Honeywell Bendix/King KFC 225 Pilot's Manual
KFC 225
Pilot’s Guide
Bendix/King
®
Automatic Flight Control System
006-18035-0000
Apr 99
N
WARNING
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COPYRIGHT NOTICE
Copyright ©1999 Honeywell Internationall Inc.
All rights reserved.
Reproduction of this publication or any portion thereof by any means without
the express written permission of Honeywell Internatinal Inc. is prohibited.
For further information contact the Manager, Technical Publications;
Honeywell, One Technology Center, 23500 West 105th Street, Olathe,
Kansas 66061.
Telephone: (913) 782-0400.
KFC 225 AUTOMATIC FLIGHT CONTROL SYSTEM
Table of Contents
i
Rev. 0
Apr/99
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
KFC 225 AUTOMATIC FLIGHT CONTROL SYSTEM
Introduction
1
Rev. 0
Apr/99
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.
Table of Contents
ii
KFC 225 AUTOMATIC FLIGHT CONTROL SYSTEM
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Apr/99
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KFC 225 AUTOMATIC FLIGHT CONTROL SYSTEM
Introduction
3
Rev. 0
Apr/99
KA 285
Remote Mode
Annunciator
OR
AIR
ı
DH
20
20
10
10
102010
20
AIR
KI 256 Attitude Gyro
KS 271C
Roll Servo
KS 270C
Pitch Servo
KS 272C
Trim Servo
TRIM
FAIL
AP
KCS 55A
Compass
System
OR
N
GS GS
33
30
W
24
21
S
15
12
E
6
3
ı
NAV HDG
EHI 40
EFIS
TST
BRT
N
A
V
1
2
HDG
REF
ADF 2
L
O
C
1
12
CRS
350
4.
5
NM
11.
5
330°
G
S
N
3
3
3
0
W
24
2
1
S
1
5
1
2
E
6
3
CRS
A
R
C
H
S
I
120 KT
KEA 346
Servoed
Altimeter
KEA 130A
Encoding
Altimeter
OR
ALT
0
1
2
3
4
5
6
7
8
9
29.99
MB IN HG
ALT
600
500
0,
B
6
101
ENCODING
0
1
2
3
4
5
6
7
8
9
ALT
Optional KRA 10A
Radar Altimeter
System
P
U
S
H
T
O
T
E
S
T
DH
1
2
3
4
5
10
15
20
25
X 100 FEET
OFF
RADAR
ALTITUDE
50
ıı
Optional
ARINC 429
GPS Interface
NAV
FPL
MODE
TRIP
CALC
STAT
SETUP
OTHER
NAV
D/T
ACTV
REF
CTR
APT
VOR
NDB
INT
SUPL
CRSRCRSR
ALT
CLR ENT
PULL
SCAN
KLN 90B TSO
B
GPS
BRT
D
MSG
Optional Dual
Control Wheel Switches
Control Wheel Switches
Aircraft
Static
Port
KCM 100
Configuration
Module
Audio Alert
A/P Master Switch
Trim Fail
Annunciaor
Remote Terminal
I/F Connector
(AFCS Maint. Plug)
KC 225
Flight Computer
AP
VS
ARM
G
KFC 225
HDG
NAV
APR REV
ALT
FD
DN
UP
YD
P R
A
L
T
S
E
L
HDG
AP
YD
APR
NAV
ARM
GS
REV
ARM
CAP
ALT
ALT
GA
VS
TRIM
KS 271C
Yaw Servo
KRG 331
or
KRG 332
Rate Gyro
Optional Yaw Axis
ı
K
R
G
3
3
2
RATE GYRO
KFC 225 System Diagram
Introduction
2
KFC 225 AUTOMATIC FLIGHT CONTROL SYSTEM
Rev. 0
Apr/99
General Description
The KFC 225 Three Axis system provides lateral, vertical and optional yaw
modes with altitude preselect.
GS GS
N
33
30
W
24
21
S
15
12
E
6
3
ı
NAV HDG
AP
VS
ARM
G
KFC 225
HDG
NAV
APR REV
ALT
FD
DN
UP
YD
P R
A
L
T
S
E
L
AIR
ı
DH
20
10
102010
20
20
10
AIR
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.
KFC 225 AUTOMATIC FLIGHT CONTROL SYSTEM
System Operation
5
Rev. 0
Apr/99
AP
VS
ARM
G
KFC 225
HDG
NAV
APR REV
ALT
FD
DN
UP
YD
P R
A
L
T
S
E
L
1
2 4 10
Full KFC 225 Three-Axis with Altitude Preselect Display
11
13 12
5 6 7 8 9
1617 15 1418
3
KFC 225 System Operation
Controls and Displays Operation
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.)
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.
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
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.
Introduction
4
KFC 225 AUTOMATIC FLIGHT CONTROL SYSTEM
Rev. 0
Apr/99
AP
VS
ARM
G
KFC 225
HDG
NAV
APR REV
ALT
FD
DN
UP
YD
P R
A
L
T
S
E
L
KFC 225 Preflight Test Complete
AP
VS
ARM
G
KFC 225
HDG
NAV
APR REV
ALT
FD
DN
UP
YD
P R
A
L
T
S
E
L
KFC 225 Preflight Test
Power Application and Preflight Tests
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.
System Operation
6
KFC 225 AUTOMATIC FLIGHT CONTROL SYSTEM
Rev. 0
Apr/99
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-
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.
KFC 225 AUTOMATIC FLIGHT CONTROL SYSTEM
System Operation
7
Rev. 0
Apr/99
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
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) 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.
KFC 225 AUTOMATIC FLIGHT CONTROL SYSTEM
System Operation
9
Rev. 0
Apr/99
will not operate. If one switch fails or
is moved and held for 3 seconds, the
trim monitoring system will detect a
switch failure resulting in a PT
annunciation on the autopilot display
and the disabling of the electric trim
system. Use of manual electric trim
during autopilot operation will disengage the autopilot. (Located on the
pilot’s control wheel.)
21. CONTROL WHEEL STEERING
(CWS) MODE BUTTON (not shown)
- When pressed and held, disengages the pitch, roll, yaw, and pitch
trim clutches allowing the pilot to
maneuver the airplane by hand.
Pressing the CWS button will also
sync the automatic flight control system PIT, ROL, ALT or VS commands to the actual attitude, altitude
or vertical speed present at the time
the button is released. ROL will
maintain wings level if CWS is
released at less than 6° bank angle.
(Located on the left horn of the
pilot’s control wheel.)
22. GO AROUND (GA) MODE
BUTTON (not shown) – When
pressed will engage the flight director in a pitch up attitude and wings
level (ROL mode). GA will disengage the autopilot, and cancel all
armed modes including an armed
altitude preselect. Lateral modes
such as HDG or NAV ARM may
subsequently be added. The autopilot may subsequently be engaged.
Modification to the commanded pitch
attitude such as through the UP/DN
button or CWS, etc. will cancel GA
and revert to pitch altitude hold.
(Located on the engine throttle).
System Operation
8
KFC 225 AUTOMATIC FLIGHT CONTROL SYSTEM
Rev. 0
Apr/99
14. SELECTED ALTITUDE/VERTICAL SPEED DISPLAY - Normally
displays the selected altitude. The
display indicates the reference vertical speed in FPM for 3 seconds after
the CWS button or the UP or DN
button is pressed and the VS mode
is engaged.
15. ALTITUDE ALERT (ALERT)
ANNUNCIATION - Illuminates as a
solid alert in the region from 1000 to
200 feet from the selected altitude if
the airplane was previously outside
of this region. Flashes (1) for two
seconds the first time the airplane
crosses the selected altitude and (2)
flashes continuously in the 200 to
1000 feet region if the airplane was
previously inside of this region (i.e.
at the selected altitude). An aural
alert consisting of five short tones is
associated with the visual alerting.
This aural alert occurs 1,000 feet
before a selected altitude while
approaching it and 200 feet after
leaving a selected altitude.
16. PITCH TRIM (PT) ANNUNCIATION - A flashing PT with an
accompanying arrow head is an indication that the request for auto trim
has lasted longer than 16 seconds.
A solid PT without an arrowhead is
an indication of a pitch trim fault. A
trim runaway will generate the solid
PT annunciation, a remote TRIM
FAIL annunciation and a continuous
alert tone. Refer to the EMERGENCY PROCEDURES in the airplane Flight Manual Supplement for
proper response to a pitch trim fault.
17. PITCH AND ROLL MODE,
AUTOPILOT AND YAW DAMPER
ANNUNCIATIONS - Displays the
active flight director pitch modes
(PIT, VS, ALT ARM, ALT CAP, ALT,
GS ARM, GS, GA, and roll modes
(ROL, HDG, NAV ARM, NAV, APR
ARM, APR, REV ARM, REV).
Displays when the autopilot (AP)
and yaw damper (YD) are engaged.
Also displayed will be a flashing AP
annunciation (5 seconds) at each
autopilot disconnect accompanied
by an aural tone (for 2 seconds).
18. YAW DAMPER (YD) BUTTON
(optional) – When pressed will
engage or disengage the yaw
damper independent of autopilot
operation. (The yaw damper
engages automatically when the
autopilot is engaged; however, the
yaw damper may then be disengaged or reengaged as desired.)
19. AUTOPILOT DISCONNECT
(AP DISC/TRIM INTER) SWITCH
(not shown) - When pressed will
disengage the autopilot and yaw
damper if installed, and interrupt
electric trim power. (Located on the
left horn of the pilot’s control wheel.
The switch is red in color.) May also
disengage the flight director depending on how the system is configured.
20. MANUAL ELECTRIC TRIM
SWITCHES (not shown) - When
both switches are pressed in the
same direction, will activate pitch
trim in the selected direction. If only
one switch is moved, the trim system
23. OMNI BEARING SELECT
KNOB - Selects the desired course
to be tracked by the autopilot
(Located on the HSI.)
24. HEADING SELECT KNOB Positions the heading bug on the
compass card (Located on the HSI.)
25. TRIM FAIL ANNUNCIATOR
(not shown) - Illuminates whenever
the automated preflight self-test
detects a pitch trim fault or a continuous monitoring system detects a
pitch trim fault in flight. (Located on
the instrument panel. The annunciator is red in color.) Refer to the
EMERGENCY PROCEDURES in
the airplane Flight Manual
Supplement for proper response to
a pitch trim fault.
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