Honeywell KCS 55/55A Pictorial Navigation System Installation Manual
The KCS 55/55A Pictorial Navigation System provides a pictorial display of the horizontal navigation situation. The KI 525/525A also provides manual controls for course and heading datum selections. Outputs from the KI 525/525A are for automatic pilot or flight director, VOR receivers and additional compass loads.
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INSTALLATION MANUAL
KCS 55/55A
PICTORIAL NAVIGATION
SYSTEM
MANUAL NUMBER 006-00111-0010
REVISION 10 FEBRUARY 2002
WARNING
Prior to the export of this document, review for export license requirement is needed.
COPYRIGHT NOTICE
©1997-2002 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) 712-0400.
BENDIX/KING KCS 55/55A
REVISION HISTORY
KCS 55/55A Installation Manual
Part Number: 006-00111-XXXX
For each revision, add, delete, or replace pages as indicated. For full reprint, replace in entirety.
REVISION No. 8, June 2001
ITEM
All pages
ACTION
Full Reprint
REVISION No. 9, January 2002
ITEM
All pages
ACTION
Full Reprint
REVISION No. 10, February 2002
ITEM
All pages
ACTION
Full Reprint
Rev 10, Feb/2002 00111I10.JA
Page RH-1
BENDIX/KING
THIS PAGE IS RESERVED
KCS 55/55A
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Rev 10, Feb/2002
BENDIX/KING
SECTION I
GENERAL INFORMATION
PARAGRAPH
UNITS AND ACCESSORIES SUPPLIED
KI 525/525A PICTORIAL NAVIGATION INDICATOR
KMT 112 MAGNETIC AZIMUTH TRANSMITTER
KA 51/51A/51B SLAVING ACCESSORY
INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
SECTION II
INSTALLATION
PARAGRAPH
UNPACKING AND INSPECTING EQUIPMENT
KI 525/525A INDICATOR INSTALLATION
Rev 10, Feb/2002 00111I10.JA
KCS 55/55A
PAGE
PAGE
Page i
BENDIX/KING
PARAGRAPH
KMT 112 TRANSMITTER INSTALLATION
KA 51/51A/51B SLAVING ACCESSORY INSTALLATION
2.8.6 ALTERNATE METHOD OF COMPENSATION ADJUSTMENTS
AVAILABILITY OF 400 HZ. POWER FROM THE KG 102/102A
SECTION III
OPERATION
PARAGRAPH
KI 525/525A INDICATOR AND CONTROLS
Page ii 00111I10.JA
PAGE
Rev 10, Feb/2002
KCS 55/55A
PAGE
BENDIX/KING KCS 55/55A
LIST OF FIGURES
FIGURE PAGE
1-1 KCS 55/55A CRIMPING, INSERTION, AND EXTRACTION TOOLS
2-2 KI 525/525A INSTALLATION DRAWING
2-3 KG 102/102A INSTALLATION DRAWING
2-4 KMT 112 INSTALLATION DRAWING
2-5 KA 51 INSTALLATION DRAWING
2-6 KA 51A INSTALLATION DRAWING
2-7 KA 51B INSTALLATION DRAWING
2-8 KA 52 INSTALLATION DRAWING
2-9 KA 57 INSTALLATION DRAWING
2-10 KCS 55 COMPASS SYSTEM INTERCONNECT DIAGRAM
KCS 55A COMPASS SYSTEM (30HZ OBS RESOLVER) INTERCONNECT DIAGRAM
KCS 55A COMPASS SYSTEM (400HZ OBS RESOLVER) INTERCONNECT DIAGRAM
2-13 KX 175/KN 73/KN 77/KI 525/525A INTERCONNECT DIAGRAM 2-31
2-14 COMPLETE SILVER CROWN SYSTEM INTERCONNECT DIAGRAM
2-15 KN 72/KN 75/KI 525A INTERCONNECT DIAGRAM
2-16 KNS 80 - KI 525A INTERCONNECT DIAGRAM
2-17 KCS 55/55A/BENDIX FCS-810 AUTOPILOT INTERFACE INTERCONNECT
2-18 KCS 55/55A/CESSNA 300 NAVOMATIC INTERFACE INTERCONNECT
2-19 KCS 55A/KA 57 CESSNA 300A/CA395A INTERCONNECT
2-20 KCS 55/55A CESSNA NAVOMATIC 400 INTERFACE INTERCONNECT
KCS 55/55A CESSNA NAVOMATIC 400A AUTOPILOT INTERFACE INTERCONNECT
2-22 KCS 55/55A/CESSNA 400B AUTOPILOT INTERFACE INTERCONNECT
IC-388, 388C, 388M, 388MC INTERFACE INTERCONNECT
KCS 55/55A MITCHELL III AUTOPILOT W/IC 388-3 COUPLER INTERFACE INTERCONNECT
2-25 KCS 55/55A MITCHELL CENTURY IV AUTOPILOT INTERFACE INTERCONNECT 2-50
KCS 55/55A - AP106/AP107/913K-1 AUTOPILOT INTERFACE INTERCONNECT
2-27 KLN 90B - KI 525A INTERCONNECT DIAGRAM
2-28 KG 102/102A 400 Hz. SUPPLY INTERCONNECT DIAGRAM
3-1 KI 525/525A INDICATOR AND CONTROLS
3-2 KA 51/51A SLAVING ACCESSORY AND CONTROLS
3-3 KA 51B SLAVING ACCESSORY AND CONTROLS
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Page iii
BENDIX/KING
TABLE
LIST OF TABLES
KCS 55/55A
PAGE
Page iv 00111I10.JA
Rev 10, Feb/2002
BENDIX/KING KCS 55/55A
SECTION I
GENERAL INFORMATION
1.1
SYSTEM COMPONENT DESCRIPTION
The KCS 55/55A Pictorial Navigation System is composed of five units: KI 525/525A Pictorial
Navigation Indicator, KG 102/102A Directional Gyro, KMT 112 Magnetic Azimuth Transmitter, KA
51/51A/51B Slaving Accessory, and the KA 52 and KA 57 Autopilot Adapters, if required.
The KI 525/525A Pictorial Navigation Indicator provides a pictorial display of the horizontal navigation situation. The KI 525/525A also provides manual controls for course and heading datum selections. Outputs from the KI 525/525A are for automatic pilot or flight director, VOR receivers and additional compass loads.
The KG 102/102A Directional Gyro is a remote mounted unit which, in conjunction with the KMT
112 Magnetic Azimuth Transmitter, provides a gyro-stabilized magnetic heading to the KI 525/
525A Indicator. In addition to the slaving circuitry this unit contains an internal power supply which provides excitation voltages for the Magnetic Azimuth Transmitter and positive and negative D.C. voltages for the Pictorial Navigation Indicator and the Slaving Accessory.
The KMT 112 Magnetic Azimuth Transmitter senses the direction of the earths magnetic field and transmits this information to the Pictorial Navigation Indicator.
The KA 51/51A/51B Slaving Accessory is a panel mounted unit which contains the slaving meter, slaving switches, and corrector circuitry which compensates for the effect of local magnetic disturbances on the Magnetic Azimuth Transmitter.
The KA 52 Autopilot Adapter is an optional remote mounted device that converts the DC heading and course datum signals from the Pictorial Navigation Indicator into two separate AC signals compatible with certain autopilot systems.
The KA 57 Autopilot Adapter is an optional remote mounted device that converts the DC heading and course datum signals from the KI 525/525A Indicator into a single, switchable AC output signal compatible with certain autopilot systems.
1.2
FUNCTIONAL
(KCS 55 System)
When power is first applied to the KCS 55 System, and the system is in the slaved gyro mode, the heading display will automatically fast slave at the rate of 180 degrees per minute to align the slaving control transformer in the KI 525 with the magnetic heading transmitted by the KMT 112. The system will remain in this fast slave mode for 120 seconds after which it will automatically revert to the normal slaving mode and slave at a constant rate of 3 degrees per minute to keep the system aligned with the earth’s magnetic field. If the system is cycled from the free gyro mode to the slaved gyro mode by means of actuating the "slave in" button on the KA 51 the "fast slave" will automatically be repeated.
(KCS 55A System)
When power is first applied to the KCS 55A System, and the system is in the slaved gyro mode, the heading display will automatically fast slave at the rate of 180 degrees per minute to align the slaving control transformer in the KI 525A with the magnetic heading transmitted by the KMT 112.
The system will remain in this fast slave mode until the slaving error is reduced to zero and then revert to the normal slaving mode and slave at a constant rate of 3 degrees per minute to keep the system aligned with the earth’s magnetic field. If the system is cycled from the free gyro mode to the slaved gyro mode by means of actuating the "slave in" button on the KA 51A (toggle switches on the KA 51B), the "fast slave" will automatically be repeated.
Rev 10, Feb/2002 00111I10.JA
Page 1-1
BENDIX/KING KCS 55/55A
The tumble detect version, (KG 102A, P/N 060-0015-02), while in slaved gyro mode will automatically switch the system to fast slave mode when rates exceed approximately 25 degrees per second. Once the system display (KI 525/525A) matches earth’s magnetic field +/- 2 degrees, the system will revert back to slow slave mode.
Stabilized heading information is supplied to the KI 525/525A by the KG 102/102A. When in the slaved gyro mode this heading signal, which may vary at rates up to 30 degrees/second, is summed with the normal slaving signal from the KMT 112 to provide the final drive signal for the heading display.
When the system is in the free gyro mode the heading signal from the KG102/102A is the only input to the heading display drive. While in the free gyro mode the pilot may command changes in the displayed heading by means of depressing the clockwise or counterclockwise push buttons on the KA 51/51A (toggle switches on the KA 51B).
1.3
TECHNICAL CHARACTERISTICS
1.3.1
KCS 55/55A
SPECIFICATION
TSO COMPLIANCE:
SYSTEM ACCURACY:
POWER REQUIREMENTS:
SLAVING RATE:
SLAVING SENSITIVITY: and
WARM-UP TIME:
CHARACTERISTIC
TSO C6c
RTCA DO-138 Environmental Categories
KI 525/525A, versions 00-03 & 09-12
DAMAAAXXXXXX
KI 525A versions 04-08 & 13 DAPAAAXXXXXX
KA 51/51A: DAMAAAXXXXXX
KG 102, KA 52; KA 57: BAJAAAXXXXXX
KG 102A: BA/JN/AAAXXXXXX
KMT 112: BA/SV/AAAXXXXXX
Accurate to within 2
°
of local magnetic heading.
14VDC 15.8 max., 3.23 A
11.0 min.
28VDC 31.6 max., 1.73 A
22.0 min.
28VDC/NVG .12 A
5VDC .4 A
Normal: 3 degrees per minute
Fast: 180 degrees per minute
±
0.5
o
when in a field strength of Hx = 0.18 gauss
Hz = 0.54 gauss.
Varies from 1 min. at +55 o
C to 5 min. at -46 o
C.
Page 1-2 00111I10.JA
Rev 10, Feb/2002
BENDIX/KING KCS 55/55A
1.3.2
KI 525/525A
SPECIFICATION
SIZE:
WEIGHT:
MOUNTING:
CHARACTERISTIC
See Fig. 2-2
See Fig. 2-2
Flanged mounted through front of the instrument panel.
MATING CONNECTORS: See Paragraph 1.5
POWER INPUTS: 14VDC, .36 amps or 28VDC, .27 amps (required for lighting and NAV flag power); the KG 102/102A)
±
15VDC,
±
5VDC (provided by
Heading synchro transmitter: Requires a 26 volt, 400Hz rotor excitation for a 3-wire stator output equal to 206 millivolts per degree of heading rotation. (066-3029-01, 066-
3046-01/03/05/07/08/09/10/11/12/13 indicators only).
SIGNAL INPUTS: Slaving control transformer; 3-wire stator input from the
KMT 112.
VOR/LOC deviation meter: 150
±
20 microamperes through a resistance of 1000
±
30 ohms for a full scale deflection of five dots.
To-From pointer 200
±
40 microamperes through a resistance of 200
±
30 ohms for full deflection.
NAV warning flag: Disappears from view with an input of
225
±
15 microamperes through a resistance of 1000
±
30 ohms.
Glideslope deviation pointers: 150
±
20 micro amperes through a resistance of 1000
±
30 ohms for a full scale of two dots.
Glideslope flag input: 230
±
50 microamperes through a resistance of 1000
±
30 ohms. When glideslope is valid and after a 2 to 12 second delay pointers will come into view displaying deviation.
30Hz Course resolver: Omnirange zeroed at 300 degrees for 30Hz. Electrically equivalent to Clifton TWH-11-
F-08.
400Hz Course resolver: Electrically zeroed at 300 degrees for 400Hz. Electrically equivalent to Clifton TSH-
11-F-08. (066-3046-02/03/06/07/11/12/13 indicators only)
Drive signal for the heading loop drive motor from the KG
102/102A.
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Page 1-3
BENDIX/KING KCS 55/55A
1.3.2
KI 525/525A (cont).
SPECIFICATION
SIGNAL OUTPUTS:
CHARACTERISTIC
Heading synchro transmitter:
Output equal to 206 millivolts per degree of heading rotation. (066-3029-01 and 066-3046-01/03/05/07/08/09/10/
11/12/13 Indicators only)
Selected heading error output:
An internally excited transducer which supplies an error output equal to 0.55 volts D.C. per degree of displacement from the lubber line.
Selected course error output:
An internally excited transducer which supplies an error output equal to .21 volts D.C. per degree of displacement from the lubber line.
1.3.3
KG 102/102A
SIZE:
WEIGHT:
See Fig. 2-3
See Fig. 2-3
MOUNTING: Shock mounted (provided in installation kit)
MATING CONNECTOR: See Paragraph 1.5
POWER INPUTS:
SIGNAL INPUTS:
POWER OUTPUTS:
14VDC, 3.0 amperes or 28VDC, 1.5 amperes
Slaving error control transformer from the KI525/525A.
±
15 and +5VDC reference voltages for the KI525/525A and the KA 51/51A/51B.
A 7.2 VRMS, 400 Hz drive signal for the primary excitation of the KMT 112 and for use in the KA 51/51A/51B.
SIGNAL OUTPUTS:
(KG 102A Only)
A 5 VA maximum of 26 VAC, 400 Hz power is available for all uses.
A drive signal for the heading loop drive motor in the KI
525/525A.
Slaving meter drive signal for the
KA 51/51A/51B.
Pin a supplies a ground when compass system is valid.
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BENDIX/KING KCS 55/55A
1.3.4
KMT 112
SIZE: See Fig. 2-4
WEIGHT:
MOUNTING:
See Fig. 2-4
Rigid mount with three #6 non-magnetic screws in a remote magnetically stable area.
MATING CONNECTOR: See paragraph 1.5
POWER INPUT: 7.2VRMS, 400Hz from the KG 102/102A.
SIGNAL OUTPUT: An 800Hz synchro control transmitter type output to the KI
525/525A
1.3.5
KA 51/51A
SPECIFICATION
SIZE:
CHARACTERISTIC
See Fig. 2-5 and 2-6
WEIGHT: See Fig. 2-5 and 2-6
MATING CONNECTOR: See paragraph 1.5
POWER INPUTS: +5VDC from KG 102/102A
7.2 VAC 400Hz from KG 102/102A
KA 51A (071-1053-03)
KA 51A (071-1053-04)
SIGNAL INPUTS:
SIGNAL OUTPUTS:
+14VDC Lamp Supply
+28VDC Lamp Supply
Slaving meter drive signal from the KG 102/102A
Magnetic Azimuth Transmitter compensation outputs for
North/South and East/West correction to the KI 525/525A.
Clockwise and counterclockwise manual slave signals to the KG 102/102A
Slaved/free gyro mode logic signal to the KG 102/102A
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Page 1-5
BENDIX/KING
1.3.6
KA 51B
SPECIFICATION
SIZE:
WEIGHT:
TSO:
POWER INPUTS:
SIGNAL INPUTS:
SIGNAL OUTPUTS:
KCS 55/55A
CHARACTERISTIC
See Fig. 2-7
See Fig. 2-7
C6c, DO-138 Env. Cat. DANAAAXXXXXX
+5VDC from KG 102A or +12VDC from KSG 105
7.2VAC 400Hz from KG 102A or 26VAC 400Hz from KSG
105
+5VDC Lamp Supply (-03 version)
+14VDC Lamp Supply (-00/-05 version)
+28VDC Lamp Supply
(-01/-02/-04/-06 versions)
Slaving meter drive signal from the KG 102A/KSG 105.
Magnetic Azimuth Transmitter compensation outputs for
North/South and East/West correction.
Clockwise and counterclockwise manual slew signals to the KG 102A/KSG 105.
Slave/free gyro mode logic signal to the KG 102A/KSG
105.
1.3.7
KA 52
SPECIFICATION
SIZE:
WEIGHT:
MOUNTING:
CHARACTERISTIC
See Fig. 2-8
See Fig. 2-8
Rigid mount with four #6 screws.
MATING CONNECTOR: See paragraph 1.5
POWER INPUTS:
±
15 volts DC from the KG 102/102A
SIGNAL INPUTS: Heading select DC input from the KI 525/525A
SIGNAL OUTPUTS:
Course datum DC input from the KI 525/525A
AC reference input from the aircraft autopilot system at 5 volts R.M.S. minimum.
Heading select AC output transformer isolated and phase locked to the reference input from the autopilot.
Course datum AC output transformer isolated and phase locked to the reference input from the autopilot.
Page 1-6 00111I10.JA
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BENDIX/KING KCS 55/55A
1.3.8
KA 57
SIZE: x 10.20 centimeters)
WEIGHT:
See Fig. 2-9
See Fig. 2-9
MATING CONNECTOR: See paragraph 1.5
POWER INPUTS:
±
15 volts DC from KG 102/102A
SIGNAL INPUTS:
SIGNAL OUTPUTS:
Heading select DC input from the KI 525/525A Course datum DC input from the KI 525/525A AC reference input from aircraft autopilot system at 7 volts R.M.S. minimum.
Localizer Normal - ground when radio coupler selector switch is at LOC Normal.
Localizer Energized - ground when NAV 1 receiver tuned to localizer frequency.
Heading select AC or course datum AC output transformer isolated and phase locked to the reference input from the autopilot.
1.4
UNITS AND ACCESSORIES SUPPLIED
1.4.1
KI 525/525A PICTORIAL NAVIGATION INDICATOR
The KI 525/525A is an internally lighted unit that displays a gyro-stabilized aircraft magnetic heading, selected course, selected heading. VOR and localizer course deviation, glideslope deviation and a TO-FROM indication for VOR flight.
In addition, warning flags are provided to signify unusable VOR/Localizer information (NAV Flag) and to indicate a valid compass system (HDG Flag). The glideslope pointer will retract from view when an unusable glideslope signal is being received.
A bootstrap heading synchro is provided as a source of slaved heading information, and heading and course select transducers provide DC signals for autopilot or flight direction information. Either of two types of course resolver is provided depending on which part number unit is chosen.
All part numbers are capable of operating at 30Hz. However, 066-03046-02/03/06/07/11/12/13 are capable of operating at either 30Hz or 400Hz. Serial number 43434 and above have glideslope damping for helicopters in all versions.
Rev 10, Feb/2002 00111I10.JA
Page 1-7
BENDIX/KING KCS 55/55A
PN
066-3046-00
066-3046-01
066-3046-02
066-3046-03
066-3046-04
066-3046-05
066-3046-06
066-3046-07
066-3046-08
066-3046-09
066-3046-10
066-3046-11
066-3046-12
066-3046-13
BEZEL
BLACK
BLACK
BLACK
BLACK
BLACK
BLACK
BLACK
BLACK
BLACK
BLACK
GRAY
GRAY
BLACK
BLACK
OBS
30 HZ
30 HZ
30/400 HZ
30/400 HZ
30 HZ
30 HZ
30/400 HZ
30/400 HZ
30 HZ
30 HZ
30 HZ
30/400 HZ
30/400 HZ
30/400 HZ
Table 1-1 KI 525A Version Chart
LIGHTING
14/28 V
14/28 V
14/28 V
14/28 V
14/28 V
14/28 V
14/28 V
14/28 V
5 V
28 V NVG
5 V
5 V
5 V
28 V NVG
X
X
X
X
X
X
X
X
X
HDG XMTR
X
PN
066-3029-00
066-3029-01
BEZEL
BLACK
BLACK
LIGHTING
14/28 VDC
14/28 VDC
OBS
30 HZ
30 HZ
Table 1-2 KI 525 Version Chart
HDG XMTR
X
1.4.2
KG 102/102A DIRECTIONAL GYRO
The KG 102/102A Directional Gyro is a remote mounted unit which, in conjunction with the KMT
112 Magnetic Azimuth Transmitter, provides a gyro stabilized magnetic heading to the KI 525/
525A Indicator. In addition to the slaving circuitry the KG 102/102A contains an internal power supply which provides gyro rotor power, excitation voltages for the Magnetic Azimuth Transmitter, and positive and negative D.C. voltages for the Pictorial Navigation Indicator and the Slaving Accessory.
PN 060-0011-00 is the only version available for the KG 102. The KG 102A is available in a standard version (PN 060-0015-00), a version with RFI filter (PN 060-0015-01), and a version with RFI filter and tumble detection (PN 060-0015-02).
Page 1-8 00111I10.JA
Rev 10, Feb/2002
BENDIX/KING KCS 55/55A
1.4.3
KMT 112 MAGNETIC AZIMUTH TRANSMITTER
The KMT 112 (PN 071-1052-00) senses the direction of the earth’s magnetic field and transmits this information to the KI 525/525A.
1.4.4
KA 51/51A/51B SLAVING ACCESSORY
The KA 51 Slaving Accessory (PN 071-1053-00) is a panel mounted unit that displays the slaving error between the KMT 112 and the KI 525 by means of a small meter movement.
The KA 51A/51B Slaving Accessory is an internally lighted panel mounted unit that displays the slaving error between the KMT 112 and KI 525A by means of a small meter movement.
KA 51A, three pushbutton switches are provided below the slaving meter. The center switch is an alternate action switch that engages the "slaved gyro" mode when depressed. When the switch is in its outer position the KCS 55/55A is in the "free gyro" mode. The other two pushbutton switches are momentary switches and provide clockwise and counterclockwise manual slaving whenever the system is in the "free gyro" mode.
The KA 51/51A also contains circuitry through which hard-iron effects upon the KMT 112 can be compensated by the adjustment of two potentiometers. Access holes labeled N/S and E/W are provided on the front surface of the KA 51/51A for access to these two potentiometers.
The KA 51B, houses two toggle switches below the slaving meter. The switch nearest the meter
(SLAVE/FREE) is a lockout type toggle switch that engages the slaved gyro mode when in the slave position and places the KCS 55A/KCS 305 in the free gyro mode when in the free position.
The lower switch (CW/CCW) is a momentary left and right toggle switch and provides clockwise and counterclockwise manual slewing whenever the system is in the free gyro mode.
The KA 51B also contains circuitry through which hard iron effects upon the KMT 112 can be compensated by the adjustment of two potentiometers. Access holes labeled N/S and E/W are provided on the side of the unit for access to the two potentiometers.
PN
071-1053-00
071-1053-01
071-1053-02
071-1053-03
071-1053-04
071-1053-05
071-1053-06
071-1053-07
071-1053-08
071-1053-09
Rev 10, Feb/2002
BEZEL
BLACK
BLACK
GRAY
BLACK
BLACK
GRAY
BLACK
GRAY
GRAY
BLACK
Table 1-3 KA 51/51A Version Chart
LIGHTING
NONE
5 V
5 V
14 V
28 V
28 V
5 V RED
5 V RED
14 V
28 V RED
00111I10.JA
Page 1-9
BENDIX/KING KCS 55/55A
PN
071-1242-00
071-1242-01
071-1242-02
071-1242-03
071-1242-04
071-1242-05
071-1242-06
071-1242-07
071-1242-08
071-1242-09
071-1242-10
071-1242-11
071-1242-12
071-1242-13
071-1242-14
GRAY
GRAY
GRAY
BLACK
BLACK
BLACK
GRAY
GRAY
BEZEL
BLACK
BLACK
GRAY
BLACK
BLACK
BLACK
BLACK
LIGHTING
14 V
28 V
28 V
5 V RED
28 V RED
14 V
28 V
5 V
5 V
28 V
5 V
5 V
28 V NVG
5 V
5 V
FACEPLATE
VERTICAL
VERTICAL
VERTICAL
VERTICAL
VERTICAL
HORIZONTAL
HORIZONTAL
HORIZONTAL
VERTICAL
HORIZONTAL
VERTICAL
HORIZONTAL
HORIZONTAL
VERTICAL
HORIZONTAL
Table 1-4 KA 51B Version Chart
1.4.5
KA 52 AUTOPILOT ADAPTER
The KA 52 Autopilot Adapter is an optional remote mounted device that converts the DC heading and course datum signals from the KI 525/525A Indicator into two separate AC signals compatible with certain autopilot systems. PN 071-1055-00 is the standard version. PN 071-1055-01 is available when 115 V 400 Hz ref. is needed by Radar for Stabilization.
1.4.6
KA 57 AUTOPILOT ADAPTER
The KA 57 Autopilot Adapter (PN 071-0017-00) is an optional remote mounted device that converts the DC heading and course datum signals from the KI 525/525A Indicator into a single, switchable AC output signal compatible with certain autopilot systems.
Page 1-10 00111I10.JA
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BENDIX/KING KCS 55/55A
1.5
INSTALLATION KITS
See figure 1-1 for crimping, insertion, and extraction tools.
A.
KI 525/525A Installation Kit P/N 050-01344-0000 (solder connector), -0001 (solder connector with extended knob), and -0002 (crimp connector) includes the following:
PN Description Qty
-0000 -0001 -0002
24
41
030-01080-0001
030-01081-0001
030-02153-0000
030-02154-0000
030-02178-0000
030-02272-0000
030-02272-0001
047-03937-0001
057-02105-0016
076-00904-0001
089-05115-0012
Conn, FM Crmp 20 AWG
Conn, ML Crmp 20 AWG
Conn, 24 Pin
Conn, Hood
Conn, Plug 41 Pin
Conn, 41P Shell
Conn Shell, 41 Pin, Male
Plate, Nut
Decal, Cut out
Spacer, Knob
Scr. PFH #6-32 x 3/4
1
-
1
4
1
2
1
1
1
2
4
1
2
1
2
1
2
4
1
1
1
B.
KMT 112 Installation Kit (050-01361-0000) includes the following:
PN
030-02190-0000
089-02157-0015
089-07009-0010
089-08036-0019
Description
Conn, 5 Pin
Nut, Hex #6-32
Scr. SPH #6-32 x 5/8
Washer #6
3
6
Qty.
1
3
C.
KG 102A Installation Kit P/N 050-01410-0001 (solder connector), -0002 (crimp connector), and -0050 includes the following:
PN
030-01080-0001
030-02154-0000
030-02221-0000
030-02272-0000
057-01611-0000
071-04025-0001
089-05909-0009
155-02001-0000
Description
Conn, FM Crmp
Conn, Hood
Conn, Rec. 37 Pins
Conn, 41P Shell
Shock Mount Hole Temp
Assy Vibration Mount
Scr. #8-32 X 9/16 PHP
GND Strap
2
1
1
1
1
1
QTY.
-01 -02 -50
37
1 1
1
1
2
1
1
1
Rev 10, Feb/2002 00111I10.JA
Page 1-11
BENDIX/KING KCS 55/55A
The shock mount assembly (P/N 071-04025-0001) contains the following:
PN
047-03221-0002
052-00008-0002
089-06073-0006
Description
Mounting Rack
Shock Mount
Screw FHP 8-32X3/8
Qty.
1
4
4
D.
KA 51A Installation Kit (050-01428-00/-01) includes the following:
PN
030-02224-0000
088-00450-0000
089-05899-0007
089-06163-0008
089-06596-0008
089-08163-0001
Description
Conn, 14 Pin
Conn, Hood
Scr., PHP, 2-56 X 7/16
Scr., FHP #4-40 X 1/2
Scr., FHP #4-40 X 1/2
Washer, Flat #2
2
4
-00
1
1
2
-01
1
1
2
4
2
E.
KA 51 Installation Kit (050-01362-0000) includes the following:
PN
030-00107-0000
088-00405-0000
089-05111-0008
089-06414-0007
Conn, 12 Pin
Conn, Hood
Scr. PHF #4-40 x 1/2
Scr. PHP #2-28 x 7/16
1
1
4
2
F. KA 52 Installation Kit (050-01390-0000) includes the following:
PN
030-00107-0011
088-00450-0000
089-05903-0007
Description
Conn, 12 Pin
Conn, Hood
Scr. PHP #4-40 x 7/16
Qty.
1
1
2
G.
KA 57 Installation Kit (050-01421-0000) includes the following:
PN
030-00107-0016
088-00438-0000
089-05903-0006
Description
Conn, 20 Pin
Conn, Hood
Scr. PHP #4-40 x 3/8
1
2
Qty.
1
Page 1-12 00111I10.JA
Rev 10, Feb/2002
BENDIX/KING KCS 55/55A
H.
The KA 51B Installation Kit 050-01928-0000 contains the following:
PN
030-02421-0000
030-02423-0000
047-05759-0002
047-05760-0002
089-06163-0008
Description
9 Pin Connector
5 Pin Connector
Mtg. Ring
Mtg. Plate
Scr., FHP #4-40 X 1/2
Qty.
1
1
1
1
2
1.6
COMPENSATOR KIT (OPTIONAL)
Also available, is an optional Compensator Kit (050-01928-0001) for installations where the installer wishes to use a different switch/meter arrangement. The Compensator Kit PN 050-01928-0001 contains the following:
PN
030-02423-0000
047-05760-0002
200-02846-0000
Description
5 Pin Connector
Mtg. Plate
Compensator Assembly
1
1
Qty.
1
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.
Rev 10, Feb/2002 00111I10.JA
Page 1-13
BENDIX/KING KCS 55/55A
CRIMPING TOOL
HONEYWELL P/N 005-02012-0017
POSITRONICS P/N 9501
DANIELS P/N M22520/1-01
POSITIONER
HONEYWELL P/N 005-02012-0018
POSITRONICS P/N 9502-1
DANIELS P/N M22520/1-03
CRIMPING TOOL / POSITIONER
BUCHANAN P/N 615710
INSERTION TOOL (NOT PICTURED)
HONEYWELL P/N 005-02012-0015
POSITRONICS P/N 9099
EXTRACTION TOOL (NOT PICTURED)
HONEYWELL P/N 005-02012-0012
POSITRONICS P/N 9081
FIGURE 1-1 KCS 55/55A CRIMPING, INSERTION, AND EXTRACTION TOOLS
Page 1-14 00111I10.JA
Rev 10, Feb/2002
BENDIX/KING KCS 55/55A
SECTION II
INSTALLATION
2.1
UNPACKING AND INSPECTING EQUIPMENT
Exercise extreme care when unpacking the equipment. Make a visual inspection of the unit for evidence of damage incurred during shipment. If a claim for damage is to be made, save the shipping container to substantiate the claim. The claim should be promptly filed with the transportation company. It would be advisable to retain the container and packaging material after all equipment has been removed in the event that equipment storage or reshipment should become necessary.
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.
NOTE
THE KG 102/102A CONTAINS A VERY SENSITIVE
GYRO. IN ORDER TO PREVENT DAMAGE DUR-
ING SHIPMENT ALL SHIPMENTS MUST BE MADE
IN THEIR ORIGINAL PACKING CONTAINERS.
2.2
PREINSTALLATION CHECK
The equipment has been completely tested before leaving the factory. To ensure that the equipment has not been damaged in shipment, it is suggested that the preinstallation bench test be per-
formed. The bench test harness or aircraft cables wired per Figures 2-9 and
this test. Inputs and performance are indicated in the component technical characteristics speci-
fications, paragraph 1.4.1 through 1.4.6.
WARNING
IT HAS BEEN DETERMINED THAT THE KCS 55/
KCS 55A PICTORIAL NAVIGATION SYSTEM AND
ITS ASSOCIATED KA 52 AND/OR KA 57 AUTOPI-
LOT ADAPTORS ARE NOT FULLY COMPATIBLE
WITH THE PIPER ALTIMATIC II AUTOPILOT.
HONEYWELL SUGGESTS THAT NO ATTEMPT
BE MADE TO INTERFACE THE KCS 55/55A SYS-
TEM WITH THE ALTIMATIC II OR ANY OTHER "RF
SENSING DESIGN" AUTOPILOT SYSTEM.
CAUTION:
EXTREME CAUTION SHOULD BE TAKEN TO EN-
SURE THAT 28 VOLTS DC IS NOT APPLIED TO
UNITS THAT ARE SWITCHED TO THE 14 VOLTS
DC POSITION ON THE KG 102/102A.
NOTE:
FOR THE CENTURY 21/31/41 AUTOPILOT INTER-
FACES, AN IC 930 ADAPTER IS AVAILABLE
FROM CENTURY FLIGHT SYSTEMS. CONTACT
AT TEL: (817) 325-2517.
Rev 10, Feb/2002 00111I10.JA
Page 2-1
BENDIX/KING KCS 55/55A
CAUTION:
THE FOLLOWING PRECAUTIONS MUST BE OB-
SERVED WHILE FABRICATING THE SYSTEM IN-
STALLATION HARNESS AND REMOVING/REIN-
STALLING UNITS FOR MAINTENANCE. TO
AVOID CONNECTOR DAMAGE:
1. WHEN FABRICATING THE INSTALLATION
HARNESS FOR THE KCS 55/KCS 55A SYSTEM,
SUFFICIENT STRAIN RELIEF SHOULD BE LEFT
IN THE HARNESS AT THE CONNECTORS SO AS
NOT TO APPLY ANY UNDUE STRESS TO THEM.
2. SYSTEM CONNECTORS SHOULD BE IN-
SPECTED FOR POSSIBLE DAMAGE DURING RE-
MOVAL AND REINSTALLATION.
3. CARE SHOULD BE TAKEN WHEN MATING THE
CONNECTORS TO INSURE THAT THE PINS EN-
GAGE WITHOUT UNDUE FORCE SO AS NOT TO
DAMAGE PINS IN EITHER CONNECTOR. DAM-
AGED CONNECTORS WILL COME UNDER
CLOSE INSPECTION TO DETERMINE THE VA-
LIDITY OF ANY WARRANTY CLAIMS.
4. AFTER INSTALLATION OF THE CABLING AND
BEFORE INSTALLATION OF THE EQUIPMENT, A
CHECK SHOULD BE MADE WITH AIRCRAFT PRI-
MARY POWER SUPPLIED TO THE MOUNTING
CONNECTOR. THIS WILL ENSURE THAT POW-
ER IS APPLIED ONLY TO THE PINS SPECIFIED
IN THE INTERCONNECTION DIAGRAMS.
The TSO identifies the minimum performance standards, tests, and other conditions applicable for issuance of design and production approval of the article. The TSO does not specifically identify acceptable conditions for installation 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
KI 525/525A INDICATOR INSTALLATION
2.3.1
GENERAL
The KI 525/525A is an internally lighted panel mounted unit that provides compass heading and navigation information for the pilot. Location for the mounting of this unit should be such that it will be easily viewed, preferably directly in front of the pilot, with a minimum of parallax.
2.3.2
MOUNTING
The KI 525/525A is mounted from the front of the aircraft panel and should be secured per Figure
2-2 with four #6-32 screws that are provided with the unit. Using the connectors provided connect
the system wiring and the navigation and lighting wiring per
Page 2-2 00111I10.JA
Rev 10, Feb/2002
BENDIX/KING KCS 55/55A
2.4
KG 102/102A GYRO INSTALLATION
2.4.1
GENERAL
The KG 102/102A Gyro is a remote mounted unit that provides gyro stabilized magnetic heading to the KI 525/525A Indicator when coupled to the KMT 112 Transmitter.
2.4.2
MOUNTING
The KG 102/102A may be mounted in any convenient location. The mounting surface should be such that when the aircraft is in level flight the mounting surface of the KG 102/102A will be level within
±
5
degrees in any direction. The unit should be secured with two #8 screws into the vibra-
tion mount per Figure 2-3 . Using the connector furnished with the unit connect the wiring as
2.5
KMT 112 TRANSMITTER INSTALLATION
2.5.1
GENERAL
The KMT 112 Transmitter detects the horizontal component of the earth’s magnetic field and transmits them to the KI 525/525A Indicator for use as long term correction information.
2.5.2
MOUNTING
The KMT 112 should be located as far as possible from all sources of local magnetic disturbances such as engines, electrical cables, or radio equipment. A wing tip or tail section location will usually be satisfactory. The use of a hand held compass can be helpful in determining if the selected area is free of magnetic disturbance. The mounting surface should be such that when the aircraft is in level flight the mounting flange of the KMT 112 will be level within
±
2 degrees. The unit should be secured per
Figure 2-4 with the three #6-32 non-magnetic screws and associated non-
magnetic hardware that are provided with the unit. Using the connector provided connect the wir-
ing to the unit as shown in Figures 2-9 and
2.6
KA 51/51A/51B SLAVING ACCESSORY INSTALLATION
2.6.1
GENERAL
The KA 51/51A/51B Slaving Accessory is a panel mounted unit that contains the slaving meter, slaving switches, and corrector circuitry which compensates for the effect of local magnetic disturbances. The KA 51A/51B is internally lighted.
2.6.2
MOUNTING
The KA 51/51A is mounted from the front of the aircraft panel and should be secured per Figure
6 with four #4-40 screws that are provided with the unit. Using the connector provided con-
nect the wiring to the unit as shown in Figure 2-9
The KA 51B is mounted from the front of the aircraft panel (the compensator assembly may be
remote mounted) and is secured per Figure 2-1 with two #4-40 screws provided in the installation
kit. Using the connector provided, connect the wiring to the unit as shown in Figure 2-2 .
Rev 10, Feb/2002 00111I10.JA
Page 2-3
BENDIX/KING KCS 55/55A
2.7
ADAPTER INSTALLATION
2.7.1
KA 52 ADAPTER
The KA 52 is an optional remote mounted unit that converts the DC heading and course datum signals from the KI 525/525A to AC signals compatible with certain autopilot systems.
2.7.2
MOUNTING
The KA 52 may be mounted in any convenient location with four #6 screws per Figure 2-7 . It is
suggested that the unit be mounted so that it is accessible in flight in order for service personnel to perform alignment adjustments for optimum performance. The mating connector is furnished
with the unit. Figures 2-9 and
2-10 shows a typical installation that incorporates the KA 52.
2.7.3
KA 57 ADAPTER
The KA 57 is an optional remote mounted unit that converts the DC heading and course datum signals from the KI 525/525A into an AC signal compatible with certain autopilots that have a single input. The KA 57 has a single output, Heading Select or Course Datum, that is determined by the Autopilot switching.
2.7.4
MOUNTING
The KA 57 may be mounted in any convenient location with four #6 screws per Figure 2-8 . It is
suggested that the unit be mounted so that it is accessible in flight in order for service personnel to perform alignment adjustments for optimum performance. The mating connector is furnished with the unit.
2.8
ADJUSTMENTS
2.8.1
KI 525/525A
No adjustments are required.
2.8.2
KG 102/102A
A switch located on the top surface of the KG 102/102A has a 14 volt and a 28 volt position. This switch must be set in the position that corresponds with the input DC voltage. To change the switch position remove the switch cover, set the switch in the desired position, then re-install the switch cover. The correct input DC voltage (14 or 28) should then be seen through the switch cover.
2.8.3
KMT 112
With the complete KCS 55/55A system operating and synchronized, position the aircraft on a compass rose and turn it to each of the four cardinal headings. Place the KA 51/51A/51B in the "Free
Gyro" mode and center the slave meter with the manual slave buttons on the KA 51/51A (toggle switches on the KA 51B) at each of these headings. Record the algebraic error between the compass rose and the heading on the KI 525/525A. Add the algebraic errors and divide by four to obtain the index error.
Loosen the mounting screws on the KMT 112 and rotate the unit an amount equal to the index error to cancel-out the index error. Retighten the mounting screws. This procedure should be repeated after the N/S E/W compensator has been adjusted (see paragraph 2.8.4).
2.8.4
KA 51/51A
With the complete KCS 55/55A system operating and the KA 51/51A in the "free gyro" mode; position the aircraft on a compass rose and adjust the compensator as follows:
Page 2-4 00111I10.JA
Rev 10, Feb/2002
BENDIX/KING KCS 55/55A
A.
B.
Place the aircraft on a North heading and rotate the compass card to NORTH with the manual slave buttons. Place a non-magnetic blade screwdriver in the N/S opening on the KA 51/51A and center the slave meter.
Place the aircraft on an East heading and rotate the compass card to EAST with the manual slave buttons. Place a non-magnetic blade screwdriver in the E/W opening on the KA 51/51A and center the slave meter.
C.
D.
Place the aircraft on a South heading and rotate the compass card to SOUTH with the manual slave buttons. Place a non-magnetic blade screwdriver in the N/S opening on the KA 51/51A and adjust the meter for one-half of the existing meter deviation.
Place the aircraft on a West heading and rotate the compass card to WEST with the manual slave buttons. Place a non-magnetic blade screwdriver in the E/W opening on the KA 51/51A and adjust the meter for one-half of the existing meter deviation.
To achieve maximum accuracy of the system the index-error of the KMT 112 should be re-adjust-
above. All reading should be within
±
2 degrees of those on the compass rose.
2.8.5
KA 51B
With the complete KCS 55A Compass System operating and the KA 51B in the "Free Gyro" mode, position the aircraft on a compass rose. Remove the two mounting screws that secure the unit to the panel and slide the unit out until the meter test jacks and compensator potentiometers are accessible. If the compensator assembly is remote mounted, gain access to the compensator potentiometers. Connect a digital millivolt meter to the unit test jacks (common connection of the millivolt meter to the black test jack of the KA 51B and positive connection of the millivolt meter to the red test jack of the KA 51B). Adjust the compensation as follows:
A.
B.
Place the aircraft on a North heading and center the compass card North under the
Lubber line with the CW/CCW switch. Place a non-magnetic blade screwdriver in the N/S potentiometer in the KA 51B Compensator Assembly and zero the external millivolt meter (0.0VDC
±
50mV).
Place the aircraft on an East heading and center the compass card East under the
Lubber line with the CW/CCW switch. Place a non-magnetic blade screwdriver in the E/W potentiometer in the KA 51B Compensator Assembly and zero the external millivolt meter (0.0VDC
±
50mV).
C.
D.
Place the aircraft on a South heading and center the compass card South under the Lubber line with the CW/CCW switch. Place a non-magnetic blade screwdriver in the N/S potentiometer in the KA 51B Compensator Assembly and adjust the external millivolt meter for 1/2 of the existing millivolt meter readout.
Place the aircraft on a West heading and center the compass card West under the
Lubber line with the CW/CCW switch. Place a non-magnetic blade screwdriver in the E/W potentiometer in the KA 51B Compensator Assembly and adjust the external millivolt meter for 1/2 of the existing millivolt meter readout.
As a final check of the KCS 55A Compass System, position the aircraft on the compass rose and turn to each of the four cardinal headings while the KCS 55A System is in the Slaved Gyro mode.
All readings should be within
±
2 o
of those on the compass rose. The KA 51B can now be resecured to the aircraft panel. The alignment is complete.
Rev 10, Feb/2002 00111I10.JA
Page 2-5
BENDIX/KING KCS 55/55A
CAUTION:
INSTRUMENT AND GYRO REPAIR MUST BE
ACCOMPLISHED BY A HONEYWELL AP-
PROVED INSTRUMENT SERVICE CENTER.
WARRANTY IS VALID ONLY WHEN THE
DUST COVER SEAL IS IN CONTACT.
2.8.6
ALTERNATE METHOD OF COMPENSATION ADJUSTMENTS FOR KMT 112
AND KA 51/KA 51A
The small slaving indicator in the KA 51/KA 51A, although shielded, is still susceptible, to magnetic and electrical interference occurring in and around the aircraft instrument panel. This interference, depending upon the KA 51/KA 51A’s location in the instrument panel, can cause an observable indicator needle offset in the compass system during power on and/or power off conditions. The following adjustment procedures should be used to align the compass system more accurately.
Remove the KA 51/KA 51A from its housing and connect a digital millivolt meter to the rear of the slaving indicator, black wire to the common and red wire to the positive connection of the millivolt meter.
A.
KMT 112 Alignment
With the complete KCS 55/KCS 55A System operating and synchronized, position the aircraft on a compass rose and turn it to each of the four cardinal headings.
Place the KA 51/KA 51A in the "Free Gyro" mode and zero the external millivolt meter with the manual slave buttons on the KA 51/KA 51A at each of these headings. Record the error, as a signed number, e.g. (-4), between the compass rose and heading on the KI 525/KI 525A. Add the errors algebraically and divide by four to obtain the index error. Loosen the mounting screws on the KMT 112 and rotate the unit an amount equal and opposite to the index error to cancel out the index error. Retighten the mounting screws.
B.
KA 51/KA 51A Adjustment
With the complete KCS 55/KCS 55A System operating and the KA 51/KA 51A in the "Free Gyro" mode; position the aircraft on a compass rose and adjust the compensation as follows:
1.
2.
3.
Place the aircraft on a North heading and center the compass card North under the lubber line with the manual slave buttons. Place a non-magnetic blade screwdriver in the N/
S potentiometer on the KA 51/KA 51A and zero the external millivolt meter. (0VDC
±
50mV)
Place the aircraft on an East heading and center the compass card East under the lubber line with the manual slave buttons. Place a non-magnetic blade screwdriver in the E/
W potentiometer on the KA 51/KA 51A and zero the external millivolt meter. (0VDC
±
50mV)
Place the aircraft on a South heading and center the compass card South under the lubber line with the manual slave buttons. Place a non-magnetic blade screwdriver in the N/
S potentiometer on the KA 51/KA 51A and adjust the external millivolt meter for 1/2 of the existing meter readout.
Page 2-6 00111I10.JA
Rev 10, Feb/2002
BENDIX/KING KCS 55/55A
4.
Place the aircraft on a West heading and center the compass card West under the lubber line with the manual slave buttons. Place a non-magnetic blade screwdriver in the E/
W potentiometer on the KA 51/KA 51A and adjust the external millivolt meter for 1/2 of the existing meter readout.
As a final check of the KCS 55/KCS 55A System, the aircraft should be positioned on the compass rose and turned to each of the four cardinal headings while the
KCS 55/KCS 55A System in the "Slaved Gyro" mode. All readings should be within
±
2 o
of those on the compass rose.
Next with the aircraft on a North heading and the KCS 55/KCS 55A System turned off but all other aircraft systems still on, adjust the KA 51/KA 51A indicator movement via the adjustment in the upper rear of the indicator to zero the slaving indicator. The KA 51/KA 51A can now be reassembled in the aircraft; the alignment is complete.
2.8.7
KA 52 AND KA 57
NOTE:
The autopilot operation must be confirmed as correct before the following adjustments are attempted. If possible, check the autopilot components alignment on the bench.
Take off the KA 52/57 dust cover by removing the two screws on the side of the unit. The HDG and CRS potentiometers at the left rear of the printed circuit board (viewing the board from the connector end) provide the gain adjustments for the course and heading modes of operation. The following is a procedure for setting the gains for the Mitchell Century II and III autopilots. The variations in the procedure for setting the gains in other autopilots are given at the end of each section.
NOTE:
On the KA 57 R108, the HDG select gain adjust is located near the outside edge of the board. R109, the
CRS datum gain adjust is located toward the center of the board. On KA 52’s, the adjustments are marked accordingly.
HDG: With the autopilot off, manually adjust the attitude gyro for +10 o
of offset (the attitude gyro artificial horizon rotated 10 o
counterclockwise from its 0 o
position). Turn on the autopilot and set it in the Heading mode (Radio Coupler selector switch set to Heading) and position the KI 525 Heading Select Marker for +10 o
of offset (Marker 10 o
clockwise from lubber line). Adjust the HDG potentiometer until there is no movement of the control wheel. Check the gain setting by repositioning the control wheel to the center of its range and observing that there is no movement either clockwise or counterclockwise.
Next, turn off the autopilot and reposition the attitude gyro for -10 o
of offset (the attitude gyro artificial horizon rotated 10 o
clockwise from its 0 o
position). Turn on the autopilot and slew the Heading Select Marker to -10 o
(Marker 10 o
counterclockwise from the lubber line).
Rev 10, Feb/2002 00111I10.JA
Page 2-7
BENDIX/KING KCS 55/55A
The control wheel should stop moving when the marker reaches -10 o
. Center the control wheel to midrange and observe there is no movement either clockwise or counterclockwise.
The absolute value of the null position clockwise and counterclockwise from the lubber line (nominally
±
10 o
) should be within two degrees of each other.
For Cessna Autopilots, the procedure for setting the HDG gain is the same as that described above except for the controller settings which are as follows:
Pull-Turn Control Knob - Pushed in
Intercept - TRK-HDG - HDG
CRS: Set the attitude gyro for 0 o
of offset, turn on the autopilot and set it for the Course
Mode (Radio Coupler Selector switch set on OMNI). Acquire a VOR station on the appropriate radio and when the KI 525/525A NAV flag disappears center the
Course pointer and deviation bar under the lubber line. Next, rotate the Course pointer to +45 o
(clockwise from the lubber line by 45 o
) and adjust the CRS potentiometer until there is no movement of the control wheel. Reposition the control wheel to the center of its range and observe there is no movement of the control wheel.
Next, check the setting of the CRS gain by slewing the Course pointer to -45 o
(counterclockwise from the lubber line by 45 o
) the control wheel should stop moving when the Course pointer reaches -45 o
. The absolute value of the two intercepts (nominally
±
45 o
) should be within 5 o
of each other.
For the Cessna Autopilots, the procedure for setting the CRS gain is the same as that described above except for the Controller Settings which are as follows:
Pull - Turn Control Knob - Pushed in
Intercept - TRK - HDG - Intercept
To check the Mitchell Century II & III Localizer operation, set the appropriate radio to a Localizer frequency and the Radio Coupler selector switch to LOC. Rotate the
KI 525/525A Course pointer clockwise and note that the control wheel also rotates clockwise. Change the Radio Coupler selector switch to LOC REV, rotate the
Course pointer clockwise and observe that the control wheel rotates in the opposite direction, counterclockwise. The back course approach is flown with the course pointer set to the front course to give proper deviation bar steering to the pilot.
NOTE:
When the KA 57 is coupled to a Mitchell Century II or
III and the system is operated incorrectly by selecting a Radio Coupler LOC mode with a VOR frequency selected on the Radio or a VOR Omni mode on the Radio Coupler with an ILS frequency on the radio, the KA 57 Course Datum output will be 180 degrees out of phase.
Page 2-8 00111I10.JA
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BENDIX/KING KCS 55/55A
2.9
AVAILABILITY OF 400 HZ POWER FROM THE KG 102/KG 102A
This section contains information pertaining to 400 Hz. power requirements and the use of the KG
102/102A as a source. Refer to
figure 2-28 for additional information.
If a KI 229, KGR 356, GC 381, or KNI 582 is installed with a KCS 55A Compass System, 26 V,
400 Hz. power is needed to excite the heading bootstrap in the KI 525/525A and the compass H and C inputs of the KI 229, KGR 356, GC 381, or KNI 582. In some cases, the KG 102/102A can supply the necessary 400 Hz. power and eliminate the requirement for a external inverter. If the following conditions are met, the KG 102/102A can supply adequate 26 V, 400 Hz. power
1. Except as noted below and in figure 2-28 , the excitation of the KI 525/525A heading
bootstrap rotor H and C will be the only load on the KG 102/102A 26 VAC output
(P1021, pins p and t).
2.
The compass heading X, Y, and Z inputs of the KI 229, KGR 356, GC 381, or KNI
582 will be the only load on the heading bootstrap output.
3.
4.
No additional loads, such as the course datum synchro in a NAV 2 indicator (for
NAV1/NAV2 autopilot transfer), will be connected to the KG 102/102A 26 VAC output (P1021, pins p and t).
Some Honeywell Flight Control Systems incorporate a KRG 331 Rate Gyro. These units are typically shown powered off of the KG 102A. The KG 102A will not simultaneously supply a KRG 331 and a KI 229 or KNI 582.
In addition, radar graphics requiring 400 Hz. power, such as the GC 381A or KRG 356, may be installed utilizing the output of the KG 102/102A. Since these units only require .01 MVA of power, they may be installed in addition to a KI 229 or KNI 582 without requiring an external inverter. Also, the KG 102A will supply enough power for a KRG 331 and KRG 356 or GC 381A.
NOTE:
The KG 102/102A has a 5 VA maximum of 26 V, 400
Hz power available for all uses. If more than 5 VA is required, an external 400 Hz. inverter will be necessary.
CAUTION:
If the 5 VA maximum is exceeded, severe damage will result to the power supply causing catastrophic failure of the compass system.
CAUTION:
Two (2) 400 Hz. outputs cannot be paralleled. An inverter, when required, must be large enough to handle the total AC load.
Rev 10, Feb/2002 00111I10.JA
Page 2-9
BENDIX/KING KCS 55/55A
Page 2-10
FIGURE 2-1 PIN LOCATIONS
(Viewed From REAR of Mating Connectors Except Where Noted)
00111I10.JA
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BENDIX/KING KCS 55/55A
Rev 10, Feb/2002
FIGURE 2-2 KI 525/525A INSTALLATION DRAWING
(Dwg. No. 155-05117-0000, R-AA)
00111I10.JA
Page 2-11
BENDIX/KING KCS 55/55A
Rev 10, Feb/2002
FIGURE 2-3 KG 102/102A INSTALLATION DRAWING
(Dwg. No. 155-05118-0000, R-AA)
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BENDIX/KING KCS 55/55A
Rev 10, Feb/2002
FIGURE 2-4 KMT 112 INSTALLATION DRAWING
(Dwg. No. 155-05130-0000, R-1)
00111I10.JA
Page 2-15
BENDIX/KING KCS 55/55A
Rev 10, Feb/2002
FIGURE 2-5 KA 51 INSTALLATION DRAWING
(Dwg. No. 155-05144-0000, R-1)
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Page 2-17
BENDIX/KING KCS 55/55A
Rev 10, Feb/2002
FIGURE 2-6 KA 51A INSTALLATION DRAWING
(Dwg. No. 155-05144-0001, R-3)
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BENDIX/KING KCS 55/55A
Rev 10, Feb/2002
FIGURE 2-7 KA 51B INSTALLATION DRAWING
(Dwg. No. 155-05371-0000, R-4)
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Page 2-21
BENDIX/KING KCS 55/55A
Rev 10, Feb/2002
FIGURE 2-8 KA 52 INSTALLATION DRAWING
(Dwg. No. 155-05143-0000, R-2)
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BENDIX/KING KCS 55/55A
Page 2-24
FIGURE 2-9 KA 57 INSTALLATION DRAWING
(Dwg. No. 155-05165-0000, R-1)
00111I10.JA
Rev 10, Feb/2002
BENDIX/KING KCS 55/55A
FIGURE 2-10 KCS 55 SILVER CROWN COMPASS SYSTEM INTERCONNECT DIAGRAM
(Dwg. No. 155-01147-0000, R-8)
Rev 10, Feb/2002
00111I10.JA
Page 2-25
BENDIX/KING KCS 55/55A
FIGURE 2-11 KCS 55A SILVER CROWN COMPASS SYSTEM (30Hz OBS RESOLVER) INTERCONNECT DIAGRAM
(Dwg. No. 155-01147-0001, R-AB)
Rev 10, Feb/2002
00111I10.JA
Page 2-27
BENDIX/KING KCS 55/55A
FIGURE 2-12 KCS 55A SILVER CROWN COMPASS SYSTEM (400HZ OBS RESOLVER) INTERCONNECT DIAGRAM
(Dwg. No. 155-01147-0002, R-AB)
Rev 10, Feb/2002
00111I10.JA
Page 2-29
BENDIX/KING KCS 55/55A
FIGURE 2-13 KX 175/KN 73/KN 77/KI 525/525A INTERCONNECT DIAGRAM
(Dwg. No. 155-01148-0000, R-3)
Rev 10, Feb/2002 00111I10.JA
Page 2-31
BENDIX/KING
THIS PAGE IS RESERVED
KCS 55/55A
Page 2-32 00111I10.JA
Rev 10, Feb/2002
BENDIX/KING KCS 55/55A
FIGURE 2-14 COMPLETE SILVER CROWN SYSTEM INTERCONNECT DIAGRAM
(Dwg. No. 155-01149-0000, R-0, Sheet 1 of 2)
Rev 10, Feb/2002
00111I10.JA
Page 2-33
BENDIX/KING KCS 55/55A
FIGURE 2-14 COMPLETE SILVER CROWN SYSTEM INTERCONNECT DIAGRAM
(Dwg. No. 155-01149-0000, R-0, Sheet 2 of 2)
Rev 10, Feb/2002
00111I10.JA
Page 2-35
BENDIX/KING KCS 55/55A
FIGURE 2-15 KN 72/KN 75/KI 525A INTERCONNECT DIAGRAM
(Dwg. No. 155-01340-0000, R-1)
Rev 10, Feb/2002
00111I10.JA
Page 2-37
BENDIX/KING KCS 55/55A
FIGURE 2-16 KNS 80 - KI 525A INTERCONNECT DIAGRAM
(Dwg. No. 155-01316-0000, R-7)
Rev 10, Feb/2002
00111I10.JA
Page 2-39
BENDIX/KING
WARNING
IT HAS BEEN DETERMINED THAT THE KCS 55/
KCS 55A PICTORIAL NAVIGATION SYSTEM AND
ITS ASSOCIATED KA 52 AND/OR KA 57 AUTOPI-
LOT ADAPTORS ARE NOT FULLY COMPATIBLE
WITH THE PIPER ALTIMATIC II AUTOPILOT.
HONEYWELL SUGGESTS THAT NO ATTEMPT
BE MADE TO INTERFACE THE KCS 55/55A SYS-
TEM WITH THE ALTIMATIC II OR ANY OTHER "RF
SENSING DESIGN" AUTOPILOT SYSTEM.
KCS 55/55A
Rev 10, Feb/2002 00111I10.JA
Page 2-41
BENDIX/KING KCS 55/55A
FIGURE 2-17 KCS 55/55A/BENDIX FCS-810 AUTOPILOT INTERFACE INTERCONNECT
Page 2-42 00111I10.JA
Rev 10, Feb/2002
BENDIX/KING KCS 55/55A
FIGURE 2-18 KCS 55/55A/CESSNA 300 NAVOMATIC INTERFACE INTERCONNECT
(Dwg. No. 155-01190-0000, R-2)
Rev 10, Feb/2002 00111I10.JA
Page 2-43
BENDIX/KING KCS 55/55A
NOTES:
1.
KA 57 MUST BE ABOVE SERIAL NUMBER 2050 AND MUST BE ALIGNED PER THE INSTALLATION MANUAL.
2.
THE OMNI ON OR NAV ENABLE LINE TO THE KA 57 MUST BE CONNECTED SO THAT WHEN NAV IS SELECTED PIN C
OF THE KA 57 IS GROUNDED. WHEN THE AUTOPILOT IS IN THE HEADING MODE, PIN C OF THE KA 57 IS OPEN. A
PANEL MOUNTED SWITCH NEAR THE AUTOPILOT MODE CONTROLLER IS RECOMMENDED.
3.
THE TRACER OSCILLATOR, I105 IN THE KA 57, MUST BE DISABLED BY REMOVING CJ101. IN EARLIER KA 57’S WITH-
OUT CJ101, REMOVE C110.
4.
THE KA 57 (KCS 55A SYSTEM) WILL INTERFACE WITH CA 395A COMPUTER AMPLIFIERS THAT ACCEPT ONLY AC IN-
PUTS [P/N 42660-1 (X) (X) (X)]. THE KA 57 WILL NOT INTERFACE WITH P/N 42660-2 (X) (X) (X) COMPUTER AMPLIFIERS.
5.
BECAUSE OF THE REQUIREMENTS OF THE CESSNA AUTOPILOT AND THE NORMAL OPERATING CHARACTERISTICS
OF THE KA 57 AUTOPILOT ADAPTER, THE KA 57 MUST BE MODIFIED SO THAT IT WILL WORK SATISFACTORILY WITH
THIS AUTOPILOT. THE MODIFICATION REQUIRED IS CONTAINED IN SERVICE BULLETIN KA 57-3 (P/N 600-01200-00XX).
THIS MODIFICATION REMOVES T102, THE REFERENCE AC INPUT TRANSFORMER, AND REPLACES IT WITH A CIRCUIT
JUMPER SO THAT THE AUTOPILOT REFERENCE AC WILL BE APPLIED DIRECTLY TO THE KA 57 SWITCHING CIRCUITS.
THIS WILL MINIMIZE THE LOAD REPRESENTED BY THE KA 57 AND ENSURE ITS PROPER OPERATION WITH A RELA-
TIVELY LOW REFERENCE EXCITATION VOLTAGE.
IN ORDER TO ENSURE THAT THE MODIFIED KA 57 IS PROPERLY INSTALLED TO PROVIDE THE PROPER HEADING SE-
LECT/NAV COURSE DATUM SWITCHING OPERATION WITH THE EXTERNAL SWITCH, THE INTERCONNECT MUST BE
WIRED IN ACCORDANCE TO THIS NOTE.
Page 2-44
FIGURE 2-19 KCS 55A/KA 57 CESSNA 300A/CA395A INTERCONNECT
00111I10.JA
Rev 10, Feb/2002
BENDIX/KING KCS 55/55A
FIGURE 2-20 KCS 55/55A CESSNA NAVOMATIC 400 INTERFACE INTERCONNECT
(Dwg. No. 155-01182-0000, R-3)
NOTE: THIS INTERCONNECT IS FOR 400A AUTOPILOT WITH FLIGHT DIRECTOR.
Rev 10, Feb/2002 00111I10.JA
Page 2-45
BENDIX/KING KCS 55/55A
FIGURE 2-21 KCS 55/55A CESSNA NAVOMATIC 400A AUTOPILOT INTERFACE INTER-
CONNECT
(Dwg. Nos. 155-01180-0000, R-2; 155-01193-0000, R-1)
Page 2-46 00111I10.JA
Rev 10, Feb/2002
BENDIX/KING KCS 55/55A
FIGURE 2-22 KCS 55/55A/CESSNA 400B AUTOPILOT INTERFACE INTERCONNECT
(Dwg. No. 155-01254-0000, R-3)
Rev 10, Feb/2002 00111I10.JA
Page 2-47
BENDIX/KING KCS 55/55A
Page 2-48
FIGURE 2-23 KCS 55/55A MITCHELL COUPLER
IC-388, 388C, 388M, 388MC INTERFACE INTERCONNECT
(Dwg. No. 155-01181-0000, R-6)
00111I10.JA
Rev 10, Feb/2002
BENDIX/KING KCS 55/55A
Rev 10, Feb/2002
FIGURE 2-24 KCS 55/55A MITCHELL III AUTOPILOT w/IC 388-3 COUPLER INTERFACE INTERCONNECT
(Dwg. No. 155-01192-0000, R-0)
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Page 2-49
BENDIX/KING KCS 55/55A
FIGURE 2-25 KCS 55/55A MITCHELL CENTURY IV AUTOPILOT INTERFACE
INTERCONNECT
(Dwg. No. 155-01191-0000, R-1)
Page 2-50 00111I10.JA
Rev 10, Feb/2002
BENDIX/KING KCS 55/55A
FIGURE 2-26 KCS 55/55A - AP106/AP107/913K-1 COMPUTER AMPLIFIER
AUTOPILOT INTERFACE INTERCONNECT
(Dwg. No. 155-01255-0000, R-0)
Rev 10, Feb/2002 00111I10.JA
Page 2-51
BENDIX/KING
THIS PAGE IS RESERVED
KCS 55/55A
Page 2-52 00111I10.JA
Rev 10, Feb/2002
BENDIX/KING KCS 55/55A
FIGURE 2-27 KLN 90B - KI 525A INTERCONNECT DIAGRAM
(Dwg. No. 155-06021-0000, R-AB, Sheet 1 of 2)
Rev 10, Feb/2002
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Page 2-53
BENDIX/KING KCS 55/55A
FIGURE 2-27 KLN 90B - KI 525A INTERCONNECT DIAGRAM
(Dwg. No. 155-06021-0000, R-AB, Sheet 2 of 2)
Rev 10, Feb/2002
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Page 2-55
BENDIX/KING KCS 55/55A
Notes:
1.
Using the KG 102/102A as a 26V, 400 Hz. supply, the compass X, Y, and Z input of the KI
229 or KNI 582 must be the only load on the compass bootstrap output.
2.
3.
The KG 102/102A has only 5 VA of available 26V, 400 Hz. power at pin p and t and should not be overloaded.
The 2.7K resistor provides a pull up for the compass valid to the KNI 582. Pin D pulls the compass valid low in an invalid condition.
FIGURE 2-28
KG 102/102A 400 Hz. Supply Interconnection Diagrams
Rev 10, Feb/2002 00111I10.JA
Page 2-57
BENDIX/KING
THIS PAGE IS RESERVED
KCS 55/55A
Page 2-58 00111I10.JA
Rev 10, Feb/2002
BENDIX/KING KCS 55/55A
SECTION III
OPERATION
3.1
DISPLAY DESCRIPTION
This section contains information pertaining to controls and indicators, operating procedures, and
emergency operation of the KCS 55/55A Pictorial Navigation System. Refer to Figures 3-1
and 3-3 for additional information.
3.1.1
KI 525/525A INDICATOR AND CONTROLS
INDICATOR AND CONTROLS
Compass Card:
Heading Select Knob:
Symbolic Aircraft:
Reciprocal Course Pointer:
Course Select Knob:
Lateral Deviation Bar:
Glideslope Pointer:
Heading Select:
NAV Warning Flag:
Lubber Line:
Heading Warning Flag: (KI 525A only)
Power Flag (KI 525 only)
Selected Course Pointer:
To-From Indicator:
Slaving Meter:
Counterclockwise Manual
Heading Drive Pushbutton:
FUNCTION
This rotating card displays gyro stabilized magnetic compass in formation beneath the lubber line.
Positions the heading select marker relative to the compass card.
Represents the relationship of the aircraft with respect to the display.
Indicates the reciprocal of the selected course.
Positions the selected course pointer with respect to the compass card.
Represents VOR radial or LOC course. When referenced to the symbolic aircraft the position of the deviation bar is the same as the position of the chosen
VOR radial or LOC Course to the air craft.
Represents the actual aircraft deviation from the glideslope path. When unusable glideslope information is present the glideslope pointer is biased out of view. When a valid glideslope signal is received there is a 2 to 12 second delay before the pointers come into view.
Indicates the selected aircraft heading.
When unusable VOR/LOC information is present the warning flag is in view.
Aircraft magnetic heading is read under this line.
Inadequate Power, manual slave, fast auto slave or spin motor less than 50% normal speed.
Inadequate Power.
Indicates the selected VOR radial or LOC course.
Indicates the direction to the VOR station along the selected radial.
Indicates the difference between the displayed heading. Positive deflection indicates a clockwise error of the compass card.
When the system is in the free gyro mode, engagement of this pushbutton will cause the compass card rotate counterclockwise at a constant rate of 360 degrees per minute.
Rev 10, Feb/2002 00111I10.JA
Page 3-1
BENDIX/KING KCS 55/55A
INDICATOR AND CONTROLS
Slave/Free Gyro Pushbutton:
Clockwise Manual
Heading Drive Pushbutton:
FUNCTION
When depressed the system is in the slaved gyro mode. When the button is in the outer position the system is in the free gyro mode.
When the system is in the free gyro mode, engagement of this pushbutton will cause the compass card to rotate clockwise at a constant rate of 360 degrees per minute.
3.2
OPERATING PROCEDURES
When power is applied to the KCS 55 System the PWR flag will disappear from view if the power is normal. If the system is in the slaved gyro mode the compass card will automatically fast slave at the rate of 180 degrees per minute towards the magnetic heading. The system will remain in this fast slave mode for 120 seconds after which it will automatically revert to the normal slaving mode and slave at a constant rate of 3 degrees per minute to keep the system aligned with the earth’s magnetic field. The slaving meter on the KA 51 indicates relative deviation from this alignment.
When power is applied to the KCS 55A System the HDG flag will remain in view until the following conditions are satisfied: The gyro spin motor is at least 50% of normal speed, the fast slave mode has been executed and normal system power is present. The fast slaving mode is initiated when power is applied and is switched to the slow slave mode when the slaving error is reduced to zero.
The fast slave rate is 180 degree/minute. The slow slave rate is 3 degree/minute to keep the system aligned with the earth’s magnetic field. The slaving meter on the KA 51A/51B indicates relative deviation from this alignment.
Set the navigation receiver to the desired VOR/LOC station and rotate the course select knob to adjust the selected course pointer to the desired course radial. When a usable navigation signal is received by the KI 525A the NAV warning flag will disappear from view.
The KI 525A lateral deviation bar represents the selected VOR/LOC course. The relationship of the deviation bar to the symbolic aircraft presents the relationship of the selected course to the aircraft.
For an ILS approach, tune the navigation receiver to the desired frequency. For LOC operation the selected course pointer should be set to the inbound localizer course. The glideslope pointer will deflect into view after a 2 to 12 second delay if a usable glideslope signal is received. The glideslope pointer indicates the relative position of the glideslope path with respect to the aircraft.
For LOC operation and ILS front course approach, tune the navigation receiver to the desired frequency, set the pointer to the selected inbound localizer course, and if a usable glideslope signal is received the glideslope pointer will deflect into view. The glideslope pointer indicates the position of the glideslope path with respect to the aircraft. The position of the deviation bar with respect to the symbolic aircraft indicates the relative position of the selected course. For backcourse operation set the course pointer to the inbound localizer course. The deviation bar position relative to the symbolic aircraft then represents the position of the backcourse with respect to the aircraft.
Page 3-2 00111I10.JA
Rev 10, Feb/2002
BENDIX/KING KCS 55/55A
3.3
EMERGENCY OPERATION
If the KI 525 input power warning flag appears, the compass system has experienced a power failure and the card indications are in error. Remove power from the KG 102; the lateral deviation bar and the To-From indicator will remain in operation.
If the KI 525A HDG flag appears in view after the system has been operating or will not go out of view after initial power up, one of the following conditions exists and the compass information will not be reliable:
1)
2)
The gyro on the KG 102A is not running above 50% of its normal speed.
The system has not rotated to the magnetic heading and switched out of fast slave on initial power up.
The power supply in the KG 102A is not functioning properly.
3)
4) KG 102A (060-0015-02). Tumble detection circuit has detected gyro tumble conditions - reverting the system back into fast slave mode to correct the error. Once the system has re-acquired proper display information by matching earth’s magnetic field, the system will revert back to slow slave mode, i.e. normal operation.
A continuous large deflection of the slaving meter or large discrepancies between the magnetic compass and the KI 525/525A compass card may indicate a failure in the slaving system and may not necessarily be annunciated by the HDG flag. If a slaving failure should occur the SLAVE IN button on the KA 51/51A/51B should be returned to its outer position. The system will now be in the free gyro mode. By depressing the clockwise or counterclockwise button (toggle switch on the
KA 51B) on the KA 51/51A the compass dial can be repositioned to the correct heading. The KCS
55/55A will continue to function normally except the heading information will be solely derived from the KG 102/102A Gyro, there will be no magnetic correction from the KMT 112.
If the KI 525/525A NAV flag appears the navigation equipment is off, improperly tuned, or malfunctioning. If possible switch to another navigation receiver. The compass card on the KI 525/525A will continue to display the aircraft heading.
If the KI 525/525A glideslope pointer remains out of view during ILS operation the glideslope transmitter or the aircraft glideslope receiver is malfunctioning. If possible switch to another glideslope receiver. The localizer and heading displays will continue to function normally.
Rev 10, Feb/2002 00111I10.JA
Page 3-3
BENDIX/KING KCS 55/55A
Page 3-4
FIGURE 3-1
KI 525/525A INDICATOR AND CONTROLS
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Rev 10, Feb/2002
BENDIX/KING KCS 55/55A
Rev 10, Feb/2002
FIGURE 3-2
KA 51/51A SLAVING ACCESSORY AND CONTROLS
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BENDIX/KING KCS 55/55A
Page 3-6
FIGURE 3-3
KA 51B SLAVING ACCESSORY AND CONTROLS
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Rev 10, Feb/2002
Advertisement
Key features
- Pictorial navigation display
- Manual controls for course and heading
- Autopilot or flight director outputs
- VOR receiver compatibility
- Additional compass loads
