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Apollo 2001 Installation Manual

1. Autopilot Nav Source Selector Relay CDI R CDI L Nav TO FROM Valid Valid ILS Enable Relay Coil and Logic Nav Source Selector Annunciator Note ILS Enable connection not required in installations using NMS for non precision approach Figure 8 Power and Avionics Connections Apollo 2001 Installation Manual 17 Installation White Passive Browi Terminator Shield Passive Terminator 2 amp fuse or breaker Avionics e aa Red Power e Black Black 17 1 NAVNETA In line power filter NAVNETB Power Control on both NAVNET leads at Install clamp on ferrite choke 2010 MCLS Power Ground NAVNETA NAVNETB Power Control NAVNET Shield 2 each and sensor unit ie NAVNET Shield Oo CN ERU f NENA 2 amp fuse Apollo or breaker E 13 2022 GPS 2001 Avionics e Power i Black Black 25 3 In li filt T n line power filter Tq 7 NAVNETA Power Control NAVNET Shield 1 Transducer Inputs 2 amp fuse or breaker a 2030 F ADS Avionics e Re Power Power e Black Black Ground 5 fuse In line power filter or breaker Heater Power Avionics e Re
2. For VFR installations the 2001GPS be installed with only power and antenna connections The 2001 TSO requires a position sensor either a 2010 MCLS or 2022 GPS CERTIFICATION The Apollo 2001 TSO is designed and tested to meet the requirements of FAA TSO C129a N8220 60 RNP 10 and C115b and is authorized for supplemental IFR en route terminal non precision approach and primary oceanic remote airspace operation using a TSO C129a B1 GPS sensor and for IFR en route and terminal operation using a TSO C60b Loran C sensor The Apollo 2001GPS is designed and tested to meet the requirements of FAA TSO C129a N8220 60 RNP 10 and C115b is authorized for supplemental IFR en route terminal non precision approach and primary oceanic remote airspace operation using its internal GPS Apollo 2001 Installation Manual Introduction sensor and for IFR en route and terminal operation using an external T SO C60b Loran C sensor UNPACKING THE EQUIPMENT Carefully unpack the equipment Visually inspect the package contents for any evidence of shipping damage Retain all shipping containers and packaging material in case reshipment is necessary PACKAGE CONTENTS As shipped from the II Morrow factory the Apollo 2001 package includes most necessary items for installation other than supplies normally available at the installation shop such as wire cable ties and required indicators and annunciators The items included in the pa
3. Output approx 2 seconds IDENT OUTPUT This message is used to output a new ident Message Format PMRRCO4ti1ii lt chksum gt lt cr gt message 1d Den list type input 111 ident four character ascii Example Message PMRRC041SLE lt space gt 99 lt cr gt Set the remote frequency ident to SLE 22 Apollo 2001 Installation Manual Serial Interface Specifications FREQUENCY LIST OUTPUT This message is used to output frequencies for the SL40 remote recall function One message is sent for each frequency available for the airport ident Message Format PMRRCOStfmk lt chksum gt lt cr gt message id lisa list type input 1 ai frequency type 0 TWR tower frequency 8 CTF common traffic advisory frequency 1 GND ground frequency 9 DEP departure 2 ATS for ATIS 3Ah FSS flight service station 3 ATF air traffic frequency 3Bh RFS for remote flight service station 4 APP for approach lt 3Ch UNI for unicom 5 ARR for arrival 3Dh MF mandatory frequency 6 AWS automatic weather station gt 3Eh not defined do not use 7 CLR clearance delivery 3Fh undefined for other frequency types mk frequency m desired frequency in MHz in hexadecimal where m desired frequency 30h with desired frequency in range of 118 to 136MHz or 162MHz k desired frequency in kHz where k desired frequency 25KHz 30h with desir
4. page 2 Press SEL rotate the SMALL knob to the desired selection then press ENT when complete The air data selections are NONE unis Subtus doeet do no air data computer connected 2090 FADE for connection to the 2030 F ADS on NAVNET 429 ADC LD gii for connection to an Arinc 429 compatible air data computer using label 204 baro altitude 429 ADE E205 rana for connection to an Arinc 429 compatible air data computer using label 203 pressure altitude NAVNET Interface if installed To check and configure the NAVNET interface 1 Make sure all connections have been made and that the terminators are installed on the ends of the network cable 2 If more than one NMC 15 connected disconnect or remove all but one NMC 3 Turn power off to all remote sensors turn off at breaker or remove fuses 4 n test mode rotate the LARGE knob to the NAVNET TEST page then press ENT to test the network The 2001 will display either a pass or fail message If a fail message is displayed refer to Expected voltages are Va 2 6 0 4 volts DC Vb 2 4 0 4 volts DC Vab 0 2 0 04 volts DC 5 f more than one NMC is installed on NAVNET select a different network address for each In test mode rotate the LARGE knob to the NET NMC page press SEL rotate the SMALL knob to change the address then press ENT to save the new address The primary NMC should be set to address 0 the second NMC to
5. 800 553 2233 US Fax 214 250 2794 Phone 604 763 2232 Fax 604 762 3374 Phone 612 927 6500 Fax 612 924 1111 Phone 818 787 1221 Fax 818 787 8916 Phone 301 799 9497 Fax 301 799 8320 Apollo 2001 Installation Manual Serial Interface Specifications APPENDIX E SERIAL INTERFACE SPECIFICATIONS This appendix includes the interface specifications for both the RS 232 and Arinc 429 communication ports RS 232 INTERFACE The RS 232 serial interface configurations supported by the 2001 are listed in Table 7 Instructions for configuring the serial ports are included in the checkout procedure on page 21 Table 7 RS 232 Serial Interface Selections Comment No input or output Moving map data output Altitude encoder converter data input IGPSSIM RX Used for factory test For internal GPS sensor on 2001 GPS Not used on 2001 Not used on 2001 Used for factory test Moving Map data alternated with SL40 com freq list data output Note Serial port channel 1 can be used for external connections on the 2001TSO only It cannot be used on the 2001GPS MOVING MAP OUTPUT The format Er the moving map data output is as follows Definitions of the output data 1s included in Table 8 8 and Table 9 A sample output message 1s included i in Fieure 12 Bald Tate a 9600 Database 8 SIOP DIS esse ctu lg 1 Pl dil acc approx 2 seconds Message length usi var
6. ANNUNCIATOR REQUIREMENTS The 2001 installed for IFR non precision approach and or oceanic remote airspace operation requires annunciators as described here Each annunciator should include a lamp of the proper voltage for the installation and legends as follows LegendColor MSG amber GPS amber PTK blue OBS HLD blue with included momentary switch APPRCH blue ACTIVE green The annunciators should be connected to a suitable dimming circuit for night time operation An example of appropriate annunciators is included in Appendix D Accessories 30 Apollo 2001 Installation Manual Specifications REAR CONNECTOR PINOUT Table 5 Connector Pinout 1 O CDi Left JCDIsleftouput S 2 O CDI rightomput ___________________ ee o o ie 5 I fArncimB_________ jArinc429channellinputB donotconnect _ 6 I fArncima Arinc429chamellinputA do notconnect O O O o o peo mtt _ oe ACTIVE annunciator TTT nT Active annunciator output pulled low to turn lamp on 12 VDi validflag Lowlevel VDI valid flag 13 O NAV validflag 1 valid flag 14 NAV VDI valid flag ground Lowlevel NAV VDI valid flagretum Reserved 0 RE RN 18 INC S NC T TxDI 1 RS 232 serial data output not available on 2001GPS NW NNNM Serial ground Serial data ground connection 2 RxDI Channel 1 RS 232 seria
7. If more than one NMC is installed check network addresses See NAVNET checkout on page Improper NAVNET connections Double check NAVNET connections and make sure terminators are installed at each end of the NAVNET cable See NAVNET checkout on Apollo 2001 Installation Manual 25 Troubleshooting CONTACTING THE FACTORY FOR ASSISTANCE If the Apollo 2001 unit fails to operate despite troubleshooting efforts contact the II Morrow factory for assistance Ask for Technical Support II Morrow Inc 2345 Turner Rd SE Salem Oregon 97302 U S A Phone 503 581 8101 In USA 1 800 525 6726 In Canada 1 800 654 3415 FAX 503 364 2138 Be prepared to offer the following information about the installation e Installation configuration accessories antenna Model number part number with mod levels and serial number Software versions Description of problem Efforts made to 1solate the problem 36 Apollo 2001 Installation Manual Periodic Maintenance APPENDIX B PERIODIC MAINTENANCE The Apollo 2001 unit 1s designed not to require any regular general maintenance There are no adjustments requiring calibration LITHIUM BATTERY REPLACEMENT The internal keep alive battery will require replacement after 4 to 6 years Regular planned replacement is not necessary The Apollo 2001 will display a low battery message when replacement is required Once the message is displayed the battery should be replaced within 1
8. connection The chokes are to reduce EMI emissions from the NAVNET cable Note NAVNET is not required with the 2001 GPS unless remote sensors are to be connected AVIONICS OUTPUTS The 2001 includes full avionics outputs for CDI HSI indicators autopilot and annunciators These outputs must be connected as appropriate for the particular installation The CDI HSI outputs may be connected to a dedicated CDI or HSI or to a shared indicator using an appropriate switching relay The avionics outputs available are listed in E resero specifications on page 28l Connect the annunciator outputs to lamp indicators as described in the specifications The minimum connections required for different installations are listed in If a switching relay 1s used to make connections to a shared CDI HSI it should be a minimum of an eight pole relay box along with an appropriate selector switch with annunciation Several suitable relays and switches are listed in Appendix D SERIAL INTERFACE The 2001TSO includes two RS 232 serial port connections The 2001GPS includes one The serial ports can be used for connecting to such devices as the Shadin Digiflow or Miniflow Fuel Flowmeter Argus moving map display Stormscope an altitude encoder or gray code converter For systems including a TSO C129a GPS sensor RxD2 must be connected to an altitude encoder or converter unless a suitable air data computer is connected either on 12 Apollo 2001 Installation Manual Insta
9. All other navigation data will be dashed when it is flagged Apollo 2001 Installation Manual Serial Interface Specifications Table 9 Moving Map Binary Route Data pte Den Fort Format designator dd waypoint number in ASCII 01h to 20h xiannnnn Sequence number x undefined 1 1 if last waypoint 1 if active waypoint nnnnn unsigned binary waypoint number ddddd ASCII waypoint identifier sddddddd Waypoint latitude packed unsigned binary xxmmmmmm s sign 0 for north for south xhhhhhhh ddddddd degrees mmmmmm minutes hhhhhhh hundredths of minutes x undefined SXXXXXXX Waypoint longitude sddddddd s sign O for east 1 for west xxmmmmmm ddddddd degrees xhhhhhhh mmmmmm minutes hhhhhhh hundredths of minutes x undefined Magnetic variation at waypoint 17 nnnnnnnn LS byte msbit Isbit 18 nnnnnnnn MS byte msbit Isbit Two s complement binary in sixteenths of degrees easterly variation 1s positive ASCII carriage return 0Dh Apollo 2001 Installation Manual 49 Serial Interface Specifications Example Moving Map Data Output AN 34 1570 34 15 70 latitude BW 118 4390 118 43 90 longitude Co 306 track angle D219 210 knots E02682 268 2nm to waypoint GR0006 0 6nm right of course 135059 305 9 desired track K5FO SFO waypoint ident L3058 305 8 bearing to waypoint 14 0 east magnetic variation No alarms data not flagged lt binary From Tab
10. Format Mnemonic Width SA ddd IAS 7 JjIndicateAirSpeedinknos S SB ddd TAS 7 TrueAirSpeedinknos o SC ddd MACH 7 MachSpeedinthousandhs SD sdddd PALT 9 Altitude in tens of feet sealevel SE sdddd DALT 9 Density Altitude in tens of feet sea level SJ Rate of Turn in degrees second is right is left SK sddd VSPD___ 8 Vertical speed in tens of fee minute SL HEAD 7 0 to 359 degrees from true north SM j dddd RFF 8 Right Engine Fuel Flow in tenths of gallons hour SN ddddd RFU____ 9 Right Engine Fuel Used in tenths of gallons SO dddd 8 Left Engine Fuel Flow in tenths of gallons hour SP ddddd LFU___ 9 Engine Fuel Used in tenths of gallons SQ ERR 7 Error Log Reason Indicator 001 temp sensor error 000 NO errors S CKSUM 7 Checksum of all characters preceding this record The checksum is a one byte checksum discarding carries including all characters from the initial STX up to and including the line feed preceding the checksum message Example Fuel Airdata Input Data AS LOSADA 51230 230 knots true air speed oC LOT 0 101 mach 223 knots indicated air speed SD 3200 32 000 feet pressure altitude SE 3312 33 120 feet density altitude S ES 5 C outside air temp o6 09 3 C true air temp SHOTO wind direction at 10 relative to true north S915 uq SK
11. NAVNET cable should be routed to any locations where NAVNET remote sensors or NMC units are to be located The cable must be routed in a daisy chain fashion not spliced and branched off Avoid routing the cable near motors or other strong sources of Apollo 2001 Installation Manual 11 Installation electromagnetic interference A network terminator part 4500 2135 must be installed at both ends of the cable SeelFigure 7 for typical NAVNET routing NAVNET Terminator Terminator Sensor Sensor Figure 7 Typical NAVNET Routing The cable part 44500 2134 available from II Morrow is a twisted pair shielded cable with power control wire included Connect the white wire to NAVNET A brown to NAVNET B and blue to power control connections The power control connection is used to automatically turn on remote sensors when the 2001 is turned on The shield must be connected to the rear of the mounting frame using one of the ground wires supplied See Figure J for typical NMS NAVNET connections Special care must be taken when connecting the NAVNET cable at each NMC or sensor When connecting units to the cable the conductors may be spliced directly to the connector or a short stub six inches or less may be used Make sure to connect the shields of each splice together and ground to the mounting frame The RF suppression chokes supplied part 16608 0009 must be clamped over both leads of the cable within six inches of the shield splice
12. and 1s approved by the Administrator Source FAA TSO C115b and TSO C 129a ORDERING INFORMATION To receive additional copies of this publication order part 560 0161 01A Apollo 2001TSO 2001GPS Installation Manual NOTES Table of Contents TABLE OF CONTENTS Antenna 2001 gps onl EQUIPMENT MOUNTING Apollo 2001 Installation Manual Table of Contents ii Apollo 2001 Installation Manual Introduction SECTION 1 INTRODUCTION ABOUT THIS MANUAL This manual describes the installation of the Apollo 2001TSO Navigation Management Computer and 2001 GPS Navigation Management Computer with GPS This manual 1s for all versions of the Apollo 2001 meeting TSO C129a N8110 60 RNP 10 and TSO C115b requirements References to the 2001 throughout this manual are for both the 2001 TSO and 2001GPS unless otherwise specified This manual is intended for use by persons certified by the Federal Aviation Administration FAA to install aircraft navigation devices It includes installation and checkout procedures for the 2001 unit to standards described in FAA advisory circulars AC 20 130A and AC 20 provides an INTRODUCTION to the Apollo 2001 unit TSO certification information 1s also included in this section Section 1 includes INSTALLATION and checkout procedures un YN S oo ection 2 SOS includes complete SPECIFICATIONS SES includes LIMITATIONS for the equipment and installation includes TROUBLESHOOTING i
13. can be used for each connection The typical cable loss for 20 feet of RG 142B coax with the supplied connectors 1s 4 dB During the post installation checkout susceptibility to harmonics of VHF COM transmitters will be evaluated If problems arise then better isolation or increased distance may be required between the GPS antenna and other transmitting antennas or a notch filter may be installed 1n series with the antenna coax of the VHF COM transceiver to reduce or eliminate the harmonic interference A notch filter for this use part 4162 1059 is available from II Morrow 14 Apollo 2001 Installation Manual Installation Clamp Nut Slit 1 4 2X Slide clamp nut over coax Strip coax as illustrated Cut two 1 4 slits in jacket 180 0 031 gt degrees apart Braid CI Step 2 bc Slide braid clamp over end of coax and St e under the braid Cap Step 3 Soldes Center Insert coax with braid clamp into Conductor connector and tighten clamp nut securely Solder the center conductor of the coax to the contact as illustrated Attach the cap and secure tightly Assembly instructions for right angle connector part 4162 1008 Apollo 2001 Installation Manual 5 Installation Clamp Nut Slip Washer Ve
14. for an update or replacement Note Each time the 2001 is turned on the database expiration date will be checked automatically This requires that the date be set correctly Apollo 2001 Installation Manual 25 Installation APOLLO 2001 POST INSTALLATION CHECKOUT LOG Date AIRPLANE MAKE MODEL TAnLNO CONFIGURATION INFORMATION O 2001TSO 430 0267 1 Mod Serial LJ 2001TSO w Arinc 430 0267 2 Mod Antenna O 2001GPS 430 0267 3 Mod LJ 2001GPS w Arinc 430 0267 4 Mod __ TEST MODE CHECKOUT Avionics Outputs Air Data Computer Selection O 0 N A CDI left mid right None O O N A VDI down mid up L 2030 FADC O O N A TO FROM flag OFF TO O A429 ADC L204 FROM 1 A429 ADC L203 O O N A External annunciators NAVNET Interface O 0 N A Valid flags O Installed Installation Configuration O Tested IFR Yes LI No Address APPR O Yes No Serial Interface Configuration OCN O Yes O No Chl RX TX Arinc 429 Configuration Ol N A Ch2 RX TX Output Labels DI None Speed O Low O High NORMAL MODE CHECKOUT Time Date and Position Interface Checks O Entered O O N A Serial input checked GPS Operation 2001GPS O O N A Serial output checked O Position check O 0 N A Arinc 429 input checked Signal reception check O O N A Arinc 429 output checked Interference from other avionics checked 1 VHF COM interference check REMOTE SENSOR SETUP AND CHECKOUT 2010 MCLS Installed
15. installation manual Contact II Morrow for information regarding the use of antennas other than the A 33 or A 34 EQUIPMENT MOUNTING Once the cable assemblies have been made attach the main 50 pin connector and coax connector for the 2001GPS to the rear of the mounting frame as illustrated in Figure 5 and Figure d Attach the connector cover over the 50 pin connector and connect any shield connections such as for NAVNET or serial cables as illustrated Route the wiring bundle to each side as appropriate and secure to the mounting frame using the cable tie mounts and cable ties provided Mounting Frame Pneumatic _ Sleeve Fitting 2X Airflow Connector _ 2X 4 Lock Washer 2X 4 40 x 3 8 Screw 2X Cable Tie Mount 9 Right Angle Panel E Mount Connector KE 2X Shoulder Bushing Y Figure 5 Rear Frame Assembly If air cooling 1s provided it can be either from ram air or an equipment cooling fan If ram air is used it should provide water free filtered air To connect the cooling air use the two air fittings provided inserting one from the rear of the mounting frame and one from inside the mounting frame Connect to the air fitting using standard air hose and clamps Slide the foam rubber sleeve over the inside airflow fitting 10 Apollo 2001 Installation Manual Installation Mounting Frame _ In Line Power Filter E 5 2X Clamp on Choke 2X 3 48 x 1 4 Screw EN 2X
16. option allows you to disable viewing of the System Mode features in normal operation The Setup Mode option allows you to disable access to the Setup pages when the unit 1s installed in the aircraft In the test mode rotate the LARGE knob to the Disable SYS Mode Setup Mode page press SEL Rotate the SMALL knob to disable YES or enable NO the SYS mode Rotate the LARGE knob to select the Setup mode Rotate the SMALL knob to disable YES or enable NO the Setup mode Press ENT when you are finished Disable Altitude and Arc Assist Nav Pages The Disable Altitude and Arc Assist NAV pages option allows you to not display the Altitude Assist and or Arc Assist pages in the NAV mode during normal operation In the test mode rotate the LARGE knob to the Disable Alt Assist Arc Assist page Press SEL Rotate the SMALL knob to disable YES or enable NO the Alt Assist NAV page Rotate the LARGE knob to select the Disable Arc Assist NAV page option and rotate the SMALL knob to disable YES or enable NO the Arc Assist NAV page Press ENT when you are finished NORMAL MODE CHECKOUT The SYS Mode and Altitude Assist NAV pages must be enabled to perform the normal mode checkout Reconfigure these two settings to the desired operation after completing the Final System Check Switch on the 2001 in the normal mode to complete the rest of the checkout The 2001 will go through a sequence of self tests Enter Time Date and Position The 2001 r
17. to 2 months If the battery 1s not replaced internal ram memory and the system clock information may be lost When the low battery message appears return the 2001 to the factory or an authorized II Morrow service center for battery replacement CLEANING THE FRONT PANEL The front bezel keypad and display can be cleaned with a soft cotton cloth dampened with clean water DO NOT use any chemical cleaning agents Extreme care must be taken to avoid scratching the surface of the display Apollo 2001 Installation Manual a7 Periodic Maintenance NOTES 3 Apollo 2001 Installation Manual Environmental Qualifications APPENDIX C ENVIRONMENTAL QUALIFICATIONS The Apollo 2001 has been tested to the following environmental categories per procedures defined in RTCA DO 160C Environmental Qualification Form Nomenclature Apollo 2001 GPS Manufacturer Apollo 2001 TSO II Morrow Inc Part No 430 0267 yxx 2345 Turner Road S E TSO No TSO CI 15b TSO C129 Salem Oregon 97302 Description of Conducted Tests Temperature and Altitude Equipment tested to Category F1 with high operating temperature of 70 C In flight Loss of Cooling 9 No cooling required Altitude 6 Equipment tested to 70 000 feet Decompression 6 Equipment tested for decompression to 55 000 feet Overpressure 6 Equipment tested for overpressure 5 0 Equipment tested to Category C 2 C min Humidity Equipment tested to Category A standard humidity envir
18. 001TSO using an external position sensor such as the 2022 GPS sensor in place of the 2001GPS Annunciators MEN Avionics Outputs Arinc 429 or Apollo 2001GPS 5 7799 T Atitude Interface Encoder Converter Figure 3 Minimum 2001GPS Installation 4 Apollo 2001 Installation Manual Introduction For complete system redundancy dual NMS systems may be desired in some applications Primary oceanic or remote airspace operation requires dual independent redundant systems Installing two systems as depicted in Figure 3 can be a means of implementing a dual redundant system configuration A system with redundant features 1s illustrated in Figure 4 The Apollo NMS can be installed with several NMC units connected on NAVNET as well as redundant sensors The Apollo NMS supports up to two NMCs two 2010 loran sensors and a GPS sensor for each NMC internal in 2001 GPS or on NAVNET A system with two NMCs with GPS can include two 200IGPS units one 2001GPS one 2001TSO and one 2022 GPS Sensor or two 200ITSO units with two 2022 GPS Sensors Annunciators CDI HSI Autopilot Avionics Outputs Pilot lt Co Pilot O O Co Pilot Apollo 2001 GPS Apollo 2001 TSO OS Arinc 429 or RS 232 NAVNET Interface Altitude Encoder Converter Figure 4 Redundant Installation Apollo 2001 Installation Manual 5 Introduction Table 2 System Configurations IFR C 2001TSO 200
19. 1TSO 2001TSO 2001GPS 2001GPS 2001GPS En route amp En route En route En route amp En route terminal terminal terminal amp terminal terminal amp approach amp approach approach amp primary oceanic ni O D O 2 Minimum Required Equipment and Connections Position Sensor 2010 or 2022 2022 2022 N A Required Required REN MN GPS Optional Equipment and Connections Redundant 2010 or 2022 2010 1 or 2 2010 1 or 2 2010 1 or 2 2010 1 or 2 2010 1 or 2 Sensors Annunciators OBS HLD OBSIHLD NA altitude input altitude input 2oso 2030 2030 _ 20380 HS 232 Moving map Moving map Moving map Moving map standard Fuel flowmeter Fuel flowmeter Fuel flowmeter Fuel flowmeter Fuel flowmeter Fuel flowmeter Altitude Fuel Air Data Fuel Air Data Fuel Air Data Fuel Air Data Fuel Air Data Fuel Air Data optional EFIS interface EFIS interface EFIS interface EFIS interface EFIS interface EFIS interface Leu Notes N A is for not applicable En route annunciators include MSG PTK and GPS Approach annunciators include MSG PTK GPS APPRCH ACTIVE and OBS HLD as well as a hold momentary switch for input The GPS annunciator 1s required for multi sensor installations only It is not required for GPS only or Loran C only installations Refer to limas page b For altitude sources The data card must be current for non precision approach operation D O D D O O Q 9 I
20. 2001GPS Number of channels cenas 8 1575 42 MHz L1 C A code Sensitivity acquisition 135 dBm Sensitivity drop lock 142 dBm Dynamic Falle Sa gt 20 dB Lat lon position accuracy 15 meters RMS typical 25 meters SEP without SA 100 meters 2DRMS with SA A O 1000 knots maximum ACCClCR AU OMe rai pede dae ie Er ace 4G maximum TTFF Time to Mesta eb 25 seconds typical with current almanac position time and ephemeris 55 seconds typical with current almanac position and time quiste 2 5 seconds typical Position update interval 1 second typical rU WGS 84 Apollo 2001 Installation Manual 29 Specifications ALTITUDE INPUT REQUIREMENTS The minimum requirements of the altitude data input 1s as follows Input t ethod ose iita RS 232 NAVNET from 2030 or Arinc 429 RSI pressure altitude on RS 232 NAVNET or Arinc 429 interface or baro altitude on Arinc 429 interface RESOLU scsi 100 feet minimum ACUTA urla must meet accuracy requirements of TSO C88a Note Installation of altitude input equipment such as encoders or air data computers must be done according to their installation instructions Note Specifications for the RS 232 altitude input are included on page 54 for the Arinc 429 input on page 55
21. 3 Lock Washer _ 2X Navnet Cable _ 4X Cable Ties Connector Cover Ground Wire connect NAVNET cable shields together and to ground N Serial Cable 50 Pin Connector Avionics Ground Wire connect with N Output Wires serial cable shield 2X 4 40 x 1 4 Screw Figure 6 Rear Connector Wiring Important The 50 pin connector must be able to float freely to ensure easy insertion of the 2001 and mating of the connector Cable strain pulling the connector up or down will make unit insertion difficult Once the connectors are attached to the mounting frame install the mounting frame assembly in the instrument panel Then slide in the 2001 and tighten the unit using a small flat bladed screwdriver in the mounting rod holes at the upper right and left corners on the front panel ELECTRICAL CONNECTIONS POWER The 2001 1s internally fused at 7 amps A separate 5 amp maximum circuit breaker or fuse should be installed for downline overload and short circuit protection Make the power connections to the 2001 using the in line power filter 4123 1009 supplied Connect the red wire to pins 25 and 50 input and the black wire to pins 24 and 49 input Use 20 AWG or larger wire to make connections from the in line filter to the aircraft power connection Note Circuits should be protected in accordance with guidelines in AC 43 13 1A chapter 11 section 2 paragraph 429 NAVNET The
22. Apollo Navigation Management Computer Model 2001TSO 2001GPS Installation Manual Manufacturer of Quality Navigation and Communication Equipment July 1999 560 0161 01 A 1999 by II Morrow Inc All rights reserved Printed in the U S A No part of this document may be transmitted reproduced or copied in any form or by any means without the prior written consent of II Morrow Inc Due to II Morrow s commitment to constantly improve the quality and performance of our products information contained in this document is subject to change without notice NAVNET and Flybrary are trademarks of II Morrow Inc II Morrow and Apollo are registered trademarks of II Morrow Inc II Morrow Inc 2345 Turner Rd S E P O Box 13549 Salem OR 97302 Salem OR 97309 U S A Phone 503 581 8101 In USA 1 800 525 6726 In Canada 1 800 654 3415 FAX 503 364 2138 HISTORY OF REVISIONS L 00 Jan 19 1996 Original release Dec 19 1996 Added SL40 Comm Serial Data Information A 34 input and Apollo ACU added IMPORTANT NOTE The conditions and tests required for TSO approval of this article are minimum performance standards It is the responsibility of those desiring to install this article either on or within a specific type or class of aircraft to determine that the aircraft installation conditions are within TSO standards The article may be installed only if further evaluation by the applicant documents an acceptable installation
23. Checked P N 430 SN Antenna 2022 GPS O Installed Checked P N 430 SN Antenna 2030 F ADS Installed LJ Checked P N S N FINAL SYSTEM CHECK Position sensors checked Direct To waypoint entered Database checked Navigation data checked COMMENTS 26 Apollo 2001 Installation Manual Specifications SECTION 3 SPECIFICATIONS This section includes detailed electrical physical environmental and performance specifications for the Apollo 2001 ELECTRICAL Input voltage le 10 VDC to 40 VDC reverse polarity protected Input oue IA at 14 VDC 875 mA for 2001 TSO 525 mA at 28 VDC 475 mA for 2001 TSO Input POWER ie 12 watts typical 15 watts maximum Internal TUS edo Eee b eee des 7 amp fast blow II Morrow 11172 1702 Buss T GMAT or equivalent Memory Internal lithium battery with a service life of approximately 4 to 6 years Note The Apollo 2001 will provide a message on the display when the lithium battery is running low and should be replaced See Appendix B for battery replacement instructions PHYSICAL Horace 2 00 inches 5 08 cm WIO 6 25 inches 15 88 10 43 inches 26 49 cm behind panel including mounting frame Weight with mounting tube 3 8 Ib 1 72kg for 2001 GPS 3 7 1b 1 68kg for 2001 TSO Required cleatance age Allow 1 inch 2 54 cm behin
24. NPUT Connect the take home sense input on pin 29 to ground on pin 30 If this pin 1s left open the 2001 will only operate in the simulation mode ANTENNA INSTALLATION AND CONNECTIONS 2001GPS ONLY The mounting location and cable connections for the GPS antenna are very important The antenna should be mounted no closer than two feet from VHF COM transmitter antennas six inches from other transmitter antennas emitting less than 25 watts and two feet from higher power antennas Special care should be taken to ensure that the GPS antenna is not mounted in close proximity to antennas that may emit harmonic interference at the LI frequency of 1575 42MHz Refer to the antenna installation manual for installation instructions The connectors are included in the installation kit Suggestion Temporarily locate the GPS antenna with coax connected to the 2001 GPS and check the GPS performance as described in the GPS Operation and Position 2001 GPS or 2001TSO with 2022 test in the Post Installation Checkout on page Once a suitable location has been verified then permanently mount the antenna g the antenna closer than two feet from a COM antenna conduct the GPS Operation and Position 2001 GPS or 2001TSO with 2022 test in the Post Installation Checkoul on pagd 24 If the 2001 passes the test then moving the antenna is not necessary Note If using an antenna that was already on the aircraft or if mountin Apollo 2001 Ins
25. ON lt TNC female A 34 Antenna II Morrow Part eene 590 1112 Manufacturer Aero Antenna Manufacturer eee nennen AT 575 93 The A 34 GPS antenna is a standard accessory item with the 2001 The A 34 includes a built in preamp and has a low profile low drag radome mounted on a die cast aluminum base It has a maximum altitude of 55 000 feet and weighs only 7 0 ozs See the installation manual Apollo 2001 Installation Manual 43 Accessories for the A 34 for complete specifications and installation instructions The A 34 mounts in the same footprint as the II Morrow A 16 and A 23 Loran antennas to simplify upgrading lt 4 68 3 00 j n p UN 0 66 ut lac TNC female 2010 Multi Chain Loran Sensor The Apollo 2010 MCLS is a multi chain loran sensor with TSO C60b approvals for IFR en route and terminal operation The 2010 1s intended for remote mounting and connects to the 2001 as part of an Apollo NMS system using NAVNET It comes complete with mounting tray and antenna The 2010 1s 6 43 inches H x 1 50 inches W x 11 97 inches L with mounting tray Several antenna options are available for the 2010 For complete information and specifications on the 2010 contact II Morrow 2022 GPS Sensor The Apo
26. RMATION Always follow good avionics installation practices per FAA Advisory Circulars AC 43 13 43 13 2A AC 20 130A AC 20 138 and AC 20 1214 later FAA approved revisions of these documents Follow the installation procedure in this section as it 1s presented for a successful installation Read the entire section before beginning the procedure Perform the post installation check out before closing the work area in case problems occur INSTALLATION OVERVIEW A successful installation should start with careful planning including determination of mounting locations for the 2001 antennas and accessory items as well as required and optional connections and cable routing Once the mounting location has been determined prepare the mounting frame for installation It may be easier to complete the wiring harness and attach the connectors to the mounting frame before installing the mounting frame INSTALLATION CONSIDERATIONS MOUNTING CONSIDERATIONS The 2001 is designed to mount in the avionics stack in the aircraft instrument panel within easy view and reach of the pilot The standard package includes a mounting frame for ease of mounting connections and service of the unit Allow an additional 1 clearance to the rear of the mounting frame for connectors For typical installations the 2001 does not require external cooling When mounting the 2001 leave a clearance of 1 4 inch between avionics to allow for air circulation I
27. address 1 Serial Interface Configuration 1 In test mode rotate the LARGE knob to the CH RX TX page to configure the serial inputs and outputs 2 Press SEL then rotate the LARGE knob to select the serial channel field rotate the SMALL knob to make the selection then press ENT when complete Refer to Appendix E for avallable selections Note The input RX and output TX for channel 1 will be set to GPS on the 2001 GPS and cannot be changed Other Test Mode Pages The test mode includes several pages that are not necessary for the checkout They are as follows TO TEST DISPLAY Can be used to check the 2001 front panel displays by pressing ENT Apollo 2001 Installation Manual 21 Installation TEST CONTROLS nera Can be used to check the 2001 front panel controls Press each button and rotate the SMALL knob to check the controls OPERATION STATUS Factory use only Should be set to STANDARD SYSTEM INITIALIZATION Used to reset all internal memory including user waypoints flight plans and configuration data All user data will be lost ARINC DOI ail Not used in 2001 SYSTEM DEFAULTS Should be set to NORMAL RAMCARD SETUPS Factory use only SERIAL PORT TEST aida Test use only Used to test the serial ports by connecting the outputs back to the inputs SYS Mode amp Setup Mode configuration The Disable SYS Mode
28. avigation Emergency search 30 flight plans of 20 waypoints each with automatic waypoint sequencing 200 user waypoints Custom navigation display pages Flybrary database cards Internal simulation software Password protected owner information pages Serial data inputs and outputs Automatic LED brightness control Parallel track offset CDI HSI Autopilot outputs Additional features when connected to a compatible fuel air data computer include e Heading information Wind speeds and direction Altitude MSL density pressure TAS Climb descent rate Fuel flow and management information Outside air temp SYSTEM CONFIGURATIONS The 2001 can be installed in many configurations depending upon individual requirements Several Apollo NMS system configurations using the 2001 are illustrated in the following figures Minimum configurations and equipment for IFR and oceanic remote airspace installations as well as optional connections are listed in Table 2 on pagel l A typical Apollo NMS installation 1s illustrated in Figure 2 Apollo 2001 Installation Manual 3 Introduction Autopilot Annunciators Avionics Outputs Arinc 429 or NAVNET RS 232 Serial Interface Altitude Encoder Converter Figure 2 Apollo NMS Typical Installation A minimum 2001GPS installation is illustrated in This is the minimum configuration required for an IFR installation A similar installation can be made with a 2
29. ch as an EFIS display REMOTE SENSOR SETUP AND CHECKOUT 2010 Loran Sensor if installed Refer to the 2010 install manual for setup and checkout instructions 1 In test mode rotate the LARGE knob to display the LORAN 1 SETUP page then rotate the SMALL knob to the setup pages and make any changes appropriate for the installation press SEL rotating SMALL knob pressing ENT 2 In normal mode verify that the seed position was entered then check the loran sensor operation as described in the 2010 install manual 3 Ifa second 2010 is installed repeat the checkout using the LORAN 2 SETUP page 2022 GPS Sensor if installed Refer to the 2022 install manual for setup and checkout instructions 1 Verify that the time date and seed position were entered 2 Check out the sensor operation as described in the 2022 install manual Note The NAVNET address on the 2022 must be setup to match the corresponding address of the NMC 2030 F ADS if installed Refer to the 2030 install manual for setup and checkout instructions 1 Make sure the 2030 FADC selection was made for the on page 21 2 Complete the setup and checkout as described in the 2030 install manual Shadin 200 Fuel Air Data Computer if installed Refer to the Shadin 200 install manual for setup and checkout instructions 1 Make sure the FADC selection was made in the Serial Interface Configuration as shown in Fable 7 lon page 2 Complete the setup an
30. ckage are listed in Table 3 Additional items required for an IFR installation are listed 1n the section Other Required Materials on pagelsl Table 3 Package Contents Part Description Nav Management Computer 430 0267 YXX Apollo 2001 T5O 2001GP5 See Table 1 MEN MEE AA Apollo 2001 Installation Kit Part 424 1204 xx 2001TSO 424 1099 xx 2001 GPS 123 1000 In line power filter 1 1 162 1008 Right angle coax plug 1 162 1060 TNC straight taper grip coax plug 1 162 3502 50 pin female solder cup connector 1 1 172 1702 7 amp fast blow fuse spare internal fuse 1 1 201 0009 Pneumaticsleevefitting 1 1 Cable tie 3 62 x 0 94 4 6 202 005 Cabletiemount A 4 Screw pan head Phillips 3 48 x 1 4 SS LO 3 3 Screw pan head Phillips 4 40 x 1 4 SS LX d 2 Screw pan head Phillips 4 40 x 3 8 SS ae Screw button head Phillips 6 32 x 1 2 SS oi 240 0310 Washer internal tooth lock 43 SS 2 2 240 0410 Washer internal tooth lock 4 SS fJ 2 308 0070 Air flow connector 2 2 310 1227 Connector cover 1 1 310 2032 Shoulderbushing 1 0 500 2143 3 groundwirewithlug 2 2 608 0009 Ferrite bead split with clamp 2 2 rr A MA A Apollo 2001 Installation Manual 7 Introduction Apollo NMS NAVNET Kit Passive Part 424 0607 xx 00 2135 NAVNET
31. d Red Heater Power Power e Black Black Heater Ground In line power filter Heater Ground NAVNETA NAVNETB Power Control NAVNET Cable NAVNET Shield Notes Make NAVNET connections as follows White wire to NAVNETA Brown wire to NAVNETB Blue wire to power control connections Connect shields to mounting frame on 2001 and to mounting tray on sensors A passive terminator must be installed at each end of the NAVNET cable The 2022 is not required with the 2001 GPS Figure 9 NMS NAVNET Connections 16 Apollo 2001 Installation Manual RS 232 Serial Interface Connections EA Shielded Connect shields to mounting frame with ground lead Arinc 429 Serial Interface Connections Shielded Cabl Arinc Out A Arinc Out B Arinc 1 In A Arinc 1 In B Arinc 2 In A Arinc 2 In B Connect shields to mounting frame with ground lead Notes TxDl RxDI are not available with the 2001 GPS Figure 10 Serial Interface Connections Apollo 2001 Installation Manual Installation Apollo SL40 Comm Radio RxD Ground Moving Map Display RxD Ground Altitude Encoder or TxD Converter Ground EFIS Arinc In A Arinc In B Air Data Computer Arinc Out A Arinc Out B 19 Installation POST INSTALLATION CHECKOUT Once the unit is installed complete the checkout procedure to verify proper opera
32. d checkout as described in the Shadin install manual 24 Apollo 2001 Installation Manual Installation FINAL SYSTEM CHECK The 2001 system should be fully functional at this time The final check includes checking the position from each sensor checking the database entering a direct to waypoint and checking the navigation functions Start with the 2001 turned on and operating in the normal mode and a datacard inserted Refer to the Apollo NMS User s Manual for operating instructions l Verify a valid position is displayed from each position sensor connected to the 2001 Press NAV rotate the LARGE knob to the IN USE lat lon page in Nav then rotate the SMALL knob to display the position from each sensor 2 To check the database a Press SYS rotate the LARGE knob to the SYSTEM INFO page and press ENT b Rotate the LARGE knob to display the APOLLO NMC software version page then rotate the SMALL knob to display the database information page The database name expiration date and version will be displayed 3 Enter a direct to waypoint Press the DIRECT TO button use the LARGE and SMALL knobs to select a nearby waypoint then press ENT or press the EMG button emergency search rotate the LARGE knob to select a waypoint press the DIRECT TO button then press ENT 4 Verify the bearing and distance to the selected waypoint If the database is expired or if a different coverage area 1s needed contact the II Morrow factory
33. d unit for connector and cable clearance Units dimensions are illustrated in on page 28l ENVIRONMENTAL The Apollo 2001 unit 1s designed and tested to meet appropriate categories of RTCA DO 160C The Environmental Qualification Form 1s included in Appendix C Operating temperature 20 C to 70 C Storage temperature mientas 55 C to 85 C Temperature variation 2 C per minute A E E E 95 at 50 C for 6 hours 2 day cycle Note The display filter is specified for lt 15 RH at 74 C for 120 hours and 50 RH at 49 C for 120 hours Apollo 2001 Installation Manual 27 Specifications Maximum altitude 770 000 feet COONS Recommended for operation above 55 Mounting Holes 10 43 APOLLO GPS dB SEL INFO ENT 6 25 Mounting Frame Dimensions in inches Figure 11 Unit Dimensions AVIONICS OUTPUTS BIBITUR sence 150 mv full scale will drive up to 200 ohm load TO OFF FROM 250 mv TO FROM indication will
34. drive up to 200 ohm load Nay Walt LE opio 300 mv for valid indication will drive up to 100 ohm load INAV superflag Vin 2 volts minimum for valid source capability of 400 mA VIO Meneses 150 mv full scale will drive up to 200 ohm load VOL Cl ias ars oo dd 300 mv for valid indication will drive up to 100 ohm load VDI superflag Vin 2 volts minimum for valid source capability of 400 mA ZUDEUTICIA LODS Ai ii Open collector outputs capable of sinking up to 400 mA for turning ON annunciator lamps e MSG message ON indicates message s active e PTK parallel track ON indicates parallel track is enabled e GPS ON indicates the NMC is not using the GPS sensor for navigation 28 Apollo 2001 Installation Manual Specifications e OBS HLD waypoint sequencing hold ON indicates waypoint sequencing is on hold e APPRCH approach enabled ON indicates the approach has been enabled e ACTIVE approach active ON indicates the approach is active CONTROL INPUTS Take home Connect to ground for normal operation leave open for take home simulation operation Waypoint sequencing hold Connect to momentary button to ground for hold input operation SERIAL INTERFACE RS orali Defined in Appendix E Serial Interface ATA E Defined in Appendix E Serial Interface Specifications RECEIVER PERFORMANCE
35. e 2 places The 2001 can be installed with other annunciators Several possible sources of annunciators are listed on page 44 VDI II Morrow Part eee 428 2011 Manufacturer Mid Continent Instrument Co Inc Manufacturer E inline MD4AO 24 The MD40 24 VDI is useful for vertical navigation guidance from the 2001 when altitude data is available See the instructions provided with the VDI for complete specifications and installation instructions Apollo 2001 Installation Manual Accessories 3 07 2513 CIO EN A eS 0 90 gt dara gt lt 0 23 PUE 0 10 4 40 Threaded insert 2 places Note Recommended rectangular panel cutout 2 44 x 0 94 with appropriate clearance holes for 4 40 mounting screws A 33 Antenna II Morrow Part eere 590 1104 Manufacturer eee eee rennen Aero Antenna Manufacturer eese AT 575 9 The A 33 antenna is a standard accessory item with the 2001 GPS The A 33 includes a built in preamp and has a low profile low drag radome mounted on a die cast aluminum base It has a maximum altitude of 55 000 feet and weighs only 3 9 oz See the installation manual for the A 33 for complete specifications and installation instructions pev ty 0 no
36. e Gasket 0 281 gt B Braid Clamp step 3 0 106 EE Contact step 4 Step 5 c i Slide clamp nut slip washer and vee gasket over end of coax Strip jacket as illustrated Comb out braid Slip braid clamp on and push back against coax jacket Fold back braid wires as illustrated trim to proper length and form over clamp Strip center conductor as illustrated Solder center conductor to contact Insert coax with braid clamp and contact into connector and tighten the clamp nut securely Assembly instructions for straight TNC connector part 162 1060 16 Apollo 2001 Installation Manual Installation C GPS Antenna Red Black Coax 5 amp fuse Red or breaker Black e Avionics Power j In line power filter Ground Ground Take Home Ground MSG GPS PTK OBS HLD APPRCH ACTIVE HOLD VDI Up VDI Down VDI Valid VDI Super CDI R CDI L TO FROM Valid Valid Nav Super Annunciators MSG y GPS OBS HLD APPRCH ACTIVE Pa E Lamp Voltage from Dimmer Circuit Normally open momentary Apollo 2001 switch combined with OBS HLD annunciator p y VDI VDI Up VDI Down Flag Flag
37. ect the ident then press ENT Entry by ident requires that a datacard be installed in the 2001 GPS Operation and Position 2001GPS or 2001TSO with 2022 This checkout is to be completed with the aircraft moved away from hangars and other structures that may obstruct the view of the satellites l 2 di Turn on the 2001GPS or 2001 TSO with 2022 and allow the unit to acquire a position Other equipment should be left off for this part of the test Check the position using the lat lon navigation page Press NAV and rotate the LARGE knob to the lat lon page The lat lon should agree with a known reference position Check the signal reception using the GPS sensor displays in System mode Press SYS rotate the LARGE knob to the POSITION SENSORS page and press ENT Then rotate the SMALL knob to display the GPS info Typical signal levels are 50 or better Turn on other avionics one at a time and check the GPS signal reception to make sure it is not affected For IFR installations check for VHF COM transmitter interference a Verify that 5 to 8 satellites are in DATA and the NAV flag is out of view b Tune the COM to 121 150 MHz and transmit for 20 seconds c Verify that the position is not lost d Repeat for additional frequencies as follows 121 125 MHz 131 225 MHz 121 175 MHz 131 250 MHz 121 200 MHz 131 275 MHz 121 225 MHz 131 300 MHz 121 250 MHz 131 325 MHz 131 200 MHz 131 350 MHz e Repeat for each COM transmitt
38. ection Main DC power input OG d Viewed from rear of mounting frame Notes NC no connection DO NOT CONNECT Apollo 2001 Installation Manual Limitations SECTION 4 LIMITATIONS INSTALLATION For minimum equipment and connections required for IFR and or oceanic remote airspace installations refer to Table 2 Installations are to be made in accordance with AC 20 138 for systems using GPS AC 20 121A for systems using loran C and AC 20 130A for systems using external or multiple position sensors For all Primary Oceanic navigation operations the aircraft must have at least two independent primary navigation systems appropriate to the intended route Each system must have an estimated Mean Time Between Failures MTBF value of at least 1000 hours Note This requirement may be satisfied by the installation of two Apollo 2001 systems OPERATIONAL An approved Aircraft Flight Manual Supplement is required for IFR and or oceanic remote airspace installations Note A sample AFM Supplement is available from Il Morrow listing operational limitations Apollo 2001 Installation Manual 29 Limitations NOTES 34 Apollo 2001 Installation Manual Troubleshooting APPENDIX A TROUBLESHOOTING This appendix provides information to assist troubleshooting if problems occur after completing the installation U
39. ed frequency in range of 000 to 975K Hz in 25KHz steps or 0 to 39 Example Message PMRRCOSIIIT64 cr Input a ground frequency type 121 900M Hz FUEL AIR DATA COMPUTER INPUT The fuel air data input 1s used to input fuel flow and airdata computer information from the Shadin ADC 200 fuel air data computer The format of the fuel air data computer input is as follows which conforms to the Shadin S format serial message Definition of the input message data that the GX50 60 65 uses 1s included in Table 11 A sample input message is illustrated in Figure 14 Bardales aiii 9600 Data bisi 8 STOP DIS te 1 as Expected input rate approx second Message rin variable 512 character max The serial input message string is expected in the following format lt STX gt lt message gt lt message gt lt message gt lt chksum gt lt ETX gt 009 c TS ASCII start of text character STX 02h lt MESSIO E ir starts with an ASCII S then an ID character followed by the message data a carriage return CR ODh and a line feed LF OAh See the following table Apollo 2001 Installation Manual 29 Serial Interface Specifications 54 lt C heck UM the message checksum same format as message SED i an i i ERI ASCII end of text character ETX 03h Table 11 Fuel Airdata Message Data Desig
40. elay 12 pole from Northern Airborne Technology NAT Apollo 2001 Installation Manual Accessories e AIS 80 1 CDI switch unit 8 pole from Avionics International Supply e AIS 12020 remote switch unit 12 pole from Avionics International Supply Several switches that can be used to control the relay and for annunciation include e PBOS switch annunciator from Northern Airborne Technology NAT e Series 582 switch annunciator from Eaton Altitude Encoders amp Converters The 2001 can use altitude data from encoder or converter units that output information on an RS 232 interface Check for the altitude input requirements on page The interface specifications required from the encoder or converter units are included in Appendix E Several altitude encoders compatible with the 2001 include e Part 8800M altitude encoder from Shadin e Model SSD120 RS232C 1 altitude encoder from Trans Cal Several altitude gray code converters compatible with the 2001 include e Part 9000 gray code converter from Shadin e Model IA RS232C 1 interface adapter from Trans Cal e Model 3000U altitude serializer from Icarus 2030 Fuel Air Data Sensor The 2030 Fuel Air Data Sensor provides fuel flow and air data information for the 2001 is intended for remote mounting and connects to the 2001 as part of an Apollo NMS system using NAVNET The 2030 1s available is several configurations depending on type of fuel flow system that it will be connected to For com
41. equires a seed position time and date to initialize the position sensors The GPS sensor requires this to know which satellites to look for The loran sensor requires this to know which loran chains to look for Once this 1s entered it will be saved and updated internally in the 2001 Note If the 2001 1s moved without being turned on the seed position may have to be reentered 1 Enter the current time and date During the startup sequence press SEL when the DATE and TIME page is displayed Rotate the LARGE knob to select different fields rotate the 22 Apollo 2001 Installation Manual Installation SMALL knob to change the information then press ENT to save the changes The time and date can also be changed in System mode Enter the seed position During the startup sequence press SEL when the PPOS page is displayed either the distance to the nearest waypoint or a lat lon will be displayed on the PPOS page The seed position can be input either by lat lon or airport ident a To input the seed by using the lat lon coordinate for the aircraft position rotate the LARGE knob to select different fields rotate the SMALL knob to change the information and press ENT to save the new seed position The seed position should be within 60 nm of the actual position b To input the seed by airport ident rotate the LARGE knob to highlight the reference position ident press ENT use the LARGE and SMALL knobs to sel
42. er f If the 2001GPS is susceptible to VHF COM transmitter interference then better isolation or distance may be required between the GPS and VHF antennas or a notch filter may be required in series with the VHF COM antenna coax Note Older VHF COM transmitters may emit higher levels of harmonic interference causing greater problems that may be more difficult to fix Interface Checks The interfaces to other equipment such as an altitude encoder moving map display or Arinc 429 air data computer should be checked Refer to the Apollo NMS User s Guide for Apollo 2001 Installation Manual 23 Installation operating instructions for this part of the checkout Make sure the other equipment is connected and switched on 1 To check the serial input verify that altitude data from the serial device can be displayed on the 2001 Press NAV rotate the LARGE knob to the ALTITUDE ASSIST page then rotate the SMALL knob to display the encoder altitude 2 To check the serial output verify that the data from the 2001 can be displayed on the other unit such as a moving map display 3 To check the Arinc 429 input verify that the altitude data can be displayed on the 2001 from the Arinc 429 air data computer input Press NAV rotate the LARGE knob to the ALTITUDE ASSIST page then rotate the SMALL knob to display the airdata altitude 4 To check the Arinc 429 output verify that the data from the 2001 can be displayed on the other unit su
43. f the 2001 1s mounted near other equipment that generates significant heat that would cause the 2001 to operate in an ambient environment greater than 55 C for longer than 30 minutes forced air cooling should be provided Refer to the specifications on page for guidance ALTITUDE INPUT Altitude input 1s required for installation of the 2001 for IFR and or oceanic GPS operation It is used by the GPS sensor in the RAIM calculations Altitude input is optional for other installations An altitude input will enable several useful altitude assist features such as altitude preset and hold and 3D airspace alerts Altitude input to the 2001 can be connected using one of the following inputs e serial encoder or converter connected to an RS 232 input e 2030 F ADS connected on NAVNET e asuitable air data computer connected to an Arinc 429 input Apollo 2001 Installation Manual 9 Installation The minimum requirements for the altitude input are listed in the Specifications section on page BO ANTENNA 2001GPS ONLY The 2001 GPS comes standard with the A 33 antenna The A 34 antenna may also be used and is designed to replace II Morrow Loran C antennas The antenna must be mounted on the top of the aircraft with clear visibility of the satellites Shadowing from such items as vertical stabilizers wings other antennas engines or propellers or the aircraft itself should be avoided For complete installation instructions refer to the antenna
44. iable approx 83 to 484 characters The serial output messages are in the following format lt STX gt lt id gt lt data gt lt it gt lt id gt lt data gt lt it gt lt id gt lt data gt lt it gt lt ETX gt do A ASCII start of text character 1 byte 02h UG item designator 1 byte from following table lt dd gt ia item data format listed in following table US ii item terminator Ibyte ODh A ASCII end of text character 1 byte 03h Apollo 2001 Installation Manual 47 Serial Interface Specifications 46 Table 8 Moving Map ASCII Navigation Data ID jDataFormat Length A sddmmhh Present latitude s sign N for north S for south dd degrees mm minutes hh hundredths of minutes sdddmmhh Present longitude s sign E for east W for west ddd degrees mm minutes hh hundredths of minutes mM E Track magnetic ddd degrees Hu speed ddd knots 5 Distance to active waypoint ddddd nm x 10 sdddd 5 Cross track error MER s sign R for right L for left of course dddd distance off course hundredths of nm Tea GENE dddd degrees x 10 Active waypoint identifier ddd dd 2 ASCII waypoint identifier dddd degrees x 10 Magnetic variation s sign E for east W for west ddd degrees x 10 Warnings The 4th character will be an A when the navigation data 1s flagged otherwise all characters will be dashed
45. l data input not available on _ 24 I Powerground Main power connection T Sower Main DC power input N HH DO as A I 30 Gromd____________ Takehomegroundcomection A ING 0 33 O FROM TO FROMflagFROM output 33 O TO JTO ROMflgTO oupu 34 O OBS HLD annunciator Hold annunciator output pulled low to turn lamp on 35 APPRCH annunciator Approach Enabled annunciator output pulled low to turn switch to ground 37 TxD2 Channel2RS 232 serial data output 39 Power Control System power control output connect to power control input on sensor units for remote power on control 40 jArincOuB Arinc429 output B Apollo 2001 Installation Manual 31 Specifications 32 Table 5 Connector Pinout 4 O Arin OwA JArincd20ouputA gt gt 4 O VD JVDledownoupu 43 O VDU jJVDleupouput 44 VDISuperflag HighlevelVDI superflag output pulled high for valid 45 NAV Superflag HighlevelNAV superflag output pulled high for valid 46 GPSAnnunciator GPS in use annunciator output pulled low to turn lamp on 47 MSG Annunciator Message annunciator output pulled low to turn lamp on gt gt PTK Annunciator Parallel Track annunciator output pulled low to turn lamp on Main power ground conn
46. l from the encoder Possible hardware problem expected from encoder indicating a temperature greater than 55 C or if data is invalid Altitude out of range expected from the encoder indicating that the altitude 1s outside specified range of the encoder Altitude in Feet Temperature Sign Internal Temperature Message Checksum Example 1 210 feet above sea level 029 92 gh with temperature of 25 C Altitude in Feet Temperature Sign Internal Temperature Message Checksum Example 2 45 feet below sea level 29 92 gh with temperature of 45 C Example 3 Message Checksum FAL Figure 13 Altitude Data Input Apollo 2001 Installation Manual Indicates encoder is warming up is still below 25 C 51l Serial Interface Specifications APOLLO SL40 COM SERIAL DATA FORMAT AND INSTALLATION INSTRUCTIONS The Apollo 2001 interfaces to the Apollo SL40 in a similar way as the moving map SL40 INSTALLATION CONFIGURATION 1 Connect the SLAO serial line in parallel with the Moving Map display serial line 1f present TxD2 on pin 37 2 Connect the SL40 ground to pin 20 Refer to Figure 10 for example installation 3 Select Map Com as the data output choice for Tx This will cause moving map and com data to be transmitted out pin 37 MESSAGE FORMAT The format of the moving map data output is as follows D aue rale uo er io 9600 DIS M iens 8 STOP DIS ara 1 eit
47. le 9 Figure 12 Moving Map Data Output ALTITUDE ENCODER CONVERTER INPUT The format of the altitude input is as follows Definition of the input message is included in able 10 Several sample messages are illustrated in Bald Tale snai 1200 Data DS sientas 8 SOP DS sala 1 MR Cp none Expected input rate vn approx 1 second Message length 17 characters Table 10 Altitude Input Data ASCII 023h ASCII A 041h ASCII L 04Ch __4__ ______ 0 oS O 5 Pot Altitude sign ASCII or 02Bh or 02Dh ddddd Altitude in feet right justified with leading zeros F or Temperature sign ASCII or 02Bh or 02Dh 13 14 Internal altimeter temperature 15 16 Checksum of bytes thru 14 computed in hex output in ASCII format 1 e FA hex ASCII carriage return 0Dh The altitude input can decode several status or error codes These codes would be in place of the altitude data in characters 5 10 as follows 4 5 ASCII T 054h 7 50 Apollo 2001 Installation Manual 09980 09981 09982 Altitude Sign Altitude Encoder Converter Identifier PAL 002L0T 25D4 Altitude Sign Altitude Encoder Converter Identifier FAL Status Code 00045T 45DE Serial Interface Specifications Heater not ready expected during encoder warm up or if there 1s a loss of signa
48. llation NAVNET or an Arinc 429 input The inputs and outputs may be connected to separate units Seel Figure 10 for typical serial connections Make serial interface connections using shielded 22 AWG two conductor for TxD or RxD and ground connections or three conductor for RxD TxD and ground connections cable The ground lead should be connected to the serial ground pin on the connector and the shield should be connected to the rear of the mounting frame using one of the ground wires supplied Once serial port connections are made the serial ports must be configured This is done during the post installation check out procedure and is included on vage PI Complete serial protocol specifications are included in Appendix E ARINC 429 INTERFACE For 2001 units that include the optional Arinc 429 interface it includes one transmit channel and one receive channel Do not connect to Arinc channel 1 input The Arinc interface can be set to low speed 12 500 bits second or high speed 100 000 bits second See for typical Arinc 429 connections Make Arinc connections using 22 AWG twisted pair shielded cable Connect the shield to the rear of the mounting frame using one of the ground wires supplied Once the Arinc connections are made the Arinc ports must be configured This is done during the post installation check out procedure and is included on page 20 Complete Arinc protocol specifications are included in Appendix E TAKE HOME SENSE I
49. llo 2022 GPS is a high performance GPS sensor with TSO C129a and TSO C115b approvals for supplemental IFR en route terminal and non precision approach and N8110 60 approval for primary oceanic and remote airspace operation The 2022 1s intended for remote mounting and connects to the 2001 as part of an Apollo NMS system using NAVNET It comes complete with a mounting tray and antenna The 2022 1s 5 380 inches H x 1 588 inches W x 8 924 inches L with mounting tray For complete information and specifications on the 2022 contact II Morrow Note The 2022 is not required with the 2001 GPS COMMERCIALLY AVAILABLE 44 The following accessories and equipment are available from sources other than II Morrow Other suitable equipment may also be available that 1s not listed here Although the 2001 1s designed to work with these items it is the responsibility of the installer to ensure the equipment is suitable for the installation including that environmental and airworthiness requirements are met to make proper connections to the equipment and to ensure proper operation is obtained Annunciators There are a number of sources of suitable annunciators besides the module available directly from II Morrow Several sources are e Series 814 from West Coast Specialties e Series 582 from Eaton Switching Relays Several relays suitable for navigation source selection include e RS08 relay 8 pole from Northern Airborne Technology NAT e RSO12 r
50. nformation Appendix B includes PERIODIC MAINTENANCE requirements Appendix C includes the ENVIRONMENTAL QUALIFICATION FORM Appendix D includes information on ACCESSORIES gt 12 yo O gt EN p gt Appendix E includes SERIAL INTERFACE specifications APOLLO 2001 DESCRIPTION The Apollo 2001 Navigation Management Computer NMC 1s the main control display and navigation computer for the Apollo Navigation Management System NMS The 2001 can be used as a multi sensor system with remotely mounted position sensors connected on NAVNET a II Morrow local area network for communicating with remote mounted sensors or as a stand alone GPS navigation receiver Used with either the internal or remotely mounted GPS sensor the 2001 can be used for supplemental IFR en route terminal and non precision approach or primary oceanic remote airspace operation The 2001 includes full Apollo 2001 Installation Manual 1 Introduction navigation capabilities with avionics outputs The 2001 GPS includes an internal GPS sensor Optionally the 2001 can also include Arinc 429 input and output The available configurations of the 2001 are listed in Table 1 Table 1 Apollo 2001 Unit Configurations Model 2001TSO nne 430 02675 2001TSO 429 430 0267 6XX 2001GPS Internal GPS 430 0267 7XX 2001GPS Internal GPS amp Arinc 429 430 0267 8XX Notes The particular configuration option is no
51. nstallations with connections to EFIS displays using the Arinc 429 interface verify that the EFIS is compatible with the variable CDI operation of TSO C129a The Bendix King EFIS 40 50 must have software version 11 or later 56 Apollo 2001 Installation Manual 9 O N AR Y I H N K N G TODAY
52. ode rotate the LARGE knob to the INSTALL OPTIONS page 2 Press SEL rotate the SMALL knob to select IFR operation YES or NO rotate the LARGE knob for APPR selection rotate the SMALL knob to select approach operation YES or NO rotate the LARGE knob to select OCN for Oceanic or Remote airspace operation YES or NO then press ENT when complete Note APPR can only be set to YES when IFR is set to YES Note Make sure that all installation requirements are complete for the selected operation mode Refer to Arinc 429 Output Configuration 1 In test mode rotate the LARGE knob to the ARINC 429 OUTPUT LABELS page to configure the Arinc 429 output 2 Press SEL rotate the SMALL knob to select the desired configuration then press ENT when complete Refer to Appendix E for available selections 3 To set the Arinc 429 output speed rotate the LARGE knob to the ARINC 429 Rx Tx SPEEDS page 4 Press SEL rotate the SMALL knob to select low speed 12 5kbps or high speed 100kbps then press ENT when complete Note Only the TX speed can be changed Note This configuration can only be changed in NMCs with the optional Arinc 429 interface 20 Apollo 2001 Installation Manual Installation Air Data Computer Selection The 2001 can be used with the 2030 F ADS connected on NAVNET or to a compatible Arinc 429 air data computer To select the air data computer 1 In test mode rotate the LARGE knob to the AIRDATA COMPUTER
53. odi SNO300 SOULI SE 03 L0 50000 Ed lt ETX gt wind speed at 15 knots 3 second right turn 50 feet second vertical air speed 359 heading relative to true north 12 3 gallons hour right engine fuel flow 30 0 gallons used right engine 13 1 gallons hour left engine fuel flow 31 0 gallons used left engine no errors Checksum example only not actual end of message string Figure 14 Fuel Airdata Data Input Apollo 2001 Installation Manual Serial Interface Specifications ARINC 429 INTERFACE This optional interface of the 2001 is the standard GAMA General Aviation Manufacturers Association Arinc 429 interface The interface can be set to either low speed 12 500 bits second or high speed 100 000 bits second Instructions for configuring the Arinc 429 interface are included in the checkout procedure on page 20 The Arinc 429 interface configurations supported by the 2001 are listed in Table 12 The input and output labels supported by the 2001 are listed 1n The labels are listed in octal Table 12 Arinc 429 Interface Selections NONE interface does not output or accept inputs Outputs all labels listed in and accepts inputs Table 13 Arinc 429 GAMA Labels 04 Omput Flight Plan ee Crosstrack Distance S Crosstrack Distance Apollo 2001 Installation Manual 25 Serial Interface Specifications Table 13 Arinc 429 GAMA Labels 326 Output A Note For i
54. onment Equipment performance and operation not affected Display filter may degrade by high humidity Operational Shocks and Crash Equipment tested for both operational and crash safety shocks Equipment operates normally during and after both operational and crash safety shocks er Equipment tested without shock mounts to Categories B M Explosion Proofness 90 Equipmentidentified as Category X no test required Fluids Susceptibility Power Input Equipment tested to Categories A B amp Z Momentary Power Interruptions 16 5 2 3 b Interruptions greater than 200msec at 28V 30msec at 14V may cause an automatic equipment reset Voltage Spike Equipment tested to Category A Audio Frequency Conducted 18 0 Equipment tested to Categories A B and Z Susceptibility Power Inputs Radio Frequency Susceptibility 20 Equipment tested to Category U Contiene emeret __ Emission of Radio Frequency 21 Equipment tested to Category Z i Safety Lightning Direct Effects Equipment identified as Category X no test required Icing Equipment identified as Category X no test required Remarks Apollo 2001 Installation Manual 39 Environmental Qualifications NOTES 40 Apollo 2001 Installation Manual Accessories APPENDIX D ACCESSORIES This appendix includes information on accessory items available for the Apollo 2001 Refer to the information that comes with these items for complete specifications and ins
55. passive terminator 00 2134 NAVNET cable 61 1060 00 Compliance certificate 2 1 1 N N gt E NO O gt c in A em Sy o em dt N QN K O O UA T bd 55 0500 60 0161 xx 60 0164 xx 60 9005 61 0228 xx Apollo NMS quick reference guide 65 1029 61 1039 xx l 48 1033 1 18 0203 l 60 0949 64 0057 xx l 590 1100 jJA33anena 1 560 5047 jA 34Instalation Guide approved alternate 590 1112 jA 34Antenna approvedalternate OTHER REQUIRED MATERIALS Additional items required for an IFR and or oceanic installation of the 2001 are as follows e Annunciators with the legends as defined in the Avionics Outputs specifications on page e CDI or HSI can be shared with existing nav equipment if connected through a relay switching network or an EFIS display e Relay switching and NAV NMS selector switch if using a shared CDI or HSI e A remote sensor if installing the 2001 TSO N m Current FAA guidelines for installation approvals should be available for reference e AC 20 130A multi sensor systems e AC 20 138 GPS installations e AC 20 121A Loran C installations S Apollo 2001 Installation Manual Installation SECTION 2 INSTALLATION This section describes the installation of the Apollo 2001 including mounting wiring and connections A post installation check out procedure is included at the end of this section PRE INSTALLATION INFO
56. plete 1nformation and specifications on the 2030 contact Shadin the manufacturer The 2030 1s available in the following configurations from Shadin Airdata Computer DF 962800 1 3 55 digital fuel flow Airdata Computer AF 962800 3 3 55 analog fuel flow Airdata Computer RF 962800 4 3 55 RF fuel flow Airdata Computer SF 962800 2 3 55 sine wave fuel flow Note Previous 2030 air data computers from Morrow are also compatible with the 2001 Accessory Vendors For West Coast Specialties annunciators West Coast Specialties Phone 206 392 3118 1105 12th Ave N W Suite 7 Bldg A Fax 206 391 0535 Issaquah WA 98027 For Eaton annunciator switches Airtechnics Inc Phone 316 267 2849 230 Ida 800 544 4070 Wichita Kansas 67211 Fax 316 267 1482 Apollo 2001 Installation Manual 43 Accessories 46 Avionics International Supply Inc 4389 Westgrove Dallas TX 75248 For relay switch units Avionics International Supply Inc 4389 Westgrove Dallas TX 75248 Northern Airborne Technology 1925 Kirschner Road Suite 14 Kelowna B C Canada VIY 4N7 For altitude encoders and gray code converters Shadin Company Incorporated 6831 Oxford Street St Louis Park Minnesota 55426 Trans Cal Industries Inc 16141 Cohasset Street Van Nuys CA 91406 Icarus Instruments Inc 7585 Washington Blvd Suite 108 Baltimore MD 21227 Phone 214 248 2233 800 553 2233 US Fax 214 250 2794 Phone 214 248 2233
57. se Table 6 to assist in troubleshooting Table 6 Troubleshooting Guide The 2001 does not power on The unit is not getting power Check power connections fuses and main avionics switch NAVNET checkout fails Test not conducted correctly or Make sure all other NMS equipment improper connections or terminators is turned off and only one NMC is connected to NAVNET when testing Make sure one passive terminator is installed at each end of NAVNET cable and double check connections at each unit The 2001 does not compute a Not receiving signals or incorrect Make sure a correct position and position seed position time and date time date have been entered Check antenna connections Make sure the aircraft is clear of hangers buildings trees etc Signal levels are very low Improper antenna installation or coax Check antenna installation routing connections and cable routing The GPS antenna must be mounted on the top of the aircraft hangers buildings trees etc RF interference at 1575 42MHz from Move GPS antenna further from COM antenna Add 1575 42M Hz notch filter in COM coax Fix or replace COM Signal levels drop when Noise interference from avionics Turn all avionics OFF then turn on avionics are powered on each piece of equipment one at a time to isolate the source of interference Route cable and antenna away from sources of interference NAVNET sensors power control connections Incorrect NAVNET addresses
58. tallation instructions FROM Il MORROW The following accessories and equipment are available from II Morrow Annunciators These Apollo ACU annunciators provide the required annunciation for IFR en route terminal and non precision approach operation See the instructions provided with the annunciator module for complete specifications and installation instructions Apollo ACU GPS NAV Annunciation Control Unit II Morrow Part 430 6080 000 14 VDC Horizontal 430 6080 100 14 VDC Vertical 430 6080 200 28 VDC Horizontal 430 6080 300 28 VDC Vertical NAV MSG OBS O GPS PTK HLD ACTV TEST A Horizontal Vertical Apollo 2001 Installation Manual 41 Accessories 42 Annunciators IL Morrow Part i seventeen eren 145 2105 Wan aC CURSE cuna West Coast Specialties Manol Ic Urei T oven E Denon ote 90 81421 1 These annunciators provide the required annunciation for the 2001 for IFR en route terminal and non precision approach operation The module is standard with 28 volt bulbs and includes a wiring pigtail See the instructions provided with the annunciator module for complete specifications and installation instructions Momentary push button y A MSG WPT SEQ APPRCH GPS OBS HLD ACTIVE 0 74 Na lt 2 11 id 4 40 floating locking 2 43 gt nut plat
59. tallation Manual 13 Installation Once the antenna mounting location has been prepared route a coax cable from the antenna to the 2001 GPS Proper selection of coax cable and assembly of connectors is critical to GPS signal performance The cable loss from the antenna to the 2001 GPS should be limited to a maximum of 4 dB Minimize the coax length for optimum performance and DO NOT coil excess cable Leave only enough for service loops When selecting a coax cable select coax cable with 50 ohms impedance and a signal loss less than 4 dB A TNC connector is required at the antenna and the right angle panel mount connector supplied is required at the 2001 GPS The vendors listed in can prepare cables in custom lengths with connectors 1f desired Because the cables listed have different diameters consult with the vendor for proper connectors Table4 Alternative Coax Cables Cable Length feet Part Number Loss OD inches Weight Good Better Best dB 100ft Ibs 100ft 4 dB loss 3 dB loss 2 dB loss Electronic Cable Specialists 1 800 ECS WIRE FAX 414 529 5505 Sio 724 0517 86 54 40 26 __ 31080 488 04532 150 80 60 39 PIC Wire amp Cable 1 800 742 3191 FAX 414 246 0450 855312 66 030 82 6G 46 32 ppp The coaxial connectors and adapters such as TNC to BNC add additional loss to the cable and should be considered when computing the maximum 4 dB loss A typical loss of 0 2 dB
60. ted by the 5 6 7 or 8 in the suffix of the part number The XX is used to denote the version of the unit Complete database capabilities are part of the Apollo NMS system using II Morrow Flybrary datacards programmed with up to date data on airports approaches VORs NDBs intersections and restricted airspace Contact II Morrow for the latest information on available datacards and revision service A block diagram of the Apollo NMS system is illustrated in VDI CDI HSI Autopilot E Annunciators Avionics Outputs RS 232 Serial Interface Apollo 2001 Arinc 429 NN Interface Moving Map Fuel Flowmeter Altitude Encoder Converter Fuel Air Data Computer Air Data Computer 2030 Fuel Air Data Sensor EFIS 70 DOD Notes The 2001GPS does not require the 2022 GPS sensor The 2010TSO loran sensor is optional when using GPS The 2030 F ADS is available from Shadin Figure 1 Apollo NMS Block Diagram Apollo 2001 Installation Manual Introduction FEATURES Features of the Apollo NMS include e Modular design allows connection of one or more NMCS and one or more remote sensors for co pilot convenience and system redundancy e System configuration can be customized to suit individual requirements e The system can be upgraded in the future Apollo 2001 features include e Non precision approach operation with a TSO C129a GPS sensor internal or remote Direct To n
61. tion Refer to the User s Guide for operating instructions Skip the steps that are not applicable to a particular installation A checkout log sheet is included on page 24 to fill out during the checkout procedure Make a photocopy of the log sheet for ease of use 1f desired The ihe and the portions of the post installation checkout should be completed with the aircraft moved clear of hangars and other structures TEST MODE CHECKOUT AND SETUP The 2001 has a built in test mode to simplify the checkout To operate the 2001 in the test mode hold down the NAV and SYS buttons while switching on the power To return to normal operation switch the power off then back on Avionics Outputs Check the avionics output connections by using the test mode as follows Rotate the LARGE knob to select each test 1 Using the CDI TRIANGLE page rotate the SMALL knob to check left mid and right 2 Using the VDI TRIANGLE page rotate the SMALL knob to check down mid and up 3 Using the To FROM FLAG page rotate the SMALL knob to check the Off To and From outputs 4 Using the LAMP OUTPUTS page rotate the SMALL knob to check all annunciators 5 Using the VALID FLAG PAGES page rotate the SMALL knob check all valid flag outputs Installation Configuration The NMC must be configured to match the operation supported by the installation This includes IFR VFR approach and oceanic remote operation selections 1 In test m

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