N

B
The information contained in this manual is for reference use only. If

any information contained herein conflicts with similar information

contained in the Airplane Flight Manual Supplement, the information in

the Airplane Flight Manual Supplement shall take precedence.

WARNING

Prior to export of this document, review for export license requirement is

needed.

COPYRIGHT NOTICE

©2000 Honeywell International Inc.

Reproduction of this publication or any portion thereof by any means without

the express written permission of Honeywell International Inc. is prohibited.

For further information contact the Manager, Technical Publications;

Honeywell Business & General Aviation; One Technology Center; 23500

West 105th Street; Olathe, Kansas 66061. Telephone: (913) 782-0400.
TABLE OF CONTENTS

INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 

What is the GA-Enhanced Ground Proximity Warning System? . . . . . . . . . . . . . . 

Regulatory Standards . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 

GA-EGPWS FUNCTIONS AND FEATURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . 

Aircraft Position . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 

Aircraft Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 

Terrain, Obstacles & Runway Database . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 

Terrain Inhibit Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 

Terrain Awareness Display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 

“Look-Ahead” Alerting and Warning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Runway Field Clearance Floor (RFCF) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Excessive Rate of Descent Alerting and Warning . . . . . . . . . . . . . . . . . . . . . . . . .

Inadvertent Descent / Loss of Altitude After Take-Off . . . . . . . . . . . . . . . . . . . . . .

GA-EGPWS Altitude Monitoring . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Altitude Callout . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 

NORMAL PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

GA-EGPWS System Self-Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Recommended Procedures for GA-EGPWS Warnings In Flight . . . . . . . . . . . . . .

Recommended Procedures for GA-EGPWS Alerts In Flight . . . . . . . . . . . . . . . . .

ADDITIONAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Audio Message Priority . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

GA-EGPWS Cockpit Lamps & Switches . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

KGP 560 System Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

KGP 560 Continued Airworthiness and Database Update Procedures . . . . . . . . .

KGP 560 Product Support . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

i

Rev 1 Preliminary KGP 560 Pilot's Gui
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Rev 1 Preliminary ii KGP 560 Pilot's Guide 
multi-engine piston aircraft as well as small turbo-props and other a

craft.

Based on 30 years experience in the development and advancement 

Ground Proximity Warning Systems for Air Transport, Regional an

Commuter Airlines, Military aircraft and Corporate aviation, Honeywe

brings this vital safety technology to all segments of General Aviatio

Using our proprietary world-wide terrain database, obstacle databas

runway database, state-of-the-art GPS technology, and proven Terra

Display with Alerting and Warning functions, the system provides th

General Aviation pilot with superior situational awareness with respect 

terrain and known obstacles. In addition, the system contains the mo

advanced alerting and warning functionality to warn the pilot of dang

with respect to terrain, man-made obstacles and other primary scenario

associated with the dangers of Controlled Flight Into Terrain (CFIT).

The KGP 560 GA-EGPWS Computer (less than 1.5 pounds)

Rev 1 Preliminary KGP 560 Pilot's Gui

1
Rev 1 Preliminary KGP 560 Pilot's Guide 

2

craft, its systems, and FAA and/or company requirements for that aircraft

as equipped with the KGP 560 General Aviation Enhanced Ground

Proximity Warning System. 

WHAT IS THE GA-ENHANCED GROUND PROXIMITY

WARNING SYSTEM?

The Bendix/King KGP 560 GA-EGPWS is a small lightweight computer

that can be installed in most single- and multi-engine piston aircraft,

small turboprop aircraft and other aircraft in which a Terrain Avoidance &

Warning System is applicable.

The KGP 560 computer is compact and rugged, and can be mounted in

any number of orientations to meet the requirements of the aircraft and

space limitations. The computer weighs less than 1.5 pounds.

The system uses information from an existing GPS (already in the aircraft) or internal GPS receiver contained in the KGP 560 computer. The

only other required input is uncorrected barometric pressure from the aircraft’s transponder or altitude reporting/encoding device. An additional

input of Outside Air Temperature (OAT) is optional and recommended.

See section on Aircraft Altitude.

The system can also accept inputs from various digital air data computers, when such equipment is available on an aircraft. The terrain

database, obstacle database, runway database and alerting / warning

functionality are contained in the KGP 560 computer, and require no pilot

action for system operation.

Outputs generated by the system are:

* Terrain / Obstacle Display

* Voice alerts / Warnings / Callouts

* Visual alerts / Warnings

During normal flight operations, the system remains essentially silent,

using GPS, altitude and temperature (optional) data in combination with
Rev 1 Preliminary 3 KGP 560 Pilot's Gui

for excessive rates of descent and inadvertent descents or altitude los

after take-off.

The system provides an aural altitude callout when 500 feet abov

runway elevation during a landing approach, and also monitors altimet

systems in the aircraft to provide alerts for possible altimeter malfun

tions or errors.

Pilot reactions to alerts and warnings differ according to weather cond

tions, visibility, type of warning, phase of flight and aircraft performanc

considerations. Pilots should be thoroughly familiar with FAA, compan

or other approved operational procedures as required by their aircra

and type of operation. Pilots should train to react properly to GA

EGPWS alerts and warnings just as one would train to react to an aircra

stall, engine failure or any other emergency situation.

REGULATORY STANDARDS

The KGP 560 GA-EGPWS satisfies the requirements for Terra

Avoidance & Warning Systems (TAWS) as defined by FAA TSO 151

Class B, when installed in aircraft in accordance with approved proc

dures. (See KGP 560 GA-EGPWS System Installation Manual). 

NOTE: All aircraft, which are required by Federal Aviation Regulations 

have a Terrain Awareness and Warning System complying with TS

C151a-class B, must be configured with the TSO curves.

The KGP 560 GA-EGPWS may also be installed in aircraft that do n

require FAA approved TAWS systems, and may be utilized with a

optional set of alerting and warning parameters that are designed esp

cially for smaller piston aircraft and their normal flight characteristic

These “optional alerting and warning parameters outside the TSO” a

set into the computer via the Configuration Module during installatio

and require no pilot interaction.
Rev 1 Preliminary 4 KGP 560 Pilot's Guide 

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Rev 1 Preliminary 5 KGP 560 Pilot's Gui

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GPS signals arrive at an antenna on the aircraft and are then processe

by the KGP 560 computer to provide both horizontal (lateral) and vertic

position (altitude) information. This position in space is then compared 

the terrain, obstacle and runway database information contained in th

KGP 560 computer to produce a “virtual” picture which can then be di

played to provide Situational Awareness for the pilot.

Other GPS information such as true track, groundspeed, vertical velocit

N/S and E/W velocity, and signal accuracy measurements are als

processed by the KGP 560 computer to provide a complete picture of n

only the aircraft position in three dimensions, but also an excellent pi

ture of the aircraft’s flight path.

This total package of information is then used to provide the Terra

Display for the pilot, and to provide alerting and warning functionality 

protect the pilot and passengers from possible conflicts with terrai

known obstacles, and other scenarios associated with the dangers 

Controlled Flight Into Terrain (CFIT).
Rev 1 Preliminary 6 KGP 560 Pilot's Guide 

y g ppy y

“Geometric Altitude”, the GPS and uncorrected pressure altitude information is blended together by the system to provide accurate altitude

information, which is using the same Mean Sea Level (MSL) reference

as the terrain, obstacle and runway databases in the system. The

blending functionality of “Geometric Altitude” means it is much less susceptible to errors or malfunctions in the use of normal altimeter systems.

(The pilot is NOT required to enter an altimeter setting specifically for the

GA-EGPWS system).

Where aircraft are routinely operated in extreme weather conditions

(either hot or cold), Honeywell strongly recommends the optional temperature input be used with the KGP 560 GA-EGPWS. This additional

factor in the blending formula of “Geometric Altitude” provides an even

more accurate vertical position to the system, and prevents serious discrepancies between actual altitude and “Geometric Altitude” under

extreme temperature conditions, especially during rapid climbing or

descending flight profiles.

The second benefit of using “Geometric Altitude” in the system is that the

pilot will now have an independent monitor of altitude. The system can

detect an abnormal difference between “Geometric Altitude” and the

uncorrected pressure altitude. Optionally, the system can provide a

voice callout and display a message to the pilot should such an

abnormal difference occur. 

Geometric Altitude
Rev 1 Preliminary 7 KGP 560 Pilot's Gui

cussed later in this guide.

Terrain data is supplied from the same proprietary database used b

other Honeywell EGPWS products, and is divided into three region

worldwide. (See pictures below). The terrain data is divided into gr

patterns of various sizes, from areas about 1/4 nm square resolution 

areas of about 5 nm square. This allows a large area of data to b

stored in the unit, and allows high-resolution data near airports, wi

lower resolution data where terrain is not a factor and airports a

sparse.

Regional Database: Americas (shaded areas)
Rev 1 Preliminary 8 KGP 560 Pilot's Guide 

Regional Database: Atlantic (shaded areas)

Regional Database: Pacific (shaded areas)

Data for known obstacles such as towers, buildings, antennas, etc. is

contained on the same data card as the terrain and airport data.

Presently, there are some 70,000-plus obstacles in the database, but

they are all in the area of North America. As more reliable information

becomes available, Honeywell will expand the capability to provide

alerting and warning for obstacles in other areas of the world. 

Obstacles in the database are those known obstacles more than 100

feet AGL, so obstacles of lower height will not produce GA-EGPWS

“Obstacle” alerts or warnings. However, terrain elevations are “rounded”

up to the next 100 feet, so alerting and warning protection is generally

available for known obstacles that are less than 100 feet AGL.
Rev 1 Preliminary 9 KGP 560 Pilot's Gui

TERRAIN INHIBIT SWITCH

The GA-EGPWS requires the installation of a "Terrain Inhibit" switch a

part of the system installation. When engaged by the pilot, this switc

will inhibit all visual and aural alerts and warnings associated with th

GA-EGPWS. Also, an external annunciator lamp is illuminated and 

message will be displayed indicating “Warnings Inhibited”. The terra

display, if installed, remains operational.

The purpose of the "Terrain Inhibit" switch is to allow aircraft to opera

without nuisance or unwanted warnings at airports that are not in th

system database. Examples might be private airports or those with ru

ways shorter than 2000 feet. Additionally, there may be some "VFR

only" airports where unique terrain features are in close proximity to th

runway, and the "Terrain Inhibit" may be used when operating in goo

VFR conditions. The "Terrain Inhibit" switch should be NOT engaged f

normal operations.

TERRAIN AWARENESS DISPLAY

The KGP 560 GA-EGPWS can be interfaced to numerous types 

cockpit displays. Graphical display of GA-EGPWS terrain and obstac

data is the most important enhancement to Situational Awareness. Th

is especially true for lower performance aircraft. In addition to showin

terrain ahead of the aircraft, (depending on configuration settings an

display types) the system shows MSL altitude, Magnetic Track, Range 

NM, and the elevations of the highest and lowest terrain features show

on the display. The color and intensity of the terrain displayed instant

alerts the pilot to areas of dangerous terrain and conversely to areas 

less precipitous terrain. (Refer to Appendix B in the KGP 560 GA

EGPWS System Installation manual for a list of supported displays

Range of the Terrain Display is selectable by the pilot from 5 nm to 32

nm, again depending upon the display type installed in the aircraft.
Rev 1 Preliminary 10 KGP 560 Pilot's Guide 
Rev 1 Preliminary 11 KGP 560 Pilot's Gui

The system will adjust colors on the Terrain Display automatically as th

aircraft altitude changes. The Terrain Display also transitions betwee

the lower altitude “relative” display and the higher altitude “peaks” displa

automatically, so no pilot action is required for system operation.

Depending upon display type, the Terrain Display can show a “rose” 

full circle pattern around the aircraft with Magnetic North at the top whe

the aircraft is on the ground. This is called a “North Up” display. Th

pilot can readily see terrain features in all directions around the aircra

for superior Situational Awareness with respect to terrain and know
Rev 1 Preliminary 12 KGP 560 Pilot's Guide 

craft Magnetic Track at the top center of the display screen throughout

the flight. 

The most important function of the system is to provide the pilot with

easily interpreted information about terrain/obstacles relative to the aircraft, and thus increase the pilot’s Situational Awareness. In brief, when

using the Terrain Display during flight, the normal presentation of green,

yellow and red colors indicate:

The following chart outlines all the various colors used by the GAEGPWS Terrain Display and their functions in providing Situational

Awareness to the pilot. Some display types may not support all colors

listed, or may display colors in slightly different densities than those

listed, but the system is designed to present the most appropriate

Terrain Display capable on the various display types which are usable by

the system.
GA-EGPWS Terrain Display at 12,000 feet approaching Aspen, CO

GA-EGPWS “Peaks” Terrain Display at 12,000 feet near Seattle, W

Rev 1 Preliminary 13 KGP 560 Pilot's Gui
Rev 1 Preliminary 14 KGP 560 Pilot's Guide 

g gp

functionality.

When the “Look-Ahead” function detects a terrain or obstacle threat

approximately one minute ahead of the aircraft, the voice alert “Caution

Terrain, Caution Terrain” (or “Caution Obstacle, Caution Obstacle”) is

given, and a bright, solid yellow “threat area” is shown on the Terrain

Display. Should the aircraft flight path continue toward the threat area,

the alert message will repeat approximately every 7 seconds.

If the aircraft flight path approaches to within approximately 30 seconds

of a threat area, the voice message “Terrain Ahead” (or “Obstacle

Ahead”) or optionally “Terrain Terrain, Pull Up” (or “Obstacle-Obstacle,

Pull Up”) will be given continuously and the threat area on the Terrain

Display will be shown in a bright, solid red color.

In either case, when the pilot reacts and changes the aircraft flight path

to one that will safely avoid the detected threat area, the voice alerts will

cease and the threat area(s) shown on the Terrain Display will be

removed. 

RUNWAY FIELD CLEARANCE FLOOR (RFCF)

The KGP 560 GA-EGPWS provides additional alerting protection for situations where aircraft descend to an altitude that is too low considering

the aircraft’s distance from a known runway. This is called the Runway

Field Clearance Floor (RFCF).
When the pilot reacts to the alert and climbs back above the RFCF f

the current distance from the known runway, the annunciator lamp w

extinguish and the voice alerts will cease.

The following figure is a graphical representation of the Runway Fie

Clearance Floor in both the “TSO” and “optional alerting and warnin

parameters outside the TSO” configurations.

Runway Field Clearance Floor (RFCF)

EXCESSIVE RATE OF DESCENT ALERTING AND

WARNING

The KGP 560 GA-EGPWS uses both GPS Vertical Velocity and pre

sure altitude to compute vertical velocity information when the aircra

does not provide specific air data for this purpose. In either case, whe

the aircraft is descending toward terrain at a high rate for its relative al

tude above terrain, the system will provide alerting and warning to th

pilot. This function is always active.

Rev 1 Preliminary 15 KGP 560 Pilot's Gui
Rev 1 Preliminary 16 KGP 560 Pilot's Guide 

Excessive Descent Rate

Initially, the voice alert “Sink Rate” will be heard, and the yellow caution

alert annunciator lamp will illuminate. If the aircraft continues in the high

rate of descent, the “Sink Rate-Sink Rate” voice alert will be repeated at

an increasing frequency.

Should the aircraft penetrate the warning boundary, the voice alert “Pull

Up” will be heard continuously and the red warning annunciator lamp will

illuminate.

In both cases, as the pilot reacts to decrease the high rate of descent

and the aircraft flight path exits the alerting/warning envelope, the annunciator lamp will extinguish and the voice alerts will cease.

Sometimes, the alerting and warning functionality for excessive rate of

descent may be overridden by the terrain “Look-Ahead” functionality.

This is normal as the “Look-Ahead” function has a higher priority in the

system alerting/warning logic. (See the Alerting/Warning Priority chart

later in this guide.)
Rev 1 Preliminary 17 KGP 560 Pilot's Gui

p

after take-off, the system will illuminate the yellow caution annunciat

lamp and provide “Don’t Sink-Don’t Sink” voice alerts to the pilot. Th

voice alerts will be repeated with increasing frequency. 

The following graph shows this alerting envelope:

Descent After Takeoff

As the pilot adjusts the flight path of the aircraft and a positive rate 

climb is re-established, the voice alert “Don’t Sink” will cease and th

yellow caution annunciator lamp will extinguish.

NOTE: It is important for the pilot not to over-react to this situation. Wh

it is important to react quickly and positively to re-establish a positive ra

of climb, the pilot should remember that in the take-off / initial climb se

ment, the margin above stall speed for many aircraft is fairly small, an

thus must be respected.
Rev 1 Preliminary 18 KGP 560 Pilot's Guide 

p

or are due to high or low-pressure systems will not normally activate the

altitude monitor. Large errors due to faulty equipment or malfunctioning

pitot-static systems will normally be detected by the monitor.

When an abnormal altitude discrepancy is detected by the system, there

will be a single voice callout of “Check Altitude”. There will also be the

text message Chk Alt shown on the Terrain Display as long as the condition that triggered the alert persists.

The pilot should check all aircraft altimeters to ensure that the correct

altimeter setting is set, that altimeter systems cross-check and that the

pilot’s altimeter is not stuck and indicating an erroneous altitude.

ALTITUDE CALLOUT

The KGP 560 GA-EGPWS provides an altitude callout for the pilot, to

indicate a position approximately 500 feet above the elevation of the

runway being approached. When the aircraft is within 5 nm of a known

runway, the altitude callout function is active, and is then triggered when

Geometric Altitude shows the aircraft 500 feet above the known runway

elevation (from the system database). Example: “Five-Hundred Above”

for installations using the optional alerting and warning parameters outside the TSO and “Five-Hundred” for TSO installations.

This callout is not accompanied by any annunciator lamp indications and

will occur only once per approach. The Altitude Callout is reset when the

aircraft climbs more than 700 feet above the runway elevation. 
Rev 1 Preliminary 19 KGP 560 Pilot's Gui

NOTE: Because the system requires GPS information to operate, it ma

be several minutes after power-up before the aircraft GPS system su

plies accurate information to the KGP 560. If the internal GPS card 

used to supply position information, it may take additional time for sate

lite acquisition depending upon the frequency of use of the system. Th

internal GPS card requires a current almanac to locate GPS satelli

positions. This almanac can take several minutes to load. When a

accurate GPS position is acquired and the rest of the GA-EGPW

system is available, the “NOT AVAILABLE” lamp will extinguish. 

To perform a normal KGP 560 GA-EGPWS Self-Test:

1. Press the Self-Test switch.

2. Observe that the amber “Not Available” and red “Warning” annunc

ator lamps associated with the system illuminate.

3. Observe that the voice callout “EGPWS SYSTEM, OK” is heard.

4. Observe that the red “Warning” annunciator lamp extinguishes, an

the amber “Caution” annunciator lamp illuminates.

5. Observe that the GA-EGPWS Terrain Display shows the Te

Pattern.

6. After 6 to 8 seconds, observe that the Terrain Display Test Pattern 

removed.

7. Observe that the amber “Caution” and amber “Not Available” annunc

ator lamps associated with the system extinguish.

This sequence indicates a proper and successful Level One Self-Test. 

Pressing the Self-Test switch as the Level One Self-Test is complete

will initiate Level Two of the internal test capability. Level Two provide

information about any faults the system may be detecting. Normally, th

will not be necessary. If a normal Self-Test is unsuccessful, a Level Tw

test is automatically initiated by the system.
Rev 1 Preliminary 20 KGP 560 Pilot's Guide 

KGP 560 GA-EGPWS Self-Test: Level 1 Messages

KGP 560 GA-EGPWS Self-Test: Level 2 Messages

NOTE: This Level 2 list contains the most commonly heard messages.

Other messages may be given, depending upon installation / equipment

types. Messages may be heard in various combinations.
per second to the aircraft’s BEST ANGLE of CLIMB attitude an

speed. (RESPECT AIRCRAFT STALL CONDITION).

2. Apply Maximum Power.

3. Continue maximum climb until all visual and aural warnings cease.

4. Advise Air Traffic Control as necessary.

If in Visual conditions during the day:

1. Evaluate aircraft flight path with respect to terrain.

2. Take corrective action as necessary to recover safe terrain clearance

3. Advise Air Traffic Control as necessary.

RECOMMENDED PROCEDURES FOR GA-EGPWS

ALERTS IN FLIGHT

Rev 1 Preliminary 21 KGP 560 Pilot's Gui
Rev 1 Preliminary 22 KGP 560 Pilot's Guide 

Intentionally left blank
Rev 1 Preliminary 23 KGP 560 Pilot's Gui

alert or warning at the same time, the higher priority message will b

heard until that condition is resolved. If the lower priority condition is s

in effect at that time, the lower priority voice message will be heard.

The following tables show the voice output that is activated for eac

callout, alert and warning condition. The messages are arranged fro

highest priority at the top, to lowest priority at the bottom of the tables.

Table 1: Standard Voice Callout Menu

Note 1: These are the only voices that can interrupt.

Note 2: The preface voices will always be given prior to the warnin

voice.

Note 3: Voice message is continuous.

Note 4: Voice message will repeat every 7 seconds.

Note 5: This callout is optional.
Rev 1 Preliminary 24 KGP 560 Pilot's Guide 

Table 2: Alternate Voice Callout Menu

Note 1: These are the only voices that can interrupt.

Note 2: The preface voices will always be given prior to the warning

voice.

Note 3: Voice message is continuous.

Note 4: Voice message will repeat every 7 seconds.

Note 5: This callout is optional.

GA-EGPWS COCKPIT LAMPS & SWITCHES

A representative sample of a possible annunciator and switch installation

is pictured below. Other configurations are at the discretion of the

installer and operational requirements of the aircraft. 

Typical Annunciator

KGP 560 SYSTEM LIMITATIONS

* The GA-EGPWS is a Situational Awareness tool, and an alerting and

warning device. It is not to be used for navigation of the aircraft.

* The KGP 560 must have an operating source of GPS information, with

enough satellites in view to provide GPS data within the accuracy

requirements of the system.

EGPWS

NOT

AVAIL

TEST

CAUT ALERT INHIBIT

WARN

ı
Rev 1 Preliminary 25 KGP 560 Pilot's Gui

Field Clearance Floor (RFCF) functions are gradually desensitize

as an aircraft nears a known runway. Aircraft operating in close pro

imity to known runways may experience very short or no advanc

warnings with respect to terrain or obstacles in this area. (See section

on GA-EPWS “Look-Ahead” and RFCF). 

KGP 560 CONTINUED AIRWORTHINESS AND

DATABASE UPDATE PROCEDURES

Normal maintenance activities performed on the KGP 560 should follo

standard industry maintenance practices. System maintenance pra

tices may included updating the Terrain, Obstacle and Runway dat

base. Other maintenance practices, such as re-programming th

Configuration Module, are addressed in the KGP 560 System Installatio

Manual. Database load procedures and database update cards a

exclusively supplied by Bendix/King Avionics.

The KGP 560 database is contained in a CompactFlash card installed 

the top of each unit. It is up the KGP 560 customer to determine if a sp

cific database is applicable to their operation. Honeywell estimates th

the KGP 560 customer will update their database approximately onc

per year. Information regarding new releases and the content details 

the database may be obtained via the internet at the following site

www.bendixking.com and www.egpws.com.

Please see the following section, KGP 560 Product Support, for conta

information to order database updates.

If possible, clearance to the top of the KGP 560 should be provided 

facilitate removal and installation of the terrain database CompactFlas

card. The terrain data base card is removed and installed with pow

NOT APPLIED to the system. The KGP 560 computer may be remove

from the aircraft to extract and install data base cards if the mountin

location does not provide enough clearance.
Rev 1 Preliminary 26 KGP 560 Pilot's Guide 

te aos ote database cad ad G560 copute

If possible, mount the KGP 560 computer such that the above can be

accomplished without requiring disassembly of the aircraft or removal of

the KGP 560 computer.

KGP 560 PRODUCT SUPPORT

Customer Support:

1-800-712-0400

To order database updates, contact Navigation Services at the following

numbers:

1-800-247-0230 if calling from within the United States or Canada

(913) 712-3145 if calling from outside the United States or Canada

(913) 712-3904 FAX

e-mail: nav.database@honeywell.com

Database updates may also be ordered on-line by visiting

www.gpsdatabase.com
Honeywell International Inc.

One Technology Center 

23500 West 105th Street

Olathe, KS 66061

Telephone (913) 782-0400 

FAX 913-712-1302

©2000 Honeywell International Inc.

006-18254-0000 Printed in U.S.A.

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