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Honeywell SPZ-8000, Maintenance Manual

The Honeywell SPZ-8000 Pilot's Manual is a comprehensive guide for aviators seeking detailed information on operating this advanced flight control system. Download the manual for free from our website and gain complete knowledge of this cutting-edge product, ensuring a seamless and informed flying experience.

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Summary of Contents for SPZ-8000

Page 1: ...neywell Inc BOX 29000 Phoenix Arizona 85038 SPZ 8000 Digital Automatic Flight Control System Gulfstream IV System Maintenance Manual Volume I System and Component Description and System Operation 22 14 00 TITLE PAGE T 1 PRINTED IN U S L PUB NO Al 5 1146 38 REVISED 15 APRIL 1993 1 JUNE 1987 ...

Page 2: ...f recipient s equipment NOTICE FREEDOM OF INFORMATION ACT 5 USC 552 AND DISCLOSURE OF CONFIDENTIAL INFORMATION GENERALLY 18 USC 1905 This document is being furnished in confidence by Honeywell Inc The information disclosed herein falls within exemption b 4 of 5 USC 552 and the prohibitions of 18 USC 1905 S93 LASEREF and PR MIJS are registered trademarks of Honeywe f Inc COLORCAL COLORARAR and LASE...

Page 3: ...mes all comments and recommendations to improve future editions of this publication Your Name Company Airline State Country Zip Telephone No FAX Date Honeywell Pub No ATA No Manual Title COMMENTS RECOMMENDATIONS LOCAL REPRODUCTION ENCOURAGED If returning by mail please tape closed Postal regulations prohibit use of staples ...

Page 4: ...FOLD From Place StampHere Honeywell Commercial Flight Systems Group Business and Commuter Aviation Systems Division Logistics Quality Administrator MS AV2CC85C3 P O Box 29000 Phoenix AZ 85038 9000 FOLD FOLD ...

Page 5: ...ny Airline Received Address State Country Zip Telephone No FAX Date Honeywell Pub No ATA No Manual Title PAGE NO PARA GRAPH FIGURE NO TABLE NO PROBLEM I HONEYWELL REPLY APPROVAL LOCAL REPRODUCTION ENCOURAGED If returning by mail please tape closed Postal regulations prohibit use of staples ...

Page 6: ...FOLD From Place Stamp Here Honeywell Commercial Flight Systems Group Business and Commuter Aviation Systems Division Logistics Quality Administrator MS AV2CC85C3 P O Box 29000 Phoenix AZ 85038 9000 FOLD FOLD ...

Page 7: ...Revisions The initials HI show Honeywell Inc is the incorporator Revision Revision Insertion Number Date Date By Revision Revision Insertion Number Date Date By 01 02 03 04 05 06 Feb 1 88 Mar 1 89 Ott 1 89 Mar 15 91 Aua 15 91 Ai r 15 93 Mar 1 88 ADr 15 89 ADr 15 91 Nov 1 91 Jul 1 93 HI HI HI HI HI HI 22 14 00 Page RR 1 RR 2 Aug 15 91 Use 01 disclosure of information on this page is subject to the ...

Page 8: ...6 6 6 6 6 6 6 6 6 6 6 6 6 Revision 4 Mar 15 91 Revision 5 Aug 15 91 Revision 6 Apr 15 93 SUBHEADING AND PAGE TC 20 TC 21 TC 23 TC 24 Introduction INTRO 1 INTRO 2 INTRO 3 INTRO 4 INTRO 5 INTRO 6 INTRO 7 INTRO 8 INTRO 9 INTRO 10 INTRo 11 INTRo 12 System Description 3 4 4 1 4 2 F 5 6 F 7 8 9 10 11 12 13 14 15 16 17 18 18 1 18 2 m REVISION 6 6 6 6 6 6 6 6 6 6 6 6 6 6 6 6 6 6 6 6 5 6 6 6 5 5 6 5 6 6 6 ...

Page 9: ... 5 5 6 5 5 6 6 6 6 6 6 8 6 6 6 6 6 6 6 WW JANCE GULFSTREAMIV SUBHEADING AND PAGE 128 12 128 13 128 14 129 130 131 132 133 134 135 136 F 137 138 139 140 141 142 143 144 145 146 147 148 149 150 151 152 153 154 155 156 157 158 159 160 161 162 163 164 165 166 166 1 166 2 F 167 168 F 169 170 171 172 173 174 175 176 177 178 179 180 181 182 8 m REVISION 6 6 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 2 5 5 6 6 6...

Page 10: ...NTENANCE MANUAL GULFSTREAMIV SUBHEADING AND PAGE REVISION 198 36 198 37 198 38 198 39 198 40 198 41 198 42 198 43 198 44 198 45 198 46 198 47 198 48 198 49 198 50 198 51 198 52 198 53 198 54 F 198 55 198 56 198 57 198 58 198 59 198 60 F 198 61 198 62 198 63 198 64 198 65 198 66 F 198 67 198 68 F 198 69 198 70 198 71 198 72 198 73 198 74 F 198 75 198 76 198 77 198 78 198 79 198 80 F 198 81 198 82 1...

Page 11: ...6 6 6 6 6 5 5 5 5 6 5 5 5 5 6 6 6 5 5 5 5 5 5 5 5 5 MAINTENANCE MANUAL GULFSTREAMIV SUBHEADING AND PAGE 198 153 198 154 198 155 198 156 198 157 198 158 198 159 198 160 198 161 198 162 198 163 198 164 198 165 198 166 198 167 198 168 198 169 198 170 198 171 198 172 198 173 198 174 198 175 198 176 198 177 198 178 198 179 198 180 198 181 198 182 198 183 198 184 198 185 198 186 198 187 198 188 198 189 ...

Page 12: ... 5 6 5 5 5 5 6 5 6 6 6 5 5 6 6 6 6 6 5 5 5 5 5 6 MAINTENANCE MANUAL GULFSTREAMIV SUBHEADING AND PAGE 243 244 245 246 247 248 249 250 251 252 253 254 255 256 257 258 259 260 261 262 263 264 265 266 F 267 268 269 270 271 272 273 274 275 276 277 278 279 280 281 282 283 284 285 286 287 288 289 290 291 292 293 294 m REVISION 5 5 6 6 5 6 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 5 6 5 z 5 5 z 5 5 5 5 5 6 5 5 ...

Page 13: ...STREAMIV SUBHEADING AND PAGE 298 36 11 298 36 12 298 36 13 298 36 14 298 36 15 298 36 16 298 36 17 298 36 18 298 37 298 38 298 39 298 40 298 41 298 42 298 43 298 44 298 45 298 46 298 47 298 48 298 49 298 50 F 298 51 298 52 F 298 53 298 54 F 298 55 298 56 F 298 57 298 58 298 59 298 60 298 61 298 62 298 63 298 64 298 65 298 66 298 67 298 68 298 69 298 70 298 71 298 72 298 73 298 74 298 75 298 76 F 2...

Page 14: ... 5 5 i 5 6 5 5 6 6 6 5 6 MAINTENANCE MANUAL GULFSTREAMIV SUBHEADING AND PAGE 298 152 F 298 153 298 154 298 155 298 156 298 157 298 158 298 159 298 160 298 161 298 162 F 298 163 298 164 298 165 298 166 298 166 1 298 166 2 298 167 298 168 298 169 298 170 298 171 298 172 298 173 298 174 298 175 298 176 298 176 1 298 176 2 298 177 298 178 298 179 298 180 298 181 298 182 298 183 298 184 298 185 298 186...

Page 15: ...298 214 6 298 215 298 216 298 217 298 218 298 219 298 220 298 221 298 222 298 223 198 224 REVISION SUBHEADING AND PAGE REVISION 9 6 6 6 6 6 8 6 5 6 5 5 6 5 5 2 22 14 00 Page LEP 8 Apr 15 93 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 16: ...18 18 4 18 5 18 5 3 Avionics Standard Communications Bus ASCB Description 19 Coml onentDescription General LASEREF II Inertial Reference System IRS A Inertial Reference Unit B Mode Select Unit Inertial System Display Unit ISDU Optional LASERTRAKW Navigation Display Unit NDU 3 ADZ 81O Air Data System 4 AA 300 Radio Altimeter System A RT 300 Radio Altimeter Receiver Transmitter B AT 222 Radio Altime...

Page 17: ...ter B CD 81O Control Display Unit C DL 800 or DL 900 Data Loader D PZ 800 Performance Computer E SM 81O Servo Autothrottle 10 Engine Pressure Ratio EPR System 11 Optional VLF Omega System A OZ 800 Receiver Processor Unit RPU B AT 800 Antenna Coupler Unit ACU Teardrop H Field C AT 801 Antenna Coupler Unit ACU Brick H Field D AT 803 Antenna Coupler Unit ACU Blade E Field 12 Optional LSZ 850 Lightnin...

Page 18: ...t Display PFD Navigation Display ND Formats Engine ENG Display Crew Alerting System CAS Display System Page Displays Compacted EICAS Display EFIS EICAS Reversionary Modes Traffic Alert and Collision Avoidance System TCAS Displays Microwave Landing System MLS 3 DFZ 820 Dual Flight Guidance System A System Performance OperatingLimits 198 192 198 192 198 196 198 204 198 204 201 201 202 202 202 206 22...

Page 19: ...io Altimeter System A Preflight Test B In Flight Test 6 EDZ 884 Electronic Display System EDS A Trend and Limit Monitoring B Troubleshooting Display Unit Red X ing 7 DFZ 820 Flight Guidance System A List of Flow Chart Figures B List of Tables 8 PRIMUS 870 Weather Radar System 9 FMZ 800 Flight Management System FMS A Airborne Logic B Runway Alignment Estimated Time Enroute k Descent Time and Fuel P...

Page 20: ...er DC 884 Display Controller CD 81O Control Display Unit DL 800 900 Data Loader or DP 884 Dimmer Panel Procedure for AZ 81O Digital Air Data Computer FZ 820 Flight Guidance Computer SG 884 Symbol Generator FC 880 Fault Warning Computer DA 884 Data Acquisition Unit or PZ 800 Performance Computer Procedure for RT 300 Radio Altimeter Receiver Transmitter Procedure for AT 222 Radio Altimeter Antennas ...

Page 21: ... TCAS Directional Antenna i Procedure for AT 800 AT 803 Antenna Coupler Unit 16 Procedure for AT 850 Antenna 17 Procedure for AT 855 Antenna and AT 801 Antenna Coupler Unit 18 Procedure for Updating the Navigation Database 9 Shiminq Handlinq and Storaqe 713 713 714 715 716 716 716 801 22 14 00 Page TC 6 Apr 15 93 Use or disclosure of informationon this page is subject to the restrictions on the ti...

Page 22: ...ode Select Unit Mode Select Unit Schematic Diagram Inertial System Display Unit SYS DSPL Switch ISDU Wiring Diagram Navigation Display Unit NDU Wiring Diagram AZ 81O Digital Air Data Computer AZ 81O Digital Air Data Computer Block Diagram RT 300 Radio Altimeter Receiver Transmitter RT 300 Radio Altimeter Receiver Transmitter Block Diagram AT 222 Radio Altimeter Antenna DU 880 Display Unit Display ...

Page 23: ...er Declutter Mode MAP Mode Menu Comp Mode Menu Plan Mode Menu NAV Mode Menu Preview Mode Submenu SENSOR Mode Menu FLT REF Mode Menu Main TRS Mode Menu TRS Mode Submenu SYSTEM Mode Menu CHECKLIST Mode Submenu TEST Mode Menu DISP Mode Menu NAV Mode Menu with MLS Selected Preview Mode Submenu with MLS Selected MAP Mode Menu with TCAS Selected Paqe 148 151 153 156 167 172 175 175 180 180 183 183 186 1...

Page 24: ...Computer Checklist Module Block Diagram Flight Guidance Computer Flight Guidance Computer Block Diagram Flight Guidance Controller Flight Guidance Controller Block Diagram Turn Turn Dual Dual Dual Dual Pitch Controller Pitch Controller Schematic Servo and SB 600 Bracket Trim Servo and TB 261 Bracket Servo Schematic Trim Servo Schematic Bracket Schematic Receiver Transmitter Receiver Transmitter Bl...

Page 25: ...iagram NZ 920 Navigation Computer NZ 920 Navigation Computer Block Diagram CD 81O Control Display Unit CD 81O Control Display Unit Block Diagram DL 800 Data Loader DL 900 Data Loader DL 800 900 Data Loader Block Diagram PZ 800 PZ 800 SM 81O SM 81O Engine Engine Performance Computer Performance Computer Servo Autothrottle Servo Schematic Block Diagram Pressure Ratio Transmitter Pressure Ratio Trans...

Page 26: ...850 Antenna AT 855 Antenna RT 91O TCAS Computer RT 91O TCAS Computer Block Diagram AT 91O Directional Antenna Typical Bottom Omnidirectional Antenna ML 850 MLS Receiver ML 850 MLS Receiver Block Diagram CM 850 MLS Control Display Unit CM 850 MLS Control Display Unit Block Diagram Global Positioning System Sensor Unit Leading Particulars Global Positioning System Sensor Unit Block Diagram 198 160 1...

Page 27: ... Indications IRS DADC PFD Failure Indications Mist IRS Test Mode Indications Map Mode Format Map Mode With Vertical Profile Map Mode With Weather Radar Display Vertical Profile Symbols Map Caution Warning Displays IRS Test Mode Display Compass Mode Display Format COMP Navigation Preview Mode NAV Compass Caution Warning Displays IRS Compass Caution Warning Displays Mist Plan Mode Display Format PLA...

Page 28: ...lic System Page Hydraulic System Page Failure Indications Fuel System Page Display Fuel System Page Failure Indications APU BLEED System Page Display APU BLEED System Page Failure Indications Engine Start Page Display Engine Start Page Failure Indications Engine APU Exceedances Page No Exceedances Recorded Format Exceedance Data Failure Indications Checklist System Page Display Checklist System Cu...

Page 29: ...on the System Page Display TCAS Resolution Advisory Test on the Primary Flight Display TCAS Extended Test on System Page Display MLS Displays on the Primary Flight Display MLS Active Mode Displays on the Navigation Display MLS Preview Mode Displays on the Navigations Displays AP YD MACH TRIM and PFD CMD Select Diagram 298 24 298 26 298 28 298 29 298 30 298 31 298 35 298 36 298 36 6 298 36 7 298 36...

Page 30: ...6 1 Basic Autothrottle Functions Over the Flight Profile 298 181 Autothrottle Switch Locations on Power Levers Autothrottle Engage Logic Diagram Autothrottle Arm Takeoff and Hold Mode Select 298 186 298 189 Diagram 298 193 Autothrottle Flight Level Change Speed IAS MACH and Go Around Mode Select Diagram 298 199 Autothrottle Mode Flow Diagram 298 205 Climb Phase with No Descents 298 214 Climb Phase...

Page 31: ... Range for the Gulfstream IV Altitude Alerting Sequence DADC AOA Block Diagram Exceedance System Page Format Diagnosing Symptoms Both FZ 820S Failing Power Up FGC 1 and 2 FAIL Messages on EICAS Single FZ 820 Failing Power Up FGC 1 or 2 FAIL Annunciated Unintended Priority Transfers AP YD or Trim Engagement Inhibited AP YD and Trim Disengagement All Engaged Functions AP or Trim Disengagement YD is ...

Page 32: ...s etc Correct Orientation of AT 222 Antennas Data to be Loaded Display Transfer of NAV Database Display Confirm Transfer of NAV Database Display Percent Complete of Transfer Display Completion of Transfer Display Paqe 458 459 705 717 717 718 718 719 22 14 00 Page TC 17 Apr 15 93 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 33: ...Inertial System Display Unit ARINC 429 Digital Output Data Inertial System Display Unit ARINC 429 Digital Input Data ARINC 429 IRU Discrete Word Octal Label 270 Paqe 1 18 2 18 2 21 24 103 104 107 111 116 119 124 128 128 128 1 ARINC 429 Time to NAV Ready Discrete Word Octal Label 351 128 2 Navigation Display Unit Leading Particulars 128 4 Navigation Display Unit ARINC 429 Digital Output Data 128 8 ...

Page 34: ...isplay Controller MLS Output Discrete Logic DC 884 Display Controller ASCB Transmitted Data DC 884 Display Controller Part No 7007540 941 942 ASCB Transmitted Data Changes for TCAS MLS Option DA 884 Data Acquisition Unit Leading Particulars DA 884 Data Acquisition Unit ASCB Transmitted Data DP 884 Dimmer Panel Leading Particulars FC 880 Fault Warning Computer Leading Particulars FC 880 Fault Warni...

Page 35: ...800 DL 900 PZ 800 PZ 800 SM 81O Engine Control Display Unit Leading Particulars Data Loader Leading Particulars Data Loader Leading Particulars Performance Computer Leading Particulars Performance Computer ASCB Transmitted Data Servo Leading Particulars Pressure Ratio Transmitter Leading Part Engine Pressure Ratio Transmitter Input Output Information OZ 800 Receiver Processor Unit Leading Particu ...

Page 36: ... Data Transponder to TCAS Computer Data Directional Antenna Leading Particulars MLS MLS MLS MLS Receiver Leading Particulars receiver ARINC 429 Outputs Control Display Unit Leading Particulars Control Display Unit Block Diagram 198 169 198 171 198 173 198 176 198 177 198 180 198 182 198 185 198 186 198 187 198 187 198 189 198 192 198 194 198 197 198 203 Positioning System Sensor Unit Leading Parti...

Page 37: ...2 298 216 VOLUME II Maintenance Test Procedure 303 Check Procedure 398 285 Test Mode Test Mode Test Mode VOLUME III ARINC 429 Output Values 404 ASCB Output Values 407 outputs 409 ISDU Display of IRU Test Mode Outputs Abbreviations for Test Modes DADC Self Test Analog Outputs DADC Self Test ARINC 429 Outputs DADC ASCB Self Test Outputs Engine and Aircraft Trend and Limit Exceedance Parameters APU R...

Page 38: ... Exceedance Recording Parameters Minimum Wiring Power Requirement for FZ 820 to Run GMT Minimum Servo Wiring Required for FZ 820 to Successfully Power Up Normal Switch States Display Format Data Loader Fault Codes Label 353 Fault Codes for Interconnect Information AC03 and BC03 430 431 432 435 435 444 445 453 460 470 472 502 22 14 00 Page TC 23 TC 24 Apr 15 93 Use or disclosure of information on t...

Page 39: ...oaic truth table for use as an aid in understanding the loqic functions on th block diagrams in Sections 2 and 3 Title SPZ 8000 DAFCS Phase II Pilot s Manual for the Gulfstream IV LASEREF II Installation Manual LASERTRAKW II NDU Installation Manual LASEREF II Pilot s Manual LASERTRAKW NDU Pilot s Manual LASERTRAK II NDU with GPS readout Pilot s Manual LASEREF II GPIRS Pilot s Manual GPIRS Installa...

Page 40: ...AGL AHRS AHRU A I AIL ALRT ALT this manual are defined as follows EQuiva ent Alternating Current Aircraft Publication No 28 1146 75 00 IB8023137 IB8023135 R1 A09 3946 01 28 1146 56 23 1988 19 23 1988 18 A09 3950 01 28 1146 54 28 1146 43 15 3840 001 28 1146 70 01 A15 3800 02 ARINC Communications Addressing and Reporting System Accelerometer Acceleration Air Data Computer Address Automatic Direction...

Page 41: ...ntrol Air Transport Requirement Attitude Auxiliary Azimuth Bank Angle Barometric Battery Back Course or Bus Controller Binary Coded Decimal Built In Test Built In Test Equipment Binary Bottom of Descent Basic Operating Weight Bearing Brake Brake Temperature Monitoring System Civil Aviation Authority British Capture Crew Alerting System or Calibrated Airspeed Circuit Breaker Counterclockwise Course...

Page 42: ...ss Side Control Transformer Control Clockwise Drift Angle Digital to Analog Digital Air Data Computer Data Acquisition Unit Database Display Controller Direct Difference in Depth of Modulation Deflection Degree Demodulator Descent Detector Detent Deviation Directional Gyro Decision Height Differential Difference Disconnect Disengage Display Displacement Distance Data Loader Direct Memory Access Di...

Page 43: ...imated Time of Arrival Estimated Time In Route Engine Vibration Monitor Expanded Localizer Extend External Federal Aviation Authority Federal Aviation Requirement Flight Director Feedback Fuel Flow Flight Fault Summary Flight Guidance Computer Flight Level Flight Level Change F1ight Flight Management System Flight Plan Feet Per Minute From Frequency Flight Test Interface Unit Flux Valve Fault Warn...

Page 44: ...lock Invert Input Output Instrument Remote Controller Inertial Reference System Inertial Reference Unit Isolation Instantaneous Vertical Velocity Kilo Bits Per Second Kilohertz Knots Left Latitude Lateral Beam Sensor Inductive Capacitive Left Hand Limit Lateral Navigation Lateral Guidance Localizer Longitude Position Sensor Type Low Pressure Latched Power Valid Long Range Navigation Line Replaceab...

Page 45: ...play Nondirectional Beacon Navigation Data Base Nautical Mile Normally Open NAV on Course Normal Notice To Airman Nonreturn To Zero Non Volatile RAM Navigation Computer Outside Air Temperature Omni Bearing Selector On Course Outer Marker Oscillator Over Station Sensor Pressure Pitch Attitude Pushbutton Performance Computer Performance Primary Flight Display Parallel In Serial Out Pitch Pitch Synch...

Page 46: ...etract Reverse Source Same as Back Course Rate Gyro Right Hand Radio Magnetic Indicator Area NAV RNAV Approach Range Rol1 Read Only Memory Revolutions Per Minute Receiver Transmitter Rate of Turn Rudder South Static Air Temperature Standby Serial Control Interface Source Single Channel Select Source Destination Identification Seconds Secondary Select Symbol Generator Standard Instrument Departure ...

Page 47: ... Turbine Gas Temperature Turn Knob Track Track Error Turn Knob Out of Detent Torque Limit Aileron Torque Limit Elevator Take Off Top Of Climb Top Of Descent Takeoff Go Around Test Point Track Thrust Reference Set True Technical Standard Order Time To Go Tuned to Localizer Universal Asynchronous Receiver Transmitter Utility Takeoff Decision Speed Takeoff Safety Speed Speed to be attained at 35 feet...

Page 48: ...500 feet AGC Vertical Track Alert West Wings Level Washed Out Weight on Wheels Waypoint Weather Radar Word Sequence Position Transfer Transmitter Cross Side Cross TRACK Yaw Damper Honeywell has an airworthiness analysis procedure performed for all its airborne products to ensure that equipment designed by Honeywell will not create a hazardous in flight condition As a result of the analysis certain...

Page 49: ... RESET R IS PULSED INPUT AND ALWAYS CAUSES OUTPUT TO SWITCH TO 6 4 SET S IS PULSED INPUT AND ALWAYS CAUSES OUTPUT TO SWITCH TO Q 5 TOGGLE T IS MOMENTARY INPUT AND CAUSES OUTPUT TO SWITCH TO Q OR 6 SUCCESSIVELY AC 3452E Logic Truth Table Table A 22 14 00 Page INTRO n INTRO 12 Apr 15 93 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 50: ...Component Qty Part No Des AZ 81O Digital Air Data Computer 2 7000700 964 9 C9 864 CAA or ASC 61 FZ 820 Flight Guidance Computer 2 7003974 905 PHASE 2 lo clo 906 _907 The 907 FZ 820 Flight Guidance Computers were factory installed on aircraft 1198 and subsequent GP 820 Flight Guidance Controller 1 7007546 901 902 11 SM 600 Dual Servo Aileron 1 4015373 705 12 SB 600 Servo Bracket Aileron 1 4015374 9...

Page 51: ...072 thru 1119 WU 870 Antenna and Receiver 1 7012640 902 59 Transmitter Unit WC 874 Weather Radar Controller 2 7006921 413 4l4 61 c61 The following two PRIMUS 870 Weather Radar System components were factory installed on aircraft 1120 and subsequent WU 870 Antenna and Receiver 1 7012640 904 59 Transmitter Unit WC 874 Weather Radar Controller 2 7006921 415 4l6 61 c61 SG 884 Symbol Generator 3 700857...

Page 52: ...be used with ASC 61 Data Loader 1 7004607 901 9O2 123 Da Loader 1 7016600 901 9O2 123 Servo Autothrottle 2 7009025 913 128 C128 Turn Pitch Controller 1 7007990 901 902 129 Display Unit PFD 2 4053000 902 9Ol 130 c130 Inclinometer Kit for PFD 2 7005400 905 906 Display Unit ND 2 4053000 902 9Ol 131 c131 Display Unit EICAS 2 4053000 902 9Ol 132 133 Fault Warning Computer 2 7007484 904 PHASE 2 134 C134...

Page 53: ...ay Unit ISDU 1 CGl136AC10 AC20 N A LASERTRAKW Navigation Display Unit l CG1230AC10 AC20 N A CG1230AC11 AC21 EFIS DISPLAY OPTION CG1230AG11 AG21 GPS READ OUTS Engine Pressure Ratio Transmitter 2 LG1189BC03 4063258 3 O tional VLF Omeqa System Components OZ 800 Receiver Processor Unit 1 7004608 901 Omega VLF AT 800 Antenna Coupler Unit 1 7011102 Teardrop H Field AT 801 Ant na Coupler Unit 1 7011103 B...

Page 54: ...lace of the AHRU The LASERTRAKW may be used in place of the ISDU The optional AC1l AC21 LASERTRAK outputs additional ARINC 429 data which is necessary for display of LASERTRAK on EFIS The AG1l AG21 LASERTRAK is available to allow GPS readouts on the LASERTRAKW display The 906 Flight Guidance Computer FGC is an update to the standard phase 2 905 FGC which improves monitor function in turbulence and...

Page 55: ...Tr 1 FZ4Zt RATIOTRANSMITTER FLIONT k QUIMNCE GuIMNCE PERFORMANCE COMPUTER COMRJTER PERFORMANCE NAwaATloN mMPuTEn COFAWTER XWUTER O 904 12ATA M XUISITION UNIT 2 T ENGINE 5 AT ANTENNA SENSOR r RT401 RAOIO AT 3 2ANTENNA ALTIMETER RECEIVEW TRANSMITTER 1 I 1 t t f i lb f f flb s J AT ANTENNA wow I Er4m4E w h SENSOR 8 wATM I b 4 i tl Tlm ur AT SAA UMOUAL S OUAL TM SSUOUAL SERVO AILEROU SERVO ELIWATOR SE...

Page 56: ...ER SG 884 SYMBOL GENERATOR SG3PILOT S SIDE NZ 9XX NAVIGATION COMPUTER PZ 800 PERFORMANCE COMPUTER FC 880 FAULT WARNING COMPUTER DA 880 DATAACQUISITION UNIT INERTIAL REFERENCEUNITS OR THIRDAHRU 7 SM 600DUALSERVO AILERON 8 TM 260DUALTRIMSERVO UNDERPEDESTAL 9 AT 222 ANTENNAS UNDERFLOOR 10 RT 300 RADIOALTIMETER RCVR XMIT UNDERFLOOR 11 SM S1OAUTOTHROTTLE SERVO UNDERFLOOR 12 RUDDERACTUATOR NONHONEYWEU 1...

Page 57: ... the stabilization and control needed to ensure optimum performance t roughout the aircraft flight regime A central serial communications network provides inter subsystem communi cations within the system The network is denoted by the nomenclature avionics standard communications bus ASCB This bus structure uses advanced communications techniques anJ safety design features to rovide high R through...

Page 58: ...ayed data The DAFCS shall receive lateral navigation roll steering commands and vertical navigation vertical targets directly via ASCB from both FMS subsystems However the DAFCS shall use the FMS navigation data only if selected for display by the EDS The system displays heading course radio bearing pitch and roll attitude barometric altitude selected alert altitude radio altitude IAS MACH targets...

Page 59: ...pt that the AHRU does not provide navigation outputs on the digital bus interfaces The AHRU provides continuous comparison monitoring in which its internally computed attitude angular rate and acceleration signals are compared to those same signals transmitted on the ASCB data bus from IRU 1 and IRU 2 The AHRU also provides backup attitude heading rate and acceleration outputs The inertial system ...

Page 60: ...adio altimeter provides a dc output voltage and an auxiliary radio altitude output which are proportional to the aircraft absolute altitude above terrain The precision output is used to drive the PFD RAD ALT display and supplies altitude information to the flight guidance system Proper system operation is indicated by the absolute altitude being in view on the PFD The RAD ALT display will be blank...

Page 61: ...play Unit failure the PFD takes priority over the ND In the case of an EICAS display failure a compacted EICAS format can be displayed on either EICAS DU 880 Display Unit The symbol generator SG functions as the data processor for the display system It receives digital and discrete inputs organizes this information into the correct formats as defined by the display controller and transmits these f...

Page 62: ...l advantage within the DFZ 820 System through sensor voting and redundancy management techniques The fail operational characteristic is extended to include sensor failures One servo of each dual servo aileron elevator and trim and the rudder actuator is connected to a flight guidance computer Only one computer will be actively controlling the servos and actuator The servo or actuator connected to ...

Page 63: ...dar System The PRIMUS 870 Weather Radar System consists of the following components WU 870 Antenna and RCVR XMTR Unit WC 874 Weather Radar Controller The PRIMUS 870 is an X Band radar designed for weather detection ground mapping and avoidance Weather indications are displayed on the DU 880 Navigation Display ND Storm intensity levels are displayed in bright colors contrasted against a deep black ...

Page 64: ...face with five long range sensors three via ARINC 429 buses and two over the ASCB bus Each navigation computer can also connect to dual Collins Proline 2 or Bendix King DME receivers and a single VOR receiver The interface to the IRS Air Data EDS and DAFCS is over the avionics standard communications bus ASCB Flight plans are also transferred between navigation computers over the ASCB while the li...

Page 65: ...tions as an autothrottle computer to directly control the A C throttles or as guidance to the pilot to optimize thrust management The performance portion of the FMZ 800 system has two primary operating modes advisory mode only and full active coupled mode The advisory mode could be considered a flight director in that it advises the pilot on proper airspeeds and engine settings It is up to the pil...

Page 66: ... 429 buses The DAU transmits the EPR data to the SG 884 Symbol Generator over the ASCB Calibrated airspeed is used for built in test only and does not affect calculation of EPR J VLF Omega The Omega Processor AT 800 AT 801 AT 803 System Optional Sensor System 0SS is comprised of the OZ 800 Receiver Unit and one of the following antennas Antenna Coupler Unit Teardrop H Field Antenna Coupler Unit Br...

Page 67: ...four basic 3 6 11 1 3 and 11 05 kHz as well as a unique to each station This unique frequency can be with the tunable 13 6 kHz VLF receiver channel nterference among stations the transmission one station to transmit a particular frequency at 2 VLF Communication Stations The U S Navy operates a worldwide VLF radio communication network Although not specifically intended as radio navigation aids the...

Page 68: ... 1 1 1 2 3 4 5 6 7 8 Location Maine Japan Washington Hawaii Maryland Australia Puerto Rico Great Britain Latitude 44 39 N 34 58 N 48 12 N 21 26 N 38 59 N 21049 S 18 23 N 55 22 N Lonqitude 67 17 W 137 01 E 121 55 W 158 09 W 76 27 W 114 1O E 67 11 W 1 11 W Fre uency 24 0 kHz 17 4 kHz 24 8 kHz 23 4 kHz 21 4 kHz 22 3 kHz 28 5 kHz 16 0 kHz Power 1026 kW 48 kW 124 kW 588 kW 588 kW 989 kW 100 kW 40 kW VL...

Page 69: ...ulls occurring along the loop axis To avoid this null a second loop is used at right angles to the first This configuration is the familiar crossed loop antenna Some selection system switching network must then be used so the appropriate loop may for each OMEGA station at different bearing angles be sequentially employed throughout the OMEGA transmission sequence Loop antennas are susceptible to m...

Page 70: ...h used for the I selection of he modes of operation k WHITE RATE 1 L TCZ 91O Traffic Alert h WHITE k WHITE RATE 2 RATE 3 Lightning Symbols B MAGENTA ALERT AD 13983 5 Figure 2 1 and Collision Avoidance Svstem Ot tional The TCZ 91O Traffic Alert and Collision Avo of the following components RT 91O TCAS Computer AT 91O TCAS Antenna dance System TCAS conssts I TCAS II is an onboard advisory system des...

Page 71: ...ML 850 MLS receiver provides guidance to the azimuth back azimuth and elevation glidepath flight path angles selected on the control unit or automatically transmitted from the ground station Guidance is output from the receiver in the form digital deviation signals Global Positioning System Optional The Global Positioning System consists of the following components Global Positioning System Sensor...

Page 72: ...ial level is achieved The bus controllers reside in each SG 884 Symbol Generator Only one bus controller is active at any time The others act as backup controllers and assume control of the bus when required due to failure of the active controller Data transfer between users on the bus is controlled by the active bus controller Each user is requested by the active bus controller using the request ...

Page 73: ...NTROLLER BACKUP 10Hz IRS1 40Hz Fwc 1 20Hz 4 I DADC 1 10Hz t J t k 40Hz 20Hz 10Hz F SG 3 BUS CONTROLLER BACKUP Example System LJsi ng the ASCB Figure 3 22 14 00 Page 20 A1 lg 15 91 Use or disclosure of information on this page IS subject to the restrictions on the title page of this document ...

Page 74: ...UND 96 16 PZ 1 BASIC 98 18 AT 1 99 19 PZ 1 BACKGROUND 9A 1A PZ 2 BASIC 9C lC AT 2 9D lD PZ 2 BACKGROUND 9E FWC 1 A3 FWC 2 A7 27 DC 1 AB 2B DC 2 AF 2F FGC 1 BO 30 FGC 2 B1 31 DAU 1A FO 70 DAU lB DAU 2A i DAU 2B F3 73 ASCB Unit Addresses Table 2 22 14 00 Page 21 Apr 15 93 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 75: ...ains 16 bits Figure 4 illustrates an example of a typical user subsystem It shows a user address defined for the DADC The defined messaqe content is shown in the box to the right Other data in front and in ba k of the actual data is control and error checking information required in all user messages BUS CONTROLLER REQUEST TRANSMISSION ADDRESS86 DADCNO 1 r FLAG RESPONSE ADDRESS06 DADC TRANSMISSION...

Page 76: ...ssages This is called a bus every 25 milliseconds Some subsystems need not per second therefore the complement of subsystems requested to transmit during a bus frame varies Some users are asked to transmit every frame some every other some every fourth etc This allows update rates of 40 20 10 and 5 times per second or slower Figure 3 illustrates the operation of the standard bus System requirement...

Page 77: ... A DAU l A OAU l A OAU l A OAU l A BUS B OAU l B OAU l B OAU l B OAU l B BUS A DAU 2 A DAU 2 A OAU 2 A OAU 2 A BUS B DAU 2 B OAU 2 B DAU 2 B DAU 2 B BUS A DC 1 Oc 1 Oc 1 Oc 1 BUS B DC 2 DC 2 Oc 2 Oc 2 BUS A FUC 1 WC 1 Fwc 1 FWC 1 BUS B FWC 2 FWC 2 FWC 2 FWC 2 BUS A NZl NZl NZl NZl BUS B NZ2 NZ2 NZ2 NZ2 BUS A Pz l P Pz l P Pz l P Pz l P BUS B Pz 2 P Pz 2 P Pz 2 P Pz 2 P Oenotes a tothrottle data De...

Page 78: ...not all be in existence on the bus Requests may be transmitted for subsystems which are optional and not installed in a particular application The bus controller database defines the length of each user message so that the bus controller may request transmission at the proper times independent of responses The ASCB interconnects for the SPZ 8000 DAFCS with EDS are shown in Figure 6 Physical charac...

Page 79: ...cally bonded to the aircraft structure c The ASCB transmission lines shall be connected in a daisy chain fashion between user subsystems The cable length between users shall not be less than 2 feet 22 14 00 Page 26 Aug 15 91 Use or disclosure of information cm this page is subject to the restrictions on the title page of this document ...

Page 80: ...O 1MSG INACTIVE I REQUEST IRSNO 2 I I REQUEST IRSNO 2 I INACTIVE IRSNO 2 MSG REQUEST DAU NO 1 A IREQUEST DAU NO 1 A I INACTIVE DAU NO 1 A MSG REQUEST DAU NO 2 A INACTIVE I REQUEST DAU NO 2 A I DAU NO 2 A MSG I REQUEST DC NO 1 I I REQUEST DC NO 1 I DC NO 1 MSG INACTIVE CONTINUED TO END OF FRAME CONTINUED TO END OF FRAME AD 1 5025 R1 Example of Bus Activity Frame O Figure 5 22 14 00 Page 27 28 Aug 1...

Page 81: ... I I I L 55A29 C121J1A l W1l II 55A21 II 55A20 II El C9Jl B 13 14 55A19 I 55A6 I AZ NO 1 9J1B 13114 55A41 I I LEFT AVIONICS BAY I RIGHT AVIONICS BAY I55A4 134Jl B 61 62 I I I i I I I I I I I I I I I I I I I55A26 55A25 13711 B 4 6 HF DA NO 2 II i S 7J1 6 55Ai7 55A50 H 55A23 I 55A1 I SG NO 1 55A51 BC NO 1 SG NO 1 u 65J1B 16117 I 55 4 4 cl JIA l H 2H IRU NO 2 II J 1 I 55A2 1 lJIA l H 2H IRU NO 1 lJIA...

Page 82: ...tronic Display System DFZ 820 Dual Flight Guidance System PRIMUS 800 Weather Radar System PRIMUS 870 Weather Radar System FMZ 800 Flight Management System FMS Engine Pressure Ratio EPR System Optional VLF Omega System Optional LSZ 850 Lightning Sensor System Optional TCZ 91O Traffic Alert and Collision Avoidance System TCAS Optional MLZ 850 Microwave Landing System MLS Optional Global Positioning ...

Page 83: ...round track and speed and wind speed and direction to the rest of the SPZ 8000 system A Inertial Reference Unit See Figures 2 1 and 2 2 and Tables 2 1 through 2 4 The inertial reference unit IRU is the main electronic 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 sens...

Page 84: ...and backup battery supply power to the IRS and provide switching to primary ac primary dc or backup battery power The aircraft electronic interfaces convert ARINC and ASCB inputs for use by the IRS The electronic interfaces also provide IRS outputs in ARINC and ASCB formats for use by the associated aircraft equipment A fault ball indicator and a manual INTERFACE TEST switch are mounted on the fro...

Page 85: ...data transmitted The IRU is capable of transmitting either 23 words transmission or 38 words transmission based upon this discrete Ground this pin short to JIA A1 for the 38 word transmission G IV uses the 38 word transmission This discrete instructs the IRU whether the installation uses a clock bus or not Ground this pin short to JIA Al for clockless G IV does not use clock bus The IRU receives w...

Page 86: ...iscrete No 1 JIB F2 Mode Discrete No 2 Refer to Table 2 4 for the data that is transmitted on these identical buses Bit rate 100 kbits sec The IRU reads the following data from these three ports label 041 set latitude label 042 set longitude label 043 set heading Labels 041 and 042 are read for Nav initialization Label 043 is read to set heading in attitude mode The following data is read from the...

Page 87: ...on Gnd Invalid condition open 1Load capacity 250 mA These outputs are only active on IRU No 3 or the AHRS The third unit compares itself with IRUS No 1 and 2 via ASCB Aground on JIA E6 miscompare between IRUS 1 and 3 A ground on JIA E7 miscompare between IRUS 2 and 3 The following are the eight parameters which are compared pitch and roll angles pitch roll and yaw rates and longitudinal lateral an...

Page 88: ... 00WN 6476 RIRSINPL II l l l l lo 00M305 I 64C6 5 15 0 COS ROLL ANGLE 1 1 1 90 OEG RANGE 6478 RIRCOSPL II i l i i l 6 15 1 TRUE HEAOING li l i l l i l Al iiiGKl 60 FLAG LOGIC 1 VALIO II 7 15 0 i i l l i l l l l lj l l II l lfi fi l goOEG 815 1 PITCHANGLE 11510 549 0 00275 li ii i l l BO FLAG 647E RIRTHETL I l l l i i i i Q 915 1 ROLL ANGLE i l l l l I 90 RIGHT UING DOWN 64B0 RIRPN1OL FLAG II l l i...

Page 89: ... lfi l TUO SCOMPLEMENT 1029 KNOTS 15 0 06248 0 03124 FORUARD 180 FLAG LOGIC1 VALIO II II 64E2FkNZL 1 5 1 TR fA RACK ANGLE 115100 09 000549 IEA5T SEMICIRLE 0 360 DEG l l i fil II LOGIC1 VALID I lfi l goOEG 64E4FASTTOL 1 2IOC04394 0 002746 Iup I 1 1 2015 4 FLIGNT PATNANGLE 6496RIRGAMAL 203 1 SPARE 200 FLAG II LOGIC1 VALID 21 15 3 VEW L ACCEL l l I l l i IK I 81 I 212 1 210 FLAG LOGIC1 VALID II II 64...

Page 90: ...64MIR RWOTLI 0 LOGIC1 VALID II II 64FAFASNOOTL 31 15 0 SPARE I II I 164ACI I 64FC II II 32 15 0 SPARE I 1 I I 1 1 1 II II 64FE I II I 33 l l l oISCRETESIRS 3315 1 mig sT TUS LsB 33 14 6500IIRMISL 3313 ADCOR IRUFAULT LOGIC1 FAULT FASAOIFL 33 12 EXCESS VE MOTION LOGIC1 EXCESSIVE NOTION FASXNOTL 33 11 NO IRSINIT1ALIZATIOH LOGIC1 NO INITIALIZATION FASNIRSL 33 10 ALIGNFAULT LoGIC1 FAULT FASALIFL 339 BA...

Page 91: ...5 3 35 2 35 1 35 0 SPARE SPARE A DOR HIMFAuLT CPUFAULT DISCRETE l OFAULT HOTFAULT SYSTEN TESTS TEHPSENSOR FAULT GYROFREQANDBIASFAULT GrKOFAULT ACCELRESIDUAL FAULT SPARE MEIIN RY FAULT SENSOR LSICFAULT 6504 LOGIC1 FAULT LOGIC1 FAULT LOGIC1 FAULT LOGIC1 FfiULT LOGIC1 FAULT LOGIC1 FAULT LOGIC1 FAULT LOGIC1 FAULT LOGIC1 FAULT LOGIC1 FAULT LOGIC1 FAULT FASADWL FASCPUFL FASDIOFL FASUINFL FASYTSTL FASTSF...

Page 92: ...1 O 1 0 0 to 255 1 O 1 O 1 0 0 5 t 0 5 k4 0 5 1 0 128 f 126 k 128 4 4 4 1 O 32 126 126 0 9 9 0 2097151 32766 k 131072 24 4 4 32768 4096 4096 B RESO LUTION 0 1 0 1 0 1 1 0 0 1 0 1 1 0 1 0 0 1 2A 4E 4 9 54E 7 9 54E 7 0 0039 9 54E 7 9 54E 7 2 44E 4 B 54E 7 9 54s 7 9 54E 7 9 54E 7 9 54E 7 1 22 E 4 9 54E 7 9 54 E 7 0 0039 0 0039 0 0039 1 22E 4 1 22E 4 1 22E 4 9 54E 7 3 05E 5 0 0039 0 0039 0 1 0 0 125 1...

Page 93: ...ARINC 113 414 K4 K5 110 Ill 429 100KHz ARINC 575 429 12 5 KHz DIGITAL PROCESSING JL E6 I MISCOMPARE NO 1 ARINC 575 426 ADC SELECT MODE DISCRETE NO 1 MODE DISCR E NO 2 REMOTE TEST IRu ORIENT IRU ORIENT 2 SDI SDI 2 J E7 MIBCOMPARE NO 2 IIB 1 F3 ALIGN ANN E3 NAV READY ANN D2 WARN FAULT ANN I El NO AIR ANN A7 I 415 E AIT FAIL ANN 15 ON BAT7 ANN J G1 IRS VALID sD141A7 IIA 7 G9 CHARGER INHIBIT J Al PROG...

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Page 95: ...in 85 7 mm Weight maximum 1 5 lb 0 7 kg Power Requirements 5 V ac and 5 V dc 2 5WMax 28 V dc 8 3 W Max each channel Mating Connectors J1 J2 J3 MS3126F18 32S MS3126F18 32SW MS3126F18 32SY Mounting Unit Dzus Fastener Mode Select Unit Leading Particulars Table 2 5 22 14 00 Page 116 Aug 15 91 Use or disclosure of information cm this page is subject to the restrictions on the title page of this documen...

Page 96: ...wnmode from the navigate mode and after 30 seconds automatically reenters the navigate mode upon completion of downmode alignment ALIGN TO ATT or NAV TO ATT The IRU enters the erect attitude submode for 20 seconds during which the MSU ALIGN annunciator lights The IRU then enters the attitude mode ATT TO ALIGN or ATT TO NAV Once the mode select switch has been set to ATT the IRU remains in the atti...

Page 97: ...ignment mode or the navigate mode without affecting basic IRS functions The test mode is inhibited in the attitude mode and in the navigate mode when the aircraft ground speed exceeds 20 knots When either switch is pressed the IRU outputs a preprogrammed set of fixed digital signals to aircraft instruments The signals are output in three eight second phases as shown in Table 2 6 During the first p...

Page 98: ...ind speed True heading Time to NAV On On On On On On 0s 90 200 kn N22 30 0 E22 30 0 30 100 kn 30 0s 0s 0s 0s 0s 0s 0s 0s 90 200 kn N22 30 0 E22 30 0 30 100 kn 30 0s 0s 0s 0s 0s 0s 0s 0s 90 200 kn N22 30 0 E22 30 0 30 100 kn 30 0s OS Original State Test Mode Outputs Table 2 6 22 14 00 Page 119 120 Aug 15 91 Use or disclosure of information on this page is subject to the restrictions on the title pa...

Page 99: ...TIVE WIRES FROM CONNECTORS J2 AND J3 I PANEL LIGHTPLATE I r I I __ 1 ALIGN 1 ANNUNCIATOR JI A4J1 4 ON BAIT ANNUNCIATOR R BATT FAIL ANNUNCIATOR l FAULT ANNUNCIATOR ALIGN SYS 1 u I 15 T u 14 ON BATT SYS 1 u I 13 T u 4 I 12 BATT FAIL SYS 1 u 11 I 1 u 10 FAULT SYS 1 14 9 T u 4 F 1 1 ANN TEST SYS 1 7 u I 6 ANNUN HI 5 A 3 I 4 PNL LTG 5 VAC B PNL LTG RTN 16 A I A4J2 TEST SW 1 3 u 8 TEST TEST SW 2 I 16 SW...

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Page 101: ...2 5 Dimensions Length 6 58 in 16 71 cm Width 5 75 in 14 6 cm Height 4 5 in 11 43 cm Weight 5 0 lb 2 27 kg Power Requirements 5Vacordc 4 5 WMax Mating Connectors J1 Mounting 28 V dc 10 W Max M83723 75R 1831 N M83723 75R 1831 7 M83723 75R 1831 6 Unit Dzus Fastener Inertial System Display Unit Leading Particulars Table 2 7 22 14 00 Page 124 Apr 15 93 Use or disclosure of information on this page is s...

Page 102: ... to be entered Single function keys are used to select only numerical data c The clear CLR and enter ENT keys contain green cue 1ights which when lit indicate that operator action is required CLR is used to remove data erroneously entered ENTJ is used to send data to the IRU Display The 13 digit alphanumeric split display shows two types of navigation data at the same time The display is separated...

Page 103: ...ed and must be held in this position TK GS selects track angle in degrees on the left display and groundspeed in knots on the right PPOS selects latitude on the left display and longitude on the right Both latitude and longitude are displayed in degrees minutes and tenths of minutes WIND selects wind direction in degrees on the left display and wind speed in knots on the right 22 14 00 Page 126 Au...

Page 104: ... KBPS initializationdata on three separately buffered digital bus output ports to ARINC 429 port no 3 on each IRU b The data is BCD transmitted upon manual command in a burst mode of 2 to 4 transmissions within 2 seconds c Refer to table 2 8 for a list of the ARINC 429 data transmitted from the ISDU to the IRU d Set heading data is accepted by the IRU only when in the attitude mode Data Inputs a T...

Page 105: ... 2 Latitude MIN Present Posit ion 011 BCD 6 180E 180W 0 1 OEG EAST 2 Longitude MIN True Heading 044 Bco 4 0 359 9 0 1 DEG CW FROM N 2 Magnet ic Heading 014 BCD 4 0 359 9 0 1 DEG CW FROM N 2 Ground Speed 012 BCD 4 0 2000 1 0 KTS ALWAYS POS 2 Track Angle 013 8C0 4 0 359 9 0 1 DEG CW FROM N 2 True W indspeed 015 BCD 3 0 256 1 0 KTS ALWAYS POS 2 Wind Oirection 016 BCD 3 0 359 1 0 DEG CW FROM N 2 True ...

Page 106: ...r data invalid 18 IRU fault BITE Not IRU fault IRU fault 19 BATT fail ON BATT Not BATT fail BATT fail 20 Alignment fault hb l lignment Alignment fault 21 No initialization Initialized Not initialized 22 Excessive motion Align mode No40i cessive Excessive motion 23 Air data computer ADC or t 4g 41 DC or IRU ADC or IRU fault IRU fault 24 Not used 25 27 Time to NAV RDY BITS Minutes 25X27 10 6 111 6 5...

Page 107: ...SD in binary coded decimal BCD 18 21 Time to NAV Most significant digit MSD in BCD 22 31 INot used ARINC 429 Time to NAV Ready Discrete Word Octal Label 351 Table 2 11 22 14 00 Page 128 2 Apr 15 93 Useor disclosure of information on this page issubject to the restrictions on the title page of this document ...

Page 108: ...UT LO ARINC 429 25 LO SPEED 26 ISDU INPUT HI 4 I SDU lNpUT LO 4 3 8 ARINC 429 27 HI SPEED L A 1 PIN ARRANGEMENT IS IDENTICAL ON A CONNECTORS J2 AND J3 2 GROUND FOR DIM AND OPEN FOR BRIGHT A 3 GROUND FOR ILLUMINATION AND OPEN FOR OFF AD 31303 ISD1 1 Wiring Diagram Figure 2 7 22 14 00 Page 128 3 Apr 15 93 Use or disclosure of information on thispage issubject to the restrictions on the title page of...

Page 109: ...nit Figure 2 8 Figures 2 8 Dimensions Length 6 0 in 15 24 cm Width 5 75 in 14 6 cm Height 4 5in 11 43 cm Weight 3 81b I 72 kg Power Requirements 5Vacordc 3WMax 28 V dc 10 WMax Mating Connectors M83723 75R 1831 N M83723 75R 1831 7 J3 M83723 75R 1831 6 Mounting Unit Dzus Fastener Navigation Display Unit Leading Particulars Table 2 12 22 14 00 Page 128 4 Apr 15 93 Use or disclosure of informationon t...

Page 110: ... and data select keyboards a Data Entry Keyboard The data entry keyboard consists of 12 keys that are used to enter display modify or transmit initialization leg change and flight plan data The ENT key is used to accept entered data that is being displayed on the data display The CLR key is used to remove the entered data and clear the display Both keys contain green cue lights that indicate when ...

Page 111: ...may include only one or two IRU If a SYSTEM SELECT key is pressed and no IRU is present the NDU displays dashes d Data Select Keyboard The data select keyboard consists of eight keys that are used to select data for display Each key contains a cue light that when lit indicates what type of data has been selected for display When the WPT LEG CHG POS or HDG STS key is pressed the operator can enter ...

Page 112: ...try When the IRU is in the nav mode the NDU displays heading in the left display and when the IRU is in the attitude mode the NDU displays magnetic heading in the left display and ATT in the right 2 s The NDU contains a data display and a FROM TO WPT a Data Display The NDU data display consists of two displays a six position display and a seven position display each having degree decimal and minut...

Page 113: ...eceives data from IRU 1 IRU 2 and IRU 3 through ports 1 2 and 3 connectors Jl J2 and J3 respectively Table 2 15 defines the NDU characteristics Table 2 16 defines the use discrete word octal label Table 2 17 defines the use Ready discrete word octal OCTAL LABEL 041 042 043 116 275 FORMAT Bco BCD BCO BNR DIS SIGNIF ICANT CHAR 5 6 4 15 Refer to Table 2 14 for octal label format OIGITAL RANGE 90s to ...

Page 114: ...1 Invalid 24 26 Not used 27 Mag True north o Magnetic 1 True 28 CDI flag o Invalid 1 Valid 29 30 Sign status matrix SSM 00 Undefined 01 No computed data NCD 10 Functional test 11 Normal 31 Parity odd ARINC 429 Status Word Discrete Octal Label 275 Table 2 14 22 14 00 Page 128 9 Apr 15 93 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 115: ...INR N True Hdg BNR 314 BNR 15 1 O 0 00003 0 5 Oeg 180 CW from 25 N W indspeed 315 BNR B O to 255 1 0 128 KtS Always 10 Pos Wind Oirection 316 BNR 8 il o 0 0039 0 5 Deg 180 CW from 10 True N TK Angle Mag 317 BNR 15 il o 0 00003 0 5 Deg 180 CW from 25 N Magnetic HDG 320 BNR 15 1 O 0 00003 0 5 Deg lBO CW from 6NR 25 N Time to NAV Ready 351 BCO 2 Oto 9 9 0 1 Min 1 Refer to table 2 16 Refer to table 2 ...

Page 116: ...ata invalid 18 IRU fault BITE Not IRU fault IRU fault 19 BATT fail ON BATT Not BATT fail BATT fail 20 Alignment fault t l lignment Alignment fault 21 No initialization Initialized Not initialized 22 Excessive motion Align mode No Oig cessive Excessive motion 23 Air data computer ADC or hJg l DC or IRU ADC or IRU fault IRU fault 24 Not used 25 27 Time to NAV RDY BITS Minutes 25 26 27 10 6 111 6 5 0...

Page 117: ...KS Least significant digit LSD in binary coded decimal BCD Most significant digit MSD in BCD ARINC 429 Time to NAV Ready Discrete Word Octal Label 351 Table 2 17 22 14 00 Page 128 12 Apr 15 93 Use or disclosure of information on this page issubject to the restrictionson the title page of this document ...

Page 118: ... PRT H 1 OUTPUT BUS OUT PRT L 429H 1 1 I lop CDIPOWER CONTROL CDI r Ii II t J I fp NOTES A 1 NDU POWER ISSUPPLIEDFROM IRUWHEN IRUISOPERATING A 2 IFINPUT ISGROUND KEYBCIARD CUE LIGHTSARE DIM WHEN ON IF INPUT ISOPEN KEYBOARD CUE LIGHTS ARE BRIGHT WHEN ON A 3 IFINPUT ISGROUND NDIJENTERS TEST MODE NDU Wiring Diagram Figure 2 9 95 83081303 22 14 00 Page 128 13 128 14 Apr 15 93 Use or disclosure of info...

Page 119: ...MAINTENANCE Honeywell YW h This page intentionally left blank 22 14 00 Page 129 Aug 15 91 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 120: ...al Air Data Computer See Figures 3 1 and 3 2 and Tables 3 1 3 2 and 3 3 AD 3037 R1 AZ 81O Digital Air Data Computer Figure 3 1 22 14 00 Page 130 Aug 15 91 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 121: ...emperature inputs for computing the standard air data functions The air data equations are solved directly using a 16 32 bit arithmetic microprocessor under the control of an 8 bit general purpose microprocessor The DADC provides outputs to the electronic display system transponder flight recorder flight guidance computer as well as other elements of the system such as fault warning computers and ...

Page 122: ...AROMT FLAG LOGIC 1 VALID 40 PRESSURE ALTFLAG LOGIC1 VAL1O 5AC6FASBALTL II l lfi fii l l 024 o 11410 25 003 25 I FASPALII S 15 2 CALIBRATE AIRSPEED 1 i FORUARO 51 SPARE 0 5AC8 L 50 CAS FLAG LOGIC 1 VALID I l l Iwo s CWPLEHENT 6 15 2 TRUEAIRSPEED I i l l l l l Mll M i l SPAltE TAS FLAG 5ACA I l l l i l FASIAS1 7 15 2 MACH II I 2 0 MACH l p 14 0 000244 O 0DO061 FORMARD 71 SPARE 0 5ACC WICII FLAO LOGI...

Page 123: ...GIC1 VALID II I l l l l l l 14 15 4 NORHAL IZEDAOA TUO S COMPLEMENT 2 o RATIO 143 0 SPARE II II 5AOA 15 15 0 SPARE I II I 1 1 I II II 5AOC I II I i l l 16 15 0 SPARE 1 II 1 I 5AOE 1 I l l l i 1715 O SPARE II II 5AE0 1 11 18 15 0 SPARE t I M I I II II 5AE2 I l l l l J I 19 15 0 SPARE II l l T SAE4 1 I l l 20 15 0 TOTAL PRESSURE i l l I 64 IN IIG II II 5AE6 5 2 MAXALLONABLE MCH I II I THO S COMPLEME...

Page 124: ...SBSETL I l l l l l l l l f 1 I SPARE VmoEXCEEOEO LOGIC 1 EXCEEOEO 5AEE 24 9 8 FLAP POS CODE 00 0 uEG FADDF2L9 249 8 ol 10 oEG FADOFIL8 24 9 8 10 20 DEG 24 9 8 11 39 oEG 24 7 CAUINPRESSNREVALID LOGIC i VALID 246 FLAP POS VALID LOGIC1 VALID 2i 5 o SPARE I l l l 25 I l l l 1 1 I II fi l l l l l 1 1 1 I 26 I lERkoR I l l l l l FJ l 27 5AF4 l l I II l l l l l 28 NOLC FLAG ...

Page 125: ... Valid CO Ma Irwalid 01 Self Test W Parity Oeck Bit Id 21md 31sd 21sd lsd Oats Field kilral Point Status IX Osta Irwalid psitim 01 Self Test Data Imalid NOTransnissim 11000001 00100001 10100001 01100001 11100001 00010001 10010001 01010001 11010001 01000010 00000101 01000101 10011111 Latel w Ckstinstim Ccd W All Call 00111001 10111001 Note 1 X Ckm tcare my cmt ain valid kss si ificant ta Note 2 Thi...

Page 126: ... TO DIGITAL CON vERTER I 101 102 103 104 105 106 JIB AOA 60 PROBE 4 INTERFACE AOA SIGNAL WIPER l I AIRCRAFT INTERLOCK KEYING 3 H 1A 1 11 PRIMARY L 2 ASCB ASCO H JIB 1 13 SECONDARY L 4 ASCB I B H IIB L 1 26 OUTPUT 27 NO 1 H 70 OUTPUT L 71 o z ARINC 429 H L 1 W OUTPUT NO 3 H 31 32 OuTpuT L 33 NO 4 3 PROGRAM MEMOFIY PROM I 33Et BARO CORRECTION POTENTIOMETER AIRCRAFT CONSTANTS VMO SSEC ALT SWITCH A S ...

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Page 128: ...104 0 mm Weight maximum 4 5 lb 2 05 kg Power Requirements 28Vdc 0 7A Transmitter characteristics nominal Type Short Pulse Modulation RF frequency 4 3 GHz Peak power 5W Receiver characteristics nominal Type Superheterodyne IF frequency 60 MHz RT 300 Radio Altimeter Receiver Transmitter Leading Particulars Table 4 1 22 14 00 Page 140 Aug 15 91 Use or disclosure Of information on this page is subject...

Page 129: ...curacy O 100 ft i 4 ft 100 500 ft f 4 500 2500 ft t 5 Altitude Trips 100 MA current sink provided at and below trip points indicated below Tri Point Accuracy 50 ft t4ft 250 ft 11 ft 500 ft 16 ft 1200 ft 6O ft Mating Connectors MS3116F16 26S TRANSMIT GRFF 4007 0002 GRFF Connectors GRFF Division Solitron Devices Inc J3 RECEIVE GRFF 4007 0002 Mounting Hard Mount RT 300 Radio Altimeter Receiver Transm...

Page 130: ...plitude of the video signal at a constant level The processor also contains the search and acquisition circuits which enable the system to initially acquire the ground return signal or reacquire the signal should tracking be interrupted The search mode is initiated upon loss of signal A sweep signal is generated which causes the system to search for the earliest return signal This process continue...

Page 131: ...NO 1 D OUTPUT I ASSEMBLY i I TEST INHIBIT NO 2 B I 1 I 1 I OUTPUTTEST E I I I A 1 I 28VDCFILTERED 1 u 1200FTTRIP V 250 FT TRIP R 50 FTTRIP L 500 FT TRIP P ALT TRIPCOMMON I L 30 VDC i 28 VDC 15 VDC INPUT PWR q Z 15 VDC OUTPUT 1 POWER 5 VDC 1 I SUPPLY 15VDC I PWR GND Q I 15 VDC OUTPUT 15VDZ RT 300 Radio Altimeter Receiver Transmitter Block Diagram Figure 4 2 22 14 00 Page 143 Aug 15 91 Use or disclo...

Page 132: ...ons maximum Width along contoured mounting surface 7 00 in 177 81Mn Height 2 75 in 69 85 mm Weight maximum 1 25 lb 0 57 kg Power Requirements 100 W average max Mating Connector J1 TNC male GRFF 4007 0002 Straight GRFF 4100 0001 Right Angle Mounting Flush mounted to aircraft skin AT 222 Radio Altimeter Antenna Leading Particulars Table 4 2 22 14 00 Page 144 Aug 15 91 Use or disclosure of informatio...

Page 133: ...NANCE Honeywell i i h 5 paraurat h5 is not amlicable to this svstem 22 14 00 Page 145 Aug 15 91 Use or disclosure of information on this page is subject to the restrtctlons on the title page of this document ...

Page 134: ...arning Computers The system displays flight attitudes headings course orientation flightpath co ands weather and mapping pr entations mode and source annunciations engine performance data crew alerting messages and checklists A DU 880 Display Unit See Figures 6 1 through 6 4 and Table 6 l AO 30251 DU 880 Display Unit Figure 6 1 22 14 00 Page 146 Aug 15 91 Use or disclosure Of reformation on this p...

Page 135: ...cuit breaker panel power may be removed from the display system by the display power panel located in the overhead on the pilot s side of the cockpit This panel is shown in Figure 6 3 The leading particulars of the DU 880 are listed in Table 6 1 The electronic display system operation is described with reference to Figure 6 4 Figure 6 5 contains a block diagram of the DU 880 Each of the six displa...

Page 136: ... Configuration Figure 6 2 r 1 i I I I I 1 I I I i I I I I I I PILOT DISPLAYS EICAS COPILOT OFF OFF 7 K OFF L e J Display Power Panel Figure 6 3 22 14 00 Page 148 Aug 15 91 Use or disclosure of information on this page is subject 10 the restrictions on the title page of this document ...

Page 137: ...ge is activated where X is position of DU in the aircraft which is displaying miscompared PFD data If the miscompare occurs on both PFDs then the red CHECK PFD message is displayed The DUS displaying engine data format additionally transmit left and right EPR left and right TGT and left and right N1 and N2 information The FWC compares the engine data received from DU3 or DU4 with compacted EICAS f...

Page 138: ... continue to increase after the raster generator has been shut off an even higher temperature trip point will shut down the low voltage power supply LVPS At the same time a discrete is provided to the FWC allowing an overtemp message to be displayed The LVPS will remain off until the temperature drops sufficiently below the higher trip point 22 14 00 Page 150 Aug 15 91 Use or disclosure of informa...

Page 139: ...29 324 325 n 341 USER OEFINEO 342 ARINC 422 345 PARAMETER SLEW RATE ALTITUDE MAcn AIRSPEED PITCH ROLL TIVtTY COUNTER LEFr EPR RIGHT EPR LEIT TGT RIGHT TGT LEFr N1 RtGHT N1 THRFSHO MAXIMUM RATES 200FT 20 mo FrMN 0 01 M 01 rniSEC am 10 KTS SEC 6 DEGREES 4QVSEC 6 OEGREES 40 SEC 0 5 50W 5 AKX 047S R1 EDZ 884 Electronic Display System Interface Figure 6 4 22 14 00 Page 151 152 Aug 15 91 Use or disclosu...

Page 140: ...L T Ro CXl ROUND r C H WX DIMMING W L Ccus w O oy SENSOR HV ENASLE FOCUS CONTROL D TEMP FwR VALID cu POWER DOWN 32 REMOTE LIGHT SENSOR GND 40 t H 53 I OUVOLTAGES REMOTE LIGHT SENSOR PWR L E4 ou OVER TSMP 65 LOW 101 V RE 28VDC 102 suPFIY 103 104 2SVOCRTN 105 10s BUSOR wx INPUT HIGH BPEEODIFFERENTIALINPUTTERMINATION rm I 1s0 o REcEIVER i lK n TERM L i AD 33252 RI DU 880 Display Unit Block Diagram Fi...

Page 141: ...MAINTENANCE Honeywell k fh This page intentionally left blank 22 14 00 Page 155 Aug 15 91 Use or disclosure Of reformation on this page is subject to the restrictions on the title page of this document ...

Page 142: ... 91 in 124 7 mm Height 7 62 in 193 5 mm Weight maximum 15 4 lb 7 0 kg Power Requirements 28 Vdc 85 WMax Mating Connector J1 DPX2MA 67S 67S 33 B 0001 Mounting Tray Honeywel1 Part No 7003272 903 SG 884 Symbol Generator Leading Particulars Table 6 2 22 14 00 Page 156 Aug 15 91 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 143: ...creating include Primary Flight Display Format Map Format Plan Format Compass Format Engine Instrument Format System Display Caution Advisory Format Compacted Engine Format The symbol generators in the display system are identical and directly interchangeable e When the display system is in its normal no failure configuration SG1 drives the pilot s displays SG2 drives the copilot s displays and SG...

Page 144: ... to 18 characters per message The FWC also provides the necessary data to display checklist information as well as exceedance displays The DC 884 Display Controller defines which fault warning computer is utilized for display purposes The symbol generators monitor the fault warning computers through comparison of checksums transmitted by each fault warning computer A detected fault warning compute...

Page 145: ... 1 previous 50 current 10 Immediate Area Navaids G 9 Immediate Area Airports Current Position TO Waypoint Curved Holding Pattern Vertical Profile Path 6 AZ 81O Digital Air Data Computer Interface The AZ 81O Digital Air Data Computers provide altitude airspeed normalized angle of attack and vertical speed ARINC 429 information for display on the PFDs The symbol generator provides comparison monitor...

Page 146: ...ME The DME sensors provide distance and frequency information for display Distance information is transmitted over the ASCB for utilization by the FZ 820 Flight Guidance Computers d ADF The ADF sensors provide the symbol generators with bearing and frequency information for display purposes only e LASERTRAKW The LASERTRAKN Navigation Display Unit may be configured to provide additional outputs for...

Page 147: ...VAL1O 2 14 8 DISPLAYEO ATTITUOE 00 H VG1 01 H VG2 5C52 02 N VG3 5CA2IEFOATTL 2 03 H INS 04 ti lNS1 05 II INS206 H lNS3 07 H ATT 1 08 N ATT 2 09 N ATT3 OA N ATT3 OC H IRS 0011 lRS1 OE N IRS2 OF N lRS3 27 0 SELECTEO ND NAVSOURCE SEEUSP5 FORDEFINITION lEFStlAUL 31 I l l l II SOURCE IDENTIFIER I 1 1 I 3 15 FLAG LOGIC 1 VALIO 3 14 8 OISPLAVEO HEAOING oAH MGl DC H MAG20EN MAG3 1211 AG4 5C54 3 OBN TRUl O...

Page 148: ...LoG Wo spARE 001 L ASCB 010 ANMOG HITH ARINC56B 011 ARINC 561 6 MIRE 100 ARINC429 Hklll SPEED 101 ARINC429 LOU SPEEO 110 R ASCB IEFSRNHL IEFLRNBL IEFLRNAL A mo 4 7 51 I 111 ANALUGtllTH ARINC S61 SOURCEIOENTIFIEII l l l l l l lii l 5 15 TRANSITION FLAG 1 TRANslTloN 0 MT TRANslT1oN 5 14 B OISPLAYED ARHEO NAV SEENEXTBYTEFORDEFINITION 57 0 SELECTED PFONAV SWtlCE NAV SWRCE DEFINITION i mH lNs 21 H INS ...

Page 149: ...DISPLAY FLAG LUGIC1 DISPLAYED 5CB0 I l i l l l l l l I 10 10 15 14 TO FHOt4 OATA 00 NONE 01 To 5C62REFTOFRL 5CB2 10 FRON 11 IN I EO 10 13 PFO VALIO LOGIC 1 VALIII 10 2 NO VALIO LOGfC 1 VAL1O FEFPLHoL 10 11 8 SPSRES 10 1 01 SPLAYED RAOALT FEFTOFllL 1 RA2 0 RA1 106 CROSSSIDEVENTCAP LOG1C1 CAPTURE G SOR EL FEFCSVCL 105 OISPLAYEO DAOCL R 1 RIGHT O LEFT FEFllAOCL 104 t4AP PLAN MOUESELECTED LOGIC1 SELEC...

Page 150: ...DEV FLAG LOGIC 1 VALID FEFLDEVL II 11 I II I 0 l 1 16 16 4 DIj LA ED VERT OEVIATION 3 TUO SCOMPLEMENT 399 2MICROANPS 12 0 195 0 0122 mA FLY UP CHll 2 1 SEE NOTE 3 SEE NOTE 3 5C6E FLAG LOGIC 1 VALIO 5CBE FEFVDEVL m II II I l fil i l f l ll l l l 5 4 Dl ED RAOIOALTITUOE TUO S COWLE NT 2047 FEET 5C70 170 FLAG LOGIC 1 VALID 5CC0 c II II 1 II I 1 1 1 18 OESIGNATOR LAT 1 18 15 12 TEN SOF MINUTES eco 18 ...

Page 151: ...E ERROR SRN 25 3 1 SPARE 5CB0 250 FLAG II LOGIC 1 VALID l l I 26 15 4 DISPLAYED HEADING l l l I I LI 263 1 SPARE 260 FLAG LOGIC 1 VALID 5C82 II l lfi Fiii ii l l l liiiii lol l 27 15 4 OfSPLAYEDVERTICALSPEED 65536FT PER 141N 15 2 0 1 0FPM 21 3 1 SPARE 5CL14 210 FLAG LOGIC 1 VALID 27 OR MAINTENANCE TEST 5CD4 II 1 l l l ii l i i i iiii 1 1 1 28 15 6 MLS SELECTEOELEV ANGLE 51 2 DEG 285 SELECTED ELEV ...

Page 152: ...NoGSELECT BUGDISPLAYED POSITION CRSSELECT RUGOISPLAYED POSITION LATDEVPOINTER OISPLAYEO POSITION NSPII lllIG TllK ERRON UiP i3 SEL OCRS SRN o II USP 25 CRS ERROR SRN NSP 15 oISPLAYEO LAT l EVO VOR 2 3 NNENHLS IS 01SPLAYED USE SELECTEO AZIMJTH AS RECEIVEO SELBUGPOSITION USP258 NSP 13 FORARINC429NLS Ie HSP4 BIT 12 0 ANO USP4 BITS FACTOR RSEl ANORESOLUTION ARE SCALE RSII APPROX RESOL LSfl 2400UA 15 B...

Page 153: ... l 5 15 8 PREVIEWNAV SUIRCE SEE NEXTBYTE FU7OEFITION I NAV SCLRCE DEFINITION 5 7 0 SELECTED PFO NAVSUJRCE 20 11 INS 24 NOTUSEO 27 11 VLF I l j l j I 6 15 NOVALIO LOGIC 1 NOVALIO 14 8 SPARE 7 MLS2 FAIL LOGIC1 MLS2 FAIL 6 MLSI FAIL LCM31C 1 MLS1 FAIL 5 SPARE TCASFAIL LCGIC 1 TCASFAIL 6 TOGAWE LOGIC1 TOGAACTIVE l f I l l l l I 7 15 12 SPARE I II I I 11 MLS LOGIC1 FAIL 73 GS GP LCKIC 1 FAIL l l l 11 1...

Page 154: ...SERIAL Bus 10 BUFFER RECEIVERS I L Jl t d I I II RAM 2k X 16BIT Id I I Ill ASCB A2 L u BUFFER RAM MAILBOX BUFFER n L G DIRECT MEMORY ACCESS 60166 RAM LOCAL PROM PROGRAM CPU SkX 16BIT 16kX 16BIT L I I LOCAL k I I 16BIT BIDIRECTIONAL DATAGLOBALBUS R BUFFER I SERIAL 1 0 MANCHESTER CONT ASCB CODERl DECODER MUX AND BUFFER ASCB 1 ASCB 2 AAH RS 232 AD 15187 R1 SG 884 Symbol Generator Block Diagram Figure...

Page 155: ... Al 1 CHANNEL 2 CHANNEL 2 ADDREss I DISPLAY UNIT CHANNEL 1 v DATA STATE ADDRESS GENERATOFiI RAM LATCH MACHINE 7 BUFFER 16kx4BlT t 1 I I I I 1 I WX INTERFACE A13 I BUS 26 Blls A BIJS B 4 DIFFERENTIAL MONITOR LINE MICRO 4 DRtVER I mCODE MoNtToR MONITOR DRIVER VLsl DATA BASE PROM I TRANBMllTER TRANSMITTER 4 DRIVER VLsl DATA BASE PROM STANDARD BUS CONTROLLER M I 1 I POWER SUPPLY r CLEAR CONTROL CIRCUI...

Page 156: ...MAINTENANCE Honeywell Hi A This page intentionally left blank 22 14 00 Page 171 Aug 15 91 Use or disclosure of information on this page is subject 10 the restriaions on the title pege of this document ...

Page 157: ...2 78 in 70 61 mm Weight maximum 13 0 lb 5 89 kg Power Requirements Primary 28 V dc 35 0 W Lighting 5 V ac ordc l OWmax Mating Connectors J1 MS3126F22 55SW J2 MS3126F18 32SW Mounting Unit Dzus Fasteners DC 884 Display Controller Leading Particulars Table 6 4 22 14 00 Page 172 Aug 15 91 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 158: ...outed to the symbol generators via the ASCB bus This information is used by the SGS to calculate left right deviation for display and the flight guidance computer The GIV system is configured to operate with two DCS installed in the control panel directly in front of each pilot above the primary EFIS displays Figure 6 8 shows the layout of the display controller Each display controller is comprise...

Page 159: ...owed by selected for display 2 DCMenu Declutter Mode The DC power up state is the menu declutter mode as shown in Figure 6 9 This mode may be selected at any time by depressing the active annunciated function key Selection of the declutter option has no effect on any of the menu selected items 3 MAP Mode Generally the MAP function is comprised of the following items Bearing Pointer Source Selectio...

Page 160: ...oller Declutter Mode Figure 6 9 i i i BGol VORl ADF1 AUTO BGO FMS2 VOR2 m immml ID VERT PROF ID AIRPT WIND VECT t 1 1 1 1 AD 11693 MAP Mode Menu Figure 6 10 22 14 00 Page 175 Aug 15 91 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 161: ...s on the bearing circle No 1 sources pointer only as shown in Figure 6 10 The copilot s AUTO selection pointer only The bearing po appears on the bear nter power up defau ng diamond No 2 sources ts are Pilot AUTO Copilot AUTO c Waypoint Declutter Mode The selection for this mode is displayed on the DC CRT as ID WAYPT This selection has three independent modes as described I ID WAYPT m IDWAYPT IDWA...

Page 162: ...ids are cll yed without IDs on the MAP display e Airport Declutter Mode The selection for this mode is displayed on the DC CRT as ID AIRPT This selection has three independent modes as described ID AIRPT This is the power up mode for this parameter With both the ID and AIRPT unboxed the active flight plan airports and IDs are not displayed on the MAP display format I w Y_l This is the next selecti...

Page 163: ...this mode is VERT PROF selected for display boxed This function is an alternate action selection on the DC i e boxed unboxed h MAP Selections General Bearing pointer and wind display selections made on this menu also change the selections on the COFIPmode menu and will be reflected on the COMP display if subsequently selected Flight plan declutter selections made on this menu are also changed on t...

Page 164: ... reflected on the MAP display if subsequently selected WIND Display Selection The WIND display format selection operation is the same as the MAP mode discussed in paragraph 6 C 3 Wind display selections made on this menu also change the selections on the MAP mode menu and will be reflected on the MAP display if subsequently selected PLAN Mode Menu The PLAN function is comprised of the following it...

Page 165: ...D 11694 Comp Mode Menu Figure 6 11 I f I 1 I 1 1 1 I f BACK FPLN SCROLL FORE I ZI 1 ID NAVAID IIml ml mml 1 PI an Mode Menu Figure 6 12 22 14 00 Page 180 Aug 15 91 Use or disclosure Of information on this page is subject to the restrictions on the title page of this document ...

Page 166: ...e reflected on the MAP display if subsequently selected WIND Display Selection WIND can be selected for display on the PLAN mode format The power up default for this mode is WIND not selected for display unboxed This function is an alternate action selection on the DC i e boxed unknown The format of the WIND display is fixed on the PLAN mode format 6 NAV Mode The NAV menu as shown in Figure 6 13 i...

Page 167: ... 1 and 2 selections of the same source Selection of a different line key moves the box to the number 1 or 2 source of that line All of the possible sources are shown in Figure 6 13 The DC must be wired in the aircraft to get the MLS ILS and LTRK selections shown on the NAV menu Although the aircraft may be wired to show MLS on the NAV menu the optional TCAS MLS DC 884 Display Controller Part No 70...

Page 168: ...EW r I AD 7016 R3 NAV Mode Menu Figure 6 13 I i 1 I i I 1 PEE w FMS 1 2 NAV Ill 2 u CRS SET ml ILS12 MLS 1 2 RETURN I AD 2734 Preview Mode Submenu Figure 6 14 22 14 00 Page 183 Aug 15 91 Use or disclosure Of information on this page is subject to the restrictions on the title page of this document ...

Page 169: ...figuration in the event of failure conditions The SENSOR menu is shown in Figure 6 15 a SENSOR Function Key Selection Selection of the SENSOR mode causes the function key to be annunciated along with the SENSOR menu to be displayed on the DC CRT Figure 6 15 The SENSOR mode menu is used to select the active sensors displayed on the PFD and ND A SENSOR function key selection has no effect on any of ...

Page 170: ... comprised of the reference data Figure 6 16 Vspeed Reference Bugs Vl VR V2 VFS VSE VREF Figure 6 15 The DC IRS 3 selection shown following settable Performance System Auto Vspeed Selection Mode Radio Altitude Set AOA Reference Bug a FLT REF Function Key Selection Selection of the FLT REFmode causes the function key to be annunciated along with the FLT REF menu to be displayed on the DC CRT Figure...

Page 171: ... 2 AIT liJ2 SENSOR Mode Menu Figure 6 15 AD 13605 R1 VI 110 AOA 59 v ml O ovs 1 30 v 124 RAD ALT ml VFS 130 AUTO VSPDI v SE m v REF 130 AD 20868 FLT REF Mode Menu Figure 6 16 22 14 00 Page 186 Aug 15 91 Use or disclosure of information on this page is subject to the restrictions on the title page of thts document ...

Page 172: ...terisk but are not boxed on the menu Both conditions will result in the amber VSPD annunciation Selection of any line select key adjacent to a Vspeed will cancel the AUTO VSPD mode on both pilot and copilot DCS The values remain displayed and can set manually as discussed in paragraph 6 C 8 C c Manual Vspeed Set Function The first selection of a line key causes reverse video to appear around the p...

Page 173: ...this parameter effects only the on side PFD format Thrust Reference System TRS Mode Menu The TRS mode is comprised of the following selections and settable reference data Figure 6 17 and 6 18 Selection of Performance System Computed EPR Limits Takeoff TO or Go Around GA EPR Reduced Takeoff FLEX EPR Climb CLB EPR Cruise CRZ EPR Maximum Continuous MCT EPR Performance System AUTO EPR Selection Mode M...

Page 174: ...AD 20869 Main TRS Mode Menu Figure 6 17 11 25 1 I 1 ml SPL I 1 4 MAN EPR 1 25 T PREVIOUS I I f I r I AD 7018 R5 TRS Mode Submenu Figure 6 18 22 14 00 Page 189 Aug 15 91 Use or disclosure of reformation on this page is subject to the restrictions on the title page of this document ...

Page 175: ...or Go Around TO or GA Climb Mode CLB Cruise Mode CRZ Maximum Continuous MCT Reduced Takeoff FLEX The reduced takeoff EPR labeled FLEX is displayed only when activated on the CD 81O Control Display Unit This value is treated as a target on the engine display green bug as opposed to a limit white tickmark When selected the FLEX target value and the TO limit value are both selected The power up defau...

Page 176: ...em Page HYD Fuel System Page FUEL APU Bleed System Page APU BLEED Engine Start Page Engine APU Exceedance Page EXCEEDANCES Waypoint Listing WAYPT LIST Checklist NOTE For optional TCAS refer to paragraph 6 C 15 b a b c SYSTEM Function Key Selection Selection of the SYSTEM mode causes the function key to be annunciated along with the SYSTEM menu to be displayed on the DC CRT Figure 6 19 The SYSTEM m...

Page 177: ...r 1 AD 7014 R4 SYSTEM Mode Menu Figure 6 19 ml 1 1 EIVIER I ENTER ADV ADV RECALL LINE PAGE ABNORM BACK BACK RETURN E AD 11792 CHECKLIST Mode Submenu Figure 6 20 22 14 00 Page 192 Aug 15 91 Use or disclosure Of information on this page IS subject to the restrictions on the title page of this document ...

Page 178: ...r backwards through the checklist by line PAGE ADV Moves the CHECKLIST cursor forward through the checklist by page PAGE BACK Moves the CHECKLIST cursor backwards through the checklist by page c ENTER Means by which a particular procedure is selected or checked off complete RECALL Returns to the first unchecked procedure within a given CHECKLIST f RETURN Selection of this key returns the main SYST...

Page 179: ...ay formats TEST selections are made using the menu driven line select keys b Crew Initiated System Tests The individual line keys of this menu select the self test mode of the named subsystem The activated test is boxed as long as the line key is depressed Tests are initiated for the on side displays only EICAS tests can be selected from either side DC 12 DISP Mode The DISP menu Figure 6 22 is dis...

Page 180: ...A T DISC l MAINT AD 13551 R1 TEST Mode Menu Figure 6 21 I 1 41 FD CMD SC CASIMACH METRIC ALTI m BARO I N AD 8685 R4 DISP Mode Menu Figure 6 22 22 14 00 Page 195 Aug 15 91 Uee or disdoswe of information on this page is subject to the restrictions on the ttfle page of this document ...

Page 181: ...selection affects only the on side PFD Metric Altitude Selection The metric altitude display can be selected on the on side PFD by using this line select key The power up default mode is the last selected state of this display Baro Set Units Selection The pilot and copilot can select the units IN or MB for the baro altitude set data on their respective PFDs The power up default is the last selecte...

Page 182: ...provides a grid open MLS select discrete at pin J1 FF Control priority over the MLS select discrete is as follows On side active NAV Cross side active NAV On side preview NAV Cross side preview NAV This implies that if the pilot has selected NAV 1 copilot selection of MLS 1 will not toggle the pilot s discrete Table 6 4 1 lists the primary cases for this MLS select discrete MLS 1 Select MLS 2 Sele...

Page 183: ...source On the pilot s side the first push of the key boxes the 1 and on the copilot s side the 2 is boxed Preview Mode Submenu Figure 6 22 2 shows the preview mode submenu with MLS The left No 4 line select key is used to select the MLS source as follows First push boxes MLS 1 pilot s side or MLS 2 copilot s side Second push boxes MLS 2 pilot s side or MLS 1 copilot s side c Third push removes the...

Page 184: ...th MLS Selected Figure 6 22 1 1 1 I 1 IPREVIEWI FMS 1 NAV 1 MLS 1 2 2 RETURN r 1 I r I t AD 34321 Preview Mode Submenu with MLS Selected Figure 6 22 2 22 14 00 Page 196 3 Apr 15 93 Use or disclosureof information on thispage issubject to the restrictions on the title page of thisdocument ...

Page 185: ...ode Menu See figure 6 22 4 While TCAS is installed the system mode menu provides a TCAS page selection on left line select key No 5 TCAS selections will be ON when boxed and OFF when unboxed Selection of the TCAS system page by either the pilot or copilot causes it to be displayed on both DCS TCAS system page will be selected on a last entered basis Power up default for the system page menu will b...

Page 186: ...nu with TCAS Selected Figure 6 22 3 I 1 I 1 1 I J HYD ENG START FUEL EXCEEDANCES APU BLEED WAYPT L I ST t f I m CHECKLIST r 1 I AD 34323 System Mode Menu with TCAS Selected Figure 6 22 4 22 14 00 Page 196 5 196 6 Apr 15 93 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 187: ... 2 10 cOMPASS LOGIC1 SELECT 29 PLAN LoGIC1 SELECT 28 PLANMINDS LOGIC1 ON 2 WO LUITER 21 LOGIC1 ON 26 UAVPOINTS LOGIC1 ON 25 AIRPORTS LOGIC1 ON 24 UAVPOINT IO LOGIC1 ON NAVAIO 10 LOGIC1 ON VERTICAL PROFILE LOGIC1 ON 21 FPLN SCROLLFORE LOGIC 1 SCkuLL 20 FPLN SCROLLBACK 31 LOGIC 1 SCROLL I II I BEARINGSELECT II I l fil l 3 IIEARIHG O 316 w 6554 LOGIC 1 SELECT 3 14 l DC 11 ONI V LOOIC 1 SELECT 313 LOG...

Page 188: ...TTESTSELECT LOGIC1 SELECT 4 l o SPAflE 51 I II SY Sl OE I l 1 l I i l l 5 15 12 HEXCODE 5 00 HYD 655a 5 5 01 AC PDUER 5 02 Dc PouER 5 03 MAYPTLlsT 5 04 FuEL s 05 APU BLEED 06 ENGEXCEEUANCE 5 01 cllEcKL sT 00 s RY 5 09 Em sT T OF oFF 5 5 11 10 SPARE OA OE SPARE CHECKLISTSELECT 9 ENERGEHCY LOGIC 1 EMERGENCY 58 ALINORHAL LOGIC 1 ADHORNAL NORMAL LOGIC 1 NORMAL LINE ADVANCE LoGIC 1 ADVANCE 55 PAGE ADVA...

Page 189: ...E 1 1 tiii ii fi l l l l l l t l 5 NAv 1 LOGIC 1 SELECT 655C 1 14 NAv 2 LOOIC 1 D SELECT 1 13 FKS 1 1 lZ LOGIC 1 SELECT WCs 2 J 11 LOUlC 1 SELECT HLS 1 L061C i SELECT 1 10 NLs 2 100IC 1 SELECT 11S 1 L N31C I sELECT 11S 2 7 OOfC 1 SELECT LTRK LOOIC 1 SELECT 16 0 SPAUE tli tfi t t l l 1 1 l 1 I 8 t5 NAu i l IC 1 SELECT 655E 8 14 NAv 2 100IC 1 SELECT 8 13 FNCS 1 8 2 100IC 1 SELECT FMCS 2 LOOIC 1 SELE...

Page 190: ...i l fi l l 1 1 1 11 15 4 REL COURSE l SELECT 11 3 1 SPARE 6564 11 0 SYNC SELECT LOBJC 1 SELECT I l l l l J 1 l l i i 5 4 REL COURSE 2 SELECT SPARE 6E66 120 SYNC SELECT II LOGIC1 SELECT 1 1 I I 110 0 7B1 I l J l 5 7 V15 j SET 80 250 BJNARY 0 511 KNOTS 6560 130 oISPLAYSELECT LOGIC 1 SELECT l l l 11 NoT f 110 000781 1 1 1 1 14 15 7 V25 o SET Bo 250 BINARY 146 1 656A 140 DISPLAYSELECT 1 LOGIC 1 SELECT...

Page 191: ...sPLAY SELECT LOGIC1 SELECT 1 11 J Q I I I 0007812 1 1 1 1 235 7 Vf psS ED SET 80 250 BINANV 0 511 KNOTS 236 1 OISPLAV SELECT 657C 230 LOGIC1 SELECT I l i I I l 1 1 1 1 I 24 24 15 FO C140 BAR 1 CROSS POINTER O CUE 657E 24 14 CAS HACH TOGGLE 1 TOOGLE l NG POINTERS oN o oFF 24 11 BAROFORMAT llno nl 24 10 W C UT 24 9 o II 1 ITBO I l l l lfi I 25 15 0 NAINT TESTUORO II 11 6580 I II I 1 1 I 26 15 0 SPAR...

Page 192: ...FUNCTIW NOTEFOFWT SCALE RSBRE93LUTICWLSB POSSENSE FTU_lSIMVAR l l 1 1 1 _l _ _ I 215 TCAS II I LOGIC 1 SELECT I l j l 5115 12 DE ID HEXCCOE 00 HYD cc TCAS fXl OE SPARE I Al I 76 1 I SPARE I I 70 MLS INSTALLED LOGIC1 INSTALLED l I 1 l j I I I I I Iii ...

Page 193: ...I POWER MATCHINGI I A MUX HOLD ISOLATION DATA B w MANCHESTER I UP NETWORK ENCODERI t I ARO DECODER L BUS SELECT A I CPU SYS SYS I 1A EPROM RAM M DATA DATA CLOCK 1 HDLC L m SERIAL INTERFACE BUS H L t SET W L BARO l I I I I 1 I J1 ENCODER DECODER I ANNUNCIATORS x I AND DRIVERS DAY NIGHT LAMP TEST DD v w b TO SHEET 2 I I ANNUNCIATOR POWER H L L J DC 884 Display Control ler Block Diagram Figure 6 23 S...

Page 194: ...TEST SELECT FGC RIGHT PRIORITY SELEC1 MAINT TEST ENABLE CALIBITEST MLS SELECT OUT FGC LEFT PRIORITY SELEC1 F CRT VIDEO CONTROLLER INTERFACE m PING PONG AMPLIFIER GI VIDEO HEATER i 1 x 4 J DEFLECTION AMPLIFIER Y I HV SYNC DISCRETE INPUT BUFFER I t DEFL STATUS KEYBOARD FUNCTION AND INTERFACE LINE SELECT KEYS 1 BRT J2 I COURSE SYNC NO 1 COURSE SYNC NO 2 E PARAMETER I SET ml INTERFACE I CRS SELECT NO ...

Page 195: ...AINTENANCE Honeywell M AM This page intentionally left blank 22 14 00 Page 198 9 Aug 15 91 Use or disclosure Of information on this page is subject to the restrictions on the title page of this document ...

Page 196: ...1 in 124 7 mm Height 7 62 in 193 5 mm Weight approximate 10 5 lb 21 3 kg Power Requirements 28V dc 15W Mating Connector J1 TR2P106P1O6PT OOO1 Mounting Tray Honeywel1 Part No 7003272 901 DA 884 Data Acquisition Unit Leading Particulars Table 6 6 22 14 00 Page 198 10 Aug 15 91 Use or disclosure of information on this page is subject to the restrititons on the title page of this document ...

Page 197: ...ch it receives The failure or removal of a DAU or the failure of a single channel in the DAU will not with the above noted exceptions affect any other sensor users This requirement is dictated by the dispatch capabilities planned for the Gulfstream IV which require a stand alone standby engine instrument display Parameters transmitted out of the DAU will be via ASCB A or ASCB B as listed in Table ...

Page 198: ... II II I 66A2 1131062344 4 l l l 3 15 3 RADIoALTITUDE TUO S COMPLEMENT 2553 FEET 32 0 SPARE 0 077930FT 6604 6654 66A4 II 1 1 I 415 12 SPARE l l l i l l 4 11 0 APUEGTDAU11 BINAJIY INT 4 11 0 SPARE OAU 2 O 1019OEGC 12 0 24i380 DEGC 6606ROAPUEGI 6656 II l i l 66A6 515 12 SPARE II 1 1 1 1 5 1 0 APURPUDAU l BINARY INT 5 11 0 SPARE OAU 2 O 122 3 RPM 12 0 02913656 X RPM 6608RDAPURPI 6658 II 1 I 6 15 10 S...

Page 199: ...l l I Al I 14 15 0 SPARE I 661A 666A 15 13 15 13 15 12 I l l l fi 15 FUELFILTER FAIL LOG 15 4 COMBNYD SYS FAIL LOG 15 14 FLT HYO SYS FAIL LOG COMB HVO SYS NOT LDG FLT HYD SYS NoT LOG IGNITION 2 LOG 15 11 CA8IN PRESSLOU LOG 15 11 MAIN CABINODORS LOG 15 10 RADIOALJ FAIL LOG 159 COUL ANTI ICEON LOG MING A l LOG IGNITION LOG 156 CALL 155 OIL PRESSURELOU 154 ENGINt 153 PYLONNIJT I 66UA IEDLOGIC l l I 1...

Page 200: ...DAULUNL 160 LOGIC 1 FDMNSL I l fi y l lLw c F 0 H l Au I 1 1 l ol l ol l 17 15 17 IS 17 14 i7 14 17 13 17 13 17 12 17 12 17 11 II II 17 10 179 178 17 B 11 7 17 7 176 176 175 174 17 3 170 SPARE STAB FLAP GROUNDSPOILERFAIL 51N6LERuDoiNLIHIT RUODERLINIT COW RUDDERNYD OFF FLT WOOER HVD OFF g l WI rcll ISOLATION VALVE ENGINESYNC AUX IIVD NOT TRU IK T LANDINGGEAR STATUS SPEEOURAKEEXT AFT E jU P NOI FUD ...

Page 201: ...FF SPARE EP14PPS FAIL SERVICE DOORS tRU FAIL BAGGAGE DOORS STALL BARROFF p 1 DAU 1 IIAU LoGIC 1 2 I AU l DAU 1 UAU LOGIC 1 12 OAU LOGIC1 N2 O NI 41 DAU LoGIC 1 2 DAU LoGIC 1 1 lIAU LOGIC 1 11 OAU LOGIC 1 82 DAU LOGIC 1 1 l AU LoGIC 1 12 I AU L061C 1 11 DAU TONE liEN FAIL LOGIC 1 II 82 OAU 11 1 II I 1 1 I 1915 8 SPARE 19 NUTCRACKER SNITCH LOGIC 1 196 6624 FOANUTSL OATT CHGR FAIL 100IC 1 VALIO O FAI...

Page 202: ... 27 11 0 UTILHVOPRESSURE DAU 1 BINARY lNT 0 4130 1 PSI 12 1 00B573 PSI IROAUNPI 21 11 0 AUX HVO PRESSURE DAU 12 RDAAIIP2 II II I 1 I I 1 1 1 2815 12 SPARE 281 I O EM BLEEDAIRPRESS BIMNY lNT O 122 3 PSI 12 0 0298656PSI RDAEDAPL II 11 I l l l l l 1 2915 12 SPAAE 29 11 0 UNEELBRAKEPRESS BINARV INT II 0 4130 1 Psl 12 1 008573 Psl RDAHBPL 11 I 1 610 025 32 I 1 l fifl l 3015 0 COW NVD ANTITY OAU l SINAN...

Page 203: ...5 12 SPARE 26 11 0 OC VOLTS B NARY lNT 0 51 047Voc II 12 0 0124657 VDC 27 15 12 SPARE l l i l 1 l 1 1 l 27 11 0 DC LOAD BINARY lNT O 163 066S 12 0 0398208 II ROADCLL 28 15 12 SPARE l l l l l l l 28 11 0 AUX DC LOAD II 0 Q i l fl l l 1 1 29 15 12 SPARE 29 11 0 AC LOAD II BINARY lNT O 203 47BII 12 0 0496894 1 1 RDAACLL I 30 15 12 SPARE l l l l l 1 30 11 0 AUXAC LOAO II l l f 1 l 1 1 l l 31 15 9 SPAR...

Page 204: ...A I 1 DA 884 Data Acquisition Unit Block Diagram Figure 6 25 22 14 00 Page 198 19 198 20 Aug 15 91 INPUT lWIE QUANTITY SERIAL DIGITAL 429 1 DC SYNCHRO 1 VARIABLE AC VOLTS 7 VARIABLE DC VOLTS 12 TACH 2 VARIABLE RESISTANCE 3 VARIABLE DC AMPS 3 SPECIAL PHASE REF MODULATED 1 THERMOCOUPLE 1 28 V DISCR E 56 GND DISCR 13 TOTAL ANMOG 31 TOTAL DISCRETE 69 DAU INTERFACE SUMMARY ASCB A AD 8974 RI Use or disc...

Page 205: ...This page intentionally left blank 22 14 00 Page 198 21 Aug 15 91 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 206: ...e DP 884 Dimmer Panel provides the brightness control for the six display units The controls consist of three dual concentric clutched potentiometers One dual concentric potentiometer each controls the pilot s PFD ND pair the EICAS DU pair and the copilot s PFD ND pair The panel contains no electronics The actual brightness control function takes place within the DUS With the DP 884 Dimmer Panel r...

Page 207: ...R2B L Cwl 10 K L 12 I I COPILOT ND H 15 H 3 cOpiLOT o BRT BRT CN L W 1 w 2 4 R3B Cwl IC K Du5 L 15 i L I COPILOT PFCI 16 1 H 3 cOplLOT FD BRT tSRT CNTL W 17 w 2 R 3A L Cwl 10K Du6 L IE I o 5 VDC Is DSi GND 2C CHASSIS GND SPARE 22 h DP 884 Dimmer Panel Schematic Figure 6 27 22 14 00 Page 198 23 Aug 15 91 Use or disclosure of Information cm this page IS subjecf to the restrictions on the title page ...

Page 208: ...Figures 6 28 and 6 29 and Tables 6 9 and 6 10 AO 302S4 FC 880 Fault Warning Computer Figure 6 28 22 14 00 Page 198 24 Aug 15 91 Use or disclosure Of information on this page is subject to the restrictions on the title page of this document ...

Page 209: ...ew alerting system CAS display portion of the EICAS display is received logically organized placed through system algorithms and transmitted from the FWC to the symbol generators over the ASCB Both channels of each DA 884 Data Acquisition Unit are monitored by both FWCS with errors between the two channels being annunciated on the CAS display The DC 884 Display Controller contains the selection ca...

Page 210: ...putting the specific LRU test commands Test results are recorded volatile memory only and displayed Critical flight data displayed on the PFDs and engine display are monitored and compared with the original source data Additionally the FWC assures the integrity of the other wrap around buses by monitoring for activity The monitoring task is performed continuously through the flight as a means of a...

Page 211: ...4 11001 27 5 11111 SPARE SPARE 4 2 LINECOLOR 000 BLACK 100 GREEN 001 RED 101 BLUE 2 010 AHBER 110 MAGENTA 2 011 VELLOU 111 UHITE 21 FLASH ENABLE I FLAsH O CoNTl ous 20 OISPLAY LINEENABLE 1 V1sABLEO BLANK l l l l l l l l l l l 3 15 8 CtlARACTEll 2 37 0 CIIARACTEN 1 ASCI 1 II l l i 1 1 1 1 1 1 1 4 15 8 CHARACTER 4 4 7 o CIIARACTER 3 ASC 11 II I IASC I 5 15 8 CHARACTER 6 l l l I l l 5 7 o CHARACTER 5...

Page 212: ...AIB f IELOOISPLAYENABLE 1 VISABLE O BLANK 523 2 52 1 BLUE FIELOFLASH ENABLE 520 BLUE FIELD DISPLAYENABLE 1 FLASH O CONTINUOUS I vlslOLE 0 BLANK I l l l l l l l 62 15 0 HESSAGELIST CHECKSUM sun OFuomsFM ALL AcTIvERED tiEs3A6Es II II 699A 0 0 I II I 63 15 0 MAINTENANCE TEST l l l II II 699C I 64 15 0 MAINTENANCE TEST l l i 1 1 I II II 689E 65 lNPUTLMSCRETES I l l l 1 1 1 65 15 L FUEL SHUTOFFOPEN LOG...

Page 213: ...lStT lO O l l I I 1 1 1 II i l i II I l l I 74 SPARE 74 117 II i fi lfi AyEo lEN 13 I II 1 l l l IS SETTO 1 I l i i i l l l l l l l 74 CHECKLIST TEXTSENTlN FR t4ES LINES1 2 3 74 74 74 74 H 74 74 74 74 74 74 15 13 8 5 4 2 ii 1 14 a CONTROLUORO SPARE 4 5 6 FRANE2 3 7 0 9 60L 2 FRAME4 5 10 11 12 FRANE6 7 CHECKLIST L NE NUMBER 0000 SPARE 0001 1100 LINES 1 12 1101 1111 SPARE CHECKLIST CONTROL o 9 A B c...

Page 214: ...ACTER 13 ASC1 II I IASC 68C0 0 i i l 1 82 15 8 1 1 I CHARACTER 16 82 7 o CHARACTER 15 II Ascll I Imcl 68C2 I II 1 83 15 8 CHARACTER 18 l i 83 O CHARACTER 17 ASCI 1 II II 68C4 1 84 15 8 CHARACTER 20 ASC11 l l l 1 1 1 84 0 CHARACTER 19 II ASCI 1 I IA C 68C6 1 I 1 1 85 16 8 CHARACTER 22 l I 85 7 O CHANACTER 21 II 1 l l l l l l l I 86 15 8 CHARACTER 24 86 o CHARACTER 23 ASCI I l l IASC 68CA 1 0 87 15 ...

Page 215: ... i iiiii ii l l l l l l 117 117 ENOING ATTRIBUTES 117 15 11 LINE NUMBER 68F4 BINARY 0 15 5 117 10 8 COLOR STANDARD COLORCODE 2 117 1 3 CHARACTER NW4BER BINARY O 63 5 1172 0 SPARE I l l l l l l l 118 CNECKSU14 II 1 ICRC 119 ERRORCHECK II l l 120 NOLC FLAG II l l 68F6 l 1 l I l l m g 68F8 3C5 l l l l l l g l l l l l l ...

Page 216: ...ECTIONAL DATA LOCAL BUS I Ill tRINC Al I ASCBA2 748 BUFFER RAM MAILBOX 6A X 16 BIT BuF 4 EACH DUAL CHANNEL 42s SERIAL 10 F BuS BUFFER J DIRECT MEMORY ACCESS SERIAL 0 CONT LOCAL 9 11 a 12 RECIEVERS 1 1 R BuFFER SERIAL VO MANCHESTER CONT ASCB CODEJU ASCB 1 DECODER MUX At40 BUFFER ARINC DATA OUT QASCB2 AAt RS 232 AD 14389 1 R2 FC 880 Fault Warning Computer Block Diagram Figure 6 29 Sheet 1 22 14 00 P...

Page 217: ... J 1 J MEMORY AS I POWERSUPPLY CONTROL CIRCUITS I I BUFFER AODRESS A6 DECODER r I i POWERSUPPLY 28Vcc TRANSFORMER CIRCUITS A FC 880 Fault Warning Computer Block Diagram Figure 6 29 Sheet 2 P CONTROL 1 CHECKLISTMODULE AS AD 143w R1 22 14 00 Page 198 35 Aug 15 91 Use or disclosure of information rm this page E sub ecf to the restrictions on the title page of this document ...

Page 218: ...cklist page is a detailed listing of the normal abnormal or emergency items within a particular procedure that a pilot may wish to check during flight operations The pilot has 10 pushbuttons which he uses to view the pages and indicate that he has completed and or checked the procedures or items These buttons are normal abnormal emergency enter recall page advance page reverse line advance line re...

Page 219: ...dex mode Emergency checklist mode Minor Disclaimer listing mode Autocallup mode This is a subset of emergency checklist mode The checklist module installs through the top of each FC 880 Fault Warning Computer in the A3 card slot Gulfstream Aerospace controls the software for the checklist module and attaches a GAC part number decal on the unit for reordering 22 14 00 Page 198 37 Aug 15 91 Use or d...

Page 220: ... FZ 820 Flight Guidance Computer See Figures 7 1 and 7 2 and Tables 7 1 and 7 2 AO 20325 FZ 820 Flight Guidance Computer Figure 7 1 22 14 00 Page 198 38 Aug 15 91 Use or disclosure of information on this page IS subject to the restrictions on the title page of this document ...

Page 221: ...around the In or The FGC has a dual processor architecture each Drocessor Derformina different control and computational functions the A processor per orms the outer loop flight control computations while the B processor performs the inner loop flight control computations as well as the autopilot and yaw damper servo loop closures Each processor monitors the other processor s flight control functi...

Page 222: ...nputs are latched however each processor has independent access to them The serialized discrete outputs to the control panel are solely under the control of the A processor The heartbeat monitor and power supply monitor interlocks ensure disengagement of the FGC in case of a processor failure a software failure a power supply failure or a power outage The servo drive engage interlocks ensure that ...

Page 223: ...UNSTATUS s vAL o o FAIL FAPFDSTL 26 EITHERCNANNELENGAGED LOGIC 1 EITIIER CIIANNEL ENGAOEO 25 FGC SENSONVALIOATILNI COMP LOGIC 1 COMPLETE COLD STAIIT LOGIC 1 START 01SENGAGEANNUNCLEAR CLEAN TRANSITION FROM LOGIC 1 TO LNIC O 22 AUNONNAL DISCONNECT L061C 1 ABNORMALDISCONNECT 21 RIGNTSEL LEFTSEL 20 1 RloHT 0 LEFT TCS ACTIVE FAFCSELL 3 LOGIC 1 ACTIVE I l l FAPTcSAL I l 1 l t f 3 15 14 AllRS lRS OAIA SE...

Page 224: ...ER 71 0 31 I fi l l l l l l l l 7 15 14 OFFSET IUENT No oFFsET 01 NEGATIVEWFSET 500C 10 poslTlvEoFFsET 11 SPARE 7 ROLL NODESARUEO IOENTSTRING 1 13 6 SPARE 1 5 o MOOE ARNEO 10ENT INTEGER II l 1 o 53 1 815 0 SPARE l l 1 1 II II 508E 915 1 SELECTEO HEADING SEMICIRCLE I O J60 DEG 115 I y t l l 90 FLAG LOGIC 1 VALIO II II 5090 FAPNOSEL I 11610000078 I 10 15 0 NACN IIEF SYNC OATA 1 DISPLAY 1 1 2 56 MACH...

Page 225: ...OUI WANO BAR 3 D 90 DEG 31 m IN VIEU LOGIC LOGIC 1 IN VIEN 5024 II I 1 60 5DA4 FAPFDRIL i II I 20 FAST SLOU COmlUI l s m m II 1 1 5BA6 gan i II F 21 STATUSFLAGS I l I mz ea 21 15 EC MOOE ON LOGIC 1 W1 C Cvg 21 14 GS VALID IN 8C LO MC 1 vAL1o 5BA8 XI A EI SPARE rz v RAO All TEST INHIBIT LOGIC 1 INHIBIT 5 21 11 LOC AZEXCESSlltE DEV LOGIC I ACTIVE m 21 10 GS EL EXCESSIVE OEV LOGIC 1 ACTIVE m 7 219 AP...

Page 226: ...4VCAP LOGIC 1 ON II 1 1 FAPVNCPL I 23 LATERALWOE ANNUM II I 1 1 23 FLAGSTO EFIS 23 15 HHOLO LOGIC1 ON 5BAC 2314 ACTIVE NDoECAP TRK CAPomTHK 23 13 VA N FAPLACTL LOGIC1 ON FAPLNARL 2312 LOGIC1 ON FAPVORAL 23 11 LOC CAP LOGIC 1 ON 23 10 TRANSITION FAPLOCCL LOGIC 1 ACTIVE FAPLNATL 239 SPARE FAPvAPAL 238 BC ARM LOGIC 1 ON FAPBCAL 237 MC ARM LoGIC I ON FAPAPLAL 236 AZ AIM LOGIC 1 ON 235 AZ CAP LOGIC 1 O...

Page 227: ...ENTION 26 CAS tUCH TARGETTO FNC 5B02 26 15 1 INTERVENTION SPEEDTARGET TMOO S COMPLEMENT 2 0 MACH 26 15 1 i4 0 000244 0 000061 FORMARD 1 1024KNOTS 14 0 125 0 03126 FORUARD 260 CAS MACNLOGIC IuNACHO CAS I l lI O 5PLAY I 1 6 10 0130 0 0 3D I 27 15 0 V S REF SVNC DATA j l l 4 426 67 FPS II II 5BI14 I ti l fi fi l 1 28 15 0 V SREFSVNCDATA CONTROL LAul 426 67 FPS II l li l l go 5006 1 610 275 o 275 I 29...

Page 228: ...TEST SPARE 11 11 I I 1 1 1 1 35 CROSSSIOE FGC STATUS 35 15 4 SPARE 35 3 CROSSAUTOTHROTTLE ARM P6 58C4 LOGIC 1 ON 352 CROSSSIDE STUCKPUSIIBUTTON LOGIC 1 STUCK 35 1 CROSSTRIM IN LIMITSFLAG LOGIC 1 ON 350 CROSSTRIM WITCH FLAG LOGIC 1 ON II II 36 15 2 SELECTEOALTI TUOE I TUO S COMPLEMENT i li l fi l l l 36 1 ALTITUDE FLAG S1 LOGIC 1 ON 360 5BC6 ALTITUDEFLAG 2 LOGIC 1 ON II 1 1 l l l l lii SENSORMIS CD...

Page 229: ...P LOGIC1 ON FAPENTUL 383 ELEVHISTNIN NOSEDN LOGIC 1 ON FAPEMTDL 38 Z TCSENGAGE LOGIC1 ON INLIMIT FAPTCSEL LOGIC1 ON FAPTRMLL FAPAPTFL 38 1 TRIM I 380 AP TRIM FAIL LOGIC 1 ON I l l l l l i i 15 10 SPARE 5BCC 399 CPL DATA INVALID LOGIC 1 ON 398 ALT OFF LOGIC 1 ON 391 HAV lUSMATCli R SEL LOGIC 1 ON FAPNVNRL 396 NAV 141 SHATCH L SEL LOGIC 1 ON FAPNVHLL 395 SELECTINH161 T LOGIC 1 ON FAPSELIL 394 ENGAGE...

Page 230: ...EARTBEAT MONiTOR SERVO DRIVE ANALOG ANDPOWERSUPPLY INPUT RAM MONITOR INTERLOCKS ENGAGE INTERLOCKS PROCESSING t DATA CONV ON 4 o B PROCESSOR DIGITAU QINNERCONTROL PULSE WIDTH 4 CONTROL LOOPS CONVERSION DISCRETE ATTITUDE LOOPS INPUTS DATA SERVO LOOPS IIOCONTROL MONITORING 1 PROGRAM MEMORY 4 SCRATCH PAD 4 MEMORY FZ 820 Flight Guidance Block Diagram Figure 7 2 AO 1SS32 Computer 22 14 00 Page 198 48 Au...

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Page 232: ... maximum 8 2 lb 3 72 kg Power Requirements Primary 28Vdc 1 6A Lighting 28Vdc 1 OA Mating Connectors J1 J2 Both connectors use strain rel MS27473E20B35SB MS27473E20B35SD ef MS27506 A20 2 Mounting Unit Screw Fasteners GP 820 Flight Guidance Controller Leading Particulars Table 7 3 22 14 00 Page 198 50 Apr 15 93 Use or disclosure of information on this page is subject to the restrictions on the title...

Page 233: ...alternate between right R and left L couple The button annunciates L or R to indicate which PFD has been selected During a dual approach both PFD CMD indications shall illuminate to that the system is averaging data received from both sides The flight guidance computer selections for attitude heading and DADC references are accomplished independently of PFD CMD Autothrottle Arm A T ARM Button This...

Page 234: ...h bank status shall occur when descending through 28 500 feet Manual selection of high bank status shall be allowed above 29 500 feet and manual selection of low bank status shall be allowed below 28 500 feet When in low bank status the button annunciates 1 2 9 Back Course BC Button This pushbutton is used to select and deselect the back course function and display for ILS back course approaches 1...

Page 235: ...ynchronize to the current aircraft heading 15 Vertical Speed V S Button and VERT SPEED Window and Knob The vertical speed knob is used to input values of vertical speed to the system The VERT SPEED window and the V S target area on the PFD display the selected value when the V S mode button is annunciated ON While TCS is engaged the PFD displays dashes the VERT SPEED window blanks 16 Altitude Pres...

Page 236: ...M UP E MAINTENANCE TESTSEL s IAw TSS7 No 1 u CS TFIIMDN ESASLE s wow 7 TW14 NO 1 K TCS NO 1 7 A POIS CON1201z Vm OISEND ENQ NO 1 71 M l DISENQJENO No I 7 o SERIAI OATA OUT W 1 1 SPEED TACH NO 1 M lm c 1 1 SPEE22TACM W 2 1 II mm TACH w I J 1 HW TACS NO 2 II vfs TAcH SD 1 I bvfs TACM w 2 cnAssJs GsD 9 WAssls QND 1 H SERIN DATA IN s27 2 L ltt lx rb u Ill I I J H PAWL s wcw IN w 2 L HI PASEL CLOCM IN ...

Page 237: ...This page intentionally left blank 22 14 00 Page 198 57 Aug 15 91 Use or disclosure of information cm this page IS subject to the restrictions on the title page of this document ...

Page 238: ...6 05 mm Height 2 63 in 66 80 mm Weight maximum 1 5 lb 0 68 kg Power Requirements Potentiometer Excitation t15Vdc 1 6vA Lighting 5 V ac or V dc 5 0 VA Mating Connector J1 MS27473E12B35SA Mounting Unit Screw Fasteners PC 880 Turn Pitch Controller Leading Particulars Table 7 4 22 14 00 Page 198 58 Aug 15 91 Use ordisclosure Ofinformation on this pageissubject tothe restrictions on the title page of t...

Page 239: ...ters to ensure fail passive pitch wheel operation Pitch wheel operation is inhibited in GS FLCH VS and VNAV modes 2 TURN Knob Rotation of the TURN knob out of detent results in a roll command The roll angle is proportional to and in the direction of the TURN knob rotation The TURN knob controls dual detent switches and potentiometers to provide identical roll commands to both flight guidance compu...

Page 240: ...TURN AS5Y NC 1 I I I l__ ________ ___ J I I I I 1 CHASSIS GROUND TURN CONTROL WIPER OUTPUT SYSTEM 1 TURN CONTROL WIPER OUTPUT SYSTEM 2 i I I I I 10 I I I SYSTEM I TURN CONTROL OETENT SWITCH TURN CONTROL DETENT SWITCH SYSTEM 2 TU7N CONTROL DETENT SWITCH TURN CONTROL OETENT SWITCH I NOW ON I __ NOSE I UP I PITCH WHEEL I I Al PITCH WHEEL ASSY H I I I I I I 19 I I I 21 I T2 I i I I I I I I I 22 I I I ...

Page 241: ...Honeywell r cE This page intentionally left blank 22 14 00 Page 198 63 Aug 15191 Use or disclosure of reformation cm this page is subject to the restrictions on the title page of this document ...

Page 242: ...STRE4MIV and TM 260 Dual Trim Servo TB 261 7 11 and Table 7 5 SM 600 Dual Servo and SB 600 Bracket Figure 7 7 TM 260 Dual Trim Servo and TB 261 Bracket Figure 7 8 22 14 00 Page 198 64 Aug 15 91 Use or disclosure of information on this page is subject to the restrictions on the tnle page of this document ...

Page 243: ...ual servo translates electrical inputs into a brake controlled rotational mechanical output The tachometer output is fed back to the flight guidance computer servo amplifier to null the command signal The SM 600 synchro position output is not used in the system Each servo of the dual servo is identical and is connected to a separate output connector Servo connector J1 is connected to the pi1ot s f...

Page 244: ...2 J1 12 J1 13 SM 600 Dual Servo Schematic Figure 7 9 22 14 00 14 W14T BLK 014N J2 WHT BLK ORN 3 15 SHIELD GNO 13 5 5 wHT BLK ORN 16 Iz 1 TACNOMCTER II OUTPUT OLX 7_ pOLARtTVsnowtt foa CCWDWU RO1ATION Y II WHT G 4F SLU r I M O K RN 0 46uF 8 2T EZ i I SLK I lF REO 1 7 d I Ll 1 Vlo I I I mm tt31 19 1 1 10 I T J WHT REO VIO I TBI ZO wHT RED GRN I i R4 I 1 wNT BLX GRN 1 I e I I 181 21 I t I DLK W4 16 W...

Page 245: ...0VOC COLI VDLTAIX I CLUTCM wHTcQ EXCITATION 101 12 13 I WHT BLN ORN 15 SHIELD GNO ts S5 4 Will 55 12 i i TACHOMETER WHT BLK ORN II OUTPUT BLK 7_ POLARITY SHOWNFOR C WORUMROTATION u 0 II WHTz6 RN WMT I I 1s1 21 r I 21 3 uF i 0 1 I 161 22 TBI E2 I I KU I LAF wwl i 1 I Ll I ED f 1 I nco Vlo I km Is I 1 1 I LK 10 I lWI 19 WH1 REO GRN II I CR4 I 1 1 I ob WHT BLK GRM I 1 I T81 20 i A3 CLUTCH i I 1 I h S...

Page 246: ... 3 i 29 1 WHT II I I II 4 I CR3 I IIB II I GRY 2 I 17 1 Vlo I 6 Cw I 4 28 I 1 I 4 CR4 1 I B 1 16RN II 8 2 K xl I CR5 HT 7 I I I x2 1 8 1 IWHT ORNI 7 L I K2 __ CR6 lWHT RNl I 216 TBl 51 l j lo lo 11 11 SPAR la 12 240 B8 lJl _ l lNPi SPLINE L __J_J h c 1 1 LIMIT SWITCH LIMIT SWITCH ES AD 656 TB 261 Bracket Schematic Figure 7 11 22 14 00 Page 198 71 Aug 15 91 Use ordisclosure ofIntonation on this pag...

Page 247: ...e Echo signals received by the antenna are routed through the waveguide to the RT and then to the receiver The receiver processes the signals encoding them into one of four levels depending on their intensity scan converts them and enters them into the random access memory This memory is read in raster scan format and its output is delivered to the indicator and electronic flight instruments bQ 53...

Page 248: ...dB at RT flange Pulse Width and Pulse Repetition Frequency Range WEATHER Scale NM w 300 180 15 200 180 15 100 440 6 50 600 3 5 25 600 3 5 10 600 3 5 MAP u 15 15 6 2 2 2 STC Digital Control WX 6 dB Octave at ranges shorter than Beam Filling 9 dB Octave at ranges greater than Beam Filling MAP 6 dB Octave WR 800 Receiver Transmitter Leadi b r i ulars 22 14 00 Page 198 73 Aug 15 91 Use ordisclosure of...

Page 249: ...na Turn Around 256 vertical x 256 horizontal 236 vertical x 240 horizontal displayed 32k REACT 3rd plane Not inhibited in any mode Approximately 1 degree from scan end antenna goes to half and then quarter speed before turn around After turn around antenna goes from quarter speed to half speed and reaches full speed approximately 1 degree after turn around Mating Connectors Cannon KPSE 06F22 55S a...

Page 250: ...OR 1 1 MAGNETRON 1 EN120DER It m i 4pyl N b 4 9 RNG 1 4 4 MODULATOR PULSE 4 PROGRAMMER 1 GENERATOR MODE 1 4 4 t T t ANTENNA i I I 1 1 5 I I ARINC 429 I L m aDq RCVR ELEVATION I DRIVE ELEVATION 1 DRIVE 4 DA POSITION CONVERTER 4 ANTENNA FEEDBACK I AMPLIFIER I 25 DECODER I AND T i SCI BuS lNDlcAToR CONTROLLER S 1 1 I Scl I MEMORY I RCVR 1 J w I i I 1 ARINC 429 1 SAMPLE AD STABILIZATION TILT PITCH ROL...

Page 251: ...Honeywell ii c This page intentionally left blank 22 14 00 Page 198 77 Aug 15 91 Use or dkclosure Of information on this page is subject to the restrictions on the title page of this document ...

Page 252: ...mm Width 5 75 in 146 1 mm Height 1 87 in 47 5 mm Weight 1 9 lb 0 86 kg Power Requirements Primary 28 V dc 0 06 Ampere Lighting 5 V dc 0 92 Ampere Mating Connector J1 MS27473E14A 18SA Mounting Unit Screw Fasteners WC 81O Weather Radar Controller Leading Particulars Table 8 2 22 14 00 Page 198 78 Aug 15 91 Use or disclosure of information on this page is subjecf to the restrictions on the title page...

Page 253: ...l areas or mountainous terrain where it may be necessary to tilt the antenna toward the ground to see weather ahead The GCR annunciator above the switch lights to indicate to the pilot that he is in the GCR mode Rain Echo Attenuation Compensation Technique RCT Mode Rain echo attenuation compensation techniques automatically increase the receiver gain in real time as a function of attenuation due t...

Page 254: ...ontrol is in the OFF position when the MODE control on the other controller is in an operating mode mode other than OFF If the MODE controls on both controllers are in the OFF position the SLV annunciator on both controllers will extinguish RANGE Select Operating ranges from 10 to 300 nautical miles provide up to 94 156 square nautical miles of weather detection Selection of FPLN causes the radar ...

Page 255: ...3U6 OE1 OE2 OE3 OE4 OE5 OE6 T PROM A3U8 N N N N N N J4 LINE SCI P UART SERIAL A3U12 DRIVER sc N i DATA A3U7 TO R T I 1 DATA BUS TBO TB6 STOPS COUNTERS WHEN MAX LOGIC OR MIN TILT IS REACHED GATES A3U3 A3U5 A3U13 A3U19 I UPIDOWN DIGITAL 0E5 N TRI STATE COUNTERS COUNT BUFFERS P A3U4 A3U14 A3U1O OE6 N A3U17 A3U15 b t ANALOG DIA A3U9 l l COUNTERS TO CORRECT ERROR c AMPLIFIER t 8 8 wv wrr tn A COUNTERS ...

Page 256: ...MAINTENANCE Honeywell h This page intentional ly left blank 22 14 00 Page 198 83 Aug 15 91 Use or disclosure of information on thispage is subject to the restrictions on the title page of this document ...

Page 257: ...9S07 X Band Quick Disconnect Airtron 63906 Operating Characteristics Power 27 5 V dc 1 3 A nominal 115 V ac 50 mA nominal Scan 60 and 120 degrees Scan Rate 14 looks per minute 120 degree scan 28 looks per minute 60 degree scan Polarization Horizontal Stabilization Line of sight 30 pitch or roll with 0 tilt Tilt Excursion 15 degrees up and 15 degrees down Elevation Excursion 30 degrees up and 30 de...

Page 258: ...rees for a total scan of 120 degrees in accordance with the logic drive signals from the RT The sector scan rate is 14 looks per minute for the 120 degree scan The antenna pedestal elevation assembly permits the radar beam to be tilted up or down 30 degrees in each direction for a total of 60 degrees when actuated by a combination of signals external to the antenna pedestal and the aircraft IRS AN...

Page 259: ...IATOR DIAMETER RATED PEAK POWER OUTPUT AND DUTY CYCLE THE GREATER OF THE DISTANCES CALCULATED FOR EITHER THE FAR FIELD OR NEAR FIELD IS BASED ON THE RECOMMENDATIONS OUTLINED INAC NO 20 68B The American National Standards Institute in their document ANSI C95 1 1982 recommends an exposure level of no more than 5 mW cm2 Honeywell Inc recommends that operators follow the 5 mW cm2 standard Figure 8 7 s...

Page 260: ... JANCE Honeywell ULFSTREAMIV This page intentionally left blank 22 14 00 Page 198 87 Aug 15 91 Use or dkclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 261: ...tion and ground mapping The WU 870 incorporates an 18 inch flat plate antenna and contains all the circuitry required for transmitting receiving signal processing scan conversion serial data and control interface I to the other system components as well as the EDS WU 870 Antenna and Receiver Transmitter Unit Figure 8 8 22 14 00 Page 198 88 Apr 15 93 Useordisclos rreof information on this page issu...

Page 262: ...ange PRF 120 240 360 and 480 Hz determined by selected range Receiver Noise Figure 8 5 dB typical IF Frequency 35 MHz IF Bandwidth 0 8 MHz nominal Video Bandwidth Commensurate with selected pulse width STC Present in all modes MDS 112 dBm nominal on 300 NM range Dist layedRanqes WX MAP 5 10 25 50 100 200 and 300 NM full scale with five concentric range rings white for WX green for MAP Flight Plan ...

Page 263: ... PROCESSOR E sl PICTLIRE BuS CONTROL BuS D q WEIGHT ON WHEELS NO i AAS SELECT NO 42s ADC NO DISCRETE ONIOFF INTERFACE PARALLEL ALTITUDE SELECT NO i 1 lNO MFO E LT EFIS RT EFIS 7 0 J Q EL MOTOR ORIVE 2 MOTOR DRIVE L Az MOTOR AZ EL EL FEEOBACK FEEOBACK MOTOR EzF Ro LTEF s RTEF s AD 14317 R3 WU 870 Antenna and Receiver Transmitter Unit Block Diagram Figure 8 9 22 14 00 Page 198 90 Aug 15 91 Use or di...

Page 264: ...WER OUTPUT AND DUTY CYCLE THE GREATEROF THE DISTANCES CALCULATED FOR EITHER THE FAR FIELD OR NEAR FIELD IS BASED ON THE RECOMMENDATIONS OUTLINED INAC NO 20 68B The American National Standards Institute in their C95 1 1982 recommends an exposure level of no more Honeywell Inc recommends that operators follow the Figure 8 9 1 shows the MPEL for the 18 inch antenna power 2 RADIUS R AIRCRAFTLUBBER LIN...

Page 265: ...ight 1 9 lb 86 kg Power Requirements Primary 22 to 32 V dc 8 5 watts Lighting 5 V ac dc at 1 0 A Mating Connectors maximum nominal J1 MS27473E14A 18S J2 MS27473E14A 18SA Both connectors use strain relief MS27506 B14 2 Mounting Unit Dzus Fasteners WC 874 Weather Radar Controller Leading Particulars Table 8 5 22 14 00 Page 198 92 Aug 15 91 Use or disclosure of information on this page is subject to ...

Page 266: ... Plan 2 5 55 2 60 4 75 4 100 4 1 150 6 200 250 Inactive 2 5 55 It should be noted that while target alert is functional at the above ranges it is improbable that a realistic target would be strong enough to be detected if its range exceeds five times the displayed range Also note that the target alert is inactive within the displayed range Selecting target alert prevents variable gain from being s...

Page 267: ... of the PRIMUS 870 permits detection of hazardous turbulence in areas of otherwise weakly reflective rainfall Any areas shown as turbulence should be avoided TRB may only be engaged in the WX mode and in selected ranges of 50 NM or less 5 Brightness BRT Control The BRT control is used to control radar raster information brightness intensity of the navigation display ND 6 GAIN A single turn rotary ...

Page 268: ...ed bv settina the mode control to G P The TILT control is turned down until the desired amount of terrain is displayed The degree of down tilt will depend upon the aircraft altitude and the selected range The receiver STC characteristics are altered to provide equalization of ground target reflection versus range As a result the selection of preset GAIN will generally provide the desired mapping d...

Page 269: ...range and beyond only heavy and extremely heavy rain can be detected The COLORCALN feature will not allow green or yellow targets at this range and will only show targets as red and magenta NOTE The boundaries at which these COLORCAL changes occur are affected by the REACT compensation system if it is active These boundaries are irregular in REACT COLORCAL is disabled when in variable GAIN 12 Hidd...

Page 270: ...oltage Failure 1500 Volts min or 2700 Volts max 04 24 Mixer Current Failure 05 25 AFC Lock Failure 05 35 AFC Sweep Failure 06 26 Fan Voltage Abnormal 07 07 07 07 07 07 07 07 07 04 07 14 17 27 34 36 37 30 Digital Air Oata Failure Pulse Pair Processor Failure Parallel Altitude Failure EPROMTest Failure VLSI Test Failure Loss of Video Ready Interrupt DADC Altitude Failure Analog Altitude Failure If i...

Page 271: ... MUX OE3 N 10F8 0E4 N A3U14 0E5 N OE6 N OE7 N N L Wx SBY h AP IW 17S DELAY POR A2U1 t POR 4 J A2U7 TST TURB IrBo TB6 1 I 0E3 N Ja 4E POWER 15VDC 28V SUPPLY INPUTPOWER AIU1 15VDC AIQ1 5VDC 1 I JsJ 1 RNG 2 RNG 2 D RNG 22 E RNG 23 FPLN A2U6 I POWER SUPPLY NOTE A REFERENCE DESIGNATIONSARE AS FOLLOWS GCR T Al POWER SUPPLY CCA 7007108 A2 LOGIC 1 CCA 701 3373 A LOGIC 2 CCA 701 3378 AD 15846 R3 Radar Cont...

Page 272: ...INTENANCE Honeywell 8 W L This page intentionally left blank 22 14 00 Page 198 101 Aug 15 91 Use or disclosure of information on this page is subject to the restrictions on the title page of thts document ...

Page 273: ...ation Computer See Figures 9 1 and 9 2 and Tables 9 1 9 2 and 9 3 Ao lle41 NZ 920 Navigation Computer Figure 9 1 22 14 00 Page 198 102 Apr 15 93 Use or disclosure of informationon this page is subject to the restrictions onthe title page of this document ...

Page 274: ...navigation normally optimizes the present position calculation accuracy by utilizing DME distance data from at least two stations versus VOR bearing and DME distance data from a single station The VOR bearing input is subject to error due to bends in the beam multipath effects station misalignment etc Using multi DME the bearing information from a station may be calculated instead of simply measur...

Page 275: ...nt to the pilot other than a periodic change in the receiver s frequency display and the RMI pointer Provision is included for remote tuning of receivers via the CDU or manual tuning through the radio control heads For remote tuning via the CDU the pilot can choose to enter the station identifier or enter the frequency The frequency of the entered station found in the database is output to the nav...

Page 276: ...The navigation computer also provides guidance and map information to the pilot via the navigation display The navigation computer will output to the Nav display the positions of 51 waypoints lateral and vertical 10 closest Navaids and 9 closest airport reference points as well as holding pattern information The display will include the course line between the waypoints The waypoint and course lin...

Page 277: ...SSSIOE NAV FP LOAOED 1 _ cHANGEoBEcAusEcRoSss OEFLIGIIT PLAN LoAoEo A 2 10 LATERALOFFSET 1 FLYINGLATERALoFFsET 29 28 7 2 2 2 26 4 22 21 20 OEGRAOEO ACCURACY 1 VALIO ithflGAT1014 t ux i lTS RAOIO 2 LTS ONLY 1 RAO1OONLY 0 DEAD RECKONING M4G TRUENOOE 1 TRuE WOE NUMUERUF WPTS TO SEOUENCEINTEGER CIIU MESSAGE ALERTING ONLY 1 MESSAGE OEAD RECKONING 1 oEAo REcKoNING APPR SENSITIVITY HIGH 0 Low o 3 2 1 WAV...

Page 278: ...MPLEMENT I II I l i fiiI 64 DEG 15 0 00390 0 00195 RIGHTBANK 200 II l VAL 10 0 INVAL 10 II 6026 FASLIACVL 21 15 1 MA tlA ARGET I I 510 mo678 I THO SCOHPLENENT l l I 1 28MACN 210 l VALlo l ALlo II II 0 0000391 6028FASMACTL I II I l fil i l 22 15 1 VE N AL SPEEOTARGET THO SCOMPLEMENT 16304 FT PERMIN 15 1 0 0 5 FPt4 220 CLlUU II l VALlo O INVALlo 602AFASALRflL 23 15 2 ALTITUDE TARGET l lfi l l l l I ...

Page 279: ... 15FE81 I I I SPME II 6038 1 3015 0 II I 15FEAI I Ii II 603A MAINTENANCE TEST I l l l l l I 15 lWINtENANCE OATA AVAILABLE I MIMT oATA AvA L SFEC 31 14 TEST IN PNOGRESS 1 TEsT IN PRoGREss 31 13 SELECTEDFOR TEST ioic 1 TNIS FMS IS SELECTEOFOR TEST 31 12 MAINTENANCE TESTOISCREIE I _ MAIMT su TcHIs OM 31 11 TRuE AIR SPEEO 80 KTS 1 TRUE AIR SPEED GO I TS OR INVALIO 31 10 vow 1 MOM 31 9 GROUNOSPEEO 50 K...

Page 280: ...C 1 TEST 1 14 VALID LU31C 1 VALID 1 13 MTABASE TRANSPSR LOGIC 1 TRANSFSN 1 12 11 SPARS 1 10 8 UmmER o 7 nsx 1 7 0 PMCSAODSSSS 12 n LSPT 16 E RIGUT I l l l l l l l 2 15 0 II l l 1 l l i l I I l l l l l i l l l l l l l l l l l l l l l l RSSBWSD II l l l l l l l l l l i i i l l t l t l l I l l l l l l l l l l l l l l l l l l l l l l i t i l l l t l l l ...

Page 281: ...C D CRSSNV SPESD TWI S CCU4PLR4SNT 1024 KNOTS 14 0 125 0 03125 15 1 FORWARD SPARS D 15 0 VALID LOGIC 1 VALID I l l l l l l l l l l 16 RSSBRVED I l l l l l l l l l l 1 l l l l l l l l l l II l l l l l l l l l 19 15 2 UNITS V SPBSD TIW S COHPLDISNT 1 1024 KNOTS 14 0 125 0 03125 19 1 PORUARD SPARS 19 0 VALID LOOIC 1 VALID 1 1 l l l l l l l l l GR MTNV SPEED T s c L T 1 1024 KNOTS 14 0 125 0 03125 FOR...

Page 282: ... l l l l l l l l l l l l l l l l l l l l l l l l l l 1 1 30 15 1 TIM TO UAYPOINT BINANY 15 0 015625 0 007812 G g 30 0 FDD l l l l l l l l l l l z DISTANCETO DESTINATION o 15 0 25 0 0125 31 0 I l l l fi l g l l l l l l g 32 15 8 MACNETIC VARIATION SmICIRCLE o 8 1 40625 0 005493 BAST VAN 32 7 1 SPARE o 32 0 m l l fl l l l l i l l l 1 33 15 6 PARALLELOFFSET TUO S C PLRIENT 1 64 NN 33 5 o 10 0 125 0 0...

Page 283: ...TIVE 39 6 VNAVALTITUDEACTIVE LOCIC 1 ACTIVE 39 5 READNSU PLIGtlT PLAN LCGIC 1 READ 39 4 0 SPARS 1 1 l l l l l l l l l LEG SEQUENCE COUNT ho 15 s NAVLSG INTEG o 255 s 1 0 40 7 o PERF LSG INT SR II l l l l 1 1 l l l 41 15 0 ACTIVE VERTICALLEG POINTER l lf flfl l l l l l l CURRENT VERTICALNOOE 42 15 ALT CAPTIME LOGIC 1 ACTIVE 42 14 CLINB DESCENT LOOIC 1 CLINS 42 13 klACRFLCll LWIC 1 ACTIVE 42 12 IAS ...

Page 284: ...l__ l l __l l i I l l li l 1 1 1 1 1 SDIICIRCJX 360 DEC N S 50 0 23 0 000043 DFG LTS 2 LAT VALID l VALID O INVALID l l l l l l l l l l l LTS 2 SENSORLONG l b Tw S XMPLWNT 180 DEG E U 23 0 000043 DEG 51 a LTS 2 LONGVALID l VALID O INVALID 51 7 o LTS 2 SENSORLAT msb 1 1 l l l l l l l l J 52 1S 0 LTS 2 SENSORLONG msw k l l l 1 1 1 l l l l LTS 3 SENSORLAT lSW SQ41CIRCLE 960 DE N S 53 0 23 0 000043 DSC...

Page 285: ...l l l l CUSTON DATA CNECKSffl l l l l l l l l l l l T ONARY MTA CtlECRSUN I l l l l l l l l l l 62 15 5 62 4 ACTIVE NAVCYCLE L IC 1 NSU 62 3 SINCLE SYSTEN BIT LOGIC 1 sINGLE 62 2 NASTER SLAVESTATUS 1 MASTER O SLAVE 62 1 CUSTOM CNECKSUN VALID LOCIC 1 VALID 62 0 TE14PORARY CNECKSUN VALID I L P31C 1 VALID l l l l l l 1 l l 63 15 0 SPARE USP 63 76 l l l l l l l 1 l J l l l l l l I I l l l l l l l l 79...

Page 286: ...6 12 6 11 6 10 69 68 ALTMTE DESTINATION TOP OF CLLMS 1 UAYPOINT 0003 a 0 4 UAYPOINTS 0004 E 5 9 WAYPOINTS 0005 U 10 14 WAYPOINTS 0006 B 15 19 WAYPOISTS 0007 E 20 24 NAYPOISTS 000S B 25 29 WAYPOINTS 0009 u 90 S4 WAYPOINTS 000A II 95 S9 WAYPOINTS 000B E 40 44 NAYPOINTS 000C ii 45 49 HAYPOINTS l l l l WAYPOINT IDENT CNARACTSR 2 ASCII CNARACTER 1 ASCII l l l l ASCII CNARACTSR 3 ASCII m l l l l ASCII C...

Page 287: ...TPOINT LA lSW II SMICIIWLE l l l l l l l l l 11 15 s WAYFOINT 1 LONW2UIWlsb SBIICIRCLE 11 7 o 24 0 000021 DEG MST LATITUDE msb l l l l l l l l l l l 12 15 0 lDNGITUDE msw l l l l l l l l l l l I 32 0 000000083 D EAST l l l u l l l l 14 15 0 C0URS6 INTO UPTS v I l fi l l l l l l l l l 15 15 0 TUO S CDMPLRfR T iilii l l l l l l l l l l i l l flfl l l l l l 1 l l l NSNT UAYPOINT DATA 17 30 I l l i l ...

Page 288: ... LONGITUDE 1sb SQ41CIRCLE mma I am I I I l l l l 1 1 1 1 u LONGITUDE maw w Wo l l l l l l l l l l 00 6 15 5 NAVAID 1 ELEVATION TkO S CCNIPLRfENT 1 20480 FEET 11 20 0 0 625 FT POS MT 2s0 6 4 O SPARE O 03 1 1 1 1 l l l l l l l c o NAVAID TYPE 2 7 15 NAVAID VALID LCGIC 1 VALID 7 14 DME LOGIC 1 DFIE 05 w 7 13 VOR LOGIC 1 VDR 7 12 ILS LOGIC 1 ILS w 7 11 nLs LfxlC 1 ULS 7 10 NOB L 31C 1 79 TUNED LCCIC 1...

Page 289: ... l l i l l l l l l NAVAID 3 17 23 l liiiiii ii iii ji l l l II l l l i l i l l NAVAID 6 38 44 l l l l l I l f f l l l 52 NAVAID 48 52 58 l 1 1 1 1 l l l l l l l 1 I I I I l I 1 1 II 1 1 l l l l l i l 1 I HAVAID 49 59 65 1 1 l l l l l l l l 1 NAVAID 10 66 72 1 1 l l l l l l l l l SPARB 73 76 II l l l l l l l i l 77 CHECNSOM II l l l l l l l 1 1 78 SRRORCHECK II l l i l l l l 1 1 l l l l l l l l l l...

Page 290: ...o LATITGDE sub i l l l l l l l l l l 515 0 I l l l l l l l 6 AZRPORT 1 RSVATION 6 15 5 ELEVATION TkN3 S CCt4PLR4SNT 20460 FEET 6 k O SPARS 11 20 0 0 625 FT I l l l l l l P ALT 7 l l l AIRPORT 1 USE LOGIC 1 VALID PAD ZERO PAD ZERO PAD ZERO PAD Zmo 7 15 AIRPORTVALIO 7 14 RESERVED 7 13 RESERVED 7 12 RESERVEO 7 11 RMERVEO 7 lo o SPARE I l a 15 o AIRPORT l RUNNAYCOURSE I l 9 AIRPORT l IDENT 9 15 8 CHAR...

Page 291: ... l l 27 AIRPORT 4 27 34 I l l l l l l l l l l l l f 1 l l l l l l l l 43 AIRPORT 6 43 50 I l l l l 1 51 AIRPORT 7 51 58 I l l l l l 59 AIRPORT48 59 66 l l l l l I 63 AIRPORT 9 67 74 l l 1 I l l 1 I l l 1 I I I 1 l l l l l l l l SPARE ltSP 75 76 l l l l l l l l l 1 1 SUMOF UOROS l l l l l l l l l l 1 mROR CNsm I l l l l l l l l l l 79 I l l l l l l l ...

Page 292: ...DUAL NAV PRIVATE PRIGIN DESTINATION ALTERNATEDESTINATION TOP OF CLINB 1 WAYPOINT 001311 DUALNAVPRIVATE O 4 UAYPOINTS 001 4tl DUAL NAV PRIVATE 5 9 WAYFOINTS 0015tl DUALNAVPRIVATE10 14 UAYPOINTS 00161J DUAL NAV PRIVATE 15 19 WAYPOINTS 001 7H DUALNAVPRIVATE 20 24 WAYPOINTS 0018H DUALNAVPRIVATE 25 29 WAYPOINTS 0019H DUALNAVPRIVATE 30 34 WAYPOINTS 00IAN DUALNAVPRIVATE 95 39 UAYPOINTS 00IBH DUAL NAVPRIV...

Page 293: ... X 16 17 18 19 23 24 PROCESSOR A SHARED 1 0 B CO PROCESSOR RAM PROCESSOR TRANSMITTER h TO BUS 1 TO BUS 2 SH2 t i SH2 s L 4 NZ 920 Navigation Computer Block Diaaram Figure 9 2 heet 1 22 14 00 26 27 32 33 43 44 45 46 50 51 19 28 31 22 23 57 58 AIRCRAFTBATTERY 28 V DC AIRCRAFTBAITERY RETURN H PRIMARY ASCB BUS L H SECONDARY ASCB BUS L H AFIS ACRS RX BUS L H MLWLS PRIMARY L H DME PRIMARY L H LTS NO 2 L...

Page 294: ...NO 1 LTS NO 1 NUMBER BITNO 2 LTS NO 2 NUMBER BIT NO 1 LTS NO 2 NUMBER BIT NO 2 LTS NO 3 NUMBER BIT NO 1 LTS NO 3 NUMBER BIT NO 2 SDI NO 3 CROSS FILL ENABLE VER B ASCB FUEL FLOW CONFIG IDO FUEL FLOW CONFIG ID1 FUEL FLOW CONFIG ID2 OPERATIONAL MODE IDO wow PERF COMP INSTALLEI LTS NO 1 CONFI LTS NO 1 CONFI LTS NO 1 CONFK LTS NO 2 CONFI LTS NO 2 CONFI LTS NO 2 CONFK N OUTPUT DISCRETES 105 I06 34 48 59...

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Page 296: ...MLF B 020 S3 ONM SLC J q 610 L 09 10Z 160 4920 DEST KSLC c1 El H B 348 4 ONM KSLC 0s t tZ J a 4560 LTN ARGIVr41 D II d f m fmmmi mairiim rm m RIGHT LINE SELECT KEYS FUNCTION KEYS MODE KEYS e R ss AD 11942 RI CD 81O Control Display Unit Figure 9 3 22 14 00 Page 198 128 Aug 15 91 Use or disclosure of information cm this page is subject to the restrictions on the title page of this document ...

Page 297: ...CRT Display A color CRT is used to display data on the CDU The displays consist of 9 lines each line containing 24 characters The first 1 ine is a title 1 ine and the ninth 1ine is the scratchpad The intermediate lines and scratchpad are available for data display and entry 2 Photosensors and Brightness Control CRT brightness control is provided in order to maintain readability under dim light as ...

Page 298: ...ining the Intercept waypoint on the active leg b Dead Reckoning DR Annunciator The DR annunciator is an alerting type amber that lights when the FMS is navigating via the DR mode which is defined to be the loss of radio updating and the loss of all position sensors The DR annunciator will light under the following conditions When the FMS has been operating in the DR mode for longer than 3 minutes ...

Page 299: ...age The annunciator turns off when the offset has been removed If there is an offset when the APRCH annunciator is lighted the offset will be removed and the annunciator turned off f Approach APRCH Annunciator The APRCH annunciator is an advisory type white that lights when in approach mode The NZ 920 Nav Computer output sensitivity of lateral deviation to the PFD will be ramped to a higher sensit...

Page 300: ...isplay are shown in the upper right hand corner of the display The format is AA BB AA signifies the number of the current page that is displayed BB signifies the total number of pages that are available for pilot viewing modification Page changes shall be done by selecting the PREV and NEXT keys When in the PLAN mode these keys will increment or decrement the map center waypoint b Clear CLR Key Th...

Page 301: ... the active flight plan with the DIRECT and INTERCEPT prompts 7 Alphanumeric Keys The control display unit provides a full alphanumeric keyboard to enable pilot inputs to the scratchpad of the CDU A key is provided for each letter of the alphabet as well as each number decimal minus sign and slash 8 Scratchpad The scratchpad is used for data entry messages and data transfer using the line select k...

Page 302: ...NNPOWER ANN INTENSITY CONTROL CHASSISGND rCPU A 16K PROG s MEM RAM I 1 I 1 MONITOR 4 HVPS G1 FOCUS VIDEO RAM A VIDEO CRT VIDEO AMPLIFIER CONTROLLER CONTROLLER HEATER VIDEO RAM B CRT SYNC 1 DEFLECTION AMPLIFIERS Y I I I I I Y i J H z c RS422 H a OUT c J1 bl I 1 KEYBOARD ANNUNCIATORS INPuT I BUFFER EE I E I I I B H I c LVPS q I s 1 F I L ANNUNCIATOR H POWER DIMCONTROL 7 CD 81O Control Display Unit B...

Page 303: ...INTENANCE Honeywell M thl This page intentionally left blank 22 14 00 Page 198 137 Aug 15 91 Useor disclosure Of reformation on this page IS subject to the restrictions on the title page of this document ...

Page 304: ... 5 75 in 146 05 mm Height 4 50 in 114 30 mm Weight maximum 5 6 lb 2 54 kg Power Requirements Primary 28Vdc 22Wmax Mating Connector J1 MS3126F16 26S Mounting Unit Dzus Fasteners DL 800 Data Loader Leading Particulars Table 9 5 22 14 00 Page 198 138 Apr 15 93 Use or disclosure of informationon this page is subject to the restrictions onthe title page of this document ...

Page 305: ...ght 2 24 in 56 9 Weight maximum s Olb l sG Power Requirements Primary zBVdct w mm mm mm kg max Mating Connector J1 MS3126F16 26S Mounting Unit Dzus Fasteners DL 900 Data Loader Leading Particulars Table 9 6 22 14 00 Page 198 139 Apr 15 93 Use or disclosure of informationon this page is subject to the restrictions onthe title page of this document ...

Page 306: ...oximately 8 minutes The LEFT RIGHT AUX switch on the front of the data loader is used to select which RS 422 port will be used to output data 2 Flight Plan Loading The DL 800 900 Data Loader also has the capability of interfacing with a ground based Lockheed JetPlan Computer or equivalent It is capable of transferring an optimized flight plan from the ground based computer to the navigation comput...

Page 307: ...I DATA BUS OUT c H T TO NAV COMPUTER CLK BUS IN J FROM NAV COMPUTER K H I CHASSIS GND b I P I B L 28 V DC POWER H c I R POWER SUPPLY CARD RIGHT D 5VDC LOADER 12VDC INSTALLED L DISCRETES FOR CPU DISCRETE FROM LE17 E NAV COMPUTER AUX F A El EQ AD l19694 2 DL 800 900 Data Loader Block Diagram Figure 9 7 22 14 00 Page 198 141 Aug 15 91 Use ordisclosure ofinformation on this pageissubjecf totherestrict...

Page 308: ... Computer See Figures 9 8 and 9 9 and Tables 9 7 and 9 8 AD 1 1 S41 PZ 800 Performance Computer Figure 9 8 22 14 00 Page 198 142 Aug 15 91 Use ordisclosure ofinformation On this pagek subject totherestrictions On thetine pageofthis document ...

Page 309: ...ot with real time information based on current aircraft and atmospheric conditions In case of changes to the flight plan the pilot can be updated immediately on the consequences of the changes This capability extends the pilots ability to conduct the flight safely and economically The performance system is enhanced by the autothrottle Aircraft parameters calculated by the performance functions can...

Page 310: ...CADER OATA O OTHERUISE PARE 6692 I lfi fi l 1 l l l 65A2 3 l I 65A4 3 15 TAKEOFFtin 3 14 1 NED TAKEOFF CAPTURE 1 CApTuR o 313 GOAROUND ANN 3 12 1 ARNED GOAROUNO CAPTURE 3 11 f RED FLCARM 3 10 39 38 34 33 32 3 FLC CAPTURE MACH ARM NACH CAPTURE CAS ARM CAS CAPTURE THROTTLENOLD THROTTLE OVERIIIOE AUTOTHROTTLE ENGAGED AUTOTHROTTLE LIMITING SEE NOTE i i CAPTURED 1 MEo 1 CAPTUREO 1 ARMEO 1 CAPTUREO 1 Ho...

Page 311: ...961 I W40 LII ITEO I vALID 65A6 MO LIMITED 1 vALIo 4 13 POHERLIMITEO 1 VALID 4 12 WEPLACARO LIMITEO 1 VALIO 4 11 9 4B LANDINGGEAR LIHITEO 1 vAL D 41 ENGAGEINHIBIT 1 INHIBIT i 6 o SPARE 61 I II I Ii i 1 1 1 CHECKSUM SUNOF UDRDS 65A8 J I i l Iac I l l l l l I 65AA I Ii I l l l l l I NOLC FLAG II 7E HEX 1 1 f 11 I Ill ...

Page 312: ...TAKEOFF GO AROUND 31 1 TAKEOFF O G A AUTOSELECT 30 TEu VALID II 11 I 111 00250 1 4 1S 5 EPRRATING MAXCON Tuo SCONPLEHENT ifi l fi l l 2 56EPR 0 000078125 44 2 SPARE 61C6 41 oSELECT 1 sELECTED 40 II 1 VAL1O l l l Iii l l 5 15 5 EPRRATIM CL1llB s i l i l l REDUCED THRUST TYPE 0 000078125 54 3 61C8 00 NONE 01 DECK 10 NOISE 11 SPARE 52 RATINO REDUCED THRUST 1 RATINo 0 REMCED TNRIJsT AUTO SELECT I sELE...

Page 313: ...ID 1 vALiD I 1 1 1 1 1 1 1 l i l l 11 15 0 II 6106 1 l l i iii 1 j i i i fil i 12 15 5 Vfe 124 3 SPARE 6106 122 1 FLAP CONFIG 00 O DEG 01 10 DEG 10 20 DEG 11 39 OEG 120 VALID 1 vALID I l lI 1 l l l 1 1 I 13 15 0 SPARE I l l lfi i l 6108 l l l l i l I 14 15 9 BANKANGLEBUFFETLIHIT 1 SPARE 61DA VALID 1 vAL o II l l l II I 15 15 0 SPARE 1 1 1 II l lfi fii l l I 61OC 16 16 4 CA CH TARGET I l i l l 16 5...

Page 314: ...SPARE II II d I 111132 10 FT lN I 6 15 5 VEN L SPEEO TUO S COllPLEtlENT 327066 FTo HIN UP 64 0 I l l lT o CMPLEMNT 1 l l i l 7 15 6 UINOSPEEO 511 KNOTS 7 5 o SPARE II 1 1 I I 10035 0 00549 i f 815 6 Ul OD RECTION THO S COMPLEMENT 180 OEGREES a 5 0 11 11 I I 106 0001953 l 9 15 8 OELTAISATEMPERATURE TWO S CO14PLEHENT 63 5DEGC 9 7 o SPARE II I lmo CWPLEHENT 1 116120 LBS 1015 0 FUEL REMAINING I 1 6553...

Page 315: ... 43 b4 1 1 2 E POWER SUPPLY 4 5 d ASCB CPU lB 1 JIA JIE 23 24 48 49 50 54 59 60 62 63 6s MONITORS 72 73 74 75 m 67 M 69 ao 91 92 xx Ell R N m I L J JJ PERFORMANCE CPU I I I AUTOTHROITLE CPU L Performance Computer Block Diagram Figure 9 9 22 14 00 17 18 I I I I I I I J SERVO CLUTCH ORIVE NO 1 SERVO CLUTCH ORIVE NO 2 CROSS SIOE NT ENGAGE AA ENGAGE MAINT TEST ENABLE GEAR DOWN LEFf RIGHT SELECT ASCS V...

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Page 317: ...ional output to automatically control the throttle setting A spline output on the clutch drives a cable drum The servo is connected to the throttle control rigging by the cable drum drive 12765 SM 81O Servo Autothrottle Figure 9 10 22 14 00 Page 198 152 Aug 15 91 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 318: ...lars Table 9 9 r P MOTOR INPUT POLAFilTY CAUSES Ccw SERVO OUTPUT ROTATION ND h 1 AS VIEWED FROM I OUTPUT END I I JI B BLK 2 L2 I R2 12 1 J ELK I II 50 R4 C3 SEL 1 I II II IN5614 TM B II c 4 1 I I Ss I wHT If 1 9 L3 6 10 RED II 1 SS2 II GRAY E iYEL S BLK 1 h I I i BRN f 13 A f WHT BLK TACH 14 ii Ir I D WHT RED II YSS5 VSS3 RY k RY SM 81O Servo Schematic Figure 9 11 AD 12766 22 14 00 Page 198 153 Au...

Page 319: ...R THAN 101 80 INHG Engine Pressure Ratio Transmitter Figure 10 1 Dimensions Height 2 35 in 59 7 MM Width 5 48 in 139 2 mm Length 7 82 in 198 6 mm Weight 3 1 lb 1 4 kg Power Requirements 115 V 400 Hz 7 watts Mating Connector MS27404T16B35S Mounting Hard Mount Engine Pressure Ratio Transmitter Leading Particulars Table 10 1 22 14 00 Page 198 154 Aug 15 91 Use or disclosure of information on this pag...

Page 320: ...of operation Initialization mode Normal operation mode c Memory access mode D The EPRT enters the initialization mode after power up or after a power transient of longer than 50 ms or after watchdog timer WDT time out The initialization mode lasts 750 ms maximum During the initialization mode the EPRT checks internal performance BITE reads the discrete input signals TRIMPLUG O through TRIt4PLUG 5 ...

Page 321: ...that the aircraft engines are tuned for the same thrust Transmits the calculated EPR on ARINC 429 bus to aircraft EPR indicator c Monitors internal EPRT performance with BITE Outputs BITE results maintenance data on ARINC 429 bus 10 F The memory access mode is used during testing and calibration only 22 14 00 Page 198 156 Aug 15 91 Use or disclosure of information on this page IS subject to the re...

Page 322: ...ation factor MF is determined by the following table parity odd Trimplug common Pin 33 1 0 0 1 1 0 0 1 1 0 1 0 0 1 0 1 1 0 1 0 0 1 1 0 0 1 0 1 1 0 32 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 NOTE 34 0 0 0 0 0 0 0 0 1 1 1 1 1 1 1 1 0 0 0 0 0 0 0 0 1 1 1 1 1 1 1 1 o Engine Pressure Ratio Transmitter Input Output Information Table 10 2 25 0 0 0 0 1 1 1 1 0 0 0 0 1 1 1 1 0 0 0 0...

Page 323: ...ded Ground clears all fault data recorded in memory Both identical outputs transmit the following data Label 340 engine pressure ratio Label 350 flight line fault code Label 352 fan duct pressure Label 353 shop fault code Engine Pressure Ratio Transmitter Input Output information Table 10 2 cent 22 14 00 Page 198 158 Aug 15 91 Use or disclosure of information on this page is subject to the restric...

Page 324: ...El 3G H L 3 c 1 FAN DUCT PRESSURE J I I 1 J1 31 39 WI 37 52 45 7 1 3 12 2 EPR OUTPUT ARINC 42S 12 8 KHZ MONITOR INPUT RS 232 1 TEST ONLY NON VOLATILE MEMORY RESET BITE FAULT AD 213E6 Engine Pressure Ratio Transmitter Block Diagram Figure 10 2 22 14 00 Page 198 159 Aug 15 91 Use or disclosure of Information on this page is subject to the restrictions on the title page of this document ...

Page 325: ...ocessor Unit RPU Table 11 1 See Figures 11 1 and AD 15616 11 2 and OZ 800 Receiver Figure Processor Unit 11 1 22 14 00 Page 198 160 Apr 15 93 Use or disclosure of informationon this page is subject to the restrictions onthe title page of this document ...

Page 326: ...on and velocity information to the FMS navigation computer The RPU receives initialization data from the FMS The RPU receives the amplified antenna signals and converts them into position information The RPU also supplies the antenna with 12 volts dc power The RPU receives the following signals over an ARINC 429 low speed bus Label Parameter Name 210 True Airspeed TAS 314 Heading 041 042 Initializ...

Page 327: ...tus Lane Ambiguity Resolution 15 14 0 0 no LAR in progress o 1 LAR in progress 1 0 insufficient signals for LAR 1 1 unsuitable geometry for LAR System is in dead reckoning DR mode Position uncertainty estimate exceeds 4 0 NM System in nonsynchronized System navigating in relative mode Minor RPU failure Major RPU failure Position uncertainty estimate in binary format with Bit 22 corresponding to 0 ...

Page 328: ...at Britain used Station NAA Maine used Station NPM Hawaii used Station NSS Maryland used Station NLK Washington used VLF i A 1 i OMEGA 1 1 1 v 1 A 1 1 1 1 vLF 1 1 1 v 1 Discrete label 272 is the same format as label 271 with the exception that the setting of a bit means the station has been either deselected by the pilot or cutoff by the RPU Label 271 Discrete Word 2 or Label 272 Discrete Word 3 F...

Page 329: ... INPUTS INTERFACE HDGITAS SYNCHRO INPUTS INTERFACE TO FMS r DIGITAL lNPUT OUTPUT 4 RPU DC 28 VDC POWER VOLTAGES REQUIRED SUPPLY 212VDC TOACU AD 1 5927 02 800 Receiver Processor Unit Block Diaqram Figure 1 2 22 14 00 Page 198 164 Apr 15 93 Useor disclosure of information on this page issubject totherestfictions onthetitle page of this document ...

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Page 331: ...plification stages These two stages amplify the received signals sufficiently to allow the signals to be cable transmittedto the OZ 800 RPU without significant signal to noise degradation A BITE capability whereby test signals are introduced directly into the ferrite rods allows monitoring of ACU sense elements and preamplifier stages Electromagnetic interference EMI protection for the ACU is prov...

Page 332: ... 0 91 kg 0 18 W max Mating Connector Tracer Part No 24952 0002 Mounting Hard mount using four 10 32 nonmagnetic hex head screws AT 800 Antenna Coupler Unit Leading Particulars Table 11 4 22 14 00 Page 198 167 Apr 15 93 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 333: ... RPU The AT 801 ACU is electrically equivalent to the AT 800 ACU described in paragraph 6 The AT BO1 ACU is used on aircraft which require internal mounting within tail cones and fin caps AT 801 Antenna Coupler Unit Figure 11 4 22 14 00 Page 198 168 Apr 15 93 Llse or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 334: ...ents lz V dc 0 18 W max Mating Connector Tracer Part No 24952 0002 Mounting Hard mount using six 10 32 nonmagnetic hex head screws AT 801 Antenna Coupler Unit Leading Particulars Table 11 5 22 14 00 Page 198 169 Apr 15 93 Useor disclosure of information on this page issubject totherestrictions on the title page of this document ...

Page 335: ...llow the signals to be cable transmitted to the OZ 800 RPU without significant signal to noise degradation The AT 803 ACU is used when a suitable location for the AT 800 or AT 801 H Field ACU cannot be located by an aircraft skin map because of excessive RFI aircraft noise AD 15619 AT 803 Antenna Coupler Unit Figure 11 5 22 14 00 Page 198 170 Apr 15 93 Use or disclosure of informationon this page ...

Page 336: ...ents t12 V dc 0 18 W max Mating Connector Tracer Part No 24627 0307 Mounting Hard mount using four 10 32 nonmagnetic hex head screws AT 803 Antenna Coupler Unit Leading Particulars Table 11 6 22 14 00 Page 198 171 Apr 15 93 Useor disclosure of information onthispage issubject totherestrictions on the title page of this document ...

Page 337: ...sor Processor See Figures 12 1 and 12 2 and Table 12 1 O O booo O OO OO AD 1 5286 LP 850 Lightning Sensor Processor Figure 12 1 22 14 00 Page 198 172 Apr 15 93 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 338: ...ty data for up to 50 cells The 429 data contains all data available for a 360 degree area with a radius of 125 NM around the aircraft and it is the task of the display device to determine which cells fall within its display area Mode selection is provided by the LU 860 Lightning Sensor Controller When the antenna assembly is mounted on the aircraft four manual adjustments may be required The adjus...

Page 339: ...NG FLAG VALID I 1 OUTPUTS INPUTI OUTPUT PROCESSOR DATA OUT 1 DATA OUT 2 ARINC 429 OUTPUTS DATA OUT 3 jl jpD r DATA OUT 4 J 1 AD 18249 R1 LP 850 Lightning Sensor Processor Block Diagram Figure 1 2 22 14 00 Page 198 174 Apr 15 93 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

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Page 341: ...Width 5 750 in 146 05 mm Height 1 125 in 28 58 mm Weight 0 61 lb 0 28 kg Lightning Power 5 V ac dc 3 5 VA maximum Mating Connector JTO6RE1O 35S SR Mounting Unit Dzus Fasteners LU 860 Lightning Sensor Controller Leading Particulars Table 12 2 22 14 00 Page 198 176 Apr 15 93 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 342: ...is inhibited but the processor is accumulating data LX System is fully operational All accumulated lightning data is displayed CLR TEST Accumulated data is cleared from memory After 3 seconds the test mode is initiated LU 860 Switch Functions Table 12 3 22 14 00 Page 198 177 Apr 15 93 Use or disclosureof information on thispage issubject to the restrictions on the title page of thisdocument ...

Page 343: ...13 5v LIGUTING LIGHTING 29V LIGUIING SW COMMON OFF sTaY cl n TEST ao12738 1 L LU 860 Lightning Sensor Controller Schematic Figure 12 4 22 14 00 Page 198 178 Apr 15 93 Use or disclosure of informationon this page is subject to the restrictions onthe title page ofthis document ...

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Page 345: ... 1 25 in 31 75 mm Weight 2 5 lb 1 13 kg Power 12 V dc from Lp 850 Mating Connector KJ6F12A35 SN Mounting Hard Mount Using Three No 10 Screws With Maximum Washer Diameter of 0 455 in AT 850 Antenna Leading Particulars Table 12 4 22 14 00 Page 198 180 Apr 15 93 Useor disclosure of information onthispage issubject totherestrictions on the title page of this document ...

Page 346: ...sensitive to vertical E fields 12 V dc power for the preamplifiers is provided to the antenna from the processor The antenna also contains a test winding During test mode this winding is driven with a simulated lightning signal and couples with the E and H elements of the antenna Thus the test mode is able to provide an evaluation of the performance of the antenna its preamplifiers and cabling to ...

Page 347: ... 45 mm n 152 40 mm in 42 42 mm 5 lb 1 13 kg dc from LP 850 Mating Connector KJ6F12A35 SN Mounting Hard Mount Using Four No 8 Screws With Maximum Washer Diameter of 0 350 in AT 855 Antenna Leading Particulars Table 12 5 22 14 00 Page 198 182 Apr 15 93 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 348: ...e most sensitive to vertical E fields flz V dc power for the preamplifiers is provided to the antenna from the processor The antenna also contains a test winding During test mode this winding is driven with a simulated lightning signal and couples with the E and H elements of the antenna Thus the test mode is able to provide an evaluation of the performance of the antenna its preamplifiers and cab...

Page 349: ......

Page 350: ...ollision avoidance algorithms to decide whether an intruder aircraft should be considered a threat and then to determine the appropriate vertical response to avoid a midair collision or near midair incident In addition output data is provided to drive displays and the aircraft audio system to inform the flight crew as to what action to take or avoid An interface is provided with an on board Mode S...

Page 351: ...Characters EOT RTS ETX Equipment ID 013 015 016 130 131 132 203 270 271 274 350 356 356 356 357 377 2 3 Hz 2 3 Hz 2 3 I Iz 2 Hz 2 3 Iiz 2 3 Hz 2 3 Hz NOTE Labels 130 131 and 132 are repeated for each successive intruder for display RT 91O TCAS Computer ARINC 429 Output Data Table 13 2 22 14 00 Page 198 186 Apr 15 93 Use or disclosure of information on this page is subject to the restrictions on th...

Page 352: ...z 270 2 3 Hz 271 2 3 Hz 271 2 3 Hz 273 274 2 3 HZ 275 276 277 350 RT 91O TCAS Computer to Mode S Transponder Data Table 13 3 The Mode S Transponder transmits ARINC 429 high speed output data to the TCAS tion Computer as listed in the following tabl This data is for coordina with other TCAS 11 equipped aircraft Parameter Signal Name Label Rate 274 Select TCAS Sensitivity 274 2 3 HZ 275 Mode S Trans...

Page 353: ... I 2 I AURAL OUTPUTS 4 SITE 1 2 ANALOG INPUTS A2 INDICATORS DIGITAL VIDEO CAS CPU INTERFACE SYNCI IRO RADIO _ ALTIT OE z AIRCRAFT 1 1 0 I aECORDEE INTERFACE OISCR INPUTS 14 I I pROCESSOR I 4 ARINC 429 0LJT L17s ARINC 429 5 1 INPUTS I I I I ARINC 615 LOAOEF INTERFACE I I I I c86 1632 RT 91O TCAS Computer Block Diagram Figure 13 2 22 14 00 Page 198 188 pr 15 93 Use or disclosure of information on th...

Page 354: ...ability to determine the bearing of the intruder Since TCAS II is a vertical only system intruder bearing is not used in the computation of the escape or limit maneuver Intruder bearing is used only to enable the flight crew to more easily locate the intruder visually The Honeywell TCAS II will also accommodate a bottom mounted directional antenna if so desired by the user refer to paragraph 13 C ...

Page 355: ...ces the forward looking lobe In addition the antenna ports are both color coded and electrically coded with a resistance to ground that is checked by the TCAS computer and can be checked by the technician J1 J2 J3 J4 O degree port Color coded yellow Located on the rear of the antenna and installed to the rear of the aircraft Resistance to ground is 1000 ohms 270 degree port Color black Installs to...

Page 356: ... replies from aircraft located beneath own aircraft Since TCAS 11 is a system intruder bearing is not used in the computation of limit maneuver The omnidirectional antenna must exhibit 50 ohms fixed resistance test Identical omnidirectional bottom antennas connected to the rcraft does enable ntruder vertical only the escape or exhibit 50 ohm imDedance and must also to ground This is necessary for ...

Page 357: ...er Requirements 18t032Vdc 15 5 VA nominal Mounting Kit Part No 7510664 901 NOTE The mounting kit contains the following components that can be ordered separately Mount Frame Tray Part No 7510654 901 Spring Finger Part No 7510835 Connector 67 Pin Part No 7500297 67 Screw CSKH CRES 4 40 x 3 8 Part No 0920 15 ML 850 MLS Receiver Leading Particulars Table 14 1 22 14 00 Page 198 192 Apr 15 93 Use or di...

Page 358: ...LS ground station and provides an accurate indication in both azimuth equivalent to localizer and elevation equivalent to glide slope of the deviation from the desired flight path The deviation data is displayed on the PFD and is output to the FZ 820 Flight Guidance Computer for use in the approach mode of operation The ML 850 operates in the frequency range of 5031 0 to 5090 7 MHz on 200 channels...

Page 359: ...rd 2A Word 3A Word 4A Word lB Word 2B Word 3B Word 4B Word lC Word 2C Word 3C Word 4C Azimuth Deviation Glidepath Deviation Selected Azimuth Angle Max Selectable Glidepath Angle Selected Glidepath Angle Basic Data Word 1 Basic Data Word 2 Basic Data Word 3 Basic Data Word 4 Basic Data Word 5 Basic Data Word 6 Absolute Glidepath Angle Absolute Azimuth Angle Localizer Deviation Glide Slope Deviation...

Page 360: ...O I I I I I RC6 TO II BITE CONTROL UNIT L 5 28 15 15 y r I I POWER SUPPLY I L d 28 VDC INPuT POWER AO 19591 ML 850 MLS Receiver Block Diagram Figure 14 2 22 14 00 Page 198 195 Apr 15 93 Useor disclosure of information onthispage issubject totherestrictions onthetitle page of this document ...

Page 361: ...ON _ MODE SELECTSWITCH ON OFFSWITCH VOLUMECONTROL KNOB OPTIONAL BfiCK AZIMUTH f jBunoN SELECTPUSHBUTTON CM 850 MLS Control Dis laY Unit PUSHBUTTON Y TUNING KNOBS AD 20722 Figure 14 3 22 14 00 Page 198 196 Apr 15 93 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 362: ... separate functions channel number ident CH glidepath GP azimuth AZ and black azimuth BK Each function has an annunciator an arrow cursor and a pushbutton associated with it Depressing any one of the pushbuttons selects that function for programming and turns on the associated arrow cursor The pushbuttons are all labeled as to their function The following paragraphs describe the operation of each ...

Page 363: ...on will allow the azimuth angle to be changed via the rotary tuning knobs If BACK is being displayed and the AZ pushbutton is pressed then the BACK annunciator will be turned off and the AZ display will then be displaying the forward azimuth Also the glidepath digits will be unblanked and will display the glidepath angle 4 GP Pushbutton Pressing the GP pushbutton will allow the glidepath angle to ...

Page 364: ... When the number reaches 69 the next rotation will cause the number to change to 50 Turning the knob counterclockwise will cause the number to decrease in the range from 69 to 50 by 1 unit When the number reaches 50 the next rotation will cause the number to change to 69 b Azimuth Selector The rotary tuning knobs can change the azimuth angle whenever the azimuth selector is on If the mode is AUTO ...

Page 365: ... 1 degree steps for each rotation of the switch No rollover of the glidepath takes place for an increment above the maximum glidepath or a decrement below 2 0 degrees A 9 to O or O to 9 transition of the LSD does carry over into the MSD S Values are incremented with clockwise rotation and decremented with counterclockwise rotation Outer Knob The outer knob is required to increment or decrement the...

Page 366: ... will cause the number to decrease in the range from 35 to 00 by 1 unit When the number reaches 00 the next rotation will cause the number to change to 35 TEST Pushbutton Pressing and holding the TEST pushbutton for 2 seconds will cause the MLS radio to be tested Pressing this pushbutton for less than 2 seconds is the same as not pressing it at all The CDU will display TST in the channel display d...

Page 367: ...EGISTERS 2x50ME I 2x5 TUNING LATCH d DRIVERS 1 m L 4 I I TEST INHIBIT DISCRETE 1 0 4 lLU 4T LU f T 28 VDC ON OFF INPUT POWER _ 30 VDC POWER OUTPUT SUPPLY 15 Voc 5 VDC DIMMING 5vAC DC INPUTS 28 VDC AO 17049 R2 CM 850 MLS Control Display Unit Block Diagram Figure 14 4 22 14 00 Page 198 202 Apr 15 93 Use or disclosure of information on this page is subject to the restrictions on the title page of thi...

Page 368: ...This page is intentionally left blank 22 14 00 Page 198 203 Apr 15 93 Use or disclosure of informationon this page is subject to the restrictions onthe title page of this document ...

Page 369: ... 215 9mm Width 8 50 in 215 9 mm Height 2 20 in 55 8 mm Weight 5 01b 2 27 kg Power Requirements 28 V dc 36 Watts maximum Mating Connector J1 M83723 77R2041N J2 TNC Female Mounting Hard Mount Using Four 10 32 Cap Screws Global Positioning System Sensor Unit Leading Particulars Table 15 1 22 14 00 Page 198 204 Apr 15 93 Use or disclosure of information on this page is subject to the restrictions on t...

Page 370: ...atellite data which includes ephemeris and almanac data When the GPSSU has acquired enough satellite data to compute position it enters the NAV mode The GPSSU reverts to the acquisition mode from the altitude aiding clock coastingsubmode when it is unable to track any satellites for 30 seconds Navigation NAV Mode In the NAV mode the GPSSU updates and transmits data on the ARINC 429 data bus to its...

Page 371: ...ime SELECTIVE AVAILABILITY OFF ON OFF ON OFF ON OFF ON OFF ON OFF ON OFF ON OFF ON LIMITATION HDOP 1 72 HDOP 1 72 HDOP 1 72 HDOP 1 72 VDOP 2 2 HDOP 1 72 VDOP 2 2 HDOP 1 72 HDOP 1 72 HDOP 1 72 AUTONOMOUS 25 meter 100 meter 1 8 Knots 1 8 Knots 0 30 0 30 100 ft min 100 ft min 138 ft 551 ft 1 8 Knots 1 8 Knots 1 8 Knots 1 8 Knots 350 ns 450 ns HYBRID 25 meter 100 meter 0 3 Knots 0 7 Knots 0 07 0 18 20...

Page 372: ...DOP VDOP Track Angle True GPS Latitude GPS Longitude GPS Ground Speed Latitude Fractions Longitude Fractions Vertical Figure of Merit UTC Fine UTC Fine Fractions UTC Vertical Velocity N S Velocity E W Velocity Horizontal Figure of Merit 061 062 063 064 065 066 070 071 072 073 074 076 101 102 103 110 111 112 120 121 136 140 141 150 165 166 174 247 Meters Meters Meters Second Meters Meters Meters Me...

Page 373: ... Table 15 4 Discrete 01S Data Format Label Units Digital Parameter Signal Name Range Resolution GPSSU Status 273 Maintenance Discrete No 2 352 System Time Counter 354 Seconds 262144 1 Maintenance Discrete No 1 355 GPSSUARINC 429 Output Data DIS Format Table 15 5 22 14 00 Page 198 208 Apr 15 93 Useor disclosure of information onthispage issubject totheresttictions on the title page of this document...

Page 374: ...9 12 5 KHz OR 1 100KHz OPEN GROUND DISCRETE J INPUTS OPEN GROUND DISCRETE OUTPUT POWER b 2 TIMEMARK 1 b 2 TIME MARK 2 P 2 TIME MARK 3 B 2 429OUT 1 2 429 OUT 2 P 2 429 OUT 3 l GPSSU FAULT 8698 301 OS 60092 01 PT1 Global Positioning System Sensor Unit Block Diagram Figure 15 2 22 14 00 Page 198 209 198 210 Apr 15 93 Use or disclosure of information on this page is subject to the restrictions on the ...

Page 375: ...ubsystems that are contained in the following paragraphs EDZ 884 DFZ 820 FMZ 800 Subsvstem paraclraDh Electronic Display System 2 Dual Flight Guidance Control System 3 Flight Management System 4 22 14 00 Page 201 Aug 15 91 Use or disclosure of information on this page is subject to the restrictions on the title page of thm document ...

Page 376: ...y Controllers DC The GIV display system contains two display controllers The DCS are used to control the various display unit formats Basically each pilot can control the formats for the on side PFD and ND displays in addition to the ENGINE and CAS displays Symbol Generators SG The GIV display system has three symbol generators each one containing the four formats described in paragraph 2 A The pu...

Page 377: ...1 PILOT ND ENGINE CAS SYSTEM Elm 1 Cockpit Layout of the EFIS EICAS Display System Figure 201 22 14 00 Page 203 Aug 15 91 Use or disclosure of information on this page is subpf to the restrictions on the title page of this document ...

Page 378: ... subsystem parameters to the SG for display on the ENGINE display DAU 1 provides left engine data and DAU 2 provides right engine data 6 Display Dimming Panel One display dimming panel has been incorporated into the GIV system for the purpose of adjusting the brightness of the six display units 7 Display Power Panel In addition to the circuit breaker panel power may be removed from the display sys...

Page 379: ...ILOT L DI SPLAYS EICAS OFF COPILOT OFF I I I I I I I I I I I I I I I 1 ____ j Display Power Panel Figure 202 22 14 00 Page 205 Aug 15 91 Usa or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 380: ...peed Target Bug with Digital Readout Fixed Airspeed Current Value Pointer with Rolling Digits V O Thermometer on Airspeed Tape Digital Mach Readout Amber VSPD Annunciation Mach Display Presentation Moving Analog Mach Tape Mach Target Bug with Digital Readout Fixed Mach Current Value Pointer with Rolling Digits M O Thermometer on Mach Tape Digital Airspeed Readout Moving Analog Altitude Tape with T...

Page 381: ...er Vertical Speed Current Value Digital Readout within Pointer Current Value Range t9900 Vertical Speed Target Bug Fixed Normalized AOA Scale with Moving Pointer AOA Current Value Digital Readout within Pointer AOA Target Bug Abnormal AOA Range Indication Comparison Monitor Annunciators Attitude Heading Air Data ILS MLS Data EICAS Wraparound Fault Warning Computer Category II ILS Mode Annunciation...

Page 382: ... reference mark is highlighted and shows up as a brighter shade of white d Aircraft Symbol The stationary yellow aircraft symbol is used to develop the relationship between aircraft pitch and roll attitudes and the movable sphere Additionally the symbol is used to align to the flight director command cue in order to satisfy the commands of the selected flight director mode e Attitude Source Annunc...

Page 383: ...nunciated in white and located in the left half of the appropriate region Captured modes are annunciated in green and located in the right half of the appropriate region As the modes transition from armed to captured a green box is drawn around the capture mode for 5 seconds Table 201 lists all the annunciated lateral and vertical FD modes as well as autothrottle modes Autopilot AP Autothrottle AT...

Page 384: ... TREND VECTOR Vs kR f000 ml RAD SOtiR E Primary Flight Display Format SENSOR Figure 203 22 14 00 Page 210 Apr 15 93 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 385: ... 4 00 t 1 AOA 20 HDG SCALE 0 m OADFf 000 0 VOR2 Primary Flight Display Format DISP Figure 204 ALTITUDE B METR1 C ALTITUDE _VEFF AL BEAR ING POINTERS 22 14 00 Page 211 Aug 15 91 Use or disclosure of information on this page is subpcf to the restrictions on the title page of this document ...

Page 386: ...eed IAS Speed Mach Hold Mode VHO Limited MHO Limited Power Limited Flap Limited Gear Limited Mode Annunciation HDG FMS VOR LOC BC AZ Mode Annunciation ALT Vs ASEL IAS MACH GA VASEL VALT VIAS VMACH VPATH VNAV GP Mode Annunciation TO x GA x FLCH IAS MACH x HOLD VMO MMO POWER FLAPS GEAR Qy x x x x x x x x x x x x x x x x x x x x x x x x x x x Flight Director AutothrottleMode Annunciations Table 201 2...

Page 387: ...e is not annunciated if it is the normal on side source for that indicator As other sources are selected a white side designator 1 or 2 is added to the RA legend When the pilot s and copilot s source are the same it is annunciated on both displays in amber Source selection for radio altitude is accomplished through the display controller as shown in Figure 203 Radio Altitude Reference Set Display ...

Page 388: ...E RISING RUNWAY AOA TARGET Jet l I 2 7 RS 1 0 000 8 0 59 1 4 2 HDG 000 Q f l 11 k 75 Primary Flight Display Format FLT REF Figure 205 BELOW 1 E go R RASTER BELOW RA E LT RADIO ALTITUDE 22 14 00 Page 214 Aug 15 91 Useor disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 389: ...0 10 w TO I CRS 000 HDG 000 Primary Flight Display Format AUTO VSPD CONFIG Mismatch Figure 206 22 14 00 Page 215 Aug 15 91 Use or disclosure of reformation on this page is subject 10 the restrictions on the title page of this document ...

Page 390: ...ation is located to the left of the attitude sphere as in a conventional T arrangement The CAS scale is presented for altitude less than 25 000 feet Figure 204 The display can be selected to a Mach scale above 25 000 feet Figure 203 via the display controller or through the flight guidance system Each display is configured to be a moving tape with fixed current value pointer The tape markings curr...

Page 391: ...scribed above the pilot has the ability to set Vspeed bugs corresponding to reference speeds for various phases of flight This data is available from the FMS PZ 800 Performance Computer automatically or is manually set through the display controller as shown in Figure 205 The Vspeeds travel along the airspeed tape in the same area as the speed target bug previously described The Vspeed bugs are di...

Page 392: ...e Mach scale endpoint extending out to MO Figure 203 When the value in the pointer exceeds VH O the digital Mach data in the current value pointer 1s urned red Mach Target Digital Readout The speed target digital data is displayed in green at the top of the Mach scale The speed target data is set by the pilot using the flight guidance controller or it is available automatically with the FMS Mach T...

Page 393: ...itude predictor term with a length equivalent to 6 seconds Altitude Select ALT SEL Digital Readout ALT SEL digital data is displayed in green at the top of the altitude scale The ALTSEL target data is set by the pilot using the flight guidance controller Altitude Select Bug The green triangular ALT SEL bug travels along the inboard side of the altitude scale The bug position on the scale correspon...

Page 394: ...tude exceeds 1000 feet the bug and readout return to their normal cyan color i Barometric Altimeter Setting The magenta baro set digital readout is located directly below the altitude tape Each pilot can set the barometric reference for the on side DADC through the baro set knob located on the display controller The pilot has the ability to select the altimeter setting for display in either inHg I...

Page 395: ...agenta heading bug is positioned around the rotating heading dial by the heading select knob located on the flight guidance controller A digital heading select readout of bug position is provided and located at the lower left hand side of the compass This data is labeled with a white HDG The digital readout is displayed in magenta corresponding to the heading bug color The center of the heading se...

Page 396: ...urces and NM Figure 203 for FMS The digital display color is consistent with the course select pointer i e green for SRNS and cyan for FMS DME hold is indicated by displaying an amber H adjacent to the distance readout Figure 207 h NAV Source Annunciations Annunciation of the navigation source is displayed in the upper right hand corner of the i compass arc the ability given insta Figure 207 the p...

Page 397: ...ay controller HSI displays function as previously described exce tthat the fliqht quidance computer cannot be coupled to this data 5 Vertical Speed Display VS a VS Analog Scale The VS tape is a fixed moving current value pointer The white display appear at O t500 t1000 t2000 minute FPM The scale labels O 1 2 white scale with scale markings on the and t3000 feet per and 3 appear at the O t1000 jZOO...

Page 398: ...b cE Fi M SELECTEI HEADING Primary Flight Display Format NAV Figure 207 22 14 00 Page 224 Aug 15 91 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 399: ... 23 4 NM 2 8 t 6 Q e 0 1 A 4 liDG o 0 t II 50 20 0 OADF1 s 325 VOR2 VNAV Primary Flight Display Format VNAV Figure 208 22 14 00 Page 225 Apr 15 93 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 400: ...gh the use of the displa controller Figure 205 7 Comparison Monitor Annunciation Selected pilot and copilot input data is compared by the symbol generator If the difference between the data exceeds predetermined levels the out of tolerance symbol is displayed These annunciations are displayed in amber and are located to the left adjacent to the attitude sphere A list of the compared signals and di...

Page 401: ... for 5 seconds and then remains displayed steady Changes back to CAT2 are handled the same way in the event that the enabling condition is restored The CAT2 annunciation is presented only if the displays are configured as above If these conditions are not met when APRmode is selected no CAT1 2 mode annunciations are displayed b Excessive Deviation Monitor When the CAT2 mode annunciation is active ...

Page 402: ...D annunciation is displayed in the left most lateral modes FGC mode annunciation box Additionally the flight director mode annunciations and cue are removed Figure 210 d Autothrottle Failure In the event of failure in the selected autothrottle an amber AT annunciation is displayed in the center autothrottle mode annunciation box Figure 210 e Radio Altitude Failure In the event of a failure of the ...

Page 403: ... I 0 0 al 0 x HDG m 3 K 2 1 0 1 2 3 PFD Failure Indications IRS DADC Figure 209 22 14 00 Page 229 Aug 15 91 Use or disclosure Of information on this page is subject to the restrictions on the title page of this document ...

Page 404: ... 1 v 20 20 lo 10 to 10 1 200 55f 1 PFD Failure Indications Mist Figure 210 22 14 00 Page 230 Apr 15 93 Use or disclosure of information on thispage is subject to the restrictions on the title page of thisdocument ...

Page 405: ...elect signals will cause the display to be replaced by amber dashes with the course pointer removed from the display This indication will also be given in the event of an invalid heading display or FMS source Figure 209 j Distance Display Failures Failure of either the DME or FMS distance signals is indicated by replacing the digital distance value with amber dashes Figure 211 k Course Deviation F...

Page 406: ... DTRK 1 I O RA FMS 1 r3 F 2 1 1 2 3 IRS Test Mode Indications Figure 211 22 14 00 Page 232 Apr 15 93 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 407: ...te Data for SAT and TAS comes from the selected DADC source and GSPD comes from the selected ND FMS source b Weather Radar WX Mode Annunciations Weather radar mode annunciations appear in the MAP COMP and PLAN modes The data is positionally stable in all three ND modes This data is displayed in the extreme lower left corner of the ND Available modes for the P 800 Weather Radar Svstem are as follow...

Page 408: ...y Mode RT Warmup Mode Stabilization Off Indication Variable Gain Mode Amber ND is not in PLAN mode to display Test Weather or Ground Map Display Weather radar tilt information is on the bottom line of the WX mode The information is displayed in half decwee increments for values between tlOO and one d gree increments for values greater than tlOO The P 870 autotilt mode is indicated by an A followin...

Page 409: ...l cue to aircraft position relative to actual heading and selected heading Actual Track Vector Actual track from the IRS is displayed from the nose of the aircraft symbol to the map lubber line as a magenta dashed line The selected IRS source provides this data Figure 212 Heading Display The displayed compass rose consists of an expanded 120 degree arc that is divided into 5 degree increments and ...

Page 410: ...15 1 Wx VAR GCR o ADF 1 OR2 r SAT 56 TAS 234 GSPD 345 FMS ALERT MESSAGES BEAR ING POINTERS HALF RANGE LABEL DATA BEARING SOURCES Map Mode Format Figure 212 22 14 00 Page 236 Aug 15 91 Use or disclosure of information on this page is subjecl to the restrictions on the title page of this document ...

Page 411: ... the current aircraft heading NAV Source Annunciations Annunciation of which FMS is driving the displayed flight plan data is located in the upper right hand corner of the ND The pilot s source is FMS1 when his active navigation source is any SRN or FMS1 When FMS2 is selected as the active NAV source the map source also becomes FMS2 The copilot s map source is FMS2 when his active navigation sourc...

Page 412: ...whenever at least one weather radar side independent controller has been turned on With both WX controllers ON STBY TEST WX or GMAP modes selected each pilot has independent control over alternate sweeps of the radar yielding independent weather display capability relative to range tilt and WX mode With one WX controller ON and the other in the OFF position the active controller selects weather ra...

Page 413: ...SAT VAR SAV12 FL41O S6 GCR TAS 234 GSPD 34s NAVAID J A D AIRPORT H ID AIRPORT JEJ EJ IICXJL Map Mode With Vertical Profile Figure 213 22 14 00 Page 239 Apr 15 93 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 414: ... c ID NAVAID VERT PROF SET Bfi E ID AIRPT WIND Y o Mif E BOX FMS 1 UX DISPLAY BOUNDARY HALF RANGE LABEL DATA Map Mode With Weather Radar Display Figure 213 1 22 14 00 Page 240 Aug 15 91 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 415: ...t Annunciations Track changes both lateral and vertical are given at the upper right hand side of the MAP arc Figure 212 The annunciations are displayed in white and labeled as follows VERTALRT Vertical Track Change TRK CHG Lateral Track Change These annunciations appear flashing for 5 seconds upon activation and remain steady for the duration of the mode When coming out of the alert mode the annu...

Page 416: ...entified follows FL300 FL300 FL300 FL300 The waypoint identifier is further by type of Tv e of Constraint At or Below At or Above At Predicted normally displayed constraint as in white to maintain consistency with the lateral flight plan The TO waypoint is the exception in that it will be displayed in magenta for consistency with lateral map and CDU The waypoint altitude is displayed in cyan and i...

Page 417: ...ced by amber dashes Additionally a red HDG FAIL label is displayed below the lubber line as shown in Figure 215 IRS test mode is shown with the label HDG TEST in the same location as the fail annunciation discussed above Figure 216 b Headinu Select Failure Failure of the heading select signals will c use the display to be replaced by amber dashes with the heading bug removed from the display This ...

Page 418: ... 50 50 1 0 ADF1 O VOR2 SAT TAS GSPD Map Caution Warning Displays Figure 215 22 14 00 Page 244 Aug 15 91 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 419: ...AM IV Ft4S 1 as 345 v NAV 1 23 4DrI L T s 3 VAU 4 o 0 IRS Test Mode Display Figure 216 22 14 00 Page 245 Apr 15 93 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 420: ...valid and less than 60 knots and the WOW switch is active Selecting the EFIS self test shows the invalid flags for the following MAP display parameters IRS DADC VERT TRK TRK CHG Annunciations 4 Compass COMP Mode The COMP mode is comprised of the following functions Figure 217 360 Degree Compass Rose Digital Heading Readout Magnetic True Annunciation Heading Bug with Digital Readout Wind Display in...

Page 421: ...ss lubber line Figure 217 c Heading MAG TRU Annunciations TheMAG TRU annunciation operation and location is identical to the MAP mode paragraph 2 D 2 d as previously discussed d Heading Bug with Readout The heading bug operation and identification is as previously discussed in the MAP mode paragraph 2 D 2 e e Wind Display The wind format is displayed in white in either an X Y Figure 217 or vector ...

Page 422: ... DME HOLD COURSE DEVIATION INDICATOR VERTICAL NAV SOURCE VERTICAL NAV SCALE BEAR ING SOURCES Compass Mode Display Format COMP Figure 217 22 14 00 Page 248 Aug 15 91 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 423: ... bar to center The SYNC mode is only operational when the displayed navigation source is VOR 9 h Distance Display The distance display indicates the nautical miles to the selected DME station or FMS waypoint The distance display is located to the upper right of the compass arc The data is labeled DME Figure 217 for SRN sources and NM Figure 218 for FMS The digital display color is consistent with ...

Page 424: ... 217 Vertical Navigational Scale The vertical navigation scale appears to the right of the compass rose Figure 217 The pointer source is selected through the display controller The vertical navigation source displayed is associated with the active lateral navigation source selected for display i e glideslope with ILS VNAV with FMS etc The display format and operation is identical to the descriptio...

Page 425: ...CRS NAV2 330 23 4DMEI L A TAS 234 GSPD 345 Navigation Preview Mode NAV Figure 218 FMS ALERT MESSAGES PREVIEWED NAV SOURCE 22 14 00 Page 251 Aug 15 91 Use or dwlosure of information on this page is subject to the restrictions on the title page of this document ...

Page 426: ...isplay and TO FROM indicator The digital heading readout is replaced by amber dashes Additionally a red HDG FAIL label is displayed below the lubber line as shown in Figure 219 lRS test mode is shown with the label HDG TEST in the same location as the fail annunciation discussed above Figure 216 b Heading Select Failure Failure of the heading select signals will cause the digital display to be rep...

Page 427: ...23 4DME s Q I 0 0 0 o 0 ADF 1 0R2 SAT 56 TAS 234 GSPD Compass Caution Warning Displays IRS Figure 219 22 14 00 Page 253 Aug 15 91 Use or disclosure of information on this page is subject 10 the restrictions on the title page of this document ...

Page 428: ...G 000 Wx IL s 33 P1 NAV 1 DME SAT TAS GSPD 345 Compass Caution Warning Displays Mist Figure 220 22 14 00 Page 254 Aug 15 91 Use or disclosure of information on this page k subject to the restrictions on the title page of this document ...

Page 429: ...Failure A failure of the previewed NAV source is shown in the same manner as the active NAV source failure previously discussed A red dashed X is displayed through the deviation scale to preserve the ghosted image of the preview symbology i EFIS Self Test This test is initiated through the on side display controller TEST mode when airspeed is valid and less than 60 knots and the WOW switch is acti...

Page 430: ... display format the heading fixed at true north up as shown by the white n the upper right corner of the display FMS source Figure 221 This is the only on given in the plan mode c Wind Display The wind format is displayed in white using head or tail wind and left or right cross wind labels with the associated magnitude Figure 221 The left right components are displayed positionally above the head ...

Page 431: ...5 VERT ALRT TRK CHG OFFSET 25 0 KNBC 2 0 KLHU 56 TAS 234 GSPD 345 Use or disclosure of reformation CE MS ALERT MESSAGES PLAN MODE POSITION Plan Mode Display PLAN Figure 221 Format 22 14 00 Page 257 Aug 15 91 on this page is subject to the restrictions on the title page of this document ...

Page 432: ... Figure 221 Navaids can be displayed with or without IDs as selected through the display controller h Airports The FMS outputs data for the nine max closest airports to present position These are displayed when selected in cyan using a circular symbol Figure 221 Airports can be displayed with or without IDs as selected through the display controller i Waypoint Annunciations Track changes both late...

Page 433: ...Warning Displays a IRS Failures and Flags Failure of the displayed heading is shown by removing the active flight plan and wind display and displaying in red the label HDG FAIL at the top center of the plan range ring Figure 222 IRS test mode is shown with the label HDG TEST in the same location as the fail annunciation discussed above see Figure 216 b FMS Failure A failure of the FMS removes the ...

Page 434: ...FAIL 25 25 r SAT TAS I IGSPD I Plan Mode Caution Warning Displays Figure 222 22 14 00 Page 260 Aug 15 91 Use or disclosure of information on this page is sublecf to the restrictions on the title page of thts document ...

Page 435: ...alve Status Indications Digital Readouts of Oil Pressure Oil Pressure Warning Indications Digital Readouts of Oil Temperature Oil Temperature Warning Indications Digital Readouts of Engine Vibration Monitor EVM LP Digital Readouts of Engine Vibration Monitor EVM HP Digital Readout of Combined Hydraulic Pressure Digital Readout of Flight Hydraulic Pressure COMB FLT Hydraulic Pressure Valve Status I...

Page 436: ...n the left two thirds of the engine display format This area is divided into five rows of engine gauges as follows Engine Pressure Ratio EPR Turbine Gas Temperature TGT Low Pressure Tach LP High Pressure Tach HP Fuel Flow FF Each engine gauge is a 225 degree arc with moving pointer and fixed current value window located above the pointer rotation point Each engine gauge type is labeled in white be...

Page 437: ...ssure Engine fan duct pressure is received pneumatically from the on side engine Total pressure is received from the on side AZ 81O Digital Air Data Computer DADC via ARINC 429 Cross side DADC is used if the on side is invalid To compensate for variations in the actual thrust versus EPR of different Rolls Royce Tay engines a seven wire trim plug discrete input is provided This allows the engine te...

Page 438: ...layed on the EPR scale in green Figure 225 corresponding positionally to the green digital readout above each EPR current value window Generally there is not a mode annunciation given for the target bug since the target corresponds to the selected limit mode FLEX mode is the one exception When FLEX mode is selected takeoff TO is the displayed limit mode and a green FLEX mode annunciation is displa...

Page 439: ...arc limit and the digits show the actual TGT value TGT exceedance amber red regions is shown by growing the colored band to twice the normal width and changing the pointer and current TGT digital value normally white color to match the arc region color 22 14 00 Page 265 Aug 15 91 Use or disclosure of information on this page is subject to the restrictions on the tttle page of this document ...

Page 440: ...ART VALVE IGNIT ON EPR TGT LP SYNC HP FF pj mo Engine instrument Display Format SENSOR Figure 223 22 14 00 Page 266 Aug 15 91 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 441: ...BOL GENERATORNO 2 r 1 rRIGHT EPR XMTR 1 J I I h OP SIDEDADC H I ARINC 429 L 49 I CROSS SIDE DADC H 55 ARINC 42S L 44 I EPR OUTPUT H 31 I NO 1 ARINC 429 L 39 I EPR OUTPUT H 37 NO 2 ARINC 429 L 52 L A XbSSODISPLAYUNIT NO 4 1 H PRIMARY SG DU L BUS I I H ALTERNATE NO i L SGIDU BUS I I H ALTERNATE No 2 I L SGIDU BUS J hA4B4 DATA I Em r 137J1A I ASCE I P H CHANNEL A L I I r SG SS4SYMBOL GENERATORNO 1 1 ...

Page 442: ...MP mm EVM LP l I HPl HYD PRESS COMB FLT ml plmq ENG FUEL TEMP mm FUEL QTY 50 Engine instrument Display Format TRS Figure 225 22 14 00 Page 269 Aug 15 91 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 443: ...iator If the crew chooses to sync the engines using LP a SYNC annunciation is displayed in green directly below the LP scale label Figure 223 High Pressure HP Tach Display The HP instruments form the fourth row of gauges on the primary engine display Figure 223 The HP arc is banded with red white amber and red colors to show the low end warning normal high end caution and high end warning ranges o...

Page 444: ...dout window is located directly above the pointer rotation point The white FF actual value corresponds to the pointer position on the scale and is readable to a 1O PPH resolution If the actual data goes below 250 PPH the pointer remains stationary at the lower limit and the digits show actual FF value If the actual data goes above 8000 PPH the pointer remains stationary at the upper limit and the ...

Page 445: ...0 C OIL TEMP 30 C WHITE 30 C OIL TEMP 105 C AMBER 105 C OIL TEMP 120 C RED 120 C OIL TEMP c Engine Vibration Monitor EVM Display The EVM displays Figure 223 consists of two sets of windows row 3 and 4 labeled LP and HP respectively EVM is displayed digitally in white to a 0 01 IPS resolution d Combined Hydraulic Pressure FLT HYD PRESS The COMB HYD PRESS digital readout is the left most display in ...

Page 446: ...W LT AUX l l 1 ENG FUEL TEMP mm FUEL CITY 50 COMB FLT PRESS VALVE CLOSED Fuel Flow Hydraulic Pressure Valve Symbology TRS MAN Figure 226 22 14 00 Page 273 Aug 15 91 Use or disclosure Of information on this page is subject to the restritilons on the title page of this document ...

Page 447: ...n white to a 1OO PSI resolution i Engine Fuel Temperature ENG FUEL TEMP Display The ENG FUEL TEMP is displayed digitally in white in the seventh row of the secondary engine parameter display Figure 223 The resolution of the digital readout is 1 C The display digits change color as a function of oil temperature as defined below RED FUEL TEMP 40 C WHITE 40 C s FUEL TEMP 90 c AMBER 90 C s FUEL TEMP 1...

Page 448: ...ut is replaced with amber dashes Figure 227 Bus Controller Failures In the event the three bus controllers fail the indication given would be that of a dual display controller failure and a dual DAU failure as previously discussed FMS Failure Failure of the PFD commanded FMS PZ causes the command bug to be removed from the display with the corresponding digital readout replaced with amber dashes F...

Page 449: ...ESS COMB FLT UTIL AU c1 l mm l NG FUEL TEMP FUEL QTY T Engine Instrument Display Failure Indications Figure 227 22 14 00 Page 276 Aug 15 91 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 450: ... one third of the usable display space The color convention and displayed priority for messages on the CAS display is defined as follows RED Warnings Top message Stack AMBER Cautions Middle Message Stack BLUE Advisories Bottom Message Stack Master Warning Caution Panel The main crew interface with the CAS display is through the warning caution panel mounted in front of each pilot on the instrument...

Page 451: ...FAIL FLIGHT REC FAIL AC EXT POWER DC EXT POWER VHF COMM 1 2 FAIL ISOLATION VLV OPEN SERVICE DOORS L OIL FILT BPASS R COWL A I E BATT 1 FAIL APU ALT OFF CPL DATA INVALID I 1 r J3 L AMBER BLUE MESSAGE STATUS MESSAGE STATUS Crew Alerting System CAS Display Format Figure 228 22 14 00 Page 278 Aug 15 91 Use or disclosure of information on this page is subject to the restrictions on the title page of th...

Page 452: ...N VHIBIT CAS SCROLL ON J AP OFFI UP I I I I I I 1 I I I 1 1 I DN I I I I d Master Warning Caution Panel Figure 229 22 14 00 Page 279 Aug 15 91 Use or disclosure of information on this page is sublect to the restrictions on the title page of this documenl ...

Page 453: ... function a Warning Red Messages The available red messages are listed in Table 202 When a red message becomes active the following indications are given red message displayed flashing on the CAS display red message aural alert is sounded red annunciator on the master warn panel is lit When the red annunciator pushbutton is selected on the master warning panel the red annunciator is extinguished a...

Page 454: ... WSP 18 BIT 1 28 0 JIB 20 WSP 15 BIT 11 2 JIB 70 WSP 18 BIT 12 CALCULATED CALCULATED JIB 69 WSP 18 BIT 11 G O JIB 31 WSP 16 BIT6 28 0 JIB 55 WSP 17 BIT 14 28 0 JIB 13 WSP 15 BIT4 28 0 JIB 24 WSP 15 BIT 15 28 0 J1B 10 WSP 15 BIT 1 28 0 JIB 12 WSP 15 BIT3 28 0 JIB 9 WSP 15 BITO 28 0 JIB 14 WSP 15 BIT5 28 0 JIB 20 WSP 15 BIT 11 28 0 JIB 31 WSP 16 BIT6 28 0 A9 1 Messa e enable state normal operation A...

Page 455: ...of the amber stack Acknowledged messages are removed from the CAS display when the condition causing the message is remedied c Advisory Blue Messages The available blue messages are listed in Table 204 When a blue message becomes active the following indications are given blue message displayed flashing on the CAS display blue message aural alert is sounded The blue message appears flashing on the...

Page 456: ...CULATED DAU 1 2 MISCMP MSG FWC CALCULATED DU FAN 1 2 FAIL DAU 1 2 JIB 78 WSP 19 BIT4 OjG EL CMB FLT HYDOFF DAU 1 2 JIB 33 WSP 16 BIT8 28 0 EL MISTRIM NOSE DN FGC WSP 38 BIT 3 EL MISTRIM NOSE UP FGC WSP38 BIT 4 ENG FLT LOOP ALRT DAU 2 JIB 69 WSP 18 BIT 11 G O EPMP BATT SW OFF DAU 1 JIB 56 WSP 17 BIT 15 28 0 EPMP POWER FAIL DAU 1 JIB 59 WSP 18 BIT 2 28 0 FGC 1 2 FAIL FGC ASCB LOGIC IN FWC FWD RADIO ...

Page 457: ... WSP 17 BIT 14 28 0 STALL BARR 1 2 FL DAU 1 2 JIB 38 WSP 16 BIT 13 0 28 STALL BARRIER OFF DAU 1 JIB 57 WSP 18 BIT O 28 0 STALL BARRIER 1 2 DAU 1 2 JIB 44 WSP 17 BIT 3 28 0 STBY PITOT HT FAIL DAU 1 JIB 76 WSP 19 BIT 2 STEER BY WIRE FAIL FWC JIA 26 A TAT PROBE HT FAIL DAU 2 JIB 76 WSP 19 BIT 2 G O TRIM LIMIT FGC WSP38 BIT 1 TRU FAIL DAU 1 JIB 58 WSP 18 BIT 1 28j0 TRU HOT DAU 2 JIB 50 WSP 17 BIT 9 28...

Page 458: ... POWER FWC JIB 9 28j0 DISP CTLR 1 2 FAIL DC ASCB DU 1 2 3 4 5 6 HOT FWC J1A 34 35 36 37 38 39 G O E BATT 1 2 DISCH DAU 1 2 JIB 39 WSP 16 BIT 14 28 0 E BATT 1 2 FAIL FWC JIA 71 72 O G ENGINE EXCEEDANCE FWC CALCULATED 5 SECOND EPR 1 DADC 2 DAU 1 WSP 11 BITS 0 1 EPR 2 DADC 1 DAU 2 WSP 11 BITS 0 1 EXT BATT SWITCH ON DAU 1 JIB 52 WSP 17 BIT 11 28 0 FGC NOT USING IRS 1 2 FGC WSP 3 BITS 14 15 FGC SYSTEM ...

Page 459: ... JIB 17 WSP 15 BIT8 28 0 JIA 85 G O WSP 6 BIT 5 WSP 6 BIT 6 WSP 6 BIT 7 b WSP 39 BIT 6 WSP 39 BIT 7 ASCB NZ 3 FWC JIA 87 ASCB JIB 19 WSP 15 BIT 10 Oj28 WSP 38 BIT 14 JIB 54 WSP 17 BIT 13 28j0 WSP 39 BIT 5 JIB 59 WSP 18 BIT 2 28j0 ASCB JIA 51 52 53 G O JIB 49 WSP 17 BIT 8 28 0 ASCB DAU VS FGC LOGIC IN FWC WSP 6 BIT 4 JIB 57 WSP 18 BIT O 0j28 CALCULATED JIB 19 20 0j28 ASCB LOGIC IN FWC JIA 25 O G WS...

Page 460: ...te the direction the message was scrolled The amber readout and arrow correspond to the amber messages scrolled off the display and is located on the left side of the status line The blue readout and arrow correspond to the blue messages scrolled off the display and is located on the right side of the status line It is possible to have a total number with arrows pointing in both directions The num...

Page 461: ...erence is detected between the DAU channels the miscompare message is activated as appropriate i e DAU 1 2 or 1 2 CHECK PFD Red Message This message is active anytime the CHECK DU message is active from both the pilot s and copilot s primary flight displays PFD The CHECK DU messages relative to the PFDs are suppressed whenever the CHECK PFD message is active Refer to the next paragraph for the CHE...

Page 462: ...e is displayed and the DU4 message is suppressed e DAU 1 2 MISCMP MSG Amber Message The fault warning computer compares the amber message activation logic between each channel A and B of a particular DAU If a difference is detected between the DAU channels the miscompare message is activated as appropriate i e DAU 1 2 or 1 2 f DAU 1 2 MISCMP ENG Amber Message The fault warning computer compares pr...

Page 463: ...sed in the previous paragraph c EICAS Self Test This test is initiated through either display controller TEST mode when airspeed is valid and less than 60 knots and the WOW switch is active Selecting the EICAS self test gives the following indications in the cockpit c All Red Messages Displayed c AP OFF Horn Active c AP OFF Light On Red Aural Alert Active EICAS Fail Discrete Active Master WARN CAU...

Page 464: ...Honeywell i wcE CAS Display Failure Indications Figure 230 22 14 00 Page 291 Aug 15 91 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 465: ...tus Indications Utility Hydraulic Pressure UTIL PRESS Digital Readout Auxiliary Hydraulic Pressure AUX PRESS Digital Readout Combined Hydraulic Quantity Analog Scale Vertical Tape Flight Hydraulic Quantity Analog Scale Vertical Tape Applied Brake Pressure Analog Scales Vertical Tape a Combined Hydraulic Pressure COMB PRESS COMB PRESS is displayed digitally in white on the left side first row of th...

Page 466: ...SS AUX PRESS m m HYDRAULIC APPLIED QUANTITY BRAKE PRESS r FULL ADD LOW d Hydraulic System Page Figure 231 22 14 00 Page 293 Aug 15 91 Use or disclosure of reformation on this page is subject to the restrictions on the title page of this document ...

Page 467: ... The triangular shaped scale pointers change color depending on the indicated quantity range The color relationship is as follows RED HYD QTYs LOW WHITE HYD QTY LOW g Applied Brake Pressure Left Right LT RT The applied brake pressure scales are located in the lower right hand corner of the hydraulic system page The left LT and right RT applied brake pressure scales are marked with tickmarks every ...

Page 468: ...adouts are located at the top first row of the fuel system page The white FF label is located between the left and right digital display windows The white current value readouts are readable to a 10 pounds per hour PPH resolution b Fuel Flow Valve Status Indications When the fuel flow valves are in the closed position amber cross hatch is displayed within the FF digital readout window Figure 226 W...

Page 469: ...S AUX PRESS HYDRAULIC tlUANTITY FULL ADD LOW APPLIED BRAKE PRESS mmEl Hydraulic System Page Failure Indications Figure 232 22 14 00 Page 296 Aug 15 91 Use or disclosure of Informellon on this page is subject to the restrictions on the title page of this document ...

Page 470: ...EMP mm FUEL TANK TEMP m FUEL QTY EElm Fuel System Page Display Figure 233 22 14 00 Page 297 Aug 15 91 Use or disclosure Of information on this page IS subject to the restrictions on the ttle page of this document ...

Page 471: ...solution The display digits go to amber when a Fuel Level Low indication is received The total window turns amber only if both sides indicate fuel level low System Page Failure Indications DAU Failures A DAU failure is indicated by replacing the current value digits with amber dashes Figure 234 The above failure indications are given on the FF left ENG FUEL TEMP left FUEL TANK TEMP and FUEL QTY le...

Page 472: ...MP FUEL TANK TEMP FUEL QTY Fuel System Page Failure Indications Figure 234 22 14 00 Paae 298 1 Aiig 15 91 Use or disclosure Of information on this page is subject to the restrictions on the title page of this document ...

Page 473: ...ES UAYPT LIST APU BLEED APU EGT m b BLEED AIR RPM PRESS APU BLEED System Page Display Figure 235 22 14 00 Page 298 2 Aug 15 91 Use or disclosure of information on this page is subject to the restrmtions on the title page of this document ...

Page 474: ... colors to indicate normal caution and warnin ran es respectively The arc boundaries range between O and 1 O R M The color range definition for APU RPM is as follows WHITE O RPM s RPM 104 RPM 4 ER 104 RPM s RPM 110 RPM 110 RPM s RPM 120 RPM The RPM current value readout corresponds to the pointer position on the scale and is readable to a 1 RPM resolution If the actual data goes above 120 RPM the ...

Page 475: ...draulic Pressure COMB HYD PRESS Digital Readout Fli ht Hydraulic Pressure FLY HYD PRESS Digital Readout 8 COM FLT Hydraulic Pressure Valve Status Indications Utility Hydraulic Pressure UTIL HYD PRESS Digital Readout 4 s Auxiliary Hydraulic Pressure AUX HYD PRES Digital Readout The ENGINE START format is available for on ground use only The display controller ENG START prompt is removed when weight...

Page 476: ...BLEED AIR PRESS E23 APU BLEED System Page Failure Indications Figure 236 22 14 00 Page 298 5 Aug 15 91 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 477: ...o I 700 600 500 40 300 200 100 50 40 J 30 20 10 R TGT R HP L OIL 35 SING RUD R OIL 35 PRESS LIMIT PRESS HYDRAULIC PRESSURE COMB FLIGHT UTIL AUX 3000 3000 3000 3000 Engine Start Page Display Figure 237 22 14 00 Page 298 6 Aug 15 91 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 478: ...he L TGT s is the first scale in the fourth row of analog scales display is a low end expansion of the TGT round dial gauge on the primary engine instruments The white scale is marked every 100 C and ranges between 100 and 700 C A set point triangular mark is shown at 425 C A white label L TGT appears at the scale bottom The data display pointer is a moving ladder type thermometer As the TGT value...

Page 479: ...type thermometer As the HP value increases the thermometer grows up the scale A ladder rung is left at each labeled tickmark i Left Engine Oil Pressure L OIL PRESS Display The L OIL PRESS digital readout is located in the first box of the fifth row of the ENGINE START format The normally white digits are readable to a 1 PSI resolution The display digits change color as a function of oil pressure a...

Page 480: ...ital readouts with amber dashes The above indications are given on the LBLEED AIR L TGT L OIL PRESS COMB PRESSURE and UTIL PRESSURE displays for a DAU 1 failure The LFUEL PRESS LOW L SVO L IGN and SING RUD LIMIT annunciations won t activate in this condition Figure 238 shows a DAU No 1 failure indication The above indications are given on the RBLEED AIR RTGT ROIL PRESS FLIGHT PRESSURE and AUX PRES...

Page 481: ... 30 20 8 a 1 10 0 lLTGTILHpl RTGTl RHp L OIL R OIL 35 PRESS PRESS HYDRAULIC PRESSURE I COMB FLIGHT UTIL AUX 3000 3000 Engine Start Page Failure Indications Figure 238 22 14 00 Page 298 10 Aug 15 91 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 482: ...essage is displayed Subsequent selection of the EXCEEDANCES system page will show the parameter that caused the engine exceedance on the TRIGGERED BY line The highest value of all parameters is recorded on the display The time clock is started only if the appropriate parameter is above the exceedance threshold The exceedance thresholds are set in accordance with the G IV flight manual The clock is...

Page 483: ... 00 49 5 0 00 49 5 0 00 80 3 0 00 80 3 0 00 TRIGGERED BY L TGT EGT RPM APU EXCEEDANCE MAX 0000 000 0 TRIGGERED BY N A Engine APU Exceedances Page Figure 239 22 14 00 Page 298 12 Aug 15 91 Use or disclosure of information on this page is subject to the restrictions on the title page of thts document ...

Page 484: ...NCES NO EXCEEDANCES RECORDED No Exceedances Recorded Format Figure 240 22 14 00 Page 298 13 Aug 15 91 Use or disclosure of informa lon on this page k subject tothe restrictions on thetitle page ofthis document ...

Page 485: ...iption Normal CHECKLIST Procedures The power up default mode of the CHECKLIST is normal procedures When selected on the display controller the normal procedure CHECKLIST index is displayed Figure 242 In this mode the normal procedure label and page index are displayed in white at the top of the index list The index contains those procedures which make up the normal operation section of the flight ...

Page 486: ...S EXCEEDANCES UNAVAILABLE Exceedance Data Failure Indications Figure 241 22 14 00 Page 298 15 Auq 15 91 Use or dkclosure of information on this page is subject to the restrictions on the Mle page of this docum t ...

Page 487: ...L PROCEDURES 1 2 3 STARTING ENGINES 4 AFTER STARTING ENGINES 5 J W FORE 6 LINE UP Checklist System Page Display Figure 242 22 14 00 Page 298 i6 Aug 15 91 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 488: ...by numerical designation CHECKLIST item skipped i e not entered f CHECKLIST Mode Exit To get out of the CHECKLIST mode a different system page must be selected g Auto Callup Of Emergency Procedures Emergency checklist procedures are called up for display automatically whenever any one of the following conditions have been detected c Engine hot Engine fire Reverser unlock APU fire Cabin pressure lo...

Page 489: ...NGINES I I 4 AFTER STARTING ENGINES 5 TAXI BEFORE TAKEOFF 6 LINE UP I I 3 LINE At tiANCES Checklist System Cursor Control Figure 243 22 14 00 Page 298 18 Aug 15 91 Use or dkclosure of information on this page is subject to the restricflons on the title page of this document ...

Page 490: ...point Data Line 2 Magenta TO Waypoint Data Line 3 c Next 8 Flight Plan Waypoints Data Lines 4 11 c Present Position PPOS Data Line 12 Each waypoint is displayed with IDENT and corresponding latitude LAT and 1ongi tude LON 15 Waypoint List Failure Mode Indications FMS Failure No Active Flight Plan In the event that the pilot s displayed FMS fails all the data in the waypoint list is replaced with a...

Page 491: ...8 ATL N 33 37 8 U 84 26 KATL N 33 38 4 U 84 2S TO 5 TO 6 To 7 TO 8 PPOS N 32 07 8 U 81 12 L Waypoint List Display Page Figure 244 FMS SOURCE UNUSED LINES 7RESENT 3osITIoN 22 14 00 Page 298 20 Aug 15 91 Use or disclosure of information on this page IS subject to the restrictions on the title page of this document ...

Page 492: ...EN FAIL VOICE REC FAIL FLIGHT REC FAIL AC EXT POWER DC EXT POWER VHF COMM 1 2 FAIL ISOLATION VLV OPEN SERVICE DOORS L OIL FILT BPASS R COWL A I E BATT 1 FAIL APU ALT OFF CPL DATA INVALID TIT 3 L d System Page Declutter Mode Figure 245 22 14 00 Page 298 21 Aug 15 91 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 493: ... Readouts of Oil Pressure Oil Pressure Warning Indications Digital Readouts of Oil Temperature Oil Temperature Warning Indications Crew Alerting System Messages Compacted EICAS General The compacted EICAS display is formed by combining primary engine data parameters with the CAS system on one display format The engine instruments ENG comprise the left two thirds of this format The crew alerting sy...

Page 494: ... Low Pressure LP Tach Display The LP instruments comprise the third row of gauges on the primary engine display The operational description of the LP tach function is provided in paragraph 2 E 2 h e Anti Ice A 1 Annunciator This annunciation is displayed in green above the LP digital readout windows The annunciation label isA I f LP Synchronization SYNC Annunciator If the crew chooses to sync the ...

Page 495: ... FAIL TONE GEN FAIL VOICE REC FAIL FLIGHT REC FAIL AC EXT POWER DC EXT POWER VHF COMM 1 2 FAIL ISOLATION VLV OPEN SERVICE DOORS L OIL FILT BPASS R COWL A I E BATT 1 FAIL APU ALT OFF CPL DATA INVALID rI r 3 Compacted EICAS Display Format Figure 246 22 14 00 Page 298 24 Aug 15191 Use or disclosure of information on this page is subjecf to the restrictions on the title page of this document ...

Page 496: ...ription is provided in paragraph 2 E 3 a Engine Oil_Temperature T Display Theengine_oil temperature T digital readouts comprise the seventh row of the engine instrument display format area The operational description is provided in paragraph 2 E 3 b Crew Alerting System CAS Display The operational description for this system is provided in paragraph 2 F The only difference between the CAS display ...

Page 497: ...0 EPR TGT LP Compacted EICAS Failure Mode Indications Figure 247 22 14 00 Page 298 26 Aug 15 91 Use or disclosure of mformalion on this page is subject to the restrictions on the title page of this document ...

Page 498: ... blue ADI ground brown and altitude and speed gray shading ND WX returns is removed The next indication is a blank display b SG Interface Mode Indications An SG or interface failure is indicated by displaying a red X over the entire DU display area as shown in Figure 249 3 DU Reversionary Modes a Pilot s DU Reversionary Modes The pilot s PFD reversion is to transfer the PFD format onto the NAV dis...

Page 499: ...E I CAS COPI LOT I I I I I I I I SYMBOL GENERATOR CONTROL I I I I I I I I I L 1 Display System Reversionary Panel Figure 248 22 14 00 Page 298 28 Aug 15 91 Use or disclosure of information on this page is subject to the restrictions on the title page of thm document ...

Page 500: ...Symbol Generator Failure Mode Indication Figure 249 22 14 00 Page 298 29 Aug 15 91 Use or disclosure of information on this page is subject to the restrictions on the title page of this dccument ...

Page 501: ... F COPILOT PFD Pilot s PFD Reversionary Mode Figure 250 22 14 00 Page 298 30 Aug 15 91 Use or disclosure of information on this page is subject to the restrictions on the title page of thw document ...

Page 502: ...ILOT S DC q l COPILOT S DC m ENGINE CAS SYSTEM Copilot s PFD Reversionary Mode Figure 251 22 14 00 Page 298 31 Aug 15 91 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 503: ...plays If SG No 3 control was selected to the alternate position prior to the SG No 1 failure then SG No 2 would be in use by all six DUS and a multiple SG failure condition would exist refer to paragraph 2 1 4 d b Symbol Generator 2 Copilot s Normal Failure A failure of SG No 2 would be shown in one of the following manners Red X on the copilot s PFD Red X on the copilot s ND c Red X on both the c...

Page 504: ...le SG Failures A single SG is capable of driving the six DUS in the G IV EFIS EICAS system in the event that any two SGS fail The pilot s and copilot s PFD and NDwould be identical in this case All same source indications amber source annunciations would be on each display The sinqle SG reverts to the pilot s DC for display command which SG is driving the six DUS If the pilot single SG reverts to ...

Page 505: ... the pilot s and copilot s DC fails the SG driving the ENGINE and CAS displays will automatically use DAU 1 channel A DAU 2 channel B and FWC 1 sources The pilot copilot PFD and ND sources for this condition are the same as previously described in paragraphs 2 I 5 a and b Dual DC failures have no effect on the FGC source other than the source cannot be manually selected via the DC 22 14 00 Page 29...

Page 506: ...S DC j EIFl COMP EICAS COPJ OT I I Engine Display Failure Reversionary Mode Figure 252 22 14 00 Page 298 35 Aug 15 91 Use or disclosure of mformatlon on Ihls page ssubject to therestrictions on thetitle page ofthis document ...

Page 507: ...l m Ellzl COMP EICAS 1 COP OT 1 COPILOT PFD CAS Failure Reversionary Mode Figure 253 22 14 00 Page 298 36 Aug 15 91 Use or disclosure Of information On this page is subject to the restrictions on the title page of this document ...

Page 508: ...ependent on selected mode S controller status as well as internal and discrete logic such as current radio altitude gear up down weight on wheels and the ground proximity warning system inhibit TCAS FAIL is displayed on the CAS in eventof failure TCAS mode of operation is displayed beside the PFD vertical speed tape and an extended test page is available on the ground on the TCAS system page 2 TCA...

Page 509: ...indicator digits are colored to correspond with the color band for the vertical speed they occupy so that if TCAS is displaying a red guarded band from 6000 fpm to 500 fpm and a green target band from 500 fpm to O fpm the vertical speed indicator digits are red from 6000 to 500 green from 500 to O and white above O to 6000 The TCAS mode is displayed on the PFD beside the vertical speed tape opposi...

Page 510: ... Data tags are the same color as their associated target The IVSA is an arrow appended to the RAD to indicate target vertical speed direction if it exceeds 499 fpm This arrow points up for climbing and down for descending traffic 9 off scale Symbol On DU 4 only targets that are being tracked but are not within the range of the display are shown as off scale targets These are regular target symbols...

Page 511: ...visories are provided for and a complete list can be found in the TCAS Pilot Manual 4 TCAS Test Figure 253 4 and 253 5 TCAS test is initiated from the test button of the ACTIVE mode S controller and lasts approximately 8 seconds TCAS test consists of the following a The TCAS system page will appear if not already selected Figure 253 4 b TCAS TEST will be announced over voice advisory c TCAS FAIL w...

Page 512: ...ile viewing the test page the Mode S Bus 2 will change from active to inactive until the breaker is reset NOTE Attempting extended test with both TCAS and transponders in standby will lockup the TCAS in test mode Activating the No 1 transponder will release it 6 TCAS Computer Test A test function is available from the front of the TCAS unit itself This test is of the current status of the TCAS and...

Page 513: ... w II I NO BEARING TARGETS II 1 1 NM 02 T 2 0 NM 23 ABOVE NORMAL OR BELOW ANNUNCIATOR PROXIMATE TRAFFIC SYMBOL RESOLUTION ADVISORY TRAFFIC SYMBOL DATA TAG OWN AI RCRA SYMBOL OTHER TRAFFIC SYMBOL NO BEARING TARGETS AD 34393 TCAS System Page Display Figure 253 1 22 14 00 Page 298 36 6 Apr 15 93 Use or disclosure of information on thispage issubject to the restrictions on the title page of thisdocume...

Page 514: ...STEM 0000 J35 5 Sfr TCAS TARGETS TCAS Targets on the Navigation Display Figure 253 2 Aoasal 22 14 00 Page 298 36 7 Apr 15 93 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 515: ...ory on the Primary Flight Display Figure 253 3 EXPANDED VERTICAL SPEED SCALE OVERTICALSPEED GREENTARGET BAND VERTICAL SPEED REDGUARDED BAND Ao s4s92 22 14 00 Page 298 36 8 Apr 15 93 Use or disclosure of information on thispage issubject to the restrictions on the title page of thisdocument ...

Page 516: ...k34S9S TCAS Test on the System Page Display Figure 253 4 22 14 00 Page 298 36 9 Apr 15 93 IJse or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 517: ... 4 1 E j J II ivdME i P 1 TEST o 0 50 o f 0 2 HOG 050 0 0 OK Owl TCASMODE ANNUNCIATOR TCAS Resolution Advisory Test on the Primary Flight Display Figure 253 5 GREEN TARG BAND LOWERRED GUARDED BAND Ao 34394 22 14 00 Page 298 36 10 Apr 15 93 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 518: ...BUS 1 ACTIVE RADIO ALT BUS 2 ACTIVE MODE S BUS 1 ACTIVE MODE S BUS 2 ACTIVE Au mq TCAS Extended Test on System Page Display Figure 253 6 22 14 00 Page 298 36 11 Apr 15193 Use or disclosure of information on thispage issubject to the restrictions on the title page of thisdocument ...

Page 519: ...rovides guidance to the azimuth and glidepath angles selected on the control unit or transmitted from the ground station Guidance is output from the receiver in the form of digital deviation signals intended to drive conventional course deviation indicator CDI displays The MLS receiver scales and biases these ARINC 429 labels to the corresponding ILS mV per dots of deviation allowing integration t...

Page 520: ... and offside sources available MLS 1 FAIL or MLS 2 FAIL is displayed in the CAS as appropriate in the G IV dual installation MLS FAIL is also supported in the FC 880 Fault Warning Computer but is for single installations a Primary Flight Display Figure 253 7 Annunciation for lateral and vertical modes with MLS are AZ and GP respectively and are displayed at the top of the PFD as with other nav sou...

Page 521: ...200 2 20 260 1500 5000 0 22M 1770M 30 021N 4 CRS 1 010 F t lm tiM 4 6 C 1 0 TA R 2 gig OADFI COURSE COURSE DEVIATION BAR POINTER VERTICAL DEVIATION INDICATOR NAV SOURCE ANNUNCIATOR DME DISPIAY AX4 U9S MLS Displays on the Primary Flight Display Figure 253 7 22 14 00 Page 298 36 14 Apr 15 93 Use or disclosure of information on this page is subject to the restrictions on the title page of this docume...

Page 522: ...e amber The vertical deviation indicator functions as with is green and is labeled P for path in glidepath DME is in the top right corner and is displayed with The distance readout will be dashed if DME is unavai Due to DME sharinq scheme the DME can be unavailable LS but MLS able to the MLS As the G IV is configured for front azimuth approaches only there is no need for a TO FROM indicator Previe...

Page 523: ...HDG 025 Wx VAR GCR I 0 ADF1 SAT 52 TAS 300 GSPD 325 DME DISPU4Y VERTICAL DEVIATION INDICATOR Ao s4397 MLS Active Mode Displays on the Navigation Display Figure 253 8 22 14 00 Page 298 36 16 Apr 15 93 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 524: ...IEW I SAT VAR I 52 GCR TAS 58 MLS1 17 2 DME I g 4 0 325 II I I r PREVIEW PREVIEW PRE VIEW A21MUTH DME NAV DISPLAY DISPLAY SOURCE ANNUNCIATOR AD 343ea MLS Preview Mode Displays on the Navigation Display Figure 253 9 22 14 00 Page 298 36 17 298 36 18 Apr 15 93 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 525: ...mit Pitch g Command Limit Up Trim Limit Down Trim Limit Roll Angle Limit Roll Rate Limit VOR VOR APP Capture Beam Intercept Angle HDG SEL Lateral Beam Sensor LBS Capture Point Rol1 Up to 75 deg Pitch Up to t50 deg Up to t35 deg max t6 deg min 20 deg up 15 deg down 3O deg Roll 5 5 deg sec 20 deg up 15 deg down o 2g 0 1 g 20 52 0 5deg 6 sdeg za deg 120 deg low bank switched on GP 820 4 0 deg sec 2 d...

Page 526: ...eg sec Up to t45 deg Course Error Up to t90 deg 14 deg 7 0 deg sec when TAS s 180 knots or 2 VOR mode cannot be armed or engaged unless IRS TRUE TRACK is valid IRS TRUE TRACK is valid only if groundspeed is 20 kts GP 820 LOC Capture LNAV Button LOC Beam Intercept Angle Up to t90 deg BC Button BC HDG SEL CRS Knob and NAV Receiver Capture Point Function of Beam Beam Closure Rate and Course Error Min...

Page 527: ...Programming Fixed Flight Director Pitch Up Command Wings Level in Roll 30 deg 7 0 deg sec 45 deg Course 224 deg 5 5 deg sec Up to t45 deg Course Error Function of Radio Altitude TAS and GS Deviation Function of Beam and Beam Closure Min Trip Point 20 mV dc Max Trip Point 37 5 mVdc 10 deg 15 deg Error Rate Vertical Acceleration Preset 0 2 g maximum Function of Radio Altitude TAS and Vertical Speed ...

Page 528: ...Pitch Limit Pitch Rate Limit VS Required for Automatic ASEL ARM O to 60 000 ft 40 ft 20 deg up 15 deg down Preset 0 1 g maximum O to 6000 ft min 8000 ft min 1OO ft min 20 deg up 15 deg down 0 1 g maximum 0 4 to 0 88 Mach 0 01 Mach 20 deg up 15 deg down 0 2 g maximum 80 to 340 KN CAS 5 KN 20 deg up 15 deg down 0 2 g maximum 60 ft min for 3 seconds in the direction of the ALT preselect value System ...

Page 529: ...apture Range Maximum Vertical Speed for Capture Capture Maneuver Damping Pitch Limit O to 60 000 ft 20 000 ft min Complemented Vert Acceleration 20 deg up 15 deg down 0 05 g with VS K 10 000 ft min 0 08 gwith VS 10 000 ft min 325 ft O to 60 000 ft 4O ft 20 deg up 15 deg down 0 1 g maximum 60 ft min for 3 seconds in the direction of the ALT preselect value O to 60 000 ft t20 000 ft min Complemented...

Page 530: ...gle Range Bias Range Pitch Limit Pitch Rate Limit 0 05g for VS 10 000 ft min 0 08g for VS 10 000 ft min 25 ft 0 4 to 0 88 Mach O 01 Mach 20 deg up 15 deg down 0 2 g maximum 80 to 340 KN 5 KN 20 deg up 15 deg down 0 2 g maximum O to 60 000 ft O to 6 deg f FMS waypoint 20 deg up 15 deg down 0 1 g maximum System Performance Operating Limits Table 205 cent 22 14 00 Page 298 42 Aug 15 91 Use or disclos...

Page 531: ...timum point for a smooth capture of the beam If the intercept angle to the beam center is very shallow the LBS will not trip until the aircraft is near beam center For this reason an override on the LBS occurs when the beam deviation reaches a specified minimum The minimum beam sensor trip point for the VOR mode is 20 mv In the LOC mode the minimum trip point is f35 mV The maximum LBS trip point i...

Page 532: ...ourse select error pitch wheel command air data commands and glideslope deviation to achieve approximately the same aircraft response regardless of the aircraft s airspeed and altitude The TAS computation is derived from airspeed altitude and outside air temperature PFD Command Bars or Cue When a command signal is applied to the bar or cue input the bar will move left or right roll or up or down p...

Page 533: ...aptured or in the track phase Glideslope deviation is less than 150 mV Either of the following conditions The VBS tripped GS deviation less than 20 mV h GS Track is satisfied Glideslope track occurs after the aircraft has captured the glideslope and is now tracking the beam The track phase provides for tighter flying of the beam The following conditions are necessary for the track mode to be satis...

Page 534: ...de the longer it takes to get through the cone of erratic radio information therefore the longer the time period must be Likewise the lower the aircraft altitude the smaller the cone of erratic radio information and the shorter the time period must be to trip AOSS 1 The required elapsed time period is also affected by the aircraft s true airspeed The faster the airspeed the quicker the aircraft wi...

Page 535: ...P 1 Localizer and back course capture 1 are the initial capture phases of their respective modes Localizer capture 1 and back course capture 1 will occur when the following conditions are all satisfied LOC armed plus 3 seconds Either of the following occurs Lateral beam sensor trips Beam deviation less than 35 mV m LOC CAP 2 and BC CAP 2 Local izer and back course capture 2 are capture phases whic...

Page 536: ...2 and BC Track 2 The track 2 submode will occur only after track 1 has been satisfied There is no visual indication to the pilot that the track 2 mode has been activated Radio altitude distance to the transmitter and a vertical velocity indicating the aircraft is descending are the factors involved in determining the track 2 condition When these conditions reach certain levels track 2 is tripped s...

Page 537: ...de For example VOR ARM sheet 2 is annunciated on the PFD when the LNAV switch is pushed on the GP 820 and the following conditions are met Tuned to VOR frequency NAV VOR Select Not tuned to localizer Lateral beam sensor has not tripped LBS TRIP All inputs to the OR gate to clear CLR or reset R the flip flop are not present If VOR is annunciated in white indicating the mode is armed the mode will b...

Page 538: ...AP AP 8 2LOCK c INOTES 1 THE GP 620 PILOT S SIDE CH IS I SHOWN THE COPILOT S SIDE CH2 IS SHOWN ON SHEET 2 2 13 LEVEL SHIFTERS NOTE 2 T SERIAL lN PARALLEL OUT A OEVICE SIPO THE INPUT IS LEVEL SHIFTED TO PROVIDE A 5 VDC PARALLEL INPUT TO THE PISO ALL CIRCLED LETTERS DENOTE TIE POINTS ON StiEET 2 w PROCESSOR wow 9 28 VOC ANNUNCIATOR VALID 9 11 r 6 K3 Is H c L J 5V PBARMMO 1 I I 8 AP I I E K DISENGAGE...

Page 539: ...c 8 INPUTS 5V I I I I I I I I I LAMP TEST2 7 4 h c STROBE CLOCK u sEFl P LAMP TEST J NOTES 1 THE GP 620 COPILOT S SIOE CH2 IS SHOWN THE PILOTS SIDE CH1 IS SHOWN ON SHEET 1 2 tHE iNPUT IS LEVEL SHIFTEO TO PROVIOE A S VOC PARALLEL INPUT TO THE PISO A PROCESSOR 3 ALE LE7TERS CIRCLED DENOTE TIE POINTS ON SHEET 1 wow 26 VOC ANNUNICATOR VAIJO m SERIAL lN PARALLEL 04JT OEVICE SIP 3 PSAJ3MN0 2 03 28 Voc f...

Page 540: ...1 CLOCK CLEAR 7 lLJ ST ANN VLCI f END A170UND I CLOCK I STROBE MRALLEL lN SERIAL OUT DEVICE PISO ANN VLO A FORALL MOOES A SECONO ACTIVATION OF THE SWITCH WILL RESET THE MODE THE INPUT IS LEVEL SHIFTED TO PROVIDE A 5 VDC PARALLEL INPUT TO THE PISD THE GPw21J PILOTS SIOE CHI IS SHOWN THE COPILOTS SIOE CH2 IS SHOWN ON SHEET 11 A PROCESSOR 8VOC ANNuNCIATOR VALIO ML CIRCLEO LETTERS OENOTE TIE POINTS ON...

Page 541: ... I LATCHESl LAMP ORIVERS TEST 2 I P I w I NOTES LAMP TEST TEST2 1 THE INPUTIS LEVELSHIFTEDTO ANNVLD ORIVE2 PROVIDE A5 VDC PARALLELINPUT I TO THE PISO END AROUND 2 THE GP 820 COPILOTS SIOE CH2 IS SHOWN THE COPILOTS SIDE CH1 I IS SHOWN ON SHEET I 3 ALL CIRCLED LETTERS DENOTE TIE 9 CLOCK I POINTS ON SHEET 1 STROBE PARALLEL IN 1 CLEAR SERIAL OUT OEVICE PISO ANN VLD 1 b 11J2 SERIAL H 7 PARALLEL DATA OU...

Page 542: ...I I I I VOR ARM 3 SEC LBS TRIPS s o vOR CAP m GA R HDG SEL LNAV SEL CLR vOR TRK L PFO CMD SEL NAV SOURCE CHANGE I TKOD AP ENG j I 3 J 3 J j I I I I I I I I I I I I I 1 B 0J2B r I I I I I I I I FGC D IRS MISCOMPARE IRS 3 I SDAOCVALID SEL LAT GUIOANCE VALID 5 SEC I CPLVALID 2SEC w I TTL I 93 _ FOR COUPLED PFD 4 NOTE vOR APPROACH MODE SELECTED AUTOMATICALLY WHEN i I I I I I L TAS 1S0 KNOTS OR FLAPS 0...

Page 543: ...ME HOLD HDG SEL LNAV SEL vOR AOSS 1 PfD CMD SEL NAV SOURCE CHANGE TKOD AP SNG Yld Jr R GA CLR HDG SEL LNAV SEL vOR AOSS 2 PFD CMD SEL NAV SOURCE CHANGE TKOD AP ENG 3 ORAO M tF GA Y h CLR HDG SEL LNAV SEL VOR TRACK PFD CMD SEL NAV SOURCE CHANGE TKOD AP ENG vOR AOSS 2 D L LATERAL ROLL MODES F1iqht Director Mode select Diagram Figure 255 Sheet 3 3 J 1 AO 13e63 R3 22 14 00 I I I I I I I I I I I I I d ...

Page 544: ...RM t R c 1 r s o LOC CAP 1 R CLR LOC CAP 1 3 SEC COURSE ERROR 35 v s DEV 175 mv LOC CAP 2 0 NOTE LOC TRACK1 3 R HDG SEL CLR LNAV SEL CS5 J L t LATERAL ROLL MODES PFD CMD SEL NAV SOURCE CHANGE TKOD AP ENG T F1ight Director Mode Select Diagram Figure 255 Sheet 4 I I I I I I I I I I I loJIB loJ2B 1 b ASCB OUTPUT 2 TO SYMBOL GENERATOR TO 4 DISPLAY SELECTED MODE ON PFD NOTE DEV f 165 mv FOR 936 907 FGC...

Page 545: ...SH1 Y APP SEL LNAV SEL GA I PFD CMD SEL NAV SOURCE CHANGE TKOD AP ENG I P I FGC VALID IRS MISCOMPARE lRS3 I SDADC CPL 2 SEC 1 K w F1iqht Director I I I I I I I I I I a w loJIB loJ2B PROCESSOR 1 Ascs ouTPuT A 2 TO SYMBOL PROCESSOR GENERATOR TO 4 DISFIAY SELECTED MODE ON PFD 5 I I I I I I I I I 1 I I I I I I L 1 LATERAUROLL MODES Mode elect Diagram Figure 255 Sheet 5 NOTE IF BOTH DADCS ARE INVALID T...

Page 546: ...D SEL NAV SOURCE CHANGE TKOD AP ENG P cTRAcK k VERT VEL 2 TAS 57 3 m LONG DIST 26K RAVAL RAO ALT 1200 RAVAL APP SEL LNAV SEL HDG SEL GA PFD CMD SEL NAV SOURCE CHANGE TKOD AP ENG I MAINTENANCE MANUAL GULFSTREAM IV 1 BC CAP 1 r s BC CAP 2 Q R CLR F s Q R CLR EC TRACK 1 I r s BC TRACK 2 0 R CLR I I I I I I I I I w10JIB 10J2B 1 ASCO OUTPUT A 2 TO SYMBOL PROCESSOR GENERATOR TO 4 DISPLAY SELECTED MODE O...

Page 547: ...BC CAP L J r SQ FMS CAP R CLR GA PFD CMD SEL TKOD AP ENG Y 5J3 a FOR COUPLEO PFD FMS VALID u FGC D IRS MISCOMPARE lRS3 _ SDADCVALID CPL VALID 2 SEC 4 I SELLAT GUIDANCE I 5SEC i I I I I I A PROCESSOR I10J1 B l OJ2B 1 ASCB OUTPUT 2 TO SYMBOL PRO SOR GENERATOR TO 4 DISPLAY SELECTED 5 MODE ON PFD I I I I I I I I I I I I I I I I I A Flight Director Mode Select Diagram Figure 255 Sheet 7 AO 13SS2 R4 22 ...

Page 548: ... OTHER VERT FD MODE ON CAP ALT SEL CAP h ALTERROR 25 ALT RATE 5 FT SEC PW MOTION ALT SEL KNOB MOTION I GA I PW MOTION ANY OTHER VERT P I F D MODE ON CAP T s Vs o T R CLR il S ALT 0 T R CLR A 1 I I I I I I I I I I Y z w 1 ASCB OUTFUT A 2 TO SYMBOL PROCESSOR GENERATOR TO 4 DISPLAY SELECTED MODE ON PFD 5 I I I I I I I I I I I I I 1 J VERTICAL PITCH MODES AD t3e62 R3 F1ight Director Mode Select Diagra...

Page 549: ...1 ALT SEL ARM Q AL SEL CAP DETECTOR TRIPS ALT sET KNOB R IN MOTION CLR PW IN MOTION ANY OTHER VERT MODE SEL CAP PFD CMD SEL GA FGC IRS MISCOMPARE IRS3WD SOADC V SG FOR COWLED PFD u s i 1 I I I 1 WI BH OJZB 1 ASEL CAP B 2 u s 4 15 d h I I I I I 1 I I b A VERTICAL PITCH MODES Flight Director Mode Select Diagram Figure 255 Sheet 9 AD 13es2 w 22 14 00 Page 298 66 Aug 15 91 Use or disclosure of informa...

Page 550: ...D 5 SEC LOCCAP TRK FGC IRSMISCOMPARE IRS3VALID SDADCW w W l Y vERT DEV RATE 10 m SEC R GA CLR PPDCMOSEL MY OTHER VERT MODE ON CAP 1 I 1 EMOTEGAsw TcH nl ANY OTHER VERT MODE ON AJP 0 4 PFD CMO S5 D R TCS CLR SG VALID FOR COUPLED PFO FGC IRS MISCOMPARE IRS3 soArx i15 VERTfCAIJPITCH MODES F1ight Director Mode Select Diagram Figure 255 Sheet 10 I I I I I I I I I I I I A PROCESSOR 10J1B 10J2B 1 ASCB OU...

Page 551: ...SDADC SWITCH OVER Y I I I I I I s a T R CLR FGC VALID SDADC V 3 SG VALI COUPLED PFD VNAV ARM I I I I I A PROCESSOR t 1 ASCB OUTPUT A 2 TO SYMBOL PROCESSOR GENERATOR TO 4 DISPLAY SELECTED 5 MODE ON PFD I I I I I I I I I L J Awl 3632 R1 Flight Director Mode Select Diagram Figure 255 Sheet 11 22 14 00 Page 298 68 Apr 15 93 Use or disclosure of information on this page is subject to the restrictions o...

Page 552: ...AV MODE I FLCH s 1 VFLCH Q T 1 J R c1 vNAV TARGET VALI D SDABC VALID IRS MISCOMPARE IRS 3 VALID FGC VALID SFMS VALID s SG VALID FOR COUPLED PFD I I I I I I N PROCESSOR 1 ASCB OUTPUT A 2 TO SYMBOL PRCCESSOR GENERATOR TO 4 DISPIAY SELECTED 5 MODE ON PFD I I I I I I I L J AD 13E62 Rl F1ight Director Mode Select Diagram Figure 255 Sheet 12 22 14 00 Page 298 69 Apr 15 93 Use or disclosure of informatio...

Page 553: ...TION PW IN MOTION ANY OTHER VERT P MODE SEL CAP PFD CMD SEL GA FGC VALI IRS MISCOMPARE lRS3 SOADC SG FOR COUPLED PFD OVERSPEED 1 L 0 VERTICAIJPITCH MODES P 6AR0 ALT VASEL F CAP s R CLR I I I I I 1 I I I I I I I I40J1 B l 0J2B 1 ASCB OUTWT 2 A TO SYMBOL PROCESSOR GENERATOR TO 4 OISPIAY SELECTED MOOE ON PFD 5 I I I d F1 ight Director Mode Select Diagram Figure 255 Sheet 13 22 14 00 Page 298 70 Aug 1...

Page 554: ... I SDADC IRS MISCOMPARE IRS 3 Vm 4 I FGCVALID I SFMS I VNAV TARGET V I SG VALID FOR COUPLED PFD BAROALT V I VNAV PUSHBUTTON r Q UALT I I I I I I I I I A PROCESSOR 10JIB 1 W2B t 7 ASCB OLJTPUT A 2 TO SYMBOL PROCESSOR GENERATOR TO 4 DISPIAY SELECTED 5 MODE ON PFD I L J I I I I I I I I I AD 15662 Rl F1ight Director Mode Select Diagram Figure 255 Sheet 14 22 14 00 Page 298 71 Apr 15 93 Use or disclosu...

Page 555: ...OVERSPEED s c T SFMS VERT TARGET VALID SG FOR C PLED PFD VNAV PUSHBUTT 34 GF IRS MISGOMPARE IRS 3 D VPTH I I I I I A PRCCE SXR 1 10J1SW3J2B T 1 ASC8 OUTPUT A 2 TO SYMSC L PRCY2ESSCR GENERATCR TO 4 DISPIAY SELECTED MOOE CN PFD 5 r I I I I I I I I I L J AD 1 3662 Rl F1ight Director Mode Select Diagram Figure 255 Sheet 15 22 14 00 Page 298 72 Apr 15 93 Use or disclosure of information on this page is...

Page 556: ...d activate servo brakes as well as completing the motor drive circuits The servo engage control provides engage status information for use by the servo switching monitors and for transmission on the ASCB When relay K2 is energized the aileron and elevator servo clutches are engaged and the aileron and elevator servo commands are allowed to drive the servo The cross side servo s brakes are applied ...

Page 557: ...ate F autopilot Again servo power enable and processor valid are partitioned between both processors thru AND gates D and E The AP drive enable is output from the B processor only The autopilot cannot be engaged if the weight on wheels or stick shaker discrete inputs into the FGC are active AP engage can be reset by deselecting AP use of the pilot or copilot take off go around TOGA switches the pi...

Page 558: ...output is active the FGC is invalid and will not engage the system should the cross channel FGC fail The servo disconnect output from AND gate H will be active whenever the FGC does not have AP YD and trim engaged As long as this output is not active this FGC is the priority channel and AP YD or trim is engaged The FGC also outputs the AP and YD power valids to the cross channel FGC e ASCB Engage ...

Page 559: ...L c 7 DATA SERIAL OATA OUT F 8 OUT 28 VDC se ANN WRAP AROUND G P DISC r LEVEL SHIFTERS 11 J2 77 C1OJ2B 66 C1OJ2B 54 PILOTS TCS SW cls4JlA l T 14 lIJ1 H SERIAL DATA IN H e COPILOTS TCSSW 2 J2 I I I I I I I P AP ON ANN DRIvER 6 wow 1OJ2B 74 PILOTS C1OJ2B 74 TOGA SW T SIPO I o 0 Q COPILOTS TOGA SW T I 11J2 54 II 28 VDC ANN PWR I I I l Autopilot Engage Logic Diagram Figure 256 Sheet 1 AD 14619 R2 22 1...

Page 560: ...IVE ENAEILE I AILERON SERVO AMPL K 12JI 1 2 21 12 14 1 SM SWDUAL AILERON SERVO PILOTS SERVO ORIVE I BRAKE I CLUTCH ExC I J H o slm c e 28 VDC G ANN WRAPAROUND A PROCESSOR I I I ELEVATOR SERVO AMPL LEvsERvOcMD I ls APROC SERVO PwR ENABLE 49 14BMONITOR A PROC VALID L HB MONITOR B PROC VALID WPROC SERVO FwR ENABLE AP DRIVE ENABLE AP ENG PB TCI T r w 11 CLUTCH 14 ExC I J I I I I I I I I I I I C124J1B ...

Page 561: ...LOTS 1 Y t TlllMSERVO CMO 1 J SERVO DRIVE I I L 2 21 BRAKE I 1 2SJ2 I S3 4 12 CLUTCH 13 Exc I I L I K4 m I r 9 9 FC SBOFWC PILOTS J A 1 L 124J1B 9 1 25 I TRIM CLUTCH I 1 1 I I L J Ao 14s19 Qf Autopi1ot Engage Logic Diagram Figure 256 Sheet 3 22 14 00 Page 298 81 Aug 15 91 Use or disclosure of information on thw page is subject to the restrictions on the title page of this document ...

Page 562: ... the pilot or copilot quick disconnect switch Prior to an FGC forcing itself invalid the FGC writes the fault data into memory This data may be retrieved by accessing the flight fault summary section of the AFGCS test when performing the ground maintenance test The instructions for the ground maintenance test are provided in section 4 Monitor recovery is enabled in all modes except VOR BC LOC trac...

Page 563: ... RE ENGAGED FROM THE PREVIOUSLY SERVOS WILL BE RE ENGAGED ENGAGED CHANNEL FROM FIRST UP CHANNEL DISENGAGE ALL SERVOS i INTERRUPTION I I I b OURATION AO 10157 Power Interruption of Both Channels Figure 257 22 14 00 page 298 83 Aug 15 91 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 564: ...ES NOW ACTIVE SERVOS WILL BE RE ENGAGED FROM FORMERLY IN THE FORMER STANDBY FROM FORMER STANDBY I CHANNEL ENGAGED CHANNEL I CHANNEL WITHIN 100 mSEC I I I I I I INTERRUPTION I I I w DuRATION AD 101 58 Power Interruption of Engaged Channel Only Figure 258 22 14 00 Page 298 84 Aug 15 91 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 565: ...the approach track the AP and YD will disengage and the DADC mismatch will be annunciated on EICAS however flight director modes will be retained A miscompare in approach track mode the flight director mode will remain in approach track APPT however reversion to constant speed gain programming will occur in order to retain operational AP and YD b IRS Comparator The different parameters compared by...

Page 566: ...ate 32 Roll Rate Normal Accel Lateral Accel 0 05 g Avg Delta Accel 32 Fore Aft Accel Heading N A A miscompare condition in the IRS monitor occurs whenever the above parameters deviate greater than the allowed threshold between the IRS monitor and IRS 1 or the IRS monitor and IRS 2 The IRS monitor will set the appropriate discrete to the FGC either IRS 1 miscompare or IRS 2 miscompare The FGC does ...

Page 567: ...elect mode To allow initiation and continuation of the mode the selected PFD data must be valid and the turn knob must be in detent To operate the mode the heading bug on the PFD and ND is positioned around the compass card to the heading the pilot desires to intercept using the heading knob on the GP 820 Flight Guidance Controller The heading select signal from the GP 820 to the FZ 820 Flight Gui...

Page 568: ... will automatically select the high bank angle limit if it is not already selected The low bank angle limit can be reselected by pressing the BANK pushbutton VOR LNAV Mode See Figure 259 sheet 2 The VOR mode provides for automatic intercept capture and tracking of a selected VOR radial utilizing the selected navigation source displayed on the active PFD and ND The navigation source displayed on th...

Page 569: ...course error signal is then sent from the DC 884 Display Controller to the symbol generator and to the FZ 820 through the avionics standard communications bus ASCB Next the course error signal is TAS true airspeed gain programmed TAS gain programming of the course error signal is performed to achieve approximately the same aircraft response for a given command regardless of the aircraft s airspeed...

Page 570: ...gnal This zone of confusion radiates upward from the station in the shape of a truncated cone In this area the radio signal becomes highly erratic and it is desirable to remove it from the roll command The over station sensor monitors for entry into the zone of confusion and opens the 0SS switch removing radio deviation from the roll command From the course cut limiter the VOR SEL command is route...

Page 571: ... course select pointer to align with the bearing pointer and provide for a zero deviation course to be flown to the VOR station Localizer Mode See Figure 259 sheet 3 The localizer mode provides for automatic intercept capture and tracking of the front course localizer beam to line up on the centerline of the runway in use Prior to mode engagement the pilot would perform the following Tune the navi...

Page 572: ... LOC TRACK submodes provide tighter control law programming on the localizer signal to better maintain a truer flightpath along the localizer beam There are no visual indications in the cockpit that these submodes have occurred When the course select pointer was set on the PFD using the course knob on the GP 820 Flight Guidance Controller the course select error signal was established This signal ...

Page 573: ...s 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 From the lateral gain programmer the localizer signal is filtered amplified and summed with the course error signal The resultant localizer command signal is then course cut limited The course cut limiter functions primarily when ...

Page 574: ...d the localizer approach intercept Any other vertical mode in use at this time will a annunciated on the PFD At localizer capture the annunciate to initiate so be PFD wi11 LOC in green and is boxed for 5 seconds to emphasize the capture phase GS in white Any other vertical mode in use at the time The flight guidance computer now generates a roll command to smoothly capture and track the localizer ...

Page 575: ...ected since the aircraft will now be closer to the localizer transmitter by the length of the runway plus 1000 feet At back course capture the flight guidance computer will generate a roll command to smoothly capture and track the back course localizer signal In addition the previous roll mode is cancelled To allow initiation or continuation of the mode the selected PFD and NAV data must be valid ...

Page 576: ...from the IRS through the AP ENG switch As the steering command is satisfied the flight director lateral steering cue is centered on the PFD and the aircraft is now flying the flight director command As the aircraft approaches the selected heading or radio beam center the flight director command diminishes in size and the roll attitude signal predominates This causes the flight director lateral ste...

Page 577: ... and then split into two paths The first path goes up through the activated AP ENG switch the roll bar bias switch and then to the symbol generator The second path routes the steering command to a M degrees position command limiter is gain adjusted and applied to a pulse width command limiter and output servo amplifier The pulse width command limiter serves two functions First it is the D A conver...

Page 578: ...d be identical to that just discussed If the summation of command and roll attitude are not exactly equal the difference between the two signals is sent to the command rate taker The signal is changed to rate and summed with tach generator rate feedback The summing of these two signals is then integrated to obtain position data and summed with the steering command This boost helps eliminate flight...

Page 579: ...sed to initiate the bank maneuver Turn knob is not active The roll hold mode can be used by the pilot to maneuver the aircraft into a bank and utilize the autopilot to hold the bank angle With the roll hold criteria being met roll attitude information from the IRS is entered into the roll hold reference block With the ROLL HOLD switch activated to the up position desired roll attitude is compared ...

Page 580: ...gs Level The go around mode is normally then engages the headi g hold be selected after the TURN position used to transition from an ILS approach to a climb out condition when a missed approach has occurred The pilot selects go around by pressing the TOGA button located on either outboard throttle handle With go around selected all armed and active flight director modes are cancelled and the autop...

Page 581: ...O OEVIATION IF ONE OF THE SIGNALS IS INVALIO AND AVERAG ING IS NOT POSSIBLE THEN THE SYSTEM SWITCHES TO SINGLE SIDE OPERATION USING THE SIGNAL FROM THE VALID SENSOR 2 THE SWITCH NOMENCLATURE CAUSES THE SWITCH TO CHANGE FROM STATE SHOWN P sY OL N TZ 65J I T ASCG OATA 16 17 I ASCB W DATA 1 NOTE 1 ASCB w INTERFACE ROLL ATTITUOE I 3 POLARITY SIGNS AT SUMMATION POINTS DENOTE SIGNAL RELATIONSHIPS HEADIN...

Page 582: ...l usJ1B NAV 41 RECEIVER NO 1 ARINC 42S RADIO DEVN A TA 16 TUNED TO vOR 42 17 24 OME ASCW MTA 16 3s 17 NOTE 1 SHI LATERAL ACCEL 111 l lJt 1 5J2 DGSE4 DISPLAY CONIROLEER M 11 SJV11SJ2 R CRS ASCB A MTA S SELECT E2 g I cm ASCB 0 OATA A SEL 2s g CRS SYNC e KNCM 1 T IRS TRUE TRACK F NA T J II 1 1 II FILTER TIME CONSTANTS vOR TFIK 10 SEC vOR TRR 4 SEC 11s 22 TO CROSS p SIDE OC SS4 Q RAOIO OEVIATK N I L D...

Page 583: ...1 PFIIMARY W OUTPUT 40 mVDc FT N 28 VOC RA VALID V C1W2B 26 27 w laAla la12e 1 z Ef 27 2i l a I I TAS GAIN PROGRAMMER lb i BCmKI CE 450 TO SH 3 Ilti RAOIO OEVIATION TO SH 3 ROLL RATE NOTE 1 KSHIJ l FROM FIG 205 cSH5 GSOEVN R FD Iow NHpRx x _ r AvEIWGEO RADIO ALT I I G nAvALIO 1 I I Cl LATERAL BEAM SENSOR AO 13663 i 73 F1ight Director Autopilot Roll Channel Mode Flow Diagram Figure 259 Sheet 3 22 1...

Page 584: ...selected the PITCH HOLD AP ENG TCS NO VERT F D MODE switch opens This clamps the synchronizer output as a reference for the pitch hold mode As long as the pitch attitude of the aircraft remains unchanged there will be no command to drive the pitch cue on the PFD If the aircraft deviates from the reference attitude established at mode engagement an error signal corresponding to the difference betwe...

Page 585: ...de The reference vertical speed may be changed by use of the VERT SPEED knob or by pressing the TCS button on the control wheel and maneuvering the aircraft to a new vertical speed reference and then releasing the TCS button Prior to mode engagement altitude rate VS information provided by the AZ 81O DADC through the ASCB is fed to a summing point where it is compared to selected vertical speed Sh...

Page 586: ... Automatic Mode The displayed speed target is input from the selected FMS which also controls the IAS Mach display format Manual Mode Manual mode speed intervention is selectable via the SPD pushbutton on the GP 820 The IAS Mach display format will not change when this mode is selected but the speed target will be synched to present speed In this mode the SPD button will be annunciated MAN and the...

Page 587: ...lected on the GP 820 when aircraft thrust is set appropriately for climb or descent When the power is not set appropriately then the AFCS should maintain zero vertical speed in order to not fly away from the preselected altitude If the target speed is changed from IAS to MACH or vice versa the FLCH or VFLCH mode should remain engaged and fly to the appropriate new speed target The DAFCS pitch guid...

Page 588: ...ual aircraft speed is at or above the FMS initialized climb Mach the PFDs will also automatically switch from a CAS to a MACH tape Conversely the FLCH mode will also automatically switch from MACH to IAS mode during a descent when the actual aircraft speed is at or above the FMS initialized descent CAS the PFDs will also automatically switch from a MACH to a CAS tape The pilot can change this auto...

Page 589: ... discussed in paragraph 3 B 8 i The FMS and air data information is used from the same side FMS and DADC as are selected for display on the in command side PFD If FMS is not selected for display the DAFCS selects the FMS on the same side as the PFD in command VNAV Path VPATH Mode See Figure 260 sheet 3 The VPATH mode is used to descend to a new flight level at a prescribed angle 1 to 6 degrees Act...

Page 590: ...T or VALT modes is automatic after either an altitude preselect capture ASEL or VNAV altitude preselect capture VASEL In the ALT or VALT mode all armed pitch F D modes are allowed but a capture of any armed pitch mode will override the ALT or VALT mode To allow the initiation or the continuation of the mode the selected DADC must be valid ALT and VALT modes are vertical axis flight director modes ...

Page 591: ...tude command and IVV signals are then TAS gain programmed to achieve approximately the same aircraft response regardless of the aircraft s airspeed and altitude The altitude command signal is routed to Figure 260 sheet 7 and is processed as discussed in paragraph 3 B 8 i 3 B 8 f Altitude Preselect ASEL and VNAV Altitude Preselect VASEL Modes Figure 260 sheet 5 The ASEL and VASEL modes are automati...

Page 592: ...is a predetermined software program Commanded altitude rate is then compared against actual altitude rate to determine the altitude capture point For the capture detector to trip the following must be true Selected DADC valid ASEL or VASEL mode is armed The ALT set knob is not being turned SLEW The pitch wheel is not in motion PW MOTION In the capture detector if commanded altitude rate is greater...

Page 593: ...r VASEL CMD signal is TAS gain programmed and routed to Figure 260 sheet 7 and is processed as discussed in paragraph 3 B 8 i Glideslope APP Mode See Figure 260 sheet 6 The glideslope mode is used for the automatic intercept capture and tracking of the glideslope beam The beam is used to guide the aircraft down to the runway in a linear descent Typical glideslope beam angles vary between 2 and 3 d...

Page 594: ...ideslope signal to compensate for the aircraft closing on the glideslope transmitter and beam convergence caused by the directional properties of the glideslope antenna Glideslope programming is normally accomplished as a function of radio altitude and vertical speed The radio altitude signal is rate limited summed with vertical speed and limited again before gain programming the glideslope signal...

Page 595: ...d copilot PFD Initiation of this flight segment of the approach phase is automatic and occurs at 1200 feet radio altitude as shown in Figure 259 1 The dual couple mode requires all the following conditions to be satisfied Pilot PFD NAV source must be NAV 1 or ILS 1 Copilot PFD NAV source must be NAV 2 or ILS 2 LOC GS track mode Radio altitude less than 1200 feet Both NAV 1 and NAV 2 sources are va...

Page 596: ...m NAV 2 If NAV 1 becomes valid the dual couple mode will automatically return NAV 2 Fails Copilot PFD command bars are removed and the PFD CMD reverts to L Approach mode continues using data from NAV 1 If NAV 2 becomes valid the dual CPL mode will automatically return Unflagged Miscompare Between NAV 1 and NAV 2 The system will automatically select the NAV source with the smallest deviation must b...

Page 597: ... following Rate Limiter Limiter Go Around Switch AP Engage Switch Pitch Bar Bias Switch The command is then routed to the symbol generators on the ASCB Pitch bar bias PBB is a fixed voltage level used to bias the vertical flight director command bar out of view to prevent the pilot from flying invalid data The vertical command bar is biased out of view if No flight director mode is selected The fl...

Page 598: ...or the servo amplifier Second as a motor driver it issues a continuous string of 28 V dc pulses at a rate of one pulse approximately every two milliseconds The pulse width of the pulses is determined by the vertical command The pulse width command limiter has its current limits established by a software program contained in the B CPU The output of the servo amplifier is sent to the SM 600 elevator...

Page 599: ...L FD MODE SELECTED switch to a synchronizer The output of the synchronizer is inverted and summed with pitch attitude to give a zero output from the summing point If the autopilot is engaged and no vertical flight director mode is selected the synchronizer switch opens clamping the synchronizer with the reference pitch attitude at the time of autopilot engagement Should the aircraft deviate from t...

Page 600: ...trol trim tab motion via digitally processed closed loop control laws which utilize motor rate tachometer and motor position synchro feedbacks Each FGC provides excitation for its own side trim synchro Trim servo travel is limited such that the trim servo does not drive into the mechanical stops by use of the trim limit switches in the trim servo bracket The manual trim wheel can be used to overri...

Page 601: ...l not drive The DAFCS monitors the pilot s and copilot s trim switch pairs for disagreements and provides individual trim switch caution flags via ASCB to the EDS system for crew alerting The electric trim rate is gain programmed as a function of true airspeed This data shall be received via ASCB from the DADCS This trim rate programming is a factor when the autopilot is engaged autotrim and when ...

Page 602: ...ot manual trim switches the Mach trim position reference is synched to position and the Mach trim control law remains manual trim switch is released The Mach trim continues to synch for a short time afterward allow the trim motor to coast to a stop This same as are act present off unt control n order Drevent at ve 1 the 1aw to the Mach trim from causing the trim to back up following a manual trim ...

Page 603: ... SSJ2B ASCB A DATA 16 17 ASCB DATA 16 17 MIDDLE MARKER GLIDE SLOPE DEVIATION FMS PRESLECT ALTITUDE FMS CMD VS IF ONE OF THE SIGNALS IS INVALID AND AVERAG ING IS NOT POSSIBLE THEN THE SY3TEM Ed SWITCHES TO SINGLE SIDE OPERATION USING THE SIGNAL FROM THE VALID SENSOR I NOTE 1 2 THE SWITCH NOMENCLATURE CAUSES THE SWITCH TO CHANGE FROM STATE SHOWN 3 POLARITY SIGNS AT SUMMATION POINTS DENOTE SIGNAL REL...

Page 604: ...ED MODE 29 FLIGHT GUIDANCE COMPUTEF SELECTED VEI T SPEED 7 Vs m w TO SH F TO H2 T0sH2 TO SH2 LONG TcUE lNAL e 1 ALT RATE NOTE 1 ISHI NOTE ALT RATE 1 LIMIT TO SH7 I J A NOTE SELECTED VERT SPEED IS SYNCHRONIZED TO EXISTING VERT SPEED UPON MODE ENGAGEMENT OR RELEASE OF TCS I TO SI 2 AO IW R4 F1ight Director Autopi 1ot Pitch Channel Mode F1ow Diagram Figure 260 Sheet 2 22 14 00 Page 298 129 298 130 Au...

Page 605: ...ATE CONVERTER 10 SH7 l 11 0 SH3 NOTE 1 SH1 r IRS I I M 14 ASCS A OATA 5 12 ASCB B OATA 13 L F AS SW PITCH RATE TAS AIRSPEECV MACH RR l r r SG S94SVMSOLGENERATOR T SsJ 1 ASC8 A OATA 16 17 I ASCB B OATA 1 CdTi i ASCB W INTERFACE I l m A A r GP S20 FLIGHT 1 GUIDANCECONTROLLER 1 m I I lxt 1 IASIMACH SPEED TACH KNOS 1 GEN L d VPATH VFLCH AND FLCH MOOES __ AD13 sw F1ight Director Autopilot Pitch Channel...

Page 606: ...GENERATOR 6SJ1N6 J2B I c ASCB A OATA 17 6 I h ASCS W OATA e 1 16 17 I v C A TO Sli9 TosH7 t I J ASCO 0 TA i FILTER TIME CONSTANT ALT HOLD 125 SEC r 1 L cEE NORMAL CC TAS ALTITUDE PITCH ATTITUDE NOTE 1 Sli 1 TAS I I I L J PITCH WASHOUT ALTITUDE NOLD ANO VNAV ALTKUDE HOLO MODES L _ F1ight Director Autopi 1ot Pitch Channel Mode Flow Diagram Figure 260 Sheet 4 22 14 00 Page 298 133 298 134 Aug 15 91 U...

Page 607: ... SH9 ASCB B H I I 1 Asca e INTERFN2E t I I I I I I L 1 NOTE 1 ISH 1 ___ __ ALT SEL CAP TAS G LIMITER I PROGRAMMER m fps I TO SH7 r 1 I TAS G LIMITER I I I NOTE L I 1 l i I I I I L 1 I PITCH WASHOUT d l FLARE I COMPUTATION I 3 ALT CONSTRAINT ALTITuDE ALT SEL ARM ALTITUOE 1 RATE COMMANO ALT SEL SMALLEST ALT ERROR FROM LOOKUP BETWEEN WJAV TABLE PRESELECT ALT OADC VALID ALT CONSTRAINT COMPARATOR PW MO...

Page 608: ...MM PASSED 250 FT I I l C1OJ2A 37 38 r L IIT 300 RADIO ALTIMETER 2UJ1 I PRIMAFW 7 w OUTPUT m 40 mVOC FT N I w 28VOC RAVALIO Y rl A o J n 1 I I 1 L Y I r RT 300 RADIO I I ALTIMETER C20J1 10J2A PF IMARY OUTPUT 7 w b 36 40 mVOC FT N m 37 28 vOC RA VALID 38 d L C1OJ2B 26 27 26 L 1 GS DEVN BEAM FILTER RATE 2 SECS LIMITER pRF2 ER FT0sH7 L L ___ _ GLIDESLOPE MODE u AO 13664 F13 F1ight Director Autopilot P...

Page 609: ...rue airspeed roll attitude and lateral acceleration combine to provide turn coordination The remaining inputs to the processor are secondary and aid in further optimizing yaw control The yaw axis may be engaged by pressing the YD pushbutton on the aircraft control panel The yaw axis is disengaged by also pressing the same YD button The yaw axis will automatically be engaged when the autopilot is e...

Page 610: ...t As the actuator drives the ball screw the LVDT is moved and provides an output that equates to commanded rudder position This signal is routed to the FZ 820 where it is demodulated and then follows two paths The first path is through a rate taker where the position signal is converted to rate of position change This signal is utilized as a damping term to minimize excessive rudder travel The sec...

Page 611: ...0 1S AVERAGED TOGETHER TO PROVIOE THE sELECTED SIOE WITH THE APPLICABLE OUTPUTS INDICATED IF ONE OF THE SIGNALS IS INVALIO AND AVERAGING IS NOT POSSIBLE THEN THE SYSTEM SWITCHES TO SINGLE SIOE OPERATION uSING THE SIGNAL FROM THE VALID SENSOR THE SWITCH NOMENCLATURE CAUSES THE SWITCH TO CHANGE FROM STATE SHOWN POLARITY SIGNS AT SUMMATION POINTS DENOTE SIGNAL RELATIoNSHIPS NOTE 1 AO 13665 I R2 22 14...

Page 612: ...AGE x ERTEA HYDRAULIC ACTUATOR PITCH ATTITUDE C1O I1A FROM g SIDE 62 H FGC 64 G 7 LATERAL ACCEL i M J I il I I I I I 9 RATE TAKER 10V 2kHz SOUARE WAVE EXC POSITION FDBK LIMITER k I I I I ENGAGE I SOLENOIO I 31 El RELAY 28 VDC SWITCHED SEE FIG 203 I J AUTOPILOT YAW AXIS AO 3665 2 14 F1ight Director Autopilot Yaw Channel Mode Flow Diagram Figure 261 Sheet 2 22 14 00 Page 298 147 298 148 Apr 15 93 Us...

Page 613: ...It also provides an important output display for the navigation and performance computers The CDU utilizes a full alphanumeric keyboard with four line selection keys on either side of the CRT Several function keys are provided to allow direct access to specific display pages Annunciators are built into the top of the unit to advise the pilot of the system s status The CDU sends ASCII characters si...

Page 614: ...throttles Previously detailed performance information was only available by spending a great deal of time in the aircraft performance manuals With the performance functions of the PZ 800 the pilot now has access to a computerized performance manual The pilot is supplied with flight planning information prior to takeoff such as fuel and time required In flight the system provides the pilot with rea...

Page 615: ...0 J RS422 CD 81O I I AD 30609 Rl Flight Management System FMS Architecture Figure 262 22 14 00 Page 298 151 Apr 15 93 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 616: ... order for the NZ 920 to use its data AZ 81O Digital Air Data Computer DADC ASCB Inputs The NZ 920 inputs both left and right side DADC data from the ASCB Selection of DADC data is performed by the navigation and guidance LNAV and VNAV subsystems of the NZ 920 The navigation subsystem selects and uses its on side DADC data if valid Otherwise it will switch to the off side DADC and use that data if...

Page 617: ...ECONDARY ASCO H SECONDARY BUS L la 1s ISG NO 2 H ARINC 429 RCVR L DME PRIMARY I ARINC 429 RCVR DME SECONOARY L DME NO 2 I I SG NO 3 1 I l G ARltW 429 RCVR LTS NO 1 L I FC NO 2 t I b z VLF OMEGA 24 H ARINC 429 RCVR L LTS NO 2 I FZ NO 1 1 H ARINC 429 RCVR L LTS NO 3 11 1 Q31 PZ NO 1 c121JiB 54 J r C121J1 AB 1 I wok NZ 920 NAVIGATfON 1 COMPUTER NO 2 TAG SYNC IN I CDU SYNC IN TAG SYNC OUT I CDU SYNC M...

Page 618: ...e nonpriority NZ 920 is displayed Guidance continues to select the EFIS selected DADC regardless of DADC validity If the selected DADC is invalid guidance is set invalid If the nonpriority NZ 920 is not displayed it defaults to its on side DADC if valid If default DADC is invalid the NZ 920 switches and uses the other remaining DADC if valid If both DADCS are invalid guidance is set invalid The no...

Page 619: ...Inputs The NZ 920 inputs and processes on side display controller data FC 880 Fault Warning Computer FWC ASCB Inputs The NZ 920 inputs both left and right FWC data b NZ 920 Navigation Computer ASCB Outputs The NZ 920 transmits two types of data onto the ASCB basic data and background data 2 RS 422 Synchronous Interface This RS 422 interface is a synchronous serial digital data bus Data is transmit...

Page 620: ... either binary binary coded decimal BCD or discrete formats The least significant bit and least significant character of each word are transmitted first Also the least significant bit of the word is the most significant bit of the label and the label is transmitted ahead of the data in each case The label is used to identify the data within the word The bus transmits at either a 100 kHz high speed...

Page 621: ...0 4096 18 h32768 Refer to Table 207 15 128 17 0 131072 Refer to Table 207 0 1 0 1 1 0 0 1 0 0625 0 00000048 0 00000095 0 125 0 0000305 1 0 0 00391 1 0 0 125 0 004 1 0 kHz MHz MHz OEG MIN OEG MIN DEG HR MIN KNOTS oEG 180 oEG 180 KNOTS 0EG1180 KNOTS DEG1180 MIN NM NM FEET N E ALWAYS POS N FROM O E FROM O CW FROM N CW FROM N TO DEST FLY LEFT Update Rate SPS NOTE1 NOTE1 NOTE1 NOTE1 NOTE1 NOTE2 NOTE2 N...

Page 622: ...lect Station 12 JXN Norway VLF 13 GOD Anthorne VLF NAU Puerto Rico VLF A Norway Omega 16 B Liberia Omega 17 C Hawaii Omega 18 D Dakota Omega E Reunion Omega F Argentina Omega 21 G Australia Omega 22 H JaDan Omeaa NWt NDT 25 GBR NAA NPM 28 NSS 29 NLK Austral a VLF Japan VLF Great Britain VLF I Maine VLF Hawaii VLF Annapolis VLF Washington VLF Output Word Formats Table 207 22 14 00 Page 298 159 Aug ...

Page 623: ...87 6543210987654321 P SSM c N M o T F A w 10111101 I P Odd Parity SSM 00 valid c N M o 01 invalid CDI Flag id Mag True North 1 True O Magnetic Message Alert 1 Message O No Message Lateral Offset 1 Offset O No Offset T F To From From or To 10 From 11 Invalid A Approach Mode 1 Approach O No Approach W Waypoint Alert 1 Waypoint Alert O Waypoint Alert Output Word Formats Table 207 cent 22 14 00 Page 2...

Page 624: ...data loader is connected to NAV computer No 1 a ground is applied to 121J1B 83 from 123J1 E If the data loader is connected to NAV computer No 2 a ground to C121J1B 83 is applied from 123J1 D Pin 123JI F is connected if a third warm spare NAV computer is installed 6 Navigation Modes The navigation computer develops a position based on a blend or mix of the sensors The navigation modes are listed b...

Page 625: ... 42s us I Cl 21JlA NZ42D NAV COMPUTER NO 2 1 II II F 77 L SOO 900 DATA LOADE 1 1 J cl l CD O1OCDU NO 2 1 1 FATA US OUT H xMTR W 32 m Lr CNTL N J3 v C U vALID Im i L C121J1A C r 0 es 1 M ATA o l 52 N I I I I I I II pil u RcvR cm ICDU VALIO NOI LOAO LEFT E i LOAD RIGNT o 23 OATA LOAOER CONNECTED 1 102 Am ENABLE L m DATA Q lJ I I I I L J Global DMU AFIS and DL 800 900 Data Loader Interconnects Figure...

Page 626: ...Z 9101 software are 18 0 nautical miles NMI oceanic 4 3 NMI enroute 2 6 NMI terminal area and 0 4 NMI on approach increased to 0 7 NMIwhen using VOR DME updating When the FMS is in radio updating VOR DME or DME DME the average GPS and radio positions are equally weighted in deriving the FMS position Thus in radio updating the FMS position could deviate a maximum 1 2 the above listed tolerances due...

Page 627: ...e configuration of a single FMS system or a default mode when two systems in a duplex installation are not communicating with the offside FMS Some installations have three 3 FMS systems installed However the third FMS interfaces with the total integrated system as a hot spare The FMS will operate in dual or initiated transfer modes only when the following criteria are met Both systems must have th...

Page 628: ...e calculations are based on the data entered during performance initialization Following takeoff the performance planning function updates the fuel and time calculations to reflect actual conditions and changes that the pilot may enter Display of performance planning information includes predicted fuel remaining and estimated time enroute ETE at each waypoint Performance planning for a stored flig...

Page 629: ...iguration comparison logic is active The configuration comparison logic continuously compares the initialized configuration for bleed air ground spoilers anti skid and flap position against the actual aircraft configuration Barometric altitude pressure altitude and outside air temperature are also continuously compared against the initialized conditions If the initialized configuration does not ma...

Page 630: ... While in the cruise mode the performance function calculates speed and recommended power settings The autothrottle controls speed of the aircraft Altitude is flown by the flight control system on the elevator The following parameters are calculated and or displayed on the CDU cruise pages for the active cruise modes Cruise altitude c Optimum altitude Step altitude based on initialized step alt c ...

Page 631: ...non UK CAA Target threshold speeds VatO dry UK CAA wet speed Vref 1 3 V stall and Vatl UK CAA only s Maximum threshold speeds all engine and single engine UK CAA only Dry runway landing field length non UK CAA Wet runway landing field length non UK CAA Data are computed for weights greater than the certified maximum landing gross weight but these data are accompanied with a message denoting exceed...

Page 632: ...e with the associated calculations being performed The following information is available while operating with both engines for fixed altitude cruise and for cruise climb Single engine cruise altitude Single engine drift up down speed Active average flight plan ground range and time to reserve fuel Active average flight plan ground range and time to zero fuel J WtlAT IF Mode The WHAT IF mode is us...

Page 633: ...o reserve Current fuel remaining Cruise pages under WHAT IF conditions 4 C 1 k Stored Flight Plan Data Performance data can be calculated for a stored flight plan The performance initialization inputs may be changed to reflect the expected conditions for the flight The default initialization values are the currently active values except for fuel weight The following is calculated and or displayed ...

Page 634: ...d If there is only one valid flap setting that flap setting is received and marked valid FGC data comes from the priority FGC provided the data is valid If both FGCS are high priority or both are low priority the FGC is considered invalid The performance computer receives the PFD selected DC 884 Display Controller DC if valid If the selected DC is invalid the other side DC is read If the PFD selec...

Page 635: ...is considered invalid for a given channel of a DAU for 400 milliseconds then the data from the other channel will be used Fuel quantity has no validity so a simple range and rate test is performed For the range check the minimum quantity is O lb and the maximum is 16 500 lb for each DAU We would expect the performance computer to continue to operate properly with these values since they are valid ...

Page 636: ... selection Other autothrottle functions such as maximum operating speed VN MO protection flap placard protection extended landing gear lmits engine limit protection and minimum thrust control are performed in parallel with the basic modes The autothrottle also provides engine low rotor speed N1 or high rotor speed N2 synchronization in speed hold mode as a function of pilot selection The only vali...

Page 637: ... depowered until the aircraft has climbed to at least 400 feet above lift off altitude see Figure 264 1 An indication of the throttle hold condition is displayed to the pilot At 400 feet the servos are repowered after a positive pilot action required is made indicating a transition from takeoff or if the flight director captures the selected altitude This action will be the selection of a flight g...

Page 638: ... provided as a function of cockpit inputs If the FGC is in flight level change mode the autothrottle decreases thrust as necessary to provide the autopilot with the energy required to accomplish the FLC descent If the descent is being made with vertical navigation VNAV guidance minimum thrust control is provided f Approach When the FGC is in glideslope path or vertical speed mode during approach t...

Page 639: ...MAINTAINS SPEED AND LIMITS EPR TO RATING SELECTED AUTO CLB OR GA PITCH HOLD MODE NOTE 3 I NOTES 1 WHEN IN HOLD MODE THE AUTOTHROITLE DOES NOT CORRECT FOR ANY CHANGES IN EPR 2 TO MODE CAN BE CANCELLED BY SELECTING ANOTHER VERTICAL FLIGHT DIRECTOR MODE OR AUTOMATICALLY BY CAPTURING ASEL 3 ENGAGING THE A P WHEN IN TO MODE WILL CHANGE THE VERTICAL MODE TO PITCH HOLD AND AUTO EPR RATING TO GA SELECTING...

Page 640: ...ottle Rate Limit 7 pLA SECOND FLCH PLA PLA Setting 2 PLA DESCENT Power Lever Angle TAKEOFF EPR EPR Control Range 0 85 to 2 0 EPR TO EPR Hold Error ol EpR Throttle Control 2 to 39 5 PLA Authority Throttle Rate Limit lo pLA SECOND GO AROUND EPR EPR Control Range 0 85to 2 0 EPR GA EPR Hold Error oool EpR Throttle Control 2 to39 5 PLA Authority Throttle Rate Limit f7 pLA SECOND Autothrottle Performanc...

Page 641: ...lect altitude EPR rating not selected LP Nl split of 20 percent Bleed air isolation valve open Engine out HP N2 41 percent NOTE This message will not be active unless the A T ARM mode is selected AT NOT IN HOLD No Message appears with A T engaged in TO mode when CAS is greater than 60 knots and the HOLD mode is not active Message automat ically cancels when RAD ALT is greater than 400 ft AGL Advis...

Page 642: ...directly affect autothrottle operation Engage disengage positive disconnect and takeoff go around switches are located on the throttles The positive disconnect switch provides a direct to hardware means for disengaging the autothrottle servos The takeoff go around button is used to select takeoff on the ground or go around mode in the air Engine synchronization switches overhead panel select engin...

Page 643: ...t enables the autothrottle system by pressing the arm button on the flight guidance controller Takeoff mode is selected by pressing the takeoff go around button on either throttle Once the aircraft has been cleared for takeoff the pilot moves the throttles above a minimum engine pressure ratio EPR threshold and engages the autothrottle Throttles are automatically advanced to the required engine po...

Page 644: ...sition to Altitude Climb Capture airspeed control capture 6 Cruise Altitude Airspeed control Altitude Hold hold 7 Top of Flight Level Transition to minimum Airspeed Descent Change thrust control 8 Descent Flight Level Maitiln minimum Airspeed Change thrust oontrol 9 Approach Glideslope Airspeed control Glideslope Track Proteot flap gear track limits 10 Landing NIA D engage Disengage 11 Go Around G...

Page 645: ...he autothrottle is unable to achieve the desired airspeed without exceeding engine limits a power limit message is displayed to the pilot c Cruise As the airplane nears the selected cruise altitude the AFCS automatically initiates an altitude capture and the autothrottle smoothly transitions to controlling airspeed Control laws have been developed to give a smooth transition with good speed contro...

Page 646: ...ars the destination the speed target is automatically set to 10 knots below the limit for 10 degrees of flaps When the pilot selects the 10 degree flap position the speed target is set to allow 20 degrees of flaps As the approach progresses the speed target is reduced until it is set to Vref 10 knots for final approach The autothrottle is designed to accurately control airspeed without excessive t...

Page 647: ... Drovided whenever the system is ot eratinain the automatic FM speed selection mode In this mode set by the PZ 800 Performance Computer and drop below Vref c Engine Limit Protection he speed command is is never allowed to The autothrottle uses the selected EPR rating as an upper limit for control in all modes of operation Automatic rating selection is available where the PZ 800 Performance Compute...

Page 648: ... each power lever Autothrottle A T ARM Button This pushbutton is located on the GP 820 and is used to arm disarm the engage disengage switches on the power levers This button must be armed before the A T recognizes any activation from the throttle mounted switches Autothrottle Engage Disengage A T ENG DISENG Switches Each power lever handle has an A T ENG DISENG switch located on the under side of...

Page 649: ...GP 820 Flight Guidance Controller A speed target is displayed in the GP 820 speed window for speed mode only An EPR limit rating has been selected MAN or AUTO for display on the DC 884 Display Controller Bleed air isolation valve must be CLOSED N1 cannot be split by more than 20 No engine out condition N2 41 Valid preselector 22 14 00 Page 298 186 Aug 15 91 Use or disclosure of information on this...

Page 650: ...provides a signal to the tone generator for manual and automatic A T disconnects Additionally an A T OFF light is annunciated for each disengagement The light is active for 1 second on a pilot activated disconnect and flashes steady for any automatic disconnect The steady annunciation can be cancelled by engaging the A T or depressing the A T DISC switch on either power lever In the event of failu...

Page 651: ... RECWIRED COMPCNENIS VAUO II 1 DISCOmNECT DISG ECT SWITCH SWITCH I I SAJIA S3 I I C124JIA 63 LOCATED ON LOCATED ON LEFT THROTTLE RIGHT THR03TLE rPZ400 COPILOTS I PRltAARY ASCB I 1 I SECCN DARYASCB 1 12211 A 33 34 81 49 46 59 B 4 5 9 9 I 1 TO FIG 266 I I I I I I AIT ENGAGEDGNI I A T ENGAG I CROSS SIDE AIT ENGAGE LEFTIIUGHT SELEC L L F SOURCE ON R G SOURCE ON I ALTITUDEPRESELECT VALVESCLOSED NT EN3A...

Page 652: ...reen in the PFD vertical mode window and in white in the PFD autothrottle mode window Takeoff is captured following ARM by Advancing both power levers above 1 17 EPR Selecting A T ENG with either power lever mounted ENG DISENG switches The white TO annunciation in the autothrottle window changes to green and is boxed for 5 seconds Autothrottle Hold Mode The hold mode is automatic during takeoff Th...

Page 653: ... I I I I ASCB INTERFACE K I I 1 r I c T 10 ARM L i ROMF GTJ Rm 4 I I SPEED TGT SPEED VC DE ONLY FLAPS VALID 1 MAN OVERRIDE AT DISC R AT ENG PB c CROSS SIDE AT SEL DADCE DAU lx FGC DAU 2 AT N1 SPLIT 2U EPR LIMIT N2 41 LSOVALVE OPEN 400 FT AGL I FDMODE AP ENG Autothrottle Arm Takeoff and Hold Mode Select Diagram b ___ ____ J AD 30613 Rl Figure 268 22 14 00 Page 298 193 298 194 Apr 15 93 Use Dr discl...

Page 654: ... in a flight level change FLCH mode IAS MACH VIAS VMACH This mode is annunciated as FLCH in green in the PFD autothrottle mode annunciation window In this mode the autothrottle is setting power a target for the climb or descent which is normally full climb power or idle as appropriate If the amount of climb is less than 6000 feet at low altitudes the autothrottle sets less than full climb power Th...

Page 655: ...GP 820 Flight Guidance Controller This mode is annunciated in green as IAS or MACH depending on the speed target Autothrottle Go Around Mode The go around mode is used to rapidly advance and set go around power This mode is selected by A T is engaged Select flight director GA mode with TOGA switch on either power lever GA is annunciated in green in the PFD vertical mode window and in green in the ...

Page 656: ... data A T Fail FGC 1 and 2 Fail G DADC 1 or DADC 2 DClorDC2 IRS 1 or IRS 2 OAT 70 C 80 C for 910 PZ Bleed air isolation valve open Speed target invalid speed hold mode only An autothrottle limit mode will drop the current autothrottle mode but will not disconnect the autothrottles d Manual Override If during autothrottle operation the pilot manually moves either of the power levers the A T autothr...

Page 657: ...FO VERTICAL MODES AT ARM PB I AT DISC AT DISC MAN OVERRIDE 3 II CROSS SIDE AT SEL AT ENG PE c I 4 IAS MACH GA 3 AT LIMIT MODE FGC VALID ISO VALVE OPEN AT VALID EPR LIMIT OAT 70 C SO C 91OPZ N 1 SPLIT 20 N2 41 DAU 1 DAU 2 DAOC lRS D DC PLAPS D I SPEED TARGET AT ENG w6w IPEED K LD AS OR MACH GO AROUND T Q R c t I I I I I I I I I I I I I I I I I I I I I I I I I I I I J AD 30614 RIU Autothrottle Fligh...

Page 658: ...nsitions are shown boxed for 5 seconds A T Priority Description The autothrottle system uses two identical performance computers Only one computer is active at any one time The pilot can manually select A T 1 or A T 2 through the display controller sensor page This selection can be made on either the pilot or copilot display controller both controllers always show the same A T selection Full syste...

Page 659: ...equalize EPR when in the autothrottle FLCH TO or GA modes Table 210 lists how engine synchronization is performed by the autothrottles Flight Director Autothrottle Parameter System Providing Mode Mode Sync ed Sync Function N A Not Engaged LP or HP Aircraft System DESCENT IAS MACH 2 DEG PLA VIAS VMACH FLCH CLIMB Autothrottle EPR I TO I TO I EPR I Autothrottl e I I GA I GA I EPR I Autothrottle I ALT...

Page 660: ...nded while smaller altitude changes result in an EPR command which is proportional to the size of the climb increment During FLCH descents a minimum thrust level is commanded When FLCH mode is initiated the FLCH EPR command processor smoothly adjusts EPR command to the appropriate level This gradual change in commanded thrust minimizes the effect on autopilot speed control The required EPR is main...

Page 661: ... L 2 Awe e t A ALTITUDE COMMANO TO SHEET 2 nnll I 1 1111 MOOE SELECTION LOGIC J f 1 TO TO TO TO TO TO TO TO TO TO TO TO TO SHEET 3 SHEET 2 SHEET 2 SHEET 2 SHEET 2 SHEET 2 SHEET 2 SHEET 2 SHEET 2 SHEET 2 SHEET 2 SHEET 2 SHEET 2 lil ENGINEPRESSURE RATIO ACCELERATION SPEEO k F L A I SELECTED Alf r a4TATF tlli 1136J1 I AB ACQUISITION UNIT PRIMARY ASC 4 H 4 I L 6 I SECONDARY ASC FLI 3HT PATH ANGLE L A ...

Page 662: ...NGE PLA COMMAND SPEED COMPLIMENTARY FILTER 4 LEFT OR RIGHT EPR SPEED HOLD PLA SPEED v SELECTED AIRSPEED ERROR COMMAND COMMAND K PROCESSOR s ENGINE PRESSURE RATIO PRIMARY EPR EPR RATE LEFT OR RIGHT COMMAND TAKEOFFIGO AROUND PLA COMMAND I I I L MODE SELECTION LOGIC II ENGINE PRESSURE RATIO d ATE EON ATE I TAKER TAKER L ___ _ J AD xM15 RI I I I Autothrottle Mode F1OW Diagram Figure 270 Sheet 2 22 14 ...

Page 663: ...LIMIT 28 V SERVO CLUTCH DRIVE NO 2 A 15 16 23 17 18 24 B 59 58 60 61 11 C122J1 B 59 L128P1 K C122J1A 61 A D B c E F G QTACH I I I CLUTCH I I LEFT THROTTLE HANDLE I 7 I a I a L 1 4 Autothrottle Mode Flow Diagram Figure 270 Sheet 3 22 14 00 E A I F I I G I L J AD 30615 Page 298 209 298 210 Aug 15 91 Use or d scloswe of Inlormal on on this page IS subject 10 the restrlct ons on the title page 01 this...

Page 664: ...uvers The EPR rate command is then integrated and bounded by engine limits to determine the commanded EPR level The closed EPR inner loop provides an increased degree of stability and accuracy to the autothrottle system during speed hold operation This loop is configured similar to the FLCH control The resulting throttle rate command is proportional to EPR error 4 D Target Speeds 1 Automatic Speed...

Page 665: ...altitude limit is entered the speed target is set to climb speed after passing the limiting altitude During climb the speed target is the climb speed schedule selected during initialization and the transition to MACH is accomplished automatically This speed schedule is observed during any intermediate level off The speed target is changed to the cruise speed as the autopilot transitions to ASELor ...

Page 666: ...r is set below the limiting altitude c When the aircraft is within 20 NM flight plan distance from the destination and less than 10 000 feet above the destination elevation the speed target is changed to the placard speed for 10 degree flaps minus 10 knots This allows for the pilot to start extending the flaps when required As the gear and flaps are extended the speed target is changed to the plac...

Page 667: ... altitude is reached the flight phase stays in cruise until another climb or the descent is started A climb or descent is recognized by an ASEL ARM towards a new preselected altitude If a climb is initiated a newTOC altitude is placed at the preselector but if a descent is started the cruise altitude does not change There are two sub phases to the cruise phase called cruise climb and cruise descen...

Page 668: ...b to Cruise Phase Figure 270 3 TOC CRUISE CRUISE xK AN CRUISE DESCENT CRUISE CLIMB ABOVE 15 000 FT AD 31 731 Cruise Climb and Cruise Descent Subphase Figure 270 4 22 14 00 Page 298 214 1 Apr 15 93 Use or disclosure of information on this page is subject to the restrictions on the title page of this document ...

Page 669: ...if a climb is initiated see Figure 270 7 If a missed approach is executed see Figure 270 8 the flight phase transitions to climb A new cruise altitude is defined at the preselector altitude and a short cruise segment will be flown before flight phase transitions to descent The Auto EPR Rating Transitions The auto EPR rating is set to TO on the ground FLEX is also boxed if selected on the TAKEOFF I...

Page 670: ...or cruise climbs then the phase becomes CLB When the flight phase is descent the auto EPR rating stays with CRZ except when the gear comes down for approach The auto EPR then changes to GA Whenever the FGC GA mode is selected the auto EPR rating will go to GA If an engine failure occurs the auto EPR rating goes to MCT provided the rating was not TO or GA when the engine failure occurred Upon landi...

Page 671: ... are displayed in large characters unless a descent angle has been manually entered in which case the speed constraint is in small characters above the angle and altitude entry b Climb speed constraints are observed until reaching the constraining waypoint 22 14 00 Page 298 214 4 Apr 15 93 Useor disclosure of information on this page issubject to the restrictions on the title page of this document...

Page 672: ...e the current speed may be latched as the speed target For example when flying a path with the preselector set lower than the last altitude constraint as the aircraft passes the last altitude constraint VNAV automatically transitions to the flight level change mode and continues the descent toward the preselector To avoid possible pitch changes the current airspeed is latched as the speed target i...

Page 673: ...oint example flight will be used The performance initialization data used are as follows Climb Speed Schedule 300 0 75 Cruise Speed Schedule 0 78 Descent Speed Schedule 300 0 80 Transition Altitude 18 000 Speed Altitude Restriction 250 10 000 Cruise Altitude 45 000 Pressing the PERF DATA prompt allows the PZ 800 to calculate the performance values for the entire flight plan Airspeed constraints wi...

Page 674: ... Climb Phase kt Descent Phase kt 250 210 220 160 39 170 VREF 1O Gear 225 Climb and Descent Schedule Table 211 The flaps down speed schedule is based on the of flight refer to paragraph 4 D l d If ASEL is armed 60 ft min for 3 seconds in the current phase on an approach direction of the altitude p eselect value with the altitude preselector above the aircraft then the phase of flight will change to...

Page 675: ...nored until the constraint waypoint is sequenced Once the constraint waypoint is sequenced the target speed returns to the initialization climb speed Rule3 Initialization climb speeds can be changed at any time and will cause the active target speed to change if no speed constraint is active Figure 272 shows the climb phase of the flight The following paragraphs refer to the circled numbers shown ...

Page 676: ...a climb and the flaps are raised to O degrees Although the flap placard for flaps 10 is 250 knots the speed target changes to 240 knots due to the speed restriction below 10 000 feet at 250 knots the system always uses 10 knots less than the entered speed restriction to prevent overshoots 9 At point 3 the speed target would change automatically to 250 knots FLA S 10 placard When the flaps are rais...

Page 677: ...tion altitude At point a constraint speed of 320 knots is entered on the active flight plan page adjacent to WPT2 but since 320 is larger than the entered 300 knots entered in PERF INIT the speed constraint is ignored and 300 remains as the speed target refer to rule 1 At point a constraint speed of 280 knots is entered adjacent to WPT3 The active speed target changes to 280 knots refer to rule 2 ...

Page 678: ...arget speed to the initial cruise speed schedule Rule4 Cruise speeds can be changed at any time The active target speed will not change to a new cruise speed schedule if the current target speed is latched to a constraint speed Figure 273 shows the cruise phase of the flight The following paragraphs refer to the circled numbers shown 6363 TOC A WPT 4 AD 3081 8 Cruise Phase Figure 273 22 14 00 Page...

Page 679: ... Phase Descent speed rules Rule 1 Only constraint speeds less than the descent speed schedule are observed Rule 2 Target speeds will latch to the constraint speed Rule3 The descent speed schedule can be changed at any time If the current target speed is latched only changes to the descent speed schedule less than the latched speed will be honored Speeds entered above the latched speed are limited ...

Page 680: ... target speed changes to 0 78 M to allow the aircraft to decelerate into WPT 7 At point the current speed target is now latched to 0 78 M but switches over to 300 KCAS when reaching the 0 78 M 300 crossover altitude At point deleting the SPD CMD on the active flight plan page returns the target speed back to the descent speed schedule of 300 0 80 22 14 00 Page 298 222 Aug 15 91 Use or disclosure o...

Page 681: ... 20 degree flap placard At point the flaps are lowered to 20 degrees which causes the speed target to automatically change to 160 knots which is 10 knots below the 39 degree flap placard At point the flaps are lowered to 39 degrees which causes the speed target to automatically change to VREF plus 10 knots The speed targets whether manual or automatic can be flown by the flight guidance system or ...

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