B767 ATA 31 Student Book

7/23/2019 B767 ATA 31 Student Book

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TRAINING MANUALFOR TRAINING PURPOSES ONLY

B767-3S2F ATA 31-40Page - 1 11/20/14 EFF - ALL

CH 31

INSTRUMENTS


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TABLE OF CONTENTS

EICAS GENERAL.................................................................................. 4

OPERATIONAL AND STATUS MODE SWITCHING............................ 6

EICAS COMPONENT LOCATIONS...................................................... 8

EICAS INTERFACE DIAGRAM........................................................... 10

EICAS MESSAGE LEVELS................................................................. 12

LEVEL A WARNING MESSAGES AND INDICATION...........................14

LEVEL B CAUTION MESSAGES AND INDICATION............................16

LEVEL C ADVISORY MESSAGES AND INDICATION.........................18

LEVEL E COMM MEDIUM MESSAGES AND INDICATION.................20

LEVEL F COMM LOW MESSAGES AND INDICATION........................22

EICAS - DISPLAY SELECT PANEL.................................................... 24

PRIMARY ENGINE DISPLAY AND SECONDARY DISPLAYS .......... 26

STATUS PAGE DISPLAY SELECT .................................................... 28

STATUS PAGE.................................................................................... 30

EICAS MESSAGE LEVELS................................................................. 32

MAINTENANCE CONTROL PANEL FUNCTIONS ............................. 34

EICAS MEC COMPONENTS .............................................................. 36

ECS/MSG DISPLAY FORMAT............................................................ 38

ELEC/HYD DISPLAY FORMAT .......................................................... 40

PERF/APU DISPLAY FORMAT ........................................................... 42

CONF/MCDP DISPLAY FORMAT....................................................... 44

ENG EXCD DISPLAY FORMAT.......................................................... 46

EPCS DISPLAY FORMAT................................................................... 48

EICAS - AUTO EVENT RECORD..........................................................50

EICAS - AUTO EVENT READ................................................................52

EICAS - MANUAL EVENT RECORD.....................................................54

EICAS - MANUAL EVENT READ...........................................................56

EVENT DATA ERASE...........................................................................58

LATCHED MESSAGES / ERASE PROCEDURE..................................60

EICAS - MESSAGE TABLE...................................................................62

EICAS - BITE OPERATIONAL FEATURES........................................ 64

EICAS - TEST COMPLETION............................................................. 66

EICAS - BITE SELECTION.................................................................. 68

EICAS - BITE TEST OPERATION ...................................................... 70

EICAS - OPC SOFTWARE CROSSLOAD.......................................... 72

STANDBY ENGINE INDICATOR ........................................................ 74

FLIGHT DATA RECORDER (FDR) SYSTEM ..................................... 76

WARNING ELECTRONICS SYSTEM - INTRODUCTION .................. 78

WARNING ELECTRONICS UNIT (WEU)............................................ 84

TAKEOFF CONFIGURATION WARNING........................................... 88

LANDING CONFIGURATION WARNING SYSTEM............................ 92

AIRCRAFT CONDITION MONITORING SYSTEM (ACMS) ............... 94

ACMS COMPONENT LOCATION....................................................... 96

DIGITAL DATA INPUTS ...................................................................... 98

MCDU FUNCTIONS / DISPLAY SUMMARY..................................... 100

MIDU................................................................................................... 102
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STUDENT NOTES:


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EICAS GENERAL

Purpose

A color display system that displays Engine Data and Warning, Caution,

Advisory, Status and Maintenance Messages for accurate and rapidinterpretation by the Flight and Ground Crews.

System Description

Input signals supplied from airplane sensors and the Display Select Panel are

processed by EICAS computers. EICAS computer output signals are routed

through the Switching Module to drive the Upper and/or Lower Display Units.

Cathode Ray Tube Display Unit Features

The Cathode Ray Tube (CRT) display units have a black background color anddisplays seven colors defined as follows:

White - general color used for all scales, normal operating range of

pointers, digital readouts and digital readout boxes

Red - used for Warning Messages, red-line limits on scales, exceedance

condition for pointers, digital readouts and digital readout boxes

Green - used for thrust mode readout, N1target cursor and reverse thrust

readouts

Blue - not used for any EICAS displays

Yellow - used for Caution And Advisory Messages, yellow-band on scales,

yellow-band condition for pointers, digital readouts, and digital readout

boxes Magenta - used for in-flight start envelope, windmilling cursor, cross bleed

message and the N1target cursor when controlled by the FMC

Cyan - used for all parameter names, status cue, total air temperature

readout and the secondary engine data cues

Flight Compartment Components

Display Select Panel - Located on Forward Electronics Panel (P9)

Display Units (DU) - Upper And Lower located between Forward Instrument

Panels (P2)

Cancel & Recall Switches - located on Captain's Instrument Panel (P1-3)Standby Engine Indicator (SEI) - located on Captain's Instrument Panel (P1-3)

Master Warning/Caution Lights - located on each end of Glareshield (P7)

Maintenance Control Panel - located on Right Side Panel (P61)

Main Equipment Center Components

Left EICAS Computer (upper) - located on rack E8-1

Right EICAS Computer (lower) - located on rack E8-2

EICAS Switching Modules (2) - located on shelf next to left computer (E8-1)

Interface Components

Warning Electronics Unit (WEU) - located in main equipment center P51 panel

Digital Flight Data Acquisition Unit (DFDAU) located in main equipment center,

rack E2-3


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EICAS GENERAL


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OPERATIONAL AND STATUS MODE SWITCHING

Initial Displays

After power is first applied to the airplane's L and R 115 vac buses, the primary

engine parameters are displayed on the Upper Display Unit (DU) and thesecondary engine parameters on the Lower DU. Alternate displays can be

obtained by utilizing the display select panel's engine or status switches as

described below.

Status Mode Display

Pressing the STATUS switch once causes the Status Mode Display to appear

on the Lower DU. Pressing the STATUS switch once again causes the Lower

DU to blank.

Since the Status Message field is limited to eleven messages per page, there

are situations where more than one page of Status Messagescan exist. In this

case, each actuation of the STATUS switch causes the next page of messages

to be displayed. After all have been displayed, a final actuation of the STATUS

switch causes the Lower DU to blank except for full time fuel flow.

Secondary Engine Parameters

Pressing the ENGINE switch once causes the Lower DU display to change from

a STATUS mode display, or blank display, to the Secondary Engine Parameter

Display. Pressing this switch again causes the Lower DU to blank.

The blank lower display will have full time fuel flow indicated.

The Display Units are interchangeable with the Electronic Horizontal Situation

Indicators.


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OPERATIONAL AND STATUS MODE SWITCHING


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EICAS COMPONENT LOCATIONS

Flight Deck Components

EICAS display units (upper and lower) - located on the P2 panel between the

Captain's and First Officer's instrument panels (P1 & P3).EICAS Display Select Panel - located on the forward electronics panel (P9).

Master Caution Lights/Switches - located on the glareshield (P7).

Cancel And Recall Switches - located on the Captain's P1-3 panel.

EICAS Maintenance Panel - located on the P61 right side panel.

Circuit Breakers - located on the P11 overhead panel.

Main Equipment Center Components

EICAS Computer Units - the left computer is located on E8-1 and the right on

E8-2.

Display Switching Modules (upper and lower) - located on the modules' shelves

beside the computer on the E8-1 rack.

Signal Consolidation Card is located in the P51 card file and converts analog

signals to digital signals which are then sent to the EICAS computers. The

signals handled by the SCC come from the Fuel Quantity Processor unit (FQIS

Processor), FWD Cargo Air Conditioning System, and TCAS.

A Signal Consolidation Card (SCC) failure will result in an EICAS status

message "EICAS SCC".


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EICAS COMPONENTS LOCATIONS


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EICAS INTERFACE DIAGRAM

EICAS Inputs

The EICAS computers receive three types of signals:

Discrete

Analog

Digital Data Bus

Over 400 analog input discretes are supplied in parallel to both computers and

may be grouped into various classifications as follows:

In general, signals sent by airplane subsystems for the generation of

EICAS Messages are analog discrete inputs. These include all Alert,

Status andMaintenance Messages.

THIRTY-two analog discretes are received as program pin inputs. These

program pins define airplane and engine model configuration plus all

customer selected display options.

Digital Data Inputs

Each EICAS computer receives digital inputs in both high and low speed ARINC

429 formats.

EICAS Outputs

Each EICAS computer outputs three types of signals: discrete, analog and

digital data bus.

Inter-computer interface

The two EICAS computers exchange the following three types of information

listed in priority:

After a long term power interrupt, the computer attempts to obtain the

necessary information to synchronize itself with the off-side computer.

Input data not available from its direct input source is obtained from its off-

side computer.

Performing cross-comparisons of its input data with its respective off-sidedata for all analog variable signals, analog input discretes, ARINC 429 bus

activity and the master caution light output discrete. If a disagreement

exists, both computers set the disagree codes on the L/R EICAS test

format.


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EICAS INTERFACE DIAGRAM


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EICAS MESSAGE LEVELS

EICAS Message Levels are:

Level A: Warning red message and light, red master warning lights and

master warning aural (bell or two tone siren). Immediate Crew ActionRequired.

Level B: Caution yellow message and amber light, amber master caution

lights and master caution aural (4 tone beeper). Immediate Crew

Awareness And Future Crew Action.

Level C: Advisory yellow message and amber light, no aural. Crew

Awareness Required, Action As Necessary.

Level E Advisory white message to alert the crew that a communication

function is required.

Level F A comm low message that provides the crew with information

about a particular system that the aircraft uses for either voice or digital

communications.

Alerts above are all displayed on upper display unit are listed in the following

priority: Warning, Caution, then Advisory top to bottom.


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LEVEL A WARNING MESSAGE AND INDICATIONS

Indications

EICAS shows a red warning message when there is a level A warning. At the

same time, warning system signals cause the master WARNING lights to comeon and the firebell or siren aural to come on.

You push one or the other master WARNING light to cause a reset of the

warning system circuit. This puts off the master WARNING lights and stops the

level A aural warnings.

Warning System

The warning system will be covered in more detail later in the chapter and

consists of a Warning Electronics Unit, aural warning loudspeakers, aural

cancel switch, and test switches. It also includes the master WARNING switch-

lights, SPEEDBRAKES light, and discrete warning light.

Input signals are received from airplane sensors, other airplane systems, or

generated by the pilots.

Signals are processed within the Warning Electronics Unit (WEU).


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LEVEL A WARNING MESSAGE AND INDICATIONS


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LEVEL B CAUTION MESSAGE AND INDICATIONS

Indications

These are the flight compartment indications when there is a level B caution:

Yellow EICAS message

Two master CAUTION lights

Beeper tone from the warning system

The level B beeper sound is from the warning system for 0.8 second.

You push one or the other master CAUTION light to cause a reset of the control

circuits for the two master CAUTION lights. This stops the aural warning.


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LEVEL B CAUTION MESSAGE AND INDICATIONS


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LEVEL C ADVISORY MESSAGE AND INDICATIONS

Indications

EICAS shows a yellow message when there is a level C advisory. The

message is one space to the right and below the last level B caution message.

No aural tones or master caution lights come on for a level C advisory.


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LEVEL C ADVISORY MESSAGE AND INDICATIONS


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LEVEL E COMM MEDIUM MESSAGES AND INDICATIONS

General

Comm medium messages show at the bottom of the message field. They are

bottom justified. The messages show in white letters with a white bullet in frontof them.

Operation

Comm medium messages alert the crew that a communication function is

necessary, such as a ground call from the nose landing gear call switch or

similar condition where voice communication is necessary. The crew responds

with the appropriate system.

EICAS sends a chime discrete to the warning unit at the same time it shows the

message. The warning unit causes a single high chime to sound in the flight

deck.

Not all comm messages have chimes.

Indications

Any indicator lights are turned on by the system that provides the input. For

example, the GROUND CALL light is turned on by the crew call system, not

EICAS.


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LEVEL E COMM MEDIUM MESSAGES AND INDICATIONS


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LEVEL F COMM LOW MESSAGE AND INDICATIONS

General

Comm low messages give the crew information about a particular system that

the airplane uses for voice or digital communication.

Operation

Comm low messages show at the bottom of the message field. They are

bottom justified and indented one space. The messages are in white letters

with a white bullet in front of them. They always show below any comm medium

messages.


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LEVEL F COMM LOW MESSAGE AND INDICATIONS


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EICAS - DISPLAY SELECT PANEL

The Display Select Panel

Is the primary unit for both pilots to control EICAS functions and displays. All

controls on this panel can be used in flight and on the ground.

Engine Display Switch

A momentary push switch used to display or remove secondary engine data on

the lower display unit.

Status Display Switch

A momentary push switch used to display or remove the status page on the

lower display unit. It will also advance pages in event of status message page

overflow.

Event Record Switch

A momentary push switch when used records all ECS, ELEC, HYD, PERF &

APU data for storage in manual event nonvolatile memory for recall on the

ground.

Computer Select Switch

A three-position rotary switch for selecting display signal source. In auto, the left

computer is primary signal source. Automatic switching to right computer

occurs when left computer becomes invalid. In the L or R positions therespective computer is the signal source with no automatic switching.

Display Units Brightness Control

Dual concentric controls with the inner control increasing brightness of both

display units when rotated clockwise. The outer control increases the

brightness of the upper display unit and decreases the brightness of the lower

display unit when rotated clockwise. Rotating the outer control

counterclockwise has the opposite effect.

Thrust Reference Index Set Controls

A dual concentric rotary switch combined with a two-way push/pull switch. The

inner control is continuously rotating with twelve detents per revolution. When

pulled out, the Thrust Reference can be manually set. Clockwise rotation of the

control increases the corresponding readout with a rotation sensitivity of 1% perdetent. Once a readout has been modified manually, its last input data will be

retained regardless of the engine selector switch position until the inner control

is reset (pushed in). The outer control is a three-position rotary switch used to

select the LEFT, BOTH or RIGHT Engine. The Thrust Management

(Autothrottle) will not limit engines to a Manually Set limit.

Maximum Indicator Reset Switch

A momentary push switch used to clear maximum exceedance readouts from

the display units. Only that data for which the exceedance no longer exists is

cleared it does not erase engine exceedance data in nonvolatile memory forreadout by maintenance (ENG EXCD page).

Cancel And Recall Switches

Associated with Caution And Advisory Messages only displayed on the upper

display unit. Momentary Cancel Switch when pushed removes Caution and

Advisory Messages currently displayed, or paging capability to display those

stored in memory, that are in excess of 11 messages. Momentary Recall Switch

when pushed re-displays the Caution and Advisory Messages on page 1

removed by the Cancel Switch.


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EICAS - DISPLAY SELECT PANEL


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PRIMARY ENGINE DISPLAY AND SECONDARY ENGINEDISPLAY

General

The operational mode shows the primary and secondary engine parametersand crew alerts necessary on the ground and in flight. This mode gives a

continuous monitor of airplane and engine systems.

The upper display is for primary engine parameters and three levels of alert

messages that automatically show. The lower display shows secondary engine

parameters.

At power-up, all engine parameters show.

Primary Engine Parameters

Primary engine parameters, N1 and EGT, show on the upper display unit (DU)

at all times. The parameters shown are only those necessary to set and monitor

engine thrust. The primary thrust parameter for the General Electric engine is

N1. N1 shows in a digital readout and by an analog pointer. EGT is a thrust

monitoring parameter.

Secondary Engine Parameters

These secondary parameters show for each engine at power-up or when

manually set to show on the lower DU:

N2 Fuel flow

Engine oil parameters

Vibration

When Maintenance pages are shown on bottom display, the upper display unit

will change to compact full format.

Exceedance Conditions

If a parameter gets to an exceedance condition, EICAS shows those engine

parameters in the exceedance color for fast crew attention and response.

These are the exceedance colors and priorities:

Red - highest priority

Yellow - medium priority

White - lowest priority


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FUEL

FLOW

N2

L HYD SYS PRESS

PARKING BRAKE

L YAW DAMPER

RUDDER RATIO

N1

EGT

VIBRATION

ENGINE

FIELD

MESSAGE

ALERT

PARAMETERS

ENGINE OIL

VVVVVVV

0.0

107.1

10

62

EGT

N1

TO

18

BBBB

N2

FF

OIL

OIL

VIB

QTY

TEMP

PRESSOIL

0.0 0.00

0.0 0.0

18

0.0 0.0

0

0.0

107.1

10

62

TAT + 15c

PRIMARYENGINE

PARAMETERS

SECONDARY

ENGINE

PARAMETERS

TAT + 15c

L HYD SYS PRESS

L YAW DAMPER

RUDDER RATIO

20

OIL TEMP

OIL QTY

VIB

OIL PRESS

BB

N

FF

EGT

2

20

0.0

00

20

0.0

00

0.0

00

0.0

PARKING BRAKE

0.0

107.1

10

62

107.1

EGT

N1

TO

0.010

62

BB

2000

UPPER DISPLAY

COMPACT FULL FORMAT

(PRIMARY AND SECONDARY ENGINE

PARAMETERS WHILE MAINTENANCE

PAGES SHOW)

PRIMARY EICAS DISPLAY AND SECONDARY ENGINE DISPLAY


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STATUS PAGE DISPLAY SELECT

General

The status mode display gives the data necessary for the crew to find if the

airplane is prepared for dispatch. The display has a relation to the minimumequipment list (MEL). You push the STATUS switch on the display select panel

to show the display. Status messages show on the upper right side of the lower

display unit (DU).

With the status messages, analog pointers show the positions of the rudder,

elevator, and aileron control surfaces. Digital readouts show selected

subsystem parameters.

If a DU has a failure in flight, the status cue and status displays inhibit. They are

not inhibited on the ground.

Some display configurations can cause subsystem data to show if they are on inthe OPC software. This system data can show on the STATUS display in

relation to the OPC:

Fuel flow full time

Hydraulic pressure

APU rpm

APU oil quantity

Bulk cargo temperature

Forward cargo temperature

Tire pressure

Brake temperature


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STATUS PAGE DISPLAY SELECT


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STATUS PAGE

Normal Sequence

The status page is displayed in flight or on the ground whenever the Status

Switch on the Display Select Panel is momentarily pressed. It is removed or

advances status pages with subsequent pressing of the STATUS switch.

Hydraulic System Features

The Hydraulic Quantity is continuously displayed in white in percentage (%) of

full. When the hydraulic quantity in flight or on the ground drops below

approximately 75%, the message RF (refill) in magenta is added after the

readout.

Brake Temperature

Continuous Brake Temperature is displayed on the status page with cyannumbers inside cyan boxes grouped in two groups of four each for each landing

gear. Only one box in a group (left or right gear) is changed from cyan to white

when more than one readout is in the threshold range (3 to 4). All boxes and

numbers 5 or greater are changed from cyan to white.

Auxiliary Power Unit (APU)

Continuous APU rpm (%), EGT (oc), and Oil Quantity are displayed on the

status page in white.

APU Oil Quantity can read: 0.25, 0.50, 0.75, or FULL in white or ADD inmagenta. FULL is 6.2 Quarts and ADD is at or below 4.2 Quarts.

Crew Oxygen Pressure

Continuous Crew Oxygen Bottle Pressure (psi) is displayed in white.

Control Surface Position Display

Continuous display of Primary Flight Control Surface Position is displayed on

the status page. These include RUDDER, INBOARD and OUTBOARD

AILERONS, and the ELEVATORS. The Rudder Position is shown on a

horizontal scale while the Ailerons And Elevators are on a vertical scale.

Status Messages

Status Messages related to systems/items Requiring Crew Awarenessprior to

dispatch or in flight are provided on the upper right side of the Status Page. A

cue message STATUS will appear in the upper left corner of the lower display to

alert the crew of a Status Message stored in memory and that the Status

Switchshould be pressed to display the Status Page and Associated Message.

Selecting the status page cancels the cue. When more than 11 status

messages are displayed, line 11 is replaced by a page 1 notation. Momentarily

pressing the STATUS switch, the status messages are paged and the page

number incremented. Pressing the STATUS switch after all overflow messages

are displayed blanks the lower display unit.

Note: There is a 15-second time delay between the new Status Messageand the display of the Status Cue (assuming the cue was not

already displayed). This is to prevent spurious cue annunciation.


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STATUS PAGE


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Alert Messages, Status, and Maintenance Messages

Level A,B,C alert messages are on the Primary EICAS Display.

Level S: Status is white message on status page selected by STATUS switch

on the Display Select Panel. MEL related items requiring Crew Awareness

Prior To Dispatch. There is no associated aural alarm. Priority is order of

occurence, listed from top to bottom.

Level M: Maintenance is white message on ECS/MSG maintenance page. No

Crew Awareness Required. There is no associated aural alarm. Priority is

order of occurence, listed from top to bottom.

On all combinations approximately 86% of the Status Messages are also

Maintenance Messages, therefore clearing these Maintenance Messages also

clears them as a Status Message.


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B767 3S2F ATA 31 40


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MAINTENANCE CONTROL PANEL FUNCTIONS

General

The Maintenance Control Panel is primarily used by maintenance personnel to

display maintenance data stored in computer nonvolatile memory during flight

or ground operations. All switches on this panel are unlighted and operate on

the ground and above 10,000 feet in the air.

Maintenance Format Display Select Switches

Six momentary push switches for selecting real time or stored display of

maintenance data on the Lower Display Unit are provided. These displays are

intended to provide system information normally available in the flight

compartment, plus additional computer configuration data and Maintenance

Messages from the MCDP. The system allows reading and erasing of auto and

manual events stored in NVM. EICAS records out-of-limit occurrences in the

airplane systems and stores them in NVM. The read and erase capability isavailable for each individual page. When any of the 6 Maintenance Pages are

selected, the upper display unit displays the full compacted format.

ECS/MSG, ELEC/HYD and PERF/APU formats

These formats can be displayed in any of the three modes: Real Time, Manual

Event orAuto Event. The Real Time mode displays current dynamic data

while Manual and Auto Event Modes display data stored in the respective

nonvolatile memory (NVM). Pressing any of the above maintenance switches

once displays the associated data on the lower display unit in real time mode.

Pressing the switch a second time with the associated data displayed causesprimary engine data to be displayed on the upper display unit and secondary

engine data on the lower unit.

Note: The maintenance messages displayed on the ECS/MSG page are

both Real Time and Latched in NVM. If more than 11 messages

exist, like the STATUS switch, the ECS/MSG switch is pressed

once for each overflow page.

CONF/MCDP and ENG EXCD formats

The CONF/MCDP format can be displayed inReal Time Only. It displays

computer configuration, selected Program Pin Options, Configuration and

Maintenance Messages from the Maintenance Control And Display Panel

(MCDP), and selected System Operational Conditions. The ENG EXCD formatdisplays various Engine Exceedances (maximum values and total time of

exceedance). The ENG EXCD page is stored data (NVM) only.

Event Read Switches

To read Autoor Manual Eventrecording select either read switch after calling

up the appropriate maintenance page format.

The Auto Readswitch causes the computer to display the selected data (ECS/

MSG, ELEC/HYD or PERF/APU) recorded during an associated alert or out-of-

limit, the event message and the statement Auto Event on the lower displayunit. Pressing the Auto Read switch a second time reverts the selected data to

real time.

The Man Readswitch will cause the computer to display the selected

maintenance page data recorded when the event record switch on the display

select panel is pressed or when the Rec switch is pressed on the Maintenance

Control Panel. Pressing the Man Read switch a second time reverts the

selected data to real time.


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MAINTENANCE CONTROL PANEL FUNCTIONS

B767 3S2F ATA 31 40


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EICAS MEC COMPONENTS

EICAS Bypass Switch

The EICAS bypass switch lets you select maintenance pages in flight. It is a

guarded, two-position switch.

The switch is on the lower rail of the E8 rack in the main equipment center and

is labeled NORMAL and BYPASS.

In the BYPASS position, the switch provides a ground to the maintenance

panel. This lets the panel operate in the air (weight-off-wheels) at any altitude.

In the NORMAL position, the switch provides a ground under these conditions

From the AIR/GND system relay when the airplane is on the ground.

From a pressure switch in the MEC when the aircraft is at 10,000 feet or

above. This switch gets a static pressure input from the right alternatestatic port.

Maintenance pages can not show in flight if either of the display units is failed.

EICAS Signal Consolidation Card (SCC)

The Signal Consolidation Card (SCC) gets signals from various airplane

systems. It combines them into one ARINC 429 bus output to the EICAS

computers. The signals handled by the SCC come from the Fuel Quantity

Processor unit (FQIS Processor), FWD Air Conditioning System, and TCAS

prior to inputing to EICAS.

A Signal Consolidation Card (SCC) failure will result in an EICAS status

message EICAS SCC.


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EICAS MEC COMPONENTS

TRAINING MANUALB767 3S2F ATA 31 40


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ECS/MSG DISPLAY FORMAT

Control Sequence

The ECS/MSG page can be displayed on the lower display unit when the

airplane is on the ground and the ECS/MSG switch is momentarily pressed.

With no Maintenance Messages displayed, or 11 or less messages, pressing

the switch a second time returns the upper display to primary engine data and

the lower display to secondary engine data.

Environmental Control Systems (ECS) Data

The 7 basic ECS parameter displays are: Duct Temperature, Trim Valve

Position, L & R Pack Outlet Temperature, L & R Duct Pressure, L & R Pack

Flow, L & R Temperature Control Valve Position and L & R Ram Inlet Door

Position.

The following displayed parameter captions and the associated readouts resultfrom program-pin selection (PP): Mid Cabin Zone Duct Temp and Trim Valve

Position - PP 18 and ECS Temp Package - PP 21 consisting of L & R Turb In

Temp, L & R Compr Out Temp, and L & R Prim Hx In Temp. ECS in US units -

PP 14 - converts all ECS temperature parameters to degrees Fahrenheit.

Maintenance Message Display

Maintenance Messages for all systems are displayed on the right side of the

ECS/MSG format. These messages, which are displayed only on the ground,

indicate conditions which do not require Flight Crew attention. They are

generated primarily to assist maintenance. Up to 11 messages can bedisplayed on this page and multiple paging capability is provided. When

displayed, these messages are a combination of Real Timeor Latched

Maintenance Messages. If an overflow condition occurs (more than 11

messages), the eleventh line message is replaced by page 1. The pages are

cycled using the ECS/MSG switch. Once the ECS/MSG is selected,

subsequent presses of the ECS/MSG switch will display additional pages of

messages.

The page notation is incremented each time a new page of messages is shown.

Pressing the switch after all messages have been cycled removes the ECS/

MSG format.

Auto/Manual Event Display

An Auto-Event recording of ECS parameters occurs only with both engines

running and the parking brake released. There are 6 different auto-events,

each recorded as the following advisory messages are generated: Flt Deck

Temp, Fwd Cabin Temp, Mid Cabin Temp , Aft Cabin Temp, L Pack Temp & RPack Temp. All ECS parameters and the associated event message are stored

in a dedicated ECS auto-event NVM. For example, the ECS message Aft Cabin

Temp is shown in real-time at the bottom left of the display to inform the

mechanic that an auto-event recording occurred.

When the Auto Event Read switch is pressed, the following is displayed: 1) the

Aft Cabin Temp Message; 2) the Auto Event label surrounded by a box; 3) all

ECS data; and 4) only the maintenance messages latch in NVM.

The manually recorded ECS parameters (not the maintenance messages) can

be displayed by pressing the Man Event Read switch. Man Eventwill then be

displayed at the bottom of the page. If the ECS/MSG format is displayed in

either event mode, pressing the ERASE switch for approximately 3 seconds

erases the ECS stored data as well as the latched maintenance messages.


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ECS / MSG DISPLAY FORMAT

TRAINING MANUALB767-3S2F ATA 31-40


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ELEC/HYD DISPLAY FORMAT

General

The ELEC/HYD page can be displayed on the lower display unit when the

airplane is on the ground and the ELEC/HYD display select switch is

momentarily pressed. At this time, the upper display unit displays the full-

compact format. Pressing the switch a second time switches the upper to

primary engines and the lower to secondary engines display.

Electrical System Features

Monitored parameters for the various Electrical components, are as listed:

Hyd Generator- AC output voltage & frequency & DC voltage

Standby Inverter - AC output voltage & frequency

Main Battery -DC voltage & charge (+)/ discharge (-) current

L & R Engine Generators - AC output load, voltage, frequency & IDG oilout and rise temperatures

L & R Transformer Rectifier Units- DC output voltage & current

APU Generator- AC output load, voltage and frequency

APU Battery Charger - charge voltage and current

Ground Power - AC output load, voltage and frequency

If the AC output voltage from the Engine/APU IDG's, Standby Inverter or

Ground Power decreases below 100 vac, the readout display drops to 0. The

main battery readout is limited to + 150 amperes. For a zero readout, the + or-

sign is blanked. When the readout value is less than + 2 amps, the readout is

also 0.

Hydraulic System Features

There are 3 basic parameters displayed for the l, C & R hydraulic systems:

hydraulic quantity, hydraulic pressure and hydraulic temperature. When the

hydraulic quantity readout is equal to, or greater than the overfull level of 1.22,

the readout is followed with the message OF (example - 1.29 OF).

When the hydraulic quantity readout is equal to, or less than the refill level of

0.75, the readout is followed with the message RF (example - 0.73 RF). The

hydraulic pressure readouts are shown in 10 psi increments.

Auto-Event Recording

An auto-event recording of the ELEC/HYD parameters is enabled only with both

engines running and the parking brake released.

Electrical System

There are 6 Electrical system conditions and associated messages that can

initiate an auto-event recording of the Electrical system parameters. The

associated messages are: L/R Gen Drive, L/R IDG Oil Temp, IDG Rise Temp &

IDG Out Temp. All Electrical system data and associated messages are stored

in the dedicated Electrical system auto-event NVM.

Hydraulic System

There are 13 conditions and associated messages that can initiate an auto-

event recording of the hydraulic system parameters. The associated messagesare: L/C/R HYD sys press, L/C/R HYD Qty, L/C/R dem Hyd Ovht, C Hyd 1 Ovht,

C Hyd 2 Ovht and L/R prim Hyd Ovht. All hydraulic system data and associated

messages are stored in the dedicated hydraulic system auto-event NVM.


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ELEC / HYD DISPLAY FORMAT



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B767 3S2F ATA 31 40Page - 42 11/20/14 EFF - ALL

PERF/APU DISPLAY FORMAT

General

The PERF/APU page is displayed on the lower display unit when the airplane is

on the ground or in flight and the maintenance panel PERF/APU switch is

momentarily pressed. Pressing the PERF/APU switch a second time removes

the display.

Environmental Data Features

Five environmental parameters (Gross Weight, Indicated Airspeed, Mach, Total

Air Temperature and Altitude) are provided for immediate evaluation with the

engine data.

Gross Weight data comes from the Flight Management Computer (FMC) and

Indicated Airspeed, Mach, Total Air Temperature and Altitude Data all come

from the Air Data Inertial Reference Computer (ADIRU).

Engine Data Features

Six engine parameters (Commanded N1, Actual N1, EGT, N2Speed, Fuel Flow

and Fuel Pressure) are displayed for each engine.

N1Command Readout, corresponding to the display select, N1when the Thrust

Reference Control is pulled out. Clockwise rotation of the control increases the

readout with a sensitivity of .1% N1for each detent. CCW rotation decreases

the readout .1% N1for each detent. The last Thrust Management Computer

(TMC) N1command data displayed is stored when the thrust reference controlis pulled out. Pushing in the Thrust Reference Control reverts the N1command

readout to real-time data.

Fuel Flow readout is in lbs/hr x 100. Fuel Pressure parameter (PSI) is also

displayed.

Engine Oil And Vibration Data

Three engine oil parameters (Oil Pressure, Oil Temperature and Oil Qty) and

three vibration parameters are displayed for each engine. Oil quantity is

displayed in U.S. quarts. Vibration parameters are displayed in tracking filter

format (all parameters) on a scale from 0-5 units.

Engine Limited Related Auto-Events

The PERF subsystem parameters like ECS, ELEC, Hyd & APU can be stored inauto-event NVM. However, the PERF data is related to engine LIMITS, not

programmed conditions that generate a message. If EGT, oil pressure or oil

temperature for either engine exceeds the yellow-band limit, an auto-event is

taken (snapshot) of the PERF data of that engine. A subsequent yellow auto-

event on that engine will be ignored. If any of these parameters then enters the

red exceedance range for that engine, a second auto-event will be taken that

overrides and erases the first. Any more yellow or red auto-events for that

engine will then be ignored. The Auto-Event message on the lower right corner

of the PERF Page identifies the parameter and level (yellow or red) of the

exceedance. An Auto-Event is also stored in NVM if N1or N2for either engine

exceeds the red line limit (no yellow-band) or if either oil qty. drops to less than 4qts. with the engine running. An Auto-Event for one engine will not effect the

Auto-Event snapshot storage event for the other engine. There are a total of 18

(9 per engine) LIMIT RELATED Auto-Events that will store the PERF format

data for the respective engine. These must be erased the same as a

MESSAGE RELATED Auto-Event on the other maintenance page formats.

APU Display Data

Two APU parameters (EGT and % RPM) are displayed. There are 2 conditions

(APU Fault & APU Oil Qty) that can initiate an Auto-Event recording of the APU

parameters. All APU parameters and the associated Auto-Event message are

stored in the dedicated APU Auto-Event NVM.


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CONF/MCDP DISPLAY FORMAT

CONF/MCDP

The CONF/MCDP (Configuration/Maintenance Control & Display Panel) page

can be displayed on the lower display unit when the airplane is on the ground

and the CONF/MCDP display select switch is momentarily pressed. At this

time, the upper display unit changes to a full-compacted format. Pressing the

CONF/MCDP switch a second time switches the lower display to secondary and

the upper to primary engine displays. The CONF/MCDP format is displayed in

real-time only.

Configuration Features

EICAS part number is the EICAS computer part number for the specific engine

configuration CF6-80C2F. Engine configuration displays are determined by

computer program pins. For the EICAS computers, program pins 1 thru 4 (left

engine) and 6 thru 9 (right engine) are allocated for engine configurationdisplays and must be properly grounded when engines are intermixed.

Program pin configuration is displayed in a hexadecimal format.

MCDP Display Features

The MCDP displayed data is supplied to the EICAS computers from the MCDP

on an arinc 429 data bus. An aim word format is used. The first line is a yellow

message stating that maintenance data is displayed on the display unit. When

the MCDP is not on and not supplying data, this line contains the white

message MCDP OFF. The second line is a yellow message stating in which of

two modes the MCDP is operating and the type of data. The two MCDP modes

are FLIGHT FAULTS and GRD TEST. The third line is blank. The fourth line is

a white message displaying the data that is contained on the top line of the

MCDP display windows. The fifth line is a white message displaying the data

that is contained on the bottom line of the MCDP display window. Lines 6 thru

11 are for future growth and not used at this time.

Input Bus Activity Features

The input bus activity is monitored for presence of one specific input word label

for each bus. No activity on a bus generates the message OFF. Active data on

a bus generates the message ON, TEST, NCD or FAIL, depending on

the SSM of the word per ARINC 429. A negative sign bit for always positive

parameters causes the FAIL message to be displayed. The following ARINC

429 bus inputs and parameters are monitored for activity:

EICAS-inter-connect bus

Display Select Panel (DSP)- all DSP switches, Cancel/Recall switches andthe maintenance panel CONF/MCDP switch

Air Data Inertial Reference Unit (ADIRU) Total Air Temp (TAT)

Radio Altimeter (RA)Radio Altitude

Thrust Management Computer (TMC)- Total Air Temperature (TAT)

Flight Management Computer (FMC)- Gross Weight (GW)

MCDP -Display Data

Fuel - Fuel Quantity Indicating System,(FQIS) Left Tank Fuel Quantity

Airborne Vibration Monitor (AVM)-Left Engine Vibration

Instrument Comparitor Unit (ICU)-Comparitor Flag Word Label 270

Electronic Engine Control (EEC)-L, R N1Command


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CONF / MCDP DISPLAY FORMAT



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ENG EXCD DISPLAY FORMAT

General

The ENG EXCD page is displayed on the lower display unit when the airplane is

on the ground and the maintenance control panel ENG EXCD switch is

momentarily pressed. The upper display unit automatically switches to the full-compacted format. Pressing the ENG EXCD switch a second time switches the

upper display to primary and the lower to secondary engine formats. The ENG

EXCD page will display stored data only.

Each engine maximum exceedance and accumulated time of exceedance for

each parameter is stored in the engine exceedance NVM (nonvolatile memory).

If no recorded data exists in the NVM, the associated readout is blank. The

parameters monitored for each engine are: N1, EGT and N2.

The stored data can be erased by pressing the ERASE switch on the

Maintenance Control Panel for approximately 3 seconds while the ENG EXCDpage and its stored data is displayed.

TOTAL


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MAINTENANCE PANEL

EXCD

MAN

EVENT

AUTO READ

RECTEST

ERASE

EPCSENGCONF

MSG

ECS ELEC

HYD

PERF

APU

DISPLAY SELECT

EICAS MAINT

MCDP

EXCEEDANCE VALUE

MAXIMUM

750

765

705

745

785

825

865

905

945

985

1025

106.7

MAX L

1038

1038

EGT

103.9N RED

N RED

EGT START

EGT RED

1

2

:06

:12

ENG EXCD

960

965

975

995

:11.3

:12.2

1:13.3

1:15.7

:03

:02.7

:03.5

:04.4

:05.2

:06.3

:07.6

:08.5

:09.1

:10.4

1:09.5

1:11.2

START

R AMBER

EGT

MAX

995

EXCEEDANCE TIME

TOTAL

EXCEEDANCE VALUE

MAXIMUM

ENG EXCD

ENG EXCD DISPLAY FORMAT



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EPCS DISPLAY FORMAT

General

Electronic Propulsion Control System (EPCS) pages consist of two pages.

Page 1 contain engine parameters from the Electronic Engine Control (EEC) forchannel in control. This page has Auto event capabilities.

Page 2 contains hexadecimal codes directly from the EEC. These are STATUS

words which represent the overall status of the engine.

They are used to augment the Propulsion Interface Monitoring Unit (PIMU)

messages when troubleshooting.


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EPCS DISPLAY FORMAT



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EICAS - AUTO EVENT RECORD

General

EICAS can store an automatic event of subsystem parameters when some out-

of-tolerance conditions occur in each of these systems:

Environmental control subsystem (ECS)

Electrical subsystem

Hydraulic subsystem

APU subsystem

Engine performance (left and right)

The PERF/APU page auto event record occurs at all times. The two engines

must be on to store auto events for the other subsystems.

Auto Event Record

An auto event record stores all the subsystem parameters in non-volatile

memory (NVM) for readout and analysis. The auto event record for the ECS,

ELEC, HYD, and APU subsystems has a limit of one event for each subsystem.

Subsequent events for these formats do not erase a related auto event record in

memory.

For the PERF and EPCS subsystem formats, there can be more than one auto

event stored on a priority basis. One auto event for each engine can be stored

and shown.


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EICAS - AUTO EVENT RECORD



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EICAS - AUTO EVENT READ

Auto Event Display

You push the AUTO EVENT READ switch on the EICAS maintenance panel to

show auto event record values on a maintenance display format. The words

AUTO EVENT show in a box at the bottom of the page.

The condition that caused the auto event record shows on the bottom of the

display in real time. The condition also shows in the auto event read modes to

show the crew that an auto event occurred.

Maintenance Messages

If the ECS/MSG page shows, and you push the AUTO EVENT READ switch, a

maintenance message list can show with the recorded ECS parameters. This

includes only those maintenance messages latched into NVM.

Switching Functions

When the auto event read mode shows, you push the AUTO EVENT READ

switch again to show the real-time data. You push the same maintenance

display select switch again to show the primary engine display on the upper DU.

The secondary engine display shows on the lower DU.


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EICAS - AUTO EVENT READ


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EICAS - MANUAL EVENT RECORD

General

The crew can manually record these formats:

ECS ELEC/HYD

PERF/APU

EPCS

The manually recorded data is known as a manual event. You do these steps to

record a manual event:

On the ground or in flight, you push the EVENT RECORD switch on the

display select panel; this records all ECS, ELEC/HYD, PERF/APU, and

EPCS without relation to the EICAS page shown

On the ground, you push the REC switch on the maintenance panel torecord the subsystem parameters from the real-time maintenance format

shown (ECS, ELEC/HYD, EPCS or PERF/APU); messages do not record

A subsequent push of the switch records the data that shows and erases the

data recorded before.


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EICAS - MANUAL EVENT RECORD


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EICAS - MANUAL EVENT READ

Manual Event Display

You do these steps to show manual event data:

Select the applicable maintenance page

Push the MAN EVENT READ switch

MANUAL EVENT shows in a box on the bottom of the screen

Push the MAN EVENT READ switch again to show the real-time data

When you show manual event data, no message list shows on the ECS/MSG

page.

You push the same display select switch to show the primary engine display

again on the upper DU. The secondary engine display shows on the lower DU.


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EICAS - MANUAL EVENT READ


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EICAS - EVENT DATA ERASE

General

The ERASE switch on the maintenance panel lets you erase the auto and

manual event data. Each maintenance page format erases independently.

ECS, ELEC/HYD, EPCS, and PERF/APU Data

You do these steps to erase the recorded data for a manual event or an auto

event:

Push the display select switch on the maintenance display panel to show

the necessary maintenance page.

Push the MAN EVENT READ switch or the AUTO EVENT READ switch on

the maintenance panel.

Push and hold the ERASE switch until the recorded event data erases.

ENG EXCD Data

You do these steps to erase the recorded engine exceedance values:

Push the ENG EXCD switch on the maintenance display panel.

Push and hold the ERASE switch until the recorded data erases.

Because the recorded exceedances show when you select the ENG EXCD

format, you do not use the AUTO or MAN EVENT READ switches to erase

engine exceedance data.


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EICAS - EVENT DATA ERASE




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EICAS - LATCHED MESSAGES / ERASE PROCEDURE

General

There are two types of status/maintenance messages, real-time and latched.

Real-time messages only show during a system fault or non-normal condition.

Latched messages are in nonvolatile memory and stay after the fault repair, orthe condition that caused them is not there.

When you push the ECS/MSG switch, the ECS/MSG maintenance data shows.

The message list that shows is real-time and latched messages.

After you do maintenance on a system that has a latched message, you must

do the erase procedure with the EICAS maintenance panel. This procedure

erases the maintenance message and the latched status message for the

related system.

Erase Procedure

The AUTO EVENT-READ switch selects the AUTO EVENT display. Only the

latched messages show. This display does not show real-time messages.

Latched messages from page one and subsequent pages show on the display.

If you push the ERASE switch while the AUTO EVENT display is on, the latched

messages and ECS AUTO EVENT data erase. System faults that are active

cause latched messages to show again on the display. In the example shown,

the message MAIN BAT CHGR shows again on the display after you push the

ERASE switch. This shows that the battery charger continues to be in a fault

condition.

Some maintenance messages only latch when the airplane is in the air or on

jacks (weight-off-wheels). If the fault condition continues for these systems,

these messages show again when there is a weight-off-wheels condition.


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EICAS - LATCHED MESSAGES / ERASE PROCEDURE




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EICAS MESSAGE TABLE

General

The complete EICAS MESSAGE LIST in the Fault Isolation/Maintenance

Manual in the FRONT MATTER section. All of the EICAS messages are in

alphabetical sequence in this tab section. This information is for a typical page.

The MESSAGE column shows the nomenclature of each message. The flag

notes with brackets show in the message column if an auto event occurs in

relation to the message:

ECS auto event

ELEC auto event

HYD auto event

APU auto event

PERF and EPCS auto event

The LEVEL column shows A, B, C, E, F, S, or M and if the message latches in

nonvolatile memory (NVM). If the message latches only when the airplane is in

the air, the LEVEL column shows NVM-AIR.

Levels A, B, and C show alert messages. Levels E and F show communication

messages. Level S shows a status message. Level M shows a maintenance

message.

The SYSTEM INPUT column shows the general conditions necessary for a

discrete signal to cause each message.

The FIM CHAP REF column lists the primary ATA chapter/section for eachmessage in the FIM.

There is a different EICAS MESSAGE LIST in each ATA chapter. This list

follows the CONTENTS section for the related chapter. The list shows all

messages for the related ATA chapter only. The list also gives a corrective

action or FIM chapter/section with the applicable figure number.


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EICAS MESSAGE TABLE




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O G U OS S Og

EICAS - BITE OPERATIONAL FEATURES

EICAS Bite Features

In addition to automatic monitoring, an EICAS system self-test routine can be

requested. This request is only honored when the airplane is on the Ground

and the Parking Brake Set. The BITE self-test mode is initiated by pressing theTEST button on the EICAS maintenance panel on the P61 panel. A second

press of the TEST button or release of the parking brake will cause the

computers to exit the test mode. The self-test routine involves and end-to-end

test of system health. When the TEST button is pressed, internally produced

signals drive the input receivers of each computer. Each EICAS computer

responds independently to the test. All the automatic monitoring continues,

however, crosstalk input data comparison is halted. Any disagreement using

crosstalk during monitoring is retained. Once the test sequence is initiated, the

cyctem provides the following indications:

The test format appears on both EICAS display units.

The Master Caution Lights come on.

The aural command output discrete is set to ground causing the WEU

(Warning Electronics Unit) to sound the Caution Aural.

The take-off thrust output discrete is set to ground, causing the WEU to

sound its take-off configuration warning signals.

The test format displays Test In Progress during test signal processing.

After processing is finished, the ground is removed from the output

discretes.

Results of the test are displayed on the test format. If any failures were

detected in the computer during test, a hexadecimal CU TEST code is

displayed. This code provides data to the shop personnel for use in fault

isolation. If a disagreement exists with an engine parameter and the message

EICAS Disagree (S) is displayed, a code is displayed on the test format. If

a disagreement exists with a non-engine parameter or an analog discrete

and the message EICAS BITE (M) is displayed, a code is also displayed on

the test format.

Fail messages are also displayed at the completion of the test as follows:

Left Cmptr Fail is displayed when the left computer detects a fault within

itself (a fault bit is set in the left computer Cu Code code).

Right Cmptr Fail - same as described for the left computer. Upper Du Fail

or Lower Du Fail is displayed if any fault discrete is set from the upper or

lower display unit, respectively.

If any fail messages are displayed, the message Test Fail is also displayed

at the top of the test format. If no faults exist, the message Test Ok is

displayed.

Proper switch operation can be verified by BITE while in the self-test mode.

When the following switches are pressed, a corresponding Key message will be

displayed: ENGINE, STATUS, CANCEL, RECALL, ECS/MSG, ELEC/HYD,

PERF/APU, CONF/MCDP, ENG EXCD, AUTO READ, MAN READ, READ And

ERASE. To erase EICAS BITE or EICAS DISAGREE messages and LRU

failure messages or any disagreement code from the test page, the test page

must be accessed and erased as follows:

Initiate manual self-test (EICAS BITE)

Press and hold erase switch and check that Key message appears

Press and hold erase switch until LRU failure message or code disappears

Press test switch to return displays to normal


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EICAS - BITE OPERATIONAL FEATURES




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EICAS TEST COMPLETION

Self-Test Completion

When the self-test is complete, the message SELF TEST COMPLETE replaces

the TEST IN PROGRESS message.

Note: If the left or right EICAS test format was automatically started due

to a program pin error, the message PROG PIN ERROR shows

above the program pin readout. Computer power must be turned

off and on again to restore the system to normal operation after

repair of a program pin fault.

Page Navigation

Instructions will be shown on the page of which switches to push and frequency

of pushes. This will allow navigation to other pages in the test mode.

Self-Test Cancellation

Push the TEST switch again, or release the parking brake to cause both

computers to leave the test mode. The display changes to the normal primary

and secondary engine displays on the upper and lower Display Units.


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EICAS TEST COMPLETION




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EICAS BITE SELECTION

Bite Page Transitions

When you select the test mode, the self test screen shows on both the upper

and lower units. With the maintenance panel, various bite pages are accessed.

These are the pages:

Present status page

Fault history page

Fault report pages

To get access the pages, push either the AUTO or MAN switch twice, as

prompted on the screen.

Note: If no data is detected or available for a particular page, the prompt

for that page is not available on the screen.

When a bite page is active, follow the directions on the screen to get access to

the reports for that particular page.


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EICAS BITE SELECTION




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EICAS - BITE TEST OPERATION

Bite Page Formats

When the self-test is complete, do these steps to get access to the bite pages:

Push AUTO two times to go to the FAULT HISTORY page Push MAN two times to go to the PRESENT STATUS page

Each page shows these two fault types:

Interface faults (six types)

Internal faults

Operation

A SELECTED prompt shows adjacent to one of the six interface fault types.

Examine the types during troubleshooting to help find a fault in the system. Use

these maintenance panel switches to get access to the data:

Push the AUTO switch to move the SELECTED prompt through the fault

types

Push the MAN switch to show the FAULT REPORT for the selected type

Push the REC switch to put the display back to the BITE page that supplied

the report

Fault Troubleshooting With the Present Status Page

The graphic shows left computer selected on the display select panel and how

to go to the PRESENT STATUS page and one of its logged failures. TheARINC 429 RECEIVER is the selected report. All supplemental data for the

fault shows in the report. In this example, the left AVM input to the left EICAS

computer has a failure.


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EICAS - BITE TEST OPERATION




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EICAS - OPC SOFTWARE CROSSLOAD

Overview

Replacing an EICAS computer generates the status message EICAS

SOFTWARE. This happens because the new computer received from spares

usually has a different or no OPC installed in the unit. When you see thismessage, you check the CONF/MCDP page for specific information.

This procedure outlines the steps required if the message EICAS SOFTWARE

shows and the CONF/MCDP page 1 shows LEFT/RIGHT SW below the EICAS

part numbers. This means the operational program configuration (OPC)

software part numbers are different for each computer. Normally, the software

installation is performed by a floppy disk load procedure using these sources:

A portable data loader (PDL) connected to the front of the EICAS computer

in the MEC.

An onborne data loader with data plug located on the P61 right side panel

in the flight deck.

Operational program software (OPS) has a procedure called EICAS

COMPUTER CROSSLOAD for quick installation of the OPC into a newly

installed computer. This is done from page 3 to the CONF/MCDP maintenance

page.

CONF/MCDP Page 3 Selection

To access to the CONF/MCDP page 3, these conditions are required:

The airplane is on the ground The parking brake is set

Both engines are off

Push the CONF/MCDP switch three times to show page 3. If any of the above

conditions are not met the display returns to the secondary engine page instead

of CONF/MCDP page 3.

Arm the System

To arm the crossload function, push these switches simultaneously for three

seconds:

ECS/MSG ELEC/HYD

PERF/APU

The display changes to the MAIN MENU SELECTION display.

The Boxed status line shows CROSS LOAD ARMED.

The boxed STATUS line in the lower center of the page shows the message

CROSS LOAD ARMED. Push MAN EVENT READ to change between the left

and right computers transmit or receive actions. In the example, the left

computer is selected to transmit the data to the right computer.

Note: This display always defaults to show the direction of the crossload

from left to right. MAKE SURE THAT YOU VERIFY WHICH

COMPUTER HAS THE CORRECT OPC AND SELECT THE

PROPER DIRECTION OF CROSSLOAD, as required. Failure to

do so could crossload the incorrect OPC into the offside (good)

computer.

Begin the Crossload

Push the maintenance panel REC switch. The boxed status line shows

CROSSLOAD IN PROGRESS and the OPC for the receiving computer blanks.The data transfers on the high speed cross talk bus to the offside computer in

less than ten seconds.

To disarm the procedure, push the maintenance panel ERASE switch. The

display will return to the basic OPC crossload page.

For crossload failures or other abnormal operation, refer to the correct

maintenance manual procedure in section FIM 31-41.


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EICAS - OPC SOFTWARE CROSSLOAD




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STANDBY ENGINE INDICATOR (SEI)

General

During normal conditions, the EICAS computer program software provides

primary engine parameters in these modes:

Status mode

All maintenance modes

The system also provides primary engine parameters during these failure

conditions:

Single unit computer failure

Single display unit failure

Display select panel failure

Multiple Component Failure

EICAS can not provide primary engine parameters during either of these failure

conditions:

Both EICAS computers fail

Both display units fail

The standby engine indicator (SEI) operates and shows the primary engine

parameters when either of these failure conditions exist. The SEI is powered by

the D.C. battery bus.

The SEI will be discussed in the engine indication chapter.


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STANDBY ENGINE INDICATOR (SEI)




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FLIGHT DATA RECORDER SYSTEM

General

The flight data recorder system has these components:

Flight Recorder Accelerometer Digital Flight Data Acquisition Unit (DFDAU)

Flight Recorder Control Panel

Flight Data Recorder (FDR)

Test connector

Flight Data Recording Function

Input signals to the flight data recorder system include mandatory and optional

parameters. Regulatory agencies set the mandatory parameters. Airlines

select the optional parameters.

Data Collection and Storage

The DFDAU receives digitaL, synchro, and discrete inputs from airplane

systems and line replaceable units (LRUs). The flight recorder accelerometer

also sends analog signals to the DFDAU. The DFDAU uses these inputs and

sets their formats into digital data and sends it to the FDR.

Fault Annunciation

The DFDAU and FDR send fault status to the flight recorder control panel and to

EICAS. EICAS makes engine indication and crew alerting messages for some

faults.

Fault indicators on the front panels of the system components show fault

conditions.

Data Output

You can monitor low-speed, real-time data at the test connector. You do a high-

speed data download through the high-speed data connector on the DFDR.


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FLIGHT RECORDING SYSTEM COMPONENTS

Component Location

The Flight Recorder Accelerometer is in the left main wheel well.

The Flight Data Recorder is on the E7 rack in Bulk Cargo Compartment.

Flight Deck Components

These are the flight recorder system components in the flight deck:

P61 panel - Flight recorder/service interphone control panel

Flight recorder system test plug - P61

General MEC Locations

These flight recorder system components are in the main equipment center(MEC):

Digital Flight Data Acquisition Unit (DFDAU) - E2-3 shelf

DFDAU coding and aircraft identification shorting receptacle - E2-3 shelf

Flight recorder-EICAS switching relay - E8 card file on the switching

module for the lower EICAS display unit

Flight recorder control relay-left - P36 panel

DFDAU bite relay

P37 has these components:

Flight recorder control relay-right System 2 air/ground relays

Flight recorder system EFIS input switching relay

Flight recorder system air/ground discrete relay


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FLIGHT DATA RECORDER CONTROL PANEL

Purpose

The flight data recorder control panel lets the crew set the flight recorder system

to on or off, do tests, and monitor the system.

Flight Recorder Power Control Switch

In the NORM position, power goes to the flight recorder when the airplane is in

the air or one of the engines is on.

In the ON position (latched), power goes to the flight recorder to operate it.

In the TEST position (momentary), power goes to the flight recorder during the

test.

Flight Recorder OFF Light

This light comes on white to show there is no power to the recorder, or there is a

fault in the flight recorder system.

Purpose of Test

The flight data recorder test is a preflight check of system performance or a

post-maintenance check.

Test Initiation

To start the test, move the power switch to TEST (momentary position). In thisposition, the switch sends 115v ac to the FDR. The flight recorder operates as

long as the switch is held in TEST. Power to the DFDAU is directly from the

circuit breaker.

Test Results

If no fault is detected, the flight recorder OFF light turns off while the switch is in

TEST. This shows that the flight recorder and DFDAU function properly.

If a fault is detected, the OFF light stays on and you must do a check of

individual system components and their indicators to locate the fault.

These are the indications of a recorder failure:

Flight recorder OFF light is on

FLT DATA REC message on EICAS STATUS and ECS/MSG pages, (only

with both engines on)

DFDAU FAIL light on front of DFDAU is on

Note: If there are both FDR and DFDAU failures, the FLT DATA ACQ

message inhibits the FLT DATA REC message.

If the DFDAU FAIL light is on, fault codes may be available from the DFDAU

memory. You access and read the codes on the face of the DFDAU.


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FLIGHT DATA RECORDER

Performance Characteristics

The capacity is 25 hours of recorded data.

The download time is less than ten minutes for the 256 words per secondmodel.

Case Features

The FDR has these three shop replaceable units:

Memory unit

Power supply

Interface and control assembly

The memory stores the last 25 hours of flight data at an input rate of 256 words

per second. An underwater locator beacon (ULB) is on the front of the unit.

Front Panel Features

Use the RS232 connector on the face of the unit for high-speed data retrieval.

Operation

There are no controls or switches on the FDR. Operation is automatic from

power-up.

The recorder receives digital ARINC 573/717 Harvard bi-phase data from theDFDAU and records the data on flash memory modules.

BITE

The FDR contains internal continuous self-test circuitry. After you supply power

to the unit, the OFF light on the flight recorder control panel goes off in five

seconds. For 60 seconds the circuitry does checks of the FDR and the input

data from the DFDAU. If the OFF light comes on during this time, it shows a

fault.

Maintenance Requirements

There is no scheduled maintenance for the solid state flight data recorder

(SSFDR).

Underwater Locator Beacon

An underwater locator beacon is on the front of the unit. This beacon transmits

an ultrasonic acoustic output after immersion in water.

Low-speed Playback - Operation

Real time data received by the flight recorder is available for low-speed

playback with ground support equipment connected to the test connector on

P61. Use the low-speed playback to do a check of system operation.

High-Speed Data Retrieval - Operation

High-speed data retrieval of recorded data is onboard or in the shop. To get the

data, connect the equipment to the copy recorder connector. Use a portable

copy recorder for onboard retrieval. Use a ground playback station for in-shop

data retrieval.


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WARNING ELECTRONICS SYSTEM - INTRODUCTION

Purpose

The Warning System provides the flight crew with visual and aural indications of

abnormal airplane systems conditions or that the airplane is out-of-configuration

for specific operating modes such as Landing and Take-Off.

System Description

Input signals are supplied from airplane sensors, mechanical and avionic

systems and the pilots. Signal processing is performed in the Warning

Electronics Unit (WEU) where 11 modules are utilized. Output functions are

aural tones and voice messages from dedicated aural warning speakers in the

flight compartment plus visual displays on flight compartment instrument panels.

Alert Message Level Aurals

Level A: Warnings - Their associated aural sounds are the Fire Belland a

Two-Tone Siren.

Level B: Cautions - Their associated aural sound is a beep-beep-beep-

beepsometimes referred to as a level B Caution Aural or as an Owl

Sound.

Level C: Advisories - No auralsounds are associated with these

advisories.

Outputs To Associated Systems

The outputs to the Stick Shaker and Stick Nudger are covered in the Flight

Controls chapter. The Stall Warning Computers also send data out to theGround Proximity Warning Computer (GPWC) for Windshear Detection and

Indication.


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WARNING ELECTRONICS UNIT (WEU)

General

Provides logic circuitry to generate warning signals for Stall Warning,

Configuration Warning (Take-Off & Landing), Altitude Alert, Master Warning and

Caution Lights and associated warning sounds. The WEU requiressupplemental cooling accomplished by blowing air through the unit in

accordance with ARINC 600.

Fault Monitoring

Two fault ball annunciators located on the front panel are provided to monitor

operation of each power supply. They are color coded black for operational and

yellow for fault conditions. A reset switch is provided for returning tripped fault

annunciators to the operational mode. Fault codes displays are for Stall

Warning System faults.

There is continuous monitoring during operation of the power supply modules Aand B. A power supply module fault or a Stall Warning fault will cause EICAS to

display the WARN ELEX (S,M) message.

Configuration Warning Modules and Stall Warning Modules tests are initiated

from the Test Panel module on the P61 panel using the appropriate test

switches. All other modules are tested by using on-board system interfaces.

These tests verify performance and proper line replaceable unit installation.

WEU Modules/Systems

Power supply modules - two redundan

B767 ATA 31 Student Book

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