Pratt & Whitney Engine Services, Inc.
249 Vanderbilt Ave
Norwood, MA 02062
ADAS+
Instructions for Continued Airworthiness
ADAS-G-260-1/A
For Cessna Caravan Model 208 Series
Manual Number:
ADAS-G-260-1/A
Preparation Date:
December 2, 2002
Prepared By:
D Elsemiller
Release Date:
December 16, 2002
Approvals:
S Sackos, Manager of Manufacturing Services
Revision Date:
November 15, 2011
Revision Ltr:
I
Total Pages:
37
J Miller, Manager of Engineering
249 Vanderbilt Avenue, Norwood, MA 02062, Phone 781-762-8600, Fax 781-762-2287
P&W ENGINE SERVICES, INC.
Cessna Aircraft Company
ADAS+
ADAS-G-260-1/A
Model 208 Series
PREFACE
Disclaimer
Like all instrumentation, the Pratt & Whitney Engine Services, Inc. ADAS+ system requires knowledgeable interpretation by
the pilot. Any recommendations and operating procedures contained in this manual shall not supersede the Aircraft or
Engine manufacturer recommendations, operating procedures, or limits. The Pratt & Whitney Engine Services, Inc. ADAS+
system should not be used as a primary guide monitoring the Aircraft and Engine manufacturers operating limits. Pratt &
Whitney Engine Services, Inc. is not liable for any damages resulting from the use of this product.
Proprietary Information Notice
This manual contains proprietary information that is protected by copyright, and all rights are reserved. No portion of this
document may be copied, photocopied, reproduced by any means, or translated into another language without the prior
written permission of P&W Engine Services.
- iADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Aircraft Company
ADAS+
ADAS-G-260-1/A
Model 208 Series
REVISION HISTORY
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LOG OF REVISIONS
REV. NO
ECO#
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DESCRIPTION
DATE
Initial Release
Change Processor Assembly Kit contents by
adding Ground Strap DPU-C-050-3
Reformat manual and add Split Lamp
Option. Correct Typos
Revise Connection Chart to show the correct
pin-out for the J2 Harness.
Correct dimensions for Split
Lamp. Correct OAT Probe connections
12/16/02
PAGES REVISED
05/27/04
I and 1
05/24/05
All
09/12/05
Cover, I – iv, and 27
07/06/06
4, 29-32
Update Split Lamp. Change UTC logo to
P&W logo. Update address. Correct
spelling and grammar.
08/22/07
All
980
Add Ice Vane Switch Kit to Parts List. Add
Continued Airworthiness Instructions for Ice
Vane Switch.
12/08/08
Cover, ii-iv, 7-33
H
994
Revise Parts List. Update Schematics.
Revise OAT, Torque, Circuit Breaker, and
Download Port Instructions. Correct
Typographical Errors.
02/23/09
Cover, ii–iv, 4, 5, 8, 10,
12-14, 17-22, 29-33
I
1103
Add optional Garmin G620 Interface Cable
P/N ADAS-C-072-1 to Parts List. Add
Schematics to support the interface cable
11/15/11
Cover, ii, iv, v, 19, 22,
34 - 37
NOTE:
Revisions to this document shall be coordinated through the Boston Aircraft Certification Office,
the Kansas City AEG, and the STC holder. If the ADAS+ Instructions for Continued
Airworthiness are revised, all operators will be provided with a copy of the applicable revision. If
you have a subscription with TurbineTracker , you will be informed via email of new revisions
to this manual. In addition to this, P&W Engine Services maintains the latest versions of all
manuals in the Support Section of TurbineTracker.
If you are not a subscriber to TurbineTracker , you may call P&W Engine Services Customer
Support at 781-762-8600 for the latest revision.
- iiADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Aircraft Company
ADAS+
ADAS-G-260-1/A
Model 208 Series
TABLE OF CONTENTS
1
INTRODUCTION ................................................................................................................................ 1
1.1
1.2
1.3
1.4
1.5
1.6
1.7
SCOPE ...................................................................................................................................................... 1
APPLICABILITY ........................................................................................................................................ 1
DEFINITIONS AND ABBREVIATIONS ........................................................................................................ 1
PRECAUTIONS .......................................................................................................................................... 1
UNITS OF MEASURE................................................................................................................................. 1
REFERENCED PUBLICATIONS .................................................................................................................. 1
DISTRIBUTION ......................................................................................................................................... 1
2
DESCRIPTION .................................................................................................................................... 2
3
CONTROL AND OPERATION INFORMATION........................................................................... 2
4
SERVICING INFORMATION........................................................................................................... 2
5
MAINTENANCE INSTRUCTIONS .................................................................................................. 3
5.1
RECOMMENDED PERIODIC SCHEDULED SERVICING TASKS.................................................................... 3
5.2
RECOMMENDED PERIODIC SCHEDULED PREVENTIVE MAINTENANCE TESTS/CHECKS .......................... 3
5.3
RECOMMENDED PERIODIC SCHEDULED INSPECTIONS ............................................................................ 3
5.3.1
System Processor............................................................................................................................. 3
5.3.2
Standard TREND Lamp or Optional Split Lamp and Download Port............................................ 4
5.3.3
Pitot / Static Transducers................................................................................................................ 5
5.3.4
Outside Air Temperature Probe...................................................................................................... 7
5.3.5
Torque Transducer.......................................................................................................................... 7
5.3.6
Particle Separator Switch ............................................................................................................... 8
5.3.7
J1, J2, and J3 Harnesses................................................................................................................. 8
5.3.8
System Test ...................................................................................................................................... 8
5.4
RECOMMENDED PERIODIC STRUCTURAL INSPECTIONS .......................................................................... 9
5.4.1
System Processor............................................................................................................................. 9
5.4.2
Standard TREND Lamp or Optional Split Lamp and Download Port............................................ 9
5.4.3
Pitot / Static Transducers.............................................................................................................. 11
5.4.4
Outside Air Temperature Probe.................................................................................................... 12
5.4.5
Torque Transducer........................................................................................................................ 13
5.4.6
Particle Separator Switch ............................................................................................................. 14
6
SYSTEM TROUBLESHOOTING.................................................................................................... 15
7
REMOVAL AND REPLACEMENT INFORMATION ................................................................. 15
7.1
7.2
7.3
7.4
7.5
7.6
7.7
PROCESSOR REMOVAL/REPLACEMENT ................................................................................................. 15
TREND SWITCH OR ENGINE/TREND SPLIT LAMP REMOVAL/REPLACEMENT ................................. 15
DOWNLOAD PORT REMOVAL/REPLACEMENT ....................................................................................... 16
PITOT/STATIC TRANSDUCER REMOVAL/REPLACEMENT ...................................................................... 16
OAT REMOVAL/REPLACEMENT ............................................................................................................ 17
TORQUE TRANSDUCER REMOVAL/REPLACEMENT ............................................................................... 17
PARTICLE SEPARATOR SWITCH REMOVAL/REPLACEMENT .................................................................. 17
8
SPECIAL INSPECTION REQUIREMENTS ................................................................................. 19
9
APPLICATION OF PROTECTIVE TREATMENTS.................................................................... 19
- iiiADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Aircraft Company
10
ADAS+
ADAS-G-260-1/A
Model 208 Series
DATA................................................................................................................................................... 19
10.1 PARTS LIST ............................................................................................................................................ 19
10.1.1 ADAS+ by Parts Kits .................................................................................................................... 19
10.1.2 Components by Kit ........................................................................................................................ 19
11
LIST OF SPECIAL TOOLS.............................................................................................................. 23
12
FOR COMMUTER CATEGORY AIRCRAFT .............................................................................. 23
13
RECOMMENDED OVERHAUL PERIODS .................................................................................. 23
14
AIRWORTHINESS LIMITATIONS ............................................................................................... 23
15
DIAGRAMS ........................................................................................................................................ 24
15.1
15.2
15.3
16
POWER/ SENSOR CABLE J1, 15 PIN S KEYED CONNECTOR ................................................................... 24
SENSOR CABLE J2, 15 PIN SA KEYED CONNECTOR .............................................................................. 25
COCKPIT TREND / SENSOR CABLE, J3, 37 PIN S KEYED CONNECTOR .................................................. 26
WIRING DIAGRAM ......................................................................................................................... 28
16.1
16.2
16.3
16.4
16.5
16.6
16.7
16.8
16.9
ADAS+ CONNECTION CHART – CESSNA MODEL 208 SERIES .............................................................. 28
ADAS+ INTERCONNECT SCHEMATIC – NO SUPPLIED TORQUE TRANSDUCERS ................................... 30
ADAS+ INTERCONNECT SCHEMATIC – SUPPLIED TORQUE TRANSDUCERS ......................................... 31
ADAS+ INTERCONNECT SCHEMATIC (SPLIT LAMP OPTION) – NO SUPPLIED TORQUE TRANSDUCERS32
ADAS+ INTERCONNECT SCHEMATIC (SPLIT LAMP OPTION) – SUPPLIED TORQUE TRANSDUCERS ..... 33
ADAS+ SCHEMATIC (GARMIN G620 OPTION) – NO SUPPLIED TORQUE TRANSDUCERS ..................... 34
ADAS+ SCHEMATIC (GARMIN G620 OPTION) – SUPPLIED TORQUE TRANSDUCERS ........................... 35
ADAS+ SCHEMATIC (GARMIN G620 / SPLIT LAMP OPTION) – NO SUPPLIED TORQUE TRANSDUCERS
.............................................................................................................................................................. 36
ADAS+ SCHEMATIC (GARMIN G620 / SPLIT LAMP OPTION) – SUPPLIED TORQUE TRANSDUCERS ..... 37
LIST OF FIGURES
FIGURE A- 1: ADAS+ MOUNTING ............................................................................................................................................ 3
FIGURE A- 2: STANDARD TREND SWITCH OR OPTIONAL ENGINE/TREND SPLIT LAMP ......................................................... 4
FIGURE A- 3: TYPICAL MOUNTING LOCATION FOR DOWNLOAD PORT...................................................................................... 4
FIGURE A- 4: STANDARD TREND SWITCH/FAULT LAMP CONNECTOR WIRING ....................................................................... 5
FIGURE A- 5: OPTIONAL ENGINE/TREND SPLIT LAMP CONNECTOR WIRING ........................................................................ 5
FIGURE A- 6: DOWNLOAD PORT CONNECTOR WIRING ............................................................................................................. 5
FIGURE A- 7: PITOT / STATIC TRANSDUCER INSTALLATION ...................................................................................................... 6
FIGURE A- 8: PITOT/STATIC WIRING ......................................................................................................................................... 6
FIGURE A- 9: OAT PROBE WIRING ........................................................................................................................................... 7
FIGURE A- 10: TORQUE TRANSDUCER WIRING ......................................................................................................................... 7
FIGURE A- 11: PROCESSOR MOUNTING CONFIGURATION ......................................................................................................... 9
FIGURE A- 12: STANDARD TREND SWITCH OR ENGINE/TREND SPLIT LAMP ...................................................................... 10
FIGURE A- 13: TYPICAL MOUNTING LOCATION FOR DOWNLOAD PORT.................................................................................. 10
FIGURE A- 14: PITOT/STATIC INSTALLATION (SIDE VIEW) ..................................................................................................... 11
FIGURE A- 15: OAT PROBE ILLUSTRATION ............................................................................................................................ 12
FIGURE A- 16: TORQUE TRANSDUCER INSTALLATION CONFIGURATION ................................................................................. 13
FIGURE A- 17: PARTICLE SEPARATOR SWITCH INSTALLATION ............................................................................................... 14
FIGURE A- 18: PARTICLE SEPARATOR SWITCH (EXPLODED VIEW) ......................................................................................... 18
FIGURE A- 19: WIRING SCHEMATIC– NO SUPPLIED TORQUE TRANSDUCERS.......................................................................... 30
FIGURE A- 20: WIRING SCHEMATIC – SUPPLIED TORQUE TRANSDUCERS ............................................................................... 31
FIGURE A- 21: WIRING SCHEMATIC (SPLIT LAMP OPTION) – NO SUPPLIED TORQUE TRANSDUCERS ..................................... 32
- ivADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Aircraft Company
ADAS+
ADAS-G-260-1/A
Model 208 Series
FIGURE A- 22: WIRING SCHEMATIC (SPLIT LAMP OPTION) – SUPPLIED TORQUE TRANSDUCER ............................................. 33
FIGURE A- 23: WIRING SCHEMATIC (GARMIN G620 OPTION) – NO SUPPLIED TORQUE TRANSDUCERS ................................. 34
FIGURE A- 24: WIRING SCHEMATIC (GARMIN G620 OPTION) – SUPPLIED TORQUE TRANSDUCERS ....................................... 35
FIGURE A- 25: WIRING SCHEMATIC (GARMIN G620 / SPLIT LAMP OPTION) – NO SUPPLIED TORQUE TRANSDUCERS............ 36
FIGURE A- 26: WIRING SCHEMATIC (GARMIN G620 / SPLIT LAMP OPTION) – SUPPLIED TORQUE TRANSDUCERS.................. 37
LIST OF TABLES
TABLE A- 1: ADAS+ CONNECTION CHART ............................................................................................................................ 29
- vADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Aircraft Company
ADAS+
ADAS-G-260-1/A
Model 208 Series
1 INTRODUCTION
1.1
Scope
The purpose of this document is to provide users of this product with P&W Engine Services approved
Instruction for Continued Airworthiness for the ADAS +. Any deviation from the procedures described within
this document could result in a failure of the product to perform properly and could possibly result in damage to
other systems of the aircraft.
1.2
Applicability
This document applies to aircraft that are altered by the installation of a P&W Engine Services’ ADAS+,
EMU-A-010-3
1.3
Definitions and Abbreviations
ADAS+ – Aircraft Data Acquisition System Plus
AML – Approved Model List
ICA – Instructions for Continued Airworthiness
MLP – Monitor Link Program
STC – Supplemental Type Certificate
1.4
Precautions
This section not applicable
1.5
Units of Measure
This section not applicable
1.6
Referenced Publications
ADAS-G-260-1 generic Instructions for Continued Airworthiness
1.7
Distribution
These Instructions for Continued Airworthiness are to be furnished with ADAS+ engine trend monitors for
Cessna Aircraft Model 208 Series aircraft and is to become part of the permanent aircraft record upon
installation.
1
ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Aircraft Company
ADAS+
ADAS-G-260-1/A
Model 208 Series
2 DESCRIPTION
A detailed description of the system can be found in ADAS-G-260-1, ADAS+ Instructions for Continued
Airworthiness, Section 2.
3 CONTROL AND OPERATION INFORMATION
A detailed description of the control and operation of the system can be found in ADAS-G-260-1, ADAS+
Instructions for Continued Airworthiness, Section 3.
4 SERVICING INFORMATION
This section is not applicable
2
ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Aircraft Company
ADAS+
ADAS-G-260-1/A
Model 208 Series
5 MAINTENANCE INSTRUCTIONS
Scheduled Maintenance Program tasks are to be added to the aircraft operator’s appropriate maintenance
program as follows:
5.1
Recommended Periodic Scheduled Servicing Tasks
The P&W Engine Services ADAS+ has been designed with the latest solid-state technology. The only
component that has a limited life span is the internal battery. This battery, under normal operating conditions, is
expected to last 10 years. If the battery is discharged, the processor must be returned to P&W Engine Services
for battery replacement.
5.2
Recommended Periodic Scheduled Preventive Maintenance Tests/Checks
None Required
5.3
Recommended Periodic Scheduled Inspections
The following information should be used to insure the continuous and trouble free operation of the ADAS +.
These inspection steps should be followed during every 200-hour inspection.
These instructions describe general inspection methods. All inspections should look for general deterioration of
hoses, brackets, and any other component of the ADAS+ system. Other than the specific periodic inspections,
maintenance is on-condition, and there is no other scheduled maintenance.
5.3.1
System Processor
The ADAS+ processor is located at approximately FS 70 in the engine compartment on the lower engine
mounting tube. For the System Processor installation (Figure A- 1), perform the following inspections:

010 Inspect processor for security to the mounting bracket.

020 Inspect electrical ground strap for proper connection.

030 Inspect electrical connectors for proper connection to ADAS+ processor.
Figure A- 1: ADAS+ Mounting
3
ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Aircraft Company
5.3.2
ADAS+
ADAS-G-260-1/A
Model 208 Series
Standard TREND Lamp or Optional Split Lamp and Download Port
The ADAS+ has a standard TREND switch / fault lamp or an optional Engine/Trend Split Lamp that is installed
in the cockpit (Figure A- 5) and consist of a 75" x .75" square Push-to-test lamp for standard TREND switch /
fault lamp or .68" x .68" for the optional Engine/Trend Split Lamp. The ADAS+ also has a download port
installed in the cockpit (Figure A- 6) and consist of a 19/32" serial download connector.
For the TREND switch / fault lamp or the optional ENGINE/TREND Split Lamp and download port
installations (Figure A- 2 and Figure A- 3), perform the following inspections:

010 Verify that the proper connectors are in place. Refer to Figure A- 4, Figure A- 5, and Figure A- 6.

020 Inspect electrical connectors for loose connections.

030 Inspect wiring for proper routing and security.

040 Inspect wiring for signs of interference and wire chaffing.
Figure A- 2: Standard Trend Switch or Optional ENGINE/TREND Split Lamp
Figure A- 3: Typical Mounting Location for Download Port
4
ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Aircraft Company
ADAS+
ADAS-G-260-1/A
Model 208 Series
Figure A- 4: Standard TREND Switch/Fault Lamp Connector Wiring
Figure A- 5: Optional ENGINE/TREND Split Lamp Connector Wiring
Figure A- 6: Download Port Connector Wiring
5.3.3
Pitot / Static Transducers
ADAS + has the capability of measuring airspeed and altitude for event monitoring or trend monitoring. Both
pitot and static transducers are plumbed (Figure A- 7) into the aircraft’s existing pitot and static systems. Both
transducers are mounted in tandem under the instrument panel on the co-pilots side. They are accessed from the
cockpit by removing the control column cover assembly and glove compartment box.
5
ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Aircraft Company
ADAS+
ADAS-G-260-1/A
Model 208 Series
Figure A- 7: Pitot / Static Transducer Installation
To insure the integrity of the system, perform the following inspection:

010 Verify that the proper connectors are in place. Refer to Figure A- 8.

020 Inspect electrical connectors for loose connections.

030 Inspect wiring for proper routing and security.

040 Inspect wiring for signs of interference and wire chaffing.
Figure A- 8: Pitot/Static Wiring
6
ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Aircraft Company
5.3.4
ADAS+
ADAS-G-260-1/A
Model 208 Series
Outside Air Temperature Probe
The temperature probe is mounted on the underside of the aircraft’s engine cowling to provide the processor
with OAT data.
For the OAT probe installation (Figure A- 9) perform the following inspection:

010 Inspect wiring for proper routing and security.

020 Inspect wiring for signs of interference and wire chaffing.
Figure A- 9: OAT Probe Wiring
5.3.5
Torque Transducer
The ADAS + obtains the engine torque level by using two (2) 0 – 150 PSIG transducers installed in the torque
pressure lines.

010 Verify that the proper connectors are in place. Refer to Figure A- 10.

020 Inspect electrical connectors for loose connections.

030 Inspect wiring for proper routing and security.

040 Inspect wiring for signs of interference and wire chaffing.
Figure A- 10: Torque Transducer Wiring
7
ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Aircraft Company
5.3.6
ADAS+
ADAS-G-260-1/A
Model 208 Series
Particle Separator Switch
The Particle Separator Switch is installed onto the Particle Separator Actuating Rod controlled by the pilot
inside the cockpit. The Particle Separator Switch is installed at Fuselage Station 77.0 on the left side of the
engine compartment.
For the Particle Separator Switch Installation (Figure A- 17), perform the following inspection:

010 Inspect Particle Separator Switch wiring for proper routing and security.

020 Inspect Particle Separator Switch wiring for signs of interference and wire chaffing.
5.3.7
J1, J2, and J3 Harnesses

010 Inspect harness for proper routing and security.

020 Inspect harness for signs of interference and wire chaffing.
5.3.8

System Test
010 With the aircraft battery connected and master switch on, verify that the TREND lamp or the optional
ENGINE/TREND Split Lamp illuminates, indicating system boot-up. After approximately 5 seconds,
the TREND lamp or the ENGINE/TREND Split Lamp will extinguish and the TREND Lamp will do one
of the following:

Remain extinguished (NORMAL STATE)

Flash (MAINTENANCE OR CAUTION STATE)

Illuminate Solid (FAULT STATE)
If the processor does NOT go into NORMAL STATE, retrieve the log data, and troubleshoot the
system.

020 Turn battery switch off.
8
ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Aircraft Company
5.4
ADAS+
ADAS-G-260-1/A
Model 208 Series
Recommended Periodic Structural Inspections
The following information should be used to insure the continuous and trouble free operation of the ADAS +.
These inspection steps should be followed during every 200-hour inspection.
These instructions describe general inspection methods. All inspections should look for general deterioration of
hoses, brackets, and any other component of the ADAS+ system. Other than the specific periodic inspections,
maintenance is on-condition, and there is no other scheduled maintenance.
5.4.1
System Processor
For the System Processor installation (Figure A- 11), perform the following inspections:

010 Inspect processor for security to the mounting bracket.

020 Inspect mounting bracket for cracking.
Figure A- 11: Processor Mounting Configuration
5.4.2
Standard TREND Lamp or Optional Split Lamp and Download Port
For the Standard TREND switch / fault lamp or the optional ENGINE/TREND Split Lamp and download port
installations (Figure A- 12 and Figure A- 13), perform the following inspections:

010 Inspect Standard TREND Switch / Fault Lamp or Optional ENGINE/TREND Split Lamp for proper
mounting.

020 Inspect Download Port for proper mounting.
9
ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Aircraft Company
ADAS+
ADAS-G-260-1/A
Model 208 Series
Figure A- 12: Standard Trend Switch or ENGINE/TREND Split Lamp
Figure A- 13: Typical Mounting Location for Download Port
10
ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Aircraft Company
5.4.3
ADAS+
ADAS-G-260-1/A
Model 208 Series
Pitot / Static Transducers
For the Pitot/Static transducer installation, perform the following inspection:

010 Inspect and make sure that transducer mountings are secure. Refer to Figure A- 14.

020 Inspect Adel™ clamps for deterioration.

030 Inspect fittings to make sure they are secure.
Figure A- 14: Pitot/Static Installation (Side View)
11
ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Aircraft Company
5.4.4
ADAS+
ADAS-G-260-1/A
Model 208 Series
Outside Air Temperature Probe
For the OAT probe installation (Figure A- 15), perform the following inspection:

010 Inspect OAT probe assembly form proper mounting.

020 Inspect aircraft skin around OAT probe for signs of cracking.

030 Perform continuity test to ensure proper bonding with the aircraft skin.
Figure A- 15: OAT Probe Illustration
12
ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Aircraft Company
5.4.5
ADAS+
ADAS-G-260-1/A
Model 208 Series
Torque Transducer
The ADAS + obtains the engine torque level by using two (2) 0 – 150 PSIG transducers installed in the torque
pressure lines. The torque transducer installation is referenced in illustration Figure A- 16.
To insure the integrity of the system, perform the following inspection:

010 Inspect and make sure that transducer mounting is secure.

020 Inspect Adel™ clamps for deterioration.

030 Inspect pressure lines for signs of deterioration.

040 Inspect fittings to make sure they are secure.

050 Inspect each transducer for signs of fluid leaking.
Figure A- 16: Torque Transducer Installation Configuration
13
ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Aircraft Company
5.4.6
ADAS+
ADAS-G-260-1/A
Model 208 Series
Particle Separator Switch
For the Particle Separator Switch installation (Figure A- 17), perform the following inspection:

010 Inspect and make sure that Particle Separator Switch Mounting Plate is secure.

020 Inspect Particle Separator Switch Mounting and Support Plate for cracking.

030 Inspect and make sure that the Particle Separator Magnetic Switches are installed properly and
secure.

040 Inspect Adel™ clamps for deterioration.
Figure A- 17: Particle Separator Switch Installation
14
ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Aircraft Company
ADAS+
ADAS-G-260-1/A
Model 208 Series
6 SYSTEM TROUBLESHOOTING
Detailed troubleshooting for the system can be found in ADAS-G-260-1, ADAS+ Instructions for Continued
Airworthiness, Section 6.
7 REMOVAL AND REPLACEMENT INFORMATION
7.1
Processor Removal/Replacement
NOTE: Insure that power is removed from the aircraft and the battery is disconnected

010 Disconnect the J1, J2, and J3 wiring harnesses from the processor.

020 Disconnect the ground strap between the processor mounting stud and the aircraft chassis.

030 Disassemble the ADAS+ processor from the mounting bracket shown in Figure A- 11.

040 Assemble the ADAS+ processor to the mounting bracket shown in Figure A- 11. Ensure that the
processor does not interfere with wiring or controls.
INSTALLATION CAUTION:

Excessive torque on the processor-mounting studs can deform the shock mounts. The locking
nut should be tightened to the point of contact with the shock mount.

050 Install ground strap between one of the processor mounting studs and the aircraft chassis.

060 Connect wiring harnesses J1, J2, and J3 to the processor.
070 Perform configuration and calibration per instructions in ADAS+ Installation Manual ADAS-G-010-1,
System Configuration and Calibration.
7.2
TREND Switch or ENGINE/TREND Split Lamp Removal/Replacement

010 Insure that power is removed from the aircraft and the battery is disconnected.

020 Disconnect TREND Switch or ENGINE/TREND Split Lamp ConXall™ connector under instrument
panel.

030 Remove TREND Switch or ENGINE/TREND Split Lamp by squeezing locking springs on sides of
switch and pushing the switch thru the hole in the instrument panel.

040 Replace TREND switch or ENGINE/TREND Split Lamp and reconnect ConXall™ connector.
15
ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Aircraft Company
7.3
ADAS+
ADAS-G-260-1/A
Model 208 Series
Download Port Removal/Replacement

010 Insure that power is removed from the aircraft and the battery is disconnected.

020 Remove nut and washer from Download Port connector.

030 Disconnect Download Port ConXall™ connector. Remove Download Port.

040 Install Download Port into Instrument Panel and secure in place with washer and nut using Loctite®
Blue on the threads of the download port.

050 Reconnect ConXall™ connector.
7.4
Pitot/Static Transducer Removal/Replacement
NOTE: A Pitot/Static Leak test must be done after the replacement of a transducer

010 Insure that power is removed from the aircraft and the battery is disconnected.

020 Refer to Figure A- 14. Disconnect Pitot hose (990-00028) from adaptor (960-00002).

030 Disconnect Tygon tubing from the Pitot Transducer.

040 Disconnect Static hose (990-00028) from “T” pipe (AN917-2D).

050 Remove the pitot and static transducers by removing the bolt, washer, and nut which secures the
two transducers to the supplied plate (ADAS-D-018-1) and clamp (ADAS-D-019-1).

060 Remove the adapter, (960-00002) from the Pitot Transducer if you are replacing the Pitot
Transducer or the “T” pipe (AN917-2D) from the Static Transducer if you are replacing the Static
Transducer.


070 Replace the appropriate transducer as necessary.

080 Apply Teflon® tape to the Pitot Transducer threads and install adapter (960-00002) or apply Teflon®
tape to the Static Transducer threads and install “T” pipe (AN917-2D).
090 Attach the pitot and static transducers to the supplied plate (ADAS-D-018-1), clamp (ADAS-D-0191), clamp (MS21919WDG26), bolt (AN3-5A), washer (AN960-10) and lock nut (AN365-1032A).

100 Connect the Pitot hose (990-00028) to the adaptor (960-00002).

110 Connect the Static hose (990-00028) to the “T” pipe (AN917-2D).

120 Connect Tygon tubing to the Pitot Transducer.


130 Secure and tighten all hoses and fittings.
140 Perform Pitot/Static calibration per instructions in ADAS+ Installation Manual ADAS-G-010-1,
System Configuration and Calibration.
16
ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Aircraft Company
7.5
ADAS+
ADAS-G-260-1/A
Model 208 Series
OAT Removal/Replacement

010 Insure that power is removed from the aircraft and the battery is disconnected.

020 Remove safety wire from OAT jam nut (TWIN-D-061-1).

030 Remove OAT jam nut.

040 Remove temperature probe from hole.

050 Insert new temperature probe into the hole and install washers (AN960-816L), “O” ring (AN6227B10) and jam nut (TWIN-D-061-1).

060 Tighten and safety wire the jam nut to the bolt P/N AN3-5A.
NOTE: Be sure not to over tighten the jam nut which could damage the O-Ring seal.
070 Apply a bead of sealant (ProSeal PR1422 or equivalent) around edge of doubler after installation
and smooth to produce a filleted profile.



7.6
080 Apply a bead of sealant (ProSeal PR1422 or equivalent) around the inner and outer edges of the
OAT probe after installation and smooth to produce a filleted profile.
090 Perform OAT calibration per instructions in ADAS+ Installation Manual ADAS-G-010-1, System
Configuration and Calibration.
Torque Transducer Removal/Replacement
NOTE: A Leak test must be done after the replacement of a transducer

010 Insure that power is removed from the aircraft and the battery is disconnected.

020 Referring to Figure A- 16, remove the “T” swivel (960-00006) from the adapter fitting (960-00015).

030 Remove the adapter (960-00015) from the transducer.

040 Remove the transducer from the clamp (MS21919WCJ14).

050 Replace the transducer.

060 Using Teflon® tape, install and torque the 0 – 150 PSIG transducers (750-00005) into the adapter
fitting (960-00015).

070 Connect the torque transducer / adapter fitting assembly to the “T” swivel (960-00006).

080 Secure / torque all lines and fittings per the manufacturer’s recommendations.

090 Perform Torque calibration per instructions in ADAS+ Installation Manual ADAS-G-010-1, System
Configuration and Calibration.
7.7
Particle Separator Switch Removal/Replacement

010 Insure that power is removed from the aircraft and the battery is disconnected.

020 Remove the nuts (P/N 910-00001), washers (P/N AN960-4), and screws (P/N MS35206-220) from
the clamps that attach the Magnetic Flange Sensor. Refer to Figure A- 18.

030 Remove Magnetic Flange Sensor (P/N 700-00016).

040 Remove the washers (P/N AN960-4) and screws (P/N MS35206-220) that attach the Magnetic
Sensor Switch to the Switch Plate assembly.

050 Remove the clamps to where the wire splices into the wire bundle.

060 Disconnect the splices and remove the Magnetic Sensor Switch (P/N 700-00015) form the airplane.

070 Replace Magnetic Sensor Switch (P/N 700-00015) and connect to the wire splices.
17
ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Aircraft Company



ADAS+
ADAS-G-260-1/A
Model 208 Series
080 Put the wire into the clamps and install the screws into the clamps.
090 Install the screws (P/N MS35206-220) and washers (P/N AN960-4) that attach the Magnetic Sensor
Switch to the Switch Plate assembly.
100 Install the screws (P/N MS35206-220), washers (P/N AN960-4), and nuts (P/N 910-00001) into the
clamps and attach the Magnetic Flange Sensor (P/N 700-00016).
NOTE: Additional washers may be installed between switch components and mounting structure as
required achieving correct alignment. The “Must Operate” distance is 5.71mm and “Release”
distance is 20.32mm.
Figure A- 18: Particle Separator Switch (Exploded View)
18
ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Aircraft Company
ADAS+
ADAS-G-260-1/A
Model 208 Series
8 SPECIAL INSPECTION REQUIREMENTS
This section is not applicable
9 APPLICATION OF PROTECTIVE TREATMENTS
This section is not applicable
10 DATA
10.1
Parts List
For Cessna Aircraft Company Model Series 208 Series:
The parts listed below consist of the installation kits for the ADAS+ system for the Cessna Model 208 Series.
Assembly kit numbers are listed in section 10.1.1 and individual components are detailed by kit numbers in
section 10.1.2.
10.1.1
ADAS+ by Parts Kits
For Cessna Aircraft Company Model Series 208:
Qty
Processor Assembly
Wiring Harness Kit
Engine Torque Kit
Aircraft OAT Kit
Aircraft Pitot Pressure Kit
Aircraft Static Pressure Kit
Cockpit Fault Lamp Assembly Kit
Cockpit Split Lamp and Download Port Kit (OPTIONAL)
Particle Separator Switch Kit
Additional Installation Materials Kit
*Cable Assy, ADAS+ to Garmin G620 (OPTIONAL)
*Requires ADAS+ Software Version 5.1.0 or Greater
*Requires G620 Software Version 6.10 or Greater
10.1.2
P/N ADAS-K-010-2
Weight
1
1
1
1
1
1
1
ADAS-K-017-1
ADAS-K-014-1
ADAS-K-013-1
DPU-K-032-4
DPU-K-034-4
DPU-K-033-5
DPU-K-046-3
1
ADAS-K-047-1
1
1
1
ADAS-K-070-1
EMU-K-023-4
ADAS-C-072-1
1.41 Lbs
5.20 Lbs
1.41 Lbs
0.39 Lbs
0.77 Lbs
0.77 Lbs
0.20 Lbs
0.20 Lbs
1.04 oz
0.40 Lbs
Components by Kit
For Cessna Aircraft Company Model Series 208:
PROCESSOR ASSEMBLY KIT
Processor
Mounting Bracket
Clamp, Processor Mounting
Shock Mounts, Lord
Washer, Processor Mount
Nut, Locking, Processor Mount
Clamp, “U” Bolt
Nut, Locking, Mount
Washer, Mount
Strap, Ground
Terminal End, #10
Terminal End, #6
ADAS-K-017-1
EMU-A-010-3
ADAS-D-029-1
ADAS-D-030-1
990-00020
920-00006
MS21042-06
NAS-3103-9-10
(Alternate: ADAS-D-016-1)
MS21042-3
AN960-10L
DPU-C-050-3
400-00030
400-00029
Qty 1
Qty 1
Qty 2
Qty 4
Qty 4
Qty 4
Qty 2
Qty 4
Qty 4
Qty 1
Qty 2
Qty 2
19
ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Aircraft Company
ADAS+
ADAS-G-260-1/A
Model 208 Series
WIRING HARNESS KIT
ADAS-K-014-1
Cable Assembly, J1
Cable Assembly, J2
Cable Assembly, J3
EMU-C-025-1
ADAS-C-011-1
ADAS-C-012-1
Qty 1
Qty 1
Qty 1
ENGINE TORQUE KIT
EMU-K-013-1
Transducer, 0 - 100 PSIG
Adapter, “O” Ring / 37 Flare
Fitting, “T” Swivel
Hose, Pressure, 12”
Clamp
Clamp
Transducer Harness
750-00005
960-00015
960-00006
AE3663162E0120
MS21919WCJ14
MS21919WCJ16
750-00006
Qty 2
Qty 2
Qty 2
Qty 2
Qty 2
Qty 2
Qty 2
AIRCRAFT OAT PROBE KIT
Probe, Temperature
Nut, Jam
Washer
Seal, “O” Ring
Bolt, Drilled
Doubler, OAT Probe
Washer
Nut, Fiber Lock
Connector, ConXall™
Connector, ConXall™
DPU-K-032-4
TWIN-A-050-2
TWIN-D-061-1
AN960-816L
AN6227B-10
AN3H-4A
DPU-D-047-1
AN960-10
AN365-1032A
400-00026
400-00027
Qty 1
Qty 1
Qty 2
Qty 1
Qty 1
Qty 1
Qty 1
Qty 1
Qty 1
Qty 1
AIRCRAFT PITOT PRESSURE KIT
Transducer, 0-3 PSID
Clamp, Inlet Pressure Transducer
Bolt, 10-32
Nut, Locking, 10-32
Washer, #10
Plate, Mounting
Clamp
Feed Through
Adapter, Pipe – 37 Flare
Hose, 306
Fitting, Hose ¼”
“T”, Barbed ¼”
DPU-K-034-4
750-00001
MS21919WDG26
AN3-5A
AN365-1032A
AN960-10
ADAS-D-018-1
ADAS-D-019-1
ADAS-D-033-1
960-00002
990-00028
960-00027
960-00028
Qty 1
Qty 1
Qty 1
Qty 1
Qty 2
Qty 1
Qty 1
Qty 1
Qty 1
Qty 1
Qty 1
Qty 1
20
ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Aircraft Company
ADAS+
ADAS-G-260-1/A
Model 208 Series
AIRCRAFT STATIC PRESSURE KIT
Transducer, 0-15 PSIA
Clamp, Nacelle Static Transducer
Bolt, 10-32
Nut, Locking, 10-32
Washer, #10
Fitting, ¼ ″ Tube to 1/8 ″ Male thrd
Tubing, Tygon 1/8 ″
Insert
Bushing ¼ - 1/8 AL
“T”, 1/4'” Thread AL
Nipple, Flared Tube ¼” Tube
Hose, 306
Fitting, Hose ¼”
“T”, Barbed ¼”
DPU-K-033-5
750-00002
MS21919WDG16
AN3-5A
AN365-1032A
AN960-10
960-00024
990-00030
920-00010
AN912-1D
AN917-2D
AN816-4-4D
990-00028
960-00027
960-00028
Qty 1
Qty 1
Qty 1
Qty 1
Qty 1
Qty 1
Qty 1 Ft
Qty 1
Qty 1
Qty 1
Qty 1
Qty 1
Qty 1
Qty 1
COCKPIT FAULT LAMP ASSEMBLY
Assy., Cockpit Fault Lamp
Lens
Connector, 6 Pin Female
Assy., Download Port
Cover
Connector, 6 Pin, Male
Screw, Pan Head, 4-40
Washer
Nut, Fiber Lock
DPU-K-046-3
DPU-A-043-1
TREND-D-041-1
400-00026
DPU-A-044-1
990-00031
400-00027
900-00009
AN960-4
910-00001
Qty 1
Qty 1
Qty 1
Qty 1
Qty 1
Qty 1
Qty 1
Qty 1
Qty 1
COCKPIT SPLIT LAMP AND DOWNLOAD PORT KIT (OPTIONAL)
Assy., Cockpit Split Lamp
Connector, 6 Pin Female
Assy., Download Port
Connector, 6 Pin, Male
Cover, Receptacle
Screw, Pan Head, 4-40
Washer
Nut, Fiber Lock
ADAS-A-043-1
400-00026
DPU-A-044-1
400-00027
990-00031
900-00009
AN960-4
910-00001
ADAS-K-047-1
Qty 1
Qty 1
Qty 1
Qty 1
Qty 1
Qty 1
Qty 1
Qty 1
PARTICLE SEPARATOR SWITCH KIT
Sensor Magnetic SPST/NO Flange
Magnet flange Mount
Screw, #4-40 X 7/8L
Mtg Plate, Particle Separator Switch
Clamp, Loop, Cush, 0.25” BLK
Nut, LCKG, SS, 4-40”
Washer #4, Flat
ADAS-K-070-1
700-00015
700-00016
MS35206-220
ADAS-D-069-1
MS21919WDG8
910-00001
AN960-4
Qty 1
Qty 1
Qty 4
Qty 1
Qty 2
Qty 4
Qty 20
21
ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Aircraft Company
ADAS+
ADAS-G-260-1/A
Model 208 Series
ADDITIONAL MATERIAL INSTALLATION KIT
Crimp Lug, Alumel
Crimp Lug, Chromel
Breaker, 1 Amp
Fuse, 1.0 Amp
Holder, Fuse
Terminal, ½”
400-00031
400-00032
990-00032
990-00033
DPU-C-057-1
400-00033
EMU-K-023-4
Qty 1
Qty 1
Qty 1
Qty 1
Qty 1
Qty 2
*CABLE ASSY, ADAS+ TO GARMIN G620 (OPTIONAL)
ADAS-C-072-1
*Requires ADAS+ Software Version 5.1.0 or Greater
*Requires G620 Software Version 6.10 or Greater
22
ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Aircraft Company
ADAS+
ADAS-G-260-1/A
Model 208 Series
11 LIST OF SPECIAL TOOLS
ConXall™ connectors are installed in this system. The following tools are recommended by the vendor for use
with these connectors (vendor P/Ns): Insertion Bit (356-20), Pin Removal Bit (356-201), Socket Removal Bit
(356-202), Handle (356-1), Crimp Tool (359-21), Locator (357-122). The vendor address is: ConXall
Corporation., 601 East Wildwood, Villa Park, IL 60181.
12 FOR COMMUTER CATEGORY AIRCRAFT
For Commuter Category Aircraft, electrical load data applicable for each system and aircraft weight and balance
must be identified. The ADAS+ has a current draw of 300 milliamps at 28V DC. The ADAS+ kit weighs 10.55
lbs.
13 RECOMMENDED OVERHAUL PERIODS
This section is not applicable
14 AIRWORTHINESS LIMITATIONS
The Airworthiness Limitations section is FAA approved and specifies maintenance required under §§ 43.16 and
91.403 of the Federal Aviation Regulations unless an alternative program has been FAA approved. There are no
airworthiness limitations for this equipment.
23
ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Aircraft Company
ADAS+
ADAS-G-260-1/A
Model 208 Series
15 DIAGRAMS
15.1
Power/ Sensor Cable J1, 15 Pin S Keyed Connector
INSTALLATION CAUTION:

Before making any wiring connections, verify all connection locations with the aircraft
manufacturer’s wiring diagram manuals.
 Perform a continuity check on all wires before final connection.
 Route all harnesses along existing harnesses wherever possible.

Connector
Pin
Cables may be marked with shrink-on labels near the terminal end. When you shorten a
cable behind a label, be sure to re-label it.
Harness
Wire Color
Signal Name
Wired To
Refer to Section 6
Pitot (Signal +)
Pitot/Static (5 VDC)
Pitot/Static (Ground)
Static (Signal +)
GRN Wire Pitot Transducer
RED Wire Pitot/Static Transducer
BLK Wire Pitot/Static Transducer
GRN Wire Static Transducer
28 VDC Bus Power
Bus Power, Supplied 1 Amp Breaker
4 COND CABLE
J1
J1
J1
J1
A
B
N
D
WHT/ORG
WHT
WHT/BLU
WHT/GRN
1 COND CABLE
J1 F
WHT
2 COND CABLE
J1 H
WHT
28 VDC Battery Power
Battery Power, 1 Amp Fuse
J1 G
WHT/BLU
System Ground
Aircraft Ground
J1
J1
J1
J1
J1
J1
J1
J1
Unused
Unused
Unused
Unused
Unused
Unused
Unused
Unused
J
K
C
E
L
M
R
P
24
ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Aircraft Company
15.2
ADAS+
ADAS-G-260-1/A
Model 208 Series
Sensor Cable J2, 15 Pin SA Keyed Connector
INSTALLATION CAUTION:
 Before making any wiring connections, verify all connection locations with the aircraft
manufacturer’s wiring diagram manuals.
 Perform a continuity check on all wires before final connection.
 Route all harnesses along existing harnesses wherever possible.
 Cables may be marked with shrink-on labels near the terminal end. When you shorten a
cable behind a label, be sure to re-label it.
Connector
Pin
Harness
Wire Color
Signal Name
Wired To
Refer to Section 6
4 COND CABLE
J2 A
WHT
J2 B
WHT/ORG
J2 C
WHT/BLU
J2 F
WHT/GRN
Eng Torque
Eng Torque
Eng Torque
Eng Torque
RED Wire Both Torque Transducers
GRN Wire High Torque Transducer
BLK Wire Both Torque Transducers
GRN Wire Low Torque Transducer
2 COND CABLE
J2 D
WHT
J2 H
WHT/BLU
Eng Ng Spd (Sig +)
Eng Ng Spd (Sig –)
N1 Tachometer +
N1 Tachometer –
2 COND CABLE
J2 E
WHT
J2 N
WHT/BLU
Eng Np Spd (Sig +)
Eng Np Spd (Sig –)
Np Tachometer +
Np Tachometer –
THERMOCOUPLE
J2 J
RED
J2 K
YEL
Eng ITT (Alumel –)
Eng ITT (Chromel +)
ITT Engine Mounting Pad –
ITT Engine Mounting Pad +
2 COND CABLE
J2 G
WHT
J2 R
WHT/BLU
Fuel Flow (Sig +)
Fuel Flow (Sig –)
Fuel Flow Transmitter +
Fuel Flow Transmitter –
J2 P
Unused
(5 VDC)
(Signal +)
(Ground)
(Signal -)
25
ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Aircraft Company
15.3
ADAS+
ADAS-G-260-1/A
Model 208 Series
Cockpit Trend / Sensor Cable, J3, 37 Pin S Keyed Connector
INSTALLATION CAUTION:




Connector
Pin
Before making any wiring connections, verify all connection locations with the aircraft
manufacturer’s wiring diagram manuals.
Perform a continuity check on all wires before final connection.
Route all harnesses along existing harnesses wherever possible. Do not connect to engine
scavenge lines.
Cables may be marked with shrink-on labels near the terminal end. When you shorten a
cable behind a label, be sure to re-label it.
Harness
Wire Color
Signal Name
Wired To
Refer to Section 6
1 COND CABLE
-WHT
SW PWR 2
Aircraft Bus Power, Supplied 1 Amp
Breaker
1 COND CABLE
J3 3
WHT
Digital 2
Bleed Air – S53
1 COND CABLE
J3 4
WHT
Digital 3
EPL (Emergency Power Lever) – S91
1 COND CABLE
J3 5
WHT
Digital 4
Particle Separator Switch
4 COND CABLE
-WHT
J3 19
WHT/ORG
J3 18
WHT/BLU
J3 1
WHT/GRN
IND SW
IND SW
IND SW
IND SW
(VCC)
(Switched)
(GND)
(TREND Switch)
1 COND CABLE (Using Standard Trend Lamp)
J3 37
WHT
IND SW Open
Lamp ConXall™ Pin 1
Lamp ConXall™ Pin 4
Lamp ConXall™ Pin 2
Lamp ConXall™ Pin 3
Cap, Coil, and Stow (Near Lamp ConXall™)
1 COND CABLE (Using Optional ENGINE/TREND Split Lamp)
J3 37
WHT
IND SW Open (Switched)
Lamp ConXall™ Pin 5
4 COND CABLE
J3 16
WHT
J3 17
WHT/ORG
J3 18
WHT/BLU
J3 2
WHT/GRN
Download Port (RS485+)
Download Port (RS485-)
Download Port (GND)
Download Port (Run/Conf)
Download ConXall™ Pin 1
Download ConXall™ Pin 2
Download ConXall™ Pin 3
Download ConXall™ Pin 4
26
ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Aircraft Company
ADAS+
ADAS-G-260-1/A
Model 208 Series
4 COND CABLE
J3 21
WHT
J3 22
WHT/BLU
J3 23
WHT/ORG
J3 24
WHT/GRN
Air Temp (“D”)
Air Temp (“G”)
Air Temp (“R+”)
Air Temp (“R–”)
OAT ConXall™ Pin 1
OAT ConXall™ Pin 2
OAT ConXall™ Pin 3
OAT ConXall™ Pin 4
4 COND CABLE
J3 31
WHT
J3 32
WHT/ORG
J3 33
WHT/BLU
J3 34
WHT/GRN
Vertical Accl. +
Vertical Accl. –
Vertical Accl. +
Vertical Accl -
Terminate and Tie Back (near download port)
Terminate and Tie Back (near download port)
Terminate and Tie Back (near download port)
Terminate and Tie Back (near download port)
2 COND CABLE
J3 35
WHT
J3 36
WHT/BLU
Digital 1 +
Digital 1 -
Hour Meter –
Aircraft Ground
4 WIRE JUMPER
7
GRN
11
GRN
14
GRN
15
GRN
Configuration Ground
Configuration ID 0
Configuration ID 1
Configuration ID 2
Set at Factory
Set at Factory
Set at Factory
Set at Factory
6
8
9
10
13
20
25
26
27
28
29
30
Unused
Unused
Unused
Unused
Unused
Unused
Unused
Unused
Unused
Unused
Unused
Unused
27
ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Aircraft Company
ADAS+
ADAS-G-260-1/A
Model 208 Series
16 Wiring Diagram
16.1
ADAS+ Connection Chart – Cessna Model 208 Series
Sensor
Wire
Number
Caravan with
Electric Torque System
Caravan with
Wet Torque System
Aircraft Component ADAS+ Connector Aircraft Component ADAS+ Connector
Aircraft Sensors
J2
Pin J Alumel Red
Pin K Chromel Yel
J2
Pin D WHT
Pin H WHT/BLU
J2
Pin A WHT
Pin B WHT/ORG
Pin C WHT/BLU
Pin F WHT/GRN
J2
Pin A WHT
Pin B WHT/ORG
Pin C WHT/BLU
Pin F WHT/GRN
Engine Assy. Block
RED
YEL
J134
Pin B BLK
Pin A WHT
P&WES Transducers
Torque RED Wire
Torque GRN Wire
Torque BLK Wire
Torque GRN Wire
P&WES Transducers
Torque RED Wire
Torque GRN Wire
Torque BLK Wire
Torque GRN Wire
J2
Pin J Alumel Red
Pin K Chromel Yel
J2
Pin D WHT
Pin H WHT/BLU
J2
Pin A WHT
Pin B WHT/ORG
Pin C WHT/BLU
Pin F WHT/GRN
J2
Pin A WHT
Pin B WHT/ORG
Pin C WHT/BLU
Pin F WHT/GRN
Propeller Speed
(Np)
AAP11B22 J34
Pin A BLK
Pin B WHT
Fuel Flow (Wf)
AAP00B22 J5
Pin A WHT
Pin B BLK
Bleed Air
AAD11A24 S53
NO
Emergency Power AAD18A24 S91
Lever
C – WH1
S/N 00001 Thru
00140
J2
Pin E WHT
Pin N WHT/BLU
J2
Pin G WHT
Pin R WHT/BLU
J3
Pin 3WHT
J3
Pin 4 WHT
J34
Pin A BLK
Pin B WHT
J5
Pin A WHT
Pin B BLK
S53
NO
S91
C – WH1
J2
Pin E WHT
Pin N WHT/BLU
J2
Pin G WHT
Pin R WHT/BLU
J3
Pin 3WHT
J3
Pin 4 WHT
Emergency Power AAD18A24 S91
Lever
C - WH4
S/N 00141 AND >
J3
Pin 4 WHT
S91
C - WH4
J3
Pin 4 WHT
Engine ITT
Engine N1 (Ng)
Engine Torque
(Tq)
Model 208
S/N 00007 thru
00096
Engine Torque
(Tq)
Model 208
S/N 00097 thru
00199
Model 208B
S/N 0001 AND
ON
Hour Meter
AAA10B22 Engine Assy. Block
RED
YEL
AAP10B22 J134
Pin B BLK
Pin A WHT
AAA20D22 J211
Pin C
Pin D
AAA20D22 J211
Pin A
Pin B
AAD10B24 IND12 (Hour Meter) J3
J305 – DF7
Pin 35 WHT
Ground
Pin 36 WHT/BLU
IND12 (Hour Meter) J3
J305 – DF7
Pin 35 WHT
Ground
Pin 36 WHT/BLU
28
ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Aircraft Company
Sensor
Wire
Number
ADAS+
ADAS-G-260-1/A
Model 208 Series
Caravan with
Electric Torque System
Caravan with
Wet Torque System
Aircraft Component ADAS+ Connector Aircraft Component ADAS+ Connector
Battery Power
Bus Power
Sensor
AAV00B22 Relay K 3
A2
Ground
AAV10A22 Relay K 3
A1
Wire
Number
J1
Pin H WHT
Pin G WHT/BLU
J1
Pin F WHT
Relay K 3
A2
Ground
Relay K 3
A1
Caravan with
Electric Torque System
J1
Pin H WHT
Pin G WHT/BLU
J1
Pin F WHT
Caravan with
Wet Torque System
Aircraft Component ADAS+ Connector Aircraft Component
ADAS+ Connector
P&W Engine Services Supplied Sensors
AAA00D24 Oat Probe
Red Wire
Wht Wire
Red Wire
Wht Wire
Airspeed /
AAA22D22 Transducers
Altitude Sensor
Pitot Grn Wire
Pitot/Static Red Wire
Pitot/Static Blk Wire
Static Grn Wire
AAD16A24 Particle Separator
Switch
Particle Separator
Switch Sensor
BLK Wire
BLK Wire
OAT Probe
J3
Pin 21 WHT
Pin 22 WHT/BLU
Pin 23 WHT/ORG
Pin 24 WHT/GRN
J1
Pin A WHT/ORG
Pin B WHT
Pin N WHT/BLU
Pin D WHT/GRN
J3
Pin 5 WHT
Aircraft Ground
Oat Probe
Red Wire
Wht Wire
Red Wire
Wht Wire
Transducers
Pitot Grn Wire
Pitot/Static Red Wire
Pitot/Static Blk Wire
Static Grn Wire
Particle Separator
Switch
BLK Wire
BLK Wire
J3
Pin 21 WHT
Pin 22 WHT/BLU
Pin 23 WHT/ORG
Pin 24 WHT/GRN
J1
Pin A WHT/ORG
Pin B WHT
Pin N WHT/BLU
Pin D WHT/GRN
J3
Pin 5 WHT
Aircraft Ground
Table A- 1: ADAS+ Connection Chart
29
ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Caravan
16.2
ADAS+
ADAS-G-260-1/A
Model 208 Series
ADAS+ Interconnect Schematic – No Supplied Torque Transducers
WHT
WHT/ORG
WHT/BLU
WHT/GRN
N/C
SIG +
N/C
SIG Transducer
AIRCRAFT
0-5 VDC
CONN J211
OEM SUPPLIED TRANSDUCER OPTION
J2 - 15 SA
AAA20D22
A
B
AIRCRAFT
CONN J134
AAP11B22
WHT
WHT/BLU
NP TACH +
NP TACH -
A
B
AAP00B22
WHT
WHT/BLU
AIRCRAFT
CONN J34
A
B
C
F
AAP10B22
WHT
WHT/BLU
N1 TACH +
N1 TACH -
FUEL FLOW +
FUEL FLOW -
A
B
AAA10B22
RED
YEL
AIRCRAFT
CONN J5
AAV31A22
GROUND STRAP
ITT- (AL)
ITT+ (CH)
TRQ 5 VDC
TRQ HI SIG
TRQ GND
TRQ LO SIG
D
H
N1 SPD +
N1 SPD -
E
N
N2 SPD +
N2 SPD -
G
R
FUEL FLOW +
FUEL FLOW -
J
K
ITT- (AL)
ITT+ (CH)
(SWITCHED POWER)
J1 - 15 S
28 VDC PWR
F
WHT
AAV10A22
1
2
ESSENTIAL BUS
CIRCUIT BREAKER 1 AMP
28 VDC BATT
GND
H
G
AAV00B22
WHT
WHT/BLU
1
BATTERY
RELAY
K3
2
FUSE 1 AMP
(DIRECT BATTERY)
P/S 5 VDC
P/S GND
PITOT SIG
STATIC SIG
B
N
A
D
AAA22D22
WHT
WHT/BLU
WHT/ORG
WHT/GRN
RED
BLK
GRN
AIRCRAFT PITOT
Transducer
.
.
RED
BLK
GRN
ENGINE T/C
BLOCK
AIRCRAFT STATIC
Transducer
ADAS+ PROCESSOR
EMU-A-010-3
WHT
WHT/BLU
WHT/ORG
WHT/GRN
N/C
AAA24D24
J3 - 37 S
Male
Female
J1.1
J1.2
J1.3
J1.4
J1.5
J1.6
J1.7
J1.8
J1.9
J1.10
1
2
3
4
5
6
AAB40D24
1
2
3
4
5
6
AC HOURMETER IND12
+
WHT - RS485 + (B)
WHT/ORG - RS485 - (A)
WHT/BLU - GND
WHT/GRN - RUN/CONF
CONNECTOR
FAULT LAMP
Lamp 1 +
Lamp 1 SW1-NO
SW1-COMM
SW1-NC
SW2-NO
SW2-COMM
SW2-NC
1
2
3
4
5
6
FAULT LAMP ASSEMBLY
OAT Probe
Male
RED
WHT
RED
WHT
AAV32A24
Female
1
2
3
4
5
6
Female
WHT
WHT/BLU
WHT/ORG
WHT/GRN
1
2
3
4
5
6
AAA00D24
AAD11A24
WHT
S53.
AIRCRAFT BLEED VALVE
HOURMETER +
HOURMETER -
16
17
18
2
RS-485+ (B)
RS-485- (A)
GND
RUN/CONF SW
1
19
37
VCC
GND
TREND SW
LAMP 1
LAMP 2
7
8
9
10
CONG GND
CONG ID1
CONG ID2
CONG ID4
21
22
23
24
OAT D
OAT G
OAT R+
OAT R-
3
BLEED SIG
4
EPL SIG
5
P/S SIG
To Bus Breaker
WHT - LAMP PWR
WHT/BLU - GND
WHT/GRN - TREND
WHT/ORG - LAMP 1 SW
WHT - LAMP 2 SW
N/C
1
2
3
4
5
6
Male
OAT-D
OAT-G
OAT-R+
OAT R-
35
36
AAV31A22
AAV30D24
MICROSWITCH PTT
Vertical Accl +
Vertical Accl SIG
Vertical Accl Vertical Accl
AAD10B24
CONNECTOR
COMM PORT
DOWNLOAD PORT ASSEMBLY
WHT
WHT/BLU
-
31
32
33
34
WHT
AAD18A24
S91
AIRCRAFT EPL
Magnetic Reed
Switch
BLK
BLK
WHT
AAD16A24
CONFIG
ID = 7
PARTICLE SEPARATOR
Figure A- 19: Wiring Schematic– No Supplied Torque Transducers
- 30 ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Caravan
16.3
ADAS+ Interconnect Schematic – Supplied Torque Transducers
HIGH
ADAS+
ADAS-G-260-1/A
Model 208 Series
Transducer
RED
GRN
BLK
ENGINE
TORQUE
J2 - 15 SA
WHT
WHT/ORG
WHT/BLU
WHT/GRN
Transducer
RED
BLK
GRN
LOW
AAV31A22
GROUND STRAP
AAA20D22
WHT
WHT/BLU
N1 TACH +
N1 TACH -
AAP10B22
A
B
AIRCRAFT
CONN J134
WHT
WHT/BLU
NP TACH +
NP TACH -
AAP11B22
A
B
WHT
WHT/BLU
AIRCRAFT
CONN J34
FUEL FLOW +
FUEL FLOW -
AAP00B22
A
B
RED
YEL
AIRCRAFT
CONN J5
ITT- (AL)
ITT+ (CH)
AAA10B22
A
B
C
F
TRQ 5 VDC
TRQ HI SIG
TRQ GND
TRQ LO SIG
D
H
N1 SPD +
N1 SPD -
E
N
N2 SPD +
N2 SPD -
G
R
FUEL FLOW +
FUEL FLOW -
J
K
ITT- (AL)
ITT+ (CH)
(SWITCHED POWER)
J1 - 15 S
28 VDC PWR
F
WHT
AAV10A22
1
2
ESSENTIAL BUS
CIRCUIT BREAKER 1 AMP
28 VDC BATT
GND
H
G
AAV00B22
WHT
WHT/BLU
1
BATTERY
RELAY
K3
2
FUSE 1 AMP
(DIRECT BATTERY)
P/S 5 VDC
P/S GND
PITOT SIG
STATIC SIG
B
N
A
D
AAA22D22
WHT
WHT/BLU
WHT/ORG
WHT/GRN
RED
BLK
GRN
AIRCRAFT PITOT
Transducer
.
.
RED
BLK
GRN
ENGINE T/C
BLOCK
AIRCRAFT STATIC
Transducer
ADAS+ PROCESSOR
EMU-A-010-3
WHT
WHT/BLU
WHT/ORG
WHT/GRN
N/C
AAA24D24
J3 - 37 S
Female
J1.1
J1.2
J1.3
J1.4
J1.5
J1.6
J1.7
J1.8
J1.9
J1.10
Male
1
2
3
4
5
6
AAB40D24
1
2
3
4
5
6
AC HOURMETER IND12
+
AAD10B24
CONNECTOR
COMM PORT
DOWNLOAD PORT ASSEMBLY
WHT
WHT/BLU
-
WHT - RS485 + (B)
WHT/ORG - RS485 - (A)
WHT/BLU - GND
WHT/GRN - RUN/CONF
CONNECTOR
FAULT LAMP
Lamp 1 +
Lamp 1 SW1-NO
SW1-COMM
SW1-NC
SW2-NO
SW2-COMM
SW2-NC
1
2
3
4
5
6
FAULT LAMP ASSEMBLY
Male
OAT Probe
RED
WHT
RED
WHT
AAV32A24
Female
1
2
3
4
5
6
AIRCRAFT BLEED VALVE
Female
WHT
WHT/BLU
WHT/ORG
WHT/GRN
1
2
3
4
5
6
AAA00D24
AAD11A24
WHT
S53.
WHT
AAD18A24
S91
AIRCRAFT EPL
35
36
HOURMETER +
HOURMETER -
16
17
18
2
RS-485+ (B)
RS-485- (A)
GND
RUN/CONF SW
1
19
37
VCC
GND
TREND SW
LAMP 1
LAMP 2
7
8
9
10
CONG GND
CONG ID1
CONG ID2
CONG ID4
21
22
23
24
OAT D
OAT G
OAT R+
OAT R-
3
BLEED SIG
4
EPL SIG
5
P/S SIG
To Bus Breaker
WHT - LAMP PWR
WHT/BLU - GND
WHT/GRN - TREND
WHT/ORG - LAMP 1 SW
WHT - LAMP 2 SW
N/C
1
2
3
4
5
6
Male
OAT-D
OAT-G
OAT-R+
OAT R-
Vertical Accl +
Vertical Accl SIG
Vertical Accl Vertical Accl
AAV31A22
AAV30D24
MICROSWITCH PTT
31
32
33
34
Magnetic Reed
Switch
BLK
BLK
WHT
AAD16A24
CONFIG
ID = 7
PARTICLE SEPARATOR
Figure A- 20: Wiring Schematic – Supplied Torque Transducers
- 31 ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
ADAS+
Cessna Caravan
16.4
ADAS+ Interconnect Schematic (Split Lamp Option) – No Supplied Torque Transducers
WHT
WHT/ORG
WHT/BLU
WHT/GRN
N/C
SIG +
N/C
SIG Transducer
0-5 VDC
J2 - 15 SA
AAA20D22
AIRCRAFT
CONN J134
AAP11B22
WHT
WHT/BLU
NP TACH +
NP TACH -
A
B
AIRCRAFT
CONN J34
A
B
C
F
AAP10B22
WHT
WHT/BLU
A
B
AAP00B22
WHT
WHT/BLU
FUEL FLOW +
FUEL FLOW -
A
B
AIRCRAFT
CONN J5
AAV31A22
GROUND STRAP
AIRCRAFT
CONN J211
OEM SUPPLIED TRANSDUCER OPTION
N1 TACH +
N1 TACH -
ADAS-G-260-1/A
Model 208 Series
AAA10B22
RED
YEL
ITT- (AL)
ITT+ (CH)
TRQ 5 VDC
TRQ HI SIG
TRQ GND
TRQ LO SIG
D
H
N1 SPD +
N1 SPD -
E
N
N2 SPD +
N2 SPD -
G
R
FUEL FLOW +
FUEL FLOW -
J
K
ITT- (AL)
ITT+ (CH)
J1 - 15 S
28 VDC PWR
F
WHT
AAV10A22
1
2
ESSENTIAL BUS
SWITCHED POWER
CIRCUIT BREAKER 1 AMP
28 VDC BATT
GND
H
G
P/S 5 VDC
P/S GND
PITOT SIG
STATIC SIG
B
N
A
D
AAV00B22
WHT
WHT/BLU
1
BATTERY
RELAY
K3
2
FUSE 1 AMP
AAA22D22
WHT
WHT/BLU
WHT/ORG
WHT/GRN
RED
BLK
GRN
DIRECT BATTERY
AIRCRAFT PITOT
Transducer
.
.
RED
BLK
GRN
ENGINE T/C
BLOCK
AIRCRAFT STATIC
Transducer
ADAS+ PROCESSOR
EMU-A-010-3
WHT
WHT/BLU
WHT/ORG
WHT/GRN
N/C
AAA24D24
J3 - 37 S
Female
COMM PORT
J1.1
J1.2
J1.3
J1.4
J1.5
J1.6
J1.7
J1.8
J1.9
J1.10
AAB40D24
Male
1
2
3
4
5
6
31
32
33
34
Vertical Accl +
Vertical Accl SIG
Vertical Accl Vertical Accl
35
36
HOURMETER +
HOURMETER -
16
17
18
2
RS-485+ (B)
RS-485- (A)
GND
RUN/CONF SW
AAV32A24
1
19
37
VCC
GND
TREND SW
LAMP 1
LAMP 2
Male
7
8
9
10
CONG GND
CONG ID1
CONG ID2
CONG ID4
21
22
23
24
OAT D
OAT G
OAT R+
OAT R-
3
BLEED SIG
4
EPL SIG
5
P/S SIG
1
2
3
4
5
6
AC HOURMETER IND12
+
-
WHT
WHT/BLU
AAD10B24
CONNECTOR
COMM PORT
WHT - RS485 + (B)
WHT/ORG - RS485 - (A)
WHT/BLU - GND
WHT/GRN - RUN/CONF
AAV31A22
Male
MICROSWITCH PTT
SPLIT LAMP
Lamp +
Lamp SW1-NO
SW1-COMM
SW1-NC
SW2-NO
SW2-COMM
SW2-NC
Lamp 2 +
Lamp 2 -
To Bus Breaker
Female
1
2
3
4
5
6
WHT - LAMP PWR
WHT/BLU - GND
WHT/GRN - TREND
WHT/ORG - LAMP 1 SW
WHT - LAMP 2 SW
AAV30D24
1
2
3
4
5
6
CONNECTOR
SPLIT LAMP
OAT-D
OAT-G
OAT-R+
OAT R-
OAT Probe
RED
WHT
RED
WHT
1
2
3
4
5
6
AIRCRAFT BLEED VAVE
WHT
WHT/BLU
WHT/ORG
WHT/GRN
1
2
3
4
5
6
AAA00D24
AAD11A24
WHT
S53 .
Female
WHT
AAD18A24
S91
AIRCRAFT EPL
Magnetic Reed
Switch
BLK
BLK
WHT
AAD16A24
CONFIG
ID = 7
PARTICLE SEPARATOR
Figure A- 21: Wiring Schematic (Split Lamp Option) – No Supplied Torque Transducers
- 32 ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Aircraft Company
16.5
ADAS+
ADAS-G-260-1/A
Model 208 Series
ADAS+ Interconnect Schematic (Split Lamp Option) – Supplied Torque Transducers
HIGH
Transducer
RED
GRN
BLK
AAV31A22
GROUND STRAP
ENGINE
TORQUE
J2 - 15 SA
WHT
WHT/ORG
WHT/BLU
WHT/GRN
Transducer
RED
BLK
GRN
AAA20D22
AAP10B22
WHT
WHT/BLU
LOW
N1 TACH +
N1 TACH -
A
B
AIRCRAFT
CONN J134
WHT
WHT/BLU
NP TACH +
NP TACH -
AAP11B22
A
B
AIRCRAFT
CONN J34
WHT
WHT/BLU
FUEL FLOW +
FUEL FLOW -
AAP00B22
A
B
AIRCRAFT
CONN J5
RED
YEL
ITT- (AL)
ITT+ (CH)
AAA10B22
A
B
C
F
TRQ 5 VDC
TRQ HI SIG
TRQ GND
TRQ LO SIG
D
H
N1 SPD +
N1 SPD -
E
N
N2 SPD +
N2 SPD -
G
R
FUEL FLOW +
FUEL FLOW -
J
K
ITT- (AL)
ITT+ (CH)
(SWITCHED POWER)
J1 - 15 S
28 VDC PWR
F
WHT
AAV10A22
1
2
ESSENTIAL BUS
CIRCUIT BREAKER 1 AMP
28 VDC BATT
GND
H
G
AAV00B22
WHT
WHT/BLU
1
BATTERY
RELAY
K3
2
FUSE 1 AMP
(DIRECT BATTERY)
P/S 5 VDC
P/S GND
PITOT SIG
STATIC SIG
B
N
A
D
AAA22D22
WHT
WHT/BLU
WHT/ORG
WHT/GRN
RED
BLK
GRN
AIRCRAFT PITOT
Transducer
.
.
RED
BLK
GRN
ENGINE T/C
BLOCK
AIRCRAFT STATIC
Transducer
ADAS+ PROCESSOR
EMU-A-010-3
WHT
WHT/BLU
WHT/ORG
WHT/GRN
N/C
AAA24D24
J3 - 37 S
Female
COMM PORT
J1.1
J1.2
J1.3
J1.4
J1.5
J1.6
J1.7
J1.8
J1.9
J1.10
Male
1
2
3
4
5
6
AAB40D24
1
2
3
4
5
6
AC HOURMETER IND12
+
WHT
WHT/BLU
-
AAD10B24
CONNECTOR
COMM PORT
WHT - RS485 + (B)
WHT/ORG - RS485 - (A)
WHT/BLU - GND
WHT/GRN - RUN/CONF
31
32
33
34
Vertical Accl +
Vertical Accl SIG
Vertical Accl Vertical Accl
35
36
HOURMETER +
HOURMETER -
16
17
18
2
RS-485+ (B)
RS-485- (A)
GND
RUN/CONF SW
1
19
37
VCC
GND
TREND SW
LAMP 1
LAMP 2
7
8
9
10
CONG GND
CONG ID1
CONG ID2
CONG ID4
21
22
23
24
OAT D
OAT G
OAT R+
OAT R-
3
BLEED SIG
4
EPL SIG
5
P/S SIG
AAV31A22
Male
MICROSWITCH PTT
SPLIT LAMP
Lamp +
Lamp SW1-NO
SW1-COMM
SW1-NC
SW2-NO
SW2-COMM
SW2-NC
Lamp 2 +
Lamp 2 -
To Bus Breaker
Female
1
2
3
4
5
6
WHT - LAMP PWR
WHT/BLU - GND
WHT/GRN - TREND
WHT/ORG - LAMP 1 SW
WHT - LAMP 2 SW
AAV30D24
1
2
3
4
5
6
AAV32A24
CONNECTOR
SPLIT LAMP
Male
OAT-D
OAT-G
OAT-R+
OAT R-
OAT Probe
RED
WHT
RED
WHT
1
2
3
4
5
6
AIRCRAFT BLEED VALVE
WHT
WHT/BLU
WHT/ORG
WHT/GRN
1
2
3
4
5
6
AAA00D24
AAD11A24
WHT
S53.
Female
WHT
AAD18A24
S91
AIRCRAFT EPL
Magnetic Reed
Switch
BLK
BLK
WHT
AAD16A24
CONFIG
ID = 7
PARTICLE SEPARATOR
Figure A- 22: Wiring Schematic (Split Lamp Option) – Supplied Torque Transducer
33
ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Caravan
16.6 ADAS+ Schematic (Garmin G620 Option) – No Supplied Torque Transducers
ADAS+
ADAS-G-260-1/A
Model 208 Series
Figure A- 23: Wiring Schematic (Garmin G620 Option) – No Supplied Torque Transducers
- 34 ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Caravan
16.7 ADAS+ Schematic (Garmin G620 Option) – Supplied Torque Transducers
ADAS+
ADAS-G-260-1/A
Model 208 Series
Figure A- 24: Wiring Schematic (Garmin G620 Option) – Supplied Torque Transducers
- 35 ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
ADAS+
Cessna Caravan
16.8 ADAS+ Schematic (Garmin G620 / Split Lamp Option) – No Supplied Torque Transducers
ADAS-G-260-1/A
Model 208 Series
Figure A- 25: Wiring Schematic (Garmin G620 / Split Lamp Option) – No Supplied Torque Transducers
- 36 ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary
P&W ENGINE SERVICES, INC.
Cessna Caravan
16.9 ADAS+ Schematic (Garmin G620 / Split Lamp Option) – Supplied Torque Transducers
ADAS+
ADAS-G-260-1/A
Model 208 Series
Figure A- 26: Wiring Schematic (Garmin G620 / Split Lamp Option) – Supplied Torque Transducers
- 37 ADAS-G-260-1/A
Pratt & Whitney Engine Services, Inc. Proprietary