Pratt and Whitney Engine Services FAST34E Engine Flight data Acquisition, Storage and Transmission User Manual DTU G 010 1 B

Pratt & Whitney Engine Services, Inc. Engine Flight data Acquisition, Storage and Transmission DTU G 010 1 B

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User Manual Part 1

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Document Author: PW46592

P&W ENGINE SERVICES, INC.
Part 23 Aircraft
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
REVISION HISTORY
Rev Status
of Sheets
Rev
Sheet
Rev
Sheet
Rev
Sheet
13
29
ii
14
30
iii
15
31
iv
16
32
17
33
18
34
19
35
20
36
21
37
22
23
24
25
10
26
11
27
12
28
LOG OF REVISIONS
REV.
NO
ECO #
DESCRIPTION
DATE
PAGES REVISED
Initial Release
11/07/03
Edit installation instructions for processor mounting and wiring
harness routing. Added WOW and power connection tables and
reference for mounting location
03/15/04
Cover, i, ii, iii, 4, 5, 6,
8, 10, 13, 14, 15, 18,
19, 20, 21
Added ADAS+ Upgrade instructions, diode protection circuit,
revised power connections, and ADAS+ Upgrade wiring schematic
04/15/04
Cover, i, ii, iii, 2, 3, 9,
11, 12, 13, 14, 17, 19,
20, 23, 24, 25, 26, 28
Added new mounting illustrations and revised Parts List
05/27/04
Cover, i, ii, iii, 4, 5, 6,
7, 8, 9
Added new mounting configuration for LAN antenna, and
instructions for Installation Summary table, revised Parts List,
mounting bracket instructions, and harness installation instructions
06/07/04
Cover, i, ii, iii, 3, 4, 5,
9, 10, 11, 13, 14, 21, 22
Revised wiring diagram for ADAS+ Upgrade Monitors and updated
photograph for antenna location on Raytheon model aircraft
06/28/04
Cover, i, ii, iii, 13, 23,
24, 25, 31
823
Update part numbers and add a kit for the ADAS+ installed on
Raytheon Models. Revise the ConXall connecter wiring instructions
for the download port and DTU Status lamp. Revise Installation
Caution regarding the length of wire from the protection device to the
power source.
06/03/05
Cover, i – iii, 2 – 32
859
Update figures B-2, B-3, and B4 to show correct configuration of the
double-stack bracket assembly.
06/14/06
Cover, i, 6, 7
962
Updated company name, address and logo. Updated formatting.
Corrected spelling and grammar. Updated wire numbers in text,
connection charts and schematics.
02/28/08
ALL
1008
1017
Add Instructions and Schematics for DTU and ADASd Interface.
Correct typographical errors. Remove LAN Antenna References.
03/01/10
ALL
1024
Update DTU RF Cable P/N in the Engine Harness Kit. Update
Raytheon 300 WOW Connection in the Connection Chart
05/04/10
Cover, i, 3, 30
This Document is Subject to the Restrictions Contained on Cover Page
The export control classification with respect to this document is contained on the first page
DTU-G-010-1/B, Rev L, June 09, 2015
i of iv
P&W ENGINE SERVICES, INC.
Part 23 Aircraft
REV.
NO
ECO #
1228
Note:
Data Transmission Unit
DESCRIPTION
Add DTU Kit for Cessna Caravan that have ADASd installed.
Update wiring schematics. Update format of document footer
DTU-G-010-1/B
Generation III Monitors
DATE
PAGES REVISED
06/09/2015
ALL
If the DTU Installation Instructions 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.
This Document is Subject to the Restrictions Contained on Cover Page
The export control classification with respect to this document is contained on the first page
DTU-G-010-1/B, Rev L, June 09, 2015
ii of iv
P&W ENGINE SERVICES, INC.
Part 23 Aircraft
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
TABLE OF CONTENTS
P&W ENGINE SERVICES, INC. – GEN III MONITOR APPLICATION............................................................ 1
1.1
SCOPE ...................................................................................................................................................................... 1
INSTALLATION AND MAINTENANCE PROCEDURES ..................................................................................... 2
2.1
PARTS LIST .............................................................................................................................................................. 2
2.1.1 DTU by Parts Kits .............................................................................................................................................. 2
2.1.2 Components by Kit ............................................................................................................................................. 3
INSTALLATION – MECHANICAL........................................................................................................................... 8
3.1
SYSTEM PROCESSOR MOUNTING ............................................................................................................................. 8
3.2
DTU STATUS SWITCH/FAULT LAMP AND COMMUNICATIONS PORT...................................................................... 14
3.2.1 Status Switch/Fault Lamp................................................................................................................................. 14
3.2.2 Download Port ................................................................................................................................................. 15
3.3
ANTENNA MOUNTING ........................................................................................................................................... 15
3.4
HARNESS INSTALLATION ....................................................................................................................................... 16
3.4.1 J1 Harness Installation..................................................................................................................................... 17
3.4.2 GSM Antenna Cable Installation...................................................................................................................... 18
INSTALLATION - ELECTRICAL ........................................................................................................................... 19
4.1
DTU STATUS LAMP AND COMMUNICATIONS PORT WIRING.................................................................................. 19
4.1.1 DTU Status Lamp Wiring ................................................................................................................................. 19
4.1.2 Download Port Connector Wiring.................................................................................................................... 21
4.2
AIRFRAME SENSORS .............................................................................................................................................. 23
4.2.1 On Ground (Weight-on-Wheels) Signal............................................................................................................ 23
4.3
ELECTRICAL POWER .............................................................................................................................................. 24
4.3.1 Battery Power / Ground Connection ................................................................................................................ 24
4.3.2 Bus (Switched) Power Connection ................................................................................................................... 25
4.4
FINAL INSTALLATION NOTES ................................................................................................................................. 25
HARNESS CONNECTOR SIGNAL PINOUTS....................................................................................................... 27
5.1
ACS CABLE J1, 37 PIN “A” KEYED CONNECTOR .................................................................................................. 27
5.2
DTU CONNECTION CHART – POWER AND RF LOCKOUT ....................................................................................... 30
5.2.1 Cessna Caravan Model 208 Series................................................................................................................... 30
5.2.2 Raytheon Model C90 ........................................................................................................................................ 30
5.2.3 Raytheon Models 200 & 200T .......................................................................................................................... 30
5.2.4 Raytheon Models 200CT, A200, A200C, & A200CT........................................................................................ 31
5.2.5 Raytheon Models B200C, B200CT, B200, B200T ............................................................................................ 31
5.2.6 Raytheon Model 300 Series .............................................................................................................................. 31
5.2.7 Raytheon Model B300 Series............................................................................................................................ 32
5.2.8 Raytheon Model 1900 & 1900C ....................................................................................................................... 32
5.2.9 Raytheon Model 1900D.................................................................................................................................... 32
WIRING DIAGRAM .................................................................................................................................................. 33
6.1
6.2
6.3
6.4
6.5
DTU / ADAS INTERCONNECT SCHEMATIC .......................................................................................................... 33
DTU / ADAS+ INTERCONNECT SCHEMATIC (EXCEPT CESSNA CARAVAN) ........................................................... 34
DTU / ADAS+ INTERCONNECT SCHEMATIC (CESSNA CARAVAN STC INSTALLATION) ........................................ 35
DTU / ADAS+ INTERCONNECT SCHEMATIC (CESSNA CARAVAN FACTORY INSTALLATION) ................................ 36
DTU / ADAS+ UPGRADE INTERCONNECT SCHEMATIC ......................................................................................... 37
This Document is Subject to the Restrictions Contained on Cover Page
The export control classification with respect to this document is contained on the first page
DTU-G-010-1/B, Rev L, June 09, 2015
iii of iv
P&W ENGINE SERVICES, INC.
Part 23 Aircraft
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
LIST OF FIGURES
FIGURE B- 1: DTU PROCESSOR ................................................................................................................................................. 8
FIGURE B- 2: DTU/GEN III PROCESSOR TO BRACKET MOUNTING .......................................................................................... 10
FIGURE B- 3: “DOUBLE STACK” MOUNTING CONFIGURATION – HONEYCOMB/SANDWICH PANEL ......................................... 10
FIGURE B- 4: “DOUBLE STACK” MOUNTING CONFIGURATION – METAL SKIN ........................................................................ 11
FIGURE B- 5: STAND ALONE BRACKET (DPU-D-098-1) TO HONEYCOMB/SANDWICH PANEL (SIDE VIEW) ........................... 12
FIGURE B- 6: STAND ALONE BRACKET (DPU-D-098-1) TO METAL SKIN (SIDE VIEW) .......................................................... 13
FIGURE B- 7: DTU STATUS LAMP ........................................................................................................................................... 14
FIGURE B- 8: DTU STATUS LAMP MOUNTING DIMENSIONS ................................................................................................... 14
FIGURE B- 9: GSM ANTENNA ................................................................................................................................................. 15
FIGURE B- 10: GSM ANTENNA LOCATION.............................................................................................................................. 16
FIGURE B- 11: DTU STATUS LAMP CONNECTOR WIRING ....................................................................................................... 19
FIGURE B- 12: DTU STATUS LAMP CONNECTOR WIRING (WITH ADAS ) .............................................................................. 20
FIGURE B- 13: DOWNLOAD PORT CONNECTOR TO DOWNLOAD PORT – ADAS+ .................................................................... 21
FIGURE B- 14: DOWNLOAD PORT CONNECTOR TO GEN III MONITOR – ADAS+ ................................................................... 22
FIGURE B- 15: DOWNLOAD PORT CONNECTOR TO GEN III MONITOR – ADAS+ UPGRADE ................................................... 22
FIGURE B- 16: WOW DIODE ORIENTATION ............................................................................................................................ 23
FIGURE B- 17: AIRCRAFT BATTERY FINAL WIRING ................................................................................................................ 24
FIGURE B- 18: AIRCRAFT BUS FINAL WIRING......................................................................................................................... 25
FIGURE B- 19: DTU / ADAS WIRING SCHEMATIC ................................................................................................................ 33
FIGURE B- 20: DTU / ADAS+ WIRING SCHEMATIC (EXCEPT CESSNA CARAVAN) ................................................................. 34
FIGURE B- 21: DTU / ADAS+ WIRING SCHEMATIC (CESSNA CARAVAN STC INSTALLATION) .............................................. 35
FIGURE B- 22: DTU / ADAS+ WIRING SCHEMATIC (CESSNA CARAVAN FACTORY INSTALLATION) ...................................... 36
FIGURE B- 23: DTU / ADAS+ UPGRADE WIRING SCHEMATIC ............................................................................................... 37
LIST OF TABLES
TABLE B- 1: DTU CONNECTION CHART CESSNA CARAVAN MODEL 208 SERIES ................................................................... 30
TABLE B- 2: DTU CONNECTION CHART RAYTHEON MODEL C90 .......................................................................................... 30
TABLE B- 3: DTU CONNECTION CHART RAYTHEON MODEL 200 & 200T .............................................................................. 30
TABLE B- 4: DTU CONNECTION CHART RAYTHEON MODEL 200CT, A200, A200C, & A200CT........................................... 31
TABLE B- 5: DTU CONNECTION CHART RAYTHEON MODEL B200C, B200CT, B200, & B200T ........................................... 31
TABLE B- 6: DTU CONNECTION CHART RAYTHEON MODEL 300 SERIES ............................................................................... 31
TABLE B- 7: DTU CONNECTION CHART RAYTHEON MODEL B300 SERIES............................................................................. 32
TABLE B- 8: DTU CONNECTION CHART RAYTHEON MODEL 1900 & 1900C.......................................................................... 32
TABLE B- 9: DTU CONNECTION CHART RAYTHEON MODEL 1900D SERIES .......................................................................... 32
This Document is Subject to the Restrictions Contained on Cover Page
The export control classification with respect to this document is contained on the first page
DTU-G-010-1/B, Rev L, June 09, 2015
iv of iv
P&W ENGINE SERVICES, INC.
Part 23 Aircraft
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
1 P&W ENGINE SERVICES, INC. – GEN III MONITOR APPLICATION
1.1
Scope
The purpose of this document is to provide users of this product with P&W Engine Services approved
installation instructions for the Data Transmission Unit (DTU). 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.
These instructions apply to the aircraft associated with existing Pratt & Whitney Engine Services, Inc.,
Generation III monitoring systems.
This Document is Subject to the Restrictions Contained on Cover Page
The export control classification with respect to this document is contained on the first page
DTU-G-010-1/B, Rev L, June 09, 2015
1 of 37
P&W ENGINE SERVICES, INC.
Part 23 Aircraft
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
2 INSTALLATION AND MAINTENANCE PROCEDURES
2.1
Parts List
For Pratt & Whitney Engine Services, Inc. – Generation III Monitors:
The parts listed below consist of the installation kits for the DTU used on Pratt & Whitney Engine Services, Inc.
Generation III monitors. Assembly kit numbers are listed in section 2.1.1 and individual components are
detailed by kit numbers in section 2.1.2.
2.1.1 DTU by Parts Kits
For ADASd Monitors Installed on Raytheon Models: Qty
P/N DTU-K-010-22
Weight
Processor Assembly
Engine Harness Kit
Fault Lamp Assembly Kit
Antenna Kit
Additional Installation Materials Kit
DTU-K-089-2
DTU-K-090-5
DTU-K-091-2
DTU-K-092-2
DTU-K-093-20
2.00 Lbs.
2.40 Lbs.
0.50 Lbs.
0.20 Lbs
0.20 Lbs
For ADAS+ Monitors Installed on Raytheon Models: Qty
P/N DTU-K-010-6
Weight
Processor Assembly
Engine Harness Kit
Fault Lamp Assembly Kit
Antenna Kit
Additional Installation Materials Kit
DTU-K-089-2
DTU-K-090-2
DTU-K-091-2
DTU-K-092-2
DTU-K-093-5
2.00 Lbs.
2.40 Lbs.
0.50 Lbs.
0.20 Lbs
0.20 Lbs.
P/N DTU-K-010-2
Weight
DTU-K-089-2
DTU-K-090-2
DTU-K-091-2
DTU-K-092-2
DTU-K-093-2
2.00 Lbs.
2.40 Lbs.
0.50 Lbs.
0.20 Lbs
0.20 Lbs.
P/N DTU-K-010-26
Weight
DTU-K-089-15
DTU-K-090-18
DTU-K-091-2
DTU-K-092-2
DTU-K-093-21
2.00 Lbs.
2.40 Lbs.
0.50 Lbs.
0.20 Lbs
0.20 Lbs.
For ADAS+ Monitors Installed on Cessna Models:
Processor Assembly
Engine Harness Kit
Fault Lamp Assembly Kit
Antenna Kit
Additional Installation Materials Kit
For ADASd Monitors Installed on Cessna Models:
Processor Assembly
Engine Harness Kit
Fault Lamp Assembly Kit
Antenna Kit
Additional Installation Materials Kit
Qty
Qty
This Document is Subject to the Restrictions Contained on Cover Page
The export control classification with respect to this document is contained on the first page
DTU-G-010-1/B, Rev L, June 09, 2015
2 of 37
P&W ENGINE SERVICES, INC.
Part 23 Aircraft
Data Transmission Unit
For ADAS+ Upgrade Monitors Only:
Qty
Processor Assembly
Engine Harness Kit
Fault Lamp Assembly Kit
Antenna Kit
Additional Installation Materials Kit
DTU-G-010-1/B
Generation III Monitors
P/N DTU-K-010-3
Weight
DTU-K-089-2
DTU-K-090-2
DTU-K-091-2
DTU-K-092-2
DTU-K-093-3
2.00 Lbs.
2.40 Lbs.
0.50 Lbs.
0.20 Lbs
0.10 Lbs.
2.1.2 Components by Kit
For ADASd Monitors Installed on Raytheon Models:
PROCESSOR ASSEMBLY KIT
Processor, Standalone
Bracket, Mounting (Dual Assembly)
Plate Bracket Assembly
Bracket, Low Profile Mntg (Stand Alone)
Shock Mounts, Lord
Washer, Processor Mount
Nut, Locking, Processor Mount
Screw, Mount
Insert
Strap, Ground
DTU-K-089-2
DTU-A-012-1
DPU-D-080-1
DPU-A-082-1
DPU-D-098-1
990-00020
920-00006
MS21042-06
MS35207-261
NAS1836-3-09
DPU-C-050-1
FAULT LAMP ASSEMBLY
Assy., Split Lamp
Lens, Switch, Dual Lamp, DTU
Connector, 6 Pin Female
DTU-K-091-2
ADAS-A-011-1
DTU-D-082-1
400-00026
ENGINE HARNESS KIT
Cable Assembly, DTU ACS, J1
RF, DTU, Rt. Angle-Straight
Cable RF, DTU, 2X Rt. Angle
Qty 1
Qty 1
Qty 1
Qty 1
Qty 4
Qty 4
Qty 4
Qty 10
Qty 6
Qty 1
Qty 1
Qty 1
Qty 1
DTU-K-090-5
DAAS-C-040-1
DTU-C-078-1
DTU-C-084-3
ANTENNA KIT
Qty 1
Qty 1
Qty 1
DTU-K-092-2
Antenna, GSM
Conn, Dust Cap, SMA Male
DTU-D-094-1
400-00136
ADDITIONAL MATERIAL INSTALLATION KIT
Mntg Plate DTU Fault Lamp/Dnld Port
SPACER, NYLON #6
Bracket, Antenna
Plug, Finishing 9/16”
Qty 1
Qty 1
DTU-K-093-20
DTU-D-104-1
940-00015
DTU-D-106-1
990-00121
Qty 1
Qty 4
Qty 1
Qty 1
This Document is Subject to the Restrictions Contained on Cover Page
The export control classification with respect to this document is contained on the first page
DTU-G-010-1/B, Rev L, June 09, 2015
3 of 37
P&W ENGINE SERVICES, INC.
Part 23 Aircraft
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
For ADAS+ Monitors Installed on Raytheon Models:
PROCESSOR ASSEMBLY KIT
Processor, Standalone
Bracket, Mounting (Dual Assembly)
Plate Bracket Assembly
Bracket, Low Profile Mntg (Stand Alone)
Shock Mounts, Lord
Washer, Processor Mount
Nut, Locking, Processor Mount
Screw, Mount
Insert
Strap, Ground
DTU-K-089-2
DTU-A-012-1
DPU-D-080-1
DPU-A-082-1
DPU-D-098-1
990-00020
920-00006
MS21042-06
MS35207-261
NAS1836-3-09
DPU-C-050-1
FAULT LAMP ASSEMBLY
Assy., Split Lamp
Lens, Switch, Dual Lamp, DTU
Connector, 6 Pin Female
DTU-K-091-2
ADAS-A-011-1
DTU-D-082-1
400-00026
ENGINE HARNESS KIT
Cable Assembly, DTU ACS, J1
RF, DTU, Rt. Angle-Straight
Cable RF, DTU, 2X Rt. Angle
Qty 1
Qty 1
Qty 1
Qty 1
Qty 4
Qty 4
Qty 4
Qty 10
Qty 6
Qty 1
Qty 1
Qty 1
Qty 1
DTU-K-090-2
DTU-C-075-1
DTU-C-078-1
DTU-C-084-1
ANTENNA KIT
Qty 1
Qty 1
Qty 1
DTU-K-092-2
Antenna, GSM
Conn, Dust Cap, SMA Male
DTU-D-094-1
400-00136
ADDITIONAL MATERIAL INSTALLATION KIT
Fuse, 1.0 Amp
Fuse Holder
Connector, 6 Pin Male
Connector, 6 Pin Female
Velcro®
Diode
Mntg Plate DTU Fault Lamp/Dnld Port
SPACER, NYLON #6
Bracket, Antenna
Qty 1
Qty 1
DTU-K-093-5
990-00033
DPU-C-057-1
400-00027
400-00026
990-00079
300-00034
DTU-D-104-1
940-00015
DTU-D-106-1
Qty 2
Qty 2
Qty 1
Qty 1
Qty 2 Ft
Qty 2
Qty 1
Qty 4
Qty 1
This Document is Subject to the Restrictions Contained on Cover Page
The export control classification with respect to this document is contained on the first page
DTU-G-010-1/B, Rev L, June 09, 2015
4 of 37
P&W ENGINE SERVICES, INC.
Part 23 Aircraft
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
For ADAS+ Monitors Installed on Cessna Models:
PROCESSOR ASSEMBLY KIT
Processor, Standalone
Bracket, Mounting (Dual Assembly)
Plate Bracket Assembly
Bracket, Low Profile Mntg (Stand Alone)
Shock Mounts, Lord
Washer, Processor Mount
Nut, Locking, Processor Mount
Screw, Mount
Insert
Strap, Ground
DTU-K-089-2
DTU-A-012-1
DPU-D-080-1
DPU-A-082-1
DPU-D-098-1
990-00020
920-00006
MS21042-06
MS35207-261
NAS1836-3-09
DPU-C-050-1
FAULT LAMP ASSEMBLY
Assy., Split Lamp
Lens, Switch, Dual Lamp, DTU
Connector, 6 Pin Female
DTU-K-091-2
ADAS-A-011-1
DTU-D-082-1
400-00026
ENGINE HARNESS KIT
Cable Assembly, DTU ACS, J1
RF, DTU, Rt. Angle-Straight
Cable RF, DTU, 2X Rt. Angle
Qty 1
Qty 1
Qty 1
Qty 1
Qty 4
Qty 4
Qty 4
Qty 10
Qty 6
Qty 1
Qty 1
Qty 1
Qty 1
DTU-K-090-2
DTU-C-075-1
DTU-C-078-1
DTU-C-084-1
ANTENNA KIT
Qty 1
Qty 1
Qty 1
DTU-K-092-2
Antenna, GSM
Conn, Dust Cap, SMA Male
DTU-D-094-1
400-00136
ADDITIONAL MATERIAL INSTALLATION KIT
Fuse, 1.0 Amp
Fuse Holder
Connector, 6 Pin Male
Connector, 6 Pin Female
Velcro®
Diode
Mntg Plate DTU Fault Lamp/Dnld Port
Qty 1
Qty 1
DTU-K-093-2
990-00033
DPU-C-057-1
400-00027
400-00026
990-00079
300-00034
DTU-D-104-1
Qty 2
Qty 2
Qty 1
Qty 1
Qty 2 Ft
Qty 2
Qty 1
This Document is Subject to the Restrictions Contained on Cover Page
The export control classification with respect to this document is contained on the first page
DTU-G-010-1/B, Rev L, June 09, 2015
5 of 37
P&W ENGINE SERVICES, INC.
Part 23 Aircraft
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
For ADASd Monitors Installed on Cessna Models:
PROCESSOR ASSEMBLY KIT
Processor, Standalone
Bracket, Low Profile Mntg (Stand Alone)
Shock Mounts, Lord
Washer, Processor Mount
Nut, Locking, Processor Mount
Screw, Mount
Strap, Ground
DTU-K-089-15
DTU-A-012-1
DPU-D-098-1
990-00020
920-00006
MS21042-06
MS35207-261
DPU-C-050-1
FAULT LAMP ASSEMBLY
Assy., Split Lamp
Lens, Switch, Dual Lamp, DTU
Connector, 6 Pin Female
DTU-K-091-2
ADAS-A-011-1
DTU-D-082-1
400-00026
ENGINE HARNESS KIT
Cable Assembly, DTU ACS, J1
Cable RF, DTU, 2X Rt. Angle
Qty 1
Qty 1
Qty 4
Qty 4
Qty 4
Qty 10
Qty 1
Qty 1
Qty 1
Qty 1
DTU-K-090-18
DAAS-C-040-2
DTU-C-084-1
ANTENNA KIT
Qty 1
Qty 1
DTU-K-092-2
Antenna, GSM
Conn, Dust Cap, SMA Male
DTU-D-094-1
400-00136
ADDITIONAL MATERIAL INSTALLATION KIT
Connector, 6 Pin Male
Connector, 6 Pin Female
Velcro®
Mntg Plate DTU Fault Lamp/Dnld Port
Plug, Finishing 9/16”
Terminal Ring #10
Rivet Nut
Qty 1
Qty 1
DTU-K-093-21
400-00027
400-00026
990-00079
DTU-D-104-1
990-00121
MS25036-103
NAS1329A3K80
Qty 1
Qty 1
Qty 2 Ft
Qty 1
Qty 1
Qty 1
Qty 8
This Document is Subject to the Restrictions Contained on Cover Page
The export control classification with respect to this document is contained on the first page
DTU-G-010-1/B, Rev L, June 09, 2015
6 of 37
P&W ENGINE SERVICES, INC.
Part 23 Aircraft
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
For ADAS+ Upgrade Monitors Only:
PROCESSOR ASSEMBLY KIT
Processor, Standalone
Bracket, Mounting (Dual Assembly)
Plate Bracket Assembly
Bracket, Low Profile Mntg (Stand Alone)
Shock Mounts, Lord
Washer, Processor Mount
Nut, Locking, Processor Mount
Screw, Mount
Insert
Strap, Ground
DTU-K-089-2
DTU-A-012-1
DPU-D-080-1
DPU-A-082-1
DPU-D-098-1
990-00020
920-00006
MS21042-06
MS35207-261
NAS1836-3-09
DPU-C-050-1
FAULT LAMP ASSEMBLY
Assy., Split Lamp
Lens, Switch, Dual Lamp, DTU
Connector, 6 Pin Female
DTU-K-091-2
ADAS-A-011-1
DTU-D-082-1
400-00026
ENGINE HARNESS KIT
Cable Assembly, DTU ACS, J1
RF, DTU, Rt. Angle-Straight
Cable RF, DTU, 2X Rt. Angle
Qty 1
Qty 1
Qty 1
Qty 1
Qty 4
Qty 4
Qty 4
Qty 10
Qty 6
Qty 1
Qty 1
Qty 1
Qty 1
DTU-K-090-2
DTU-C-075-1
DTU-C-078-1
DTU-C-084-1
ANTENNA KIT
Qty 1
Qty 1
Qty 1
DTU-K-092-1
Antenna, GSM
Antenna, RF
Conn, Adapter Jack to Jack
DTU-D-094-1
DTU-D-095-1
960-00048
ADDITIONAL MATERIAL INSTALLATION KIT
Fuse, 1.0 Amp
Fuse Holder
Connector, 6 Pin Male
Velcro®
Diode
Harness
Bracket, Antenna
Mntg Plate DTU Fault Lamp/Dnld Port
Spacer
Qty 1
Qty 1
Qty 1
DTU-K-093-3
990-00033
DPU-C-057-1
400-00027
990-00079
300-00034
TWIN-C-080-1
DTU-D-106-1
DTU-D-104-1
940-00015
Qty 2
Qty 2
Qty 1
Qty 2 Ft
Qty 2
Qty 1
Qty 1
Qty 1
Qty 4
This Document is Subject to the Restrictions Contained on Cover Page
The export control classification with respect to this document is contained on the first page
DTU-G-010-1/B, Rev L, June 09, 2015
7 of 37
P&W ENGINE SERVICES, INC.
Part 23 Aircraft
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
3 INSTALLATION – MECHANICAL
3.1
System Processor Mounting
The system processor (Figure B- 1) may be remotely mounted. The processor will not require access during
normal operation. P&W Engine Services offers three mounting bracket options. For aircraft with ample space
in the location of the previously installed Generation III processor (IntelliStart+, SmartCycle+, ADAS d,
ADAS+, and TrendCheck+), the utilization of the double stack bracket (DPU-D-080-1 and DPU-A-082-1) is
recommended. For aircraft with limited clearance, the low profile bracket (DPU-D-098-1) is recommended.
DPU-D-030-1 is the bracket utilized in ADAS+, SmartCycle+, and IntelliStart+ installations. DPU-D-082-1 is
the bracket utilized in the ADASd installation.
Figure B- 1: DTU Processor
Note: The aircraft and available space will determine how the DTU will be installed. With the supplied
mounting brackets the DTU can be mounted in two different configurations.
1. If the current location of the Gen III processor has sufficient space the DTU can me mounted
in the “Double stack” configuration. Refer to Figure B- 3 or Figure B- 4.
2. If the current location of the Gen III processor does not have sufficient space, the DTU can
me mounted in another location using the Low Profile Bracket (DPU-D-098-1). See Figure B5 or Figure B- 6. Refer to the applicable aircraft maintenance manual for specific
instructions regarding standard practices for structural mounting.
3. The location of the processor must be recorded in the Installation Summary Table provide in
Instructions for Continued Airworthiness, DTU-G-260-1/B, Section 7.1
INSTALLATION CAUTION:





If another area is used to mount the DTU, the area must have sufficient structural integrity to
support the unit. Sheet metal panels should be .025” thick, with material comparable or
stronger than 2024-T3 aluminum.
When installing in a sandwich panel, an undercut shall be made around the periphery of the
insert hole to spoil the core in the area immediately around the insert hole. The panel shall
be a minimum of .50” thick.
The area chosen must be inspected for any evidence of dents, contraction, cracking, and
deterioration of metal. Reference AC 43.13-2A, Chapters 1 & 2 for specific guidelines in
determining a mounting location.
The area chosen must allow full and free movement of any control system cables or tubes.
The control mechanisms must be able to operate over their complete range of movement.
The DTU processor is not certified to be mounted in the engine compartment.
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DTU-G-010-1/B, Rev L, June 09, 2015
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P&W ENGINE SERVICES, INC.
Part 23 Aircraft
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
For Bracket Mounting Option 1 – Double Stack (except for ADASd)
The system processors shall be mounted in accordance with the following procedure:

010 Remove the Gen III processor and its mounting bracket from the aircraft. Discard the original
mounting bracket.

020 Ensure that the original inserts securing the bracket to the honeycomb panel are NAS1836-3 or
equivalent.

030 For installations in a honeycomb/sandwich panel, using the supplied mounting bracket (DPU-A082-1) as a template, mark the location of the 2 additional mounting holes and drill to accommodate a
NAS1836-3 potted insert.



040 Install six (6) NAS1836-3 potted inserts in accordance with manufacturer’s instructions
050 For installations in a metal skin, using the supplied mounting bracket (DPU-A-082-1) as a template,
mark the location of the two (2) additional mounting holes and drill to accommodate a #10 screw.
060 Assemble the DTU and Gen III processors to the mounting bracket as shown in Figure B- 2
INSTALLATION CAUTION:

Excessive torque on the processor-mounting studs can deform shock mounts. The locking
nut should be tightened to the point of contact with the shock mount.

070 Assemble the “Double Stack” mounting bracket and install the Gen III processor and the DTU
processor. Refer to applicable Figure B- 3 or Figure B- 4

080 Install ground strap DPU-C-050-2 between one of the processor-mounting studs and the aircraft
chassis for both the Gen III and DTU processors

090 Mount the “Double Stack” bracket containing the Gen III processor and the DTU to the aircraft using
the required hardware.
For Bracket Mounting Option 1 – Double Stack (ADASd Only)
The system processors shall be mounted in accordance with the following procedure:

010 Assemble the DTU to the “Double Stack” mounting bracket P/N DPU-D-080-1, as shown in Figure B2.
INSTALLATION CAUTION:

Excessive torque on the processor-mounting studs can deform shock mounts. The locking
nut should be tightened to the point of contact with the shock mount.

020 Attach the DTU and the “Double Stack” mounting bracket to the Gen III processor bracket using the
required hardware. Refer to applicable Figure B- 3 or Figure B- 4

030 Install ground strap DPU-C-050-2 between one of the processor-mounting studs and the aircraft
chassis for both the Gen III and DTU processors
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The export control classification with respect to this document is contained on the first page
DTU-G-010-1/B, Rev L, June 09, 2015
9 of 37
P&W ENGINE SERVICES, INC.
Part 23 Aircraft
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
Figure B- 2: DTU/Gen III Processor to Bracket Mounting
Figure B- 3: “Double Stack” Mounting Configuration – Honeycomb/Sandwich Panel
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DTU-G-010-1/B, Rev L, June 09, 2015
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P&W ENGINE SERVICES, INC.
Part 23 Aircraft
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
Figure B- 4: “Double Stack” Mounting Configuration – Metal Skin
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DTU-G-010-1/B, Rev L, June 09, 2015
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P&W ENGINE SERVICES, INC.
Part 23 Aircraft
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
For Bracket Mounting Option 2 – Stand Alone
The system processor shall be mounted in accordance with the following procedure:






010 For installations in a honeycomb/sandwich panel, when a location has been determined for the
DTU processor, using the supplied mounting bracket (DPU-D-098-1) as a template, mark the
location of the four (4) holes and drill to accommodate a NAS1836-3 potted insert.
020 Install four (4) NAS1836-3 potted inserts in accordance with manufacturer’s instructions
030 For installations in a metal skin, when a location has been determined for the DTU processor,
using the supplied mounting bracket (DPU-D-098-1) as a template, mark the location of the four (4)
mounting holes and drill to accommodate a #10 screw.
040 Assemble the DTU processor to the mounting bracket as shown in Figure B- 2
050 Install ground strap DPU-C-050-1 between one of the processor mounting studs and the aircraft
chassis.
060 Mount the DTU processor and bracket using the required hardware. Refer to applicable Figure B- 5
or Figure B- 6.
Figure B- 5: Stand Alone Bracket (DPU-D-098-1) to Honeycomb/Sandwich Panel (Side View)
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DTU-G-010-1/B, Rev L, June 09, 2015
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P&W ENGINE SERVICES, INC.
Part 23 Aircraft
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
Figure B- 6: Stand Alone Bracket (DPU-D-098-1) to Metal Skin (Side View)
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DTU-G-010-1/B, Rev L, June 09, 2015
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P&W ENGINE SERVICES, INC.
Part 23 Aircraft
3.2
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
DTU Status Switch/Fault Lamp and Communications Port
3.2.1 Status Switch/Fault Lamp
Assembly Notes
The DTU has a status switch / fault lamp, which consists of a rectangular push-to-test combination lamp
(Figure B- 7). The location of the DTU Status/Fault Lamp must be recorded in the Installation Summary Table
provide in Instructions for Continued Airworthiness, DTU-G-260-1/B, Section 7.1
Figure B- 7: DTU Status Lamp
INSTALLATION CAUTION:


The DTU Status lamp should be mounted in a location accessible to maintenance personnel.

The DTU Status lamp is not certified to be mounted in the cockpit.
If a suitable location is available, the supplied lamp mounting bracket (DTU-D-104-1) can be
used to remotely mount the DTU Status Lamp.

010 If the double stack configuration is used, the lamp can me mounted on the DTU processor mounting
bracket (DPU-D-080-1) using the supplied lamp mounting bracket (DTU-D-104-1).

020 Using the lamp mounting bracket as a template, mark and drill the three (3) #10 mounting holes on
the processor mounting bracket.

030 Secure the lamp mounting bracket to the processor mounting bracket.

040 Install the DTU Status Lamp into the bracket.

050 If the lamp cannot be mounted on the DTU processor mounting bracket, find a suitable location and
following Figure B- 8, mark and punch a 1.14 x 0.75 inch rectangular hole for mounting of the Status
Lamp.

060 Install the DTU Status Lamp into the panel.
Figure B- 8: DTU Status Lamp Mounting Dimensions
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DTU-G-010-1/B, Rev L, June 09, 2015
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P&W ENGINE SERVICES, INC.
Part 23 Aircraft
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
3.2.2 Download Port
The DTU will wire into the existing download port installed in the aircraft from the previously installed
Generation III system.
3.3
Antenna Mounting
For ADAS+ Monitors Only (Except Raytheon Models):
The DTU incorporates a GSM antenna that will be mounted internal to the airframe. Velcro® is used to attach
the GSM antenna to the mounting surface. The location of the GSM antenna must be recorded in the
Installation Summary Table provide in Instructions for Continued Airworthiness, DTU-G-260-1/B, Section 7.1
INSTALLATION CAUTION:





The specific mounting location is important due to curvatures and uneven surfaces that can
be found on various aircraft. A flat surface is the desired GSM antenna mounting location.
The installer must ensure that the antenna is not mounted in a location totally encompassed
by metal
If the antenna is mounted in the cabin of the aircraft it must be securely fastened to the
aircraft to prevent their movement during a hard landing. The preferred method is to mount
the antenna in a secondary containment area.
010 The surface that will come in contact with the Velcro® tape must be free of paint, dust, oil, grease,
and other contamination prior to antenna installation. Clean the aircraft surface thoroughly.
020 Cut the supplied Velcro® tape to the length of the GSM antenna (Figure B- 9) and remove the
release film.

030 Firmly press the tape to the aircraft panel.

040 Cut the supplied Velcro® tape to the length of the GSM antenna and remove the release film.


050 Firmly press the tape to the back of the GSM antenna. The front of the GSM antenna is identified by
the coaxial connector mounting and the identification label. Figure B- 9 shows the front of the GSM
antenna.
060 Mount GSM antenna to the Velcro® tape installed on the aircraft panel by firmly pressing the
antenna to the tape.
Figure B- 9: GSM Antenna
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DTU-G-010-1/B, Rev L, June 09, 2015
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P&W ENGINE SERVICES, INC.
Part 23 Aircraft
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
For All Gen III Monitors (Raytheon Models Only):
The DTU incorporates a GSM antenna that will be mounted internal to the airframe. A supplied mounting
bracket is used to attach the GSM antenna to the mounting surface.
INSTALLATION CAUTION:


The specific mounting location is important due to curvatures and uneven surfaces that can
be found on various aircraft.
The installer must ensure that the antenna are not mounted in a location totally
encompassed by metal

010 Remove the fiberglass nose cover from the nose of the aircraft

020 Locate the GSM antenna mounting bracket (DTU-D-106-1) as shown in Figure B- 10. Using the
bracket as a template mark and drill two mounting holes to accommodate a #10 screw.

030 Secure the GSM antenna to the mounting bracket using the supplied hardware and spacers.

040 Secure the mounting bracket assembly to the aircraft.
GSM Antenna
Figure B- 10: GSM Antenna Location
3.4
Harness Installation
INSTALLATION CAUTION:


Route all cables to follow existing wiring harnesses. Ensure that all cables and individual wires do not
interfere with any control cables. Secure all cables and wires with cable ties and where necessary, use
spiral tubing to protect wires from chaffing and abrasion. Do not secure cables to any existing power
cable.
Avoid sharp bends and routing RF cable near high energy sources
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DTU-G-010-1/B, Rev L, June 09, 2015
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P&W ENGINE SERVICES, INC.
Part 23 Aircraft
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
3.4.1 J1 Harness Installation
For ADASd Monitors Only:

010 Connect the J1 harness to the J1 connector on the DTU processor.

020 Disconnect the existing 10 Pin Lemo connector (J2) from the ADAS . Route the DAAS-C-040
(10 pin Lemo connector “male”) cable from the DTU and connect to the ADAS (J2).

030 Route the AAB49B24 cable (10 pin Lemo connector “female”) to the ADAS and connect it to the
AAB40D24 cable (10 pin Lemo connector “male”) that was previously removed from the ADAS .

040 Route the AAV39E24 cable to the DTU Status Lamp.

050 Route the AAD09A24 cable to airframe ground.
For ADAS+ Monitors Only:

010 Connect the J1 harness to the J1 connector on the DTU processor.

020 Route the AAV09B24 cable and connect the “WHT” wire to a source that has “Hot” battery power all
the time. The “WHT/BLU” wire is connected to aircraft ground. Refer to Section 5.2 for your specific
aircraft model wiring.

030 Route the AAV19A24 cable and connect the “WHT” wire to a source that has “Switched on” battery
power. Refer to Section 5.2 for your specific aircraft model wiring.

040 Route the AAD09A24 cable to a weight on wheels switch (WOW). Refer to Section 5.2 for your
specific aircraft model wiring.
NOTE: Cessna Caravan installations will connect this wire to aircraft ground per section 5.2.


050 Route the AAB49B24 cable coming from the DTU to the existing Download Port.

070 Route the AAB48C24 cable to the GEN III cable previously connected to the Download Port and
assemble the ConXall™ of the AAB48C24 cable to the existing Gen III processor cable.

080 Route the AAV39D24 & AAV38A24 cables to the installed DTU Status Lamp.
060 Disconnect the ConXall™ connector from the existing Download Port to the Gen III processor and
connect the Download Port to the ConXall™ connector on the AAB49B24 cable.
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DTU-G-010-1/B, Rev L, June 09, 2015
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P&W ENGINE SERVICES, INC.
Part 23 Aircraft
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
For ADAS+ Upgrade Monitors Only:

010 Connect the J1 harness to the J1 connector on the DTU processor.

020 Split the harness and route the AAV09B24 cable and connect the “WHT” wire to a source that has
“Hot” battery power all the time. The “WHT/BLU” wire is connected to aircraft ground.

030 Route the AAV19A24 cable and connect the “WHT” wire to a source that has “Switched on” battery
power.

040 Route the AAD09A24 cable to a weight on wheels switch (WOW).

050 Route the AAB49B24 and the AAB48C24 connector cables coming from the DTU processor to the
ADAS+ Upgrade processor.

060 Route the AAV39D24 cable to the installed DTU Status Lamp.
3.4.2 GSM Antenna Cable Installation

010 Connect the GSM antenna cable to the DTU processor GSM connection. Torque SMA Connector to
5 inch pounds or 56 N-cm. The GSM antenna cable is the one with a 90° connection on both ends.

020 Route the GSM cable (90° connector) to the GSM antenna. Torque SMA Connector to 5 inch
pounds or 56 N-cm.
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DTU-G-010-1/B, Rev L, June 09, 2015
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P&W ENGINE SERVICES, INC.
Part 23 Aircraft
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
4 INSTALLATION - ELECTRICAL
4.1
DTU Status Lamp and Communications Port Wiring
4.1.1 DTU Status Lamp Wiring
Wiring Notes:
ConXall™ connectors are installed in this and the next section. 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.
For All Gen III Monitors (except ADASd):
INSTALLATION CAUTION:

The DTU Status Lamp and the Download Port cables both use 6 pin connectors. The DTU
Status Lamp cable uses a socket connector (6SG type) and the Download Port cable uses a
pin connector (6PG type). Be sure to use the correct connector with the appropriate cable.
Figure B- 11: DTU Status Lamp Connector Wiring
Wiring Instructions

010 Trim the Ind Sw “AAV39D24” cable to length, and slide the correct ConXall™ connector backshell
parts onto the cable.

020 Refer to the illustration Figure B- 11and connect the cable to the included ConXall™ connector
using the socket configuration shown. Splice a short wire lead to the cable shield with a shrink-on
solder sleeve to make the Pin 6 shield connection.

030 Assemble the backshell to the connector, connect it to the lamp, and secure all wiring.
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DTU-G-010-1/B, Rev L, June 09, 2015
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P&W ENGINE SERVICES, INC.
Part 23 Aircraft
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
For ADASd Monitors:
Figure B- 12: DTU Status Lamp Connector Wiring (with ADAS )
Wiring Instructions

010 Trim the Ind Sw “AAV39E24” cable to length, and slide the correct ConXall™ connector backshell
parts onto the cable.

020 Refer to the illustration Figure B- 12 and connect the cable to the included ConXall™ connector
using the socket configuration shown. Splice a short wire lead to the cable shield with a shrink-on
solder sleeve to make the Pin 6 shield connection.

030 Assemble the backshell to the connector, connect it to the lamp, and secure all wiring.
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DTU-G-010-1/B, Rev L, June 09, 2015
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P&W ENGINE SERVICES, INC.
Part 23 Aircraft
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
4.1.2 Download Port Connector Wiring
For ADAS+ Monitors Only:
INSTALLATION CAUTION:

The connections to the Download Port cables (DL PORT and G3 MONITOR) use a pin connector
(6PG type) and a socket connector (6SG type). Be sure to use the correct connector with the
appropriate cable.
Wiring Instructions

010 Trim the DL PORT “AAB49B24” connector cable to length, and slide the 6PG type ConXall™
connector backshell parts onto the cable. This connector will connect to the existing Download Port
connector mounted in the aircraft.

020 Refer to the illustration in Figure B- 13, and connect the cable to the included ConXall™ plug
connector using the illustrated pin configuration. Pin 1 is identified by a dimple. Pins 3, 4, and 5
have no connection. Splice a short wire lead to the cable shield with a shrink-on solder sleeve to
make the Pin 6 shield connection

030 Assemble the backshell to the connector, connect it to the port, and secure all wiring.
Figure B- 13: Download Port Connector to Download Port – ADAS+

040 Trim the G3 MONITOR “AAB48C24” connector cable to length, and slide the 6SG type ConXall™
connector backshell parts onto the cable. This connector will connect to the existing ConXall™
connector coming from the GEN III processor

050 Refer to the illustration in Figure B- 14, and connect the cable to the included ConXall™ plug
connector using the illustrated pin configuration. Pin 1 is identified by a dimple. Pins 3 and 5 have
no connection. Splice a short wire lead to the cable shield with a shrink-on solder sleeve to make
the Pin 6 shield connection

060 Assemble the backshell to the connector, connect it to the port, and secure all wiring.
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DTU-G-010-1/B, Rev L, June 09, 2015
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P&W ENGINE SERVICES, INC.
Part 23 Aircraft
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
Figure B- 14: Download Port Connector to GEN III Monitor – ADAS+
For ADAS+ Upgrade Monitors Only:
INSTALLATION CAUTION:

The connections to the Download Port cables (DL PORT and G3 MONITOR) for the ADAS+
Upgrade use a single pin connector (6PG type).

010 Trim the DL PORT “AAB49B24” and the G3 MONITOR “AAB48C24” connector cable connector
cable to length, and slide the 6PG type ConXall™ connector backshell parts onto the cable. This
connector will connect to the supplied harness ConXall™ connector.

020 Refer to the illustration Figure B- 15 and connect the cable to the included ConXall™ connector
using the socket configuration shown. Splice a short wire lead to the cable shields on both the DL
PORT “AAB49B24” and G3 MONITOR “AAB28C24” cables with a shrink-on solder sleeve to make
the Pin 6 shield connection.

030 Assemble the backshell to the connector, connect it to the lamp, and secure all wiring.
Figure B- 15: Download Port Connector to GEN III Monitor – ADAS+ Upgrade
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DTU-G-010-1/B, Rev L, June 09, 2015
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P&W ENGINE SERVICES, INC.
Part 23 Aircraft
4.2
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
Airframe Sensors
4.2.1 On Ground (Weight-on-Wheels) Signal
For All Gen III Monitors (except ADASd and Cessna Models):
INSTALLATION CAUTION:



The “ON GROUND SW” cable is a single conductor shielded wire. Care must be taken to
strip back and secure shield to prevent possible shorting to the signal wire. Use plastic
spiral wrap where necessary to prevent chaffing and abrasion.
Weight on Wheels (WOW) is a secondary hardware lockout preventing the DTU from
transmitting in flight. The sensor requires an electrical ground, signaling that the aircraft is
not in flight.
The “ON GROUND SW” cable uses a diode to protect the WOW circuit if the cable is shorted
to ground. This diode must be installed per the installation instructions and wiring diagram.

010 Trim the ON GROUND SW “AAD09A24” cable to length.

020 Splice the 1N4001 (300-00034) diode to the ON GROUND SW “AAD09A24” cable. Refer to Figure
B- 16 for the correct orientation of the diode. The diode must be located as close as possible to the
WOW connection point.

030 Splice to the Weight-on-Wheels connection. Refer to Section 5.2 for the applicable WOW
connection
Color
WHT

Aircraft On Ground Signal
“WOW” Switch
040 Secure all wiring.
Figure B- 16: WOW Diode Orientation
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DTU-G-010-1/B, Rev L, June 09, 2015
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P&W ENGINE SERVICES, INC.
Part 23 Aircraft
4.3
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
Electrical Power
4.3.1 Battery Power / Ground Connection
For All Gen III Monitors (except ADASd):
INSTALLATION CAUTION:

Power to the DTU must be available any time DC power is applied to the aircraft.

010 Following the illustration (Figure B- 17) connect the AC BATTERY “AAV09B24” white (positive)
wire to supplied fuse holder. Connect to the aircraft battery so that DC power is available at all
times to the processor. Refer to Section 5.2 for the applicable power connection.

020 Following the illustration (Figure B- 17) connect the AC BATTERY “AAV09B24” white/blue
(negative) wire to aircraft ground.
INSTALLATION CAUTION:


Ensure that any connection to aircraft power incorporates a minimal wire length from the
power source to the protection device, fuse or breaker. Recommended length is six (6)
inches or less.
Ensure that the wire is protected from shorting out against the airframe or any other sharp
objects.
Color
WHT
WHT/BLU

Aircraft Power Source
Aircraft Battery +
Aircraft Ground –
030 Secure all wiring.
Figure B- 17: Aircraft Battery Final Wiring
This Document is Subject to the Restrictions Contained on Cover Page
The export control classification with respect to this document is contained on the first page
DTU-G-010-1/B, Rev L, June 09, 2015
24 of 37
P&W ENGINE SERVICES, INC.
Part 23 Aircraft
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
4.3.2 Bus (Switched) Power Connection
For All Gen III Monitors (except ADASd):
INSTALLATION CAUTION:


Ensure that any connection to aircraft power incorporates a minimal wire length from the
power source to the protection device, fuse or breaker. Recommended length is six (6)
inches or less.
Ensure that the wire is protected from shorting out against the airframe or any other sharp
objects.

010 Following the illustrations (Figure B- 18) connect the AC BUS “AAV19A24” wire to supplied fuse
holder. Connect to aircraft bus (switched) power. Refer to Section 5.2 for the applicable power
connection

020 Secure all wiring.
Figure B- 18: Aircraft Bus Final Wiring
4.4
Final Installation Notes
For ADAS+ Monitors Only:


010 Connect the cable from the DTU marked DL PORT “AAB49B24” to the existing Download Port
ConXall™ connector that is mounted in the aircraft.
020 Connect the G3 MONITOR “AAB48C24” cable to the existing Download Port cable (from the GEN III
processor) at the ConXall™ connector.

030 Connect the DTU STATUS LAMP “AAV39D24” connector to the DTU status lamp.

040 Route and secure all wires making sure engine / aircraft control movements will not be affected by
the DTU wiring. Properly dress any splices and shield terminations. Make sure wire harnesses will
not come in contact with sharp sections of the aircraft.

050 Install all aircraft panels.

060 Record the location of the processor, GSM antenna, and the DTU Status Lamp in the Installation
Summary Table provide in Instructions for Continued Airworthiness, DTU-G-260-1/B, Section 7.1
This Document is Subject to the Restrictions Contained on Cover Page
The export control classification with respect to this document is contained on the first page
DTU-G-010-1/B, Rev L, June 09, 2015
25 of 37
P&W ENGINE SERVICES, INC.
Part 23 Aircraft
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
For ADAS+ Upgrade Monitors Only:



010 Disconnect the cable to the COMM port on the ADAS+ Upgrade processor.
020 Connect P1 of the supplied harness (TWIN-C080-1) to the COMM port on the ADAS+ Upgrade
processor
030 Connect J1 of the supplied harness (TWIN-C-080-1) to the COMM cable that was removed in Step
020.

040 Connect the ConXall™ connector on the supplied harness (TWIN-C-080-1) to the ConXall™
connector from the DTU processor.

050 Connect the DTU “STATUS LAMP” connector to the DTU status lamp.

060 Route and secure all wires making sure engine / aircraft control movements will not be affected by
the DTU wiring. Properly dress any splices and shield terminations. Make sure wire harnesses will
not come in contact with sharp sections of the aircraft.

070 Install all aircraft panels.

080 Record the location of the processor, GSM antenna, and the DTU Status Lamp in the Installation
Summary Table provide in Instructions for Continued Airworthiness, DTU-G-260-1/B, Section 7.1
This Document is Subject to the Restrictions Contained on Cover Page
The export control classification with respect to this document is contained on the first page
DTU-G-010-1/B, Rev L, June 09, 2015
26 of 37
P&W ENGINE SERVICES, INC.
Part 23 Aircraft
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
5 HARNESS CONNECTOR SIGNAL PINOUTS
5.1
ACS Cable J1, 37 Pin “A” 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.
For ADASd Monitors Only:
Connector
Harness
Pin
Wire Color
Signal Name
Wired To
28V BUS
28V AUX
28V BAT
RUN/CONF
28V RTN
10 Pin Male Connector (Pin 9)
10 Pin Male Connector (Pin 6)
10 Pin Male Connector (Pin 5)
10 Pin Male Connector (Pin 4)
10 Pin Male Connector (Pin 3)
RS485A (–)
RS485B (+)
10 Pin Male Connector (Pin 2)
10 Pin Male Connector (Pin 1)
Shield
RS485A (–)
RS485B (+)
10 Pin Female Connector (Pin 5)
10 Pin Female Connector (Pin 2)
10 Pin Female Connector (Pin 1)
Shield
LAMP 2
SWITCH
LAMP 1
GROUND
LAMP PWR
6 Pin Female Connector (Pin 6)
6 Pin Female Connector (Pin 5)
6 Pin Female Connector (Pin 4)
6 Pin Female Connector (Pin 3)
6 Pin Female Connector (Pin 2)
6 Pin Female Connector (Pin 1)
On-Ground Sw
Aircraft Ground
5 COND CABLE
J1-1
J1-36
J1-4
J1-32
J1-2
WHT
WHT/ORG
WHT/GRN
WHT/RED
WHT/BLU
2 COND CABLE
J1-6, 8
J1-5, 7
WHT/BLU
WHT
2 COND CABLE
Shield
J1-16, 19
J1-18, 17
Shield
WHT/BLU
WHT
5 COND CABLE
Shield
J1-34
J1-34
J1-37
J1-2
J1-1
Shield
WHT/ORG
WHT/RED
WHT/GRN
WHT/BLU
WHT
1 COND CABLE
J1-15
WHT
Note: All shields are terminated to the backshell.
This Document is Subject to the Restrictions Contained on Cover Page
The export control classification with respect to this document is contained on the first page
DTU-G-010-1/B, Rev L, June 09, 2015
27 of 37
P&W ENGINE SERVICES, INC.
Part 23 Aircraft
For ADAS+ Monitors Only:
Connector
Harness
Pin
Wire Color
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
Signal Name
Wired To
ACS1– RS485B (+)
ACS1– RS485A (–)
RUN/CONF
Download Port Pin–1
Download Port Pin–2
Download Port Pin–4
DIAG SWITCH
INDIC SW LAMP 2
INDIC SW LAMP 1
GROUND
Status Lamp Pin–4
Status Lamp Pin–5
Status Lamp Pin–3
Status Lamp Pin–2
LAMP POWER
Status Lamp Pin–1
RS485A (–)
RS485B (+)
Conn Download Port Pin–2
Conn Download Port Pin–1
Aircraft Battery Power +
Aircraft Ground –
A/C Battery Positive
A/C Battery Ground
Aircraft Bus Power +
A/C Switched Power
3 COND CABLE
J1-5, 7
J1-6, 8
J1-32
WHT/ORG
WHT
WHT/BLU
4 COND CABLE
J1-23
J1-34
J1-37
J1-2
WHT/GRN
WHT
WHT/ORG
WHT/BLU
1 COND CABLE
J1-1
WHT
2 COND CABLE
J1-19, 16
J1-18, 17
WHT
WHT/BLU
2 COND CABLE
J1-4
J1-3
WHT
WHT/BLU
1 COND CABLE
J1-1
WHT
1 COND CABLE (Except Cessna Caravan)
J1-15
WHT
On-Ground Sw
Aircraft Weight-on-Wheels
1 COND CABLE (Cessna Caravan Only)
J1-15
WHT
On-Ground Sw
Aircraft Ground
Note: All shields are terminated to the backshell.
This Document is Subject to the Restrictions Contained on Cover Page
The export control classification with respect to this document is contained on the first page
DTU-G-010-1/B, Rev L, June 09, 2015
28 of 37
P&W ENGINE SERVICES, INC.
Part 23 Aircraft
Data Transmission Unit
For ADAS+ Upgrade Monitors Only:
Connector
Harness
Pin
Wire Color
Signal Name
DTU-G-010-1/B
Generation III Monitors
Wired To
3 COND CABLE
J1-5, 7
J1-6, 8
J1-32
WHT/ORG
WHT
WHT/BLU
ACS1-RS485B (+)
ACS1-RS485A (–)
RUN/CONF
Download Port Pin–1
Download Port Pin–2
Download Port Pin–3
DIAG SWITCH
INDIC SW LAMP 2
INDIC SW LAMP 1
GROUND
Status Lamp Pin–4
Status Lamp Pin–5
Status Lamp Pin–3
Status Lamp Pin–2
LAMP POWER
Status Lamp Pin–1
RS485A (–)
RS485B (+)
Download Port Pin–4
Download Port Pin–5
Aircraft Battery Power +
Aircraft Ground –
A/C Battery Positive
A/C Battery Ground
Aircraft Bus Power +
A/C Switched Power
Aircraft Weight-On-Wheels
Aircraft Weight-on-Wheels
4 COND CABLE
J1-23
J1-34
J1-37
J1-2
WHT/GRN
WHT
WHT/ORG
WHT/BLU
1 COND CABLE
J1-1
WHT
2 COND CABLE
J1-19, 16
J1-18, 17
WHT
WHT/BLU
2 COND CABLE
J1-4
J1-3
WHT
WHT/BLU
1 COND CABLE
J1-1
WHT
1 COND CABLE
J1-15
WHT
Note: All shields are terminated to the backshell.
This Document is Subject to the Restrictions Contained on Cover Page
The export control classification with respect to this document is contained on the first page
DTU-G-010-1/B, Rev L, June 09, 2015
29 of 37
P&W ENGINE SERVICES, INC.
Part 23 Aircraft
5.2
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
DTU Connection Chart – Power and RF Lockout
For All Gen III Monitors (except ADASd):
5.2.1 Cessna Caravan Model 208 Series
Sensor
A/C Bus
Wire Number
AAV19A24
A/C Battery
AAV09B24
Aircraft
Ground
AAD09A24
Connection Chart
Aircraft Component
Relay K 3
A1
Relay K 3
A2
Ground
Aircraft Ground
Aircraft Ground
DTU Connector
J1
Pin 1 WHT
J1
Pin 4 WHT
Pin 3 WHT/BLU
J1
Pin 15 WHT
Table B- 1: DTU Connection Chart Cessna Caravan Model 208 Series
5.2.2 Raytheon Model C90
Sensor
A/C Bus
Wire Number
AAV19A24
A/C Battery
AAV09B24
WOW
AAD09A24
Connection Chart
Aircraft Component
Main Bus
Supplied Circuit Breaker
Battery
A228 Box Assy. – Bat Bus
Aircraft Ground
WOW Cockpit Control
J125 – Pin 2
DTU Connector
J1
Pin 1 WHT
J1
Pin 4 WHT
Pin 3 WHT/BLU
J1
Pin 15 WHT
Table B- 2: DTU Connection Chart Raytheon Model C90
5.2.3 Raytheon Models 200 & 200T
Sensor
A/C Bus
Wire Number
AAV19A24
A/C Battery
AAV09B24
WOW
AAD09A24
Connection Chart
Aircraft Component
Main Bus
Supplied Circuit Breaker
Battery
W103 Bus Bar Panel Assy.
Aircraft Ground
WOW Cockpit Control
A100 – Pin 1
DTU Connector
J1
Pin 1 WHT
J1
Pin 4 WHT
Pin 3 WHT/BLU
J1
Pin 15 WHT
Table B- 3: DTU Connection Chart Raytheon Model 200 & 200T
This Document is Subject to the Restrictions Contained on Cover Page
The export control classification with respect to this document is contained on the first page
DTU-G-010-1/B, Rev L, June 09, 2015
30 of 37
P&W ENGINE SERVICES, INC.
Part 23 Aircraft
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
5.2.4 Raytheon Models 200CT, A200, A200C, & A200CT
Sensor
A/C Bus
Wire Number
AAV19A24
A/C Battery
AAV09B24
WOW
AAD09A24
Connection Chart
Aircraft Component
Main Bus
Supplied Circuit Breaker
Battery
W103 A228 Panel Assy. Battery Bus Power
Aircraft Ground
WOW Cockpit Control
A100 – Pin 1
DTU Connector
J1
Pin 1 WHT
J1
Pin 4 WHT
Pin 3 WHT/BLU
J1
Pin 15 WHT
Table B- 4: DTU Connection Chart Raytheon Model 200CT, A200, A200C, & A200CT
5.2.5 Raytheon Models B200C, B200CT, B200, B200T
Sensor
A/C Bus
Wire Number
AAV19A24
A/C Battery
AAV09B24
WOW
AAD09A24
Connection Chart
Aircraft Component
Main Bus
Supplied Circuit Breaker
Battery
W103 A228 Panel Assy.Battery Bus Power
Aircraft Ground
WOW Cockpit Control
A100 – Pin 1
DTU Connector
J1
Pin 1 WHT
J1
Pin 4 WHT
Pin 3 WHT/BLU
J1
Pin 15 WHT
Table B- 5: DTU Connection Chart Raytheon Model B200C, B200CT, B200, & B200T
5.2.6 Raytheon Model 300 Series
Sensor
A/C Bus
Wire Number
AAV19A24
A/C Battery
AAV09B24
WOW
AAD09A24
Connection Chart
Aircraft Component
Main Bus
Supplied Circuit Breaker
Battery
W1 A1 Circuit Breaker Box
Assy.
Aircraft Ground
WOW Cockpit Control
A100 – Pin 1
DTU Connector
J1
Pin 1 WHT
J1
Pin 4 WHT
Pin 3 WHT/BLU
J1
Pin 15 WHT
Table B- 6: DTU Connection Chart Raytheon Model 300 Series
This Document is Subject to the Restrictions Contained on Cover Page
The export control classification with respect to this document is contained on the first page
DTU-G-010-1/B, Rev L, June 09, 2015
31 of 37
P&W ENGINE SERVICES, INC.
Part 23 Aircraft
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
5.2.7 Raytheon Model B300 Series
Sensor
A/C Bus
Wire Number
AAV19A24
A/C Battery
AAV09B24
WOW
AAD09A24
Connection Chart
Aircraft Component
Main Bus
Supplied Circuit Breaker
Battery
W1 A1 Circuit Breaker Box
Assy.
Aircraft Ground
WOW Cockpit Control
A100 – Pin 1
DTU Connector
J1
Pin 1 WHT
J1
Pin 4 WHT
Pin 3 WHT/BLU
J1
Pin 15 WHT
Table B- 7: DTU Connection Chart Raytheon Model B300 Series
5.2.8 Raytheon Model 1900 & 1900C
Sensor
A/C Bus
Wire Number
AAV19A24
A/C Battery
AAV09B24
WOW
AAD09A24
Connection Chart
Aircraft Component
Main Bus
Supplied Circuit Breaker
Battery
W214 Bus Bar-Hot Battery
Aircraft Ground
WOW Cockpit Control
J125 – Pin 2
DTU Connector
J1
Pin 1 WHT
J1
Pin 4 WHT
Pin 3 WHT/BLU
J1
Pin 15 WHT
Table B- 8: DTU Connection Chart Raytheon Model 1900 & 1900C
5.2.9 Raytheon Model 1900D
Sensor
A/C Bus
Wire Number
AAV19A24
A/C Battery
AAV09B24
WOW
AAD09A24
Connection Chart
Aircraft Component
Main Bus
Supplied Circuit Breaker
Battery
P202 Pin 11 or 12
Aircraft Ground
WOW Cockpit Control
J542 – Pin M
DTU Connector
J1
Pin 1 WHT
J1
Pin 4 WHT
Pin 3 WHT/BLU
J1
Pin 15 WHT
Table B- 9: DTU Connection Chart Raytheon Model 1900D Series
This Document is Subject to the Restrictions Contained on Cover Page
The export control classification with respect to this document is contained on the first page
DTU-G-010-1/B, Rev L, June 09, 2015
32 of 37
P&W ENGINE SERVICES, INC.
Part 23 Aircraft
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
6 WIRING DIAGRAM
6.1
DTU / ADASd Interconnect Schematic
Figure B- 19: DTU / ADAS Wiring Schematic
This Document is Subject to the Restrictions Contained on Cover Page
The export control classification with respect to this document is contained on the first page
DTU-G-010-1/B, Rev L, June 09, 2015
33 of 37
P&W ENGINE SERVICES, INC.
Part 23 Aircraft
6.2
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
DTU / ADAS+ Interconnect Schematic (Except Cessna Caravan)
Figure B- 20: DTU / ADAS+ Wiring Schematic (Except Cessna Caravan)
This Document is Subject to the Restrictions Contained on Cover Page
The export control classification with respect to this document is contained on the first page
DTU-G-010-1/B, Rev L, June 09, 2015
34 of 37
P&W ENGINE SERVICES, INC.
Part 23 Aircraft
6.3
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
DTU / ADAS+ Interconnect Schematic (Cessna Caravan STC Installation)
Figure B- 21: DTU / ADAS+ Wiring Schematic (Cessna Caravan STC Installation)
This Document is Subject to the Restrictions Contained on Cover Page
The export control classification with respect to this document is contained on the first page
DTU-G-010-1/B, Rev L, June 09, 2015
35 of 37
P&W ENGINE SERVICES, INC.
Part 23 Aircraft
6.4
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
DTU / ADAS+ Interconnect Schematic (Cessna Caravan Factory Installation)
Figure B- 22: DTU / ADAS+ Wiring Schematic (Cessna Caravan Factory Installation)
This Document is Subject to the Restrictions Contained on Cover Page
The export control classification with respect to this document is contained on the first page
DTU-G-010-1/B, Rev L, June 09, 2015
36 of 37
P&W ENGINE SERVICES, INC.
Part 23 Aircraft
6.5
Data Transmission Unit
DTU-G-010-1/B
Generation III Monitors
DTU / ADAS+ Upgrade Interconnect Schematic
Figure B- 23: DTU / ADAS+ Upgrade Wiring Schematic
This Document is Subject to the Restrictions Contained on Cover Page
The export control classification with respect to this document is contained on the first page
DTU-G-010-1/B, Rev L, June 09, 2015
37 of 37
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