Chapter 7: Electronic Display System TABLE OF CONTENTSgld manual arm park/emer brake on

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



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


7-1



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).

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789

ITTSYNC

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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


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



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


7-3



EICAS DISPLAY

L ENG FLAMEOUTFUEL LO QTYFUEL IMBALANCEYD OFF

GLD MANUAL ARMPARK/EMER BRAKE ON

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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




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


7-5



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




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


7-7



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




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


7-9



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




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


7-11



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




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


7-13



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




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


BARO SETNAV SRC

BRG V/L BRGFMS

HSI

Honeywell PUSH STD

MASTERWARNING/CAUTION

ROLL SPLRS

PLT CONT

ROLLSEL

PLTROLL

WARNING

CAUTION

DIMOFF

BRT

HUD


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


WARNING

CAUTION


WARNING

CAUTION

GX

_0

7_

01

2


ROLL SPLRS

PLT CONT

ROLLSEL

PLTROLL

WARNING

CAUTION

DIMOFF

BRT

HUD


ROLL SPLRS

CPLT CONT

ROLLSEL

CPLTROLL

WARNING

CAUTION


PUSH DCT PUSH DCT

ALTHDG

DN

UP

P

I

T

C

H

Honeywell

FD FDAP

CPL

YD


APR VS

BC

PUSH CHG PUSH SYNC


WARNING

CAUTION


WARNING

CAUTION

GX

_0

7_

01

3


BARO SETNAV SRC

BRG V/L BRGFMS

HSI

Honeywell PUSH STD


BARO SETNAV SRC

BRG V/L BRGFMS

HSI

Honeywell PUSH STD


7-15



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


WARNING

CAUTION

L ENG FLAMEOUT

GX

_0

7_

01

5Single Chime

Glareshield

Aural

EICAS Display


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




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


7-17



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.



<– FUEL XFER ON


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Gear/Slats/FlapsPop-UpIcon

14messages 24

messages

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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

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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

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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

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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.

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7-19



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




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


7-21



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




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


OFF

OFF

OFF

OFF

OFF

OFF

M

BRT



NEXTPAGE

CNTL TEST

BUS

EMERCONT

TEST CONTROL 1/2

FIRE TEST

STALL TEST



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

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7-23



• 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.

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• 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


7-25



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




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


7-27



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.




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

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30

09

8

7

65

4

3

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10 13

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220200180 250

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Honeywell HoneywellHoneywell

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ET


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

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10

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9500

10500

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220

210

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190

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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


9500

29.92

AT1

VTA

M

0.450M

FMS1LOC1DTK

360

HDG330

10400

20

20

10

10

20

20

10

10

9500

10500

300

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LE

F1

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150

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0

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1

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ATT

HDGT

EICAS

GS

LOC

HDG

RAD

IASALT

HDG2

VOR 1

ADF 2

0010020

80


WX

ET


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

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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

––


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7-29



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


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

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190

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150

1856

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1

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1

2

3

ATT

HDGT

EICAS

GS

LOC

HDG

RAD

IASALT

HDG2

VOR 1

ADF 2

0010020

80


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

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9500

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FMS1LOC1DTK

360

HDG330

10400

20

20

10

10

20

20

10

10

9500

10500

300

220

210

200

190

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LE

F1

2160

150

1856

4

N33

30

W24

21S

15

12

E6

3

0

1

2

3

1

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3

ATT

HDGT

EICAS

GS

LOC

HDG

RAD

IASALT

HDG2

VOR 1

ADF 2

0010020

80



1.54

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N2

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OIL TEMP

OIL PRESS

93.4575O11581

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IGN

START START

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1.54

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T/ON1SYNC

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ITTSYNC

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–TRIMS–

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AIL

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7.2

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93.4575O11581

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END




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


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


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


WX

ET


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


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


END


7-31



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


WX

ET


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


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


WX

ET


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


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


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


WX

ET


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


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


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


DU 5

EICAS

ALTN 3

ALTN 1NORMALTN 2

EICAS

ALTN 3

ALTN 1NORMALTN 2

• EICAS displayedon DU 4

ALTN 1 –


ALTN 2 –


ALTN 3 –


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


END


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


END


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


END




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


7-33



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


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


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


WX

ET


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


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


END




SG REVERSION (Cont)

GX

_0

7_

03

0

SG 1 FAIL

SG 3 SG 2SG 1



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


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


WX

ET


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



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


WX

ET


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


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


END


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


END


7-35



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


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


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


WX

ET


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



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


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


END


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


END




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


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

––


7-37



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



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




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


7-39



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


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


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


WX

ET


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

–• –• –


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


END




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


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


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


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


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


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


WX

ET


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

%

% %


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


END


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


END


7-41



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)




• 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


7-43



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




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


7-45



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.




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


7-47



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






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




7-49



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 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






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




7-51



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






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




7-53



ADVISORY MESSAGES (CYAN)


→ 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




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




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




7-55



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






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




7-57



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






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




7-59



STATUS MESSAGES (WHITE)


→ 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




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 3A OFF Hydraulic pump 3A selected off 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




7-61



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






PAGE INTENTIONALLY LEFT BLANK


7-63



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


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


WX

ET


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


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


WX

ET


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




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


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


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


Honeywell

WX

ET


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


PUSH DCT PUSH DCT

ALTHDG

DN

UP

P

I

T

C

H

Honeywell

FD FDAP

CPL

YD


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


BARO SETNAV SRC

BRG V/L BRGFMS

HSI

Honeywell PUSH STD


BARO SETNAV SRC

BRG V/L BRGFMS

HSI

Honeywell PUSH STD


7-65



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



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




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


7-67



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.




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.


7-69



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




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


7-71



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




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


7-73



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




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


7-75



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




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


7-77



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




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


WYPTONONONSC

DESTOFFOFFOFF

CP

1/2

MFD CONTROL PANEL

MFD MENU

PITCH DOWN COMMAND PITCH UP COMMAND

ROLL LEFT COMMAND

SINGLE CUE

DISPLAY


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


7-79



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




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


7-81



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




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.


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).


7-83



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.




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


7-85



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).




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


7-87



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




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


7-89



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




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


7-91



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.




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.


7-93



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..




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.


7-95



TERRAIN (TERR) BUTTON


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).




NAVAIDS/AIRPORTS (NAV/APT) BUTTON


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.


7-97



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




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


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.


NORMALPROCEDURES

1/2


7-99



NORM - BEFORE START

TCAS MENU

EMER

TERRMAP

PLAN

NAV

APT

NORM ABN

SKP

RCL

PAG

ENT

GX

_0

7_

07

2


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.


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.




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


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


1. Selecting ABN will display AbnormalProcedures index.


7-101



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


2. Pull down on joystick to select next line. Linethat is selected is inside of box.

1. Selecting EMER will display EmergencyProcedures index.




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


7-103



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




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


7-105



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




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


7-107



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




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


7-109



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.




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


7-111




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.





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.


7-113




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.




EMS CIRCUIT PROTECTION

M

1/1CB - CMS SYSTEM

IN

INCKPT PRINTER

CAIMS PMAT LAPTOP DC 1

DC 1

M

BRT


2/2CIRCUIT BREAKER - STATUS

DOORS

ELECAIR COND/PRESS

AFCS

ENGINE

FIRE

APU

BLEED

CAIMS


NEXTPAGE

CNTL TEST

BUS

EMERCONT

COMM

FLT CONTROLS

FUEL

GX

_0

7_

08

4


7-115



EMS CIRCUIT PROTECTION (Cont)

M

M

M

M

M

M

BRT


2/2CIRCUIT BREAKER - STATUS

NAV

OILICE

HYD

OXYGEN

THRUST REV

IND/RECORD

LDG GEAR

LIGHTS


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




EMS CIRCUIT PROTECTION (Cont)

M

M

M

M

M

M

M

BRT



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

Documents

Chapter 7: Electronic Display System TABLE OF CONTENTSgld manual arm park/emer brake on