BendixKing KFC 500 User Manual

KFC 500

Pilot’s Guide

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.

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-but-

ton 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 of Front Cover, 1, 2, 25, 26, 27, 28, 29, 30, 31, 32, 33, Back Cover

Remove Yaw Trim - 18, 51 Revise Attitude and Heading Hold Roll Command Limit - 74

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Table of Contents

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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 ...................................................................8

AFCS GROUND TEST ........................................................8

SCAS & AP PWR/OFF ........................................................8

TEST/BRT/DIM (AFCS Lamp Test).....................................9

SCAS/AP Annunciators .....................................................10

Modes of Operation ...........................................................11

SCAS Mode.......................................................................11

AP Mode............................................................................11

Lateral Command Control..................................................13

Pitch Command Control.....................................................14

SCAS/Autopilot Disconnect ...............................................15

Force Trim Release (FTR).................................................15

Yaw Force Trim Release ...................................................15

Flight Director.........................................................................17

SCAS/Autopilot/Flight Director Block Diagram ..................19

SCAS/AP Operation (Flight Director Installed) ..................20

Yaw Force Trim Release.............................................20

Flight Director Operation....................................................21

Modes of Operation.....................................................21

Pitch Attitude & Roll Attitude Hold (FD).......................22

Lateral Command Control ...........................................23

Vertical Command Control ..........................................24

Force Trim Release (FTR)...........................................25

Flight Director Off ........................................................26

Go Around...................................................................26

Autopilot/Flight Director Mode Annunciation ...............26

KMS 540 Flight Director Mode Selection...........................27

Heading Select (HDG).................................................27

Bank Angle Limit (BL)..................................................27

Navigation Mode (NAV)...............................................28

Approach Mode (APR) ................................................28

Autolevel Mode............................................................30

Altitude Select (ALT SEL)............................................30

Altitude Hold (ALT)......................................................31

Introduction

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The KFC 500 Automatic Flight Control System is available in two configurations for the Bell 430. There is a basic three axis SCAS/Autopilot system and a three axis SCAS/Autopilot with Flight Director.

The KFC 500 SCAS/Autopilot with Flight Director is integrated with the KAD 480 Central Air Data System and the electronic flight instrument system to enhance user-friendliness as well as system annunciation.

This system combines complete stability augmentation, autopilot, and optional 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 generation systems.

Digital, solid-state design throughout the Flight Control System provides maximum reliability while economizing on system weight and required installation space.

The KFC 500 is designed to optimize passenger and flight crew comfort, while still providing accurate control response in any flight situation.

Whenever possible, autopilot induced aircraft motions border on the lower limits of human perceptibility, ensuring exceptionally smooth flight. The Flight Control System’s maximum command values were tailored for the Bell 430 during the aircraft certification process.

Internal safety monitors and automatic self-test functions keep constant track of the KFC 500’s status, and provide signals for automatic shutdown of impaired control axes or flight director functions if available. When the KFC 500 de-couples 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.

In addition to reliability and light weight, the KFC 500 is designed to be easily maintained in the field. Selfcontained diagnostic tests assist trouble-shooting done by maintenance personnel at Honeywell factory approved service centers. The Built-In-Test functions enable a technician to trace faults. Qualified Honeywell service centers around the world are ready to provide assistance whenever necessary.

Table of Contents

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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 ..............................................32

KSM 575 Linear Actuator Assembly............................32

KCP 520 Flight Computer............................................33

AFCS Sensors ...................................................................33

KVG 350 Attitude Gyro ................................................33

KCS 305 Slaved Compass System .............................33

KRG 333 Rate/Acceleration Sensor ............................34

Control Position Transducer ........................................34

KAD 480 Air Data System ...........................................34

KDC 481T Air Data Computer...............................34

KAV 485 Altitude/Vertical Speed Indicator............35

Emergency Procedures/Limitations............................................39

Preflight Procedures.....................................................................41

Operational Examples ..................................................................43

Performance Specifications.........................................................69

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KFC 500

SCAS/Autopilot

Normal Operation

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Introduction

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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.

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Normal Operation

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SCAS

KRG 333 Rate/Acceleration Sensor

KCP 520 Flight Computer

KMS 541

Mode Selector

KCS 305 Compass #2

Trim Actuator

Linear Actuator

Control Position

Synchro

Cyclic

Switches

PITCH

ROLL

YAW

Collective

Switches

KVG 350 VG #2

IIDS

Control Position

Synchro

Control Position

Synchro

Collective Control Position Synchro

Trim Actuator

Linear Actuator

Trim Actuator

Linear Actuator

SCAS/AP Remote Switches

MANCWAUTO

CCW

KSG 105

AFCS

GROUND

TEST

SCAS & AP PWR

OFF

FORCE

TRIM

OFF

AP ON

SCAS ON

RADIO

ICS

FOOT

RADIO

ICS

FOOT

Basic KFC 500 SCAS/Autopilot System Block Diagram

P 5

Normal Operation

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Normal Operation

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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.

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.

SCAS & AP PWR/OFF

Depressing the SCAS & AP PWR/OFF switch will turn power on or off to the SCAS/AP system. Power is available to the system when the OFF annunciation is not illuminated.

Basic SCAS/AP Operation

This section provides the Normal Operating Procedures for the basic SCAS/AP version of the KFC 500 System.

SCAS/AP Remote Switches

There are three remote switches for the system. They are located in the pedestal, one just above, and two to the right of the AFCS Mode Select Panel.

Force Trim/OFF

Depressing the FORCE TRIM/OFF switch will turn power on or off to the Force Trim system. Power is available and the system is on when the OFF annunciation is not illuminated.

RADIO

ICS

FOOT

RADIO

ICS

FOOT

FORCE

TRIM

OFF

AP ON

SCAS ON

FORCE

TRIM

OFF

AFCS

GROUND

TEST

SCAS &

AP PWR

OFF

SCAS &

AP PWR

FORCE

TRIM

TEST/BRT/DIM (AFCS LAMP TEST)

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.

TEST

DIM

B R T

Normal Operation

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Normal Operation

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Modes of Operation

The KMS 541 Mode Select Panel provides control and annunciation of the KFC 500’s SCAS and AP (attitude retention) modes. To activate the SCAS or AP modes using the Mode Select Panel, press the desired push-button. The corresponding mode lamp will illuminate above the switch. Alternatively, to deactivate the SCAS or AP mode when activated, depress the respective push-button and then release (The AP mode reverts to SCAS when deselected).

There is a remote repeater annunciator located above the mode selector panel. This annunciator will mimic the annunciators 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

Depressing the SCAS button on the Mode Select Panel will activate the stability augmentation mode. The annunciator above the switch on the MSP and above the MSP on separate panel will illuminate to verify that the flight computer has recognized the button push.

The SCAS (Stability Control Augmentation System) mode provides rate damping. It may be referred to as a damper system that is stabilizing the helicopter against outside disturbances and thereby is augmenting the pilot effort. The SCAS mode is designed so that pilot control inputs which cause helicopter attitude changes 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.

AP Mode

The autopilot (AP) push-button engages the pitch, roll, and yaw axes and provides trim follow-up for those axes. Depressing the AP button on the Mode Select Panel will activate this mode. The annunciator above the switch on the MSP and above the MSP on separate panel will illuminate to verify that the flight computer has recognized the button push. The Force Trim system must be on for this mode to operate.

SCAS/AP Annunciators

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 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 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 non-selected system will annunciate AP and SCAS Fail annunciation for single axis failures in roll, pitch and/or Rate Gyro failure. The nonselected 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.

SCAS

KMS 541 SCAS/AP Mode Select Panel

AFCS

GROUND

TEST

SCAS &

AP PWR

OFF

SCAS

SCAS ON

Normal Operation

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Normal Operation

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Lateral Command Control

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 commanded to follow the pilot’s or copilot’s input to roll left or roll right. If the switch is given a discrete push the first click will yield 6° of bank and 1° per click thereafter. 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.

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 level attitude and maintain the heading at the time the aircraft rolls level.

Desired roll and pitch attitudes may be selected by several methods. Adjusting the helicopter’s attitude manually may be accomplished by pressing the Force Trim Release (FTR) switch (on the cyclic) to the first detent while moving the cyclic (and 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 and hold the existing heading. The pilot may manually fly the aircraft to a new attitude, press and release the FTR switch, and release the cyclic (Fly Through mode). When the system senses pilot fly through (detents made in force feel springs) the system will

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. Alternatively, attitude hold commands may be modified by moving the Cyclic mounted Beep Trim (CBT) switch in the appropriate directions.

The yaw axis augments rotorcraft stability by opposing uncommanded yaw motion and providing ball centering. Loss of #1 hydraulic system automatically disconnects the flight control system from the yaw axis. In case of #1 hydraulic power loss, consult the Rotorcraft Flight Manual for the procedures specified for AFCS yaw axis operation.

AFCS DISC

CYCLIC GRIP SWITCHES

CBT

FTR

AP ON

Normal Operation

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Normal Operation

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Activating Discrete or Continuous Lateral Command has the following effect upon the command reference for autopilot operation:

SCAS/Autopilot Disconnect

The cyclic mounted AFCS DISC switch when pushed disconnects 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.

Force Trim Release (FTR)

The FTR switch is a double detent switch. Actuation to the first detent allows the pitch and roll clutches to release for free cyclic movement. Depressing through the second detent releases the yaw clutch in addition to the pitch and roll, allowing 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 with the present helicopter attitude.

When the FTR switch is pressed, the AFCS will revert to SCAS (when AP is engaged) and the trim servo magnetic clutches 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 must be on for the AP mode to operate.

Yaw Force Trim Release

A collective mounted Yaw Force Trim Release is provided. If the Force Trim System is on, 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 force trim release is released.

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.

Activating Discrete or Continuous Pitch Command has the following effect upon the command reference for autopilot operation:

Autopilot Lateral Command Values

Discrete Command System Response

Roll Attitude First Click=6°, Subsequent=1° per click

Continuous Command

Roll Attitude Constant Roll Rate

Autopilot Pitch Command Values

Discrete Command System Response

Pitch Attitude 0.5° per click

Continuous Command

Pitch Attitude Maintains constant. acceleration profile

until release

CBT

AFCS DISC

FTR

YAW FORCE TRIM RELEASE

KFC 500

Flight Director

Normal Operation

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Normal Operation

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Normal Operation

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ALT

VS ALT

1000 FT/MIN

UP DN

IN HG HPa

DEN ALT

SEL

1,160

30.08 1,700

ENG SEL

BARO

SEL

ALT

ALERT

APRHDG

ALT

IAS

NAV

SCAS

KCP 520

AFCS

Computer

KMS 540

Mode Selector

Trim Actuator

Linear Actuator

Control Position

Synchro

Cyclic

Switches

PITCH

ROLL

YAW

Collective

Switches

IIDS

Control Position

Synchro

Control Position

Synchro

Collective Control Position Synchro

Trim Actuator

Linear Actuator

Trim Actuator

Linear Actuator

Display System

Navigation

Receivers

SCAS/AP Remote Switches

KRG 333 Rate/Acceleration Sensor

KCS 305 Compass #2

KVG 350 VG #2

MANCWAUTO

CCW

KDC 481T Air Data Computer

KAV 485

Altimeter/

VSI

F F

LIGH

RADIO

ICS

FOOT

RADIO

ICS

FOOT

PIC

FORCE

TRIM

OFF

AP ON

SCAS ON

AFCS

GROUND

TEST

SCAS &

AP PWR

OFF

EFIS PWR

PL1

OFF

EFIS PWR

CPL1

KFC 500 SCAS/Autopilot/Flight Director System Block Diagram

KCP 520

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