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Revision History and Instructions
ManualKFC 225 AFCS Pilot’s Guide
Revision1, September 2004
Part Number006-18035-0000
This revision incorporates a note further explaining the Altitude Hold
function.
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
NAVHDG
E
12
6
GSGS
3
N
33
30
ı
15
S
21
24
W
VS
YD
G
P R
AP
HDG
FD
APRREV
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
Rev. 0
Apr/99
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
MBIN HG
7
3
29.99
101
6
4
5
B
KEA 346
Servoed
Altimeter
NAV HDG
N
3
3
3
GSGS
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
APRREV
APRREV
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.
4
KFC 225 AUTOMATIC FLIGHT CONTROL SYSTEM
Rev. 0
Apr/99
KFC 225 System Operation
Controls and Displays Operation
System Operation
1617151418
YD
G
P R
1
AP
2410
3
HDG
FD
56789
NAV
APRREV
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
1312
ARM
S
T
L
A
E
L
VS
KFC 225
11
Rev. 0
Apr/99
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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