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INSTALLATION MANUAL
B
KLN 94
GPS NAVIGATION SYSTEM
MANUAL NUMBER 006-10599-0004
REVISION 4 JANUARY, 2003
WARNING
Prior to export of this document, review for export license requirement is needed.
COPYRIGHT NOTICE
2000, 2003 Honeywell International, Inc.
Reproduction of this publication or any portion thereof by any means without the expressed written permission of Honeywell is prohibited. For further information contact the Manager of Technical Publications, Honeywell, Olathe, KS 66061. Telephone: (913) 782-0400
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KLN 94
MANUAL
REVISION
PART NUMBER
REVISION INSTRUCTIONS AND HISTORY
KLN 94 GPS NAVIGATION SYSTEM INSTALLATION
2
006-10599-0002
Where R & R appears in the action column, remove the page now in the installation manual and replace it with the enclosed page; otherwise, ADD or DESTROY pages as listed.
Retain these instructions in the front of the installation manual as a Record of Revisions.
______________________________________________________________________
PAGE ACTION REASON FOR CHANGE
______________________________________________________________________
KLN 94 IM Covers R&R
Revision History ADD
1-1 thru 1-6
1-9 thru 1-10
R&R
R&R
2-5 thru 2-12
2-23 thru 2-82
R&R
R&R
Updated
Updated
Updated
Corrected
Updated
Updated
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KLN 94
MANUAL
REVISION
PART NUMBER
REVISION INSTRUCTIONS AND HISTORY
KLN 94 GPS NAVIGATION SYSTEM INSTALLATION
3
006-10599-0003
Where R & R appears in the action column, remove the page now in the installation manual and replace it with the enclosed page; otherwise, ADD or DESTROY pages as listed.
Retain these instructions in the front of the installation manual as a Record of Revisions.
______________________________________________________________________
PAGE ACTION REASON FOR CHANGE
______________________________________________________________________
KLN 94 IM Covers R&R
Revision History R&R
1-5 thru 1-6 R&R
Updated
Updated
Corrected
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KLN 94
MANUAL
REVISION
PART NUMBER
REVISION INSTRUCTIONS AND HISTORY
KLN 94 GPS NAVIGATION SYSTEM INSTALLATION
4
006-10599-0004
Where R & R appears in the action column, remove the page now in the installation manual and replace it with the enclosed page; otherwise, ADD or DESTROY pages as listed.
Retain these instructions in the front of the installation manual as a Record of Revisions.
______________________________________________________________________
PAGE ACTION REASON FOR CHANGE
______________________________________________________________________
KLN 94 IM Covers R&R
Revision History R&R
1-5 thru 1-6
2-78 thru 2-79
R&R
R&R
Updated
Updated
Revised
Revised
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KLN 94
THIS PAGE IS RESERVED
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KLN 94
SECTION I
GENERAL INFORMATION
Paragraph Page
............................................................................................... 1-1
................................................................... 1-1
1.3.4 KA 198 Comm Filter Technical Characteristics
................................................. 1-5
1.4 UNITS AND ACCESSORIES SUPPLIED ......................................................... 1-6
....................................................................................... 1-6
....................................................................................... 1-6
1.5 ACCESSORIES REQUIRED, BUT NOT SUPPLIED ........................................ 1-8
........................................................................................... 1-9
1.5.3 CDI Indicator With “MSG” and “WPT” Annunciators ......................................... 1-9
............................................................................. 1-9
........................................................................................ 1-13
...................................................................................... 1-13
............................................................................. 1-13
1.8 RECOMMENDATIONS FOR IFR APPROVAL .................................................. 1-13
....................................................................................... 1-13
1.8.2 Aircraft Installation Requirements
..................................................................... 1-13
1.8.3 Approved Airplane Flight Manual Supplement
.................................................. 1-14
1.9 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS ................................. 1-14
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KLN 94
SECTION II
INSTALLATION
Paragraph Page
2.2 UNPACKING AND INSPECTING EQUIPMENT
............................................... 2-1
2.3.1 Avionics Cooling Requirements For Panel Mounted Equip . .............................. 2-1
2.3.2 KLN 94 Mechanical Installation
......................................................................... 2-2
2.3.4 Antenna Installation Considerations
.................................................................. 2-2
2.4 POST INSTALLATION CHECK OUT INFORMATION ....................................... 2-67
........................................................................................... 2-67
SECTION III
OPERATION
Paragraph Page
............................................................................... 3-1
APPENDIXES
..................................................................................... B-1
APPENDIX C - SUPPLEMENTAL TYPE CERTIFICATE ..................................................... C-1
APPENDIX D - DIRECT REPLACEMENT OF A KLN-89B WITH A KLN-94
....................... D-1
APPENDIX E - ENVIRONMENTAL QUALIFICATION FORMS
............................................ E-1
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KLN 94
LIST OF ILLUSTRATIONS
Figure Page
2-1 KLN 94 P941 CONNECTOR PIN FUNCTIONS ................................................ 2-10
2-2 KLN 94 P942 CONNECTOR PIN FUNCTIONS ................................................ 2-11
2-3 KLN 94 P943 CONNECTOR PIN FUNCTIONS
................................................ 2-13
2-4 KLN 94 CRIMPING AND INSERTION/EXTRACTION TOOLS
......................... 2-14
.............................................................................. 2-17
2-7 KA 91 INSTALLATION DRAWING
..................................................................... 2-19
2-8 KA 91 BACKPLATE OUTLINE DRAWING ........................................................ 2-21
2-10 KA 92 INSTALLATION DRAWING
..................................................................... 2-27
2-11 KA 92 BACKPLATE OUTLINE DRAWING ........................................................ 2-29
2-12 KA 91/92 TNC ANTENNA COAX/CONNECTOR ASSEMBLY (0-40FT) ........... 2-31
2-13 KA 91/92 BMA ANTENNA COAX/CONNECTOR ASSEMBLY
......................... 2-33
2-14 KA 91/92 TNC/BMA ANTENNA COAX/CONNECTOR ASSEMBLY (0-80FT) .. 2-35
2-15 KA 33 P/N 071-4037-00/01 FINAL ASSEMBLY ................................................ 2-37
2-16 KA 33 P/N 071-4037-00/01 OUTLINE AND MOUNTING DRAWING ............... 2-39
2-17 CUTLER-HAMMER SWITCH/ANNUN. MOUNTING DRAWING
...................... 2-41
2-18 CUTLER-HAMMER SWITCH/ANNUN. INTERNAL SCHEMATIC
.................... 2-43
2-19 KLN 94 SERIAL RECEIVERS & TRANSMITTERS INTERCONNECT DWG . .. 2-47
2-20 KLN 94 ALTITUDE AND RMI / OBI INTERCONNECT DRAWING
.................... 2-49
2-21 KLN 94 DEVIATION AND FLAGS INTERCONNECT DRAWING ..................... 2-51
2-22 KLN 94 OBS RESOLVER INTERCONNECT DRAWING
.................................. 2-53
2-23 KLN 94 INTERCONNECT DRAWING .............................................................. 2-55
2-24 KLN 94 FCS & EXTERNAL ANNUNCIATOR INTERCONNECT DRAWING .... 2-57
2-25 KLN 94 BACKLIGHTING & ALT. ALERTING INTERCONNECT DRAWING
..... 2-59
2-26 KLN 94 PC LOADER AND ANTENNA INTERCONNECT DRAWIN G .............. 2-61
2-27 KLN 94 DATA LOADER/PC INTERFACE
........................................................... 2-63
2-28 KLN 94 QUICKTUNE INTERCONNECT DRAWING
........................................ 2-65
LIST OF TABLES
Table Page
.....................................................................2-81
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KLN 94
SECTION I
GENERAL INFORMATION
1.1 INTRODUCTION
This manual contains information relative to the physical, mechanical, and electrical characteristics of the BENDIX/KING KLN 94 Global Positioning System (GPS) Receiver. General installation procedures are also included.
1.2 EQUIPMENT DESCRIPTION
The KLN 94 is a panel mounted, long range, GPS based airborne navigation system with a database. The KLN 94 also provides VFR, IFR enroute, and IFR non-precision approach functions. The primary purpose of the equipment is to provide the pilot with present position information and to display guidance information with respect to a flight plan defined by the pilot.
Flight plan information is entered by the pilot via various knobs and buttons on the front panel.
The unit can use its present position information to determine crosstrack error, distance to waypoint, ground speed, track angle, time to waypoint, bearing to waypoint, and advisory VNAV guidance. The database of the KLN 94 contains information concerning airports, VORs, NDBs, intersections, DP/STARs, outer markers, roads, rivers, railroads, lakes, etc., throughout the database’s coverage area. Waypoints are stored in the database by their ICAO identifiers. The
ICAO identifiers are in most cases taken directly from Jeppesen Sanderson or government aeronautical charts. The KLN 94 has instrument approach capabilities.
The information stored in the database eventually becomes out of date; therefore, to provide a means of updating the information, the database is housed in a data card which plugs into the front of the KLN 94. It is designed so that the user may easily remove the old database and install a current database. A secondary method of updating the database is by loading the information via an IBM compatible laptop computer. For more information on availability and cost of updating the database of the KLN 94, refer to the KLN 94 Pilot’s Guide P/N 006-18207-0000.
1.3 TECHNICAL CHARACTERISTICS
1.3.1 KLN 94 TECHNICAL CHARACTERISTICS
TSO/JTSO Compliance: TSO-C129a, JTSO-C129a - See
for environmental qualification.
Physical Dimensions: Refer to KLN 94 installation drawing, Figure
Mounting: Panel mounted with Honeywell supplied mounting rack
Cooling Requirements:
Temperature Range:
Altitude Range:
4 CFM (cubic feet per minute) provided by blower motor such as KA33 or equivalent.
-20°C to +55°C
Up to 55,000 Feet
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KLN 94
Power Inputs: 11 to 33 VDC at 3.0 A Max. (-20°C to +55°C)
13.75 VDC @ 2.5 A Nominal
27.5 VDC @ 1.25 A Nominal
Panel Lighting Current Requirements:
14 VDC Lighting:
28 VDC Lighting:
220 mA Maximum
110 mA Maximum
SIGNAL INPUTS
GPS DISPLAYED:
OPEN:
GND
GPS displayed (when an indicator resolver is connected to the OBS resolver inputs)
GPS not displayed (when an indicator resolver is not connected)
TAKE HOME:
OPEN: Normal Operation
Take Home Mode GND:
SPARE IN 0:
SPARE IN 1:
SPARE IN 2:
SPARE IN 3:
TEST:
These are reserved pins for future use.
OPEN:
GND:
APPROACH ARM IN:
DATA LOADER RS 232 IN:
SPARE RS 232 IN:
GRAY CODE INPUTS:
(A1, A2, A4, B1, B2, B4, C1, C2, C4, D4)
OBS SIN:
Normal Operation
Test Mode
This pin is normally open with a momentary low while the panel button is pressed.
This RS 232 input is designated to communicate with devices, ie. air data and fuel
flow sensors via RS 232 format. (refer to RS
232 Format Definitions Appendix )
This RS 232 input is reserved for future use.
Gray Code Altitude Signals. (0 to 28 VDC)
These inputs are diode isolated inside the KLN
94.
OBS resolver sine. Nominal input impedance is
33.8 K ohms (AC) and 100 K ohms (DC)
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KLN 94
OBS COS: OBS resolver cosine. Nominal input impedance is 33.8 K ohms (AC) and 100 K ohms (DC).
A/C POWER MONITOR: This pin senses the aircraft power bus voltage.
This high impedance input operates from 0 to
33 V with accuracy of 0.1 V.
CONFIGURATION MODULE: Refer to
OBI SYNC, OBI CLOCK, & OBI DATA:
SIGNAL OUTPUTS:
Honeywell Serial Data containing bearing to the active waypoint.
DATA LOADER/QUICKTUNETM RS 232 OUT: The Data Loader/QuickTune RS 232 output is designed to communicate with an IBM compatible personal computer.
GENERAL RS 232 OUT: The RS 232 output is designed to interface with certain ARNAV ELTs and certain moving map displays, and Shadin fuel flow systems (refer to
RS 232 Format Definitions Appendix ).
GPS SENSOR RS 232 OUT:
WAYPOINT ANNUNCIATE:
MESSAGE ANNUNCIATE:
APPROACH ACTIVE ANNUNCIATE:
APPROACH ARM ANNUNCIATE:
SPARE ANNUNCIATE 1:
SPARE ANNUNCIATE 2:
ROLL STEERING VALID
N/A on -0101
ROLL STEERING HI
N/A on -0101
The GPS Sensor RS 232 output is a buffered connection to the GPS sensor (Xpress) transmitter connection to the host processor. It is designed to interface with a EGPWS, and for testing.
OPEN = Inactive
LOW = Active (Output can sink up to 250 mA)
OPEN = Inactive
LOW = Active (Output can sink up to 250 mA)
OPEN = Inactive
LOW = Active (Output can sink up to 250 mA)
OPEN = Inactive
LOW = Active (Output can sink up to 250 mA)
Spare annunciators are reserved for future use.
Spare annunciators are reserved for future use.
Valid =
≥
18 V in 28 VDC installations;
≥
10 V in
14 VDC installations. Invalid =
≤
3.5 V in all installations while sinking 1 mA. Output can source at least 250 mA.
Output Range:
550mV per degree of Bank.
2V per degree per second of
Turn Rate.
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ROLL STEERING LO
FCS LOC ENG:
LATERAL DEV FLAG +:
LATERAL DEV FLAG -:
VERTICAL DEV FLAG +:
VERTICAL DEV FLAG -:
LATERAL SUPERFLAG:
VERTICAL SUPERFLAG:
LATERAL DEV +L:
LATERAL DEV +R-:
VERTICAL DEV +UP:
VERTICAL DEV +DOWN:
OBS OUT:
+TO / +FROM Flag Outputs:
To Indication:
From Indication:
ALTITUDE ALERT ANNUNCIATE:
ALT ALERT AUDIO:
KLN 94
This is an output. It is always grounded
OPEN = Inactive
LOW = Active (Output can sink up to 250 mA)
Valid: 350 to 900 mV (high)
Flag in view:
≤
50mV (low)
Output is capable of driving five 1k ohm parallel loads.
Reserved for future use.
Valid =
≥
18 V in 28 VDC installations;
≥
10 V in
14 VDC installations. Invalid =
≤
3.5 V in all installations while sinking 1 mA. Output can source at least 250 mA.
Reserved for future use.
These outputs are differential pairs (+L and
+UP are positive). Output range is
±
300 mV and is capable of driving five 1k ohm parallel loads.
Reserved for future use.
Used to excite the OBS resolver rotor. Nominal output frequency = 450 Hz. Nominal unloaded peak amplitude = 6 V. Output drive capability =
40 mA.
+100 to +900 mV on +TO with respect to
+FROM when desired course is within
±
85
°
of the bearing to the active waypoint.
-100 to -900 mV on +TO with respect to
+FROM when desired course is within 180
±
85
°
with respect to the bearing of the active waypoint. Outputs are capable of driving up to five 200 ohm parallel loads.
HIGH = Inactive
LOW = Active (can sink up to 250 mA)
This output is active whenever ALTITUDE
ALERT ANNUNCIATE is active, Signal is 1Khz,
3.5 Vrms max into 500 ohms. Refer to
for the procedure to adjust the volume.
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1.3.2 KA 91 ANTENNA TECHNICAL CHARACTERISTICS
KLN 94
TSO Compliance: TSO-C129 - See Appendix C
for environmental qualification.
Physical Dimensions: Refer to KA 91 installation drawing,
Airspeed Rating:
Output Impedance:
DC Voltage:
DC Current:
600 Kts. TAS
50 Ohms (nominal)
5 Volts
±
0.5 Volt
50 mA (maximum)
1.3.3 KA 92 ANTENNA TECHNICAL CHARACTERISTICS
TSO Compliance: TSO-C129 - See Appendix C
for environmental qualification.
Physical Dimensions: Refer to KA 92 installation drawing, Figure
Airspeed Rating: 600 Kts. TAS
Output Impedance:
DC Voltage:
DC Current:
50 Ohms (nominal)
5 Volts
±
0.5 Volt
50 mA (maximum)
1.3.4 KA 198 COMM FILTER TECHNICAL CHARACTERISTICS (P/N 071-01565-0000)
Center Notch Frequency:
Attenuation at 1575.42
±
1.5 MHz
Insertion Loss from 118.00 to 137.00 MHz
Impedance from 118.00 to 137.00 MHz
VSWR from 118.00 to 137.00 MHz
1575.42 MHz
35 dB (minimum)
.3dB (maximum)
50 ohms
1.5:1
NOTE
The conditions and tests performed on this article are minimum performance standards. It is the responsibility of those desiring to install this article either on or within a specific type or class of aircraft to determine that the aircraft installation conditions are within these performance standards. The article may be installed only if further evaluation by the applicant documents an acceptable installation and is approved by the Administrator.
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1.4 UNITS AND ACCESSORIES SUPPLIED
1.4.1 KLN 94 GPS RECEIVER
The KLN 94 is available in the following versions
PART NUMBER
069-01034-0101
069-01034-0102
14V / 28V
LAMPS
X
X
BLACK
BEZEL
X
X
KLN 94
CERTIFICATION
VFR / IFR (BRNAV)
VFR / IFR (BRNAV and
DC Roll Steering)
VERSION
KLN 94
KLN 94
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 89/89B/94 INSTALLATION KIT
The KLN 89/89B/94 Installation Kit (P/N 050-03321-0000) is available with crimp connectors only.
A list of the required crimp tools and insertion/ extraction tools can be found in Section 2 of this manual. The kit and a complete list of the items contained in the kit is given below.
P/N DESCRIPTION UM -0000
VENDOR
NAME & P/N
030-01173-0000 CONN SUB-D HSG 25S (FEMALE PINS) EA
030-01175-0000 CONN SUB-D HGS 37S (FEMALE PINS) EA
073-01030-0502 CONNECTOR MOUNTING BRACKET
076-03019-0002 SHOULDER SCREW 4-40 W/FIN
EA
RF
089-05903-0004 SCR PHP 4-40 x 1/4
030-01157-0011 SOCKET CRMP 20G
089-05907-0004 SCR PHP 6-32 x 1/4
089-02353-0001 NUT CLIP 6-32
RF
EA
EA
EA
089-05903-0007 SCR PHP 4-40 x 7/16
089-06012-0006 SCR PHP 6-32 x 3/8
090-00019-0007 RING RTNR .438
030-00101-0002 PANEL MOUNT PLUG
187-01352-0000 GASKET
EA
EA
EA
EA
EA
4
6
4
62
1
4
1
1
1
1
2
6
1
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P/N DESCRIPTION
047-05959-0002 STRAIN RELIEF W/H
047-05960-0001 STRAIN RELIEF W/F
200-08334-0000 EXT EEPROM BD
033-00230-0000 TELEPHONE JACK, 4 CONDUCTOR
057-05621-0000 DECAL DATA LOADER
057-05628-0000 GPS DISCLAIMER
089-08252-0030 WASHER
1.4.4 KA 91/92 INSTALLATION KIT
The KA 91 Installation Kit (P/N 050-03195-0000), including its contents, is shown below.
KLN 94
UM -0000
VENDOR
NAME & P/N
EA
EA
EA
EA
EA
EA
EA
1
1
1
1
1
2
2
P/N DESCRIPTION
050-03195-0000 KA 91 INSTALL
030-00134-0001 RIGHT ANGLE CONN COAX
047-10130-0002 BACKPLATE, ANTENNA
089-06908-0012 SCREW, AIRCRAFT
187-01807-0000 KA 91 GASKET
EA
EA
EA
EA
UM -0000 VENDOR NAME & P/N
X
1
1
4
1
TED Mfg. 5-30-102
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.
P/N DESCRIPTION
050-03318-0000 KA 92 INSTALL
030-00134-0001 RIGHT ANGLE CONN COAX
047-10735-0002 BACKPLATE, ANTENNA
089-05909-0012 SCREW, PHP 8-32x3/4
187-01831-0000 KA 92 GASKET
EA
EA
EA
EA
UM -0000 VENDOR NAME & P/N
X
1
1
4
1
TED Mfg. 5-30-102
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KLN 94
1.4.5 DATABASE
The KLN 94 is supplied with two different kinds of databases:
1) NAVIGATION DATABASE
This is required to be current for IFR non-precision approaches. Our navigation database is available on a twenty-eight day cycle.
2) CARTOGRAPHY DATABASE
This includes features such as roads, rivers, railroads, etc. and is provided for reference only.
Cartography database updates are available on a less frequent basis than the navigation database updates. Updating the cartography database will require a cartridge exchange.
The KLN 94 navigation database cartridge and diskettes are available for three separate geographic areas. Database cartridges are available only for users in the United States Of
America and Canada. Diskettes are available to all users. Also database files can be dowloaded via the Internet at the following address: http://www.gpsdatabase.com
KLN 94 DATABASE
Atlantic International Database
Pacific International Database
Americas Database
CARTRIDGE
(navigation and cartography)
071-00163-0101
071-00163-0102
071-00163-0103
DISKETTE
(navigation only)
223-111YY-00CC
223-112YY-00CC
223-113YY-00CC
NOTE
YY represents the year of the database cycle.
CC represents the cycle of the database.
1.5 ACCESSORIES REQUIRED, BUT NOT SUPPLIED
1.5.1 Forced Air Cooling
A KA 33 Cooling Kit or equivalent is required for the KLN 94 installation.
DESCRIPTIOIN PART NUMBER
KA 33 Blower for 14 VDC installations 071-4037-00
KA 33 Blower for 28 VDC installations 071-4037-01
KA 33 Blower Installation Kit 050-02204-0000
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1.5.2 Indicators and HSIs
KLN 94
DESCRIPTION
KI 202 or KI 206 (P/N 066-3034-XX)
Navigation Indicator and Installation Kit (050-01524-0000)
KI 208A or KI 209A (P/N 066-3056-XX)
Navigation Indicator and Installation Kit (050-01524-0000)
KPI 553A (P/N 066-3045-XX)
Horizontal Situation Indicator and Installation Kit (050-01791-XXXX)
KPI 553B (P/N 066-3069-XX)
Horizontal Situation Indicator and Installation Kit (050-02167-XXXX)
KI 525A (P/N 066-3046-XX)
Horizontal Situation Indicator and Installation Kit (050-01334-XXXX)
NOTE
The KPI 553A/553B DME distance display is not compatible with the KLN 94.
The KPI 553A models that do not have an OBS knob on the indicator were special for the KNR 665 system and are not compatible with the GPSs.
1.5.3 CDI Indicator with "MSG" and "WPT" Annunciators
Some stand alone CDI indicators are available with WPT/MSG annunciators built in. One commonly used is the Model MD40-39, manufactured by Midcontinent Instrument, telephone
(316) 683-5619. These devices have no resolver interface. The use of an OBS resolver will reduce pilot workload.
1.6 OPTIONAL ACCESSORIES
1.6.1 PC Interface Kit
The navigation database may be loaded directly from the PC to the KLN 94 installed in an aircraft
by means of the bezel jack (refer to Section 2.4.4.8
for details). To utilize the bezel jack for loading of the database, order kit part number 050-03612-0000.
If the installation was previously a KLN 89B installation and utilized an external jack, order interface kit P/N 050-03213-0000 in order to load the navigation database from a personal computer. The kit contains a ready to use cable which connects between the aircraft connector and the computer’s 9 pin or 25 pin serial connector. The kit is necessary whether the user is loading from a Honeywell diskette or a database obtained via the Internet.
The cartography database is contained in the Sandisk cartridge. The cartography data is not updated as frequently as the navigation data.
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KLN 94
It is necessary to swap cards to update the cartography data. Updating the navigation database will not compromise the cartography database.
Laptop computers used to load the database require the following:
1. IBM compatibility
2. An available Com 1,2,3, or Com 4 serial port
NOTE
The PC must be fully IBM compatible and must have a 3.5" high density diskette drive, If the database is loaded from a diskette sent from Honeywell. For more information, contact Honeywell Product
Services by telephoning (913) 712-0600.
1.6.2 Annunciators and Switch/Annunciators
(Refer to I.B. 363 for additional information pertaining to switch/annunciators for GPS systems)
The devices shown below are Eaton 582/584 series switch/annunciators and are representative of those used in our original certification. They were chosen because of their excellent sunlight readable characteristics and meet or exceed the requirements of Advisory Circular 20-138.
These are high quality devices and we encourage their use. However, there are other comparable devices on the market that may be substituted at the installer’s/customer’s choice.
These switch/annunciators are available through Honeywell Service Stock or direct from our supplier, LCOMP Inc. It is advantageous to order direct from LCOMP, if possible, in order to avoid additional price mark-ups. On international orders, it may be necessary to order through
Honeywell as LCOMP, at the time of this publication, is not prepared to handle international orders. The address and telephone numbers for LCOMP are listed as follows:
LCOMP Aerospace Controls c/o Carlton-Bates Co.
9214 Bond St.
Overland Park, KS 66214
(913) 438-4848 Telephone
(800) 786-0617 Toll Free
(913) 438-4839 Fax
NOTE
The switch/annunciators listed below in many cases show two numbers. The part numbers that are shown in parentheses are devices previously called out and may be used until supply is depleted. The 031-00785-XXXX are the preferred
Switch/Annunciator assemblies.
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KLN 94
KLN 94 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 94 IFR enroute/terminal installations. They are optional for KLN 94 VFR installations.
The KLN 94 has internal annunciators. Hence, the external annunciators may be optional in some installations:
KLN 94/89/89B Annunciator Set - 28 VDC Lighting
NAV / GPS Sw. Ann
WPT / MSG Ann.
031-00785-0711 or 031-00763-0711
031-00785-0505 or 031-00763-0505 / -0718
KLN 94/89/89B Annunciator Set - 14 VDC Lighting
NAV / GPS Sw. Ann
WPT / MSG Ann.
031-00785-0712 or 031-00763-0712
031-00785-0762 or 031-00763-0762 / -0719
KLN 94 Approach Set for CDI or Elect. Mech. HSI Installations
The following switch/annunciators are being offered for CDI or HSI switching, APR switching, and annunciation in KLN 94 non-precision approach installations:
KLN 94/89B Annunciator Set - 28 VDC Lighting
NAV / GPS Sw. Ann 031-00785-0711 or 031-00763-0711
WPT / MSG Ann.
031-00785-0505 or 031-00763-0505 / -0718
GPS APR ARM / ACT Sw. Ann. 031-00785-0766
KLN 94/89B Annunciator Set - 14 VDC Lighting
NAV / GPS Sw. Ann
WPT / MSG Ann.
031-00785-0712 or 031-00763-0712
031-00785-0762 or 031-00763-0762 / -0719
GPS APR ARM / ACT Sw. Ann. 031-00785-0767
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NAV/GPS Switch/Annunciator
Installations where the outputs from KLN 94 and an existing navigation system are switched between a common indicator or HSI may require some type of annunciation. A NAV/GPS switch/annunciator is available that provides both the annunciation and a switch contact to energize the switching relay(s) required for the switching of the outputs. This Switch/Annunciator is available in 5 V, 14 V, or 28 V versions as shown below.
LIGHTING Honeywell P/N Honeywell P/N
28 VDC 031-00763-0711 031-00785-0711
14 VDC 031-00763-0712 031-00763-0712
(Eaton Series 584) (Eaton Series 582)
Old Style Preferred
WPT/MSG Remote Annunciators
TWO FIELD ANNUNCIATORS (WPT/MSG)
LIGHTING Honeywell P/N Honeywell P/N
28 VDC 031-00763-0505
14 VDC 031-00763-0506
031-00785-0505
031-00763-0506
(Eaton Series 584) (Eaton Series 582)
Old Style Preferred
NOTE
(WPT) AND (MSG) will be in amber color. These annunciators will be deadface and readable only when lit.
GPS APR, ARM/ACTV Switch/Annunciator
A switch/annunciator can be used for arming or activating the approach mode. It will provide remote annunciation of ARM and ACTV and provide a momentary switch function to arm, disarm, or deactivate the Approach Mode and change the CDI scale factors. The KLN 94 may require an annunciator to display when approach is armed or active.
LIGHTING Honeywell P/N
28 VDC 031-00763-776
14 VDC 031-00763-767
(Eaton Series 582)
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1.6.3 NAV/GPS Switching
Installations in which the outputs from a KLN 94 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.
1.6.4 Right Angle Connector
The part number for a right angle connector for the KA 91 or KA 92 antenna connection is
030-00134-0001. This right angle connector was originally an option but has been included in the installation kit as the standard connector.
1.7 LICENSE REQUIREMENTS
None.
1.8 RECOMMENDATIONS FOR IFR APPROVAL
1.8.1 Aircraft Logbook Entry
1.8.2 Aircraft Installation Requirements
NOTE
For the following subsections, refer to
for allowable configurations where applicable. Refer to Section II
for illustrations.
1.8.2.1 TSO/JTSO’d Antenna
The antenna must be a TSO/JTSO’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/JTSO’d antennas have a five digit serial number.
1.8.2.2 Nav Instrumentation
The navigation information (D-Bar, Nav Flag, and To-From) must be displayed on an instrument in the pilot’s panel. Electromechanical indicators are capable of displaying the variable scale factors of enroute, terminal, and approach modes.
1.8.2.3 OBS Interface
The use of an OBS resolver will reduce pilot workload during an instrument approach. It allows the OBS setting to be changed on the navigation indicator when the KLN 94 is operating in the
OBS mode. Without the OBS resolver connection, the OBS may be changed from the KLN 94 controls. OBS mode is commonly used during procedure turns and holding patterns.
Some certification agencies may require the use of the OBS resolver for approach certification.
Consult your approval agency for additional information. Refer to Section 1.3
for additional OBS information.
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1.8.2.4 Switch/Annunciators
1.8.2.4.1 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.
1.8.2.4.2 WPT/MSG (Annunciator)
The KLN 94 has internal annunciators. The “WPT” and “MSG” external annunciators may be required in some installations.
1.8.2.4.3 GPS APR, ARM/ACT (Switch/Annunciator)
A switch/annunciator can be used 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 and activate the Approach Mode and change the CDI scale factors. The KLN 94 may require an annunciator to display when approach is armed or active. Refer to
for additional switch/annunciator information.
1.8.2.4.4 Altitude Source
An altitude source is required for IFR certification. The altitude may be derived from a compatible encoding altimeter and some RS 232 air data systems.
1.8.3 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 006-00839-0000. Refer to the
Procedures Appendix for information on preparing a flight manual supplement and a copy of the
STC approval.
1.8.4 Pilots Guide
The KLN 94 pilots guide must be placed in the aircraft in a location that is accessible to the pilot.
The pilots guide is P/N 006-18207-0000.
1.9 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
The instructions for continued airworthiness given in the TC or STC approvals for this product supplements or supersedes the instructions for continued airworthiness in this manual.
Most Honeywell products are designed and manufactured to allow "on condition maintenance".
On condition maintenance is described as follows; There are no periodic service requirements necessary to maintain continued airworthiness. No maintenance is required until the equipment does not properly perform it’s intended function. When service is required, a complete performance test should be accomplished following any repair action. Consult the appropriate unit Maintenance/Overhaul Manual for complete performance test information.
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SECTION II
INSTALLATION
2.1 GENERAL INFORMATION
This section contains general suggestions and information to consider before installation of the
KLN 94 GPS RNAV. Close adherence to these suggestions will assure optimum performance from the equipment.
NOTE
For aircraft equipped with a KLN 89B that is being replaced by a
KLN 94 refer to Appendix D , Direct Replacement of a KLN 89B with
a KLN 94, at the end of this manual.
NOTE
The conditions and tests required for TSO/JTSO approval of this article are minimum performance standards. It is the responsibility of those desiring to install this article either on or within a specific type or class of aircraft to determine that the aircraft installation conditions are within TSO/JTSO standards. The article may be installed only if further evaluation by the applicant documents an acceptable installation and is approved by the Administrator.
2.2 UNPACKING AND INSPECTING EQUIPMENT
Exercise extreme care when unpacking the equipment. Make a visual inspection of the unit for evidence of damage incurred during shipment. If a claim for damage is to be made, save the shipping container to substantiate the claim. The claim should be promptly filed with the transportation company. It would be advisable to retain the container and packaging material after all equipment has been removed in the event that equipment storage or reshipment should become necessary.
2.3 EQUIPMENT INSTALLATION
2.3.1 AVIONICS COOLING REQUIREMENTS FOR PANEL MOUNTED EQUIPMENT
The greatest single contributor to increased reliability of all modern day avionics is to limit the maximum operating temperature of the individual units whether panel mounted or remote mounted. While modern day individual circuit designs consume much less electrical energy, watts per cubic inch dissipated within the avionics unit remains much the same due to the high density packaging techniques utilized. Consequently, the importance of providing cooling to the avionics stack is still with us today.
While each individual unit may or may not require forced air cooling, the combined heat load of several units operating in a typical avionics location will significantly degrade the reliability of the avionics if provisions for cooling are not incorporated in the initial installation. Failure to provide cooling to the equipment will lead to increased avionics maintenance costs and may also void the
Honeywell warranty.
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In the case of the KLN 94, installation of a KA 33, (P/N 071-4037-XX), or equivalent cooling system is required. Ram air cooling is not acceptable. For installation information on the KA 33 refer to the KA 33 installation manual, P/N 006-01069-XXXX or Installation Bulletin 258.
2.3.2 KLN 94 MECHANICAL INSTALLATION
The KLN 94 installation will conform to standards designated by the customer, installing agency, and existing conditions as to the unit location and type of installation. However, the following suggestions will assure a more satisfactory performance from the equipment.
A. Plan a location on the aircraft panel so that the KLN 94 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.
for the panel cutout dimensions. Mark and cut the panel opening.
2.3.3 ANTENNA SELECTION
The KA 91 and KA 92 GPS active antennas, P/N 071-01545-0200 and 071-01553-0200 respectively, are the designated antennas for the KLN 94.
2.3.4 ANTENNA INSTALLATION CONSIDERATIONS
The antenna should be mounted on top of the fuselage near the cockpit. Avoid mounting the antenna near any projections, the propeller, and the T-tail of the aircraft, where shadows could occur. It is recommended that there be a separation of at least 3 ft between the KLN 94 GPS antenna and any VHF Comm antenna on the aircraft. Antenna baseplate must be level within
± 5° in both axes when the aircraft is in level flight. If the antenna is tilted more than 5° or is mounted close to other objects that shadow it, loss of some of the satellites will occur and system performance may be degraded. Antenna cable and connector information, including vendor
information, is listed below. Refer to figure 2-10
(TNC) and
(BMA) for cable/connector assembly instructions for the 0 to 40 feet category using RG 400/U or RG 142B/U. Refer to
(for both TNC and BMA) for the 0 to 80 feet and 0 to 100 feet categories.
NOTE
KA 91/92 nominal gain and noise figures are 26.5 dB and 2.3 dB respectively. With 0.050 ice on radome, gain will not decrease by more than 2.0 dB when viewing a satellite from 30° above the horizon to zenith, as compared to a no ice condition.
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CABLE
LENGTH
CABLE
PART NUMBER
BMA
CONNECTOR
TNC
CONNECTOR
0 to 40 ft
0 to 80 ft
0 to 100 ft
100 to 165 ft
P/N: 024-00002-0000
VPN: RG142B/U
P/N: 024-00051-0060
VPN: RG400/U
P/N: 030-00101-0002
VPN: TED Mfg. 9-30-10
P/N: 030-00101-0002
VPN: TED Mfg. 9-30-10
P/N: 030-00134-0001
VPN: TED Mfg. 5-30-102
P/N: 030-00134-0001
VPN: TED Mfg. 5-30-102
P/N: 024-00072-0000
VPN: ECS 311601
P/N: 030-00452-0000
VPN: TED Mfg. 9-30-26
P/N: 030-00108-0002
VPN: TED Mfg. 5-10-307
P/N: 024-00071-0000
VPN: ECS 311201
P/N: 030-00452-0001
VPN: TED Mfg. 9-30-25
P/N: 030-00108-0003
VPN: TED Mfg. 5-10-306
Contact TED, ECS or PIC for complete cable/connector assembly.
MAXIMUM
ALLOWABLE
LOSS (dB)
8.0
8.0
8.0
8.0
NOTE
A right angle antenna connector is available from Honeywell
(P/N 030-00134-0001) or from TED.
TED Manufacturing Corp.
11415 Johnson Drive
Shawnee, Kansas 66203
Tel: (913) 631-6211
Electronic Cable Specialists
5300 West Franklin Drive
Franklin, Wisconsin 53132
Tel: (800) ECS-WIRE or (414) 421-5300
PIC Wire and Cable
N53 W 24747 S. Corporate Circle
P.O. Box 330
Sussex, Wisconsin 53089
Tel: (800) 742-3191
or (262) 246-0500
2.3.5 ANTENNA MECHANICAL INSTALLATION
2.3.5.1 General
To maintain good performance from the antenna system, do not wax or paint the antenna.
2.3.5.2 Installation Procedure
A. Using the correct template for the antenna chosen, mark the mounting holes on the aircraft fuselage.
B. Drill and/or punch the required holes.
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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 aircraft 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 prevent oxidation.
F. Refer to
Figure 2-5 for the KA 91 installation drawing or
Figure 2-8 for the KA 92 installation
drawing and mount the antenna as shown. First rivet the doubler plate in place. 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 94 antenna (KA 91/KA 92) do not exceed 50 inch/lbs of torque on the antenna mounting screws.
H. Apply a bead of sealant around the base of the antenna and seal the antenna mounting screw holes to prevent water damage.
2.3.6 ELECTRICAL INSTALLATION
2.3.6.1 General Information
The KLN 94 will operate with an input voltage from 11 to 33 VDC but the front panel lighting circuit must be wired for either +14 VDC or +28 VDC, depending upon the aircraft lighting bus.
Refer to the KLN 94 interconnect diagram for wiring details.
A. The installing facility will supply and fabricate all external cables. The required connectors are supplied as part of the installation kit.
B. The length and routing of the external cables must be carefully planned before attempting the actual installation. Avoid sharp bends or locating the cable near aircraft control cables.
C. The KLN 94 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 94 itself, a point to point continuity check of the wiring harness should be done to verify proper wiring. The aircraft power input to the unit should be made to insure that power is applied to only the specified power pin(s).
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2.3.6.2 Functional Pinout Descriptions
This section gives a brief description of some of the inputs and outputs of the KLN 89/89B. It is provided so the installer can determine what specific wiring needs to be done to the aircraft in which the unit is to be installed. Unless otherwise specified, pins not used are to be left open.
CONNECTOR P941
Pin 1; GENERAL RS 232 IN
Pin 1 is the RS 232 input. The KLN 94 must be configured correctly for the type of equipment (or no equipment) connected to this input. Refer to
for the configuration procedure.
It is not necessary to connect this input to the GENERAL RS 232 OUT when this input is not used as the “No Fuel Mgt Sys” and “No Air Data” configuration choices indicate this input is unused and inhibit the “No RS-232 Data” message. For specific label information, refer to
Pin 2; GENERAL RS 232 OUT
The KLN 94 outputs data in RS 232 format on this pin. It can be used to interface with certain types of ELT’s, fuel sensors, moving map displays, and fuel management systems. For specific
label information, refer to RS 232 Format Definitions Appendix
.
Pin 3; DATA LOADER RS 232 IN
Pin 3 inputs Data Loader information in RS 232 format. It can be used to interface with a laptop
IBM compatible PC to load the database.
Pin 4; DATA LOADER/QUICKTUNE
TM
RS 232 OUT
Pin 4 outputs Data Loader information in RS 232 format. It can be used to interface with a laptop
IBM compatible PC to load the database and to quick-tune some VHF COMM units..
Pin 5; SPARE RS 232 IN
Pin 5 is a spare RS 232 input.
Pin 6; GPS SENSOR RS 232 OUT
Pin 6 is a GPS Sensor RS 232 output; Typically used for RPGWS interface.
Pin 7; OBI SYNC
Pin 8; OBI CLOCK
Pin 9; OBI DATA
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.
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The output can also be converted by a Honeywell KDA 692 which provides standard 4-wire
SINE/COSINE OBI information.
Pin 10; LATERAL DEV FLAG+
Pin 11; LATERAL DEV FLAG-
Pin 12; VERTICAL DEV FLAG+
Pin 13; VERTICAL DEV FLAG-
These are deviation flag outputs. DEV FLAG+ outputs with respect to DEV FLAG-. For the
specifications on these outputs refer to Section 1.3
of this manual.
Pin 14; A/C GROUND
Pin 14 is tied to aircraft ground. Wiring harness shields are not to be terminated on this pin. Refer
Pin 15; WAYPOINT ANNUNCIATE
Pin 15 is the Waypoint Alert annunciator output. This output is tied to a remote annunciator lamp.
When the line is pulled low the annunciator lamp will illuminate. The annunciator will be on whenever waypoint alerting is occurring. For more complete information refer to the KLN 94
Pilots Guide, P/N 006-18207-0000.
Pin 16; MESSAGE ANNUNCIATE
Pin 16 is the Message annunciator output. This output is tied to a remote annunciator lamp.
When the line is pulled low the annunciator lamp will illuminate. The annunciator will be on whenever the message prompt on the KLN 94 is on. For more complete information refer to the
KLN 94 Pilots Guide, P/N 006-18207-0000.
Pin 17; APPROACH ARM ANNUNCIATE
Pin 17 is the Approach Arm annunciator output. This output is tied to a remote annunciator lamp.
When the line is pulled low the annunciator lamp will illuminate. The annunciator will be on whenever the unit is in the approach arm mode. For more complete information refer to the KLN
94 Pilots Guide, P/N 006-18207-0000.
Pin 18; APPROACH ACTIVE ANNUNCIATE
Pin 18 is the Approach Active annunciator output. This output is tied to a remote annunciator lamp. When the line is pulled low the annunciator lamp will illuminate. The annunciator will be on whenever the unit is in the approach active mode. For more complete information refer to the
KLN 94 Pilots Guide, P/N 006-18207-0000.
Pin 19; ALTITUDE ALERT ANNUNCIATE
Pin 19 is the Altitude Alert output pin. The altitude alert feature can be enabled or disabled at installation time from the maintenance configuration pages as described in
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This feature is normally disabled if another altitude alerter (selector) is already installed in the aircraft. If altitude alerting is enabled, the pilot can choose to turn it on or off. If it is disabled, the pilot is not able to turn it on.
Pin 20; SPARE ANNUNCIATOR 1
Pin 21; SPARE ANNUNCIATOR 2
Pins (20-21) are spare annunciator outputs.
Pin 22; ROLL STEERING VALID --This is a Roll Steering Superflag. (same logic as other
superflags.)
Pin 23; ROLL STEERING HI-- Combined with Rool Steering LO, this provides a DC Roll Steering
Command to the Autopilot
Pin 24; LIGHTING 28V/LO
Pin 25; LIGHTING 14V
The lighting bus will use the DC power input pin as lighting low. For 14 V operation, LIGHTING
28V/LO is connected to ground and LIGHTING 14V is connected to the 14 V panel lighting bus.
For 28 V operation, LIGHTING 28V/LO is connected to the 28 V panel lighting bus and
LIGHTING 14V is not connected.
CONNECTOR P942
Pin 1; TEST
Pin 1, when grounded on power-up, will place the unit in the test mode. Once in the test mode, the unit will remain in that mode until power to the unit is turned off. Test mode is provided to assist in manufacturing and field service troubleshooting.
Pin 2; TAKE HOME
Pin 2, when grounded, places the KLN 94 in Take-Home mode which is used for trip planning and flight simulation. It performs as if it is receiving adequate GPS signals to determine its position. It displays the latitude and longitude of its last known position or of whatever position it is initialized to on the Setup Page. Pin 2 should always be left open in the aircraft installation. Take-Home mode must not be allowed during actual flight.
Pin 3; SPARE IN 1
Pin 4; SPARE IN 2
Pin 5; SPARE IN 3
Pin 6; ROLL STEERING LO-- Combined with Roll Steering HI provides a DC Roll Steering
Signal.
Pin 7; SPARE IN 0
Pin 8; APPROACH ARM IN
Pin 8 is used as a select input. If the installation is not certified for approach, the external switch/ annunciator is not needed.
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If the installation is approved for approach and the external switch/annunciator is installed, then a momentary ground on pin 8 will alternately arm or disarm the approach mode.
Pin 9; LATERAL SUPER FLAG
Pin 10; VERTICAL SUPER FLAG
On superflag outputs, a logic high shall be
≥
18 VDC when the voltage at pin 19 is
≥
24.8 VDC. A logic high shall be
≥
10 VDC when the voltage at pin 19 is
≥
12.4 VDC. A logic high shall be
≥
20
VDC when the voltage at pin 19 is + 27.5 VDC. A logic low shall be
≤
3.5 VDC.
Pin 11; LATERAL DEV +L
Pin 12; LATERAL DEV +R
Pin 13; VERTICAL DEV +UP
Pin 14; VERTICAL DEV +DOWN
These pins are deviation outputs and function as differential pairs. For the specifications on these outputs, refer to
Pin 15; ALTITUDE ALERT AUDIO
Pin 16; ALTITUDE ALERT AUDIO LO
These pins represent the Altitude Alert Audio output, which is active whenever ALTITUDE ALERT
ANNUNCIATE is active.
Pin 17; FCS LOC ENG
This annunciator is active when the lateral deviation scale factor is 0.3 nm. It is also active while the scale is transitioning from 1.0 nm down to 0.3 nm.
Pin 18; A/C POWER MONITOR
Pin 18 is the aircraft power monitor. It senses voltages ranging from 0 to 33 V. The KLN 94 can be configured to allow the selection of a voltage alert set point and a voltage alert delay interval for
use with this input. Refer to Section 2.4.1
for the configuration procedure. The “Low Bus Voltage,
Check Charging System” message is displayed when voltage at this pin is below the voltage alert set point for greater than the voltage alert delay interval.
Pin 19; 11-33 VDC A/C POWER
Pin 19 is the DC aircraft power input. The KLN 94 will accept from 11 VDC to 33 VDC input power.
Pin 20; A/C GROUND
Pin 20 is tied to aircraft ground. Wiring harness shields are not to be terminated on this pin. Refer to
.
Pin 21; D4
Pin 22; A1
Pin 23; A2
Pin 24; A4
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KLN 94
Pin 25; B1
Pin 26; B2
Pin 27; B4
Pin 28; C1
Pin 29; C2
Pin 30; C4
These pins are gray code altitude inputs from an encoding altimeter. If the KLN 94 is paralleled with another unit such as a transponder, it may be necessary to install isolation diodes between one or both units and the encoder. The KLN 94 has diodes already installed internally.
Pin 31; GPS DISPLAYED
This pin is used as an input to tell the unit whether an external indicator is connected to the analog OBS resolver inputs, in which case it will be high. This pin will be grounded if an indicator is not connected or coupled to the unit.
Pin 32; +TO
Pin 33; +FROM
These outputs function like the outputs from standard navigation converters. For the specifications on these outputs, refer to
of this manual.
Pin 34; OBS OUT
Pin 35; OBS SIN
Pin 36; OBS COS
Pin 37; OBS RETURN
These pins are the OBS Resolver Interface. This interface is compatible with indicators that are electrically zeroed (EZ) at 300 degrees and indicators that are omni-ranged zero at 300 degrees.
This interface will operate properly with either “0.85 gain” resolvers or “0.41 gain” resolvers with no special programming requirements. OBS Resolver Out is a 450 Hz output used to excite the resolver. The resolver output voltage is then received by the OBS Resolver sine and cosine inputs.
CONFIGURATION MODULE
The configuration module is a separate module from the main rear I/O connector. It is a serial
EEPROM containing at least 32 bytes or 16, 16 (sixteen) 16-bit words.of capacity.
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KLN 94
17
18
19
20
13
14
15
16
21
22
23
24
25
9
10
11
12
7
8
5
6
P941
1
2
3
4
←
---------------------------
---------------------------
→
GENERAL RS 232 IN
---------------------------
→
GENERAL RS 232 OUT
←
--------------------------DATA LOADER RS232 IN
DATA LOADER/QUICKTUNE
TM
RS 232 OUT
←
--------------------------SPARE RS 232 IN
---------------------------
→
GPS SENSOR RS 232 OUT
---------------------------
→
OBI SYNC
---------------------------
→
OBI CLOCK
---------------------------
→
OBI DATA
---------------------------
→
LATERAL DEV FLAG +
---------------------------
→
LATERAL DEV FLAG -
---------------------------
→
VERTICAL DEV FLAG +
---------------------------
→
VERTICAL DEV FLAG -
←
--------------------------A/C GROUND
---------------------------
→
WAYPOINT ANNUNCIATE
---------------------------
→
MESSAGE ANNUNCIATE
---------------------------
→
APPROACH ARM ANNUNCIATE
---------------------------
→
APPROACH ACTIVE ANNUNCIATE
---------------------------
→
ALTITUDE ALERT ANNUNCIATE
---------------------------
→
SPARE ANNUNCIATE 1
---------------------------
→
SPARE ANNUNCIATE 2
---------------------------
→
ROLL STEERING VALID
---------------------------
→
ROLL STEERING HI
←
---------------------------
→
LIGHTING 28V/LO
←
---------------------------
→
LIGHTING 14V
←
INPUTS OUTPUTS
→
Figure 2-1 KLN 94 P941 CONNECTOR PIN FUNCTIONS
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KLN 94
P942
12
13
14
15
10
11
8
9
6
7
4
5
1
2
3
20
21
22
23
24
16
17
18
19
←
---------------------------
←
---------------------------
←
---------------------------
←
---------------------------
←
---------------------------
TEST
TAKE HOME
SPARE IN 1
SPARE IN 2
SPARE IN 3
---------------------------
→
ROLL STEERING LO
←
---------------------------
SPARE IN 0
←
---------------------------
APPROACH ARM IN
---------------------------
→
LATERAL SUPER FLAG
---------------------------
→
VERTICAL SUPER FLAG
---------------------------
→
LATERAL DEV +L
---------------------------
→
LATERAL DEV +R
---------------------------
→
VERTICAL DEV +UP
---------------------------
→
VERTICAL DEV +DOWN
---------------------------
→
ALTITUDE ALERT AUDIO
---------------------------
→
ALTITUDE ALERT AUDIO LO
---------------------------
→
FCS LOC ENG
←
---------------------------
←
---------------------------
A/C POWER MONITOR
11-33 VDC AC POWER
←
---------------------------
←
---------------------------
←
---------------------------
←
---------------------------
A/C GROUND
D4
A1
A2
←
---------------------------
←
INPUTS OUTPUTS
→
A4
Figure 2-2 KLN 94 P942 CONNECTOR PIN FUNCTIONS
(Sheet 1 of 2)
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P942
29
30
31
32
25
26
27
28
33
34
35
36
37
←
---------------------------
←
---------------------------
←
---------------------------
←
---------------------------
←
---------------------------
←
---------------------------
B1
B2
B4
C1
C2
C4
←
--------------------------GPS DISPLAYED
---------------------------
→
+TO
---------------------------
→
+FROM
---------------------------
→
OBS OUT
←
--------------------------OBS SIN
←
--------------------------OBS COS
---------------------------
→
OBS RETURN
←
INPUTS OUTPUTS
→
Figure 2-2 KLN 94 P942 CONNECTOR PIN FUNCTIONS
(Sheet 2 of 2)
KLN 94
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P943
6
A
4
5
1
2
3
D
E
B
C
F
---------------------------
→
EXT_EEPRM_CS
←
---------------------------
←
---------------------------
EXT_EEPRM
TMCP_ENABLEn
---------------------------
→
+5 V
←
---------------------------
RTI_TAKEHOME_ENABLEn
←
---------------------------
TMCP_IN
---------------------------
→
SERIAL OUT
←
---------------------------
←
---------------------------
SERIAL_IN
SERIAL_CLK
---------------------------
GROUND
---------------------------
GROUND
---------------------------
→
TMCP_OUT
←
INPUTS OUTPUTS
→
Figure 2-3 KLN 94 P943 CONNECTOR PIN FUNCTIONS
KLN 94
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KLN 94
FIGURE 2-4 CRIMPING AND INSERTION/EXTRACTION TOOLS
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KLN 94
FIGURE 2-5 KLN 94 INSTALLATION DRAWING
Dwg. No. 155-06020-0000 Rev. AC
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B
KLN 94
FIGURE 2-6 KA 91 OUTLINE
Dwg. No. 071-01545-0200 Rev. 4
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KLN 94
THIS PAGE IS RESERVED.
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KLN 94
FIGURE 2-7 KA 91 INSTALLATION DRAWING
Dwg. No. 155-05999-0000 Rev. 5
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KLN 94
FIGURE 2-8 KA 91 BACKPLATE OUTLINE
Dwg. No. 155-10130-0000/0002 Rev. 2
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KLN 94
FIGURE 2-9 KA 92 OUTLINE
Dwg. No. 071-01553-0200 Rev. AB
Sheet 1 of 3
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KLN 94
FIGURE 2-9 KA 92 OUTLINE
Dwg. No. 071-01553-0200 Rev. AB
Sheet 2 of 3
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KLN 94
NOTES
1.
For best performance, electrical bond between aircraft and antenna should be less than 10 milliohms measured from TNC connector to aircraft skin.
2.
Antenna to be mounted with four 8-32 x 3/4 inch long Pan Head phillips stainless steel screws (Honeywell P/N 089-05909-0012).
3.
Serial tags to be vendor supplied in accordance with Honeywell P/N 057-05753-0000 and
Comant P/N B40585-1.
4.
Airspeed Rating: 600 knots TAS maximum.
5.
Antenna to be installed with installation kit Honeywell part number 050-03318-0000.
6.
Antennas to be bulk packaged as per good commercial practice.
7.
Finished antenna assembly to be tested utilizing Honeywell Test Chamber 190-2361-XX or equivalent, and CHU Associates source antenna model CA3224, or Tecom Model
401163-2.
FIGURE 2-9 KA 92 OUTLINE
Dwg. No. 071-01553-0200 Rev. AB
Sheet 3 of 3
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KLN 94
THIS PAGE IS RESERVED
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KLN 94
FIGURE 2-10 KA 92 INSTALLATION DRAWING
Dwg. No. 155-06019-0000 Rev. 2
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KLN 94
FIGURE 2-11 KA 92 BACKPLATE OUTLINE
Dwg. No. 047-10735-0000 Rev. 1
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KLN 94
FIGURE 2-12A KA 91/92 TNC ANTENNA COAX / CONNECTOR ASSEMBLY
(RG142B/U or RG400 - 0 to 40 FEET)
(Straight Connector P/N 030-00134-0000)
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KLN 94
FIGURE 2-12B KA 91/92 TNC ANTENNA COAX / CONNECTOR ASSEMBLY
(RG142B/U or RG400 - 0 to 40 FEET)
(Right-Angle Connector P/N 030-00134-0001)
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KLN 94
FIGURE 2-13 KA91/92 BMA ANTENNA COAX/CONNECTOR ASSEMBLY
(RG142 B/U or RG400 - 0 to 40 FEET)
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KLN 94
FIGURE 2-14 KA 91/92 TNC ANTENNA COAX / CONNECTOR ASSEMBLY
0 to 80 FEET / 0 to 100 FEET
(For Cable P/Ns 024-00071-0000 Rev. 0 / 024-00072-0000 Rev. 0)
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KLN 94
THIS PAGE IS RESERVED.
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KLN 94
FIGURE 2-15 KA 33 P/N 071-4037-00 /01 FINAL ASSEMBLY
Dwg. No. 300-03256-0000 Rev. AA
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KLN 94
FIGURE 2-16 KA 33 P/N 071-4037-00/01 OUTLINE AND MOUNTING
Dwg. No. 155-05574-0000 Rev. 5
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KLN 94
FIGURE 2-17 CUTLER-HAMMER SWITCH / ANNUNCIATOR MOUNTING
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KLN 94
FIGURE 2-18 CUTLER-HAMMER SWITCH / ANNUNCIATOR INTERNAL SCHEMATIC
Sheet 1 of 2
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KLN 94
THIS PAGE IS RESERVED.
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KLN 94
FIGURE 2-18 CUTLER-HAMMER SWITCH / ANNUNCIATOR INTERNAL SCHEMATIC
Sheet 2 of 2
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KLN 94
FIGURE 2-19 KLN 94 SERIAL RECEIVERS & TRANSMITTERS INTERCONNECT
Dwg. No. 155-01732-0000 Rev. B
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KLN 94
FIGURE 2-20 KLN 94 ALTITUDE & RMI / OBI INTERCONNECT
Dwg. No. 155-01732-0001 Rev.-
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KLN 94
FIGURE 2-21 KLN 94 DEVIATION & FLAGS INTERCONNECT
Dwg. No. 155-01732-0002 Rev.-
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KLN 94
FIGURE 2-22 KLN 94 OBS RESOLVER INTERCONNECT
Dwg. No. 155-01732-0003 Rev.-
Sheet 1 of 2
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KLN 94
FIGURE 2-23 KLN 94 INTERCONNECT
Dwg. No. 155-01732-0003 Rev.-
Sheet 2 of 2
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KLN 94
FIGURE 2-24 KLN 94 FCS & EXT. ANNUNC. INTERCONNECT
Dwg. No. 155-01732-0004 Rev. A
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KLN 94
FIGURE 2-25 KLN 94 BACKLIGHTING & ALT. ALERTING INTERCONNECT
Dwg. No. 155-01732-0005 Rev.-
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FIGURE 2-26 KLN 94 PC LOADER & ANTENNA INTERCONNECT
Dwg. No. 155-01732-0006 Rev.-
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KLN 94
FIGURE 2-27 KLN 94 DATA LOADER / PC INTERFACE
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KLN 94
FIGURE 2-28 KLN 94 QUICKTUNE INTERCONNECT
Dwg. No. 155-01732-0007 Rev.-
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KLN 94
2.4 POST INSTALLATION CHECK OUT INFORMATION
2.4.1 Maintenance Pages
As part of every KLN 94 installation it is necessary to enter the Maintenance (MNT) pages in order to configure the unit properly for the specific installation. Electronically configuring the units replaces the need of installing strapping or configuration wires in the harness. This makes it easier to configure the unit at the time of initial installation and also later on if changes are made to the aircraft such as the later addition of a fuel management system, air data system, or reconfigure from VFR to IFR.
This configuration data is stored both in the external configuration module (mounted in the back plate of the mounting tray) and in memory internal to the KLN 94. When the KLN 94 is initially shipped from the factory, the configuration data is set to the same default values/status in both the external configuration module and the units internal memory. The initial defaults are specified below. When the Maintenance pages are entered and changes made to the configuration data, the changes are stored both in the external configuration module and the internal memory. If the configuration data differs in the external configuration module from the units internal memory, the external configuration module data is automatically used. Differences could occur if after configuring the KLN 94 the initial unit was removed and a second unit inserted into the rack. For example, if the KLN 94 is initially configured correctly and a loaner unit is later installed in the aircraft, the external configuration module would ensure that the proper configuration data was used. The external configuration module is part of the installation kit and should be utilized in every installation to make sure that proper operation occurs regardless of the unit that may later be inserted into the mounting tray.
To enter the Maintenance pages, the MSG button must be depressed before the unit is turned and held. Hold the MSG button down and watch for a flash in the "Earth with Satellites" picture.
Continue to depress the MSG button for 10 seconds (+- 2 seconds) after the flash of the "Earth with Satellites". During that 10 seconds, you will see the picture change from monochrome to color. At the end of the 10 second period, release the MSG button for 1 second and momentarily press the MSG button again. After about a 15 second period the "Earth with Satellites" picture will change to a MNT Page. After entering the Maintenance pages if the configuration data is different between the external module and the units internal memory, the following page is displayed (this page will not be displayed if they are the same):
CONFIGURATION
1. Copy Module to Unit?
2. Copy Unit to Module?
Select: 1 OK?
If you wish to copy the configuration data from the external configuration module to the unit’s internal memory or if you plan to manually change the configuration data, simply press the ENT button.
If you wish to copy the configuration data from the unit’s internal memory to the external module, turn the large outer knob counterclockwise to position the flashing cursor over the 1. Turn the small inner knob to select a 2. Turn the large outer knob one step clockwise to position the cursor back over the OK? and then press the ENT button.
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2.4.1.1 Maintenance 1 (MNT 1) Pages
The MNT+1 page is now displayed. There are three MNT+1 pages. The + sign indicates that there is more than one MNT 1 page. The first MNT 1 page has the following selection choices and format:
1.Whether the unit is certified as IFR or VFR.
2.Whether the unit is certified for IFR enroute/terminal use only or for both enroute/terminal and non-precision approach.
3.Whether the altitude alerting feature is enabled or disabled. If the aircraft has another source of altitude alerting such as that associated with a flight control preselector, this feature should be disabled.
First MNT +1 Page Format
IFR/VFR: IFR
IFR Apr/Enr: Apr
ALT alt: Enabled
Selection Choices Default
IFR or VFR VFR
Apr or Enr (blank if line one above is VFR) Enr
Enabled or Disabled Disabled
To change a selection:
Press the CRSR button to bring the flashing cursor on the screen. Turn the larger outer knob to position the cursor over the desired selection. Turn the small inner knob to change the selection.
Make any additional changes on this page at this time. When finished, press the CRSR button to turn off the cursor.
To select different MNT pages:
Turn the small inner knob (the flashing cursor must be off the page. If it is on, press the CRSR button to turn it off). Select the second MNT+1 page.
The second MNT+1 page has the following selection choices and format. Changes are made using the CRSR button and concentric knob as described above.
1.Whether the KLN 94 is interfaced with a fuel management system.
2.Whether the fuel management system includes it own control/indicator used to enter fuel quantity. (Not a choice if there is no fuel management system).
3.What is the full fuel quantity of the aircraft. (Not a choice if there is no fuel management system or if the fuel management system has its own control/indicator used to enter fuel quantity).
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Second MNT +1 Page Format
Installed Equipment
Fuel Mgt Sys: Y
Fuel Mgt Ind: N
Full Fuel: 0064
Selection Choices
Y or N for yes or no
Y or N
(this line blank if N is selected above)
0000 to 9999
(this line blank if no fuel mgt sys or if fuel mgt sys has its own control/indicator)
Default
N
N
0000
The third MNT+1 page has the following selection choices and format.
1.Whether the KLN 94 is installed with an air data computer.
2.Whether the KLN 94 is installed with a back-up emergency battery (not available from
Honeywell).
3.Below what aircraft bus voltage should the back-up battery be used. (Not a choice if there is no emergency battery).
Third MNT +1 Page Format
Installed Equipment
232 Air Data: Y
Emerg Bat: Y
Use Bat: 10.2 V
Selection Choices
Y or N for yes or no
Y or N for yes or no
0-33 V (this line blank if no emerg bat)
Default
N
N
10.2 V
2.4.1.2 Maintenance 2 (MNT 2) Page
The MNT 2 page displays total hours of operation and number of power cycles on the KLN 94 and is not configurable.
2.4.1.3 Maintenance 3 (MNT 3) Page
The MNT 3 page is used to calibrate the OBS setting of the aircraft’s HSI or CDI to the KLN 94 so that the KLN 94 reads the value the pilot selects on the HSI or CDI. It is necessary to configure this page only if the KLN 94 is interfaced to an HSI or CDI resolver such that the KLN 94 is able to read the course selected on the HSI or CDI. To calibrate the OBS:
1.Select a course using the course select/OBS knob on the HSI or OBS that is interfaced with the
KLN 94. It is suggested that a course increment of 10 degrees (example 10,150, 270, etc.) be used so that the course can be selected as precisely as possible.
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2.Press the CRSR button to turn on the cursor.
3.Use the small inner knob to select the exact course that is selected on the HSI or CDI in step 1 above.
4.Adjust the HSI or CDI to another course which is not 180× away from the original course, and verify the correct course is displayed within 2×. If not, the OBS resolver interface may be miswired.
5.Press the CRSR button to turn off the cursor. The calibration is now complete.
2.4.1.4 Maintenance 4 (MNT 4) Page
The MNT 4 page is used to set the bus monitor voltage and alert delay so that if the aircraft’s charging system were to fail (i.e. generator/alternator failure) the pilot would be given timely notification of the failure. The alert delay is selected so that momentary voltage drops which could be caused by such things as cycling the aircraft’s gear or flaps do not cause nuisance notifications to the pilot. When the bus voltage falls below the selected alert voltage for the selected alert delay time the unit notifies the pilot with the following message that is displayed on the message page:
Low Bus Voltage
Check Charging System
This Power Monitor feature can be turned on and off by the pilot on the SET 9 page but actual configuration can only be done from the MNT 4 page. The SET 9 page displays to the pilot the actual bus voltage to the KLN 94 as well as the alert voltage and alert delay that have been configured on the MNT 4 page. Changes are made to the MNT 4 page using the CRSR button and the concentric knobs as described in
.
The MNT 4 page has the following format and choices:
MNT 4 Page Format
Bus Monitor
Alert Volt 12.8 V
Alert Delay 15 S
Selection Choices
0.0 - 33.0 V
0 - 99 seconds
Default
10.0 V
15 S
The following procedure is suggested as a means of determining what voltage to use for the alert voltage. Cycle power to the KLN 94 to exit the Maintenance pages. View the SET 9 page to determine the actual voltage being supplied to the KLN 94 while the engine is running
(alternator/generator supplying the bus voltage). You may want to do this with the engine at idle so that you see the lowest possible voltage supplied by the alternator/ generator. Next, determine the actual voltage being supplied to the KLN 94 when only the battery is supplying the voltage
(alternator/generator turned off or engine not running).
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The alert voltage should be chosen to be about half way between these two voltages. For example, in a 14 volt aircraft say the alternator supplied voltage is 13.8 volts as displayed on the
SET 9 page with the engine running. The battery supplied voltage with the engine not running is
12.0 volts. An appropriate alert voltage in this case would be 12.9 volts. If an alternator were to fail in flight and the voltage drop to 12.0 volts for at least 15 seconds (or whatever alert delay time was selected), the pilot would be notified of the problem.
NOTE
In order to prevent nuisance messages, this feature should be disabled (Alert
Volt OFF) on the SET 9 page on aircraft where the alternator/generator output drops down to a voltage close to the battery voltage during engine idle.
When the maintenance pages are configured as desired, it is necessary to cycle power to the unit in order to leave the maintenance pages and allow normal operation.
2.4.1.5 Maintenance 5 (MNT 5) Page
The MNT 5 page is used to configure the Quicktune

outputs of the KLN 94. The COMM frequencies stored in the KLN 94 may be sent to up to 4 COMMs that recognize the Quicktune
 labels transmitted over the RS232 bus. The Bendix/King KX155A and KX165A are examples of such a radio.
Similarly, the NAV frequencies stored in the KLN 94 may be sent to up to 4 NAV radios. If a
Quicktune

compatible COMM or NAV is assigned in the KLN94 MNT 5 page (i.e. COMM-2, and
NAV-1), then the specific COMMs and NAVs must be configured themselves with the same identifier. For the specific procedure on how to assign an identifier to a KX155A, refer to section
3.1.4.3 of the KX155A Installation Manual.
If a radio number is assigned in the KLN94, a similar operation must be performed in the radio. In other words, if COMM-2 is assigned in the KLN94 as being a valid output, the KX155A (or other
Quicktune

-valid receiver) must be configured to accept Quicktune

frequencies and identified as “COMM2”.
If an installation allows more than one Quicktune

radio (i.e. two or more KX155A), it is not necessarily recommended that both radios should be configured for Quicktune

operation, but rather consult with the owner and ask for the owner’s recommendation. If only one valid
Quicktune

COMM radio is chosen in the MNT 5 page, when the user sets the CRSR over a
COMM frequency and presses ENT, the frequency will automatically be placed in the STANDBY slot of the radio. On the other hand, if two or more valid Quicktune

COMMs are chosen in the
MNT 5 page, after pressing ENT on a COMM frequency, the user will be asked to which radio that frequency should be sent. While it increases flexibility, this could be considered a nuisance.
When the installation is complete, the user will be able to choose the default Quicktune

radios for both COMM and NAV on the SET 14 page. Consult the KLN94 Pilot’s Guide for additional information.
2.4.1.6 Maintenance 6 (MNT 6) Page
The MNT 6 page allows the installer to change the nomenclature of the internal annunciators of the KLN94, shown on the right hand side of the KLN94 display.
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There are only two combinations allowed. The choices are shown below.
KLN 94
MNT 5 Page Format Choice 1 Choice 2 Default Settings
Annun: APR ARM TERM
APR ACTV APR
APR ARM
APR ACTV
If the KLN94 is meant to replace an existing KLN89B and there is already an installation with external annunciators that display “APR ARM” and “APR ACTV”, then the same combination must be chosen in the MNT 6 page in order to have conformity throughout the aircraft. This will also allow the installer to keep the existing external annunciators and switches in place.
In a new KLN 94 installation, the external annunciators may not be required. In this case, the user may prefer “choice 2” since it is shorter and more descriptive.
2.4.1.7 Maintenance 7 (MNT 7) Page
The MNT 7 page allows the installer to select between the Standard RS232 Serial Output and the Enhanced RS232 Serial Output. The Enhanced RS232 bus will only work with the
Bendix/King Skyforce KMD550 Multifunctional Display, at the time of publication of this manual.
In an installation of the KLN94 with a KMD550 also has additional moving map equipment, the standard RS232 should be chosen, as it will be able to drive a minimal subset of labels in the
KMD550 as well as additional equipment.
If you see no published interconnect for your MFD or Moving Map Display, consult the manufacturer for installation information.
2.4.1.8 Maintenace 8 (MNT 8) Page
A Configuring the KLN 94 to operate without roll steering.
1. Select MNT 8 page.
2. Push CRSR button. The cursor will appear over the second line.
3. Select “None” and push CRSR again. The screen should look like:
Configuration
Module
DC Roll Steering
None
MNT 8
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B. Configuring the KLN 94 to operate with KFC 225 (attitude-based flight control system):
1. Select MNT 8 page.
2. Push CRSR button. The cursor will appear over the second line.
3. Select “Bank Angle” and push CRSR again. The screen should look like:
Configuration
Module
DC Roll Steering
Bank Angle
MNT 8
C. Configuring the KLN 94to operate with KAP 140 (turn-rate-based flight control system):
1. Select MNT 8 page.
2. Push CRSR button. The cursor will appear over the second line.
3. Select “Turn Rate”. “Max Turn Rate” should appear on the fourth line.
4. Turn the outer knob once. The cursor should move to the bottom line.
5. Dial in the autopilot’s maximum turn rate. For KAP 140 as of 7/17/2002, it is 2.7 degrees per second.
6. Push the CRSR agin. The screen should look like:
Configuration
Module
DC Roll Steering
Turn Rate
MNT 8
Max Turn Rate
2.7 dps
2.4.2 POST INSTALLATION CHECKOUT PROCEDURE
This procedure is divided into two major sections. The first section deals with “Stand Alone” installations in which none of the signal Input/Output capability of the unit is utilized, (except for the RF input signal from the antenna). In this type of installation the only connections to the KLN
94 are the cable from the GPS antenna, the aircraft power and ground leads, and the lighting bus wires.
NOTE
All output data is read from the unit front panel display and all input to the unit is via the front panel controls.
The second part of this procedure deals with an installation in which some or all of the electrical 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.
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KLN 94
It is assumed that the operator’s manual for the various units connected to the KLN 94 (as well as the manual for the KLN 94 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 P942 pin 19, and that there is a ground on P941 pin 14 and
P942 pin 20. In installations using 28 V lighting, lighting bus voltage should be present between
P941 pins 24 and 14. In installations using 14 V lighting, lighting bus voltage should be present between P941 pins 25 and 14. Verify that there are no voltages or grounds present on any other pins of P941 and P942.
A.Verify that aircraft power is OFF or the unit circuit breaker is pulled. Making sure that the power
On/Off switch, located on the front panel of the KLN 94 is rotated the “off” position (power off), plug the unit into the mounting rack and verify that the panel lighting works properly.
B.Energize the unit by rotating the power control switch to the “on” position.
C.Manipulate the controls as necessary to display the Set 1 Page on the right half of the screen.
On the Set 1 Page, enter the airport name or the present position (latitude and longitude) for the installation location accurate to within 60 nautical miles. Display the Set 2 Page. Verify that the date and time are correct to within 10 minutes and update if necessary.
D.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. (To speed up the next test it is helpful to turn unit power off then on again once the system is away from structures).
E.Proceed to the AUX 1 page. The State shown on the display should change to Acquire (ACQ) from INIT and after a period of not more than 5 minutes, (typically two minutes depending upon the satellite coverage), the unit should display Latitude and Longitude values on the Nav 2 Page that are correct for the installation location. If the unit has not been turned on for 6 months, the unit will take up to 20 minutes to calculate a position.
F.Select the AUX 2 page, verify that no asterisks appear next to any satellite with an elevation greater than 25°. Select 121.15 MHz on COMM 1. Transmit on COMM 1 for a period of 20 seconds and verify that no asterisks appear indicating satellites with an elevation of greater than
25°. Repeat for the following frequencies: 118.000, 120.925, 121.175, 121.200, 123.825,
127.100, 130.625, 131.250, 131.275 131.300 and 134.150 MHz. Repeat the above procedure for all VHF COMM’s on board the aircraft.
If any of the above tests do not pass (any asterisks appear on satellites with greater than 25° during the above tests), it will be necessary to identify the source of the interference. There are two common sources of interference:
1.The 12th and 13th harmonics of the above mentioned frequencies can be radiated from the
VHF COMM at a level strong enough to be a problem to the GPS but still be well low enough to meet TSO/JTSO requirements for the VHF COMM.
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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 responsibility of those desiring to install this article either on or within a specific type or class of aircraft to determine that the aircraft installation conditions are within these performance standards. The article may be installed only if further evaluation by the applicant documents an acceptable installation and is approved by the Administrator.
2.The other possibility is re-radiation from an ELT. The radiated RF from the VHF COMM can excite the output tank circuit of the ELT and cause it to oscillate and radiate RF strong enough to interfere with the GPS. If disconnecting the ELT antenna eliminates the GPS interference, the manufacturer of the ELT should be contacted for a recommended solution.
G.Select the AUX 14 page and verify that the first line of that page on the unit display screen reads as follows:
SW REVISION 0X0X
(where 0X0X is the last four digits of the KLN 94 Application Software 206- number)
An entry must be made in the aircraft log book upon installation of the KLN 94, indicating the applicable software revision level. The recommended log book wording is as follows:
KLN 94 Application Software is at SW REVISION 0X0X on DD MMM YYYY.
(where 0X0X represents the last four digits of the KLN 94 Application Software 206- number and DD MMM YYY represents the Day, Month and Year of the installation)
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 KLN94. It should be clearly determined which of the signals are intended to be used in any given installation and then only the paragraphs pertaining to those signals should be performed.
2.4.4.1 All Installations
Perform all steps defined in Paragraph 2.4.3
and leave the system energized with a valid GPS signal being received.
2.4.4.2 CDI/HSI Interface
Cycle the power on the KLN94, 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.
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Verify that the TO/FROM flag is indicating FROM. Verify that the nav flag is pulled from view.
Verify that the selected course from the CDI/HSI is interfaced properly to the KLN 94 in the OBS
Mode. The OBS value on the third line of the self-test page should match the selected course on the CDS/HSI and be with satellite coverage or in take-home mode.
You must create an active waypoint on the Flightplan 0 page to check the following function. The
OBS/LEG selection is controlled through the OBS button located on the front panel of the KLN
94. Pressing this button toggles between DTK and OBS with the normal position being DTK.
During OBS mode, the DTK indication (located left of the vertical page divider) will change to a three digit course value.
Verify that the selected course value agrees with the value displayed on the HSI Course Pointer.
Change the selected course value on the HSI or CDI using the OBS knob. Verify that the selected course value displayed on the KLN94 tracks the new value selected. In the OBS mode with the
GPS displayed on the CDI/HSI, the resolver is disconnected from the NAV converter. Verify that the KNS 80 or 81 groundspeed is still functional and the Radial display for the KX 165 or KNS 81 is still functional. These units must have jumpers or resistors across them when the resolver is removed.
In the OBS mode with the GPS not displayed on the CDI/HSI, the resolver is reconnected to the
NAV converter. Verify that change in the OBS resolver will not affect the selected OBS on the
KLN 94.
2.4.4.3 Gray Code Altitude Inputs
With gray code altitude being supplied by a compatible encoding altimeter, verify that the proper altitude is indicated on the ALT page (provided no other altitude sources are active and that proper baro setting has been entered).
Verify that there is no interference between the KLN 94, transponder, and any other loads on the encoding altimeter output. Remove power from each of the loads on the encoder to verify that the remaining equipment still performs properly. If interference exists, one or more of the units are not diode isolated and isolation diodes will need to be added to the aircraft wiring.
2.4.4.4 RMI Interface
Cycle power on the KLN 94 which will cause the self test page to be displayed. Verify that the
RMI indicates 130°.
2.4.4.5 ELT Interface
The following test must be conducted within five minutes after the hour with ELT transmissions limited to 3 (Three) sweeps. A sweep occurs each time there is a voice transmission. Verify that the present position is displayed on the KLN 94 Nav 2 page. Activate the Comm Receiver and tune it to 121.5 MHz. Switch the ELT cockpit toggle switch to TEST. The ELT light should flash and the “sweeping” sound of the ELT should be heard on the Comm Receiver.
Within 1 (one) minute, a voice transmission should be heard which contains the present position displayed on the KLN94 Nav 2 page. Switch the toggle switch to AUTO and push the reset button until it stops flashing.
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2.4.4.6 Moving Map Interface
If the KLN 94 is interfaced to a moving map display, verify operation by moving the aircraft out to an open location to acquire a satellite position. Enter an active flightplan or active waypoint to develop a presentation on the map.
Some moving maps require 2 kts of ground speed to display, as the sense track angle is used instead of the heading. The KLN 94 does not output track angles when the groundspeed is below
2 kts.
2.4.4.7 External Annunciators
Recycle the power on the KLN 94 which will cause the Self Test Page to be displayed. Verify that all external annunciators are energized. Cycle the KLN 94 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 KLN94 to determine if the lighted annunciator is justified.
NOTE
Annunciators should be checked one at a time in order to verify that the correct one lights.
2.4.4.8 Quicktune

Interface
If the KLN 94 is interfaced to a KX 155A / KX 165A for Quicktune

operation, the following test must be performed to verify the installation. Turn on the KLN 94 and display the APT5 page, where airport frequencies are displayed. choose any airport with at least one frequency. Press the CRSR button, move the cursor on any frequency and press the ENT button. Verify that the selected frequency now appears in the COMM Standby Frequency of the KX155A / KX165A. To verify the NAV part of the operation, display the VOR1 page. Press the CRSR button, move the cursor on the VOR frequency and press the ENT button. Verify that the selected frequency now appears in the NAV Standby Frequency of the KX 155A / KX 165A.
2.4.4.9 Dataloader
The database cartridge may be updated with a new navigation database using a laptop computer. The laptop computer must be IBM compatible and have an available COM port (1, 2, 3, or 4).
Internet Update
A new navigation database can be obtained via the Internet at the following address: http://www.gpsdatabase.com
Store the new database on the hard drive of the PC. Then connect the laptop via the PC loader kit PN 050-03612-0000 (refer to
Figure 2-26 ). Turn on the KLN 94 to the SET 3 page. Then run
the program NETLOAD.EXE and follow the appropriate instructions.
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Diskette Update
Connect the laptop via the PC loader kit PN 050-03612-0000 (ref figure 2-26 ). Turn on the KLN
94 to the SET 3 page. Insert the 3.5" Database diskette into the PC. Cycle the power of the PC and follow the menu driven instructions. (A small number of PC’s may exhibit problems during the load because a few select BIOS services are incompatible with the Honeywell diskettes. If there is uncertainty relating to this, contact Honeywell Product Services at (913) 782-0600, or
Navigation Services at 1-800-247-0230 or (913) 712-3145.)
NOTE
The KLN 94 database may be updated using a PC with the KLN 94 mounted in an aircraft (refer to
Cartography databases are only updateable via card exchange. Update frequency has not yet been established but will most likely be annually.
2.4.4.10 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 has been configured
“Enable”.
2.4.4.11 Heading Interface
Heading information may be interfaced to the KLN 94 by RS 232 to aid in the calculation of wind vectors and for heading orientation of the NAV 4 or moving map. RS 232 heading information may be provided from an analog to RS 232 converter, such as the Shadin fuel/air data device, through the RS 232 input.
Display the NAV 4 page and select the HDG orientation to test the heading function. If a valid heading source is available, HDG orientation will be selectable. Turn the cursor on the Nav 4 page to display the heading value when the HDG orientation is selected.
2.4.4.12 Flight Control Roll Steering Ground Test
NOTE
This ground test assumes that a KFC 225 Flight Control System is installed.
Ground Test is not available for other Flight Control Systems
Ensure That:
All Gyros used by the Flight Control System need to be spun up to speed and the aircraft needs to be level in the roll axis.
The Attitude Gyro is fully erected and stabilized.
The Flight Control System has conducted and completed a successful pre-flight test.
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The GPS is the selected sensor on the primary NAV indicator. The primary NAV indicator shows the signals that the autopilot uses.
Turn the KLN 94 on to initiate its self-test sequence. While the KLN 94 performs its display test, be ready to engage NAV mode on the autopilot, but do not engage the NAV mode yet.
When the NAV flag on the CDI/HSI moves out of view, immediately press the NAV button on the
KFC 225 computer to engage NAV coupled mode. If unsuccessful, the autopilot will only NAV
ARM and not show NAV coupled. If this happens, the KLN 94 must be turned OFF, then turned
ON again before the next attempt is made to engage the NAV coupled mode.
When the autopilot is in NAV coupled mode, then:
Turn OFF the KLN 94 cursor by pushing the CRSR button.
Push the KLN 94 PROC button.
Push the KLN 94 OBS button.
Push the KLN 94 PROC button.
Push the KLN 94 OBS button.
The KLN 94 should be outputting a signal equivalent to a 10 degree right bank. This should be evident by the command bars indicating an approximate 10 degree right bank.
Push the KLN 94 CRSR button. The command bars should return to the wings-level state.
2.4.4.13 Aircraft Logbook Entry
Select the AUX 14 page and verify that the first line of that page on the unit display screen reads:
SW REVISION 0X0X
(where 0X0X is the last four digits of the KLN 94 Application Software 206- number)
An entry must be made in the aircraft log book upon installation of the KLN 94, indicating the applicable software revision level. The recommended log book wording is as follows:
KLN-94 Application Software is at SW REVISION 0X0X on DD MMM YYYY.
(where XXXX represents the last four digits of the KLN 94 Application Software 206- number and
DD MMM YYY represents the Day, Month and Year of the installation)
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2.5 ERROR CODES
The KLN 94 provides numeric error codes and text messages for certain failures. The following table may assist in identifying the root cause of these problems.
GPS Rec.
Error Codes
RCVR Hardware
Error: XXXX:
RCVR Hardware
Error: 0002
RCVR Hardware
Error: 0004
RCVR Hardware
Error: 0008
RCVR Hardware
Error: 0010
RCVR Hardware
Error: 0080
Definition Suggested Action
This message appears when the
KLN 94 fails a specific internal test for the GPS receiver. The possible error codes are described below:
ROM Failure: The ROM memory has failed self-test.
RAM Failure: The RAM memory has failed self-test.
Nonvolatile Memory Failure: The battery-backed RAM has failed a checksum test. Non-volatile memory will be cleared.
Bad ROM. Return for service.
Bad RAM. Return for service.
It could be one of the following, in the order of probability:
1. The battery-backup power to the GPS Receiver was lost. This could be due to either a dead internal battery or a bad connection on the cable to the receiver.
RF Failure: This means the receiver is not sensing a proper RF signal from the satellites/antenna.
2. The RAM memory is bad.
It could be one of the following, in the order of probability:
1. Coax open or shorted. Confirm the 5 volts at the antenna end.
ASIC Failure: The GPS Correlator
ASIC fails self-test.
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 signal at the input.
It could be one of the following, in the order of probability:
1. The flex cable between the Receiver and Main
Board may have come out of the socket in the GPS.
2. Bad ASIC on receiver module in GPS. Substitute the GPS unit.
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GPS Rec.
Error Codes
RCVR Hardware
Error: 0100
RCVR Hardware
Error: 0400
RCVR Hardware
Error: 0800
RCVR Hardware
Error: 1000
RCVR Hardware
Error: 2000
RCVR Hardware
Error: 8000
KLN 94
Definition Suggested Action
BBP Timeout: The 1 mS baseband processing timer has failed self-test.
It could be one of the following, in the order of probability:
1. The 5 volt supply to the antenna could be shorted out in the coax. This disables the oscillator in the GPS.
2. The flex cable between the Receiver and Main
Board may have come out of the socket in the GPS.
RS 232 Receiver Failure: The GPS
Receiver did not receive any initialization data from the host computer on the RS 232 port.
3. Bad TCXO or ASIC on receiver module in GPS.
Substitute the GPS unit.
It could be one of the following, in the order of probability:
1. The flex cable between the Receiver and Main
Board may have come out of the socket in the GPS.
EEPROM Failure: The EEPROM memory has failed its checksum.
RS 232 Channel 2 Failure: The second RS 232 UART on the receiver has failed the loop-back test. This self-test can only be enabled during test mode on the receiver and should not be seen in normal operation.
BBP Underflow: The baseband processing loop detected an error in the 1mS processing loop.
2. Bad 32KHz crystal, UART, or processor on
Receiver Module in GPS. Substitute the GPS unit.
Bad EEPROM. Return for service.
It could be one of the following, in the order of probability:
1. The receiver was put in test mode without looping back the two serial ports.
2. Bad ASIC or Microprocessor on the receiver.
It could be one of the following, in the order of probability:
1. The flex cable between the Receiver Board and the Main Board mat have come out of the socket in the GPS.
BBP Overflow: The baseband processing loop detected an error in the 1mS processing loop.
2. Bad TCXO, MMIC, or ASIC on the Receiver
Board.
It could be one of the following, in the order of probability
1. The flex cable between the Receiver Board and the Main Board mat have come out of the socket in the GPS.
2. Bad TCXO, MMIC, or ASIC on the Receiver
Board.
TABLE 2-1 GPS RECEIVER ERROR CODES
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GPS Page
Messages
Altitude Fail
Definition Suggested Action
Indicates a missing or erroneous altitude.
The altitude input on the gray code input from the encoder is wrong.
The altitude from the encoder may be in error due to a miswire, or the absence of isolation diodes between the encoder and the transponder.
The GPS is configured for IFR and there is no altitude source available.
NAV Superflag Failure Indicates an internal test of the
NAV Superflag output has failed.
RAIM position error
If the GPS is configured for IFR, it must have a valid altitude. Verify the presence of altitude on the
Self-Test or Altitude Pages (press the ALT button).
When the flag is supposed to be valid, it should reach a minimum voltage. Usually a failure is due to overloading of the output. The output can be tested when the Self-Test Page is displayed.
It could be one of the following, in the order of probability:
Cross check position
RAIM is a method of calculating integrity of the GPS position. It calculates the position multiple times using different sets of satellites and compares the answers. If they have excessive differences, the message appears.
1. This probably is a GPS failure. Cross check your position by other means of navigation. Return for service.
No RS 232 Data
RAIM not available
Cross check position
There is no RS 232 data at the RS
232 input port.
This means there are not enough satellites available to compute integrity (RAIM).
2. The GPS has detected a problem with one of the satellites and cannot be assured to be within IFR limits.
The Air Data/Fuel Flow source is not outputting RS
232 data to the GPS. If no source of RS 232 is interfaced, the receiver input must be jumpered back to the RS 232 output.
The aircraft should be in an open area with good visibility and the SNR (Signal to Noise Ratio) on the
AUX 2 page should be:
1. The satellites are blocked from view by obstructions.
2. The satellites are too low on the horizon for use or too high for adequate geometry.
A KLN 94 will usually have 6-8 satellites shown and the majority of their SNR values will be 7 to 9. SNR values of 3 and below are unusable, 4 is marginal and 5-9 are considered good. If the SNR values are low, it could be one of the following, in order of probability:
3. There is a loss of sensitivity in the antenna, the coax or receiver module.
1. Check the antenna coax and connection for 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.
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GPS Page
Messages
RAIM not available
Cross check position
Definition Suggested Action
This means there are not enough satellites available to compute integrity (RAIM).
The aircraft should be in an open area with good visibility and the SNR (Signal to Noise Ratio) on the
AUX 2 page should be:
1. The satellites are blocked from view by obstructions.
A KLN 94 will usually have 6-8 satellites shown and the majority of their SNR values will be 7 to 9. SNR values of 3 and below are unusable, 4 is marginal and 5-9 are considered good. 2. The satellites are too low on the horizon for use or too high for adequate geometry.
If the SNR values are low, it could be one of the following, in order of probability:
3. There is a loss of sensitivity in the antenna, the coax or receiver module.
1. Check the antenna coax and connection for problems.
2. Verify that 5 volts is present at the antenna end of the coax.
3. Substitute the receiver to check for sensitivity.
RAIM not available
Approach mode inhibited
This is a calculated prediction of
RAIM availability. The message appears when integrity monitoring
(RAIM) is predicted to not be available at either the FAF or MAP.
Predict RAIM on AUX
3 The GPS will not allow the unit to go into APR ACTV mode until conditions improve.
4. Substitute the antenna to check for sensitivity.
This is a feature, not a system failure.
Turn to the AUX 3 page to perform a RAIM prediction. It will give you an indication of how long it will be until RAIM is available.
This prediction can also be performed prior to departure to insure RAIM at your arrival.
TABLE 2-2 GPS PAGE MESSAGES
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GPS System
Error Codes
KLN 94
System Error
Code XXXX
001
003
006
017
025
101
102
103
Definition Suggested Action
System Error Codes reflect an error detected deep in the system.
Some of the numeric codes will be described below:
Initialization Failure
Failed Powerup Self-Test
Exception Interrupt Detected. The processor received an undesirable interrupt request.
Run Time Database Checksum
Failed. An error was detected on the internal NAV database chip.
ADC reference failed. The reference voltage to the Analog to
Digital Converter is not at a proper level.
Unit Not Responding
Bad Application Program
Invalid or Missing Database Card
Most of the System Errors require the attention of a service center. Please note as many details as possible when the failure occurred and identify if it is repeatable.
Cycle the power and see if the error is repeatable. If repeatable, take the unit to a Service Center.
Bad internal NAV database chip. Return for service.
TABLE 2-3 GPS SYSTEM ERROR CODES
NOTE
If any error code appears other than the ones listed above, contact Honeywell
Product Support at (913) 782-0600.
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KLN 94
SECTION III
OPERATION
3.1 GENERAL INFORMATION
For an explanation of the operating controls of the KLN 94 GPS RNAV refer to the KLN 94 Pilot’s
Guide (P/N 006-18207-0000) or the aircraft’s flight manual supplement.
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THIS PAGE IS RESERVED.
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APPENDIX A
RS-232 FORMAT DEFINITIONS
KLN 94
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1.0 GENERAL RS-232 IN
The RS-232 interface will have the following characteristics:
BYTE FORMAT
Electrical per EIA RS 232C
9600 baud, 8 bits, 1 stop bit, no parity
MARK is a logical 1 (one) and SPACE is a logical 0 (zero)
START bit begins as MARK, goes to SPACE
The receiving order of data bits within each data byte shall be:
START bit
Data bit 0 (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
KLN 94
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Fuel/air data input protocol
Fuel/air data sent by the Airdata computer shall be received in a block having one of the following formats:
FORMAT A (13 BYTE ASCII STRING)
DESCRIPTION / FORMAT BYTE
1
2
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
7
12
13
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 BCD representation. Using BCD arithmetic, sum the 4
BCD values and convert the lower-order BCD digit to an ASCII coded numeric digit.
Example:
The checksum for a value of 432 would be “9” (39H).
8-11 Fuel Flow Rate (units / hours)
ASCII-coded decimal format as used for Fuel Remaining.
Fuel Flow Rate Checksum
Sum of fuel flow rate bytes computed as described for Fuel Remaining checksum.
EXT (ASCII code 03H)
NOTE:
1. Fuel remaining and fuel flow rate information shall be for the complete aircraft.
2. This 13 byte record shall be transmitted every 1.6 seconds ± 0.16 seconds.
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KLN 94
FORMAT B (52 BYTE ASCII STRING)
DESCRIPTION BYTE
1
2
STX (ASCII code 02H)
Unit of Measure
G = .1 gallon
I = .1 imperial gallon
L = 1 liter
K = 1 kilogram
B = 1 pound
3-8 Total Fuel Remaining
ASCII-coded decimal format (least significant digit is tenths), LSB first
9
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 BCD representation. Using BCD arithmetic, sum the 4
BCD values and convert the lower-order BCD digit to an ASCII coded numeric digit.
Example:
The checksum for a value of 543.2 would be “4” (34H).
10-15 Total Fuel Flow Rate
16
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
23
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.
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KLN 94
FORMAT B (52 BYTE ASCII STRING) - con’t
BYTE
30
DESCRIPTION
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
37
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
44
ASCII-coded decimal format as for Total Fuel Remaining
Engine One Fuel Used Checksum
Sum of Left Engine Fuel Flow Rate bytes computed as for Total Fuel Remaining
45-50 Engine Two Fuel Used
51
ASCII-coded decimal format as used for Total Fuel Remaining
Engine Two Fuel Used Checksum
52
Sum of Left Engine Fuel Flow Rate bytes computed as for Total Fuel Remaining
ETX (ASCII code 03H)
NOTE:
1. In the case of single engine aircraft, all Engine One and Engine Two data (including checksums) shall be asterisks (ASCII code 2AH).
2. This 52 byte record shall be transmitted every 1.6 seconds ± 0.16 seconds.
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FORMAT C (108 BYTE ASCII STRING)
BYTE DESCRIPTION / FORMAT
1-51 Same as Format B described above except that in the Units of Measure field, “I =
Imperial Gallons” is undefined.
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 55
Break each decimal value into BCD representation. Using BCD arithmetic, sum the 3
BCD values and convert the lower-order BCD digit to an ASCII coded numeric digit.
56-58 True Airspeed (TAS, knots)
59
ASCII-coded decimal format as for IAS
True Airspeed Checksum
Sum for TAS bytes computed for IAS.
60-62 MACH (airspeed/speed of sound)
ASCII-coded decimal format with an implicit leading decimal point (least significant digit is thousands).
Example:
A MACH value of .492 would be sent as “294” (32H, 39H, 34H).
MACH Checksum 63
Sum for MACH bytes computed as for IAS.
64-69 Pressure Altitude (PALT, feet)
ASCII-coded decimal format with a sign character.
70
Example:
A PALT of 34500 feet would be sent as “00543+” (30H, 30H, 35H, 34H, 33H, 2BH).
Pressure Altitude Checksum
Sum for PALT bytes, excluding the sign character.
Example:
The sum for -850 feet would be “3” (33H).
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FORMAT C (108 BYTE ASCII STRING) - con’t
BYTE
71-76 Density Altitude (DALT, feet)
DESCRIPTION / FORMAT
77
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 (×C)
ASCII-coded decimal format with a sign character
Example:
An OAT of 25×C would be sent as “52+”.
Total Air Temperature Checksum 81
Sum for total air temperature bytes, excluding the sign byte, as for PALT.
82-84 Wind Direction (degrees from true North)
ASCII-coded decimal format
Example:
122 degrees would be sent as “22” (32H, 32H, 31H).
Wind Direction Checksum 85
Sum for wind direction bytes, as for IAS
86-88 Wind Speed (knots)
89
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:
7 right would be sent as “70R”, 14 left would be sent as “41L”.
KLN 94
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KLN 94
BYTE
93 Drift Checksum
FORMAT C (108 BYTE ASCII STRING) - con’t
DESCRIPTION / FORMAT
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 “012-” (30H, 31H, 32H, 30H,
2DH).
Rate of change of PALT checksum 99
100-
102
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
103 Magnetic Heading Checksum
104-
106
Sum for magnetic heading bytes, as for IAS
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 Static Air Temperature Checksum
Sum for static air temperature bytes, excluding the sign character, as for PALT.
108 ETX (ASCII code 03H)
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KLN 94
FORMAT D (121 BYTE ASCII STRING)
BYTE
1-
107
108-
112
DESCRIPTION / FORMAT
Same as Format C described above except that bytes 3 through 9 shall be filled with asterisks if total fuel remaining is not available and consequently must be entered through the KLN 94.
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 BCD representation. Using BCD arithmetic, sum the 4
BCD values and convert the lower-order BCD digit to an ASCII-coded numeric digit.
Example:
The checksum for a value of 29.83 would be “2” (32H).
Baro-corrected Altitude (feet) 114-
119
ASCII-coded decimal format with a sign character
Example:
A baro-corrected altitude of +11000 feet would be sent as “00011+” (30H, 30H, 30H,
31H, 31H, 2BH).
120 Baro-corrected Altitude Checksum
Sum for baro-corrected altitude bytes computed, excluding sign character, as for pressure altitude.
121 EXT (ASCII code 03H)
FUEL FLOW & AIR DATA CONFIGURATION
The fuel flow and air data equipment configuration can be setup on MNT 1 page.
1. Fuel flow equipment installed and Air data equipment not installed:
Any the above formats may be received. If format C or D is received, the airdata portions are ignored, the fuel data portions are used, and no error message is given.
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KLN 94
2. Fuel flow equipment not installed and Air data equipment installed:
If format C or D is received, fuel data portions are ignored, the airdata portions are used and no error message is given. If format A or B is received, the “GEN RS-232 In Data Error” message is displayed.
3. Both fuel flow equipment and air data equipment not installed:
If no data is received for this setup, the “No GEN RS-232 In Data” message will be displayed.
Fuel/Air Data Timing Requirement
A grace period of 2.4 seconds, in addition to the 1.6 second transmission interval, shall be given to every fuel/air data transmission. The unit invalidates all local copies if fuel/air data is not received for 4.0 seconds ± .40 seconds.
2.0 GENERAL RS232 OUT
Functional Description
BYTE FORMAT
Electrical per EIA RS 232C
9600 baud, 8 bits, 1 stop bit, no parity
MARK is a logical 1 (one) and SPACE is a logical 0 (zero)
START bit begins as MARK, goes to SPACE
The 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
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Data Protocol
Data shall be sent in blocks having the following format:
<STX><id><dddd><it><id><dddd><it>...<id><dddd><it><ETX>
<STX> ASCII start of text character
<id> item designator
<dddd> item data
<it> item terminator
<CR> ASCII carriage return character
<STX> ASCII end of text character
<STX> ASCII end of text character
<id> item designator
<dddd> item data
<it> item terminator
<CR> ASCII carriage return character
<STX> ASCII end of text character
KLN 94
Any data which is invalid or exceeds the data format will be filled with dashes.
RS232 OUTPUT DATA ITEM DEFINITIONS
There are two RS232 output data item definitions, as represented in the following tables. The first table
shows the Standard definitions, as selected on the MNT7 page (see paragraph 2.4.1.7
Item
Designator
A
Data
Format s dd mmhh
STANDARD RS232
Data Field
Width
9
Description present latitude; dash if position flag is set.
s=sign: N for North, S for South dd=degrees mm=minutes hh=hundreths of minutes
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KLN 94
STANDARD RS232
Item
Designator
B
C
D
E
G
(INDIA)
K
L
Q
T l
I
(lima) u w
Data
Format s ddd mmhh ddd ddd ddddd sdddd dddd ddddd dddd sddd
---A----dddddd free fromat ddsiiiiilllLLLLmm
Data Field
Width
10
3
3
5
5
4
5
4
4
6
17
Description present longitude; dash if position flag is set s=sign: E for East, W for West ddd=degrees mm=minutes hh=hundreths of minutes magnetic track, degrees; dash if GS is set groundspeed, knots; dash if position flag is set
10 x distance to active waypoint, nm; dash if
Nav Flag is set crosstrack error; dash if Nav Flag is set s=sign: R for aircraft position right of course, L for aircraft position left of course.
dddd=1000 x crosstrack error, nm
10 x magnetic desired track, degrees (use selected course in OBS mode); dash if Nav Flag is set.
active waypoint identifier
10 x magnetic bearing to active waypoint, degrees (use radial from active waypoint 180 in
OBS mode); dash if Position Flag is set.
magnetic variation; dash if Position Flag is set s=sign: E for East, W for West add=10 magnetic variation, degrees warnings; 4th character is “A” if estimated position error exceeds 3.8nm, otherwise “-”
10 x distance to destination, nm; dash if Nav
Flag is set for development testing only flight plan waypoint data; this item is sent for each waypoint in the active flight plan dd=waypoint number (01-25) s=sequence number bits: 76543210 xlannnnn x=unused, l=1 is last waypoint, a=1 if active wpt nnnnn=sequential number, unassigned binary iiiii=identifier
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Item
Designator a t j
Data
Format
Snnnnn hh:mm:ss abcdefghij
KLN 94
STANDARD RS232
Data Field
Width
17
8
10
Description baro-corrected external altitude input
S=sign: + or nnnnn=altitude, feet (to nearest foot); dash if not valid
UTC time of data
GPS discretes a=W for waypoint alert; T for turn; else dashed b=N for new message; P for persistent message; else dashed c=E for enroute; T for terminal; R for approach arm; or A for approach active d=L for leg; D for Direct-to; O for OBS; T for
OBS Æ LEG transition e=T for TO; F for FROM; else dashed fghij= reserved for future use; currently dashed
Item
Designator
A
B
C
D
E ddd ddd ddddd
Data
Format s dd mmhh s ddd mmhh
ENHANCED RS232
Data Field
Width
9
10
3
3
5
Description present latitude; dash if position flag is set.
s=sign: N for north, S for south dd=degrees mm=minutes hh=hundredths of minutes present longitude; dash if position flag is set.
s=sign: E for east, W for west ddd=degrees mm=minutes hh=hundredths of minutes magnetic track, degrees; dash if GS<2 kts or position flag is set. groundspeed, knots; dash if position flag is set.
10 ¥ distance to active waypoint, nm; dash if nav flag is set.
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Item
Designator
G
Data
Format sdddd
I (upper case INDIA) dddd
K
L ddddd dddd
Q j l q
T a sddd
---A----snnnnn hh:mm:ss dddddd ttfffff
KLN 94
ENHANCED RS232
Data Field
Width
5
4
5
4
4
9
6
8
6
7
Description crosstrack error; dash if nav flag is set.
s=sign: R for aircraft position right of course, L for aircraft position left of course dddd=100 X crosstrack error, nm
10 X magnetic desired track, degrees (use selected course in OBS mode); dash if nav flag is set.
active waypoint identifier
10 X magnetic bearing to active waypoint, degrees (use radial from active waypoint ±180° in OBS mode); dash if position flag is set.
magnetic variation; dash if position flag is set.
s=sign: E for east, W for west ddd=10 X magnetic variation, degrees warnings; 4th character is "A" if estimated position error exceeds 3.8 nm, otherwise "-" baro-corrected external altitude input s=sign: + or nnnnn=altitude, feet (to nearest foot); dash if not valid
UTC time of data hh=hours; mm=minutes; ss=seconds
10 X distance to destination, nm; dash if nav flag is set.
QuickTune™ frequency t = target radio f = frequency data
This item is sent once when a COMM or NAV frequency is selected for external QuickTune. It is not sent as part of the normal data stream.
This data shall be sent at the first available time slot on the bus. The time delay shall be no greater than one second.
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KLN 94
Item
Designator q
(cont) t u w ttfffff
Data
Format abcdefghij free format ddsiiiiilllLLLLmm
ENHANCED RS232
Data Field
Width
7
Description
Byte 1--System Type:
ASCII 0 is undefined
ASCII 1 = COM
ASCII 2 = NAV
ASCII 3 and above are currently undefined
10
17
Byte 2--System Number:
ASCII 0 is undefined
ASCII 1 = System 1
ASCII 2 = System 2
ASCII 3 = System 3
ASCII 4 = System 4
ASCII 5 and above are currently undefined
Bytes 3-7—Frequency:
This data is equal to (Frequency – 100) * 1000
It is assumed that all frequencies are in the
100-199 MHz range, so hundreds of megahertz are omitted.
GPS discretes a=W for waypoint alert; T for turn; else dashed b=N for new message; P for persistent
message; else dashed c=E for en route; T for terminal; R for
approach arm; or A for approach active d=L for LEG; D for direct-to; O for OBS; T for
OBS->LEG transition, V for VTF.
e=T for TO; F for FROM; else dashed fghij=reserved for future use; currently dashed for development testing only flight plan waypoint data
1,2,3
; this item is sent for each waypoint in the active flight plan dd=waypoint number (01 ~ 25) s=discretes
bits: 76543210
xladsgit t=0 leg follows; t=1 arc follows i=1 no-point-symbol in map (for invisible wpt ) g=1 gap follows (for visible non-connected wpt )
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KLN 94
Item
Designator w
(cont)
ENHANCED RS232
Data
Format ddsiiiiilllLLLLmm
Data Field
Width
17
Description s=1 active segment follows (for other magenta segments ) d=0 solid line; d=1 dashed line a=1 active wpt l=1 last waypoint x=unused iiiii=identifier (ASCII characters); a value of 7F hex in first byte indicates unknown ident, remaining bytes should be ignored.
lll=waypoint latitude; packed, unsigned binary values:
76543210 76543210 76543210 sddddddd xxmmmmmm xhhhhhhh s=sign: 0 for north, 1 for south ddddddd=degrees x=unused mmmmmm=minutes hhhhhhh=hundredths of minutes
A value of 7F hex in the first byte indicates that latitude and longitude are unknown, and remaining bytes should be ignored.
LLLL=waypoint longitude; packed, unsigned binary values:
76543210 76543210 76543210 76543210 sxxxxxxx dddddddd xxmmmmmm xhhhhhhh s= sign: 0=East 1=West, x=unused, d=degrees, m=minutes, h=hundredth mm=magnetic variation at waypoint
76543210 76543210 nnnnnnnn nnnnnnnn nnnnnnnnnnnnnnnn=Magnetic variation at waypoint
Two's complement binary in sixteenths of degrees.
Easterly variation is positive.
A value of 7FH in byte 16 indicates that magnetic variation is not presently available and bytes 16 and 17 should be ignored.
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Item
Designator x srr
Data
Format z
(lower case) aaaaa
KLN 94
ENHANCED RS232
Data Field
Width
3 Arc Description
Description
5 s= misc
bits: 76543210
xljnnnnn nnnnn=waypoint number –uns bin(01 ~ 25) j=1 “>180°“; j=0 “<180°“ l=1 clockwise; l=0 counterclockwise x=unused rr=100 X radius, nm; uns.binary (655.36 max)
Current GPS altitude in feet. If altitude is negative, this label shall format “-aaaa” (Note only four digits).
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KLN 94
THIS PAGE IS RESERVED.
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APPENDIX B
Includes the following:
KLN 94 SUPPLEMENTAL PROCEDURES MANUAL
KLN 94 FLIGHT MANUAL SUPPLEMENT
KLN 94
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KLN 94
FLIGHT MANUAL SUPPLEMENT PROCEDURE
For the installation of the KLN 94 GPS to be FAA approved for enroute and approach IFR operation, it is necessary for the installer to create a flight manual supplement that is unique for the installation and to submit that supplement to the FAA for approval.
Following, you will find a copy of the flight manual supplement created by Honeywell
International, Inc. for the initial STC installation of the KLN 94 in Mooney model M20C. Use this supplement as a guide in creating the supplement for your installation (do not copy the 006- part number in the footer). If your installation is interfaced to the same equipment (i.e. switches, annunciators, RMI, autopilot, etc.) as the initial installation, copy the guide supplement in its entirety, changing only the installers name and address, aircraft make and model, approval authorization and section titles/numbers to suit your circumstances as detailed below. More likely, if your installation is not identical to the initial installation, it will be necessary for you to determine the differences and alter your supplement accordingly. Elements of the supplement which may need to be altered for your installation are as follows:
1. FORMAT
The format of the finished supplement should match, as closely as possible, the format of the aircraft’s flight manual and/or pilot’s operating handbook. Sizing of your manual to match the aircraft’s flight manual is most easily accomplished by creating it first as an 8 1/2" X 11"
(standard typewriter size paper) document and then reducing that on a reducing copier to the size required before submitting it to the FAA for approval. (Most small aircraft have flight manuals of 5 1/2" X 8 1/2" size. This size has a different height/width ratio than the 8 1/2" X
11" size; the width is narrower. The guide supplement is proportioned correctly for reduction to 5 1/2" X 8 1/2" size; copy its proportions if you are planning to reduce your supplement).
The headers and footers of the guide supplement may be rearranged to match the format of your aircraft’s flight manual; however, most of the information shown is required on every page. The Honeywell part number should not appear in your supplement, but the footer should include the page number, in the format "PAGE _OF _", and the words "FAA
APPROVED" and a blank space for the date of the approval in place of the "ORIGINAL
ISSUE" of the guide supplement. The aircraft for which the supplement applies should also be identified by manufacturer and model number as shown on the aircraft’s serial data plate, i.e. Beech A36 or Piper PA-46-310P (not marketing name like Bonanza, Malibu, etc.).
Headers must identify the section of the supplement for that page. Additionally, we have found it useful to include identification of the system in the header for ease of pilot reference.
The section numbers and names in the guide supplement are typical of many aircraft; however, you should check the aircraft’s flight manual and match those section numbers and names when organizing your supplement.
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KLN 94
2. COVER
The cover page for your supplement should essentially be identical to the guide supplement with the following exceptions:
A. In the header, substitute the installers name and address (whoever is writing the flight manual supplement) in place of the name and address of Honeywell.
B. Substitute the manufacturer’s name and model number (as shown on the serial data plate) for your aircraft in place of the Mooney models listed.
C. In the second line of text, where the sample supplement states "is installed in accordance with STC SA00244WI-D.", substitute "is installed in accordance with unit Installation
Manual 006-_____-____ , Rev.__, and FAA Form 337 dated ." (Insert the part number and revision of the manual you have used).
D. Remove "CHRIS DURKIN, DAS Coordinator, Honeywell International, Inc." and
"DAS4CE" from below the FAA APPROVED line. (Your supplement will be approved by an FAA representative).
E. Remove the footer on the cover page. (The footer on the guide supplement cover page is for Honeywell internal reference only).
3. TABLE OF CONTENTS
If the section names and numbers of your aircraft’s flight manual do not match those of the sample flight manual supplement, you should arrange your Table of Contents and your supplement in accordance with the format of your aircraft’s flight manual.
4. BODY OF TEXT
The body of text for all sections other than NORMAL PROCEDURES should be copied in its entirety. The text for the NORMAL PROCEDURES section may vary depending on the equipment interfaced with the KLN 94. Some of the annunciators, switches and/or controls described in paragraph B may differ slightly or may not be included as part of your installation. Should this be the case, you will need to alter the text of this paragraph and its subparagraphs to accurately describe the operation of the KLN 94 as it exists in your installation. Do not include descriptions of annunciators, switches or controls not present in your installation. Make sure that the nomenclature on the items you do use matches the description in your flight manual supplement.
This concludes the procedure for writing a KLN 94 GPS Aircraft Flight Manual Supplement.
Reduce the pages as required to match the format of your aircraft’s flight manual, and you are ready to submit the new document to your local FAA representative for approval.
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THIS PAGE IS RESERVED.
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APPENDIX C
SUPPLEMENTAL TYPE CERTIFICATE
KLN 94
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KLN 94
THIS PAGE IS RESERVED
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APPENDIX D
DIRECT REPLACEMENT OF A KLN 89B WITH A KLN 94
KLN 94
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KLN 94
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KLN 94
If the aircraft is equipped with a Bendix/King KLN 89B GPS receiver, the KLN 89B unit can be removed and a KLN 94 unit installed. No changes to the existing mounting rack or electrical harness are required. However, if the KLN 89B is configured only for IFR Enroute operations, the
KLN 94 must be configured the same way.
The KLN 94 also has additional features, such as QuickTune™, which may be added. When the
KLN 94 additional features are utilized in existing KLN 89B installations, wiring harness changes will be necessary. See the KLN 94 wiring diagrams in this book.
Once the KLN 94 has been installed, a post installation checkout procedure must be performed.
Also see the KLN 89B / KLN 94 substitution letter following this page.
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THIS PAGE IS RESERVED.
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APPENDIX E
ENVIRONMENTAL QUALIFICATION FORMS
KLN 94
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THIS PAGE IS RESERVED.
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