Owner's manual

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Pilot’s Guide

Bendix/King

Autopilot System

KAP 140

Summary of content (102 pages)

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KAP 140 Bendix/King® Autopilot System Pilot’s Guide
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WARNING The enclosed technical data is eligible for export under License Designation NLR and is to be used solely by the individual/organization to whom it is addressed. Diversion contrary to U.S. law is prohibited. COPYRIGHT NOTICE Copyright © 1998, 2002, 2005 Honeywell International Inc. All rights reserved. Reproduction of this publication or any portion thereof by any means without the express written permission of Honeywell International Inc. is prohibited.
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Revision History and Instructions Manual KAP 140 Pilot’s Guide Revision 3, November 2005 Part Number 006-18034-0000 This revision changes CW to CCW on page 116.
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Revision History and Instructions Manual KAP 140 Pilot’s Guide Revision 2, May 2002 Part Number 006-18034-0000 This revision makes some of the changes for software version 03/01 more consistent throughout the Pilot’s Guide. The affected pages are 9, 12, 13, 55, 58, 83, 86 and 109.
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Revision History and Instructions Manual KAP 140 Pilot’s Guide Revision 1, April 2002 Part Number 006-18034-0000 This revision incorporates changes for software version 03/01.
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Revision History and Instructions Manual KAP 140 Pilot’s Guide Revision 0, June 1998 Part Number 006-18034-0000 This is the original version of this publication.
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Table of Contents Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 General Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 KAP 140 Single Axis Autopilot System . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 KAP 140 Two Axis Autopilot System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 KAP 140 Two Axis/Altitude Preselect Autopilot System . . . . . . . . . . .
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Table of Contents GPS Capture Using HSI . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .64 Outbound On Front Course For Procedure Turn To ILS Approach Using DG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .66 Outbound On Front Course For Procedure Turn To ILS Approach Using HSI . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .68 Front Course ILS Approach Using DG . . . . .
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Introduction Introduction The KAP 140 Autopilot System is a rate based digital autopilot system offering smooth performance and enhanced features found only in more expensive autopilots. The first of its type developed by Honeywell, this system brings digital technology and reliability into the light aircraft cockpit. It is also significant that the KAP 140 series autopilots have been designed from their inception to interface with the Silver Crown package of products.
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Introduction General Description KAP 140 Single Axis Autopilot System KAP 140 Two Axis/Altitude Preselect Autopilot System The KAP 140 Single Axis system is an entry level digital panel-mount autopilot, offering lateral modes only with an electric trim option. The KAP 140 Two Axis system provides both lateral and vertical modes with altitude preselect. D.C. ELEC. D.C. ELEC. TURN COORDINATOR TURN COORDINATOR L R L R 2 MIN. 2 MIN.
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Introduction HSI DG Turn Coordinator Automatic Electric Elevator Trim Manual Electric Trim FUNCTIONS/MODES ALT Hold (ALT) ALT Preselect/ALERT Heading Select (HDG) NAV (VOR/RNAV/GPS) Approach (APR) Glideslope (GS) Back Course (REV) Control Wheel Steering (CWS) Vertical Speed Hld Auto Capture Auto Track All Angle Intercept Auto 45-degree Intercept TEST Manual and Auto Trim Monitor Acceleration Monitor KAP 140 Two Axis Alt.
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Introduction System Integration The individual system diagrams on pages 5, 6, and 7 show the components and their relationship in typical KAP 140 Single Axis, KAP 140 Two Axis, and KAP 140 Two Axis/Altitude Preselect systems. The actual components on individual systems may vary slightly in order to optimize certification and installation requirements.
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Introduction Middle VOR/LOC/RNAV/ Marker GPS Deviation D.C. ELEC. G TURN COORDINATOR KAP 140 L TRIM FAIL R HDG AP NAV APR REV 2 MIN. NO PITCH INFORMATION KC 140 Single Axis Computer/Controller/ Annunciator contains computer functions, mode control buttons, and annunciations in a single unit.
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Introduction VOR/LOC/RNAV/ Static GPS Deviation Pressure Glideslope Middle Deviation Marker D.C. ELEC. G TURN COORDINATOR KAP 140 TRIM FAIL DN L HDG AP R NAV APR REV ALT UP 2 MIN. NO PITCH INFORMATION Turn Coordinator KC 140 Two Axis Computer/ Controller/ Annunciator contains computer functions, mode control buttons, and annunciations in a single unit. Also contains static pressure sensor and accelerometer.
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Introduction VOR/LOC/ RNAV/ Encoding GPS Altimeter Deviation Baro Setting Glideslope Deviation Middle Marker KC 140 Two Axis with Altitude Preselect Computer/Controller/ Annunciator contains computer functions, mode control buttons, and annunciations in a single unit. Also contains static pressure sensor and accelerometer. Static Pressure D.C. ELEC. G TURN COORDINATOR ARM KFC 140 BARO UP L R HDG AP NAV APR REV ALT TRIM FAIL DN 2 MIN.
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Introduction Power Application and Preflight Tests G KAP 140 AP HDG NAV APR REV KAP 140 Preflight Test G KAP 140 AP HDG NAV APR REV KAP 140 Preflight Test Complete A preflight test is performed upon power application to the computer. This test is a sequence of internal checks that validate proper system operation prior to allowing autopilot engagement. The preflight test (PFT) sequence is indicated by “PFT” with an increasing number for the sequence steps.
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Single Axis Operation KAP 140 Single Axis Operation The KAP 140 is a high-performance digital, panel-mounted autopilot system for light aircraft. 8 7 G KAP 140 P R HDG AP NAV APR REV Single-axis Flight Control Computer G KAP 140 P R HDG AP 1 2 3 NAV APR 4 REV 5 6 Full Single-axis KAP 140 Display 1. AUTOPILOT ENGAGE/DISENGAGE (AP) BUTTON - When pushed, engages autopilot if all logic conditions are met.
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Single Axis Operation 5. APPROACH (APR) MODE SELECTOR BUTTON - When pushed, will arm the Approach mode. This mode provides automatic beam capture and tracking of VOR, GPS and LOC, as selected for presentation on the HSI or CDI. APR mode is recommended for instrument approaches. 6. BACK COURSE APPROACH (REV) MODE SELECTOR BUTTON - When pushed, will arm the Back Course approach mode. This mode functions similarly to the approach mode except that the autopilot response to LOC signals is reversed. 7.
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Single Axis Operation This page intentionally left blank Rev.
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Single Axis Operation System Operating Modes G KAP 140 HDG AP NAV APR REV Wing Leveler (ROL) Mode In the roll mode, the autopilot maintains wings level flight. D.C. ELEC. TURN COORDINATOR L R 2 MIN. NO PITCH INFORMATION 12 1. Engage autopilot - Press AP. For software version 03/01 and later, the AP button must be pressed and held for 0.25 seconds to engage the autopilot. NOTE: The KAP 140 engages into ROL mode as a default. KAP 140 AUTOPILOT SYSTEM Rev.
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Single Axis Operation G KAP 140 HDG AP NAV APR REV Heading Select (HDG) Mode In the heading mode, the autopilot will fly a selected heading. The following steps should be taken to operate in the heading mode: D.C. ELEC. TURN COORDINATOR L 1. Move the heading “bug” to the desired heading on the DG or HSI using the Heading Select knob. R 2 MIN. NO PITCH INFORMATION 33 N 2. Engage autopilot - Press AP. For software version 03/01 and later, the AP button must be pressed and held for 0.
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Single Axis Operation G KAP 140 HDG AP NAV APR REV Navigation (NAV) Mode Using a DG from HDG Mode (45° Intercept) D.C. ELEC. In the navigation (NAV) mode, the autopilot intercepts and tracks VOR/RNAV and GPS courses. TURN COORDINATOR L To arm NAV mode (with the KAP 140 currently in the HDG mode): R 2 MIN. NO PITCH INFORMATION 1. Select the desired frequency for VOR or RNAV. For GPS, verify the desired waypoint or destination. 6 E 2. OBS Knob - SELECT desired course. 3.
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Single Axis Operation 4. Heading Selector Knob ROTATE BUG to agree with OBS course. Note Instruments: CDI needle to left. Intercept heading 45° to the left of selected (heading bug) course. 5. If the Course Deviation Bar is greater than 2 to 3 dots: the autopilot will annunciate NAV ARM; when the computed capture point is reached the ARM annunciator will go out and the selected course will be automatically captured and tracked.
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Single Axis Operation G KAP 140 HDG AP NAV APR REV Navigation (NAV) Mode Using a DG from ROL Mode (All Angle Intercept) D.C. ELEC. In the navigation (NAV) mode, the autopilot intercepts and tracks VOR/RNAV and GPS courses. TURN COORDINATOR L To arm NAV mode (with the KAP 140 currently in the ROL mode): R 2 MIN. NO PITCH INFORMATION 1. Maneuver the aircraft to the desired intercept angle prior to selecting ROL mode. 6 2. Select the desired frequency for VOR or RNAV.
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Single Axis Operation 5. Heading Selector Knob ROTATE BUG to agree with OBS course. Note Instruments: CDI needle to left. Intercept heading 30° to the left of selected (heading bug) course. 6. If the Course Deviation Bar is greater than 2 to 3 dots: the autopilot will annunciate NAV ARM; when the computed capture point is reached the ARM annunciator will go out and the selected course will be automatically captured and tracked.
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Single Axis Operation G KAP 140 HDG AP NAV In the navigation (NAV) mode, the autopilot intercepts and tracks VOR/RNAV and GPS courses. TURN COORDINATOR L R 2 MIN. NO PITCH INFORMATION 6 N 30 S 33 15 21 24 W 18 GS 12 ı To arm NAV mode (with the KAP 140 currently in the HDG mode): 1. Select the desired frequency for VOR or RNAV. For GPS, verify the desired waypoint or destination. E 3 REV Navigation (NAV) Mode Using an HSI D.C. ELEC. GS APR 2.
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Single Axis Operation 5. If the Course Deviation Bar is greater than 2 to 3 dots: the aircraft will continue in HDG mode (or ROL if HDG is not selected) with NAV ARM annunciated; when the computed capture point is reached HDG will disengage, the ARM annunciator will go out and the selected course will be automatically captured and tracked.
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Single Axis Operation G KAP 140 HDG AP NAV APR Approach (APR) Mode Using a DG from HDG Mode (45° Intercept) D.C. ELEC. The Approach (APR) mode allows the autopilot to intercept and track LOC, VOR/RNAV and GPS courses. TURN COORDINATOR L R To arm APR mode (with the KAP 140 currently in the HDG mode): 2 MIN. NO PITCH INFORMATION 1. Select the desired frequency for LOC, VOR or RNAV. For GPS, verify the desired approach. 6 E 2. OBS Knob - SELECT desired approach course.
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Single Axis Operation 4. Heading Selector Knob ROTATE BUG to agree with desired approach course. Note Instruments: CDI needle to left. Intercept heading 45° to the left of selected (heading bug) course. 5. If the Course Deviation Bar is greater than 2 to 3 dots: the autopilot will annunciate APR ARM; when the computed capture point is reached the ARM annunciator will go out and the selected course will be automatically captured and tracked.
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Single Axis Operation G KAP 140 HDG AP NAV APR Approach (APR) Mode Using a DG from ROL Mode (All Angle Intercept) D.C. ELEC. The Approach (APR) mode allows the autopilot to intercept and track LOC, VOR/RNAV and GPS courses. TURN COORDINATOR L R To arm APR mode (with the KAP 140 currently in the ROL mode): 2 MIN. NO PITCH INFORMATION 6 1. Maneuver the aircraft to the desired intercept angle prior to selecting ROL mode. E 2. Select the desired frequency for LOC, VOR or RNAV.
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Single Axis Operation 5. Heading Selector Knob ROTATE BUG to agree with desired approach course. Note Instruments: CDI needle to left. Intercept heading 30° to the left of selected (heading bug) course. 6. If the Course Deviation Bar is greater than 2 to 3 dots: the autopilot will annunciate APR ARM; when the computed capture point is reached the ARM annunciator will go out and the selected course will be automatically captured and tracked.
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Single Axis Operation G KAP 140 HDG AP NAV APR REV Approach (APR) Mode Using an HSI D.C. ELEC. The Approach (APR) mode allows the autopilot to intercept and track LOC, VOR/RNAV and GPS courses. TURN COORDINATOR L R 2 MIN. NO PITCH INFORMATION To arm APR mode (with the KAP 140 currently in the HDG mode): 1. Select the desired frequency for LOC, VOR or RNAV. For GPS, verify the desired approach. 6 E N 30 S 33 15 21 24 W ı 24 GS 12 3 GS 2.
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Single Axis Operation 5. If the Course Deviation Bar is greater than 2 to 3 dots: the aircraft will continue in HDG mode (or ROL if HDG is not selected) with the APR ARM annunciated; when the computed capture point is reached HDG mode will disengage, the ARM annunciator will go out and the selected course will be automatically captured and tracked.
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Single Axis Operation G KAP 140 HDG AP NAV APR REV Back Course (REV) Mode Using a DG from HDG Mode (45° Intercept) D.C. ELEC. The Back Course (REV) mode allows the autopilot to intercept and track a localizer back course. TURN COORDINATOR L To arm REV mode (with the KAP 140 currently in the HDG mode): R 2 MIN. NO PITCH INFORMATION 1. Select the desired frequency for LOC. 2. OBS Knob - SELECT front course inbound heading. 24 21 15 30 12 S W 33 3. REV Mode Selector Button PRESS.
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Single Axis Operation 4. Heading Selector Knob ROTATE BUG to agree with the FRONT COURSE inbound heading. Note Instruments: CDI needle to the right. Intercept heading 45° to the left of the back course. 5. If the Course Deviation Bar is greater than 2 to 3 dots: the autopilot will annunciate REV ARM; when the computed capture point is reached the ARM annunciator will go out and the selected course will be automatically captured and tracked.
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Single Axis Operation G KAP 140 HDG AP NAV APR REV Back Course (REV) Mode Using a DG from ROL Mode (All Angle Intercept) D.C. ELEC. The Back Course (REV) mode allows the autopilot to intercept and track a localizer back course. TURN COORDINATOR L To arm REV mode (with the KAP 140 currently in the ROL mode): R 2 MIN. NO PITCH INFORMATION 1. Maneuver the aircraft to the desired intercept angle prior to selecting ROL mode. 2. Select the desired frequency for LOC. 24 21 15 30 12 W S 33 3.
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Single Axis Operation 5. Heading Selector Knob ROTATE BUG to agree with the FRONT COURSE inbound heading. Note Instruments: CDI needle to the right. Intercept heading 30° to the left of the back course. 6. If the Course Deviation Bar is greater than 2 to 3 dots: the autopilot will annunciate REV ARM; when the computed capture point is reached the ARM annunciator will go out and the selected course will be automatically captured and tracked.
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Single Axis Operation G KAP 140 HDG AP NAV The Back Course (REV) mode allows the autopilot to intercept and track a localizer back course. TURN COORDINATOR L R 2 MIN. NO PITCH INFORMATION 24 21 REV Back Course (REV) Mode Using an HSI D.C. ELEC. To arm REV mode (with the KAP 140 currently in the HDG mode): 1. Select the desired frequency for LOC. 2. Course Bearing Pointer - SET to the FRONT COURSE inbound heading. W S 30 GS APR 15 33 N 12 GS 3.
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Single Axis Operation 5. If the Course Deviation Bar is greater than 2 to 3 dots: the aircraft will continue in HDG mode (or ROL if HDG is not selected) with the REV ARM annunciated; when the computed capture point is reached HDG mode will disengage, the ARM annunciator will go out and the selected course will be automatically captured and tracked.
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Single Axis Operation Single Axis Operation OPERATIONS WITH THE KAP 140 Takeoff And Climb To Assigned Altitude N 2 3 4 01 0° 1 D.C. ELEC. D.C. ELEC. D.C. ELEC. D.C. ELEC. TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR R L L R R 2 MIN. 2 MIN. 2 MIN. NO PITCH INFORMATION NO PITCH INFORMATION NO PITCH INFORMATION 30 33 W 30 24 33 30 24 H H W 30 W 3 3 24 3 3 N 33 30 W 24 N N 21 24 33 33 S W 21 24 W 24 30 H S 21 W 30 1.
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Single Axis Operation Single Axis Operation GPS Capture Using DG N 4 3 010° 40 ° 2 * Description of GPS operation based on Bendix/King GPS receiver. Others may require different operation. D.C. ELEC. D.C. ELEC. D.C. ELEC. D.C. ELEC. TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR L R L R 2 MIN. 2 MIN. NO PITCH INFORMATION NO PITCH INFORMATION W S 24 W 30 21 KAP 140 1. Continuing on heading 010°, a GPS waypoint is established. A 30° intercept is desired.
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Single Axis Operation Single Axis Operation GPS Capture Using HSI N 4 3 010° 40 ° 2 * Description of GPS operation based on Bendix/King GPS receiver. Others may require different operation. D.C. ELEC. D.C. ELEC. D.C. ELEC. D.C. ELEC. TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR L R L R L R 2 MIN. 2 MIN.
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Single Axis Operation Single Axis Operation Outbound On Front Course For Procedure Turn To LOC Approach Using DG 8° 05 283° N 270° 1 2 3 283° 103° 4 8° 23 D.C. ELEC. D.C. ELEC. D.C. ELEC. D.C. ELEC. TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR R L R L L R 2 MIN. 2 MIN. 2 MIN.
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Single Axis Operation Single Axis Operation Outbound On Front Course For Procedure Turn To LOC Approach Using HSI 8° 05 N 270° 1 2 3 283° 103° 4 8° 23 D.C. ELEC. D.C. ELEC. D.C. ELEC. D.C. ELEC. TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR L R R R L 2 MIN. NO PITCH INFORMATION GS S 3 N 15 S 21 12 15 E 15 6 33 3 6 12 6 E 12 E G KAP 140 KAP 140 1. The aircraft is heading 270° with heading engaged.
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Single Axis Operation Single Axis Operation Front Course LOC Approach Using DG 8° 05 N 090° 4 3 2 1 8° 23 D.C. ELEC. D.C. ELEC. D.C. ELEC. D.C. ELEC. TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR L L R 2 MIN. NO PITCH INFORMATION W 24 N 33 N 33 33 30 ı 24 W 30 W G KAP 140 1. Continuing the maneuver on page 38, APR coupling occurs (HDG annunciation changes to APR). The autopilot will capture the localizer and the CDI course index will center.
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Single Axis Operation Single Axis Operation Front Course LOC Approach Using HSI 8° 05 N 090° 4 3 2 1 8° 23 D.C. ELEC. D.C. ELEC. D.C. ELEC. D.C. ELEC. TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR L R L R R L 2 MIN. 2 MIN. NO PITCH INFORMATION NO PITCH INFORMATION 6 3 E GS 6 E GS N 33 33 33 30 30 N 21 W 24 33 30 21 W 24 W 24 W 30 G G G KAP 140 KAP 140 KAP 140 REV 1.
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Single Axis Operation Single Axis Operation Outbound on GPS Approach Using DG 8° 05 2 1 N 270° 3 283° 103° 4 8° 23 D.C. ELEC. D.C. ELEC. D.C. ELEC. D.C. ELEC. TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR L R L R L R L 2 MIN. 2 MIN. 2 MIN.
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Single Axis Operation Single Axis Operation Outbound on GPS Approach Using HSI 8° 05 2 1 N 270° 3 283° 103° 4 * Description of GPS operation based on Bendix/King GPS receiver. Others may require different operation. D.C. ELEC. D.C. ELEC. D.C. ELEC. D.C. ELEC. TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR L R L R L R L 2 MIN. 2 MIN. 2 MIN.
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Single Axis Operation Single Axis Operation Inbound on GPS Approach Using DG 05 N 8° 090° 4 FAF 3 2 1 D.C. ELEC. D.C. ELEC. D.C. ELEC. TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR L R L R 2 MIN. 2 MIN. NO PITCH INFORMATION NO PITCH INFORMATION 24 24 W 1. Continuing the maneuver on page 46, APR mode capture occurs. The autopilot initiates a left turn to track the 058° GPS course. Approach active is indicated on the GPS annunciator.
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Single Axis Operation Single Axis Operation Inbound on GPS Approach Using HSI 05 N 8° 090° 4 FAF 3 2 * Description of GPS operation based on Bendix/King GPS receiver. Others may require different operation. 1 8° D.C. ELEC. D.C. ELEC. D.C. ELEC. D.C. ELEC. TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR L R L R L R L 2 MIN. 2 MIN. 2 MIN.
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Single Axis Operation This page intentionally left blank 54 KAP 140 AUTOPILOT SYSTEM Rev.
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Two Axis Operation KAP 140 Two Axis Operation The KAP 140 is a digital, panel-mounted autopilot system for light aircraft. 13 12 14 11 10 G KAP 140 UP P R HDG AP NAV APR REV DN ALT Two-axis Flight Control Computer G KAP 140 UP 1 P R HDG AP 2 3 4 NAV 5 APR REV 6 DN ALT 7 8 9 Full Two-Axis KAP 140 Display 1.
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Two Axis Operation 5. NAVIGATION (NAV) MODE SELECTOR BUTTON - When pushed, will arm the navigation mode. The mode provides automatic beam capture and tracking of VOR, LOC or GPS as selected for presentation on the HSI or CDI. NAV mode is recommended for enroute navigation tracking. NAV mode may also be used for front course LOC tracking when GS tracking is not desired. 6. APPROACH (APR) MODE SELECTOR BUTTON - When pushed, will arm the Approach mode.
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Two Axis Operation 12. PITCH MODE DISPLAY Displays the active and armed pitch modes (VS, ALT ARM, ALT, and GS. 13. ROLL MODE DISPLAY Displays the active and armed roll modes (ROL, HDG, NAV ARM, NAV, APR ARM, APR, REV ARM, REV, GS ARM). Also displayed will be flashing AP annunciation (5 seconds) at each autopilot disconnect accompanied by an aural tone (for 2 seconds).
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Two Axis Operation G KAP 140 UP AP HDG NAV APR REV ALT DN Vertical Speed (VS) Mode The Vertical Speed (VS) mode allows variable vertical speed climbs and descents. The ALT button toggles between altitude hold and vertical speed modes. Note: The KAP 140 engages into VS mode as a default. To operate in the VS mode (with autopilot currently disengaged): 1. AP button - Press. Note ROL, VS and current vertical speed is displayed.
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Two Axis Operation G KAP 140 UP AP HDG NAV APR REV ALT DN Altitude Hold (ALT) Mode The Altitude Hold (ALT) mode maintains the pressure altitude acquired upon selection of altitude hold. The ALT button toggles between altitude hold and vertical speed modes. To operate in the ALT mode (with autopilot currently in the Vertical Speed mode): 1. ALT button - Press. Note ALT is annunciated and autopilot maneuvers to maintain pressure altitude acquired at button selection. 2.
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Two Axis Operation Two Axis Operation OPERATIONS WITH THE KAP 140 Takeoff And Climb To Assigned Altitude N 2 3 4 01 0° 1 D.C. ELEC. D.C. ELEC. D.C. ELEC. D.C. ELEC. TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR R L L R R 2 MIN. 2 MIN. 2 MIN. NO PITCH INFORMATION NO PITCH INFORMATION NO PITCH INFORMATION 30 33 W 24 33 3 30 N 24 30 W 3 N 33 30 H H W 3 3 24 33 30 W 24 N N 21 24 33 33 S W 21 24 W 24 30 H S 21 2.
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Two Axis Operation Two Axis Operation GPS Capture Using DG N 4 3 010° 40 ° 2 * Description of GPS operation based on Bendix/King GPS receiver. Others may require different operation. D.C. ELEC. D.C. ELEC. D.C. ELEC. D.C. ELEC. TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR R L R 2 MIN. 2 MIN. NO PITCH INFORMATION NO PITCH INFORMATION Rev.
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Two Axis Operation Two Axis Operation GPS Capture Using HSI N 4 3 010° 40 ° 2 * Description of GPS operation based on Bendix/King GPS receiver. Others may require different operation. D.C. ELEC. D.C. ELEC. D.C. ELEC. D.C. ELEC. TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR L R L R L R 2 MIN. 2 MIN. NO PITCH INFORMATION NO PITCH INFORMATION 33 33 30 30 W W W 24 S 24 15 24 15 21 S 21 64 G KAP 140 KAP 140 UP DN 1.
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Two Axis Operation Two Axis Operation Outbound On Front Course For Procedure Turn To ILS Approach Using DG 8° 05 283° N 270° 1 2 3 283° 103° 4 8° 23 D.C. ELEC. D.C. ELEC. D.C. ELEC. D.C. ELEC. TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR R L R L L R 2 MIN. 2 MIN. 2 MIN.
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Two Axis Operation Two Axis Operation Outbound On Front Course For Procedure Turn To ILS Approach Using HSI 8° 05 N 270° 1 2 3 283° 103° 4 8° 23 D.C. ELEC. D.C. ELEC. D.C. ELEC. D.C. ELEC. TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR L R R 12 15 6 GS GS S 3 N N 21 E GS 15 21 S N 33 S 30 24 GS 33 33 21 W GS 3 W 21 GS 30 GS N 24 30 S W 15 12 3 6 12 G 6 E KAP 140 KAP 140 UP DN 12 E 1.
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Two Axis Operation Two Axis Operation Front Course ILS Approach Using DG 8° 05 N 090° 4 3 2 1 D.C. ELEC. D.C. ELEC. D.C. ELEC. D.C. ELEC. TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR L R L R 2 MIN. 2 MIN. NO PITCH INFORMATION NO PITCH INFORMATION N 33 N 33 33 33 N N N 30 30 N N N 24 21 W 24 21 H H 33 30 24 W 33 33 21 30 21 W 30 30 24 24 W H 21 W 30 S Rev.
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Two Axis Operation Two Axis Operation Front Course ILS Approach Using HSI 8° 05 N 090° 4 3 2 1 3 2 4 D.C. ELEC. D.C. ELEC. D.C. ELEC. D.C. ELEC. TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR L R L R 6 E GS 33 33 33 30 30 21 W 24 21 W 24 30 30 21 W 24 AP HDG NAV APR REV ALT KAP 140 UP DN AP 2. The autopilot is following the localizer. At the outer marker, the glideslope deviation needle is at midscale.
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Two Axis Operation Two Axis Operation Outbound on GPS Approach Using DG 8° 05 2 1 N 270° 3 283° 103° 4 8° 23 D.C. ELEC. D.C. ELEC. D.C. ELEC. D.C. ELEC. TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR L R L R L L R 2 MIN. 2 MIN. 2 MIN.
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Two Axis Operation Two Axis Operation Outbound on GPS Approach Using HSI 8° 05 2 1 N 270° 3 283° 103° 4 * Description of GPS operation based on Bendix/King GPS receiver. Others may require different operation. D.C. ELEC. D.C. ELEC. D.C. ELEC. D.C. ELEC. TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR L R L R R 2 MIN.
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Two Axis Operation Two Axis Operation Inbound on GPS Approach Using DG 05 N 1 8° 090° 4 FAF 2 3 2 1 D.C. ELEC. D.C. ELEC. D.C. ELEC. TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR L R L R 2 MIN. 2 MIN. NO PITCH INFORMATION NO PITCH INFORMATION 3 N Rev. 1 Apr/02 30 H W 24 24 21 Remember, speed needs to be controlled with the throttle.
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Two Axis Operation Two Axis Operation Inbound on GPS Approach Using HSI 05 N 1 8° 090° 4 FAF 2 3 2 3 4 * Description of GPS operation based on Bendix/King GPS receiver. Others may require different operation. D.C. ELEC. D.C. ELEC. D.C. ELEC. TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR R L R L R 2 MIN. 2 MIN. NO PITCH INFORMATION NO PITCH INFORMATION 3 N 33 30 KAP 140 REV ALT UP DN AP 24 W 24 2.
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Two Axis/Altitude Preselect Operations KAP 140 Two Axis with Altitude Preselect Operation The KAP 140 is a digital, panel-mounted autopilot system for light aircraft. 18 17 16 15 14 G ARM KAP 140 BARO UP P R HDG AP NAV APR REV DN ALT Two-axis w/Altitude PreSelect Flight Control Computer 12 13 11 G ARM KAP 140 BARO UP 1 P R HDG AP 2 3 4 NAV APR 5 REV 6 DN ALT 7 8 9 10 Full KAP 140 Two-Axis with Altitude Preselect Display 1.
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Two Axis/Altitude Preselect Operations 5. NAVIGATION (NAV) MODE SELECTOR BUTTON - When pushed, will arm the navigation mode. The mode provides automatic beam capture and tracking of VOR, LOC or GPS as selected for presentation on the HSI or CDI. NAV mode is recommended for enroute navigation tracking. NAV mode may also be used for front course LOC tracking when GS tracking is not desired. 6. APPROACH (APR) MODE SELECTOR BUTTON - When pushed, will arm the Approach mode.
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Two Axis/Altitude Preselect Operations vice versa. Once the baro setting display is visible the rotary knobs may be used to manually adjust the baro setting if automatic baro correction is not available. 12. ALTITUDE ARM (ARM) BUTTON - When pushed will toggle altitude arming on or off. When ALT ARM is annunciated, the autopilot will capture the altitude alerter displayed altitude (provided the aircraft is climbing or descending in VS to the displayed altitude).
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Two Axis/Altitude Preselect Operations System Operating Modes The lateral modes (HDG, NAV, APR and REV) operate identically as depicted in the KAP 140 Single Axis Operating Modes section. Please refer to that section for text descriptions of lateral mode operation. G ARM KAP 140 BARO UP AP HDG NAV APR Vertical Speed (VS) Mode The Vertical Speed (VS) mode allows variable speed climbs and descents. The ALT button toggles between altitude hold and vertical speed modes.
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Two Axis/Altitude Preselect Operations G ARM KAP 140 BARO UP AP HDG NAV APR REV ALT DN Altitude Hold (ALT) Mode The Altitude Hold (ALT) mode maintains the pressure altitude acquired upon selection of altitude hold. The ALT button toggles between altitude hold and vertical speed modes. To operate in the ALT mode (with autopilot currently in the Vertical Speed mode): 1. ALT button - Press. Note ALT is annunciated and autopilot maneuvers to maintain pressure altitude acquired at button selection.
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Two Axis/Altitude Preselect Operations Altitude Alerting and Preselect The Altitude Preselect function allows capturing of a desired altitude and transferring into altitude hold. Manual input of desired altitude is accomplished through the rotary knobs on the faceplate of the KAP 140. The Altitude Alerting function will visually and aurally announce approaching, acquiring and deviation from a selected altitude.
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Two Axis/Altitude Preselect Operations alerting is an aural alert (five short tones) which occurs 1000 ft. from the selected altitude upon approaching the altitude and 200 ft. from the selected altitude on leaving the altitude. G ARM KFC 140 BARO UP AP HDG NAV APR REV ALT 1. ALTITUDE SELECT knob ROTATE until desired altitude is displayed. ARM annunciation occurs automatically upon altitude selection when the autopilot is engaged. G ARM KFC 140 BARO UP HDG NAV APR REV ALT DN 2.
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Two Axis/Altitude Preselect Operations Two Axis/Altitude Preselect Operations OPERATIONS WITH THE KAP 140 Takeoff And Climb To Assigned Altitude N 2 3 4 01 0° 1 D.C. ELEC. D.C. ELEC. D.C. ELEC. D.C. ELEC. TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR R L L R R 2 MIN. 2 MIN. 2 MIN.
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Two Axis/Altitude Preselect Operations Two Axis/Altitude Preselect Operations GPS Capture Using DG N 4 3 010° 40 ° 2 * Description of GPS operation based on Bendix/King GPS receiver. Others may require different operation. D.C. ELEC. D.C. ELEC. D.C. ELEC. D.C. ELEC. TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR R L R 2 MIN. 2 MIN. NO PITCH INFORMATION NO PITCH INFORMATION 30 W 33 30 33 30 33 33 33 30 30 W 30 3 N 30 15 S 21 24 H Rev.
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Two Axis/Altitude Preselect Operations Two Axis/Altitude Preselect Operations GPS Capture Using HSI N 4 3 010° 40 ° 2 * Description of GPS operation based on Bendix/King GPS receiver. Others may require different operation. D.C. ELEC. D.C. ELEC. D.C. ELEC. D.C. ELEC. TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR L R L R L R 2 MIN. 2 MIN.
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Two Axis/Altitude Preselect Operations Two Axis/Altitude Preselect Operations Outbound On Front Course For Procedure Turn To ILS Approach Using DG 8° 05 283° N 270° 1 2 3 283° 103° 4 8° 23 D.C. ELEC. D.C. ELEC. D.C. ELEC. D.C. ELEC. TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR R L R L L R 2 MIN. 2 MIN. 2 MIN.
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Two Axis/Altitude Preselect Operations Two Axis/Altitude Preselect Operations Outbound On Front Course For Procedure Turn To ILS Approach Using HSI 8° 05 N 270° 1 2 3 283° 103° 4 8° 23 D.C. ELEC. D.C. ELEC. D.C. ELEC. D.C. ELEC.
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Two Axis/Altitude Preselect Operations Two Axis/Altitude Preselect Operations Front Course ILS Approach Using DG 8° 05 N 090° 4 3 2 1 D.C. ELEC. D.C. ELEC. D.C. ELEC. D.C. ELEC. TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR L R L R 2 MIN. 2 MIN. NO PITCH INFORMATION NO PITCH INFORMATION N 33 30 30 H Rev. 1 Apr/02 OBS PUSH US H 24 21 24 W KAP 140 AUTOPILOT SYSTEM N 33 33 30 33 21 W 2. The autopilot is following the localizer.
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Two Axis/Altitude Preselect Operations Two Axis/Altitude Preselect Operations Front Course ILS Approach Using HSI 8° 05 N 090° 4 3 2 1 3 2 4 D.C. ELEC. D.C. ELEC. D.C. ELEC. D.C. ELEC. TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR L R L R 6 E GS 33 33 33 30 30 21 W 24 21 W 24 30 30 21 BARO G ARM KAP 140 24 UP DN W 1.
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Two Axis/Altitude Preselect Operations Two Axis/Altitude Preselect Operations Outbound on GPS Approach Using DG 8° 05 2 1 N 270° 3 283° 103° 4 8° 23 D.C. ELEC. D.C. ELEC. D.C. ELEC. D.C. ELEC. TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR L R L R L R L 2 MIN. 2 MIN. 2 MIN.
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Two Axis/Altitude Preselect Operations Two Axis/Altitude Preselect Operations Outbound on GPS Approach Using HSI 8° 05 2 1 N 270° 3 283° 103° 4 * Description of GPS operation based on Bendix/King GPS receiver. Others may require different operation. D.C. ELEC. D.C. ELEC. D.C. ELEC. D.C. ELEC. TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR L R L R R 2 MIN.
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Two Axis/Altitude Preselect Operations Two Axis/Altitude Preselect Operations Inbound on GPS Approach Using DG 05 N 1 8° 090° 4 FAF 2 3 2 1 D.C. ELEC. D.C. ELEC. D.C. ELEC. TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR R L R 2 MIN. 2 MIN. NO PITCH INFORMATION NO PITCH INFORMATION Rev. 1 Apr/02 30 H W 24 24 21 Remember, speed needs to be controlled with the throttle. 33 N 33 30 33 H 21 H DN 2.
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Two Axis/Altitude Preselect Operations Two Axis/Altitude Preselect Operations Inbound on GPS Approach Using HSI 05 N 1 8° 090° 4 FAF 2 3 2 3 4 * Description of GPS operation based on Bendix/King GPS receiver. Others may require different operation. D.C. ELEC. D.C. ELEC. D.C. ELEC. TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR L R R L R 2 MIN. 2 MIN.
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Two Axis/Altitude Preselect Operations This page intentionally left blank 112 KAP 140 AUTOPILOT SYSTEM Rev.
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KCS 55A Compass System KCS 55A Compass System The KCS 55A Compass System, which includes the KA 51B Slaving Control and Compensator Unit, the KMT 112 Magnetic Slaving Transmitter and the KG 102 Directional Gyro as well as the KI 525A Pictorial Navigation Indicator is an optional part of the KAP 140 Autopilot System.
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KCS 55A Compass System KI 525A Indicator heading and VOR/LOC/Glideslope information into one compact display. By providing a simple, comprehensive visual presentation of the aircraft’s heading and position in relation to a desired course, the pilot’s navigation workload is considerably reduced. The KI 525A Pictorial Navigation Indicator is the panel display for the KCS 55A Compass System.
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KCS 55A Compass System Selected Course Pointer - On this two-part arrow, the “head” indicates the desired VOR or Localizer course and the “tail” indicates the reciprocal. This pointer is set by rotating the course select knob. Course Select Knob - Used to rotate the course pointer to the desired course on the compass card. This knob corresponds to the Omni Bearing Selector (OBS) on standard NAV indicators.
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KCS 55A Compass System Compass Warning Flag - A red flag labeled “HDG” becomes visible in the upper right quadrant of the display whenever the electrical power is inadequate or the directional gyro is not up to speed. Compass failures can occur which will not be annunciated by the “HDG” flag. Therefore, periodic comparison with the standby compass is advised. NAV Warning Flag - A red flag labeled “NAV” becomes visible in the upper left quadrant of the display whenever a usable signal is not being received.
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KCS 55A Compass System KMT 112 Magnetic Slaving Transmitter This unit senses the direction of the earth’s magnetic field and continuously transmits this information through the slaving circuitry to the directional gyro which is automatically corrected for precession or “drift”. This sensor is mounted remotely – usually in a wingtip – to eliminate the possibility of magnetic interference.
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KCS 55A Compass System Under some conditions it is possible for the system to stop slaving exactly 180 degrees from the correct heading. If this should occur, move the “Slave” switch on the KA 51B to the unslaved (free) position. Rotate the compass card ±10 degrees from the incorrect heading by using the manual rotation switch and then return the system to slaved operation. The system will then slave to the correct heading. 8.
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KCS 55A Compass System 12. The glideslope pointers indicate the relative position of the glideslope path with respect to the aircraft. (In other words, if the pointers are above the center marker, the aircraft is below the glideslope.) Abnormal Circumstances If the Warning Flag (HDG) appears during operation, the compass card indications will be in error. Power may be removed from the KG 102A Directional Gyro by pulling the appropriate circuit breaker.
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KCS 55A Compass System KCS 55A Compass System 12 3 33 N N N 3 N N 33 33 33 30 W 30 33 24 W 30 30 21 Rev. 0 Jun/98 ı GS S The “TO” indicator starts to swing to “FROM” as you fly over the Napoleon VORTAC station. At this time, set the selected course pointer on the V-12 course of 088°. As you begin your left turn to track V-12, notice that the KI525A HSI continuously displays an accurate picture of the relationship between your aircraft and the ANX 088 radial.
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KCS 55A Compass System KCS 55A Compass System E E 12 6 GS E GS N 3 33 3 N E 30 N N 33 W 33 24 24 30 W 24 30 ı S W 30 24 ı 15 33 6 12 N 3 GS 21 21 33 GS S S 21 21 W 30 122 12 6 GS S S ı GS 15 GS 15 3 12 15 GS 15 3 6 GS W 12 ı 24 E 21 6 GS ı 6. 7. 8. Airway Interception 9. 10. As you fly over the Columbia station, the TO/FROM indicator changes to “FROM”.
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KCS 55A Compass System 0 HOLDING PATTERN 1 9 27 2 064 244 3 4 6 E 3 GS 15 12 GS S GS N E 21 12 GS 18 6 33 24 15 W 3 30 S 30 21 N 33 W 24 ı ı 1. Approaching the STL VORTAC, the controller asks you to hold southwest of the VORTAC on the 244° radial, right turns. You are now over the station with a 064° course selected (the TO/FROM indicator has swung to “FROM”).
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KCS 55A Compass System 2000 E Arc 13 DM ILS APPROACHFRONT COURSE 1 2 3 13 0 2000 13 DME Arc 4 LOM MM E 30 N 6 W 15 GS 24 33 12 21 12 GS 30 S GS S 15 W 33 3 N 24 21 GS 3 E 6 ı ı 1. You are vectored from the holding pattern to the 13 DME arc. The aircraft is turning, with the heading bug set on 170° to intercept the localizer. You have already set the selected course pointer on the inbound ILS course 130° and the KI 525A shows the localizer course is directly ahead.
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KCS 55A Compass System BACK COURSE APPROACH - (REV) 24 21 1 058 2 193 3 21 S W GS GS W 12 30 S 15 GS 24 GS 4 236 013 If a back course approach is required, it can be accomplished as easily as a front course approach. The course arrow should always be set on the front course inbound localizer course. This will result is conventional pictorial deviation sensing even on back course.
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Abnormal Procedures Abnormal Procedures Autopilot Malfunction An autopilot, autopilot trim or manual electric trim malfunction may be recognized as an uncommanded deviation in the airplane flight path or when there is abnormal control wheel or trim wheel motion. The primary concern in reacting to an autopilot or trim malfunction, or to an automatic disconnect of the autopilot, is in maintaining control of the airplane.
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Honeywell Aerospace Business and General Aviation Honeywell International Inc. 23500 West 105th Street Olathe, KS 66061 Tel: 913-712-0400 Fax: 913-712-1302 www.honeywell.com 006-18034-0000 Rev. 3 November 2005 ©1998, 2002, 2005 Honeywell International Inc.