Sandel SN3308 User manual

90106-IM-G(4) INSTALLATION MANUAL W SIG.DOC
SN3308 Navigation Display
Installation Manual
Document No. 90106-IM
Revision G(4)
9/25/03
SANDEL AVIONICS
2401 DOGWOOD WAY
VISTA, CA 92081
PHONE [phone]
FAX[phone]
WEBSITE WWW.SANDEL.COM
EMAIL [email protected]

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SN3308 Navigation Display
Installation Manual
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Table Of Contents
1 GENERAL INFORMATION 8
1.1 Introduction 8
1.2 Equipment Description 8
1.2.1 Features 8
1.3 Installation Planning 9
1.4 Interface Planning 10
1.4.1 Compass System 10
1.4.2 GPS (Loran) Switching 11
1.4.3 GPS Annunciators 12
1.4.4 Nav Interface 12
1.4.5 Marker Beacon 13
1.4.6 Composite Nav and ADF 13
1.4.7 RESERVED FOR FUTURE USE 13
1.4.8 ARINC Channels and DME Interface 13
1.4.9 RS232 / RS422 Serial Communication 14
1.4.10 GARMIN GNS430 GPS/VOR/LOC Combination Receiver 15
Required SN3308 Setup Items 16
Required GARMIN GNS430 Setup Items, Receiver 1 16
Required GARMIN GNS430 Setup Items, Receiver 2 16
1.4.11 UPS GXXX RS232 INTERFACE 17
Configuration Notes: 17
1.4.12 Pilot-Controlled Switches 17
1.4.13 Autopilot Interface 17
1.4.14 Brightness Control 17
1.5 Disclaimer 18
2 TECHNICAL INFORMATION 19
2.1 General 19
2.2 SN3308 Approval, Physical, and Electrical Properties 19
2.2.1 Approval Data 19
2.2.2 Physical Dimensions 19
2.2.3 Operational Characteristics: 20
2.3 Interface Conventions 20
2.3.1 Connector P1 21
2.3.2 Connector P2 22
2.3.3 Connector P3 23

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2.4 ARINC 419/429 Serial Data Receivers Interfaces 24
2.5 ARINC 419/429 Serial Transmitter Interfaces 25
2.6 Basic Component Part Number and Variants 25
2.7 Installation Kit And Accessories 25
2.8 Bill of Materials – SN3308 Install Kit 26
2.9 License Requirements 26
2.10 Technical Standard Order Stipulation 26
2.11 Installation and Operational Approval Procedures 26
3 INSTALLATION 28
3.1 General 28
3.1.1 Unpacking and Inspecting Equipment 28
3.2 Installation Considerations 28
3.2.1 General Considerations 28
3.2.2 Cooling Considerations 28
3.2.3 Mechanical Installation Considerations 29
3.2.4 Electrical Installation Considerations 29
3.3 Connector P-1 Pinout Description 31
3.4 Connector P-2 Pinout Descriptions 34
3.5 Connector P-3 Pinout Descriptions 38
4 SETUP PROCEDURES 41
4.1 General 41
4.2 Accessing The Maintenance Menus 41
4.3 Equipment/Configuration Selections 41
5 OPERATING DETAILS 42
6 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS 43
6.1 General 43
6.2 Projection Lamp Replacement Procedures 43
7 APPENDIX A: POST-INSTALLATION PROCEDURES 1

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8 APPENDIX B: ENVIRONMENTAL QUALIFICATION FORM 1
9 APPENDIX C: SAMPLE FAA FORM 337 1
10 APPENDIX D: SAMPLE AIRPLANE FLIGHT MANUAL SUPPLEMENT 1
11 APPENDIX E: CHECKOUT PROCEDURES 1
11.1 Functional Ground Test Procedures/Report 1
11.1.1 Introduction 3
11.1.2 Test Procedures and Results 3
11.1.3 Physical Installation 3
11.1.4 Wiring Verification and Initial Power-Up 3
11.1.5 System Configuration 4
11.1.6 System Functions 5
11.1.7 Compass System Interface 5
11.1.8 NAV Source Selection 5
11.1.9 BRG Source Selection 6
11.1.10 DME Selection 6
11.1.11 GPS Interface and Control 7
11.1.12 Marker Beacon Interface 8
11.1.13 Flight Control System Interface 9
11.1.14 Stormscope ® Interface 9
11.1.15 Additional Testing 9
11.2 EMI/RFI Test Procedures 10
11.2.1 Nav/Com Testing 10
11.2.2 General Testing 10
11.2.3 Additional Testing 11
11.3 Operational Flight Test Procedures/Report 12
11.4 Introduction 14
11.5 Test Procedures 14
11.5.1 Pre-Departure Operations 14
11.5.2 Enroute Operations 15
11.5.3 GPS Approach Operations 15
11.5.4 ILS Approach Operations 16
11.5.5 Additional Testing 16
12 APPENDIX F: LIST OF EFFECTIVE DRAWINGS AND ATTACHMENTS 1

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Revision History
Revision Date Comments
A 10 June 98 Initial release
B 11 July 98
Added sample Flight Manual Supplement.
Added requirements for dimmer pot and data port.
Changed Maint. Page 4 to “Bearing Ptr Select”,
added composite nav selections.
Installation drawings revised.
DO-160C Categories revised.
C
8/31/98
Note about Darlington discrete outputs. Changed
flight manual supplement to say “magnetic compass”
not “wet compass”. Note on ILS Energize Inputs.
Minor changes in flight/ground test procedures.
Added notes on resolver troubleshooting.
D9/20/98 Far’s referenced in 337. Renamed flight manual
supplement. Repaginated.
E 12/10/98 Effective Drawing List added. Software version
numbers updated. Post-install temperature test.
Adds information about software 1.09 features:
Temperature indication, Sys page inverter/fan speed
readout, ILS Lockout selection. Incorrect FCS ref
note removed. Cooling considerations text changed.
ILS Energize pin descriptions changed. Maintenance
page text changed on ADF, FCS, NAV Change,
System. Note on BC, Bootstrap output. New Airplane
Flight Manual Supplement added.
F 5/26/99 1.4.10 Added Garmin Receiver
1.4.8 Note on DME.
2.3.3 Pinout Table names changed for clarity.
2.4 Added VHF NAV and GS inputs
2.5 Clarified ARINC Serial Transmitter Interface
2.8 Updated Bill Of Material
3.3 Typo on connector numbers
6.2 Updated BOM and added LMP CHG operation to
lamp replacement procedures.
Appd’x A:
MP2: Fluxgate, new data added
MP4: Brg Pointers, added info on ARINC 429 NAV.
MP5: FCS added Century DC autopilots to lists.
MP6: Changed nomenclature and tips.
MP8: FCS Emulation updated
MP10: FCS Change updated
MP15: NAV Chg, added info on ARINC NAV ops

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MP16: Relay Sense, new page.
MP17: SYS added info on inverter items
MP21: Updated Brightness
MP22-25: DVM pages added
MP26: Serial Diagnostics added.
G 10/27/00 Incorporated A/R 245 Page 44 updated installation
instructions for the new chassis and ejector lock tray.
Page 43 Lamp Replacement Kit was P/N 90120.
Page 24 Bendix/King Bezel Kit was 90118
G(1) 01/04/01 Incorporated A/R 346 Update Flight Manual
Supplement in Appendix D
PC Applicable revision screen nomenclature
G(2) 04/03/01 Incorporated A/R 360
1.4.7 Deleted ref to Radar Altimeter
2.3.2 Deleted ref to Radar Altimeter
2.3.3 Deleted ref to Radar Altimeter
P1-32 was triple conductor wire
P2-8 Deleted ref to Radar Altimeter
P2-27 Deleted ref to Radar Altimeter
P2-13 Deleted ref to Radar Altimeter
P3-24 Deleted ref to Radar Altimeter
6.1 Lamp hours were 200
Appd’x A added Garmin GNS430 to LNAV-1 Select
G(3) 10/04/02 Incorporated A/R 573
Updated Appendix F, Drawings
Corrected KR-22 Interface, Dwg 16 of 29
Added HDG Datum Low for KFC150, DWG 22 of 29
Added New DWG 24 of 29, Bendix M4D & FCS810
Corrected GNS430 Pinout on DWG 28 of 29
Corrected GNS430 Pinout on DWG 29 of 29
G(4) 9/25/03 Incorporated A/R 661
Updated Appendix F, Drawings
Added King KDM 706 to Dwg 17 of 29
Added GNS530 to Drawing 25, 26, 27, 28, and 29

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SN3308 Navigation Display
Installation Manual
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SN3308 Navigation Display
Installation Manual
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1 GENERAL INFORMATION
1.1 Introduction
The information contained within this Installation Manual describes the features,
functions, technical characteristics, components, approval procedures, installation
considerations, setup procedures, checkout procedures, and instructions for
continued airworthiness for the Sandel Avionics SN3308 Navigation Display. The
SN3308 is available in several dash-number configurations depending on installation
on pilot’s side, copilot’s side, or center panel. In the manual any reference to GPS
receivers is generic and can be applied to Loran receivers.
1.2 Equipment Description
1.2.1 Features
The Sandel SN3308 Navigation Display is an advanced microprocessor controlled
airborne multipurpose electronic display which is FAA approved under technical
standard order TSO-C113. The SN3308 employs a patent-pending active matrix
liquid crystal (AMLCD) projection display. It is designed to combine the functions of:
x Horizontal Situation Indicator (HSI)
x DME Readout
x Marker Beacon Indicator
x WX-500 Stormscope® Display
x Long-Range Navigation (GPS or Loran) Map Display
x GPS Annunciators and External Mode Switches
Outputs of heading and course datum and bootstrap heading output are provided.
The versatile digital and analog interface properties of the unit provide for
compatibility with most VHF navigation receivers, ADF’s, DME’s, GPS’s, remote
gyros and flux gates.
The SN3308 is designed to display the downloaded flightplan data from a connected
GPS receiver or from a Jeppesen database (available on software version 2.00 or
later). The moving map database for the SN3308 as well as the internal operating
system software are field uploadable through the use of a portable computer
equipped with a Windows operating system and an RS-232C Serial Port.

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Although simple, retrofit replacement of most existing three-inch PNI’s or HSI’s is
possible without additional features, we strongly encourage complete installation of
the unit with all compatible peripheral equipment interconnected to maximize its
functional capability.
1.3 Installation Planning
Sandel Avionics has taken many equipment interface possibilities into consideration
during the design of the SN3308 to ensure maximum interoperability with other
avionics. Contact the factory with any questions about interfacing to specific avionics
equipment not covered in the installation drawings.
To simplify installation and installation planning, signals are wired to the SN3308 pins
per the installation diagrams and software setups are used in a post-installation
procedure to assign protocols/gradients to each pin based on the equipment
connected. There are separate maintenance menu pages for each equipment
function and in most cases the selections are made by equipment make/model.
In addition to connecting the desired equipment, the installer must provide the
following components:
x Dimmer Control
An external pot must be mounted near the SN3308 to provide for
convenient dimming of the display. This is not a rheostat, it is simply a
10K, ½ Watt pot which provides a control voltage.
x Data-load Port
A ¼” phone jack must be installed in any convenient location and wired to
one of the SN3308’s serial input ports, as shown on NAV-2,GPS1(RS422),
GPS-2, DATALOAD Installation Drawing. This port will be used to upload
new software and database revisions.
Refer to the installation schematics at the rear of this manual for details on connecting
these two required components.
The installation planning cycle is summarized as follows:
1) Compile an equipment list for the aircraft.
2) Study the feature list below, and determine the desired functional
characteristics for the installation.
3) Study the installation drawings to determine a basic interconnect scheme
and check for conflicts.
4) Develop the specific wiring diagrams unique to the aircraft.

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The post installation procedures are summarized as follows:
1) Prior to power-up review correct wiring by using standard ohm meter and
voltage checks . Insure the correct orientation and positioning of the three
SN3308 ‘D’ connectors. The connector numbers are printed on the back
of the SN3308 for reference.
2) Review special items such as connection of the Nav receiver resolver
wiring.
3) Apply power to the SN3308, bring up in maintenance mode (see page 41)
and sequentially access each SN3308 maintenance page to correctly
select the installed equipment.
4) Allow the unit to operate for 30 minutes at maximum brightness and check
the internal temperature readout on maintenance page 17 for an
approximate temperature rise of approximately 10qC or 18qF. This
checks proper cooling airflow.
5) Perform Ground Test procedures
6) Perform Flight Test procedures.
1.4 Interface Planning
1.4.1 Compass System
Determine whether the SN3308 is to be used internally slaved or unslaved.
Unslaved operation would be appropriate when the SN3308 is bootstrapped to an
already slaved compass system or is being slaved to a panel mounted XYZ DG.
Plan for:
 High Resolution Digital Output from a Mid-Continent 4305 series DG with
compass valid output, flux gate 10 VAC Fluxgate Excitation and Internal
26VAC Inverter
 Quadrature stepper motor drive input from a Bendix/King KG 102 series
DG with compass valid output and flux gate support,
 3-wire ARINC 407 synchro DG with or without compass valid input and
fluxgate.ARINC Low Speed 429 Heading Input. Sandel monitors for Label
320, Magnetic Heading Data and Label 270 System Status

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SN3308 Navigation Display
Installation Manual
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Internal slaving requires connection of the flux gate excitation to the SN3308 flux gate
reference input P1-7. This input is used only to demodulate the flux gate signals.
Synchro DG’s require the master 400Hz inverter to be connected to the SN3308
400Hz reference input P2-4. This input is used to lock all 400Hz inputs and outputs
in the SN3308. This input presents no loading to the source.
Follow the information on the installation drawings, and plan to set up the appropriate
compass selections on the compass system maintenance page.
Slaving does not require the use of an external slaving accessory. Compass
calibration is performed using the SN3308 Compass maintenance page and offers a
unique 4-quadrant setup with no interaction between N-S-E-W. The SN3308 will
provide standby heading operation from the flux gate alone in the event of directional
gyro (DG) failure.
The SN3308 has a 3-wire ARINC 407 synchro bootstrap compass output if required.
(Software 1.05 and later).
1.4.2 GPS (Loran) Switching
The SN3308 has 3 Darlington open collector relay output discretes which operate
when the pilot selects NAV-2, GPS-1, or GPS-2 respectively. These outputs are
restricted to 35ma maximum current – do not exceed 35ma on serial numbers 2699
and below. These outputs pull only to within 1 volt of ground. Serial numbers 2700
and above have 250ma maximum current. Serials numbers 2700 and above outputs
pull to within 1 ohm of ground. Check to insure the remote switching relay is
compatible. If a multi-coil relay is used the SN3308 should be configured to drive the
first coil and a contact from the first coil can then be used to drive the remaining coils.
Nav 1 selection is the default selection and no relay driver output discrete is available.
The NAV-2, GPS-1, or GPS-2 outputs can be used to operate a switching relay for
each source, allowing the pilot to control the nav source selection from the front panel
of the SN3308. This is referred to as “master” mode and it is the preferred mode of
installation. In this configuration an additional remote switch/annunciator panel for a
GPS receiver is not required.
In the event the aircraft has an existing GPS switch/annunciator panel or it is desired
that one be installed, the “GPS SELECTED-” input (P2-30) on the SN3308 is used to
remote sense the selection of the GPS-1 and annunciate the selection. This is
referred to as “slave” mode. It allows annunciation of the selection on the SN3308
but does not use the front panel NAV switch to select the GPS receiver. This mode is
only available for use with a single GPS.
Master/Slave mode selection is done in the NAV maintenance page.
The SN3308 can be configured to accept a RELAY SENSE input, which provides
feedback as to the actual state of the switching relay. A single pole on the relay is

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SN3308 Navigation Display
Installation Manual
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used to ground an SN3308 input pin when the relay is in the energized position. If
the low signal is not detected, the SN3308 annunciates the relay failure by redlining
the nav source display. The actual pin number used for the RELAY SENSE input is
selected in the RELAY SENSE maintenance page.
1.4.3 GPS Annunciators
Discrete annunciator inputs are provided for ARM, ACT, WPT or HLD, MSG,
OBS/LEG Mode, and Parallel Track. Connect the pins appropriate to the installed
receiver and select the receiver type on the LNAV maintenance page. See
GPS/SWITCH/ANNUNCIATORS Installation Drawing for the complete matrix of
outputs and annunciators.
Discrete control outputs are provided for APPR ARM, OBS Mode (King KLN90) and
HOLD (II Morrow). These are open-collector Darlington outputs which pull to within 1
volt of ground. Ensure these outputs are compatible with the associated receiver.
The Garmin GNS430 uses ARINC-429 for the annunciator functions so no discrete
connections are used.
1.4.4 Nav Interface
The SN3308 has a conventional set of analog inputs for deviation, flags, etc. from the
primary nav receiver. See the installation diagram for details. These inputs are not
connected with the use of the Garmin GNS430 Arinc Nav receiver, which uses
ARINC-429 only.
There are only low level flag inputs. If it is desired to use a Superflag instead of a low-
level flag from the nav receiver, a series resistor must be used to the low level ‘+’
input and the ‘-‘ input is grounded. See the installation drawings.
ILS lockout of the GPS selection is provided by an ILS Energize 1/2 input pins. This
feature can be disabled on the NAV maintenance page. In the Master mode this will
cause the SN3308 to revert to and annunciate NAV-1 when an ILS is tuned on NAV-
1, or NAV-2 when an ILS is tuned on NAV-2. Disabling of ILS lockout is called for
when the customer does not want ILS lockout operation, or when a GPS receiver
with vertical guidance is used to drive the ILS Energize pin during GPS operation. In
this situation NAV1/GPS1 use ILS Energize 1, and NAV2/GPS2 use ILS Energize 2
to display vertical guidance.
Two types of resolvers are supported on different sets of pins.
a) An electronic OBS resolver with rotor input and SIN/COS outputs is
provided. An associated DC reference pin (P1-28) must be connected to
the stator low-side connection of the NAV receiver. This may be ground
but may also be a DC reference voltage of approximately 4.5vdc.
WARNING: You must check the nav receiver wiring before installation
planning and before applying power to the system to prevent NAV receiver

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damage from inadvertent miswiring. Refer to the Sandel installation
drawing.
This resolver will operate from 30Hz to 500Hz and is calibrated in the NAV
maintenance page
b) An electronic 400Hz differential resolver is provided for use with 400Hz
receivers such as Collins VIR-30A. This interconnect uses SIN/COS
inputs (ground referenced) and SIN/COS outputs (ground referenced).
(Software 1.33 and later)
1.4.5 Marker Beacon
Three inputs are provided for Marker Beacon. These are DC level-sensitive inputs.
The thresholds and logic levels are adjusted by selection of the appropriate
equipment type on the MKR maintenance page. Note the use of lamp load resistors
in the installation drawing, which are required for some receiver types.
1.4.6 Composite Nav and ADF
The bearing pointers can derive their information from any of the connected
navigation receivers, including two composite nav inputs, ADF’s and the long range
navigation receivers through the serial ports.
ADF’s can be connected as ARINC 407 synchro or DC sine/cosine inputs. See the
installation drawings for interconnection data and select the appropriate format from
the ADF maintenance page.
The composite Nav inputs accept standard .5v inputs. For 3v inputs a series resistor
is required, please see the appropriate installation drawing. Selection of 0/180
phase is made by the appropriate maintenance page calibration.
1.4.7 RESERVED FOR FUTURE USE
.
1.4.8 ARINC Channels and DME Interface
There are three ARINC 429 receiver channels. Channel 1 supports ARINC 429 only.
Channels 2/3 support King Serial Digital DME data and ARINC 568 (software 1.33
and later) for ARINC digital DME’s such as Collins DME40. After the appropriate
ports are assigned for the aircraft’s equipment, any remaining port may be assigned
as an ARINC-429 Nav receiver channel to support the Garmin GNS430.
 Channel 1 (P3-10/28) is normally used for GPS-1, Loran-1 receivers or ARINC
Low Speed 429 Heading Input. Channel 1 also features an ARINC 429
Transmit channel which is used to send course and heading datum to external
equipment such as GPS receivers. This is preferred over RS-232 connections

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of these receivers as more data is available to the SN3308 and it also
eliminates the requirement for the course resolver relay switching. See the
installation drawings.
 Channel 2 (P3-9/27) is normally used for Digital DME-1 along with clock pin
P3-8; it may also be used for the ARINC-429 Nav channel of the Garmin
GNS-430 or ARINC Low Speed 429 Heading Input.
 Channel 3 (P3-26/7) is normally used for a second GPS ,DME or ARINC Low
Speed 429 Heading Input.
ARINC channels 2/3 are also capable of ARINC 568/419 DME (Software
1.33 and later) or King Serial Digital using an additional pin. This pin is used
for 568 SYNC or King DME REQ. The type of communication protocol is
selected on the DME maintenance page.
Channel 3 may also be used for the ARINC-429 Nav channel of the Garmin
GNS-430 if channel 2 is in use by a DME.
King KN-63 DME’s require the use of the KDI-572 controller in order to supply the
DME REQ signal as shown on the installation drawings.
The KN62/64 panel mount DME’s can be remote-indicated by connecting
CLK/DATA/DME REQ to the SN3308 as shown in the installation drawings. A KDI-
572 is not required. NOTE: when the KN62/64 is switched to “FREQ”, the DME
readout on the SN3308 will continue to associate with NAV-1 or NAV-2 depending on
the DME1-NAV2 select pin, see below.
Two DME HOLD inputs are provided for annunciation. In single DME installations
DME2 HOLD can alternately be used to annunciate DME1-NAV2 (i.e. cross side
selection of DME1) to associate the DME with the correct bearing pointer selection.
See the installation drawings.
A single 40 mV DC/nautical mile DME distance input is provided to substitute for
serial digital DME 1 or 2. In this case DME2 HOLD is used as ANALOG DME VALID
input and DME2 HOLD is not available.
1.4.9 RS232 / RS422 Serial Communication
Two RS232 (or RS422) ports are provided for communication with Loran, GPS, or
WX-500 Stormscope®.
Channel-1 (P3-16/34 and P3-12) is normally used for GPS-1. Use this only if ARINC
429 is not available for the associated receiver. (ARINC 429 is the preferred
hookup).
Channel-2 (P3-14/32 and P3-30) is normally used for the WX-500 Stormscope® or a
second GPS receiver. It is also used for data loading map and program data from a

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remote host PC. See the installation drawings for the recommended method for
connecting channel 2.
Both of these ports support RS422 transmission which can be connected if desired.
The RS-232 and RS-422 transmitters are on separate pins and operate
simultaneously.
Note that the same receiver pins are used for either RS232/422. The SN3308 uses a
differential receiver compatible with both standards. RS-232 is connected to the
minus input of the receiver, and the plus input is grounded because RS-232 is an
inverted signal, i.e. –10v is logic one and +10v is logic zero.
1.4.10 GARMIN GNS430 GPS/VOR/LOC Combination Receiver
The complete interface between the SN3308 and the GNS430 can be done using the
ARINC 429 ports. The ARINC 429 data carries all GPS and VOR/LOC data, resolver
information and flags & annunciators.
For a single GNS430 installation, the SN3308 429 Port 1 is used to receive GPS
data, and either Port 2 or Port 3 is used to receive VOR/LOC data. If a DME is to be
interfaced to the SN3308 as well, it must be on Port 2 which will necessitate
connecting the GNS430 VOR/LOC to Port 3. ARINC 429 output data from the
SN3308 must go to the GNS430 GPS 429 Input port (see installation drawing). No
composite NAV signals are required, because the bearing pointers receive data via
the ARINC 429.
For a dual GNS430 installation, a relay is required to switch the ARINC 429 data from
the two VOR/LOC receivers into the single available SN3308 input port. In addition,
the composite NAV signal from the two VOR/LOC receivers are connected to the
SN3308 to provide uninterrupted NAV bearing pointers irrespective of the selected
receiver. As in a single GNS430 installation, ARINC 429 output data from the
SN3308 must go to the GNS430 GPS 429 Input ports.
In some dual GNS430 installations, the second GNS430 is wired to a mechanical
indicator and will not be selectable for primary navigation on the SN3308. In this
case, composite NAV and GPS ARINC 429 data from the second receiver can be
connected to the SN3308 to provide RMI bearing pointers only. The SN3308 is
configured as though it were connected to a single GNS430, with the additional
bearing pointer sources enabled. NOTE: It is not possible to enable GPS 2 as a
bearing pointer source without having it also available as a primary nav source.
After installation, ensure that the following setup items are configured on both the
SN3308 and the GNS430:

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Required SN3308 Setup Items
Hardware MOD1 STATUS OR LATER
Software 1.30 OR LATER
STUDY THE SANDEL MAINTENANCE PAGE ITEMS ON THE
APPROPRIATE GNS430 INSTALLATION DRAWINGS, AND SET AS
INDICATED.
IN A DUAL GNS430 INSTALLATION MAKE SURE BOTH NAV-1 AND
NAV-2 ARE DOUBLE-ASSIGNED TO ARINC PORT-2.
Maintenance
Page Items
IN A SINGLE GNS430 INSTALLATION NAV-1 MAY BE ASSIGNED TO
ARINC PORT-3, ALLOWING A SINGLE DIGITAL DME TO BE
ASSIGNED TO ARINC PORT-2.
Relay Sense: ASSIGN THE RELAY SENSE ITEMS SHOWN ON THE INSTALLATION
DRAWING TO THE SPARE PINS YOU HAVE SELECTED. IN A
GNS430 INSTALLATION THIS WILL USUALLY BE P2-11 AND/OR P2-
29 (FORMER MSG/WPT ANNUNCIATORS, NOT USED).
Relay Mode MASTER
ILS Lockout OFF
DME: A DUAL GNS430 INSTALLATION WILL USE ALL THE PORTS AND A
DIGITAL DME CANNOT BE USED. ENSURE THE DME IS
UNASSIGNED.
Required GARMIN GNS430 Setup Items, Receiver 1
Software Main 2.07 or later
IN 1: Low, Sandel EHSI
OUT: Low, GAMA 429 Grph w/Int Note: NOT ARINC 429!
Main ARINC 429
Configuration
SDI: LNAV 1 SDI1
Speed RX: Low
Speed TX: Low
VOR/LOC/GS
ARINC 429
Configuration SDI: VOR/ILS 1 SDI1
Required GARMIN GNS430 Setup Items, Receiver 2
Software Main 2.07 or later
IN 1: Low, Sandel EHSI
OUT: Low, GAMA 429 Grph w/Int Note: NOT ARINC 429!
Main ARINC 429
Configuration
SDI: LNAV 2 SDI2
Speed RX: Low
Speed TX: Low
VOR/LOC/GS
ARINC 429
Configuration SDI: VOR/ILS 2 SDI2

Sandel Avionics
SN3308 Navigation Display
Installation Manual
90106-IM-G(4) Installation Manual W SIG.doc Page 17
1.4.11 UPS GXXX RS232 INTERFACE
Starting with software 2.07, the SN3308 is able to take advantage of the
IIMorrow/UPSAT GX Series Extended Moving Map Data Output. This allows the
CDI, VDI and annunciator information to be received via the RS-232 serial line.
Configuration Notes:
GX Series Notes: In Setup, enable Extended MovMap Data Format
SN3308 Unit: Set LNAV selection to IIMorrow GX (RS-232 ENH)
Vertical deviation (if desired) requires the ILS input pin pulled low.
Testing The GX unit will not output RS-232 data in manual test mode
Upon power on, the GX will go through IFR Output Test Mode and the
following test can be observed:
CDI & Flags
VDI & Flags (if enabled on Sandel)
Annuciators
1.4.12 Pilot-Controlled Switches
Provision has been made for pilot controlled external switch closures (P2-22/14). We
suggest that this wiring be installed but capped and stowed, until the switch functions
are assigned in future versions of software. They may be used for remote map
functions in later versions of software, or for other remote selection functions.
1.4.13 Autopilot Interface
Course and heading datum outputs are provided. These can be selected to be AC or
DC in the Flight Control System (FCS) maintenance page and the direction sense of
these signals can be reversed as required.
A Back-course discrete output is provided for annunciation or AFCS reverse-course
control when required.
For older Century autopilots a Datum Excitation (5Khz) input is provided. However,
an external transformer coupler must be fabricated. See installation drawings.
1.4.14 Brightness Control
A separate brightness control only for the SN3308 must be installed externally. The
SN3308 does not have an internal photocell, so the pilot must be able to adjust the
dimming of the SN3308 separately from the other avionics. This control allows the
pilot to control the brightness of the display from 0% to 100% of normal brightness.

Sandel Avionics
SN3308 Navigation Display
Installation Manual
90106-IM-G(4) Installation Manual W SIG.doc Page 18
1.5 Disclaimer
Sandel Avionics does not assume any risk for nor accept any responsibility for the
interface descriptions contained within this Installation Manual. It is the responsibility
of the installer to ensure that such equipment is compatible with the SN3308 as
described, and to ensure that the installation of the SN3308 is accomplished with
such equipment using the specific equipment manufacturer’s installation and
technical instructions. No other representations are expressed herein.

Sandel Avionics
SN3308 Navigation Display
Installation Manual
90106-IM-G(4) Installation Manual W SIG.doc Page 19
2 Technical Information
2.1 General
The SN3308 is enclosed in an ARINC 408, 3ATI form factor enclosure and is
mounted to an instrument panel using a specially designed clamp tray fixture
containing provision for up to three captive D-Sub 37 pin connectors. A black bezel is
standard which accepts a cosmetic bezel mounting adapter for customization to an
appearance similar to a Bendix/King KI-525 series PNI.
The SN3308 operates on an input voltage from 11 to 33 Volts DC and requires 3.3
amperes of current at 11 Volts DC when the AMLCD display is operating at maximum
brightness. Also, 26 Volts AC, 400 Hertz reference excitation with a current
requirement of less than 1 milliampere is required when the functions of AC synchro
inputs or outputs are required for use with peripheral equipment. This reference
excitation must be obtained from the aircraft inverter source.
The following section describes the technical characteristics which include the
appliance approval basis, physical and electrical properties, electrical connector pin
allocation which details function and gradient or equipment protocol, and ARINC label
support. Also included is the description of the SN3308 installation components,
other equipment and installation requirements. A review of the installation approval
procedures is provided for filing with authorities.
2.2 SN3308 Approval, Physical, and Electrical Properties
2.2.1 Approval Data
Technical Standard Order: TSO-C113, “Airborne Multipurpose Electronic Displays”
Software Certification: RTCA/DO-178, Level C
Environmental Categories: RTCA/DO-160C: F1CANBMXXXXXXZBABBWA/ZXXX
RTCA/DO-160D: XXXXXXXXXXXXXXXXX(E/F-2)XX
2.2.2 Physical Dimensions
Form Factor: 3ATI (ARINC 408)
Width: 3.175 in. (8.04 cm.)
Height: 3.175 in. (8.04 cm.)
Length: 10.65 in. (26.24 cm.) overall, excluding knobs

Sandel Avionics
SN3308 Navigation Display
Installation Manual
90106-IM-G(4) Installation Manual W SIG.doc Page 20
Weight: 2.9 lbs. (7.5 Kg.)
CG: 5.1” from rear of bezel.
Clamp Tray: 3ATI x 10.4 in. - Sandel Avionics P/N 61013
Cooling Requirements: Internal fan requiring ambient air at fan input.
2.2.3 Operational Characteristics:
Temperature/Altitude: -20° C to +70° C - up to 55,000 F
Power Inputs: 11 to 33 VDC @ 3.2 Amperes Maximum (35 watts)
13.75 VDC @ 2.5 Amperes Nominal
27.5 VDC @ 1.5 Ampere Nominal
2.3 Interface Conventions
The SN3308 was designed to interface and operate with several generations of
avionics equipment. It is compatible with DC analog and/or ARINC standard synchro
and serial digital signals, as well as industry standard and adopted AC and DC sine,
cosine, and discrete input and output voltages. The SN3308 design and operation is
optimized for efficient adaptability to both new and existing avionics equipment and
systems.
The lists on the following pages reflect the configurable input and output signal types
for various equipment types. See “SETUP PROCEDURES” on page 41 for more
information on maintenance setup pages.