p&w engine services, inc. -...

P&W ENGINE SERVICES, INC. ADAS+ ADAS-G-010-1/ACessna Caravan Model 208 Series Revision K

This Document is Subject to the Restrictions Contained on Cover PageThe export control classification with respect to this document is contained on the first page

ADAS-G-010-1/A - i-

PREFACE

Disclaimer

Like all instrumentation, the Pratt & Whitney Engine Services, Inc. ADAS+ system requires knowledgeable interpretation bythe pilot. Any recommendations and operating procedures contained in this manual shall not supersede the Aircraft orEngine 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.



ADAS-G-010-1/A - ii-

REVISION HISTORYRev Statusof Sheets

Rev I K I J J I J I I J I I J I I ISheet i ii iii iv v 1 2 3 4 5 6 7 8 9 10 11Rev I I I I I I I I I I I K I J J JSheet 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27Rev J J J J J J J J J J J J J J J JSheet 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43Rev J J J J J J J J J JSheet 44 45 46 47 48 49 50 51 52 53

LOG OF REVISIONS

REV.NO

ECO # DESCRIPTION Date PAGESREVISED

A Initial Release 12/16/02

B 735 Correct errors in OAT wiring diagram and Fuel Flowconnection, change contents of Processor Assembly Kit

05/27/04i, 2, 24, 25, and

39

C 812 Add Split Lamp Option. Revise Footer Information.Correct Typos.

05/24/05 All

D 839 Revise Connection Chart to show the correct pin-out forthe J2 Harness.

09/12/05Cover, i – iv, and

38

E 850 Correct part number for Processor Mounting Bracket 01/27/06 Cover, ii, and 5

F 860 Correct dimensions for SplitLamp. Correct OAT Probe connections

07/06/06 7, 8, 40-43

G 957 Revise Connection Chart to include wire numbering.Revise Schematics to include wire numbering. Revise

Split Lamp and all associated text. Revised part numbersand associated text. Corrected spelling. Updated

company name and address

11/05/07 All

H 980 Add Ice Vane Switch Kit to Parts List. Add Ice VaneInstallation Instructions.

12/08/08Cover, ii –v, 21 –

49

I 994 Revise Parts List. Update Schematics. Revise OAT,Torque, Circuit Breaker, and Download PortInstructions. Correct Typographical Errors.

02/23/09 All

J 1103 Add optional Garmin G620 Interface Cable P/NADAS-C-072-1 to Parts List. Add Installation Steps and

Schematics to support the interface.11/15/11

Cover, ii, iv, v, 2,5, 8, 25 - 53

K 1123 Correct Typographical Error - Hour Meter wire number 12/04/12 Cover, ii, 23

NOTE:If the ADAS+ Installation Manuals are revised, all operators will be provided with a copy of theapplicable revision. If you have a subscription with TurbineTracker™, you will be informed viaemail of new revisions to this manual. In addition to this, P&W Engine Services maintains thelatest 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 CustomerSupport at 781-762-8600 for the latest revision.



ADAS-G-010-1/A - iii-

TABLE OF CONTENTS

1 CESSNA CARAVAN MODEL 208 SERIES APPLICATION....................................................... 1

1.1 SCOPE ................................................................................................................................................ 1

2 INSTALLATION AND MAINTENANCE ..................................................................................... 2

2.1 PARTS LIST ........................................................................................................................................ 22.1.1 ADAS+ by Parts Kits.................................................................................................................. 22.1.2 Components by Kit ..................................................................................................................... 2

3 INSTALLATION – MECHANICAL .............................................................................................. 6

3.1 PROCESSOR ........................................................................................................................................ 63.1.1 System Processor Mounting........................................................................................................ 6

3.2 COCKPIT COMPONENTS ...................................................................................................................... 83.2.1 Standard TREND Lamp or Optional Engine/Trend Split Lamp and Download Port .................... 8

3.3 AIRFRAME COMPONENTS ................................................................................................................. 113.3.1 Circuit Breaker Mounting......................................................................................................... 11

3.4 NAVIGATION .................................................................................................................................... 123.4.1 Pitot / Static Pressure Transducer Mounting............................................................................. 123.4.2 Outside Air Temperature Probe................................................................................................ 16

3.5 ENGINE INDICATING ......................................................................................................................... 183.5.1 Torque Transducer Installation ................................................................................................ 183.5.2 Firewall Connector Installation................................................................................................ 203.5.3 Particle Separator Switch Installation ...................................................................................... 22

3.6 HARNESS INSTALLATION .................................................................................................................. 233.6.1 “J1” Harness Installation......................................................................................................... 233.6.2 “J2” Harness Installation......................................................................................................... 233.6.3 “J3” Harness Installation......................................................................................................... 23

4 INSTALLATION - ELECTRICAL .............................................................................................. 24

4.1 COCKPIT COMPONENTS .................................................................................................................... 244.1.1 Standard Cockpit TREND Switch Wiring .................................................................................. 244.1.2 Optional ENGINE/TREND Split Lamp Wiring.......................................................................... 254.1.3 Download Port Connector Wiring ............................................................................................ 25

4.1.3.1 Optional Garmin G620 Interface Cable“ADAS-C-072-1” ..................................................... 264.2 NAVIGATION .................................................................................................................................... 27

4.2.1 Pitot / Static Pressure Transducer Wiring................................................................................. 274.2.2 Outside Air Temperature (OAT) Probe Wiring.......................................................................... 27

4.3 ENGINE INDICATING ......................................................................................................................... 294.3.1 Engine Temp (ITT) ................................................................................................................... 294.3.2 Engine N1 (Ng) Speed Sensor ................................................................................................... 304.3.3 Engine Np Speed Sensor........................................................................................................... 304.3.4 Engine Wf Sensor ..................................................................................................................... 304.3.5 Engine Torque Wiring .............................................................................................................. 314.3.6 Particle Separator Switch Wiring ............................................................................................. 32

4.4 AIRFRAME SENSORS......................................................................................................................... 324.4.1 Engine Hour Meter................................................................................................................... 324.4.2 Bleed Air .................................................................................................................................. 324.4.3 Engine EPL .............................................................................................................................. 32

4.5 ELECTRICAL POWER......................................................................................................................... 32



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4.5.1 Battery Power / Ground Connection ......................................................................................... 324.5.2 Bus (Switched) Power Connection ............................................................................................ 33

4.6 FINAL INSTALLATION NOTES............................................................................................................ 34

5 HARNESS CONNECTOR SIGNAL PINOUTS........................................................................... 35

5.1 POWER/ SENSOR CABLE J1, 15 PIN S KEYED CONNECTOR ................................................................ 355.2 SENSOR CABLE J2, 15 PIN SA KEYED CONNECTOR........................................................................... 365.3 COCKPIT TREND / SENSOR CABLE, J3, 37 PIN S KEYED CONNECTOR ................................................ 37

6 WIRING DIAGRAM..................................................................................................................... 39

6.1 ADAS + CONNECTION CHART – CESSNA MODEL 208 SERIES ........................................................... 396.2 ADAS+ SCHEMATIC – NO SUPPLIED TORQUE TRANSDUCERS........................................................... 416.3 ADAS+ SCHEMATIC – SUPPLIED TORQUE TRANSDUCERS ................................................................ 426.4 ADAS+ SCHEMATIC (SPLIT LAMP OPTION) – NO SUPPLIED TORQUE TRANSDUCERS ........................ 436.5 ADAS+ SCHEMATIC (SPLIT LAMP OPTION) – SUPPLIED TORQUE TRANSDUCERS.............................. 446.6 ADAS+ SCHEMATIC (GARMIN G620 OPTION) – NO SUPPLIED TORQUE TRANSDUCERS .................... 456.7 ADAS+ SCHEMATIC (GARMIN G620 OPTION) – SUPPLIED TORQUE TRANSDUCERS .......................... 466.8 ADAS+ SCHEMATIC (GARMIN G620 / SPLIT LAMP OPTION) – NO SUPPLIED TORQUE TRANSDUCERS

........................................................................................................................................................ 476.9 ADAS+ SCHEMATIC (GARMIN G620 / SPLIT LAMP OPTION) – SUPPLIED TORQUE TRANSDUCERS..... 48

7 APPENDIX A................................................................................................................................. 49

7.1 PARTICLE SEPARATOR SWITCH INSTALLATION................................................................................. 49

LIST OF FIGURES

FIGURE A- 1: ADAS+ PROCESSOR LOCATION .................................................................................................... 6FIGURE A- 2: PROCESSOR INSTALLATION CONFIGURATION................................................................................ 7FIGURE A- 3: PROCESSOR MOUNTING TOP VIEW ............................................................................................... 7FIGURE A- 4: PROCESSOR INSTALLATION LOCATION ON CESSNA CARAVAN 208B ............................................. 8FIGURE A- 5: TYPICAL MOUNTING LOCATION FOR TREND SWITCH OR ENGINE/TREND SPLIT LAMP............. 9FIGURE A- 6: TYPICAL MOUNTING LOCATION FOR DOWNLOAD PORT................................................................ 9FIGURE A- 7: TREND SWITCH OR ENGINE/TREND SPLIT LAMP INSTALLATION IN CESSNA CARAVAN 208B. 10FIGURE A- 8: TYPICAL DOWNLOAD PORT INSTALLATION IN CESSNA CARAVAN 208B ..................................... 10FIGURE A- 9: CIRCUIT BREAKER INSTALLATION IN CESSNA CARAVAN 208B................................................... 11FIGURE A- 10: PITOT STATIC MOUNTING LOCATION........................................................................................ 12FIGURE A- 11: PITOT/STATIC INSTALLATION CONFIGURATION ........................................................................ 14FIGURE A- 12: PITOT / STATIC TRANSDUCER INSTALLATION ON CESSNA CARAVAN 208B ............................... 15FIGURE A- 13: PITOT / STATIC TRANSDUCER ALTERNATE MOUNTING CONFIGURATION .................................. 15FIGURE A- 14: OAT PROBE MOUNTING LOCATION .......................................................................................... 16FIGURE A- 15: OAT INSTALLATION CONFIGURATION ...................................................................................... 16FIGURE A- 16: OAT PROBE INSTALLATION - EXTERIOR SKIN OF CESSNA CARAVAN 208B............................... 17FIGURE A- 17: TORQUE TRANSDUCER INSTALLATION CONFIGURATION ........................................................... 19FIGURE A- 18: TORQUE TRANSDUCER INSTALLATION ON CESSNA CARAVAN 208B ......................................... 19FIGURE A- 19: FEEDTHRU MOUNTING LOCATION ............................................................................................ 20FIGURE A- 20: FIREWALL FEEDTHRU INSTALLATION ON CESSNA CARAVAN 208B........................................... 21FIGURE A- 21: PARTICLE SEPARATOR SWITCH LOCATION................................................................................ 22FIGURE A- 22: STANDARD TREND SWITCH AND LAMP CONNECTOR WIRING .................................................. 24FIGURE A- 23: OPTIONAL ENGINE/TREND SPLIT LAMP CONNECTOR WIRING ............................................... 25FIGURE A- 24: DOWNLOAD PORT CONNECTOR ................................................................................................ 25



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FIGURE A- 25: CONNECTOR PG01 LOCATED BEHIND PANEL SHOWN................................................................. 26FIGURE A- 26: CONNECTOR PG01 LOCATION (BEHIND COPILOT PANEL) .......................................................... 26FIGURE A- 27: PITOT/STATIC TRANSDUCER WIRING. ....................................................................................... 27FIGURE A- 28: PROCESS CABLE CONNECTOR ................................................................................................... 28FIGURE A- 29: OAT PROBE CONNECTOR ......................................................................................................... 28FIGURE A- 30: OAT PROBE WIRING................................................................................................................. 28FIGURE A- 31: ITT WIRING.............................................................................................................................. 29FIGURE A- 32: ENGINE TACHOMETER WIRING ................................................................................................. 31FIGURE A- 33: ENGINE TORQUE WIRING.......................................................................................................... 31FIGURE A- 34: AIRCRAFT BATTERY FINAL WIRING.......................................................................................... 33FIGURE A- 35: FUSE HOLDER INSTALLED IN POWER BOX ON CESSNA CARAVAN 208B .................................... 33FIGURE A- 36: AIRCRAFT BUS FINAL WIRING .................................................................................................. 34FIGURE A- 37: WIRING SCHEMATIC– NO SUPPLIED TORQUE TRANSDUCERS .................................................... 41FIGURE A- 38: WIRING SCHEMATIC – SUPPLIED TORQUE TRANSDUCERS ......................................................... 42FIGURE A- 39: WIRING SCHEMATIC (SPLIT LAMP OPTION) – NO SUPPLIED TORQUE TRANSDUCERS................. 43FIGURE A- 40: WIRING SCHEMATIC (SPLIT LAMP OPTION) – NO SUPPLIED TORQUE TRANSDUCER .................. 44FIGURE A- 41: WIRING SCHEMATIC (GARMIN G620 OPTION) – NO SUPPLIED TORQUE TRANSDUCERS............. 45FIGURE A- 42: WIRING SCHEMATIC (GARMIN G620 OPTION) – SUPPLIED TORQUE TRANSDUCERS................... 46FIGURE A- 43: WIRING SCHEMATIC (GARMIN G620 / SPLIT LAMP OPTION) – NO SUPPLIED TORQUE

TRANSDUCERS ......................................................................................................................................... 47FIGURE A- 44: WIRING SCHEMATIC (GARMIN G620 / SPLIT LAMP OPTION) – SUPPLIED TORQUE TRANSDUCERS

................................................................................................................................................................ 48

APPENDIX A

FIGURE 1: PARTICLE SEPARATOR SWITCH INSTALLATION – SHEET 1 OF 5........................................................ 49FIGURE 2: PARTICLE SEPARATOR SWITCH INSTALLATION – SHEET 2 OF 5........................................................ 50FIGURE 3: PARTICLE SEPARATOR SWITCH INSTALLATION – SHEET 3 OF 5........................................................ 51FIGURE 4: PARTICLE SEPARATOR SWITCH INSTALLATION – SHEET 4 OF 5........................................................ 52FIGURE 5: PARTICLE SEPARATOR SWITCH INSTALLATION – SHEET 5 OF 5........................................................ 53

LIST OF TABLESTABLE A- 1: ADAS+ CONNECTION CHART ...................................................................................................... 40



ADAS-G-010-1/A - 1-

1 Cessna Caravan Model 208 Series Application

1.1 Scope

The purpose of this document is to provide users of this product with P&W Engine Services approvedinstallation instructions for the ADAS+. Any deviation from the procedures described within this documentcould result in a failure of the product to perform properly and could possibly result in damage to other systemsof the aircraft.



ADAS-G-010-1/A - 2-

2 INSTALLATION AND MAINTENANCE

2.1 Parts List

For Cessna Caravan Model 208 Series:

The parts listed below consist of the installation kits for the ADAS+ system for the Cessna Caravan Model 208series. Assembly kit numbers are listed in section 2.1.1 and individual components are detailed by kit numbersin section 2.1.2.

2.1.1 ADAS+ by Parts Kits

For Cessna Aircraft Company Model 208 Series: Qty P/N ADAS-K-010-2 Weight

Processor Assembly 1 ADAS-K-017-1 1.41 LbsWiring Harness Kit 1 ADAS-K-014-1 5.20 LbsEngine Torque Kit 1 ADAS-K-013-1 1.41 LbsAircraft OAT Kit 1 DPU-K-032-4 0.39 LbsAircraft Pitot Pressure Kit 1 DPU-K-034-4 0.77 LbsAircraft Static Pressure Kit 1 DPU-K-033-5 0.77 LbsCockpit Fault Lamp Assembly Kit 1 DPU-K-046-3 0.20 LbsCockpit Split Lamp and Download Port Kit (OPTIONAL) 1 ADAS-K-047-1 0.20 LbsParticle Separator Switch Kit 1 ADAS-K-070-1 1.04 ozAdditional Installation Materials Kit 1 EMU-K-023-4 0.40 Lbs*Cable Assy, ADAS+ to Garmin G620 (OPTIONAL) 1 ADAS-C-072-1 4.00 oz

*Requires ADAS+ Software Version 5.1.0 or Greater*Requires G620 Software Version 6.10 or Greater

2.1.2 Components by Kit

For Cessna Aircraft Company Model 208 Series:

PROCESSOR ASSEMBLY KIT ADAS-K-017-1

Processor EMU-A-010-3 Qty 1Mounting Bracket ADAS-D-029-1 Qty 1Clamp, Processor Mounting ADAS-D-030-1 Qty 2Shock Mounts, Lord 990-00020 Qty 4Washer, Processor Mount 920-00006 Qty 4Nut, Locking, Processor Mount MS21042-06 Qty 4Clamp, “U” Bolt NAS-3103-9-10 Qty 2

(Alternate: ADAS-D-016-1)Nut, Locking, Mount MS21042-3 Qty 4Washer, Mount AN960-10L Qty 4Strap, Ground DPU-C-050-3 Qty 1Terminal End, #10 400-00030 Qty 2Terminal End, #6 400-00029 Qty 2



ADAS-G-010-1/A - 3-

WIRING HARNESS KIT ADAS-K-014-1

Cable Assembly, J1 EMU-C-025-1 Qty 1Cable Assembly, J2 ADAS-C-011-1 Qty 1Cable Assembly, J3 ADAS-C-012-1 Qty 1

ENGINE TORQUE KIT ADAS-K-013-1

Transducer, 0 - 100 PSIG 750-00005 Qty 2Adapter, “O” Ring / 37 Flare 960-00015 Qty 2Fitting, “T” Swivel 960-00006 Qty 2Hose, Pressure, 12” AE3663162E0120 Qty 2Clamp MS21919WCJ14 Qty 2Clamp MS21919WCJ16 Qty 2Transducer Harness 750-00006 Qty 2

AIRCRAFT OAT PROBE KIT DPU-K-032-4

Probe, Temperature TWIN-A-050-2 Qty 1Nut, Jam TWIN-D-061-1 Qty 1Washer AN960-816L Qty 2Seal, “O” Ring AN6227B-10 Qty 1Bolt, Drilled AN3H-4A Qty 1Doubler, OAT Probe DPU-D-047-1 Qty 1Washer AN960-10 Qty 1Nut, Fiber Lock AN365-1032A Qty 1Connector, ConXall 400-00026 Qty 1Connector, ConXall 400-00027 Qty 1

AIRCRAFT PITOT PRESSURE KIT DPU-K-034-4

Transducer, 0-3 PSID 750-00001 Qty 1Clamp, Inlet Pressure Transducer MS21919WDG26 Qty 1Bolt, 10-32 AN3-5A Qty 1Nut, Locking, 10-32 AN365-1032A Qty 1Washer, #10 AN960-10 Qty 2Plate, Mounting ADAS-D-018-1 Qty 1Clamp ADAS-D-019-1 Qty 1Feed Through ADAS-D-033-1 Qty 1Adapter, Pipe – 37 deg. Flare 960-00002 Qty 1Hose, 306 990-00028 Qty 1Fitting, Hose ¼” 960-00027 Qty 1Tee, Barbed ¼” 960-00028 Qty 1



ADAS-G-010-1/A - 4-

AIRCRAFT STATIC PRESSURE KIT DPU-K-033-5

Transducer, 0-15 PSIA 750-00002 Qty 1Clamp, Nacelle Static Transducer MS21919WDG16 Qty 1Bolt, 10-32 AN3-5A Qty 1Nut, Locking, 10-32 AN365-1032A Qty 1Washer, #10 AN960-10 Qty 1Fitting, ¼ ″ Tube to 1/8 ″ Male thrd 960-00024 Qty 1 Tubing, Tygon 1/8 ″ 990-00030 Qty 1 Ft Insert 920-00010 Qty 1Bushing ¼ - 1/8 AL AN912-1D Qty 1Tee, ¼” Thread AL AN917-2D Qty 1Nipple, Flared Tube ¼” Tube AN816-4-4D Qty 1Hose, 306 990-00028 Qty 1Fitting, Hose ¼” 960-00027 Qty 1Tee, Barbed ¼” 960-00028 Qty 1

COCKPIT FAULT LAMP ASSEMBLY DPU-K-046-3

Assy., Cockpit Fault Lamp DPU-A-043-1 Qty 1Lens TREND-D-041-1 Qty 1Connector, 6 Pin Female 400-00026 Qty 1Assy., Download Port DPU-A-044-1 Qty 1Cover 990-00031 Qty 1Connector, 6 Pin, Male 400-00027 Qty 1Screw, Pan Head, 4-40 900-00009 Qty 1Washer AN960-4 Qty 1Nut, Fiber Lock 910-00001 Qty 1

COCKPIT SPLIT LAMP AND DOWNLOAD PORT KIT (OPTIONAL) ADAS-K-047-1

Assy., Cockpit Split Lamp ADAS-A-043-1 Qty 1Connector, 6 Pin Female 400-00026 Qty 1Assy., Download Port DPU-A-044-1 Qty 1Connector, 6 Pin, Male 400-00027 Qty 1Cover, Receptacle 990-00031 Qty 1Screw, Pan Head, 4-40 900-00009 Qty 1Washer AN960-4 Qty 1Nut, Fiber Lock 910-00001 Qty 1

PARTICLE SEPARATOR SWITCH KIT ADAS-K-070-1

Sensor Magnetic SPST/NO Flange 700-00015 Qty 1Magnet flange Mount 700-00016 Qty 1Screw, #4-40 X 7/8L MS35206-220 Qty 4Mtg Plate, Particle Separator Switch ADAS-D-069-1 Qty 1Clamp, Loop, Cush, 0.25” BLK MS21919WDG8 Qty 2Nut, LCKG, SS, 4-40” 910-00001 Qty 4Washer #4, Flat AN960-4 Qty 20



ADAS-G-010-1/A - 5-

ADDITIONAL MATERIAL INSTALLATION KIT EMU-K-023-4

Crimp Lug, Alumel 400-00031 Qty 1Crimp Lug, Chromel 400-00032 Qty 1Breaker, 1 Amp 990-00032 Qty 1Fuse, 1.0 Amp 990-00033 Qty 1Holder, Fuse DPU-C-057-1 Qty 1Terminal, ½” 400-00033 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



ADAS-G-010-1/A - 6-

3 INSTALLATION – MECHANICAL

3.1 Processor

3.1.1 System Processor Mounting

The system processor (Figure 1) is mounted in the engine compartment using mounting bracket,ADAS-D-029-1. The processor will not require access during normal operation.

Figure A- 1: ADAS+ Processor Location

010 Attach the processor mounting bracket to the outboard engine mount tube using the two (2) U-bolts,four (4) flat washers, and four (4) lock-nuts as shown in Figure A-2.

020 Assemble the ADAS+ processor to the mounting bracket shown in Figure A- 2 and Figure A- 3.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. Thelocking nut should be tightened to the point of contact with the shock mount.

030 Install ground strap between one of the processor mounting studs and the aircraft chassis.

Location forProcessor MountingFS 90-95



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Figure A- 2: Processor Installation Configuration

Figure A- 3: Processor Mounting Top View



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Figure A- 4: Processor Installation Location on Cessna Caravan 208B

3.2 Cockpit Components

3.2.1 Standard TREND Lamp or Optional Engine/Trend Split Lamp and Download Port

The ADAS+ has a standard TREND switch / fault lamp or an optional Engine/Trend Split Lamp that is installedin 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 portinstalled in the cockpit (Figure A- 6) and consist of a 19/32" serial download connector.

010 Following Figure A- 5, mark and punch a .75" square hole for mounting of the standard TRENDswitch/fault lamp or mark and punch a .68" square hole for mounting of the optional Engine/TrendSplit Lamp.

020 Install the standard TREND switch/fault lamp or the optional Engine/Trend Split Lamp into theinstrument panel.

030 Mark and drill out 19/32” hole for the data download port in the avionics rack sidewall coverassembly. See Figure A- 6 and Figure A- 8 for typical installation location.

040 Install the download port cable (P/N DPU-A-044-1) into the cover assembly using Loctite® Blue onthe threads of the download port. Refer to Figure A- 6 and Figure A- 8

NOTE: Download Port Cable P/N ADAS-C-072-1 will replace the above mentioned download portcable if the optional G620 interface is used. This option requires ADAS+ software version5.1.0. or greater and Garmin G620 software version 6.10 or greater.

Mounting Locationfor Processor



ADAS-G-010-1/A - 9-

Figure A- 5: Typical Mounting Location for TREND Switch or ENGINE/TREND Split Lamp

Figure A- 6: Typical Mounting Location for Download Port



ADAS-G-010-1/A - 10-

Figure A- 7: TREND Switch or ENGINE/TREND Split Lamp Installation in Cessna Caravan 208B

Figure A- 8: Typical Download Port Installation in Cessna Caravan 208B

Typical mountinglocation for DownloadPort

Mounting locationfor TRENDswitch/fault lamp orENGINE/TRENDSplit Lamp



ADAS-G-010-1/A - 11-

3.3 Airframe Components

3.3.1 Circuit Breaker Mounting

The 1 amp circuit breaker automatically interrupts the electrical circuit under abnormal conditions. The breakeris mounted in the power box located in the engine compartment (Figure A- 9).

010 Ensure that no power is connected to the aircraft and that the battery cable is disconnected from thebattery.

020 Open the engine cowling on the left side of the engine compartment.

030 Remove the cover from the power box.

040 Mount the circuit breaker in one of the spare openings in the box.

050 Identify circuit breaker as “ETM” (Engine Trend Monitor) or an equivalent marking that distinguishesthe circuit breaker.

Figure A- 9: Circuit Breaker Installation in Cessna Caravan 208B

Mounting location forcircuit breaker



ADAS-G-010-1/A - 12-

3.4 Navigation

3.4.1 Pitot / Static Pressure Transducer Mounting

ADAS+ is capable of measuring airspeed and altitude for event monitoring or trend monitoring. Bothtransducers are mounted behind the instrument panel on the co-pilots outboard instrument panel stringer (FigureA- 10).

If the supplied static transducer is not plumbed into the aircraft’s static system, airspeed andaltitude may not be accurate in a climb or decent.

Figure A- 10: Pitot Static Mounting Location

Mounting location forpitot/static transducers



ADAS-G-010-1/A - 13-


Use Teflon® tape on all pipe threads to prevent leakage and galling.

010 Remove the cover assembly on the co-pilot’s control column

020 Remove the glove box assembly

030 Apply Teflon® tape to the Pitot Transducer threads and install adapter (960-00002).

040 Apply Teflon® tape to the Static Transducer threads and install “T” Pipe (AN917-2D).

050 Apply Teflon® tape to the Flare Nipple (AN816-4-4D) threads and install onto “T” Pipe.

060 Install Bushing (AN912-1D) onto the “T” Pipe.

070 Install Insert (920-00010) onto yellow Tygon tubing and insert the Male Nylo-Seal fitting (960-00024)into the yellow Tygon tubing.

080 Install the yellow Tygon tubing (Insert) onto the Bushing that was previously installed in step 060.

090 Following Figure A- 12, attach the pitot and static transducers to the outboard instrument stringer onthe co-pilot’s side using supplied plate (ADAS-D-018-1), clamp (ADAS-D-019-1), clamp(MS21919WDG26), bolt (AN3-5A), washer (AN960-10) and lock nut (AN365-1032A).

100 Locate a suitable place to tap into the aircraft pitot line and cut it, making sure that the cut isperpendicular to the side of the pitot line.

110 Install barb T fitting (960-00028) into the aircraft pitot line. Refer to Figure A- 11.

120 Using the supplied hose (990-00028), connect the T fitting (960-00028) and the pitot transducerfitting (960-00002). Do this by inserting the hose in the 3rd leg of the T fitting (960-00028) and thefitting (960-00002). Refer to the illustration Figure A- 11.

130 Locate a suitable place to tap into the aircraft static line and cut it, making sure that the cut isperpendicular to the side of the static line.

140 Install T fitting (990-00028) into the aircraft static line. Refer to figure 12.

150 Using the supplied hose (990-00028), connect the T fitting (960-00028) and the “T” Pipe (AN917-2D). Do this by inserting the hose in the 3rd leg of the T fitting (960-00028) and the “T” Pipe(AN917-2D). Refer to the illustration Figure A- 11.

160 Secure and tighten all hoses and fittings.

170 Reinstall glove box.

180 Reinstall cover assembly on the co-pilot’s control column.



ADAS-G-010-1/A - 14-

Figure A- 11: Pitot/Static Installation Configuration



ADAS-G-010-1/A - 15-

Figure A- 12: Pitot / Static Transducer Installation on Cessna Caravan 208B

Figure A- 13: Pitot / Static Transducer Alternate Mounting Configuration

Static Transducer

Pitot Transducer



ADAS-G-010-1/A - 16-

3.4.2 Outside Air Temperature Probe

The temperature probe is mounted on the left, underside of the engine cowling (Figure A- 14) to provide theprocessor with OAT data.

Figure A- 14: OAT Probe Mounting Location

Refer to the illustration Figure A- 15 for a pictorial representation of the installation.

Figure A- 15: OAT Installation Configuration

Mounting location forOAT Probe



ADAS-G-010-1/A - 17-

010 Gain access to the underside of the aircraft.

020 Recommended location for the OAT probe is between Fuselage Stations 90 and 100 in FuselageZone 121.

030 Using the doubler as a guide, mark and drill 5 # 40 holes through the aircraft skin, increase thediameter of the holes using a # 20 / 21 drill bit.

040 Using the doubler as a guide, mark and drill .5”dia hole through the aircraft skin.

050 Deburr all the holes in the aircraft skin and the doubler.

060 Burnish an area on the aircraft skin and the doubler to ensure bonding between the two surfaces

070 Coat all exposed surfaces (except the burnished areas) of the doubler and the aircraft skin with ZincChromate Primer.

080 Reinstall the doubler on the inside surface of the aircraft skin.

090 Using a Cherrymax Grip Gauge, measure four of the five small holes for the proper rivet grip length.

100 Coat the end of four CR3213-5-X Cherrymax rivets with Zinc Chromate Primer.

110 With the Zinc Chromate Primer still wet, install the CR3213-5-X Cherrymax rivets. Four rivets are tobe installed 90 degrees apart from each other, inserted from the outside of the aircraft.

120 Insert the temperature probe into the hole and install washers (AN960-816L), “O” ring (AN6227B-10)and jam nut (TWIN-D-061-1).

130 Install bolt (AN3-5A), washer (AN960-10), and nut (AN365-1032A) in the fifth hole drilled through thedoubler / skin).

140 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.

150 Apply a bead of sealant (ProSeal™ PR1422 or equivalent) around edge of doubler after installationand smooth to produce a filleted profile

Figure A- 16: OAT Probe Installation - Exterior Skin of Cessna Caravan 208B



ADAS-G-010-1/A - 18-

3.5 Engine Indicating

3.5.1 Torque Transducer Installation


Care should be taken to mount transducers away from the engine hot section.

The ADAS+ obtains the engine torque level by using two (2) 0 – 100 PSIG transducers installed in the torquepressure lines as referenced in Figure A- 17. The transducers are to be mounted (Adel clamped to) on theexisting engine mounting tube.

010 Using Teflon® tape, install and torque the 0 – 100 PSIG transducer (750-00005) into adapter (960-00015).

020 Remove the engine high pressure line coming from the engine at the engine connection point.

030 Install the fitting, “T” swivel (960-00006), on the male fitting at the engine connection.

040 Install the engine torque pressure line to the “T” swivel.

050 Install the pressure transducer on one end of the supplied pressure hose (AE3663162E0120) andattach the other end of the hose to the branch side of the “T” swivel.

060 Route the ADAS+ torque hose and transducer to run parallel with the engine mounting tube (FigureA- 17).

070 Secure transducers to the engine mounting tube using the supplied clamps. Refer to Figure A- 17and Figure A- 18.

080 Secure / torque all lines and fittings per the manufacturer’s recommendations.

090 Repeat the process for the engine low pressure line.

NOTE: Both Transducers should be routed parallel and secured to the engine mounting tube.



ADAS-G-010-1/A - 19-

Figure A- 17: Torque Transducer Installation Configuration

Figure A- 18: Torque Transducer Installation on Cessna Caravan 208B

FWD

AFT

Torque HI

Torque LOSupplied TorqueTransducers



ADAS-G-010-1/A - 20-

3.5.2 Firewall Connector Installation

The wiring from the engine compartment to the cockpit passes thru the Caravan’s firewall, and all of the wiringis routed thru a stainless steel feedthru and sealed with a high temperature resistant potting compound (FigureA- 19 and Figure A- 20). Please refer to FAR 21.1191 and the Cessna Model 208 Maintenance Manual fordirections on firewall penetration and high-temperature sealing practices.

The following sealants are acceptable for firewall sealing applications:Number ManufacturerDapco 2100 D Aircraft Products CoRTV106 General Electric Co/Silicone ProductsPR-810 PRC-DeSoto International

010 Locate an accessible area on the firewall as shown in Figure A- 19.

020 Mark and drill a 41/64” hole thru the firewall.

030 Remove all insulation and soundproofing from around the hole on the cockpit side of the firewall.

040 Insert the feedthru (ADAS-D-033-1) and mark and drill the holes to mount the connector to thefirewall.

050 Mount the feedthru to the firewall.

060 Seal around firewall feedthru with the appropriate sealing compound.

Figure A- 19: Feedthru Mounting Location

Mount location forFirewall feedthru



ADAS-G-010-1/A - 21-

Figure A- 20: Firewall Feedthru Installation on Cessna Caravan 208B



ADAS-G-010-1/A - 22-

3.5.3 Particle Separator Switch Installation

NOTE: For Detailed Particle Separator Switch Installation Drawings, Refer to Appendix A, Section 7.1.

The Particle Separator position is controlled by mechanical linkage actuated from the pilot in the cockpit. AMagnetic Reed Switch will be installed on the left side of the engine compartment to determine the ParticleSeparator position. This Magnetic Reed Switch will be located at Fuselage Station 77 as shown in Figure A-21.

Figure A- 21: Particle Separator Switch Location

010 Gain access to the Particle Separator Assembly from the left engine cowling.

020 Using the supplied Switch Plate assembly (P/N ADAS-D-069-1) as a guide, mark and drill (3) three0.125” diameter holes in the Particle Separator Actuator Support assembly. Refer to Appendix A,section 7.1 for more details and dimensions.

030 Deburr all the holes.

040 Using a Cherrymax Grip Gauge, measure the three holes for the proper rivet grip length.

050 Coat the end of three CR3213-4-X Cherrymax rivets or equivalent (supplied by the installer) withZinc Chromate Primer.

060 With the Zinc Chromate Primer still wet, install the CR3213-4-X Cherrymax rivets or equivalent.

070 Install the Magnetic Sensor Switch (P/N 700-00015) to the switch plate assembly using the suppliedscrews (P/N MS35206-220) and washers (P/N AN960-4).

080 Assemble and secure the Magnetic Flange Sensor (P/N 700-00016) to the Particle SeparatorActuating Rod using the supplied clamp (P/N MS21919WDG-8), screws (P/N MS35206-220),washers (P/N AN960-4) and Nuts (P/N 910-00001).

NOTE: Additional washers may be installed between switch components and mounting structure asrequired achieving correct alignment. The “Must Operate” distance is 5.71mm and “Release”distance is 20.32mm. All pictures and drawings of the switch are shown in the “closed position”.

090 Close left engine cowling.



ADAS-G-010-1/A - 23-

3.6 Harness Installation

NOTE: Route all cables to follow existing wiring harnesses.

3.6.1 “J1” Harness Installation

010 Connect the J1 harness to the J1 connector on the ADAS+ processor.

020 Route the AAV00B24 cable to the aircraft battery and ground connections. This power source will beprotected by a 1 Amp fuse and is not accessible by the pilot and/or crew.

030 Route the AAV10A22 cable to the aircraft switched power connection. This power source will beprotected by a 1 Amp circuit breaker and is not accessible by the pilot and/or crew.

040 Route the AAA22D22 cable to the installed Pitot and Static transducers.



020 Route the AAA20D24 cable to the installed torque transducers.

030 Route the AAP10B24 cable to the N1 (Ng) engine compartment tachometer.

040 Route the AAP11B24 cable to the NP engine compartment tachometer.

050 Route the AAP00B24 cable to the fuel flow engine compartment tachometer.

060 Route the AAA10B22 cable to the engine Temp (ITT) engine compartment mounting pad.



020 Route the AAV30D24 cable to the installed TREND switch / fault lamp assembly.

030 Route the AAB40D24 cable to the installed download port.

040 Route the AAA00D24 cable to the installed OAT sensor.

050 Route the AAD11A24 cable to the Bleed Air switch.

060 Route the AAD18A24 cable to the EPL switch located in the pedestal console in the cockpit.

070 Route the AAD10B24 cable to the cockpit hour meter.

080 Route the AAD16A24 cable to the Particle Separator switch.

090 Tie back and secure any spare cables.



ADAS-G-010-1/A - 24-

4 INSTALLATION - ELECTRICAL

4.1 Cockpit Components

Wiring Notes:

ConXall™ connectors are installed in this and the next section. The following tools are recommended by thevendor for use with these connectors (vendor P/Ns): Insertion Bit (356-20), Pin Removal Bit (356-201), SocketRemoval 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.

4.1.1 Standard Cockpit TREND Switch Wiring


The TREND switch and the download port cables both use 6 pin connectors. The TRENDswitch cable uses a socket connector (6SG type) and the download port cable uses a pinconnector (6PG type). Be sure to use the correct connector with the appropriate cable.

Figure A- 22: Standard TREND Switch and Lamp Connector Wiring

Wiring Instructions

010 Trim the Ind Sw “AAV30D24” and Ind Sw Open “AAV32A24” cables to length, and slide the correctConXall™ connector backshell parts onto the cable.

NOTE: The “Ind Sw Open” cable is not used, but should be tied back near the lamp ConXall ™connector for future upgrades.

020 Refer to the illustration Figure A- 22 and connect the cable to the included ConXall™ connectorusing the socket configuration shown. Splice a short wire lead to the cable shield with a shrink-onsolder sleeve to make the Pin 6 shield connection, upper and middle.

030 Assemble the backshell to the connector, connect it to the lamp, and secure all wiring.



ADAS-G-010-1/A - 25-

4.1.2 Optional ENGINE/TREND Split Lamp Wiring


The ENGINE/TREND Split Lamp and the download port cables both use 6 pin connectors.The ENGINE/TREND Split Lamp cables use a socket connector (6SG type) and the downloadport cable uses a pin connector (6PG type). Be sure to use the correct connector with theappropriate cable.

Figure A- 23: Optional ENGINE/TREND Split Lamp Connector Wiring

Wiring Instructions

040 Trim the Ind Sw “AAV30D24” and Ind Sw Open “AAV32A24” cables to length, and slide the correctConXall™ connector backshell parts onto the cable.

050 Refer to the illustration Figure A- 23 and connect the cable to the included ConXall™ connectorusing the socket configuration shown. Splice a short wire lead to the cable shield with a shrink-onsolder sleeve to make the Pin 6 shield connection, upper and middle.

060 Assemble the backshell to the connector, connect it to the lamp, and secure all wiring.

4.1.3 Download Port Connector Wiring

Wiring Instructions

010 Trim the download port connector “AAB40D24” cable to length, and slide the correct ConXall™connector backshell parts onto the cable.

020 Refer to the illustration Figure A- 24, and connect the cable to the included ConXall™ plugconnector using the illustrated pin configuration. Pin 1 is identified by a dimple. Pin 6 has noconnection.

030 Assemble the backshell to the connector, connect it to the port, and secure all wiring.

'

Figure A- 24: Download Port Connector



ADAS-G-010-1/A - 26-

4.1.3.1 Optional Garmin G620 Interface Cable“ADAS-C-072-1”

NOTE: This option requires ADAS+ software version 5.1.0 or greater and Garmin G620 software version6.10 or greater.

010 Route the “AAB45B24” cable from the download port to the Garmin G620 connector PG01, behindthe copilots panel, as shown in Figure A- 25 and Figure A- 26.

020 Connect PG01 / JG01 together and secure wiring.

030 Route the “AAD18A24” cable from the JG01 connector to the TREND Switch / Fault Lamp. Refer toSection 6.6 thru 6.9 for more details.

040 Trim the “AAD18A24” cable to length and splice to pin 3 (WHT/GRN) of the TREND Switch / FaultLamp female ConXall Connector. Refer to Section 6.6 thru 6.9 for more details.

050 Secure all wiring.

Figure A- 25: Connector PG01 located behind panel shown

Figure A- 26: Connector PG01 Location (behind copilot panel)

PG01

PG01



ADAS-G-010-1/A - 27-

4.2 Navigation

4.2.1 Pitot / Static Pressure Transducer Wiring

010 Trim the Pitot/Static “AAA22D22” cable to length. Following Figure A- 27, splice to the transducerharnesses using the following wire splice configuration:

Color Transducer WiresWHT/ORG GRN Wire Pitot Pressure TransducerWHT RED Wire Both TransducersWHT/BLU BLK Wire Both TransducersWHT/GRN GRN Wire Static Pressure Transducer


Figure A- 27: Pitot/Static Transducer Wiring.

4.2.2 Outside Air Temperature (OAT) Probe Wiring

The OAT probe uses 6 pin ConXall™ connectors to facilitate removal of the engine cowling. The cable from theprocessor uses a socket connector (6SG type), and the cable from the OAT probe uses a pin connector 6PGtype, (). Be sure to use the correct connector with the appropriate cable.

010 Trim the OAT “AAA00D24” cable from the processor to length. Following Figure A- 28, connect thecable to the ConXall™ connector.

Processor Wires OAT WiresWHT/ORG RED OAT Probe WireWHT RED OAT Probe WireWHT/BLU WHT OAT Probe WireWHT/GRN WHT OAT Probe Wire



ADAS-G-010-1/A - 28-

Figure A- 28: Process Cable Connector

020 Trim the cable from the OAT probe to length. Following Figure A- 29, connect the cable to theConXall™ connector.

Figure A- 29: OAT Probe Connector

030 Connect the two connectors.


Figure A- 30: OAT Probe Wiring.



ADAS-G-010-1/A - 29-

4.3 Engine Indicating

4.3.1 Engine Temp (ITT)

010 Trim the ITT ”AAA10B22” cable to length

020 Crimp terminal lugs to the thermocouple cable attaching the “CR” lug to the yellow wire and the “AL”lug to the red wire.

030 Following the illustration Figure A- 31, connect the thermocouple cable to the appropriateconnections on the engine mounting pad using the following pin configuration.

Color Engine ITT Mounting PadRED Engine ITT Mounting Pad – Alumel –YEL Engine ITT Mounting Pad – Chromel +


AIRCRAFT INDICATORHARNESS

REDWIRE

YELWIRE

SHRINKSLEEVING" Pull Back and CoverShield "

2-CONDENG ITT

CHROMEL

ALUMEL

Figure A- 31: ITT Wiring



ADAS-G-010-1/A - 30-

4.3.2 Engine N1 (Ng) Speed Sensor

010 Trim the N1 SPD ”AAP10B22” cable to length.

020 Following Figure A- 32, splice to the N1 (Ng) engine compartment tachometer using the followingpin configuration.

Color Engine N1 (Ng) Speed SensorWHT N1 Signal +WHT/BLU N1 Signal –


4.3.3 Engine Np Speed Sensor

010 Trim the Np ”AAP11B22” cable to length.

020 Following Figure A- 32, splice to the Np engine compartment tachometer using the following pinconfiguration.

Color Engine Np Speed SensorWHT N2 Signal +WHT/BLU N2 Signal –


4.3.4 Engine Wf Sensor

010 Trim the Wf “AAP00B22” cable to length.

020 Following Figure A- 32, splice to the Wf Speed Sensor in the engine compartment using thefollowing pin configuration.

Color Engine Wf Speed SensorWHT Wf Signal +WHT/BLU Wf Signal –




ADAS-G-010-1/A - 31-

AIRCRAFT INDICATOR HARNESS SIG +

WHT

WIR

E

SHRINK SLEEVING" Pull Back and Cover Shield "

N1, N2 or NP MarkedHarness

WHT/B

LUW

IRE

SIG -

Engine Tachometer

RAYCHEM SPLICE

Figure A- 32: Engine Tachometer Wiring

4.3.5 Engine Torque Wiring

010 Trim the Eng Torque “AAA20D22” cable to length. Following Figure A- 33, splice to the transducerharnesses using the following wire splice configuration:

Color Transducer WiresWHT/ORG GRN Wire Torque Pressure Transducer HIGHWHT RED Wire Both TransducersWHT/BLU BLK Wire Both TransducersWHT/GRN GRN Wire Torque Pressure Transducer LOW


Figure A- 33: Engine Torque Wiring



ADAS-G-010-1/A - 32-

4.3.6 Particle Separator Switch Wiring

010 Trim the Particle Separator Switch “AAD16A24” cable to length.

020 Splice to either one of the BLK wires from the Particle Separator Switch. The other BLK wire fromthe Particle Separator Switch will be tied to aircraft ground.


4.4 Airframe Sensors

4.4.1 Engine Hour Meter

010 Trim the DIGITAL 1 “AAD10B24” cable to length.

020 Splice to the hour meter located on the co-pilots side of the instrument panel using the following pinconfiguration:

Color Aircraft Hour meter SignalWHT Hour Meter –WHT/BLU Aircraft Ground


4.4.2 Bleed Air

010 Trim the DIGITAL 2 “AAD11A24” cable to length.

020 Splice to the NO position of switch S53 in the cockpit.


4.4.3 Engine EPL

010 Trim the DIGITAL 3 “AAD18A24” cable to length.

020 Splice to the C Terminal of the S91 switch located in the engine control console.


4.5 Electrical Power

4.5.1 Battery Power / Ground Connection

010 Trim the Cont Pwr “AAV00B22” cable to length.

020 Following the illustration Figure A- 34, connect the white (positive) wire to supplied fuse, connect tothe K3 Aircraft Battery Relay, and connect the white/blue (negative) wire to aircraft ground followingthe pin configuration below:

Color Aircraft Power SourceWHT K3 Aircraft Battery RelayWHT/BLU Aircraft Ground




ADAS-G-010-1/A - 33-

Figure A- 34: Aircraft Battery Final Wiring

Figure A- 35: Fuse Holder Installed in Power Box on Cessna Caravan 208B

4.5.2 Bus (Switched) Power Connection

010 Refer to the wiring diagram and Figure A- 36. Trim the SW PWR 1 “AAV10A22” and Sw Pwr 2“AAV31A22” cable to length.

020 Connect the supplied breaker to aircraft bus (switched) power.


K3 AircraftBattery Relay



ADAS-G-010-1/A - 34-

Figure A- 36: Aircraft Bus Final Wiring

4.6 Final Installation Notes

010 Route and secure all wires making sure engine / aircraft control movements will not be affected bythe ADAS+ wiring. Properly dress all splices and shield terminations. Make sure wiring will not comein contact with hot sections of the engine. Make sure wire harness will not come in contact withsharp sections of the aircraft.

020 Refer back to Installation Manual ADAS-G-010-1 for all calibration and system verificationprocedures.



ADAS-G-010-1/A - 35-

5 HARNESS CONNECTOR SIGNAL PINOUTS

5.1 Power/ Sensor Cable J1, 15 Pin S Keyed Connector


Before making any wiring connections, verify all connection locations with the aircraftmanufacturer’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 acable behind a label, be sure to re-label it.

Connector Harness Wired ToPin Wire Color Signal Name Refer to Section 6

4 COND CABLEJ1 A WHT/ORG Pitot (Signal +) GRN Wire Pitot TransducerJ1 B WHT Pitot/Static (5 VDC) RED Wire Pitot/Static TransducerJ1 N WHT/BLU Pitot/Static (Ground) BLK Wire Pitot/Static TransducerJ1 D WHT/GRN Static (Signal +) GRN Wire Static Transducer

1 COND CABLEJ1 F WHT 28 VDC Bus Power Bus Power, Supplied 1 Amp Breaker

2 COND CABLEJ1 H WHT 28 VDC Battery Power Battery Power, 1 Amp Fuse

J1 G WHT/BLU System Ground Aircraft Ground

J1 J UnusedJ1 K UnusedJ1 C UnusedJ1 E UnusedJ1 L UnusedJ1 M UnusedJ1 R UnusedJ1 P Unused



ADAS-G-010-1/A - 36-

5.2 Sensor Cable J2, 15 Pin SA Keyed Connector




Route all harnesses along existing harnesses wherever possible.



4 COND CABLEJ2 A WHT Eng Torque (5 VDC) RED Wire Both Torque TransducersJ2 B WHT/ORG Eng Torque (Signal +) GRN Wire High Torque TransducerJ2 C WHT/BLU Eng Torque (Ground) BLK Wire Both Torque TransducersJ2 F WHT/GRN Eng Torque (Signal –) GRN Wire Low Torque Transducer

2 COND CABLEJ2 D WHT Eng N1 Spd (Sig +) N1 Tachometer +J2 H WHT/BLU Eng N1 Spd (Sig –) N1 Tachometer –

2 COND CABLEJ2 E WHT Eng Np Spd (Sig +) Np Tachometer +J2 N WHT/BLU Eng Np Spd (Sig –) Np Tachometer –

2 COND CABLEJ2 G WHT Eng Fuel Flow (Sig +) Fuel Flow Transmitter +J2 R WHT/BLU Eng Fuel Flow (Sig –) Fuel Flow Transmitter –

THERMOCOUPLEJ2 J RED Eng ITT (Alumel –) ITT Engine Pad –J2 K YEL Eng ITT (Chromel +) ITT Engine Pad +

J2 P Unused



ADAS-G-010-1/A - 37-

5.3 Cockpit Trend / Sensor Cable, J3, 37 Pin S Keyed Connector




Route all harnesses along existing harnesses wherever possible. Do not connect to enginescavenge lines.



1 COND CABLE-- WHT SW PWR 2 Aircraft Bus Power, Supplied 1 Amp

Breaker

1 COND CABLEJ3 3 WHT Digital 2 Bleed Air - S53

1 COND CABLEJ3 4 WHT Digital 3 EPL (Emergency Power Lever) - S91

1 COND CABLEJ3 5 WHT Digital 4 Particle Separator Switch

4 COND CABLE-- WHT IND SW (VCC) Lamp ConXall™ Pin 1

J3 19 WHT/ORG IND SW (Switched) Lamp ConXall™ Pin 4J3 18 WHT/BLU IND SW (GND) Lamp ConXall™ Pin 2J3 1 WHT/GRN IND SW (TREND Switch) Lamp ConXall™ Pin 3

1 COND CABLE (Using Standard Trend Lamp)J3 37 WHT IND SW Open 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 CABLEJ3 16 WHT Download Port (RS485+) Download ConXall™ Pin 1J3 17 WHT/ORG Download Port (RS485–) Download ConXall™ Pin 2J3 18 WHT/BLU Download Port (GND) Download ConXall™ Pin 3J3 2 WHT/GRN Download Port (Run/Conf) Download ConXall™ Pin 4



ADAS-G-010-1/A - 38-

4 COND CABLEJ3 21 WHT Air Temp (“D”) OAT ConXall™ Pin 1J3 22 WHT/BLU Air Temp (“G”) OAT ConXall™ Pin 2J3 23 WHT/ORG Air Temp (“R+”) OAT ConXall™ Pin 3J3 24 WHT/GRN Air Temp (“R–”) OAT ConXall™ Pin 4

4 COND CABLEJ3 31 WHT Vertical Accl. + Terminate and Tie Back (near download port)J3 32 WHT/ORG Vertical Accl. – Terminate and Tie Back (near download port)J3 33 WHT/BLU Vertical Accl. + Terminate and Tie Back (near download port)J3 34 WHT/GRN Vertical Accl. – Terminate and Tie Back (near download port)

2 COND CABLEJ3 35 WHT Digital 1+ Hour Meter –J3 36 WHT/BLU Digital 1 – Aircraft Ground

4 WIRE JUMPER7 GRN Configuration Ground Set at Factory8 GRN Configuration ID 0 Set at Factory9 GRN Configuration ID 1 Set at Factory10 GRN Configuration ID 2 Set at Factory

6 Unused8 Unused9 Unused10 Unused12 Unused13 Unused20 Unused25 Unused26 Unused27 Unused28 Unused29 Unused30 Unused



ADAS-G-010-1/A - 39-

6 Wiring Diagram

6.1 ADAS + Connection Chart – Cessna Model 208 Series

Sensor WireNumber

Caravan with Electric Torque System Caravan with Wet Torque System

Aircraft Component ADAS+ Connector Aircraft Component ADAS+ Connector

Aircraft Sensors

Engine ITT AAA10B22 Engine Assy. Block J2 Engine Assy. Block J2

RED Pin J Alumel Red RED Pin J Alumel Red

YEL Pin K Chromel Yel YEL Pin K Chromel Yel

Engine N1 (Ng) AAP10B22 J134 J2 J134 J2

Pin B BLK Pin D WHT Pin B BLK Pin D WHT

Pin A WHT Pin H WHT/BLU Pin A WHT Pin H WHT/BLU

Engine Torque (Tq) AAA20D22 J211 J2 Supplied Transducers J2

Model 208 Pin A WHT Torque RED Wire Pin A WHT

S/N 00007 thru 00096 Pin C Pin B WHT/ORG Torque GRN Wire Pin B WHT/ORG

Pin C WHT/BLU Torque BLK Wire Pin C WHT/BLU

Pin D Pin F WHT/GRN Torque GRN Wire Pin F WHT/GRN

Engine Torque (Tq) AAA20D22 J211 J2 Supplied Transducers J2

Model 208 Pin A WHT Torque RED Wire Pin A WHT

S/N 00097 thru 00199 Pin A Pin B WHT/ORG Torque GRN Wire Pin B WHT/ORG

Model 208B Pin C WHT/BLU Torque BLK Wire Pin C WHT/BLU

S/N 0001 AND ON Pin B Pin F WHT/GRN Torque GRN Wire Pin F WHT/GRN

Propeller Speed (Np) AAP11B22 J34 J2 J34 J2

Pin A BLK Pin E WHT Pin A BLK Pin E WHT

Pin B WHT Pin N WHT/BLU Pin B WHT Pin N WHT/BLU

Fuel Flow (Wf) AAP00B22 J5 J2 J5 J2

Pin A WHT Pin G WHT Pin A WHT Pin G WHT

Pin B BLK Pin R WHT/BLU Pin B BLK Pin R WHT/BLU

Bleed Air AAD11A24 S53 J3 S53 J3

NO Pin 3WHT NO Pin 3WHT

Emergency PowerLever

AAD18A24 S91 J3 S91 J3

S/N 00001 Thru 00140 C – WH1 Pin 4 WHT C – WH1 Pin 4 WHT

Emergency PowerLever

AAD18A24 S91 J3 S91 J3

S/N 00141 AND > C - WH4 Pin 4 WHT C - WH4 Pin 4 WHT

Hour meter AAD10B24 IND12 (Hour Meter) J3 IND12 (Hour Meter) J3

J305 – DF7 Pin 35 WHT J305 – DF7 Pin 35 WHT

Ground Pin 36 WHT/BLU Ground Pin 36 WHT/BLU

Battery Power AAV00B22 Relay K 3 J1 Relay K 3 J1

A2 Pin H WHT A2 Pin H WHT

Ground Pin G WHT/BLU Ground Pin G WHT/BLU

Bus Power AAV10A22 Relay K 3 J1 Relay K 3 J1

A1 Pin F WHT A1 Pin F WHT



ADAS-G-010-1/A - 40-

Sensor WireNumber

Caravan with Electric Torque System Caravan with Wet Torque System

Aircraft Component ADAS+ Connector Aircraft Component ADAS+ Connector

Supplied Sensors

OAT Probe AAA00D24 Oat Probe J3 Oat Probe J3

Red Wire Pin 21 WHT Red Wire Pin 21 WHT

Wht Wire Pin 22 WHT/BLU Wht Wire Pin 22 WHT/BLU

Red Wire Pin 23 WHT/ORG Red Wire Pin 23 WHT/ORG

Wht Wire Pin 24 WHT/GRN Wht Wire Pin 24 WHT/GRN

Airspeed / AltitudeSensor

AAA22D22 Transducers J1 Transducers J1

Pitot Grn Wire Pin A WHT/ORG Pitot Grn Wire Pin A WHT/ORG

Pitot/Static Red Wire Pin B WHT Pitot/Static Red Wire Pin B WHT

Pitot/Static Blk Wire Pin N WHT/BLU Pitot/Static Blk Wire Pin N WHT/BLU

Static Grn Wire Pin D WHT/GRN Static Grn Wire Pin D WHT/GRN

Particle SeparatorSwitch Sensor

AAD16A24 Particle SeparatorSwitch

J3 Particle SeparatorSwitch

J3

BLK Wire Pin 5 WHT BLK Wire Pin 5 WHTBLK Wire Aircraft Ground BLK Wire Aircraft Ground

Table A- 1: ADAS+ Connection Chart



ADAS-G-010-1A - 41 -

6.2 ADAS+ Schematic – No Supplied Torque Transducers

AAV30D24

AAB40D24

123456

123456

AAD18A24

DOWNLOAD PORT ASSEMBLY

Female

N/C

OEM SUPPLIED TRANSDUCER OPTION

WHT/GRN - TREND

SwitchBLKMagnetic ReedBLK

PARTICLE SEPARATOR

AAA24D24

28 VDC PWR

28 VDC BATTGND

P/S 5 VDCP/S GND

PITOT SIGSTATIC SIG

J1 - 15 S

F

HG

BNAD

WHTAAD16A24

TRQ 5 VDCTRQ HI SIGTRQ GNDTRQ LO SIG

N2 SPD -

FUEL FLOW -

N1 SPD -N1 SPD +

N2 SPD +

ITT- (AL)

FUEL FLOW +

ITT+ (CH)

J2 - 15 SA

ABCF

E

D

N

GR

J

H

K Transducer

REDBLKGRN

FUSE 1 AMP

1 2

CIRCUIT BREAKER 1 AMP

1 2

Transducer

REDBLKGRN

N1 TACH +N1 TACH -

AB

NP TACH +NP TACH -

AB

FUEL FLOW +FUEL FLOW -

AB

ITT- (AL)ITT+ (CH) .

.

123456

123456

J1.1J1.2J1.3J1.4J1.5J1.6J1.7J1.8J1.9

J1.10

123456

MICROSWITCH PTT Lamp 1 +Lamp 1 -SW1-NO

SW1-COMMSW1-NCSW2-NO

SW2-COMMSW2-NC

123456

OAT Probe

OAT-GWHT

OAT-R+RED

OAT-DRED

OAT R-WHT

Transducer

0-5 VDC

SIG -

SIG +

S53.

S91

AC HOURMETER IND12

+ -

RUN/CONF SW

RS-485+ (B)RS-485- (A)GND

TREND SW

VCCGND

LAMP 1LAMP 2

CONG GNDCONG ID1CONG ID2CONG ID4

OAT DOAT GOAT R+OAT R-

EPL SIG

HOURMETER +HOURMETER -

BLEED SIG

P/S SIG

Vertical Accl +Vertical Accl SIGVertical Accl -Vertical Accl

J3 - 37 S

2

161718

119

78910

37

21222324

4

3536

3

5

3433

3132

AAV31A22

AAV31A22

(DIRECT BATTERY)

(SWITCHED POWER)

AIRCRAFT PITOT

AIRCRAFT STATIC

ADAS+ PROCESSOREMU-A-010-3

WHT

WHT

WHT

WHT/BLU

WHT/BLU

WHT/BLU

YELRED

N/C

N/C

CONFIGID = 7

WHT/GRN - RUN/CONF

WHT/ORG - RS485 - (A)

CONNECTORCOMM PORT

WHT - LAMP PWR

WHT - RS485 + (B)

WHT/BLU - GND

WHT/ORG - LAMP 1 SW

WHT/BLU - GND

WHT - LAMP 2 SW

WHTWHT/BLU

ENGINE T/C

BLOCK

AIRCRAFT

CONN J134

AIRCRAFT

CONN J34

AIRCRAFT

CONN J5

ESSENTIAL BUS

GROUND STRAPAIRCRAFT

CONN J211

AIRCRAFT BLEED VALVE

BATTERYRELAY

K3

WHT

WHT

WHT

WHTWHT/BLU

WHT/BLU

WHT/GRNWHT/ORG

WHT/ORG

WHTWHT/BLU

WHT/GRN

WHT

AIRCRAFT EPL

AAV00B22

AAV10A22

To Bus Breaker

AAP11B22

AAP10B22

AAA22D22

AAA10B22

AAP00B22

AAD10B24

AAA20D22

AAD11A24

AAV32A24

AAA00D24

WHT/BLUWHT/ORG

WHT

WHT/GRN

Male

Female

Female

Male

FAULT LAMP ASSEMBLY Male

CONNECTORFAULT LAMP

WHT

WHT/BLUWHT/ORG

WHT/GRN

N/C

Figure A- 37: Wiring Schematic– No Supplied Torque Transducers



ADAS-G-010-1A - 42 -

6.3 ADAS+ Schematic – Supplied Torque Transducers

123456

DOWNLOAD PORT ASSEMBLY

Female

LOW

HIGH

N/C


AAV30D24

PARTICLE SEPARATOR

AAD16A24WHT

WHT/GRN - TREND

AAA24D24


N2 SPD -

FUEL FLOW -

N1 SPD -N1 SPD +

N2 SPD +

ITT- (AL)

FUEL FLOW +

ITT+ (CH)

J2 - 15 SA

ABCF

E

D

N

GR

J

H

K

28 VDC PWR

28 VDC BATTGND

P/S 5 VDCP/S GND

PITOT SIGSTATIC SIG

J1 - 15 S

F

HG

BNAD


1 2

FUSE 1 AMP

1 2

Transducer

REDBLKGRN

N1 TACH +N1 TACH -

AB

Transducer

REDBLKGRN

NP TACH +NP TACH -

AB

123456


.


AB

123456

J1.1J1.2J1.3J1.4J1.5J1.6J1.7J1.8J1.9

J1.10

123456

123456

MICROSWITCH PTT Lamp 1 +Lamp 1 -SW1-NO

SW1-COMMSW1-NCSW2-NO

SW2-COMMSW2-NC

S53.

OAT Probe

OAT-GWHT

OAT-R+RED

OAT-DRED

OAT R-WHT

S91

AC HOURMETER IND12

+ -

RUN/CONF SW

RS-485+ (B)RS-485- (A)GND

TREND SW

VCCGND

LAMP 1LAMP 2



EPL SIG


BLEED SIG

P/S SIG


J3 - 37 S

2

161718

119

78910

37

21222324

4

3536

3

5

3433

3132

AAV31A22

AAV31A22

AIRCRAFT STATIC

AIRCRAFT PITOT

(DIRECT BATTERY)

(SWITCHED POWER)

WHT/GRNWHT/BLU


WHTWHT/ORG

WHT

YELRED

WHT/BLU

WHT/BLU

WHT/BLU

WHT

WHT

CONFIGID = 7

WHT - RS485 + (B)

WHT/BLU - GNDWHT/GRN - RUN/CONF


CONNECTORCOMM PORT

WHT - LAMP 2 SWWHT/ORG - LAMP 1 SW

WHT/BLU - GNDWHT - LAMP PWR

AIRCRAFT

CONN J5

ENGINE T/C

BLOCK

WHT/BLUWHT

WHT


BATTERYRELAYK3

ESSENTIAL BUS

GROUND STRAP

AIRCRAFT

CONN J134

AIRCRAFT

CONN J34 WHT/GRNWHT/ORG

WHTWHT/BLU

WHT/BLUWHT

WHT

WHT/GRNWHT/ORG

WHTWHT/BLU

AIRCRAFT EPL

WHT

AAV00B22

AAV10A22

To Bus Breaker

AAB40D24

AAD10B24

AAA20D22

AAA10B22

AAP00B22

AAP11B22

AAP10B22

AAA22D22

AAA00D24

AAD18A24

AAD11A24

AAV32A24

WHTWHT/BLUWHT/ORGWHT/GRN

Transducer

RED

GRNBLK

Male

Transducer

RED

BLKGRN

Female

FemaleMale

N/C

ENGINETORQUE

FAULT LAMP ASSEMBLY

CONNECTORFAULT LAMP

Male

123456

Figure A- 38: Wiring Schematic – Supplied Torque Transducers



ADAS-G-010-1A - 43 -

6.4 ADAS+ Schematic (Split Lamp Option) – No Supplied Torque Transducers

AAV30D24

OEM SUPPLIED TRANSDUCER OPTION

WHT/GRN - TREND

AAA24D24

28 VDC PWR

28 VDC BATTGND

P/S 5 VDCP/S GND

PITOT SIGSTATIC SIG

J1 - 15 S

F

HG

BNAD


N2 SPD -

FUEL FLOW -

N1 SPD -N1 SPD +

N2 SPD +

ITT- (AL)

FUEL FLOW +

ITT+ (CH)

J2 - 15 SA

ABCF

E

D

N

GR

J

H

K Transducer

REDBLKGRN

FUSE 1 AMP

1 2


1 2

Transducer

REDBLKGRN

N1 TACH +N1 TACH -

AB

NP TACH +NP TACH -

AB


AB


.

OAT Probe

OAT-GWHT

OAT-R+RED

OAT-DRED

OAT R-WHT

Transducer

0-5 VDC

SIG -

SIG +

S53.

S91

AC HOURMETER IND12

+ -

RUN/CONF SW

RS-485+ (B)RS-485- (A)GND

TREND SW

VCCGND

LAMP 1LAMP 2



EPL SIG


BLEED SIG

P/S SIG


J3 - 37 S

2

161718

119

78910

37

21222324

4

3536

3

5

3433

3132

AAV31A22

AAV31A22

DIRECT BATTERY

SWITCHED POWER

AIRCRAFT PITOT

AIRCRAFT STATIC


WHT

WHT

WHTWHT/BLU

WHT/BLU

YELRED

WHT/BLU

N/C

N/C

CONFIGID = 7

WHT/GRN - RUN/CONF

WHT/ORG - RS485 - (A)WHT - RS485 + (B)

WHT/BLU - GND

WHT/ORG - LAMP 1 SW

WHT/BLU - GNDWHT - LAMP PWR

WHT - LAMP 2 SW

WHTWHT/BLU

ENGINE T/C

BLOCK

AIRCRAFT

CONN J134

AIRCRAFT

CONN J34

AIRCRAFT

CONN J5

GROUND STRAPAIRCRAFT

CONN J211

AIRCRAFT BLEED VAVE

BATTERYRELAYK3

ESSENTIAL BUS

WHT

WHT

WHT

WHT/BLU

WHT/BLU

WHT/GRNWHT/ORG

WHT

WHT/ORG

WHTWHT/BLU

WHT/GRN

WHT

AIRCRAFT EPL

AAV00B22

AAV10A22

To Bus Breaker

AAP10B22

AAA22D22

AAA10B22

AAP00B22

AAP11B22

AAD10B24

AAA20D22

AAD11A24

AAV32A24

AAA00D24

AAD18A24

WHT/ORG

WHT

WHT/GRN

WHT/BLU

FemaleMale

WHT/BLUWHT/ORGWHT

WHT/GRN

123456

123456

AAB40D24

COMM PORT

123456

123456

J1.10J1.9J1.8J1.7J1.6J1.5J1.4J1.3J1.2J1.1

SPLIT LAMP

123456

123456

MICROSWITCH PTTLamp +Lamp -

SW1-NOSW1-COMM

SW1-NCSW2-NO

SW2-COMMSW2-NCLamp 2 +Lamp 2 -

Female Male

Male Female

CONNECTOR

COMM PORT

CONNECTOR

SPLIT LAMP


PARTICLE SEPARATOR

WHTAAD16A24

N/C

Figure A- 39: Wiring Schematic (Split Lamp Option) – No Supplied Torque Transducers



ADAS-G-010-1A - 44 -

6.5 ADAS+ Schematic (Split Lamp Option) – Supplied Torque Transducers


PARTICLE SEPARATOR

HIGH

LOW

123456

AAV30D24

WHT/GRN - TREND

123456

Male

AAA24D24

28 VDC PWR

28 VDC BATTGND

P/S 5 VDCP/S GND

PITOT SIGSTATIC SIG

J1 - 15 S

F

HG

BNAD


N2 SPD -

FUEL FLOW -

N1 SPD -N1 SPD +

N2 SPD +

ITT- (AL)

FUEL FLOW +

ITT+ (CH)

J2 - 15 SA

ABCF

E

D

N

GR

J

H

K Transducer

REDBLKGRN

FUSE 1 AMP

1 2


1 2

Transducer

REDBLKGRN

N1 TACH +N1 TACH -

AB

NP TACH +NP TACH -

AB


AB


.

OAT Probe

OAT-GWHT

OAT-R+RED

OAT-DRED

OAT R-WHT

S53.

S91

AC HOURMETER IND12

+ -

RUN/CONF SW

RS-485+ (B)RS-485- (A)GND

TREND SW

VCCGND

LAMP 1LAMP 2



EPL SIG


BLEED SIG

P/S SIG


J3 - 37 S

2

161718

119

78910

37

21222324

4

3536

3

5

3433

3132

AAV31A22

AAV31A22

(SWITCHED POWER)

(DIRECT BATTERY)

AIRCRAFT PITOT

AIRCRAFT STATIC


WHT/BLUWHT/GRN

WHT/ORGWHT

WHT

WHT

WHT

WHT/BLU

WHT/BLU

WHT/BLU

REDYEL

CONFIGID = 7


WHT/GRN - RUN/CONFWHT/BLU - GND

WHT - RS485 + (B)

WHT - LAMP PWR

WHT - LAMP 2 SW

WHTWHT/BLU

ENGINE T/C

BLOCK

AIRCRAFT

CONN J5

AIRCRAFT

CONN J34

AIRCRAFT

CONN J134

GROUND STRAP

ESSENTIAL BUS

BATTERYRELAYK3


WHT

WHT

WHTWHT/BLU

WHT/BLUWHT

WHT/ORGWHT/GRN

WHT/BLUWHT

WHT/ORGWHT/GRN

WHT

AIRCRAFT EPL

To Bus Breaker

AAV10A22

AAV00B22

AAA22D22

AAP10B22

AAP11B22

AAP00B22

AAA10B22

AAA20D22

AAD10B24

AAV32A24

AAD11A24

AAD18A24

AAA00D24

AAD16A24WHT

WHT

WHT/ORGWHT/BLU

WHT/GRN

Transducer

RED

GRNBLK

Transducer

RED

BLKGRN

Female

ENGINETORQUE

WHT/BLU - GND

AAB40D24

COMM PORT

123456

123456

J1.10J1.9J1.8J1.7J1.6J1.5J1.4J1.3J1.2J1.1

SPLIT LAMP

123456

123456

MICROSWITCH PTTLamp +Lamp -

SW1-NOSW1-COMM

SW1-NCSW2-NO

SW2-COMMSW2-NCLamp 2 +Lamp 2 -

N/C

WHT/ORG - LAMP 1 SW

MaleFemale

FemaleMale

CONNECTOR

COMM PORT

CONNECTOR

SPLIT LAMP

Figure A- 40: Wiring Schematic (Split Lamp Option) – No Supplied Torque Transducer



ADAS-G-010-1A - 45 -

6.6 ADAS+ Schematic (Garmin G620 Option) – No Supplied Torque Transducers

Figure A- 41: Wiring Schematic (Garmin G620 Option) – No Supplied Torque Transducers



ADAS-G-010-1A - 46 -

6.7 ADAS+ Schematic (Garmin G620 Option) – Supplied Torque Transducers

Figure A- 42: Wiring Schematic (Garmin G620 Option) – Supplied Torque Transducers



ADAS-G-010-1A - 47 -

6.8 ADAS+ Schematic (Garmin G620 / Split Lamp Option) – No Supplied Torque Transducers

Figure A- 43: Wiring Schematic (Garmin G620 / Split Lamp Option) – No Supplied Torque Transducers



ADAS-G-010-1A - 48 -

6.9 ADAS+ Schematic (Garmin G620 / Split Lamp Option) – Supplied Torque Transducers

Figure A- 44: Wiring Schematic (Garmin G620 / Split Lamp Option) – Supplied Torque Transducers



ADAS-G-010-1A - 49 -

7 Appendix A

7.1 Particle Separator Switch Installation

Figure 1: Particle Separator Switch Installation – Sheet 1 of 5



ADAS-G-010-1A - 50 -




ADAS-G-010-1A - 51 -




ADAS-G-010-1A - 52 -




ADAS-G-010-1A - 53 -


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