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(2) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS. WARNING. f o g y n r i r a t e e e i n r i p g o n r P SE A M. i a r T. g n i n. This document is intended for the purposes of training only. The information contained herein is as accurate as possible at the time of issue, and is subject to ongoing amendments where necessary according to any regulatory journals and documents. Where the information contained in this document is in variation with other official journals and/or documents, the latter must be taken as the overriding document. The contents herein shall not be reproduced in any form without the expressed permission of ETD. For Training Purposes Only. Issue 2 Revision 0 Oct 2011 Page ii.
(3) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS. TABLE OF CONTENT 5.1 ELECTRONICS INSTRUMENT SYSTEM (DCAM Ref 5.1) Level 3……………………………………………………………………………….……….. 1. g n i n. 5.1.1 Introduction………………………………………………………………………………………………………………………………………………………. 1 5.1.2 Integrated Digital Avionics System…………………………………………………………………………………………………………………………….. 4 5.1.3 Electronics Flight Instruments System (EFIS)………………………………………………………………………………………………………………… 6 5.1.4 Electronic Centralized Aircraft Monitoring (ECAM)……………………………………………………………………………………………………………14 5.1.5 Engine Indicating and Crew Alerting System (EICAS)………………………………………………………………………………………………………. 16 5.1.6 Flight Management System (FMS)…………………………………………………………………………………………………………………………….. 18 5.1.7 Cockpit Layouts…………………………………………………………………………………………………………………………………………………...20. f o g y n r i r a t e e e i n r i p g o n r P SE A M. i a r T. 5.2 NUMBERING SYSTEMS (DCAM Ref 5.2) Level 2………………………………………………………………………………………….…..……………. 24 5.2.1 Decimal System………………………………………………………………………………………………………………………………………………….. 24 5.2.2 The Binary System………………………………………………………………………………………………………………………………………………. 26 5.2.3 The Octal System…………………………………………………………………………………………………………………………………………………38 5.2.4 Hexadecimal System……………………………………………………………………………………………………………………………………………..44 5.2.5 Binary Coded Decimal……………………………………………………………………………………………………………………………………………49 5.2.6 Adding……………………………………………………………………………………………………………………………………………………………...52 5.2.7 Subtraction………………………………………………………………………………………………………………………………………………………... 52 5.3 DATA CONVERSION (DCAM Ref 5.3) Level 2…………………………………………………………………………….…………………………………..56 5.3.1 Digital and Analogue Computers………………………………………………………………………………………………………………………………. 56 5.3.2 Digital Bus………………………………………………………………………………………………………………………………………………………… 59 5.3.3 Typical Digital System Inputs…………………………………………………………………………………………………………………………………… 60 5.3.4 Typical Digital Systems Outputs………………………………………………………………………………………………………………………………...62 5.3.5 Digital to Analogue / Analogue to Digital Conversion………………………………………………………………………………………………………... 64. For Training Purposes Only. Issue 2 Revision 0 Oct 2011 Page iii.
(4) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS. 5.4 DATA BUSES (DCAM Ref 5.4) Level 2…………………………………………………………………………………………………………………………90 5.4.1 What is Data Bus?.................................................................................................................................................................................................... 91 5.4.2 About ARINC……………………………………………………………………………………………………………………………………………………... 93 5.4.3 Data Encoding……………………………………………………………………………………………………………………………………………………. 93 5.4.4 ARINC 429………………………………………………………………………………………………………………………………………………………... 97 5.4.5 MIL-STD-1553B………………………………………………………………………………………………………………………………………………….. 104 5.4.6 ARINC 629………………………………………………………………………………………………………………………………………………………... 106 5.4.7 Ethernet…………………………………………………………………………………………………………………………………………………………… 122. f o g y n r i r a t e e e i n r i p g o n r P SE A M. i a r T. g n i n. 5.5 LOGIC CIRCUITS (DCAM Ref 5.5) Level 2……………………………………………………………………………………………………………………..128 5.5.1 Logic Gates……………………………………………………………………………………………………………………………………………………….. 128 5.5.2 Electronic Gates in Circuit……………………………………………………………………………………………………………………………………… 138 5.5.3 Gate Application in Aircraft Systems……………………………………………………………………………………………………………………………150 5.5.4 Tri-state Devices…………………………………………………………………………………………………………………………………………………. 154 5.6 BASIC COMPUTER STRUCTURE (DCAM Ref 5.6) Level 2…………………………………………………………………………………………………156 5.6.1 Central Processing Unit…………………………………………………………………………………………………………………………………………. 157 5.6.2 Memories…………………………………………………………………………………………………………………………………………………………. 160 5.6.3 Magnetic Memory Types…………………………………………………………………………………………………………………………………………162 5.6.4 Solid State Memories……………………………………………………………………………………………………………………………………………. 172 5.6.5 Storage Capacity………………………………………………………………………………………………………………………………………………….179 5.6.6 Highway Structure……………………………………………………………………………………………………………………………………………….. 179 5.6.7 Instruction Words………………………………………………………………………………………………………………………………………………… 180 5.7 MICROPROCESSORS (DCAM Ref 5.7) Level 2………………………………………………………………………………………………………………181 5.7.1 Microprocessor (CPU) Structure and Operation……………………………………………………………………………………………………………… 181. For Training Purposes Only. Issue 2 Revision 0 Oct 2011 Page iv.
(5) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS. 5.8 INTEGRATED CIRCUITS (DCAM Ref 5.8) Level 2…………………………………………………………………………………………………..……….184 5.8.1 Adders…………………………………………………………………………………………………………………………………………………………….. 184 5.8.2 Flip-Flops…………………………………………………………………………………………………………………………………………………………. 192 5.8.3 Counters…………………………………………………………………………………………………………………………………………………………... 197 5.8.4 Decoders………………………………………………………………………………………………………………………………………………………….. 200 5.8.5 Encoders………………………………………………………………………………………………………………………………………………………….. 210. i a r T. g n i n. 5.9 MULTIPLEXING (DCAM Ref 5.9) Level 2…………………………………………………………………………………………………………………..…..216. f o g y n r i r a t e e e i n r i p g o n r P SE A M. 5.9.1 Multiplexers……………………………………………………………………………………………………………………………………………………….. 216 5.9.2 De-multiplexer……………………………………………………………………………………………………………………………………………………. 220 5.10 FIBRE OPTICS (DCAM Ref.5.10) Level 2…………………………………………………………………………………………………………………….224 5.10.1 Definition of Fibre Optics………………………………………………………………………………………………………………………………………. 224 5.10.2 Fibre Optic Data Links…………………………………………………………………………………………………………………………………………. 224 5.10.3 Fibre Optic Systems……………………………………………………………………………………………………………………………………………. 226 5.10.4 Advantages and Disadvantages of Fibre Optics……………………………………………………………………………………………………………. 228 5.10.5 Frequency and Bandwidth…………………………………………………………………………………………………………………………………….. 230 5.10.6 Fibre Optic Concepts……………………………………………………………………………………………………………………………………………232 5.10.7 Transmission of Light Through Optical Fibres………………………………………………………………………………………………………………. 236 5.10.8 Basic Structure of an Optical Fibre…………………………………………………………………………………………………………………………… 242 5.10.9 Propagation of Light along a Fibre…………………………………………………………………………………………………………………………… 244 5.10.10 Fibre Types……………………………………………………………………………………………………………………………………………………. 253 5.10.11 Properties of Optical Fibre Transmission……………………………………………………………………………………………………………………260 5.10.12 Choice of Fibres………………………………………………………………………………………………………………………………………………..274 5.10.13 Joining Optical Fibre………………………………………………………………………………………………………………………………………….. 275 5.10.14 Aircraft Fibre Optic Networks………………………………………………………………………………………………………………………………… 279 5.10.15 Applications in Aircraft Systems……………………………………………………………………………………………………………………………...284 5.10.16 Fibre Optic Testing……………………………………………………………………………………………………………………………………………. 287. For Training Purposes Only. Issue 2 Revision 0 Oct 2011 Page v.
(6) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS. 5.11 ELECTRONIC DISPLAYS (DCAM Ref.5.11) Level 2……………………………………….………………………………………….……………………288 5.11.1 Light Emitting Diodes (LEDs)…………………………………………………………………………………………………………………………………..288 5.11.2 Liquid Crystal Displays (LCDs)………………………………………………………………………………………………………………………………...290 5.11.3 Cathode Ray Tube (CRT)………………………………………………………………………………………………………………………………………294 5.11.4 Principle of the Colour CRT…………………………………………………………………………………………………………………………………… 302. i a r T. g n i n. 5.12 ELECTROSTATIC SENSITIVE DEVICES (DCAM Ref.5.12) Level 2………………………………….…………….…………………………………….304 5.12.1 What is an Electrostatic Discharge?....................................................................................................................................................................... 304 5.12.2 Typical Electrostatic Voltages…………………………………………………………………………………………………………………………………. 306 5.12.3 ESDS Equipment and Material Handling……………………………………………………………………………………………………………………. 310. f o g y n r i r a t e e e i n r i p g o n r P SE A M. 5.13 SOFTWARE MANAGEMENT (DCAM Ref.5.13) Level 2……………………………..……………………………………………………………..………316 5.13.1 Introduction……………………………………………………………………………………………………………………………………………………… 316 5.13.2 Requirements…………………………………………………………………………………………………………………………………………………… 317 5.14 ELECTROMAGNETIC ENVIRONMENT (DCAM Ref.5.14) Level 2………………………………………………………………………………………..320 5.14.1 General…………………………………………………………………………………………………………………………………………………………...320 5.14.2 Lightning versus Static Discharge………………………………………………………………………………………………………………………….… 322 5.14.3 Electromagnetic Interference (HIRF)………………………………………………………………………………………………………………………… 324 5.14.4 Lightning Strikes……………………………………………………………………………………………………………………………………………….. 325 5.14.5 Protection………………………………………………………………………………………………………………………………………………………... 326 5.14.6 Maintenance…………………………………………………………………………………………………………………………………………………….. 326 5.14.7 Static……………………………………………………………………………………………………………………………………………………………... 327 5.15 TYPICAL ELECTRONIC/DIGITAL AIRCRAFT SYSTEMS (DCAM Ref.5.15) Level 2……………………………………………………..……………334 5.15.1 On Board Maintenance and BITE……………………………………………………….……………………………………………………………………. 334 5.15.2 ARINC Communication Addressing and Reporting System (ACARS)…………………………………………………………………………………… 342 5.15.3 Electronic Centralised Aircraft Monitors (ECAM)…………………………………………………………………………………………………………….344 For Training Purposes Only. Issue 2 Revision 0 Oct 2011 Page vi.
(7) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS. 5.15.4 Electronic Flight Instrument Systems (EFIS)…………………………………………………………………………………………………………………354 5.15.5 Engine Indicating and Crew Alerting System (EICAS)……………………………………………………………………………………………………. 372 5.15.6 Fly-By-Wire……………………………………………………………………………………………………………………………………………………… 396 5.15.7 Flight Management Systems (FMS)………………………………………………………………………………………………………………………….. 416 5.15.8 Global Positioning Systems (GPS)…………………………………………………………………………………………………………………………… 422 5.15.9 Inertial Reference Systems (IRS)…………………………………………………………………………………………………………………………….. 438 5.15.10 Traffic Alert Collision Avoidance System (TCAS)…………………………………………………………………………………………………………. 464 5.15.11 Integrated Modular Avionics (IMA)………………………………………………………………………………………………………………………….. 476 5.15.12 Cabin Systems………………………………………………………………………………………………………………………………………………… 480 5.15.13 Information Systems………………………………………………………………………………………………………………………………………….. 496. f o g y n r i r a t e e e i n r i p g o n r P SE A M For Training Purposes Only. i a r T. g n i n. Issue 2 Revision 0 Oct 2011 Page vii.
(8) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS. f o g y n r i r a t e e e i n r i p g o n r P SE A M THIS PAGE INTENTIONALLY LEFT BLANK. For Training Purposes Only. i a r T. g n i n. Issue 2 Revision 0 Oct 2011 Page viii.
(9) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS ELECTRONIC INSTRUMENT SYSTEM (DCAM 5.1 L3) 5.1 ELECTRONIC INSTRUMENT SYSTEM (EIS) 5.1.1 Introduction In a modern aircraft, the cockpit crew is provided with many different information. To handle this amount of data with a minimum of manpower and ’in time’; it is necessary to reduce the number of indicators in the cockpit, i.e. no longer using a separate indicator for each system/sensor.. f o g y n r i r a t e e e i n r i p g o n r P SE A M. i a r T. g n i n. Figure 1.1 Cockpit of Conventional Design (Separate indicator for each system/sensor). For Training Purposes Only. Issue 2 Revision 0 Oct 2011 Page 1.
(10) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS ELECTRONIC INSTRUMENT SYSTEM (DCAM 5.1 L3) This is achieved by displaying all data from the various systems on some few ‘multi-purpose indicators’. A system which handles the flow and display of data of many or all aircraft systems is called an ’integrated digital avionic system’. The advantages of such a system are - it provides a better overview over the actual condition of each connected system - it reduces the flight crew’s workload - less time (and money) is required for maintenance - it saves electrical power consumption - the weight is reduced (wiring, units).. f o g y n r i r a t e e e i n r i p g o n r P SE A M. i a r T. g n i n. Figure 1.2 Cockpit with EFIS (Multi-purpose Indicators). For Training Purposes Only. Issue 2 Revision 0 Oct 2011 Page 2.
(11) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS ELECTRONIC INSTRUMENT SYSTEM (DCAM 5.1 L3) A digital avionic system replaces the former instrumentation by an electronic flight instrument system (EFIS) and/or an engine indication and crew alerting system (EICAS). This includes the change from old analogue equipment to modern systems, because digital outputs are required.. f o g y n r i r a t e e e i n r i p g o n r P SE A M. i a r T. g n i n. Figure 1.3 ‘Fully Integrated’ Cockpit Design with EFIS and EICAS. For Training Purposes Only. Issue 2 Revision 0 Oct 2011 Page 3.
(12) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS ELECTRONIC INSTRUMENT SYSTEM (DCAM 5.1 L3) 5.1.2 Integrated Digital Avionics System The new generation of aircraft avionics is highly integrated. It saves electrical power and weight. It provides high accuracy and reliability. The level of integration varies (whether only the main avionic systems are combined or all), depending on the type of aircraft.. g n i n. An essential function of an integrated digital avionic system is the exchange of information between subsystems and/or between line replaceable units (LRU) within a subsystem. Note: A line--replaceable unit (LRU) (also called ’black box’) is a unit, which can be replaced at flight--line level in a short time.. i a r T. To incorporate a fully integrated digital avionic system and to ensure the required information exchange, a digital data bus is required. This bus is used to provide a 2-way interface between various computers, sensors and indicators. The interface between computers and/or external devices (e.g. transceivers, receivers) is accomplished via the digital data bus. Data may travel ’one way’ or in 2 directions, depending on the system design.. f o g y n r i r a t e e e i n r i p g o n r P SE A M. Figure 1.4 Conventional and Integrated Designs. For Training Purposes Only. Issue 2 Revision 0 Oct 2011 Page 4.
(13) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS ELECTRONIC INSTRUMENT SYSTEM (DCAM 5.1 L3) Typically, the data bus is a serial bus on which the data are transmitted sequentially, i.e. one word after the other. A serial bus is commonly used for longdistance data transmissions (more than 50 m) as required in large aircraft. The bus is made up of a twisted pair of wires which are shielded and jacketed. The shielding is grounded at all terminal ends and breakouts to keep bit distortion at a low level. Shield grounding and high voltage spike protection within the individual data--receiving components ensure accurate transmissions.. g n i n. Transmission of data within micro-computers, between micro-computers and external devices as well as between other components can be accomplished with 8-, 16-, 32- and 64-bit digital data words, depending on the system layout.. i a r T. Some of these information are in the form of discrete data. Typically, these data are formed by switching between +28 V DC and open (or between ground and open). Discrete data are carried on a single wire.. f o g y n r i r a t e e e i n r i p g o n r P SE A M. This type of information is used for annunciators, warnings and wherever simple ‘condition information’ is sufficient. This is a small portion of the total information interchange.. For Training Purposes Only. Issue 2 Revision 0 Oct 2011 Page 5.
(14) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS ELECTRONIC INSTRUMENT SYSTEM (DCAM 5.1 L3) 5.1.3 Electronics Flight Instruments System (EFIS) A basic EFIS system is more than an Electronic Flight Director with Electronics Attitude and Direction Indicators (EADIs) or Primary Flight Displays (PFDs) and Electronic Horizontal Situation Indicators (EHSIs) or Navigation Displays (NDs) as display units. A typical EFIS system consists of two or more display units and their associated drive and control units. 5.1.3.1 Electronic Attitude and Direction Indicator The electronic attitude direction indicator (EADI - see Fig. 1.5) is normally comprises: • • • • • • • •. an attitude indicator a fixed aircraft symbol pitch and bank command bars a glide slope indicator a localizer deviation indicator a slip indicator flight mode anunciator various warning flags. f o g y n r i r a t e e e i n r i p g o n r P SE A M. i a r T. g n i n. The aircraft' s attitude relative to the horizon is indicated by the fixed aircraft symbol and the flight command bars. The pilot can adjust the symbol to one of three flight modes. To fly the aircraft with the command bars armed, the pilot simply inserts the aircraft symbol between the command bars. The command bars move up for a climb or down for descent, roll left or right to provide lateral guidance. They display the computed angle of bank for standard-rate turns to enable the pilot to reach and fly a selected heading or track. The bars also show pitch commands that allow the pilot to capture and fly an ILS glide slope, a pre-selected pitch attitude, or maintain a selected barometric altitude. To comply with the directions indicated by the command bars, the pilot manoeuvres the aircraft to align the fixed symbol with the command bars. When not using the bars, the pilot can move them out of view. The glide slope deviation pointer represents the centre of the instrument landing system (ILS) glide slope and displays vertical deviation of the aircraft from the glide slope centre. The glide slope scale centreline shows aircraft position in relation to the glide slope.. For Training Purposes Only. Issue 2 Revision 0 Oct 2011 Page 6.
(15) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS ELECTRONIC INSTRUMENT SYSTEM (DCAM 5.1 L3) The localizer deviation pointer, a symbolic runway, represents the centre of the ILS localizer, and comes into view when the pilot has acquired the glide slope. The expanded scale movement shows lateral deviation from the localizer and is approximately twice as sensitive as the lateral deviation bar in the horizontal situation indicator. The selected flight mode is displayed in the lower left of the EADI for pitch modes, and lower right for lateral modes. The slip indicator provides an indication of slip or skid indications.. f o g y n r i r a t e e e i n r i p g o n r P SE A M. i a r T. g n i n. Figure 1.5 A typical EADI display. For Training Purposes Only. Issue 2 Revision 0 Oct 2011 Page 7.
(16) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS ELECTRONIC INSTRUMENT SYSTEM (DCAM 5.1 L3) 5.1.3.2 Electronic Horizontal Situation Indicator The electronic horizontal situation indicator (EHSI) assists pilots with the interpretation of information provided by a number of different navigations aids. There are various types of EHSI but essentially they all perform the same function. An EHSI display (see Fig. 1.6) can be configured to display a variety of information (combined in various different ways) including: • • • • • •. heading indication radio magnetic indication (RMI) track indication range indication wind speed and direction VOR, DME, ILS or ADF information.. f o g y n r i r a t e e e i n r i p g o n r P SE A M. i a r T. g n i n. Figure 1.6 A typical EHSI display. For Training Purposes Only. Issue 2 Revision 0 Oct 2011 Page 8.
(17) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS ELECTRONIC INSTRUMENT SYSTEM (DCAM 5.1 L3) 5.1.3.3 Flight Director Systems The major components of a flight director system (FDS) are the electronic attitude and direction indicator (EADI) and electronic horizontal situation indicator (EHSI) working together with a mode selector and a flight director computer.. g n i n. The FDS combines the outputs of the electronic flight instruments to provide an easily interpreted display of the aircraft' s flight path. By comparing this information with the pre-programmed flight path, the system can automatically compute the necessary flight control commands to obtain and hold the desired path. The flight director system receives information from the: • • • • •. f o g y n r i r a t e e e i n r i p g o n r P SE A M. attitude gyro VOR/localizer/glide slope receiver radio altimeter compass system barometric sensors. i a r T. The flight director computer uses this data to provide flight control command information that enables the aircraft to: • • • • •. fly a selected heading fly a predetermined pitch attitude maintain altitude intercept a selected VOR track and maintain that track fly an ILS glide slope/localizer. For Training Purposes Only. Issue 2 Revision 0 Oct 2011 Page 9.
(18) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS ELECTRONIC INSTRUMENT SYSTEM (DCAM 5.1 L3) The flight director control panel comprises a mode selector switch and control panel that provides the input information used by the FDS. The pitch command control pre-sets the desired pitch angle of the aircraft for climb or descent. The command bars on the FDS then display the computed attitude to maintain the pre-selected pitch angle. The pilot may choose from among many modes including the HDG (heading) mode, the VOR/LOC (localizer tracking) mode, or the AUTO APP or G/S (automatic capture and tracking of ILS and glide path) mode. The auto mode has a fully automatic pitch selection computer that takes into account aircraft performance and wind conditions, and operates once the pilot has reached the ILS glide slope. Flight director systems have become increasingly more sophisticated in recent years.. f o g y n r i r a t e e e i n r i p g o n r P SE A M For Training Purposes Only. i a r T. g n i n. Issue 2 Revision 0 Oct 2011 Page 10.
(19) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS ELECTRONIC INSTRUMENT SYSTEM (DCAM 5.1 L3) 5.1.3.4 Primary Flight Display (PFD) The typical EFIS PFD is a multicolour cathode ray tube (CRT) or liquid crystal display (LCD) display unit that presents a display of aircraft attitude and flight control system commands including VOR, localizer, TACAN (Tactical Air Navigation), or RNAV (Area Navigation) deviation together with glide slope or preselected altitude deviation. Various other information can be displayed including mode annunciation, radar altitude, decision height and excessive ILS deviation.. f o g y n r i r a t e e e i n r i p g o n r P SE A M. i a r T. g n i n. Figure 1.7 EFIS primary flight display. For Training Purposes Only. Issue 2 Revision 0 Oct 2011 Page 11.
(20) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS ELECTRONIC INSTRUMENT SYSTEM (DCAM 5.1 L3) 5.1.3.5 Navigation Display (ND) Like the EFIS PFD, a typical EFIS ND takes the form of a multicolour CRT or LCD display unit. However, in this case the display shows the aircraft' s horizontal situation information which, according to the display mode selected, can include compass heading, selected heading, selected VOR, localizer, or RNAV course and deviation (including annunciation or deviation type), navigation source annunciation, digital selected course/desired track readout, excessive ELS deviation, to/from information, distance to station/waypoint, glide slope, or VNAV deviation, ground speed, time-to-go, elapsed time or wind, course information and source annunciation from a second navigation source, weather radar target alert, waypoint alert when RNAV is the navigation source, and a bearing pointer that can be driven by VOR, RNAV or ADF sources as selected on the display select panel. The display mode can also be set to approach format or en-route format with or without weather radar information included in the display.. f o g y n r i r a t e e e i n r i p g o n r P SE A M. i a r T. g n i n. Figure 1.8 EFIS navigation display. For Training Purposes Only. Issue 2 Revision 0 Oct 2011 Page 12.
(21) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS ELECTRONIC INSTRUMENT SYSTEM (DCAM 5.1 L3) 5.1.3.6 Display Select Panel (DSP) The display select panel provides navigation sensor selection, bearing pointer selection, format selection, navigation data selection (ground speed, time-togo, time, and wind direction/speed), and the selection of VNAV (if the aircraft has this system), weather, or second navigation source on the ND. A DH SET control that allows decision height to be set on the PFD is also provided. Additionally, course, course direct to, and heading are selected from the DSP. 5.1.3.7 Display Processor Unit (DPU). i a r T. g n i n. The display processor unit provides sensor input processing and switching, the necessary deflection and video signals, and power for the electronic flight displays. The DPU is capable of driving two electronic flight displays with different deflection and video signals. For example, a PFD on one display and an ND on the other.. f o g y n r i r a t e e e i n r i p g o n r P SE A M. 5.1.3.8 Weather Radar Panel (WXP). The weather radar panel provides MODE control (OFF, STBY, TEST, NORM, WX, and MAP), RANGE selection (10, 25, 50, 100, 200 and 300 nm), and system operating Controls for the display of weather radar information on the MFD and the ND when RDR is selected on the MFD and/or the DSP. 5.1.3.9 Multifunction Display (MFD). The multifunction display takes the form of another multicolour CRT or active-matrix LCD display unit. The display is normally mounted on the instrument panel in the space provided for the weather radar (WXR) indicator. Standard functions displayed by the unit include weather radar, pictorial navigation map, and in some systems, check list and other operating data. Additionally, the MFD can display flight data or navigation data in case of a PFD or ND failure. 5.1.3.10 Multifunction Processor Unit (MPU). The multifunction processor unit provides sensor input processing and switching and the necessary deflection and video signals for the multifunction display. The MPU can provide the deflection and video signals to the PFD and ND displays in the event of failures in either or both display processor units.. For Training Purposes Only. Issue 2 Revision 0 Oct 2011 Page 13.
(22) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS ELECTRONIC INSTRUMENT SYSTEM (DCAM 5.1 L3) 5.1.4 Electronic Centralized Aircraft Monitoring (ECAM) Technical information concerning the state of an Airbus aircraft is displayed using the aircraft' s electronic centralized aircraft monitor (ECAM— see Fig. 1.9). This normally takes the form of two CRT or LCD displays that are vertically arranged in the centre of the instrument panel. The upper (primary) display shows the primary engine parameters (N1/fan speed, EGT, N2/high pressure turbine speed), as well as the fuel flow, the status of lift augmentation devices (flap and slat positions), along with other information. The lower (secondary) ECAM display presents additional information including that relating to any system malfunction and its consequences.. f o g y n r i r a t e e e i n r i p g o n r P SE A M. i a r T. g n i n. Figure 1.9 A320 ECAM displays located above the centre console between the captain and first officer. For Training Purposes Only. Issue 2 Revision 0 Oct 2011 Page 14.
(23) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS ELECTRONIC INSTRUMENT SYSTEM (DCAM 5.1 L3) Test your understanding Figure 1.10 shows a flight deck display.. f o g y n r i r a t e e e i n r i p g o n r P SE A M. i a r T. g n i n. Figure 1.10. (a) (b) (c) (d) (e). Identify the display. What information is currently displayed? Where is the display usually found? What fan speed is indicated? What temperature is indicated?. For Training Purposes Only. Issue 2 Revision 0 Oct 2011 Page 15.
(24) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS ELECTRONIC INSTRUMENT SYSTEM (DCAM 5.1 L3) 5.1.5 Engine Indicating and Crew Alerting System (EICAS) In Boeing aircraft the equivalent integrated electronic aircraft monitoring system is known as the engine indicating and crew alerting system (EICAS). This system provides graphical monitoring of the engines of later Boeing aircraft, replacing a large number of individual panel-mounted instruments. In common with the Airbus ECAM system, EICAS uses two vertically mounted centrally located displays (see Fig. 1.11).. g n i n. The upper (primary) EICAS display shows the engine parameters and alert messages whilst the lower (secondary) display provides supplementary data (including advisory and warning information).. f o g y n r i r a t e e e i n r i p g o n r P SE A M For Training Purposes Only. i a r T. Issue 2 Revision 0 Oct 2011 Page 16.
(25) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS ELECTRONIC INSTRUMENT SYSTEM (DCAM 5.1 L3). f o g y n r i r a t e e e i n r i p g o n r P SE A M. i a r T. g n i n. Figure 1.11 EICAS display. For Training Purposes Only. Issue 2 Revision 0 Oct 2011 Page 17.
(26) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS ELECTRONIC INSTRUMENT SYSTEM (DCAM 5.1 L3) 5.1.6 Flight Management System (FMS) The flight management system (FMS) fitted to a modern passenger aircraft brings together data and information gathered from the electronic flight instruments, aircraft monitoring and navigation systems, and provides outputs that can be used for automatic control of the aircraft from immediately after take-off to final approach and landing. The key elements of an FMS include a flight management computer (FMC), control and display unit (CDU), IRS, AFCS, and a system of data buses that facilitates the interchange of data with the other digital and computerized systems and instruments fitted to the aircraft.. i a r T. g n i n. Two FMS are fitted, one for the captain and one for the first officer. During normal operation the two systems share the incoming data. However, each system can be made to operate independently in the event of failure. By automatically comparing (on a continuous basis) the indications and outputs provided by the two systems it is possible to detect faults within the system and avoid erroneous indications. The inputs to the FMC are derived from several other systems including IRS, EICAS, engine thrust management computer, and the air data computer. Figures 1.12 and 1.13 shows the FMC control and display units fitted to an A320 aircraft.. f o g y n r i r a t e e e i n r i p g o n r P SE A M. For Training Purposes Only. Issue 2 Revision 0 Oct 2011 Page 18.
(27) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS ELECTRONIC INSTRUMENT SYSTEM (DCAM 5.1 L3). f o g y n r i r a t e e e i n r i p g o n r P SE A M Figure 1.12 Captain’s FMS CDU. i a r T. g n i n. Figure 1.13 A320 cockpit layout. For Training Purposes Only. Issue 2 Revision 0 Oct 2011 Page 19.
(28) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS ELECTRONIC INSTRUMENT SYSTEM (DCAM 5.1 L3) 5.1.7 Cockpit Layouts Major developments in display technology and the introduction of increasingly sophisticated aircraft computer systems have meant that cockpit layouts have been subject to continuous change over the past few decades. At the same time, aircraft designers have had to respond to the need to ensure that the flight crew are not overburdened with information and that relevant data is presented in an appropriate form and at the time that it is needed.. g n i n. Figure 1.14 shows how the modern EFIS layouts have evolved progressively from the basic-T instrument configuration found in non-EFIS aircraft. Maintaining the relative position of the instruments has been important in allowing pilots to adapt from one aircraft type to another. At the same time, the large size of modern CRT and LCD displays, coupled with the ability of these instruments to display combined data (for example, heading, airspeed and altitude) has led to a less-cluttered instrument panel (see Fig. 1.15). Lastly, a number of standby (or secondary) instruments are made available in order to provide the flight crew with reference information which may become invaluable in the case of a malfunction in the computer system.. f o g y n r i r a t e e e i n r i p g o n r P SE A M. Basic T'flight instrument configuration. Basic EFIS flight instrument configuration. i a r T. Enhanced EFIS flight instrument configuration. Figure 1.14 Evolution of instrument layouts. For Training Purposes Only. Issue 2 Revision 0 Oct 2011 Page 20.
(29) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS ELECTRONIC INSTRUMENT SYSTEM (DCAM 5.1 L3). f o g y n r i r a t e e e i n r i p g o n r P SE A M. i a r T. g n i n. Figure 1.15 Captain' s flight instrument and display layout on the A320. For Training Purposes Only. Issue 2 Revision 0 Oct 2011 Page 21.
(30) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS ELECTRONIC INSTRUMENT SYSTEM (DCAM 5.1 L3) Test your understanding 1. Identify each of the Boeing 767 flight instruments and displays shown in Fig. 1.16. 2. Classify the flight instruments in Question 1 as either primary or standby.. f o g y n r i r a t e e e i n r i p g o n r P SE A M. i a r T. g n i n. Figure 1.16. For Training Purposes Only. Issue 2 Revision 0 Oct 2011 Page 22.
(31) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS ELECTRONIC INSTRUMENT SYSTEM (DCAM 5.1 L3) NOTES. f o g y n r i r a t e e e i n r i p g o n r P SE A M For Training Purposes Only. i a r T. g n i n. Issue 2 Revision 0 Oct 2011 Page 23.
(32) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS NUMBERING SYSTEMS (DCAM 5.2 L2) 5.2 NUMBERING SYSTEMS Most digital transmission in today' s modern aircraft uses various types of number systems. Typically these would be decimal, binary, octal and hexadecimal, or various forms of these systems. 5.2.1 Decimal System. g n i n. This is the system in everyday use, there are 10 digits (0 to 9 inclusive), so it has a ‘base’ or ‘radix'(number of digits used in the system) of 10. Taking the number 72306 can be written as:. (7 × 10,000) + (2 × 1000) + (3 × 100) + (0 × 10) + (6 × 1). (. ) (. ) (. ) (. ) (. = 7 × 10 4 + 2 × 10 3 + 3 × 10 2 + 0 × 101 + 6 × 10 0 = 72306. ). f o g y n r i r a t e e e i n r i p g o n r P SE A M. Each digit is effectively multiplied by a power of 10.. i a r T. Note that to write 19.526 in powers of 10 then:. (1× 10 ) + (9 × 10 ) + (5 × 10 ) + (2 × 10 ) + (6 × 10 ) 1. 0. −1. −2. −3. 1 1 1 = .006 = .02 + 6 × = .5 + 2 × 10 100 1000 = 10 + 9 + .5 + .02 + .006 = 10 + 9 + 5 × = 19.526. Note that 100 = 1, in fact any number to the power of nought = 1. Proof, using the number 3 i.e. 30 = 1. 1=. 9 32 = 2 = 3 2 × 3 − 2 = 3 2+ ( − 2 ) = 3 0 9 3. 3 was used because it is an easy number to show you that any number to the power of nought is equal to 1. For Training Purposes Only. Issue 2 Revision 0 Oct 2011 Page 24.
(33) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS NUMBERING SYSTEMS (DCAM 5.2 L2) It can be seen that the decimal system is based on successive powers of 10, the number with the smallest value (100) is known as the least significant digit (LSD) and the number with the highest value is known as the most significant digit (MSD). The disadvantage of the decimal system for use in a digital computer is that the circuits which would be used, e.g. transistors, would have to have 10 discrete levels at collector current. For example 0mA (milliamps) = 0, 1mA = 1, 2mA - 2, 3mA = 3 etc. Such a system would be extremely difficult to operate because: a) Any variation of power supply would cause errors. b) Component tolerance would have to be virtually zero, and be unaffected by temperature variations. c) Component values will change with age.. i a r T. g n i n. Any errors from the above may cause an error increment of one or two, giving an incorrect output (e.g. instead of 8 [correct reading] it might be 7 or 9).. f o g y n r i r a t e e e i n r i p g o n r P SE A M. Precision is important, and to expect a circuit to be infallible in distinguishing between 10 different magnitudes of current is a bit much.. Where accuracy and speed are important it would be better to use a system which has just two states. Reliance is high because the circuit is either HIGH (voltage level) or LOW (voltage level) or ON and OFF and component characteristics variations are unimportant. The system that is the basis of today' s digital processing is the "two states" BINARY SYSTEM.. For Training Purposes Only. Issue 2 Revision 0 Oct 2011 Page 25.
(34) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS NUMBERING SYSTEMS (DCAM 5.2 L2) 5.2.2 The Binary System This has a base or radix of 2. As in the decimal system, we can represent any number in successive powers of 2. For example:. 27 = 2 4 + 2 3 + 21 + 2 0 = 16 + 8 + 2 + 1 further expanded. f o g y n r i r a t e e e i n r i p g o n r P SE A M. = 1 × 2 4 + 1 × 2 3 + 0 × 2 2 + 1 × 21 + 1 × 2 0 ↓ 1. ↓ 1. ↓ 0. ↓ 1. ↓ 1. i a r T. g n i n. means the binary number for 27 = 110112. To avoid confusion between systems with different radix this would be written as 110112 to identify it as a binary number. What about the fraction expressed as powers of 2?. 1 = 0.5 2 1 .012 = 2 − 2 = 2 = 0.25 2 1 .0012 = 2 −3 = 3 = 0.125 2 1 .00012 = 2 − 4 = 4 = 0.0625 2 .12 = 2 −1 =. For Training Purposes Only. Issue 2 Revision 0 Oct 2011 Page 26.
(35) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS NUMBERING SYSTEMS (DCAM 5.2 L2) Example Change 17.75 decimal to binary.. 17.75 = 2 4 + 2 0 + 2 −1 + 2 −2 expanded gives. = 1 × 2 4 + 0 × 2 3 + 0 × 2 2 + 0 × 21 + 1 × 2 0 + 1 × 2 −1 + 1 × 2 −2 ↓ ↓ ↓ 1 0 0 17.75 = 10001.112. ↓ 0. ↓ 1. ↓ ⋅ 1. ↓ 1. f o g y n r i r a t e e e i n r i p g o n r P SE A M. Note a binary digit is termed a bit.. For Training Purposes Only. i a r T. g n i n. Issue 2 Revision 0 Oct 2011 Page 27.
(36) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS NUMBERING SYSTEMS (DCAM 5.2 L2) 5.2.2.1 Binary/Decimal Equivalents The table below shows the relationship between Binary and Decimal numbers up to Decimal 21, but it could obviously be continued for larger numbers. Decimal Number 0 1 2 3 4 5 6 7 8 9 10. 24 0 0 0 0 0 0 0 0 0 0 0. 5-bit binary number (Word) Decimal Number 23 22 21 20 0 0 0 0 11 0 0 0 1 12 0 0 1 0 13 0 0 1 1 14 0 1 0 0 15 0 1 0 1 16 0 1 1 0 17 0 1 1 1 18 1 0 0 0 19 1 0 0 1 20 1 0 1 0 21 BINARY/DECIMAL EQUIVALENTS. f o g y n r i r a t e e e i n r i p g o n r P SE A M. 24 0 0 0 0 0 1 1 1 1 1 1. g n i n. 5-bit binary number (Word) 23 22 21 1 0 1 1 1 0 1 1 0 1 1 1 1 1 1 0 0 0 0 0 0 0 0 1 0 0 1 0 1 0 0 1 0. i a r T. 20 1 0 1 0 1 0 1 0 1 0 1. From the table it can be seen that the binary number is longer than the decimal number but because of the very fast switching speeds of modern circuits this does not present a problem. Also because of the reliability of the two-state system, the practical advantages gained by using binary numbers are considerable.. ACTIVITY: Write the successive powers of 2 for the following decimal numbers and then expand to finally give the binary number. a) 19 b) 29 c) 15.125 d) 22.0625 This method is OK but when you get larger numbers it becomes much more difficult, to convert from decimal to binary, the successive division by two may be employed, the ' remainder'of any division (which must be either 0 or 1) is then recorded successively in a separate column. The following examples show the method used. For Training Purposes Only. Issue 2 Revision 0 Oct 2011 Page 28.
(37) PART 66 CAT B1.1/B2 MODULE 5 DIGITAL TECHNIQUES & ELECTRONIC INSTRUMENT SYSTEMS NUMBERING SYSTEMS (DCAM 5.2 L2). Example 1 Convert 796 to binary 2 2 2 2 2 2 2 2 2 2. 796 398 199 99 49 24 12 6 3 1 0. remainder remainder remainder remainder remainder remainder remainder remainder remainder remainder. f o g y n r i r a t e e e i n r i p g o n r P SE A M For Training Purposes Only. i a r T. g n i n 0 0 1 1 1 0 0 0 1 1. Issue 2 Revision 0 Oct 2011 Page 29.
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