CESSNA CARAVAN 208 SERIES
MAINTENANCE SCHEMATIC MANUAL
SECOND EDITION
Revision 0
NOTICE: These commodities, technology or software were exported
from the United States in accordance with the Export Administration
Regulations. Diversion contrary to U.S. law is prohibited.
Courses for the Cessna Caravan 208 aircraft are taught at the following FlightSafety learning center:
FlightSafety International
Wichita Cessna Maintenance Learning Center
2021 S. Eisenhower
Wichita, Kansas 67209-1960
Phone: (316) 361-3900
Toll-Free: (800) 491-9796
FAX: 316-361-3899
Copyright © 2016 FlightSafety International, Inc.
Unauthorized reproduction or distribution is prohibited.
All rights reserved.
ii
INSERT LATEST REVISED PAGES, DESTROY SUPERSEDED PAGES
LIST OF EFFECTIVE PAGES
Dates of issue for original and changed pages are:
Original..................... 0........... April 2016
NOTE:
For printing purposes, revision numbers in footers occur at the bottom of every page that
has changed in any way (grammatical or typographical revisions, reflow of pages, and other
changes tha­­t do not necessarily affect the meaning of the manual).
THIS PUBLICATION CONSISTS OF THE FOLLOWING:
Page
No.
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No.
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iii
Introduction
01
ATA 2200
02
5-12
Aircraft General
NOTICE
The material contained in this training manual is based on information
­obtained from the aircraft manufacturer’s pilot manuals and maintenance
manuals. It is to be used for familiarization and training purposes only.
At the time of printing it contained then-current information. In the event of
conflict between data provided herein and that in publications issued by the
manufacturer or the applicable regulatory agency, that of the manufacturer
or the regulatory agency shall take precedence.
We at FlightSafety want you to have the best training possible. We welcome
any suggestions you might have for improving this manual or any other aspect
of our training program.
Standard Practices
20
Air Conditioning
21
Autoflight
22
Communications
23
Electrical Power
24
Equipment and Furnishings
25
Fire Protection
26
Flight Controls
27
Fuel
28
Ice and Rain Protection
30
Indicating and Recording
31
v
Landing Gear
32
Lights
33
Navigation
34
Oxygen
35
Pneumatics
36-37
Structures
51-57
Propellers
61
Powerplant
71-80
71-80
vii
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
CONTENTS
CONTENTS
Page
Page
INTRODUCTION......................................................................................................................... 1-1
ICE AND RAIN PROTECTION................................................................................................. 30-1
ATA 2200....................................................................................................................................... 2-1
General................................................................................................................................. 30-1
Maintenance Publications........................................................................................................ 2-1
INDICATING AND RECORDING............................................................................................. 31-1
AIRCRAFT GENERAL................................................................................................................ 5-1
General................................................................................................................................. 31-1
General Organization.............................................................................................................. 5-1
LANDING GEAR....................................................................................................................... 32-1
STANDARD PRACTICES.......................................................................................................... 20-1
General................................................................................................................................. 32-1
General................................................................................................................................. 20-1
LIGHTS....................................................................................................................................... 33-1
AIR CONDITIONING................................................................................................................ 21-1
General................................................................................................................................. 33-1
General................................................................................................................................. 21-1
NAVIGATION............................................................................................................................. 34-1
AUTO FLIGHT............................................................................................................................ 22-1
General................................................................................................................................. 34-1
General................................................................................................................................. 22-1
OXYGEN..................................................................................................................................... 35-1
Description........................................................................................................................... 22-2
Oxygen Systems................................................................................................................... 35-1
COMMUNICATIONS................................................................................................................. 23-1
PNEUMATICS/VACUUM.......................................................................................................... 36-1
General................................................................................................................................. 23-1
Pneumatic System—General................................................................................................ 36-1
ELECTRICAL POWER.............................................................................................................. 24-1
Vacuum System—General................................................................................................... 36-1
General................................................................................................................................. 24-1
STRUCTURES............................................................................................................................ 51-1
EQUIPMENT & FURNISHINGS............................................................................................... 25-1
General................................................................................................................................. 51-1
Flight Compartment - General............................................................................................. 25-1
PROPELLERS............................................................................................................................. 61-1
FIRE PROTECTION................................................................................................................... 26-1
General................................................................................................................................. 61-1
Fire Detection System.......................................................................................................... 26-1
POWERPLANT........................................................................................................................... 71-1
FLIGHT CONTROLS................................................................................................................. 27-1
General................................................................................................................................. 71-1
General................................................................................................................................. 27-1
FUEL............................................................................................................................................ 28-1
General................................................................................................................................. 28-1
Revision 0
FOR TRAINING PURPOSES ONLY
ix
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
x
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
ILLUSTRATIONS
Figure
Title
ILLUSTRATIONS
Page
Figure
Title
Page
1-1
Cessna Caravan 208 King................................................................................................. 1-2
24-4
G1000 Overview—Typical Electrical System............................................................... 24-5
1-2
Cessna Caravan 208 G530................................................................................................. 1-3
24-5
1-3
Cessna Caravan 208 G1000............................................................................................... 1-4
Non-G1000 Overview—
Typical Electrical System (with Optional Standby Electrical System).......................... 24-6
2-1
ATA 2200 Overview......................................................................................................... 2-2
24-6
Power Distribution Box.................................................................................................. 24-8
2-2
Electrical Symbols............................................................................................................. 2-3
24-7
Electrical Circuit........................................................................................................... 24-10
5-1
Zones Overview................................................................................................................. 5-2
24-8
Standby Alternator Circuit........................................................................................... 24-24
5-2
Lifting and Shoring............................................................................................................ 5-3
24-9
Volt—Ammeter............................................................................................................ 24-26
21-1
Bleed Air Heat................................................................................................................ 21-2
25-1
Pilot and Copilot Seats................................................................................................... 25-2
21-2
Heating System Overview.............................................................................................. 21-3
25-2
ME 406 ELT................................................................................................................... 25-3
21-3
Air Conditioning Components Location........................................................................ 21-4
26-1
Fire Warning Circuit....................................................................................................... 26-2
21-4
Ventilation Blowers........................................................................................................ 21-5
27-1
Aileron Control System.................................................................................................. 27-2
21-5
Vapor Cycle AC Electrical ............................................................................................ 21-6
27-2
Elevator Control System................................................................................................. 27-3
21-6
Bleed Air Heat................................................................................................................ 21-7
27-3
Rudder System................................................................................................................ 27-4
22-1
Garmin GFC 700 Interconnect....................................................................................... 22-2
27-4
Flap Drive System.......................................................................................................... 27-5
22-2
KFC—225 Schematic..................................................................................................... 22-3
27-5
Flap System Components............................................................................................... 27-6
22-3
King KAP 150—3 Axis Autopilot................................................................................. 22-4
27-6
Legacy Series Normal Flap System............................................................................... 27-7
22-4
King KFC 150 —3 Axis Autopilot................................................................................ 22-5
27-7
Legacy Series Standby Flap System............................................................................... 27-8
23-1
208 King Audio Control System.................................................................................... 23-2
27-8
Caravan EX Standby Flap System................................................................................. 27-9
23-2
208 G1000 Audio Panel Controls (GMA 1347)............................................................. 23-3
28-1
Caravan G1000 Fuel System General Overview............................................................ 28-2
23-3
G1000 Communications Block Diagram....................................................................... 23-4
28-2
Non-G1000 Fuel Select and Warning System................................................................ 28-4
23-4
G1000 Navigation/Communication Data Paths............................................................. 23-5
28-3
G1000 Fuel Select and Warning..................................................................................... 28-7
24-1
Electrical Switch Panel and Annunciator Panel............................................................. 24-2
28-4
Fuel Reservoir.............................................................................................................. 28-12
24-2
Power Distribution—Battery Power............................................................................... 24-3
28-5
Auxiliary Fuel Pump.................................................................................................... 28-13
24-3
Power Distribution—External Power............................................................................. 24-4
28-6
Non-G1000 Fuel Quantity Indicating........................................................................... 28-15
28-7
G1000 Fuel Quantity Indicating................................................................................... 28-17
Revision 0
FOR TRAINING PURPOSES ONLY
xi
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
ILLUSTRATIONS
Figure
Title
ILLUSTRATIONS
Page
Figure
Title
Page
30-1
TKS Ice System Overview............................................................................................. 30-2
61-4
Reversing Propeller Engine Controls (Full Reverse)..................................................... 61-8
30-2
Pneumatic De-Ice System Overview.............................................................................. 30-3
71-1
PT6A Small Turboprop.................................................................................................. 71-2
30-3
Dual Element Windshield Anti-Ice................................................................................ 30-4
71-2
Compressor Bleed Valve—Pre SB 1588........................................................................ 71-4
30-4
Single Element Windshield Anti-Ice.............................................................................. 30-5
71-3
Compressor Bleed Valve—Post SB 1588...................................................................... 71-5
30-5
De-Ice Boot System........................................................................................................ 30-7
71-4
Lubrication System Overview (PT6A-114 & PT6A-114A).......................................... 71-6
30-6
TKS Anti-Ice System with G1000................................................................................. 30-9
71-5
Lubrication System Overview (PT6A-140) .................................................................. 71-8
30-7
Legacy Series Propeller Anti-Ice System..................................................................... 30-10
71-6
Thermostatic Bypass & Check Valve Overview (PT6A-140)....................................... 71-9
30-8
G1000 Prop Anti-Ice System........................................................................................ 30-12
71-7
Oil Filter Components.................................................................................................. 71-10
31-1
Annunciator Panels......................................................................................................... 31-2
71-8
Engine Controls............................................................................................................ 71-11
31-2
G1000 Invalid Display Fields......................................................................................... 31-5
71-9
Fuel Pump Overview.................................................................................................... 71-12
32-1
Main Landing Gear......................................................................................................... 32-2
71-10
Fuel Control Unit—Cross Section (PT6A-114/114A)................................................. 71-13
32-2
Drag Link Spring............................................................................................................ 32-3
71-11
Fuel Control System (PT6A-140)................................................................................ 71-14
34-1
Avionics Systems (King)................................................................................................ 34-2
71-12
Engine Indicating System............................................................................................. 71-16
34-2
Avionics Systems (G530)............................................................................................... 34-3
71-13
Inter Turbine Temperature Indicator............................................................................ 71-17
34-3
Avionics Systems (G1000)............................................................................................. 34-4
71-14
T5 Wiring Diagram...................................................................................................... 71-18
34-4
G1000 MFD Power-Up Page......................................................................................... 34-5
34-5
Garmin G1000 Integrated Avionics Architecture.......................................................... 34-6
34-6
G1000 Flight Instrument Data Paths.............................................................................. 34-7
34-7
G1000 Navigation/Communication Data Paths............................................................. 34-8
35-1
Oxygen System Overview.............................................................................................. 35-2
36-1
Model 208B Vacuum System Overview........................................................................ 36-2
61-1
Hartzell Propeller............................................................................................................ 61-2
61-2
McCauley Propeller........................................................................................................ 61-3
61-3
Propeller Governor......................................................................................................... 61-4
xii
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
TABLES
Table
Title
Page
31-1
Non-G1000 Annunciators.............................................................................................. 31-3
31-2
G1000 CAS Messages.................................................................................................... 31-6
Revision 0
FOR TRAINING PURPOSES ONLY
xiii
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
CHAPTER 1
INTRODUCTION
INTRODUCTION
This training manual provides a description of the major airframe and engine systems on the Cessna 208 Caravan aircraft. This
information is an instructional aid only; it does not supersede, nor is it meant to substitute for, any of the manufacturer’s maintenance
or operating manuals. This material has been prepared from basic design data and all subsequent changes in aircraft appearance or
system operation will be covered during academic training and subsequent revisions to this manual.
Revision 0
FOR TRAINING PURPOSES ONLY
1-1
01
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
FOR
N
30 60
E 120 150
STEER
359 028 059 090 120 148
N 24 21 S
FOR
S 210 240 W 300 330
STEER
176 207 238 270 302 330
ON A
NO
01
MAX
RPM TORQUE
1900
1865
1800
1970
1700
1970
1600
1970
ANNUN PANEL
LAMP
NIGHT
FIRE
DETECT
GENERATOR
OFF
EMERGENCY
POWER LEVER
AUX FUEL
PUMP ON
FUEL PRESS
LOW
VACUUM
LOW
RESERVOIR
FUEL LOW
LEFT
FUEL LOW
RIGHT
FUEL LOW
STBY ELEC
PWR ON
BATTERY
OVERHEAT
BATTERY
HOT
CHIP
DETECTOR
STBY ELEC
PWR INOP
DOOR
WARNING
DAY
STARTER
ENERGIZED
IGNITION
ON
WINDSHIELD
ANTI-ICE
5
10
TORQUE
0
FUEL SELECT
OFF
FT-LB
X100
DE-ICE
PRESSURE
8
15
20
25
12
16
4
20
0 PROP
T.O
OFF
3456
12
ITT
7
¡C x 100
ST.LIM
1090¡
10
11
RPM X 100
40
Ng
%R
20
8
0
9
9
120
60
PSI
40
100
2
6
5
-40
4
4
3
4
0
4
2
E
2
1
E
PPHX100 5
0
3
7
2
3
1FUEL FLOW
140
110
55
¡C 10
OIL
85
80
1
8
F
N208FS
TEST
OIL PRESS
LOW
OF
TEST
ENGINE
FIRE
VOLTAGE
LOW
BA
5 6 7
8
8 10
6 FUEL
9
12
14
16
QTY
11
4
3
4
2
E
2
1
E
GA
LLONS X 10
BA
SE LBSX100 GAL
D ON
6.7 LBS
5 6 7
8
8 10
6 FUEL
9
12
14
16
QTY
11
SE LBSX100 GAL
D ON
6.7 LBS
AIR
S
15
12
--.- NM' - - - KT - - MIN
N1
OFF
HLD
.5
VERTICAL
SPEED
1
2
3
6
E
ON
MIC
PITOT/STATIC
HEAT
2
S
OB
TO
NAV
DH
MSG
V
ENG S
0
CCW
1
2
RADAR ALT
X 100 FEET
2 MIN TURN
D.C. ELEC.
FR
D
2:3 1
BFO
FRQ
CAL
SET
>CLR
AIRSPEED
CRSR
PULL SCAN
ENT
ADF
FLT
ET
FLT
FRQ
ET
SET
IDT
FL
80
140
BRT
1
2
0
0
7
100
0
FEET
1
ALTITUDE
2
29.7
29.8
6
PULL
FOR
QUICK
ER T
EC
100
4
5
3
0 0 0 1 9
ON ALT
TST
V
L
8888
ALT ON R
GND SBY
TST
SBY
GND
W 30
24
R
ON
ALT
OFF
PUSH
VFR
2 MIN TURN
D.C. ELEC.
SBY
OFF
RNG
8
TOTAL HOURS
SBY
OFF
ON
TST
0
80
0
0
OFF
VFR
888
120
2
1
VOL
RST
1200
SBY
9
60
240 40
160
STBY / TIMER
BFO
40
KNOTS
200
180
OTH
KT 71 TSO
VACUUM
.5
1
0
.5
1
VERTICAL
SPEED
FT/MIN
X 1000
2
VENT
PULL ON
3
2
PUSH
XPDR 1
10
A
ARM L
T
SET
3,000
FT
RNG
VP
PULL
VS
60
MAP
ASSURE THAT SEAT IS LOCKED IN POSITION
PRIOR TO TAXI, TAKEOFF, AND LANDING.
FAILING TO PROPERLY LATCH SEAT AND HEED
THE SAFETY INSTRUCTIONS CAN RESULT IN
BOTH INJURY OR DEATH.
TRK
20
3
5
WARNING
XPDR 2
TRK
40
TEST
NAV
4
UP
PHONE
WARNING
DN
GAIN
PULL STAB OFF
FD
ALT
HDG
ALT
HDG
GS
NAV
APR
BC
NAV
APR
BC
KFC 150
FD
TRIM
TEST
ASSURE THAT ALL CONTAMINANTS, INCLUDE
WATER, ARE REMOVED FROM FUEL AND ALL
SYSTEM BEFORE FLIGHT. FAILURE TO AS????
INSTRUCTIONS AND OWNER ADVISORIES ????
TO FLIGHT CAN RESULT IN BODILY INJURY
DEATH.
AP
MIC
AP
ENG
CABIN
STALL
HEAT
ON
DEICE/ANTI-ICE
WING
W/S
LIGHT
PROP
L FLT PANEL
L FLOOD
BOOT
PRESS
AUTO
YAW
DAMP
LOCK
R FLT PANEL
R FLOOD
INERTIAL SEPARATOR
BYPASS-PULL
NORMAL-PUSH
OFF
LWR PANEL/
PED/OVHD
SW/CKT BKR
ALT STATIC AIR
PULL ON
OFF
FPL
NRST
IDT
NAV
PULL
RAD
PULL
IDENT
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POWER
ALT
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KT 79 TSO
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MANUAL
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ACT
USE
071
068
USE
KX 165 TSO
USR
KR 87 TSO
ADF
117.90
STBY
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323
ANT
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RAD
123.25
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STBY / RAD
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128.55
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KLN 89B TSO
GPS
¡¡¡¡¡¡¡¡¡¡¡
Alt 1400ft
OBS ---¡
Pass Ok?
T
GPS
WAYPOINT
RIGHT
LDG
ON
START
VOR
TIL
SLAVE
34.5 nm
Baro:30.00"
RMI 130¡
ANNUN ON
OFF ON
CW
ARM ACTV
R
KMA 24 TSD
068
USE
Wx
WxA
L
COM 1 COM 2
TEL
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EXT
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COMM
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LIGHTS BRT
BUS
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117.90
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UP
PHONE
MKR
MIC
123.25
KX 165 TSO
GS
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24
21
3
FT/MIN
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USE
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S
1
.5
0
1 COM 2
128.55
29.8
15
GS
TEL
3
SEAT
BELT
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LO
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E
N
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T
S
T
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20
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N
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OVERSPEED
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M
33
21
ALT
200
-50
LIGHTS
TAXI/
RECOG
ON
CAP
O
33
A
D
F
GEN
150
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5
ALT
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A
30
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D
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30
4
ENCODING
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25
0
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3
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BC
DC
33 N
5
0
7
100
8
100
15
10
VOLTS 20
1005
30
50
IN.Hg
AP
HDG
7
GS
AMPS
2
6
SUCTION
IN HG
VENT
PULL ON
1
ALT
1010
mb
FEET
S 21
10
20
9
MP
H
10
20
8
6
15k
20k
25k
30k
20
10
3
5
4
3
20
10
15
80
140
120
2
MP
H
160
30
PROP ANTI-ICE
AMPS
DH
60
E 12
5
0
100
40
6
6
KNOTS
240 40
H
7
180
MP
QUARTZ
3
4
H
10 20
2
MP
0
200
CLOCK
E
L
T
RESET
MAX WT MANEUVER SPEED 148 KIAS
SEE POH FOR OTHER WEIGHTS
AIRSPEED
10
9
8
11 12 1
ON
A
U
T
O
GA
LLONS X 10
BATTERY
CABIN HEAT
AIR CONDITIONING
ENG INST
RADIO
AC FANS
AFT
HIGH
LEFT
COOL
RIGHT
TEMP
HOT
BLEED AIR HEAT
ON
MIXING AIR
GND-PULL
FLT-PUSH
AFT CABIN-PULL
FWD CABIN-PUSH
DEFROST-PULL
FWD CABIN-PUSH
OFF
PARKING
BRAKE
PULL
OFF
LOW
VENTILATE
ON
RESET
NORM
ON
OFF
TRIP
FUEL
BOOST
GENERATOR
ON
ON
OFF
NORM
MIC
START
A/P DISC
TRIM INTER
OFF
STBY PWR
TRIM
DN
CWS
TRIM
UP
MOTOR
IGNITION
STARTER
1 - ON - 2
Cessna
LEFT
TURN/
BANK
ANNUN
PANEL
GEN
CONT
GEN
FIELD
5
5
5
5
15
ANNUN
PANEL
STALL
WARN
AIR
COND
CONT
T
R
I
M
MAP LIGHT
LO
HI
0705028-3
30
40
10
10
BUS
2
PWR
STBY
PWR
LEFT
VENT
BLWR
RIGHT
VENT
BLWR
30
40
BUS
1
PWR
FIRE
DET
30
5
BUS
2
PWR
ITT
GAGE
30
BUS
1
PWR
5
FUEL
TOTAL
FUEL
FLOW
5
FUEL RIGHT
AUX
CONT TURN
FUEL
PUMP HEATER BANK
10
10
5
10
LEFT
FUEL
QTY
OIL
TEMP
BLEED
AIR
HEAT
AFT
VENT
BLWR
W/S
W/S
LEFT
PITOT ANTI-ICE ANTI-ICE
CONT
HEAT
5
5
5
RIGHT
FUEL
QTY
AIR
SPEED
WARN
PROP
O-SPD
TEST
20
5
LEFT STROBE BEACON MAP
LIGHT LIGHT LIGHT
LDG
LIGHT
DE-ICE
BOOT
5
INST
WING
LIGHT ICE DET
LIGHT
20
15
30
10
5
10
5
5
RIGHT
LDG
LIGHT
TAXI
LIGHT
NAV
LIGHT
RADIO
FLOOD
LIGHT
RH
ATT
GYRO
ENC
ALTM
30
10
15
10
5
5
2
XPDR
1
10
5
COM/NAV
2
XPDR
2
5
2
5
AVIONICS BUS 2
ADF
DME
2
15
T.
O.
5
NOSE
UP
P
R
O
P
P
O
W
E
R
R
P
M
I
D
L
E
I
D
L
E
N
O
R
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A
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E
L O
N
C
O
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D
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T
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O
N
M
I
N
UP
H I
I D
G L
H E
L I
OD
L
WE
-20
100
40
-40
C
-60
C
U
T
O
F
F
60
120
140
F
10¡
1
5
0
20¡
F
U
L
L
MAX
CAUTION
STBY FLAP MOTOR
DOWN
NORMAL
1
2
5
F
L
A
P
S
K
I
A
S
USE BETA AND REVERSE ONLY
WITH ENGINE RUNNING AND
PROPELLER OUT OF FEATHER
UP
AILERON TRIM
L
R
5
80
20
-20
-40
F
E
A
T
H
E
R
B
ER
TE
AV
E
R
S
E
60
0
0
1
7
5
STBY
FUEL SHUTOFF
PULL OFF
TORQUE
IND
SEAT
BELT
SIGN
30
AVIONICS BUS 1
WX
ADF
DG
RADAR
1
NOSE
DOWN
RIGHT PROP PROP
PITOT ANTI-ICE ANTI-ICE
CONT
HEAT
BUS
2
PWR
COM/NAV
1
2
5
15
P
O
W
E
R
M
A
X
5
NOSE
L
RMI
AUD/
MKR
A/P
FD
ELEV
TRIM
2
5
10
5
RNAV
RADIO
ALT
AVN
FAN
AUDIO
AMP
ENGINE
FIRE
OIL PRESS
LOW
GENERATOR
OFF
EMERGENCY
POWER LEVER
AUX FUEL
PUMP ON
FUEL PRESS
LOW
VOLTAGE
LOW
VACUUM
LOW
RESERVOIR
FUEL LOW
LEFT
FUEL LOW
RIGHT
FUEL LOW
STBY ELEC
PWR ON
BATTERY
OVERHEAT
BATTERY
HOT
CHIP
DETECTOR
STBY ELEC
PWR INOP
DOOR
WARNING
STARTER
ENERGIZED
RUD TRIM
NOSE
R
IGNITION
ON
FUEL SELECT
OFF
WINDSHIELD
ANTI-ICE
V
E
N
T
FAN/OP
EN
AN
OPEN/F
OFF
O
X
Y
G
E
N
A
I
R
CLOSE
DE-ICE
PRESSURE
PSI
5
START
CONT
M
A
X
V
E
N
T
A
I
R
MADE IN USA
15
IGN
M
A
X
1000
500 1500
2000
STBY
FLAP
MOTOR
40
20
E
M
E
R
G
E
N
C
Y
OXYGEN
SUPPLY PRESSURE
STDBY FLAP
PWR MOTOR
Caravan I
E
L
E
V
A
T
O
R
0
BUS
1
PWR
Cessna
Caravan I
OFF
AVIONICS
USE NO
OIL
AVIONICS AVIONICS
BUS TIE
STBY
PWR
CLOSE
ON
Cessna
YAW
GYRO
5
1
1
2
5
5
5
OFF
2
FT
LE
CABIN HEAT
FIREWALL SHUTOFF
PULL OFF
OFF
FUEL TANK
SELECTORS
ON
165
GAL
HT
5
GPS/
LORAN
RIG
10
FUEL
SEL
WARN
ON
165
GAL
332 GAL WITH BOTH TANKS ON
MAXIMUM FUEL UNBALANCE IN FLIGHT 200 LBS
Figure 1-1. Cessna Caravan 208 King
1-2
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
N
FOR
30 60
E 120 150
STEER
359 028 059 090 120 148
N 24 21
FOR
S 210 240 W 300 330
STEER
176 207 238 270 302 330
AUX FUEL
PUMP ON
FUEL PRESS
LOW
LEFT
FUEL LOW
RIGHT
FUEL LOW
STBY ELEC
PWR ON
SPARE
SPARE
CHIP
DETECTOR
STBY ELEC
PWR INOP
DOOR
WARNING
DAY
STARTER
ENERGIZED
IGNITION
ON
WINDSHIELD
ANTI-ICE
10
15
5 TORQUE
20
0
FUEL SELECT
OFF
FT-LB
X 100
DE-ICE
PRESSURE
12
8
16
4
TO
20
0 PROP
25
OFF
12
3456
40
ITT
7
°C X 100
ST.LIM
1090°
10
11
RPM X 100
MAX WT MANEUVER SPEED 148 KIAS
SEE POH FOR OTHER WEIGHTS
120
60
Ng
0
9
1
8
6
AIRSPEED
DISCONNECT AUTOPILOT AT FIRST INDICATION OF ICE
ACCRETION.
QUARTZ
3
4
5
160
80
140
120
30
5
SENS
TERR
TERR
INHIB
TEST
COM1
COM2
COM3
NAV1
COM1
MIC
COM2
MIC
COM3
MIC
COM
1/2
HDG
gs
TERR N/A
TERR
INHIB
P
ALT
AP
a lt
A YD
R
M
DME
FT/MIN
X 1000
1
FD
L
HDG
CREW
A LER T
PULL
PASS
VOL
APR
REV
BATTLE GROUND
KSPB 27
D
40
(H)----116.60 BTG
PDX
VS
ALT SEL
UP
KFC 225
17S
18
9
2S6
KUAO
2
S
–––
O
M
O
240 M
DIS
–––
0.0
Trk:
GS:
343° 135 kt
Pan
O
M
SLAVE
GPS
WAYPOINT
NAV
DH
MSG
0
CCW
1
RADAR ALT
X 100 FEET
2 MIN TURN
ELEC
CDI
PUSH
C/V
10
MSG
FPL
VNAV
CLR
IDENT
ENT
VFR
Custom Map
Info
N1
OFF
HLD
STBY
ALT
1
PUSH
CRSR
2
ANT
ADF
4363
3
4
C
COM
C
PWR
121.900
118.200
VOL/ PUSH
SQ
V
4
332
BFO
FRQ
COM
TEST
19R
110.30
113.80
VLOC
ENR
PUSH
C/V
–––––
19L
DIS
DIK
14
KICT
GS
2.0 –2
n
m
overzoom
VLOC
MSG
–––
N
M
–––
N
M
0.0
NAV
OBS
FPL
ADF
RNG
DPT
N
VLOC
V
VOL/ PUSH
ID
BUS
PITOT/STATIC
HEAT
STALL
HEAT
ON
ON
W/S
PROP
SECONDARY
AUTO
OFF
STARTER
OFF
OFF
L FLT PANEL
L FLOOD
BOOT
PRESS
ALT STATIC AIR
PULL ON
BATTERY
ALT
HDG
ALT
HDG
GS
FL
6
13.5 nm
013
7
20
10
8
10
20
10
20
7
100
FOR
QUICK
100
0
FEET
ALTITUDE
1
2
29.7
6
5
4
3
29.8
ECT
24
D.C.
ELEC.
MENU
ENT
FUNC
CRSR
START
STOP
CLR
8
9
L
W
21
2 MIN.
NO PITCH
INFORMATION
R
VACUUM
.5
1
0
.5
1
VERTICAL
SPEED
FT/MIN
X 1000
2
VENT
PULL ON
3
2
PUSH
D
MENU
CLR
ENT
DEFAULT
NAV
K
L
ADF
6 : 1 1 FLTET
STBY / TIMER
BFO
FLT
FRQ
ET
SET
RST
VOL
OFF
CONTINUED FLIGHT IN ICING CONDITIONS IS PROHIBITED
AFTER ENCOUNTERING ONE OR MORE OF THE FOLLOWING:
RES
VIR
APR
BC
AIRSPEED DECREASE OF 10 KIAS THAT CANNOT BE
PREVENTED BY INCREASE TO MAX CONTINUOUS POWER.
RES
RES
PUSH
CRSR
RNG
FD
NAV
APR
BC
TEST
RNG: 80
TRK:240 GS: 18 KT POS: 0.5SE KICT WICHITA
n
AP
ENG
DATA
m
OVLY
WARNING
OFF ON
INERTIAL SEPARATOR
MAP
BYPASS-PULL
NORMAL-PUSH
WX
TRFC
TERR
ASSURE
THAT
SEAT
IS
LOCKED
IN
POSITION
PRIOR
TO
TAXI,
TAKEOFF,
AND
LANDING.
FAILURE
TO
PROPERLY
LATCH
SEAT
AND
HEED
ALL
SAFETY
INSTRUCTIONS
CAN
RESULT
IN
BODILY
INJURY
OR
DEATH.LLLLLLLLLLLLLLLLLLLLLLLLLL
AUX
SKYWATCH
0705097-1
ON OFF
OPERATION OF THE ANTI-ICE PANEL
MAY CAUSE COMPASS DEVIATION OF
MORE THAN 10 DEGREES
2605028-2
RADIO
AC FANS
AFT
HIGH
LEFT
COOL
WARNING
CABIN HEAT
AIR CONDITIONING
ENG INST
TEMP
HOT
RIGHT
BLEED AIR HEAT
ON
MIXING AIR
GND-PULL
FLT-PUSH
AFT CABIN-PULL
FWD CABIN-PUSH
ASSURE THAT ALL CONTAMINATES, INCLUDING WATER, ARE REMOVED FROM
FUEL AND FUEL SYSTEM BEFORE FLIGHT. FAILURE TO ASSURE CONTAMINATE
FREE FUEL AND HEED ALL SAFETY INSTRUCTIONS AND OWNER ADVISORIES
PRIOR
TO
FLIGHT
CAN
RESULT
IN
BODILY
INJURY
OR
D E AT H . L L L L L L L L L L L L L L L L L L L L L L L L L L L L L L L L L L
DEFROST-PULL
FWD CABIN-PUSH
0705098-1
OFF
PARKING
BRAKE
PULL
MIC
MEA OR MOCA IF APPLICABLE ON CURRENT LEG FALLS
INTO AREA “C” OF ICING SERVICE CEILING CHART
CONTAINED IN SECTION 5 OF THE POH/AFM KNOWN
ICING EQUIPMENT SUPPLIMENT.
2605070–8
RNG
AP
TRIM
PHONE
AIRSPEED OF 120 KIAS CANNOT BE MAINTAINED IN
LEVEL FLIGHT.
N
GPS
PROC
NAV
KFC 150
UP
LOCK
R FLT PANEL
R FLOOD
LWR PANEL/
PED/OVHD
SW/CKT BKR
ON
RESET
20
10
PULL
OFF
MANUAL
OFF
EXTERNAL
POWER
FD
DN
LIGHTS BRT
MIC
Distance:
PRESSURE ALT
5
USE
KR 87 TSO
GNS 430
N2
CABIN
DEICE/ANTI-ICE
W/S
WING
PRIMARY
LIGHT
120
OFF
ALT
ON
80
140
GTX 330
ON
0
GPS
PROC
--.- NM' - - - KT - - MIN
2
3
5
OBS
CDI
PHONE
9
60
TURN COORDINATOR
DEFAULT
NAV
K
L
NAV
40
4S9
Baro:
Out
KNOTS
240 40
160
MENU
GS
72K
10 nm –2
overzoom
VLOC
7S9
200
180
FN
D
TRK
71K
KICT
ENR
VLOC
Alt:
KC
ER
10,300 ft 29.92”
In
–––
110.30
113.80
ICT
KICT
ILS 01R
LOC
VOLPUSH
ID
Zoom:(Trk Up)
50 nm
RNG
DTK
VLOC
V
V
COM
XTK
N
343°
03S
S48
5S9
27
117.40 UBG
065°FR 15NM
DN
ALT
NEWBERG
AIRSPEED
+
ON
OFF
Wpt Bearing:
W58
7S3
0
D
(H)
9
18 18
W56
40 400
40
PORTLAND
27 11 KVOO
20
59S201W1
D
PORTLAND
9 AP
KPDX
4S4
(L)---- 114.80 PDX
40
18
KTTD
KHIO
17
40
23
COPILOT
ARM
FT
K32
COM
C
VOL SQ
LL O NS X 10
L BS X 100
E D O N 6 .7 LBS /GA L
GMX 200
Waypoint:
SQ
PILOT
ICS ISOLATION VOL
PA
1.300
A
R
M
NAV
126.700
126.700
PWR PUSH
GPS
OB
ARM ACTV
R
NAV
VLOC
15
3
C
W
B AS
E D O N 6 .7 LB S /GA L
CW
RIGHT
LDG
BCN
S
2
24
5 6 7
8
8 10
6 FUEL
9
12
14
16
QTY.
11
GA
TEST
ADF
SPKR
OFF
.5
VERTICAL
SPEED
21
L BS X 100
4
2
E
2605070-6
NAV2
CABIN AUDIO
R
AP
12
15 S
12
E
SEAT
BELT
HI
LO
YD
TERR
4
3
2
1
E
LL O NS X 10
33 N
NO
SMOKE
MKR
MUTE
SQ
OFF/
VOL
Y
STB
NAV
ON
3
GA
GMA 340
A O M
29.8
4
2
E
30
1
.5
0
20
15
STROBE
VS
N
FREE
GPS APR
OVERSPEED
GOVERNOR
PUSH TO TEST
TRIM
29.7
NAV
VOLT
LIGHTS
TAXI/
RECOG
ON
5
GA
M
33
NAV
BATT
GS
N
200
W
21
24
ALT
25
-50
LEFT
LDG
4
CAP
O
30
A
D
F
GEN
150
HDG
33
A
D
F
30
IN.Hg
ENCODING
ALT
GS
KMMV
NAV
30
5
0
6
REV
A
PILOT
1005
7
NAV
APR
BC
DC
8
GS
0
2
AP
HDG
7
100
AMPS
15
10
VOLTS 20
1
ALT
1010
mb
100
SUCTION
IN HG
50
10
20
8
FEET
6
2
VENT
PULL ON
10
20
6
4
15k
20k
25k
30k
3
20
10
3
PROP ANTI-ICE
AMPS
20
10
0
100
E
6
60
240 40
9
6
7
180
DH
MP
H
2
40
3
10 20
CLOCK
KNOTS
2
1
E
H
MP
0
200
H
MP
10
9
8
ICE DET
P/TEST
11 12 1
5 6 7
8
8 10
6 FUEL
9
12
14
16
QTY.
11
4
3
4
5
BAS
AIR
ICE DETECTOR
SYSTEM IS
ADVISORY ONLY
PPH X 100
0
4
5
0
-40
3
7
°C 10
PSI
40
100
2
2
1FUEL FLOW3
140
110
55
OIL
85
20 % RPM 80
8
9
15 S
EMERGENCY
POWER LEVER
RESERVOIR
FUEL LOW
12
GENERATOR
OFF
VACUUM
LOW
MP
H
N208FS
TEST
OIL PRESS
LOW
F
OF
TEST
ENGINE
FIRE
VOLTAGE
LOW
E
ANNUN PANEL
LAMP
NIGHT
FIRE
DETECT
MAX
RPM TORQUE
1900
1865
1800
1970
1700
1970
1600
1970
BELOW
ICING
MIN SPD
ETM
01
6
ENGINE
120 KIAS MINIMUM IN ICING FLAPS UP EXCEPT 110 KIAS
IF CLIMBING TO EXIT ICING.
2605070-5
NO
3
ON A
OFF
LOW
VENTILATE
NORM
ON
OFF
TRIP
FUEL
BOOST
GENERATOR
MIC
ON
ON
START
A/P DISC
TRIM INTER
TRI
DN M
CWS
OFF
OFF
NORM
STBY PWR
TRIM
UP
MOTOR
IGNITION
STARTER
1 - ON - 2
Cessna
Cessna
Caravan I
AVIONICS AVIONICS
STBY
BUS TIE
PWR
BUS
1
PWR
STBY
PWR
FLAP
MOTOR
2605070-9
STBY
FLAP
MOTOR
40
10
10
STBY
PWR
LEFT
VENT
BLWR
RIGHT
VENT
BLWR
IGN
5
START
CONT
5
LEFT
TURN/
BANK
5
AUX
FUEL RIGHT
FUEL
CONT TURN
PUMP HEATER BANK
30
40
15
15
10
10
5
BUS
1
PWR
FIRE
DET
FUEL
TOTAL
LEFT
FUEL
QTY
OIL
TEMP
BLEED
AIR
HEAT
AFT
VENT
BLWR
30
5
5
5
5
5
15
BUS
2
PWR
ITT
GAGE
FUEL
FLOW
RIGHT
FUEL
QTY
AIR
SPEED
WARN
PROP
O-SPD
TEST
DE-ICE
BOOT
5
5
5
5
5
5
30
LEFT STROBE BEACON MAP
LDG
LIGHT LIGHT LIGHT
LIGHT
30
10
5
BUS
2
PWR
RIGHT
LDG
LIGHT
TAXI
LIGHT
30
10
15
COM
1
GPS
1
XPDR
1
5
10
10
A/P
COMP
5
5
5
GPS/
LORAN
2
HF
XMT
5
AVIONICS BUS 2
A/P
DME
ALERT
5
5
AVIONICS BUS 2
HF
HF
XMT
RCVR
5
5
15
ANNUN
PANEL
STALL
WARN
AIR
COND
CONT
5
10
15
20
15
SEAT
BELT
SIGN
5
30
T.
O.
5
NOSE
UP
M
A
X
M
A
X
P
R
O
P
P
O
W
E
R
R
P
M
I
D
L
E
I
D
L
E
N
O
R
M
A
L
C
O
N
D
I
T
I
O
N
UP
H I
I D
G L
H E
F
U
E
L O
N
M
I
N
L I
O D
L
WE
1
7
5
UNLOCK
C
U
T
O
F
F
10°
1
5
0
F
E
A
T
H
E
R
B
ER
TE
AV
E
R
S
E
20°
F
U
L
L
MAX
CAUTION
STBY FLAP MOTOR
DOWN
NORMAL
1
2
5
F
L
A
P
S
K
I
A
S
UP
STBY
USE BETA AND REVERSE ONLY
WITH ENGINE RUNNING AND
PROPELLER OUT OF FEATHER
AILERON TRIM
R
L
20
30
FUEL SHUTOFF
PULL OFF
SERVO
20
ELEV
TRIM
2
5
5
10
SKY
WATCH
RADIO
ALT
AVN
FAN
AUDIO
AMP
5
5
5
RADAR TAWS
R/T
5
M
A
X
PROP PROP
ANTI-ICE ANTI-ICE
CONT
5
AUD/
MKR
E
M
E
R
G
E
N
C
Y
P
O
W
E
R
NOSE
DOWN
15
RIGHT
W/S TORQUE
PITOT ANTI-ICE IND
HEAT
SEC
5
5
T
R
I
M
LEFT
W/S
W/S
PITOT ANTI-ICE ANTI-ICE
HEAT
PRI
CONT
ENC
ALTM
MFD
E
L
E
V
A
T
O
R
MAP LIGHT
LO
HI
0705028-3
RH
ATT
GYRO
RMI
GEN
FIELD
5
ENGINE
FIRE
OIL PRESS
LOW
GENERATOR
OFF
EMERGENCY
POWER LEVER
AUX FUEL
PUMP ON
FUEL PRESS
LOW
VOLTAGE
LOW
VACUUM
LOW
RESERVOIR
FUEL LOW
LEFT
FUEL LOW
RIGHT
FUEL LOW
STBY ELEC
PWR ON
SPARE
SPARE
CHIP
DETECTOR
STBY ELEC
PWR INOP
DOOR
WARNING
STARTER
ENERGIZED
NOSE
L
IGNITION
ON
RUD TRIM
NOSE
R
FAN/OP
EN
1000
500 1500
2000
0
O
X
Y
G
E
N
USE NO
OIL
V
E
N
T
A
I
R
PSI
OXYGEN
SUPPLY PRESSURE
MADE IN USA
15
CLOSE
ON
DE-ICE
PRESSURE
OFF
Cessna
STM
SCP
N
OPEN/FA
OFF
A
I
R
CLOSE
FUEL SELECT
OFF
WINDSHIELD
ANTI-ICE
V
E
N
T
FT
LE
OFF
FUEL TANK
SELECTORS
HT
HSI
2
5
5
GEN
CONT
RIG
5
GPS
2
2
15
AVIONICS BUS 1
ADF
HSI
1
1
5
1
5
ICE
RADIO
NAV
LIGHT DETECTOR FLOOD
LIGHT
COM
2
FUEL
SEL
WARN
2
INST
WING
LIGHT ICE DET
LIGHT
ANNUN
PANEL
WING FLAPS
30
BUS
2
PWR
BUS
1
PWR
Caravan I
DO NOT TAKEOFF WITH ICE/FROST/SNOW ON THE
AIRCRAFT.
OFF
AVIONICS
CABIN HEAT
FIREWALL SHUTOFF
PULL OFF
ON
165
GAL
ON
165
GAL
5
332 GAL WITH BOTH TANKS ON
MAXIMUM FUEL UNBALANCE IN FLIGHT 200 LBS
Figure 1-2. Cessna Caravan 208 G530
Revision 0
FOR TRAINING PURPOSES ONLY
1-3
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
30 33 N
01
HDG
20
10
130
30
CABIN
33
N
21
??????
INSET
S
OAT__– 5°c
37.9NM
EHF
NAV1
SENSOR
PFD
OBS
15
BACKUP
ON
CDI
DME
FRAME
324°
73.2NM
334°
10.0NM
KFAT
R LCL
NRST
08:44:27
ALERTS
OFF
FPL
PROC
CLR
ENT
DFLT MAP
PFD
1
XPDR
1
ADF
1
5
5
5
2
A/P
SERVOS
A/P
CONT
ELT
NAV
INTFC
RADIO
ALT
RADAR
R/T
5
5
5
5
5
5
COM
2
NAV
2
MFD
ADC
2
AHRS
2
PFD
2
XPDR
2
5
5
5
5
5
5
AVN
BUS
1
AUDIO
TEST SWITCH
FIRE DETECT–UP
FUEL SELECT OFF–DN
PHONE
PASS
FMS
2605070-10
TAS
XM–DATA
LINK
STM
SCOPE
HF
RCVR
HF
AMP
5
5
5
5
5
30
V107
1900
KRFL
KSMX
95
85
V27
GMN
379
BAT AMPS
BUS VOLTS
4
28.5
A–ICE GAL
4.7
V107
V137
V22
AVIONICS
MAP WPT AUX NRST
TERRAIN AIRWY LO STRMSCP NEXRAD XM LTNG
PARKING
BRAKE
PULL
D
MENU
FPL
PROC
CLR
ENT
DFLT MAP
BACK
10
10200
10100
HDG
328°
33
GPS
CRS
OAT__– 5°c
FMS
??????
INSET
331°
N
ENR
OBS
CDI
0 5 1 0 0
1
PUSH
1-2
ON
BARO
-900
ARM
PUSH
STD
9700
29.92IN
1
10
ARTEX
ELT
1
9800
328°
30
37.9NM
EHF
NAV1
SENSOR
PFD
9900
10
80
PUSH
VOL SQ
COM
EMERG
2
2
TEST/RESET
PRESS ON
WAIT 1 SECOND
PRESS ARM
RANGE
–
+
PUSH
PAN
D
DME
FPL
50.0NM
FLW
NAV2
XPDR
XPDR1
IDENT
4234 ALT
TMR/REF
R LCL
NRST
08:44:27
ALERTS
MENU
PROC
CLR
DFLT MAP
ENT
FMS
SQ
PUSH CRSR
TEMP °C
30+ 0 –30
100
40
200 PRESS
ALT
180 AIRSPEED 60
160
80
140 KNOTS
120 100
8
9
7
6
PUSH CRSR
1
4
5
VENT–PULL ON
HF
FEET
0
ALTIMETER
1015
1010
VACUUM
1
2
3
10
E
15
5 TORQUE
29.8
29.9
30.0
20
0
FT–LB
X 100
EMER
T.O.
VOL
25
PUSH
PWR
5.000
R 1
TEST
FUNC
FREQ CHAN
MOD
RX
PHONE
TUNE
ENT
TX
SQL
OPT
MIC
LOCK
332
ADF
INERTIAL SEPARATOR
KR 87 TSO
BYPASS–PULL
NORMAL–PUSH
BENDIX / KING
CB/PED/
OVHD
LEFT
FLOOD
3:10
USE
ADF
WARNING
ADF
FLT
ASSURE THAT ALL CONTAMINATES, INCLUDING
WATER, ARE REMOVED FROM FUEL AND FUEL
SYSTEM BEFORE FLIGHT. FAILURE TO ASSURE
CONTAMINATE FREE FUEL AND HEED ALL SAFETY
INSTRUCTIONS AND OWNER ADVISORIES PRIOR
TO FLIGHT CAN RESULT IN BODILY INJURY OR
DEATH.LLLLLLLLLLLLLLLLLLLLLLLLLLLLLLLLLL
07 050 98 -1
STBY/TIMER
BFO
FRQ
FLT
ET
SET
RST
AIR CONDITIONING
RIGHT
FLOOD
COOL
ALTSTATIC AIR
PULL ON
150NM
V197
V23
DISPLAY BACKUP
DIMMING
SW/CB PNLS
/ ANNUN
STANDBY
IND
KVCV
V386
XWHP
V107
XBUR
V107
TOPO
V12
V201
KCMA
KNTD
10
10
PUSH
KPMD
127.100 COM1
122.450 COM2
128.375
121.500
20
PAN
KWJP
V27
316
+
KEDW
V12
KSBA
V25
V186
–
KMHV
FUEL QTY
LBS
R
FFLOW PPH
120
331°
310000
100
130
PUSH
STD
V23
V137
V183
BRG
150
RANGE
V25
20
145
L
KNID
20
140
V459
KVBC
1-2
V165
EHF
DIS 38.0NM
EHF
AP YD ALT 10000FT
10
000
10300
160
PUSH
1-2
BARO
V485
0
AVN
BUS
2
DME
KSBP
GMN
GPS
115.40 EHF
117.80 FLW
NAV
PUSH
KDLO
V113
V27
NAV1 116.90
NAV2 112.50
PUSH
VOL ID
COM
KPTV
V23
16
CONTINUED FLIGHT IN ICING CONDITIONS IS
PROHIBITED AFTER ENCOUNTERING ONE OR
MORE OF THE FOLLOWING:
AIRSPEED OF 120 KIAS CANNOT BE MAINTAINED
IN LEVEL FLIGHT.
AIRSPEED DECREASE OF 10 KIAS THAT CANNOT
BE PREVENTED BY INCREASE TO MAX
CONTINUOUS POWER.
MEA OR MOCA IF APPLICABLE ON CURRENT LEG
FALLS INTO AREA”C” OF ICING SERVICE CEILING
CHART CONTAINED IN SECTION 5 OF THE POH/
AFM KNOWN ICING EQUIPMENT SUPPLEMENT.
PUSH
VOL SQ
TRACK UP
170
2 141618
ADF
2
10KT
V165
V459
R
96.5
TRAFFIC
180
AHRS
1
5
700
O
F
F
COPLT
127.100 COM1
122.450 COM2
128.375
121.500
DIS 38
KVISV459
24CL
TAS
ADC
1
5
900
PLAY
PILOT
KHJO
V137
KPRB
100
OIL °C
200
ENG
INTFC
5
PROP RPM
ICS ISOLATION
PUSH CRSR
NAV
1
12
% RPM
CREW
PILOT
THE SIGHT GAGE ON THE TKS TANK IS THE
ONLY APPROVED MEANS OF ASSURING
ADEQUATE DISPATCH FLUID QTY
COM
1
°C
L
MAN
SQ
MENU
GS 175
600
50
NAV2
VOL
700026
MIC
PUSH
331°
MAP - NAVIGATION MAP
EMERG
1650
0
AUX
38.0NM
DTK
C80
V248
ITT
1-2
NAV1
ADF
PAN
D
331°
4234 ALT
HI
SENS
+
DTK
DIS
– – –° – – – –NM
TMR/REF
SPKR
ETE 13:47
N
20
OIL PSI
–
EHF
XPDR1
TEL
PA
MKR
MUTE
115.40 EHF
117.80 FLW
15
FT–LB
X100
10
0
COM
1/2
DME
RANGE
KLGB / KFAT
VENT–PULL ON
OVERSPEED
GOVERNOR
PUSH TO TEST
2
116.90
112.50
NAV
Ng
PUSH
STD
GMN
IDENT
NAV 1
NAV 2
TRQ
PUSH
VOL ID
PUSH
1-2
V23.FRAME
50.0NM
FLW
NAV2
XPDR
COM3
PUSH
BARO
-900
FLIGHT PLAN
12
OFF
FLUID CONTROL
MAX FLOW
AIRFRAME
N
O
R
M
WINDSHIELD
COM2
COM3
MIC
E
PRIMARY
HIGH
COM1
COM2
MIC
6
24
ENR
1
1
9700
29.92IN
E
ANTI-ICE
331°
2
COM1
MIC
PUSH DIR
3
GPS
CRS
6
MANUAL
WINDSHIELD ANTI-ICE MUST BE
OFF FOR TAKEOFF AND LANDING
328°
80
9800
3
SEAT
BELT
ON
HDG
9900
10
328°
W
NO
SMOKE
WING
LIGHT
10100
3100 00
100
O
F
F
STALL
HEAT
ON
10
PUSH
VOL SQ
COM
EMERG
PUSH DIR
EMERGENCY USE ONLY
10
140
120
127.100 COM1
122.450 COM2
128.375
121.500
2605076-5
C
R
E
W
331°
10200
150
BCN
CRS2
SPD
W
NAV
ON
FLC
DN
24
160
20
VS
VNV
21
20
145
STROBE
PROP
HEAT
AUTO
P/S HEAT /
LOW A/S
AWARE
BRG
ALT
ALT SEL
YD
UP
PUSH SYNC
10
000
10300
170
1-2
OFF
DIS 38.0NM
EHF
AP YD ALT 10000FT
XFR
AP
S
RIGHT
LDG
PUSH
POWER
OUTLET
ALL
GMN
GPS
115.40 EHF
117.80 FLW
NAV
FD
BANK
15
LEFT
LDG
NAV1 116.90
NAV2 112.50
PUSH
VOL ID
NAV
CRS1
BC
12
N208FS
LIGHTS
TAXI/
RECOG
ON
APR
HDG
BELOW
ICING
MIN SPD
WHEN TAKEOFF TORQUE SETTINGS ARE BELOW
1865 FT-LBS, THE AIR CONDITIONER MUST BE
OFF FOR TAKEOFF AND LANDING
2605031-3
MAX WT MANEUVERING SPEED 148 KIAS
SEE POH OTHER WEIGHTS
LEFT
AC FANS
AFT
HIGH
RIGHT
OFF
VOL
TEMP
HOT
BLEED AIR
HEAT
ON
WARNING
ASSURE THAT SEAT IS LOCKED IN POSITION
PRIOR TO TAXI, TAKEOFF, AND LANDING. FAILURE
TO PROPERLY LATCH SEAT AND HEED ALL
SAFETY INSTRUCTIONS CAN RESULT IN BODILY
INJURY OR DEATH.LLLLLLLLLLLLLLLLLLLLLLLLLL
07 050 97 -1
CABIN HEAT
MIXING AIR
AFT CABIN–PULL
GND–PULL
FWD CABIN–PUSH
FLT–PUSH
DEFROST–PULL
FWD CABIN–PUSH
OFF
DAY
VENTILATE
OFF
LOW
DO NOT TAKEOFF WITH ICE/FROST/SNOW ON THE
AIRCRAFT.
2605070-9
M
TRI
DN
M
TRI
UP
WING FLAPS
Caravan
ON
BUS
STARTER
OFF
OFF
RESET
EXTERNAL
POWER
NORM
OFF
TRIP
NORM
PRI
ANTI–
ICE
TORQUE
IGN
START
CONT
GEN
CONT
30
5
5
5
5
5
GEN
FIELD
15
BUS
2
PWR
STBY
PWR
RIGHT
PITOT
HEAT
PROP
ANTI–ICE
CONT
BACKUP
ANTI–
ICE
W/S
ANTI–ICE
AUX
12V DC
PWR
LEFT
FUEL
QTY
AUX
FUEL
PUMP
FUEL
SEL
WARN
40
15
5
5
2
10
5
10
RDNG
LIGHT
INST
LIGHT
LEFT
LDG
LIGHT
STROBE
LIGHT
BEACON
LIGHT
WING
ICE DET
LIGHT
RIGHT
FUEL
QTY
F FLOW
NG & NP
STARTER
30
7
5
10
5
10
5
5
2
10
2
BUS
2
PWR
SEAT
BELT
SIGN
AVN
FLOOD
LIGHT
RIGHT
LDG
LIGHT
TAXI
LIGHT
NAV
LIGHT
FIRE
DET
PROP
O-SPD
TEST
AIR
COND
CONT
DECK
SKIN
FAN
30
5
5
10
15
10
MOTOR
IGNITION
1
ON
OFF
AVIONICS
AVIONICS AVIONICS
BUS TIE
STBY
PWR
PROP
ANTI–
ICE
15
30
FUEL
BOOST
START
OFF
STBY ALT PWR
LEFT
PITOT
HEAT
40
BUS
1
PWR
GENERATOR
ON
OFF
STBY
PWR
30
BATTERY
ON
ON
ON
BUS
1
PWR
Caravan
BUS
1
PWR
30
7
5
10
5
BUS
2
PWR
30
7
5
10
5
FUEL
CONT
HEATER
5
5
5
5
FLAP
MOTOR
AIR
SPEED
WARN
AFT
VENT
BLWR
LEFT
VENT
BLWR
10
5
10
10
STBY
FLAP
MOTOR
STALL
WARN
BLEED
AIR
HEAT
RIGHT
VENT
BLWR
10
10
5
10
AUX AUDIO IN
Figure 1-3. Cessna Caravan 208 G1000
1-4
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
CHAPTER 2
ATA 2200
02
INTRODUCTION
This chapter describes the arrangement, numbering system, and special features of the Air Transport Association (ATA 2200) format
for aircraft technical publications. To take advantage of all the material presented in an ATA 2200 format manual, the maintenance
technician must become thoroughly familiar with the outline and contents presented. The ATA 2200 format is a standard for the
presentation of information that includes section numbering, chapter numbering, and page numbering for maintenance manuals, parts
catalogs, wiring diagram manuals, avionics installation manuals and structural repair manuals.
MAINTENANCE PUBLICATIONS
The Cessna Caravan I Maintenance Manual, Illustrated Parts Catalog,
Wiring Diagram Manual, and Structural Repair Manual are prepared
in accordance with the Air Transport Association Specification for
manufacturers’ technical data. These manuals assist maintenance perRevision 0
FOR TRAINING PURPOSES ONLY
sonnel in servicing and maintaining Caravan I aircraft. They provide
the necessary information to service, inspect, troubleshoot, remove
and replace components, and repair systems.
2-1
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
WIRE IDENTIFICATION
EQUIPMENT LIST
The wiring diagrams in the 208 manual do not show the wire number for each wire; however, the wires in the aircraft have wire numbers as shown in the following example:
All electrical and electronic equipment used in the wiring diagrams
are identif ied by an alphanumeric reference designator. This reference designator is used as a cross-reference symbol to the equipment list where the part number, part description, zone, and five -digit
Federal Supply Code are given. Manufacturer’s names and addresses that correspond with the Federal Supply Code may be found
in the Introduction.
02
/ * B JT007-PA002 (24) (SP 2-B)
Color of Wire
Numerical
Sequence**
TP—Twisted Pair
TT—Twisted
Triple
SS—Single
Conductor
Shielded
SP—Shielded Pair
ST—Shielded
Triple
CX—Coax
Wire Size
Connector
(or Other Component)
Connector Pin
Connector (or Other Component)
Connector Pin
Connector Pin Following is Lower Case
Indicates Wire is Spliced with Other
Wires within 3 Inches of Component
Figure 2-1. Wire identification
** A numerical sequence for each type of wire (SP1, SP2, SP3; ST1,
ST2, ST3) on a diagram page. May be used to identify wires within
a shield or twisted group when they are not drawn adjacent and
enclosed by a twisted or shielded symbol. Example: SP2-B and
SP2-W are the two wires within a shield.
Reference designators consist of two letters followed by three numbers. A reference designator assigned by this method provides information about where a component is located in the aircraft. The
following list shows the categories assigned to basic equipment designator letters:
COLUMN A EQUIPMENT LIST
Splice .................................................................................... A%###
Controller ............................................................................. B%###
Capacitor .............................................................................. C%###
Diode .................................................................................... D%###
Instrument ............................................................................ E%###
Light ...................................................................................... F%###
Ground.................................................................................. G%###
CB/Fuse/Bus Bar ................................................................ H%###
Receptacle ............................................................................. J%###
Relay ..................................................................................... K%###
Inductor ................................................................................ L%###
Servo/Motor ........................................................................ M%###
Printed CKT BD.................................................................. N%###
Plug........................................................................................ P%###
Transistor ............................................................................. Q%###
Resistor................................................................................. R%###
Switch ................................................................................... S%###
Thermal................................................................................. T%###
Element Unit/Module ........................................................ U%###
Valve ..................................................................................... V%###
Solenoid .............................................................................. W%###
JCT/Terminal BD................................................................ X%###
Cessna Assembly ................................................................. Z%###
COLUMN B LOCATION IN AIRCRAFT
Aft Bulkhead......................................................................... *A###
FWD Fuselage Bulkhead .................................................... *B###
Fuselage (Cabin)—LH ........................................................ *C###
LH Engine (Nacelle) ........................................................... *D###
RH Engine (Nacelle)............................................................ *E###
Fuselage (Cabin)—RH ........................................................ *F###
Landing Gear ........................................................................ *G###
Horizontal Stabilizer ........................................................... *H###
Instrument Panel .................................................................... *I###
Aft Baggage Area ................................................................. *K###
LH Wing ................................................................................. *L###
LH Wing Feedthrough ........................................................ *M###
Forward Nose ........................................................................ *N###
RH Wing ................................................................................ *R###
RH Wing Feedthrough ......................................................... *S###
Tail Cone................................................................................ *T###
Vertical Stabilizer ................................................................ *V###
**Insertion Cable ..................................................................... *X###
Fuselage Fairing ................................................................... *Y###
Inside Cessna Assembly ...................................................... *Z###
Code:
%—Letter from Column B
*—Letter from Column A
#—0, 1, 2, 3, 4, 5, 6, 7, 8, or 9
(001–299 to be used for electrical diagrams;
300–999 to be used for avionics diagrams)
Examples:
PB105 Forward Bulkhead Plug
EI302 Instrument in Instrument Panel
**Def inition:
Insertion Cable—A cable which originates from
optional equipment and plugs into a break in a
standard cable, and will have an “XX” reference
designator as indicated above.
The reference designator codes for a bulkhead feedthrough receptacle and its attaching plugs contain the same numeric value. For
example:
JS140—Receptacle, RH Wing Feedthrough
PR140—Plug in RH Wing
PF140—Plug in RH Cabin
Figure 2-1. ATA 2200 Overview
2-2
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
+
BATTERY
–
DIODE
REGULAR—Low resistance forward,
high resistance reverse.
IN
OUT
WHT
ZENER—Low resistance forward, high
resistance reverse until a specific
voltage is applied, then conducts freely.
BUS
TRANSORB—A transorb is similar to a
zener, but with higher peak current limit.
CAP AND STOW
VARISTOR—High resistance either way
until a specific voltage is applied, then
conducts freely. Example: V47ZA1
conducts freely above 47 volts.
CAPACITOR
CIRCUIT BREAKER
VARISTOR—Encapsulated for moisture
protection.
IN
OUT
IN
OUT
+
IN
OUT
FILTER
Passes direct current but opposes pulsating
current; used to reduce noise in sensitive
avionics equipment.
The switch contacts connect to an
annunciator system to warn when
a circuit breaker is open.
28V
LOAD
CURRENT
A1 SENSOR
MOT
OR GATE—Output is low until either or
both inputs are high, then output is high.
FUSE/LIMITER
NOR GATE—Output is high until either or
both inputs are high, then output is low.
INVERTER—Output is low when input
is high, output is high when input is low.
OPERATIONAL AMPLIFIER (OP AMP)—
Amplifies the difference in voltage between
the two inputs. The minus input is the
inverting input, and the plus is the noninverting input. If an input is applied to the
minus input, with the plus input grounded,
the polarity of the output will be opposite to
the input. If an input is applied to the plus
input, with the minus input grounded, the
polarity of the output will be the same as
that of the input.
MOT
WHT
HI
LOW
GROUND
RELAY
CURRENT FLOW
WITH POWER
APPLIED
HEADSET
HEATER
CONNECTOR
INTEGRATED CIRCUIT
MOTOR
HORN/SPEAKER
Integrated circuits do not necessarily work
on the principle of ON–OFF as a switch;
instead some work on high and low voltage.
Example: high might be 5.0 volts and low
might be 0.5 volts.
IN
OUT
RED
AND GATE—Output is low until both
inputs are high, then the output is high.
IN
OUT
NAND GATE—Output is high until both
inputs are high, then the output is low.
REVERSIBLE MOTOR—Direction of
rotation is controlled by reversing power and
ground on input wires.
BLK
CW
CURRENT TRANSFORMER
Current flowing in wire produces a voltage
in coil.
MOT P
M
MOT
CURRENT SENSOR
Current flowing in coil opens switch to
indicate circuit is functioning correctly.
M
Basic symbol for motor.
The black circle indicates contact will
accept 16 gage wire. A black triangle
indicates contact will accept 12 gage
wire. Unmarked contacts accept 20
gage wire.
CURRENT FLOW
THE INSTANT
POWER IS
REMOVED
A diode is connected across the input
wires of relays and solenoid-operated
devices, such as valves, to protect voltage
sensitive navigation and electronics equipment. The diode is reverse-biased for
normal power and no current flows through
the diode. Current flowing through the coil
of wire produces a magnetic field to
operate the relay or valve. The instant
power is removed from the coil, the
collapsing magnetic field produces a
momentary spike of high voltage which
can be several hundred volts, depending
on the current and the number of turns of
wire in the coil. The diode is forwardbiased for the power generated in the coil
and the high voltage spike is dissipated
through the diode. A varistor is used in
place of the diode on some relays.
CONTROL SWITCH
(RELAY)
Remote circuit breakers combine the functions of circuit
breaker and relay. A 1 amp or 0.5 amp circuit breaker is
used at pilot’s circuit breaker panel to indicate an overload
and can be opened by the pilot to disable the system.
Remote circuit breakers have a visual indicator to the right
of the connector. OPEN and CLOSED labels on red and
green backgrounds indicate the position of relay contacts.
The symbol for the solenoid may be a box
or a coil, the operation is identical.
+
–
LAMP
LOGIC
3
02
NONREVERSIBLE MOTOR—Two-speed
controlled by applying power to either input
wire.
PHONE JACK
TIMER—Changes the output from high to
low in a regular pattern.
A2
NONREVERSIBLE MOTOR—Direction of
rotation is controlled by design; input wires
may be connected either way.
MOT
CCW
REVERSIBLE MOTOR—Direction of
rotation is controlled by applying power to
either field winding input wire.
28 DVC
ANNUNCIATOR
LOAD
An annunciator relay has a connection on
the material contact to indicate by a light
or annunciator panel when the relay is
energized.
Figure 2-2. Electrical Symbols (Sheet 1 of 2)
Revision 0
FOR TRAINING PURPOSES ONLY
2-3
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
RELAY (Cont.)
The contacts of a time delay relay do not
move to the energized position usually
when power is applied.
TIME
DELAY
02
7
3
Jumper wire gives 0.1 seconds of delay.
6
1
2C
4
This symbol with no sp reference
designator is a permanent splice;
when identified with an sp reference
designator, it is an environmental
disconnect splice.
1C
2C
3C
ENVIRONMENTAL DISCONNECT
4C
SWITCH
VARIABLE OR ADJUSTABLE—
Resistance changes with mechanical input.
RHEOSTAT—Type of variable resistor
with two wires.
POTENTIOMETER—Type of variable
resistor with three wires.
SOLENOID/SOLENOID VALVE
NO (normally open) or NC (normally
closed) by a solenoid-operated valve
indicates the position of the valve with
no power applied to the solenoid.
E CLOSED
F
B CLOSE
B CLOSE
D CLOSED
M
E MOTOR
F ANNUNCIATOR
(MOTOR ON)
A OPEN
C OPENED
SHOWN OPEN
G MOTOR
A OPEN
C OPENED
D
SHOWN OPEN
MOTOR-OPERATED—Limit switches stop
power when limit of travel is reached.
C
OPPOSITE
SINGLE-POLE/SINGLE-THROW (SPST)
SINGLE-POLE/DOUBLE-THROW (SPDT)—
May have OFF position in the center.
DOUBLE-POLE/DOUBLE-THROW (DPDT)—
May have OFF position in the center.
Dashed line indicates all parts move
simultaneously.
E
D
E
C
K
A
D
E
C
K
B
4NO
Handle position is reference to the
flat side of the mounting threads.
E
PNP
NOTE:
Some switches of this type do not
have a center position.
COLLECTOR
BASE
EMITTER
1C
2C
3C
5C
TWO-POLE ROTARY—On rotary or
multipole switches controlled by a knob,
the poles (or decks) are identified on wiring
diagrams as A, B, C, with A being the part
on the knob or shaft end.
B
2NC
3NC
3NO
4NC
C
TO FLAT
1NC
2NO
4-POLE
4C
ROTARY OR MULTI-POSITION
1NO
6C
1NO
1NC
2NO
2NC
3NO
3NC
4NC
4NO
5NC
5NO
6NC
6NO
Contact 1 of 2-pole
Contacts 1 and 2 of
4-pole
Contacts 1, 2, and 3 of
6-pole
Contact 2 of 2-pole
Contacts 3 and 4 of
4-pole
Contacts 4, 5, and 6 of
6-pole
TO FLAT
CENTER*
NO
NO
C
C
NC
C
NC
C
NO
NC
NO
CONTROL
SIGNAL
MAIN
CURRENT
FLOW
OPPOSITE
C
NC
C IS THE COMMON TERMINAL
NC IS THE NORMALLY CLOSED TERMINAL
NO IS THE NORMALLY OPEN TERMINAL
NO
C
B
DARLINGTON
NC
C
E
NC
NO
WIRE
6-POLE
TWISTED
PRESSURE-OPERATED
D
E
C
K
C
SHIELDED
C C C
1 1 1
2 2 2
2
3 3 3
3
1 10 9
TEMPERATURE-OPERATED
8
GRAYHILL
M
Transistor contacts are identified as base,
collector and emitter. Flow of current
through a transistor is controlled by the
signal applied to the base. The control
current (3–5% of total current) flows
between base and emitter. The main flow of
current (95–97%) is between the collector
and emitter. Transistors may be drawn
without the circle.
CENTER (NOTE)
ENVIRONMENTAL
TEMPERATURE-CONTROLLED—
Resistance changes with the temperature.
TRANSISTOR
B
2NO
SPLICE
EXTERNAL
RESISTOR
REGULAR—Resistance does not change.
1NC
2NC
TWO-STAGE—Two-pole, four-pole or sixpole switch designed so that all moveable
switch contacts do not move simultaneously.
NPN
Other resistors give a delay time between
0.1 second and 10 seconds.
RESISTOR
1NO
2-POLE
160,000 OHM resistor gives a 10-second
delay.
TIME A
DELAY
2
5
B
1C
For some time delay relays, the delay time
is part of the relay design.
For some time delay relays, the delay time
is controlled by the size of an external resistor.
9
SHUNT
SIDE VIEW
WITH TYPICAL TERMINAL NUMBERING
4 5 6
Q12A20
7
REAR VIEW
HIGH-TEMPERATURE WIRE
TERMINAL STRIP
C = Common terminal for each deck
1—10 = Switch terminal position
EXAMPLE:
AC = Common terminal of deck A
B1 = Switch position 1 on deck B
TRANSFORMER
Figure 2-2. Electrical Symbols (Sheet 2 of 2)
2-4
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
CHAPTER 5-12
AIRCRAFT GENERAL
5-12
INTRODUCTION
This chapter presents information pertaining to Chapters 5 through 12 of the Model 208 and 208B Airplane Maintenance Manuals (AMMs). It is meant to be an overview or guide to the information found
in these chapters and not a specific source. References for this chapter and further specific information can be found in Chapter 5—“Time Limits/Maintenance Checks,”Chapter 6—“Dimensions and
Areas,” Chapter 7—“Lifting and Shoring,” Chapter 8—“Leveling and Weighing,” Chapter 9—“Towing and Taxiing,” Chapter 10—“Parking and Mooring,”and Chapter 12—“Servicing” of the AMMs.
GENERAL ORGANIZATION
The Cessna 208 can be either a Caravan I or Cargomaster. Cessna
208B is a Caravan I, Super Cargomaster, or a Grand Caravan. The
basic airframe difference between the 208 and 208B is the length of
the fuselage; 208B is a lengthened version. This is ­immediately visible in the distance between the windshield and the wing leading edge
also the length of the fuselage.
The aircraft has a fuselage of conventional formed sheet metal bulkhead, stringer, and skin (semi-monocoque). The wings, which are
externally braced, contain integral fuel tanks.
The aircraft is all metal, high-wing, single-­engine aircraft with fixed
tricycle spring steel landing gear. The Amphibian model has ­retractable
dual/main landing gear. The nose gear f­ eatures a full castering nose
wheel mounted on a composite nose spring, which retracts into the
float nose to provide a dock bumper.
The empennage has conventional vertical s­ tabilizer, rudder, horizontal
stabilizer, and e­ levator. Each elevator has trim tabs.
Revision 0
The aircraft has ailerons and Fowler type flaps. The left aileron incorporates a servo tab while the right aileron incorporates a trim-able servo tab.
FOR TRAINING PURPOSES ONLY
The engine is either PT6A-114 (600 HP), PT6A-114A (675 HP), or PT6A140 (867 HP). Propellers are Hartzell or McCauley with three blades.
Cessna 208 Cargomaster has no passenger door or passenger windows.
Cessna 208B Super Cargomaster has a lengthened fuselage.
Cessna 208B Grand Caravan has windows installed with a passenger
door at the rear of the fuselage.
5-1
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
110
211
(212)
215
(216)
231
(232)
251
(252)
213
(214)
217
(218)
233
(234)
801
(802)
255
(256)
311
(312)
5-12
130
253
(254)
257
(258)
803
(804)
320
330
MODEL 208 FUSELAGE ZONES
110
130
211
(212)
215
(216)
231
(232)
251
(252)
213
(214)
217
(218)
233
(234)
801
(802)
255
(256)
253
(254)
257
(258)
311
(312)
803
(804)
320
330
MODEL 208B FUSELAGE ZONES
240
243
242
244
122
121
MODEL 208B TOP DOWN VIEW
241
Figure 5-1. Zones Overview
5-2
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
JACK
POINT
ASSEMBLY
TAIL
JACK
STAND
TAIL
TIE-DOWN
HYDRAULIC
MAIN/NOSE
JACK
5-12
JACK
CAP
FS 100.00
FS 207.44
A
JACK
CAP
B
HYDRAULIC
MAIN/NOSE
JACK
HYDRAULIC
MAIN/NOSE
JACK
RBL
23.77
LBL
23.77
.125”
LANDING GEAR
TRUNNION
BEARING CAP
MAIN LANDING GEAR
INTEGRAL JACK PAD
1.00”
JACK
BRAKE ASSEMBLY
DETAIL B
DETAIL A
Figure 5-2. Lifting and Shoring
Revision 0
FOR TRAINING PURPOSES ONLY
5-3
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
5-12
5-4
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
CHAPTER 20
STANDARD PRACTICES
20
INTRODUCTION
Maintenance practices unique to a particular system or subject are described in the appropriate ATA chapter in the manufacturer’s maintenance
manual. Standard maintenance practices, however, for maintaining and repairing items of the airframe and systems are discussed in Chapter 20. The
chapter contains sections on airframe hardware, electrical/electronic practices, and solvents, sealants, and adhesives. Conversion data is also provided.
GENERAL
This chapter is divided into sections. A short description of each section is given below. Refer to the Table of Contents at the start of this
chapter to find an applicable maintenance practice concept or subject.
The section on Airplane and Systems Hardware gives the maintenance
procedures for the items that follow:
• Tubing, hoses, and fittings
• Tube bending criteria
• Non-flare fittings and nylon tubing
• Packing and backup rings
• Safetying
• Control cables, seals, and pulleys
Revision 0
FOR TRAINING PURPOSES ONLY
• Rivetless nutplates
• Torque data for bolts, screws, nuts, and fittings
The section on Electric/Electronic Practices gives data for electrical
examination and requirements for installation and repair of electrical
wiring and interconnecting hardware components, wire bundle repair,
and electrical bonding.
The section on Solvents, Sealants, and Adhesives gives the description
and uses for the items that follow:
• Solvents and cleaners
• Fuel, weather, pressure, and high temperature sealing
• Application of adhesives and solvent bonding
20-1
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
20
20-2
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
CHAPTER 21
AIR CONDITIONING
21
INTRODUCTION
This chapter provides a description of the heating, ventilation, and air conditioning systems. For each system, emphasis is on component location and system operation. References for this chapter and further
specific information are available in the Manufacturer’s Maintenance Manual under the following chapters: 36 Pneumatics, 21 Air Conditioning, 5 Time Limits/Maintenance Checks, and 12 Servicing.
GENERAL
The environmental system consists of heating, defrosting, ventilation,
and the vapor cycle air conditioning subsystems and the ducts associated with each system. The environmental system is identical for all
208 series aircraft except for the following:
Air Distribution System
The environmental subsystems regulate the temperature and volume
of airflow to the cabin. Each system uses separate plenums and ducts.
• Model 208 and 208B passenger ventilation systems include
wemac valves, ducts, and plenums for pilot, copilot, and each
passenger seat position.
For cockpit ventilation, ram air is ducted from each side of the aircraft just aft of the firewall to outlets on the left and right sides of
the instrument panel. Push-pull control knobs are above each outlet.
• Model 208B cargo ventilation systems include wemac valves
and plenums for pilot and copilot seat positions only.
Defroster nozzles are on each side of the glareshield below the windshield.
Revision 0
FOR TRAINING PURPOSES ONLY
For cabin ventilation, all aircraft are equipped with a fresh air vent
system mounted in the wing and cabin overhead. The 208 and 208B
passenger models may have optional blower fans upstream of the
plenum. These are used during ground operations to provide a more
comfortable cabin environment. If desired, the blower fans may be
operated during flight.
21-1
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
LEGEND
HIGH PRESSURE BLEED AIR
P3 AIR
P2.5 AIR
LOW PRESSURE BLEED AIR
REGULATED BLEED AIR
SUCTION/VACUUM
CABIN AIR
VACUUM
EJECTOR
HEATING AIR
CONDITION:
IN FLIGHT
FLOW
CONTROL
VALVE
PRESSURE
REGULATOR
21
DE-ICE AIR
SOURCE
MIXING AIR
VALVE - FLT
CONTROL
PANEL
MIXER /
MUFFLER
TEMP
LIMIT
SWITCH
FIREWALL
SHUTOFF
VALVES
SAFETY
SWITCH
COCKPIT
OUTLETS
CABIN
OUTLETS
Figure 21-1. Bleed Air Heat
21-2
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
P3 AIR
FLOW CONTROL VALVE
NOTES
MIXER / MUFFLER
P2.5 AIR
FIREWALL SHUTOFF
VALVE CONTROL (2)
MIXING AIR VALVE
CABIN HEAT
SELECTOR VALVE
VENTILATING AIR DOOR
(ONE EACH SIDE)
DEFROST AIR /
FORWARD CABIN AIR
SELECTOR VALVE
DEFROSTER OUTLETS (2 EA)
INSTRUMENT PANEL
VENTILATING OUTLETS
AND CONTROLS (2)
21
ADJUSTABLE PILOT AND
FRONT PASSENGER
OVERHEAD VENTILATING
OUTLETS (2 EA)
VENTILATING AIR INLET
IN UPPER WING STRUT
FAIRING (2)
VENT AIR
CONTROL
ON OVERHEAD
CONSOLE
VENT AIR
CONTROL
ON OVERHEAD
CONSOLE
SHUTOFF VALVE
SHUTOFF VALVE
HEATER OUTLETS
2 ON EACH CABIN SIDEWALL
AT FLOOR LEVEL
ADJUSTABLE REAR
PASSENGER OVERHEAD
VENTILATING OUTLETS (8)
LEGEND
HEATED AIR
VENTILATION AIR
Figure 21-2. Heating System Overview
Revision 0
FOR TRAINING PURPOSES ONLY
21-3
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
AFT EVAPORATOR
WING EVAPORATORS
21
RECEIVER/DRYER
SIGHT GLASS
(R12 ONLY)
SERVICE PORTS
CONDENSER
COMPRESSOR
Figure 21-3. Air Conditioning Components Location
21-4
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
RH
VENT
BLWR
LH
VENT
BLWR
10
10
HF1
HF7
L L
K K
HF15
HF17
HF22
HF23
RH VENT
FAN MOTOR
6 78 5
6 78 5
HF10
HF20
HF4
HF8
RH
VENT
BLWR 10
RH
WING
9 9
8 8
HF5
HF6
LH
VENT
BLWR 10
1 1
2 2
HF1
HF7
L L
K K
HF15
HF17
RH VENT
FAN MOTOR
6 78 5
6 78 5
HF10
HF4
HF8
A
RH
WING
HF22
HF23
HF20
9 9
8 8
HF5
HF6
1 1
2 2
HF21
9 9
19 19
HF11
HF12
1 1
2 2
A
RH SWITCH
RH SWITCH
HF21
HF2
9 9
19 19
HF11
HF12
I
LEGEND
LH SWITCH
POSITIVE POWER OR
SWITCHABLE POWER
CONDITION:
BATTERY ON
LH
WING
OVERHEAD CONSOLE
LEGEND
1 1
2 2
BATTERY POWER
LH VENT
FAN MOTOR
HF2
I
LH SWITCH
POSITIVE POWER OR
SWITCHABLE POWER
GROUND
CONDITION:
BATTERY ON
LH SELECTED ON
Figure 21-4. Ventilation Blowers (Sheet 1 of 2)
LH
WING
LH VENT
FAN MOTOR
OVERHEAD CONSOLE
21
Figure 21-4. Ventilation Blowers (Sheet 2 of 2)
NOTES
Revision 0
FOR TRAINING PURPOSES ONLY
21-5
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
CONTROL
SWITCH
CONTROL
SWITCH
AFT
VENT
BLO
BLOWER
SWITCHES
VENT
10
HE1
N
N
HE5
HE21
HE22
OFF
HE10
COOL
RH
VENT
BLO
LH
VENT
BLO
AC
10
10
5
HE2
r
r
HE6
HE56
HE57
1
2
1
2
3
RH WING CONN.
HE23
HE24
HE11
1
2
1
2
HE51
HE50
1
3
4
2
1
3
4
2
HE33
HE34
HE46
1
2
3
1
2
3
1
2
3
ORN
RED
BLK
AFT
VENT
BLO
M
10
HE1
N
N
HE5
AFT EVAP.
HE21
HE22
OFF
HE10
COOL
1
2
HE56
HE57
1
2
RH WING CONN.
HE58
ORN
RED
BLK
X
M
RH
VENT
BLO
RH EVAP.
10
HE2
r
r
HE6
HE3
HE74
EE EE
s
s
HE7
HE78
HE25
HE26
HE12
POSITIVE POWER OR SWITCHABLE POWER
3
4
HE52
HE53
HE35
HE36
HE47
1
2
3
1
2
3
ORN
RED
BLK
M
LH
VENT
BLO
LH EVAP.
LH WING CONN.
HE82
HE83
1
2
1
2
BLK/GRN
1
4
3
2
10
AC
ORN
COMPRESSOR
CLUTCH
N M
5
1
2
3
ORN
RED
BLK
M
AFT EVAP.
HE58
HE11
1
2
1
2
HE51
HE50
1
3
4
2
1
3
4
2
HE33
HE34
HE46
1
2
3
1
2
3
ORN
RED
BLK
HE12
HE25
HE26
3
4
3
4
HE52
HE53
1
4
3
2
1
4
3
2
HE35
HE36
HE47
1
2
3
1
2
3
ORN
RED
BLK
X
M
RH EVAP.
HE55
HE3
EE EE
HE7
HE54
RH & LH VENT
& AC CONN.
16 GA.
JUMPER
BATTERY POWER
3
4
1
4
3
2
1
2
3
HE23
HE24
HE55
LEGEND
21
1
2
BLOWER
SWITCHES
VENT
HE74
s
s
HE78
LEGEND
LH EVAP.
HE54
RH & LH VENT
& AC CONN.
16 GA.
JUMPER
M
LH WING CONN.
HE82
HE83
1
2
1
2
ORN
COMPRESSOR
CLUTCH
N M
BATTERY POWER
GROUND
BLK/GRN
BLK/GRN
BLK/GRN
POSITIVE POWER OR SWITCHABLE POWER
CONDITION:
BATTERY ON
PRESSURE
SWITCH
CONDITION:
BATTERY ON
COOL SELECTED
Figure 21-5. Vapor Cycle AC Electrical (Sheet 1 of 2)
PRESSURE
SWITCH
Figure 21-5. Vapor Cycle AC Electrical (Sheet 2 of 2)
NOTES
21-6
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
(G1000 ONLY)
20 GA. JUMPER
A
HB16
A
A
B
B
BLEED AIR HEAT SWITCH
CABIN HEAT
HB16
B
HB20
Z
HB17
THERMAL SWITCH
A
A
C
C
A
A
B
B
Z
A
A
C
C
HB14
HB14
LEGEND
CONDITION:
POWER ON BUS
HB20
THERMAL SWITCH
HB21
LEGEND
POSITIVE POWER OR
SWITCHABLE POWER
CABIN HEAT
Z
HB17
FLOW CONTROL
VALVE SOLENOID
Z
FLOW CONTROL
VALVE SOLENOID
HB21
#1 GIA63W
ON
#1 GIA63W
ON
CABIN HEAT
OFF
HB15
A
BLEED AIR HEAT SWITCH
B
20 GA. JUMPER
CABIN HEAT
OFF
HB15
#2 GIA63W
(G1000 ONLY)
#2 GIA63W
NC
NO
5
BATTERY POWER
5
POSITIVE POWER OR
SWITCHABLE POWER
GROUND
BLEED AIR HEAT
C
CONDITION:
ON SELECTED
SAFETY SWITCH
Figure 21-6. Bleed Air Heat (Sheet 1 of 2)
NC
NO
21
BLEED AIR HEAT
C
SAFETY SWITCH
Figure 21-6. Bleed Air Heat (Sheet 2 of 2)
NOTES
Revision 0
FOR TRAINING PURPOSES ONLY
21-7
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
21
21-8
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
CHAPTER 22
AUTO FLIGHT
22
INTRODUCTION
The Cessna 208 has several options for autoflight. Typical installations include the Garmin G1000 integrated avionics system, the King
KFC-225 or the King KFC/KAP-150 autopilot/flight control system (AFCS). Other installations include the Sperry 400B navomatic
autopilot or the Sperry 400B integrated flight control system and the King KFC-250 flight control system.
GENERAL
Any of these systems allows the crew to automatically or manually
control the flight of the aircraft.
• Pitch command
The systems provide the following functions:
• Back course switching
• Tracking of any magnetic heading
• NAV 1 or NAV 2 receiver selection
• Automatic intercept and tracking of VOR radials or ILS localizer and glide slope beams
• Pitch attitude disengagement with associated warning tone
• Automatic pitch synchronization and trim
• Manual turn (400B only)
Revision 0
• Altitude hold
FOR TRAINING PURPOSES ONLY
The autoflight system includes annunciator lights. The Sperry 400B system
includes an A/P ROLL TRIM indicator that signals any adjustments necessary to neutralize autopilot roll effort and a prior-to-flight test function.
22-1
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
DESCRIPTION
HDG
APR
NAV
HDG
FD
XFR
ALT
CRS1
VS
BC
BANK
YD
AP
The Cessna Caravan aircraft has the GFC 700 AFCS to help decrease
the pilot workload during flight. This section describes the controller
and autopilot servo installations used by the AFCS. This section also
has references to the Garmin G1000 integrated avionics system. For a
general description of the G1000 system, refer to Chapter —”Navigation.”
FLC
DN
ALT SEL
CRS2
VNV
SPD
UP
E
160
1-2
20
20
10
10
10200
10100
150
20
3100 00
100
145
140
10
130
120
HDG
10
21
15
CDI
+
DME
IDENT
331°
38.0NM
FRAME
324°
73.2NM
334°
10.0NM
R LCL
NRST
08:44:27
ALERTS
D
MENU
FPL
PROC
ENT
DFLT MAP
700
24CL
V107
FMS
EHF
FFLOW PPH
379
4
28.0
A–ICE GAL
4.7
TRAFFIC
V25
V186
V22
V137
V201
V107
AIRWY
XWHP
V107
XBUR
V23
10
HDG
GDC 74A #1
Air Data
Computer
OAT
Airspeed
Altitude
Vertical Speed
GRS 77 #1
AHRS
Attitude
Pitch
Rate Of Turn
Slip/Skid
GMU 44 #1
Magnetometer
Heading
GSA 81 Pitch Trim
10200
10100
V12
MAP WPT AUX NRST
D
MENU
FPL
PROC
CLR
ENT
TERRAIN
KVCV-- 100FT
80NM
BACK
–1000FT
DFLT MAP
33
GPS
OAT__– 5°c
FMS
??????
INSET
37.9NM
EHF
NAV1
SENSOR
PFD
80
127.100 COM1
122.450 COM2
CRS
331°
N
ENR
OBS
CDI
PUSH
VOL SQ
COM
EMERG
2
1
PUSH
1-2
BARO
-900
1
9800
328°
30
PUSH
9900
10
328°
PAN
V386
V197
128.375
121.500
20
+
KWJP
KPMD
V27
316
10
PUSH
STD
9700
29.92IN
2
RANGE
–
+
GDC 74A #2
Air Data
Computer
OAT
Airspeed
Altitude
Vertical Speed
GRS 77 #2
AHRS
Attitude
Pitch
Rate Of Turn
Slip/Skid
GMU 44 #2
Magnetometer
Heading
GSA 81 Yaw Servo
The GRS 77 AHRS, 74A Air Data Computer, and GMU 44 Magnetometer are responsible for providing the G1000 system with flight
instrumentation. Data consists of aircraft attitude, heading, altitude,
airspeed vertical speed and outside air temperature information, all
displayed on the Primary Flight Display (PFD) (data is displayed on
the MFD in reversionary mode).
PUSH
PAN
D
DME
MENU
FPL
50.0NM
FLW
NAV2
XPDR
XPDR1
IDENT
4234 ALT
TMR/REF
R LCL
NRST
08:44:27
ALERTS
PROC
CLR
DFLT MAP
ENT
FMS
PUSH CRSR
PUSH CRSR
S
22
GSA 81 Pitch Servo
120
331°
310000
100
130
–
KEDW
KCMA
KNTD
20
10
150
PUSH
STD
V23
KMHV
V107
20
145
RANGE
V137
V183
TERRIAN
160
1-2
BRG
10
000
10300
170
L
V459
V25
PUSH CRSR
No. 1 GIA 63W
Integrated Avionics Unit
VHF COM
VHF NAV/LOC
GPS
Glideslope
AFCS Mode Logic
Flight Director Computations
Servo Management
KNID
V12
KSBA
TOPO
PUSH
DIS 38.0NM
EHF
AP YD ALT 10000FT
140
GMN
BAT AMPS
BUS VOLTS
NAV
PUSH
1-2
KRFL
FUEL QTY
LBS
R
O
F
F
COM
GMN
GPS
115.40 EHF
117.80 FLW
V165
KSMX
V27
VOL ID
BARO
V485
KVBC
NAV1 116.90
NAV2 112.50
PUSH
PUSH
VOL SQ
TRACK UP
KDLO
KSBP
1900
95
10KT
KPTV
V23
V113
V27
127.100 COM1
122.450 COM2
128.375
121.500
V165
V459
R
V137
96.5
85
PAN
CLR
900
OIL °C
L
GMN
TMR/REF
DIS 38
KVISV459
EMERG
V248
KPRB
100
OIL PSI
PUSH
DTK
DIS
– – –° – – – –NM
4234 ALT
% RPM
PROP RPM
RANGE
–
V23.FRAME
XPDR1
°C
0
12
2
KFAT
KHJO
600
50
FLIGHT PLAN
12
OBS
1-2
1-2
BARO
KLGB / KFAT
50.0NM
FLW
NAV2
XPDR
GS 175
N
20
1650
0
331°
MAP - NAVIGATION MAP
ITT
-900
GMN
FT–LB
X100
10
DTK
C80
E
INSET
PUSH
1
PUSH
STD
9700
29.92IN
E
??????
NAV
PUSH
2
ETE 13:47
6
24
ENR
6
OAT__– 5°c
331°
COM
15
3
GPS
CRS
N
3
W
33
VOL ID
1
9800
328°
328°
30
37.9NM
EHF
NAV1
SENSOR
PFD
9900
80
EMERG
115.40 EHF
117.50 FLW
NAV 2 112.50
TRQ
PUSH
PUSH
VOL SQ
W
170
NAV 1 116.90
127.100 COM1
122.450 COM2
128.375
121.500
10
000
10300
NAV
PUSH
331°
24
BRG
21
DIS 38.0NM
EHF
AP YD ALT 10000FT
S
GMN
GPS
115.40 EHF
117.80 FLW
PUSH DIR
15
NAV1 116.90
NAV2 112.50
PUSH
VOL ID
PUSH DIR
12
PUSH SYNC
Data outputs from the GRS and GDC 74A are sent directly to the PFD
1 and 2 and the MFD via ARINC 429. Additional communications
paths connect the GRS and GDC 74A to on-side GIA 63W units,
providing quadruple redundant interface.
The GRS 77 received GPS data from both GIAs, airspeed data from
the GDC 74A, and magnetic heading from the GMU. Using these
three external sources, combined with internal sensor data, the GRS
accurately calculates aircraft attitude and heading.
No. 2 GIA 63W
Integrated Avionics Unit
VHF COM
VHF NAV/LOC
GPS
Glideslope
AFCS Mode Logic
Flight Director Computations
Servo Management
NOTES
GSA 81 Roll Servo
Figure 22-1. Garmin GFC 700 Interconnect
22-2
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
A/P Master Switch
AP
NAV
REV
ALT
VS
HDG
APR
GS
CAP
GA
YD
ARM
ARM
ALT
TRIM
AP
Audio Alert
Remote Terminal
I/F Connector
(AFCS Maint. Plug)
TRIM
FAIL
OR
KA 285
Remote Mode
Annunciator
Trim Fail
Annunciator
DH
HDG
YD
20
10
10
20
10
20
gs
P
KCM 100
Configuration
Module
KC 225
Flight Computer
AIR
20
10
NOTES
ALT
AP
a lt
A YD
R
M
A
R
M
1.300
ALERT
FT
ARM
VS
ALT SEL
Aircraft
Static
Port
UP
R
AP
FD
HDG
NAV
APR
REV
ALT
DN
KFC 225
KI 256 Attitude Gyro
ALT
0
9
6001
0, 500
400
8
ALT
7
9
8
2
mb
100
FEET
0
1
ALT
1010
MB
IN HG
29.99 3
1016
5
6
7
4
5
6
OR
B
ENCODING
5
4
KS 271C
Roll Servo
2
IN.Hg
1005
3
29.7
29.8
KEA 130A
Encoding
Altimeter
KEA 346
Servoed
Altimeter
DC
TST
CRS
1
2
N
W
21
12
G
S
12
1
H
S
I
E
33
OR
KS 272C
Trim Servo
REF
11.
5
3
6
30
24
L
O
C
N
A
V
N
30
33
24
GS
S
W
15 S
4. NM
5120 KT
350
12
HDG
21
15
NAV
GS
22
KS 270C
Pitch Servo
A
R
C
330°
3
ADF 2
6
E
CRS
HDG
BRT
KCS 55A
Compass
System
Optional Yaw Axis
EHI40
EFIS
KS 271C
Yaw Servo
CRSR
NAV
FPL
MODE
TRIP
CRSR
CALC
STAT
SETUP
OTHER
MSG
ALT
D
CLR
ENT
Optional
ARINC 429
GPS Interface
NAV
D/T
ACTV
REF
CTR
PULL
SCAN
20
15
APT
VOR
NDB
INT
SUPL
KRG 331
OR
KRG 332
Rate Gyro
O
G
33
2
2
KR
1
GYR
0
RADAR ALT
X 100 FEET
RA
TE
BRT
ı
DH
GPS
B
KLN 90B TSO
3
10
5
4
TEST
Optional
KRA 10A
Radar Altimeter System
TRIM
DN
TRIM
UP
Cessna
Cessna
Caravan I
Caravan I
MAP LIGHT
LO
HI
0705028-3
Optional Dual
Control Wheel Switches
Control Wheel Switches
Figure 22-2. KFC—225 Schematic
Revision 0
FOR TRAINING PURPOSES ONLY
22-3
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
AP
NAV
REV
ALT
HDG
APR
GS
CAP
GA
BC
A
O
M
TRIM
NOTES
VOR/LOC/RNAV
Deviation
VS
Glideslope
Deviation
KA 185 Mode Annunciator
(Optional on some aircraft)
Static
Pressure
Middle
Marker
KC 191 Computer/
Controller/Annunciator
contains computer
functions, mode control
buttons and annunciator
lights in a single unit.
Also contains altitude
sensor.
AIR
DH
Pitch Attitude/Roll Attitude
10
20
10
20
DC
TO
BC
TRIM
TEST
ALT
HDG
NAV
APR
BC
AP
AP
ENG
KS 178
Roll
Servo
15
N
FR
12
N
3
S
OB
E
15 S
APR
33
GS
33
12
NAV
W
S
GS
30
6
E
22
GS
30
W
24
24
21
HDG
21
GS
HDG
KAP
Heading Select & Course Datum
KG258 Attitude
Reference Indicator
NAV
ALT
DN
UP
6
20
10
3
20
10
KS 177
Pitch
Servo
KI 204 OR other
Course Deviation
Indicator (not included)
KG 107
Directional Gyro
KS 179
Pitch Trim
Servo
OR
DC
NAV
KG 102A
Slaved DG
HDG
W
21
GS
Autopilot
Disconnect
Trim Interrupt
30
33
15 S
GS
ING
WARN
N
12
24
3
TRIM
DN
6
E
TRIM
UP
KMT 112
Flux Detector
KI 525A Pictorial
Navigation
Indicator
Cessna
Caravan I
-
KCS 55A Slaved
Compass System
(Optional)
+
FREE
CW
SLAVE
CCW
MAP LIGHT
LO
HI
0705028-3
OR
SLAVE
IN
KA 51A
Manual
Electric Trim
KA 51B
Control
Wheel
Steering
Slaving Accessory
DN
UP
ALT
HDG
ALT
HDG
GS
NAV
APR
BC
NAV
APR
BC
KAP
TRIM
TEST
O
GYR
ı
RA
TE
KR
G
33
2
KC 191 Autopilot
Computer/Controller
Annunciator
AP
AP
ENG
YD Annunciator
Panel-Mounted
Yaw Control
Switch
YAW
DAMP
(May not be included
in all Yaw Damper
installations)
YD Engage &
Roll Crossfeed
K296
THIS IS A
PUTER
YAW COM
KRG 331
Rate Gyro
KS 178
Yaw Servo
KC 296
Yaw Computer
Figure 22-3. King KAP 150—3 Axis Autopilot
22-4
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
VOR/LOC/RNAV
Deviation
AP
NAV
REV
ALT
VS
HDG
APR
GS
CAP
GA
BC
A
O
M
TRIM
Glideslope
Deviation
KA 185 Mode Annunciator
(Optional on some aircraft)
Static
Pressure
Middle
Marker
AIR
DH
20
10
20
10
10
20
10
20
Pitch Altitude/ Roll Altitude
FD
DN
ALT
HDG
ALT
HDG
GS
NAV
APR
BC
NAV
APR
BC
TRIM
KFC 150
UP
FD
TEST
AP
AP
ENG
Pitch Command/
Roll Command
KC 192 Computer/
Controller/Annunciator
contains computer
functions, mode control
buttons and annunciator
lights in a single unit.
Also contains altitude
sensor.
KI 256 Flight
Command Indicator
DC
NAV
HDG
W
21
GS
Heading Select & Course Datum
30
33
15 S
GS
KS 178
Roll Servo
N
12
24
3
E
6
KI 525A Pictorial
Navigation Indicator
KS 177
Pitch Servo
KMT 112
Flux
Detector
KG 102A
Slaved DG
22
KS 179
Trim Servo
ING
WARN
Autopilot Disconnect /
Trim Interrupt
TRIM
DN
TRIM
UP
Manual
Electric Trim
-
FREE
+
CW
Cessna
SLAVE
SLAVE
IN
Caravan I
Control Wheel
Steering
OR
CCW
MAP LIGHT
LO
HI
0705028-3
KA 51B
KA 51A
Slaving Accessory
DN
UP
ALT
HDG
ALT
HDG
GS
NAV
APR
BC
NAV
APR
BC
KAP
TRIM
TEST
G
KR
ı
RA
TE
GYR
O
33
2
KC 191 Autopilot
Computer/Controller
Annunciator
AP
AP
ENG
YD Annunciator
Panel-Mounted
Yaw Control
Switch
YAW
DAMP
(May not be included
in all Yaw Damper
installations)
YD Engage &
Roll Crossfeed
K296
THIS IS A
PUTER
YAW COM
KRG 331
Rate Gyro
KS 178
Yaw Servo
KC 296
Yaw Computer
Figure 22-4. King KFC 150—3 Axis Autopilot
Revision 0
FOR TRAINING PURPOSES ONLY
22-5
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
22
22-6
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
CHAPTER 23
COMMUNICATIONS
23
INTRODUCTION
This chapter briefly describes various communication systems, units and components that permit internal, airplane-to-airplane, or
airplane-to-ground communications. The aircraft can be configured with multiple configurations from Garmin, Sperry and King
GENERAL
Revision 0
Garmin G1000
Non-G1000
The Garmin system uses G1000®­line replaceable units (LRU’s)
for the major subsystems and supporting equipment. The system is
regulated and coordinated by central processing computers in the two
Garmin® integrated avionics units (GIA’s), which contain essential
navigation and communications avionics equipment.
A typical installation includes the King KX 165 NAV/COMM system
and the King KMA-24 audio console with two communication jacks,
a handheld microphone on the center pedestal, a yoke microphone
switch on the pilot yoke, two headsets, and an antenna.
FOR TRAINING PURPOSES ONLY
23-1
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
23
Figure 23-1. 208 King Audio Control System
23-2
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
COM1 MIC
COM1
COM2 MIC
COM2
COM3 MIC
COM3
COM 1/2
PA
MKR/MUTE
DME
TEL
SPKR
HI SENS
NAV1
23
ADF
NAV2
AUX
MAN SQ
PILOT
PILOT KNOB
PLAY
COPLT
PASS KNOB
REVERSIONARY MODE
(DISPLAY BACKUP) BUTTON
Figure 23-2. 208 G1000 Audio Panel Controls (GMA 1347)
Revision 0
FOR TRAINING PURPOSES ONLY
23-3
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
GDL 69A
XM SATELLITE
RADIO RECEIVER
REAL-TIME WEATHER
DIGITAL AUDIO ENTERTAINMENT
15
FT–LB
X100
170
1-2
E
20
20
10
10
10200
10100
150
20
3100 00
100
145
140
10
130
120
HDG
N
ENR
2
12
DME
IDENT
4234 ALT
TMR/REF
OIL PSI
95
OIL °C
85
MKR
MUTE
HI
SENS
NAV1
ADF
NAV2
331°
324°
334°
R LCL
NRST
D
MENU
FPL
PROC
CLR
ENT
38.0NM
73.2NM
10.0NM
08:44:27
ALERTS
DFLT MAP
MAN
SQ
CREW
PILOT
1900
EHF
KRFL
KSMX
V137
V183
GMN
379
BAT AMPS
BUS VOLTS
4
28.0
A–ICE GAL
4.7
V25
V186
V107
V137
316
V107
AIRWY
XWHP
V107
XBUR
V23
V12
V197
20
10
10
KVCV-- 100FT
80NM
BACK
–1000FT
FPL
10
HDG
30
ENT
FMS
COPLT
PASS
PUSH CRSR
OAT__– 5°c
??????
INSET
37.9NM
EHF
NAV1
SENSOR
PFD
9900
10
33
GPS
80
127.100 COM1
122.450 COM2
CRS
331°
N
ENR
OBS
CDI
PUSH
VOL SQ
COM
EMERG
2
1
PUSH
1-2
BARO
-900
1
9800
328°
328°
PROC
CLR
DFLT MAP
10100
20
130
120
128.375
121.500
10200
140
MENU
331°
310000
100
TERRAIN
V386
MAP WPT AUX NRST
20
150
PUSH
D
KPMD
BRG
145
PAN
KWJP
V201
KCMA
KNTD
TERRIAN
1-2
+
KEDW
V22
V27
TOPO
160
PUSH
–
KMHV
V12
KSBA
O
F
F
FFLOW PPH
L
PUSH
STD
V23
DIS 38.0NM
EHF
AP YD ALT 10000FT
10
000
10300
170
RANGE
V25
V27
FUEL QTY
L
LBS
R
TRAFFIC
KNID
V459
KVBC
GMN
GPS
115.40 EHF
117.80 FLW
V165
FMS
15
S
PUSH CRSR
NAV1 116.90
NAV2 112.50
NAV
ICS ISOLATION
PILOT
VOL
23
PLAY
V107
96.5
12
TEL
SPKR
1-2
BARO
V485
100
COM3
DME
KSBP
VOL ID
PUSH
KDLO
V113
V27
PUSH
STD
9700
29.92IN
2
RANGE
–
+
PUSH
PAN
D
E
FRAME
KFAT
XPDR1
PAN
700
PA
PUSH
DTK
DIS
– – –° – – – –NM
% RPM
900
6
21
+
COM
PUSH
°C
0
COM
1/2
AUX
V23.FRAME
E
CDI
RANGE
–
GMN
OBS
1-2
KLGB / KFAT
50.0NM
FLW
NAV2
XPDR
1-2
PUSH
VOL SQ
TRACK UP
KPTV
V23
600
PUSH
PROP RPM
PUSH
BARO
-900
GMN
COM2
COM3
MIC
1
PUSH
STD
9700
29.92IN
COM1
COM2
MIC
127.100 COM1
122.450 COM2
10KT
EMERG
R
V137
KPRB
ITT
COM1
MIC
50
FLIGHT PLAN
6
INSET
331°
2
1
9800
CRS
24
GPS
80
PUSH
VOL SQ
COM
EMERG
128.375
121.500
V165
V459
3
W
33
3
??????
37.9NM
EHF
NAV1
SENSOR
PFD
9900
10
328°
328°
30
OAT__– 5°c
127.100 COM1
122.450 COM2
128.375
121.500
10
000
10300
160
PUSH
331°
DIS 38
KVISV459
24CL
W
BRG
KHJO
24
DIS 38.0NM
EHF
AP YD ALT 10000FT
GS 175
S
GMN
GPS
115.40 EHF
117.80 FLW
NAV
331°
MAP - NAVIGATION MAP
15
NAV1 116.90
NAV2 112.50
PUSH
DTK
C80
V248
1650
0
ETE 13:47
N
20
21
10
VOL ID
115.40 EHF
117.50 FLW
NAV 2 112.50
TRQ
NAV
12
NAV 1 116.90
PUSH
VOL ID
DME
FPL
50.0NM
FLW
NAV2
XPDR
XPDR1
IDENT
4234 ALT
TMR/REF
R LCL
NRST
08:44:27
ALERTS
MENU
PROC
CLR
DFLT MAP
ENT
FMS
SQ
PUSH CRSR
DISPLAY BACKUP
NO. 1 GIA 63W
INTEGRATED AVIONICS UNIT
NO. 2 GIA 63W
INTEGRATED AVIONICS UNIT
SYSTEM INTEGRATION PROCESSORS
I/O PROCESSORS
VHF COM
VHF NAV/LOC
GPS
GLIDESLOPE
AFCS MODE LOGIC
FLIGHT DIRECTOR CALCULATIONS
SERVO MANAGEMENT
GPS OUTPUT
SYSTEM INTEGRATION PROCESSORS
I/O PROCESSORS
VHF COM
VHF NAV/LOC
GPS
GLIDESLOPE
AFCS MODE LOGIC
FLIGHT DIRECTOR CALCULATIONS
SERVO MANAGEMENT
GPS OUTPUT
Figure 23-3. G1000 Communications Block Diagram
23-4
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
GMA 1347 #2 (OPT)
AUDIO PANEL
NOTES
REVERSIONAL
CONTROL
MARKER BEACON
INTERCOM CONTROL
DIGITAL AUDIO CONTROL
REV. MODE
GDU 1040A
MFD
HIGH-SPEED DATA BUS (ETHERNET)
REV. MODE
TRANSPONDER INTERFACE
(REVERSIONARY MODE ONLY)
HIGH-SPEED DATA BUS (ETHERNET)
CONTROL & DISPLAY OF:
COM/NAV RADIOS
VARIOUS NAVIGATIONAL FUNCTIONS
GDU 1040A
PFD
GDU 1040A
PFD
CONTROL & DISPLAY OF:
COM/NAV RADIOS
TRANSPONDER INTERFACE
VARIOUS NAVIGATIONAL FUNCTIONS
CONTROL & DISPLAY OF:
COM/NAV RADIOS
TRANSPONDER INTERFACE
VARIOUS NAVIGATIONAL FUNCTIONS
HIGH-SPEED DATA BUS
(ETHERNET)
NO. 1 GIA 63W
INTEGRATED AVIONICS UNIT
VHF COM
VHF NAV/LOC
GPS
GLIDESLOPE
VARIOUS I/O PROCESSORS
DIGITAL COM/NAV AUDIO
VOICE ALERTS
GMA 1347
AUDIO PANEL
REVERSIONAL
CONTROL
23
MARKER BEACON
INTERCOM CONTROL
DIGITAL AUDIO CONTROL
NO. 2 GIA 63W
INTEGRATED AVIONICS UNIT
GTX 33
MODE S
TRANSPONDER
VHF COM
VHF NAV/LOC
GPS
GLIDESLOPE
VARIOUS I/O PROCESSORS
DIGITAL COM/NAV AUDIO
VOICE ALERTS
GTX 33
MODE S
TRANSPONDER
(OPTIONAL)
Figure 23-4. G1000 Navigation/Communication Data Paths
Revision 0
FOR TRAINING PURPOSES ONLY
23-5
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
23
23-6
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
CHAPTER 24
ELECTRICAL POWER
24
INTRODUCTION
This chapter provides a description of the electrical system used on the CARAVAN I series aircraft. Included is information on system
regarding generation, distribution, monitoring and system controls. Accompanying this chapter is a selection of electrical system
schematics, found in the program supplemental book, which will be used to enhance understanding of the aircraft electrical systems
and components. References for this chapter and further specific information can be found in Chapter 24–Electrical Power, Chapter
80–Starting; Chapter 5–Time Limits/Maintenance Checks, and Chapter 12–Servicing of the Model 208 Maintenance Manual.
GENERAL
The electrical system is a 28-volt, single wire, negative ground, direct
current system. The system has two general buses, two avionics buses
with a normally open bus tie switch, and a battery bus. A 200-amp
starter/generator and a battery supply power.
Revision 0
FOR TRAINING PURPOSES ONLY
An optional 300-amp starter/generator may be installed.
An optional 75-amp alternator provides standby electrical power.
An external power source is available through an airframe-mounted
receptacle.
24-1
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
ALTERNATOR
STARTER-GENERATOR
GENERATOR
CONTACTOR
ALT
SHUNT
GEN
SHUNT
ALTERNATOR
CONTACTOR
ALTERNATOR
CONTROL UNIT
EXTERNAL
POWER
SWITCH
GENERATOR
CONTROL
UNIT
NOTES
STANDBY
ALTERNATOR
POWER
SWITCH
NO. 1
BUS
INTERNAL
START
CONTACTOR
EXTERNAL
START
CONTACTOR
ALTERNATOR
BUS
GROUND
POWER
MONITOR
AVIONICS
STANDBY
POWER
SWITCH
EXTERNAL
POWER
NO. 2
BUS
EXTERNAL
POWER
CONTACTOR
24
BATTERY
CONTACTOR
NO. 1 AVIONICS
POWER SWITCH
BATT
SHUNT
BATTERY
SWITCH
BUS TIE
SWITCH
NO. 1
TO HOURMETER
NO. 2 AVIONICS
POWER SWITCH
TO CABIN LIGHTS
BATTERY
TO ELT
TO ETM
TO ANTICYCLE SWITCH
BATTERY BUS
LEGEND
BATTERY POWER
POWER
DISTRIBUTION
BUS
NO. 2
CONDITIONS:
BATTERY CONNECTED
BATTERY SWITCH—OFF
GROUND
Figure 24-1. Electrical Switch Panel and Annunciator Panel
24-2
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
ALTERNATOR
STARTER-GENERATOR
ALT
SHUNT
GEN
SHUNT
GENERATOR
CONTACTOR
ALTERNATOR
CONTACTOR
ALTERNATOR
CONTROL UNIT
EXTERNAL
POWER
SWITCH
GENERATOR
CONTROL
UNIT
NOTES
STANDBY
ALTERNATOR
POWER
SWITCH
NO. 1
BUS
INTERNAL
START
CONTACTOR
EXTERNAL
START
CONTACTOR
ALTERNATOR
BUS
GROUND
POWER
MONITOR
AVIONICS
STANDBY
POWER
SWITCH
EXTERNAL
POWER
NO. 2
BUS
EXTERNAL
POWER
CONTACTOR
BATTERY
CONTACTOR
NO. 1 AVIONICS
POWER SWITCH
24
BATT
SHUNT
BATTERY
SWITCH
BUS TIE
SWITCH
NO. 1
TO HOURMETER
NO. 2 AVIONICS
POWER SWITCH
TO CABIN LIGHTS
BATTERY
TO ELT
TO ETM
TO ANTICYCLE SWITCH
BATTERY BUS
LEGEND
BATTERY POWER
POWER
DISTRIBUTION
BUS
NO. 2
CONDITIONS:
BATTERY CONNECTED—ON
BATTERY SWITCH—ON
GROUND
Figure 24-2. Power Distribution—Battery Power
Revision 0
FOR TRAINING PURPOSES ONLY
24-3
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
ALTERNATOR
STARTER-GENERATOR
ALT
SHUNT
GEN
SHUNT
GENERATOR
CONTACTOR
ALTERNATOR
CONTACTOR
ALTERNATOR
CONTROL UNIT
EXTERNAL
POWER
SWITCH
GENERATOR
CONTROL
UNIT
NOTES
STANDBY
ALTERNATOR
POWER
SWITCH
NO. 1
BUS
INTERNAL
START
CONTACTOR
EXTERNAL
START
CONTACTOR
ALTERNATOR
BUS
GROUND
POWER
MONITOR
AVIONICS
STANDBY
POWER
SWITCH
EXTERNAL
POWER
NO. 2
BUS
EXTERNAL
POWER
CONTACTOR
24
BATTERY
CONTACTOR
NO. 1 AVIONICS
POWER SWITCH
BATT
SHUNT
BATTERY
SWITCH
BUS TIE
SWITCH
NO. 1
TO HOURMETER
NO. 2 AVIONICS
POWER SWITCH
TO CABIN LIGHTS
BATTERY
TO ELT
TO ETM
POWER
DISTRIBUTION
BUS
TO ANTICYCLE SWITCH
BATTERY BUS
LEGEND
BATTERY POWER
NO. 2
CONDITIONS:
EXTERNAL POWER CONNECTED—ON
EXTERNAL POWER SWITCH—BUS
GROUND
Figure 24-3. Power Distribution—External Power
24-4
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
GENERATOR
FIELD
GENERATOR
CONTACTOR
L PITOT HT
BUS 1
FROM
START
CONTROL
CIRCUIT
BREAKER
STARTER
SWITCH
TO NO. 1
BUS
GEN
CONTROL
GENERATOR OFF
PROP ANTI-ICE
PRIM PRIM ANTI-ICE
FUEL SEL WARN
LINE
CONT
SENSE
START CONT
TRQ IND
IGNITION SWITCH
STARTER/
GENERATOR
GEN AMPS
TO NO. 1
BUS
INTERNAL
START
CONTACTOR
RDNG LIGHT
BUS 1
INST LIGHT
L LDNG LIGHT
STROBE LIGHT
BEACON LIGHT
TO NO. 1
BUS
WING ICE DET LIGHT
R FUEL QTY
GROUND
SNUBBER DIODE GROUND
GENERATOR INTERPOLE
FUEL FLOW NG & NP
IGNITION ON
FUEL CONT HEATER
SPEED SENSOR
TO NO. 2
BUS
START INPUT
POWER INPUT
GENERATOR EXITATION
GENERATOR TRIP
GENERATOR ON
GENERATOR
SWITCH
BUS 1
AIRSPEED WARN
LEFT VENT BLWR
AFT VENT BLWR
TO NO. 2
BUS
POINT OF REGULATION
ANTI-CYCLE SIGNAL
LINE CONTACTOR SENSE
FROM
START
CONTROL
CIRCUIT
BREAKER
FLAP MTR
EXTERNAL
START
CONTACTOR
GENERATOR RESET
STBY PWR INOP
STBY PWR
GENERATOR
SHUNT
START POWER
TO LEFT PITOT HEAT
TO PRIM ANTI-ICE
ALTERNATOR
BUS
TO FUEL SELECTOR OFF
WARNING SYSTEM
ALTERNATOR ON
ALTERNATOR OUT
POWER IN
REMOTE SENSE
FIELD
AUXILIARY SENSE
LINE CONTACTOR
REMOTE SENSE
ALTERNATOR
CONTROL UNIT
TO STARTER SW. AND GCU
TO TORQ IND
TO IGNITION
TO READING LIGHT
ALT
SHUNT
TO INST LIGHT
TO LEFT LDG LIGHT
TO STROBE LIGHT
TO BEACON LIGHT
TO WING ICE DET LIGHT
AVIONICS
STANDBY
POWER
SWITCH/
BREAKER
ALTERNATOR
CONTACTOR
STBY
REGULATOR
ALT AMPS
ALTERNATOR
TO RIGHT FUEL QTY
LED
TO FUEL FLOW NG & NP
TO FUEL CONT HEATER
TO FLAP MOTOR
FROM
HOURMETER/ACU
C/B
STANDBY POWER SWITCH
TO AUDIO
AUDIO
TO AIRSPEED WARN
A/P SERVOS
TO LEFT VENT
BLWR/AIR COND
TO AFT VENT BLWR
AVIONICS
BUS
SPARE
SPARE
SPARE
SPARE
SPARE
RT PITOT HT
BUS VOLTS
EXTERNAL
POWER
SWITCH
GROUND
TO NO. 2
BUS
BUS 2
PROP ANTI-ICE CONT
BACKUP ANTI-ICE
EXTERNAL
POWER
CONTACTOR
W/S ANTI-ICE
AUX 12VDC PWR
BAT AMPS
L FUEL QTY
TO NO. 1
AVIONICS
POWER
SWITCH/
BREAKER
EXTERNAL
POWER
RECEPTACLE
AUX FUEL PUMP
ELT NAV INTFC
FUEL SEL WARN
TO RADAR R/T
RADAR R/T
SPARE
SPARE
SPARE
SEAT BELT SIGN
TO PROP ANTI-ICE CONT
COM 1
TO BACKUP ANTI-ICE
NAV 1
TO W/S ANTI-ICE
ENG INTFC
TO AUX 12VDC POWER
ADC 1
TO LEFT FUEL QTY
AHRS 1
TO FUEL SEL WARN
BUS 2
GROUND
POWER
MONITOR
TAXI LIGHT
TO NO. 2
AVIONICS
POWER
SWITCH/
BREAKER
BATTERY
CONTACTOR
RT LANDING LIGHT
NAV LIGHT
FIRE DET
PROP OVRSPD TST
AIR COND CONT
BATTERY
SWITCH
BAT SWITCH
TO HOURMETER
HOURMETER/ACU
CABIN LTS
BCN MONITOR
TO CABIN LIGHTS
BATTERY
SHUNT
DECK SKIN FANS
STBY FLAP MTR
POWER
DISTRIBUTION
BUS
BUS 2
STALL WARN
BLEED AIR HT
RIGHT VENT BLWR
TO RIGHT LANDING LIGHT
TO TAXI LIGHT
TO ETM
ETM CONTINUOUS POWER
AVIONICS
BUS 1
ADF 1
AVIONICS
BUS TIE
SWITCH/
BREAKER
COM 2
NAV 2
MFD
AVIONICS
BUS 2
TO FIRE DETECTION
TO PROP OVERSPEED TST
TO AIR CONDITIONING
CONTROL
TO DECK SKIN FANS
TO STANDBY FLAP MOTOR
TO STALL WARNING
ADC 2
AHRS 2
PFD 2
NUMBER 2
AVIONICS
POWER
SWITCH/
BREAKER
XPDR 2
TO COMMUNICATION RECEIVER 1
TO NAVIGATION RECEIVER 1
TO ENGINE INTERFACE
TO ATTITUDE HEADING REF SYSTEM 1
TO PRIMARY FLIGHT DISPLAY 1
TO TRANSPONDER 1
TO AUTO DIRECTION FINDER
SPARE
TO COMMUNICATION RECEIVER 2
TO NAVIGATION RECEIVER 2
TO MFD
TO AIR DATA COMPUTER 2
TO ATTITUDE HEADING REF SYSTEM 2
TO PRIMARY FLIGHT DISPLAY 2
TO TRANSPONDER 2
SPARE
SPARE
TAS
TO RIGHT VENT BLOWER
XM DATA LINK
AVIONICS
BUS 2
STORM SCOPE
HF RCVR
HF AMP
24
TO AIR DATA COMPUTER 1
DME
TO BLEED AIR HEAT
ANTI-CYCLE SWITCH
PFD 1
XPDR 1
TO NAVIGATION LIGHT
SPARE
SPARE
SPARE
SPARE
SPARE
TO ELT
NUMBER 1
AVIONICS
POWER
SWITCH/
BREAKER
TO SEAT BELT SIGN
TO AVN FLOOD LIGHT
TO ELT NAV INTFC
TO RADIO ALT
RADIO ALT
TO RIGHT PITOT HEAT
TO AUX FUEL PUMP
TO A/P SERVOS
TO A/P CONT
A/P CONT
STBY PWR
START OUT
LINE CONTACTOR
GENERATOR CONTROL UNIT
BATTERY
STBY PWR ON
TO PROP ANTI-ICE
TO DISTANCE MEASURING EQUIPMENT
TO TRAFFIC ADVISORY SYSTEM
TO XM – DATA LINK
TO STORM SCOPE
TO HIGH FREQUENCY RECEIVER
TO HIGH FREQUENCY AMP
SPARE
SPARE
SPARE
BATTERY
BUS
Figure 24-4. G1000 Overview—Typical Electrical System
Revision 0
FOR TRAINING PURPOSES ONLY
24-5
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
STBY PWR
FLAP MOTOR
STANDBY FLAP MOTOR
GENERATOR
FIELD
GENERATOR
SHUNT
GENERATOR
CONTACTOR
BUS 1
IGN
FUEL SEL WARN
TO PRIMARY FLAP MOTOR
TO STANDBY FLAP MOTOR
TO IGNITION EXCITER
TO FUEL SELECTOR OFF
WARNING SYSTEM
TO STARTER SW AND GCU
FROM
START
CONTROL
CIRCUIT
BREAKER
STARTER
SWITCH
START CONT
LEFT TURN BANK
GEN
CONTROL
LINE
CONT
SENSE
ANNUN PANEL
FIRE DET
BUS 1
STARTER/
GENERATOR
FUEL TOTAL
LEFT FUEL QTY
OIL TEMP
INTERNAL
START
CONTACTOR
BLEED AIR TEMP
AFT VENT BLWR
LEFT PITOT HEAT
W/S ANTI/ICE
W/S A/ICE CONT
GROUND
SNUBBER DIODE GROUND
GENERATOR INTERPOLE
LEFT LDG LIGHT
BUS 1
VOLT
AMMETER
SPEED SENSOR
BEACON LIGHT
START INPUT
POWER INPUT
GENERATOR EXITATION
GENERATOR TRIP
GENERATOR ON
GENERATOR
SWITCH
ANTI-CYCLE SIGNAL
LINE CONTACTOR SENSE
24
INST LIGHT
WING ICE DET LIGHT
SEAT BELT SIGN
VOLT/
AMMETER
SELECTOR
SWITCH
POINT OF REGULATION
FROM
START
CONTROL
CIRCUIT
BREAKER
MAP LIGHT
EXTERNAL
START
CONTACTOR
GENERATOR RESET
STROBE LIGHT
AMPHIB GEAR CONT
AMPHIB GEAR PUMP
START POWER
START OUT
LINE CONTACTOR
LEFT VENT BLWR
BUS 2
EXTERNAL
POWER
SWITCH
GROUND
RIGHT VENT BLWR
AUX FUEL PUMP
EXTERNAL
POWER
CONTACTOR
FUEL CONT HEATER
RIGHT TURN/BANK
ANNUN PANEL
STALL WRN
AIR COND CONT
ITT GAGE
FROM ANNUN
CIRCUIT BREAKER
BUS 2
FUEL FLOW
RIGHT FUEL QTY
AIR SPEED WARN
GROUND
POWER
MONITOR
PROP O-SPD TEST
DE-ICE BOOT
BATTERY
CONTACTOR
RIGHT PITOT HEAT
PROP ANTI-ICE
BATTERY SWITCH
+
CLOCK
–
BATTERY
SWITCH
TO CLOCK AND HOURMETER
TO CABIN LIGHTS
POWER
DISTRIBUTION
BUS
PROP ANTI-ICE CONTROL
RIGHT LDG LIGHT
BUS 2
TAXI LIGHT
NAV LIGHT
RADIO/FLOOD LIGHT
KEEP ALIVE 2
KEEP ALIVE 1
BATTERY
SHUNT
TO AVIONICS FREQUENCY MEMORY
RDNG LIGHT
RH ATT GYRO
BATTERY
ANTI-CYCLE SIGNAL
BATTERY
BUS
RH DIR GYRO
ENC ALTM
ELEV TRIM
ALTERNATOR
BUS
TO ANNUNCIATOR PANEL
AUXILIARY SENSE
LINE CONTACTOR
REMOTE SENSE
ALTERNATOR
CONTROL UNIT
TO FIRE DETECTOR SYSTEM
TO FUEL TOTALIZER
TO LEFT FUEL QUANTITY INDICATOR
TO OIL TEMPERATURE GAGE
ALT
SHUNT
TO BLEED AIR HEATER
AVIONICS STANDBY
CIRCUIT BREAKER
TO AIR CONDITIONING SYSTEM
TO LEFT PITOT HEATER
TO WINDSHIELD ANTI-ICE HEATER
TO WINDSHIELD ANTI-ICE CONTROL
ALTERNATOR
CONTACTOR
TO VOLT/ B
ALTERNATOR
AMMETER I
SELECTOR
F
SWITCH
G
TO LEFT LANDING LIGHT
TO STROBE LIGHTS
STANDBY POWER SWITCH
TO BEACON LIGHTS
COM 1
TO MAP LIGHTS
NAV 1
TO INSTRUMENT LIGHTS
AVIONICS
STANDBY
POWER
SWITCH/
BREAKER
TO WING ICE DETECTOR LIGHT
TO FASTEN SEAT BELT &
NO SMOKING SIGN
TO LANDING GEAR CONTROL
(AMPHIBIAN)
TO LANDING GEAR PUMP
(AMPHIBIAN)
STBY PWR
GENERATOR CONTROL UNIT
EXTERNAL
POWER
RECEPTACLE
TO LEFT TURN AND BANK INDICATOR
ALTERNATOR ON
ALTERNATOR OUT
POWER IN
REMOTE SENSE
FIELD
TO LEFT VENTILATION BLOWER
TO RIGHT VENTILATION BLOWER
TO AUXILIARY FUEL PUMP
TO ENGINE FUEL CONTROL HEATER
TO RIGHT TURN AND BANK INDICATOR
AVIONICS
BUS 1
ADF 1
GYRO SLAVE
NUMBER 1
AVIONICS
POWER
SWITCH/
BREAKER
AUD/MKR
A/P ACTR
A/P CONT
AVIONICS
BUS TIE
SWITCH/
BREAKER
COM 2
NAV 2
AVIONICS
BUS 2
TO STALL WARNING SYSTEM
DME
TO ITT INDICATOR
TO AIRSPEED WARNING SYSTEM
TO PROPELLER OVERSPEED
VALVE ASSEMBLY
TO WING AND STABILIZER
DE-ICE SYSTEM
TO RIGHT PITOT HEATER
GLSP 2
ADF 2
TO AIR CONDITIONER
TO RIGHT FUEL QUANTITY INDICATOR
GLSP 1
HSI 1
TO ANNUNCIATOR PANEL
TO FUEL FLOW INDICATOR
XPDR 1
RNAV
RADIO ALT
NUMBER 2
AVIONICS
POWER
SWITCH/
BREAKER
TO PROPELLER ANTI-ICING SYSTEM
AVN FAN
AUDIO AMP
AVIONICS
BUS 2
HF XMT
TO PROPELLER ANTI-ICING CONTROL
TO RIGHT LANDING LIGHT
HF RCVR
TO TAXI LIGHTS
RADAR CONT
TO RADIO AND FLOOD LIGHTS
TO NAVIGATION RECEIVER 1
TO TRANSPONDER 1
TO GLIDE SLOPE RECEIVER 1
TO ADF RECEIVER 1
TO HORIZONTAL SITUATION INDICATOR 1
TO GYRO SLAVING
TO AUDIO CONTROL CONSOLE AND
MARKER BEACON RECEIVER
TO AUTO PILOT ACTUATOR
TO AUTOPILOT CONTROL
TO COMMUNICATION RECEIVER 2
TO NAVIGATION RECEIVER 2
SPARE
TO GLIDE SLOPE RECEIVER 2
TO ADF RECEIVER 2
TO DME
TO AREA NAVIGATION SYSTEM
TO RADIO ALTIMETER
TO AVIONICS FAN
TO AUDIO AMPLIFIER
SPARE
SPARE
SPARE
HF XMT
TO NAVIGATION LIGHTS
TO COMMUNICATIONS RECEIVER 1
RADAR R-T
TO HIGH FREQUENCY TRANSMITTER
TO HIGH FREQUENCY TRANSMITTER
TO HIGH FREQUENCY RECEIVER
TO WEATHER RADAR
TO WEATHER RADAR
SPARE
SPARE
TO READING LIGHTS
TO RH ATTITUDE INDICATOR
TO RH DIRECTIONAL INDICATOR
TO ENCODING ALTIMETER
TO ELECTRIC ELEVATOR TRIM
Figure 24-5. Non-G1000 Overview—Typical Electrical System (with Optional Standby Electrical System)
24-6
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
24
Revision 0
FOR TRAINING PURPOSES ONLY
24-7
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
3
2
1
6
4
5
24
7
9
8
10
1. Ground Power Monitor
2. External Start Contactor
3. External Power Contactor
4. Internal Start Contactor
5. Battery Contactor
6. Generator Contactor
7. Battery Shunt
8. Generator Shunt
9. Bus Feeder Current Limiters
10. Field Current Limiter
Figure 24-6. Power Distribution Box
24-8
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
24
Revision 0
FOR TRAINING PURPOSES ONLY
24-9
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
OPEN ELECTRICAL
GROUND
STARTER CUTOFF
OVERVOLTAGE
PROTECTION >40VDC
DIFFERENTIAL
VOLTAGE SENSING
FIELD
WEAKENING
CONTROL
OVERVOLTAGE
PROTECTION
GENERATOR CONTROL UNIT
H Z V
PB 86
PC 20
PC 21
PC 17
PC 19
PC 18
PA 12
PA 11
PA 8
DA 20
DA 22
DA 21
DA 23
ANNUN
PB 36
PB 98
MM
ANNUN
STARTER
ENERGIZED
GEN OFF
A*
PB 20
PB 21
A C B
WHT
BLK
PB 5
PB 25
PB 4
PB 6
40
YEL
PB 28
BATT
SHUNT
40
3
3
PB 65
PB 47
6
6
PB 67
30
30
PB 49
12 12
PB 69
30
PB 46
2
PB 66
30
PB 48
5
5
PB 68
PB 50
11 11
PB 70
PB 73
1
1
PB 59
PB 74
10 10
PB 60
PB 87
7
7
POWER BOX
8
12
11
5
5
2
IGN. EXC.
V
GEN. FLD.
10
9
7
6
A
B
PB 42
PB 41
40
11
KA 13
KA 6
15
PB 30
4
3
1
KA 11
KA 8
KA 4
KA 14
PB 45
2
KA 12
PB 42
PB 41
40
KA 15
PB 81
40
GEN. SW.
PB 13
PB 12
PB 11
PB 10
GRN
40
40
POL SENSE
LOW V SENSE
b
6
PB 20
30
AVN 1
PWR
30
AVN 2
PWR
20
GEN
CONT
20
5
BUS 2 PWR
GND PWR
MONITOR
WJ 1
12
4
E
BUS 1 PWR
CONDITIONS:
BATTERY IN AIRPLANE AND CONNECTED
BATTERY BUS BELOW 24.5 VDC
PWR DISTRIBUTION BUS
GROUND
WHT
ORN
VOLTAGE
LOW
A+
40
a b j
8
PA 9
PA 10
GEN
SHUNT
h k
9
10
ANTI
CYCLE
40
T S U M
2
BLU/WHT
EXT PWR
–
POSITIVE POWER OR SWITCHABLE POWER
3
7
S
BLU/WHT
WHT
WHT
PC 14
PC 4
ANNUN
1
EXT. PWR.
1
PB 82
PB 83
PB 84
PB 85
5
BATT
CONT
A W S
F D K L
PB 23
PB 16
PC 2
PC 1
PB 33
RED
BLK BLU
1 4
3 2
PB 29
EXT START
BATTERY POWER
3 2
PA 1
PA 2
BATT BUS
D
PB 80
PB 16
PB 15
PB 8
PB 34
LEGEND
BATT.
4
5
+
PA 5
BAT. SW.
PC 7
PC 8
PC 3
PC 6
PC 5
PB 1
PB 40
PC 10
PC 9
PC 12
V B A G
VOLTAM SW
START/GEN
+
E N P A B
DA 30
B+
B+
INT START
1 2 3 4 5 6 7 8 9
PB 35
A
B
H J
PA 4
24
PB 26
PB 9
PB 31
PB 32
VOLTAMM.
W V T U
PA 7
PC 3
PA 6
PB 2
PB 3
PC 11
LINE CONT
SENSE
PB 27
5
GEN
E
E
F N H A C J L K P R S
M E
T R J U
ANNUN
IGN ON
DA 24
DA 25
E D
PB 13
PB 93
A E
PB 17
PB 92
B D
START POWER
START INPUT
POWER INPUT
E
POINT OF REGULATION
LINE CONTACT SENSE
M
GEN. RESET
GEN. ON
GEN. TRIP
GROUND
X Y
ANTI-CYCLE SIGNAL
SPEED SENSOR
SPEED SENSOR
B F Q C G
FROM A
START OUT
GEN. ON LINE
GEN. INTERPOLE
SNUBBER DIODE GND
GROUND
GROUND
GEN. EXCITATION
REVERSE CURRENT
PROTECTION
START RELAY
CONTROL
LINE CONTACTOR
CONTROL
VOLTAGE
REGULATOR
IGN
5
KA 5
KA 2
KA 1
KA 3
TRUTHTABLE FOR
SWITCHES
KA 7
5
START
CONTROL
KA 9
STR. SW.
IGN. SW
KA 10
PB 61
PB 57
AVN BUS 1
20
PB 58
PB 62
AVN BUS TIE
CIRCUIT
BREAKER
PANEL
AVN BUS 2
PB 15
GENERATOR
SWITCH POSITION
RESET
(ON)
TRIP
1–2
4–5
7–8
10–11
2–3
4–5
7–8
11–12
2–3
5–6
8–9
11–12
OFF
START
BUS
EXT. POWER
SWITCH POSITION
PB 42
Figure 24-7. Electrical Circuit (Sheet 1 of 7)
24-10
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
24
Revision 0
FOR TRAINING PURPOSES ONLY
24-11
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
OPEN ELECTRICAL
GROUND
STARTER CUTOFF
OVERVOLTAGE
PROTECTION >40VDC
DIFFERENTIAL
VOLTAGE SENSING
FIELD
WEAKENING
CONTROL
OVERVOLTAGE
PROTECTION
GENERATOR CONTROL UNIT
H Z V
PB 86
PC 20
PC 21
PC 17
PC 19
PC 18
PA 12
PA 11
PA 8
DA 20
DA 22
DA 21
DA 23
ANNUN
PB 36
PB 98
MM
ANNUN
STARTER
ENERGIZED
GEN OFF
A*
PB 20
PB 21
A C B
WHT
BLK
PB 5
PB 25
PB 4
PB 6
GRN
YEL
11
5
5
2
40
PB 28
BATT
SHUNT
40
3
3
PB 65
PB 47
6
6
PB 67
30
30
PB 49
12 12
PB 69
30
PB 46
2
PB 66
30
PB 48
5
5
PB 68
PB 50
11 11
PB 70
PB 73
1
1
PB 59
PB 74
10 10
PB 60
PB 87
7
7
POWER BOX
IGN. EXC.
V
GEN. FLD.
10
9
7
6
A
B
15
PB 30
4
3
1
KA 11
KA 8
KA 4
KA 14
PB 45
2
8
12
KA 13
KA 6
PB 42
PB 41
b
40
40
POL SENSE
LOW V SENSE
WJ 1
40
KA 12
PB 42
PB 41
CONDITIONS:
BATTERY SWITCH—ON
BATTERY BUS—BELOW 24.5 VDC
40
KA 15
PB 81
SECONDARY POWER
GND PWR
MONITOR
VOLTAGE
LOW
A+
6
PB 20
30
AVN 1
PWR
30
AVN 2
PWR
20
GEN
CONT
20
5
BUS 2 PWR
ORN
ANNUN
12
4
E
BUS 1 PWR
GROUND
PWR DISTRIBUTION BUS
POSITIVE POWER OR SWITCHABLE POWER
WHT
40
GEN. SW.
11
8
PA 9
PA 10
–
a b j
2
BLU/WHT
40
h k
9
10
ANTI
CYCLE
40
GEN
SHUNT
BATTERY POWER
S
BLU/WHT
WHT
WHT
EXT PWR
LEGEND
3
7
T S U M
PB 13
PB 12
PB 11
PB 10
5
PC 14
PC 4
RED
BLK BLU
1
EXT. PWR.
1
PB 82
PB 83
PB 84
PB 85
PB 33
BATT
CONT
PB 29
EXT START
+
PA 1
PA 2
BATT BUS
5
A W S
F D K L
PB 23
PB 16
PC 2
PC 1
PB 8
PB 34
D
PB 80
PB 16
PB 15
PB 1
PB 40
PC 10
PC 9
PC 12
1 4
3 2
PC 7
PC 8
PC 3
PC 6
PC 5
4
3 2
PA 5
BAT. SW.
VOLTAM SW
START/GEN
+
V B A G
BATT.
E N P A B
DA 30
B+
B+
INT START
1 2 3 4 5 6 7 8 9
PB 35
A
B
H J
PA 4
24
W V T U
PB 26
PB 9
PB 31
PB 32
VOLTAMM.
PA 7
PC 3
PA 6
PB 2
PB 3
PC 11
LINE CONT
SENSE
PB 27
5
GEN
E
E
F N H A C J L K P R S
M E
T R J U
ANNUN
IGN ON
DA 24
DA 25
E D
PB 13
PB 93
A E
PB 17
PB 92
B D
START POWER
START INPUT
POWER INPUT
E
POINT OF REGULATION
LINE CONTACT SENSE
M
GEN. RESET
GEN. ON
GEN. TRIP
GROUND
X Y
ANTI-CYCLE SIGNAL
SPEED SENSOR
SPEED SENSOR
B F Q C G
FROM A
START OUT
GEN. ON LINE
GEN. INTERPOLE
SNUBBER DIODE GND
GROUND
GROUND
GEN. EXCITATION
REVERSE CURRENT
PROTECTION
START RELAY
CONTROL
LINE CONTACTOR
CONTROL
VOLTAGE
REGULATOR
IGN
5
KA 5
KA 2
KA 1
KA 3
TRUTHTABLE FOR
SWITCHES
KA 7
5
START
CONTROL
KA 9
STR. SW.
IGN. SW
KA 10
PB 61
PB 57
AVN BUS 1
20
PB 58
PB 62
AVN BUS TIE
CIRCUIT
BREAKER
PANEL
AVN BUS 2
PB 15
GENERATOR
SWITCH POSITION
RESET
(ON)
TRIP
1–2
4–5
7–8
10–11
2–3
4–5
7–8
11–12
2–3
5–6
8–9
11–12
OFF
START
BUS
EXT. POWER
SWITCH POSITION
PB 42
Figure 24-7. Electrical Circuit (Sheet 2 of 7)
24-12
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
24
Revision 0
FOR TRAINING PURPOSES ONLY
24-13
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
OPEN ELECTRICAL
GROUND
STARTER CUTOFF
14
DIFFERENTIAL
VOLTAGE SENSING
FIELD
WEAKENING
CONTROL
PB 86
PC 20
PC 21
PC 17
PC 19
PC 18
PA 12
PA 11
PA 8
DA 20
DA 22
DA 21
DA 23
ANNUN
PB 36
ANNUN
STARTER
ENERGIZED
GEN OFF
A*
PB 20
PB 21
A C B
WHT
BLK
PB 5
PB 25
PB 4
PB 6
RED
BLK BLU
GROUND
SECONDARY POWER
SIGNAL OR SENSE
CONDITIONS:
BATTERY SWITCH—ON
BATTERY BUS—BELOW 24.5 VDC
STARTER SWITCH—START
ENGINE—BELOW 41 TO 46% Ng
WHT
ORN
GND PWR
MONITOR
ANNUN
VOLTAGE
LOW
A+
b
GRN
40
40
40
40
40
40
POL SENSE
LOW V SENSE
WJ 1
YEL
6
5
5
2
PB 28
POWER BOX
BATT
SHUNT
40
3
3
PB 65
PB 47
6
6
PB 67
PB 49
12 12
PB 69
30
PB 46
2
PB 66
30
PB 48
5
5
PB 68
PB 50
11 11
PB 70
PB 73
1
1
PB 59
PB 74
10 10
PB 60
PB 87
7
7
11
4
4
3
1
KA 11
KA 8
KA 4
KA 14
PB 45
2
15
PB 30
7
6
11
IGN. EXC.
V
GEN. FLD.
10
9
8
A
B
3
PB 20
30
30
30
AVN 1
PWR
30
AVN 2
PWR
20
GEN
CONT
20
BUS 2 PWR
POSITIVE POWER OR SWITCHABLE POWER
PWR DISTRIBUTION BUS
BATTERY POWER
40
12
KA 13
KA 6
PB 42
PB 41
GEN
SHUNT
–
KA 12
PB 42
PB 41
+
12
4
E
BUS 1 PWR
LEGEND
40
GEN. SW.
11
8
BLU/WHT
EXT PWR
PC 10
PC 9
PC 12
a b j
2
PA 9
PA 10
PC 14
PC 4
h k
9
10
ANTI
CYCLE
BLU/WHT
WHT
WHT
KA 15
PB 81
5
T S U M
PB 13
PB 12
PB 11
PB 10
PB 33
3
7
2
S
EXT. PWR.
1
PB 82
PB 83
PB 84
PB 85
EXT START
BATT
CONT
PB 29
5
+
PA 1
PA 2
BATT BUS
A W S
F D K L
PB 23
PB 16
PC 2
PC 1
PB 8
PB 34
9
START/GEN
1
VOLTAM SW
INT START
PB 1
PB 40
1 4
3 2
DA 30
B+
B+
3 2
8
PA 5
BAT. SW.
PC 7
PC 8
PC 3
PC 6
PC 5
10
4
E N P A B
PA 4
A
B
10
BATT.
PB 35
INTERPOLE
WINDINGS
SENSES
REV CURR.
H J
V B A G
PA 7
PC 3
PA 6
24
PB 32
VOLTAMM.
1 2 3 4 5 6 7 8 9
PB 9
PB 31
13 PIN D
ANNUN
IGN ON
W V T U
PB 26
PC 11
PB 2
PB 3
LINE CONT
SENSE
PB 27
5
GEN
E
E
D
PB 80
PB 16
PB 15
16
F N H A C J L K P R S
M E
T R J U
5 PIN W
START SIG IN W
START SIG OUT Z
DA 24
DA 25
B D
E D
PB 13
PB 93
A E
PB 17
PB 92
7 PIN Z
H Z V
START POWER
START INPUT
POWER INPUT
GENERATOR CONTROL UNIT
POINT OF REGULATION
E
GEN. RESET
GEN. ON
GEN. TRIP
LINE CONTACT SENSE
M
ANTI-CYCLE SIGNAL
GROUND
X Y
MM
6
FROM A
START OUT
GEN. ON LINE
SPEED SENSOR
SPEED SENSOR
B F Q C G
PB 98
START RELAY
CONTROL
LINE CONTACTOR
CONTROL
VOLTAGE
REGULATOR
OVERVOLTAGE
PROTECTION
GEN. INTERPOLE
SNUBBER DIODE GND
GROUND
GROUND
GEN. EXCITATION
15 PIN B
REVERSE CURRENT
PROTECTION
OVERVOLTAGE
PROTECTION >40VDC
IGN
5
KA 3
1
KA 7
5
START
CONTROL
KA 9
STR. SW.
IGN. SW
KA 10
PB 61
PB 57
AVN BUS 1
20
PB 58
PB 62
AVN BUS TIE
CIRCUIT
BREAKER
PANEL
AVN BUS 2
PB 15
5
12
KA 5
KA 2
KA 1
TRUTHTABLE FOR
SWITCHES
GENERATOR
SWITCH POSITION
RESET
(ON)
TRIP
1–2
4–5
7–8
10–11
2–3
4–5
7–8
11–12
2–3
5–6
8–9
11–12
OFF
START
BUS
EXT. POWER
SWITCH POSITION
PB 42
Figure 24-7. Electrical Circuit (Sheet 3 of 7)
24-14
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
24
Revision 0
FOR TRAINING PURPOSES ONLY
24-15
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
OPEN ELECTRICAL
GROUND
STARTER CUTOFF
OVERVOLTAGE
PROTECTION >40VDC
DIFFERENTIAL
VOLTAGE SENSING
FIELD
WEAKENING
CONTROL
OVERVOLTAGE
PROTECTION
GENERATOR CONTROL UNIT
H Z V
PB 86
PC 20
PC 21
PC 17
PC 19
PC 18
PA 12
PA 11
PA 8
DA 20
DA 22
DA 21
DA 23
ANNUN
PB 36
PB 98
MM
ANNUN
STARTER
ENERGIZED
GEN OFF
A*
PB 20
PB 21
A C B
WHT
BLK
PB 5
PB 25
PB 4
PB 6
CONDITIONS:
BATTERY SWITCH—ON
BATTERY BUS—BELOW 24.5 VDC
STARTER SWITCH—START
ENGINE—ABOVE 41 TO 46% Ng
GND PWR
MONITOR
ANNUN
VOLTAGE
LOW
A+
b
GRN
40
40
40
POL SENSE
LOW V SENSE
WJ 1
40
YEL
11
5
5
2
PB 28
BATT
SHUNT
40
3
3
PB 65
PB 47
6
6
PB 67
30
30
PB 49
12 12
PB 69
30
PB 46
2
PB 66
30
PB 48
5
5
PB 68
PB 50
11 11
PB 70
PB 73
1
1
PB 59
PB 74
10 10
PB 60
PB 87
7
7
POWER BOX
IGN. EXC.
V
GEN. FLD.
10
9
7
6
A
B
15
PB 30
4
3
1
KA 11
KA 8
KA 4
KA 14
PB 45
2
8
12
KA 13
KA 6
PB 42
PB 41
SIGNAL OR SENSE
ORN
40
KA 12
PB 42
PB 41
SECONDARY POWER
WHT
40
KA 15
PB 81
GROUND
6
PB 20
30
AVN 1
PWR
30
AVN 2
PWR
20
GEN
CONT
20
5
BUS 2 PWR
RED
BLK BLU
12
4
E
BUS 1 PWR
–
40
GEN. SW.
11
8
PA 9
PA 10
GEN
SHUNT
a b j
9
10
ANTI
CYCLE
40
h k
2
BLU/WHT
EXT PWR
POSITIVE POWER OR SWITCHABLE POWER
S
BLU/WHT
WHT
WHT
PWR DISTRIBUTION BUS
BATTERY POWER
3
7
T S U M
PB 13
PB 12
PB 11
PB 10
5
PC 14
PC 4
+
1
EXT. PWR.
1
PB 82
PB 83
PB 84
PB 85
PB 33
BATT
CONT
PB 29
EXT START
LEGEND
PA 1
PA 2
BATT BUS
5
A W S
F D K L
PB 23
PB 16
PC 2
PC 1
PB 8
PB 34
D
PB 80
PB 16
PB 15
PB 1
PB 40
PC 10
PC 9
PC 12
1 4
3 2
PC 7
PC 8
PC 3
PC 6
PC 5
4
3 2
PA 5
BAT. SW.
VOLTAM SW
START/GEN
+
V B A G
BATT.
E N P A B
DA 30
B+
B+
INT START
1 2 3 4 5 6 7 8 9
PB 35
A
B
H J
PA 4
24
W V T U
PB 26
PB 9
PB 31
PB 32
VOLTAMM.
PA 7
PC 3
PA 6
PB 2
PB 3
PC 11
LINE CONT
SENSE
PB 27
5
GEN
E
E
F N H A C J L K P R S
M E
T R J U
ANNUN
IGN ON
DA 24
DA 25
E D
PB 13
PB 93
A E
PB 17
PB 92
B D
START POWER
START INPUT
POWER INPUT
E
POINT OF REGULATION
LINE CONTACT SENSE
M
GEN. RESET
GEN. ON
GEN. TRIP
GROUND
X Y
ANTI-CYCLE SIGNAL
SPEED SENSOR
SPEED SENSOR
B F Q C G
FROM A
START OUT
GEN. ON LINE
GEN. INTERPOLE
SNUBBER DIODE GND
GROUND
GROUND
GEN. EXCITATION
REVERSE CURRENT
PROTECTION
START RELAY
CONTROL
LINE CONTACTOR
CONTROL
VOLTAGE
REGULATOR
IGN
5
KA 5
KA 2
KA 1
KA 3
TRUTHTABLE FOR
SWITCHES
KA 7
5
START
CONTROL
KA 9
STR. SW.
IGN. SW
KA 10
PB 61
PB 57
AVN BUS 1
20
PB 58
PB 62
AVN BUS TIE
CIRCUIT
BREAKER
PANEL
AVN BUS 2
PB 15
GENERATOR
SWITCH POSITION
RESET
(ON)
TRIP
1–2
4–5
7–8
10–11
2–3
4–5
7–8
11–12
2–3
5–6
8–9
11–12
OFF
START
BUS
EXT. POWER
SWITCH POSITION
PB 42
Figure 24-7. Electrical Circuit (Sheet 4 of 7)
24-16
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
24
Revision 0
FOR TRAINING PURPOSES ONLY
24-17
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
OPEN ELECTRICAL
GROUND
STARTER CUTOFF
DIFFERENTIAL
VOLTAGE SENSING
FIELD
WEAKENING
CONTROL
H Z V
PB 86
PC 20
PC 21
PC 17
PC 19
PC 18
PA 12
PA 11
PA 8
DA 20
DA 22
DA 21
DA 23
ANNUN
PB 36
PB 98
ANNUN
STARTER
ENERGIZED
GEN OFF
A*
PB 20
PB 21
A C B
WHT
BLK
PB 5
PB 25
PB 4
PB 6
YEL
PB 28
BATT
SHUNT
40
6
3
3
PB 65
PB 47
6
6
PB 67
PB 49
12 12
PB 69
30
PB 46
2
2
PB 66
30
PB 48
5
5
PB 68
30
PB 50
11 11
PB 70
AVN 1
PWR
30
AVN 2
PWR
20
GEN
CONT
20
PB 73
1
1
PB 59
PB 74
10 10
PB 60
PB 87
7
7
GEN. SW.
2
11
8
8
12
11
IGN. EXC.
V
GEN. FLD.
10
9
7
6
A
B
15
PB 30
4
3
2
5
1
KA 11
KA 8
KA 4
KA 14
PB 45
POWER BOX
a b j
KA 13
KA 6
PB 42
PB 41
GRN
40
KA 12
PB 42
PB 41
b
40
40
POL SENSE
LOW V SENSE
WJ 1
40
KA 15
PB 81
VOLTAGE
LOW
A+
40
h k
PB 13
PB 12
PB 11
PB 10
GND PWR
MONITOR
40
PB 82
PB 83
PB 84
PB 85
CONDITIONS:
BATTERY SWITCH—ON
AVIONICS PWR—1 & 2 ON
BATTERY BUS—28.5 VDC
STARTER SWITCH—OFF
ENGINE RUNING—GEN ONLINE
WHT
ORN
ANNUN
12
4
E
PB 20
30
30
5
BUS 2 PWR
SIGNAL OR SENSE
PWR DISTRIBUTION BUS
POSITIVE POWER OR SWITCHABLE POWER
40
T S U M
9
10
BUS 1 PWR
GEN
SHUNT
SECONDARY POWER
3
7
2
ANTI
CYCLE
40
–
RED
BLK BLU
1
BLU/WHT
EXT PWR
GROUND
EXT. PWR.
PA 9
PA 10
BATTERY POWER
1
S
BLU/WHT
WHT
WHT
A W S
F D K L
PB 23
PB 16
PC 2
PC 1
5
BATT
CONT
PB 29
PB 33
PC 14
PC 4
PC 10
PC 9
PC 12
3 2
PA 1
PA 2
BATT BUS
D
PB 80
PB 16
PB 15
PB 8
PB 34
EXT START
+
1 4
DA 30
PB 1
PB 40
5
+
3 2
BAT. SW.
PC 7
PC 8
PC 3
PC 6
PC 5
4
PA 5
PA 4
BATT.
E N P A B
VOLTAM SW
START/GEN
LEGEND
DA 24
DA 25
B+
B+
INT START
V B A G
PB 35
A
B
H J
1 2 3 4 5 6 7 8 9
PB 9
PB 31
PB 32
VOLTAMM.
W V T U
PB 26
T R J U
ANNUN
IGN ON
PA 7
PC 3
PA 6
24
LINE CONT
SENSE
PB 27
5
GEN
E
E
F N H A C J L K P R S
M E
PC 11
PB 2
PB 3
E D
PB 13
PB 93
A E
PB 17
PB 92
B D
START POWER
START INPUT
POWER INPUT
GENERATOR CONTROL UNIT
POINT OF REGULATION
E
GEN. RESET
GEN. ON
GEN. TRIP
LINE CONTACT SENSE
M
ANTI-CYCLE SIGNAL
GROUND
X Y
FROM A
START OUT
GEN. ON LINE
SPEED SENSOR
SPEED SENSOR
B F Q C G
MM
START RELAY
CONTROL
LINE CONTACTOR
CONTROL
VOLTAGE
REGULATOR
OVERVOLTAGE
PROTECTION
GEN. INTERPOLE
SNUBBER DIODE GND
GROUND
GROUND
GEN. EXCITATION
REVERSE CURRENT
PROTECTION
OVERVOLTAGE
PROTECTION >40VDC
IGN
5
KA 5
KA 2
KA 1
KA 3
TRUTHTABLE FOR
SWITCHES
KA 7
5
START
CONTROL
KA 9
STR. SW.
IGN. SW
KA 10
PB 61
PB 57
AVN BUS 1
20
PB 58
PB 62
AVN BUS TIE
CIRCUIT
BREAKER
PANEL
AVN BUS 2
PB 15
GENERATOR
SWITCH POSITION
RESET
(ON)
TRIP
1–2
4–5
7–8
10–11
2–3
4–5
7–8
11–12
2–3
5–6
8–9
11–12
OFF
START
BUS
EXT. POWER
SWITCH POSITION
PB 42
Figure 24-7. Electrical Circuit (Sheet 5 of 7)
24-18
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
24
Revision 0
FOR TRAINING PURPOSES ONLY
24-19
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
OPEN ELECTRICAL
GROUND
STARTER CUTOFF
DIFFERENTIAL
VOLTAGE SENSING
FIELD
WEAKENING
CONTROL
H Z V
PB 86
PC 20
PC 21
PC 17
PC 19
PC 18
PA 12
PA 11
PA 8
DA 20
DA 22
DA 21
DA 23
ANNUN
PB 36
PB 98
ANNUN
STARTER
ENERGIZED
GEN OFF
A*
PB 20
PB 21
A C B
WHT
BLK
PB 5
PB 25
PB 4
PB 6
GEN
SHUNT
–
6
11
8
8
GROUND
WHT
ORN
GND PWR
MONITOR
ANNUN
VOLTAGE
LOW
A+
b
GRN
40
40
40
40
40
POL SENSE
LOW V SENSE
WJ 1
40
YEL
PB 28
BATT
SHUNT
40
PB 45
3
3
PB 65
PB 47
6
6
PB 67
PB 49
12 12
PB 69
30
PB 46
2
2
PB 66
30
PB 48
5
5
PB 68
30
PB 50
11 11
PB 70
AVN 1
PWR
30
AVN 2
PWR
20
GEN
CONT
20
PB 73
1
1
PB 59
PB 74
10 10
PB 60
PB 87
7
7
POWER BOX
12
11
IGN. EXC.
V
GEN. FLD.
10
9
7
6
A
B
15
PB 30
4
3
5
2
1
KA 11
KA 8
KA 4
KA 14
PB 20
30
30
5
BUS 2 PWR
PWR DISTRIBUTION BUS
RED
BLK BLU
40
GEN. SW.
KA 13
KA 6
PB 42
PB 41
12
4
E
BUS 1 PWR
40
a b j
2
PA 9
PA 10
EXT PWR
h k
9
10
ANTI
CYCLE
BLU/WHT
WHT
WHT
KA 12
PB 42
PB 41
S
KA 15
PB 81
3
7
T S U M
PB 13
PB 12
PB 11
PB 10
1
PB 82
PB 83
PB 84
PB 85
5
BATT
CONT
A W S
F D K L
PB 23
PB 16
PC 2
PC 1
1
EXT. PWR.
BLU/WHT
PC 10
PC 9
PC 12
POSITIVE POWER OR SWITCHABLE POWER
CONDITIONS:
BATTERY SWITCH—OFF
EXTERNAL POWER UNIT—ON
EXTERNAL POWER SWITCH—BUS
1 4
3 2
PB 29
PB 33
BATTERY POWER
SECONDARY POWER
3 2
PA 1
PA 2
BATT BUS
D
PB 80
PB 16
PB 15
PB 8
PB 34
PC 14
PC 4
EXTERNAL POWER
PC 7
PC 8
PC 3
PC 6
PC 5
PB 1
PB 40
EXT START
+
PA 5
BAT. SW.
BATT.
4
5
LEGEND
V B A G
VOLTAM SW
START/GEN
+
E N P A B
DA 30
B+
B+
INT START
1 2 3 4 5 6 7 8 9
PB 35
A
B
PB 26
PB 9
PB 31
PB 32
H J
PA 4
24
E
E
VOLTAMM.
W V T U
PA 7
PC 3
PA 6
PB 2
PB 3
PC 11
LINE CONT
SENSE
PB 27
5
GEN
F N H A C J L K P R S
M E
T R J U
ANNUN
IGN ON
DA 24
DA 25
E D
PB 13
PB 93
A E
PB 17
PB 92
B D
START POWER
START INPUT
POWER INPUT
GENERATOR CONTROL UNIT
POINT OF REGULATION
E
GEN. RESET
GEN. ON
GEN. TRIP
LINE CONTACT SENSE
M
ANTI-CYCLE SIGNAL
GROUND
X Y
FROM A
START OUT
GEN. ON LINE
SPEED SENSOR
SPEED SENSOR
B F Q C G
MM
START RELAY
CONTROL
LINE CONTACTOR
CONTROL
VOLTAGE
REGULATOR
OVERVOLTAGE
PROTECTION
GEN. INTERPOLE
SNUBBER DIODE GND
GROUND
GROUND
GEN. EXCITATION
REVERSE CURRENT
PROTECTION
OVERVOLTAGE
PROTECTION >40VDC
IGN
5
KA 5
KA 2
KA 1
KA 3
TRUTHTABLE FOR
SWITCHES
KA 7
5
START
CONTROL
KA 9
STR. SW.
IGN. SW
KA 10
PB 61
PB 57
AVN BUS 1
20
PB 58
PB 62
AVN BUS TIE
CIRCUIT
BREAKER
PANEL
AVN BUS 2
PB 15
GENERATOR
SWITCH POSITION
RESET
(ON)
TRIP
1–2
4–5
7–8
10–11
2–3
4–5
7–8
11–12
2–3
5–6
8–9
11–12
OFF
START
BUS
EXT. POWER
SWITCH POSITION
PB 42
Figure 24-7. Electrical Circuit (Sheet 6 of 7)
24-20
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
24
Revision 0
FOR TRAINING PURPOSES ONLY
24-21
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
OPEN ELECTRICAL
GROUND
STARTER CUTOFF
DIFFERENTIAL
VOLTAGE SENSING
FIELD
WEAKENING
CONTROL
OVERVOLTAGE
PROTECTION >40VDC
OVERVOLTAGE
PROTECTION
GENERATOR CONTROL UNIT
H Z V
PB 86
PC 20
PC 21
PC 17
PC 19
PC 18
PA 12
PA 11
PA 8
DA 20
DA 22
DA 21
DA 23
ANNUN
PB 36
MM
ANNUN
STARTER
ENERGIZED
GEN OFF
A*
PB 20
PB 21
A C B
WHT
BLK
PB 5
PB 25
PB 4
PB 6
ANNUN
VOLTAGE
LOW
A+
b
GRN
40
40
40
POL SENSE
LOW V SENSE
WJ 1
40
YEL
PB 28
BATT
SHUNT
40
3
3
PB 65
PB 47
6
6
PB 67
PB 49
12 12
PB 69
30
PB 46
2
PB 66
30
PB 48
5
5
PB 68
PB 50
11 11
PB 70
PB 73
1
1
PB 59
PB 74
10 10
PB 60
PB 87
7
7
8
12
11
IGN. EXC.
V
GEN. FLD.
10
9
7
6
A
B
15
PB 30
4
3
5
2
1
KA 11
KA 8
KA 4
KA 14
PB 45
2
11
KA 13
KA 6
PB 42
PB 41
GND PWR
MONITOR
40
KA 12
PB 42
PB 41
ORN
SECONDARY POWER
CONDITIONS:
BATTERY SWITCH—ON
EXTERNAL POWER UNIT—ON
BATTERY BUS—BELOW 24.5 VDC
EXTERNAL POWER SWITCH—START
STARTER SWITCH—START
ENGINE—BELOW 41 TO 46% Ng
WHT
40
KA 15
PB 81
EXTERNAL POWER
6
PB 20
POWER BOX
30
30
30
AVN 1
PWR
30
AVN 2
PWR
20
GEN
CONT
20
5
BUS 2 PWR
RED
BLK BLU
40
GEN. SW.
PB 13
PB 12
PB 11
PB 10
GROUND
12
4
E
BUS 1 PWR
POSITIVE POWER OR SWITCHABLE POWER
–
GEN
SHUNT
a b j
8
PA 9
PA 10
+
h k
9
10
ANTI
CYCLE
40
T S U M
2
BLU/WHT
EXT PWR
PWR DISTRIBUTION BUS
BATTERY POWER
3
7
S
BLU/WHT
WHT
WHT
PC 14
PC 4
EXT. PWR.
1
PB 82
PB 83
PB 84
PB 85
5
BATT
CONT
PB 29
PB 33
EXT START
PC 10
PC 9
PC 12
PA 1
PA 2
BATT BUS
A W S
F D K L
PB 23
PB 16
PC 2
PC 1
PB 8
PB 34
D
PB 80
PB 16
PB 15
PB 1
PB 40
5
+
1
VOLTAM SW
START/GEN
LEGEND
1 4
3 2
PA 5
BAT. SW.
DA 30
B+
B+
INT START
4
3 2
PB 35
A
B
V B A G
BATT.
E N P A B
PC 7
PC 8
PC 3
PC 6
PC 5
PB 9
PB 31
PB 32
H J
1 2 3 4 5 6 7 8 9
PA 7
PC 3
PA 6
24
W V T U
PB 26
PC 11
PB 2
PB 3
VOLTAMM.
PA 4
LINE CONT
SENSE
PB 27
5
GEN
E
E
F N H A C J L K P R S
M E
T R J U
ANNUN
IGN ON
DA 24
DA 25
E D
PB 13
PB 93
A E
PB 17
PB 92
B D
START POWER
START INPUT
POWER INPUT
E
POINT OF REGULATION
LINE CONTACT SENSE
M
GEN. RESET
GEN. ON
GEN. TRIP
GROUND
X Y
ANTI-CYCLE SIGNAL
SPEED SENSOR
SPEED SENSOR
B F Q C G
FROM A
START OUT
GEN. ON LINE
GEN. INTERPOLE
SNUBBER DIODE GND
GROUND
GROUND
GEN. EXCITATION
REVERSE CURRENT
PROTECTION
PB 98
START RELAY
CONTROL
LINE CONTACTOR
CONTROL
VOLTAGE
REGULATOR
IGN
5
KA 5
KA 2
KA 1
KA 3
TRUTHTABLE FOR
SWITCHES
KA 7
5
START
CONTROL
KA 9
STR. SW.
IGN. SW
KA 10
PB 61
PB 57
AVN BUS 1
20
PB 58
PB 62
AVN BUS TIE
CIRCUIT
BREAKER
PANEL
AVN BUS 2
PB 15
GENERATOR
SWITCH POSITION
RESET
(ON)
TRIP
1–2
4–5
7–8
10–11
2–3
4–5
7–8
11–12
2–3
5–6
8–9
11–12
OFF
START
BUS
EXT. POWER
SWITCH POSITION
PB 42
Figure 24-7. Electrical Circuit (Sheet 7 of 7)
24-22
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
24
Revision 0
FOR TRAINING PURPOSES ONLY
24-23
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
SHUNT
ALTERNATOR
B
G
S
F
PH5
PH4
100 Ω CARBON
RESISTOR
PH37
40 AMP CURRENT LIMITERS
F19
PH38
40
F20
PH39
40
PH3
PH2
PH33
F14
F15
2
2
2
F16
F17
2
RELAY
PH8
PH25
PH7
ALTERNATOR
CONTROL UNIT
GROUND
– REM SENSE
FIELD
AUX SENSE
LINE CONT.
+ REM SENSE
CURRENT (–)
POWER IN
ALT. OUT
ALT. ON
PH40
30
PH41
40
PH42
PH20
12 12
5 5
13 13
7 7
9 9
2 2
10 10
3 3
6 6
4 4
7 1 2
7 1 2
3
3
4
4
5
5
40
6
6
PH6
PH30
PH29
PH32
PH10
PH11
PH24
DA35
DA36
TO ANNU. PANEL
x x
PH18
PH12
C C
PH19
WF20
V V
z z
PH35
PH14
CLOCK
5
BATTERY POWER
DC1
PH26
a a
TO INDICATING
AND RECORDING
100 Ω CARBON
RESISTOR
PH3
PH2
POSITIVE POWER OR
SWITCHABLE POWER
GROUND
SIGNAL OR SENSE
F14
F15
2
2
2
F16
F17
2
RELAY
PH8
ALTERNATOR
CONTROL UNIT
GROUND
– REM SENSE
FIELD
AUX SENSE
LINE CONT.
+ REM SENSE
CURRENT (–)
POWER IN
ALT. OUT
ALT. ON
OFF
ON
PH13
STBY PWR SWITCH
30
PH41
PH25
5
7 1 2
7 1 2
3
3
4
4
5
5
6
6
PH6
PH30
PH29
PH32
PH10
PH11
PH24
40
STBY
PWR
40
STBY
PWR
PH42
PH20
12 12
5 5
13 13
7 7
9 9
2 2
10 10
3 3
6 6
4 4
DA35
DA36
TO ANNU. PANEL
PH28
x x
PH18
PH12
C C
PH19
WF20
V V
z z
PH35
PH14
PH13
22
LEGEND
ANNUNCIATOR PANEL
CLOCK
5
Figure 24-8. Standby Alternator Circuit (Sheet 1 of 4)
BATTERY POWER
PH36
DC1
PH26
a a
TO INDICATING
AND RECORDING
15
COM
1
OFF
ON
STBY PWR SWITCH
18 GA JUMPER
TO VOLT AMMETER
23
CONDITIONS:
BATTERY INSTALLED
AND ON STBY PWR
SWITCH OFF / < 7VDC
PIN 7 GENERATOR ON
LINE / NORMAL ENGINE
RUNNING
PH40
16 GA JUMPER
DA33
PH31
PH9
DA34
18 GA JUMPER
LEGEND
PH36
PH5
PH4
PH7
STBY
PWR
PH28
TO VOLT AMMETER
ANNUNCIATOR PANEL
S
F
STBY
PWR
22
23
15
B
G
COM
1
PH33
5
F18
PH37
40 AMP CURRENT LIMITERS
F19
PH38
40
F20
PH39
40
PH1
16 GA JUMPER
DA33
PH31
PH9
DA34
SHUNT
ALTERNATOR
F18
PH1
POSITIVE POWER OR
SWITCHABLE POWER
GROUND
SIGNAL OR SENSE
CONDITIONS:
BATTERY INSTALLED
AND ON STBY PWR
SWITCH ON / < 7VDC
PIN 7 GENERATOR ON
LINE / NORMAL ENGINE
RUNNING
Figure 24-8. Standby Alternator Circuit (Sheet 2 of 4)
NOTES
24
24-24
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
SHUNT
ALTERNATOR
B
G
S
F
PH5
PH4
100 Ω CARBON
RESISTOR
PH3
PH2
PH33
F14
F15
PH37
40 AMP CURRENT LIMITERS
F19
PH38
40
F20
PH39
40
2
2
2
F16
F17
2
RELAY
PH8
PH25
PH7
ALTERNATOR
CONTROL UNIT
GROUND
– REM SENSE
FIELD
AUX SENSE
LINE CONT.
+ REM SENSE
CURRENT (–)
POWER IN
ALT. OUT
ALT. ON
PH40
30
PH41
40
PH42
PH20
12 12
5 5
13 13
7 7
9 9
2 2
10 10
3 3
6 6
4 4
7 1 2
7 1 2
3
3
4
4
5
5
40
6
6
PH6
PH30
PH29
PH32
PH10
PH11
PH24
DA35
DA36
B
G
COM
1
TO ANNU. PANEL
x x
PH18
PH12
C C
PH19
WF20
V V
z z
PH35
PH14
PH5
PH4
100 Ω CARBON
RESISTOR
PH3
PH2
5
DC1
PH26
a a
TO INDICATING
AND RECORDING
2
2
F16
F17
2
PH8
ALTERNATOR
CONTROL UNIT
GROUND
– REM SENSE
FIELD
AUX SENSE
LINE CONT.
+ REM SENSE
CURRENT (–)
POWER IN
ALT. OUT
ALT. ON
OFF
ON
PH13
PH40
7 1 2
7 1 2
3
3
4
4
PH41
PH25
5
5
DA35
DA36
5
40
STBY
PWR
40
STBY
PWR
PH42
6
6
TO ANNU. PANEL
PH28
x x
PH18
PH12
C C
PH19
WF20
V V
z z
PH35
PH14
PH13
22
COM
1
OFF
ON
STBY PWR SWITCH
18 GA JUMPER
TO VOLT AMMETER
23
15
16 GA JUMPER
PH6
PH30
PH29
PH32
PH10
PH11
PH24
30
PH20
12 12
5 5
13 13
7 7
9 9
2 2
10 10
3 3
6 6
4 4
STBY PWR SWITCH
18 GA JUMPER
LEGEND
PH36
2
DA33
PH31
PH9
DA34
LEGEND
ANNUNCIATOR PANEL
BATTERY POWER
BATTERY POWER
CLOCK
F14
F15
RELAY
PH7
STBY
PWR
PH28
TO VOLT AMMETER
ANNUNCIATOR PANEL
S
F
STBY
PWR
22
23
15
PH33
5
F18
PH37
40 AMP CURRENT LIMITERS
F19
PH38
40
F20
PH39
40
PH1
16 GA JUMPER
DA33
PH31
PH9
DA34
SHUNT
ALTERNATOR
F18
PH1
POSITIVE POWER OR SWITCHABLE POWER
CLOCK
5
GROUND
PH36
DC1
SIGNAL OR SENSE
CONTROLLING POWER
PH26
a a
TO INDICATING
AND RECORDING
GROUND
SIGNAL OR SENSE
CONTROLLING POWER
CONDITIONS:
BATTERY INSTALLED AND OFF
STBY PWR SWITCH ON / < 7VDC PIN 7
GENERATOR OFF LINE / FAILED
ENGINE NOT RUNNING
ALTERNATOR POWER
CONDITIONS:
BATTERY INSTALLED AND ON
STBY PWR SWITCH ON / > 10 AMPS
GENERATOR OFF LINE / FAILED
ENGINE RUNNING
Figure 24-8. Standby Alternator Circuit (Sheet 3 of 4)
24
Figure 24-8. Standby Alternator Circuit (Sheet 4 of 4)
NOTES
Revision 0
FOR TRAINING PURPOSES ONLY
24-25
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
LEGEND
LEGEND
BATTERY POWER
BATTERY POWER
SECONDARY POWER
SECONDARY POWER
DA46
ALTERNATOR POWER
FIRST
DECK
NO. 1 GENERATOR
CONDITIONS:
GEN POSITION SELECTED
GENERATOR ON LINE
VOLT
4
JUMPER
SECOND
DECK
4
GEN
1
1
DA41
2
BATT ALT
3
+
FIRST
DECK
NO. 1 GENERATOR
AMMETER
3
DA46
ALTERNATOR POWER
CONDITIONS:
ALT POSITION SELECTED
GENERATOR ON LINE
–
2
VOLT
4
JUMPER
SECOND
DECK
AMMETER
1
3
DA38
1
1
DA42
DA39
2
2
DA40
3
3
4
4
DA44
DA43
5
5
6
6
+
DA40
DA44
DA43
DA45
7
7
8
8
1
1
9
9
2
2
3
3
4
4
5
5
6
6
7
7
8
8
TO GENERATOR
CONTACTOR
WHT
T T
DA21
DA23
DA25
DA30
DA22
D
WHT
PH29
DA35
DA36
PH32
2
3
4
5
2
3
4
5
PH9
DA33
DA34
PH31
WHT
T T
DA21
BLU/WHT U U
DA23
DA30
TO
RELAY
DA22
LOAD
BUS
ALTERNATOR
SHUNT
D
TO
LIMITERS
V V
BLU/WHT W W
GEN
SHUNT
TO
RELAY
LOAD
BUS
9
9
DA24
DA24
BLU/WHT U U
–
2
DA45
DA25
BATT
SHUNT
3
DA42
DA39
DA38
TO GENERATOR
CONTACTOR
GEN
SHUNT
1
DA41
2
BATT ALT
DA37
DA37
4
GEN
BATT
SHUNT
DA20
WHT
PH29
DA35
DA36
PH32
2
3
4
5
2
3
4
5
PH9
DA33
DA34
PH31
TO
LIMITERS
V V
BLU/WHT W W
ALTERNATOR
SHUNT
DA20
TO BATTERY
CONTACTOR
TO BATTERY
CONTACTOR
Figure 24-9. Volt—Ammeter (Sheet 1 of 4)
Figure 24-9. Volt—Ammeter (Sheet 2 of 4)
24
NOTES
24-26
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
LEGEND
LEGEND
BATTERY POWER
BATTERY POWER
GROUND
SECONDARY POWER
DA46
ALTERNATOR POWER
FIRST
DECK
NO. 1 GENERATOR
CONDITIONS:
BATT POSITION SELECTED
GENERATOR ON LINE
VOLT
4
JUMPER
SECONDARY POWER
SECOND
DECK
AMMETER
3
1
DA41
2
BATT ALT
DA37
4
GEN
1
DA40
CONDITIONS:
GEN POSITION SELECTED
GENERATOR ON LINE
DA44
DA43
FIRST
DECK
NO. 1 GENERATOR
–
2
DA42
DA39
DA38
3
+
DA46
ALTERNATOR POWER
VOLT
4
JUMPER
SECOND
DECK
AMMETER
1
3
DA39
DA37
DA38
1
1
2
2
3
3
4
4
5
5
6
6
7
7
8
8
TO GENERATOR
CONTACTOR
9
9
1
1
WHT
T T
BLU/WHT U U
4
4
DA22
D
WHT
5
5
6
6
DA45
7
7
8
8
9
9
DA24
PH29
DA35
DA36
PH32
2
3
4
5
2
3
4
5
PH9
DA33
DA34
PH31
GEN
SHUNT
ALTERNATOR
SHUNT
WHT
T T
DA21
BLU/WHT U U
DA23
DA30
TO
RELAY
DA22
LOAD
BUS
D
TO
LIMITERS
V V
BLU/WHT W W
DA43
DA25
TO
RELAY
LOAD
BUS
BATT
SHUNT
DA44
DA42
DA40
3
3
–
2
DA30
DA21
DA23
3
+
TO GENERATOR
CONTACTOR
DA24
DA25
GEN
SHUNT
2
2
1
DA41
2
BATT ALT
DA45
4
GEN
DA20
BATT
SHUNT
TO BATTERY
CONTACTOR
WHT
PH29
DA35
DA36
PH32
2
3
4
5
2
3
4
5
PH9
DA33
DA34
PH31
TO
LIMITERS
V V
BLU/WHT W W
ALTERNATOR
SHUNT
DA20
TO BATTERY
CONTACTOR
Figure 24-9. Volt—Ammeter (Sheet 3 of 4)
Figure 24-9. Volt—Ammeter (Sheet 4 of 4)
24
NOTES
Revision 0
FOR TRAINING PURPOSES ONLY
24-27
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
24
24-28
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
CHAPTER 25
EQUIPMENT & FURNISHINGS
INTRODUCTION
25
This chapter describes the equipment and furnishings of the flight and passenger compartments as well as the cargo area. In addition,
the section on the emergency locator transmitter discusses five different versions available throughout the Cessna 208 fleet.
FLIGHT COMPARTMENT - GENERAL
The flight compartment equipment includes the pilot seat, optional
copilot seat, seat belts, shoulder harnesses, and optional right side
controls. Two beverage cup holders are underneath the forward edge
of the instrument panel.
On the 208 and 208B Passenger aircraft, the pilot and copilot seats
have dual strap shoulder harness, lap belt, and inertia reel as one assembly. Shoulder harness and lap belts are bolted to the lower seat
frame. The inertia reel is mounted at the bottom of the seat back frame.
Sunvisors are standard equipment for the pilot and optional for the
copilot. They are fully adjustable.
On the 208B, the pilot and copilot seats have a five-point restraint
system that consists of seat belts, crotch strap, and an inertia reel with
double strap shoulderharness.
Pilot and Copilot Seats
The pilot seat and optional copilot seat are adjustable forward or aft and
up or down. The angle of the seat also can be changed depending on the
aircraft serial number. There are three variants of the seat belt layouts.
Revision 0
FOR TRAINING PURPOSES ONLY
25-1
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
SCREW
AIRPLANES 20800001
THRU 20800110
RIVET
SPACER
STOP BOLT
SEAT
PANEL
PILOT OR
COPILOT
CREW SEAT
SCREW
RIVET
STOP BOLT
SPACER
SPACER
NUT
NUT
DETAIL A
SPACER
A
SEAT
PANEL
ARMREST
SEAT
PANEL
25
PILOT OR
COPILOT
CREW SEAT
PILOT OR
COPILOT
CREW SEAT
FIVE-POINT
RESTRAINT
SYSTEM
FIVE-POINT
RESTRAINT
SYSTEM
CROTCH
STRAP
CROTCH
STRAP
AIRPLANES 2080011 THRU 20800237
AIRPLANES 208B0001 THRU 208B0381
AIRPLANES 20800238 AND SUBSEQUENT
AIRPLANES 208B0382 AND SUBSEQUENT
Figure 25-1. Pilot and Copilot Seats
25-2
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
EMERGENCY LOCATOR
TRANSMITTER (ELT)
A
ELECTRICAL
CONNETOR
(PZ153)
DETAIL A
BNC
CONNECTOR
(PZ148)
TO ELT
ANTENNA
BRACKET
BUZZER
25
ELT STRAP
ASSEMBLY
FWD
LATCH
Figure 25-2. ME 406 ELT
Revision 0
FOR TRAINING PURPOSES ONLY
25-3
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
25
25-4
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
CHAPTER 26
FIRE PROTECTION
26
INTRODUCTION
This chapter presents the fire protection system, which includes fire detection and fire extinguishing. Component location and operation as well as general maintenance considerations and functional and operational checks are covered. References for this chapter
and further specific information can be found in Chapter 26—”Fire Protection”; Chapter 5—”Time Limits/Maintenance Checks” and
Chapter 12— “Servicing” of the Manufacturer’s Maintenance Manual. (MMM)
FIRE DETECTION SYSTEM
The fire detection system detects an overheat condition or fire in the engine
compartment, and alerts the crew by a visual and audible indication. The
system consists of a heat detector loop, control box, alarm module, test
switch, and annunciator warning light or CAS message on G1000 models.
Revision 0
FOR TRAINING PURPOSES ONLY
Bus 1 powers system components through the 5-amp FIRE DET circuit breaker
26-1
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
LEGEND
LEGEND
BATTERY POWER
POSITIVE POWER OR
SWITCHABLE POWER
GROUND
DETECTION
LOOP
BATTERY POWER
ALARM
MODULE
GROUND
SIGNAL OR SENSE
CONDITION:
BATTERY ON
FIREWALL
CONTROL
BOX
OPERATE
GRN
YEL
VIO
ORN
BLK
1
2
3
4
5
1
2
3
4
5
BRN
RED
6 6
7 7
2
3
1
4
FD5
WC12
W
WC10
H
GRN
YEL
VIO
ORN
BLK
1
2
3
4
5
1
2
3
4
5
BRN
RED
6 6
7 7
FD6
1
FF
46
20 GA.
JUMPER
FIRE
DET
WC8
Figure 26-1. Fire Warning Circuit (Sheet 1 of 3)
5
WC10
H
FROM A/S
WARNING
MODULE
4
TEST
2 3 4
2 3 4
FD5
WC12
20 GA.
JUMPER
WC7
TO AUDIO
PANEL
W
WC9
BLK
YEL
BRN
VIO
3
WC5
WC6
WC3
WC1
ANNUNCIATOR
PANEL
FF
20 GA.
JUMPER
5
2
OPERATE
WC2
7 7
8 8
WC7
TO AUDIO
PANEL
WC1
WC11
20 GA.
JUMPER
WC4
CONTROL
BOX
2 3 4
2 3 4
20 GA.
JUMPER
WC2
FROM A/S
WARNING
MODULE
TEST
WC5
WC6
WC3
FIREWALL
CONDITION:
BATTERY ON—HIGH TEMP
BLK
YEL
BRN
VIO
20 GA.
JUMPER
WC4
FIRE
DET
ALARM
MODULE
SECONDARY POWER
SIGNAL OR SENSE
WC9
DETECTION
LOOP
7 7
8 8
WC11
FD6
ANNUNCIATOR
PANEL
46
WC8
Figure 26-1. Fire Warning Circuit (Sheet 2 of 3)
LEGEND
BATTERY POWER
POSITIVE POWER OR
SWITCHABLE POWER
GROUND
DETECTION
LOOP
ALARM
MODULE
SECONDARY POWER
26
FIREWALL
CONDITION:
BATTERY ON—TEST
20 GA.
JUMPER
WC4
2
CONTROL
BOX
OPERATE
GRN
YEL
VIO
ORN
BLK
1
2
3
4
5
1
2
3
4
5
BRN
RED
6 6
7 7
WC2
1
FF
20 GA.
JUMPER
FIRE
DET
5
WC10
H
4
TEST
2 3 4
2 3 4
FD5
WC12
20 GA.
JUMPER
WC7
TO AUDIO
PANEL
W
WC9
FROM A/S
WARNING
MODULE
3
WC5
WC6
WC3
WC1
BLK
YEL
BRN
VIO
7 7
8 8
WC11
FD6
ANNUNCIATOR
PANEL
46
WC8
Figure 26-1. Fire Warning Circuit (Sheet 3 of 3)
26-2
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
CHAPTER 27
FLIGHT CONTROLS
INTRODUCTION
This chapter provides a description of the flight control system with special emphasis on components and operation. General maintenance considerations are included along with an introduction to functional and operational checks. References and further specific
information are in Chapter 27— “Flight Controls”, Chapter 20—”Standard Practices-Airframe”, Chapter 5—”Time Limits/Maintenance
Checks”, and Chapter 12—”Servicing” of the Manufacturer’s Maintenance Manual.
GENERAL
27
The flight controls for the Caravan are conventional systems that provide roll, pitch and yaw control for the aircraft. The system consists
of the following:
• Aileron, elevator, and rudder control surfaces
• Aileron, elevator, and rudder trim systems
• Roll spoilers
• Wing flaps
Cockpit controls include pilot and copilot wheels for aileron and
elevator controls. Rudder pedals are on the pilot and copilot sides of
the cockpit floor.
Rudder trim, aileron trim, and elevator trim wheels are located on
the control pedestal. The primary flap selector handle and position
indicator are also on the control pedestal.
Circuit breakers for the system are the 10-amp FLAP MOTOR, 10amp STBY FLAP MOTOR, and 10-amp STALL.
• Stall warning system
Revision 0
FOR TRAINING PURPOSES ONLY
27-1
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
TRIM TAB
AILERON
SPOILER
SPOILER
AILERON
SERVO TAB
27
CONTROL
WHEELS
Figure 27-1. Aileron Control System
27-2
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
ELEVATOR AFT BELLCRANK
ELEVATOR
27
ELEVATOR FWD BELLCRANK
Figure 27-2. Elevator Control System
Revision 0
FOR TRAINING PURPOSES ONLY
27-3
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
RUDDER
27
RUDDER PEDALS
Figure 27-3. Rudder System
27-4
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
INTERCONNECT
ROD
BELLCRANK
AUXILIARY FLAP MOTOR
INTERCONNECT ROD
CONNECTING ROD
PRIMARY
FLAP MOTOR
BARREL
PUSHROD
BELLCRANK
D
FW
FLAP CABLE
BELLCRANK
27
Figure 27-4. Flap Drive System
Revision 0
FOR TRAINING PURPOSES ONLY
27-5
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
PINIION GEAR
FLAP SWITCH ASSEMBLY
27
FLAP TRANSMISSION
Figure 27-5. Flap System Components
27-6
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
LEGEND
LEGEND
BATTERY POWER
POSITIVE POWER OR
SWITCHABLE POWER
POSITIVE POWER OR
SWITCHABLE POWER
GROUND
CC 53
CONDITION:
FLAPS SELECTED UP
CC 55
CC 30
d d
CC 51
CC 51
CC 54
FLAP
MOTOR
CC 60
CC 58
CC 59
CC 63
10
CC 67
CC 66
f f
CC 68
CC 65
BLK
PRIMARY
MOTOR
10
CC 30
d d
CC 51
CC 51
CC 54
16 GA JUMPER
MANUAL
SWITCH
STBY
CC 56
CC 61
CC 70
CC 62
1 1
BLK
YEL
STANDBY
MOTOR
STANDBY
FLAP
MOTOR
10
DOWN
CC 66
f f
CC 65
16 GA JUMPER
MANUAL
SWITCH
Figure 27-6. Legacy Series Normal Flap System (Sheet 1 of 3)
CC 58
2 2
YEL
BLK
PRIMARY
MOTOR
UP
DOWN SWITCH
CC 64
1 1
NORM
PRIMARY
STANDBY SWITCH
CC 63
2 2
CC 57
CC 60
CC 59
UP
DOWN SWITCH
CC 64
2 2
CC 55
YEL
NORM
PRIMARY
STANDBY SWITCH
CC 70
CC 62
STANDBY
FLAP
MOTOR
1 1
GIA63W
AFCS
10K Ω
CC 69
STBY
CC 56
10K Ω
CC 52
10K Ω
CC 57
CC 61
CC 53
GIA63W
AFCS
CC 69
GUARDED
TO NORM
UP SWITCH
10K Ω
CC 52
FLAP
MOTOR
10
CONDITION:
FLAPS STATIONARY
GUARDED
TO NORM
UP SWITCH
CC 67
2 2
CC 68
1 1
BLK
YEL
STANDBY
MOTOR
DOWN
Figure 27-6. Legacy Series Normal Flap System (Sheet 2 of 3)
NOTES
LEGEND
BATTERY POWER
POSITIVE POWER OR
SWITCHABLE POWER
GROUND
GUARDED
TO NORM
UP SWITCH
CC 53
CONDITION:
FLAPS SELECTED DOWN
10K Ω
CC 69
CC 55
CC 30
GIA63W
AFCS
CC 52
FLAP
MOTOR
10
10K Ω
d d
CC 51
CC 51
CC 54
CC 56
CC 59
CC 70
CC 62
10
CC 66
f f
CC 65
CC 58
2 2
YEL
BLK
PRIMARY
MOTOR
UP
DOWN SWITCH
CC 64
1 1
NORM
PRIMARY
STANDBY SWITCH
CC 63
STANDBY
FLAP
MOTOR
CC 57
CC 60
CC 61
27
STBY
16 GA JUMPER
MANUAL
SWITCH
CC 67
2 2
CC 68
1 1
BLK
YEL
STANDBY
MOTOR
DOWN
Figure 27-6. Legacy Series Normal Flap System (Sheet 3 of 3)
Revision 0
FOR TRAINING PURPOSES ONLY
27-7
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
LEGEND
LEGEND
BATTERY POWER
BATTERY POWER
POSITIVE POWER OR
SWITCHABLE POWER
POSITIVE POWER OR
SWITCHABLE POWER
GROUND
GROUND
SIGNAL OR SENSE
CONDITION:
FLAPS SELECTED UP
CC 53
GIA63W
AFCS
CC 55
CC 30
d d
CC 51
CC 51
CC 54
CC 58
CC 63
CC 67
CC 66
f f
BLK
PRIMARY
MOTOR
10
CC 30
d d
CC 51
CC 51
CC 54
CC 68
CC 65
16 GA JUMPER
MANUAL
SWITCH
10K Ω
STBY
CC 56
CC 61
CC 70
CC 62
1 1
BLK
YEL
STANDBY
MOTOR
STANDBY
FLAP
MOTOR
10
DOWN
CC 66
f f
CC 65
16 GA JUMPER
MANUAL
SWITCH
Figure 27-7. Legacy Series Standby Flap System (Sheet 1 of 3)
CC 58
2 2
YEL
BLK
PRIMARY
MOTOR
UP
DOWN SWITCH
CC 64
1 1
NORM
PRIMARY
STANDBY SWITCH
CC 63
2 2
CC 57
CC 60
CC 59
UP
DOWN SWITCH
CC 64
2 2
CC 55
YEL
NORM
PRIMARY
STANDBY SWITCH
CC 70
CC 62
10
1 1
10K Ω
GIA63W
AFCS
CC 52
FLAP
MOTOR
CC 60
CC 59
STANDBY
FLAP
MOTOR
CC 53
CC 69
STBY
CC 56
CC 57
CC 61
CONDITION:
FLAPS UP / STATIONARY
10K Ω
CC 69
GUARD OPEN
STANDBY SELECTED
UP SWITCH
10K Ω
CC 52
FLAP
MOTOR
10
SIGNAL OR SENSE
GUARD OPEN
STANDBY SELECTED
UP SWITCH
CC 67
2 2
CC 68
1 1
BLK
YEL
STANDBY
MOTOR
DOWN
Figure 27-7. Legacy Series Standby Flap System (Sheet 2 of 3)
NOTES
LEGEND
BATTERY POWER
POSITIVE POWER OR
SWITCHABLE POWER
GROUND
SIGNAL OR SENSE
GUARD OPEN
STANDBY SELECTED
UP SWITCH
CC 53
CONDITION:
FLAPS SELECTED DOWN
27
GIA63W
AFCS
CC 52
10K Ω
CC 69
FLAP
MOTOR
CC 55
10
CC 30
d d
CC 51
CC 51
CC 54
STBY
CC 56
CC 59
CC 70
CC 62
CC 66
f f
CC 65
CC 58
2 2
YEL
BLK
PRIMARY
MOTOR
UP
DOWN SWITCH
CC 64
1 1
NORM
PRIMARY
STANDBY SWITCH
CC 63
10
CC 57
CC 60
CC 61
STANDBY
FLAP
MOTOR
10K Ω
16 GA JUMPER
MANUAL
SWITCH
CC 67
2 2
CC 68
1 1
BLK
YEL
STANDBY
MOTOR
DOWN
Figure 27-7. Legacy Series Standby Flap System (Sheet 3 of 3)
27-8
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
UP SWITCH
UP SWITCH
GUARD OPEN
STANDBY SELECTED
CC 53
CC 52
CC 52
CC 69
FLAP
MOTOR
CC 30
d d
CC 51
CC 51
CC 54
CC 60
CC 61
CC 69
CC 56
CC 55
10
PRIMARY
STANDBY
SWITCH
CC 57
CC 59
CC 58
1 1
2 2
YEL
PRIMARY
MOTOR
BLK
FLAP
MOTOR
CC 30
d d
CC 51
CC 51
CC 67
CC 63
2 2
BLK
PRIMARY
STANDBY
SWITCH
CC 57
1 1
CC 59
CC 58
2 2
YEL
PRIMARY
MOTOR
BLK
NORM
CC 70
CC 68
1 1
CC 66
DOWN
MANUAL
SWITCH
16 GA JUMPER
CC 68
f f
UP
2 2
BLK
STANDBY
MOTOR
YEL
STBY FLAP MOTOR
CC 65
CC 67
CC 63
DOWN SWITCH
STANDBY
MOTOR
f f
CC 64
CC 60
CC 62
DOWN SWITCH
10
CC 54
CC 61
NORM
CC 70
CC 56
CC 55
10
CC 62
STANDBY
FLAP
MOTOR
GUARD OPEN
STANDBY SELECTED
CC 53
LEGEND
1 1
YEL
STBY FLAP MOTOR
BATTERY POWER
POSITIVE POWER OR
SWITCHABLE POWER
GROUND
CONDITION:
FLAPS SELECTED UP
UP
STANDBY
FLAP
MOTOR
CC 66
10
CC 64
Figure 27-8. Caravan EX Standby Flap System (Sheet 1 of 3)
DOWN
CC 65
16 GA JUMPER
MANUAL
SWITCH
LEGEND
BATTERY POWER
POSITIVE POWER OR
SWITCHABLE POWER
GROUND
CONDITION:
FLAPS STATIONARY
Figure 27-8. Caravan EX Standby Flap System (Sheet 2 of 3)
NOTES
UP SWITCH
GUARD OPEN
STANDBY SELECTED
CC 53
CC 52
CC 69
FLAP
MOTOR
CC 56
CC 55
10
CC 30
d d
CC 51
CC 51
CC 54
CC 60
CC 61
PRIMARY
STANDBY
SWITCH
CC 57
1 1
CC 59
CC 58
2 2
YEL
PRIMARY
MOTOR
BLK
NORM
CC 70
CC 62
CC 63
CC 67
2 2
CC 68
1 1
27
BLK
DOWN SWITCH
STANDBY
MOTOR
f f
YEL
STBY FLAP MOTOR
UP
STANDBY
FLAP
MOTOR
CC 66
10
CC 64
DOWN
CC 65
16 GA JUMPER
LEGEND
BATTERY POWER
POSITIVE POWER OR
SWITCHABLE POWER
GROUND
CONDITION:
FLAPS SELECTED DOWN
MANUAL
SWITCH
Figure 27-8. Caravan EX Standby Flap System (Sheet 3 of 3)
Revision 0
FOR TRAINING PURPOSES ONLY
27-9
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
27
27-10
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
CHAPTER 28
FUEL
INTRODUCTION
The fuel system description is limited to the airframe fuel system in this chapter. Discussion begins with fuel storage. Components and operations are emphasized. General maintenance considerations are
included. References are in Chapter 28—”Fuel”, Chapter 5—”Time Limits/Maintenance Checks”, and Chapter 12—”Servicing” of the Manufacturer’s Maintenance Manual.
GENERAL
The fuel system consist of one wet wing fuel tank in each wing, two
fuel shutoff valves for each main tank, a fuel selectors off warning
system, a float type fuel quantity indicating system, low fuel level
sensors, reservoir tank, electric auxiliary fuel boost pump, main ejector
pump, motive flow check valve, manifold assembly with low pressure
switch, firewall shut-off valve, fuel filter and a EPA fuel canister.
On S/N 5000 and on, the fuel system will have the following additional
components installed: Larger inlet screens, Motive Flow Shutoff
valve, Larger Fuel Oil Heat Exchanger, and Ecology Tank, along with
the removal of the Fuel Filter &EPA Can.
Revision 0
The two wing tanks of the fuel system hold a total of 332.0 usable
gallons. Filling is through outboard (non-vented) filler caps as the
fuel gravity feeds through shutoff valves.
Each tank contains a low fuel sensor that illuminates an annunciator in the cockpit when quantity is 25 gallons or less. Fuel quantity
indicators in each tank provide indication on the cockpit fuel gage.
Approved fuels have been tested in the aircraft fuel delivery system
to ensure they meet FAA certification requirements. The list i ncludes
several types of jet fuel and avgas for emergency use only:
FOR TRAINING PURPOSES ONLY
• Jet A and Jet A-1
28
• Jet B
• JP-1, JP-4, JP-5, JP-8
• Russian RT
• Russian TS-1
Use of avgas and a nonspecific combination of avgas and jet fuel is limited to 150 hours between engine overhauls. A mixture of one part avgas
and three parts jet fuel is limited to 450 hours between engine overhauls.
28-1
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
FUEL SELECT OFF
RES FUEL LOW
FUEL PRESS LOW
AUX FUEL PMP ON
FUEL LVL LOW L
FUEL LVL LOW R
FUEL LVL LO L-R
TRQ
15
FUEL
MANIFOLD
FT–LB
X100
10
20
1666
0
FUEL CAN
AND DRAIN
ITT
VENT
600
FUEL FLOW
TRANSDUCER
900
°C
700
0
12
% RPM
100
96.5
OIL PSI
95
OIL °C
85
L
FUEL FILTER
BYPASS
INDICATOR
1900
PROP RPM
ON
FUEL
CONTROL
UNIT
Ng
50
FLOW
DIVIDER/
DUMP VALVE
OFF
ENGINE DRIVEN
FUEL PUMP
BATTERY
FUEL
HEATER
ON
NORM
OFF
FUEL
BOOST
FUEL
FILTER
START
FIREWALL
SHUTOFF
VALVE
FUEL QTY
LBS
R
FIREWALL
GEN
FIELD
STARTER
5
5
15
2
LEFT
FUEL
QTY
AUX
FUEL
PUMP
FUEL
SEL
WARN
5
10
MOTOR
P
1
BOOST PUMP
MAIN EJECTOR
PUMP
379
GEN
CONT
OFF
VENT
RESERVOIR
MANIFOLD
ASSEMBLY
FFLOW PPH
START
CONT
RESERVOIR
LOW-FUEL SENSOR
ON
OFF
AVIONICS
FUEL QUANTITY
TRANSMITTERS
FUEL QUANTITY
TRANSMITTERS
FUEL DRAIN
RESERVOIR
FUEL CAP
FUEL CAP
SHUTOFF
VALVES
28
LEFT FUEL TANK
RIGHT FUEL TANK
FUEL LOW
SWITCH
FUEL LOW
SWITCH
FUEL SWITCH
VENT WITH
FLOAT VALVE
AND PRESSURE
RELIEF VALVE
FUEL DRAINS
SHUTOFF
VALVES
FUEL DRAINS
VENT WITH
FLOAT VALVE
AND PRESSURE
RELIEF VALVE
Figure 28-1. Caravan G1000 Fuel System General Overview
28-2
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
28
Revision 0
FOR TRAINING PURPOSES ONLY
28-3
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
LEGEND
RELAY ASSEMBLY
37
BATTERY POWER
POSITIVE POWER OR
SWITCHABLE POWER
GROUND
4
HORN NO 1
D5
P2
2
1
–
+
CONDITIONS:
BATTERY ON
RIGHT ON
LEFT OFF
NO WARNING
9
R1
7
10
BB
1/2
12
X1
1
5
d
2
X1
1
K3
D8
X
X2
2
2
D9
D10
3
7
7
4
4
8
8
6
–
+
2
1
P1
L LOW FUEL
10
12
32
D4
K3
X
5
2
2
D9
D10
6
7
7
4
4
8
8
K1
12
OPEN
START
SW
ANNUNCIATOR
TEST SWITCH
P3
S4
OPEN
28 VDC
Figure 28-2. Non-G1000 Fuel Select and Warning System (Sheet 1 of 7)
–
+
b
D6
2
1
P1
W
GCU
9
D1
10 D2
3
4
8
6
L LOW FUEL
10
R LOW FUEL
12
X1
12
32
D4
X2
3
6
26
9
5
11
K2
RES LOW
2
P3
FUEL VALVE
MONITOR SWITCHES
CLOSED
CLOSED
S3
5
30
X2
d
D8
X2
1
3
D3
P
2
X1
1
1
6
12
X1
1
START
3
HORN NO 2
OPEN
BB
1/2
CLOSED
CLOSED
W
GCU
11
FUEL SEL WARN
FUEL VALVE
MONITOR SWITCHES
S2
10
11
P3
S1
R1
7
CIRCUIT BKR PANEL
RES LOW
9
f
CONDITIONS:
BATTERY ON
RIGHT OFF
LEFT OFF
HORN #1 ON
LIGHT ON
9
D5
P2
2
1
–
+
5
2
OPEN
b
D6
6
4
HORN NO 1
X2
4
R2
8
R LOW FUEL
12
X1
K2
9
RELAY ASSEMBLY
37
BATTERY POWER
POSITIVE POWER OR
SWITCHABLE POWER
GROUND
26
5
11
3
D7
HORN NO 2
D1
10 D2
6
CLOSED
START
SW
9
X2
P
3
5
K1
D3
START
5
3
11
11
1
6
CIRCUIT BKR PANEL
FUEL SEL WARN
1
LEGEND
30
S1
R2
OPEN
D7
CLOSED
CLOSED
S2
OPEN
12
9
f
OPEN
S3
CLOSED
P3
ANNUNCIATOR
TEST SWITCH
S4
OPEN
28 VDC
Figure 28-2. Non-G1000 Fuel Select and Warning System (Sheet 2 of 7)
NOTES
LEGEND
RELAY ASSEMBLY
37
BATTERY POWER
POSITIVE POWER OR
SWITCHABLE POWER
GROUND
4
HORN NO 1
P2
2
1
–
+
CONDITIONS:
BATTERY ON
RIGHT OFF
LEFT ON
START ON
HORN #1 ON
HORN #2 ON
LIGHT ON
9
D5
R1
7
11
3
1/2
5
28
K3
d
D8
X2
X
D10
6
7
4
4
8
8
3
6
4
–
+
b
D6
2
1
P1
W
GCU
6
L LOW FUEL
10
5
11
R LOW FUEL
12
X1
K2
8
12
32
D4
RES LOW
2
P3
FUEL VALVE
MONITOR SWITCHES
S1
CLOSED
S2
OPEN
12
9
D7
HORN NO 2
10 D2
26
9
X2
OPEN
R2
D1
3
CLOSED
START
SW
9
X2
P
2
X1
2
D9
7
K1
D3
START
3
1
12
X1
1
5
6
CIRCUIT BKR PANEL
BB
1
5
2
10
11
FUEL SEL WARN
1
30
f
CLOSED
OPEN
S3
CLOSED
S4
OPEN
P3
ANNUNCIATOR
TEST SWITCH
28 VDC
Figure 28-2. Non-G1000 Fuel Select and Warning System (Sheet 3 of 7)
28-4
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
LEGEND
RELAY ASSEMBLY
37
BATTERY POWER
POSITIVE POWER OR
SWITCHABLE POWER
GROUND
4
HORN NO 1
D5
P2
2
1
–
+
CONDITIONS:
BATTERY ON
RIGHT ON
LEFT ON
START ON
HORN #1 OFF
HORN #2 OFF
LIGHT OFF
9
R1
7
10
BB
1/2
5
2
X1
K3
X2
X
2
2
D9
D10
6
7
7
4
4
8
8
3
6
4
–
+
b
D6
2
1
P1
W
GCU
6
L LOW FUEL
10
R LOW FUEL
12
X1
f
4
HORN NO 1
12
32
D4
CLOSED
OPEN
BB
1/2
5
K3
X
CLOSED
5
2
2
D9
D10
6
7
7
4
4
8
8
K1
12
P3
START
SW
ANNUNCIATOR
TEST SWITCH
S4
OPEN
–
+
28 VDC
Figure 28-2. Non-G1000 Fuel Select and Warning System (Sheet 4 of 7)
b
D6
2
1
P1
W
GCU
9
D1
10 D2
3
4
8
6
L LOW FUEL
10
R LOW FUEL
12
X1
12
32
D4
X2
3
6
26
9
5
11
K2
RES LOW
2
P3
FUEL VALVE
MONITOR SWITCHES
CLOSED
CLOSED
OPEN
5
30
X2
d
D8
X2
1
3
D3
P
2
X1
1
1
6
12
X1
1
START
3
HORN NO 2
S3
11
FUEL SEL WARN
FUEL VALVE
MONITOR SWITCHES
S2
10
11
P3
S1
R1
7
CIRCUIT BKR PANEL
RES LOW
2
9
D5
P2
2
1
–
+
CONDITIONS:
BATTERY ON
RIGHT ON
LEFT ON
RIGHT FUEL LOW
RIGHT LOW LIGHT ON
HORN #1 OFF
LIGHT OFF
5
11
K2
8
9
D7
HORN NO 2
10 D2
9
RELAY ASSEMBLY
37
BATTERY POWER
POSITIVE POWER OR
SWITCHABLE POWER
GROUND
26
X2
OPEN
R2
D1
3
CLOSED
START
SW
9
X2
d
D8
5
K1
D3
P
3
1
12
X1
1
START
5
3
11
11
1
6
CIRCUIT BKR PANEL
FUEL SEL WARN
1
LEGEND
30
S1
R2
OPEN
D7
CLOSED
CLOSED
S2
OPEN
12
9
f
OPEN
S3
CLOSED
P3
ANNUNCIATOR
TEST SWITCH
S4
OPEN
28 VDC
Figure 28-2. Non-G1000 Fuel Select and Warning System (Sheet 5 of 7)
NOTES
28
Revision 0
FOR TRAINING PURPOSES ONLY
28-5
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
LEGEND
RELAY ASSEMBLY
37
BATTERY POWER
POSITIVE POWER OR
SWITCHABLE POWER
GROUND
4
HORN NO 1
D5
P2
2
1
–
+
CONDITIONS:
BATTERY ON
RIGHT ON
LEFT OFF
RIGHT FUEL LOW
RIGHT LOW LIGHT ON
HORN #1 ON
LIGHT ON
9
R1
7
10
BB
1/2
5
2
X1
K3
2
2
D9
D10
6
–
+
b
D6
2
1
P1
W
GCU
10 D2
7
7
4
4
8
8
9
8
6
L LOW FUEL
10
R LOW FUEL
12
X1
4
HORN NO 1
X
6
4
32
5
RES LOW
K3
OPEN
f
CLOSED
12
P3
START
SW
ANNUNCIATOR
TEST SWITCH
HORN NO 2
OPEN
S3
5
2
2
D9
D10
6
7
7
4
4
8
8
K1
S4
OPEN
–
+
28 VDC
Figure 28-2. Non-G1000 Fuel Select and Warning System (Sheet 6 of 7)
b
D6
2
1
P1
W
GCU
9
D1
10 D2
3
4
8
6
L LOW FUEL
10
R LOW FUEL
12
X1
12
32
D4
X2
3
6
26
9
5
11
K2
RES LOW
2
P3
FUEL VALVE
MONITOR SWITCHES
CLOSED
9
CLOSED
X
5
30
X2
d
D8
X2
1
3
D3
P
2
X1
1
6
12
X1
1
START
3
CLOSED
S2
BB
1/2
D4
FUEL VALVE
MONITOR SWITCHES
S1
11
FUEL SEL WARN
P3
OPEN
R2
10
11
12
2
R1
7
CIRCUIT BKR PANEL
X2
3
9
D5
P2
2
1
–
+
CONDITIONS:
PUSH TO TEST
5
11
K2
BATTERY POWER
POSITIVE POWER OR
SWITCHABLE POWER
GROUND
26
RELAY ASSEMBLY
37
1
D7
HORN NO 2
D1
3
CLOSED
START
SW
9
X2
d
D8
X2
5
K1
D3
P
3
1
12
X1
1
START
5
3
11
11
1
6
CIRCUIT BKR PANEL
FUEL SEL WARN
1
LEGEND
30
S1
R2
OPEN
D7
CLOSED
CLOSED
S2
OPEN
12
9
f
OPEN
S3
CLOSED
P3
ANNUNCIATOR
TEST SWITCH
S4
OPEN
28 VDC
Figure 28-2. Non-G1000 Fuel Select and Warning System (Sheet 7 of 7)
NOTES
28
28-6
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
JS001
PS001
DOOR POST/RH WING
JR007
PR007
LOW FUEL SW
16
(20)
(20)
A
B
C
GR002
REFER TO
91-20-02
FUEL SELECT OFF
NOTES
SR002
LOW FUEL SW
DECENDING FUEL
R FUEL TANK
FUEL SELECT OFF – One or both fuel tank selectors are off.
GDU PFDs
OFF
UI005
GEA 71
PC001
JC001
ELEFUS/L DOOR POST
PI001
R FUEL SELECT SW OFF
(20)
(20)
12
71
10
12
(20)
(20)
ON NO
SR001
R FUEL
SELECT SW
C
NC
JC035
PC035A
PC035B
AUX FUEL PUMP
RESERVOIR LOW FUEL
41
5
5
RESERVOIR TANK
FLOAT SWITCH
OFF
PC043
JC043
ELEFUS/L DOOR POST
RIGHT LOW FUEL
3
1
(20)
JM001
PM001
DOOR POST/LH WING
L FUEL SELECT SW OFF
70
6
(20)
22
12
(20)
LEFT LOW FUEL
2
FUEL SELECT WARN HORN (GND)
FUEL SELECT WARN HORN (GND)
2
3
ON
(20)
(20)
NO
C
NC
5
SL001
L FUEL
SELECT SW
GC002
GND
PI002
B
(20)
JL007
PL007
LOW FUEL SW
(20)
16
(20)
(20)
GL003
REFER TO 91-20-02
SL002
LOW FUEL SW
A
B
C
DECENDING FUEL
L FUEL TANK
SI031
TEST WARN
UI006
#1 GIA63W
PI507
P605
FUEL SELECT WARN CB ENGAGE
16
PI005
JI005
AVN/ELECT DISC
34
(20)
GC001
GND
(REFER TO FIRE DETECT)
26-10-01
(20)
(20)
F
UI007
#2 GIA63W
PI506
P605
FUEL SELECT WARN CB ENGAGE
3
1
5
6
4
FIRE WARN
(MOM)
OFF
FUEL WARN
(MOM)
16
DC003
JC005
PC005
L CB PNL
LEGEND
BATTERY POWER
POSITIVE POWER OR SWITCHABLE POWER
GROUND
2
BB
(20)
BLK
WHT
JC047
PC047
ELEFUS/L DOORPOST
(20)
(20)
2
1
JC045
PC045
WARN HORN
(20)
(20)
2
1
(20)
(20)
–
(20)
+
UC004
SONALERT
FUEL SEL WARN
28 VDC
REFER TO 24-60-03
28
DC004
WHT
BLK
(20)
(20)
3
(20)
3
(20)
+
–
UC003
SONALERT
CONDITIONS:
FUEL SELECTORS—OFF
L AND R SELECTORS—OFF
BATTERY SWITCH—ON
AVIONICS SWITCHES—1 AND 2 ON
HORNS—ONE SOUNDING
Figure 28-3. G1000 Fuel Select and Warning (Sheet 1 of 5)
Revision 0
FOR TRAINING PURPOSES ONLY
28-7
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
JS001
PS001
DOOR POST/RH WING
JR007
PR007
LOW FUEL SW
16
(20)
(20)
A
B
C
GR002
REFER TO
91-20-02
FUEL SELECT OFF
NOTES
SR002
LOW FUEL SW
DECENDING FUEL
R FUEL TANK
FUEL SELECT OFF – One or both fuel tank selectors are off.
GDU PFDs
OFF
UI005
GEA 71
PC001
JC001
ELEFUS/L DOOR POST
PI001
R FUEL SELECT SW OFF
(20)
(20)
12
71
10
12
(20)
(20)
ON NO
SR001
R FUEL
SELECT SW
C
NC
JC035
PC035A
PC035B
AUX FUEL PUMP
RESERVOIR LOW FUEL
41
5
5
RESERVOIR TANK
FLOAT SWITCH
OFF
PC043
JC043
ELEFUS/L DOOR POST
RIGHT LOW FUEL
3
1
(20)
JM001
PM001
DOOR POST/LH WING
L FUEL SELECT SW OFF
70
6
(20)
22
12
(20)
LEFT LOW FUEL
2
FUEL SELECT WARN HORN (GND)
FUEL SELECT WARN HORN (GND)
2
3
ON
(20)
(20)
NO
C
NC
5
SL001
L FUEL
SELECT SW
GC002
GND
PI002
B
(20)
JL007
PL007
LOW FUEL SW
(20)
16
(20)
(20)
GL003
REFER TO 91-20-02
SL002
LOW FUEL SW
A
B
C
DECENDING FUEL
L FUEL TANK
SI031
TEST WARN
UI006
#1 GIA63W
PI507
P605
FUEL SELECT WARN CB ENGAGE
16
PI005
JI005
AVN/ELECT DISC
34
(20)
GC001
GND
(REFER TO FIRE DETECT)
26-10-01
(20)
(20)
F
UI007
#2 GIA63W
PI506
P605
FUEL SELECT WARN CB ENGAGE
3
1
5
6
4
FIRE WARN
(MOM)
OFF
FUEL WARN
(MOM)
16
DC003
JC005
PC005
L CB PNL
BB
28
2
LEGEND
BATTERY POWER
GROUND
(20)
WHT
BLK
JC047
PC047
ELEFUS/L DOORPOST
(20)
(20)
JC045
PC045
WARN HORN
2
1
(20)
(20)
2
1
(20)
(20)
3
(20)
3
(20)
–
(20)
+
UC004
SONALERT
FUEL SEL WARN
28 VDC
REFER TO 24-60-03
DC004
WHT
BLK
(20)
(20)
+
–
UC003
SONALERT
CONDITIONS:
START CONTROL AND FUEL SELECT CBs—IN
R FUEL SELECTOR—OFF
BATTERY SWITCH—ON
AVIONICS SWITCHES—1 AND 2 ON
START SWITCH—START
BOTH HORNS—SOUNDING
Figure 28-3. G1000 Fuel Select and Warning (Sheet 2 of 5)
28-8
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
JS001
PS001
DOOR POST/RH WING
JR007
PR007
LOW FUEL SW
16
FUEL SELECT OFF
(20)
(20)
FUEL SELECT OFF – One or both fuel tank selectors are off.
FUEL LVL R LOW
A
B
C
GR002
REFER TO
91-20-02
NOTES
SR002
LOW FUEL SW
DECENDING FUEL
R FUEL TANK
FUEL LVL LOW R – Right fuel tank is low.
GDU PFDs
OFF
UI005
GEA 71
PC001
JC001
ELEFUS/L DOOR POST
PI001
R FUEL SELECT SW OFF
(20)
(20)
12
71
10
12
(20)
(20)
ON NO
SR001
R FUEL
SELECT SW
C
NC
JC035
PC035A
PC035B
AUX FUEL PUMP
RESERVOIR LOW FUEL
41
5
5
RESERVOIR TANK
FLOAT SWITCH
OFF
PC043
JC043
ELEFUS/L DOOR POST
RIGHT LOW FUEL
3
1
(20)
JM001
PM001
DOOR POST/LH WING
L FUEL SELECT SW OFF
70
6
(20)
22
12
(20)
LEFT LOW FUEL
2
FUEL SELECT WARN HORN (GND)
FUEL SELECT WARN HORN (GND)
2
3
ON
(20)
(20)
NO
C
NC
5
SL001
L FUEL
SELECT SW
GC002
GND
PI002
B
(20)
JL007
PL007
LOW FUEL SW
(20)
16
(20)
(20)
GL003
REFER TO 91-20-02
SL002
LOW FUEL SW
A
B
C
DECENDING FUEL
L FUEL TANK
SI031
TEST WARN
UI006
#1 GIA63W
PI507
P605
FUEL SELECT WARN CB ENGAGE
16
PI005
JI005
AVN/ELECT DISC
34
(20)
GC001
GND
(REFER TO FIRE DETECT)
26-10-01
(20)
(20)
F
UI007
#2 GIA63W
PI506
P605
FUEL SELECT WARN CB ENGAGE
2
3
1
5
6
4
FIRE WARN
(MOM)
OFF
FUEL WARN
(MOM)
16
LEGEND
BATTERY POWER
POSITIVE POWER OR SWITCHABLE POWER
GROUND
DC003
JC005
PC005
L CB PNL
BB
(20)
JC047
PC047
ELEFUS/L DOORPOST
(20)
(20)
2
1
JC045
PC045
WARN HORN
(20)
(20)
2
1
(20)
(20)
–
(20)
+
UC004
SONALERT
FUEL SEL WARN
28 VDC
REFER TO 24-60-03
28
DC004
WHT
CONDITIONS:
START CONTROL AND FUEL SELECT CBs—IN
R FUEL SELECTOR—ON
L FUEL SELECTOR—OFF
BATTERY SWITCH—ON
AVIONICS SWITCHES—1 AND 2 ON
R FUEL LEVEL—25 GALS OR LESS
HORNS UC004—SOUNDING
BLK
WHT
BLK
(20)
(20)
3
(20)
3
(20)
+
–
UC003
SONALERT
Figure 28-3. G1000 Fuel Select and Warning (Sheet 3 of 5)
Revision 0
FOR TRAINING PURPOSES ONLY
28-9
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
JS001
PS001
DOOR POST/RH WING
JR007
PR007
LOW FUEL SW
(20)
(20)
16
FUEL SELECT OFF
FUEL SELECT OFF – One or both fuel tank selectors are off.
FUEL LVL L LOW
A
B
C
GR002
REFER TO
91-20-02
NOTES
SR002
LOW FUEL SW
DECENDING FUEL
R FUEL TANK
FUEL LVL LOW L – Left fuel tank is low.
GDU PFDs
OFF
UI005
GEA 71
PC001
JC001
ELEFUS/L DOOR POST
PI001
R FUEL SELECT SW OFF
(20)
(20)
12
71
10
12
(20)
(20)
ON NO
SR001
R FUEL
SELECT SW
C
NC
JC035
PC035A
PC035B
AUX FUEL PUMP
RESERVOIR LOW FUEL
41
5
5
RESERVOIR TANK
FLOAT SWITCH
OFF
PC043
JC043
ELEFUS/L DOOR POST
RIGHT LOW FUEL
3
1
(20)
JM001
PM001
DOOR POST/LH WING
L FUEL SELECT SW OFF
70
6
(20)
22
12
(20)
LEFT LOW FUEL
2
FUEL SELECT WARN HORN (GND)
FUEL SELECT WARN HORN (GND)
2
3
ON
(20)
(20)
NO
SL001
L FUEL
SELECT SW
C
NC
5
GC002
GND
PI002
B
(20)
JL007
PL007
LOW FUEL SW
(20)
16
(20)
(20)
GL003
REFER TO 91-20-02
SL002
LOW FUEL SW
A
B
C
DECENDING FUEL
L FUEL TANK
SI031
TEST WARN
UI006
#1 GIA63W
PI507
P605
FUEL SELECT WARN CB ENGAGE
16
JI005
PI005
AVN/ELECT DISC
34
(20)
GC001
GND
(REFER TO FIRE DETECT)
26-10-01
(20)
(20)
F
UI007
#2 GIA63W
PI506
P605
FUEL SELECT WARN CB ENGAGE
3
1
5
6
4
FIRE WARN
(MOM)
OFF
FUEL WARN
(MOM)
16
LEGEND
BATTERY POWER
POSITIVE POWER OR SWITCHABLE POWER
28
2
GROUND
DC003
JC005
PC005
L CB PNL
BB
(20)
WHT
JC047
PC047
ELEFUS/L DOORPOST
(20)
(20)
JC045
PC045
WARN HORN
2
1
(20)
(20)
2
1
(20)
(20)
3
(20)
3
(20)
–
(20)
+
UC004
SONALERT
FUEL SEL WARN
28 VDC
REFER TO 24-60-03
DC004
WHT
CONDITIONS:
START CONTROL AND FUEL SELECT CBs—IN
R FUEL SELECTOR—OFF
L FUEL SELECTOR—ON
BATTERY SWITCH—ON
AVIONICS SWITCHES—1 AND 2 ON
L FUEL LEVEL—25 GALS OR LESS
HORNS UC004—SOUNDING
BLK
BLK
(20)
(20)
+
–
UC003
SONALERT
Figure 28-3. G1000 Fuel Select and Warning (Sheet 4 of 5)
28-10
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
JS001
PS001
DOOR POST/RH WING
JR007
PR007
LOW FUEL SW
16
(20)
(20)
A
B
C
GR002
REFER TO
91-20-02
FUEL SELECT OFF
NOTES
SR002
LOW FUEL SW
DECENDING FUEL
R FUEL TANK
FUEL SELECT OFF – One or both fuel tank selectors are off.
GDU PFDs
OFF
UI005
GEA 71
PC001
JC001
ELEFUS/L DOOR POST
PI001
R FUEL SELECT SW OFF
(20)
(20)
12
71
10
12
(20)
(20)
ON NO
SR001
R FUEL
SELECT SW
C
NC
JC035
PC035A
PC035B
AUX FUEL PUMP
RESERVOIR LOW FUEL
41
5
5
RESERVOIR TANK
FLOAT SWITCH
OFF
PC043
JC043
ELEFUS/L DOOR POST
RIGHT LOW FUEL
3
1
(20)
JM001
PM001
DOOR POST/LH WING
L FUEL SELECT SW OFF
70
6
(20)
22
12
(20)
LEFT LOW FUEL
2
FUEL SELECT WARN HORN (GND)
FUEL SELECT WARN HORN (GND)
2
3
ON
(20)
(20)
NO
C
NC
5
SL001
L FUEL
SELECT SW
GC002
GND
PI002
B
(20)
JL007
PL007
LOW FUEL SW
(20)
16
(20)
(20)
GL003
REFER TO 91-20-02
SL002
LOW FUEL SW
A
B
C
DECENDING FUEL
L FUEL TANK
SI031
TEST WARN
UI006
#1 GIA63W
PI507
P605
FUEL SELECT WARN CB ENGAGE
16
PI005
JI005
AVN/ELECT DISC
34
(20)
GC001
GND
(REFER TO FIRE DETECT)
26-10-01
(20)
(20)
F
UI007
#2 GIA63W
PI506
P605
FUEL SELECT WARN CB ENGAGE
2
3
1
5
6
4
FIRE WARN
(MOM)
OFF
FUEL WARN
(MOM)
16
DC003
JC005
PC005
L CB PNL
LEGEND
BATTERY POWER
GROUND
CONDITIONS:
START CONTROL AND FUEL SELECT CBs—IN
R FUEL SELECTOR—ON
L FUEL SELECTOR—ON
BATTERY SWITCH—ON
AVIONICS SWITCHES—1 AND 2 ON
FUEL SELECT OFF, TEST SWITCH—DOWN
BOTH HORNS—SOUNDING
BB
(20)
WHT
BLK
JC047
PC047
ELEFUS/L DOORPOST
(20)
(20)
2
1
JC045
PC045
WARN HORN
(20)
(20)
2
1
(20)
(20)
–
(20)
+
UC004
SONALERT
FUEL SEL WARN
28 VDC
REFER TO 24-60-03
28
DC004
WHT
BLK
(20)
(20)
3
(20)
3
(20)
+
–
UC003
SONALERT
Figure 28-3. G1000 Fuel Select and Warning (Sheet 5 of 5)
Revision 0
FOR TRAINING PURPOSES ONLY
28-11
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
FUEL INLET
FROM AUX
PUMP
NOTES
FROM MAIN
EJECTOR
VENT OUTLET
FLAPPER CHECK
VALVE
(FOUR EACH)
VENT OUTLET
VENT LINE
FUEL INLET
(FOUR EACH)
LOW LEVEL
SWITCH
MAIN EJECTOR PUMP
MOTIVE FLOW
CHECK VALVE
AUXILIARY ELECTRIC
FUEL PUMP
28
DRAIN VALVE
Figure 28-4. Fuel Reservoir
28-12
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
AUX
FUEL 10
PUMP
QA1
FUEL
BOOST
3
2
1
6
4
5
QA16
R R
QA2
QA13
QA15
e e
WW
QA17
AUX
FUEL 10
PUMP
KK
QA3
PRESSURE
SWITCH
BLK (REF)
1 1
QA5
4 4
QA6
QA12
QA14
RED (REF)
WHT (REF)
QA4
2 2
QA7
QA1
AUX
FUEL
PUMP
QA10
QA11
FUEL
BOOST
3
2
1
6
4
5
QA16
R R
QA2
QA13
QA15
e e
WW
QA17
AUX
FUEL 10
PUMP
KK
3 5
QA3
PRESSURE
SWITCH
3 5
BLK (REF)
FUEL
PUMP
RELAY
QA5
4 4
QA6
QA12
QA14
RED (REF)
QA4
WHT (REF)
OPEN > 6.0 PSI
CLOSED < 4.75 PSI
1 1
2 2
QA7
QA10
QA11
G1000 ONLY
26
29
QA8
QA9
ANNUNCIATOR
PANEL
LEGEND
POSITIVE POWER OR
SWITCHABLE POWER
GROUND
4
Figure 28-5. Auxiliary Fuel Pump (Sheet 1 of 6)
R R
QA2
QA13
QA15
e e
WW
QA17
KK
QA3
PRESSURE
SWITCH
3 5
BLK (REF)
FUEL
PUMP
RELAY
1 1
QA5
4 4
QA6
QA12
2 2
QA7
QA14
RED (REF)
WHT (REF)
QA4
AUX
FUEL
PUMP
QA10
3 5
QA11
3 5
FUEL
PUMP
RELAY
OPEN > 6.0 PSI
CLOSED < 4.75 PSI
GEA71
FUEL PRESSURE LOW
AUX FUEL PUMP ON
G1000 ONLY
CONDITIONS:
OFF SELECTED
PRESSURE < 4.75 PSI
ENGINE NOT RUNNING
5
QA16
3 5
GEA71
65
71
6
OPEN > 6.0 PSI
CLOSED < 4.75 PSI
GEA71
FUEL PRESSURE LOW
AUX FUEL PUMP ON
QA1
AUX
FUEL
PUMP
FUEL
BOOST
3
2
1
65
71
26
29
QA8
QA9
ANNUNCIATOR
PANEL
LEGEND
BATTERY POWER
GROUND
FUEL PRESSURE LOW
AUX FUEL PUMP ON
G1000 ONLY
CONDITIONS:
ON SELECTED
RELAY ENERGIZED
PUMP RUNNING
Figure 28-5. Auxiliary Fuel Pump (Sheet 2 of 6)
65
71
26
29
QA8
QA9
ANNUNCIATOR
PANEL
LEGEND
POSITIVE POWER OR
SWITCHABLE POWER
CONDITIONS:
NORM SELECTED
PRESSURE > 6.0 PSI
PRESSURE SWITCH OPEN
Figure 28-5. Auxiliary Fuel Pump (Sheet 3 of 6)
NOTES
28
Revision 0
FOR TRAINING PURPOSES ONLY
28-13
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
AUX
FUEL 10
PUMP
QA1
FUEL
BOOST
3
2
1
6
4
5
QA16
R R
QA2
QA13
QA15
e e
WW
QA17
AUX
FUEL 10
PUMP
KK
QA3
PRESSURE
SWITCH
BLK (REF)
1 1
QA5
4 4
QA6
QA12
QA14
RED (REF)
WHT (REF)
QA4
2 2
QA7
QA1
AUX
FUEL
PUMP
QA10
QA11
FUEL
BOOST
3
2
1
6
4
5
QA16
R R
QA2
QA13
QA15
e e
WW
QA17
AUX
FUEL 10
PUMP
KK
3 5
QA3
PRESSURE
SWITCH
3 5
BLK (REF)
FUEL
PUMP
RELAY
QA5
4 4
QA6
QA12
QA14
RED (REF)
QA4
WHT (REF)
OPEN > 6.0 PSI
CLOSED < 4.75 PSI
1 1
2 2
QA7
QA10
QA11
G1000 ONLY
26
29
QA8
QA9
ANNUNCIATOR
PANEL
LEGEND
POSITIVE POWER OR
SWITCHABLE POWER
GROUND
4
Figure 28-5. Auxiliary Fuel Pump (Sheet 4 of 6)
R R
QA2
QA13
QA15
e e
WW
QA17
KK
QA3
PRESSURE
SWITCH
3 5
BLK (REF)
FUEL
PUMP
RELAY
1 1
QA5
4 4
QA6
QA12
2 2
QA7
QA14
RED (REF)
WHT (REF)
QA4
AUX
FUEL
PUMP
QA10
3 5
QA11
3 5
FUEL
PUMP
RELAY
OPEN > 6.0 PSI
CLOSED < 4.75 PSI
GEA71
FUEL PRESSURE LOW
AUX FUEL PUMP ON
G1000 ONLY
CONDITIONS:
OFF SELECTED
PRESSURE < 4.75 PSI
ENGINE NOT RUNNING
5
QA16
3 5
GEA71
65
71
6
OPEN > 6.0 PSI
CLOSED < 4.75 PSI
GEA71
FUEL PRESSURE LOW
AUX FUEL PUMP ON
QA1
AUX
FUEL
PUMP
FUEL
BOOST
3
2
1
65
71
26
29
QA8
QA9
ANNUNCIATOR
PANEL
LEGEND
BATTERY POWER
GROUND
FUEL PRESSURE LOW
AUX FUEL PUMP ON
G1000 ONLY
CONDITIONS:
ON SELECTED
RELAY ENERGIZED
PUMP RUNNING
Figure 28-5. Auxiliary Fuel Pump (Sheet 5 of 6)
65
71
26
29
QA8
QA9
ANNUNCIATOR
PANEL
LEGEND
POSITIVE POWER OR
SWITCHABLE POWER
CONDITIONS:
NORM SELECTED
PRESSURE > 6.0 PSI
PRESSURE SWITCH OPEN
Figure 28-5. Auxiliary Fuel Pump (Sheet 6 of 6)
NOTES
28
28-14
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
RH FUEL
QUANTITY
5
EB1
J
J
EB14
A
C
B
RH WING
RH FUEL
INDICATOR
EB11
3
EB2
2
2
EB23
EB7
3
3
EB24
3
EB3
EB6
DD DD
EB13
EB17
EB18
3
EB8
LH WING
5
XMTR6
INBD
3
LH FUEL
QUANTITY
XMTR4
INBD
XMTR5
EB20
XMTR8
XMTR3
B
A
C
EB21
LH FUEL
INDICATOR
EB19
XMTR7
OUTBD
EB12
EB22
H
XMTR10
EB5
OUTBD
XMTR9
LEGEND
CONDITIONS:
FUEL QUANTITY INDICATING
BATTERY SWITCH—ON
BATTERY POWER
GROUND
EB10
SECONDARY POWER
Figure 28-6. Non-G1000 Fuel Quantity Indicating (Sheet 1 of 4)
RH FUEL
QUANTITY
5
EB1
J
J
A
C
B
EB14
RH WING
RH FUEL
INDICATOR
EB11
3
EB2
2
2
EB23
EB7
3
3
EB24
3
EB3
EB6
DD DD
EB17
EB18
3
EB8
LH WING
5
XMTR6
INBD
3
LH FUEL
QUANTITY
OPEN CIRCUIT
XMTR4
INBD
XMTR5
EB20
XMTR8
XMTR3
B
A
C
EB13
LH FUEL
INDICATOR
EB21
EB19
XMTR7
OUTBD
EB12
XMTR10
EB5
OUTBD
XMTR9
LEGEND
BATTERY POWER
GROUND
SECONDARY POWER
28
EB22
H
CONDITIONS:
FUEL QUANTITY INDICATING
BATTERY SWITCH—ON
OPEN CIRCUIT—MAXIMUM
QUANTITY INDICATION RH
EB10
Figure 28-6. Non-G1000 Fuel Quantity Indicating (Sheet 2 of 4)
Revision 0
FOR TRAINING PURPOSES ONLY
28-15
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
RH FUEL
QUANTITY
5
EB1
J
J
EB14
A
C
B
RH WING
RH FUEL
INDICATOR
EB11
3
EB2
2
2
EB23
EB7
3
3
EB24
3
EB3
EB6
DD DD
EB13
EB17
EB18
3
EB8
LH WING
5
XMTR6
INBD
3
LH FUEL
QUANTITY
SHORT CIRCUIT
XMTR4
INBD
XMTR5
EB20
XMTR8
XMTR3
B
A
C
EB21
LH FUEL
INDICATOR
EB19
XMTR7
OUTBD
EB12
EB22
H
XMTR10
EB5
OUTBD
XMTR9
LEGEND
CONDITIONS:
FUEL QUANTITY INDICATING
BATTERY SWITCH—ON
SHORT CIRCUIT—LOW
QUANTITY INDICATION RH
BATTERY POWER
GROUND
SECONDARY POWER
EB10
Figure 28-6. Non-G1000 Fuel Quantity Indicating (Sheet 3 of 4)
RH FUEL
QUANTITY
5
EB1
J
J
EB14
A
C
B
RH WING
RH FUEL
INDICATOR
EB11
3
EB2
2
2
EB23
EB7
3
3
EB24
3
EB3
EB18
3
EB8
LH WING
5
EB6
DD DD
EB13
B
A
C
LH FUEL
INDICATOR
XMTR6
EB17
INBD
3
LH FUEL
QUANTITY
XMTR4
INBD
XMTR5
EB20
XMTR8
XMTR3
EB21
230 OHM
RESISTOR
EB19
XMTR7
OUTBD
EB12
28
EB22
H
XMTR10
EB5
OUTBD
XMTR9
LEGEND
BATTERY POWER
GROUND
CONDITIONS:
FUEL QUANTITY INDICATING
BATTERY SWITCH—ON
CALIBRATE FULL
EB10
SECONDARY POWER
Figure 28-6. Non-G1000 Fuel Quantity Indicating (Sheet 4 of 4)
28-16
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
LEGEND
UR002
R FUEL LEVEL
SENSOR (OUTBD)
PR002
BATTERY POWER
11
13
8
9
6
12
5
GROUND
SIGNAL OR SENSE
CONDITIONS:
BATTERY ON
NOTES
CONFIG RETURN
CONFIG 3
CONFIG 2
CONFIG 1
CONFIG 0
CAN TERM RES START
CAN TERM RES END
120Ω
(WHT)
(BLU)
(BLU)
(WHT)
2
1
3
4
GROUND
28 VDC
CAN (HI)
CAN (LO)
1
UR001
R FUEL LEVEL
SENSOR (INBD)
PR001
11
13
8
9
6
12
5
JS001
PS001
L DOOR POST/R WING
CONFIG RETURN
CONFIG 3
CONFIG 2
CONFIG 1
CONFIG 0
CAN TERM RES START
CAN TERM RES END
120Ω
PC043
JC043
CAB/L DOOR POST
JC011
PC011
L CB PNL
R FUEL QTY
28 VDC
J
5
REFER TO 24-60-03
(20)
AC006
(WHT) (20)
(BLU) (20)
2
3
(WHT) (20)
(BLU) (20)
(BLU) (20)
(WHT) (20)
4
10
11
(BLU) (20)
(WHT) (20)
(WHT) (20)
(BLU) (20)
12
13
(BLU) (20)
(WHT) (20)
14
15
16
GC001
GND
17
3
(WHT)
(BLU)
4
3
18
19
20
(BLU)
(WHT)
1
2
CAN (LO)
CAN (HI)
28 VDC
GROUND
1
L
U
M
JC005
PC005
L CB PNL
L FUEL QTY
28 VDC
DD
5
(20)
AC007
REFER TO 24-60-03
JM001
PM001
L DOOR POST/L WING
UL001
L FUEL LEVEL
SENSOR (INBD)
PL001
(WHT) (20)
(BLU) (20)
14
15
(WHT)
(BLU)
2
1
(BLU) (20)
(WHT) (20)
3
18
20
(BLU)
(WHT)
3
4
GROUND
28 VDC
CAN (HI)
CAN (LO)
120Ω
5
12
6
9
8
13
11
JI005
PI005
ELE/AVN DISC
UI007
GIA2
(WHT) (20)
(BLU) (20)
14
15
1
PI502
CAN BUS (LO)
CAN BUS (HI)
30
32
UL002
L FUEL LEVEL
SENSOR (OUTBD)
PL002
(WHT)
(BLU)
(BLU)
(WHT)
UI006
GIA1
4
3
1
2
32
30
28
CAN (LO)
CAN (HI)
28 VDC
GROUND
120Ω
PI503
CAN BUS (HI)
CAN BUS (LO)
CAN TERM RES END
CAN TERM RES START
CONFIG 0
CONFIG 1
CONFIG 2
CONFIG 3
CONFIG RETURN
5
12
6
9
8
13
11
(BLU) (20)
(WHT) (20)
(BLU) (20)
(WHT) (20)
16
17
26
CAN TERM RES END
CAN TERM RES START
CONFIG 0
CONFIG 1
CONFIG 2
CONFIG 3
CONFIG RETURN
1
Figure 28-7. G1000 Fuel Quantity Indicating
Revision 0
FOR TRAINING PURPOSES ONLY
28-17
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
28
28-18
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
CHAPTER 30
ICE AND RAIN PROTECTION
INTRODUCTION
This chapter presents the ice and rain protection systems. Emphasis is on component location and operation. Discussions include
methods of ice protection and removal. General maintenance considerations are included along with an introduction to operational and
functional checks. References for this chapter and further specific information are in Chapter 30—”Ice and Rain Protection”, Chapter
5—”Time Limits and Maintenance Checks”, and Chapter 12—”Servicing” of the Manufacturer’s Maintenance Manual.
GENERAL
The ice and rain protection systems detect, remove, or prevent ice
formation on critical surfaces of the aircraft. Pneumatic deice boots
protect the wing surfaces while electrothermal boots protect the propeller. Electrical heaters are available for the stall warning vane, pitot
probe, and windshield. The DEICE/ANTI-ICE panel on the lower left
instrument panel controls the various systems.
Revision 0
FOR TRAINING PURPOSES ONLY
These items coupled with an airspeed awareness system and ice detection
lights fulfill the FAA regulations for flight into known icing conditions.
208 units 500 and on and 208B units 2000 and on are ice protected
with an optional TKS porous system.
30-1
30
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
PROPELLER BOOTS
LEFT WING PANELS
RIGHT WING PANELS
W/S SPRAY BAR
PROPORTIONING
UNIT
PROPELLER
NOZZLE
PROPORTIONING
UNIT
STRUT PANELS
STRUT PANELS
FILTERS
LEVEL
SENDER
VENT
LOW
LEVEL
SWITCH
TANK
SOLENOID
VALVE
PROPORTIONING
UNIT
VENT
HIGH
PRESSURE
SWITCH
METERING
PUMPS
CRACKING VALVES
WINDSHEILD PUMP
LOW PRESSURE SWITCH
30
LOW PRESSURE SWITCH
LEGEND
1/2”
5/16”
3/16”
TAIL PANELS
Figure 30-1. TKS Ice System Overview
30-2
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
P3 BLEED AIR
BLEED AIR PRESSURE REGULATOR
(18 PSI)
RELAY
FIREWALL
TIMER
EJECTOR FLOW
CONTROL VALVES
PRESSURE SWITCHES
(15 PSI)
RH OUTBD WING
LH OUTBD WING
LH INBD WING
RH INBD WING
LH WING STRUT
RH WING STRUT
LH GEAR
RH GEAR
POD
LEGEND
P3 BLEED AIR
REGULATED BLEED AIR (18 PSI)
1st CYCLE
2nd CYCLE
VERTICAL STABILIZER
30
3rd CYCLE
LH HORIZONTAL STABILIZER
RH HORIZONTAL STABILIZER
Figure 30-2. Pneumatic De-Ice System Overview
Revision 0
FOR TRAINING PURPOSES ONLY
30-3
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
19
HA18
ANNUNCIATOR PANEL
19
HA65
W/S
ANTI
ICE
HA12
Y Y
(BLK)
A
B
C
D
E
HA60
HA64
HA1
K26
(BLK)
A
B
C
D
E
BLK
BLK
BLU
BLU
W/S
ANTI
ICE
PRIMARY
HEATING
ELEMENT
HA54
20
HA12
Y Y
HA64
HA1
(BLK)
K26
WHT
WHT
HA68
HA61
W/S
ANTI
ICE
CONT
5
HA13
U U
AUTO
OFF
HA4
SECONDARY
HEATING
ELEMENT
HA62 HA3 HA66 HA57 HA52 HA53
MANUAL
7
4
W/S
ANTI
ICE
CONT
5
HA13
U U
HA4
1
3
SECONDARY POWER
CONDITIONS:
PRIMARY—AUTO
SECONDARY—AUTO
HA51
KA25
HA56 HA55
SECONDARY SWITCH
19
SECONDARY
HEATING
ELEMENT
W/S
ANTI
ICE
SEC
5
2
20
A A
LEGEND
8
6
BATTERY POWER
HA9
1
3
GND
BLOCK
POSITIVE POWER OR
SWITCHABLE POWER
N R
HA49
OFF
HA17
MANUAL
HA56 HA55
SECONDARY SWITCH
GROUND
KA25
HA51
SECONDARY POWER
CONDITIONS:
PRIMARY—AUTO
SECONDARY—OFF
HA63 HA19
PRIMARY
HEATING
ELEMENT
HA54
HA64
HA1
7
4
Figure 30-3. Dual Element Windshield Anti-Ice (Sheet 2 of 3)
HA65
Y Y
WHT
WHT
HA18
ANNUNCIATOR PANEL
HA12
L L
M M
HA62 HA3 HA66 HA57 HA52 HA53
AUTO
Figure 30-3. Dual Element Windshield Anti-Ice (Sheet 1 of 3)
20
SENSE
ELEMENT
HA59
HA5
CONTROLLER
GROUND
N R
HA49
OFF
MANUAL
W/S
ANTI
ICE
BLK
BLK
BLU
BLU
MANUAL
BATTERY POWER
HA9
5
2
GND
BLOCK
HA17
AUTO
OFF
LEGEND
8
6
AUTO
A A
A
B
C
D
E
PRIMARY SWITCH
CONTROLLER
20
A
B
C
D
E
HA61
HA5
PRIMARY SWITCH
W/S
ANTI
ICE
SEC
HA60
(BLK)
SENSE
ELEMENT
HA59
L L
M M
HA68
HA63 HA19
HA65
PRIMARY
HEATING
ELEMENT
HA54
20
HA18
ANNUNCIATOR PANEL
HA63 HA19
(BLK)
HA60
K26
(BLK)
HA68
A
B
C
D
E
A
B
C
D
E
L L
M M
NOTES
BLK
BLK
BLU
BLU
SENSE
ELEMENT
HA59
WHT
WHT
HA61
W/S
ANTI
ICE
CONT
5
HA13
U U
AUTO
OFF
HA4
HA5
SECONDARY
HEATING
ELEMENT
HA62 HA3 HA66 HA57 HA52 HA53
MANUAL
PRIMARY SWITCH
CONTROLLER
30
7
4
5
2
HA9
1
3
GND
BLOCK
AUTO
W/S
ANTI
ICE
SEC
20
A A
HA49
OFF
HA17
MANUAL
LEGEND
8
6
HA56 HA55
SECONDARY SWITCH
N R
BATTERY POWER
POSITIVE POWER OR
SWITCHABLE POWER
GROUND
KA25
HA51
CONDITIONS:
PRIMARY—MANUAL
SECONDARY—MANUAL
Figure 30-3. Dual Element Windshield Anti-Ice (Sheet 3 of 3)
30-4
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
19
19
ANNUNCIATOR PANEL
ANNUNCIATOR PANEL
HA11
HA15
HEATING
ELEMENT
JUMPERS
W/S
ANTI
ICE
20
HA12
Y Y
HA14
HA1
HA11
HA15
RELAY
5
2
6
3
7
4
1
8
HA2
A
B
C
D
E
A
B
C
D
E
BLK
BLK
WHT
WHT
W/S
ANTI
ICE
20
HA12
Y Y
HA14
HA1
RELAY
SENSE
ELEMENT
5
2
6
3
7
4
1
8
HA2
HA35
W/S
ANTI
ICE
CONT
5
HA13
U U
HA4
AUTO
OFF
HA7
HA8
MANUAL
CONTROLLER
7
4
5
2
8
6
HA3 HA6 HA10
W/S
ANTI
ICE
CONT
BATTERY POWER
POSITIVE POWER OR
SWITCHABLE POWER
GROUND
5
HA13
3
GND
BLOCK
N R
A
B
C
D
E
BLK
BLK
WHT
WHT
SENSE
ELEMENT
U U
HA4
AUTO
OFF
HA5
HA7
HA8
MANUAL
HA3 HA6 HA10
LEGEND
BATTERY POWER
GROUND
SIGNAL OR SENSE
CONTROLLER
HA9
1
A
B
C
D
E
HA35
LEGEND
HA5
HEATING
ELEMENT
JUMPERS
CONDITIONS:
W/S ANTI-ICE
AUTO SELECTED
SENSOR < 359Ω
RELAY ENERGIZED
7
4
5
2
8
6
SIGNAL OR SENSE
HA9
1
3
GND
BLOCK
Figure 30-4. Single Element Windshield Anti-Ice (Sheet 1 of 4)
N R
CONDITIONS:
W/S ANTI-ICE
AUTO SELECTED
SENSOR = 359Ω
RELAY DEENERGIZED
Figure 30-4. Single Element Windshield Anti-Ice (Sheet 2 of 4)
NOTES
30
Revision 0
FOR TRAINING PURPOSES ONLY
30-5
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
19
19
ANNUNCIATOR PANEL
ANNUNCIATOR PANEL
HA11
HA15
HEATING
ELEMENT
JUMPERS
W/S
ANTI
ICE
20
HA12
Y Y
HA14
HA1
HA11
HA15
RELAY
5
2
6
3
7
4
1
8
HA2
A
B
C
D
E
A
B
C
D
E
BLK
BLK
WHT
WHT
W/S
ANTI
ICE
20
HA12
Y Y
HA14
HA1
RELAY
SENSE
ELEMENT
5
2
6
3
7
4
1
8
HA2
LEGEND
5
HA13
U U
HA4
AUTO
OFF
HA5
HA7
HA8
MANUAL
CONTROLLER
7
4
5
2
8
6
W/S
ANTI
ICE
CONT
BATTERY POWER
POSITIVE POWER OR
SWITCHABLE POWER
GROUND
5
HA13
SIGNAL OR SENSE
HA9
1
HA3 HA6 HA10
3
GND
BLOCK
N R
A
B
C
D
E
A
B
C
D
E
BLK
BLK
WHT
WHT
SENSE
ELEMENT
HA35
HA35
W/S
ANTI
ICE
CONT
HEATING
ELEMENT
JUMPERS
U U
HA4
AUTO
OFF
HA5
HA7
CONTROLLER
CONDITIONS:
W/S ANTI-ICE
AUTO SELECTED
SENSOR = 354Ω
RELAY ENERGIZED
HA8
MANUAL
7
4
5
2
HA9
3
GND
BLOCK
Figure 30-4. Single Element Windshield Anti-Ice (Sheet 3 of 4)
LEGEND
BATTERY POWER
POSITIVE POWER OR
SWITCHABLE POWER
GROUND
8
6
1
HA3 HA6 HA10
N R
CONDITIONS:
W/S ANTI-ICE
MANUAL SELECTED
Figure 30-4. Single Element Windshield Anti-Ice (Sheet 4 of 4)
NOTES
30
30-6
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
LH WING
LH WING
DEICE
BOOT
AUTO
HD1
5
C C
OFF
HD2
MANUAL
HD4 11 11
HD3 7 7
HD27
HD28
14 14 HD5
15 15 HD6
HD21 6 6
HD29
20 20
18 18
DEICE
BOOT
AUTO
HD1
5
C C
OFF
HD2
MANUAL
HD4 11 11
HD3 7 7
HD27
HD28
HD21 6 6
HD29
LH WING
14 14 HD5
15 15 HD6
DEICE
BOOT
20 20
18 18
HD16
4 4
HD30
HD20
36
3
HD22
HD17
HD7
ANNUNCIATOR
PANEL
HD16
4 4
HD30
7
HD8
HD9
HD19
1
OFF
HD2
MANUAL
14 14 HD5
15 15 HD6
HD21 6 6
HD29
20 20
18 18
4 4
HD30
8
HD20
JUMPER
TIMER
36
3
HD22
HD17
HD7
ANNUNCIATOR
PANEL
6
9
C C
HD27
HD28
TIMER
TIMER
36
AUTO
HD1
5
HD4 11 11
HD3 7 7
7
9
HD19
1
3
HD22
HD17
HD7
ANNUNCIATOR
PANEL
6
HD8
HD9
HD16
8
HD20
6
7
HD8
HD9
9
HD19
1
JUMPER
JUMPER
HD18
HD18
8
HD18
1
1
2
3
4
5
6
HD10
HD13
2
7
CYCLE
1
2
3
3
4
TIME ACTIVE (SEC)
6
6
6
CYCLE 3 CYCLE 2 CYCLE 1
OUTBD
INBD
TAIL
WING &
WING
STRUT
HD14
LEGEND
BATTERY POWER
HD12
HD15
GROUND
CONDITION:
DE-ICE BOOTS AUTO
SELECTED MOMENTARILY
Figure 30-5. De-Ice Boot System (Sheet 1 of 6)
6
7
1
CYCLE
1
2
3
HD13
HD11
HD11
5
HD10
CYCLE 3 CYCLE 2 CYCLE 1
OUTBD
INBD
TAIL
WING &
WING
STRUT
HD12
HD14
2
TIME ACTIVE (SEC)
6
6
6
HD15
CONDITION:
DE-ICE BOOTS AUTO / CYCLE 1
Figure 30-5. De-Ice Boot System (Sheet 2 of 6)
4
5
6
HD10
HD13
LEGEND
BATTERY POWER
POSITIVE POWER OR
SWITCHABLE POWER
GROUND
3
CYCLE 3 CYCLE 2 CYCLE 1
OUTBD
TAIL
INBD
WING &
WING
STRUT
HD11
HD14
HD12
HD15
7
CYCLE
1
2
3
TIME ACTIVE (SEC)
6
6
6
LEGEND
BATTERY POWER
POSITIVE POWER OR
SWITCHABLE POWER
GROUND
CONDITION:
DE-ICE BOOTS AUTO / CYCLE 2
Figure 30-5. De-Ice Boot System (Sheet 3 of 6)
NOTES
30
Revision 0
FOR TRAINING PURPOSES ONLY
30-7
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
DEICE
BOOT
AUTO
HD1
5
C C
OFF
HD2
HD21 6 6
MANUAL
14 14 HD5
15 15 HD6
HD29
LH WING
LH WING
LH WING
HD27
HD28
HD4 11 11
HD3 7 7
DEICE
BOOT
20 20
18 18
AUTO
HD1
5
C C
OFF
HD2
MANUAL
HD4 11 11
HD3 7 7
HD27
HD28
14 14 HD5
15 15 HD6
HD21 6 6
HD29
20 20
18 18
DEICE
7.5
BOOT
HD16
4 4
HD30
HD20
36
3
HD22
HD17
HD7
ANNUNCIATOR
PANEL
HD16
4 4
HD30
7
9
HD19
1
OFF
HD2
MANUAL
14 14 HD5
15 15 HD6
HD21 6 6
HD29
20 20
18 18
4 4
HD30
TIMER
8
HD20
36
3
HD22
HD17
HD7
ANNUNCIATOR
PANEL
6
HD8
HD9
C C
HD27
HD26
TIMER
TIMER
36
AUTO
HD1
HD4 11 11
HD3 7 7
7
9
HD19
1
8
HD20
1
2
3
4
5
6
HD10
HD13
2
3
4
CYCLE
1
2
3
CYCLE 3 CYCLE 2 CYCLE 1
INBD
TAIL
OUTBD
WING
WING &
STRUT
HD12
HD14
HD15
6
HD10
TIME ACTIVE (SEC)
6
6
6
HD13
HD11
HD11
5
7
LEGEND
BATTERY POWER
POSITIVE POWER OR
SWITCHABLE POWER
GROUND
CONDITION:
DE-ICE BOOTS AUTO / CYCLE 3
Figure 30-5. De-Ice Boot System (Sheet 4 of 6)
CYCLE 3 CYCLE 2 CYCLE 1
INBD
TAIL
OUTBD
WING
WING &
STRUT
HD12
HD14
HD8
HD9
9
HD19
1
HD18
HD18
1
1
7
CYCLE
1
2
3
2
CONDITION:
DE-ICE BOOTS MANUAL SELECTED
Figure 30-5. De-Ice Boot System (Sheet 5 of 6)
5
6
7
7 7
HD34
1 1 HD44
8 8
HD10
CYCLE 3 CYCLE 2 CYCLE 1
OUTBD
TAIL
INBD
WING &
WING
STRUT
HD50
HD49
4 4
HD48
FIREWALL
HD35
HD36
HD11
HD14
HD12
HD15
HD51
3 3
2 2 HD45
HD47
3 3 HD46
LEGEND
HD15
4
CYCLE TIME ACTIVE (SEC)
1
6
6
2
3
6
8
9 9
TIME ACTIVE (SEC)
6
6
6
BATTERY POWER
POSITIVE POWER OR
SWITCHABLE POWER
GROUND
3
7
1 1
2 2
JUMPER
HD18
6
HD39
HD40
JUMPER
JUMPER
3
HD22
HD17
HD7
ANNUNCIATOR
PANEL
6
HD8
HD9
HD16
LH WING
CYCLE 2
CARGO POD
& LDG GEAR
FAIRINGS
LEGEND
BATTERY POWER
POSITIVE POWER OR
SWITCHABLE POWER
GROUND
CONDITION:
DE-ICE BOOTS WITH CARGO POD AND
LANDING GEAR FAIRING BOOTS
Figure 30-5. De-Ice Boot System (Sheet 6 of 6)
NOTES
30
30-8
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
JC011
PC011
L CB PNL
W/S ANTI-ICE
28VDC
A
BACKUP ANTI-ICE
28VDC
C
PRIMARY ANTI-ICE
28 VDC
B
PI003
L SW PNL
TKS BELLY
FEEDTHROUGH
JI003
ELEFUS
GC001
20
21
22
HH
N
JD002
ELEFUS
SI024
6
BACKUP
ON
B
A
BKP PUMP GND
BKP PUMP PWR
J
V
U
T
W/S POWER
BKP LOW PRESS CMN
LOW PRESS CMN
MAX FLOW CMN
16
S
MAX FLOW ACTIVATE
15
R
W/S ACTIVATE
14
P
W/S ACTIVATE CMN
11
23
5
4
3
19
2
OFF
JD001
ELEFUS
18
1
17
SI023
MAX FLOW
6
AIRFRAME
(MOM)
5
4
3
2
WINDSHIELD
(MOM)
1
SI022
PRIMARY
HIGH
6
5
NORM
4
3
OFF
2
OFF
C
1
L
HIGH POWER
10
K
NORM TIMER POWER
12
M
MAX FLOW POWER
13
N
NORM PUMP POWER
*A
Z
Y
LOW PRESS 1 CMN
LOW PRESS 2 CMN
LOW PRESS ACTIVE
F
GROUND
B
A
W
C
LOW PRESS ANNUN
HIGH PRESS ANNUN
LOW FLUID ANNUN
HIGH MODE ANNUN
D
NORM MODE ANNUN
G
SYSTEM ON
X
ANNUN TEST GND
E
H
*B
LVL SENDR SIGNAL
LVL SENDR POWER
LVL SENDR GND
(VEND)
1
(VEND)
(VEND)
R LO PRESS SW
2
(VEND)
C
(VEND)
1
(VEND)
1
2
(VEND)
L LO PRESS SW
2
(VEND)
3
NC
NC
PT003
TAILCONE
R
UI005
GEA71
PI002
(P702)
A/I LOW PRESS
A/I HIGH PRESS
A/I FLUID LOW
A/I HIGH
A/I NORMAL
LEGEND
BATTERY POWER
POSITIVE POWER OR SWITCHABLE POWER
GC001
77
67
70
69
68
GROUND
SECONDARY POWER
SIGNAL OR SENSE
CONDITION:
SYSTEM OFF
UI005
GEA71
PI001
(P701)
A/I QTY SIGNAL
SENDER PWR (12V)
SENDER PWR GND
A/I QTY LO
22
16
13
23
(ORN)
(WHT)
(BLU)
30
Figure 30-6. TKS Anti-Ice System with G1000
Revision 0
FOR TRAINING PURPOSES ONLY
30-9
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
TIMER
PROP
ANTI-ICE
30
CONDITION:
BATTERY ON
AUTO
OFF
MANUAL
HA27
5
HA26
HA26
S S
HA40
B
HA22
HA34
OIL
PRESSURE
SWITCH
NO
C
HA41
3
2
1
NC
POSITIVE POWER OR SWITCHABLE POWER
CONTROL
SWITCH
HA30
PROP
ANTI-ICE
CONTROL
LEGEND
A
HA37
HA36
F
C
3
2
1
BRUSHES
TRANSORB
AMMETER
HA42
BOOTS
HA38
HA30
HA24
ED4
HH
Figure 30-7. Legacy Series Propeller Anti-Ice System (Sheet 1 of 4)
TIMER
PROP
ANTI-ICE
30
A
HA37
HA36
POSITIVE POWER OR SWITCHABLE POWER
GROUND
HA27
5
HA26
HA26
S S
HA40
B
HA22
HA34
OIL
PRESSURE
SWITCH
NO
C
30
NC
BATTERY POWER
AUTO
OFF
MANUAL
HA30
PROP
ANTI-ICE
CONTROL
LEGEND
CONTROL
SWITCH
HA41
3
2
1
3
2
1
F
C
CONDITION:
BATTERY ON
BOOTS HEATING 90 SECONDS
BRUSHES
TRANSORB
AMMETER
HA42
HA30
BOOTS
HA38
HA24
ED4
HH
Figure 30-7.
30-10
Legacy Series Propeller Anti-Ice System (Sheet 2 of 4)
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
TIMER
PROP
ANTI-ICE
30
HA37
HA36
POSITIVE POWER OR SWITCHABLE POWER
GROUND
HA27
5
HA26
HA26
S S
HA40
OIL
PRESSURE
SWITCH
C
HA41
3
2
1
NC
CONDITION:
BATTERY ON / AUTO SELECTED
BOOTS COOLING 90 SECONDS
B
HA22
HA34
NO
BATTERY POWER
AUTO
OFF
MANUAL
HA30
PROP
ANTI-ICE
CONTROL
LEGEND
A
CONTROL
SWITCH
F
C
3
2
1
BRUSHES
TRANSORB
AMMETER
HA42
HA30
BOOTS
HA38
HA24
ED4
HH
Figure 30-7. Legacy Series Propeller Anti-Ice System (Sheet 3 of 4)
TIMER
PROP
ANTI-ICE
30
A
HA37
HA36
POSITIVE POWER OR SWITCHABLE POWER
GROUND
HA27
5
HA26
HA26
S S
HA40
B
HA22
HA34
OIL
PRESSURE
SWITCH
NO
C
NC
BATTERY POWER
AUTO
OFF
MANUAL
HA30
PROP
ANTI-ICE
CONTROL
LEGEND
CONTROL
SWITCH
HA41
3
2
1
3
2
1
F
C
CONDITION:
BATTERY ON / MANUAL SELECTED
BOOTS HEATING CONTINUOUSLY
BRUSHES
TRANSORB
AMMETER
HA42
HA30
BOOTS
HA38
HA24
30
ED4
HH
Figure 30-7.
Revision 0
Legacy Series Propeller Anti-Ice System (Sheet 4 of 4)
FOR TRAINING PURPOSES ONLY
30-11
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
PROP ANTI-ICE CONT
28 VDC
(20)
5
PC057
PROP ANTI-ICE
28 VDC
(12)
30
LEGEND
UC011
TIMER
POSITIVE POWER OR SWITCHABLE POWER
GROUND
PROP POWER IN
A
CONDITIONS:
ENGINE RUNNING
SYSTEM OFF
PI023
JI023
L SWITCH PNL DISC
(12)
(12)
2
1
3
(12)
(12)
PI003
JI003
L SWITCH PNL DISC
(20)
6
(20)
3
SI032
PROP DEICE
5
AUTO
OFF
(12)
2
6
4
3
1
(20)
PROP HEAT POWER
PROP HEAT POWER ON
4
10
TIMER POWER
C
PROP POWER OUT
F
GND
GC001
LH FIREWALL
4
WH1
WH2
RC005
10.0K OHMS
PI505
P604
B
(12)
5
WH1
WH2
RC006
10.0K OHMS
MANUAL (MOM)
UI006
#1 GIA63W
(20)
ELEFUS
ENGINE
(20)
(20)
AA
3
1
2
NO (VEND)
C (VEND)
NC (VEND)
37
36
12
AN005
(12)
(VEND)
PROP HEAT POWER
PROP HEAT POWER ON
PI504
P604
4
10
30
AN004
(12)
I
G
1 2
RN002
VARISTOR
PI002
(1P702)
PROP HEAT CURRENT HI
50
PROP HEAT CURRENT LO
51
PI506
P605
PROP HEAT AUTO POWER
(VEND)
UN026
BRUSH BLOCK ASSY
38
UI005
GEA71
ENGINE/AIRFRAME
UI007
#2 GIA63W
40 PSI
JI005
PI005
AVN/ELE DISC
PI507
P605
PROP HEAT AUTO POWER
UN025
OIL PRESSURE
SWITCH
JN027
PN027
OIL PRESS SWITCH DISC
4
RZ006
PST
1
PST
(12)
(12)
GN009
REFER TO 91-20-02
12
Figure 30-8. G1000 Prop Anti-Ice System (Sheet 1 of 4)
30-12
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
30
Revision 0
FOR TRAINING PURPOSES ONLY
30-13
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
PROP ANTI-ICE CONT
28 VDC
(20)
5
PC057
PROP ANTI-ICE
28 VDC
(12)
30
LEGEND
UC011
TIMER
BATTERY POWER
GROUND
PROP POWER IN
A
SIGNAL OR SENSE
PI023
JI023
L SWITCH PNL DISC
(12)
(12)
2
1
3
CONDITIONS:
ENGINE RUNNING IN AUTO 90 SECONDS ON
(12)
(12)
PI003
JI003
L SWITCH PNL DISC
(20)
6
(20)
3
SI032
PROP DEICE
5
AUTO
OFF
(12)
2
6
4
3
1
(20)
PROP HEAT POWER
PROP HEAT POWER ON
4
10
TIMER POWER
C
PROP POWER OUT
F
GND
GC001
LH FIREWALL
4
WH1
WH2
RC005
10.0K OHMS
PI505
P604
B
(12)
5
WH1
WH2
RC006
10.0K OHMS
MANUAL (MOM)
UI006
#1 GIA63W
(20)
ELEFUS
ENGINE
(20)
(20)
AA
3
1
2
NO (VEND)
C (VEND)
NC (VEND)
37
36
12
AN005
(12)
(VEND)
PROP HEAT POWER
PROP HEAT POWER ON
PI504
P604
4
10
30
AN004
(12)
I
G
1 2
RN002
VARISTOR
PI002
(1P702)
PROP HEAT CURRENT HI
50
PROP HEAT CURRENT LO
51
PI506
P605
PROP HEAT AUTO POWER
(VEND)
UN026
BRUSH BLOCK ASSY
38
UI005
GEA71
ENGINE/AIRFRAME
UI007
#2 GIA63W
40 PSI
JI005
PI005
AVN/ELE DISC
PI507
P605
PROP HEAT AUTO POWER
UN025
OIL PRESSURE
SWITCH
JN027
PN027
OIL PRESS SWITCH DISC
4
RZ006
PST
1
PST
(12)
(12)
GN009
REFER TO 91-20-02
12
Figure 30-8. G1000 Prop Anti-Ice System (Sheet 2 of 4)
30-14
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
30
Revision 0
FOR TRAINING PURPOSES ONLY
30-15
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
PROP ANTI-ICE CONT
28 VDC
(20)
30
PC057
PROP ANTI-ICE
28 VDC
(12)
5
LEGEND
UC011
TIMER
BATTERY POWER
POSITIVE POWER OR SWITCHABLE POWER
PROP POWER IN
A
GROUND
PI023
JI023
L SWITCH PNL DISC
(12)
(12)
2
1
3
CONDITIONS:
ENGINE RUNNING IN AUTO 90 SECONDS OFF
(12)
(12)
PI003
JI003
L SWITCH PNL DISC
(20)
6
(20)
3
SI032
PROP DEICE
5
AUTO
OFF
(12)
2
6
4
3
1
(20)
PROP HEAT POWER
PROP HEAT POWER ON
4
10
TIMER POWER
(12)
C
PROP POWER OUT
F
GND
GC001
LH FIREWALL
4
WH1
WH2
RC005
10.0K OHMS
PI505
P604
B
5
WH1
WH2
RC006
10.0K OHMS
MANUAL (MOM)
UI006
#1 GIA63W
(20)
ELEFUS
ENGINE
(20)
(20)
AA
3
1
2
NO (VEND)
C (VEND)
NC (VEND)
37
36
12
AN005
(12)
(VEND)
PROP HEAT POWER
PROP HEAT POWER ON
PI504
P604
4
10
30
AN004
(12)
I
G
1 2
RN002
VARISTOR
PI002
(1P702)
PROP HEAT CURRENT HI
50
PROP HEAT CURRENT LO
51
PI506
P605
PROP HEAT AUTO POWER
(VEND)
UN026
BRUSH BLOCK ASSY
38
UI005
GEA71
ENGINE/AIRFRAME
UI007
#2 GIA63W
40 PSI
JI005
PI005
AVN/ELE DISC
PI507
P605
PROP HEAT AUTO POWER
UN025
OIL PRESSURE
SWITCH
JN027
PN027
OIL PRESS SWITCH DISC
4
RZ006
PST
1
PST
(12)
(12)
GN009
REFER TO 91-20-02
12
Figure 30-8. G1000 Prop Anti-Ice System (Sheet 3 of 4)
30-16
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
30
Revision 0
FOR TRAINING PURPOSES ONLY
30-17
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
PROP ANTI-ICE CONT
28 VDC
(20)
5
PC057
PROP ANTI-ICE
28 VDC
(12)
30
LEGEND
UC011
TIMER
BATTERY POWER
POSITIVE POWER OR SWITCHABLE POWER
PROP POWER IN
A
GROUND
SIGNAL OR SENSE
PI023
JI023
L SWITCH PNL DISC
(12)
(12)
2
1
3
(12)
CONDITIONS:
ENGINE OFF
SWITCH IN MANUAL
(12)
PI003
JI003
L SWITCH PNL DISC
(20)
6
(20)
3
SI032
PROP DEICE
5
AUTO
OFF
(12)
2
6
4
3
1
(20)
PROP HEAT POWER
PROP HEAT POWER ON
4
10
TIMER POWER
C
PROP POWER OUT
F
GND
GC001
LH FIREWALL
4
WH1
WH2
RC005
10.0K OHMS
PI505
P604
B
(12)
5
WH1
WH2
RC006
10.0K OHMS
MANUAL (MOM)
UI006
#1 GIA63W
(20)
ELEFUS
ENGINE
(20)
(20)
AA
3
1
2
NO (VEND)
C (VEND)
NC (VEND)
37
36
12
AN005
(12)
(VEND)
PROP HEAT POWER
PROP HEAT POWER ON
PI504
P604
4
10
30
AN004
(12)
I
G
1 2
RN002
VARISTOR
PI002
(1P702)
PROP HEAT CURRENT HI
50
PROP HEAT CURRENT LO
51
PI506
P605
PROP HEAT AUTO POWER
(VEND)
UN026
BRUSH BLOCK ASSY
38
UI005
GEA71
ENGINE/AIRFRAME
UI007
#2 GIA63W
40 PSI
JI005
PI005
AVN/ELE DISC
PI507
P605
PROP HEAT AUTO POWER
UN025
OIL PRESSURE
SWITCH
JN027
PN027
OIL PRESS SWITCH DISC
4
RZ006
PST
1
PST
(12)
(12)
GN009
REFER TO 91-20-02
12
Figure 30-8. G1000 Prop Anti-Ice System (Sheet 4 of 4)
30-18
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
30
Revision 0
FOR TRAINING PURPOSES ONLY
30-19
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
30
30-20
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
CHAPTER 31
INDICATING AND RECORDING
INTRODUCTION
This chapter helps to familiarize the technician with the indicating and recording systems in the cockpit. It also assists in locating
specific components.
GENERAL
The instrument and switch panels section provides a description of
the instrument panel and switch panels.
The Garmin G1000 system section gives a description of the G1000
system and the different subsystems that interface with the computer
to supply flight instrumentation, position, navigation, communication,
and identification data to the flight crew.
Revision 0
FOR TRAINING PURPOSES ONLY
The central warning system section includes information on how visual
or aural warnings are sent to the flight crew. It includes the engine
indication and crew alerting system (EICAS) system.
31
31-1
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
ENGINE
FIRE
OIL PRESS
LOW
GENERATOR
OFF
EMERGENCY
POWER LEVER
AUX FUEL
PUMP ON
FUEL PRESS
LOW
VOLTAGE
LOW
VACUUM
LOW
RESERVOIR
FUEL LOW
LEFT
FUEL LOW
RIGHT
FUEL LOW
STBY ELEC
PWR ON
BATTERY
OVERHEAT
BATTERY
HOT
CHIP
DETECTOR
STBY ELEC
PWR INOP
WINDSHIELD
ANTI-ICE
DE-ICE
PRESSURE
STARTER
ENERGIZED
IGNITION
ON
DOOR
WARNING
STARTER
ENERGIZED
IGNITION
ON
FUEL SELECT
OFF
208 KING ANNUNCIATOR PANEL
ENGINE
FIRE
OIL PRESS
LOW
GENERATOR
OFF
EMERGENCY
POWER LEVER
AUX FUEL
PUMP ON
FUEL PRESS
LOW
VOLTAGE
LOW
VACUUM
LOW
RESERVOIR
FUEL LOW
LEFT
FUEL LOW
RIGHT
FUEL LOW
STBY ELEC
PWR ON
SPARE
SPARE
CHIP
DETECTOR
STBY ELEC
PWR INOP
DOOR
WARNING
FUEL SELECT
OFF
WINDSHIELD
ANTI-ICE
DE-ICE
PRESSURE
208 G530 ANNUNCIATOR PANEL
31
Figure 31-1. Annunciator Panels
31-2
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
Table 31-1. NON-G1000 ANNUNCIATORS
ANNUNCIATOR
NOTES
DESCRIPTION
An excessive temperature condition and/or possible fire has occured in the
engine compartment.
Indicates engine oil pressure is less than 38 psi.
The generator is not connected to the power distribution bus.
The emergency power lever is advanced out of the NORMAL position.
Electrical system bus voltage is below 24.5 volts, and power is being supplied from
the battery.
The vacuum system suction is less than approximately 3.0 in. Hg.
The fuel level in the reservoir tank is approximately one-half or less.
One or both fuel tank selectors are off, the fuel selector warning circuit breaker is
not set or the start control circuit breaker is not set.
One or both upper rear doors are not properly secured.
The auxiliary fuel pump is operating.
Fuel pressure in the fuel manifold assembly is below 4.75 psi.
The starter-generator is operating in the starter mdoe.
Fuel quantity in the left fuel tank is 25 gallons or less.
Fuel quantity in the right fuel tank is 25 gallons or less.
31
Standby alternator is supplying electrical power to the bus.
Revision 0
FOR TRAINING PURPOSES ONLY
31-3
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
Table 31-1. NON-G1000 ANNUNCIATORS (CONTINUED)
ANNUNCIATOR
NOTES
DESCRIPTION
*The left and right Chip Detector annunciator bulbs illuminate independent of one another.
The left side will illuminate indicating that metal chips have been detected in the accessory
gearbox case of the engine. The right side will illuminate indicating that metal chips have
been detected in the reduction gearbox case of the engine.
Electrical power is not available from the standby alternator.
Electrical power is being supplied to the engine ignition system.
Electrical power is being suppled to the windshield anti-ice power relay.
(not available on TKS equipped aircraft)
Pressure in the deice boot system has reached approximately 15 psig.
(not available on TKS equipped aircraft)
BATTERY
OVERHEAT
BETA
GENERATOR
OVERHEAT
BATTERY
HOT
STDBY ALT
OVRHT
ENGINE
Indicates that the temperature of the cooling air being exhausted from the startergenerator exceeds 300°F. (not required for US certification.)
The electrolyte temperature in the NiCad battery is at least 140°F. (included only
with NiCad equipped aircraft.)
The 75-amp alternator cooling air is at least 300°F. (not required for US
certification.)
ETM
BELOW
ICING
MIN SPD
The annunciator illuminates for aircraft equipped with boots when the prop heat
switch is in the AUTO position and the airspeed has been reduced to less than 110
KIAS. For TKS equipped aircraft, the annunciator illuminates when the P/S
HEAT/LOW A/S AWARE switch is in the ON position and the airspeed has been
reduced to less than 97.5 +/- 2 knots.
CAUT WARN
31-4
Indicates when the propeller blade angle has been reduced into the beta range.
(not required for US certification.)
Engine Trend Monitor has two annunciators. The white annunciator illuminates if an
engine limitation has been exceeded. The amber annunciator illuminates if the
event exceeds Pratt & Whitney time frames.
(not available on TKS equipped aircraft.)
ANTI-ICE ON
31
The electrolyte temperature in the NiCad battery is at least 160°F.
(included only with NiCad battery-equipped aircraft.)
The upper element ANTI-ICE ON illuminates when the primary switch is in either
NORM or HIGH. The amber CAUT element illuminates if there is high pressure in
the system or due to low fluid quantity. The red WARN element illuminates if a low
pressure condition exists. (TKS equipped aircraft only)
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
NO. 1 GIA 63W
GDC 74A
AIR DATA
COMPUTER
ALTITUDE:
GRS 77 AHRS
HEADING:
GRS 77 OR GMU 44
NO. 1 GIA 63W
NO. 2 GIA 63W
NO. 2 GIA 63W
GDC 74A
AIR DATA
COMPUTER
NO.1 AND 2 GIA 63W
OR GEA 71 OR
EQUIVALENT
ENGINE/AIRFRAME
SENSORS
GDC 74A
AIR DATA
COMPUTER
GIA 63W
NO. 1 AND 2
GDC 74A
AIR DATA
COMPUTER
GIA 63W NO. 1 AND 2
GTX 33
TRANSPONDER
OR GIA 63
NO.1 AND 2
31
Figure 31-2. G1000 Invalid Display Fields
Revision 0
FOR TRAINING PURPOSES ONLY
31-5
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
Table 31-2. G1000 CAS MESSAGES
A-ICE PRESS LOW
FUEL SELECT OFF
DESCRIPTION Anti-ice system pressure is low.
DESCRIPTION
OPTIONAL
AUDIO ALERT
Yes
Repeating Chime
OPTIONAL
AUDIO ALERT
OIL PRESS LOW
One or both fuel tank selectors are off.
No
Repeating Chime
DESCRIPTION Engine oil pressure is low.
OPTIONAL
No
AUDIO ALERT Repeating Chime
BATTERY OVHT
GENERATOR OVHT
VOLTAGE LOW
DESCRIPTION Battery temperature is critically high.
DESCRIPTION Generator temperature is critically
DESCRIPTION Bus voltage is low.
high.
OPTIONAL
AUDIO ALERT
Yes
Repeating Chime
OPTIONAL
AUDIO ALERT
Yes
Repeating Chime
BETA
ENGINE FIRE
DESCRIPTION Propeller is operating in beta mode.
DESCRIPTION Excessive temperature or fire in
OPTIONAL
AUDIO ALERT
No
Repeating Chime
VOLTAGE HIGH
DESCRIPTION
Bus voltage is high.
engine compartment.
OPTIONAL
Yes
Repeating Chime
OPTIONAL
No
AUDIO ALERT Repeating Chime
EMERG PWR LVR
RSVR FUEL LOW
DESCRIPTION Emergency power lever is not
DESCRIPTION Fuel starvation imminent.
OPTIONAL
No
AUDIO ALERT Repeating Chime
normal.
OPTIONAL
No
AUDIO ALERT Repeating Chime
OPTIONAL
No
AUDIO ALERT Repeating Chime
31
31-6
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
Table 31-2. G1000 CAS MESSAGES (CONTINUED)
A-ICE FLUID LO
BATTERY HOT
DESCRIPTION Anti-ice system fluid level is low.
DESCRIPTION
OPTIONAL
AUDIO ALERT
Yes
Single Chime
OPTIONAL
AUDIO ALERT
FUEL BOOST ON
DESCRIPTION Auxiliary fuel pump is operating.
Battery temperature is high.
OPTIONAL
Yes
AUDIO ALERT
Single Chime
No
Single Chime
A-ICE PRESS HI
CHIP DETECT
FUEL PRESS LOW
DESCRIPTION Anti-ice system pressure is high.
DESCRIPTION Metal chips detected in oil.
DESCRIPTION Fuel pressure is low.
OPTIONAL
AUDIO ALERT
Yes
Single Chime
OPTIONAL
AUDIO ALERT
No
OPTIONAL
Single Chime
No
AUDIO ALERT Single Chime
ALTNR AMPS
DOOR UNLATCHED
GENERATOR AMPS
DESCRIPTION Check alternator current.
DESCRIPTION Upper cargo/aft passenger door not
DESCRIPTION
Check generator current.
latched.
OPTIONAL
AUDIO ALERT
No
Single Chime
OPTIONAL
AUDIO ALERT
DESCRIPTION Standby alternator temperature is
AUDIO ALERT
No
Single Chime
DESCRIPTION Engine Trend Monitor has detected
an exceedance.
critically high.
OPTIONAL
Single Chime
ETM EXCEED
ALTNR OVHT
AUDIO ALERT
OPTIONAL
No
Yes
Single Chime
OPTIONAL
AUDIO ALERT
No
Single Chime
31
Revision 0
FOR TRAINING PURPOSES ONLY
31-7
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
Table 31-2. G1000 CAS MESSAGES (CONTINUED)
GENERATOR OFF
L P/S HEAT
DESCRIPTION Generator is not connected to the
DESCRIPTION
aircraft bus.
OPTIONAL
AUDIO ALERT
No
Single Chime
OPTIONAL
AUDIO ALERT
STALL HEAT
Left pitot/static heater is inoperative.
No
Single Chime
DESCRIPTION Stall vane heater is inoperative.
OPTIONAL
AUDIO ALERT
No
Single Chime
L-R FUEL LOW
PROP DE-ICE
STARTER ON
DESCRIPTION Both fuel tanks are low.
DESCRIPTION Propeller heater is inoperative.
DESCRIPTION Starter-generator is in starter mode.
OPTIONAL
AUDIO ALERT
No
Single Chime
L-R P/S HEAT
DESCRIPTION Both pitot/static heaters are
inoperative.
OPTIONAL
AUDIO ALERT
No
Single Chime
OPTIONAL
AUDIO ALERT
Yes
Single Chime
DESCRIPTION Right fuel tank is low.
DESCRIPTION
OPTIONAL
AUDIO ALERT
No
Single Chime
DESCRIPTION Left fuel tank is low.
DESCRIPTION Right pitot/static heater is in-
No
Single Chime
AUDIO ALERT Single Chime
STBY PWR INOP
R P/S HEAT
OPTIONAL
No
R FUEL LOW
L FUEL LOW
AUDIO ALERT
OPTIONAL
OPTIONAL
AUDIO ALERT
Standby alternator is inoperative.
No
Single Chime
operative.
OPTIONAL
AUDIO ALERT
No
Single Chime
31
31-8
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
Table 31-2. G1000 CAS MESSAGES (CONTINUED)
A-ICE HIGH
ETM FAULT
DESCRIPTION Anti-ice system is operating in high
DESCRIPTION
mode.
OPTIONAL
AUDIO ALERT
Yes
None
A-ICE NORM
DESCRIPTION Anti-ice system is operating in normal
mode.
OPTIONAL
AUDIO ALERT
Yes
None
ETM CAPTURE
DESCRIPTION Engine Trend Monitor is logging trend
data.
OPTIONAL
AUDIO ALERT
No
None
ETM EXCEED
DESCRIPTION Engine Trend Monitor has detected
OPTIONAL
AUDIO ALERT
PFD2 FAN FAIL
Engine Trend Monitor is experiencing
a problem.
No
None
DESCRIPTION PFD2 cooling fan has failed.
OPTIONAL
AUDIO ALERT
No
None
IGNITION ON
PREV EXCEED
DESCRIPTION Engine ignition is active.
DESCRIPTION Engine Trend Monitor shows a pre-
OPTIONAL
AUDIO ALERT
No
None
vious exceedance.
OPTIONAL
AUDIO ALERT None
MFD FAN FAIL
SPD NOT AVAIL
DESCRIPTION MFD cooling fan has failed.
DESCRIPTION
OPTIONAL
AUDIO ALERT
No
None
No
OPTIONAL
AUDIO ALERT
PFD1 FAN FAIL
STBY PWR ON
DESCRIPTION PFD1 cooling fan has failed.
DESCRIPTION
“SPD” key pressed on Autopilot
Mode Control Panel.
No
None
Standby alternator is on.
an event.
OPTIONAL
AUDIO ALERT
No
None
OPTIONAL
AUDIO ALERT
No
None
OPTIONAL
AUDIO ALERT
No
None
31
Revision 0
FOR TRAINING PURPOSES ONLY
31-9
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
31
31-10
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
CHAPTER 32
LANDING GEAR
INTRODUCTION
This chapter presents the landing gear and brake system. General maintenance considerations are included. References for this chapter
and further specific information are in Chapter 32 Landing Gear, Chapter 5 Time Limits/Maintenance Checks, and Chapter 12 Servicing
of the Manufacturer’s Maintenance Manual.
GENERAL
The Cessna Caravan I employs a fixed, tricycle landing gear assembly.
The steerable nose gear is supported with a tubular spring drag link.
Within the trunnion is an oil snubber assembly that dampens stresses
to the gear caused by landing and taxiing. The main gear is a rugged
three-piece tubular spring design.
Revision 0
FOR TRAINING PURPOSES ONLY
A tubular spring steel main gear spring provides main gear shock
absorption. The spring has a center main gear tube that connects the
two outer main gear legs at the gear attach trunnions.
The main gear has hydraulically actuated disc brakes.
32-1
32
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
32
BRAKE HYDRAULIC LINE
TRUNNION
MAIN GEAR SPRING
WHEEL ALIGNMENT SHIM
AXLE
BRAKE CALIPER
ANCHOR PLATE
Figure 32-1. Main Landing Gear
32-2
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
32
NOSE GEAR SPRING
SUPPORT ASSEMBLY
NOSE GEAR
ASSEMBLY
NOSE GEAR
SPRING FORK
ASSEMBLY
Figure 32-2. Drag Link Spring
Revision 0
FOR TRAINING PURPOSES ONLY
32-3
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
32
32-4
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
CHAPTER 33
LIGHTS
33
INTRODUCTION
This chapter presents the interior and exterior lighting systems on the Cessna 208 ­series aircraft. General maintenance considerations are included in each section along with a description of components and
operation. References for this chapter and further specific information are in Chapter 33 Lights, Chapter 5 Time Limits/Maintenance Checks, and Chapter 12 Servicing of the Manufacturer’s Maintenance Manual.
GENERAL
The aircraft lighting systems are described in one of the following two
lighting sections in this chapter. The interior lighting section consists of:
• Cockpit lighting
• Overhead console lighting
• Floodlights
• Passenger cargo lights
• All associated controls
The exterior lighting section consists of:
• Landing lights
• Taxi and recognition lights
Revision 0
• Navigation lights
• 5-amp INST LIGHT
• Anti-collision lights
• 5-amp WING ICE DET LIGHT
• Courtesy light
• 5-amp SEAT BELT SGN
• Ice detector lights
• 10-amp RIGHT LDG LIGHT
Circuit breakers for the system include the following:
• 15-amp TAXI LIGHT
• 10-amp LEFT LDG LIGHT
• 10-amp NAV LIGHT
• 5-amp STROBE LIGHT
• 5-amp RADIO FLOOD LIGHT
• 10-amp BEACON LIGHT
• 2-amp MAP LIGHT
FOR TRAINING PURPOSES ONLY
33-1
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
33
33-2
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
CHAPTER 34
NAVIGATION
34
INTRODUCTION
This chapter describes the various systems and instruments that allow the crew to navigate the aircraft. These include the pitot-static
system, Garmin G1000 Integrated Avionics System, gyros, compasses, VOR and indicators. Because Federal Aviation Regulations
require malfunctioning instruments be sent to an approved instrument overhaul and repair station or returned to the manufacturer for
servicing, the chapter does not deal with specific instrument repairs
GENERAL
The Garmin G1000 integrated avionics system presents flight
instrumentation, position, navigation, communication, hazard, and
identification information to the pilot through large format displays.
The system includes a weather radar, terrain avoidance and warning
system (TAWS) information, flight information, and traffic advisory
system (TAS).
Revision 0
FOR TRAINING PURPOSES ONLY
The system uses G1000 line replaceable units (LRUs) for major
subsystems and supporting equipment. The system is regulated
and coordinated by central processing computers in the two Garmin
integrated avionics units (GIAs), which contain essential navigation
and communications avionics equipment.
34-1
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
FOR
N
30 60
E 120 150
STEER
359 028 059 090 120 148
N 24 21 S
FOR
S 210 240 W 300 330
STEER
176 207 238 270 302 330
ON A
MAX
RPM TORQUE
1900
1865
1800
1970
1700
1970
1600
1970
ANNUN PANEL
LAMP
NIGHT
FIRE
DETECT
TEST
GENERATOR
OFF
EMERGENCY
POWER LEVER
AUX FUEL
PUMP ON
FUEL PRESS
LOW
VOLTAGE
LOW
VACUUM
LOW
RESERVOIR
FUEL LOW
LEFT
FUEL LOW
RIGHT
FUEL LOW
STBY ELEC
PWR ON
DOOR
WARNING
DAY
BATTERY
OVERHEAT
BATTERY
HOT
CHIP
DETECTOR
STARTER
ENERGIZED
IGNITION
ON
FUEL SELECT
OFF
STBY ELEC
PWR INOP
WINDSHIELD
ANTI-ICE
5
10
TORQUE
0
FT-LB
X100
DE-ICE
PRESSURE
8
15
20
25
12
16
4
20
0 PROP
T.O
RPM X 100
OFF
3456
12
ITT
7
¡C x 100
ST.LIM
1090¡
10
11
40
Ng
%R
20
8
0
9
9
1
3
5
PSI
2
3
1FUEL FLOW
140
110
55
¡C 10
40
100
2
7
OIL
85
80
8
6
120
60
-40
5 6 7
8
8 10
6 FUEL
9
12
14
16
QTY
11
G
4
3
4
2
E
2
1
E
PPHX100 5
0
4
4
3
4
0
2
1
E
0
AL
LONS X 1
BA
SE LBSX100 GAL
D ON
6.7 LBS
5 6 7
8
8 10
6 FUEL
9
12
14
16
QTY
11
G
RESET
1
6
E
N1
OFF
HLD
128.55
USE
STBY
ON
SEAT
BELT
PITOT/STATIC
HEAT
NAV
TO
GS
15
OFF
2
S
FR
ALT
NAV
FPL
D
NRST
2:3 1
BFO
FRQ
CAL
SET
>CLR
AIRSPEED
CRSR
OTH
PULL SCAN
ENT
ADF
FLT
ET
FRQ
FLT
ET
SET
IDT
NAV
PULL
RAD
H
160
80
140
120
1
2
0
0
7
100
0
FEET
1
ALTITUDE
2
29.7
29.8
6
P U LL
FOR
QUICK
ER T
EC
5
4
3
0 0 0 1 9
TST
V
8888
ALT ON R
GND SBY
TST
SBY
GND
L
W 30
24
R
ON
ALT
OFF
PUSH
VFR
2 MIN TURN
D.C. ELEC.
SBY
OFF
RNG
8
ON ALT
OFF
ON
TST
0
80
0
0
100
KT 71 TSO
BRT
2
1
TOTAL HOURS
SBY
VFR
888
FL
IDT
PULL
IDENT
9
60
OFF
KT 79 TSO
COMM
240 40
VOL
RST
1200
SBY
40
KNOTS
200
180
STBY / TIMER
BFO
071
STBY / RAD
PULL
25K
PULL
TEST
ACT
USE
068
USE
KX 165 TSO
USR
KR 87 TSO
ADF
117.90
STBY
NDB
OBS
323
ANT
ADF
PULL
RAD
123.25
NDB
MSG
PULL
IDENT
128.55
W
VOR
¡¡¡¡¡¡¡¡¡¡¡
Alt 1400ft
OBS ---¡
Pass Ok?
STBY / RAD
COMM
USE
NAV
DH
MSG
V
ENG S
0
CCW
1
2
RADAR ALT
X 100 FEET
2 MIN TURN
D.C. ELEC.
10
A
ARM L
T
SET
3,000
FT
PULL
VS
VACUUM
.5
1
0
.5
1
VERTICAL
SPEED
FT/MIN
X 1000
2
3
VENT
PULL ON
2
PUSH
XPDR 1
RNG
VP
60
MAP
TEST
NAV
5
WARNING
XPDR 2
ASSURE THAT SEAT IS LOCKED IN POSITION
PRIOR TO TAXI, TAKEOFF, AND LANDING.
FAILING TO PROPERLY LATCH SEAT AND HEED
THE SAFETY INSTRUCTIONS CAN RESULT IN
BOTH INJURY OR DEATH.
TRK
40
TRK
20
3
4
UP
PHONE
WARNING
DN
GAIN
PULL STAB OFF
FD
TEST
DN
ALT
HDG
ALT
HDG
GS
NAV
APR
BC
NAV
APR
BC
KFC 150
FD
TRIM
TEST
ASSURE THAT ALL CONTAMINANTS, INCLUDE
WATER, ARE REMOVED FROM FUEL AND ALL
SYSTEM BEFORE FLIGHT. FAILURE TO AS????
INSTRUCTIONS AND OWNER ADVISORIES ????
TO FLIGHT CAN RESULT IN BODILY INJURY
DEATH.
AP
MIC
AP
ENG
CABIN
YAW
DAMP
LIGHTS BRT
MIC
34.5 nm
Baro:30.00"
RMI 130¡
ANNUN ON
OFF ON
068
USE
PULL
TEST
UP
NO
SMOKE
KMA 24 TSD
T
SLAVE
GPS
WAYPOINT
20
15
PHONE
117.90
PULL
25K
S
2
123.25
KX 165 TSO
N2
24
21
OB
RIGHT
LDG
BCN
MIC
PHONE
CW
ARM ACTV
R
COM 1 COM 2
TEL
INT
EXT
OFF
TIL
FREE
L
ADF AUTO
Wx
WxA
GPS APR
NAV
ON
--.- NM' - - - KT - - MIN
NAV
VOLT
STROBE
29.8
3
FT/MIN
X 1000
MKR
APT
12
S
15
12
.5
3
-50
0
VERTICAL
SPEED
DME
3
BATT
1
.5
1 NAV 2
N
NAV
GS
1 COM 2
29.7
E
24 HDG
W
TEL
N
200
LEFT
LDG
SPEAKER
HI
LO
S
E
N
S
33
21
ALT
OVERSPEED
GOVERNOR
PUSH TO TEST
MKR
T
S
T
A
O
M
33
A
D
F
GEN
150
25
LIGHTS
TAXI/
RECOG
ON
VS
30
NAV
A
D
F
30
5
TRIM
DC
8
100
AMPS
15
10
VOLTS 20
4
ENCODING
GA
M
7
33 N
5
0
6
3
CAP
O
OFF
30
50
7
100
GS
0
1005
ALT
GS
6
SUCTION
IN HG
VENT
PULL ON
IN.Hg
REV
A
MP
10
20
1010
mb
2
ALT
NAV
APR
BC
6
15k
20k
25k
30k
10
20
8
AP
HDG
3
3
2
20
10
1
S 21
120
5
4
H
80
140
30
PROP ANTI-ICE
AMPS
MP
160
20
10
FEET
15
5
60
9
E 12
6
240 40
DH
H
7
180
0
100
40
KLN 89B TSO
GPS
MP
QUARTZ
3
4
KNOTS
H
10 20
2
MP
0
200
CLOCK
E
L
T
MAX WT MANEUVER SPEED 148 KIAS
SEE POH FOR OTHER WEIGHTS
AIRSPEED
11 12 1
A
U
T
O
0
AL
LONS X 1
BA
SE LBSX100 GAL
D ON
6.7 LBS
AIR
10
9
8
ON
4
2
E
6
N208FS
TEST
OIL PRESS
LOW
OFF
34
ENGINE
FIRE
NO
STALL
HEAT
ON
DEICE/ANTI-ICE
W/S
WING
LIGHT
PROP
BOOT
PRESS
AUTO
OFF
L FLT PANEL
L FLOOD
LOCK
R FLT PANEL
R FLOOD
INERTIAL SEPARATOR
BYPASS-PULL
NORMAL-PUSH
OFF
LWR PANEL/
PED/OVHD
SW/CKT BKR
MANUAL
ALT STATIC AIR
PULL ON
PARKING
BRAKE
PULL
CABIN HEAT
AIR CONDITIONING
ENG INST
RADIO
COOL
LEFT
AC FANS
AFT
HIGH
RIGHT
TEMP
HOT
BLEED AIR HEAT
ON
MIXING AIR
GND-PULL
FLT-PUSH
AFT CABIN-PULL
FWD CABIN-PUSH
DEFROST-PULL
FWD CABIN-PUSH
OFF
VENTILATE
LOW
OFF
NOTES
Figure 34-1. Avionics Systems (King)
34-2
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
N
FOR
30 60
E 120 150
STEER
359 028 059 090 120 148
N 24 21
FOR
S 210 240 W 300 330
STEER
176 207 238 270 302 330
RESERVOIR
FUEL LOW
SPARE
LEFT
FUEL LOW
RIGHT
FUEL LOW
STBY ELEC
PWR ON
SPARE
CHIP
DETECTOR
STBY ELEC
PWR INOP
IGNITION
ON
20
0
FUEL SELECT
OFF
WINDSHIELD
ANTI-ICE
10
15
5 TORQUE
FT-LB
X 100
DE-ICE
PRESSURE
12
8
16
4
TO
20
0 PROP
25
OFF
12
3456
ITT
7
°C X 100
ST.LIM
1090°
MAX WT MANEUVER SPEED 148 KIAS
SEE POH FOR OTHER WEIGHTS
120
60
Ng
% RPM
0
9
9
10
11
RPM X 100
40
20
8
1
8
PSI
-40
4
5
DISCONNECT AUTOPILOT AT FIRST INDICATION OF ICE
ACCRETION.
AIRSPEED
3
4
5
120
VS
MKR
MUTE
HI
LO
SQ
OFF/
VOL
29.7
SENS
TERR
INHIB
TEST
TERR
COM2
COM3
NAV1
COM1
MIC
COM2
MIC
COM3
MIC
COM
1/2
gs
TERR N/A
TERR
COM1
HDG
YD
29.8
TERR
INHIB
P
ALT
AP
a lt
A YD
R
M
NAV2
DME
FD
PA
CREW
1.300
A
R
M
ALE RT
PULL
PASS
VOL
HDG
NAV
APR
VS
ALT SEL
UP
NEWBERG
D
(H)
KFC 225
17S
18
9
2S6
KUAO
2
15 S
3
6
E
FREE
CW
SLAVE
CCW
ARM ACTV
R
GPS
WAYPOINT
NAV
0
1
RADAR ALT
X 100 FEET
20
15
2 MIN TURN
ELEC
VOLPUSH
ID
VLOC
10
2
N1
OFF
HLD
71K
KICT
240
DIS
–––
O
M
O
M
GS
72K
10 nm –2
overzoom
VLOC
CDI
OBS
0.0
FPL
VNAV
C
C
VOL/ PUSH
SQ
V
COM
121.900
118.200
VLOC
V
VOL/ PUSH
ID
COM
110.30
113.80
VLOC
ENR
PUSH
C/V
VLOC
CDI
19R
VFR
DIS
DIK
14
KICT
GS
2.0nm –2
overzoom
OBS
N
M
–––
N
M
0.0
NAV
MSG
–––
0
STBY
1
2
ANT
ADF
FPL
D
MENU
CLR
ENT
DEFAULT
NAV
K
L
Trk:
GS:
Custom Map
4363
NO
SMOKE
ON
SEAT
BELT
CABIN
MIC
PITOT/STATIC
HEAT
STALL
HEAT
ON
DEICE/ANTI-ICE
W/S
WING
PRIMARY
LIGHT
W/S
PROP
SECONDARY
AUTO
OFF
OFF
BOOT
PRESS
L FLT PANEL
L FLOOD
3
4
KR 87 TSO
332
BFO
FRQ
ADF
FL
LOCK
R FLT PANEL
R FLOOD
FD
ALT
HDG
ALT
HDG
GS
NAV
APR
BC
NAV
APR
BC
13.5 nm
5
6
013
7
TEST
LWR PANEL/
PED/OVHD
SW/CKT BKR
FUNC
CRSR
START
STOP
CLR
8
FLT
ET
SET
OPERATION OF THE ANTI-ICE PANEL
MAY CAUSE COMPASS DEVIATION OF
MORE THAN 10 DEGREES
2605028-2
PARKING
BRAKE
PULL
W
R
VACUUM
29.7
6
5
4
3
29.8
.5
1
0
.5
1
VERTICAL
SPEED
FT/MIN
X 1000
2
3
RST
2
OFF
WX
AIRSPEED DECREASE OF 10 KIAS THAT CANNOT BE
PREVENTED BY INCREASE TO MAX CONTINUOUS POWER.
TRFC
BLEED AIR HEAT
ON
LOW
MIXING AIR
GND-PULL
FLT-PUSH
PHONE
AIRSPEED OF 120 KIAS CANNOT BE MAINTAINED IN
LEVEL FLIGHT.
TERR
MIC
MEA OR MOCA IF APPLICABLE ON CURRENT LEG FALLS
INTO AREA “C” OF ICING SERVICE CEILING CHART
CONTAINED IN SECTION 5 OF THE POH/AFM KNOWN
ICING EQUIPMENT SUPPLIMENT.
2605070–8
RNG
DATA
RNG: 80 n m
TRK:240 GS: 18 KT POS: 0.5SE KICT WICHITA
AP
ENG
VENT
PULL ON
PUSH
AP
TEMP
HOT
2
24
21
RNG
OFF
VENTILATE
2 MIN.
NO PITCH
INFORMATION
1
VOL
OVLY
WARNING
ASSURE THAT SEAT IS LOCKED IN POSITION
PRIOR TO TAXI, TAKEOFF, AND LANDING. FAILURE
TO PROPERLY LATCH SEAT AND HEED ALL
SAFETY INSTRUCTIONS CAN RESULT IN BODILY
INJURY OR DEATH.LLLLLLLLLLLLLLLLLLLLLLLLLL
0705097-1
AUX
WARNING
CABIN HEAT
RIGHT
L
FEET
ADF
6 : 1 1 FLTET
FRQ
ON OFF
AC FANS
AFT
HIGH
PULL
FOR
QUICK
E
RECT
RES
RES
AIR CONDITIONING
LEFT
7
0
ALTITUDE
9
SKYWATCH
COOL
10
20
N
MAP
RADIO
10
20
100
D.C.
ELEC.
MENU
ENT
OFF ON
ENG INST
8
100
CONTINUED FLIGHT IN ICING CONDITIONS IS PROHIBITED
AFTER ENCOUNTERING ONE OR MORE OF THE FOLLOWING:
GPS
INERTIAL SEPARATOR
BYPASS-PULL
NORMAL-PUSH
20
10
RES
VIR
PUSH
CRSR
TRIM
20
10
STBY / TIMER
BFO
PROC
KFC 150
UP
Distance:
OFF
MANUAL
ALT STATIC AIR
PULL ON
FD
DN
LIGHTS BRT
120
PRESSURE ALT
ALT
PHONE
80
140
GTX 330
ALT
RNG
–––––
19L
9
60
OFF
ON
PUSH
CRSR
DPT
N
40
160
343° 135 kt
Info
USE
PWR
TEST
IDENT
ENT
GPS
PROC
KNOTS
240 40
TURN COORDINATOR
CLR
DEFAULT
NAV
K
L
NAV
MSG
Baro:
Pan
200
180
4S9
10,300 ft 29.92”
Out
KC
MENU
GNS 430
N2
4
Alt:
7S9
AIRSPEED
+
ON
OFF
343°
FN
D
--.- NM' - - - KT - - MIN
3
5
O
M
TRK
ENR
COM
Zoom:(Trk Up)
50 nm
RNG
In
–––
110.30
113.80
LOC ICT
KICT
ILS 01R
PUSH
C/V
DH
MSG
RIGHT
LDG
BCN
S
OB
–––
DTK
VLOC
V
V
GPS
N
BY
L
VOL SQ
XTK
K32
COM
126.700
126.700
C
PWR PUSH
34
0
LONS X 1
03S
S48
5S9
27
117.40 UBG
065°FR 15NM
ST
1
NAV
VLOC
AL
L
S E DB S X 1 0 0 /G A L
O N 6. 7 L B S
Wpt Bearing:
W58
7S3
0
DN
ALT
9
18 18
W56
40 400
40
PORTLAND
27 11 KVOO
20
59S201W1
D
PORTLAND
9 AP
KPDX
4S4
(L)---- 114.80 PDX
40
18
KTTD
KHIO
17
40
23
COPILOT
ARM
FT
REV
BATTLE GROUND
KSPB 27
D
40
(H)----116.60 BTG
PDX
F
FT/MIN
X 1000
C
W
BA
5 6 7
8
8 10
6 FUEL
9
12
14
16
QTY.
11
GMX 200
Waypoint:
SQ
PILOT
ICS ISOLATION VOL
OF
.5
3
24
0
LONS X 1
S E DB S X 1 0 0 /G A L
O N 6. 7 L B S
4
2
E
33 N
0
VERTICAL
SPEED
S
.5
21
2
N
12
1
15
GS
AL
L
4
3
2
1
E
TEST
ADF
SPKR
CABIN AUDIO
R
AP
5 6 7
8
8 10
6 FUEL
9
12
14
16
QTY.
11
30
24
GPS APR
NAV
ON
TRIM
PILOT
NAV
VOLT
-50
STROBE
GA
M
33
BATT
W
N
NAV
HDG
21
ALT
200
OVERSPEED
GOVERNOR
PUSH TO TEST
CAP
O
30
A
D
F
GEN
150
LEFT
LDG
5
ALT
GS
12
NAV
25
LIGHTS
TAXI/
RECOG
ON
4
ENCODING
REV
A
DC
8
100
30
6
3
NAV
APR
BC
4
2
E
GMA 340
A O M
AP
HDG
BA
KMMV
A
D
F
15
10
VOLTS 20
7
33
5
0
10
20
30
50
2
IN.Hg
1005
100
GS
0
1
5
7
SUCTION
IN HG
AMPS
FEET
ALT
1010
mb
0
100
6
15k
20k
25k
30k
2
VENT
PULL ON
8
20
10
10
20
80
140
5
4
3
20
10
160
30
PROP ANTI-ICE
AMPS
60
9
E
6
DH
6
7
240 40
H
QUARTZ
180
MP
2
40
3
10 20
CLOCK
KNOTS
PPH X 100
2
1
E
H
MP
0
200
H
MP
10
9
8
ICE DET
P/TEST
11 12 1
0
4
3
4
2605070-6
AIR
ICE DETECTOR
SYSTEM IS
ADVISORY ONLY
2
1FUEL FLOW3
0
3
6
°C 10
40
100
2
7
140
110
55
OIL
85
80
15 S
VACUUM
LOW
STARTER
ENERGIZED
12
FUEL PRESS
LOW
H
VOLTAGE
LOW
DOOR
WARNING
DAY
AUX FUEL
PUMP ON
MP
EMERGENCY
POWER LEVER
G
GENERATOR
OFF
G
N208FS
TEST
OIL PRESS
LOW
OFF
TEST
ENGINE
FIRE
MAX
RPM TORQUE
1900
1865
1800
1970
1700
1970
1600
1970
BELOW
ICING
MIN SPD
ETM
E
ANNUN PANEL
LAMP
NIGHT
FIRE
DETECT
ENGINE
6
120 KIAS MINIMUM IN ICING FLAPS UP EXCEPT 110 KIAS
IF CLIMBING TO EXIT ICING.
2605070-5
NO
3
ON A
AFT CABIN-PULL
FWD CABIN-PUSH
DEFROST-PULL
FWD CABIN-PUSH
ASSURE THAT ALL CONTAMINATES, INCLUDING
WATER, ARE REMOVED FROM FUEL AND FUEL
SYSTEM BEFORE FLIGHT. FAILURE TO ASSURE
CONTAMINATE FREE FUEL AND HEED ALL SAFETY
INSTRUCTIONS AND OWNER ADVISORIES PRIOR
TO FLIGHT CAN RESULT IN BODILY INJURY OR
DEATH.LLLLLLLLLLLLLLLLLLLLLLLLLLLLLLLLLL
0705098-1
OFF
NOTES
Figure 34-2. Avionics Systems (G530)
Revision 0
FOR TRAINING PURPOSES ONLY
34-3
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
30 33 N
HDG
HDG
10100
9800
328°
30
33
N
21
INSET
S
??????
OBS
15
OAT__– 5°c
CDI
GMN
331°
38.0NM
FRAME
324°
73.2NM
334°
10.0NM
50.0NM
FLW
NAV2
XPDR1 4234 ALT R LCL
08:44:27
XPDR
IDENT TMR/REF NRST ALERTS
MKR
MUTE
HI
SENS
DME
NAV1
ADF
NAV2
PAN
D
MENU
PROC
OFF
DFLT MAP
ENG
INTFC
ADC
1
AHRS
1
PFD
1
XPDR
1
ADF
1
5
5
5
5
5
5
2
50
A/P
CONT
ELT
NAV
INTFC
RADIO
ALT
RADAR
R/T
5
5
5
5
5
5
COM
2
NAV
2
MFD
ADC
2
AHRS
2
PFD
2
XPDR
2
5
5
5
5
5
5
PROP RPM
XM–DATA
LINK
STM
SCOPE
HF
RCVR
HF
AMP
5
5
5
5
5
30
700
KHJO
PASS
FMS
V27
V107
96.5
1900
OIL PSI
95
OIL °C
85
KRFL
KSMX
V27
V137
V183
FFLOW PPH
379
BAT AMPS
BUS VOLTS
4
28.5
A–ICE GAL
4.7
V107
V25
V186
V137
V22
V386
XWHP
V107
XBUR
V107
150NM
V197
V23
MAP WPT AUX NRST
TERRAIN AIRWY LO STRMSCP NEXRAD XM LTNG
D
MENU
FPL
PROC
CLR
DFLT MAP
BACK
10
10200
10100
HDG
ENT
OAT__– 5°c
FMS
??????
INSET
37.9NM
EHF
NAV1
SENSOR
PFD
9900
10
33
GPS
80
127.100 COM1
122.450 COM2
CRS
331°
N
ENR
OBS
CDI
PUSH
VOL SQ
0 5 1 0 0
COM
EMERG
2
1
PUSH
1-2
ON
BARO
-900
ARM
PUSH
STD
9700
29.92IN
1
10
ARTEX
ELT
1
9800
328°
328°
30
PUSH CRSR
TEMP °C
30+ 0 –30
100
40
200
180 AIRSPEED
160
140 KNOTS
120 100
8
60
9
2
TEST/RESET
PRESS ON
WAIT 1 SECOND
PRESS ARM
RANGE
–
+
PUSH
PAN
DME
50.0NM
FLW
NAV2
XPDR
XPDR1
IDENT
4234 ALT
TMR/REF
R LCL
NRST
08:44:27
ALERTS
D
MENU
FPL
PROC
CLR
DFLT MAP
ENT
FMS
7
VACUUM
ALTIMETER
6
PUSH CRSR
1
4
5
VENT–PULL ON
HF
FEET
0
1015
1010
80
1
2
3
10
15
5 TORQUE
29.8
29.9
30.0
20
0
FT–LB
X 100
5.000
E R 1
EMER
T.O.
VOL
25
PUSH
PWR
TEST
FUNC
FREQ CHAN
MOD
RX
PHONE
TUNE
ENT
TX
SQL
OPT
MIC
LOCK
332
ADF
INERTIAL SEPARATOR
KR 87 TSO
BYPASS–PULL
NORMAL–PUSH
ADF
BENDIX / KING
CB/PED/
OVHD
LEFT
FLOOD
3:10
USE
FRQ
FLT
ET
SET
RST
AIR CONDITIONING
RIGHT
FLOOD
WARNING
ADF
FLT
ASSURE THAT ALL CONTAMINATES, INCLUDING
WATER, ARE REMOVED FROM FUEL AND FUEL
SYSTEM BEFORE FLIGHT. FAILURE TO ASSURE
CONTAMINATE FREE FUEL AND HEED ALL SAFETY
INSTRUCTIONS AND OWNER ADVISORIES PRIOR
TO FLIGHT CAN RESULT IN BODILY INJURY OR
DEATH.LLLLLLLLLLLLLLLLLLLLLLLLLLLLLLLLLL
0705098-1
STBY/TIMER
BFO
COOL
PARKING
BRAKE
PULL
KVCV
DISPLAY BACKUP
DIMMING
SW/CB PNLS
/ ANNUN
STANDBY
IND
V12
10
10
PAN
KPMD
128.375
121.500
20
PUSH
KWJP
V201
KCMA
KNTD
316
+
KEDW
V27
TOPO
120
331°
310000
100
130
–
KMHV
GMN
V12
KSBA
20
145
PUSH
STD
V23
20
150
RANGE
V25
BRG
140
V459
KVBC
1-2
L
KNID
DIS 38.0NM
EHF
AP YD ALT 10000FT
10
000
10300
160
PUSH
1-2
V165
EHF
FUEL QTY
LBS
R
TRAFFIC
PUSH
BARO
V485
GMN
GPS
115.40 EHF
117.80 FLW
NAV
KPTV
V23
KDLO
KSBP
NAV1 116.90
NAV2 112.50
PUSH
VOL ID
COM
170
0
AVIONICS
PUSH
VOL SQ
TRACK UP
V165
V459
R
16
CONTINUED FLIGHT IN ICING CONDITIONS IS
PROHIBITED AFTER ENCOUNTERING ONE OR
MORE OF THE FOLLOWING:
AIRSPEED OF 120 KIAS CANNOT BE MAINTAINED
IN LEVEL FLIGHT.
AIRSPEED DECREASE OF 10 KIAS THAT CANNOT
BE PREVENTED BY INCREASE TO MAX
CONTINUOUS POWER.
MEA OR MOCA IF APPLICABLE ON CURRENT LEG
FALLS INTO AREA”C” OF ICING SERVICE CEILING
CHART CONTAINED IN SECTION 5 OF THE POH/
AFM KNOWN ICING EQUIPMENT SUPPLEMENT.
10KT
SQ
PRESS
ALT
ADF
2
127.100 COM1
122.450 COM2
128.375
121.500
DIS 38
KVISV459
24CL
V113
100
PLAY
COPLT
ENT
2605070-10
TAS
GS 175
V137
KPRB
900
O
F
F
2 141618
AVN
BUS
2
DME
% RPM
12
180
A/P
SERVOS
V248
20
CREW
PUSH CRSR
NAV
1
°C
ICS ISOLATION
PILOT
331°
MAP - NAVIGATION MAP
600
0
L
PILOT
DTK
C80
ITT
1-2
TAS
PHONE
SPKR
200
TEST SWITCH
FIRE DETECT–UP
FUEL SELECT OFF–DN
TEL
PA
VOL
AVN
BUS
1
AUDIO
COM
1/2
ETE 13:47
EMERG
1650
0
MAN
SQ
FPL
CLR
FT–LB
X100
10
AUX
EHF
KFAT
DME
COM3
+
PUSH
THE SIGHT GAGE ON THE TKS TANK IS THE
ONLY APPROVED MEANS OF ASSURING
ADEQUATE DISPATCH FLUID QTY
COM
1
ALTSTATIC AIR
PULL ON
–
V23.FRAME
700026
MIC
PUSH
STD
RANGE
DTK
DIS
– – –° – – – –NM
N
Ng
1
KLGB / KFAT
VENT–PULL ON
OVERSPEED
GOVERNOR
PUSH TO TEST
BARO
2
115.40 EHF
117.80 FLW
15
PUSH
1-2
-900
116.90
112.50
NAV
PUSH
FLIGHT PLAN
12
BACKUP
ON
NAV 1
NAV 2
TRQ
PUSH
VOL ID
E
OFF
FLUID CONTROL
MAX FLOW
AIRFRAME
N
O
R
M
WINDSHIELD
9700
29.92IN
COM2
COM3
MIC
2
1
COM2
MIC
PUSH DIR
6
24
ENR
E
PRIMARY
HIGH
331°
PUSH
VOL SQ
COM
EMERG
PUSH DIR
3
GPS
CRS
6
ANTI-ICE
37.9NM
EHF
NAV1
SENSOR
PFD
9900
10
328°
CABIN
O
F
F
WINDSHIELD ANTI-ICE MUST BE
OFF FOR TAKEOFF AND LANDING
10200
3
SEAT
BELT
ON
127.100 COM1
122.450 COM2
COM1
EMERGENCY USE ONLY
10
130
W
NO
SMOKE
WING
LIGHT
10
140
120
128.375
121.500
20
3100 00
100
80
MANUAL
STALL
HEAT
ON
10
150
BCN
PUSH SYNC
COM1
MIC
2605076-5
C
R
E
W
PROP
HEAT
AUTO
P/S HEAT /
LOW A/S
AWARE
20
CRS2
SPD
W
NAV
ON
331°
FLC
DN
24
160
20
145
STROBE
BRG
VS
VNV
UP
10
000
10300
170
1-2
OFF
DIS 38.0NM
EHF
AP YD ALT 10000FT
ALT
ALT SEL
YD
21
RIGHT
LDG
PUSH
POWER
OUTLET
ALL
GMN
GPS
115.40 EHF
117.80 FLW
NAV
XFR
AP
S
LEFT
LDG
NAV1 116.90
NAV2 112.50
PUSH
VOL ID
FD
BANK
15
N208FS
LIGHTS
TAXI/
RECOG
ON
NAV
CRS1
BC
12
34
APR
HDG
BELOW
ICING
MIN SPD
WHEN TAKEOFF TORQUE SETTINGS ARE BELOW
1865 FT-LBS, THE AIR CONDITIONER MUST BE
OFF FOR TAKEOFF AND LANDING
2605031-3
MAX WT MANEUVERING SPEED 148 KIAS
SEE POH OTHER WEIGHTS
LEFT
AC FANS
AFT
HIGH
RIGHT
OFF
VOL
TEMP
HOT
BLEED AIR
HEAT
ON
WARNING
ASSURE THAT SEAT IS LOCKED IN POSITION
PRIOR TO TAXI, TAKEOFF, AND LANDING. FAILURE
TO PROPERLY LATCH SEAT AND HEED ALL
SAFETY INSTRUCTIONS CAN RESULT IN BODILY
INJURY OR DEATH.LLLLLLLLLLLLLLLLLLLLLLLLLL
0705097-1
CABIN HEAT
MIXING AIR
AFT CABIN–PULL
GND–PULL
FWD CABIN–PUSH
FLT–PUSH
DEFROST–PULL
FWD CABIN–PUSH
OFF
DAY
VENTILATE
LOW
OFF
NOTES
Figure 34-3. Avionics Systems (G1000)
34-4
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
NAV 1
NAV 2
TRQ
PUSH
VOL ID
116.90
112.50
115.40 EHF
117.80 FLW
15
NAV
FT–LB
X100
10
DTK
331°
GS 175
C80
KHJO
°C
0
Ng
50
12
% RPM
PROP RPM
V248
20
KPRB
900
700
V27
COM
KPTV
V23
96.5
95
OIL °C
85
1-2
BARO
V485
V107
1900
PUSH
KDLO
KSBP
EHF
V165
KRFL
KSMX
V27
PUSH
STD
RANGE
V25
V137
V183
V23
GMN
FFLOW PPH
379
BAT AMPS
BUS VOLTS
4
28.5
A–ICE GAL
4.7
V107
PUSH
PAN
KWJP
KPMD
V201
V107
TOPO
V137
V22
KCMA
KNTD
316
+
KEDW
V12
KSBA
V25
V186
V27
–
KMHV
FUEL QTY
L
LBS
R
O
F
F
L
KNID
V459
KVBC
34
V165
V459
R
V137
V113
100
OIL PSI
TRAFFIC
10KT
PUSH
VOL SQ
TRACK UP
EMERG
24CL
600
1-2
127.100 COM1
122.450 COM2
KVISV459
ITT
PUSH
128.375
121.500
DIS 38
MAP - NAVIGATION MAP
N
1650
0
ETE 13:47
V12
KVCV
V386
XWHP
V107
XBUR
150NM
V197
V23
MAP WPT AUX NRST
TERRAIN AIRWY LO STRMSCP NEXRAD XM LTNG
BACK
D
MENU
FPL
PROC
CLR
ENT
DFLT MAP
FMS
PUSH CRSR
Figure 34-4. G1000 MFD Power-Up Page
Revision 0
FOR TRAINING PURPOSES ONLY
34-5
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
HIGH-SPEED DATA BUS (ETHERNET)
GDL 69A
XM SATELLITE
RADIO RECEIVER
REAL-TIME WEATHER
DIGITAL AUDIO ENTERTAINMENT
34
NO. 1 GIA 63W
INTEGRATED AVIONICS UNIT
SYSTEM INTEGRATION PROCESSORS
I/O PROCESSORS
VHF COM
VHF NAV/LOC
GPS
GLIDE SLOPE
AFCS MODE LOGIC
FLIGHT DIRECTOR CALCULATIONS
SERVO MANAGEMENT
GPS OUTPUT
GDC 74A #1
AIR DATA
COMPUTER
OAT
AIRSPEED
ALTITUDE
VERTICAL SPEED
GWX 68
ONBOARD
RADAR
GDC 74A #2
AIR DATA
COMPUTER
OAT
AIRSPEED
ALTITUDE
VERTICAL SPEED
GRS 77 #1
AHRS
ATTITUDE
RATE OF TURN
SLIP/SLID
GRS 77 #2
AHRS
ATTITUDE
RATE OF TURN
SLIP/SLID
NO. 2 GIA 63W
INTEGRATED AVIONICS UNIT
SYSTEM INTEGRATION PROCESSORS
I/O PROCESSORS
VHF COM
VHF NAV/LOC
GPS
GLIDE SLOPE
AFCS MODE LOGIC
FLIGHT DIRECTOR CALCULATIONS
SERVO MANAGEMENT
GPS OUTPUT
GEA 71
ENGINE/AIRFRAME
UNIT
GTX 33
TRANSPONDER
GMU 44 #1
MAGNETOMETER
HEADING
GSA 81
PITCH TRIM
GMU 44 #2
MAGNETOMETER
HEADING
GSA 81
PITCH
GSA 80
ROLL
GTX 33
TRANSPONDER
GSA 80
YAW
Figure 34-5. Garmin G1000 Integrated Avionics Architecture
34-6
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
HIGH SPEED DATA BUS (ETHERNET)
GDU 1040A
PFD
HIGH SPEED DATA BUS (ETHERNET)
DISPLAY OF FLIGHT
INSTRUMENTATION
DISPLAY OF FLIGHT
INSTRUMENTATION
NO. 1 GIA 63W
INTEGRATED
AVIONICS UNIT
GDU 1040A
MFD
HIGH SPEED DATA BUS (ETHERNET)
HIGH SPEED DATA BUS
(ETHERNET)
NO. 1 GDC 74A
AIR DATA
COMPUTER
NO. 2 GDC 74A
AIR DATA
COMPUTER
OAT
AIRSPEED
ALTITUDE
VERTICAL SPEED
OAT
AIRSPEED
ALTITUDE
VERTICAL SPEED
GDU 1040A
PFD
34
DISPLAY OF FLIGHT
INSTRUMENTATION
NO. 2 GIA 63W
INTEGRATED
AVIONICS UNIT
GPS
OUTPUT
GPS
OUTPUT
NO. 1 GRS 77
AHRS
NO. 2 GRS 77
AHRS
ATTITUDE
RATE OF TURN
SLIP/SKID
ATTITUDE
RATE OF TURN
SLIP/SKID
NO. 1 GMU 44
MAGNETOMETER
NO. 1 GMU 44
MAGNETOMETER
HEADING
HEADING
Figure 34-6. G1000 Flight Instrument Data Paths
Revision 0
FOR TRAINING PURPOSES ONLY
34-7
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
GMA 1347 #2 (OPT)
AUDIO PANEL
NOTES
REVERSIONAL
CONTROL
MARKER BEACON
INTERCOM CONTROL
DIGITAL AUDIO CONTROL
REV. MODE
34
GDU 1040A
MFD
HIGH-SPEED DATA BUS (ETHERNET)
REV. MODE
TRANSPONDER INTERFACE
(REVERSIONARY MODE ONLY)
HIGH-SPEED DATA BUS (ETHERNET)
CONTROL & DISPLAY OF:
COM/NAV RADIOS
VARIOUS NAVIGATIONAL FUNCTIONS
GDU 1040A
PFD
GDU 1040A
PFD
CONTROL & DISPLAY OF:
COM/NAV RADIOS
TRANSPONDER INTERFACE
VARIOUS NAVIGATIONAL FUNCTIONS
CONTROL & DISPLAY OF:
COM/NAV RADIOS
TRANSPONDER INTERFACE
VARIOUS NAVIGATIONAL FUNCTIONS
HIGH-SPEED DATA BUS
(ETHERNET)
NO. 1 GIA 63W
INTEGRATED AVIONICS UNIT
VHF COM
VHF NAV/LOC
GPS
GLIDESLOPE
VARIOUS I/O PROCESSORS
DIGITAL COM/NAV AUDIO
VOICE ALERTS
GMA 1347
AUDIO PANEL
REVERSIONAL
CONTROL
MARKER BEACON
INTERCOM CONTROL
DIGITAL AUDIO CONTROL
NO. 2 GIA 63W
INTEGRATED AVIONICS UNIT
GTX 33
MODE S
TRANSPONDER
VHF COM
VHF NAV/LOC
GPS
GLIDESLOPE
VARIOUS I/O PROCESSORS
DIGITAL COM/NAV AUDIO
VOICE ALERTS
GTX 33
MODE S
TRANSPONDER
(OPTIONAL)
Figure 34-7. G1000 Navigation/Communication Data Paths
34-8
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
CHAPTER 35
OXYGEN
35
INTRODUCTION
This chapter describes the oxygen systems. In addition to system description, the chapter emphasizes maintenance and servicing precautions along with functional testing. References for this chapter and
further specific information is in Chapter 35 Oxygen, Chapter 5 Time Limits/Maintenance Checks, and Chapter 12 Servicing of the Manufacturer’s Maintenance Manual.
OXYGEN SYSTEMS
There are seven oxygen systems that are ­available for the 208 Caravan:
• 17-port system with two pressure compensated regulators
• 14-port system with two pressure compensated regulators
• 13-port system with two compensated regulators
• 10-port system with two pressure compensated regulators
• 10-port system with a single pressure compensated regulator
• 8-port system with two pressure compensated regulators
• 2-port system with a non-pressure compensated regulator
Revision 0
The two-port system uses a 50.67 cubic-foot capacity oxygen cylinder.
The 8-port, 10-port, 13-port, 14-port, and 17-port systems use a
116.95 cubic-foot capacity oxygen cylinder. Both oxygen cylinders
are composite c­ onstruction and include a shutoff valve.
All 116.95 cubic-foot capacity oxygen cylinders have an altitude
compensated regulator that changes oxygen pressure with altitude.
208B0466 through thru 208B1170), and 17-port system (airplanes
208B0466 and on), there are two altitude compensated regulators to
change the oxygen output with altitude.
The 50.67 cubic-foot oxygen cylinders without an altitude compensated regulator keep an operating pressure of 70 psi and must have
quick-don oxygen masks with a mounted diluter demand regulator.
On aircraft equipped with the 10-port system, (aircraft 20800208
through 20800395), there is a single pressure compensated regulator
to change the oxygen output with altitude. On aircraft that have the
8-port system (aircraft 20800396 and on), 10-port system (airplanes
FOR TRAINING PURPOSES ONLY
35-1
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
0
NOTES
1000
500 1500
2000
USE NO
OIL
PSI
OXYGEN
SUPPLY PRESSURE
MADE IN USA
15
ON
OFF
TO
COPILOT’S
FACE
MASK
TO
PILOT’S
FACE
MASK
35
NOTE: TEN PORT SYSTEM
WITH ALTITUDE
COMPENSATOR
REGULATOR
LEGEND
REGULATED/COMPENSATED PRESSURE OXYGEN
ALTITUDE
COMPENSATOR
MODEL 208
PASSENGER
HIGH-PRESSURE OXYGEN
MECHANICAL ACTUATOR
CONTINUOUS FLOW COUPLING
FILLER
VALVE
Figure 35-1. Oxygen System Overview
35-2
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
CHAPTER 36-37
PNEUMATICS/VACUUM
36-37
INTRODUCTION
This chapter describes two small systems in the Caravan I: Pneumatic and vacuum. The pneumatic system distributes engine P3 bleed
air to the heating and the ice and rain ­protection systems. The vacuum system furnishes vacuum air (suction) to operate the horizon
and directional gyros.
PNEUMATIC SYSTEM—GENERAL
VACUUM SYSTEM—GENERAL
The system consists of a pressure regulator valve and a pressure line
that delivers engine bleed air to the primary heating system of the
aircraft and the pneumatic deice boots. The manufacturer’s maintenance manual includes procedures on removal and installation of the
pressure regulator and the distribution line.
The horizontal indicator gyro in the left ­removable flight panel visually
indicates the aircraft pitch and roll attitude with respect to the earth.
The directional gyro directly below the horizontal indicator displays
a stable indication of the aircraft heading when properly set to agree
with the magnetic compass.
Optional directional gyros also provide the ­autopilot with electrical
heading information.
Revision 0
FOR TRAINING PURPOSES ONLY
36-1
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
BLEED
AIR
BLEED AIR
EXHAUST
VACUUM
EJECTOR
18 PSI PRESSURE
REGULATOR
22 PSI PRESSURE
RELIEF
VALVE
VACUUM
LOW
VACUUM
RELIEF
VALVE
VACUUM LOW
WARNING
ANNUNCIATOR
36-37
ATTITUDE
INDICATOR
(VACUUM)
VACUUM LOW
WARNING
SWITCH
ATTITUDE
INDICATOR
(ELECTRICAL)
VACUUM
SYSTEM AIR
FILTER
DIRECTIONAL
INDICATOR
(ELECTRICAL)
LEGEND
INLET AIR
DIRECTIONAL
INDICATOR
(VACUUM)
SUCTION
GAGE
VACUUM
BLEED AIR
ELECTRIC
Figure 36-1. Model 208B Vacuum System Overview
36-2
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
CHAPTER 51-57
STRUCTURES
51-57
INTRODUCTION
This chapter provides a general overview and description of the structural makeup of the Caravan I series aircraft. The information is
general in nature and not intended to be all-inclusive. References for this chapter and further specific information are in Chapter 20
Standard Practices-Airframe, Chapter 51 Standard Practices and Structures-General, Chapter 52 Doors, Chapter 53 Fuselage, Chapter
55 Stabilizers, Chapter 56 Windows, and Chapter 57 Wings in the Maintenance Manual and the Structural Repair Manual.
GENERAL
Standard practices for work on the aircraft structures are in the
manufacturer’s manuals. These include general descriptions along
with general repair practices, materials, and procedures.
Chapter 51 of the maintenance manual describes categories of damage for
the many types of permissible repairs that can be performed. These include
negligible damage, repairable damage, and major replacement damage.
The categories provide the mechanic with some general guidelines to use
in determining the extent and criticalness of any damage.
Revision 0
FOR TRAINING PURPOSES ONLY
In addition, extensive information on corrosion and severity maps of
the world are included. The corrosion resistance of materials in the
aircraft can drastically change with only small environmental changes.
Corrosion is also divided into categories: light, moderate, and severe.
Aircraft exposed to salt air, heavy atmospheric industrial pollution, warm
humid environments, and/or over-water operations require more stringent
corrosion prevention and control programs than aircraft operated in dry
environments. Corrosion repair information is also available.
51-1
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
51-57
51-2
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
CHAPTER 61
PROPELLERS
61
INTRODUCTION
This chapter describes the propellers on the aircraft. It also includes topics such as the propeller control system, propeller governor,
overspeed governor, and beta valve. Emphasis is on component locations and operation. The information also covers maintenance
considerations, inspections, and functional checks. References and further specific information are Chapter 61 Propellers, Chapter 76
Engine Controls, Chapter 5 Time Limits/Maintenance Checks, and Chapter 12 Servicing of the Manufacturer’s Maintenance Manual.
GENERAL
There are two possible Hartzell propeller installations for the Model
208/208B airplanes. Airplanes 208B5000 and On have a HC-B3TN3AFX/T10890CNB propeller assembly installed. Airplanes 20800001
thru 20800188 and airplanes 208B0001 thru 208B0217 have a Hartzell
Model HC-B3MN-3/M10083 propeller assembly installed.
Revision 0
FOR TRAINING PURPOSES ONLY
1. The Model HC-B3TN-3AFX/T10890CNB propeller is a
three-bladed, constant-speed, full-feathering, reversible, governorregulated propeller equipped with aluminum blades.
2. The Model HC-B3MN-3/M10083 propeller is a three-bladed,
constant-speed, full-feathering, reversible, governor-regulated
propeller equipped with composite blades.
61-1
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
FEEDBACK RING
NOTES
BLADE BASE
FEATHER SPRING
PISTON
LOCK NUT
61
BETA ROD
BLADE
CLAMP
LOW PITCH STOP NUT
PITCH CHANGE LINK
COUNTERWEIGHT
Figure 61-1. Hartzell Propeller
61-2
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
BLADE ACTUATING PIN
BLADE BASE
PITCH CHANGE LINK
FEATHER SPRING
LOCK
RINGS
61
PISTON
PISTON ROD
BETA ROD
FEEDBACK RING
Figure 61-2. McCauley Propeller
Revision 0
FOR TRAINING PURPOSES ONLY
61-3
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
PROP. SPEED ADJ. LEVER
AIR BLEED ORIFICE
NOTES
SPEEDER SPRING
Py
RELIEF VALVE
AIR BLEED LINK
PILOT VALVE
MAX. STOP
MIN. GOV. ADJ.
61
BETA VALVE
TO SUMP
TO PROPELLER
PUMP GEARS
LEGEND
OIL SUPPLY
PRESSURIZED OIL
STATIC OIL PRESSURE
BYPASS OIL
PY (CDP AIR)
NO FLOW
GOV. PUMP
CONDITION:
ON SPEED
ENGINE OIL SUPPLY
Figure 61-3. Propeller Governor (Sheet 1 of 4)
61-4
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
PROP. SPEED ADJ. LEVER
AIR BLEED ORIFICE
NOTES
SPEEDER SPRING
Py
RELIEF VALVE
AIR BLEED LINK
PILOT VALVE
MAX. STOP
MIN. GOV. ADJ.
61
BETA VALVE
TO SUMP
TO PROPELLER
PUMP GEARS
LEGEND
OIL SUPPLY
PRESSURIZED OIL
BYPASS OIL
PY (CDP AIR)
NO FLOW
GOV. PUMP
CONDITION:
UNDER SPEED
ENGINE OIL SUPPLY
Figure 61-3. Propeller Governor (Sheet 2 of 4)
Revision 0
FOR TRAINING PURPOSES ONLY
61-5
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
PROP. SPEED ADJ. LEVER
AIR BLEED ORIFICE
NOTES
SPEEDER SPRING
Py
RELIEF VALVE
AIR BLEED LINK
PILOT VALVE
MAX. STOP
MIN. GOV. ADJ.
61
BETA VALVE
TO SUMP
TO PROPELLER
PUMP GEARS
LEGEND
OIL SUPPLY
PRESSURIZED OIL
RETURN OIL
BYPASS OIL
PY (CDP AIR)
NO FLOW
GOV. PUMP
CONDITION:
OVER SPEED
ENGINE OIL SUPPLY
Figure 61-3. Propeller Governor (Sheet 3 of 4)
61-6
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
PROP. SPEED ADJ. LEVER
AIR BLEED ORIFICE
NOTES
SPEEDER SPRING
Py
RELIEF VALVE
AIR BLEED LINK
PILOT VALVE
MAX. STOP
MIN. GOV. ADJ.
61
BETA VALVE
TO SUMP
TO PROPELLER
PUMP GEARS
LEGEND
OIL SUPPLY
PRESSURIZED OIL
RETURN OIL
BYPASS OIL
PY (CDP AIR)
NO FLOW
GOV. PUMP
CONDITION:
FEATHERED
ENGINE OIL SUPPLY
Figure 61-3. Propeller Governor (Sheet 4 of 4)
Revision 0
FOR TRAINING PURPOSES ONLY
61-7
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
CRUISE POSITION
LEGEND
OIL PRESSURE
PUSH-PULL CONTROL
NOTES
CONDITION:
BETA MODE
RETURN OIL
PY AIR
CAM
STATIC OIL
IT
OS
EP
UIS
CR
ION
SEEDER SPRING
PILOT VALVE
F.C.U ARM
Py AIR
FUEL CONTROL UNIT
RESET POST
BETA VALVE
AIR BLEED LINK
61
MIN. GOVERNING
ADJ.
TO
SUMP
ENGINE
OIL
SUPPLY
BETA ROD
BETA NUT
Figure 61-4. Reversing Propeller Engine Controls (Full Reverse)
61-8
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
CHAPTER 71-80
POWERPLANT
INTRODUCTION
71-80
This chapter describes the Pratt and Whitney PT6A powerplant installed on the Caravan I Series aircraft. Components or operational differences among models are listed in the appropriate section such as
fuel, lubrication, ignition, and engine controls. General maintenance considerations in each section accompanies information on functional and operational checks. References for this chapter and further
information are in Chapters 71-80, Chapter 5 Time Limits/Maintenance Checks, and Chapter 12 Servicing of the Manufacturer’s Maintenance Manual.
GENERAL
Power plant installed in Model 208 Series airplanes is a Pratt and
Whitney Aircraft of Canada, Ltd., Model PT6A-114 (600 SHP) gas
turbine engine. Airplanes 20800277 and On, Airplanes 208B0179
thru 208B2196, and 208B2198 thru 208B4999, and 208B0001 thru
208B0178, incorporating SK208-80, have a PT6A-114A (675 SHP)
gas turbine engine is installed. The power plant installed in Model
208B Airplane 208B2197 and Airplanes 208B5000 and On is a Pratt
and Whitney Aircraft of Canada, Ltd., PT6A-140 (867 SHP) engine.
The PT6A is a free turbine engine with two independent turbine
sections: One drives the compressor in the gas generator section while
the second drives the propeller shaft through a reduction gearbox.
Revision 0
The engine is self-sufficient because the gas generator-driven
lubrication system provides lubrication for all areas of the engine.
A hydro-pneumatic fuel control unit (FCU) schedules fuel flow to
maintain power settings selected with a power lever. The propeller
governor keeps constant propeller speeds between 1,600 rpm to 1,900
rpm (governing range).
Circuit breakers for the powerplant include the following on the
cockpit CB panel:
• 5-amp IGN
• 5-amp OIL TEMP
• 5-amp ITT GAGE
• 5 amp FUEL FLOW
• 5 amp TORQUE IND (if electrical torque gage installed)
• 10 amp FUEL CONT HEATER
Cockpit controls include engine controls, ignition and start switches,
engine instruments, and annunciators.
• 5-amp START CONT
FOR TRAINING PURPOSES ONLY
71-1
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
COMPRESSOR
TURBINE
REDUCTION GEARBOX
ACCESSORY
GEAR BOX
POWER
TURBINE
COMPRESSOR
DIFFUSER
PIPE
EXHAUST
PROPELLER SHAFT
OIL
TANK
71-80
AIR INLET
COMBUSTION
CHAMBER
FUEL NOZZLE
BLEED
VALVE
CASE
DRAIN
Figure 71-1. PT6A Small Turboprop
71-2
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
71-80
Revision 0
FOR TRAINING PURPOSES ONLY
71-3
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
P2.5
LEGEND
P2.5 AXIAL COMPRESSOR AIR PRESSURE
P3 COMPRESSOR DISCHARGE AIR PRESSURE
Pa AMBIENT AIR PRESSURE
CONDITION:
ENGINE RUNNING
P3
SEAT
SPRING PIN
METERING
ORIFICE
Pa
ROLLING
DIAPHRAGM
VALVE OPEN - LOW POWER SETTING
71-80
SLEEVE
PISTON
GUIDE PIN
COTTER PIN
VALVE CLOSED - HIGH POWER SETTING
CONVERGENT
DIVERGENT ORIFICE
Figure 71-2. Compressor Bleed Valve—Pre SB 1588
71-4
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
LEGEND
P2.5 AXIAL COMPRESSOR AIR PRESSURE
P3 COMPRESSOR DISCHARGE AIR PRESSURE
Pa AMBIENT AIR PRESSURE
CONDITION:
ENGINE RUNNING
P2.5
P2.5
AIRAIR
P3
AIR
P3 AIR
PISTON
ADJUSTABLE
PRIMARY ORIFICE
TESTDIAPHRAGM
PORT
71-80
FINAL
METERING
FINAL METERING
PLUGPLUG
PORT
TEST TEST
PORT
DIFFUSER
DIFFUSER
Px PRESSURE
Px PRESSURE
Figure 71-3. Compressor Bleed Valve—Post SB 1588
Revision 0
FOR TRAINING PURPOSES ONLY
71-5
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
OIL TANK BREATHER
LEGEND
SCAVENGE OIL
PRESSURE OIL
TORQUE OIL
CONTROL VALVE
AIR
DEAERATOR
FROM
OIL COOLER
CHECK VALVE
FUEL HEATER
40 PSI
CHECK VALVE
PROP GOVENOR
OIL FILLER AND DIPSTICK
OIL SUPPLY
TO PROP
FILTER BYPASS
TO OIL
COOLER
CENTRIFUGAL
BREATHER
OIL FILTER AND
CHECK VALVE
ASSEMBLY
RELEIF VALVE
RETURN TO
OIL TANK
71-80
AGB DRAIN
RELEIF VALVE
OIL PRESSURE PUMP
SCAVAGE OIL FROM
PROP AND RGB
TO COCKPIT
INSTRUMENTS
OIL TANK DRAIN
OIL SUPPLY TO
PROP AND RGB
CHIP DETECTOR—DRAIN
Figure 71-4. Lubrication System Overview (PT6A-114 & PT6A-114A)
71-6
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
71-80
Revision 0
FOR TRAINING PURPOSES ONLY
71-7
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
FUEL HEATER
OIL IN FROM
AIRFRAME
COOLER
THERMOSTATIC BYPASS
& CHECK VALVE
CENTRIFUGAL
BREATHER
TO OIL
AIRFRAME
COOLER
MAIN OIL FILTER
OIL PRESS.
PUMP
P
R
V
71-80
PRESSURE TRANSMITTER
TEMP. BULB
SCAVENGE OIL
OIL SUPPLY TO PROPELLER & REDUCTION
TANK DRAIN
LEGEND
SCAVENGE OIL
PRESSURE OIL
SUPPLY OIL
Figure 71-5. Lubrication System Overview (PT6A-140)
71-8
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
EXPANSIVE
MATERIAL
THERMOSTATIC
ELEMENT
OIL OUT
TO TANK
BYPASS
VALVE
RETURN
SPRING
OIL
FROM
AGB
SCAVENGE
RELIEF
SPRING
RETURN FROM COOLER
AGB
CHECK
VALVE
OIL
TANK
OIL OUT TO
AIR FRAME COOLER
FCU
71-80
FUEL
OUT
LEGEND
SCAVENGE OIL
FUEL IN
FUEL HEATER
THERMOSTATIC
BYPASS
AIR & OIL MIST
AIRCRAFT BOOST FUEL PRESSURE
CONDITION:
ENGINE RUNNING
OUT TO COOLER
RGB SCAVENGE
Figure 71-6. Thermostatic Bypass & Check Valve Overview (PT6A-140)
Revision 0
FOR TRAINING PURPOSES ONLY
71-9
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
LEGEND
OIL PRESSURE - UNFILTERED
OIL PRESSURE - FILTERED
STATIC OIL
CONDITION:
ENGINE RUNNING
FILTER ELEMENT
COVER
OIL FILTER HOUSING
OIL PUMP HOUSING
INLET CASE
CHECK VALVE SEAT
71-80
CHECK VALVE
BY-PASS
CHECK VALVE SPRING
BY-PASS VALVE
SECONDARY FILTER
Figure 71-7. Oil Filter Components
71-10
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
POWER LEVER
PROPELLER
LEVER
TRIGGER
CONDITION
LEVER
FRICTION
KNOB
71-80
EMERGENCY POWER LEVER
Figure 71-8. Engine Controls
Revision 0
FOR TRAINING PURPOSES ONLY
71-11
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
HIGH PRESSURE FUEL
TO FCU
OUTLET
FILTER
FILTER BYPASS
VALVE
CARBON
SEAL
CARBON
SEAL
BRASS
BUSHINGS
COUPLING TO
ACCESSORY
GEARBOX
FCU BYPASS
RETURN
71-80
INLET FILTER
(SELF RELIEVING)
LEGEND
FUEL INLET PRESSURE
BYPASS PRESSURE
REGULATING VALVE
BYPASS FUEL
PUMP DELIVERY PRESSURE
LOW PRESSURE FUEL
FROM FUEL HEATER
Figure 71-9. Fuel Pump Overview
71-12
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
P2
ACCELERATION
ADJUSTMENT
MAX FLOW STOP
GAS GEN. SPEED
SCHEDULING
CAM
BYPASS VALVE
GOV.
BELLOWS
RETURN TO TANK
IDLE SPEED
ADJ.
TO
THROTTLE
RETURN
TO PUMP
TO PROP.
GOV.
TORQUE
TUBE
HIGH PRESSURE
RELIEF VALVE
P1 FROM
FUEL PUMP
71-80
ACCEL.
BELLOWS
EVACUATED
Pa
LEGEND
Px METERING
ORIFICE
P1 PUMP DELIVERY FUEL
Py METERING
ORIFICE
P2 METERED FUEL
P0 BYPASS FUEL
P3 COMPRESSOR DISCHARGE AIR
P3 AIR
Px ACCELERATION AIR PRESSURE
Py GOVERNING AIR PRESSURE
CONDITION:
Engine Running
Figure 71-10. Fuel Control Unit—Cross Section (PT6A-114/114A)
Revision 0
FOR TRAINING PURPOSES ONLY
71-13
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
FUEL CONTROL UNIT (FCU)
FUEL PUMP
FUEL METERING
MAIN FLOW
FUEL CONDITION
LEVER AND
HIGH IDLE
CAM
Po
PUMP
UNLOADING VALVE
Po
P2
FUEL INLET
(FROM FUEL
HEATER)
HIGH
PRESSURE
RELIEF VALVE
Po
PUMP
P1
POWER
LEVER
P1
3D
CAM
FUEL VALVE
FOLLOWER
Po
Po
MINIMUM
FLOW
Pt
Pt BLEED
TO Po
71-80
BYPASS
VALVE
FUEL
VALVE
3D CAM
FOLLOWER
P1
P2
P2
P1
Po
P2
FLYWEIGHT
GOVERNOR
COMPRESSOR
SPEED (NG)
DRAIN
Pz
Py
P3
COMPRESSOR
PRESSURE
(P3)
TO
DISTRIBUTION SYSTEM
MINIMUM
PRESSURIZING
AND
SHUTDOWN
VALVE
P2
Py
LEGEND
P1 PUMP DELIVERY FUEL
P2 METERED FUEL
P0 BYPASS FUEL
P3 AIR FILTER
P3 SENSOR
BELLOWS
P3 COMPRESSOR DISCHARGE AIR
TO
PROPELLER GOVERNOR
Px ACCELERATION AIR PRESSURE
Pt FUEL SERVO PRESSURE
Pz INTERMEDIATE FUEL PRESSURE
CONDITION:
Engine Running
Figure 71-11. Fuel Control System (PT6A-140)
71-14
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
71-80
Revision 0
FOR TRAINING PURPOSES ONLY
71-15
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
GARMIN G1000
71-80
208 CARAVAN
Figure 71-12. Engine Indicating System
71-16
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
JK4
ITT
GAGE
5
CB402
P74
L
EK 1
L
EK 3
ITT HARNESS
20 GA JUMPER
J30
IND8
ENGINE TEMP HI
36
ENGINE TEMP LO
38
T5 TERMINAL
BLOCK SIDE
OF ENGINE
F
GEA71
ITT
GAGE
A
(GRN)
B
(WHT)
G
G1000 ONLY
C
71-80
(YEL)
4
(RED)
EK 4
EK 2
LEGEND
BATTERY POWER
GROUND
TRIMMING
THERMOCOUPLE
ALUMEL
CHROMEL
J
M
J9
TRIM PROBE (+)
TRIM PROBE (–)
CONDITION:
POWER ON
Figure 71-13. Inter Turbine Temperature Indicator
Revision 0
FOR TRAINING PURPOSES ONLY
71-17
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
EX 1
0.190-32 UNF-3B
ALUMEL
EX 2
EX 3
EX 4
X
X
X
EX 5
0.164-32 UNC-3B
CHROMEL
CHROMEL RESISTOR
X
T1 TRIM
THERMOCOUPLE
HARNESS (BUS BAR)
X
X
X
X
X
X
X
X
8 THERMOCOUPLES
71-80
X
Trim
Value =
(R1 + R2 + R3 + R4 + R5 + R6 + R7 + R8) / 8
OR
To Instrument
Sum of all functional thermocouples divided by
number of functional thermocouples.
Figure 71-14. T5 Wiring Diagram
71-18
FOR TRAINING PURPOSES ONLY
Revision 0
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
71-80
Revision 0
FOR TRAINING PURPOSES ONLY
71-19
CARAVAN 208 SERIES MAINTENANCE SCHEMATIC MANUAL
NOTES
71-80
71-20
FOR TRAINING PURPOSES ONLY
Revision 0