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BENDIX/KING

KCS 55/55A

Page 1-4

©Honeywell International Inc. Do not print without express permission of Honeywell

Rev 11, Apr/2007

1.3.3

KG 102/102A

1.3.4

KMT 112

SPECIFICATION

CHARACTERISTIC

SIGNAL OUTPUTS:

Heading synchro transmitter:
Output equal to 206 millivolts per degree of heading rota-
tion. (066-3029-01 and 066-3046-01/03/05/07/08/10/11/
12 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 displace-
ment 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.

SIZE:

See Fig. 2-3

WEIGHT:

See Fig. 2-3

MOUNTING:

Shock mounted (provided in installation kit)

MATING CONNECTOR:

See Paragraph 1.5 Installation Kits

POWER INPUTS:

14VDC, 3.0 amperes or 28VDC, 1.5 amperes

SIGNAL INPUTS:

Slaving error control transformer from the KI525/525A.

POWER OUTPUTS:

±

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.

A 5 VA maximum of 26 VAC, 400 Hz power is available
for all uses.

SIGNAL OUTPUTS:

A drive signal for the heading loop drive motor in the KI
525/525A.

Slaving meter drive signal for the
KA 51/51A/51B.

(KG 102A Only)

Pin a supplies a ground when compass system is valid.

RELEASED FOR THE EXCLUSIVE USE BY: AIRCRAFT ELECTRONICS ASSOCIATION

UP536434

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Содержание BENDIX/KING KCS55

Страница 1: ...INSTALLATION MANUAL KCS 55 55A PICTORIAL NAVIGATION SYSTEM MANUAL NUMBER 006 00111 0011 REVISION 11 April 2007 RELEASED FOR THE EXCLUSIVE USE BY AIRCRAFT ELECTRONICS ASSOCIATION UP536434 ...

Страница 2: ...ion 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 RELEASED FOR THE EXCLUSIVE USE BY AIRCRAFT ELECTRONICS ASSOCIATION UP536434 ...

Страница 3: ...n agreement related to the operation maintenance or repair of Honeywell aerospace products Honeywell hereby grants you a limited non exclusive license to use these Materials to maintain or repair the subject Honeywell aerospace products only at the facility to which these Materials have been shipped the Licensed Facility Transfer of the Materials to another facility owned by you is permitted only ...

Страница 4: ...es and damages resulting from a breach of this License Agreement 8 Limitation of Liability IN NO EVENT WILL HONEYWELL BE LIABLE FOR ANY INCIDENTAL DAMAGES CONSEQUENTIAL DAMAGES SPECIAL DAMAGES INDIRECT DAMAGES LOSS OF PROFITS LOSS OF REVENUES OR LOSS OF USE EVEN IF INFORMED OF THE POSSIBILITY OF SUCH DAMAGES TO THE EXTENT PERMITTED BY APPLICABLE LAW THESE LIMITATIONS AND EXCLUSIONS WILL APPLY REGA...

Страница 5: ...s permission of Honeywell Page RH 1 KCS 55 55A Part Number Rev Date Description 006 00111 0008 08 Jun 2001 006 00111 0009 09 Jan 2002 006 00111 0010 10 Feb 2002 006 00111 0011 11 Apr 2007 Updated to remove NVG versions of the unit RELEASED FOR THE EXCLUSIVE USE BY AIRCRAFT ELECTRONICS ASSOCIATION UP536434 ...

Страница 6: ...IGHLIGHTS Rev 11 Apr 2007 Honeywell International Inc Do not print without express permission of Honeywell Page RH 2 Part Number Rev Date Description RELEASED FOR THE EXCLUSIVE USE BY AIRCRAFT ELECTRONICS ASSOCIATION UP536434 ...

Страница 7: ...SUPPLIED 1 7 1 4 1 KI 525 525A PICTORIAL NAVIGATION INDICATOR 1 7 1 4 2 KG 102 102A DIRECTIONAL GYRO 1 8 1 4 3 KMT 112 MAGNETIC AZIMUTH TRANSMITTER 1 9 1 4 4 KA 51 51A 51B SLAVING ACCESSORY 1 9 1 4 5 KA 52 AUTOPILOT ADAPTER 1 10 1 4 6 KA 57 AUTOPILOT ADAPTER 1 10 1 5 INSTALLATION KITS 1 11 1 6 COMPENSATOR KIT OPTIONAL 1 13 1 7 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS 1 13 SECTION II INSTALLATION P...

Страница 8: ... 2 7 1 KA 52 ADAPTER 2 4 2 7 2 MOUNTING 2 4 2 7 3 KA 57 ADAPTER 2 4 2 7 4 MOUNTING 2 4 2 8 ADJUSTMENTS 2 4 2 8 1 KI 525 525A 2 4 2 8 2 KG 102 102A 2 4 2 8 3 KMT 112 2 4 2 8 4 KA 51 51A 2 4 2 8 5 KA 51B 2 5 2 8 6 ALTERNATE METHOD OF COMPENSATION ADJUSTMENTS FOR KMT 112 AND KA 51 KA 51A 2 6 2 8 7 KA 52 and KA 57 2 7 2 9 AVAILABILITY OF 400 HZ POWER FROM THE KG 102 102A 2 9 SECTION III OPERATION PARA...

Страница 9: ...ONNECT DIAGRAM 2 37 2 16 KNS 80 KI 525A INTERCONNECT DIAGRAM 2 39 2 17 KCS 55 55A BENDIX FCS 810 AUTOPILOT INTERFACE INTERCONNECT 2 42 2 18 KCS 55 55A CESSNA 300 NAVOMATIC INTERFACE INTERCONNECT 2 43 2 19 KCS 55A KA 57 CESSNA 300A CA395A INTERCONNECT 2 44 2 20 KCS 55 55A CESSNA NAVOMATIC 400 INTERFACE INTERCONNECT 2 45 2 21 KCS 55 55A CESSNA NAVOMATIC 400A AUTOPILOT INTERFACE INTERCONNECT 2 46 2 2...

Страница 10: ...ithout express permission of Honeywell Rev 11 Apr 2007 LIST OF TABLES TABLE PAGE 1 1 KI 525A VERSION CHART 1 8 1 2 KI 525 VERSION CHART 1 8 1 3 KA 51A VERSION CHART 1 9 1 4 KA 51B VERSION CHART 1 10 RELEASED FOR THE EXCLUSIVE USE BY AIRCRAFT ELECTRONICS ASSOCIATION UP536434 ...

Страница 11: ...rse 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 sig nal compatible with certain autopilot systems 1 2 FUNCTIONAL KCS 55 System When po...

Страница 12: ... 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 1 3 2 KI 525 525A SPECIFICATION CHARACTERISTIC TSO COMPLIANCE TSO C6c RTCA DO 138 Environmental Categories KI 525 525A vers...

Страница 13: ...through a resistance of 1000 30 ohms for a full scale de flection of five dots To From pointer 200 40 microamperes through a resis tance 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...

Страница 14: ...D C per degree of displacement from the lubber line SIZE See Fig 2 3 WEIGHT See Fig 2 3 MOUNTING Shock mounted provided in installation kit MATING CONNECTOR See Paragraph 1 5 Installation Kits POWER INPUTS 14VDC 3 0 amperes or 28VDC 1 5 amperes SIGNAL INPUTS Slaving error control transformer from the KI525 525A POWER OUTPUTS 15 and 5VDC reference voltages for the KI525 525A and the KA 51 51A 51B A...

Страница 15: ...25A SPECIFICATION CHARACTERISTIC SIZE See Fig 2 5 and 2 6 WEIGHT See Fig 2 5 and 2 6 MATING CONNECTOR See paragraph 1 5 Installation Kits POWER INPUTS 5VDC from KG 102 102A 7 2 VAC 400Hz from KG 102 102A KA 51A 071 1053 03 14VDC Lamp Supply KA 51A 071 1053 04 28VDC Lamp Supply SIGNAL INPUTS Slaving meter drive signal from the KG 102 102A SIGNAL OUTPUTS Magnetic Azimuth Transmitter compensation out...

Страница 16: ...orrection Clockwise and counterclockwise manual slew signals to the KG 102A KSG 105 Slave free gyro mode logic signal to the KG 102A KSG 105 SPECIFICATION CHARACTERISTIC SIZE See Fig 2 8 WEIGHT See Fig 2 8 MOUNTING Rigid mount with four 6 screws MATING CONNECTOR See paragraph 1 5 Installation Kits POWER INPUTS 15 volts DC from the KG 102 102A SIGNAL INPUTS Heading select DC input from the KI 525 5...

Страница 17: ...or flight direction information Ei ther 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 are capable of operating at either 30Hz or 400Hz Serial number 43434 and above have glideslope damping for helicopters in all versions SIZE x 10 20 centimeters See Fig 2 9 WEIGHT See F...

Страница 18: ...is available in a stan dard 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 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 PN BEZEL OBS LIGHTING HDG XMTR 06...

Страница 19: ...nt 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...

Страница 20: ...mote mounted device that con verts the DC heading and course datum signals from the KI 525 525A Indicator into a single swit chable AC output signal compatible with certain autopilot systems 1 5 INSTALLATION KITS See figure 1 1 for crimping insertion and extraction tools PN BEZEL LIGHTING FACEPLATE 071 1242 00 BLACK 14 V VERTICAL 071 1242 01 BLACK 28 V VERTICAL 071 1242 02 GRAY 28 V VERTICAL 071 1...

Страница 21: ...0 AWG 41 030 02153 0000 Conn 24 Pin 1 1 030 02154 0000 Conn Hood 2 2 2 030 02178 0000 Conn Plug 41 Pin 1 1 030 02272 0000 Conn 41P Shell 1 030 02272 0001 Conn Shell 41 Pin Male 1 047 03937 0001 Plate Nut 1 1 1 057 02105 0016 Decal Cut out 1 1 1 076 00904 0001 Spacer Knob 2 2 089 05115 0012 Scr PFH 6 32 x 3 4 4 4 4 PN Description Qty 030 02190 0000 Conn 5 Pin 1 089 02157 0015 Nut Hex 6 32 3 089 070...

Страница 22: ...6 Screw FHP 8 32X3 8 4 PN Description 00 01 030 02224 0000 Conn 14 Pin 1 1 088 00450 0000 Conn Hood 1 1 089 05899 0007 Scr PHP 2 56 X 7 16 2 2 089 06163 0008 Scr FHP 4 40 X 1 2 4 089 06596 0008 Scr FHP 4 40 X 1 2 4 089 08163 0001 Washer Flat 2 2 2 PN 030 00107 0000 Conn 12 Pin 1 088 00405 0000 Conn Hood 1 089 05111 0008 Scr PHF 4 40 x 1 2 4 089 06414 0007 Scr PHP 2 28 x 7 16 2 PN Description Qty 0...

Страница 23: ...ll 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 perfor mance test should be accomplished following any ...

Страница 24: ...ITIONER 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 RELEASED FOR THE EXCLUSIVE USE BY AIRCRAFT ELECTRONI...

Страница 25: ...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 equip ment has not been damaged in shipment it is suggested that the preinstallation bench test be per formed The bench test harness...

Страница 26: ...TERCONNECTION 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 docu menting all limitations and conditions suitable for installation of the article An applic...

Страница 27: ...actory 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 provide...

Страница 28: ... 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 the...

Страница 29: ...ntiometers 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 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 magnet...

Страница 30: ...t meter with the manual slave buttons on the KA 51 KA 51A at each of these head ings 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 ...

Страница 31: ...t 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 vari ations 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 ...

Страница 32: ...g of the CRS gain by slewing the Course pointer to 45o counterclockwise from the lubber line by 45o the control wheel should stop mov ing when the Course pointer reaches 45o The absolute value of the two inter cepts nominally 45o should be within 5o 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 ...

Страница 33: ...n the heading bootstrap output 3 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 out put P1021 pins p and t 4 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 simul taneously supply a KRG 331 and ...

Страница 34: ...International Inc Do not print without express permission of Honeywell Rev 11 Apr 2007 FIGURE 2 1 PIN LOCATIONS Viewed From REAR of Mating Connectors Except Where Noted RELEASED FOR THE EXCLUSIVE USE BY AIRCRAFT ELECTRONICS ASSOCIATION UP536434 ...

Страница 35: ...IX KING KCS 55 55A Rev 11 Apr 2007 Honeywell International Inc Do not print without express permission of Honeywell Page 2 11 FIGURE 2 2 KI 525 525A INSTALLATION DRAWING Dwg No 155 05117 0000 R AA UP536434 ...

Страница 36: ...BENDIX KING KCS 55 55A Page 2 12 Honeywell International Inc Do not print without express permission of Honeywell Rev 11 Apr 2007 UP536434 ...

Страница 37: ...IX KING KCS 55 55A Rev 11 Apr 2007 Honeywell International Inc Do not print without express permission of Honeywell Page 2 13 FIGURE 2 3 KG 102 102A INSTALLATION DRAWING Dwg No 155 05118 0000 R AA UP536434 ...

Страница 38: ...BENDIX KING KCS 55 55A Page 2 14 Honeywell International Inc Do not print without express permission of Honeywell Rev 11 Apr 2007 UP536434 ...

Страница 39: ...ENDIX KING KCS 55 55A Rev 11 Apr 2007 Honeywell International Inc Do not print without express permission of Honeywell Page 2 15 FIGURE 2 4 KMT 112 INSTALLATION DRAWING Dwg No 155 05130 0000 R 1 UP536434 ...

Страница 40: ...BENDIX KING KCS 55 55A Page 2 16 Honeywell International Inc Do not print without express permission of Honeywell Rev 11 Apr 2007 UP536434 ...

Страница 41: ...BENDIX KING KCS 55 55A Rev 11 Apr 2007 Honeywell International Inc Do not print without express permission of Honeywell Page 2 17 FIGURE 2 5 KA 51 INSTALLATION DRAWING Dwg No 155 05144 0000 R 1 UP536434 ...

Страница 42: ...BENDIX KING KCS 55 55A Page 2 18 Honeywell International Inc Do not print without express permission of Honeywell Rev 11 Apr 2007 UP536434 ...

Страница 43: ...ENDIX KING KCS 55 55A Rev 11 Apr 2007 Honeywell International Inc Do not print without express permission of Honeywell Page 2 19 FIGURE 2 6 KA 51A INSTALLATION DRAWING Dwg No 155 05144 0001 R 3 UP536434 ...

Страница 44: ...BENDIX KING KCS 55 55A Page 2 20 Honeywell International Inc Do not print without express permission of Honeywell Rev 11 Apr 2007 UP536434 ...

Страница 45: ...ENDIX KING KCS 55 55A Rev 11 Apr 2007 Honeywell International Inc Do not print without express permission of Honeywell Page 2 21 FIGURE 2 7 KA 51B INSTALLATION DRAWING Dwg No 155 05371 0000 R 4 UP536434 ...

Страница 46: ...BENDIX KING KCS 55 55A Page 2 22 Honeywell International Inc Do not print without express permission of Honeywell Rev 11 Apr 2007 UP536434 ...

Страница 47: ...2007 Honeywell International Inc Do not print without express permission of Honeywell Page 2 23 FIGURE 2 8 KA 52 INSTALLATION DRAWING Dwg No 155 05143 0000 R 2 RELEASED FOR THE EXCLUSIVE USE BY AIRCRAFT ELECTRONICS ASSOCIATION UP536434 ...

Страница 48: ...oneywell International Inc Do not print without express permission of Honeywell Rev 11 Apr 2007 FIGURE 2 9 KA 57 INSTALLATION DRAWING Dwg No 155 05165 0000 R 1 RELEASED FOR THE EXCLUSIVE USE BY AIRCRAFT ELECTRONICS ASSOCIATION UP536434 ...

Страница 49: ... 55 55A Rev 11 Apr 2007 Honeywell International Inc Do not print without express permission of Honeywell Page 2 25 FIGURE 2 10 KCS 55 SILVER CROWN COMPASS SYSTEM INTERCONNECT DIAGRAM Dwg No 155 01147 0000 R 8 UP536434 ...

Страница 50: ...BENDIX KING KCS 55 55A Page 2 26 Honeywell International Inc Do not print without express permission of Honeywell Rev 11 Apr 2007 UP536434 ...

Страница 51: ...v 11 Apr 2007 Honeywell International Inc Do not print without express permission of Honeywell Page 2 27 FIGURE 2 11 KCS 55A SILVER CROWN COMPASS SYSTEM 30Hz OBS RESOLVER INTERCONNECT DIAGRAM Dwg No 155 01147 0001 R AB UP536434 ...

Страница 52: ...BENDIX KING KCS 55 55A Page 2 28 Honeywell International Inc Do not print without express permission of Honeywell Rev 11 Apr 2007 UP536434 ...

Страница 53: ... 11 Apr 2007 Honeywell International Inc Do not print without express permission of Honeywell Page 2 29 FIGURE 2 12 KCS 55A SILVER CROWN COMPASS SYSTEM 400HZ OBS RESOLVER INTERCONNECT DIAGRAM Dwg No 155 01147 0002 R AB UP536434 ...

Страница 54: ...BENDIX KING KCS 55 55A Page 2 30 Honeywell International Inc Do not print without express permission of Honeywell Rev 11 Apr 2007 UP536434 ...

Страница 55: ...l International Inc Do not print without express permission of Honeywell Page 2 31 FIGURE 2 13 KX 175 KN 73 KN 77 KI 525 525A INTERCONNECT DIAGRAM Dwg No 155 01148 0000 R 3 RELEASED FOR THE EXCLUSIVE USE BY AIRCRAFT ELECTRONICS ASSOCIATION UP536434 ...

Страница 56: ...CS 55 55A Page 2 32 Honeywell International Inc Do not print without express permission of Honeywell Rev 11 Apr 2007 THIS PAGE IS RESERVED RELEASED FOR THE EXCLUSIVE USE BY AIRCRAFT ELECTRONICS ASSOCIATION UP536434 ...

Страница 57: ...55A Rev 11 Apr 2007 Honeywell International Inc Do not print without express permission of Honeywell Page 2 33 FIGURE 2 14 COMPLETE SILVER CROWN SYSTEM INTERCONNECT DIAGRAM Dwg No 155 01149 0000 R 0 Sheet 1 of 2 UP536434 ...

Страница 58: ...BENDIX KING KCS 55 55A Page 2 34 Honeywell International Inc Do not print without express permission of Honeywell Rev 11 Apr 2007 UP536434 ...

Страница 59: ...55A Rev 11 Apr 2007 Honeywell International Inc Do not print without express permission of Honeywell Page 2 35 FIGURE 2 14 COMPLETE SILVER CROWN SYSTEM INTERCONNECT DIAGRAM Dwg No 155 01149 0000 R 0 Sheet 2 of 2 UP536434 ...

Страница 60: ...BENDIX KING KCS 55 55A Page 2 36 Honeywell International Inc Do not print without express permission of Honeywell Rev 11 Apr 2007 UP536434 ...

Страница 61: ...ING KCS 55 55A Rev 11 Apr 2007 Honeywell International Inc Do not print without express permission of Honeywell Page 2 37 FIGURE 2 15 KN 72 KN 75 KI 525A INTERCONNECT DIAGRAM Dwg No 155 01340 0000 R 1 UP536434 ...

Страница 62: ...BENDIX KING KCS 55 55A Page 2 38 Honeywell International Inc Do not print without express permission of Honeywell Rev 11 Apr 2007 UP536434 ...

Страница 63: ...X KING KCS 55 55A Rev 11 Apr 2007 Honeywell International Inc Do not print without express permission of Honeywell Page 2 39 FIGURE 2 16 KNS 80 KI 525A INTERCONNECT DIAGRAM Dwg No 155 01316 0000 R 7 UP536434 ...

Страница 64: ...BENDIX KING KCS 55 55A Page 2 40 Honeywell International Inc Do not print without express permission of Honeywell Rev 11 Apr 2007 UP536434 ...

Страница 65: ...CS 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 RELEASED FOR THE EXCLUSIVE USE BY AIRCRAFT ELECTRONICS ASSOCIATION UP536434 ...

Страница 66: ...ywell International Inc Do not print without express permission of Honeywell Rev 11 Apr 2007 FIGURE 2 17 KCS 55 55A BENDIX FCS 810 AUTOPILOT INTERFACE INTERCONNECT RELEASED FOR THE EXCLUSIVE USE BY AIRCRAFT ELECTRONICS ASSOCIATION UP536434 ...

Страница 67: ... International Inc Do not print without express permission of Honeywell Page 2 43 FIGURE 2 18 KCS 55 55A CESSNA 300 NAVOMATIC INTERFACE INTERCONNECT Dwg No 155 01190 0000 R 2 RELEASED FOR THE EXCLUSIVE USE BY AIRCRAFT ELECTRONICS ASSOCIATION UP536434 ...

Страница 68: ... 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 CIRC...

Страница 69: ...ithout express permission of Honeywell Page 2 45 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 RELEASED FOR THE EXCLUSIVE USE BY AIRCRAFT ELECTRONICS ASSOCIATION UP536434 ...

Страница 70: ...not print without express permission of Honeywell Rev 11 Apr 2007 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 RELEASED FOR THE EXCLUSIVE USE BY AIRCRAFT ELECTRONICS ASSOCIATION UP536434 ...

Страница 71: ...International Inc Do not print without express permission of Honeywell Page 2 47 FIGURE 2 22 KCS 55 55A CESSNA 400B AUTOPILOT INTERFACE INTERCONNECT Dwg No 155 01254 0000 R 3 RELEASED FOR THE EXCLUSIVE USE BY AIRCRAFT ELECTRONICS ASSOCIATION UP536434 ...

Страница 72: ...nc Do not print without express permission of Honeywell Rev 11 Apr 2007 FIGURE 2 23 KCS 55 55A MITCHELL COUPLER IC 388 388C 388M 388MC INTERFACE INTERCONNECT Dwg No 155 01181 0000 R 6 RELEASED FOR THE EXCLUSIVE USE BY AIRCRAFT ELECTRONICS ASSOCIATION UP536434 ...

Страница 73: ...nal Inc Do not print without express permission of Honeywell Page 2 49 FIGURE 2 24 KCS 55 55A MITCHELL III AUTOPILOT w IC 388 3 COUPLER INTERFACE INTERCONNECT Dwg No 155 01192 0000 R 0 RELEASED FOR THE EXCLUSIVE USE BY AIRCRAFT ELECTRONICS ASSOCIATION UP536434 ...

Страница 74: ...nal Inc Do not print without express permission of Honeywell Rev 11 Apr 2007 FIGURE 2 25 KCS 55 55A MITCHELL CENTURY IV AUTOPILOT INTERFACE INTERCONNECT Dwg No 155 01191 0000 R 1 RELEASED FOR THE EXCLUSIVE USE BY AIRCRAFT ELECTRONICS ASSOCIATION UP536434 ...

Страница 75: ... Inc Do not print without express permission of Honeywell Page 2 51 FIGURE 2 26 KCS 55 55A AP106 AP107 913K 1 COMPUTER AMPLIFIER AUTOPILOT INTERFACE INTERCONNECT Dwg No 155 01255 0000 R 0 RELEASED FOR THE EXCLUSIVE USE BY AIRCRAFT ELECTRONICS ASSOCIATION UP536434 ...

Страница 76: ...CS 55 55A Page 2 52 Honeywell International Inc Do not print without express permission of Honeywell Rev 11 Apr 2007 THIS PAGE IS RESERVED RELEASED FOR THE EXCLUSIVE USE BY AIRCRAFT ELECTRONICS ASSOCIATION UP536434 ...

Страница 77: ...CS 55 55A Rev 11 Apr 2007 Honeywell International Inc Do not print without express permission of Honeywell Page 2 53 FIGURE 2 27 KLN 90B KI 525A INTERCONNECT DIAGRAM Dwg No 155 06021 0000 R AB Sheet 1 of 2 UP536434 ...

Страница 78: ...BENDIX KING KCS 55 55A Page 2 54 Honeywell International Inc Do not print without express permission of Honeywell Rev 11 Apr 2007 UP536434 ...

Страница 79: ...CS 55 55A Rev 11 Apr 2007 Honeywell International Inc Do not print without express permission of Honeywell Page 2 55 FIGURE 2 27 KLN 90B KI 525A INTERCONNECT DIAGRAM Dwg No 155 06021 0000 R AB Sheet 2 of 2 UP536434 ...

Страница 80: ...BENDIX KING KCS 55 55A Page 2 56 Honeywell International Inc Do not print without express permission of Honeywell Rev 11 Apr 2007 UP536434 ...

Страница 81: ...82 must be the only load on the compass bootstrap output 2 The KG 102 102A has only 5 VA of available 26V 400 Hz power at pin p and t and should not be overloaded 3 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 RELEASED FOR THE EXCLUSIVE USE BY AIRCRA...

Страница 82: ...CS 55 55A Page 2 58 Honeywell International Inc Do not print without express permission of Honeywell Rev 11 Apr 2007 THIS PAGE IS RESERVED RELEASED FOR THE EXCLUSIVE USE BY AIRCRAFT ELECTRONICS ASSOCIATION UP536434 ...

Страница 83: ...osen VOR radial or LOC Course to the air craft Glideslope Pointer Represents the actual aircraft deviation from the glideslope path When unusable glideslope informa tion 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 Heading Select Indicates the selected aircraft heading NAV Warni...

Страница 84: ...ag 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 g...

Страница 85: ...rmal 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 fre...

Страница 86: ...age 3 4 Honeywell International Inc Do not print without express permission of Honeywell Rev 11 Apr 2007 FIGURE 3 1 KI 525 525A INDICATOR AND CONTROLS RELEASED FOR THE EXCLUSIVE USE BY AIRCRAFT ELECTRONICS ASSOCIATION UP536434 ...

Страница 87: ...11 Apr 2007 Honeywell International Inc Do not print without express permission of Honeywell Page 3 5 FIGURE 3 2 KA 51 51A SLAVING ACCESSORY AND CONTROLS RELEASED FOR THE EXCLUSIVE USE BY AIRCRAFT ELECTRONICS ASSOCIATION UP536434 ...

Страница 88: ...e 3 6 Honeywell International Inc Do not print without express permission of Honeywell Rev 11 Apr 2007 FIGURE 3 3 KA 51B SLAVING ACCESSORY AND CONTROLS RELEASED FOR THE EXCLUSIVE USE BY AIRCRAFT ELECTRONICS ASSOCIATION UP536434 ...

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