B767 ATA 31 Student Book

INSTRUMENTS CH 31

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TRAINING MANUAL FOR TRAINING PURPOSES ONLY

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TABLE OF CONTENTS

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

MIDU................................................................................................... 102

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

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 rapid interpretation 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 and displays 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, N1 target 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 N1 target 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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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 the secondary 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 Messages can 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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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 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 and Maintenance 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 offside computer. • Performing cross-comparisons of its input data with its respective off-side data 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 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 Action Required. • 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 come on 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 switchlights, 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 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 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 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 front of 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 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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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 the respective 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% per detent. 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 for readout 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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PRIMARY ENGINE DISPLAY AND SECONDARY ENGINE DISPLAY General The operational mode shows the primary and secondary engine parameters and 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

TAT + 15c

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L HYD SYS PRESS L YAW DAMPER RUDDER RATIO PARKING BRAKE

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TEMP

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FUEL FLOW

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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 minimum equipment 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 in the 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 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 cyan numbers 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 in magenta. 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 Awareness prior 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 Switch should 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 Message and the display of the Status Cue (assuming the cue was not already displayed). This is to prevent spurious cue annunciation.

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EICAS MESSAGE LEVELS 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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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 is available 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 or Auto 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 causes primary 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 in Real 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 format displays various Engine Exceedances (maximum values and total time of exceedance). The ENG EXCD page is stored data (NVM) only. Event Read Switches To read Auto or Manual Event recording select either read switch after calling up the appropriate maintenance page format. The Auto Read switch causes the computer to display the selected data (ECS/ MSG, ELEC/HYD or PERF/APU) recorded during an associated alert or out-oflimit, the event message and the statement Auto Event on the lower display unit. Pressing the Auto Read switch a second time reverts the selected data to real time. The Man Read switch 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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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 alternate static 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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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 result from 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 be displayed on this page and multiple paging capability is provided. When displayed, these messages are a combination of Real Time or 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 & R Pack 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 Event will 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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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 fullcompact 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 oil out 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 + orsign 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 autoevent recording of the hydraulic system parameters. The associated messages are: 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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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, N2 Speed, Fuel Flow and Fuel Pressure) are displayed for each engine. N1 Command Readout, corresponding to the display select, N1 when the Thrust Reference Control is pulled out. Clockwise rotation of the control increases the readout with a sensitivity of .1% N1 for each detent. CCW rotation decreases the readout .1% N1 for each detent. The last Thrust Management Computer (TMC) N1 command data displayed is stored when the thrust reference control is pulled out. Pushing in the Thrust Reference Control reverts the N1 command 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 in auto-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 autoevent 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 N1 or N2 for either engine exceeds the red line limit (no yellow-band) or if either oil qty. drops to less than 4 qts. 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 configuration displays 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 and the 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 N1 Command

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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 fullcompacted 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 EXCD page and its stored data is displayed.

TOTAL EXCEEDANCE TIME

:06 :12

106.7 1038

MAXIMUM EXCEEDANCE VALUE

ENG EXCD N 1RED

EGT START EGT RED N 2RED

MAX

L

:03

103.9

EGT START

1038 1025 985 945 905 865 825 785 745 705 765 750

:02.7 :03.5 :04.4 :05.2 :06.3 :07.6 :08.5 :09.1 :10.4 :11.3 :12.2

MAXIMUM EXCEEDANCE VALUE

R EGT AMBER

995 975 965 960

1:09.5 1:11.2 1:13.3 1:15.7

MAX

995

ENG EXCD EICAS MAINT DISPLAY SELECT AUTO PERF ECS ELEC MSG

HYD

CONF

ENG

MCDP

EXCD

EVENT READ

APU TEST

REC

EPCS

MAINTENANCE PANEL

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MAN


ERASE

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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) for channel 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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EICAS - AUTO EVENT RECORD General EICAS can store an automatic event of subsystem parameters when some outof-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 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 - 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 to record 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 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 - 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 - 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, or the 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 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 each message 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 - 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 the TEST 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 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 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 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. The ARINC 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 - OPC SOFTWARE CROSSLOAD Arm the System 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 this message, 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.

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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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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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 highspeed 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 this position, 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 Maintenance Requirements Performance Characteristics The capacity is 25 hours of recorded data. The download time is less than ten minutes for the 256 words per second model.

There is no scheduled maintenance for the solid state flight data recorder (SSFDR). Underwater Locator Beacon

Case Features

An underwater locator beacon is on the front of the unit. This beacon transmits an ultrasonic acoustic output after immersion in water.

The FDR has these three shop replaceable units:

Low-speed Playback - Operation

• 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 the DFDAU 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.

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 Bell and a Two-Tone Siren. • Level B: Cautions - Their associated aural sound is a beep-beep-beepbeep sometimes referred to as a level B Caution Aural or as an Owl Sound. • Level C: Advisories - No aural sounds 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 the Ground 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 requires supplemental 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 A and 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 redundant power supplies require 115 vac, 400 hz, single-phase power to develop internal DC power +12 volts and +5 volts for all modules. Power supply fault indicators are located on the front door. Stall Warning Modules - Two Stall Warning Modules are provided with the left module providing the captain's warning signals and the right module providing the first officer's. These modules are each micro-processor controlled. Configuration Warning Modules - two Configuration Warning Modules are provided. One provides Take-Off Warning signals and the other provides Landing Warning Signals.

Altitude Alert Module - one Altitude Alert Module, provides altitude capture advisory information and departure cautions. Master Warning Module - one Master Warning Module controls Master Warning Lights. Aural Warning Modules - three Aural Warning Modules are provided which are logic circuit controlled. They contain four tone generators: bell, two-tone siren, caution aural and a single stroke chime. One module contains the fire bell and chime generator as well as a warning inhibit during take-off. The other two modules contain the siren, caution aural generators, preamp gain control circuit and a preamplifier. Signal Consolidation Card (SCC) - converts analog signals to digital signals for use by the EICAS computers. The majority of the signals handled by the SCC come from the Fuel Quantity Processor Unit prior to inputting to EICAS.

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TAKEOFF CONFIGURATION WARNING Test Function General The Takeoff Configuration Warning Module provides aural and visual warnings for improper airplane configuration during takeoff. Seven areas are monitored for Takeoff Configuration Warning. These include flaps, slats, horizontal stabilizer, speedbrakes, parking brake, air/ground logic, and EICAS takeoff logic. Warning Indications Improper aircraft configuration detected when the throttles are advanced is announced by: • Illumination of the red, CONFIG light on the P1-3 panel • Illumination of the red, MASTER WARNING lights on the P7 glareshield panel • Actuation of the Aural Warning Sirens • Annunciation of the appropriate red warning message on the upper EICAS display unit: FLAPS, STABILIZER, PARK BRAKE or SPOILER Conditions Monitored The Takeoff Configuration Warning System monitors the leading edge slats, the trailing edge flaps, the horizontal stabilizer position, the speedbrake handle position, the parking brake position and the air/ground mode of the airplane. The system is activated by sensing advanced throttle position (N1 greater than 66 %), or by actuation of the test switch. On B767-300 airplanes, the flap positions for takeoff are 5, 15, 20. Signal Processing The input signals are processed by the Takeoff Configuration Warning Electronic Unit (P51).

A Takeoff Configuration Warning test is initiated by the CONFIG T/O - LDG test switch. Setting the test switch to T/O simulates the engines at takeoff condition and arms takeoff warning logic. One or all error conditions are set to generate the test. The WEU illuminates the CONFIG light and the siren.

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PUSHBUTTON TAKEOFF CONFIGURATION CHECK SWITCH Takeoff Configuration Check Switch The Pushbutton Takeoff Configuration Check Switch is on the Pilot’s P1-3 instrument panel above the marker beacon lights. This manual switch shall be provided to check for proper takeoff configuration prior to start of takeoff with a visual warning of improper configuration.

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LANDING CONFIGURATION WARNING SYSTEM General The Landing Configuration Warning System monitors the configuration of the airplane whenever certain landing systems are activated. Improper configuration of the airplane for landing is indicated by the master warning light, siren aural warning, a level A warning and GEAR NOT DOWN message. Improper use of speedbrakes below 800' radio altitude is indicated by a level B caution and SPEED BRAKE EXT message. Pressing the master caution light will reset only the caution light and owl aural caution. The SPEEDBRAKES amber light and the EICAS message SPEEDBRAKE EXT will remain illuminated until the improper configuration is corrected by retracting the speedbrakes, climbing to 800 feet, or retracting the flaps. Conditions Monitored • • • • • •

Landing Gear Position from the PSEU Slat Position from the PSEU Flap Position from the center FSPM module in the P50 Altitude from the left radio altitude transceiver in the E5 Thrust Lever Position from the autothrottle switch pack Speedbrake Position from a spoiler control module (2l) LVDT input

Signal Processing The input signals are processed by the landing configuration warning module located in the warning electronic unit (P51). The module may be tested by use of the test switch on the P61 on the flight deck. Operation Enable criteria: • landing gear not down and locked, as sensed by the PSEU, provides an enable for the microprocessor to process warning signals • flaps in landing range (25o or 30o) • left, right, or both thrust levers set to idle position • altitude data as well as failure from radio altimeter system • a clean-wing or not clean-wing configuration

Activation criteria: The microprocessor controls outputs to actuate the warnings, as a result of the following situation: • Situation 1 - radio altitude <800 feet, either throttle at idle and any landing gear not down and locked • Situation 2 - flaps in landing range (equal to or greater than 25o) and any landing gear not down and locked • Situation 3 - left radio altitude system failure, either throttle at idle, clean wing/not clean wing configuration and any landing gear not down and locked (the system defaults to altitude <800 feet) Indications for the above situations are the siren, master warning lights, CONFIG warning light, and level A EICAS message GEAR NOT DOWN. If the wing is clean in situation 3, only the CONFIG light and EICAS GEAR NOT DOWN message will annunciate. Only correction of the configuration problem can remove the message and extinguish the configuration light. Test Function The test can be initiated in flight or on the ground from the LDG CONFIG test switch on the P61 test panel. Test results are: • • • • •

Master warning lights illuminate SPEED BRAKES discrete caution light illuminates CONFIG discrete warning light illuminates Siren sounds EICAS displays GEAR NOT DOWN

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AIRCRAFT CONDITION MONITORING SYSTEM (ACMS) GENERAL General Honeywell Digital Flight Data Acquisition Unit (DFDAU) consists of a Flight Data Recording System (FDRS) mandatory section and an Airplane Condition Monitoring System (ACMS) section. Boeing Commercial Aviation Services (CAS) provides Airplane Health Management (AHM). Included in this service is custom alerting for: • • • • •

Operational Exceedances System Monitoring Fault Discretes Servicing ACARS Management

AHM can also provide ACARS Management for ACMS Report Configuration, Input Monitoring, and Snapshots. Virtual Central Maintenance Computing correlating EICAS data is also available.

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AIRCRAFT CONDITION MONITORING SYSTEM (ACMS) COMPONENT LOCATION General Location Either Mult-purpose Control Display Unit (MCDU) or the Mult-purpose Interactive Display Unit (MIDU) located on the P9 and P8 panels is used to access aircraft information. The printer located on the P8 panel can be used to print reports. The Honeywell Digital Flight Data Acquisition Unit (DFDAU) is located on the E 2-3 shelf of the Main Equipment Center (MEC). The ACARS Management Unit is on the E 2-5 shelf.

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DIGITAL DATA INPUTS General The Honeywell Digital Flight Data Acquisition Unit (DFDAU) consists of a Flight Data Recording System (FDRS) mandatory section and an Airplane Condition Monitoring System (ACMS) section. Interface with ACMS is through either Mult-purpose Control Display Unit (MCDU) or the Mult-purpose Interactive Display Unit (MIDU). Information can be downloaded from the aircraft to ground locations though ACARS or printed on the aircraft. The DFDAU can have software loaded from the plug and Data Loader location on the P 61 panel in the flight deck.

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MCDU FUNCTIONS / DISPLAY SUMMARY General When selecting Aircraft Condition Monitoring System (ACMS) using the Multipurpose Control And Display Unit (MCDU) or Multi-purpose Interactive Display Unit (MIDU), the system user can control and display ACMS functions. Display And Control Functions • All headers and advisory messages are in small font. • Titles, commands and data fields are in small font. • The data display and/or data entry section of the MCDU screen is separated by equal(=) signs from the command section. • Depression of the RETURN key will result in displaying the previously selected menu. • Depression of the MAIN MENU switch will result in termination of whatever ACMS display was in progress and returns to the MCDU main menu. • Depression of the NEXT PAGE or PREV PAGE switches will display the next or previous page or record in a multi-page display. • Where line select key R6 indicates START PRINT, activation of this key will start a dynamic printout of the displayed parameters. During printing R6 will change to STOP PRINT. If selected again, printing will terminate and the indication will revert back to START PRINT. • On displays where R6 line select key indicates PRINT, activation of this key will result in the printout of the screen contents. ACMS Main Menu To access the ACMS main menu on the MCDU: • First, push the MENU key. • Then, push the line select next to ACMS.

From the ACMS main menu these sub-menus can be selected: • • • • • •

REPORTS INSTANT REPORTS DATA DISPLAY DOCUMENTARY DATA REPROGRAM EEC FAULT CODE

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MIDU General The Multipurpose Interactive Display Unit (MIDU) provides the means for inserting documentary data into and retrieving data from the DFDAU. The DFDAU interfaces with ACARS Multipurpose Interactive Display Unit (MIDU), which is also used as an ACARS Control Panel. The MIDU provides the means for inserting documentary data into the DFDAU and the controls to call up and display Flight Data Recorder System parameters.

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B767 ATA 31 Student Book

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