Page 2 Business and Commuter Aviation Systems Honeywell Inc. Box 29000 Phoenix, Arizona 85038--9000 U.S.A. SPZ--8000 Digital Integrated Flight Control System for the Challenger CL 601--3A/3R Pilot’s Manual Revised September 1999 Printed in U.S.A. Pub. No. A28--1146--055--02 Apr 1988...
Page 3 Honeywell Inc. Neither this document nor the information contained herein shall be used, reproduced, or disclosed to others without the written authorization of Honeywell Inc., except to the extent required for installation or maintenance of recipient’s equipment. NOTICE -- FREEDOM OF INFORMATION ACT (5 USC 552) AND...
Page 4 Upon receipt of a revision, insert the latest revised pages and dispose of superseded pages. Enter revision number and date, insertion date, and the incorporator’s initials on this Record of Revisions. The typed initials HI are used when Honeywell Inc. is the incorporator of the revision. Revision...
Page 5 SPZ--8000 Digital Integrated Flight Control System Record of Temporary Revisions Upon receipt of a temporary revision, insert the yellow temporary revision pages according to the filing instructions on each page. Then, enter the temporary revision number, issue date, and insertion date on this page.
Page 6 SPZ--8000 Digital Integrated Flight Control System List of Effective Pages Original Apr 1988 Revision Oct 1991 Revision Sep 1999 Subheading and Page Revision Subheading and Page Revision Title Page 2--3 2--4 Record of Revisions 2--5 RR--1/RR--2 2--6 2--7 Record of Temporary Revisions 2--8 RTR--1/RTR--2 2--9...
Page 7 SPZ--8000 Digital Integrated Flight Control System Subheading and Page Revision Subheading and Page Revision Electronic Flight Instrument System 4--65 (EFIS) (cont) 4--66 4--18 4--67/4--68 4--19 4--20 Multifunction Display (MFD) System 4--21 5--1 4--22 5--2 4--23 5--3 4--24 5--4 4--25 5--5 4--26 5--6 4--27...
Page 8 9--4 8--12 9--5 8--13 9--6 9--7 8--14 8--15 9--8 8--16 9--9 8--17 9--10 8--18 9--11/9--12 8--19 9--13/9--14 8--20 Honeywell Product Support 8--21 10--1 8--22 10--2 8--23 10--3 8--24 10--4 8--25 8--26 Acronyms and Abbreviations 8--27 11--1 8--28 11--2 8--29 11--3...
Page 9 SPZ--8000 Digital Integrated Flight Control System Subheading and Page Revision Subheading and Page Revision Appendix A Appendix D A--1 D--1 A--2 D--2 A--3 D--3 A--4 D--4 A--5 D--5/D--6 A--6 Index A--7 Index--1 A--8 Index--2 A--9 Index--3 A--10 Index--4 Appendix B Index--5 B--1 Index--6...
Page 10: Table Of Contents
SPZ--8000 Digital Integrated Flight Control System Table of Contents Section Page 1. INTRODUCTION ......2.
Page 11 SPZ--8000 Digital Integrated Flight Control System Table of Contents (cont) Section Page 4. ELECTRONIC FLIGHT INSTRUMENT SYSTEM (EFIS) ( CONT Typical EADI Display Presentations ... . . 4-15 Takeoff Using Go--Around Mode .
Page 12 SPZ--8000 Digital Integrated Flight Control System Table of Contents (cont) Section Page 5. MULTIFUNCTION DISPLAY (MFD) SYSTEM . . . MFD System Information ..... . MFD Controller .
Page 13 SPZ--8000 Digital Integrated Flight Control System Table of Contents (cont) Section Page 7. SYSTEM LIMITS ( CONT VOR After Over station Sensor 1/2 (AOSS 1/2) ......System Performance/Operating Limits .
Page 14 SPZ--8000 Digital Integrated Flight Control System Table of Contents (cont) Section Page 10. HONEYWELL PRODUCT SUPPORT ..10-1 Publication Ordering Information ....
Page 15 SPZ--8000 Digital Integrated Flight Control System Table of Contents (cont) Section Page C--1 PRIMUS 870 WEATHER RADAR ... . . C--1 Introduction ....... . . C--1 Description .
Page 16 SPZ--8000 Digital Integrated Flight Control System Table of Contents (cont) List of Illustrations Figure Page 1--1 Challenger CL--601--3A Cockpit ....2--1 SPZ--8000 DIFCS Block Diagram .
Page 17 SPZ--8000 Digital Integrated Flight Control System Table of Contents (cont) List of Illustrations (cont) Figure Page 4--26 Flight Director Failure Flag ....4-33 4--27 Airspeed, Altitude Preselect, Cross--Side Data, Glideslope, Radio Altitude and Localizer...
Page 18 SPZ--8000 Digital Integrated Flight Control System Table of Contents (cont) List of Illustrations (cont) Figure Page 5--7 MFD MAP Mode With Airport Data ... . . 5-12 5--8 MFD PLAN Mode Display .
Page 19 SPZ--8000 Digital Integrated Flight Control System Table of Contents (cont) List of Illustrations (cont) Figure Page 8--21 Back Course Mode Intercept ....8-26 8--22 Back Course Mode Tracking Cockpit Displays .
Page 20 SPZ--8000 Digital Integrated Flight Control System Table of Contents (cont) List of Illustrations (cont) Figure Page B--5 Maximum Permissible Exposure Level Boundary . . . B--14 C--1 Weather Radar Controller ..... C--3 C--2 EFIS Test Pattern (Typical) 120_ Scan Shown .
Page 21 SPZ--8000 Digital Integrated Flight Control System Table of Contents (cont) List of Tables (cont) Table Page 6--1 SAT/TAT/TAS Message Format ....6--2 Lateral and Vertical Armed Mode Annunciators .
Page 22: Introduction
SPZ--8000 Digital Integrated Flight Control System Introduction This manual describes the operation, components, typical flight applications, and operating procedures for the Honeywell SPZ--8000 Digital Integrated Flight Control System (DIFCS) as factory installed in the CANADAIR Challenger CL--601--3A and CL--601--3R aircraft.
Page 23 SPZ--8000 Digital Integrated Flight Control System Equipment covered in this manual is listed in table 1--1. Model Unit Part No. Cockpit Mounted ED--800 Electronic Display 7003110--901 or --931 (Civil Aviation Authority) DC--810 DC--810 7005819--707 RI--815 Instrument Remote 7011345--902 or --912 Controller MC--800 MFD Controller 7007062--921...
Page 24 SPZ--8000 Digital Integrated Flight Control System Model Unit Part No. Remote Mounted SG--815 Symbol Generator (SG) 7011674--VAR MG--815 MFD Symbol Generator 7011675--VAR FZ--800 Flight Guidance Computer 7003974--VAR (FGC) AZ--810 Digital Air Data Computer 7003974--VAR (DADC) RT--300 Radio Altimeter Receiver 7001840--912 Transmitter (RT) SM--600 Servo 4015373--813 or 816...
Page 25 SPZ--8000 Digital Integrated Flight Control System Model Unit Part No. Optional SG--815 Symbol Generator (With 7011674--VAR TCAS) (Optional) MG--815 MFD Symbol Generator 7011675--VAR (with TCAS) LU--850 LSS Controller (Optional) 7011865--90X LP--850 LSS Procesor (Optional) 7011822--9XX AT--850 LSS Antenna (Teardrop) 4057697--901 (Optional) AT--855 LSS Antenna (Brick)
Page 26: Figure
SPZ--8000 Digital Integrated Flight Control System Challenger CL--601--3A Cockpit Figure 1--1 A28--1146--055 Introduction REV 2 1-5/(1-6 blank)
Page 27: System Description
SPZ--8000 Digital Integrated Flight Control System System Description The SPZ--8000 Digital Integrated Flight Control System, shown in block diagram form in Figure 2--1, includes the following subsystems: STANDARD Air data system Electronic flight instrument system Multifunction display system Dual flight guidance system Flight management system Radio altimeter system PRIMUS...
Page 28 SPZ--8000 Digital Integrated Flight Control System The system data communication is split between the main ASCB system bus and private--line paths that transmit sensitive data required for fault isolation. These specific private--line paths include the following: IRS attitude and heading to EFIS and position to FMS DADC Mach/airspeed to the Mach/airspeed indicator (analog) and to EFIS DADC vertical speed to VSI...
Page 29: Air Data System (Ads)
SPZ--8000 Digital Integrated Flight Control System Pitch and roll steering commands developed by the flight guidance computer in conjunction with the flight guidance controller are displayed as steering pointers that direct the pilot to reach and/or maintain the desired flightpath or attitude. With very few exceptions, most of this system is powered from 28 V dc.
Page 30: Electronic Flight Instrument System (Efis)
SPZ--8000 Digital Integrated Flight Control System ELECTRONIC FLIGHT INSTRUMENT SYSTEM (EFIS) The EFIS consists of the following components: Electronic displays (EADI and electronic horizontal situation indicator (EHSI)) Symbol generator Display controller Instrument remote controller. The EFIS displays the following: Pitch and roll attitude Heading Course orientation Flightpath commands...
Page 31: Multifunction Display System (Mfd)
SPZ--8000 Digital Integrated Flight Control System MULTIFUNCTION DISPLAY SYSTEM (MFD) The MFD system consists of the following components: MFD symbol generator MFD controller Electronic display. The MFD system displays normal and emergency checklists, navigation maps, TCAS data (optional), and weather radar. In addition, the MFD symbol generator backs up the EFIS symbol generator and EHSI displays.
Page 32: Flight Management System (Fms)
SPZ--8000 Digital Integrated Flight Control System The FGS has redundant flight control functions that make it fail--operational. It uses redundancy management techniques and sensor voting to evaluate the information from dual attitude/heading and air data sensors. The fail--operational characteristic includes sensor failures.
Page 33: Radio Altimeter System
RADIO ALTIMETER SYSTEM The radio altimeter system consists of the following components: Radio altimeter receiver/transmitter Antennas (not supplied by Honeywell). The radio altimeter system displays the following: An absolute altitude from 0 to 2500 feet Decision height (DH) selection Failure annunciator Internal self--test information.
Page 34: Primusr
SPZ--8000 Digital Integrated Flight Control System PRIMUS 650 WEATHER RADAR SYSTEM The PRIMUS 650 Weather Radar System consists of the following components: Weather radar receiver transmitter antenna Weather radar controllers (one or two). A brief operational description is included in Appendix B. The PRIMUS 650 Weather Radar System is an X--band radar designed for weather detection and analysis.
Page 35: Laserefr
SPZ--8000 Digital Integrated Flight Control System The radar can also be used for ground mapping. In the ground mapping mode, prominent landmarks are displayed that the crew can use to identify coastline, hilly or mountainous regions, cities, or large structures. The reflected signals from various ground surfaces are displayed as magenta, yellow, or cyan (most to least reflective).
Page 36: Lightning Sensor System (Lss) (Optional)
SPZ--8000 Digital Integrated Flight Control System LIGHTNING SENSOR SYSTEM (LSS) (Optional) The LSS consists of the following: Controller Processor Antenna. The LSS is used to locate areas of lightning activity in a 100--nautical mile radius around the aircraft. The lightning information is displayed on the EHSI or MFD.
Page 37: Other Switches And Controls
SPZ--8000 Digital Integrated Flight Control System OTHER SWITCHES AND CONTROLS Autopilot Disconnect Switches The autopilot disconnect switches are mounted on the control wheel. When an autopilot disconnect switch is pushed, the autopilot is disconnected. Touch Control Steering (TCS) When the TCS button is pushed, the crew can manually change aircraft attitude, altitude, and/or vertical speed without disengaging the autopilot.
Page 38: Spz--8000 Difcs Block Diagram
SPZ--8000 Digital Integrated Flight Control System AD--11495--R14@ SPZ--8000 DIFCS Block Diagram Figure 2--1 A28--1146--055 System Description REV 2 2-13/(2-14 blank)
Page 39: Air Data System (Ads)
SPZ--8000 Digital Integrated Flight Control System Air Data System (ADS) The cockpit locations of the ADS controls and indicators are shown in Figure 3--1. PUSH PUSH PUSH PUSH PUSH SYNC SYNC MACH INSTRUMENT REMOTE INSTRUMENT REMOTE CONTROLLER CONTROLLER MACH/AIR SPEED INDICATOR (M/IAS) IN HG 29 9 2...
Page 40: Mach/Airspeed Indicator
SPZ--8000 Digital Integrated Flight Control System MACH/AIRSPEED INDICATOR The Mach/airspeed indicator is shown in Figure 3--2. AD--58050@ Mach/Airspeed Indicator Figure 3--2 The Mach/airspeed indicator has the following features: Pointer display of computed airspeed in knots (white pointer) Pointer display of maximum allowable airspeed (V ) in knots (striped pointer) Counter drum display of Mach...
Page 41: Barometric Altimeter
SPZ--8000 Digital Integrated Flight Control System Failure conditions for the Mach/airspeed indicator and the resulting flags are explained in Table 3--1. Flag Failure Condition Displayed Absence of primary instrument power Internal power supply failure Loss of reference voltage Excessive indicated airspeed (IAS) servo null signal Absence of external IAS data valid signal Excessive V servo null signal...
Page 42 SPZ--8000 Digital Integrated Flight Control System The barometric altimeter has the following features: Counter drum display of barometrically corrected pressure altitude from the DADC, marked in 20--foot increments. Pointer display of altitude between 1000--foot levels with 20--foot graduations. Black--and--white crosshatch in the left--hand digit position of the counter display for altitudes below 10,000 feet.
Page 43: Vertical Speed Indicator (Vsi)
SPZ--8000 Digital Integrated Flight Control System VERTICAL SPEED INDICATOR (VSI) The VSI is shown in Figure 3--4. 1 2 4 VERTICAL SPEED DOWN 1000 FT PER AD--58052@ Vertical Speed Indicator Figure 3--4 The VSI is a servoed pointer display of vertical speed information from the DADC.
Page 44: Digital Air Data Computer (Dadc) Self--Test Mode
SPZ--8000 Digital Integrated Flight Control System DIGITAL AIR DATA COMPUTER (DADC) SELF--TEST MODE The digital air data computer (DADC) incorporates a self--test mode that is activated with a cockpit test switch. The DADC outputs static test data that is displayed on the altimeter, vertical speed indicator, Mach/airspeed indicator and EFIS.
Page 45: Air Data Display Parameters
SPZ--8000 Digital Integrated Flight Control System AIR DATA DISPLAY PARAMETERS Table 3--3 gives the units of measure and range of the air data information that is displayed on the EFIS. Parameter Units Data Pressure altitude --1000 to 60,000 Baro corrected altItude --1000 to 60,000 Altitude rate ft/min...
Page 46: (Efis)
SPZ--8000 Digital Integrated Flight Control System Electronic Flight Instrument System (EFIS) Figure 4--1 shows the cockpit locations of the EFIS components. AUTO CB TEST ANTI--ICE ENV. CONT FAIL MLG BAY ANTI--SKID OVHT FAIL RECALL 10 CHANNEL SYSTEM ANNUNCIATOR PANEL PUSH PUSH PUSH PUSH...
Page 47: Electronic Display Controls
SPZ--8000 Digital Integrated Flight Control System ELECTRONIC DISPLAY CONTROLS Display Controller The display controller, shown in Figure 4--2, controls the EFIS display format. AD--58055@ Display Controller Figure 4--2 The display controller functions are described in the following paragraphs. FULL/ARC Button -- The FULL/ARC button changes the EHSI display from full--compass to partial--compass format.
Page 48 SPZ--8000 Digital Integrated Flight Control System GSPD/TTG (Groundspeed/Time--To--Go) Button -- GSPD/TTG is displayed in the lower right corner of the EHSI. Pushing the GSPD/TTG button toggles the display between GSPD and TTG. ET (Elapsed Time) Button -- Pushing the ET button displays elapsed time in place of the GS/TTG display.
Page 49 SPZ--8000 Digital Integrated Flight Control System BRG (Bearing) Source Select Knobs -- The EHSI can display two independent bearing pointers. The rotary knob is used to select the NAV sources as described in Table 4--1. BRG f f f f BRG Z Z Z Z VOR 1 VOR 2...
Page 50: Instrument Remote Controllers
SPZ--8000 Digital Integrated Flight Control System Instrument Remote Controllers The instrument remote controllers, shown in Figure 4--3, are used to select heading, course, altitude preselect (copilot only), and indicated airspeed or Mach references (pilot only). AD--58057@ AD--58056@ Instrument Remote Controllers Figure 4--3 The function of each control on the pilot’s and copilot’s controller is described in the following paragraphs.
Page 51: Electronic Attitude Director Indicator (Eadi)
SPZ--8000 Digital Integrated Flight Control System Pilot’s IAS/MACH Knob and PUSH CHG Button -- The IAS/MACH knob is used to set the IAS or MACH reference speed (displayed on the EADI) for the flight director flight level change (FLC) mode. The power--up value for selected speed is 80 kts IAS. Pushing the PUSH CHG button toggles the display between IAS and MACH.
Page 52: Eadi Displays And Annunciators
SPZ--8000 Digital Integrated Flight Control System VERTICAL CAPTURE (GREEN) LATERAL ARM (WHITE) ASEL VPATH VERTICAL ARM ROLL (WHITE) VFLC FLIGHT DIRECTOR ATTITUDE MODE ANNUNCIATORS POINTER VASL DECISION VALT FD COUPLE ROLL HEIGHT AUTOPILOT ENGAGE ARROW SCALE ANNUNCIATOR ANNUNCIATOR MARKER BEACON MARKER BEACON ANNUNCIATOR OM (BLUE)
Page 53: Eadi Displays And Annunciators
SPZ--8000 Digital Integrated Flight Control System EADI Displays and Annunciators The following paragraphs describe the symbols displayed on the EADI in Figure 4--5. Decision Height Display and Annunciator -- Decision height is displayed in the lower right corner of the EADI. The range is from 20 to 990 feet in 10--foot increments.
Page 54 SPZ--8000 Digital Integrated Flight Control System Mode Transition Flashing Annunciator Vertical Modes ASEL arm to ASEL capture ASEL Glideslope (GS) arm to GS capture VPTH capture to VALT VALT VPTH capture to VFLC VFLC Flashing Annunciator for Flight Director Mode Transitions Table 4--2 Flight Director Couple Arrow -- The direction that the couple arrow is pointing indicates the EHSI and DADC that are coupled to the...
Page 55 SPZ--8000 Digital Integrated Flight Control System Marker Beacon -- Marker beacon information is displayed in the upper right corner of the EADI. The marker annunciators are for outer marker, for middle marker, and IM (white) for inner marker. Altitude Preselect Display -- The five--digit display indicates the altitude from 0 to 60,000 feet that is selected using the ALT SEL knob on the copilot’s instrument remote controller.
Page 56 SPZ--8000 Digital Integrated Flight Control System Radio Altitude Display -- The radio altitude is displayed in green in the lower right--hand corner of the EADI and indicates radio altitude from 0 to 2500 feet. The radio altitude display resolution is described in Table 4--4.
Page 57 SPZ--8000 Digital Integrated Flight Control System Mach Display -- When in flight, the Mach readout is displayed at Mach 0.45 and it is removed at Mach 0.40. Resolution is Mach 0.002. The color of the Mach display is described in Table 4--5. Mach Display Color Condition Green...
Page 58 SPZ--8000 Digital Integrated Flight Control System The color of the IAS display is described in Table 4--6. IAS Display Condition Color Green The on--side DADC data is selected for display. IAS is above V Amber The FMS over/under speed monitor is exceeded.
Page 59: Typical Eadi Display Presentations
SPZ--8000 Digital Integrated Flight Control System TYPICAL EADI DISPLAY PRESENTATIONS The following figures show EADI displays that the pilot typically sees during various flight phases. These examples do not show all display formats or configurations. Takeoff Using Go--Around Mode Figure 4--6 shows a display with the aircraft at the end of the runway ready for takeoff.
Page 60: Climb To Initial Altitude
SPZ--8000 Digital Integrated Flight Control System Climb to Initial Altitude Figure 4--7 shows a display with the aircraft on climbout at 200 kts in heading (HDG) and pitch attitude hold mode (not annunciated) with the autopilot (AP) engaged. The flight director commands are satisfied. AD--58059@ Climb To Initial Altitude Figure 4--7...
Page 61: Enroute Cruise
SPZ--8000 Digital Integrated Flight Control System Enroute Cruise Figure 4--8 shows the aircraft straight and level at the preselected altitude of 24,000 ft, flying heading (HDG) and altitude hold (ALT) with VOR (white) armed for capture. The autopilot is engaged (AP) and coupled to the left side EHSI.
Page 62: Setup For Approach
SPZ--8000 Digital Integrated Flight Control System Setup for Approach Figure 4--9 shows the aircraft flying heading (HDG) and flight level change (FLC) modes, and armed for LOC (white) and GS (white) capture. With approach mode selected, the glideslope and localizer displays are in view.
Page 63: Approach Capture Tracking Below Decision Height (Dh)
SPZ--8000 Digital Integrated Flight Control System Approach Capture Tracking Below Decision Height (DH) Figure 4--10 shows the aircraft setup on final approach with localizer (LOC) and glideslope (GS) captured, and autopilot engaged (AP). The radio altitude of 150 feet is below the 200--foot decision height, so is displayed in the attitude sphere.
Page 64: Efis Reversion (Eadi)
SPZ--8000 Digital Integrated Flight Control System EFIS REVERSION (EADI) Pushing the panel--mounted REV buttons (IRS, SG, IAS, or flight director) on one side performs the reversion operation on that side, and locks out the reversion function on the other side, as shown in Figure 4--11.
Page 65: 12 Eadi Reversion Annunciators
SPZ--8000 Digital Integrated Flight Control System The location of the IAS, SG, and IRS reversion annunciators is shown in Figure 4--12. EADI Reversion Annunciators Figure 4--12 The location of the reversion annunciators for TCAS--equipped aircraft is shown in Figure 4--13. EADI Reversion Annunciators -- TCAS--Equipped Aircraft Figure 4--13 A28--1146--055...
Page 66: Irs Reversions
SPZ--8000 Digital Integrated Flight Control System IRS Reversions IRS reversions depend on how many inertial reference systems are installed. With two IRSs, either IRS can be transferred to the other side. With three IRSs, the third IRS can be transferred to one or both sides. The applicable EADI and EHSI annunciators are as follows: Dual IRS -- When IRS reversion is selected, the source side displays in an...
Page 67: 15 Cross--Side Irs Reversion
SPZ--8000 Digital Integrated Flight Control System The cross--side (side selecting IRS for reversion) displays XIRS amber box, as shown in Figure 4--15. AD--58064@ Cross--Side IRS Reversion Figure 4--15 Triple IRS -- In a triple installation, pilot or copilot IRS reversion is only between IRS No.
Page 68: Ias Reversions
SPZ--8000 Digital Integrated Flight Control System When both sides select the No. 3 IRS, an XIRS is shown in an amber on BOTH sides. The power--up state for the IRS is IRS No. 1 for the pilot’s side and IRS No.
Page 69 SPZ--8000 Digital Integrated Flight Control System The reversion switch on the MFD controller can transfer the MFD symbol generator to one side or the other. When this is done, MG (white) in a white box is displayed on the EADI on the side that selected the reversion, as shown in Figure 4--18.
Page 70: Flight Director Reversions
SPZ--8000 Digital Integrated Flight Control System When the optional TCAS is installed, the locations of most reversionary annunciators change, as shown in Figure 4--19. Symbol Generator Reversion Annunciator Location for TCAS--Equipped Aircraft Figure 4--19 Flight Director Reversions flag on the EADI indicates an invalid flight director on that side. The pilot or copilot can select the cross--side flight director to supply information to the on--side symbol generator and EADI.
Page 71: Nav Source Reversions
SPZ--8000 Digital Integrated Flight Control System AD--58069@ Flight Director Reversionary Mode, Couple Arrow Figure 4--20 NAV Source Reversions NAV source reversions are performed using the V/L and FMS buttons on the display controller. Repeatedly pushing the V/L or FMS buttons scrolls through the available NAV sources.
Page 72: Eadi Category Ii Annunciators
SPZ--8000 Digital Integrated Flight Control System EADI CATEGORY II ANNUNCIATORS Category II Failure -- If Category II approach capability is lost after Category II has been selected, a boxed CAT 2 is displayed in the upper right corner of the attitude sphere. The box and annunciator amber if the radio altitude is between 200 feet and 1200 feet, and flashing...
Page 73: Eadi Comparison Monitoring
SPZ--8000 Digital Integrated Flight Control System EADI COMPARISON MONITORING Figure 4--22 shows the location of the comparison monitors described below. AD--58071@ EADI Comparison Monitoring Figure 4--22 Attitude Comparison Monitor -- On--side displayed IRS data and cross--side IRS data are compared in the symbol generator. The attitude miscompare annunciator is displayed when there is a 3...
Page 74 SPZ--8000 Digital Integrated Flight Control System Glideslope Comparison Monitor -- On--side displayed glideslope data is compared with cross--side glideslope data in the symbol generator. The glideslope miscompare annunciator is displayed when there is a 50--microampere difference (about 2/3 dot) between on--side and cross--side glideslope data (both valid and RA less than 1200 feet).
Page 75: Eadi Excessive Attitude Display
SPZ--8000 Digital Integrated Flight Control System EADI EXCESSIVE ATTITUDE DISPLAY Excessive attitude is when the roll attitude exceeds 65 or the pitch attitude exceeds 30 up or 20 down. If the condition is excessive pitch attitude, excessive pitch chevrons are displayed, as shown in Figure 4--23.
Page 76: Eadi Failure Warning Flags
SPZ--8000 Digital Integrated Flight Control System EADI FAILURE WARNING FLAGS Figure 4--24 shows the location of the failure warning flags described below. AD--58073@ EADI Failure Warning Flags Figure 4--24 A28--1146--055 Electronic Flight Instrument System (EFIS) 4-32 REV 2...
Page 77: 25 Attitude Failure Flag
SPZ--8000 Digital Integrated Flight Control System Attitude Failure -- Invalid attitude, shown in Figure 4--25, is indicated by the following: — removing the pitch scale and roll pointer — removing the flight director cue — removing sky/ground raster — displaying a boxed flag.
Page 78: 27 Airspeed, Altitude Preselect, Cross--Side Data
SPZ--8000 Digital Integrated Flight Control System The following failure annunciators are shown in Figure 4--27: Indicated airspeed (IAS) failure Altitude preselect (ASEL) failure Cross--side data (XDATA) failure Vertical speed (optional) (VS) failure Glideslope (GS) failure Radio altitude (RA) failure Localizer (LOC) failure. Airspeed, Altitude Preselect, Cross--Side Data, Glideslope, Radio Altitude and Localizer Failure Flags Figure 4--27...
Page 79: 28 Symbol Generator Failure Flag
SPZ--8000 Digital Integrated Flight Control System Vertical Speed (Optional) Failure -- Loss of valid vertical speed is indicated by the following: — Removing the vertical speed scale — Removing the vertical speed window — Displaying a boxed flag. Glideslope Failure -- Loss of the valid glideslope or VNAV is indicated by the following: —...
Page 80: 29 Eadi With Optional Tcas Failure Flags
SPZ--8000 Digital Integrated Flight Control System TCAS Messages and Failure Annunciators -- TCAS messages and failure annunciators are displayed along the left side of the vertical speed scale, as shown in Figure 4--29. These messages are explained in the following paragraphs: —...
Page 81: Electronic Horizontal Situation Indicator (Ehsi)
SPZ--8000 Digital Integrated Flight Control System ELECTRONIC HORIZONTAL SITUATION INDICATOR (EHSI) The EHSI displays aircraft position relative to VOR radials, FMS waypoints, and localizer and glideslope beams. The FULL, ARC, WX, MAP, or MAP/WX displays are selected with switches on the display controller.
Page 82: Ehsi Displays And Annunciators In The Full Compass Or Arc Modes
SPZ--8000 Digital Integrated Flight Control System WX AND MAP/WX MODES ONLY WX range WX mode annunciator WX return display MAP AND MAP/WX MODES ONLY Waypoints and track lines VOR, DME, and VOR/DME symbols Cross--track distance TCAS traffic display (optional) EHSI Displays and Annunciators in the FULL Compass or ARC Modes The locations of the EHSI annunciators and displays are shown in Figure 4--30.
Page 83: 30 Ehsi Displays And Annunciators
SPZ--8000 Digital Integrated Flight Control System FORE LUBBER MESSAGE LINE ANNUNCIATOR HEADING WIND TARGET ALERT HEADING SOURCE DRIFT VECTOR ANNUNCIATOR SELECT BUG ANNUNCIATOR DISPLAY HEADING DIAL FMS APPROACH ANNUNCIATOR COURSE/DESIRED TRACK DISPLAY DISTANCE DISPLAY NAV SOURCE COURSE ANNUNCIATOR SELECT/DESIRED WAYPOINT/DME TRACK POINTER IDENTIFIER VOR1...
Page 84 SPZ--8000 Digital Integrated Flight Control System Heading Source Annunciator -- The selected heading source (MAG or TRU) is annunciated in white at the top center of the EHSI. FMS Message (MSG) Annunciator -- The annunciator flashes to alert the pilot that there are messages posted by the FMS on the control display unit.
Page 85 SPZ--8000 Digital Integrated Flight Control System Course Preselect Pointer and Deviation Bar-- When the FMS navigation mode is selected for display on the EHSI and a localizer frequency is tuned with the on--side VHF NAV receiver, pushing the V/L button on the display controller displays the magenta course preselect pointer on the EHSI.
Page 86 SPZ--8000 Digital Integrated Flight Control System If TTG, GS, or ET is not available or invalid, the annunciator remains displayed, but the digital readout is removed. Reciprocal Course Pointer -- The reciprocal course pointer indicates 180 from the course select pointer. Reciprocal Course Preselect Pointer -- The reciprocal course preselect pointer indicates 180...
Page 87 SPZ--8000 Digital Integrated Flight Control System Navigation Source Annunciator -- This annunciator indicates the source of the course and deviation information selected with the NAV source buttons on the display controller. The annunciator is VOR 1/VOR 2, LOC 1/LOC 2, or FMS 1/FMS 2. A green annunciator indicates on--side NAV source selection and yellow...
Page 88: Typical Ehsi Full Compass Display Presentations
SPZ--8000 Digital Integrated Flight Control System TYPICAL EHSI FULL COMPASS DISPLAY PRESENTATIONS The following figures show EHSI presentations that the pilot typically sees when using the FULL compass display mode. Figure 4--31 shows a standard HSI display that is using information from 1.
Page 89: 31 Ehsi Full Compass Display
SPZ--8000 Digital Integrated Flight Control System When the FMS navigation mode is selected for display on the EHSI, and the flight guidance computer has captured the course, selecting a localizer frequency on the on--side NAV receiver and pushing the V/L button on the on--side display controller displays the magenta course...
Page 90: Arc Mode Display
SPZ--8000 Digital Integrated Flight Control System ARC MODE DISPLAY The majority of arc mode display elements operate identically to their related display elements in the FULL compass mode. A typical ARC mode display is shown in Figure 4--33. AD--58076@ ARC Mode Display Figure 4--33 A28--1146--055 Electronic Flight Instrument System (EFIS)
Page 91: 34 Ehsi Displays And Annunciators (Arc Mode)
SPZ--8000 Digital Integrated Flight Control System The ARC mode displays and annunciators are shown in Figure 4--34. They operate the same way as the FULL compass mode annunciators shown in Figure 4--30. EHSI Displays and Annunciators (Arc Mode) Figure 4--34 A28--1146--055 Electronic Flight Instrument System (EFIS) 4-48...
Page 92: Ehsi Map Mode With Vor Selected For Display
SPZ--8000 Digital Integrated Flight Control System EHSI MAP MODE WITH VOR SELECTED FOR DISPLAY In the MAP mode, when VOR is selected for display, the normal ARC course select display (pointer, scale, and deviation) is removed and replaced by the display shown in Figure 4--35. The VOR or VOR/DME station is displayed at its geographical position with the corresponding symbol.
Page 93 SPZ--8000 Digital Integrated Flight Control System If the VOR station is out of the display range, an arrow is added to the course line to indicate the direction of the location of the station, as shown in Figure 4--36. AD--58078@ VOR Out of Map Range Figure 4--36 If the selected VOR bearing (1 or 2) is different from the VOR NAV...
Page 94: 37 Ehsi Map Format -- Vor Selected For Display
SPZ--8000 Digital Integrated Flight Control System If the selected VOR bearing (1 or 2) is the same as the VOR NAV source (VOR 1 or VOR 2), a magenta number that corresponds to the VOR bearing number is displayed to the left of the green yellow VOR symbol.
Page 95: Ehsi Map Mode With Fms Selected For Display
SPZ--8000 Digital Integrated Flight Control System EHSI MAP MODE WITH FMS SELECTED FOR DISPLAY In the MAP mode, when FMS is selected for display, the normal ARC course select display (pointer, scale, and deviation) is removed and replaced as described below. Figure 4--38 shows the EHSI in the MAP mode with the FMS selected for display.
Page 96 SPZ--8000 Digital Integrated Flight Control System If the on--side FMS bearing is selected, a cyan number (1 or 2) is displayed to the left of the TO waypoint symbol. If the TO waypoint is out of map range, a cyan FMS bearing pointer is displayed.
Page 97: Ehsi Weather Radar Displays
(TURB) detection, and autotilt modes. For a more detailed description of weather radar operation, refer to Appendix B and Honeywell Pub. No. A28--1146--048 for the PRIMUS 650 and Appendix C, Honeywell Pub. No. A28--1146--056, for the PRIMUS 870. EHSI Weather Radar Mode and Target Alert Annunciators Figure 4--40...
Page 98 SPZ--8000 Digital Integrated Flight Control System Mode Annunciator (WX and MAP/WX formats only) -- The weather radar modes are annunciated on the EHSI as shown Table 4--9. Operating Feature Mode Target Alert Mode Selected Annunciator Annunciator WAIT Any Selection WAIT ---- STANDBY ----...
Page 99: 41 Weather Radar Display
SPZ--8000 Digital Integrated Flight Control System AD--58080@ Weather Radar Display Figure 4--41 NOTES: 1. The weather radar antenna tilt is annunciated on the MFD weather display or shown by the weather controller. 2. Later installations display the radar antenna tilt angle below the radar mode annunciator on the EHSI.
Page 100: Ehsi Arc Mode With Tcas Traffic Display (Optional)
SPZ--8000 Digital Integrated Flight Control System EHSI ARC MODE WITH TCAS TRAFFIC DISPLAY (OPTIONAL) When selected with the external EHSI TCAS switch, ARC mode with TCAS traffic information is displayed on the EHSI. The range is fixed at 6 NM. All the features of the ARC mode display apply, except that groundspeed, TTG, and elapsed time are removed.
Page 101: Efis Reversion (Ehsi)
SPZ--8000 Digital Integrated Flight Control System No Bearing Data -- This is displayed in the lower right corner when the system has range but no bearing information for other traffic. TCAS Altitude Display Submodes (Optional) -- The following are TCAS submodes: —...
Page 102: Nav Source Reversions
SPZ--8000 Digital Integrated Flight Control System NAV SOURCE REVERSIONS NAV source reversions are performed using the V/L and FMS buttons on the display controller. Repeatedly pushing the V/L or FMS buttons scrolls through the available NAV sources. The NAV source reversions are indicated by annunciating the NAV source (VOR 1, VOR 2, LOC 1, LOC 2 FMS 1, FMS 2) and by changing the following annunciators and displays from...
Page 103: Ehsi Heading Comparison Monitoring
SPZ--8000 Digital Integrated Flight Control System EHSI HEADING COMPARISON MONITORING On--side displayed heading is compared with cross--side heading. The heading comparison annunciator is displayed when there is a 3 difference in heading, both compared data sources are valid, and the same type of heading (MAG/TRU) is selected on both sides.
Page 104: Ehsi Failure Warning Flags
SPZ--8000 Digital Integrated Flight Control System EHSI FAILURE WARNING FLAGS Heading Failure -- Invalid heading, as shown in Figure 4--46, is indicated by the following: — Removing the TRU/MAG annunciator — Removing the HDG/TRK bug — Removing the course pointer and deviation bar —...
Page 105: 47 Ehsi Nav Source And Glideslope Failure Flags
SPZ--8000 Digital Integrated Flight Control System Navigation Source Failure -- A failure of the NAV source, as shown in Figure 4--47, is indicated by the following: — Removing DTK pointer, deviation, and readout (FMS only) — Removing the deviation bar and the TO/FROM display (VOR/LOC) —...
Page 106: 48 Ehsi Arc Display With Tcas Failure
SPZ--8000 Digital Integrated Flight Control System TCAS Failure (Optional) -- TCAS failures, as shown in Figure 4--48, are indicated by the following: — Removing TCAS symbols (as appropriate) — Displaying fail messages: TCAS TEST (White) -- Displayed during TCAS self--test. TCAS OFF (White) -- TCAS is selected off.
Page 107: Composite Display
SPZ--8000 Digital Integrated Flight Control System COMPOSITE DISPLAY If a display unit fails, turning the HSI or ADI dimmer knob on the display controller to the OFF position displays a composite attitude and NAV format on the remaining good display, as shown in Figure 4--49. The composite display is different from the individual EADI and EHSI displays in that all elements are not displayed at the same time.
Page 108: 50 Composite Mode -- Cruise
SPZ--8000 Digital Integrated Flight Control System Whether or not an element is displayed is determined by flight phase, NAV radio tuning, selected flight director mode, absolute altitude, etc. The failure warning, reversionary, and comparison annunciators are not shown below but are similar to the normal display mode. Figure 4--50 shows the composite display in a cruise flight configuration.
Page 109: Test Symbols On Eadi
SPZ--8000 Digital Integrated Flight Control System Figure 4--51 shows the composite display in the approach configuration. AD--58084@ Composite Mode -- Approach Figure 4--51 EFIS SELF--TEST Test Symbols on EADI The test display is initialized by pushing the TEST button on the display controller and the test pattern is displayed as long as the button is pushed.
Page 110: Test Symbols On The Ehsi
SPZ--8000 Digital Integrated Flight Control System After 4 seconds, all comparison annunciators are removed and all flags are displayed, as shown in Figure 4--53. EADI Test Pattern (After 4 Seconds) Figure 4--53 For the whole duration of the test, TEST is displayed on the EADI.
Page 111: Multifunction Display (Mfd) System
SPZ--8000 Digital Integrated Flight Control System Multifunction Display (MFD) System Figure 5--1 shows the location of the elements of the MFD system mounted in the cockpit. MULTI--FUNCTION DISPLAY (MFD) MFD CONTROLLER MFD SYMBOL GENERATOR ANNUNCIATOR AD--65716@ MFD Components Figure 5--1 A28--1146--055 Multifunction Display (MFD) System REV 2...
Page 112: Mfd System Information
SPZ--8000 Digital Integrated Flight Control System MFD SYSTEM INFORMATION The MFD system has five major display functions: Navigation data TCAS traffic display (optional) Weather radar Checklist EFIS reversion (described in the EFIS section of this manual). The MFD system expands on the navigation mapping capabilities of the EFIS because the MFD area can be used exclusively for MAP formats without displaying essential heading and NAV data that is displayed on the EHSI.
Page 113: Mfd Controller
SPZ--8000 Digital Integrated Flight Control System MFD CONTROLLER The MFD controller, shown in Figure 5--2, is used to select MFD modes and format. AD--43040@ MFD Controller Figure 5--2 The following paragraphs describe the MFD controller buttons, switches, and joystick. Navigation MAP/PLAN Button -- Pushing the MAP/PLAN button toggles between displaying the heading up MAP mode and the north up PLAN mode.
Page 114 SPZ--8000 Digital Integrated Flight Control System VOR Button -- The VOR button adds VOR/DME symbols and designators to the MAP and PLAN displays. The toggling sequence — The first push displays the tuned VOR/DMEs. — The second push displays all VOR/DMEs within display range (a maximum of four).
Page 115: Designator Control
SPZ--8000 Digital Integrated Flight Control System Designator Control SKP (Skip) Button -- When this button is pushed, the designator skips to the next displayed waypoint. If the button is pushed when the designator is at the last displayed waypoint, the designator returns to present position.
Page 116 SPZ--8000 Digital Integrated Flight Control System Checklist Control -- The SKP, RCL, PAG, and ENT buttons and the joystick control checklist functions are described in the following paragraphs. — RCL BUTTON -- Pushing the RCL button displays the page containing the lowest order skipped item with that item selected. —...
Page 117: Mfd Reversion
SPZ--8000 Digital Integrated Flight Control System MFD Reversion The mode selector on the MFD controller lets the operator select MFD system backup of the EHSI and EFIS symbol generators. The mode selector switch is a five--position rotary switch that selects the following MFD modes of operation: MFD -- This position selects normal MFD operation.
Page 118: Mfd Map Mode
300, 600, or 1200 miles, or the next route segment can be displayed. With a compatible NAV source with a stored data base (i.e., the Honeywell FMS), other navigation data beyond route mapping such as VOR station locations and time--to--go to the next waypoint, can be displayed.
Page 119: Mfd Map Mode Symbols
SPZ--8000 Digital Integrated Flight Control System The MAP mode displays and annunciators, shown in Figure 5--4, are described in the following paragraphs. MFD MAP Mode Symbols Figure 5--4 Heading Dial and Lubber Line -- The heading dial indicates the actual heading of the aircraft with respect to the lubber line. It is the same heading information as displayed on the EHSI.
Page 120 SPZ--8000 Digital Integrated Flight Control System Weather Radar Mode -- The weather radar mode annunciator displays the status of the weather radar system. When in STBY, no weather information is displayed. Weather is added to the display and WX is annunciated when the WX button on the MFD controller is pushed.
Page 121: Mfd Map Mode Flight Plan Displays
SPZ--8000 Digital Integrated Flight Control System Range Rings -- Range rings are displayed to aid in the use of radar returns and position of NAVAIDS. If the WX mode is selected, the outer range ring is the compass card boundary and represents the selected range on the radar.
Page 122: Mfd Map Mode With Vor Data
SPZ--8000 Digital Integrated Flight Control System Figure 5--6 shows the MFD MAP mode with VOR data displayed. 0.5L 4:39 33. 3 AD--58091@ MFD MAP Mode With VOR Data Figure 5--6 Figure 5--7 shows the MFD MAP mode with airport data displayed. 0.5L 4:39 33.
Page 123: Mfd Plan Mode
SPZ--8000 Digital Integrated Flight Control System MFD PLAN Mode The MFD PLAN format, shown in Figure 5--8, has a north--up orientation where the aircraft is positioned with respect to the NAV route. The aircraft progresses along the route, while the maximum range is shown by a circle around the outer perimeter.
Page 124: Mfd Plan Mode Flight Plan Data
SPZ--8000 Digital Integrated Flight Control System MFD PLAN Mode Flight Plan Data As in the MAP mode, the flight plan can be displayed with waypoints, VOR data, airport data, or any combination of the three. The same flight plan is shown in each of the following drawings for ease of comparing the different information on the three displays.
Page 125: 10 Mfd Plan Mode With Vor Data
SPZ--8000 Digital Integrated Flight Control System Figure 5--10 shows the MFD PLAN mode with VOR data displayed. 0.5L 4:39 33. 3 AD--58094@ MFD PLAN Mode With VOR Data Figure 5--10 Figure 5--11 shows the MFD PLAN mode with airport data displayed. 0.5L 4:39 33.
Page 126: Changing A Waypoint
SPZ--8000 Digital Integrated Flight Control System Changing a Waypoint When the MFD is operating with the FMS, waypoints can be added, deleted, or moved, as described in Table 5--1. The procedure adds a waypoint between IRW and PER (IRW/056/47.1). Step Procedure Using the SKP button on the MFD controller, move the designator from ADM (the TO waypoint) to IRW.
Page 127 SPZ--8000 Digital Integrated Flight Control System Step Procedure On the FMS CDU, the designator position is shown in the scratch pad at the bottom of the screen. Use the appropriate line select key to insert this position in the flight plan.
Page 128: Tcas Mode Traffic Display (Optional)
SPZ--8000 Digital Integrated Flight Control System TCAS Mode Traffic Display (Optional) The TCAS display, shown in Figure 5--14, is displayed on the MFD in one of two ways: Pilot selected with the MAP/PLAN button on the MFD controller Automatically displayed when the TCAS is in AUTO and detects a TA or RA traffic condition.
Page 129 SPZ--8000 Digital Integrated Flight Control System The MFD TCAS display range is controlled with the MFD range controller at 6, 10, 25, and 50 NM range. The display is similar to the PLAN format with the following specific symbols: 2 NM TCAS range ring NOTE: When a display range greater than 10 NM is selected, the 2 NM range ring is removed.
Page 130: Mfd Weather Radar Mode
SPZ--8000 Digital Integrated Flight Control System MFD Weather Radar Mode The two basic weather radar (WX) modes are described below: WX with MAP is similar to the EFIS WX mode. Two range rings are displayed at selected range and half range WX ONLY differs from WX with MAP by displaying four range rings with azimuth lines at 0, 30, and 60.
Page 131: 16 Mfd Weather Annunciators
SPZ--8000 Digital Integrated Flight Control System A target alert annunciator is displayed below the mode annunciator to warn of level or stronger targets within 7.5 of the aircraft heading and beyond the displayed range. is displayed when target alert is on.
Page 132: Mfd Checklist Display
SPZ--8000 Digital Integrated Flight Control System MFD Checklist Display The MFD symbol generator can store and display several pages of text. The content of these pages is defined by the aircraft operator. Each page has 12 lines with a maximum of 24 characters per line. The text pages are used to store operator defined checklists and waypoint data.
Page 133: 18 Emergency Checklist Display
SPZ--8000 Digital Integrated Flight Control System Pushing the EMER button on the MFD controller displays the first page of the emergency checklist index with the first checklist selected, as shown in Figure 5--18. The SKP, RCL, PAG, and ENT buttons and the joystick are used to control the emergency checklist.
Page 134: Automatic Flight Control System
SPZ--8000 Digital Integrated Flight Control System Automatic Flight Control System (AFCS) The AFCS components and their locations in the aircraft are shown in Figure 6--1. AFCS Components Figure 6--1 A28--1146--055 Automatic Flight Control System (AFCS) REV 2...
Page 135: Flight Guidance Controller
SPZ--8000 Digital Integrated Flight Control System FLIGHT GUIDANCE CONTROLLER The flight guidance controller, shown in Figure 6--2, is used to engage the system, select the operating modes, and select the EHSI and DADC being used to interface with the flight guidance computer. The function of each switch or control is described in the following paragraphs.
Page 136 SPZ--8000 Digital Integrated Flight Control System BC (Back Course) Button -- The BC button selects approach mode guidance to capture and track a back course ILS. There is no glideslope capture during the BC mode. APP (Approach) Button -- The APP button arms the lateral guidance for localizer capture and vertical guidance for glideslope capture.
Page 137 SPZ--8000 Digital Integrated Flight Control System AP (Autopilot) and YD (Yaw Damper) Button -- The AP button engages autopilot and yaw damper functions simultaneously, but it only disengages the autopilot functions. The YD button engages the yaw damper only, and disengages the yaw damper and autopilot functions.
Page 138: Turn Pitch Controller
SPZ--8000 Digital Integrated Flight Control System TURN PITCH CONTROLLER The turn pitch controller, shown in Figure 6--3, is used to manually control the autopilot using the turn knob and pitch wheel. The paragraphs below describe each control. NOSE TURN NOSE AD--58104@ Turn Pitch Controller Figure 6--3...
Page 139: Advisory Display
SPZ--8000 Digital Integrated Flight Control System ADVISORY DISPLAY The advisory display, shown in Figure 6--4, is used to request data from the crew and display system mode and status annunciators. Advisory Display Figure 6--4 The display format is shown in Figure 6--5. Messages are sent to the advisory display from the master flight guidance computer.
Page 140 SPZ--8000 Digital Integrated Flight Control System Operational Messages (white) — Static air temperature (SAT)/total air temperature (TAT)/true airspeed (TAS) display — Flight director lateral and vertical arm modes — Flight director lateral and vertical active modes — AFCS status messages. Warning/Caution Messages -- Warning/caution messages are displayed on the second line in amber.
Page 141: Advisory Display Annunciators And Messages
SPZ--8000 Digital Integrated Flight Control System Advisory Display Annunciators and Messages Table 6--1 gives the parameters of the SAT/TAT/TAS messages. Message Range/Resolution Comments dd _C SAT (field 1 99 _C (1 _C) Updated at 1 Hz rate white) dd _C TAT (field 2 99 _C (1 _C) Digits replaced by white)
Page 142 SPZ--8000 Digital Integrated Flight Control System Table 6--3 lists the flight director lateral and vertical mode annunciators. Reverse Video Message Field Comments (5 Sec) HI bank mode HDG/LO LO bank mode Capture mode VOR/LO LO bank capture mode Capture mode Capture mode Capture mode Capture mode...
Page 143 SPZ--8000 Digital Integrated Flight Control System Reverse Video Message Field Comments (5 Sec) VS + dddd Updated at 10--Hz rate GO AROUND VFLC VASL Capture mode VALT VPTH Capture mode VPTH Lateral and Vertical Active Mode Annunciators Table 6--3 Table 6--4 lists the AFCS status message annunciators. Timed--out Message Field...
Page 144 SPZ--8000 Digital Integrated Flight Control System Table 6--5 lists the flashing disengage message annunciators. Timed--out Reset (5 Sec) Message Comments Light On Pushing either the AP/YD/M--TRIM RESET button, Disengaged quick disconnect quick disconnect, AP/YD or go--around Disengaged switch clears the switch clears the message and turns AP/YD...
Page 145 SPZ--8000 Digital Integrated Flight Control System Table 6--6 lists the primary caution message annunciators. Timed--out Reset Message (5 Sec) Comments Light On PITCH TRIM FAIL Pilot must manually disconnect autopilot (AP). This action also clears the messages. MISTRIM [TRIM Message is NOSE UP/DN] displayed only while excessive...
Page 146 SPZ--8000 Digital Integrated Flight Control System Table 6--7 lists the sensor failure message annunciators. Timed--out Reset Message (5 sec) Comments Light On These messages CPL DATA INVALID are displayed for are displayed for 5 seconds if an CPL NAV DATA attempt is made INVALID to manually...
Page 147 SPZ--8000 Digital Integrated Flight Control System Table 6--8 lists the steady advisory caution message characteristics. Timed--out Reset Message (5 sec) Comments Light On AMBER DASHED ---- ---- The dashed line LINE is displayed after an ASCB failure. L AFCS OFF This message is R AFCS OFF displayed if either...
Page 148 SPZ--8000 Digital Integrated Flight Control System Timed--out Reset Message (5 sec) Comments Light On AP FAIL/YD AVAIL Indicates that only the AP failed, but not yaw damper (YD). NAV MISMATCH When a NAV MISMATCH [LEFT NAV] occurs, the FGC automatically selects the most NAV MISMATCH reasonable NAV...
Page 149 SPZ--8000 Digital Integrated Flight Control System Table 6--9 lists the steady invalid operation message annunciators. Timed--out Reset Message (5 sec) Comments Light On CHECK NAV This message SOURCE indicates that the mode cannot engage because of an improper NAV source selection on active EHSI.
Page 150 SPZ--8000 Digital Integrated Flight Control System Timed--out Reset Message (5 sec) Comments Light On CAT 2 INVALID CAT 2 status is invalid when selected on the flight guidance controller. TURN KNOB Engaging the AP ACTIVE is inhibited because the turn knob is out of detent.
Page 151: Glossary Of Terms
SPZ--8000 Digital Integrated Flight Control System System Limits GLOSSARY OF TERMS This glossary gives a brief description of the flight guidance computer control laws. These terms are used throughout this section and the Modes of Operation section. The performance and operating limits for these items are defined in Table 7--1.
Page 152: Glideslope Gain Programming
SPZ--8000 Digital Integrated Flight Control System Glideslope Gain Programming Gain programming starts after the VBS trips. The gain is programmed as a function of radio altitude and vertical speed. If the radio altimeter is invalid, gain programming occurs at glideslope capture and is controlled by a runway height estimator.
Page 153: Lateral Beam Sensor (Lbs)
SPZ--8000 Digital Integrated Flight Control System Lateral Beam Sensor (LBS) When flying to intercept the VOR or LOC beam, the LBS is tripped as a function of beam deviation, course error, TAS, and DME. In the LOC mode, the course error is compared with the beam deviation signal and rate of crossing the beam to determine the LBS trip point.
Page 154: Loc Track 1 And Bc Track 1
SPZ--8000 Digital Integrated Flight Control System LOC TRACK 1 and BC TRACK 1 Localizer track 1 and back course track 1 mean the aircraft is on beam center and the roll rate limit is decreased from 7.0/second (during the capture phase) down to 5.5/second. When track occurs, the course error is eliminated from the control signal, leaving beam deviation and lateral acceleration from the IRS to maintain the aircraft on beam center.
Page 155: Vertical Beam Sensor (Vbs)
SPZ--8000 Digital Integrated Flight Control System Vertical Beam Sensor (VBS) The VBS determines the point of glideslope capture using a number of inputs. The VBS is armed when NAV radio is tuned to a LOC frequency, the LOC receiver is valid, and the LBS has tripped. The VBS trips as a function of vertical speed, TAS, and glideslope deviation.
Page 156: Vor After Over Station Sensor 1/2 (Aoss 1/2)
SPZ--8000 Digital Integrated Flight Control System VOR Over Station Sensor (VOR OSS) The OSS detects the erratic radio signals encountered in the area above the VOR transmitter. When these radio signals reach a certain level of deviation, they no longer are useful and the OSS eliminates them from the control signal.
Page 157: System Performance/Operating Limits
SPZ--8000 Digital Integrated Flight Control System VOR AOSS 2 occurs when the following conditions are all satisfied: — VOR AOSS 1 has tripped plus 3 seconds — Beam deviation is less than 2 dots — Once VOR AOSS 2 trips, beam deviation is again part of the control signal.
Page 158 SPZ--8000 Digital Integrated Flight Control System Control or Sensor Mode Parameter Value Course knob Course knob VOR Track: VOR Track: and NAV and NAV receiver Roll angle limit 17_ low bank switched Roll rate limit 4.0 degrees/second Crosswind Correction Up to 45_ course error Overstation course Up to 120_ change...
Page 159 SPZ--8000 Digital Integrated Flight Control System Control or Sensor Mode Parameter Value APR or Course knob LOC Track: and NAV and NAV receiver Roll angle limit Roll rate limit 5.5_/second Crosswind correction Up to 45_ course error LOC gain programming LOC gain programming Function of radio altitude, Function of radio altitude,...
Page 160 SPZ--8000 Digital Integrated Flight Control System Control or Sensor Mode Parameter Value DADC MACH engage range 0.4 to 0.9 Mach MACH hold error 0.01 Mach Pitch limit Pitch rate limit .3g maximum IAS engage range 80 to 400 kts IAS hold engage error 5 kts DADC and ALT Preselect capture...
Page 161 SPZ--8000 Digital Integrated Flight Control System Control or Sensor Mode Parameter Value VFLC MACH engage range Mach 0.4 to 0.9 MACH hold error Mach 0.01 Pitch limit Pitch rate limit .3g maximum IAS engage range 80 to 400 kts IAS hold engage 5 kts Pitch limit Pitch rate limit...
Page 162: Modes Of Operation
SPZ--8000 Digital Integrated Flight Control System Modes of Operation HEADING HOLD AND WINGS LEVEL The basic lateral mode of the autopilot is heading hold. Heading hold is defined as: Autopilot engaged (AP) No lateral flight director mode selected Bank angle less than 6. If these conditions are satisfied, the autopilot rolls the aircraft to a wings level attitude.
Page 163: Roll Hold Mode
SPZ--8000 Digital Integrated Flight Control System ROLL HOLD MODE The autopilot recognizes the roll hold mode as being operational when: No lateral flight director mode is selected and, The aircraft’s bank angle is greater than 6, but less than 45 and, Touch control steering (TCS) was used to initiate the roll maneuver.
Page 164: Heading Select Mode
SPZ--8000 Digital Integrated Flight Control System HEADING SELECT MODE The heading select mode is used to intercept and maintain a magnetic heading. The mode is engaged by pushing the HDG button on the flight guidance controller. is annunciated on the EADI. Engaging the heading select mode resets all previously selected lateral modes.
Page 165: Vor (Nav) Mode
SPZ--8000 Digital Integrated Flight Control System VOR (NAV) MODE The VOR mode automatically intercepts, captures, and tracks a selected VOR radial, using the selected navigation source displayed on the EHSI. The navigation source displayed on the EHSI is selected with the NAV source buttons on the display controller.
Page 166: Vor (Nav) Mode Intercept
SPZ--8000 Digital Integrated Flight Control System When the procedure is completed, the EADI annunciates VOR (white) and HDG, as shown in Figure 8--3. AD--58109@ AD--58110@ VOR (NAV) Mode Intercept Figure 8--3 A28--1146--055 Modes of Operation REV 2...
Page 167: Vor (Nav) Mode Intercept Profile
SPZ--8000 Digital Integrated Flight Control System The flight guidance computer is armed to capture the VOR signal and it generates a roll command to fly the heading select mode, as shown in Figure 8--4. VOR (NAV) Mode Intercept Profile Figure 8--4 A28--1146--055 Modes of Operation REV 2...
Page 168: Vor (Nav) Mode Capture
SPZ--8000 Digital Integrated Flight Control System When the aircraft reaches the lateral beam sensor trip point, the system automatically drops the heading select mode and switches to the VOR capture mode. The following is displayed on the EADI, as shown in Figure 8--5: The white VOR annunciator is removed annunciator is removed...
Page 169: Vor (Nav) Mode Capture Profile
SPZ--8000 Digital Integrated Flight Control System The flight guidance computer generates the proper roll command to bank the aircraft to capture and track the selected VOR radial, as shown in Figure 8--6. VOR (NAV) Mode Capture Profile Figure 8--6 When the course select pointer is set on the EHSI using the CRS knob on the instrument remote controller, the course select error signal is established.
Page 170: Course Cut Limiter
SPZ--8000 Digital Integrated Flight Control System When flying a VOR intercept, the optimum intercept angle should be less than 45. If the intercept angle is greater than 45, course cut limiting may occur. The course cut limiter works primarily when approaching the VOR radial at an intercept angle that is greater than 45...
Page 171: Vor (Nav) Mode Track
SPZ--8000 Digital Integrated Flight Control System When the aircraft satisfies VOR track conditions, the course error signal is removed from the lateral steering command. This leaves radio deviation, roll attitude, and lateral acceleration to track the VOR signal and to compensate for beam standoff in the presence of a crosswind. The system automatically compensates for a crosswind of up to 45...
Page 172: Vor Over Station Operation
SPZ--8000 Digital Integrated Flight Control System VOR Over Station Operation As the aircraft approaches the VOR station, it enters a zone of unstable radio signal, as shown in Figure 8--9. This zone of confusion radiates upward from the station in the shape of a truncated cone. In this area, the radio signal becomes erratic and it must be removed from the roll command.
Page 173: Vor Direct To Function
SPZ--8000 Digital Integrated Flight Control System VOR DIRECT TO Function Another option is to fly a VOR intercept that has a zero deviation to the VOR station. This procedure is described in Table 8--2. Step Procedure Establish the VOR intercept as previously described. Set the bearing selector to the same NAV source that is being used for the VOR intercept on the display controller.
Page 174 SPZ--8000 Digital Integrated Flight Control System AD--58118@ AD--58119@ VOR DIRECT TO Function Figure 8--10 A28--1146--055 Modes of Operation REV 2 8-13...
Page 175: Flight Management System (Fms) Steering
SPZ--8000 Digital Integrated Flight Control System The VOR NAV mode is cancelled by: Pushing the NAV button on the flight guidance controller Selecting go--around mode Selecting standby mode Selecting the heading lateral steering mode Coupling to the cross--side EHSI With the autopilot engaged, moving the turn knob out of detent Course change greater than 3...
Page 176: 11 Fms Steering Cockpit Displays
SPZ--8000 Digital Integrated Flight Control System AD--58121@ AD--58122@ FMS Steering Cockpit Displays Figure 8--11 A28--1146--055 Modes of Operation REV 2 8-15...
Page 177: 12 Fms Steering
SPZ--8000 Digital Integrated Flight Control System With FMS selected as the navigation source, LNV capture occurs at one of the following points: When the aircraft is within 2.5 miles of the desired track and moving away from it, or At a calculated point, as a function of track error and groundspeed if the aircraft is flying toward the desired track.
Page 178: Localizer (Nav) Mode
SPZ--8000 Digital Integrated Flight Control System LOCALIZER (NAV) MODE The localizer mode automatically intercepts, captures, and tracks the front course localizer beam to line up on the centerline of the runway in use. To engage localizer (NAV) mode, follow the procedure in Table 8--3.
Page 179 SPZ--8000 Digital Integrated Flight Control System The EADI annunciates the following, as shown in Figure 8--13: LOC (white) HDG. AD--58124@ AD--58125@ Localizer (NAV) Mode Intercept Cockpit Displays Figure 8--13 A28--1146--055 Modes of Operation 8-18 REV 2...
Page 180 SPZ--8000 Digital Integrated Flight Control System The aircraft is flying the heading intercept and the system is armed for automatic localizer beam capture, as shown in Figure 8--14. Localizer (NAV) Mode Intercept Figure 8--14 With the aircraft approaching the selected course intercept, the lateral beam sensor monitors localizer beam deviation, beam rate, and TAS.
Page 181 SPZ--8000 Digital Integrated Flight Control System When the lateral beam sensor trips, the EADI displays LOC, as shown in Figure 8--16. The annunciator flashes for 5 seconds to indicate that capture has occurred. AD--58127@ AD--58128@ Localizer (NAV) Mode Capture Cockpit Displays Figure 8--16 A28--1146--055 Modes of Operation...
Page 182 SPZ--8000 Digital Integrated Flight Control System As the aircraft continues toward localizer beam center, the computer enters the LOC CAP 2 submode. With the aircraft almost lined up on localizer beam center, the computer automatically changes to the LOC TRACK 1 and the LOC TRACK 2 submodes. The LOC CAP 2 and LOC TRACK submodes apply tighter control law programming on the localizer signal fly a tighter flightpath along the localizer beam.
Page 183 SPZ--8000 Digital Integrated Flight Control System If radio altitude information is not valid, then distance is estimated as a function of glideslope deviation and TAS. If neither radio altitude nor glideslope data is valid, then distance is estimated as a function of TAS and time.
Page 184: Back Course (Bc) Mode
SPZ--8000 Digital Integrated Flight Control System The localizer mode is cancelled by: Pushing the NAV button on the flight guidance controller Selecting go--around mode Selecting standby mode Selecting the heading lateral steering mode Selecting the back course lateral steering mode Coupling to the cross--side EHSI Tuning another NAV frequency With the autopilot engaged, moving the turn knob out of detent.
Page 185: 19 Back Course Armed Cockpit Displays
SPZ--8000 Digital Integrated Flight Control System With the aircraft outside the normal localizer capture limits, the EADI annunciates the following, as shown in Figure 8--19: BC (white) HDG. AD--58133@ AD--58134@ Back Course Armed Cockpit Displays Figure 8--19 A28--1146--055 Modes of Operation 8-24 REV 2...
Page 186: 20 Back Course Mode Capture
SPZ--8000 Digital Integrated Flight Control System At localizer capture, the annunciator on the EADI is displayed and flashes for 5 seconds to indicate that capture has occurred, as shown in Figure 8--20. AD--58135@ 8. 0 AD--58136@ Back Course Mode Capture Figure 8--20 A28--1146--055 Modes of Operation...
Page 187: 21 Back Course Mode Intercept
SPZ--8000 Digital Integrated Flight Control System When the back course mode is selected on the flight guidance controller, logic in the flight guidance computer internally reverses the polarity of the course error and localizer signals, as shown in Figure 8--21. A gain change takes place in the computer when BC is selected, since the aircraft is closer to the localizer transmitter by the length of the runway plus 1000 feet.
Page 188: 22 Back Course Mode Tracking Cockpit Displays
SPZ--8000 Digital Integrated Flight Control System At back course capture, the flight guidance computer generates a roll command to smoothly capture and track the back course localizer signal. The back course tracking mode cockpit displays are shown in Figure 8--22. AD--58137@ AD--58138@ Back Course Mode Tracking Cockpit Displays...
Page 189: Preselected Course Approach
SPZ--8000 Digital Integrated Flight Control System The back course mode is cancelled by: Pushing the BC button on the flight guidance controller Selecting the heading or go--around modes Selecting standby mode Coupling to the cross side EHSI Selecting the APP or NAV modes Tuning a different NAV frequency or source.
Page 190: 23 Preselected Course Approach Cockpit Displays
SPZ--8000 Digital Integrated Flight Control System AD--58139@ AD--58140@ Preselected Course Approach Cockpit Displays Figure 8--23 A28--1146--055 Modes of Operation REV 2 8-29...
Page 191: Approach Mode
SPZ--8000 Digital Integrated Flight Control System APPROACH MODE The approach mode automatically intercepts, captures, and tracks the front course localizer and glideslope signals. When this mode is engaged, the pilot can fly a fully coupled ILS approach. The mode is set up and flown exactly like the localizer mode, except that the APP button on the flight guidance controller is pushed to arm the approach mode.
Page 192: 25 Approach Mode Intercept Cockpit Displays
SPZ--8000 Digital Integrated Flight Control System AD--58142@ AD--58143@ Approach Mode Intercept Cockpit Displays Figure 8--25 A28--1146--055 Modes of Operation REV 2 8-31...
Page 193 SPZ--8000 Digital Integrated Flight Control System At localizer capture, the EADI annunciates: GS (white) Any other active vertical mode in green annunciator flashes for 5 seconds to indicate capture mode. The flight guidance computer generates a roll command to smoothly capture and track the localizer signal.
Page 194: (Before Glideslope Capture)
SPZ--8000 Digital Integrated Flight Control System With the localizer captured and the aircraft outside the normal glideslope capture limits, the EADI annunciates the following, as shown in Figure 8--27: in green GS (white) Any other active vertical mode in green. AD--58145@ AD--58146@ Approach Mode Capture Cockpit Displays...
Page 195 SPZ--8000 Digital Integrated Flight Control System When the aircraft approaches the glideslope beam, the vertical beam sensor monitors TAS, vertical speed, and glideslope deviation to determine the correct capture point. When glideslope capture occurs, the computer drops all other active vertical modes, and automatically generates a pitch command to track the glideslope beam, as shown in Figure 8--28.
Page 196: (After Glideslope Capture)
SPZ--8000 Digital Integrated Flight Control System AD--58148@ AD--58149@ Approach Mode Capture Cockpit Displays (After Glideslope Capture) Figure 8--29 A28--1146--055 Modes of Operation REV 2 8-35...
Page 197: Dual Couple (Cpl) Approach Mode
SPZ--8000 Digital Integrated Flight Control System The approach mode is cancelled by: Pushing the APP, NAV, or HDG buttons on the flight guidance controller Selecting go--around mode Selecting standby mode Coupling to the cross--side EHSI Tuning a different NAV frequency or source. DUAL COUPLE (CPL) APPROACH MODE During the tracking phase of an ILS approach, the system uses localizer and glideslope flightpath information from both the pilot’s and copilot’s...
Page 198: 30 Eadi In Dual Couple Approach Mode
SPZ--8000 Digital Integrated Flight Control System Figure 8--30 shows the EADI for the dual couple approach mode. AD--58150@ EADI in Dual Couple Approach Mode Figure 8--30 Dual couple approach mode is cancelled in one of two ways: Automatic Cancellation — Whenever invalid data from one ILS receiver is detected, the flight guidance computer selects the remaining side ILS data for guidance.
Page 199: Category Ii Approach
SPZ--8000 Digital Integrated Flight Control System CATEGORY II APPROACH Pushing the CAT 2 button with the approach mode armed and radio altitude greater than 800 feet enables the Category II approach functions (monitors and annunciators). If all conditions for a Category II approach are valid, CAT 2 (white) is displayed on the advisory display, as shown in Figure 8--31.
Page 200: 32 Category Ii Invalid Annunciator
SPZ--8000 Digital Integrated Flight Control System If the above conditions are not met when CAT 2 is selected, CAT 2 INVALID is displayed on line two of the advisory display for 5 seconds, as shown in Figure 8--32. AD--58152@ Category II Invalid Annunciator Figure 8--32 Once the aircraft has flown below 800 feet radio altitude, the following conditions must be met for CAT 2 to remain valid:...
Page 201: Pitch Attitude Hold Mode
SPZ--8000 Digital Integrated Flight Control System PITCH ATTITUDE HOLD MODE The pitch attitude hold mode is the basic vertical flight director mode. It is activated when a flight director roll mode is selected without an accompanying pitch mode. There is no annunciator for pitch hold mode, as shown in Figure 8--33.
Page 202: Vertical Speed Hold Mode
SPZ--8000 Digital Integrated Flight Control System VERTICAL SPEED HOLD MODE The vertical speed hold mode automatically maintains the aircraft at a pilot--selected vertical speed. To engage vertical speed hold, the pilot maneuvers the aircraft to the desired climb or descent attitude, establishes the vertical reference, and pushes the VS button on the flight guidance controller.
Page 203: Flight Level Change Mode
SPZ--8000 Digital Integrated Flight Control System When the vertical speed reference is changed using the pitch wheel, the advisory display indicates the commanded vertical speed reference. The VSI displays actual aircraft vertical speed. Selecting vertical speed resets all previously selected vertical modes. The following actions cancel the vertical speed mode: Pushing the VS button Selecting another vertical mode...
Page 204: 35 Flight Level Change Mode
SPZ--8000 Digital Integrated Flight Control System In FLC mode, is displayed in the vertical capture location, as shown in Figure 8--35. AD--58156@ Flight Level Change Mode Figure 8--35 If the TCS button is pushed and held, the pilot can maneuver the aircraft without disengaging the FLC mode.
Page 205 SPZ--8000 Digital Integrated Flight Control System In the FLC mode, all armed pitch flight director modes are allowed, but capturing any armed pitch mode overrides the FLC mode. The FLC mode is cancelled by: Pushing the FLC button on the flight guidance controller Moving the pitch wheel on the pitch turn controller Selecting any other vertical mode on, or captured Selecting go--around mode...
Page 206: Altitude Hold Mode
SPZ--8000 Digital Integrated Flight Control System ALTITUDE HOLD MODE The altitude hold mode is a vertical flight director mode that maintains a barometric altitude reference. The vertical command for altitude hold is displayed with the flight director pitch command cue on the EADI. Refer to Table 8--6 for the procedure for using the altitude hold mode.
Page 207: Altitude Preselect Mode
SPZ--8000 Digital Integrated Flight Control System The altitude hold mode is cancelled by: Moving the pitch wheel on the pitch turn controller Pushing the ALT button on the flight guidance controller Selecting any other vertical mode on, or captured Selecting go--around mode Selecting standby mode Coupling to the cross--side EHSI.
Page 208 SPZ--8000 Digital Integrated Flight Control System When these three conditions are met, the altitude preselect mode is dropped and the system automatically transitions to the altitude hold mode. The altitude hold mode is dropped if the pitch wheel is moved. Altitude preselect is automatically armed if the aircraft is 250 feet away from the altitude preselect setting and has a vertical speed component in the direction of the selected altitude.
Page 209 SPZ--8000 Digital Integrated Flight Control System The altitude preselect mode is automatically armed, as shown in Figure 8--38, when the following conditions exist: — Selected altitude is more than 250 feet from present altitude — Vertical speed toward the selected altitude is greater than 1.3 feet/second for 3 seconds —...
Page 210: 39 Transition To Altitude Hold Mode
SPZ--8000 Digital Integrated Flight Control System The aircraft begins a nonlinear flare, dependent upon vertical speed. Altitude preselect capture is dropped and altitude hold is automatically engaged, as shown in Figure 8--39. AD--58160@ Transition to Altitude Hold Mode Figure 8--39 The altitude preselect capture submode is cancelled by: Moving the ALT set knob Moving the pitch wheel on the turn pitch controller...
Page 211: Vertical Navigation Mode
SPZ--8000 Digital Integrated Flight Control System VERTICAL NAVIGATION MODE Pushing the VNAV button on the flight guidance controller selects the vertical navigation mode and overrides all active pitch flight director modes. In the VNAV mode, the AFCS tracks the vertical flight profile of the FMS with the following submodes possible: Vertical Flight Level Change (VFLC) -- VFLC operates the same way as FLC except that the target speed and altitude from the FMS...
Page 212 SPZ--8000 Digital Integrated Flight Control System Vertical Path (VPTH) Mode -- VPTH mode is used to fly a fixed flightpath angle to a vertical waypoint during descent. The VPTH mode engages whenever the FMS initiates a path descent, which can occur while in VFLC or VALT modes. When the mode captures, VPTH is displayed on the EADI.
Page 213: Go--Around Mode
SPZ--8000 Digital Integrated Flight Control System GO--AROUND MODE The go--around mode is normally used to transition from an ILS approach to a climb out condition when a missed approach has occurred. The pilot selects go--around by pushing the GA button located on either outboard throttle handle.
Page 214: Troubleshooting
This section contains descriptions of troubleshooting methods and recommendations for writing accurate and complete pilot squawks, including descriptions of operations at time of occurrence. TECHNICAL SUPPORT To assist the pilot with troubleshooting, the following Honeywell Support Line is available: Honeywell Hot Line 602--436--4400 CAUTION THE FLIGHT CONTROL SYSTEM HAS BEEN DESIGNED TO EXHIBIT A HIGH DEGREE OF FUNCTIONAL INTEGRITY.
Page 215: Troubleshooting Digital Avionics
SPZ--8000 Digital Integrated Flight Control System TROUBLESHOOTING DIGITAL AVIONICS Maintenance of digital flight control systems requires a different approach than that of analog systems. Crew members and maintenance personnel can more effectively operate this digital system by understanding the differences between it and analog systems. Control law functions, once done with resistors, capacitors, coils, and op amps, are now programmed digitally with microprocessors.
Page 216: Flight Guidance System Typical Problems
SPZ--8000 Digital Integrated Flight Control System A digital system is more likely to have an external sensor problem (i.e., MADC, gyros, accelerometers, NAV/DME), than it is to have a problem with the avionics computers. The avionics computers perform extensive self--testing and continuous monitoring that positively affects maintainability and reliability.
Page 217: Lateral Mode Conditions/Problems
SPZ--8000 Digital Integrated Flight Control System Lateral Mode Conditions/Problems Figure 9--1 (cont) A28--1146--055 Troubleshooting REV 2...
Page 218 SPZ--8000 Digital Integrated Flight Control System Lateral Mode Conditions/Problems Figure 9--1 A28--1146--055 Troubleshooting REV 2...
Page 219: Vertical Mode Problems
SPZ--8000 Digital Integrated Flight Control System Vertical Mode Problems Refer to Table 9--3 and see Figure 9--2 for an in--flight pattern graphic representation of vertical mode problems. Mode Problems Air data hold modes (ALT, VS, Oscillates IAS, MACH) Porpoising Won’t hold reference Altitude preselect (ASEL) Misses capture Undershoots capture...
Page 220: Vertical Mode Conditions/Problems
SPZ--8000 Digital Integrated Flight Control System Vertical Mode Conditions/Problems Figure 9--2 A28--1146--055 Troubleshooting REV 2...
Page 221: Combined Vertical And Lateral Mode Problems
SPZ--8000 Digital Integrated Flight Control System Combined Vertical and Lateral Mode Problems Refer to Table 9--4 for combined vertical and lateral mode problems. Mode Problems Mode logic problems Modes won’t engage Modes won’t clear Autopilot problems Won’t engage Doesn’t follow commands Stick bump Stick buzz Combined Vertical and Lateral Mode Problems...
Page 222 Figure 9--5. Flight Fault Summary Figure 9--5 The alphanumeric codes should be recorded for use by Honeywell personnel in troubleshooting the problems. When the RESET button is pushed again, the fault data for the second flight guidance computer is displayed.
Page 223: Pilot Write--Up
SPZ--8000 Digital Integrated Flight Control System PILOT WRITE--UP Honeywell provides squawk check sheets on the back of flight plan forms (Honeywell Form Number 20323--000) to aid in flight planning and system troubleshooting. (See Figure 9--6.) The following paragraphs present general guidelines for making pilot write--ups for maintenance technicians.
Page 224: Pilot's Flight Plan Form And Squawk Sheet
SPZ--8000 Digital Integrated Flight Control System AD--62751--R1@ Pilot’s Flight Plan Form and Squawk Sheet Figure 9--6 A28--1146--055 Troubleshooting REV 2 9-11/(9-12 blank)
Page 225: Commonly Used Terms
SPZ--8000 Digital Integrated Flight Control System The description should define the problem and should always include specific conditions under which the problem exists, such as: Flags showing (which ones, if any) Mode or modes selected IAS when the problem occurs Period and magnitude of any oscillations Do any inputs fail to work (such as heading bug when in heading hold mode)?
Page 226: 10. Honeywell Product Support
All articles are returned to Reconditioned Specifications limits when they are processed through a Honeywell repair facility. All articles are inspected by quality control personnel to verify proper workmanship and conformity to Type Design and to certify that the article meets all controlling documentation.
Page 227 SPZ--8000 Digital Integrated Flight Control System The Honeywell Support Centers listed below will assist with processing exchange/rental orders. 24--HOUR EXCHANGE/RENTAL SUPPORT CENTERS U.S.A. -- DALLAS CANADA -- OTTAWA 800--872--7739 800--267--9947 972--402--4300 613--728--4681 ENGLAND -- BASINGSTOKE AUSTRALIA -- TULLAMARINE 44--1256--72--2200 61--3--9330--1411...
Page 228 MIAMI, FL 33122 TEL: 305--436--8722 FAX: 305--436--8532 CUSTOMER SUPPORT CENTERS -- REST OF THE WORLD United Kingdom Support Center France Support Center Honeywell Avionics Systems Ltd Honeywell Aerospace Edison Road, Ringway North 1 Rue Marcel--Doret, B.P.14 BASINGSTOKE, HANTS, 31701 BLAGNAC CEDEX,...
Page 229: Publication Ordering Information
Additional copies of this manual can be obtained by contacting: Honeywell Inc. P.O. Box 29000 Business and Commuter Aviation Systems Phoenix, Arizona 85038--9000 Attention: Publication Distribution, Dept. M/S V19A1 Telephone No.: (602) 436--6900 FAX: (602) 436--1588 E--MAIL CAS--publications--distribution@ CAS.honeywell.com A28--1146--055 Honeywell Product Support 10-4 REV 2...
Page 230: 11. Acronyms And Abbreviations
SPZ--8000 Digital Integrated Flight Control System 11. Acronyms and Abbreviations Abbreviations used in this manual are defined as follows: TERMS DEFINITION Attitude Director Indicator Air Data System AFCS Automatic Flight Control System Above Ground Level ALIGN Alignment Altitude ANSI American National Standards Institute AOSS After Over Station Sensor Autopilot...
Page 231 SPZ--8000 Digital Integrated Flight Control System TERMS DEFINITION Decision Height DIFCS Digital Integrated Flight Control System Distance Distance Measuring Equipment DSPL Display Desired Track EADI Electronic Attitude Director Indicator EFIS Electronic Flight Instrument System EGPWS Enhanced Ground Proximity Warning System EHSI Electronic Horizontal Situation Indicator EMER...
Page 232 SPZ--8000 Digital Integrated Flight Control System TERMS DEFINITION Left Lateral Beam Sensor Lateral Navigation Localizer Long Range Navigation Lightning Sensor System LTRK LASERTRAK Lightning Sensor System Mach Multifunction Display System Middle Marker MPEL Maximum Permissible Exposure Level Message Mean Sea Level Mode Select Unit Magnetic True Navigation...
Page 233 SPZ--8000 Digital Integrated Flight Control System TERMS DEFINITION Static Air Temperature SBY, STBY Standby SECT Sector Select Symbol Generator Skip Slaved SPEX Spares Exchange Source STAB Stabilization Sensitivity Timing Control Status System True Airspeed Total Air Temperature TCAS Traffic Alert And Collision Avoidance System Touch Control Steering Target Time...
Page 234 SPZ--8000 Digital Integrated Flight Control System TERMS DEFINITION Wind Direction Weight--On--Wheels Waypoint Wind Speed Weather Radar XDATA Cross--Side Data Transfer XMTR Transmitter Crosstrack Yaw Damper A28--1146--055 Acronyms and Abbreviations REV 2 11-5/(11-6 blank)
Page 235: Inertial Reference System (Irs
This brief description is a summary of the operation of the LASEREF II and III. For a detailed description of system operation, refer to Honeywell Pub. No. M95--8172--000 (LASEREF II Model No. YG1779) or M28--3343--001 (LASEREF III Model No. YG4004AB).
Page 236: A--1 Laseref Irs Interface Diagram
SPZ--8000 Digital Integrated Flight Control System A typical LASEREF IRS installation, shown in Figure A--1, interfaces with the following associated equipment: Automatic flight control system Flight management system Digital air data computer Electronic flight instrument system Weather radar. LASEREF IRS Interface Diagram R R R R Figure A--1 A28--1146--055...
Page 237: Inertial Reference Unit (Iru
SPZ--8000 Digital Integrated Flight Control System INERTIAL REFERENCE UNIT (IRU) The IRU is the main electronics assembly of the IRS. The IRU contains an inertial sensor assembly, microprocessors, power supplies, and aircraft electronic interfaces. Accelerometers and laser gyros in the inertial sensor assembly measure aircraft accelerations and angular rates.
Page 238: Mode Select Unit (Msu
SPZ--8000 Digital Integrated Flight Control System MODE SELECT UNIT (MSU) The MSU, shown in Figure A--2, is used to make IRU mode selection, display IRS status, and initiate the remote test. As many as three MSUs can be installed. Refer to Figure A--2 for the locations of annunciators and controls described below.
Page 239: Annunciators
SPZ--8000 Digital Integrated Flight Control System NAV--To--ALIGN--To--NAV -- The IRU enters ALIGN downmode from the NAV mode and, after 30 seconds, automatically re--enters the NAV mode when the downmode alignment is complete. ALIGN--To--ATT Or NAV--To--ATT -- The IRU enters the erect attitude submode for 20 seconds.
Page 240: Power--On And Alignment Operation
SPZ--8000 Digital Integrated Flight Control System POWER--ON AND ALIGNMENT OPERATION The power--on and alignment procedure is given in Table A--1. Step Procedure Verify that MSU mode select switch is set to OFF. CAUTION NAVIGATION PERFORMANCE MAY BE DEGRADED IF THE IRU IS ALIGNED AT LATITUDES ABOVE 70_ _ _ _ . Set aircraft circuit breakers for IRU to ON position.
Page 241: Inertial System Display Unit (Isdu
SPZ--8000 Digital Integrated Flight Control System INERTIAL SYSTEM DISPLAY UNIT (ISDU) The ISDU, shown in Figure A--3, is used to enter the aircraft’s present position directly to any of the installed IRUs. It also displays several IRS parameters. It is intended as a backup interface to the IRS systems. Inertial Reference System Display Unit Figure A--3 NOTES:...
Page 242 SPZ--8000 Digital Integrated Flight Control System Below is a brief description of the controller switch functions. System Display Switch (SYS DSPL) -- This switch turns the ISDU on, and selects the IRS from which data is displayed. Display Select Switch (DSPL SEL) -- This switch selects the parameters to be displayed on the selected IRS as follows: —...
Page 243: Lasertrak
IRUs. A left--right course deviation display is shown on either a stand--alone unit or on the EHSI. A brief description of the controller is given below. For a complete description, refer to Honeywell Pub. No. M95--8440. NDU Front Panel Figure A--4...
Page 244 SPZ--8000 Digital Integrated Flight Control System System Select Keyboard -- The system select keyboard is used to select the active IRU. Data Select Keyboard -- This keyboard selects the following data for display: — WPT -- Displays latitude/longitude in the data display and the waypoint number in the WPT window.
Page 245: R 650 Weather Radar System
After proper evaluation, the crew can chart a course to avoid storm areas. This appendix gives a brief summary of the system operation. For complete operating instructions on the PRIMUS 650 Weather Radar System, refer to Honeywell Pub. No. A28--1146--048. A28--1146--055 PRIMUS 650 Weather Radar System REV 2...
Page 246: Description
SPZ--8000 Digital Integrated Flight Control System DESCRIPTION The PRIMUS 650 Weather Radar System consists of the following components: Receiver transmitter antenna (RTA) Weather radar controller. NOTE: Two radar controllers can be installed. When a single controller is used, all weather radar displays show the same radar data.
Page 247: Weather Radar Controller Operation
SPZ--8000 Digital Integrated Flight Control System WEATHER RADAR CONTROLLER OPERATION Controls and display features described below are numbered to match the numbered callouts in Figure B--1. Lighting for all annunciators and controls is controlled by the dimming bus for the aircraft panel. Weather Radar Controller Figure B--1 RANGE Buttons...
Page 248 SPZ--8000 Digital Integrated Flight Control System STAB (Stabilization) Button Pushing the STAB button toggles attitude stabilization on and off. When turned off, OFF is annunciated above the button. TGT (Target) Button Pushing the TGT button toggles the radar target alert feature on and off. Target alert is selectable in all but the 300--mile range.
Page 249 CLR/TST (Clear/Test) -- In this position accumulated data is cleared from the memory of the LSS. After 3 seconds the LSS test mode is initiated. Refer to the LSZ--850 Lightning Sensor System Pilot’s Handbook (Honeywell Pub. No. A28--1146--054) for a detailed description of LSS operation. SLV (Slaved) Annunciator In dual controller installations, the displayed weather data on one side can be slaved to the opposite side controller.
Page 250 SPZ--8000 Digital Integrated Flight Control System RADAR Mode Select Switch The following paragraphs explain the switch positions for the RADAR mode select switch: OFF -- For a single controller installation, this mode turns the controller functionally off. Electrical power is not switched off until the avionics bus is turned off.
Page 251 SPZ--8000 Digital Integrated Flight Control System FP (Flight Plan) --The FP position puts the radar system in the flight plan mode. In the flight plan mode, the radar data is cleared from the display and other data is displayed (i.e., navigation displays, electrical discharge (lightning) data).
Page 252: Weather Radar Operating Procedures
SPZ--8000 Digital Integrated Flight Control System WEATHER RADAR OPERATING PROCEDURES Preliminary Control Settings Place the system controls in the following positions before applying power from the aircraft electrical system. Mode Control -- OFF GAIN Control -- Preset Position TILT Control -- +15 Precautions If the radar system is to be operated in any mode other than standby while the aircraft is on the ground:...
Page 253: Standby
SPZ--8000 Digital Integrated Flight Control System Standby When standby is selected, the antenna is stowed in a tilt--up position and is neither scanning nor transmitting. If two controllers are installed, both must be selected to standby for the system to be in standby. Standby should be selected any time the operator wants to keep system power on without transmitting.
Page 254: Self--Test
SPZ--8000 Digital Integrated Flight Control System Self--Test The TST position selects the radar test mode. The test pattern is described Figure B--2. EFIS Test Pattern (Typical) 120    Scan (WX) Figure B--2 A28--1146--055 PRIMUS 650 Weather Radar System B--10 REV 2...
Page 255 SPZ--8000 Digital Integrated Flight Control System If a failure is detected during TEST mode, a corresponding fault code is displayed next to the TEST mode field, as described in Table B--2. EFIS Fault Fault Description Code No fault detected. The antenna is not scanning or it is not scanning correctly.
Page 256: In--Flight Roll Compensation Adjustment Of The Primusr
SPZ--8000 Digital Integrated Flight Control System In--Flight Roll compensation Adjustment of the PRIMUS 650 Weather Radar System Table B--3 describes the in--flight roll compensation adjustment procedure for the PRIMUS 650 Weather Radar platform. Step Procedure If two controllers are installed, one must be turned off. If an indicator is used as the controller, the procedure is the same as given below.
Page 257: Tilt Management
SPZ--8000 Digital Integrated Flight Control System TILT MANAGEMENT Figures B--3 and B--4 are visual aids that show the relationship between tilt angle, flight altitude, and selected range. The figures show the distance above and below aircraft altitude that is illuminated by the flat--plate radiator during level flight with 0_ tilt, and a representative low altitude situation with the antenna adjusted for 2.8_ up--tilt.
Page 258: Maximum Permissible Exposure Level (Mpel
Radio Frequency Electronic Fields 3kHz to 300 GHz (IEEE C95.1--1991), recommends an exposure level of no more than 5 mW/cm Honeywell Inc. recommends that operators follow the 5 mW/cm standard. Figure B--5 shows MPEL for both exposure levels. Maximum Permissible Exposure Level Boundary...
Page 259: R 870 Weather Radar
This appendix gives a brief summary of the system operation. For complete operating instructions on the PRIMUS 870 Weather Radar System, refer to Honeywell Pub. No. A28--1146--056. A28--1146--055 PRIMUS 870 Weather Radar REV 2...
Page 260: Description
SPZ--8000 Digital Integrated Flight Control System DESCRIPTION The PRIMUS 870 Weather Radar System consists of the following components: Weather radar receiver transmitter antenna (RTA) Weather radar controller. NOTE: Two radar controllers can be installed. When a single controller is used, all weather radar displays show the same radar data.
Page 261: Weather Radar Controller Operation
SPZ--8000 Digital Integrated Flight Control System WEATHER RADAR CONTROLLER OPERATION Controls and display features described below are numbered to match the numbered callouts in Figure C--1. Lighting for all annunciators and controls is controlled by the dimming bus for the aircraft panel. Weather Radar Controller Figure C--1 Range Buttons...
Page 262 A complete description of turbulence detection capabilities can be found in the PRIMUS 870 Weather Radar System Pilot’s Manual (Honeywell Pub. No. A28--1146--056). GCR (Ground Clutter Reduction) Button Pushing the GCR button enables and disables the GCR circuitry. When GCR is selected the GCR annunciator is displayed on the EFIS/MFD.
Page 263 SPZ--8000 Digital Integrated Flight Control System TGT (Target) Button Pushing the TGT button toggles the radar target alert feature on and off. Target alert is selectable in all but the 300--mile range. In target alert mode, the system monitors beyond the selected range and 7.5 on each side of the aircraft heading.
Page 264 SPZ--8000 Digital Integrated Flight Control System SECT (Sector Scan) Button Pushing the SECT button toggles between full azimuth (120_) or sector scan (60_). In sector scan the display is updated more often since the antenna sweeps a shorter arc than in full azimuth mode. TILT Knob The TILT knob selects the tilt angle of the antenna beam relative to the horizon.
Page 265 CLR/TST (Clear/Test) -- In this position accumulated data is cleared from the memory of the LSS. After 3 seconds the LSS test mode is initiated. Refer to the Honeywell’s LSZ--850 Lightning Sensor System Pilot’s Handbook, Pub No. A28--1146--054, for a detailed description of LSS operation.
Page 266 SPZ--8000 Digital Integrated Flight Control System WX -- This position selects the weather mode. In the weather mode the system is fully operational and WX is displayed in the mode field. If WX is selected before the initial RTA warmup period is over, WAIT is displayed in the mode field.
Page 267 SPZ--8000 Digital Integrated Flight Control System WARNING WEATHER TYPE TARGETS ARE NOT CALIBRATED WHEN THE RADAR IS IN THE GMAP MODE. BECAUSE OF THIS, DO NOT USE THE GMAP MODE FOR WEATHER DETECTION. As a constant reminder that the system is in the ground mapping mode, the alphanumerics are changed to green and the color...
Page 268 SPZ--8000 Digital Integrated Flight Control System TST (Test) -- The TST position selects the radar test mode. A test pattern is displayed to verify system operation. TEST is displayed in the mode field. For test patterns and fault code descriptions, see the self--test section of this appendix.
Page 269 SPZ--8000 Digital Integrated Flight Control System GAIN knob The GAIN knob is a rotary control and push/pull switch that controls the receiver gain. Push the GAIN knob in to put the system into preset (calibrated) gain mode. Preset gain is the normal mode of operation and is recommended for weather avoidance.
Page 270: Weather Radar Operating Procedures
SPZ--8000 Digital Integrated Flight Control System WEATHER RADAR OPERATING PROCEDURES Preliminary Control Settings Place the MODE control, GAIN control, and TILT control, as shown below, before powering up the aircraft electrical system. Mode Control -- Off GAIN Control -- Preset Position TILT Control -- +15 Precautions If the radar system is to be operated in any mode other than standby...
Page 271: Standby
SPZ--8000 Digital Integrated Flight Control System Standby When standby is selected, the antenna is stowed in a tilt--up position and is neither scanning nor transmitting. If two controllers are installed, both must be selected to standby for the system to be in standby. Standby should be selected any time the operator wants to keep system power on without transmitting.
Page 272: Self--Test
SPZ--8000 Digital Integrated Flight Control System Self--Test The TST position selects the radar test mode. The test pattern is described in Figure C--2. EFIS Test Pattern (Typical) 120    Scan Shown Figure C--2 A28--1146--055 PRIMUS 870 Weather Radar C--14 REV 2...
Page 273 SPZ--8000 Digital Integrated Flight Control System If a failure is detected during TEST mode, a corresponding fault code is generated. Fault codes are displayed as part of the FAIL annunciator i.e., FAIL “N”, where “N” is the fault code. (Refer to Table C--3.) NOTES: 1.
Page 274: 870 Weather Radar System
SPZ--8000 Digital Integrated Flight Control System In--Flight Roll Compensation Adjustment of the PRIMUS 870 Weather Radar System r r r r Table C--4 describes in--flight roll compensation adjustment procedure for the PRIMUS 870 Weather Radar platform. Step Procedure If two controllers are installed, one must be turned off. If an indicator is used as the controller, the procedure is the same as given below.
Page 275: Tilt Management
SPZ--8000 Digital Integrated Flight Control System TILT MANAGEMENT Figures C--3 and C--4 show the relationship between tilt angle, flight altitude, and selected range. The figures show the distance above and below aircraft altitude that is illuminated by a 12 inch flat--plate radiator during level flight with 0_ tilt, and a representative low--altitude situation, with antenna adjusted for 2.8_ up--tilt.
Page 276: Maximum Permissible Exposure Level (Mpel
The American National Standards Institute, in their document ANSI C95.1--1982, recommends an exposure level of no more than 5 mW/cm Honeywell Inc. recommends that operators follow the 5 mW/cm standard. Figure C--5 shows the MPEL for PRIMUS 870 radar power.
Page 277: System (Optional
SPZ--8000 Digital Integrated Flight Control System Appendix D Enhanced Ground Proximity Warning System (Optional) The enhanced ground proximity warning system (EGPWS) is a terrain proximity warning system that combines information from aircraft navigation equipment, i.e., global positioning system (GPS), IRS, FMS, radar altimeter, with stored terrain data to give the pilot a radar--like display of terrain along the flightpath.
Page 278: Single Weather Radar Controller
SPZ--8000 Digital Integrated Flight Control System Single Weather Radar Controller With a single weather radar controller, pushing the MFD EGPWS switch toggles the display in the following sequence: Terrain data with map  terrain data only  terrain data with map. If the WX ONLY display is disabled, pushing the MFD EGPWS switch only displays terrain data with map.
Page 279: Limited System Operation
SPZ--8000 Digital Integrated Flight Control System LIMITED SYSTEM OPERATION The limited system is controlled with one cockpit--mounted toggle switch that controls the MFD. Push the EGPWS (terrain) switch to select terrain data for display. The display automatically switches to the map mode. Terrain cannot be displayed in the plan mode.
Page 280 SPZ--8000 Digital Integrated Flight Control System Figure D--1 shows the EGPWS over KPHX airport at 3000 feet MSL, heading north. The terrain shows the mountains to the north of Phoenix. AD--64771@ EHSI Display Over KPHX Airport With the EGPWS Display Figure D--1 Figure D--2 shows the EGPWS on the MFD.
Page 281 SPZ--8000 Digital Integrated Flight Control System When the EGPWS is selected for display, it can be tested. Push the EGPWS TEST button to display the test format shown in Figure D--3. AD--64773@ EGPWS Test Display Figure D--3 A28--1146--055 Enhanced Ground Proximity Warning System (Optional) REV 2 D--5/(D--6 blank)
Page 282 SPZ--8000 Digital Integrated Flight Control System Index Automatic flight control system (AFCS), 6-1 flight guidance controller, 6-2 Abbreviations, 11--1 turn pitch controller, 6-5 Acronyms, 11--1 Advisory display, 6-6 annunciators and messages, 6-8 advisory caution message (steady), 6-14 Back course mode, 8-23 AFCS status message Barometric altimeter, 3-3 annunciators, 6-10...
Page 283 SPZ--8000 Digital Integrated Flight Control System Index (cont) PRIMUS 650 Weather Radar HSI DIM knobs, 4-4 Controller (cont) MAP button, 4-2 RADAR mode select switch, TST button, 4-4 B--6 V/L button, 4-3 RANGE buttons, B--3 WX button, 4-2 RCT button, B--3 WX DIM knob, 4-4 SECT button, B--5 Displays:...
Page 284 SPZ--8000 Digital Integrated Flight Control System Index (cont) map mode with FMS selected localizer pointer, localizer scale, for display, 4-52 and rising runway, 4-12 map mode with VOR selected Mach display, 4-13 for display, 4-49 marker beacon, 4-11 NAV source reversion, 4-59 maximum velocity indicator, weather radar displays, 4-54 4-14...
Page 285 SPZ--8000 Digital Integrated Flight Control System Index (cont) Electronic attitude director indicator course--desired track display, (EADI) (cont) 4-41 typical display presentations, 4-15 distance display, 4-44 approach capture tracking elapsed time display, 4-42 below DH, 4-19 FMS drift bug, 4-41 climb to initial altitude, 4-16 FMS message annunciator, enroute cruise, 4-17 4-41...
Page 286 SPZ--8000 Digital Integrated Flight Control System Index (cont) typical full compass display indicated airspeed failure, 4-34 presentations, 4-45 localizer failure, 4-35 weather radar displays, 4-54 radio altitude failure, 4-35 mode annunciator (WX and symbol generator internal NAV/WX formats only), 4-55 failure, 4-35 range ring and annunciator TCAS messages and failure...
Page 287 Heading hold mode and wings power--on/alignment operation, level, 8-1 A--6 Heading select mode, 8-3 Lateral mode problems, 9-3 Honeywell product support, 10-1 Lightning sensor system (LSS) 24--hour exchange/rental support (optional), 2-10 centers, 10-2 Localizer (NAV) mode, 8-17 Customer support centers, 10-2...
Page 288 SPZ--8000 Digital Integrated Flight Control System Index (cont) pitch attitude hold mode, 8-40 weather radar, 5-20 preselected course approach, 8-28 roll hold mode, 8-2 vertical navigation modes, 8-50 altitude hold , 8-50 altitude select, 8-50 Navigation display unit, A--9 flight level change, 8-50 vertical path mode, 8-51 vertical speed hold mode, 8-41 VOR (NAV) mode, 8-4...
Page 289 SPZ--8000 Digital Integrated Flight Control System Index (cont) PRIMUS 870 Weather Radar power--on alignment, A--6 System, 2-8, C--1 VOR (NAV) mode engage, 8-4 controller, C--3 VOR DIRECT TO function, 8-12 GAIN knob, C--11 Publication ordering information, GCR button, C--4 10-4 LSS select switch (optional), C--7 mode select switch, C--7...
Page 290 SPZ--8000 Digital Integrated Flight Control System Index (cont) vertical path mode, 8-51 Vertical speed hold mode, 8-41 Vertical speed indicator, 3-5 Takeoff using go--around mode, 4-15 VOR (NAV) mode, 8-4 Target alert warning, activation, B--4 approach mode, 8-11 Technical support, 9-1 DIRECT TO function, 8-12 Traffic alert and collision avoidance over station operation, 8-11...
Page 291 SPZ--8000 Digital Integrated Flight Control System Index (cont) PRIMUS 650 Weather radar System (cont) precautions, B--8 preliminary control settings, B--8 radar mode -- ground mapping, B--9 radar mode -- weather, B--9 self--test, B--10 standby, B--9 tilt management, B--13 PRIMUS 870 , C--1 description, C--2 in--flight compensation adjustment, C--16...

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