Pilot’s Guide KFC 500 Bendix/King® Dual Automatic Flight Control System for the Model 430 006-18081-0000 June 1999
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Revision History Revision History and Instructions Manual KFC 500 Pilot’s Guide Revision 1, June 1999 Part Number 006-18081-0000 This revision consists of the folowing: Add text further describing the operation of the push-buttons, the push-button annunciators, and the EADI annunciators to the following pages - 20, 23, 25, 26, 27, 30, 31, 37, 46, 47, 50, 51, 53, 56, 57, 59, 60, 61, 63, 64, 65, 67, 68, 69, 71, 72, 73 Administrative changes to the following pages - Front Cover, Inside of Front Cover, 1,
Revision History June 15, 1999 R-2 006-08769-0000
Table of Contents Introduction ................................................................................3 Normal Operation SCAS/Autopilot ....................................................................5 SCAS/Autopilot Block Diagram ............................................7 Basic Dual SCAS/AP Operation ..........................................8 SCAS/AP Remote Switches ................................................8 Force Trim 1/OFF ........................................................
Introduction Table of Contents Normal Operation (Continued) Autolevel Mode............................................................32 Altitude Select (ALT SEL)............................................32 Altitude Hold (ALT) ......................................................33 Indicated Airspeed Hold (IAS) .....................................34 Overspeed Protection..................................................34 Vertical Speed Hold (VS).............................................
Introduction tained diagnostic tests assist troubleshooting done by maintenance personnel at Honeywell factory approved service centers. The BuiltIn-Test functions enable a technician to trace faults. Qualified Honeywell service centers around the world are ready to provide assistance whenever necessary. available. When the KFC 500 decouples a SCAS/autopilot axis it both engages the affected servo brake and shuts off motor drive power, providing dual layers of protection against servo over-control.
Normal Operation Basic Dual KFC 500 SCAS/Autopilot System Block Diagram This page intentionally left blank.
Normal Operation Normal Operation This section provides the Normal Operating Procedures for the basic dual SCAS/AP version of the KFC 500 System. may be selected to continue the flight with basic AP and SCAS modes available. Any modes engaged when AP Select switch is toggled will be canceled and desired modes on newly selected system must be reengaged.
Normal Operation Normal Operation TEST/BRT/DIM (AFCS LAMP TEST) TEST B R T DIM Moving the TEST/BRT/DIM Switch, located on the overhead panel below the Emergency Bus 1 Breakers, to the test position will invoke an AFCS test function that will turn on the annunciators in the KMS 541 Mode Select Panel. These annunciations shall remain on as long as the switch is held in test position up to a maximum of 15 seconds.
Normal Operation Normal Operation level attitude and maintain the heading at the time the aircraft rolls level. is stabilizing the helicopter against outside disturbances and thereby is augmenting the pilot effort. The SCAS mode is designed so that helicopter attitude changes caused by pilot control inputs are not significantly counteracted by the stability augmentation system. Only helicopter motions caused by outside disturbances are counteracted.
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 If within ± 6° of level flight: First Click=6°, Subsequent=1° per click If greater than ± 6° of level flight: Each click=1° per click FTR Continuous Command Roll Attitude Roll Rate of 7° per second Pitch Command Control Using
Normal Operation Yaw Force Trim Release YAW FORCE TRIM RELEASE KFC 500 Flight Director A collective mounted Yaw ForceTrim Release switch (Yaw FTR) is provided for the primary system only (Force Trim power # 1). If the Force Trim System # 1 is on and primary system selected, depressing this switch releases the yaw clutch (AFCS yaw axis will revert to SCAS if engaged), allowing free anti-torque pedal movement. The AFCS will annunciate SCAS under this condition until the Yaw FTR switch is released.
Normal Operation KFC 500 Dual SCAS/Autopilot/Single 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 dual KFC 500 SCAS/AP System when equipped with Flight Director. The Flight Director functions are only available when the primary (#1) system is selected. If Flight Director modes are engaged when secondary system is selected they will be canceled.
Normal Operation Normal Operation tive mounted push-button provides the engage function only. To disconnect Go Around select another pitch mode. 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 existing roll attitude if greater than 6°. AFCS DISC Roll attitudes of less than six degrees of bank will cause the Flight Director to FD OFF revert to commands for roll-level flight with heading hold. When heading select (HDG) mode is engaged, the heading bug on the EHSI may be re-positioned to a new heading using the CBT switch. CBT Moving the CBT switch to the left will slew the heading bug counterclockwise FTR while movement to the right will slew the bug clockwise.
Normal Operation Normal Operation Autolevel, HDG select, NAV or APR modes including GS. Upon release of the FTR switch, the flight director will provide commands to return to or maintain the steering required for these modes, while FTR is held pressed the commands displayed will be synchronized to the helicopter’s reference.
Normal Operation Normal Operation Autopilot/Flight Director Mode Annunciation KMS 540 Flight Director Mode Selection Heading Select (HDG) 2 3 4 5 AP NAV HDG 120 KT 1 6 IAS BL25 7 ALT GS 20 FD 1. Bank Angle Limit 2.Autopilot Engaged Annunciator 3. Armed Lateral Mode 4. Active Lateral Mode 8 7 20 5. Command Reference Value 6. Active Vertical Mode 7. Armed Vertical Mode 8. Flight Director Flag Depressing the HDG push-button on the mode select panel activates Heading Select mode.
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°). vation of NAV or another lateral mode.
Normal Operation Normal Operation tion 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. played in the KAV 485’s selected altitude window.
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 KSM 575 Linear Actuator Assemblies Flight Control System Components (SCAS, Autopilot, and Flight Director) pitch and roll axes will remain in AP mode (SCAS annunciated on Mode Select Panel and on discrete annunciator). When the cyclic is released back to the detent postion, the AFCS will automatically return the pitch and roll attitudes to their original values. The pilot or copilot may manually fly the aircraft at any time using this method (Pilot Fly-Through Mode).
Normal Operation Normal Operation mation to the EFIS and each Flight Computer.The Free/Slave switch allows the pilot to select either Free or Slaved Magnetic Heading mode. The slew switch is utilized for manually correcting heading information during flight operations at higher latitudes.
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 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 KFC 500 Important: This Pilot’s Guide provides a general description of the various operational characteristics of the dual 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 crew should be prepared for control / main rotor and/or tail rotor movement. 2. Activate SCAS & AP PWR 1 and SCAS & AP PWR 2 switches (OFF extinguished on each switch). SCAS & AP PWR 1 Caution: Operation of the Autopilot (AP) on the ground may cause undesired main rotor or tail rotor control/movement.
Preflight Procedures 481T will set the Altitude Select display at 28,000 ft. and will set the displayed aircraft altitude to 26,800 ft. The aircraft’s displayed altitude will then ramp up to the selected altitude at a 3500 ft. per minute rate of climb. system may still be displayed if that axis has failed preflight test. Autopilot/SCAS engagement is allowed using axis/axes that passed test and are valid.
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). Upon release of the switch, the yaw magnetic brake will re-engage, and the autopilot will command ball centered. Select the desired navigation source on the EHSI. 2.
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 CRS HDG 090 006-18081-0000 117.95 W 24 N 33 21 006-18081-0000 1 2 . 6 NM 3 N 21 30 33 H 12 24 HDG LOC E 1 010 60 10 125DH 6 W June 15, 1999 V O R S CRS 10 010 E 090 20 117.95 15 1 20 1 2 . 6 NM 12 V O R 6 3 H 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 West 105th Street Olathe, Kansas 66061 FAX 913-712-1302 Telephone: (913) 782-0400 ©1998, 1999 Honeywell International Inc. 006-18081-0000 Rev.
