Honeywell KX165A Installation Manual
INSTALLATION MANUAL
KX 155A/165A
COMM/NAV SYSTEM
MANUAL NUMBER 006-10542-0002
REVISION 2, APRIL 2000
PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICE
WARNING
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COPYRIGHT NOTICE
©2000 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.
PRELIMINARY - SUBJECT TO CHANGE WITHOUT NOTICE
BENDIX/KING
KX 155A/165A
COMM/NAV SYSTEM
SECTION I
GENERAL INFORMATION
1.1 INTRODUCTION
This manual contains information relative to the physical, mechanical, and electrical characteristics of the Bendix/King Silver Crown KX155A VHF COMM Transceiver/Navigation/VOR/LOC
Glideslope Receiver. Installation and operating procedures are also included.
Information relative to th e maintenance, alignment, and procur ement of replacement parts ma y be
found in the KX155A Maintenance/Overhaul Manual, P/N 006-15542-XXXX.
1.2 EQUIPMENT DESCRIPTION
The KX155A is a VHF NAV/COMM Transceiver which provides the following functions.
A. Two-way voice communication within the frequency range of 118.00 MHz to
136.975 MHz (760 Channels) in 25 kHz increments.
B. Reception of navigation signals withi n the frequency range of 108.00 MHz to
117.95 MHz in 50 kHz increments (200 channels).
C. Opt ional reception of glideslope signals withi n the frequency range of 329.15
MHz to 335.00 MHz in 150 kHz increments (40 channels).
D. High level speaker audio output plus limited audio intercom inputs and out-
puts.
E. Provides a count down timer.
The KX155A is a panel mounted unit. Connections to the unit are made through one 36 and one
50 pin Molex printed circuit board edge connector and three BNC coax connectors at the rear of
the unit.
Electrically, the KX155A consists of the following sections:
• COMM Transmitter
• COMM Receiver
• NAV Receiver
• Main Board
• Glideslope Receiver and Converter (Optional)
• Gas Discharge Display
• 4 Ω Audio Amplifier
The KX155A is backward compatibl e with existing KX155 instal lations. See Section 2. 3 Additional
Installation Notes for details.
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1.3 TECHNICAL CHARACTERISTICS
Table 1-1
KX155A/KX165A GENERAL SPECIFICATIONS
ENVIRONMENTAL TSO COMPLIANCE:
TEMPERATURE RANGE: -20°C to +55°C with short time operation at +70°C.
ALTITUDE: -15,000 feet to 50,000 feet
WEIGHT:
KX 155A VERSIONS WEIGHT Mtg Rack
KX155A/KX165A Technica l Spe c ifi cati o ns
RTCA DO-160C, Eurocae ED-14C Env Cat (s ee Appendix
E)
(Operational to -40°C)
(nominal) w/hardware
069-01032-0101 4.2 lbs (1.9 kg) 1.1 lbs (0.5 kg)
069-01032-0201 3.7 lbs (1.7 kg) 1.1 lbs (0.5 kg)
VERSIONS WEIGHT Mtg Rack
(nominal) w/hardware
KX 165A 069-01033-0101 4.0 lbs (1.8 kg) 1.1 lbs (0.5 kg)
069-01033-0201 4.0 lbs (1.8 kg) 1.1 lbs (0.5 kg)
PHYSICAL DIMENSIONS
(NOMINAL) :
Width: 6.25 inches (15.875 cm)
Height: 2.00 inches (5.08 cm)
Depth: 10.16 inches (25.81 cm) to end of connector
MOUNTING: Panel mounted, no shock mounting required
POWER CONSUMPTION:
RECEIVE TRANSMIT
VERSIONS: TYP. PEAK
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COMM/NAV SYSTEM
069-01032-0101 0.8 A 2.2 A 6.0 A (MAX)
069-01032-0201 0.8 A 2.2 A 6.0 A (MAX)
069-01033-0101 0.6 A 0. 7 A 4.0 A (MAX)
069-01033-0201 0.6 A 0. 7 A 4.0 A (MAX)
NOTE: Peak currents occur only when installation is configured for the 4Ω audio output & both
COMM and NAV volumes are adjusted to full.
Specifications are at 25°C unless otherwise specified.
COMM TRANSCEIVER
TSO COMPLIANCE:
Transmit: C37d (DO-186A, Class 4 - all flavors/
Class 4 & 6 069-01033-0201)
Receive: C38d (DO-186A, Class C & D - all flavors/
Class C, D, & E 069-01033-0201)
APPLICABLE DOCUMENTS: RTCA DO-186A, DO-160C,
*EUROCAE ED-23B, ED-14C
DUTY CYCLE: 10%, 4.5 minutes receive, 0.5 minutes transmit
FREQUENCY RANGE: 118.000 MHz to 136.975 MHz
COMM TRANSMITTER
POWER OUTPUT: 10 Watts minimum
10 Watts typical (KX 155A pre-Mod 5)
MODULATION: 70% minimum modulation capability with less than 15%
distortion. Audio leveling circuit used.
SIDETONE OUTPUT: Adjustable up to 100 mW ( 5.1 mW Mod 1 w/o Mod 6 ) into
500 Ω headphones
MICROPHONE: Standard carbon or dynamic mic containing transistorized
pre-amp. (Must provide 100 mVrms into 100 Ω load.)
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HARMONIC CONTENT: -56 dBc, minimum. Typically greater than -60 dBc
HIGH TEMPERATURE PROTECTION:
TRANSMITTER TIME OUT: If MIC key is enabled for greater than 30 ( Nominal) sec-
If the transmitter and modulator circuits become hot
enough to potentially damage any components in the
transceiver, a protection circuit will automatically reduce
the transmitter power consumption and output power.
onds, the transmitter will shut down. The transmitter is reset upon release of MIC key.
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COMM/NAV SYSTEM
COMM RECEIVER
RECEIVER SENSITIVITY: -107 dBm (2µV hard) or less for 6 dB S + N/N with
1,000 Hz tone modulated 30 %.
RECEIVER SELECTIVITY:
Class C & D operating modes 6 dB bandwidth ±8.0 kHz, minimum
60 dB bandwidth ±22.0 kHz, maximum
Class E operating mode 6 dB bandwidth ±2.778 kHz, minimum
60 dB bandwidth ±7.37 kHz, maximum
RECEIVER AUDIO OUTPUT: 100 mW into 500 Ωs minimum.
AGC CHARACTERISTICS: From -93 dBm to -33 dBm audio output will not
vary more than 3 dB. Active from no signal to +3
dBm.
SQUELCH: Automatic squelch (internall y adjust abl e carrier t o
noise setting) with manual disable and carrier
squelch override. Both squelch adjustments are
externally accessible. The aut omatic squelch has
a typical factory setting of -106 dBm.
OUT OF BAND SPURIOUS RESPONSE,
INTERMODULATION AND
DESENSITIZATION
NAV RECEIVER
TSO COMPLIANCE: C36e (DO-195, Class A) Localizer
APPLICABLE DOCUMENTS: RTCA DO-195, RTCA DO-196, RTCA DO-160C
FREQUENCY RANGE: 108.00 MHz to 117.95 MHz in 50 kHz increments
OUT OF BAND SPURIOUS RESPONSES,
INTERMODULATION AND
DESENSITIZATION:
* Pre-Mod 5 units may not meet all applicable EUROCAE requirements.
At least 60 dB down
C40c (DO-196) VOR
*EUROCAE ED-22B, & ED-46B, ED-14C
At least 60 dB down
Meets ICAO FM Immunity requirements consistent with RTCA DO-195,196 and
*Eurocae ED-22B,46B
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VOR COURSE ACCURACY: Two sigma limit 3° as specified in RTCA DO-196
when used with indicators per secti on 1.7.3 of this
installation manual.
Three sigma limit 2.7° as specified in *Eurocae
ED-22B when used with indicators per section
1.7.3 of this Installation manual.
AUDIO OUTPUT: With a 1 kHz tone 30% modulation at least 100
mW output into 500 Ω loads
IDENT/VOICE: With 100 mV input, 30% modulation at 1020 Hz,
the ident/voice tone ratio shall no t be l ess than 15
dB.
LOC CENTERING ERROR: Two sigma limit ±9.9 µA as specified in RTCA DO-
195 and *Eurocae ED-46B when used with indicators per section 1.7.2 of this installation manual.
GLIDESLOPE RECEIVER
TSO COMPLIANCE: C34e (DO-192)
APPLICABLE DOCUMENTS: RTCA DO-192, DO-160C
*EUROCAE ED-47B, ED-14C
CENTERING ACCURACY: Two sigma limit ±10µA as specified in RTCA DO-
192 and *Eurocae ED-47B when used with indicators per section 1.7.1 of this Installation Manual.
DEFLECTION CHARACTERISTICS: A difference in depth of modulation of 0.091 ddm,
or 2 dB, shall produce a deflection of
78 ±3µA (typical). The deviation under opposite
polarity shall be 78 ±3 µA (typical).
FREQUENCY RANGE: 329.15 MHz to 335.00 MHz 40 channels (150 kHz
spacing).
SPURIOUS RESPONSE: All responses in the range from 90 kHz to 1500
MHz at least 60 dB below center frequency response, excluding the range from 328.60 MHz to
335.40 MHz.
* Pre-Mod 5 units may not meet all applicable EUROCAE requirements.
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COMM/NAV SYSTEM
VOR/LOC CONVERTER (KX 165A ONLY)
TSO COMPLIANCE:
ACCURACY - VOR:
- LOC:
COURSE WIDTH:
VOR:
LOC:
INPUT IMPEDANCE:
LOADS:
C40c (DO-196)
C36d (DO-195, Class A)
Typical bearing error of less than 0.5° with precision track selector (2° max. error).
Typical centering error of less t han 3µA (7µA max
error).
10° ±1° externally adjustable
90 µA ±5µA for ddm 0f 0.093 ddm of 4 dB
60 kΩ for 0.5 Vrms input (VOR mode)
Five 1000Ω deviation loads, three 1000Ω flag
loads and three 200Ω from-to loads
AUDIO AMP (KX 155A ONLY)
4 Ω Output: 8 watts nominal
Inputs: Three 500 Ω Auxiliary Inputs
* Pre-Mod 5 units may not meet all applicable EUROCAE requirements.
1.4 UNITS AND ACCESSORIES SUPPLIED
1.4.1 KX 155A/KX 165A
The Bendix/King KX 155A/KX 165A Transceivers are available in the following configurations.
Table 1-2
Part Number 28V Glideslope Receiver
069-01032-0101 X X
069-01032-0201 X
KX 155A Configurations Available
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COMM/NAV SYSTEM
Table 1-3
Part Number 28V 8.33 kHz
069-01033-0101 X
069-01033-0201 X X
1.4.2 INSTALLATION KIT
Bendix/King KX 155A/KX 165A Installation Kit (P/N 050-03378-0000/0001), listed in Table 1-4
contains the following parts: 0000 for units with glideslope and 0001 for units without glideslope.
KX 165A Configurations Available
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Table 1-4
Part Number Descripti on 0000 0001
030-00101-0002 PANEL MOUNT PLUG 3 2
030-01094-0060 CONN 18 POS 1 1
030-01094-0088 CONN HOUSING (2 X 2.50 ) W
030-01107-0078 CONNECTOR TERM 78T 1 0
030-01107-0068 CONNECTOR TERM 68T 0 1
047-05959-0002 STRAIN RELIEF W/H 2 2
047-05960-0001 STRAIN RELIEF W/F 2 2
073-00431-0007 CONN MTG PLATE COMPLETE 1 1
089-02051-0024 NUT, SPEED, U, 6-32 4 4
089-02353-0001 NUT, CLIP, 6-32 6 6
089-05878-0005 SCR, PHP, 4-40 X 5/16 2 2
089-05878-0012 SCR, PHP, 4-40 X 3/4 4 4
Installation Kit (050-03378-XXXX)
11
POLARIZING KEY
089-05907-0006 SCR, PHP, 6-32 X 3/8 4 4
089-06012-0008 SCR, FHP, 6-32 X 1/2 6 6
090-00019-0007 RING, RTNR, .438 3 2
1.5 ACCESSORIES REQUIRED BUT NOT SUPPLIED
A. Broad band 50 Ω vertically polarized Communications antenna with coaxial cable.
B. Headphones: 500 Ωs nominal impedance.
C. Mi crophone: Low impedance carbon or dynamic with transistorized pre-amp.
D. Broad band 50 Ω horizontally polarized Navigation antenna with coaxial cable.
E. Broad band 50 Ω horizontally polarized Glideslope antenna with coaxial cable or
low loss splitter used with the navigation antenna.
F. VOR, LOC, Glideslope Indicators. See section 1.7.6 for TSO’d systems.
G. In some installations it may be desirable to allow the Glideslope Receiver to oper-
ate using the aircraft’s navigat ion antenna. In other installati ons it may be desirable
to operate two NAV/LOC Receivers or two GS Receivers using a common anten-
na. Low-loss couplers are available to allow such operation.
An overall degradation in sensitiv ity will be realized due to the inse rtion loss of the
coupler. The installer must verify that acceptable sensitivity and proper system
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KX 155A/165A
COMM/NAV SYSTEM
performance is realized in a system that uti lizes a coupler. A minimum of 20 dB of
GS receiver-to-receiver isolation is required in dual installations employing a KX
155A/KX 165A GS receiver. Examples of s ome common couplers are listed below.
Contact the coupler manufacturer for specif ications for the couplers listed.
Table 1-5
Coupler to allow one
antenna to operate:
One Nav and one GS GSNC 20-05 H22-1
Two Navs DRC 20-04 or 14830 H21-1
Two Glideslopes DGSC 20-02 or 16009 H24-1
Two Navs and two GSs DOC 20-06 or 16010 H69-1
Dayton-Granger
(954) 463-3451
Common Couplers
Dorne Margolin
(516) 585-4000
1.6 LICENSE REQUIREMENTS
The KX 155A/KX 165A NAV/COMM transceiver is to be utilized in an aircraft which already has a
station license, no additional radio station license is required.
If the transceiver is to be used as a ground station then a Ground Station Authorizat ion is required.
Call the Federal Communications Commission (FCC) at 1-800-322-1117, or use the included FCC
Form 207, to order FCC Form 406, “Application for Ground Station Authori zation in the Aviation
Services”.
You may also use the FCC’s FAX form service by calling 1-202-418-0177.
This equipment has been accepted by the FCC and entere d into their list of Typ e Accepted Equip-
ment as AlliedSignal Avionics, Inc. Model KX 155A/KX 165A.
For more information call the FCC Hot line at 1- 800-322-1117, pr ess “2" for assist ance with radi o
service, then press “1" for ship and aircraft licensing information. To get information from the internet, visit the FCC web page at
The KX 155A/KX 165A owner/operator accepts all responsibi lity for obtaining the proper licensin g
before using the transmitter.
http://www.fcc.gov.
CAUTION
THE VHF TRANSMITTER IN THIS EQUIPMENT IS
GUARANTEED TO MEET FEDERAL COMMUNICATIONS
COMMISSION ACCEPTANCE OVER THE OPERATING
TEMPERATURE RANGE ONLY WHEN A BENDIX/KING
CRYSTAL IS USED IN THE STABILIZED MASTER OSCILLATOR.
USE OF OTHER THAN A BENDIX/KING CRYSTAL IS
CONSIDERED AN UNAUTHORIZED MODIFICATION,
AND WILL VOID THE WARRANTY.
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COMM/NAV SYSTEM
An Aircraft Radio Stat ion License is no longer required for this equipment f or domestic oper ation.
For international travel, f orms (FCC For m 404, New Air craft Stati on L icense, or FCC Form 405A,
Renewal of Aircraft Station License) can be obtained from your nearest FCC Field Office.
1.7 REQUIREMENTS FOR TSO’D VOR/ILS GLIDESLOPE SYSTEMS
The additional units used in conjunc tion wi th the KX 155 A/KX 165A must meet the speci ficati ons
listed below to comprise a completely TSO’d navigation system.
1.7.1 KX 155A/KX 165A GLIDESLOPE INDICATOR REQUIREMENTS
A. The indicator shall meet all applicable requi rements of TSO C34e.
B. Centering current to be 0 ±6.6 µA with a 95% probability under all environ-
mental conditions listed in RTCA Paper DO-192, Minimum Performance
Standards -- Airborne ILS Glideslope Receiving Equipment, Paragraph 2.1,
sub-paragraph B, Centering Accuracy
C. The cour se deviation pointer shall visibly deflect at least ±5/8 inch along its
scale when the input current is changed from zero to ±150 µA.
D. Def lection linearity over the deflec tion range from zero to 150 µA shall be with-
in 10% of being proportional to the input c urr ent. Addi tional ly , as the cur rent
is increased beyond that producing full scale defl e ction to a value of ±685.7
µA, the indicator deflection shall not decrease.
E. When the input current is abrupt ly changed from any value f rom zero to ±150
µA, the pointer shall reach 67% of its ultimate defl ection within 2 seconds and
pointer overshoot shall not exceed 5%.
F. The input impedance shall be 1 K Ωs ±5% for both the deviation indic ator and
warning signal.
G. A warning signal input current of 150
warning flag. A warning signal input cur rent of 260
a fully concealed warning flag.
.
µ
A or less shall produce a fully visible
µ
A or greater shall produce
1.7.2 KX 155A LOCALIZER CONVERTER AND INDICATOR REQUIREMENTS
A. The indicator shall meet all appli cable r equire ments o f C36e (RTCA DO- 195
Class A) or C36d (RTCA DO-131 Class D).
B. Centering current to be 0 ±6.0 µA with a 95% probability under all environ-
mental conditions listed in RTCA Paper DO-195, Minimum Performance
Standards -- Airborne ILS Localizer Receiving Equipment, Paragraph 2.1,
sub-paragraph b, Centering Accuracy
C. The course deviation pointer shall visibly deflect at least ±3/8 inch along its
scale when the input current is changed from zero to ±90 µA.
D. Deflection linearity over the deflection range from zero to ±90 µA shall be with-
in 10% of being proportional to the diff erence in depth of modulat ion of the 90
and 150 Hz signals, or the deflection shall be within 5% of standard defle ction
(±90 µA) of being proportional to the diff erence in depth o f modulation, whichever is greater. Additionally, as the difference in depth of modulation is increased beyond that producing f ull scale deflection (±150 µA) to a value of 0.4
ddm, the course deviation pointer deflection shall not decrease.
.
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E. When the input current is abruptly changed f rom zero to ±150 µA, the pointer
shall reach 67% of its ultimate deflection within 2 seconds and pointer overshoot shall not exceed 5%.
F. The input impedance of the indicator for both the deviation indicator and warn -
ing signal shall be 1 KΩ ±5%.
G. A warning signal input current of 125 µA or less shall prod uce a full y visible
warning flag. A warning signal input current of 260 µA or greater sh all produce a fully concealed warning flag.
1.7.3 KX 155A VOR CONVERTER AND INDICATOR REQUIREMENTS
A. The indicator shall meet all applicable requi rements of TSO C40c.
B. The bearing error shall be less than 2.5° with a 95% probability under all en-
vironmental conditions li sted in RTCA Paper DO-196 , Minimum Performance
Standards -- Airborne VOR Receiving Equipment, Paragraph 2.1, sub-paragraph 2.1.2, Bearing Accuracy
For older converters/indicators, the Bearing Error
shall be less than 2.7° with a 95% probability under
all environmental conditions listed in RTCA Paper
DO-114, MINIMUM PERFORMANCE STANDARDS
-- AIRBORNE VOR RECEIVING EQUIPMENT,
Paragraph 2.1, Sub-paragraph B, BEARING ACCURACY.
.
NOTE
C. The course deviation pointer shall visibly deflect at least ±1/2 inch (for DO-
196) or 3/8 inch (for DO-114) along its scale when the input current is
changed from zero to ±150 µA.
D. Deflection Linearity
The deflection shall be proportional to t he change in phase between the two
components of the standard VOR test signal, withi n 20% of the deflection produced by a 10° (±150 µA) change in phase. This re quirement shall be met at
all deflections produced when t he phase difference i s varied fro m plus 10° to
minus 10° of that producing an "on course" indicati on.
The pointer deflection shall not dec rease as the phase difference is increased
from producing an "on course" indicati on to that producing an indication which
is equivalent to ±80° from "on course".
E. Deflection Response
When the difference in phase between the two components of an "on course"
standard VOR test signal is abruptl y changed, the pointer shal l reach 70% of
its ultimate position within 3 seconds and the pointer overshoot shall not exceed 20%.
F. The input impedance of the indicator for both the bearing error and warning
signal shall be 1 KΩ ±5%.
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G. A warning signal input current of 125 µA or less shall prod uce a full y visible
warning flag. A warning signal input current of 266 µA or greater sh all produce a fully concealed warning flag.
H. The input impedance of the TO/FROM indicator shall be 200 Ωs ±200 µA
sensitivity.
1.7.4 KX 165A VOR INDICATOR REQUIREMENTS
A. The indicator shall meet all applicable requi rements of TSO C40c.
B. The bearing error shall be less than 1.9° with 95% probabil ity under all environmen-
tal conditions listed in RTCA Paper DO-196, Minimum Perfor ma nce Standards -Airborne VOR Receiving Equipment, Paragraph 2.1, sub- paragraph 2.2.1, Bearing
Accuracy.
NOTE
For older indicators, the Bea ri ng Error shall be l ess than
2.7° with a 95% probability under all environmental
conditions listed in RTCA Paper DO-114, MINIMUM
PERFORMANCE STANDARDS -- AIRBORNE VOR
RECEIVING EQUIPMENT, Paragraph 2.1, Subparagraph B, BEARING ACCURACY.
C. The course deviation pointer shall visibly deflect at least ≈1/2 inch (for DO-196) 3/
8 inch (for DO-114) along its sc ale when the i nput cur re nt is changed from zer o t o
±150 µA.
D. Deflection Linearity
The deflection shall be proportion al to the change in phase between the two components of the standard VOR test signal, within 20% of the deflection produced by
a 10° (±150 µA) change in phase. This requirement shall be met at all defle ctions
produced when the phase difference is varied from plus 10° to minus 10° of that
producing an “on course” indication.
The pointer deflection s hall not decrease as the p hase difference is inc reased from
the producing an “on course” indication to that producing an indication which is
equivalent to ±80° from “on course”.
E. Deflection Response
When the difference in phase between the two components of an “on course” standard VOR test signal is abruptly changed, the pointer shal l reach 70% of its ultimate
position within 3 seconds and the pointer overshoot shall not exceed 20%.
F. The input impedance of the indicator for both the bearing error and warn ing signal
shall be 1 KΩ ±5%.
G. A warning signal input current of 50 µA or less shall produc e a fully visible warni ng
flag. A warning signal input current of 350 µA or greater shall produce a fully concealed warning flag.
H. The input impedance of the TO/FROM indicator shall be 200 Ω ±200 µA sensitivity.
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1.7.5 KX 165A LOCALIZER INDICATOR REQUIREMENTS
A. The indicator shall meet all applicable requi rements of C36e.
B. The localizer centering current to be 0 ±3.2 µA with a 95% probability under
all environmental conditions listed in RTCA DO-195, Minimum Performance
Standards -- Airborne ILS Localizer Receiving Equipment, Paragraph 2.2.1,
sub-paragraph B, Centering Accuracy
C. The course deviation pointer shall visibly deflect at least ±3/8 inch along its
scale when the input current is changed from zero to ±90 µA.
D. Deflection linearity over the range from zero to ±90 µA shall be within 10% of
being proportional to the difference in depth of modulat ion of the 90 and 150
Hz signals, or the deflection shall be within 5% of standard deflection (±90 µA)
of being proportional to the difference in depth of modulation, whichever is
greater.
Additionally, as the differ ence in depth of modulation is increased beyond t hat
producing full scale deflection (±150 µA) to a value of 0.4 ddm, the course de-
viation pointer deflection shall not decrease.
E. When the input current is abruptly changed f rom zero to ±150 µA, the pointer
shall reach 67% of its ultimate deflection within 2 seconds and pointer overshoot shall not exceed 5%.
F. The input impedance of the indicator for both the deviation indicator and warn -
ing signal shall be 1 KΩ ±5%.
G. A warning signal input current of 50 µA or less shall produce a fully visible
warning flag. A warning signal input current of 350 µA or greater shall pro-
duce a fully concealed warning flag.
.
1.7.6 FULLY TSO’D SYSTEMS
The following systems when used in conjunction with the KX 155A will meet all T SO system requirements.
1. KI 203
2. KI 204
3. KI 208/A
4. KI 209/A
5. KN 72, KI 206
6. KN 72, KI 525A
7. KN 72, KPI 552
8. KN 72, KPI 553
9. KN 72, KI 202
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SECTION II
INSTALLATION
2.1 GENERAL
This section contains sugges tions and factors to consider before installi ng the KX 155A/KX 165A.
Close adherence to these suggestions will assure a more satisfactory performance from the
equipment.
The conditions and tests requi red for TSO app roval of this ar ticle are mi nimum 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 e valuation 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 unit. Make a visual inspec tion 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 use in unit storage or reshipment.
2.3 EQUIPMENT INSTALLATION
The KX 155A/KX 165A installation will conform to standards designated by the customer, installing agency and existing conditions as to the unit loca tion and type of installation. However, the
following suggestions should be consider ed before instal ling your KX 1 55A/KX 165A. The ins talling agency will supply and fabricate all external cables. The connectors r equired are suppli ed by
AlliedSignal. Interconnect diagrams are
NOTE
Use good quality stranded wire with at least 600 volt insulation that will not support a flame. If more than one Glideslope Receiver is to be operated from a single antenna, an
antenna coupler such as the DORNE and MARGOLIN INC.
(Model DMB H4-1) or equivalent should be used.
2.3.1 AVIONICS COOLING REQUIREMENTS FOR PANEL MOUNTED EQUIPMENT
The greatest single contribut or to increased reliabil ity of all modern day avionics i s to limit the maximum operating temperature of the individual unit s. While modern day individual circuit designs
consume much less electrical ene rgy, the wat ts pe r cubic i nch dissi pated wit hin avionics units re mains much the same due to high density packaging t echniques . Conseque ntly, the import ance
of providing avionics stack cooling is still with us.
Forced air cooling is required for the KX 155A/KX 165A. Forced air must be provided to the KX
155A/KX 165A through the air inlet port located on the back of the unit. Forced air must be supplied by a source capable of delivering a minimum air flow of 3. 5 CFM to the uni t und er the st atic
pressure conditions that will exist at the unit’ s air inlet port (typically, not more than .032 psi relative
to ambient pressure). I n order to maintai n frequency stabi lity per TSO specifi cations, the blower’s
inlet air temperature must not exceed 55° C. However, in order to provide optimum equ ipment
reliability, it is strongly recommended that inlet air temperature not exceed 35° C.
Figures 2-12
through
2-16
.
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KX 155A/165A
COMM/NAV SYSTEM
Recommendations on stack cooli ng are contained in Alli edSignal Installati on Bulletin #55. Failur e
to provide stack cooling wil l certain ly lead to i ncreased avionics main tenance cost s and may void
the AlliedSignal warranty.
2.3.2 MOUNTING RACK INSTALLATION
A. The KX 155A/KX 165A is mounted rigidly in the aircraft panel. Select a posi-
tion in the panel that is not too close to any high external heat source. Remember to allow adequate space for installation of cables and connectors.
Avoid sharp bends and placing the cables near aircraft control cables.
B. Refer to Figure 2-10 for the KX 155A/KX 165A mounting dimensions. Mark
and drill the mounting holes.
C. Secure the mounting rack to the instrument panel per Figure 2-11. The rear
mounting bosses should be attached to the aircraf t by mean s of support
brackets.
2.3.3 ANTENNA INSTALLATION
A. Conventional 50 ohm horizontally polarized NAV Gli deslope and vertically po-
larized COMM antennas are required with the KX 155A/KX 165A. Vertically
bent whip antennas are not recommended. Wideband COMM antennas provide efficient operation over the COMM band. Antennas should be installed
per manufacturer’s recommendations. Additional recommendations are as
follows:
1. COMM Antenna
a. Mount antenna on flat metal surface or install a ground plane at
least 18 inches square.
b. The antenna should be well removed from any projections and the
engine(s) and propeller.
2. Navigation Antennae (VOR/LOC & Glideslope)
a. The location should be well removed from other antennas, projec-
tions and engine(s). It shoul d have a clea r lin e of s ight ar ea if pos sible.
b. The antenna must be mounted symmetrically with the center line of
the aircraft.
c. Avoid running other coaxial and wires near the NAV antenna cable.
B. The antenna connectors on the KX 155A/KX 165A are identified on the rear
die casting.
NOTE
With KX 155A/KX 165A viewed from the front, the NAV antenna connector is on the ri ght and the COMM antenna con nector is on the left. This means that the NAV Frequency
Selector and NAV Antenna are on the same side of the radio. The COMM Frequency Selector and COMM Antenna
Connector are also on the same side of the radio. The
Glideslope Antenna Connector is right above the NAV Antenna Connector.
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KX 155A/165A
COMM/NAV SYSTEM
2.3.4 CABLE HARNESS AND CONNECTOR ASSEMBLY
The KX 155A/KX 165A uses a special co nnect or that mat es dire ctl y wit h the pr in ted circui t boar d
inside the unit. Assembly of the connector is as foll ows:
A. Contact Terminal Assembly using Molex Crimper (Figure 2-1 through 2-6)
1. Strip each wire 5/32" for contact terminal (Part Number 030-01107XXXX). (The last two digit s of the contact terminal part number i ndicates
the number of terminals required).
2. Open the Molex hand crimper HT 1921 with the engraved side toward
the operator. Place the conductor tab section of a contact terminal on
Anvil B with the contact portion facing away from the operato r. Close the
crimper slightly until the contact tabs touch the female jaw.
3. Insert the stripped conductor until the insulation is even with the side of
the crimper facing the operator. Cri mp the conductor tabs by squeezing
the handles together until the jaws are fully closed or a sufficient crimp
is obtained.
4. Move the lead to Anvil A. Place the insulating tab section on Anvil A.
Crimp again until the jaws are fully closed or a sufficient crimp is obtained.
B. Contact Insertion into Molex Connector Housing
1. After the contact terminals have been insta lled on the wiring harness, the
contact terminals can be in serted i nto the pro per l ocatio n in the connec tor housing (P/N 030-01094-00XX). The termi nal cannot be inserted upside down. Be sure to push the terminal all the way in, until a click can
be felt or heard.
2. The self locking feature can be tested by gently pulling on the wire.
C. Location of Polarizing Key in Housing
1. Prior to insertion of connector into rear of unit, check polarizing key position between contacts 3 and 4 for P155A1/P165A2 & between contacts
A & B and T & V of P155A1/P165A2.
2. Refer to Figure 2-11 to check correct position of polarizing key.
D. Extraction of Contact from Molex Connector
1. Slip the flat narrow blade of a Molex contact ejector tool, HT-1884 (P/N
005-02012-0011), under the contac t on the mating side of the connector.
By turning the connector upside down one can see the blade slide into
the stop.
2. When the ejector is slid into place, the retaining tab 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 th at retai ning tab " A" extends as shown (see Fig ure
2-1).
E. Coax Connector
Refer to Figure 2-9 for the details for mounting the right angle coaxial BNC
connector to the coax cable. Install the connector into the mounting rack.
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KX 155A/165A
COMM/NAV SYSTEM
2.3.5 KX 155A/KX 165A INSTALLATION
CAUTION
SEE PARAGRAPH 2.3.1 FOR COOLING
REQUIREMENTS.
A. Looking at the top of t he unit, ma ke sure the fr ont lobe of t he holddown device is in
a vertical position.
B. Slide the unit into the moun ting rack unt il the fr ont lobe touches the mounting rack .
C. Insert a 3/32" Allen wrench through the hole in t he front panel to engage the lo cking
screw. Turn clockwise until the rear lobe engages the mounting rack. Continue
turning until the unit is secure in the mounting rack. Do not overtighten.
D. For removal, turn the locking screw counterclockwise using a 3/32" Allen wrench
until the unit disengages from the mounting rack. Pul l the unit out of the mo unting
rack by pulling on the metal tabs located behind the front panel on each side of the
unit.
2.3.6 ELECTRICAL INSTALLATION NOTES
RETROFIT
CAUTION
Damage may occur in retrofit applications if the old
installation used COMM REMOTE TRANSFER or
NAV REMOTE TRANSFER. If a COMREMOTE
TRANSFER wire was connected to pin P or R, it
must be moved to P155A/165A1-23. If a NAV REMOTE TRANSFER wire was connected to pin 13 or
14, it must be removed. The KX 155A/KX 165A
does not support NAV REMOTE TRANSFER. Failure to remove the wire(s) will result in a direct short
to ground through the remote transfer switch to the
NAV/COM circuit breaker when the switch is
pressed. The circuit breaker and switch will be
damaged.
EFIS 40/50
The KX 165A may be interfaced to the Bendix/King EFIS 40/50 by using the KX 165A’s OBI
CLOCK, OBI DATA, and OBI SYNC outputs for VOR bearing (RMI needle) and deviation, the
COURSE DEVIATION +RIGHT and +LEFT for localizer deviation, and the GLIDESLOPE DEVIATION +UP and +DOWN for glideslope deviation. In order to use the KX 165A as a navigation
source, the EFIS 40/50 must be configured for KNS 81 as VOR/LOC 1 or 2. Additionally, t he KX
165A must be configured for Type II OBI data (see paragraph 3.1.4).
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