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KAP 140 PG R3

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1. 3 At the missed approach point the pilot disen 4 The pilot initiates the missed approach and sta gages the autopilot with the button on the con bilizes the aircraft in the climb The heading trol wheel This cancels all operating modes bug is set to the missed approach heading of The flashing AP annunciations are displayed and 090 By depressing the HDG button on the KAP 140 the autopilot engages into the head ing mode commencing a right turn to a head ing of 090 Note Press and hold the AP button for 0 25 seconds to engage the autopilot applicable only to software version 03 01 and later a disconnect tone will sound Rev 1 Apr 02 KAP 140 AUTOPILOT SYSTEM 43 Single Axis Operation Single Axis Operation Front Course LOC Approach Using HSI M4 D C ELEC D C ELEC Dic ELEC D C ELEC TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR z L 2MIN 4 2MIN 2MIN J 2 MIN No PITCH A NO PITCH NO PITCH y NO PITCH INFORMATION INFORMATION _ e INFORMATION e INFORMATION Hil LJ Hlc SHH tt Tar a uu m moo 1 Continuing the maneuver on page 40 APR cou 2 The autopilot is following the localizer The 3 At the missed approach point the pilot disen 4 The pilot initiates the missed approach and sta pling occurs HDG annunciation changes to autopilot will make bank changes as necessary gages the autopilot with the button on the con bilizes the aircraft in the climb
2. 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 annun ciator will go out and the selected course will be automatically cap tured and tracked If the D Bar is less than 2 to 3 dots the HDG mode will disengage upon select ing REV mode the REV annunci ator will illuminate and the capture track sequence will automatically begin Note Intercept angles greater than 45 can result in course overshoot when close to the station Therefore intercept angles greater than 45 are not recommended Rev 1 Single Axis Operation Apr 02 KAP 140 AUTOPILOT SYSTEM 29 Single Axis Operation BENDIX KING KAP 140 Back Course REV Mode Using an HSI The Back Course REV mode allows the autopilot to intercept and D C ELEC TURN COORDINATOR track a localizer back course mm To arm REV mode with the tr KAP 140 currently in the HDG RUN mode INFORMATION 1 Select the desired frequency for LOC 2 Course Bearing Pointer SET to the FRONT COURSE inbound heading 3 Heading Selector Knob SET BUG to provide desired intercept angle 4 REV Mode Selector Button PRESS Note REV ARM annunci lt 3 RE 257 y 9 XS nT o or ated BENDIX KING Rev 1 30 KAP 140 AUTOPILOT SYSTEM Apr 02 5 If
3. e oun amua Bp L3 CJ CJ CJ cg E3 1 The aircraft is in APR mode approaching the 2 Upon waypoint alerting at the IAF the heading IAF Approach arm is indicated on the GPS bug is set to 238 the GPS s Leg OBS mode annunciator switching is set to OBS mode and the OBS is set to 238 The autopilot initiates a left turn to track the 238 GPS course Rev 1 14 KAP 140 AUTOPILOT SYSTEM Apr 02 D C ELEC TURN COORDINATOR 3 At the desired point heading mode is used to initiate the procedure turn During the procedure turn outbound the deviation bar shows that the aircraft is flying away from the GPS course at a 45 angle on a selected heading of 283 Rev 1 Two Axis Operation m af d 2 MIN NOPITCH INFORMATION 4 The heading bug has been set to 103 and the aircraft has made a left turn to this heading The GPS s Leg OBS mode switching is set to Leg mode and the OBS is set to 058 Select approach mode by depressing the APR button The HDG annunciation will flash for five sec onds then extinguish Move the heading bug within five seconds to 058 Since the 45 intercept is 103 the aircraft will not turn until the course is captured Apr 02 KAP 140 AUTOPILOT SYSTEM 15 Two Axis Operation Outbound on GPS Approach Using HSI Description of GPS operation based on Bendix King GPS receiver Others may require different operation D C ELEC TURN COORDINATOR m ERE 2 MIN NO PIT
4. e Dc ELEC DC ELEC TURN COORDINATOR TURN COORDINATOR SS SS Ll L R 2MIN 2 MIN NO PITCH INFORMATION No PITCH e INFORMATION ir a omg LJ EJ rg EJ a omaaae 1 Continuing the maneuver on page 76 APR 2 At the FAF ALT is depressed to activate vertical mode capture occurs The autopilot initiates a speed mode The desired descent rate is left turn to track the 058 GPS course obtained using the DH button Approach active is indicated on the GPS Remember speed needs t be controlled wih annunciator the Proto Rev 1 80 KAP 140 AUTOPILOT SYSTEM Apr 02 OCT TURN COORDINATOR d4 Ld A NE y 2MIN 4 NO PITCH e INFORMATION noo ao At the MDA the ALT button is depressed caus ing the autopilot to level off and maintain a con stant altitude At the MAP the pilot disengages the autopilot with the button on the control wheel A flashing AP annunciation is displayed and a distinctive tone will sound Rev 1 Two Axis Operation D C ELEC TURN COORDINATOR 2MIN No PITCH INFORMATION _ 4 The pilot initiates the missed approach and sta bilizes the aircraft in the climb The heading bug is set to the missed approach heading of 090 By depressing the HDG button on the KAP 140 the autopilot engages into the head ing and vertical speed modes commencing a right turn to a heading of 090 and maintaining the rate of climb existing a
5. 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 Preselect Optional Standard Standard Optional Optional Yes Yes Yes Yes Yes Yes Yes Optional Yes Yes Yes Standard with DG or optional HSI Standard with DG only Both Yes Optional Standard Standard Optional Optional Yes Yes Yes Yes Yes Yes Optional Yes Yes Yes Standard with DG or optional HSI Standard with DG only Both Yes KAP 140 System Capabilities Rev 1 Apr 02 KAP 140 AUTOPILOT SYSTEM Introduction KAP 140 KAP 140 Two Axis Single Axis Optional Standard Standard Yes Yes Yes Yes Optional Yes Yes Standard with DG or optional HSI Standard with DG only Both Introduction System Integration The individual system diagrams on pages 5 6 and 7 show the compo nents and their relationship in typical KAP 140 Single Axis KAP 140 Two Axis and KAP 140 Two Axis Altitude Preselect systems The actual com ponents on individual systems may vary slightly in order to optimize cer tification and installation require ments Each system has a number of inputs sensor outputs are shown in red combination inputs are shown in blue display outputs are shown in orange and aircraft control shown in green The systems diagrams reflect that the
6. You must now select the approach mode by depressing the APR button on the KAP 140 The HDG annunciation will flash for five sec onds then extinguish While the HDG annuncia tion is flashing move the heading bug to the front course 058 Since the 45 intercept is 103 the aircraft will not turn until the front course is captured Apr 02 KAP 140 AUTOPILOT SYSTEM 67 Two Axis Operation Outbound On Front Course For Procedure Turn To ILS Approach Using HSI D C ELEC TURN COORDINATOR 2 MIN NO PITCH INFORMATION 1 The aircraft is heading 270 with heading and altitude hold engaged To intercept and fly the ILS front course outbound set the front course on the HSI and depress the back course REV button The back course REV mode is selected to go outbound on the front course The capture point is now being computed based on closure rate 68 2 MIN NO PITCH INFORMATION E3 mmu L9 tcu E3 2 When the computed capture point is reached HOG mode is cancelled and reverse localizer mode is automatically activated and a left turn outbound on the localizer is initiated by the autopilot Mote he iliran deviations at Tie NS course heed e aperafe just as Dough voy were Dying a TORT COMES anpreach Rev 1 KAP 140 AUTOPILOT SYSTEM Apr 02 Dic ELEC TURN COORDINATOR At the desired point HDG mode is used to initi ate the procedure turn Select HDG and set the heading bug to 283 Duri
7. m EA m umuma The autopilot is following the localizer At the outer marker the glideslope deviation needle is at midscale Altitude hold is automatically disen gaged when the glideslope is captured The ALT annunciator extinguishes and GS is displayed The autopilot will make pitch and bank changes as necessary to maintain localizer and glides lope Rev 1 Apr 02 D C ELEC TURN COORDINATOR SSS E L R 2MIN INFORMATION e LJ 3 At the middle marker the pilot disengages the autopilot with the button on the control wheel This cancels all operating modes The flashing AP annunciations are displayed and a discon nect tone will sound Rev 1 Two Axis Altitude Preselect Operations d d D C ELEC TURN COORDINATOR 2 MIN NO PITCH INFORMATION 4 The pilot initiates the missed approach and sta bilizes the aircraft in the climb The heading bug is set to the missed approach heading of 090 By depressing the HDG button on the KAP 140 the autopilot engages into the head ing and vertical speed modes commencing a right turn to a heading of 090 and maintaining the rate of climb existing at engagement Note Press and hold the AP button for 0 25 seconds to engage the autopilot applicable only to software version 03 01 and later Apr 02 KAP 140 AUTOPILOT SYSTEM 101 Two Axis Altitude Preselect Operations Two Axis Altitude Preselect Operations Front Course ILS Approach Using HS
8. Back Course REV Mode Using an HSI 0 00 ee eee eee 30 Operations With The KAP 140 0 0 ccc cece eee 32 Takeoff And Climb To Assigned Altitude 0 000 32 GPS Capture Using DG Saas erre e RR e haere we 34 GPS Capture Using HSI sise vre lisse 36 Outbound On Front Course For Procedure Turn To LOC Approach Ur gut 38 Outbound On Front Course For Procedure Turn To LOC Approach Using HS scis usce minem ncm tne Roh tari i RUD Teese Ebrei a Bro HU 40 Front Course LOC Approach Using DG sslsese essere 42 Front Course LOC Approach Using HSI 0 0 00 e ee ee 44 Outbound on GPS Approach Using DG 000 eee eee 46 Outbound on GPS Approach Using HSI 0 00 0 eee eee 48 Inbound on GPS Approach Using DG 0 cee ee 50 Inbound on GPS Approach Using HSI 0 00 e eee eee 52 KAP 140 Two Axis Operation 2 00 cece eee eee eee eee 55 System Operating Modes 06 cece eee eee ees 57 Vertical Speed VS Mode 1 ete 58 Altitude Hold ALT Mode sseseere m IK 59 Operations With The KAP 140 socrii kinesine ee a eee 60 Takeoff And Climb To Assigned Altitude 0 0004 60 GPS Capture USING DG osse np AFER amp RE Rd 62 Rev 0 Jun 98 KAP 140 AUTOPILOT SYSTEM i Table of Contents GPS Capture Using HSI tiet troc e tete ke cede kir 64 Outbound On Front Course For Procedure Turn To ILS Approach Using DG br Rr
9. The heading APR The autopilot will capture the localizer to maintain localizer trol wheel This cancels all operating modes bug is set to the missed approach heading of and the CDI course index will center 090 By depressing the HDG button on the KAP 140 the autopilot engages into the head ing mode commencing a right turn to a head ing of 090 Note Press and hold the AP button for 0 25 seconds to engage the autopilot applicable only to software version 03 01 and later Rev 1 Rev 1 44 KAP 140 AUTOPILOT SYSTEM Apr 02 Apr 02 KAP 140 AUTOPILOT SYSTEM 45 Single Axis Operation Outbound on GPS Approach Using DG Description of GPS operation based on Bendix King GPS receiver Others may require different operation D C ELEC TURN COORDINATOR SS SS Ld L R 2MIN NO PITCH e INFORMATION EE E RD E E 1 The aircraft is in APR mode approaching the IAF Approach arm is indicated on the GPS annunciator OF nc niec TURN COORDINATOR i 2 MIN NO PITCH INFORMATION googgag 63 Upon waypoint alerting at the IAF the heading bug is set to 238 the GPS s Leg OBS mode switching is set to OBS mode and the OBS is set to 238 The autopilot initiates a left turn to track the 238 GPS course Rev 1 46 KAP 140 AUTOPILOT SYSTEM Apr 02 TURN COORDINATOR gt Ld L R 2 MIN INFORMATION e LJ Ea C3 UJ CJ LJ amu 3 At the desired point heading mode is use
10. VS and current vertical speed is displayed If no other modes are selected the autopilot will operate in the ROL and vertical speed hold modes For software version 03 01 and later the AP button must be pressed and held for 0 25 seconds to engage the autopilot 2 UP or DN button Select desired climb or descent rate Each button stroke will increment the vertical speed commanded up or down by 100 ft min per button press or at the rate of approxi mately 300 ft min per second if held continuously To initiate a climb or descent from Altitude Hold ALT mode 1 ALT button Press Note ALT 86 KAP 140 AUTOPILOT SYSTEM changes to VS and current vertical speed is displayed 2 UP or DN button Select desired climb or descent rate Each button stroke will increment the vertical speed commanded up or down by 100 ft min per button press or at the rate of approxi mately 300 ft min per second if held continuously Note VS command value will be dis played during Control Wheel Steering CWS and for three sec onds following VS engagement or pressing the UP or DN button Both altitude and vertical speed utilize the same display area Altitude is always displayed except during vertical speed selection If the VS command value is not displayed pressing and releasing the UP or DN button will not change the indicated altitude ref erence but will display the VS com mand value Note When operating at or near the
11. c AUTOPILOT OPERATION CONTINUE if satisfied that the out of trim condition was tempo rary DISCONTINUE if evidence indicates a failure of the auto trim function The following optional voice mes sages will be annunciated if the sys tem is configured for voice messag ing 1 ALTITUDE 1000 feet before approaching selected alti tude 2 LEAVING ALTITUDE 200 feet away departing selected alti tude 3 AUTOPILOT Autopilot has disengaged either through pilot action or automatically Two Axis Altitude Preselect Operations OPERATIONS WITH THE KAP 140 Takeoff And Climb To Assigned Altitude 1 The aircraft is well off the ground and estab 2 lished at a safe climb rate The heading bug on the DG or HSI is turned to the desired heading of 080 runway heading By depressing the HDG button on the KAP 140 the autopilot engages into the heading and ver tical speed modes and maintains the selected heading of 080 and current rate of climb Note Press and hold the AP button for 0 25 seconds to engage the autopilot applicable only to software version 03 01 and later 90 KAP 140 AUTOPILOT SYSTEM The heading bug on the DG or HSI is turned to the new desired heading of 010 and the aircraft begins to respond with an immediate left turn A cruise altitude of 7 000 feet is entered using the rotary knobs Altitude ARM annunciation occurs automatically upon selection Rev 1 Apr 02
12. AUTOPILOT SYSTEM Apr 02 Dic ELEC TURN COORDINATOR At the desired point HDG mode is used to initi ate the procedure turn Select HDG and set the heading bug to 283 During the procedure turn outbound the deviation bar shows that the air craft is flying away from the localizer centerline at a 45 angle on a selected heading of 283 Rev 1 Single Axis Operation goog wg 4 Now you have reset the heading bug to 103 and made a 180 turn to this heading The 103 heading will intercept the front course of 058 You must now select the approach mode by depressing the APR button on the KAP 140 Automatic capture of the localizer will occur Apr 02 KAP 140 AUTOPILOT SYSTEM 41 Single Axis Operation Front Course LOC Approach Using DG p c ELEC Dic ELEC A TURN COORDINATOR TURN COORDINATOR i 2 MIN 2 MIN NO PITCH NO PITCH INFORMATION INFORMATION go U3 UJ CJ w ta omnu 1 Continuing the maneuver on page 38 APR cou 2 The autopilot is following the localizer The pling occurs HDG annunciation changes to autopilot will make the bank changes as neces APR The autopilot will capture the localizer sary to maintain localizer and the CDI course index will center Rev 1 42 KAP 140 AUTOPILOT SYSTEM Apr 02 Single Axis Operation TA d Dic ELEC S p c ELEC TURN COORDINATOR TURN COORDINATOR SSS Ld L R 2MIN 2 MIN NO PITCH NO PITCH e INFORMATION e INFORMATION
13. ILS Approach MSHA ASU iie ter erben arse oranda xeu shady toa A emer 98 Front Course ILS Approach Using DG 000 100 Front Course ILS Approach Using HSI isusslslsseesssse 102 Outbound on GPS Approach Using DG 0 0 00000 104 Outbound on GPS Approach Using HSI 0 00000 106 Inbound on GPS Approach Using DG 0 0 lesse 108 Inbound on GPS Approach Using HSI 0 0 00000 110 KCS 55A Compass System 0 2 cece eee eee 113 KI 525A Iridicator i csos es tanp rios rad ORR EOE SRY Rt ER ERE 114 Description of Indicator and Display Functions 114 Slaving Meter KA51B sssseessees eene 116 KMT 112 Magnetic Slaving Transmitter 0 000 117 KG 102A Directional Gyro us sn di ris kx ne edo e RO RE t17 Abnormal Circumstances score piti carortngr turais eee 119 Flight Procedures with the KCS 55A 2 eee eee 120 Abnormal Procedures sseeeee nnne 127 Autopilot Malfunction 2s ss ee eR ber ERR hh Rm Rh RR CR 127 Rev 0 ii KAP 140 AUTOPILOT SYSTEM Jun 98 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 signif
14. INFORMATION e LJ e LN E 3 When the computed capture point is reached 4 The turn is complete and the autopilot is track the ROL annunciation changes to HAV and a ing the GPS course right turn is initiated by the autopilot Rev 1 Apr 02 KAP 140 AUTOPILOT SYSTEM 35 Single Axis Operation Single Axis Operation GPS Capture Using HSI Description of GPS operation based on Bendix King GPS receiver Others may require different operation D C ELEC D C ELEC Dic ELEC D C ELEC TURN COORDINATOR TURN COORDINATOR mm Pu Dy Mr Ly y TURN COORDINATOR TURN COORDINATOR T x Ll LJ L R 2MIN p 2MIN NOPITCH rT A No prrcH e ioi a INFORMATION _ 2 MIN 2 MIN NO PITCH NO PITCH INFORMATION e INFORMATION _ E wer D L ouu E a ouu a ouu Lu 1 Continuing on heading 010 a GPS waypointis 2 GPS data is selected for the HSI The course 3 When the computed capture point is reached 4 The turn is complete and the autopilot is track established A 30 intercept is desired pointer is set to 040 The HAV button is the HDG annunciation changes to NAW and a ing the GPS course depressed and HAW ARM is annunciated right turn is initiated by the autopilot Rev 1 Rev 1 36 KAP 140 AUTOPILOT SYSTEM Apr 02 Apr 02 KAP 140 AUTOPILOT SYSTEM 31 Single Axis Operation Outbound On Front Course For Procedure Turn To LOC Approach Using DG OCT D C ELEC TURN COORDINATOR TURN COORDINATOR
15. an indication of a pitch trim fault During manual electric trim operation autopilot disengaged detection of a stuck MET switch will be indicated by a solid PT When the fault is corrected the annunciation will extinguish 16 PITCH MODE DISPLAY Displays the active and armed pitch modes VS ALT ARM ALT and GS 17 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 sec onds at each autopilot disconnect accompanied by an aural tone for 2 seconds 18 AUTOPILOT ENGAGED AP ANNUNCIATION Illuminates when ever the autopilot is engaged Flashes during pilot initiated or auto matic disengagement Only applica ble for software versions 03 01 or later KAP 140 AUTOPILOT SYSTEM 85 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 sec tion for text descriptions of lateral mode operation BENDIX KING KAP 140 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 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
16. easy reference Mate Far system Hmifalons refer ip vour F ght Mana Suppe ment Rev 0 126 KAP 140 AUTOPILOT SYSTEM Jun 98 Abnormal Procedures Abnormal Procedures Autopilot Malfunction An autopilot autopilot trim or manual electric trim malfunction may be recog nized as an uncommanded deviation in the airplane flight path or when there is abnormal control wheel or trim wheel motion The primary concern in react ing to an autopilot or trim malfunction or to an automatic disconnect of the autopilot is in maintaining control of the airplane Immediately grasp the con trol wheel and press and hold down the A P DISC TRIM INTER switch throughout the recovery Manipulate the controls as required to safely main tain operation of the airplane within all of its operating limitations CAUTION Refer to the Airplane Flight Manual or the Airplane Flight Manual Supplement for your particular aircraft for pertinent emergency procedures Rev 0 Jur 98 KAP 140 AUTOPILOT SYSTEM 127 Abnormal Procedures This page intentionally left blank Rev 0 128 KAP 140 AUTOPILOT SYSTEM Jun 98 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 H n 006 18034 0000 o e e Rev 3 November 2005 1998 2002 2005 Honeywell International Inc
17. make the bank changes as neces left turn to track the 058 GPS course sary to maintain the GPS course Approach active is indicated on the GPS annunciator Rev 1 52 KAP 140 AUTOPILOT SYSTEM Apr 02 Single Axis Operation oe go d D C ELEC D C ELEC TURN COORDINATOR TURN COORDINATOR SS SE Ld L 2 MIN 4 2MIN No PITCH No prrcH e INFORMATION INFORMATION Mi pe t3 C9 t ww 3 At the missed approach point the pilot disen 4 The pilot initiates the missed approach and sta gages the autopilot with the button on the con bilizes the aircraft in the climb The heading trol wheel This cancels all operating modes bug is set to the missed approach heading of The flashing AP annunciations are displayed and 090 By depressing the HDG button on the a disconnect tone will sound KAP 140 the autopilot engages into the head ing mode commencing a right turn to a head ing of 090 Note Press and hold the AP button for 0 25 seconds to engage the autopilot applicable only to software version 03 01 and later Rev 1 Apr 02 KAP 140 AUTOPILOT SYSTEM 53 Single Axis Operation This page intentionally left blank Rev 1 54 KAP 140 AUTOPILOT SYSTEM Apr 02 Two Axis Operation KAP 140 Two Axis Operation The KAP 140 is a digital panel mounted autopilot system for light air craft 13 14 12 BENDIX KING Two axis Flight Control Computer BENDIX KING KAP 140 2
18. right The aircraft is flying away from the localizer centerline at a 45 angle on a selected heading of 283 Check the heading displayed on the DG against the magnetic compass and reset if necessary Rev 1 Two Axis Altitude Preselect Operations p o TURN COORDINATOR Eum monn R 2 MIN INFORMATION e e 4 Now you have reset the heading bug to 103 and made a 180 turn to this heading This 103 heading will intercept the front course of 058 You must now select the approach mode by depressing the APR button on the KAP 140 The HDG annunciation will flash for five sec onds then extinguish While the HDG annuncia tor is flashing move the heading bug to the front course 058 Since the 45 intercept is 103 the aircraft will not turn until the front course is captured Apr 02 KAP 140 AUTOPILOT SYSTEM 97 Two Axis Altitude Preselect Operations Outbound On Front Course For Procedure Turn To ILS Approach Using HSI D C ELEC TURN COORDINATOR 2 MIN 2 MIN NO PITCH NO PITCH INFORMATION INFORMATION AM E moo me Du E 1 The aircraft is heading 270 with heading and 2 When the computed capture point is reached altitude hold engaged To intercept and fly the ILS front course outbound set the front course on the HSI and depress the back course REV button The back course RE mode is selected to go outbound on the front course The capture point is now being c
19. system to stop slaving exactly 180 degrees from the cor rect 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 rota tion switch and then return the system to slaved operation The System will then slave to the cor rect heading 4 For the free gyro operation check the magnetic compass to deter mine the correct magnetic head ing Then use the manual slave Switch to align the system with the earth s magnetic field Periodic checks with the standby compass are recommended to check and correct for gyro precession 5 Until a usable navigation signal is being received by the NAV sys tem a red flag labeled NAV will be visible in the upper left quad rant of the KI 525A Indicator In operation this warning flag should be visible whenever an inade quate navigation signal is being received 6 For normal navigation to or from a VOR or VORTAC set the NAV receiver to the desired VOR or VORTAC frequency and the red navigation flag NAV should dis appear from view if a usable sig nal is being received 7 Rotate the course select knob to position the course pointer to the desired VOR course 118 KAP 140 AUTOPILOT SYSTEM 8 The VOR deviation bar represents the selected course and the rela tionship of this bar to the symbolic aircraft in the center of the instru ment visually pres
20. 02 Two Axis Altitude Preselect Operations OCT TURN COORDINATOR d4 Ld A NE y 2MIN 4 NO PITCH e INFORMATION gt nono ao 3 At the MDA the ALT button is depressed caus ing the autopilot to level off and maintain a con stant altitude At the MAP the pilot disengages the autopilot with the button on the control wheel The flashing AP annunciations are dis played and a distinctive tone will sound Rev 1 D C ELEC TURN COORDINATOR 2MIN No PITCH INFORMATION _ 4 The pilot initiates the missed approach and sta bilizes the aircraft in the climb The heading bug is set to the missed approach heading of 090 By depressing the HDG button on the KAP 140 the autopilot engages into the head ing and vertical speed modes commencing a right turn to a heading of 090 and maintaining the rate of climb existing at engagement Note Press and hold the AP button for 0 25 seconds to engage the autopilot applicable only to software version 03 01 and later Apr 02 KAP 140 AUTOPILOT SYSTEM 111 Two Axis Altitude Preselect Operations This page intentionally left blank Rev 1 112 KAP 140 AUTOPILOT SYSTEM Apr 02 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 I
21. 1 Apr 02 KAP 140 AUTOPILOT SYSTEM 21 Single Axis Operation D C ELEC TURN COORDINATOR 2 MIN NO PITCH INFORMATION Approach APR Mode Using a DG from ROL Mode All Angle Intercept The Approach APR mode allows the autopilot to intercept and track LOC VOR RNAV and GPS courses To arm APR mode with the KAP 140 currently in the ROL mode 1 Maneuver the aircraft to the desired intercept angle prior to selecting ROL mode 2 Select the desired frequency for LOC VOR or RNAV For GPS verify the desired approach 3 OBS Knob SELECT desired approach course For a localizer set it to serve as a memory aid 4 APR Mode Selector Button PRESS Note APR ARM annun ciated NOTE When APR is selected the autopilot will flash HDG for 5 sec onds to remind the pilot to reset the HDG bug to the desired approach course Check the heading dis played on the DG against the mag netic compass and reset if neces Sary Rev 1 22 KAP 140 AUTOPILOT SYSTEM Apr 2 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 annun ciator will go out and the selected course will be automatically cap tured and tracked If
22. 2 MIN 2 MIN NO PITCH NO PITCH INFORMATION INFORMATION ogo ww NN En TURN COORDINATOR e E R 2 MIN No PITCH INFORMATION e LN E am Single Axis Operation pa o TURN COORDINATOR Eum monn R 2MIN INFORMATION e e a ooo 1 The aircraft is heading 270 with heading 2 When the computed capture point is reached 3 At the desired point HDG mode is used to initi 4 Now you have reset the heading bug to 103 engaged To intercept and fly the LOC front course outbound set the front course on the OBS and depress the back course REV but ton While the HDG annunciation is flashing move the heading bug to the front course 058 Since HDG was active upon selection of REV auto intercept mode is cancelled the reverse localizer mode is automatically activated and a left turn outbound on the localizer is initiated by the autopilot ate the procedure turn Select HDG and set the heading bug to 283 During the procedure turn outbound the CDI course index goes off scale to the right The aircraft is flying away from the localizer centerline at a 45 angle on a selected heading of 283 and made a 180 turn to this heading This 103 heading will intercept the front course of 058 You must now select the approach mode by depressing the APR button on the KAP 140 While the HD amp annunciation is flashing move the heading bug to the front course 058 Since Mote he em r
23. 3 The autopilot is responding to the heading select mode with a left bank The climb rate has been decreased using the DH button in preparation Two Axis Altitude Preselect Operations 4 Desired altitude has been reached and auto matic altitude capture occurs The autopilot has completed the turn and is now established on a for level out The vertical speed value will be 010 heading displayed upon selection of the DH button and will remain for three seconds Rev 1 Apr 02 KAP 140 AUTOPILOT SYSTEM 9 Two Axis Altitude Preselect Operations GPS Capture Using DG Description of GPS operation based on Bendix King GPS receiver Others may require different operation Za Dc ELEC ev Dc ELEC Y TURN COORDINATOR TURN COORDINATOR uu SS SS L4 L D L Dy 2 MIN 2 MIN NO PITCH NO PITCH Cy INFORMATION e INFORMATION oun ooo 1 Continuing on heading 010 a GPS waypoint is 2 The HDG button is depressed to select ROL established A 30 intercept is desired mode which will allow an all angle intercept GPS data is selected for the CDI and the OBS is set to 040 The HAV button is depressed and HAV ARM is annunciated ROL will change to HDG and flash for five seconds ROL will then be redisplayed While the HDG annunciation is flashing move the heading bug to the desired course of 040 The aircraft will remain wings level until the capture point Rev 1 92 KAP 140 AUTOPILOT SYSTEM Apr 02 T
24. 3 4 5 Full Two Axis KAP 140 Display 1 PITCH AXIS P ANNUNCIATOR When illuminated indicates failure of the pitch axis and will disengage the autopilot when the failure occurs and not allow engagement of the pitch axis 2 AUTOPILOT ENGAGE DISEN GAGE AP BUTTON When pushed engages autopilot if all logic conditions are met The autopilot will engage in the basic roll ROL mode which functions as a wing lev eler and in the vertical speed VS hold mode The commanded verti cal speed will be displayed in the upper right corner of autopilot dis play area The captured VS will be the vertical speed present at the moment of AP button press When pressed again will disengage the autopilot For software version 03 01 Rev 2 May 02 KAP 140 AUTOPILOT SYSTEM 11 10 and later the AP button must be pressed and held for 0 25 seconds to engage the autopilot 3 ROLL AXIS R ANNUNCIATOR When illuminated indicates failure of the roll axis and will disengage the autopilot and not allow engagement 4 HEADING HDG MODE SELEC TOR BUTTON When pushed will arm the Heading mode which com mands the airplane to turn to and maintain the heading selected by the heading bug on either the DG or HSI A new heading may be selected at any time and will result in the airplane turning to the new head ing Button can also be used to tog gle between HDG and ROL modes This button will engage the autopilot in units with
25. 40 Pilot s Guide Revision 0 June 1998 Part Number 006 18034 0000 This is the original version of this publication Table of Contents introduction ien dne ER E sedis duerme ee eee ar Rn 1 General Description ss cssieese ere nex nm tai hon athe eb RU RU Be 2 KAP 140 Single Axis Autopilot System seeseeesssse 2 KAP 140 Two Axis Autopilot System 0 0 00000 0000 2 KAP 140 Two Axis Altitude Preselect Autopilot System 2 System Integration insi rese ee REO pnis MEEKER EOE Bade RA 4 Power Application and Preflight Tests 6 ee eee 8 KAP 140 Single Axis Operation leere 9 System Operating Modes risi ciini misties eee 12 Wing Leveler ROL Mode seeesesn tee 12 Heading Select HDG Mode 0 0 0 c eee eee eee 13 Navigation NAV Mode Using a DG from HDG Mode 45 InterCept iue ede eer a peace a ves 14 Navigation NAV Mode Using a DG from ROL Mode All Angle Intercept sra nir 00 eee ee RII 16 Approach APR Mode Using a DG from HDG Mode 45 Intercept HET 20 Approach APR Mode Using a DG from ROL Mode All Angle Intercept i e ee ea nee be nas Ro en iea ene ES 22 Approach APR Mode Using an HSI 0000 c eee eee ee 24 Back Course REV Mode Using a DG from HDG Mode 457 Intercept idee oes eene se thon e RA op ea daten 26 Back Course REV Mode Using a DG from ROL Mode All Angle Intercept sss ek bea nm Ie n 9 RR emm s 28
26. Altitude Alerting function will visually and aurally announce approaching acquiring and deviation from a selected altitude Altimeter Setting Installations with remote baro input 1 BARO setting CHECK depressing the BARO button will display the baro setting for three seconds Installations without remote baro input Upon successful completion of pre flight test the baro display will flash 1 BARO setting Enter baromet ric setting using the rotary knobs OR if correct as displayed press BARO m oD v rj m m m rg E Note It is recommended that the baro value be updated whenever the aircraft altimeter setting is changed 88 KAP 140 AUTOPILOT SYSTEM Baro unit conversion The barometric pressure display can toggled between IN HG and HPA as needed by the pilot 1 BARO button Press and hold for two seconds Em oD 9 o u mma Altitude Alerter The function of the Altitude Alerter is independent of the autopilot 1 ALTITUDE SELECT knob ROTATE until the desired altitude is displayed 7773 KFC 140 w Loc munn a aua Note The ALERT annunciation is illuminated 1000 ft prior to the selected altitude extinguishes 200 ft prior to the selected altitude and illu minates momentarily when the selected altitude is reached Once the selected altitude is reached a flashing ALERT illumination signifies that the 200 ft safe band has been exceeded and will remain illum
27. BS mode The autopilot ini tiates a left turn to track the 238 GPS course Rev 1 48 KAP 140 AUTOPILOT SYSTEM Apr 02 Single Axis Operation D C ELEC D C ELEC TURN COORDINATOR TURN COORDINATOR c m Ae R J WS R 2 MIN VA 2MIN NO PITCH No PITCH e o INFORMATION L goo UJ LJ L3 amu googgag m 3 At the desired point heading mode is used to 4 The heading bug has been set to 103 and the initiate the procedure turn During the procedure aircraft has made a left turn to this heading turn outbound the deviation bar shows that the The GPS s Leg OBS mode switching is set to aircraft is flying away from the GPS course at a Leg mode and the course pointer is set to 45 angle on a selected heading of 283 D approach mode by depressing the utton Rev 1 Apr 02 KAP 140 AUTOPILOT SYSTEM 49 Single Axis Operation Inbound on GPS Approach Using DG Description of GPS operation based on Bendix King GPS receiver Others may require different operation Dec ELEC A p c ELEC TURN COORDINATOR TURN COORDINATOR L4 L R 2 MIN 2 MIN NO PITCH NO PITCH INFORMATION e INFORMATION Duono a U3 UJ C3 L3 mw 1 Continuing the maneuver on page 46 APR 2 The autopilot is following the GPS course The mode capture occurs The autopilot initiates a autopilot will make the bank changes as neces left turn to track the 058 GPS course sary to maintain the GPS course Appro
28. 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 and GS is disabled 8 ALTITUDE HOLD ALT MODE SELECT BUTTON When pushed will select the Altitude Hold mode This mode provides tracking of the reference altitude The reference alti tude is the altitude at the moment the ALT button is pressed If the ALT button is pressed with an established VS rate present there will be altitude overshoot approximately 1096 of the VS rate with the airplane returned positively to the reference altitude This button will engage the autopilot in units with software prior to soft ware version 03 01 84 KAP 140 AUTOPILOT SYSTEM 9 VERTICAL TRIM UP DN BUT TONS The action of these buttons is dependent upon the vertical mode present when pressed If VS mode is active the initial button stroke will bring up the commanded vertical speed in the display Subsequent immediate button strokes will incre ment the vertical speed commanded either up or down at the rate of 100 ft min per button press or at the rate of approximately 300 ft min per sec ond if held continuously If ALT mode is active incremental button strokes will move the altitude hold reference altitude either up or down at 20 feet per press or if held contin uously will command the airplane up or down at the rate of 500 ft min synchronizing the alti
29. Bar is less than 2 to 3 dots the HDG mode or ROL if HDG is not selected will disen gage upon selecting APR mode the APR annunciator will illumi nate and the capture track sequence will automatically begin Note Intercept angles greater than 45 can result in course overshoot when close to the station Therefore intercept angles greater than 45 are not recommended Rev 1 Apr 02 KAP 140 AUTOPILOT SYSTEM 25 Single Axis Operation Back Course REV Mode Using a DG from HDG Mode 45 Intercept The Back Course REV mode TURN COORDINATOR allows the autopilot to intercept and track a localizer back course D C ELEC To arm REV mode with the KAP 140 currently in the HDG 2 MIN mode NO PITCH INFORMATION 5 1 Select the desired frequency for LOC 2 OBS Knob SELECT front course inbound heading 3 REV Mode Selector Button PRESS Note REV ARM annun ciated NOTE When REV is selected the autopilot will flash HDG for 5 sec onds to remind the pilot to reset the HDG bug to the front course inbound heading Check the heading dis played on the DG against the mag netic compass and reset if neces sary Rev 1 26 KAP 140 AUTOPILOT SYSTEM Apr 02 Single Axis Operation 4 Heading Selector Knob ROTATE BUG to agree with the FRONT COURSE inbound head ing Note Instruments CDI needle to the right Intercept heading 45 to the left of the back course 5 If the Course De
30. CH INFORMATION 1 The aircraft is in APR mode approaching the 2 IAF Approach arm is indicated on the GPS annunciator 76 KAP 140 AUTOPILOT SYSTEM mw ow o Upon waypoint alerting at the IAF the course pointer is set to 238 the GPS s Leg OBS mode Switching is set to OBS mode The autopilot ini tiates a left turn to track the 238 GPS course Rev 1 Apr 02 Two Axis Operation OCT TURN COORDINATOR SSS Ld L R 2 MIN d INFORMATION Q i a Duuu 3 At the desired point heading mode is used to initiate the procedure turn During the procedure turn outbound the deviation bar shows that the aircraft is flying away from the GPS course at a 45 angle on a selected heading of 283 Rev 1 Dic ELEC TURN COORDINATOR 2 MIN NO PITCH INFORMATION _ a a UC3 CJ C3 C32 tu E3 The heading bug has been set to 103 and the aircraft has made a left turn to this heading The GPS s Leg OBS mode switching is set to Leg mode and the course pointer is set to 058 Select approach mode by depressing the APR button Apr 02 KAP 140 AUTOPILOT SYSTEM 77 Two Axis Operation Inbound on GPS Approach Using DG 6 Description of GPS operation based on Bendix King GPS receiver Others may require different operation P Dc ELEC ev Dc ELEC Yo TURN COORDINATOR TURN COORDINATOR SSS Ld LJ L R 2 MIN 2 MIN NO PITCH NO PITCH INFORMATION INFORMATION nog aoe 1 Cont
31. ERROR p bah ea want REF aes doe 66 Outbound On Front Course For Procedure Turn To ILS Approach Using ASI ss usns he nep Re RE RR RG SRE REE Ra EAM 68 Front Course ILS Approach Using DG issslseeseesesese 70 Front Course ILS Approach Using HSI 0002 72 Outbound on GPS Approach Using DG slsseslsesesess 74 Outbound on GPS Approach Using HSI 0 00 00 eee ee eee 76 Inbound on GPS Approach Using DG 0 eee 78 Inbound on GPS Approach Using HSI 00 cee eee eee 80 KAP 140 Two Axis with Altitude Preselect Operation 83 System Operating Modes 0 0 ce eee cee eee 86 Vertical Speed VS Mode 1 ett 86 Altitude Hold ALT Mode sseseeren m m I 87 Altitude Alerting and Preselect 0 2 0 0 cece eee eee eee 88 Altit de Alerter 1 ess sss been Mee Pg Roe wee OR Re we 88 Altimeter Setting ecdesiae e tendon ee dede 88 Altitude Preselect coss aie ei capes EROR Se Mea bok eolen a 89 Voice MeSSaging eire mace ek een ee ne oes ae 89 Operations With The KAP 140 00 eee eee kakra 90 Takeoff And Climb To Assigned Altitude 0 0000 90 GPS Capture Using DG 2 cn rok eet Eee UR E ERR s 92 GPS Capture Using HSI 5 erbe ht e RR gain Ede etre 94 Outbound On Front Course For Procedure Turn To ILS Approach Using DG i bre RR REPRE RI eos eee SERT 96 Outbound On Front Course For Procedure Turn To
32. Free Switch should be moved to select the free gyro mode Then by using manual clockwise or counterclockwise corrections the compass can be rotated to the cor rect heading as indicated on the standby compass The KCS 55A system should continue to function normally except the heading infor mation will be solely derived from the KG 102A Directional Gyro There will be no automatic heading correction and periodic adjustments must be made manually to correct for preces sion by reference to the standby magnetic compass as with any directional gyro Note It is desirable to disconnect the autopilot under the following condi tions 1 HDG flag comes into view 2 System is in fast slave 3 During manual slaving The system has the capability to supply the autopilot with an auto matic disconnect signal under these conditions Note For system limitations in your particular aircraft type refer to your Flight Manual Supplement KAP 140 AUTOPILOT SYSTEM 119 KCS 55A Compass System DE SOTO EMP 1126 Chan75 Loke W nnebogo Mun CONTROL TONE Ereactive 1300 050011 MOT IN EFFECT HOLIDAYS Flight Procedures with the KCS 55A The next few pages depict a normal flight departure from MKC enroute to STL via Victor Airway V 12 The charts shown here are for illustration pur poses only not to be used for navigation Careful study of these illustration of the KI525A HSI should give you a better idea o
33. G Mode 45 Intercept The Approach APR mode TURN COORDINATOR allows the autopilot to intercept and track LOC VOR RNAV and GPS courses D C ELEC To arm APR mode with the aos VA KAP 140 currently in the HDG THD e mode 1 Select the desired frequency for LOC VOR or RNAV For GPS verify the desired approach 2 OBS Knob SELECT desired approach course For a localizer Set it to serve as a memory aid 3 APR Mode Selector Button PRESS Note APR ARM annun ciated NOTE When APR is selected the autopilot will flash HDG for 5 sec onds to remind the pilot to reset the HDG bug to the desired approach course Check the heading dis played on the DG against the mag netic compass and reset if neces sary Rev 1 20 KAP 140 AUTOPILOT SYSTEM Apr 02 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 annun ciator will go out and the selected course will be automatically cap tured and tracked If the D Bar is less than 2 to 3 dots the HDG mode will disengage upon select ing APR mode the APR annunci ator will illuminate and the capture track sequence will automatically begin Rev
34. I 1 D C ELEC TURN COORDINATOR 2 MIN NO PITCH INFORMATION Continuing the maneuver on page 98 APR cou pling occurs HDG annunciation changes to APR and the glideslope mode is automatically armed The autopilot will capture the localizer and the CDI course index will center 02 KAP 140 AUTOPILOT SYSTEM D C ELEC TURN COORDINATOR 2MIN No PITCH INFORMATION _ tity ak oun aoe The autopilot is following the localizer At the outer marker the glideslope deviation needle is at midscale Altitude hold is automatically disen gaged when the glideslope is captured The ALT annunciation extinguishes and BS is displayed The autopilot will make pitch and bank changes as necessary to maintain localizer and glides lope Rev 1 Apr 02 OCT TURN COORDINATOR z L 2MIN NOPITCH dd e mrono e HIIS LM 3 At the middle marker the pilot disengages the autopilot with the button on the control wheel This cancels all operating modes The flashing AP annunciations are displayed and a discon nect tone will sound Rev 1 D C ELEC TURN COORDINATOR 2 MIN NO PITCH INFORMATION _ 4 The pilot initiates the missed approach and sta bilizes the aircraft in the climb The heading bug is set to the missed approach heading of 090 By depressing the HDG button on the KAP 140 the autopilot engages into the head ing and vertical speed modes commencing a righ
35. KAP 140 Honeywell BENDIX KING KAP 140 Ag T is BARO zd zi i j A Bendix King Autopilot System Pilo s Guide 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 For further information contact Aerospace Technical Publications Honeywell One Technology Center 23500 West 105th Street Olathe Kansas 66061 Telephone 913 712 0400 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 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 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 Revision History and Instructions Manual KAP 1
36. KAP 140 systems control both pitch and roll axes of the aircraft 4 KAP 140 AUTOPILOT SYSTEM Rev 1 Apr 02 Introduction Middle VOR LOC RNAV KC 140 Single Axis Marker GPS Deviation Computer Controller Annunciator contains computer functions mode control buttons and annunciations in a single unit KS 271C Roll Servo Directional Gyro KI 204 or other Course Deviation Indicator OR KG102A Slaved DG KS 272C Pitch Trim N Servo Optional Autopilot KI 525A Pictorial KMT 112 Disconnect Navigation Indicator Flux Detector Trim Interrupt Optional KCS 55A Slaved Compass System Optional KA 51B Slaving Accessory Puce SSeS SS SS a Control Manual WheelSteering Electrical Trim Optional Optional KAP 140 Single Axis System Diagram Rev 1 Apr 02 KAP 140 AUTOPILOT SYSTEM 5 Introduction VOR LOC RNAV Static KC 140 Two Axis GPS Deviation Pressure Computer Glideslope Middle Controller Deviation Marker Annunciator contains computer functions mode control buttons and annunciations in a single unit Also contains static pressure sensor and accelerometer KS 271C Roll Servo Directional Gyro KI 204 or other Course Deviation Indicator not included KG102A 23 Slaved DG 2 KMT 112 KI 525A Pictorial jn Flux Detector Navigation Indicator Autopilot Disconnect Trim Interrupt KCS 55A Slaved Com
37. ach active is indicated on the GPS annunciator Rev 1 50 KAP 140 AUTOPILOT SYSTEM Apr 02 Single Axis Operation oe go d D C ELEC 74 TURN COORDINATOR TURN COORDINATOR e L4 2MIN INFORMATION e J nog E P Duo um 3 At the missed approach point the pilot disen 4 The pilot initiates the missed approach and sta gages the autopilot with the button on the con bilizes the aircraft in the climb The heading trol wheel This cancels all operating modes bug is set to the missed approach heading of The flashing AP annunciations are displayed and 090 By depressing the HDG button on the a disconnect tone will sound KAP 140 the autopilot engages into the head ing mode commencing a right turn to a head ing of 090 Note Press and hold the AP button for 0 25 seconds to engage the autopilot applicable only to software version 03 01 and later Rev 1 Apr 02 KAP 140 AUTOPILOT SYSTEM 51 Single Axis Operation Inbound on GPS Approach Using HSI Description of GPS operation based on Bendix King GPS receiver Others may require different operation D C ELEC D C ELEC TURN COORDINATOR TURN COORDINATOR R 2MIN 2 MIN ma 4 INFORMATION INFORMATION _ goomgagd w go CU UJ C3 L3 t4 1 Continuing the maneuver on page 48 APR 2 The autopilot is following the GPS course The mode capture occurs The autopilot initiates a autopilot will
38. ages the autopilot with the button on the control wheel This cancels all operating modes The flashing AP annunciationa are displayed and a discon nect tone will sound Rev 1 Two Axis Operation TA d D C ELEC TURN COORDINATOR 2 MIN NO PITCH INFORMATION 4 The pilot initiates the missed approach and sta bilizes the aircraft in the climb The heading bug is set to the missed approach heading of 090 By depressing the HDG button on the KAP 140 the autopilot engages into the head ing and vertical speed modes commencing a right turn to a heading of 090 and maintaining the rate of climb existing at engagement Note Press and hold the AP button for 0 25 seconds to engage the autopilot applicable only to software version 03 01 and later Apr 02 KAP 140 AUTOPILOT SYSTEM 71 Two Axis Operation Front Course ILS Approach Using HSI 12 D C ELEC TURN COORDINATOR 2 MIN NO PITCH INFORMATION Continuing the maneuver on page 68 APR cou pling occurs HDG annunciation changes to APR and the glideslope mode is automatically armed The autopilot will capture the localizer and the CDI course index will center KAP 140 AUTOPILOT SYSTEM D C ELEC TURN COORDINATOR 2 MIN NO PITCH INFORMATION _ tity ak oun P P The autopilot is following the localizer At the outer marker the glideslope deviation needle is at midscale Altitude hold is automatically disen
39. best rale of climb airspeed at climb power settings and using vertical speed hold it is easy to decelerate to an airspeed where continued decreases in airspeed will result in a reduced rate of climb Continued operation in vertical speed mode can result in a stall Rev 2 May 02 Two Axis Altitude Preselect Operations BENDIX KING KAP 140 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 selec tion 2 UP or DN button Select to change altitude Incremented but ton strokes will move the refer ence altitude by 20 feet per press or if held continuously will com mand a 500 ft min altitude change acquiring a new reference altitude upon button release Note Incremented altitude changes should be limited to 500 ft of change Rev 1 Apr 02 KAP 140 AUTOPILOT SYSTEM 8T 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
40. course inbound localizer course This will result is conventional pic torial deviation sensing even on back course The KI 525A display gives you an accurate picture of where you are at all times during the approach and procedure turn Cae BS pb M BENDIX KING 1 You are outbound on the back localizer course having already set the course pointer to the inbound front course at 238 The heading bug is preset at 193 for the procedure turn Since there is usually no glideslope signal on a back course the glideslope pointers are out of sight iam XN VAC EA S H SN LATET 3 Now you ve reset the heading bug to 013 and made a 180 turn to this heading This 013 heading will intercept the back course The KI 525A clearly pictures the course you are to intercept and the angle of intercep tion During the procedure turn outbound the deviation bar shows pictorially that the air craft as represented by the symbolic air craft in the center of the KI 525A is flying away from the localizer centerline at a 45 angle when the heading bug is under the lubber line Note that left right deviations of the course bar give fly to indicators just as on the front course You have smoothly intercepted the back course Since the course arrow is set on the front course 238 the KI 525A shows a true picture of the situation flying inbound on the back course You may reset the heading bug to 058 for
41. d to initiate the procedure turn During the procedure turn outbound the deviation bar shows that the aircraft is flying away from the GPS course at a 45 angle on a selected heading of 283 Check the heading displayed on the DG against the magnetic compass and reset if necessary Rev 1 Single Axis Operation D C ELEC TURN COORDINATOR a Ld L R 2MIN NO PITCH e INFORMATION ooo ow 4 The heading bug has been set to 103 and the aircraft has made a left turn to this heading The GPS s Leg OBS mode switching is set to Leg mode and the OBS is set to 058 Select approach mode by depressing the APR button The HDG annunciation will flash for five sec onds then extinguish While the HDG annuncia tion is flashing move the heading bug to 058 Since the 45 intercept is 103 the aircraft will not turn until the course is captured Apr 02 KAP 140 AUTOPILOT SYSTEM 47 Single Axis Operation Outbound on GPS Approach Using HSI Description of GPS operation based on Bendix King GPS receiver Others may require different operation OCT D C ELEC TURN COORDINATO j PL L TURN COORDINATOR NP 2MIN NO PITCH y INFORMATION _ a U3 UC CO LJ t3 ooo EE 1 The aircraft is in APR mode approaching the 2 Upon waypoint alerting at the IAF the course IAF Approach arm is indicated on the GPS pointer is set to 238 the GPS s Leg OBS mode annunciator switching is set to O
42. e desired intercept angle prior to selecting ROL mode 2 Select the desired frequency for VOR or RNAV For GPS verify the desired waypoint or destina tion 3 OBS Knob SELECT desired course 4 NAV Mode Selector Button PRESS Note NAV ARM annunci ated NOTE When NAV is selected the autopilot will flash HDG for 5 sec onds to remind the pilot to reset the HDG bug to the OBS course Check the heading displayed on the DG against the magnetic compass and reset if necessary Rev 1 KAP 140 AUTOPILOT SYSTEM Apr 02 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 annun ciator will go out and the selected course will be automatically cap tured and tracked If the D Bar is less than 2 to 3 dots the ROL mode will disengage upon select ing NAV mode the NAV annunci ator will illuminate and the capture track sequence will automatically begin Note Intercept angles greater than 45 can result in course overshoot when close to the station Therefore intercept angles greater than 45 are not recommended Rev 1 Single Axis Operation Apr 02 KAP 140 AUTOPILOT SYSTEM 17 Single Axis Operation BENDIX KING KAP 140 Navi
43. e side or the other Since the entire VOR and Localizer display rotates with the compass card the angular relation ship between the deviation bar and the symbolic aircraft provides a pic torial symbolic display of the air craft s position with respect to the Selected course Deviation Scale When tuned to a VOR frequency each white dot rep resents two degrees of deviation left or right of course When tuned to a Localizer the deviation is 1 2 degree per dot When GPS data is selected for presentation refer to the Pilot s Guide for the GPS receiver Rev 0 Jun 98 KCS 55A Compass System Heading Select Bug A movable orange marker on the outer perime ter of the display used primarily to Select the desired heading you wish to fly This desired heading is cou pled to the KAP 140 Autopilot to pro vide the Heading Select function Heading Select Knob Used to rotate the heading select bug to a desired point on the compass card To From Indicator A white triangle near the center of the display that indicates with reference to the OBS setting whether the course selected is to or from the selected VOR station and or RNAV waypoint Dual Glideslope Pointers Chartreuse triangular pointers on either side of the display drop into view when a usable glideslope sig nal is received and retract out of view when the glideslope signal becomes marginal During an ILS approach these pointers represent the ver
44. engagement The preflight test PFT sequence is indicated by PFT with an increasing number for the sequence steps Successful completion of self test is identified by all display segments being illumi nated Display Test and the discon nect tone sounding 8 KAP 140 AUTOPILOT SYSTEM For two axis units only NOTE Following the preflight test the red P warning on the face of the autopilot may illuminate indicating that the pitch axis cannot be engaged This condition should be temporary lasting no more than 30 seconds The P will extinguish and normal operation will be available NOTE The red P warning may illu minate when the autopilot is not engaged This can occur when autopilot G limits have been exceeded during turbulence or air craft maneuvering Autopilot engagement is locked out during red P illumination If power to the autopilot is cycled in flight i e through the autopilot circuit breaker for instance it is possible that a 5 minute delay may be neces sary prior to autopilot engagement to allow the pitch axis accelerometer circuit to stabilize Engagement prior to stabilization may result in mildly erratic pitch axis behavior Rev 1 Apr 02 Single Axis Operation KAP 140 Single Axis Operation The KAP 140 is a high performance digital panel mounted autopilot sys tem for light aircraft 7 8 BENDIX KING KAP 140 Single axis Flight Control Computer BENDIX KING 1 2 3 4 Full Sin
45. ents the actual relationship of the selected course to your aircraft heading In other words if the symbolic aircraft on the display indicates approaching the deviation bar at 45 degrees that is the angle at which your air craft is actually approaching the Selected course 9 To prepare for an ILS approach tune the NAV receiver to the desired Localizer frequency If a usable Localizer signal is being received the NAV warning flag will disappear 10 For a front or back course approach rotate the course select knob to set the course pointer on the inbound Localizer course As with normal navigation 6 above the LOC deviation bar represents the desired course The relation ship between this bar and the symbolic aircraft gives a true pic ture of your aircraft s position with respect to the Localizer course Always setting the course pointer to the inbound Localizer course provides the correct deviation bar sensing whether flying a front or back course approach 11 The glideslope deviation pointers should become visible on both sides of the display when a usable glideslope signal is received If they do not come into view a usable glideslope signal is not being received Rev 0 Jun 98 12 The glideslope pointers indicate the relative position of the glides lope path with respect to the air craft In other words if the point ers are above the center marker the aircraft is below the glides lope Abno
46. er functions are independent of the arming process thus providing full time alerting even when the autopilot is disengaged 13 ALTITUDE ALERTER VERTI CAL SPEED BARO SETTING DIS PLAY Normally displays the alti tude alerter selected altitude If the UP or DN button is pushed while in VS hold the display changes to the command reference for the VS mode in FPM for 3 seconds If the BARO button is pushed the display changes to the autopilot baro setting in either IN HG or HPA for 3 sec onds NOTE This display may be dashed for up to 3 minutes on start up if a blind encoder is installed which requires a warm up period 14 ALTITUDE ALERT ALERT ANNUNCIATION The ALERT annunciate is illuminated 1000 ft prior to the selected altitude extin guishes 200 ft prior to the selected altitude and illuminates momentarily when the selected altitude is Rev 1 Apr 02 reached Once the selected altitude is reached a flashing ALERT illumi nation signifies that the 200 ft safe band has been exceeded and will remain illuminated until 1000 ft from the selected altitude Associated with the visual alerting is an aural alert 5 short tones which occurs 1000 feet from the selected altitude upon approaching the altitude and 200 feet from the selected altitude on leaving the altitude 15 PITCH TRIM PT ANNUNCIA TION A flashing PT with arrows indicates the direction of required pitch trim A solid PT without an arrow head is
47. f and maintain a con bilizes the aircraft in the climb The heading stant altitude At the MAP the pilot disengages bug is set to the missed approach heading of the autopilot with the button on the control 090 By depressing the HDG button on the wheel A flashing AP annunciation is displayed KAP 140 the autopilot engages into the head and a distinctive tone will sound ing and vertical speed modes commencing a right turn to a heading of 090 and maintaining the rate of climb existing at engagement Note Press and hold the AP button for 0 25 seconds to engage the autopilot applicable only to software version 03 01 and later Rev 2 May 02 KAP 140 AUTOPILOT SYSTEM 109 Two Axis Altitude Preselect Operations Inbound on GPS Approach Using HSI o Description of GPS operation based on Bendix King GPS receiver Others may require different operation e Dc ELEC Dic ELEC TURN COORDINATOR TURN COORDINATOR SSS T 2 MIN 2 MIN NOPITCH NO PITCH 5 INFORMATION A INFORMATION _ noo aoe 1 Continuing the maneuver on page 106 APR 2 At the FAF ALT is depressed to activate vertical mode capture occurs The autopilot initiates a left turn to track the 058 GPS course Approach active is indicated on the GPS annunciator 110 KAP 140 AUTOPILOT SYSTEM speed mode The desired descent rate is obtained using the DH button Remember speed needs im be conmtretied wih Phe ratte Rev 1 Apr
48. f how simple and comprehensive the dis play is NAPOLEON ANX 1140 Chan 87 1 Vectors to Intercept a Radial After takeoff from Kansas City we select a heading of 060 with the heading bug to intercept the 110 course to Napoleon ANX VOR Selected course pointer is set on 110 with the course knob The KI 525A HSI conveniently and accurately displays the intercept angle 120 KAP 140 AUTOPILOT SYSTEM f XS qo X 2 The VOR deviation bar begins to center as we approach the 110 course to Napoleon The KI 525A HSI makes it possi ble to intercept the course smoothly without overshoot ing or bracketing One method of doing this is to adjust your heading so that the top of the deviation bar always touches the lubber line As your aircraft heading approaches the new course the deviation bar will swing towards the center and the angle of intercept will decrease Rev 0 Jun 98 27 i15 Higginsville Industriol Mun HIG 32 110 6 7 VIERTEL 3 Turn to Intercept a Victor Airway 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 As you begin your left turn to track V 12 notice that the KI525A HSI continuously dis plays an accurate picture of the relationship between your aircraft and the ANX 088 radial Once again you can make a pre cise coordinated course inter ce
49. gage the autopilot in units with software prior to software version 03 01 9 VERTICAL TRIM UP DN BUT TONS The action of these buttons is dependent upon the vertical mode present when pressed If VS mode is active button strokes will incre ment the vertical speed commanded either up or down at the rate of 100 ft min per button press or at the rate of approximately 300 ft min per sec ond if held continuously If ALT mode is active incremental button strokes will move the altitude hold reference altitude either up or down at 20 feet per press or if held contin uously will command the airplane up or down at the rate of 500 ft min synchronizing the altitude hold refer ence to the actual airplane altitude upon button release 10 VERTICAL SPEED DISPLAY Displays the commanded vertical speed in VS mode 11 PITCH TRIM PT ANNUNCIA TION A flashing PT with arrows indicates the direction of required pitch trim A solid PT without an arrow head is an indication of a pitch trim fault During manual electric trim operation autopilot disengaged detection of a stuck MET switch will be indicated by a solid PT When the fault is corrected the annunciation will extinguish Rev 1 Apr 02 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 disp
50. gaged when the glideslope is captured The ALT annunciator extinguishes and GS is displayed The autopilot will make pitch and bank changes as necessary to maintain localizer and glides lope Rev 1 Apr 02 OCT TURN COORDINATOR z L 2MIN NOPITCH dd e mrono e HIIS LU 3 At the middle marker the pilot disengages the autopilot with the button on the control wheel This cancels all operating modes The flashing AP annunciations are displayed and a discon nect tone will sound Rev 1 Two Axis Operation D C ELEC TURN COORDINATOR 2 MIN NO PITCH INFORMATION _ 4 The pilot initiates the missed approach and sta bilizes the aircraft in the climb The heading bug is set to the missed approach heading of 090 By depressing the HDG button on the KAP 140 the autopilot engages into the head ing and vertical speed modes commencing a right turn to a heading of 090 and maintaining the rate of climb existing at engagement Note Press and hold the AP button for 0 25 seconds to engage the autopilot applicable only to software version 03 01 and later Apr 02 KAP 140 AUTOPILOT SYSTEM 13 Two Axis Operation Outbound on GPS Approach Using DG Description of GPS operation based on Bendix King GPS receiver Others may require different operation P D C ELEC D C ELEC TURN COORDINATOR TURN COORDINATOR uu L R 2 MIN 2 MIN NO PITCH NO PITCH Cy INFORMATION INFORMATION
51. gation NAV Mode Using an HSI D C ELEC In the navigation NAV mode ENIC OOROINATOR the autopilot intercepts and tracks VOR RNAV and GPS courses To arm NAV mode with the KAP 140 currently in the HDG 2 MIN mode R INFORMATION e 1 Select the desired frequency for VOR or RNAV For GPS verify the desired waypoint or destina tion 2 Course Bearing Pointer SET to desired course 3 Heading Selector Knob SET BUG to provide desired intercept angle 4 NAV Mode Selector Button PRESS Note NAV ARM annunciated Rev 1 18 KAP 140 AUTOPILOT SYSTEM Apr 02 Single Axis Operation 5 If the Course Deviation Bar is greater than 2 to 3 dots the air craft 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 If the D Bar is less than 2 to 3 dots the HDG mode or ROL if HDG is not selected will disen gage upon selecting NAV mode the NAV annunciator will illumi nate and the capture track sequence will automatically begin Note Intercept angles greater than 45 can result in course overshoot when close to the station Therefore intercept angles greater than 45 are not recommended Rev 1 Apr 02 KAP 140 AUTOPILOT SYSTEM 19 Single Axis Operation Approach APR Mode Using a DG from HD
52. gle axis KAP 140 Display 1 AUTOPILOT ENGAGE DISEN GAGE AP BUTTON When pushed engages autopilot if all logic conditions are met The autopilot will engage in the basic roll ROL mode which functions as a wing lev eler When pressed again will disen gage the autopilot For software ver sion 03 01 and later the AP button must be pressed and held for 0 25 seconds to engage the autopilot 2 ROLL AXIS R ANNUNCIATION When illuminated indicates failure of the roll axis and will disengage the autopilot and not allow engagement 3 HEADING HDG MODE SELEC TOR BUTTON When pushed will select the Heading mode which commands the airplane to turn to Rev 2 May 02 and maintain the heading selected by the heading bug on either the DG or HSI A new heading may be selected at any time and will result in the airplane turning to the new head ing Button can also be used to tog gle between HDG and ROL modes This button will engage the autopilot in units with software prior to soft ware version 03 01 4 NAVIGATION NAV MODE SELECTOR BUTTON When pushed will arm the navigation mode The mode provides auto matic 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 KAP 140 AUTOPILOT SYSTEM 9 Single Axis Operation 5 APPROACH APR MODE SELECTOR BUTTON When pushed will arm the Approach mode This mode pr
53. he TO FROM indicator the selected course pointer on changes to TO 098 and fly to keep the devi ation bar centered Rev 0 122 KAP 140 AUTOPILOT SYSTEM Jun 98 KCS 55A Compass System TERMINAL CONTROL AREA i MSTRCTIONS TO VFR FLIGH ANO LANDING 9000 FEET SEE ST LOUIS TERMINAL AREA CHART OR PPROPRIATE PUBLICATIONS FOR OETAILS ST LOUIS Sn 117 4 Chan 121 122 6 122 45 122 1R ST LOUIS STL 7 FORISTELL FTZ z 2 110 8 ST LOUIS PU ON 4 7 OB OW A EIS BENDIX ING 8 Airway Interception 3 Your clearance is V 12 to As you cross the Foristell Foristell then V 14 to the St VORTAC the deviation bar Louis STL VORTAC direct will align with the course Lambert Field Approaching arrow Now set the heading the FTZ station the heading bug to 062 and turn left to bug is on 100 as a reference follow V 14 to the STL VOR CIVIC i CVM FIDELITY CONTROL ZIONE EFFECTIVE 1200 040023 e Cc Mem o 544165 4 gt You are now established on V 14 flying to the STL VOR TAC Once again if you fly to keep the deviation bar cen tered correction for wind drift will automatically be accom for the V 12 course or as TAC plished heading command for the autopilot if used Select the M St Louis VORTAC on the NAV N id d sys j m aurs receiver and set the course 5 2 A un anda pointer on the STL 062 URE ment course d KAP 140 AUTOPILOT SYSTEM Jun 98 123 KCS 55A C
54. iaht deviations af fe CUI course dewater needle are reversed vou mustum nah iv center a dewaten of the index to me fer his needle reversing Takes mace because Voy are fw ing outbound on a front course the 45 intercept is 103 the aircraft will not the autopilot will initiate a 45 intercept to the turn until the front course is captured m In this case the aircraft will turn to Check the heading displayed on the DG against the magnetic compass and reset if necessary Rev 1 Rev 1 38 KAP 140 AUTOPILOT SYSTEM Apr 02 Apr 02 KAP 140 AUTOPILOT SYSTEM 39 Single Axis Operation Outbound On Front Course For Procedure Turn To LOC Approach Using HSI D C ELEC TURN COORDINATOR 2 MIN No PITCH INFORMATION _ 1 The aircraft is heading 270 with heading engaged To intercept and fly the LOC front course outbound set the front course on the HSI and depress the back course REV but ton The back course REV mode is selected to go outbound on the front course The capture point is now being computed based on closure rate 40 2 MIN NO PITCH INFORMATION a UC3 UJ LJ L3 2 When the computed capture point is reached HDG mode is cancelled and reverse localizer mode is automatically activated and a left turn outbound on the localizer is initiated by the autopilot Mote he em riaht deviations at The NS course heed e aperafe just as Dough voy were Dying a Wontcourse approach Rev 1 KAP 140
55. icant that the KAP 140 series autopilots have been designed from their inception to interface with the Silver Crown pack age of products Consider the advantage of having your avionics working together as an integrated system rather than as a group of components built by several manu factures Your new KAP 140 roll axis features include wing leveler heading select and VOR LOC intercept and track ing The KAP 140 can also be cou pled to GPS and RNAV receivers as well Roll rate information is derived from the turn coordinator Pitch axis features include vertical speed glideslope and altitude hold along with the optional altitude preselect Pitch information is derived from a pressure sensor and accelerometer The KAP 140 Autopilot System oper ates independent of the aircraft s artificial horizon Therefore the autopilot retains roll stabilization and all vertical modes in the event of vac uum system failure Rev 1 Apr 02 Introduction Internal monitors keep constant track of the KAP 140 s status and provide for automatic shutdown of the autopilot or trim system in the event of a malfunction In addition to relia bility the KAP 140 is designed to be easily maintained in the field Qualified Honeywell Service Centers are located around the world to pro vide assistance whenever neces sary To fully realize the capability of your new panel mount digital autopilot System you must understand the performance capabi
56. inated until 1000 ft from the selected alti tude Associated with the visual Rev 1 Apr 02 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 alti tude m oD v po Po To E E c C Altitude Preselect 1 ALTITUDE SELECT knob ROTATE until desired altitude is displayed ARM annunciation occurs automatically upon altitude selection when the autopilot is engaged rm oD v po Po To E E NL 2 Airplane ESTABLISH desired vertical speed to intercept the selected altitude m m I mo o mmu 3 Upon altitude capture ALT ARM will extinguish and ALT will be annunciated Note Altitude preselect captures are not recommended on non precision approaches to capture the MDA Glideslope coupling will preclude an altitude capture on an ILS m oD seat E KAP 140 AUTOPILOT SYSTEM 89 Rev 1 Apr 02 Voice Messaging The following standard voice mes sages will be annunciated as condi tions warrant 1 TRIM IN MOTION TRIM IN MOTION Pitch trim running for more than 5 seconds 2 CHECK PITCH TRIM An out of trim condition has existed for 15 seconds a Airplane Control Wheel GRASP FIRMLY press CWS and check for an out of pitch trim condition Manually retrim as required b CWS button RELEASE
57. int or destina tion 2 OBS Knob SELECT desired course 3 NAV Mode Selector Button PRESS Note NAV ARM annunci ated NOTE When NAV is selected the autopilot will flash HDG for 5 sec onds to remind the pilot to reset the HDG bug to the OBS course Check the heading displayed on the DG against the magnetic compass and reset if necessary Rev 1 Apr 02 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 annun ciator will go out and the selected course will be automatically cap tured and tracked If the D Bar is less than 2 to 3 dots the HDG mode will disengage upon select ing NAV mode the NAV annunci ator will illuminate and the capture track sequence will automatically begin Rev 1 Apr 02 KAP 140 AUTOPILOT SYSTEM 15 Single Axis Operation 16 D C ELEC TURN COORDINATOR gt Ld L R 2 MIN VA INFORMATION A O an Navigation NAV Mode Using a DG from ROL Mode All Angle Intercept In the navigation NAV mode the autopilot intercepts and tracks VOR RNAV and GPS courses To arm NAV mode with the KAP 140 currently in the ROL mode 1 Maneuver the aircraft to th
58. inuing the maneuver on page 74 APR 2 At the FAF ALT is depressed to activate vertical mode capture occurs The autopilot initiates a speed mode The desired descent rate is left turn to track the 058 GPS course obtained using the DH button Approach active is indicated on the GPS Remember speed needs fo be controlled with annunciator the fororis Rev 1 18 KAP 140 AUTOPILOT SYSTEM Apr 02 Dic ELEC TURN COORDINATOR 3 At the MDA the ALT button is depressed caus ing the autopilot to level off and maintain a con stant altitude At the MAP the pilot disengages the autopilot with the button on the control wheel A flashing AP annunciation is displayed and a distinctive tone will sound Rev 1 y TURN COORDINATOR E es A E Two Axis Operation Dy 2 MIN NOPITCH e INFORMATION 4 The pilot initiates the missed approach and sta bilizes the aircraft in the climb The heading bug is set to the missed approach heading of 090 By depressing the HDG button on the KAP 140 the autopilot engages into the head ing mode commencing a right turn to a head ing of 090 Note Press and hold the AP button for 0 25 seconds to engage the autopilot applicable only to software version 03 01 and later Apr 02 KAP 140 AUTOPILOT SYSTEM 19 Two Axis Operation Inbound on GPS Approach Using HSI o Description of GPS operation based on Bendix King GPS receiver Others may require different operation
59. layed will be flashing AP annunciation 5 sec onds at each autopilot disconnect accompanied by an aural tone for 2 seconds 14 AUTOPILOT ENGAGED AP ANNUNCIATION Illuminates whenever the autopilot is engaged Flashes during pilot initiated or auto matic disengagement Only applica ble for software versions 03 01 or later Rev 1 Apr 02 Two Axis Operation System Operating Modes The lateral modes HDG NAV APR and REV operate identically as described in the KAP 140 Single Axis Operating Modes section Please refer to that section for text descriptions of lateral mode opera tion KAP 140 AUTOPILOT SYSTEM 57 Two Axis Operation BENDIX KING KAP 140 Vertical Speed VS Mode The Vertical Speed VS mode allows variable vertical speed climbs and descents The ALT button tog gles between altitude hold and verti cal 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 If no other modes are selected the autopilot will operate in the ROL and vertical speed hold modes For software version 03 01 and later the AP button must be pressed and held for 0 25 seconds to engage the autopilot 2 UP or DN button Select desired climb or descent rate Each button stroke will increment the vertical speed commanded up or down by 100 ft min per button pres
60. lities and basic operational requirements of the sys tem This pilot s guide provides information to aid in this and is divided up into six sections The first section provides general familiariza tion of each autopilot system includ ing the associated panel mounted displays The second section describes the KAP 140 Single Axis Autopilot System The third section describes the KAP 140 Two Axis Autopilot System The fourth section describes the KAP 140 Two Axis Altitude Preselect Autopilot System The fifth section describes the optional KCS 55A slaved com pass system The Sixth section describes abnormal procedures KAP 140 AUTOPILOT SYSTEM 1 Introduction General Description KAP 140 Single Axis KAP 140 Two Axis Altitude Autopilot System Preselect Autopilot System The KAP 140 Single Axis system is The KAP 140 Two Axis system pro an entry level digital panel mount vides both lateral and vertical modes autopilot offering lateral modes only with altitude preselect with an electric trim option o omnu KAP 140 Two Axis Autopilot System The KAP 140 Two Axis system pro vides both lateral and vertical modes Tasos Rev 1 2 KAP 140 AUTOPILOT SYSTEM Apr 02 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
61. n set to 103 and the aircraft has made a left turn to this heading The GPS s Leg OBS mode switching is set to Leg mode and the OBS is set to 058 Select approach mode by depressing the APR button The HDG annunciation will flash for five sec onds then extinguish While the HDG annuncia tion is flashing move the heading bug to 058 Since the 45 intercept is 103 the aircraft will not turn until the course is captured Apr 02 KAP 140 AUTOPILOT SYSTEM 105 Two Axis Altitude Preselect Operations Outbound on GPS Approach Using HSI Description of GPS operation based on Bendix King GPS receiver Others may require different operation D C ELEC TURN COORDINATOR Ll m Ld A R 2 MIN INFORMATION e e um m 1 The aircraft is in APR mode approaching the 2 IAF Approach arm is indicated on the GPS annunciator 106 KAP 140 AUTOPILOT SYSTEM Dic ELEC TURN COORDINATO a IL ud v z Upon waypoint alerting at the IAF the course pointer is set to 238 the GPS s Leg OBS mode Switching is set to OBS mode The autopilot ini tiates a left turn to track the 238 GPS course Rev 1 Apr 02 Two Axis Altitude Preselect Operations 2MIN NO PITCH o 3 At the desired point heading mode is used to initiate the procedure turn During the procedure turn outbound the deviation bar shows that the aircraft is flying away from the GPS course at a 45 angle on a selected headi
62. nd to be fully deflected during a turn If the needle stays fully deflected left or right during level flight the free gyro mode can be used to center it as follows 116 KAP 140 AUTOPILOT SYSTEM SIE 10 MAN ccw cw KA 51B Slaving Meter Slave and Free Gyro Switch When the switch is in the AUTO position the system is in the slaved gyro mode When the switch is in the MAN position the system is in the free gyro mode Clockwise Adjustment When the system is in the free gyro mode holding the manual heading switch to the CW position will rotate the compass card to the right to elimi nate left compass card error Counterclockwise Adjustment When the system is in the free gyro mode holding the manual heading switch to the CCW position will rotate the compass card to the left to eliminate right compass card error The KA 51B Slaving Control and Compensator Unit is a small slaving accessory which can be used in installations where panel space is limited The KA 51B can be mounted either vertically or horizon tally Rev 3 Nov 05 KMT 112 Magnetic Slaving Transmitter This unit senses the direction of the earth s magnetic field and contin uously transmits this information through the slaving circuitry to the directional gyro which is automati cally corrected for precession or drift This sensor is mounted remotely usually in a wingtip to eliminate the possibility of magnetic in
63. ndicator is an optional part of the KAP 140 Autopilot System 24 2 Me 2 9 MAN cw KG 102A The panel mounted KI 525A HSI combines the display functions of both the standard Directional Gyro and the Course Deviation Indicator s VOR LOC Glideslope information to provide the pilot with a single pre sentation of the complete horizontal navigation situation This greatly simplifies course orientation inter ception and tracking while eliminat ing the need for scan coordination between two separate indicators KI 525A KMT 112 KCS 55A Compass System Rev 0 Jun 98 KAP 140 AUTOPILOT SYSTEM 113 KCS 55A Compass System KI 525A Indicator The KI 525A Pictorial Navigation Indicator is the panel dis play for the KCS 55A Compass System It replaces the standard Directional Gyro and Course Deviation Indicator CDI in the air craft s panel combining slaved NAV warningO Flag Heading O SelectO BugO o Dual O GlideslopeO Pointers Symbolic Aircraft VOR and LOC Deviation Bar Course Select Knob VOR LOCH Deviation Scale KI 525A Pictorial Navigation Indicator Description of Indicator and Display Functions Compass Card Responding to the input from the slaved directional gyro this card rotates within the dis play so that the aircraft heading is always at the top under the lubber line 114 KAP 140 AUTOPILOT SYSTEM Lubber Line heading and VOR LOC Glideslo
64. ng of 283 Rev 1 Dic ELEC TURN COORDINATOR lt a L R 2MIN Y NO PITCH J i 4 The heading bug has been set to 103 and the aircraft has made a left turn to this heading The GPS s Leg OBS mode switching is set to Leg mode and the course pointer is set to 058 Select approach mode by depressing the APR button Apr 02 KAP 140 AUTOPILOT SYSTEM 107 Two Axis Altitude Preselect Operations Inbound on GPS Approach Using DG o Description of GPS operation based on Bendix King GPS receiver Others may require different operation D C ELEC A Dc ELEC TURN COORDINATOR TURN COORDINATOR SS R 2 MIN 2 MIN NO PITCH NO PITCH INFORMATION INFORMATION 1 Continuing the maneuver on page 104 APR 2 At the FAF ALT is depressed to activate vertical mode capture occurs The autopilot initiates a speed mode The desired descent rate is left turn to track the 058 GPS course obtained using the DH button Approach active is indicated on the GPS Remember speed needs fv be controlled wih annunciator the forore Rev 1 108 KAP 140 AUTOPILOT SYSTEM Apr 02 Two Axis Altitude Preselect Operations Dic ELEC S Dc ELEC TURN COORDINATOR TURN COORDINATOR 34 p 5 L4 L4 L L Dy Ly 2MIN 2 MIN NO PITCH No PITCH Cy INFORMATION e INFORMATION 3 At the MDA the ALT button is depressed caus 4 The pilot initiates the missed approach and sta ing the autopilot to level of
65. ng the procedure turn outbound the deviation bar shows that the air craft is flying away from the localizer centerline at a 45 angle on a selected heading of 283 Rev 1 Two Axis Operation Now you have reset the heading bug to 103 and made a 180 turn to this heading The 103 heading will intercept the front course of 058 You must now select the approach mode by depressing the APR button on the KAP 140 Automatic capture of the localizer will occur Apr 02 KAP 140 AUTOPILOT SYSTEM 69 Two Axis Operation Front Course ILS Approach Using DG TURN COORDINATOR 2 MIN NO PITCH INFORMATION Continuing the maneuver on page 66 APR cou pling occurs HDG annunciation changes to APR and the glideslope mode is automatically armed The autopilot will capture the localizer and the CDI course index will center 70 KAP 140 AUTOPILOT SYSTEM D C ELEC TURN COORDINATOR i 2 MIN NO PITCH INFORMATION 7 a P E E EU The autopilot is following the localizer At the outer marker the glideslope deviation needle is at midscale Altitude hold is automatically disen gaged when the glideslope is captured The ALT annunciator extinguishes and GS is displayed The autopilot will make pitch and bank changes as necessary to maintain localizer and glides lope Rev 1 Apr 02 D C ELEC TURN COORDINATOR E L R 2MIN INFORMATION e LJ 3 At the middle marker the pilot diseng
66. ngaged and the aircraft maintains the reference altitude Apr 02 KAP 140 AUTOPILOT SYSTEM 61 Two Axis Operation GPS Capture Using DG Description of GPS operation based on Bendix King GPS receiver Others may require different operation P b c ELEC ev Dc ELEC Y TURN COORDINATOR TURN COORDINATOR Hu SS L4 L D L Dy 2 MIN 2 MIN NO PITCH NO PITCH Cy INFORMATION e INFORMATION oun amua 1 Continuing on heading 010 a GPS waypoint is 2 The HDG button is depressed to select ROL established A 30 intercept is desired mode which will allow an all angle intercept GPS data is selected for the CDI and the OBS is set to 040 The HAV button is depressed and HAV ARM is annunciated ROL will change to HDG and flash for five seconds ROL will then be redisplayed While the HDG annunciation is flashing move the heading bug to the desired course of 040 The aircraft will remain wings level until the capture point Rev 1 62 KAP 140 AUTOPILOT SYSTEM Apr 02 Two Axis Operation Dic ELEC TURN COORDINATOR F c E Im L3 L R 2 MIN 2 MIN NOPITCH INFORMATION 3 When the computed capture point is reached 4 The turn is complete and the autopilot is track the ROL annunciation changes to MAW and a ing the GPS course right turn is initiated by the autopilot Rev 1 Apr 02 KAP 140 AUTOPILOT SYSTEM 63 Two Axis Operation GPS Capture Using HSI Description of GPS operation based
67. ompass System HOLDING PATTERN 1 Approaching the STL VORTAC the con troller 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 Set your heading bug to the reciprocal or outbound heading of 244 for easy reference and begin your right turn holding pattern 3 Outbound you are using the heading bug as reference for 244 The 244 radial is off the right wing and parallel to your outbound course MAS Zo HY e x e gt 2 Halfway through the outbound turn the KI 525A display shows the deviation bar behind the symbolic aircraft You know therefore that you must eventually fly back to the radial in order to be on course during the inbound leg of the holding pattern Halfway through your turn to the inbound 064 course the KI 525A shows the sym bolic aircraft approaching the deviation bar at a right angle By keeping the top of the deviation bar on the lubber line you can complete your turn and roll out precisely on Course Mate For system Hmifalions refer ip vour Fight Mana Summe ment Rev 0 124 KAP 140 AUTOPILOT SYSTEM Jun 98 ILS APPROACH FRONT COURSE You are vectored from the holding pattern to the 13 DME arc The aircraft is turning with the heading bug set on 170 to inter cept the localizer You have already set the selected cou
68. omputed HOG mode is cancelled and reverse localizer mode is automatically activated and a left turn outbound on the localizer is initiated by the autopilot Mote Phe iliran deviations at Tie NS course heed e aperafe just as Dough voy were Dying a mFontcourse anpreach based on closure rate Rev 1 98 KAP 140 AUTOPILOT SYSTEM Apr 02 Dic ELEC TURN COORDINATOR m S nw oO u me At the desired point HDG mode is used to initi ate the procedure turn During the procedure turn outbound the deviation bar shows that the aircraft is flying away from the localizer center lne at a 45 angle on a selected heading of Rev 1 Two Axis Altitude Preselect Operations Now you have reset the heading bug to 103 and made a 180 turn to this heading The 103 heading will intercept the front course of 058 You must now select the approach mode by depressing the APR button on the KAP 140 Automatic capture of the localizer will occur Apr 02 KAP 140 AUTOPILOT SYSTEM 99 Two Axis Altitude Preselect Operations Front Course ILS Approach Using DG TURN COORDINATOR 2 MIN NO PITCH INFORMATION 1 Continuing the maneuver on page 96 APR cou pling occurs HDG annunciation changes to APR and the glideslope mode is automatically armed The autopilot will capture the localizer and the CDI course index will center 100 KAP 140 AUTOPILOT SYSTEM D C ELEC TURN COORDINATOR i 2 MIN NO PITCH INFORMATION
69. on Bendix King GPS receiver Others may require different operation D C ELEC TURN COORDINATOR TURN COORDINATOR um L4 R 2 MIN 2 MIN NO PITCH NO PITCH e INFORMATION INFORMATION p i a L3 C9 CJ CJ Cu E3 1 Continuing on heading 010 a GPS waypoint is 2 GPS data is selected for the HSI The course established A 30 intercept is desired pointer is set to 040 The HAV button is depressed and HAV ARM is annunciated Rev 1 64 KAP 140 AUTOPILOT SYSTEM Apr 02 Two Axis Operation D C ELEC D C ELEC TURN COORDINATOR TURN COORDINATOR a Rx L4 L hal 2MIN 2MIN No PITCH No PITCH e INFORMATION e INFORMATION um p oa EE E P E E n 3 When the computed capture point is reached 4 The turn is complete and the autopilot is track the HDG annunciation changes to HAV and a ing the GPS course right turn is initiated by the autopilot Rev 1 Apr 02 KAP 140 AUTOPILOT SYSTEM 65 Two Axis Operation Outbound On Front Course For Procedure Turn To ILS Approach Using DG OCT TURN COORDINATOR 2 MIN NO PITCH INFORMATION 1 The aircraft is heading 270 with heading and altitude hold engaged To intercept and fly the ILS front course outbound set the front course on the OBS and depress the reverse course REV button The HDG annunciation will flash for five seconds then extinguish While the HDG annunciation is flashing move the head ing bug to the front c
70. ontinuously will com mand a 500 ft min altitude change acquiring a new reference altitude upon button release Note Incremented altitude changes should be limited to 500 ft of change Rev 1 Apr 02 KAP 140 AUTOPILOT SYSTEM Two Axis Operation 59 Two Axis Operation Two Axis Operation OPERATIONS WITH THE KAP 140 Takeoff And Climb To Assigned Altitude N N f RD E O e 70 P KAN io pol p 080 0 e e o TURN COORDINATOR 1 The aircraft is well off the ground and estab 2 The heading bug on the DG or HSI is turned to 3 The autopilot is responding to the heading select 4 The autopilot has completed the turn and is lished at a safe climb rate The heading bug on the DG or HSI is turned to the desired heading of 080 runway heading By depressing the HDG button on the KAP 140 the autopilot engages into the heading and ver tical speed modes and maintains the selected heading of 080 and current rate of climb Note Press and hold the AP button for 0 25 seconds to engage the autopilot applicable only to software version 03 01 and later 60 the new desired heading of 010 and the aircraft begins to respond with an immediate left turn Rev 1 KAP 140 AUTOPILOT SYSTEM Apr 02 mode with a left bank The climb rate has been decreased using the DH button in preparation for level off Rev 1 now established on a 010 heading Desired altitude has been reached altitude hold ALT has been e
71. ourse 058 Since HDG was active upon selection of REW the autopilot will initiate a 45 intercept to the localizer In this case the aircraft will turn to 283 66 D C ELEC TURN COORDINATOR 2 MIN NO PITCH INFORMATION 2 When the computed capture point is reached auto intercept mode is cancelled and reverse localizer mode is automatically activated and a left turn outbound on the localizer is initiated by the autopilot Mote The em right deviations ot fe CUI course dewater needle are reversed vou mustum nah iv center a dewatien of he index to me fer his needle reversing fakes mace because Vou are fw ing outbound on a front course Rev 1 KAP 140 AUTOPILOT SYSTEM Apr 02 TURN COORDINATOR e E R 2 MIN No PITCH INFORMATION e 3 At the desired point HDG mode is used to initi ate the procedure turn Select HDG and set the heading bug to 283 During the procedure turn outbound the CDI course index goes off scale to the right The aircraft is flying away from the localizer centerline at a 45 angle on a selected heading of 283 Check the heading displayed on the DG against the magnetic compass and reset if necessary Rev 1 Two Axis Operation pa e TURN COORDINATOR Eum monn R 2 MIN INFORMATION e e 4 Now you have reset the heading bug to 103 and made a 180 turn to this heading This 103 heading will intercept the front course of 058
72. ovides auto matic 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 ROLL MODE DISPLAY Displays the active and armed roll modes ROL HDG NAV ARM NAV APR ARM APR REV ARM REV Also displayed will be flash ing AP annunciation 5 seconds at each autopilot disconnect accompa nied by an aural tone for 2 sec onds 8 AUTOPILOT ENGAGED AP ANNUNCIATION Illuminates whenever the autopilot is engaged Flashes during pilot initiated or auto matic disengagement Only applica ble for software versions 03 01 or later 10 KAP 140 AUTOPILOT SYSTEM Rev 1 Apr 02 Single Axis Operation This page intentionally left blank Rev 1 Apr 02 KAP 140 AUTOPILOT SYSTEM 11 Single Axis Operation System Operating Modes BENDIX KING KAP 140 Wing Leveler ROL Mode D C ELEC In the roll mode the autopilot maintains wings level flight TURN COORDINATOR 1 Engage autopilot Press AP n For software version 03 01 and later A the AP button must be pressed and L held for 0 25 seconds to engage the zT autopilot e INFORMATION e NOTE The KAP 140 engages into ROL mode as a default Re
73. pass System Optional KA51B Slaving Accessory ESRA AARNE SRA eO R E Control Manual WheelSteering Electrical Trim optional KAP 140 Two Axis System Diagram Rev 1 6 KAP 140 AUTOPILOT SYSTEM Apr 02 VOR LOC Baro RNAV Encoding Setting GPS Altimeter Deviation Glideslope Middle Static Deviation Marker Pressure EU Directional Gyro KI 204 or other Course Deviation Indicator not included KG102A Slaved DG Em KMT 112 KI 525A Pictorial peor T COE Flux Detector l l l l i l i I l L I i l Navigation Indicator i l i l l i l i l l l l i l i KCS 55A Slaved Compass System Optional KA 51B Control WheelSteering optional Introduction 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 KS 271C Roll Servo Autopilot Disconnect Trim Interrupt Manual Electrical Trim KAP 140 Two Axis Altitude Preselect System Diagram Rev 1 Apr 02 KAP 140 AUTOPILOT SYSTEM Introduction Power Application and Preflight Tests BENDIX KING KAP 140 KAP 140 Preflight Test Complete A preflight test is performed upon power application to the com puter This test is a sequence of internal checks that validate proper System operation prior to allowing autopilot
74. pe information into one compact dis play By providing a simple compre hensive visual presentation of the aircraft s heading and position in relation to a desired course the pilot s navigation workload is consid erably reduced CompassH Warning Flag Coursell SelectO Pointer To FromO Indicator GlideslopeO Deviation L1 Scale Heading O Select O Knob Compass Card Lubber Line A fixed white marker at the top of the display that indi cates aircraft magnetic heading on the compass card Symbolic Aircraft A fixed repre sentation of the actual aircraft This miniature aircraft always points toward the top of the display and the lubber line Rev 0 Jun 98 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 VOR RNAV and LOC Deviation This bar corresponds to the left right needle on standard course deviation indicators When the air craft is precisely on the VOR radial or Localizer course it forms the cen ter section of the selected course pointer and will be positioned under the symbolic aircraft When off course or approaching a new course it will move to on
75. ption by adjusting your head ing to keep the top of the deviation bar touching the lub ber line Rev 0 Jun 98 VER vot 347 KCS 55A Compass System 122 1R COLUMBIA MO UN ana 4 When the deviation bar is centered and aligned with the course arrow you are on course Notice that correction for wind drift in this case a 080 heading on a 088 course is completely auto matic as long as you keep the deviation bar centered JAMESTOWN About midway between Napoleon and Columbia CBI you switch to the CBI VOR and the TO FROM indi cator immediately swings to TO Also note the course arrow should be moved from 088 to 090 which is the V 12 inbound course to CBI KAP 140 AUTOPILOT SYSTEM 121 KCS 55A Compass System WLY 114 2 Chan 89 i ho COLUMBIA E a 1 mo 5 E EE T Tm Viertel mu 772 s L3 a 24 l art 8 Columbia Regional 889165 5 22 65 gt gt MBIA coup 4 JAMESTOWN A NY S N 4 Jefferson City Memi E 4000 220 2 2m Ps WA i gt gah Ca Ho Gorin BENDIX KING B 7 Near the Herman intersection you switch to Foristell VOR TAC and move the course arrow to 100 which is the V 12 inbound course to FTZ As you fly over the Columbia station the TO FROM indica tor changes to FROM Since the outbound course for V 12 from Columbia to Foristell FTZ is 098 you now set T
76. re Turn To ILS Approach Using DG OCT TURN COORDINATOR 2 MIN NO PITCH INFORMATION 1 The aircraft is heading 270 with heading and altitude hold engaged To intercept and fly the ILS front course outbound set the front course on the OBS and depress the reverse course REV button The HDG annunciation will flash for five seconds then extinguish While the HDG annunciation is flashing move the head ing bug to the front course 058 Since HDG was active upon selection of REV the autopilot will initiate a 45 intercept to the localizer sig nal In this case the aircraft will turn to 283 96 D C ELEC TURN COORDINATOR 2 MIN NO PITCH INFORMATION 2 When the computed capture point is reached auto intercept mode is cancelled and reverse localizer mode is automatically activated and a left turn outbound on the localizer is initiated by the autopilot Mote The dotrigat deviations ot fe CUI course dewater needle are reversed vou mustum riant iv center a dewaten of the index fp me fer This needle reversing fakes mace because Voy are fw ing outbound on a front course Rev 1 KAP 140 AUTOPILOT SYSTEM Apr 02 TURN COORDINATOR e E R 2 MIN No PITCH INFORMATION e s T ouo o mua 3 At the desired point HDG mode is used to initi ate the procedure turn Select HDG and set the heading bug to 283 During the procedure turn outbound the CDI course index goes off scale to the
77. rmal Circumstances If the Warning Flag HDG appears during operation the com pass card indications will be in error Power may be removed from the KG 102A Directional Gyro by pulling the appropriate circuit breaker The Selected Course VOR LOC Deviation Bar the NAV flag and the To From Indicator will remain in operation If the Navigation Warning Flag NAV appears during operation there are several possibilities 1 the NAV receiver is not turned on 2 the NAV receiver is improperly tuned 3 the ground VOR or LOC station is malfunctioning 4 the air craft is out of range of the selected ground station or 5 the aircraft NAV receiver has malfunctioned The compass card will continue to display the aircraft heading even if a usable NAV signal is not being received If the glideslope pointers remain out of view during a front course ILS approach wither the air craft glideslope receiver or the ground station glideslope transmitter is malfunctioning Glideslope is usu ally not available during a back course approach The VOR and LOC course display will continue to Rev 0 Jun 98 KCS 55A Compass System function normally even if a usable glideslope signal is not being received A continuous large deflection of the slaving meter or large discrepan cies between the magnetic compass and the KI 525A compass card may indicate a failure in the slaving sys tem If a slaving failure should occur the Slave
78. rse pointer on the inbound ILS course 130 and the KI 525A shows the localizer course is directly ahead The glideslope pointers came into view when the ILS frequency was tuned since a usable glideslope signal is being received SOR HOT Yow RR 865 2 amp o as ES z Re phage gett SN L2 7 amp Vg NS Hum 3 The KI 525A shows you that you have inter cepted the localizer course The glideslope pointers have started to center although the display indicates your aircraft is still below the glidepath at this point KCS 55A Compass System plished without overshooting or bracketing with the same technique you used in inter cepting an enroute course Simply keep the top of the deviation bar on the lubber line and coordinate your turn until the bar is centered with the course arrow Each dot on the LOC deviation scale represents 1 2 degree of deviation when tuned to an ILS frequency VI TT A NP 15s NE e bas You are now centered on the localizer and the glideslope Once again the KI 525A shows your aircraft is crabbed about 5 to the right to maintain the localizer course Mate Far system imitations refer i vour Fight Manat Supple ment Rev 0 Jun 98 KAP 140 AUTOPILOT SYSTEM 125 KCS 55A Compass System BACK COURSE APPROACH REV 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
79. s or at the rate of approxi mately 300 ft min per second if held continuously 58 KAP 140 AUTOPILOT SYSTEM To initiate a climb or descent from Altitude Hold ALT mode 1 ALT button Press Note ALT changes to VS and current vertical speed is displayed 2 UP or DN button Select desired climb or descent rate Each button stroke will increment the vertical speed commanded up or down by 100 ft min per button press or at the rate of approxi mately 300 ft min per second if held continuously Note When operating at or near the best rate of climb airspeed at climb power settings and using vertical speed hold it is easy to decelerate to an airspeed where continued decreases in airspeed will result in a reduced rate of climb Continued operation in vertical speed mode can result in a stall Rev 2 May 02 BENDIX KING KAP 140 au o C RO RE mo 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 selec tion 2 UP or DN button Select to change altitude Incremented but ton strokes will move the refer ence altitude by 20 feet per press or if held c
80. software prior to soft ware version 03 01 59 Two Axis Operation 5 NAVIGATION NAV MODE SELECTOR BUTTON When pushed will arm the navigation mode The mode provides auto matic 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 track ing is not desired 6 APPROACH APR MODE SELECTOR BUTTON When pushed will arm the Approach mode This mode provides auto matic beam capture and tracking of VOR GPS LOC and Glideslope GS on an ILS as selected for pre sentation on the HSI or CDI APR mode is recommended for instru ment approaches 7 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 and GS is disabled 8 ALTITUDE HOLD ALT MODE SELECT BUTTON When pushed will select the Altitude Hold mode This mode provides tracking of the reference altitude The reference altitude is the altitude at the moment the ALT button is pressed If the ALT button is pressed with an estab lished VS rate present there will be altitude overshoot approximately 56 KAP 140 AUTOPILOT SYSTEM 1096 of the VS rate with the air plane returned positively to the refer ence altitude This button will en
81. t engagement Note Press and hold the AP button for 0 25 seconds to engage the autopilot applicable only to software version 03 01 and later Apr 02 KAP 140 AUTOPILOT SYSTEM 81 Two Axis Operation This page intentionally left blank Rev 1 82 KAP 140 AUTOPILOT SYSTEM Apr 02 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 air craft BENDIX KING KAP 140 Two axis w Altitude PreSelect Flight Control Computer BENDIX KING KAP 140 2 3 4 5 Full KAP 140 Two Axis with Altitude Preselect Display 1 PITCH AXIS P ANNUNCIATOR When illuminated indicates failure of the pitch axis and will disengage the autopilot when the failure occurs and not allow engagement of the pitch axis 2 AUTOPILOT ENGAGE DISEN GAGE AP BUTTON When pushed engages autopilot if all logic conditions are met The autopilot will engage in the basic roll ROL mode which functions as a wing leveler and in the vertical speed VS hold mode The commanded vertical speed is be displayed in the upper right corner of autopilot display area for three seconds after engagement or if either the UP or DN button is pressed The captured VS will be the vertical speed present at the moment of AP button press When pressed again will disengage the autopilot For software version 03 01 Rev 2 May 02 15 14 and later the AP b
82. t turn to a heading of 090 and maintaining the rate of climb existing at engagement Note Press and hold the AP button for 0 25 seconds to engage the autopilot applicable only to software version 03 01 and later Apr 02 KAP 140 AUTOPILOT SYSTEM 103 Two Axis Altitude Preselect Operations Outbound on GPS Approach Using DG Description of GPS operation based on Bendix King GPS receiver Others may require different operation P D C ELEC D C ELEC TURN COORDINATOR TURN COORDINATOR uu L R 2 MIN 2 MIN NO PITCH NO PITCH Cy INFORMATION INFORMATION oun aoe 1 The aircraft is in APR mode approaching the 2 Upon waypoint alerting at the IAF the heading IAF Approach arm is indicated on the GPS bug is set to 238 the GPS s Leg OBS mode annunciator switching is set to OBS mode and the OBS is set to 238 The autopilot initiates a left turn to track the 238 GPS course Rev 1 104 KAP 140 AUTOPILOT SYSTEM Apr 02 D C ELEC TURN COORDINATOR 3 At the desired point heading mode is used to initiate the procedure turn During the procedure turn outbound the deviation bar shows that the aircraft is flying away from the GPS course at a 45 angle on a selected heading of 283 Check the heading displayed on the DG against the magnetic compass and reset if necessary Rev 1 Two Axis Altitude Preselect Operations p d 2 MIN NOPITCH INFORMATION 4 The heading bug has bee
83. terference KG 102A Directional Gyro The directional gyro provides gyro stabilization for the system and contains the slaving circuitry neces sary for operation of the system Power may be for either 14 or 28 volts DC This sensor is also remote mounted Operating Instructions 1 Until power is applied to the KCS 55A System and the direc tional gyro is up to speed a red flag labeled HDG will be visible in the upper right quadrant of the KI 525A Indicator In operation this warning flag will be visible whenever the power being sup plied is inadequate or the gyro is not up to speed 2 With the application of power to the KCS 55A System and gyro up to operating speed the red HDG flag should disappear from view Rev 0 Jun 98 KCS 55A Compass System KMT 112 Magnetic Slaving Transmitter KG 102A Directional Gyro 3 If the KCS 55A System is in the slaved gyro mode the compass card will automatically fast slave at the rate of 180 degrees per minute toward the aircraft s magnetic heading Immediately after apply ing power this compass card movement should be quite visi ble It will continue to fast slave until the proper magnetic heading is indicated after which it will slave at a constant rate of three degrees per minute to keep the system aligned with the earth s magnetic field KAP 140 AUTOPILOT SYSTEM 117 KCS 55A Compass System Under some conditions it is possi ble for the
84. the Course Deviation Bar is greater than 2 to 3 dots the air craft 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 disen gage the ARM annunciator will go out and the selected course will be automatically captured and tracked If the D Bar is less than 2 to 3 dots the HDG mode or ROL if HDG is not selected will disen gage upon selecting REV mode the REV annunciator will illumi nate and the capture track sequence will automatically begin Note Intercept angles greater than 45 can result in course overshoot when close to the station Therefore intercept angles greater than 45 are not recommended Rev 1 Apr 02 Single Axis Operation KAP 140 AUTOPILOT SYSTEM 31 Single Axis Operation Single Axis Operation OPERATIONS WITH THE KAP 140 Takeoff And Climb To Assigned Altitude D go oaog w 1 The aircraft is well off the ground and estab 2 The heading bug on the DG or HSI is turned to 3 The autopilot is responding to the heading select 4 The autopilot has completed the turn and is lished at a desired climb rate the new desired heading of 010 and the aircraft mode with a left bank now established on a 010 heading The heading bug on the DG or HSI is turned to begins to respond with an immediate left turn the desired heading of 080 runway heading By depressing the HDG button on the KAP 140 the au
85. the D Bar is less than 2 to 3 dots the ROL mode will disengage upon select ing APR mode the APR annunci ator will illuminate and the capture track sequence will automatically begin Note Intercept angles greater than 45 can result in course overshoot when close to the station Therefore intercept angles greater than 45 are not recommended Rev 1 Single Axis Operation Apr 02 KAP 140 AUTOPILOT SYSTEM 23 Single Axis Operation BENDIX KING KAP 140 Approach APR Mode Using an HSI D C ELEC The Approach APR mode allows the autopilot to intercept and URN COORDINATOR track LOC VOR RNAV and GPS courses tr To arm APR mode with the EN KAP 140 currently in the HDG mode NO PITCH INFORMATION 1 Select the desired frequency for LOC VOR or RNAV For GPS verify the desired approach 2 Course Bearing Pointer SET to desired course 3 Heading Selector Knob SET BUG to provide desired intercept angle 4 APR Mode Selector Button PRESS Note APR ARM annun ciated Rev 1 24 KAP 140 AUTOPILOT SYSTEM Apr 02 Single Axis Operation 5 If the Course Deviation Bar is greater than 2 to 3 dots the air craft 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 disen gage the ARM annunciator will go out and the selected course will be automatically captured and tracked If the D
86. tical orientation of the aircraft with respect to the center of the glideslope beam When on glides lope the pointers will align with the center markers on the glideslope scale Glideslope Deviation Scale White dots on each side of the display which in conjunction with the glides lope pointers indicate either above below or on glideslope during an ILS approach KAP 140 AUTOPILOT SYSTEM 115 KCS 55A Compass System Compass Warning Flag A red flag labeled HDG becomes visible in the upper right quadrant of the dis play whenever the electrical power is inadequate or the directional gyro is not up to speed Compass failures can occur which will not be annunci ated 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 Slaving Meter KA 51B This meter indicates any differ ence between the displayed heading and the magnetic heading Right or up deflection indicates a clockwise error of the compass card Left or down deflection indicates a counter clockwise error of the compass card Whenever the aircraft is in a turn and the card rotates it is normal for this meter to show a full deflection to one side or another NOTE During level flight it is normal for the meter needle to continuously move from side to side a
87. topilot engages into the heading mode and maintains the selected heading of 080 Note Press and hold the AP button for 0 2 Mote The autopilot controls only the rot axis The PILOT must maintain control of seconds to engage the autopilot applicable only to software version 03 01 and later the bitch and vaw axis Rev 1 Rev 1 32 KAP 140 AUTOPILOT SYSTEM Apr 02 Apr 02 KAP 140 AUTOPILOT SYSTEM 33 Single Axis Operation GPS Capture Using DG Description of GPS operation based on Bendix King GPS receiver Others may require different operation p c ELEC Dic ELEC TURN COORDINATOR TURN COORDINATOR SS SS L4 L R i 2 MIN 2 MIN NO PITCH NO PITCH e INFORMATION INFORMATION go U3 UJ CJ w 1 Continuing on heading 010 a GPS waypoint is 2 The HDG button is depressed to select ROL established A 30 intercept is desired mode which will allow an all angle intercept GPS data is selected for the CDI and the OBS is set to 040 The HAV button is depressed and HAV ARM is annunciated ROL will change to HDG and flash for five seconds ROL will then be redisplayed While the HDG annunciation is flashing move the heading bug to the desired course of 040 The aircraft will remain wings level until the capture point Rev 1 34 KAP 140 AUTOPILOT SYSTEM Apr 02 Single Axis Operation uU pese TURN COORDINATOR TURN COORDINATOR ae Rm a Ld R L R 2MIN 2 MIN INFORMATION
88. tude hold refer ence to the actual airplane altitude upon button release Note that the altitude hold reference is not displayed The display will continue to show the altitude alerter reference 10 ROTARY KNOBS Used to set the altitude alerter reference altitude or may be used immediately after pressing the BARO button to adjust the autopilot baro setting to match that of the airplane s altimeter when manual adjustment is required In some installations the baro setting is automatically synced to that of the altimeter 11 BARO SET BARO BUTTON When pushed and released will change the display from the altitude alerter selected altitude to the baro setting display either IN HG or HPA for 3 seconds If pushed and held for 2 seconds will change the baro set ting display from IN HG to HPA or Rev 1 Apr 02 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 correc tion is not available 12 ALTITUDE ARM ARM BUT TON When pushed will toggle alti tude arming on or off When ALT ARM is annunciated the autopilot will capture the altitude alerter dis played altitude provided the aircraft is climbing or descending in VS to the displayed altitude When the autopilot is engaged ALT arming is automatic upon altitude alerter alti tude selection via the rotary knobs Note that the alert
89. utton must be pressed and held for 0 25 seconds to engage the autopilot 3 ROLL AXIS R ANNUNCIATOR When illuminated indicates failure of the roll axis and will disengage the autopilot and not allow engagement 4 HEADING HDG MODE SELEC TOR BUTTON When pushed will arm the Heading mode which com mands the airplane to turn to and maintain the heading selected by the heading bug on either the DG or HSI A new heading may be selected at any time and will result in the airplane turning to the new head ing Button can also be used to tog gle between HDG and ROL modes This button will engage the autopilot in units with software prior to soft ware version 03 01 KAP 140 AUTOPILOT SYSTEM 83 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 presen tation on the HSI or CDI NAV mode is recommended for enroute naviga tion tracking NAV mode may also be used for front course LOC track ing when GS tracking is not desired 6 APPROACH APR MODE SELECTOR BUTTON When pushed will arm the Approach mode This mode provides auto matic beam capture and tracking of VOR GPS LOC and Glideslope GS on an ILS as selected for pre sentation on the HSI or CDI APR mode is recommended for instru ment approaches 7 BACK COURSE APPROACH REV MODE SELECTOR
90. v 2 12 KAP 140 AUTOPILOT SYSTEM May 02 Single Axis Operation Heading Select HDG Mode D C ELEC In the heading mode the autopilot will fly a selected heading The following steps should be taken TUR COORDINATOR to operate in the heading mode 1 Move the heading bug to the desired heading on the DG or EET HSI using the Heading Select knob INFORMATION 2 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 3 Depress the HDG button on the KAP 140 to engage the heading select mode The autopilot will turn the aircraft in the shortest direction to intercept and fly the heading 4 f you move the heading bug again while the heading select mode is engaged the autopilot will immediately turn the aircraft in the direction of the newly selected head ing 5 Press HDG button again and the autopilot will return to the ROL mode May 02 KAP 140 AUTOPILOT SYSTEM 13 Single Axis Operation 14 D C ELEC TURN COORDINATOR 2 MIN 7A NO PITCH d INFORMATION e KAP 140 AUTOPILOT SYSTEM Navigation NAV Mode Using a DG from HDG Mode 45 Intercept In the navigation NAV mode the autopilot intercepts and tracks VOR RNAV and GPS courses 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 waypo
91. viation Bar is greater than 2 to 3 dots the autopilot will annunciate REV ARM when the computed capture point is reached the ARM annun ciator will go out and the selected course will be automatically cap tured and tracked If the D Bar is less than 2 to 3 dots the HDG mode will disengage upon select ing REV mode the REV annunci ator will illuminate and the capture track sequence will automatically begin Rev 1 Apr 02 KAP 140 AUTOPILOT SYSTEM 21 Single Axis Operation D C ELEC TURN COORDINATOR 2 MIN 7A NO PITCH d INFORMATION e Back Course REV Mode Using a DG from ROL Mode All Angle Intercept The Back Course REV mode allows the autopilot to intercept and track a localizer back course To arm REV mode with the KAP 140 currently in the ROL mode 1 Maneuver the aircraft to the desired intercept angle prior to selecting ROL mode 2 Select the desired frequency for LOC 3 OBS Knob SELECT front course inbound heading 4 REV Mode Selector Button PRESS Note REV ARM annunci ated NOTE When REV is selected the autopilot will flash HDG for 5 sec onds to remind the pilot to reset the HDG bug to the front course inbound heading Check the heading dis played on the DG against the mag netic compass and reset if neces Sary Rev 1 28 KAP 140 AUTOPILOT SYSTEM Apr 02 5 Heading Selector Knob ROTATE BUG to agree with the FRONT COURSE inbound head ing
92. wo Axis Altitude Preselect Operations Dic ELEC TURN COORDINATOR F inc E Im La L R 2 MIN 2 MIN NOPITCH INFORMATION 3 When the computed capture point is reached 4 The turn is complete and the autopilot is track the ROL annunciation changes to HAV and a ing the GPS course right turn is initiated by the autopilot Rev 1 Apr 02 KAP 140 AUTOPILOT SYSTEM 93 Two Axis Altitude Preselect Operations Two Axis Altitude Preselect Operations GPS Capture Using HSI Description of GPS operation based on Bendix King GPS receiver Others may require different operation Dic ELEC D C ELEC D C ELEC D C ELEC TURN COORDINATOR TURN COORDINATOR ae Lg t T TURN COORDINATOR hal 2MIN 2MIN 2MIN 2MIN No PITCH No PITCH INFORMATION e uM NO PITCH NO PITCH A INFORMATION INFORMATION _ 3 num p m m oa oun omua 1 Continuing on heading 010 a GPS waypoint is 2 GPS data is selected for the HSI The course 3 When the computed capture point is reached 4 The turn is complete and the autopilot is track established A 30 intercept is desired pointer is set to 040 The HAV button is the HDG annunciation changes to HAV and a ing the GPS course depressed and HAV ARM is annunciated right turn is initiated by the autopilot Rev 1 Rev 1 94 KAP 140 AUTOPILOT SYSTEM Apr 02 Apr 02 KAP 140 AUTOPILOT SYSTEM 95 Two Axis Altitude Preselect Operations Outbound On Front Course For Procedu

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