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757, 767 Boeing EICAS description and operation.

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  1. 1. 757 EICASRM&E Instructor 1
  3. 3. The engine Indication and Crew Alerting System(EICAS) includes two color Display Units(DU), two computers, and two control panels. Inaddition to these components we havecancel/recall switches , and captain’s and firstofficer’s master caution lights, jointly performthe various EICAS functions.The EICAS computer process and formats datato display all engine and airplane systeminformation required by the crew. Only onecomputer is used at any particular time fordisplaying the data on both display units. The leftcomputer is always the primary one and right issecondary. Manual computer selection can bedone on the display control panel. 3
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  5. 5. EICAS DISPLAY CATEGORIESEICAS is designed to categorize alerts and displaysaccording to function and usage. This results in threemodes of display:•Operational Mode•Status Mode•Maintenance modeOperational Mode display those engine parametersrequired on the ground and in flight operation andprovide monitoring of the airplane and enginesubsystems. The upper DU is dedicated full time toprimary engine parameters and alert messages formonitoring by the crew. The lower DU showssecondary engine parameters.Status Mode provide subsystem parameters as wellas status messages on the lower DU. This are usedby the crew to determine readiness of the airplanefor dispatch and closely associated with the MEL.Maintenance Mode provide airplane subsystemsparameters and maintenance messages on the lowerDU. This data is available on the ground only forpost-flight maintenance and troubleshooting action. 5
  6. 6. EICAS OPERATIONAL MODEPrimary engine parameters displayed on the upper DUare EPR, N1 and EGT.This are required to set and monitor thrust. All primaryparameters are displayed by a digital readout and ananalog pointer.Alert Messages are display in the upper DU left corner.Secondary Engine Parameters – N2, N3, fuel flow, oilpressure, oil temperature, oil quantity and vibration –are displayed on the lower DU at power up or whenmanually selected on the display selector panel.Secondary parameters are displayed by a digitalreadout and an analog pointer.EICAS automatically display engine exceedancecondition and the respective color for fast crewattention and action. 6
  7. 7. EICAS ALERT MESSAGES & CANCEL/RECALLAlert messages displayed on the upper DU are divided by Cancel and Recall switches control the display of thispriority: messages, Cancel remove any caution and advisory messages• Warnings - Red required immediate action. from the upper display and will show the next page of Messages• Cautions - Yellow. if any. RECALL switch will return to view those Messages that are still applicable.• Advisories -Yellow and are indented. Warning Messages can not be canceled due to the level of• White - data or communication. importance related to them. 7
  8. 8. EICAS DISPLAY CONTROL PANELThe display select panel provides all control function to theEICAS computer units system operation both in flight and on theground. The display select panel functions include:• Display format selection: • Display brightness control: ENG and STATUS. upper and lower.•Recording subsystem parameters: • Thrust reference setting control:  EVENT RECORD  AUTO/MANUAL• Computer source selection: • Clearing/display engine exceedance data:  L, both and R.  MAX IND RESET 8
  9. 9. EICAS STATUS MODEThe Status Mode display is selected by manually pressingthe STATUS switch on the display select panel. Dataneeded by the crew to determined readiness for dispatch isdisplayed on the upper left corner.On the upper right corner the following are displayed• HYD QTY and PSI.•APU RPM/EGT all displayed in digital format.• Crew O2 PSI.In addition on the lower left corner analog pointers areused to indicate the position of the Rudder, Elevators andAileron control surfaces.The status mode can be useful in flight for anticipatingpossible ground maintenance action that will be required ifequipped or activated prior dispatch. For this function, aSTATUS cue is provided in the upper left corner lower DUwhenever a change in status Msg occurs while the statuspage is not being displayed.For specific messages refer to the FIM, if a DU fails inflight, the status cue and status displays are inhibited untilairplane is on the ground. 9
  10. 10. EICAS MAINTENACE MODE/PANELThere are five maintenance formats with on the EICASMaintenance Mode. They are designed to provide maintenance • Environmental Control Systems/Messages - ECS/MSGinformation to aid the ground crew in troubleshooting and • Electrical/Hydraulic - ELEC/HYDverification testing of the major subsystems. They are also used torecord systems parameters on the ground or at the time of an in- •Performance/Auxiliary Power Unit – PERF/APUflight fault for later readout on the ground • Engine Exceedance – ENG EXCDThe five different formats are displayed in the lower DU and •The Configuration Porting – CONF/MCDPaccess from the EICAS Maintenance Panel this provides all thecontrols functions for maintenance and troubleshooting The EICAS maintenance panel contains BITE switch to initiateinformation , the I/O signals interfaces with the air-ground relay the SELF bite function of the two computers.and the display panel: Also on the Maintenance control panel contains the AUTO/MANUAL EVENT read switches and REC/ERASE switches. 10
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  12. 12. EICAS AUTO AND MANUAL EVENT DISPLAY & RECORDINGEICAS feature automatic event recording ofthe subsystems parameters . Whenever certainauto or manual events messages are initiatedby one of the following subjects:• APU subsystem.• Electrical subsystem.• Engine performance• Environmental control system.• Hydraulic subsystem.This events are recorded on a nonvolatilememory for later readout and evaluation. TheAUTO (or MANUAL) switch on themaintenance panel is use to access and erasethis pages.The Manual Event recording will storediscrete from engine parameters or either theECS/MSG, ELEC/HYD, or PERF/APUmaintenance formats. The last data storedoverwrites previously stored data, only the lastdata is available for review. 12
  13. 13. RH IDG High out tempDate and time 13
  14. 14. ENGINE EXCEEDANCE DATATo erase the auto recorded values of engines exceedance, call up the Since the Stored exceedance are automatically displayed when theENG EXCD page by pressing the ENG EXCD switch on the form is called up, the AUTO or MAN events read switches do notmaintenance panel and then press the ERASE switch. have to be used. You must also clear exceedance from the Display Select Panel. 14
  15. 15. EICAS COMPUTERSThe EICAS computer are located in the main electronic and the circuit breakers are located on the overhead P11 compartment on the E4-2 rack. The computer unit Normally (AUTO) the left computer is on command of displaysperform all interface, data processing, control and display and the right computer is on backup mode in case the left fails.generation function required and is software controlled. Manual selection of the active computer is provided by selecting L or R rather than the AUTO position .The front case has no system lights, BITE or controls. There is aconnector for software load with the appropriate tool or Care should be taken when replacing this computer due toequipment. There is also a data load point in the flight deck electrostatic sensitivity devise.behind the F/O on P61.115 VAC is supplied from the respective right and left ac buses P61 data port 15
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  17. 17. DISPLAY UNITS (DU)The EICAS display units (DU) provide a multicolor(red, yellow, cyan (light blue), magenta (pink), white, and green)CRT presentation of EICAS data.Video display and deflection signals from the EICAS switchingmodules are provided to drive the CRTs.Manual and automatic intensity signals are provided from thedisplay select panel and from remote light sensors in the upperright corner of the front panel.EICAS DU problems that are detected within each unitlike, beam stuck on or off, failure discrete, or over temperaturewill cause the unit to shut down automatically.The DU are interchangeable, to remove, unscrew the handle, liftand pull out, refer to the AMM for proper procedure. 17
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  19. 19. EICAS BITE OPERATIONEICAS BITE test can only be accomplished when the airplane is on theground and the parking brake set.The EICAS self test mode is initiated by pressing the TEST switch onthe EICAS maintenance panel.After depressing the TEST switch, the DUs will display: •Identical formats with the message “TEST IN PROCESS”. •Master CAUTION lights and the beeper tone are acute. •Level B aural command output signal are generated. •The master WARNING lights, the CONFIG light and siren are activated. •The takeoff ground signal is generated. •The SEI comes on if selected on auto.The computer will test the interface and circuits of the completeEICAS system and will display all characters and colors. The FIM isused for any faults noted.When the test is completed a massage: TEST OK, SELF TESTCOMPLETED or TEST FAIL is displayed. 19
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  21. 21. STANDBY ENGINE INDICATORThe Standby Engine Indicator(SEI) provides primaryEngine information to the flight crew in the event of anEICAS failure, which will result n the loss of the normalprimary engine Parameters displays. When operating , the SEI presents digital LCD Displaysof the primary engine parameters. This displays includeEPR, N1, EGT and N3 and the max values are shown onred decals next to the digits. The SEI is controlled by aswitch on the front with two positions, ON and AUTO.To perform a display test, a spring loaded switch locatedopposite to the On/off switch is used, the digital numberswill read ones and eight.This is a LRU and does not required special software. Theengine placards must be removed from the old andinstalled on the new one. 21
  22. 22. Q&A 22