Pilot’s Guide KFC 500 Bendix/King® Flight Control System Honeywell International Inc. One Technology Center 23500 W. 105th Street Olathe, Kansas 66061 FAX 913-791-1302 Telephone: (913) 712-0400 Copyright ©1993 Honeywell International Inc. All rights reserved. 006-08750-0000 Rev.
Introduction The KFC 500 Automatic Flight Control System combines complete autopilot and flight director computation functions in a single computer. Its digital flight computer and integrated architecture enable the KFC 500 to determine helicopter control requirements sooner, and to execute them with greater smoothness and accuracy than previous autopilot systems.
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 FAA Approved Rotorcraft Flight Manual Supplement for complete system familiarization and operating limitations.
Table of Contents Introduction............................................................................................1 System Components .............................................................................5 System Description Normal Flight Control Operations KMS 540 Flight Director Mode Select Panel ....................................8 Basic Flight Director Mode ...............................................................8 Pitch Attitude Hold/Roll Attitude/Heading Hold.....................
DG SEL 1-2 ....................................................................................23 DME HOLD ....................................................................................23 VG FAST ERECT ...........................................................................23 Cyclic Grip Switch Assembly ..........................................................24 Collective Switch Assembly............................................................25 Basic EFS 40 Description ED 461 EFIS Display....
KFC 500 SYSTEM BLOCK DIAGRAM FOUR TUBE EFS 40 SYSTEM ED 462 ı AZ GS 500 RA ED 462 KAV 485 ı 1 AZ GS 500 RA 0 9 20 10 S N 10 10 20 20 10 KLN 90/90A 3 DH 200 CRSR NAV FPL MODE TRIP 33 GPS ı KLN 90 CALC STAT SETUP OTHER EMP =TOP |PRESENT POS dddddid‹ddd| DIS 89.4nm|BUM 300^FR GS 180kt| 37.4NM ETE :29| N 38^01.4' BRG 026^| W 95^32.
6
KFC 500 Normal Operation 7
Normal Operation KMS 540 Flight Director Mode Select Panel HDG NAV ALT VS AP SCAS APR a new altitude in Altitude Select, does not affect active tracking modes such as Heading or Vertical Speed Hold. It is often useful to engage a separate mode to provide flight guidance to the capture point for a course or altitude selected in an Arm mode. The Flight Control System will transition automatically to capture the armed mode, cancelling the previous selection.
Hold and Roll Attitude/Heading Hold automatically engage unless other tracking modes are selected. Pitch Attitude Hold and Roll Attitude/Heading Hold are annunciated on the EADI as PIT and ROL, respectively. the KSG 305 Compass System's Directional Gyro provides heading informantion to the Flight Director/Autopilot. Selecting any horizontal or vertical tracking mode cancels Roll Attitude Hold or Pitch Attitude Hold, respectively.
attitude. Roll attitudes of less than six degrees of bank will cause the Flight Director to revert to commands for roll-level flight with heading hold.
Vertical Command has the effect upon command values in flight director operations shown in the preceding table. ment. The Force Trim System must be “ON” for the AFCS to operate. Navigation Standby NAV Standby Force Trim Release (FTR) FTR When the Flight Director is active, the Force Trim Release switch allows the crew to synchronize flight director commands in pitch and roll to the actual helicopter position.
Yaw Trim Yaw Force Trim Release Yaw Force Trim Release Yaw Trim A Collective mounted Yaw Trim Switch is provided. Holding the switch to the right or left moves the Yaw Axis in the corresponding direction at a constant rate. Yaw Damper must be operational and active for Yaw Trim to function. A Collective mounted Yaw Force Trim Release is provided. Depressing this switch releases the Yaw brake, allowing free pedal movement when the autopilot or Yaw Damper is engaged.
KMS 540 Lateral Mode Selection HDG (heading select) Heading Select Bug 1 Depressing the HDG pushbutton on the mode select panel activates Heading Select mode. The Heading mode will provide flight director commands to track the heading bug on the EHSI. The heading lamp on the mode select panel illuminates and “HDG” is displayed on the EADI when the heading select mode is activated. Activating Heading Select cancels any other lateral tracking mode.
ation), or if the rate of closure with the new course is sufficiently high, the flight director initiates the NAV Capture sequence immediately. Selected Course Course Pointer 1 TST 7.5 NM 140 KT 090 1 2 6 3 N 33 30 S 24 1 H S I 15 V O R N A V REF E A R C 21 CRS 12 W localizer and then depress the APR pushbutton to activate Approach Mode when tracking inbound on the appropriate course.
engages Glideslope Arm (GS ARM), Capture and Track (GS) sequences during ILS front course approaches. The localizer must be captured in order for glideslope to ARM or couple. Glideslope coupling is inhibited during back course procedures. Any horizontal tracking mode may be employed during Approach Arm phases and will cancel automatically upon initiation of Approach Capture and Track.
KMS 540 Vertical Mode Selection deactivated to inhibit capture and tracking of the preselected altitude. If the value of selected altitude is changed while in altitude capture, the system reverts to pitch attitude hold mode. In the event of sustained invalid altitude, ALT SEL mode will deactivate. To disengage Altitude Select, press the SEL mode pushbutton on the KAV 485. Detailed operation of the KAV 485 is described on page 34.
of Attitude Hold engagement is used. Selecting Altitude Hold after the Altitude Select mode has been engaged cancels Altitude Select (white “ALT” on EADI). The flight director will command the aircraft to hold the altitude present at the moment of mode selection. Altitude Hold commands may be modified by moving the CBT switch forward (decrease reference altitude) or rearward (increase reference altitude).
the absence of a preselected vertical speed, engaging the mode will cause the flight director to command a climb or descent at the current helicopter vertical speed. In addition, vertical speed commands may be modified through use of the autopilot CBT switch. The vertical speed select (VS SEL) knob on the Altimeter/Vertical Speed Indicator changes selected vertical speed. The small knob changes the vertical speed 100 fpm per click and the large knob 1000 fpm per click.
KMS 540 Autopilot and Yaw Damper Mode Selection YD (yaw damper) AP (autopilot) AP The lamp above the YD pushbutton illuminates and a green “YD” appears on the EADI when yaw damp is engaged. The YD pushbutton alternately engages and disengages yaw damper functions independently of autopilot operation. The yaw damper will automatically engage when the autopilot is engaged. Autopilot disengagement will NOT, however, disengage the yaw damper.
KSA 572 TRIM ACTUATOR KLA 570 LINEAR ACTUATOR The KFC 500 incorporates three trim actuators (one per axis) in parallel with the helicopter control linkage to provide low-speed command inputs into the control system. The trim actuators provide the long-term control guidance by moving the control system to allow the linear actuators to maintain control authority.
KRG 332 YAW RATE GYRO RA KRG 33 TE 2 GY RO SLAVED COMPASS ı KCS 305 SYSTEM 1 KSG 10 5 + MAN CCW CW The KCS 305 system is comprised of the KSG 105 Directional Gyro, the KA 51B Slaving Accessory, and the KMT 112 Flux Valve. The slaved compass system provides directional information to the EFIS Symbol Generator and the Flight Computer. The Free/Slave switch provides the pilot a means to manually compensate for magnetic effects in the vicinity of the Flux Valve.
KCP 520 FLIGHT COMPUTER ı MSTR (Pilot) switching is located on the pedestal. EFS 40 EADI brightness is controlled via the respective ADI BRT knob located on switch panel. The Autopilot Master switch provides the power input to the Automatic Flight Control System. Switching the AP MSTR to the "OFF" position while autopilot coupled will result in an autopilot disconnect. Flight director will remain operational when the AP MSTR is "OFF".
VG SEL 1-2 DME HOLD The vertical gyro select switch/annunciator allows the pilot (co-pilot as well 1 2 in a four-tube EFS 40 installation) to select an alternate vertical gyro reference for display on the EADI. The on-side vertical gyro is illuminated in green when activated for display. The cross-side vertical gyro is annunciated in amber when activated for display. The DME HOLD switch/annunciator allows the pilot to activate DME hold.
Cyclic Grip Switch Assembly 1 NAV Stand-By Switch — Located on the cyclic, the NAV Stand-By Switch disengages the flight director when pressed. The autopilot and yaw damper remain engaged in the default modes, Pitch Attitude Hold and Roll Attitude/Heading Hold. 2 3 Force Trim Release Switch — Mounted on each of the cyclics, the Force Trim Release (FTR) Switch provides synchronization of the flight director pitch and roll axes as well as releasing the magnetic brake in the trim actuator.
Collective Switch Assembly Yaw Force Trim Release Go-Around Pushbutton– GoAround mode cancels any lateral flight director mode and commands a pitch attitude necessary for 750 fpm rate of climb. The autopilot if engaged remains engaged. Any lateral flight director mode can be subsequently reengaged without cancelling the Go-Around mode. Selecting any vertical mode, or pressing the FTR switch, cancels the Go-Around mode. Yaw Trim Yaw Trim– Commands trim drive for the yaw axis when the autopilot is engaged.
EFS 40 Electronic Flight Instrument System 1 TST 12.6 NM 359 1 2 W G S E 24 12 S 1 H S I 3 6 L O C N A V N 30 33 REF 11. 5 15 CRS 360° 21 ADF 2 DIR SYNC BRT ED 461 EFIS Display Refer to the EFS 40 Electronic Flight Instrument System Pilot’s Guide for complete EFIS operation. A R C “Push Sync” – Syncs the heading bug with the lubber line. TST-SYS – alternates display of time to station and ground speed. When depressed and held, the system activates preflight test.
EADI 40 Electronic Attitude Indicator EFS 40 is the state-of-the-art Electronic Flight Instrumentation System with four inch displays. Because EFS 40 is so broad in its capabilities, the following section attempts to describe only the information about the system that pertains to the KFC 500 Flight Control System. Normal Attitude Display Pitch Attitude — Pitch scale reference marks extend above and below the horizon line indicating 10, 20, 25, 30, 40, 50, 60, 70, 80 and 90 degrees.
1 2 3 4 5 6 7 ı AP YD 129 K T HDG LOC 20 IAS ALT 20 1. Yaw Damper Annunciator 2. Autopilot Annunciator 3. Active Lateral Mode 4. Armed Lateral Mode 5. Command Reference Value 6. Active Vertical Mode 7. Armed Vertical Mode If the flight director data becomes invalid, a red “FD” enclosed in a red box will be displayed at the right center of the display and the command bars will be removed. Autopilot engagement is annunciated by a green “AP”.
Rising Runway — The display of the rising runway is available in the Approach mode when a localizer or MLS and radar altitude are available. The symbolic rising runway will be displayed in the lower center of the display just above the LOC/MLS lateral deviation scale. Marker Beacon Annunciation — The three marker beacon annunciations are capable of being displayed on the EADI.
EHI 40 Electronic Horizontal Situation Indicator The EHI 40 Electronic Horizontal Situation Indicator has capabilites far superior to any electromechanical HSI currently available. Because the EHI 40 is so broad in its capabilities, this section will only attempt to describe the EHI 40 features that apply to the KFC 500 Flight Control System. For additional information on the EHI 40, please refer to the EFS 40/50 Pilot’s Guide. while RNAV approach indicates1.25 mile linear displacement.
1 TST 1 2 5 7 12 1 H S I G S E L O C N A V 11. 5 3 W 4 6 REF 6 3 N 30 33 24 2 S 1 12.6 NM 359 15 CRS 360° A R C 21 ADF 2 DIR SYNC BRT 1. Heading Bug 2. Course Pointer 3. Compass Card 4. Navigation Source 5. Course Deviation Indicator 6. Lubber Line 7. Vertical Scale Pointer The EFS 40 Electronic Flight Instrument System is integrated with the KFC 500 to simplify the navigation interface and switching.
KAD 480 Air Data System The KAD 480 Digital Air Data System is comprised of the KDC 481T Central Air Data Computer, and the KAV 485 Altitude/Vertical Speed Indicator. 1 KDC 481 KDC 481T Central Air Data Computer The heart of the KAD 480 Air Data System, the KDC 481T Central Air Data Computer, processes pitot and static pressures and air temperature inputs, and supplies the processed information to the KCP 520 Flight Computer and KAV 485 Altimeter/ Vertical Speed Indicator.
Intentionally Left Blank 33
KAV 485 Altitude/Vertical Speed Indicator ı 1 0 9 2 8 1 ALT ALT 2 3 7 2 1 UP 0 DN VS 3 1000 FT/MIN 3 1 ALT BARO T E S T PUL L SEL SEL ENG 12 1. 2. 3. 4. 5. 6. 7. 8. 10 2 VS PUSH 9 VS .5 7 8 ALERT DEN ALT SEL IN HG HPa .5 6 3 30.08 1,700 4 5 1,160 6 4 5 11 V S 13 Hg/HPa Pushbutton Altimeter Flag Altimeter Barometric Pressure Setting Vertical Speed Bug Vertical Speed Flag IVSI Diplay Barometric Pressure Setting Selector/Test 9. Altitude Alert Annunciation 10.
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.
Altitude Select/Density Altitude — Provides continuous display of altitudes selected for altitude alerting and flight director capture and tracking, or momentary display of current density altitude derived by the Central Air Data Computer. Preselected altitudes are displayed in 100-foot increments. The current density altitude displays for approximately five seconds at the end of the air data system’s preflight test function.
Vertical Speed Engage Pushbutton — Pressing the Vertical Speed Engage pushbutton causes the flight director to command the aircraft to climb or descend at the rate indicated by the vertical speed bug on the IVSI. Altitude Select Pushbutton — When pressed, the altitude select key engages the flight director’s Altitude Arm function in coordination with the digital altitude display in the KAV 485’s altitude preselect window.
38
KFC 500 Emergency Procedures 39
Emergency Procedures Autopilot Emergencies The KFC 500 monitors autopilot operations continuously through sensors that monitor the aircraft’s pitch attitude and acceleration, as well as servo motor operation. If monitors in the KFC 500 detect a problem, the autopilot will disconnect, illuminate an AP annunciation, and provide an aural disconnect tone.
Manual Autopilot Shutdown It is important to realize the different ways an autopilot can be manually disconnected. The following list describes the alternate methods used to manually disable the autopilot. 1. Autopilot Mode pushbutton — PRESS AP, THEN RELEASE. 2. Force Trim Release Switch — PRESS AND HOLD. Both autopilot and yaw damper will be inhibited while depressed through the second detent. 3. Move the AP Master to the "OFF" position. 4. AFCS Circuit Breaker — PULL. 5.
42
KFC 500 Preflight Procedures 43
Preflight Procedures Caution: Operation of the Autopilot on the ground may cause undesired rotor control/movement. The Bell 230 has preflight test sequences required in addition to the general procedures described here. See the FAA approved Rotorcraft Flight Manual Supplement for particular details. Air Data System Self Test 1. Verify correct altimeter setting on the altimeter/vertical speed indicator. 2. Press the PUSH TEST BARO control. 3.
Electronic Flight Instrument Self Test See EFS 40/50 Pilot’s Guide and the Aircraft Flight Manual Supplement for procedures.
46
KFC 500 Operational Examples 47
Operational Examples Attitude Hold ı AP YD HDG Attitude Hold Operation maintains the helicopter’s reference attitude (not altitude) OR IAS 20 20 10 10 10 10 3. The reference attitude may be modified using the vertical and lateral command control (Cyclic Beep Trim). Alternatively: 1. Establish the desired pitch and roll attitude. OR 2. Depress the "AP" pushbutton on the mode select panel. Note: Arrows indicate external force AP 1. Establish the desired pitch attitude.
If the autopilot is engaged, the pitch attitude present at selection of NAV STBY is maintained. Roll attitude defaults to roll-level/heading hold. Attitude Hold mode becomes active. 1 CRS N 3 30 6 33 W E V O R 12 24 1 21 S Force Trim Release A R C 15 H S I REF 140 KT 1 2 N A V 11. TST 5 11.0 NM 090 010° DIR SYNC BRT The HDG knob is used to move the heading bug on the HSI. FTR SYNC 2.
Go-Around Mode 4. When appropriate, a new lateral mode and/or vertical mode may be engaged to provide guidance. 1. Prior to or when the MDA or DH is reached, add appropriate climb collective power and depress the GO-AROUND pushbutton on the collective switch panel. Navigation Coupling 1. Select the navigation source to be coupled to the NA AFCS by depressing the NAV V pushbutton on the EHSI. The system will not couple to ADF. GoAround 2. Use the COURSE knob to select the course DIR to be tracked.
Yaw Force Trim Release Yaw Force Trim Release To reposition the pedals when the Yaw Damper is engaged, press and hold the Yaw Force Trim Release switch. The Yaw brake will disengage, allowing free pedal movement. Autopilot operation in the pitch and roll axes will not be disturbed. Upon release of the switch, the Yaw brake will reengage, and the Autopilot/Yaw Damper will command ball centered yaw axis.
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 Supplement for specific operating instructions and limitations. 4 N 1 2 3 0° 01 090° ı Objective: Depart the assigned runway, turn to a 010° heading and climb to 3000 feet. Prior to hover perform the autopilot preflight procedures as described on page 47. 1. Prior to takeoff, press the FD switch.
2. After takeoff establish the appropriate climb attitude. When a safe altitude has been reached, activate the Heading Select mode by depressing the HDG pushbutton on the mode select panel. Activate the desired vertical mode by selecting the appropriate button on the mode select panel. This will result in flight director commands to turn to maintain (heading bug) heading and pitch to the appropriate vertical attitude.
ı AP YD HDG IAS 20 20 10 10 10 10 20 20 1 TST CRS 11.0 NM 090 1 2 N 30 W E V O R 3 6 33 N A V 12 24 1 S H S I REF 140 KT 21 DIR BRT A R C 15 4. A momentary tone and alert annunciation is initiated 1,000 feet prior to reaching the selected altitude. Prior to reaching the selected altitude, the autopilot transitions from Altitude ARM to Altitude Capture (CAPT) and then engages Altitude Hold automatically.
Procedure Turn to an ILS Approach 8° 05 N 2 270° 1 3 283° 4 8° 23 ı Objective: Fly outbound, execute a procedure turn, and fly a coupled ILS approach. AP YD 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 pointer. EFS 40 automatically determines Back Course from the course selection and aircraft heading.
2. When the computed capture point is reached, the LOC Approach Coupled mode is automatically activated and a left turn outbound on the localizer is commanded by the flight director and satisfied by the autopilot. Note the left/right deviations are directional. ı AP YD BC ALT 20 20 10 10 10 10 20 20 LOC BC 1 TST CRS 1 2 24 S 33 15 12 A R C 3 H S I G S N 1 REF 11. 5 W 30 21 L O C N A V E 6 3.
4. At the point specified to begin the procedure turn inbound, select 103° with the heading bug for a 180° turn toward the localizer front course. The deviation bar shows pictorially the course you are to intercept. Depress the APR pushbutton to arm the Approach mode. Automatic capture will occur to direct the aircraft on the localizer inbound. 20 G S 10 10 10 10 20 20 LOC 1 TST CRS 17.1 NM 058 1 2 E 3 6 N 33 W 1 H S I 24 L O C N A V REF 140 KT 11.
ILS Transition to Missed Approach 8° 05 N 2 090 3 1 8° 23 Objective: Transition from an ILS approach to missed approach and Go-Around. Continuing the maneuver on the preceding page, Approach Coupling occurs and the Glideslope mode is annunciated as it is coupled. ı AP YD LOC GS 20 20 10 10 G S 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.
2. At Decision Height, a missed approach is initiated by pressing the Go-Around button as collective is added. The Go-Around button is located on the collective. The GoAround pushbutton activates the Go-Around mode which provides flight director commands to certification specific vertical speed and roll-level attitude. At the discretion of the crew, another flight director mode may be activated to complete the missed approach.
Localizer Back Course Approach ° 45 N 5 090° 4 2 3 13 5° 1 OBJECTIVE: Fly outbound on the localizer, complete a procedure turn and fly the localizer back course approach to the airport. ı AP YD 1. In Heading Select and Altitude Hold mode with the localizer frequency selected in the active navigation receiver, the aircraft is flying 45° to intercept the localizer. The localizer front course of 090° is selected with the HSI course pointer.
Note: Always select the navigation course pointer to the localizer front course. (This course will be opposite helicopter heading when inbound on a back course approach.) 2. When the computed capture point is reached, the Approach mode is automatically activated and a right turn outbound on the localizer is commanded by the flight director and satisfied by the autopilot.
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 pictorially the course you are to intercept as well as the angle of intercept. Depress the APR pushbutton 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.
6. Disengage the autopilot or press the Go-Around pushbutton at the missed approach point. The GoAround pushbutton will activate the Go-Around mode in which the flight director commands a 750 fpm cllmb and roll-level flight. The Go-Around pushbutton is located on the collective. Altitude Select must be manually armed by depressing the ALT SEL pushbutton on the KAV 485. At the pilots discretion, the autopilot may be reengaged. The autopilot is not to be coupled below approved approach minimums.
Performance Specifications Mode Parameter KFC 500 Value Attitude Hold Pitch Command Profile Pitch Hold Accuracy Roll Angle Limit Roll Command Rate Limit Roll Hold Accuracy 0.1G or 2 Deg/Sec ± .
Mode Parameter KFC 500 Value Go-Around Pitch Up Command Pitch to 750 fpm Climb Alt Sel Engage Range Engage Vert Spd Limit 0 to 55,000 Ft. Function of Vert. Speed Max “G” During Capture ± 0.1G Alt Hold Engage Range Engage Vert Spd Limit Accuracy Pitch Rate Limit -1,000 to 20,000 Ft. ± 2,000 Ft/Min ± 40 Ft* 0.1G Vert Accel IAS Hold Engage Range Accuracy Pitch Rate Limit 50 Kts to VMO ± 3 Kts 0.
Pilot’s Guide KFC 500 Bendix/King® Flight Control System Honeywell International Inc. One Technology Center 23500 W. 105th Street Olathe, Kansas 66061 FAX 913-791-1302 Telephone: (913) 712-0400 Copyright ©1993 Honeywell International Inc. All rights reserved. 006-08750-0000 Rev.
