Pilot’s Guide KFC 500 Bendix/King® Automatic Flight Control System for the Model 430 006-08769-0000 June 15, 1999
WARNING Prior to export of this document, review for export license requirement is needed. COPYRIGHT NOTICE Copyright ©1996, 1999 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 the Manager, Technical Publications; Honeywell; One Technology Center; 23500 West 105th Street; Olathe, Kansas 66061. Telephone: (913) 712-0400.
Revision History Revision History and Instructions Manual KFC 500 Pilot’s Guide Revision 1, June 1999 Part Number 006-08769-0000 This revision consists of the folowing: Add text further describing the operation of the push-buttons, the push-button annunciators, and the EFIS annunciators to the following pages - 8, 9, 20, 23, 25, 26, 27, 29, 30, 31, 42, 44, 46, 47, 49, 51, 52, 53, 54, 55, 57, 58, 59, 61, 62, 63, 65, 66, 67, 69, 70, 71 Administrative changes to the following pages - Front Cover, Inside
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Table of Contents Introduction ................................................................................3 Normal Operation SCAS/Autopilot ....................................................................5 SCAS/Autopilot Block Diagram ............................................7 Basic SCAS/AP Operation...................................................8 SCAS/AP Remote Switches ................................................8 Force Trim/OFF .......................................................
Introduction Table of Contents Normal Operation (Continued) Indicated Airspeed Hold (IAS) .....................................29 Overspeed Protection..................................................30 Vertical Speed Hold (VS).............................................30 Flight Control System Components ...................................31 KSA 572 Trim Actuator................................................31 Force Trim and AP Trim ..............................................
Introduction Important: This Pilot’s Guide provides a general description of the various operational characteristics of the KFC 500 Flight Control System. However, operation of the system should not be attempted without first reviewing the applicable Transport Canada and/or Federal Aviation Administration Approved Rotorcraft Flight Manual for complete system familiarization and operating limitations.
Normal Operation Basic KFC 500 SCAS/Autopilot System Block Diagram This page intentionally left blank.
Normal Operation Normal Operation Basic SCAS/AP Operation AFCS GROUND TEST This momentary switch is used to initiate the SCAS/AP System preflight test, if desired, after the initial test that occurs at system power up. Preflight test must be run prior to attempting system engagement. This section provides the Normal Operating Procedures for the basic SCAS/AP version of the KFC 500 System.
Normal Operation Normal Operation is lost. If it is only a yaw trim axis failure the annunciator will extinguish if SCAS engaged. An Autotrim failure indication means that roll or pitch trim has failed and more attention will need to be given to see that the system is kept within the control authority of the main servo by using the FTR switch to keep the system working within its control range.
Normal Operation Normal Operation revert to SCAS. The system will return to AP (attitude hold) after the FTR switch is released. The system will hold the existing pitch attitude reference existing at the time of release and will return to roll level/heading hold. The pilot may momentarily fly the aircraft manually at any time. After release of the cyclic the autopilot will return to attitude hold (AP annunciated), and fly the aircraft back to the attitude existing at the time that the pilot intervened.
Normal Operation Normal Operation Activating Discrete or Continuous Lateral Command has the following effect upon the command reference for autopilot operation: SCAS/Autopilot Disconnect AFCS DISC Autopilot Lateral Command Values Discrete Command Roll Attitude System Response First Click=6°, Subsequent=1° per click Continuous Command Roll Attitude Constant Roll Rate Pitch Command Control Using the same cyclic beep switch as mentioned in the previous paragraph, the autopilot’s reference pitch attitu
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Normal Operation KFC 500 SCAS/Autopilot/Flight Director System Block Diagram This page intentionally left blank.
Normal Operation Normal Operation The following section provides an explanation of the normal operating procedures for the flight director functions of the KFC 500 SCAS/AP System when equipped with Flight Director. SCAS/AP operation is identical to that of the basic SCAS/AP System, described in the proceeding section, with the following exceptions.
Normal Operation Normal Operation push-button provides the engage function only. To disconnect Go Around select another pitch mode. PIC L R The Flight Director provides the basic modes - Roll Attitude level/Heading Hold and Pitch Attitude Hold. These default modes provide basic flight stability and serve as safety backups in the event that the flight director cancels an active mode due to loss of a required navigation signal or sensor failure.
Normal Operation Normal Operation Activating Discrete or Continuous Lateral Command has the following effect upon command values in flight director operations: Flight Director Vertical Command Values Flight Director Lateral Command Values Discrete Command Discrete Command System Response Roll Attitude Hold First Click=6°, Subsequent=1° per click Heading Select 1° Heading Bug novement per click Continuous Command Roll Attitude Hold Constant Roll Rate Heading Select 16° Heading Bug movement per
Normal Operation Normal Operation Flight Director Off Go Around KMS 540 Flight Director Mode Selection Heading Select (HDG) Depressing the HDG push-button on the mode select panel activates Heading Select mode. This mode will provide flight director commands to track the heading bug on the EHSI. The annunciator above the switch on the mode select panel illuminates and “HDG” is displayed, in green, on the EADI when the heading select mode is activated.
Normal Operation Normal Operation angles up to 25° unless a bank limit is selected. Bank limiting is allowed in this situation and can affect tracking performance. If improved Long Range NAV tracking is desired, set the bank limit to the default value (20°). for five seconds. This flash sequence will terminate upon reactivation of NAV or another lateral mode.
Normal Operation Normal Operation receiver, invalid selected course from EHSI). The flashing annunciation may be extinguished by pressing and releasing the APR push-button (pilot acknowledgment) on the mode select panel. If glideslope invalid occurs for approximately 30 seconds during glideslope arm the system will revert back to the previously engaged pitch mode. If glideslope invalid occurs for approximately 5 seconds during the capture or track phase the system will revert to pitch attitude hold.
Normal Operation Normal Operation Indicated Airspeed Hold ☛ IAS The lamp above the IAS push-button illuminates when the airspeed hold mode is activated by depressing the IAS push-button on the mode select panel. Engaging the Indicated Airspeed Hold mode causes the flight director to command pitch attitudes to maintain the indicated airspeed current upon selection. The airspeed displayed on the pilot’s or copilot’s airspeed indicator may not exactly agree with the value being used by the AFCS.
Normal Operation Normal Operation Flight Control System Components (SCAS, Autopilot, and Flight Director) ready to allow the autopilot to take KSA 572 Trim Actuator over, the force trim switch may be pushed and the cyclic and antitorque pedals (if applicable) positioned as desired or release the stick and pedals and allow the autopilot to return to its original reference. At activation of the FTR switch, the cyclic and the pedals the spring cartridge detent switches will release.
Normal Operation Normal Operation in the vicinity of the Flux Valve. The switch allows the pilot to select either Free or Slaved Magnetic Heading mode. The slew switch is also utilized for manually correcting heading information during flight operations at higher latitudes. KAD 480 Air Data System KAV 485 Altitude/Vertical Speed Indicator The KAD 480 Digital Air Data System is comprised of the KDC 481T Central Air Data Computer, the KAV 485 Altimeter/Vertical Speed Indicator, and a temperature probe.
Normal Operation Normal Operation KAV 485 Altitude/Vertical Speed Indicator The KAV 485 Altitude/ Vertical Speed Indicator provides centralized display and control of some of the KFC 500’s most commonly used altitude and vertical speed functions. Display features include an electrically driven altimeter and instantaneous vertical speed indicator (IVSI); altitude and vertical speed preselect; barometric correction; and an altitude alerter.
Normal Operation Vertical Speed Engage Pushbutton - Pressing the vertical speed engage push-button (ENG) causes the flight director to command the aircraft to climb or descend at the rate indicated by the vertical speed bug on the IVSI. KFC 500 SCAS/Autopilot Note: If the VS bug is in view when VS is engaged, the preselected VS will be commanded. If the bug is not in view when VS is engaged, the helicopter’s current VS will be maintained and the bug will come into view synchronized with the VS pointer.
Emergency Procedures/Limitations Important: This Pilot’s Guide provides a general description of the various operational characteristics of the KFC 500 Flight Control System. However, operation of the system should not be attempted without first reviewing the applicable Transpor t Canada and/or Federal Avaition Administration Approved Rotorcraft Flight Manual for complete system familiarization, Emergency Procedures and Operating Limitations.
Preflight Procedures Preflight Procedures Caution: The Autopilot (AP) moves the controls during preflight test on the ground or in the air, and the crew should be prepared for control/main and/or tail rotor movement. is then followed by SCAS and AP (yellow) on for minimum of 3 seconds followed by AFCS PIT, AFCS ROL and AFCS YAW (yellow) on for minimum of 3 seconds.
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Operational Examples Attitude Hold 2. Depress Flight Director push button on the mode select panel. Attitude Hold Operation maintains the helicopter’s reference attitude (not altitude). ☛ Alternatively: FD Flight Director command bars come into view with the reference pitch attitude commanded. Roll attitude is commanded to horizon level (roll level/heading hold). 1. Establish the desired pitch and roll attitude. 2. Depress the “AP” push button on the mode select panel. OR 3.
Operational Examples Flight Director Off Heading Select Flight Director Off causes the flight director to declutter and the autopilot to revert to Attitude Hold. 1. Position the Heading Bug flight director. FD OFF 1. Depress the FD OFF switch on the cyclic. 000 2. All flight director modes deactivate and the command bars are removed from view. 30 3 W 24 S 21 CRS 15 Force Trim Release 117.95 12 1 N 1 2 .
Operational Examples Navigation Coupling Yaw Force Trim Release 1. To reposition the pedals when the yaw axis is engaged, press and hold the Yaw Force Trim Release switch. The yaw magnetic brake will disengage, allowing free pedal movement. Autopilot operation in the pitch and roll axes will not be disturbed (SCAS is annunciated).
Operational Examples Go Around Mode AP LOC GS 20 20 10 10 200 RA 200DH AP LOC GA BL25 GS 20 20 10 10 200 RA 200DH G S G S 10 10 20 20 000 1 2 . 6 NM L O C 1 W 3 15 21 CRS 359 G S 12 HDG 000 N 117.95 E G S 12 24 33 1 2 . 6 NM 30 30 3 E S 21 CRS 359 LOC 000 117.95 6 1 20 6 L O C N 20 W 33 10 24 3. After reaching a safe altitude select another pitch mode if desired. LOC 10 S 2.
Operational Examples Take Off and Climb The following examples describe possible applications of the KFC 500 Flight Control System, other applications may be available. Consult the Rotorcraft Flight Manual for specific operating instructions and limitations. 1. Prior to takeoff, press the FD switch on the mode selector. Select the assigned altitude on the altitude select portion of the altimeter/vertical speed indicator. The altitude selector should automatically arm when the new atitude value is selected.
Operational Examples F HDG VS 500 M BL25 ALT GS 20 0 RA 125DH AP HDG 10 10 10 20 20 LOC 070 10 10 20 20 30 W 24 N 33 21 006-08769-0000 CRS HDG 090 006-08769-0000 2 . 6 NM 117.95 3 N 21 30 33 H1 12 24 HDG LOC E 1 010 58 10 125DH 6 W June 15, 1999 V O R S CRS 10 010 E 090 20 2 . 6 NM 15 1 20 117.95 12 V O R 6 3 H1 RA ALT GS 20 10 3000 FT BL25 S AP 4.
Operational Examples Procedure Turn to an ILS Approach 8° 05 N 1. With heading and altitude hold engaged, the aircraft is flying 270° to intercept the localizer outbound. The localizer front course (inbound) of 58° is selected with the EHSI course knob. The display system automatically determines Back Course from the course selection and aircraft heading. Depress the APR push button for flight director commands to capture and track the localizer outbound. 2 270° 2.
Operational Examples During the procedure turn outbound, the deviation bar shows pictorially that the aircraft is flying away from the localizer centerline at a 45° angle. Note: When activating approach arm, it is important that the aircraft be relatively close to and not making any turns away from the localizer. Side lobes or false signals are often present from the localizer transmitter. These false signals may cause the autopilot to approach couple prior to reaching the actual localizer signal. 4.
Operational Examples ILS Approach 8° 05 N 2 1. The autopilot is following the flight director commands which maintain localizer centerline tracking. At the outer marker the glideslope pointers are approximately at midpoint. At the glideslope capture point, glideslope automatically transitions from arm (GS in white) to coupled (GS in green) and altitude hold or other vertical mode is disengaged. The point of glideslope capture is based on the glideslope deviation and the rate of closure to the beam.
Operational Examples 2. At decision height decide to complete the landing. The AFCS will track the localizer and glideslope down to 100 foot radar altitude where the system will transition to autolevel. The system will hold 50 foot radar altitude until disconnected. A missed approach may be initiated by pressing the Go Around button as collective is added. The Go Around button is located on the collective switch box.
Operational Examples 1. In heading select and the desired pitch mode with the localizer frequencey selected as the active navigation receiver, the aircraft is flying 45° to intercept the localizer. The localizer front course of 090° is selected with the EHSI course knob. Remember that the course pointer is always selected to the inbound heading for the localizer front course to obtain correct “fly to” indications on the EHSI.
Operational Examples 4. At the point specified to begin the procedure turn inbound, select 315° with the heading bug for a 180° turn toward the localizer. The deviation bar shows pictorally the course you are to intercept as well as the angle of intercept. Depress the APR push button to arm the back course approach mode. Note that the left/right deviations of the course deviation bar give “fly to” indications. Automatic capture will occur to direct the aircraft on the localizer.
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Performance Specifications Mode Attitude Hold Heading Hold Parameter KFC 500 Value Pitch Command Profile Pitch Hold Accuracy Roll Angle Limit Roll Command Rate Limit Roll Hold Accuracy 0.1G or 2 Deg/Sec ± .
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Honeywell International Inc. One Technology Center 23500 W 105th Street Olathe, Kansas 66061 FAX 913-791-1302 Telephone: (913) 712-0400 Copyright ©1996, 1999 Honeywell International Inc. All rights reserved. Rev.
