Honeywell GPS Receiver GPS RNAV User Manual

INSTALLATION MANUAL

KLN 90B

GPS RNAV

MANUAL NUMBER 006-10521-0005

REVISION 5 April, 2003

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BENDIX/KING

KLN 90B

SECTION I

GENERAL INFORMATION

Paragraph

Page

1.1

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

1.2

1.3

1.3.1

1.3.3

1.4

1.4.1

1.4.2

1.4.3

1.4.4

1.4.5

1.5

1.6

1.7

1.8

1.9

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BENDIX/KING

KLN 90B

SECTION II

INSTALLATION

ParagraphPage

2.1

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

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

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

AVIONICS COOLING REQUIREMENTS

2.2

2.3

2.3.1

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

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

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

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

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

2.3.2

2.3.3

2.3.4

2.3.5

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

2.4.2

2.4.3

2.4.4

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

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

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

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

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

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

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BENDIX/KING

KLN 90B

SECTION III

OPERATION

Paragraph

Page

3.1

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

LIST OF ILLUSTRATIONS

Figure

2-1

Page

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

2-2

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

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

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

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

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

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

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

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

KA 91/92 TNC ANTENNA COAX/CONNECTOR ASSEMBLY

2-3

2-4

2-5

2-6

2-7

2-8

2-9

2-10

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

KA 91/92 BMA ANTENNA COAX/CONNECTOR ASSEMBLY

2-11

2-12

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

KA 91/92 TNC/BMA ANTENNA COAX/CONNECTOR ASSEMBLY

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

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

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

CUTLER-HAMMER SWITCH/ANNUNCIATOR UNIT

2-13

2-14

2-15

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

CUTLER-HAMMER SWITCH/ANNUNCIATOR UNIT

2-16

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

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

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

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

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

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

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

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

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

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

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

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

2-17

2-18

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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

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BENDIX/KING

KLN 90B

SECTION I

GENERAL INFORMATION

1.1 INTRODUCTION

This manual contains information relative to the physical, mechanical, and electrical character-

istics of the BENDIX/KING KLN 90B Global Positioning System (GPS) Receiver. General instal-

lation 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 informa-

tion 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 dis-

play consists of a right and left page and a status line at the bottom of the display. The informa-

tion on the left page is controlled by the concentric knobs on the left side of the unit and the in-

formation 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-way-

point, ground speed, track angle, time to waypoint, bearing to waypoint and advisory VNAV guid-

ance. 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 Jeppe-

sen 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 car-

tridge 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 avail-

ability 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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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

306

307

SELECTED COURSE

NAV/WPT/APT LATITUDE

NAV/WPT/APT LONGITUDE

TRUE HEADING

314

320

MAGNETIC HEADING

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

307

NAV/WPT/APT LATITUDE

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

LABEL(OCTAL) DESCRIPTION

203

204

205

210

211

213

ALTITUDE (1013.25 MB)

BARO CORRECTED ALTITUDE

MACH

TRUE AIRSPEED

TOTAL AIR TEMPERATURE

STATIC AIR TEMPERATURE

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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

002

012

074

075

100

113

114

115

116

121

147

150

251

252

261

275

300

DISTANCE TO GO (BCD)

TIME TO GO (BCD)

GROUND SPEED (BCD)

DATA RECORD HEADER

ACTIVE WAYPOINT FROM/TO DATA

SELECTED COURSE #1

MESSAGE CHECKSUM

DESIRED TRACK (TRUE)

WAYPOINT BEARING (TRUE)

CROSS TRACK DISTANCE

HORIZONTAL COMMAND

MAGNETIC VARIATION

GREENWICH MEAN TIME

DISTANCE TO GO

TIME TO GO

GPS DISCRETE WORD

LONG RANGE NAV STATUS

STATION MAGNETIC VARIATION,

TYPE, AND CLASS

303

304

305

306

307

MESSAGE LENGTH/TYPE/NUMBER

MESSAGE CHARACTERS 1-3

MESSAGE CHARACTERS 4-6

NAV/WPT/APT LATITUDE

NAV/WPT/APT LONGITUDE

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KLN 90B

310

311

312

313

314

315

316

321

326

351

PRESENT POSITION LATITUDE

PRESENT POSITION LONGITUDE

GROUND SPEED

TRACK ANGLE (TRUE)

TRUE HEADING

WIND SPEED

WIND ANGLE (TRUE)

DRIFT ANGLE

LATERAL DEVIATION SCALE FACTOR

DISTANCE TO DESTINATION (VIA

FLIGHT PLAN)

352

TIME TO DESTINATION (VIA FLIGHT

PLAN)

371

377

SPECIFIC EQUIPMENT IDENT

EQUIPMENT HEX ID CODE

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

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KLN 90B

1.3.3 UNIT TECHNICAL CHARACTERISTICS

Table 3-6 KLN 90b

TSO Compliance

Physical Dimensions:

Width:

SEE TSO APPENDIX

6.312 in. (16.03 cm.)

Height:

2.00 in. (5.08 cm.)

12.55 in. (31.87 cm.)

6.30 lbs. (2.86 Kg.)

Length:

Weight:

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:

Altitude Range:

-40° C to +70° C

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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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:

SDI 1/2:

OPEN = Normal Operation

GND = Take Home Mode

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:

ARM SELECT:

See Section 1.3.1

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

and later as a select input.

LEG/OBS CONTROL:

DATA LOADER IN:

RS 232 IN:

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

and later as a control input.

The Data Loader RS 232 input is designed to communi-

cate with the dataloader

The RS 232 input is designed to communicate with devic-

es, i.e. air data and fuel flow sensors via RS 232 format

(refer to Appendix A)

ALT ALERT:

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

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 Gray Code Altitude Signals (0 V. to 28 V.) These inputs are diode

4,C1,C2,C4,D4)

isolated inside the KLN 90B on all units above S/N 1542

OBS RES SIN:

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

and 100 K ohms (dc)

OBS RES COS:

OBS resolver cosine, nominal input impedance = 36.5 K ohms

(ac) and 100 K ohms (dc)

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KLN 90B

Table 3-9 KLN 90B Signal Outputs

OBI SYNC,

CLOCK, & DA-

TA:

Honeywell Serial Data containing bearing to the active waypoint

RS 232 OUT:

The RS232 output is designed to interface with certain ARNAV ELTs

and certain moving map displays, storm scopes, and Shadin fuel

flow systems (refer to Appendix A)

WPT ALERT:

OPEN = Inactive

(Waypoint Alert) LOW = Active (Output can sink up to 250 mA

MSG:

(Message)

OPEN = Inactive

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

APPROACH

ACTIVE:

OPEN = Inactive

LOW = Active (Output can sink up to 250 mA

APPROACH

ARM:

OPEN = Inactive

LOW = Active (Output can sink up to 250 mA

CDI Output:

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

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 rela-

tive 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

1 or .3 nautical mile scale factor selectable

.3 nautical mile scale factor only

Approach Arm:

Approach:

Table 3-10 KLN 90B NAV Flag Output

Flag Pulled out

of view:

350 to 900 mV

Flag in view:

< 50mVOutput capable of driving up to five 1 KW parallel loads

Nav Super Flag

Output:

Valid = >18 V in 28 VDC aircraft installations; >10 V in 14 VDC air-

craft installations Invalid = <3.5 V in all installations while sinking 1

mA max. Output can source up to 250mA

OBS Resolver

Out:

Nominal output frequency = 450 Hz Nominal unloaded peak ampli-

tude = 6 V Output drive capability = 40mA

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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 Xmit-

ter:

See Section 1.3.1

DATA LOADER The Data Loader RS 232 output is designed to communicate with an

OUT:

IBM compatible personal computer

ALT ALERT:

HIGH = Inactive

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)

ALT ALERT AU- This output is active whenever ALT ALERT is active, Signal is 1

DIO:

KHz., 3.5 V rms max into 500 W

KA 91 ANTENNA

Table 3-12 KA 91

TSO Compliance:

SEE TSO APPENDIX

Physical Dimensions:

Width:

2.90 in. (7.37 cm.)

0.75 in. (1.91 cm.)

4.70 in. (11.94 cm.)

0.5 lbs. (0.227 Kg.)

600 Kts. TAS

Height:

Length:

Weight:

Airspeed Rating:

Output Impedance:

DC Voltage:

DC Current:

50 Ohms (nominal)

5 Volts $0.5 Volt

50 mA maximum

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KLN 90B

Table 3-13 KA 92

KA 92 ANTENNA

TSO Compliance:

SEE TSO APPENDIX

Physical Dimensions:

Width:

2.70 in. (6.86 cm.)

0.70 in. (1.78 cm.)

4.30 in. (10.92 cm.)

0.27 lbs. (0.12 Kg.)

600 Kts. TAS

Height:

Length:

Weight:

Airspeed Rating:

Output Impedance:

DC Voltage:

DC Current:

50 Ohms (nominal)

5 Volts $0.5 Volt

50 mA maximum

Table 3-14 KA 198 Comm Filter

P/N 071-01565-0000

Center Notch Frequency:

1575.42 MHz.

35 dB min.

.3dB Max.

50 ohms

Attenuation at 1575.42 ;1.5 MHz:

Insertion loss from 118.00 to137.00 MHz:

Impedance from 118.00 to137.00 MHz:

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 ei-

ther 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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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

NIGHT

VISION

GREY

BLACK BEZEL

BRNAV

CAPABLE

(1)

UPGRADED

KLN 90B’s

ARINC

734A

CAPABLE

(2)

GOGGLE BEZEL

066-04031-1121

066-04031-1221

066-04031-1321

066-04031-1421

066-04031-1521

066-04031-1621

066-04031-2121

066-04031-2221

066-04031-2321

066-04031-2421

066-04031-1122

066-04031-1222

066-04031-1322

066-04031-1422

066-04031-1522

066-04031-1622

066-04031-2122

066-04031-2222

066-04031-2322

066-04031-2422

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

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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 man-

ual. 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

0000 VENDOR NAME

P/N

050-03096-0000

030-00101-0002

030-01157-0011

KLN90 INSTALL-CRIMP

PANEL MOUNT PLUG (J902)

SOCKET CRMP 20G

TED Mfg. 9-30-10

Positronics

FC6020D-14

030-01176-0000

030-01428-0006

CONN SUB-D HSG 50S (J901)

HOOD W/SPCL LCK 50P

Positronics

RD50F00000-

782.0

Positronics

D50000 GVLD

033-00230-0000

057-05621-0000

057-05628-0000

071-01541-0000

071-06121-0000

089-02353-0001

089-06012-0008

089-08252-0030

090-00019-0007

187-01722-0000

DATA LOADER JACK

DECAL DATA LOADER

GPS DISCLAIMER

MOUNTING RACK ASSY

ALLEN WRENCH .094

NUT CLIP 6-32

SCR FHP 6-32X1/2

WASHER

RING RTNR .438

GASKET

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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

VENDOR NAME &

0000 P/N

050-03195-0000 KA91 INSTALL

030-00134-0001 RIGHT ANGLE CONN

COAX

TED MFG 5-30-102

047-10130-0002 BACKPLATE, ANTENNA

089-06908-0012 SCREW, AIRCRAFT

187-01807-0000 KA 91 GASKET

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

-0000

VENDOR NAME & P/

050-03318-0000

030-00134-0001

KA92 INSTALL

RIGHT ANGLE CONN

COAX

TED MFG 5-30-102

047-10735-0002

089-05909-0012

187-01831-0000

BACKPLATE, ANTENNA

SCREW, PHP 8-32x3/4

KA 92 GASKET

1.4.5 DATABASE

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

North American Database

071-01523-0302

071-01523-0304

071-01523-0305

Atlantic International Database

Pacific International Database

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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, tele-

phone (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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KLN 90B

Functions of the -0101 include converting 3-wire heading sources to ARINC 429, convert-

ing 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 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 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 sys-

tems)

The devices shown below are Eaton 582/584 series switch/annunciators and are repre-

sentative of those used in our original certification. They were chosen because of their

excellent sunlight readable characteristics and meet or exceed the requirements of Advi-

sory Circular 20-138. These are high quality devices and we encourage their use, Howev-

er, there are other comparable devices on the market that may be substituted at the install-

er/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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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

037-00009-0007

037-00009-0008

037-00009-0006

14V

28V

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 in-

stallations.

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 Ann. Set

KLN 90B

(28 V. Ltg.)

NAV/GPS Sw. Ann.

WPT/MSG Ann.

GPS CRS OBS/LEG

Sw. Ann.

031-00785-0711 or (031-00763- 0711)

031-00785-0505 or (031-00763- 0505/-0718)

031-00785-0778 or (031-00785-0763)

031-00785-0766

GPS APR ARM/ACT

Sw. Ann.

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

NAV/GPS Sw. Ann.

WPT/MSG Ann.

031-00785-0712 or (031-00763- 0712)

031-00785-0762 or (031-00763- 0762/-0719)

GPS CRS OBS/LEG

Sw. Ann.

031-00785-0779 or (031-00785-0764)

031-00785-0767

GPS APR ARM/ACT

Sw. Ann.

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

NAV/GPS Sw. Ann.

WPT/MSG Ann.

031-00785-0713 or (031-00763- 0713)

031-00785-0506 or (031-00763- 0506/-0720)

GPS CRS OBS/LEG

Sw. Ann.

031-00785-0780 or (031-00785-0765)

031-00785-0768

GPS APR ARM/ACT

Sw. Ann.

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/annunci-

ators are needed.

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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EFIS or KLN90A to 90B Upgrade Ann. Set (28 V. ltg.)

KLN 90B

GPS CRS OBS/LEG

Sw. Ann.

031-00785-0778 or (031-00785-0763)

031-00785-0766

GPS APR ARM/ACT

Sw. Ann.

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/an-

nunciator 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

28 V

Honeywell P/N

031-00763-0711

031-00763-0713

031-00763-0712

(Eaton Series 584)

031-00785-0711

031-00785-0713

031-00785-0712

(Eaton Series 582)

5 V

14 V

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 de-

sign is being offered that contains only the (WPT) and (MSG) fields which allows improved read-

ability. Both options are listed in the following.

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KLN 90B

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

LIGHTING

28 V

Honeywell P/N

031-00763-0718

031-00763-0719

031-00763-0720

14 V

5 V

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

28 V

Honeywell P/N

031-00763-0505

031-00763-0506

031-00763-0762

(Eaton Series 584)

031-00785-0505

031-00785-0506

031-00785-0762

(Eaton Series 582)

14 V

5 V

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/Annun-

ciator 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 re-

mote switch is not installed, the front panel controls will function as before.

LIGHTING

28 V

Honeywell P/N

031-00785-0763

031-00785-0764

031-00785-0765

031-00785-0778 or

031-00785-0779 or

031-00785-0780 or

(Eaton Series 582)

14 V

5 V

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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

28V

Honeywell P/N

031-00785-0766

031-00785-0767

031-00785-0768

(Eaton Series 582)

14V

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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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 me-

chanical 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 charac-

teristics).

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)

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 D-Bar scale factors. (Refer to section 1.6.C for typical switch/annuncia-

tors).

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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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 informa-

tion 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 mainte-

nance”. On condition maintenance is described as follows; There are no periodic service re-

quirements 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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KLN 90B

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KLN 90B

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 stan-

dards. 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 ship-

ping 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 max-

imum 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 sys-

tem 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 sug-

gestions 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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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 respec-

tively, 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 an-

tenna 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 be-

low. 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

CABLE PART NUM-

BER

BMA CONNECTOR

TNC CONNECTOR MAX. Allowable

Loss (dB)

0 to 40 ft.

0 to 80 ft.

024-00002-0000

RG142B/U

030-00101-0002

TED Mfg. 9-30-10

030-00134-0000

TED Mfg. 5-10-30

8.0

024-00051-0060

RG400/U

030-00101-0002

TED Mfg. 9-30-10

030-00134-0000

TED Mfg. 5-10-30

024-00072-0000

ECS 311601

030-00452-0000

TED Mfg. 9-30-26

030-00108-0002

TED Mfg. 5-10-307

0 to 100

ft.

024-00071-0000

ECS 311201

030-00452-0001

TED Mfg. 9-30-25

030-00108-0003

TED Mfg. 5-10-306

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

Shawnee, Kansas 66203 Franklin, Wisconsin 53132

11227 W. Forest Home Avenue

N63 W 22619 Main Street

P.O. Box 330

Tel: (913) 631-6211

Page 2-2

Tel: (800) ECS-WIRE

or (414) 421-5300

Sussex, Wisconsin 53089

Tel: (800) 742-3191

or (414) 246-0500

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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 inter-

connect 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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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 oth-

erwise 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 con-

nected 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 po-

sition 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 spe-

cific 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 Sec-

tion 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 pro-

vides standard 4-wire SINE/COSINE OBI information.

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KLN 90B

H. Pin 13; RS 232 Out

The KLN 90B outputs data in RS 232 format on this pin. It can be used to inter-

face 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 illumi-

nate. 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 annun-

ciator 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 illumi-

nate. 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 illumi-

nate. 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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KLN 90B

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 in-

terface will operate properly with either "0.85 gain" resolvers or "0.41 gain" re-

solvers 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 inter-

connect 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/annun-

ciator is not required. This function can be eliminated by connecting the AP-

PROACH 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 CONTROL

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.

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U. Pin 34; Data Loader Out

KLN 90B

Pin 34 outputs Data Loader information in RS 232 format. It can be used to in-

terface 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 inter-

face 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 Manage-

ment 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 DA-

TA" messages. For more information refer to KLN 90B Pilots Guide, P/N 006-

08773-0000. 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 air-

craft. 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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KLN 90B

Page 2-8

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KLN 90B

FIGURE 2-1 KLN 90B CONNECTOR PIN FUNCTIONS

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KLN 90B

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

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KLN 90B

Page 2-12

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KLN 90B

FIGURE 2-3 KLN 90B INSTALLATION DRAWING

(DWG. NO. 155-05818-0000 R-AB)

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KLN 90B

FIGURE 2-4 KA 91 OUTLINE

(DWG. NO. 071-01545-0200 R-4)

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KLN 90B

Page 2-16

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KLN 90B

FIGURE 2-5 KA 91 INSTALLATION DRAWING

(DWG. NO. 155-05999-0000 R-5)

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KLN 90B

FIGURE 2-6 KA 91 BACKPLATE OUTLINE

(DWG. NO. 047-10130-0000/0002 R-2)

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KLN 90B

FIGURE 2-7 KA 92 OUTLINE DRAWING

(DWG. NO. 071-01553-0200 R-AB)

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KLN 90B

Page 2-22

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KLN 90B

FIGURE 2-8 KA 92 INSTALLATION DRAWING

(DWG. NO. 155-06019-0000 R-2)

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KLN 90B

FIGURE 2-9 KA 92 BACKPLATE OUTLINE

(DWG. NO. 047-10735-0000/0002 R-1)

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KLN 90B

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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KLN 90B

Page 2-28

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KLN 90B

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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KLN 90B

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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KLN 90B

Page 2-32

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KLN 90B

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

(DWG. NO. 300-03256-0000, R-AA)

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KLN 90B

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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KLN 90B

FIGURE 2-15 CUTLER-HAMMER SWITCH/ANNUNCIATOR MOUNTING

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KLN 90B

FIGURE 2-16 CUTLER-HAMMER SWITCH/ANNUNCIATOR INTERNAL SCHEMATIC

(SHEET 1 OF 2)

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KLN 90B

Page 2-40

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KLN 90B

FIGURE 2-16 CUTLER-HAMMER SWITCH/ANNUNCIATOR INTERNAL SCHEMATIC

(SHEET 2 OF 2)

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KLN 90B

FIGURE 2-17 KLN 90B INTERCONNECT DRAWING

(DWG. NO. 155-06021-0000, R-AC)

(SHEET 1 OF 10)

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KLN 90B

FIGURE 2-17 KLN 90B INTERCONNECT DRAWING

(DWG. NO. 155-06021-0000, R-AC)

(SHEET 2 OF 10)

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KLN 90B

FIGURE 2-17 KLN 90B INTERCONNECT DRAWING

(DWG. NO. 155-06021-0000, R-AC)

(SHEET 3 OF 10)

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KLN 90B

FIGURE 2-17 KLN 90B INTERCONNECT DRAWING

(DWG. NO. 155-06021-0000, R-AC)

(SHEET 4 OF 10)

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KLN 90B

FIGURE 2-17 KLN 90B INTERCONNECT DRAWING

(DWG. NO. 155-06021-0000, R-AC)

(SHEET 5 OF 10)

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KLN 90B

FIGURE 2-17 KLN 90B INTERCONNECT DRAWING

(DWG. NO. 155-06021-0000, R-AC)

(SHEET 6 OF 10)

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KLN 90B

FIGURE 2-17 KLN 90B INTERCONNECT DRAWING

(DWG. NO. 155-06021-0000, R-AC)

(SHEET 7 OF 10)

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KLN 90B

FIGURE 2-17 KLN 90B INTERCONNECT DRAWING

(DWG. NO. 155-06021-0000, R-AC)

(SHEET 8 OF 10)

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KLN 90B

FIGURE 2-17 KLN 90B INTERCONNECT DRAWING

(DWG. NO. 155-06021-0000, R-AC)

(SHEET 9 OF 10)

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KLN 90B

FIGURE 2-17 KLN 90B INTERCONNECT DRAWING

(DWG. NO. 155-06021-0000, R-AC)

(SHEET 10 OF 10)

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KLN 90B

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

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KLN 90B

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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KLN 90B

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 Installa-

tions 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-

sponsibility of those desiring to install this article ei-

ther 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

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 in-

terference, 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 in-

tended 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/ an-

nunciator 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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KLN 90B

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 Ra-

dial 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 prop-

er 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 Receiv-

er 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 posi-

tion 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

KLN 90B

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, 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 ALT ALERT output, if ALT ALERT is not strapped

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 nec-

essary 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.

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KLN 90B

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 ap-

prove the page. While on this page you can engage the flight director and observe the com-

mand 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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KLN 90B

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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KLN 90B

APPENDIX A

RS-232 FORMAT DEFINITIONS

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THIS PAGE RESERVED

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KLN 90B

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 nav-

igation and self-test data output is by recycling the power.

1.1.1 NORMAL AND TEST MODES:

ELT and/or

moving map

and/or PC

RS-232

navigation data

self-test data

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fuel data

Fuel Sensor

RS-232

ELT and/or

moving map

and/or PC

navigation data

self-test data

Fuel data and air data

Fuel Sensor

Air Data

RS-232

ELT and/or

moving map

and/or PC

navigation data

self-test data

Fuel data and air data

Fuel Sensor

Air Data

RS-232

navigation data

self-test data

Fuel data

Fuel Sensor

1.1.2 TEST MODE ONLY :

memory/port read/write request

I <

RS-232

O >

memory/port read/write response

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KLN 90B

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>

ASCII start of text character

item designator

<dddd>

<it>

item data

item terminator: <CR>

ASCII end of text character

<ETX>

item

field

desg item format

width item description

----

-----------

-----

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

1234567890

s dd mmhh

present latitude

s=sign: N for north, S for south

dd=degrees

mm=minutes

hh=hundredths of minutes

present longitude

s ddd mmhh10

s=sign: E for east, W for west

ddd=degrees

mm=minutes

hh=hundredths of minutes

track (magnetic) -- dashed if groundspeed < 2KT

ddd=degrees

ddd

ground speed

ddd=knots

ddddd

sdddd

distance to active waypoint

ddddd=nm * 10

cross track error

s=sign: R for aircraft position right of course,

L for aircraft position left of course

dddd=nm * 100

dddd

ddddd

dddd

sddd

desired track (magnetic) * 10

dddd=degrees * 10

active waypoint identifier

ddddd=ASCII active waypoint identifier

bearing to active waypoint (magnetic)

dddd=degrees * 10

magnetic variation

s=sign: E for east, W for west

ddd=degrees * 10

---------

this field will always be dashed

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dddddd

distance to destination

dddddd=nm * 10

abcdefghij

GPS discretes

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

(described later in this section) self-test data

(described later in this section) flight plan data

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.

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

desired track

bearing to active waypoint

magnetic variation

TK - LMV

DTK - LMV

BRG - LMV

LMV

TK - WMV

MSC

RAD - WMV ?180°

WMV

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KLN 90B

Self-test Data

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

: 28 bytes

abcdeeeeffffgggghhhhiiiijjjj

where

Bit

Message Description

DB missing or DB Checksum Error

Battery Low : Service required to prevent loss of user data

User data lost

No RCVR data

No RS-232 Data

RS-232 Data Error

RS-232 Output Error

Data Loader Error

ARINC 429 Output Fail

EFIS RCVR Failure

RDRG RCVR Failure

Air Data Fail

WPT Annunciator OCD/FAIL

MSG Annunciator OCD/FAIL

Approach ACTV OCD/FAIL

Approach ARM OCD/FAIL

NAV SUPER Flag Failure

unused

eeee

ffff

gggg

unused

Receiver Error Status Word

IC designator in case of EEPROM failure

IC designator in case of CPU failure

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KLN 90B

hhhh

iiii

IC designator in case of RAM failure

IC designator in case of EPROM failure

IC designator in case of NV RAM failure

jjjj

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 in-

formation shall be transmitted for waypoints beyond a fence in a flight plan when the active way-

point is before the fence. Likewise, no information shall be transmitted for waypoints after the be-

ginning 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

Bit

76543210

xlannnnn

= undefined

nnnnn = Sequential waypoint number, Unsigned binary

= 1 if waypoint is active

= 1 if last waypoint of flight plan

Waypoint Identifier

Byte

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

Bit

76543210

sddddddd

76543210

xxmmmmmm xhhhhhhh

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KLN 90B

= 0 North latitude

= 1 South latitude

= 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

Bit 76543210

sxxxxxxx

76543210

dddddddd

76543210

xxmmmmmm xhhhhhhh

= 0 East longitude

= 1 West longitude

= Undefined

dddddddd = Longitude degrees

mmmmmm = Longitude minutes

hhhhhhh = Longitude hundredths of minutes

Magnetic Variation

Byte

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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KLN 90B

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

STX (ASCII code 02H)

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).

Fuel Remaining Checksum

Break each decimal value into its BCD representation. Using BCD arithmetic, sum the 4 BCD val-

ues 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.

Fuel Flow Rate Checksum

Sum of fuel flow bytes computed as for Fuel Remaining.

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

STX (ASCII code 02 hex)

Units of Measure

G = gallons

I = Imperial gallons

L = liters

K = kilograms

B = pounds

3-8

Total Fuel Remaining

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KLN 90B

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).

Total Fuel Remaining Checksum

Break each decimal value into its BCD representation. Using BCD arithmetic, sum the 4 BCD val-

ues and convert the low-order BCD digit to an ASCII coded numeric digit. Example: The checksum

for a value of 543.2 would be "4" (34H).

10-15 Total Fuel Flow Rate

ASCII-coded decimal format as for Total Fuel Remaining.

Total Fuel Flow Rate Checksum

Sum of fuel flow bytes computed as for Total Fuel Remaining.

17-22 Engine One Fuel Flow Rate

ASCII-coded decimal format as for Total Fuel Remaining.

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

ASCII-coded decimal format as for Total Fuel Remaining.

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

ASCII-coded decimal format as for Total Fuel Remaining.

Total Fuel Used Checksum

Sum of Total Fuel Used bytes computed as for Total Fuel Remaining.

38-43 Engine One Fuel Used

ASCII-coded decimal format as for Total Fuel Remaining.

Engine One Fuel Used Checksum

Sum of Left Engine Fuel Used bytes computed as for Total Fuel Remaining.

45-50 Engine Two Fuel Used

ASCII-coded decimal format as for Total Fuel Remaining.

Engine Two Fuel Used Checksum

Sum of Right Engine Fuel Used bytes computed as for Total Fuel Remaining.

ETX (ASCII code 03 hex)

This 52 byte record shall be transmitted every 1.6 sec $.16 sec.

In the case of single engine aircraft, all Engine One and Engine Two data (including checksums)

shall be asterisks (ASCII code 2A hex).

Format C

A 108 byte ASCII string shall be transmitted. Bytes 1 through 51 shall be the same as format B,

described above except that in the Units of Measure field, "I = Imperial Gallons" is undefined. The

remaining bytes shall be defined as follows. (If valid data for a particular data item is received both

on this bus and on an ARINC 429 input, the ARINC 429 data shall be used, and the RS-232 data

shall be ignored.)

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KLN 90B

Byte Data

52-54 indicated airspeed (IAS, knots)

ASCII-coded decimal format (least 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, add the three BCD

values and convert the low-order BCD digit to an ASCII-coded numeric digit. Example: Checksum

for "892" would be "9" (39H).

56-58 true airspeed (TAS, knots)

ASCII-coded decimal format as for IAS.

true airspeed checksum

Sum for TAS bytes computed as for IAS.

60-62 MACH (airspeed/speed of sound)

ASCII-coded decimal format with an implicit leading decimal point (least significant digit is thou-

sandths). Example: A MACH value of .492 would be sent as "294" (32H, 39H, 34H).

MACH checksum

Sum for MACH bytes computed as for IAS.

64-69 pressure altitude (PALT, feet)

ASCII-coded decimal format with a sign character. Example 1: A PALT of 34500 feet would be sent

as "00543+" (30H, 30H, 35H, 34, 33H, 2BH).

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)

ASCII-coded decimal format with a sign character, as for PALT.

density altitude checksum

Sum for DALT bytes, excluding the sign character, as for PALT.

78-80 total air temperature (^oC)

ASCII-coded decimal format with a sign character. Example: An OAT of 25^oC would be sent as

"52+".

total air temperature checksum

Sum for total air temperature bytes, excluding the sign character, as for PALT.

82-84 wind direction (degrees from true north)

ASCII-coded decimal format. Example: 122^owould be sent as "221" (32H, 32H, 31H).

wind direction checksum

Sum for wind direction bytes, as for IAS.

86-88 wind speed (knots)

ASCII-coded decimal format, as for IAS.

wind speed checksum

sum for wind speed bytes, as for IAS.

90-92 drift (degrees)

ASCII-coded decimal format with a direction character. Example 1: 7° right would be "70R".

Example 2: 14° left would be "41L".

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drift checksum

sum for drift bytes, excluding the direction character. Example: The sum for "41L" would be "5"

(35H).

94-98

rate of change of PALT (feet/minute)

ASCII-coded decimal format with a sign character. Example: A PALT 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 (degrees from magnetic north)

ASCII-coded decimal format, as for wind direction.

magnetic heading checksum

100-102

103

sum for magnetic heading bytes, as for IAS.

104-106 static air temperature (°C)

ASCII-coded decimal format with a sign character. Example: A static air temperature of -2°C

would be sent as "20-".

107

108

static air temperature checksum

Sum for static air temperature bytes, excluding the sign character, as for PALT.

ETX (ASCII code 03H)

This 108 byte record shall be transmitted every 1.6 sec ;.16 sec. If data is invalid or unavailable,

the field will be filled with dashes.

Format D

A 121 byte ASCII string shall be transmitted. Bytes 1 through 107 shall be the same as Format C,

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 90B. The remaining bytes shall be defined as

follows. (If valid data for a particular data item is received both on this bus and on an ARINC 429

input, the ARINC 429 data shall be used, and the RS-232 data shall be ignored.)

Byte

Data

108-112 barometric setting (Inches HG)

ASCII-coded decimal format (least significant digit is hundredth of inches), LSB first.

Example: A 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 low-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 +11000 ft, would be "00011+" (30H, 30H, 30H, 31H,

31H,

2BH).

120

baro-corrected altitude checksum

Sum for baro-corrected altitude, excluding sign character, as for pressure altitude.

ETX (ASCII code 03H)

121

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APPENDIX B

Includes the following:

KLN 90B SUPPLEMENTAL PROCEDURES MANUAL

KLN 90B AIRPLANE FLIGHT MANUAL SUPPLEMENT

KLN 90B SUPPLEMENTAL TYPE CERTIFICATE

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APPENDIX C

GPS FAULT/ERROR CODES AND MESSAGES

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KLN 90B GPS FAULT/ERROR CODES, MESSAGES(FROM INSTALLATION BULLETIN 410)

The following tables contain some helpful information to aid in the troubleshooting of the KLN

90B GPS. When the GPS display or the personal computer monitor indicates a GPS Rec. Error

Code, GPS Page Message, or Data Loader Error Message, refer to the tables for an explanation

and suggested action.

The column headings are:

Error Code or Message - the displayed fault indication seen by the user.

Definition - what the message or fault means.

Action Suggested - the probable cause and some possible solutions.

NOTE

If more than one error occurs, the codes can be combined. For instance, if an error code 0800

and an 0008 are both detected, they will be displayed as an 0808. So, if you see an error code

displayed that does not exist in the table, check to see if it is a combination of 2 or more error

codes.

GPS Rec. error Definition

Codes

Suggested Action

RCVR Hardware ROM Failure: The

Bad ROM (Read Only Memory). Return for service.

Bad RAM (Random Access Memory). Return for ser-

Error: 0002

ROM failed self-test.

RCVR Hardware RAM Failure: The

Error: 0004 RAM failed self-test. vice.

RCVR Hardware Nonvolatile Memory It could be one of the following, in the order of prob-

Error: 0008

Failure: The battery-

backed RAM failed

sum-check test.

Nonvolatile memory

will be cleared.

ability:

1. Newly upgraded unit software will display this prior

to receiving satellite signals.

2. The battery back-up power to the GPS Receiver

was lost. This could be due to either a dead internal

battery or a bad connection on the flex cable to the

receiver.

3. Bad RAM.

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GPS Rec. error Definition

Codes

Suggested Action

RCVR Hardware RF Failure: This

It could be one of the following, in the order of prob-

Error: 0010

meansthereceiveris ability:

not sensing a proper 1. Coax open or shorted. Confirm the 5 volts at the

RF signal from the

satellites/antenna.

antenna end.

2. Bad antenna. Substitute the antenna, or inject a

signal at the coax.

3. Bad Receiver Module in GPS. Substitute the GPS

unit, or inject a signal at the input.

RCVR Hardware ASIC Failure: The

Error: 0080 GPS Correlator

It could be one of the following, in the order of prob-

ability:

ASIC failed self-test. 1. The flex cable between the Receiver Board and

Main Board may have come out of the socket in the

GPS.

2. Bad ASIC on the Receiver Module in the GPS.

Substitute the GPS unit.

RCVR Hardware BBP Timeout: The 1 It could be one of the following, in the order of prob-

Error: 0100 mS baseband pro- ability:

cessing timer failed 1. The 5 volt supply to the antenna could be shorted

self-test.

out in the coax. This disables the oscillator in the

GPS.

2. The flex cable between the Receiver Board and

Main Board may have come out of the socket in the

GPS.

3. Bad TCXO or ASIC on the Receiver Module in the

GPS. Substitute the GPS unit.

RCVR Hardware RS-232 Receive

Error: 0400

It could be one of the following, in the order of prob-

Failure: The GPS ability:

Receiver did not re- 1. The flex cable between the Receiver Board and

ceive any initializa- the Main Board may have come out of the socket in

tion data from the

the GPS.

host computer on the 2. Bad 32kHz crystal, UART, or processor on the Re-

RS-232 port.

RCVR Hardware EEPROM Failure:

ceiver Module in the GPS. Substitute the GPS unit.

Bad EEPROM. Return for service.

Error: 0800

The EEPROM failed

sum-check self-test

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GPS Rec. error Definition

Codes

Suggested Action

RCVR Hardware RS-232 Channel 2

It could be one of the following, in the order of prob-

Error: 1000

Failure: The second ability:

RS-232 UART on the 1. The receiver was put in test mode without looping

receiver failed the

back the two serial ports.

loop-back test. This 2. Bad ASIC or Microprocessor on the Receiver

self-test can only be Board.

enabled during test

mode on the receiv-

er, and should not be

seen in normal oper-

ation.

RCVR Hardware BBP Underflow: The It could be one of the following, in the order of prob-

Error: 2000

baseband process- ability:

ing loop detected an 1. The flex cable between the Receiver Board and

error in the 1 mS pro- Main Board may have come out of the socket in the

cessing loop.

GPS.

2. Bad TCXO, MMIC, or ASIC on the Receiver

Board.

RCVR Hardware BBP Overflow: The It could be one of the following, in the order of prob-

Error: 8000

baseband process- ability:

ing loop detected an 1. The flex cable between the Receiver Board and

error in the 1 mS pro- Main Board may have come out of the socket in the

cessing loop.

GPS.

2. Bad TCXO, MMIC, or ASIC on the Receiver

Board.

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GPS Page/Laptop Messages

GPS Message

Definition

Suggested Action

Altitude Fail

Indicates a missing or

The altitude from the encoder may be in error due

to a miswire or the absence of isolation diodes be-

tween the encoder and the transponder.

erroneous altitude.

⋅ The altitude input on

the gray code input from If the GPS is configured for IFR, it must have a

the encoder is wrong.

valid altitude. Verify the presence of altitude on

⋅ The GPS is configured the Self-Test or NAV 4 Page.

for IFR, and there is no

altitude source avail-

able.

ARINC 429 Air

Data Fail

There is no ARINC 429 The Air Data source is not providing 429 data to

data at the Air Data 429 the GPS.

input port.

If no source of ARINC 429 data is interfaced, the

receiver input should be jumpered back to the

Main Transmitter.

The software and hardware of the KLN 90B are in-

compatible. Refer to Service Bulletin KLN 90B-2.

EEPROM Fail-

ure: Icxxxx

Indicates a detected

If the xxxx field is:

EEPROM failure in ei- ⋅ 1xxx - indicates a failure in the processor in the

ther the GPS unit or the KLN 90/A/B GPS unit.

database cartridge.

⋅ 03xx/04xx - indicates a failure in the processor in

the KLN 90/A/B database cartridge.

NAV Superflag

Failure

Indicates an internal

When the flag is supposed to be valid, it should

test of the NAV Super- reach a minimum voltage. Usually a failure is due

flag output failed.

to overloading the output. The output can be test-

ed when the Self-Test Page is displayed.

RAIM position er- RAIM is a method of cal- It could be one of the following, in the order of

ror

culating integrity in the

probability:

Cross check posi- GPS position. It calcu-

1. This probably is a GPS receiver failure. Cross

check your position by other means of navigation.

Return for service.

2. The GPS detected a problem with one of the

satellites, and cannot be assured that the unit it-

self is within IFR limits.

tion

lates the position multi-

ple times using different

sets of satellites and

compares the answers.

If they have excessive

difference, the message

appears.

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GPS Page/Laptop Messages

Suggested Action

Definition

GPS Message

RAIM not avail-

able

This means there are

not enough satellites

The aircraft should be in an open area with good

visibility, and the SNR (Signal to Noise Ratio) on

Cross check posi- available to compute in- the STA 1 or OTH 2 should be as noted below:

tion

tegrity (RAIM).

⋅ KLN 89s will usually have 6-8 satellites shown,

and the majority of their SNRs will be 7 to 9. SNRs

of 3 and below are unusable, 4 is marginal, and 5

through 9 are considered good.

1. The satellites are

blocked from view by

obstructions.

2. They are too low on ⋅ KLN 90/900s will usually have 6-8 satellites

the horizon for use, or shown, and the majority of their SNRs will be 40s.

too high for adequate

geometry.

SNRs of 30 and below are unusable, 30-35 are

marginal and 35-48 are considered good.

3. There is a loss of sen- If the SNRs are low, it could be one of the follow-

sitivity in the antenna, ing, in the order of probability:

the coax, or the Receiv- 1. Check the antenna coax and connection for

er Module.

problems.

2. Verify that 5 volts is present at the antenna end

of the coax.

3. Substitute the receiver to check for sensitivity.

4. Substitute the antenna to check for sensitivity.

No RS-232 Data There is no RS-232data The Air Data/Fuel Flow source is not providing RS

at the RS-232 input

port.

232 data to the GPS.

If no source of RS-232 is interfaced, the receiver

input must be jumpered back to the RS-232 out-

put on KLN 89/89Bs and KLN 90/90A/90Bs.

If no source of RS-232 is interfaced to a KLN 900,

the configuration may be set up wrong.

RCVR hardware These are error codes Refer to the GPS Fault/Error Code table.

error:__

that are detected in the

GPS receiver.

RAIM not avail-

able

Approach mode ability. The message

inhibited

This is a calculated pre- This is a feature, not a system failure.

diction of RAIM avail-

Turn to the OTH 3 or STA 5 page to perform a

RAIM prediction. It will give you an indication of

appears when integrity how long it will be until RAIM is available.

Predict RAIM on monitoring (RAIM) is

OTH 3 or STA 5 predicted to not be

available at either the

This prediction can also be performed prior to de-

parture to insure RAIM at your arrival.

FAF or MAP. The GPS

will not allow the unit to

go into APR ACTV

mode until conditions

improve.

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GPS Page/Laptop Messages

Definition Suggested Action

GPS Message

No RS-232 Data There is no RS-232data The Air Data/Fuel Flow source is not providing RS

at the RS-232 input

port.

232 data to the GPS.

If no source of RS-232 is interfaced, the receiver

input must be jumpered back to the RS-232 out-

put on KLN 89/89Bs and KLN 90/90A/90Bs.

If no source of RS-232 is interfaced to a KLN 900,

the configuration may be set up wrong.

RCVR hardware These are error codes Refer to the GPS Fault/Error Code table.

error:__

that are detected in the

GPS receiver.

RAIM not avail-

able

Approach mode ability. The message

inhibited

This is a calculated pre- This is a feature, not a system failure.

diction of RAIM avail-

Turn to the OTH 3 or STA 5 page to perform a

RAIM prediction. It will give you an indication of

appears when integrity how long it will be until RAIM is available.

Predict RAIM on monitoring (RAIM) is

OTH 3 or STA 5 predicted to not be

available at either the

This prediction can also be performed prior to de-

parture to insure RAIM at your arrival.

FAF or MAP. The GPS

will not allow the unit to

go into APR ACTV

mode until conditions

improve.

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Data Loader Error Messages

Suggested Action

Data Loader Er- Definition

ror

Messages

Loader Not Ready This indicates that the 1. Since the database is not a DOS program, it is

computer and the GPS not compatible with WINDOWS.

are not making a con- It is necessary to boot the computer from the dis-

nection with each other. kettes, and not allow WINDOWS to ever start.

2. Some computers do not have the Com Ports

enabled until WINDOWS is running. Through the

Configuration Setup of your computer, the Com

Port can be enabled. Refer to the owner’s manual

of your computer.

3. Verify the wiring of the data loader cable and

aircraft harness.

Check sum error Indicates an error on the Try an old cycle. If the old cycle diskette works,

database diskettes.

contact AlliedSignal Navigation Services for a re-

placement diskette.

Disk compatibility This indicates a prob-

Verify that Windows is not running and that you

booted the computer from the database diskette.

Try an old cycle. If the old cycle diskette works,

contact AlliedSignal Navigation Services for a re-

placement diskette.

problem

lem with the diskette.

AvailableUpdates The disk has been pre- Obtain a new disk from AlliedSignal Navigation

Already Used

viously used on another Services.

GPS. When a disk

writes to a GPS, the disk

gets keyed so that it

may not be used to up-

date another GPS. The

disk may be used as

many times as desired

on that GPS, but not on

more than one.

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TSO APPENDIX

RTCA DO-160C

ENVIRONMENTAL QUALIFICATION

FORMS

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