AlliedSignal AEROSPACE INSTALLATION MANUAL BENDIX/KING* KLN 89/89B GPS RNAV MANUAL NUMBER 006- 10522-0003 5 REVISION 3, May, 1999 ™ fhe Ss & 2" WealWARNING Prior to export of this document, review for export license requirement is need- od. COPYRIGHT NOTICE ©1996 - 1999 AlliedSignal Inc. Reproduction of this publication or any portion thereof by any means without the ‘express written permission of AlliedSignal Inc. is prohibited. For further infor- mation contact the Manager. Technical Publications, AlliedSignal , One ‘Technology Center, 23500 West 105th Street, Olathe, Kansas. 66062-1294. Telephone: (913) 782-0400AlliedSignal BENDIX/KING KLN 89/89B GPS RNAV SECTION! GENERAL INFORMATION Paragraph wa INTRODUCTION 12 EQUIPMENT DESCRIPTION 13 TECHNICAL CHARACTERISTICS 1.3.1 UNIT TECHNICAL CHARACTERISTICS 14 UNITS AND ACCESSORIES SUPPLIED 1.4.1 KLN89/89B GPS RECEIVER 1.4.2 GPS ANTENNA 1.4.3. KLN 89/69B INSTALLATION KITS, 1.4.4 KA91/92 INSTALLATION KIT 1.45 DATABASE 15 ACCESSORIES REQUIRED, BUT NOT SUPPLIED 1.6 OPTIONAL ACCESSORIES 1 LICENSE REQUIREMENTS 1.8 RECOMMENDATIONS FOR IFR APPROVAL 19 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS SECTION I INSTALLATION Paragraph 24 GENERAL INFORMATION 22 UNPACKING AND INSPECTING EQUIPMENT 23 EQUIPMENT INSTALLATION 23.1 AVIONICS COOLING REQUIREMENTS FOR PANEL MOUNTED EQUIPMENT 2.3.2 KLN 89/89B MECHANICAL INSTALLATION 2.33 ANTENNA SELECTION 2.3.4 ANTENNA INSTALLATION CONSIDERATIONS 2.3.5 ANTENNA MECHANICAL INSTALLATION 23.5.1 GENERAL 2.3.5.2 INSTALLATION PROCEDURE 2.3.6 ELECTRICAL INSTALLATION 2.3.6.1 GENERAL INFORMATION 2.8.62 — FUNCTIONAL PINOUT DESCRIPTIONS 24 POST INSTALLATION CHECK OUT INFORMATION 2.4.1 MAINTENANCE PAGES 2.4.1.1 MAINTENANCE 1 (MNT 1) PAGES 2.4.1.2 MAINTENANCE 2 (MNT 2) PAGES 2.4.1.3 MAINTENANCE 3 (MNT 3) PAGES IMKLN89/BLT Rev 3 May/99AlliedSignal BENDIX/KING KLN89/89B GPS RNAV MAINTENANCE 4 (MNT 4) PAGES 2-64 POST INSTALLATION CHECKOUT PROCEDURE 2-65 INSTALLATION CHECK OUT 2-65 INTEGRATED INSTALLATION CHECK OUT 2-68 ALL INSTALLATIONS 2-66 CDYHSI INTERFACE 2-66 GRAY CODE ALTITUDE INPUTS 2-67 RMI INTERFACE 2-67 ELT INTERFACE 2-67 MOVING MAP INTERFACE 2-67 EXTERNAL ANNUNCIATORS 2-68 DATALOADER 2-68 ALT ALERT, ALT ALERT AUDIO 2-68 HEADING INTERFACE 2-68 ERROR CODES 2-69 SECTION Ill OPERATION Paragraph Page 3.1 GENERAL INFORMATION 3-4 Page ji IMKLNE9/BLT Rev 3 May/s9Figure 2-4 2-4 2-4 22 2-3 24 2-5 27 2-8 2-9 2-10 a1 2-12 2-13 2-14 2-15 2-16 2-17 2-17 2-17 2417 2-47 217 2-17 247 2-18 AlliedSignal BENDIX/KING KLN 89/89B GPS RNAV LIST OF ILLUSTRATIONS. KLN 89/898 CONNECTOR PIN FUNCTIONS (Page 1) KLN 89/898 CONNECTOR PIN FUNCTIONS (Page 2) KLN 89/898 CONNECTOR PIN FUNCTIONS (Page 3) KLN 89/89B CRIMPING AND INSERTION/EXTRACTION TOOLS KLN 89/898 INSTALLATION DRAWING KA 91 OUTLINE DRAWING KA 91 INSTALLATION DRAWING KA 91 BACKPLATE DRAWING KA 92 OUTLINE DRAWING KA 92 INSTALLATION DRAWING KA 92 BACKPLATE DRAWING KA 91/92 TNC ANTENNA COAX/CONNECTOR ASSEMBLY KA 91/92 BMA ANTENNA COAX/CONNECTOR ASSEMBLY KA 91/92 TNC/BMA ANTENNA COAX/CONNECTOR ASSEMBLY KA 33 P/N 071-4037-00/01 FINAL ASSEMBLY KA 33 P/N 071-4037-00/01 INSTALLATION DRAWING CUTLER-HAMMER SWITCH/ANNUNCIATOR INSTALLATION DRAWING CUTLER-HAMMER SWITCH/ANNUNCIATOR INTERNAL SCHEMATIC (Page 1) CUTLER-HAMMER SWITCH/ANNUNCIATOR INTERNAL SCHEMATIC (Page 2) KLN 89/898 INTERCONNECTION DRAWING (Page 1) KLN 89/898 INTERCONNECTION DRAWING (Page 2) KLN 89/898 INTERCONNECTION DRAWING (Page 3) KLN 89/898 INTERCONNECTION DRAWING (Page 4). KLN 89/898 INTERCONNECTION DRAWING (Page 5) KLN 89/898 INTERCONNECTION DRAWING (Page 6) KLN 89/898 INTERCONNECTION DRAWING (Page 7) KLN 89/898 INTERCONNECTION DRAWING (Page 8) KLN 89/89B DATALOADERIPC INTERFACE DRAWING IMKLN69/BLT Rev 3 May/99 Page 2-9 2-10 2-11 2-12 2-13 248 2-17 219 2-21 2-23 2-25 2-27 2-29 2-31 2-33 2-35 2-37 2-39 2-41 2-45 2-47 2-49 2-51 2-53 2-55 2-57 2-59 PagPage iv AlliedSignal BENDIX/KING KLN89/89B GPS RNAV RS-232 FORMAT DEFINITIONS APPENDIX FLIGHT MANUAL SUPPLEMENT PROCEDURES APPENDIX KLN 89/89B AIRPLANE FLIGHT MANUAL SUPPLEMENT KLN 89/89B SUPPLEMENTAL PROCEDURES MANUAL, KLN 89/89B SUPPLEMENTAL TYPE CERTIFICATE TSO APPENDIX ENVIRONMENTAL QUALIFICATION FORMS IMKLN89/BLT Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/89B GPS RNAV SECTION! GENERAL INFORMATION 1.1 INTRODUCTION This manual contains information relative to the physical, mechanical, and electrical characteristics of the BENDIX/KING KLN 89/89B Global Positioning System (GPS) Receiver. General installation procedures are also included. 1.2 EQUIPMENT DESCRIPTION The KLN 89/898 are pane! mounted, long range, GPS based airborne navigation systems with adata base. The KLN 89 is a VFR only device while the KLN 89B provides VFR, IFR enroute, and IFR non-precision approach functions. The primary purpose of the equipment is to provide the pilot with present position information and to display guidance information with respect to a flight plan defined by the pilot. Flight plan information is entered by the pilot via various knobs and buttons on the front panel. The unit can use its present position information to determine crosstrack error, distance-to-waypoint, ground speed, track angle, time to waypoint, bearing to waypoint, and advisory VNAV guidance. The internal data base of the KLN 89/89B contains information concerning airports, VORs, NDBs, intersections, SIDs/STARs, and outer markers throughout the world. Waypoints are stored in the data base by their ICAO identifiers. The ICAO identifiers are in most cases taken directly from Jeppesen Sanderson or government aeronautical charts. The KLN 898 has instrument approach capabilities. The information stored in the data base eventually becomes out of date; therefore, to provide a ‘means of updating the information, the database is housed in a data card which plugs into the front of the KLN 89/898. It is designed so that the user may easily remove the old database and install a current database. A secondary method of updating the database is by loading the information via an IBM compatible laptop computer. For more information on availability and cost of updating the database of the KLN 89/898 refer to the KLN 89/89B Pilots Guide P/N 006-08786-0000. 1.3 TECHNICAL CHARACTERISTICS 1.3.1 UNIT TECHNICAL CHARACTERISTICS KLN 89/898. TSO Compliance: SEE TSO APPENDIX Physical Dimensions: Refer to KLN 89/69B installation drawing, figure 2-3 Mounting: Panel mounted with AlliedSignal supplied mounting rack Cooling Requirements: 4 CFM (cubic feet per minute) provided by blower motor such as KA 33 or equivalent OPERATIONAL CHARACTERISTICS: ‘Temperature Range: -40° Cto +55°C Altitude Range: Up to 35,000 FT Power Inputs: 11 to. 33 VDC at 3.0 A MAX (-40° C to +55° C) 13.75 VDC @ 2.5 A Nominal 27.5 VDC @ 1.25 A Nominal IMKLN89/BLT Page 1-1 Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/898 Panel Lighting Current Requirements: 28 VDC Lighting: 14 VDC Lighting: SIGNAL INPUTS: GPS DISPLAYED: Tai APPROACH ARMIN: DATA LOADER RS 232 IN: GENERAL RS 232 IN: SPARE RS 232 IN: Gray Code Inputs: (A1,A2,A4,B1,B2,B4,C1,C2,C4,D4) OBS SIN: OBS COs: AJC POWER MONITOR CONFIGURATION MODULE SIGNAL OUTPUTS: OBI SYNC, OBI CLOCK, & OBI DATA: Page 1-2 GPS RNAV 110 mA max 220 mA max OPEN = GPS displayed (when an indicator resolver is connected to the OBS resolver inputs) GND = GPS not displayed (when an indicator re- solver is not connected) OPEN = Normal Operation GND = Take Home Mode These are reserved pins for future use, OPEN = normal operation GND = test mode This pin is normally open with a momentary low while the panel button is pressed The Data Loader RS 232 input is designed to com- municate with the dataloader This RS 232 input is designed to communicate with devices, i.e. air data and fuel flow sensors via RS 232 format (refer to RS 232 format definitions ap- pendix) This RS 232 input is reserved for future use. Gray Code Altitude Signals (0 V. to 28 V.) These inputs are diode isolated inside the KLN 89/89B OBS resolver sine, nominal input impedance = 33.8 K ohms (ac) and 100 K ohms (dc) OBS resolver cosine, nominal input impedance = 33.8 K ohms (ac) and 100 K ohms (dc) This pin senses the aircraft power bus voltage. This high impedance input operates from 0 to 33 V with accuracy of 0.1 V Refer to section 2.3.6.2 AlliedSignal Serial Data containing bearing to the active waypoint IMKLN89/BLT Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/898 GPS RNAV e@ DATA LOADER RS 232 OUT: The Data Loader RS 232 output is designed to communi- cate with an IBM compatible personal computer GENERAL RS 232 OUT: ‘The RS232 output is designed to interface with certain ARNAV ELTs and certain moving map displays, and Sha- din fuel flow systems (refer to RS 232 format definitions appendix) SPARE RS 232 OUT: This RS 232 output is reserved for future use WAYPOINT ANNUNCIATE: OPEN = Inactive LOW = Active (Output can sink up to 250 mA) 7 MESSAGE ANNUNCIATE: OPEN = Inactive LOW = Active (Output can sink up to 250 mA) : APPROACH ACTIVE Al TE: OPEN = Inactive LOW = Active (Output can sink up to 250 mA) APPROACH ARM ANNUNCIATE: OPEN = Inactive LOW = Active (Output can sink up to 250 mA) SPARE ANNUNCIATE 1: SPARE ANNUNCIATE 2: ‘SPARE ANNUNCIATE 3: TATE @ ‘Spare annunciators are reserved for future use @ FCSLOC ENG: OPEN = Inactive LOW = Active (Output can sink up to 250 mA) LATERAL DEV FLAG +: Valid: 950 to 900 mV (high) LATERAL DEV FLAG -: Flag in view: = 50 mV (low) ‘Output is capable of criving five 1k ohms parallel loads VERTICAL DEV FLAG +: Reserved for future use VERTICAL DEV FLAG - LATERAL SUPERFLAG: Valid = > 18 V in 28 VDC aircraft installations; = 10 V in 14 VDC aircratt installations. Invalid = < 3.5 V in all installations while sinking 1 mA Output can source at least 250 mA, : VERTICAL SUPERFLAG: Reserved for future use LATERAL DEV +L: ‘These outputs are differential pairs (+L and +UP are posi- LATERAL DEV +R: tive). Output range is + 300 mV and is capable of ariv- ing five 1k ohms parallel loads. VERTICAL DEV +UP: Reserved for future use VERTICAL DEV +DOWN: OBS OUT: Used to excite the OBS resolver rotor. Nominal output frequency = 450 Hz. Nominal unloaded peak amplitude = 6V. Output drive capability = 40 mA IMKLN89/BLT Page 1-3 Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/89B GPS RNAV +TO/+FROM Flag Outputs: To Indication: +100 to +900 mV on +TO with respect to +FROM when desired course is within 85° of the bearing to the active waypoint. From Indication: ~100 to -900 mV on +TO with respect to +F ROM when desired course is within 180 + 85°with respect to the bearing to the active waypoint. Outputs are capable of driving up to five 200 © parallel loads ALTITUDE ALERT ANNUNCIATE: — HIGH = Inactive LOW = Active (can sink up to 250 mA). A DIO: This output is active whenever ALTITUDE ALERT AN- NUNCIATE is active, Signal is 1 KHz., 3.5 V rms max into 500 @ Refer to paragraph 2.4.4.9 for the procedure to adjust the volume. KA 91 ANTENNA TSO Compliance: ‘SEE TSO APPENDIX Physical Dimensions: Refer to KA 91 installation drawing, figure 2-5. Airspeed Rating: 600 Kts. TAS Output Impedance: 50 Ohms (nominal) DC Voltage: 5 Volts +0.5 Volt DC Current: 50 mA maximum KA 92 ANTENNA TSO Compliance: ‘SEE TSO APPENDIX Physical Dimensions: Refer to KA 92 installation drawing, figure 2-8. Airspeed Rating: 600 Kts. TAS Output Impedance: 50 Ohms (nominal) DC Voltage: 5 Volts +0.5 Volt DC Current: 50 mA maximum Page 1-4 IMKLNE9/BLT Rev 3 May/S9AlliedSignal BENDIX/KING KLN 89/89B GPS RNAV KA 198 COMM FILTER (PIN 071-01565-0000) ‘Center Notch Frequency: 1575.42 MHZ. Attenuation at 1575.42 =1.5 MHz: 35 dB min. Insertion loss from 118.00 to 137.00 MHz: .3dB Max, Impedance from 118.00 to 137.00 MHz: 50 ohms VSWR from 118.00 to 137.00 MHz: 15:1 NOTE The conditions and tests performed on 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 these performance standards. The article may be installed only if further evaluation by the applicant documents an acceptable installation and is approved by the Administrator. 1.4 UNITS AND ACCESSORIES SUPPLIED 1.4.1 KLN 89/898 GPS RECEIVER The KLN 89/898 is available in the following versions: PARTNUMBER = 14V/28V. Ss BLACK CERTIFICATION VERSION LAMPS BEZEL 066-01148-0101 x x VERIIFR KLN 898, 066-01148-0102 x x VFRIIFR (BRNAV) —KLN 898 066-01148-1111 x x VER ONLY KLN 89 066-01148-1112 x x VFR ONLY (BRNAV) KLN 89 1.4.2 GPS ANTENNA ‘The KA91 antenna is available by ordering P/N 071-01545-0200. The KA 92 antenna is available by ordering P/N 071-01553-0200. IMKLN89/BLT Page 1-5 Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/898 GPS RNAV 1.4.3 KLN 89/898 INSTALLATION KITS The KLN 89/89B Installation Kit (P/N 050-03321-0000) is available with crimp connectors only. A\list of the required crimp tools and insertion/ extraction tools can be found in Section 2 of this manual, The kit and a complete list of the items contained in the kit is given below. PIN DESCRIPTION UM -0000 VENDOR NAME & P/N 050-03321-0000 _ KLN 89/89B INSTALL-CRIMP——X 030-00101-0002 PANEL MOUNT PLUG EA TED Mfg. 9-30-10 1 030-01157-0011 SOCKET CRMP 20G EA 62 Positronic FC6020D-14 030-03271-0000 CONN SUB-D 37PSKT RF 1 030-03272-0000 CONN SUB-D 25P SKT RF 1 033-00280-0000 TELEPHONE JACK EA 1 047-05959-0002 STRAIN RELIEF W/H EA 2 047-05960-0001 STRAIN RELIEF W/F EA 2 057-05621-0000 DATALOADERDECAL EA 1 057-05628-0000 DISCLAIMER TAG EAS 073-00629-0002 CONNECT,MTG BRACKET EA 1 089-02353-0001 NUT CLIP 6-32 EA 6 089-05903-0004 SCR PHP 4-40X1/4 EA 8 089-05903-0007 SCR PHP 4-40X7/16 By 4 089-05907-0004 SCR PHP 6-32X1/4. EA 4 089-06012-0006 SCR FHP 6-32X3/8 EA 6 089-08252-0030 WASHER EA 1 090-00019-0007 RING RTNR .438 EA 1 187-01352-0000 GASKET cay 200-08334-0000 CONFIG MODULE eA 1.4.4 KA 91/92 INSTALLATION KIT THE KA 91 INSTALLATION KIT (P/N 050-03195-0000), INCLUDING ITS CONTENTS, IS SHOWN BELOW. PIN DESCRIPTION UM — -0000 VENDOR NAME & P/N 050-03195-0000 —_KAQ1 INSTALL x 030-00134-0001 RIGHTANGLE CONNCOAX EA 1 TED MFG 5-30-102 047-10130-0002 BACKPLATE, ANTENNA EA 089-06908-0012 SCREW, AIRCRAFT EA 4 187-01807-0000 KA91 GASKET EA 1 Earlier installation kits included a straight TNC coax connector, P/N 030-00134-0000. Page 1-6 IMKLN89/BLT Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/898 GPS RNAV The KA 92 Installation Kit (P/N 050-03318-0000), including its contents, is shown below. PIN DESCRIPTION UM — -0000 VENDOR NAME & P/N 050-03318-0000 _ KA92 INSTALL 030-00134-0001 RIGHT ANGLE CONN COAX EA 047-10735-0002 BACKPLATE, ANTENNA. EA 089-05909-0012 SCREW, PHP 8-32x3/4 EA 187-01831-0000 _ KA92 GASKET EA TED MFG 5-30-102 Acie) 1.4.5 DATABASE The KLN 89/89B database cartridge and diskettes are available for three separate geographic areas. Database cartridges are available only for users in the United States Of America and Canada. Diskettes are available to all users. Also database files can be dowloaded via the Internet at the following address: http:/www.gpsdatabase.com CARTRIDGE DISKETTE Atlantic International Database 071-00094-0101 223-08500-0000 Pacific International Database 071-00094-0102 223-08600-0000 Americas Database 071-00094-0103 223-08700-0000 1.5 ACCESSORIES REQUIRED, BUT NOT SUPPLIED A. Forced Air Cooling AKA 33 Cooling Kit or equivalent is required for the KLN 89/89B installation. 1. available under P/N 071-4037-00. 2. KA 33 Blower for 28 VDC installations available under P/N 071-4037-01. 3. The installation kit for the KA 33 Blower is available under P/N 050-02204-0000. B. Indicators and HSIs An indicator, CDI or HSI, isrequired for IFR. Listed below are common AlliedSignal models that are available 1. KI 202 or KI 206 (P/N 066-3034-XX) Navigation Indicator and installation kit (P/N 050-01524-0000). 2. KI 208A or KI 209A (P/N 066-3056-XX) Navigation Indicator and installation kit (P/N 050-01524-0000). 3. KPI SSSA (P/N 066-3045-XX) Horizontal Situation Indicator and installation kit (P/N 050-01791 -XXXxX). 4. KPI 553B (P/N 066-3069-XX) Horizontal Situation Indicator and installation kit {PIN 050-02167-X00%) NOTE ‘The KP! 553A/553B DME distance display is not compatible with the KLN 89/898. IMKLN89/BLT Page 1-7 Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/898 GPS RNAV 5. KI 25A (P/N 066-3046-XX) Horizontal Situation Indicator and installation kit (PIN 050-01344-XXXX). C. CDI Indicator with "MSG" and "WPT" Annunciators. Some standalone CDI indicators are available with WPT/MSG annunciators built in. One commonly used is the Model MD40-39, manufactured by Midcontinent instrument, telephone (316) 683-5619. These devices have no resolver interface. The use of an OBS. resolver will reduce pilot workload. 1.6 OPTIONAL ACCESSORIES A. PC Interface Kit To load the database from a personal computer via diskettes, order interface kit P/N 050-03213-0000. The kit contains a ready to use cable which connects between the aircraft connector and the computer's 9 pin or 25 pin serial connector. The kit is necessary whether the user is loading from an AlliedSignal diskette or a database obtained via the INTERNET. The database may be loaded directly from the PC to the KLN 89/898 installed in an aircraft (refer to section 2.4.4.8 and Figure 2-18 for details). Laptop computers used to load the data base require the following: 1. IBM compatibility 2. An available Com 1,2,3, or Com 4 serial port NOTE Ifloading the database from a diskette sent from AlliedSignal then the PC must have 3.5" high density diskette drive. Also afew select BIOS services are incompatible with the AlliedSignal diskettes. If there is uncertainty relating to this, contact AlliedSignal Product Services by telephoning (913) 782-0600. B. Annunciators and Switch/Annunciators (Refer to .B. 363 for additional information pertaining to switch/annunciators for GPS systems) The devices shown below are Eaton 582/584 series switch/annunciators and are representative of those used in our original certification. They were chosen because of their excellent sunlight readable characteristics and meet or exceed the requirements of Advisory Circular 20-138. These are high quality devices and we encourage their use. However, there. are other comparable devices on the market that may be substituted at the installer/customers choice. These switch/annunciators are available through AlliedSignal Service Stock or direct from our supplier, LCOMP Inc. It is advantageous to order direct from LCOMP, if possible, in order to avoid additional price mark-ups. On international orders, it may be necessary to order through AlliedSignal as LCOMP, at the time of this publication, is not prepared to handle international orders. LCOMP’s address and telephone numbers are listed as follows: Page 1-8 IMKLN89/BLT Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/89B GPS RNAV @ LCOMP Aerospace Controls Telephone: c/o Carlton-Bates Co. (800) 786-0617 9214 Bond St. (913) 438-4848 Overland Park, KS 66214 (913) 438-4839 Fax NOTE The switch/annunciators listed below in many cases show two numbers. The part numbers that are shown in parentheses are devices previously called out and may be used until supply is depleted. The _031-00785-XXXX are the preferred Switch/Annunciator assemblies. KLN 89/898 Enroute/Terminal Set for CDI or Elect. Mech. HSI Installations ‘The following switch/annunciators are being offered for CDI or HSI switching and annunciation in the KLN 89B IFR enroute/terminal installations. They are optional for KLN 89/89B VFR installations. KLN 89/89B Ann. Set NAVIGPS Sw. Ann. WPT/MSG Ann, (28 V. Itg.) 031-00785-0711 or (031-00763-071 1) 031-00785-0505 or (031-00763-0505/-0718) KLN 89/89B Ann. Set NAV/GPS Sw. Ann. WPT/MSG Ann. (14 Vi Itg.) 031-00785-0712 or (031-00763-0712) 031-00785-0762 or (031-00763-0762/-0719) KLN 89B Approach Set for CDI or Elect. Mech. HSI Installations The following switch/annunciators are being offered for CDI or HSI switching, APR switching, and annunciation in KLN 89/898 non-precision approach installations. KLN 89B Ann, Set NAVIGPS Sw. Ann, : WPT/MSG Ann, (28 V. Lig.) 031-00785-0711 or (031-00763- 0711) 031-00785-0505 or (031-00763- 0505/-0718) GPS APR ARM/ACT ‘Sw. Ann. 031-00785-0766 KLN 89B Ann. Set NAV/GPS Sw. Ann. (14V. Lig.) 031-00785-0712 or (031-00763- 0712) WPT/MSG Ann, 031-00785-0762 or (031-00763- 0762/0719) GPS APR ARM/ACT Sw. Ann, 031-00785-0767 IMKLN89/BLT Page 1-9 Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/89B GPS RNAV NAV/GPS Switch/Annunciator Installations where the outputs from KLN 89/89B and an existing navigation system are switched between a common indicator or HS! may require some type of annunciation. A NAV/GPS switch/annunciator is available that provides both the annunciation and a switch contact to energize the switching relay(s) required for the switching of the outputs. This Switch/Annunciator is available in 5 V, 14 V, or 28 V versions as shown below. LIGHTING _ALLIEDSIGNAL P/N ALLIEDSIGNAL P/N 28V 031-00763-0711 031-00785-0711 14V 031-00763-0712 031-00785-0712 (Eaton Series 584) (Eaton Series 582) fd Style Prefered WPT/MSG Remote Annunciators TWO FIELD ANNUNCIATORS (WPT/MSG) LIGHTING __ ALLIEDSIGNAL P/N ALLIEDSIGNAL P/N 28V 031-00763-0505 (031-00785-0505 14V 031-00763-0506 031-00785-0506 (Eaton Series 584) (Eaton Series 582) 01 Sie Prefered NOTE (WPT) AND (MSG) will be in amber color. These annunciators will be deadface and readable only when lit GPS APR, ARM/ACTV Switch/Annunciator A switch/annunciator can be used for arming or activating the approach mode. It will provide remote annunciation of ARM and ACTV and provide a momentary switch function to arm, disarm, or deactivate the Approach Mode and change the CDI scale factors. The KLN 89B requires an annunciator to display when approach is armed or active. LIGHTING ALLIEDSIGNAL P/N 2aV 031-00785-0766 1av 031-00785-0767 (Eaton Series 582) C. NAVIGPS Switching Installations in which the outputs from a KLN 89/89B and an existing navigation system are being ‘switched onto a common indicator will require some remote relay switching that is controlled by the NAV/GPS switch/annunciator. Page 1-10 IMKLN89/BLT Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/89B GPS RNAV D. Right Angle Connector The part number for a right angle connector for the KA 91 or KA 92 antenna connestion is 030-00134-0001. This right angle connector was originally an option but has been included in ‘the installation kit as the standard connector. 1.7 LICENSE REQUIREMENTS None. 1.8 RECOMMENDATIONS FOR IFR APPROVAL 1. Aircraft Logbook Entry 2. Aircraft Installation Requirements NOTE For the following subsections, refer to sections 1.5 and 1.6 for allowable configurations where applicable. Refer to section I! for illustrations. TSO’d Antenna ‘The antenna must be a TSO'd KA 91, P/N 071-01545-0200 or KA 92 P/N 071-01553-0200. Ifthe P/N of the KA 91 is not available, it may be identified by the serial number as the TSO’d antennas have a five digit serial number. Nav Instrumentation The navigation information (D-Bar, Nav Flag, and To-From) must be displayed on an instrument in the pilot's panel. Electromechanical indicators are capable of displaying the variable scale factors of enroute, terminal, and approach modes. OBS Interface The use of an OBS resolver will reduce pilot workload during an instrument approach. Itallows the OBS setting to be changed on the navigation indicator when the KLN 89/89B is operating in the OBS mode. Without the OBS resolver connection, the OBS may be changed from the KLN89/89B controls. OBS mode is commonly used during procedure turns and holding patterns ‘Some certification agencies may require the use of the OBS resolver for approach certification. Consult your approval agency for additional information. Refer to sections 1.3 and 2.3.6 for additional OBS information. ‘Switch/Annunciators: NAV/GPS (Switch/Annunciator) If the navigation information is displayed on a shared primary indicator a switch/annunciator will be required to select and annunciate the source. WPT/MSG (Annunciator) ‘The required annunciators are "WPT" and "MSG" only. Even though the information is available on the KLN 89/898 display, a remote annunciator is also required in the pilots panel. IMKLN89/BLT Page 1-11 Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/89B GPS RNAV GPS APR, ARM/ACT (Switch/Annunciator) A.switch/annunciator can be used for arming, disarming, or deactivating the approach mode. {twill provide remote annunciation of ARM and ACTV and provide amomentary switch function to arm and activate the Approach Mode and change the CDI scale factors. The KLN 89B requires an annunciator to display when approach is armed or active. Refer to section 1.6 for additional switch/annunciator information. Altitude Source An attitude source is required for IFR certification. The altitude may be derived from a compatible encoding altimeter, and some RS 232 air data systems. 3. Approved Airplane Flight Manual Supplement flight manual supplement will need to be prepared and approved. The supplement may be prepared based on the sample, P/N 006-00839-0000. Refer to the flight manual ‘supplement procedures appendix for information on preparing a flight manual supplement and a copy of the STC approval. 4, Pilot's Guide The KLN 89/898 pilots’ guide must be placed in the aircraft in a location that is accessible tothe pilot. The pilot’s guide is P/N 006-08786-0000 and the quick reference is P/N 006-08787-0000. AlliedSignal Electronic And Avionics Systems BENDIX/KING KLN 89/89B GPS RNAV 1.9 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS ‘The instructions for continued airworthiness given in the TC or STC approvals for this product supplements or supercedes the instructions for continued airworthiness in this manual. Most AlliedSignal products are designed and manufactured to allow "on condition maintenance.” On condition maintenance is described as follows; There are no periodic service requirements necessary to maintain continued airworthiness. No maintenance is required until the equipment does not properly perform it's intended function. When service is required, a complete performance test should be accomplished following any repair action. Consult the appropriate unit Maintenance/Overhaul Manual for complete performance test information. Page 1-12 IMKLN@9/BLT Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/89B. GPS RNAV SECTION Il INSTALLATION 2.1 GENERAL INFORMATION This section contains general suggestions and information to consider before installation of the KLN 89/89 GPS RNAV. Close adherence to these suggestions will assure optimum performance from the equipment. 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 iffurther evaluation by the applicant documents an acceptable installation and is approved by the Administrator. 2.2 UNPACKING AND INSPECTING EQUIPMENT Exercise extreme care when unpacking the equipment. Make a visual inspection of the unit for evidence of damage incurred during shipment. If a claim for damage is to be made, save the shipping container to substantiate the claim. The claim should be promptly filed with the transportation company. It would be advisable to retain the container and packaging material after all equipment has been removed in the event that equipment storage or reshipment should become necessary. 2.3 EQUIPMENT INSTALLATION 2.3.1 AVIONICS COOLING REQUIREMENTS FOR PANEL MOUNTED EQUIPMENT The greatest single contributor to increased reliability of all modern day avionics is to limit the maximum operating temperature of the individual units whether panel mounted or remote mounted. While modern day individual circuit designs consume much less electrical energy, watts er cubic inch dissipated within the avionics unit remains much the same due to the high density Packaging techniques utilized. Consequently, the importance of providing cooling to the avionics stack is still with us today. While each individual unit may or may not require forced air cooling, the combined heat load of several units operating in a typical avionics location will significantly degrade the reliability of the avionics if provisions for cooling are not incorporated in the initial installation. Failure to provide cooling to the equipment will lead to increased avionics maintenance costs and may also void the AlliedSignal warranty. In the case of the KLN 89/898, installation of a KA 33, (P/N 071-4037-XX), or equivalent cooling system is required. Ram air cooling is not acceptable. For installation information on the KA 33 refer to the KA 33 installation manual, P/N 006-01069-XXXX or Installation Bulletin 258. 2.3.2 KLN 89/898 MECHANICAL INSTALLATION The KLN 89/898 installation will conform to standards designated by the customer, installing agency, and existing conditions as to the unit location and type of installation. However, the following suggestions will assure a more satistactory performance from the equipment. IMKLN89/BLT Page 2-4 Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/89B GPS RNAV A. Plan a location on the aircraft panel so that the KLN 89/89B is plainly visible to the pilot and so that he has complete access to all front panel controls. Check to be sure that there is adequate depth behind the panel for the mounting rack and all the connectors and cabling. Be sure that the mounting location is not close to heater vents or other sources of high heat B. Refer to figure 2-3 for the panel cutout dimensions. Mark and cut the panel opening. 2.3.3 ANTENNA SELECTION The KA91 and KA92 GPS active antennas, P/N 071-01545-0200 and 071-01553-0200 respectively, are the designated antennas for the KLN 89/89B. 2.3.4 ANTENNA INSTALLATION CONSIDERATIONS The antenna should be mounted on top of the fuselage near the cockpit. Avoid mounting the antenna near any projections, the propeller, and the T-tail of the aircraft, where shadows could occur. It is recommended that there be a separation of at least 3 ft between the KLN 89/898 GPS antenna and any VHF Comm antenna on the aircraft. Antenna baseplate must be level within = 5° in both axes when the aircraft is in level flight. if the antenna is tilted more than 5° or is mounted close to other objects that shadow it, loss of some of the satellites will occur and system performance may be degraded. Antenna cable and connector information, including vendor information, is listed below. Refer to figure 2-10 (TNC) and figure 2-11 (BMA) for cable/connector assembly instructions for the 0 to 40 feet category using RG 400/U or RG 142B/U. Refer to figure 2-12 (for both TNC and BMA) for the 0 to 80 feet and 0 to 100 feet categories. NOTE KA 91/92 nominal gain and noise figures are 26.5 dB and 2.3 dB respectively. With 0.050 ice on radome, gain will not decrease by more than 2.0 dB when viewing a satellite from 30° above the horizon to zenith, as compared to a no ice condition, CABLE CABLE PARTNUMBER BMA CONNECTOR ‘TNC CONNECTOR MAX. ALLOWABLE LENGTH LOSS (48) Oto40f. PIN: 024-00002-0000 PIN: 090-00101-0002 PIN: 030-00134-0000 80 \VPN: RG1426/U VPN: TED Mig. 9-30-10 VPN: TED tig. 5-10-30 PIN: 024-00051-0060 PIN: 090-00101-0002 PIN: 030-00134-0000 80 ‘VPN: RG400U VPN: TED Mig. 9-90-10 VPN: TED tig. 5-10-30 Oto BO. PIN 024-00072-0000 PIN: 030-00452-0000 PIN: 030-00108-0002 80 VPN: ECS 311601 \VPN: TED Mig. 9-90-26 VPN: TED Mig. 5-10-307 10 100. PIN 024-00071-0000 PIN: 030-00452-0001 PN: 030-00108-0009 80 VPN: ECS 911201, ‘VPN: TED Mig. 9-90-25 VPN: TED Mig, 5-10-306 10010 165 f. Contact TED, ECS or PIC for complete cablelconnector assembly. Page 2-2 IMKLN89/BLT Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/898 GPS RNAV NOTE A right angle antenna connector is available from AlliedSignal (P/N 030-00134-0001) or from TED. TED Manufacturing Corp. Bectronic Cable Specialists (ECS) PIC Wire and Cable 11415 Johnson Drive 11227 W. Forest Home Avenue N63 W 22619 Main Street ‘Shawmee, Kansas 66203 Franklin, Wisconsin 53132 P.O. Box 330 ‘Tet (919) 631-6211 Tet: (800) ECS-WIRE Sussex, Wisconsin 53089 cor (414) 421-5300 Tek: (800) 742-3191 cor (414) 248-0500 2.3.5 ANTENNA MECHANICAL INSTALLATION 2.3.5.1 General ‘To maintain good performance from the antenna system, do not wax or paint the antenna. 2.3.5.2 Installation Procedure A. Using the correct template for the antenna chosen, mark the mounting holes on the aircraft fuselage. B. Drill and/or punch the required holes. . Use apiece of fine sandpaper or emery cloth to sand the area on the fuselage skin on which ‘the doubler plate for the antenna is to be mounted and on the aircraft skin under where the antenna will be mounted. D. Apply Alumiprep No. 33, P/N 016-01127-0000, to both the fuselage and to the back of the doubler plate. Follow the cleanse the metal of any left over residue. E. Apply Alodine, P/N 016-01128-0000, to both locations following the directions on the container. This is used to ensure good bonding of the antenna and to prevent oxidation. F. Refer to figure 2-5 for the KA 91 installation drawing or figure 2-8 for the KA 92 installation drawing and mount the antenna as shown. First rivet the doubler plate in place. Itis imperative that the doubler plate make a good electrical bond with the inside of the aircraft ‘skin and that the antenna itself be well bonded to the aircraft. G. When installing the KLN 89/89B antenna do not exceed 50 inchilbs of torque on the antenna mounting screws. and outside areas of the cctions on the container to H. Apply a bead of sealant around the base of the antenna and seal the antenna mounting screw holes to prevent water damage. 2.3.6 ELECTRICAL INSTALLATION 2.3.6.1 General Information ‘The KLN 89/898 will operate with an input voltage from 11 to 33 VDC, but the front panel lighting circuit must be wired for either +14 VDC or +28 VDC depending on the aircraft lighting bus. Refer to the KLN 89/89B interconnect diagram for wiring details. IMKLNS9/BLT Page 2-3, Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/898, GPS RNAV A. The installing facility will supply and fabricate all external cables. The required connectors are supplied as part of the installation kit. B. The length and routing of the external cables must be carefully planned before attempting the actual installation. Avoid sharp bends or locating the cable near aircraft control cables. C. The KLN 89/89B and associated wiring must be kept at least a minimum of 3 ft. from. high Noise sources and not routed with cables from high power sources to insure optimum performance from the system. D. Do not route the antenna cable near any cable used for a transmitting antenna. Prior to installing the KLN 89/898 itseff, a point to point continuity check of the wiring harness should be done to verify proper wiring. The aircraft power input to the unit should be made to insure that power is applied to only the specified power pin(s). 2.3.6.2 Functional Pinout Descriptions This section gives a brief description of some of the inputs and outputs of the KLN 89/89B. Itis provided so the installer can determine what specific wiring needs to be done to the aircraft in which the unitis to be installed. Unless otherwise specified, pins not used are to be left open. CONNECTOR P891 Pin 1; GENERAL RS 232 IN Pin 1 is the RS 232 input. The KLN 89/89B must be configured correctly for the type of equipment (or no equipment) connected to this input. Refer to section 2.4.1 for the configuration procedure. Itis not necessary to connect this input to the GENERAL RS 232 OUT when this input is not used as the "No Fuel Mgt Sys” and "No Air Data” configuration choices indicate this input is unused and inhibit the "No RS-232 Data” message. For specific label information, refer to RS 232 format definitions appendix. Pin 2; GENERAL RS 232 OUT ‘The KLN 89/898 outputs data in RS 232 format on this pin. It can be used to interface with certain types of ELT's, fuel sensors, moving map displays, and fuel management systems. For specific label information, refer to RS 232 format definitions appendix. Pin 3; DATA LOADER RS 232 IN Pin 3 inputs Data Loader information in RS 232 format. It can be used to interface with a laptop IBM compatible PC to load the database. Pin 4; DATA LOADER RS 232 OUT Pin 4 outputs Data Loader information in RS 232 format. It can be used to interface with a laptop IBM compatible PC to load the database. Pin 5; SPARE LOADER RS 232 IN Pin 5 is a spare RS 232 input. Pin 6; SPARE RS 232 OUT Pin 6 is a spare RS 232 output. Pin 7; OBI SYNC. Pin 8; OBI CLOCK Page 2-4 IMKLN89/BLT Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/89B GPS RNAV Pin 9; OBI DATA This is a three wire data bus that provides bearing to the active waypoint. The data is in AlliedSignal format and can be used to drive certain AlliedSignal RMI units. The output can also be converted by a AlliedSignal KDA 692 which provides standard 4-wire SINE/COSINE OB! information. Pin 10; LATERAL DEV FLAG+ Pin 11; LATERAL DEV FLAG- Pin 12; VERTICAL DEV FLAG+ Pin 13; VERTICAL DEV FLAG- These are deviation flag outputs. DEV FLAG: outputs with respect to DEV FLAG-. For the specifications on these outputs refer to section 1.3 of this manual. Pin 14; AC GROUND Pin 14 is tied to aircraft ground. Wiring harness shields are not to be terminated on this pin. Refer to figure 2-17 Pin 15; WAYPOINT ANNUNCIATE Pin 18is the Waypoint Alert annunciator output. This output is tied to a remote annunciator lamp. When the line is pulled low the annunciator lamp will illuminate, The annunciator will be on whenever waypoint alerting is occurring. For more complete information refer the KLN 89/89B Pilots Guide, P/N 008-08786-0000. Pin 16; TATE Pin 16isthe Message annunciator output. This outputs tied to aremote annunciator lamp. When the line is pulled low the annunciator lamp wil illuminate. The annunciator will be ‘on whenever the message prompt on the KLN 89/89B is on. For more complete information refer to the KLN 89/898 Pilots Guide, P/N 006-08786-0000. Pin 17; APPROACH ARM ANNUNCIATE, Pin 17 is the Approach Arm annunciator output. This output is tied to a remote annunciator lamp. When the line is pulled low the annunciator lamp will illuminate. The annunciator willbe on whenever the unit is inthe approach arm mode. For more complete information refer the KLN 89/898 Pilots Guide, P/N 006-08786-0000. Pin 18; APPROACH ACTIVE ANNUNCIATE Pin 18 is the Approach Active annunciator output. This output is tied to a remote annunciator lamp. When the line is pulled low the annunciator lamp will illuminate. The annunciator will be on whenever the unit is in the approach active mode. For more ‘complete information refer the KLN 89/89B Pilots Guide, P/N 006-08786-0000. Pin 19; ALTITUDE ALERT ANNUNCIATE Pin 19 is the Altitude Alert output pin. The altitude alert feature can be enabled or disabled at installation time from the maintenance configuration pages as described in section 2.4.1 This feature is normally disabled if another altitude alerter (selector) is already installed in the aircraft. If altitude alerting is enabled, the pilot can choose to turn it on or off. If itis disabled, the pilot is not able to turn it on. Pin 20; TATOR 4 Pin 21; SPARE ANNUNCIATOR 2 IMKLN89/BLT Page 2-5 Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/89B GPS RNAV Pin 22; SPARE ANNUNCIATOR 3 Pin 23; SPARE ANNUNCIATOR 4 These pins are spare annunciator outputs. Pin 24; LIGHTING 28V/LO Pin 25; LIGHTING 14V ‘The lighting bus will use the DC power input pin as lighting low. For 14 V operation, LIGHTING 28V/LO is connected to ground and LIGHTING 14V is connected to the 14 V Panel lighting bus. For 28 V operation, LIGHTING 28V/LO is connected to the 28 V panel lighting bus and LIGHTING 14V is not connected, CONNECTOR Pas2 Pin 1; TEST Pin 1, when grounded on power-up, will place the unit in the test mode. Once in the test. mode, the unit will remain in that mode until power to the unit is turned off. Test mode is provided to assist in manufacturing and field service troubleshooting, Pin 2; TAKE HOME Pin 2, when grounded, places the KLN 89/89B in Take-Home mode which is used for ‘trip planning and fight simulation. It performs as if itis receiving adequate GPS signals to determine its position. It displays the latitude and longitude of its last known Position or of whatever position itis initialized to on the Setup Page. Pin 2 should always be left open in the aircraft installation. Take-Home mode must not be allowed during actual flight. Pin 3; SPARE INT Pin 4; SPARE IN? Pin 5; SPARE INS. Pin 6; SPARE IN 4 Pin 7; SPARE INO. These pins are spare inputs. Pin 8; APPROACH ARM IN Pin 8 is used as a select input. If the installation is not certified for approach, the external switch/annunciator is not needed. If the installation is approved for approach and the external switch/annunciator is installed, then a momentary ground on pin 8 will alternately arm or disarm the approach mode. Pin 9; LATERAL SUPER FLAG Pin 10; VERTICAL SUPER FLAG On supertiag outputs, a logic high shall be = 18 VDC when the voltage at pin 19 is > 24.8 VOC. A logic high shall be = 10 VDC when the voltage at pin 19is = 12.4 VDC. A logic high shall be 2 20 VDC when the voltage at pin 19 is + 27.5 VDC. A logic low shall be = 3.5 VDC. Pin 11; LATERAL DEV +L Pin 12; LATERAL DEV +R. Pin 13; VERTICAL DEV +UP Page 2-6 IMKLN89/BLT Rev 3 May/99BENDIX/KING KLN 89/898 GPS RNAV e Pin 14; VERTICAL DEV +DOWN These are deviation outputs and function as differential pairs. For the specifications on these outputs refer to section 1.3 of this manual. Pin 15; ALTITUDE ALERT AUDIO Pin 16; ALTITUDE ALERT AUDIO LO These pins represent the Altitude Alert Audio output which is active whenever ALTITUDE ALERT ANNUNCIATE is active. Pin 17; FOSTOCENG This annunciator is active when the lateral deviation scale factor is 0.3 nm. Itis also active while the scale is transitioning from 1.0 nm down to 0.3 nm. Pin 18; AC POWER MONITOR Pin 18 is the aircraft power monitor. It senses voltages ranging from 0 to 33 V, The KLN89/89B can be configured to allow the selection of a voltage alert set point and a voltage alert delay interval for use with this input. Refer to section 2.4.1 for the configuration procedure, The "Low Bus Voltage, Check Charging System” message is displayed when voltage at this pin is below the voltage alert set point for greater than the voltage alert delay interval. Pin 19; 11-33 VDC A/C POWER Pin 19 is the DC aircraft power input. The KLN 89/89B will accept from 11 VDC to 33 VDC. input power. e Pin 20; AIC GROUND Pin 20 is tied to aircraft ground. Wiring hamess shields are not to be terminated on this pin. Refer to figure 2-17. Gray Code Inputs Pin 21; D4 Pin 22; A1 Pin 23; A2 Pin 24; Aa : Pin 25; B1 Pin 26; B2 : Pin 27; B4 Pin 28; C1 Pin 29; C2 Pin 30; C4 These pins are gray code altitude inputs from an encoding altimeter. If the KLN 89/89B is paralleled with another unit such as a transponder, it may be necessary to install isolation diodes between one or both units and the encoder. The KLN 89/898 has diodes already installed internally. IMKLN89/BLT Page 2-7 Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/898 GPS RNAV Pin 31; GPS DISPLAYED This pin is used as an input to tell the unit whether an external indicator is connected to the analog OBS resolver inputs, in which case it will be high. This pin will be grounded if {an indicator is not connected or coupled to the unit Pin 32; +TO Pin 33; +FROM These outputs function like the outputs from standard navigation converters. For the specifications on these outputs refer to section 1.3 of this manual. OBS Resolver Interface Pin 34; OBS OUT Pin 35; OBS SIN Pin 36; OBS COS Pin 37; OBS RETURN This interface is compatible with indicators that are electrically zeroed (EZ) at 300 degrees and indicators that are omni-ranged zero at 300 degrees. This interface will operate Properly with either "0.85 gain” resolvers or "0.41 gain” resolvers with no special Programming requirements. OBS Resolver Out is a 450 Hz output used to excite the resolver. The resolver output voltage is then received by the OBS Resolver sine and cosine inputs. CONFIGURATION MODULE. The configuration module is a separate module from the main rear /O connector. Itis a serial EEPROM containing at least 16 bytes of capacity. Page 2-8 IMKLN89/BLT Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/898 GPS RNAV GENERAL RS 232 IN — GENERAL RS 232 OUT DATA LOADER RS 232 IN DATA LOADER RS 232 OUT SPARE RS 232 IN SPARE RS 232 OUT OBI SYNC 0B! CLOCK OB! DATA, LATERAL DEV FLAG + LATERAL DEV FLAG - VERTICAL DEV FLAG + VERTICAL DEV FLAG - ANC GROUND POINT ANI 1A MESSAGE ANNUNCIATE APPROACH ARM ANNUNCIATE APPROACH ACTIVE ANNUNCIATE ACTITUDE ALERT ANNUNCIATE ‘SPARE ANNUNCIATE 1 ‘SPARE ANNUNCIATE 2 ‘SPARE ANNUNCIATE 3 PARE ANT TATE LIGHTING 28V/LO LIGHTING 14V 4 beet eda iste eters 2 “INPUTS OUTPUTS — FIGURE 2-1 KLN 89/89B CONNECTOR PIN FUNCTIONS. (Pg. 1 of 3) IMKLNB9/BLT Page 2.9 Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/89B. GPS RNAV SPARE ING SPARE INS ‘SPAREING SPARE ING APPROACH ARM IN- LATERAL SUPER FLAG VERTICAL SUPER FLAG LATERAL DEV +L LATERAL DEV +R VERTICAL DEV +UP VERTICAL DEV +DOWN ALTITUDE ALERT AUDIO ALTITUDE ALERT AUDIO LO FCS LOC ENG AIC POWER MONITOR 11-33 VDC A/C POWER AVC GROUND D4 AI a2 Aa Bt B2 B4 C1 c2 C4 GPS DISPLAYED —+TO — +FROM = OBS OUT OBS SIN OBS COS 7 + OBS RETURN INPUTS OUTPUTS = FIGURE 2-1 KLN 89/89B CONNECTOR PIN FUNCTIONS (Pg. 2 of 3) evr OHs0N=9 eects bbudsdadda a ev tetet tet fet ete ae Page 2-10 IMKLN9/BLT Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/898 GPS RNAV PKT702 (Configuration Module Connector) - + EXT_EEPRM_CS EXT_EEPRM NIC — +5V NIC NIC — SERIAL_OUT SERIAL_IN ‘SERIAL_CLK GROUND Nic NIC AMOQDyPOHUs OWA INPUTS OUTPUTS —> P1011 (Software Programming Connector) — VPP = vec EXT_BOOT RESET HD(0) BFWR BF_WR EXT_BOOT_EN VBAT BOOT_VPP GROUND FLASH_VPP 4 4 4 + 4 INPUTS OUTPUTS —> FIGURE 2-1 KLN 89/898 CONNECTOR PIN FUNCTIONS (Pg. 3 of 3) IMKLNB9/BLT Page 2-11 Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/89B GPS RNAV CRIMPING Sane va naar Peres 0021 HAN, BOSTTRONIC yu e 308 POSITIONER P/N: 005-02012-0023 BUCHANAN P/N 612513 e@ POSITRONIC P/N: 9502-7 ee eec tN ps ALN: ee 02012-0025 MIL spre BAN 8 M24508/18- 12 FIGURE 2-2 KLN 89/898 CRIMPING AND INSERTION/EXTRACTION TOOLS. Page 2-12 IMKLN89/BLT Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/89B GPS RNAV FIGURE 2-3 KLN 89/89B INSTALLATION DRAWING (DWG. NO. 155-06020-0000 REV 3) IMKLNE9/BLT Page 2.13, Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/89B GPS RNAV — 75 MAX. | i 47 % 1.00 RAD BLEND OQ x USERAL7 1.600, SERIAL | 2.35 RAD BLEND & +1 To 5x 2.90 | I AREA I Li—4 Z 211 DIA. eee THRU HOLE BLEND 2.00 RAD, 4x ¢| tee “* t S20 390 x .375 peo 147 RAD DEEP, 4x STR prop BLEND \-———_ 911 TNC Connector io 2x .094 RAD BLEND 2x Sf 7 1.00 RAD BLEND, 2x 20.00 SURFACE RAD FIGURE 2-4 KA 91 OUTLINE Dwg. No. 071-01545-0200, R-4 IMKLN89/BLT Page 2-15 Rev 3 May/99IMKLN89/BLT Rev 3 May/99 AlliedSignal BENDIX/KING KLN 89/89B 8 e GPS RNAV 1— .s00 187-01807-0000 7 4% 089-08808-0012 #10-32 PHP SCREW. [12.70] CONDUCTIVE GASKET 047- 10130-0002 [20.32] BACKING PLATE }— .240 Sw (e.19) — luaho-~ — he 1 = ai =| 4.700 3.300 Lj | i (119.38) (33-02) ! i T i i 071-01845-0100/0200- +} z.200. 030-00134-0000 a ANTENNA TNC CONNECTOR notes: 1. REMOVE PAINT IN AREA OF ANTENNA INSTALLATION. 2. DIMENSIONS IN INCHES ( MILLIMETERS } 3. FOR BEST PERFORMANCE, BOND BETWEEN AIRCRAFT AND ANTENNA TO BE 10 MILLIOHNS RESISTANCE OF LESS 4. UNIT WEIGHT 5 LBS ¢ .227 KG. 1 S. FILL MOUNTING SCREW HOLES WITH RTV SEALANT. APBLY "WHITE RTV SEALANT. AROUND BASE OF INSTALLED ANTENNA. KPN 016-01128-0000 OR EQUIVALENT. 6. ANTENNA SHOULD BE MOUNTED 25° WITH AIRCRAFT AT LEVEL FLIGHT ATTITUDE. 7. 00 NOT PAINT ANTENNA 8. AIRSPEED RATING 600 KTS MAX TAS. FIGURE 2-5 KA 91 OUTLINE AND MOUNTING Dwg. No. 155-05999-0000, R-5 Page 2-17 AIRCRAFT SKIN, 1.600. [40.64] MOUNTING PATTERN 155059990000~ 70 19.701AlliedSignal BENDIX/KING KLN 89/89B GPS RNAV 4x @ .250 # .001 (ST e-or7 Oye) | 5755p — 80) —J See {je +082 NOTES: Te MATERIAL 15 ALUMINUM SHEET L— [iso] | a ae 3003 H'T4! 2062 THK, 2. DEBURR AND REMOVE SHARP EDGES 3.000 70 .010'R MAX= un L----------------------------=-------- ALTERNATE VIEW FIGURE 2-6 KA 91 BACKPLATE OUTLINE Dwg. No. 047~10130-0000/0002, R-2 IMKLN@9/BLT Page 2-19 Rev 3 May/S9AlliedSignal BENDIX/KING KLN 89/89B GPS RNAV sso 8 [ (Blend) os3 k Dimensions: Inches ty Wows 4 = NT 2B ; = saxo i i - SNe Conn. eat tho bee 2768 430 wx 1750 575 On, conn ae -Eiccones ie seat IMKLN89/BLT Rev 3 May/99 ‘® 32. R. 173 Die. Thru Hole, C'Bore Farside .352' Dio. 4 Places FIGURE 2-7 KA 92 OUTLINE Dwg. No. 071-01553-0200, R-1 Page 2-21IMKLN89/BLT Rev 3 May/99 AlliedSignal BENDIX/KING KLN 89/898 GPS RNAV }—.70 une : 2.70 wax——a (7.6) 7.4] Tee 8087187 p22 . Fe Shen 7 so YO ax 6 2s (ies) 4] 8 1.00 5.4) cs. fm —- [e3.5] 071-01383-0200- ANTENNA a 047-10735-0002 ‘TNC CONNECTOR: BACKING PLATE 187-0131 -0000- " “ CONDUCTIVE GASKET (AIRCRAFT KIND NOTES LNLESS OTHERWISE SPECIFIED: Ts REMOVE PAINT IN AREA. OF ANTENNA INSTALLATION. 21 DIMENSION IN INCHES {MILLIMETERS } 3. FOR BEST PERFORMANCE, BOND BETHEEN AIRCRAFT AMO ANTENNA TO BE 10 MILLIOMS RESISTANCE OF LESS. 4. UNIT WEIGHT 15 .27 USS (12 KO) St APPLY WHITE FTV SEALANT AROUND ASE OF INSTALLED ANTENNA. FILL MOUNTING SCREW HOLES WITH RTV SEALANT. {MPN 016-01129-0000 OR EQUIVALENT? ©. ANTENNA SHOULD BE MOUNTED LEVEL #5* WITH AIRCRAFT AT LEVEL FLIGHT ATTITUDE. 7. D0_NOT PRINT. ANTENNA, 13506019000: 8. AIRSPEED RATING GOOK1S MAX TAS. FIGURE 2-8 KA 92 INSTALLATION DRAWING Dwg. No. 155-06019-0000, R-2 Page 2-23AlliedSignal + (.060) IMKLN89/BLT Rev 3 May/99 FIGURE 2-9 KA 92 BACKPLATE OUTLINE Dwg. No. 047-10735-0000/0002, R-1 Page 2-25 BENDIX/KING KLN 89/898 GPS RNAV [+ 3.00 —————_-+ 4x @ .219 #.002 ueSoo [9 .030@AyeIc $1 .014@A + — $ 1.000 $[f.03@) ATSIC 5.00 1.750 4 2.500 2750 — 4X RADIUS OR CHAMFER .O8MAX 688 1.625 oa? NOTES UNLESS OTHERWISE SPECIFIED: ZX MATERIAL IS ALUMINUM 2024-73 Q0-A-25074, 4083 STOCK THICK AX FINISH 1S GOLD IRIDITE MIL-c-5541 CLASS 1A 3 DEBURR AND REMOVE SHARP EDGES +O1R MAX 047107350000-0002--0L.prtAlliedSignal BENDIX/KING KLN 89/89B GPS RNAV sieuBie Ton i v it ‘D WAShER INSULATOR cH nur coset — sHoUCbER © cONTACT PLUG B00" wahee ~0000 STRAIGHT CONNECTOR © i [© =0001_ RIGHT ANGLE CONNECTOR i} Place nut and gasket, with "V" groove toward Ea clamp, over cable and cut jacket to Lt fab dimension shown, i He Lt fond push bock ogcinst cable. jacket ttt it im a iA ( | srs tel mit svl eae Geet Sip teflon dar ever contac Insert prepared cable termination into connector ody. Make sure sharp edge of clomp seats property in gosket. Tighten nut FIGURE 2-10 KA 91/92 TNC ANTENNA COAX/CONNECTOR ASSEMBLY RG142B/U OR RG400 0 to 40 ft. (P/N 030-00134-0000, R-3 / 030-00134-0001, R-0) IMKLN89/BLT Page 2-27 Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/898, GPS RNAV COAX: CUT, STRIP AND SOLDER AS SHOWN. > INSTALL J 50 OHM MATCH AVOID EXCESS SOLDER oN = ON CENTER CONDUCTOR. G ‘AFTER INSTALLING CAP, TACK SOLDER — 2 PLACES. NOTES: 1. WHEN SOLDERING, AVOID APPLYING EXCESS HEAT TO CONNECTOR BODY, HEAT SINK SPRING CONTACTS, AND CENTER CONDUCTOR INSULATOR. FIGURE 2-11 KA 91/92 BMA ANTENNA COAX/CONNECTOR ASSEMBLY (RG142 B/U OR RG400 0 to 40 FT.) (Dwg. No. 030-00101-0002 Rev. 9) IMKLN89/BLT Page 2-29 Rev 3 May/99 >| 0.25de— HEAT SHRINK TUBING — | fe 0.125 ALOMTER SHIELD x INNER SHIELD OUTER SHIELD at STRIP RG-142B/U (P/N 024-00002-0000) AND PLACE 1” HEAT SHRINK TUBING (P/N 150-00025~-0010) OVER COAX SOLDER CENTER CONTACT AND SOLDER INNER SHIELD INSIDE. SEE NOTE 1 SOLDER OUTER SHIELD OUTSIDE. SEE NOTE 1. SLIDE HEAT SHRINK TUBING FORWARD (FLUSH WITH CONNECTOR) AND ADD HEAT TO SHRINK THE TUBING.liedSignal BENDIX/KING KLN 89/89B GPS RNAV SPLIT 4 PLACES 0.675 1. Place cable nut, bushing and i braid clamp over outer jacket. Mn = > 0.250 Trim cable jacket, braid and ' dielectric to dimensions shown. ' F4 Split outer jacket in 4 places Tally (approx. 90° apart) to dimension. ~ 0.050 Lightly tin center conductor. 0.350 Ny 2. Fold back braid, foil and inner Ky shield to expose dielectric. 3, Slide contact assembly (pin or CABLE NUT — gpaip socket) between inner dielectric y RAR. cont «aan bance a assy contact assembly is pushed on cable to flare outer jacket and center conductor is visible through inspection hole. Smooth shields CW back over contact assembly and v solder center contact as shown. BUSHING een CONNECTOR BODY Z 4. Push braid clamp and bushing forward over shield as far as [ possible. Slide cable nut over bushing and insert finished assembly into connector body. Tighten cable nut completely to seal cable assembly. FIGURE 2-12 KA 91/92 TNC ANTENNA COAX/CONNECTOR ASSEMBLY 0 to 80 ft. / 0 to 100 ft. (For Cable P/N’s 024-00071-0000, R-0 / 024-00072-0000, R-0) IMKLN89/BLT Rev 3 May/99 Page 2.31AlliedSignal BENDIX/KING KLN 89/89B GPS RNAV FIGURE 2-13 KA 33 P/N 071-4037-00/01 FINAL ASSEMBLY Dwg. No. 300-03256-0000, R-6 IMKLN89/BLT Page 2-33, Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/898 GPS RNAV |S WEIGHT! L28 LB8. (0.57 KG) FIGURE 2-14 KA 33 P/N 071-4037-00/01 OUTLINE AND MOUNTING IMKLN89/BLT Rev 3 May/99 Dwg. No. 155-05574-0000, R-5 Page 2-35 he voe.AlliedSignal BENDIX/KING KLN 89/89B GPS RNAV INSTALLATION ANO REMOVAL TOOLS (AVAILABLE FROM LCOMP) TPE EATON 7 PART NUMBER CONNECTOR PIN CRIMP TOOL Sat 105 CONNECTOR PIN REMOVAL TOOL, 587-104 |LoonnecTOR PIN REVOVE TP 587 105-2 ag -- ° jo} 2 ~~ I Sicora aay tH: ell PPL ees ete CONNECTOR BLOCK a T es ease | SOUR cm ° _ forks c jo] 7 NOo— swe alee fe] 6 al a frees & SWIICH CIRCUIT a sree S Sy (031676519000) NOTES: 1. MOMENTARY SWITCH TRAVEL IS SUCH THAT THE CAPSULE IS FLUSH WTS, OR RECESSED INTO, THE BEZEL OF THE SWITCH BODY WHEN FULLY ACTUATED. 2. ALTERNATE ACTION SWITCH TRAVEL AND RETAINED POSITION ARE SUCH THAT THE CAPSULE IS FLUSH WiTH, OR RECESSED INTO, THE BEZEL. OF THE SWITCH BODY WHEN ACTUATED 3. COMPLETE ANNUNCATORS/SMITCHES ARE AVAILABLE FROM LCOMP. PARTS FOR CONVERSION OR REPAIR ARE ALSO AVALABLE. COMP Aerospace Controls TELEPHONE: 9244 gone (313) «36—saeg Overland Pork, «5 86214 (goo) S2im291¢ (913) 438-4838 (FAX) FIGURE 2-15 CUTLER-HAMMER SWITCH/ANNUNCIATOR MOUNTING IMKLN9/BLT Page 2-37 Rev 3 May/S9 MP CaPsuAs i 088 (rage) 7| (REF) Stoo suten) ‘Bey amt nuwaca rg note, wovcares a ot 4 MOUNTING SLEEVES aE, UEDSGNAL [VENDOR RHcNEsS || BART NUMBER [PART NUMBER OMENSION “At ed eenedaean sz" tO 072" | ast-o07es-oOxe | —a686=29 [ oss" ro 103 | os1-o0765-00% | 4685-30 11s" To 135" | os1-o076s-o0s1 | 4686-51 USE THE ABOVE WIT EATON SERES sa O52" 10 072" | Os1-0078S-OO2 | A68E-29 oe 10 tas" | osi-oa7es-oox | ~ae5-30 TE" TO 138" | OBI-DOTES-OOH | —aB8E=37 THREE. SLEEVES AND & CONNECTOR BLOCK ARE PROVIDED USE THE ABOVE MIM EATON SERES S82 Z cprecron F SONNECTOR BLOCKS ARE P/N 031~00763-0060 FOR EATON SERIES 584 AND 031-00785-0060 FOR EATON SERIES 587, WIN EACH ANKUNCATOR/SWITCH ASSEMBLY TO ACCOMMODATE aU RANGE OF PANEL THICKNESSES, ee | i | uf ; ie os a 38) 4 | 7 Pel RECOMMENDED PANEL CUTOUTAlliedSignal BENDIX/KING KLN 69/898 GPS RNAV Ps, SPS ug [usc _] awecr) wer | (awaer) ANNUNCIATOR 28 Vv -0505, 44 v ~0762 Sv ~0508 DAY/NIGHT DIM PRESS TO TEST (GROUND = TEST) t MESSAGE ANNUNCIATE WAYPOINT ANNUNCIATE ops switching |_NAY PRESS To TEST (GROUND = TEST) (GREEN) (ewe) Ps, ‘SWITCH/ANNUNGIATOR 28 v -o711 44 v -o712 SV -o713 GPS SWITCHES/ANNUNCIATORS 031—00763~XXXX __ FIGURE 2-16 CUTLER-HAMMER SWITCH/ANNUNCIATOR INTERNAL SCHEMATIC (Sheet 1 of 2) IMKLN89/BLT Rev 3 May/99 Page 2-39AlliedSignal BENDIX/KING KLN 89/89B GPS RNAV Ps status i ops (wisiaLe wurTe) [ces crs SPS Ag [_wse_] (awaer) (awser) oas|uec| (oreen) wer | (awseR) (ec) ANNUNCIATOR ANNUNCIATOR 28 Vv -0763 28 V -0505 14 v 0764 14 v ~0762 oav/NIGHT DIM Sv -0765 SV 0506 7 PRESS TO TEST DAY/NIGHT OM — (GROUND = TEST) PRESS TO TEST T (GROUND = TEST) 1 MESSAGE ANNUNCIATE ! ce eee WAYPOINT ANNUNGIATE (105 aNnunciate i Ne sw, aa | i ' No i Ne wa, = No (GPs APR) Ps status, i ops fn (wisiace ware) [ops APR FS cane |_NAY_] (GREEN) ware) [arefacry| (oReeN) cps_| (e.ue) oe ‘SWITCH/ANNUNCIATOR ‘SWITCH/ANNUNCIATOR 28 V -0766 PRESS TO TEST 14 v ~0767 PRESS To TEST (GROUND = Test) Sv -0768 (GROUND = TEST) GPS APR ANNUNCITE bay /NIGHT DIM ARM ANNUNGIATE: ACTV ANNUNCIATE, No. o—o GPS SWITCHES/ANNUNCIATORS 031—00785—XXXX FIGURE 2-16 CUTLER-HAMMER SWITCH/ANNUNCIATOR INTERNAL SCHEMATIC (Sheet 2 of 2) IMKLN89/BLT Rev 3 May/99 Page 2-41IMKLN89/BLT Rev 3 May/99 AlliedSignal BENDIX/KING KLN 89/898 GPS RNAV aoe 9 oye sn TORRE ON 7 ame) “a cee eter FUEL/ARORTA COMPUTER a aod eee |e Soe TAROT COPTER] ra ; 7 BS 292 FUEL/AIROATA WITH FUEL FLOW WOIGATOR ee Eee | = ea sere usm [iiseay ASSL a a aN a eee ee ere r T= 7 oe v SHANI “SHAR “SHADD FueL sensor | oiGIGFLOW MINIFLOW MINIFLOW CEE OME MATOUT tao AIRDATAY rom RQ MREAP TE so RERTRRE HN TTB) | eae ce eee fil seater eee ee eee fleet a IE — a] FIGURE 2-17 KLN 89/89B INTERCONNECT DRAWING DWG. NO. 155-06023-0000, REV. AB (Sheet 1 of 8) Page 2-43 1 LOWERCASE ETTER CONNECTOR FIN DESCNATORS ARE SHOW 2 AL WIRES ARE_24-ANG MINIMUM UNLESS OTHERWISE NOTED. 3. GENRAL RS 232 OUT CAN ORIVE SEVERAL INPUTS. ONLY ONE ‘ausMirien CAN BE CONNECTED TO GENERAL RS 292 IN ATA TME. 4. 5 232 RECEIERS MAY NOT BE USED AS THE PRIMARY FLIGHT BIseLAY Fo TH KUN 8 5. L COMECT THESE SHIELD CROUNOS To AIRCRAFT CHASSIS = Wi AS SHosT A'CONOUCTOR AS PRAGTIONLAlliedSignal BENDIX/KING KLN 89/89B GPS RNAV e GRAY CODE (GILLHAM) ALTITUDE — |KEA T27 [REA 129 [REA 130 Fem T30a] nea 3x6 892[BENDIX/KING KLN 897898 Calliaat 7 7 7 a pe AL 2 2 a a 8 +--WHH_——- 4 22 Ja a2| 3 3 3 5 © 5 | an as] 4 + 3 : me NN 2 |e Bikle 5 5 5 Ns | e2| 9 9 9 9 een SEINE Es ee a) |) | ota w | oN oe | ae a} on n " n oe |r ce} os | a3 fous J os 8 | co] 2 | a2 | a2 | wv vf 5 | ce SIGNAL COMMON | _6 6 6 é r - El RADIO MAGNETIC INDICATOR BENOIX/KING | BENDIX/KING | EENDIX7KING | BENDIX/KING KI 229 kui 982 | kNI-s82. | KDA 692 growrer | y2 Pointer PID i POR esi [BENDIX/KING KLN 89/898 oat DATA IN| 19 16 L 9 | ont pata oat cock i} 12 8 7 1" J 8 | os1 crock x oat sync inf 11 33 24 u SH] 7 | 081 src Notes: 1. LOWERCASE LETTER CONNECTOR PIN DESIGNATORS ARE SHOWN AS UNDERLINED UPPERCASE LETTERS. 2. ALL WIRES ARE 24 AWG MINIMUM UNLESS OTHERWISE NOTED. 3. SOME RECEIVERS OF THE ALTITUDE ENCODER DO NOT HAVE INTERNAL ISOLATION DIODES TO PREVENT THE UNIT FROM PULLING THE ENCODER LINES TO GROUND WHEN THE UNIT IS OFF. SOME TRANSPONDERS AND OTHER DEVICES D0 NOT HAVE THE INTERNAL DIODES. THESE UNITS REQUIRE A DIODE TO BE ADDED TO THE INSTALLATION HARNESS FOR EVERY ENCODER LINE. THE DIODES ARE INSERTED AT THE CONNECTION TO THE UNIT THAT DOES NOT HAVE INTERNAL DIODES. THE ANODE IS ON THE RECEIVING UNITS SIDE AND THE CATHODE IS_ON THE ENCODER SIDE. A 1N80Q7, OUR PART NUMBER 967-06048-2000, MEETS HIRF_AND LIGHTNING REQUIREMENTS, A SET OF DIODES 1S REQUIRED FOR EACH UNIT WITHOUT INTERNAL DIODES. 4. L CONNECT THESE SHIELD GROUNDS TO AIRCRAFT CHASSIS WITH AS SHORT A CONDUCTOR AS PRACTICAL. FIGURE 2-17 _KLN 89/89B INTERCONNECT DRAWING DWG. NO. 155-06023-0000, REV. AB e (Sheet 2 of 8) IMKLN89/BLT Page 2-45 Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/898 BENDIX/KING KLN 89/898 VERTICAL OEVATION +0? VERTICAL OEMATION +00¥N VERTICAL DEVIATION FLAG + VERTICAL DEVIATION FLAG ~ VERTICAL SUPERFLAG LATERAL OEMATION +8 LATERAL OEMATION +1. LATERAL DEMATON FLAG 4 [LATERAL DEWATON FLAG = GPS RNAV @ NAV INDICATOR _BENODK7RNG)BEROR ANG SENODRINGISENOTRING]SENOI ANG] COLLINS | COALS] COLLNS | > [Fh : lt : aaa LOC ENGAGE - ~ -t ISEE NOTE 4 - Le - te te CcouRse oewaTion 48] ' was! 20 Hs peeslee course cewanion 44 a |v x lat 2» talote couRse cewamion 4stacl 8 nik £ al * Hel) He nay sureneiac] = iC . Sie iv| fe nav supemrinc @)] > = ie : > dri : tw] ois +mou| s |r « z |ai 2 t2| fe +n 2 v_ fast ES tid da 1. LOWERCASE LETTER CONNECTORS PLN OESIONATORS ARE SHOWN SSTUNBeRE MED UPPERCASE LETTERS 2 ALL WRES ARE 24 AWG MINIMUM UNLESS OTHERWISE NOTED. 3 NOT ALL RELAYS ARE NEEDED FOR ALL INSTALATIONS. A flat is Wor REGORED TF AN WblGRION PTS NOT SOW for Twar RELAY 4. A RELAY 5 NOT REQUIRED FOR THE LOC ENGAGE CONNECTION {ohn wolentam as TS Pi BEES NOT NAVE, A COURSE evation FUNCTION, I I USEO TO Pare THe Rit NEEDLE SL OMMECT THESE SUELO GROUNDS TO AIRERAFT CHASSIS = Win aS QuORT A CONDUCTOR AS PRAgTION, 6 ME GUOESLOPE DEY. NO FLAG SHOULD BE STEED SO THAT Mis osconmecIED rRow THE NAV HOKCATOR AND. AUTOMLOT in he oes wane FIGURE 2-17 KLN 89/898 INTERCONNECT DRAWING DWG. NO. 155-06023-0000, REV. AB @ (Sheet 3 of 8) IMKLN89/BLT Page 2-47 Rev 3 May/99 {LATERAL SUPERELAG + FROMIMKLN89/BLT Rev 3 May/99 AlliedSignal BENDIX/KING KLN 89/89B GPS RNAV [see notes Nav IF THE NAV RECEIVER IS NOT AFFECTED BY THE SHORTING To GROUND OF THE NAV INDICATOR OBS PINS CONNECTED To THE KLM 89/898 Oa RETURN, P892-57, THEN THESE RELAY CONTACTS ARE NOT REQUIRED. 4. THE 16% 165 NAY/COM AND THE KNS 98 AND KNS 81 RNAVS WILL FLAG SOME OF THEIR OUTPUTS WHEN. THEY ARE NOT CONNECTED TO AN OBS RESOLVER IF THE KUN 99/899 SHARES ‘THE NAY INDICATOR WITH ONE OF THESE UNITS THROUGH THE’ NAV/GPS RELAY, THE NAV RECEIVER'S O88 RESOLVENS MUST BE LoadeD AS SHOWN" “RESISTORS ARE 1/4. W, SI ‘OMISSION OF THESE sUMPeRS WiLL RESULT IN'A FLAGGED RADIAL DISPLAY ANO FROZEN GROUND. SPEED IN RNAY MODES. 5. aL CONNECT THESE SHIELD GROUNDS TO. AIRCRAFT CHASSIS, WITH AS SHORT A CONDUCTOR AS PRACTICAL FIGURE 2-17 KLN 89/898 INTERCONNECT DRAWING WG. NO. 155-06023-0000, REV. AB (Sheet 4 of 8) Page 2-49 ‘ i pon | BENDIX7KING KX 165 — i 2 | RoroR © tea i 3 | stator LD b= | onouno Ny i LINC Oe [BENDIX /KING]BENDIX/KING]BENDIX/KING]BENOIX/KING|BENDIX/KING|BENDIX/KING] COLLINS ‘COLLINS ‘COLLINS: ‘PERRY PERRY } wr ne” | cage | KIs25q | nel 352. | 10 S52" | KPLss2’| Hslee | Soia-ce | Sora-se | AO sea | RD 659 38/400 H2 | 38°42 ONLY gp HZ ONLY ‘COMBO BENDIX/KING parm | rau | rez | cum | em | rien m fevee| festa tea Rete rad fevers soa] KLN 89/898 os wml € ¢ Tx | w * 1 7 ee oy geno ala. ele cose} - : ts] ow 2 ee le tit csc] z 2 baloy SEE v 3 so fst fri fet bybie t SHEET t ‘ ' Ae 9s 0 (cos wy] L Reval z ‘ a fat fat fel A 7 ' 5 i t } Hi AI 85 08 ces E(costo)| ° ty 4 a‘ 5 5 st mat wt 4 fil Ute i : : : . aes cos r(swto)| t tel oy y . e fet foi fui A f Shoe 08s 6 (SIN) | ow. w t x 7 7 73 cot fa a Bl ¢ ” £ x pe a Hg] 35 | 08s SIN 31 |oPs orseuaven _ i : RNAV i BENDIX RING [ BENDIX FING se nore 4 | mNS 60" | KS’ Notes: eet Part 1. LONERCASE LETTER CONNECTORS PIN DESIGNATORS ARE SHOMN ” | Roror w ZAS"UNGERLNED UPPERCASE LETTERS 2. ALL WRES ARE 24 AWG MINIMUM UNLESS OTHERWISE NOTED. 1 3. NOT ALL RELAYS ARE NEEDED FOR ALL INSTALLATIONS, A Lu 7 = eel RELAY iS NOT REQUIRED IAN MOICATON PINES ROT OWN FoR Tar relat.AlliedSignal BENDIX/KING KLN 89/898 GPS RNAV NAV INDICATOR Con INTERCONNE: SEE NOTE 5 30 HZ ONLY [Pt 085 0 (cos Ht) 038 £ (cos Lo) cas NAY INDICATOR aeevere yy BENDIX/KING KX 165 ROTOR ¢ STATOR F ROUND (PRIMARY, jaeioD ING) INTERCONNECT) |e®t 382/583 : SEE NOTE 5 38.HZ ONLY i Pra BENDIX/KING KIN 89/896] as ¢ (sm mp] a 085 out ows F (sw co) cash] ow 088 cos ossc| v 08s RETURN case] ow 8s SIN Notes: 1. LOWERCASE LETTER CONNECTORS PIN DESIGNATORS ARE SHOWN ‘AS UNDERLINED UPPERCASE LETTERS, 2. ALL WIRES ARE 24 ANG MINIMUM UNLESS OTHERWISE NOTED, 3.NOT ALL RELAYS ARE NEEDED FOR ALL INSTALLATIONS. A RELAY IS NOT REQUIRED IF AN INDICATOR IN TS NOT SHOWN, For’ Har RELAY. WF TE NAV RECEIVER 15 NOT AFFECTED BY THE SHORTING 4o GROUND OF THE NAV INDICATOR OBS PINS CONNECTED TO THE KLN 89 OBS RETURN, P9237, THEN THESE. RELAY CONTACTS ARE NOT REQUIRED. 4 THE Kx 165 NAV/COM AND THE KNS Bf AND KNS 81 RNAVS: WiLi FLAG SOME OF THEIR OUTPUTS WHEN THEY ARE_NOT CONNECTED TO AN OES RESOLVER IF THE KLN 89. SARES THE NAV INDICATOR wiTit ONE OF THESE UNITS THROUGH THE NAV/GPS RELAY, THE NAV RECEIVER'S OBS RESOLVERS MUST BE LOADED AS SHOWN" RESISTORS. ARE’ 1/40, SH OMISSION OF THESE JUMPERS WiLL RESULY INA FLAGGED RADIAL OISPLAY ANO FROZEN GROUND SPEED IN RNAW MODES, FIGURE 2-17 KLN 89/89B INTERCONNECT DRAWING DWG. NO. 155-06023-0000, REV. AB (Sheet 5 of 8) 31 | 0s o1sPLayeD RNAV BENODX/AING] BENDIX/RING KNS 60 | KS 81 Pa Patt 1° F | RoroR w: e x | stator 0 5. SOME KPI $52/553'5 MAY HAVE LEFT THE FACTORY WITH A RESOLVER WINDING REVERSED. THE MAJORITY OF THE. UNITS WILE WORK CORRECTLY IF WIRED|PLR THE PAIMARY INIERCONNECT, USE THE ALTERNATE INTERCONNECT IF THE PRIARY DOES NOT WORK, USE OF THE WRONG INTERCONNECT RESULTS INTHE KUN 900.095 DISPLAY INCREWENTING WHEN THE INDIGATOR ‘OBS OECREWENTS AND VICE VERSA 6 CONNECT THESE SHIELO GROUNDS TO AIRCRAFT CHASSIS = wits AS SHORT A CONDUCTOR AS PRACTICAL IMKLN89/BLT Page 2-51 Rev 3 May/99IMKLN89/BLT Rev 3 May/99 AlliedSignal BENDIX/KING KLN 89/898 GPS RNAV r _ q 28 V DC LIGHTING ,.. ENGINE KIN BHTERE] 14 OC LIGHTING aq SEROTTAINE KN 677873] | FBMRE BO —] 24 | owe 20 v / 10 uuowmc gus vo—[24 | ucimnc 28 v / 10 N/c 4 25 | ucHTING 14 v 14. YoOC PANEL. = tos | LicuminG 14 v | ucHTINe Bus to—14 | a/c GROUND aHTING Bus Lo—14 | /¢ GROUND | L = — a ALTITUDE ALERTING DISABLED 251 [BENDIX/KING KIN 697898 NOTE: ALTITUDE ALERTING SHOULD OE DISABLED, ON THE MNT 1 PAGE, IF ANOTHER ALTITUDE ALERTING DEVICE 1S INSTALLED IN THE” AERA. nce —e-{r9 | ACTODEAERT ANwUNciATE n/e—e{s | arnmune arr avo10 N/e =| te | aLnTUDe ALERT AVOIO Lo ADDITION TO"THE. SONALERT. IDE ALERTING pee [BENDIX/KING KLN 89/898 fe Power SONALERT ALI sg | aca ERT annuncrareé njo—={1s | antune avert avoro n/c] 16 | aLntuoe aLeRr avDio Lo NOTE: AN ANNUNCIATOR LAMP MAY BE ORIVEN IN PLACE OF OR IN “ AUDIO SYSTEM ALTITUDE ALERTING ‘AUDIO SYSTEM BENDIK/RINE ] BENOIX/RING | BENOIXZENE | BENODZRING [BENOIX/KING KLN 897898 nfo —ef se | ROTTODE-ACERT ANNU un 2a | Svaa 24H | UKMA 20H | HUA 26 ve ee [5/51752/55 | 7071 Paes zai ean 201 . 192 nswircHeo UNMUTED AUOIO] T 1° 2 fis | anmuoe acer auoio crow | 1 © 3 Hate | arrrupe ALERT av010 10 NOTE: AN UNSWITGHED, UNMUTED INPUT MUST BE USED INTO THE AUDIO SYSTEM. F MULTIPLE AUDIO OUTPUTS ARE_CONNECTED TO A SINGLE INPUT ON AN. ‘AUDIO. PANEL. THE AUDIO OUTPUT LEVEL GF ALL GF THE UNITS CONNECTED JO'THE PIN Ts REDUCED. THE AUDIO LEVEL MUST THEN BE ADIUSTED. At THE AUDIO PANEL OF AT EACH OF THE CONNECTED UNITS ANY “Te"AN ADDITIONAL UNIT TS CONNECTED, VERIFY THAT TURNING THE POWER OFF ON EAGH OF THE souRCES Does L NOT Sto Tue: AUDIO FROM ALL THE SOURCES SHARING THE INPUT. FIGURE 2-17 KLN 89/898 INTERCONNECT DRAWING DWG. NO. 155-06023-0000, REV. AB (Sheet 7 of 8) Page 2-55 1. LOWERCASE LETTER CONNECTOR PIN OESIGNATORS ARE SHOWN [AS UNDERLINED UPPERCASE LETTERS. 2. ALL WIRES ARE 26 AWG MINIMUM UNLESS OTHERWISE NOTED, 3 CONNECT THESE SHIELD GROUNDS TO. ARRAFT CHASSIS = WIM AS SHORT & CONDUCTOR AS PRACTICALAlliedSignal BENDIX/KING KLN 89/89B GPS RNAV @ aot [BENDIX/KING KLN 89/898 L fa} 5 4 |oxta Loanen es 232 ovr To. SERIAL PoRT [-Y poe f 3 Ht TET 5 | Bata tonpen ne 232 1 a SEE NOTE « ed [GROUND TO AIRFRAME) n/c 5 | SPARE RS 232 IN ieoeelneeniee jom—e}] 6 | soane as 232 out (20 awe) 14 | A/C GROUND oon o Use | are orcuno A/C POWER — > (26 AWG) 19 | 11-33 V DC A/C POWER 12 |e power wcnrTon SEE NOTE 3-=— 2 | TAKEHONE ee res KA 91/KA 92 Me Sieh se No 4 a & ls) 2 ANTENNA rou NOTES: 1. LOWERCASE LETTER CONNECTOR PIN DESIGNATORS ARE SHOWN 5 AS UNDERLINED UPPERCASE LETTERS. 2. ALL WIRES ARE 24 AWG MINIMUM UNLESS OTHERWISE NOTED. 3. THIS PIN MUST ALWAYS BE OPEN WHEN THE UNIT IS USED FOR - NAVIGATION. THIS PIN IS CONNECTED TO GROUND TO PLACE THE UNIT IN THE TAKE HOME FLIGHT SIMULATION MODE. 4. PART OF 950-03213-0000 INTERFACE KIT. 5, WIRE TYPE VARIES WITH WIRE LENGTH. REFER TO ANTENNA INSTALLATION CONSIDERATIONS SECTION OF INSTALLATION MANUAL FOR DETAILS. 6. L CONNECT THESE SHIELD GROUNDS TO AIRCRAFT CHASSIS WITH AS SHORT A CONDUCTOR AS PRACTICAL. FIGURE 2-17_ KLN 89/89B_ INTERCONNECT DRAWING DWG. NO. 155-06023-0000, REV. AB (Sheet 8 of 8) IMKLN89/BLT Page 2.57 Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/898, GPS RNAV AIRCRAFT PANEL PC NEXUS. P/N MSI77/4~1 WN Ee (ON AIRCRAFT GROUND 25 PIN CONNECTOR, AN ADAPTER (SEE DETAIL 8) MUST BE USED. ATA LOADER OUT ROUND DATA LOADER IN KLN 89/898 e Pas DETAIL A DETAIL B DETAIL C FIGURE 2-18 KLN 89/89B DATA LOADER/PC INTERFACE DRAWING IMKLN9/BLT Page 2-59 Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/898, GPS RNAV 2.4 POST INSTALLATION CHECK OUT INFORMATION 2.4.1 Maintenance Pages ‘As part of every KLN 89 and KLN 898 installation itis necessary to enter the Maintenance (MNT) pages in order to configure the unit properly for the specific installation. Electronically configuring the units replaces the need of installing strapping or configuration wires in the harness. This makes. it easier to configure the unit at the time of intial installation and also later on if changes are made tothe aircraft such as the later addition of a fuel management system, air data system, or upgrade from VFR to IFR. This configuration data is stored both in the external configuration module (mounted in the back plate of the mounting tray) and in memory internal to the KLN 89/8. When the KLN 89/B is initially shipped from the factory, the configuration data is set to the same default values/status in both the external configuration module and the units internal memory. The initial defaults are specified below. When the Maintenance pages are entered and changes made to the configuration data, the changes are stored both in the external configuration module and the internal memory. If the ‘configuration data differs in the external configuration module from the units internal memory, the external configuration module data is automatically used. Differences could occur if after configuring the KLN 89/B the initia! unit was removed and a second unit inserted into the rack. For example, if the KLN 89/8 is initially configured correctly and a loaner unit is later installed in the aircraft, the external configuration module would ensure that the proper configuration data was used. The external configuration module is part of he installation kit and should be utilized in every installation to make sure that proper operation occurs regardless of the unit that may later be inserted into the mounting tray. ‘To enter the Maintenance pages, the MSG button must be depressed before the unit is tumed on and continue to be depressed for 10 seconds (+/- 2 seconds) after turn on. At the end of the 10 ‘second period, release the MSG button for 1 second and momentarily press the MSG button again. Following this sequence, the unit will automatically enter the Maintenance (MNT) pages. After entering the Maintenance pages if the configuration data is different between the external module and the units internal memory, the following page is displayed (this page will not be displayed if they are the same): CONFIGURATION 1. Copy Module to Unit? 2. Copy Unit to Module? Select:1 OK? lf you wish to copy the configuration data from the external configuration module to the units internal memory OR if you plan to manually change the configuration data, simply press the ENT button, Hf you wish to copy the configuration data from the units internal memory to the external module, turn the large outer knob counterclockwise to position the flashing cursor over the 1. Turn the small inner knob to select a 2. Turn the large outer knob one step clockwise to position the cursor back over the OK? and then press the ENT button. IMKLN89/BLT Page 2-61 Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/898 GPS RNAV 2.4.1.1 Maintenance 1 (MNT 1) pages ‘The MNT+1 page is now displayed. There are three MNT+1 pages. The + sign indicates that there is more than one MNT 1 page. The first MNT 1 page has the following selection choices and format: 1. Whether the unit is certified as IFR or VFR (KLN 898 only, KLN 89 does not offer this choice since it is always VFR). 2. Whether the unit is certified for IFR en route/terminal use only or for both en route/terminal and Nnon-precision approach (applicable to KLN 89B only). 3. Whether the altitude alerting feature is enabled or disabled. If the aircraft has another source of altitude alerting such as that associated with a flight control preselector, this feature should be disabled, First MNT+1 Page format Selection Choices Default IFRIVFR: IFR IFR (KLN 898 only) or VFR VFR IFR Apr/Enr: Apr Apr or Enr (KLN 898 only - blank Enr if ine one above is VFR) ALT alt: Enabled Enabled or Disabled Disabled To change a selection: Press the CRSR button to bring the flashing cursor on the screen. Turn the larger outer knob to position the cursor over the desired selection. Turn the small inner knob to change the selection. Make any additional changes on this page at this time. When finished, press the CRSR button to turn off the cursor. To select different MNT pages: ‘Tum the small inner knob (the flashing cursor must be off the page. fit is on, press the CRSR button to turn it off). Select the second MNT+1 page. ‘The second MNT+1 page has the following selection choices and format. Changes are made using ‘the CRSR button and concentric knob as described above. 1. Whether the KLN 89/8 is interfaced with a fuel management system. 2. Whether the fuel management system includes it own controlindicator used to enter fuel quantity. (Not a choice if there is no fuel management system), 3. Whatis the full fuel quantity of the aircraft. (Not a choice if there is no fuel management system or if the fuel management system has its own control/indicator used to enter fuel quantity), Second MNT+1 Page format Selection Choices Defautt Installed Equip Fuel Mgt Sys: Y Y of N for yes and no N Fuel Mgt Ind: N Y oF N (this line blank if N is selected above) N Full Fuel: 0064 0000 to 9999 (this line blank if no fuel mgt sys or if fuel mgt sys has its own control/indicator) 0000 Page 2-62 IMKLN89/BLT Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/898 GPS RNAV 2.4.1.4 Maintenance 4 (MNT 4) Page The MNT 4 page is used to set the bus monitor voltage and alert delay so that if the aircraft's charging system were to fail (ie. generator/alternator failure) the pilot would be given timely notification of the failure. The alert delay is selected so that momentary voltage drops which could be caused by such things as cycling the aircraft's gear or flaps do not cause nuisance notifications tothe pilot. When the bus voltage falls below the selected alert voltage for the selected alert delay time the unit notifies the pilot with the following message that is displayed on the message page: Low Bus Voltage ‘Check Charging System This Power Monitor feature can be turned on and off by the pilot on the SET 10 page but actual configuration can only be done from the MNT 4 page. The SET 10 page displays to the pilot the actual bus voltage to the KLN 89/B as well as the alert voltage and alert delay that have been Configured on the MNT 4 page. Changes are made to the MNT 4 page using the CRSR button and the concentric knobs as described in section 2.4.1.1. ‘The MNT 4 page has the following format and choices: MNT 4 Page format ‘Selection Choices Default BUS MONITOR Alert Volt 12.8V 0.0 - 33.0V 10.0V Alert Delay 15S 0 - 99 seconds 15 seconds The following procedure is suggested as a means of determining what voltage to use for the alert voltage. Cycle power to the KLN 89/6 to exit the Maintenance pages. View the SET 10 page to determine the actual voltage being supplied to the KLN 89/B while the engine is running (alternator/generator supplying the bus voltage). You may want to do this with the engine at idle so that you see the lowest possible voltage supplied by the alternator/ generator. Next, determine the actual voltage being supplied to the KLN 89/8 when only the battery is supplying the voltage {alternator/generator turned off or engine not running). ‘The alert voltage should be chosen to be about half way between these two voltages. For example, ina 14 volt aircraft say the alternator supplied voltages 13.8 volts as displayed on the SET 10 page with the engine running. The battery supplied voltage with the engine not running is 12.0 volts. An appropriate alert voltage in this case would be 12.9 volts. If an alternator were to fail in flight and the voltage drop to 12.0 volts for at least 15 seconds (or whatever alert delay time was selected), the pilot would be notified of the problem. NOTE In order to prevent nuisance messages, this feature should be disabled (Alert Volt OFF) on the SET 10 page on aircraft where the alternator/generator output drops down to a voltage close to the battery voltage during engine idle. When the maintenance pages are configured as desired, itis necessary to cycle power to the unit, in order to leave the maintenance pages and allow normal operation. Page 2-64 IMKLN89/BLT Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/89B GPS RNAV e The thitd MNT+1 page has the following selection choices and format. 1. Whether the KLN 89/8 is installed with an air data computer. 2. Whether the KLN 89/B is installed with a back-up emergency battery (not available from AlliedSignal). 3. Below what aircraft bus voltage should the back-up battery be used. (Not a choi no emergency battery). if there is Third MNT+1 Page format Selection Choices Default Installed Equip : Air Data: Y Y of N for yes and no N Emerg Bat: Y Yorn N 5 Use Bat: 10.2V 0 ~ 33 volts (this line blank if no emerg bat) 10.2V 2.4.1.2. Maintenance 2 (MNT 2) Page ‘The MNT 2 page displays hours and number of power cycles on the KLN 89/B and is not configurable. 2.4.1.3 Maintenance 3 (MNT 3) Page e@ ‘The MNT 3 page is used to calibrate the OBS setting of the aircraft's HSI or CDI to the KLN 89/8 sothat the KLN 89/8 reads the value the pilot selects on the HSI or CDI. Itis necessary to configure this page only if the KLN 89/8 is interfaced to an HSI or CDI resolver such that the KLN 89/B is able to read the course selected on the HSI or CDI. To calibrate the OBS: 1. Select a course using the course select/OBS knob on the HSI or OBS that is interfaced with the KLN 89/B . Itis suggested that a course increment of 10 degrees (example 10,150, 270, etc.) be used so that the course can be selected as precisely as possible. 2. Press the CRSR button to turn on the cursor. Use the small inner knob to select the exact course that is selected on the HSI or CDI in step : 1 above. 4. Adjust the HSI or CDI to another course which is NOT 180° away from the original course, and : verity the correct course is displayed within 2° . If not, the OBS resolver interface may be miswired. 5. Press the CRSR button to turn off the cursor. The calibration is now complete, IMKLNS9/BLT Page 2-63, Rev 3 May/99.AlliedSignal BENDIX/KING KLN 89/89B GPS RNAV 2.4.2 POST INSTALLATION CHECKOUT PROCEDURE ‘This procedure is divided into two major sections. The first section deals with Stand Alone” installations in which none of the signal Input/Output capability of the unit is utilized, (except for the AF input signal from the antenna). In this type ofinstallation the only connections tothe KLN 89/89B are the cable from the GPS antenna, the aircraft power and ground leads, and the lighting bus wires. NOTE All output datais read from the unit front panel display and alll input to the unit is via the front panel controls. The second part of this procedure deals with an installation in which some or all of the electrical ssignal /O have been utilized. This second section is divided in such a way that each input or output signal is treated separately, and hence only those subsections that apply to a given installation will be conducted. Itis assumed that the operator's manual for the various units connected to the KLN 89/89B (as well as the manual for the KLN 89/898 itself), are available or that the installer is familiar with operating the units. 2.4.3 INSTALLATION CHECK OUT Before inserting the unit into the mounting rack, verify that at the rear connector of the mounting rack, aircraft power is present on P892 pin 19, and that there is a ground on P891 pin 14 and P892 pin 20. In installations using 28 V lighting, lighting bus voltage should be present between P891 pins 24 and 14. In installations using 14 V lighting, lighting bus voltage should be present between P891 pins 25 and 14. Verify that there are no voltages or grounds present on any other pins of P89t and P892. ‘A. Making sure that the power On/Off switch, located on the front panel of the KLN 89/898, is. rotated the “off” position (power off), plug the unit into the mounting rack and verify that the panel lighting works properly. Energize the unit by rotating the power control switch to the “on” position. C. Manipulate the controls as necessary to display the Set 1 Page on the right half of the screen. ‘On the Set 1 Page, enter the airport name or the present position (latitude and longitude) for the installation location accurate to within 60 nautical miles. Display the Set 2 Page. Verify that the date and time are correct to within 10 minutes and update if necessary. D. Atthis point the aircraft will have to be movedto alocation known to have reasonable GPS signal coverage. This implies an outside location away from tall structures that could mask low elevation satellites. (To speed up the next test itis helpful to turn unit power off then on again once the system is away from structures) » IMKLNB9/BLT Page 2-65 Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/898. GPS RNAV E. Proceed to the OTH 1 page. The State shown on the display should change to Acquire (ACQ) from INIT and after a period of not more than 5 minutes, (typically two minutes depending on the satelite coverage), the unit should display Latitude and Longitude values on the Nav 2Page that are correct for the installation location. ifthe unit has not been turned on for 6 months, the Unit will take up to 20 minutes to calculate a position. F. Select the OTH 2 page, verify that no asterisks appear next to any satellite with an elevation greater than 25". Select 121.15 MHz on COMM 1. Transmit on COMM 1 for a period of 20 seconds and verify that no asterisks appear indicating satellites with an elevation of greater than 25°. Repeat for the following frequencies 121.175, 121.20, 131.250, 131.275 and 131.30 MHz. Repeat the above procedure for all VHF COMM's on board the aircraft. If any of the above tests do not pass (any asterisks appear on satellites with greater than 25° during the above tests), it will be necessary to identify the source of the interference. There are two common sources of interference: 1. The 12th and 13th harmonics of the above mentioned frequencies can be radiated from the VHF COMM at a level strong enough to be a problem to the GPS but still be well low enough tomeet TSO requirements for the VHF COMM. If the interference is from the radiating VHF COMM, an optional notch filter (i.e. the KA 198 P/N 071-01565-0000 or TED Mfg 4-70-54) will need to be installed. The recommended location for the inline filter should be as close to the VHF RT as practical. NOTE The conditions and tests performed on this article are minimum performance standards. It is the responsibilty 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 these performance standards. The article may be installed only if further evaluation by the applicant documents an acceptable installation and is approved by the Administrator. 2. The other possibilty is re-radiation from an ELT. The radiated RF from the VHF COMM can excite the output tank circuit of the ELT and cause it to oscillate and radiate RF strong enough to interfere with the GPS. If disconnecting the ELT antenna eliminates the GPS interference, the manufacturer of the ELT should be contacted for a recommended solution. 2.4.4 INTEGRATED INSTALLATION CHECK OUT The following paragraphs define checkout procedures for all possible Input/Output signals that can be connected to the KLN 89/89B. It should be clearly determined which of the signals are intended tobe used in any given installation and then only the paragraphs pertaining to those signals should be performed. 2.4.4.1 All Installations Perform all steps defined in Paragraph 2.4.3 and leave the system energized with a valid GPS signal being received. 2.4.4.2 CDIHSI Interface Cycle the power on the KLN 89/89B which will cause the self test page to be displayed. Verity that the CDI needle, after ithas settled, is indicating half scale right deflection. Verify that the TO/FROM flag is indicating FROM. Verify that the nav flag is pulled from Page 2-66 IMKLN89/BLT Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/898 GPS RNAV Verify the selected course from the CDI/HSI is interfaced properly to the KLN 89/89B in the OBS Mode. You must create an active waypoint on the Flightplan 0 page to check the following function, The OBSILEG selection is controlled through the OBS button located on the front panel of the KLN 89/898. Pressing this button toggles between LEG and OBS with the normal position being LEG. During OBS mode, the LEG indication (located lett of the vertical page divider) will change to athree digit course value. Verify that the selected course value agrees with the value displayed on the HSI Course Pointer. ‘Change the selected course value on the HSI or CDI using the OBS knob. Verify that the selected course value displayed on the KLN 89/89B tracks the new value selected. Inthe OBS mode with the GPS displayed on the CDI/HSI, the resolveris disconnected from the NAV converter. Verify that the KNS 80 or 81 groundspeed is still functional and the Radial display for the KX 165 or KNS 81 is stil functional. These units must have jumpers or resistors across them when the resolver is removed. In the OBS mode with the GPS not displayed on the CDI/HSI, the resolver is reconnected to the NAV converter. Verify that change in the OBS resolver will not affect the selected OBS on the KLN 89/898. 2.4.4.3 Gray Code Altitude Inputs With gray code altitude being supplied by a compatible encoding altimeter, verify that the proper altitude is indicated on the ALT page (provided no other altitude sources are active and that proper aro setting has been entered). Verify that there is no interference between the KLN 89/89B, transponder, and any other loads on the encoding altimeter output. Remove power from each of the loads on the encoder to verify that the remaining equipment still performs properly. If interference exists, one or more of the units are not diode isolated and isolation diodes will need to be added to the aircraft wiring, 2.4.4.4 RMI Interface Cycle power on the KLN 89/898 which will cause the self test page to be displayed. Verify that the RM| indicates 130°. 2.4.4.5 ELT Interface The following test must be conducted within five minutes after the hour with ELT transmissions limited to 3 (Three) sweeps. A sweep occurs each time there is a voice transmission. Verify that the present position is displayed on the KLN 89/89B Nav 2 page. Activate the Comm Receiver and tune it to 121.5 MHz. Switch The ELT cockpit toggle switch to TEST. The ELT light should flash and the “sweeping” sound of the ELT should be heard on the Comm Receiver. Within 1 (one) ‘minute, a voice transmission should be heard which contains the present position displayed on the KLN 89/898 Nav 2 page. Switch the toggle switch to AUTO and push the reset button until it stops flashing. 2.4.4.6 Moving Map Interface Ifthe KLN 89/898 is interfaced to a moving map display, verify operation by moving the aircraft out to an open location to acquire a satelite position. Enter some active flightplan or waypoint to develop a presentation on the map. Some moving maps require 2 kts of ground speed to display as the sense track angle is used instead of the heading. The KLN 89/89B does not output track angles when the groundspeed is below 2 kts. IMKLN89/BLT Page 2-67 Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/89B GPS RNAV 2.4.4.7 External Annunciators Recycle the power on the KLN 89/898 which will cause the Self Test Page to be displayed. Verity that all external annunciators are energized. Cycle the KLN 89/89B display past all initialization pages. Verify all external annunciators are extinguished. If the message light comes on, view the Message Page to verify that there is a message. If any other annunciator remains lighted, review the status of the KLN 89/89B to determine if the lighted annunciator is justified. NOTE Annunciators should be checked one at a time in order to verify that the correct one lights. 2.4.4.8 Dataloader The data base cartridge may be updated with a new database using a laptop computer. The laptop computer must be IBM compatible, have an open COM port (1,2,3, or 4). Internet Update ‘Anew database can be obtained via the INTERNET at the following address: http://www.gpsdatabase.com Store the new database on the hard drive of the PC. Then connect the laptop via the PC loader kit PN 050-03213-0000 (ref. figure 2-18). Turn on the KLN 89/89B to the SET 3 page. Then run the program NETLOAD.EXE and follow the appropriate instructions. Diskette Update Connect the laptop via the PC loader kit PN 050-032-0000 (ref figure 2-18). Turn on the KLN 89/898 to the SET 3 page. Insert the 3.5” Database diskette into the PC. Cycle the power of the PC and follow the menu driven instructions. (A small number of PC's may exhibit problems during the load because a few select BIOS services are incompatible with the AlliedSignal diskettes. If there is uncertainty relating to this, contact AlliedSignal Product Services (913) 782-0600.) NOTE ‘The KLN 89/89B database may be updated using a PC with the KLN 89/89B mounted in an aircraft (ref. figure 2-18). 2.4.4.9 ACTALERT, ALT ALERT AUDIO Upon approval of the self test page, five (5) beeps will be issued on the audio output and five (5) sonalert bursts will be produced by the ALTALERT output, if ACT ALERT has been configured “Enable”. 2.4.4.10 Heading Interface Heading information may be interfaced to the KLN 89/89B by RS 2320 aid in the calculation of wind vectors and for heading orientation of the NAV 4 or moving map. RS 232 heading information may be provided from an analog to RS 232 converter, such as the Shadin fuel/air data device, through the RS 282 input. Display the NAV 4 page and select the HDG orientation to test the heading function. If a valid heading source is available, HDG orientation will be selectable. Tum the cursor on the Nav 4 page to display the heading value when the HDG orientation is selected, Page 2-68 IMKLN89/BLT Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/898 GPS RNAV 2.5 ERROR CODES The KLN 89/B provides numeric error codes and text messages for certain failures. The following table may assist in identifying the root cause of these problems. Table 2-1 GPS Rec. Error Codes Definition Suggested Action XXXX: RCVR Hardware Error: 0002 RCVR Hardware Error: 0004 RCVR Hardware Error: 0008 RCVR Hardware Error: 0010 RCVR Hardware Error: 0080 RCVR HW Error: ‘This message appears when the KLN 89/B fails a specific internal test for the GPS receiver. The possible failure codes are described below. ROM Failure: The ROM memory has failed self-test. RAM Failure: The RAM memory has failed self-test /Nonvolati Memory Failure: ‘The battery-backed RAM has failed a checksum test. Non- volatile memory will be cleared. ‘This means the receiver is not sensing a proper RF signal from the satellites! antenne, ASIC Failure: The GPS (Correlator ASIC fails self-test Bad ROM. Return for service. Bad RAM. Return for service Tt could be one of the following, in the order of probability: 1. The battery-backup power to the GPS Receiver was lost. This could be due to either a dead internal battery or a bad connection on the cable to the receiver 2, The RAM memory is bad. could be one of the following, in the order of probability: 1, Coax open or shorted. Confirm the 5 volts at the antenna end, 2. Bad antenna. Substitute the antenna or inject signal atthe coax. 3. Bad Receiver Module in GPS. Substitute the GPS unit or inject signal atthe input. It could be one of the following, in the order of probability: 1, The flex cable between the Receiver and Main Board may have come out of the socket in the GPS, 2. Bad ASIC on receiver module in GPS. Substitute the GPS unit IMKLNB9/BLT Rev 3 May/99 Page 2-69AlliedSignal BENDIX/KING KLN 89/898 GPS RNAV Table 2-1 (cont.) GPS Rec. Error Codes Definition Suggested Action RCVR Hardware BBP Timeout: The 1mS | could be one of the Following, inthe order of Error: 0100 baseband processing timer has. probability failed self-test 1, The 5 volt supply tothe antenna could be shorted out in the coax. This disables the ‘oscillator in the GPS. 2. The flex cable between the Receiver and Main Board may have come out of the socket in the GPS. 3. Bad TCXO or ASIC on receiver module in GPS. Substitute the GPS unit RCVR Hardware RS-232 Receive Failure: | could be one of the following, inthe order of Error: 0400 The GPS Receiver did not | probability receive any initialization data |The flex cable between the Receiver and {rom the host computer on the |” Main Board may have come out of the RS-252 port socket in the GPS. 2. Bad 32KHz crystal, UART, or processor on Receiver Module in GPS. Substitute the GPS unit. RCVR Hardware EEPROM Failure: The | Bad EEPROM. Return for service. Error: 0800 EEPROM memory has failed its checksum. RCVR Hardware RS-232 Channel 2 Failure: {It could be one of the following, in the order of Exror: 1000 The second RS-232 UART on | probability the receiver has failed the loop |) the receiver was putin test mode without fmtieecetegen” | Deseret na tn smd only be enabled during te Misdeoa the eae eat |2. ad ASIC or Microprocessor onthe should not be seen in normal | feceiver. operation, Page 2-70 IMKLN89/BLT Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/89B GPS RNAV Table 2-2 GPS Page Messages Suggested Action ‘Alttde Fail Todicales missing oF NAV Superflag Faiture RAIM position ertor Cross check position No RS-232 Data RAIM not available [Cross check position erroneous altitude ‘The altitude input on the gray Jcode input from the encoder is wrong. ‘The GPS is configured for IER, and there is no altitude source available {indicates an internal test of the NAV Superflag output has failed. RAIM is a method of calculating integrity in the GPS position. It calculates the position multiple times using different sets of satellites and. ‘compares the answers. If they have excessive difference, the message appears, ‘There is no RS-232 data atthe /RS-232 input port. ‘This means there are not enough satelites available to ‘compute integrity (RAIM). 1, The satellites are blocked from view by obstructions, 2. They are fo0 low on the ho~ rizon for use of too high for adequate geometry. 3. There is loss of sensitivity in the antenna, the coax or re= ceiver module. The altitude from the encoder may be in error Jdue to a miswite, or the absence of isolation [diodes between the encoder and the transponder. If the GPS is configured for IFR, it must have a valid altitude. Verify the presence of altitude fon the Self-Test or Altitude Pages (press the [ALT button). When the flag is supposed to be valid, it should reach a minimum voltage. Usually a failure is due to overloading of the output. The output can be tested when the Self-Test Page is displayed. It could be one of the following, in the order of probability 1. This probably is a GPS receiver failure. Cross check your position by other means of navigation. Return for service. 2. The GPS has detected a problem with one of the satellites, and cannot be assured to be with- in TER limits. ‘The Air Data/Fuel Flow source is not outputting RS 232 data to the GPS, If no source of RS-232 is interfaced, the receiver input must be jumpered back to the RS-232 Output. ‘The aircraft should be in an open area with ‘good visibility, and the SNR’s (Signal to Noise Ratio) on the STA 1 or OTH 2 should be: A KLN 89/B will usually have 6-8 satellites shown, and the majority of their SNR’s will be 7 t0 9. SNR’s of 3 and below are unusable, 4 is marginal, and 5-9 are considered good. If the SNR’s are low, it could be one of the following, in the order of probability 1. Check the antenna coax and connection for problems, 2. Verify that 5 volts is present atthe antenna ‘end of the coax. 3. Substitute the receiver to check for sensitivity. 4. Substitute the antenna to check for sensitivity. IMKLN89/BLT Rev 3 May/99 Page 2-71AlliedSignal BENDIX/KING KLN 89/898 GPS RNAV Table 2-2 (cont) GPS Page Messages Definition ‘Suggested Action [RAIM not available | This isa calculated prediction | This isa feature, nota system falure /Approach mode jof RAIM availability. The inhibited ‘message appears when ‘Turn to the OTH 3 page to perform a RAIM. pee itegnty monitoring AIM). | region, It wil give you an indication of . {is predicted to not be available | how long it will be until RAIM is availabl jon OTH al either the FAF or MAP. cobalt * The GPS will not allow the This prediction can also be performed prior to unit t0 go into APR ACTV | departure to insure RAIM at your arrival mode until conditions improve. Table 2-3 GPS System Error Codes Definition Suggested Action KLNGHB) ‘System Error Codes reflec an | Most ofthe System Errors require the attention System Error error detected deep in the of a service center. Please note as many details Code XXX system. Some of the numeric {as possible when the failure occurred and Codes will be described below | identify if itis repeatable. oor Initialization Failure 003 Failed Powerup Self Test 006 Exception Interrupt Detected. | Cycle the power and see if the error is ‘The processor received an | repeatable. If repeatable take the unit toa lundesirable interrupt request | Service Center. 17 Run Time Database Checksum | The database cartridge needs replacement, Failed. An ertor was detected | Simply reloading a database into the cartridge Jon the database cartridge | will not fx the problem long-term, 02s [ADC reference failed. The reference voltage to the ‘Analog to Digital Converter is, not ata proper level 046 VCC Failed 047 Reference SV Failed 048 13V bus Failed 049 ~12V bus Failed 050 High Voltage bus Failed os Filtered power bus Failed 052 [OBS Signal Error oss OBS Overcurrent detected Page 2-72 IMKLNS9/BLT Rev 3 May/99AlliedSignal BENDIX/KING KLN 89/89B GPS RNAV SECTION Ill OPERATION 3.1 GENERAL INFORMATION For an explanation of the operating controls of the KLN 89/89B GPS RNAV refer to the KLN 89/89B pilots guide (P/N 006-08786-0000) or the aircraft's flight manual supplement. IMKLN89/BLT Page 3-1 Rev 3 May/99APPENDIX A RS-232 FORMAT DEFINITIONS1.0 GENERAL RS-232 IN The RS-232 interface will have the following characteristics: Byte format Electrical per EIA RS232C 9600 baud, 8 bits, 1 stop bit, no parity MARK is a logical 1 (one) and SPACE is a logical 0 (zero) START bit begins as MARK, goes to SPACE The receiving order of data bits within each data byte shall be: START bit Data bit 0 ('sb) Data bit 1 Data bit 2 Data bit 3 Data bit 4 Data bit § Data bit 6 Data bit 7 (msb) STOP bit Fuel/air data input protocol Fuel/air data sent by the Airdata computer shall be received in block having one of the following format: Fl BYTES ASCII STRIN Byte ——_Description\Format 1 STX (ASCII code 02H) 2 Unit of Measure G=.1 gallon imperial gallon liter K= 1 kilogram B= 1 pound 3-6 Fuel Remaining ASCII-coded decimal format, LSB first. Example: A fuel remaining value of 432 would be sent as "2340" (32H, 33H, 34H, 30H). IMKLN89/BLT Page A-1 Rev 3 May/99N 12 13 3-8 Page A-2 Description\Format Fue! Remaining Checksum Break each decimal value into its BCD representation. Using BCD arithmetic, sum the 4 BCD values and convert the lower-order BCD digit to an ASCII coded numeric digit Example: ‘The checksum for a value of 432 would be "9" (39H). Fuel Flow Rate (units/hours) ASCll-coded decimal format as for Fuel Remaining, Fuel Flow Rate Checksum ‘Sum of fuel flow rate bytes computed as for Fue! Remaining. ETX (ASCII code 03H) NOTE 1. Fuel remaining and fuel flow rate information shall be for the complete aircraft 2. This 13 byte record shall be transmitted every 1.6 sec = .16 sec. FORMAT B (52 BY I STRIN' Des mat STX (ASCII code 02H) Unit of Measure 1 gallon 1 imperial gation liter kilogram B =1 pound Total Fuel Remaining ASCII-coded decimal format (least significant digit is tenths), LSB first. Example’ A fuel remaining value of 543.2 would be sent as "2.3450" (32H, 2EH, 33H, 34H, ‘35H, 30H). IMKLN89/BLT Rev 3 May/99Deseription\Formal Total Fuel Remaining checksum Break each decimal value into its BCD representation. Using BCD arithmetic, sum the 4BCD values and convert the lower-order BCD digittoan ASCII coded numeric digit. Example: The checksum for a value of 543.2 would be "4" (34H). 10-15 Total Fuel Flow Rate ASCll-coded decimal format as for Total Fuel Remaining. 16 Total Fuel Flow Rate Checksum Sum of fuel flow bytes computed as for Total Fuel Remaining. 17-22 Engine One Fuel Flow Rate ASCIl-coded decimal format as for Total Fuel Remaining. 23 Engine One Fuel Flow Rate Checksum ‘Sum of Left Engine Fuel Flow Rate bytes computed as for Total Fuel Remaining. 24-29 Engine Two Fuel Flow Rate ASCil-coded decimal format as for Total Fuel Remaining, 30 Engine Two Fuel Flow Rate Checksum ‘Sum of Right Engine Fuel Flow Rate bytes computed as for Total Fuel Remaining. 31-36 Total Fuel Used ASCll-coded decimal format as for Total Fuel Remaining 37 Total Fuel Used Checksum ‘Sum of Total Fuel Used bytes computed as for Total Fuel Remaining. 38-43 Engine One Fuel Used ASCll-coded decimal format as for Total Fuel Remaining 44 Engine One Fuel Used Checksum ‘Sum of Left Engine Fuel Flow Rate bytes computed as for Total Fuel Remaining, 45-50 Engine Two Fuel Used ASCil-coded decimal format as for Total Fuel Remaining IMKLN89/BLT Page A3 Rev 3 May/99Byte 51 52 Byte 1-51 52-54 55 56-58 59 60-62 Page A-4 Description\Format Engine Two Fuel Used Checksum Sum of Left Engine Fuel Flow Rate bytes computed as for Total Fuel Remaining. ETX (ASCII code 03H) NOTE 1. In the case of single engine aircraft, all Engine One and Engine ‘Two data (including checksums) shall be asterisks (ASCII code 2A). 2. This 52 byte record shall be transmitted every 1.6 sec = .16 sec. FORMAT C (108 BYTES ASCII STRING) Description/Format ‘Same as Format B described above except that in the Units of Measured field, "I = Imperial Gallons” is undefined. Indicated Airspeed (IAS, knots) ASCli-coded decimal format (east significant digit is units), LSB first. Example: ‘An IAS of 298 knots would be sent as "892" (38H, 39H, 32H). Indicated Airspeed Checksum Break each decimal value into its BCD representation. Using BCD arithmetic, sum the 3BCD values and convert the lower-order BCD digit to an ASCII coded numeric digit. Example: The checksum for "892" would be "9” (39H). True Airspeed (TAS, knots) ASCll-coded decimal format as for IAS. True Airspeed Checksum ‘Sum for TAS bytes computed as for IAS. MACH (airspeed/speed of sound) ‘ASCIl-coded decimal format with an implicit leading decimal point (least significant digit is thousandths) Example: AMACH value of .492 would be sent as "294"(32H, 39H, 34H). IMKLN89/BLT Rev 3 May/9963 MACH checksum ‘Sum for MACH bytes computed as for IAS. 64-69 Pressure Altitude (PALT, feet) ASCll-coded decimal format with a sign character. Example: APALT of 34500 feet would be sent as "0543+" (30H, 30H, 35H,34H,33H, 2BH). 70 Pressure Altitude Checksum ‘Sum for PALT bytes, excluding the sign character. Example: ‘The sum for -850 feet would be "3" (33H), 71-76 Density Altitude (DALT, feet) ASCll-coded decimal format with a sign character, as for PALT. 7 Density Altitude Checksum ‘Sum for DALT bytes, excluding the sign character, as for PALT. 78-80 Total Air Temperature ( C) ASCIl-coded decimal format with a sign character. Example: ‘An OAT of 25° C would be sent as "52+", 81 Total Air Temperature Checksum ‘Sum for total air temperature bytes, excluding the sign byte, as for PALT. 82-84 Wind Direction (degrees from true North) ASCIl-coded decimal format. Example: 122° C would be sent as "221" (32H, 32H, 31H). 85 Wind Direction Checksum ‘Sum for wind direction bytes, as for IAS. 86-88 — Wind Speed (knots) ASCIl-coded decimal format, as for IAS. 89 Wind Speed Checksum ‘Sum for wind speed bytes, as for IAS. IMKLN89/BLT Page AS Description\Format Rev 3 May/99Byte 90-92 94-98 99 100-102 103 104-106 107 108 Page A-6 Description\Format Drift (degrees) ASCIl-coded decimal format with a direction character. Example: 7 right would be sent as "70R”, 14 left would be sent as "41L". Drift checksum ‘Sum for drift bytes, excluding the direction character. Example: ‘The sum for "41L" would be "5" (35H). Rate of change of PALT (feet/minute) ASCll-coded decimal format with a sign character. Example: APALT rate of change of -210 ft/min (descent), would be "0120-" (30H, 31H, 32H, 30H, 2DH). Rate of change of PALT Checksum ‘Sum for PALT rate of change bytes, excluding the sign character, as for PALT. Magnetic Heading (degree from magnetic North) ASCll-coded decimal format, as for wind direction. Magnetic Heading Checking ‘Sum for magnetic heading bytes, as for IAS. Static Air Temperature ( C) ASCIl-coded decimal format with a sign character. Example: Astatic air temperature of -2° C would be sent as "20-”. Static Air Temperature Checksum ‘Sum for static air temperature bytes, excluding the sign character, as PALT. TX (ASCII code 03H) NOTE 1. This 108 byte record shall be transmitted every 1.6 sec + .16 sec. IMKLN9/BLT Rev 3 May/99@ FORMAT D (121 BYTES ASCII STRII Byte Description/Format 1-107 Same as Format C described above except that bytes 3 through 9 shall be filled with asterisks if total fuel remaining is not available and consequently must be entered through the KLN 89. 108-112 Barometric setting (Inches HG) ASCII-coded decimal format (least significant digit is hundredth of inches), LSB first. Example: ‘An barometric setting of 29.83 inches hg would be sent as "38.92" (33H, 38H, 2EH, 39H, 32H) 113 Barometric setting Checksum Break each decimal value into its BCD representation. Using BCD arithmetic, sum the 4 BCD values and convert the lower-order BCD digit to an ASCII coded numeric digit. Example: The checksum for a value of 29.83 would be "2” (32H). 114-119 Baro-corrected altitude (feet) @ ASCII-coded decimal format with a sign character. Example: A baro-corrected altitude of +11000ft, would be "00011+" (30H, 30H, 30H, 31H, 31H, 28H); 120 Baro-corrected altitude Checksum ‘Sum for baro-corrected altitude bytes computed, excluding sign character, as for pressure altitude. 124 ETX (ASCII code 03H) FUEL FLOW & AIR DATA CONFIGURATION The Fuel flow and Air data equipment configuration can be setup on MNT 1 page. . 1, Fuel flow equipment installed and Air data equipment not installed Any of the above Formats may be received. If format Cor Dis received, the airdata portions are ignored, the fuel data portions are used, and no error message is given. IMKLN89/BLT Page A-7 Rev 3 May/992. Fuel flow equipment not installed and Air data equipment installed format C or D is received, fuel data portions are ignored, the airdata portions are used, and no error message is given. If format A or Bis received, the "GEN RS-232 In Data Error” message is displayed 3. Both Fuel flow equipment and Air data equipment not installed lf no data is received for this setup, the "No GEN RS-232 In Data” message will be displayed. Fuel/Air Data Timing Requirement Agrace periods of 2.4 sec, in addition to the 1.6 sec transmission interval, shall be given to every Fuelair data transmission. The unit invalidates all local copies if fueVair data is not received for 4.0 sec + .40 sec. 20 GENERAL RS232 OUT Functional Description Byte format Electrical per EIA RS232C 9600 baug, 8 bits, 1 start bit, 1 stop bit, no parity MARK is a logical 1 (one) and SPACE is a logical 0 (zero) START bit begins as MARK, goes to SPACE The order of transmission within each data byte shall be: START bit Data bit 0 (Isb) Data bit 1 Data bit 2 Data bit 3 Data bit 4 Data bit 5 Data bit 6 Data bit 7 (msb) STOP bit Page A-8 IMKLN89/BLT Rev 3 May/99Data Protocol Data shall be sent in blocks having the following format: -... _ ASCII start of text character item designator item data item terminator: ASCII carriage return character _—_ASCil end of text character _ ASCII start of text character item designator item data item terminator: ASCII carriage return character ASCII end of text character Any data which is invalid or exceeds the data format will be filled with dashes. RS 232 Output Data Item Definitions tem Data Format Data Field Description Designator ‘Width A s dd mmhh 9 present latitude; dash if position flag is set. ign: N for north, S for south dd=degrees mm=minutes hh=hundredths of minutes B ddd mmhh 10 present longitude; dash if position flag is set. ‘s=sign: E for east, W for west ddd=degrees mm=minutes hhshundredths of minutes c ddd 3 magnetic track, degrees; dash if GS is set. IMKLN89/BLT Page A-9 Rev 3 May/99_— Description a ftom Data Format Data Field Designator Width D ddd 3 E ddddd 5 G sdddd 5 1 (upper case INDIA) dddd 4 kK ddddd 5 L dddd 4 a sddd 4 7 9 Page A-10 groundspeed, knots; dash if position flag is set. 10 x distance to active waypoint, nm; dash if nav flag is set. crosstrack error; dash if nav flag is set. s=sign: R for aircraft position right of course, L for aircraft position left of course dddd=100 x crosstrack error, nm 10 x magnetic desired track, degrees (use selected course in OBS mode); dash if nav flag is set. active waypoint identifier 10xmagnetic bearing to active waypoint, degrees (use radial from active waypoint 180 in OBS mode); dash if position flag is set. magnetic v ; dash if position flag is ‘sel. s=sign: E for east, W for west ddd=10 magnetic variation, degrees warnings; 4th character is "A" itestimated Position error exceeds 3.8 nm, otherwise "-" IMKLN89/BLT Rev 3 May/99Item Data Format Designator Width Data Field Description (lower case LIMA) dddddd 6 u free format w dsiiilILLLLmm 17 IMKLN89/BLT Rev 3 May/99 10 x distance to destination, nm; dash if nav flag is set. for development testing only flight plan waypoint data; this item is sent for each waypoint in the active flight plan dd=waypoint number (01 ~ 25) ‘s=sequence number bits: 76543210 xlannnnn X=unused, Ist if last waypoint, a=1 if active wpt Annnn=sequential number, unsigned binary ili~identifier (ASCIt characters); a value of 7F hex in first byte indicates unknown ident, remaining bytes should be ignored, lli=waypoint latitude; packed, unsigned binary values: 76543210 76543210 76543210 sddddddd sommmmmm —xhhhhhhh sssign: 0 for north, 1 for south ddddddd=degrees xeunused mmmmmm=minutes hhhhhhh=hundredths of minutes Avalue of 7F hexin the first byte indicates ‘that latitude and longitude are unknown, and remaining bytes should be ignored. LLLL=waypoint longitude; packed, unsigned binary values: 76543210 76543210 76543210 76543210 Page A-11=— Hem Data Format Data Field Description Designator Width as son. dddddddd »xmmmmmm xhhhhhhh_ = sign: O=East 1=West, x-unused, legrees, m=minutes, h=hundredth jagnetic variation at waypoint mi 76543210 76543210 Annnnnan nnannnnn Annnnnnnnnnnnnnn=Magnetic variation at waypoint ‘Two's complement binary in sixteenths of degrees. Easterly variation is positive. Avvalue of 7FH in byte 14 indicates that ‘magnetic variation is not presently available and bytes 14 and 15 should be ignored. a Snnnnn 7 baro-corrected external altitude input S = sign: + or - Annnn = altitude, feet (to nearest foot); dash if not valid i hh:mm:ss. 8 UTC time of data hh=hours; mm=minutes; s t abcdefghij 10 GPS discretes a=W or waypoint alert; T for turn; else dashed beN for new message; P for persistent message; else dashed ‘¢-E for en route; T for terminal; for approach arm; of A for approach active 4d-L for LEG; D for Direct-to; 0 for OBS; T for OBS-LEG transition ‘e=T for TO; F for FROM; else dashed ghij=reserved for future use; currently dashed =seconds Page A-12 IMKLN89/BLT Rev 3 May/99SPECIAL HANDLING: 1. Active flight plan data in LEG mode ‘A maximum of 26 flight plan waypoints shall be transmitted. When the number of flight plan waypoints exceeds 25, 25 of the waypoints will be broadcast. Except for the special cases of fences and DME arcs, all the fight plan waypoints will be broadcast when the number of flight plan waypoints does not exceeds 25. When the number of fight plan waypoints exceeds 25, the first waypoints in the flight plan shall be omitted as necessary, unless a waypoint in the active leg would be omitted. In this case, the first waypoint in the active leg and the subsequent 24 waypoints shall be transmitted, eliminating waypoints from the end of the flight plan. No information shall be transmitted for waypoints beyond a fence in a flight plan when the active waypoint is before the fence. Likewise, when a DME arc is present in FPL 0, only the straight segments of FPL 0 adjacent to the active waypoint will be transmitted. This means waypoints prior to the active waypoint will only be transmitted from the previous DME arc end Point or beginning of FPL 0, which ever is later. Also, waypoints following the active waypoint will only be transmitted to the beginning of the next DME arc, the end of FPL 0 or the MAP fence, whichever is next. 2. Active flight plan data in DIRECT-TO mode or OBS-TO-LEG mode, (i) ifthe "direct-to” waypoint is in the active flight plan, the “direct-from” waypoint, the "direct-to" waypoint and those waypoints, if any, coming after the "direct-to” waypoint in the active flight plan should be transmitted, the sequence and waypoint numbers should start from "1" (ii) ifthe “direct-to” waypoint is not in the active flight plan, only the “direct-from” waypoint and the “direct-to” waypoint should be transmitted. The sequence and waypoint numbers, in this case, should start from "1". (i 8. Active flight plan data in OBS mode, (no fight plan data shall be transmitted. Identifier field of the "direct-from” waypoint shall always be blanked Performance All RS232 data shall be transmitted at least once every 2 sec. IMKLN89/BLT Page A-13 Rev 3 May/99APPENDIX B Includes the following: KLN 89/B SUPPLEMENTAL PROCEDURES MANUAL, KLN 89/B AIRPLANE FLIGHT MANUAL SUPPLEMENT KLN 89/B SUPPLEMENTAL TYPE CERTIFICATEFLIGHT MANUAL SUPPLEMENT PROCEDURE For the installation of the KLN 89B GPS to be FAA approved for enroute and approach IFR operation, itis necessary for the installer to create a flight manual supplement that is unique for the installation and to submit that supplement to the FAA for approval. Following, you will ind a copy of the flight manual supplement created by AlliedSignal Avionics Inc. for the initial STC installation of the KLN 89B in Mooney model M20C. Use this supplement as a guide in creating the supplement for your installation (do not copy the 006- part number in the footer). If your installation is interfaced to the same equipment (i.e. switches, annunciators, RMI, autopilot, etc.) as the initial installation, copy the guide supplement inits entirety, changing only the installers name and address, aircraft make and model, approval authorization and section titles/numbers to suit your circumstances as detailed below. More likely, if your installation is not identical to the initial installation, it will be necessary for you to determine the differences and alter your supplement accordingly. Elements of the supplement which may need to be altered for your installation are as follows: ‘ FORMAT The format of the finished supplement should match, as closely as possible, the format of the aircraft's flight manual and/or pilot's operating handbook. Sizing of your manual to match the aircraft's flight manual is most easily accomplished by creating it first as an 8 1/2" X 11" (standard typewriter size paper) document and then reducing that on a reducing copier to the size required before submitting it to the FAA for approval (Most small aircraft have fight manuals of 5 1/2" X8 1/2" size. This size has a different height/width ratio than the 8 1/2" X 11” size; the width is narrower. The guide supplement is proportioned correctly for reduction to 5 1/2" X 8 1/2" size; copy its proportions if you are planning to reduce your supplement) The headers and footers of the guide supplement may be rearranged to match the format of your aircraft's fight manual; however, most of the information shown is required on every page. The AlliedSignal part number, 006-00839-0000, should not appear in your supplement, but the footer should include the page number, in the format "PAGE _OF _”, and the words "FAA APPROVED” and a blank space for the date of the approval in place of the "ORIGINAL ISSUE” of the guide supplement. The aircraft for which the supplement applies should also be identified by ‘manufacturer and model number as shown on the aircraft's serial data plate, i.e. Beech A36 or Piper PA-46-310P (not marketing name like Bonanza, Malibu, etc.) Headers must identify the section of the supplement for that page. Additionally, we have found it useful to include identification of the system in the header for ease of pilot reference. The section numbers and names in the guide supplement are typical of many aircraft; however, you should check the aircraft's flight manual and match those section numbers and names when organizing your supplement. 2, COVER ‘The cover page for your supplement should essentially be identical to the guide supplement with the following exceptions: A. Inthe header, substitute the installers name and address (whoever is writing the flight manual supplement) in place of the name and address of AlliedSignal Avionics Inc.B. Substitute the manufacturer's name and model number (as shown on the serial data plate) for your aircraft in place of the Mooney models listed. C. Inthe second line of text, where the sample supplement states "is installed in accordance with STC SA0024aWI-D.”, substitute “is installed in accordance with unit Installation Manual 006-__-_, Rev.__, and FAA Form 337 dated.” (Insert the part number and revision of the manual you have used). D. Remove “CHRIS DURKIN, DAS Coordinator, AlliedSignal Avionics Inc.” and "DAS4CE” from below the FAA APPROVED line. (Your supplement will be approved by an FAA representative). E. Remove the footer on the cover page. (The footer on the guide supplement cover page is for AlliedSignal internal reference only) 3. TABLE OF CONTENTS Ifthe section names and numbers of your aircraft's flight manual do not match those of the sample flight manual supplement, you should arrange your Table of Contents and your supplement in accordance with the format of your aircraft's flight manual 4. BODY OF TEXT The body of text for all sections other than NORMAL PROCEDURES should be copiedin its entirety. The text forthe NORMAL PROCEDURES section may vary depending onthe eq} with the KLN 89B. Some of the annunciators, switches and/or controls described in paragraph B may differ slightly or may not be included as part of your installation. Should this be the case, you will need to alter the text of this paragraph and its subparagraphs to accurately describe the operation ofthe KLN 89B asiit existsin your installation, Do notinclude descriptions of annunciators, switches or controls not present in your installation. Make sure that the nomenclature on the items you do use matches the description in your flight manual supplement. This concludes the procedure for writing a KLN 89B GPS Aircraft Flight Manual Supplement. Reduce the pages as required tomatch the format of your aircraft's flight manual, and you are ready to submit the new document to your local FAA representative for approval.BENDIXIKING’ KLN 898 SUPPLEMENT ‘AiiedSignal Avionics ie Olathe, Kansas 66062 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT FoR MOONEY MODEL M20C with KLN 898 GPS NAVIGATION SYSTEM Reg. No. Ser. No “This supplement must be attached to the FAA Approved Airplane Flight Manual when the BendixKing KLN 898 GPS i installes in accordance with STC SAOQQ4WI-D. The information contained herein supplements or cupersedes the basic manual only in those areas isted herein. For imitaions, procedures, and performance information not contained in this supplement; consult he basic Airplane Fight Manual ran appnoven: CA! Doth CHRIS DUAKIN DAS Coordinator AlliedSignal Avionies Ine. DASACE oate:_2°23-96 FAA APPROVED: REVISION 1 (006-00839-0000BENDIXIKING’ KLN 698 SUPPLEMENT Loc oF Revisions HEV PAGER) DESCRIPTION TAPPROVEDIDATE Ta TRided turn anticipation warring To Section IV, paragraph A Chee Domb 8 Added turn antcaton warning to paragraph 48 Cris Durkin 9 Removed third GENERAL NOTE, "it | DAS Coordnator the destination apor isthe acive | AlledSignal Avonis Inc. seaypoit = Dasece ai | Repaginaied to include adional mater oate:_2-29-46 MOONEY MODEL Ma20c 006-00890-0000 FAR APPROVED: REVISION 1 PAGE!BENDIXIKING’ KLN 898 SUPPLEMENT TABLE OF CONTENTS ‘Section Description Page ' GENERAL, 1 " LIMITATIONS | 2 W EMERGENCY PROCEDURES 3 v NORMAL PROCEDURES. 3 v PERFORMANCE " MOONEY MODEL M20c (006-00839-0000 FAA APPROVED: REVISION 1 PAGEBENDIXIKING? KLN ‘SUPPLEMENT SECTION I- GENERAL The KLN 898 GPS panel mounted unit contains the GPS sensor, the navigation computer, a CRT display, and all controls required to operate the uni, It also houses the data base card which plugs directly into the front ofthe unt ‘The data base card is an electronic memory containing information on airports, navaids, intersections, SiD's, STAR’s, intument approaches, special use airspace, and other items of value tothe plat. Every 28 days, BendiKing receives new data base information from Jeppesen ‘Sanderson for the North American data base region. This information is processed and downloaded onto the data base cards. BendiwKing makes these dala base card Updates available to KLN 696 GPS users, Provided the KLN 89B GPS navigation system is receiving adequate usable signals, i has been demonstrated capable of and has been shown to meet the accuracy specifications of VERIFR en route oceanic and remote, en route domestic, terminal and instument approach (GPS, Loran-C, "VOR, VOR-DME, TACAN, NDB, NDB-DME. RNAV) ‘operation win the U.S. National Airspace Sysiem, Nom Atanic Minimum Navigation Periormance Speciications (MNPS) Airspace and iattudes bounded by 74 North and 60” South using the WGS-84 (or NAD 83) coordinate reference datum in accordance withthe ertaria of AG 20-138, AC 91-49, and AC 120-33. Navigation data is based Upon use of only the global positioning system (GPS) operated by the United States. NOTE ‘Aircraft using GPS for oceanic IFR ‘operations may use the KLN 898 to replace one of the other approved ‘means. of long-range navigation. A Single KLN 898 GPS instalation may ‘also be used on short oceanic routes ‘which require only one means of long range navigation, Note FAA approval of the KLN 898 does ‘ot necessarly constitute approval for sein foreign airspace. MOONEY MODEL mz0c ‘006-00839-0000, FAA APPROVED: REVISION 1 PAGE 1 OF 11BENDIXIKING’ KLN 898 SUPPLEMENT SECTION 11- LIMITATIONS. ‘A. The KLN 898 GPS Pilot's Guide, P/N 006-08786-0000, dated May, 1995 (or later applicable revision) must be immediately avaiable to the fight crew ‘whenever navigation is predicated on the use of the system. The Operational Revision Status (ORS) of the Pils Guide must match te ORS level nnunciated on the Sell Test page. 8. _IFR Navigation is restricted as follows: 1 The system must utlize ORS level 0 or later FAA approved revision, 2. The data on the self test page must be verfied prior to use. 3. IFR en route and terminal navigation is prohitited unless the pilot verlies the currency of the data base or veriies each selected waypoint for accuracy by reference to current approved data, 4 Instrument approaches must be accomplished in accordance with approved instrument approach procedures that are ravievod from the KUN 898 data base. The KLN B98 data base must incorporate the current update cycle, (a) The KLN 698 Quick Relerence, P/N 006-08787-0000, dated 5/95 (or later applicable revision) must be mmedately avaiable to the fight crew during instrument approach ‘operations. (©) Instrument approaches must be conducted in the approach ‘made and RAIM must be available a the Final Approach Fix. (©) APRLACTV mode must be annunciated at the Final Approach Fix (6) Accomplishment of ILS, LOC, LOC-BC, LDA, SOF, and MLS approaches are not authorized (2) When an alternate airport is required by the applicable ‘Operating rules, must be served by an approach based on ‘other than GPS of Loran-C navigation, (The KLN 898 can only be used for approach guidance the relerence coordinate’ datum system for the instrument approach is WGS-84 or NAD-83._ (All approaches in the KUN 898 data base use the WGS-84 or the NAD-B3 geodetic alums.) 5. The aieraft_must have other approved navigation equipment appropriate tothe route o fight installed and operational ‘006-00830-0000 MOONEY MODEL M20c PAGE 20F 11 FAR APPROVED: REVISION 1BENDIXIKING’ KLN 898 SUPPLEMENT ‘SECTION Ill EMERGENCY PROCEDURES ABNORMAL PROCEDURES ‘A. tt the KLN 898 GPS information is not available or invalid, uiize remaining ‘operational navigation equipment as required B. —It_a “RAIM NOT AVAILABLE” message is displayed while conducting an instrument approach, terminate the approach. Execute a missed approach if required ©. Ita "RAIM NOT AVAILABLE” message is displayed in the en route or terminal ‘phase of fight, continue to navigate using the KLN 898 or revert to an alternate ‘means of navigation appropnate to the route and phase of flight When Continuing to use GPS navigaton, postion must be veriied every 15 minutes using another IFF approved navigation system. D. Refer to he KLN 898 Pilot's Guide, Appendices B and C, for appropriate plot actions to be accomplished in response fo annuncated messages. SECTION IV - NORMAL PROCEDURES Familiarity with the en route ‘operation of the KLN 898 does not ‘constitute proficiency in approach operations. Do not attempt ‘approach operations in IMC prior to attaining proficiency in the use of the KLN 898. A. OPERATION Normal operating procedures are outined in the KLN 896 GPS Pilots Guide, PIN 006-08786.0000, dated May 1995, (or later appicable revision). A KLN 898, Quick Reference, PIN 096-08787-0000 dated 5/89 (0 later applicable revision) containing an approach sequence, operating ‘ips and approach elated messages iS intended for cockpit use by the KLN 696 familiar pilot when Conducting instrument approaches, MOONEY MODEL M20c 06-00839-0000 FAA APPROVED: REVISION 1 PAGE 3 OF 11