EASA Module 1

Basic MaintenanceTraining Manual Module 5 Digital Technology / EIS 5.1 Electronic Instrument Systems 5.1 Electronic Instrument Systems Sep04 / THTT Copyright by SR Technics Switzerland Corresponding with EASA Part-66 For training purposes only Cat: B2 5.1 - 1 Basic Maintenance Training Manual Module 5 Digital Technology / EIS 5.1 Electronic Instrument Systems Introduction Regarding the Electronic Instrument System of modern aircraft, it is difficult, if not impossible, to give a description without referring to specific Aircraft types such as Airbus A320, MD11 etc. The Airbus A320 was the first civil aircraft with an all-electronic flight deck indication system and now many aircraft, both large and small - including helicopters, have Cathode Ray Tube flight deck displays. (or even LCD Displays for the newest aircraft types). In this submodule follows a general introduction with a view of the transition from old fashioned cockpit instruments to the modern Electronic Instrument System. A short description of the Electronic Instrument System of the MD11 is given. After that, to give a detailed description of the typical system arrangement of modern Electronic Instrument Systems, two Aircraft types are chosen as examples. These are the Airbus A320, that represents the larger modern civil aircraft, and the Embraer 145 that represents the smaller modern turbofan transport aircraft. If you work on a different type of aircraft, the system may be different from the ones described in this submodule, and may also have different names for the components used. But after studying the two Aircraft Electronic Instrument system, that will be discussed on the following pages, you will have a good base and the necessary knowledge for the further study of aircraft type rating courses. Sep04 / THTT Copyright by SR Technics Switzerland Corresponding with EASA Part-66 For training purposes only Cat: B2 5.1 - 2 Basic Maintenance Training Manual Digital electronics has opened an extreme wide door for new developments. Cathode Ray Tubes (CRTs) are used as multifunctional displays in the modern “glass cockpits”. A single display replaces a number of mechanical analog type indicators. Module 5 Digital Technology / EIS 5.1 Electronic Instrument Systems In addition of displaying instrument indications, CRTs may be used to display check lists and operational history of the portions of a system which are showing trouble, suggest corrective action, and display any performance reduction caused by the malfunction. Figure 1: Analog vs. Digital Cockpit Instrument Systems Sep04 / THTT Copyright by SR Technics Switzerland Corresponding with EASA Part-66 For training purposes only Cat: B2 5.1 - 3 Basic Maintenance Training Manual Electronic Instrument System - General Module 5 Digital Technology / EIS 5.1 Electronic Instrument Systems Figure 2: EIS Interface Block Diagram of an MD11 The Electronic Instrument System (EIS) is an avionics system connected with most of the aircraft systems to carry out the two following main display functions: Electronic Flight Instrument System & Electronic Centralized Aircraft Monitor. EIS = EFIS + ECAM The Electronic Flight Instrument System (EFIS) enables all flight and navigation informations to be communicated to the crew. The cathode ray tube display units group together the parameters from the following conventional instruments as installed on the DC-10. Listed in the right column are the corresponding EIS display units, featuring those indications on an MD-11, see block diagram to the right. Attitude Director Indicator, ADI PFD Horizontal Situation Indicator, HSI ND Altimeter PFD Mach Airspeed Indicator PFD Weather Radar indicator ND Flight Mode Annunciator, FMA PFD The Electronic Centralized Aircraft Monitor (ECAM) enables the visualisation of the information concerning normal and abnormal state of the aircraft systems (EAD and SD). In other aircraft it’s named Engine Indication And Crew Alerting System (EICAS). Note: As a typical system arrangement the simplified block diagram on the right side shows the EIS interface of an MD-11. A short description of the components is given in the introduction on the next page. Sep04 / THTT Copyright by SR Technics Switzerland Corresponding with EASA Part-66 For training purposes only Cat: B2 5.1 - 4 Basic Maintenance Training Manual MD-11 Electronic Instrument System Arrangement • The EIS components are: • • • • • • six Display Units (DU), mounted on the instrument panel, two Source Input Select Panels (SISP), mounted on the instrument panel, two Electronic Flight Instrument Control Panels (ECP), located in the glareshield, one Systems Control Panel (SCP), located in the pedestal, one Remote Light Sensor (RLS), located on the glareshield, and three Display Electronic Units (DEU), located in the Electronics Bay. Note: Each DEU manages all EIS functions (EFIS on PFD and ND and ECAM on EAD and SD) and - in case of dual DEU faults - a single DEU could control all six display units simultaneously (see EIS SOURCE switching on the previous block diagram). Module 5 Digital Technology / EIS 5.1 Electronic Instrument Systems SYSTEMS DISPLAY (SD) Displays either secondary engine data (engine oil temperature, pressure, and quantity), or systems pages like hydraulics, electrical, air (environmental), fuel, configuration and miscellaneous (not categorized systems) with the associated alerts and consequences. The SD can also present the aircraft status and consequences, resulting from all alerts, and it may be used to display an ND image in case of a DU fault. EIS Controls The PFD and ND are controlled through an EFIS Control Panel (ECP), one for each pilot, located to the left and to the right of the Flight Control Panel (FCP). All of them are part of the Glareshield Control Panel (GCP). The Systems Display is controlled through a Systems Control Panel (SCP) located in the pedestal aft of the throttles. The EIS displays consist of: • • • PRIMARY FLIGHT DISPLAY (PFD) Displays attitude, airspeed, barometric altitude, radio altitude, vertical speed, heading, vertical and lateral deviation, limits, configuration, and flight modes. NAVIGATION DISPLAY (ND) Displays a pictorial representation of the aircraft position and relevant waypoints, navaids, airports and other flight plan background data and weather radar or terrain displays (the last available, if an Enhanced Ground Proximity Warning System is installed). ENGINE/ALERT DISPLAY (EAD) Displays the primary engine data N1, N2, EGT, (EPR optional), fuel flow and alert messages. Sep04 / THTT Copyright by SR Technics Switzerland Corresponding with EASA Part-66 For training purposes only Cat: B2 5.1 - 5 1 . • EFIS DU’s = PFD + ND EFIS 2 DU’s are installed on the center instrument panel. The Electronic Instrument System (EIS) comprises captain's and copilots EFIS (Electronic Flight Instrument System) and the ECAM (Electronic Centralized Aircraft Monitor) system. They display flight and navigation data on each pilot instrument panel. DMC-3 is in stand-by. Each pilot's EFIS includes 2 DU’s. In normal configuration: EIS data are presented on 6 identical color Cathode Ray Tubes (CRT) type Display Units (DU). the remaining DU’s can be reconfigured to ensure the display of all required information.Basic Maintenance Training Manual Module 5 Digital Technology / EIS 5. DMC-2 supplies data to copilot's EFIS DU’s and the SD (lower ECAM DU). The upper DU will be allocated to the Engine/Warning Display (E/WD) and ECAM The ECAM data are displayed on an upper DU. called Engine and Warning Display (E/WD) and a lower DU called System Display (SD). In case of a DU failure.6 . The layout of the 6 DU’s will be presented as follows: General 2 DU’s are installed side by side in front each pilot. an EIS DMC switching selector allows to replace the failed DMC by DMC-3. one ND and either ECAM E/WD or SD. Each DMC has independent EFIS and ECAM channels and is able to drive simultaneously one PFD.1 Electronic Instrument Systems A320 Electronic Instrument System Presentation EIS data are presented on 6 identical Display Units (DU). The outer DU will be allocated to the Primary Flight Display (PFD) function and the inner DU will be allocated to the Navigation Display (ND) function. The ECAM channel acquires and processes signals received from sensors and computers via two SDAC’s (System Data Acquisition concentrator) and from two FWC’s (Flight Warning Computer) and generate the images to be displayed on E/ WD and SD. The EFIS channel acquires and processes signals received from navigation and auto flight systems and generate the images to be displayed on PFD and ND. • ECAM DU’s = E/WD + SD Figure 3 illustrates the cockpit arrangement of the EIS system Figure 3: Cockpit Arrangement Display Management Computer EFIS and ECAM DU’s are driven by three identical Display Management Computers (DMC). Sep04 / THTT Copyright by SR Technics Switzerland EIS SWITCHING PANEL Corresponding with EASA Part-66 For training purposes only Cat: B2 5. a Primary Flight Display (PFD) and a Navigation Display (ND). DMC-1 supplies data to captain's PFD and ND (EFIS DU’s) and the E/WD (upper ECAM DU). the lower DU will be allocated to the System Display (SD). If DMC-1 or 2 fails (indicated by a diagonal line on the corresponding DU’s). one above the other. In normal operation. Upper ECAM DU failed or switched OFF The E/WD image is automatically transferred to the lower ECAM DU. Sep04 / THTT Copyright by SR Technics Switzerland Corresponding with EASA Part-66 For training purposes only Cat: B2 5. which will cross-change the images between the PFDU and the NDU. W This transfer can also be achieved manually by pressing the PFD/ND XFR push button. the E/WD will reappear.Basic Maintenance Training Manual DU Reconfiguration Module 5 Digital Technology / EIS 5. SDU FAILED NDU failed or switched OFF In case of a NDU failure. After 30 seconds. the E/WD will reappear.1 Electronic Instrument Systems Figure 4: DU Reconfiguration PFDU failed or selected OFF In case of a PFD Unit failure.7 . the ND image can be displayed on the PFDU instead of the PFD image by pressing the PFD/ND XFR push button. The SD images may be displayed instead of the E/WD image on a NDU (ECAM/ND XFR selector on CAP or F/O) by depressing and holding the desired system page key on ECAM control panel. Lower ECAM DU failed or switched OFF The SD image may be displayed either: • On NDU by means of the ECAM/ND XFR selector on the SWITCHING panel or • On the upper ECAM DU instead of the E/WD image by depressing and holding the desired system page key on ECAM control panel. The SD images may be recovered either: • On a NDU by use of the ECAM/ND XFR selector on the SWITCHING panel or • On the lower ECAM DU instead of the E/WD image by depressing and holding the desired system page key on the ECAM control panel.1 . After 30 seconds. Both ECAM DU’s failed • • The E/WD image may be displayed on the NDU by use of the ECAM/ND XFR selector on the SWITCHING panel. After 30 seconds. the E/WD will reappear. the PFD image is automatically transferred to the ND Unit. • Vertical and lateral deviations. • To navigate by means of two Navigation Displays (ND). In case of avionic ventilation failure. DMC 2 Normally. the grey background is suppressed in order to limit PFDU power consumption and to prevent them from overheating. Primary Flight Display (PFD) ECAM DU 2 MASTER WARN MASTER WARN ECAM CONTROL PANEL MASTER CAUT MASTER CAUT DMC 1 DMC 3 The Primary Flight Display provides mainly: • Attitude and guidance information.1 Electronic Instrument Systems ND 2 ECAM DU 1 The Electronic Flight Instrument System (EFIS) presents to the flight crew the data necessary: • To control the aircraft by means of two Primary Flight Displays (PFD).FLIGHT PHASE . • Radio Nav information (ILS.RED WARNINGS . • FMGS modes (flight mode annunciation).SYSTEM PAGES . PFD 2 PFDU’s and NDU’s are driven by the EFIS channels of the DMC’s. a grey background is displayed on speed.MEMO INFO Sep04 / THTT Copyright by SR Technics Switzerland SDAC 2 A/C SYSTEMS SENSORS INPUTS FOR : .AMBER CAUTIONS .8 . FWC 1 SDAC 1 A/C SYSTEMS SENSORS INPUTS FOR : .1 .Basic Maintenance Training Manual Main Components and Subsystems Figure 5: EIS A320 System Architecture EFIS 1 PFD 1 EFIS EFIS 2 ND 1 Module 5 Digital Technology / EIS 5. heading and altitude are monitored by the FWC’s.SYSTEM PAGES FWC 2 NA V & AFS SENSORS FADEC FQI LGCIU FCDC Corresponding with EASA Part-66 For training purposes only Cat: B2 5. heading and altitude windows. • Airspeed. • Altitude (baro and radio) and vertical speed • Heading and track. DME). Main parameters such as attitude. Wind direction and speed: Wind direction in numeric form with respect to true north and by green arrow with respect to magnetic north (only displayed when wind speed is >2 kt). NOTE: In case of avionic ventilation failure. the following characteristics of the corresponding navaid are displayed in white for VOR or in green for ADF on the onside ND: a) Type of navaid (ADF or VOR-1 on left side. ADF or VOR-2 on right side). 3. d) DME distance if VOR is selected and a co-located DME station is available. e) Mode of tuning.9 .1 Electronic Instrument Systems Navigation Display (ND) Five different display modes are available: • ROSE VOR • ROSE ILS • ROSE NAV • ARC • PLAN A weather radar image can be superimposed on the ND in all modes except PLAN. Fixed small white triangles are arranged at 45° intervals around the circumference line. Corresponding with EASA Part-66 For training purposes only Cat: B2 5. b) Shape and color of associated bearing pointer c) Navaid identification.Basic Maintenance Training Manual Figure 6: PFD General Arrangement Module 5 Digital Technology / EIS 5. the weather radar image is suppressed in order to limit DU power consumption and to prevent them from overheating. 6. In case of no wind or no wind information available. Sep04 / THTT Copyright by SR Technics Switzerland 1. the corresponding numerical value is replaced by dashes (ADIRS computed) 7. Aircraft symbol (yellow): Fixed.1 . Ground Speed / True Air Speed (green) Computed by ADIRS. pointing vertically up to the yellow lubberline. 4. Navaids: When on the EFIS control panel either ADF/OFF/VOR selector switch is set to ADF or VOR. Aircraft heading: The aircraft magnetic heading is given by a fixed yellow lubber line and a white moving compass rose. Actual track (green) 5. Selected heading or track (blue): Displays the value indicated on the HDG TRK counter of the FCU. 2. "TRU" is displayed when true heading is displayed instead of magnetic heading (latitude above N 73° or S 60°). VOR course pointer (blue): Dagger shaped symbol points to the selected VOR course. Localizer deviation bar (magenta): Moves laterally on a scale with respect to the course pointer. 13 4 ROSE ILS Mode 3 1. provided LOC TRK or LAND TRK mode is engaged. When lateral deviation is above 10°. Glide slope deviation: Magenta diamond moves on a vertical scale. ILS-2 information is displayed on PFD-2 and ND-1. VOR APP message (green): Displayed when a VOR approach has been selected. The arrow on the bar gives the TO/FROM indication.8°. The scale consists of two white dots on each side of the yellow reference line. Chrono indication (white): Displays elapsed time when onside chrono is started. If no course has been entered. 3. Figure 7: ROSE VOR Mode 11. Nothing for navaid automatically tuned by the FMGC. 9.Basic Maintenance Training Manual f) g) h) M (underlined and dimmed) for navaid manually tuned on the MCDU. Selected ILS information: Selected ILS frequency (magenta) course (blue) and identification (magenta). In case of excessive deviation (1 dot) above 100 ft RH. the associated bearing pointer is not displayed. 8 10 1 14 9 80 160 11 M 7 8. 2 5 13. Lateral deviation bar (blue): Indicates the VOR deviation on a lateral scale. 10. the scale and diamond will flash. ILS APP message (green): Displayed when an ILS approach has been selected. VOR information (white): Selected VOR frequency.1 Electronic Instrument Systems Bearing pointer: a) ADF in green b) VOR in white c) If the tuned navaid is not received. Each dot represents 5°. 5. Range marks: The range scale value selected on the EFIS control panel (10 to 320 NM) governs the scale of the ND. ILS course pointer (magenta): Dagger shaped symbol points to the selected ILS course. 2. the bar remains displayed on the outer dot. 12. R (underlined and dimmed) for navaid tune on an RMP. provided G/S TRK or LAND TRK mode is engaged. 4.1 . 12 6 14.4°. Sep04 / THTT Copyright by SR Technics Switzerland Corresponding with EASA Part-66 For training purposes only Cat: B2 5. In case of excessive deviation (1/4 dot) above 15 ft RH. the bar and scale will pulse.10 . Each dot represents a deviation of about 0. course and identification (decoded by the receiver) and the mode of tuning (M or R). the value is defaulted to 360°. Its scale consists of two dots on either side of zero deviation. The ILS is selected either by FMGC (auto tuned or manually) or through the RMP in back up mode. ILS-1 information is displayed on PFD-1 and ND-2. Each dot represents a deviation of about 0. The VOR course is selected either by FMGC (auto tuned or manually) or through RMP in back up mode. Module 5 Digital Technology / EIS 5. Heading scale 1/2 of the selected range. Figure 8: Rose ILS Mode 4 5 3 8. Cross track error: Lateral deviation in NM Left or Right from the active flight plan (related to great circle route). TO waypoint information (see ARC mode) 10.1 Electronic Instrument Systems Navaids are displayed as follows: • Green if it is a current waypoint of the actual flight plan. • Blue when it is tuned for display either automatically by the FMGC or manually through the MCDU. 6 8 Figure 9: NAVAIDS DME or TACAN VOR VOR/DME NDB Sep04 / THTT Copyright by SR Technics Switzerland Corresponding with EASA Part-66 For training purposes only Cat: B2 5. 7. (selected for display with option keys on EFIS control panel).11 . • Magenta when the navaid is not part of the flight.1 . provided an ILS station has been selected.Basic Maintenance Training Manual Module 5 Digital Technology / EIS 5. 2 Figure 10: Rose Nav Mode 80 160 10 1 9 11 Rose Nav Mode 7 See "Figure 10: Rose Nav Mode" on page 11 6. ILS course (magenta): Displayed when the ILS key on EFIS control panel is pressed. Flight plan (see ARC mode) 9. Range marks and values: Inner circle represents 1/4 of the selected range. • White if it is the TO waypoint. Range marks and values: Inner circle represents 1/4 of the selected range. If the primary flight plan is not active. The part of the flight plan which is before the interception point is drawn as a green dotted line. except the last WPT of the SID and the first WPT of the STAR are not displayed when ND range 160 or 320 is selected. Active flight plan remains displayed. 1. Corresponding with EASA Part-66 For training purposes only Cat: B2 5. it is represented by a green dotted line. The scale of the map is chosen by the range selector (the diameter of the outer circle corresponds to the selected range). ARC mode provides the same information as ROSE NAV mode. Temporary flight plan: The revised portion of the flight plan is represented by a yellow dotted line. PLAN mode Displays statistically the F-PLN legs on a true north oriented map.12 . 2.1 Electronic Instrument Systems SID and STAR. Secondary flight plan: Represented by a continuous white line. Only the part of the flight plan which is ahead of the aircraft is displayed as well as the waypoints which are still to be overflown plus the waypoint from which the aircraft is coming. Missed approach and alternate flight plan: The missed approach is represented by a continuous blue line and the alternate flight plan route by a dotted blue line. Third circle represents 3/ 4 of the selected range.Basic Maintenance Training Manual ARC Mode Figure 11: ARC Mode – 2 – – – 1 Module 5 Digital Technology / EIS 5. Second circle represents 1/2 of the selected range. Heading scale represents selected range. selectable through the MCDU.1 . Flight plan: Various types of flight plan can be displayed. ROSE NAV or PLAN mode when a missed approach waypoint and/or an alternate F–PLN waypoint are displayed on the onside MCDU. – Active flight plan: A continuous green line represents the flight plan actually followed by the aircraft when AFS NAV mode is engaged. limited to the forward 90° sector. Flight plan capture: When the aircraft is off the primary flight plan and flying towards it in HDG mode and NAV mode armed. The map is centered on a map reference point which is chosen by the pilot on his MCDU using slew keys. the new active flight plan is displayed in a continuous green line provided the FMGC has computed the intercept path. Sep04 / THTT Copyright by SR Technics Switzerland Navaids data and bearing pointers are not available in this mode. They are displayed in ARC. 13 . Its position represents the actual aircraft position in respect to the flight plan. Sep04 / THTT Copyright by SR Technics Switzerland Corresponding with EASA Part-66 For training purposes only Cat: B2 5. Map reference point: Waypoint displayed on the second line of the flight plan displayed on the MCDU F-PLN page. Aircraft symbol (yellow): The orientation of the aircraft symbol indicates the true track.1 .7L WR WEAK 3 _ 1. 1. 3. Failure messages: Following failure message can be displayed: – WR RT (red) radar transceiver failure – WR ANT (red) antenna failure – WR CTL (red) control panel failure – WR RNG (red) range error – WR WEAK (amber) calibration failure – WR ATT (amber) attitude information failure Offset annunciation: Indicates cross track deviation to the left (L) or right (R) of the flight plan route in NM. Weather radar image: Displayed when the radar is selected on and the ND is not in PLAN mode. It can be either the active TO waypoint or any other waypoint of the flight plan. 2. red and magenta according to the precipitation rates. Tilt angle / gain mode: Shows antenna tilt angle (angle between horizon and radar beam axis) in degrees and quarter of a degree (blue). When selected. yellow. the MAN gain mode is displayed in green. 3. The echoes are displayed in green. 2.1 Electronic Instrument Systems Weather Radar Display Figure 12: ¨Plan Mode Figure 13: Weather Radar Display 2 1 1 2 3 .Basic Maintenance Training Manual Module 5 Digital Technology / EIS 5. The echo refresh rate depends on the selected range. 14 . the weather radar TILT is replaced by a blue TERR. EGPWS terrain picture: The ND presents the EGPWS terrain picture when the TERR ON ND switch is selected ON and the ND is not in PLAN mode. If the message is in amber. 3.1 . if the current selected display mode is PLAN.1 Electronic Instrument Systems Figure 15: Colour Code of the EGPWS WR STAB (amber) antenna stabilization failure In case of red failure messages. TERR indication: To differentiate the terrain from the weather display. 4. is displayed and there is no failure. TERR: CHANGE MODE indication: Displayed in red (or amber) in case of Terrain Awareness Display (TAD) warning (or caution) alert. The terrain picture replaces the weather radar image. these messages are flashing 9 seconds. and the terrain display sweeps from the center outward to both sides of the ND.Basic Maintenance Training Manual – Module 5 Digital Technology / EIS 5. EGPWS Figure 14: EGPWS Display 1. the image is not affected. Sep04 / THTT Copyright by SR Technics Switzerland 2. then remain steady until the caution or warning alert condition disappears. no radar image is displayed. – TERR RNG (red) for a RANGE error warning – TERR TST (amber) appears during the EGPWS test when the terrain pattern. Corresponding with EASA Part-66 For training purposes only Cat: B2 5. Warning and caution messages: – TERR AHEAD (amber) for a caution – TERR AHEAD (red) for a warning When triggered. The terrain appears in different colours and densities according to its relative height: see "Figure 15: Colour Code of the EGPWS" on page 14. 15 . Sep04 / THTT Copyright by SR Technics Switzerland Corresponding with EASA Part-66 For training purposes only Cat: B2 5. the system does not protect against FMS 1 position error. Thus the Terrain Awareness Display (TAD) does not protect against baro setting errors.1 . Module 5 Digital Technology / EIS 5. the terrain is automatically displayed and the ON light of the TERR ON ND push button switch comes on. CAUTION: a) The relative height of the aircraft is computed using the captain baro setting.1 Electronic Instrument Systems The Terrain Awareness Display and Terrain Clearance Floor (TCF) functions operate using the FMS 1 position.Basic Maintenance Training Manual b) Figure 16: EGPWS Display 5. Thus. The area of conflict is displayed in solid yellow. Terrain caution alert: This alert is generated when a conflict exists between the terrain caution envelope ahead the aircraft and obstacles stored in the database. 6. Terrain warning alert: This alert is generated when a conflict exists between the terrain warning envelope ahead the aircraft and obstacles stored in the database. The area of conflict is displayed in solid red. NOTE: When an alert is generated (either caution or warning) and the TERR ON ND is not selected. System Data Acquisition Concentrator (SDAC) Priority rules Three levels have been defined for warnings / cautions: A level 3 warning has priority over level 2 caution which has priority over level 1 caution. fuel quantity indication. Two identical units acquire data required by the 3 DMC’s. • Decision height call out. • Warning and caution alerts or memo messages. • Permanent flight data. memo informations. • RED: For configuration or failure needing immediate action. • BLUE: For actions to be carried out or limitations. In a same level. Aural alert and voice messages are emitted through the cockpit loudspeakers. • GREEN: For normal long term operation. master warning and master caution lights for each pilot and the ECAM control panel. for inhibition messages). The ECAM presents following data on an Engine/Warning Display (E/WD) and a System Display (SD): • Engine primary indications. Items affected by such a bulletin cause the display of the message "REFER TO QRH PROC" on the EWD and/or SD.1 Electronic Instrument Systems ECAM Color code The ECAM (Electronic Centralized Aircraft Monitor) consists of 2 DU’s (upper and lower). • Through the SDAC’s for amber cautions. Additional FWC functions are: • Radio altitude call out. Sep04 / THTT Copyright by SR Technics Switzerland Corresponding with EASA Part-66 For training purposes only Cat: B2 5. Secondary failure: Loss of an item of equipment or system resulting from a primary failure The alert messages elaborated by the FWC’s are displayed on the ECAM DU’s.g. flaps and slats position indication.Basic Maintenance Training Manual Module 5 Digital Technology / EIS 5. 2 System Data Acquisition Concentrators (SDAC). • WHITE: For titles and remarks used to guide during procedures. cautions and procedures which are affected by Operations Engineering Bulletins (OEB). aural alerts. • Landing distance and landing speed increments computation. Types of failure Primary failure: Failures of an item of equipment or system causing loss of others in the aircraft. Two identical computers acquire data for the generation of alert messages. synthetic voice messages and flight phases computation: • Directly from A/C sensors or systems to generate red warnings. A color code is used on both ECAM DU’s according to the importance of the failure or the indication. • A/C systems synoptic diagrams or status messages. for the display of system pages and engine parameters and by the FWC’s for generation of ECAM messages and aural alerts.16 . • AMBER: For configuration or failure needing awareness but not immediate action. an order of priority has been defined in the FWC. The DU’s are driven by independent ECAM channels contained in the DMC’s. even when they are switched off. 2 Flight Warning Computers (FWC).1 . A database in the FWC’s enables to store a list of warnings. Flight Warning Computer (FWC) Independent failure: Failures which affect an isolated item of equipment or system without influence on others in the aircraft. • MAGENTA: For particular messages (e. Warning message (red) on E/WD. Failures leading to a loss of redundancy or system degradation. Single Chime (SC).g. Sep04 / THTT Copyright by SR Technics Switzerland Corresponding with EASA Part-66 For training purposes only Cat: B2 5. Automatic call of the relevant system page on SD*. • System failure altering flight safety (e. eng. overspeed).1 Electronic Instrument Systems ECAM Warnings and Cautions Table 1: ECAM Warning / Caution classification Level Signification Level 3 Red warning Situation needing immediate action: • Aircraft in dangerous configuration or limit flight conditions (e. MASTER CAUT light amber steady. None Master Warn light red flashing or specific red light. The affected parameter pulses green. Automatic call of relevant system page on SD*. • Automatic call of the relevant system page on the SD. None • • • Advisory System parameters monitoring None Memo Information Recalls normal or automatic selection of functions which are temporarily used.17 . • Green. Caution message (amber) on E/WD.g. • Caution message (amber) on E/WD generally without procedure.1 . System failure having no direct consequence on flight safety (e. excess cabin alt) Failure Mode Level 2 Level 1 Aural Visual • Continuous Repetitive Chime (CRC) or specific sound or synthetic voice. fire. amber or magenta message on E/WD: Information * Some warnings do not automatically call up a system page.Basic Maintenance Training Manual Module 5 Digital Technology / EIS 5. Amber caution Requires crew monitoring. BLUE HYD LO PR). stall.g. • • Amber caution Abnormal situation needing immediate crew awareness but no immediate action. even if a inhibition phase follows. LDG INHIBIT PITCH TRIM NOT IN TO RANGE (red) RUD TRIM NOT IN TO RANGE (red) NOTE: These flight phases are different and independent from the ones used by the FMGC. AFTER LIFT OFF LIFT OFF 80 KT 1ST ENG to PWR ELEC PWR 1ST ENG STARTED Figure 17: Flight Phases Table 2: Configuration Warnings SLATS/FLAPS NOT IN TO RANGE (red) 10 In order to avoid disturbing alerts especially during high workload phases like takeoff or landing. CONFIG push button is pressed (ECAM control panel) or when take-off power is applied: 1 2 3 4 5 6 7 8 9 5MIN AFTER 2ND ENG SHUT DOWN 80 KT TOUCH DOWN 800 FT 1500 FT OR 2 MIN.O. the warning will come on immediately and remain displayed as long as it is present. Sep04 / THTT Copyright by SR Technics Switzerland Corresponding with EASA Part-66 For training purposes only Cat: B2 5. If the failure occurs during an inhibition flight phase.1 Electronic Instrument Systems Flight phases Configuration warnings The FWC computes ten flight phases: The FWC’s trigger following warnings/cautions when the aircraft is not in take-off configuration when the T.O. When those inhibitions are in effect.O. the alert will come on only when the inhibition phase is over and will remain displayed as long as the failure is present. Config Test T. INHIBIT.Basic Maintenance Training Manual Module 5 Digital Technology / EIS 5. Power applied DOOR NOT CLOSED (amber) 3 4 PARK BRAKE ON (red) 5 FLEX TEMP NOT SET (amber) Effect on E/WD: a) b) If a failure occurs before the inhibited flight phase.O.18 .1 . SPEED BRAKES NOT RETRACTED (red) Flight Phase Inhibition SIDESTICK FAULT (red) Figure 18: Flight Phase Inhibition BRAKES HOT (amber) a b 1 2 inhibited phase T. following magenta MEMO messages will be displayed: T. warning/caution inhibitions related to flight phases are performed. Basic Maintenance Training Manual Module 5 Digital Technology / EIS 5. NIL Emergency cabin call 3 sec.40. repeated 3 times NIL *** Mechanic call As long as p/b depressed. NIL SELCAL call Permanent Depress RESET key on ACP. Height announcement below 400 ft Permanent NIL See GPWS Permanent NIL Corresponding with EASA Part-66 For training purposes only Cat: B2 5.5 sec. Amber caution 1/2 sec. Altitude alert 1. Second push on TAKE OVER p/b. Landing capability change 1/2 sec. NIL A/P disconnection by TAKE OVER p/b 1.19 . 50. (3 pulses) NIL Stall Permanent NIL Cabin call 3 sec. 100. 30.1 Electronic Instrument Systems Sounds Definition Table 3: WARNING SIGNALS Continuous Repetitive Chime Single Chime Cavalry charge Click Cricket +STALL (synthetic voice) Buzzer*** Continuous Buzzer *** C Chord Auto call out 300. 10 MINIMUMS (synthetic voice) Ground Proximity Warning (synthetic voice) Sep04 / THTT Copyright by SR Technics Switzerland CONDITION DURATION SILENCING * Red warnings Permanent Depress ** MASTER WARNING light. 20. A/P disconnection due to failure Permanent Depress MASTER WARNING light or TAKE OVER p/b. or permanent Select new altitude or press MASTER WARNING light.5 sec.1 . Every 5 seconds until thrust is increased. TCAS (synthetic voice) See TCAS Permanent NIL Current thrust is not sufficient to recover a positive flight through pitch control. *** May be cancelled by depressing MASTER CAUT push button. Sep04 / THTT Copyright by SR Technics Switzerland Corresponding with EASA Part-66 For training purposes only Cat: B2 5.20 .1 Electronic Instrument Systems Table 3: WARNING SIGNALS CONDITION DURATION SILENCING * WINDSHEAR (synthetic voice) Windshear Repeated 3 times NIL PRIORITY LEFT PRIORITY RIGHT (synthetic voice) A/P take over p/b 1 sec. NIL RETARD (synthetic voice) Thrust lever not in idle position for landing Permanent Retard thrust levers. Thrust lever(s) Both sidesticks are moved simultaneously Every 5 seconds One sidestick deactivated SPEED SPEED SPEED (synthetic voice) DUAL INPUT (synthetic voice) * All aural warnings may be cancelled by depressing the EMER CANC key on the ECAM control panel.1 .Basic Maintenance Training Manual Module 5 Digital Technology / EIS 5. ** Except for OVERSPEED or L/G NOT DOWN warnings. Independent Failure Messages elaborated by the FWC: • Warning/Caution messages when a failure occurs. • Slats/Flaps position. Figure 20: Independent Failure 1 2 Figure 19: Engine Warning Display 3 4 1. It presents: Memo or On the upper part: • Engine parameters.Basic Maintenance Training Manual Module 5 Digital Technology / EIS 5. As soon as a failure is detected by the FWC and provided there is no flight phase inhibition active. The scrolling of the messages can be controlled by successive CLR actions on the ECAM control panel.g. On the lower part: Special messages (e. LAND ASAP). • Fuel on board (FOB). (e. 4.1 . the E/WD displays the title of the failure and actions to be taken. The lower part dedicated to ECAM messages is divided in two parts of seven lines each. • Memo messages. Most action lines are automatically cleared when corresponding actions have been taken. Insufficient space to display all messages on the right or left part) a special symbol is displayed.g. AP OFF. Name of the system affected by a failure and displayed here in case of overflow of the left part (amber or red).21 .1 Electronic Instrument Systems Engine / Warning Display (E/WD) Secondary failure or The Engine/Warning Display is normally displayed on the upper ECAM DU. Overflow symbol (green) In case of overflow. Action line (blue) 3. Left part: Primary or independent warnings / cautions or Memo information. Independent failure (amber or red) 2. Right part: Title of system affected by a primary or independent warning / caution in case of overflow on the left part or Sep04 / THTT Copyright by SR Technics Switzerland Corresponding with EASA Part-66 For training purposes only Cat: B2 5. Basic Maintenance Training Manual Primary and Secondary Failure Figure 22: T.O CONFIG test is requested again if the configuration becomes abnormal. Blue if action is not done.O. The LDG MEMO appears: • Below 2000 ft RH if the landing gear is down. disappears when action is performed. provided at least one engine is running.22 .1 Electronic Instrument Systems Green Blue as long as action not performed. A secondary failure is identified by a star preceding the title of the affected system.O. Secondary failures (amber) Module 5 Digital Technology / EIS 5. Primary failure (amber or red) 6. TO and LDG memos or • TO and LDG memo are displayed during the related flight phases as follows: The T.. Action line (blue) 7.. CONFIG NORMAL" if the aircraft configuration is correct.1 . "T.O. but can be amber in case of abnormal situation. Sep04 / THTT Copyright by SR Technics Switzerland Corresponding with EASA Part-66 For training purposes only Cat: B2 5.. "AUTO BRK MAX" will be displayed in green. CONFIG test push button is pressed. It disappears at take-off power application.O.O. Manual T.O. } 7 A primary failure is identified by a boxed title. When action is performed. The memo messages are normally green. It disappears after touch down (<80 kt). The memo gives the list of functions or systems which are temporarily used under normal operation. Memos Figure 21: Primary and Secondary Failure 5 6 5. or • When the T.. MEMO Display It is replaced by "T.TEST" disappears when the T. Below 800 ft RH if the landing gear is not down... MEMO appears: • 2 minutes after second engine start. CONFIG push button is pressed. NOTE: The overflow symbol can also be displayed in case of secondary failures overflow. CONFIG. It presents: • Either an aircraft system synoptic diagram page.. related to a failure: As soon as a warning is triggered. CAB PRESS (cabin pressurization) 4.Basic Maintenance Training Manual Module 5 Digital Technology / EIS 5. ground spoilers) 11. braking.. FUEL 7. CRUISE Sep04 / THTT Copyright by SR Technics Switzerland Corresponding with EASA Part-66 For training purposes only Cat: B2 5... COND (air conditioning) 9. ENGINE (secondary engine parameters) 2. Automatic. WHEEL (landing gear.. the relevant system page is automatically displayed.1 Electronic Instrument Systems Selection modes Figure 23: Landing Memos Manual: Any system page (except CRUISE page) may be selected at any time be depressing the appropriate key on the ECAM control panel.... or • Automatic advisory mode: When a parameter drifts out of the normal range.. APU (auxiliary power unit) 8. The advisory mode is inhibited in some flight phases.. Figure 24: Example of a System Display The status page. "FLAPS.1 . The corresponding key will illuminate. HYD (hydraulic) 6..FULL" is displayed if GPWS LDG FLAP 3 push button is off.23 . "FLAPS. BLEED (air bleed) 3... The value (green) pulses as long as it is over the limit. A manual selection is cancelled in case of failure or advisory.. 1. System Display (S/D) The System / Status Display is normally displayed on the lower ECAM DU.CONF 3" is displayed if GPWS LDG FLAP 3 push button is pressed.. the relevant system page associated with the first warning message is automatically shown.. System pages 12 system pages can be displayed (for details see associated chapter).. F/CTL (flight controls) 12... ELEC (electrical power) 5... DOOR/OXY (doors / oxygen) pulsing parameter (green) 12 H 47 10.... Cruise Page Figure 28: Flight phase related system page display Provided no other mode is engaged. Figure 25: Advisory Message Advisory message Module 5 Digital Technology / EIS 5.1 Electronic Instrument Systems ** >1500 ft and slats/flaps retracted and not T. when the ENG MODE selector is set to NORM. It disappears 10 seconds after the end of the start sequence.1 . 5 6 Sep04 / THTT Copyright by SR Technics Switzerland 7 8 5 MIN AFTER 2ND ENG SHUT DOWN 80 KT TOUCH DOWN <10000 FT AND L/G EXTENDED 800 FT LIFT OFF 1500 FT Figure 27: 9 10 Corresponding with EASA Part-66 For training purposes only Cat: B2 5. after reaching 1500 ft with T. • The APU page appears when the APU MASTER switch is set to ON.O PWR 1ST ENG STARTED ELEC PWR Figure 26: 2 / 3 4 Phase 2: F/CTL page replaces WHEEL page for 20 sec. when either sidestick is moved (deflection >3° on pitch or roll) or when rudder pedals deflection is >22°.Basic Maintenance Training Manual NOTE: When an advisory is triggered while in ECAM single display configuration (one ECAM DU failed). It disappears when APU RPM >95% for 10 seconds or when the APU MASTER switch is set to OFF. an ADV message is displayed and the associated system key on the ECAM control panel will flash. the flight phase related system page is displayed as follows: 1 80 KT 1ST ENG T.O power or 1 min. • The ENGINE page appears at the beginning of the start sequence or CRANK selection.O power or slats/flaps extended.24 . except when the page is empty. GMT Greenwich Mean Time. Symbol displayed in case of overflow of left or right area. 7.Basic Maintenance Training Manual Status Page Displays following summary of the aircraft status after the occurrence of a failure: 1. Cancelled caution in white. Sep04 / THTT Copyright by SR Technics Switzerland Corresponding with EASA Part-66 For training purposes only Cat: B2 5. Procedures (correction to apply for landing) in blue. The altitude selected on the FCU is displayed in green when metric unit is selected. flight level) in blue. G load / ALT SEL The load factor (G LOAD) is displayed in amber when the value is out of limits (> 1. 9.25 . GW The Gross Weight is displayed in green as soon as the second engine is started.1 Electronic Instrument Systems } 10. 12. }6 4 { } 5 { }7 Temperature indications: Total Air Temperature (TAT) and Static Air Temperature (SAT) values are displayed in green. 5. 6. Maintenance status in white. Moreover the STATUS page appears automatically during descent when slats are extended.7 g). red or amber. 3. 2. It may be manually called by pushing the STS key on the ECAM control panel. Inoperative system in amber. If STATUS messages other than in the CANCELLED CAUTION or MAINTENANCE field are present. 8 NOTE: The titles of the different parts are white and underlined. Information in green. (Inhibited during flight phase 1 and 2). synchronized with the cockpit clock or CFDS internal clock. Limitations (speed. The STATUS page appears automatically once the crew has cleared all the pages corresponding to the current failure. 11. provided G LOAD parameter is not displayed. a boxed STS (status reminder) message is displayed on the E/ WD. Figure 30: Permanent Data 10 9 NOTE: Scrolling is controlled by successive CLR key action. Approach procedures in white. is displayed in green.1 . 8.4 or <0. the STS (status reminder) will flash. { 2 { 3 { 12 ALT SEL12000M GW 66000KG 11 Figure 29: Status Page 1 Module 5 Digital Technology / EIS 5. Moreover if at engine shut down MAINTENANCE is displayed. 4. • CLR keys illuminate.Basic Maintenance Training Manual Module 5 Digital Technology / EIS 5. Example: Figure 31: No Failure Detected E/WD RSVR OVHT SD Independent failure: . • SD presents the affected system page. Cockpit indication: • Single chime sounds. a local warning light directly controlled by the affected system can illuminate. • Master Caution or Master Warning lights illuminate (level 3 and level 2 alerts only).Title of failure . the crew must depress the CLR key until the normal E/WD and SD presentation reappears: • MEMO messages on the E/WD. • CLR keys extinguished. • MASTER CAUTION lights illuminate steady. • CLEAR keys on the ECAM control panel illuminate.1 Electronic Instrument Systems ECAM Sequence Failure detected In case of a failure detected by the ECAM: • E/WD presents the warning/caution messages. Corresponding with EASA Part-66 For training purposes only Cat: B2 5.1 . • Audio sound is triggered (level 3 and level 2 alerts only). (Example: Hydraulic reservoir overheat) In addition. OVHT is displayed in amber / MEMO information Sep04 / THTT Copyright by SR Technics Switzerland Flight phase related system page. Figure 32: Failure Detected E/WD SD After completion of the procedure. • FAULT light illuminates on overhead panel.26 .Actions to be performed MEMO information Synoptic of affected system appears automatically . • System page related to the present flight phase. • FAULT/OFF lights on. Figure 34: SD E/WD Figure 33: E/WD SD RSVR OVHT MEMO information Secondary failure F/CTL system page is automatically displayed. showing faulty spoiler (no.1 . Module 5 Digital Technology / EIS 5. the blue hydraulic system is depressurized. Independent failure and primary failure Sep04 / THTT Copyright by SR Technics Switzerland Secondary failure Corresponding with EASA Part-66 For training purposes only Cat: B2 5.27 .Basic Maintenance Training Manual The crew applies the ECAM required actions • By cancelling the MASTER CAUTION light.1 Electronic Instrument Systems The crew depresses CLR key Cockpit indications: • CLR keys remain illuminated. Cockpit indications: • FAULT/OFF lights illuminate on overhead panel. • By switching off the BLUE ELEC pump. • CLR keys illuminated. 3) and surface actuators pressure indication B in amber. Basic Maintenance Training Manual Module 5 Digital Technology / EIS 5. Cockpit indications: • FAULT/OFF lights on. The STATUS page is automatically displayed. • STS key illuminates.1 Electronic Instrument Systems The crew depresses CLR key a second time The crew depresses CLR key a third time Cockpit indications: • FAULT/OFF lights on. Sep04 / THTT Copyright by SR Technics Switzerland Corresponding with EASA Part-66 For training purposes only Cat: B2 5.1 . • List of inoperative systems. • Landing distance factors and information. providing: • Approach procedures. • CLR keys remain illuminated. Figure 36: SD E/WD Figure 35: E/WD SD / STATUS reminder MEMO display System page related to the flight phase reappears.28 . ND Brightness Control Knob B EFIS Display Controls The outer knob controls the brightness of both the weather radar image and the EGPWS(if installed) terrain display. In case of PFD failure. Full counterclockwise rotation switches the ND off. F/O 3 DMC-3 replaces DMC-2. The inner knob controls the general brightness of the ND symbology . B EIS DMC Selector A NORM E A DMC-1 supplies data to PFD-1. Sep04 / THTT Copyright by SR Technics Switzerland Corresponding with EASA Part-66 For training purposes only Cat: B2 5. PFD Brightness Control Knob Full counterclockwise rotation switches the PFD off . ND-2 and lower ECAM DU. DMC-2 supplies data to PFD-2.1 . EIS Switching Panel PFD / ND XFR Pushbutton Allows to manually transfer the PFD to the NDU and vice versa. The ND may be recovered by means of the PFD / ND XFR pushbutton. In this case the PFD image is automatically displayed on the NDU.29 .Basic Maintenance Training Manual Module 5 Digital Technology / EIS 5. the PFD is automatically transferred to the NDU.1 Electronic Instrument Systems Controls Figure 37: Cockpit Control Panels related to the EIS System C ECAM / ND Selector D Allows to transfer SD to either Captain's or Copilot's ND . ND-1 and upper ECAM DU. In case of dual failure (E/WD and SD). CAPT 3 DMC-3 replaces DMC-1. the selector allows to transfer the E/WD to either ND. Outer knob : Display Mode Selector Baro Reference Display Window Range 745 HP to 1050 HP. Adjusts the QNH value either in HPA or IN HG. Selects desired navigation display on onside ND . The light will extinguish when the warning situation no longer exists or when the MASTER CAUT. Pushing the knob from STD position activates the QNH bar setting again. The bars on the key are illuminated when FD/FPD display is selected ON.The ECAM panel EMER CANC key is pushed. Range Selector Selects desired viewing range on onside ND: NOTE: In case of mode or range data failure. MASTER WARN Lights (2) Flash red for level 3 warnings. The bars on the key are illuminated when function is ac tive. ARC or ROSE NAV mode. The deviation symbols are displayed when a valid ILS signal is received. Sep04 / THTT Copyright by SR Technics Switzerland Corresponding with EASA Part-66 For training purposes only Cat: B2 5. FD Key Selects/deselects FD bars display on PFD or Flight Path Director symbol display. Inner knob : C EFIS Control Panel Rotating it selects either HPA (Hecto Pascal) or IN HG (inches of mercury) display.1 Electronic Instrument Systems Figure 38: EFIS Control Panel and Master Warning. ADF / VOR Selectors (2) PFD CONTROL PART ND CONTROL PART Selects display of the VOR / ADF bearing pointers and DME distance on onside ND. MASTER CAUT Lights (2) Illuminate steady amber for level 2 cautions. specific sound or synthetic voice. STD will be displayed on PFD. The bars on the key are illuminated when ILS display is selected ON. Pulling knob selects standard baro reference setting. the default selection will be ROSE NAV mode and 80 NM range. accompanied by a continuous repetitive chime. when TRK FPA reference is se lected.Basic Maintenance Training Manual Module 5 Digital Technology / EIS 5. Only one key can be active at a time. Master Caution Lights Optional Data Display Keys (5) Baro Reference Selector Selects/deselects display of optional data in addition to the permanently displayed flight plan data. accompanied by a single chime. when in PLAN.The ECAM panel EMER CANC key is pushed.1 . . the CLR key or the EMER CANC key is pushed. .The MASTER WARN light is pushed (except for overspeed and STALL warning). The light will extinguish when the warning situation no longer exists or when: . Rotating the knob in STD mode has no effect. .The MASTER WARN light is pushed (except for overspeed and STALL warning).30 . D WARN The aural warning stops when: . ILS Key Selects/deselects LOC and GS display on the PFD.The ECAM panel CLR key is pushed (except for overspeed and STALL warning). -Cautions (level 2 and level 1) Depressing the key cancels any present caution alert (MC lights.. displaying following message: CANCELLED CAUTION .Holding the STS key depressed. NORMAL will be displayed for 5 seconds.... The STATUS page may be cleared by the CLR key or by depressing the STS key a second time.. then the E/WD will automatically appear again.. all system pages appear successively at 1 seconds interval as long as the key is depressed....In case of of a warning condition. The STATUS page is automatically selected.1 .O. The next status page. When depressed more than 3 seconds.. If no warning/caution is present.. E ECAM Control Panel STS Key When depressed the STATUS page appears on the SD.Warnings (level 3) Depressing the key cancels the present aural warning and extinguish MASTER WARNING lights.. the message T. displays the status page for 30 seconds.. system pages may be displayed by pressing and holding the system page key . the caution messages which have been cancelled by the EMER CANC key are recalled.. CLR Key RCL Key (2) Depress to recall warning/caution messages and the status page previously cleared by the CLR key or by the flight phase related automatic inhibition. Sep04 / THTT Copyright by SR Technics Switzerland EMER CANC Key (guarded) . .. if any will be displayed by releasing the key and pressing it again. When released the presently displayed page will remain displayed. . will change the ECAM display.. the key light will flash (no automatic system page display). In mono ECAM display: .Basic Maintenance Training Manual Module 5 Digital Technology / EIS 5. NORMAL will be displayed for 5 seconds.. Depressing the illuminated key a second time recalls the system page related to the present flight phase or the current warning. The ECAM message display is not affected. TO power application is simulated. a warning will be triggered.31 . Key illuminates after manual selection or when an advisory is detected. When depressed.(title of failure which is inhibited) The inhibition is automatically cancelled when flight phase 1 is initiated or manually when RCL key is depressed for more than 3 seconds. Full counterclockwise rotation switches the associated DU off. In mono ECAM display.The STATUS is only displayed when the STS key is pressed and hold... If the configuration is correct...1 Electronic Instrument Systems Figure 39: ECAM Control Panel System Page Keys (11) Display Brightness Control Knobs (2) TO CONFIG Key Depress to select the desired system page on the SD ... Manual brightness control is combined with automatic adjustment of the display brightness according ambient light conditions. CONFIG NORMAL is displayed. the E/WD image appears automatically on the lower DU . .. there will be no illuminated key light nor automatic system page display. Cat: B2 5.In case of an advisory condition. Depressing the CLR key when illuminated. When the upper display is turned off . If the aircraft is not in TO configuration. Corresponding with EASA Part-66 For training purposes only Illuminates as long as a warning/caution message or a status message is displayed. If there is no status message present.. ECAM message) for the rest of the flight. Illuminates as long as the STS page is displayed. ALL Key When depressed and held.. analog. Each integrates the EFIS and ECAM functions and is able to drive simultaneously one PFD. ND. These codes are sent in digital form. The acquisition modules enables the DMC to acquire all inputs signals: discrete. through a shielded pair of wires.1 . The three channels to the DU’s enable the DMC to process simultaneously data for three different images: PFD. Figure 40: Display Management Computer The operational programs corresponding to each channel are loaded into memory modules. digital and a dedicated weather radar bus. one ND and either ECAM display. The DMC’s acquire and process all the signals received from various aircraft sensors and computers. Each channel will ensure data management and processing in order to elaborate Sep04 / THTT Copyright by SR Technics Switzerland Corresponding with EASA Part-66 For training purposes only Cat: B2 5.Basic Maintenance Training Manual Display Management Computer Module 5 Digital Technology / EIS 5. called dedicated serial data link to the DU’s The DMC comprises four parts: Data acquisition.1 Electronic Instrument Systems the instructions for drawing the images which are required according to the pilot controls/selections and the A/C status/configuration. This design has been chosen to facilitate the independent reprogramming of the DMC for each channel Figure 41: General DMC Operation Basic Sections and Data Flow The 3 DMC’s are identical.and ECAM channel. in order to generate proper codes of graphic instructions corresponding to the images to be displayed. slipped in their respective slots through the DMC dog house front face. PFD -. using a very high speed transmission.32 . ND and one (upper or lower) ECAM Display Unit. analog board and brightness control circuit. The DU can be divided into the following basic sections: Cathode ray tube (CRT) assembly.1 . two light sensors located on the face of the tube. The digital board receives from the DMC. an optical filter on the face of the tube which improves the image contrast and reduces the reflection on the display screen. green and blue required to draw the image on the screen Figure 43: Cathode Ray Tube. digital board and interconnection board.1 Electronic Instrument Systems The High Voltage Power Supply provides all the voltage necessary to the CRT operation: Anode voltage. command modes and control words and generates the deviation signals X and Y and the video signals red. via the interconnection board. low voltage power supply. Sep04 / THTT Copyright by SR Technics Switzerland Corresponding with EASA Part-66 For training purposes only Cat: B2 5. very high voltage power supply. A screening assembly which protects the tube from electromagnetic fields. The CRT assembly consists of a shadow mask tube. electron beam focusing and acceleration voltage. The Low Voltage Power Supply is used to generate the DC voltage necessary to the electronic operation. a symbol generator program.Basic Maintenance Training Manual Display Unit Module 5 Digital Technology / EIS 5. a deviator which includes the deviation coils X and Y. Figure 42: Display Unit The analog board contains the electronic circuits necessary to control the CRT.33 . 1 .1 Electronic Instrument Systems Student Notes Sep04 / THTT Copyright by SR Technics Switzerland Corresponding with EASA Part-66 For training purposes only Cat: B2 5.34 .Basic Maintenance Training Manual Module 5 Digital Technology / EIS 5. and • EICAS (Engine Indicating and Crew alerting System) visualisation of the information concerning normal and abnormal state of the Engines and the aircraft systems The output of these systems is presented in the cockpit on five Display Units as shown in Figure 44 and via the Loudspeakers. flight control system. and crew alerting systems. pilot side • EICAS Display on DU#3. Center Main Instrument Panel • Multi-Function Display (MFD) on DU#4.1 Electronic Instrument Systems Display Description • Introduction Similar as on the other aircraft types the Electronic Instrument System on the Embraer 145 is divided into the following systems • EFIS (Electronic Flight Instrument System) providing all primary flight and navigation informations to the crew. Within the Electronic Instrument System. Through the MFD. integrated into one box. • • Primary Flight Display . and radio aids. navigation. there is a cross-talk bus called Intercommunication Control Bus (ICB). The PFD has references for airspeed. altitude. APU. The Integrated Computers system together with controllers and sensors form the Primus-1000 (P-1000) Honeywell System.PFD (DU’s 1 AND 5) The PFD is the primary flight reference for the flight crew members. ECS. you can set up to five system pages. The IC # 1 normally provides images to DU’s 1/2/3. the Integrated Computers perform symbol generator function for the EFIS. Other parts of the Integrated Computer are used for flight director and autopilot functions.35 . copilot side • Primary Flight Display (PFD) on DU#5. copilot side Electronic Instrument System Architecture Figure 44: Cockpit Arrangement of the Display Units These computers are called Integrated Computers because there are different parts with different functions. but it can be either a PFD or EICAS display. EICAS Display (DU-3) The EICAS display shows engine parameter. while the IC # 2 provides images to DU’s 4/5. Figure 45 shows the architecture of the system. Between the Integrated Computers. one electronic checklist page. attitude. fuel system. A detailed description of the interfaces to the different aircraft systems shown in the block diagram will follow in the paragraphs on EFIS and EICAS.Basic Maintenance Training Manual Embraer 145 EIS Presentation Module 5 Digital Technology / EIS 5. which is used for comparison purposes.1 . pilot side • Multi-Function Display (MFD) on DU#2.MFD (DU’s 2 AND 4) The MFD is used as navigation display in normal operation. Multi-function Display . Multi-Function Display Sep04 / THTT Copyright by SR Technics Switzerland Multi-Function Display Corresponding with EASA Part-66 For training purposes only Cat: B2 5. The five Displays are: • Primary Flight Display (PFD) on DU#1. symbol generator function as well as processing of the different warnings and messages for the EICAS. heading. EICAS Display Primary Flight Display Primary Flight Display The Integrated Computers system is the primary component of the whole avionics system. one TCAS page and one displayable maintenance messages page. Only the left MFD (DU-2) is also used to show the displayable maintenance messages. Basic Maintenance Training Manual Module 5 Digital Technology / EIS 5. Alt Radio Altimeter Radar Weather Radar RSB Radio System Bus Sep04 / THTT Copyright by SR Technics Switzerland Corresponding with EASA Part-66 For training purposes only Cat: B2 5.1 Electronic Instrument Systems Figure 45: Electronic Instrument System Architecture IC 600 Integrated Computer AHRS Attitude Heading Reference System WOW Weight on Wheel Sensing DAU Data Acquisition Unit TCAS Traffic Collision Avoidance System EGPWS Enhanced Ground Proximity Warning System R.1 .36 . Display Units (DU’s 1 and 5). This system uses four of large 8" x 7" CRT displays: • Two Primary Flight Displays (PFD’s). On the Primary Flight Display. Bezel of the PFD Side Slip Indicator Sep04 / THTT Copyright by SR Technics Switzerland Reference Value Selection for Altitude Corresponding with EASA Part-66 For training purposes only Cat: B2 5. • Two Multi-Function Displays (MFD’s).1 Electronic Instrument Systems Both the Primary Flight Display (PFD) and the Multi-Function Display (MFD) are divided into two parts: • Display Unit (DU).Basic Maintenance Training Manual Electronic Flight Instrument System (EFIS) The Electronic Flight Instrument System (EFIS) provides accurate flight indications through its displays. the most important parameters for the pilots to control the aircraft are displayed as shown on Figure 46. while the bezels have different part numbers. Figure 46: Description of the Primary Flight Display Flight Control System (Flight Mode Annunciator) Attitude Airspeed Altitude EHSI (Full or Partial Compass). Wind Vector Navigation (Heading Annunciation). Module 5 Digital Technology / EIS 5. DME Photocell Automatically adjusts the display brightness related to ambient illumination. These DU’s receive image information from the two integrated computers (IC-600 1 and 2).37 . • Bezel. Navigation (Active Source Annunciation). VSI/TCAS.1 . The DU’s have the same part number. Display Units (DU’s 2 and 4). will give you an overview of the EFIS System and will help you to understand the detailed diagram as shown on Sep04 / THTT Copyright by SR Technics Switzerland The DC-550 controls: • Navigation and weather radar display selection.IC-600 • Two Display Controllers . • Self-test function selection.38 . navigation information is displayed which enables the pilots to navigate the aircraft. EICAS information such as electronic checklist can also be displayed.Basic Maintenance Training Manual The Multifunction Display is divided into two parts: • On the upper part. • Set bearing pointer sources.1 .BL-871 • Two Integrated Computers . information about aircraft systems and engines is displayed. Aircraft System and Engine data Module 5 Digital Technology / EIS 5. Each DU-870 is a CRT with three video guns (red. Figure 47: Example of the Multifunction Display Navigation (Map and/or Plan Format). • On the lower part of the display. In case of failure of a system. Integrated Computer The IC-600 is the primary component of all the avionics system. and green) and with stroke and raster scanning techniques. or EICAS displays. Corresponding with EASA Part-66 For training purposes only Cat: B2 5.1 Electronic Instrument Systems The integrated display system of the aircraft has a 4-tube configuration.DC-550 • Two EFIS reversionary panels • A Flight Guidance Controller (GC-550) • Interface signals Display Unit The DU-870 is the electronic display used to supply the PFD EICAS and MFD information in the Primus-1000 system. and EICAS display. MFD. MFD’s. blue. Selection Keys for the Aircraft System Indication Display Controller Components of the EFIS The description of the Components and interfaces that follows. This configuration includes: • Two Primary Flight Displays (PFD’s) DU-870 • Two PFD bezels BL-870 • Two Multi-Function Displays (MFD’s) DU-870 • Two MFD bezels . The IC-600 has: • Symbol generator function • EICAS function • Flight director function • Autopilot function Bezel of the MFD Each IC-600 gives three distinctive images: for PFD’s. Bezel Different bezels are attached to the front part of the DU-870 to make them either: PFD. and other aircraft sensors. Each AHRS (or IRS) sends data separately to each IC-600. the DC-550 digitizes the signals to transmit them to the IC-600. systems. Reversionary Panel This panel supplies each flight crew member with cross-side information for: • Symbol generator • ADC • AHRS (or IRS) • Reversion of EFIS components Flight Guidance Controller This unit is responsible for the selection of: • Vertical speed target • Indicated airspeed or mach target • Preset altitude • Course • Heading • "Cross" bar or "V" bar • • Interfaces to other Aircraft Systems • • AHRS (or IRS) The IC-600 receives information from the two AHRS sources (or from the two IRS sources). RADIO ALTIMETER (AA-300) This system supplies analog radio altitude signals between .Hg. N. LONG RANGE NAV (FMS OPTION) The Primus-1000 receives LRN data for waypoint and navigation data. while the primary bus receives information from the two radio systems. ILS approach data. WEIGHT ON WHEELS (WOW LOGIC) Both IC-600 receives WOW logic from an aircraft-mounted switch. These data are: – Pressure altitude – Baro altitude – Mach – CAS – VMO – TAS – TAT – Altitude – SAT – Baro correction in HPA or In. DME and ADF). marker beacons. DATA ACQUISITION UNIT (DAU) The IC-600 receives data from the DAU’s to display information relative to engine.1 or N. The WOW logic is internally processed in the Landing Gear Electronic Unit (LGEU). This data permits the IC-600 to show: – Flight plan waypoints – Waypoint bearing – Desired track – Cross track deviation – Waypoint distance – Time to waypoint. This bus transmits short range navigation data (VOR bearings. PRIMUS II RADIO The Primus II radio system supplies navigation data to the IC-600 through the Radio System Bus (RSB).2 separately. Corresponding with EASA Part-66 For training purposes only Cat: B2 5. The IC-600 1 receives data from a secondary bus and the primary bus. Sep04 / THTT Copyright by SR Technics Switzerland • • • Module 5 Digital Technology / EIS 5. The RSB has: – Two secondary buses – One primary bus The secondary buses receive information from the radio system. TCAS COMPUTER The IC-600 receives a vertical deviation signal for display on the PFD. This signal is grounded when the aircraft is on the ground and not when it is in flight.39 . The IC-600 2 receives data from a secondary bus and the primary bus.500 ft. • The DC-550 activates the self-test function for several systems. This makes sure that a single failure does not impair the data path from AHRS (or IRS) sources.20 ft to 2.Basic Maintenance Training Manual It also moves analog signals from the GC-550 and bezels.1 .1 Electronic Instrument Systems MICRO AIR DATA COMPUTER . Then.MADC (AZ-840) Each IC-600 receives data from the two MADC’s. 40 .1 .1 Electronic Instrument Systems Figure 48: Detailed EFIS Block Diagram Sep04 / THTT Copyright by SR Technics Switzerland Corresponding with EASA Part-66 For training purposes only Cat: B2 5.Basic Maintenance Training Manual Module 5 Digital Technology / EIS 5. The following aircraft systems are interfacing with the EICAS for indication and alert functions: • Power plant • Landing gear • Flaps • Spoilers • Pressurization • APU • Trims • Brakes • Hydraulics • Electrical • Fuel • Ice/rain protection • Oxygen • Doors • Air conditioning • (Aircraft with CAT-IIIa configuration) Head-up guidance system.Basic Maintenance Training Manual EICAS Module 5 Digital Technology / EIS 5. data acquisition unit. can be used to display EICAS information (engine parameters and critical messages) as a backup in case of failure of an Integrated Computer. The Radio Management Units. where the analog signal is changed to a digital one. and symbol generators. and is divided in three parts: • Engine indications • System indications • Crew alerting Engine Indication The most important parameters of the engines are presented on the EICAS primary format on DU 3 as shown on Figure 49.41 .1 . The DAU 1 collects the data from the sources located in the front part of the aircraft and engine # 1. Sep04 / THTT Copyright by SR Technics Switzerland EICAS Primary Format The EICAS primary format is always shown at the DU-3. two separate displays which are normally used for Radio Management purpose. and sent to the integrated computer (IC-600). The architecture of the system (EICAS) starts from the engine and system sensors. The Engine Indication and Crew Alerting System (EICAS) receives and processes signals from engine and system sensors.1 Electronic Instrument Systems Either message or indication goes through DAU. The Data Acquisition Unit (DAU) receives analog and digital signals for using them in the EICAS. In this system there are two Data Acquisition Units (DAU’s) which collect data from systems of all parts of the aircraft. Corresponding with EASA Part-66 For training purposes only Cat: B2 5. The following aircraft systems are interfacing the EICAS for alerting purposes only: • Air turbine starter • Master announcement • Aural warning • Central Maintenance Computer (CMC) • Fire protection • (E)GPWS/windshear • Rudder • Smoke • Stall protection system • Thrust reverser This system also uses reversion switches for display units. The DAU 2 collects the data from the sources located in the rear part of the aircraft and engine # 2. The integrated architecture of the system uses the EICAS display and MFD’s for indications. The indication bug follows the same color as found along the analog band Indication of other Aircraft Systems Figure 50 highlights the Indication of the other aircraft systems that are continuously shown on the EICAS primary Format. Warning (red color) messages are displayed on top. followed by caution (amber color) messages.42 . The message types are warning. advisory. The CAS area location is at the upper right field of the EICAS display.Basic Maintenance Training Manual Module 5 Digital Technology / EIS 5. and advisory (cyan color) messages. The last line shows the status line. Roll and Yaw Trims ECS and APU Oil Pressure (PRESS) High Pressure Vibration (HP) Crew Alerting Low Pressure Vibration (LP) Oil Temperature (TEMP) For any exceeded parameter. This field has the capability of 16 lines of 18 characters per line. which is selected through the reversionary panel.1 Electronic Instrument Systems Figure 50: Indication of other Aircraft Systems on EICAS Display Figure 49: Engine Indications on EICAS Display Engine Fan Speed (N1) Interturbine Temperature (ITT) Landing Gear.1 . Flap and Spoiler Engine Turbine Speed (N2) Fuel Flow (FF) Fuel Quantity (FQ) Pitch. caution. Sep04 / THTT Copyright by SR Technics Switzerland Corresponding with EASA Part-66 For training purposes only Cat: B2 5. and generates messages for the flight crew members. The EICAS continuously monitors the status of various aircraft and avionics system. and advisory. and status signals from systems. The IC that controls the EICAS display. Each IC-600 receives warning. More than 150 messages will be shown on the CAS according to the message type. the message will flash. The newest message will be displayed on top of its respective queue. caution. will have the messages displayed. the indication will become red and flash for 10 seconds and then stay ON. When a new message occurs. respectively. If there are no messages. and electronic check list). The "END" message will not be included in the count of messages scrolled off the bottom of the display. The "END" message will always be the last message on the status line. the 16th line (status line) will show text "XX. located on the glareshield panel.43 . This text refers to the number of messages scrolled off the top and bottom of the display. • For advisory message: automatically. Advisory Status Line Sep04 / THTT Copyright by SR Technics Switzerland Module 5 Digital Technology / EIS 5. Through the MFD. and menu. located on the glareshield panel. after five seconds. On the right window of the page. Figure 52: Takeoff page (MFD partially displayed) Corresponding with EASA Part-66 For training purposes only Cat: B2 5. Caution The takeoff data is shown as digital quantities. while the status of the doors is a graphical representation.1 Electronic Instrument Systems On aircraft power-up. then the status line will stay blank. you can select different types of system pages in the lower part of the display. There are five different system pages and three other pages (TCAS. you can select 6 different menus. from the primary menu. If there are 15 messages.1 . maintenance page. • For caution message: by pushing the master caution button.Basic Maintenance Training Manual Message recognition is done as follows: • For warning message: by pushing the master warning button.messages ¯XX". there is a schematic door status. the MFD goes directly to the takeoff page which is the default page. Figure 51: Example of Crew Alerting Indications on EICAS Display MFD System Page Formats Through the MFD. The system pages available in the MFD software are: • Takeoff page • Environmental control page • Fuel system page • Hydraulic system page • Electrical system page Takeoff Page Warning The takeoff system page shows engine takeoff reference data on the left window of the page. 44 . The bleed temperature is part of the system page which provides a linear analog type display for left/right precooler outlet temperatures. temperature. An analog display of oxygen pressure is located in the center position of the ECS page. which provides the digital read-out of the cockpit and cabin temperatures. Figure 54: Fuel System Page (MFD partially displayed) Sep04 / THTT Copyright by SR Technics Switzerland The electrical system page provides the following information: • Brush less generators and APU starter-generator current and voltage. The right one-third part of the page shows the brake system information.1 Electronic Instrument Systems Environmental Control Page Hydraulics System Page The ECS is part of the system page. and pump status.Basic Maintenance Training Manual Module 5 Digital Technology / EIS 5.1 . • GPU voltage • Essential buses • Battery voltage/temperatures Figure 56: Electrical System Page Corresponding with EASA Part-66 For training purposes only Cat: B2 5. located on the left of the display. Figure 55: Hydraulics System Page (MFD partially displayed) Figure 53: Environmental Control Page (MFD partially displayed) Electrical System Page Fuel System Page The fuel system page provides fuel display for used quantity. The hydraulic and brake system page provides a display of the hydraulic system on the left two-thirds of the page. 1 Electronic Instrument Systems The first page includes the Engine Indication (EI).45 . Figure 57: EICAS Backup Format on Radio Management Unit Location of Radio Management Units Sep04 / THTT Copyright by SR Technics Switzerland Corresponding with EASA Part-66 For training purposes only Cat: B2 5.1 . while the second page includes the Crew Alerting System (CAS) information.Basic Maintenance Training Manual RMU EICAS Backup Format The Radio Management Unit (RMU) provides two pages for EICAS backup. Module 5 Digital Technology / EIS 5. The DAU receives discrete and analog inputs. These signals are changed for the digital ones by an analog/digital converter and sent to the integrated computer (IC-600). except for the excitation source for signals that do not require it. Only the RMU # 1 supplies the backup EICAS information in emergency operation. Module 5 Digital Technology / EIS 5. but.1 .MFD The MFD (DU 2/4) is similar to DU-3. Figure 58: Architecture of the EICAS System Data Acquisition Unit (DAU) The DAU is the central data collection point for the EICAS. Multi-function Display . as follows: • Takeoff page • ECS page • Fuel page • Hydraulic/brake page • Electrical page Integrated Computer The integrated computer (IC-600) is the unit which receives digitized signals (ARINC 429) from DAU’s for generating images to DU’s.1 Electronic Instrument Systems IC # 1. IC # 2. 2 and 3. which is identical to the PFD’s and MFD’s. The DAU is a dual (A and B) channel unit. EICAS Display The DU-3 is a full color CRT 8 x 7 inch electronic display. the channels being redundant. for normal operation. controls DU’s 1.Basic Maintenance Training Manual Components of the EICAS: • • The EICAS includes the following components: • Two DAU’s (DAU # 1/2) • One EICAS display (DU # 3) • Two MFD’s (DU # 2/4) • Two integrated computers (IC-600) • Two Radio Management Units (RMU’s) • Two reversionary panels • One EICAS reversion panel.RMU Both RMU’s provide backup EICAS information through the engine backup page. as follows: Sep04 / THTT Copyright by SR Technics Switzerland Radio Management Unit . you can get access to system pages. controls DU’s 4 and 5. through its menu. Corresponding with EASA Part-66 For training purposes only Cat: B2 5. In the IC-600 there is a symbol generator which controls the display units in normal condition. For these DU’s only the bezels are completely different either in the format or in the operation.46 . As on the Airbus A320 Warnings. depending on the seriousness of the failure. It also permits Reconfiguration of the MFD either for EICAS display or Primary Flight Display (PFD). On the Embraer 145. will also trigger an aural warning. as follows: Sep04 / THTT Copyright by SR Technics Switzerland Corresponding with EASA Part-66 For training purposes only Cat: B2 5. the aural warnings are discussed in a separate sub chapter in the AMM called "Aural Warning". you can deenergize the failed channel (only channel A) of DAU 1/2. This is just a different philosophy of defining the different parts of the systems. EICAS Reversion Panel Through the EICAS reversion panel. and warning and caution tones associated with a failure. On the Airbus A320 the aural warnings are part of the ECAM system. and Caution messages triggered by a system failure will be shown on the display units (EICAS displays for Embraer). As the aural warnings are also part of the Electronic Instrument System. Aural Warning Levels The aural warnings are divided into four levels.47 . The relation between Messages on the screens and aural warnings is very similar on all modern aircraft. 34-43) • Windshear detection system • GPWS/EGPWS • IC-600 • Fire detection system • Stall protection system • Trims • Flaps • Brakes • Spoilers • Radio altimeter • Autopilot The system generates voice messages. a short description of the system will be given on the following pages.Basic Maintenance Training Manual Module 5 Digital Technology / EIS 5. The tones have different forms. Figure 59: Some Warnings. Figure 60: System Description The aural warning system receives signals from the following aircraft systems: • TCAS (Ref.1 Electronic Instrument Systems Reversionary Panel Aural Warning A reversionary panel is provided for each pilot to permit Symbol Generator (SG) reversion.1 . plus the voice message.48 . Information The information alerts are related to information situations.1 Electronic Instrument Systems Emergency Associated with situations that can be dangerous. the aural warning is repeated every second until cancellation through the master warning light or until the failure is removed. three chimes. every five seconds.1 . the Aural Warning Unit (AWU) generates a specific sound. Abnormal Associated with malfunctions or failures. The system can generate a voice. In any condition. Advisory Associated with the least important failures such as loss of redundancy or degradation of a system. without voice message associated. with voice message. If an emergency fault occurs. The AWU generates a master caution tone.Basic Maintenance Training Manual • • • • Module 5 Digital Technology / EIS 5. If an emergency fault occurs. the AWU generates only master warning tone.^ Sep04 / THTT Copyright by SR Technics Switzerland Corresponding with EASA Part-66 For training purposes only Cat: B2 5. until cancellation through the master caution light or the failure is removed. 1 Clacker None No Windshear condition 2 None Windshear No Ground Proximity Condition 3 None Several Ground Proximity Warning Messages Possible No Traffic Proximity Condition 4 None Several TCAS Warning Messages possible No Fire in Engine or APU / ENG 1 (2) FIRE.000 ft.1 .1 Electronic Instrument Systems The "AURAL LEVEL" table shows the aural message priorities and levels. APU FIRE 5 Bell None Yes Airspeed above VMO 6 three chimes High Speed No Landing Gear not locked down for landing 7 three chimes Landing Gear No Cabin Altitude above 10.Basic Maintenance Training Manual Module 5 Digital Technology / EIS 5. Table 4: Aural Level Level Associated Condition/EICAS Messages Priority Tone Voice Message Cancel Emergency Stall Condition. 8 three chimes Cabin Yes Associated with takeoff configuration warning 9 three chimes Takeoff plus one of the conditions: • Flaps • Brakes • Trim • Spoiler No Associated with emergency failures 10 Master Warning None No Associated with glide slope deviation None None Glide Slope Yes Traffic proximity condition None None Traffic Yes Associated with abnormal failures None Master Caution None Yes Abnormal Abnormal cont’d Sep04 / THTT Copyright by SR Technics Switzerland Corresponding with EASA Part-66 For training purposes only Cat: B2 5.49 . "three chimes" will be generated. TCAS. No other voice message is generated with them to avoid misunderstanding. the advisory alerts operate. the abnormal alerts operate. Only stall condition has priority over windshear. if there are no other alerts. but is sufficiently distinct to permit the crew to understand the voice message and the discrete sound easily. Finally. A special condition occurs in the emergency fault level without voice message.K. After cancelling the emergency aural alerts. "three chimes" is inhibited when any other alert occurs at the same time. Sep04 / THTT Copyright by SR Technics Switzerland Corresponding with EASA Part-66 For training purposes only Cat: B2 5. and TCAS alerts. The amplitude of the discrete sound (clacker or bell) is reduced. GPWS/EGPWS.900 Hz three times None No Both channels of AWU are operating normally on power-up test None None Aural Unit O. No Takeoff configuration test successful None None Takeoff O. the highest level (emergency) alert operates first.1 Electronic Instrument Systems Table 4: Aural Level Level Associated Condition/EICAS Messages Priority Tone Voice Message Cancel Advisory Autopilot disengagement during approach None None Autopilot Yes Associated with decision height crossing None None Minimum No Power-up test detected a failure in one channel of AWU None None Aural Unit One Channel No Associated with SELCAL callings None None Selcal No Airplane is crossing or has reached a pre-selected altitude None 2. If a stall or fire fault occurs at the same time as any emergency fault with voice message associated. the two operate simultaneously. A special condition occurs for windshear. But. then the information alerts operate.50 . any alert that is in progress will be completed before another alert signal starts to operate (even if the priority is higher). If all emergency and abnormal alerts are cancelled.K. No Power supply 1 or 2 failure None None Aural Unit One Power Interrupt No Information If multiple alerts occur. or GPWS/EGPWS alert condition. Only after cancelling an alert generated by the AWU system.Basic Maintenance Training Manual Module 5 Digital Technology / EIS 5.1 . The pilot or copilot can cancel all the alerts through the master warning/caution lights. namely: – SELCAL – Altitude alert – Autopilot • Pilot/copilot and observer digital audio panels outputs The aural warning system interfaces the 3 audio panels to have head phone and speaker outputs. AWU total fail output This output informs the EICAS if the AWU fails totally. There is a switch in the control pedestal to simulate a condition of power-levers in the take-off configuration.51 . These inputs will cause the AWU to generate master warning tone (three chimes) and master caution tone. advisory and information inputs These inputs are connected to some systems. The associated light flashes when an emergency or caution failure occurs. • Emergency. • TCAS auxiliary audio input There is an auxiliary audio input for the audio generated in the TCAS computer. • Rolling take-off configuration input This input is used for a take-off configuration simulation during aircraft taxi. on the pilot and copilot audio panels can never be switched off from crew members' action.1 . A ground signal comes through the switches. except: • Stall • Landing configuration alarm generated because of the flaps • GPWS/EGPWS • Windshear • TCAS R/A.1 Electronic Instrument Systems Abnormal and emergency inputs The two inputs come from EICAS when an emergency or abnormal fault occurs associated only to the CAS messages on the EICAS display. NOTE: The AWU uses these interfaces to give priority of alerts. They are the master warning light and the master caution light. Sep04 / THTT Copyright by SR Technics Switzerland Corresponding with EASA Part-66 For training purposes only Cat: B2 5. • (E)GPWS/windshear auxiliary audio input There is an auxiliary audio input for the audio generated in the GPWS/EGPWS and W/S computer. for warning purposes. The speaker output. Overspeed. Abnormal and emergency outputs The two outputs go to the EICAS when the AWU is ready to generate the audio signal. Advisory and information alerts • • Module 5 Digital Technology / EIS 5. This function permits the crew to do a takeoff configuration test during aircraft taxi. the AWU sends a ground signal to cancel the light flashing. Even when the master warning light of master caution light is pushed.Basic Maintenance Training Manual Master Warning and Master Caution • There are two switches to cancel emergency or abnormal failures. Figure 61 shows the interfaces with the different aircraft systems Interfaces to the Aural Warning System The aural warning system makes interface with: • Master warning and master caution light inputs They are used to cancel a warning or a caution fault. 1 Electronic Instrument Systems Figure 61: Aural Warning Block Diagram Sep04 / THTT Copyright by SR Technics Switzerland Corresponding with EASA Part-66 For training purposes only Cat: B2 5.52 .Basic Maintenance Training Manual Module 5 Digital Technology / EIS 5.1 .