PRODUCT SUPPORT & SERVICES
SYSTEMS
SCAN YOUR AIRCRAFT
42 PEC 72 PEC
Glass cockpit - 600
Introduction
Introduction
This Systems guide is an essential tool for all ATR flight crews and engineers to learn or
review ATR systems operation. To make learning process easier, systems are introduced in
a user-friendly and efficient training method, including diagrams and schematics and displays
as appropriate.
This guide is a comprehensive document that efficiently complements FCOM 1st part
– Systems description. Systems are organized as per FCOM chapters, including their ATA
classification along with cockpit location. Cockpit panels familiarisation is presented with
each relevant system description in a separate annex.
This new guide release is intended for training on ATR 42-500 and 72-212A New Avionics
Suite (42-600 and 72-600). It presents a generic aircraft not customized to your own aircraft
systems. Should you find any discrepancy between Systems guide and your customized
ATR operational documentation (AFM, FCOM & QRH), the latter takes precedence.
NB: This Systems guide is also available for ATR 42-300, 72-200 not PEC, 42-500 and 72-212A.
The Training and Flight Operations support team.
S y s t e m s 4 2/72 - 6 0 0
Chapter A. Aircraft general
1. Doors location .....................................................................................................................................................................................................................................................8
2. Cargo door panel ...........................................................................................................................................................................................................................................9
3. Doors panel ...........................................................................................................................................................................................................................................................9
4. External lights ................................................................................................................................................................................................................................................10
5. EXT LT panel .....................................................................................................................................................................................................................................................11
6. Memo panel display .................................................................................................................................................................................................................................11
7. Signs panel .........................................................................................................................................................................................................................................................11
8. Internal lighting ............................................................................................................................................................................................................................................12
9. LT panel ...................................................................................................................................................................................................................................................................13
10. ANN LT panel ...............................................................................................................................................................................................................................................13
11. Side panel .........................................................................................................................................................................................................................................................13
12. FLT COMPT LT panel .........................................................................................................................................................................................................................13
Chapter B. Integrated systems
1. Integrated Modular Avionics (IMA)......................................................................................................................................................................................16
2. Multi Function Computer (MFC)..............................................................................................................................................................................................17
3. Multi Purpose Computer (MPC) ..............................................................................................................................................................................................18
4. Schematic..............................................................................................................................................................................................................................................................19
Chapter C. Flight warning system
1. Cockpit colors philosophy ............................................................................................................................................................................................................22
2. FWS description ..........................................................................................................................................................................................................................................24
3. Alert window ....................................................................................................................................................................................................................................................25
4. EMER audio cancel & TO config test .............................................................................................................................................................................28
5. Aural alarms ......................................................................................................................................................................................................................................................29
Chapter D. Air
1. Pneumatic system......................................................................................................................................................................................................................................32
1.1. Schematic .................................................................................................................................................................................................................................................32
1.2. AIR BLEED panel.............................................................................................................................................................................................................................33
2. Air conditionning ........................................................................................................................................................................................................................................39
2.1. Schematic .................................................................................................................................................................................................................................................39
2.2. COMPT TEMP panel ...................................................................................................................................................................................................................40
3. Avionics ventilation .................................................................................................................................................................................................................................44
3.1. Schematic .................................................................................................................................................................................................................................................44
3.2. AVIONICS VENT panel .............................................................................................................................................................................................................44
4. Pressurization ................................................................................................................................................................................................................................................45
4.1. Schematic .................................................................................................................................................................................................................................................45
4.2. Cabin pressure indicators ..................................................................................................................................................................................................46
4.3. AUTO PRESS panel .....................................................................................................................................................................................................................46
4.4. MAN RATE KNOB and CABIN PRESS panel..............................................................................................................................................46
Chapter E. Automatic flight control system
1. Schematic ............................................................................................................................................................................................................................................................50
2. FMA ..............................................................................................................................................................................................................................................................................51
3. FGCP (Flight Guidance and Control Panel) ............................................................................................................................................................56
4. ICP (Index Control Panel) .................................................................................................................................................................................................................56
Chapter F. Communications
1. Schematic............................................................................................................................................................................................................................................................. 58
2. PTT selector and NOSE WHEEL STEERING CONTROL SW.............................................................................................................58
3. Audio control panel ..................................................................................................................................................................................................................................59
4. VHF control ..........................................................................................................................................................................................................................................................59
5. AUDIO SEL pb..................................................................................................................................................................................................................................................60
6. Loudspeaker volume knobs .........................................................................................................................................................................................................60
2
Contents
7. TCAS control box ........................................................................................................................................................................................................................................60
8. EMER LOC XMTR panel .....................................................................................................................................................................................................................61
9. Cabin attendant handset...................................................................................................................................................................................................................61
10. Handmike and handset....................................................................................................................................................................................................................61
11. CALLS panel ...................................................................................................................................................................................................................................................61
12. Head set / boom set / hand mike panels ...................................................................................................................................................................61
13. ATC control.......................................................................................................................................................................................................................................................62
14. CVR panel...........................................................................................................................................................................................................................................................62
15. Crew oxygen mask ................................................................................................................................................................................................................................62
Chapter G. Electrical systems
1. Sources of power ........................................................................................................................................................................................................................................64
2. DC-AC schematic .......................................................................................................................................................................................................................................66
2.1. Normal supply: On ground with battery only ............................................................................................................................................66
2.2. Normal Supply: On ground with external power .........................................................................................................................................67
2.3. Hotel mode or DC GEN 1 FAULT ................................................................................................................................................................................68
2.4. Normal supply: with two generators on line..............................................................................................................................................69
2.5. Emergency supply: In dual DC GEN LOSS with the battery toggle switch on OVRD .......................70
2.6. Emergency supply: In dual DC GEN LOSS with the battery toggle switch on OVRD and
second OVRD selected ..........................................................................................................................................................................................................71
2.7. Emergency supply: In dual DC GEN LOSS with TRU ....................................................................................................................72
3. DC-AC panel ......................................................................................................................................................................................................................................................73
4. Elec SD ......................................................................................................................................................................................................................................................................74
5. ACW schematic .............................................................................................................................................................................................................................................78
6. ACW panel ............................................................................................................................................................................................................................................................80
7. SD page ....................................................................................................................................................................................................................................................................81
8. Breaker panels ................................................................................................................................................................................................................................................82
8.1. Overhead panel .................................................................................................................................................................................................................................82
8.2. Electric rack behind F/O .......................................................................................................................................................................................................83
Chapter H. Emergency equipment
1. Emergency equipment situation.............................................................................................................................................................................................86
2. Emergency lighting system ...........................................................................................................................................................................................................86
3. First aid kit ............................................................................................................................................................................................................................................................87
4. Crash axe ...............................................................................................................................................................................................................................................................87
5. Megaphone ..........................................................................................................................................................................................................................................................87
6. Flashing light .....................................................................................................................................................................................................................................................87
7. Life jacket ..............................................................................................................................................................................................................................................................87
8. Escape rope ........................................................................................................................................................................................................................................................87
9. Gloves .........................................................................................................................................................................................................................................................................88
10. Water extinguisher .................................................................................................................................................................................................................................88
11. Halon extinguisher .................................................................................................................................................................................................................................88
12. Oxygen schematic..................................................................................................................................................................................................................................88
13. Oxygen panel and display ............................................................................................................................................................................................................89
14. Cockpit crew oxygen mask .......................................................................................................................................................................................................89
15. Portable oxygen bottle......................................................................................................................................................................................................................90
16. Passenger oxygen mask ................................................................................................................................................................................................................90
17. Protective breathing equipment ..........................................................................................................................................................................................90
Chapter I. Fire protection
1. Schematic..............................................................................................................................................................................................................................................................92
2. Avionics FWD and AFT smoke detection ...................................................................................................................................................................92
3. Fire handle ............................................................................................................................................................................................................................................................93
4. EWD (Engine and Warning Display)....................................................................................................................................................................................93
5. Condition levers fuel light ................................................................................................................................................................................................................93
6. Compartment smoke panel...........................................................................................................................................................................................................94
7. SD cabin...................................................................................................................................................................................................................................................................94
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Chapter J. Flight control
1. Roll schematic.................................................................................................................................................................................................................................................96
2. Pitch schematic .............................................................................................................................................................................................................................................96
3. Yaw schematic ................................................................................................................................................................................................................................................97
4. Gust lock .................................................................................................................................................................................................................................................................97
5. Stick Shaker/Stick Pusher push button and display ..................................................................................................................................97
6. Spoilers position indicator..............................................................................................................................................................................................................98
7. Pitch trim asym light ...............................................................................................................................................................................................................................98
8. Trim position indicator .........................................................................................................................................................................................................................98
9. Trim controls ......................................................................................................................................................................................................................................................99
10. Flaps schematic .................................................................................................................................................................................................................................... 100
11. Flaps position indicator............................................................................................................................................................................................................... 100
12. Flaps control lever .............................................................................................................................................................................................................................. 101
Chapter K. Flight instruments
1. Schematic.......................................................................................................................................................................................................................................................... 104
2. PFD (Primary Fight Display) ...................................................................................................................................................................................................... 105
3. MFD (Multi Function Display) .................................................................................................................................................................................................. 106
4. EWD (Engine and Warning Display)................................................................................................................................................................................ 107
5. ND - ARC MODE with terrain or weather radar information ...................................................................................................... 108
6. Source failure alert ................................................................................................................................................................................................................................ 108
7. Switching panel ......................................................................................................................................................................................................................................... 109
8. EFCP (control panel) ........................................................................................................................................................................................................................... 109
9. MCP (Multipurpose Control Panel) ................................................................................................................................................................................. 110
10. Weather radar control ................................................................................................................................................................................................................... 111
Primus 660 ........................................................................................................................................................................................................................................................ 111
11. TAT/SAT indicator ............................................................................................................................................................................................................................... 112
12. CLOCK................................................................................................................................................................................................................................................................ 112
13. RCDR panel ................................................................................................................................................................................................................................................. 113
14. STBY instruments ............................................................................................................................................................................................................................... 113
15. Airspeed indicator .............................................................................................................................................................................................................................. 114
16. Altimeter........................................................................................................................................................................................................................................................... 115
17. Vertical speed indicator and TCAS .............................................................................................................................................................................. 116
Chapter L. Fuel system
1. Schematic.......................................................................................................................................................................................................................................................... 118
2. Electrical fuel pump OFF............................................................................................................................................................................................................... 119
3. Starting procedure................................................................................................................................................................................................................................. 120
4. Normal procedure................................................................................................................................................................................................................................... 121
5. Cross feed procedure........................................................................................................................................................................................................................ 122
6. Engine feed jet pump low pressure................................................................................................................................................................................ 124
7. Low level ............................................................................................................................................................................................................................................................. 125
8. Engine fire procedure ........................................................................................................................................................................................................................ 126
9. Fuel panel........................................................................................................................................................................................................................................................... 127
10. SD Engine ....................................................................................................................................................................................................................................................... 127
11. Fuel QTY indication ........................................................................................................................................................................................................................... 128
12. XFEED advisory on memo panel display ............................................................................................................................................................. 128
Chapter M. Hydraulic system
1. Schematic.......................................................................................................................................................................................................................................................... 130
3. SD ACW and hydraulic ..................................................................................................................................................................................................................... 131
2. HYD PWR panel ......................................................................................................................................................................................................................................... 131
4. Pressure indication ............................................................................................................................................................................................................................... 132
5. AUX pump pedestal switch ....................................................................................................................................................................................................... 132
6. Hydraulic on Ramp (only on battery) ............................................................................................................................................................................ 133
7. Hydraulic on Ramp (aux pump P/B selected on the pedestal) ................................................................................................. 133
8. Hydraulic system normal operation............................................................................................................................................................................... 134
4
Contents
9. Hydraulic system failures ............................................................................................................................................................................................................. 135
10. Hydraulic system crossfeed operation .................................................................................................................................................................. 135
11. Both main hydraulic pumps loss .................................................................................................................................................................................... 136
12. Both hydraulic systems loss ................................................................................................................................................................................................ 137
N. Ice and rain protection
1. Schematic.......................................................................................................................................................................................................................................................... 140
2. Probes and windshield HTG ..................................................................................................................................................................................................... 141
3. Rain protection ........................................................................................................................................................................................................................................... 141
4. Ice detector panel and icing AOA ..................................................................................................................................................................................... 141
5. Aircraft Performance Monitoring (APM) .................................................................................................................................................................. 142
6. De-icing schematic............................................................................................................................................................................................................................... 143
7. Airframe air bleed FAULT .............................................................................................................................................................................................................. 144
8. Anti-icing & de-icing panel ......................................................................................................................................................................................................... 145
9. De-icing/anti-icing indication (memo panel display) .............................................................................................................................. 145
O. Landing gear
1. Landing gear description ............................................................................................................................................................................................................. 148
2. Brakes schematic ................................................................................................................................................................................................................................... 148
3. LDG GEAR position indicators .............................................................................................................................................................................................. 149
4. Landing gear handles ........................................................................................................................................................................................................................ 149
5. Brakes temperatureand antiskid ....................................................................................................................................................................................... 149
6. Emergency parking brake handle..................................................................................................................................................................................... 150
7. Steering handwheel ............................................................................................................................................................................................................................. 150
P. Navigation system
1. Nav control ....................................................................................................................................................................................................................................................... 152
2. Marker sensibility setting ............................................................................................................................................................................................................. 152
3. ADF control ...................................................................................................................................................................................................................................................... 152
4. TAWS alert modes .................................................................................................................................................................................................................................. 153
5. TAWS pb............................................................................................................................................................................................................................................................... 157
6. TAWS panel...................................................................................................................................................................................................................................................... 157
7. ND OVERLAY ................................................................................................................................................................................................................................................. 158
8. FMS ............................................................................................................................................................................................................................................................................ 159
Q. Power plant
1. Engine schematic/72 .......................................................................................................................................................................................................................... 162
2. Power and propeller controls/72 ....................................................................................................................................................................................... 163
3. Engine indication ..................................................................................................................................................................................................................................... 166
4. ENG START panel/72 .......................................................................................................................................................................................................................... 168
5. ENG control panel/72......................................................................................................................................................................................................................... 168
6. PWR MGT panel/72............................................................................................................................................................................................................................... 169
7. ATPCS test panel/72 ........................................................................................................................................................................................................................... 169
8. Idle gate/72 ...................................................................................................................................................................................................................................................... 169
Annexes
Annex 1. Cockpit panels ....................................................................................................................................................................................................................... 173
Annex 2. Abbreviations ........................................................................................................................................................................................................................... 187
5
A. Aircraft general
FCOM 1.00
7
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1. Doors location
Cargo door
Pilot communication
hatch
8
Emergency exit
type III
Rear entry door /
emergency exit type I
ATA 52
Service door /
emergency exit type I
Pilot emergency hatch
Aft avionics
compartment door
Forward avionics
access hatch
A. Aircraft general
2. Cargo door panel
ATA 52
ARMED light
– Selector armed green light is ON,
when actuator selection switch
working conditions are met:
– cover panel opened
– door unlocked by operating handle:
all hooks are disengaged and FWD
latchlock is unfastened
LCHD light
blue light is ON when all door hooks
and latch locks are fully engaged
GND HDL light
Ground handling bus ON BAT red light
is ON when ground handling bus is
directly supplied by HOT main bat bus:
means that the battery is discharging
even if the BAT toggle switch is in OFF
position (visible even when the cover
panel is closed)
This red light is ON when:
– The refueling panel is open
– The cargo door control panel is open
– The passenger door is open and
alert, that the battery is discharging before leaving the aircraft
Actuator selection switch
is used to operate the door (OPEN
or CLOSE) when the CARGO
DOOR ARMED green light is on
Panel cover switch
connects the ground handling bus on
line when the panel cover is opened
and allows operation of cargo door.
During the opening, a self test of the
MFC 1A and 2A is performed to initiate
the control system of the cargo door.
CARGO LIGHT switch
allows activation of the cargo
bay light from outside
3. Doors panel
ATA 52
CAB OK and SVCE OK
Light on when SW TEST depressed
and check microswitches operation
UNLK
At least 1 micro switch is opened
SW TEST
Tests continuity of microswitch system
(on ground, doors opened)
9
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4. External lights
ATA 33
ABCDE F GH-
Navigation lights
Taxi and T/O lights
Landing lights
Wing lights
Beacon lights
Strobe lights
Logo lights
Emergency light
Cabin panel
Memo panel display
10
A. Aircraft general
5. EXT LT panel
ATA 33
BEACON and NAV
supplied by SVCE BUS and BUS 1
LOGO
supplied by SVCE BUS
STROBE, LAND
supplied by ACW BUS 1
(Left Hand), ACW BUS 2
(Right Hand)
TAXI & T.O
Supplied by ACW BUS 2
WING
Supplied by DC BUS 2
6. Memo panel display
ATA 33
SEAT BELT
displayed in cyan when associated
switch is selected ON
NO DEVICE
displayed in cyan when associated switch is selected ON
SEAT BELT
displayed in amber crossed when the
signal is invalid.
NO DEVICE
displayed in amber crossed when
the signal is invalid.
7. Signs panel
ATA 33
ON
emergency exit lights illuminates.
Supply: DC STBY or 6 V BAT packs
NO DEVICE and SEAT
BELTS
Cyan message on memo
panel display when ON.
(DC BUS 2)
ARM
Emergency lights illuminate
when <18 V on STBY bus
or if both DC GEN off line.
Emergency lights extinguish
when >20V on STBY bus and
at least 1 GEN operating
DISARM
system deactivated
11
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8. Internal lighting
ATA 33
0,33('
29+'
The STORM switch overrides the
MIP/PED rotary selector to put in
the maximum intensity setting
12
A. Aircraft general
9. LT panel
ATA 33
MIP / PED
Selects activation and intensity of
integral lighting of the main instrument panels (MIP) and pedestal
(PED)
0,33('
29+'
OVHD rotary selector
selects activation and intensity of overhead panels integral lighting
10. ANN LT panel
FLOOD knob
selects activation and intensity panel
flood lighting. (OFF TO BRT)
ATA 33
To check and control the intensity of:
– the annunciator lights on the overhead
and pedestal panels
– the overhead panel flow bars
TEST: All the associated lights come
on bright
BRT: associated light illuminate bright
DIM: associated light are dimmed
11. Side panel
ATA 33
CAPT READING LT knob
selects activation and intensity
of the respective spot light
CAPT CONSOLE LT knob
selects activation and intensity of
the respective lateral console
12. FLT COMPT LT panel
DOME switch
BRT: dome lights are supplied
with maximum intensity
DIM: dome lights are dimmed
OFF: both dome are off
DOME light: the F/O dome light
becomes BRT when the switch in
BRT or DIM if:
– dual DC GEN loss
– or on ground, with BAT supply
only
ATA 33
STORM switch
On position, it overrides the MIP/
PED rotary selector to put in the
maximum intensity setting
STBY COMPASS switch
to illuminate the STBY COMPASS
ON and OFF position
13
B. Integrated systems
FCOM 1.01
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1. Integrated Modular Avionics (IMA)
ATA 42
The Integrated Modular Avionic (IMA) provides computation, memory and Input/Output data processing resources, shared
between several avionics applications.
The Integrated Modular Avionic is mainly composed of the dual Core Avionic Cabinets (CAC 1&2).
The term CAC (Core Avionic Cabinet) designs the whole equipment composed of the rack and the set of cards.
In the basic configuration, each CAC is composed of:
– 1 CPM (Core Processing Module)
The CPMs provide shared memory and computation resources to execute hosted avionics applications.
– 1 IOM-S (Input/Output Module)
This IO Module is dedicated to provide ARINC and discrete I/O for all functions
– 1 IOM-AP (Input/Output Module)
This IO Module is dedicated to provide discrete and analog I/O for the Auto-Flight application.
– 2 IOM-DC (Input/Output Module)
The IOM-DC provide discrete and analog I/O for Data Concentration Application (DCA) .
– 1 SWM (gateway and SWitch Module)
This module is dedicated to connect together CPM and other Avionics Data Network subscribers.
The communication means is based on AFDX network, linking network subscribers through SWM.
The main applications hosted by the Core Avionic Cabinets are :
– Flight Warning (FWA)
– Auto-Flight (AFCA)
– Centralized Maintenance (CMA) (only on CAC 1)
– Data Concentration (DCA)
The CAC 1 & 2, communicate with five display units and systems through different data bus formats:
– AFDX: Avionics Full DupleX switched ethernet
– A429: ARINC 429
– Analogic
– Discretes
Two of the five displays units (DU2 and DU4) are dedicated to two other functions:
– Flight Management Application (FMA)
– Radio Management Application (RMA)
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B. Integrated systems
2. Multi Function Computer (MFC)
ATA 31
Numerous logic funtions are performed by two independant computers (MFC1 and MFC2).
Each computer includes two independant modules (A and B)
The purpose of these computers is to:
– monitor, control, authorise operation
of the aircraft systems
– manage system failures and flight
enveloppe anomalies and command
triggering of associated warning
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FAULT
illuminates and the FWS is activated when a
malfunction or electrical supply fault is detected.
The module automatically becomes inoperative.
This light also flashes during self-test of the
module.
During powering, since all 4 modules are
selected ON, the following sequence is
executed:
MFC 1A and MFC 2A FAULT lights flashing (selftest of these modules)
MFC 1A and MFC 2A FAULT lights extinguish.
MFC 1B and MFC 2B FAULT lights flashing (selftest of these modules)
MFC 1B and MFC 2B FAULT lights extinguish
OFF
The module stops operating
The MFC functions can be processed: – in one module only
– in several modules (redundancy)
– partially in 2 modules
NOTE: If the cargo door control panel is opened,
the self test of MFC 1A and 2A are already done,
and only the MFC 1B and 2B are tested. (See
chapter A.2)
Example:
MODULE
SYSTEM
FUNCTION
1A
FLIGHT
STICK PUSHER
CONTROLS
STALL WARNING
1B
2A
2B
– The stick pusher function is integrated in modules 1A, 1B, 2A and 2B.
– The stall warning function is integrated in modules 1B and 2B.
– The stick pusher function is available if modules (1A AND 2A) OR (1A AND 2B) OR (1B AND 2A) OR (1B AND 2B) operate. This
function is therefore not available if modules (1A AND 1B) OR (2A AND 2B) are lost.
– The stall warning is available if modules 1B OR 2B operate.
This function is therefore not available if modules 1B AND 2B are lost.
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3. Multi Purpose Computer (MPC)
ATA 31
The MPC unit is including two parts:
– Flight Data Acquisition unit (FDAU)
– Data Management unit (DMU)
A) FDAU Part
The MPC acquires data in digital, analog or discrete format from aircraft systems for various FDAU functions:
– Flight Data Recording (SSFDR) (refer to chapter Flight Instruments).
– Aircraft Performance Monitoring (APM) (Refer to chapter Ice and Rain Protection).
– Data broadcast to CAC (to avionics system).
– Time management.
– Flight time management.
– Flight number management.
– Configuration management (A/C type, A/C ident, APM version).
B) DMU Part
The MPC has the capability to manage ACMS functions (Aircraft Condition Monitoring System) in order to:
– facilitate the maintenance of the aircraft.
– record data for the Flight Data Monitoring purpose (FDM)
The main possible ACMS functions are:
– QAR/DAR recording on a PCMCIA disk (QAR when the data frame is the FDR one’s/DAR when it is reprogrammed by
a ground support equipment) A FDM purpose
– Management of reports (take-off, cruise... ) A FDM purpose
– Dialogue with the following aircraft equipments: MCDU, Printer, ACARS (optional)
– Other maintenance functions.
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B. Integrated systems
4. Schematic
19
C. Flight warning system
FCOM 1.02
21
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1. Cockpit colors philosophy
ATA 31
In normal operation, all lights are extinguished (Dark cockpit philosophy). With some exceptions, the lights illuminate to
indicate a failure or an abnormal condition.
HIGH LEVEL COLOR CODE RULES FOR ATR 600
COLOR USED for DISPLAY PICTURES – PRINTING – PUSH
BUTTONS – CONTROL PANELS
WHITE
WHITE means an inert information
– Unit data and external world reference: graduations on IAS strip, Baro-Alt strip, VS strip &
Heading rose. Engine & system parameter indicators graduations
– Consulted data (MCDU)
– Normal (non icing) speed references (VMLBO, Flaps retraction speed)
– System selected OFF (displayed on Display Unit), Push Button OFF light on control panels, inert
shape on Display Unit
– Title, comments & action menu list
– Advisory messages on MCDU (no crew action required)
– Segregation area with horizontal or vertical lines
LIGHT GREY
LIGHT GREY is used for typing, for system picture inoperative functions & for virtual control
buttons (VCP)
– Light grey typing on Display Unit means associated virtual control is inhibited
– Pipe shapes (fuel or air or hydraulics) are displayed light grey when no flow or pressure is detected
– Virtual control button light grey means button is not auto maintained pushed
Specific for ANF (Airport Navigation Virtual Control Panel): opened menu on a light grey background summarizes MCP (Manual Control Panel) current active PB functions
DARK GREY
DARK GREY is used for virtual control button (on Virtual Control Panel)
– Dark grey virtual push button means associated virtual control is auto maintained pushed for
a given time (i.e. IDENT for ATC transponder)
YELLOW
YELLOW is used for A/C references, for temporary information, for reversion configuration
– On PFD & ND: IAS strip, Baro-Alt strip, VS strip & Heading rose A/C references are yellow in
relationship with A/C mock up displayed yellow (same philosophy as Airbus)
– Temporary data on Display Units & MCDU: manual insertion in progress (active flight plan update in progress, COM or NAV or SURV radio tuning in progress, Take Off performances data
not yet confirmed)
– Temporary FMA message (7 seconds) following an “unable” AP-FD manual selection (associated to triple “clic”)
– Temporary System TEST phase launched by crew
– Manual ADC, AHRS or NAV Source reversion: new active source is typed yellow to advise crew
that a single source is used by both sides (amber is inappropriate as long as current source in
not malfunctioning)
22
C. Flight warning system
AMBER
AMBER is used for Icing condition data, for detected malfunction, for abnormal range data, for
aircraft parameter or computation result out of normal range
– In icing conditions flight, aircraft may have downgraded performances and handling qualities.
Crew shall not disregard it. An amber CAUTION level is associated (for ATR) to this flight condition change. Speed references are adjusted, icing speed references (VMLBO, Flaps retraction
speed) are displayed amber to point out icing conditions effects (icing color reference is amber)
– CAUTION alerts & messages (requiring crew action) are typed amber to point out icing or malfunction detected
– Active or selected Abnormal Procedure title are typed amber (and displayed according to a defined priority level)
– Active Status title associated to a previous system malfunction is typed amber
– If a data resulting of a system calculation is out of range, this data is typed amber to point out
the crew needs to adjust some flight parameters in order to recover normal target range (for
instance, if unable to match an altitude constraint, constraint data will be typed amber, crew
must react to fulfill the constraint)
– If data (flight or system) are out of normal range, data parameter are displayed amber (Push
Button Fault, dedicated amber light on a panel, system picture displayed amber, parameter
value typed amber)
– Invalid signals are displayed by amber crosses or dashes
RED
RED is associated to a warning & requests an immediate crew action
– WARNING alerts & messages are typed red
– Active or selected Emergency Procedure title are typed red (and displayed according to a defined priority level)
– If a system is detected out of limits, data parameter are displayed red (dedicated red light,
system picture displayed red, parameter value typed red)
MAGENTA
MAGENTA is associated to current constraint.
– FMS Managed Speed and FMS current leg guidance are considered as current constraints.
– Current FMS active leg data & lateral deviations are considered as current constraints information and displayed magenta to point out FMS source.
– Active Speed and Altitude constraints are displayed magenta
– Some specific constraints (Take Off pitch trim, GO-AROUND Torque) are displayed magenta
– ANF (Airport Navigation) selections are magenta (according to Airbus rules applied).
CYAN
CYAN is dedicated to manual operations
– Manual insertion are typed cyan
– Manual target selections are cyan bugs (IAS, HDG, Baro-Alt, VS) or cyan dots (selected flaps
or man selected TO TQ)
– Active VCP selection in a menu (except ANF)
– Alternate system selection is indicated cyan (XFEED valve) on system page and on control
panel light
– Override system selection is indicated cyan on system page and on control panel light
– Armed AP-FD modes
LIGHT BLUE
LIGHT BLUE is dedicated to VCP area of Display Unit to make evident that VHF manual management page is active and discriminate it from the other ones.
GREEN
GREEN is dedicated to automatic normal functioning & to computed data in normal range
for each interface: CONTROL PANEL, DISPLAY UNIT format & MCDU.
23
S y s t e m s 4 2/72 - 6 0 0
2. FWS description
ATA 31
The FWS draws crew’s attention when a failure is detected and guides the crew to the system affected by the failure
Three types of visual devices are used: – MASTER WARNING and MASTER CAUTION lights
– FWS alert and procedure windows
– LOCAL ALERT lights
Detection sequence
INFORMATION
IDENTIFICATION
ISOLATION
Example: ACW Generator 1 failure
Local alert: fault light on the
ACW gen 1 push-button
MASTER
CAUTION light
flashing
+ Single Chime
ELEC ACW GEN 1
on alert window
and ACW GEN 1 on
procedure window
Local alert: ACW GEN 1 FAULT
on ACW/HYD Schematic Display (SD)
24
C. Flight warning system
3. Alert window
ATA 31
ENGINE
ENG 1 FIRE / ENG 2 FIRE
Engine fire detected
ENG 1 OUT / ENG 2 OUT
Engine 1 or 2 sensed out, in takeoff / go-around configuration
ENG 1+2 OUT
Both engine sensed out with aircraft in flight configuration
SINGLE ENGINE
Aircraft in flight configuration and one engine sensed out
ENG START
Start light ON past 45% NH or GCU failure during start
ELEC X START
Cross start failure. Opposite generator has not come on line to assist
start at 10% NH (on ground only).
ENG EXCESS ITT
ITT more than 800°C (715°C in hotel mode)
ENG START NO NH
NH <20%, 10s after starter push button ON
ENG NO ITT
ITT <400°C, 10s after opening the fuel
NAC OVHT
RH NAC OVHT >170°C
LOOP 1A / LOOP 1B / LOOP 2A / LOOP 2B
engine fire loop fault
PROP BRK
Prop brake not in full, locked or in full, released position
ENG EEC / ENG EEC 1+2
EEC or both EECs Failure
ENG BOOST
Disagreement between the EEC rating and the push button position
ENG 1 OUT / ENG 2 OUT
Engine 1 or 2 sensed out in flight configuration
IDLE GATE
Automatic idle gate system failure
ENG 1 LO PITCH / ENG 2 LO PITCH
propeller blande angle <8° in flight
ENG PROP NP1 / ENG PROP NP2
Unexpected 100% NP (triggered >86%)
ENG 1 PROP LIM / ENG 2 PROP LIM
NP >106%
ENG 1 PEC SG CH / ENG 2 PEC SG CH
Lost of one PEC channel ----> operation on single channel
ENG 1 PEC / ENG 2 PEC
PEC Failure
ENG 1 OVER LIM / ENG 2 OVER LIM
TQ >120%, NH >106.4%, NL >106.8% and start rotary selector OFF
ENG1 OIL TEMP L / ENG2 OIL TEMP L
Oil temp low on ground <0°C / Oil temp low <45°C with engine running
and PL>30°
ENG1 OIL TEMP H / ENG2 OIL TEMP H
Oil temp between 125°C and 140°C
ENG 1 OIL OVHT / ENG 2 OIL OVHT
Oil temp >140°C
ENG 1 OIL PRESS / ENG 2 OIL PRESS
Oil press <40 Psi (inhibited 30 sec during engine start)
FUEL
FUEL 1 TEMP HI / FUEL 2 TEMP HI
Fuel temperature >50°C
FUEL 1 TEMP LO / FUEL 2 TEMP LO
Fuel temperature <0°C
ENG FUEL CLOG
Fuel press loss in corresponding HP pump fuel filter ΔPSI >25 PSI. Filter
blocked and by-passed when ΔPSI >45 PSI
FUEL FEED LO PR
Engine feed low press <4 psi
FUEL LO LVL
Fuel tank <160 kg or Fuel tank >160 kg and feeder tank not full
FUEL MISMATCH
Difference between fuel FMS and fuel quantity indicator: on ground
>200 kg during 10s, in flight >200 kg during 60s
FUEL UNBALANCED
Difference between both tanks >200 kg
ELEC
ELEC DC GEN 1+2
Dual DC GEN Loss
ELEC DC 1 / ELEC DC 2
DC BUS 1 or 2 not supplied
ELEC AC 1 / ELEC AC 2
AC BUS 1 or 2 not supplied
ELEC ACW 1 / ELEC ACW 2 / ELEC ACW 1+2 ACW BUS 1 or/and 2 not supplied
ELEC DC ESS
DC essential bus not supplied
25
S y s t e m s 4 2/72 - 6 0 0
ELEC DC EMER
DC emergency bus not supplied
ELEC DC GEN
One DC GEN Loss
ELEC INV 1 / ELEC INV 2
Inverter failure or supply loss
ELEC ACW GEN 1 / ELEC ACW GEN 2
One ACW GEN Loss
ELEC DC SHED
One of the DC SVCE / UTLY 1 and 2 busses is shed
ELEC BAT CHG
Thermal runaway / Bus voltage <25V / start sequence/Bat sw on OVRD.
ELEC CHG LOSS
Both batteries chargers fault
ELEC BAT DISCH
Main or Emergency battery discharge
ELEC STBY UNDV
DC STBY <19.5V
HYDRAULIC
HYD BLUE LO LVL / HYD GREEN LO LVL
Associated compartment <2,5 liters
HYD PUMPS LOSS
Both main pump loss. Blue pressure can be recovered with the aux
pump in approach (Landing gear lever in down position)
HYD SYS LOSS
Both system loss.
HYD BLUE (GREEN) LO PR / HYD AUX LO PR
Pump delivery pressure <1500 psi
HYD BLUE (GREEN) OVHT / HYD AUX OVHT
Temperature >121°C (250°F)
FLIGHT CONTROL
FLAPS UNLK
Spurious Flaps retraction more than 3° (42-600), 4° (72-600)
FLAPS ASYM
>6.7° between the left and right flaps. Flaps frozen in current position
FLAPS JAM
Triggerred when the difference between the average flaps position and
the selected position is >1°
PITCH TRIM ASYM
pitch tabs desynchronization greater than 0.7°
FLT CTL RUD RCU
RCU supplied by DC current for more than 60s
PITCH DISC
Elevator uncoupling
PITCH RECONNCT
Appears during the procedure of pitch reconnection on ground
FLT CTL PUSHER
Stick pusher failure
FLT CTL TLU
System disagree / two ADC failures / ADC datas incoherence / TLU
position synchro failure. T/O or T/O Config Test and TLU not LO SPD
AIL LOCK LIT
Triggered whenever one of the locking actuators is in disagreement with
the gust lock lever position (lock or unlock position)
LANDING GEAR
LDG GEAR NOT DN
Any gear not seen down and locked and:
1. flaps 25° or flaps 30°, ZRA <500 ft and PL at low power.
2. at least one PL at FI and ZRA <500 ft
LDG GEAR
Landing lever down, but at least one landing gear is not sensed in lock
down position
WHEELS A-SKID
Anti-skid failure
WHEELS BRK HOT
Brake temp >160° (42-600) and >150° (72-600)
AIR
FWD SMK
Forward cargo smoke
AFT SMK
Aft cargo or lavatory smoke
ELEC SMK
Avionics smoke
AUX AFT SMK
Smoke in auxiliary aft compartment (optional)
AIR BLEED 1 / AIR BLEED 2
Bleed valve disagreement with P/B selected position
AIR BLEED1 OVHT / AIR BLEED2 OVHT
Bleed DUCT temp >274°c
AIR LEAK 1 / AIR LEAK 2
Leak detected with a loop when the temperature >153°C
AIR X VALVE
Air cross feed valve open in flight
AIR PACK / AIR PACK 1+2
Pack valve disagreement with PB selected position or Ovht downstream
pack comp (>204°C).
AIR RECIR FAN 1 / AIR RECIR FAN 2
Fan low speed or motor overheat.
AIR DUCT OVHT
Duct overheat >92°C.
26
C. Flight warning system
EXCESS CAB ALT
Cabin altitude over threshold (10.000 ft or 11.000 ft if mod High Alt Rwy)
AIR AUTO PRESS
Auto press digital controller failure.
AIR VENT EXH
Avionic extraction fan failure or overheat
AIR OVBD
Ovbd Valve in disagreement with Ovbd Valve SW position.
EXCESS CAB ΔP
Cabin/ Outside pressure difference in excess of 6.6 psi
AIR FWD DET FAN
Forward fan sensed inop
AIR AFT DET FAN
Lavatory fan sensed inop
AIR DITCH
Ditch P/B selected on
OXY
Oxygen supply off or oxygen lo pressure sensed
ANTI ICE
A-ICING BLEED
Airframe bleed fault alert covering low pressure, overheat and AFR
airbleed P/B off
A-ICING FRAME
Airframe deicing fault confirmed by MFC
A-ICING AUTO
Auto mode fault detected or MAN mode selected
A-ICING SEL
Mode selector fault
A-ICING DETECT
Ice detector fault
A-ICING ENG 1 / A-ICING ENG 2
Deicing boots fault detected on engine 1 or 2
A-ICING PROP 1 / A-ICING PROP 2
Blade deicing fault detected on at least one blade on enigne 1 or 2
A-ICING HORNS 1 / A-ICING HORNS 2
Horn deicing fault detected on Horns 1 (rudder & left elevator) or Horns 2
(aileron & right elevator)
A-ICING L WSHLD / A-ICING R WSHLD
Windshield deicing fault detected on left (L) or right (R) side
A-ICING WINDOWS
Either Left or Right side windows deicing fault detected
A-ICING PROBE
Either Left or Right or both alpha probe deicing fault detected
A-ICING PIT CPT / --- PIT F/O / --- PIT SBY
Pitot heating fault (captain, first officer or stand by)
A-ICING TAT CPT / A-ICING TAT F/O
TAT probe heating fault (captain or first officer)
ICING
Ice accretion detected by ice detector
AUTO PILOT
AP PITCH TRIM
Pitch trim failed
PITCH MISTRIM
Pitch mistrim
AILERON MISTRIM
Aileron mistrim
RUDDER MISTRIM
Rudder mistrim
AP YAW TRIM
Yaw auto trim fail
MPC
APM FAULT
A fault has been detected in the APM system
DEGRADED PERF
Abnormal drag increase
INCREASE SPEED
Aircraft speed lower than Minimum Severe Icing Speed + 2kt
AVIONICS
AUDIO SEL CAPT / AUDIO SEL F/O
RCAU on CAPT or F/O side is sensed fault or has a power loss
SGL DME / DME LOSS
One DME lost (2 DME config)/ Both DME lost (2 DME config) or DME
lost (single DME config)
RMS / RMS 1+2
One RMS lost / RMS 1+2 lost
TCAS
TCAS sensed fault
XPDR
At least one XPDR detected fault
AHRS / AHRS 1+2
One AHRS fault / Both AHRS fault
AHRS NOT ALIGN
AHRS sensed not aligned
ADC / ADC 1+2
One ADC fault / Both ADC fault
ATT DISAGREE
3° pitch and 3° roll discrepancy
HDG DISAGREE
8° discrepancy
ALT DISAGREE
60ft + (Zp1 + Zp2)/460
IAS DISAGREE
10kt discrepancy
27
S y s t e m s 4 2/72 - 6 0 0
VHF / VHF 1+2 / HF / HF 1+2
VHF or HF set(s) sensed failed
VHF EMITTING / HF EMITTING
Transmitting / Emitting for more than 29s
DU 1(2)(3)(4)(5) DISCRPNCY
Discrepancy on one DU (internal and external with other DU)
DU DISCREPANCY
Discrepancy on not identified DU (at least 2 DU discrepancy)
DU TEMP HI
Temperature >70°C after brightness reduction
MULTI DUs T HI
Temperature >70°C after brightness reduction for at least 2 DUs
FWS SGL CH
Flight Warning Application (FWA) loss on one CAC
SWITCH SGL CH
gateway and SWitching Module (SWM) card loss on one CAC
CPM 1 / CPM 2
Core Processing Module (CPM) card loss on one CAC
IOM 12 / IOM 13 / IOM 22 / IOM 23
Input/Output Module (IOM) card loss
CPM x + IOM xx
Core Processing Module (CPM) card loss on one CAC and Input/
Output Module (IOM) card loss on the other CAC
IOM xx + xx
2 Input/Output Module (IOM) cards loss
MISCELLANEOUS
CONFIG
Configuration warning refer to chapter C.4 here below
RAD-ALT
Single RA loss on 2 RA installed configuration
RAD-ALT LOSS
RA loss on single RA configuration or dual RA loss on 2 RA configuration
GPWS
GPWS fault sensed
TERRAIN
Terrain mode fault sensed
DOORS
Any door sensed open on ground
DOOR EMER / DOOR FWD COMPT
Emergency hatch or Forward compartment door sensed unlocked in
flight
DOOR LH (RH) FWD / DOOR LH (RH) AFT
Respective door sensed unlocked in flight
DATALINK
CMU fault or loss of link for more than 120s
MAINT PANEL
Maintenance panel sensed open
DATA RECORDER
Loss of power supply to Data recorder detected
VOICE RECORDER
Loss of power supply to Voice recorder detected
FDAU
FDAU sensed failed
BAD CONF / CONF UPDATED
At least one DU software discrepancy at A/C power up
MFC
MFC 1A / MFC 1B / MFC 2A / MFC 2B
Single MFC channel failure
MFC 1A(1B)(2A)(2B) + 1B (1A)(2A)(2B)
Multiple MFC channels failures (combinations)
4. EMER audio cancel & TO
config test
EMER AUDIO CANCEL
Guarded switch, cancel the aural
specific of an undue continuous
aural except for landing gear,
VMO, VFE, VLE, stall warning,
pitch trim whooler, landing gear,
AP disconnection
28
ATA 31
TO CONFIG TEST
– To check T/O configuration (PWR
MGT in T/O+ TLU LO SPD illuminated
+ pitch trim in green sector+flaps 15° +
no AIL LOCK LIT on FWS) by simulating
power levers at T/O position, except
PARK BRAKE
– To perform an automatic RECALL
C. Flight warning system
5. Aural alarms
ATA 31
CLACKER
VMO
VLO - 5 kt
VFE - 5 kt
DOOR BELL
Attendant or
ground calls
WHOOLER
Pitch trim in motion
(more than 1s)
CAVALRY CHARGE
AP Disconnects
C CHORD
Altitude alerts
CRICKET
Stall warning associated
STICK SHAKER/PUSHER
AOA (Angle Of Attack)
29
D. Air
FCOM 1.03
31
S y s t e m s 4 2/72 - 6 0 0
1. Pneumatic system
ATA 21/36
The pneumatic system supplies aircraft systems which use pressurized air:
These systems are: – Air conditioning
– Ventilation
– Pressurization
– De-icing
1.1. Schematic
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D. Air
1.2. AIR BLEED panel
ENG BLEED
Controls both bleed and HP
valves. Spring loaded closed.
Must have air and electricity to
open
Auto closure when OVHT, leak,
overpressure, fire handle pulled,
UPTRIM triggered or prop
brake on (left one only). Inhibited
during eng start
GRD X FEED
Spring loaded closed. Inhibited in
flight. Auto opens on ground when
only one bleed valve is opened
PACK VALVE
FAULT
pack valve disagreement with
pb / or OVHT downstream pack
comp. (>204°C). FWS. Valve
auto closed. Ground cooling
turbo fan failure
OVHT
either duct temp switch above
274°C. FWS. Auto closure
bleed valves (LP and HP). May
be reset after cooling
OVERHEAD PANEL
ENG BLEED
FAULT
Bleed valve disagreement with
selected position (or in case
of OVHT or LEAK). FWS.
Associated valves auto closed
PACK VALVE
Spring loaded closed. Must
have air and elec power to
open. 6’’ delay on RH valve for
pax comfort
LEAK
activates when T° detected by
bleed loop exceeds 153 ±8°C.
EWD. Auto closure after 1’’ of
following valves: Bleed, HP,
pack and GND Xfeed if left
bleed leak affected
DO NOT RESET BLEED
33
S y s t e m s 4 2/72 - 6 0 0
2
4
3
1
5
34
D. Air
Item
Display
Description
BLEED VALVE ON , OPENED
AND ENGINE RUNNING
Item
Description
BLEED
OFF
BLEED VALVE OFF
BLEED
FAULT
BLEED VALVE FAULT
3
LEAK
BLEED LEAK
4
OVHT
BLEED OVERHEAT
2
BLEED VALVE OFF
1
Display
BLEED VALVE ON BUT CLOSED
X FEED
NORMAL OPERATION
X FEED OPEN & AIR FLOW
BLEED VALVE OFF BUT NOT
CLOSED AND ENGINE RUNNING
X FEED
BLEED VALVE OFF BUT NOT
CLOSED AND ENGINE NOT
RUNNING
X FEED
5
X FEED
X FEED
NORMAL OPERATION
XFEED CLOSED
NOTHING DISPLAYED
X FEED NORMALLY CLOSED
BUT OPENED & AIR FLOW
X FEED NORMALLY CLOSED
BUT OPENED & NO AIR FLOW
X FEED NORMALLY OPENED
BUT CLOSED
35
S y s t e m s 4 2/72 - 6 0 0
AIR CONDITIONING IN HOTEL MODE
On ground, when engine 2 is started in hotel mode:
– The right HP bleed valve is opened (air supplied by HP
compressor at low engine power)
– The right Eng bleed valve opened (at NH 45% + 30s)
– The cross feed valve is opened
– Both packs are supplied with air at 38 psi
36
D. Air
AIR CONDITIONING IN NORMAL FLIGHT
– Both HP bleed valves are closed (air supplied by LP
compressor at high engine power)
– The cross feed valve is closed
– Each pack is supplied by its dedicated engine with air at
25 psi
37
S y s t e m s 4 2/72 - 6 0 0
AIR CONDITIONING IN FLIGHT WITH A BLEED FAULT
In case of:
• Overtemperature (T>274°C)
• Leak (T>153°C outside the duct)
• Overpressure (P>80 psi)
The eng bleed valve is closed and the FAULT is triggered on
the bleed P/B and on the pack P/B.
The other engine supplies the cockpit and cabin ducts throught the mixing chamber
– HP bleed valves is closed (air supplied by LP compressor at high engine power)
– The cross feed valve is closed
– One pack is supplied by its dedicated engine with air at 25 psi
38
D. Air
2. Air conditionning
ATA 21
The air conditionning system is provided to keep the flight compartments at the required temperature, pressure, humidity
and cleanliness for the comfort of the passengers and crew.
2.1. Schematic
Cooling of air:
– by ground turbo fans:
• IAS ≤ 150 kt and ldg gear is retracted for less than 10 min
• IAS ≤ 150 kt and ldg gear is extended.
– by ram air when IAS >150 kt
39
S y s t e m s 4 2/72 - 6 0 0
2.2. COMPT TEMP panel
RECIRC FAN
Assists pack air flow
RECIRC FAN
FAULT: fan low speed or motor overheat + FWS. No auto
disconnect
COMPT INDICATOR
Duct temperature limited to
88°C. (191°F) by pneumatic
temp.limiter
TEMP SEL
OVHT: duct overheat >92 °C +
FWS. Pack valve will not auto
close
MAN
compt temp knob controls
directly temp control valve
40
TEMP SEL
AUTO: the temperature is
regulated by the electronic
temperature controller, taking
into account:
– duct temperature
– zone temperature demand
selector
– associated compartment
temperature
– aircraft skin temperature
FLOW
NORM: 22 psi (pack valves)
HIGH: 30 psi (pack valves)
S y s t e m s 4 2/72 - 6 0 0
4
5
3
6
1
8
7
2
42
D. Air
Item
Display
PACK
1
Description
Item
Display
PACK VALVE ON
PACK
OFF
PACK VALVE OFF
PACK
FAULT
PACK FAULT
PACK
STBY
PACK VALVE STANDBY
P/B DEPRESSED AND
BLEED VALVE P/B RELEASED OUT
EXTRACT FAN ON
4
EXHAUST
OVBD
EXHAUST MODE P/B RELEASED
EXHAUST
FAULT
EXTRACTION FAN FAULT DISPLAY
FULL OPEN
FULL CLOSE
RECIRCULATION FAN ON
RECIRCULATION FAN FAULT
RECIRC
RECIRCULATION FAN 1 OR 2 OFF
RECIRC
RECIRCULATION FAN 1 OR 2
FAULT
AUTOMATIC MODE
OVBD VLV PARTIALLY OPEN
6
3
MANUEL MODE
OVBD VLV FULL CLOSED
AUTOMATIC MODE
OVBD VLV FULL CLOSED
5
BOTH PACK VALVES ON OR
BOTH RECIRC FANS ON
LEFT PACK VALVE AND RECIRC
FAN 2 OFF OR FAULT
MANUEL MODE
OVBD VLV FULL OPEN
AUTOMATIC MODE
OVBD VLV FULL OPEN
RECIRCULATION FAN OFF
2
Description
OVBD VALVE
OVBD VLV FAULT DISPLAY
OVBD VLV OPEN
OVBD VALVE
OVBD VLV FAULT DISPLAY
OVBD VLV CLOSED
AUTO
AUTOMATIC TEMPERATURE
CONTROL
MAN
MANUAL TEMPERATURE
CONTROL
OVHT
DUCT OVERHEAT ALERT
21 °C
VALID SENSOR MEASUREMENT
-- °C
INVALID MEASUREMENT
AIR
HIGH FLOW
HIGHT FLOW SELECTED
7
8
RIGHT PACK VALVE AND RECIRC
FAN 1 OFF OR FAULT
PACK VALVES AND RECIRC FANS
OFF OR FAULT ON BOTH SIDES
43
S y s t e m s 4 2/72 - 6 0 0
3. Avionics ventilation
ATA 21
The ventilation system provides cooling through ambient air extraction to limit the internal operating temperature of the
electronic equipment
3.1. Schematic
(/(&60.
3.2. AVIONICS VENT panel
FAULT
fan failure/overheat (fan inhibited
for 120 s. after eng start or after
a GPU power on. FWS)
EXHAUST MODE
NORM
– On ground, ENG 1 off: extract
fan on. OVBD valve full open, U/F
valve closed
– Air/ground, ENG 1 on: extract
fan operates. OVBD valve closed.
U/F valve opened
OVBD
extract fan off
OVBD valve partially opened (in
flight only). U/F valve closed
44
FAULT
OVBD valve in disagreement with
ovbd valve SW position
OVBD VALVE
– AUTO except in emergency
– direct control of OVBD valve.
The full open position is possible
only if the delta P is <1 psi
D. Air
4. Pressurization
ATA 21
Compressed air is delivered by the packs. Pressure is controlled by the amount of cabin air discharged outboard.
4.1. Schematic
FL 250 = DIFF 6 PSI
Cabin altitude 6740 ft
Normal rate = 50% aircraft
VS, max +600 ft/min
FL 200 = DIFF 5 PSI
normal rate – 400 ft/min
fast rate – 500 ft/min
Normal rate = 30% aircraft
VS, max +550 ft/min
FL 100 = DIFF 4 PSI
3500 ft
Cabin altitude = airport altitude
– 300 ft before LDG
0 ft after LDG
Digital controller
AUTO MODE
T/O elevation up to 3500 ft
Electropneumatic
outflow valve
Baro setting by CAPT
Altimeter (ADC 1) or 1013
(ADC 2) if failure ADC 1
Landing elevation
Safety device
if DIFF > 6.35 PSI
or < –0.5
Cabin pressure
Manual controller knob
MANUAL MODE
Pneumatic
outflow valve
45
S y s t e m s 4 2/72 - 6 0 0
4.2. Cabin pressure indicators
Pressure control mode
AUTO or MAN
DIFF
Differential pressure:
max +6.35 / –0.5
ALT
Cabin alt: based on 29.92 in.hg
(1013,2 Hpa)
RATE
Cabin rate of climb
4.3. AUTO PRESS panel
AUTO PRESS (DC BUS )
Memorize departure field elevation
up to 3500 ft
DUMP
FUNCTION ON
(guarded pusbutton)
Both outflow valves fully open in
auto mode only.
ELV SET
Trigger switch to set landing
elevation
DESCENT RATE
NORM= –400 ft/min
FAST= –500 ft/min
Fast is used when Vs > –1500 ft/
min
TEST
Displays alternately 18800 and
–8800, FAULT appears on MAN pb.
Test is inhibited in flight
4.4. MAN RATE KNOB and CABIN PRESS panel
NORM
AUTO MODE position. When used
in MAN mode, cabin rate selection
+2500/–1500 fpm
FAULT
digital controller failure. FWS
DITCH
pb ON both outflows are fully
closed
46
MAN
digital controller out of operation.
(no more digits on landing elevation
display)
D. Air
1
Item
Display
3
Description
6
8
3.00
6P NOMINAL DISPLAY
0
6
8
0.25
6P PRE-ALERTING DISPLAY
0
6
8
7.00
6P ALERTING DISPLAY
6
8
-.--
INVALID 6P
0
2
Item
0
2
0
0
2000
2000
2000
2000
Description
AUTO
PRESS
XXXX
CAB ALT AUTOMATIC PRESSURE CONTROL
5020 FT NOMINAL DISPLAY
1300 FT
AUTO
PRESS
XXXX
CAB ALT AUTOMATIC PRESSURE CONTROL
1300 FT FAULT
1300 FT
CAB ALT MANUAL PRESSURE CONTROL
MAN
5020 FT
ALT
TARGET 5020 FT NOMINAL DISPLAY
1
0
Display
3
CAB ALT MANUAL PRESSURE CONTROL
MAN
2050 FT
ALT
TARGET ____ FT INVALID TARGET
CAB ALT
MAN
____ FT INVALID CAB ALT
ALT
TARGET 2050 FT
700 UP
RATE OF CLIMB
1000 DN
RATE OF DESCENT
- --
INVALID RATE
CAB ALT
MAN
8900 FT CAB ALT PRE-ALERTING DISPLAY
ALT
TARGET 5020 FT
MAN
CAB ALT
ALT
10100 FT CAB ALT ALERTING DISPLAY
TARGET 5020 FT
2000
2000
47
E. Automatic flight
control system
FCOM 1.04
49
S y s t e m s 4 2/72 - 6 0 0
1. Schematic
QUICK
DISC/ TCS
AP quick disconnect pb
– disconnect AP when depressed once
– depressed again, clears AP OFF alert
(aural and visual)
50
ATA 22
QUICK
DISC/TCS
Touch Control Steering
pb allows to control temporary the
aircraft. AP arrows extinguish.
In basic mode, attitude limits < ± 15°
and bank angle limits < ± 35°
E. Automatic flight control system
2. FMA
ATA 22
2
1
3
5
4
6
PITCH HOLD
ALT SEL
CHECK NAV SRC
ROLL HOLD LO
ICING
DGD PERF
VOR
RETRIM ROLL R WING DN CAT1
1
9
2
Mode change
BANK ANGLE
Description
HDG HOLD
‘’LO‘’ or ’‘ ‘’
HDG HOLD MODE
(BASIC MODE)
ROLL HOLD
ROLL HOLD
‘’LO‘’ or ’‘ ‘’
ROLL HOLD MODE
(BASIC MODE)
WING LVL
WING LVL
‘’LO‘’ or ’‘ ‘’
WING LVL MODE
(BASIC MODE)
HDG SEL
HDG SEL
‘’LO‘’ or ’‘ ‘’
HDG SEL
(UPPER MODE)
2
ARM
Mode change +
CAPTURE
VOR
VOR 9
3
+7s
VOR 9
HOLD
VOR
BANK ANGLE
Description
‘’LO‘’ or ’‘ ‘’
NAV MODE ASSOCIATED WITH
A VOR (UPPER MODE)
LOC
LOC 9
LOC 9
LOC
‘’LO‘’ or ’‘ ‘’
NAV MODE ASSOCIATED WITH
A LOC (UPPER MODE)
APP MODE ASSOCIATED WITH
AN ILS (COMMON UPPER
MODE)
BC
BC 9
BC 9
BC
‘’LO‘’ or ’‘ ‘’
BC --> BACK COURSE OF THE
LOC (UPPER MODE)
BC * LNAV ‘’LO‘’ or ’‘ ‘’
NAV MODE ASSOCIATED WITH
A FMS (UPPER MODE)
LNAV
BC
LNAV
BC *
10
3
HOLD
HDG HOLD
1
8
AP FD DUAL
SPD HLD TCS
FD SINGLE CH
13
ARM
7
51
S y s t e m s 4 2/72 - 6 0 0
4
5
ARM
Mode change
+7s
PITCH HOLD
PITCH HOLD
VOR
IAS
IAS
IAS MODE
(UPPER MODE)
VOR
VS
VS
VS MODE
(UPPER MODE)
4
5
Mode change + CAPTURE
+7s
HOLD
ALT SEL
ALT 9
ALT 9
ALT
ALT MODE
(UPPER MODE)
GS
GS 9
GS9
GS
APP MODE ASSOCIATED WITH AN ILS
(COMMON UPPER MODE)
1
2
Mode change
HDG HOLD
LOC
PITCH HOLD MODE
(BASIC MODE)
VOR
ARM
ARM
Description
LOC9
4
+7s
HOLD
HDG HOLD
LOC9
Item
LOC
5
ARM
Mode change
0
GA
GS
GS9
Display
Description
+7s
HOLD
GA
GS9
GA MODE COMMON MODE
GS
Description
AP
ENGAGEMENT OF THE AP/YD ON THE
FGCP (W AP X AND W YD X)
YD
ENGAGEMENT OF THE YD ON THE FGCP
(W YD X)
FD
FLIGHT DIRECTOR COMMAND BARS
DISPLAYED ON THE PFD
6
7
COUPLING ON CAPT SIDE WITH THE CPL
P/B ON THE FGCP (W CPL)
COUPLING ON F/O SIDE WITH THE CPL P/B
ON THE FGCP (CPL X)
8
DUAL
DUAL COUPLING IN CAT 2 APPROACH
(W CPL X)
9
SPD HLD
SPEED HOLD IN PROVISION FOR CAT 3
10
TCS
ACTIVATION OF THE TCS PUSH BUTTON
CAT 1
ILS CAT 1 APPROACH
CAT 2
ILS CAT 2 APPROACH
13
52
Description
APP MODE COMMON MODE
E. Automatic flight control system
16
15
ROLL HOLD LO
ICING
DGD PERF
VOR
RETRIM ROLL R WING DN CAT1
PITCH HOLD
ALT SEL
CHECK NAV SRC
14
12
AP FD DUAL
SPD HLD TCS
FD SINGLE CH
11
11 AP/YD disengagement, approach category retrogression, AFCS internal failure.
Message
AP DISENG
Message + 7s
Aural alert
AP DISENG
AP/YD DISENG
AP/YD DISENG
YD DISENG
AP/YD DISENG
YD DISENG
AP/YD DISENG
AP/YD INVALID
YD DISENG
AP INVALID
AP/YD DISENG
AP INHIBIT
YD DISENG
YD INHIBIT
Cavalry Charge
Display logic
Comments
Red message, reverse
The AP/YD can be disengaged either
video flashing. Reset by the
automatically or manually
Quick Disconnect P/B
Amber message, reverse
The AP/YD can be disengaged either
video flashing. Reset by the
automatically or manually
Quick Disconnect P/B
Amber message, reverse
video flashing.
When an AFCS Internal failure inhibits AP/YD or
YD engagement
AP/YD DISENG
Yellow message, steady for
7 seconds
When AP or YD engagement are attempted and
an AFCS External failure or condition inhibits AP
engagement
SPD HLD INHIBIT
YD INHIBIT
YD DISENG
AP/YD DISENG
Yellow message, steady for
7 seconds
When speed hold engagement are attempted
and an AFCS External failure or condition inhibits
speed hold engagement
CHECK SPD HLD
YD INHIBIT
CHECK SPD HLD
AP/YD DISENG
Amber message, reverse
video flashing
When speed hold is unable to maintain target
speed
FD SINGLE CH
YD INHIBIT
FD SINGLE CH
AP/YD DISENG
Amber message, reverse
video flashing for 7
seconds, then steady until
failure is cleared
When one FD channel is lost
Amber permanent steady
message
When “single AHRS” and /or “single ADC”
configuration is active. After an AHRS or ADC
failure, the “single AHRS” and/or “single ADC”
configuration is selected on the switching
control panel
FD SINGLE SRC
YD INHIBIT
FD SINGLE SRC
AP/YD DISENG
CAT 2 INVALID
YD INHIBIT
FD SINGLE SRC
AP/YD DISENG
Triple clicks
Amber message, reverse
video flashing for 7
seconds, then disappears
Loss of CAT2 valid requirements during a CAT2
approach
CAT 3 INVALID
YD INHIBIT
FD SINGLE SRC
AP/YD DISENG
Triple clicks
Amber message, reverse
video flashing for 7
seconds, then disappears
Loss of CAT3 valid requirements during a CAT3
approach
53
S y s t e m s 4 2/72 - 6 0 0
12 Unexpected mode change, or problem in navigation parameters
Message flashing
CHECK NAV SRC
CHECK NAV SRC
CHECK T/O SPEED
Message + 7s
PITCH MISTRIM
CHECK NAV SRC
CHECK T/O SPEED
ADC INVALID
CHECK T/O SPEED
ATT INVALID
CHECK T/O SPEED
HDG INVALID
CHECK T/O SPEED
NAV INVALID
CHECK T/O SPEED
SPD AUTO INOP
SPD AUTO INOP
EXCESS DEV
ALT OFF
FD MODE CHG
CHECK T/O SPEE
CHECK T/O SPEED
EXCESS DEV
EXCESS DEV
FD MODE CHG
Aural alert
Display logic
Yellow message flashing for
7 seconds then disappears
Amber message, reverse
video flashing for
7 seconds, then steady until
failure is cleared by trying to
engage another FD mode,
or by pressing STBY pb
Amber message, reverse
video flashing for
7 seconds, then steady
Comments
If the crew try to engage a NAV mode where as the wrong nav
source is selected, or if the navigation source is lost
– If an armed or engaged NAV mod dropped off following a nav
source change
– If a VOR/LOC nav frequency change induces the current mode
loss
– In case of coupling change
If VCP lcing selection disagrees with the actual icing conditions
– In case of ADC data miscomparison, the AP/YD is disengaged
(disengagement only for discrepancy on CAS and TAS). After
clearing the AP/YD DISENG warning, the FMA displays ADC
Yellow message, flashing for
INVALID, associated with CHECK ALT or CHECK IAS on the PFD
7 seconds, then disappears
– Or in case of loss of ADC redundant sensor indicated by a
flag, the AP/YD is disengaged. After clearing the AP/YD DISENG
warning, the FMA displays ADC INVALID
– In case of AHRS data miscomparison, the AP/YD is disengaged
(disengagement only for discrepancy on attitude parameter).
After clearing the AP/YD DISENG warning, the FMA displays
Yellow message, flashing for ATT INVALID, associated with CHECK ATT on PFD if Roll or Pitch
7 seconds, then disappears angles are not coherent
– Or in case of loss of AHRS redundant sensor indicated by a
flag, the AP/YD is disengaged. After clearing the AP/YD DISENG
warning, the FMA displays ATT INVALID
– In case of AHRS data miscomparison, the FMA displays HDG
Yellow message, flashing for INVALID, associated with CHECK HDG on the PFD & ND, if
7 seconds, then disappears magnetic headings are not coherent (No AP/YD disengagement)
– Or in case of loss of AHRS redundant sensor indicated by a flag
Yellow message, flashing for
In case of loss of NAV redundant sensor indicated by a flag
7 seconds, then disappears
If AUTO is selected with the ”AUTO/MAN” SEL P/B and the speed
target from both FMS is not valid. The AUTO speed mode is
Amber message, reverse
not available and the speed is automatically switched to MAN
video flashing for
7 seconds, then disappears (Cyan Speed Target Bug). The Speed Target Bug is automatically
synchronized to the current value of A/C speed
Yellow message, flashing for When the ICP AUTO/MAN push-button is pressed while man is
7 seconds, then disappears selected and IAS target from the selected FMS is invalid
Red message, reverse video
flashing for 7 seconds, then
steady amber
Amber message, reverse
video flashing for
7 seconds, then disappears
Amber message, reverse
video flashing for 7 seconds,
then steady until failure is
cleared by changing AHRS
source selection, or by
selecting another FD mode,
or by pressing STBY P/B
Excessive deviation on the GS or the LOC. The message on the
FMA is associated with the GS or the LOC deviation scale flashing
amber to indicate a flight path excusion
During Altitude Capture
– When the selected altitude is changed (transition to basic pitch)
– When baro correction is changed (transition to basic pitch)
When an AHRS failure (ATT INVALID
or HDG INVALID) leads to the FD mode cancellation
STEEP APP
EXCESS DEV
Green message steady
When steep approach is selected
AFCS TEST
EXCESS DEV
Amber flashing
During the AFCS test (maintenance opération)
54
E. Automatic flight control system
14 Trim status
Message
Message + 7s
AP PITCH TRIM FAIL
AP PITCH TRIM FAIL
PITCH MISTRIM
PITCH MISTRIM
Aural alert
Display logic
Comments
Displayed when the AFCS is not able
to command the pitch trim and the AP is
engaged
When the pitch servo motor reaches
a torque value threshold
RETRIM ROLL R WING DN RETRIM ROLL R WING DN
RETRIM ROLL L WING DN RETRIM ROLL L WING DN
NIL
Amber message, reverse
video flashing 7 seconds,
then steady
When the aileron servo motor reaches
a first torque value threshold
AILERON MISTRIM
AILERON MISTRIM
When the aileron servo motor reaches
a second torque value threshold
AP YAW TRIM FAIL
AP YAW TRIM FAIL
Displayed when the AFCS is not able to
command the yaw autotrim
RUDDER MISTRIM
RUDDER MISTRIM
When the rudder servo motor reaches
a second torque value threshold
15 Icing message (refer to chapter ice and rain protection)
16 APM message (refer to chapter ice and rain protection)
When both FD channel are lost. The FMA is black. The AFCS FAIL is the only message displayed
AFCS FAIL
55
S y s t e m s 4 2/72 - 6 0 0
3. FGCP (Flight Guidance and Control Panel)
NAV SOURCE Selector CAPT side
Select the NAV source for CAPT EHSI
and/or ND (FMS1, VOR/ILS1, VOR/
ILS2, FMS2)
VS mode
to use FD with a desired vertical
speed
IAS mode
to use FD with a target indicated airspeed.
(Cyan speed bug: MAN on ICP)
(Magenta speed bug: AUTO on ICP)
NAV mode
to use FD with VOR
and LNAV course
HDG mode
to use FD with
HDG SEL
ATA 22
AP pb
engages autopilot and yaw damper
and disengages only autopilot
NAV SOURCE Selector F/O side
Select the NAV source for F/O
EHSI and/or ND (FMS1, VOR/
ILS1, VOR/ILS2, FMS2)
CRS 1 knob
selects course
on CAPT EHSI
and/or ND
FD bars
P/B to set
ON/OFF
CRS 2 knob
selects course
on F/O EHSI
and/or ND
HDG knob
selects HDG bug on both
EHSI and/or ND. Pushing
on the knob, synchronize
the heading to the actual
one.
APP mode
to use FD with ILS information course
(lateral and vertical):
– lateral (LOC)
– vertical (GS)
BC mode
to use FD with localizer in back course
Pitch wheel
to adjust VS or
pitch attitude in
basic mode
ALT mode
to use FD with a desired
altitude
FD bars
P/B to set ON/OFF
YD pb
engages yaw damper and disengages
yaw damper and autopilot if engaged
CPL pb
permit to couple AP/FD on CAPT or F/O side.
Dual coupling for CAT 2
STBY pb
cancels all FD upper modes (armed and captured
and active modes) and returns in basic modes.
4. ICP (Index Control Panel)
Speed target selection
Selection of the speed bug
between:
– AUTO: Speed bug managed
by the FMS (Magenta)
– MAN: Speed bug set manually
by the speed knob (Cyan)
56
ALT knob
controls the preselected
altitude on PFD
ATA 22,31
Speed knob
Used to set the speed bug
In MAN mode
F. Communications
FCOM 1.05
57
S y s t e m s 4 2/72 - 6 0 0
1. Schematic
ATA 23
The communication system provides communication between:
– aircraft and ground stations
– cockpit crew stations
– cabin attendant station
– ground crew stations
CAPT SIDE
oxy mask mike
hand mike
boom set
head set
PTT switch
nose wheel steering
control PTT
– loudspeaker
– loudspeaker audio level
– audio control panel
COM SYSTEM
–
–
–
–
–
–
NAVIGATION SYSTEM
COCKPIT VOICE
RECORDER
CABIN ATTENDANT
OBSERVER SIDE
– oxy mask
– boom set
– head set
– PTT switch
REMOTE
CONTROL
AUDIO
UNIT
GROUND CREW
PASSENGER
F/O SIDE
– oxy mask mike
– hand mike
– boom set
– head set
– PTT switch
– loudspeaker
– loudspeaker audio level
– audio control panel
PUBLIC ADDRESS SYSTEM
2. PTT selector and NOSE WHEEL
STEERING CONTROL SW
PTT selector
interphone: forward position
neutral: center position
radio: backward position
58
GPWS
TCAS
ATA23
NOSE WHEEL STEERING
CONTROL switch
When depressed, BOOM SET
or OXY mike is connected for
transmission
F. Communications
3. Audio control panel
Transmission keys
Only one key can be engaged at
a time. It illuminates white when
selected
VOICE ONLY key
When depressed, it inhibits NAV receivers
station identification. Light illuminates
amber when selected.
Volume control knob
to set volume from associated
communication or navigation
facilities
ATA 23
INT/RAD selector
Provides selection of transmission
mode when using OXY MASK or
BOOM SET mike
INT: hot mike position. Interphone
is always operative between crew
stations. Other transmissions require
to select a transmission key and use
a PTT pb
NEUTRAL: Interphone is inoperative.
Other transmissions require selecting
a transmission key and using a PTT
pushbutton.
RAD: This position is required
to automatically connect for
transmissions BOOM SET and OXY
MASK mikes without using a PTT pb,
when released the selector is springloaded to NEUTRAL.
4. VHF control
ATA 23
VCP
MCDU
MCP
MCP and MCDU allow to tune VHF frequencies
MCDU allows to:
– set the squelch (SQL - ON/OFF)
– set directly the EMER frequency (121.5 Mhz)
VHF 1 Frequency Display
Selection Push Button
To change the selection cursor
To VHF
Rotary selector
To tune the VHF frequency
59
S y s t e m s 4 2/72 - 6 0 0
5. AUDIO SEL pb
FAULT
illuminates amber and the FWS
is activated when an associated
RCAU processing board failure or
power loss is detected
ATA 23
AUDIO SEL
Controls functioning of associated
RCAU processing board.
NORM: RCAU functions normally
ALTN
affected crew station is connected
directly to VHF 1 for CAPT station
or VHF 2 for F/O station.
Volume is adjusted by affected
loudspeaker volume control
6. Loudspeaker volume knobs
ATA 23
LOUDSPEAKER
Communication reception.
In case of aural alert:
– normal volume is always available
regardless of knobs position.
– during any transmission the volume of
both loudspeakers is muted
7. TCAS control box
ATA 34
VCP
MCDU
MCP
MCP and MCDU allow to set between
AUTO, TA ONLY and STBY
MCDU allows to set between ABV, NORM,
BLW on the displays.
60
F. Communications
8. EMER LOC XMTR panel
AUTO TEST RST
is used in case of undue alert or to
test the emergency beacon. two
cases are possible for the test
– network X MIT ALERT illuminates
amber during 2’’
– failure XMIT ALERT lt flashes
during 15 seconds
9. Cabin attendant handset
ATA 23
Switch
AUTO transmission is made
automatically on 121.5 MHz,
243 MHz and 406 MHz when
deceleration exceeds 5 g
MAN allows commanded
operation or test
ATA 23
Cabin attendant handset
PA: public adress to make an
annoncement to passengers
INT: internal communications with
crew
EMER: emergency call
10. Handmike and handset
ATA 23
11. CALLS panel
ATA 23
EMER
illuminates in case of
emergency call from cabin
12. Head set / boom set /
hand mike panels
CALLS
ATTND to call cabin from cockpit.
One time for a normal call
three times for an emergency call
MECH to call the ground crew from cockpit
A horn is generated
In case of cabin crew or ground crew call,
depress RESET to cancel both associated
visual and aural alerts
ATA 23
Head set / boom set panel /
hand mike panels
allows connection of a boom set,
a head set and a hand mike
61
S y s t e m s 4 2/72 - 6 0 0
13. ATC control
ATA 23
VCP
MCDU
MCP and MCDU allow:
– to set the transponder
code
– to set the mode (ON/
STBY)
– to set the ALT mode
(ON/OFF)
– to set XPDR 1 or 2
MCP
MCDU allows to:
– set the flight
identification (FLT ID)
– set directly the EMER
code (7700)
14. CVR panel
TEST pb
when depressed and held, the test circuit
is activated
– the pointer moves to a location between
graduations 8 and 10
– if a headset is plugged into the jack, the
600 HZ signal is heard
COCKPIT VOICE RECORDER
Monitor indicator for test only.
Movement of pointer in white band
indicates all channels are operative
ERASE pb
provides fast erasure of recordings when
the landing gear shock absorbers are
compressed and parking brake is set
(depress for 2 sec. to completly erase)
During erasure, a 400Hz audio signal can
be heard in the headset
HEADSET jack
when headset is plugged into the
jack:
– cockpit sounds picked up by the
microphone are audible
– erase tone is audible when
ERASE pb is depressed
MICROPHONE
picks up cockpit conversations and alert
sounds
15. Crew oxygen mask
A micro phone is incorporated
inside the crew oxygen mask
62
ATA 23
ATA 23
G. Electrical systems
FCOM 1.06
63
S y s t e m s 4 2/72 - 6 0 0
1. Sources of power
ATA 24
Three type of currents are available: Direct current (DC)
Alternating current with constant frequency (AC)
Alternating current with variable frequency (ACW)
Two DC starter/generators
<45% NH starter mode
>61,5% NH generator mode
Two batteries
DC power 28 VDC
Two inverters
AC power
VAC 26 V
VAC 115 V
ACW power
115V/200V
TRU (Emergency
supply)
DC power 28 VDC
DC GPU
Two AC wild frequency
alternators
minimum NP 66%
AC GPU
64
The TRU provides power to the emergency loads in case of dual DC generators
loss. It is supplied by the ACW bus 2.
G. Electrical systems
The DC Starter Generator is driven by the HP spool throught the Accessorry Gear Box (AGB)
– From 0 to 45% NH as a
Starter
– Above 61.5% as a
Generator
The ACW Generator is driven by the Reduction Gear Box, and is available when NP > 66%
DC Starter
Generator
Accessory
gear box
ACW
Generator
Reduction
gear box
In Hotel Mode or with the propeller feathered, there is no ACW.
When the propeller is unfeathered (CL in AUTO /100% OVRD), The NP is maintained at a minimum of 70,8%, in order to
have ACW (minimum 66%)
DC Starter
Generator
Accessory
gear box
ACW
Generator
Reduction
gear box
HOTEL MODE OR PROPELLER FEATHERED
65
S y s t e m s 4 2/72 - 6 0 0
2. DC-AC schematic
ATA 24
2.1. Normal supply: On ground with battery only
AC BUS 1
AC BUS 2
AC STBY BUS
BAT
INV 1
INV 2
ON
TRU
DC STBY BUS
DC
EMER
BUS
EMER
BAT CHG
DC
ESS
BUS
HOT
EMER
BAT
BUS
HOT
MAIN
BAT
BUS
MAIN
BAT CHG
DC/AC overhead panel
UTLY
BUS 1
DC BUS 1
UTLY
BUS 2
DC BUS 2
BTC
DC SVCE BUS
DC GEN 1
EXT. PWR
)$8/7
$9$,/
GND HDLG
BUS
DC GEN 2
)$8/7
The GOUND HANDLING BUS is supplied only on
ground, by three different ways:
– BAT OFF or BAT ON with the EXT PWR not available,
the GND HDLG BUS is supplied by the HOT MAIN BAT
BUS for ground servicing only when:
- The refueling panel is open
- The cargo door control panel is open
- The passenger door is open
– BAT OFF or BAT ON with the EXT PWR available but
not ON, the GND HDLG BUS is supplied from the EXT
PWR via the DC SVCE BUS
– BAT ON with EXT PWR ON or with one GEN on line,
the GND HDLG BUS is supplied by the from the DC
BUS 1 via DC SVCE BUS.
NOTE: The GND HDLG BUS is disconnected when airborne.
ELEC SD page: on battery only
66
ELEC SD page: on battery + GPU available
G. Electrical systems
2.2. Normal Supply: On ground with external power
AC BUS 1
AC BUS 2
AC STBY BUS
BAT
INV 1
INV 2
ON
TRU
DC STBY BUS
DC
EMER
BUS
EMER
BAT CHG
DC
ESS
BUS
HOT
EMER
BAT
BUS
HOT
MAIN
BAT
BUS
UTLY
BUS 1
DC BUS 1
UTLY
BUS 2
MAIN
BAT CHG
DC BUS 2
DC/AC overhead panel
BTC
DC SVCE BUS
DC GEN 1
)$8/7
GND HDLG
BUS
EXT. PWR
DC GEN 2
$9$,/
)$8/7
21
The BTC is closed and the GPU supplies all the DC and AC busses.
Even if the GEN are available, the GPU has always priority.
ELEC SD page
67
S y s t e m s 4 2/72 - 6 0 0
2.3. Hotel mode or DC GEN 1 FAULT
AC BUS 1
AC BUS 2
AC STBY BUS
BAT
INV 1
INV 2
ON
TRU
DC STBY BUS
DC
EMER
BUS
EMER
BAT CHG
DC
ESS
BUS
HOT
EMER
BAT
BUS
HOT
MAIN
BAT
BUS
UTLY
BUS 1
DC BUS 1
UTLY
BUS 2
MAIN
BAT CHG
DC BUS 2
DC/AC overhead panel
BTC
DC SVCE BUS
DC GEN 1
EXT. PWR
DC GEN 2
)$8/7
GND HDLG
BUS
The BTC is closed and the GEN 2 supplies all the DC and AC busses.
In hotel mode the GND HDLG BUS is supplied by the DC BUS 1 through
the DC SVCE BUS.
ELEC SD page
68
G. Electrical systems
2.4. Normal supply: with two generators on line
AC BUS 1
AC BUS 2
AC STBY BUS
BAT
INV 1
INV 2
ON
TRU
DC STBY BUS
DC
EMER
BUS
EMER
BAT CHG
DC
ESS
BUS
HOT
EMER
BAT
BUS
HOT
MAIN
BAT
BUS
UTLY
BUS 1
DC BUS 1
UTLY
BUS 2
MAIN
BAT CHG
DC BUS 2
DC/AC overhead panel
BTC
DC SVCE BUS
DC GEN 1
EXT. PWR
DC GEN 2
GND HDLG
BUS
The BTC is opened and each GEN supply its respective busses.
On ground the GND HDLG BUS is supplied by the DC BUS 1 through
the DC SVCE BUS, and disconnected when airborne.
ELEC SD page
69
S y s t e m s 4 2/72 - 6 0 0
2.5. Emergency supply: In dual DC GEN LOSS with the
battery toggle switch on OVRD
AC BUS 1
AC BUS 2
AC STBY BUS
BAT
INV 1
INV 2
OVRD
The BAT toggle switch has to be selected to
OVRD.
The OVRD position ensures that busses are
supplied by their respective battery by overriding
all protections. This position is protected by
a switch guard.
TRU
DC STBY BUS
DC
EMER
BUS
EMER
BAT CHG
DC
ESS
BUS
HOT
EMER
BAT
BUS
HOT
MAIN
BAT
BUS
UTLY
BUS 1
DC BUS 1
UTLY
BUS 2
MAIN
BAT CHG
DC BUS 2
BTC
DC SVCE BUS
DC GEN 1
EXT. PWR
)$8/7
)$8/7
DC/AC overhead panel
GND HDLG
BUS
ELEC SD page
70
DC GEN 2
G. Electrical systems
2.6. Emergency supply: In dual DC GEN LOSS with the
battery toggle switch on OVRD and second OVRD selected
AC BUS 1
AC BUS 2
AC STBY BUS
BAT
INV 1
INV 2
OVRD
After a Dual DC GEN loss, the UNDV is triggered
when the DC STBY BUS <19,5 V.
Then, by pushing on the OVRD the DC and AC
STBY BUS are transfered from the HOT MAIN
BAT BUS to the HOT EMER BAT BUS.
When passing to OVRD, the DC STBY BUS
voltage is recovered and the UND/V extinguishes.
TRU
DC STBY BUS
DC
EMER
BUS
EMER
BAT CHG
DC
ESS
BUS
HOT
EMER
BAT
BUS
HOT
MAIN
BAT
BUS
UTLY
BUS 1
DC BUS 1
UTLY
BUS 2
MAIN
BAT CHG
DC BUS 2
BTC
DC SVCE BUS
DC GEN 1
EXT. PWR
DC GEN 2
)$8/7
)$8/7
DC/AC overhead panel
GND HDLG
BUS
ELEC SD page:
Dual DC GEN Loss with first
and second override (DC
STBY BUS)
71
S y s t e m s 4 2/72 - 6 0 0
2.7. Emergency supply: In dual DC GEN LOSS with TRU
AC BUS 1
AC BUS 2
AC STBY BUS
BAT
INV 1
INV 2
OVRD
TRU
ON
DC STBY BUS
DC
EMER
BUS
EMER
BAT CHG
DC
ESS
BUS
HOT
EMER
BAT
BUS
HOT
MAIN
BAT
BUS
UTLY
BUS 1
DC BUS 1
UTLY
BUS 2
MAIN
BAT CHG
DC BUS 2
DC/AC overhead panel
BTC
DC SVCE BUS
DC GEN 1
EXT. PWR
)$8/7
DC GEN 2
)$8/7
GND HDLG
BUS
The TRU connected to the ACW BUS 2 supplies DC EMER BUS,
DC ESS BUS, DC&AC STBY BUSSES.
ELEC SD page
72
G. Electrical systems
3. DC-AC panel
UNDV
DC STBY < 19.5 V.
ELEC STBY UNDV on FWS
ATA 24
BUS OFF
Associated bus deenergized.
ELEC AC 1 (2) on FWS
INV FAULT
Under/over voltage at INV output.
(INV failure or supply loss). AutoXfer of all AC busses to remaining
inverter. ELEC INV 1 (2) on FWS
OVRD
Xfer/stby busses from HOT MAIN
to HOT EMER BAT BUS
Arrows
Emergency supply indicators
(respective battery discharging)
OVRD
Insures basic mode operation by
overriding all other protections
TRU
ON PB in. TRU is connected to
ACW BUS 2. Arrow illuminates
green when DC EMER, DC STBY,
INV 1, AC STBY and DC ESS BUS
are supplied by TRU
ON
Basic mode: STBY busses
supplied by HOT MAIN BAT BUS.
Ext or gen power: DC STBY bus
transferred to HOT EMER BAT BUS
AC STBY BUS to DC BUS 1
EMER BAT CHG
FAULT: Overheat detected by
MFC or failure of contactor. ELEC
BAT CHG on FWS
Contactor auto opens if: thermal
runaway/bus voltage <25 V. Start
sequence: Bat sw on OVRD
OFF
ESS BUS, DC STBY BUS + INV 1 are
isolated from HOT MAIN BAT BUS
DC EMER BUS is isolated from
HOT EMER BAT BUS
DC BUS OFF
Respective bus not supplied.
ELEC DC 1 (2) on FWS
BTC
The BPCU controls BTC operation.
Ext power, hotel mode or single
gen operation, BTC is closed
(green flow bar)
DC SVCE/UTLY BUS
DC SVCE supplies power in flight
and on ground during airplane
servicing operations.
UTLY BUSSES supply nonessential loads
SHED: In automatic shedding
One of the DC SVCE/UTLY 1 and
2 busses is shed by the BPCU.
SHED: In manual shedding (P/B
selected OFF)
all DC SVCE/UTLY 1 and 2 busses
are shed
ISOL
BTC and BTR opened (released
out)
DC GEN 1/2
FAULT: protection trip by GCU;
Auto reset if underspeed. BTC
auto closes ELEC DC 1 ( 2) on
FWS
DC GEN 1/2
Generator FAULT Lt.
Extinguishes above 61.5% NH if
GEN is operating normally
AVAIL
GPU has been checked by BPCU
for over/under voltage, over
current and polarity
X START FAIL
Opposite generator has not come
on line to assist start at 10 % NH
ELEC X START on FWS
EXT PWR
AVAIL + ON: GPU has prioity on
both generators
73
S y s t e m s 4 2/72 - 6 0 0
4. Elec SD
9
10
11
8
4
1
74
6
5
2
7
3
G. Electrical systems
Item
Display
Description
Item
DC GEN P/B ON & NORMAL
OPERATION
DC GEN X
Display
TRU
TRU
ACW
1
DC GEN P/B OFF
TRU
8
ACW
DC GEN FAULT
TRU
ACW
EXT PWR
AVAIL
ON
EXT PWR
AVAIL
ON
EXTERNAL POWER AVAILABLE
AND SELECTED (ON)
TRU
ACW
EXT PWR
BTC
BTC
DC BUS X
ON
OFF
TRU P/B OFF WITH ACW BUS 2 ON
AND TRU SUPPLY AVAILABLE
GREEN LINE WITH FULL ARROW
COMING FROM “ACW” WHITE LABEL
OVRD UNDV
DC STBY BUS
DC STBY BUS VALID VOLTAGE AND
>18V WITH OVRD UND/V PB IN
NORM POS.
OVRD UNDV
DC STBY BUS
DC STBY BUS VALID VOLTAGE AND
>18V WITH OVRD UND/V PB IN
OVRD POS.
DC BUS ON
OVRD UNDV
DC STBY BUS
DC STBY BUS INVALID VOLTAGE
AND/OR <18V
DC BUS OFF
ESS BUS
DC ESS BUS 1 (OR 2) VALID
VOLTAGE AND >18V
ESS BUS
DC ESS BUS 1 (OR 2) INVALID
VOLTAGE AND <18V
10
4
DC BUS X
TRU P/B ON WITH ACW BUS OFF
EMER BUS INVALID VOLTAGE AND/
OR <18V
ISOL CONDITION
ISOL
7
TRU P/B ON WITH ACW BUS 2 ON
AND TRU SUPPLY AVAILABLE
GREEN LINE WITH FULL ARROW
COMING FROM “ACW” WHITE LABEL
EMER BUS
9
3
11
UTLY BUS X
DC UTLY BUS ON
UTLY BUS X
DC UTLY BUS OFF
UTLY BUS X
DC UTLY BUS FAULT
SHED
TRU P/B ON WITH ACW BUS 2 ON
AND TRU SUPPLY NOT AVAILABLE
GREEN LINE WITH FULL ARROW
COMING FROM “ACW” WHITE LABEL
EMER BUS VALID VOLTAGE AND
>18V
NORM CONDITION
ISOL
6
TRU P/B OFF WITH ACW BUS 2 ON
AND TRU SUPPLY NOT AVAILABLE
GREEN LINE WITH FULL ARROW
COMING FROM “ACW” WHITE LABEL
EMER BUS
EXTERNAL POWER NOT
AVAILABLE BUT SELECTED
ON
ON
5
TRU P/B OFF WITH ACW BUS 2
OFF
EXTERNAL POWER AVAILABLE
TRU
2
Description
DC UTILITY BUS SHED MESSAGE
SVCE BUS
DC SVCE BUS ON
OFF
SVCE BUS
DC SVCE BUS OFF
OFF
SVCE BUS
DC SVCE BUS FAULT
75
S y s t e m s 4 2/72 - 6 0 0
21
22
10
23
19
15
16
12
18
17
20
76
14
13
20
G. Electrical systems
Item
Display
Description
HOT BUS
DC MAIN BUS VALID VOLTAGE AND
>18V
MAIN BAT
28 V
HOT BUS
12
MAIN BAT
28 V
HOT BUS
MAIN BAT
28 V
DC MAIN BUS VALID VOLTAGE AND
>18V WITH BAT TOGGLE P/B SW
IN OVRD POSITION
Item
Display
HOT BUS
EMER BAT
28 V
HOT BUS
16
EMER BAT
28 V
HOT BUS
DC MAIN BUS INVALID VOLTAGE
OR <18V
EMER BAT
28 V
EMER BAT
XX V
13
DC MAIN BAT VALID VOLTAGE AND
>18V
XX V
DC MAIN BAT VALID VOLTAGE AND
<18V
-- V
DC MAIN BAT INVALID VOLTAGE
XX V
EMER BAT
XX V
17
-- V
OFF
OFF
CHG
OFF
14
CHG
OFF
CHG
FAULT
15
MAIN BAT CHG P/B SW RELEASED
(CHARGE CONTACTOR OPENED)
MAIN BAT CHG P/B SW PRESSED
IN (CHARGE CONTACTOR CLOSED)
WITH DC BUS 2 NOT SUPPLYING
THE MAIN BATTERY OR WITH
TOGGLE P/B SW ON OVRD
POSITION, OR CAUTION ON MAIN
DC BAT
CHG
OFF
18
MAIN BAT CHG P/B SW PRESSED
IN (CHARGE CONTACTOR CLOSED)
WITH DC BUS 2 SUPPLYING THE
MAIN BATTERY OR WITH TOGGLE
P/B SW NOT ON OVRD POSITION
CHG
MAIN BAT CHG P/B SW PRESSED
IN (CHARGE CONTACTOR CLOSED)
WITH DC MAIN DC BAT IN FAULT
CHG
IF ABNORMAL DISCHARGE OF THE
MAIN BATTERY
DC EMER BUS VALID VOLTAGE
AND >18V
DC EMER BUS VALID VOLTAGE
AND >18V WITH BAT TOGGLE
P/B SW IN OVRD POSITION
DC EMER BAT INVALID VOLTAGE
OR <18V
DC EMER BAT VALID VOLTAGE
AND >18V
DC EMER BAT VALID VOLTAGE
AND <18V
EMER BAT
CHG
CHG
Description
OFF
FAULT
DC EMER BUS INVALID VOLTAGE
EMER BAT CHG P/B SW
RELEASED (CHARGE CONTACTOR
OPENED)
EMER BAT CHG P/B SW PRESSED
IN (CHARGE CONTACTOR CLOSED)
WITH DC BUS 1 NOT SUPPLYING
THE EMER BATTERY OR WITH
TOGGLE P/B SW ON OVRD
POSITION
EMER BAT CHG P/B SW PRESSED
IN (CHARGE CONTACTOR CLOSED)
WITH DC BUS 1 SUPPLYING
THE EMER BATTERY AND WITH
TOGGLE P/B SW NOT ON OVRD
POSITION, OR CAUTION ON EMER
DC BAT
EMER BAT CHG P/B SW PRESSED
IN (CHARGE CONTACTOR CLOSED)
WITH DC EMER BAT IN FAULT
IF ABNORMAL DISCHARGE OF THE
EMER BATTERY
19
20
BAT OVRD
IF TOGGLE SW IN OVRD POSITION
Item
Display
Description
AC BUS 1
OF
AC BUS ON
AC BUS X
OFF
AC BUS OFF
21
AC STBY BUS
AC STBY BUS ON
AC STBY BUS
AC STBY BUS OFF
22
INV X
FAULT
INVERTER NORMAL
FUNCTIONNING
INV X
FAULT
INVERTER FAULT
23
77
S y s t e m s 4 2/72 - 6 0 0
5. ACW schematic
ACW BUS 1
ACW BUS 2
ATA 24
TRU
SVCE BUS
ACW
GEN 1
ACW
GPU
ACW
GEN 2
NP=0
NP=0
ACW supplied by the External Power
– When the AC GPU is available (AVAIL) but not ON, the GPU supplies only the ACW
Service Bus, if the GND Service Bus switch, on the flight attendant panel, is ON.
– When the AC GPU is ON, the GPU supplies through the BTC, the ACW BUS 1, the ACW
BUS 2 and the ACW SVCE BUS.
– Even if one ACW generator is available, the GPU has always priority.
ACW BUS 1
ACW BUS 2
TRU
SVCE BUS
ACW
GEN 1
NP=0
ACW
GPU
ACW
GEN 2
NP=0 in hotel mode
NP<20% with prop feathered
ACW in Hotel mode or with the propeller feathered
NOTE: An ACW Generator is available if the NP is above 66%.
– When the right engine is running in hotel mode, the NP=0.
– When the engines are running but the propellers are feathered, the NP is bellow 20%
In both cases the ACW Busses are not supplied
78
G. Electrical systems
ACW BUS 1
ACW BUS 2
TRU
SVCE BUS
ACW
GEN 1
ACW
GPU
NP=0
ACW
GEN 2
NP=70.8%
The propeller unfeathered and one ACW GEN on line
On ground, when the propeller is unfeathered, the engine is running on fuel governing mode.
The fuel governing mode, maintain a minimum NP of 70.8%, in order to have the ACW
available (ACW GEN on line at 66%)
The ACW GEN supplies, the ACW BUS 2 and ACW BUS 1 through the BTC, but the SVCE
BUS is shed (one generator is not able to supply all the busses)
CAUTION: on ground in case of an EEC or PEC fault, the fuel governing mode is lost and the
ACW generator is not available (NP<66%)
ACW BUS 1
ACW BUS 2
TRU
SVCE BUS
ACW
GEN 1
NP=100%
ACW
GPU
ACW
GEN 2
NP=100%
Normal condition in flight
– The ACW GEN 1 supplies the ACW BUS 1 and the ACW SVCE BUS
– The ACW GEN 2 supplied the ACW BUS 2.
– The TRU is connected to the ACW BUS 2
79
S y s t e m s 4 2/72 - 6 0 0
ACW BUS 1
ACW BUS 2
TRU
SVCE BUS
ACW
GEN 1
ACW
GPU
NP=100%
ACW
GEN 2
NP=100%
One Generator Fault
When one generator is fault, the other one supplies the ACW BUS1 and the ACW BUS 2
through the BTC.
The SVCE BUS is automatically shed (one generator is not able to supply all the busses)
6. ACW panel
ATA 24
BTC (green flow bar)
Auto closure when either ACW
GEN drops off line
ACW BUS OFF
Associated bus not supplied.
ELEC ACW 1 (2) on FWS
ACW GEN 1 /2
FAULT: Auto reset in case of
under/over speed.
ACW SVCE BUS auto shed
if 1 GEN is out. ELEC ACW
GEN 1(2) on FWS
80
EXT PWR
AVAIL + ON GPU has priority over
both GEN
ACW GEN 2 and
ACW GEN 1
Min NP for ACW = 66 %. The
fuel governing mode maintains
a MIN NP of 70.8% to be
always above 66%.
The fuel governing mode is
cancelled with the propeller
feathered (No ACW)
G. Electrical systems
7. SD page
Item
1
6
5
2
3
1
4
Display
Description
Item
Display
ACW GEN1
ACW GEN ON
DC
ACW GEN1
OFF
ACW GEN OFF
DC
ACW GEN1
FAULT
ACW GEN FAULT
ACW BUS x
OFF
ACW BUS ON
ACW BUS x
OFF
ACW BUS OFF
BTC
ISOL
NORM CONDITION
BTC
ISOL
ISOL CONDITION
TRU P/B OFF WITH ACW BUS 2
OFF
TRU
TRU P/B OFF WITH ACW BUS 2 ON
AND TRU SUPPLY NOT AVAILABLE
TRU
TRU P/B ON WITH ACW BUS 2 ON
AND TRU SUPPLY NOT AVAILABLE
TRU
TRU P/B ON WITH ACW BUS 2 ON
AND TRU SUPPLY AVAILABLE
DC
2
TRU
DC
TRU
3
4
TRU
DC
5
EXTERNAL POWER AVAILABLE
EXT AC
AVAIL
ON
EXTERNAL POWER AVAILABLE
AND SELECTED ON
EXT AC
AVAIL
ON
EXTERNAL POWER NOT
AVAILABLE BUT SELECTED ON
TRU P/B ON WITH ACW BUS 2 OFF
TRU P/B OFF WITH ACW BUS 2 ON
AND TRU SUPPLY AVAILABLE
DC BUS 2
HYD AUX PUMP SUPPLYING,
DC BUS 2 ON
MAIN BAT
HYD AUX PUMP SUPPLYING,
DC BUS 2 OFF AND DC MAIN BAT
VOLTAGE >18V
6
EXT AC
AVAIL
ON
Description
81
S y s t e m s 4 2/72 - 6 0 0
8. Breaker panels
8.1. Overhead panel
82
ATA 24
G. Electrical systems
8.2. Electric rack behind F/O
83
H. Emergency equipment
FCOM 1.07
85
S y s t e m s 4 2/72 - 6 0 0
The aircraft is equipped with fire fighting, oxygen, first aid equipment and emergency lightning.
1. Emergency equipment situation
– halon
extinguisher
– crash axe
emergency
exit type III
life jackets
type I service
door
– oxygen bottle
– oxygen mask
– life jacket
– flash light
– flash light
– goggles
– oxygen
masks
halon
extinguisher
fire resistant
gloves
– hood
– goggles
– oxygen mask
– water
extinguisher
– flash light
– smoke hood
emergency exit
type III
– first aid kit
– bag containing
oxygen masks
smoke hood
2. Emergency lighting system
Emergency exit
signs
type I entry door
ATA 33
Emergency exit
signs
External
emergency lighting
Cabin general
illumination
External
emergency lighting
Emergency
exit sign
Emergency
exit sign
Floor proximity escape path marking
Emergency exit
signs
86
External
emergency lighting
Emergency exit
signs
H. Emergency equipment
3. First aid kit
ATA 25
contains bandages, burn dressings, small
adhesive dressings, antiseptic wound cleaner,
adhesive wound closures, disposable
resuscitation aid, wound dressings, large
and small, adhesive tape, safety pins and
scissors, simple analgesic, antiemetic, nasal
decongestant, first-aid handbook, splints,
suitable for upperand lower limbs, gastrointestinal antacid, anti-diarrhoel medication,
disposable gloves
4. Crash axe
ATA 25
Crash axe with pick and edge
Handle insulated up to 2000V to
open a door or a compartment
5. Megaphone
ATA 25
megaphone (72 only)
6. Flashing light
ATA 25
With batteries, morse code switch
7. Life jacket
ATA 25
With oral inflation tube, CO2
sparklets, inflation red toggle,
whistle, straps, battery, light
8. Escape rope
ATA 25
used to evacuate the cockpit
87
S y s t e m s 4 2/72 - 6 0 0
9. Gloves
ATA 25
To protect against heat
10. Water extinguisher
ATA 26
Water extinguisher
2 liters of water with an anti-ice
additive
discharge time: 30 to 40 ‘‘
11. Halon extinguisher
ATA 26
Halon extinguisher
1.2 kg of halon gas
discharge time: 8 to 10 ‘‘
12. Oxygen schematic
ATA 35
To flight
crew
members
Modules for 72/42- 600
Oxygen bottle
88
H. Emergency equipment
13. Oxygen panel and display
MAIN SUPPLY
pb in: crew supply only
ATA 35
PAX SUPPLY
ON 25% off the passengers
HP INDICATOR
oxygen bottle pressure.
Red arc 0 to 85 psi
Green arc 85 to 2025 psi
If below 1400 psi, use table
LO PR
supply below 50 psi. OXY on FWS
MAIN SUPPLY OFF
MAIN SUPPLY ON
PAX SUPPLY OFF
PRESSURE AVAILABLE
MAIN SUPPLY ON
PAX SUPPLY ON
PRESSURE AVAILABLE
MAIN SUPPLY ON
PAX SUPPLY OFF
LOW PRESSURE DETECTED
MAIN SUPPLY ON
PAX SUPPLY ON
LOW PRESSURE DETECTED
14. Cockpit crew oxygen mask
ATA 35
PRESS TO TEST AND RESET
permits a test of oxygen flow
without removing the mask from
the container. It is springloaded to
the reset position
BLINKER
displays a yellow cross when there
is oxygen flow and black when
there is none.
N/100% PUSH
rocker controls the selection of normal or 100% oxygen for mask delivery. It is locked in the 100% position by the unlock rocker
OXYGEN MASKS
quick donning inflatable harness
type
release clips: squeeze them to unlock the container doors
EMERGENCY
selector activates pressurization of
mask delivery flow when N/100%
rocker is at 100%
89
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15. Portable oxygen bottle
ATA 35
Portable oxygen bottle (green) with
pressure gauge and
re-charge valve
120 liters under pressure
(1800 psi)
duration: 30 min at 4 ltr/mn
– 1 bottle ––> 42
– 2 bottles ––> 72
16. Passenger oxygen mask
ATA 35
–12 Oxygen masks for 42
–19 Oxygen masks for 72
equipped with valves, bag and
elastic strap
17. Protective breathing equipment
Protective breathing equipment
(PBE)
to supply 15 min pure oxygen with
hood, visor, speaking diaphragm
and oronasal mask
– 2 PBE ––> 42
– 3 PBE ––> 72
90
PBE
stowage box
ATA 26
I. Fire protection
FCOM 1.08
91
S y s t e m s 4 2/72 - 6 0 0
The fire protection system provides detection, warning and extinguishing for each engine, cabin and lavatory.
1. Schematic
ATA 26
FIRE DETECTION
FIRE EXTINGUISHING SYSTEM
AND
/223$
Bottle N°1
Bottle N°2
(1*),5(
ENG 1
ENG 2
2. Avionics FWD and AFT smoke
detection
92
ATA 26
FORWARD CARGO SMOKE DETECTION
AFT CARGO OR LAVATORY SMOKE DETECTION
AVIONICS COMPARTMENT SMOKE DETECTION
AIR CAUTION / FAN FAILURE
I. Fire protection
3. Fire handle
SQUIB TEST
Electrical test of the squibs
ATA 26
LOOP
FAULT: change in resistance,
inhibits fire signal until turned off.
LOOP 1A (1B, 2A, 2B) on FWS
(DC emer)
AGENT 1
DISCH: Bottle depressurized.
Opposite agent DISCH light will
also illuminate on other fire panel.
Bottle located in the wing fairing of
the associated side
ENGINE FIRE HANDLE
Pulled on the respective engine:
– PROP: feather
– FUEL: LP valve closed
– AIR: BLEED and HP valve closed
– DEICING: deice and shutoff
valve closed
– ELEC : DC and ACW gen.
disconnected
– SQUIBS armed lts illumination
+ Hydraulic to prop brake closed
on engine 2
Agent 2 bottle located on the
opposite side
FIRE TEST
MW + CRC + ENG 1 FIRE on FWS
+ fire handle illuminated + FUEL
S/O light on CL (if out of FUEL S/O
position)
AGENT
SQUIB
armed when T handle pulled.
Discharges bottle.
(DC EMER/HOT MAIN BAT)
FAULT TEST
MC + SC + LOOP on FWS
Fault lights in A/B loop pb
OFF
takes respective loop out of
parallel circuit. Allows other loop to
activate fire signal alone.
4. EWD (Engine and Warning Display)
Engine Fire detected by two
loops. (Not detected if one loop
fault. Detection recovered when
the faulty loop is selected OFF)
LOOP
Engine fire loop FAULT. When a
loop FAULT. No detection of Engine
Fire (Detection recovered when the
faulty loop is selected OFF)
NAC OVHT
RH Nacelle Overheat >170°C
Alert on FWS
5. Condition levers fuel light
ATA 26
FUEL SO
Illuminates red in case of fire
signal from associated engine.
Extinguishes after CL is set at fuel
shut off position or if fire detection
signal stops
93
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6. Compartment smoke panel
ATA 26
NORM
one fan runs
FAULT: the fan is out of order
and illuminates amber + FWS is
activated
ALTN: The alternate fan runs,
ALTN light illuminates cyan
SMK TEST
Tests the smoke detectors
operation
Normal operation
Fan Fault associated with
AIR AFT DET FAN on FWS
DET FANS
ALTN DET FANS
Aft Fan Fault, selection
of the alternate FAN
On SD CABIN
7. SD cabin
Avionics smoke
Forward cargo
smoke
Aft cargo
compartment
smoke
Lavatory smoke
Aft compartment
& lavatory
Detection fans
94
J. Flight control
FCOM 1.09
95
S y s t e m s 4 2/72 - 6 0 0
The elevators, ailerons and rudder are mechanically actuated
The spoilers and flaps are hydraulically
actuated.
1. Roll schematic
ATA 27
2. Pitch schematic
ATA 27
In case of jamming, pitch control will be recovered by disengaging the pitch coupling
system (by applying a differential force of
52 daN).
96
J. Flight control
3. Yaw schematic
ATA 27
4. Gust lock
ATA 27
GUST LOCK lever
permits to lock mechanically the
roll and pitch axes against wind
gusts. The PL travel is limited to
slightly above FI.
Aircraft equipped with a spring tab on the aileron.
The roll locking system is composed of two electro-mechanical
locking devices.
The AIL LOCK is triggered whenever one of the locking
actuators is in disagreement with the gust lock position (lock
or unlock position)
5. Stick Shaker/Stick Pusher
push button and display
ATA 27
STICK SHAKER / PUSHER PB
– FAULT light indicates a stick
pusher or stick shaker failure
– OFF position: enables to switch
OFF the stick pusher and the stick
shaker system
STICK PUSHER
illuminates to indicate that the stick
pusher is operating
97
S y s t e m s 4 2/72 - 6 0 0
6. Spoilers position indicator
ATA 27
SPOILERS position indicator
When illuminated, each green light
indicates that the associated spoiler is
not in the fully retracted position (more
than 2.5° aileron travel)
7. Pitch trim asym light
ATA 27
PITCH TRIM ASYM
Amber labels are displayed to indicate
a pitch tabs desynchronization greater
than 0.7°
8. Trim position indicator
ATA 27
Pitch trim position
indicates the right trim actuator
controlled tab travel.
A green sector identifies the take off
range. If take off (or take off config
test) is performed with pitch trim out
of this range, CONFIG warning will
be generated by the FWS.
Roll trim position
indicates the LH aileron trim
controlled tab travel
Yaw trim position
indicates units of trim motor
displacement
98
J. Flight control
AP engaged
Manual mode
Associated to:
PITCH TRIM ASYM on FWS
Or
PITCH MISTRIM or AP PITCH TRIM FAIL with AP engaged,
on FMA and FWS
Or
Pointer outside of green band in pre take off condition
(Take off CONFIG)
AP engaged
Yaw Damper engaged
(Yaw Auto Trim active)
Manual mode
Associated to:
RETRIM ROLL L(R) WING DN
In case of roll retrim with AP engaged
The cyan arrow indicates the side to retrim
The trim is inhibited on the other side.
Associated to:
AILERON MISTRIM
On FMA
The cyan arrow indicates the side to retrim
The trim is inhibited on the other side
9. Trim controls
Yaw TRIM control switches
controls the yaw trim actuator.
As a safety device both levers
must be moved and held in the
same direction (nose LH or nose
RH) to energize the system and
trim the aircraft. When used, the
RCU is declutched. The Yaw TRIM
manual control is inhibited when
the autopilot is engaged (Yaw
autotrim)
When the autopilot is engaged, the
“RUDDER MISTRIM” message
can be triggered on FMA.
Manual mode
Yaw Damper off (no Yaw Auto Trim)
Associated to:
RUDDER MISTRIM on FMA
Or
YAW AUTOTRIM FAIL on FWS
The cyan arrow indicates the side to retrim
ATA 27
Roll TRIM control SW
controls the roll trim actuator. For
operation, both sws must be moved
and held in the same direction (L WING
DN or R WING DN) to energize the
system (safety reasons).
The roll trim is inhibited during autopilot
operation.
When the autopilot is engaged, the
“RETRIM ROLL R(L) WING DOWN”
or “AILERON MISTRIM” messages
can be triggered on the FMA. These
messages authorize to retrim on the
dedicated side. The other side is still
inhibited
STBY PITCH control SW
is a guarded sw which controls the
electrical motors of each trim actuator.
Action on this switch will disengage the
autopilot.
Pitch trim rocker
two switches installed on each control wheel. It is necessary
to operate both rocker switches to activate the normal
electrical motor of each trim actuator and to control nose up
or down. The switches are spring loaded to neutral position.
An aural whooler is generated by the FWS if trim is used for
more than 1 second.
Action on this switch will disengage the autopilot.
99
S y s t e m s 4 2/72 - 6 0 0
10. Flaps schematic
11. Flaps position indicator
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ATA 27
J. Flight control
12. Flaps control lever
ATA 27
FLAPS control lever
controls the flaps operation.
Distinct positions correspond to
flaps 0°, 15°, 30° (72-600) or 25°,
35° (42-600)
101
K. Flight instruments
FCOM 1.10
103
S y s t e m s 4 2/72 - 6 0 0
1. Schematic
ATA 31
The Avionics Full DupleX switched ethernet (AFDX) allows transmission of data in all directions between the CAC
1&2 and the DUs. The AFDX is controlled by the SWM’s (Module of the CAC). The SWM (Gateway and Switch module) is
connecting together CPM (Core Processing Module) and other Avionics Data Network subscribers.
SWM external interface mainly consists of: AFDX with the 5 Display Units, AFDX with the CPM, AFDX interconnection between the 2 SWM, Ethernet with dataloading Port.
AFCS (Auto Flight Control System) is managed by the two Auto Flight Control Application (AFCA) of the CACs.
The AFCAs receives data from the two ADC, two AHRS and aircraft equipments as navigation and some sensors.The
AFCAs receives data from the two FMS (Flight Management Application: DU 2 & 4). The AFCS generates commands to
flight control actuators and to the FD bars.
AHRS (Attitude and Heading Reference System) comprises: (1) An AHRU (Attitude and Heading Reference Unit)
which integrates inertial components, to compute the gyro-heading, the attitude, acceleration and the vertical speed.
(2) A Removable Memory Module to store compensation parameters (3) A flux valve which detects the direction of the
earth’s magnetic field line. The AHRS gyro-magnetic heading computation automatically updates the heading value with
the magnetic heading of the flux valve.
ADC (Air Data Computers) is supplied with static air pressure (static ports), total air pressure (pitot ports), total air
temperature (TAT probe). With these inputs, the ADC computes pressure altitude, IAS, TAS, TAT, SAT.
DU (Display Unit):
– Collects all the data, coming from the AFDX (CAC 1 & 2), from Arinc 429 (control panels, CACs, aircraft equipments),
from discrete lines
– Converts the data in video format, through the FDA (Flight Display Application).
NOTES: The FMA (Flight Management Application) and RMA (Radio Management Apllication) are part of the DU 2 & 4
Each DU can display three different formats: the Primary Flight Display (PFD), the Multi Function Display (MFD), the Engine
and Warning Display (EWD)
104
K. Flight instruments
2. PFD (Primary Fight Display)
ROLL ATTITUDE
scale 0 , 10, 20, 30, 45 and 60°
Lateral ARM, CAPTURE9 and
HOLD mode
Bank angle limit:
two green ticks
Flight Mode Annunciator
(FMA)
ATA 31
Vertical ARM, CAPTURE9 and
HOLD mode
SLIP indicator
Horizon and pitch scale
is white and has reference marks
every 2.5° up to 20° up or down,
then marks at 25, 30, 50, 80°.
FLIGHT DIRECTOR
command bars (green)
Vertical deviation indication
RADIO ALTITUDE indication
VSI (Vertical Speed Indicator)
Altimeter: altitude tape
Lateral deviation indication
TCAS and Transponder
annunciator
DH indication
Indication of True Air Speed,
Ground Speed, and wind
Airspeed indicator: Speed tape
EHSI (Electronic Horizontal
Situation Indicator). The EHSI
can be replaced by a mini ND
(Navigation Display) when the the
ND is replaced by an other format
on the MFD.
105
S y s t e m s 4 2/72 - 6 0 0
3. MFD (Multi Function Display)
ATA 31
MFD upper window
Memo panel display
VCP (Virtual Control Panel Window)
MFD upper window selection
106
K. Flight instruments
4. EWD (Engine and Warning Display) ATA 31
Trim indicator
Primary engine
display
Brake messages
Test status
Permanent Data
Flap indicator
Alert window
Procedure window
S y s t e m s 4 2/72 - 6 0 0
5. ND - ARC MODE with terrain
or weather radar information
TERRAIN
6. Source failure alert
DU total loss
AHRS failure
108
ATA 31
WEATHER RADAR
ATA 31
FAIL
A fatal failure has been
detected by DU software
or by the hardware
ADC failure
K. Flight instruments
7. Switching panel
ATA 34
ATT/HDG pb
enables to use AHRS 2
information. When captain pb
is depressed SYS 2 illuminates
white on CAPT pb, CAPT 2
illuminates green on F/O pb
DISPLAY pb
In normal conditions,
enables to cycle the three
formats on DU 2 (capt
switching), on DU 4 (F/O
switching). In case of failure
of any DU (DU 1 or 2 on
capt side or DU 4 or 5 on
F/O side) enables to cycle
the three formats on the
remaining DU
ADC pb
enables to use ADC 2 information. When captain pb
is depressed SYS 2 illuminates white on CAPT pb,
CAPT 2 illuminates green on F/O pb
8. EFCP (control panel)
MFD PERF page:
The performance page can be
displayed, by pressing on the
PERF push button.
MFD ND page:
Three different ND format can be
displayed on the MFD, by pressing on the
ND push button, and then by selecting
the format on the FORMAT rotary knob.
MFD SYS page:
Four different system pages can be
displayed on the MFD, by pressing the
SYS push button consecutively.
BRG1(2)push button:
By pressing it, VOR1(2) or
ADF1(2) or no indication
is displayed.
RANGE “+/–” push button:
By pressing it, the range of
the Navigation Display page is
increased/decreased.
ATA 31
MFD VID page:
In provision for video display
FORMAT rotary knob:
By turning it, the format of
the ND is changed.
RCL PB
A first push enables to display in the
Alert Window the alert messages
previously cleared but still detected.
A second push scrolls down the alert
messages list in case of overflow in
the alert window.
MAN DEL
By pressing on it, procedures
inserted manually are deleted
MFD MISC page:
Engine run up page
MFD MAP page:
Airport map page
(option)
Procedure control pb:
Allows to move on
upward/downward line
in the procedure window
and to validate actions
CLR PB
By pressing on it, a clearable
alert displayed on the Alert
Window is cleared.
PROC MENU
By pressing on it, procedure
menu is displayed in the
procedure window.
109
S y s t e m s 4 2/72 - 6 0 0
9. MCP (Multipurpose Control Panel)
ATA 31
Multi directionnal pad
To move the cursor for choosing a
selection area
COM P/B
Selection on VCP
– VHF
– HF 1 (if installed)
– HF 2 (if installed)
Enter P/B
To validate the selection area
NAV P/B
Selection on VCP
– VOR
– ADF
– ND OVLY (ND
Overlay)
SURV P/B
(surveillance)
Selection on VCP
– XPDR
– TCAS
110
ESC P/B
(Escape)
Before validation, the
escape P/B allows to
recover the previous value
Numeric Key Board
Allows setting the frequency or
transponder code.
K. Flight instruments
10. Weather radar control
ATA 34
Primus 660
GAIN
setting to set receiving amplification
MODE selector
OFF radar is off
STBY radar is on but no pulse is sent
by the antenna
TEST range at 100 NM, 3 arcs green,
yellow and red
WX normal operating position,
intensity of weather obstacles is
displayed by different colors (black:
no cloud; green: normal cloud; yellow:
dense; red: severe storm)
G MAP enables to display ground
obstacles (black, pale blue, yellow,
magenta)
RCT pb
activates Rain Echo Attenuation
Compensation technique function and
permits display with more accurracy
the weather situation behind storms
TGT pb
activates target alert
SECT pb
Used to select either the normal
12 looks/minute 120° sector scan
or the faster update 24 looks/
minute 60° sector scan
TILT control
to adjust radar antenna in pitch
axis from 15° down to 15° up
Turns the pitch and roll stability
on and off. When selected off, an
amber legend illuminates above the
pushbutton
111
S y s t e m s 4 2/72 - 6 0 0
11. TAT/SAT indicator
ATA 34
TAT indicator
indicates total air temperature
SAT indicator
indicates static air temperature
TAS indicator
indicates true air speed
12. CLOCK
MODE P/B
By pressing the MODE pushbutton, six
annunciators (DT, GPS, INT, LT, ET and CHR)
indicate which mode is selected (the functions
INT, LOC and DT are available in succession,
ET and CHR functions are controlled by the
ET and CHR buttons respectively, the GPS is
automatically selected when GPS is valid).
Chronometer (CHR) P/B
– START: Display is active and the chronometer
starts incrementing
– STOP: The value displayed at the instant the
push-button was depressed is held as long as
no action occurs on this push button.
– RESET: the LCD display is zeroed and blanked.
ATA 31
Elapsed time (ET) P/B
– When selecting the ET push button, the ET
display comes on.
– When the elapsed time counter is stopped,
by pressing the ET push button for more than
two seconds the display is blanked and value
is zeroed.
For the time set, the ET P/B is used to
decrease the digits (-)
TEST P/B
For the time set, the TEST P/B is used to
increase the digits (+)
Six digits display of either:
– Universal Time Coordinated (from GPS or
internal time)
– Date: MONTH / DAY / YEAR
– Local Time
Four digits display of either:
– ELAPSED TIME (ET)
– CHRONOMETER TIME (CHR)
ELAPSED TIME
When depressed ON
the flight time starts
automatically
when airborne
112
K. Flight instruments
13. RCDR panel
ATA 31
RCDR pb
when depressed, both cockpit
voice recorder and digital flight data
recorder are energized (manual
mode). ON lt illuminates cyan
RESET pb
when depressed, inhibits recording
in the manual mode
14. STBY instruments
ATA 34
STANBY COMPASS
STANDBY COMPASS
Hidden in up position. Compass
control should be placed on DN for
use. The compass rose is graduated
in 10 degrees increments
IESI: Integrated Electronic Standby Instrument
Menu P/B
Enable sub function selection menu
STD P/B
Reset at 1013.25Hpa, when
pushed more than 0.2 sec.
LATERAL ACCELERATION
INDEX
indicates the aircraft’s lateral
acceleration. It is represented by
a trapezoidal index that moves
beneath the roll index.
STANDBY AIRSPEED
INDICATOR
The actual airspeed is given in a T
shaped window positioned in the
center of the white moving speed
tape on the left of the IESI.
Brightness
STANDBY HORIZON
– The pitch scale has markers
every 2.5 degrees up to ±20°.
If pitch exceeds ±25° degrees
large red chevron will indicate
excessive attitude and direction
to follow to resume normal
attitude.
– The roll scale has markers are
set at 10, 20, 30, 45, 60 degrees
of bank.
SEL P/B
Change cursor selection
between VHF COM, VHF
NAV, BARO SETTING
and COURSE when
VOR mode.
SET ROTARY SWITCH
– Sub fonction menu scroller
– Baro setting
– VHF com tuning
– VHF nav tuning
– Course setting in VOR
mode
STANDBY ALTIMETER
The altitude indication is given in
a rectangular window positioned
in the center of the white moving
altitude tape on the right of the
IESI.
Altitude in meters can also be
displayed on the IESI underneath
the altitude tape.
The barometric reference is
displayed in cyan. It corresponds
to either the selected barometric
pressure or the standard pressure.
113
S y s t e m s 4 2/72 - 6 0 0
15. Airspeed indicator
ATA 34
VmLB0 (icing
condition)
Speed bug read out
Speed trend
Predicted airspeed
in 10s
VmLB0 (normal
condition)
Maximum speed
Vmo/Mmo or Vfe or Vle
or Vtlu
Flaps retraction speed
Speed bug
–Automatic speed bug
(Magenta) managed
by the FMS.
–Manual speed bug
(Cyan) selected on
the ICP.
VminOPS
Upper amber limit
VPROT
Upper red limit
Activation of the stick
shaker
V1, VR and V2 (Cyan)
Actual IAS
Before rotation
Initial climb
Cruise
Flaps extension speed
(VFE NEXT)
VmHB15 normal (white line)
VmHB15 icing (amber line)
Flaps retraction speed
Vref
VmHB30 or Vmcl whichever is higher
Approach Flaps
15°
Approach Flaps
30°
The speed bug is
controlled by the ICP
(Index Control Panel)
Speed target selection
Selection of the speed bug
between:
– AUTO: Speed bug managed
by the FMS
– MAN: Speed bug set manually
by the speed knob
114
Speed knob
Used to set the speed bug
In MAN mode
K. Flight instruments
16. Altimeter
ATA 34
Selected Altitude
ALT SEL
Current altitude or FL
ALTITUDE ALERT
An amber frame is flashing
(± 1000ft) then a yellow frame
is steady (± 250ft)
DA / MDA
Landing Elevation
Barometric setting in
Hpa and InHG
Barometric setting knob
The knob is used to set the
barometric reference.
Pushing the knob sets standard
barometric reference (29.92 INHG /
1013.25 Hpa)
DH / MDA knob
Outer knob permits to select between
DH (Decision Height) or MDA (Minimum
Descent Altitude).
Inner knob is used to set DH or MDA
values, depending of the outer knob
position.
115
S y s t e m s 4 2/72 - 6 0 0
17. Vertical speed indicator and TCAS ATA 34
VS target readout
Set by the FGCP
Pitch Wheel (PW)
VS digital readout
VS scale
VERTICAL SPEED
INDICATOR
based on both inertial
(AHRS) and
barometric data (ADC).
VS pointer
VS target
Set by the FGCP
Pitch Wheel (PW)
Above (+) or Below (–)
separation height
descending or climbing
Open diamond
Other traffic
Solid diamond
Proximate traffic (PA) traffic
within ± 1200 ft and 6 NM
Solid circle
Traffic Advisory (TA)
Traffic in caution area 20 to
48s before collision area
Solid cube
Resolution Advisory (RA)
Traffic in warning area 15
to 35s before collision area
TCAS Status
RANGE RING
2.5NM around the
A/C
AIRCRAFT
own aircraft symbol
TCAS no bearing advisory:
In case the bearing of the TA or RA intruder is not available,
a message provides an indication on the two most
dangerous RA or TA intruders
116
Resolution Advisory (RA)
vertical rates to be avoided.
L. Fuel system
FCOM 1.11
117
S y s t e m s 4 2/72 - 6 0 0
1. Schematic
ATA 28
The fuel is stored in two tanks, one in each wing. Each tank is fitted with:
– a vent surge tank to ensure positive pressure and allows a thermal expansion without spillage
– a main wing tank
– a feeder tank, always full to protect the engine feed system against negative or lateral load factors
Total quantity 4500 kg
ATR 42
Refueling panel
Refueling point
Gravity filling cap
Access door
Main wing tank
Vent surge tank (100 l)
Main wing tank
Feeder tank (200 l / 160 kg)
Vent surge tank
Total quantity 5000 kg
ATR 72
Refueling panel
Gravity filling cap
Access door
Main wing tank
Refueling point
Vent surge tank (100 l)
Main wing tank
118
Feeder tank (200 l / 160 kg)
Vent surge tank
L. Fuel system
2. Electrical fuel pump OFF
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119
S y s t e m s 4 2/72 - 6 0 0
3. Starting procedure
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ENGINE SHUT DOWN WITH ELECTRICAL PUMP RUNNING
Both fuel engine electrical pumps push buttons are pressed IN and green RUN lights illuminate.
The electrical pumps are energized and begin to supply fuel to engines.
The FEED LO PR amber light extinguishes when the pressure is > 4 psi in the pipe.
At the same time, the feeder jet pump is activated by the electrical pump output pressure, to supply and maintain the
feeder tank full.
120
L. Fuel system
4. Normal procedure
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ENGINE RUNNING / NORMAL OPERATION OF THE FUEL SYSTEM
After engine start, the flow, from return line of the HMU, opens the Motive Flow Valve, in order to supply the Engine Feed
Jet Pump.
The Engine Feed Jet Pump begins to operate by driving fuel from the feeder tank.
At the same time, it supplies the Feeder Jet Pump.
When the Engine Feed Jet Pump outlet pressure reaches 8.5 PSI, the electrical pump is de-energized after 30s time
delay.
In normal operation of the fuel system, the engine is only supplied by the Engine Feed Jet Pump and the electrical pump is
de-energized.
Conditions to energize the electrical pump (See details on pages hereafter)
– Cross feed operation
– Engine Feed Jet Pump outlet pressure drops below 5 psi
– Low Level
121
S y s t e m s 4 2/72 - 6 0 0
5. Cross feed procedure
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Cross feed valve could be used to supply an engine from the opposite tank.
The cross feed is not used to tranfer fuel from one tank to the other tank.
With the Xfeed valve push button pressed IN, the valve opens, green flow bar is horizontal. Both electrical pump are
energized.
122
L. Fuel system
CROSS FEED PROCEDURE CONT’D
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By selecting OFF the corresponding PUMP push button, the electrical pump is de-energized and the motive flow valve is
supplied to close. The engine is fed from the opposite tank.
123
S y s t e m s 4 2/72 - 6 0 0
6. Engine feed jet pump low pressure ATA 28
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In the event of engine feed jet pump failure, the pressure switch (<5 psi) provides electrical pump running control which
ensures fuel supply to the engine.
The electrical pump delivers the necessary flow rate for engine consumption.
124
L. Fuel system
7. Low level
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When the low level is triggered in one tank, its electrical pump is automatically activated.
Two low level cases:
– LO LVL with fuel quantity indicator < 160 kg
→ Low level of remaining fuel in the tank.
– LO LVL with fuel quantity indicator > 160 kg
→ Feeder tank not full due to a failure of the feeder jet pump.
In this condition, the fuel is transfered from the main tank to the feeder tank through the flappers.
LO LVL with FQI <160kg
LO LVL with FQI >160kg (feeder tank not full)
125
S y s t e m s 4 2/72 - 6 0 0
8. Engine fire procedure
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In case of engine fire, when corresponding engine fire handle is pulled, it closes associated LP shut off valve.
126
L. Fuel system
9. Fuel panel
ATA 28
XFEED valve
Activates both elect fuel
pumps.
FEED LO PR
Delivery pressure < 4 PSI.
Pump failure or fuel starvation.
FWS.
PUMP
Control electrical pump power
and jet pump motive flow
valve.
Runs automatically if:
– jet pump press < 5 PSI or till
reaching 8.5 PSI during engine
start.
– XFEED in line
– fuel LO LVL
* When the quantity is
< 160 kg
or * When the quantity is
> 160 kg, but the feeder
tank is not full (Feeder jet
pump failure)
– during fuel quantity test
FLOW BAR
Shows position of valve. No
bar: valve fault or moving.
RUN
illuminates green when elec
fuel pump is running.
10. SD Engine
ATA 31
FUEL TEMPERATURE in °C
Fuel Xfeed valve
Fuel Xfeed valve open
Fuel LP valve
OFF
Electrical pump OFF
RUN
Electrical pump ON and
the pump is running
Fuel LP valve closing or
opening
Electrical pump ON and
the pump is not running
Fuel LP valve closed
XFEED
XFEED
XFEED
Fuel Xfeed valve closing
or opening
Fuel Xfeed valve closed
Fuel Xfeed valve not
closed or not open after
XFEED 3s
Electrical pump OFF and
the pump is running
Fuel LP valve open
Fuel LP valve not closed
or not open after 3s
127
S y s t e m s 4 2/72 - 6 0 0
11. Fuel QTY indication
Fuel used
ATA 28
Fuel On Board
(FMS computed)
Fuel quantity indication
If >160 kg
If <160 kg and >50 kg
If <50 kg
FUEL LO LVL
– When the quantity
is <160 kg or
– When the quantity
is >160 kg, but
the feeder tank is
not full (Feeder jet
pump failure)
12. XFEED advisory on memo
panel display
LO LVL with FQI <160kg
LO LVL with FQI >160kg
(feeder tank not full)
ATA 28
FUEL X FEED
is displayed as soon as the
fuel crossfeed is selected on.
128
M. Hydraulic system
FCOM 1.12
129
S y s t e m s 4 2/72 - 6 0 0
1. Schematic
ATA 29
The aircraft has two hydraulic systems, designated blue and green. Each system is pressurized by an electric pump,
supplied by ACW power. The blue system is also provided with an auxilliary pump, supplied by DC power (automatic or
manual mode).
Total fluid volume:
normal filling:
minimum filling:
alert level:
5(7851
29+7
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29+7
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%/8(3803
/235
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/235
21
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130
9.6 l
9.35 l
8.5 l
2.5 l
M. Hydraulic system
2. HYD PWR panel
BLUE PUMP
Supplied by ACW, controlled by
DC EMER BUS
Auxiliary pump
Automatic running conditions
(simultaneoustly):
– AUX Pump pb depressed
– at least one engine running
– blue system press <1500 psi
– prop brake off
– gear lever down
(supply: DC BUS 2 or Hot main bat bus)
LO PRESS
pump delivery pressure less
than1500 psi. FWS (no auto off)
OVHT
drain > 121°C (250°F). FWS. (no
auto off).
ATA 29
GREEN PUMP
Supplied by ACW, controlled by
DC BUS 2 or DC EMER BUS
LO PR
pump delivery pressure less
than 1500 psi. FWS (no auto
off).
X FEED
Pb released Xfeed closed. if LO LVL
automatic closure. (DC STBY BUS).
3. SD ACW and hydraulic
LO LEVEL
associated compartment <2.5 l.
HYD on FWS.
ATA 29
X feed valve
X feed closed
Auxiliary hydraulic pump
OFF
P/B OFF
STBY
– P/B OFF and DC hot main
bus <18V
– or DC BUS 2 OFF
STBY
P/B ON and pump not running
P/B ON and pump running in
automatic mode
INHIB
P/B ON and
low pressure (<1500 psi)
P/B ON and
overheat (> 121°C / 250° F)
associated to OVHT
LO LVL
X feed open
Main hydraulic pump
OFF
P/B ON and pump running in
manual mode (pedestal P/B)
LO
PR
X feed opening is
inhibited after a
Pump OFF
Pump ON
LO
PR
Pump ON and
low pressure
(<1500 psi)
Pump ON and
Overheat (>121°C
/ 250° F)
associated to
OVHT
131
S y s t e m s 4 2/72 - 6 0 0
4. Pressure indication
Blue HYD SYST
Blue system hydraulic pressure
indicator.
BRAKE ACCU
by blue system. for emer brakes
max 6 applications. (DC STBY)
5. AUX pump pedestal switch
ATA 29
Green HYD SYST
Green system hydraulic
pressure indicator.
ATA 29
AUX PUMP pedestal switch
– energizes for 30’’, the auxiliary
DC hydraulic pump with the
HOT MAIN BAT BUS
– supplies power to the
pressure indicators
NOTE: intensive use could
discharge the main battery.
132
M. Hydraulic system
6. Hydraulic on Ramp (only on battery)
ATA 29
On battery or DC GPU, the brake accumulator maintains a pressure for the parking brake (No hydraulic pump running)
7. Hydraulic on Ramp
(aux pump P/B selected on the pedestal)
ATA 29
When depressing the auxiliary pump P/B on the pedestal, the aux pump is supplied by the DC HOT MAIN BAT BUS. the
blue system is available (prop brake releasing operation)
133
S y s t e m s 4 2/72 - 6 0 0
8. Hydraulic system normal operation ATA 29
When both engine are running and the propellers are unfeathered, the blue and green pump are supplied by the ACW (blue
and green systems available)
134
M. Hydraulic system
9. Hydraulic system failures
ATA 29
– Main pump low pressure (<1500PSI) or overheat (>121°C) ––> after cross feed both system are still available
– Low level (<2.5l) ––> cross feed inhibited (one system loss)
10. Hydraulic system crossfeed operation ATA 29
After a main pump low pressure (<1500PSI) or overheat (>121°C) both systems are recovered by crossfeed operation
135
S y s t e m s 4 2/72 - 6 0 0
11. Both main hydraulic pumps loss
ATA 29
When the green system is lost, and there is a LO PR or OVHT on the blue system,
the BOTH MAIN HYD PUMPS LOSS check list has to be applied.
When both main pumps are lost, the blue pressure is recovered in approach, by the aux pump, when the landing gear lever
is selected down.
136
M. Hydraulic system
12. Both hydraulic systems loss
ATA 29
When the green system is lost, and there is a LO LVL on the blue system, the BOTH HYD SYS LOSS check list has to be
applied. Only the emergency braking is available with the brake accumulator.
137
N. Ice and rain protection
FCOM 1.13
139
S y s t e m s 4 2/72 - 6 0 0
Aircraft ice protection is provided by a pneumatic and an electrical system adapted for the critical areas. Ice detector
monitors ice accretion. It is connected to the FWS.
1. Schematic
AILERON HORNS
(ELECTRICAL)
WINGS BOOTS
(PNEUMATIC)
ATA 30
ENGINE AIR
INTAKE BOOTS
(PNEUMATIC)
HORIZONTAL TAILPLANE BOOTS
(PNEUMATIC) / RUDDER
AND ELEVATOR HORNS
(ELECTRICAL)
PROPELLER
(ELECTRICAL)
WINSHIELD
(ELECTRICAL)
SIDE WINDOWS
(ELECTRICAL)
140
ICING EVIDENCE
PROBE
PROBES
(ELECTRICAL)
ICE DETECTOR
N. Ice and rain protection
2. Probes and windshield HTG
ALPHA
ACW supply. Amber LT
illuminates in case of failure or
power loss. FWS
PITOT STBY
not heated.
ACW BUS 1 or 115 AC STBY
BUS as back up.
TAT
not heated. FWS. (ACW supply)
heating inhibited on ground.
ATA 30
WINDSHIELD HTG
ACW supply. Outer surface
+2°C. Inner +21°C
WINDSHIELD HTG FAULT
Power loss or failure. FWS.
PITOT tube
not heated. FWS. (ACW bus
1 for CPT and ACW bus 2 for
F/O).
STAT
Static port not heated (On
ground only, not monitored in
flight). FWS. (DC BUS)
CAPT, STBY and F/O
Normal operation - ON
(depressed) and OFF (released).
3. Rain protection
CAPT WIPER rotary
selector
OFF: wiper stops at the end
of travel (park) position.
SLOW: wiper operates at 80
cycles/min
FAST: wiper operates at 130
cycles/min
ATA 30
F/O WIPER rotary selector
OFF: wiper stops at the end
of travel (park) position.
SLOW: wiper operates at 80
cycles/min
FAST: wiper operates at 130
cycles/min
4. Ice detector panel and icing AOA
PTT pb
press for 3’’:
– icing will flash, on FMA, if system works
correctly.
– A-ICING DETECT is displayed steady
on FWS if ice detector failure is detected
ICING AOA Lt
(DC emer BUS).
Illuminates green as soon as 1 horn anti-icing on.
Stall alarm + stick shaker threshold lowered.
When light ON, the angle of attack for the stall
warning is reduced.
It can be extinguished manually only by
releasing ICING AOA P/B provided both horns
anti-icing are selected OFF
ATA 30
ICE DET indicator Lt: ACW bus 2.
ICING
illuminates amber when ice accretion
is detected provided both horns antiicing and airframe de-icing are selected
ON.
ICING
flashes amber when ice accretion is
detected and horns anti-icing and/or
airframe de-icing are not selected ON
141
S y s t e m s 4 2/72 - 6 0 0
5. Aircraft Performance Monitoring (APM)
ATA 30
FAULT
The APM FAULT will be triggered by the MPC in
case of internal failure or invalid aircraft parameters.
OFF
APM function in OFF position
APM PTT pb
Used to test the APM function.
This test shall be performed daily by the crew,
to determine whether the APM components are
operational.
APM alert lights:
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cruise only. An abnormal drag increase induces a speed
decrease >10kt
'*'3(5)
cruise and climb. An abnormal drag increase induces
a speed decrease or a loss of rate of climb
,1&5($6(
63(('
After degraded perf. Drag abnormally high and IAS lower
than RED BUG + 10 kt
ROLL HOLD LO
ICING
DGD PERF
VOR
RETRIM ROLL R WING DN CAT1
142
PITCH HOLD
ALT SEL
CHECK NAV SRC
AP FD DUAL
SPD HLD TCS
FD SINGLE CH
N. Ice and rain protection
6. De-icing schematic
Following the cycle
diagram, after the
engines boots, inflation
of the boots A (outer
boots), for 5s
Then boots B (outer
boots), for 5s, followed
by the inner boots and
horizontal stabilizer
143
S y s t e m s 4 2/72 - 6 0 0
7. Airframe air bleed FAULT
An AFR AIR BLEED FAULT is triggered for an underpressure in the line (<14 psi) or an overtemperature on engine 1 or 2
bleeding (>230°C)
Following the check list, after the deselection of the AFR AIR BLEED P/B:
– If DE-ICING ENG FAULT light illuminates after 10s ––> OVERHEAT
– If not
––> UNDERPRESSURE
In case of overheat, the ENG P/B is deselected, the AFR AIR BLEED is selected again to isolate the affected engine.
144
N. Ice and rain protection
8. Anti-icing & de-icing panel
PROP
ACW supply. Inhibited below
NP 63%
HORNS
ACW supply. Inhibited on
ground. Either horn activates
AOA Lt
FAULT
power loss on at least 1 blade.
A-ICING PROP 1 (2) on FWS
DE ICING
air is always available
regardless of bleed pb.
NORM: 60’’ / cycle
SLOW: 240’’ / cycle
MODE SEL AUTO
Automatic selection of cycle
depending on ADC1/2 to
MFC1B/2B
FAULT when ADC or MFC fail:
Fast mode is automatically
selected for ENG and
AIRFRAME DEICING and High
Power for PROP ANTI-ICE.
A-ICING AUTO on FWS.
MAN: manual selection of
cycles depending on SAT
FAULT
both MFC modules have failed
to control boots cycles.
The monitoring is preformed
by the stby controller.
A-ICING SEL on FWS
AFR AIR BLEED
OVRD: no MFC. Boots
inflated by separate stantby
controller (cycle 60’’)
ENG
FAULT: distribution valve
opened but no air pressure.
OR valve closed and pressure
detected OR AFR AIR BLEED
off and air temp above deice
valve >230°C for more than
6’’. A-ICING ENG 1 ( 2) on
FWS
MODE SEL ENG AND
AIRFRAME
SLOW: 240’’/cycle
FAST: 60’’/cycle
HORNS FAULT
Power loss. A-ICING HORNS
1 (2) on FWS
SIDE WINDOWS
Defog only. FAULT for power
loss. A-ICING WINDOWS
on FWS. (DC BUS)
MODE SEL PROP
NORM: 10’’ on per 3 blades;
then 10’’ off between cycles.
ON (HIGH POWER): 20’’ on
per 3 blades.
No stop between cycles.
ENG
ON: signal sent to MFC
to start deice cycle on the
engine air intake, deice valve
opened even if AFR AIR
BLEED off
ATA 30
AIR FRAME
FAULT: valve opened but
no downstream pressure. Or
valve closed and downstream
pressure detected. A-ICING
FRAME on FWS
AIR FRAME
ON: signal sent to MFC
to start deice cycle on the
airframe
AFR AIR BLEED
FAULT: air dowstream deice
valve < 14 psi more than 10’’
OR Air upstream of the deice
valve > 230°C. A-ICING
BLEED on FWS
9. De-icing/anti-icing indication
(memo panel display)
OFF : isol valves closed.
Deice valves closed unless
ENG 1 / 2 deice on.
ATA 30
CYAN
When selected ON
AMBER
When FAULT
145
O. Landing gear
FCOM 1.14
147
S y s t e m s 4 2/72 - 6 0 0
1. Landing gear description
ATA 32
The landing gear is hydraulically operated. In case of hydraulic failure, it may be extended by gravity.
LANDING GEAR
CONTROL
STEERING
HANDWHEEL
2. Brakes schematic
EMERGENCY /
PARKING BRAKE
HANDLE
148
ATA 32
PILOT BRAKE
PEDALS
O. Landing gear
3. LDG GEAR position indicators
ATA 32
System 2
UNLK gear not locked in selected
position or (on GND) uplock box
not opened.
Green Lt down lock engaged
System 1
UNLK gear not locked in selected
position or (on GND) uplock box
not opened.
Green Lt down lock engaged.
4. Landing gear handles
LDG GEAR EMERGENCY
EXTENSION HANDLE
permits to unlock the landing gear
5. Brakes temperature
and antiskid
BRK TEMP
WHEELS BRK HOT on FWS
for any brake T° >160°C (42)
T° >150°C (72)
OFF
Pb released, system
deactivated
ATA 32
GEAR HANDLE RED LIGHT
any gear not sensed down and
locked with some conditions.
FWS.
ATA 32
ANTISKID
Operative if speed > 10 kts.
Activates when speed > 23 kts +
50% diff between wheels (locked
wheel protection).
Braking action inhibited at
touchdown as long as wheel spin up
speed < 35 kts or 5 sec. (touchdown
protection).
CAUTION: THE TEST INHIBITS
BRAKES
TEST pb
(inhibited if speed > 17 kts)
= MC + SC+ FWS.
Test duration: 3 sec. in flight and
6 sec. on ground
F (FAULT)
wheel channel failure +
WHEELS A-SKID on FWS
149
S y s t e m s 4 2/72 - 6 0 0
6. Emergency parking
brake handle
EMERGENCY BRAKE HANDLE
permits to apply a metered pressure.
The brake accumulator allows at least six
braking applications without any antiskid
operation if the blue hydraulic system is not
available (Springloaded to the off position)
7. Steering handwheel
N/W STEERING SW
activates or deactivates the nose wheel
steering system (guarded type in the ON
position)
OFF: unpressurizes the steering system
(91° of deflection)
150
ATA 32
PARKING BRAKE
permits a full pressure on the brakes. When brake
handle is not in the fully released position, amber
PRKG BRK caution light is displayed on FWS and
is taken into account by the T/O CONFIG.
(Springloaded to the off position)
ATA 32
THE STEERING HAND WHEEL
controls the nose wheel angle up to 60° in
either direction:
– clockwise: steering to the right
– counter clockwise: steering to the left
P. Navigation system
FCOM 1.15
151
S y s t e m s 4 2/72 - 6 0 0
1. Nav control
ATA 34
VCP
MCDU
MCP
MCP and MCDU allow:
– to tune VOR/ILS/DME frequencies
– to set tune mode (AUTO/ MAN)
– to do DME HOLD
In AUTO tuning, the NAV source has to be on FMS (Inhibited on V/ILS)
2. Marker sensibility setting
ATA 34
MCDU
MCDU allows to set MKR sensibility
(LO/HI position)
3. ADF control
ATA 34
VCP
MCDU
MCP
MCP and MCDU allow:
– to tune ADF frequencies
– to set mode (ADF/ANT)
– to set tone (OFF/ON)
152
P. Navigation system
4. TAWS alert modes
ATA 34
The Terrain Awareness Warning System provides visual and aural alerts in case of dangerous flight path conditions which
would result inadvertent ground contact if maintained.
The TAWS performs the following alert modes:
– Reactive warning modes
* Mode 1: excessive descent rate
* Mode 2: excessive terrain closure rate
* Mode 3: altitude loss after take-off
* Mode 4: unsafe terrain clearance
* Mode 5: below glideslope
* Mode 6: altitude callouts
– Predictive warning modes:
* Terrain Caution and Warning
* Obstacle Caution and Warning
MODE 1
excessive descent rate
MODE 2
excessive terrain closure rate
153
S y s t e m s 4 2/72 - 6 0 0
MODE 3
altitude loss after take-off
MODE 4
unsafe terrain clearance
MODE 5
below glideslope
154
P. Navigation system
MODE 6
altitude callouts
TERRAIN CLEARANCE FLOOR (TCF)
The Terrain Clearance Floor (TCF) mode creates
an increasing terrain clearance envelope around
the airport runway directly related to the distance
from the runway.
Runway Field Clearance Floor (RFCF)
155
S y s t e m s 4 2/72 - 6 0 0
TERRAIN AND OBSTACLE AWARENESS
This function use the aircraft geographic position from the GPS, aircraft altitude and a worldwide terrain database to
predict potential conflict between the aircraft flight path and the terrain, and to provide aural alert and graphic displays of
the conflicting terrain.
The terrain advisory line is drawn
along the points where a terrain
caution alert will occur if the
aircraft continues along its current
trajectory.
“TERRAIN AHEAD”
or
“OBSTACLE AHEAD”
When a terrain caution or warning
occurs, the terrain advisory line
is removed from the display and
the terrain display is changed to
identify the terrain that caused the
alert.
“TERRAIN AHEAD,
PULL UP”
Or
“OBSTACLE AHEAD
PULL UP”
The Pull-Up Warning is generated
as long as the current aircraft
trajectory will not safely clear
the terrain, and the aircraft
performances are able to clear the
terrain in climb
156
P. Navigation system
“AVOID TERRAIN”
The Pull-Up maneuver will not
allow for a safe clearance with
terrain, and the crew has to
immediately initiate an appropriate
vertical and/or turning escape
maneuver in order to avoid terrain
5. TAWS pb
ATA 34
6. TAWS panel
ATA 34
TAWS selector
is guarded in the norm position.
FLAP OVRD mode 4 alert caused
by flap extension is inhibited to avoid
nuisance in case of reduced flaps
landing
157
S y s t e m s 4 2/72 - 6 0 0
7. ND OVERLAY
The MCP allows to set ND OVLY
– Traffic
– Weather radar
– Terrain
– Navaid
– Airport
158
ATA 31
P. Navigation system
8. FMS
ATA 34
The dual THALES Flight Management System (FMS) installed on ATR 72/42-600 aircraft is composed of two identical sets
of software applications, called FMS1 and FMS2. Each FMS is hosted within the DU2 and DU4, normally used with the
MFD format.This dual FMS is built on dual cockpit system architecture.
It is used to be normally handled with both FMS, synchronized by the cross talk function.
159
S y s t e m s 4 2/72 - 6 0 0
160
Q. Power plant
FCOM 1.16
161
S y s t e m s 4 2/72 - 6 0 0
1. Engine schematic
ATA 61/72
Aircraft fitted with
– two Pratt &Whitney, PW 127 M (72-600/42-600)
– two, six blades propellers (Hamilton)
It is a free turbines engine, composed of 3 concentric shafts of spools:
– The shaft of the HP spool composed of the HP turbine and the HP compressor (rotation speed of the HP spool: NH). The
HP spool drives the accessory gear box (AGB)
– The shaft of the LP spool composed of the LP turbine and the LP compressor (rotation speed of the LP spool: NL)
– The Power shaft composed of 2 power turbines (Free turbines). This 2 power turbines drive the propeller through the
reduction gear box (RGB) (rotation speed of the propeller NP)
REDUCTION GEAR BOX
These equipments are fitted on the RGB
– the ACW generator
– the Propeller Valve Module (PVM)
– the propeller pump (HP) and overspeed
governor
– the auxiliary feathering pump
– the propeller brake (on RH engine only)
HIGH PRESSURE COMPRESSOR
centrifugal type
LOW PRESSURE COMPRESSOR
centrifugal type
HIGH PRESSURE
TURBINE
POWER TURBINE
ACCESSORY GEAR BOX
driven by the HP spool.
Drives
– the DC starter/generator
– the HP fuel pump
– the engine oil pumps
DIFFUSER PIPES
ANNULAR COMBUSTION
CHAMBER
6 blades propeller
162
LOW PRESSURE TURBINE
Q. Power plant
2. Power and propeller controls
ATA 61/72
The different powers ratings for the engine are: (SHP: Shaft Horse Power)
– RTO (Reserve Take Off) (maximum power)
Used in case of an engine flame out during take off
(up trim) or in case of go around (ramp)
– MCT (Maximum continuous)
– TO (Take Off 0,9 RTO)
– Climb
– Cruise
72-600
2750 SHP
42-600
2400 SHP
2500 SHP
2475 SHP
2192 SHP
2132 SHP
2400 SHP
2160 SHP
2160 SHP
2132 SHP
Power (PWR) = Torque (TQ) x NP
For the same power: If TQ increases, NP decreases
If TQ decreases, NP increases
Power setting is characterized by constant power lever (PL) and condition lever (CL) positions. The power adapted to the
flight phase is selected by the pilot through a power management selector (PWR MGT).
– With input coming from the PWR MGT and the position of the PL, the EEC (Engine Electronic Control) control the fuel
flow to the engine.
MAX PWR (Full stop): Maximum Power → TQ up to115% (On emergency only)
GO around position (Beginning of the ramp): RTO → TQ up to100%
NOTCH position:
PWR MGT in – TO:
– MCT
– CLB
– CRZ
→ NP 100% and 0,9 RTO → TQ up to 90%
→ NP 100% and TQ up to 90,9% (72-600)
→ NP 100% and TQ up to 100% (42-600)
→ NP 82% and TQ up to 97% (72-600)
→ NP 82% and TQ up to 109,7% (42-600)
→ NP 82% and TQ up to 94,5% (72-600)
→ NP 82% and TQ up to 108,3% (42-600)
Reversion in manual mode when EEC FAULT (green band <52°)
Flight Idle position
Ground Idle position
Reverse position
163
S y s t e m s 4 2/72 - 6 0 0
– With the PWR MGT input and the CL position, the PEC (Propeller Engine Control) control the NP (propeller speed) by changing the
blades angle.
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Regardless of the PWR MGT position, NP is at 100%
AUTO position:
→ Blade angle governing mode. The NP is regulated by the PEC (Blade angle
change). PWR MGT in: – TO → NP = 100%
– MCT → NP = 100%
– CLB → NP = 82%
– CRZ → NP = 82%
→ Fuel governing mode. The NP is regulated by the EEC (Fuel Flow change)
ground operation in low power.
The NP is maintained at 70.8% to have the ACW available.
(The ACW generator is on line when NP > 66%)
FTR (Feather position). The fuel governing mode is cancelled
(No ACW generator)
Fuel Shut Off position: Close the shut off valve on the HMU
164
Q. Power plant
– The PWR MGT has four positions: TO, MCT, CLB, CRZ
– Considering that CLs are in AUTO and the PLs are in the notch, the
control system delivers max rated power corresponding to the mode
selected (the max rated power is delivered only when the engine is
not thermodynamically limited)
ATR 72-600
NORMAL OPERATION, EEC ON, ISA CONDITIONS
SHP
115% TQ
A
102% TQ
100% TQ
RTO (UP TRIM)
2750
2500
2475
2192
2132
MCT OR TO
B
TO 90% TQ
C
D
LINE A: One engine out operation
LINE B: Normal TO or MCT
LINE C: CLB
LINE D: CRZ
NOTE: Sensible sector designed to
allow for fix throttle engine control.
100% Np
100% Np
MCT 90.9% TQ
RAMP
100% Np
WALL
NOTCH
0
50
67
81
100
POWER LEVER ANGLE
– TO
– MCT
– CLB
– CRZ
PWR = 2475 SHP
PWR = 2500 SHP
PWR = 2192 SHP
PWR = 2132 SHP
NP=100%
NP=100%
NP=82%
NP=82%
TQ = 90%
TQ = 90,9%
TQ = 97%
TQ = 94,5%
The RTO (Reserve Take-Off) is obtained in case of up trim (one engine out during take off) or with the PL to the ramp
– RTO
PWR = 2750 SHP
ATR 42-600
NP=100%
TQ = 100%
NORMAL OPERATION, EEC ON, ISA CONDITIONS
SHP
115% TQ
A
2400
MCT OR TO
2160
102% TQ
100% TQ
RTO (UP TRIM)
B
90% TQ
100% Np
100% Np
C
2132
LINE A: One engine out operation
LINE B: Normal TO or MCT
LINE C: CRZ
NOTE: Sensible sector designed to
allow for fix throttle engine control.
RAMP
WALL
NOTCH
0
– TO
– MCT
– CLB
– CRZ
PWR = 2160 SHP
PWR = 2400 SHP
PWR = 2160 SHP
PWR = 2132 SHP
50
NP=100%
NP=100%
NP=82%
NP=82%
67
TQ = 90%
TQ = 100%
TQ = 109,7%
TQ = 108,3%
81
100
POWER LEVER ANGLE
The RTO (Reserve Take-Off) is obtained in case of up trim (one engine out during take off) or with the PL to the ramp
– RTO
PWR = 2400 SHP
NP=100%
TQ = 100%
165
S y s t e m s 4 2/72 - 6 0 0
3. Engine indication
ATA 31
Power Management selection
Analogic indication
RTO Torque at TO
Objective TQ in MCT CLB CRZ
hWdZ/D
ATPCS uptrim
activation
GO Around Torque
ϵϭ͘ ϭ
ϭϬϮ ͘ ϱ
ϭϮϱ ͘ ϲ
ͲͲͲ ͘ Ͳ
,s
> >KW/d,
>KW/d,
EK Zs
Normal
Abnormal
Over-limit
Invalid numeric torque
HBV failure
Discrepancy between EEC and
aircraft configuration
Lo Pitch Normal operation on ground
Lo Pitch Abnormal operation in flight
No Lo Pitch on ground with PL before FI
Lost of propeller control
by one PEC channel
hdK&dZ
Auto Feather activation
Propeller brake is applied
Red line for “S”: limit
during engine start
ͲͲͲ͘Ͳ
EW
й
Red line for “H”: limit
during Hotel Mode
ͲͲͲ͘Ͳ
NP information
ϵϬ ͘Ϭ
ϭϭϬ ͘Ϭ
ϭϮϮ ͘Ϭ
ͲͲͲ ͘ Ͳ
166
Normal operation
Abnormal operation
Red limit
NP invalid signal
ϱϬϬ
ϴϬϬ
ͲͲͲ ͘ Ͳ
ϵϵϵ
ITT numeric counter
ITT invalid signal
Q. Power plant
ϲϬ
Normal
Ϭ
ϵϬ
ϭϵ͘ϱ
Normal transient range
ϴϭ͘Ϭ
Normal operating range
ϲϬ
Ϭ
ϭϯϳ
Amber
exceedance
ϲϬ
Ϭ
Amber exceedance range
ϭϭϬ͘Ϭ
Red limit
ͲͲͲ͘Ͳ
Invalid data
ϲϬ
ʹϯϱ
Ϭ
ϭϵϬ
ϭϬϰ͘Ϭ
ϲϬ
Red limit
Ϭ
ϭϬϬ͘Ϭ
ϭϬϱ
ϭϲϰ ͘Ϭ
ͲͲͲ ͘ Ͳ
ͲͲͲ͘Ͳ
Normal
ϯϭ
ϲϯ
ϭϬϬ
Amber exceedance range
Red limit
Invalid data
E>
й
ͲͲͲ͘Ͳ
NL information
Amber
exceedance
Red limit
KG/H or LBS/H
> &h>
ʹʹ ʹ
Normal operating range
Invalid data
ϭнϮ
ϯϵϰ
ͲͲͲ Ͳ
> ^dZd
Start in progress
^dZd
Fault occurs during a start
sequence
^dZd
Start invalid signal
y^dZd&/> Cross start failed flag
y^dZd&/> Cross start failed invalid signal
&>Kt <'ͬ,
ϭϮ͘Ϭ
<'ͬDE
The fuel quantity consumed
by two engines/minute
Fuel flow unit is set to KG/MN
or LBS/MN
ϵϬ͘Ϭ
ϭϭϬ͘Ϭ
ϭϮϮ͘Ϭ
ͲͲͲ ͘ Ͳ
Normal operation
Abnormal operation
Red limit
NL invalid signal
Fuel CLOG when ΔPSI>25 PSI.
Filter blocked and by-passed when
ΔPSI>45 PSI
Normal indication
Invalid data
Unit or type discrepancy
ϱϬϬ
ϴϬϬ
ͲͲͲ ͘ Ͳ
ϵϵϵ
ITT numeric counter
ITT invalid signal
/'E
ITT is displayed only during start sequence
Red line for “S”: limit
during engine start
Red line for “H”: limit
during Hotel Mode
167
S y s t e m s 4 2/72 - 6 0 0
4. ENG START panel
CRANK
dry motoring (no ignition)
ON
starter engaged. At 45% NH,
light goes off and the starter is
disconnected
START A OR B
on ground, only exciter A or
B is supllied (except for the
position A&B)
In flight regardless of start
selection (A, B or A+B) both
exciters are energized
UNLOCK
PROP BRAKE not fully
locked or not fully released.
After 15 sec: FWS alarm. Also
used to check lock/unlock
time:
– 5 sec. to unlock
– 10 sec. to lock
ATA 61/72
FAULT
Illuminates when:
– remains ON with NH
>45%
or – GCU failure during start
or – starter failure
or – ENG 2 only: ENG START
selector on start position
+ PROP BRK ON + GUST
lock not engaged
ON
Continuous ignition (both A &
B). Memo panel light.
42/72 PEC
READY
engagement or disengag.
conditions are met:
– A/C on ground
– gust lock engaged
– CL on FTH or FUEL S/O
– blue hyd press available
on the prop brake input
>2100psi
– Fire handle not pulled
PROP BRK
Brake fully locked same
indication on the memo panel
5. ENG control panel
ARMING CONDITIONS
PWR MGT sel on TO
+ATPCS pb in
+both PL > 49°
+both TQ > 46% (72) and
> 53% (42)
= (arm green LT illuminated)
ATPCS
– ARM on ground = uptrim +
auto FTR (2.15’’ delay)
– ARM in flight (In case of go
around) = auto FTR only
ATA 61/72
TRIGGER
one TQ below 18%
Cancel: PWR MGT out of TO
or ATPCS pb OFF or at least
one PL retarded below 49°
or both TQ <46% (72) and
< 53% (42)
EEC
acts on stepper motor to
regulate Fuel Flow
FAULT flashing
EEC failure. The fuel flow is
frozen to maintain the power
FAULT steady: EEC failure,
HMU base law = reversion
When FAULT flashing, do not
deselect the EEC.
Retard first, the PL in the
green sector (FAULT become
steady: PL < 52°)
OFF
HMU base law = reversion
168
Q. Power plant
6. PWR MGT panel
BOOST (if installed)
ON
The boost can be selected on ground with the
PL below FI, or in flight after an engine failure.
When the torque is thermodynamically limited ,
the boost increase the torque:
– With PWR MGT in TO by:
– 4.5% up to 4000ft
– 4% above 4000ft
– With PWR MGT in MCT by 4%
The selection of the boost is latched when the
PLs are advanced above FI, and can not be
changed during flight (except in case of engine
failure).
FAULT
For any disagreement between the position
of the push button and the rating of both EEC
(MC+SC+FAULT+ENG BOOST on FWS).
ATA 61/72
PWR MGT
2 co-axial sw. (LH: bottom /
RH: TOP) providing FDAU,
PEC and EEC with basic
power requirements
FAULT
illuminates when both PEC
channels are lost. FWS
OFF
PEC is deactivated and NP is limited at
102,5% if power is sufficient
7. ATPCS test panel
ATA 61/72
ATPCS TEST
selector allows to check the
correct functionning of the
ATPCS.
This rotary selector is spring
loaded to neutral position
8. Idle gate
IDLE GATE FAIL
light illuminates amber and the FWS
is activated when the gate does not
engage automatically in flight or does
not retract at landing
ATA 61/72
IDLE GATE LEVER
enables manual override
in case of failure of the
automatic logic or no DC
power.
In flight: push
On groung: pull. A red band
appears
169
Annexes
171
Annexes
Annex 1. Cockpit panels
SQUIB TEST
Elect test of squibs.
FAULT
resistance/capacitance.
Inhibits fire signals until turned
off.
LOOP on FWS (DC EMER)
SQUIB
armed when T handle pulled.
Discharges bottle.
(DC EMER / HOT MAIN BAT).
DISCH
bottle depressurized. Opposite
agent DISCH Lt will also
illuminate on other fire panel.
TLU FAULT
system disagree / two
ADC failures / ADC datas
incoherence / TLU position
synchro failure. T/O or T/O
Config Test and TLU not LO
SPD
TLU manual operation
Above 195 kts (42) / 185 kts
(72): HI SPD
Below 190 kts (42) / 180 kts
(72): LOW SPD
SPLR
activates when >2.5° aileron
travel. Lt ON=Spoiler not fully
retracted (BLUE HYD PWR).
Light on when SW
TEST depressed and all
door microsws opened.
(Passengers and service doors
opened)
At least 1 microsw is opened.
(DC BUS 2)
Tests continuity of microsw.
System (on ground, doors
opened).
Fuel delivery pressure below
4 PSI. Pump failure or fuel
starvation. FWS.
ENGINE FIRE HANDLE
Pulled: on the respective engine
Prop
Feather
Fuel
LP valve closed
Air
Bleed valve closed
Deice
Deice & shutoff valve closed
Elect
DC & ACW gen. disconnected
Squibs Armed (Lts illuminated)
Hydraulic Hyd prop brake (eng 2 only)
Fire test
MW+CRC+ ENG 1 FIRE on
EWD and FWS
+Fire handle illuminated
+FUEL S/O Lt on CL (if out of
Fuel S/O position)
Fault test
MC+SC+ loop on FWS
FAULT Lts on A/B Loop pb.
OFF
Takes respective loop out of
parallel circuit. Allows other
loop to activate fire signal.
The opening of the cargo door
control panel cover. Self Test
of MFC 1A/2A.
FAULT
Malfunction or electrical supply
fault: AUTO disengagement
– FWS
Gear position secondary
system as sensed by MFC 2.
UNLK
gear not in selected position or
uplock not opened (on Gnd)
Green Lt
down lock engaged
Controls XFEED valve.
Activates both elect fuel
pumps.
Controls elect pump power
supply and jet pump motive
flow valve.
Runs automatically if:
Jet pump press <5 PSI
or Xfeed in line
or Fuel LO LVL
– <160 kg
– >160 kg (with feeder
tank not full)
or During Fuel Quantity test
Shows position of valve.
No bar = valve fault or moving.
RUN
Illuminates green when elec
fuel pump is running.
OFF
disconnect the elect pump
and force to close the motive
flow valve
Both domes (DC BUS 1)
F/O only in basic mode (DC
EMER).
To call cabin from cockpit (SC)
To be called by cabin
attendant: cyan Lt and door
bell.
Cancelled when pressing
RESET pb.
To call mechanic= HORN is
activated .
To be called by mechanic:
Cyan LT and Door Bell.
Cancelled when depressing
RESET Pb
Use in basic mode to limit Lts
in cabin.
Light on the RH side only.
Main Instruments Panel (MIP)
lights under glareshield are set
to the maximum intensity.
Do not use above 160 kts.
ESS BUS.
173
S y s t e m s 4 2/72 - 6 0 0
UNDV
DC STBY <19.5V. FWS.
OVRD
Transfert of STBY buses from
HOT MAIN to HOT EMER BAT
BUS.
INV FAULT
Inv failure or supply loss AutoXfer of all AC buses to remaining
inverter. FWS.
Emergency supply indicators
(Amber arrows) (Respective
battery discharging).
ON
Pb pressed IN (ON illuminated
CYAN). TRU is connected
to ACW BUS 2 – ARROW
illuminates green when supply
of DC EMER BUS, DC STBY
BUS, INV 1 (AC STBY BUS)
and DC ESS BUSS from TRU is
effective.
FAULT
Battery charger failure detected
by MFC. FWS.
Contactor Auto opens (MFC) if:
thermal runaway/ Bus voltage
<25V / start sequence / Bat sw
on OVRD.
Respective bus not supplied.
FWS.
SHED
One of the DC SVCE / UTLY 1
and 2 busses is shed (BPCU).
FWS.
OFF: all the DC SVCE BUS/
UTLY 1 and 2 busses are shed
Opposite generator has not
come on line to assist start at
10% NH (on ground only).
Generator FAULT LT
Extinguishes above 61.5% NH if
GEN is operating normally.
ON
started engaged. At 45% NH,
light out, starter disengages
automatically.
CRANK
dry monitoring (no ignition).
START
selects a start sequence.
In flight regardless of start
selection (A, B, A+B) both
exciters are energized.
Prop Brake not fully locked or
not fully released. After 15 sec
= FWS.
Supplied by ACW.
On external power, pedestal PB
must be on to power CVR test
Associated bus deenergized.
FWS.
OVRD
insures basic mode operation by
overriding all other protections.
ON
Basic mode: STBY Busses
supplied by HOT MAIN BAT BUS.
EXT or GEN power: DC
STBY BUS transfered to HOT
EMER BAT BUS; AC STBY
BUS to DC BUS 1.
OFF
ESS BUS, DC STBY BUS +
INV 1 are isolated from HOT
MAIN BAT BUS.
DC EMER BUS is isolated
from HOT EMER BAT BUS.
Allows BPCU to control BTC
operation (Bus Tie Contactor).
Ext power, Hotel mode or
single gen operation. BTC is
closed (green flow bar).
ISOL
BTC opened (released out).
BTR (Bus Tie Relay) locked
open (Tie between AC Busses)
AVAIL
GPU has been checked by
BPCU for over/under voltage,
over current and polarity.
AVAIL+ON
The GPU supplies the
electrical system. GPU has
priority on both generators.
FAULT
Protection triggered by GCU.
Auto reset if underspeed: in
other cases manual reset.
BTC auto closes
FAULT
illuminates when:
starter remains ON with
NH>45%
or GCU failure during start
or starter failure
or ENG2 only PROP BRK
ON+Gust lock not engaged
(Starting not inhibited).
ON
Continuous ignition (both A & B).
Memo panel display label.
READY
engagement or disengagement
cond. Are met:
– A/C on ground
– gust lock engaged
– CL on FTH of FUEL S/O
– blue hyd press > 2100 PSI
– fire handle not pulled
PROP BRK
Prop brake fully locked. Memo
panel display label.
Supplied by DC SVCE BUS
(Back up DC BUS 1).
Supplied by DC BUS 2.
174
Annexes
Main BLUE PUMP
Supplied by ACW, controlled by DC
EMER BUS.
Main GREEN PUMP
Supplied by ACW, controlled
by DC ESS BUS.
AUX PUMP
Running conditions:
– AUX PUMP pb depressed
– at least one engine running
– blue system press <1500psi
– prop brake off
– gear lever down
(supply: DC BUS 2 or HOT MAIN BAT
BUS)
XFEED
PB released. Xfeed closed
PB pressed: ON LT illuminated
CYAN, Xfeed valve selected
OPEN. (Except in case of LO
LVL where the Xfeed is locked
closed)
LO PR
pump delivery pressure less
than 1500 psi. FWS. No auto
off has to be switched off
manually.
OVHT
Temp >121°C (250°F). FWS (no auto off)
Associated bus not supplied
LO LEVEL
associated compartment <2,5 lt
FWS. Xfeed opening inhibited.
AVAIL
GPU has been checked by BPCU
AVAIL + ON
GPU supplied ACW system. GPU has
always the priority on both GEN
BTC
Allows BPCU to control BTC
operation.
Ext Pwr or simple GEN
operation: BTC is closed
(Green Flow BAR).
Auto closure when either ACW
GEN drops off line.
AUTO reset in case of under/over speed:
manual reset otherwise. ACW SVCE
BUS auto shed if one GEN is out.
ALPHA
ACW supply
Amber LT illuminates in case of Failure
or Pwr loss. FWS.
ISOL
BTC opened (Pb released out).
Min Np for ACW= 66%.
TAT
no heated. FWS (ACW supply). Heating
inhibited on ground.
FAULT
Power loss or failure; FWS.
PITOT
tube not heated. FWS (ACW BUS for
CPT & F/O).
STAT
Static source not heated or
failed. FWS on ground only
(DC BUS). (no alarm in flight)
PITOT STBY
not heated (FWS).
ACW bus 1 or 115 AC STBY BUS as
back up.
ON
ACW supply (inhibited when NP <63%).
ON
FAULT
power loss on at least 1 Blade.
FWS.
FAULT
Defog only.
for power loss or failure; FWS
(DC BUS).
NORM
10 sec on per 3 blades; then 10 sec off
between cycles.
ON
HIGH POWER
20 sec on per 3 blades. No stop between
cycles (ON LT illuminates cyan).
ON
ACW supplied. Horns heating
inhibited on ground; either
horn activates AOA light.
FAULT
Power loss. FWS.
MODE SEL AUTO
Automatic selection of cycle depending
on ADC1/2 input to MFC1B/2B.
FAULT
valve opened but no
downstream press. OR valve
closed and downstream press
detected. FWS.
FAULT
when ADC or MFC or CPM/IOM fail
Fast mode is automatically selected for
ENG and AIRFRAME DEICING and High
Power for Prop Anti-ice.
ON
signal sent to MFC to start
deice cycle on the airframe.
MAN
mode enables manual selection of
cycles depending on SAT (MAN
illuminated CYAN).
FAULT
both MFC modules controlling
boots have failed resulting
in an incorrect inflation
sequencing.
DEICE air is always available regardless
of bleed pb.
FAST: 60 sec / cycle
SLOW: 240 sec / cycle (SLOW
illuminates cyan)
FAULT
distribution valve opened but no air press.
OR valve closed and press. Detected
OR air temp upstream of the deice valve
>230°C for more than 6 sec.
ON
deice valve opened even if AFR
AIRBLEED off.
OVRD
no MFC. Boots inflated by a
separate standby controller.
Fast cycle only (cycle 60°).
ON
emergency exit lights illuminated.
Supply: 6V Bat packs.
Cyan labels
on MEMO
panel display
when ON (DC
BUS2).
ARM
– lights on if DC STBY BUS <18V
– lights off if DC STBY >20V
– or in case of dual DC GEN loss
DISARM
system desactivated
FAULT
Air downstream deice valve
<14 psi more than 10 sec. Air
upstream deice valve >230°.
FWS.
OFF
isol valves closed. Deice valves
closed unless ENG 1/2 deice on.
175
S y s t e m s 4 2/72 - 6 0 0
Tests all three smoke
detections (elec. fwd.
aft smoke Red alarms in
FWS+MW+CRC).
Stops extract fan, only on
ground (FAULT on EXHAUST
MODE).
To restart extract fan it is
necessary to reset EXHAUST
MODE Pb
PB in: Crew supply only.
If below 1400 psi, use table.
NORM
– On ground, ENG 1 off:
extract fan on. Ovbd valve full
open, U/F valve closed.
– On ground, ENG 1 on :
extract fan on. Ovbd valve
closed, U/F valve opened.
FAULT
Fan failure / overheat (fan
inhibited for 120s after every
eng start. FWS).
OVBD
Extract fan off. OVBD valve
partially opened (in flight only).
U/F valve closed.
Duct temperature limited to
88°C. (191°F) by pneumatic
temp limiter.
NORM: 22 psi
HIGH: 30 psi
regulated by pack valve
Spring loaded closed. Ground
only. Auto opens when only 1
Bleed valve is opened.
Controls both Bleed and HP
valves. Spring loaded closed.
Must have air & elec to open.
Auto Bleed valve closes when
Ovht, Leak, Overpressure
(>80 psi), Fire T pulled, when
UPTRIM is triggered or prop
brk on (left one only). Inhibited
during eng start.
FAULT
Bleed valve disagreement
with selected position (case of
Ovht, Overpressure or Leak).
FWS. Associated valves auto
closed.
OVHT
either bleed duct temp thermal
switch above 274°C. FWS.
Associated valves auto closed.
May be reset after cooling.
Do not use above 160 knots.
DC BUS 2.
176
FAULT
fan inop. FWS.
ALTN
activates altn fan.
LO PR
supply below 50 psi.
ON
25% of Pax are supplied.
FAULT
Ovbd Valve in disagreement
with Ovbd Valve SW position.
AUTO except for emergency.
In emergency, the full open
position is possible only if the
Delta P is < 1 psi
Assists pack air flow.
FAULT
Fan low speed or motor
overheat. FWS. No auto
deselected.
OVHT
Duct overheat > 92°C. FWS.
Pack valve will not auto close.
MAN
Compt temp knob controls
directly temp control valve.
Selects the zone where T°
check is desired.
PACK VALVE
Spring loaded closed. Must
have air pressure and select
power to open (6 sec delay on
RH pack for pax comfort).
FAULT
pack valve disagreement with
PB or Ovht downstream of
pack comp (>204°C). FWS.
Valve auto closed.
LEAK
activates when temperature
detected by bleed loop
exceeds 156°C. FWS. Auto
closure after 1 sec of following
valves: Bleed, HP, PACK and
GND XFeed. DO NOT RESET
BLEED.
Tests all lights.
Ldg Elev indicators show all
8 segments.
Annexes
Menu P/B
Enable sub function selection
menu
Brightness
SEL P/B
Change cursor selection
between VHF COM, VHF NAV,
BARO SETTING and COURSE
when VOR mode.
BOOST (if installed)
ON
The boost can be selected
on ground with the PL below
FI, or in flight after an engine
failure.
When the torque is
thermodynamically limited, the
boost increase the torque:
– With PWR MGT in TO by:
– 4.5% up to 4000ft
– 4% above 4000ft
– With PWR MGT in MCT by
4%
The selection of the boost
is latched when the PLs are
advanced above FI, and can
not be changed during flight
(except in case of engine
failure).
FAULT
For any disagreement between
the position of the push
button and the rating of both
EEC (MC+SC+FAULT+ENG
BOOST on FWS).
FAULT
stick shaker or pusher failure.
OFF
turns off both shaker and pusher
STD P/B
Reset at 1013.25Hpa, when
pushed more than 0.2 sec.
IESI (Integrated Electronic
Stantby Instrument) displays
the following information:
– Attitude
– Airspeed
– Altitude
– Baro pressure setting
– VHF 1
– VOR/ILS 1
SET ROTARY SWITCH
– Sub fonction menu scroller
– Baro setting
– VHF com tuning
– VHF nav tuning
– Course setting in VOR mode
PWR MGT
2 co-axial sw, (LH: Bottom/RH:
Top) providing FDAU (MPC),
PEC, PIU and EEC with basic
power requirements.
FAULT: illuminates when both
PEC channels are lost FWS.
OFF: PEC is deactivated and
Np is limited at 102.5% by the
overspeed governor if power
is sufficient.
APM FAULT
Failure in the APM function
computation
APM Test PTT
performed daily
PTT pb
press for 3 sec.
– icing will flash on the display
if system works correctly
(steady if ice detector failure is
detected).
– FAULT LT illuminate.
A-ICING DETECT is
displayed steady on the FWS.
ICING AOA Lt
illuminates green as soon
as 1 horn anti-icing ON.
Stall alarm (stick shaker
threshold lowered). It can be
extinguished manually only by
releasing ICING AOA Pb (DC
EMER) provided both Horns
anti-icing selected OFF.
177
S y s t e m s 4 2/72 - 6 0 0
Panel with EWD format.
Arming conditions:
PWR MGT sel on TO
+ATPCS pb in
+ both PL >49°
+ both TQ > 53%(42)
both TQ > 46% (72)
ARM green LT on.
ATPCS
– ARM on ground = uptrim +
auto FTR (2.15” delay)
– ARM in flight (In case of go
around) = auto FTR only.
UPTRIM
signal sent to respective
eng during ATPCS
sequence.
Eng power = RTO.
ATPCS
Trigger
one TQ <18% (42)
one TQ <18% (72).
Cancel
PWR MGT out of TO
or ATPCS pb OFF
or at least one PL retarded <49°
or both TQ <53% (42) and <
46% (72)
EEC
acts on stepper motor, to regulate
Fuel Flow.
TORQUE Ind display
2 probes sending info:
– to pointer (via AFU).
– to digital counter (via
EEC).
FAULT flashing
EEC Failure. The fuel flow is frozen
to maintain the power. (Do not
deselect EEC when flashing)
The PL has to be retarded to the
green sector before deselection of
the EEC
Internal bug
computed by FDAU (MPC);
shows RTO when PWR
MGT on TO, otherwise
max TQ depending on
PWR MGT selection.
FAULT steady
EEC Failure. HMU base law =
reversion. Fault become steady
when the PL is retarded in the
green band.
OFF
HMU base law = reversion.
Trim indicator display.
LO PITCH
blade angle < 8° (below
FI).
Primary engine
parameters display
Brake messages and
test status display
Permanent Data
display
Flaps indicator display
ITT Ind Display
> 800°C (or > 715°C on
ENG2 in hotel mode).
FWS.
NP Ind display
Alert window
TAT-SAT indicator
ELAPSED TIME
When the ELAPS TM P/B
(right side of the F/O) is
depressed ON the flight
time starts automatically
when airborne
178
Procedure window
FUEL USED Readout
DISPLAY UNIT 3 (DU3)
In the normal configuration,
the EWD format is displayed.
Annexes
Gear position sensed by system I (MFC 1A)
ANTISKID
Operative if speed >10 kts.
Activates when speed >23 kts
+ 50% diff between wheels
(locked wheel protection).
Braking action inhibited at
touchdown as long as wheel
spin up speed <35 kts or
5 sec. (touchdown protection).
CAUTION: THE TEST
INHIBITS BRAKES
TEST pb
(inhibited if speed >17 kts)
= MC + SC EWD 4 amber F
on EWD.
Test duration: 3 sec. in flight
and 6 sec. on ground
Gear handle red Lt
any gear not sensed down
and locked with the further
conditions:
a) Any gear not down and
locked + flaps normal landing
configuration + Zra <500 ft +
PL at low power (impossible
to cancel)
b) Any gear not down and
locked +1 PL at low power +
Zra < 500 ft.
OFF
Pb released, system
deactivated
NOTE: Any gear not down must
be sensed by each MFCs
UNLOCK
gear not locked in handle
selected position (on ground,
up lock box not open)
Green Lt
gear downlock engaged
AUTO PRESS (DC BUS 1)
+550 ft/mn up to FL 200
+620 ft/mn above FL 200
Memorizes departure field elev
up to 3500 ft
ELV SET
Select switch to set landing
elevation
FAST
descent rate increased from
–400 to –500 ft/mn
To be used if VS>-1500 ft/mn
NORM
AUTO mode selection
MAN
digital controller out of
operation. No more digits in
landing elevation display
TEST
displays alternatively 18800
and –8800, FAULT appears on
MAN pb
(Test inhibited in FLT)
FAULT
digital controller failure. FWS
DUMP
ON (guarded)
both outflow valves fully open
in AUTO mode only
ON
both outflow valves
forced to fully closed
CABIN RATE KNOB
NORM
AUTO MODE position. When
used in MAN mode, cabin rate
selection +2500/–1500 ft/mn
179
S y s t e m s 4 2/72 - 6 0 0
MCDUs (Multifunction
Control Display Unit)
Access to the FMS, MPC, and
ACARS (Data Link) when the
ACARS is installed.
WEATHER RADAR
CONTROL PANEL
COCKPIT DOOR CONTROL
PANEL
Allows to control CDLS
(Cockpit Door Locking
System)
MULTIPURPOSE CONTROL
PANEL (MCP)
Allows cockpit crew to control
the virtual control panel format
(VCP) on MFD
POWER LEVER ( PL )
EMER & PARKING BRAKE
CONDITION LEVER (CL)
GA push button
when depressed the GA FD
mode is selected with:
– HDG HOLD lateral mode
with the wings level
– GA vertical mode
EMER AUDIO CANCEL
This SW cancels an undue
aural alert.
Cancelled aural warning will be
reactivated:
– at next A/C energization
– after MFC 1B/2B reset
– after pressing RCL pb
– following TO config test
The alerts here after are
rearmed as soon as the
triggering condition disappears
– landing gear
– VMO, VFE, VLE
– Stall warning
– Pitch trim whooler
– AP disconnect
HYD AUX PUMP CONTROL
(HOT MAIN BAT BUS)
– Aux pump stopped 30” after
p/b released (MFC supplied)
– Aux pump stopped after p/b
released (MFC not supplied)
IDLE GATE
IDLE GATE FAIL
activated when the gate does
not engage automatically
in flight or does not extend
automatically on ground
In this case the idle gate lever
enables manual override in
case of failure of the automatic
logic
– In flight: push
– On ground pull (an amber
band appears)
F/O AUDIO
CONTROL PANEL
Manual recording on
DFDR or CVR (when
supplied by GPU)
Manual recording
stopped with the
reset P/B
EFis Control Panel (EFCP)
Allows to control:
-Display of the MFD pages
(ND, SYST, PERF, MISC, VID
and MAP)
-Navigation Display (ND)
functionalities
-Warning Display (WD)
CAPT AUDIO
CONTROL
PANEL
180
FLAPS
TO CONFIG TEST pb:
Check if the TO configuration
is correct for take off:
– PWR MGT TO
– Flaps 15°
– Pitch trim in the green band
– TLU LO SPD
– no AIL LOCK light
The same test is performed
when advancing the PL with
this additional requirement:
– Parking Brake released
ACARS & MPC
PRINTER
Panel & flood
light control
Aileron, rudder &
stby pitch trims
ATPCS test (static
or dynamic)
Annexes
FD lateral mode
FD vertical mode
NAV SOURCE Selector CAPT
side
Selects the NAV SOURCE for CAPT
EHSI and/or ND depending on
display configuration
ALT knob controls the
preselected altitude on the
PFD
NAV SOURCE Selector F/O side
Selects the NAV SOURCE for F/O
EHSI and/or ND depending on
display configuration
FD bars ON/OFF switch
Chrono P/B
Start/Stop/Zero
Chrono P/B
Start/Stop/Zero
CRS 1 knob selects
Course on CAPT EHSI
STBY COMPASS
Hidden in up position. Compass
Control should be place on DN
For use. The compass rose is
graduated in 10 degrees
increments
Pitch wheel to adjust
– VS or
– Pitch attitude in basic
mode
CRS 2 knob selects
Course on F/O EHSI
and ND
– AP pb engages autopilot and
yaw damper and disengages
only autopilot
HDG knob selects HDG bug
on both EHSI and ND
– YD pb engages yaw damper
and disengages yaw damper
and autopilot if engaged
– CPL pb permit to couple AP/FD
On CAPT or F/O side
In CAT 2 (ILS selected on NAV 1&2)
– 1200 ft RA: Dual coupling < >
– 800 ft RA: CAT 2 invalid if still in single
coupling
– 500 ft RA: ILS excess dev activated
– 100 ft RA: GS excess dev deactivated
181
S y s t e m s 4 2/72 - 6 0 0
TAWS
TAWS visual alert
GPWS
If any TAWS mode is activated
PULL UP
Alert triggered after the GPWS
alert in mode 1, 2 and terrain and
obstacle awareness modes
GPWS switch and associated lights:
ON: All basic GPWS modes are operative
FLAP OVRD: In reduced flaps landing, to inhib the
mode 4 alert
OFF: All basic GPWS modes inhibited. OFF: light
come on
FAULT: GPWS FAULT ——
> some or all GPWS basic
modes are lost
FAULT: TERR FAULT ——
> some or all enhanced
modes are lost
OFF: All enhanced (TCF&TAD) modes inhibited
AHRS switching P/B
To select the opposite side AHRS
source.
When depressed, SYS 2 is
illuminated on CAPT side, while
CAPT / 2 is illuminated green on
F/O side
The CAPT P/B has priority
ACARS message
ATC DLK (ATC Data LinK) is
illuminated when a message is
received through the ACARS.
The message can be read on the
MCDU
MASTER WARNING
MASTER CAUTION
Display P/B
The P/B allows to switch formats
(PFD/EWD/MFD) on the DU2, or
on DU1 if DU2 is OFF.
ADC switching P/B
To select the opposite side ADC
source.
When depressed, SYS 2 is
illuminated on CAPT side, while CAPT
/ 2 is illuminated green on F/O side
The CAPT P/B has priority
MFD upper window
Displays the different
pages selected on the
EFCP:
– ND page (Navigation
Display: shown here)
– SYST page (System)
– PERF page
(Performance)
– MAP page (airport
mapping)
– MISC page (in
provision)
– VD page (Video in
provision)
ND page
(Navigation
Display)
Different mode
selected on the
EFCP:
– ARC mode
– ROSE mode
– PLAN mode
STEEP APP P/B (optional)
When selected ON, moves
the mode 1 threshold, to
avoid TAWS triggering in
steep slope approach
AUDIO 1 SEL
FAULT: When the associated
RCAU part is failed.
ALTN: Affected crew station is
connected directly to VHF1 if
CAPT station is affected.
Index Control Panel (ICP)
Baro setting control
Index Control Panel (ICP)
Speed target control
DISPLAY UNIT 1 (DU1)
In the normal configuration,
with CAPT as PF, the PFD
format is displayed
182
Memo Panel Display
Displays the following system
information when selected
FUEL XFEED
PROP
HORN
SIDE WINDOW
ENG
AIFRAME
NO DEVICE
SEAT BELT
VCP window (Vitual Control
Panel)
Displays the informations about:
The COM selection
The NAV selection (shown here)
The SURV (surveillance) selection
DISPLAY UNIT 2 (DU2)
In the normal configuration, with
CAPT as PF, the MFD format is
displayed with the ND page.
The FMA 1 (Flight Management
Application 1) and the RMA 1 (Radio
Management Application 1) are
included in the DU2 functions
Annexes
MFD upper window
Displays the different pages
selected on the EFCP:
– ND page (Navigation
Display)
– SYST page (System: shown
here)
– PERF page (Performance)
– MAP page (airport mapping)
– MISC page (in provision)
– VD page (Video in provision)
Display P/B
The P/B allows to switch
formats (PFD/EWD/MFD) on
the DU4, or on DU5 if DU4 is
OFF.
Airspeed Indicator (ASI)
Flight Mode Annuciator (FMA)
MASTER WARNING
MASTER CAUTION
ELAPSED TIME P/B
When the ELAPS TM P/B is
depressed ON
the flight time starts
automatically, on the EWD,
when airborne
Attitude Display Indicator (ADI)
Altimeter
ADC switching P/B
To select the opposite side
ADC source.
When depressed, SYS 1
is illuminated on F/O side,
while F/O /1 is illuminated
green on CAPT side
The CAPT P/B has priority
Vertical Speed
Indicator (VSI)
SYST page (System
page)
Different mode selected
on the EFCP:
– ACW-HYDRAULIC
– ENGINE (secondary
engine display)
– CABIN (shown here)
– AC-DC ELECTRIC
CLOCK
AHRS switching P/B
To select the opposite side
AHRS source.
When depressed, SYS 1
is illuminated on F/O side,
while F/O /1 is illuminated
green on CAPT side
The CAPT P/B has priority
LOUDSPEAKERS
VOLUME KNOBS
Individual knob for
each loudspeaker
VCP window (Vitual
Control Panel)
Displays the
informations about:
The COM selection
(shown here)
The NAV selection
The SURV (surveillance)
selection
DISPLAY UNIT 4 (DU4)
In the normal configuration, with
F/O as PM, the MFD format is
displayed with the SYST page.
The FMA 2 (Flight Management
Application 2) and the RMA 2
(Radio Management Application
2) are included in the DU4
functions
DISPLAY UNIT 5
(DU5)
In the normal
configuration, with F/O
as PM, the PFD format
is displayed.
Navigation Area
With the ND on the
MFD, the EHSI is
displayed on the PFD.
With an other page on
the MFD, a mini ND is
displayed on the PFD.
The mini ND can be in
ARC mode or ROSE
mode, selected on the
EFCP.
Index Control Panel
(ICP)
Speed target control:
– Speed target selection
Selection of the speed
bug between:
– AUTO: Speed bug
managed by the FMS
(Magenta)
– MAN: Speed bug set
manually by the speed
knob (Cyan)
– Speed knob
Used to set the speed
bug
In MAN mode (Cyan)
Index Control Panel
(ICP)
Baro setting control:
– Barometric setting
knob
The knob is used to set
the barometric reference.
Pushing the knob sets
standard barometric
reference (29.92 INHG /
1013.25 Hpa)
– DH / MDA knob
Outer knob permits
to select between DH
(Decision Height) or MDA
(Minimum
Descent Altitude).
Inner knob is used to
set DH or MDA values,
depending of the outer
knob position.
READING LT knob
Control the
respective spot light
CONSOLE LT knob
Control the lights of
the associated lateral
console
AUDIO 2 SEL
FAULT: When the
associated RCAU part is
failed.
ALTN: Affected crew
station is connected
directly to VHF2 if F/O
station is affected.
183
S y s t e m s 4 2/72 - 6 0 0
Parking/emergency braking
accumulator pressure indicator
This indicator is used when the
MFDs are not energized, to check
brake accumulator pressure.
When the switch is activated,
the indicator is energized for two
minutes
When the accumulator pressure
is <1700 psi or >3100 psi, the
indicator displays blinks.
N/W STEERING
ON: The steering solenoid valve is
electrically armed.
The steering is available with an
angle up to 60° in either direction
OFF: The steering system is
unpressurized. Should be OFF for
towing and push back
The steering is disconnected
with an angle up to 91° in either
direction
Nose wheel steering Push To Talk
When depressed, BOOM SET or
OXY mike is connected for
transmission over the selected
communication facility
Test & Reset slider
Blinker indicator
Normal/100% selector
RH red grips (inflate harness)
Emergency rotaty knob
Position of the selector:
EXT PWR
DC panel indicates the DC GPU voltage & current
AC panel indicates the AC GPU voltage, load &
current
GEN 1/ 2
DC panel indicates the DC Generator voltage &
current
AC panel indicates the ACW Generator voltage,
load & current
INV 1/ 2
No indication on DC panel
AC panel indicates the AC Inverter voltage, load
& current
MAIN and EMER BAT
DC panel indicates the DC Main & Emer Battery
voltage & current
No indication on AC panel
PRELIMINARY COCKPIT PREPARATION: OXYGEN MASK TEST
INT/RAD SELECTOR (On AUDIO CONTROL PANEL) .................................SET TO INT
PRESS TO TEST AND RESET PB ............................................. DEPRESS AND HOLD
NOTE: Hose and mask charged with oxygen. Observe blinker momentarily turns yellow and
must turn dark if there is no leak
PRESS TO TEST AND RESET PB ...................................................................... HOLD
RED GRIPS ON EACH SIDE OF THE HOSE ......................................................PRESS
NOTE: Oxygen pressure inflates the harness. Observe blinker momentarily turns yellow and
must turn dark
PRESS TO TEST AND RESET PB ...................................................................... HOLD
EMERGENCY KNOB ....................................................................................... SELECT
NOTE: Emergency flow is tested. Observe blinker momentarily turns yellow during oxygen
flow and must turn dark when the knob is released.
NOTE: In this 3 cases, check that oxygen flow sounds though loudspeakers
OXY LO PR LIGHT ................................................................. CHECK EXTINGUISHED
N/100% Selector ..................................................................................... SET to 100%
184
Annexes
FLIGHT DECK VENTILATION ISOLATION
EXTRACT AIR FLOW
CAUTION: Close only in case of FWD COMPT
smoke
Enables, in case of smoke in the forward cargo
compartment, to isolate the flight deck ventilation
preventing smoke to enter the flight compartment
BITE LOADED magnetic indicator
Indicates that a failure has been
recorded by the maintenance system.
Report to maintenance
MAIN PNL
Before the flight, check that all the
switch and selector are in the normal
position.
If not, the MAIN PANEL is displayed
on the FWS
BRK TEMP TEST
When depressed, MC, SC,
WHEELS BRK HOT on FWS
185
Annexes
Annex 2. Abbreviations
A
AAS
AC
A/C
ACARS
AC BTC
AC BTR
ACW
ADC
ADF
ADI
ADN
ADS
AFCS
AFDX
A/FEATH
AFCA
AFT
AFU
AGB
AHRS
AHRU
AIL
ALT
ALTM
ALTN
AMP
AOA
AP
APP
APU
APAU
ARINC
A 429
ARM
ASI
ASYM
ATC
ATPCS
ATT
ATTND
AUTO
AUX
AVAIL
Anti-icing Advisory System
Alternating Current
Aircraft
ARINC Communication Addressing
and Reporting System
AC Bus Tie Contactor
AC Bus Tie Relay
Alternating Current Wild Frequency
Air Data Computer
Automatic Direction Finder
Attitude Director Indicator
Avionic Data Network
Air Data System
Automatic Flight Control System
Avionic Full DupleX
Auto Feathering
Auto Flight Control Application
Rear Part
Auto Feather Unit
Accessory Gear Box
Attitude and Heading Reference
System
Attitude and Heading Reference Unit
Aileron
Altitude
Altimeter
Alternate
Ampere
Angle of Attack
Auto-Pilot
Approach
Auxiliary Power Unit
AutoPilot Actuator Unit
Aeronautical Radio INCorporated
ARINC 429
Armed
Air Speed indicator
Asymmetry
Air Traffic Control
Automatic Take off Power Control
System
Attitude
Attendant
Automatic
Auxiliary
Available
B
BARO
BAT
BC
BITE
BPCU
BPU
Barometric
Battery
Back Course
Built in Test Equipment
Bus Power Control Unit
Battery Protection Unit
BRG
BRK
B-RNAV
BRT
BTC
BTR
Bearing
Brake
Basic Area Navigation
Bright
Bus Tie Contactor
Bus Tie Relay
C
CAB
CAC
CAPT
CAT
C/B
CDI
CDLS
CHAN
CHC
CL
CLA
CLB
CLR
CMA
CMS
CMPTR
CMU
COM
COMPT
CONFIG
CPL
CPM
CRC
CRS
CRZ
CTL
CVR
Cabin
Core Avionic Cabinet
Captain
Category
Circuit Breaker
Course Deviation Indicator
Cockpit Door Locking System
Channel
Charge Contactor
Condition Lever
Condition Lever Angle
Climb
Clear
Centralized Maintenance Application
Cabin Management System
Computer
Communication Management Unit
(ACARS)
Communication
Compartment
Configuration
Auto Pilot Coupling
Core Processing Module
Continuous Repetitive Chime
Course
Cruise
Control
Cockpit Voice Recorder
D
DC
DCA
DELTA P
DEV
DFDR
DGR
DH
DIFF
DISCH
DIM
DIST
DLK
DME
DMU
DN
DSPL
DU
Direct Current
Data Concentration Application
Differential Pressure
Deviation
Digital Flight Data Recorder
Degraded
Decision Height
Differential
Discharge
Light Dimmer
Distance
Data LinK
Distance Measuring Equipment
Data Management Unit
Down
Display
Display Unit
187
S y s t e m s 4 2/72 - 6 0 0
E
EEC
EFCP
EFIS
EHSI
EHV
ELEC
ELV
EMER
ENG
EQPT
ESS
ETOPS
EWD
EXT
H
Engine Electronic Control
EFis Control Panel
Electronic Flight Instrument System
Electronic Horizontal Situation
Indicator
Electro Hydraulic Valve
Electrical
Elevation
Emergency
Engine
Equipment
Essential
Extended Twin Operations
Engine & Warning Display
Exterior, External
F
F
FAIL
FAP
FCOC
FCU
FD
FDA
FDAU
FEATH, FTR
FF
FGC
FGCP
FGS
Fl
FLT
FMA
FMA
FMS
F/O
FOS
FQI
FT
FU
FWD
FWS
Farenheit
Failed, Failure
Flight Attendant Panel
Fuel Cooled Oil Cooler
Fuel Control Unit
Flight Director
Flight Data Application
Flight Data Acquisition Unit
Feathered, Feathering
Fuel Flow
Flight Guidance Computer
Flight Guidance and Control Panel
Flight Guidance System
Flight Idle
Flight
Flight Management Application
Flight Modes Annunciators
Flight Management System
First Officer
Flight Operations Software
Fuel Quantity Indication
Foot, Feet
Fuel Used
Forward
Flight Warning System
G
GA
GCU
GEN
GI
GND
GPS
GPU
GRD
G/S
GSPD
188
Go Around
Generator Control Unit
Generator
Ground Idle
Ground
Global Positioning System
Ground Power Unit
Ground
Glide Slope
Ground Speed
HBV
HDG
HF
HI
HLD
HMU
HP
HSI
HTG
HYD
Handling Bleed Valve
Heading
High Frequency
High
Hold
Hydromechanical Unit
High Pressure
Horizontal Situation Indicator
Heating
Hydraulic
I
IAS
ICP
IDT
IESI
IGN
ILS
IMA
IND
IN/HG
INHI
INOP
INST
INT
INV
IOM
ISOL
ITT
Indicated Air Speed
Index Control Panel
Ident
Integrated Electronic Standby
Instrument
Ignition
Instrument Landing System
Integrated Modular Avionics
Indicator
Inches of Mercury
Inhibit
Inoperative
Instrument
Interphone
Inverter
Input Output Module
Isolation
Inter Turbine Temperature
JK
KHZ
KT
Kilo-Hertz
Knot
L
LAT
LAV
LB
LDG
L/G
LH
LMU
LNAV
LO
LOC
LO-PR
LP
LT
LVL
Lateral
Lavatory
Pound
Landing
Landing Gear
Left Hand
Light Management Unit
Lateral Navigation
Low
Localizer
Low Pressure
Low Pressure
Light
Level
M
MAX
MAP
MB
MC
MCDU
MCP
Maximum
Mapping
Millibar
Master Caution
Multifunction Control Display Unit
Multifunction Control Panel
Annexes
MCT
MECH
MFC
MFCU
MFD
MGT
MHZ
MIC
MLG
MIN
MIP
MISC
MKR
MLW
MM
MMO
MOD
MPC
MPU
MSG
MSN
MTOW
MW
MZFW
Maximum Continous
Mechanic
Multi Function Computer
Mechanical Fuel Control Unit
Multi Function Display
Management
Megahertz
Microphone
Main Landing Gear
Minimum
Main Instrument Panel
Miscellaneous
Marker
Maximum Landing Weight
Millimeter
Maximum Operating Mach
Modification
Multi Purpose Computer
Micro Processor Unit
Messages
Manufacturer Serial Number
Maximum lake off Weight
Master Warning
Maximum Zero Fuel Weight
N
NAC
NAV
ND
NDB
NEG
NH
NIL
NL
NM
NORM
NP
N/W
NWS
Nacelle
Navigation
Navigation Display
Non Directional Beacon
Negative
High Pressure Spool Rotation Speed
Nothing, No Object
Low Pressure Spool Rotation Speed
Nautical Mile
Normal
Propeller Rotation Speed
Nose Wheel
Nose Wheel Steering
O
OAT
OVBD
OVERTEMP
OVHT
OVRD
OXY
Outside Air Temperature
Overboard
Overtemperature
Overheat
Override
Oxygen
P
PA
PB
PEC
PED
PERF
PFD
PIU
PL
PLA
PNL
Passenger Address
Push Button
Propeller Electronic Control
Pedestal
Performance
Primary Flight Display
Propeller Interface Unit
Power Lever
Power Lever Angle
Panel
POS
P-RNAV
PRESS
PRIM
PRKG
PROP
PSI
PSU
PT
PT (TCAS)
PTB
PTT
PTW
PVM
PWR
PW
Position
Precision Area Navigation
Pressurization, Pressure
Primary
Parking
Propeller
Pound per Square Inch
Pax Service Unit
Point
Proximity traffic
Pitch Trim Box
Push To Talk, Push To Test
Pitch Thumb Wheel (same as PW)
Propeller Valve Module
Power
Pitch Wheel (same as PTW)
Q
QAR
QT
QTY
Quick Access Recorder
Quart
Quantity
R
RA (TCAS)
RA
RAD/ALT
RAD/INT
RCAU
RCDR
RCL
RCU
RECIRC
REV
RGA
RGB
RH
RLY
RMA
RMI
RMS
RNP
RPM
RTO
RUD
Resolution Advisory
Radio Altitude
Radio Altitude
Radio/Interphone
Remote Control Audio Unit
Recorder
Recall
Releasable Centering Unit
Recirculation
Reverse
Reserve Go-Around
Reduction Gear Box
Right Hand
Relay
Radio Management Application
Radio Magnetic Indicator
Radio Management System
Required Navigation Performance
Revolution Per Minute
Reserve Take-Off
Rudder
S
SAT
SBY
SC
SEL
SGL
SGU
SMK
SMKG
S/O (SO)
SOV
SPD
SPLR
SPLY
Static Air Temperature
Stand By
Single Chime, Starter Contactor
Selector
Single
Symbol Generator Unit
Smoke
Smoking
Shut Off
Shut Off Valve
Speed
Spoiler
Supply
189
S y s t e m s 4 2/72 - 6 0 0
STBY
STRG
SSFDR
SURV
SVCE
SW
SWM
SYS
Stand By
Steering
Solid State Flight Data Recorder
Surveillance
Service
Switch
gateway and SWitch Module
System
T
TA (TCAS)
TAD
TAS
TAT
TAWS
TCF
TCS
TEMP
TGT
TK
TLU
T/O (TO)
TOW
TQ
TRU
TTG
TRAFFIC Advisory
Terrain Awareness Display
True Air Speed
Total Air Temperature
Terrain Awareness Warning System
Terrain Clearance Floor
Touch Control Steering
Temperature
Target
Tank
Travel Limiting Unit
Take off
Take off weight
Torque
Transformer Rectifier Unit
Time To Go
U
U/F
UHF
UNCPL
UNDV
190
Underfloor
Ultra High Frequency
Uncouple
Undervoltage
UNLK
UTLY
Unlock
Utility
V
VC
VCP
VENT
VERT
VHF
VID
VMO
VNAV
VOR
VSI
Calibrated Airspeed
Virtual Control Panel
Ventilation
Vertical
Very High Frequency
Video
Maximum Operating Speed
Vertical Navigation
VHF OMNI Directional Range
Vertical Speed Indicator
W
WARN
WOW
XFEED
XFR
Warning
Weight On Wheel
Cross feed
Transfer
XY
YD
YDAU
Yaw Damper
Yaw Damper Actuator Unit
Z
ZA
ZCTH
ZFW
ZP
ZRA
Aircraft Altitude
Theoretical Cabin Altitude
Zero Fuel Weight
Pressure Altitude
Radio Altimeter Altitude
Dear Readers,
Every effort has been made to ensure document quality.
However please do not hesitate to share your comments and information
with us by using the following address: flight-ops-support@atr.fr
Yours faithfully,
Printed on 100% recycled paper using vegetable inks
Your ATR Training and Flight Operations support team.
© ATC June 2012
All reasonable care has been taken by ATC to ensure the accuracy of the present document.
However this document does not constitute any contractual commitment from the part of ATC which will offer, on request,
any further information on the content of this brochure. Information in this brochure is the property of ATC and will be treated
as confidential. No use or reproduction or release to a third part may be made there of other than as expressely authorised by ATC.
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