Pilot’s Guide EFS 50 5-inch Electronic Flight Instrumentation System B AlliedSignal General Aviation Avionics 400 North Rogers Road Olathe, Kansas 66062-1212 TELEX 669916 KINGRAD FAX 913-791-1302 TELEPHONE (913) 768-3000 ©1995 AlliedSignal Inc. 4/95 006-08485-0000 1K PRINTED IN THE U.S.A.
Registration This pilot's guide has been tailored by the installation and or certification agency to cover the following EFS 50 installation: AIRCRAFT TYPE AIRCRAFT TAIL OR SERIAL NUMBER AIRCRAFT OWNER EFIS TYPE EFIS SYSTEM CONFIGURATION EFIS SYSTEM SOFTWARE LEVEL EFIS DISPLAY UNIT TYPE EFIS CONTROL PANELS REVERSIONARY MODES Throughout this pilot's guide various configuration options are described. A ✔❏ (check box) precedes each configuration option.
Registration
Table of Contents TABLE OF CONTENTS Section I INTRODUCTION I.1 Section 1 SYSTEM CONFIGURATION GENERAL CONTROL DISPLAY CONTROL DISPLAY OPTIONS SYMBOL GENERATOR EQUIPMENT INTERFACE & OPERATING CONFIGURATION SOFTWARE 06 CONFIGURATION PAGES SOFTWARE 07 CONFIGURATION PAGES (includes both 0701 and 0702) SOFTWARE 08 CONFIGURATION PAGES SOFTWARE 11 CONFIGURATION PAGES 1.1 1.1 1.1 1.3 1.3 1.5 1.6 1.10 1.14 1.
Table of Contents RADAR OPERATION Radar Controls, (CP 466A & CP 466B) OFF-STBY-TST-ON OFF STBY TST ON WX WXA GND MAP LIGHTNING VP TRK GAIN PULL ARL TILT 2.3.1 2.3.3 2.3.4 2.3.4 2.3.4 2.3.4 2.3.4 2.3.4 2.3.4 2.3.4 2.3.5 2.3.5 2.3.6 2.3.7 2.3.7 2.3.
Table of Contents Section 4 EHSI DISPLAYS EFS 50 Color Standards Standard EHSI Displays NORMAL COMPASS CARD NAVIGATION SOURCE ANNUNCIATION SYMBOLIC AIRCRAFT HEADING SELECT “BUG” COURSE SELECT LATERAL COURSE DEVIATION SCALE LATERAL COURSE DEVIATION BAR TO/FROM INDICATOR DISTANCE, GROUNDSPEED and TIME-TO-STATION DUAL MULTI CHANNEL DME INSTALLATION DME HOLD BEARING POINTER MAGNETIC/TRUE HEADING ANNUNCIATIONS GLIDE SLOPE/VERTICAL NAVIGATION WIND VECTOR DRIFT ANGLE POINTER (LNAV only) LNAV MODE ANNUNCIATIONS 360
Table of Contents PERSPECTIVE LINES SYMBOLIC AIRCRAFT HEADING TAPE FLIGHT DIRECTOR COMMAND BARS AUTOPILOT/FLIGHT DIRECTOR MODE ANNUNCIATION STANDARD 429 AUTOPILOT/FLIGHT DIRECTOR MODE ANNUNCIATION RADIO ALTIMETER DECISION HEIGHT SET DECISION HEIGHT ALERT PRECISION APPROACH MODE FORMAT EXPANDED LATERAL DEVIATION SCALE RISING RUNWAY GLIDESLOPE/VERTICAL NAVIGATION MARKER BEACON ANNUNCIATION FAST/SLOW RATE OF TURN DISPLAY CATEGORY II ANNUNCIATOR CATEGORY II OPERATION ANNUNCIATIONS CATEGORY II THRESHOLDS ATTITUD
Table of Contents VERTICAL PROFILE (VP) SYMBOLIC AIRCRAFT RANGE RINGS ALTITUDE LINE PROFILE ANGLE PLAN-VIEW, NORTH-UP MAP TCAS INTERFACE TCAS ONLY SELECTION TCAS DISPLAY FORMAT TCAS TRAFFIC SYMBOLOGY Intruder Symbols Vertical Speed Arrow Data Tag Off-Scale Traffic TCAS DISPLAY ANNUNCIATIONS Traffic TCAS TCAS Status TCAS Mode Range Range Rings Above/Norm/Below No-Bearing Traffic FLXXX and FL Weather/Lightning Annunciation CHECKLIST INTERFACE LOADING AND MODIFYING CHECKLIST DATA NOTICE CHECKLIST PAGE ORGANIZA
Table of Contents RMI 1 RMI 2 CRS(NOT) SEL TST REF CRS Knob 4.4.15 4.4.15 4.4.15 4.4.15 4.4.15 Section 5 OPERATING INSTRUCTIONS PREFLIGHT PROCEDURES START UP SELF TEST PUSH BUTTON TEST PRE-TAKEOFF PROCEDURES IN-FLIGHT OPERATION ADF LNAV (RNAV) VNAV APPROACH PROCEDURES ILS APPROACH BACK COURSE APPROACH ADF APPROACH LNAV (RNAV) APPROACH VOR APPROACH DECISION HEIGHT SELECTION LIMITATIONS EMERGENCY PROCEDURES 5.1 5.1 5.1 5.1 5.1 5.1 5.2 5.2 5.2 5.3 5.3 5.3 5.3 5.4 5.4 5.4 5.4 5.5 5.
Table of Contents BEARING POINTER ANNUNCIATIONS ALPHANUMERIC READOUT ANNUNCIATIONS CHECK CONFIG WEATHER RADAR ANNUNCIATIONS WX FLT WX OFF BUSY VP STB LMT 429 FLT ANT FLT TX FLT RANGE STB OFF WAIT TCAS FAULT MESSAGES FAULT MESSAGES 6.3 6.3 6.4 6.4 6.4 6.4 6.4 6.4 6.4 6.4 6.4 6.4 6.5 6.5 6.5 6.5 Section 7 REVERSIONARY MODES CMPST - COMPOSITE DISPLAY (EADI) DOWN SG 3 7.1 7.2 7.3 7.4 Section 8 GLOSSARY 8.1 Section 9 INDEX Issued 4/95 9.1 SW 06/07/08/11 TOC.
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Introduction INTRODUCTION This pilot’s guide describes the components, operation, and operational procedures of the BENDIX/KING EFS 50 Electronic Flight Instrumentation System (EFS) containing system software 0601 and 0701, 0702, 0801, 0802, and 1101. These software versions will normally be referred to as 06, 07, 08, and 11 where version 07 includes both 0701 (version 07, mod 1) and 0702 (version 07, mod 2). Likewise 08 includes both 0801 and 0802.
Introduction brightness. In many cases, unrealistic displays provide the most informative display possible on a single display. Therefore, we ask that you use and treat the graphic illustrations contained in this pilot’s guide as they were intended. These illustrations are to familiarize the pilot with the type and placement of data to be provided by the EFS 50. Note: The data presented in this pilot’s guide is general in nature and not tailored toward a specific installation.
System Configuration SYSTEM CONFIGURATION GENERAL CONTROL DISPLAY The 5 tube EFS 50 system Electronic Flight Instrumentation System) offered on the Lear 31A consists of: Refer to figure 1.1 for the Control Display configurations.
System Configuration ı 1 DH RALT TST SYS HSI ARC NAV REF BRT RNG CRS HDG RNG 1-2 EADI, EHSI CONTROL DISPLAY 2 EA ED 551A & CP 467 ı TCAS ONLY ARC HSI ENT CHK LIST NAV CRS 1-2 CRS TST SEL REF BRT ON TST Wx WxA VP TK GND MAP BRT STBY OFF TK OFF GAIN PULL ARL UP TILT O PULL AUTO DN MFD CONTROL DISPLAY ED 551/A, CP 469/A & CP 466B Figure 1.1 CONTROL DISPLAY CONFIGURATIONS 1.
System Configuration CONTROL DISPLAY OPTIONS The CP 467 and CP 469/A mode controllers offer a simple means for the pilot to select the desired display format, such as standard compass rose or sectored compass rose, 360-degree map or sectored map and weather radar overlay. Also incorporated on the mode controller is the course and heading (CP 467) select knobs with auto sync.
System Configuration 1 AP 12555 K T LOC 1257 GS RA YD 20 20 10 10 F N A N 3 6 10 10 20 20 T ED 551A G S 1 S LOC CRS 340 23 DH 257 243 KT 3 V O R 1 VOR 1 36.7 NM 359 126 W ADF 2 ED 551A G S E 12 24 ° NM 3.5 3 6 S 1 N 30 33 15 CRS 90 40 ARL WXA A 2.2 ANT FLT ı I L S ED 551A 36.
System Configuration EQUIPMENT INTERFACE & OPERATING CONFIGURATION The following pages are provided to document the EFS 50 equipment interface and operating configuration established at the time of installation and certification. Those pages referring to software configuration versions not applicable to this aircraft are to be removed from this pilot’s guide. Issued 4/95 SW 06/07/08/11 1.
System Configuration SOFTWARE 06 CONFIGURATION PAGES The EHSI, EADI, MFD and Reversion software will display the following pages. All display information will be identical on the EHSI and MFD,, however, the EADI will not display the rack configurations, it will display a comparison of the EHSI and EADI configuration data. The descriptions given in this section refer to side 1 (left side) as the pilot’s side and side 2 (right side) as the co-pilot’s side.
System Configuration 1 2 3 4 5 6 7 8 9 10 11 12 13 ——————————| VIEW/EDIT EQUIPMENT ITEM VNAV RADAR ALT AFCS TYPE AFCS COMMAND BAR AFCS MODE ANN F/S AIR DATA RADAR TYPE RADAR CTL PNL RADAR INDICATOR CHECKLIST ..MORE..
System Configuration 1 2 3 4 5 6 7 8 9 10 11 12 13 ——————————| VIEW/EDIT OPERATING CHAR PG 06 ITEM VERT SCALE SIDE _______________ DCLTR GS ON BC _______________ FULLTIME FMS MAP _______________ DISPLAY WIND VEC _______________ DISPLAY DRIFT _______________ DG ONLY MODE _______________ DME DIST ONLY _______________ RADAR ONLY MODE _______________ HOVER MODE _______________ MFD NAV CONTROL _______________ ..MORE..
System Configuration 1 2 3 4 5 6 7 8 9 10 11 ——————————| VIEW/EDIT OPERATING ITEM NORTH UP MAP VERT PTR TYPE DISPLAY FMS MSG SEL HDG COLOR CMD BAR COLOR REV MODE ANN RISING RUNWAY ADI DEV SRC CMD BAR FILTER Issued 4/95 PG 08 _______________ _______________ _______________ _______________ _______________ _______________ _______________ _______________ _______________ SW 06/07/08/11 1.
System Configuration SOFTWARE 07 CONFIGURATION PAGES (includes both 0701 and 0702) The EHSI, EADI, MFD and Reversion software will display the following pages. All display information will be identical on the EHSI and MFD, however, the EADI will not display the rack configurations, it will display a comparison of the EHSI and EADI configuration data. The descriptions given in this section refer to side 1 (left side) as the pilot’s side and side 2 (right side) as the co-pilot’s side.
System Configuration 1 2 3 4 5 6 7 8 9 10 11 12 13 ——————————| VIEW/EDIT EQUIPMENT ITEM DME #1 DME #2 MLS #1 MLS #2 FMS #1 FMS #2 RNAV #1 RNAV #2 TACAN #1 TACAN #2 ..MORE.. 1 2 3 4 5 6 7 8 9 10 11 12 13 ——————————| VIEW/EDIT EQUIPMENT ITEM VNAV RADAR ALT AFCS TYPE AFCS COMMAND BAR AFCS MODE ANN F/S AIR DATA RADAR TYPE RADAR CTL PNL RADAR INDICATOR CHECKLIST ..MORE..
System Configuration 1 2 3 4 5 6 7 8 9 ——————————| VIEW/EDIT EQUIPMENT ITEM JOYSTICK TCAS HOMING #1 HOMING #2 LIGHTNING DET HOVER MODE CABLE MODE 1 2 3 4 5 6 7 8 9 10 11 12 13 ——————————| VIEW/EDIT OPERATING CHAR PG 06 ITEM VERT SCALE SIDE _______________ DCLTR GS ON BC _______________ FULL TIME FMS MAP _______________ DISPLAY WIND VEC _______________ DISPLAY DRIFT _______________ DG ONLY MODE _______________ DME DIST ONLY _______________ RADAR ONLY MODE _______________ SPARE _______________ MFD NAV CONT
System Configuration 1 2 3 4 5 6 7 8 9 10 11 12 13 ——————————| VIEW/EDIT OPERATING ITEM DISPLAY HDG TAPE COMMAND BARS ROLL INDICATOR DCLTR UNUS ATT CAT II AVAILABLE PERSPECTIVE LINES DH SELECT CTL PNL SYNC SEL HDG SYNC SEL CRS SYNC ..MORE..
System Configuration SOFTWARE 08 CONFIGURATION PAGES The EHSI, EADI, MFD and Reversion software will display the following pages. All display information will be identical on the EHSI and MFD, however, the EADI will not display the rack configurations, it will display a comparison of the EHSI and EADI configuration data. The descriptions given in this section refer to side 1 (left side) as the pilot’s side and side 2 (right side) as the co-pilot’s side.
System Configuration 1 2 3 4 5 6 7 8 9 10 11 12 13 ——————————| VIEW/EDIT EQUIPMENT ITEM VNAV RADAR ALT AFCS TYPE AFCS COMMAND BAR AFCS MODE ANN F/S AIR DATA RADAR TYPE RADAR CTL PNL RADAR INDICATOR CHECKLIST ..MORE..
System Configuration 1 2 3 4 5 6 7 8 9 10 11 12 13 1 2 3 4 5 6 7 8 9 10 11 12 13 1.16 ——————————| VIEW/EDIT OPERATING CHAR PG 06 ITEM VERT SCALE SIDE _______________ DCLTR GS ON BC _______________ FULL TIME FMS MAP _______________ DISPLAY WIND VEC _______________ DISPLAY DRIFT _______________ DG ONLY MODE _______________ DME DIST ONLY _______________ RADAR ONLY MODE _______________ SPARE _______________ MFD NAV CONTROL _______________ ..MORE..
System Configuration 1 2 3 4 5 6 7 8 9 10 11 12 13 ——————————| VIEW/EDIT OPERATING ITEM NORTH UP MAP VERT PTR TYPE DISPLAY FMS MSG SEL HDG COLOR CMD BAR COLOR REV MODE ANN RISING RUNWAY ADI DEV SRC CMD BAR FILTER MLS VRT ANNUNC ..MORE..
System Configuration SOFTWARE 11 CONFIGURATION PAGES The EHSI, EADI, MFD and Reversion software will display the following pages. All display information will be identical on the EHSI and MFD, however, the EADI will not display the rack configurations, it will display a comparison of the EHSI and EADI configuration data. The descriptions given in this section refer to side 1 as the pilot’s side and side 2 as the co-pilot’s side.
System Configuration 1 2 3 4 5 6 7 8 9 10 11 12 13 ——————————| VIEW/EDIT EQUIPMENT ITEM FMS VNAV RADAR ALT AFCS TYPE AFCS COMMAND BAR AFCS MODE ANN F/S AIR DATA RADAR TYPE RADAR CTL PNL RADAR INDICATOR CHECKLIST ..MORE..
System Configuration 1 2 3 4 5 6 7 8 9 10 11 12 13 ——————————| VIEW/EDIT OPERATING ITEM DISPLAY HDG TAPE ADI PLANE/CMD BAR ROLL INDICATOR DCLTR UNUS ATT CAT II AVAILABLE PERSPECTIVE LINES DH SELECT CTL PNL SYNC SEL HDG SYNC SEL CRS SYNC ..MORE.. 1 2 3 4 5 6 7 8 9 10 11 12 13 ——————————| VIEW/EDIT OPERATING ITEM NORTH UP MAP VERT PTR TYPE DISPLAY FMS MSG SEL HDG COLOR CMD BAR COLOR REV MODE ANN RISING RUNWAY ADI DEV SRC CMD BAR FILTER MLS VRT ANNUNC ..MORE..
System Configuration 1 2 3 4 ——————————| VIEW/EDIT OPERATING ITEM RADAR SDI PITCH SYNC DISC Issued 4/95 PG 10 _______________ _______________ SW 06/07/08/11 1.
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EHSI Operation EHSI OPERATION DETAILED OPERATING CONTROLS All possible EFS 50 Interfacing Equipment is described in the Detailed Operating Controls section of the EFS 50 Pilot’s Guide, however, all may not be active in a specific installation. and the EHSI section of the CP 467 EHSI/EADI control panel. The EADI operation of the CP 467 is covered in section 2.2, EADI Operation. The CP 466A/B radar control panels are covered in section 2.3, RADAR Operation.
EHSI Operation SECTORED MODE SELECT ARC COMPASS ROSE ARC NAV MAP ARC NAV MAP WITH WX ARC COMPASS ROSE WITH WX 360 MODE SELECT HSI COMPASS ROSE NAV MAP NAV MAP WITH WX DG PULL SET RADIO ALTIMETER NAV SOURCE SELECT VOR, LOC,TCN or RNV TCN FMS, LOR, OMG or GPS NAV MLS ADF TEST/REF HOM TEST *GROUND SPEED *TIME-TO-STATION NAV MAP FORMAT PUSH TEST RADIO ALTIMETER DH RALT TST SYS HSI ARC NAV REF RNG CRS HDG 1-2 #1 BEARING POINTER SELECT DECLUTTER VOR, TCN OR RNV TCN FMS, LOR, OMG, or GPS NAV MLS A
EHSI Operation EHSI CONTROLS (CP 467) HSI 360-DEGREE MODE SELECTION HSI The EFS 50 has four possible 360-degree display formats: standard HSI compass rose, NAV map, NAV map with weather, and DG mode. Each press of the HSI button sequentially selects the next display format. A press of the HSI button while in the ARC mode will change the display to the standard HSI compass rose.
EHSI Operation played and the ARC button is pressed, the resulting display format will be ARC NAV MAP WITH WEATHER. The ARC display selection list may include the following: ARC COMPASS ROSE ARC NAV MAP A R C ARC NAV MAP WITH WEATHER (OPTIONAL) ARC COMPASS ROSE WITH WEATHER (OPTIONAL) ARC WEATHER ONLY (OPTIONAL ON MFD) WEATHER is an option selected at the time of installation and is included in the system certification.
EHSI Operation press of the NAV sensor select button sequentially selects the next available sensor from the list of those installed. Primary Navigation Data is defined as the distance in the upper right corner, selected course, course pointer and deviation. The Primary Navigation Sensor is annunciated at the side of the ON-SIDE EFS N A V display unit opposite the vertical scale. Only those sensors interfaced to the EFS 50 in a specific installation will be selectable for use and display.
EHSI Operation 1 EHSI NAV push button is pressed, the next available number 1 NAV sensor will be selected. ADF D-Bar presentation may not be available if the ADF does not provide a suitable flag output. Software 08 treats unlike LNAV sources (i.e. FMS, LOR, OMG, or GPS) as single sensors. When two unlike LNAV sources are configured, the EFS will display both the on-side LNAV and the off-side LNAV without a system number and the NAV button is used to select between them.
EHSI Operation The following is an all-inclusive list, in order, of the bearing pointer sensors that may be interfaced with the EFS 50: DECLUTTER, (NO #1 OR #2 BEARING POINTER INFORMATION IS DISPLAYED) VOR, (VOR OR TCN) TCN, (ONLY AVAILABLE WHEN THE TACAN HAS AN INDEPENDENT CONTROL HEAD) OR LNAV, (FMS, LOR, OMG, OR GPS) MLS ADF DME DISTANCE ONLY, (OPTIONAL) Only those sensors interfaced to the EFS 50 will be included in the sequence.
EHSI Operation When the map range on the MFD or pilot’s EHSI no longer matches the range selected on the copilot’s EHSI the copilot will display stale weather information for 30 seconds. A “WX FLT” warning will then display on the RADAR fault warning line alerting the pilot of range mismatch. TST/REF SYS REF The TST/REF button performs three functions: SELF TEST display, Ground speed or Time-toStation selection and LNAV MAP formatting.
EHSI Operation Note: Time-to-station is replaced with Time-to-waypoint when the selected primary nav is an LNAV providing this information. ◗ REF MAP FORMAT When the selected EFS 50 display is LNAV MAP, the TST/REF button allows selection of the desired NAV MAP format. To determine the present MAP format momentarily press the TST/REF button. The momentary button press will activate the present MAP format annunciation.
EHSI Operation COURSE SELECT KNOB CRS Rotation of the COURSE SELECT knob allows the course pointer and digital course to be set at the desired course. The CP 467 and CP 468 provide a ”DIRECT TO” feature. Pulling the CP 467 or CP 468 COURSE SELECT knob will cause the course pointer and digital course read out on the EHSI to slew to the direct course to the selected NAVAID. If the selected NAV sensor is an LNAV system, it may have modes of operation that control the selected course.
EADI Operation EADI OPERATION EADI DETAILED OPERATING CONTROLS This section, EADI Operation, of the EHI 50 Pilot’s Guide describes the EADI operational controls of the CP 467 used with an ED 551/A EADI. EADI controls are limited to three basic functions: EADI display brightness adjustment, DH (deci- DH sion height) set and Radio Altitude test. For clarification on a particular display or operational feature refer to section IV, EADI DISPLAYS or section V, OPERATING INSTRUCTIONS.
EADI Operation Decision Height selected, turning counter clockwise will decrease the Decision Height. The DH set knob is variable rate, the faster the knob is turned, the greater the change in a given amount of rotation. The Decision Height range is from “OFF” to 2,500 feet and will be displayed in one foot increments up to 500 feet and then in 10 foot increments to 2,500 feet. Once the desired DH is selected, push in the DH set knob to lock the selected DH altitude.
Radar Operation Radiation WARNING! This Instrument generates microwave radiation DO NOT OPERATE UNTIL YOU HAVE READ AND CAREFULLY FOLLOWED ALL SAFETY PRECAUTIONS AND INSTRUCTIONS IN THE OPERATING AND SERVICE MANUALS IMPROPER USE OR EXPOSURE MAY CAUSE SERIOUS BODILY INJURY Caution: 1. Maintain prescribed safe distance when standing in front of a radiation antenna.* 2. Never expose eyes or any part of the body to an unterminated waveguide.
Radar Operation Maximum Permissible Exposure Level (MPEL) In order to avoid the envelope in which the radiation level exceeds the U.S. Government standard of 10 mW per square centimeter, all personnel should remain beyond the distance indicated in the illustration below.
Radar Operation RADAR OPERATION RADAR CONTROLS, (CP 466A & CP 466B) The following section provides general operating information on EFS 50 radar control panels, CP 466A & CP 466B. Figure 2.3.1 shows the CP 466A used with an RDS 81, RDS 82 or RDS 82VP, RDS 84 or ON TST RDS 84VP. Figure 2.3.2 shows the CP 466B used with an RDS 86 or RDS 86VP. For detailed information on the specific weather radar functions, refer to the appropriate radar pilot’s guide.
Radar Operation OFF-STBY-TST-ON ON ation. Depending on the selected mode of operation, WX,WXA or MAP is displayed below the NAV source annunciator on the radar mode line. TST STBY OFF The rotary OFF-STBY-TST-ON knob selects the desired operating condition for the radar. ◗ OFF Disables the ART (Antenna, Receiver and Transmitter) power supply. “OFF” is displayed below the NAV source annunciator on the radar mode line. ◗ STBY After 30 seconds in this mode, the system is in a state of readiness.
Radar Operation annunciator on the radar mode line. (Magenta is not active in the GND MAP mode.) LIGHTNING ❏ (Optional) Enables the Lightning display when pressed if a weather mode is selected for display. VP VP ❏ (Optional) Once the desired azimuth is selected with the TRK button, press the VP button to enter the Vertical Profile mode of operation. The Vertical Profile Screen will appear.
Radar Operation Beginning with EFS software version 11, a Split Screen mode is added to the VP button selection sequence immediately following the Vertical Profile mode. Durng this Split Screen mode the EFS will toggle the antenna between vertical and horizontal scans every 6 seconds, allowing both to be displayed simultaneously on the MFD. See Figure 4.4.4.
Radar Operation GAIN GAIN Manual gain control becomes active when GND MAP is selected. In all other modes, gain is internally set. PULL ARL PULL ARL Only present when an RDS 86 or RDS 86VP is installed. Automatic Range Limit displays a blue area behind weather systems where weather detection is no longer possible because of attenuation. If a CP 466A is installed, pull the Tilt selector knob, PULL STAB OFF, for “STAB OFF” operations.
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MFD Operation MFD OPERATION MULTI FUNCTION DISPLAY CONTROL PANEL The EFS 50 Multi Function Display Control Panel provides for display of a more meaningful variety of data than was previously accessible on EFIS MFD displays. In fact, the EFS 50 MFD may be used as a second EHSI by the pilot or copilot, providing them the ability to cross check their primary EHSI, preview or set up for a potential navigation scenario, and still function as a primary weather radar or LRN map display.
MFD Operation CONTROL PANEL BUTTON OPERATIONS Those push buttons which have common operation between the MFD and EHSI control panels, CP 467 and CP 468, will function as defined in the section 2.1, EHSI Operation unless otherwise noted in this section. For detailed operational information on those buttons please refer section 2.1. pendent of, the one on the CP 467. The MFD ARC button will allow the selection of an optional radar only MFD display. This display will not contain navigation or map data.
MFD Operation the pilot can complete the entire checklist by using only the enter button. Normally, pressing the ‘ENT’ button will cause an unchecked checklist line to be checked and the cursor to advance to the next unchecked line. At the end of a page pressing the ‘ENT’ button will cause the cursor to advance to the next page (if available) and to check the first unchecked line on that page.
MFD Operation The course select knob will function identical to, but independent of the one on the EHSI control panel, CP 467, when the CRS SEL button is activated. This provides independent selection of course on the MFD referenced to the same or a different nav sensor. Will function identical to, but independent of, the one on the CP 467. If the CRS SEL button is not activated, the course select knob on the CP 469 will not be active.
MFD Operation pendent of the display range selected. The cursor is not allowed to exit the compass. When an LNAV is selected as the primary navigation source, Lat/Lon coordinates of the cursor will be displayed in the lower center of the display. The cursor position information can be transferred to the LNAV that is selected as the primary navigation sensor, by pressing the ENTER button while the cursor and its coordinates are displayed.
MFD Operation ◗ CHECKLIST MODE (available with software 08) In the Checklist mode, the Joystick commands will be limited to four positions: UP, DOWN, LEFT and RIGHT. The 45° commands will be ignored. A down push on the joystick will advance the cursor checklist line. A down push at the bottom of a checklist page will advance the cursor to the next page if available. Continuous downward pushes will wrap the cursor within a checklist. An up push on the joystick will move the cursor up one checklist line.
MFD Operation TST/REF BUTTON TST REF With checklist inactive, this button will function identical to, but independent of, the TST/REF button on the CP 467. With checklist active, thIs button will cause a checklist “help” page to be displayed on the MFD. The help page contains a list of all CP 469A buttons that are active and thier function during the checklist mode. Refer to section 2.1 EHSI OPERATION for detailed information. Issued 4/95 SW 06/07/08/11 2.4.
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Abbreviated Operations 360 MODE SELECT HSI COMPASS ROSE NAV MAP NAV MAP WITH WX DG ONLY (OPTIONAL) PLAN VIEW (OPTIONAL) SECTORED MODE SELECT ARC COMPASS ROSE ARC NAV MAP ARC NAV MAP WITH WX ARC COMPASS ROSE WITH WX WX ONLY (OPTIONAL) COURSE SELECT ACTIVATE DEACTIVATE NAV SOURCE SELECT VOR, LOC,TCN or RNV TCN FMS, LOR or *GPS NAV MLS ADF HOM TEST/REF TEST +GROUND SPEED +TIME-TO-STATION NAV MAP FORMAT CRS SEL HSI ARC TST NAV REF RNG BRT CRS 1-2 #1 BEARING POINTER SELECC DECLUTTER VOR, TCN OR RN
Abbreviated Operations 360 MODE SELECT HSI COMPASS ROSE NAV MAP NAV MAP WITH WX DG ONLY (OPTIONAL) PLAN VIEW (OPTIONAL) SECTORED MODE SELECT ARC COMPASS ROSE ARC NAV MAP ARC NAV MAP WITH WX ARC COMPASS ROSE WITH WX WX ONLY (OPTIONAL) COURSE SELECT ACTIVATE DEACTIVATE NAV SOURCE SELECT VOR, LOC,TCN or RNV TCN FMS, LOR or *GPS NAV MLS ADF HOM TEST/REF TEST +GROUND SPEED +TIME-TO-STATION NAV MAP FORMAT CRS SEL HSI ARC TST NAV REF RNG BRT CRS 1-2 #1 BEARING POINTER SELECC DECLUTTER VOR, TCN OR RNV
Abbreviated Operations 360 MODE SELECT HSI COMPASS ROSE NAV MAP NAV MAP WITH WX DG ONLY (OPTIONAL) PLAN VIEW (OPTIONAL) TCAS ONLY SELECT ACTIVATE DEACTIVATE NAV SOURCE SELECT VOR, LOC,TCN or RNV TCN FMS, LOR or GPS NAV MLS RANGE SELECT ADF CHECKLIST LEVEL HOM NAV MAP WX TCAS SECTORED MODE SELECT ARC COMPASS ROSE ARC NAV MAP ARC NAV MAP WITH WX ARC COMPASS ROSE WITH WX WX ONLY (OPTIONAL) ENTER SENDS JOYSTICK WAYPOINT TO LNAV CHECKS OFF CHECKLIST ITEMS TCAS ONLY HSI ARC ENT CRS CHECKLIST SELECT ACTI
EHSI Displays EHSI DISPLAYS EFS 50 COLOR STANDARDS The EFS 50 uses a defined color set which aids the pilot in interpreting displayed information.
EHSI Displays Dual selectable compass inputs are provided for. If a second compass system is installed, the cross-side source is selected by means of a remote mounted switch. Once the alternate compass source has been selected, a yellow HDG1 or HDG2 will be displayed to the left of the lubber line. If both systems select the same heading source, a yellow “HDG1” or “HDG2” with a yellow box around it will appear on both EHSIs alerting the pilots that they have the same source selected.
EHSI Displays NORMAL V O R P I L O T V O R 1 2 GREEN GREEN SAME SOURCE C O P I L O T V O R 2 P I L O T V O R 2 C O P I L O T YELLOW GREEN YELLOW BOX AROUND SENSOR BOTH SELECT CROSS SIDE V O R 2 P I L O T V O R 1 C O P I L O T YELLOW YELLOW Figure 4.1.2 SAME NAVIGATION SOURCE SELECTION ANNUNCIATION NAV source annunciators will be The heading bug is used to indiyellow with no yellow box.
EHSI Displays indicates the selected navigation course in degrees. When in a NAV map display mode, the course pointer will not be displayed, the alphanumeric readout will be the only reference for the selected course. Note: Desired track readout (DTK) generated by an LNAV system replaces (CRS) in LNAV mode. Some LNAV systems may display CRS or DTK depending on the selected mode. MLS may display AZ (azimuth) or BAZ (back azimuth) depending on the selected mode.
EHSI Displays MODE ANGULAR DEV (DEGREES) VOR/TAC 1 dot 5.0 deg 2 dots 10.0 deg ADF 1 dot 7.5 deg 2 dots 15.0 deg LNAV or RNAV LNAV or RNAV APPR LINEAR DEV (MILES) 1 dot 2.5 NM 2 dots 5.0 NM 1 dot 0.625 NM 2 dots 1.25 NM LATERAL DEVIATION SCALE Aircraft displacement selected navigation or localizer course. Note: The Lateral Course Deviation Bar may not be used as the primary means of navigation during an ADF approach.
EHSI Displays in the lower left corner below the NAV 1 source annunciator. The readout for NAV 2 (the doublebar bearing pointer) is in the lower right corner below the NAV 2 source annunciator. These readouts show distance (in nautical miles) to the selected station when in VOR, TACAN, ILS or MLS mode. When in LNAV or RNAV mode, distance to the waypoint is shown. Each of these three distance readouts is displayed in the same color as the source annunciator and pointer with which it is associated.
EHSI Displays whose primary job is servicing the number one VOR/ILS, failed, the symbol generator would look to DME number two for VOR/ILS DME number one distance information. If the information was present, a yellow boxed DME 2 would be displayed in the upper right hand corner of the number one EHSI and MFD. This alerts the pilot he is now getting distance information from the copilot’s DME.
EHSI Displays and the DME assigned to that side is placed in HOLD, the large ADF annunciation will reduce in size as the white held DME range information and orange “H” is displayed below it. Please note that the range information being displayed is not referenced to the ADF, but to whatever channel the DME was tuned to when the pilot placed it in HOLD. DME and DME HOLD operation may vary greatly from installation to installation.
EHSI Displays verted to MAGNETIC reference. If the compass card is TRUE referenced, MAGNETIC bearing sensor pointers, such as VOR and ADF, may be displayed if valid mag var (magnetic variation) is provided to the EFS 50. In this case, the MAGNETIC sourced bearing pointer information will be converted to TRUE reference. In most cases mag var is provided by an LNAV. In a single LNAV installation the EFS 50 will use the single mag var source to compute display correction for both number 1 and number 2 sensors.
EHSI Displays pointer is pointing 30 degrees to the right of the lubber line, you must remember that the pointer in this instance is referenced to the compass card — not the lubber line or symbolic aircraft. When interpreting bearing pointer number two in this example, remember that ADF indications are referenced to the lubber line and the symbolic aircraft. They are not referenced to the compass card. The compass card can be used only to help you determine ADF relative bearing.
EHSI Displays provided by an LNAV in the approach mode, however after 08 SW, this scaling can be configured to be ±1000, ±500, ±250, or ±200 feet. If the selected sensor is ILS, a “GS” will be displayed in the vertical pointer. When MLS is the selected sensor, this annunciation will be “GS” for SW 06 and 07, but beginning with SW 08, either “GS” or “GP” (for Glide Path) may be annunciated. “VN” will be annunciated if the selected sensor is an LNAV with VNAV selected.
EHSI Displays WIND VECTOR ❏ When the aircraft is equipped with the appropriate LNAV equipment, an optional full time wind vector indicating approximate wind direction and speed may be displayed in white in the upper left corner below the selected course. Wind vector information will be available only when valid data is provided by the LNAV. The information provided by this vector is advisory only.
EHSI Displays 360 MAP DISPLAYS Refer to Figures. 4.1.7 and 4.1.8 while reviewing 360 MAP DISPLAYS. The EFS 50 provides two basic map formats, a 360-degree map display about the aircraft and an approximately 85-degree sectored map display in front of the aircraft. Information which may be displayed includes waypoints, navaids, airports and weather radar information. The type and amount of data presented on the map will depend on the interfacing equipment.
EHSI Displays the selected primary NAV sensor is LNAV or en route RNAV the inbound “TO” course line is cyan (green in approach mode). Any time the cross-side sensor is selected as the primary NAV sensor the inbound “TO” course line is yellow. If the primary NAV sensor distance or bearing information becomes invalid the NAV symbol and course line will be removed. “NO MAP” will be displayed to alert the pilot that insufficient data is present to calculate and plot the primary NAV sensor map.
EHSI Displays netic bearing pointers when the compass card is True referenced and the display of True bearing pointers when the compass card is magnetic referenced. REFERENCE WAYPOINT When the joystick is interfaced to an EFS 50 system, it can be used to generate and move a single Reference Waypoint on the display unit. This reference waypoint can then be entered into the KNS 660 or any other LNAV using an appropriate GAMA 429 interface.
EHSI Displays move a waypoint on the copilot’s EHSI, and any waypoint created by the pilot can be loaded only into the #1 RNAV or #1 LNAV. Conversely, the co-pilot’s joystick will not be allowed to create or move a waypoint on the pilot’s EHSI, and any waypoint created by the co-pilot can be loaded only into the #2 RNAV or #2 LNAV.
EHSI Displays radar provide dual range selection by allowing the radar indicator and EHSI or dual EHSIs to select independent ranges. Only one source of radar mode, tilt and gain is supported. When the ranges selected on the two controlling indicators do not match, the weather presentation will be updated on alternating sweeps of the radar antenna. Example: if pilot’s EHSI is updated on the right sweep then the radar indicator will be updated on the left sweep or vice versa.
EHSI Displays button (see section 2.3) which will alternately select and deselect lightning for display, however when selected, the lightning data will be in addition to the weather radar information if both are provided. The weather radar may be placed in standby if only lightning information is desired. A single lightning data field is located immediately above the weather radar data fields. Three annunciations are possible in this field as shown in figure 4.1.8 at the end of this section.
EHSI Displays tion must be accomplished according to the raw data presented by the selected primary NAV sensor being displayed on the lateral and vertical deviation pointers, not by the LNAV map. The LNAV map will be displayed only if an LNAV is installed on the same side as the selected ILS or ADF primary NAV sensor and the map mode is being displayed. Note: Extreme care must be taken when this mode is used not to focus on the LNAV map.
EHSI Displays ARC (EXPANDED SECTORED MODE) DISPLAYS The expanded sectored (ARC) format provides an enlarged display of weather radar information and increased resolution of navigation data due to the enlarged compass scale presentations. Note: The following will address only those areas of the EFS 50 ARC mode which are different from the standard EHSI compass or MAP presentations. HDG BUG (ALL ARC FORMAT MODES) Heading bug operation is the same in all modes.
EHSI Displays 1 CRS 345 175 NM 150 KT 1:10 030 W 12 24 E S 21 FMS 1 200 NM 15 1 3 6 V O R N 30 33 020° ADF Figure 4.1.3 TYPICAL EHI 50 DISPLAY Issued 4/95 SW 06/07/08/11 4.1.
EHSI Displays 1 CRS 120 6 E 2 1 3 S N 5 2 33 1 24 W 1 120 KT 0:02 1 V O R 4.2 NM HDG 30 VOR 4.2 NM ADF Figure 4.1.4 LOSS OF HEADING DISPLAY Issued 4/95 SW 06/07/08/11 4.1.
EHSI Displays Drift Angle Bug Lubber Line DG Mode OR Source Course/Desired Track Wind Speed 33 Vertical Deviation Scale W G S 24 12 21 ADF 1 12.6 NM H S 1 3 15 L O C N Selected MLS Glidepath Angle 3.5 E #1 System Bearing Pointer NM 117.95 H 6 Deviation Bar 12.
EHSI Displays Course Selection FDG HDG1 HDG2 CRS DTK AZ BAZ Range Annunciation N M Ground Speed or DME Hold Frequency KT H 1 CRS 359 23 Selected Glidepath Angle W X.XX G S 24 12 S 21 ADF 1 12.6 NM H System Annunciator VNAV FT AN E 1 FT 3 6 L O C N 30 33 VOR LOC RNV TCN FMS LOR GPS NAV MLS ADF HOM TST H:MM 0:06 15 Primary Navigation Source Time-To-Station 12. N 6117.95 MH FDG Vertical Scale Sources GS GP VN 360° VOR 2 50.
EHSI Displays Map To/From True Heading Indicator Annunciator Courseline 1 CRS 327TO 36.7 NM 243 KT 0:09 T 23 W 40 24 15 S 21 ARL WXA A 2.2 ANT FLT 12 WX Radar Tilt Angle 1 VORTAC Map Symbol Range Ring E WX Radar Automatic Range Limiting WX Radar Mode 3 6 WX Radar Scan Limits V O R N 30 33 360° ADF 1 WX Radar Fault/Warning Half Range Distance 360 Degree Map Compass Course Deviation Indicator Course Deviation Bar Figure 4.1.
EHSI Displays TO FR 1 CRS 327TO 23 3 30 N 24 W 40 15 S 21 N ON ARL WXA A 2.2 ANT FLT LEVEL 1 Lightning cell LEVEL 2 Lightning cell LEVEL 3 Lightning cell 12 WX WXA MAP STBY TEST Blank 33 E ARL Blank NM 243 KT 0:09 6 N ON N OFF N FLT V O R 1 36.7 T 360° ADF 1 WX FLT WX OFF WAIT RANGE STB LMT 429 FLT ANT FLT TX FLT RANGE STB OFF Blank BUSY VP Figure 4.1.8 EHSI MAP SYMBOL DEFINITION Issued 4/95 SW 06/07/08/11 4.1.
EHSI Displays 1 CRS 340 23 36.7 NM N 3 33 Arc Compass Card Auto Tilt Annunciator V O R 1 N ON ARL WXA A 2.2 ANT FLT 90 ° Off Scale Heading Bug Read Out 40 VOR 1 36.7 NM To/From Pointer 243 KT 0:09 ADF 2 Course Deviation Bar Course Deviation Scale Figure 4.1.9 EHSI ARC MAP SYMBOL DEFINITION Issued 4/95 SW 06/07/08/11 4.1.
EHSI Displays 1 6.2 CRS 359 NM 117.95 H 23 W G S VERTICAL EXCESSIVE DEVIATION ARROWS 12 24 E 15 S 1 3 6 L O C N 30 33 21 ADF 1 360° CAT II VOR 2 30.8 NM CAT II ANNUNCIATION HORIZONTAL EXCESSIVE DEVIATION ARROWS Figure 4.1.10 EHSI CAT II SYMBOLOGY Issued 4/95 SW 06/07/08/11 4.1.
EADI Displays EADI DISPLAYS NORMAL ATTITUDE DISPLAY PITCH ATTITUDE played in the form of a hollow triangle. Refer to Figure 4.2.4. A moving white simulated horizon line rotates angularly with the roll of the aircraft and moves up and down with the pitch of the aircraft. Blue sky above the horizon and brown ground below the horizon align with the horizon line as it follows the aircraft’s pitch and roll.
EADI Displays able horizon. The symbolic aircraft is flown to satisfy the command cues of the flight director. The EFS 50 offers two symbolic aircraft symbols, the Bull’s Eye and Delta. Selection of the single cue command bars will present a delta aircraft symbol, while selection on the double cue command bars will provide a traditional bull’s eye aircraft symbol. Level Attitude 20° Right Roll SKY POINTER ROLL SCALE In the event of an attitude failure, the roll indicator is removed from the display.
EADI Displays FLIGHT DIRECTOR COMMAND BARS ❏ Flight director commands are displayed as moving green or magenta bars when the flight director is engaged. Located in the center of the EADI display about the fixed aircraft symbol, indicating roll and pitch required to satisfy the computed flight director commands. Deselecting the flight director or an invalid “FD” will cause the command bars to be removed. The flight director command bards are pilot selectable between single or dual cue via an external switch.
EADI Displays The following table and figure describes those modes supported and location in which they may be displayed. AUTOPILOT AP SR HB CWS YD LATERAL HDG NAV LOC APR BC ROL AZ BAZ FLIGHT DIRECTOR VERTICAL ALT ALTC VS MACH IAS VNAV GS (H,L,N)CLB (H,L,N,)DES GA PIT 1 AP YD SR HB CWS 12555 K VNAV T ALT GS NAV LOC 20 1257 RA 20 F Software release 06 added the following autopilot failure warning annunciations.
EADI Displays If the flight director data becomes invalid, a RED “FD” enclosed in a RED box will be displayed at the right center of the display. If the autopilot has been on and then disengaged, a RED “AP” will be annunciated in the upper left hand corner of the display. The RED “AP” will flash when disengaged. Dual autopilot installations, the active side is annunciated by a green “AP” and the inactive side will be annunciated by a yellow “AP” with a yellow arrow pointing toward the active side.
EADI Displays bottom of its scale and moves laterally to indicate the LOC or MLS deviation. DECISION HEIGHT SET A part time green alphanumeric readout, located in the lower right corner, displays the letters DH and selected decision height in feet as manually established by the DH set control knob. With the control pulled out, the DH set value is displayed and may be set regardless of aircraft altitude. With the control knob “in”, DH is displayed only for radio altimeter altitude less than 2500 feet AGL.
EADI Displays pilot that back course information is being displayed. Refer to Figure 4.2.3 and 4.2.4. Software version 07 and higher will display the expanded LOC/MLS scale as three dots. Note: Warning, some conventional ADI expanded ILS and MLS displays represent 1/4 of the full scale displayed by the HSI. The EFS 50 provides 1/2 the EHSI displayed deviation to provide better pilot interface.
EADI Displays GLIDESLOPE/VERTICAL NAVIGATION When the selected primary NAV sensor is ILS, MLS or LNAV with VNAV selected, a stationary white vertical deviation scale will appear on the right or left side of the EADI display as configured at the time of installation and certification. This scale provides a reference for the vertical deviation pointer. The deviation pointer moves in relation to the scale to indicate glide path center with respect to aircraft position.
EADI Displays played when the airspeed is less than 50 knots or less than 0.45 mach from the airspeed bug selected setting. The scale and pointer will be removed when the airspeed is greater than 50 knots or 0.45 mach from the airspeed bug. The scale provides ±10 knots indication and ±13 knots full scale deflection. AS will be annunciated in the pointer. Configuration options selectable at the time of installation and certification: ❏ Display of Fast/Slow on the display. Three pointer styles are provided.
EADI Displays Activation of the remote Category II switch by the pilot will cause a yellow CAT II to be displayed on the ADI and HSI to indicate that Category II annunciations are active. The remote Category II selection switch will be a momentary contact type for software 06 and 0701, but must be alternate action for software 0702 and 08 (or later). Category II can be activated at any time and in all normal modes of the EFS.
EADI Displays excessive deviation arrows (>> <<) will appear on the ADI and HSI localizer and glideslope scales. If the rising runway is configured for display, green chevrons will be displayed within it. Location of the excessive deviation arrows on the localizer and glideslope scales will be displayed according to the Category II limits.
EADI Displays Note: FAR localizer limits will change on initial 300 feet crossing and will remain at new limits. An additional configuration option provided with 0702 and 08 software allows CAT II operation without any deviation monitoring. When activated, Category II deviation limit (>> <<) indicators are displayed on the glideslope and localizer scale, chevrons will also be displayed on the rising runway if it is configured for display.
EADI Displays available) differ by more than 6 degrees. The miscompare will also be displayed if the failure warning flags differ. SG2 configured can cause miscompare annunciations only with software versions before 11. Note: In reversionary modes the EHSI Attitude may be used for comparison if required.
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EADI Displays 1 20 20 10 10 N 3 6 10 10 20 20 T Figure 4.2.1 TYPICAL EADI 50 DISPLAY Issued 4/95 SW 06/07/08/11 4.2.
EADI Displays AP/FD MODE ANNUNCIATORS DIGITAL RADAR ALTIMETER DISPLAY SKY POINTER ı AP HEADING TAPE YD SR HB CWS NAV 275 K T VNAV ALT 20 20 10 10 1257 RA RADIO ALTIMETER ANN HEADING BUG F N A S FAST SLOW POINTER 3 6 10 10 20 20 G S T S LOC OM DH 200 FAST SLOW SCALE SELECTED DECISION HEIGHT LATERAL DEVIATION BAR LOC SCALE STANDARD LATERAL DEVIATION SCALE Figure 4.2.2 EADI SYMBOLOGY DEFINITION Issued 4/95 SW 06/07/08/11 4.2.
EADI Displays LATERAL FD/AP MODE AP COMMAND DATA AP MODES VERTICAL FD/AP MODES ı AP YD SR HB CWS 12555 K T NAV LOC VNAV ALT GS 20 20 10 10 1257 RA VERTICAL DEVIATION POINTER F N A S SINGLE CUE FD COMMAND BARS 3 6 10 10 20 20 G S T VERTICAL DEVIATION SCALE S LOC DH 200 PITCH SCALE RISING RUNWAY LATERAL DEVIATION EXPANDED LATERAL DEVIATION SCALE Figure 4.2.3 EADI SYMBOLOGY DEFINITION Issued 4/95 SW 06/07/08/11 4.2.
EADI Displays ı AP YD SINGLE CUE FLIGHT DIRECTOR COMMAND BARS SR HB CWS 12555 K T NAV LOC VNAV ALT GS 20 20 10 10 1257 RA HORIZON LINES WITH HEADING TAPE F N A S 3 6 10 10 20 20 G S T PERSPECTIVE LINES S IM LOC DH 200 SINGLE CUE DELTA AIRCRAFT SYMBOL SCALE ANNUNCIATOR EXPANDED LATERAL DEVIATION SCALE Figure 4.2.4 EADI SYMBOLOGY DEFINITION Issued 4/95 SW 06/07/08/11 4.2.
EADI Displays CHECK CONFIGURATION MESSAGE ATTITUDE MISCOMPARE RADIO ALTIMETER MISCOMPARE ı AP YD NAV SR HB CWS F ATT 275 K T 1257 VNAV ALT DECISION HEIGHT ALERT RA 20 20 CHECK CONFIG 10 10 DH ATT1 ATTITUDE SELECT FLAG N 3 6 G S T A S HDG1 10 HEADING SELECT FLAG 10 SG IM MM OM HDG SG 3 COPY S 20 20 GLIDE SLOPE MISCOMPARE HEADING MISCOMPARE LOC DH 1300 MARKERS RATE OF TURN SCALE LOCALIZER MISCOMPARE RATE OF TURN POINTER Figure 4.2.
EADI Displays ATTITUDE FAIL ANNUNCIATOR ı AP YD SR HB CWS 12555 K T NAV APR 20 DISPLAY UNIT FAN FLAG RA FLIGHT DIRECTOR FAILURE ANNUNCIATOR 20 10 TEST 10 FD HDG N A S CONTROL PANEL FLAG --- VNAV ALT ATTITUDE FAIL F FLIGHT TEST MODE ANNUNCIATOR 3 6 G S T HEADING FAILURE ANNUNCIATOR S CP DU SG SG 10 10 20 20 LOC DH 200 SG FLAG SG FAN FLAG Figure 4.2.6 EADI FAULTS SYMBOLOGY Issued 4/95 SW 06/07/08/11 4.2.
EADI Displays ı AP LOC 20 20 10 10 33 100 GS RA DH N G S 10 10 20 20 CAT II RISING RUNWAY CHEVRONS CAT II VERTICAL EXCESSIVE DEVIATION ARROWS CAT II ANNUNCIATOR LOC DH 200 LATERAL EXCESSIVE DEVIATION ARROWS Figure 4.2.7 CAT II SYMBOLOGY Issued 4/95 SW 06/07/08/11 4.2.
EADI Displays ı AP YD SR HB CWS NAV 275 K T VNAV ALT 20 20 10 10 2490 RA F N A S 3 6 10 10 20 20 S DH 200 Figure 4.2.8 EXAMPLE EADI ENROUTE DISPLAY WITH 08 SOFTWARE Issued 4/95 SW 06/07/08/11 4.2.
EADI Displays ı AP YD SR HB CWS NAV 275 K T 1257 VNAV ALT 20 20 10 10 RA F N A S 3 G S 6 10 10 20 20 S OM LOC DH 200 Figure 4.2.9 EXAMPLE EADI APPROACH DISPLAY WITH 08 SOFTWARE Issued 4/95 SW 06/07/08/11 4.2.
COMPOSITE Displays COMPOSITE DISPLAYS COMPOSITE MODE Refer to Figures 4.3.1 and 4.3.2 while reviewing this section. In the event of a display unit or EADI symbol generator section failure, the composite mode may be selected for display on the remaining good display unit by means of an external switch. The base composite display utilizes the standard EADI display for its foundation.
COMPOSITE Displays selected heading. In addition to the digital display, on the heading tape is a hollow orange heading bug which provides a visual cue of the selected heading with reference to the aircraft heading. Note: As the aircraft heading changes, the selected course pointer and heading bug will follow the heading tape and may disappear from view.
COMPOSITE Displays Beginning with software 11, the deviation bar and scale are decluttered when lateral deviation information is provided in ARINC 429 format with a status of No Computed Data (NCD). The red “X” is still displayed for invalid or missing data. TO/FROM Displayed left of the center diamond on the lateral deviation scale, a white “TO” or “FR” will provide TO/FROM information when in non-ILS or non-MLS modes.
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COMPOSITE Displays ı 20 20 10 10 N 33 V O R 1 175 NM 10 10 20 CRS 355 3 20 TO HDG 020 Figure 4.3.1 COMPOSITE ENROUTE MODE DISPLAY Issued 4/95 SW 06/07/08/11 4.3.
COMPOSITE Displays ı 100 COURSE POINTER RA PRIMARY NAVIGATION SENSOR 20 10 10 N 33 L O C 1 175 NM DME/LNAV DISTANCE 20 IM 10 10 20 20 CRS 355 SELECTED COURSE 3 HEADING BUG G S HDG 020 SELECTED HEADING Figure 4.3.2 COMPOSITE APPROACH MODE DISPLAY Issued 4/95 SW 06/07/08/11 4.3.
MFD Displays MFD DISPLAYS The MFD’s primary purpose is to provide weather radar and/or LNAV moving map information. In addition to providing the traditional display functionality, the EFS 50 MFD also has the ability to function as an independent EHSI if the system is configured to provide such functionality. In such cases, the information displayed on the MFD follows the same basic display format as the EHSI. Therefore this section will only address those areas of the MFD that differ from the EHSI.
MFD Displays ◗ ALTITUDE LINE Three horizontal altitude lines are present on the VP display. The center line is off the nose (bore line) of the symbolic aircraft, representing the actual aircraft’s present altitude. Equally spaced above and below the 0 foot center line are two altitude lines a certain number feet above and below the aircraft. The number associated with these lines varies with the selected range to compensate for the radar beam width at the various ranges.
MFD Displays TCAS INTERFACE ❏ With software 08 and higher a configuration option available at the time of installation and certification, provides a TCAS ONLY traffic display on the MFD. A “TRAFFIC” message is provided for the pilot and co-pilot EHSI displays during an active TA or RA, but intruder traffic will not be shown on these displays, only the MFD. NOTE: In some installations TCAS “TRAFFIC” and status advisories may not be displayed on the EHSI’s.
MFD Displays ◗ TCAS DISPLAY FORMAT TCAS ONLY display will be 360° format and normally contain the following elements: * Small cyan symbolic aircraft symbol located in the center of the 360° TCAS ONLY display. * Two NM range ring consisting of cyan dots positioned every 30 degrees to represent the 12 clock positions is presented on 5 NM and 10 NM ranges only.
MFD Displays tude) in hundreds of feet between the intruder and own aircraft. (+ = intruder above own aircraft) During selection of actual altitude, and with a valid source of own altitude provided by the TCAS processor, the data tag will consist of three digits representing hundreds of feet above MSL. Actual altitudes below sea level will be displayed as two digits preceded by a minus sign. The data tag will be centered on the intruder symbol and positioned above it when the intruder is above own aircraft.
MFD Displays TCAS Status TCAS mode, range, above/norm/below selection, and actual altitude (FL) selection will be presented in the bottom right corner of the display normally used for the RMI 2 pointer annunciations. FLxxx and ABV/BLW are both provided in the same five character field when specific conditions are satisfied as shown in the following table.
MFD Displays a Traffic Advisory (TA). The color will be cyan when there are no intruders classified as a TA. TCAS I installations will indicate TA during normal operation. TA/RA - Indicates normal operation for TCAS II. This annunciation will not appear when TCAS I is installed. Range Range is annunciated in cyan without an alpha prefix immediately to the left of the TCAS status information. The ranges available are 2, 5, 10, 20 and 40 NM.
MFD Displays will be “FL” (without the three digit number) in yellow when actual altitude has been selected but a valid source of own aircraft actual altitude is not provided by the TCAS processor. Negative actual altitudes will be displayed as two digits preceded by a negative sign. (FL-XX) NOTE: At the time of this publication TCAS display in conjunction with other display formats was not certified.
MFD Displays NOTICE THE USER IS SOLELY RESPONSIBLE FOR CHECKLIST CONTENT more detailed information on generating and modifying checklist and note pages. The PC must have DOS version 3.0 or greater and should have at least 512 Kbytes of free RAM. A cable, KPN 155-02794-0002 is required to load the checklist data from the PC to the CP 469A via RS 232. Checklist data in the CP 469A can also be downloaded from the CP 469A to the PC where it may be modified and then re-loaded back into the CP 469A.
MFD Displays low any user-defined index entries. The user is not required to have any NOTE pages, but the index entry will always be present. The user-defined index entries may point to sub-index pages, or directly to a checklist. The user is free to name these entries, and to determine their organization. Typically, the first entry on the root page would be ‘EMERGENCY PROCEDURES’, but the user is free to provide another organization.
MFD Displays is similar in format to the index pages, but with some important differences. The title line consists of title text and a relative page number indication, as with the index pages. The checklist item portion consists of eleven lines of text, with the first two character columns reserved like the index pages. A checklist entry can span more than one line, but cannot span across checklist pages.
MFD Displays oritized discrete lines for emergency page use. Using the PC, the user can bind these active low inputs to specific checklist pages, which can be tailored to the nature of the emergency discrete. Any discretes which are not bound using the PC will be ignored by the CP 469A.
MFD Displays provide approximately 800 pages of normal, abnormal, and emergency data. Joystick The joystick can be moved side to side, up and down, and to the 45 degree points. The 45 degree points will be ignored in checklist mode.Joystick position data will be transmitted continually to the EFS MFD for use in MAP processing, and will be used by the CP 469A processor to enable movement through checklist pages (when the CP 469A is in checklist mode).
MFD Displays the cursor is placed on the first unchecked index entry of the parent index list. If no unchecked index entries exist at that level, the search continues up the checklist tree until an uncompleted index entry is found, or until the cursor reaches the root index page. If the item is checked off and the enter button is depressed, the line will be unchecked and the cursor will remain at the line just unchecked.
MFD Displays 1-2 CRS (NOT) SEL When checklist mode is active, the 1-2 key normally will not be active. However, if the active emergency summary page is currently displayed, the 1-2 key will cause the checklist unit to display an informational page listing all currently ‘bound’ emergency discretes. This page lists all eight emergency discretes, and the title of the checklist page that each was bound to using the DEU utility software.
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MFD Displays ı NOT CRS SELECT ANNUNCIATION CRS 340 23 36.7 NM N 3 33 ARC COMPASS CARD V O R 1 AUTO TILT ANNUNCIATOR 90 ° OFF SCALE HEADING BUG READOUT 40 ARL WXA A 2.2 ANT FLT VOR 1 36.7 NM TO/FROM POINTER 243 KT 0:09 ADF 2 COURSE DEVIATION BAR COURSE DEVIATION SCALE Figure 4.4.1 MFD ARC COMPASS + WX SYMBOL DEFINITION Issued 4/95 SW 06/07/08/11 4.4.
MFD Displays TRACK LINE LOCATION ANNUNCIATION ı SELECTED RANGE L 25 40 TRACK LINE RANGE RINGS RADAR MODE 20 STBY 2 .2 TILT ANGLE SYMBOLIC AIRCRAFT Figure 4.4.2 MFD WEATHER ONLY DISPLAY Issued 4/95 SW 06/07/08/11 4.4.
MFD Displays ı PROFILE ANGLE PROFILE R 42 +30 0 SYMBOLIC AIRCRAFT 5 WX ALTITUDE LINES -30 10 15 20 WEATHER MODE RANGE RINGS Figure 4.4.3 MFD VP DISPLAY Issued 4/95 SW 06/07/08/11 4.4.
MFD Displays TRACK LINE (INDICATES AZIMUTH OF VERTICAL SLICE) ı L12 TRACK LINE LOCATION TILT LINE (INDICATES TILT OF HORIZONTAL SLICE) 40 30 20 10 SYMBOLIC AIRCRAFT -20 WXA ↑ 10 ANT FLT +60 0 10 20 30 40 -60 ALTITUDE LINES Figure 4.4.4 MFD SPLIT SCREEN DISPLAY (NOTE: SW 11 and later) Issued 4/95 SW 06/07/08/11 4.4.
MFD Displays TRUE NORTH ANNUNCIATION PLAN VIEW MODE ANNUNCIATION ı LNAV MESSAGE ANNUNCIATION PLAN “NORTH-UP” ANNUNCIATION T N CENTER OF MAP DISPLAY MSG PRIMARY NAVIGATION SOURCE F M S 5 FULL SCALE RANGE RING IXDA WAYPOINT SYMBOL OJC HALF SCALE RANGE RING FLIGHT PLAN DESIRED TRACK LINE AIRPORT SYMBOL SYMBOLIC AIRCRAFT (PRESENT POSITION) VORTAC SYMBOL Figure 4.4.5 MFD PLAN VIEW DISPLAY Issued 4/95 SW 06/07/08/11 4.4.
MFD Displays NO BEARING INTRUDERS ı 2 NM RANGE RING RA0.8NM/+01 TA5.7NM/-06 -05 -03 DISPLAY MODE T C A S PROXIMATE INTRUDER +02 TA INTRUDER -01 RA INTRUDER (TCAS II ONLY) 10 TCAS RANGE OTHER TRAFFIC TA/RA FLABV ACTUAL/RELATIVE ALTITUDE SELECTION TCAS MODE SELECTION (TA/RA - TCAS II ONLY) ABOVE/NORM/BELOW ALTITUDE SELECTION Figure 4.4.6 TCAS ONLY DISPLAY Issued 4/95 SW 06/07/08/11 4.4.
MFD Displays USER CREATED GENERAL USE LINES FIXED TEXT LINES (YELLOW) USER CAN NOT CHANGE TST/REF BUTTON BRINGS UP HELP PAGE CHECKED OFF INDEX ENTRY PARTIALLY CHECKED OFF INDEX ENTRY ı TITLE CREATOR/VERSION DATA LINE USER/INSTALLER IS RESPONSIBLE FOR THE CHECKLIST CONTENTS TST/REF-HELP ✓ EMERGENCY PROCEDURES * NORMAL PROCEDURES ➩ ABNORMAL PROCEDURES OTHER PROCEDURES NOTE PAGES CLEAR ALL CHECKED ITEMS CURSOR LOCATION Figure 4.4.7 MFD CHECKLIST ROOT INDEX PAGE DEFINITION Issued 4/95 SW 06/07/08/11 4.
MFD Displays ı TAXI CHECK BRAKES CHECK FLIGHT INSTRUMENTS SET NAV EQUIPMENT ELECTRICAL POWER CHECK MONITOR CHECK 5. ENGINE INSTRUMENTS 6. THRUST REVERSERS CHECK AND STOWED ANTI ICE SYSTEMS 7. CHECK AS REQD ✓ 1. ✓ 2. ✓ 3. ➩ 4. Figure 4.4.8 MFD CHECKLIST SAMPLE PAGE Issued 4/95 SW 06/07/08/11 4.4.
Operating Instructions OPERATING INSTRUCTIONS Consult Aircraft Flight Manual Supplement for specific procedures and limitations in operation. PREFLIGHT PROCEDURES should be serviced. Refer to figure 5.1 and 5.2, Self Test annunciation. Additionally, the pilot should ensure that the compass scale is white, which indicates that all three colors are operational in the display unit.
Operating Instructions mary NAV sensor with the NAV source select push button. Set the desired course and heading, and check that the appropriate display is present on the indicator. Set the desired NAV frequencies for the departure phase of the flight. Then press the appropriate push buttons (HSI, ARC, BEARING #1, BEARING #2, etc.) on the EFS 50 control panel for the desired display presentation. heading bug under the lubber line (pull SYNC knob).
Operating Instructions Pointer #1 to the desired #1 bearing source. Using CRS knob, select desired course TO or FROM the waypoint (for the on-side LNAV only). The course deviation bar on the EHSI now provides guidance in flying the selected course. Waypoint passage is indicated by the TOFROM indicator and waypoint BEARING pointer reversal.
Operating Instructions ◗ ADF APPROACH After selecting ADF mode and tuning ADF #1 receiver to the desired NDB, set Bearing pointer #1 to ADF which will be used for primary navigation. Using CRS control, select desired course TO or FROM the NDB. The course deviation bar on the EHSI now provides left-right guidance in flying the selected course as it would in flying a VOR course. This eliminates the mental calculations required while tracking an NDB course in the conventional manner.
Operating Instructions LIMITATIONS For information on EFS 50 system operating limitations please refer to the approved Flight Manual Supplement for the particular aircraft in question, if one is provided. EMERGENCY PROCEDURES For information on EFS 50 system emergency procedures please refer to the approved Flight Manual Supplement for the particular aircraft in question, if one is provided. Issued 4/95 SW 06/07/08/11 5.
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Operating Instructions 1 360 HDG 33 W 30 SG E RCP 24 SELF TEST PASS S 21 ADF 1 12 1 CHECK CONFIG 3 6 T S T N 15 CRS DUSG VOR 2 --- NM Figure 5.1 EHSI SELF TEST Issued 4/95 SW 06/07/08/11 5.
Operating Instructions 1 --RA CHECK CONFIG ATTITUDE FAIL ATT T S T FD HDG SELF TEST PASS HDG 1 CP DU SG SG CRS 360 HDG 360 DH OFF Figure 5.2 EADI SELF TEST Issued 4/95 SW 06/07/08/11 5.
Fault Annunciations FAULT ANNUNCIATIONS GENERAL EXTERNAL SYSTEM FAILURES ◗ HEADING system is inhibited. Refer to Figure 6.2 and 6.3. Once a heading failure is detected, the EHSI lubber line and course pointer head and tail are removed. The lubber line is replaced by a RED box with a RED HDG inside it. The course deviation scale is frozen horizontally to perform the function of a conventional CDI. Selected course reference is provided by the alphanumeric CRS readout in the upper left corner.
Fault Annunciations the Symbol Generator. Once annunciated, the Symbol Generator will continue to operate for at least 30 minutes if the rated ambient temperature is not exceeded. To extend the operating time, reduce display information and brightness to a minimum. Refer to Figure 6.1 and 6.3. ◗ CP—CONTROL PANEL (CP 467 OR CP 469/A) A RED CP enclosed by a RED box is annunciated left center of the EHSI and lower left of the EADI if a control panel switch becomes stuck for greater than 10 seconds.
Fault Annunciations ◗ SG—SYMBOL GENERATOR A RED SG enclosed by a RED box is annunciated at the upper left center of the EHSI or lower left of the EADI if certain monitored functions are detected invalid. If the RED SG annunciation is encountered extreme caution should be used to validate any data used on the display for navigation. Even after validation and revalidation the data should only be used as supplementary information.
Fault Annunciations will be placed in the data field. Refer to Figure 6.3. ◗ CHECK CONFIG A yellow “CHECK CONFIG” message will display in the upper right corner of the EHSI and EADI whenever the system configuration memory in the symbol generator and aircraft installation rack do not match. Test routines resident in the symbol generator select the best possible system configuration to use, however, the selected configuration may not be the intended one.
Fault Annunciations ❏ Installation with an RDS 81, RDS 82 or RDS 82VP with software 07 or later, “RANGE” will annunciate when the 5 NM, 320 NM or 1000 NM range is selected. ❏ Installation with software 06 “WX FLT” (weather fault) will annunciate when the 5 NM or 320 NM range is selected. These annunciations alert the pilot of a range mismatch because the RDS 81, RDS 82 and RDS 82VP do not support these radar ranges.
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Fault Annunciations ı 360 ---NM N SG W RCP CP S 21 ADF1 12 24 E 1 3 6 L O C 30 33 DU SG 15 CRS 045° VOR 2 16.3 NM Figure 6.1 EHSI FAULT ANNUNCIATION Issued 4/95 SW 06/07/08/11 6.
Fault Annunciations ı 360 HDG W E 24 12 21 ADF 1 S 1 6 L O C DME1 11. 5 3 30 33 N ---NM 15 CRS 045° VOR 2 16.3 NM Figure 6.2 EHSI FAULT ANNUNCIATION Issued 4/95 SW 06/07/08/11 6.
Fault Annunciations ı AP YD SR HB CWS 12555 K T NAV APR 20 VNAV --ALT RA GS CHECK CONFIG 20 ATTITUDE FAIL F 10 TEST 10 FD G S HDG N 3 6 T A N S DME1 CP DU SG SG 10 10 20 20 LOC DH 200 Figure 6.3 EADI FAULTS Issued 4/95 SW 06/07/08/11 6.
REVERSIONARY Modes REVERSIONARY MODES The EFS 50 provides four different reversionary modes of operation in the event of a system component failure; composite, display down and SG 3. The reversionary modes offered in a particular aircraft will vary depending on EFIS system configuration, installation wiring and certification. The following section describes the various reversionary modes offered. Issued 4/95 All external switches and placards are part of the installation supplied by the installer.
REVERSIONARY Modes CMPST - COMPOSITE Refer to Figure 7.1 , COMPOSITE MODE SELECTION. CMPST (composite) is generally used to compensate for a failure of a display unit or the EADI section of the symbol generator. A single switch input to the SG 465 instructs the symbol generator to output the CMPST display on the EADI and EHSI. See section 4.3 for details on the composite display.
REVERSIONARY Modes DISPLAY (EADI) DOWN Refer to Figure 7.2, EADI DOWN MODE SELECTION. DISPLAY (ADI) DOWN mode selection is generally used to compensate for a failure of the EADI display unit or section of the symbol generator. Available for use in two, three, four and five-tube installations. The DISPLAY DOWN mode will allow the pilot or copilot to transfer the normal EADI display to the EHSI below the failed EADI and transfer the EHSI display to the MFD if one is installed.
REVERSIONARY Modes SG 3 Refer to Figure 7.3 PILOT STBY MODE SELECTION. SG 3 mode selection is generally used to compensate for a failed pilot’s or copilot’s symbol generator. The SG 3 mode selection will allow the pilot or copilot to substitute the MFD symbol generator for his onside symbol generator. A single momentary switch input removes the failed onside symbol generator drive from the EADI and EHSI and transfers the MFD display drive to the onside EADI and EHSI.
Glossary GLOSSARY ABBREVIATIONS ABV ADF ADS ADI AHRS AHS AN ANT ARINC ATR ATT AZ BAZ BC BLW BRG BRT CCP` CDI Above Automatic Direction Finder Air Data System Attitude Director Indicator Attitude Heading Reference System Attitude Heading System Angle Antenna Aeronautical Radio INCorporated Air Transport Radio Attitude Azimuth Back Azimuth Back Course Below Bearing Bright Checklist Control Panel Course Deviation Indicator or Course Deviation Information CDU Control Display Unit CONFIG Configuration CP Contro
Glossary FPL FR FT GP GPS GS HDG HSI ICAO ID ILS IRU KTS LMT LNAV LOR MLS NAV NM OBI OMG RA RCP REF RMI RNAV SG SN STB STBY SW SYNC TA TACAN TCAS TCN TD TST TTS TTW TX VNAV VOR VORTAC VP WX WXA 8.
Index INDEX A ADF ADF 1 1.6, 1.10, 1.14, 2.1.6-7, 5.2, 5.4 ADF 2 1.6, 1.10, 1.14, 2.1.7 ALPHANUMERIC READOUT ANNUNCIATIONS 6.3 AN I.1, 1.1, 1.3, 2.1.3-10, 2.2.1, 2.3.1, 2.3.3, 2.3.6, 2.4.1-6, 4.1.1-2, 4-20, 4.2.1-3, 4.2.5-6, 4.2.8-12, 4.3.1-3, 4.4.1-3, 5, 7-8, 11-14, 5.2-4, 6.1, 6.4-5, 8.1 ANT FLT 6.4 APPROACH PROCEDURES 5.3 ARC ARC NAV MAP 2.1.4 ARC SECTORED MODE SELECTION 2.1.3 ATT 1.8, 1.13, 1.16, 4.2.10, 4.2.12, 8.1 ATTITUDE 1.6, 1.10, 1.14, 4.1.1, 4.2.1-2, 4.2.6, 4.2.10, 4.2.12, 6.1, 6.5, 8.
Index CRS KNOB 2.4.4, 4.1.4, 4.4.1, 4.4.15, 5.3-4 CP 466A I.1, 1.1, 2.1.1, 2.3.3, 2.3.6 CP 466B I.1, 1.2, 2.3.3, 2.3.6 CP 468 2.1.1, 2.1.10, 2.4.2 CP 469A I.1, 1.1, 2.4.1, 2.4.5-6, 4.4.3, 4.4.8-9, 4.4.11-13, 6.2 D DETAILED OPERATING CONTROLS 2.1.1, 2.2.1 DG 1.8, 1.12, 1.16, 2.1.3, 4.1.1, 8.1 DIRECT TO 1.3, 2.1.10, 5.2 DISPLAY BRIGHTNESS CONTROL 2.1.10, 2.2.1 DISTANCE, GROUNDSPEED AND TIME-TO-STATION 4.1.5 DME DME HOLD 4.1.6-8, 4.3.1, 4.3.3, 5.3 DRIFT ANGLE POINTER 4.1.2, 4.1.12 DTK 2.4.4, 4.1.3-4, 5.3-4, 6.
Index HEADING SYNC 2.1.10 HSI 2.1.3, 2.4.2, 2.4.4, 4.1.15, 4.2.7, 4.2.9-10, 4.4.14, 5.2, 8.2 I ILS ILS APPROACH 4.1.4, 5.3 IN-FLIGHT OPERATION 5.2 K KNS 81 2.4.4 L LATERAL COURSE LATERAL COURSE DEVIATION BAR 4.1.5, 4.3.2 LATERAL COURSE DEVIATION SCALE 4.1.4, 4.3.2 LIGHTNING LIGHTNING DETECTION 4.1.17 LIMITATIONS 5.1, 5 LNAV LNAV MAP 2.1.8-9, 2.4.2, 2.4.4, 4.1.18-19 LOC 4.1.14, 4.2.6-7, 4.2.12, 5.3 LOR 2.1.6, 4.1.9, 4.1.12, 8.2 M MAGNETIC MAG 4.1.9-10 MAG VAR 4.1.9-10 MAP 360 MAP DISPLAYS 4.1.
Index N NAV 1-2 NAVIGATION SYSTEM SELECT 2.1.6 NAV CDI MAP 2.1.3 NAV MAP 2.1.3-4, 2.1.7, 2.1.9, 2.4.4, 4.1.4, 4.1.15-16, 4.4.2, 5.3 NAV NAVIGATION SENSOR SELECT 2.1.4 NAVIGATION SOURCE ANNUNCIATION 4.1.2, 4.3.2 NDB 4.1.10, 5.2, 4 O OFF 2.2.2, 2.3.4, 2.3.6, 2.4.3-4, 2.4.6, 4.1.10, 4.1.13, 4.1.15-16, 4.1.18-19, 4.2.3, 4.2.6, 4.4.2, 4.4.9-10, 4.4.12-14, 5.1, 6.4 OFF-STBY-TST-ON 2.3.4 OMG 2.1.6, 4.1.9, 4.1.12, 8.2 ON I.1-2, 1.1, 1.3, 1.6, 1.8, 1.10, 1.12, 1.14, 1.16, 2.1.2-8, 2.1.10, 2.2.1, 2.3.3-6, 2.4.1-6, 4.
Index ROLL 1.8, 1.13, 1.16, 4.2.1-4, 4.2.12, 4.3.1, 6.1, 6.4 S SELECTED COURSE 2.1.5, 2.1.10, 2.4.4, 4.1.3-5, 4.1.11-14, 4.2.6, 4.2.8, 4.3.1-2, 4.4.1, 5.2-4, 6.1 SELF TEST 2.1.8, 2.2.2, 5.1 SN 8.2 SOFTWARE SOFTWARE 06 1.6, 2.1.8-9, 2.4.2-3, 4.2.3, 4.2.9-10, 6.5 SOFTWARE 07 1.10, 2.1.7, 2.4.2, 4.1.6, 5.1, 6.4 SOFTWARE 08 1.14, 2.1.6-8, 2.4.1-3, 2.4.5, 4.1.5-7, 4.1.11, 4.2.8, 4.4.3, 4.4.8 SOFTWARE 11 1.18, 2.3.6, 4.1.4-5,4.1.11, 4.2.13, 4.3.3, 4.4.20 STAB OFF 2.3.6, 6.4 STANDARD EHSI DISPLAYS 4.1.1, 4.1.
Index TST 2.1.8-9, 2.2.2, 2.3.4, 2.4.6, 4.4.3, 4.4.15, 5.1, 8.2 TST/REF SELF TEST 2.1.8, 2.2.2, 5.1 TX FLT 6.4 V VN 4.1.11, 4.2.8, 6.3 VNAV 1.7, 1.11, 1.15, 1.17, 4.1.10-11, 4.2.3, 4.2.7-8, 5.3, 8.2 VOR VOR APPROACH 5.4 VERTICAL PROFILE VP 2.3.2-3, 2.3.5-6, 4.4.1-2, 6.4-5, 8.2 W WAIT 2.3.5, 6.5 WEATHER WEATHER RADAR ANNUNCIATIONS 6.4 WX 2.1.8, 2.3.4-5, 4.1.16-17, 6.4-5, 8.2 WX FLT 2.1.8, 4.1.17, 6.4-5 WXA 2.3.4-5, 4.1.17, 8.2 WIND VECTOR WIND VECTOR INFORMATION 4.1.12 9.
Pilot’s Guide EFS 50 5-inch Electronic Flight Instrumentation System B AlliedSignal General Aviation Avionics 400 North Rogers Road Olathe, Kansas 66062-1212 TELEX 669916 KINGRAD FAX 913-791-1302 TELEPHONE (913) 768-3000 ©1995 AlliedSignal Inc. 4/95 006-08485-0000 1K PRINTED IN THE U.S.A.
