200-00041-000 DAU
InstructionsFor Continued Airworthiness
AVIDYNE
CORPORATION
55 Old Bedford Road
Lincoln, MA 01773
Document Number AVSIU-011 Control Category CC2
Revision Description ECO Date
00 Initial Release 03-266 11/03/03
01 Update with FAA input DRO 03-001 11/20/03
02 Added STC number ECO-04-010 01/23/04
Confidential property of Avidyne Corporation
Not to be disclosed without permission
Confidential property of Avidyne Corporation
Not to be disclosed without permission
200-00041-000 DAU Instructions For Continued Airworthiness
Table of Contents
1. Introduction 5
1.1 Aircraft Description 5
1.2 Scope 5
1.3 Applicability 5
1.4 Definitions and Abbreviations 5
1.5 Precautions 5
1.6 Units of Measure 6
1.7 Referenced Publications 6
1.8 Distribution 6
2. Description of Installation 6
3. Control, operation information 8
4. Servicing information 8
5. Maintenance Instructions 8
5.1 Recommended periodic scheduled servicing 9
6. TroubleshootingInformation 9
7. Removal and Replacement Information 12
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200-00041-000 DAU InstructionsFor Continued Airworthiness
7.1 Removal 12
7.2 Installation 12
7.3 System Setup and Checkout 13
7.3.1 DAU Checkout 13
7.3.2 Engine Sensor Checkout 14
7.3.3 Fuel Quantity Calibration 14
8. Diagrams 15
9. Special Inspection Requirements 15
10. Application of Protective Treatments 15
11. Data 15
12. List of Special Tools 15
13. For Commuter Category Aircraft 15
14. Recommended Overhaul Periods 15
15. Airworthiness Limitation Section 15
16. Revision 16
17. Assistance 16
18. Implementation and Record Keeping 16
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200-00041-000 DAU InstructionsFor Continued Airworthiness
1. Introduction
1.1 Aircraft Description
Make: Various
Model: Various
Reference:
AVPFD-170 700-00006-0XX-0 PFD Approved Model List
STC #SA00190BO
STC No.: #SA00190BO
1.2 Scope
This document identifies the Instructions For Continued
Airworthiness for the modification of the above aircraft by
installation of an Avidyne 200-00041-000 Data Acquisition Unit
(DAU).
This ICA satisfies the requirements of 14 CFR 23.1529.
1.3 Applicability
Applies to aircraft altered by the installation of Avidyne 200-
00041-000 Data Acquisition Unit (DAU).
1.4 Definitionsand Abbreviations
ICA - Instructions for Continued Airworthiness
STC - Supplemental Type Certificate
MFD - Multifunction Display
AEG - Aircraft Evaluation Group
CMOS - Complementary Metal Oxide Semiconductor
DAU - Data Acquisition Unit
CHT - Cylinder Head Temperature
EGT - Exhaust Gas Temperature
1.5 Precautions
This section not applicable.
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200-00041-000 DAU InstructionsFor Continued Airworthiness
1.6 Units of Measure
This section not applicable.
1.7 Referenced Publications
This section not applicable.
1.8 Distribution
This Instructions For Continued Airworthiness is to be furnished
to the owner of an aircraft equipped with Avidyne Data
Acquisition Unit (DAU), P/N 200-00041-000, and is to become
part of the permanent aircraft record.
A current revision of this ICA shall be available on the Avidyne
website at www.avidyne.com (Technical Publications).
2. Description of Installation
The data acquisition subsystem is responsible for the collection of
data from aircraft sensors for its supported inputs (refer Section
3). The subsystem consists of an Avidyne 200-00041-000 Data
Acquisition Unit (DAU), engine/power/fuel/environmental
sensors, and associated wiring harnesses.
An engine wire harness collects signals from up to Six cylinder
head temperature (CHT) sensors, six exhaust gas temperature
(EGT) sensors, one turbine inlet temperature (TIT) sensor,
tachometer (RPM), weight-on-wheels (WOW) sensor and one fuel
flow sensor. This harness is routed through a firewall feed-
through. The feed-through is sealed with a heat resistant sealant,
such as RTV736. Aft of the firewall this harness is joined with
wiring that collects the other supported signals and routes them
to the DAU located behind the instrument panel. A block
diagram of the DAU, engine sensors and airframe sensors is
presented in Figure 1.
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200-00041-000 DAU Instructions For Continued Airworthiness
Sensors
VacuumPressure
TIT Probe(1)
EGT Probe(8)
CHT Probe(6)
OAT Sensor
OAT/ALTSource
(PFD)
MAP Guage
Fuel FlowSensor
OilTempSensor (AvldyneMFD/PFD)
Oil PressureSensor -
TachGenerator
Alternator 1
Battery 1
L/R Fuel Quantity
Figure1 - System Sensors, DAU, and Display Interfaces
The DAU is a remote-mounted unit with dimensions as shown in
Figure 2. The unit nominal weight is 1.6 lbs and has a maximum
power consumption of 3.5 W. Moritz Corporation manufactures
the DAU under Avidyne part number 200-00041-000.
The DAU interfaces to sensors and transmits an RS-232 output of
the following engine and electrical system parameters:
* Engine RPM * OAT
* Engine EGT (6 cylinders) Engine Oil Temperature
* Engine MAP * Engine Oil Pressure
* Engine CHT (6 cylinders) * Vacuum
* Engine TIT * Alternator current
* Engine Fuel Flow * Bus voltage & Current
* Engine Fuel Used * Fuel Quantity
Weight-on-Wheels
The DAU RS-232 serial data are received by multifunction
displays where the data is processed and displayed to the pilot.
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200-00041-000 DAU InstructionsFor Continued Airworthiness
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200-00041-000 DAU InstructionsFor Continued Airworthiness
5.1 Recommended periodic scheduled servicing
This section not applicable.
6. TroubleshootingInformation
The DAU data stream, transmits on two RS-232 data buses,
includes diagnostic information. Connect the DAU to an
Avidyne 700-00004-XXX-() MFD or a Personal Computer via an
RS-232 port to access this information. The RS-232 serial data are
transmitted at 19,200-baud, no parity bit, 8 data bits, 1 stop bit, at
a rate of 8 Hz. One header message is transmitted after each
group of 15 data records. If no MFD is available the data can be
viewed on a PC with a terminal emulator program (i.e. Microsoft
Windows Hyperterm).
The Avidyne MFD incorporates a message bar located at the
bottom of the display. Messages are generated by the system and
displayed on the message bar and are helpful in troubleshooting
system problems. The following table presents the messages that
are generated by the Engine application.
Table 1 - Engine Messages
Message Meaning
Engine Sensor Unit isnot No RS 232 Engine Sensor Unit data
communicating isbeing received by the MFD.
Engine Sensor Unit Verification that Engine Sensor Unit
Operating Normally data is valid.
Engine Sensor Unit RS-232 data received but the
Configuration Error harness jumper settings are
incorrect.
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200-00041-000 DAU InstructionsFor Continued Airworthiness
Table 2 provides a listing of DAU electrical connector pin
assignments to assist in troubleshooting.
Table 2 - DAU Pinout
Pin J1 J2
1 +28VDC Power Input High +28VDC Power Input High
2 VAC Main Bus Signal Input High No Connection
3 No Connection No Connection
4 VDC Main Bus Signal Input High No Connection
5 Prop RPM Signal Input High Fuel Flow Signal Input High
6 AMP Battery Signal Input High No Connection
7 AMP Alternator Signal Input High No Connection
8 Oil Pressure Signal Input High MAP Signal Input High
9 Oil Temperature Signal Input High No Connection
10 Fuel Quantity Signal Input High- Right Fuel Quantity Signal Input High- Right
11 TIT Input - Chromel No Connection
12 EGT Cyl. 6 Input - Chromel CHT Cyl. 6 Input - Chromel
13 EGT Cyl. 5 Input - Chromel CHT Cyl. 5 Input - Chromel
14 EGT Cyl. 4 Input - Chromel CHT Cyl. 4 Input - Chromel
15 EGT Cyl. 3 Input - Chromel CHT Cyl. 3 Input - Chromel
16 EGT Cyl. 2 Input - Chromel CHT Cyl. 2 Input - Chromel
17 EGT Cyl. 1 Input - Chromel CHT Cyl. 1 Input - Chromel
18 RS232 Ground RS232 Ground
19 RS232 Transmit Channel 1 RS232 Transmit Channel 2
20 Power Input Return Power Input Return
21 VAC Signal Input Return No Connection
22 No Connection No Connection
23 Prop RPM Signal Input Return Fuel Flow Signal Input Return
24 AMP Battery Signal Input Low No Connection
25 AMP Alternator Signal Input Low No Connection
26 Oil Pressure Signal Input Return Fuel Quantity Signal Input Low - Left
27 Oil Temperature Signal Input Low MAP Signal Input Return
28 Fuel Quantity Signal Input Low - Right No Connection
29 TIT Input - Alumel No Connection
30 EGT Cyl. 6 Input - Alumel CHT Cyl. 6 Input - Alumel
31 EGT Cyl. 5 Input - Alumel CHT Cyl. 5 Input - Alumel
32 EGT Cyl. 4 Input - Alumel CHT Cyl. 4 Input - Alumel
33 EGT Cyl. 3 Input - Alumel CHT Cyl. 3 Input- Alumel
34 EGT Cyl. 2 Input- Alumel CHT Cyl. 2 Input- Alumel
35 EGT Cyl. 1 Input - Alumel CHT Cyl. 1 Input- Alumel
36 Shield Shield
37 RS232 Receive Channel 1 RS232 Receive Channel 2
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200-00041-000 DAU InstructionsFor Continued Airworthiness
Table 3 provides a listing of DAU electrical connector pin
assignments to assist in troubleshooting. Table 4 contains
compatible sensor information.
Table 3 - DAU Pinout
J3
Pin Description Pin Description
1 +12VDC Fuel Flow Sensor Exc. 9 Aircraft Type Designation Input - 2
2 +12VDC RPM Sensor Exc. 10 Aircraft Type Designation Input - 3
3 No Connection 11 WOW Signal Input
4 No Connection 12 Shield
5 No Connection 13 No Connection
6 No Connection 14 No Connection
7 No Connection 15 No Connection
8 Aircraft Type Designation Input - 1
Table 4 - DAU Sensor Compatibility
Parameter Sensor Excitation Sensor Information
MAP +28 VDC Kulite P/N -251 -1000 -25A
RPM +12 VDC B&D P/N 0404-102
EGT N/A K-Type Thermocouple
Norwich P/N 101-00103
TIT N/A K-Type Thermocouple
Norwich P/N 101-00103
FF +12 VDC Floscan P/N 201C-6
CHT N/A Transmitter per MS24482-1, -2
Output per MIL-T-25446D
OP +28 VDC Kulite P/N -252 -2000 -150G
OT N/A Resistance Bulb per MS28034
Output per MIL-T-7990B
Alternator Current N/A 100 amps @ 50mv Shunt
+28vdc common mode
Battery Current N/A 100 amps @50mv Shunt
+28vdc common mode
Main Bus Voltage N/A Aircraft Power Bus
VAC +28 VDC Kulite P/N -253 -1000 -3D
Fuel Quantity N/A Rochester P/N 7740 -204 L.INBD
Rochester P/N 7740 -204 R.INBD
Rochester P/N 7740 -204 L.OUTBD
Rochester P/N 7740 -204 R.OUTBD
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200-00041-000 DAU InstructionsFor Continued Airworthiness
7. Removal and Replacement Information
7.1 Removal
Removal of the DAU requires access to its mounting location
behind the instrument panel.
i) Locate the DAU by inspection behind the instrument panel.
Refer to the applicable aircraft maintenance manual to
determine recommended procedures to access avionics
behind the instrument panel.
ii) Remove the three sub-D connectors, J1, J2, and J3, on the
cable harness by loosening the connector jackscrews with a
Philips head screw drive.
The DAU is secured to its mounting surface by four bolts with
locking nuts. Access to these fasteners must be made.
iii) If the DAU mount plate or shelf does not provide
unobstructed access to DAU mounting screws, either;
a. Remove interfering hardware in accordance with
aircraft maintenance manual or approved
supplemental data, or
b. Unfasten the mounting tray or shelf and position to
gain access to the DAU Mounting hardware.
iv) With a Philips head screw drive, remove the 4 screws
securing the DAU to the mount plate or shelf.
7.2 Installation
To install the DAU, reverse the removal process.
i) With a Philips head screw drive, secure the DAU to the
mount plate or shelf with the 4 screws mounting screws.
ii) If necessary, re-secure the mounting shelf and any
hardware removed to gain access to the DAU.
iii) Connect the three sub-D connectors, J1, J2, and J3, on the
cable harness to the DAU and tighten the connector
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200-00041-000 DAU Instructions For Continued Airworthiness
jackscrews with a Philips head screw drive. Match the
wire labels with the DAU connector labels, as the
connectors are not unique.
Upon reinstallation, a functional check should be performed in
accordance with the System Setup and Checkout procedures
detailed in Section 7.3
7.3 System Setup and Checkout
Any time the DAU is removed and sent to the factory for service,
or is replaced with another un it, these MFD system setup
procedures must be performed to assure that the MFD and DAU
are properly configured for the installation. This section should
also be referenced if it is suspected that the unit may be mis-
configured.
7.3.1 DAU Checkout
If the DAU is connected to an Avidyne 700-00004-XXX-0 MFD,
use the MFD to checkout the DAU.
i) Apply power to the DAU and MFD.
Upon initial system power-up, the MFD will
execute a start-up sequence. During this time, the
screen will initially display the FlightMax logo,
followed by a blank screen until a blue screen
with the text "Initializing-Please Wait..." is
displayed. The startup sequence is finished when
the text "Press any bezel key to Continue..." is
displayed. The initialization screen displays the
loaded software version, along with NavData
and Obstacle database expiration dates.
ii) Press any bezel key.
The Initial Fuel page is displayed next.
iii) Press the Fuel Done button to exit.
The MFD configuration is accomplished in the setup pages that
are accessed through the Maintenance Mode, which is accessed as
follows:
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200-00041-000 DAU InstructionsFor Continued Airworthiness
iv) Upon completion of system initialization, rotate the page
knob to the Setup page.
v) Simultaneously press and hold the top and middle left-
hand bezel keys for at least 5 seconds until the
maintenance page appears.
Configuration Item Selections
Sensor TypeNot installed,
Avidyne DAU
Port Com 1,Corn 2,Corn 3, Corn 4
Aircraft Model Various
vi) Depress bezel key next to the Sensor Type legend until
"Avidyne DAU" is displayed
The Aircraft Model setting automatically established
between the MFD and DAU.
vii) Select the Port and Aircraft Type
viii) Press the Save bezel key. The MFD must be restarted for
the settings to take effect.
7.3.2 Engine Sensor Checkout
After the MFD has been restarted, view the Engine page to verify
data communication. Operate the aircraft engine to confirm
correct operation of all sensors. Refer to Section 6,
Troubleshooting Information, for resolution of error messages.
7.3.3 Fuel Quantity Calibration
After replacement of the DAU it is necessary to perform an
aircraft fuel quantity calibration. This process involves loading
and unloading fuel. The following steps cover fuel calibration.
i) View the Engine Setup page, and press "Fuel Cal".
ii) Ensure the fuel tanks are empty then press "Begin Cal".
iii) Follow the instructions on the Fuel Calibration display to
calibrate both left and right tanks.
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200-00041-000 DAU Instructions For Continued Airworthiness
iv) When finished, press "Cal Complete".
8. Diagrams
This section not applicable.
9. Special Inspection Requirements
This section not applicable.
10. Application of Protective Treatments
This section not applicable.
11. Data
This section not applicable.
12. List of Special Tools
This section not applicable.
13. For Commuter Category Aircraft
This section not applicable.
14. Recommended Overhaul Periods
This section not applicable.
15. Airworthiness Limitation Section
The Airworthiness Limitations section is FAA approved and
specifies maintenance required under §43.16 and §91.403 of the
Federal Aviation Regulations unless an alternative program has
been FAA approved.
There are no additional airworthiness limitations as a result of
this modification.
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200-00041-000 DAU InstructionsFor Continued Airworthiness
16. Revision
Revisions to this document shall be coordinated through the
Boston Aircraft Certification Office, the Kansas City AEG, and the
STC holder.
17. Assistance
For questions or assistance regarding this ICA, contact Avidyne
at:
Avidyne Corporation
55 Old Bedford Road
Lincoln, MA 01773
Service: 1-888-723-7592
Web Site: www.avidyne.com
18. Implementation and Record Keeping
This ICA is to be made part of the applicable section 91.409 or
135.419 aircraft inspection program for this aircraft.
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