indicating recording systems

SINGLE AISLE
TECHNICAL TRAINING MANUAL
MAINTENANCE COURSE - M35 LINE MECHANICS
(CFM56-5B/ME)
INDICATING/RECORDING SYSTEMS

This document must be used for training purposes only

Under no circumstances should this document be used as a reference

It will not be updated.

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

SINGLE AISLE TECHNICAL TRAINING MANUAL

INDICATING/RECORDING SYSTEMS
ELECTRONIC INSTRUMENT SYSTEM (EIS) (Classic) UP & DOWN DATA LOADING SYSTEM
EIS Architecture (1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 Up & Down Data Loading System Presentation (1) . . . . . . . . . . . . 180
Engine/Warning Display Presentation (1) . . . . . . . . . . . . . . . . . . . . . . 4 Up & Down Data Loading System Utilization (2) . . . . . . . . . . . . . . 184
ECAM Advisory & Failure Related Modes (3) . . . . . . . . . . . . . . . . . 12
ECAM Warnings Presentation (1) . . . . . . . . . . . . . . . . . . . . . . . . . . . 20
DIGITAL FLIGHT DATA RECORDING SYSTEM (DFDRS)
EIS Abnormal Operation (3) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 DFDRS Description/Operation (3) . . . . . . . . . . . . . . . . . . . . . . . . . . 188
EIS Warnings (3) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50 DFDRS Warnings (3) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 192
ELECTRONIC INSTRUMENT SYSTEM (EIS) (Enhanced) AIRCRAFT INTEGRATED DATA SYSTEM (AIDS-SFIM)
EIS Architecture (1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52 Print Report STD Header Description (3) . . . . . . . . . . . . . . . . . . . . 194
Engine/Warning Display Presentation (1) . . . . . . . . . . . . . . . . . . . . . 54 Individual Print Report Description (3) . . . . . . . . . . . . . . . . . . . . . . 200
ECAM Advisory & Failure Related Modes (3) . . . . . . . . . . . . . . . . . 62
ECAM Warnings Presentation (1) . . . . . . . . . . . . . . . . . . . . . . . . . . . 70 A/C INTEGRATED DATA SYS (AIDS-TELEDYNE)
EIS Abnormal Operation (3) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 78 (option)
EIS Warnings (3) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 110 Print Report STD Header Description (3) . . . . . . . . . . . . . . . . . . . . 228
CLOCK Individual Print Report Description (3) . . . . . . . . . . . . . . . . . . . . . . 234

Electrical Clock D/O (2) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 112 MAINTENANCE PRACTICE
CENTRALIZED FAULT DISPLAY SYSTEM (CFDS) Computer Removal and Installation (3) . . . . . . . . . . . . . . . . . . . . . . 264
Pushbutton Removal and Installation (3) . . . . . . . . . . . . . . . . . . . . . 266
CFDS Fault Processing (3) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 118
CFDS Aircraft System Types (1) . . . . . . . . . . . . . . . . . . . . . . . . . . . 124
CFDS Failure Classification (1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . 126
CFDS Reports (1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 134
CFDS Phases (2) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 160
Trouble Shooting Procedure with CFDS (3) . . . . . . . . . . . . . . . . . . 162
U3T06191 - U0M35M0

PRINTER
Printer Presentation (1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 172
Printer Paper Loading (2) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 174

MAINTENANCE COURSE - M35 LINE MECHANICS TABLE OF CONTENTS May 11, 2006
(CFM56-5B/ME) Page 1
31 - INDICATING/RECORDING SYSTEMS


EIS ARCHITECTURE (1)
and which are not related to warning, are directly sent to the DMCs. The
EFIS-ECAM inputs received by the SDACs are used to elaborate amber warnings.
These signals will then be sent to the FWC to generate warnings.
The Electronic Instrument System (EIS) is shown on 6 identical Cathode
Ray Tubes (CRTs). The Electronic Flight Instrument System (EFIS) are
displayed on identical Display Units (DUs) and controlled through the
EFIS control panels and the lighting/loudspeaker control panels. The
Electronic Centralized Aircraft Monitoring (ECAM) pages are displayed
on identical DUs and controlled through the ECAM Control Panel (ECP).

DMC
The Display Management Computers (DMCs) process data in order to
generate codes and graphic instructions related to the image to display.
Note the particular role of DMC 3 is to be switched instead of DMC 1
or DMC 2. Each DMC can process three displays: Primary Flight Display
(PFD), Navigation Display (ND) and upper or lower ECAM display.

FWC
The Flight Warning Computers (FWCs) monitor the aircraft systems.
These computers are the heart of the ECAM system. Each FWC generates
all warning messages to display and supplies the attention getters. It also
computes the flight phases and supplies aural warnings.
U3T06191 - U0M35M0 - UM31P2000000002

SDAC
The System Data Acquisition Concentrators (SDACs) receive various
signals from the aircraft systems and send them to the FWCs and DMCs.
The SDACs acquire most of the signals used to display system pages and
used by the FWCs to generate amber warnings.

INPUTS
The inputs received by the FWC are used to elaborate red warnings.
Various items of information for systems like engines, fuel, navigation

MAINTENANCE COURSE - M35 LINE MECHANICS EIS ARCHITECTURE (1) May 10, 2006

U3T06191 - U0M35M0 - UM31P2000000002

EFIS-ECAM ... INPUTS



ENGINE/WARNING DISPLAY PRESENTATION (1)
GENERAL OVERVIEW
The Engine/Warning Display (EWD) is normally on the upper Electronic
Centralized Aircraft Monitoring (ECAM) Display Unit (DU). It is divided
into two areas: the upper area and the lower area.
The upper area displays:
- engine primary parameters,
- Fuel On Board (FOB),
- slats and flaps position.
The lower area is used for:
- warning and caution messages,
- memo messages.
U3T06191 - U0M35M0 - UM31P4000000003

MAINTENANCE COURSE - M35 LINE MECHANICS ENGINE/WARNING DISPLAY PRESENTATION (1) May 10, 2006

U3T06191 - U0M35M0 - UM31P4000000003

GENERAL OVERVIEW



ENGINE/WARNING DISPLAY AREAS
UPPER AREA
The symbols of the upper area are permanently displayed. The
parameters are provided in the form of analog and/or digital indications
(refer to related chapter for detailed description).
LEFT MEMO AREA
Takeoff (TO) or landing memo, normal memo, independent failure
messages, or primary failure messages and actions to do are displayed
in the left memo area. As soon as a failure is detected, the memo
messages are replaced by warning/caution messages.
RIGHT MEMO AREA
Normal memo and secondary failure messages are displayed in the
right memo area. For example when an ENGine ANTI ICE P/B is set
to ON, ENG A.ICE appears on the right memo area. During TO and
landing, most of the warnings are inhibited to avoid distraction of the
crew. For example, at TO, when the second engine is set to TO power
and until the aircraft has reached 1.500 ft, TO INHIB is displayed.
U3T06191 - U0M35M0 - UM31P4000000003


U3T06191 - U0M35M0 - UM31P4000000003

ENGINE/WARNING DISPLAY AREAS - UPPER AREA ... RIGHT MEMO AREA



ADVISORY AND STATUS INDICATION
Advisory and status indications are "attention getters" on the display.
ADVISORY INDICATION
ADV: Advisory white message appears only in single display
configuration. It flashes on the lower memo area to signal to the pilot
that a parameter drifts from its normal value. As the corresponding
system page cannot be displayed on the lower ECAM DU, the pilot
has to fetch the information on the ECAM Control Panel (ECP): the
associated key flashes to indicate which system is concerned.

NOTE: In normal display configuration (dual display), the relevant
system page is automatically displayed on System Display
(SD), so the ADV indication doesn't appears on the EWD.
U3T06191 - U0M35M0 - UM31P4000000003


U3T06191 - U0M35M0 - UM31P4000000003

ADVISORY AND STATUS INDICATION - ADVISORY INDICATION



ADVISORY AND STATUS INDICATION (continued)
STATUS AND ARROW INDICATION
STS: Status indicates that a status message is present on the ECAM
SD page. Overflow arrow: only concerns the warning messages and
indicates that the messages exceed the capacity of the display on the
left memo area. In this case, the heading titles of the warning messages
are displayed on the right memo area.
U3T06191 - U0M35M0 - UM31P4000000003


U3T06191 - U0M35M0 - UM31P4000000003

ADVISORY AND STATUS INDICATION - STATUS AND ARROW INDICATION



ECAM ADVISORY & FAILURE RELATED MODES (3)
The level 2 system failure has no direct consequence on flight safety.
ALERT CLASSIFICATION
LEVEL 1
GENERAL Level 1 agrees with a configuration requiring crew monitoring, mainly
The alerts are classified in three levels. They depend on the importance failures leading to a loss of redundancy or degradation of a system.
and urgency of the corrective actions required. The attention getters (lights and sounds) are not activated by a level
- level 3: warnings (highest priority), 1 alert.
- level 2: cautions,
STATUS
- level 1: cautions,
- status messages. Some defects which do not trigger warnings or cautions, but which
At each level, the alert messages are also classified by priority order. require further maintenance actions, will be indicated to the crew by
means of a status indication, pulsing after engine shutdown. It is
LEVEL 3 necessary to call the status page manually to see the title of the affected
Level 3 agrees with an emergency configuration. Corrective or system.
palliative action must be taken by the crew immediately.
These warnings are associated with:
- Continuous Repetitive Chime (CRC) or specific sound,
- warning messages on Cathode Ray Tube (CRT),
- MASTER WARNing light flashing red.
Typical level 3 warnings are:
- aircraft in dangerous configuration or limit flight conditions (Stall,
overspeed),
- system failure altering flight safety (Engine fire, excess cabin
U3T06191 - U0M35M0 - UM31D3000000001

altitude),
- serious system failure (Dual hydraulic failure).
LEVEL 2
Level 2 agrees with an abnormal configuration. Immediate crew
awareness is required, but not immediate corrective action. The crew
must decide when to take the corrective action.
- Single Chime (SC),
- MASTER CAUTion light amber,
- warning messages on CRT.

MAINTENANCE COURSE - M35 LINE MECHANICS ECAM ADVISORY & FAILURE RELATED MODES (3) May 10, 2006

U3T06191 - U0M35M0 - UM31D3000000001

ALERT CLASSIFICATION - GENERAL ... STATUS



TYPE OF FAILURE NOTE: This part can be used if necessary to display heading titles
of warnings if the left part of the EWD is full.
GENERAL
The failures may be of three different types, independently of their
classification.
There are 3 separate types of warnings or cautions:
- those associated with an independent failure,
- those associated with a primary failure,
- those associated with a secondary failure.
INDEPENDANT FAILURE
An independent failure is a failure, which affects an isolated item of
equipment or system without affecting another one.
Example: Flight Warning Computer (FWC) 1 failure.

NOTE: An independent failure is displayed with the title underlined.
PRIMARY FAILURE
A primary failure is a failure of an item of equipment or system
causing the loss of other equipment.
Example: Green hydraulic system failure may lead to the loss of a
pair of spoilers.
U3T06191 - U0M35M0 - UM31D3000000001

NOTE: A primary failure is displayed with a box around the failure.
SECONDARY FAILURE
A secondary failure is a loss of an item of equipment or system
resulting from a primary failure.
Example: Loss of a pair of spoilers after a hydraulic system failure.
The titles of the system pages corresponding to the secondary failures
are indicated on the lower right part of the Engine/Warning Display
(EWD) by an asterisk.


U3T06191 - U0M35M0 - UM31D3000000001

TYPE OF FAILURE - GENERAL ... SECONDARY FAILURE



ADVISORY
ADVISORY MODE IN NORMAL DUAL DISPLAY
The value of some critical system parameters is monitored by an
advisory mode. In Electronic Centralized Aircraft Monitoring (ECAM)
normal display, when a value drifts from its normal range, the
corresponding system page is displayed automatically in order to
attract crew attention well before reaching the warning or caution
level. The affected parameter and the system page title pulse. The
corresponding key light on the ECAM Control Panel (ECP) is on.
Example: The CAB PRESS page will be displayed if the cabin altitude
increases above its normal value, but is still well below the threshold
of the warning. In this case the crew may revert to manual pressure
control and prevent warning activation.

NOTE: An advisory may or may not lead to a failure. They are
totally independent one from the other.
U3T06191 - U0M35M0 - UM31D3000000001


U3T06191 - U0M35M0 - UM31D3000000001

ADVISORY - ADVISORY MODE IN NORMAL DUAL DISPLAY



ADVISORY (continued)
ADVISORY MODE IN ECAM MONO DISPLAY
In ECAM MONO display mode (one ECAM CRT remaining), when
a value drifts from its normal range, a white ADV message flashes in
the center of the EWD to attract crew attention. As the related system
page cannot be displayed automatically on the System Display (SD),
the pilot has to fetch the information on the ECP: the associated key
light flashes to indicate which system is concerned.

NOTE: The CAB PRESS system page is given as an example.
U3T06191 - U0M35M0 - UM31D3000000001


U3T06191 - U0M35M0 - UM31D3000000001

ADVISORY - ADVISORY MODE IN ECAM MONO DISPLAY



ECAM WARNINGS PRESENTATION (1)
ECAM DISPLAY WITH AIRCRAFT SYSTEM FAILURE
In case of aircraft system failure, an aural warning, the Single Chime
(SC), a visual warning and the MASTER CAUTion, attract your attention.
The Engine/Warning Display (EWD) indicates the title of the failure and
the actions to take. On the status and System Display (SD), the hydraulic
page is called automatically. The CLeaR P/Bs come on and as long as
the failure is not cleared, they stay on. On the hydraulic panel the FAULT
lights come on, indicating the P/Bs to release out.

NOTE: In this module, parameters are given for a CFM engine. For an
IAE engine, the parameters will be shown as follows: Engine
Pressure Ratio (EPR), EGT, N1 and N2). The graphics show
an example of sequence of Electronic Centralized Aircraft
Monitoring (ECAM) displays in case of green hydraulic system
fault. This may be different to your aircraft configuration.
U3T06191 - U0M35M0 - UM31P6000000001

MAINTENANCE COURSE - M35 LINE MECHANICS ECAM WARNINGS PRESENTATION (1) May 10, 2006

U3T06191 - U0M35M0 - UM31P6000000001




CREW CORRECTIVE ACTIONS
CORRECTIVE ACTIONS
When you press the MASTER CAUT, it goes off. Then, actions
indicated on the EWD have to be done. First, switch OFF the Power
Transfer Unit (PTU) P/B on the hydraulic panel, and then switch OFF
the GREEN ENGine 1 PUMP P/B.
RESULTS
The corrective actions have been taken. All the FAULT lights are off.
On the EWD, the messages associated to the corrective action have
disappeared. On the left hand side of the EWD, the result of the failure
appears indicating that it is a primary failure. On the right hand side,
the secondary failures are displayed.
U3T06191 - U0M35M0 - UM31P6000000001


U3T06191 - U0M35M0 - UM31P6000000001

CREW CORRECTIVE ACTIONS - CORRECTIVE ACTIONS & RESULTS



CLEARING OF THE WARNINGS
When you press CLR, on the left hand part of the EWD the title of the
failure disappears and MEMO messages come back. The system page
corresponding to the first secondary failure is displayed. When you press
CLR again, the title of the first secondary failure disappears. The system
page associated with the next secondary failure is displayed. When you
press CLR a third time, the title of the secondary failure disappears. The
MEMO message comes back on the right hand part of the EWD. The
STATUS page is displayed.
U3T06191 - U0M35M0 - UM31P6000000001


U3T06191 - U0M35M0 - UM31P6000000001

CLEARING OF THE WARNINGS



STATUS REMINDER AND RECALL FUNCTION
When you press CLR a last time, the STATUS reminder STS on the
EWD indicates that the STATUS page is not empty and the CLR P/Bs
go off. On the status page, the cruise page (related to the present flight
phase) comes back. The warning has been cleared. The ReCalL P/B lets
the crew reactivate the Cathode Ray Tube (CRT) presentation of an alert
inhibited either through the flight phase or by the CLR function.
U3T06191 - U0M35M0 - UM31P6000000001


U3T06191 - U0M35M0 - UM31P6000000001

STATUS REMINDER AND RECALL FUNCTION



EIS ABNORMAL OPERATION (3)
FAILURE OF ONE EFIS DISPLAY UNIT
In case of Electronic Flight Instrument System (EFIS) Display Unit (DU)
failure the Primary Flight Display (PFD) image has priority over the
Navigation Display (ND) image. The PFD is displayed on the remaining
DU.

Pressure Ratio (EPR), EGT, N1 and N2.
U3T06191 - U0M35M0 - UM31D4000000003

MAINTENANCE COURSE - M35 LINE MECHANICS EIS ABNORMAL OPERATION (3) May 10, 2006

U3T06191 - U0M35M0 - UM31D4000000003

FAILURE OF ONE EFIS DISPLAY UNIT



FAILURE OF THE ENGINE/WARNING DISPLAY UNIT
The Engine/Warning Display (EWD) has priority over the System Display
(SD). The EWD is automatically transferred to the lower Electronic
Centralized Aircraft Monitoring (ECAM) DU, replacing the system/status
display. All ECAM information and system/status pages are available
on this single display. This configuration is called "ECAM mono display".
U3T06191 - U0M35M0 - UM31D4000000003


U3T06191 - U0M35M0 - UM31D4000000003

FAILURE OF THE ENGINE/WARNING DISPLAY UNIT



FAILURE OF BOTH ECAM DISPLAY UNITS
ECAM/ND transfer (XFR) is done to get the engine/warning image back.
All the ECAM images are lost momentarily. However the crew can
recover the engine/warning image by using the ECAM/ND XFR rotary
selector. The engine/warning image will then be displayed instead of the
ND. This configuration is called "ECAM mono display" because all
ECAM information is available on a single display.
U3T06191 - U0M35M0 - UM31D4000000003


U3T06191 - U0M35M0 - UM31D4000000003

FAILURE OF BOTH ECAM DISPLAY UNITS



FAILURE OF ONE DMC
The crew will select Display Management Computer (DMC) 3 to replace
the failed DMC. The following message with the action to do is indicated
on the EWD:
EIS DMC 1 FAULT
- EIS DMC SWITCH.... CAPT
Or
EIS DMC 2 FAULT
- EIS DMC SWITCH.... F/O
Depending on the faulty (DMC).
U3T06191 - U0M35M0 - UM31D4000000003


U3T06191 - U0M35M0 - UM31D4000000003

FAILURE OF ONE DMC



FAILURE OF DMC 1+3
The ECAM system page can temporarily be displayed instead of the
engine/warning image by manual page call.
- loss of PFD and ND images on CAPT instrument panel.
- loss of ECAM system page. ECAM in mono display.
MASTER CAUTion light comes on. The following message is displayed:
EIS DMC 1+ 3 FAULT
U3T06191 - U0M35M0 - UM31D4000000003


U3T06191 - U0M35M0 - UM31D4000000003

FAILURE OF DMC 1+3



ECAM CONTROL PANEL FAILURE
The EMERgency CANCel, CLeaR, ReCalL, ALL and StaTuS functions
remain available. They let the use of the Electronic Instrument System
(EIS).
U3T06191 - U0M35M0 - UM31D4000000003


U3T06191 - U0M35M0 - UM31D4000000003

ECAM CONTROL PANEL FAILURE



FAILURE OF ONE SDAC
There is no operational consequence due to the redundancy of the EIS
system.
The following message is displayed:
FWS SDAC 1 FAULT
Or
FWS SDAC 2 FAULT
Depending on the faulty System Data Acquisition Concentrator (SDAC).
U3T06191 - U0M35M0 - UM31D4000000003


U3T06191 - U0M35M0 - UM31D4000000003

FAILURE OF ONE SDAC



FAILURE OF SDAC 1+2
Loss of most of amber warnings. The following message is displayed:
FWS SDAC 1+ 2 FAULT
- MONITOR OVERHEAD PANEL
- ECAM ENG FUEL F/CTL WHEEL SYS PAGES AVAIL
U3T06191 - U0M35M0 - UM31D4000000003


U3T06191 - U0M35M0 - UM31D4000000003

FAILURE OF SDAC 1+2



FAILURE OF ONE FWC
There is no operational consequence due to the redundancy of the EIS
system.
The following message is displayed:
FWS FWC 1 FAULT
Or
FWS FWC 2 FAULT
Depending on the faulty Flight Warning Computer (FWC).

NOTE: Only the half part of each MASTER WARN and MASTER
CAUT light remains operative.
U3T06191 - U0M35M0 - UM31D4000000003


U3T06191 - U0M35M0 - UM31D4000000003

FAILURE OF ONE FWC



FAILURE OF FWC 1+2
Loss of aural warnings. Loss of text messages on EWD display. Loss of
attention getters. The DMC receives no data from the FWCs and displays
the following message:
FWS FWC 1+ 2 FAULT
- MONITOR SYS
- MONITOR OVERHEAD PANEL.
U3T06191 - U0M35M0 - UM31D4000000003


U3T06191 - U0M35M0 - UM31D4000000003

FAILURE OF FWC 1+2



EXTERNAL SOURCE INFORMATION FAILURES
In the case of external source information failures, the lost information
appears in red on the PFD or ND. It is possible to recover certain
information by following the EWD instructions: in this example "ATT
HDG SWTG F/O" on the switching panel. This enables manual source
reconfiguration for attitude and heading data. On the EWD, the failed
component is also displayed.
U3T06191 - U0M35M0 - UM31D4000000003


U3T06191 - U0M35M0 - UM31D4000000003

EXTERNAL SOURCE INFORMATION FAILURES



EIS WARNINGS (3)
CAPT EFIS. The lower ECAM DU displays the Engine/Warning Display
FWC 1+2 FAULT (EWD) images (possibility to display a system or status image
temporarily). The ECAM is in mono display.
In this case, only an Electronic Centralized Aircraft Monitoring (ECAM)
message is given. There is no MASTER light and aural warning as they DMC 1(2)+3 FAULT
are generated by the Flight Warning Computers (FWCs). The crew has
to closely monitor the aircraft systems through the overhead panel or In case of DMC1 and DMC3 fault, the aural warning sounds and the
ECAM system pages. MASTER CAUT comes on. The captain PFD and ND data, and the
ECAM System Display (SD) data lost. The ECAM is in mono display.
FWC 1(2) FAULT
NOTE: If DMC 2+3 fail, the F/O EFIS and ECAM SD data is lost.
As two identical FWCs are given, ECAM operation is not affected.
DMC 1(2) FAULT
SDAC 1+2 FAULT
If the DMC1 (or DMC2) fails, the aural warning sounds and the MASTER
In case of System Data Acquisition Concentrators (SDACs) fault, the
CAUT comes on. The captain (or first officer) PFD and ND data, and
aural warning sounds and the MASTER CAUTion comes on. Most of
the ECAM SD data are lost. The captain has to transfer to DMC 3 to
the amber warnings are lost. The crew has to carefully monitor the
recover the three DUs.
overhead panel. ENG, FUEL, F/CTL and WHEEL ECAM system pages
remain available. DMC 3 FAULT
SDAC 1(2) FAULT When the DMC3 fails, the aural warning sounds and the MASTER CAUT
comes on. There is no change on the six DUs but a single warning
As two identical SDACs are given, ECAM operation is not affected.
message is displayed on the EWD to indicate this DMC 3 fault.
U3T06191 - U0M35M0 - UM31W1000000001

DMC 1+2 FAULT OPERATING LIMITATIONS
In case of Display Management Computer (DMC) 1 and DMC2 fault,
One among SDAC, FWC, DMC and DU may be inoperative for dispatch.
the aural warning sounds and the MASTER CAUT comes on. All
Electronic Flight Instrument System (EFIS) and ECAM images are lost.
One pilot must place the Electronic Instrument System (EIS) DMC
selector switch to the position CAPT 3, or F/O 3 to have his Primary
Flight Display (PFD), Navigation Display (ND) and either upper or lower
ECAM images driven by the DMC 3. In the position CAPT 3, a diagonal
line is displayed on lower ECAM Display Unit (DU) and F/O EFIS. In
the position F/O 3, a diagonal line is displayed on upper ECAM DU and

MAINTENANCE COURSE - M35 LINE MECHANICS EIS WARNINGS (3) May 10, 2006

U3T06191 - U0M35M0 - UM31W1000000001

FWC 1+2 FAULT ... OPERATING LIMITATIONS

MAINTENANCE COURSE - M35 LINE MECHANICS EIS WARNINGS (3) May 10, 2006


EIS ARCHITECTURE (1)
EFIS-ECAM INPUTS
The Electronic Instrument System (EIS) is shown on 6 identical Liquid The inputs received by the FWC are used to elaborate red warnings.
Crystal Display (LCD) units and controlled through the EIS control Various items of information for systems like engines, fuel, navigation
panels. The Electronic Centralized Aircraft Monitoring (ECAM) displays and which do not agree with a warning, are directly sent to the DMCs.
are identical and controlled through the ECAM Control Panel (ECP). The inputs received by the SDACs are used by the DMCs to display
The Electronic Flight Instrument System (EFIS) displays are controlled system pages and by the FWCs to generate amber warnings.
by the EFIS control panels and the lighting/loudspeaker control panels.

DMC
The Display Management Computers (DMCs) are data concentrator and
receive data from aircraft sensors and systems. They send them to the
Display Units (DUs). The DUs compute and display the images on each
unit. In normal operation DMC1 drives the CAPT Primary Flight Display
(PFD), the CAPT Navigation Display (ND), Engine/Warning Display
(EWD) and System Display (SD). In normal operation DMC 2 drives
the F/O PFD and ND DUs. If DMC 1 fails, it is automatically replaced
by DMC 2 for ECAM only. DMC 2 cannot drive the CAPT PFD and
ND; a manual switching to DMC 3 is required. DMC 3 can drive any of
the six DUs. DMC 3 is a hot spare awaiting the failure of DMC 1 or 2
and can be switched to drive the DUs linked to the failed DMC.
U3T06191 - U0M35M0 - UM31P2000000001

FWC
The Flight Warning Computers (FWCs) monitor the aircraft systems.
Each FWC generates all warning and caution messages, supplies the
attention getters, computes the flight phase and provides aural warnings.

SDAC
The System Data Acquisition Concentrators (SDACs) receive various
signals from the aircraft systems and send them to the FWCs and to the
DMCs.


U3T06191 - U0M35M0 - UM31P2000000001

EFIS-ECAM ... INPUTS



GENERAL
The Engine/Warning Display (EWD) is normally on the upper Display
Unit (DU), it is divided into upper and lower areas. The EWD is dedicated
to the presentation of information.
EWD INFORMATION
On the upper area are permanently displayed:
- Primary engine parameters,
- Slat/flap position indication,
- Fuel On Board (FOB).
On the lower area are displayed:
- Memos, failure messages and actions to be performed. During
TakeOff (TO) and landing, most of the warnings are inhibited.
U3T06191 - U0M35M0 - UM31P4000000001


U3T06191 - U0M35M0 - UM31P4000000001

GENERAL - EWD INFORMATION



ADVISORY AND STATUS INDICATION
There are conditions when additional symbols are displayed, on the EWD
lower area. The symbols are ADV (Advisory), STS (Status) and an arrow
(overflow).
ADVISORY INDICATION
Advisory (ADV) appears in single display configuration, it flashes
on the lower memo area if a parameter drifts from its normal value.
Also the relevant ECAM Control Panel (ECP) key flashes.

NOTE: Note: in normal display configuration (dual display) the
related SD page is automatically shown, so the ADV symbol
is not needed.
U3T06191 - U0M35M0 - UM31P4000000001


U3T06191 - U0M35M0 - UM31P4000000001

ADVISORY AND STATUS INDICATION - ADVISORY INDICATION



STATUS INDICATION
Status (STS) indicates that a status message is present on the SD STS
page.
U3T06191 - U0M35M0 - UM31P4000000001


U3T06191 - U0M35M0 - UM31P4000000001

ADVISORY AND STATUS INDICATION - STATUS INDICATION



ARROW INDICATION
The overflow arrow in green color indicates that warning messages
exceed the capacity of the display on the left memo area.
U3T06191 - U0M35M0 - UM31P4000000001


U3T06191 - U0M35M0 - UM31P4000000001

ADVISORY AND STATUS INDICATION - ARROW INDICATION



The level 2 system failure has no direct consequence on flight safety.
ALERT CLASSIFICATION
LEVEL 1
GENERAL Level 1 agrees with a configuration requiring crew monitoring, mainly
The alerts are classified in three levels. They depend on the importance failures leading to a loss of redundancy or degradation of a system.
and urgency of the corrective actions required. The attention getters (lights and sounds) are not activated by a level
- level 3: warnings (highest priority) 1 alert.
- level 2: cautions
STATUS
- level 1: cautions
- status messages Some defects which do not trigger warnings or cautions, but which
At each level, the alert messages are also classified by priority order. require further maintenance actions, will be indicated to the crew by
means of a status indication, pulsing after engine shutdown. It is
LEVEL 3 necessary to call the status page manually to see the title of the affected
Level 3 corresponds to an emergency configuration. Corrective or system.
palliative action must be taken by the crew immediately.
- Continuous Repetitive Chime (CRC) or specific sound,
- warning messages on Liquid Crystal Display (LCD),
- MASTER WARNing light flashing red.
Typical level 3 warnings are:
- aircraft in dangerous configuration or limit flight conditions (Stall,
overspeed),
- system failure altering flight safety (Engine fire, excess cabin
U3T06191 - U0M35M0 - UM31D3000000002

altitude),
- serious system failure (Dual hydraulic failure).
LEVEL 2
Level 2 agrees with an abnormal configuration. Immediate crew
awareness is required, but not immediate corrective action. The crew
must decide when to take the corrective action.
- Single Chime (SC),
- MASTER CAUTion light amber,
- warning messages on LCD.


U3T06191 - U0M35M0 - UM31D3000000002

ALERT CLASSIFICATION - GENERAL ... STATUS



TYPE OF FAILURE NOTE: This part can be used if necessary to display heading titles
of warnings if the left part of the EWD is full.
GENERAL
The failures may be of three different types, independently of their
classification.
There are 3 separate types of warnings or cautions:
- those associated with an independent failure,
- those associated with a primary failure,
- those associated with a secondary failure.
INDEPENDANT FAILURE
An independent failure is a failure, which affects an isolated item of
equipment or system without affecting another one.
Example: Flight Warning Computer (FWC) 1 failure.

NOTE: An independent failure is displayed with the title underlined.
PRIMARY FAILURE
A primary failure is a failure of an item of equipment or system
causing the loss of other equipment.
Example: Green hydraulic system failure may lead to the loss of a
pair of spoilers.
U3T06191 - U0M35M0 - UM31D3000000002

NOTE: A primary failure is displayed with a box around the failure.
SECONDARY FAILURE
A secondary failure is a loss of an item of equipment or system
resulting from a primary failure.
Example: Loss of a pair of spoilers after a hydraulic system failure.
The titles of the system pages corresponding to the secondary failures
are indicated on the lower right part of the Engine/Warning Display
(EWD) by an asterisk.


U3T06191 - U0M35M0 - UM31D3000000002

TYPE OF FAILURE - GENERAL ... SECONDARY FAILURE



ADVISORY
ADVISORY MODE IN NORMAL DUAL DISPLAY
The value of some critical system parameters is monitored by an
advisory mode. In Electronic Centralized Aircraft Monitoring (ECAM)
normal display, when a value drifts from its normal range, the
corresponding system page is displayed automatically in order to
attract crew attention well before reaching the warning or caution
level. The affected parameter and the system page title pulse. The
corresponding key light on the ECAM Control Panel (ECP) is on.
Example: The CAB PRESS page will be displayed if the cabin altitude
increases above its normal value, but is still well below the threshold
of the warning. In this case the crew may revert to manual pressure
control and prevent warning activation.

NOTE: An advisory may or may not lead to a failure. They are
totally independent one from the other.
U3T06191 - U0M35M0 - UM31D3000000002


U3T06191 - U0M35M0 - UM31D3000000002

ADVISORY - ADVISORY MODE IN NORMAL DUAL DISPLAY



ADVISORY (continued)
ADVISORY MODE IN ECAM MONO DISPLAY
In ECAM MONO display mode (one ECAM LCD remaining), when
a value drifts from its normal range, a white ADV message flashes in
the center of the EWD to attract crew attention. As the corresponding
system page cannot be displayed automatically on the System Display
(SD), the pilot has to fetch the information on the ECP: the associated
key light flashes to indicate which system is concerned.

NOTE: The CAB PRESS system page is given as an example.
U3T06191 - U0M35M0 - UM31D3000000002


U3T06191 - U0M35M0 - UM31D3000000002

ADVISORY - ADVISORY MODE IN ECAM MONO DISPLAY



In case of aircraft system failure, an aural warning, the Single Chime
(SC), a visual warning and the MASTER CAUTion, attract your attention.
The Engine/Warning Display (EWD) indicates the title of the failure and
the actions to take. On the status and System Display (SD), the hydraulic
page is called automatically. The CLeaR P/Bs come on and as long as
the failure is not cleared, they stay on. On the hydraulic panel the FAULT
lights come on, indicating the P/Bs to release out.

Pressure Ratio (EPR), EGT, N1 and N2). The graphics show
an example of sequence of Electronic Centralized Aircraft
Monitoring (ECAM) displays in case of green hydraulic system
fault. This may be different to your aircraft configuration.
U3T06191 - U0M35M0 - UM31P6000000002


indicating recording systems

Recommandé

Recommandé

Contenu connexe

Tendances

Tendances (20)

En vedette

En vedette (19)

Similaire à indicating recording systems

Similaire à indicating recording systems (20)

Dernier

Dernier (20)

indicating recording systems