Atr Systems STD 2 PDF
Atr Systems STD 2 PDF
Atr Systems STD 2 PDF
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.
This version is consistent with the New Avionics Suite standard 2 (STD 2). Standard 2 is
associated with 3 options concerning GNSS approaches. The information dedicated to
each of the 3 options are indicated as follows:
NB: This Systems guide is also available for ATR 42-300, 72-200 not PEC, 42-500 and 72-212A.
1
SYSTEMS 42/72 - 600
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 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 F. COMMUNICATIONS
1. SCHEMATIC ....................................................................................................................................................................................................................................................................................................62
2. PTT SELECTOR AND NOSE WHEEL STEERING CONTROL SW .............................................................................................................................62
3. AUDIO CONTROL PANEL .......................................................................................................................................................................................................................................................63
4. VHF CONTROL ..........................................................................................................................................................................................................................................................................................63
5. AUDIO SEL PB .............................................................................................................................................................................................................................................................................................64
6. LOUDSPEAKER VOLUME KNOBS ...............................................................................................................................................................................................................................64
2
CONTENTS
7. TCAS CONTROL BOX .....................................................................................................................................................................................................................................................................64
8. EMER LOC XMTR PANEL.............................................................................................................................................................................................................................................................65
9. CABIN ATTENDANT HANDSET........................................................................................................................................................................................................................................65
10. HANDMIKE AND HANDSET .............................................................................................................................................................................................................................................65
11. CALLS PANEL .............................................................................................................................................................................................................................................................................................65
12. HEAD SET / BOOM SET /HAND MIKE PANELS...................................................................................................................................................................................65
13. ATC CONTROL ......................................................................................................................................................................................................................................................................................66
14. CVR PANEL ..................................................................................................................................................................................................................................................................................................66
15. CREW OXYGEN MASK ............................................................................................................................................................................................................................................................66
3
SYSTEMS 42/72 - 600
CHAPTER J. FLIGHT CONTROL
1. ROLL SCHEMATIC ............................................................................................................................................................................................................................................................................. 100
2. PITCH SCHEMATIC .......................................................................................................................................................................................................................................................................... 100
3. YAW SCHEMATIC................................................................................................................................................................................................................................................................................ 101
4. GUST LOCK .................................................................................................................................................................................................................................................................................................. 101
5. STICK SHAKER/STICK PUSHER PUSH BUTTON AND DISPLAY ............................................................................................................................. 101
6. SPOILERS POSITION INDICATOR .......................................................................................................................................................................................................................... 102
7. PITCH TRIM ASYM LIGHT ....................................................................................................................................................................................................................................................... 102
8. TRIM POSITION INDICATOR ........................................................................................................................................................................................................................................... 102
9. TRIM CONTROLS................................................................................................................................................................................................................................................................................ 103
10. FLAPS SCHEMATIC ..................................................................................................................................................................................................................................................................... 104
11. FLAPS POSITION INDICATOR................................................................................................................................................................................................................................... 104
12. FLAPS CONTROL LEVER.................................................................................................................................................................................................................................................... 105
4
CONTENTS
9. HYDRAULIC SYSTEM FAILURES.................................................................................................................................................................................................................................. 139
10. HYDRAULIC SYSTEM CROSSFEED OPERATION ..................................................................................................................................................................... 139
11. BOTH MAIN HYDRAULIC PUMPS LOSS .................................................................................................................................................................................................. 140
12. BOTH HYDRAULIC SYSTEMS LOSS ................................................................................................................................................................................................................. 141
ANNEXES
ANNEX 1. COCKPIT PANELS...................................................................................................................................... 177
ANNEX 2. ABBREVIATIONS........................................................................................................................................................................................................................................................ 191
5
A.
AIRCRAFT
GENERAL
FCOM 1.00
7
SYSTEMS 42/72 - 600
1. DOORS LOCATION ATA 52
8
A. AIRCRAFT GENERAL
2. CARGO DOOR PANEL ATA 52
UNLK
At least 1 micro switch is opened
SW TEST
Tests continuity of microswitch system
(on ground, doors opened)
9
SYSTEMS 42/72 - 600
4. EXTERNAL LIGHTS ATA 33
A- Navigation lights
B- Taxi and T/O lights
C- Landing lights
D- Wing lights
E - Beacon lights
F - Strobe lights
G- Logo lights
H- Emergency light
Cabin panel
10
A. AIRCRAFT GENERAL
5. EXT LT PANEL ATA 33
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
DISARM
system deactivated
11
SYSTEMS 42/72 - 600
8. INTERNAL LIGHTING ATA 33
12
A. AIRCRAFT GENERAL
9. LT PANEL ATA 33
MIP / PED
Selects activation and intensity of
integral lighting of the main instru-
ment panels (MIP) and pedestal
(PED)
13
B.
INTEGRATED
SYSTEMS
FCOM 1.01
15
SYSTEMS 42/72 - 600
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 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)
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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
(self-test of these modules)
MFC 1A and MFC 2A FAULT lights extinguish.
MFC 1B and MFC 2B FAULT lights flashing
(self-test of these modules)
OFF MFC 1B and MFC 2B FAULT lights extinguish
The module stops operating
NOTE: If the cargo door control panel is opened,
The MFC functions can be processed: – in one module only the self test of MFC 1A and 2A are already done,
– in several modules (redundancy) and only the MFC 1B and 2B are tested. (See
– partially in 2 modules chapter A.2)
Example:
MODULE
SYSTEM FUNCTION
1A 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.
17
SYSTEMS 42/72 - 600
3. MULTI PURPOSE COMPUTER (MPC) ATA 31
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)
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18
B. INTEGRATED SYSTEMS
4. SCHEMATIC FGCP
DU 1 DU 2 DU 3 DU 4 DU 5
FMA 1 FMA 2
RMA 1 RMA 2
AFDX
ICP
MCDU MCDU ICP
Switching panel
MCP MCP Switching panel
IESI
EFCP EFCP
GPS 1 GPS 2
Stby Stby
Pitot Static
Clock 1 Clock 2
NAV 2
NAV 1
VHF 2
VHF 1
CAC 1 CAC 2
ADF 2
ADF 1
CPM IOM IOM IOM IOM SWM CPM IOM IOM IOM IOM SWM
1 /S /AP /DC /DC 1 2 /S /AP /DC /DC 2
1 11 12 13 2 21 22 23 DME 2
DME 1
GPS 2
GPS 1 AFCA 1 AFCA 2
FWA 1 FWA 2
DCA 1 DCA 2 HF 2
HF 1 CMA 1
RA 2
RA 1
AHRS 1 Flux valve Flux valve AHRS 2
ATC 2
ATC 1
Pitot 1 Pitot 2
ADC 1 Static 1 Static 2 ADC 2 EEC 2
EEC 1 TAT 1 TAT 2
ACARS
MPC MFC 1 MFC 2 AFDX
VHF 3
ARINC, discretes,...
DMU AFCS control
CMU MODULE MODULE MODULE MODULE
1A 1B 2A 2B Optional
AFDAU
SSFDR
19
C.
FLIGHT
WARNING
SYSTEM
FCOM 1.02
21
SYSTEMS 42/72 - 600
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.
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 back-
ground 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 (as-
sociated 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 quali-
ties. 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
LIGHT BLUE LIGHT BLUE is dedicated to VCP area of Display Unit to make evident that VHF manual man-
agement 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
SYSTEMS 42/72 - 600
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
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 ITT – excessive ITT during start (fast increasing to a limit of 765°C)
or
– no ITT during start
ENG START NH <20%, 10s after starter push button ON
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 blade angle <8° in flight
ENG PROP NP 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 BUS 1 / ELEC DC BUS 2 DC BUS 1 or 2 not supplied
ELEC AC BUS 1 / ELEC AC BUS 2 AC BUS 1 or 2 not supplied
25
SYSTEMS 42/72 - 600
ELEC ACW BUS 1 / ELEC ACW BUS 2 / ACW BUS 1 or/and 2 not supplied
ELEC ACW 1+2
ELEC DC ESS DC essential bus not supplied
ELEC AC STBY AC STBY BUS not supplied
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
ELEC DC SBY BUS DC STBY BUS not supplied
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 BLEED1 LEAK / AIR BLEED2 LEAK Leak detected with a loop when the temperature >153°C
26
C. FLIGHT WARNING SYSTEM
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 1 OVHT / AIR DUCT 2 OVHT Duct overheat >92°C.
CAB ALT Cabin altitude >9.500 ft
EXCESS CAB ALT Cabin altitude over threshold 10.000 ft
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
CAB ΔP Cabin delta P >6.25 PSI
EXCESS CAB ΔP Cabin/ Outside pressure difference in excess of 6.6 psi
NEGATIVE CAB ΔP Cabin delta P < –0.5 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 ALPHA / A-ICING ALPHAs 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
YAW AUTO 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
27
SYSTEMS 42/72 - 600
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
ALT DISAGREE 60ft + (Zp1 + Zp2)/460
75ft when the RNP AR is engaged
(associated with CHECK ALT on the PFD)
IAS DISAGREE 10kt discrepancy (associated with CHECK IAS on the PFD)
ATT DISAGREE 3° pitch and 3° roll discrepancy (associated with CHECK ATT on the
PFD)
HDG DISAGREE 8° discrepancy (associated with CHECK HDG on the PFD)
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
DUs DISCREPANCY Discrepancy on not identified DU (at least 2 DU discrepancy)
DU TEMP HI Temperature >70°C after brightness reduction
DUs TEMP HI Temperature >70°C after brightness reduction for at least 2 DUs
FWS SGL CH Flight Warning Application (FWA) loss on one CAC
AVNX SGL SWITCH Gateway and SWitching Module (SWM) card loss on one CAC
AVNX CPM 1 / CPM 2 Core Processing Module (CPM) card loss on one CAC
AVNX IOM 12 / IOM 13 / IOM 22 / IOM 23 Input/Output Module (IOM) card loss
AVNX CPM x + IOM xx Core Processing Module (CPM) card loss on one CAC and Input/
Output Module (IOM) card loss on the other CAC
AVNX IOM xx + xx 2 Input/Output Module (IOM) cards loss
RNP AR GPS 1 / GPS 2 Only available on dual GPS configuration.
LPV At least one parameter coming from GPS1/GPS2 is invalid or GPS1/
GPS2 status is fault.
RNP AR GPS LOSS Available on single and dual GPS configuration
LPV – On single GPS configuration: GPS failure will raise GPS LOSS
message (At least one parameter coming from GPS is invalid or
GPS status is fault.)
– On dual GPS configuration: GPS1 and GPS2 fault (At least one
parameter coming from GPS1 is invalid or GPS1 status is fault
AND At least one parameter coming from GPS2 is invalid or GPS2
status is fault.)
RNP AR FMS 1 / FMS 2 Flight phase parameter coming from FMS1 or FMS 2 is invalid and:
LPV If the RNP is engaged:
– FD DISAGREE and, FMS1 or FMS 2 waypoint list are not
consistent with last valid waypoint list
– FD DISAGREE and GPS1 used and FMS1 position different from
GPS1 position (Threshold 75m) and no GPS DISAGREE
– FD DISAGREE and GPS2 used and FMS2 position different from
GPS2 position (Threshold 75m) and no GPS DISAGREE
RNP AR FMS 1+2 Flight phase parameter coming from FMS1 and FMS 2 is invalid
LPV
RNP AR GPS DISAGREE Both GPS are valid and GPS 1 position is different from GPS 2
position (Threshold 50m)
RNP AR RNP LNAV GUID When the RNP AR is engaged, Difference > 8° between the FD roll
bar (associated with FD DISAGREE on the PFD)
RNP AR RNP LOSS Lost of the RNP AR capability. RNP LOSS shall have priority on other
RNP AR alert.
DME LOSS or DME One or both DME (if DME2 installed) are unavailable.
LPV LPV LOSS / LP LOSS LPV/LP capability are unavailable.
28
C. FLIGHT WARNING SYSTEM
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 At least one DU software discrepancy at A/C power up
CONF UPDATED The avionics configuration has been modified and loaded properly
on all DUs
ADS B ADS B function lost
RMS Failure of RMS1 or RMS2 application
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)
29
SYSTEMS 42/72 - 600
5. AURAL ALARMS ATA 31
CLACKER
VMO
VLO
VFE
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)
30
D.
AIR
FCOM 1.03
31
SYSTEMS 42/72 - 600
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
29+7 29+7
7/223 7/223
/($. /($.
7!& 7!&
(1* (1*
%/((' %/(('
)$8/7 )$8/7
(1*),5( 7!& 7!& (1*),5(
2)) 2))
3523%5.
6(/(&725
2))
%/((' %/(('
21 9$/9( 9$/9(
29(535(6685(
6:,7&+36,
+3 +3
9$/9( 9$/9(
7!& 7!&
(1* :,1* (1*:,1*
'(,&,1* +3 /3 /3 +3 '(,&,1*
(1* (1*
/()7/($.'(7(&7,21/223
5,*+7/($.'(7(&7,21/223
32
D. AIR
1.2. AIR BLEED PANEL
ENG BLEED
Controls both bleed and HP
valves. Spring loaded closed.
Must have air and electricity GRD X FEED PACK VALVE
to open Spring loaded closed. Inhibited in Spring loaded closed. Must
Auto closure when OVHT, flight. Auto opens on ground when have air and elec power to
leak, overpressure, fire handle only one bleed valve is opened open. 6’’ delay on RH valve
pulled, UPTRIM triggered or for pax comfort
prop brake on (left one only).
Inhibited during eng start
PACK VALVE
FAULT
pack valve disagreement with
OVHT pb / or OVHT downstream
either duct temp switch above pack comp. (>204°C). FWS.
274°C. FWS. Auto closure Valve auto closed. Ground
bleed valves (LP and HP). May cooling turbo fan failure
be reset after cooling
33
SYSTEMS 42/72 - 600
34
D. AIR
Item Display Description Item Display Description
X FEED
NORMAL OPERATION
X FEED OPEN & AIR FLOW
BLEED VALVE OFF BUT NOT
CLOSED AND ENGINE RUNNING
X FEED NORMAL OPERATION
XFEED CLOSED
BLEED VALVE OFF BUT NOT NOTHING DISPLAYED
CLOSED AND ENGINE NOT
RUNNING
X FEED
X FEED NORMALLY CLOSED
5 BUT OPENED & AIR FLOW
X FEED
X FEED NORMALLY OPENED
BUT CLOSED
35
SYSTEMS 42/72 - 600
Collective & Individual
Distribution
OVHT OVHT
Duct Tem x2 Duct Tem x2
GROUND UNIT
CONNECTION
ELECTRICAL
MOTORS (DITCH)
Manual Torque
Controller Motor
MIXING
CHAMBER Pneumatic ElectroPneumatic
Out Flow Valve Out Flow Valve
PRESSURISATION
PACK PACK
PACK 1 VALVE VALVE PACK 2
GND X VALVE
OVHT OVHT
OVHT OVHT
HP BLEED
VALVE HP BLEED
VALVE
ENG / WING
De icing AIR CONDITIONING & PRESSURISATION ENG / WING
De icing
36
D. AIR
Collective & Individual
Distribution
FLT CMPT
CABIN
RECIRCULATION FAN 2
UNDER FLOOR
RECIRCULATION FAN 1
OVHT OVHT
Duct Tem x2 Duct Tem x2
GROUND UNIT
CONNECTION
ELECTRICAL
MOTORS (DITCH)
Manual Torque
Controller Motor
MIXING
CHAMBER Pneumatic ElectroPneumatic
Out Flow Valve Out Flow Valve
PRESSURISATION
GND X VALVE
OVHT OVHT
OVHT OVHT
HP BLEED HP BLEED
VALVE VALVE
37
SYSTEMS 42/72 - 600
Collective & Individual
Distribution
OVHT OVHT
Duct Tem x2 Duct Tem x2
GROUND UNIT
CONNECTION
ELECTRICAL
MOTORS (DITCH)
Manual Torque
Controller Motor
MIXING
CHAMBER Pneumatic ElectroPneumatic
Out Flow Valve Out Flow Valve
PRESSURISATION
PACK PACK
PACK 1 VALVE VALVE PACK 2
LEAK when
P > 80 PSI ENG T > 153°C ENG
OVER PRESS OVER PRESS
BLEED VALVE LEAK SENSING ELEMENT LEAK SENSING ELEMENT BLEED VALVE
GND X VALVE
OVHT OVHT
OVHT OVHT
HP BLEED T > 274°C HP BLEED
VALVE VALVE
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
SYSTEMS 42/72 - 600
2.2. COMPT TEMP PANEL
RECIRC FAN
Assists pack air flow
RECIRC FAN
FAULT: fan low speed or mo-
tor overheat + FWS. No auto
disconnect
COMPT INDICATOR
Duct temperature limited to
88°C. (191°F) by pneumatic
temp.limiter
TEMP SEL
AUTO: the temperature is
regulated by the electronic
temperature controller, taking
into account:
– duct temperature
– zone temperature demand
selector
– associated compartment
TEMP SEL temperature
OVHT: duct overheat >92 °C + – aircraft skin temperature
FWS. Pack valve will not auto
close
MAN FLOW
compt temp knob controls NORM: 22 psi (pack valves)
directly temp control valve HIGH: 30 psi (pack valves)
40
D. AIR
41
SYSTEMS 42/72 - 600
4 5
3
6
1
8
7
2
42
D. AIR
Item Display Description Item Display Description
PACK
OFF PACK VALVE OFF 4 EXHAUST EXHAUST MODE P/B RELEASED
OVBD
1
PACK
PACK FAULT EXHAUST EXTRACTION FAN FAULT DISPLAY
FAULT FAULT
PACK VALVE STANDBY MANUEL MODE
PACK FULL OPEN
P/B DEPRESSED AND
STBY OVBD VLV FULL OPEN
BLEED VALVE P/B RELEASED OUT
MANUEL MODE
RECIRCULATION FAN ON FULL CLOSE
OVBD VLV FULL CLOSED
AUTOMATIC MODE
RECIRCULATION FAN OFF
OVBD VLV FULL OPEN
MANUAL TEMPERATURE
6 MAN
CONTROL
3 AIR
8 HIGH FLOW HIGHT FLOW SELECTED
43
SYSTEMS 42/72 - 600
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
VENTILATION
AFT CARGO
SMOKE DETECTOR
TEMP SENSOR
ELECTRONIC RACKS
LAVATORY
ELECTRIC AND
FLT CMPT
EXTRAC CABIN
AIR FLOW VALVE OVBD VALVE UNDER FLOOR
(/(&60.
OVBD VALVE
OVBD – AUTO except in emergency
extract fan off FAULT – direct control of OVBD valve.
OVBD valve partially opened (in OVBD valve in disagreement with The full open position is possible
flight only). U/F valve closed ovbd valve SW position only if the delta P is <1 psi
44
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
3500 ft
Cabin altitude = airport altitude
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
Cabin pressure or < –0.5
45
SYSTEMS 42/72 - 600
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
RATE
(1013,2 Hpa)
Cabin rate of climb
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 MAN
closed digital controller out of operation.
(no more digits on landing elevation
display)
46
D. AIR
1 3 2
6
0 8 ΔP PRE-ALERTING DISPLAY MAN PRESS
MANUAL PRESSURE CONTROL
CAB ALT 5020 FT
0.25 TARGET 5020 FT NOMINAL DISPLAY
1
MAN PRESS
MANUAL PRESSURE CONTROL
6 CAB ALT 2050 FT
0 8 ΔP ALERTING DISPLAY TARGET ____ FT INVALID TARGET
7.00 3
MAN PRESS
CAB ALT ____ FT INVALID CAB ALT
TARGET 2050 FT
6
0 8 INVALID ΔP MAN PRESS
CAB ALT 8900 FT CAB ALT PRE-ALERTING DISPLAY
TARGET 5020 FT
MAN PRESS
2000 CAB ALT 10100 FT CAB ALT ALERTING DISPLAY
0 700 UP RATE OF CLIMB TARGET 5020 FT
2000
MAN PRESS NO DESTINATION IN
CAB ALT 5200 FT
TARGET LDG ELEV FMS AND <FL140
2000
2 0 1000 DN RATE OF DESCENT
2000
2000
0 - -- INVALID RATE
2000
47
E.
AUTOMATIC FLIGHT
CONTROL SYSTEM
FCOM 1.04
49
SYSTEMS 42/72 - 600
1. SCHEMATIC ATA 22
FGCP
FMA FMA
AFDX
ICP 1 ICP 2
CAC 1 CAC 2
EEC 1 EEC 2
CPM IOM IOM IOM IOM SWM CPM IOM IOM IOM IOM SWM
ADC 1 1 /S /AP /DC /DC 1 2 /S /AP /DC /DC 2 ADC 2
1 11 12 13 2 21 22 23
AHRS 1 AHRS 2
AFCA 1 AFCA 2
FWA 1 FWA 2
NAV 1 NAV 2
DCA 1 DCA 2
CMA 1
GPS 1 GPS 2
MCDU 1 MCDU 2
Power
Pitch trim box
Power
Yaw trim box
QUICK QUICK
DISC / TCS DISC / TCS
50
E. AUTOMATIC FLIGHT CONTROL SYSTEM
2. FMA ATA 22
2 1 3 5 4 6 7 8
13 9 10
1 2 3
ARM Mode change HOLD BANK ANGLE Description
HDG SEL
HDG SEL HDG SEL ‘‘LO‘‘ or ‘‘ ‘‘ (UPPER MODE)
1 2 3
Mode change +
ARM +7s HOLD BANK ANGLE Description
CAPTURE
51
SYSTEMS 42/72 - 600
4 5
ARM Mode change + CAPTURE +7s HOLD Description
IAS MODE
IAS IAS IAS
(UPPER MODE)
VS MODE
VS VS VS
(UPPER MODE)
ALT MODE
ALT SEL ALTÍ ALTÍ ALT
(UPPER MODE)
1 2 4 5
Mode change + Mode change +
ARM +7s HOLD ARM +7s HOLD Description
CAPTURE CAPTURE
LOC LOC9 LOC9 LOC GS GS9 GS9 GS APP MODE COMMON MODE
52
E. AUTOMATIC FLIGHT CONTROL SYSTEM
Item Display Description
LPV LP LP APPROACH
53
SYSTEMS 42/72 - 600
16 15
14 12 11
AP/YD INVALID Amber message, reverse When an AFCS Internal failure inhibits AP/YD or
AP INVALID video flashing. YD engagement
54
E. AUTOMATIC FLIGHT CONTROL SYSTEM
12 Unexpected mode change, or problem in navigation parameters
Message flashing Message + 7s Aural alert Display logic Comments
If the crew try to engage a NAV mode where as the
wrong nav source is selected, or if the navigation
Yellow message flashing for source is lost
CHECK NAV SRC
LPV 7 seconds then disappears Q LPV
If the crew try to engage a NAV mode when the LPV
track is in angular mode
– If an armed or engaged NAV mod dropped off
Amber message, reverse following a nav source change
video flashing for – If a VOR/LOC nav frequency change induces the
7 seconds, then steady until current mode loss
CHECK NAV SRC CHECK NAV SRC
failure is cleared by trying to – In case of coupling change
LPV engage another FD mode, Q LPV
or by pressing STBY pb loss of LP/LPV lateral or vertical ARM/CAPT/TRACK
mode
Amber message, reverse If VCP lcing selection disagrees with the actual icing
CHECK T/O SPEED CHECK T/O SPEED video flashing for conditions
7 seconds, then steady (HORNS ON/OFF)
– 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 INVALID, associated
Yellow message, flashing for
ADC INVALID 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 ATT INVALID, associated
Yellow message, flashing for with CHECK ATT on PFD if Roll or Pitch angles are
ATT INVALID
7 seconds, then disappears 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 INVALID, associated with CHECK HDG
Yellow message, flashing for on the PFD & ND, if magnetic headings are not
HDG INVALID
7 seconds, then disappears coherent (No AP/YD disengagement)
– Or in case of loss of AHRS redundant sensor
indicated by a flag
In case of loss of NAV redundant sensor indicated by
a flag
BaroVNAV QQBaroVNAV / RNP AR
RNP AR – If the crew wants to descend manually, VS mode
can be used
Yellow message, flashing for – If the crew wants to descend automatically,
NAV INVALID
7 seconds, then disappears wait until entering in new TOD-5’area then use
VNAV pushbutton or perform a Vertical direct to
any waypoint (available upon vertical revision on
MCDU). This action will recompute a new vertical
profil and upon VNAV pushbutton press may allow
engaging VNAV PATH Mode.
LPV INVALID
Yellow message, flashing for
LPV The LPV or LP fonctions are not available
7 seconds, then disappears
LP INVALID
55
SYSTEMS 42/72 - 600
If AUTO is selected with the ”AUTO/MAN” SEL P/B
and the speed target from both FMS is not valid. The
Amber message, reverse
AUTO speed mode is not available and the speed
SPD AUTO INOP video flashing for
is automatically switched to MAN (Cyan Speed
7 seconds, then disappears
Target Bug). The Speed Target Bug is automatically
synchronized to the current value of A/C speed
– When the ICP AUTO/MAN push-button is pressed
while man is selected and IAS target from the
selected FMS is invalid
– The aircraft is not in the good configuration before
Yellow message, flashing for
SPD AUTO INOP selecting SPD AUTO
7 seconds, then disappears
good configuration: - Flaps 15°
- PWR MGT TO
- Alt sel > Alt A/C
- IAS mode engaged
On ILS:
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
Red message, reverse video
path excusion
EXCESS DEV EXCESS DEV flashing for 7 seconds, then
RNP AR QOn RNP AR (if installed):
steady amber
Excessive deviation:
– vertically: VDEV > 75ft and aircraft is higher than DA
– laterally: cross track
XTK > RNP value – √PDE2+EPE2 (refer to PBN brochure)
During Altitude Capture
Amber message, reverse – When the selected altitude is changed (transition to
ALT OFF video flashing for basic pitch)
7 seconds, then disappears – When baro correction is changed (transition to
basic pitch)
Amber message, reverse
video flashing for 7 seconds, – When an AHRS failure (ATT INVALID or HDG
then steady until failure is INVALID) leads to the FD mode cancellation
LPV FD MODE CHG FD MODE CHG cleared by changing AHRS Q When LPV AFCS modes are disarmed
source selection, or by The “FD MODE CHG” and “LPV (or LP) INVALID”
selecting another FD mode, messages are displayed
or by pressing STBY P/B
AFCS TEST Amber flashing During the AFCS test (maintenance opération)
56
E. AUTOMATIC FLIGHT CONTROL SYSTEM
CHECK ALT SEL if VNAV descent mode cannot be engaged
BaroVNAV Yellow message flashing for because ALT SEL is above A/C, OR VNAV climb mode cannot
CHECK ALT SEL
RNP AR 7 seconds, then disappears be engaged because ALT SEL is below A/C, OR ALT capture
is in progress
Amber message flashing
BaroVNAV REDUCE SPD when aircraft reaches protection speed in
REDUCE SPD for 7 seconds, then
RNP AR VNAV PATH mode.
disappears
Yellow message flashing for APP INVALID if GPS data failure or loss of LPV capability
LPV APP INVALID
7 seconds, then disappears leads to FD mode engagement inhibition.
Yellow message flashing for SELECT VTF in HDG SEL mode on an attempt to arm LPV
LPV SELECT VTF
7 seconds, then disappears modes (P/B APP) before activating the VTF
BaroVNAV Yellow message flashing for VNAV INHIB upon any VNAV mode engagement attempted
VNAV INHIB
RNP AR 7 seconds, then disappears and VNAV option not installed.
14 Trim status
RETRIM ROLL R WING DN RETRIM ROLL R WING DN When the aileron servo motor reaches a first torque
RETRIM ROLL L WING DN RETRIM ROLL L WING DN Amber message, reverse value threshold
NIL video flashing 7 seconds,
then steady When the aileron servo motor reaches a second
AILERON MISTRIM AILERON MISTRIM
torque value threshold
When both BOTH AF APPLICATIONS are lost. The FMA is black. The AFCS FAIL is the only message displayed
AFCS FAIL
57
SYSTEMS 42/72 - 600
3. FGCP (FLIGHT GUIDANCE AND
CONTROL PANEL) ATA 22
IAS mode
to use FD with a target indicated airspeed.
(Cyan speed bug: MAN on ICP) NAV SOURCE Selector F/O side
(Magenta speed bug: AUTO on ICP) Select the NAV source for F/O
EHSI and/or ND (FMS1, VOR/
NAV mode HDG mode ILS1, VOR/ILS2, FMS2)
to use FD with VOR to use FD with
and LNAV course HDG SEL
BC mode
to use FD with localizer in back course VNAV mode BaroVNAV RNP AR
to use FD with associated VNAV path coded in
the FMS database.
STBY pb The VNAV mode has to be used with the LNAV
cancels all FD upper modes (armed and mode.
captured and active modes) and returns NOTE: If VNAV P/B is pressed and VNAV function
in basic modes. is not available, a yellow message VNAV INHIB
will be generated on FMA
58
E. AUTOMATIC FLIGHT CONTROL SYSTEM
4. ICP (INDEX CONTROL PANEL) ATA 22,31
59
F.
COMMUNICATIONS
FCOM 1.05
61
SYSTEMS 42/72 - 600
1. SCHEMATIC ATA 23
The communication system provides communication between:
– aircraft and ground stations
– cockpit crew stations
– cabin attendant station
– ground crew stations
CABIN ATTENDANT
OBSERVER SIDE
REMOTE
– oxy mask CONTROL
– boom set GROUND CREW
AUDIO
– head set UNIT
– PTT switch
PASSENGER
F/O SIDE
– oxy mask mike PUBLIC ADDRESS SYSTEM
– hand mike
– boom set
– head set
– PTT switch
GPWS
– loudspeaker
– loudspeaker audio level
– audio control panel TCAS
62
F. COMMUNICATIONS
3. AUDIO CONTROL PANEL ATA 23
INT/RAD selector
VOICE ONLY key
Provides selection of transmission
When depressed, it inhibits NAV receivers
mode when using OXY MASK or
station identification. Light illuminates
BOOM SET mike
Transmission keys amber when selected.
INT: hot mike position. Interphone
Only one key can be engaged at
is always operative between crew
a time. It illuminates white when
stations. Other transmissions require
selected
to select a transmission key and use
a PTT pb
NEUTRAL: Interphone is inoperative.
Volume control knob Other transmissions require selecting
to set volume from associated a transmission key and using a PTT
communication or navigation pushbutton.
facilities 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 spring-
loaded to NEUTRAL.
MCDU
MCP
63
SYSTEMS 42/72 - 600
5. AUDIO SEL PB ATA 23
AUDIO SEL
Controls functioning of associated
RCAU processing board.
FAULT NORM: RCAU functions normally
illuminates amber and the FWS
is activated when an associated
RCAU processing board failure or ALTN
power loss is detected 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
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
MCDU
MCP
64
F. COMMUNICATIONS
8. EMER LOC XMTR PANEL ATA 23
65
SYSTEMS 42/72 - 600
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
MCP
(ON/OFF)
– to set XPDR 1 or 2
TEST pb
when depressed and held, the test circuit
is activated
mod 7075 – the pointer moves to a location between
graduations 8 and 10
COCKPIT VOICE RECORDER – if a headset is plugged into the jack, the
Monitor indicator for test only. 600 HZ signal is heard
Movement of pointer in white
band indicates all channels are ERASE pb
operative provides fast erasure of recordings when
the landing gear shock absorbers are
compressed and parking brake is set
HEADSET jack (depress for 2 sec. to completly erase)
when headset is plugged into the During erasure, a 400Hz audio signal can
jack: be heard in the headset
– cockpit sounds picked up by
the microphone are audible
– erase tone is audible when MICROPHONE
ERASE pb is depressed picks up cockpit conversations and alert
sounds
66
G.
ELECTRICAL
SYSTEMS
FCOM 1.06
67
SYSTEMS 42/72 - 600
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
AC power
Two batteries DC power 28 VDC Two inverters VAC 26 V
VAC 115 V
DC GPU
AC GPU
The TRU provides power to the
emergency loads in case of dual DC
generators loss. It is supplied by the ACW
bus 2.
68
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
DC Starter
Generator Accessory
gear box
ACW
Generator
Reduction
gear box
69
SYSTEMS 42/72 - 600
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 DC
EMER ESS
BUS BUS
HOT HOT
EMER MAIN
BAT BAT
BUS BUS
EMER MAIN
BAT CHG BAT CHG
AC STBY BUS
BAT
INV 1 INV 2
ON
TRU
DC STBY BUS
DC DC
EMER ESS
BUS BUS
HOT HOT
EMER MAIN
BAT BAT
BUS BUS
EMER MAIN
BAT CHG BAT CHG
BTC
DC SVCE BUS
DC GEN 1 EXT. PWR DC GEN 2
21
GND HDLG
BUS
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
71
SYSTEMS 42/72 - 600
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 DC
EMER ESS
BUS BUS
HOT HOT
EMER MAIN
BAT BAT
BUS BUS
EMER MAIN
BAT CHG BAT CHG
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.
ELEC SD page
72
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 DC
EMER ESS
BUS BUS
HOT HOT
EMER MAIN
BAT BAT
BUS BUS
EMER MAIN
BAT CHG BAT CHG
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
73
SYSTEMS 42/72 - 600
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
The BAT toggle switch has to be selected to
OVRD.
BAT The OVRD position ensures that busses are
INV 1 INV 2 supplied by their respective battery by overriding
OVRD all protections. This position is protected by
a switch guard.
TRU
DC STBY BUS
DC DC
EMER ESS
BUS BUS
HOT HOT
EMER MAIN
BAT BAT
BUS BUS
EMER MAIN
BAT CHG BAT CHG
BTC
DC SVCE BUS
DC GEN 1 EXT. PWR DC GEN 2
)$8/7 )$8/7
ELEC SD page
74
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
TRU
DC STBY BUS
DC DC
EMER ESS
BUS BUS
HOT HOT
EMER MAIN
BAT BAT
BUS BUS
EMER MAIN
BAT CHG BAT CHG
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)
75
SYSTEMS 42/72 - 600
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 DC
EMER ESS
BUS BUS
HOT HOT
EMER MAIN
BAT BAT
EMER BUS BUS
MAIN
BAT CHG BAT CHG
BTC
DC SVCE BUS
DC GEN 1 EXT. PWR DC GEN 2
)$8/7 )$8/7
GND HDLG
BUS
ELEC SD page
76
G. ELECTRICAL SYSTEMS
3. DC-AC PANEL ATA 24
INV FAULT
OVRD Under/over voltage at INV output.
Xfer/stby busses from HOT MAIN (INV failure or supply loss). Auto-
to HOT EMER BAT BUS Xfer of all AC busses to remaining
inverter. ELEC INV 1 (2) on FWS
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 ON
green when DC EMER, DC STBY, Basic mode: STBY busses
INV 1, AC STBY and DC ESS supplied by HOT MAIN BAT BUS.
BUS are supplied by TRU 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. OFF
ELEC BAT CHG on FWS ESS BUS, DC STBY BUS + INV 1 are
Contactor auto opens if: thermal isolated from HOT MAIN BAT BUS
runaway/bus voltage <25 V/Start DC EMER BUS is isolated from
sequence /Bat sw on OVRD HOT EMER BAT BUS
DC BUS OFF
BTC
Respective bus not supplied.
The BPCU controls BTC
ELEC DC 1 (2) on FWS
operation. Ext power, hotel mode
or single gen operation, BTC is
DC SVCE/UTLY BUS closed (green flow bar)
DC SVCE supplies power in flight
and on ground during airplane
servicing operations. ISOL
UTLY BUSSES supply non- BTC and BTR opened (released
essential loads out)
SHED: In automatic shedding
One of the DC SVCE/UTLY 1 and
2 busses is shed by the BPCU. DC GEN 1/2
SHED: In manual shedding (P/B FAULT: protection trip by GCU;
selected OFF) Auto reset if underspeed. BTC
all DC SVCE/UTLY 1 and 2 auto closes ELEC DC 1 ( 2) on
busses are shed FWS
DC GEN 1/2
AVAIL
Generator FAULT Lt.
GPU has been checked by BPCU
Extinguishes above 61.5% NH if
for over/under voltage, over
GEN is operating normally
current and polarity
X START FAIL
Opposite generator has not come EXT PWR
on line to assist start at 10 % NH AVAIL + ON: GPU has prioity on
ELEC X START on FWS both generators
77
SYSTEMS 42/72 - 600
4. ELEC SD
9 10 11
1 6 5 2 7 3
78
G. ELECTRICAL SYSTEMS
Item Display Description Item Display Description
OFF
7 SVCE BUS DC SVCE BUS OFF
OFF
SVCE BUS DC SVCE BUS FAULT
79
SYSTEMS 42/72 - 600
21 22 10
23
19
15
16
12
18
14
17
13
20
20
80
G. ELECTRICAL SYSTEMS
Item Display Description Item Display Description
HOT BUS HOT BUS
MAIN BAT
DC MAIN BUS VALID VOLTAGE AND EMER BAT
DC EMER BUS VALID VOLTAGE
28 V >18V 28 V AND >18V
HOT BUS
DC MAIN BUS VALID VOLTAGE AND HOT BUS
DC EMER BUS VALID VOLTAGE
12 MAIN BAT
28 V
>18V WITH BAT TOGGLE P/B SW 16 EMER BAT
28 V
AND >18V WITH BAT TOGGLE
IN OVRD POSITION P/B SW IN OVRD POSITION
HOT BUS HOT BUS
MAIN BAT
DC MAIN BUS INVALID VOLTAGE EMER BAT
DC EMER BAT INVALID VOLTAGE
28 V OR <18V 28 V OR <18V
EMER BAT
DC MAIN BAT VALID VOLTAGE AND DC EMER BAT VALID VOLTAGE
XX V XX V
>18V AND >18V
EMER BAT
DC EMER BAT VALID VOLTAGE
DC MAIN BAT VALID VOLTAGE AND 17 XX V
13 XX V
<18V
AND <18V
EMER BAT
-- V DC EMER BUS INVALID VOLTAGE
-- V DC MAIN BAT INVALID VOLTAGE
EMER BAT CHG P/B SW
CHG
OFF
RELEASED (CHARGE CONTACTOR
CHG MAIN BAT CHG P/B SW RELEASED OPENED)
OFF
(CHARGE CONTACTOR OPENED) EMER BAT CHG P/B SW PRESSED
IN (CHARGE CONTACTOR CLOSED)
MAIN BAT CHG P/B SW PRESSED CHG WITH DC BUS 1 NOT SUPPLYING
IN (CHARGE CONTACTOR CLOSED) OFF
THE EMER BATTERY OR WITH
WITH DC BUS 2 NOT SUPPLYING TOGGLE P/B SW ON OVRD
CHG
OFF
THE MAIN BATTERY OR WITH POSITION
TOGGLE P/B SW ON OVRD
POSITION, OR CAUTION ON MAIN
18 EMER BAT CHG P/B SW PRESSED
14 DC BAT
IN (CHARGE CONTACTOR CLOSED)
WITH DC BUS 1 SUPPLYING
MAIN BAT CHG P/B SW PRESSED CHG
OFF
THE EMER BATTERY AND WITH
IN (CHARGE CONTACTOR CLOSED) TOGGLE P/B SW NOT ON OVRD
CHG
OFF
WITH DC BUS 2 SUPPLYING THE POSITION, OR CAUTION ON EMER
MAIN BATTERY OR WITH TOGGLE DC BAT
P/B SW NOT ON OVRD POSITION
EMER BAT CHG P/B SW PRESSED
CHG
MAIN BAT CHG P/B SW PRESSED IN (CHARGE CONTACTOR CLOSED)
CHG FAULT
FAULT
IN (CHARGE CONTACTOR CLOSED) WITH DC EMER BAT IN FAULT
WITH DC MAIN DC BAT IN FAULT
IF ABNORMAL DISCHARGE OF THE
19 EMER BATTERY
IF ABNORMAL DISCHARGE OF THE
15 MAIN BATTERY
20 BAT OVRD IF TOGGLE SW IN OVRD POSITION
AC BUS 1
OF AC BUS ON
21
AC BUS X
OFF AC BUS OFF
81
SYSTEMS 42/72 - 600
5. ACW SCHEMATIC ATA 24
ACW BUS 1 ACW BUS 2 TRU
SVCE BUS
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.
SVCE BUS
82
G. ELECTRICAL SYSTEMS
ACW BUS 1 ACW BUS 2 TRU
SVCE BUS
NP=0 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%)
SVCE BUS
NP=100% NP=100%
83
SYSTEMS 42/72 - 600
ACW BUS 1 ACW BUS 2 TRU
SVCE BUS
NP=100% NP=100%
84
G. ELECTRICAL SYSTEMS
7. SD PAGE
6 5
2 3
1 4
ACW GEN1 ACW GEN FAULT TRU P/B ON WITH ACW BUS 2 ON
FAULT
TRU AND TRU SUPPLY NOT AVAILABLE
5
ACW BUS x DC TRU P/B ON WITH ACW BUS 2 ON
OFF
ACW BUS ON
TRU AND TRU SUPPLY AVAILABLE
2
ACW BUS x
OFF ACW BUS OFF TRU P/B ON WITH ACW BUS 2 OFF
TRU
85
SYSTEMS 42/72 - 600
8. BREAKER PANELS ATA 24
86
G. ELECTRICAL SYSTEMS
8.2. ELECTRIC RACK BEHIND F/O
87
H.
EMERGENCY
EQUIPMENT
FCOM 1.07
89
SYSTEMS 42/72 - 600
The aircraft is equipped with fire fighting, oxygen, first aid equipment and emergency lightning.
– flash light
– goggles
– oxygen
masks
halon
extinguisher
fire resistant
gloves
– water
– hood extinguisher – first aid kit
– goggles – flash light emergency – bag containing
– oxygen mask – smoke hood exit type III oxygen masks smoke hood type I entry door
Emergency
Emergency
exit sign
exit sign
90
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, gastro-
intestinal antacid, anti-diarrhoel medication,
disposable gloves
5. MEGAPHONE ATA 25
91
SYSTEMS 42/72 - 600
9. GLOVES ATA 25
Water extinguisher
2 liters of water with an anti-ice
additive
discharge time: 30 to 40 ”
Halon extinguisher
1.2 kg of halon gas
discharge time: 8 to 10 ”
To flight
crew
members
Modules for 72/42- 600
Oxygen bottle
92
H. EMERGENCY EQUIPMENT
13. OXYGEN PANEL AND DISPLAY ATA 35
MAIN SUPPLY
pb in: crew supply only PAX SUPPLY
ON 25% off the passengers
HP INDICATOR
oxygen bottle pressure.
Red arc 0 to 85 psi
Green arc 85 to 2025 psi LO PR
If below 1400 psi, use table supply below 50 psi. OXY on FWS
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
EMERGENCY
selector activates pressurization
of mask delivery flow when
N/100% rocker is at 100%
93
SYSTEMS 42/72 - 600
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
94
I.
FIRE
PROTECTION
FCOM 1.08
95
SYSTEMS 42/72 - 600
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
EXHAUST
ELECTRIC RACK
EXTRACT AIR
FLOW VALVE FWD
FLIGHT CARGO
DECK
OVBD
SMOKE
CCAS DET RECIRCULATED
EXTRACT
ELECTRONIC
RACK FAN U/F
96
I. FIRE PROTECTION
3. FIRE HANDLE ATA 26
AGENT
SQUIB OFF
armed when T handle pulled. FAULT TEST takes respective loop out of
Discharges bottle. MC + SC + LOOP on FWS parallel circuit. Allows other loop to
(DC EMER/HOT MAIN BAT) Fault lights in A/B loop pb activate fire signal alone.
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
97
SYSTEMS 42/72 - 600
Normal operation
On SD CABIN
7. SD CABIN
Avionics smoke
Forward cargo
smoke
Aft cargo
compartment
smoke
Lavatory smoke
Aft compartment
& lavatory
Detection fans
98
J.
FLIGHT
CONTROL
FCOM 1.09
99
SYSTEMS 42/72 - 600
Elevator
Aileron
Spoiler
Rudder
Flaps
The elevators, ailerons and rudder are
mechanically actuated
Flaps
The spoilers and flaps are hydraulically
actuated. Spoiler
Aileron
L WING DN R WING DN
AIL AIL
CABLE TENSION
AP REGULATOR
FDAU
TOFA-01-09-20-001-A100AA
POSITION
POSITION TRANSMITTER
POSITION TRANSMITTER AP ROLL
TRANSMITTER ACTUATOR
SPOILER
VALVE
BLOCK
LEFT RIGHT
SPOILER SPOILER
CONTROL
COLUMN
STICK
SHAKER
REGULATOR
NOSE UP
STICK
PROBES
PUSHER
M.F.C.
AUTO
TRIM
M.F.C.
CAC
1/2
STICK
PUSHER
ACTUATOR POWER
AP PITCH PITCH
ACTUATOR TRIM BOX
CCAS
F.D.A.U.
FLEXIBLE
In case of jamming, pitch control will be re- TRIM SHAFT
ACTUATOR TRIM
covered by disengaging the pitch coupling ACTUATOR
CCAS
system (by applying a differential force of ELEVATOR
PITCH UNCOUPLING
ELEVATOR
MECHANISM
52 daN). TAB TAB
POSITION PITCH
F.D.A.U. TRANSMITTER DISCONNECT
100
J. FLIGHT CONTROL
3. YAW SCHEMATIC ATA 27
CAC
NOSE LH NOSE RH 1/2
F.D.A.U.
POSITION
TRANSMITTER
TO BRAKE
CONTROL
RUDDER
PEDAL POSITION RELEASABLE DAMPER
ADJUSTER CENTERING
UNIT
R0FA-01-0940-007-A001AA
AP YAW
ACTUATOR TRIM
ACTUATOR
TLU (TRAVEL
LIMITATION UNIT)
FORCE DETECTOR ROD
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
101
SYSTEMS 42/72 - 600
6. SPOILERS POSITION INDICATOR ATA 27
102
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
Manual mode (Yaw Auto Trim active)
103
SYSTEMS 42/72 - 600
10. FLAPS SCHEMATIC ATA 27
)
/
$
3 6(/
F
L Flaps retracted
A
P SEL 0°
Flaps extension
toward 15°
SEL 15°
Flaps extended
at 15°
SEL 15°
104
J. FLIGHT CONTROL
12. FLAPS CONTROL LEVER ATA 27
105
K.
FLIGHT
INSTRUMENTS
FCOM 1.10
107
SYSTEMS 42/72 - 600
1. SCHEMATIC ATA 31
SWITCHING PANEL EFCP EFCP SWITCHING PANEL
MCP MCP
CAPT SWITCHING F/O SWITCHING
2VM 6VM
DISCRETE
ARINC 429
CPM IOM IOM IOM IOM SWM CPM IOM IOM IOM IOM SWM AFDX
1 /S1 /AP1 /DC /DC 1 2 /S2 /AP2 /DC /DC 2
11 12 13 21 22 23
IESI
AFCA 1 AFCA 2
FWA 1 FWA 2
DCA 1 DCA 2
CMA 1
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)
108
K. FLIGHT INSTRUMENTS
2. PFD (PRIMARY FLIGHT DISPLAY) ATA 31
FLIGHT DIRECTOR
command bars (green)
DH / MDA indications
109
SYSTEMS 42/72 - 600
3. MFD (MULTI FUNCTION DISPLAY) ATA 31
110
K. FLIGHT INSTRUMENTS
4. EWD (ENGINE AND WARNING DISPLAY) ATA 31
Brake messages
Test status
Permanent Data
Flap indicator
Alert window
Procedure window
111
SYSTEMS 42/72 - 600
5. ND - ARC MODE WITH TERRAIN
OR WEATHER RADAR INFORMATION ATA 31
112
K. FLIGHT INSTRUMENTS
7. SWITCHING PANEL ATA 34
ATT/HDG pb
enables to use AHRS 2 DISPLAY pb
information. When captain pb In normal conditions,
is depressed SYS 2 illuminates enables to cycle the three
white on CAPT pb, CAPT 2 formats on DU 2 (capt
illuminates green on F/O pb switching), on DU 4 (F/O
switching). In case of
failure of any DU (DU 1 or
2 on capt side or DU 4
ADC pb
or 5 on F/O side) enables
enables to use ADC 2 information. When captain pb
to cycle the three formats
is depressed SYS 2 illuminates white on CAPT pb,
on the remaining DU
CAPT 2 illuminates green on F/O pb
BRG1(2)push button: FORMAT rotary knob: MAN DEL Procedure control pb:
By pressing it, VOR1(2) or By turning it, the format of By pressing on it, procedures Allows to move on
ADF1(2) or no indication the ND is changed. inserted manually are deleted upward/downward line
is displayed. in the procedure window
and to validate actions
RCL PB
CLR PB
A first push enables to display in the
By pressing on it, a clearable
Alert Window the alert messages
alert displayed on the Alert
RANGE “+/–” push button: previously cleared but still detected.
Window is cleared.
By pressing it, the range of A second push scrolls down the alert
the Navigation Display page is messages list in case of overflow in
increased/decreased. the alert window. PROC MENU
By pressing on it, procedure
menu is displayed in the
procedure window.
113
SYSTEMS 42/72 - 600
9. MCP (MULTIPURPOSE CONTROL PANEL) ATA 31
COM P/B
Selection on VCP
– VHF
Enter P/B
– HF 1 (if installed)
To validate the selection area
– HF 2 (if installed)
NAV P/B
Selection on VCP
– VOR
– ADF
– ND OVLY (ND
Overlay)
114
K. FLIGHT INSTRUMENTS
10. WEATHER RADAR CONTROL ATA 34
PRIMUS 660
RCT pb TGT pb
activates Rain Echo Attenuation activates target alert
GAIN Compensation technique function and
setting to set receiving amplification permits display with more accurracy
the weather situation behind storms SECT pb
Used to select either the normal
MODE selector 12 looks/minute 120° sector scan
OFF radar is off or the faster update 24 looks/
STBY radar is on but no pulse is sent minute 60° sector scan
by the antenna
TEST range at 100 NM, 3 arcs green,
yellow and red TILT control
WX normal operating position, to adjust radar antenna in pitch
intensity of weather obstacles is axis from 15° down to 15° up
displayed by different colors (black:
no cloud; green: normal cloud; yellow:
dense; red: severe storm) Turns the pitch and roll stability
G MAP enables to display ground on and off. When selected off, an
obstacles (black, pale blue, yellow, amber legend illuminates above the
magenta) pushbutton
115
SYSTEMS 42/72 - 600
11. TAT/SAT INDICATOR ATA 34
TAT indicator
indicates total air temperature
SAT indicator
indicates static air temperature
TAS indicator
indicates true air speed
ELAPSED TIME
When depressed ON
the flight time starts
automatically
when airborne
116
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
STANDBY COMPASS
Hidden in up position. Compass
control should be placed on DN for
use. The compass rose is graduated
in 10 degrees increments
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 STANDBY AIRSPEED
acceleration. It is represented by INDICATOR
a trapezoidal index that moves The actual airspeed is given in a T
beneath the roll index. shaped window positioned in the
center of the white moving speed
tape on the left of the IESI.
Brightness
STANDBY ALTIMETER
The altitude indication is given in
STANDBY HORIZON a rectangular window positioned
– The pitch scale has markers ev- in the center of the white moving
ery 2.5 degrees up to ±20°. If altitude tape on the right of the
pitch exceeds ±25° degrees IESI.
large red chevron will indicate Altitude in meters can also be
excessive attitude and direc- displayed on the IESI underneath
tion to follow to resume normal the altitude tape.
attitude. SET ROTARY SWITCH The barometric reference is
– The roll scale has markers are SEL P/B – Sub fonction menu scroller displayed in cyan. It corresponds
set at 10, 20, 30, 45, 60 de- – Change cursor – Baro setting to either the selected barometric
grees of bank. selection between VHF – VHF com tuning pressure or the standard pressure.
COM, VHF NAV, BARO – VHF nav tuning
SETTING and COURSE – Course setting in VOR
when VOR mode. mode
– Used to validate
manual entry.
117
SYSTEMS 42/72 - 600
15. AIRSPEED INDICATOR ATA 34
Actual IAS
Vref
VmHB30 or Vmcl whichever is higher
118
K. FLIGHT INSTRUMENTS
16. ALTIMETER ATA 34
Selected altitude: ALT SEL
-Manual: bug set manually
with the FGCP
BaroVNAV RNP AR
-Auto: bug managed by
the FMS when VNAV
mode engaged
ALTITUDE ALERT
Current altitude or FL An amber frame is flashing
(± 1000ft) then a yellow frame
is steady (± 250ft)
DA / MDA
Landing Elevation
Barometric setting in
Hpa and InHG
DH / MDA knob
Barometric setting knob Outer knob permits to select between
The knob is used to set the DH (Decision Height) or MDA (Minimum
barometric reference. Descent Altitude).
Pushing the knob sets standard Inner knob is used to set DH or MDA
barometric reference (29.92 INHG / values, depending of the outer knob
1013.25 Hpa) position.
119
SYSTEMS 42/72 - 600
17. VERTICAL SPEED INDICATOR AND TCAS ATA 34
VS digital readout VS target readout
Set by the FGCP
Pitch Wheel (PW)
VS scale
VERTICAL SPEED
INDICATOR
based on both inertial
(AHRS) and VS pointer
barometric data (ADC).
VS target
– Manual: bug set manually
with the FGCP
pitch Wheel (PW)
BaroVNAV RNP AR
– Auto: bug managed by
the FMS
Open diamond
Other traffic
Solid diamond
Proximate traffic (PA) traffic TCAS Status Resolution Advisory (RA)
within ± 1200 ft and 6 NM vertical rates to be avoided.
Solid cube
Resolution Advisory (RA) AIRCRAFT
Traffic in warning area 15 own aircraft symbol
to 35 s before collision area
120
L.
FUEL
SYSTEM
FCOM 1.11
121
SYSTEMS 42/72 - 600
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
Refueling panel
Refueling point
Gravity filling cap
Access door
Main wing tank Feeder tank (200 l / 160 kg) Vent surge tank
Refueling panel
Gravity filling cap
Access door
Refueling point
Vent surge tank (100 l)
Main wing tank Feeder tank (200 l / 160 kg) Vent surge tank
122
L. FUEL SYSTEM
2. ELECTRICAL FUEL PUMP OFF ATA 28
(1*,1(
+08
):6
)&2&
)(('
/235
027,9(
)/2:
9$/9( /39$/9(
(1*,1(),5(
38//
57$1.
&5266)(('
9$/9(
3803
581
2))
(1*,1(
)(('(5 (/(&752 )(('-(7
-(73803 3803 3803
0(023$1(/
',63/$<
/7$1. )(('(5&203$570(17
123
SYSTEMS 42/72 - 600
3. STARTING PROCEDURE ATA 28
(1*,1(
+08
):6
)&2&
)(('
/235
027,9(
)/2:
9$/9( /39$/9(
(1*,1(),5(
38//
57$1.
&5266)(('
9$/9(
3803
581
2))
(1*,1(
)(('(5 (/(&752 )(('-(7
-(73803 3803 3803
0(023$1(/
',63/$<
/7$1. )(('(5&203$570(17
124
L. FUEL SYSTEM
4. NORMAL PROCEDURE ATA 28
(1*,1(
+08
):6
)&2&
)(('
/235
027,9(
)/2:
9$/9( /39$/9(
(1*,1(),5(
38//
57$1.
&5266)(('
9$/9(
3803
581
2)) (1*,1(
)(('(5 (/(&752 )(('-(7
-(73803 3803 3803
3!36,
V
0(023$1(/
',63/$<
/7$1. )(('(5&203$570(17
125
SYSTEMS 42/72 - 600
5. CROSS FEED PROCEDURE ATA 28
(1*,1(
+08
):6
)&2&
)(('
/235
027,9(
)/2:
9$/9( /39$/9(
(1*,1(),5(
38//
57$1.
&5266)(('
9$/9(
3803
581
2)) (1*,1(
)(('(5 (/(&752 )(('-(7
-(73803 3803 3803
0(023$1(/
',63/$<
/7$1. )(('(5&203$570(17
Cross feed valve could be used to supply an engine from the opposite tank.
The cross feed is not used to tranfer fuel from one tank to the other tank.
With the Xfeed valve push button pressed IN, the valve opens, green flow bar is horizontal. Both electrical pump are
energized.
126
L. FUEL SYSTEM
CROSS FEED PROCEDURE CONT’D
(1*,1(
+08
):6
)&2&
)(('
/235
027,9(
)/2:
9$/9( /39$/9(
(1*,1(),5(
38//
57$1.
&5266)(('
9$/9(
3803
581
2)) (1*,1(
)(('(5 (/(&752 )(('-(7
-(73803 3803 3803
0(023$1(/
',63/$<
/7$1. )(('(5&203$570(17
By selecting OFF the corresponding PUMP push button, the electrical pump is de-energized and the motive flow valve is
supplied to close. The engine is fed from the opposite tank.
127
SYSTEMS 42/72 - 600
6. ENGINE FEED JET PUMP LOW PRESSURE ATA 28
(1*,1(
+08
):6
)&2&
)(('
/235
027,9(
)/2:
9$/9( /39$/9(
(1*,1(),5(
38//
57$1.
&5266)(('
9$/9(
3803
581
2)) (1*,1(
)(('(5 (/(&752 )(('-(7
-(73803 3803 3803
336,
0(023$1(/
',63/$<
/7$1. )(('(5&203$570(17
In the event of engine feed jet pump failure, the pressure switch (<5 psi) provides electrical pump running control which
ensures fuel supply to the engine.
The electrical pump delivers the necessary flow rate for engine consumption.
128
L. FUEL SYSTEM
7. LOW LEVEL ATA 28
(1*,1(
+08
):6
)&2&
)(('
/235
027,9(
)/2:
9$/9( /39$/9(
(1*,1(),5(
38//
57$1.
&5266)(('
9$/9(
)/$33(56 3803
581
2)) (1*,1(
)(('(5
-(7 (/(&752 )(('-(7
3803 3803 3803
0(023$1(/
',63/$<
/7$1. )(('(5&203$570(17
When the low level is triggered in one tank, its electrical pump is automatically activated.
Two low level cases:
– LO LVL with fuel quantity indicator < 160 kg → Low level of remaining fuel in the tank.
– LO LVL with fuel quantity indicator > 160 kg → Feeder tank not full due to a failure of the feeder jet pump.
In this condition, the fuel is transfered from the main tank to the feeder tank through the flappers.
129
SYSTEMS 42/72 - 600
8. ENGINE FIRE PROCEDURE ATA 28
(1*,1(
+08
):6
)&2&
336, )(('
/235
027,9(
)/2:
9$/9( /39$/9(
(1*,1(),5(
38//
57$1.
&5266)(('
9$/9(
3803
581
2)) (1*,1(
)(('(5 (/(&752 )(('-(7
-(73803 3803 3803
3!PEDU
0(023$1(/
',63/$<
/7$1. )(('(5&203$570(17
In case of engine fire, when corresponding engine fire handle is pulled, it closes associated LP shut off valve.
130
L. FUEL SYSTEM
9. FUEL PANEL ATA 28
PUMP
FLOW BAR Control electrical pump power
Shows position of valve. No and jet pump motive flow
bar: valve fault or moving. valve.
Runs automatically if:
– jet pump press < 5 PSI or till
reaching 8.5 PSI during engine
RUN start.
illuminates green when elec – XFEED in line
fuel pump is running. – 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
FUEL TEMPERATURE in °C
131
SYSTEMS 42/72 - 600
11. FUEL QTY INDICATION ATA 28
If <50 kg
FUEL LO LVL
– When the quantity LO LVL with FQI <160kg
is <160 kg or
– When the quantity
is >160 kg, but
the feeder tank is LO LVL with FQI >160kg
not full (Feeder jet (feeder tank not full)
pump failure)
FUEL X FEED
– Is displayed as soon as the
fuel crossfeed is selected on.
– Flashing when empty tank
selected.
132
M.
HYDRAULIC
SYSTEM
FCOM 1.12
133
SYSTEMS 42/72 - 600
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: 9.6 l
normal filling: 9.35 l
minimum filling: 8.5 l
alert level: 2.5 l
5(7851
/2/9/ 29+7
29+7 /2/9/
0 0
%/8(3803
/235 *5((13803
2)) /235
2))
0
;)(('
29+7
$8;3803
21
/235
21
126(:+((/
67((5,1*
/$1',1**($5
)/$36
632,/(56
3523(//(5%5$.(
%5$.,1*
(0(5*$1' 1250$/
3$5.,1*
134
M. HYDRAULIC SYSTEM
2. HYD PWR PANEL ATA 29
Auxiliary pump
Automatic running conditions
(simultaneoustly):
BLUE PUMP – AUX Pump pb depressed GREEN PUMP
Supplied by ACW, controlled by – at least one engine running Supplied by ACW, controlled by
DC EMER BUS – blue system press <1500 psi DC ESS BUS
– prop brake off
– gear lever down
(supply: DC BUS 2 or Hot main bat bus)
LO PRESS LO PR
pump delivery pressure less pump delivery pressure less
than1500 psi. FWS (no auto off) than 1500 psi. FWS (no auto
off).
X feed valve
135
SYSTEMS 42/72 - 600
4. PRESSURE INDICATION ATA 29
136
M. HYDRAULIC SYSTEM
6. HYDRAULIC ON RAMP (ONLY ON BATTERY)
Press Gauge
ATA 29
PRESS
TRANSMIT
1600 PSI HYDRAULICS
(SD HYD/ACW)
BRAKING
1600 PSI
NOSE WHEEL
STEERING
LDG GEAR
FLAPS
SPOILERS
PROP BRAKE
OVHT
Press Gauge
1500 PSI 1500 PSI Press Gauge
OVHT
AC LOW LOW ACCUMULATOR
LEVEL LEVEL
BLUE GREEN
PUMP PUMP
P P
PRESS LO PRESS PRESS
TRANSMIT OVHT LO PRESS TRANSMIT
(SD HYD/ACW) < 1500 PSI AUX < 1500 PSI (SD HYD/ACW)
0 PSI PUMP 0 PSI
P
LO PRESS
X FEED
< 1500 PSI
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
Press Gauge
PRESS
TRANSMIT
3000 PSI HYDRAULICS
(SD HYD/ACW)
BRAKING
NOSE WHEEL
STEERING
LDG GEAR
FLAPS
SPOILERS
PROP BRAKE
OVHT
Press Gauge
3000 PSI 1500 PSI Press Gauge
OVHT
AC LOW LOW ACCUMULATOR
LEVEL LEVEL
BLUE GREEN
PUMP PUMP
P P
PRESS PRESS
TRANSMIT LO PRESS OVHT LO PRESS TRANSMIT
(SD HYD/ACW) < 1500 PSI AUX < 1500 PSI (SD HYD/ACW)
3000 PSI PUMP 0 PSI
P
DC HOT MAIN
LO PRESS
BAT BUS X FEED
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)
137
SYSTEMS 42/72 - 600
8. HYDRAULIC SYSTEM NORMAL OPERATION ATA 29
Press Gauge
PRESS
TRANSMIT
3000 PSI HYDRAULICS
(SD HYD/ACW)
BRAKING
3000 PSI
NOSE WHEEL
STEERING
LDG GEAR
FLAPS
SPOILERS
PROP BRAKE
OVHT
Press Gauge 3000 PSI Press Gauge
3000 PSI
OVHT
AC LOW LOW ACCUMULATOR
LEVEL LEVEL
BLUE GREEN
PUMP PUMP
P P
PRESS PRESS
LO PRESS OVHT LO PRESS
TRANSMIT TRANSMIT
(SD HYD/ACW) (SD HYD/ACW)
AUX
3000 PSI ACW PUMP
ACW 3000 PSI
P
LO PRESS
X FEED
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)
138
M. HYDRAULIC SYSTEM
9. HYDRAULIC SYSTEM FAILURES ATA 29
Press Gauge
PRESS
TRANSMIT
3000 PSI HYDRAULICS
(SD HYD/ACW)
BRAKING
3000 PSI
NOSE WHEEL
STEERING
LDG GEAR
FLAPS
SPOILERS
PROP BRAKE
OVHT
Press Gauge Press Gauge
3000 PSI < 2.5 l > 121 °C
OVHT
AC LOW LOW ACCUMULATOR
LEVEL LEVEL
BLUE GREEN
PUMP PUMP
P P
PRESS PRESS
TRANSMIT LO PRESS OVHT LO PRESS TRANSMIT
(SD HYD/ACW)
AUX < 1500 PSI (SD HYD/ACW)
3000 PSI ACW PUMP
ACW
P
LO PRESS
X FEED
– 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)
3000 PSI
NOSE WHEEL
STEERING
LDG GEAR
FLAPS
SPOILERS
PROP BRAKE
OVHT
Press Gauge 3000 PSI Press Gauge
3000 PSI
OVHT
AC LOW LOW ACCUMULATOR
LEVEL LEVEL
BLUE GREEN
PUMP PUMP
P P
PRESS PRESS
TRANSMIT LO PRESS OVHT LO PRESS TRANSMIT
(SD HYD/ACW)
AUX
< 1500 PSI (SD HYD/ACW)
3000 PSI ACW PUMP 3000 PSI
P
LO PRESS
X FEED
After a main pump low pressure (<1500PSI) or overheat (>121°C) both systems are recovered by crossfeed operation
139
SYSTEMS 42/72 - 600
11. BOTH MAIN HYDRAULIC PUMPS LOSS ATA 29
Press Gauge
PRESS
TRANSMIT
HYDRAULICS
(SD HYD/ACW)
BRAKING
NOSE WHEEL
STEERING
LDG GEAR
FLAPS
SPOILERS
PROP BRAKE
OVHT
Press Gauge Press Gauge
OVHT
AC >121°C LOW
LEVEL
LOW
LEVEL
ACCUMULATOR
BLUE GREEN
PUMP PUMP
P P
PRESS PRESS
TRANSMIT LO PRESS OVHT LO PRESS TRANSMIT
(SD HYD/ACW)
AUX
< 1500 PSI (SD HYD/ACW)
PUMP
P
LO PRESS
X FEED
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.
Press Gauge
PRESS
TRANSMIT
HYDRAULICS
(SD HYD/ACW)
BRAKING
NOSE WHEEL
STEERING
LDG GEAR
FLAPS
SPOILERS
PROP BRAKE
OVHT
Press Gauge Press Gauge
OVHT
AC >121°C LOW
LEVEL
LOW
LEVEL
ACCUMULATOR
BLUE GREEN
PUMP PUMP
P P
PRESS LO PRESS
PRESS
TRANSMIT OVHT LO PRESS TRANSMIT
(SD HYD/ACW) AUX
< 1500 PSI (SD HYD/ACW)
PUMP
P
LO PRESS DC BUS 2
X FEED
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.
140
M. HYDRAULIC SYSTEM
12. BOTH HYDRAULIC SYSTEMS LOSS ATA 29
Press Gauge
PRESS
TRANSMIT
HYDRAULICS
(SD HYD/ACW)
BRAKING
NOSE WHEEL
STEERING
LDG GEAR
FLAPS
SPOILERS
PROP BRAKE
OVHT
Press Gauge Press Gauge
<2.5 l
OVHT
AC LOW LOW ACCUMULATOR
LEVEL LEVEL
BLUE GREEN
PUMP PUMP
P P
PRESS PRESS
TRANSMIT LO PRESS OVHT LO PRESS TRANSMIT
(SD HYD/ACW)
AUX
< 1500 PSI (SD HYD/ACW)
PUMP
P
LO PRESS
X FEED
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.
141
N.
ICE AND RAIN
PROTECTION
FCOM 1.13
143
SYSTEMS 42/72 - 600
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 ATA 30
HORIZONTAL TAILPLANE BOOTS
AILERON HORNS ENGINE AIR (PNEUMATIC) / RUDDER
WINGS BOOTS INTAKE BOOTS AND ELEVATOR HORNS
(ELECTRICAL) (PNEUMATIC) (PNEUMATIC) (ELECTRICAL)
PROPELLER
(ELECTRICAL)
WINSHIELD
(ELECTRICAL)
144
N. ICE AND RAIN PROTECTION
2. PROBES AND WINDSHIELD HTG ATA 30
TAT
not heated. FWS. (ACW supply)
heating inhibited on ground.
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
CAPT, STBY and F/O
Static port not heated (On
Normal operation - ON
ground only, not monitored in
(depressed) and OFF (released).
flight). FWS. (DC BUS)
PTT pb
press for 3’’: ICE DET indicator Lt: ACW bus 2.
– icing will flash, on FMA, if system works ICING
correctly. illuminates amber when ice accre-
– A-ICING DETECT is displayed steady tion is detected provided both horns
on FWS if ice detector failure is detected anti-icing and airframe de-icing are
selected ON.
ICING AOA Lt ICING
(DC emer BUS). flashes amber when ice accretion is
Illuminates green as soon as 1 horn anti-icing on. detected and horns anti-icing and/or
Stall alarm + stick shaker threshold lowered. airframe de-icing are not selected ON
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
145
SYSTEMS 42/72 - 600
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.
146
N. ICE AND RAIN PROTECTION
6. DE-ICING SCHEMATIC
147
SYSTEMS 42/72 - 600
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.
148
N. ICE AND RAIN PROTECTION
8. ANTI-ICING & DE-ICING PANEL ATA 30
PROP HORNS HORNS FAULT
ACW supply. Inhibited below ACW supply. Inhibited on Power loss. A-ICING HORNS
NP 63% ground. Either horn activates 1 (2) on FWS
AOA Lt
FAULT
power loss on at least 1 blade. SIDE WINDOWS
A-ICING PROP 1 (2) on FWS 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. DE ICING
ON (HIGH POWER): 20’’ on air is always available
per 3 blades. regardless of bleed pb.
No stop between cycles. NORM: 60’’ / cycle
SLOW: 180’’ / cycle
MODE SEL AUTO
Automatic selection of cycle
FAULT
depending on ADC1/2 to
both MFC modules have
MFC1B/2B
failed to control boots cycles.
FAULT when ADC or MFC fail:
The monitoring is preformed
Fast mode is automatically
by the stby controller.
selected for ENG and
A-ICING SEL on FWS
AIRFRAME DEICING and High
Power for PROP ANTI-ICE.
A-ICING AUTO on FWS. AFR AIR BLEED
MAN: manual selection of OVRD: no MFC. Boots
cycles depending on SAT inflated by separate stantby
controller (cycle 60’’)
ENG
FAULT: distribution valve
opened but no air pressure. AIR FRAME
OR valve closed and pressure FAULT: valve opened but
detected OR AFR AIR BLEED no downstream pressure. Or
off and air temp above deice valve closed and downstream
valve >230°C for more than pressure detected. A-ICING
6’’. A-ICING ENG 1 ( 2) on FRAME on FWS
FWS
ENG
ON: signal sent to MFC to AIR FRAME
start deice cycle on the engine ON: signal sent to MFC
air intake, deice valve opened to start deice cycle on the
even if AFR AIR BLEED off airframe
AFR AIR BLEED
FAULT: air dowstream deice
MODE SEL ENG AND valve < 14 psi more than 10’’
AIRFRAME OR Air upstream of the deice OFF : isol valves closed.
SLOW: 180’’/cycle valve > 230°C. A-ICING Deice valves closed unless
FAST: 60’’/cycle BLEED on FWS ENG 1 / 2 deice on.
9. DE-ICING/ANTI-ICING INDICATION
(MEMO PANEL DISPLAY) ATA 30
CYAN
When selected ON
AMBER
When FAULT
149
O.
LANDING
GEAR
FCOM 1.14
151
SYSTEMS 42/72 - 600
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
BLUE GREEN
AUXILIARY
PUMP
BLUE PUMP GREEN PUMP
M M X FEED M
PILOT PEDALS
EMERGENCY
EMERGENCY / BRAKE
PARKING BRAKE ACCUMULATOR
HANDLE BRK
OFF PILOT BRAKE
PEDALS
EMERGENCY NORMAL
AND PARKING MODE
E E MODE METERING L R METERING
M
E
M
E
VALVE VALVE
R R
PARKING
ANTI SKID
VALVES
SHUTTLE
VALVES
FUSES
152
O. LANDING GEAR
3. LDG GEAR POSITION INDICATORS ATA 32
System 2
UNLK gear not locked in select-
ed 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.
153
SYSTEMS 42/72 - 600
6. EMERGENCY PARKING ATA 32
BRAKE HANDLE
EMERGENCY BRAKE HANDLE PARKING BRAKE
permits to apply a metered pressure. permits a full pressure on the brakes. When brake
The brake accumulator allows at least six handle is not in the fully released position, amber
braking applications without any antiskid PRKG BRK caution light is displayed on FWS
operation if the blue hydraulic system is not and is taken into account by the T/O CONFIG.
available (Springloaded to the off position) (Springloaded to the off position)
7. STEERING
HANDWHEEL ATA 32
N/W STEERING SW
activates or deactivates the nose wheel THE STEERING HAND WHEEL
steering system (guarded type in the ON controls the nose wheel angle up to 60°
position) in either direction:
OFF: unpressurizes the steering system – clockwise: steering to the right
(91° of deflection) – counter clockwise: steering to the left
154
P.
NAVIGATION
SYSTEM
FCOM 1.15
155
SYSTEMS 42/72 - 600
1. NAV CONTROL ATA 34
VCP
MCDU
MCP
MCDU
MCP
156
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.
MODE 1
excessive descent rate
MODE 2
excessive terrain closure rate
157
SYSTEMS 42/72 - 600
MODE 3
altitude loss after take-off
MODE 4
unsafe terrain clearance
MODE 5
below glideslope
158
P. NAVIGATION SYSTEM
MODE 6
altitude callouts
159
SYSTEMS 42/72 - 600
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.
“TERRAIN AHEAD”
or
“OBSTACLE AHEAD”
“TERRAIN AHEAD,
PULL UP”
Or
“OBSTACLE AHEAD
PULL UP”
160
P. NAVIGATION SYSTEM
“AVOID TERRAIN”
5. TAWS PB 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
161
SYSTEMS 42/72 - 600
7. ND OVERLAY ATA 31
162
P. NAVIGATION SYSTEM
8. FMS ATA 34
DU 2 DU 4
FGCP
FMA 1 FMA 2
RMA 1 RMA 2
MFD MFD
DU 1 DU 3 DU 5
AFDX
GPS 1 GPS 2
EFCP EFCP
Clock 1 Clock 2
NAV 2
NAV 1
VHF 2
VHF 1
CAC 1 CAC 2
ADF 2
ADF 1 CPM IOM IOM IOM IOM SWM CPM IOM IOM IOM IOM SWM
1 /S /AP /DC /DC 1 2 /S /AP /DC /DC 2
1 11 12 13 2 21 22 23 DME 2
DME 1
AFCA 1 AFCA 2
GPS 2
GPS 1 FWA 1 FWA 2
DCA 1 DCA 2
CMA 1
HF 2
HF 1
RA 2
RA 1
AHRS 1 Flux valve Flux valve AHRS 2 AFDX
ATC 2 ARINC,
ATC 1 discretes,...
Pitot 1 Pitot 2
AFCS Control
ADC 1 Static 1 Static 2 ADC 2 EEC 2
EEC 1 TAT 1 TAT 2
Optional
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.
163
SYSTEMS 42/72 - 600
NAVIGATION
HEADING ACCURACY
REFERENCE (EPE)
RMS MENU
QUICK ACCESS FMS PAGE
KEYS
SLEW KEYS
EXECUTE
active light
REQUEST
light
EXECUTION
KEY
MULTI SYSTEMS
SELECTION KEY
BRIGHTNESS
CONTROL KEYS
ALPHA NUMERIC
KEYBOARD
SPARE KEY CLEAR KEY
for CMU or SATCOM
164
Q.
POWER PLANT
FCOM 1.16
165
SYSTEMS 42/72 - 600
1. ENGINE SCHEMATIC ATA 61/72
Aircraft fitted with
– two Pratt &Whitney, PW 127 M or PW 127 N (72-600/42-600)
– two, six blades propellers (Hamilton)
POWER TURBINE
6 blades propeller
166
Q. POWER PLANT
2. POWER AND PROPELLER CONTROLS ATA 61/72
The different powers ratings for the engine are: (SHP: Shaft Horse Power)
72-600 42-600
– RTO (Reserve Take Off) (maximum power) 2750 SHP 2400 SHP
Used in case of an engine flame out during take off
(up trim) or in case of go around (ramp)
– MCT (Maximum continuous) 2500 SHP 2400 SHP
– TO (Take Off 0,9 RTO) 2475 SHP 2160 SHP
– Climb 2192 SHP 2160 SHP
– Cruise 2132 SHP 2132 SHP
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)
NOTCH position:
PWR MGT in – TO: → NP 100% and 0,9 RTO → TQ up to 90%
– MCT → NP 100% and TQ up to 90,9% (72-600)
→ NP 100% and TQ up to 100% (42-600)
– CLB → NP 82% and TQ up to 97% (72-600)
→ NP 82% and TQ up to 109,7% (42-600)
– CRZ → NP 82% and TQ up to 94,5% (72-600)
→ NP 82% and TQ up to 108,3% (42-600)
Reverse position
167
SYSTEMS 42/72 - 600
– 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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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%)
Fuel Shut Off position: Close the shut off valve on the HMU
168
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
NOTCH
0 50 67 81 100
POWER LEVER ANGLE
– TO PWR = 2475 SHP NP=100% TQ = 90%
– MCT PWR = 2500 SHP NP=100% TQ = 90,9%
– CLB PWR = 2192 SHP NP=82% TQ = 97%
– CRZ PWR = 2132 SHP NP=82% 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 NP=100% TQ = 100%
ATR 42-600
NORMAL OPERATION, EEC ON, ISA CONDITIONS
SHP 115% TQ
A 102% TQ
NOTCH
0 50 67 81 100
POWER LEVER ANGLE
– TO PWR = 2160 SHP NP=100% TQ = 90%
– MCT PWR = 2400 SHP NP=100% TQ = 100%
– CLB PWR = 2160 SHP NP=82% TQ = 109,7%
– CRZ PWR = 2132 SHP NP=82% TQ = 108,3%
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%
169
SYSTEMS 42/72 - 600
3. ENGINE INDICATION ATA 31
Analogic indication
RTO Torque at TO
Objective TQ in MCT CLB CRZ
ϵϭ͘ ϭ Normal
hWdZ/D
ATPCS uptrim
activation
ϭϬϮ ͘ ϱ Abnormal
GO Around Torque
ϭϮϱ ͘ ϲ Over-limit
ϵϬ ͘Ϭ Normal operation
170
Q. POWER PLANT
ϲϬ
ϲϬ
ʹϯϱ ϲϬ
Red limit ϲϬ
ϭϵϬ ͲͲͲ͘Ͳ Invalid data
Ϭ
E>
Normal ͲͲͲ͘Ͳ й ͲͲͲ͘Ͳ
ϯϭ
NL information
ϭϬϬ
Red limit
KG/H or LBS/H ͲͲͲ ͘ Ͳ NL invalid signal
171
SYSTEMS 42/72 - 600
4. ENG START PANEL ATA 61/72
CRANK ON FAULT
dry motoring (no ignition) starter engaged. At 45% NH, Illuminates when:
light goes off and the starter – remains ON with NH
is disconnected >45%
or – GCU failure during start
or – starter failure
or – ENG 2 only: ENG
START selector on start
position + PROP BRK ON
START A OR B + GUST lock not engaged
on ground, only exciter A or
B is supllied (except for the ON
position A&B) Continuous ignition (both A &
In flight regardless of start B). Memo panel light.
selection (A, B or A+B) both
exciters are energized
READY
engagement or disengag.
conditions are met:
UNLOCK – A/C on ground
PROP BRAKE not fully – gust lock engaged
locked or not fully released. – CL on FTH or FUEL S/O
After 15 sec: FWS alarm. Also 42/72 PEC – blue hyd press available
used to check lock/unlock on the prop brake input
time: >2100psi
– 5 sec. to unlock – Fire handle not pulled
– 10 sec. to lock
PROP BRK
Brake fully locked same
indication on the memo panel
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
172
Q. POWER PLANT
6. PWR MGT PANEL ATA 61/72
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: PWR MGT
– With PWR MGT in TO by: 2 co-axial sw. (LH: bottom /
– 4.5% up to 4000ft RH: TOP) providing FDAU,
– 4% above 4000ft PEC and EEC with basic
– With PWR MGT in MCT by 4% power requirements
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 FAULT
For any disagreement between the position of illuminates when both PEC
the push button and the rating of both EEC channels are lost. FWS
(MC+SC+FAULT+ENG BOOST on FWS).
OFF
PEC is deactivated and NP is limited
at 102,5% if power is sufficient
ATPCS TEST
selector allows to check the
correct functionning of the
ATPCS.
This rotary selector is spring
loaded to neutral position
173
page blanche
ANNEXES
175
ANNEXES
ANNEX 1. COCKPIT PANELS
Fire test
SQUIB TEST ENGINE FIRE HANDLE MW+CRC+ ENG 1 FIRE on
Elect test of squibs. Pulled: on the respective engine EWD and FWS
Prop Feather
FAULT Fuel LP valve closed +Fire handle illuminated
resistance/capacitance. Air Bleed valve closed +FUEL S/O Lt on CL (if out of
Inhibits fire signals until turned Deice Deice & shutoff valve closed Fuel S/O position)
Elect DC & ACW gen. disconnected
off. Squibs Armed (Lts illuminated) Fault test
LOOP on FWS (DC EMER) Hydraulic Hyd prop brake (eng 2 only) MC+SC+ loop on FWS
FAULT Lts on A/B Loop pb.
SQUIB
armed when T handle pulled. OFF
Discharges bottle. Takes respective loop out of
(DC EMER / HOT MAIN BAT). parallel circuit. Allows other
loop to activate fire signal.
DISCH
bottle depressurized. Opposite
agent DISCH Lt will also
The opening of the cargo door
illuminate on other fire panel. control panel cover. Self Test
of MFC 1A/2A.
TLU FAULT FAULT
system disagree / two Malfunction or electrical supply
ADC failures / ADC datas fault: AUTO disengagement
incoherence / TLU position – FWS
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 Gear position secondary
Below 190 kts (42) / 180 kts system as sensed by MFC 2.
(72): LOW SPD
UNLK
gear not in selected position or
SPLR uplock not opened (on Gnd)
activates when >2.5° aileron
travel. Lt ON=Spoiler not fully Green Lt
retracted (BLUE HYD PWR). down lock engaged
177
SYSTEMS 42/72 - 600
mod 7075
FAULT
MODE SEL AUTO valve opened but no
Automatic selection of cycle depending downstream press. OR valve
on ADC1/2 input to MFC1B/2B. closed and downstream press
detected. FWS.
FAULT
when ADC or MFC or CPM/IOM fail ON
Fast mode is automatically selected for signal sent to MFC to start
ENG and AIRFRAME DEICING and High deice cycle on the airframe.
Power for Prop Anti-ice. FAULT
MAN both MFC modules controlling
mode enables manual selection of boots have failed resulting
cycles depending on SAT (MAN in an incorrect inflation
illuminated CYAN). sequencing.
LO PR
NORM supply below 50 psi.
– On ground, ENG 1 off:
ON
extract fan on. Ovbd valve full
25% of Pax are supplied.
open, U/F valve closed.
– On ground, ENG 1 on :
extract fan on. Ovbd valve FAULT
closed, U/F valve opened. Ovbd Valve in disagreement
FAULT with Ovbd Valve SW position.
Fan failure / overheat (fan AUTO except for emergency.
inhibited for 120s after every In emergency, the full open
eng start. FWS). position is possible only if the
OVBD Delta P is < 1 psi
Extract fan off. OVBD valve
partially opened (in flight only).
Assists pack air flow.
U/F valve closed.
FAULT
Fan low speed or motor
Duct temperature limited to overheat. FWS. No auto
88°C. (191°F) by pneumatic deselected.
temp limiter. OVHT
NORM: 22 psi Duct overheat > 92°C. FWS.
HIGH: 30 psi Pack valve will not auto close.
regulated by pack valve MAN
Spring loaded closed. Ground Compt temp knob controls
only. Auto opens when only 1 directly temp control valve.
Bleed valve is opened. Selects the zone where T°
Controls both Bleed and HP check is desired.
valves. Spring loaded closed. PACK VALVE
Must have air & elec to open. Spring loaded closed. Must
Auto Bleed valve closes when have air pressure and select
Ovht, Leak, Overpressure power to open (6 sec delay on
(>80 psi), Fire T pulled, when RH pack for pax comfort).
UPTRIM is triggered or prop FAULT
brk on (left one only). Inhibited pack valve disagreement with
during eng start. PB or Ovht downstream of
FAULT pack comp (>204°C). FWS.
Bleed valve disagreement Valve auto closed.
with selected position (case of LEAK
Ovht, Overpressure or Leak). activates when temperature
FWS. Associated valves auto detected by bleed loop
closed. exceeds 156°C. FWS. Auto
OVHT closure after 1 sec of following
either bleed duct temp thermal valves: Bleed, HP, PACK and
switch above 274°C. FWS. GND XFeed. DO NOT RESET
Associated valves auto closed. BLEED.
May be reset after cooling.
180
ANNEXES
FAULT
stick shaker or pusher failure. PTT pb
press for 3 sec.
OFF
– icing will flash on the display
turns off both shaker and pusher
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.
181
SYSTEMS 42/72 - 600
Panel with EWD format. ATPCS
Trigger
one TQ <18% (42)
Arming conditions: ATPCS
one TQ <18% (72).
PWR MGT set on TO – ARM on ground = uptrim +
+ ATPCS pb in auto FTR (2.15” delay) Cancel
+ both PL >49° – ARM in flight (In case of go PWR MGT out of TO
+ both TQ > 53%(42) around) = auto FTR only. or ATPCS pb OFF
both TQ > 46% (72) or at least one PL retarded <49°
ARM green LT on. or both TQ <53% (42) and
<46% (72)
UPTRIM
signal sent to respective
eng during ATPCS
sequence.
Eng power = RTO.
EEC
TORQUE Ind display acts on stepper motor, to regulate
2 probes sending info: Fuel Flow.
– to pointer (via AFU). FAULT flashing
– to digital counter (via EEC Failure. The fuel flow is frozen
EEC). to maintain the power. (Do not
Internal bug deselect EEC when flashing)
computed by FDAU (MPC); The PL has to be retarded to the
shows RTO when PWR green sector before deselection of
MGT on TO, otherwise the EEC
max TQ depending on FAULT steady
PWR MGT selection. EEC Failure. HMU base law =
reversion. Fault become steady
when the PL is retarded in the
Trim indicator display. green band.
OFF
HMU base law = reversion.
LO PITCH
blade angle < 8° (below
FI).
Primary engine
parameters display
Permanent Data
display
Flaps indicator display
Alert window
TAT-SAT indicator
Procedure window
ELAPSED TIME
When the ELAPS TM P/B
(right side of the F/O) is
FUEL USED Readout
depressed ON the flight
time starts automatically
DISPLAY UNIT 3 (DU3)
when airborne
In the normal configuration,
the EWD format is displayed.
182
ANNEXES
Gear position sensed by system I (MFC 1A)
ANTISKID TEST pb
Operative if speed >10 kts. (inhibited if speed >17 kts)
Activates when speed >23 kts = MC + SC EWD 4 amber F
+ 50% diff between wheels on EWD.
(locked wheel protection). Test duration: 3 sec. in flight
Braking action inhibited at and 6 sec. on ground
touchdown as long as wheel
spin up speed <35 kts or
5 sec. (touchdown protection). Gear handle red Lt
CAUTION: THE TEST any gear not sensed down
INHIBITS BRAKES and locked with the further
conditions:
a) Any gear not down and
OFF locked + flaps normal landing
Pb released, system configuration + Zra <500 ft +
deactivated PL at low power (impossible
to cancel)
b) Any gear not down and
locked +1 PL at low power +
Zra < 500 ft.
NOTE: Any gear not down must be
UNLOCK sensed by each MFCs
gear not locked in handle
selected position (on ground,
up lock box not open)
Green Lt
AUTO PRESS (DC BUS 1)
gear downlock engaged
+ 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
NORM
–400 to –500 ft/mn
AUTO mode selection
To be used if VS>-1500 ft/mn
MAN
TEST
digital controller out of
displays alternatively 18800
operation. No more digits in
and –8800, FAULT appears on
landing elevation display
MAN pb
FAULT (Test inhibited in FLT)
digital controller failure. FWS
DUMP
ON (guarded)
both outflow valves fully open
in AUTO mode only
183
SYSTEMS 42/72 - 600
MCDUs (Multifunction WEATHER RADAR
Control Display Unit) CONTROL PANEL
Access to the FMS, MPC, and
ACARS (Data Link) when the
ACARS is installed. COCKPIT DOOR CONTROL
PANEL
Allows to control CDLS
(Cockpit Door Locking
MULTIPURPOSE CONTROL
System)
PANEL (MCP)
Allows cockpit crew to control
the virtual control panel format
(VCP) on MFD
TO CONFIG TEST pb:
Check if the TO configuration
is correct for take off:
POWER LEVER ( PL ) – PWR MGT TO
– Flaps 15°
– Pitch trim in the green band
– TLU LO SPD
EMER & PARKING BRAKE – no AIL LOCK light
CONDITION LEVER (CL) FLAPS
The same test is performed
when advancing the PL with
GA push button this additional requirement:
when depressed the GA FD – Parking Brake released
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
HYD AUX PUMP CONTROL reactivated:
(HOT MAIN BAT BUS) – at next A/C energization
– Aux pump stopped 30” after – after MFC 1B/2B reset
p/b released (MFC supplied) – after pressing RCL pb
– Aux pump stopped after p/b – following TO config test
released (MFC not supplied) The alerts here after are
rearmed as soon as the
triggering condition disappears
IDLE GATE – landing gear
IDLE GATE FAIL – VMO, VFE, VLE
activated when the gate does – Stall warning
not engage automatically – Pitch trim whooler
in flight or does not extend – AP disconnect
automatically on ground
In this case the idle gate lever
enables manual override in
case of failure of the automatic F/O AUDIO
logic CONTROL PANEL
– In flight: push
– On ground pull (an amber
band appears) Manual recording on
DFDR or CVR (when
supplied by GPU)
Manual recording
EFis Control Panel (EFCP) stopped with the
Allows to control: reset P/B
– Display of the MFD pages
(ND, SYST, PERF, MISC, VID
and MAP)
– Navigation Display (ND)
functionalities
– Warning Display (WD)
CAPT AUDIO
CONTROL ACARS & MPC Panel & flood Aileron, rudder & ATPCS test (static
PANEL PRINTER light control stby pitch trims or dynamic)
184
ANNEXES
185
SYSTEMS 42/72 - 600
TAWS TAWS visual alert
GPWS MFD upper window
GPWS switch and associated lights:
If any TAWS mode is activated Displays the different
ON: All basic GPWS modes are operative PULL UP pages selected on the
FLAP OVRD: In reduced flaps landing, to inhib the Alert triggered after the GPWS EFCP:
mode 4 alert alert in mode 1, 2 and terrain and – ND page (Navigation
OFF: All basic GPWS modes inhibited. OFF: light obstacle awareness modes Display: shown here)
come on
– SYST page (System)
FAULT: GPWS FAULT —— > some or all GPWS basic
– PERF page
modes are lost
ACARS message (Performance)
FAULT: TERR FAULT —— > some or all enhanced ATC DLK (ATC Data LinK) is – MAP page (airport
modes are lost illuminated when a message is mapping)
OFF: All enhanced (TCF&TAD) modes inhibited received through the ACARS. – MISC page (in
The message can be read on the provision)
MASTER WARNING – VD page (Video in
MCDU
MASTER CAUTION provision)
AHRS switching P/B
To select the opposite side AHRS
source. Display P/B
When depressed, SYS 2 is The P/B allows to switch formats
illuminated on CAPT side, while (PFD/EWD/MFD) on the DU2, or ND page
CAPT / 2 is illuminated green on on DU1 if DU2 is OFF. (Navigation
F/O side Display)
The CAPT P/B has priority Different mode
selected on the
EFCP:
ADC switching P/B – ARC mode
To select the opposite side ADC – ROSE mode
source. – PLAN mode
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
AUDIO 1 SEL Index Control Panel (ICP) Memo Panel Display VCP window (Vitual Control
FAULT: When the associated Baro setting control Displays the following system Panel)
RCAU part is failed. information when selected Displays the informations about:
ALTN: Affected crew station is FUEL XFEED The COM selection
connected directly to VHF1 if PROP The NAV selection (shown here)
CAPT station is affected. Index Control Panel (ICP) HORN The SURV (surveillance) selection
Speed target control SIDE WINDOW
ENG
AIFRAME DISPLAY UNIT 2 (DU2)
DISPLAY UNIT 1 (DU1) NO DEVICE In the normal configuration, with
In the normal configuration, SEAT BELT CAPT as PF, the MFD format is
with CAPT as PF, the PFD displayed with the ND page.
format is displayed The FMA 1 (Flight Management
Application 1) and the RMA 1 (Radio
Management Application 1) are
included in the DU2 functions
186
ANNEXES
Display P/B
MFD upper window Airspeed Indicator (ASI) The P/B allows to switch
Displays the different pages
formats (PFD/EWD/MFD) on
selected on the EFCP:
the DU4, or on DU5 if DU4 is
– ND page (Navigation
Flight Mode Annuciator (FMA) OFF.
Display)
– SYST page (System: shown
here) ELAPSED TIME P/B
Attitude Display Indicator (ADI)
– PERF page (Performance) When the ELAPS TM P/B is
– MAP page (airport mapping) depressed ON
– MISC page (in provision) the flight time starts
– VD page (Video in provision) Altimeter automatically, on the EWD,
when airborne
LOUDSPEAKERS
VOLUME KNOBS
Individual knob for
each loudspeaker
VCP window (Vitual DISPLAY UNIT 5 Index Control Panel Index Control Panel READING LT knob
Control Panel) (DU5) (ICP) (ICP) Control the
Displays the In the normal Speed target control: Baro setting control: respective spot light
informations about: configuration, with F/O – Speed target selection – Barometric setting
The COM selection as PM, the PFD format Selection of the speed knob
(shown here) is displayed. bug between: The knob is used to set
The NAV selection – AUTO: Speed bug the barometric reference. CONSOLE LT knob
The SURV (surveillance) managed by the FMS Pushing the knob sets Control the lights of
selection (Magenta) standard barometric the associated lateral
– MAN: Speed bug set reference (29.92 INHG / console
Navigation Area manually by the speed 1013.25 Hpa)
With the ND on the knob (Cyan) – DH / MDA knob
DISPLAY UNIT 4 (DU4) MFD, the EHSI is – Speed knob Outer knob permits
Used to set the speed to select between DH AUDIO 2 SEL
In the normal configuration, with displayed on the PFD.
bug (Decision Height) or MDA FAULT: When the
F/O as PM, the MFD format is With an other page on
In MAN mode (Cyan) (Minimum associated RCAU part is
displayed with the SYST page. the MFD, a mini ND is
Descent Altitude). failed.
The FMA 2 (Flight Management displayed on the PFD.
Inner knob is used to ALTN: Affected crew
Application 2) and the RMA 2 The mini ND can be in
set DH or MDA values, station is connected
(Radio Management Application ARC mode or ROSE
depending of the outer directly to VHF2 if F/O
2) are included in the DU4 mode, selected on the
knob position. station is affected.
functions EFCP.
187
SYSTEMS 42/72 - 600
Blinker indicator
Normal/100% selector
188
ANNEXES
189
ANNEXES
ANNEX 2. ABBREVIATIONS
A BRG Bearing
AAS Anti-icing Advisory System BRK Brake
AC Alternating Current B-RNAV Basic Area Navigation
A/C Aircraft BRT Bright
ACARS ARINC Communication Addressing and BTC Bus Tie Contactor
Reporting System BTR Bus Tie Relay
AC BTC AC Bus Tie Contactor
AC BTR AC Bus Tie Relay C
ACW Alternating Current Wild Frequency CAB Cabin
ADC Air Data Computer CAC Core Avionic Cabinet
ADF Automatic Direction Finder CAPT Captain
ADI Attitude Director Indicator CAT Category
ADN Avionic Data Network C/B Circuit Breaker
ADS Air Data System CDI Course Deviation Indicator
AFCS Automatic Flight Control System CDLS Cockpit Door Locking System
AFDX Avionic Full DupleX CHAN Channel
A/FEATH Auto Feathering CHC Charge Contactor
AFCA Auto Flight Control Application CL Condition Lever
AFT Rear Part CLA Condition Lever Angle
AFU Auto Feather Unit CLB Climb
AGB Accessory Gear Box CLR Clear
AHRS Attitude and Heading Reference System CMA Centralized Maintenance Application
AHRU Attitude and Heading Reference Unit CMS Cabin Management System
AIL Aileron CMPTR Computer
ALT Altitude CMU Communication Management Unit
ALTM Altimeter (ACARS)
ALTN Alternate COM Communication
AMP Ampere COMPT Compartment
AOA Angle of Attack CONFIG Configuration
AP Auto-Pilot CPL Auto Pilot Coupling
APP Approach CPM Core Processing Module
APU Auxiliary Power Unit CRC Continuous Repetitive Chime
APAU AutoPilot Actuator Unit CRS Course
ARINC Aeronautical Radio INCorporated CRZ Cruise
A 429 ARINC 429 CTL Control
ARM Armed CVR Cockpit Voice Recorder
ASI Air Speed indicator
ASYM Asymmetry D
ATC Air Traffic Control DC Direct Current
ATPCS Automatic Take off Power Control DCA Data Concentration Application
System DELTA P Differential Pressure
ATT Attitude DEV Deviation
ATTND Attendant DFDR Digital Flight Data Recorder
AUTO Automatic DGR Degraded
AUX Auxiliary DH Decision Height
AVAIL Available DIFF Differential
DISCH Discharge
B DIM Light Dimmer
BARO Barometric DIST Distance
BaroVNAV Barometric Vertical NAVigation DLK Data LinK
BAT Battery DME Distance Measuring Equipment
BC Back Course DMU Data Management Unit
BITE Built in Test Equipment DN Down
BPCU Bus Power Control Unit DSPL Display
BPU Battery Protection Unit DU Display Unit
191
SYSTEMS 42/72 - 600
E H
EEC Engine Electronic Control HBV Handling Bleed Valve
EFCP EFis Control Panel HDG Heading
EFIS Electronic Flight Instrument System HF High Frequency
HI High
EHSI Electronic Horizontal Situation Indicator
HLD Hold
EHV Electro Hydraulic Valve
HMU Hydromechanical Unit
ELEC Electrical
HP High Pressure
ELV Elevation HSI Horizontal Situation Indicator
EMER Emergency HTG Heating
ENG Engine HYD Hydraulic
EQPT Equipment
ESS Essential I
ETOPS Extended Twin Operations IAS Indicated Air Speed
EWD Engine & Warning Display ICP Index Control Panel
EXT Exterior, External IDT Ident
IESI Integrated Electronic Standby Instrument
IGN Ignition
F ILS Instrument Landing System
F Farenheit
IMA Integrated Modular Avionics
FAIL Failed, Failure IND Indicator
FAP Flight Attendant Panel IN/HG Inches of Mercury
FCOC Fuel Cooled Oil Cooler INHI Inhibit
FCU Fuel Control Unit INOP Inoperative
FD Flight Director INST Instrument
FDA Flight Data Application INT Interphone
FDAU Flight Data Acquisition Unit INV Inverter
FEATH, FTR Feathered, Feathering IOM Input Output Module
ISOL Isolation
FF Fuel Flow
ITT Inter Turbine Temperature
FGC Flight Guidance Computer
FGCP Flight Guidance and Control Panel JK
FGS Flight Guidance System KHZ Kilo-Hertz
Fl Flight Idle KT Knot
FLT Flight
FMA Flight Management Application L
FMA Flight Modes Annunciators LAT Lateral
FMS Flight Management System LAV Lavatory
F/O First Officer LB Pound
LDG Landing
FOS Flight Operations Software
L/G Landing Gear
FQI Fuel Quantity Indication
LH Left Hand
FT Foot, Feet
LMU Light Management Unit
FU Fuel Used LNAV Lateral Navigation
FWD Forward LO Low
FWS Flight Warning System LOC Localizer
LO-PR Low Pressure
G LP Low Pressure
GA Go Around LPV Localizer Performance with Vertical
GCU Generator Control Unit guidance
GEN Generator LT Light
LVL Level
GI Ground Idle
GND Ground
M
GPS Global Positioning System
MAX Maximum
GPU Ground Power Unit MAP Mapping
GRD Ground MB Millibar
G/S Glide Slope MC Master Caution
GSPD Ground Speed MCDU Multifunction Control Display Unit
192
ANNEXES
MCP Multifunction Control Panel PNL Panel
MCT Maximum Continous POS Position
MECH Mechanic P-RNAV Precision Area Navigation
MFC Multi Function Computer PRESS Pressurization, Pressure
MFCU Mechanical Fuel Control Unit PRIM Primary
MFD Multi Function Display PRKG Parking
MGT Management PROP Propeller
MHZ Megahertz PSI Pound per Square Inch
MIC Microphone PSU Pax Service Unit
MLG Main Landing Gear PT Point
MIN Minimum PT (TCAS) Proximity traffic
MIP Main Instrument Panel PTB Pitch Trim Box
MISC Miscellaneous PTT Push To Talk, Push To Test
MKR Marker PTW Pitch Thumb Wheel (same as PW)
MLW Maximum Landing Weight PVM Propeller Valve Module
MM Millimeter PWR Power
MMO Maximum Operating Mach PW Pitch Wheel (same as PTW)
MOD Modification
MPC Multi Purpose Computer Q
MPU Micro Processor Unit QAR Quick Access Recorder
MSG Messages QT Quart
MSN Manufacturer Serial Number QTY Quantity
MTOW Maximum lake off Weight
MW Master Warning R
MZFW Maximum Zero Fuel Weight RA (TCAS) Resolution Advisory
RA Radio Altitude
N RAD/ALT Radio Altitude
NAC Nacelle RAD/INT Radio/Interphone
NAV Navigation RCAU Remote Control Audio Unit
ND Navigation Display RCDR Recorder
NDB Non Directional Beacon RCL Recall
NEG Negative RCU Releasable Centering Unit
NH High Pressure Spool Rotation Speed RECIRC Recirculation
NIL Nothing, No Object REV Reverse
NL Low Pressure Spool Rotation Speed RGA Reserve Go-Around
NM Nautical Mile RGB Reduction Gear Box
NORM Normal RH Right Hand
NP Propeller Rotation Speed RLY Relay
N/W Nose Wheel RMA Radio Management Application
NWS Nose Wheel Steering RMI Radio Magnetic Indicator
RMS Radio Management System
O RNP Required Navigation Performance
OAT Outside Air Temperature RNP AR RNP with Authorization Required
OVBD Overboard RPM Revolution Per Minute
OVERTEMP Overtemperature RTO Reserve Take-Off
OVHT Overheat RUD Rudder
OVRD Override
OXY Oxygen S
SAT Static Air Temperature
P SBY Stand By
PA Passenger Address SC Single Chime, Starter Contactor
PB Push Button SEL Selector
PEC Propeller Electronic Control SGL Single
PED Pedestal SGU Symbol Generator Unit
PERF Performance SMK Smoke
PFD Primary Flight Display SMKG Smoking
PIU Propeller Interface Unit S/O (SO) Shut Off
PL Power Lever SOV Shut Off Valve
PLA Power Lever Angle SPD Speed
193
SYSTEMS 42/72 - 600
SPLR Spoiler UNDV Undervoltage
SPLY Supply UNLK Unlock
STBY Stand By UTLY Utility
STRG Steering
SSFDR Solid State Flight Data Recorder V
SURV Surveillance VC Calibrated Airspeed
SVCE Service VCP Virtual Control Panel
SW Switch VENT Ventilation
SWM gateway and SWitch Module VERT Vertical
SYS System VHF Very High Frequency
VID Video
T VMO Maximum Operating Speed
TA (TCAS) TRAFFIC Advisory VNAV Vertical Navigation
TAD Terrain Awareness Display VOR VHF OMNI Directional Range
TAS True Air Speed VSI Vertical Speed Indicator
TAT Total Air Temperature
TAWS Terrain Awareness Warning System W
TCF Terrain Clearance Floor WARN Warning
TCS Touch Control Steering WOW Weight On Wheel
TEMP Temperature XFEED Cross feed
TGT Target XFR Transfer
TK Tank
TLU Travel Limiting Unit XY
T/O (TO) Take off YD Yaw Damper
TOW Take off weight YDAU Yaw Damper Actuator Unit
TQ Torque
TRU Transformer Rectifier Unit Z
TTG Time To Go ZA Aircraft Altitude
ZCTH Theoretical Cabin Altitude
U ZFW Zero Fuel Weight
U/F Underfloor ZP Pressure Altitude
UHF Ultra High Frequency ZRA Radio Altimeter Altitude
UNCPL Uncouple
194
Dear Readers,
Yours faithfully,
e-mail: atc@atr.fr