Honeywell GPS RNAV, KLN 90B User Manual

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INSTALLATION MANUAL

KLN 90B

GPS RNAV

MANUAL NUMBER 006-10521-0005

REVISION 5 April, 2003

WARNING

Prior to Export of this Document, review for export license requirement is needed.

Reproduction of this publication or any portion thereof by any means without the express written permission of Honeywell is prohibited. For further information contact the Manager, Technical Publications, Honeywell, One Technology Center, 23500 West 105th Street Olathe KS 66061 Telephone: (913) 782-0400.

BENDIX/KING KLN 90B

SECTION I

GENERAL INFORMATION

Paragraph Page

1.1 INTRODUCTION...........................................................................................1-1

1.2 EQUIPMENT DESCRIPTION ......................................................................1-1

1.3 TECHNICAL CHARACTERISTICS ..............................................................1-1

1.3.1 ARINC 429 GAMA FORMAT INFORMATION .............................................1-1

1.3.3 UNIT TECHNICAL CHARACTERISTICS .....................................................1-5

1.4 UNITS AND ACCESSORIES SUPPLIED ....................................................1-10

1.4.1 KLN 90B GPS RECEIVER ...........................................................................1-10

1.4.2 GPS ANTENNA ............................................................................................1-11

1.4.3 KLN 90/90B INSTALLATION KITS ..............................................................1-11

1.4.4 KA 91/92 INSTALLATION KIT .....................................................................1-12

1.4.5 DATABASE ..................................................................................................1-12

1.5 ACCESSORIES REQUIRED, BUT NOT SUPPLIED ...................................1-13

1.6 OPTIONAL ACCESSORIES ........................................................................1-13

1.7 LICENSE REQUIREMENTS ........................................................................1-19

1.8 RECOMMENDATIONS FOR IFR APPROVAL ............................................1-19

1.9 INSTRUCTIONS FOR CONTINUED AIR WORTHINESS............................1-21

Rev 5, April/2003 10521I05.TDC Page i

BENDIX/KING KLN 90B

SECTION II

INSTALLATION

ParagraphPage

2.1 GENERAL INFORMATION .......................................................................... 2-1

2.2 UNPACKING AND INSPECTING EQUIPMENT .......................................... 2-1

2.3 EQUIPMENT INSTALLATION...................................................................... 2-1

2.3.1 AVIONICS COOLING REQUIREMENTS

FOR PANEL MOUNTED EQUIPMENT........................................................ 2-1

2.3.2 KLN 90B MECHANICAL INSTALLATION .................................................... 2-1

2.3.3 ANTENNA SELECTION ............................................................................... 2-2

2.3.4 ANTENNA INSTALLATION CONSIDERATIONS......................................... 2-2

2.3.5 ANTENNA MECHANICAL INSTALLATION ................................................. 2-3

2.3.5.1 General......................................................................................................... 2-3

2.3.5.2 Installation Procedure................................................................................... 2-3

2.3.6 ELECTRICAL INSTALLATION..................................................................... 2-3

2.3.6.1 General Information...................................................................................... 2-3

2.3.6.2 Functional Pinout Descriptions ..................................................................... 2-4

2.4 POST INSTALLATION CHECK OUT INFORMATION................................. 2-65

2.4.1 KLN 90B RESOLVER CALIBRATION METHOD ......................................... 2-65

2.4.2 POST INSTALLATION CHECKOUT PROCEDURE .................................... 2-65

2.4.3 INSTALLATION CHECK OUT...................................................................... 2-66

2.4.4 INTEGRATED INSTALLATION CHECK OUT.............................................. 2-67

2.4.4.1 All Installations.............................................................................................. 2-67

2.4.4.2 EFIS or CDI/HSI Interface ............................................................................ 2-67

2.4.4.3 Radar Graphics Interface.............................................................................. 2-68

2.4.4.4 Air Data Interface.......................................................................................... 2-68

2.4.4.5 Gray Code Altitude Inputs............................................................................. 2-68

2.4.4.6 RMI Interface ................................................................................................ 2-68

2.4.4.7 ELT Interface ................................................................................................ 2-68

2.4.4.8 Moving Map Interface ................................................................................... 2-68

2.4.4.9 External Annunciators................................................................................... 2-69

2.4.4.10 Distance Indicator......................................................................................... 2-69

2.4.4.11 Dataloader .................................................................................................... 2-69

2.4.4.12 ALT ALERT

2.4.4.13 Heading Interface ......................................................................................... 2-69

2.4.4.14 Roll Steering Interface .................................................................................. 2-70

Page ii 10521I05.TDC Rev 5, April/2003

, ALT ALERT AUDIO ................................................................ 2-69

BENDIX/KING KLN 90B

SECTION III

OPERATION

Paragraph Page

3.1 GENERAL INFORMATION ......................................................................... 3-1

LIST OF ILLUSTRATIONS

Figure Page

2-1 KLN 90B CONNECTOR PIN FUNCTIONS .................................................. 2-9

2-2 KLN 90B CRIMPING AND INSERTION/EXTRACTION TOOLS.................. 2-11

2-3 KLN 90/A/B INSTALLATION DRAWING...................................................... 2-13

2-4 KA 91 OUTLINE DRAWING......................................................................... 2-15

2-5 KA 91 INSTALLATION DRAWING............................................................... 2-17

2-6 KA 91 BACKPLATE DRAWING ................................................................... 2-19

2-7 KA 92 OUTLINE DRAWING......................................................................... 2-21

2-8 KA 92 INSTALLATION DRAWING............................................................... 2-23

2-9 KA 92 BACKPLATE DRAWING ................................................................... 2-25

2-10 KA 91/92 TNC ANTENNA COAX/CONNECTOR ASSEMBLY

(RG142B/U OR RG400 0 to 40 ft.) .................................................................... 2-27

2-11 KA 91/92 BMA ANTENNA COAX/CONNECTOR ASSEMBLY

(RG142 B/U OR RG400 0 to 40 ft.) ................................................................... 2-29

2-12 KA 91/92 TNC/BMA ANTENNA COAX/CONNECTOR ASSEMBLY

(0 to 80 ft./0 to 100 ft.)...................................................................................... 2-31

2-13 KA 33 P/N 071-4037-00/01 FINAL ASSEMBLY........................................... 2-33

2-14 KA 33 P/N 071-4037-00/01 INSTALLATION DRAWING.............................. 2-35

2-15 CUTLER-HAMMER SWITCH/ANNUNCIATOR UNIT

INSTALLATION DRAWING.......................................................................... 2-37

2-16 CUTLER-HAMMER SWITCH/ANNUNCIATOR UNIT

INTERNAL SCHEMATIC.............................................................................. 2-39

2-17 KLN 90B INTERCONNECTION DRAWING (Page 1 of 10) ......................... 2-43

2-17 KLN 90B INTERCONNECTION DRAWING (Page 2 of 10) ......................... 2-45

2-17 KLN 90B INTERCONNECTION DRAWING (Page 3 of 10) ......................... 2-47

2-17 KLN 90B INTERCONNECTION DRAWING (Page 4 of 10) ......................... 2-49

2-17 KLN 90B INTERCONNECTION DRAWING (Page 5 of 10) ......................... 2-51

2-17 KLN 90B INTERCONNECTION DRAWING (Page 6 of 10) ......................... 2-53

2-17 KLN 90B INTERCONNECTION DRAWING (Page 7 of 10) ......................... 2-55

2-17 KLN 90B INTERCONNECTION DRAWING (Page 8 of 10) ......................... 2-57

2-17 KLN 90B INTERCONNECTION DRAWING (Page 9 of 10) ......................... 2-59

2-17 KLN 90B INTERCONNECTION DRAWING (Page 10 of 10) ....................... 2-61

2-18 KLN 90B DATALOADER/PC INTERFACE DRAWING ................................ 2-63

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BENDIX/KING KLN 90B

APPENDIX A

RS-232 FORMAT DEFINITIONS

APPENDIX B

KLN 90B SUPPLEMENTAL PROCEDURES MANUAL

KLN 90B AIRPLANE FLIGHT MANUAL SUPPLEMENT

KLN 90B SUPPLEMENTAL TYPE CERTIFICATE

APPENDIX C

GPS FAULT/ERROR CODES DATABASE LOADER MESSAGES

TSO APPENDIX

ENVIRONMENTAL QUALIFICATION FORMS

Page iv 10521I05.TDC Rev 5, April/2003

BENDIX/KING KLN 90B

SECTION I

GENERAL INFORMATION

1.1 INTRODUCTION

This manual contains information relative to the physical, mechanical, and electrical characteristics of the BENDIX/KING KLN 90B Global Positioning System (GPS) Receiver. General installation procedures are also included.

1.2 EQUIPMENT DESCRIPTION

The KLN 90B is a panel mounted, long range, GPS based airborne navigation system with a data base. 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 display consists of a right and left page and a status line at the bottom of the display. The information on the left page is controlled by the concentric knobs on the left side of the unit and the information on the right page is controlled by the concentric knobs on the right side of the unit. Present position information will be displayed on the unit CRT or can also be displayed on an EFIS or Radar Graphics unit.

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 90B contains information concerning airports, VORs, NDBs, intersections, 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 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 cartridge which plugs into the back of the KLN 90B. It is designed so that the user may easily remove the old database cartridge and install a current database cartridge. 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 90B refer to the KLN 90B Pilots Guide P/N 006-08773-0000.

1.3 TECHNICAL CHARACTERISTICS

1.3.1 ARINC 429 GAMA FORMAT INFORMATION

ARINC 429 is a serial bus interface that provides information to and from the KLN 90B to external equipment. The serial bus conforms to ARINC 429 specifications for electrical characteristics, receiving, and transmission interval. The format of the labels are GAMA 429 format.

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BENDIX/KING KLN 90B

The following labels are received on the EFIS 429 receiver inputs (Pins 4 and 5 of P901):

TABLE 3-1 EFIS 429 Receiver Inputs

LABEL(OCTAL) DESCRIPTION

100 SELECTED COURSE

306 NAV/WPT/APT LATITUDE

307 NAV/WPT/APT LONGITUDE

314 OR 320

The following labels are received on the Radar Graphics 429 receiver inputs (Pins 6 and 7 of P901):

TABLE 3-2 Radar Graphics 429 Receiver Inputs

LABEL(OCTAL) DESCRIPTION

306 NAV/WPT/APT LATITUDE

307 NAV/WPT/APT LONGITUDE

The following labels are received by the KLN 90B on the Air Data 429 receiver inputs (Pins 8 and 9 of P901):

TABLE 3-3 Air Data 429 Receiver Inputs

TRUE HEADING

MAGNETIC HEADING

LABEL(OCTAL) DESCRIPTION

203 ALTITUDE (1013.25 MB)

204 BARO CORRECTED ALTITUDE

205 MACH

210 TRUE AIRSPEED

211 TOTAL AIR TEMPERATURE

213 STATIC AIR TEMPERATURE

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BENDIX/KING KLN 90B

The following labels are transmitted by the KLN 90B on the ARINC 429 transmitter output (Pins 23 and 24 of P901):

TABLE 3-4 Arinc 429 Gama Transmitter Output)

LABEL(OCTAL) DESCRIPTION

001 DISTANCE TO GO (BCD)

002 TIME TO GO (BCD)

012 GROUND SPEED (BCD)

074 DATA RECORD HEADER

075 ACTIVE WAYPOINT FROM/TO DATA

100 SELECTED COURSE #1

113 MESSAGE CHECKSUM

114 DESIRED TRACK (TRUE)

115 WAYPOINT BEARING (TRUE)

116 CROSS TRACK DISTANCE

121 HORIZONTAL COMMAND

147 MAGNETIC VARIATION

150 GREENWICH MEAN TIME

251 DISTANCE TO GO

252 TIME TO GO

261 GPS DISCRETE WORD

275 LONG RANGE NAV STATUS

300 STATION MAGNETIC VARIATION,

TYPE, AND CLASS

303 MESSAGE LENGTH/TYPE/NUMBER

304 MESSAGE CHARACTERS 1-3

305 MESSAGE CHARACTERS 4-6

306 NAV/WPT/APT LATITUDE

307 NAV/WPT/APT LONGITUDE

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BENDIX/KING KLN 90B

310 PRESENT POSITION LATITUDE

311 PRESENT POSITION LONGITUDE

312 GROUND SPEED

313 TRACK ANGLE (TRUE)

314 TRUE HEADING

315 WIND SPEED

316 WIND ANGLE (TRUE)

321 DRIFT ANGLE

326 LATERAL DEVIATION SCALE FACTOR

351 DISTANCE TO DESTINATION (VIA

FLIGHT PLAN)

352 TIME TO DESTINATION (VIA FLIGHT

PLAN)

371 SPECIFIC EQUIPMENT IDENT

377 EQUIPMENT HEX ID CODE

For RS 232 I/O formats, refer to Appendix A.

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BENDIX/KING KLN 90B

1.3.3 UNIT TECHNICAL CHARACTERISTICS

Table 3-6 KLN 90b

TSO Compliance SEE TSO APPENDIX

Physical Dimensions:

Width: 6.312 in. (16.03 cm.)

Height: 2.00 in. (5.08 cm.)

Length: 12.55 in. (31.87 cm.)

Weight: 6.30 lbs. (2.86 Kg.)

Mounting: Panel mounted with Honeywell 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° C to +70° C

Altitude Range: Up to 50,000 FT

Power Inputs: 11 to 33 VDC at 2.5 A MAX (-40°C to

+70°C)

Panel Lighting Current Requirements:

28 VDC Lighting: 286 mA max

14 VDC Lighting: 572 mA max

5 VDC Lighting: 1.0 A max

5 VAC Lighting 1.0 A max (400 Hz rms)

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BENDIX/KING KLN 90B

Table 3-7 KLN 90B Signal Inputs

GPS DISPLAYED: OPEN = GPS displayed (when an indicator resolver is

connected to the OBS resolver inputs) GND = GPS not displayed (when an indicator resolver is not connected)

TAKE HOME: OPEN = Normal Operation

GND = Take Home Mode

SDI 1/2: OPEN = Primary Long-range Navigation System

GND = Secondary Long-range Navigation System

EFIS 429 RCVR inputs: See Section 1.3.1

RDRG (Radar Graphics) 429 inputs:

AIR DATA 429 Inputs: See Section 1.3.1

ARM SELECT: This pin is used as a mode programming pin on power-up

LEG/OBS CONTROL: This pin is used as a mode programming pin on power-up

DATA LOADER IN: The Data Loader RS 232 input is designed to communi-

RS 232 IN: The RS 232 input is designed to communicate with devic-

ALT ALERT: ENABLED = Open (or tied to A/C Power thru a passive

See Section 1.3.1

and later as a select input.

and later as a control input.

cate with the dataloader

es, i.e. air data and fuel flow sensors via RS 232 format (refer to Appendix A)

load) DISABLED = GND (This pin also functions as an output, refer to section 2.3.6.2.X. for details)

Table 3-8 KLN 90B Gray Code Inputs

(A1,A2,A4,B1,B2,B 4,C1,C2,C4,D4)

OBS RES SIN: OBS resolver sine, nominal input impedance = 36.5 K ohms (ac)

OBS RES COS: OBS resolver cosine, nominal input impedance = 36.5 K ohms

Page 1-6 10521I05.TDC Rev 5, April/2003

Gray Code Altitude Signals (0 V. to 28 V.) These inputs are diode isolated inside the KLN 90B on all units above S/N 1542

and 100 K ohms (dc)

(ac) and 100 K ohms (dc)

BENDIX/KING KLN 90B

Table 3-9 KLN 90B Signal Outputs

OBI SYNC, CLOCK, & DATA:

RS 232 OUT: The RS232 output is designed to interface with certain ARNAV ELTs

WPT ALERT: (Waypoint Alert)

MSG: (Message)

APPROACH ACTIVE:

APPROACH ARM:

CDI Output: Output is capable of driving up to five 1 KW parallel loads, Output

Honeywell Serial Data containing bearing to the active waypoint

and certain moving map displays, storm scopes, and Shadin fuel flow systems (refer to Appendix A)

OPEN = Inactive LOW = Active (Output can sink up to 250 mA

OPEN = Inactive LOW = Active (Output can sink up to 250 mA)

OPEN = Inactive LOW = Active (Output can sink up to 250 mA

drive range: $300 mV ($ 150 mV full scale) 30 mV per nautical mile (Full scale = 5 nautical mile) 150 mV per nautical mile (Full scale = 1 nautical mile) 500 mV per nautical mile (Full scale = .3 nautical mile)(Voltage at pin 22 is relative to voltage at pin 25) The CDI output can manually be selected to the sensitivity of one of the three sensitive modes listed below.

Enroute: 5, 1 or .3 nautical mile scale factor selectable

Approach Arm: 1 or .3 nautical mile scale factor selectable

Approach: .3 nautical mile scale factor only

Table 3-10 KLN 90B NAV Flag Output

Flag Pulled out of view:

Flag in view: < 50mVOutput capable of driving up to five 1 KW parallel loads

Nav Super Flag Output:

OBS Resolver Out:

350 to 900 mV

Valid = >18 V in 28 VDC aircraft installations; >10 V in 14 VDC aircraft installations Invalid = <3.5 V in all installations while sinking 1 mA max. Output can source up to 250mA

Nominal output frequency = 450 Hz Nominal unloaded peak amplitude = 6 V Output drive capability = 40mA

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BENDIX/KING KLN 90B

Table 3-11 KLN 90B To/From Flag Output

To Indication: +40 to +160 mV on Pin 21 with respect to Pin 20

From Indication: -40 to -160 mV on Pin 21 with respect to Pin 20

Output capable of driving up to five 200 W parallel loads

Arinc 429 Xmitter:

DATA LOADER OUT:

ALT ALERT: HIGH = Inactive

ALT ALERT AUDIO:

TSO Compliance: SEE TSO APPENDIX

Physical Dimensions:

See Section 1.3.1

The Data Loader RS 232 output is designed to communicate with an IBM compatible personal computer

LOW = Active (can sink up to 250 mA). This pin also functions as an input, refer to section 2.3.6.2.X. for details)

This output is active whenever ALT ALERT is active, Signal is 1 KHz., 3.5 V rms max into 500 W

KA 91 ANTENNA

Table 3-12 KA 91

Width: 2.90 in. (7.37 cm.)

Height: 0.75 in. (1.91 cm.)

Length: 4.70 in. (11.94 cm.)

Weight: 0.5 lbs. (0.227 Kg.)

Airspeed Rating: 600 Kts. TAS

Output Impedance: 50 Ohms (nominal)

DC Voltage: 5 Volts $0.5 Volt

DC Current: 50 mA maximum

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BENDIX/KING KLN 90B

Table 3-13 KA 92

KA 92 ANTENNA

TSO Compliance: SEE TSO APPENDIX

Physical Dimensions:

Width: 2.70 in. (6.86 cm.)

Height: 0.70 in. (1.78 cm.)

Length: 4.30 in. (10.92 cm.)

Weight: 0.27 lbs. (0.12 Kg.)

Airspeed Rating: 600 Kts. TAS

Output Impedance: 50 Ohms (nominal)

DC Voltage: 5 Volts $0.5 Volt

DC Current: 50 mA maximum

Table 3-14 KA 198 Comm Filter

P/N 071-01565-0000

Center Notch Frequency: 1575.42 MHz.

Attenuation at 1575.42 ;1.5 MHz: 35 dB min.

Insertion loss from 118.00 to137.00 MHz: .3dB Max.

Impedance from 118.00 to137.00 MHz: 50 ohms

VSWR from 118.00 to 137.00 MHz: 1.5:1

NOTE

The conditions and tests performed on this article

are minimum performance standards. It is the re-

sponsibility 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 ap-

proved by the Administrator.

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BENDIX/KING KLN 90B

1.4 UNITS AND ACCESSORIES SUPPLIED

1.4.1 KLN 90B GPS RECEIVER

The KLN 90B is available in the following versions. New manufactured KLN 90B units are P/N 066-04031-1X21/1X22/1X24 and KLN 90/A units that have been converted to KLN 90B are P/N 066-04031-2X21/2X22/2X24.

Table 3-15 KLN 90B Versions

PART NUMBER 14/

28V

LAMP

066-04031-1121 X - - X - - - -

066-04031-1221 - X - X - - - -

066-04031-1321 X - - - X - - -

066-04031-1421 - X - - X - - -

066-04031-1521 X - X X - - - -

066-04031-1621 - X X X - - - -

066-04031-2121 X - - X - - X -

066-04031-2221 - X - X - - X -

066-04031-2321 X - - - X - X -

066-04031-2421 - X - - X - X -

066-04031-1122 X - - X - X - -

066-04031-1222 - X - X - X - -

LAMP

NIGHT VISION

GOGGLE

BLACK BEZEL

GREY

BEZEL

BRNAV

CAPABLE

(1)

UPGRADED

KLN 90B’s

ARINC

734A

CAPABLE

(2)

066-04031-1322 X - - - X X - -

066-04031-1422 - X - - X X - -

066-04031-1522 X - X X - X - -

066-04031-1622 - X X X - X - -

066-04031-2122 X - - X - X X -

066-04031-2222 - X - X - X X -

066-04031-2322 X - - - X X X -

066-04031-2422 - X - - X X X -

(1) BRNAV Capable - Is capable of meeting the JAA AMJ 20X2 requirements.

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BENDIX/KING KLN 90B

1.4.2 GPS ANTENNA

The KA 91 antenna is available by ordering P/N 071-01545-0200. The KA 92 antenna is available by ordering P/N 071-01553-0200.

1.4.3 KLN 90/90B INSTALLATION KITS

The KLN 90/90B Installation Kit (P/N 050-03096-0000) 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.

Table 3-16 KLN 90B Installation Kits

P/N DESCRIPTION UM 0000 VENDOR NAME

P/N

050-03096-0000 KLN90 INSTALL-CRIMP X

030-00101-0002 PANEL MOUNT PLUG (J902) EA 1 TED Mfg. 9-30-10

030-01157-0011 SOCKET CRMP 20G EA 50 Positronics

FC6020D-14

030-01176-0000 CONN SUB-D HSG 50S (J901) EA 1 Positronics

RD50F00000-

782.0

030-01428-0006 HOOD W/SPCL LCK 50P EA 1 Positronics

D50000 GVLD

033-00230-0000 DATA LOADER JACK EA 1

057-05621-0000 DECAL DATA LOADER EA 1

057-05628-0000 GPS DISCLAIMER EA 1

071-01541-0000 MOUNTING RACK ASSY RF X

071-06121-0000 ALLEN WRENCH .094 EA 2

089-02353-0001 NUT CLIP 6-32 EA 4

089-06012-0008 SCR FHP 6-32X1/2 EA 4

089-08252-0030 WASHER EA 1

090-00019-0007 RING RTNR .438 EA 1

187-01722-0000 GASKET EA 1

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BENDIX/KING KLN 90B

1.4.4 KA 91/92 INSTALLATION KIT The KA 91 Installation Kit (P/N 050-03195-0000), including its contents, is shown below.

Table 3-17 KA 91 Installation Kits

P/N DESCRIPTION UM -

0000

050-03195-0000 KA91 INSTALL X

030-00134-0001 RIGHT ANGLE CONN

COAX

047-10130-0002 BACKPLATE, ANTENNA EA 1

089-06908-0012 SCREW, AIRCRAFT EA 4

187-01807-0000 KA 91 GASKET EA 1

Earlier installation kits included a straight TNC coax connector, P/N 030-00134-0000. The KA 92 Installation Kit (P/N 050-03318-0000), including its contents, is shown below.

Table 3-18 KA 92 Installation Kits

P/N DESCRIPTION UM -0000 VENDOR NAME & P/

EA 1 TED MFG 5-30-102

VENDOR NAME & P/N

050-03318-0000 KA92 INSTALL X

030-00134-0001 RIGHT ANGLE CONN

COAX

047-10735-0002 BACKPLATE, ANTENNA EA 1

089-05909-0012 SCREW, PHP 8-32x3/4 EA 4

187-01831-0000 KA 92 GASKET EA 1

1.4.5 DATABASE

The KLN 90/90B database cartridge is available for three separate geographic areas.

North American Database 071-01523-0302 Atlantic International Database 071-01523-0304 Pacific International Database 071-01523-0305

EA 1 TED MFG 5-30-102

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BENDIX/KING KLN 90B

1.5 ACCESSORIES REQUIRED, BUT NOT SUPPLIED

A. Forced Air Cooling

A KA 33 Cooling Kit or equivalent is required for the KLN 90B installation.

1. KA 33 Blower for 14 VDC installations is available under P/N 071-4037-00.

2. KA 33 Blower for 28 VDC installations is 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, is required for IFR. Listed below are common Honeywell models that are available.

1. KI 202 (P/N 066-3034-XX) Navigation Indicator and installation kit (P/N 050-01524-0000).

2. KI 206 (P/N 066-3034-XX) Navigation Indicator and installation kit (P/N 050-01524-0000).

3. KPI 553A (P/N 066-3045-XX) Horizontal Situation Indicator and installation kit (P/N 050-01791-XXXX).

NOTE

The DME distance display is not compatible with the

KLN 90B. KPI 553A used with the KNR 665 Digital

Gold Crown is not compatible.

4. KPI 553B (P/N 066-3069-XX) Horizontal Situation Indicator and installation kit (P/N 050-02167-XXXX).

5. KI 525A (P/N 066-3046-XX) Horizontal Situation Indicator and installation kit (P/N 050-01344-XXXX). Refer to section 2.4.1, KLN 90B OBS Resolver Calibration Procedure for 30 Hz indicator calibration.

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.

1.6 OPTIONAL ACCESSORIES

A. KA 90 Interface Adapter

Order P/N 071-01508-0101 or 071-01508-0202 for a KA 90 Interface Adapter. The KA 90 interfaces the KLN 90B with various other avionics in an aircraft. It converts GAMA 429 output to analog in order to drive mechanical HSI/CDI devices. It also converts analog heading and HSI/CDI outputs into 429 data.

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BENDIX/KING KLN 90B

Functions of the -0101 include converting 3-wire heading sources to ARINC 429, converting the resolver output of a non-driven HSI to ARINC 429 so that the KLN 90B can read the selected course from the HSI, converting binary ARINC 429 data to BCD ARINC 429, and converting low speed ARINC 429 to high speed ARINC 429. Functions of the 0201/ 0202 include all of the functions of the -0101 plus converting ARINC 429 bearing outputs from the KLN 90B to 3-wire XYZ RMI and 4-wire sin/cos OBI formats, converting ARINC 429 distance information to ARINC 561/568 6-wire format, providing interface with Collins EHSI 74 and EFIS 85/85A/86A/86B/86C, and converting ARINC 429 roll steering data to an analog format.

B. PC Interface Kit

To load the database from a personal computer via diskettes, order interface kit P/N 05003213-0000. 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 database may be loaded directly from the PC to the KLN 90B installed in an aircraft, or the PC may be used to update the KLN 90B while it is installed in a KCC 90 (refer to

section 2.4.4.11 and Figure 2-18 for details) or Commander 2000K from Lone Star Avion-

ics phone (817)548-7768.

Laptop computers used to load the data base require the following:

1. IBM compatibility

2. An available Com 1 or Com 2 serial port

3. A 3.5" high density diskette drive

NOTE

Not all laptops conform to the above requirements. If

there is uncertainty relating to this, contact Honeywell

Product Services by telephoning (913) 782-0600.

C. Annunciators and Switch/Annunciators

(Refer to I.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, such as the Mid-Continent Instrument, MD41.

These switch/annunciators are available through Honeywell Service Stock or direct from our supplier, LCOMP Aerospace Controls. It is advantageous to order direct from LCOMP, if possible, in order to avoid additional price mark-ups. LCOMP’s address and telephone number are listed as follows:

LCOMP Aerospace Controls c/o Carlton-Bates Co. (800) 786-0617 9214 Bond St. (913) 438-4848 Overland Park, KS 664214 (913) 438-4839 Fax

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BENDIX/KING KLN 90B

NOTE

The part numbers shown in parenthesis are annun-

ciators previously called out and may be used until

supply is depleted.

Replacement bulbs for 031-00785-xxxx 5V 037-00009-0007 14V 037-00009-0008 28V 037-00009-0006

KLN 90B 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 90B IFR enroute/terminal installations. They are optional for KLN 90B/KLX 135 VFR installations.

KLN 90/B or KLX 135 Ann. Set (28 V. ltg.)

NAV/GPS Sw. Ann. 031-00785-0711 or (031-00763-0711) WPT/MSG Ann. 031-00785-0505 or (031-00763-0505/-0718)

KLN 90/B or KLX 135 Ann. Set (14 V. ltg.)

NAV/GPS Sw. Ann. 031-00785-0712 or (031-00763-0712) WPT/MSG Ann. 031-00785-0762 or (031-00763-0762/-0719)

KLN 90/B or KLX 135 Ann. Set (5 V. ltg.)

NAV/GPS Sw. Ann. 031-00785-0713 or (031-00763-0713) WPT/MSG Ann. 031-00785-0506 or (031-00763-00506/-0720)

KLN 90B Approach Set for CDI or Elect. Mech. HSI Installations The following switch/annunciators are being offered for CDI or HSI switching, GPS CRS and APR

switching, and annunciation in KLN 90B non-precision approach installations.

NOTE

The GPS CRS OBS/LEG switch annunciators were

available in two different color configurations. Both

versions were approved for use with the GPS’s. The

white OBS was the preferred version.

The 031-00785-0763/0764/0765 versions were visible white for the GPS CRS field, yellow for the OBS field and green for the LEG field.

The 031-00785-0778/0779/0780 versions were visible white for the GPS CRS field, white for the OBS field and green for the LEG field.

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BENDIX/KING KLN 90B

KLN 90B Ann. Set (28 V. Ltg.)

NAV/GPS Sw. Ann. 031-00785-0711 or (031-00763- 0711) WPT/MSG Ann. 031-00785-0505 or (031-00763- 0505/-0718) GPS CRS OBS/LEG Sw. Ann. 031-00785-0778 or (031-00785-0763) GPS APR ARM/ACT Sw. Ann. 031-00785-0766

KLN 90B Ann. Set (14 V. Ltg.)

NAV/GPS Sw. Ann. 031-00785-0712 or (031-00763- 0712) WPT/MSG Ann. 031-00785-0762 or (031-00763- 0762/-0719) GPS CRS OBS/LEG Sw. Ann. 031-00785-0779 or (031-00785-0764) GPS APR ARM/ACT Sw. Ann. 031-00785-0767

KLN 90B Ann. Set ( 5 V. Ltg.)

NAV/GPS Sw. Ann. 031-00785-0713 or (031-00763- 0713) WPT/MSG Ann. 031-00785-0506 or (031-00763- 0506/-0720) GPS CRS OBS/LEG Sw. Ann. 031-00785-0780 or (031-00785-0765) GPS APR ARM/ACT Sw. Ann. 031-00785-0768

KLN 90A Upgrade to KLN90B Approach Set

If a KLN 90A is upgraded to a KLN 90B, the additional GPS CRS and GPS APR switch/annunciators are needed.

or KLN 90B with EFIS Approach Set Most EFIS systems will provide NAV/GPS switching and WPT/MSG annunciation but still require

external GPS CRS and GPS APR switch/annunciators.

NOTE

The GPS CRS OBS/LEG switch annunciators were

available in two different color configurations. Both

versions were approved for use with the GPS’s. The

white OBS was the preferred version.

The 031-00785-0763/0764/0765 versions were visible white for the GPS CRS field, yellow for the OBS field and green for the LEG field.

The 031-00785-0778/0779/0780 versions were visible white for the GPS CRS field, white for the OBS field and green for the LEG field.

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BENDIX/KING KLN 90B

EFIS or KLN90A to 90B Upgrade Ann. Set (28 V. ltg.) GPS CRS OBS/LEG Sw. Ann. 031-00785-0778 or (031-00785-0763) GPS APR ARM/ACT Sw. Ann. 031-00785-0766

EFIS or KLN90A to 90B Upgrade Ann. Set (14 V. ltg.) GPS CRS OBS/LEG Sw. Ann. 031-00785-0779 or (031-00785-0764) GPS APR ARM/ACT Sw. Ann. 031-00785-0767

EFIS or KLN90A to 90B Upgrade Ann. Set (5 V. ltg.) GPS CRS OBS/LEG Sw. Ann. 031-00785-0780 or (031-00785-0765) GPS APR ARM/ACT Sw. Ann. 031-00785-0768

NAV/GPS Switch/Annunciator Installations where the outputs from KLN 90B and an existing navigation system are switched be-

tween a common indicator or HSI 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 Honeywell P/N Honeywell P/N

28 V 031-00763-0711 031-00785-0711 5 V 031-00763-0713 031-00785-0713 14 V 031-00763-0712 031-00785-0712

(Eaton Series 584) (Eaton Series 582)

WPT/MSG Remote Annunciators The KLN 90B contains two outputs: 1) Waypoint Alert (WPT) and 2) Message (MSG). Annuncia-

tion of these outputs is required for certification purposes. A remote annunciator unit is available to annunciate these outputs and is offered in either 5 V, 14 V, or 28 V versions as shown below. The original design of this unit contained the required (WPT) and (MSG) plus two additional fields (-/-) as it was expected that additional annunciation would be required in the future. It has now been determined, however, that additional annunciation will not be required. Therefore, a new design is being offered that contains only the (WPT) and (MSG) fields which allows improved readability. Both options are listed in the following.

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BENDIX/KING KLN 90B

FOUR FIELD ANNUNCIATORS (WPT/MSG/---/---)

LIGHTING Honeywell P/N

28 V 031-00763-0718 14 V 031-00763-0719

5 V 031-00763-0720

NOTE: (WPT) AND (MSG) will be in amber color and the dashes in green. These an-

nunciators will be deadface and readable only when lit. Dashes will only be lit during an annunciator test as a function of the aircraft installation.

TWO FIELD ANNUNCIATORS (WPT/MSG)

LIGHTING Honeywell P/N Honeywell P/N

28 V 031-00763-0505 031-00785-0505 14 V 031-00763-0506 031-00785-0506 5 V 031-00763-0762 031-00785-0762

(Eaton Series 584) (Eaton Series 582)

NOTE: (WPT) AND (MSG) will be in amber color. These annunciators will be deadface

and readable only when lit.

GPS CRS, OBS/LEG Switch/Annunciator The KLN 90B may operated in either of two modes, LEG or OBS. In LEG mode, the flightplan legs

will automatically sequence as determined by present position. In OBS mode, the active waypoint and inbound or outbound course will be manually selected. The Remote OBS/LEG Switch/Annunciator is recommended for non-precision approaches to reduce pilot workload.

The selection of OBS or LEG may be accomplished in either of two methods.

Method 1:

Select the Mode Page by rotating the left outer knob Turn the left inner knob to select OBS or LEG Press ENTER to activate the mode

Method 2:

Press the Remote OBS/LEG switch/annunciator to change modes

If the Remote OBS/LEG Switch/Annunciator is installed, the KLN 90B will sense its presence, on turn-on, and disallow selection of OBS/LEG modes by the KLN90B front panel controls. If the remote switch is not installed, the front panel controls will function as before.

LIGHTING Honeywell P/N or Honeywell P/N

28 V 031-00785-0778 or 031-00785-0763 14 V 031-00785-0779 or 031-00785-0764 5 V 031-00785-0780 or 031-00785-0765

(Eaton Series 582)

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BENDIX/KING KLN 90B

GPS APR, ARM/ACTV Switch/Annunciator

The KLN 90B requires a switch/annunciator for arming, disarming, or deactivating 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.

LIGHTING Honeywell P/N

28V 031-00785-0766 14V 031-00785-0767 5V 031-00785-0768

(Eaton Series 582)

D. NAV/GPS Switching

Installations in which the outputs from a KLN 90B 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.

E. Straight TNC antenna Connector

The part number for a straight connector for the KA 91 or KA 92 antenna connection is 030-00134-0000.

1.7 LICENSE REQUIREMENTS

None.

1.8 RECOMMENDATIONS FOR IFR APPROVAL

1. Aircraft Logbook Entry

2. Aircraft Installation Requirements The following interface functions were not required for a VFR KLN 90 but are required for

an IFR’d KLN 90B installation. 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. If the 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. If the antenna is a non-TSO’d KA 91, P/N 071-01545-0100, and the KLN 90B is a modified KLN 90, the antenna is eligible for exchange as part of the upgrade program.

xNav 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. If the NAV information is displayed on an EFIS system, it must be capable of displaying variable D- Bar scaling required for GPS approaches. This may require a modification to the EFIS system. (Refer to section 1.5 for a list of typical Nav indicators).

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BENDIX/KING KLN 90B

NOTE

The KPI 552/553/553A’s interfaced to the KNR 665 digital Gold Crown are not compatible with the KLN

90B.

xOBS Interface

For approach approval, the OBS resolver must be interfaced so that selected course through the HSI/CDI indicator will be sent to the KLN 90B for D-Bar resolution. In mechanical indicators, it will be accomplished by switching the OBS resolver lines; and in EFIS installations, it will be usually through the serial busses. Some EFIS applications may require an adapter. (Refer to section 2.3.6.2.P for OBS resolver interface characteristics).

xSwitch/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 unless the indicator is part of an EFIS system that provides that function.

WPT/MSG (Annunciator) The required annunciators are "WPT" and "MSG" only. Even though the information is

available on the KLN 90B display, a remote annunciator is also required in the pilots panel unless it is accomplished in an HSI/CDI or EFIS display.

GPS CRS, OBS/LEG (Switch/Annunciator)

The KLN 90B may operate in either of two modes, LEG or OBS. In LEG mode, the flightplan legs will automatically sequence as determined by present position. In OBS mode, the active waypoint and inbound or outbound course will be manually selected. The Remote OBS/LEG Switch/Annunciator is recommended for non-precision approaches to reduce pilot workload.

GPS APR, ARM/ACTV (Switch/Annunciator)

xAltitude Source An altitude source is required for IFR certification. The altitude may be derived from a

compatible encoding altimeter, some RS 232 air data systems, and most ARINC 429 air data systems. (Refer to figure 2-17 for typical altitude sources).

xIsolation Diodes KLN 90’s below S/N 1542 did not have isolation diodes on the encoding altimeter in-

puts.

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BENDIX/KING KLN 90B

The KLN 90/90A’s upgraded to KLN 90B’s that are below S/N 1542 still will not have isolation diodes and may need to have them added to the installation. If the KLN 90B is without diode isolation and is paralleled with another unit such as a transponder, the combination can cause a loading effect which may result in one or all of the units in parallel being disabled. If the KLN 90B is connected to a dedicated encoding altimeter, the diodes are not necessary.

3. Approved Airplane Flight Manual Supplement A flight manual supplement will need to be prepared and approved. The supplement may

be prepared based on the sample, P/N 006-00835-0000. Refer to Appendix B for information on preparing a flight manual supplement and a copy of the STC approval.

4. Pilot’s Guide The KLN 90B pilots’ guide must be placed in the aircraft in a location that is accessible to

the pilot. The pilot’s guide is P/N 006-08773-0000 and the abbreviated pilot’s guide is P/N 006-08774-0000.

1.9 INSTRUCTIONS FOR CONTINUED AIR WORTHINESS

The instructions for continued air worthiness given in the TC or STC approvals for this product supplements or supercedes the instructions for continued air worthiness in this manual.

Most Honeywell 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 air worthiness. No maintenance is required until the equipment does not properly perform the 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.

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SECTION II

INSTALLATION

2.1 GENERAL INFORMATION

This section contains general suggestions and information to consider before installation of the KLN 90B GPS RNAV. Close adherence to these suggestions will assure optimum performance from the equipment.

The conditions and tests required for TSO approval of this article are minimum performance standards. It is the responsibility of those desiring to install this article either on or within a specific type or class of aircraft to determine that the aircraft installation conditions are within TSO standards. The article may be installed only if further evaluation by the applicant documents an acceptable installation 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 per 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 Honeywell warranty.

In the case of the KLN 90B, 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 90B MECHANICAL INSTALLATION

The KLN 90B 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 satisfactory performance from the equipment.

A. Plan a location on the aircraft panel so that the KLN 90B 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 open-

ing.

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BENDIX/KING KLN 90B

2.3.3 ANTENNA SELECTION

The KA 91 and KA 92 GPS active antennas, P/N 071-01545-0200 and 071-01553-0200 respectively, are the designated antennas for the KLN 90B.

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 90B 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 ze-

nith, as compared to a no ice condition.

CABLE

Length

0 to 40 ft. 024-00002-0000

0 to 40 ft. 024-00051-0060

0 to 80 ft. 024-00072-0000

0 to 100

ft.

CABLE PART NUM-

BER

RG142B/U

RG400/U

ECS 311601

024-00071-0000

ECS 311201

BMA CONNECTOR TNC CONNECTOR MAX. Allowable

Loss (dB)

030-00101-0002

TED Mfg. 9-30-10

030-00101-0002

TED Mfg. 9-30-10

030-00452-0000

TED Mfg. 9-30-26

030-00452-0001

TED Mfg. 9-30-25

030-00134-0000

TED Mfg. 5-10-30

030-00134-0000

TED Mfg. 5-10-30

030-00108-0002

TED Mfg. 5-10-307

030-00108-0003

TED Mfg. 5-10-306

8.0

100 to 165 ft. Contact TED, ECS or PIC for complete cable/connector assembly.

NOTE

A right angle antenna connector is available from

Honeywell (P/N 030-00134-0001) or from TED.

TED Manufacturing Corp. Electronic Cable Specialists (ECS) PIC Wire and Cable

11415 Johnson Drive 11227 W. Forest Home Avenue N63 W 22619 Main Street Shawnee, Kansas 66203 Franklin, Wisconsin 53132 P.O. Box 330 Tel: (913) 631-6211 Tel: (800) ECS-WIRE Sussex, Wisconsin 53089 or (414) 421-5300 Tel: (800) 742-3191 or (414) 246-0500

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BENDIX/KING KLN 90B

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. C. Use a piece 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 air-

craft skin under where the antenna will be mounted. D. Apply Alumiprep No. 33, P/N 016-01127-0000, to both the inside and outside

areas of the fuselage and to the back of the doubler plate. Follow the directions

on the container to 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 pre-

vent 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. It is 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 90B antenna do not exceed 25 inch/lbs of torque on

the antenna mounting screws. H. Apply white RTV sealant around base of installed antenna. Fill mounting screw

holes with RTV sealant (P/N 016-01129-0000 or equivalent).

2.3.6 ELECTRICAL INSTALLATION

2.3.6.1 General Information

The KLN 90B will operate with an input voltage from 11 to 33 VDC, but the front panel lighting circuit must be wired for either +14 VDC, +28 VDC, +5 VDC, or 5 VAC depending upon the version of unit installed. Refer to the KLN 90B interconnect diagram for wiring details.

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 90B 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 90B itself, a point to point continuity check of the wir-

ing 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).

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BENDIX/KING KLN 90B

2.3.6.2 Functional Pinout Descriptions

This section gives a brief description of some of the inputs and outputs of the

KLN 90B. It is provided so the installer can determine what specific wiring needs to be done to the aircraft in which the unit is to be installed. Unless otherwise specified, pins not used are to be left open.

A. Pin 1; 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.

B. Pin 2; TAKE HOME

Pin 2, when grounded, places the KLN 90B in Take-Home mode which is used for trip planning only. It performs as if it is receiving adequate GPS signals to determine its position. It displays the latitude and longitude of its last known position or of whatever position it is initialized to on the Setup Page. Pin 2 should always be left open in the aircraft installation.

C. Pin 3; SDI 1/2

Pin 3 sets the Long-range Navigation System as primary or secondary. If the pin is open, the ARINC 429 setup is for primary. If the pin is grounded, the ARINC 429 setup is for secondary. This pin is read each time the KLN 90B is turned on. This pin is used only for dual long range navigation installations when a KLN 90B is interfaced, through ARINC 429, as system #2.

D. Pins 4 and 5; EFIS 429 Receiver Inputs

The KLN 90B receives information from the Electronic Flight Instrument System (EFIS) or KA 90 display adapter in GAMA 429 format on this input bus. This bus should be left open if no EFIS or adapter is connected to the KLN 90B. For specific label information refer to

Paragraph 1.3.1 in Section 1 of this manual.

E. Pins 6 and 7; Radar Graphics 429 Receiver Inputs

The KLN 90B receives information from the Radar Graphics unit in GAMA 429 format on this input bus. This bus should be left open if no Radar Graphics unit is connected to the KLN 90B. For specific label information refer to Paragraph

1.3.1 in Section 1 of this manual.

F. Pins 8 and 9; Air Data 429 Receiver Inputs

The KLN 90B can receive information from the Air Data unit in GAMA 429 format on this input bus. For specific label information refer to Paragraph 1.3.1 in Section 1 of this manual. If not used, these inputs must be connected to pins 23 and 24 respectively to eliminate unnecessary "air data fail" messages.

G. Pins 10, 11, and 12; OBI Data, Clock, and Sync

This is a three wire data bus that provides bearing to the active waypoint. The data is in Honeywell format and can be used to drive certain Honeywell RMI units. The output can also be converted by a Honeywell KDA 692 which provides standard 4-wire SINE/COSINE OBI information.

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H. Pin 13; RS 232 Out

The KLN 90B outputs data in RS 232 format on this pin. It can be used to interface with certain types of ELT’s, fuel sensors, and moving map displays, and fuel management systems. For specific label information, refer to Appendix A.

I. Pin 14; WPT ALERT

Pin 14 is 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 90B Pilots Guide, P/N 006-08773-

0000.

J. Pin 15; MSG

Pin 15 is the Message 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 message prompt on the KLN 90B is on. For more complete information refer to the KLN 90B Pilots Guide, P/N 006-08773-

0000.

K. Pin 16; APPROACH ACTIVE

Pin 16 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 mode. For more complete information refer the KLN 90B Pilots Guide, P/N 006-08773-

0000.

L. Pin 17; APPROACH ARM

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 will be on whenever the unit is in the approach arm mode. For more complete information refer the KLN 90B Pilots Guide, P/N 006-08773-

0000.

M. Pin 18; Nav Super Flag

Pin 18 is the GPS NAV Super Flag output. A logic high shall be > 18 VDC when the voltage at pin 40 is > 24.8 VDC. A logic high shall be > 10 VDC when the voltage at pin 40 is > 12.4 VDC. A logic high shall be > 20 VDC when the voltage at pin 40 is + 27.5 VDC. A logic low shall be < 3.5 VDC.

N. Pins 19, 20, 21, 22, and 25; NAV Flag +, +From, +To, + RIGHT, and +LEFT/

NAV Flag -

These outputs function like the outputs from standard navigation converters. For the specifications on these outputs refer to Paragraph 1.3.2 in Section 1 of this manual.

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O. Pins 23 and 24; GPS 429 Transmitter outputs

Pins 23 and 24 are the GPS ARINC 429 transmitter output port of the KLN 90B. For specific label information transmitted on this bus refer to Paragraph 1.3.1 in Section 1 of this manual.

P. OBS Resolver Interface

Pin 26; OBS Resolver Sine

Pin 31; OBS Resolver Out

Pin 37; OBS Resolver Cosine

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.

Refer to section 2.4.1, KLN 90B OBS Resolver Calibration Procedure for 30 Hz indicator calibration.

Q. Pin 27; A/C GROUND

Pin 27 is tied to aircraft ground. Wiring harness shields are not to be terminated on this pin. Refer to figure 2-17.

R. Pins 28, 29, and 32; 28 V Light/Light Lo, 14 V/5 V Light, and Light Lo

Pins 28, 29, and 32 are the pins used for the panel lighting. Refer to the interconnect drawing for the correct method of connecting these pins and connecting to the aircraft dimmer bus.

S. Pin 30; Approach Arm Select

Pin 30 is used as a mode programming pin on power-up and later as a select input. If the installation is not certified for approach, the external switch/annunciator is not required. This function can be eliminated by connecting the APPROACH ARM SELECT, pin 30, to the APPROACH ARM ANNUNCIATOR, pin

17. On power- up, it will be monitored to determine whether external switches are installed. If the installation is approved for approach and the external switch/ annunciator is installed, then a momentary ground on pin 30 will alternately arm or disarm the approach mode.

T. Pin 33;LEG/OBS

Pin 33 is used as a mode programming pin on power-up and later as a select input. If the installation does not require an external switch/annunciator to select the OBS mode, then connect the LEG/OBS CONTROL, pin 33, to the + TO, pin

21. On power-up, it will be monitored to determine whether external switches are installed. If the external switch/annunciator is not installed, the selection of OBS and LEG will be performed by means of the left inner and outer knobs on the MODE page. If the installation is approved for approach and the external switch/ annunciator is installed, then a ground on pin 33 will switch the unit between LEG and OBS modes. The MODE page on the left inner and outer knob will be disabled.

CONTROL

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U. Pin 34; Data Loader Out

Pin 34 outputs Data Loader information in RS 232 format. It can be used to interface with a laptop IBM compatible PC to load the database.

V. Pin 35; Data Loader In

Pin 35 inputs Data Loader information in RS 232 format. It can be used to interface with a laptop IBM compatible PC to load the database.

W. Pin 36; RS 232 In

Pin 36 is the RS 232 input. If there is not an RS 232 input, i.e. a Fuel Management or Air Data sensor connected to the KLN 90B, Pin 36 (RS 232 In) should be connected to Pin 13 (RS 232 Out) to eliminate unnecessary "NO RS-232 DATA" messages. For more information refer to KLN 90B Pilots Guide, P/N 00608773-0000. Pin 36 may be connected to pin 13 even though Pin 13 is also used to drive another load. For specific label information, refer to Appendix A.

X. Pin 38; ALT ALERT

Pin 38 is the Altitude Alert input/output pin. Configuration is determined by a sampling at powerup. If pin 38 is grounded, it is configured as an input. All pilot selectable altitude alert functions of the KLN 90B will be disabled. This option should be considered if another altitude preselector is already installed in the aircraft. If pin 38 is open or connected to drive an alerting device, it is configured as an output. Altitude alert functions will be selectable through the KLN 90B front panel controls.

Y. Pin 39; ALT ALERT AUDIO

Pin 39 is the Altitude Alert Audio output which is active whenever ALT ALERT is active.

Z. Pin 40; A/C Power

Pin 40 is the DC aircraft power input. The KLN 90B will accept from 11 VDC to 33 VDC input power.

AA. Pins 41 thru 50; Gray Code Inputs

Pins 41 through 50 are gray code altitude inputs from an encoding altimeter. If the KLN 90B 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.

KLN 90/90B with serial numbers 1542 and above have diodes already installed internally. Units with serial numbers below 1542 will only need the diodes in the aircraft harness if it is interfaced to an encoder and another unit.

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FIGURE 2-1 KLN 90B CONNECTOR PIN FUNCTIONS

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FIGURE 2-2 KLN 90B CRIMPING AND INSERTION/EXTRACTION TOOLS

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FIGURE 2-3 KLN 90B INSTALLATION DRAWING (DWG. NO. 155-05818-0000 R-AB)

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FIGURE 2-4 KA 91 OUTLINE (DWG. NO. 071-01545-0200 R-4)

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FIGURE 2-5 KA 91 INSTALLATION DRAWING (DWG. NO. 155-05999-0000 R-5)

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FIGURE 2-6 KA 91 BACKPLATE OUTLINE (DWG. NO. 047-10130-0000/0002 R-2)

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FIGURE 2-7 KA 92 OUTLINE DRAWING (DWG. NO. 071-01553-0200 R-AB)

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FIGURE 2-8 KA 92 INSTALLATION DRAWING (DWG. NO. 155-06019-0000 R-2)

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FIGURE 2-9 KA 92 BACKPLATE OUTLINE (DWG. NO. 047-10735-0000/0002 R-1)

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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)

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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 R-9)

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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)

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FIGURE 2-13 KA 33 P/N 071-4037-00/01 FINAL ASSEMBLY (DWG. NO. 300-03256-0000, R-AA)

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FIGURE 2-14 KA 33 P/N 071-4037-00/01 OUTLINE AND MOUNTING (DWG. NO. 155-05574-0000, R-5)

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FIGURE 2-15 CUTLER-HAMMER SWITCH/ANNUNCIATOR MOUNTING

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FIGURE 2-16 CUTLER-HAMMER SWITCH/ANNUNCIATOR INTERNAL SCHEMATIC (SHEET 1 OF 2)

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FIGURE 2-16 CUTLER-HAMMER SWITCH/ANNUNCIATOR INTERNAL SCHEMATIC (SHEET 2 OF 2)

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FIGURE 2-17 KLN 90B INTERCONNECT DRAWING (DWG. NO. 155-06021-0000, R-AC) (SHEET 1 OF 10)

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FIGURE 2-17 KLN 90B INTERCONNECT DRAWING (DWG. NO. 155-06021-0000, R-AC) (SHEET 2 OF 10)

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FIGURE 2-17 KLN 90B INTERCONNECT DRAWING (DWG. NO. 155-06021-0000, R-AC) (SHEET 3 OF 10)

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FIGURE 2-17 KLN 90B INTERCONNECT DRAWING (DWG. NO. 155-06021-0000, R-AC) (SHEET 4 OF 10)

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FIGURE 2-17 KLN 90B INTERCONNECT DRAWING (DWG. NO. 155-06021-0000, R-AC) (SHEET 5 OF 10)

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FIGURE 2-17 KLN 90B INTERCONNECT DRAWING (DWG. NO. 155-06021-0000, R-AC) (SHEET 6 OF 10)

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FIGURE 2-17 KLN 90B INTERCONNECT DRAWING (DWG. NO. 155-06021-0000, R-AC) (SHEET 7 OF 10)

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FIGURE 2-17 KLN 90B INTERCONNECT DRAWING (DWG. NO. 155-06021-0000, R-AC) (SHEET 8 OF 10)

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FIGURE 2-17 KLN 90B INTERCONNECT DRAWING (DWG. NO. 155-06021-0000, R-AC) (SHEET 9 OF 10)

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FIGURE 2-17 KLN 90B INTERCONNECT DRAWING (DWG. NO. 155-06021-0000, R-AC) (SHEET 10 OF 10)

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FIGURE 2-18 KLN 90B DATALOADER/PC INTERFACE DRAWING

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2.4 POST INSTALLATION CHECK OUT INFORMATION

2.4.1 KLN 90B RESOLVER CALIBRATION METHOD The KLN 90B supports both 400 Hz and 30 Hz resolvers. However, to assure maximum

accuracy, the KLN 90B will need to be calibrated so that it will work with either type. The following is a procedure for calibrating the resolver in the KLN 90B.

1. With the unit off, press and hold the left cursor button.

2. Turn the unit on, continuing to hold the left cursor button for at least 8 seconds.

3. Allow the unit to start up normally.

4. Make sure that the unit has an active waypoint and the aircraft is located where it can acquire a valid satellite position.

5. Put the unit into the OBS mode by pressing the external switch (if installed) or by using the MOD 2 page.

6. Turn to the STA 3 page using the left inner and outer knobs.

7. Make sure that the KLN 90B is the displayed NAV source on the desired indicator.

8. Using the course pointer (for HSIs) or the OBS knob (on CDIs), adjust the selected course to 0°.

9. Note what the KLN 90B is using for the OBS angle (shown on the bottom line near the center of the screen). If the OBS angle on the KLN 90B agrees with the selected course on the external indicator, then no calibration is necessary.

10. If the two values do not agree, then the KLN 90B will need to be calibrated. This is done by pressing the left cursor button and adjusting the value next to OBS CAL. A value of 100 is the default setting and represents no correction. It is possible to make adjustments of up to ; 10°. An OBS CAL value of 0 represents -10° and an OBS CAL value of 200 represents a calibration of + 10°.

11. Once the KLN 90B agrees with the external indicator, then the calibration is complete. Turn off the left cursor button.

12. Reset power to restore normal operation.

2.4.2 POST INSTALLATION CHECKOUT PROCEDURE This procedure is divided into two major sections. The first section deals with "Stand Alone" in-

stallations in which none of the signal Input/Output capability of the unit is utilized, (except for the RF input signal from the antenna). In this type of installation the only connections to the KLN 90B are the cable from the GPS antenna, the aircraft power and ground leads, and the lighting bus wires. Connect the unused ARINC 429 Airdata Receiver to the 429 Transmitter and connect the unused RS 232 IN to the RS 232 OUT. All output data is read from the unit front panel display and all input to the unit is via the front panel controls.

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The second part of this procedure deals with an installation in which some or all of the electrical signal I/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.

It is assumed that the operator’s manual for the various units connected to the KLN 90B (as well as the manual for the KLN 90B 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 Pin 40, and that there is a ground on Pin 27. In installations using 28 V lighting, lighting bus voltage should be present between Pins 28 (Hi) and 32 (Lo). In Installations using 5 V or 14 V lighting, lighting bus voltage should be present between Pins 29 (Hi) and 28/32 (Lo), that is both Pins 28 and 32 must be low. Verify that there are no voltages or grounds present on any other pins.

A. Verify that the blower is operating properly. B. Making sure that the power On/Off switch, located on the front panel of the KLN 90B, is in

the "out" position (power off), plug the unit into the mounting rack and verify that the panel

lighting works properly. C. Energize the unit by pushing in the power control switch. D. Manipulate the controls as necessary to display Nav 2 Page on the right half of the screen

and Set 1 Page on the left half of the screen.

On the Set 1 Page, enter the present position 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. If the date is off by a large amount and the date cannot be set back to

the correct year, make the receiver blind to the satellites by disconnecting the coax, setting

the date while on the bench with no antenna, covering the antenna with aluminum foil or pull

the aircraft in where the satellites are not available, such as in the hanger.

E. At this point the aircraft will have to be moved to a location known to have reasonable GPS

signal coverage. This implies an outside location away from tall structures that could mask

low elevation satellites.

F. Display the Status 1 Page. The State shown on the page should change to Acquire (ACQ)

and after a period of not more than 5 minutes, (typically two minutes depending on the sat-

ellite coverage), the unit should display Latitude and Longitude values on the Nav 2 Page

that are correct for the installation location. If the State shown is Search the Sky (STS), the

unit will take up to 15 minutes to calculate a position.

G. Display the Status 1 Page and 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 pe-

riod of 20 seconds and verify that no asterisks appear on the Status 1 Page for 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:

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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

to meet 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 re-

documents an acceptable installation and is ap-

proved by the Administrator

2. The other possibility 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 90B. It should be clearly determined which of the signals are intended to be 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 EFIS or CDI/HSI Interface

Cycle the power on the KLN 90B which will cause the self test page to be displayed. Verify that the CDI needle, after it has settled, is indicating half scale right deflection. Verify that the TO/ FROM flag is indicating FROM. Verify that the nav flag is pulled from view.

Verify the selected course from the EFIS or CDI/HSI is interfaced properly to the KLN 90B in the OBS Mode. The OBS Mode can be selected by two methods:

1. In IFR Non-Precision Approach configurations, the OBS/LEG selection will usually be con-

trolled by means of a GPS CRS external switch/annunciator. Each press of the switch/ annunciator will cause the mode to change between OBS and LEG.

2. In VFR or IFR Enroute/Terminal configurations, the OBS/LEG selection will usually be con-

trolled through the front panel controls of the KLN 90B. Select the Mode Page 2 on the left. If the OBS mode is not active, press the enter button.

Verify that the selected course value on the Mode Page 2 agrees with the value displayed on the EFIS Course Pointer or the HSI Course Pointer, if it is a remotely driven type. Press the left cursor button and modify the selected course value. Again, verify the course pointer tracks the new value. Change the selected course value on the EFIS, HSI or CDI using the

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OBS knob. Verify that the selected course value displayed on the Mode Page 2 tracks the new value selected.

In the OBS mode with the GPS displayed on the CDI/HSI, the resolver is 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 still 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 90B.

2.4.4.3 Radar Graphics Interface

Activate a flight plan. Verify that the flight plan can be observed on the Radar Graphics display. Select a "Joystick" waypoint on the Radar Graphics Unit. Verify that the selected waypoint appears on the SUP Page of the KLN 90B display.

2.4.4.4 Air Data Interface

With altitude being supplied by a compatible Air Data Computer, verify that the proper altitude is indicated on the ALT page (provided the proper baro setting has been entered and if the Air Data Computer does not provide baro-corrected altitude).

2.4.4.5 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 baro has been entered).

Verify that there is no interference between the KLN 90B, 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.

2.4.4.6 RMI Interface

Cycle power on the KLN 90B which will cause the self test page to be displayed. Verify that the RMI indicates 130°.

2.4.4.7 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 90B Nav Page 2. 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 90B Nav Page 2. Switch the toggle switch to AUTO and push the reset button until it stops flashing.

2.4.4.8 Moving Map Interface

If the KLN 90B is interfaced to a moving map display, verify operation by moving the aircraft out to an open location to acquire a satellite position. Enter some active flightplan or waypoint to develop a presentation on the map. Some moving maps require 30 kts of speed to display as the sense track angle is used instead of the heading. Output track angles below 30 kts. are not output.

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2.4.4.9 External Annunciators

Recycle the power on the KLN 90B which will cause the Self Test Page to be displayed. Verify that all external annunciators are energized. Cycle the KLN 90B 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 90B to determine if the lighted annunciator is justified. OBS and LEG annunciators are controlled directly by the annunciator switch contacts and are not driven by the KLN 90B. Toggle the GPS CRS switch to verify that the annunciator switch matches the KLN 90B mode.

NOTE

Annunciators should be checked one at a time in or-

der to verify that the correct one lights.

2.4.4.10 Distance Indicator

Verify that during self test, the distance indicator displays 34.5 NM, 0 KTS, 0 MIN.

2.4.4.11 Dataloader

The data base cartridge may be updated using a 3.5" disk and a laptop computer. The laptop computer must be IBM compatible, have an open COM 1 or COM 2 serial port, and have a

3.5" high density diskette drive. Connect an IBM compatible laptop via PC loader kit P/N 050-03213-0000 (ref. figure 2-18).

Set the KLN 90B to the Set 0 page. Put the #1 diskette into the PC. Cycle the power of the PC and follow the menu driven instructions.

NOTE

The KLN 90B database may be updated using a PC

with the KLN 90B mounted in an aircraft, or via a

KCC 90 (ref. figure 2-18).

2.4.4.12 ALT ALERT

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 ALT ALERT low.

2.4.4.13 Heading Interface

Heading information may be interfaced to the KLN 90B by ARINC 429 or RS 232 to aid in the calculation of wind vectors and for heading orientation of the NAV 5 or moving map, and to enable the ARINC 429 roll steering output. ARINC 429 heading information is provided from an EFIS 40/50 system or a KA 90 interface adapter through the EFIS 429 receiver. 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 232 input.

Display the NAV 5 page and select the HDG orientation to test the heading function. If a valid heading source is available, HDG orientation will be selectable. If the heading is from an RS 232 source and the KLN 90B has not been upgraded to software 1102 or later, it will be necessary to have a valid GPS position before the heading input will be recognized. ARINC 429 heading information is recognized with or without a valid position and may be tested in the hanger.

, ALT ALERT AUDIO

output, if ALT ALERT is not strapped

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2.4.4.14 Roll Steering Interface

Roll Steering is dependent on ground speed to calculate and cannot be displayed on the ground in the Nav mode. However the KLN 90B will test the roll steering while on the system test page and activate all the outputs. The Roll Steering will be valid and active until you approve the page. While on this page you can engage the flight director and observe the command bars change from 0 degrees to 5 degrees right and back to 0 degrees. This will validate the drivers and wiring so you will feel confident.

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SECTION III

OPERATION

3.1 GENERAL INFORMATION

For an explanation of the operating controls of the KLN 90B GPS RNAV refer to the KLN 90B pilots guide (P/N 006-08773-0000) or the aircraft’s flight manual supplement.

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APPENDIX A

RS-232 FORMAT DEFINITIONS

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THIS PAGE RESERVED

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1.0 RS-232

The RS-232 interface will have the following characteristics:

Electrical per EIA RS232C 9600 baudrate, 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 (lsb) Data bit 1 Data bit 2 Data bit 3 Data bit 4 Data bit 5 Data bit 6 Data bit 7 (msb) STOP bit

1.1 HOOK-UP CONFIGURATIONS

The RS-232 input and output can be hooked up in different configurations. For normal operations, the RS-232 input will be connected to a fuel sensor and/or air data. In

installations where the RS-232 input is not connected to a fuel sensor and air data, it will be looped back to RS-232 output. However, in test mode, the RS-232 input and output can be connected to a PC to read or write from or to a memory location or port.

The RS-232 output provides navigation and self-test data in normal and test modes. In test

mode, if a memory or port read or write request is received, the system will send the corresponding response packet(s) and stops sending navigation and self-test data. The only way to resume navigation and self-test data output is by recycling the power.

1.1.1 NORMAL AND TEST MODES:

RS-232 navigation data

ELT and/or moving map and/or PC

self-test data

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fuel data

I <

Fuel Sensor

RS-232

O >

navigation data

self-test data

I <

navigation data

self-test data

Fuel data and air data

navigation data

self-test data

ELT and/or moving map and/or PC

Fuel Sensor

Air Data

ELT and/or moving map

and/or PC

Fuel Sensor

Air Data

Fuel data

I <

Fuel Sensor

RS-232

1.1.2 TEST MODE ONLY :

memory/port read/write request

I <

RS-232

O >

memory/port read/write response

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1.2 RS-232 OUTPUTS

1.2.1 NAVIGATION AND SELF-TEST DATA RS-232 data will be output with the following format:

<STX><id><dddd><it><id><dddd><it>...<id><dddd><it><ETX> <STX> ASCII start of text character <id> item designator <dddd> item data <it> item terminator: <CR> <ETX> ASCII end of text character

item field desg item format width item description

---- ----------- ----- ----------------

A s dd mmhh 9 present latitude

B s ddd mmhh10 present longitude

C ddd 3 track (magnetic) -- dashed if groundspeed < 2KT

D ddd 3 ground speed

E ddddd 5 distance to active waypoint

G sdddd 5 cross track error

I dddd 4 desired track (magnetic) * 10

K ddddd 5 active waypoint identifier

L dddd 4 bearing to active waypoint (magnetic)

Q sddd 4 magnetic variation

T --------- 9 this field will always be dashed

1234567890

s=sign: N for north, S for south dd=degrees mm=minutes hh=hundredths of minutes

s=sign: E for east, W for west ddd=degrees mm=minutes hh=hundredths of minutes

ddd=degrees

ddd=knots

ddddd=nm * 10

s=sign: R for aircraft position right of course, L for aircraft position left of course dddd=nm * 100

dddd=degrees * 10

ddddd=ASCII active waypoint identifier

dddd=degrees * 10

s=sign: E for east, W for west ddd=degrees * 10

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l dddddd 6 distance to destination

dddddd=nm * 10

t abcdefghij 10 GPS discretes

u (described later in this section) self-test data w (described later in this section) flight plan data

a=W for waypoint alert, T for in turn, dashed otherwise b=N for new message, P for persistent message, dash if not c=E for en route, T for terminal, R for approach arm, A for approach active D=L for leg mode, D for direct to, O for OBS mode, or T for OBS to leg transition e=T for TO, F for FROM, dashed if NAV flagged f, g, h, i, and j=all dashed, reserved for future use

If data is invalid, transmit the item designator and fill the rest of the field with dashes. Blank or space character occurs in the item format field will be sent as ASCII character 20H. The following table defines the output data for track, desired track, bearing to active waypoint, and

magnetic variation in leg and OBS modes. The following definitions are used.

TK angle of the course that the aircraft is flying relative to true north DTK angle of the course line at the point nearest the present position relative to true north RAD true radial from the active waypoint to the present position (angle is measured at the

waypoint)

MSC angle of the course line at the active waypoint relative to magnetic north; if the waypoint is a VOR or an approach waypoint, magnetic north is based on the published magnetic variation for that VOR.

LMV magnetic variation at present position WMV magnetic variation at the active waypoint; if the waypoint is a VOR or an approach

waypoint, its published magnetic variation is used, otherwise the computed magnetic

variation at that point. BRG true bearing from the present position to the active waypoint

description

leg mode OBS mode

track TK - LMV TK - WMV desired track DTK - LMV MSC bearing to active waypoint BRG - LMV RAD - WMV ?180° magnetic variation LMV WMV

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Self-test Data The following ASCII format is used for self-test data:

abcdeeeeffffgggghhhhiiiijjjj : 28 bytes

where

Bit Message Description a0 DB missing or DB Checksum Error a1 Battery Low : Service required to prevent loss of user data a2 User data lost a3 No RCVR data a4 No RS-232 Data a5 RS-232 Data Error a6 RS-232 Output Error a7 1 b0 Data Loader Error b1 ARINC 429 Output Fail b2 EFIS RCVR Failure b3 RDRG RCVR Failure b4 Air Data Fail b5 WPT Annunciator OCD/FAIL b6 MSG Annunciator OCD/FAIL b7 1 c0 Approach ACTV OCD/FAIL c1 Approach ARM OCD/FAIL c2 NAV SUPER Flag Failure c3 unused c4 unused c5 unused c6 unused c7 1 d0 unused d1 unused d2 unused d3 unused d4 unused d5 unused d6 unused d7 1 eeee Receiver Error Status Word ffff IC designator in case of EEPROM failure gggg IC designator in case of CPU failure

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hhhh IC designator in case of RAM failure iiii IC designator in case of EPROM failure jjjj IC designator in case of NV RAM failure

Flight Plan Data

Item designator, sequence number, waypoint identifier, latitude/ longitude, and magnetic variation of each waypoint defined in the active flight plan are transmitted with the following format: No information shall be transmitted for waypoints beyond a fence in a flight plan when the active waypoint is before the fence. Likewise, no information shall be transmitted for waypoints after the beginning of a DME arc that is part of a procedure if the active waypoint is before the last waypoint on the arc. No information shall be transmitted for waypoints prior to the last waypoint on the DME arc if the active waypoint is after the arc.

Item Designator

wdd w = ’w’ dd = 01 to 99

NOTE

A maximum of 32 waypoints will be transmitted.

Sequence Number

Byte 1 Bit 76543210

xlannnnn x = undefined nnnnn = Sequential waypoint number, Unsigned binary a = 1 if waypoint is active l = 1 if last waypoint of flight plan

Waypoint Identifier

Byte23456 Bit 76543210 76543210 76543210 76543210 76543210

aaaaaaaa aaaaaaaa aaaaaaaa aaaaaaaa aaaaaaaa aaaaaaaa = ASCII characters of five-character identifier

NOTE

A value of 7FH in byte 2 indicates that the waypoint

identifier is unknown and bytes 2 through 6 should

be ignored.

Latitude/Longitude Latitude and longitude of waypoint. Packed, unsigned binary values for degrees, minutes, and

hundredths of minutes.

Byte 7 8 9 Bit 76543210 76543210 76543210

sddddddd xxmmmmmm xhhhhhhh

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s = 0 North latitude s = 1 South latitude x = Undefined ddddddd = Latitude degrees mmmmmm = Latitude minutes hhhhhhh = Latitude hundredths of minutes

NOTE

A value of 7FH in byte 7 indicates that latitude and

longitude are not presently available and bytes 7

through 13 should be ignored.

Byte 10 11 12 13 Bit 76543210 76543210 76543210 76543210

sxxxxxxx dddddddd xxmmmmmm xhhhhhhh s = 0 East longitude s = 1 West longitude x = Undefined dddddddd = Longitude degrees mmmmmm = Longitude minutes

hhhhhhh = Longitude hundredths of minutes Magnetic Variation Byte 14 15 Bit 76543210 76543210 nnnnnnnn nnnnnnnn

nnnnnnnnnnnnnnnn = Magnetic variation at waypoint. Two’s complement binary in

sixteenths of degrees. Easterly variation is positive.

NOTE

A value of 7FH in byte 14 indicates that magnetic

variation is not presently available and bytes 14 and

15 should be ignored.

If the flight plan is invalid no flight plan data will be transmitted. The data, including all of the waypoints in the active flight plan, shall be output every 2 sec $ 0.5

sec.

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1.3 RS-232 INPUTS

1.3.1 FUEL/AIR DATA INPUT One of the following 4 ASCII formats shall be transmitted. Any data which is not valid shall be in-

dicated by dashes (ASCII 2DH). Format A A 13 byte ASCII string shall be transmitted per the following format: Byte Data 1 STX (ASCII code 02H) 2 Unit of measure

G = .1 gallon I = .1 imperial gallon L = 1 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).

7 Fuel Remaining Checksum

Break each decimal value into its BCD representation. Using BCD arithmetic, sum the 4 BCD values and convert the low-order BCD digit to an ASCII coded numeric digit. Example: The checksum for a value of 432 would be "9" (39H).

8-11 Fuel Flow Rate (units/hour)

ASCII-coded decimal format as for Fuel Remaining.

12 Fuel Flow Rate Checksum

Sum of fuel flow bytes computed as for Fuel Remaining.

13 ETX (ASCII code 03H) This 13 byte record shall be transmitted every 1.6 sec $.16 sec. Fuel remaining and fuel flow rate information shall be for the complete aircraft.

Format B A 52 byte ASCII string shall be transmitted per the following format: Byte Data 1 STX (ASCII code 02 hex) 2 Units of Measure

G = gallons I = Imperial gallons L = liters K = kilograms B = pounds

3-8 Total Fuel Remaining

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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).

9 Total Fuel Remaining Checksum

10-15 Total Fuel Flow Rate