Garmin 174 GPS Receiver User Manual
Contents
1. J100 J521 PS25A1 P2021 P2061 40 1 GPS D BAR LEFT a N v N N 2 11 11 20 5 GPS D BAR RICHT M B d 1 12 12 21 3 D GPS FLAG s K N N 7 7 48 4 ors Fuc T F F F 8 8 3 6 GPS FROM T s s 4 10 10 42 2 ers 1 2 3 9 9 43 KI 229 2291 7 GPS OBI CLOCK S 12 8 GPS OBI DATA 19 23 GPS OBI SYNC 11 ARGUS STORMSCOPE SHADIN BECT GARMIN SERIES INTL 3000 5000 7000 En n Hy pao 91204 910531 962801 pw j GPS 195 605 II 24 AH 85232 TX DATA 16 16 16 5 9 H 5 16 5 DATA IN RS232 TX DATA LOW 4 4 4 3 2 D 9 SHELL 1 GND ELECT EM SHADIN COMPANY _ wre 3000 88001 9000T 92007 91204 91053 962801 FC 10 10 FP 5L 17 A 5232 RX DATA HI 2 7 7 7 6 J 6 2 2 15 85232 RX DATA LOW SHELL 15 15 15 2 D 9 4 4 SHELL 19 85232 TX DATA GARMIN NMEA 0183 PC SOFTWARE COMPATIBLE 85232 TX DATA LOW MAPPING DEVICE i ga NN SUPER FLAG 7 10 NAV SUPER FLAG 500 mA Source 20 MESSAGE LOW 500 mA Sink 0 POWER OR DIMMER BUSS 12 ARRIVAL ALARM LOW 500 mA Sink 0 POWER OR DIMMER BUSS EFIS or other 15 ARINC 429 OUT B ARING 429 16 ARINC 429 OUT A compatible device See note 1 B A 25 AIRCRAFT POWER 10 33 VDC ps o A C POWER 26 NOTES 1 THE FAA HAS EVALUATED THE ARINC 429 INTERFACE WITH A BENDIX KING EFIS 40 AND FOUND IT TO BE2. 1 1 Ensure the Arrival Annunciator is OFF ON Ensure the Arrival Annunciator is ON Select the Power Test Page by removing the cursor from the Annunciator Test Page and turning the outer knob one detent to the right Verify the following status is displayed Using EXTERNAL POWER Memory Batt OK Intrnl Batt OK Note Depending on the power source for the unit aircraft wall charger or internal battery and the status of battery charging the top line may read Battery power charger power external power Turn the GPS 150 off in preparation for a signal acquisition test The following tests assume that the aircraft is outside the hangar facility and well away from buildings or other obstructions that might interfere with satellite signal reception With power applied to the aviation rack turn the GPS 150 on The Self Test Page will be displayed followed by the Data Base Page Upon approval of the Data Base Page the Satellite Status Page will be displayed If unable to acquire satellites relocate the aircraft away from obstructions which might be shading reception If the situation does not improve check the antenna installation Once GPS position information is available use the DIRECT key to activate the navigation function to a nearby NAVAID intersection or airport Ensure the ARGUS STORMSCOPE EFIS fuel management system or other mapping device is receiving data from the GPS 150 and is functionin
3. 2 d Q OU Ke SECTION 3 59 U9 59 C A DH SECTION 4 SECTION 5 APPENDIX APPENDIX B APPENDIX C TABLE OF CONTENTS GENERAL DESCRIPTION INTRODUCTION TECHNICAL CHARACTERISTICS PHYSICAL CHARACTERISTICS OPERATIONAL CHARACTERISTICS INTERFACES INSTALLATION CONSIDERATIONS ANTENNA CONSIDERATIONS SATELLITE VISIBILITY NOISE SOURCES ELECTRICAL BONDING ANTENNA LIMITATIONS VHF COMM INTERFERENCE RACK CONSIDERATIONS ACCESSIBILITY CABLING AND WIRING COOLING AIR ANNUNCIATORS EXTERNAL ALTITUDE INPUT INSTALLATION PROCEDURE INSTALLATION ACCESSORIES ANTENNA INSTALLATION CABLE INSTALLATION RACK INSTALLATION GPS 150 INSTALLATION AND REMOVAL PLACARD CHECKOUT PROCEDURE CONTINUED AIRWORTHINESS INSTALLATION DETAILS FOR BEECH V35B CONNECTOR CHANGES STC PERMISSION Av Kit Install Manual 190 00026 00 Rev Q Page 3 FIGURE E 1 1 1 1 V 0290 09 C9 b2 b2 1 DH BE gt gt gt gt 1 Av Install Manual 190 00026 00 Rev Q Page 4 LIST OF ILLUSTRATIONS PINOUT DEFINITION INTERCONNECT SCHEMATIC ANTENNA INSTALLATION CONSIDERATIONS GPS INSTALLATION CONSIDERATIONS STUD MOUNT GA 56 INSTALLATION FLANGE MOUNT GA 56 INSTALLATION COAX CABLE INSTALLATION AVIATION RACK DIMENSIONS AVIATION RACK INSTALLATION FUNC
4. ARMIN GPS 150 INSTALLATION MANUAL GARMIN INTERNATIONAL INC PART NUMBER 190 00026 00 1200 151st STREET REVISION Q 3 APRIL 1998 OLATHE KANSAS 66062 3426 Av Kit Install Manual 190 00026 00 Rev Q Page 1 Copyright 1992 1998 Garmin Corporation All Rights Reserved This publication is the proprietary property of Garmin International Inc It may not be reproduced or transmitted in any form whether printed or electronic without the expressed written consent of Garmin International Garmin International Inc 1200 15154 Street Olathe Kansas 66062 3426 U S A REVISION RECORD 2264 Rev E 25 June 1993 Change Section 3 1 to reflect accessory configuration Rev 23 July 1993 Reverse Pin locations on Fig 1 1 Rev G 18 Aug 1993 Add Altitude Serializer interface details Rev H 15 Oct 1993 Remove Warning Low from Pin out improve Super Flag description add rack dimension 12 Sept 1994 Chg designation to pin 12 on arrival alarm annunciator K 30 Dec 1994 Add additional fuel flow options remove old antenna options add 56 antennas 28 June 1996 Chg to barrel type crimp conn 21 Jan 1997 Correct Database Option Numbers 10 Dec 1997 Add additional antenna install instructions 28 Jan 1998 Chg to from voltages install dwg 3 April 1998 Misc chgs Av Kit Install Manual 190 00026 00 Rev Q Page 2 SECTION 1 WON
5. C FROM 1 FLAG COMMON C FLAG tte lt L POWER IN lt _ RIGHT A COMMON 1 COMMON LEFT LEFT TU 2 TD LA HSI IL L 23 n COMMON _ GPS 150 S 2 ol FLAG 3 FLAG eZi 1 LA 2i COMMON ca Y CELA 4 C FLAG Tl LS che ni st NAV1 ON HSI 25 POWER IN WHEN LIT WHEN LIT NO NO o GND AUTO PILOT wa le X TRANSFER ge tea MESSAGE ACTIVE __ A I F I I 9 1 4 522 anes CIRCUIT BREAKER ENABLE lt lt 3 RADID BUSS ayin n n 16V 1 A 3 I Q NORMAL DIM 1039 Lab 1 I e NAV1 l I CIRCUIT BREAKER P Oi BUSS L3c L3df I I _ Bar NOTES 1 GPS CIRCUIT BREAKER TO BE MS26574 3 OR EQUIVALENT TRANSFER SWITCH SD TO BE AEROSPACE OPTICS 95 43 15 B6 58823 OR EQUIVALENT ANNUNCIATOR LAMPS L1 AND L2 ARE PART OF TRANSFER SWITCH SI 4 MESSAGE ANNUNCIATOR 132 TO BE AEROSPACE OPTICS 95 40 17 H6 58824 OR EQUIVALENT 5 ALL WIRING TO BE 24 AWG UNLESS OTHERWISE NOTED FIG A 4 WIRING DIAGRAM Av Kit Install Manual 190 00026 00 Rev Q Page 27 APPENDIX CONNECTOR CHANGES STAMPED CONTACT CONNECTOR USAGE Garmin panel mount GPS radios have previously been shipped with stamped crimp type contacts All products are now being shipped with machined mil spec contacts with color coded barre
6. adequate depth for the rack in the instrument panel A location away from heating vents or other sources of heat generation is optimal Figure 2 2 illustrates a typical aviation rack installation 2 3 CABLING AND WIRING The recommended antenna cable type is M17 155 0001 RG 58A U per MIL C 17 Maximum allowable length for this cable type is 40 feet Other cable types with 50 ohms nominal impedance and longer lengths can be used provided the installer insures that the attenuation does not exceed 10dB at 1 5 GHz for the specific installation Check that there is ample space for the cabling and mating connectors Avoid sharp bends in cabling and routing near aircraft control cables 2 4 COOLING AIR Cooling air is not required for the GPS 150 however as with any electronic equipment reduced operating temperature can contribute to increased reliability Additionally location of the GPS 150 in a stack of other power dissipating equipment can produce unacceptably high ambient air temperatures around the unit A 5 8 inch diameter air fitting is provided on the rear of the mounting rack for the purpose of admitting cooling air under such conditions 2 5 ANNUNCIATORS If the installation includes any electrical interface with other flight instruments an annunciator may be required Refer to current FAA directives 2 6 EXTERNAL ALTITUDE INPUT Pressure altitude input from an external source may benefit GPS 150 system performance during times o
7. INSTALLATION Av Kit Install Manual 190 00026 00 Rev Q Page 19 T Fr L a dd N S EE ID nn o 2 I e CI Q No W n Dg X oo S 3 S ba Li Lob 3 000 76 20 COG 6 348 161 24 S I u 3 T14 8 ou a o fe por a 8 lt R H 3543 89 99 v a 0 437 11 10 NM mum 5 642 143 30 ox CI Av Install Manual 190 00026 00 Rev Q Page 20 6 792 172 531 FIGURE 3 4 AVIATION RACK DIMENSIONS COG FIGURE 3 5 AVIATION RACK INSTALLATION Av Kit Install Manual 190 00026 00 Rev Q Page 21 APPENDIX A INSTALLATION DETAILS FOR BEECH V35B 1 0 INTRODUCTION This appendix provides airframe specific information which is necessary to install the GARMIN GPS 150 navigation system in the Beech Bonanza Model V35B in accordance with STC SA00066WI See Appendix for copy of STC When so installed the GPS 150 system is approved for use as a supplementary navigation system under Visual Flight Rules VFR only A functional block diagram of the system is shown in Figure 1 The information provided herein is to be considered supplemental to the information contained in the GARMIN GPS 150 Aviation
8. Kit Installation Manual P N 190 00026 00 Within this appendix the base document will be referred to as the Installation Manual 2 0 INSTALLATION INSTRUCTIONS 2 1 ANTENNA The GPS 150 antenna is to be installed on top of the cabin on the aircraft centerline at fuselage station 130 Figure A 2 illustrates the proper antenna positioning Refer to section 2 1 of the Installation Manual for general antenna mounting requirements 2 2 AVIATION RACK INSTALLATION The GPS 150 aviation rack is to be installed in the instrument panel radio rack as shown in figure A 3 The controls and display of the GPS 150 must be readily visible to the pilot when seated at the controls To install the aviation rack position it in the instrument panel in the desired position assuring that the front is not twisted out of square Match drill the flanges on the radio rack to the installation holes on the GPS 150 aviation rack Using 4 each 6 32 screws and self locking nuts attach the aviation rack to the aircraft panel For additional information refer to the Installation Manual 2 3 WIRING Fabricate an appropriate cable to connect the GPS 150 aviation rack to 28VDC power a message annunciator a remote switch for selecting between GPS and standard navigation equipment a transfer switch with integral white illuminated annunciators with black markings to control and indicate the status of the remote switch Wiring connections are to be made in accordance
9. with Figure A 4 Breaker locations are to be as shown in Figure A 3 Route and connect the wiring in accordance with Advisory Circular AC 43 13 2A After the wiring installation is complete carefully check the operation of all flight controls throughout their range to assure that no operational interference exists Av Kit Install Manual 190 00026 00 Rev Q Page 22 2 4 PLACARDS After completion of the GPS 150 system installation affix durable placard the instrument panel in the location shown in Figure A 3 which states GPS limited to VFR use only GARMIN placard p n 161 00024 00 or an appropriate equivalent should be used for this purpose 3 0 OPERATIONAL CHECKOUT When the installation is complete conduct a post installation checkout as specified in section 4 of the Installation Manual being sure to check the proper operation of all connected instruments 4 0 RETURN TO SERVICE After installation a new weight and balance must be computed to show the GPS 150 components The aircraft should then be returned to service by completion of FAA form 337 by an appropriately certificated person 5 0 CONTINUED AIRWORTHINESS Maintenance of the GPS 150 is on condition only Periodic maintenance of the GPS 150 is not required Av Kit Install Manual 190 00026 00 Rev Q Page 23 YOLVIONANNY J YSSIN 49 Sd9 YOLVIONANNY GNV HOLIMS 599 1 AVN AVN OGL 549 NINYVS HOLIMS AV 133 STI YOA FIG 1 FU
10. 0 is limited to VFR use must be installed on the panel in clear view of the pilot The placard may be Garmin p n 161 00024 00 as supplied with the unit or a suitable equivalent SECTION 4 CHECKOUT PROCEDURE The GPS 150 ground test procedure incorporates a series of four 4 display pages to test CDI flag OBI annunciator and power functions of the unit These pages can be selected by ensuring the flashing cursor is off and rotating the outer knob either direction To change data on the displayed test page depress the CRSR key and the cursor will begin flashing on the first selectable field on the page The inner knob will change data on the selected field The ENT key or the outer knob will advance to the next field on the page Pressing the CRSR key again will stop the current field from flashing allowing the outer knob to select the next test page see Chapter 2 of the GPS 150 Pilot s Guide for more information on page and data selection Av Kit Install Manual 190 00026 00 Rev Q Page 11 With power applied to the aviation rack the GPS 150 unit off continuously depress the ENT key and turn the unit on release the ENT key when the display activates Rotate the outer knob and the CDI Test Page will be displayed Using the controls on the GPS 150 front panel make the selections indicated below and verify the interfaces as appropriate CDI Full scale left Ensure the CDI is deflected full scale left 5 dots Full scale right En
11. 320 x 2 000 hole in the instrument panel Exercise caution when installing the rack into the instrument panel The rack is designed to facilitate removal of the GPS 150 for portable use Deformation of the rack may make it difficult to install and remove the GPS 150 B Install the rack in the aircraft panel using four 6 32 countersunk screws and four self locking nuts The screws are inserted from the inside through the holes in the sides of the rack see Figure 3 5 3 5 GPS 150 INSTALLATION AND REMOVAL The GPS 150 is installed in the rack by sliding it straight in until about I inch short of the final position A 3 32 inch hex drive tool is then inserted into the access hole at the bottom of the unit face Rotate the hex tool clockwise while pressing on the left side of the Bezel until the unit is firmly seated in the rack It may be necessary to insert the hex drive tool into the access hole and rotate the mechanism 90 counter clockwise to insure correct position prior to placing the unit in the rack To remove the unit from the rack insert the hex drive tool into the access hole on the unit face and rotate counter clockwise until the unit is forced out about 3 4 inch and can be freely pulled from the rack Be sure not to over tighten the unit into the rack The application of hex drive tool torque exceeding 15 in lbs can damage the locking mechanism 3 6 PLACARD After completing the installation a placard stating that the GPS 15
12. ACCEPTABLE OTHER EFIS INSTALLATIONS WOULD REQUIRE FAA EVALUATION FIGURE 1 2 INTERCONNECT SCHEMATIC Av Kit Install Manual 190 00026 00 Rev Q Page 15 Antenna masked by vertical fin T tail or dorsal fin Antenna must be on top of aircraft FIG 2 1 ANTENNA INSTALLATION CONSIDERATIONS Maintain 6 16 cm compass safe distance van ago LIC 2 2 GPS INSTALLATION CONSIDERATIONS Av Kit Install Manual 190 00026 00 Rev Q Page 16 011 00134 00 ANTENNA AVIATION CA56 FORWARD aa 253 00002 00 GASKET NEOPRENE AIRCRAFT SKIN ON TOP OF FUSELAGE 115 00031 00 BACKING PLATE 210 10004 09 48 32 SELF LOCKING NUT 4 PLCS co Si Z N 2 59 65 8 4 23 107 44 8 EN NN i i I LOT BNC CONNECTOR SIDE VIEW FRONT VIEW v o x O Jw 0 813 20 64 2 PLCS p SI I L N Li 7 Lu e 0 188 4 78 4 PLCS T 1 A l 2 P 20 575 5 FORWARD e A N 4 1 N k 2 600 66 04 REF MOUNTING CUTOUT FIG 3 1 STUD MOUNT GA 56 ANTENNA INSTALLATION Av Kit Install Manual 190 00026 00 Rev Q Page 17 211 62212 14 10 32 FHP X 625 LG 4 PLCS FORWARD 011 00147 00 GAS6 ANTENNA FLANGE MOUNT 255 0001 1 00 GA
13. NCTIONAL BLOCK DIAGRAM Av Kit Install Manual 190 00026 00 Rev Page 24 Q Cin llo 141 24 ARM MOMENT 66 130 32 50 WEIGHT bs 2 14 0 25 UNIT LOW PROFILE ANTENNA GPS 150 F S 130 00 F S 66 0 GPS150 FIG A 2 FUSELAGE STATIONS AND WEIGHT AND BALANCE DATA Av Kit Install Manual 190 00026 00 Rev Q Page 25 1 SDVSSSW 549 H LIAS WI IVW IJLIAS daaSNVdl ISH ISH O O O O O OOO O O OOO 0 0 ds 9 OOO O OO O O OOO O O O O O Qo 6 C No 549 DSW T AWN Sd5 we 84 ad OSI 549 NIWAVD FIG A 3 PANEL LAYOUT AND BREAKER LOCATION Av Kit Install Manual 190 00026 00 Rev Page 26 9 RIGHT COMMON LEFT TO COMMON
14. Q Page 30
15. S DATABASE MEMORY CARD INTERNATIONAL DATABASE MEMORY CARD WORLDWIDE DATABASE MEMORY CARD USER MISCELLANEOUS OPTIONS 190 00048 00 190 00048 01 330 00067 00 362 00010 00 GPS 150 PILOT S GUIDE GPS 150 QUICK REFERENCE GUIDE GPS 1 57542 GHZ NOTCH FILTER WALL CHARGER 110 220VAC 3 2 ANTENNA INSTALLATION The GA 56 Antenna outline and footprint dimensions are shown in Figures 3 1 and 3 2 A Using the backing plate as a template mark the location of the mounting holes and the through hole for coax cable Drill or punch the holes B The antenna installation must provide adequate support for the antenna considering a maximum drag load of 5 lbs for the GA 56 antennas at subsonic speed a doubler plate to reinforce thin skinned aircraft Install Observe guidelines for acceptable installation practices as outlined in AC 43 13 2A C Seal the antenna and gasket to the fuselage using a good quality electrical grade sealant Use caution to insure that the antenna connector is not contaminated Av Kit Install Manual 190 00026 00 Rev Q Page 9 with sealant Insure that the mounting screws are fully tightened and that the antenna base is well seated against the gasket CAUTION Do not use construction grade RTV sealant or sealants containing acetic acid These sealants may damage the electrical connections to the antenna Use of these type sealants may void the antenna warranty 3 3 CABLE INSTALLATION R
16. SKET NEOPRENE AIRCRAFT SKIN ON TOP OF FUSELAGE 115 00080 00 PLATE Ke e a 4 43 112 52 5 4 23 107 44 boa dL 1 gt ae SIDE VIEW BNC CONNECTOR FRONT VIEW S u pu oo 1 850 47 00 d 0 925 23 50 I gp gt 90188 4 78 4 PLCS l I ti FORWARD I 20 575 14 60 9 MOUNTING CUTOUT FIGURE 3 2 FLANGE MOUNT GA 56 ANTENNA INSTALLATION Av Kit Install Manual 190 00026 00 Rev Q Page 18 GASKET NUT 1 PLACE AND GASKET CABLE AND STRIP JACKET TO DIMENSION SHOWN 1h 2 COMB OUT BRAID AND TRIM DIELECTRIC 1 DIMENSION SHOWN 114 3 PULL BRAID WIRES FORWARD AND TAPER TOWARD CENTER CONDUCTOR PLACE CLAMP OVER BRAID AND PUSH BACK AGAINST CABLE JACKET 4 FOLD BACK BRAID OVER CLAMP AS SHOWN TRI FF EXCESS BRAID SOLDER CONTACT TO CENTER CONDUCTOR 5 INSERT CABLE CLAMP AND GASKET INTO CONNECTOR BODY MAKING SURE THAT SHARP EDGE CLAMP SEATS PROPERLY AND TIGHTEN NUT FIGURE 3 3 COAX CABLE
17. TIONAL BLOCK DIAGRAM FUSELAGE STATIONS AND WEIGHT BALANCE DATA PANEL LAYOUT AND BREAKER LOCATION WIRING DIAGRAM SECTION 1 GENERAL DESCRIPTION 1 1 INTRODUCTION This manual describes the physical mechanical and electrical characteristics and the installation requirements for the GPS 150 Aviation Kit After installation of the GPS 150 system FAA Form 337 must be completed by an appropriately certificated agency to return the aircraft to service 1 2 TECHNICAL CHARACTERISTICS The GPS 150 offers the versatility of fixed installation in a panel mounted aviation rack as well as complete portability 1 2 1 PHYSICAL CHARACTERISTICS Width 6 25 Inches Height 2 inches Depth 5 65 inches GPS 150 Weight 2 14 Ibs GA 56 Antenna Weight 4 oz Aviation Rack Weight 14 oz Max Air Speed Subsonic Structural rating for antenna 1 2 2 OPERATIONAL CHARACTERISTICS Operating Temperature Range 20 to 55 C Humidity 95 non condensing Altitude Range 1 500 to 50 000 ft Power Input 10 to 33 VDC 5 watts Max 1 2 3 INTERFACES The GPS 150 provides interfaces to various general aviation instruments Figure 1 1 defines the function of each pin on the 37 pin DSUB connector located at the back of the rack Figure 1 2 depicts the interconnects between the rack and other instruments The following interfaces are provided CDI Capable of driving up to three 1000 ohm parallel Pins 1 and 5 loads 150 millivolts full scale def
18. del V35B Z pmo Charge In amp tallation of GARMIN Global Positioning System GPS 159 Data Required 1 GARMIN Master Drawing List 005 00007 00 Reviaion A dated May l 1993 2 GARMIN Jnternational Inc Drawing No 190 D0025 00 Revision A dated May 24 1993 or later approved revisions of 41 or 21 P This approval should not be extended to other specific airplanes cf this model on which other previously approved modifications are incorporated unless it is determined by thc installer that the interrelatiouship between this change and any cf those other previously approved modifications will introduce no adverse effect upon the airworthiness of that airplane This m ads andthe an fermer aic a ho batis fer ford shall renani dev pr a dune vendred tesi maa ora erri an a tv olbanssite aa ael dye the Dena of the and baden rrr ntis S eu December 23 1992 Konte May 24 1993 T ute arse rested By direction of the Py Rathg hEr acting Manager ichita Aircraft Certification Office Fitie _ 6 alteration af this certificate it punishable o fine of met exceeding 21 200 ar imprisonment not ezezeding 3 years o balh 7246 certificate ma by ram ferr d mi accirdancr wuih FAR 21 42 FA toau 8110 2 119 0 Av Kit Install Manual 190 00026 00 Rev
19. f minimal satellite coverage or poor satellite geometry Provisions for RS 232 compatible serial altitude input are described in the Interfaces section Section 1 2 3 of this manual Av Kit Install Manual 190 00026 00 Rev Q Page 8 SECTION 3 INSTALLATION PROCEDURE 3 1 INSTALLATION ACCESSORIES The following installation accessories are available ANTENNA AND RACK OPTIONS 010 10040 01 010 10040 02 011 00059 00 310 00006 00 320 00003 00 320 00003 02 325 00014 00 330 00087 00 011 00313 01 GA 56 LOW PROFILE ANTENNA KIT Stud mount GA 56 antenna mounting hardware no cable GA 56 FLANGE MOUNT ANTENNA KIT Flange mount GA 56 antenna mounting hardware no cable MOUNTING RACK w CONNECTOR RG 58A U CABLE 15 FT LOW LOSS AVIATION ANTENNA EXTENSION CABLE w RIGHT ANGLE BNC CONN 30 FT LOW LOSS AVIATION ANTENNA EXTENSION CABLE w RIGHT ANGLE BNC CONN GPS 100 to GPS 150 WIRING HARNESS ADAPTER CONNECTOR BNC MALE CLAMP CONNECTOR J1 only KIT The mounting rack is required for approved installations The following hardware is required for installation of the mounting rack but is not provided 6 32 Flat Head Screw 4 ea 6 32 Self locking Nut 4 ea Cable and two BNC connectors are required to make the antenna cable or it can be fabricated by the installer from materials meeting the requirements of paragraph 2 3 DATA BASE OPTIONS 010 10038 00 010 10038 01 010 10038 02 010 10032 03 MEMORY CARD AMERICA
20. g properly see Chapter 5 of the GPS 150 Pilot s Guide for more information on the Direct function Av Kit Install Manual 190 00026 00 Rev Q Page 13 J101 PIN NO 1 D BAR LEFT 2 3 FLAG 4 FLAG 5 D BAR RIGHT 6 FROM 7 BI CLOCK 8 BI DATA 9 not used 10 NAV SUPER FLAG 11 RESERVED ARRIVAL ALARM LOW 3 RESERVED 4 not used 5 ARINC 429 OUT 6 ARINC 429 OUT A 7 RS23e 1 8 RESERVED 9 RS23e OUT 2 20 MESSAGE LOW el RESERVED 22 RESERVED 23 BI SYNC 24 RS232 OUT 25 AIRCRAFT POWER 10 33 VDC 26 GROUND 27 not used 28 RESERVED 29 RESERVED 30 RESERVED 31 RESERVED 32 RESERVED 33 RESERVED 34 RESERVED 35 ot used 36 RESERVED 37 RESERVED FIGURE 1 1 PINOUT DEFINITION Kit Install Manual 190 00026 00 Rev Q Page 14 YUMA Oo 520 525A 202 206 MCI GI 102 106 209A
21. lection with a maximum output of 300 millivolts To From Capable of driving up to three 200 ohm parallel Pins 2 and 6 loads 82 millivolts full scale deflection Units with Mod Status 1 190 millivolts full scale deflection Av Kit Install Manual 190 00026 00 Rev Q Page 5 Flag Pins 3 and 4 OBI data Pins 7 8 and 23 Message annunciators Pin 20 RS232 chan 1 output data Pin 24 RS232 chan 2 output data Pin 19 RS232 chan 1 input data Pin 17 Arrival alarm annunciator Pin 12 ARINC 429 Output A amp B Pins 15 and 16 NAV Super Flag Output Pin 10 Av Kit Install Manual 190 00026 00 Rev Q Page 6 Capable of driving up to three 1000 ohm parallel loads 375 millivolts for flag out of view and 40 millivolts for flag in view Output providing bearing to waypoint data for a Bendix King RMI KI 229 or equivalent Output capable of driving negative logic message annunciators by sinking up to 500mA Output capable of driving ARGUS3000 5000 7000 STORMSCOPE SERIES II with NAVAID moving map displays Shadin 91204X T 91053X T Electronics International FP 5L fuel flow systems or Shadin 962801 Fuel Airdata Computer Conforms to the EIA specification RS 232C Output capable of driving real time plotting interface on GARMIN PC software or NMEA 0183 version 2 0 compatible mapping device Conforms to the EIA specification RS 232C Input capable of receiving serial al
22. ls The following figures can be used to identify which type contact you have a II ppee gt LAA RD gt NANMTANT Aa x CTAMDEM ROK N VV AN S W Ke Tob 1 N VIAN NLL LAA IN J 7 M WALL OI FAIV L L When working with the stamped crimp type contacts the following tools should be used Tools 37 position connectors Supplier Crimp Tool Extraction Tool Amp 58448 2 91067 22 ITT Cannon 995 2000 000 980 0008 124 Cinch HTD 544 CIET 20 HDB Part numbers shown are not maintained by Garmin and consequently are subject to change without notice Av Kit Install Manual 190 00026 00 Rev Q Page 28 APPENDIX STC PERMISSION Consistent with N8110 69 or Order 8110 4 Aviation Authority approved installers are hereby granted permission to use STC SA00066WI data to modify aircraft Av Kit Install Manual 190 00026 00 Rev Q Page 29 MI of Transportation federal Aviation Administration Supplemental Type Certificate Member SA00056WI asw Mene o GARMIN International 9875 Widmer Road Lenexa Kansas 66215 Mie shango in the dye for the following onem aon do ant rmm n cile harean the msveovlhiviasssasguiremante gf Tut 3 Civil Air patior __ 3415 Beech Mo
23. oute the coax cable to the rack location keeping in mind the recommendations of Section 2 Secure the cable in accordance with good aviation practice Trim the coaxial cable to the desired length and install the BNC connector 330 00087 00 per the cabling instructions on Figure 3 3 If the connector is provided by the installer follow the connector manufacturer s instructions for cable preparation Contacts for the 37 pin connector must be crimped into the individual wires of the aircraft wiring harness The following table lists recommended crimp tools ontacts tandard Density Connectors 7 socket connector J1 on unit 20 24 AWG socket contact 336 00022 00 M39029 63 368 205090 1 ositronic 39029 63 368 031 1007 042 4 Hand Standard Density Connectors size 20 contacts Crimping or socket contacts 20 24 AWG Tool positioner military pin M22520 2 08 ositronic Cannon 995 0001 584 995 0001 604 mp 601966 5 aniels stro 615725 Insert extract tools from ITT Cannon are all plastic others are plastic with metal tip AS m Non GARMIN part numbers shown are not maintained by GARMIN and consequently are subject to change without notice See Appendix B for information regarding obsolete stamped type contacts Av Kit Install Manual 190 00026 00 Rev Q Page 10 3 4 RACK INSTALLATION A Figure 3 4 shows outline dimensions for the aviation rack Install the rack in a rectangular 6
24. rtion caused by the blades 2 1 2 NOISE SOURCES The antenna should be located at least 3 ft from transmitting antennas such as VHF Comm HF transmitter DME Transponder and Radar Cabling for the GPS 150 should not be routed near components or cabling which are sources of electrical noise 2 1 3 ELECTRICAL BONDING No special precautions need to be taken to provide a bonding path between the antenna and the aircraft structure 2 1 4 ANTENNA LIMITATIONS GARMIN S GA 56 Antennas are recommended for installations where the airspeed of the aircraft will be subsonic 2 1 5 VHF COMM INTERFERENCE On many panel mounted aircraft the VHF COMM radiates strong harmonics from the unit and the antenna If the antenna is found to be the problem a 1 57542 GHz notch filter GPN 330 00067 00 may be installed in the VHF COMM coax as close to the COMM as possible If the box is found to be radiating the following can be done 1 Place the antenna as far from the VHF COMM unit and antenna as possible Av Kit Install Manual 190 00026 00 Rev Q Page 7 2 Replace or clean VHF COMM rack connector to assure good coax ground 3 Place a grounding brace between the GPS 150 VHF COMM and ground 4 Shield the VHF COMM wiring harness 2 2 RACK CONSIDERATIONS 2 2 1 ACCESSIBILITY Plan a location which gives the pilot complete and comfortable access to the entire keypad and which is plainly visible from the pilot s perspective Check that there is
25. sure the CDI is deflected full scale right 5 dots Centered Ensure the CDI is centered Maximum scale left Ensure the CDI is deflected beyond full scale left Maximum scale right Ensure the CDI is deflected beyond full scale right TO FROM FLAG TO Ensure TO flag is visible FROM Ensure FROM flag is visible FLAG Ensure TO and FROM are NOT visible CDI FLAG IN VIEW Ensure CDI flag is in view OUT OF VIEW Ensure CDI flag is out of view SUPERFLAG IN VIEW Ensure superflag is in view OUT OF VIEW Ensure superflag is out of view Select the OBI Test Page by removing the cursor from the CDI Test Page and turning the outer knob one detent to the right Using the controls on the GPS 150 front panel make the selections indicated below and verify the interfaces as appropriate OBI Data VALID Ensure that the OBI indicates the proper value INVALID Ensure the OBI is invalid OBI Value Ensure that the OBI displays the value entered when the VALID option is selected Select the Annunciator Test Page by removing the cursor from the OBI Test Page and turning the outer knob one detent to the right Using the controls on the GPS 150 front panel make the selections indicated below and verify the interfaces as appropriate Panel OFF Ensure no panel annunciators are illuminated ON Ensure all panel annunciators are illuminated Msg OFF Ensure the Message Annunciator is OFF ON Ensure the Message Annunciator is ON Av Kit Install Manual 190 00026 00 Rev Q Page 12
26. titude data from either an ICARUS Instruments 3000 Shadin Company formerly Rosetta MicroAvionics 8800 9000T or 9200T series altitude serializer encoder Shadin 91204XT 91053XT Series Fuel management system FC 10 FT 10 fuel computer totalizer Electronics International FP 5L fuel flow system or Shadin 962801 Fuel Airdata Computer Conforms to the EIA specification RS 232C Output capable of driving negative logic annunciator by sinking up to 500mA Output capable of interfacing with any device that has an input conforming to the GAMA ARINC 429 specification Output capable of driving positive logic NAV Super Flag by sourcing up to 500mA for flag out of view NAV valid SECTION 2 INSTALLATION CONSIDERATIONS Careful planning and consideration of the suggestions in this section are required to achieve the desired performance and reliability from the GPS 150 2 1 ANTENNA CONSIDERATIONS 2 1 1 SATELLITE VISIBILITY The GPS 150 GA 56 Antenna must be mounted on top of the aircraft For best performance select a location with an unobstructed view of the sky above the aircraft when in level flight Figure 2 1 illustrates a typical antenna installation For rotorcraft locate the GA 56 antenna 1 As far from the main rotor hub as possible This reduces the percentage of time the blade blocks the antenna 2 As far below the blade surface as possible if installing the antenna under the blade This reduces signal disto
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