Last Updated on 4 years by teboo
022 13 01 00 Electronic display units
022 13 01 01 Design, limitations
(01) “List the different technologies used, e.g. CRT and LCD, and the associated limitations:
— cockpit temperature;
— glare;
— resolution.”
022 13 02 00 Mechanical integrated instruments
022 13 02 01 Attitude and director indicator (ADI)/ horizontal situation indicator (HSI)
(01) Describe an ADI and an HSI.
(02) List all the information that can be displayed on either instrument.
022 13 03 00 Electronic flight instrument systems (EFISs)
022 13 03 01 Design, operation
Syllabus reference BK Syllabus details and associated Learning Objectives
(01) “List the following parts of an EFIS:
— control panel;
— display units;
— symbol generator;
— remote light sensor.”
(02) Describe the typical layout of the EFIS display units and how there may be a facility to transfer the information from one display unit on to another if a display unit fails.
(03) Explain the need for standby instruments to supplement the EFIS in the event of all the display units failing and the challenge of using these standby instruments, namely their size and position on the flight deck.
(04) Explain the difference between a symbol generator failing and a display unit failing, and the implications if there are redundant symbol generators available.
(05) “Describe the purpose of an EFIS control panel and typical selections that may be available:
— altimeter pressure setting;
— navigation display (ND) mode selector;
— ND range selector;
— ND data selector (waypoints, facilities, constraints, data, etc.);
— radio-navigation aids selector (VOR 1/2 or ADF 1/2);
— decision altitude (DA)/decision height (DH) selection.”
Syllabus reference BK Syllabus details and associated Learning Objectives
022 13 03 02 Primary flight display (PFD), electronic attitude director indicator (EADI)
(01) “Describe that a PFD (or an EADI) presents a dynamic colour display of all the parameters necessary to control the aircraft, and that the main layout conforms with the ‘basic T’ principle:
— attitude information in the centre;
— airspeed information on the left;
— altitude information on the right;
— heading/track indication lower centre;
— flight mode annunciation;
— basic T;
— take-off and landing reference speeds;
— minimum airspeed;
— lower selectable airspeed;
— Mach number.”
(02) “Describe the typical design of the attitude information:
— artificial horizon with aircraft symbol;
— superimposed flight director command bars.”
(03) “Describe the typical design of the speed tape:
— rolling speed scale with numerical read-out of current speed;
— limiting airspeeds according to configuration;
— speed trend vector;
— bug/indication for selected airspeed.”
Syllabus reference BK Syllabus details and associated Learning Objectives
(04) Explain the Mach number indications and how a selected Mach number is presented with the speed bug on a corresponding IAS on the speed tape with the Mach number shown as a numerical indication outside the speed tape.
(05) “Describe the typical design of the altitude information:
— rolling altitude scale with numerical read-out of current altitude;
— altimeter pressure setting;
— bug/indication for selected altitude;
— means of highlighting the altitude if certain criteria are met.”
(06) “Describe the typical design of the heading/track information:
— rolling compass scale/rose with numerical read-out of current heading/track;
— bug/indication for selected heading/track.”
(07) “Describe the typical design and location of the following information:
— flight mode annunciators (FMAs);
— vertical speed indicator including TCAS RA command indications;
— radio altitude;
— ILS localiser/glideslope and RNP/PBN, GBAS or SBAS horizontal/vertical flight path deviation indicator;
— decision altitude/height (DA/H).”
Syllabus reference BK Syllabus details and associated Learning Objectives
022 13 03 03 Navigation display (ND), electronic horizontal situation indicator (EHSI)
(01) Describe that an ND (or an EHSI) provides a mode- selectable colour flight ND.
(02) “List the following four modes typically available to be displayed on an ND unit:
— MAP (or ARC);
— VOR (or ROSE VOR);
— APP (or ROSE LS);
— PLAN.”
(03) “List and explain the following information that can be displayed with the MAP (or ARC) mode selected on an ND unit:
— aircraft symbol, compass scale and range markers;
— current heading and track (either one may be ‘up’ depending on selection), true or magnetic;
— selected heading and track;
— TAS/GS;
— wind direction and speed (W/V);
— raw data radio magnetic indicator (RMI) needles/pointers for VOR/automatic direction- finding equipment (ADF), if selected, including the frequency or ident of the selected navigation facility;
— route/flight plan data from the FMS;
— TO/next waypoint data from the FMS;
— data from the navigation database such as airports,”
Syllabus reference BK Syllabus details and associated Learning Objectives
“waypoints or navigation facilities as selected;
— weather radar information;
— TCAS traffic information (no TCAS commands);
— TAWS (EGPWS) terrain information;
— failure flags and messages.”
(04) “List and explain the following information that can be displayed with the VOR or APP (or ROSE VOR or ROSE LS) mode selected on an ND unit:
— aircraft symbol and compass scale;
— current heading and track (either one may be ‘up’ depending on selection), true or magnetic;
— selected heading and track;
— TAS/ground speed (GS);
— wind direction and speed (W/V);
— VOR or ILS frequency and identification of the selected navigation aid;
— VOR selected course, deviation indicator and a TO/FROM indicator in a HSI-type display format when in VOR mode;
— localiser selected course, deviation indicator and glideslope indicator in a HSI-type display format when in APP mode.
— weather radar information;
— TCAS traffic information (no TCAS commands);
— TAWS (EGPWS) terrain information;
— failure flags and messages.”
Syllabus reference BK Syllabus details and associated Learning Objectives
(05) “List and explain the following information that can be displayed with the PLAN mode selected on an ND unit:
— north-up compass rose and range markers;
— aircraft symbol oriented according to aircraft heading;
— TAS/GS;
— wind direction and speed (W/V);
— route/flight plan data from the FMS;
— TO/next waypoint data from the FMS;
— data from the navigation database such as airports, waypoints or navigation facilities as selected;
— failure flags and messages.”
(06) “Explain the purpose of PLAN mode and its characteristics such as:
— no compass information;
— north is up on the display unit at all times;
— the centre waypoint is the selected waypoint on the FMS CDU;
— scrolling through the flight plan on the FMS CDU will shift the map view along the flight path;
— the aircraft symbol will be positioned in the appropriate place along the flight path;
— using PLAN mode as the primary mode during flight may lead to disorientation and loss of situational awareness.”
(07) Distinguish the difference between the appearance of an EXPANDED or FULL/ROSE mode and how the
Syllabus reference BK Syllabus details and associated Learning Objectives
displayed range differs between them.
(08) Explain the combination of mode and range selection including how selecting the appropriate range and displayed data can improve situational awareness for a given phase of flight.
022 13 04 00 Engine parameters, crew warnings, aircraft systems, procedure and mission display systems
022 13 04 01 Purposes of systems, display systems, checklists
(01) “State the purpose of the following systems:
— engine instruments centralised display unit;
— crew alerting system/aircraft display unit;
— facility for appropriate on-screen checklists;
— that the aircraft systems display unit enables the display of normal and degraded modes of operation of the aircraft systems;
— that the systems/aircraft display unit is able to show pictorial systems diagrams/schematics and associated parameters.”
(02) Describe the similarities to EFIS with regard to basic system architecture.
(03) “Give the following different names by which engine parameters, crew warnings, aircraft systems and procedures display systems are known:
— multifunction display unit (MFDU);
— engine indication and crew alerting systems (EICASs);
— engine and warning display (EWD);”
Syllabus reference BK Syllabus details and associated Learning Objectives
“— electronic centralised aircraft monitor (ECAM);
— systems display (S/D).”
(04) “Give the names of the following different display systems and describe their main functions:
— vehicle engine monitoring display (VEMD);
— integrated instruments display system (IIDS).”
(05) State the purpose of a mission display unit.
(06) Describe the architecture of each system and give examples of display.
(07) Explain why awareness of the consequences of the actions commanded by the automatic checklist is required.
(08) Explain the limited ability of the computer to assess a situation other than using the exceedance of certain thresholds to trigger the main and subsequent events and programmed actions.
(09) “Describe an appropriate procedure for following an on- screen checklist associated with a failure scenario including the following:
— confirm the failure with the other flight crew member prior to performing any of the actions;
— seek confirmation prior to manipulating any guarded switches or thrust levers;
— follow the checklist slowly and methodically;
— assess the possible implications of making certain selections, such as opening the fuel cross-feed if”
Syllabus reference BK Syllabus details and associated Learning Objectives
there is a fuel leak even though the electronic checklist may ask for the action.
022 13 05 00 Engine first limit indicator
022 13 05 01 Design, operation, information on display
(01) Describe the principles of design and operation, and compare the different indications and displays available.
(02) Describe what information can be displayed on the screen, when the screen is in the limited composite mode.
022 13 06 00 Electronic flight bag (EFB)
022 13 06 01 Purpose, certification, malfunctions
(01) “Explain the purpose of the EFB and list typical equipment:
— computer laptop;
— tablet device;
— integrated avionics suite in the aircraft.”
(02) “Describe the ‘class’ hardware certification:
— portable: portable electronic device (PED) that can be used inside or outside the aircraft, is not part of the certified aircraft configuration and does not require tools to remove it from the flight-deck cradle, if one exists;
— installed: an electronic device that is considered an aircraft part covered by the aircraft airworthiness”
Syllabus reference BK Syllabus details and associated Learning Objectives
approval, thus is a minimum equipment list (MEL) item in the event of failure.
(03) “Describe the ‘type’ software certification:
— type A: applications whose misuse or malfunctions have no adverse effect on flight safety;
— type B: applications for which evaluation of the hazards presented by misuse or malfunctions is required.”
(04) “Explain implications of malfunctions with the EFB installation in a fully electronic flight-deck environment:
— mass and balance calculations;
— performance calculations;
— access to charts;
— access to manuals.”
022 13 07 00 Head-up display (HUD), synthetic vision system (SVS) and enhanced visual system (EVS)
022 13 07 01 Components, benefits, modes of operation
(01) “State the components of a typical HUD installation:
— HUD projector and stowable combiner;
— HUD controls such as declutter and dimmer;
— HUD computer.”
(02) “Explain the reasons and benefits of having an HUD:
— increased situational awareness due to reduced need to look inside to view primary flight information;
— lower minima for both departure and landing;
— improved accuracy of flying thus reduced”
Syllabus reference BK Syllabus details and associated Learning Objectives
susceptibility to enter a state of aircraft upset.
(03) “Describe how the HUD replicates the information on the primary flight display (PFD) by showing the following data:
— altitude;
— speed, including speed trend;
— heading;
— flight path vector (track and vertical flight path);
— flight mode annunciator (FMA);
— CAS, TAWS and wind shear command annunciations.”
(04) “Describe the following modes of operation of an HUD:
— normal display mode that may automatically adapt the information based on the phase of flight;
— declutter function.”
(05) “Describe the principle of SVS:
— an enhanced database used as reference to provide terrain and ground features to be shown on the PFD;
— limitations due to being a synthetic image not based on actual sensory information thus not lowering landing minima;
— implications if aircraft position accuracy becomes reduced.”
(06) “Describe the principle of EVS:
— includes external sensors such as infrared cameras to generate a real-time image on the PFD or on the HUD;”
Syllabus reference BK Syllabus details and associated Learning Objectives
“— limitation of the fact that an infrared camera uses temperature and temperature difference in order to produce an image;
— enables lower minima because of the real-time image, thus enhancing the visibility as experienced by the pilot.”