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For Training Purposes OnlySept 04
7-i
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
Chapter 7: Electronic Display System
TABLE OF CONTENTS
Page
Introduction .........................................................................................................................7-1Aural and Visual Warning System ......................................................................................7-1
EICAS Display.........................................................................................................7-3Systems Synoptics........................................................................................................7-4
Status Page.............................................................................................................7-4Bleed/Anti-Ice Synoptic Page..................................................................................7-5Air Conditioning Synoptic Page...............................................................................7-6Hydraulic Synoptic Page .........................................................................................7-7AC Electrical Synoptic Page ...................................................................................7-8DC Electrical Synoptic Page ...................................................................................7-9Fuel Synoptic Page ...............................................................................................7-10Flight Controls Synoptic Page...............................................................................7-11
Description ........................................................................................................................7-12Electronic Display System...........................................................................................7-12Crew Alerting System..................................................................................................7-13
Master Warning/Master Caution Lights.................................................................7-14Warning/Caution Messages ..................................................................................7-15Advisory/Status Messages....................................................................................7-16
Message Scrolling.......................................................................................................7-18Aurals ..........................................................................................................................7-19
Alphabetical List of Voice Messages.....................................................................7-20Aural Warning Test ...............................................................................................7-22Aural Warning Panel .............................................................................................7-23
Inhibits.........................................................................................................................7-23Takeoff Configuration Warnings..................................................................................7-26Landing Configuration Warning...................................................................................7-26Stall Warning...............................................................................................................7-27Reversion Control Panel .............................................................................................7-28
EICAS Reversion Control......................................................................................7-30SG Reversion Control ...........................................................................................7-32
ADC Reversion ...........................................................................................................7-36IRS Reversion .............................................................................................................7-37EICAS Control Panel...................................................................................................7-38Systems SELECT Control...........................................................................................7-39
Systems SELECT .................................................................................................7-40Flight Data Recorder ...................................................................................................7-41Central Aircraft Information and Maintenance System (CAIMS).................................7-41
Messages Summary .............................................................................................7-44Electronic Flight Instruments.............................................................................................7-63
EFIS Network ..............................................................................................................7-64Description ........................................................................................................................7-65
Pitot-Static System......................................................................................................7-65
7-ii For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
Pitot-Static Schematic ........................................................................................... 7-66Air Data System .................................................................................................... 7-67
Primary Flight Instruments .......................................................................................... 7-68Primary Flight Display ........................................................................................... 7-69Airspeed Tape....................................................................................................... 7-71Altitude Tape......................................................................................................... 7-74Radio Altitude........................................................................................................ 7-76Attitude Director Indicator (ADI) ............................................................................ 7-77Vertical Speed Indicator (VSI)............................................................................... 7-81
PFD Control Panel ...................................................................................................... 7-82MINIMUMS Knob .................................................................................................. 7-83PFD (HSI).............................................................................................................. 7-84BARO SET Knob................................................................................................... 7-85
Multifunction Display (MFD)........................................................................................ 7-86Map Format........................................................................................................... 7-86Plan Format........................................................................................................... 7-87MFD Control Panel................................................................................................ 7-88Traffic Collision Avoidance System (TCAS) Button .............................................. 7-89Map/Plan Button.................................................................................................... 7-90Menu Button.......................................................................................................... 7-91Terrain (TERR) Button .......................................................................................... 7-95Navaids/Airports (NAV/APT) Button...................................................................... 7-96
Normal Procedures (NORM)....................................................................................... 7-97Waypoint Listing.................................................................................................... 7-97NORM - Disclaimer ............................................................................................... 7-98NORM - Before Start............................................................................................. 7-99Abnormal Procedures (ABN) Button ................................................................... 7-100
Emergency Procedures ............................................................................................ 7-101Standby Attitude Indicator......................................................................................... 7-102Standby Altimeter/Airspeed Indicator........................................................................ 7-103Standby Magnetic Compass ..................................................................................... 7-104Clock ......................................................................................................................... 7-105
Time Setting ........................................................................................................ 7-106Standby Airspeed/Altitude/Altimeter (if installed) ...................................................... 7-107PFD Comparison Monitor Annunciations.................................................................. 7-108System Integration .................................................................................................... 7-108Electronic Display System EICAS Messages ........................................................... 7-109EMS Circuit Protection.............................................................................................. 7-114
For Training Purposes OnlySept 04
7-1
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
INTRODUCTIONThe following chapter introduces the BD 700 Electronic Display System. The first part of this chapter covers the aural and visual warning system whereas the second part covers the electronic flight instrument system.
AURAL AND VISUAL WARNING SYSTEMThe aural and visual warning system provides indications to warn of potentially unsafe operating conditions or airplane configurations, system malfunctions, and non-normal situations. Indications can be generated by the following:
• Crew alerting subsystem within the Engine Indication and Crew Alerting System (EICAS)
• Enhanced Ground Proximity Warning System (EGPWS)• Weather Radar (WX) system• Traffic alert and Collision Avoidance System (TCAS)• Altitude alert portion of the Air Data Computer (ADC)• Stick shaker portion of the Stall Protection System (SPS)
EICAS provides the crew with the necessary displays for airplane engine control and monitoring, control surface monitoring, and all major subsystem synoptic displays. During normal operation the engine and control surface information is displayed on the EICAS Display Unit (DU3) and the system synoptic information is displayed on the SYSTEMS display (DU4).
TOTAL FUEL (LBS) 4155O
1.54
146OO 146OO1OOOO
N2
FF (PPH)
OIL TEMP
OIL PRESS
93.4575O11581
1.65
CRZEPR
IGN
START START
IGN
NDSTAB
1.54
1.65
73.3
T/ON1SYNC
73.3
789
ITTSYNC
789 DN DN DN
OUT
3O
GEAR
–TRIMS–
NL NRRUDDER
AIL
RWDLWD
7.2
NU
93.4575O11581
235O
NO TAKEOFFPARK/EMER BRAKE ON
END1234567
20
10
30
20
10
30
09
8
7
65
4
3
2
1100 FEET
ALT
1 00032
4
10 13
mb/hPa
29 9 2
IN HG
IAS KNOTS
220200180 250
BARO
Honeywell HoneywellHoneywell Honeywell
13000.00
00
90
13 13
2019 20
22 2220
OXYGEN
AFTCABIN (°C)
FWDCABIN (°C)
CKPT (°C)
OPEN OPEN
OUTFLOW VALVES
CAB ALT
P
CAB RATE
LDG ELEV
00
1 2
1 2
1 2
QTY
ENG
APU
RES
OIL (QTS)
APU DOOR 11.2°
RPM EGT
BRAKE TEMP
11.5
650100
0603 03 03
11.55.26.0
%
% %
Honeywell
9500
29.92
AT1
VTA
M
0.450M
FMS1LOC1DTK
360
HDG330
10400
20
20
10
10
20
20
10
10
9500
10500
300
220
210
200
190
180
170
F3
LE
F1
2160
150
1856
4
N33
30
W24
21S
15
12
E6
3
0
1
2
3
1
2
3
ATT
HDGT
EICAS
GS
LOC
HDG
RAD
IASALT
HDG2
VOR 1
ADF 2
0010020
80
THRUST HDG ASEL ATT 2AP1VAPP VNAV ADC 3
9500
29.92
AT1
VTA
M
0.450M
FMS1LOC1DTK
360
HDG330
10400
20
20
10
10
20
20
10
10
9500
10500
300
220
210
200
190
180
170
F3
LE
F1
2160
150
1856
4
N33
30
W24
21S
15
12
E6
3
0
1
2
3
1
2
3
ATT
HDGT
EICAS
GS
LOC
HDG
RAD
IASALT
HDG2
VOR 1
ADF 2
0010020
80
THRUST HDG ASEL ATT 2AP1VAPP VNAV ADC 3
WX
ET
NO BEARINGRA 9 . 8NM +13TA 4 . 5NM -04
SAT
GSPD
TERR
-56
TAT
TAS
-40
234
345
INHIB
LX
00 : 10 0 . 05L
MAG2HDG315
ETE 1+36
12 . 5KDVT
NM
FLBELOW
TCAS TEST
FMS1360
N
5 5
3
6
33
30
- 02
- 02
+ 12- 04
KABC
KKLM
KKLM
TOC
TOC
KGHJ
KGHJ
LUF
KDEF
KDEF
4000 4000
FL180
+ 09
GX
_0
7_
00
1DU 1
PFD 1 MFD 1
DU 2
EICAS
DU 3
SYSTEMS
DU 4
MFD 2
DU 5
PFD 2
DU 6
WX
T5 . 0%
LX
G85%
STAB
ET 235°50 . 0NM00 : 10
TRU
N
ETE1+36
12 . 5KDVT
NM
FMS1
50 50
KNOP
KKLM
TOC
KGHJ
KABCLUF
KDEF
134
136
N 023° 29 . 6W 112° 01 . 5
SAT
GSPD
TERR
-56
TAT
TAS
-40
234
345
INHIB
KKLMTOC
KGHJKDEF
4000 4000
FL180
7-2 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
EICAS displays:• Primary engine parameters • Secondary engine parameters• Fuel quantities • Landing gear position• Flaps/slats/spoilers positions • Surface trim indication• Crew Alerting System (CAS) messages
SYSTEMS provides synoptic displays of:• Bleed/Anti-Ice • Air Conditioning• Hydraulics • AC Electrical• DC Electrical • Fuel• Flight Controls • Status
For Training Purposes OnlySept 04
7-3
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
EICAS DISPLAY
L ENG FLAMEOUTFUEL LO QTYFUEL IMBALANCEYD OFF
GLD MANUAL ARMPARK/EMER BRAKE ON
<– FUEL XFER ON
TOTAL FUEL (LBS) 415OO
1.54
146OO 146OO1OOOO
N2
FF (PPH)
OIL TEMP
OIL PRESS
93.4575O11581
1.65
CRZEPR
IGN
START START
IGN
NDSTAB
1.54
1.65
73.3
T/ON1SYNC
73.3
789
ITTSYNC
789
–TRIMS–
NL NRRUDDER
AIL
RWDLWD
7.2
NU
93.4575O11581
23OO
L ENG FLAMEOUTFUEL LO QTYFUEL IMBALANCEYD OFF
GLD MANUAL ARMPARK/EMER BRAKE ON
<– FUEL XFER ON
TOTAL FUEL (LBS) 415OO
1.54
146OO 146OO1OOOO
N2
FF (PPH)
OIL TEMP
OIL PRESS
93.4575O11581
1.65
CRZEPR
IGN
START START
IGN
NDSTAB
1.54
1.65
73.3
T/ON1SYNC
73.3
789
ITTSYNC
789 DN DN DN
OUT
3O
GEAR
–TRIMS–
NL NRRUDDER
AIL
RWDLWD
7.2
NU
93.4575O11581
23OO
Crew Alerting System Window14 message lines with Gear/Slats/Flaps pop-up displayed.
Slats/Flaps, Spoilers, and Gear Position Pop-UpThe pop-up display will be removed from the primarypage (in flight only) 30 seconds after gear andflaps indicate up, and nomalfunctions exist, or Flight spoilers out.
The pop-up display will appear with flap selectiongreater than zero degrees, gear selected downand/or if any predetermined malfunctions exist.
thepredetermined
TRIMSIndications for Aileron, Rudder, and Stabilizer trim.
Crew Alerting System Window24 message lines with Gear/Slats/FlapsPop-up not displayed.NOTE:
EICAS will automatically be displayedwhen the airplane is powered up(BATT MASTER ON).
Engine IndicatingIndications of EPR, N1, ITT, N2,Fuel Flow, Oil temperatureand Pressure.
FuelIndications of total fuel quantity andindividual tank quantity.
GX
_0
7_
00
2
Aft tank not applicable to Global 5000
Aft tank not applicable to Global 5000
7-4 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
SYSTEMS SYNOPTICSTo view SYSTEMS synoptic displays, select the appropriate button on the EICAS control panel.
STATUS PAGE
NOTESTAT page will automatically be displayed when airplane is powered up (BATT MASTER ON).
STAT
HYDAC
ELECBLEED
AIRCOND
DCELEC
FUELFLT
CTRL
SCROLL
EICAS
SYSTEMS SELECT
NORMMFD 2MFD 1
CKPT/CABINTemperatureIndications ofcockpit, forward,and Aft Cabinselected (cyan)and actual (green)temperature.
OIL Q YTIndication ofengine, APU andreservoir oilquantity.
APUIndication of APURPM and EGT.Indication of APUdoor position iffailed in otherthan commandedposition.
DOORSIndication ofpassenger entrydoor, overwingemergency exit,baggage doorand servicedoors.
BRAKE TEMPIndication of braketemperatures.
OUTFLOWVALVESIndication ofoutflow valvesposition (manualmode only).
OXYGENIndication ofoxygen quantity.
CAB ALT, Pand CAB RATEIndications ofcabin altitude,cabin differentialpressure andcabin rate ofclimb. Cabin rateshown in manualonly.
GX
_07_003
OIL QTY (QTS)
ENG
APU
RES
APU DOOR 11.2°
RPM EGT
BRAKE TEMP
12 . 3
1300
90%
13% 13%
0 . 00
650100
0603 03 03
12.35.23.2
20
19 20
22 22
20
CABIN (°C) CABIN (°C)
OXYGEN
AFTCKPT (°C)
OPEN OPEN
OUTFLOW VALVES
CAB ALT
CAB RATE
P
00
1 2
1 2
1 2
For Training Purposes OnlySept 04
7-5
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
BLEED/ANTI-ICE SYNOPTIC PAGE
STAT
HYDAC
ELECBLEED
AIRCOND
DCELEC
FUELFLT
CTRL
SCROLL
EICAS
SYSTEMS SELECT
NORMMFD 2MFD 1
GX
_0
7_
00
4
BLEED / ANTI-ICE
APU
LP
AIRCOND
HP
L
LP
HP26PSI
26PSI
R
7-6 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
AIR CONDITIONING SYNOPTIC PAGE
STAT
HYDAC
ELECBLEED
AIRCOND
DCELEC
FUELFLT
CTRL
SCROLL
EICAS
SYSTEMS SELECT
NORMMFD 2MFD 1
GX
_3
1_
00
5
AIR CONDITIONING
RAM AIR
BLEED BLEED
12 °C 15 °C
23 °C23 °C23 °C
R PACKL PACK
CKPT
°C20FWD
°C20AFT
°C23
20°C 20°C 23°C
TRIM AIR
For Training Purposes OnlySept 04
7-7
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
HYDRAULIC SYNOPTIC PAGE
STAT
HYDAC
ELECBLEED
AIRCOND
DCELEC
FUELFLT
CTRL
SCROLL
EICAS
SYSTEMS SELECT
NORMMFD 2MFD 1
GX
_0
7_
00
6
RUDL ELEV
L AILFLT SPLRS
GND SPLRSL REVERSER
RUDELEV RAIL RFLT SPLRSGEARREVERSER R
RUDL ELEV RL AIL R
GND SPLRSGEAR
NOSE STEERPARK/ BRAKEEMER
INBDBRAKES
PSI3050
OUTBDBRAKES
NORM
2B3A 3B
HYDRAULIC
3050PSI
3050PSI
2A
RAT
3050PSI
22 °C
1B
62%
38 °C
61%
20 °C
60%
1A
7-8 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
AC ELECTRICAL SYNOPTIC PAGE
STAT
HYDAC
ELECBLEED
AIRCOND
DCELEC
FUELFLT
CTRL
SCROLL
EICAS
SYSTEMS SELECT
NORMMFD 2MFD 1
GX
_0
7_
00
7
AC ELECTRICAL
AC BUS 1
AC ESSBUS
AC BUS 4
11515
V
KVA
AC BUS 2
11512
V
KVA
AC BUS 3
11512
V
KVA
1150
400
V
KVA
HZ
11515
V
KVA
GEN2
GEN1
GEN3
GEN
APU
GEN4
For Training Purposes OnlySept 04
7-9
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
DC ELECTRICAL SYNOPTIC PAGE
STAT
HYDAC
ELECBLEED
AIRCOND
DCELEC
FUELFLT
CTRL
SCROLL
EICAS
SYSTEMS SELECT
NORMMFD 2MFD 1
GX
_0
7_
00
8
DC ELECTRICALAC BUS 2FEEDER
DC BUS 1
TRU 1
28V
35A
24V 25V
0A 0A
20°C20°C
AC BUS 1FEEDER
DC ESSBUS
ESSTRU 1
28V
35A
AC ESSBUS
BATT BUS
DC EMERBUS
AV BATTDIR BUS
AVBATT
APUBATT
APU BATTDIR BUS
ESSTRU 2
28V
35A
AC BUS 3FEEDER
DC BUS 2
TRU 2
28V
35A
7-10 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
FUEL SYNOPTIC PAGE (Global 5000 – See Appendix 1)
STAT
HYDAC
ELECBLEED
AIRCOND
DCELEC
FUELFLT
CTRL
SCROLL
EICAS
SYSTEMS SELECT
NORMMFD 2MFD 1
Honeywell
PPP
P
P P
P
PP
P
FUEL
AUX
–1O°C°C
APU
–1O°C°C
TOTAL FUELTOTAL FUEL
4355OLBS
15O5OLBS
AUX
LBS1115O
15O5OLBS
FUEL USEDFUEL USED
OLBS
LO PRESSLO PRESS
32°C°C23OOLBS
32°C°C
LO PRESSLO PRESS
GX
_0
7_
00
9
For Training Purposes OnlySept 04
7-11
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
FLIGHT CONTROLS SYNOPTIC PAGE
STAT
HYDAC
ELECBLEED
AIRCOND
DCELEC
FUELFLT
CTRL
SCROLL
EICAS
SYSTEM SELECT
NORMMFD 2MFD 1
FLIGHT CONTROLSFLIGHT CONTROLS
FLAP 3O
AILELEV
RUDDER
SLAT OUT
AILELEV
GX
_0
7_
01
0
7-12 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
DESCRIPTION
ELECTRONIC DISPLAY SYSTEMThe Electronic Display System (EDS) provides the crew with displays for aircraft control, navigation, engine control and monitoring and system synoptics. Other systems information displayed are WX, TCAS, EGPWS, and the Lightning Sensor System (LSS).Data is transmitted from aircraft systems to 4 dual channel Data Acquisition Units (DAU) through the Avionics Standard Communication Bus (ASCB) to 3 Integrated Avionics Computers (IAC), and finally to the Display Units (DU).The 4 dual channel DAUs operate with one channel active and the other channel on standby, with both channels updating data at the same time.The ASCB is the principal communications network interconnecting the system components. Data traffic flow on the ASCB is managed by 3 bus controllers (one bus controller in each IAC). Only one bus controller is in control at a time with the other 2 in standby status.The three IACs each contain a Symbol Generator (SG) and a Fault Warning Computer (FWC). The SGs process data from various sources and output the data to the 6 DUs. The FWC compares sensor input data, verifies all critical display data and displays Warning, Caution, Advisory and Status messages as applicable.
GX
_0
7_
011
IAC 3
FWC SG
IAC 2
FWC SG
IAC 1
FWC SG
DAU 1
CH A CH B
DAU 2
CH A CH B
DAU 4
CH A CH B
DAU 3
CH A CH B
AIRPLANE DATA
ASCB
DU 2 DU 3 DU 4 DU 5DU 1 DU 6
For Training Purposes OnlySept 04
7-13
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
The IACs perform the following functions:
CREW ALERTING SYSTEMThe crew alerting system portion of EICAS continually monitors all airplane systems. If an operationally significant fault occurs on a system, EICAS displays a crew alerting message on the EICAS display unit. In addition to the display messages, some crew alerts are also indicated by aural tones, voice advisories, MASTER WARNING and MASTER CAUTION lights.
All crew alerting system messages are divided into one of four categories and in the following priority:
• Warning messages: RED• Caution messages: AMBER• Advisory messages: CYAN• Status messages: WHITE
Red warning messages are generated when immediate recognition and corrective or compensatory action is required. They are the most urgent type of crew alerts. They always appear at the top of the message stack on the EICAS display. All warning messages cause the MASTER WARNING lights on the glareshield to flash and generate an aural alert of a triple-chime. Specific warnings are also accompanied by a voice message. Once acknowledged, by pressing the warning light, the light will extinguish and the system will re-arm to indicate any additional warning messages. Failure to re-arm the system will mean that any subsequent CAS Warning Message will not be announced by the triple chime and Master Warning lights, however, related voice messages will remain valid.
NOTEThe Stall Warning System is not part of the MASTER WARNING light system. The approach of an aerodynamic stall will be indicated by a separate warning indication.
IAC 1 IAC 3 IAC 2
EFIS, EICAS, FWC, CAIMS EFIS, EICAS, FWC, CAIMS EFIS, EICAS, FWC, CAIMS
Tone/Aural generator LASERTRACK (if installed) Tone/Aural generator
Flight Management System FMS 3 (if installed) Flight Management System
Autothrottle Autothrottle
AFCS AFCS
7-14 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
MASTER WARNING/MASTER CAUTION LIGHTSTwo MASTER WARNING switch/lights come on flashing when any EICAS warning message occurs. The lights remain on as long as the warning exists. Pushing either MASTER WARNING switch/light extinguishes both MASTER WARNING lights for the duration of that warning and resets the lights for future warnings.
Pushing the MASTER WARNING also silences the related aural warnings except for the following cases:
• Configuration warnings• Gear horn
Two MASTER CAUTION switch/lights flash when any caution occurs. Pushing either MASTER CAUTION switch/light extinguishes both MASTER CAUTION lights for the duration of that caution and resets the lights for future cautions.
Certain aural alerts/voice messages are not part of MASTER WARNING/MASTER CAUTION light alerting system. The following aural alerts/voice messages will not trigger a MASTER WARNING/MASTER CAUTION light:
- Stall warnings - Trim clacker- EGPWS/TCAS (voice and aurals) - Autopilot disconnect cavalry charge- Overspeed continuous horn (A-Chord) - Gear horn
MINIMUMSBARO HpaRAD IN
BARO SETNAV SRC
BRG V/L BRGFMS
HSI
Honeywell PUSH STD
MINIMUMSBARO HpaRAD IN
BARO SETNAV SRC
BRG V/L BRGFMS
HSI
Honeywell PUSH STD
MASTERWARNING/CAUTION
ROLL SPLRS
PLT CONT
ROLLSEL
PLTROLL
WARNING
CAUTION
DIMOFF
BRT
HUD
MASTERWARNING/CAUTION
ROLL SPLRS
CPLT CONT
ROLLSEL
CPLTROLL
WARNING
CAUTION
SPD MANFMSCRS 1 CRS 2
PUSH DCT PUSH DCT
ALTHDG
DN
UP
P
I
T
C
H
Honeywell
FD FDAP
CPL
YD
FLC NAV BANKHDG VNAV ALT
APR VS
BC
PUSH CHG PUSH SYNC
MASTERWARNING/CAUTION
WARNING
CAUTION
MASTERWARNING/CAUTION
WARNING
CAUTION
GX
_0
7_
01
2
MASTERWARNING/CAUTION
ROLL SPLRS
PLT CONT
ROLLSEL
PLTROLL
WARNING
CAUTION
DIMOFF
BRT
HUD
MASTERWARNING/CAUTION
ROLL SPLRS
CPLT CONT
ROLLSEL
CPLTROLL
WARNING
CAUTION
SPD MANFMSCRS 1 CRS 2
PUSH DCT PUSH DCT
ALTHDG
DN
UP
P
I
T
C
H
Honeywell
FD FDAP
CPL
YD
FLC NAV BANKHDG VNAV ALT
APR VS
BC
PUSH CHG PUSH SYNC
MASTERWARNING/CAUTION
WARNING
CAUTION
MASTERWARNING/CAUTION
WARNING
CAUTION
GX
_0
7_
01
3
MINIMUMSBARO HpaRAD IN
BARO SETNAV SRC
BRG V/L BRGFMS
HSI
Honeywell PUSH STD
MINIMUMSBARO HpaRAD IN
BARO SETNAV SRC
BRG V/L BRGFMS
HSI
Honeywell PUSH STD
For Training Purposes OnlySept 04
7-15
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
WARNING/CAUTION MESSAGESWarning messages cannot be removed from view unless the applicable failure has been rectified. If the failure is rectified, messages which appeared below the deleted message will move up one line. When a new fault occurs, the new message will move to the top of the stack.
Amber caution messages are generated when immediate crew awareness is required and subsequent crew action will be required. Caution messages appear immediately below the warnings messages in the message stack on the EICAS display. All cautions cause the MASTER CAUTION lights on the glareshield to flash and have an aural alert consisting of a single chime. Once acknowledged by pressing the CAUTION Light, the flashing stops and the system is re-armed to indicate any further caution messages. Failure to re-arm the system will mean that any subsequent CAS Caution Message will not be announced by the single chime and Master Caution lights.
Caution messages can be paged and scrolled from view using the SCROLL knob on the EICAS control panel. If a new abnormal situation occurs, the corresponding caution message will flash and the remaining messages will remain steady. The new message will be displayed at the top of the stack. To view all of the non-displayed messages, turn the SCROLL knob on the EICAS control panel.
L ENG FIRE
GX
_0
7_
01
4
Triple Chime
“LEFT ENGINE FIRE”
Glareshield
Aural
EICAS Display
MASTERWARNING/CAUTION
WARNING
CAUTION
L ENG FLAMEOUT
GX
_0
7_
01
5Single Chime
Glareshield
Aural
EICAS Display
MASTERWARNING/CAUTION
WARNING
CAUTION
STAT
HYDAC
ELECBLEED
AIRCOND
DCELEC
FUELFLT
CTRL
SCROLL
EICAS
SYSTEMS SELECT
NORMMFD 2MFD 1
ScrollKnob
EICAS Control Panel
GX
_0
7_
01
6
7-16 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
ADVISORY/STATUS MESSAGESCyan advisory messages are generated when crew awareness is required and subsequent crew action may be required. Advisory messages appear immediately below the caution message in the message stack on the EICAS display. When a new advisory message appears, it will flash for 5 seconds then remain steady. There is no aural alert for advisory messages.
Advisory messages can be paged and scrolled from view using the SCROLL knob on the EICAS control panel. To view all of the non-displayed messages, turn the SCROLL knob on the EICAS control panel.
White status messages are generated to indicate non-normal pilot selections and are reminders to the crew. They are set in the message stack below the advisories. There is no aural alert for status messages.
L REVERSER FAULT
EICAS Display
GX
_0
7_
01
7
L ENG SOV CLSD
EICAS Display
GX
_0
7_
01
8
For Training Purposes OnlySept 04
7-17
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
Status messages can be scrolled from view using the SCROLL knob on the EICAS control panel. To view all of the non-displayed messages, turn the SCROLL knob on the EICAS control panel.
The EICAS message window displays up to 14 messages with the Gear/Slats/Flaps pop-up icon displayed. With the Gear/Slats/Flaps pop-up icon not displayed, the window can display up to 24 messages.
If there are non-displayed messages above the top of the display or below the bottom of the display, “xxx↑ messages ↓xxx” symbols will appear at the bottom of the message window. The number of non-displayed messages will be indicated beside the “ ↑ ” or “ ↓ ” arrows. If there are no more messages, an “END” symbol will appear below the last message. The color of the status line corresponds to the highest level of messages not displayed. Warning messages cannot be scrolled from view, they will remain at the top of the message stack.
L ENG FLAMEOUTFUEL LO QTYFUEL IMBALANCEYD OFF
GLD MANUAL ARMPARK/EMER BRAKE ON
<– FUEL XFER ON
TOTAL FUEL (LBS) 415OO
1.54
146OO 146OO1OOOO
N2
FF (PPH)
OIL TEMP
OIL PRESS
93.4575O11581
1.65
CRZEPR
IGN
START START
IGN
NDSTAB
1.54
1.65
73.3
T/ON1SYNC
73.3
789
ITTSYNC
789 DN DN DN
OUT
3O
GEAR
–TRIMS–
NL NRRUDDER
AIL
RWDLWD
7.2
NU
93.4575O11581
23OO
L ENG FLAMEOUTFUEL LO QTYFUEL IMBALANCEYD OFF
GLD MANUAL ARMPARK/EMER BRAKE ON
<– FUEL XFER ON
TOTAL FUEL (LBS) 415OO
1.54
146OO 146OO1OOOO
N2
FF (PPH)
OIL TEMP
OIL PRESS
93.4575O11581
1.65
CRZEPR
IGN
START START
IGN
NDSTAB
1.54
1.65
73.3
T/ON1SYNC
73.3
789
ITTSYNC
789
–TRIMS–
NL NRRUDDER
AIL
RWDLWD
7.2
NU
93.4575O11581
23OO
Gear/Slats/FlapsPop-UpIcon
14messages 24
messages
GX
_0
7_
01
9
CRZEPR
73.3
T/ON1SYNC
73.3
789 789 DN DN DN
GEAR
789
CMACH TRIM FAIL
1234567
R FADEC FAIL
1O MESSAGES O
R OIL PRESS
PITCH DISC FAULTR OIL FILTERIAC 1 WOW INOPR ENG BLEED OFFTRIM AIR OFF
END
CRZEPR
73.3
T/ON1SYNC
73.3
789 789 DN DN DN
GEAR
789
HYD 1 LO PRESSHYD 2 LO PRESSHYD 3 LO PRESSICE DETECTOR FAILAC BUS 1 FAILL REVERSER UNLKDNW STEERING FAILLATERAL MODE OFFMATCH TRIM FAILMACH TRIM FAIL12 MESSAGES 6
GX
_0
7_
02
0
12 MESSAGES 6 END 1O MESSAGES O
7-18 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
MESSAGE SCROLLING
N2
FF (PPH)
93.4575O
IGN
START START
IGN
73.3
T/ON1SYNC
73.3
789
ITTSYNC
789
–TRIMS–NU
93.4575O
789
R PACK FAILHYD 1 LO PRESSHYD 2 LO PRESSHYD 3 LO PRESSICE DETECTOR FAILASCB FAILBLEED CONFIG FAILDAU 1 FAILELEC SYS FAULTAT IRS MISCOMPAUTOBRAKE FAILSTAB CH 1 OFFTRIM AIR OFFDAU 1B SELECTEDPARK BRAKE ON
END
N2
FF (PPH)
93.4575O
IGN
START START
IGN
73.3
T/ON1SYNC
73.3
789
ITTSYNC
789
–TRIMS–NU
93.4575O
789
L PACK FAILLATERAL MODE OFFMACH TRIM FAILAFCS PFD 2 IRS REVAFCS STBY ADC FAILAFT EQUIP BAY DOORR PACK FAILHYD 1 LO PRESSHYD 2 LO PRESSHYD 3 LO PRESSICE DETECTOR FAILASCB FAILBLEED CONFIG FAIL
O MESSAGES 6
DAU 1 FAILELEC SYS FAULT
SCROLL
EICAS
STAT
HYDAC
ELECBLEED
AIRCOND
DCELEC
FUELFLT
CTRL
SCROLL
EICAS
SYSTEMS SELECT
NORMMFD 2MFD 1
EICAS SCROLL KnobUsed to scroll messages out of view and/or display nondisplayed messages.Warning messages cannot be scrolled out of view.• Turning SCROLL knob clockwise will scroll messages up• Turning SCROLL knob counterclockwise will scroll messages down.
NOTE:Each “click” of theSCROLL knob willmove the messagestack, one line upor down.
GX
_0
7_
02
1
For Training Purposes OnlySept 04
7-19
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
AURALSAurals and tones that call attention to warnings and cautions.
AURAL/TONE INDICATION CHAPTER REFERENCE
C-chord (1 second) Altitude alert Chapter 7, Electronic Display System
Cavalry Charge Autopilot disconnect Chapter 2, Automatic Flight Control System
Caution (Single chime) Tone that precedes an aircraft system caution message Chapters 2 through 17
Clacker Excessive stabilizer movement Chapter 10, Flight Controls
Landing Gear Horn Landing gear not down-and-locked for landing Chapter 14, Landing Gear
Double C-chord VNAV vertical track alert Chapter 2, Automatic Flight Control System
Horn Continuous (A-chord) Overspeed warningChapter 2, Automatic Flight Control SystemChapter 10, Flight Controls
Stick Shaker Stall Chapter 10, Flight Controls
Warning (Triple chime)Tone that precedes an aircraft system warning message and/or voice advisory
Chapters 2 through 17
Whoop-WhoopEGPWS mode 1 or 2 (excessive descent rate or excessive closure rate) (if installed)
EGPWS, Chapter 16, Navigation
7-20 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
ALPHABETICAL LIST OF VOICE MESSAGES
VOICE MESSAGE - ALPHABETICALW = WARNINGSYS = SYSTEM EICAS/PFD INDICATION
VOICE MESSAGE TYPE CH.REF
Adjust Vertical Speed, Adjust SYS 16 TCAS - Reduce vertical speed
APU FIRE W 9 APU FIRE
Bank Angle SYS 16 EGPWS - Excessive bank angle on final approach
CABIN ALTITUDE W 13 CABIN ALT/Cabin altitude >9000 feet
Clear of Conflict SYS 16 TCAS - Encounter has ended and separation increasing
Climb, Climb SYS 16 TCAS - Indicates climb, put AC symbol in green box
Climb, Crossing, ClimbClimb, Crossing, Climb SYS 16 TCAS - Indicates climb, put AC symbol in green
box
Climb, Climb, NowClimb, Climb, Now SYS 16
TCAS - Following a descent advisory, a reversal of vertical speed is necessary to provide adequate separation
Descent, Crossing, DescentDescent, Crossing, Descent SYS 16 TCAS - Descent, the airplane flightpath will cross
intruder’s altitude
Descend, Descend SYS 16 TCAS - Descent, put AC symbol in green box
Descend, Descend, NowDescend, Descend, Now SYS 16
TCAS - Following a climb advisory, a reversal of vertical speed is necessary to provide adequate separation
Don’t Sink SYS 16 EGPWS - Sink after takeoff
GEAR BAY OVERHEAT W 9 MLG BAY OVHT/Main wheel well overheat
Glideslope SYS 16 EGPWS - Excessive deviation below glideslope
Increase ClimbIncrease Climb SYS 16 TCAS - Increase climb, put AC symbol in green box
Increase DescentIncrease Descent SYS 16 TCAS - Increase descent, put AC symbol in green
box
LEFT ENGINE FIRE W 9 L ENG FIRE
Minimums SYS 16 At minimum altitude selected on PFD
Monitor Vertical Speed SYS 16 TCAS - Monitor vertical speed to keep AC symbol out of red prohibited areas
For Training Purposes OnlySept 04
7-21
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
NO TAKEOFF W 7 & 12CONFIG AIL TRIM CONFIG RUD TRIMCONFIG SLATS/FLAPS CONFIG SPOILERSCONFIG STAB TRIM PARK BRAKE ON
Pull Up SYS 16 EGPWS - Corrective action after excessive descent rate during approach
Maintain Vertical Speed, Maintain SYS 16 TCAS: Stay in green box
Maintain Vertical Speed, Crossing Maintain SYS 16 TCAS: Stay in green box
RIGHT ENGINE FIRE W 9 R ENG FIRE
Selcal SYS 16 SELCAL HF, SELCAL VHF 1, SELCAL VHF 2, SELCAL VHF 3
Sink Rate SYS 16 EGPWS - Excessive descent rate during approach
SMOKE W 9
Global Express Global 5000SMOKE AVIONICS BAY SMOKE AVIONICS BAYSMOKE CABIN SMOKE AV RACKSMOKE BAGGAGE SMOKE BAGGAGESMOKE FWD LAV SMOKE CLOSETSMOKE AFT LAV SMOKE FWD LAVSMOKE CLOSET SMOKE AFT LAV
Terrain, Terrain SYS 16 EGPWS - Excessive terrain closure
Too Low Flap SYS 16 EGPWS - Insufficient flap, low altitude
Too Low Gear SYS 16 EGPWS - Gear up, low altitude
Too Low Terrain SYS 16 EGPWS - Terrain closure low altitude
Traffic, Traffic SYS 16 TCAS - Conduct visual search for intruder
Windshear, Windshear SYS 16 EGPWS - WINDSHR (decreasing performance)
500, 100, 50, 30 SYS 16 EGPWS - Descending altitude callouts
VOICE MESSAGE - ALPHABETICALW = WARNINGSYS = SYSTEM EICAS/PFD INDICATION
VOICE MESSAGE TYPE CH.REF
7-22 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
AURAL WARNING TESTMost aural alerts are exercised as part of their own system test. For all other aural alerts, an AURAL WARNING TEST can be initiated via the Electrical Management System Control Display Unit (EMS CDU) located on the pilot’s and copilot’s side panel. There are two warning test selections provided to test the Integrated Avionics Computer (IAC 1 and IAC 2).
NOTETEST is initiated by pressing activation key and can be terminated by pressing activation key again.
The test sequences through each tone and/or voice message in the following priority order:
• AURAL WARNING TEST 1 aural or AURAL WARNING TEST 2• STALL (stall shaker active)• Continuous tone (overspeed)• Triple Chime tone (any warning)• NO TAKEOFF• LEFT ENGINE FIRE• RIGHT ENGINE FIRE• APU FIRE• SMOKE • CABIN ALTITUDE• GEAR BAY OVERHEAT• LEFT REVERSER UNLOCKED• RIGHT REVERSER UNLOCKED• NORMAL BRAKE FAIL• Single Chime (any caution)
M
BRT
CIRCUIT BREAKER SYSTEM
STAT SYS BUSPREVPAGE
NEXTPAGE
CNTL TEST
BUS
EMERCONT
TEST CONTROL 1/2
FIRE TEST
STALL TEST
AURAL WARNING TEST 2
LAMP TEST 1
LAMP TEST 2
AURAL WARNING TEST 1
OFF
OFF
OFF
OFF
OFF
OFF
M
BRT
CIRCUIT BREAKER SYSTEM
STAT SYS BUSPREVPAGE
NEXTPAGE
CNTL TEST
BUS
EMERCONT
TEST CONTROL 1/2
FIRE TEST
STALL TEST
AURAL WARNING TEST 1
AURAL WARNING TEST 2
LAMP TEST 1
LAMP TEST 2
TEST
OFF
OFF
OFF
OFF
OFF
NOTE: TEST is initiated by pressing activation key andcan be terminated by pressing activation key again.Test duration is 60 seconds.
Activation Key
GX
_0
7_
02
2
For Training Purposes OnlySept 04
7-23
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
• GEAR• Single Cavalry Charge tone (autopilot disengage)• AUTOTHROTTLE aural• C-chord tone (altitude alert - capture)• Double C-chord (vertical track alert)• Trim clacker (trim in motion)• MINIMUMS• SELCAL
AURAL WARNING PANELThe aural warning panel, located on the overhead panel, is used to disable the tone/aural generators located in IAC 1 and IAC 2. Aurals for EGPWS and TCAS will not be inhibited by muting the IACs.
INHIBITSDuring takeoff and landing, the IAC fault warning computer will process inhibit logic to minimize spurious or distracting messages. Warnings and status messages are not inhibited except for CABIN ALT and APU OVERTEMP (T/O only), NORMAL BRAKE FAIL, BRAKE OVHT, CABIN DELTA-P.
During takeoff, the caution and advisory messages are inhibited when:
• Weight On Wheels; and• Indicated airspeed transitions from less than 80 knots to greater than or equal to 80
knots
The caution and advisory messages inhibit is removed:
• 25 seconds after Weight Off Wheels; or• Pressure Altitude is greater than or equal to takeoff altitude +400 feet; or• Indicated airspeed is less than 50 knots; or
AURAL WARNING
PUSH TO MUTE
IAC 1 IAC 2
MUTED MUTED
IAC 1 and IAC 2 PUSH TO MUTE SwitchesUsed to disable respective tone/aural generatorlocated in respective IACs.
GX
_0
7_
02
3
7-24 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
• Takeoff inhibit has been active for 60 consecutive seconds
During landing, the caution and advisory messages are inhibited when:
• Landing gear down; and• Radio altitude from 200 feet to less than or equal to 200 feet
The caution and advisory message inhibit is removed:
• 25 seconds after air to ground transition; or• Radio altitude greater than 200 feet; or• Indicated airspeed less than 50 knots
The following caution messages are NOT inhibited during takeoff and/or landing.
AIRPLANE SYSTEM CAUTION MESSAGES ADVISORY MESSAGES
AFCS
AP TRIM is NU (ND) (Ldg only)AP TRIM LWD - RWD (Ldg only)YD 1-2 FAILYD OFF
YD NOT CENTERED (TO only)
Air Conditioning Pressurization EMER DEPRESSL-R PACK FAIL
Aural and Visual Warnings CHECK DU 1 (2) (3) (4) (5) (6)SG 1 (2) (3) FAIL
Electrical Power BATT MASTER OFF BATT EMER PWR ONRAT GEN ON (Ldg only)
Doors and Exits
CARGO DOORLARGE SERV DOORSR EMER EXITPASSENGER DOORSMALL SERV DOORS
Flight Controls
ELEVATOR SPLITFLT SPLR DEPLOYEDFLT SPOILERS FAILGND LIFT DUMPROLL SELECTROLL SPOILERS FAILRUD AUTHORITY LOWSLAT-FLAP FAILSTAB TRIMSTALL PROTECT FAIL
FLT SPOILERS FAULTGND LIFT DUMPNO TAKEOFF (TO only)RUD AUTHORITY SAFESHAKER 1 (2) FAILSLAT-FLAP BITSLAT-FLAP HALFSPDSTALL WARN ADVANCE
Hydraulic Power HYD 1 (2) (3) LO PRESSHYD RAT PUMP FAIL (Ldg only)
Ice and Rain Protection ICE
Instruments ADC 1 (2) (3) MISCMPALL ADC MISCMP ADC 1 (2) (3) FAIL
For Training Purposes OnlySept 04
7-25
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
Landing Gear
BRAKE 50% DEGRADEDCPLT BRAKE FAULTGEAR DISAGREEINBD BRK LO PRESSL (R) INBD BRAKE FAILL (R) OUTBD BRAKE FAILNOSE STEER FAILOUTBD BRK LO PRESSPARK/EMER BRAKE ON (Ldg only)PLT BRAKE FAULTUNCOMMANDED BRAKE
BRAKE TEMP (TO only)GEAR SYS FAULTNO TAKEOFF (TO only)
Lighting EMER LIGHTS OFF
Navigation ALL IRS MISCMP
Power Plant
A/T NOT IN HOLD (TO only)L (R) FADEC N1 CTLL (R) FUEL FILTERL (R) REV LOCK FAILL (R) REVERSER FAIL (Ldg only)
A/T 1-2 FAIL
AIRPLANE SYSTEM CAUTION MESSAGES ADVISORY MESSAGES
7-26 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
TAKEOFF CONFIGURATION WARNINGSTakeoff configuration warnings are armed when the airplane is on the ground and both engines are accelerated towards takeoff thrust (throttle position ≥ 30°). A voice warning, EICAS warning message, and both MASTER WARNING lights come on for any of the following:
All configuration warning indications are canceled when the configuration error is corrected, or the airplane is airborne, or either thrust lever is retarded. A NO TAKEOFF CAS Advisory message will indicate a configuration error prior to the throttles being advanced towards takeoff.
LANDING CONFIGURATION WARNINGThe “GEAR” aural will sound if any gear is not down and locked and:
• The radio altitude is less than 1,000 feet AGL and the descent rate is more than 400 feet per minute; or
• The radio altitude is less than 500 feet AGL and either throttle is below 25º throttle lever angle and the flap position is 30º
• The radio altitude is less than 500 AGL and both throttles are below 25º throttle lever angle and the flap position is not at 30º
NOTEThe “GEAR” aural can not be muted during any of these conditions.
The “Too Low Gear” (EGPWS) aural warning is heard if any landing gear is not down and locked with the radio altitude less than 500 feet AGL and the indicated airspeed at less than 190 knots.
CONDITION VOICE MESSAGE EICAS MESSAGE
Aileron trim outside of takeoff range “NO TAKEOFF” CONFIG AIL TRIM
Parking brake on during takeoff “NO TAKEOFF” PARK BRAKE ON
Rudder trim outside of takeoff range “NO TAKEOFF” CONFIG RUD TRIM
Flaps not in takeoff position “NO TAKEOFF” CONFIG SLATS/FLAPS
Spoilers not in takeoff position “NO TAKEOFF” CONFIG SPOILERS
Horizontal stabilizer outside of takeoff range (“green band”) ‘’NO TAKEOFF” CONFIG STAB TRIM
For Training Purposes OnlySept 04
7-27
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
If neither radio altimeter is valid, the “GEAR” aural will sound if any gear is not down and locked and the airplane is below 16,500 feet. The landing gear horn may be muted by pressing the mute horn switch/light on the landing gear control panel. With both thrust levers at IDLE, (less than three degrees throttle lever angle) the horn cannot be muted.
STALL WARNINGWarning of an impending stall is provided by independent stall protection systems. Both systems are energized in flight and deactivated on the ground through air/ground logic. The flight displays indicate airplane approach to stall speed by low speed cues (red band) on the primary flight displays (PFDs) airspeed tape.
Stall warnings are provided by an aural STALL, a STALL icon appears on the PFD and vibration of both control columns. If the airplane angle-of-attack continues to increase to the point of an aerodynamic stall, the stick pusher pushes the control column forward. For more information refer to Chapter 10 FLIGHT CONTROLS.
7-28 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
REVERSION CONTROL PANELThe reversion panel located on the pedestal can be used to revert the EICAS display to alternate display units, and to revert IRSs, ADCs, and SGs.
20
10
30
20
10
30
09
8
7
65
4
3
2
1100 FEET
ALT
1 00032
4
10 13
mb/hPa
29 9 2
IN HG
IAS KNOTS
220200180 250
BARO
Honeywell HoneywellHoneywell
WX
ET
NO BEARINGRA 9 . 8NM +13TA 4 . 5NM -04
SAT
GSPD
TERR
-56
TAT
TAS
-40
234
345
INHIB
LX
00 : 10 0 . 05L
MAG2HDG315
ETE 1+36
12 . 5KDVT
NM
FLBELOW
TCAS TEST
FMS1360
N
5 5
3
6
33
30
- 02
- 02
+ 12- 04
KABC
KKLM
KKLM
TOC
TOC
KGHJ
KGHJ
LUF
KDEF
KDEF
4000 4000
FL180
+ 09
Honeywell
13000.00
00
90
13 13
2019 20
22 2220
OXYGEN
AFTCABIN (°C)
FWDCABIN (°C)
CKPT (°C)
OPEN OPEN
OUTFLOW VALVES
CAB ALT
P
CAB RATE
LDG ELEV
00
1 2
1 2
1 2
QTY
ENG
APU
RES
OIL (QTS)
APU DOOR 11.2°
RPM EGT
BRAKE TEMP
11.5
650100
0603 03 03
11.55.26.0
%
% %
Honeywell
9500
29.92
AT1
VTA
M
0.450M
FMS1LOC1DTK
360
HDG330
10400
20
20
10
10
20
20
10
10
9500
10500
300
220
210
200
190
180
170
F3
LE
F1
2160
150
1856
4
N33
30
W24
21S
15
12
E6
3
0
1
2
3
1
2
3
ATT
HDGT
EICAS
GS
LOC
HDG
RAD
IASALT
HDG2
VOR 1
ADF 2
0010020
80
THRUST HDG ASEL ATT 2AP1VAPP VNAV ADC 3
9500
29.92
AT1
VTA
M
0.450M
FMS1LOC1DTK
360
HDG330
10400
20
20
10
10
20
20
10
10
9500
10500
300
220
210
200
190
180
170
F3
LE
F1
2160
150
1856
4
N33
30
W24
21S
15
12
E6
3
0
1
2
3
1
2
3
ATT
HDGT
EICAS
GS
LOC
HDG
RAD
IASALT
HDG2
VOR 1
ADF 2
0010020
80
THRUST HDG ASEL ATT 2AP1VAPP VNAV ADC 3
WX
ET
NO BEARINGRA 9 . 8NM +13TA 4 . 5NM -04
SAT
GSPD
TERR
-56
TAT
TAS
-40
234
345
INHIB
LX
00 : 10 0 . 05L
MAG2HDG315
ETE 1+36
12 . 5KDVT
NM
FLBELOW
TCAS TEST
FMS1360
N
5 5
3
6
33
30
- 02
- 02
+ 12- 04
KABC
KKLM
KKLM
TOC
TOC
KGHJ
KGHJ
LUF
KDEF
KDEF
4000 4000
FL180
+ 09
DU 1
PFD 1 MFD 1
DU 2
EICAS
DU 3
SYSTEMS
DU 4
MFD 2
DU 5
PFD 2
DU 6
IRS ADC ADC IRS
SG 3
EICAS
SG 2SG 1
PFD 1
ALTN 3
ALTN
ALTN 1
ALTNALTN
ALTN
NORM
NORM
NORMNORM
NORM
PFD 1 PFD 2
PFD 2
ALTN 2 ALTN NORM
GX
_0
7_
02
4
EICAS KnobUsed to revert EICASdisplay to alternatedisplay units.
IRS and ADCPushbuttonsUsed to revert IRSand ADCs.
SG 1, SG 2, SG 3 KnobsUsed to revert applicablesymbol generators tospecific displays.
PFD 1 and PFD 2 Reversion KnobsNORMALTN
• PFD 1 displayed on DU 1 , PFD 2 displayed on DU 6• PFD 1 displayed on DU 2, PFD 2 displayed on DU 5
––
TOTAL FUEL (LBS) 4155O
1.54
146OO 146OO1OOOO
N2
FF (PPH)
OIL TEMP
OIL PRESS
93.4575O11581
1.65
CRZEPR
IGN
START START
IGN
NDSTAB
1.54
1.65
73.3
T/ON1SYNC
73.3
789
ITTSYNC
789 DN DN DN
OUT
3O
GEAR
–TRIMS–
NL NRRUDDER
AIL
RWDLWD
7.2
NU
93.4575O11581
235O
NO TAKEOFFPARK/EMER BRAKE ON
END
For Training Purposes OnlySept 04
7-29
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
PFD REVERSION
PFD 1 and PFD 2 Reversion KnobsALTN• PFD 1 displayed on DU 2, PFD 2 displayed on DU 5–
20
10
30
20
10
30
09
8
7
65
4
3
2
1100 FEET
ALT
1 00032
4
10 13
mb/hPa
29 9 2
IN HG
IAS KNOTS
220200180 250
BARO
Honeywell HoneywellHoneywell Honeywell
13000.00
00
90
13 13
2019 20
22 2220
OXYGEN
AFTCABIN (°C)
FWDCABIN (°C)
CKPT (°C)
OPEN OPEN
OUTFLOW VALVES
CAB ALT
P
CAB RATE
LDG ELEV
00
1 2
1 2
1 2
QTY
ENG
APU
RES
OIL (QTS)
APU DOOR 11.2°
RPM EGT
BRAKE TEMP
11.5
650100
0603 03 03
11.55.26.0
%
% %
Honeywell
9500
29.92
AT1
VTA
M
0.450M
FMS1LOC1DTK
360
HDG330
10400
20
20
10
10
20
20
10
10
9500
10500
300
220
210
200
190
180
170
F3
LE
F1
2160
150
1856
4
N33
30
W24
21S
15
12
E6
3
0
1
2
3
1
2
3
ATT
HDGT
EICAS
GS
LOC
HDG
RAD
IASALT
HDG2
VOR 1
ADF 2
0010020
80
THRUST HDG ASEL ATT 2AP1VAPP VNAV ADC 3
DU 2 DU 5
IRS ADC ADC IRS
SG 3
EICAS
SG 2SG 1
PFD 1
ALTN 3
ALTN
ALTN 1
ALTNALTN
ALTN
NORM
NORM
NORMNORM
NORM
PFD 1 PFD 2
PFD 2
ALTN 2 ALTN NORM
GX
_0
7_
02
5
9500
29.92
AT1
VTA
M
0.450M
FMS1LOC1DTK
360
HDG330
10400
20
20
10
10
20
20
10
10
9500
10500
300
220
210
200
190
180
170
F3
LE
F1
2160
150
1856
4
N33
30
W24
21S
15
12
E6
3
0
1
2
3
1
2
3
ATT
HDGT
EICAS
GS
LOC
HDG
RAD
IASALT
HDG2
VOR 1
ADF 2
0010020
80
THRUST HDG ASEL ATT 2AP1VAPP VNAV ADC 3
TOTAL FUEL (LBS) 4155O
1.54
146OO 146OO1OOOO
N2
FF (PPH)
OIL TEMP
OIL PRESS
93.4575O11581
1.65
CRZEPR
IGN
START START
IGN
NDSTAB
1.54
1.65
73.3
T/ON1SYNC
73.3
789
ITTSYNC
789 DN DN DN
OUT
3O
GEAR
–TRIMS–
NL NRRUDDER
AIL
RWDLWD
7.2
NU
93.4575O11581
235O
NO TAKEOFFPARK/EMER BRAKE ON
END
7-30 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
EICAS REVERSION CONTROL
EICAS Reversion KnobNORMALTN 1ALTN 2ALTN 3
• EICAS displayed on DU 3• EICAS displayed on DU 4• EICAS displayed on DU 2• EICAS displayed on DU 5
––––
20
10
30
20
10
30
09
8
7
65
4
3
2
1100 FEET
ALT
1 00032
4
10 13
mb/hPa
29 9 2
IN HG
IAS KNOTS
220200180 250
BARO
Honeywell HoneywellHoneywell
WX
ET
NO BEARINGRA 9 . 8NM +13TA 4 . 5NM -04
SAT
GSPD
TERR
-56
TAT
TAS
-40
234
345
INHIB
LX
00 : 10 0 . 05L
MAG2HDG315
ETE 1+36
12 . 5KDVT
NM
FLBELOW
TCAS TEST
FMS1360
N
5 5
3
6
33
30
- 02
- 02
+ 12- 04
KABC
KKLM
KKLM
TOC
TOC
KGHJ
KGHJ
LUF
KDEF
KDEF
4000 4000
FL180
+ 09
Honeywell
13000.00
00
90
13 13
2019 20
22 2220
OXYGEN
AFTCABIN (°C)
FWDCABIN (°C)
CKPT (°C)
OPEN OPEN
OUTFLOW VALVES
CAB ALT
P
CAB RATE
LDG ELEV
00
1 2
1 2
1 2
QTY
ENG
APU
RES
OIL (QTS)
APU DOOR 11.2°
RPM EGT
BRAKE TEMP
11.5
650100
0603 03 03
11.55.26.0
%
% %
Honeywell
9500
29.92
AT1
VTA
M
0.450M
FMS1LOC1DTK
360
HDG330
10400
20
20
10
10
20
20
10
10
9500
10500
300
220
210
200
190
180
170
F3
LE
F1
2160
150
1856
4
N33
30
W24
21S
15
12
E6
3
0
1
2
3
1
2
3
ATT
HDGT
EICAS
GS
LOC
HDG
RAD
IASALT
HDG2
VOR 1
ADF 2
0010020
80
THRUST HDG ASEL ATT 2AP1VAPP VNAV ADC 3
9500
29.92
AT1
VTA
M
0.450M
FMS1LOC1DTK
360
HDG330
10400
20
20
10
10
20
20
10
10
9500
10500
300
220
210
200
190
180
170
F3
LE
F1
2160
150
1856
4
N33
30
W24
21S
15
12
E6
3
0
1
2
3
1
2
3
ATT
HDGT
EICAS
GS
LOC
HDG
RAD
IASALT
HDG2
VOR 1
ADF 2
0010020
80
THRUST HDG ASEL ATT 2AP1VAPP VNAV ADC 3
WX
ET
NO BEARINGRA 9 . 8NM +13TA 4 . 5NM -04
SAT
GSPD
TERR
-56
TAT
TAS
-40
234
345
INHIB
LX
00 : 10 0 . 05L
MAG2HDG315
ETE 1+36
12 . 5KDVT
NM
FLBELOW
TCAS TEST
FMS1360
N
5 5
3
6
33
30
- 02
- 02
+ 12- 04
KABC
KKLM
KKLM
TOC
TOC
KGHJ
KGHJ
LUF
KDEF
KDEF
4000 4000
FL180
+ 09
DU 2
EICAS
DU 3 DU 4 DU 5
IRS ADC ADC IRS
SG 3
EICAS
SG 2SG 1
PFD 1
ALTN 3
ALTN
ALTN 1
ALTNALTN
ALTN
NORM
NORM
NORMNORM
NORM
PFD 1 PFD 2
PFD 2
ALTN 2 ALTN NORM
GX
_0
7_
02
6
TOTAL FUEL (LBS) 4155O
1.54
146OO 146OO1OOOO
N2
FF (PPH)
OIL TEMP
OIL PRESS
93.4575O11581
1.65
CRZEPR
IGN
START START
IGN
NDSTAB
1.54
1.65
73.3
T/ON1SYNC
73.3
789
ITTSYNC
789 DN DN DN
OUT
3O
GEAR
–TRIMS–
NL NRRUDDER
AIL
RWDLWD
7.2
NU
93.4575O11581
235O
NO TAKEOFFPARK/EMER BRAKE ON
END
For Training Purposes OnlySept 04
7-31
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
EICAS REVERSION
20
10
30
20
10
30
09
8
7
65
4
3
2
1100 FEET
ALT
1 00032
4
10 13
mb/hPa
29 9 2
IN HG
IAS KNOTS
220200180 250
BARO
Honeywell HoneywellHoneywell Honeywell
WX
ET
NO BEARINGRA 9 . 8NM +13TA 4 . 5NM -04
SAT
GSPD
TERR
-56
TAT
TAS
-40
234
345
INHIB
LX
00 : 10 0 . 05L
MAG2HDG315
ETE 1+36
12 . 5KDVT
NM
FLBELOW
TCAS TEST
FMS1360
N
5 5
3
6
33
30
- 02
- 02
+ 12- 04
KABC
KKLM
KKLM
TOC
TOC
KGHJ
KGHJ
LUF
KDEF
KDEF
4000 4000
FL180
+ 09
Honeywell
9500
29.92
AT1
VTA
M
0.450M
FMS1LOC1DTK
360
HDG330
10400
20
20
10
10
20
20
10
10
9500
10500
300
220
210
200
190
180
170
F3
LE
F1
2160
150
1856
4
N33
30
W24
21S
15
12
E6
3
0
1
2
3
1
2
3
ATT
HDGT
EICAS
GS
LOC
HDG
RAD
IASALT
HDG2
VOR 1
ADF 2
0010020
80
THRUST HDG ASEL ATT 2AP1VAPP VNAV ADC 3
9500
29.92
AT1
VTA
M
0.450M
FMS1LOC1DTK
360
HDG330
10400
20
20
10
10
20
20
10
10
9500
10500
300
220
210
200
190
180
170
F3
LE
F1
2160
150
1856
4
N33
30
W24
21S
15
12
E6
3
0
1
2
3
1
2
3
ATT
HDGT
EICAS
GS
LOC
HDG
RAD
IASALT
HDG2
VOR 1
ADF 2
0010020
80
THRUST HDG ASEL ATT 2AP1VAPP VNAV ADC 3
WX
ET
NO BEARINGRA 9 . 8NM +13TA 4 . 5NM -04
SAT
GSPD
TERR
-56
TAT
TAS
-40
234
345
INHIB
LX
00 : 10 0 . 05L
MAG2HDG315
ETE 1+36
12 . 5KDVT
NM
FLBELOW
TCAS TEST
FMS1360
N
5 5
3
6
33
30
- 02
- 02
+ 12- 04
KABC
KKLM
KKLM
TOC
TOC
KGHJ
KGHJ
LUF
KDEF
KDEF
4000 4000
FL180
+ 09
DU 4
EICAS
ALTN 3
ALTN 1NORMALTN 2
GX
_0
7_
02
7
20
10
30
20
10
30
09
8
7
65
4
3
2
1100 FEET
ALT
1 00032
4
10 13
mb/hPa
29 9 2
IN HG
IAS KNOTS
220200180 250
BARO
Honeywell HoneywellHoneywell Honeywell
13000.00
00
90
13 13
2019 20
22 2220
OXYGEN
AFTCABIN (°C)
FWDCABIN (°C)
CKPT (°C)
OPEN OPEN
OUTFLOW VALVES
CAB ALT
P
CAB RATE
LDG ELEV
00
1 2
1 2
1 2
QTY
ENG
APU
RES
OIL (QTS)
APU DOOR 11.2°
RPM EGT
BRAKE TEMP
11.5
650100
0603 03 03
11.55.26.0
%
% %
Honeywell
9500
29.92
AT1
VTA
M
0.450M
FMS1LOC1DTK
360
HDG330
10400
20
20
10
10
20
20
10
10
9500
10500
300
220
210
200
190
180
170
F3
LE
F1
2160
150
1856
4
N33
30
W24
21S
15
12
E6
3
0
1
2
3
1
2
3
ATT
HDGT
EICAS
GS
LOC
HDG
RAD
IASALT
HDG2
VOR 1
ADF 2
0010020
80
THRUST HDG ASEL ATT 2AP1VAPP VNAV ADC 3
9500
29.92
AT1
VTA
M
0.450M
FMS1LOC1DTK
360
HDG330
10400
20
20
10
10
20
20
10
10
9500
10500
300
220
210
200
190
180
170
F3
LE
F1
2160
150
1856
4
N33
30
W24
21S
15
12
E6
3
0
1
2
3
1
2
3
ATT
HDGT
EICAS
GS
LOC
HDG
RAD
IASALT
HDG2
VOR 1
ADF 2
0010020
80
THRUST HDG ASEL ATT 2AP1VAPP VNAV ADC 3
WX
ET
NO BEARINGRA 9 . 8NM +13TA 4 . 5NM -04
SAT
GSPD
TERR
-56
TAT
TAS
-40
234
345
INHIB
LX
00 : 10 0 . 05L
MAG2HDG315
ETE 1+36
12 . 5KDVT
NM
FLBELOW
TCAS TEST
FMS1360
N
5 5
3
6
33
30
- 02
- 02
+ 12- 04
KABC
KKLM
KKLM
TOC
TOC
KGHJ
KGHJ
LUF
KDEF
KDEF
4000 4000
FL180
+ 09
DU 2
20
10
30
20
10
30
09
8
7
65
4
3
2
1100 FEET
ALT
1 00032
4
10 13
mb/hPa
29 9 2
IN HG
IAS KNOTS
220200180 250
BARO
HoneywellHoneywell Honeywell
WX
ET
NO BEARINGRA 9 . 8NM +13TA 4 . 5NM -04
SAT
GSPD
TERR
-56
TAT
TAS
-40
234
345
INHIB
LX
00 : 10 0 . 05L
MAG2HDG315
ETE 1+36
12 . 5KDVT
NM
FLBELOW
TCAS TEST
FMS1360
N
5 5
3
6
33
30
- 02
- 02
+ 12- 04
KABC
KKLM
KKLM
TOC
TOC
KGHJ
KGHJ
LUF
KDEF
KDEF
4000 4000
FL180
+ 09
Honeywell
13000.00
00
90
13 13
2019 20
22 2220
OXYGEN
AFTCABIN (°C)
FWDCABIN (°C)
CKPT (°C)
OPEN OPEN
OUTFLOW VALVES
CAB ALT
P
CAB RATE
LDG ELEV
00
1 2
1 2
1 2
QTY
ENG
APU
RES
OIL (QTS)
APU DOOR 11.2°
RPM EGT
BRAKE TEMP
11.5
650100
0603 03 03
11.55.26.0
%
% %
Honeywell
9500
29.92
AT1
VTA
M
0.450M
FMS1LOC1DTK
360
HDG330
10400
20
20
10
10
20
20
10
10
9500
10500
300
220
210
200
190
180
170
F3
LE
F1
2160
150
1856
4
N33
30
W24
21S
15
12
E6
3
0
1
2
3
1
2
3
ATT
HDGT
EICAS
GS
LOC
HDG
RAD
IASALT
HDG2
VOR 1
ADF 2
0010020
80
THRUST HDG ASEL ATT 2AP1VAPP VNAV ADC 3
9500
29.92
AT1
VTA
M
0.450M
FMS1LOC1DTK
360
HDG330
10400
20
20
10
10
20
20
10
10
9500
10500
300
220
210
200
190
180
170
F3
LE
F1
2160
150
1856
4
N33
30
W24
21S
15
12
E6
3
0
1
2
3
1
2
3
ATT
HDGT
EICAS
GS
LOC
HDG
RAD
IASALT
HDG2
VOR 1
ADF 2
0010020
80
THRUST HDG ASEL ATT 2AP1VAPP VNAV ADC 3
DU 5
EICAS
ALTN 3
ALTN 1NORMALTN 2
EICAS
ALTN 3
ALTN 1NORMALTN 2
• EICAS displayedon DU 4
ALTN 1 –
• EICAS displayedon DU 2
ALTN 2 –
• EICAS displayedon DU 5
ALTN 3 –
TOTAL FUEL (LBS) 4155O
1.54
146OO 146OO1OOOO
N2
FF (PPH)
OIL TEMP
OIL PRESS
93.4575O11581
1.65
CRZEPR
IGN
START START
IGN
NDSTAB
1.54
1.65
73.3
T/ON1SYNC
73.3
789
ITTSYNC
789 DN DN DN
OUT
3O
GEAR
–TRIMS–
NL NRRUDDER
AIL
RWDLWD
7.2
NU
93.4575O11581
235O
NO TAKEOFFPARK/EMER BRAKE ON
END
TOTAL FUEL (LBS) 4155O
1.54
146OO 146OO1OOOO
N2
FF (PPH)
OIL TEMP
OIL PRESS
93.4575O11581
1.65
CRZEPR
IGN
START START
IGN
NDSTAB
1.54
1.65
73.3
T/ON1SYNC
73.3
789
ITTSYNC
789 DN DN DN
OUT
3O
GEAR
–TRIMS–
NL NRRUDDER
AIL
RWDLWD
7.2
NU
93.4575O11581
235O
NO TAKEOFFPARK/EMER BRAKE ON
END
TOTAL FUEL (LBS) 4155O
1.54
146OO 146OO1OOOO
N2
FF (PPH)
OIL TEMP
OIL PRESS
93.4575O11581
1.65
CRZEPR
IGN
START START
IGN
NDSTAB
1.54
1.65
73.3
T/ON1SYNC
73.3
789
ITTSYNC
789 DN DN DN
OUT
3O
GEAR
–TRIMS–
NL NRRUDDER
AIL
RWDLWD
7.2
NU
93.4575O11581
235O
NO TAKEOFFPARK/EMER BRAKE ON
END
7-32 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
SG REVERSION CONTROL
IRS ADC ADC IRS
SG 3
EICAS
SG 2SG 1
PFD 1
ALTN 3
ALTN
ALTN 1
ALTNALTN
ALTN
NORM
NORM
NORMNORM
NORM
PFD 1 PFD 2
PFD 2
ALTN 2 ALTN NORM
SG 1, SG 2, SG 3 Reversion Knobs• SG1 NORM SG1 drives DU1 and DU2• SG2 NORM SG2 drives DU5 and DU6• SG3 NORM SG3 drives DU3 and DU4
–––
GX
_0
7_
02
8
For Training Purposes OnlySept 04
7-33
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
SG REVERSION
SG 3 SG 2SG 1
ALTN ALTNALTN NORM NORMNORM
• SG1 drives DU1 and DU2• SG2 drives DU5 and DU6• SG3 drives DU3 and DU4
SG1 NORMSG2 NORMSG3 NORM
–––
GX
_0
7_
02
9
Honeywell HoneywellHoneywell Honeywell
13000.00
00
90
13 13
2019 20
22 2220
OXYGEN
AFTCABIN (°C)
FWDCABIN (°C)
CKPT (°C)
OPEN OPEN
OUTFLOW VALVES
CAB ALT
P
CAB RATE
LDG ELEV
00
1 2
1 2
1 2
QTY
ENG
APU
RES
OIL (QTS)
APU DOOR 11.2°
RPM EGT
BRAKE TEMP
11.5
650100
0603 03 03
11.55.26.0
%
% %
Honeywell
9500
29.92
AT1
VTA
M
0.450M
FMS1LOC1DTK
360
HDG330
10400
20
20
10
10
20
20
10
10
9500
10500
300
220
210
200
190
180
170
F3
LE
F1
2160
150
1856
4
N33
30
W24
21S
15
12
E6
3
0
1
2
3
1
2
3
ATT
HDGT
EICAS
GS
LOC
HDG
RAD
IASALT
HDG2
VOR 1
ADF 2
0010020
80
THRUST HDG ASEL ATT 2AP1VAPP VNAV ADC 3
9500
29.92
AT1
VTA
M
0.450M
FMS1LOC1DTK
360
HDG330
10400
20
20
10
10
20
20
10
10
9500
10500
300
220
210
200
190
180
170
F3
LE
F1
2160
150
1856
4
N33
30
W24
21S
15
12
E6
3
0
1
2
3
1
2
3
ATT
HDGT
EICAS
GS
LOC
HDG
RAD
IASALT
HDG2
VOR 1
ADF 2
0010020
80
THRUST HDG ASEL ATT 2AP1VAPP VNAV ADC 3
WX
ET
NO BEARINGRA 9 . 8NM +13TA 4 . 5NM -04
SAT
GSPD
TERR
-56
TAT
TAS
-40
234
345
INHIB
LX
00 : 10 0 . 05L
MAG2HDG315
ETE 1+36
12 . 5KDVT
NM
FLBELOW
TCAS TEST
FMS1360
N
5 5
3
6
33
30
- 02
- 02
+ 12- 04
KABC
KKLM
KKLM
TOC
TOC
KGHJ
KGHJ
LUF
KDEF
KDEF
4000 4000
FL180
+ 09
WX
T5 . 0%
LX
G85%
STAB
ET 235°50 . 0NM00 : 10
TRU
N
ETE1+36
12 . 5KDVT
NM
FMS1
50 50
KNOP
KKLM
TOC
KGHJ
KABCLUF
KDEF
134
136
N 023° 29 . 6W 112° 01 . 5
SAT
GSPD
TERR
-56
TAT
TAS
-40
234
345
INHIB
KKLMTOC
KGHJKDEF
4000 4000
FL180
TOTAL FUEL (LBS) 4155O
1.54
146OO 146OO1OOOO
N2
FF (PPH)
OIL TEMP
OIL PRESS
93.4575O11581
1.65
CRZEPR
IGN
START START
IGN
NDSTAB
1.54
1.65
73.3
T/ON1SYNC
73.3
789
ITTSYNC
789 DN DN DN
OUT
3O
GEAR
–TRIMS–
NL NRRUDDER
AIL
RWDLWD
7.2
NU
93.4575O11581
235O
NO TAKEOFFPARK/EMER BRAKE ON
END
7-34 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
SG REVERSION (Cont)
GX
_0
7_
03
0
SG 1 FAIL
SG 3 SG 2SG 1
ALTN ALTNALTN NORM NORMNORM
Honeywell HoneywellHoneywell Honeywell
13000.00
00
90
13 13
2019 20
22 2220
OXYGEN
AFTCABIN (°C)
FWDCABIN (°C)
CKPT (°C)
OPEN OPEN
OUTFLOW VALVES
CAB ALT
P
CAB RATE
LDG ELEV
00
1 2
1 2
1 2
QTY
ENG
APU
RES
OIL (QTS)
APU DOOR 11.2°
RPM EGT
BRAKE TEMP
11.5
650100
0603 03 03
11.55.26.0
%
% %
Honeywell
9500
29.92
AT1
VTA
M
0.450M
FMS1LOC1DTK
360
HDG330
10400
20
20
10
10
20
20
10
10
9500
10500
300
220
210
200
190
180
170
F3
LE
F1
2160
150
1856
4
N33
30
W24
21S
15
12
E6
3
0
1
2
3
1
2
3
ATT
HDGT
EICAS
GS
LOC
HDG
RAD
IASALT
HDG2
VOR 1
ADF 2
0010020
80
THRUST HDG ASEL ATT 2AP1VAPP VNAV ADC 3
9500
29.92
AT1
VTA
M
0.450M
FMS1LOC1DTK
360
HDG330
10400
20
20
10
10
20
20
10
10
9500
10500
300
220
210
200
190
180
170
F3
LE
F1
2160
150
1856
4
N33
30
W24
21S
15
12
E6
3
0
1
2
3
1
2
3
ATT
HDGT
EICAS
GS
LOC
HDG
RAD
IASALT
HDG2
VOR 1
ADF 2
0010020
80
THRUST HDG ASEL ATT 2AP1VAPP VNAV ADC 3
WX
ET
NO BEARINGRA 9 . 8NM +13TA 4 . 5NM -04
SAT
GSPD
TERR
-56
TAT
TAS
-40
234
345
INHIB
LX
00 : 10 0 . 05L
MAG2HDG315
ETE 1+36
12 . 5KDVT
NM
FLBELOW
TCAS TEST
FMS1360
N
5 5
3
6
33
30
- 02
- 02
+ 12- 04
KABC
KKLM
KKLM
TOC
TOC
KGHJ
KGHJ
LUF
KDEF
KDEF
4000 4000
FL180
+ 09
WX
T5 . 0%
LX
G85%
STAB
ET 235°50 . 0NM00 : 10
TRU
N
ETE1+36
12 . 5KDVT
NM
FMS1
50 50
KNOP
KKLM
TOC
KGHJ
KABCLUF
KDEF
134
136
N 023° 29 . 6W 112° 01 . 5
SAT
GSPD
TERR
-56
TAT
TAS
-40
234
345
INHIB
KKLMTOC
KGHJKDEF
4000 4000
FL180
SG 1 FAIL
SG 3 SG 2SG 1
ALTN ALTNALTN NORM NORMNORM
Honeywell HoneywellHoneywell Honeywell
13000.00
00
90
13 13
2019 20
22 2220
OXYGEN
AFTCABIN (°C)
FWDCABIN (°C)
CKPT (°C)
OPEN OPEN
OUTFLOW VALVES
CAB ALT
P
CAB RATE
LDG ELEV
00
1 2
1 2
1 2
QTY
ENG
APU
RES
OIL (QTS)
APU DOOR 11.2°
RPM EGT
BRAKE TEMP
11.5
650100
0603 03 03
11.55.26.0
%
% %
Honeywell
9500
29.92
AT1
VTA
M
0.450M
FMS1LOC1DTK
360
HDG330
10400
20
20
10
10
20
20
10
10
9500
10500
300
220
210
200
190
180
170
F3
LE
F1
2160
150
1856
4
N33
30
W24
21S
15
12
E6
3
0
1
2
3
1
2
3
ATT
HDGT
EICAS
GS
LOC
HDG
RAD
IASALT
HDG2
VOR 1
ADF 2
0010020
80
THRUST HDG ASEL ATT 2AP1VAPP VNAV ADC 3
WX
ET
NO BEARINGRA 9 . 8NM +13TA 4 . 5NM -04
SAT
GSPD
TERR
-56
TAT
TAS
-40
234
345
INHIB
LX
00 : 10 0 . 05L
MAG2HDG315
ETE 1+36
12 . 5KDVT
NM
FLBELOW
TCAS TEST
FMS1360
N
5 5
3
6
33
30
- 02
- 02
+ 12- 04
KABC
KKLM
KKLM
TOC
TOC
KGHJ
KGHJ
LUF
KDEF
KDEF
4000 4000
FL180
+ 09
TOTAL FUEL (LBS) 4155O
1.54
146OO 146OO1OOOO
N2
FF (PPH)
OIL TEMP
OIL PRESS
93.4575O11581
1.65
CRZEPR
IGN
START START
IGN
NDSTAB
1.54
1.65
73.3
T/ON1SYNC
73.3
789
ITTSYNC
789 DN DN DN
OUT
3O
GEAR
–TRIMS–
NL NRRUDDER
AIL
RWDLWD
7.2
NU
93.4575O11581
235O
NO TAKEOFFPARK/EMER BRAKE ON
END
TOTAL FUEL (LBS) 4155O
1.54
146OO 146OO1OOOO
N2
FF (PPH)
OIL TEMP
OIL PRESS
93.4575O11581
1.65
CRZEPR
IGN
START START
IGN
NDSTAB
1.54
1.65
73.3
T/ON1SYNC
73.3
789
ITTSYNC
789 DN DN DN
OUT
3O
GEAR
–TRIMS–
NL NRRUDDER
AIL
RWDLWD
7.2
NU
93.4575O11581
235O
NO TAKEOFFPARK/EMER BRAKE ON
END
For Training Purposes OnlySept 04
7-35
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
SG REVERSION (Cont)
SG 1-2 FAIL
With a dual Symbol Generator failure the remainingSymbol Generator will always drive DU1, DU3, DU5 and DU6
GX
_0
7_
03
1
SG 3 SG 2SG 1
ALTN ALTNALTN NORM NORMNORM
Honeywell HoneywellHoneywell HoneywellHoneywell
9500
29.92
AT1
VTA
M
0.450M
FMS1LOC1DTK
360
HDG330
10400
20
20
10
10
20
20
10
10
9500
10500
300
220
210
200
190
180
170
F3
LE
F1
2160
150
1856
4
N33
30
W24
21S
15
12
E6
3
0
1
2
3
1
2
3
ATT
HDGT
EICAS
GS
LOC
HDG
RAD
IASALT
HDG2
VOR 1
ADF 2
0010020
80
THRUST HDG ASEL ATT 2AP1VAPP VNAV ADC 3
9500
29.92
AT1
VTA
M
0.450M
FMS1LOC1DTK
360
HDG330
10400
20
20
10
10
20
20
10
10
9500
10500
300
220
210
200
190
180
170
F3
LE
F1
2160
150
1856
4
N33
30
W24
21S
15
12
E6
3
0
1
2
3
1
2
3
ATT
HDGT
EICAS
GS
LOC
HDG
RAD
IASALT
HDG2
VOR 1
ADF 2
0010020
80
THRUST HDG ASEL ATT 2AP1VAPP VNAV ADC 3
WX
ET
NO BEARINGRA 9 . 8NM +13TA 4 . 5NM -04
SAT
GSPD
TERR
-56
TAT
TAS
-40
234
345
INHIB
LX
00 : 10 0 . 05L
MAG2HDG315
ETE 1+36
12 . 5KDVT
NM
FLBELOW
TCAS TEST
FMS1360
N
5 5
3
6
33
30
- 02
- 02
+ 12- 04
KABC
KKLM
KKLM
TOC
TOC
KGHJ
KGHJ
LUF
KDEF
KDEF
4000 4000
FL180
+ 09
SG 1-2 FAIL
SG 3 SG 2SG 1
ALTN ALTNALTN NORM NORMNORM
Honeywell HoneywellHoneywell Honeywell
13000.00
00
90
13 13
2019 20
22 2220
OXYGEN
AFTCABIN (°C)
FWDCABIN (°C)
CKPT (°C)
OPEN OPEN
OUTFLOW VALVES
CAB ALT
P
CAB RATE
LDG ELEV
00
1 2
1 2
1 2
QTY
ENG
APU
RES
OIL (QTS)
APU DOOR 11.2°
RPM EGT
BRAKE TEMP
11.5
650100
0603 03 03
11.55.26.0
%
% %
Honeywell
TOTAL FUEL (LBS) 4155O
1.54
146OO 146OO1OOOO
N2
FF (PPH)
OIL TEMP
OIL PRESS
93.4575O11581
1.65
CRZEPR
IGN
START START
IGN
NDSTAB
1.54
1.65
73.3
T/ON1SYNC
73.3
789
ITTSYNC
789 DN DN DN
OUT
3O
GEAR
–TRIMS–
NL NRRUDDER
AIL
RWDLWD
7.2
NU
93.4575O11581
235O
NO TAKEOFFPARK/EMER BRAKE ON
END
TOTAL FUEL (LBS) 4155O
1.54
146OO 146OO1OOOO
N2
FF (PPH)
OIL TEMP
OIL PRESS
93.4575O11581
1.65
CRZEPR
IGN
START START
IGN
NDSTAB
1.54
1.65
73.3
T/ON1SYNC
73.3
789
ITTSYNC
789 DN DN DN
OUT
3O
GEAR
–TRIMS–
NL NRRUDDER
AIL
RWDLWD
7.2
NU
93.4575O11581
235O
NO TAKEOFFPARK/EMER BRAKE ON
END
7-36 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
ADC REVERSION
IRS ADC ADC IRS
SG 3
EICAS
SG 2SG 1
PFD 1
ALTN 3
ALTN
ALTN 1
ALTNALTN
ALTN
NORM
NORM
NORMNORM
NORM
PFD 1 PFD 2
PFD 2
ALTN 2 ALTN NORM
GX
_0
7_
04
0
PILOT’SSELECTED
ADC
COPILOT’SSELECTED
ADC
PFD1 SOURCEANNUNCIATION
PFD2 SOURCEANNUNCIATION
ADC1 ADC1 ADC1ADC1
ADC1 ADC2
ADC2 ADC1 ADC1ADC2
ADC2 ADC2 ADC2ADC2
ADC1 ADC3 ADC3
ADC2 ADC3 ADC3ADC2
ADC3 ADC3 ADC3ADC3
ADC3 ADC1 ADC1ADC3
ADC3 ADC2 ADC3
ADC SwitchesUsed to selectreversion onappropriate ADC.
PFD ANNUNCIATION
Pilot’s SideNormally fed as follows:• ADC 1 – if reverted then• ADC 3 if reverted then• ADC 2
–Copilot’s SideNormally fed as follows:• ADC 2 if reverted then• ADC 3 if reverted then• ADC 1
––
For Training Purposes OnlySept 04
7-37
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
IRS REVERSION
IRS ADC ADC IRS
SG 3
EICAS
SG 2SG 1
PFD 1
ALTN 3
ALTN
ALTN 1
ALTNALTN
ALTN
NORM
NORM
NORMNORM
NORM
PFD 1 PFD 2
PFD 2
ALTN 2 ALTN NORM
GX
_0
7_
04
1
PILOT’SSELECTED
ADC
COPILOT’SSELECTED
ADC
PFD1 SOURCEANNUNCIATION
PFD2 SOURCEANNUNCIATION
IRS1 IRS1 ATT1ATT1
IRS1 IRS2
IRS2 IRS1 ATT1ATT2
IRS2 IRS2 ATT2ATT2
IRS SwitchesUsed to select
reversion onappropriate IRS
PFD ANNUNCIATION
Pilot’s SideNormally fed as follows:• IRS 1 if reverted then• IRS 3 if reverted then• IRS 2
––
Copilot’s SideNormally fed as follows:• IRS 2 if reverted then• IRS 3 if reverted then• IRS 1
––
ATT2
MFD1 SOURCEANNUNCIATION
MFD2 SOURCEANNUNCIATION
MAG1 MAG1
MAG2 MAG2
IRS1 IRS3 ATT3
IRS2 IRS3 ATT3ATT2
IRS3 IRS3 ATT3ATT3 MAG3 MAG3
IRS3 IRS1 ATT1ATT3
IRS3 IRS2 ATT3
7-38 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
EICAS CONTROL PANELThe EICAS control panel located on the pedestal, can be used to revert SYSTEMS display, scroll non-displayed messages, and to display SYSTEMS synoptic pages.
STAT
HYDAC
ELECBLEED
AIRCOND
DCELEC
FUELFLT
CTRL
SCROLL
EICAS
SYSTEMS SELECT
NORMMFD 2MFD 1
BLEED ButtonUsed to displayBLEED/ANTI-ICEsynoptic.
AIR COND ButtonUsed to displayAIR CONDITIONINGsynoptic.
HYD ButtonUsed to displayHYDRAULICsynoptic.
AC ELEC ButtonUsed to displayAC ELECTRICALsynoptic.
DC ELEC ButtonUsed to displayDC ELECTRICALsynoptic.
FUEL ButtonUsed to displayFUEL synoptic.
FLT CTRL ButtonUsed to displayFLIGHT CONTROLSsynoptic.
EICAS SCROLL KnobUsed to scroll out of viewand/or scroll into view allmessages, except forwarning messages
STAT ButtonUsed to displaystatus synoptic.
SYSTEMS SELECT KnobUsed to revert SYSTEMSdisplay to alternate displays.
GX
_0
7_
03
2
For Training Purposes OnlySept 04
7-39
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
SYSTEMS SELECT CONTROL
GX
_0
7_
03
3STAT
HYDAC
ELECBLEED
AIRCOND
DCELEC
FUELFLT
CTRL
SCROLL
EICAS
SYSTEMS SELECT
NORMMFD 2MFD 1
20
10
30
20
10
30
09
8
7
65
4
3
2
1100 FEET
ALT
1 00032
4
10 13
mb/hPa
29 9 2
IN HG
IAS KNOTS
220200180 250
BARO
Honeywell HoneywellHoneywell Honeywell
13000.00
00
90
13 13
2019 20
22 2220
OXYGEN
AFTCABIN (°C)
FWDCABIN (°C)
CKPT (°C)
OPEN OPEN
OUTFLOW VALVES
CAB ALT
P
CAB RATE
LDG ELEV
00
1 2
1 2
1 2
QTY
ENG
APU
RES
OIL (QTS)
APU DOOR 11.2°
RPM EGT
BRAKE TEMP
11.5
650100
0603 03 03
11.55.26.0
%
% %
Honeywell
9500
29.92
AT1
VTA
M
0.450M
FMS1LOC1DTK
360
HDG330
10400
20
20
10
10
20
20
10
10
9500
10500
300
220
210
200
190
180
170
F3
LE
F1
2160
150
1856
4
N33
30
W24
21S
15
12
E6
3
0
1
2
3
1
2
3
ATT
HDGT
EICAS
GS
LOC
HDG
RAD
IASALT
HDG2
VOR 1
ADF 2
0010020
80
THRUST HDG ASEL ATT 2AP1VAPP VNAV ADC 3
9500
29.92
AT1
VTA
M
0.450M
FMS1LOC1DTK
360
HDG330
10400
20
20
10
10
20
20
10
10
9500
10500
300
220
210
200
190
180
170
F3
LE
F1
2160
150
1856
4
N33
30
W24
21S
15
12
E6
3
0
1
2
3
1
2
3
ATT
HDGT
EICAS
GS
LOC
HDG
RAD
IASALT
HDG2
VOR 1
ADF 2
0010020
80
THRUST HDG ASEL ATT 2AP1VAPP VNAV ADC 3
WX
ET
NO BEARINGRA 9 . 8NM +13TA 4 . 5NM -04
SAT
GSPD
TERR
-56
TAT
TAS
-40
234
345
INHIB
LX
00 : 10 0 . 05L
MAG2HDG315
ETE 1+36
12 . 5KDVT
NM
FLBELOW
TCAS TEST
FMS1360
N
5 5
3
6
33
30
- 02
- 02
+ 12- 04
KABC
KKLM
KKLM
TOC
TOC
KGHJ
KGHJ
LUF
KDEF
KDEF
4000 4000
FL180
+ 09
DU 1
PFD 1 MFD 1
DU 2
EICAS
DU 3
SYSTEMS
DU 4
MFD 2
DU 5
PFD 2
DU 6
WX
T5 . 0%
LX
G85%
STAB
ET 235°50 . 0NM00 : 10
TRU
N
ETE1+36
12 . 5KDVT
NM
FMS1
50 50
KNOP
KKLM
TOC
KGHJ
KABCLUF
KDEF
134
136
N 023° 29 . 6W 112° 01 . 5
SAT
GSPD
TERR
-56
TAT
TAS
-40
234
345
INHIB
KKLMTOC
KGHJKDEF
4000 4000
FL180
SYSTEMS SELECT Knob• NORM SYSTEMS displays on DU4
MFD1 SYSTEMS displayed on DU2MFD2 SYSTEMS displayed on DU5
–• –• –
TOTAL FUEL (LBS) 4155O
1.54
146OO 146OO1OOOO
N2
FF (PPH)
OIL TEMP
OIL PRESS
93.4575O11581
1.65
CRZEPR
IGN
START START
IGN
NDSTAB
1.54
1.65
73.3
T/ON1SYNC
73.3
789
ITTSYNC
789 DN DN DN
OUT
3O
GEAR
–TRIMS–
NL NRRUDDER
AIL
RWDLWD
7.2
NU
93.4575O11581
235O
NO TAKEOFFPARK/EMER BRAKE ON
END
7-40 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
SYSTEMS SELECT
20
10
30
20
10
30
09
8
7
65
4
3
2
1100 FEET
ALT
1 00032
4
10 13
mb/hPa
29 9 2
IN HG
IAS KNOTS
220200180 250
BARO
Honeywell HoneywellHoneywell Honeywell
13000.00
00
90
13 13
2019 20
22 2220
OXYGEN
AFTCABIN (°C)
FWDCABIN (°C)
CKPT (°C)
OPEN OPEN
OUTFLOW VALVES
CAB ALT
P
CAB RATE
LDG ELEV
00
1 2
1 2
1 2
QTY
ENG
APU
RES
OIL (QTS)
APU DOOR 11.2°
RPM EGT
BRAKE TEMP
11.5
650100
0603 03 03
11.55.26.0
%
% %
Honeywell
9500
29.92
AT1
VTA
M
0.450M
FMS1LOC1DTK
360
HDG330
10400
20
20
10
10
20
20
10
10
9500
10500
300
220
210
200
190
180
170
F3
LE
F1
2160
150
1856
4
N33
30
W24
21S
15
12
E6
3
0
1
2
3
1
2
3
ATT
HDGT
EICAS
GS
LOC
HDG
RAD
IASALT
HDG2
VOR 1
ADF 2
0010020
80
THRUST HDG ASEL ATT 2AP1VAPP VNAV ADC 3
9500
29.92
AT1
VTA
M
0.450M
FMS1LOC1DTK
360
HDG330
10400
20
20
10
10
20
20
10
10
9500
10500
300
220
210
200
190
180
170
F3
LE
F1
2160
150
1856
4
N33
30
W24
21S
15
12
E6
3
0
1
2
3
1
2
3
ATT
HDGT
EICAS
GS
LOC
HDG
RAD
IASALT
HDG2
VOR 1
ADF 2
0010020
80
THRUST HDG ASEL ATT 2AP1VAPP VNAV ADC 3
SYSTEMS
DU 5
WX
T5 . 0%
LX
G85%
STAB
ET 235°50 . 0NM00 : 10
TRU
N
ETE1+36
12 . 5KDVT
NM
FMS1
50 50
KNOP
KKLM
TOC
KGHJ
KABCLUF
KDEF
134
136
N 023° 29 . 6W 112° 01 . 5
SAT
GSPD
TERR
-56
TAT
TAS
-40
234
345
INHIB
KKLMTOC
KGHJKDEF
4000 4000
FL180
20
10
30
20
10
30
09
8
7
65
4
3
2
1100 FEET
ALT
1 00032
4
10 13
mb/hPa
29 9 2
IN HG
IAS KNOTS
220200180 250
BARO
Honeywell HoneywellHoneywell Honeywell
13000.00
00
90
13 13
2019 20
22 2220
OXYGEN
AFTCABIN (°C)
FWDCABIN (°C)
CKPT (°C)
OPEN OPEN
OUTFLOW VALVES
CAB ALT
P
CAB RATE
LDG ELEV
00
1 2
1 2
1 2
QTY
ENG
APU
RES
OIL (QTS)
APU DOOR 11.2°
RPM EGT
BRAKE TEMP
11.5
650100
0603 03 03
11.55.26.0
%
% %
Honeywell
9500
29.92
AT1
VTA
M
0.450M
FMS1LOC1DTK
360
HDG330
10400
20
20
10
10
20
20
10
10
9500
10500
300
220
210
200
190
180
170
F3
LE
F1
2160
150
1856
4
N33
30
W24
21S
15
12
E6
3
0
1
2
3
1
2
3
ATT
HDGT
EICAS
GS
LOC
HDG
RAD
IASALT
HDG2
VOR 1
ADF 2
0010020
80
THRUST HDG ASEL ATT 2AP1VAPP VNAV ADC 3
9500
29.92
AT1
VTA
M
0.450M
FMS1LOC1DTK
360
HDG330
10400
20
20
10
10
20
20
10
10
9500
10500
300
220
210
200
190
180
170
F3
LE
F1
2160
150
1856
4
N33
30
W24
21S
15
12
E6
3
0
1
2
3
1
2
3
ATT
HDGT
EICAS
GS
LOC
HDG
RAD
IASALT
HDG2
VOR 1
ADF 2
0010020
80
THRUST HDG ASEL ATT 2AP1VAPP VNAV ADC 3
WX
ET
NO BEARINGRA 9 . 8NM +13TA 4 . 5NM -04
SAT
GSPD
TERR
-56
TAT
TAS
-40
234
345
INHIB
LX
00 : 10 0 . 05L
MAG2HDG315
ETE 1+36
12 . 5KDVT
NM
FLBELOW
TCAS TEST
FMS1360
N
5 5
3
6
33
30
- 02
- 02
+ 12- 04
KABC
KKLM
KKLM
TOC
TOC
KGHJ
KGHJ
LUF
KDEF
KDEF
4000 4000
FL180
+ 09
DU 2
SYSTEMS
SYSTEMS SELECT
NORMMFD 2MFD 1
SYSTEMS SELECT
NORMMFD 2MFD 1
• SYSTEMS displayed on DU2MFD1 –
• – SYSTEMS displayed on DU5MFD2
NOTE:When SYSTEMS SELECT is reverted to either MFD 1 or MFD 2,all system synoptics can be displayed on the applicable DU.
GX
_0
7_
03
4
13000.00
00
90
13 13
2019 20
22 2220
OXYGEN
AFTCABIN (°C)
FWDCABIN (°C)
CKPT (°C)
OPEN OPEN
OUTFLOW VALVES
CAB ALT
P
CAB RATE
LDG ELEV
00
1 2
1 2
1 2
QTY
ENG
APU
RES
OIL (QTS)
APU DOOR 11.2°
RPM EGT
BRAKE TEMP
11.5
650100
0603 03 03
11.55.26.0
%
% %
13000.00
00
90
13 13
2019 20
22 2220
OXYGEN
AFTCABIN (°C)
FWDCABIN (°C)
CKPT (°C)
OPEN OPEN
OUTFLOW VALVES
CAB ALT
P
CAB RATE
LDG ELEV
00
1 2
1 2
1 2
QTY
ENG
APU
RES
OIL (QTS)
APU DOOR 11.2°
RPM EGT
BRAKE TEMP
11.5
650100
0603 03 03
11.55.26.0
%
% %
TOTAL FUEL (LBS) 4155O
1.54
146OO 146OO1OOOO
N2
FF (PPH)
OIL TEMP
OIL PRESS
93.4575O11581
1.65
CRZEPR
IGN
START START
IGN
NDSTAB
1.54
1.65
73.3
T/ON1SYNC
73.3
789
ITTSYNC
789 DN DN DN
OUT
3O
GEAR
–TRIMS–
NL NRRUDDER
AIL
RWDLWD
7.2
NU
93.4575O11581
235O
NO TAKEOFFPARK/EMER BRAKE ON
END
TOTAL FUEL (LBS) 4155O
1.54
146OO 146OO1OOOO
N2
FF (PPH)
OIL TEMP
OIL PRESS
93.4575O11581
1.65
CRZEPR
IGN
START START
IGN
NDSTAB
1.54
1.65
73.3
T/ON1SYNC
73.3
789
ITTSYNC
789 DN DN DN
OUT
3O
GEAR
–TRIMS–
NL NRRUDDER
AIL
RWDLWD
7.2
NU
93.4575O11581
235O
NO TAKEOFFPARK/EMER BRAKE ON
END
For Training Purposes OnlySept 04
7-41
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
FLIGHT DATA RECORDEREICAS channels aircraft systems data (including altitude, airspeed, heading, acceleration, and radio communications events) to the Flight Data Recorder (FDR). DAU 4 gathers sensor data for transmission to the FDR.
DAU 4 is fully self-monitoring and provides CAS messages in the event of a failure. If DAU 4B channel fails, FDR information is not available.
To record an additional event, in the FDR, push the PILOT EVENT button on the landing gear control panel located on the pedestal. Pushing the PILOT EVENT will also encode the Central Aircraft Information Maintenance System (CAIMS).
CENTRAL AIRCRAFT INFORMATION AND MAINTENANCE SYSTEM (CAIMS)The CAIMS collects diagnostic and fault data from other airplane systems. From this data, the CAIMS assembles a fault record that can be used to monitor system performance during the flight. Maintenance personnel use CAIMS to accomplish system tests and to isolate defective components.
The CAIMS supplies fault data during all phases of airplane operation through the Portable Maintenance Access Terminal (PMAT) touch screen located in the passenger cabin. The PMAT hard-disk contains approximately 8 MB of operational software files and 25 MB of loadable diagnostic files. A CD-ROM of the Aircraft Maintenance manual (AMM) can be installed in the PMAT CD-ROM drive.
The crew has the option of monitoring the PMAT display for active faults and/or may print the report on the cockpit printer. For more information on the printer, refer to chapter 5 COMMUNICATIONS.
The CAIMS is comprised of the following components:
• PMAT (located in the cabin)
7-42 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
• DATA UPLOAD/DOWNLOAD switch and PRINT MAINT REPORT switch (located on bulkhead behind pilot)
Honeywell
PowerSwitch
Mode / FaultAnnunciation
3.5" Disk DriveAccess Port
POWER FAULTHARDDRIVE
OVERTEMP
PORTABLE MAINTENANCEACCESS TERMINAL
AM-200
GX
_0
7_
03
5
Honeyw
ell
Inte
rnatio
nal I
nc.
Ho
ne
ywe
llIn
tern
atio
na
l In
c.
AM
–2
00
AM
–2
00
CD ROM DriveAccess Port
For Training Purposes OnlySept 04
7-43
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
UP
DN
DN LCKRELEASE
LDG GEARNOSE STEER
HORN
BTMS OVHTWARN RESET
EVENT
ARMED
OFF
RMED
MUTED
PRINT MAINTREPORT
DATAUPLOAD/DOWNLOAD
DAU 1AIAC 1
IAC 2IAC 3
GPWSSATCOM
SDU
GPS 1GPS 2
ADC 1ADC 2
ADC 3
DAU 1B
WXR
DAU 2ADAU 2B
DAU 3A
IRS 1IRS 2
DAU 3B
DAU 4A
DAU 4B
IRS 3
CAIMS PRINT MAINT REPORT SwitchUsed to get a report of active faults fromthe cockpit printer.
DATA SELECTOR SwitchUsed to select system toupload/download a copy ofnon-volatile data on to a3.5-inch disk.
FDR/CAIMS Event ButtonUsed to record additional datain non-volatile memory ofCAIMS.
• Pilot Event Marker (located on the landing gear control panel).
GX
_0
7_
08
1
7-44 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
MESSAGES SUMMARY
NOTEA single message or a combined message can be displayed on a message line, up to a maximum of 18 characters.Example: L REVERSER UNLKD or R REVERSER UNLKD orL-R REVERSER UNLKD.
WARNING MESSAGES (RED)
CAS MESSAGE DESCRIPTION SOUND/VOICE CH.
APU FIRE APU fire APU FIRE 9
APU OVERSPEED Annunciated when an APU overspeed protective shutdown occurs 4
APU OVERTEMP Annunciated when an APU EGT overtemperature condition occurs 4
BRAKE OVHTOne or more hot brakes resulting in wheels at fuse plug release temperature during low speed portion of takeoff or landing/taxi
14
CABIN ALTExcessive cabin altitude. Note: Warning level is normally set at 9000 feet except when a/c takes off or lands at higher altitudes
CABIN ALTITUDE 13
CABIN DELTA P Excessive cabin differential pressure (positive or negative) 13
CHECK PFD Data wrap-around failed on both PFDs. Both PFDs may have misleading data 7
CONFIG AIL TRIM Displayed during T.O., aileron trim is out of the certified range (green band) NO TAKEOFF 7/10
CONFIG RUD TRIM Displayed during T.O., rudder is out of the certified range (green band) NO TAKEOFF 7/10
CONFIG SLAT/FLAP Flaps are not at either 6° or 16° during takeoff. Slats are not at out during takeoff NO TAKEOFF 7/10
CONFIG SPOILERS
Displayed during T.O. A spoiler is deployed for uses other than roll assistance. This happens in case of proportional lift dumping, GLD operation, uncommanded GS or MFS deployment
NO TAKEOFF 7/10
CONFIG STAB TRIM Displayed during T.O. Pitch trim is out of the certified range (green band) NO TAKEOFF 7/10
DUAL ENGINE OUT Double engine flameout
EMER PWR ONLYEither of the batteries are powering the DC ESS Bus and BATT Bus or the RAT Line Connector (LC) is in the RAT position
6
For Training Purposes OnlySept 04
7-45
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
ENG FIRE L (R) Left or right engine fire L-R ENGINE FIRE 9/17
GEAR Gear warning logic is indicating that the gear is not selected down GEAR 7/14
MLG BAY OVHT Main wheel well overheat (left and/or right main wheel well overheat)
GEAR BAY OVERHEAT 9/14
NORM BRAKE FAIL Loss of normal (pedal) braking NORMAL BRAKE FAIL 14
OIL LO PRESSL L (R) Left or right engine has low oil pressure while the engine is running 9/17
PARK/EMER BRAKE ON Park brake is on during takeoff NO TAKEOFF 14
REVERSER UNLKD L (R) Left and/or right thrust reverser not stowed with thrust lever in forward thrust range
L-R REVERSER UNLOCKED 9/17
SMOKE AVIONICS BAY Smoke warning ON in avionics bay SMOKE
SMOKE AV RACK Smoke warning ON in avionics rack (Global 5000 only) SMOKE Appx 1
SMOKE AFT LAV Smoke warning in the aft lavatory SMOKE 9
SMOKE BAGGAGE Smoke warning in the baggage compartment SMOKE 9
SMOKE CABIN Smoke warning in the cabin (Global Express only) SMOKE 9
SMOKE CLOSET Smoke warning in any four of the applicable closet areas SMOKE 9
SMOKE FWD LAV Smoke warning in the forward lavatory SMOKE 9
WING A/ICE OVHT Overtemperature detected in wing anti-ice system 3
WARNING MESSAGES (RED)
CAS MESSAGE DESCRIPTION SOUND/VOICE CH.
7-46 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
CAUTION MESSAGES (AMBER)
CAS MESSAGE DESCRIPTION CH.
→ FUEL XFER FAIL Left to right fuel transfer failure 11
← FUEL XFER FAIL Right to left fuel transfer failure 11
→ FUEL XFER ON Left to right fuel transfer failed on 11
← FUEL XFER ON Right to left fuel transfer failed on 11
AC BUS 1 (2) (3) (4) FAIL AC bus 1, 2, 3, or 4 is not powered or has a fault 6
AC ESS BUS FAIL AC essential bus is not powered due to a fault 6
ADC 1, 2, 3 MISCMP ADC 1, 2 or 3 has miscompared with the other two ADCs 16
AFCS ENGAGE INVAL FWC detects invalid engagement of AP 2
AFT XFER FAIL AFT tank fuel transfer failure (Not applicable G-5000) 6
AFT XFER OFF SCHED AFT tank fuel transfer off schedule (Not applicable G-5000) 6
ALL ADC MISCMP All valid ADCs have miscompared 16
ALL IRS MISCMP All valid IRSs have miscompared 16
AOA HEAT FAIL L (R) Left and/or right AOA heater has failed when it should be ON 3
AP PITCH TRIM FAIL AP pitch trim inoperative monitor detects invalid trim (only when down to one AP) 2
AP TRIM IS LWD Roll mistrim monitor detects excessive forces. For LWD, if AP disconnects, A/C will roll RWD 2
AP TRIM IS ND Pitch mistrim monitor detects excessive forces. If AP disconnects, A/C will pitch nose down 2
AP TRIM IS NU Pitch mistrim monitor detects excessive forces. If AP disconnects, then A/C will pitch nose up 2
AP TRIM IS RWD Roll mistrim monitor detects excessive forces. For RWD, if AP disconnects, A/C will roll LWD
APU BATT FAIL APU battery has failed 6
APU BLEED SYS FAIL Annunciated when the APU LCV position does not match command, or Bleed leak detection has been lost and APU bleed is not to be used 4
APU DOOR FAIL Annunciated when the APU door position does not match command 4
APU EGT SENSORS Annunciated when WOW is not true and both EGT thermocouple rakes have failed 4
APU FIRE FAIL APU detection element system dual loop failure (Complete loss or fire detection capability in APU) 4
APU FUEL SOV APU fuel shutoff valve failure 4
APU GEN OVERHEAT APU generator is overheating (to excessive temperatures). Message generated in-air only since the APU will not automatically shut down in flight 4
APU GEN OVLD There is an overload on APU generator 4
For Training Purposes OnlySept 04
7-47
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
APU OIL HI TEMP Annunciated when WOW is not true and a high oil temperature condition exists 4
APU OIL LO PRESS Annunciated when WOW is not true and a low oil pressure condition exists 4
APU REVERSE FLOW Annunciated when WOW is not true and a reverse flow condition exists 4
ASCB FAIL Loss of communication with all three bus controllers. Loss of cockpit instruments. All AFCS functions not operational 7
A/T NOT IN HOLD A/T not in T/O Hold Mode following the transition above 60 knots during T/O roll and until the aircraft transitions 400 ft. AGL
AUTO PRESS FAIL Automatic pressurization control is inoperative 13
AUTOBRAKE FAIL Autobrake not available 14
AV BATT FAIL Avionics battery has failed 6
AV FANS FAIL Both fans failed on ground (Global 5000 only) 13
BATT BUS FAIL Battery bus is not powered or has a fault 6
BATT MASTER OFF Battery master switch is off 6
BLEED LEAK L (R) Bleed leak detected on left or right bleed duct 13
BLEED SYS FAIL L (R) Bleed system failure 13
BRAKE 50% DGRAD Loss of two brakes (or more brakes if indication comes from discretes in BCU) 14
CABIN ALT Cabin altitude exceedance. Note: Caution level is normally set at 8200 ft. except when a/c takes off or lands at high altitude 13
CARGO DOOR Cargo bay door not closed 1
CAT 2 INVALID CAT 2 was active, but all conditions no longer valid 16
CB TRIP AC FEEDER A circuit breaker for an AC feeder/AC cabin feeder has tripped 6
CB TRIP DC FEEDER A circuit breaker for a DC feeder/DC cabin feeder has tripped 6
CHECK DU 1 (2) (3) (4) (5) (6) Data wrapped around from DUs does not match data from sensor 6
COWL A/ICE FAIL L (R) Left/right CAIV closed (valve switch or low pressure) but commanded open 3
CPLT BRAKE FAULT One or both copilot brake pedals not available 14
CTR FUEL XFER FAIL Center tank fuel transfer failure 11
CTR TANK FULL Center tank high level shutoff greater than 1000 gallons (Global 5000 only) Appx 1
DC BUS 1 FAIL DC bus 1 is inop 6
DC BUS 2 FAIL DC bus 2 is inop
DC EMER BUS FAIL DC emergency bus has failed 6
DC ESS BUS FAIL DC essential bus is not powered or has a fault 6
DISP CTLS FAIL Total loss of display control 7
CAUTION MESSAGES (AMBER)
CAS MESSAGE DESCRIPTION CH.
7-48 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
DOOR SYS FAIL Loss of fuselage & gear door indication 1
ELEC SYS FAIL A major fault detected in the electrical system ground only 6
ELEVATOR SPLIT Asymmetric elevator operation 10
ELT TRANSMITTING ELT is transmitting 8
EMER DEPRESS Emergency depressurization (dump) has been selected 13
EMER EXIT L (R) Left or right emergency exit door not closed and locked 8
EMER LIGHTS OFF Emergency lighting selected off 8
ENG FIRE FAIL L (R) Left or right engine detection element system dual loop failure. (Complete loss of fire detection capability for left or right engine) 9
ENG FLAMEOUT L (R) Left or right engine flameout 17
ENG FUEL LO TEMP L (R) Left/right engine inlet fuel temperature is below 5°C with engine running 17
ENG FUEL SOV L (R) Left and/or right engine fuel shutoff valve failure 17
ENG OVERSPED L (R) Left and/or right engine shutdown caused by Independent Overspeed Protection 17
ENG OVHT L (R) Left and/or right turbine cooling air overheat 17
ENG SAV FAIL L (R) Corresponding engine start air valve failure 17
FADEC FAIL L (R) Major FADEC failure in both lanes. Engine operation may be affected 17
FADEC N1 CTL L (R) Left and/or right engine is in N1 control; left and/or right FADEC has detected a fault and reverted to N1 control 17
FADEC OVHT L (R) Internal EEC temperature monitor tripped 17
FIRE BTL1 LO PRESS Extinguishing bottle #1 low pressure 9
FIRE BTL2 LO PRESS Extinguishing bottle #2 low pressure 9
FLAP FAIL Flap actuation inop 10
FLAP FAULT Flaps have been shut down 10
FLT SPLR DEPLOYED Displayed to alert crew that flight spoilers are deployed at low altitude (RA between 10 and 300 ft.) or when throttle is at high power 10
FLT SPOILERS FAIL Displayed if control of at least 2 pairs of flight spoilers fail. In case of loss of hydraulic power, failure is declared only if panel is upfloating 10
FUEL COMPUTR FAIL Fuel computer failure 11
FUEL FILTER L (R) Left and right fuel filter bypass 11
FUEL IMBALANCE Fuel imbalance 11
FUEL LO PRESS L (R) Left and/or right low engine fuel feed pressure with the HPSOV open 17
FUEL LO QTY Low fuel quantity 11
FUEL RECIRC FAIL L (R) Recirculation valve not in commanded position 11
CAUTION MESSAGES (AMBER)
CAS MESSAGE DESCRIPTION CH.
For Training Purposes OnlySept 04
7-49
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
FUEL TEMP SENSOR Bulk fault temperature no longer reliable 11
FUEL UNIT MISMATCH Fuel unit discrepancy between the fuel quantities displayed on the EICAS and the Refuel/Defuel Panel 11
GEAR DISAGREE Gear not at selected position within 30 seconds of command or any gear unsafe 14
GEAR SYS FAIL Normal gear operation not available 14
GEN 1 (2) (3) (4) OVLD There is an overload on generator 1, 2, 3 or 4 6
GND LIFT DUMP
Displayed when:· System power-on self tests detects a valve jammed in the deploy position.· During T.O. or landing:GLD not armed (loss or absence of automatic sum or OFF switch which affects at least two pairs of spoilers (i.e. GS or MFS)· GLD is lost or degraded (deployment delayed) for at least two pairs of spoiler (GS or MFS), due to loss of one ground condition· Two pairs of ground spoilers failed in retracted position (unless associated hydraulics is low)· One pair of ground spoilers failed in retracted position and one pair of flight spoilers failed.
10
HYD 1 (2) (3) HI TEMP Indicates that hydraulic system No. 1-2-3 oil temperature is hot (≥ 96°C) 12
HYD 1 (2) (3) LO PRESS Indicates that hydraulic system No. 1-2-3 oil pressure is low (<1800 psi) 12
HYD 1 (2) (3) LO QTY Hydraulic system fluid level is too low for normal aircraft operation during flight 12
HYD 1-2 LO PRESS Indicates that both hydraulic systems have less than 1800 psi 12
HYD 1-3 LO PRESS Indicates that both hydraulic systems have less than 1800 psi 12
HYD 2-3 LO PRESS Indicates that both hydraulic systems have less than 1800 psi 12
HYD 3 OVERFILLED On ground, hydraulic system 3 fluid quantity exceeds 70% of its capacity. Current level does not allow for fluid replacement when landing gear is retracted 12
HYD RAT PUMP FAIL Indicates that the hydraulic ram air turbine (RAT) hydraulic pump is not producing pressure (<1800 psi) when it should be 12
HYD SOV FAIL L (R)
Indicates that the left and/or right engine hydraulic fire wall shutoff valve (SOV) did not go to its commanded position (open or closed) when the pilot has manually armed or disarmed the left and/or right engine fire extinguishing system
12
IAC 1 (2) (3) OVHT IAC has overheated, resulting in possible loss of function 7
ICE Cowl or wing icing detected with one of the three anti-ice systems off (L/R cowl or wing) 3
ICE DETECTOR FAIL Loss of both ice detectors 3
INBD BRAKE FAIL L (R) Failure on affected inboard brake 14
INBD BRK LO PRESS Inboard brakes supply depleted (hydraulic system 3) 14
INT CABIN DOOR Internal door not open and latched for takeoff or landing
IRS 1 (2) (3) MSCMP IRS 1, 2 or 3 has miscompared with the other two IRSs 16
CAUTION MESSAGES (AMBER)
CAS MESSAGE DESCRIPTION CH.
7-50 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
IRS 1 (2) (3) OVHT Annunciated when the IRS has overtemp condition (> about 70-73°C) 16
IRS 1 (2) (3) SET HDG IRS has defaulted to heading of 360° upon entering attitude mode 16
LARGE SERV DOORS One or more of AFT equipment bay, refuel/defuel, hydraulic access or belly fairing stowage access doors/panels not closed 1
MACH TRIM FAILDisplayed to alert the crew that due to loss of mach data acquisition, the mach trim function has failed and will not compensate for pitching moments caused by mach changes. Failure of pitch trim is covered by STAB TRIM message
10
MAIN GEAR DOOR L (R) Left and/or right main gear door not closed 14
MLG BAY OVHT FAIL Left and/or right main landing gear bay overheat detection element failure. (Complete loss of overheat detection for main landing gear) 14
NOSE DOOR Nose gear door not closed 1
NOSE STEER FAIL Loss of nosewheel steering, nosewheel casters 14
OIL LO QTY L (R) Engine oil quantity is low 5
OUTBD BRAKE FAIL L (R) Failure on affected outboard brake 14
OUTBD BRK LO PRESS Outboard brakes supply depleted (hydraulic system 2) 14
OXYGEN LO QTY Either the oxygen quantity is low or one or more of the oxygen bottles are not available 1
PACK AUTO FAIL L-R Left and right pack automatic control inoperative 13
PACK AUTO FAIL L (R) Pack control inoperative
PACK FAIL L (R) Left or right pack fail (overheat)
PACK FAIL L-R Left and right pack failed due to Ram air inlet duct rupture 13
PACK TEMP L (R) Manual temperature selection out of range 13
PARK/ EMER BRAKE ON Park brake is on with weight off wheels 7/14
PASSENGER DOOR Passenger door not closed 1
PITOT 1 (2) (3) HT FAIL Pitot 1-2-3 heat has failed 7
PLT BRAKE FAULT One or both pilot brake pedals not available 14
PRI FUEL PUMPS L (R) Left and/or right primary (AC) fuel pumps failure 11
RAT GEN FAIL A fault has been detected in the RAT generator system during power up BIT check 6
REV LOCK FAIL L (R) Left and/or right thrust reverser locks (2 of 3) not locked with thrust lever in forward thrust range. Thrust reverser will not deploy 17
REVERSER FAIL L (R) Left and/or right thrust reverser has failed and doors will stay in current position 17
ROLL SELECT Displayed to alert the crew that the pilot and copilot roll control are disconnected and that no roll priority has been selected within 30 seconds from roll disconnect 10
ROLL SPOILERS FAIL Displayed if roll spoiler function is inoperative for at least 2 pairs of flight spoilers 10
CAUTION MESSAGES (AMBER)
CAS MESSAGE DESCRIPTION CH.
For Training Purposes OnlySept 04
7-51
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
RUD AUTHORITY HIGHDisplayed to alert the crew that the rudder authority available is too high for the indicated airspeed. This message will not be displayed if the rudder limiter position or airspeed is indeterminate
10
RUD AUTHORITY LOW
Displayed in combination with “RUD LIMITER FAIL” to alert the crew that the rudder limiting capability failed and that authority available is low (rudder limiting failed in low authority position) for engine failure compensation or crosswind. Not displayed if the system is not able to determine its authority status
10
RUD LIMITER FAIL
Displayed to alert the crew that rudder limiting capability is lost. If the system is able to determine its rudder authority level versus the current A/C configuration, one and only one of the following messages will be displayed also: “Rud authority high” (system failed with too much authority available). “Rud authority low” (system failed without enough authority available), “Rud authority safe” (system failed with enough authority available and no risk of structure damage)
10
SG 1 (2) (3) FAIL Loss of communication with the SG, or the SG is indicating a power-up failure 7
SLAT FAIL Slat actuation system inop 10
SLAT FAULT Slats have been shut down 10
SLAT-FLAP FAIL Slat and/or flap actuation system inoperative, the slats and/or flaps can no longer be selected 10
SLAT-FLAP FAULT
Slat and/or flap systems have shutdown and may be out of the selected position due to jam, loss of power, overheat, etc. Once the condition clears, if the control lever is selected to a new position, the system will again attempt to drive and the message will disappear
10
SMALL SERV DOORS One or more of the small/access service doors not closed 1
SMOKE AFT (FWD) LAV FAIL Smoke detector installed in the aft lavatory has failed 9
SMOKE AV BAY FAIL Smoke detector installed in the avionics bay has failed 9
SMOKE AV RACK FAIL Smoke detector in avionics rack has failed (Global 5000 only) 9
SMOKE BAGGAGE FAIL Smoke detector installed in the baggage compartment has failed (one or both smoke detectors installed in baggage compartment have failed) 9
SMOKE CABIN FAIL Smoke detector in cabin has failed (Global Express only) 9
SMOKE CLOSET FAIL One or more (i.e. up to four) closet smoke detectors have failed 9
SPLR LEVER FAIL The flight spoiler function for at least two pairs of flight spoilers is inoperative. The ground lift dumping and roll assist functions are not affected 10
STAB TRIM
Displayed to alert the crew that the pitch trim function is not available due to both pitch trim channels inoperative (failure, channel disconnect through PTRIM DISCONNECT pushbutton, master disconnect switch pressed for more than 5 continuous seconds)
10
STALL PROTECT FAIL Pusher has failed, has been manually deactivated, a SPC channel has failed, an AOA sensor has failed, or the pusher switch is enabled 10
START ABORTED L (R) FADEC has aborted an automatic start 17
STBY PITOT HT FAIL Standby pitot heat has failed 7
CAUTION MESSAGES (AMBER)
CAS MESSAGE DESCRIPTION CH.
7-52 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
THROTTLE FAIL L (R) Corresponding throttle has failed. Engine operation will be affected as a function of aircraft configuration 17
TRIM AIR FAIL Trim air failed (overheat) 10
TRIM AIR LEAK Leak detected in trim air duct 13
UNCOMMANDED BRAKE Brake on when pedals not applied 14
WINDOW HEAT FAIL L (R) Left/right side window temperature controller has failed and cannot heat 3
WING A/ICE FAIL L (R) Low temperature, left/right WAI valve closed or left/right bleed off with CBW closed 3
WING A/ICE LEAK Bleed leak detected in wing anti-ice duct 11
WING A/ICE LO HEAT Low temperature detected on affected wing 3
WING FUEL HI TEMP Either the left or right or both wing fuel temperature is high 11
WING FUEL LO TEMP Either the left or right or both wing fuel temperature is low 11
WING FULL L (R) Left or right wing fuel overfill 11
WING TO CTR LEAK Wing tank to center tank leak 11
WOW FAIL Loss of WOW function 14
WSHLD HEAT FAIL L (R) Left/right windshield temperature controller has failed and cannot heat 3
XBLEED FAIL Bleed crossfeed failed (open or closed) 13
YD 1 (2) FAIL Affected yaw damper failed 2
YD 1-2 FAIL YD 1 and 2 fail 2
YD OFF FWC detects no YD engaged 2
CAUTION MESSAGES (AMBER)
CAS MESSAGE DESCRIPTION CH.
For Training Purposes OnlySept 04
7-53
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
ADVISORY MESSAGES (CYAN)
CAS MESSAGE DESCRIPTION CH.
→ FUEL XFER ON Left to right fuel transfer on 11
→ XFER VALVE OPEN Left to right transfer valve open 11
← FUEL XFER ON Right to left fuel transfer on 11
← XFER VALVE OPEN Right to left fuel transfer valve open 11
A/T 1-2 FAIL A/T 1 and/or 2 has stopped communicating or is invalid (as determined by FWC), or the A/T reports a hardware or servo failure 17
A/T ADC MISCMP Selected A/T system is unavailable due to ADC data miscompare required for dual coupled approach A/T operation 17
A/T IRS MISCMP Selected A/T system is unavailable due to IRS data miscompare required for dual coupled approach A/T operation 17
AC BUS 1 (2) (3) (4) XFER FAULT Transfer of alternative power supply to AC BUS1-2-3-4 may be lost 6
ADC 1 (2) (3) DEGRADED Set when the displayed ADC is unreliable. Degraded static error correction. Note: To be reviewed when triple failure condition for RVSM criteria 16
ADC 1 (2) (3) FAIL Annunciated when either ADC1, ADC2 and/or ADC3 has failed 16
AFCS 1 (2) FAILFault Warning determines that one or both AFCS function/s failed, either by examining in-line validity or by invalidating data being transmitted. The AFCS function includes the YD, Autopilot and Flight Director
2
AFT R/D VALVE OPEN AFT refuel/defuel valve failed open (not applicable to Global 5000) 11
AFT XFER FAULT AFT tank fuel transfer fault (not applicable to Global 5000) 11
AFT XFER OFF SCHED AFT tank fuel transfer off schedule (not applicable to Global 5000) 11
AP 1-2 FAIL Both autopilots are failed 2
APU BATT CHGR FAIL APU battery charger has detected a fault and shutdown 6
APU BLEED DISABLEDAnnunciated when the LCV command is received and either the aircraft is above 35,000 ft. Or the 60 second warm-up period after speed reaches 99% is not complete (ground only)
4
APU FADEC FAIL Annunciated when no data is received by the DAU 4
APU FAULTAnnunciated when failure of a single speed sensor or EGT thermocouple rake is detected or the fuel solenoid has failed to close or the fuel/oil filters have gone into impending bypass or the LOP switch is failed (flight only)
4
APU FIRE FAULT APU fire detection element system fault (one channel of the system is unreliable, other channel is still operational 4
APU GEN FAIL APU generator has failed 4
APU IN BITE Annunciated after Run is selected from the APU switch until prestart BITE is complete and the inlet door is positioned (ground only) 4
APU NOT AVAILABLE Annunciated when the APU cockpit selector switch is set to Start or Run and the FADEC NVM is being downloaded or the door rigging test is active 4
APU OIL LO QTY Annunciated when APU oil level drops below 2 quarts and WOW is true 4
7-54 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
APU SHUTDOWN Annunciated when an APU protective shutdown occurs other than overspeed or overtemperature 4
APU SQUIB 1 (2) FAIL Fire bottle 1-2 is not available to APU 4/9
ASCB CTLR 1 (2) (3) FAIL Loss of communication with the bus controller 7
ASCB FAULT An LRU transmitting on the ASCB is able only to transmit on one of its busses (displayed on-ground only) 7
ATS ENVELOPE FADEC has determined that the aircraft is within the starter assisted envelope 17
AUTO PRESS FAULT Automatic control of cabin pressure from one controller is inoperative 13
AUX FUEL PUMP L (R) Left and/or right auxiliary (DC) fuel pump failure 11
AV BATT CHGR FAIL Avionics battery charger has detected a fault and shutdown 6
AV FANS FAIL Both fans failed in flight (Global 5000 only) 13
AV RACK FAN FAIL Avionics rack fan failed (Global 5000 only) 13
AVIONIC FAN FAIL Avionics fan failed in the underfloor avionics bay 13
BATT BUS XFER FAULT Transfer of alternative power supply to BATT BUS may be lost 6
BATT EMER PWR ON The batteries are the only source of electrical power 6
BLEED FAULT L (R) Loss of redundancy on left and/or right bleed system (but PRV is already open) 3
BLEED MISCONFIG Improper bleed configuration for engine start 13
BRAKE FAULT Loss of redundancy in brake control system 14
BRAKE TEMP One or more brake indications are in the white brake temperature indication band 14
CAB ALT LEVEL HI Message displayed when the warning or the caution level have been set higher than their normal values due to landing or takeoff at high altitude 13
CB TRIP A circuit breaker has tripped 6
CHECKLIST MISMATCH Checklists are not identical in all IACs (message active on ground only) 7
COWL A/ICE FAULT L (R) Left/right cowl anti-icing degradation has occurred but operationally safe 3
CTR XFER FAULT Center Fuel Transfer Fault (either left or right fuel transfer not working or management fault) 11
DAU 1A-1B FAIL Loss of communication with DAU, or DAU is indicating a failure 7
DAU 2A-2B FAIL Loss of communication with DAU, or DAU is indicating a failure 7
DAU 3A-3B FAIL Loss of communication with DAU, or DAU is indicating a failure 7
DAU 4A-4B FAIL Loss of communication with DAU, or DAU is indicating a failure 7
DC BUS 1 (2) XFER FAULT Transfer of alternative power supply to DC BUS 1-2 may be lost 6
DC ESS XFER FAULT Transfer of alternative power supply to DC ESS may be lost 6
DU 1 (2) (3) (4) (5) (6) FAN DUs cooling fans have failed, resulting in possible loss of function 6
ADVISORY MESSAGES (CYAN)
CAS MESSAGE DESCRIPTION CH.
For Training Purposes OnlySept 04
7-55
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
ELEC SYS FAULT Loss of redundancy on EPGDS logic 6
ENG FIRE FAULT L (R) Left and/or right engine fire detection element system fault (one channel of the corresponding system is unreliable, other channel is still operational) 9
ENG SQUIB 1 (2) FAIL L(R) Fire bottle 1-2 is not available to LH/RH engine 9
ENG SYNC FAIL Selected Sync system is unavailable due to a detected failure 17
ENG SYNC LIMITSelected Sync system is unable to perform the pilot selected sync function due to an authority limit. Engine sync unavailable due to engine split greater than engine sync authority
17
ESS TRU 1 (2) FAIL Ess TRU 1/2 has failed 6
EXT AC PWR AVAIL External AC power is available 6
EXT DC PWR AVAIL DC external power is available 6
FADEC FAULT L (R) Minor FADEC fault. Engine operation should not be affected 17
FDR ACCEL FAIL Flight Data Recorder (FDR) accelerometer has failed 7
FDR FAIL Flight Data Recorder failure 7
FIRE SYS FAULTFIDEEX System fault: Fire + Smoke detection + Fire extinguishing are still operational. Fire loop, smoke detector and squib pressure bottle failures can no longer be annunciated. EMS CDU “FIRE TEST” will operate normally
9
FLAP DRIVE OVHTSystem shutdown due to overheat on at least one channel. Message self-clears once the channel has cooled down. Always displayed in conjunction with “FLAP FAULT”
10
FLAPS HALFSPD System operating at half speed 10
FLT SPOILERS FAULT
Displayed if one of a single pair of flight spoilers is inoperative (may be retracted or deployed); objective is to allow dispatch with this message, provided that affected panels are verified to be retracted. (In the event of hydraulics failure, message inhibited if panels are retracted)
10
FMS 1 (2) (3) FAIL Either FMS is reporting a failure or the FMS data transmitted is invalid 16
FUEL COMPUTR FAULT Fuel computer fault (one of the two channels only) 11
FUEL FILTER L (R) Left or right impending fuel filter bypass 11
FUEL QTY DEGRAD Fuel quantity degraded accuracy 11
FUEL RECIRC ON Fuel recirculation on in an unauthorized configuration (not applicable to Global 5000 and -9 FMQ GC or later) 11
GEAR SYS FAULT Loss of redundancy for downlock indications or EICAS communication 14
GEN 1 (2) (3) (4) FAIL Gen 1, 2, 3 and/or 4 has failed 6
GND LIFT DUMP For one pair of ground spoilers, the ground lift-dump function is inoperative; or, a ground spoiler upfloat is occurring in flight 10
GND PROX FAIL EGPWS INOP and NOT SUPPRESSED when EGPWS SYSTEMS FAIL message is displayed (i.e. COMPUTER FAIL or EGPWS not communicating) 16
ADVISORY MESSAGES (CYAN)
CAS MESSAGE DESCRIPTION CH.
7-56 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
GPWS SYSTEMS FAIL COMPUTER FAIL or EGPWS not communicating 16
HUMIDIFIER FAIL Humidifier failed 13
HYD EDP 1A (2A) FAIL Indicates that the hydraulic engine driven pump 1A-2A is not producing pressure (< 1800 psi) when it should be 12
HYD PUMP 1B (2B) (3B) FAIL
Indicates that the hydraulic electrical pump 1B-2B-3B is not producing pressure (< 1800 psi) when it should be 12
HYD PUMP 3A FAIL Hydraulic pump 3A not producing 1800 psi 12
IAC 1 (2) (3) INVALID Invalid software configuration in IAC, or incorrect aircraft ID 7
IAC 1 (2) (3) MEM FULL Trend and/or Exceedance memory is more than 80% full. Continued use will overwrite previous recordings 7
IAC 1 (2) (3) WOW INOP WOW discrete into IAC is failed, resulting in no power-up testing and possible function loss 7
IAC 1 (2) AURAL FAIL No 28V power to aural warning, or BIT failure being indicated 7
IAC CONFIG MISMTCH IACs not configured with the same options or aircraft configuration 7
ICE Cowl or wing icing detected with anti-ice systems on (left/right cowl and wing) 3
ICE DETECTOR FAULT Loss of one ice detector 3
IRS 1 (2) (3) AUX FAIL Annunciated when the indicated IRU backup power source has failed 16
IRS 1 (2) (3) AUX PWR Annunciated when the indicated IRS has lost its normal power source and has reverted to Auxiliary DC power 16
IRS 1 (2) (3) FAIL Annunciated when the indicated IRS has failed. (IRU detects an internal failure) 16
IRS 1 (2) (3) NO ALIGN Set when IRS fails to properly align: e.g., annunciated due to improper position entry or excessive airplane motion while in align mode 16
LTRK FAIL Annunciated when the LaserTrak (third navigation source for a dual FMS installation) has failed or has been selected off 16
MACH XDUCER FAIL Mach transducer has failed 7
MAN PRESS FAULT One of the two altitude limitation systems in inoperative in the associated manual channel 13
MFD CTLR 1 (2) FAIL Loss of one side’s MFD controller 16
MLG BAY OVHT FAULT Main landing gear bay detection element system fault (one channel of the system is unreliable, other channel is still operational) 14
NAV LIGHTS FAIL Both the primary/secondary navigation lights for either the left wing or right wing have failed or one minimum of the tail navigation lights have failed 1
NO TAKEOFF Indicates that the airplane is not configured for takeoff during taxi 7
OIL FILTER L (R) Left and/or right impending oil filter bypass 17
OIL RES LO QTY Oil system requires replenishment 17
OUTFLOW VLV 1 (2) FAIL Fwd/Aft outflow valve inoperative 13
ADVISORY MESSAGES (CYAN)
CAS MESSAGE DESCRIPTION CH.
For Training Purposes OnlySept 04
7-57
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
PACK FAULT L (R) Left and/or right pack fault 13
PASSENGER OXY ON Oxygen, either manually selected or automatically turned on, is flowing to the main cabin oxygen masks 1
PITCH DISC FAULT Pitch disconnect solenoid has failed in the locked or unlocked position 10
PITCH FEEL FAULT Displayed to alert the crew that either pitch feel is inoperative, or degraded (force gradient not nominal) on one or both channels 10
PRI FUEL PUMP L (R) Left and/or right primary (AC) fuel pump failure 11
PROBE MON FAIL L (R) Monitoring LRU has failed. Heater status on probes and associated systems is not verified 7
R/D VALVE OPEN L (R) Left and/or right defuel valve failed open 11
RAM AIR FAIL Ram air failure 13
RAT GEN ON The RAT is deployed and the RAT LC is on 6
RECIRC FAN FAIL Both recirculation fans failed 6
REV LOCK FAULT L (R) One of two primary stow switches on corresponding thrust reverser indicating unstowed with thrust lever in forward thrust range 17
REVERSER FAULT L (R) Minor fault in the thrust reverser system. Thrust reverser operation should be normal 17
REVRSION CTLR FAIL Loss of rev control functions due to improper connection 16
RUD AUTHORITY SAFE
Displayed in combination with “RUD LIMITER FAIL” to alert the crew that the rudder limiting capability failed and that authority available is safe in current configuration and speed. Not displayed if the system is not able to determine its authority status
10
RUD LIMITER FAULT Displayed to alert the crew that one and only one channel is failed 7
SAFETY VALVE OPEN Safety valve 1 or safety valve 2 not fully closed 13
SELCAL HF1 (2) Annunciated when the HF1-2 indicates an incoming message. Voice: “SEL-CALL” twice. Reset with Push-To-Talk (PTT) 5
SELCAL VHF1 (2) (3) Annunciated when the VHF1-2-3 indicates an incoming message. Voice: “SEL-CALL” twice. Reset with Push-To-Talk (PTT) 5
SET LDG ELEV No landing information is received by CPC from FMS or LDG ELEV is selected MAN and no value was selected on the CPCS control panel 16
SHAKER 1 (2) FAIL
1. Pilot’s shaker has failed (the actual motor) or the commanding SPC channel has failed2. Copilot’s shaker has failed (the actual motor) or the commanding SPC channel has failed
10
SLAT DRIVE OVHTSystem shutdown due to overheat on at least one channel. Message self-clears once the channel has cooled down. Always displayed in conjunction with “SLAT FAULT”
10
SLAT FAULT Slats inoperative 10
ADVISORY MESSAGES (CYAN)
CAS MESSAGE DESCRIPTION CH.
7-58 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
SLAT HALFSPD System operating at half speed 10
SLAT-FLAP HALFSPD Slat actuation system (and/or flap actuation system) operating at half speed, due to a fail or fault condition in one channel only of the slats and/or flaps 10
SLAT/FLAP BIT Posts on the ground only when maintenance action is required on the slat/flap system prior to the 500 hour scheduled interval 10
SLAT-FLAP FAULT Slat and flap inoperative 10
SPLRS/STAB BIT Posts on ground only when maintenance required 10
SPLRS/STAB IN TESTDisplayed when the spoilers and stab trim systems perform their on-ground self-test, once all hydraulics are ON, since spoilers and stab trim are inoperative during the test (approximately 20 sec.)
10
STAB CH 1 (2) FAIL Displayed only when Stab Trim Channel 1 (or 2 but not both) is failed or inhibited by abnormal master switch operation 10
STALL WARN ADVANCE Stall reversion mode has been activated - can be done automatically based on a/c condition or manually 10
STALL WARN BASIC 1. Stall erroneously set in basic mode, or2. Split between L and R AOR vanes 10
TAT 1 (2) (3) FAIL TAT probe 1, 2 and/or 3 failed 7
TAT HT 1 (2) (3) FAIL1: Left engine TAT heater failed, or2: Right engine TAT heater failed, or3: Fuselage TAT heater failed
7
TERR FAILTERRAIN AWARENESS INOP and NOT SUPPRESSED when EGPWS SYSTEMS FAIL message is displayed (i.e. COMPUTER FAIL or EGPWS not communicating)
16
TRIM AIR FAULT Trim air fault 13
TRU 1 (2) FAIL TRU 1/2 has failed 6
WINDMILL ENVELOPE FADEC has determined that the aircraft is within the windmill start envelope 17
WINDSHEAR FAIL(WINDSHEAR INOP) and NOT [(COMPUTER FAIL) or (EGPWS not communicating)] SUPPRESSED when EGPWS SYSTEMS FAIL message is displayed
16
WING A/ICE FAULT Loss of redundancy on wing a/ice system (CBW failed, one temperature sensor fail, opening of CBW and closing of one WAIV) 3
WING A/ICE SENSOR Failure of both outboard wing a/ice temperature sensors 3
WOW FAULT Loss of redundancy on WOW 14
XFEED VALVE FAIL Crossfeed valve failure 11
YD HEAT 1 (2) FAIL Yaw damper actuator 1-2 heater failed. System is heating unused YD 10
YD NOT CENTERED YD linear actuator not centered while on ground 10
ADVISORY MESSAGES (CYAN)
CAS MESSAGE DESCRIPTION CH.
For Training Purposes OnlySept 04
7-59
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
STATUS MESSAGES (WHITE)
CAS MESSAGE DESCRIPTION CH.
→ FUEL XFER ON Left to right transfer on 11
← FUEL XFER ON Right to left transfer on 11
AC BUS 1 (2) (3) (4) MAN OFF AC bus 1-2-3-4 has been manually isolated 6
AFT FUEL XFER OFF Aft fuel transfer off (not applicable to Global 5000) 11
AFT FUEL XFER ON Aft fuel transfer on (not applicable to Global 5000) 11
APU BLEED OFF Annunciated when the APU LCV switch is in the manual OFF position and the load valve is closed 4
APU BLEED ON Annunciated when the APU LCV switch is in the manual ON position and the load valve is open 4
APU GEN OFF APU generator is OFF 4
APU SOV CLSD APU shutoff valve closed 4
APU SOVS CLSD APU fire handle has been pulled and the fuel and bleed shutoff valves closed as commanded 4
AUTOBRAKE HI Autobrake is armed for high decel braking 14
AUTOBRAKE LO Autobrake is armed for low decel braking 14
AUTOBRAKE MED Autobrake is armed for medium decel braking 14
AUX PRESS ON Auxiliary pressurization on 13
AUX PUMP OFF L (R) Left and/or right auxiliary (DC) pump off 11
BATT BUS MAN OFF Battery bus has been manually isolated 6
COWL A/ICE AUTO L (R) Left/right cowl anti-ice selected AUTO
COWL A/ICE ON L (R) Left and/or right cowl anti-ice selected on 3
CPLT ROLL SPLRS Displayed if the copilot roll spoilers control PBA is selected; the message is accompanied by the illumination of the “CPLT ROLL” legend on the PBA 7
DC BUS 1 (2) MAN OFF DC bus 1/2 has been manually isolated 6
DC ESS BUS MAN OFF DC essential bus has been manually located 6
DITCHING ON Ditching PBA has been pressed and ditching sequence will initiate if below 15,000 ft 13
EGPWS FLAP OVRD
Flight crew member has engaged the flap override PBA which inputs a LANDING FLAPS discrete to the EGPWS, to avoid nuisance alerts issued when landing flaps are required by logic, yet are not deployed due to required aircraft performance
10
EGPWS G/S MUTED Flight crew member has engaged the Glideslope Mute PBA, suppressing the BELOW GLIDESLOPE aural annunciation
7/10/16
EMER LIGHTS ON Emergency lighting selected on 8
ENG BLEED OFF L (R) Left and/or right bleed selected off 13
7-60 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
ENG BLEED ON L (R) Left and/or right bleed selected ON 13
ENG SHUTDOWN L (R) Pilot initiated engine shutdown 17
ENG SOV CLSD L (R) Left and/or right engine shutoff valve closed 17
ENG SOVS CLSD L (R) Left and/or right engine fire handle has been pulled, and the fuel, hydraulic and bleed shutoff valves operated normally 17
EXT AC PWR ON External AC power is ON 6
EXT DC PWR ON DC external power is ON 6
FADEC N1 CTRL L (R) Left and/or right engine is in N1 control due to cockpit selection 17
FUEL RECIRC OFF L (R) Fuel recirculation has been closed (Global 5000 and -9 FMQ GC or later only) 11
FUEL RECIRC ON Fuel recirculation on (not applicable to Global 5000 and -9 FMQ GC or later) 11
GEAR HORN MUTED Pilot has selected gear horn mute 14
GEN 1 (2) (3) (4) OFF Gen 1, 2, 3 and/or 4 is off 6
GLD MANUAL ARM Displayed if “GND LIFT DUMP” MANUAL ARM is selected 10
GND LIFT DUMP OFF Displayed if “GND LIFT DUMP” OFF is selected 10
HIGH PRESS RATE Cabin rate is selected to the HIGH setting 13
HYD PUMP 1B OFF Hydraulic pump 1B selected off 12
HYD PUMP 1B ON Hydraulic pump 1B selected on 12
HYD PUMP 2B OFF Hydraulic pump 2B selected off 12
HYD PUMP 2B ON Hydraulic pump 2B selected on 12
HYD PUMP 3A OFF Hydraulic pump 3A selected off 12
HYD PUMP 3B OFF Hydraulic pump 3B selected off 12
HYD PUMP 3B ON Hydraulic pump 3B selected on 12
HYD SOV CLSD L (R) Indicates that the left and/or right engine hydraulic fire wall shutoff valve (SOV) is closed when the pilot has manually selected it closed 1/8/12
IAC 1-2 AURAL MUTE Aural warning mute selected 7
IGNITION ON L (R)
Left and/or right engine, 2 igniters per engine energized and the IGNITION ON PBA has been selected. The EICAS IGN (green) icon will appear when at least one igniter exciter is energized. The IGNITION ON PBA will light concurrently with L (AND/OR R) IGNITION ON status message
17
IRS 1 (2) (3) IN ATT Annunciated when the indicated IRU is in the attitude mode as a result of manual pilot action 16
LDG ELEV MAN The source of LDG ELEV information selected on MAN (pilot input) 13
MAN PRESS CONTROL Manual pressurization mode is selected 13
OUTFLOW VLV 1 (2) CLSD Fwd/aft outflow valve has been manually selected closed 13
STATUS MESSAGES (WHITE)
CAS MESSAGE DESCRIPTION CH.
For Training Purposes OnlySept 04
7-61
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
PACK HIGH FLOW L (R) Left and/or right pack in high flow mode 13
PACK LOW FLOW L (R) Left and/or right pack in low flow mode 13
PACK MAN TEMP L (R) Left and/or right pack manual selection 13
PACK OFF L (R) Left and/or right pack off 13
PARK/EMER BRAKE ON Park brake is on with aircraft stopped 4/10/1
PLT ROLL SPLRS Displayed if the pilot roll spoilers control PBA is selected; the message is accompanied by the illumination of the “PLT ROLL” legend on the PBA 10
PRI PUMPS OFF L (R) Left and/or right primary (AC) pump off 11
RAM AIR ON Ram air on 13
RAT GEN OFF The RAT is deployed and the RAT Line Connector (LC) is selected off 6
RECIRC FAN OFF Recirculation fan off 13
STAB CH 1 (2) OFFDisplayed if channel 1-2 of the horizontal stabilizer trim is selected OFF via the cockpit panel CH1/CH2 PTRIM OFF PBA; the message is accompanied by the lighting of this PBA
10
TRIM AIR OFF Trim air off 13
WING A/ICE AUTO Wing anti-ice manually selected to AUTO 3
WING A/ICE ON Wing anti-ice manually selected on 3
WING FUEL XFER OFF Wing fuel transfer off 11
WING XBLEED FROM L Wing anti-ice supplied by left bleed 3
WING XBLEED FROM R Wing anti-ice supplied by right bleed 3
WSHLD HEAT OFF L (R) Left windshield temperature controller switch (and/or right windshield temperature controller switch) is at off/reset 3
XBLEED CLOSED Bleed crossfeed closed 13/17
XBLEED OPEN Bleed crossfeed open 13/17
XFEED VALVE OPEN Fuel crossfeed open 11
STATUS MESSAGES (WHITE)
CAS MESSAGE DESCRIPTION CH.
7-62 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
PAGE INTENTIONALLY LEFT BLANK
For Training Purposes OnlySept 04
7-63
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
ELECTRONIC FLIGHT INSTRUMENTSThe flight instruments require pitot-static data, air data, attitude and heading data, and input from various electronic components to provide the following information to the flight crew:
Each Primary Flight Display (PFD) and Multifunction Display (MFD) receives altitude, heading, airspeed and attitude data from the on-side sensors. Flight crew access to display format and display controls is provided via the PFD control panel, located on the glareshield, the reversion control panel and MFD control panel, both located on the pedestal.
• Altitude (barometric/radio) • True Airspeed
• Groundspeed • Temperature Data
• Airspeed (MACH/KIAS) • Airplane Attitude
• Vertical Speed • Navigation Information
• Airspeed & Vertical Speed Trend • Heading Information
MINIMUMSBARO HpaRAD IN
BARO SETNAV SRC
BRG V/L BRGFMS
HSI
Honeywell PUSH STD
AIRSPEED LIMITS - (INDICATING SPEEDS)VSE (SLATS OUT, 0°FLAPS) . . . . . . . . . . . .VFE (SLATS OUT, 6°FLAPS) . . . . . . . . . . . .VFE (SLATS OUT, 16°FLAPS) . . . . . . . . . . .VFE (SLATS OUT, 30°FLAPS) . . . . . . . . . . .VA (MANEUVERING)(AT SEA LEVEL @ 96,000 LB) . . . . . . . . . . .(AT 20,000 FT @ 78,600 LB) . . . . . . . . . . . . .
VMOVMOMMOMMOMMOMMOVLOVLOVLE
(BELOW 8,000 FT) . . . . . . . . . . . . . .(8,000FT TO 30,267 FT) . . . . . . . . . .30,267FT TO 35,000 FT) . . . . . . . . . .(AT 41,000 FT) . . . . . . . . . . . . . . . . .(AT 47,000 FT) . . . . . . . . . . . . . . . .(AT 51,000 FT) . . . . . . . . . . . . . . . .(EXT) (L/G EXTENSION) . . . . . . . . .(RET) (L/G RETREACTION) . . . . . .(L/G EXTENDED) . . . . . . . . . . . . . . .
225210210185
254250
3003400.890.88
0.8580.842
200200250
AIRSPEED LIMITS - (INDICATING SPEEDS)VSE (SLATS OUT, 0°FLAPS) . . . . . . . . . . . .VFE (SLATS OUT, 6°FLAPS) . . . . . . . . . . . .VFE (SLATS OUT, 16°FLAPS) . . . . . . . . . . .VFE (SLATS OUT, 30°FLAPS) . . . . . . . . . . .VA (MANEUVERING)(AT SEA LEVEL @ 96,000 LB) . . . . . . . . . . .(AT 20,000 FT @ 78,600 LB) . . . . . . . . . . . . .
VMOVMOMMOMMOMMOMMOVLOVLOVLE
(BELOW 8,000 FT) . . . . . . . . . . . . . .(8,000FT TO 30,267 FT) . . . . . . . . . .30,267FT TO 35,000 FT) . . . . . . . . . .(AT 41,000 FT) . . . . . . . . . . . . . . . . .(AT 47,000 FT) . . . . . . . . . . . . . . . .(AT 51,000 FT) . . . . . . . . . . . . . . . .(EXT) (L/G EXTENSION) . . . . . . . . .(RET) (L/G RETREACTION) . . . . . .(L/G EXTENDED) . . . . . . . . . . . . . . .
225210210185
254250
3003400.890.88
0.8580.842
200200250
STATIC GROUND OPERATIONPROHIBITED BETWEEN 66-80% N1
20
10
30
20
10
30
09
8
7
65
4
3
2
1100 FEET
ALT
1 00032
4
10 13
mb/hPa
29 9 2
IN HG
IAS KNOTS
220200180 250
BARO
Honeywell HoneywellHoneywell Honeywell
WX
ET
NO BEARINGRA 9 . 8NM +13TA 4 . 5NM -04
SAT
GSPD
TERR
-56
TAT
TAS
-40
234
345
INHIB
LX
00 : 10 0 . 05L
MAG2HDG315
ETE 1+36
12 . 5KDVT
NM
FLBELOW
TCAS TEST
FMS1360
N
5 5
3
6
33
30
- 02
- 02
+ 12- 04
KABC
KKLM
KKLM
TOC
TOC
KGHJ
KGHJ
LUF
KDEF
KDEF
4000 4000
FL180
+ 09
TOTAL FUEL (LBS) 25750
1.021.02
25.425.4
443443
12950 1280000
NDSTAB
NU
RUDDERNL
LWD RWD
NR
AIL
– TRIMS –
6.0
N2
FF (PPH)
OIL TEMP
OIL PRESS
61.46907551
61.46908049
1 . 641 . 64
98.5 98.5
T/OEPR
N1
ITT
GEAR
PARK/EMER BRAKE ONNO TAKEOFF
IGN
START START
IGN
IN
0
DN DN DN
END
Honeywell
13000.00
00
90
13 13
2019 20
22 2220
OXYGEN
AFTCABIN (°C)
FWDCABIN (°C)
CKPT (°C)
OPEN OPEN
OUTFLOW VALVES
CAB ALT
P
CAB RATE
LDG ELEV
00
1 2
1 2
1 2
QTY
ENG
APU
RES
OIL (QTS)
APU DOOR 11.2°
RPM EGT
BRAKE TEMP
11.5
650100
0603 03 03
11.55.26.0
%
% %
Honeywell
9500
29.92
AT1
VTA
M
0.450M
FMS1LOC1DTK
360
HDG330
10400
20
20
10
10
20
20
10
10
9500
10500
300
220
210
200
190
180
170
F3
LE
F1
2160
150
1856
4
N33
30
W24
21S
15
12
E6
3
0
1
2
3
1
2
3
ATT
HDGT
EICAS
GS
LOC
HDG
RAD
IASALT
HDG2
VOR 1
ADF 2
0010020
80
THRUST HDG ASEL ATT 2AP1VAPP VNAV ADC 3
9500
29.92
AT1
VTA
M
0.450M
FMS1LOC1DTK
360
HDG330
10400
20
20
10
10
20
20
10
10
9500
10500
300
220
210
200
190
180
170
F3
LE
F1
2160
150
1856
4
N33
30
W24
21S
15
12
E6
3
0
1
2
3
1
2
3
ATT
HDGT
EICAS
GS
LOC
HDG
RAD
IASALT
HDG2
VOR 1
ADF 2
0010020
80
THRUST HDG ASEL ATT 2AP1VAPP VNAV ADC 3
WX
ET
NO BEARINGRA 9 . 8NM +13TA 4 . 5NM -04
SAT
GSPD
TERR
-56
TAT
TAS
-40
234
345
INHIB
LX
00 : 10 0 . 05L
MAG2HDG315
ETE 1+36
12 . 5KDVT
NM
FLBELOW
TCAS TEST
FMS1360
N
5 5
3
6
33
30
- 02
- 02
+ 12- 04
KABC
KKLM
KKLM
TOC
TOC
KGHJ
KGHJ
LUF
KDEF
KDEF
4000 4000
FL180
+ 09
TCAS MENU
EMER
TERRMAP
PLAN
NAV
APT
NORM ABN
SKP
RCL
PAG
ENT
IRS ADC ADC IRS
SG 3
EICAS
SG 2SG 1
PFD 1
ALTN 3
ALTN
ALTN 1
ALTNALTN
ALTN
NORM
NORM
NORMNORM
NORM
PFD 1 PFD 2
PFD 2
ALTN 2 ALTN NORM
GX
_0
7_
03
6
REVERSION CONTROL PANEL
MFD CONTROL PANEL
Primary Flight Displays
Multifunction Displays
PFD CONTROL PANEL
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
7-64 For Training Purposes OnlySept 04
EFIS NETWORK
MAXTHRUST
IDLEREV
MAX REV
ENGRUN
OFF OFF
RL
SYSTEM SELECT FAULT
ON
FROM TO WPT
WPTLEGCHG
XTKDTK
WDWS
DISTIM
HDGSTS
POSTKGS
1MT2
BRTDIM3 TST
ENTBCK
0 CLR
7 S8
9
W4
5E6
1N2
3
88888
88
8 8888888
PFD CONTROL PANEL NO. 1 PFD CONTROL PANEL NO. 2
REVERSION CONTROL PANEL
GUIDANCE PANEL
TO IAC1, 2, 3
GX
_0
7_
03
7
MFDPANEL NO. 1
CONTROL MFD CONTROLPANEL NO. 2
EICASCONTROLLER
IRS MODESELECTOR
UNIT
NAVIGATIONDISPLAY UNIT
TO IRU 1, 2, 3
THROTTLE QUADRANTASSEMBLY
YAW DAMPERS
DUALSERVOS
DAU 1 DAU 2 DAU 3 DAU 4 ADC 3
ADC 1 ADC 2
IRU 2IAC 2
IAC 1IRU 1
IRU 3
EGPWS
IAC 3
AILERON ELEVATOR
1 2
WX RADARCONTROLLER 2
WX RADARCONTROLLER 1 RX/TX
ANTENNA
SYSTEMSAND
SENSORS
SYSTEMSAND
SENSORS
Honeywell
WX
ET
NO BEARINGRA 9 . 8NM +13TA 4 . 5NM -04
SAT
GSPD
TERR
-56
TAT
TAS
-40
234
345
INHIB
LX
00 : 10 0 . 05L
MAG2HDG315
ETE 1+36
12 . 5KDVT
NM
FLBELOW
TCAS TEST
FMS1360
N
5 5
3
6
33
30
- 02
- 02
+ 12- 04
KABC
KKLM
KKLM
TOC
TOC
KGHJ
KGHJ
LUF
KDEF
KDEF
4000 4000
FL180
+ 09
Honeywell
TOTAL FUEL (LBS) 25750
1.021.02
25.425.4
443443
12950 1280000
NDSTAB
NU
RUDDERNL
LWD RWD
NR
AIL
– TRIMS –
6.0
N2
FF (PPH)
OIL TEMP
OIL PRESS
61.4690
7551
61.4690
8049
1 . 641 . 64
98.5 98.5
T/OEPR
N1
ITT
GEAR
PARK/EMER BRAKE ONNO TAKEOFF
IGN
START START
IGN
IN
0
DN DN DN
END
Honeywell
13000.00
00
90
13 13
2019 20
22 2220
OXYGEN
AFTCABIN (°C)
FWDCABIN (°C)
CKPT (°C)
OPEN OPEN
OUTFLOW VALVES
CAB ALT
P
CAB RATE
LDG ELEV
00
1 2
1 2
1 2
QTY
ENG
APU
RES
OIL (QTS)
APU DOOR 11.2°
RPM EGT
BRAKE TEMP
11.5
650100
0603 03 03
11.55.26.0
%
% %
Honeywell
9500
29.92
AT1
VTA
M
0.450M
FMS1LOC1DTK
360
HDG330
10400
20
20
10
10
20
20
10
10
9500
10500
300
220
210
200
190
180
170
F3
LE
F1
2160
150
1856
4
N33
30
W24
21S
1512
E6
3
0
1
2
3
1
2
3
ATT
HDGT
EICAS
GS
LOC
HDG
RAD
IASALT
HDG2
VOR 1
ADF 2
0010020
80
THRUST HDG ASEL ATT 2AP1VAPP VNAV ADC 3
Honeywell
9500
29.92
AT1
VTA
M
0.450M
FMS1LOC1DTK
360
HDG330
10400
20
20
10
10
20
20
10
10
9500
10500
300
220
210
200
190
180
170
F3
LE
F1
2160
150
1856
4
N33
30
W24
21S
15
12
E6
3
0
1
2
3
1
2
3
ATT
HDGT
EICAS
GS
LOC
HDG
RAD
IASALT
HDG2
VOR 1
ADF 2
0010020
80
THRUST HDG ASEL ATT 2AP1VAPP VNAV ADC 3
Honeywell
WX
ET
NO BEARINGRA 9 . 8NM +13TA 4 . 5NM -04
SAT
GSPD
TERR
-56
TAT
TAS
-40
234
345
INHIB
LX
00 : 10 0 . 05L
MAG2HDG315
ETE 1+36
12 . 5KDVT
NM
FLBELOW
TCAS TEST
FMS1360
N
5 5
3
6
33
30
- 02
- 02
+ 12- 04
KABC
KKLM
KKLM
TOC
TOC
KGHJ
KGHJ
LUF
KDEF
KDEF
4000 4000
FL180
+ 09
TCAS MENU
EMER
TERRMAP
PLAN
NAV
APT
NORM ABN
SKP
RCL
PAG
ENT
IRS ADC ADC IRS
SG 3
EICAS
SG 2SG 1
PFD 1
ALTN 3
ALTN
ALTN 1
ALTNALTN
ALTN
NORM
NORM
NORMNORM
NORM
PFD 1 PFD 2
PFD 2
ALTN 2 ALTN NORM
SPD MANFMSCRS 1 CRS 2
PUSH DCT PUSH DCT
ALTHDG
DN
UP
P
I
T
C
H
Honeywell
FD FDAP
CPL
YD
FLC NAV BANKHDG VNAV ALT
APR VS
BC
PUSH CHG PUSH SYNC
RADAR LSS TILTTST
FP
GMAP CLRTST
SBY OFFRCT LXWX SBY
PULLACT
+
–GAIN
MIN MAX
PULLVAR
TRB STAB TGT SECT
OFF
RADAR LSS TILTTST
FP
GMAP CLRTST
SBY OFFRCT LXWX SBY
PULLACT
+
–GAIN
MIN MAX
PULLVAR
TRB STAB TGT SECT
OFF
TCAS MENU
EMER
TERRMAP
PLAN
NAV
APT
NORM ABN
SKP
RCL
PAG
ENT
FMS 1 FMS 2
STAT
HYDAC
ELECBLEED
AIRCOND
DCELEC
FUELFLT
CTRL
SCROLL
EICAS
SYSTEMS SELECT
NORMMFD 2MFD 1
IRS 3IRS 1 IRS 2
NAVNAV NAVALNALN ALN
OFFOFF OFF
ATTATT ATT
MINIMUMSBARO HpaRAD IN
BARO SETNAV SRC
BRG V/L BRGFMS
HSI
Honeywell PUSH STD
MINIMUMSBARO HpaRAD IN
BARO SETNAV SRC
BRG V/L BRGFMS
HSI
Honeywell PUSH STD
For Training Purposes OnlySept 04
7-65
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
DESCRIPTION
PITOT-STATIC SYSTEMThree pitot-static (PS) systems designated PS1, PS2, and PS3 and a standby PS source are provided to supply variable pressure inputs to the 3 Air Data Computers (ADC), the standby instruments and to the Mach transducer. Use and distribution of these pitot-static probes is as follows (refer to “Pitot-Static Schematic” on page 7-66):
Three Total Air Temperature (TAT) probes are provided to supply temperature input to the ADCs. Ice protection is provided by electric heating elements for the PS probes and TAT probes. Please refer to Chapter 3, ANTI-ICE SYSTEMS.
PRESSURE SOURCE FROM TO
P1 Pitot/Static Probe No. 1 MADC No. 1
P2 Pitot/Static Probe No. 2 MADC No. 2
P3 Pitot/Static Probe No. 3 MADC No. 3
Ps Standby Pitot/Static Probe Standby Instruments / Mach Transducer
S1/S2 Pitot/Static Probe No. 1 and Standby MADC No. 1
S1/S2 Pitot/Static Probe No. 2 and No. 3 MADC No. 2
S1/S2 Pitot/Static Probe No. 3 and No. 2 MADC No. 3
S1/S2 Standby Pitot/Static Probe and No. 1 Standby Instruments / Mach Transducer
TOPVIEW
PS 3 PS 2
PS 1 PSStandby
TAT 2
PS2TAT 3
TAT 3
PSStandby
ENGINE INLET
TAT 1/2Probe
PS3
PS1 TAT1
GX
_0
7_
03
8
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
7-66 For Training Purposes OnlySept 04
PITOT-STATIC SCHEMATIC
GX
_07_039
p
p p
s2
s2 s2
s1
s1
p
s2s1
s1
MADCNO. 1
MADCNO. 3
MACHTRANSDUCERVALVE
P3LOWERLEFT
P1UPPERLEFT
P2LOWER
RIGHT
P/SSTDBYUPPERRIGHT
MADCNO. 2
STANDBY ALTIMETER /AIRSPEED INDICATOR
MACHTRANSDUCER
LOWERMANIFOLD
UPPERMANIFOLD
DRAINS DRAINS
DRAINS
DRAINS
S IN
SOUT
P IN
POUT
P
P
P
P
SS
S
S
P3
P1
P2
P/S
DRAINS DRAINS
09
8
7
65
4
3
2
1100 FEET
ALT
1 00032
4
10 13
mb/hPa
29 9 2
IN HG
IAS KNOTS
220200180 250
BARO
MACH TRANSDUCERRANSD
PITOT
CLOSED
STATIC
CLOSED
For Training Purposes OnlySept 04
7-67
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
AIR DATA SYSTEMThe air data system provides computed air data (speed, altitude and temperature data) to various systems:
• Integrated Avionics Computers (IAC)• Data Acquisition Units (DAU)• Inertial Reference System (IRS)• Stall Protection Computer (SPC)• Electronic Display System (EDS) – EFIS and EICAS• Automatic Flight Control System (AFCS)
Pitot and static pneumatic inputs and total air temperature provide raw air data information to the ADCs. Static input to each ADCs absolute sensors produces the altitude sensor data. Static and pitot inputs to each ADCs differential sensor produces the airspeed sensor data.
Each ADC computes the following:
• Pressure altitude and barometric-corrected altitude• Vertical speed, indicated airspeed, Mach number and true airspeed (TAS)• Static Air Temperature (SAT), Total Air Temperature (TAT), and temperature
variations from ISA• IAS reference (SPD switch on guidance panel, FMS or manual input)• Vertical speed reference (VS switch on guidance panel)• Attitude reference• Airspeed and altitude trend vector• Alerts• Static source error correction• Maximum speed values• Overspeed warning
The reversion control panel, located on the pedestal, is used for pilot input to the air data system and was covered earlier in this chapter.
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
7-68 For Training Purposes OnlySept 04
PRIMARY FLIGHT INSTRUMENTSPFD 1 and PFD 2 are digital CRT-based versions of the traditional (analog/ mechanical) flight instruments. Input to the PFDs is derived from the ADCs and IRS units selected, and commands set on the PFD control panel, and the MFD control panel. The PFDs function as the following flight instruments:
• Attitude Director Indicator (ADI)• Horizontal Situation Indicator (HSI)• Radio Magnetic Indicator (RMI)• Attitude Indication• Radio Altimeter Indicator• Airspeed Indicator (Mach and IAS)• Vertical Speed Indicator (VSI)
The mode annunciator panel for flight director and autopilot is above the ADI display, directly on the PFD. Messages and cues for windshear alerts, TCAS traffic alerts and commands are also provided on the ADI.
For Training Purposes OnlySept 04
7-69
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
PRIMARY FLIGHT DISPLAY
220
200
190
180
170
160
150
LIM HDG
9500
210 29.92 INBARO
ASELAP1
AT1
VTA
SPD VAPP VNAV
M
0.856M
DTK360
HDG330
SRP
1000
VS 1000
54
MSG 0
1
2
3
1
2
3
9500
10500
10000
VOR 1VOR 2
ATT2ADC1
20 20
10 10
10 10
20 20
20
1300
200
1856
4
10400
20008060
95
N33
30
W24
21S
15
12
E6
3
H23.4NMFMS1
GX
_0
7_
04
2
NavigationAnnunciation
AirspeedIndication
AutothrottleAnnunciation
Flight Director/AutopilotMode Annunciations
SourceAnnunciation
AltitudeIndication
BARO Set
Vertical SpeedTarget Readout
Compass
Vertical SpeedIndication
Honeywell
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
7-70 For Training Purposes OnlySept 04
PRIMARY FLIGHT DISPLAY (Cont)
220
200
190
180
170
160
150
LIM HDG
29.92 IN
ASELAP1SPD VAPP VNAV
0.856M
CRS360
HDG330
1000
VS 1000
MSG 0
1
2
3
1
2
3
9500
10500
10000
VOR 1VOR 2
ATT2ADC1
20 20
10 10
10 10
20 20
20
1300
200
1856
4
10400
20008060
95
N33
30
W24
21S
1512
E6
3
LOC1
Attitude DirectorIndicator (ADI)
Flight DirectorCommand Bars
LubberLine
Bearing 2Pointer
Course Select/DesiredTrack Pointer
Bearing 1 PointerHeadingSelect Display
Bearing 2Annunciation
Bearing 1Annunciation
FMSAnnunciation
CourseSelectReadout
NavigationSource
GX
_0
7_
04
3
For Training Purposes OnlySept 04
7-71
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
AIRSPEED TAPEIndicated airspeed is derived from the selected ADC. An airspeed tape capable of displaying from 30 to 900 knots (inclusive) and an airspeed trend vector are displayed on both PFDs.
The airspeed tape will display a range of ± 40 knots from current airspeed. The tape is labeled every 10 knots below 200 knots and every 20 knots above 200 knots. A VMO thermometer will appear for an overspeed condition and a low speed thermometer will appear for a low speed condition. When IAS equals or exceeds VMO or less than calculated stall warning speed, the digits turn red.
Airspeed Trend VectorAirspeed trend vector represents the airspeed the airplane will attain in 10 seconds, if current acceleration is maintained. Maximum movement of the vector is 30 knots from current airspeed. When the vector exceeds VMO or less than calculated stall speed, by 1 knot, the digits turn amber.
Selected Airspeed Reference DisplaySelected airspeed is always displayed. The readout can be displayed in knots (1 knot increments) or Mach (0.01 Mach increments). Pushing the SPD PUSH CHG button inner knob will toggle the speed reference from IAS to MACH or vice versa.
The Electronic Flight Instruments System (EFIS) automatically switches the speed reference from IAS to MACH at the altitude of 32,600 feet when climbing. If MACH is switched back to IAS after climbing above 32,600 feet, the manual speed will remain the last selected. The EFIS will also switch the speed reference from MACH to IAS at the altitude of less than 32,400 feet when descending. If IAS is switched back
220
200
190
180
170
160
150
1856
4
GX
_0
7_
04
4
AirspeedTape
AirspeedRolling Digits
320
300
280285
6
4320
1
990
1109
130
120
110
100
90
1256
4
VMO Thermometer
VMOEXCEEDENCE
Low speedThermometer
STALLEXCEEDENCE
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
7-72 For Training Purposes OnlySept 04
to MACH after descending below 32,400 feet, the manual speed will remain the last selected.
Rotating the SPD PUSH CHG button outer knob sets IAS. The readout reflects the position of the IAS/MACH target bug on both PFDs. MACH is displayed at ≥ 0.450 M and is removed when ≤ 0.400 M.
Airspeed Reference BugThe active speed bug (“bucket” shaped) is positioned on the inside of the speed tape. The standby speed bug (triangular shaped) is positioned on the outside of the speed tape. The color convention for both bugs is: cyan = MAN, magenta = FMS. The standby bug always shows the current speed of the nonselected SPD mode (i.e., shows the FMS speed when MAN is the current SPD mode, and vice versa). The MAN speed button may be used to change the value of the MAN speed bug, even when FMS is the selected SPD mode. However, the PUSH CHG to swap from IAS to Mach, or Mach to IAS, only functions when MAN is the active SPD mode. These features allow monitoring the current value of the standby speed bug prior to making that speed bug the active speed bug.
SPD MANFMS
FLC
PUSH CHG
SPD MANFMS
FLC
PUSH CHG
220
200
190
180
170
160
150
1856
4
GX
_0
7_
04
5
0.88
0.86M
GUIDANCEPANEL
220
200
190
180
170
160
150
1856
4
210
Selected AirspeedReference Display
Selected AirspeedReference Bug
Airspeed TrendVector
MANFMS GUIDANCEPANEL
320
300
280285
6
4
140
130
120
110
100
1256
4
SelectedMach DigitalReadout
PreselectedFMS AirspeedBug
Actual MachReadout
StallExceedenceForecast
VMOExceedenceForecast
For Training Purposes OnlySept 04
7-73
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
Takeoff V-SpeedsV-speeds are displayed on the speed tape. Digital V-speeds are displayed on the bottom of the speed tape and V-speed bugs are displayed on the outside of the speed tape. V speeds are selected through the FMS, automatically or manually.
180
170
160
150
140
130
120
110
1456
4
100
90
80
60
50
40
701
9
GX
_0
7_
04
6
180
1
60
50
40
301
9
NOTE:Digital readout will scroll outof view as airplane acceleratesand will disappear when speedtape comes alive.
T
2
R
1
Speed Bugs(cyan if manual)
164
133
125
115
T
2
R
1
Digital Readout(cyan if manual)
NOTE:Speed bugs willdisappear when airplanespeed exceeds VFTO +10 kts and at an altitudegreater than 1500 ft AGL.
164
133
125
115
T
2
R
1
R
2
T
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
7-74 For Training Purposes OnlySept 04
Flap/Slat/Gear Extension Speed BugsThe flap/slat/gear extension speed bugs will appear anytime the airplane is 18,000 feet and below or anytime that the landing gear is extended, the flaps are selected out of 0 degrees and/or slats are out.
ALTITUDE TAPEAn altitude tape capable of displaying altitudes between - 980 and 65,000 feet (incl.) and the current barometric altitude ± 550 feet. The altitude tape is labeled at every 500 feet and has a double-lined chevron at each 1000-foot altitude and a single-lined chevron at each 500 feet. A boxed-barberpole symbol will appear if the digital readout is < 10,000 feet. A minus sign will appear when a negative altitude is displayed.
GX
_0
7_
04
7
240
240
220
200
190
180
2156
4
SO SO Slats Extended / Flaps 0° - 225 knots.
F F Flaps Extended 6°/16° - 210 knots.
LO LO Landing Gear in Operation - 200 knots.
F3 F3 Flaps Extended 30° - 185 knots.
950080
20
-020020
80
GX
_0
7_
04
8
9500
10500
AltitudeTape
500 feet
1000 feet
Below10,000 feet
NegativeAltitude
1000080
20
10000
For Training Purposes OnlySept 04
7-75
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
Altitude Trend VectorAltitude trend vector information is derived from the selected ADC. It will indicate what the altitude of the airplane will be in 6 consecutive seconds, based on current vertical speed.
Selected Altitude ReadoutThe readout reflects the position of the altitude reference bug on both PFDs, with a range of 0 to 51,000 feet. The readout can be displayed in metric, with a range of 0 to 15,500 meters, using the MENU display selection on the MFD control panel, located on the pedestal.
Selected Altitude BugThe altitude bug is set using the ALT knob on the guidance panel. The bug will park at the appropriate end of the altitude tape when off scale. At this position, one half of the bug will be in view.
ALT
TCAS MENU
EMER
TERRMAP
PLAN
NAV
APT
NORM ABN
SKP
RCL
PAG
ENT
3000M
0080
20
1050010500
GX
_0
7_
04
9
SelectedAltitude Bug
AltitudeTrendVector
SelectedAltitudeReadout
AltitudeRollingDigits
GUIDANCE PANEL
MFD MENU
MFD CONTROL PANEL
SELECTED ALTITUDE READOUT - METRIC
DIST/TIMEIDENTSVERT PROFILEMETRIC ALTFLIGHT DIR
WYPTONONONSC
DESTOFFOFFOFF
CP
DISPLAY 1/2
0080
20
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
7-76 For Training Purposes OnlySept 04
RADIO ALTITUDERadio altitude is displayed on the bottom of the attitude indicator. The radio altitude readout range is from 0 feet to 2550 feet and is displayed as follows:
• 5-foot increments - Altitude less than 200 feet• 10-foot increments - Altitude ≥ 200 feet but < 1500 feet• 50-foot increments - Altitude ≥ 1500 feet
Radio Altitude Low Altitude AwarenessLow altitude awareness is displayed as an indication of the ground with respect to current barometric altitude. Low altitude awareness is displayed when radio altitude is between 0 and 550 feet.
29.92 IN
20
1010
20
29.92 IN
20
1010
200
29.92 IN GX
_0
7_
05
0
Radio AltitudeReadout 300 feet
Radio AltitudeReadout 0 feet
Low AltitudeAwareness 300 feet
Low AltitudeAwareness 0 feet
Low AltitudeAwareness - 300 feet
100080
20
70080
20
- 30 0020
80
300
For Training Purposes OnlySept 04
7-77
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
ATTITUDE DIRECTOR INDICATOR (ADI)The ADI provides pitch, roll and roll pointer (slip/skid) information.
10 10
10 10
15°
5°2.5°
VERTICAL TAPE
20 20
10 10
10 10
20 20
20
40
3030
3030
45
60
60
90
90
20 20
10 10
10 10
20 20
20
0° 10° 20° 30°
45°
60°
ATTITUDE INDICATOR
ADVERSE YAW INDICATIONS
ROLL POINTER
GX
_0
7_
05
1
ROLL SCALE
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
7-78 For Training Purposes OnlySept 04
Flight Director Command BarsThe Flight Director command bars can be displayed in Single Cue (SC) airplane symbol or Cross Pointer (CP) airplane symbol. Selections are made on the MFD control panel, located on the pedestal, using the MENU button. If pitch or roll command is invalid, the flight director command bars are removed.
DESIRED ATTITUDE
TCAS MENU
EMER
TERRMAP
PLAN
NAV
APT
NORM ABN
SKP
RCL
PAG
ENT
20 20
10 10
10 10
20 20
20
20 20
10 10
10 10
20 20
20
DISPLAY
DIST/TIMEIDENTSVERT PROFILEMETRIC ALTFLIGHT DIR
WYPTONONONSC
DESTOFFOFFOFF
CP
1/2
MFD CONTROL PANEL
MFD MENU
PITCH DOWN COMMAND PITCH UP COMMAND
ROLL LEFT COMMAND
SINGLE CUE
DISPLAY
DIST/TIMEIDENTSVERT PROFILEMETRIC ALTFLIGHT DIR
WYPTONONONCP
DESTOFFOFFOFF
SC
1/2
MFD MENU
CROSS POINTER
DESIRED ATTITUDE
PITCH UP COMMAND PITCH DOWN COMMAND
GX
_0
7_
05
2
ROLL RIGHT COMMAND
ROLL RIGHT COMMANDROLL LEFT COMMAND
For Training Purposes OnlySept 04
7-79
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
Attitude DeclutterAn excessive attitude occurs when roll is greater than 65°, or when pitch is greater than 30° or less than - 20°. When there is excessive pitch, red chevrons will appear, directing the pilot to follow the direction of the chevron. When there is an excessive attitude, the following symbology will be removed:
• Autopilot Flight Director Mode Annunciations Autopilot• HSI Select Arrow• Low Bank Limit Arc• Autopilot Flight Director Command Bars• Vertical deviation Scale/Pointer Annunciator• Marker Beacons• Airspeed Reference Bug/Readout• Airspeed VNAV Speed Bug• Airspeed V Speed Bugs/Readout• Radio Altitude Readout• Decision Height Readout• Minimum descent Altitude Readout/Bug• Selected Altitude Readout/Bug• Altitude VNAV Target Readout/Bug• All failure flags for the items listed above• The following comparators: HDG, RAD, LOC, AZ, GS, GP, EICAS
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
7-80 For Training Purposes OnlySept 04
NOTEThe symbology will be restored when:
1. Roll is 63 degrees or less
2. Pitch is between 28 and - 18° (inclusive)
10 10
20 20
3030
45
20 20
10 10
20
40
3030
60
10
10
20
20
20 20
10 10
10 10
20 20
20
40
3030
3030
45
60
60
90
90
20
20
10
10
10
10
20
20
20
GX
_0
7_
05
3
For Training Purposes OnlySept 04
7-81
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
VERTICAL SPEED INDICATOR (VSI)
GX
_0
7_
05
4
-15000
1
2
3
1
2
3
0
1
2
1
10000
1
2
3
1
2
3
Vertical Speed ScaleTick marks are placed at the following: 0, ±1000, ± 2000 and ± 3000 fpm• At vertical speeds in excess of ± 3600 fpm,the pointer will park at ± 3600 fpm.• Only one half of the arrowhead and one halfof the target bug will be in view.
40000
1
2
3
1
VERTICAL SPEED READOUTThe vertical speed readout has a range of ±9999 fpm.• For vertical speeds less than ± 1000 fpminformation is rounded to the nearest50 fpm.• For vertical speeds more than± 1000 fpm information is rounded to thenearest 100 fpm.• The digital readout and box is removed forvertical speeds less than or equal to± 500 fpm, and enabled for vertical speedsgreater than or equal to ± 600 fpm.
Vertical Speed Target BugDisplayed when flight director VS mode orFMS VPTH mode active. The bug is cyanin VS mode or magenta in VPTH mode.• When vertical speed target is within rangeof ± 1000 fpm it is rounded to the nearest50 fpm.• For vertical speed target is greater than orequal to ± 1000 fpm information is roundedto the nearest 100 fpm.
VerticalSpeedPointer
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
7-82 For Training Purposes OnlySept 04
PFD CONTROL PANELThe PFD control panels (2) are located on the glareshield. Both the pilot’s and copilot’s control panels are identical but have separate on-side functions. The PFD control panel is used for selection of bearing pointers, VOR/LOC source, FMS source, setting of minimums and barometric settings and compass display format.
MINIMUMSBARO HpaRAD IN
BARO SETNAV SRC
BRG V/L BRGFMS
HSI
Honeywell PUSH STD
GX
_0
7_
05
5
BRG ButtonUsed to select bearingsources, VOR 1, ADF 1,FMS 1 (FMS 3 if installed).
V/L ButtonUsed to select VOR or LOCas a primary NAV source.
FMS ButtonUsed to select FMS 1, FMS 2 orFMS 3 (if installed) source or, FMS 1,FMS 2 or LTRK (if installed).
BRG BUTTONUsed to select bearingsources, VOR 2, ADF 2,FMS 2. (FMS 3 if installed)
MINIMUMS KnobRAD
BARO
– Used for CAT2approaches.
– Sets the MinimumDescent Altitude (MDA) orDecision Height (DH) valueon PFD in MSL.
HSI ButtonUsed to select full orpartial compass display.
BARO SET KnobPUSH STD – When pushed will eitherdisplay 29.92 (in)hg or 1013 (HPa).
For Training Purposes OnlySept 04
7-83
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
The following describes the operation of the MINIMUMS knob, the BARO SET knob and the HSI button.
MINIMUMS KNOB
20 20
10 10
10 10
20 20
20
HDG ASELGS
AP1LOC200
500
1500220
200
190
180
170
160
150
1856
41000
80
20
F
LO
F3
1400
20 20
10 10
10 10
20 20
20
HDG ASELGS
AP1LOC200
500
1500220
200
190
180
170
160
150
1856
41000
80
20
F
LO
F3
1400
MINIMUMS KnobRAD
BARO
– Used for CAT2approaches.
– Sets the MinimumDescent Altitude (MDA) ordecision height (DH) value onPFD in MSL.
BARORAD
BARORAD
MINIMUMSBARORAD
MINIMUMS
MINIMUMS
GX
_0
7_
05
6
29.92 IN500 RAD
29.92 IN210 BARO
MINIMUMS InnerKnobSlow rotation of inner knoballows for precise setting of data(1 “click” of knob = 10 feet).Rapid rotation of inner knobwill change the data at a fasterrate (1 “click” of knob = 100 feet).
RADValue set from 10 to 2500 feet.
BAROValue set from 10 to 16000 feet.
MDA BugOnly in view when within theends of the altitude tape.
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
7-84 For Training Purposes OnlySept 04
PFD (HSI)
HSI
GX
_0
7_
05
7
HDG
29.92 IN
ASELAP1LOC VPTH
LOC1
CRS360
HDG360
1000
VS 1000
200 10400
9500
10500220
200
190
180
170
160
150
1856
4
0
1
2
3
1
2
3
20 20
10 10
10 10
20 20
20
HDG
29.92 IN
ASELAP1VPTH
1000
VS 1000
200 10400
9500
10500220
200
190
180
170
160
150
1856
4
FMS360
CRS360
HDG330
N33 3
0
1
2
3
1
2
3
HSI ButtonUsed to select full or arc (partial compass)display. Selecting HSI button will display arc(partial compass). Selecting HSI buttonagain, will display full compass.
PFD (HSI)
360CRS120
HDG240
N33 3
Heading Bug Arrow Course Pointer Arrow
Note:If heading bug or course select pointer areout of view, an arrow will be displayed,indicating the shortest direction to the bugor pointer. When the bug or pointer comesback into view, the applicable arrow willdisappear.
20 20
10 10
10 10
20 20
20
1000080
20
1000080
20
LNAV
N33
30
W24
21S
15
12
E6
3
For Training Purposes OnlySept 04
7-85
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
BARO SET KNOB
BARO SET
PUSH STD
HpaIN
BARO SET
PUSH STD
HpaIN
HpaINBARO SET
PUSH STD
HDG
29.92 IN
ASELAP1LOC VPTH
LOC1VS 1000
200 10400
9500
10500220
200
190
180
170
160
150
1856
4
N 3
20 20
10 10
10 10
20 20
20
1000080
20
HDG
1013 HPA
ASELAP1LOC VPTH
LOC1VS 1000
200 10400
9500
10500220
200
190
180
170
160
150
1856
4
3
20 20
10 10
10 10
20 20
20
1000080
20
GX
_0
7_
05
8
INInches of mercury display rangefrom 15.00 to 32.77 IN inclusive.
HPAHPa display range from 50to 204.7 HPa inclusive.
BARO SET KnobIN
HPa
– Sets the altimeterfor inches of mercury.
– Sets thealtimeter for
PUSH STD - When pushedwill either display 29.92 (in)/hgor 1013 (HPa).
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
7-86 For Training Purposes OnlySept 04
MULTIFUNCTION DISPLAY (MFD)MFD1 and MFD2 function as an electronic version of an HSI/RMI, and display weather radar information, terrain map and TCAS traffic resolution advisories. The MFD can either be displayed in MAP format or PLAN format, using the MFD control panel.
MAP FORMAT
GX
_0
7_
05
9
WX
T5.0
G85%
LX
STAB
SAT
GSPD
TERR INHIB
-56
TAT
TAS
-40
234
345
38
0 . 05L
HDG315
ETE1+36
12 . 5DVTNM
FMS1360
N
50 50
3
6
33
30
KLAX
PHX
KPHX
TOC
TOC
KSRP
LUF
DVT
KDVT
4000 4000
FL180
SelectedHeading
Drift Bug Heading
Heading Scale120° Arc
60° or 30° TickMarks
WX SelectedSector
Distance
Waypoint Ident
Estimated TimeEn-Route
SelectedHeading
Bug
LateralDeviationReadout
VerticalProfile
WX SAT -56
TAT -40
TAS 234GSPD 345
TERR FAILLX
ETE1+36
12 . 5DVT
NM
Pop-Up WindowDisplay area
WX Mode &Status
Annunciation
LightningAnnunciation
LightningSRP
For Training Purposes OnlySept 04
7-87
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
PLAN FORMAT
GX
_0
7_
06
0
WX SAT -56
TAT -40
TAS 234GSPD 345
TERR FAILLX
ETE1+36
12 . 5DVT
NM
Pop-Up WindowDisplay area
FMS1TRU
N
LAX
PHX
TOC
SRP
LAXLUF
DVT
SAT
GSPD
TERR INHIB
-56
TATTAS
-40234
345
0 . 05L ETE1+36
12 . 5DVTNM
PHXTOC
SRPDVT
4000 4000
FL180
Static and TotalAir Temperature
True Airspeed andGroundspeed
VerticalProfile
True NorthIndication
NAV SourceAnnunciation
Range Ring• 5 NM• 10 NM• 25 NM• 50 NM• 100 NM• 200 NM• 300 NM• 500 NM• 1000 NM
Terrain Mode &Status Annunciation
NOTE:Range rings for MAP orPLAN formats are identical.
g3
1-6
1-0
18
.cd
r_N
C
100 100
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
7-88 For Training Purposes OnlySept 04
MFD CONTROL PANELThe MFD control panels (2) are located on the pedestal. Both the pilot’s and copilot’s control panels are identical but have separate on-side functions. The MFD control panel is used to display TCAS, display a multifunction pop-up menu, display terrain awareness, display NAV Aids and airport symbology and checklist control/display functions.
TCAS MENU
EMER
TERRMAP
PLAN
NAV
APT
NORM ABN
SKP
RCL
PAG
ENT
GX
_0
7_
06
1TCAS ButtonUsed to displayTCAS format
NORM ButtonUsed to displaynormal checklist.
ABN ButtonUsed to displayabnormal checklist.
ENT ButtonMomentary actionused to enter aselected item.
EMER ButtonUsed to displayemergencychecklist.
RCL ButtonMomentary actionused to move backone line.
SKP ButtonMomentary actionused to skip a line.
MAP/PLAN ButtonUsed to select eitherMAP format or PLANformat
MENU ButtonUsed to displaypop-up menu
NAV / APT KeyUsed to displayNAV AIDS, AIRPORTSor both
PAG ButtonMomentary actionused to enter aselected item
TERR ButtonUsed to enableterrain display
UP/DOWN ButtonUsed to range control.
JOYSTICKMomentary action.
PageForward
PageBackward
Skip Up
Skip Down
will increase range
will decrease range
For Training Purposes OnlySept 04
7-89
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
The following describes the function of the buttons on the MFD control panel:
TRAFFIC COLLISION AVOIDANCE SYSTEM (TCAS) BUTTON
TUNE
SQ
ID
DIM
PGE
1/2
TST
STO
DME
COM 1 NAV 1
TCAS DSPY 1
ATC-TCAS
HF 1
ADF 1
RANGE: 6 15423
15600LV
ADF1 TA/RA
MEMORY-1 MEMORY-1
NORMAL
121.82
118.02
1200
117.45
110.00
1799.5
TCAS MENU
EMER
TERRMAP
PLAN
NAV
APT
NORM ABN
SKP
RCL
PAG
ENT
GX
_0
7_
06
2
The button sequence is as follows:OFF – TCAS (Zoom window) – TCAS (MAPformat) – TCAS (Zoom window) – OFF
1. Selecting TCAS button, will display TCAS ZoomWindow at the last selected range.
2. To increase or decrease TCAS range in the zoomwindow, use the line selected key and tuning knob onthe RMU. When in overlay mode use the arrowbuttons on the control panel.
SAT
GSPD
TERR INHIB
-56TATTAS
-40234345
ETE 1+36
12 . 5DVT
NM
W X
T 5 . 0 6- 02
- 04 + 12
HDG315
FMS1360
N
50 50
3
6
33
30
LAX
PHX
TOC
LUF
DVT
SRP
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
7-90 For Training Purposes OnlySept 04
MAP/PLAN BUTTON
NOTEFor more information, refer to Chapter 16, NAVIGATION.
TCAS MENU
EMER
TERRMAP
PLAN
NAV
APT
NORM ABN
SKP
RCL
PAG
ENT
TCAS MENU
EMER
TERRMAP
PLAN
NAV
APT
NORM ABN
SKP
RCL
PAG
ENT
GX
_0
7_
06
3
1. Selecting MAP/PLAN button, will displayMAP or PLAN format in sequence.
WX SAT
GSPD
TERR INHIB
-56
TAT
TAS
-40
234
345
0 . 05L
HDG315
ETE1+36
12 . 5DVT
NM
FMS1360
N
50 50
3
6
33
30
PHX
PHX
TOC
TOC
SRP
LUF
DVT
DVT
4000 4000
FL180
MAP Format
FMS1TRU
N
LAX
PHX
TOC
SRP
LAXLUF
DVT
SAT
GSPD
TERR INHIB
-56
TATTAS
-40234
345
0 . 05L ETE1+36
12 . 5DVTNM
PHXTOC
SRPDVT
4000 4000
FL180
PLAN Format
SRP
2. To increase or decrease MAP format orPLAN format use up or down button.
100 100
For Training Purposes OnlySept 04
7-91
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
MENU BUTTON
WX SAT
GSPD
-56
TAT
TAS
-40
234
345
HDG315
ETE1+36
12 . 5DVT
NM
FMS1360
N
50 50
3
6
33
30
PHX
TOC
LUF
DVT
SRP
TCAS MENU
EMER
TERRMAP
PLAN
NAV
APT
NORM ABN
SKP
RCL
PAG
ENT
TCAS MENU
EMER
TERRMAP
PLAN
NAV
APT
NORM ABN
SKP
RCL
PAG
ENT
GX
_0
7_
06
4
1. Selecting MENU will display pop-up menu.DISPLAY 1/3 on Ground (Display 1/2 in Air).First line of text will be inside of box (default).
DIST/TIME
IDENTS
VERT PROFILE
METRIC ALT
FLIGHT DIR
WYPT
ON
ON
ON
SC
DEST
OFF
OFF
OFF
CP
DISPLAY 1/2
WX SAT
GSPD
-56
TAT
TAS
-40
234
345
HDG315
ETE1+36
12 . 5DVT
NM
FMS1360
N
50 50
3
6
33
30
PHX
TOC
LUF
DVT
DIST/TIME
IDENTS
VERT PROFILE
METRIC ALT
FLIGHT DIR
WYPT
ON
ON
ON
SC
DEST
OFF
OFF
OFF
CP
DISPLAY 1/2
SRP
2. Pull down on joystick to select next line.Line that is selected is inside box.
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
7-92 For Training Purposes OnlySept 04
MENU BUTTON (Cont)
TCAS MENU
EMER
TERRMAP
PLAN
NAV
APT
NORM ABN
SKP
RCL
PAG
ENT
TCAS MENU
EMER
TERRMAP
PLAN
NAV
APT
NORM ABN
SKP
RCL
PAG
ENT
GX
_0
7_
06
5
WX SAT
GSPD
-56
TAT
TAS
-40
234
345
HDG315
ETE1+36
12 . 5DVT
NM
FMS1360
N
50 50
3
6
33
30
PHX
TOC
LUF
DVT
FGC
AUTOTHROTTLE
1
1
2
2
SYSTEM 2/3
WX
T5 .0
LX
SAT
GSPD
-56
TAT
TAS
-40
234
345
ETE1+36
12 . 5DVT
NMFGC
AUTOTHROTTLE
2
1
1
2
SYSTEM 2/3
SRP
1. Selecting MENU a second time will displaySYSTEM 2/3. First line of text will be inside ofbox (default).
2. Select ENT to change mode or source.Mode or source will be cyan when active.
For Training Purposes OnlySept 04
7-93
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
MENU BUTTON (Cont)
TCAS MENU
EMER
TERRMAP
PLAN
NAV
APT
NORM ABN
SKP
RCL
PAG
ENT
TCAS MENU
EMER
TERRMAP
PLAN
NAV
APT
NORM ABN
SKP
RCL
PAG
ENT
GX
_0
7_
06
6
EXCEEDENCE 3/3
NO EXCEEDENCE RECORDED
WX SAT
GSPD
TERR INHIB
-56
TAT
TAS
-40
234
345
HDG315
ETE1+36
12 . 5DVT
NM
FMS1360
N
50 50
3
6
33
30
PHX
TOC
SRPLUF
DVT
TERR INHIB
SAT -56
TAT -40
TAS 234
GSPD
TERRINHIB
345
PHXTOC
SRPDVT
4000 4000
FL180
Note:If no engine exceedence has occured:
DATE: 10/12/98 TIME: 10:45LH RH
MAX TIME MAX TIME
TRIGGERED BY : LN1
N1:N2:ITT:
OIL P:OIL T:
N1 VIB:N2 VIB:
12085
79050850.60.6
9580
80050880.60.6
2:150:000:000:000:000:000:00
0.000:000:000:000:000:000:00
EXCEEDENCE 3/3
1. Selecting MENU a third time will displaySYSTEM 3/3, engine EXCEEDENCEdisplay (on ground only).
2. Select MENU a fourth time will display the vertical profile (if previously selected)or remove the pop-up window..
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
7-94 For Training Purposes OnlySept 04
Menu Pages
GX
_0
7_
06
7
DIST/TIME
IDENTS
VERT PROFILE
METRIC ALT
FLIGHT DIR
WYPT
ON
ON
ON
SC
DEST
OFF
OFF
OFF
CP
DISPLAY 1/3
FGC
AUTOTHROTTLE
1
2
2
1
SYSTEM 2/3
DIST/TIME
IDENTS
VERT PROFILE
METRIC ALT
FLIGHT DIR
Used to indicate display of distance and timeinformation to either the go-to waypoint ordestination waypoint.
Used to indicate identification of waypointsand navaids on flight plan.
Used to enable/disable display of the verticalprofile data.
Used to enable/disable display of the metricaltitude data.
Used to select between Single Cue (SC) orCross Pointers (CP) flight director.
FGC
AUTOTHROTTLE
Used to select/change Flight GuidanceComputer (FGC) priority.
Used to select between the two autothrottlecomputers.
DATE: 10/12/98 TIME: 10:45LH RH
MAX TIME MAX TIME
TRIGGERED BY : LN1
N1:N2:ITT:
OIL P:OIL T:
N1 VIB:N2 VIB:
12085
79050850.60.6
9580
80050880.60.6
2:150:000:000:000:000:000:00
0.000:000:000:000:000:000:00
EXCEEDENCE 3/3
EXCEEDENCEDisplays any given exceedence transmittedby the engine Engine Electronic Control(EEC). Only displayed when the airplane ison the ground. For more information, seechapter 5 POWER PLANT.
For Training Purposes OnlySept 04
7-95
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
TERRAIN (TERR) BUTTON
NOTEFor more information, refer to Chapter 16, NAVIGATION.
TCAS MENU
EMER
TERRMAP
PLAN
NAV
APT
NORM ABN
SKP
RCL
PAG
ENT
GX
_0
7_
06
8
SAT
GSPD
TERR
-56
TAT
TAS
-40
234
345
0 . 05L ETE12:45
12 . 5KDVT
NM
KPHXTOCWX
KSRPKDVT
4000 4000
FL180
HDG315
FMS1360
50 50
6
30
33
N KPHX3
TOC
KSRP
KDVT
WX SAT
GSPD
-56
TAT
TAS
-40
234
345
0 . 05L
HDG315
ETE1+36
12 . 5DVTNM
FMS1360
N
50 50
3
6
33
30
PHX
PHX
TOC
TOC
SRP
SRP
DVT
DVT
4000 4000
FL180
TERR ButtonSelecting TERR button enables terrain displaysand automatically deselects WX radar (if WXradar selected on). If selected again, TERRdisabled and WX RADAR enabled (if selected on).
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
7-96 For Training Purposes OnlySept 04
NAVAIDS/AIRPORTS (NAV/APT) BUTTON
NOTEFor more information, refer to Chapter 16, NAVIGATION.
TCAS MENU
EMER
TERRMAP
PLAN
NAV
APT
NORM ABN
SKP
RCL
PAG
ENT
GX
_0
7_
06
9
WX SAT
GSPD
TERR INHIB
-56
TAT
TAS
-40
234
345
0 . 05L
HDG315
ETE1+36
12 . 5DVTNM
FMS1360
N
50 50
3
6
33
30
PHX
PHX
TOC
TOC
SRP
SRP
DVT
DVT
4000 4000
FL180
Waypoint
Navaid: VOR/DME
Navaid: DME only
Navaid: VOR only
Airport
TOC/TOD/BOSC
NAV/APT ButtonUsed to display NAVAIDS, AIRPORTS or both.
The button sequence is as follows:NAVAIDS – AIRPORTS – BOTH – OFF.
For Training Purposes OnlySept 04
7-97
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
NORMAL PROCEDURES (NORM)
WAYPOINT LISTING
TCAS MENU
EMER
TERRMAP
PLAN
NAV
APT
NORM ABN
SKP
RCL
PAG
ENT
TCAS MENU
EMER
TERRMAP
PLAN
NAV
APT
NORM ABN
SKP
RCL
PAG
ENT
GX
_0
7_
07
0
PHX N 33 26.7 W 112 00.5PRC N 34 39.1 W 112 25.2FLG N 35 08.3 W 111 40.7
TO2TO3TO4TO5TO6TO7PPOS N 32 04.4 W 110 45.7
IDENT LAT LON FMS 1
1. Selecting NORM will display NormalProcedures index. First line is inside of box(default).
2. Select ENT to view boxed information.
WX SAT
GSPD
TERR INHIB
-56
TAT
TAS
-40
234
345
HDG315
ETE1+36
12 . 5DVT
NM
FMS1360
N
50 50
3
6
33
30
PHX
TOC
SRPLUF
DVT
1.
2.3.4.5.6.7.8.9.
WAYPOINTLISTINGDISCLAIMERBEFORE STARTAFTER STARTTAXI/TAKEOFFAFTER TAKEOFFCLIMBCRUISEDESCENT
NORMALPROCEDURES
1/2
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
7-98 For Training Purposes OnlySept 04
NORM - DISCLAIMER
TCAS MENU
EMER
TERRMAP
PLAN
NAV
APT
NORM ABN
SKP
RCL
PAG
ENT
TCAS MENU
EMER
TERRMAP
PLAN
NAV
APT
NORM ABN
SKP
RCL
PAG
ENT
GX
_0
7_
07
1
2. Select ENT to view boxed information.
DISCLAIMER 1/2
USE OF THIS CHECKLIST
EITHER IN ITS ORIGINAL
FORM OR AS SUBSEQUENTLY
MODIFIED BY THE USER
DOES NOT RELIEVE THE
FLIGHT CREW OF ITS
RESPONSIBILITY TO COMPLY
WITH CHECKLIST AS
1. Pull down on joystick to select next line. Line that isselected is inside of box.
WX SAT
GSPD
TERR INHIB
-56
TAT
TAS
-40
234
345
HDG315
ETE1+36
12 . 5DVT
NM
FMS1360
N
50 50
3
6
33
30
PHX
TOC
SRPLUF
DVT
1.
2.3.4.5.6.7.8.9.
WAYPOINTLISTINGDISCLAIMERBEFORE STARTAFTER STARTTAXI/TAKEOFFAFTER TAKEOFFCLIMBCRUISEDESCENT
NORMALPROCEDURES
1/2
For Training Purposes OnlySept 04
7-99
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
NORM - BEFORE START
TCAS MENU
EMER
TERRMAP
PLAN
NAV
APT
NORM ABN
SKP
RCL
PAG
ENT
GX
_0
7_
07
2
2. Select ENT to view boxed information.
1. Pull down on joystick to select next line. Linethat is selected is inside of box.
BEFORE STARTCABIN SIGNS
CHECKLIST COMPLETE
ALTIMETERSEFISCASTAKE-OFF DATAFMS/IRSRADIOS/NAVAIDST/O BRIEFINGDOORSBLEED AIR PRESSBEACONENGINES
SETSET FOR DEPARTURE
CHECKEDPROGRAMMEDPROGRAMMED
SETCOMPLETE
CLOSEDCHECKED
ONSTART
ON
WX SAT
GSPD
TERR INHIB
-56
TAT
TAS
-40
234
345
HDG315
ETE1+36
12 . 5DVT
NM
FMS1360
N
50 50
3
6
33
30
PHX
TOC
SRPLUF
DVT
1.
2.3.4.5.6.7.8.9.
WAYPOINTLISTINGDISCLAIMERBEFORE STARTAFTER STARTTAXI/TAKEOFFAFTER TAKEOFFCLIMBCRUISEDESCENT
NORMALPROCEDURES
1/2
BEFORE STARTCABIN SIGNS
CHECKLIST COMPLETE
ALTIMETERSEFISCASTAKE-OFF DATAFMS/IRSRADIOS/NAVAIDST/O BRIEFINGDOORSBLEED AIR PRESSBEACONENGINES
SETSET FOR DEPARTURE
CHECKEDPROGRAMMEDPROGRAMMED
SETCOMPLETE
CLOSEDCHECKED
ONSTART
ON
TCAS MENU
EMER
TERRMAP
PLAN
NAV
APT
NORM ABN
SKP
RCL
PAG
ENT
TCAS MENU
EMER
TERRMAP
PLAN
NAV
APT
NORM ABN
SKP
RCL
PAG
ENT
3. To acknowledge checklist item, select ENTbutton. Once item is acknowledged, it willannunciate green and the box automaticallyscrolls to the next line.
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
7-100 For Training Purposes OnlySept 04
ABNORMAL PROCEDURES (ABN) BUTTON
TCAS MENU
EMER
TERRMAP
PLAN
NAV
APT
NORM ABN
SKP
RCL
PAG
ENT
TCAS MENU
EMER
TERRMAP
PLAN
NAV
APT
NORM ABN
SKP
RCL
PAG
ENT
TCAS MENU
EMER
TERRMAP
PLAN
NAV
APT
NORM ABN
SKP
RCL
PAG
ENT
GX
_0
7_
07
3
2. Select ENT to view boxed information.
PRECAUTIONARY SHUTDOWNAFFECTED ENGINE:
CHECKLIST COMPLETE
THRUST LEVERENG RUN SWITCHSINGLE ENGINEPROCEDURE
IDLEOFF
ACCOMPLISH
POWERPLANT 1/2ENGINE FAILED PROCEDURE
PRECAUTIONARY SHUTDOWNSINGLE ENGINE PROCEDUREFUEL SOV FAILENGINE OVERSPEEDENGINE SOV FAILENGINE FLAME-OUTFADEC FAILFADEC N1 CONTFUEL LO PRESSOIL COOL FAILOIL LO QTYREVERSER FAILREVERSER UNLKDSTART ABORTED
WX SAT
GSPD
TERR INHIB
-56
TAT
TAS
-40
234
345
HDG315
ETE1+36
12 . 5DVT
NM
FMS1360
N
50 50
3
6
33
30
PHX
TOC
SRPLUF
DVT
1.2.
3.4.5.6.7.8.9.
POWERPLANTBLEED MANAGEMENT
AUTOMATIC FLIGHT CONTROLSAPUDOORSELECTRICALFIRE PROTECTIONFLIGHT CONTROLSFUEL
ABNORMALPROCEDURES
1/2
3. To acknowledge checklist item, select ENTbutton. Once item is acknowledged, it willannunciate green and the box automaticallyscrolls to the next line.
1. Selecting ABN will display AbnormalProcedures index.
For Training Purposes OnlySept 04
7-101
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
EMERGENCY PROCEDURES
TCAS MENU
EMER
TERRMAP
PLAN
NAV
APT
NORM ABN
SKP
RCL
PAG
ENT
TCAS MENU
EMER
TERRMAP
PLAN
NAV
APT
NORM ABN
SKP
RCL
PAG
ENT
TCAS MENU
EMER
TERRMAP
PLAN
NAV
APT
NORM ABN
SKP
RCL
PAG
ENT
TCAS MENU
EMER
TERRMAP
PLAN
NAV
APT
NORM ABN
SKP
RCL
PAG
ENT
GX
_0
7_
07
4
3. Select ENT to view boxed information
APU FIRE
APU SWITCHAPU DISCH HANDLEAPU DISCH HANDLEFIRE HANDLE UNLK PINAPU DISCH HANDLE
LAND AT NEAR SUITABLE AIRPORT
OFFPULLTURNSLIDETURN
1/4EMERGENCYPROCEDURES
WX SAT
GSPD
TERR INHIB
-56
TAT
TAS
-40
234
345
HDG315
ETE1+36
12 . 5DVT
NM
FMS1360
N
50 50
3
6
33
30
PHX
TOC
SRPLUF
DVT
1.2.3.4.5.6.7.8.9.
1.2.3.4.5.6.7.8.9.
ENGINE FIREAPU FIREELECTRICAL SMOKE/FIREAIR COND SMOKECABIN SMOKESMOKE REMOVAL PROCEDUREGEAR BAY OVHTBRAKE OVHTWING OVHT
ENGINE FIREAPU FIREELECTRICAL SMOKE/FIREAIR COND SMOKECABIN SMOKESMOKE REMOVAL PROCEDUREGEAR BAY OVHTBRAKE OVHTWING OVHT
EMERGENCYPROCEDURES
1/2
4. To acknowledge checklist item, select ENTbutton. Once item is acknowledged, it willannunciate green and the box automaticallyscrolls to the next line.
2. Pull down on joystick to select next line. Linethat is selected is inside of box.
1. Selecting EMER will display EmergencyProcedures index.
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
7-102 For Training Purposes OnlySept 04
STANDBY ATTITUDE INDICATORThe standby attitude indicator displays airplane pitch and bank angle. It is a 28 volt DC-driven gyro that provides pitch and roll information, in the event of loss of AC electrical power.
20
10
30
20
10
30
GX
_0
7_
07
5
Ball LevelIndicator
DrumRollIndex
RollPointer
Failure Flag
AircraftSymbol
HorizontalLine
CageKnob
For Training Purposes OnlySept 04
7-103
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
STANDBY ALTIMETER/AIRSPEED INDICATORThe Standby Altimeter/Airspeed indicator uses the standby pitot-static source. The standby indicated airspeed readout displays noncorrected indicated airspeed.
09
8
7
65
4
3
2
1100 FEET
ALT
1 00032
4
10 13
mb/hPa
29 9 2
IN HG
IAS KNOTS
220200180 250
BARO
GX
_0
7_
07
6
IAS KNOTS
220140 200120 18010080600 250 300 350 400 450160
SPEED IAS RANGE
ALTITUDE DRUM RANGE
ALTITUDE RANGE
-1,000 to + 51,000 FT
10,000 FTDRUM
1,000 FTDRUM
100 FTDRUM
NEG87654321
9876543210
000
900
BelowSea LevelIndication
Below10,000 feetIndication
ALTIMETER RANGE
mb/hPa746
10131049
in Hg22.0029.9230.99
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
7-104 For Training Purposes OnlySept 04
STANDBY MAGNETIC COMPASSA standby magnetic compass is located below the overhead panel, at the center of the windscreen. The standby magnetic compass retracts into a compartment in the overhead panel. The compass lighting is controlled by the Cockpit Lights Integral panel, located on the pedestal.
GX
_0
7_
07
7
B C1010
6 3 33 3N
TO FLY N 45 E 135 225 W 315S
STEER
STBY COMPASS WITH ALL RADIOS ON SWUNG / / BY
Bracket
Compensators
CompassDial
Light UnitCompassCorrectionCard
6 3 33 3N
For Training Purposes OnlySept 04
7-105
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
CLOCKTwo digital electronic clocks are installed on the side panels, and are the time base source for the avionics equipment.
SEL
RST
ET
CHR
MODE
GPS
CHR
11:1350
01:43
GX
_0
7_
07
8
Time/Date DisplayGMT, Local Time or Datedisplayed here. Date isdisplayed as month/day/yearand the colon (:) is removedwhen in Date mode.
Mode ControlDTGPSINT
LT
– Date (mo/dy/yr)– GPS fed GMT
– Internally computedGMT (Manual selection)
– Local Time
Elapsed Time (ET) /Chronometer (CHR)FunctionET
CHR
– Corresponds to theaircraft’s flight time fromtakeoff (weight off wheels)to landing (weight onwheels). Automatic.
– Displayed as soonas the CHR button ispressed. Replaces ET ifpresent.
CHR Control1st push
2nd push3rd push
– Start and replaces ET inbottom window if it was displayed.
– Stop. Value is held.– Reset. Display zeroed
and blanked.
ET ControlsSEL
RST
– ET comes on in bottomwindow. Does not incrementon ground.
– Blanks the digits andresets to zero. Ground only.
Mode DisplayDTGPSINT
LT
– Date (mo/dy/yr)– GPS fed GMT
– Internally computedGMT (Manual selection)
– Local Time
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
7-106 For Training Purposes OnlySept 04
TIME SETTING
Set at Power-upAt the first application of power, the clock will be in GMT minutes adjustment if GPS is invalid and the clock is not transmitting on the ARINC bus. If the GPS data is valid, the clock is automaticafly updated and swiched in GPS mode.
In the SET function, the GMT minute’s digits are flashing. The flashing rate is one flash per second. The setting is obtained by pressing the ET SEL pusbbutton to decrease the data and pressing the ET RST button to increase the data. The counter increments one digit for each push of the button. The INT flag is lit.
• By depressing the MODE button, the GMT hour’s digit is flashing, and you can adjust the display in the same way. The INT flag is lit
• By depressing the MODE button once more, the year’s digits are flashing and you can adjust the display in the same way. The DT flag is lit
• By depressing the MODE button once, the month’s digits are flashing and you can adjust the display in the same way. The DT flag is lit
• By depressing the MODE button once, the day’s digits are flashing and you can adjust the display in the same way. The DT flag is lit
• By depressing the MODE button once, the LT minutes’s digits are flashing and you can adjust the display in the same way. The LT flag is lit
• By depressing the MODE button once, the LT hours’s digits are flashing and you can adjust the display in the same way. The LT flag is lit
• One more press on MODE button will lead to GMT minutes adjustment• Press the MODE button for more than two seconds to start the clock operation
The default time and date for the SET mode at initialization of the clock will be: The 1st of January 2002 at 00 hr and 00 min.
Set after Synchronization by GPS or Manual StartingIf the GPS data is valid, only the LT mode can be set.
The setting is obtained by means of the SET function which is available by pressing the MODE pushbutton for a minimum of two seconds.
• By depressing the MODE button, the setting roll in LT time if the LT setting is chosen
• By depressing the MODE button, the setting roll in DATE if the DT setting is chosen
• By depressing the MODE button, the setting roll in the INT time if the INT setting is chosen
For Training Purposes OnlySept 04
7-107
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
STANDBY AIRSPEED/ALTITUDE/ALTIMETER (IF INSTALLED)Incorporated in the indicator is a light sensor that provides ambient light level data to the automatic lighting system.
A navigation (NAV) button is selected to display ILS (localizer and glideslope) deviation information. The ATT button is used to erect the display.
GX
_0
7_
07
9
20
20
10
10
20
20
10
10
1300
360 200
340 000
300
NAV ATT
600
290 400
320 26800
M.789 1013 HP
29.92 IN
Light Sensor
Attitude Barometric Set
AltimeterSetting Inches
AttitudeIndicator
AltitudeTape
Altimeter SettingHectopascals
Navigation
MACH Number
AirspeedTape
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
7-108 For Training Purposes OnlySept 04
PFD COMPARISON MONITOR ANNUNCIATIONSComparison monitor annunciations are displayed when the difference between the data received by the pilot’s and copilot’s PFD, exceeds the predetermined trip thresholds.
If both PFDs have misleading data, CHECK PFD message will be displayed on the EICAS display.
SYSTEM INTEGRATIONThe Electronic Flight Instrument is tightly coupled with both the Automatic Flight Control and Navigation Systems. This is the case as it reflects the output of these systems for pilot consumption and action while providing the source data upon which it is based. The three-sided, interdependent relationship between these systems can make fault determination difficult in the event of a failure in one. Aircrew need to be cognizant of this fact and address such eventualities in a disciplined, step-by-step manner.
GX
_0
7_
08
0
20 20
10 10
10 10
20 20
20
HDG
29.92 IN
ASELAP1
CRS030
HDG030
1000
VS 1000
200 10400
1000080
20
9500
10500220
210
200
190
180
170
160
150
1856
4
0
1
2
3
1
2
3
LOC
LOC
FWC
HDGFWC
EICAS
ALT
RADRAD
ATT
GS
GS
IAS
IAS
PIT
ALT
ROL
ATT
HDG
EICAS
Indicates amiscompare of± 20 knots.
Indicates amiscompare of± 5° of pitch.
Indicates amiscompare of± 0.24°.
Indicates amiscompareof ± 10 feet.
Indicates amiscompareof ± 1/2 dot.
Indicates CASmessagemiscompare(warnings, cautionsand advisories) formore than 7seconds.
Indicates amiscompare of± 200 feet.
Indicates amiscompare of± 6° of roll.
Indicates amiscompare of ± 5°of pitch and ± 6° ofroll.
Indicates amiscompareof ± 10°.
Indicates engine datamiscompare between thesensors (DAU) and theengine parameters formore than 3 seconds.
N
33
30
W
2421
S
15
12
E
63
For Training Purposes OnlySept 04
7-109
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
ELECTRONIC DISPLAY SYSTEM EICAS MESSAGES
GX
_0
7_
08
5
CHECK PFDADC 1 MISCMPADC 2 MISCMPADC 3 MISCMP
ALL IRS MISCMPASCB CTRL 1 FAILASCB CTRL 2 FAILASCB CTRL 3 FAILASCB FAILCAT 2 INVALID
DISP CTLS FAILHUD FAILHUD MISCOMPARE
ALL ADC MISCMP
CHECK DU 1CHECK DU 2CHECK DU 3CHECK DU 4CHECK DU 5CHECK DU 6
IAC 1 OVHTIAC 2 OVHTIAC 3 OVHT
CHECK PFDIndicates that both PFDs havemisleading data.
ADC 1 (2) (3) MISCOMPIndicates that respective ADChas miscompared.
DISP CTLRS FAILLoss of communication with alldisplay controllers.
IRS 1 (2) (3) OVHTIndicates IRS has anovertemperature condition.
ALL ADC MISCMPIndicates that all three ADCshave miscompared.
ALL IRS MISCMPIndicates that all three IRSshave miscompared.
ASCB CTRL 1 (2) (3) FAILIndicates loss ofcommunication with two ofthree bus controllers.
ASCB FAILIndicates loss ofcommunication with all threebus controllers. Loss of allflight instruments and AFCSfunctions.
CAT 2 INVALIDIndicates that CAT 2 conditionshave become invalid afterbeing enabled.
HUD FAILIndicates total loss of Heads-Up display and functions.
HUD MISCOMPAREIndicates that the HFGS andthe PFD have differentinformation.
CHECK DU 1 (2) (3) (4) (5) (6)Indicates that data fromaffected DU does not matchdata from sensor.
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
7-110 For Training Purposes OnlySept 04
ELECTRONIC DISPLAY SYSTEM EICAS MESSAGES (Cont)
IRS 1 (2) (3) MISCMPIndicates that respective IRShas miscompared.
IRS 1 (2) (3) SET HDGIndicates IRS has defaulted toa heading of 360 degrees uponentering attitude mode.
IAC 1 (2) (3) OVHTIndicates that IAC hasoverheated, resulting inpossible loss of functions.
SG 1 (2) (3) FAILIndicates that there is a loss ofcommunications with affectedSG, or SG is indicating a powerup failure.
GX
_0
7_
08
6
IRS 1 MISCMPIRS 2 MISCMPIRS 3 MISCMP
SG 1 FAILSG 2 FAILSG 3 FAIL
IRS 1 OVHTIRS 2 OVHTIRS 3 OVHTIRS 1 SET HDGIRS 2 SET HDGIRS 3 SET HDG
For Training Purposes OnlySept 04
7-111
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
ELECTRONIC DISPLAY SYSTEM EICAS MESSAGES (Cont)
GX
_0
7_
08
7
ADC 1 FAILADC 2 FAILADC 3 FAILADC 1 DEGRADEDADC 2 DEGRADEDADC 3 DEGRATEDASCB BUS FAULTASCB CTRL 1 FAULTASCB CTRL 2 FAULTASCB CTRL 3 FAULTCHECKLIST MISMATCHDAU 1A-1B FAILDAU 2A-2B FAILDAU 3A-3B FAILDAU 4A-4B FAILDU 1 FANDU 2 FANDU 3 FANDU 4 FANDU 5 FANDU 6 FANHUD FAN FAILHUD MISALIGN
ADC 1 (2) (3) FAILIndicates that ADC has failed.
ADC 1 (2) (3) DEGRADEDIndicates that ADC isunreliable. Degraded staticerror correction.ASCB BUS FAULT
Indicates ASCB single busfailure (on ground only). ASCB CTRL 1 (2) (3) FAULT
Indicates loss ofcommunication with one buscontroller.CHECKLIST MISMATCH
Indicates that checklists arenot identical in all IACs(on ground only).
DAU 1A-1B (2A-2B) (3A-3B)( 4B) FAIL4A-Indicates that there is a loss ofcommunication with the
DAU, or DAU hasfailed.affected
DU 1 (2) (3) (4) (5) (6) FANIndicates that DU hasoverheated, resulting inpossible loss of fu ctions.n
HUD MISALIGNIndicates that the combiner isnot in the down and lockedposition.
HUD FAN FAILIndicates loss of Heads-Updisplay fan.
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
7-112 For Training Purposes OnlySept 04
ELECTRONIC DISPLAY SYSTEM EICAS MESSAGES (Cont)
GX
_0
7_
08
8
IAC CONFIG MSMTCHIAC 1 AURAL FAILIAC 2 AURAL FAILIAC 1 INVALIDIAC 2 INVALIDIAC 3 INVALIDIAC 1 MEM FULLIAC 2 MEM FULLIAC 3 MEM FULLIAC 1 WOW INOPIAC 2 WOW INOPIAC 3 WOW INOPIRS 1 AUX FAILIRS 2 AUX FAILIRS 3 AUX FAILIRS 1 FAILIRS 2 FAILIRS 3 FAILIRS 1 NO ALIGNIRS 2 NO ALIGNIRS 3 NO ALIGNMFD CTLR 1 FAILMFD CTLR 2 FAILREVRSION CTLR FAIL
IAC 1 (2) AURAL FAILIndicates that there is no DCpower to aural warningsystem, or a BIT failure isbeing indicated and not muted.
IAC CONFIG MSMTCHIndicates that the IACs are notconfigured with the sameoptions or aircraft configuration.
IAC 1 (2) (3) INVALIDIndicates that there is invalidsoftware configuration in IAC,or incorrect airplane ID.
IAC 1 (2) (3) MEM FULLIndicates that affected IAC hasreached its memory limit.
IAC 1 (2) (3) WOW INOPIndicates that there is a loss ofpower up testing and functionloss. IAC WOW input isinconsistent withparameters.
other airplane
IRS 1 (2) (3) FAILIndicates IRS has failed.(IRU has detected an internalfailure). IRS 1 (2) (3) NO ALIGN
Indicates IRS fails to properlyalign due to improper positionentry or excessive airplanemotion, while in align mode.
IRS 1 (2) (3) AUX FAILIndicates IRS back-up powersource has failed.
MFD CTLR 1 (2) FAILIndicates that the affectedMFD controller has failed.
REVERSION CTLR FAILIndicates that there is a loss ofreversionary control functions.May not be able to revert SGsor DUs.
For Training Purposes OnlySept 04
7-113
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
ELECTRONIC DISPLAY SYSTEM EICAS MESSAGES (Cont)
GX
_0
7_
08
9
HUD ONIRS 1 IN ATTIRS 2 IN ATTIRS 3 IN ATTIAC 1 AURAL MUTEIAC 2 AURAL MUTE
IRS 1 (2) (3) IN ATTIndicates that IRS modeselector has been selected toATT.
HUD ONIndicates that the HUD hasbeen selected on, using theswitch located on theglareshield panel.
IAC 1 (2) AURAL MUTEIndicates that the AURALWARNING IAC 1 (2) switchhas been pushed. The auralwarnings for the applicableIAC (s) are disabled.
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
7-114 For Training Purposes OnlySept 04
EMS CIRCUIT PROTECTION
M
1/1CB - CMS SYSTEM
IN
INCKPT PRINTER
CAIMS PMAT LAPTOP DC 1
DC 1
M
BRT
CIRCUIT BREAKER SYSTEM
2/2CIRCUIT BREAKER - STATUS
DOORS
ELECAIR COND/PRESS
AFCS
ENGINE
FIRE
APU
BLEED
CAIMS
STAT SYS BUSPREVPAGE
NEXTPAGE
CNTL TEST
BUS
EMERCONT
COMM
FLT CONTROLS
FUEL
GX
_0
7_
08
4
For Training Purposes OnlySept 04
7-115
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
EMS CIRCUIT PROTECTION (Cont)
M
M
M
M
M
M
BRT
CIRCUIT BREAKER SYSTEM
2/2CIRCUIT BREAKER - STATUS
NAV
OILICE
HYD
OXYGEN
THRUST REV
IND/RECORD
LDG GEAR
LIGHTS
STAT SYS BUSPREVPAGE
NEXTPAGE
CNTL TEST
BUS
EMERCONT
CB - IND/RECORD SYSTEM 1/5
ADC 1
ADC 2
ADC 3
AURAL WARNING 1
AURAL WARNING 2
CLOCK 1
BATT
DC 1
DC ESS
BATT
DC ESS
BATT
IN
IN
IN
IN
IN
IN
CLOCK 2
CLOCK BACK UP
CVR
CVR ERASE
DATA LOADER
DAU 1 CH A
DC 1
AV BATT
DC ESS
DC 2
DC 2
BATT
IN
IN
IN
IN
IN
IN
DCPC
3/5
DAU 1 CH B
DAU 2 CH A
DAU 2 CH B
DAU 3 CH A
DAU 3 CH B
DAU 4 CH A
DC 1
BATT
DC 2
BATT
DC 2
BATT
IN
IN
IN
IN
IN
IN
4/5
DAU 4 CH B
DU 1
DU 2
DU 3 PWR A
DU 3 PWR B
DU 4 PWR B
DC 1
DC ESS
DC ESS
BATT
DC 1
BATT
IN
IN
IN
IN
IN
IN
5/5
DU 4 PWR B
DU 5
DU 6
FDR
FDR ACCELEROMETER
DC 2
DC 2
DC 2
DC 2
DC 2
IN
IN
IN
IN
IN
2/5CB - IND/RECORD SYSTEM
CB - IND/RECORD SYSTEM
CB - IND/RECORD SYSTEM
CB - IND/RECORD SYSTEMG
X_
07
_0
82
P I L O T T R A I N I N G G U I D E
ELECTRONIC DISPLAY SYSTEM
7-116 For Training Purposes OnlySept 04
EMS CIRCUIT PROTECTION (Cont)
M
M
M
M
M
M
M
BRT
CIRCUIT BREAKER SYSTEM
STAT SYS BUSPREVPAGE
NEXTPAGE
CNTL TEST
BUS
EMERCONT
GX
_0
7_
08
3
CIRCUIT BREAKER-SYSTEM 2/2
GEAR
HYD
ICE
IND/RECORD
LIGHTS
NAV
OIL
OXYGEN
THRUST REV
CB - NAV SYSTEM 1/6
ADF 1
ADF 2
DME 1
DME 2
FMS 1 CDU
FMS 2 CDU
DC 1
DC ESS
DC 2
DC ESS
BATT
DC 2
IN
IN
IN
IN
IN
IN
2/6
IN
IN
IN
IN
IN
IN
DC 1
DC 1
DC 2
DC 1
DC 2
DC 2
CB - NAV SYSTEM
FMS 3 CDU
GPS 1
GPS 2
GPWS
HUD
HUD CTL PANEL
CB - NAV SYSTEM 4/6
IRS 3 FAN
IRS 3 PWR A
IRS 3 PWR B
LIGHTNING SENSOR
MFD 1 CTLR
MFD 2 CTLR
IN
IN
IN
IN
IN
IN
DC 1
DC 1
DC ESS
DC 1
BATT
DC 2
CB - NAV SYSTEM 5/6
RAD ALT 1
RAD ALT 2
STBY ADI
STBY ALT/ASI
TCAS
VOR/ILS 1
IN
IN
DC PC IN
IN
IN
IN
DC 1
DC 2
AV BATT
DC ESS
DC ESS
DC 2
CB - DC BUS 1 3/6
IRS 1 FAN
IRS 1 PWR A
IRS 1 PWR B
IRS 2 FAN
IRS 2 PWR A
IRS 2 PWR B
IN
IN
IN
IN
IN
IN
DC ESS
DC ESS
BATT
DC 2
DC 2
DC ESS
CB - NAV SYSTEM 6/6
VOR/ILS 2
VOR/ILS 3
WX RADAR
WX RADAR CTLR 1
WX RADAR CTLR 2
IN
IN
IN
IN
IN
DC ESS
DC 1
DC 1
DC 1
DC 1
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