Pilot's Guide KFC 500 Bendix/King Dual Automatic Flight . - EDMO

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. SCAS/AP Remote Switches Force Trim 1/OFF Basic Dual SCAS/AP Operation RADIO FORCE TRIM 1 FORCE TRIM 2 OFF OFF FORCE TRIM 1 AP ON AP 1 2 SCAS ON RADIO FOOT SW FOOT SW ICS OFF ICS There are seven remote switches for the system. They are located on the center pedestal and overhead panels. Depressing the FORCE TRIM 1/OFF switch, located on the center pedestal just above the Mode Select Panel, will turn power on or off to the Force Trim system when the primary flight control system is selected. Power is available and the system is on when the OFF annunciation is not illuminated. AP 1/2 Select Switch AP 1 2 FORCE TRIM 1 Depressing the AP 1/2 switch located on the center pedestal just above the Mode Select Panel will alternately select the primary (1) or secondary (2) AFCS systems. When 1 is illuminated the primary system is selected and when 2 is illuminated the secondary system is selected. Force Trim 2/OFF FORCE TRIM 2 OFF AP AP 1 2 1 Depressing the FORCE TRIM 2/OFF switch, located on the center pedestal just above the Mode Select Panel, will turn power on or off to the Force Trim system when the secondary flight control system is selected. Power is available and the system is on when the OFF annunci- 2 Normally the primary system will be used, unless a failure has occurred affecting AP mode availability, in which case the secondary system March 27, 1998 8 006-18081-0000 ation is not illuminated. SCAS & AP PWR 1 /OFF SCAS & AP PWR 1 FORCE TRIM 2 OFF Depressing the SCAS & AP PWR 1/OFF switch located on the center pedestal, just to the right of the Mode Select Panel, will turn power on or off to the Primary (#1) SCAS/AP system. Power is available to the system when the OFF annunciation is not illuminated. AFCS GROUND TEST AFCS GROUND TEST This momentary switch, located on the overhead panel below the Emergency Bus 2 Breakers, is used to initiate the SCAS/AP System preflight test, on both systems if desired, after the initial test that occurs at system power up. At power up, or when AFCS Ground Test switch is pressed, the non-selected system will continue to annunciate the associated system AP and SCAS FAIL Cautions until such time the system is selected and allowed to complete interactive power up preflight tests. Preflight test must be run prior to attempting system engagement on the selected system. SCAS/AP engagement will be disallowed in any axis that has not successfully passed preflight test. The system will allow engagement and use of any available axis (roll, pitch, and/or yaw) that has passed. While performing preflight test is only recommended on the ground it may be performed in the air as well, see Transport Canada and/or Federal Aviation Administration Approved Rotorcraft Flight Manual for any restrictions placed on this operation in the air. 006-18081-0000 SCAS & AP PWR 1 SCAS & AP PWR 2/OFF SCAS & AP PWR 2 OFF Depressing the SCAS & AP PWR 2/OFF switch located on the center pedestal, just to the right of the Mode Select Panel, will turn power on or off to the Secondary (#2) SCAS/AP system. Power is available to the system when the OFF annunciation is not illuminated. SCAS & AP PWR 2 9 March 27, 1998

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. This lamp test function can be invoked any time desired by the pilot and has no effect on mode operation. An automatic lamp test function is performed upon power up of the Mode Select Panel and will turn on all MSP annunciators for approximately 2 seconds immediately after power is applied. These annunciators may also be turned on by a special test bit from the FCC during part of its preflight testing. See Bell Helicopter 430 Flight Manual for other functions activated by this switch in the test position. SCAS/AP Annunciators ROL (yellow), AFCS YAW (yellow), and AUTOTRIM (yellow). The SCAS (1)/(2) and AP (1)/(2) failure annunciators will be illuminated any time prior to preflight test being performed, after a major system failure There are nine annunciators for the system available on the IIDS (Integrated Instrument Display System), AFCS DISC (red), 1 SCAS and SCAS 2 (yellow), 1 AP and AP 2 (yellow), AFCS PIT (yellow), AFCS SCAS & AP PWR 1 OFF SCAS & AP PWR 2 OFF has been detected or if SCAS/AP PWR is OFF. Single axis failures will not cause the SCAS (yellow) or AP (yellow) annunciation’s to light on the selected system. You will get an axis failure only (i.e. AFCS PIT). A roll or pitch axis failure indicates that control of that axis has been lost. A yaw axis failure indication means that yaw axis or trim follow up in yaw axis 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. The nonselected system will annunciate AP and SCAS Fail annunciation for single axis failures in roll, pitch and/or Rate Gyro failure. The non-selected system will annunciate AP Fail for pitch and roll trim axis failure and / or when vertical acceleration is invalid or Vertical Gyro is invalid after normal power up delay. If this side is selected then the annunciation will display the single or multiple axis failures applicable and clear the AP and / or SCAS Fail annunciation if any axis is available for use. button. The corresponding mode lamp will illuminate above the switch. Alternatively, to deactivate the SCAS or AP mode when activated, momentarily press the respective push-button (The AP mode reverts to SCAS when deselected). There are remote repeater AP ON, SCAS ON annunciators located above the mode selector panel that is switched to the selected system. These annunciators will mimic the ones located above the mode switches on the Mode Select Panel. The brightness of the annunciator lamps on the mode controller is adjusted automatically by a photocell located on the face of the unit. The button nomenclature back lighting is controlled by the pedestal dimmer control on the overhead panel. SCAS Mode Momentarily pressing the SCAS button on the Mode Select Panel will activate the stability augmentation mode on the selected system. The mode lamp above the switch on the MSP and the remote repeater SCAS ON annunciator will illuminate to verify that the selected flight computer has recognized the button push. Modes of Operation AP SCAS ı KMS 541 SCAS/AP Mode Select Panel March 27, 1998 10 006-18081-0000 The KMS 541 Mode Select Panel provides control and annunciation of the KFC 500’s SCAS and AP (attitude retention) modes of the selected system. To activate the SCAS or AP modes using the Mode Select Panel, momentarily press the desired push- 006-18081-0000 SCAS SCAS ON The SCAS (Stability Control Augmentation System) mode provides rate damping. It may be referred to as a damper system that 11 March 27, 1998

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. Some amount of SCAS counteraction is designed into the system for better pilot feel in the Bell 430. Desired roll and pitch attitudes may be selected by several methods. With the autopilot engaged the pilot can manually adjust the attitude of the helicopter by pressing and holding depressed the Force Trim Release (FTR) switch on the cyclic while repositioning the helicopter to the desired attitude. Upon release of the FTR, the autopilot will provide commands to maintain the target pitch and roll attitude if greater than 6 . If the roll attitude is less than 6 the system will return to roll level attitude and hold the existing heading. While the Autopilot is engaged the pilot may press the FTR switch, manually move the controls to fly the aircraft to a new attitude and release the FTR switch and cyclic. The system will then hold this new attitude in pitch and roll if greater than 6 degrees. If less than 6 degrees bank angle the system will roll wings level and assume the new heading. On the primary system the pilot may momentarily fly the aircraft manually at any time (via the Fly Through mode with detent switch activation). When detents are activated the system will temporarily revert to SCAS. After release of the cyclic (overpower force is removed and detent switches not activated) the autopilot will return to attitude hold (AP annunciated), and fly the aircraft AP Mode The autopilot (AP) push-button engages the pitch, roll, and yaw axes of the selected system and provides trim follow-up for those axes. Momentarily pressing the AP button on the Mode Select Panel will activate this mode. The mode lamp above the switch on the MSP and the remote repeater AP ON annunciator will illuminate to verify that the selected flight computer has recognized the button push. The Force Trim system power for selected system must be on and Force Trim system not overpowered (detent switches not activated on primary system) for this mode to engage. AP ON AP Autopilot mode will provide commands to maintain the current pitch attitude and heading. If the roll attitude is not level upon AP engagement, the autopilot will command a June 15, 1999 12 006-18081-0000 back to the attitude existing at the time that the pilot intervened. Alternatively, attitude hold commands may be modified by moving the Cyclic mounted Beep Trim (CBT) switch in the appropriate direction. The yaw axis augments rotorcraft stability by opposing uncommanded yaw motion and providing ball centering. The yaw axis also provides turn coordination and yaw trim (using lateral acceleration). Lateral acceleration is used by the system to provide the described functionality anytime that the acceleration sensor is valid. Loss of #1 hydraulic system automatically disconnects the flight control system from the yaw axis. In case of #1 hydraulic power loss, consult the Bell 430 Rotorcraft Flight Manual for the procedures specified for AFCS yaw axis operation. commanded to follow the pilot’s or copilot’s input to roll left or roll right. If within 6 of level flight when the switch is given a momentary push the first click will yield 6 of bank in respective direction. If greater than 6 of bank in either direction a momentary push will result in 1 per click. If the switch is pressed continuously the system will command a constant roll rate until the beep trim switch is released. Upon release of the CBT switch, the autopilot will command the aircraft to maintain the existing roll attitude. Roll attitudes of less than six degrees of bank will cause the autopilot to revert to commands for roll-level with heading hold. The AFCS is designed with absolute attitude limits and rate limits. During fly through or other modes of operation , the aircraft attitude/rate must be less than or 45 /15 per second in roll and or 15 /10 per second in pitch and 15 per second in yaw for the AP mode to remain engaged. If these limits are exceeded the autopilot will automatically disconnect. AFCS DISC Lateral Command Control CBT FTR Activated by the Cyclic Beep Trim (CBT) switch when the AP mode is on, Lateral Command Control modifies the autopilot’s reference roll attitude. When Lateral Command Control is used, the aircraft will be 006-18081-0000 CYCLIC GRIP SWITCHES 13 March 27, 1998

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 the same cyclic beep switch as mentioned in the previous paragraph, the autopilot’s reference pitch attitude can be modified by moving the pitch command switch fore or aft. Moving the switch forward adjusts the helicopter’s pitch attitude downward, while moving it aft adjusts the attitude upward. CBT Activating Discrete or Continuous Pitch Command has the following effect upon the command reference for autopilot operation: Autopilot Pitch Command Values Discrete Command Pitch Attitude System Response The cyclic mounted dual contact (separate power, primary/secondary) AFCS DISC switch when pushed disconnects the selected AP and/or SCAS mode if engaged. This switch provides the pilot or copilot a quick and easy means to disconnect either of these two control coupled modes of the selected system. Force Trim Release (FTR) The cyclic FTR switch is a double pole single detent switch interrupting Force Trim 1 Power when the primary system is selected and interrupting Force Trim 2 Power when the secondary system is selected. Switch actuation allows the pitch, roll and yaw clutches to be released for free cyclic and anti-torque pedal movement. Pushing and releasing the FTR switch when the autopilot mode is on (attitude hold), causes the system to synchronize its reference attitude and heading with the present helicopter attitude and heading. When the FTR switch is pressed, the AFCS will temporarily revert to SCAS (when AP is engaged) and the trim servo magnetic clutches will release eliminating the artificial feel system and allowing the pilot or copilot free movement of the cyclic. When the switch is released the AP and trim clutch reengages. The Force Trim System Power must be on to the selected system for the AP mode to engage. (Also the Force Trim Detent switches, in the force feel system, must not be activated for the primary AP mode to engage). 0.5 per click Continuous Command Pitch Attitude March 27, 1998 Maintains constant. acceleration profile of 0.1 g or 2 per second whichever is less until release 14 006-18081-0000 006-18081-0000 15 March 27, 1998

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. March 27, 1998 Normal Operation 16 006-18081-0000 006-18081-0000 17 March 27, 1998

Normal Operation KFC 500 Dual SCAS/Autopilot/Single Flight Director System Block Diagram This page intentionally left blank. Collective Switches KMS 541 Mode Selector SCAS & AP PWR 1 Cyclic Switches OFF SCAS/AP Remote Switches/Annunciators RADIO FORCE TRIM 1 FORCE TRIM 2 OFF OFF PIC 1 2 ALT VS APR BL SCAS & AP PWR 2 OFF IAS Display System EFIS PWR PLT OFF SCAS ON RADIO FOOT SW AP FOOT SW ICS NAV AP ON AP R HDG SCAS FD EFIS PWR COPLT ı ICS OFF Navigation Receivers Primary Pitch Linear Actuator Primary KVG 350 Vertical Gyro PITCH ı KCP 520 Trim Actuator Primary Roll Linear Actuator Primary KRG 333 Rate/Acceleration Sensor DIR ECT OF IO FLIG N HT Control Position Synchro Primary KCP 520 Flight Computer ROLL AFCS GROUND TEST KCS 305 Compass IIDS ı Trim Actuator Control Position Synchro KCP 520 1 Secondary KCP 520 Flight Computer KSG 105 - AUTO MAN CCW CW KDC 481T Air Data Computer YAW KAV 485 Altimeter/VSI ı 0 9 Linear Actuator 8 7 1 KDC 481 1 ALT ALT 2 1,160 4 5 6 3 ALERT 30.08 1,700 DEN ALT SEL IN HG HPa 1 DN 0 3 3 VS .5 1 PUSH 2 VS 1000 FT/MIN .5 UP Trim Actuator 2 VS ALT ENG SEL BARO T Control Position Synchro DIR ECT OF IO FLIG N HT Secondary KRG 333 Rate/Acceleration Sensor Collective Control Position Synchro Secondary Pitch Linear Actuator Secondary Roll Linear Actuator March 27, 1998 18 006-18081-0000 006-18081-0000 19 March 27, 1998 Secondary KVG 350 Vertical Gyro E S T PUL L SEL V S

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. Flight Director modes will also be canceled and or not allowed when AP coupled and a roll or pitch trim failure has occurred. Dual system SCAS/AP operation when not coupled to the Flight Director is identical to that of the basic dual SCAS/AP System, described in the proceeding section, with the following exceptions: SCAS/AP Operation (Flight Director installed) SCAS & AP PWR 1 OFF HDG APR NAV BL SCAS & AP PWR 2 OFF ALT Yaw Force Trim Release EFIS PWR PLT IAS VS OFF YAW FORCE TRIM RELEASE When the Flight Director is included in the system a central air data system is also installed. The air data system allows the AFCS to provide additional functionality in the yaw axis plus improved performance with airspeed gain scheduling in all axes. The yaw axis, as described in the previous section, augments rotorcraft stability by opposing uncommanded yaw motion (rate damping keeps nose from moving), ball centering, and also provides turn coordination as well as yaw trim (using lateral acceleration). With the air data system installed Lateral acceleration is used by the

KFC 500 Dual SCAS/ Autopilot Normal Operation 006-18081-0000 March 27, 1998 4 Introduction March 27, 1998 006-18081-0000 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