BendixKing KI 525A User Manual

Pilot’s Guide

KFC 225

Bendix/King®

Automatic Flight Control System

006-18035-0000

September 2004

N

WARNING

The enclosed technical data is eligible for export under Licanse Designation NLR and is to be used solely by the individual/organization to whom it is addressed. Diversion contrary to U.S. law is prohibited.

COPYRIGHT NOTICE

Copyright ©1999, 2004 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: [phone].

Revision History and Instructions

Manual	KFC 225 AFCS Pilot’s Guide
Revision	1, September 2004
Part Number	006-18035-0000

This revision incorporates a note further explaining the Altitude Hold function.

The following pages were changed:

Front Cover, Copyright, 9, 13, Back Cover

R-1

Revision History and Instructions

Manual	KFC 225 AFCS Pilot’s Guide
Revision	0, April 1999
Part Number	006-18035-0000

This is the original version of this publication.

R-2

	Table of Contents
Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .	. . . . . . . . . . .	.1
General Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . .	. . . . . . . . . . .	. . . . .2
System Integration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .	. . . . . . . . . . .	. . . . .2
Power Application and Preflight Tests . . . . . . . . . . . . . .	. . . . . . . . . . .	. . . . .4
KFC 225 System Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .	. . . .5
Controls and Displays Operation . . . . . . . . . . . . . . . . . . .	. . . . . . . . . . .	. . . . .5
Altitude Alerting and Preselect . . . . . . . . . . . . . . . . . . . . .	. . . . . . . . . . .	. . . .10
Altitude Alerter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .	. . . . . . . . . . .	. . . .10
Altitude Preselect . . . . . . . . . . . . . . . . . . . . . . . . . . . . .	. . . . . . . . . . .	. . . .10
Voice Messaging . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .	. . . . . . . . . . .	. . . .11
System Operating Modes . . . . . . . . . . . . . . . . . . . . . . . . .	. . . . . . . . . . .	. . . .12
Pitch and Roll Attitude Hold (PIT) Modes . . . . . . . . . .	. . . . . . . . . . .	. . . .12
Altitude Hold (ALT) Mode . . . . . . . . . . . . . . . . . . . . . . .	. . . . . . . . . . .	. . . .13
KFC 225 Detailed System Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .	14
Takeoff And Climb To Assigned Altitude . . . . . . . . . . . .	. . . . . . . . . . .	. . . .14
GPS Capture . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .	. . . . . . . . . . .	. . . .16
Outbound On Front Course For Procedure Turn To ILS Approach . .		. . . .18
Front Course ILS Approach . . . . . . . . . . . . . . . . . . . . .	. . . . . . . . . . .	. . . .20
Outbound on GPS Approach . . . . . . . . . . . . . . . . . . . . .	. . . . . . . . . . .	. . . .22
Inbound on GPS Approach . . . . . . . . . . . . . . . . . . . . . .	. . . . . . . . . . .	. . . .24
KCS 55A Compass System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .	. .27
KI 525A Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .	. . . . . . . . . . .	. . . .28
Description of Indicator and Display Functions . . . . . . . .	. . . . . . . . . . .	. . . .28
Slaving Meter (KA 51B) . . . . . . . . . . . . . . . . . . . . . . . . . .	. . . . . . . . . . .	. . . .30
KMT 112 Magnetic Slaving Transmitter . . . . . . . . . . . . . .	. . . . . . . . . . .	. . . .31
KG 102A Directional Gyro . . . . . . . . . . . . . . . . . . . . . . . .	. . . . . . . . . . .	. . . .31
Abnormal Circumstances . . . . . . . . . . . . . . . . . . . . . . . . .	. . . . . . . . . . .	. . . .33
Flight Procedures with the KCS 55A . . . . . . . . . . . . . . . .	. . . . . . . . . . .	. . . .34
General Emergency Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .	.41
Autopilot Malfunction . . . . . . . . . . . . . . . . . . . . . . . . . . . .	. . . . . . . . . . .	. . . .41

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Table of Contents

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ii	KFC 225 AUTOMATIC FLIGHT CONTROL SYSTEM	Rev. 0
		Apr/99

Introduction

Introduction

The pressures of single-pilot instrument flying place critical demands on the skill and concentration of any pilot. To aid you in meeting these challenges, Honeywell has developed the KFC 225 Flight Control System. This system places recent flight control advances normally found only in high end ‘jet’ autopilots into the cockpits of General Aviation Aircraft.

The heart of the system is a lightweight, integrated autopilot computer combining the functions of computer, mode selector, altitude pre-selector, and the optional yaw damper into one unit. The system has been designed to work with your Bendix/King equipment from day one. It can interface directly with your EFIS system, take roll steering commands from your KLN 90B IFR GPS, and, when available, listen to your KRA 10A radar altimeter to improve approach tracking.

It is significant that this Silver Crown Plus flight control system has been designed from the beginning to interface with your Silver Crown Plus package of avionics. Consider the advantage of having your avionics working together as an integrated system rather than as a group of unrelated components built by several different manufacturers.

To fully utilize the impressive capabilities of this full-featured system it is important that the pilot understand the capabilities and limitations of the system. The pilot should take time to read and thoroughly understand the FLIGHT MANUAL SUPPLEMENT for the autopilot installation specific to his aircraft. This Pilot’s Guide should be used to gain additional insight into the operation of the system through the specific operating scenarios. The FLIGHT MANUAL SUPPLEMENT information shall always take precedence over the information found in this manual.

Rev. 0	KFC 225 AUTOMATIC FLIGHT CONTROL SYSTEM	1
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Introduction

General Description

The KFC 225 Three Axis system provides lateral, vertical and optional yaw modes with altitude preselect.

AIR

DH

20	20
10	10
10	10
20	20

AIR

ı

NAV

6

GS

3

N

33

E

HDG

12 GS

15

S 21

30	W

ı

YD

24

ARM VS

G

							UP
P	R
AP	FD	HDG	NAV	APR	REV	ALT	DN

ALT

SEL

KFC 225

System Integration

The system diagram on the next page shows the components and their relationship in a typical KFC 225 system. The actual components on individual systems may vary slightly depending on certification and installation requirements.

The system diagram reflects that the KFC 225 system controls pitch, roll and yaw (optional) axes of the aircraft.

2	KFC 225 AUTOMATIC FLIGHT CONTROL SYSTEM	Rev. 0
		Apr/99

Introduction

A/P Master Switch

AP

AP

NAV

REV

ALT

VS

OR

TRIM

HDG

APR

GS

CAP

GA

YD

ARM

ARM

ALT

TRIM

FAIL

KA 285

Trim Fail

Remote Mode

Annunciaor

Annunciator

KC 225

AIR

Flight Computer

DH

YD

ARM

VS

20

20

G

ALT SEL

10

10

UP

10

10

P

R

20

20

AIR

AP

FD

HDG

NAV

APR

REV

ALT

DN

KFC 225

ı

KI 256 Attitude Gyro

ALT

9

0

9

0

1

6001

8

2

8

0, 500

2

ALT

ALT

OR

7

MB

IN HG

3

7

3

1016

29.99

5

6

ENCODING 4

6

4

5

5

B

KEA 346

KEA 130A

Servoed

Encoding

Altimeter

Altimeter

TST

CRS 350

4.

NM

REF

12

5120 KT

NAV

N

HDG

1

N

11.

33

3

2

33

3

5

GS

0

6

GS

OR

A

L

3

0

6

G

3

N

O

W

E

V

C

W

E

S

1

1

2

4

2

1

4

H

A

2

51

S

12

1

R

12

S

I

S

5

330°

C

ADF 2

ı

CRS

BRT

HDG

KCS 55A

EHI 40

Compass

EFIS

System

OFF

B

GPS

DH 501

KLN 90B TSO

BRT

2

RADAR

CRSR

CRSR

ALTITUDE

3

NAV

CALC

NAV

APT

4

D/T

VOR

FPL

STAT

ACTV

PULL

NDB

25

X 100 FEET

MODE

SETUP

REF

SCAN

INT

5

TRIP

OTHER

MSG

ALT

D

CLR

ENT

CTR

SUPL

ES

20 15 10

ı

Optional

Optional KRA 10A

ARINC 429

Radar Altimeter

GPS Interface

System

Audio Alert

Remote Terminal

I/F Connector

(AFCS Maint. Plug)

KCM 100

Configuration

Module

Aircraft

Static

Port

KS 271C

Roll Servo

KS 270C

Pitch Servo

KS 272C

Trim Servo

Optional Yaw Axis

KS 271C

Yaw Servo

KRG 331 or KRG 332 Rate Gyro

	Optional Dual	Control Wheel Switches
	Control Wheel Switches
	KFC 225 System Diagram

Rev. 0	KFC 225 AUTOMATIC FLIGHT CONTROL SYSTEM	3
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Introduction

Power Application and Preflight Tests

YD

G

P R

ARM VS

ALT SEL

UP

AP

FD

HDG

NAV

APR

REV

ALT

DN

KFC 225

KFC 225 Preflight Test

YD

G

P R

ARM VS

ALT SEL

UP

AP

FD

HDG

NAV

APR

REV

ALT

DN

KFC 225

KFC 225 Preflight Test Complete

A preflight test is performed upon power application to the computer. This test is a sequence of internal checks that validate proper system operation prior to allowing autopilot engagement. The preflight test (PFT) sequence is indicated by “PFT” with an increasing number for the sequence steps. Successful completion of self test is identified by all display segments being illuminated (Display Test), the Flight Director command bars brought into view and the disconnect tone sounding.

NOTE: Following the preflight test, the red P warning on the face of the autopilot may illuminate indicating

that the pitch axis cannot be engaged. This condition should be temporary, lasting no more than 30 seconds. The P will extinguish and normal operation will be available.

4	KFC 225 AUTOMATIC FLIGHT CONTROL SYSTEM	Rev. 0
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System Operation

KFC 225 System Operation

Controls and Displays Operation

18

17

16

15

14

13

12

YD

G

1

P R

ARM VS

ALT SEL

UP

AP

FD

HDG

NAV

APR

REV

ALT

DN

KFC 225

2

3

4

5

6

7

8

9

10

11

Full KFC 225 Three-Axis with Altitude Preselect Display

1.PITCH AXIS, (P ) ANNUNCIA- 4. FLIGHT DIRECTOR (FD )

TOR - When illuminated, indicates failure of the pitch axis and will lead to disengagement of the autopilot. (Will also illuminate during short term vertical accelerations in excess of +1.6g or less than +0.4g which may not cause autopilot disengagement.)

2.ROLL AXIS (R ) ANNUNCIATOR - When illuminated, indicates failure of the roll axis and will disengage the autopilot.

3.AUTOPILOT ENGAGE/DISENGAGE (AP ) BUTTON - When pressed, engages the flight director, autopilot and yaw damper (if installed). If the flight director is not already engaged, the system will engage into the basic wings level (ROL) and pitch (PIT) attitude hold modes. The pitch attitude maintained will be the pitch attitude present at the moment of AP button press. When pressed again, will disengage the autopilot.

MODE SELECTOR BUTTON – When pressed will engage the flight director into the basic roll (ROL) mode which functions as a wing leveler, and into the pitch attitude (PIT) hold mode. The pitch attitude maintained will be the pitch attitude present at the moment of FD button press. When pressed again (and the autopilot is not engaged) will disengage the flight director.

5. HEADING (HDG ) MODE SELECTOR BUTTON - When pressed, will engage the Heading mode, which commands the airplane to turn to and maintain the heading selected by the heading bug on the HSI. A new heading may be selected at any time and will result in the airplane turning to the new heading. Button can also be used to toggle between HDG and ROL modes. This button will engage the flight director.

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System Operation

6.NAVIGATION (NAV ) MODE SELECTOR BUTTON - When pressed, will arm the navigation mode. If the selected navigation sensor is less than 50% deflected when armed, the system will automatically capture. Otherwise the capture point will vary based on needle deflection and closure rate. The mode provides automatic beam capture and tracking of VOR, LOC or GPS as selected for presentation on the HSI. NAV mode is recommended for en route navigation tracking. If pressed when NAV mode is either armed or coupled, will disengage the mode. This button will engage the flight director.

7.APPROACH (APR ) MODE SELECTOR BUTTON - When pressed, will arm the Approach mode. If the selected navigation sensor is less than 50% deflected when armed, the system will automatically capture. Otherwise the capture point will vary based on needle deflection and closure rate. This mode provides automatic beam capture and tracking of VOR, GPS or LOC with Glideslope (GS) on an ILS, as selected for presentation on the HSI. APR ARM will annunciate. If pressed when APR mode is either armed or coupled, will disengage the mode. This button will engage the flight director. (See the NOTE following item 8).

8.BACK COURSE APPROACH (REV ) MODE SELECTOR BUTTON

– (not available when optional ED

461EHSI installed). When pressed, will select the back course approach mode. If the selected navigation sen-

sor is less than 50% deflected when armed, the system will automatically capture. Otherwise the capture point will vary based on needle deflection and closure rate. This mode functions similarly to the approach mode except that the autopilot response to LOC signals is reversed and glideslope is inhibited. This button will engage the flight director.

NOTE: If the opti

onal ED 461

EHSI is installed, front and back course selection is automatic and is dependent upon the relative difference between the airplane heading

and the selected approach course. If the airplane heading differs from the selected course by greater than 105°, REV ARM will automatically annunciate in anticipation of tracking

a localizer back course. If prior to localizer capture the heading changes (ie. during radar vectors or

a procedure turn) and falls within 105° of the selected course, APR ARM will annunciate in anticipation of tracking the localizer front course.

9. ALTITUDE HOLD (ALT ) MODE SELECT BUTTON - When pressed, will engage the Altitude Hold mode. The altitude maintained is the altitude at the moment the ALT button is pressed. If the ALT button is pressed with an established climb or descent rate present, there will be approximately a 10% (of VS rate) overshoot, with the airplane returned positively to the selected altitude. If pressed when ALT hold mode is engaged, will disengage the mode, defaulting to PIT mode. This button will engage the flight director.

6	KFC 225 AUTOMATIC FLIGHT CONTROL SYSTEM	Rev. 0
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System Operation

10.VERTICAL TRIM (UP /DN ) BUTTONS - The response of these buttons is dependent upon the vertical mode present when pressed. If PIT mode is active, successive button presses will move the pitch attitude hold reference either up or down by 0.5° per press, or at the rate of 0.8° per second if held continuously, synchronizing the pitch attitude reference to the current pitch attitude upon release. If VS mode is active, the initial button press will bring up the commanded vertical speed in the display. Subsequent immediate button presses will increment the vertical speed command either up or down at the rate of 100 ft/min per button press, or at the rate of approximately 300 ft/min per second if held continuously. If ALT mode is active, successive button presses will move the altitude hold reference altitude either up or down by 20 feet per press, or if held continuously will command the airplane up or down at the rate of 500 ft/min, synchronizing the altitude hold reference to the actual airplane altitude upon button release. (Note that neither the pitch attitude nor the altitude hold reference is displayed. The display will continue to show the altitude alerter reference.)

11.ROTARY KNOBS - Used to set the altitude alerter/altitude preselect reference altitude. Large (outer) knob changes reference by 1000’s of feet, and the small (inner) knob changes reference by 100’s of feet. When the flight director is engaged, will automatically arm a preselect altitude hold capture.

12.VERTICAL SPEED (VS ) MODE SELECTOR BUTTON – When pressed will engage the vertical speed hold mode. The vertical speed maintained is the vertical speed present at the moment the VS button is pressed. The vertical speed command reference will initially be displayed in place of the altitude alert annunciation, defaulting back in

3seconds to the altitude alerter value. Pressing either the UP or DN button will again cause the vertical speed command reference to be displayed while causing it to increase or decrease. When the VS button is pressed again, it will disengage the vertical speed mode. This button will engage the flight director.

13.ALTITUDE ARM (ARM ) BUTTON - When pressed will toggle altitude arming on or off. When ALT ARM is annunciated, the automatic flight control system will capture the altitude displayed in the Altitude Alerter/Vertical Speed Display (provided the aircraft is climbing or descending to the displayed altitude). ALT ARM mode is engaged automatically whenever the selected altitude is changed via the rotary knobs. Note that the alerter functions are independent of the arming process thus providing full time alerting, even when the flight director is disengaged. This button will engage the flight director.

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