.
- Operation of emergency configuration is always available. (EMERG CONFIG)
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Cancelling malfunction and depressing “RAT RESET” restores normal operation.
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CHAPTER 11: ELECTRICAL POWER 1
MALFUNCTION : GEN 1 TRANSFER CONTACTOR OPEN
MALFUNCTION DESCRIPTION :
CAUSE : Contactor BTC1 11XU1 coil failure
CONSEQUENCE :
- If AC BUS 1XP is powered by GEN 1 and AC BUS 2XP powered by GEN 2 or APU GEN: no effect. Normalconfiguration.
- If GEN 1 off and one of GEN 2 or APU GEN or EXT PWR ready: loss of AC BUS 1XP.& AC ESS BUS.
• AC ESS “FAIL” light is illuminated.
If the aircraft is in phase 1, 2, 3, 5, 6, 7, 9, 10:
• The single chime sounds,
• “CAUT” light illuminates,
• Messages appears on DU-ECAM upper.(LA24090E)
• CRT supply is lost on DU-ECAM upper
- If GEN 2 off and APU GEN off and ext-PWR off and GEN 1 ready: loss of AC BUS 2XP.
If the aircraft is in phase 1, 2, 3, 5, 6, 7, 9, 10:
• The single chime sounds,
• “CAUT” light illuminates,
• CRT supply is lost on DU-ECAM lower
• Messages appears on DU-ECAM upper. (LA24100E)
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Cancelling the malfunction and depressing MASTER RESET on Instructor station restores normal operation.
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CHAPTER 11: ELECTRICAL POWER 1
MALFUNCTION : GEN 1 FREQUENCY INC/DEC
PARAMETER : GEN 1 FREQUENCY
MIN VALUE : 300 Hz MAX VALUE: 500 Hz CHANGE RATE:6 Hz/s
MALFUNCTION DESCRIPTION :
CAUSE : Faulty CSD speed regulation
CONSEQUENCE :
- Over 433 Hz or under 363 Hz after 3 seconds:
• GEN 1 “FAULT” light illuminates.
- If aircraft is in flight phase 1, 2, 3, 6, 9:
• The single chime sounds,
• “Caut” light illuminates,
• ELEC page appears on DU-ECAM lower,
• A message appears on DU-ECAM upper. (LA24000F)
- When GEN 1 push-button is switched off:
• “FAULT” light goes out,
• “OFF” light comes on.
- After successive “CLR” (ECAM Control Panel):
• The appropriate status page appears on SYS CRT.
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Cancelling the malfunction restores normal operation.
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CHAPTER 11: ELECTRICAL POWER 1
MALFUNCTION : AC BUS TIE CONTACTOR 1 OPEN
MALFUNCTION DESCRIPTION :
CAUSE : 9XU1 (GCL1) contactor coil failure andBTC1 11XU1 contactor coil failure
CONSEQUENCE :
Loss of AC BUS 1XP
- If the aircraft is in flight phase 1, 2, 3, 5, 6, 7, 9, 10:
• The single chime sounds,
• “CAUT” light illuminates,
• Messages appears on DU-ECAM lower, (LA24070D) and (LA24090E)
• CRT supply is lost on DU-ECAM upper.
• AC ESS FEED “FAIL” light comes on
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Cancelling the malfunction and depressing MASTER RESET on Instructor station restores normal operation.
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CHAPTER 11: ELECTRICAL POWER 1
MALFUNCTION : GALLEY LOADS INC/DEC
PARAMETER : GALLEY LOAD
MIN VALUE : 0 kVA MAX VALUE: 200 kVA CHANGE RATE:15 kVA/s
MALFUNCTION DESCRIPTION :
CAUSE : Faulty galley supply cable
CONSEQUENCE :
- If generators are over loaded (current 277 A during 13 seconds)
- If the aircraft is in flight phase 1, 2, 6, 9, 10:
• Single chime sounds.
• Master caution comes on.
• Appropriate message appears on DU-ECAM upper. (LA24165D)
• “ELEC” page appears on DU-ECAM lower.
• Galley “FAULT” light illuminates.
- When Galley push-button is switched off:
• “FAULT” light goes out,
• “OFF” light comes on.
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Cancelling the malfunction restores normal operation.
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CHAPTER 12 - ELECTRICAL POWER 2
CONTENTS:
AC BUS 1 FAULT
AC BUS 2 FAULT
DC BUS 1 FAULT
DC BUS 2 FAULT
AC ESS BUS FAULT
AC ESS SHED BUS FAULT
AC ESS FEED CONTACTOR FAIL
DC ESS BUS FAULT
DC ESS SHED BUS FAULT
BAT 1 CHARGE UNIT
BAT 2 CONTACTOR STUCK
BAT OVERHEAT
ESS TR FAIL
EMERG GEN FAULT
EMERG GEN OVRD FAIL
EMERG GEN TEST FAIL
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CHAPTER 12: ELECTRICAL POWER 2
MALFUNCTION : AC BUS 1 FAULT
MALFUNCTION DESCRIPTION :
CAUSE : Differential protection zone 2 leading to the openingof GLC and BTC by GCU.
CONSEQUENCE :
- AC BUS 1 is lost. (LA24070D) and (LA24090E).
- GEN 1 is lost.
- AC ESS BUS lost if AC ESS FEED p/b is in pushed position
If the aircraft is in flight phase 1, 2, 3, 5, 6, 7, 9, 10:
• The single chime sounds,
• “CAUT” light illuminates,
• Messages appears on DU-ECAM lower, (LA24090E)
• CRT supply is lost on DU-ECAM upper.
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
Cancelling malfunction and depressing “MASTER RESET” on instructor station restore normal operation.
Manual recycling of the corresponding CB is required to reset this malfunction.
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CHAPTER 12: ELECTRICAL POWER 2
MALFUNCTION : AC BUS 2 FAULT
MALFUNCTION DESCRIPTION :
CAUSE : Differential protection zone 2 leading to the openingof GLC and BTC by GCU.
CONSEQUENCE :
- AC BUS 2 is lost.
- GEN 2 is lost.
If the aircraft is in flight phase 1, 2, 3, 5, 6, 7, 9, 10:
• The single chime sounds,
• “CAUT” light illuminates,
• CRT supply is lost on DU-ECAM lower,
• Messages appear on DU-ECAM upper. (LA24100E)
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
Cancelling malfunction and depressing “MASTER RESET” on instructor station restore normal operation.
Manual recycling of the corresponding CB is required to reset this malfunction
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CHAPTER 12: ELECTRICAL POWER 2
MALFUNCTION : DC BUS 1 FAULT
MALFUNCTION DESCRIPTION :
CAUSE : Short circuit.
CONSEQUENCE :
If the aircraft is in flight phase 1, 2, 3, 5, 6, 7, 9, 10:
• The single chime sounds,
• “caut” light illuminates,
• ELEC page appears on DU-ECAM lower,
• A message appears on DU-ECAM upper. (LA24120E)
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
Cancelling malfunction and depressing “MASTER RESET” on instructor station restore normal operation.
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CHAPTER 12: ELECTRICAL POWER 2
MALFUNCTION : DC BUS 2 FAULT
MALFUNCTION DESCRIPTION :
CAUSE : Short circuit.
CONSEQUENCE :
If the aircraft is in flight phase 1, 2, 3, 5, 6, 7, 9, 10:
• The single chime sounds,
• “caut” light illuminates,
• ELEC page appears on DU-ECAM lower,
• A message appears on DU-ECAM upper. (LA24130E)
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
Cancelling malfunction and depressing “MASTER RESET” on instructor station restore normal operation.
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CHAPTER 12: ELECTRICAL POWER 2
MALFUNCTION : AC ESS BUS FAULT
MALFUNCTION DESCRIPTION :
CAUSE : Default of voltage detection on the AC ESS BUSleading to the opening of contactor 3XC.
CONSEQUENCE :
- AC ESS BUS 4XP and AC shed ESS 8XP are lost.
If the aircraft is in flight phase 1, 2, 3, 5, 6, 7, 9, 10:
• AC ESS FEED “FAULT” light comes on
• the single chime sounds,
• “CAUT” light illuminates,
• DU-ECAM upper is lost.
• Appropriate message appears on ECAM lower (E/W PAGE) (LA24070D)
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
Cancelling malfunction restores normal operation.
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MALFUNCTION : AC ESS SHED BUS FAULT
MALFUNCTION DESCRIPTION :
CAUSE : Contactor 8XH coil fail
CONSEQUENCE :
If the aircraft is in flight phase 1, 2, 3, 5, 6, 7, 9, 10:
• The single chime sounds,
• “CAUT” light illuminates,
• ELEC page appears on DU-ECAM lower,
• A message appears on DU-ECAM upper. (LA24070D)
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
Cancelling malfunction restores normal operation.
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MALFUNCTION : AC ESS FEED CONTACTOR FAIL
MALFUNCTION DESCRIPTION :
CAUSE : Contactor 3XC side 1 and 2 fail open.
CONSEQUENCE :
If emergency generator is not running:
Loss of AC ESS BUS 4XP and AC SHED BUS 8XP.
If the aircraft is in flight phase 1, 2, 3, 5, 6, 7, 9, 10:
• The single chime sounds,
• “CAUT” light illuminates,
• Messages appears on DU-ECAM lower. (LA24070D)
• DU-ECAM upper is lost.
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
Cancelling malfunction restores normal operation.
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MALFUNCTION : DC ESS BUS FAULT
MALFUNCTION DESCRIPTION :
CAUSE : Over current leading to the opening of contactor 4PC.
CONSEQUENCE :
DC 4PP and 8PP bus bars are lost.
If the aircraft is in flight phase 1, 2, 3, 5, 6, 7, 9, 10:
• The single chime sounds,
• “CAUT” light illuminates,
• ELEC page appears on DU-ECAM lower,
• A message appears on DU-ECAM upper. (LA24150D).
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
Cancelling malfunction restores normal operation.
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MALFUNCTION : DC ESS SHED BUS FAULT
MALFUNCTION DESCRIPTION :
CAUSE : Contactor 8PH stuck open.
CONSEQUENCE :
If the aircraft is in flight phase 1, 2, 3, 5, 6, 7, 9, 10:
• The single chime sounds
• “CAUT” light illuminates,
• ELEC page appears on DU-ECAM lower,
• A message appears on DU-ECAM upper. (LA24160F)
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
Cancelling malfunction restores normal operation.
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MALFUNCTION : BAT 1 CHARGE UNIT
MALFUNCTION DESCRIPTION :
CAUSE : Ramdom short in BAT 1 charge control unit circuity
CONSEQUENCE :
- BAT 1 never comes in line. Its voltage decreases continuously
- Cancelling malfunction restores normal operation
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MALFUNCTION : BAT 2 CONTACTOR STUCK
MALFUNCTION DESCRIPTION :
CAUSE : BAT 2 contactor stuck in position
CONSEQUENCE :
- If stuck open:
• BAT 2 never comes in line. Its voltage decreases slowly and continuously
- If stuck closed:
• If BUS BAR 3PP supplied by transformer-rectifier then BAT 2 is charged continuously else DC BUS BAR 3PP isalways supplied by BAT 2.
- Cancelling malfunction restores normal operation
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MALFUNCTION : BAT OVERHEAT
MALFUNCTION DESCRIPTION :
CAUSE : Faulty BAT 1 overheat detection
CONSEQUENCE :
BAT “FAULT” light illuminates.
If the aircraft is in flight phase 1, 2, 6, 9, 10:
• The single chime sounds,
• “CAUT” light illuminates,
• ELEC page appears on DU-ECAM lower,
• A message appears on DU-ECAM upper. (LA24050D)
• Battery line contactor 1 is automatically lockout.
When BAT 1 is switched off:
• “FAULT” light goes out,
• “OFF” light comes on.
After successive “CLR” (ECAM Control Panel):
• The 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.
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CHAPTER 12: ELECTRICAL POWER 2
MALFUNCTION : ESS TR FAIL
MALFUNCTION DESCRIPTION :
CAUSE : Primary winding cut
CONSEQUENCE :
- IF DC ESS BUS and DC SHED BUS powered by ESS TR: (Los of AC BUS 1 for example)
Then loss of DC ESS 4PP and DC SHED 8PP
- If the aircraft is in flight phase 1, 2, 3, 5, 6, 7, 9, 10:
• The single chime sounds
• “caut” light illuminates
• Messages appears on ECAM CRT powered (LA24150D)
• “ELEC” page appears on DU-ECAM lower.
- In other case malfunction has no effect
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Normal operation is restored by cancelling malfunction and depressing “MASTER RESET” pb on instructor station.
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MALFUNCTION : EMERG GEN FAULT
MALFUNCTION DESCRIPTION :
CAUSE : Failure of constant speed motor
CONSEQUENCE :
- If only emergency power available loss of total AC power except AC static inverter.
- If emergency Gen test sequence:
On Elec page: emergency Gend doesn’t appear.
• AC ESS BUS is supplied by battery via static inverter.
• Appropriate message appears on DU-ECAM upper.
• RAT & EMER GEN “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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MALFUNCTION : EMERG GEN OVRD FAIL
MALFUNCTION DESCRIPTION :
CAUSE : 24XE push-button fail EMR GEN “MAN” on ELEC
CONSEQUENCE :
- RAT manual extension is impossible. (see HYDRAULIC page)
- No electrical power is given by the CSM/G.
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Cancelling malfunction restores normal operation.
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MALFUNCTION : EMERG GEN TEST FAIL
MALFUNCTION DESCRIPTION :
CAUSE : Relay 21XE fail
CONSEQUENCE :
- On elec page “Emer Gen” doesn’t appear.
- Appropriate message appears on DU-ECAM upper.
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Cancelling malfunction restores normal operation.
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CHAPTER 13 - ENGINE CFM
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
INGNITION FAIL #1
REVERSER UNLOCKED # 1
CHAPTER 13 - ENGINE CFM (CONT’D)
SERIOUS ENG DAMAGE WITH EXTINGUISH. FIRE #1
SERIOUS ENG DAMAGE WITH EXTINGUISH. FIRE #2
SERIOUS ENG DAMAGE WITH UNEXTING FIRE #1
SERIOUS ENG DAMAGE WITH UNEXTING FIRE #2
SERIOUS ENG DAMAGE WITH PARTIAL PWR LOSS #1
SERIOUS ENG DAMAGE WITH PARTIAL PWR LOSS #2
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THROTTLE INOPERATIVE (POWER STUCK) #1
THROTTLE INOPERATIVE (POWER STUCK) #2
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
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CHAPTER 13: ENGINE CFM
MALFUNCTION : BOTH ENGINES FLAME OUT
MALFUNCTION DESCRIPTION :
CAUSE : Engines 1 § 2 flame out
CONSEQUENCE :
As long as engines 1 § 2 are greater than 48 % FADEC 1 § 2 try to restart engines 1 §2, energizing both ignitors.
Engines 1 § 2 stop
On ground:
• Complete loss of electrical supply
In flight:
• CRC sounds
• Master warning light comes on
• Corresponding messages appear on the E/W CRT (LA77275)
Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
Cancelling malfunction restores normal operation.
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CHAPTER 13: ENGINE CFM
MALFUNCTION : FLAME OUT #1
MALFUNCTION DESCRIPTION :
CAUSE : Combustion stopped
CONSEQUENCE :
- As long as N2 is greater than 48 % , 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 (LA77240)
- 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 snapshotdata corresponding to malfunction are displayed on the MCDU. (when BITE TSD maintenance option selected)
- Cancelling malfunction restores normal operation.
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CHAPTER 13: ENGINE CFM
MALFUNCTION : FLAME OUT # 2
MALFUNCTION DESCRIPTION :
CAUSE : Combustion stopped
CONSEQUENCE :
- As long as N2 is greater than 48 % , 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 the E/W CRT (LA77250)
- 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
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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 goes out
- 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 RESET
• On fire panel ENG 1 AGENT 1 “DISH” light goes out.
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CHAPTER 13: ENGINE CFM
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 (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 (LA26020 then 77270)
• “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 ENG2 “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
• If activated
• Master “Warn” light goes out
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Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
In order to recover normal operation:
- Cancel malfunction
- Release the “ENG2 FIRE” push button (FIRE PANEL)
• On fire panel, ENG2 AGENTS “SQUIB” lights go out
- On instructor station set the AGENT FIRE RESET
- On fire panel ENG2 AGENT1 1 and 2 “DISH” lights go out.
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CHAPTER 13: ENGINE CFM
MALFUNCTION : UNEXTINGUISHABLE 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 (LA26010 then LA77260)
• 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 “SQUIB” lights come on
• All warnings remain on
• Engine 1 is stopped
Push the AGENT 2 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
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Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
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
- On fire panel ENG 1 AGENT 1 and 2 “DISH” light goes out.
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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 (LA26020 then LA77270)
• “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 comes 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
• Engine 2 is stopped
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CHAPTER 13: ENGINE CFM
Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
Cancelling malfunction restores 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
• On fire panel ENG 2 AGENTS 1 and 2 “DISH” lights go out.
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MALFUNCTION : COMPRESSOR STALL #1
MALFUNCTION DESCRIPTION :
CAUSE : Compressor stall
CONSEQUENCE :
• If N1 > 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
• Cancelling malfunction restores normal operation
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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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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
• 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
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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
- When CFDS is operating in MENU mode and BITE TSD (Trouble Shooting Data) function is selected, the snapshotdata corresponding to malfunction are displayed on the MCDU. (when BITE TSD maintenance option selected)
- Cancelling malfunction restores normal operation
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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 for6 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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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 secondsas soon as start failure is detected:
• Appropriate message appears on the E/W CRT
- 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
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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).
Cancelling malfunction restores normal operation
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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)
Cancelling malfunction restores normal operation
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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)
- Appropriate messages will be available on MCDU (CFDS function) when CFDS maintenance option selected.
- Cancelling malfunction restores normal operation.
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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)
- Appropriate messages will be available on MCDU (CFDS function) when CFDS maintenance option selected.
- Cancelling malfunction restores normal operation
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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)
• “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.
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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)
• “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.
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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).
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Cancelling malfunction restores normal operation.
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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)
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Cancelling malfunction restores normal operation
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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).
Cancelling the malfunction restores normal operation.
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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,
• Master caution comes on
• Appropriate message appears E/W CRT, (LA77860)
• ENGINE page appears on the SYS CRT (if applying).
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- 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
N.B. Failure on, engine 1 can’t be started
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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
• Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Cancelling malfunction restores normal operation.
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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
• After 10 seconds, all fire warnings remain on
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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 malfunction
- Release the “ENG1 FIRE” pushbutton (FIRE PANEL)
- On instructor station set the AGENT FIRE RESET
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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
• After 10 seconds, all fire warnings remain on
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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
In order to recover normal operation:
- Cancel malfunction
- Release the “ENG2 FIRE” pushbutton (FIRE PANEL)
- On instructor station set the AGENT FIRE RESET
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MALFUNCTION : SERIOUS ENG DAMAGE WITH UNEXTINGFIRE #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).
Cancelling malfunction restores normal operation.
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MALFUNCTION : SERIOUS ENG DAMAGE WITH UNEXTINGFIRE 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).
Cancelling malfunction restores normal operation.
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MALFUNCTION : SERIOUS ENG DAMAGE WITH PARTIAL PWRLOSS #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 normaloperation.
- 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.
- Cancelling malfunction restors normal operation.
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MALFUNCTION : SERIOUS ENG DAMAGE WITH PARTIAL PWRLOSS #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:
• Compressor stall disappears
- If throttle 2 is reduced, normal vibrations value is restored
- Cancelling malfunction restores normal operation
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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 throttleposition is.
• No warning
Cancelling malfunction restores normal operation.
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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 throttleposition is.
• No warning
Cancelling malfunction restores normal operation.
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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
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Cancelling malfunction restores normal operation.
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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 SYSCRT). 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
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Cancelling malfunction restores normal operation.
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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)
• “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
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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
- 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 snapshotdata corresponding to malfunction are displayed on the MCDU. (when BITE TSD maintenance option selected)
- Cancelling malfunction restores normal operation
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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).
Cancelling malfunction restores normal operation.
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MALFUNCTION : IDLE CONTROL FAIL #1
MALFUNCTION DESCRIPTION :
CAUSE : EIU 1 failure
CONSEQUENCE :
- Only flight idle can be obtained on engine 1
- No warning
- Cancelling malfunction restores normal operation
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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 snapshotdata corresponding to malfunction are displayed on the MCDU. (when BITE TSD maintenance option selected)
Cancelling malfunction restores normal operation.
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MALFUNCTION : MAN START FAULT #1
MALFUNCTION DESCRIPTION :
CAUSE : Disagree between Master Switch position andHPSOV 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.
N.B. cf IGNITION A+B FAULT if FWC requests are not proceeded
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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).
- Cancelling malfunction restores normal operation.
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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))
VIBRATIONS N2 PEAK (# 2 (%/U))
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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).
- Cancelling malfunction and/or engine oil pressure greater than 18 psi restore normal operation
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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
- 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
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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.
N.B. Oil quantity maximum values is limited to initial quantity.
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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
N.B. Oil quantity maximum value is limited to initial quantity.
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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 CHANGERATE: 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.
N.B. EGT minimum value is limited to static air temperature.
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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 CHANGERATE: 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
N.B. EGT minimum value is limited to static air temperature.
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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)
- If N1 has overriden 102 %, N1 maximum value is memorized and a small red line is positioned at that value on theindicator.
- Appropriate messages will be available on MCDU (CFDS function)(when CFDS maintenance option selected).
- Cancelling malfunction restores normal operation.
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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)
- If N1 has overridden 102 % , N1 maximum value is memorized and a small red line is positioned at that value on theindicator
- Appropriate messages will be available on MCDU (CFDS function)(when CFDS maintenance option selected).
- Cancelling malfunction restores normal operation
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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.
- Appropriate messages will be available on MCDU (CFDS function)(when CFDS maintenance option selected).
- Cancelling malfunction restores normal operation.
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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
- Appropriate messages will be available on MCDU (CFDS function)(when CFDS maintenance option selected).
- Cancelling malfunction restores normal operation
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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.
- Engine 1 N1 numerical indication is replaced by amber crosses on the E/W CRT.
- Cancelling the malfunction restors normal operation.
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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
- Cancelling malfunction restores normal operation
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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 CHANGERATE: 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 snapshotdata corresponding to malfunction are displayed on the MCDU. (when BITE TSD maintenance option selected).
- Cancelling malfunction restores normal operation
N.B. Oil temperature minimum value is limited to static air temperature
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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
If fuel flow decreases, all engine 1 parameters decrease too
- Cancelling malfunction restores normal operation.
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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
Complementary data: NACELLE TEMP minimum value is limited to SAT value.
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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.
N.B. N1 vibrations advisory level depends on N1 actual value and EVMU initial values.
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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
N.B. N2 vibrations advisory level depends on N2 actual value and EVMU initial values.
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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 abnormalengine 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 thevibration 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
N.B. All advisories are always functionnal but there is no real correlation with bite unbalance functions (ifavailable on simulators).
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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 abnormalengine 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 thevibration 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
N.B.: All advisories are always functionnal but there is no real correlation with bite unbalance functions (ifavailable on simulators).
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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 abnormalengine 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 thevibration 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
N.B.: All advisories are always functionnal but there is no real correlation with bite unbalance functions (ifavailable on simulators).
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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 abnormalengine 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 thevibration 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
N.B.: All advisories are always functionnal but there is no real correlation with bite unbalance functions (ifavailable on simulators).
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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
RUDDER TRIMS RESET INOPERATIVE
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MALFUNCTION : YAW DAMPER SYS 1 FAULT
MALFUNCTION DESCRIPTION :
CAUSE : Electrical power failure of Actuator 1 (detected byFAC1)
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)
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Cancelling malfunction restores normal operation
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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:
• 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
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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 indicatorManual 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)
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Cancelling malfunction restores normal operation
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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 indicatorManual 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)
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Cancelling malfunction restores normal operation
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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:
• 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 snapshotdata 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 isnecessary
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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).
- Cancelling malfunction restores normal operation
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CHAPTER 15: FAC
MALFUNCTION : FAC 1 FAIL
MALFUNCTION DESCRIPTION :
CAUSE : This fault corresponds to a detected failure in theFlight 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)
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 isnecessary
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CHAPTER 15: FAC
MALFUNCTION : FAC 2 FAIL
MALFUNCTION DESCRIPTION :
CAUSE : This fault corresponds to an internal hardware failurein 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)
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 isnecessary
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CHAPTER 15: FAC
MALFUNCTION : RUDDER TRIMS RESET INOPERATIVE
MALFUNCTION DESCRIPTION :
CAUSE : This fault corresponds to an electrical cut betweenthe 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 snapshotdata corresponding to malfunction are displayed on the MCDU. (when BITE TSD maintenance option selected)
2 - Cancelling malfunction restores normal operation
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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)
THR TARGET NEEDLE FAIL
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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.
- Cancelling malfunction restores normal operation
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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.
- Cancelling malfunction restores normal operation
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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 snapshotdata corresponding to malfunction are displayed on the MCD. (when BITE TSD maintenance option selected)
- Cancelling malfunction restores normal operation
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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
• 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
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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)
• “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 snapshotdata corresponding to malfunction are displayed on the MCDU. (when BITE TSD maintenance option selected)
- Cancelling malfunction restores normal operation
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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)
• “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
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CHAPTER 16: FADEC CFM
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 phasewhatever the throttle 1 position is.
- Cancelling malfunction restores normal operation
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CHAPTER 16: FADEC CFM
MALFUNCTION : INCORR REV PWR ENG 2 (HIGH)
MALFUNCTION DESCRIPTION :
CAUSE : Sensors failure
CONSEQUENCE :
- Engine 2 reverse extends normally but engine 2 performances reached then remain at high power during the wholereverse phase whatever the throttle 2 position is.
- Cancelling malfunction restores normal operation
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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
- Cancelling malfunction restores normal operation
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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
AFT CARGO SMOKE
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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
• 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
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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
• Master “WARN” light comes on
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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)
(when CFDS maintenance option selected).
- Cancelling malfunction restores normal operation
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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
• 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
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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
• Master “WARN” light goes out
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Cancelling malfunction restores normal operation
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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
• smoke is extracted automatically (about 2 min).
- Cancelling malfunction restores normal operation
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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 breakerEIS 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).
- Cancelling malfunction restores normal operation
- The E/W CRT smoke warning is resetted in flight phase 10
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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
• 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.
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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
- On instructor station, set the AGENT FIRE RESET, if it is installed the “DISH” lights go out
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CHAPTER 18 - FLIGHT COMPUTER
CONTENTS:
SEC 1 FAIL
SEC 2 FAIL
SEC 3 FAIL
ELAC 1 FAIL
ELAC 2 FAIL
FCDC 2 FAIL
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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 OFFlight is illuminated.
5) Appropriate messages will be available on MCDU (CFDS function)
(when CFDS maintenance option selected).
6) Cancelling the malfunction restores normal operation after reset of SEC 1 computer.
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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 OFFlight is illuminated.
5) Appropriate messages will be available on MCDU (CFDS function)(when CFDS maintenance option selected).
6) Cancelling the malfunction restores normal operation after reset of SEC 2 computer.
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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 OFFlight is illuminated.
5) Appropriate messages will be available on MCDU (CFDS function)(when CFDS maintenance option selected).
6) Cancelling the malfunction restores normal operation after reset of SEC 3 computer.
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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 OFFlight is illuminated.
5) Appropriate messages will be available on MCDU (CFDS function)
(when CFDS maintenance option selected).
6) Cancelling the malfunction restores normal operation after reset of ELAC 1 computer.
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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 OFFlight is illuminated.
5) Appropriate messages will be available on MCDU (CFDS function)(when CFDS maintenance option selected).
6) Cancelling the malfunction restores normal operation after reset of ELAC 2 computer.
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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
5) Cancelling the malfunction restores normal operation
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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
FCU FAIL
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CHAPTER 19: FMGC
MALFUNCTION : AP1 DISENGAGED (FD1 AVAILABLE)
MALFUNCTION DESCRIPTION :
CAUSE : Cut between AP INSTINCTIVE DISCONNETswitch 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).
3 - Cancelling malfunction restores normal operation AP1 can be reengaged by pilot action on AP1 pushbutton.
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CHAPTER 19: FMGC
MALFUNCTION : AP2 DISENGAGED (FD2 AVAILABLE)
MALFUNCTION DESCRIPTION :
CAUSE : Cut between AP INSTINCTIVE DISCONNECTswitch 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).
3 - Cancelling malfunction restores normal operation AP1 can be reengaged by pilot action on AP2 pushbutton.
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CHAPTER 19: FMGC
MALFUNCTION : AP1 LOC CAPTURE FAIL
MALFUNCTION DESCRIPTION :
CAUSE : LOC deviation sent by ILS1 and ILS2 to FMGC1 isfixed 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 LOCbeam
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
LOC deviation value is no more fixed.
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CHAPTER 19: FMGC
MALFUNCTION : AP2 LOC CAPTURE FAIL
MALFUNCTION DESCRIPTION :
CAUSE : LOC deviation sent by ILS1 and ILS2 to FMGC2 isfixed 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 engagedbut 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
LOC deviation value is no more fixed.
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CHAPTER 19: FMGC
MALFUNCTION : AP1 GLIDE CAPTURE FAIL
MALFUNCTION DESCRIPTION :
CAUSE : GLIDE deviation sent by ILS1 and ILS2 to FMGC1is 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 conditionsare 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).
3 - Cancelling malfunction restores normal operation GLIDE deviation value is no more fixed.
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CHAPTER 19: FMGC
MALFUNCTION : AP2 GLIDE CAPTURE FAIL
MALFUNCTION DESCRIPTION :
CAUSE : GLIDE deviation sent by ILS1 and ILS2 to FMGC2is 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 MODEdoesn’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
Glide deviation value is no more fixed.
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CHAPTER 19: FMGC
MALFUNCTION : AP1 ALIGN FAIL
MALFUNCTION DESCRIPTION :
CAUSE : Error on FMGC1 output sent to Flight controls: Bodyyaw 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
5 - Cancelling malfunction or ALIGN SUBMODE disengagement (loss of LAND TRACK MODE, AP1disengagement, ROLL OUT SUBMODE engagement). restores normal operation
- Appropriate messages will be available on MCDU (CFDS function)(when CFDS maintenance option selected).
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CHAPTER 19: FMGC
MALFUNCTION : AP2 ALIGN FAIL
MALFUNCTION DESCRIPTION :
CAUSE : Error on FMGC2 output sent to Flight controls: Bodyyaw 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
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).
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CHAPTER 19: FMGC
MALFUNCTION : ATHR1 FAIL
MALFUNCTION DESCRIPTION :
CAUSE : Cut of A/THR Bus information between FMGC1 andEIU.
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
3 - Cancelling malfunction restores normal operation ATHR1 can be reengaged by pilot action on ATHR pushbutton
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CHAPTER 19: FMGC
MALFUNCTION : ATHR2 FAIL
MALFUNCTION DESCRIPTION :
CAUSE : Cut of A/THR Bus information between FMGC2 andEIU.
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
3 - Cancelling malfunction restores normal operation ATHR2 can be reengaged by pilot action on ATHR pushbutton
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CHAPTER 19: FMGC
MALFUNCTION : NO FLARE
MALFUNCTION DESCRIPTION :
CAUSE : Error in the radio altitude transmitted by the Radioaltimeter 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).
3 - Cancelling malfunction restores normal operation FMGC1 and FMGC2 receive the true radio altitude.
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CHAPTER 19: FMGC
MALFUNCTION : LONG FLARE
MALFUNCTION DESCRIPTION :
CAUSE : Error in the radio altitude transmitted by the Radioaltimeter 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).
3 - Cancelling malfunction restores normal operation
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CHAPTER 19: FMGC
MALFUNCTION : DRIFT LOC BEAM (AUTOLAND)
MALFUNCTION DESCRIPTION :
CAUSE : LOC Deviation sent by ILS1 and ILS2 to FMGC1and 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
FMGC1 and FMGC2 receive the true loc deviation
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CHAPTER 19: FMGC
MALFUNCTION : LAND CAPABILITY CHANGE
MALFUNCTION DESCRIPTION :
CAUSE : Error on the signal “Power supply split” (input ofFMGC1)
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).
3 - Cancelling malfunction restores normal operation
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CHAPTER 19: FMGC
MALFUNCTION : RADIO ALTI DISCREPANCY (AUTOLAND)
MALFUNCTION DESCRIPTION :
CAUSE : Radio altitudes delivered by RA1 and RA2 present adifference 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
Cancelling the malfunction restores normal operation
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CHAPTER 19: FMGC
MALFUNCTION : LOC CAPT STUCK
MALFUNCTION DESCRIPTION :
CAUSE : Bad coupling of the LOC antenna on the LOCreceiver 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 indexremains 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).
Cancelling the malfunction restores normal operation.
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CHAPTER 19: FMGC
MALFUNCTION : LOC CAPT DRIFT
MALFUNCTION DESCRIPTION :
CAUSE : Bad coupling of the LOC antenna on the LOCreceiver 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 indexdrifts 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 thenremains 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).
Cancelling the malfunction restores normal operation.
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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.
Cancelling the malfunction restores normal operation.
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CHAPTER 19: FMGC
MALFUNCTION : PVI FAIL
MALFUNCTION DESCRIPTION :
CAUSE : Loss of power supply to the PVI
CONSEQUENCE :
PVI is no more operational and shows no information.
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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
3 - Cancelling the malfunction and resetting circuit breaker restore normal operation
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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).
3 - Cancelling malfunction restores normal operation
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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.
- Appropriate messages will be available on MCDU (CFDS function)(when CFDS maintenance option selected).
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CHAPTER 19: FMGC
MALFUNCTION : FLIGHT MANAGEMENT 1 FAIL
MALFUNCTION DESCRIPTION :
CAUSE : NOT POSSIBLE
CONSEQUENCE :
NOT POSSIBLE
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CHAPTER 19: FMGC
MALFUNCTION : FCU SPEED SYNCHRO FAIL
MALFUNCTION DESCRIPTION :
CAUSE : NO TRANSMISSION OF THE SPEED FROM THEFCU 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 bothPFD’s. ATS function does not follow new FCU speed selection and keeps as target the selected speed valid whenmalfunction breakdown.
- Appropriate messages will be available on MCDU (CFDS function)(when CFDS maintenance option selected).
Cancelling the malfunction on instructor station restores normal operation.
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CHAPTER 19: FMGC
MALFUNCTION : FCU REDONDANCY LOST
MALFUNCTION DESCRIPTION :
CAUSE : Cut between FCU and FMGC1 and FMGC2 of thesignal 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).
Cancelling the malfunction restores normal operation
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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 bereengaged 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
Normal operation
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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
REFUELLING FAIL
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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):
• 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.
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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:
• Appropriate STATUS page appears on SYS CRT
- Cancelling malfunction restores normal operation.
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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):
• 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.
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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):
• 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.
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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):
• Appropriate STATUS page appears on SYS CRT
- Appropriate messages will be available on MCDU (CFDS function)(when CFDS maintenance option selected).
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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):
• 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.
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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 isaffected
CONSEQUENCE :
- For all flight phases:
• Left inner cell fuel quatity displayed by ECAM varies in accordance with the quantity selected by the instructor andtotal 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.
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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 isaffected
CONSEQUENCE :
- For all flight phases:
• Right inner cell fuel quantity displayed by ECAM varies in accordance with the quantity selected by the instructorand 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.
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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):
• 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.
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CHAPTER 20: FUEL A320
MALFUNCTION : RIGHT WING QTY PROBE FAILED
MALFUNCTION DESCRIPTION :
CAUSE : PROBE 21QT2 and 33QT2 failed
CONSEQUENCE :
- For all flight phases:
• Right outer cell Fuel quantity and total fuel quantity displayed by ECAM are downgraded (the two least significantdigits 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.
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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.
- Appropriate messages will be available on MCDU (CFDS function)(when CFDS maintenance option selected).
- Cancelling malfunction restores normal operation.
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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):
• 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.
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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.
- Cancelling malfunction restores normal operation.
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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
RAT NO AUTOMATIC EXTENSION # B
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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 thequantity 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
• 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
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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).
- Cancelling malfunction restores normal operations.
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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 thequantity 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:
• 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.
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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 thequantity 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
• The action is fed back on the E/W and SYS CRT’s (HYD and status pages)
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- 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).
- Cancelling malfunction restores normal operations.
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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 overheatdisappears
- Whatever the PTU (AUTO) P/B (40 VU) position, its “FAULT” light comes on, and remains on until overheatdisappears
- 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
• 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.
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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 themalfunction 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.
• 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.
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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 untilOVERHEAT disappears
- Whatever the PTU (AUTO) P/B (40 VU) position, its “FAULT” light comes on, and remains until overheatdisappears
- Whatever the yellow elec. pump P/B (40 VU) position, its “FAULT” light comes on, and remains on untilOVERHEAT 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
• The action is fed back on the E/W and SYS CRT’s unit (HYD’s and STATUS pages)
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- 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)
- 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.
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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
• 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.
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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
• 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
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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
• Blue system pressure increases until 3000 psi
• Message and warning reappear on SYS CRT but not on E/W CRT
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- 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
• Message and warning reappear on SYS CRT and E/W CRT
- To delete message you must lose electrical power
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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
• 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.
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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 arefailed
CONSEQUENCE :
- Pressure indicated on the HYD page (SYS CRT) and low pressure detected by the switch (system) are according tothe value generated by the indicator.
- But the real system pressure is not changed and the system working is correct, so no physical consequences but onlywarning consequences.
NOTE: The system pressure value is constantly refreshed on the HYD page and to the ELAC (elevator andaileron 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:
• 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.
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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)
- Appropriate messages will be available on MCDU (CFDS function)(when CFDS maintenance option selected).
- Cancelling malfunction restores normal operations.
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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 arefailed
CONSEQUENCE :
- Pressure indicated on the HYD’s page (SYS CRT) and low pressure detected by the switch (system) are according tothe value generated by the instructor.
- But the real system pressure is not changed and the system working is correct, so no physical but only warningconsequences.
NOTE: The system pressure value is constantly refreshed on the HYD page and to the ELAC (elevator andaileron 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,
• SPOILER 4
• FLAPS
- Appropriate messages will be available on MCDU (CFDS function)(when CFDS maintenance option selected).
- Cancelling malfunction restores normal operations.
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MALFUNCTION : ELEC PUMP FAIL # B
MALFUNCTION DESCRIPTION :
CAUSE : The three-phases AC bus control unit is failed, anddeenergizes 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 configurationits “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 blueelec. 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)
• 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.
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MALFUNCTION : ELEC PUMP FAIL # Y
MALFUNCTION DESCRIPTION :
CAUSE : The three phases AC bus control unit is failed anddeenergizes 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 isoperating
- 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
- 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.
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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
• 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.
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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, andchange one of these conditions.
- 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
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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)
• 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.
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MALFUNCTION : RAT NO AUTOMATIC EXTENSION #B
MALFUNCTION DESCRIPTION :
CAUSE : Rat deployement solenoid 1 failed
CONSEQUENCE :
RAT can only be extended by electrical deployment system
- Cancelling malfunction restores normal operation.
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CHAPTER 22 - INSTRUMENTS
CONTENTS:
STAND BY ASI FAIL
STAND BY HORIZON FAIL
STAND BY ALTI FAIL
VOR/DME RMI FAIL
ADF RMI FAIL
PRINTER FAIL
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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
- Cancelling the malfunction restores normal operation
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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.
Cancelling the malfunction restores normal operation.
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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
- Cancelling the malfunction restores normal operation.
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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.
ACTION: NIL
- Cancelling the malfunction restores normal operation.
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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
- Cancelling the malfunction restores normal operation
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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.
- 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 documentwas just being printed, before the malfunction, the listing is lost.
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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
RUDDER STEERING FAIL
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CHAPTER 23: LANDING GEAR
MALFUNCTION : LEFT L/G NOT DOWN LOCKED
MALFUNCTION DESCRIPTION :
CAUSE : LH gear does not lock in down positionLH 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 notilluminate. 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 LHgear retract at landing.
- ECAM warning and messages are conformed to ’32245’ referenced primary failure.
- Cancelling the malfunction restores normal operation.
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CHAPTER 23: LANDING GEAR
MALFUNCTION : RIGHT L/G NOT DOWN LOCKED
MALFUNCTION DESCRIPTION :
CAUSE : RH gear does not lock in down positionRH gear down lock inoperativeNota: 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 notilluminate. 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 RHgear retract at landing.
- ECAM warning and messages are conformed to ’32245’ referenced primary failure.
- Cancelling the malfunction restores normal operation.
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CHAPTER 23: LANDING GEAR
MALFUNCTION : NOSE L/G DEFINITIVELY RETRACTED
MALFUNCTION DESCRIPTION :
CAUSE : Gear actuator does not operate: mechanicallystuck gear locking actuatorNota: Malfunction is active only when set beforeL/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.
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CHAPTER 23: LANDING GEAR
MALFUNCTION : RIGHT L/G DEFINITIVELY RETRACTED
MALFUNCTION DESCRIPTION :
CAUSE : Gear actuator does not operate: mechanically stuckgear locking actuatorNota: Malfunction is active only when set before L/Gunlocked 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.
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CHAPTER 23: LANDING GEAR
MALFUNCTION : L/G DEFINITIVELY RETRACTED
MALFUNCTION DESCRIPTION :
CAUSE : The 3 gear actuators do not operate:Mechanically stuck gear locking actuatorsNota: 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.
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CHAPTER 23: LANDING GEAR
MALFUNCTION : L/G LEVER LOCKED
MALFUNCTION DESCRIPTION :
CAUSE : Internal interlock prevents to set landing gear lever toup position, on system 1 and 2.
CONSEQUENCE :
- L/G cannot be retracted.
- Motion vibrations will increase rapidly above 240 knots.
- Cancelling the malfunction restores normal operation.
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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/Gis 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.
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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.
- It is impossible to use landing gear by selector lever, gravity extension is only possible but without any indicatorlight.
- 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.
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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).
- Cancelling the malfunction restores normal operation.
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CHAPTER 23: LANDING GEAR
MALFUNCTION : LEFT L/G MAIN DOOR STAYS OPEN
MALFUNCTION DESCRIPTION :
CAUSE : LH door actuator jams in open position (duringretraction 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.
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CHAPTER 23: LANDING GEAR
MALFUNCTION : L/G PANEL INDICATOR FAIL
MALFUNCTION DESCRIPTION :
CAUSE : Circuit breaker 1GA trips
CONSEQUENCE :
- The indicator lights and the control lever down arrow light remain off, whatever is the state of the landing gear. Thelight test remains operative.
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CHAPTER 23: LANDING GEAR
MALFUNCTION : ABNORMAL VIBRATION FROM NOSE L/G(DOWN)
MALFUNCTION DESCRIPTION :
CAUSE : Tire retread of nose L/G unsticks
CONSEQUENCE :
- 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.
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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 isvalid.
- 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.
- Cancelling the malfunction restores normal operation.
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CHAPTER 23: LANDING GEAR
MALFUNCTION : RUDDER STEERING FAIL
MALFUNCTION DESCRIPTION :
CAUSE : The order coming from the pedals fails beforecoming in the BSCU
CONSEQUENCE :
- 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.
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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
THS MOTOR 3 FAIL
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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.
3) Cancelling the malfunction restores normal operation.
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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.
3) Cancelling the malfunction restores normal operation.
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CHAPTER 24: PITCH CONTROL
MALFUNCTION : CAPT SIDE STICK INOP
MALFUNCTION DESCRIPTION :
CAUSE : CAPT side stick wiring is disconnected (pitch androll 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).
6) Cancelling the malfunction restores normal operation
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CHAPTER 24: PITCH CONTROL
MALFUNCTION : F/O SIDE STICK INOP
MALFUNCTION DESCRIPTION :
CAUSE : F/O side stick wiring is disconnected (pitch and rollaxis)
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).
6) Cancelling the malfunction restores normal operation
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CHAPTER 24: PITCH CONTROL
MALFUNCTION : ERRONEOUS CAPT PITCH UP ORDER
MALFUNCTION DESCRIPTION :
CAUSE : Erroneous potentiometers order in Pitch to ELACsand SECs
CONSEQUENCE :
1) The CAPT side stick Pitch order is blocked to up deflection
2) No message on the ENGINES WARNINGS display.
3) Cancelling the malfunction restores normal operation.
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CHAPTER 24: PITCH CONTROL
MALFUNCTION : ERRONEOUS F/O PITCH UP ORDER
MALFUNCTION DESCRIPTION :
CAUSE : Erroneous potentiometers order in Pitch to ELACsand SECs
CONSEQUENCE :
1) The F/O side stick Pitch order is blocked to up deflection.
2) No message on the ENGINES WARNINGS display.
3) Cancelling the malfunction restores normal operation.
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CHAPTER 24: PITCH CONTROL
MALFUNCTION : ERRONEOUS CAPT PITCH DOWN ORDER
MALFUNCTION DESCRIPTION :
CAUSE : Erroneous potentiometers order in Pitch to ELACsand SECs
CONSEQUENCE :
1) The CAPT side stick Pitch order is blocked to down deflection.
2) No message on the ENGINES WARNINGS display.
3) Cancelling the malfunction restores normal operation.
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CHAPTER 24: PITCH CONTROL
MALFUNCTION : ERRONEOUS F/O PITCH DOWN ORDER
MALFUNCTION DESCRIPTION :
CAUSE : Erroneous potentiometers order in Pitch to ELACsand SECs
CONSEQUENCE :
1) The F/O side stick Pitch order is blocked to down deflection.
2) No message on the ENGINES WARNINGS display.
3) Cancelling the malfunction restores normal operation.
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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).
5) Cancelling the malfunction restores normal operation.
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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).
5) Cancelling the malfunction restores normal operation.
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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).
5) Cancelling the malfunction restores normal operation.
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MALFUNCTION : SLATS/FLAPS HANDLE INOP
MALFUNCTION DESCRIPTION :
CAUSE : Slat/flap handle order fails before coming to theSFCCs (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 snapshotdata corresponding to malfunction are displayed on the MCDU. (when BITE TSD maintenance option selected).
6) Cancelling the malfunction restores normal operation
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MALFUNCTION : SLATS STUCK BY TIP BRAKE
MALFUNCTION DESCRIPTION :
CAUSE : The SFCCs detect asymmetric slats movement aftercontrol 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).
6) Cancelling the malfunction restores normal operation
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MALFUNCTION : FLAPS STUCK BY TIP BRAKE
MALFUNCTION DESCRIPTION :
CAUSE : The SFCCs detect asymmetric flaps movement aftercontrol 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 snapshotdata corresponding to malfunction are displayed on the MCDU. (when BITE TSD maintenance option selected)
6) Cancelling the malfunction restores normal operation
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MALFUNCTION : STAB YELLOW SERVO JAM
MALFUNCTION DESCRIPTION :
CAUSE : Jamming of the THS yellow hydraulic motor controlvalve 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).
5) Cancelling the malfunction restores normal operation.
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MALFUNCTION : LEFT ELEVATOR GREEN SERVO JAM
MALFUNCTION DESCRIPTION :
CAUSE : Jamming of a slide in the left elevator servo fed bythe 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).
5) Cancelling the malfunction restores normal operation.
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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).
6) Cancelling the malfunction restores normal operation.
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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).
6) Cancelling the malfunction restores normal operation.
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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
3) Cancelling the malfunction restores normal operation.
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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 snapshotdata corresponding to malfunction are displayed on the MCDU.(when BITE TSD maintenance option selected)
5) Cancelling the malfunction restores normal operation
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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).
5) Cancelling the malfunction restores normal operation.
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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).
5) Cancelling the malfunction restores normal operation.
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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
8) Cancelling the malfunction and resetting circuit breaker restore normal operation after reset of ELAC 2 computer.
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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).
6) Cancelling the malfunction restores normal operation after reset of ELAC 1 and ELAC 2 computers.
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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
LEFT AILERON BLUE SERVO JAM
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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.
3) Cancelling the malfunction restores normal operation.
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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.
3) Cancelling the malfunction restores normal operation.
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CHAPTER 25: ROLL CONTROL
MALFUNCTION : ERRONEOUS CAPT ROLL LEFT ORDER
MALFUNCTION DESCRIPTION :
CAUSE : Erroneous potentiometers order in Roll to ELACsand SECs
CONSEQUENCE :
1) The CAPT side stick roll order is blocked to left deflection.
2) No message on the ENGINES WARNINGS display.
3) Cancelling the malfunction restores normal operation.
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CHAPTER 25: ROLL CONTROL
MALFUNCTION : ERRONEOUS F/O ROLL LEFT ORDER
MALFUNCTION DESCRIPTION :
CAUSE : Erroneous potentiometers order in Roll to ELACsand SECs
CONSEQUENCE :
1) The F/O side stick Roll order is blocked to left deflection.
2) No message on the ENGINES WARNINGS display.
3) Cancelling the malfunction restores normal operation.
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CHAPTER 25: ROLL CONTROL
MALFUNCTION : ERRONEOUS CAPT ROLL RIGHT ORDER
MALFUNCTION DESCRIPTION :
CAUSE : Erroneous potentiometers order in Roll to ELACsand SECs
CONSEQUENCE :
1) The CAPT side stick roll order is blocked to right deflection.
2) No message on the ENGINES WARNINGS display.
3) Cancelling the malfunction restores normal operation.
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CHAPTER 25: ROLL CONTROL
MALFUNCTION : ERRONEOUS F/O ROLL RIGHT ORDER
MALFUNCTION DESCRIPTION :
CAUSE : Erroneous potentiometers order in Roll to ELACsand SECs
CONSEQUENCE :
1) The F/O side stick roll order is blocked to right deflection.
2) No message on the ENGINES WARNINGS display.
3) Cancelling the malfunction restores normal operation.
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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).
5) Cancelling the malfunction restores normal operation.
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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).
5) Cancelling the malfunction restores normal operation.
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CHAPTER 25: ROLL CONTROL
MALFUNCTION : LEFT SPEED BRAKE 3 NOT RETRACTED
MALFUNCTION DESCRIPTION :
CAUSE : The left speed brake 3 fails to retract for mechanicalreasons
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).
5) Cancelling the malfunction restores normal operation.
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CHAPTER 25: ROLL CONTROL
MALFUNCTION : RIGHT SPEED BRAKE 2 & 3 NOT RETRACTED
MALFUNCTION DESCRIPTION :
CAUSE : The right speed brakes 2 & 3 fail to rectract formechanical 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).
5) Cancelling the malfunction restores normal operation.
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CHAPTER 25: ROLL CONTROL
MALFUNCTION : LEFT AILERON BLUE SERVO JAM
MALFUNCTION DESCRIPTION :
CAUSE : Jamming of a slide in the left aileron servo fed by theblue 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).
5) Cancelling the malfunction restores normal operation.
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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
RMP 2 FAIL
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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 ispressed, 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 messageis displayed in the LH lower corner of the CAPT and F/O ND screens.
ACTION: NIL
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Cancelling the malfunction restores normal operation.
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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 redmessage is displayed in the RH lower corner of the CAPT and F/O ND screens.
ACTION: NIL
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Cancelling the malfunction restores normal operation.
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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 1informations 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 aredisplayed.
- 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 CAT3single 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
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Cancelling the malfunction restores normal operation.
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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 2informations 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 messagesare 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 CAT3single 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).
- Cancelling the malfunction restores normal operation.
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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 theassociated 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 isshowing above the A/C symbol.
ACTION: NIL
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Cancelling the malfunction restores normal operation.
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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 theassociated 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 isshowing above the A/C symbol.
ACTION: NIL
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Cancelling the malfunction restores normal operation.
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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 ofcategory.
- Indications and warning symbols/messages generated by ECAM: report to FWC boards 34360 + 34590.
ACTION: NIL
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Cancelling the malfunction restores normal operation.
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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 ofcategory.
- Indications and warning symbols/messages generated by ECAM: report to FWC board 34370 + 34600.
ACTION: NIL
- Appropriate messages will be available on MCDU (CFDS function) (when CFDS maintenance option selected).
- Cancelling the malfunction restores normal operation.
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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 theassociated 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).
- Cancelling the malfunction restores normal operation.
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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 theassociated 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).
- Cancelling the malfunction restores normal operation.
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CHAPTER 26: RADIO NAV
MALFUNCTION : MLS 1 RECEIVER FAIL
MALFUNCTION DESCRIPTION :
CAUSE : OPTION
CONSEQUENCE :
OPTION
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CHAPTER 26: RADIO NAV
MALFUNCTION : MLS 2 RECEIVER FAIL
MALFUNCTION DESCRIPTION :
CAUSE : OPTION
CONSEQUENCE :
OPTION
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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 isalso 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).
- Cancelling the malfunction restores normal operation.
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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 theFMGC2 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).
- Cancelling the malfunction restores normal operation.
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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)
BRAKES FAN INOP
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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.
Wheel 3 temperature returns immediately to the coldest wheel value.
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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.
Wheel 1, 2, 4 temperatures return immediately to the coldest wheel value.
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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).
Cancelling the malfunction restores normal operation.
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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).
Cancelling the malfunction restores normal operation.
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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).
Cancelling the malfunction restores normal operation.
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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).
Cancelling the malfunction restores normal operation.
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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).
Cancelling the malfunction restores normal operation.
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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).
Cancelling the malfunction restores normal operation.
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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).
Cancelling the malfunction restores normal operation.
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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 BRKindications 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)
Cancelling the malfunction restores normal operation.
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CHAPTER 27: TIRES/BRAKES
MALFUNCTION : AUTO BRAKE FAIL
MALFUNCTION DESCRIPTION :
CAUSE : Failure of Normal selector valve which remains inclosed 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, ifL/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).
Cancelling the malfunction restores normal operation.
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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.
Cancelling the malfunction restores normal operation.
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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.
Cancelling the malfunction restores normal operation. Wheel 8 temperature return immediately to the coldest wheelvalue.
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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.
Cancelling the malfunction restores normal operation.
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CHAPTER 28 - YAW CONTROL
CONTENTS:
RUDDER PEDALS BLOCKED
RUDDER GREEN SERVO JAM
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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).
2) Cancelling the malfunction restores normal operation.
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CHAPTER 28: YAW CONTROL
MALFUNCTION : RUDDER GREEN SERVO JAM
MALFUNCTION DESCRIPTION :
CAUSE : Jamming of a slide in the rudder servo fed by thegreen hydraulic circuit
CONSEQUENCE :
1) An additional force is felt on the rudder pedals
2) Cancelling the malfunction restores normal operation.
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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
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
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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
AUTOMATIC REVERSION TO N1 UNRATED MODE # 2
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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 energizingboth 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
Cancelling malfunction restores normal operation.
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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.
- Cancelling malfunction restores normal operation.
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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
- Cancelling malfunction restores normal operation.
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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).
• 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.
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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
• If activated: Master “Warn” light goes out
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In order to recover normal operation:
- Cancel malfunction
- Realease the “ENG2 FIRE” push button (FIRE PANEL)
• 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
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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
• Engine 1 is stopped
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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
• On fire panel ENG 1 AGENT 1 and 2 “DISH” light goes out
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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.
• Engine 2 is stopped.
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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
• On fire panel, ENG 2 AGENTS 1 and 2 “DISH” lights go out.
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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
Cancelling malfunction restores normal operation.
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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
Cancelling malfunction restores normal operation.
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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
Cancelling malfunction restores normal operation
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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
Cancelling malfunction restores normal operation.
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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.
Cancelling malfunction restore normal operation.
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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.
Cancelling malfunction restores normal operation.
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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. Ifnot flight phase 3, 4, 5:
• Appropriate message appears on the E/W CRT.
- Engine stays to reverse idle.
Cancelling malfunction restores normal operation.
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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 notflight phase 3, 4 or 5:
• Appropriate messages appear on the E/W CRT
- Engine stays at reverse idle.
Cancelling malfunction restores normal operation.
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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 valueis 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.
Cancelling malfunction restores normal operation.
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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 valueis 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.
Cancelling malfunction restores normal operation.
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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.
Cancelling malfunction restores normal operation.
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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.
Cancelling malfunction restores normal operation.
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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.
Cancelling malfuntion restores normal operation.
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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
Cancelling malfunction restores normal operation.
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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).
Cancelling malfunction restores normal operation.
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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 takenon 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.
(**) TOP + 75 sec in flight.
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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
Cancelling malfunction restores normal operation.
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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 normaloperation
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
• After 10 seconds, all fire warnings remain on
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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)
On instructor station set the AGENT FIRE RESET
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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 normaloperation
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
• After 10 seconds, all fire warnings remain on
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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)
On instructor station set the AGENT FIRE RESET
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MALFUNCTION : SERIOUS ENG DAMAGE WITH UNEXTINGFIRE # 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.
Cancelling malfunction restores normal operation.
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MALFUNCTION : SERIOUS ENG DAMAGE WITH UNEXTINGFIRE # 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.
Cancelling malfunction restores normal operation.
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MALFUNCTION : SERIOUS ENG DAMAGE WITH PARTIAL PWRLOSS # 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 normaloperation.
• 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.
Cancelling malfunction restores normal operation.
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MALFUNCTION : SERIOUS ENG DAMAGE WITH PARTIAL PWRLOSS # 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.
Cancelling malfunction restores normal operation.
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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 throttleposition is.
• No warning.
Cancelling malfunction restores normal operation.
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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)
Cancelling malfunction restores normal operation.
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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). Afew 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 displayunit.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).
Cancelling malfunction restores normal operation.
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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
Cancelling malfunction restores normal operation.
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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
Cancelling malfunction restores normal operation.
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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
Cancelling malfunction restores normal operation.
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MALFUNCTION : IDLE CONTROL FAIL # 1
MALFUNCTION DESCRIPTION :
CAUSE : EIU 1 failure
CONSEQUENCE :
- Only flight idle can be obtained on engine 1
- No warning
Cancelling malfunction restores normal operation
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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
Cancelling malfunction restores normal operation.
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MALFUNCTION : MAN START FAULT # 1
MALFUNCTION DESCRIPTION :
CAUSE : Disagree between Master Switch position andHPSOV 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.
Cancelling malfunction restores normal operation.
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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
Cancelling malfunction restores normal operation.
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MALFUNCTION : AUTOMATIC REVERSION TO N1 RATEDMODE # 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)
- Cancelling the malfunction restores normal operation providing ENG 1 N1 MODE P/B has been depressed on theoverhead panel.
- Appropriate messages will be available on MCDU (CMC function when CMC maintenance option selected).
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MALFUNCTION : AUTOMATIC REVERSION TO N1 UNRATEDMODE # 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)
- Cancelling the malfunction restores normal operation providing ENG 2 N1 MODE P/B has been depressed on theoverhead panel.
- Appropriate messages will be available on MCDU (CMC function when CMC maintenance option selected).
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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))
VIBRATIONS N2 PEAK (# 2 (%/U))
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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 psiCHANGE 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
Cancelling malfunction and/or engine oil pressure greater than 85 psi restore normal operation
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MALFUNCTION : OIL PRESS INC/DEC # 2 (psi)
PARAMETER : PARAMETER: ENGINE 2 OIL PRESSURE
MIN VALUE : MIN VALUE: 0 psi MAW VALUE: 400 psiCHANGE 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
Cancelling malfunction and/or engine oil pressure greater than 85 psi restore normal operation
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MALFUNCTION : OIL QUANTITY INC/DEC # 1 (qt)
PARAMETER : PARAMETER: engine 1 OIL QUANTITY
MIN VALUE : MIN VALUE: 0 qt MAX VALUE: 23.5 qtCHANGE 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.
N.B. Oil quantity maximum values is limited to initial quantity.
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MALFUNCTION : OIL QUANTITY INC/DEC # 2 (qt)
PARAMETER : PARAMETER: ENGINE 2 OIL QUANTITY
MIN VALUE : MIN VALUE: 0 qt MAX VALUE: 23.5 qtCHANGE 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
N.B. Oil quantity maximum value is limited to initial quantity.
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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.
N.B. EGT minimum value is limited to static air temperature.
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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
N.B. EGT minimum value is limited to static air temperature.
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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 theindicator.
Cancelling malfunction restores normal operation.
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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%, 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 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 theindicator
Cancelling malfunction restores normal operation
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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.
Cancelling malfunction restores normal operation.
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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
Cancelling malfunction restores normal operation
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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.
Cancelling the malfunction restores normal operation.
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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.
Cancelling malfunction restores normal operation.
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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 snapshotdata corresponding to malfunction are displayed on the MCDU. (when BITE TSD maintenance option selected)
Cancelling malfunction restores normal operation
N.B. Oil temperature minimum value is limited to static air temperature
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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
Cancelling malfunction restores normal operation.
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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
Complementary data: NACELLE TEMP minimum value is limited to SAT value.
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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
N.B. This malfunction have no effect when the N1 backup mode is selected.
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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
N.B. This malfunction have no effect when the N1 backup mode is selected.
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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
N.B. This malfunction have no effect when N1 backup mode is selected.
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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
N.B. This malfunction have no effect when the N1 backup mode is selected.
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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.
N.B. N1 vibrations advisory level depends on N1 actual value and EVMU initial values.
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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.
N.B. N2 vibrations advisory level depends on N2 actual value and EVMU initial values.
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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 abnormalengine 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 thevibration 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
N.B.: All advisories are always functionnal but there is no real correlation with bite unbalance functions (ifavailable on simulators).
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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 abnormalengine 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 thevibration 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
N.B.: All advisories are always functionnal but there is no real correlation with bite unbalance functions (ifavailable on simulators).
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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 abnormalengine 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 thevibration 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
N.B.: All advisories are always functionnal but there is no real correlation with bite unbalance functions (ifavailable on simulators).
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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 abnormalengine 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 thevibration 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
N.B.: All advisories are always functionnal but there is no real correlation with bite unbalance functions (ifavailable on simulators).
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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)
THR TARGET NEEDLE FAIL
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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.
Cancelling malfunction restores normal operation
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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.
Cancelling malfunction restores normal operation
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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
Cancelling malfunction restores normal operation
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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
Cancelling malfunction restores normal operation
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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
Cancelling malfunction restores normal operation
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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
Cancelling malfunction restores normal operation.
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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 phasewhatever the throttle 1 position is.
Cancelling malfunction restores normal operation
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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 wholereverse phase whatever the throttle 2 position is.
Cancelling malfunction restores normal operation
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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
Cancelling malfunction restores normal operation
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