BendixKing KI 525A User Manual

Pilot’s Guide
KFC 225
Bendix/King
Automatic Flight Control System
®
006-18035-0000 September 2004
N
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: (913) 712-0400.
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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KFC 225 AUTOMATIC FLIGHT CONTROL SYSTEM
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Table of Contents
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KFC 225 AUTOMATIC FLIGHT CONTROL SYSTEM
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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 Apr/99
KFC 225 AUTOMATIC FLIGHT CONTROL SYSTEM
1
Introduction
20
10
102010
20
20
10

General Description

The KFC 225 Three Axis system provides lateral, vertical and optional yaw modes with altitude preselect.
AIR
DH
AIR
ı
NAV HDG
E
12
6
GS GS
3
N
33
30
ı
15
S
21
24
W
VS
YD
G
P R
AP
HDG
FD
APR REV
NAV
ARM
S
E
T
L
L
A
UP
ALT
DN
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
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Introduction
20
20
10
10
102010
20
600 500
6
A/P Master Switch
AP
NAV
REV
ALT
VS
HDG
APR
GS
CAP
GA
YD
ARM
ARM
ALT
TRIM
KA 285
Remote Mode
Annunciator
DH
KI 256 Attitude Gyro
ALT
0
9
1
0,
2
8
ALT
MB IN HG
7
3
29.99
101
6
4
5
B
KEA 346
Servoed
Altimeter
NAV HDG
N
3
3
3
GS GS
6
0 3
E
W
1 2
4
2
1
5
1
2
S
ı
KCS 55A
Compass
System
B
KLN 90B TSO
NAV
CALC
FPL
STAT
MODE
SETUP
TRIP
OTHER
ALT
D
CLR ENT
MSG
Optional
ARINC 429
GPS Interface
OR
Annunciaor
AIR
AIR
ı
OR
OR
NAV D/T ACTV REF CTR
AP
TRIM FAIL
Trim Fail
1 2
N A V
H S I
CRS
GPS
BRT
CRSRCRSR
APT VOR
PULL
NDB
SCAN
INT SUPL
YD
G
P R
AP
FD
0
1
9
8
2
ALT
3
7
ENCODING
4
6
5
KEA 130A
Encoding
Altimeter
CRS
4.
350
120 KT
5
12
N
3
3
3
6
0 3
L O
E
W
C
1
1
4
2
2
1
5
1
2
S
ADF 2
BRT
EHI 40
EFIS
ALTITUDE
O
T
H
S
U
P
Optional KRA 10A
Radar Altimeter
HDG
TST
NM
REF
11. 5
G S
A
R C
330°
HDG
DH
RADAR
X 100 FEET
25
20
15
T
E
S
T
ıı
System
Audio Alert
Remote Terminal
I/F Connector
(AFCS Maint. Plug)
KCM 100
Configuration
Aircraft
Static
Port
Module
KS 271C
Roll Servo
KS 270C
Pitch Servo
KS 272C
Trim Servo
KC 225
Flight Computer
VS
ARM
S
E
T
L
L
A
APR REV
NAV
UP
ALT
DN
KFC 225
Optional Yaw Axis
KS 271C
Yaw Servo
OFF
50
1
2
3
4
5
10
2 3
3 G R K
RATE GYRO
ı
KRG 331
or
KRG 332
Rate Gyro
Optional Dual
Control Wheel Switches
Control Wheel Switches
KFC 225 System Diagram
Rev. 0 Apr/99
KFC 225 AUTOMATIC FLIGHT CONTROL SYSTEM
3
Introduction

Power Application and Preflight Tests

YD
G
P R
AP
HDG
FD
KFC 225 Preflight Test
YD
G
P R
AP
HDG
FD
KFC 225 Preflight Test Complete
NAV
NAV
APR REV
APR REV
VS
ARM
S
E
T
L
L
A
UP
ALT
DN
UP
ALT
DN
ARM
KFC 225
VS
S
E
T
L
L
A
KFC 225
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.
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KFC 225 AUTOMATIC FLIGHT CONTROL SYSTEM
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KFC 225 System Operation

Controls and Displays Operation

System Operation
1617 15 1418
YD
G
P R
1
AP
2 4 10
3
HDG
FD
5 6 7 8 9
NAV
APR REV
ALT
Full KFC 225 Three-Axis with Altitude Preselect Display
1. PITCH AXIS, (P) ANNUNCIA-
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.)
4. FLIGHT DIRECTOR (FD)
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
2. ROLL AXIS (R) ANNUNCIA-
TOR - When illuminated, indicates
failure of the roll axis and will disen-
press. When pressed again (and the autopilot is not engaged) will disen­gage the flight director.
gage the autopilot.
5. HEADING (HDG) MODE
3. AUTOPILOT ENGAGE/DISEN-
GAGE (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 main-
tained will be the pitch attitude pre-
sent at the moment of AP button
press. When pressed again, will dis-
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.
engage the autopilot.
UP
DN
13 12
ARM
S
T
L
A
E
L
VS
KFC 225
11
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KFC 225 AUTOMATIC FLIGHT CONTROL SYSTEM
5
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 461 EHSI installed). When pressed, will select the back course approach mode. If the selected navigation sen-
6
KFC 225 AUTOMATIC FLIGHT CONTROL SYSTEM
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 optional 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.
Rev. 0
Apr/99
System Operation
10. VERTICAL TRIM (UP/DN) BUT-
TONS - The response of these but-
tons 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, syn-
chronizing the pitch attitude refer-
ence 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 but-
ton presses will increment the verti-
cal 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 refer-
ence is displayed. The display will
continue to show the altitude alerter
reference.)
11. ROTARY KNOBS - Used to
set the altitude alerter/altitude prese-
lect 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 3 seconds 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) BUT-
TON - 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.
Rev. 0
Apr/99
KFC 225 AUTOMATIC FLIGHT CONTROL SYSTEM
7
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