ICA-208B-77

Transcription

ICA-208B-77

CESSNA AIRCRAFT COMPANY
AIRCRAFT DIVISION
WICHITA, KANSAS 67277
FUEL TEMPERATURE PROBE
ICA Supplement
MODEL NO: 208/208B
SUPPLEMENT NO: ICA-208/208B-77-00002
SUPPLEMENT DATE: 2/16/2015
© Cessna Aircraft Company
Form 2261 Rev 1
AIRCRAFT DIVISION
REVISIONS
ICA-208-77-00002
Rev: -
ICA Summary
Pages 1-6
Manuals Affected
Description
Title
Maintenance Manual
Introduction
Pages 1-11
Supplier Publication List
•
Updated publication list to include the Pratt and Whitney PT6A-140 Illustrated Parts Catalog.
Maintenance Manual
•
28-01-00 Pages
101-111
28-43-00 Page
401
73-10-00 Page
1
Fuel Temperature Probe - Removal/Installation
Fuel Distribution - Description and Operation
Updated CAS message and references to the Garmin Line Maintenance Manual and the Pratt and
Whitney PT6A-140 Engine Maintenance Manual.
Appendix A: Illustrated Parts
Catalog
Not Used
Appendix B: Wiring Diagram
Manual
77-40-01 Pages
0-5
1.
Fuel System - Troubleshooting
Added removal and installation procedure for the fuel temperature probe.
Maintenance Manual
•
Fuel System - Description and Operation
Added fuel temperature probe/sensor troubleshooting procedure.
Maintenance Manual
•
28-01-00 Pages
1-5
Updated CAS message and references to the Garmin Line Maintenance Manual and the Pratt and
Whitney PT6A-140 Engine Maintenance Manual.
Maintenance Manual
•
Date: Feb/16/2016
ENGINE AIRFRAME MONITOR
Export Compliance
A.
This publication contains technical data and is subject to U.S. export regulations. This information has
been exported from the United States in accordance with export administration regulations. Diversion
contrary to U.S. law is prohibited.
ECCN: 9E991
2.
Revision Bars
A.
3.
Revision bars in this ICA supplement identify new ICAs and/or changes to the current ICAs in the
released maintenance manual.
•
New ICAs that are not in the current maintenance manual will have a revision bar from top to
bottom along the left margin.
•
ICAs that are in the current maintenance manual and have information added, deleted or revised
will have a revision bar(s) in the left margin adjacent to the added, deleted or revised information.
•
New or changed illustrations will have a change bar for the entire length of the page.
Page Numbering
A.
The page number system for ICA included in this supplement have three-element numbers that are
separated by dashes. The three-element number is found at the bottom right corner of the page, left
of the page number. The date is found below the page number.
ICA-208/208B-77-00002
Page 1 of 6
Feb 16/2015
Form 2261 Rev 1
AIRCRAFT DIVISION
B.
When the chapter/system element number is followed with zeros in the section/subsystem and
subject/unit element number (28-00-00), the information is applicable to the entire system.
C.
When the section/subsystem element number is followed with zeros in the subject/unit element
number (28-21-00), the information is applicable to the subsystems in the system.
D.
The subject/unit element number is used to identify information applicable to units in the subsystems.
The subject/unit element number continues in sequence from the number -01- with the number of
subsystem units in which maintenance information is necessary.
E.
All system/subsystem/unit (chapter/section/subject) maintenance data is separated into speciied
types of information: Description and Operation, Troubleshooting, Maintenance Practices, etc.
Blocks of page numbers that are in sequence are used to identify the type of information:
(1) Description and Operation or Troubleshooting information may not be included if the procedure
is easy. When subtopics are short, they may be put together into the Maintenance Practices
section. Maintenance Practices can have a mix of subtopics that includes information to service,
remove, install, adjust, test, clean, paint or do approved repairs.
(2) Longer procedures that are not as easy to do may be included in a speciied section.
Page 1 through 99 - Description and Operation
Page 101 through 199 - Troubleshooting
Page 201 through 299 - Maintenance Practices
Page 301 through 399 - Servicing
Page 401 through 499 - Removal/Installation
Page 501 through 599 - Adjustment/Test
Page 601 through 699 - Inspection/Check
Page 701 through 799 - Cleaning/Painting
Page 801 through 899 - Approved Repairs
F.
A typical page number:
G.
Illustrations use the same igure numbers as the page block in which they appear. For example, Figure
202 would be the second igure in a Maintenance Practices section.
ICA-208/208B-77-00002
Page 2 of 6
Feb 16/2015
Form 2261 Rev 1
AIRCRAFT DIVISION
4.
5.
Supplement Revisions
A.
Revisions to this supplement may be accomplished if changes to this supplement are required after
release of the original issue and prior to incorporation into the manuals listed in the REVISIONS table.
B.
All revisions to this supplement will have changes identiied in detail in the revision block(s) above.
C.
All pages in this ICA supplement will have the same date and are valid as of the date shown.
ICA Incorporation into Applicable Manuals
NOTE:
Most ICA supplements will be incorporated in the next available revision to the manuals listed
above and should be used in conjunction with those manuals until the next available revision is
released.
A.
The ICA Supplement List located in the Introduction section of each manual listed in the REVISIONS
table will indicate the incorporation status as of the release date of the published revision.
B.
The manual revision level of the supplement incorporation will be listed in the "Manual Incorporation
Status" column in the ICA Supplement List, when those ICAs associated with that manual have been
incorporated. After ICAs are incorporated, the manual that they are incorporated in must now be used
for those ICAs instead of the supplement.
•
Based on revision cycle times for the affected manuals, MM ICAs, WDM ICAs, etc. in this
supplement may be incorporated in the manuals at different times.
•
There will not be a revision to this supplement to indicate incorporation in the manuals. Users are
required to check the ICA Supplement List for each manual affected to determine incorporation
status.
C.
This supplement will be completely superseded by the manuals listed in the REVISIONS table when
it has been incorporated in all of the manuals.
ICA-208/208B-77-00002
Page 3 of 6
Feb 16/2015
Form 2261 Rev 1
AIRCRAFT DIVISION
INTRODUCTION
1.
Purpose
A.
The purpose of this Supplement is to provide the maintenance technician with the information
necessary to ensure the correct functionality and performance of the Fuel Temperature Probe on the
Cessna Model 208B until this information gets incorporated into the next revision to the manuals
listed in the "REVISIONS" section of this supplement.
B.
This ICA supplement is designed to satisfy the requirements of 14 CFR 23.1529 "Instructions for
Continued Airworthiness" associated with this installation. This document is a supplement to the
Model 208/208B Maintenance Manual, and the Model 208/208B Wiring Diagram Manual, and will be
incorporated in the next revision to the manual.
C.
When this information is incorporated in the next revision to the manuals listed in the "REVISIONS"
section, those manuals shall take precedence over this supplemental document. Refer to the "ICA
Supplement List" in the "Introduction" section of the respective manual for the status of all applicable
ICA Supplements.
D.
Revisions to this supplement may occur if there is a change to any of the ICAs in this supplement
prior to incorporation into all of the affected manuals.
NOTE:
2.
This document must be placed with the aircraft operator's Technical Library CD-ROM or
Model 208/208B Maintenance Manual, and the Model 208/208B Wiring Diagram Manual,
and incorporated into the operator's scheduled maintenance program.
Effectivity
A.
These Instructions for Continued Airworthiness (ICA) are effective for the following aircraft model and
serialization.
Model
Beginning Effectivity
Ending Effectivity
208B
002197, 005000
and On
3.
Complete ICA Documents
A.
4.
The following document(s), in conjunction with this supplement, constitute the Instructions for
Continued Airworthiness for the FUEL TEMPERATURE PROBE on the Cessna Model 208B. All
items must be available to the operator at initial delivery.
(1) Model 208/208B Maintenance Manual
(2) Model 208/208B Wiring Diagram Manual
System Components
A.
Refer to Appendix B: Wiring Diagram Manual.
ICA-208/208B-77-00002
Page 4 of 6
Feb 16/2015
Form 2261 Rev 1
AIRCRAFT DIVISION
LIST OF INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
1.
2.
Model 208/208B Maintenance Manual
A.
Chapter 28, Fuel
(1) ATA Introduction, Supplier Publication List
(2) ATA 28-01-00, Fuel System - Description and Operation
(3) ATA 28-01-00, Fuel System - Troubleshooting
(4) ATA 28-43-00, Fuel Temperature Probe- Removal and Installation
B.
Chapter 73, Engine Fuel and Control
(1) ATA 73-10-00, Fuel Distribution - Description and Operation
Model 208/208B Wiring Diagram Manual
A.
Chapter 77-40-01 ENGINE AIRFRAME MONITOR
(1) Refer to Appendix B, 77-40-01 Engine Airframe Monitor wiring diagram.
ICA-208/208B-77-00002
Page 5 of 6
Feb 16/2015
Form 2261 Rev 1
AIRCRAFT DIVISION
INSPECTION PROGRAM AND AIRWORTHINESS LIMITATIONS
1.
Continuous Inspection Program
A.
2.
This ICA Supplement does not affect the current inspection program.
Airworthiness Limitations
A.
Cessna Aircraft Company Model 208/208B Maintenance Manual, Chapter 4, Airworthiness
Limitations, contains the system and airframe limitations for the Model 208/208B.
NOTE:
(1)
The Airworthiness Limitations section is FAA-approved and speciies maintenance
required under Section 43.16 and 91.403 of Title 14 Code of Federal Regulations, unless
an alternative program has been FAA approved.
There are no new (or additional) airworthiness limitations associated with this equipment and/or
installation.
ICA-208/208B-77-00002
Page 6 of 6
Feb 16/2015
Form 2261 Rev 1
MODEL 208
MAINTENANCE MANUAL
SUPPLIER PUBLICATION LIST
1.
List of Manufacturers Technical Publications Available Through Cessna
A.
The following listed publications are necessary for the support of your Model 208. Contact the
appropriate manufacturer to order the publications that are necessary for the support of your Model
208.
NOTE:
The publications made by King Radio and Sigmatek Inc./ARC Avionics must be ordered
directly from the manufacturer. The publication names, numbers and addresses are listed
after this section.
Table 1. Chapter 21 - Air Conditioning
Item
Manufacturers Part
Number
Publication Part
Number
Publication Title
Manufacturer
Vent
Blower
33E83-2
37E661-13
33E83 Blower
Assembly Component
Maintenance Manual
(Vent Blower) with
Illustrated Parts List
FL Aerospace Corp.
Janitrol Aero Div.
4200 Surface Rd.
Columbus, OH 43228
Flow Control Valve,
and Temperature
Control
Valve
1H101-4,
1H102-2
CM-200-1
Airborne Component
Overhaul Manual With
Parker-Hanniin Corp.
Airborne Division
711 Taylor St.
P.O. Box 4032
Elyria, OH 44036
Publication Part
Number
Publication Title
Manufacturer
19000869-00
G1000 Caravan Line
Maintenance Manual
Garmin
International,
Inc.
1200 E. 151st Street
Olathe, Kansas 66062
Cessna
Part
Number
Table 2. Chapter 22 - Auto Flight
Item
Cessna
Part
Number
Manufacturers Part
Number
GFC -700
Autopilot
Autopilot
Servo
GSA
8X/GSM 85
19000303-72
Installation Manual
Garmin
Inc.
International,
Autopilot
Servo Gear
box
GSM 86
19000303-83
Installation Manual
Garmin
Inc.
International,
Manufacturers Part
Number
Publication Part
Number
Publication Title
Manufacturer
01100987-00
19000355-02
Garmin GDL 69/69A
Installation Manual
Garmin
International,
Inc.
1200 E. 151st Street
Olathe, Kansas 66062
Table 3. Chapter 23 - Communications
Item
Cessna
Part
Number
Garmin
GDL
69/69A
ICA-208/208B-77-00002
Page 01
Feb 16/2015
Form 2261 Rev 1
MODEL 208
MAINTENANCE MANUAL
Table 4. Chapter 24 - Electrical Power
Item
Manufacturers Part
Number
Publication Part
Number
Publication Title
Manufacturer
DC to DC
Power
Converter
RG40
83706C
Removal/Installation
Manual Model RG40
Regulated DC to
DC Converter (FAA
TSO-C71 Approved)
KGS Electronics, Inc.
418A E. Live Oak Ave.
Arcadia, CA 91006-5690
Battery
G6381E
GSM68213
Gill Battery Service
Manual
Teledyne Battery
Products
840 W. Brockton Ave.
P.O. Box 431
Redlands, CA 92373
Battery
30994-001
BA89-9/
92-13
Battery Instruction
Manual (NICAD)
Marathon Battery
Service Manual
Marathon Power
Technologies Co.
8301 Imperial Dr.
Waco, TX 76712-6588
Table 5.
Chapter 27 - Flight Controls
Publication Part
Number
Publication Title
Manufacturer
AT-RL1001-ICA
Rudder Gust Lock Kit
Maintenance Manual
with Illustrations
Aero Twin Inc.
2404 Merrill Field Dr.
Anchorage, AK 99501
Cessna
Part
Number
Item
Cessna
Part
Number
Rudder
Gust Lock
Kit
Manufacturers Part
Number
ICA-208/208B-77-00002
Page 02
Feb 16/2015
Form 2261 Rev 1
MODEL 208
MAINTENANCE MANUAL
Table 6. Chapter 30 - Deice
Item
Manufacturers Part
Number
Publication Part
Number
Publication Title
Manufacturer
Propeller
De-Ice
Brush
Block
3E2090-1
68-04714K13
Propeller Deice System
Brush Block Assembly
Overhaul Manual and
Illustrated Parts Catalog
BF Goodrich
Aerospace Div.
Engineered
Polymer
Products
150 Division Dr.
Wilmington, NC 28401
Propeller
De-Ice
3E2205-4
68-04712D-13
Propeller Deice System
Maintenance Manual
BF Goodrich
Aerospace Div.
Engineered
Polymer
Products
150 Division Dr.
Wilmington, NC 28401
Propeller
Anti-icing
Boot
183
61-12-83
Propeller Anti-icing Boot
Removal and Installation
Manual
Hartzell Propeller Inc.
One Propeller Place
Piqua, OH
U.S.A 45356- 2634
Web:
http://
www.hartzellprop.com/
service_support.php
Propeller
Ice
Protection
180
30-61-80
Propeller Ice Protection
System Manual
One Propeller Place
Piqua, OH
U.S.A 45356- 2634
Web:
http://
service_support.php
8304151-13
McCauley
Electrothermal Deice
Systems Service Parts
Manual
McCauley Propeller
Systems
P.O. Box 7704
Wichita, KS 67277-7704
Propeller
De-Ice
Cessna
Part
Number
9910587202
P70363680154
Pnuematic
De-Ice
Boots
BFG
30-10-31
Pneumatic De-Icer
Installation, Maintenance
and Repair Manual
Goodrich Corporation
Aerospace Div.
Ice Protection Systems
1555 Corporate Woods
Parkway
Uniontown, OH 44685
Pnuematic
De-Ice
Boots
BFG
30-10-70
Fastboot Pneumatic
De-Icer Installation
Instructions
Goodrich Corporation
Aerospace Div.
Ice Protection Systems
1555 Corporate Woods
Parkway
Uniontown, OH 44685
ICA-208/208B-77-00002
Page 03
Feb 16/2015
Form 2261 Rev 1
MODEL 208
MAINTENANCE MANUAL
Table 7. Chapter 31 - Indicating/Recording Systems
Item
Publication Part
Number
Publication Title
Manufacturer
L-3 FA2100
CVDR
165E184
7-01
L-3 Communications
FA2100 CVDR
Installation and
Operation Manual
L-3
Communications
Aviation Recorders P.O.
Box 3041 Sarasota, FL
34230
L-3 FA2100
CVDR
165E163
0-00
Lao Communications
Portable Interface (PI)
Operators Manual
L-3
Communications
34230
L-3 FA2100
CVDR
165E1696002 (rev 3
or higher)
L-3 Communications
ROSE / PI Software
Version 3.0 Operators
Manual
L-3
Communications
34230
Publication Part
Number
Publication Title
Manufacturer
AWBCMM0001-X
Component
Maintenance Manual
for External Design
Wheels & Brakes
Parker-Hanniin
Corp.
Aircraft Wheel and Brake
Division
1160 Center Road
Avon, OH 44011
Brake Lining
Identiication Guide
Parker-Hanniin
Corp.
Aircraft Wheel and Brake
Division
1160 Center Road
Avon, OH 44011
Table 8.
Cessna
Part
Number
Manufacturers Part
Number
Chapter 32 - Landing Gear
Item
Cessna
Part
Number
Brake
Assemblies
Brake
Linings
Manufacturers Part
Number
ICA-208/208B-77-00002
Page 04
Feb 16/2015
Form 2261 Rev 1
MODEL 208
MAINTENANCE MANUAL
Table 9.
Chapter 34 - Navigation
Item
Cessna
Part
Number
Manufacturers Part
Number
Publication Part
Number
Publication Title
Manufacturer
Bendix/King
TAS 870
006-106090005
KHM 880/KTA 870
Multi-Hazard Awareness
Trafic Advisory System
Technical Publications,
Honeywell
One Technology Center
23500 West 105th
Olathe, KS 66061
Bendix/King
KR 87
006-001840005
KR 87
Automatic
Finder
Honeywell
23500 West 105th
Olathe, KS 66061
Bendix/King
KN 63
006-001760004
KN 63
Distance
Equipment
G1000
system
components
01100878-00
85 Servo
Mount
GSM 86
Servo Mount
Supplier
PN: GSM
86
G1000
Integrated
Flight Deck
NAV/COMM
Test Set (IFR
4000)
Supplier PN
IFR 4000
Direction
Measuring
Honeywell
23500 West 105th
Olathe, KS 66061
19000869-00
G1000 Line Maintenance
Manual (Cessna
Caravan)
Garmin International,
Inc.
1200 E. 151st St.
Olathe, KS 66062
19000303-72
GSA 8X/GSM 85(A)
Installation Manual
Garmin
Inc.
International,
19000303-83
GSM 86 Servo Gear Box
Installation Manual
Garmin
Inc.
International,
19000749-05
G1000 Pilot's Guide
Cessna Caravan
Garmin
Inc.
International,
Aerolex
NAV/COMM
Test Set
IFR 4000
Operation
Manual
AC0823
CD
Stormscope
Series II
Weather
Mapping
Systems
WX-500
WX-500
00911500-001
Stormscope Series
II Weather Mapping
Systems WX-500
Installation Manual
L-3 Communications
Avionics Systems
5353 52ND Street, S.E.
Grand Rapids, MI
49512-9704
Stormscope
Series II
Weather
Mapping
Systems
WX-1000
78-80519150-0
Stormscope Series
II Weather Mapping
Systems WX-1000
Installation Manual
L-3 Communications
Avionics Systems
5353 52ND Street, S.E.
Grand Rapids, MI
49512-9704
Aerolex Wichita Division
10200 West York
Wichita, KS 67215
ICA-208/208B-77-00002
Page 05
Feb 16/2015
Form 2261 Rev 1
MODEL 208
MAINTENANCE MANUAL
Table 10.
Item
Chapter 35 - Oxygen
Cessna
Part
Number
Portable
Oxygen
Bottle
Table 11.
Item
Manufacturers Part
Number
Publication Part
Number
5500AGWFF23A
Publication Title
Manufacturer
AVOX Component
Maintenace Manual
AVOX Systems Inc.
225 Erie St.
Lancaster, NY 14086
Chapter 36 - Pneumatic
Manufacturers Part
Number
Publication Part
Number
Publication Title
Manufacturer
1H75-14
CM200-1
Airborne Component
Overhaul Manual with
Parker-Hanniin Corp.
711 Taylor St.
P.O. Box 4032
Elyria, OH 44036
Manufacturers Part
Number
Publication Part
Number
Publication Title
Manufacturer
Propeller
HC-B3MN3/
M10083
135C-13
Composite Blade
Inspection, Repair, and
Overhaul Instructions
TRW Hartzell Propeller
Division of TRW Inc.
1800 Covington Ave.
Piqua, OH 45356
Propeller
HC-B3N211
00S
139
61-00-39
Propeller Owner's
Manual and Logbook
(Steel Hub Turbine
Propellers with
Aluminum Blades)
One Propeller Place
Piqua, OH
U.S.A 45356- 2634
Web:
http://
service_support.php
Propeller
HC-B3N210
50S
146
61-00-46
Propeller Owner's
Manual and Logbook
Models: HC-B3MN-3
HC-B4MN-5AL
HC-B4MP-3A
One Propeller Place
Piqua, OH
U.S.A 45356- 2634
Propeller
Spinner
D4898P
D4899
127-13
Spinner Assembly
Maintenance Instruction
Guide
TRW Hartzell Propeller
Division of TRW Inc.
1800 Covington Ave.
Piqua, OH 45356
P7036368-0
1
810301213
McCauley C700
Propeller Service Manual
McCauley Propeller
Systems
P.O. Box 7704
Wichita, KS 67277-7704
Cessna
Part
Number
Pressure
Regulator
Table 12. Chapter 61 - Propellers
Item
Propeller
Cessna
Part
Number
9910587201
ICA-208/208B-77-00002
Page 06
Feb 16/2015
Form 2261 Rev 1
MODEL 208
MAINTENANCE MANUAL
Table 13. Chapter 71 - Engine
Item
Cessna
Part
Number
Manufacturers Part
Number
Publication Part
Number
Publication Title
Manufacturer
Engine
600SHP
991057
9-1
PT6A-114
3043512
Pratt & Whitney
PT6A-114/116/135/135A
Maintenance Manual
Pratt & Whitney Canada
Inc.
100 Marie-Victorin Blvd.
Longueuil, Quebec
Canada J4G 1A1
Engine
600SHP
991057
9-1
PT6A-114
3043514
Pratt & Whitney
PT6A-114/116/135/135A
Inc.
Longueuil, Quebec
Canada J4G 1A1
Engine
675SHP
991058
9-1
PT6A-114A
3043512
Pratt & Whitney PT6A114/114A/116/135/135A
Maintenance Manual
Inc.
Longueuil, Quebec
Canada J4G 1A1
Engine
675SHP
991058
9-1
PT6A-114A
3043514
Pratt & Whitney PT6A114/114A/116/135/135A
Inc.
Longueuil, Quebec
Canada J4G 1A1
Engine
867SHP
265000
1-2
PT6A-140
3075742
Pratt & Whitney
PT6A-140 Illustrated
Parts Catalog
Inc.
Longueuil, Quebec
Canada J4G 1A1
Engine
867SHP
265000
1-2
PT6A-140
3075742
Pratt & Whitney
PT6A-140 Maintenance
Manual
Inc.
Longueuil, Quebec
Canada J4G 1A1
ICA-208/208B-77-00002
Page 07
Feb 16/2015
Form 2261 Rev 1
MODEL 208
MAINTENANCE MANUAL
Table 14. Chapter 77 - Engine Indicating
Item
Cessna
Part
Number
Manufacturers Part
Number
Publication Part
Number
Publication Title
Manufacturer
FAST
Engine
Trend
Monitor
2618507
FAST-A010-4
3077188
Abbreviated Component
Maintenance Manual
(ACMM)
Inc.
Longueuil, Quebec
Canada J4G 1A1
FAST
Engine
Trend
Monitor
2618507
Monitor Transfer Module
Help Manual and
Reference Manual
Inc.
Longueuil, Quebec
Canada J4G 1A1
FAST
Engine
Trend
Monitor
2618507
FAST Coniguration and
Test
Pratt & Whitney Engine
Services.
249 Vanderbilt, Ave.
Blvd.
Norwood, MA 02062
Table 15. Chapter 80 - Starter/Generator
Item
Cessna
Part
Number
Manufacturers Part
Number
Publication Part
Number
Publication Title
200SGL119
Q-2
Starter/
Generator
200SGL119
Q-2RX
200SGL153
Q
TM105A
with Illustrated
Parts Breakdown
- Starter-Generator
Models 200SGL-XXXX
200SGL153
QRX
Starter/
Generator
300SGL145
Q
TM109
with Illustrated
Parts Breakdown
- Starter-Generator
Models 300SGL-XXXX
Manufacturer
Skurka Aerospace Inc.
4600 Calle Bolero
P.0. Box 2869
Camarillo, CA 93011
Web:
www.skurkaaero.com
Skurka Aerospace Inc.
ICA-208/208B-77-00002
Page 08
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Form 2261 Rev 1
MODEL 208
MAINTENANCE MANUAL
Table 15. Chapter 80 - Starter/Generator (continued)
Item
Cessna
Part
Number
Starter/
Generator
Starter/
Generator
Generator
Control Unit
Assembly
2.
Manufacturers Part
Number
Publication Part
Number
Publication Title
23081-22
23081023-3-13
Lear Siegler 23081
DC Starter/ Generator
Overhaul Manual with
Lucas Aerospace
Power Equipment Corp.
777 Lena Drive
Aurora, OH 44202
23081-22
237006-13
Lucas Aerospace
DC Generators and
Starter-Generators
Maintenance Manual
Lucas Aerospace
777 Lena Drive
Aurora , OH 44202
51539012N
51539012-13
Lear Siegler 51539-012
DC Generator Control
Unit Overhaul Manual
with Illustrated Parts List
Lucas Aerospace
777 Lena Drive
Aurora, OH 44202
Manufacturer
Radio Manufacturer Manuals
A.
The following publications must be ordered directly from Honeywell. Refer to the following list for
address and telephone numbers:
UNITED STATES OPERATIONS
Honeywell International, Inc.,
Aerospace Electronics Systems
1 Technology Center
23500 W. 105th Street
Olathe, KS 66061
800-257-0726 - Direct line to the Product Support Operator for assistance from Customer Service,
Product Specialists, Warranty, Field Engineering and Training.
913-782-0600 - 24 hour emergency service during nonworking hours.
Telex: WUD (0) 4-229
Cable: KINGRAD
EUROPEAN MARKETING OFFICE:
Telephone: Switzerland 22 98 58 80
Telex: Switzerland 289445. Answer back: King CHGeneva, Switzerland
Telephone: France 4 422 1747
Telex: France 150952. Answer back: KINGRAD
Ivry-Le Temple
MANUAL
NUMBER
MANUAL TITLE
006-0180-01
Audio Panel/Marker Beacon Receiver Installation Manual (Type KMA-24)
006-5180-01
Audio Panel/Marker Beacon Receiver Overhaul/Maintenance Manual (Type
KMA-24)
006-0179-03
VHF NAV/COMM Transceiver Installation Manual (Type KX-155/KX-165)
006-5179-03
Weather Radar Installation Manual (Type KX-155/KX-165)
006-0191-01
Weather Radar Installation Manual (Type KWX-56, KI- 244, KA-126)
006-5193-01
Weather Radar Overhaul/Maintenance Manual (Type KWX-56, KI-244, KA-126)
ICA-208/208B-77-00002
Page 09
Feb 16/2015
Form 2261 Rev 1
MODEL 208
MAINTENANCE MANUAL
MANUAL
NUMBER
MANUAL TITLE
006-0184-02
Automatic Direction Finder Installation Manual (Type KR-87, KI-227, KA-44B)
006-0534-01
Transponder Installation Manual (Type KT-79)
006-5534-00
Transponder Overhaul/Maintenance Manual (Type KT-79)
006-0176-03
DME/Master Indicator/Slave Indicator Installation Manual (Type
KN-63/KDI-572/KDI-573/KDI-574)
006-5176-01
DME Overhaul/Maintenance Manual (Type KN-63)
006-5178-00
DME Indicator Overhaul/Maintenance Manual (Type KDI-572/KDI-573/KDI-574)
006-0193-01
Radio Magnetic Indicator Installation Manual (Type KNI-582)
006-5193-00
Radio Magnetic Indicator Installation Manual (Type KNI-582)
006-0137-03
VOR/LOC/GS Indicator Installation Manual (Type KI-202, KI-203, KI-204, KI-206,
KI-207)
006-5137-03
VOR/LOC/GS Indicator Overhaul/Maintenance Manual (Type KI-202, KI-203,
KI-204, KI-206, KI-207)
006-0185-00
Digital Area Navigation System Installation Manual (Type KNS-81)
006-5185-00
Digital Area Navigation System Overhaul/Maintenance Manual (Type KNS-81)
006-0152-02
Radar Altimeter Installation Manual (Type KRA-10A) (KI-250 Included)
006-5152-02
Radar Altimeter Overhaul/Maintenance Manual (Type KRA-10A) (KI-250 Included)
006-10536-02
Radar Altimeter Installation Manual (Type KRA-405B) (KNI-415/416 Included)
006-10557-0006
Autopilot Installation Manual (Type KFC225)
006-00702-0000
Flight Control and Avionics System Installation Maintenance Manual
006-0169-03
VHF Comm Transceiver Installation Manual (Type KY-196)
006-5169-03
VHF Comm Transceiver Overhaul/Maintenance Manual (Type KY-196)
006-0192-02
Radio Magnetic Indicator Installation Manual (Type KI-229)
006-5192-00
Radio Magnetic Indicator Overhaul/Maintenance Manual Type KI-229)
3.
Sigmatek Inc./ARC Avionics Manufacturer Manuals
NOTE:
Following listed Sigmatek Inc./ARC publications must be ordered directly from Sigmatek
Inc./ARC Avionics, Attn: ARC Order Entry, 1001 Industrial Rd., Augusta, Kansas 67010, USA.
Telephone No. 316-775-1178.
MANUAL NUMBER
MANUAL TITLE
RP0070104-320
300/400 Series Navigation Indicators
RP0070104-310
400 Nav/Com (Type RT-485B) Service/Parts Manual
RP0070104-370
400 Marker Beacon (Type R-402) Service/Parts Manual
RP0070103-580
400 Glide Slope Receiver (Type R-443B) Service/Parts Manual
RP0070104-140
400 RMI (Type IN-404A) Service/Parts Manual
RP0070103-610
400 ADF (Type R-546E) Service/Parts Manual
RP0070103-780
400 ADF (Type R446A) Service/Parts Manual
ICA-208/208B-77-00002
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Feb 16/2015
Form 2261 Rev 1
MODEL 208
MAINTENANCE MANUAL
MANUAL NUMBER
MANUAL TITLE
RP0070104-280
400/1000 DME (Type RN-477A) Service/Parts Manual
RP0070104-290
400/1000 RNAV (Type RN-479A) Service/Parts Manual
RP0070104-341
400B Autopilot/IFCS Vol. I (Type AF-550A & IF-550A)
RP0070104-342
400B Autopilot/IFCS Vol. II (Type AF-550A & IF-550A)
RP0070104-343
400B Autopilot/IFCS Vol. III (Type AF-550A & IF-550A)
RP0070104-344
400B Autopilot/IFCS Vol. IV (Type AF-550A & IF-550A)
RP0070104-440
400 Audio Ampliier (Type SDM-490A) Service/Parts Manual
RP0070104-447
300 DME (Type SDM-77A) Service/Parts Manual
RP0070104-330
300/400/800 Transponder (Type RT-359A & RT-459A) Service/Parts Manual
7010429
400 RNAV (Type RN-479A) Service/Parts Manual
D4551-13
400 Encoding Altimeter (Type EA-401A) Service/Parts Manual
D4551-13
800 Encoding Altimeter (Type EA-801A) Service/Parts Manual
D4556-13
800 Alerter (Type AA-801A) Service/Parts Manual
ICA-208/208B-77-00002
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Form 2261 Rev 1
MODEL 208
MAINTENANCE MANUAL
FUEL SYSTEM - DESCRIPTION AND OPERATION
1.
General
A.
2.
The fuel system consists of two vented, integral fuel tanks (one in each wing), fuel reservoir, two
selector valves, fuel strainer, electrically operated auxiliary fuel (boost) pump, and ejector pump (both
pumps are submerged in the fuel reservoir). For a fuel system schematic refer to the related illustration
that follows:
(1) For Airplane 208B2197 and Airplanes 208B5000 and On with the PT6A-140 engine installed,
refer to Figure 1 for a fuel system .
(2) For Airplanes 208B0001 thru 208B2196 and Airplanes 208B2198 thru 208B4999 with the PT6A114/PT6A-114A engine installed, refer to Figure 1 for a fuel system .
Description and Operation
A.
Fuel lows from the tanks through two fuel tank shut-off valves in each tank. The valves are
mechanically controlled by two fuel selectors in the overhead console. The selectors are labeled:
LEFT TANK ON, OFF and RIGHT TANK ON, OFF. Left or right fuel tank, or both at the same time
may be selected. In normal operation both tanks should be selected, however, in level cruise light,
fuel may be supplied from either left or right tank.
B.
Fuel lows by gravity from each tank to the fuel reservoir, located under the loorboard at the lowest
point in the fuel system. The ejector boost pump and auxiliary electric fuel pump are located in the
fuel reservoir. The fuel pumps are submerged in fuel, which helps prevent pump cavitation. Fuel is
pumped from the reservoir through the fuel manifold into the engine by the ejector boost pump or
auxiliary fuel pump. The ejector boost pump is driven by motive fuel low from the engine fuel control
unit. If the ejector boost pump should fail, the auxiliary electric fuel pump will automatically energize
and supply fuel to the engine. The auxiliary electric fuel pump is also utilized to supply fuel to the
engine during starts.
C.
A irewall shutoff valve is provided to isolate the fuel supply from engine compartment in case of ire.
The manually operated shutoff valve control knob is located on the control pedestal.
D.
For Airplanes 208B0001 thru 208B2196 and Airplanes 208B2198 thru 208B4999 with the PT6A-114/
PT6A-114A engine installed, a fuel ilter is located on the irewall downstream of the shutoff valve.
A red warning button is located on top of the ilter. If the button is "popped up", the ilter screen is
clogged, and fuel is forced to bypass the ilter. Do not ly the airplane until after the source of fuel
contamination is discovered and eliminated.
E.
The fuel is then routed through the fuel heater and engine-driven fuel pump. The engine-driven pump
delivers fuel, under pressure to the engine fuel ilter. The engine fuel ilter routes the fuel to a low
divider which distributes the fuel to 14 fuel nozzles in the combustion chamber of the engine.
F.
Excessive fuel accumulated during the engine shutdown is routed as follows:
(1) For Airplanes 20800001 and On, and Airplanes 208B0001 thru 208B2196, and 208B2198 thru
208B4999 with PT6A-114/PT6A-114A engines, excessive fuel, accumulated during the engine
shutdown, drains into a ire proof EPA fuel reservoir can on the engine side of the irewall. The
reservoir must be drained daily or it could overlow on the ground.
(2) For Airplane 208B2197 and Airplanes 208B5000 and On with PT6A-140 engine, have a fuel
ecology system installed that recycles unused excessive fuel back to the fuel system during the
next engine run.
G.
The fuel system is vented by two vent valves attached to lines running from each tank outboard to the
wing tips, then aft to wing trailing edge. Fuel reservoir is vented to each fuel tank. Complete blockage
of the vent system will result in zero fuel low to engine.
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MAINTENANCE MANUAL
Fuel System Schematic
Figure 1 (Sheet 1)
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MAINTENANCE MANUAL
Fuel System Schematic
Figure 1 (Sheet 2)
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MAINTENANCE MANUAL
H.
The auxiliary (boost) fuel pump switch is located on left sidewall switch and circuit breaker panel,
and labeled as follows: FUEL BOOST OFF, NORM and ON. When the switch is in NORM position,
auxiliary fuel pump is armed and will operate anytime fuel manifold pressure drops below 4.75 psi.
Place the switch in ON position for engine starting and continuous operation of auxiliary fuel pump.
(1) For Airplane 208B2197 and Airplanes 208B5000 and On with PT6A-140 engines. When the
switch is in NORM position the motive low shutoff-valve (MFSOV) opens. There is a two second
delay fuel pump delay relay that keeps the boost pump operating to allow the motive fuel pump
to built pressure. Once the motive low is established the residual fuel is removed from the fuel
ecology tank.
I.
Fuel quantity is measured by four fuel quantity transmitters in each tank (one inboard, one center
inboard, one center outboard, and one outboard) and indicated by two electrically operated fuel
quantity indicators located on the instrument panel. The indicators are calibrated in pounds and
gallons. For Airplanes 20800500 and On and Airplanes 208B2000 and On an empty fuel tank is
indicated by the fuel gage indicator showing at the red line on the Multifunction Display (MFD) engine
display fuel quantity indicator. For Airplanes 20800001 thru 20800499, and Airplanes 208B0001 thru
208B1999, an empty fuel tank is indicated by a red line and the letter E.
J.
For Airplane 208B2197 and Airplanes 208B5000 and On with the PT6A-140 engine installed, the
Fuel-Oil Heat Exchanger (FOHE) has a temperature probe (UN042) installed on the outlet that will
activate a FUEL TEMP LOW Crew Alert System (CAS) message. The message will display on the
Primary Flight Display (PFD) when the probe indicates the fuel temperature is 41°F (5°C) or less.
For additional information on maintenance of the fuel temperature probe, refer to this Chapter, Fuel
Temperature Probe - Removal and Installation. For additional information on troubleshooting for the
CAS FUEL TEMP LOW message, refer to Fuel System - Troubleshooting, Fuel Temperature System
(PT6A-140).
K.
Airplanes 20800500 and On and Airplanes 208B2000 and On show fuel level crew alert system (CAS)
messages on the Primary Flight Display (PFD). In addition, if a fuel selector is selected to the OFF
position an OFF message will show next to the applicable fuel quantity display and a warning horns
sound. Refer to Table 1.
Table 1. Fuel System Related CAS Messages
CAS Message
Color
CAS Message description
RSVR FUEL LOW
RED
RSVR FUEL LOW Indicates the
fuel level in the reservoir tank is
approximately one-half or less.
There is adequate fuel in the
fuel reservoir for approximately 3
minutes of maximum continuous
power or approximately 9 minutes
at idle power.
FUEL SELECT OFF
RED
Indicates left and right fuel
selectors are both OFF at any
time, or left fuel selector is OFF
when right tank is low, or right fuel
selector is OFF when the left tank
is low; or that either left or right
selectors are OFF when starter
switch is ON. It can also indicate
that the FUEL SEL WARN circuit
breaker has been pulled.
L FUEL LEVEL LOW
AMBER
Indicates fuel quantity in the left
fuel tank is 25 gallons (170 lbs) or
less.
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MAINTENANCE MANUAL
Table 1. Fuel System Related CAS Messages (continued)
CAS Message
Color
CAS Message description
R FUEL LEVEL LOW
AMBER
Indicates fuel quantity in the right
fuel tank is 25 gallons (170 lbs) or
less.
L-R FUEL LEVEL LOW
AMBER
Indicates fuel quantity in both
the left and right fuel tanks is 25
gallons (170 lbs) or less.
FUEL BOOST ON
AMBER
Indicates the auxiliary fuel boost
pump is operating.
FUEL PRESS LOW
AMBER
Indicates fuel pressure in the fuel
manifold assembly is below 4.75
psi.
FUEL TEMP LOW
AMBER
Indicates fuel temperature is 41°F
(5°C) or less.
L.
Airplanes 20800001 thru 2080499, and Airplanes 208B0001 thru 208B1999, have amber and red fuel
system condition warning lights that are located on the annunciator panel. Two amber lights (one for
each fuel tank) are labeled, LEFT FUEL LOW and RIGHT FUEL LOW. Each of the lights come on
when the fuel level of it respective tank reaches 25 gallons, +5 or –5 gallons. An annunciator light
(red), placarded RESERVOIR FUEL LOW comes on when fuel level in the reservoir drops below 2.15
to 1.95 gallons. An annunciator light (amber), placarded FUEL PRESSURE LOW comes on when the
fuel manifold pressure drops below 4.75 psi.
M.
An additional fuel selectors off warning system is incorporated to alert pilot if one or both of the fuel tank
selectors are left in the OFF position inadvertently. The system includes redundant warning horns,
a red annunciator light labeled FUEL SELECT OFF, actuation switches, and miscellaneous electrical
hardware. The dual aural warning system is powered through the START CONT circuit breaker with
a FUEL SEL WARN circuit breaker that you cannot manually disengage, installed in series to protect
the integrity of the start system. The annunciator is powered from the ANNUN PANEL circuit breaker.
N.
The fuel system has drain valves to examine the fuel and remove contamination from the system.
The fuel must be drained and examined before the irst light of the day, and after each refueling.
NOTE:
(1)
(2)
Do not drain fuel on asphalt or concrete surfaces.
For Airplanes 20800001 and On, and Airplanes 208B0001 thru 208B2196, and 208B2198 thru
208B4999 engines. An EPA approved fuel reservoir can is installed on the front left side of the
irewall to catch residual fuel after the engine shutdown. Before the irst light of the day, use the
drain valve on the bottom of the cowling to empty the EPA fuel reservoir can into an appropriate
container.
For Airplane 208B2197 and Airplanes 208B5000 and On with PT6A-140 engines. These
airplanes have a fuel ecology tank installed that replaces the EPA fuel reservoir can. There is
no drain associated with the ecology tank.
ICA-208/208B-77-00002
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Form 2261 Rev 1
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MAINTENANCE MANUAL
FUEL SYSTEM - TROUBLESHOOTING
1.
General
A.
This section gives troubleshooting information to help the technician ind and correct problems in the
fuel system. For troubleshooting systems related to the Garmin G1000 System, refer to the Garmin
G1000 Line Maintenance Manual (Cessna Caravan). Refer to the Supplier Publication List.
B.
For fuel system problems reference the applicable troubleshooting charts that follow:
(1) For engine fuel low problems refer to Figure 101.
(2) For fuel quantity problem for airplanes with the Garmin G1000 system refer to Figure 102
(3) For fuel low problem for airplanes with the Garmin G1000 system refer to Figure 103
(4) For fuel low problem for airplanes that do not have the Garmin G1000 system refer to Figure
104
(5) For boost pump operation problems for airplanes with the PT6A-140 engine installed Figure 105.
C.
Engine Fuel Flow Troubleshooting
(1) To troubleshoot engine fuel low problems refer to Figure 101.
D.
Fuel Quantity and Fuel Flow Troubleshooting (G1000)
(1) To troubleshoot fuel quantity problems for airplanes with the Garmin G1000 system refer to
Figure 102.
(2) To troubleshoot fuel low problems for airplanes with the Garmin G1000 system refer to Figure
103.
E.
Fuel Quantity and Fuel Flow Troubleshooting (Non-G1000)
(1) To troubleshoot fuel quantity and fuel low problems for airplanes that do not have the Garmin
G1000 system refer to Figure 104.
ICA-208/208B-77-00002
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MAINTENANCE MANUAL
Engine Fuel System Troubleshooting Chart
Figure 101 (Sheet 1)
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MAINTENANCE MANUAL
Engine Fuel System Troubleshooting Chart
ICA-208/208B-77-00002
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Feb 16/2015
Form 2261 Rev 1
MODEL 208
MAINTENANCE MANUAL
Fuel Quantity Troubleshooting (G1000)
ICA-208/208B-77-00002
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Feb 16/2015
Form 2261 Rev 1
MODEL 208
MAINTENANCE MANUAL
Fuel Quantity Troubleshooting (G1000)
ICA-208/208B-77-00002
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Feb 16/2015
Form 2261 Rev 1
MODEL 208
MAINTENANCE MANUAL
Fuel Flow Troubleshooting (G1000)
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MAINTENANCE MANUAL
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MAINTENANCE MANUAL
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MAINTENANCE MANUAL
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MAINTENANCE MANUAL
F.
Boost Pump Troubleshooting (PT6A-140)
(1) To troubleshoot boost pump problems for airplanes with the PT6A-140 engine installation refer
to Figure 105.
G.
Fuel Temperature System (PT6A-140)
(1) The PT6A-140 engine has a fuel temperature probe (UN042) installed on the outlet of the fuel
oil heat exchanger (FOHE) that will activate a FUEL TEMP LOW CAS message if the probe
detects that the fuel temperature is 41°F (5°C) or less.
NOTE:
(2)
Engines must be running for the CAS message to be enabled.
To troubleshoot the system when the FUEL TEMP LOW CAS message is on, do as follows:
NOTE:
To determine the current recorded temperature of the fuel temp probe, Refer to
Chapter 77, Live Data Sensor Test - Engine Off.
(a)
(3)
Disconnect the electrical connector (PI001) from the GEA-71 Garmin Engine Airframe Unit
(UI005) and the electrical connector (PN051) from the temperature probe (UN042).
(b) Use a multimeter to make sure there is continuity between pin 26 of the GEA-71 Garmin
Engine Airframe Unit connector and pin A of the temperature probe connector.
(c) Use a multimeter to make sure there is continuity between pin 27 of the GEA-71 Garmin
Engine Airframe Unit connector and pin B of the temperature probe connector.
If there is no continuity between the pins, repair the wiring as necessary. Refer to the
1
Model 208/208B Wiring Diagram Manual Chapter 77.
2
If there is continuity between the pins, replace the temperature probe. Refer to Fuel
Temperature Probe - Removal/Installation in this chapter.
(d) Complete an engine run to make sure the FUEL TEMP LOW CAS message is not shown on
the Primary Flight Display (PFD) and the engine oil temperature is within normal operating
limits for takeoff. (Refer to the approved Model 208B 867 SHP Garmin G1000 Aircraft
Flight Manual).
(e) If FUEL TEMP LOW CAS message is shown on the PFD, and the engine oil temperature
is within normal operating limits for takeoff (refer to the approved Model 208B 867 SHP
Garmin G1000 Aircraft Flight Manual); refer to the troubleshooting section of the G1000
Garmin Engine Airframe Monitor system. Refer to the (Cessna Caravan). Refer to the
Supplier Publication List.
If FUEL TEMP LOW CAS message continues to show on the PFD, and the engine oil
temperature is within normal operating limits for takeoff (refer to the approved Model 208B 867
SHP Garmin G1000 Aircraft Flight Manual); replace the fuel oil heat exchanger. Refer to the
Pratt and Whitney PT6A-140 Engine Maintenance Manual, refer to Supplier Publication List.
ICA-208/208B-77-00002
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MAINTENANCE MANUAL
Boost Pump Troubleshooting (PT6A-140)
ICA-208/208B-77-00002
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MAINTENANCE MANUAL
FUEL TEMPERATURE PROBE - REMOVAL/INSTALLATION
1.
2.
General
A.
This section gives the removal and installation procedures for the fuel temperature probe. For a
general description of the temperature probe, refer to Fuel System - Description and Operation.
B.
The fuel temperature probe is installed on the Pratt and Whitney PT6A-140 engine and is located on
the outlet of the fuel oil heat exchanger.
Tools and Equipment
A.
3.
For a list of tools and equipment, refer to Fuel - General.
Fuel Temperature Probe Removal and Installation
WARNING: When you do work on the fuel system, make sure that you obey all of the
safety precautions in the Fuel - Maintenance Practices section. Injury
or death can occur if you do not obey these precautions.
A.
Remove the Fuel Temperature Probe (UN042).
(1) Remove external electric power from the airplane.
(2) Pull the fuel irewall shutoff control out (off).
(3) Open or remove the upper right cowling to get access to the engine fuel inlet line. Refer to
Chapter 71, Engine Cowling and Nose Cap- Maintenance Practices.
(4) Remove and cap/cover the electrical connector (PN051) from the fuel temperature probe.
(5) Place suitable container underneath the fuel temperature probe to catch residual fuel.
(6) Remove the safety wire from the fuel temperature probe.
(7) Remove fuel temperature probe from the Fuel Oil Heat Exchanger (FOHE) outlet.
(8) Discard packings. Refer to the Pratt and Whitney PT6A-140 Parts Catalog, refer to Supplier
Publication List.
(9) Clean and inspect the fuel temperature probe for defects, replace as necessary.
B.
Install the Fuel Temperature Probe.
(1) Install the new packings on the temperature probe. Refer to the Pratt and Whitney PT6A-140
Parts Catalog, refer to Supplier Publication List.
(2) Install the temperature probe into the FOHE outlet.
(3) Torque the fuel temperature probe to 65-75 inch pounds (7.35-8.48 Nm), refer to Chapter 20,
Torque Data - Maintenance Practices.
(4) Install new safety wire, refer to Chapter 20, Safetying - Maintenance Practices.
(5) Remove cap/cover and install electrical connector (PN051) to the fuel temperature probe.
(6) Push the fuel irewall shutoff control fully in.
(7) Install or close the upper right cowling. Refer to Chapter 71, Engine Cowling and Nose CapMaintenance Practices.
(8) Complete an engine run to make sure there are no visible luid leaks and to make sure the FUEL
TEMP LOW CAS message is not shown on the Primary Flight Display (PFD) when the engine
oil temperature is within normal operating limits for takeoff. (Refer to the approved Model 208B
867 SHP Garmin G1000 Aircraft Flight Manual)
ICA-208/208B-77-00002
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MAINTENANCE MANUAL
FUEL DISTRIBUTION - DESCRIPTION AND OPERATION
1.
Description and Operation
A.
The engine fuel system consists of an fuel-oil-heat-exchanger (FOHE), an engine-driven fuel pump,
a fuel control unit, a low divider and dump valve, a dual fuel manifold with 14 simplex nozzles, a fuel
low indicator system, and two fuel drain lines. The system provides fuel low to satisfy the speed
and power demands of the engine. Fuel from the airplane fuel reservoir is delivered to the FOHE
which utilizes heat from the engine lubricating oil system to preheat fuel before it is delivered to the
fuel control unit. A fuel temperature-sensing oil bypass valve regulates fuel temperature by either
allowing oil to low through heater circuit or bypass it to engine oil tank.
NOTE:
If the fuel temperature sensing oil bypass valve fails to regulate fuel temperature on the
PT6A-140, there is a fuel temperature probe (UN042) installed on the outlet of the FOHE.
The temperature probe will activate the amber CAS message FUEL TEMP LOW if the
probe detects that the fuel temperature is 41°F (5°C) or less. For additional information on
maintenance of the fuel temperature probe, refer to Chapter 28, Fuel Temperature Probe Removal and Installation. For additional information on troubleshooting for the CAS FUEL
TEMP LOW message, refer to Fuel System - Troubleshooting.
B.
Fuel from fuel-oil-heat-exchanger (FOHE) then enters engine-driven fuel pump chamber through a
74-micron inlet screen. The inlet screen is spring-loaded and should it become blocked, the increase
in differential pressure will overcome the spring and allow uniltered fuel to low into pump chamber.
The pump increases fuel pressure and delivers it to fuel control unit via a 10-micron ilter in pump
outlet. A bypass valve and cored passages in pump body enables uniltered high pressure fuel to
low to fuel control unit in the event outlet ilter becomes blocked.
C.
The fuel control unit consists of a fuel metering section, a temperature compensating section, and a
gas generator (Ng) pneumatic governor. The fuel control unit determines the proper fuel schedule to
provide power required as established by power lever input. This is accomplished by controlling speed
of compressor turbine. The temperature compensating section alters the acceleration fuel schedule to
compensate for fuel density differences at different fuel temperatures, especially during engine start.
The temperature compensator alters the acceleration fuel schedule of fuel control unit to compensate
for variations in compressor inlet air temperature. Engine characteristics vary with changes in inlet air
temperature, and the acceleration fuel schedule must, in turn, be altered to prevent compressor stall
and/or excessive turbine temperatures. The power turbine governor, located in propeller governor
housing, provides power turbine overspeed protection in the event of propeller governor failure. This
is accomplished by limiting fuel to gas generator. During reverse thrust operation, maximum power
turbine speed is controlled by power turbine governor.
D.
The low divider schedules the metered fuel, from fuel control unit, between primary and secondary
fuel manifolds. The fuel manifold and nozzle assemblies deliver fuel to combustion chamber through
ten primary and four secondary fuel nozzles. During engine start, metered fuel is delivered initially to
the primary nozzles, with secondary nozzles cutting in above a preset valve. All nozzles are operative
at idle and above.
E.
For Airplane 208B2197 and Airplanes 208B5000 and On, the fuel ecology tank collects the remaining
fuel from the nozzles and plumbing at engine shutdown. Once the motive low is established during
the next engine run, the low will automatically drain this residual fuel and return it back to the engine
for combustion during the next engine run.
F.
For Airplanes 20800001 and On, and Airplanes 208B0001 thru 208B2196, and 208B2198 thru
208B4999, when the fuel cutoff valve in the fuel control unit closes during engine shutdown, both
primary and secondary manifolds are connected to a dump valve port and the residual fuel in the
manifolds drains into the EPA fuel reservoir can that is attached to the irewall.
NOTE:
For more data applicable to the airplane engine fuel components not included in this chapter,
refer to the Pratt & Whitney maintenance manual listed in the List of Publications in the front of
this manual. For proper fuel grades and speciications, refer to Chapter 12, Fuel - Servicing.
ICA-208/208B-77-00002
73-10-00
Page 1
Feb 16/2015
Form 2261 Rev 1
AIRCRAFT DIVISION
APPENDIX A: ILLUSTRATED PARTS CATALOG
NOT APPLICABLE
Form 2261 Rev 1
AIRCRAFT DIVISION
APPENDIX B: WIRING DIAGRAM MANUAL
Form 2261 Rev 1
MODEL 208
WIRING DIAGRAM MANUAL
Figure 03 (Sheet 1)
Figure 03
Page 0
ICA-208-77-00002
© CESSNA AIRCRAFT COMPANY
77-40-01
Feb 16/2016
MODEL 208
FIG
REF
DES
03
GC001
JC011
JI005
JI019
JI024
JI900
PC011
PI001
PI002
-
PI005
PI019
PI502
PI503
TI001
UI005
UI006
UI007
UI008
UI019
UI024
UI024
PART NUMBER
204814-1
S2099-3
S2099-4
S2096-1
S2099-3
S2099-4
205843-1
S2035-2
S1636-1
M24308/2-283F
M24308/25-6
M39029/63-368
M85049/48-1-3
S2350-8
S2351-4
S2353-5
201359-1
S2353-4
336-00044-00
336-00021-00
205842-1
M39029/63-368
S2351-4
S2035-1
S1635-1
011-01000-01
011-01000-01
011-00981-00
011-00797-03
011-00979-00
S1856-1
85-292-1
85-292-1
1234567
. GROUND BLOCK . . . . . . . .
. . CONTACT
. . CONTACT
. CONNECTOR . . . . . . . . . . .
. . CONTACT
. . CONTACT
. CONNECTOR AVN/ELE DISC
. CONNECTOR . . . . . . . . . . .
. . CONTACT
. CONNECTOR . . . . . . . . . . .
. . SCREW LOCK
. . CONTACT
. . STRAIN RELIEF
. CONNECTOR . . . . . . . . . . .
. . CLAMP
. . PIN
. CONNECTOR . . . . . . . . . . .
. . PIN
. CONNECTOR . . . . . . . . . . .
. CONNECTOR . . . . . . . . . . .
.
.
.
.
.
.
.
.
.
.
.
.
.
.
.
UNITS
EFFECTIVITY
PER
FROM TO
ASSY
NOMENCLATURE
. . . . . . . . . . . . . . . . . . . . . . . . . V00779
V71379
V71379
.........................
B5272 & ON
.........................
.........................
.........................
.........................
.........................
. . . . . . . . . . . . . . . . . . . . . . . . . V0TRC3
. . . . . . . . . . . . . . . . . . . . . . . . . V0TRC3 0500
& ON
B2000 & ON
CONNECTOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . V00779
. SOCKET CONTACT
V81349
. CLAMP
V71379
HOUSING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
. CONTACT
CONNECTOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
CONNECTOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
THERMOCOUPLE ASSY . . . . . . . . . . . . . . . . . . . . . . . . . . . .
GEA71 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
GIA 63W . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
GIA 63W . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
CONFIGURATION MODULE . . . . . . . . . . . . . . . . . . . . . . . . . .
SENSOR EPL POSITION. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
SIGNAL CONDITIONER . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
SIGNAL CONDITIONER . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
- ITEM NOT ILLUSTRATED
ICA-208-77-00002
77-40-01
01
AR
AR
01
01 R
01 R
01
01
AR R
01
AR R
AR R
01 R
01
01 R
AR R
01
01 R
01
01
01 R
AR R
AR R
01
AR R
RF
RF
01
01
RF
RF
01
01
01
01
Figure 03
Page 1
Feb 16/2016
MODEL 208
Figure 03 (Sheet 2)
Figure 03
Page 2
ICA-208-77-00002
77-40-01
Feb 16/2016
MODEL 208
FIG
REF
DES
03
GC001
GI002
GN011
GN011
GN012
JC005
JC011
JI005
JI019
JI024
JI900
-
PC005
PC011
PI001
PI002
-
PI005
PI019
PI502
PI503
PI900
-
PN030
PN031
PN032
PN033
PN034
PN035
PN036
PN038
PN051
SN009
TI001
UI005
UI006
UI007
UI008
UI019
PART NUMBER
204814-1
S2099-3
S2099-4
200277-2
S2099-12
S2099-3
S2096-1
S2099-3
S2099-4
205843-1
S2035-2
S1636-1
M24308/2-283F
M24308/25-6
M39029/63-368
M85049/48-1-3
S2350-8
S2351-4
S2353-5
200276-2
S2353-3
S2353-5
201359-1
S2353-4
336-00044-00
336-00021-00
205842-1
M39029/63-368
S2351-4
S2035-1
S1635-1
011-01000-01
011-01000-01
S2349-5
S2099-8
D38999/26FB98SN
S3627-11
M83723/95G1005N
M85049/52-1-10N
MS3126F10-6S
MS3459L12S3S
S3744-12
MS3459L12S3S
S3744-12-90
M83723/95G10056
M85049/51-1-10N
M83723/95G10056
M85049/52-1-10N
M83723/95R1006N
M85049/52-1-10N
MS3459L12S3S
S3744-12-90
431-0101-01
011-00981-00
011-00797-03
011-00979-00
S1856-1
1234567
. GROUND BLOCK . . . . . . . .
. . CONTACT
. . CONTACT
. GROUND . . . . . . . . . . . . . .
. GROUND . . . . . . . . . . . . . .
. GROUND . . . . . . . . . . . . . .
. GROUND TERMINAL . . . . . .
. CONNECTOR LH CB PNL . . .
. . CONTACT
. . CONTACT
. CONNECTOR . . . . . . . . . . .
. . CONTACT
. . CONTACT
. CONNECTOR AVN/ELE DISC
. CONNECTOR . . . . . . . . . . .
. . CONTACT
. CONNECTOR . . . . . . . . . . .
. . SCREW LOCK
. . CONTACT
. . STRAIN RELIEF
. CONNECTOR . . . . . . . . . . .
. . CLAMP
. . PIN
. CONNECTOR LH CB PNL . . .
. . PIN
. . PIN
. CONNECTOR . . . . . . . . . . .
. . PIN
. CONNECTOR . . . . . . . . . . .
. CONNECTOR . . . . . . . . . . .
.
.
.
.
.
.
.
.
.
.
.
.
.
.
.
.
.
.
.
.
.
.
.
.
.
.
.
.
.
.
.
.
.
UNITS
EFFECTIVITY
PER
FROM TO
ASSY
NOMENCLATURE
. . . . . . . . . . . . . . . . . . . . . . . . . V00779
V71379
V71379
.........................
.........................
.........................
.........................
. . . . . . . . . . . . . . . . . . . . . . . . . V00779
V71379
V71379
.........................
B5272 & ON
.........................
.........................
.........................
.........................
. . . . . . . . . . . . . . . . . . . . . . . . . V00779
V71379
V71379
.........................
. . . . . . . . . . . . . . . . . . . . . . . . . V0TRC3
. . . . . . . . . . . . . . . . . . . . . . . . . V0TRC3 0500
& ON
B2000 & ON
CONNECTOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . V00779
. SOCKET CONTACT
V81349
. CLAMP
V71379
HOUSING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
. CONTACT
CONNECTOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
CONNECTOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
CONNECTOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
. CONTACT
PLUG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . V81349
. BACKSHELL
V71379
CONNECTOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . V81349
. STRAIN RELIEF
V81349
PLUG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . V96906
PLUG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . V96906
. BACKSHELL
V71379
PLUG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . V96906
. BACKSHELL
V71379
CONNECTOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . V81349
. STRAIN RELIEF
V81349
CONNECTOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . V81349
. STRAIN RELIEF
V81349
PLUG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . V81349
. STRAIN RELIEF
V81349
PLUG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . V96906
. BACKSHELL
V71379
MAGNETIC REED SWITCH . . . . . . . . . . . . . . . . . . . . . . . . . . V0TMJ9
THERMOCOUPLE ASSY . . . . . . . . . . . . . . . . . . . . . . . . . . . .
GEA71 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
GIA 63W . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
GIA 63W . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
CONFIGURATION MODULE . . . . . . . . . . . . . . . . . . . . . . . . . .
SENSOR EPL POSITION. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
ICA-208-77-00002
77-40-01
01
AR
AR
RF
RF R
RF R
RF R
01
01 R
01 R
01
01 R
01 R
01
01
AR R
01
AR R
AR R
01 R
01
01 R
AR R
01
01 R
01 R
01
01 R
01
01
01 R
AR R
AR R
01
AR R
RF
RF
01
AR R
01 R
01 R
01 R
01 R
01 R
01 R
01 R
01 R
01 R
01 R
01 R
01 R
01 R
01 R
01 R
01 R
01 R
01 R
01
01
RF
RF
01
01
Figure 03
Page 3
Feb 16/2016
MODEL 208
Figure 03 (Sheet 2)
ICA-208-77-00002
Figure 03
Page 4
77-40-01
Feb 16/2016
MODEL 208
FIG
REF
DES
-
UI024
UN029
UN030
UN031
UN032
UN033
UN034
UN035
UN036
UN038
UN042
UN042
PART NUMBER
85-292-1
1-321897-0
1-321898-0
9910338-6
9912034-1
9912034-1
1234567
.
.
.
.
.
.
.
.
.
.
.
.
.
UNITS
EFFECTIVITY
PER
FROM TO
ASSY
NOMENCLATURE
SIGNAL CONDITIONER . . .
TERMINAL-CHROMEL . . . .
. TERMINAL-ALUMEL
OIL PRESS TRANSDUCER .
OIL TEMP PROBE . . . . . . .
FUEL FLOW TRANSMITTER
TACH GEN . . . . . . . . . . . .
TACH GEN . . . . . . . . . . . .
RGB CHIP DET . . . . . . . . .
AGB CHIP DET . . . . . . . . .
TORQUE TRANSDUCER . .
FUEL TEMP PROBE . . . . .
FUEL TEMP PROBE . . . . .
..........................
. . . . . . . . . . . . . . . . . . . . . . . . . . V00779
V00779
..........................
..........................
. . . . . . . . . . . . . . . . . . . . . . . . . . V71379
. . . . . . . . . . . . . . . . . . . . . . . . . . V71379
. . . . . . . . . . . . . . . . . . . . . . . . . . V71379
..........................
..........................
..........................
..........................
..........................
ICA-208-77-00002
77-40-01
01
01 R
01 R
RF R
RF R
01 R
01 R
01 R
RF R
RF R
RF R
RF R
RF R
Figure 03
Page 5
Feb 16/2016

ICA-208B-77

Transcription

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