PILOT TRAINING GUIDE AURAL/VISUAL WARNING · List of Figures Graphic Title Figure For Training...

Table of Contents

For Training Purposes OnlyMay 03

3-i

AURAL/VISUAL WARNINGP I L O T T R A I N I N G G U I D E

Introduction .........................................................................................................................3-1

Engine Indicating and Crew Alerting System (EICAS)........................................................3-3Description ....................................................................................................................3-3Components and Operation ..........................................................................................3-3

EICAS Control Panel...............................................................................................3-3EICAS Displays.......................................................................................................3-3Data Concentrator Unit (DCU) ................................................................................3-4

Controls and Indicators .......................................................................................................3-6Master Warning Switch/Lights.......................................................................................3-6Master Caution Switch/Lights........................................................................................3-6Aural Warning Testing...................................................................................................3-7Aural Alert Disable ........................................................................................................3-8EICAS Control Panel.....................................................................................................3-8

PRI ..........................................................................................................................3-8STAT .......................................................................................................................3-8STEP.......................................................................................................................3-9HYD.........................................................................................................................3-9ELEC.......................................................................................................................3-9CAS.........................................................................................................................3-9F/CTL ......................................................................................................................3-9

EICAS Primary Page...................................................................................................3-10Engine Indications.................................................................................................3-10Fuel Quantity.........................................................................................................3-10Crew Alerting System Messages ..........................................................................3-10Cabin Pressurization .............................................................................................3-10Landing Gear and Flaps........................................................................................3-10Landing Gear Horn................................................................................................3-11Trim Settings .........................................................................................................3-11

EICAS Status Page.....................................................................................................3-13Crew Alerting System Messages ..........................................................................3-13Flight Spoilers .......................................................................................................3-13Auxiliary Power Unit ..............................................................................................3-13Cabin Temperature ...............................................................................................3-13Bleed Air Pressure ................................................................................................3-13Fuel Temperature..................................................................................................3-13Oxygen Pressure ..................................................................................................3-13Cabin Pressurization .............................................................................................3-13Synoptic Pages .....................................................................................................3-14

EICAS Messages ........................................................................................................3-14Warning Messages ...............................................................................................3-14Caution Messages ................................................................................................3-15Advisory Messages ...............................................................................................3-15

AURAL/VISUAL WARNING

3-ii For Training Purposes OnlyJan 04

P I L O T T R A I N I N G G U I D E

Status Messages................................................................................................... 3-16Takeoff Configuration Warning ................................................................................... 3-16Inhibited EICAS Caution Messages............................................................................ 3-16Display Reversionary Control ..................................................................................... 3-18

EICAS Reversionary Mode ................................................................................... 3-18Display Reversionary Control Panel ..................................................................... 3-18PFD Reversionary Mode....................................................................................... 3-18MFD Reversionary Mode ...................................................................................... 3-18

Maintenance Diagnostic Computer............................................................................. 3-20Description ............................................................................................................ 3-20Operation .............................................................................................................. 3-20

Flight Data Recorder................................................................................................... 3-21Description ............................................................................................................ 3-21Components and Operation .................................................................................. 3-21FDR EVENT Switch .............................................................................................. 3-21

EICAS Messages........................................................................................................ 3-22

List of FiguresGraphic Title Figure


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AURAL/VISUAL WARNINGP I L O T T R A I N I N G G U I D E

EICAS Displays Location ....................................................................................................3-1EICAS Control Panel (ECP)................................................................................................3-2Master Warning and Caution Lights....................................................................................3-3AURAL WARN / LAMP TEST Panel ...................................................................................3-4DCU Disable Controls.........................................................................................................3-5EICAS Control Panel ..........................................................................................................3-6EICAS Primary Page ..........................................................................................................3-7EICAS Status Page Displays ..............................................................................................3-8Display Reversionary Control Panel ...................................................................................3-9Maintenance Diagnostic Computer Switch .......................................................................3-10FDR EVENT Switch ..........................................................................................................3-11

3-iv For Training Purposes OnlyMay 03

AURAL/VISUAL WARNING P I L O T T R A I N I N G G U I D E

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3-1


CHAPTER 3: AURAL/VISUAL WARNING

IntroductionThe aural and visual warning system components provide the flight crew with aural, visual and tactile indications of potentially unsafe conditions as well as information about airplane configurations and engine data. The system also warns of airplane system malfunctions and non-normal situations.


3-2 For Training Purposes OnlySept 04


EICAS Displays Location Figure 3-1

EICAS Control Panel (ECP) Figure 3-2

BRTBRT

EICAS DISPLAY 1 (ED 1) EICAS DISPLAY 2 (ED 2)

AILERON MON OKPARKING BRAKE ONFLAPS MOTOR OVHT

CABIN TEMP

BLEED PRESS

FUEL TEMP

ENGINE

BULK

OXY

C ALT

RATE

P

502048

70 75

-20

2000

3200

200

-0.5SPOILERS

APU

95 430

RPM EGT

P6

04

_0

3_

00

1

BRTBRT

85.0 85.0

HOT

925 750

N190.0

ITT

N2

GEAR DISAGREEAUTO PRESS

DN DN DN

- GEAR - - FLAPS -

C ALT

STAB

RATE

- TRIM -

P

3200 200 -0.5

20

NU

ND

4.0

RUDDER

AIL

RWDLWD

NRNL

FF

OIL PRESS

OIL TEMP

FAN VIB

7160 4870

200004.2

115

82

3500

3140

- FUEL QTY - TOTAL

3500

82

165

1.2

4870

75.0 95.0

VIB

REV APR

PRI STAT STEP CKLST RCL EMER

HYD ELEC LMFD

RMFD

SEL/AUTO

CAS F/CTL SKP/3D

UP/PLAN

DN/SIDE

M

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3-3


Engine Indicating and Crew Alerting System (EICAS)

DescriptionThe function of the EICAS is to display the engine instruments and to provide visual and aural crew-alert messages and real-time interpretation of aircraft system operation.

Two EICAS displays present the data on different selectable display pages. Some display pages are shown by default, others are available through crew selection. The EICAS control panel (ECP), located on the center pedestal, controls the displayed information.

Engine indications are provided on the EICAS primary page. Color is used to depict normal and non-normal ranges of operation.

The Crew Alerting System (CAS) provides visual and aural alerts as determined by the Data Concentrator Unit (DCU) upon occurrence of a malfunction. The CAS prioritizes messages by order of occurrence and order of importance.

Components and Operation

EICAS Control Panel

The EICAS control panel is located on the center pedestal. The panel remains illuminated during a complete AC power failure and the PRI, STAT, STEP and CAS keys remain operational.

EICAS Displays

The EICAS displays are computer-controlled video displays. EICAS display No. 1 (ED 1) is installed on the left of the center instrument panel and EICAS display No. 2 (ED 2) is installed on the right of the center panel (Figure 3-1).

The EICAS displays present system information on primary, status, synoptic and menu pages. ED 1 displays the primary page by default. ED 2 is defaulted to the status page. Page selection is accomplished via the ECP (Figure 3-2).


3-4 For Training Purposes OnlyMay 03


Data Concentrator Unit (DCU)

The data concentrator unit is the heart of the EICAS. The DCU collects data from various aircraft systems, processes the information and relays it to the proper component or display. In a standard configuration, there are two DCUs installed in the aircraft. They are designated DCU 1 and DCU 2. An optional third DCU can be installed and is labeled DCU 3 as per service bulletin 604-31-001.

All DCUs share in providing information to the EICAS displays. Internal switching logic determines how the information is provided by the two or three DCUs. If a partial or complete failure of a DCU occurs, system redundancy ensures that no displayed data is lost. In aircraft with the optional third DCU, an additional level of redundancy is provided.

Data concentrator units receive inputs from the following systems:

• Engines• Landing gear• Flaps• Spoilers• Auxiliary Power Unit (APU)• Flight controls• Avionics• Stall Protection System• Ground Proximity Warning System (GPWS)• Traffic Alert and Collision Avoidance System (TCAS)• Crew Alerting System (CAS)• Air Data Computer (ADC) altitude alerting

The DCUs process and format this information then transmit the data on the ARINC bus to the following:

• EICAS displays• Lamp Driver Unit (LDU)• Audio Electronic Control Unit (AECU)• Flight Data Recorder (FDR)• Maintenance Diagnostic Computer (MDC)

The two-channel lamp driver unit receives information from the DCUs and controls the associated panel and glareshield switch/light illumination.

When a DCU generates an EICAS message, the data is sent to the LDU. The LDU then interprets the information and illuminates the switch/light on the appropriate control panel.



3-5


Should one channel of the LDU fail, the remaining channel continues to operate. Testing the LDU and panel lamps is accomplished by using the test switch located on the miscellaneous test panel. The three-position LAMP TEST switch is spring-loaded to the center OFF position. Holding the switch to position 1 or 2 tests the associated LDU channel and lamps.

AC power is required to perform the lamp test.

NOTE




Controls and Indicators

Master Warning Switch/LightsThe master warning switch/lights are located on the glareshield. When the DCUs generate a warning message, the two master warning switch/lights flash red. A triple attenson always accompanies the master warning lights and, in addition, dedicated tones or voice messages may sound.

When the switch/light is pressed, the flashing red light and the audio alerts are reset.

Master Caution Switch/LightsThe master caution switch/lights are located on the glareshield. When the DCUs generate a caution message, the two master caution switch/lights flash amber. A single attenson always accompanies the master caution lights.

When the switch/light is pressed, the flashing amber light is reset.

Master Warning and Caution Lights Figure 3-3

LH ENGFIREPUSH

GPWSTERRINHB

MASTERWARNING BOTTLE 1

ARMEDPUSH TO

DISCH

STALLMASTERCAUTION

PULL UP

GND PROX

ATS

N2 SYNC

ATS

N1 TO

FAIL

ATS

N1 TO

FAIL

APUFIREPUSH

RH ENGFIREPUSH

GPWSTERRINHB

MASTERWARNINGBOTTLE 2

ARMEDPUSH TO

DISCH

BOTTLEARMED

PUSH TODISCH

STALLMASTERCAUTION

PULL UP

GND PROX

RIGHT GLARESHIELD

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LEFT GLARESHIELD



3-7


Aural Warning TestingA two-position spring-loaded to neutral AURAL WARN TEST switch is located on the miscellaneous test panel. The switch is used to test the audio outputs of the DCUs.

When the switch is selected to position 1 or 2 and released, DCU 1 or DCU 2 aural and voice warnings are sounded sequentially. When the switch is selected again, the test is interrupted.

AURAL WARN / LAMP TEST Panel Figure 3-4

Aural Warning Test Sounds Table 3-1

SOUND INDICATION

WARBLER STALL

FIRE BELL FIRE WARNING

CLACKER VMO / MMO, FLAP OVERSPEED

CLACKER “DRUM ROLL” EXCESSIVE STAB TRIM MOVEMENT

CAVALRY CHARGE AUTOPILOT DISCONNECT

HORN GEAR NOT DOWN

C-CHORD ALTITUDE ALERT

DOUBLE C-CHORD VERTICAL TRACK ALERT

TRIPLE ATTENSON PRECEDES ANY WARNING MESSAGE

SINGLE ATTENSON PRECEDES ANY CAUTION MESSAGE

VOICE VOICE WARNINGS

P6

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3_

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4

AURALWARN TEST

LAMPTEST

1

2

1

2




Aural Alert DisableTwo (third optional) DISABLE switch/lights, located on the AUDIO WARNING panel on the copilot side console, are used to disable and silence the aural warnings of a malfunctioning DCU. When DCU 1 is selected to DISABLE, DCU 2 will provide the aural warning function. When both DCU 1 and 2 are disabled, the optional DCU 3 (if installed) provides the aural warnings. The ground proximity warning system (GPWS) and the traffic alert and collision avoidance system (TCAS) aural warnings are not disabled by selections at the audio warning panel.

DCU Disable Controls Figure 3-5

In order to test DCU 3 audio warnings, DCU 1 or 2 must be disabled from the audio warning disable panel.

EICAS Control Panel

PRI

Selecting PRI causes the primary page to be displayed on ED 1.

STAT

Pressing the STAT button causes the status page to be displayed on ED 2. If the status page is already displayed, the button will remove the status message(s) and display a white MSGS icon. Pressing the STAT a second time will cause the status message(s) to reappear. DCU generation of a new status message will remove the MSGS icon and the new status message will be displayed on the top of the status message stack.

NOTE

DCU 1 DCU 2 DCU 3

AUDIO WARNING

DISABLEDISABLEDISABLE

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3-9


STEP

The STEP button will sequentially step through all available pages, including primary, secondary and synoptic. There are four synoptic pages. Synoptic pages use a schematic format that includes relevant system operating parameters. Three synoptic buttons can access the synoptic pages directly.

HYD

Selecting the HYD synoptic button displays the hydraulic system.

ELEC

Selecting the ELEC synoptic button displays the AC electrical system. Selecting the button a second time displays the DC electrical system. Further selections will alternately cycle through the AC and DC pages.

CAS

During flight or on the ground when both engines are stabilized at idle, it is possible to remove the displayed caution message(s) from the primary page. Selecting the CAS button will remove the caution messages and display a white MSGS icon. Pressing the CAS button a second time will cause the caution message(s) to reappear. If a new caution is generated, the MSGS icon will be removed and the new message will be displayed on the top of the caution message stack.

F/CTL

Selecting the F/CTL synoptic button displays the flight control system.

EICAS Control Panel Figure 3-6

PRI STAT STEP CKLST RCL EMER

HYD ELEC LMFD

RMFD

SEL/AUTO

CAS F/CTL SKP/3D

UP/PLAN

DN/SIDE

M

P6

04

_0

3_

00

2




EICAS Primary PageED 1’s default display is the EICAS primary page.

Engine Indications

Engine indications are presented in both traditional analog gauge format and digital readouts. Displayed engine parameters include:

• N1 speed gauge• N1 Takeoff thrust setting• Inter-Turbine Temperature (ITT) gauge• N2 speed gauge• fuel flow• oil pressure• oil temperature• fan vibration

Fuel Quantity

In the bottom left-hand corner of the primary page, EICAS provides the pilot with a summary of current fuel quantities. This includes the individual main tank quantities, the auxiliary tank system total quantity, the tail tank system total quantity and the aircraft’s total fuel quantity readout.

Crew Alerting System Messages

Warning and Caution messages are presented only on the EICAS primary page.

Cabin Pressurization

Cabin pressurization data is displayed on the primary page when the pressurization control (PRESS CONT) switch is selected to MANUAL on the Cabin Pressurization control panel. This function is further explained in the Air Conditioning/Pressurization chapter.

Landing Gear and Flaps

Landing gear and flap position information is presented on the EICAS primary page. During flight, the landing gear and flap information is removed from view after 30 seconds when both of the following conditions exist:

• landing gear is up and locked• flaps are up



3-11


Landing Gear Horn

A landing gear horn will sound if certain parameters are not met with respect to combinations of altitude, speed, flap and power lever positions. (See Chapter 15 Landing Gear and Brakes)

Trim Settings

Aileron, horizontal stabilizer and rudder trim settings are continuously displayed on the primary page.

EICAS Primary Page Figure 3-7

BRTBRT

85.0 85.0

95.0

HOT

750 750

N190.0

ITT

N2

GEAR DISAGREEAUTO PRESS

DN DN DN

- GEAR - - FLAPS -

C ALT

STAB

RATE

- TRIM -

P

3100 2000 3.0

20

NU

ND

4.0

RUDDER

AIL

RWDLWD

NRNL

FF

OIL PRESS

OIL TEMP

FAN VIB

7160 4870

20000

1.2

115

82

3500

3140

- FUEL QTY - TOTAL

3500

82

115

1.2

4870

PressurizationIndications(in MANUALmode only)

FuelQuantityIndications

GEAR and FLAPIndications

EngineIndications

P6

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75.0

VIB

REV APR

TrimDisplay




EICAS Status Page Displays Figure 3-8

113405

V

HZEXTAC

AC ELECTRICAL

UTIL BUS 1

GEN2

SHEDSHED

AUTOXFEROFF

GEN1

AUTOXFERFAIL

APU

BUS 1

UTIL BUS 2

000

KVAVHZ

GEN

00

V

HZADG

ESS BUS

15115400

KVAVHZ

000

KVAVHZ

BUS 2

AC ELECTRICAL

BRTBRT

Advisory EICASMessages

OxygenPressure

CabinAltitude

Cabin Rate

Cabin Diff.SpoilerDeploymentIndication

L and R 10th-Stage BleedAir Pressure

FuelTemperature

Flight SpoilerIndicatorIndicatesrelative spoilerposition

Ground SpoilerIndicator

CabinTemperature

WING A/ICE OKT/O CONFIG OKL FUEL PUMP ONR FUEL PUMP ONHYD SOV1 CLSDHYD SOV2 CLSDPARKING BRAKE ONAC UTIL 1 OFFFUEL CH 1 FAILYD 1 INOP

CABIN TEMP

BLEED PRESS

FUEL TEMP

ENGINE

BULK

OXY

C ALT

RATE

P

502050

40 30

-20

1850

200

0

-0.5SPOILERS

APU

95 430

RPM EGT

P6

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3_

00

7

FLIGHT CONTROLS

FLAPS 30

FLAPS MOTOR OVERHEAT

AIL AIL

RUDDER

YAW DAMPERSTAB TRIM CH1 INOP

ELEV ELEV

FLIGHT CONTROLS

DC ELECTRICAL

TRU 1

V

A

2818

TRU 2

V

A

2818

2711

V

A

V

A

2711

240

V

A

240

V

A

ESSTRU 2

APUBATT

MAINBATT

ESSTRU 1

BUS 1

BUS 2

UTIL BUS 1

UTIL BUS 2

EMER BUS

APU BATTDIR BUS

MAIN BATTDIR BUS

AC BUS 1 AC BUS 2AC ESS

BUS

CHGR OFF

TIE

ESS BUS

BATT BUS

DC ELECTRICAL

1B 3A 3B 2B

3050PSI

3000PSI

2950PSI

INBDBRAKES

PSI3000

OUTBDBRAKES

PSI3000

80 °C 15 °C

RUDDERL ELEVATORL AILERONFLT SPLRGND SPLR

RUDDERL ELEVATOR RL AILERON RLNDG GEARN/W STEERNOSE DOOR

RUDDERELEVATOR RAILERON RFLT SPLR

MLG AUX ACT

1A 2A

49%

HYDRAULIC

95 °C

82% 76%

HYDRAULIC

Status EICASMessages

APU RPM andEGT Indicators



3-13


EICAS Status PageThe status page is the default display of ED 2.

Crew Alerting System Messages

Advisory and status messages are presented only on the EICAS status page.

Flight Spoilers

When deployed, the flight spoilers’ extension will be presented at the bottom left-hand corner of the EICAS status page. When retracted, the display disappears.

Auxiliary Power Unit

The APU RPM and EGT gauges are displayed on the EICAS status page when the APU PWR FUEL switch is selected.

Cabin Temperature

The cabin temperature is displayed in degrees Celsius.

Bleed Air Pressure

The bleed air pressure of the left and right 10th-stage manifold is indicated in pounds per square inch (psi).

Fuel Temperature

The fuel temperatures at the engines and in the left main tank (bulk) is provided in degrees Celsius.

Oxygen Pressure

The gaseous oxygen pressure is continuously displayed on the status page. Green indicates normal pressure and amber identifies pressure below 800 psi.

Cabin Pressurization

Cabin pressurization is displayed on the status page. The information includes:

• cabin altitude in feet• rate of climb or descent in feet/minute• differential pressure in psi




Synoptic Pages

Synoptic pages are normally displayed on ED 2. In cases of ED 2 failure or crew preference, they can also be displayed on ED 1 or on a MFD.

The synoptic pages provide the pilot with real-time interpretation of aircraft hydraulic, electrical and flight controls system operation. Color logic is used to depict normal, precautionary and maximum system limit as follows:

• normal range, indication is green• precautionary range, the system indicator turns amber• exceeds the limits, the indicator turns red

Flow lines are used on a number of synoptic pages. Although not all pages will display the four colors, generally the color logic is as follows:

• black, indicates no flow• amber, indicates below normal values• green, indicates normal value• red, indicates exceeding normal values

EICAS MessagesThe Crew Alerting System (CAS) provides visual and aural alerts when the DCUs detect a malfunction. The CAS prioritizes messages by order of occurrence and categorizes them by importance as follows:

• order of occurrence: The most recent message appears on the top of its message category

• order of importance: There are four levels of CAS message importance: Warning, Caution, Advisory and Status

Warning Messages

The most urgent messages are called Warnings and are red in color. Warning messages are presented on the top of the primary page and remain in view until the problem is resolved.

Warning messages require immediate action and are always accompanied by:

• a triple attenson• flashing master warning lights• red light on the faulted control switch or a red indication on EFIS, EICAS, or a

synoptic page

Warning messages, in addition to the above indications, can also generate one or both of the following:



3-15


• aural warning tone• voice message

Pressing either master warning switch/light:

• silences the aural alerts• stops the master warning lights from flashing• resets the switch/light to allow it to indicate another fault

Caution Messages

Caution messages are second in order of importance. Caution messages are presented in amber on the primary page and appear directly below any warning messages that may be displayed. It is possible to have more than one page of caution messages. The CAS pushbutton on the ECP allows the pilot to page forward and backward to view the entire list of caution messages. During flight or on the ground when both engines are stabilized at idle, caution message(s) can be removed from view or recalled to the screen by pressing the CAS key on the ECP. A white MSGS icon will appear, advising the crew that the caution message(s) are out of view. Pressing the CAS button a second time will cause the caution message(s) to reappear. DCU generation of a new caution message will remove the MSGS icon and the new message will be displayed on the top of the caution message stack.

Caution messages require prompt action and are always accompanied by:

• a single attenson• flashing master caution lights• amber light on the faulted control switch or an amber indication on EFIS, EICAS,

or a synoptic page

Pressing either master caution switch/light:

• stops the flashing of the master caution lights• resets the master caution switch/light to allow it to annunciate another fault

Advisory Messages

Green advisory messages are presented at the top of the status page. Advisory messages cannot be removed from view until the cause is deselected or deactivated. Advisory messages are used to advise of:

• aircraft configuration for a particular phase of flight• successful system test• confirmation of SOV closure• SELCAL


3-16 For Training Purposes OnlyJan 04


Status Messages

White status messages are presented on the status page and appear directly below any advisory messages that may be present. Status message(s) can be removed from view or recalled to the screen by pressing the STAT key on the ECP. A white MSGS icon will appear, advising the crew that the status message(s) are out of view. Pressing the STAT button a second time will allow the status message(s) to reappear. DCU generation of a new status message will remove the MSGS icon and the new message will be displayed on the top of the status message stack. Status messages are used to inform of:

• status of a specific system that has been manually or automatically activated/deactivated

• low-priority system failures

Takeoff Configuration WarningThe Takeoff Configuration Warnings are armed on the ground when both engines accelerate as a result of thrust levers being advanced above 70% N1. A voice warning, an EICAS warning message and flashing red Master Warning annunciators are provided for any of the following conditions:

All TOC warnings are canceled when the configuration error is corrected.

Inhibited EICAS Caution MessagesDuring takeoff and landing, the DCU logic inhibits distracting EICAS caution messages. The logic inhibits messages during takeoff when the left and right engine N1 are greater or equal to 79% and above 80 kts with weight-on-wheels. On landing, the messages are inhibited when radio altitude is less than 400 feet above ground level (AGL) with landing gear extended.

CONDITION VOICE WARNING EICAS MESSAGE MASTER WARNING

AUTOPILOT ENGAGED “CONFIG AUTOPILOT” CONFIG AP FLASHES

FLAPS NOT SET FOR TAKEOFF “CONFIG FLAPS” CONFIG FLAPS FLASHES

ALL SPOILERS NOT IN TAKEOFF POSITION “CONFIG SPOILERS” CONFIG SPOILERS FLASHES

HORIZONTAL STAB NOT IN T/O RANGE “CONFIG TRIM” CONFIG STAB FLASHES

PARKING BRAKE SET “CONFIG BRAKES” PARKING BRAKE FLASHES

Takeoff Configuration Warnings Table 3-2


For Training Purposes OnlyJan 04

3-17


The inhibit logic is removed when:

• left and right engine N1 are less than 67.6%; or• radio altitude is greater than 400 feet AGL with the landing gear extended; or• 30 seconds after the inhibit starts; or• 30 seconds after the air-to-ground transition

Caution messages and their associated aural alerts that are NOT inhibited during takeoff and landings are shown in the following table.

AIRPLANE SYSTEM CAUTION MESSAGE NOT INHIBITED TAKEOFF LANDING

POWER PLANT

APR INOP √ √

APR CMD SET √

L (R) REV UNLOCKED √ √

L (R) REV UNSAFE √ √

AUTOMATIC FLIGHT CONTROL SYSTEM

AP TRIM IS LWD (RWD) (ND) (NU) √

AP PITCH TRIM √

YAW DAMPER √

FIRE PROTECTIONAPU BTL LO √

ENG BTL 1 (2) LO √

FLIGHT CONTROLS

ELEVATOR SPLIT √ √

FLAPS FAIL √

FLT SPLRS √

FLT SPLRS DEPLOY √

GND SPLRS √

GND SPLRS DEPLOY √ √

GND SPLRS NOT ARMED √

STAB TRIM √

FUELFUEL IMBALANCE √

L (R) FUEL LO PRESS √ √

HYDRAULICS HYD 3 LO PRESS √

INSTRUMENTS EFIS COMP MON √ √

LANDING GEAR

A/SKID INBD (OUTBD) √ √

INBD (OUTBD) BRAKE PRESS √ √

PROX SYS √

STEERING INOP √

WOW INPUT OR OUTPUT √

Caution Messages Not Inhibited during Takeoff and Landing Table 3-3




Display Reversionary Control

EICAS Reversionary Mode

The EICAS reversionary mode provides an alternate method of displaying EICAS information should ED 1 or ED 2 fail.

In the event of ED 1 failure, the primary page is automatically transferred to ED 2. This automatic feature ensures that engine indications and warning and caution messages are always available to the pilot. There is no automatic transfer of status page information should ED 2 fail.

Display Reversionary Control Panel

The display reversionary control panel is located on the center pedestal. The reversionary selector switches (L MFD, EICAS, R MFD) are used when a malfunction exists.

The L MFD and R MFD reversionary switches are identical, and have three positions designated as PFD, NORM and EICAS. In EICAS position, the status-page information is displayed by default on the MFD.

The EICAS reversionary selector is also a three-position switch designated as NORM, ED 1 and ED 2. In the NORM position, normal EICAS display is represented on ED 1 and ED 2. When the selector is moved to either ED 1 or ED 2 position, the opposite ED is disabled and blanked while the primary and secondary information is available on the selected display.

PFD Reversionary Mode

When a primary flight display (PFD) fails, the information can be transferred to the associated MFD. The L (R) MFD rotary knob on the display reversionary control panel, when selected to the PFD position, effects the transfer.

MFD Reversionary Mode

There is no reversionary mode for the data normally presented on the multifunction displays (MFDs).



3-19


Display Reversionary Control Panel Figure 3-9

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VFE (45 FLAPS)VFE (30 FLAPS)VFE (20 FLAPS)VA (MANEUVERING)(AT SEA LEVEL 48,200LB)(AT 20,000FT 26,000LB)VNO (BELOW 8,000FT)VNO (8,000 TO 22,150 FT)

AIRSPEED LIMITS - (INDICATED SPEEDS)

MMO (22,150FT TO 26,570FT)VMO (26,570FT TO 30,990FT)MMO (30,990FT TO 41,000FT)VLO (EXT) (L/G EXTENSION)VLO (RET) (L/G RETRACTION)VLE (L/G EXTENDED)

189197231

248187300348

0.783180.85197197250

P

UL L

P

UL L

TO

C A G

E

C A G

E

CLI MB

DI VE

OFF

BRT

BRT

BRT

0.0

0.0

0.0

0.0

180 180

N1

ITT

N2

STAB- TRIM -

NU

ND

5.0

RUDDER

AIL

RWDLWD

NRNL

FF (PPH)

OIL PRESS

OIL TEMP

FAN VIB

0 4050

81000.0

33

0

0

0

- FUEL (LBS) - TOTAL

0

0

33

0.0

4050

DN DN DN

- GEAR - - FLAPS - 20

R ENG OIL PRESSL ENG OIL PRESSL WSHLD HEATL WINDOW HEATINBD BRAKE PRESSR WSHLD HEATR WINDOW HEATOUTBD BRAKE PRESSR PROBE HEAT OFFL PROBE HEAT OFFHYD 3 LO PRESS

BRT

CABIN TEMP

BLEED PRESS

FUEL TEMP

ENGINE

BULK

OXY

C ALT

RATE

P

47

23

0

36 35

1820

100

0

0.0

APU

100 323

RPM EGT

R FUEL PUMP ONL FUEL PUMP ONDOOR CLOSEDPARKING BRAKE ONPROX SYS FAULTFDR FAIL

SPOILERS

15

2 000234

ALT

0

7 3

2

1

4

9

6 29925

1014

400

350

300 250

200

150

10060

KTS

IAS

FEET

X 1000

CABIN

ALTITUDE

0

4

2

68

10

20

30

45

BRT

BRT

80

60

20

00

20

10

10

20

300

200

100

100

000

80004

RA2IRS2ADC2DCP2

TERM

VOR1

TRU

NO FLIGHT PLAN

TCASOFF

29.92 IN

2400M

GSRA

TOLOC 1

DR TOALTS

FMS1

12DTK 333

.7YUL

NM

4

4

2

2

1

1

2500M200

N33 1

512

E6

3

0

3000

40

VT 150

V2 133

VR 121

V1 113

ADF2

0FT

2

1




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60

20

00

20

10

10

20

300

200

100

100

000

80004

RA2IRS2ADC2DCP2

VOR1

TRU

TCASOFF

29.92 IN

2400M

GSRA

TOLOC 1

DR TOALTS

4

4

2

2

1

1

2500M200

0

3000

40

VT 150

V2 133

VR 121

V1 113

ADF2

0FT

2

1

FMS2

12DTK 056

.2LONNA

NM

TERM

N33 1

512

E6

3

CABIN TEMP

BLEED PRESS

FUEL TEMP

ENGINE

BULK

OXY

C ALT

RATE

P

47

23

0

36 35

1820

100

0

0.0

APU

100 323

RPM EGT


SPOILERS

15

PFD EICASNORM

L MFD

EICAS PFDNORM

R MFD

ED1

ED2

NORMEICAS

D EIC2

AS PF

PFD EICASNORM

L MFD

1 2

NORMADC

1 2

NORMDCP

EICAS PFDNORM

R MFD

ED1

ED2

NORMEICAS

2

D EIC2

AS PF

2

REVERSIONARY SELECTORS -DISPLAY REVERSIONARY CONTROL PANEL

Display ReversionarySelector must be selectedto display PFD on MFD




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UL L

P

UL L

TO

C A G

E

C A G

E

CLI MB

DI VE

OFF

BRT

BRT

BRT

0.0

0.0

0.0

0.0

180 180

N1

ITT

N2

STAB- TRIM -

NU

ND

5.0

RUDDER

AIL

RWDLWD

NRNL

FF (PPH)

OIL PRESS

OIL TEMP

FAN VIB

0 4050

81000.0

33

0

0

0


0

0

33

0.0

4050

DN DN DN



BRT

CABIN TEMP

BLEED PRESS

FUEL TEMP

ENGINE

BULK

OXY

C ALT

RATE

P

47

23

0

36 35

1820

100

0

0.0

APU

100 323

RPM EGT


SPOILERS

15

2 000234

ALT

0

7 3

2

1

4

9

6 29925

1014

400

350

300 250

200

150

10060

KTS

IAS

FEET

X 1000

CABIN

ALTITUDE

0

4

2

68

10

20

30

45

BRT

BRT

80

60

20

00

20

10

10

20

300

200

100

100

000

80004

RA2IRS2ADC2DCP2

TERM

VOR1

TRU

NO FLIGHT PLAN

TCASOFF

29.92 IN

2400M

GSRA

TOLOC 1

DR TOALTS

FMS1

12DTK 333

.7YUL

NM

4

4

2

2

1

1

2500M200

N33 1

512

E6

3

0

3000

40

VT 150

V2 133

VR 121

V1 113

ADF2

0FT

2

1




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60

20

00

20

10

10

20

300

200

100

100

000

80004

RA2IRS2ADC2DCP2

VOR1

TRU

TCASOFF

29.92 IN

2400M

GSRA

TOLOC 1

DR TOALTS

4

4

2

2

1

1

2500M200

0

3000

40

VT 150

V2 133

VR 121

V1 113

ADF2

0FT

2

1

FMS2

12DTK 056

.2LONNA

NM

TERM

N33 1

512

E6

3




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UL L

P

UL L

TO

C A G

E

C A G

E

CLI MB

DI VE

OFF

BRT

059

WX + TRBUTC TAS GS TAT11:01 0 0 15 C

VOR 1 ADF 2

VOR1YULTTG--:--

CRS 01212.7NM

SAT 15 C

FMS2LONNA

DTK05612.2 NMTTG --:--

33

30

21

S15

12

6

3

N

E

W

24

BRT

BRT

0.0

0.0

0.0

0.0

180 180

N1

ITT

N2

STAB- TRIM -

NU

ND

5.0

RUDDER

AIL

RWDLWD

NRNL

FF (PPH)

OIL PRESS

OIL TEMP

FAN VIB

0 4050

81000.0

33

0

0

0


0

0

33

0.0

4050

DN DN DN



BRT

CABIN TEMP

BLEED PRESS

FUEL TEMP

ENGINE

BULK

OXY

C ALT

RATE

P

47

23

0

36 35

1820

100

0

0.0

APU

100 323

RPM EGT


SPOILERS

15

2 000234

ALT

0

7 3

2

1

4

9

6 29925

1014

400

350

300 250

200

150

10060

KTS

IAS

FEET

X 1000

CABIN

ALTITUDE

0

4

2

68

10

20

30

45

BRT

BRT

80

60

20

00

20

10

10

20

300

200

100

100

000

80004

RA2IRS2ADC2DCP2

TERM

VOR1

TRU

NO FLIGHT PLAN

TCASOFF

29.92 IN

2400M

GSRA

TOLOC 1

DR TOALTS

FMS1

12DTK 333

.7YUL

NM

4

4

2

2

1

1

2500M200

N33 1

512

E6

3

0

3000

40

VT 150

V2 133

VR 121

V1 113

ADF2

0FT

2

1

CYUL

TOC

ALEXS

3

059

N

E

12

25

WX+TRB

UTC TAS GS TAT11:01 0 0 SAT 15 C 15 C

VOR 1 FMS MAP ADF 2

CYULLONNAALEXSCYUL

1NM12NM20NM

111NM

0:030:040:23

11:0211:0511:0711:25 7137LB 35.6GM

12.5

DME 1

YUL12.7

DME 2–– – –

LONNA




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60

20

00

20

10

10

20

300

200

100

100

000

80004

RA2IRS2ADC2DCP2

VOR1

TRU

TCASOFF

29.92 IN

2400M

GSRA

TOLOC 1

DR TOALTS

4

4

2

2

1

1

2500M200

0

3000

40

VT 150

V2 133

VR 121

V1 113

ADF2

0FT

2

1

FMS2

12DTK 056

.2LONNA

NM

TERM

N33 1

512

E6

3

PFD EICASNORM

L MFD

EICAS PFDNORM

R MFD

ED1

ED2

NORMEICAS

D EIC2

AS PF

Display ReversionarySelector must be selectedto display EICAS on MFD




Maintenance Diagnostic Computer

Description

The maintenance diagnostic computer (MDC) is an onboard computer that is used to record aircraft mechanical and avionics system data. Maintenance personnel can retrieve the information for use in engine trend analysis, significant event recording and for avionics/aircraft system failure detection.

Operation

The MDC continuously records data for fault analysis and engine trend monitoring. The MDC data is downloadable to a maintenance facility computer.

MDC data is available on the flight deck by means of a red guarded switch on circuit breaker panel number one (CBP 1). Data can be displayed on MFD 1 or MFD 2, as determined by switch selection. Instructions on MDC data presentation are displayed on the selected MFD.

Maintenance Diagnostic Computer Switch Figure 3-10

P6

04

_0

3_

00

8

7.5

POWER MUST BE OFF BEFORE OPENING PANEL CBP-1

R

S

T

TEST

NORM

OFF

MAINT ADSHC

MFD 1

MFD 2

FIREEXT 2

R ENGR ENG

R ENG

FIREEXT 1

APUFIREEXT

PWRSENSE

FEED

L ENGL ENG

R ENGL ENG L ENG

28 VDC EMERGENCY BUS

28 VDC EMERGENCY BUS

APU

FUEL SOV HYD SOV

1

1

1

2

2

2

3

3

3

4

4

4

5

5

5

6

6

6

7

7

7

203 333

3

3

7.5 7.5 7.57.5

CIRCUIT BREAKER PANEL CBP - 1(LOWER)

MFD Guarded Switch



3-21


Flight Data Recorder

Description

The flight data recorder (FDR) records aircraft flight parameters. The FDR system includes a digital FDR, an underwater locator device (ULD) and a triaxial accelerometer. (See also Chapter 6 Communications)

Components and Operation

The FDR is located in the aft equipment bay and records the last 25 hours of flight data in a solid-state memory. The FDR is specially constructed to survive the shock of an aircraft crash. It is automatically turned on when the right engine start switch is pushed.

FDR EVENT Switch

The FDR EVENT switch is located on the PASS SIGNS and EMER LTS panel. When the FDR EVENT switch is pushed, the DCUs place a marker into the FDR memory for quick data retrieval of the recorded event. A green advisory message FDR EVENT is then displayed on the secondary EICAS page.

FDR EVENT Switch Figure 3-11

PASS SIGNS EMER LTS

NO SMKG SEAT BELTS

ONOFFARM

FDREVENT

ONOFFAUTO

ONOFFAUTO

OA A

P6

04

_0

3_

01

0




EICAS Messages

MESSAGE MEANING

EICAS COMP INOP EICAS comparator inoperative (N1, N2 or ITT data comparison not active).

FDR EVENT FDR EVENT marker switch pushed and FDR installed.

CAS MISCOMP Valid XTALK labels from another DCU are available, and a miscompare for any warning, caution, or aural messages exists for more than 20 seconds.

DCU 1, 2, (3)* AURAL INOP DCU 1, 2, (3) * aural warning card fault/fault detection, or DCU 1, 2, (3)* AUDIO WARNING DISABLE switch/light input open.

DCU 1, 2, (3)* INOP DCU 1, 2, (3) * fault detected.

FDR FAIL Indicates flight data recorder failure.

* = if installed

EICAS Messages Table 3-4

PILOT TRAINING GUIDE AURAL/VISUAL WARNING · List of Figures Graphic Title Figure For Training...

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Transcript of PILOT TRAINING GUIDE AURAL/VISUAL WARNING · List of Figures Graphic Title Figure For Training...