Honeywell KT73 Mode S Transponder, KT73 User Manual 73im

Honeywell International Inc. Mode S Transponder, KT73 73im

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Date Submitted2002-11-07 00:00:00
Date Available2002-11-07 00:00:00
Creation Date2002-09-16 09:10:41
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Document Author: E050982

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INSTALLATION MANUAL
KT 73
MODE S
TRANSPONDER
MANUAL NUMBER 006-10563-0000
REVISION 0 OCTOBER, 2002
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WARNING
Prior to the export of this document, review for export license requirement is needed.
COPYRIGHT NOTICE
©2002 Honeywell International Inc.
Reproduction of this publication or any portion thereof by any means without the express written
permission of Honeywell is prohibited. For further information contact the manager, Technical
Publications, Honeywell, One Technology Center, 23500 West 105th Street Olathe KS 66061
telephone: (913) 782-0400.
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REVISION HISTORY
KT 73 Installation Manual
Part Number: 006-10563-XXXX
For each revision, add, delete, or replace pages as indicated.
REVISION: Rev 0, October/2002
ITEM
ACTION
New manual
No previous manual revision exists.
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TABLE OF CONTENTS
SECTION I
GENERAL INFORMATION
PARAGRAPH
PAGE
1.1
INTRODUCTION
1-1
1.2
EQUIPMENT DESCRIPTION
1-1
1.2.1
GENERAL DESCRIPTION
1-1
1.2.2
HARDWARE
1-1
1.2.3
FEATURES
1-2
1.3
TECHNICAL CHARACTERISTICS
1-3
1.3.1
KT 73 TECHNICAL CHARACTERISTICS
1-3
1.3.2
KT 73 RECEIVER CHARACTERISTICS
1-4
1.3.3
KT 73 TRANSMITTER CHARACTERISTICS
1-4
1.3.4
ANTENNA
1-5
1.4
UNITS AND ACCESSORIES SUPPLIED
1-6
1.4.1
CONFIGURATIONS AVAILABLE
1-6
1.4.2
KT 73 INSTALLATION KIT
1-6
1.5
ACCESSORIES REQUIRED, BUT NOT SUPPLIED
1-7
1.6
LICENSING REQUIREMENTS
1-8
1.7
INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
1-8
SECTION II
INSTALLATION
PARAGRAPH
PAGE
2.1
GENERAL INFORMATION
2-1
2.2
UNPACKING AND INSPECTING EQUIPMENT
2-1
2.3
EQUIPMENT INSTALLATION
2-1
2.3.1
GENERAL
2-1
2.3.2
AVIONICS COOLING REQUIREMENTS FOR PANEL MOUNTED EQUIPMENT
2-2
2.3.3
KT 73 INTERCONNECTION AND CABLE HARNESS FABRICATION
2-2
2.3.4
EQUIPMENT LOCATION
2-7
2.3.5
KT 73 INSTALLATION
2-8
2.3.6
MOLEX CONNECTOR ASSEMBLY PROCEDURE
2-9
2.3.7
POSITRONIC CONNECTOR ASSEMBLY PROCEDURE
2-10
2.4.1
TRANSPONDER SYSTEM CHECKOUT
2-51
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SECTION III
OPERATION
PARAGRAPH
PAGE
3.1
GENERAL
3-1
3.2
PROGRAMMING MODE
3-1
3.2.1
PROGRAMMABLE PARAMETERS
3-2
3.3
DETAILED OPERATING MODES
3-9
3.3.1
FUNCTIONAL MODES
3-9
3.3.2
FRONT PANEL OPERATION
3-15
3.3.3
BUILT IN TEST EQUIPMENT (BITE)
3-17
FIGURES
FIGURE
PAGE
2-1
CRIMPING TOOLS (MOLEX)
2-11
2-2
CRIMPING TOOLS (POSITRONIC)
2-15
2-3
KT 73 PINOUT DIAGRAMS
2-19
2-4
KT 73 INSTALLATION DRAWING
2-23
2-5
SINGLE KT 73 BASIC INTERCONNECTION DRAWING
2-25
2-6
SINGLE KT 73 WITH TIS INTERCONNECTION DRAWING
2-27
2-7
SINGLE KT 73 WITH ADLP OR ADS-B INTERCONNECTION DRAWING
2-29
2-8
SINGLE KT 73 WITH SERIAL ALTITUDE INPUTS INTERCONNECTION
DRAWING
2-31
2-9
DUAL KT 73 BASIC INTERCONNECTION DRAWING
2-33
2-10
DUAL KT 73 WITH SERIAL ALTITUDE INPUTS INTERCONNECTION DRAWING 2-37
2-11
RF CONNECTOR DRAWING
2-43
2-12
ACCEPTABLE CABLE CONNECTIONS DRAWING
2-45
2-13
CABLE CONNECTOR DRAWING
2-47
2-14
TYPE “N” AND “C” CONNECTOR ASSEMBLY DRAWING
2-48
2-15
BNC CONNECTOR ASSEMBLY DRAWING
2-49
3-1
KT 73 FRONT PANEL
3-1
3-2
KT 73 CONFIGURATION MENU
3-3
3-3
KT 73 FIRST 4 OCTAL DIGITS OF THE AIRCRAFT ADDRESS
3-5
3-4
KT 73 LAST 4 OCTAL DIGITS OF THE AIRCRAFT ADDRESS
3-5
3-5
KT 73 LOWER AND UPPER MAXIMUM AIRSPEED
3-6
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FIGURES (cont).
FIGURE
PAGE
3-6
KT 73 STANDBY MODE
3-10
3-7
KT 73 GROUND MODE
3-10
3-8
KT 73 ON MODE
3-11
3-9
KT 73 ALTITUDE MODE
3-12
3-10
KT 73 FLIGHT ID MODE
3-13
3-11
KT 73 TEST MODE
3-13
TABLES
TABLE
PAGE
2-1
INSPECTION/CHECK PROCEDURE
2-51
2-2
RAMP TESTS
2-53
3-1
BITE FAULT CODES
3-18
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SECTION I
GENERAL INFORMATION
1.1
INTRODUCTION
This manual contains information relative to the physical, mechanical, and electrical characteristics of the Honeywell KT 73 Mode S Transponder. Installation and operating procedures are also
included. Information relative to the maintenance, alignment, and procurement of the replacement
parts may be found in the KT 73 Maintenance/Overhaul Manual, P/N 006-15563-0000.
1.2
1.2.1
EQUIPMENT DESCRIPTION
General Description
The KT 73 General Aviation Mode S Transponder is designed to meet TSO-C112 for a Class 2A
ATCRBS/Mode Select Airborne Transponder System. It is a panel mounted transponder that fulfills the role of the airborne beacon equipment according to the requirements of the Air Traffic Radar Beacon System (ATCRBS). Its functionality includes replying to ATCRBS Mode A and C, Intermode and Mode S interrogations as well as handling Comm A and B Mode S Data Link protocols. The basic surveillance capability of the KT 73 satisfies the European Mode S mandate.
The KT 73 will pass Surveillance (UF 4 and 5) and Comm-A (UF 20 and 21) interrogations (minus
the 24 bit Aircraft Address) to the ADLP (Airborne Data Link Processor). It will also be capable of
receiving messages from the ADLP. It will also be capable of receiving messages from the ADLP
and sending the messages to the ground in Comm-B (DF 20 and 21) replies. The transponder/
ADLP will communicate using a RS-232 hardware interface and the RS-232 protocol developed
by Lincoln Labs. Other Mode S formats that the KT 73 can handle include Uplink Formats 0 and
11 and Downlink Formats 0, 4, 5, 11, 16, 17, and 18.
The KT 73 also provides Mode "C" or altitude reporting information. When the KT 73 is operated
in the "ALT" Mode and used in conjunction with an encoding altimeter, the flight level altitude is
displayed in addition to the 4096 code, and the altitude information is transmitted to the ground in
response to Mode "C" interrogations.
The Mode S function of the KT 73 will allow the ground station to individually select the aircraft by
its Aircraft Address assigned to the aircraft by the FAA.
When the "IDT" button is pressed, the current 4096 code and an additional special ident pulse are
transmitted by the KT 73 in response to a Mode A interrogation, to insure positive identification.
A test mode is also included in the KT 73 to confirm that the unit is operational.
The KT 73 implements the following DO-181C functions: Basic Transponder, Minimum Data Link
Transponder, and Extended Squitter Capability. The KT 73 implements its data link via an RS232 bus. The KT 73 does not support enhanced data link.
The KT 73 does not have full ELM capability and does not support Comm-D ELM protocol. The
KT 73 is not a TCAS-compatible transponder.
1.2.2
Hardware
The KT 73 features an all solid state transmitter with microprocessor control. Mode and Code selection are performed by the rotary knobs, and all functions including flight level altitude, 4096
code, and aircraft address are presented on the gas discharge display. The KT 73 is derived from
the KT 70 Mode S transponder and will retrofit into KT 70, KT 71, and KT 76C installations.
The KT 73 has a Gas Discharge Display, Mode Select Knob, VFR pushbutton, Ident pushbutton,
and four ident code selector knobs.
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The KT 73 has an Air/Ground discrete which, when connected to a strut switch on the aircraft, can
disable ATCRBS and Mode S All-Call replies when the aircraft is on the ground. A front panel
switch position, ’GND’, can also be used by the pilot instead of the strut switch.
1.2.3
Features
The KT 73 is capable of interfacing to the Traffic Information Service (TIS). This data link is intended to improve the safety and efficiency of “see and avoid” flight by providing the pilot automatic
display of nearby traffic and warnings of any potentially threatening conditions. The display of TIS
traffic requires a compatible MFD, currently the KMD 540. TIS is only provided within the service
volume of most Mode S terminal radar facilities and only in the contiguous United States (US).
The KT 73 is also capable of Automatic Dependent Surveillance - Broadcast (ADS-B) operation
which allows an aircraft or surface vehicle to transmit position, altitude, vector, and other information for use by other aircraft, surface vehicles, or ground facilities. ADS-B requires a source of
GPS data, currently the KLN 94/KLN 900 are the only acceptable sources. The KT 73 has the
capability to transmit extended squitters and to operate in the Extended Squitter/Non Transponder
mode.
NOTE:
ADS-B is not currently operational but may be at a
later date.
The KT 73 has the ability to enter and display an 8-digit alpha-numeric Flight ID code. The Flight
ID information is entered by the pilot via front panel controls or is received from an ADLP. Flight
ID is selected for display from the front panel.
When the KT 73 receives Mode A interrogations from the ground radar facility, it will transmit a
coded group of pulses which consist of a four digit identification number that has been assigned
by the Air Traffic Controller. This code is entered into the KT 73 by the pilot and is transmitted
back to the ground as a Mode "A" reply. This coded information is presented on the ground radar
display at the appropriate range and azimuth. The Air Traffic Controller can then identify each aircraft that is transponder equipped by its distinct coded number.
The VFR code, aircraft address, maximum air speed, display adjust, and installation parameters
can be programmed from the front panel of the KT 73 and stored in nonvolatile memory. Pilot adjustments include VFR code, Flight ID, and display brightness. Installation adjustments include
aircraft address, maximum airspeed, and configuration parameters (refer to Section 3 for specific
programming sequences). A configuration module is provided to store the address with the rack,
allowing units to be swapped from rack to rack without having to reprogram the aircraft address
or other configuration parameters.
NOTE:
The above features must be enabled via the programming mode.
The flight ID information can be entered by the pilot via front panel controls. Flight ID can be selected for display from the front panel.
The KT 73 has BITE (Built-In-Test-Equipment) which constantly monitors the operational health
of the unit. When a fault is detected, the transponder will display an error code on the front panel
display in order to help diagnose problems. When a critical fault is detected, the unit will turn on
an amber FAIL light on the front of the unit.
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1.3
TECHNICAL CHARACTERISTICS
1.3.1
KT 73 TECHNICAL CHARACTERISTICS
TSO COMPLIANCE:
SEE ENVIRONMENTAL QUALIFICATIONS APPENDIX
PHYSICAL DIMENSIONS:
See figure 2-4
WEIGHT:
See figure 2-4
APPLICABLE DOCUMENTS:
TSO-C112 Class 2A ARINC 718-4
RTCA DO-181C
RTCA DO-160D
ICAO DOC 9688-AN/952
ICAO ANNEX 10, AMENDMENT 71
RTCA DO-178B
RTCA DO-239
RTCA DO-260
EUROCAE ED-102
EUROCAE ED-14D
EUROCAE ED-73A
MOUNTING:
PANEL MOUNTED
TEMPERATURE:
-20 ° C TO +55 ° C
Canadian cold soak tested to -35 ° C
ALTITUDE RANGE:
51,500 FT
COOLING:
NO FORCED-AIR COOLING REQUIRED,
BUT RECOMMENDED.
VIBRATION:
DO-160D
CATEGORY S (CURVES B &M)
CATEGORY R (CURVE G)
ZONE 2
SHOCK:
RIGID MOUNTING 6 G OPERATIONAL 20 G CRASH
SAFETY.
POWER INPUT:
35 WATTS (MAX)
1.25 A @ 27.50 V DC
2.50 A @ 13.75 V DC
Lighting Current
320 mA @ 14 V
160 mA @ 28 V
NOTE:
All measurements are made with a 2.0 dB cable loss
at the antenna end.
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1.3.2
KT 73 RECEIVER CHARACTERISTICS
Sensitivity Variation with Frequency:
The RF input level required to produce 90% replies will not vary by more than 1 dB and will at no
time exceed a level of -69 dBm for standard ATCRBS interrogations in the frequency range between 1029.8 and 1030.2 MHz.
Bandwidth:
A standard ATCRBS interrogation signal required to trigger the transponder below 1005 MHz and
above 1055 MHz will be at least 60 dB stronger than that required to trigger the transponder at
1030 MHz with the same reply efficiency.
Sensitivity and Dynamic Range:
The minimum triggering level (MTL) is defined as the minimum input power level that results in a
90% reply ratio if the interrogation has nominal pulse characteristics.
A.
The MTL for ATCRBS and ATCRBS/Mode S All- Call interrogations will be -73
dBm ± 4 dB.
B.
The MTL for Mode S interrogations will be - 74 dBm ±3 dB.
C.
The reply ratio will be at least 99% for all Mode S interrogations between MTL +3
dB and -21 dBm and at least 90% for ATCRBS and ATCRBS/Mode S All-Call interrogations between MTL and -21 dBm.
D.
The variation of MTL between ATCRBS Mode A and Mode C interrogations will not
exceed 1 dB.
ATCRBS, Mode S,ATCRBS/Mode S All-Call Low-Level Reply Ratio:
The reply ratio will not be more than 10% for interrogations at signal levels below -81 dBm.
L.O. Leakage:
L.O. level at 970 MHz will not exceed -73 dBm.
1.3.3
KT 73 TRANSMITTER CHARACTERISTICS
Reply Transmission Frequency:
The transmitter frequency of the reply will be 1090 ±1 MHz when observed into a 50 ohm load with
a VSWR of 1.5:1 or less.
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RF Peak Power Output:
The transmitter output power will be 125 watts (21.0 dBW) peak power minimum and 500 watts
(27.0 dBW) peak power maximum at the terminals of the transponder antenna. The pulse amplitude variation between any two pulses in an ATCRBS reply will not exceed 1 dB. A Mode S reply
will not contain a pulse amplitude variation, between any two pulses, of greater than 2 dB.
ATCRBS Reply Rate Capability:
The transponder will be able to continuously generate at least 500 ATCRBS 15-pulse replies per
second and will have the capability of a peak reply rate of 1,200 ATCRBS 15-pulse replies for a
duration of 100 ms.
NOTE:
A 15-pulse reply includes 2 framing pulses, the 12 information pulses, and the SPI pulse.
Mode S Reply Rate Capability:
The transponder will have the capability of generating the following reply rates for short Mode S
downlink formats:
A.
50 Mode S replies in a 1 second interval.
B.
18 Mode S replies in a 100 ms interval.
C.
8 Mode S replies in a 25 ms interval.
D.
4 Mode S replies in a 1.6 ms interval.
The transponder will have the capability of generating the following reply rates for long Mode S
downlink formats:
A.
At least 16 of the 50 Mode S replies in any 1 second interval.
B.
At least 6 of the 18 Mode S replies in a 100 msec interval.
C.
At least 4 of the 8 Mode S replies in a 25 msec interval.
D.
At least 2 of the 4 Mode S replies in a 1.6 msec interval.
Unwanted Output Power:
The RF output power at 1090 MHz ±3 MHz, at the RF output of the transponder, will not exceed 50 dBm when the transmitter is in the inactive state. The inactive state is defined to include the
entire period between ATCRBS and/or Mode S transmissions less 10 µsec transition periods, if
necessary, preceding and following the extremes of the transmission.
1.3.4
ANTENNA
Any L-Band blade antenna is suitable for use with the KT 73 provided it is certified to TSO-C74c.
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1.4
1.4.1
UNITS AND ACCESSORIES SUPPLIED
CONFIGURATIONS AVAILABLE
P/N 066-01164-0101 is the only version of the KT 73 that is currently available. Included with the
KT 73 is the mounting rack and the configuration module. The configuration module is optional
but is strongly suggested. With the module, the installation unique configuration is maintained if
a different KT 73 is swapped into the aircraft.
1.4.2
KT 73 INSTALLATION KIT
The KT 73 Transponder installation kit P/N 050-03451-0000 contains the following parts:
050-03451-0000 INSTALL KIT KT 73 Rev. B
--------------------------------------------------------------SYMBOL
PART NUMBER
FIND NO DESCRIPTION
UM -0000
--------------------------------------------------------------030-00101-0002
PANEL MOUNT PLUG
EA
1.00
030-01094-0002
CONNECTOR 12/24 P
EA
1.00
030-01096-0000
KEY POLARIZER
EA
1.00
030-01107-0024
CONNECTOR TERM 24T EA
1.00
030-01407-0000
CONTACT FEMALE
EA
7.00
030-03454-0002
CONN, RECT, RECPT, EA
1.00
057-05944-0024
KT 73 INSTALL KIT
EA
1.00
089-02013-0037
NUT FLAT 6-32
EA
3.00
089-02147-0022
NUT LOCK 6-32
EA
2.00
089-02353-0001
NUT CLIP 6-32
EA
6.00
089-05903-0007
SCR PHP 4-40X7/16
EA
2.00
089-05907-0006
SCR PHP 6-32X3/8
EA
1.00
089-06012-0008
SCR FHP 6-32X1/2
EA
6.00
089-08016-0037
WSHR INTL LK #6
EA
2.00
089-08027-0030
WSHR FLT STD #6
EA
1.00
089-08094-0030
WSHR FLT STD .446
EA
1.00
089-08110-0034
WSHR SPLT LK #6
EA
1.00
089-08168-0002
WASHER WAVE
EA
1.00
090-00019-0007
RING RTNR .438
EA
1.00
091-00031-0005
NY CA CLAMP .312
EA
1.00
155-06046-0000
INSTALLATION DWG
RF
.00
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1.5
ACCESSORIES REQUIRED, BUT NOT SUPPLIED
The following parts are recommended for a cable setup with dimensions of 4.5 feet to 11 feet:
(See Figure 2-12, Sheet 1 of 2).
Honeywell PART NUMBER
DESCRIPTION
QUANTITY
030-00101-0002
Connector, Coax
024-00051-0060
Cable,Coax
11 ft.
030-00005-0000
Connector, Coax Mod Type BNC
The following parts are recommended for a cable setup with dimensions of 10 feet to 25 feet:
(See Figure 2-12, Sheet 2 of 2).
Honeywell PART NUMBER
DESCRIPTION
QUANTITY
030-00102-0001
Connector, Type Unit
024-00072-0000
Cable,Coax
25 ft.
030-00435-0000
Connector, Antenna
The following parts are recommended for a cable setup with dimensions of 16 feet to 32 feet (See
Figure 2-12, Sheet 2 of 2):
Honeywell PART NUMBER
DESCRIPTION
QUANTITY
030-00101-0002
Connector Type Unit
024-00051-0060
Cable, Coax
6 in.
024-00071-0000
Cable, Coax
32.5 ft.
030-00138-0000
Connector, Unit extension to antenna connector
6 in.
030-00434-0000
Connector, Antenna
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1.6
LICENSING REQUIREMENTS
For US registered aircraft, the transmitter, as installed in the aircraft, requires an Aircraft Radio
Station License. This license is obtained by filing the FCC Form 404. While awaiting the receipt
of the station license, a copy of FCC Form 404 must be kept in the aircraft.
This equipment has been type accepted by the FCC and entered on the type accepted equipment
list, as FCC ID: ASYKT73 and must be identified as FCC ID: ASYKT73 on your Form 404, Aircraft
Radio Station License application.
For non-US registered aircraft, follow applicable licensing requirements as required.
1.7
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 its 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 suggestions and factors to consider before installing the KT 73 Mode S Transponder. Close adherence to these suggestions will assure a more satisfactory performance from
the equipment.
The conditions and tests required for TSO approval of this article are minimum performance standards. It is the responsibility of those desiring to install this article either on or within a specific
type or class of aircraft to determine that the aircraft installation conditions are within TSO standards. The article may be installed only if further evaluation by the applicant documents an acceptable installation and is approved by the Administrator.
2.2
UNPACKING AND INSPECTING EQUIPMENT
Exercise extreme caution when unpacking the unit. Make a visual inspection of the unit for evidence of damage incurred during shipment. If a claim for a damage is to be made, save the shipping container to substantiate the claim. When all equipment is removed, place all packing materials in the shipping container for future storage or reshipment of the unit.
2.3
2.3.1
EQUIPMENT INSTALLATION
GENERAL
The following paragraphs contain information pertaining to the initial installation of the KT 73 Mode
S Transponder, including instructions concerning the location and mounting of the supporting antenna.
The equipment should be installed in the aircraft in a manner consistent with acceptable workmanship and engineering practices and in accordance with the instructions set forth in this publication.
To ensure that the system has been properly and safely installed in the aircraft, the installer should
make a through visual inspection and conduct an overall operational check of the system on the
ground prior to flight.
CAUTION:
AFTER INSTALLATION OF THE CABLING
AND BEFORE INSTALLATION OF THE
EQUIPMENT, A CHECK SHOULD BE MADE
WITH THE AIRCRAFT PRIMARY POWER
SUPPLIED TO THE MOUNTING CONNECTOR TO ENSURE THAT POWER IS APPLIED
ONLY TO THE PINS SPECIFIED IN THE INTERCONNECTION DRAWINGS, FIGURES 25 THRU 2-10.
The installation should be installed in accordance with standards established by the customer’s
installing agency and existing conditions as to unit location and type of installation. However, the
following suggestions should be considered before installing the system. Close adherence to
these suggestions will assure a more satisfactory performance from the equipment. The installing
agency will supply and fabricate all external cables. The connectors required are supplied by Honeywell.
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NOTE:
The TSO identifies the minimum performance standards, tests, and other conditions applicable for issuance of design and production approval of the article. The TSO applicant is responsible for documenting all limitations and conditions suitable for installation of the article. An applicant requesting approval
for installation of the article within a specific type or
class of product is responsible for determining environmental and functional compatibility.
2.3.2
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 or remote mounted. While modern day individual circuit designs consume much less electrical energy, the watts per cubic inch
dissipated within avionics units remains much the same because of high density packaging techniques utilized. Consequently, the importance of providing avionics stack cooling is essential to
the life span of the equipment.
While each individual unit may not require forced air cooling, the combined heat load of several
units operating in a typical avionics stack will significantly degrade the reliability of the avionics if
provisions for stack cooling are not incorporated in the initial installation. Recommendations on
stack cooling are contained in Honeywell Installation Bulletin #55. Failure to provide stack cooling
will certainly lead to increased avionics maintenance costs and may void the warranty.
2.3.3
KT 73 INTERCONNECTION AND CABLE HARNESS FABRICATION
2.3.3.1
General
The KT 73 Mode S Transponder receives primary power from the aircraft power source. Power
connections, voltage requirements, and circuit breaker requirements are shown on the interconnect diagrams (Figures 2-5 through 2-10).
The length of the wires to parallel pins should be approximately the same length, so that the best
distribution of current can be effected. Honeywell recommends that all wires, including spares as
shown on the interconnect diagram be included in the fabrication of the wiring harness. However;
if full wiring is not desired, the installer should ensure that the minimum wiring requirements for
the features and functions to be used have been incorporated.
When cables are installed in the aircraft, they must be supported firmly enough to prevent movement and should be carefully protected against chaffing. Additional protection should also be provided in all locations where the cable may be subjected to abuse.
In wire bundles, the cabling should not be tied tightly together as this tends to increase the possibility of noise pickup and similar interference. When routing cables through the aircraft the cables
should cross high level rf lines at right angles.
Prior to installing any equipment, make a continuity check of all wires and cables associated with
the system. Then apply power and check for proper voltages at system connectors, and then remove power before completing the installation.
The following guidelines are recommended:
(1)
The installing facility will supply and fabricate all external cables (see figures 2-1
through 2-3, 2-5 through 2-15). The required connectors are supplied as part of the
installation kit (P/N 050-03451-0000).
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(2)
The KT 73 must be kept a minimum of three feet from the antenna. Additionally, the
antenna coax cable should not be bundled with the other wiring harnesses to the KT
73.
(3)
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. The cables should be of a length to allow for a “maintenance loop”.
That is, the length should be adequate to access and extend the connectors aft of
the panel for future maintenance purposes. Excess cabling should be secured and
stowed by tie-wrapping until such maintenance is required.
(4)
The cables should be supported firmly enough to prevent movement. They should
be carefully protected wherever one may chafe against another or against some other object. Extra protection should be provided in all locations where the cables may
be subject to abuse. Shields on shielded wires should be grounded as shown on
the system interconnection diagrams.
(5)
Shields should be carried through any obstruction via a thru-bulkhead connector. If
shielding cannot be carried through by use of a bulkhead/connector pin, precautions
should be taken to ensure each segment of the shielded lead be grounded at only
one point. A ground connection of not more than two inches in length should be
used. The preceding discussion does not apply to coaxial and quadraxial cable.
(6)
Avoid routing cabling near high noise and high power sources.
(7)
Do not route the transponder antenna coax near ADF sense or loop antenna cables.
NOTE:
The total losses in the coaxial cable run and interconnects between the antenna and the KT 73 transponder must not be less than 1 dB and must not be
more than 2.1 dB at 1030MHz. Use Figures 2-5
through 2-10 as a reference and adhere to the dimensions prescribed in Figure 2-13.
2.3.3.2
Primary Power and Circuit Breaker Requirements and Wiring
The KT 73 transponder receives primary power from the aircraft power circuit breakers. The KT
73 is designed to operate over the range of 11-33V dc. Power connections, wire sizes, and circuit
breaker requirements are shown on the interconnection diagrams Figures 2-5 through 2-10.
2.3.3.3
Functional Pinout Descriptions
This section gives a brief description of the inputs and outputs of the KT 73 (refer also to figure 2-3). It is provided so that the installer can determine what aircraft specific wiring requirements
are needed in order to install the unit. Unless otherwise specified, pins not used are to be left
open.
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Main Connector - JKT73-1
Pin 1;
Pin 2;
Pin 3;
Pin 4;
Pin 5;
Pin 6;
Pin 7;
Pin 8;
Pin 9;
Pin 10;
Pin 11;
Pin 12;
Pin A;
Pin B;
Pin C;
AIRCRAFT GROUND
This pin provides an internal connection to chassis and may be used as the third wire
for RS-232 busses.
+14 V DC LIGHTING
+14 VDC lighting (320mA ± 32 mA) Open for +28 V DC lighting.
+28 V DC LIGHTING
+28 VDC lighting (160mA ± 16 mA). Ground for +14 V DC lighting.
ARINC SUPPRESSION I/O
As an input, a voltage ≥ 18 V and ≤ 70 V will cause suppression. A steady state voltage
≥ 18 V will cease suppression. As an output, this pin will go ≥ 18 V when the
transponder transmits. This pin conforms to ARINC 718A Attachment 6.
EXTERNAL AIR/GROUND
GND (<10 ohms) on this pin will inhibit ATCRBS replies and replies to Mode S All Call
messages.
TIS 429 TX B
This line is half of a standard differential ARINC 429 output used to broadcast traffic
information services to a display.
RS232 ALT RX
This line is programmable as the receive line of an RS-232 port used to report altitude.
GILLHAM ALTITUDE D4/RS232 ALT TX
This line is programmable as a Gillham altitude input or as the transmit line of an
RS-232 port used to report altitude. As a Gillham input, HIGH = voltage > 18.5 VDC
or resistance-to-ground > 100KΩ. Per ARINC 572, Attachment 4, input is an active
LOW pulse where LOW = voltage < 2.0 volts or resistance-to-ground < 15 KΩ.
9 V SUPPRESSION IN
This line is a 9V Suppression Input. Voltage ≥ 5 will suppress. Voltage < 3.5V or an
open will not suppress the transponder.
EXTERNAL STANDBY~
GND (<10 ohms) on this pin will prevent replies and squitters.
11 - 33 V DC
Aircraft Power
11 - 33 V DC
Aircraft Power
AIRCRAFT GROUND
This pin provides an internal connection to chassis and may be used as the third wire
for RS-232 busses.
GILLHAM ALTITUDE B4/RS232 GPS RX
This line is programmable as a Gillham altitude input as defined for pin 8 or as the
receive line of an RS-232 port used to receive GPS information to support ADS-B.
GILLHAM ALTITUDE B2/RS232 GPS TX
This line is programmable as a Gillham altitude input as defined for pin 8 or as the
transmit line of an RS-232 port used to receive GPS information to support ADS-B.
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Pin D;
Pin E;
Pin F;
Pin H;
Pin J;
Pin K;
Pin L;
Pin M;
Pin N;
GILLHAM ALTITUDE C1/ARINC429 RX 0B
This line is programmable as a Gillham altitude input as defined for pin 8 or as the
receive line of an ARINC 429 port used to report altitude.
GILLHAM ALTITUDE B1/ARINC429 RX 0A
This line is programmable as a Gillham altitude input as defined for pin 8 or as the
receive line of an ARINC 429 port used to report altitude.
EXTERNAL IDENT~
GND (<10 ohms) will initiate IDENT sequence. HIGH = resistance-to-ground > 100KΩ
(inactive IDENT).
GILLHAM ALTITUDE C4/RS485 RX B
This line is programmable as a Gillham altitude input as defined for pin 8 or as the
receive line reserved for a future interface.
GILLHAM ALTITUDE A4/RS485 RX A
This line is programmable as a Gillham altitude input as defined for pin 8 or as the
receive line reserved for a future interface.
GILLHAM ALTITUDE A2/RS485 TX B
This line is programmable as a Gillham altitude input as defined for pin 8 or as the
transmit line reserved for a future interface.
GILLHAM ALTITUDE C2/RS485 TX A
This line is programmable as a Gillham altitude input as defined for pin 8 or as the
transmit line reserved for a future interface.
GILLHAM ALTITUDE A1
This line is programmable as a Gillham altitude input as defined for pin 8.
TIS 429 TX A
Standard ARINC 429 output used to broadcast traffic information services to a display.
Auxiliary Connector - JKT73-2
Pin 1;
Pin 2;
Pin 3;
Pin 4;
Pin 5;
Pin 6;
Pin A;
Pin B;
EXTERNAL EEPROM CS
Voltage ≥ 2.0 VDC selects external EEPROM.
EXTERNAL EEPROM
Voltage ≥ 2.0 VDC indicates external EEPROM is available.
AUDIO HI
Message audio output.
+5 V DC
This pin provides +5 VDC ± 0.3 VDC out to power external EEPROM.
AUDIO LO
Message audio output.
AUDIO INHIBIT
Mutes audio with input of <3.0 V DC or < 10 ohms. Input > 100 K ohms will not mute.
SERIAL DATA OUT
Used by microprocessor to write data to external EEPROM.
SERIAL DATA IN
Used by microprocessor to read data from external EEPROM.
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Pin C;
Pin D;
Pin E;
Pin F;
SERIAL CLOCK
Used by microprocessor to provide serial clocking for pins A and B.
AIRCRAFT GROUND
This pin provides an internal connection to chassis and may be used as the third wire
for RS-232 busses.
ARINC429 RX 1A/RS232 RX
Programmable line to receive ARINC 429 TIS control or provide RS-232 RX input for
either ADLP or ADS-B.
ARINC429 RX 1B/RS232 TX
Programmable line to receive ARINC 429 TIS control or provide RS-232 TX output for
either ADLP or ADS-B.
Antenna Connector - JKT73-3
Pin 1;
RF RX/TX PORT
Receive at 1030 MHz ± 0.01 MHz; Transmit at 1090 MHz ± 1.00 MHz.
External Connector - JKT73-4
Pin A;
Pin B;
Pin C;
Pin D;
Pin E;
Pin F;
AUDIO INHIBIT
Mutes audio with input of <3.0 V DC or < 10 ohms. Input > 100 K ohms will not mute.
This input is designed for installations including an EGPWS system. In that case, the
Audio Out discrete of the EGPWS must be connected to this pin.
AIRCRAFT GROUND
This pin provides an internal connection to chassis and may be used as the third wire
for RS-232 busses.
ARINC429 RX 1A/RS232 RX
Programmable line to receive ARINC 429 TIS control or provide RS-232 RX input for
either ADLP or ADS-B.
ARINC429 RX 1B/RS232 TX
Programmable line to receive ARINC 429 TIS control or provide RS-232 TX output for
either ADLP or ADS-B.
AUDIO HI
Message audio output.
AUDIO LO
Message audio output.
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2.3.4
EQUIPMENT LOCATION
Care should be exercised to avoid mounting components near equipment operating with high
pulse current or high power outputs such as radar and satellite communications equipment. In
general, the equipment should be installed in a location convenient for operation, inspection, and
maintenance, and in an area consistent with the TSO environmental limits.
Refer to the mechanical installation drawing (figure 2-4), cable and connector assembly diagrams
(figures 2-1, 2-2, 2-11 through 2-15, interconnection drawings (figures 2-5 through 2-10), and connector pin assignments diagrams (figure 2-3) as required. Determine the mounting location for
system components following the guidelines below.
2.3.4.1
Transponder And Mounting Tray Locations
The tray-mounted KT 73 Mode S Transponder can be installed in any convenient location on the
panel that is free from excessive heat and vibration and which provides reasonable access for inspection and maintenance. To achieve maximum performance, the KT 73 should be installed adjacent to other receivers with similar functions.
To allow for inspection or repair of the wiring of the connector assembly itself, sufficient lead length
should be left so that when the mounting hardware for the rear connectors and antenna coaxial
cable is removed the assembly may be pulled forward several inches. Also, a bend should be
made in the harness (at the rear connectors) to allow water droplets that might form on the harness due to condensation, to drip off at the bend and not collect in the connection.
Except for antenna cables, (see Figure 2-12) the lengths of the cables from the KT 73 transponder
mounting tray connector to other system units are not critical because unit interfaces are designed
with high impedance inputs, low impedance outputs, and low noise susceptibility characteristics.
Forced air cooling is recommended but is not a requirement. Outline drawing Figure 2-4 shows
transponder and mounting tray dimensions.
2.3.4.2
Antenna
The antenna should be well removed from other antenna projections, the engine(s), and propeller(s). It should also be well removed from landing gear doors, access doors, or other openings
which will break the ground plane for the antenna. The surface directly beneath the antenna
should be a flat plane over as large an area as possible.
A back-up plate should be used for added strength on thin-skinned aircraft.
To prevent rf interference, the antenna must be physically mounted a minimum distance of three
feet from the KT 73 and the wiring harness.
The transponder antenna should be mounted a minimum of six feet away from the DME antenna
and four feet from the ADF sense antenna.
Where practical, plan the antenna location to keep cable lengths as short as possible and avoid
sharp bends in the cable to minimize the VSWR.
Avoid running other cables or wires near the antenna cable.
On pressurized aircraft, the antenna should be sealed using RTV No. 3145 (P/N 016-01082-0000)
or equivalent around the connector and mounting hardware.
The antenna mounting should be sealed from the outside for moisture protection using RTV or
equivalent.
Mount the antenna in as clean as environment as possible, away from exhaust gases and oils.
The antenna should be kept clean. If left dirty (oil covered), the range of the transponder may be
affected.
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2.3.5
KT 73 INSTALLATION
The mounting tray for the transponder should be mounted using the dimensions specified in the
outline and mounting drawing, Figure 2-4. The mounting tray should be wired according to the
system interconnect diagram, Figure 2-5 through 2-10.
2.3.5.1
Retrofit into existing KT 70, KT 71, and KT 76C Installations
If the KT 73 is replacing an existing KT 70, KT 71, or KT 76C without adding new functionality such
as TIS, ADLP, or ADS-B, the KT 73 may simply be installed in the existing rack, provided that the
installation is in a fixed wing aircraft. If the installation is in a rotary wing aircraft, the existing rack
will have to be replaced with a new rack. If the new rack in installed, it is suggested that a new
configuration module be used even if the existing installation did not have one. The KT 73 must
be programmed per section 3.2.
2.3.5.2
New Transponder Tray Installations
(1)
Rear connector wiring must be completed before permanently fastening the mounting tray to the panel.
(2)
Remove the panel area specified on the outline and mounting drawing (see Figure
2-4) for front and rear dimensions. Care must be taken to avoid damage to the adjacent equipment and cables.
(3)
Secure the tray to the panel. The mounting tray must be secured in the rear by attaching the tray to a structural member of the airframe.
(4)
Look at the bottom of the unit and confirm the front lobe of the hold-down device is
in a vertical position. This can be accomplished by using a 3-32 inch Allen wrench
through the front plate.
2.3.5.3
Transponder
(1)
Slide the transponder into the tray until the front lobe touches the mounting tray.
(2)
Turn the Allen wrench clockwise until the rear lobe engages the mounting tray slot.
Continue turning the wrench clockwise until tight.
(3)
For removal, turn the 3-32 inch Allen wrench counter-clockwise until the unit disengages from the mounting tray slot. The unit can now be pulled completely out.
CAUTION:
DO NOT OVERTIGHTEN THE LOCKING FASTENER
2.3.5.4
Aircraft Address Programming Options
The Mode S aircraft address and maximum airspeed data must be programmed for use by the KT
73. In installations having an external EEPROM module (also referred to as a Configuration Module), this information is contained in that module as well as in the memory internal to the KT 73.
In these cases, the data in the external Configuration Module will automatically be copied into the
internal memory of any KT 73 plugged into the rack. This assumes that the external module has
been previously programmed by a KT 73 as described elsewhere in this manual.
Data that has been programmed into an external Configuration Module as part of a KT 70 installation will be automatically replaced by data contained in the internal memory of the KT 73. All
new installations will have a Configuration Module as these installations use a new rack (P/N 20010069-0000) which includes the Configuration Module.
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In retrofit installations where a Configuration Module does not exist, the KT 73 will recognize this
condition and operate from the data contained in the internal memory. In this arrangement, the
configuration data will be lost when the KT 73 is replaced with a different unit, such as a loaner,
and must be re-entered.
NOTE:
THE AIRCRAFT MODE S ADDRESS MUST BE OBTAINED FROM FAA AND PROGRAMMED INTO
THE KT 73 OR EXTERNAL ADDRESS EEPROM.
FOR US REGISTERED AIRCRAFT, THE ICAO
AIRCRAFT ADDRESS CODE CAN BE FOUND ON
THE AIRCRAFT REGISTRATION.
AIRCRAFT MODE S ADDRESSES MAY BE OBTAINED BY CALLING THE FAA AIRMAN AND AIRCRAFT REGISTRY DIVISION AT (405)-954-3116.
IF THREE (3) OR MORE ADDRESSES ARE NEEDED,
WRITE TO AIRCRAFT REGISTRATION
BRANCH, ANV-450, P.O. BOX 25082, OKLAHOMA
CITY, OK 73125.
To program the aircraft address and/or the maximum air speed please refer to Section 3.2.
2.3.5.5
Antenna
For L-band blade antenna outline drawing, installation procedures, and mounting dimensions, refer to the manufacturer’s instructions.
2.3.6
MOLEX CONNECTOR ASSEMBLY PROCEDURE
The KT 73 uses a special connector that mates directly with the printed circuit board inside the
unit (see Figure 2-1). Assemble the connector using the following procedure:
2.3.6.1
Solderless Contact Terminal Assembly using Molex Crimper
Refer to instructions in Figure 2-1.
2.3.6.2
Solderless Contact Terminal Assembly using Pliers
(1)
Strip each wire 5/32 inches for contact terminal (P/N 030-01107-0024). The last two
digits of the contact terminal part number indicates the number of terminals furnished.
(2)
Tin the exposed conductor.
(3)
Using needle nosed pliers, fold over each conductor tab, in turn, onto the exposed
conductor. when both tabs have been folded, firmly press the tabs against the conductor.
(4)
Repeat step (3) for insulator tabs.
(5)
Apply a small amount of solder (using minimum heat) to the conductor/tab connection to assure a good electro-mechanical joint.
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2.3.6.3
Contact Insertion into Molex Connector Housing
(1)
After the contact terminals have been installed on the wiring harness, the contact
terminals can be inserted into the proper location in the connector housing (P/N 03001094-0066). The terminal cannot be inserted upside down. Be sure to push the
terminal all the way in, until a click can be heard or felt.
(2)
The self-locking feature can be tested by gently pulling on the wire.
2.3.6.4
2.3.7
Extraction of Contact from Molex Connector
(1)
Slip the flat narrow blade of a Molex contact ejector tool, HT-1884 (Honeywell P/N
047-05099-0001), under the contact on the mating side of the connector. By turning
the connector upside down one can see the blade slide to the stop.
(2)
When the ejector is positioned against the stop the locking key of the contact is
raised, allowing the contact to be removed by pulling moderately on the lead.
(3)
Neither the contact or position is damaged by removing a contact; however, the contact should be checked visually before reinstalling in connector, to be certain that retaining tab "A" extends as shown (see Figure 2-1) for retention in connector.
POSITRONIC CONNECTOR ASSEMBLY PROCEDURE
Assemble the Positronic connector using the procedures detailed in figure 2-2.
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FIGURE 2-1 CRIMPING TOOLS (MOLEX)
(Sheet 1 of 3)
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FIGURE 2-1 CRIMPING TOOLS (MOLEX)
(Sheet 2 of 3)
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Once the terminal is in the correct position, close the jaws gently until the terminal is held loosely in place. Push the wire
stop down so that it rests snugly behind the contact portion of the terminal.
Strip off 1/8 inch of the wire insulation and insert the wire through the insulation tabs into the conductor tabs until the insulation hits the conductor jaw face or until the conductor touches the wire stop.
Squeeze the handles until the crimp jaws close and the ratchet releases.
Straighten the terminal if necessary, then release the plier grips and remove the crimped terminal.
CRIMPING PRESSURE ADJUSTMENT
If too much or too little pressure is needed to release the crimper’s ratchet pawl at the end of the crimp stroke, the ratchet
can be easily adjusted. A spanner wrench provided with the tool can be used to loosen the lock nut, and rotate the keyed
stud clockwise for increased pressure and counter-clockwise for decreased pressure. Once the desired pressure has been
set, the lock nut must be tightened again. Newer models may have a screwdriver adjustment.
FIGURE 2-1 CRIMPING TOOLS (MOLEX)
(Sheet 3 of 3)
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FIGURE 2-2 CRIMPING TOOLS (POSITRONIC)
(Sheet 1 of 3)
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FIGURE 2-2 CRIMPING TOOLS (POSITRONIC)
(Sheet 2 of 3)
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FIGURE 2-2 CRIMPING TOOLS (POSITRONIC)
(Sheet 3 of 3)
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Main Connector - JKT73-1 Front View
Pin #
I/O ............................Description
10
11
12
O........................... AIRCRAFT GROUND
I............................. +14 V DC LIGHTING
I............................. +28 V DC LIGHTING
I/O......................... ARINC SUPPRESSION I/O
I ................................EXTERNAL AIR/GROUND
O ..............................TIS 429 TX B
I ................................RS232 ALT RX
I ................................GILLHAM ALTITUDE D4/RS232 ALT TX
I ................................9 V SUPPRESSION IN
I ................................EXTERNAL STANDBY~
I ................................11-33 V DC
I ................................11-33 V DC
O........................... AIRCRAFT GROUND
I ................................GILLHAM ALTITUDE B4/RS232 GPS RX
I ................................GILLHAM ALTITUDE B2/RS232 GPS TX
I ................................GILLHAM ALTITUDE C1/ARINC 429 RX 0B
I ................................GILLHAM ALTITUDE B1/ARINC 429 RX 0A
I ................................EXTERNAL IDENT~
I ................................GILLHAM ALTITUDE C4/RS485 RX B
I ................................GILLHAM ALTITUDE A4/RS485 RX A
I ................................GILLHAM ALTITUDE A2/RS485 TX B
I ................................GILLHAM ALTITUDE C2/RS485 TX A
I ................................GILLHAM ALTITUDE A1
O ..............................TIS 429 TX A
FIGURE 2-3 KT 73 Pinout Diagrams
(Sheet 1 of 3)
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Auxiliary Connector - JKT73-2 Front View
Pin
I/O......................... Description
O........................... EXTERNAL EEPROM CS
I............................. EXTERNAL EEPROM
O........................... AUDIO HI
O........................... +5 V DC
O........................... AUDIO LO
I............................. AUDIO INHIBIT
O........................... SERIAL DATA OUT
I............................. SERIAL DATA IN
O........................... SERIAL CLOCK
O........................... AIRCRAFT GROUND
I............................. ARINC429 RX 1A/RS232 RX
I/O......................... ARINC429 RX 1B/RS232 TX
Antenna Connector - JKT73-3
Pin
I/O......................... Description
I/O......................... RF RX/TX PORT
FIGURE 2-3 KT 73 Pinout Diagrams
(Sheet 2 of 3)
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External Connector - JKT73-4 Front View
Pin
I/O......................... Description
I............................. AUDIO INHIBIT
O........................... AIRCRAFT GROUND
I............................. ARINC429 RX 1A/RS232 RX
I/O......................... ARINC429 RX 1B/RS232 TX
O........................... AUDIO HI
O........................... AUDIO LO
FIGURE 2-3 KT 73 Pinout Diagrams
(Sheet 3 of 3)
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FIGURE 2-4 KT 73 INSTALLATION DRAWING
(Dwg. 155-06046-0000 Rev. D)
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FIGURE 2-5 SINGLE KT 73 BASIC INTERCONNECTION DRAWING
(Dwg. 155-01689-0001 Rev. -)
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FIGURE 2-6 SINGLE KT 73 WITH TIS INTERCONNECTION DRAWING
(Dwg. 155-01689-0002 Rev. -)
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FIGURE 2-7 SINGLE KT 73 WITH ADLP OR ADS-B INTERCONNECTION DRAWING
(Dwg. 155-01689-0003 Rev. -)
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FIGURE 2-8 SINGLE KT 73 WITH SERIAL ALTITUDE INPUTS INTERCONNECTION DRAWING
(Dwg. 155-01689-0004 Rev. -)
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FIGURE 2-9 DUAL KT 73 BASIC INTERCONNECTION DRAWING
(Dwg. 155-01689-0005 Rev. -, Sheet 1 of 2)
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FIGURE 2-9 DUAL KT 73 BASIC INTERCONNECTION DRAWING
(Dwg. 155-01689-0005 Rev. -, Sheet 2 of 2)
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FIGURE 2-10 DUAL KT 73 WITH SERIAL ALTITUDE INPUTS INTERCONNECTION DRAWING
(Dwg. 155-01689-0006 Rev. -, Sheet 1 of 3)
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FIGURE 2-10 DUAL KT 73 WITH SERIAL ALTITUDE INPUTS INTERCONNECTION DRAWING
(Dwg. 155-01689-0006 Rev. -, Sheet 2 of 3)
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FIGURE 2-10 DUAL KT 73 WITH SERIAL ALTITUDE INPUTS INTERCONNECTION DRAWING
(Dwg. 155-01689-0006 Rev. -, Sheet 3 of 3)
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FIGURE 2-11 RF CONNECTOR DRAWING
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FIGURE 2-12 ACCEPTABLE CABLE CONNECTIONS DRAWING
(Sheet 1 of 2)
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FIGURE 2-12 ACCEPTABLE CABLE CONNECTIONS DRAWING
(Sheet 2 of 2)
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FIGURE 2-13 CABLE CONNECTOR DRAWING
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PART NUMBER
024-00075-0000
024-00051-0060
SIZE
RG/U CABLE
393
400
DIMENSION
9/32 1/8 5/32 3/64
9/32 1/8 5/32 3/64
FIGURE 2-14 TYPE “N” AND “C” CONNECTOR ASSEMBLY DRAWING
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FIGURE 2-15 BNC CONNECTOR ASSEMBLY DRAWING
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2.4.1
TRANSPONDER SYSTEM CHECKOUT
The post-installation test is used to apply power and functionally checkout the system. Successful
completion of the post-installation test verifies the proper operation of the KT 73 Mode S Transponder System.
Table 2-1 is a visual inspection/check procedure that should be performed after system installation
as part of a system checkout. A post-installation test per paragraph 2.4.1.2 should be performed.
In addition, the procedure should be used as a periodic maintenance inspection check.
EQUIPMENT
INSPECTION/CHECK PROCEDURE
KT 73 Mode S
A. Inspect external surface for damage.
Transponder
B. Check that the unit is securely installed and that retaining
mechanism is securely tightened.
C. Ensure that all connections in the mounting tray are properly
mounted and secure.
Antennas
A. Inspect external surfaces for damage.
B. Check that antenna is properly mounted and mounting screws
are tight.
C. Ensure that antenna coaxial cable connectors are properly mated
and secure.
TABLE 2-1 INSPECTION/CHECK PROCEDURE
2.4.1.1
Inspection
Perform the following inspection on the overall system:
(1)
Check that cables do not interfere with aircraft controls or other equipment.
(2)
Check cabling for proper routing and check security of tie-down points. Inspect and
adjust cable runs to ensure that cables are not strained, kinked, or severely twisted
and are not exposed to rough or sharp surfaces.
2.4.1.2
Post-Installation Checkout/Operation
(1)
General
Installation of the transponder system requires three stages of testing to ensure the
proper operation of the Mode S transponder. Initially, prior to the installation of the
transponder and antenna, a system interwiring check should be performed. This
check verifies that the aircraft and all transponder interconnections are correct, before power is applied. After the units are installed a visual inspection of the equipment and connections is made. Finally, a ramp test is performed.
(2)
System Interwiring Check
To check the aircraft and transponder system interconnections proceed as follows:
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(3)
(a)
Check that all cables and interwiring are installed in accordance with the Interwiring and Cable Harness Fabrication instructions (paragraph 2.3.3).
(b)
Using the interconnect diagram (see Figure 2-5 through 2-10), check wiring
for proper destination, opens, and shorts.
(c)
Check rf cables for insertion loss and VSWR.
Visual Inspection
In conjunction with system installation, perform the inspection/check procedure (Table 2-1 in this section).
(4)
Post-Installation Test
The Post-Installation Test verifies the proper operation of the KT 73 Mode S Transponder System. Utilizing the self-test function and a ramp tester, this procedure is
used after the system units have been installed and thereafter as an operational
check. This procedure is comprised of a pretest setup, manual test and ramp test.
The following tests are performed on the ground.
(a)
(b)
Pretest Setup
Check KT 73 system source power as follows:
1)
Confirm that aircraft 11-33V dc is operational.
2)
Confirm that the aircraft panel background lighting power source is operational by adjusting the cockpit dimmer switch for proper cockpit panel
illumination.
Operate appropriate aircraft circuit breakers and switches to apply power to
the system as follows:
1)
Apply 11-33V dc to Mode S transponder #1 and if applicable transponder #2.
2)
Apply primary power inputs to all equipment that interfaces with the transponder(s) per the system configuration.
(c)
Verify that all KT 73 circuit breakers are closed.
(d)
Allow one minute for warm-up.
(e)
Verify the 4096 code is annunciated on the ATC IDENT code display with
mode select switch in the "ON" position.
(f)
Verify that "GND" is annunciated with the mode selector switch in the "GND"
position.
(g)
Self-Test
Refer to 3.3.3 (Section III) for Built In Test Equipment (BITE) procedures.
(h)
Manual Test
This test checks the ATC IDENT code switches and display.
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(5)
1)
Rotate ident code selector knob. Verify the most significant digit increases from zero to seven with clockwise rotation and decreases with a
counter-clockwise rotation.
2)
Repeat step 1) for the remaining three digits of the squawk code.
3)
Momentarily push the IDENT switch to store the selected code. (The
code will automatically be stored after a five second period if Ident switch
is not momentarily pushed.)
Conformity Inspection
Visually inspect the installed equipment to determine the use of acceptable workmanship and engineering practices. Verify that all mechanical and electrical connections have been made properly.
(6)
Ramp Test (see section 2.4.1.3, 2.4.1.4)
The following test will be conducted to verify operation.
1)
Aircraft Address and Maximum Airspeed Verification.
Verify that the correct Aircraft Address and Maximum Airspeed has been programmed correctly.
The Aircraft Address may be verified when the KT 73 is first powered on. See
Section 3.2.1 for details.
2)
Reply Frequency
Verify that the reply frequency is 1090 ± 1 MHz.
2.4.1.3
Ramp Test (Per AC 20-131A)
This test requires the use of a Mode S Ramp Tester. Specific instructions for operating the ramp
tester are contained in the applicable operator’s manual. In systems with dual transponders and
altitude sources configure the system to check each function. Table 2-2 lists tests that will be performed during ramp testing. In addition, Table 2-2 contains a brief description of each test and the
pass/fail criteria.
TEST
DESCRIPTION
PASS/FAIL
CRITERIA
RF Power Output
Measures the effective radiated power
output from the antenna.
Minimum of 125 watts.
RF Frequency
Measures the transmit frequency
1090 MHz ±1 MHz
ATCRBS Receiver
Sensitivity
Measures the receiver minimum triggering
level (MTL) for a 90% reply rate.
-74 dBm ±3.0 dBm
Mode S
Reply Delay
Measures the time difference between the
transponder interrogation and reply.
128 µsec ± 0.25 µsec.
TABLE 2-2 RAMP TESTS
(Sheet 1 of 2)
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TEST
DESCRIPTION
PASS/FAIL
CRITERIA
Mode S
Reply Jitter
Measures transmitted pulse to pulse
time variations.
0.05 µsec.
ATCRBS
SLS Level
Checks sidelobe suppression function by
varying the SLS pulse level and monitoring
transponder reply rates.
Reply if P1 exceeds P2 by
9 dB or more. No reply if
P2 equals or exceeds P1
ATCRBS Reply
Verifies transponder replies to Mode A and
C interrogations. Measures F1 to F2 spacing and duration of pulses.
Replies to interrogations.
F1 to F2 spacing, 20.3 µsec
±0.1 µsec. F1 and F2 pulse
width, 0.45 µsec ± 0.10
µsec.
ATCRBS Only
All-Call
Verifies that the Mode S transponder does
not respond to Mode A only or Mode C
only interrogations.
No reply.
Mode S All-Call
Verifies that the transponder replies, with
the proper address, to a Mode S All-Call
interrogation.
Proper reply address.
Invalid Mode S
Address
Verifies that the transponder does not
reply to Mode S interrogations that
contain invalid addresses.
No reply.
Ident
Verifies Ident function is operating.
Reply with SPI present in
ATCRBS Mode A only.
Reply with SPI absent.
Mode S UF 0
Verifies that the transponder replies to a
Mode S UF 0 interrogation with the
correct altitude, address, and format.
Proper DF 0 reply.
Mode S UF 4
Verifies that the transponder replies to a
Mode S UF 4 interrogation with the
correct altitude, address, and format.
Proper DF 4 reply.
Mode S UF 5
Verifies that the transponder replies to a
Mode S UF 5 interrogation with the
correct ID, address, and format.
Proper DF 5 reply.
Mode S UF 11
Verifies that the transponder replies to a
Mode S UF 11 interrogation with the
correct address, and format.
Proper DF 11 reply.
Squitter
Verifies squitters are transmitted from the
transponder at varying intervals about a
one second rate.
1 second (0.8 to 2.4
seconds).
TABLE 2-2 RAMP TESTS
(Sheet 2 of 2)
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2.4.1.4
Ramp Test (TIS and/or ADS-B Functions)
The following procedures check the TIS and ADS-B functions of an installation without requiring
a ramp tester with more capability than required for the testing of ATCRBS and Mode S functionality.
If the system includes the TIS function, use the following procedure (requires a KMD 550/850):
(1)
Press the “TRFC” button on the Display Unit (KMD 550/850).
(2)
Switch the mode to “ON”.
(3)
Verify that the message “TIS UNAVAILABLE” is being displayed on the KMD 550/
850.
(4)
If the message “NO DATA RECEIVED FROM TRAFFIC UNIT” is being displayed,
this indicates that no data is being received from the KT 73. This could be due to
the following.
(a)
The KT 73 is not powered up.
(b)
The wiring between the KT 73 and the KMD 550/850 is not correct.
(c)
The KT 73 has not been configured to provide the TIS function.
If the system includes the ADS-B function, use the following procedure (requires a KLN 94 or KLN
900):
(1)
Place the KT 73 in the Test Mode (see 3.3.1 “When the unit is in TST (Test) mode:”).
(2)
After performing the self-test sequence, the KT 73 should display “TEST OK”. The
KT 73 will issue the audio message “TEST OK”.
(3)
Switch the KLN 94 off.
(4)
Momentarily switch the KT 73 to “ON” then back to the “TST” mode.
(5)
The KT 73 should display “SBY F604” and the audio should announce “CHECK
FAULT CODES”.
(6)
Switch the KLN 94 on and allow it to complete its initialization activity.
(7)
Momentarily switch the KT 73 to “ON” and then back to the “TST’ mode.
(8)
The KT 73 should display “TEST OK”. The KT 73 will issue the audio message
“TEST OK”.
(9)
If in step 2 the KT 73 displays a fault code, consult the fault code table in paragraph
3.3.3 and take the indicated corrective action.
(10) If in step 2 any of the “F6XX” codes or the “F501” code are (is) displayed, check that
the appropriate source has power. If is does, check the wiring between the source
and the KT 73.
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SECTION III
OPERATION
3.1
GENERAL
Section 3 describes the operation of the KT 73. Where applicable, illustrations of the displays are
furnished to assist the operator in understanding the operation of the unit and also provide a visual
aide for programming sequences. Figure 3-1 illustrates the various panel controls and displays of
the unit.
NOTE:
The KT 73 and all other avionics, should be turned
off before starting the aircraft engine(s).
FIGURE 3-1 KT 73 FRONT PANEL
3.2
PROGRAMMING MODE
NOTE:
While in the programming mode, the KT 73 will not
transmit RF energy.
The programming mode is entered using the following procedure:
(1)
Place the unit in Standby mode.
(2)
Select 0000 ident code.
(3)
Simultaneously depress the IDT and VFR buttons for a minimum of 2 seconds.
To select the programming mode menu, rotate the cursor (CRSR) knob either clockwise or
counter clockwise to advance either up or down, respectively, through the following menu options
and then depress the IDENT button.
(1)
A/C ADDR
(Aircraft Address)
(2)
MAX AIR
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(3)
ALT SRC
(Altitude Source Select)
(4)
ENH FUNC
(Enhanced function when Gillham altitude source is selected)
(5)
ENH FUNC
(Enhanced function when ARINC 429 or RS-232 altitude source is
selected)
(6)
AUTO GND
(Automatic on ground determination)
(7)
AIR VOL
(Audio volume while in the air)
(8)
GND VOL
(Audio volume while on the ground)
(9)
ADSB EMT
(ADS-B emitter category)
(10)
OTHER
(Reserved for Factory Only)
Upon completing the programming of the KT 73, power down the unit. The settings chosen are
now stored in the unit’s internal memory and configuration module.
For a listing of the above menus and their respective sub-menus, refer to figure 3-2 on the following page. To navigate the programming menu and sub-menus depicted in figure 3-2, use the following procedure:
(1)
Rotate the CRSR knob to move across the major headings.
(2)
Press the IDT button to select a particular heading option.
(3)
Rotate the cursor (CRSR) knob to cycle between choices.
For example, when ALT SRC is selected as the major heading option, the CRSR
knob is rotated to cycle between the following choices:
429 (706)
RS-232
Gillham
If the RS-232 sub-menu option is selected, three sub-options may also be selected
by first pressing the IDT button and then rotating the CRSR button. They are listed
below:
8800M (Shadin Models compatible with UPS AT, formerly IIMorrow)
8800G (Shadin Models compatible with Magellan)
8800T (Shadin Models compatible with Trimble)
In summary, the CRSR knob cycles between heading choices. Once a given choice is displayed,
the IDT knob selects it and moves the cursor to the next major heading. In this case, the cursor
would move from ALT SRC to ENH FUNC (Gillham Selected).
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FIGURE 3-2 KT 73 CONFIGURATION MENU
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3.2.1
PROGRAMMABLE PARAMETERS
3.2.1.1
Programmable Parameters
The following parameters must be programmed prior to installation:
A/C ADDR:
When the unit is in the A/C ADDR (Aircraft Address) program menu:
(a)
The aircraft address is programmable (see section 2.3.5.4 for address information).
(b)
The aircraft address consists of 8 octal digits.
FIGURE 3-3 KT 73 FIRST 4 OCTAL DIGITS OF THE AIRCRAFT ADDRESS
FIGURE 3-4 KT 73 LAST 4 OCTAL DIGITS OF THE AIRCRAFT ADDRESS
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MAX AIR:
When the unit is in the MAX AIR (Maximum Airspeed (knots)) program menu the maximum airspeed is programmable to one of the following ranges:
(a)
0 to 75
(b)
75 to 150
(c)
150 to 300
(d)
300 to 600
(e)
600 to 1200
(f)
--- to 1200
FIGURE 3-5 KT 73 LOWER AND UPPER MAXIMUM AIRSPEED
ALT SRC:
The ALT SRC (altitude source) is programmable to the following:
(a)
ARINC 429 (706)
(b)
RS-232
(c)
Shadin 8800M
Shadin 8800G
Shadin 8800T
Gillham
NOTE:
If a Trancal RS-232 altitude source is used, refer to
the manufacturer’s data to configure it as 8800M,
8800G, or 8800T.
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ENH FUNC (Gillham Selected):
The Enhanced Function coding includes one of the following:
(a)
TIS
(b)
ADLP
(c)
ADS-B (JKT73-4, Pin C - GPS RX)
(d)
Non XPDR (Squitter Only) (JKT73-4, Pin C - GPS RX)
(e)
None (No enhanced function selected)
ENH FUNC (429 or 232 Selected):
The Enhanced Function coding includes one of the following:
(a)
TIS
(b)
ADLP
(c)
ADS-B (JKT73-1, Pin B - GPS RX)
(d)
TIS and ADS-B (JKT73-1, Pin B - GPS RX)
(e)
ADLP and ADS-B (JKT73-1, Pin B - GPS RX)
(f)
Non XPDR (JKT73-1, Pin B - GPS RX)
(g)
None
AUTO GND:
The KT 73 has AUTO GND (Automatic Ground Programming) capability when enabled.
(a)
Enable
(b)
Inhibit
NOTE:
Automatic Grounding refers to external discrete being connected to the landing gear strut switch where
applicable.
AIR VOL:
Air Volume includes one of the following audio power levels while the aircraft is in flight:
(a)
AIR 4 (4 mw)
(b)
AIR 6 (4 mw)
(c)
AIR 10 (10 mw)
(d)
AIR 16 (16 mw)
(e)
AIR 25 (25 mw)
(f)
AIR 40 (40 mv)
(g)
AIR 63 (63 mw)
(h)
AIR 100 (100 mw)
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NOTE:
WHILE PROGRAMMING THE AIR OR GND VOLUME, PUSHING THE VFR BUTTON WILL CAUSE
THE AUDIO MESSAGE “TEST OK” TO BE ISSUED
AT THE APPROPRIATE AUDIO LEVEL.
GND VOL:
Ground Volume includes one of the following audio power levels while the aircraft is on the ground:
(a)
GND 4 (4 mw)
(b)
GND 6 (4 mw)
(c)
GND 10 (10 mw)
(d)
GND 16 (16 mw)
(e)
GND 25 (25 mw)
(f)
GND 40 (40 mw)
(g)
GND 63 (63 mw)
(h)
GND 100 (100 mw)
ADSB EMT:
The KT 73’s ADS-B Emitter Categories are configurable to one of the following:
(a)
Category set “A” code:
(b)
No ADS-B Emitter Category Information
Light (<15,500 lbs.)
Small (15,500 to 75,000 lbs.)
Large (75,000 to 300,000 lbs.)
High-Vortex Large (aircraft such as B-757)
Heavy (> 300,000 lbs.)
High Performance (>5g acceleration and > 400 knots)
Rotorcraft
Category set “B” code:
No ADS-B Emitter Category Information
Glider/Sailplane
Lighter-than-air
Parachutist/Skydiver
Ultralight/hang-glider/paraglider
Reserved
Unmanned Aerial Vehicle
Space/Transatmospheric Vehicle
ADSB EMT: (cont).
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(c)
Category set “C” code:
(d)
No ADS-B Emitter Category Information
Surface Vehicle - Emergency Vehicle
Surface Vehicle - Surface Vehicle
Fixed Ground or Tethered Obstruction
4-7 Reserved
Category set “D” code:
No ADS-B Emitter Category Information
1-7 Reserved
OTHER:
Reserved for factory use only.
3.3
3.3.1
DETAILED OPERATING MODES
FUNCTIONAL MODES
The functional mode is selected by the mode select switch, see the display below. The following
modes are available.
(a)
OFF
(b)
SBY (Standby)
(c)
GND (Ground)
(d)
ON (On)
(e)
ALT (Altitude)
(f)
FLT ID (Flight ID)
(g)
TST (Test)
OFF:
The unit is not energized. When the unit is in the OFF mode the Backlighting will be illuminated if
either the 14 VDC or 28 VDC lighting bus has power applied.
When the unit is powered up (switched from the OFF position to another mode) the following will
occur:
(a)
The unit will reply and/or squitter according to the selected mode within two (2) seconds.
(b)
The display will show the information associated with the mode that it is in.
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SBY: (see below)
FIGURE 3-6 KT 73 STANDBY MODE
When the unit is in the SBY (Standby) mode:
(a)
The unit is energized but inhibited from replying to any interrogation.
(b)
"SBY" will be annunciated in the Altitude window.
(c)
The 4096 code will be displayed in the Ident window.
(d)
The unit will enter the next selected mode within 5 seconds of coming out of the
STANDBY mode.
GND: (see below)
FIGURE 3-7 KT 73 GROUND MODE
NOTE:
This feature is controlled by the AUTOGND feature
of the installation menu.
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When the unit is in the GND (Ground) mode:
(a)
The unit will inhibit replies to ATCRBS.
(b)
The unit will inhibit replies to ATCRBS/Mode S All-Call.
(c)
The unit will inhibit replies to Mode S-only All Call interrogations.
(d)
The unit will generate Mode S squitter transmissions.
(e)
The unit will reply to discretely addressed Mode S interrogations.
(f)
The 4096 code will be displayed in the Ident window.
(g)
"GND" will be displayed in the Altitude window.
(h)
The unit will enter the next selected mode within 5 seconds of coming out of the
GROUND mode.
(i)
Altitude reporting will be enabled.
ON: (see below)
FIGURE 3-8 KT 73 ON MODE
When the unit is in the ON mode:
(a)
The transmission of altitude information will be inhibited.
1.
The ATCRBS framing pulses in ATCRBS Mode C replies
will be retained.
2.
All ZEROs will be transmitted in the altitude field of the
Mode S replies.
(b)
The altitude window will be blank.
(c)
The 4096 code will be displayed in the Ident window.
(d)
The unit will reply to ATCRBS.
(e)
The unit will reply to ATCRBS/Mode S All-Call.
(f)
The unit will reply to Mode S-only All Call interrogations.
(g)
The unit will generate Mode S squitter transmissions.
(h)
The unit will reply to discretely addressed Mode S interrogations.
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ALT: (see below)
FIGURE 3-9 KT 73 ALTITUDE MODE
When the unit is in ALT (Altitude) mode:
(a)
The unit will transmit altitude information according to DO-181C paragraph
2.2.13.1.2(a)(1) in response to accepted Mode C interrogations.
(b)
The unit will transmit altitude information according to DO-181C paragraph
2.2.13.1.2(a)(2) in response to accepted Mode S interrogations.
(c)
The unit will reply with selected 4096 Code according to DO-181C: 2.2.13.1.2.b in
response to accepted Mode A interrogations.
(d)
The unit will reply with framing pulses if the derived altitude is invalid / altitude not
available in response to an accepted Mode C interrogation.
(e)
The unit will transmit zeros in each of the 13 bits of the AC field if the derived altitude is invalid / altitude not available in response to an accepted Mode S interrogation.
(f)
The unit will display altitude information according to Altitude Display parameters
(see listing in section 3.2.2).
(g)
The unit will display the 4096 Code in the Ident window.
NOTE:
The KT 73 will accept altitude from a Gillham source
between the range of -1000 ft. to 62749 ft. The KT
73 will accept altitude from an ARINC/GAMA 429
source in the range of -1025 ft. to 62749 ft. All other
altitude values are considered invalid.
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FLT ID: (see below)
FIGURE 3-10 KT 73 FLIGHT ID MODE
When the unit is in FLT ID (Flight ID) mode:
(a)
The 8 character Flight ID will be displayed.
(b)
Each character of the Flight ID will be either a number, letter, or space.
(c)
The "FLT ID" nomenclature will be displayed.
(d)
The ability to modify the Flight ID will be provided only if Flight ID is not received
from the ADLP source.
(e)
The unit will not transmit.
(f)
An asterisk will be displayed for characters that are not alphanumeric OR a space
for Flight ID received from an ADLP.
NOTE:
Spaces will be removed from Flight ID when entered
from the front panel.
TST: (see below)
FIGURE 3-11 KT 73 TEST MODE
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When the unit is in TST (Test) mode:
(a)
The unit is inhibited from transmitting.
(b)
The transponder illuminates all display segments for a minimum of 4 seconds.
(c)
If no faults have been detected by BITE, "TEST" will be displayed in the altitude
window and "OK" will be displayed in the ident window. The KT 73 will issue the
audio message “TEST OK”.
(d)
If one or more fault is detected by BITE, "SBY" will be displayed in the alt window.
If the fault(s) are associated with external data (non-critical), the KT 73 will issue
the audio message “CHECK FAULT CODES”.
(e)
If one or more fault is detected by BITE, the fault(s) will be displayed in the ident
window in the format FXYY (where X represents the primary fault and YY represents the secondary fault). The audio message “TRANSPONDER TEST FAIL” is
issued if any critical fault exists.
(f)
If more than one fault is detected by BITE, the ident window will cycle through detected fault codes.
(g)
If BITE determines that a fault is not active, the ident window will display only the
active faults.
(h)
If BITE determines that all faults are cleared, “TEST” is displayed in the altitude
window and “OK” is displayed in the ident window.
(i)
All faults are logged.
NOTE:
Primary and secondary fault codes are listed in Table 3-1, BITE Fault Codes.
(j)
If the VFR button is pushed, the Altitude window and Ident window will display the
software revisions for a minimum of 4 seconds, each as follows:+
Altitude
Ident
APPL (Application SW)
xxxx (where xxxx is the revision code for
each type of SW.
BOOT (Bootcode)
xxxx
FIRM (Firmware)
xxxx
VOIC (Voice messages)
xxxx
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3.3.2
FRONT PANEL OPERATION
Refer to figure 3-1 for an illustration relating to front panel operation.
IDT (IDENT):
The KT 73’s Ident pushbutton (marked IDT) is pressed when the ground control requests an
“Ident” or “Squawk Ident” from the aircraft.
x An input pin is located on the rear connector for an external ident pushbutton.
x The external and front panel IDENT operate identically in all applicable modes of operation.
x The SPI pulse is not be transmitted when replying to Mode C interrogations.
(a)
On/Altitude Mode
Depressing the "IDT" momentary contact switch while in the ON or ALTITUDE
mode:
1.
will cause the special position identification pulse (SPI) to be
appended to Mode A replies for a period of 18 ± 1 seconds.
2.
will be reflected in the Flight Status field of Mode S downlink
format 4 and 5 replies for a period of 18 ± 1 seconds.
3.
will cause the unit to display the "IDT" nomenclature for a
period of 18 ± 1 seconds.
4.
will be reflected in the ME field of Mode S downlink 17 for a
period of 18 ± 1 seconds.
(b)
Ground Mode
Depressing the "IDT" momentary contact switch while in the GROUND mode:
1.
will cause the special position identification pulse (SPI) to be
reflected in the Flight Status field of Mode S downlink format
4 AND 5 replies to discretely addressed Mode S interrogations for a period of 18±1 seconds.
2.
will cause the unit to display the "IDT" nomenclature for a
period of 18±1 seconds.
4096 ID CODE:
x While in the Standby, Ground, On, or Altitude modes, the 4096 code is displayed in the IDENT
window on the right side of the display.
x Modification of the 4096 code is performed via the VFR push button or four Transponder Code
Selector Knobs. Each knob selects a separate digit of the identification code.
x The 4096 Identification code digits range from 0 to 7.
(a)
Code Entry
Upon entering a 4096 code:
1.
The new 4096 ID code will be stored in EEPROM 3.5 ± 0.5
seconds after the entry is completed.
2.
The new 4096 ID code will be transmitted 3.5 ± 0.5 seconds
after the entry is completed.
3.
If the "IDT" push-button is depressed, the chosen code will
be immediately stored in EEPROM and transmitted along
with the appropriate Mode A SPI pulse in response to a
Mode A interrogation.
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(b)
Code restoration on Power-up
On power-up, the displayed code will be the last active code used before power
was removed.
VFR OPERATION:
x Momentarily depressing the "VFR" pushbutton will cause the preprogrammed VFR code to
supersede whatever 4096 Code was previously entered.
x The 4096 Code will be accepted for interrogation reply sequences.
x The 4096 Code will be stored as the last active 4096 Code just as if it were programmed from
the front panel.
(a)
VFR Programming
The VFR code will be programmable pending the following conditions:
1.
The mode select knob indicates Standby mode.
2.
The 4096 code to be programmed is displayed.
3.
While the "IDT" pushbutton is latched, the “VFR” pushbutton
is depressed.
(b)
Last Code Reversion
1.
Pressing the "VFR" Pushbutton for 2±0.5 seconds will display the last non-VFR 4096 code.
2.
The non-VFR code will be transmitted 3.5±0.5 seconds after
the code is displayed.
REPLY:
If the unit is replying to a valid Mode S interrogation, the reply nomenclature "R" will be illuminated
twice per second. If the unit is replying to ATCRBS interrogations, the reply nomenclature "R" will
be illuminated once per second.
ALTITUDE DISPLAY:
(a)
When in the ALTITUDE mode, when an altitude source is available, and when the
derived altitude is valid, the KT 73 will display the Flight Level altitude in the Altitude
window of the display. The altitude will be displayed in hundreds of feet.
(b)
When in the ALTITUDE mode the Flight Level nomenclature, "FL", will be illuminated.
NOTE:
Flight Level is a term to indicate that the altitude is
not true altitude but barometric altitude which is not
corrected for local pressure. For Example, "FL 040"
corresponds to an altitude of 4000 feet, meaning sea
level pressure of 29.92 inches of mercury.
(c)
(d)
When in the ALTITUDE mode and an altitude source is unavailable, the altitude
window will display dashes.
When in the ALTITUDE mode and the derived altitude is invalid, the altitude window will display dashes.
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NOTE:
The KT 73 will accept altitude from a Gillham source
between the range of -1000 ft. to 62749 ft. The KT
73 will accept altitude from an ARINC/GAMA 429 or
RS-232 source in the range of -1025 ft. to 62749 ft.
All other altitude values are considered invalid.
DISPLAY BRIGHTNESS ADJUSTMENT:
(a)
The display brightness is adjustable in the TEST mode.
(b)
Eight carets are provided below the alpha-numeric display characters to indicate
the brightness setting (relative to the photocell reading).
(c)
Maximum brightness is indicated by all 8 carets being illuminated.
(d)
Minimum brightness is indicated by no carets being illuminated.
(e)
The factory default setting is indicated by 4 carets being illuminated.
(f)
To adjust the display brightness, place the unit into TEST mode and rotate knob
either clockwise or counterclockwise to adjust the brightness up or down, respectively.
INTERNAL EEPROM AND REMOTE CONFIGURATION MODULE:
(a)
The KT 73 has the capability to utilize a configuration module if installed.
(b)
The presence of the external configuration module is indicated by + 5 volts being
present on Pin 2 of connector JKT73-2.
GAS DISCHARGE DISPLAY:
(a)
The brightness of the display is determined by the photocell relative to the programmed brightness level.
(b)
The illuminance is a function of the PHOTO_CEL voltage provided to the microcontroller from the photocell.
(c)
When going from bright to dim, an approximate 6 ± 0.5 second time constant is
used.
(d)
When going from bright to dim, 63% of the change will take place in each time constant period.
3.3.3
BUILT IN TEST EQUIPMENT (BITE)
FAULT ANNUNCIATION:
Built In Test Equipment (BITE) failure parameters are monitored by a time averaging process to
ensure that transient events, typical of the aircraft environment, are not the cause of fault annunciation.
The following list the fault annunciation parameters during STANDBY, GROUND, ON, and ALTITUDE modes.
Critical faults are defined as faults that may cause the transponder to behave in an undetermined
manner. The following are critical and non-critical faults.
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Primary Fault
Fault Code
(X)
Secondary Fault
Fault Code
(YY)
SEVERITY
Acquisition Squitter
Squitter Data
01
Critical
Acquisition Squitter
Squitter Rate
02
Critical
Extended Squitter
Squitter Data
03
Critical
Extended Squitter
Squitter Rate
04
Critical
Internal EEPROM
Internal EEPROM (write)
01
Critical
External EEPROM
External EEPROM (write)
02
Critical
External EEPROM
EEPROM Checksum
03
Critical
Internal EEPROM
SPR Read
04
Critical
Hardware
Boot ROM CRC
01
Critical
Hardware
Application ROM CRC
02
Critical
Hardware
Voice ROM CRC
03
Critical
Hardware
RAM Initial Verification
04
Critical
Hardware
RAM Verification
05
Critical
Hardware
+3.3V
06
Critical
Hardware
+5V
07
Critical
Hardware
+6V
08
Critical
Hardware
+12V
09
Critical
Hardware
+65V
10
Critical
Hardware
+95V
11
Critical
Hardware
-12V
12
Critical
Hardware
-90V
13
Critical
Hardware
-5V
14
Critical
Hardware
Suppression
15
Critical
Hardware
ATCRBS Tx Data
16
Critical
Mode S Address
Mode S Address/Max Airspeed
01
Critical
Non-critical
Gillham
01
Non-Critical
Non-critical
Executive
02
Non-Critical
Interface
Data Source - ALT. (429)
01
Non-Critical
Interface
Data Source - TIS (429)
02
Non-Critical
Interface
Data Source - ADLP (RS- 232)
03
Non-Critical
Interface
Data Source - GPS (RS- 232)
04
Non-Critical
Interface
Data Source - ALT. (RS- 232)
05
Non-Critical
TABLE 3-1 BITE FAULT CODES
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TSO APPENDIX
ENVIRONMENTAL QUALIFICATION FORMS
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THIS PAGE IS RESERVED
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THIS PAGE IS RESERVED
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TSO-4
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