Sandel SN3308 Installation manual

SN3308 Navigation Display

Installation Manual

Document No. 90106-IM

Revision J

10-JUL-2008

SANDEL AVIONICS

2401 DOGWOOD WAY

VISTA, CA 92081

PHONE (760) 727-4900

FAX(760) 727-4899

WEBSITE WWW.SANDEL.COM

EMAIL [email protected]

90106-IM-J INSTALLATION MANUAL.DOC



Table Of Contents

1 GENERAL INFORMATION

1.1

Introduction

1.2

Equipment Description

1.2.1

Features

1.3

Installation Planning

9

9

10

1.4

Interface Planning

1.4.1

Compass System

1.4.2

GPS (Loran) Switching

1.4.3

GPS Annunciators

1.4.4

NAV Interface

1.4.5

Marker Beacon

1.4.6

Composite NAV and ADF

1.4.7

RESERVED FOR FUTURE USE

1.4.8

ARINC Channels and DME Interface

14

14

14

14

1.4.9

RS232 / RS422 Serial Communication 15

1.4.10

GARMIN GNS430 GPS/VOR/LOC Combination Receiver 16

11

11

12

13

13

Required SN3308 Setup Items

Required GARMIN GNS430 Setup Items, Receiver 1

17

17

Required GARMIN GNS430 Setup Items, Receiver 2

1.4.11

UPS GXXX RS232 INTERFACE

Configuration Notes:

1.5

1.4.12

Pilot-Controlled Switches

1.4.13

Autopilot Interface

1.4.14

Brightness Control

Disclaimer

17

18

18

18

18

18

19

9

9

2 TECHNICAL INFORMATION

2.1

General

2.2

SN3308 Approval, Physical, and Electrical Properties

2.2.1

Approval Data

2.2.2

Physical Dimensions

2.2.3

Operational Characteristics:

2.3

Interface Conventions

2.3.1

Connector P1

2.3.2

Connector P2

2.3.3

Connector P3

90106-IM-J Installation Manual.doc

20

20

20

20

20

21

21

22

23

24

Page 2

2.4

ARINC 419/429 Serial Data Receivers Interfaces

2.5

ARINC 419/429 Serial Transmitter Interfaces

2.6

Basic Component Part Number and Variants

2.7

Installation Kit And Accessories

2.8

Bill of Materials – SN3308 Install Kit

2.9

License Requirements

2.10

Technical Standard Order Stipulation

2.11

Installation and Operational Approval Procedures



3 INSTALLATION 29

3.1

General

3.1.1

Unpacking and Inspecting Equipment

3.2

Installation Considerations

3.2.1

General Considerations

3.2.2

Cooling Considerations

3.2.3

Mechanical Installation Considerations

3.2.4

Electrical Installation Considerations

3.3

Connector P-1 Pinout Description

3.4

Connector P-2 Pinout Descriptions

3.5

Connector P-3 Pinout Descriptions

35

39

29

29

29

29

29

29

30

32

25

26

26

26

27

27

27

27

4 SETUP PROCEDURES

4.1

General

4.2

Accessing The Maintenance Menus

4.3

Equipment/Configuration Selections

42

42

42

42

5 OPERATING DETAILS

6 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS

6.1

General

6.2

Projection Lamp Replacement Procedures

7 APPENDIX A: POST-INSTALLATION PROCEDURES

43

44

44

44

1

90106-IM-J Installation Manual.doc Page 3



8 APPENDIX B: ENVIRONMENTAL QUALIFICATION FORM 1

9 APPENDIX C: SAMPLE FAA FORM 337 1

10 APPENDIX D: SAMPLE AIRPLANE FLIGHT MANUAL SUPPLEMENT

11 APPENDIX E: CHECKOUT PROCEDURES

11.1

Functional Ground Test Procedures/Report

11.1.1

Introduction

11.1.2

Test Procedures and Results

11.1.3

Physical Installation

11.1.4

Wiring Verification and Initial Power-Up

11.1.5

System Configuration

11.1.6

System Functions

11.1.7

Compass System Interface

11.1.8

NAV Source Selection

11.1.9

BRG Source Selection

11.1.10

DME Selection

11.1.11

GPS Interface and Control

11.1.12

Marker Beacon Interface

11.1.13

Flight Control System Interface

11.1.14

Stormscope ® Interface

11.1.15

Additional Testing

11.2

EMI/RFI Test Procedures

11.2.1

Nav/Com Testing

11.2.2

General Testing

11.2.3

Additional Testing

11.3

Operational Flight Test Procedures/Report

11.4

Introduction

11.5

Test Procedures

11.5.1

Pre-Departure Operations

11.5.2

Enroute Operations

11.5.3

GPS Approach Operations

11.5.4

ILS Approach Operations

11.5.5

Additional Testing

12 APPENDIX F: LIST OF EFFECTIVE DRAWINGS AND ATTACHMENTS

1

1

10

10

10

11

8

9

9

9

5

6

6

7

3

4

4

4

1

3

3

3

12

14

14

14

15

15

16

16

1




Revision History

Revision Date

A 10 June 98 Initial release

B 11 July 98

Comments

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

D

E

F

8/31/98

9/20/98

12/10/98

5/26/99

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.

Far’s referenced in 337. Renamed flight manual supplement. Repaginated.

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.

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


G

G(2)

G(3)

G(4)

H

10/27/00

04/03/01

10/04/02

9/25/03

3/24/08



MP16: Relay Sense, new page.

MP17: SYS added info on inverter items

MP21: Updated Brightness

MP22-25: DVM pages added

MP26: Serial Diagnostics added.

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

Supplement in Appendix D

PC Applicable revision screen nomenclature

Incorporated A/R 360

1.4.7 Deleted ref to Radar Altimeter



P1-32 was triple conductor wire

P2-8 Deleted ref to Radar Altimeter




6.1 Lamp hours were 200

Appd’x A added Garmin GNS430 to LNAV-1 Select


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


Updated Appendix F, Drawings

Added King KDM 706 to Dwg 17 of 29

Added GNS530 to Drawing 25, 26, 27, 28, and 29


Sample Flight Manual Supplement revised.

Added drawing 90106-10 Rev. A (pp.30) “Heading

Repeater Gyro Flag Override”

Revised Ground test procedure for checking free gyro mode.


J 7/10/08




Sample Flight Manual Supplement revised.

Deleted drawing 90106-10 Rev. A (pp.30) “Heading

Repeater Gyro Flag Override”

Revised Ground test procedure for checking free gyro mode.


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:

• Horizontal Situation Indicator (HSI)

• DME Readout

• Marker Beacon Indicator

• WX-500 Stormscope® Display

• Long-Range Navigation (GPS or Loran) Map Display

• 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.




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:

• 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.

• 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.




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 42) 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 10

° C or 18° F. 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




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



Installation Manual 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 lowlevel 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


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



Installation Manual 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


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 is 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:




Required SN3308 Setup Items

Hardware

Software

Maintenance

Page Items

MOD1 STATUS OR LATER

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.

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

Relay Mode

ILS Lockout

DME:

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).

MASTER

OFF

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 ARINC 429

Configuration

VOR/LOC/GS

ARINC 429

Configuration

IN 1:

OUT:

Main 2.07 or later

Low, Sandel EHSI

Low, GAMA 429 Grph w/Int Note: NOT ARINC 429!

SDI1

Speed RX: Low

Speed TX: Low

SDI1

Required GARMIN GNS430 Setup Items, Receiver 2

Software

Main ARINC 429

Configuration

VOR/LOC/GS

ARINC 429

Configuration

IN 1:

OUT:

Main 2.07 or later

Low, Sandel EHSI

Low, GAMA 429 Grph w/Int Note: NOT ARINC 429!

SDI2

Speed RX: Low

Speed TX: Low

SDI2


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.


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.




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”

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




Weight: 2.9 lbs. (7.5 Kg.)

Clamp Tray: 3ATI x 10.4 in. - Sandel Avionics P/N 61013

Cooling Requirements: Internal fan requires ambient air at fan input.

2.2.3 Operational Characteristics:

Temperature/Altitude:

Power Inputs:

2.3 Interface Conventions

-20° C to +70° C - up to 55,000 F

11 to 33 VDC @ 3.2 Amperes Maximum (35 watts)

13.75 VDC @ 2.5 Amperes Nominal

27.5 VDC @ 1.5 Ampere Nominal

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 42 for more information on maintenance setup pages.


2.3.1 Connector P1



3

4

1

2

20

21

22

23

Display Primary Power Input

Display Primary Power Input

Clock Keep Alive Power

N/C (Key)

Display Power Return (Ground)

Display Power Return (Ground)

Signal Ground Return Input

DME Distance Analog LO Input

Note 1

Note 1

See Install Diagrams

Note 1

Note 1

5

7

24

25

26

DME Distance Analog HI Input

Flux Gate Z Input

Flux Gate Y Input 6

Flux Gate X Input

Flux Gate Excitation Input

Display Brightness

VHF NAV-2 ILS Energize Input 8

9

10

27

28

29

VHF NAV-1 ILS Energize Input

Directional Gyro Valid Input

OBS Resolver DC Reference Input for P1-13

VHF NAV 2 VOR Composite Input

VHF NAV 1 VOR Composite Input

KG 102 DG Stepper C Input

KG 102 DG Stepper A Input

DG Synchro Y Input

DG Synchro X Input

Note 2

Note 2

11

12

30

31

Note 3

Note 3

13

14

15

16

17

18

19

32

33

34

35

36

37

OBS Resolver H Input

OBS Resolver COS Output of P1-13

OBS Resolver SIN Output of P1-13

Glideslope –FLAG Input

Glideslope +FLAG Input

Glideslope +DOWN Deviation Input

Glideslope +UP Deviation Input

VOR +FROM Pointer Input

VOR +TO Pointer Input

VOR-LOC –FLAG Input

VOR-LOC +FLAG Input

VOR-LOC +LEFT Deviation Input

VOR-LOC +RIGHT Deviation Input

Note 1. Wire to both sets of power/ground connections. See installation drawings.

Note 2. 3 volt composite inputs require the use of a series resistor. See installation drawings.

Note 3: For XYZ inputs Z is signal ground P1-4.




2.3.2 Connector P2

15

16

13

14

17

11

12

9

10

18

19

5

6

7

8

3

4

1

2

24

25

22

23

28

29

26

27

30

31

20

21

34

35

32

33

Vert. Superflag Out

Lat. Superflag Out

Vert. Deviation Out

Reserved

Reserved

Reserved

Lat. Deviation Out

DME2 Hold/Analog DME Valid/DME1 Nav-2 Sense

Reserved

External Switch1 In

26VAC/400Hz Primary AC Excitation In

HDG/CRS Datum Excitation

Audio out

AFCS Back Course Discrete Output (Darlington)

Reserved

Heading Bootstrap Y Out

Heading Bootstrap X Out

Note 1

Note 1

Course Datum Output

Heading Datum Output

Reserved for Future Use Reserved

Reserved for Future Use

Spare Y Output

Spare X Output

DME-1 Hold In

Reserved

Note 1

Note 1

WPT Annunciator Input

MSG Annunciator Input

GPS Selected- In

ACT (Approach Active) Annunciator Input

ARM (Approach Arm) Annunciator Input

Reserved Reserved for Future Use

OBS-/LEG, HLD-/AUTO or PAR TRK- Annun. In

External Switch 2 In

Spare Input 1

Inner Marker Beacon Input

Middle Marker Beacon Input

Outer Marker Beacon Input

ADF-1 AC-Y or DC-COS Input Note 1

36

ADF-1 AC-X or DC-SIN Input

ADF-2 DC Ref or ADF-2 AC-Y Input

ADF-1 DC Ref or ADF-2 AC-X Input

Note 1

Note 1

Note 1

37 400Hz Diff. Resolver COS or ADF-2 DC COS

400Hz Diff. Resolver SIN or ADF-2 DC SIN

Note 1

Note 1

Note 1: For XYZ inputs Z is signal ground P1-4. For XYZ Outputs Z is power ground

P1-3/22.


2.3.3 Connector P3



8

9

6

7

3

4

5

1

2

10

11

20

21

22

23

24

25

26

27

28

29

Auxiliary Power Output

Spare1 Discrete Out (Darlington)

GPS OBS- or HOLD- Command Discrete Out (Darlington)

GPS-2 Switching Relay Discrete Out (Darlington)

Reserved

Reserved

GPS-1 Switching Relay Discrete Out (Darlington)



APPR ARM- Command Discrete Out (Darlington)

VHF NAV-2 Switching Relay Discrete Out (Darlington)

RESERVED FOR FUTURE USE

Reserved for Future Use

Reserved

Reserved

Reserved

DME-2 568-Clock / King Clock In

DME-2 568-Sync / King DME REQ / GPS-2 429-B

DME-2 568-Data / King Serial Data / GPS-2 429-A

DME-1 568-Clock / King Clock In

Reserved

PORT3

PORT3

DME-1 568-Sync / King DME REQ / NAV 429-B

DME-1 568-Data / King Serial Data / NAV 429-A

GPS-1 ARINC 429-B In

GPS-1 ARINC 429-A In

ARINC 429-B OUT

PORT2

PORT2

PORT1

PORT1

ARINC 429-A OUT

GPS-2 WX-500 RS-232 TX Output

GPS-1 RS-232 TX Output

GPS-2 WX-500 RS-422 TX- Output

12

30

31

13

14

15

16

17

18

19

32

33

34

35

36

37

GPS-2 WX-500 RS-422 TX+ Output

GPS-2 WX-500 RX 422- or 232 Signal Input

GPS-2 WX-500 RX 422+ or 232 Ground

GPS-1 RS-422 TX- Output

GPS-1 RS-422 TX+ Output

GPS-1 RX 422- or 232 Signal Input

GPS-1 RX 422+ or 232 GROUND

TTL Low Speed Data

TTL Low Speed Clk

RS-422 High Speed Clock-

RS-422 High Speed Clock+

RS-422 High Speed Data-

RS-422 High Speed Data+

Reserved

Reserved

Reserved

Reserved

Reserved

Reserved

Note: Darlington outputs serial numbers 2699 and below 35ma MAX. Serial numbers 2700 and above 250ma MAX.


2.4 ARINC 419/429 Serial Data Receivers Interfaces



The ARINC 419/429 serial data bus interface provides an information link between the SN3308 and peripheral avionics equipment. The bus conforms to 419/429 specifications for electrical characteristics, receiving, and transmission interval.

The SN3308 is capable of receiving the following low speed ARINC 419/429 longrange NAV, VHF NAV, GS or DME inputs for processing and display as follows:

034

074 Data Record Header

075 Active To/From Data

100

200

1000

100

50

BCD

BNR

DSC

BNR

114

115

116

Waypoint Bearing (True)

Cross Track Distance

121 Horizontal Command

147

173

174

222

252

261

Time-to-Go

50

50

50

50

1000

50

50

50

100

1000

BNR

BNR

BNR

BNR

BNR

BNR

BNR

BNR

BNR

DSC

275 Long-Range NAV Status 200

300 Mag. Station Decl, Wpt. Type, Class 100

303 Message Length, Type, Number 100

304

305

306

307

310

311

312

313

Message Characters 1-3

Message Characters 4-6

NAV Waypoint Latitude

NAV Waypoint Longitude

Present Position Latitude

Present Position Longitude

Track Angle (True)

100

100

100

100

100

100

50

50

DSC

BNR

BNR

BNR

BNR

BNR

BNR

BNR

BNR

BNR

BNR

BNR

BNR

314

320

Equipment Hex ID Code

50

50

321

326 Lateral Deviation Scale Factor

200

100

BCD

BNR

351 Distance-to-Destination (Flight Plan) 500 BNR

352 Time-to-Destination 500 BNR

371

377

1000

1000

DSC

BNR


2.5 ARINC 419/429 Serial Transmitter Interfaces



The SN3308 is capable of transmitting the following low-speed ARINC 419/429 data:

100G

320

(Using extended SDI)

2.6 Basic Component Part Number and Variants

The part number for the Sandel SN3308 is:

SN3308{X}-XX-XX

major minor bezel mounting

200

200

BNR

BNR

The “L”, “C”, and “R” variants signify the position in which the unit is to be mounted within one of the three predominate locations, i.e. Left instrument panel, Center panel, and Right instrument panel. The viewing properties of the display are optimized by the correct selection of part number.

Part number SN3308-00-BL [Black-Left] is the standard version of the SN3308.

“Minor variations” are reserved for future product enhancements or special applications.

The current version of software is displayed on the power-up screen.

2.7 Installation Kit And Accessories

90112 SN3308 installation kit

90124 Bezel Adapter Kit KI-525 Flush


2.8 Bill of Materials – SN3308 Install Kit



32001 Conn., D- 37 Pin Female

(part of 61013 tray assy)

3 ITT

32003 Connector, Female Pins D

32037 Conn., Jack, Phone

100

1

ITT 031-1007-073

Switchraft 14B

38058 Pot 10K

41020 Shrink Tubing 1/8” Black

1 1N4002

1 Clar. RV6NAYSA103AP

1”

1

1 60137 Knob Nut Cover 11mm

60138 Knob Cap, EHSI DIM

61013 Clamp Tray Fixture with hardware

1

1

1 90106-IM Installation Manual, SN3308

2.9 License Requirements

None.

2.10 Technical Standard Order Stipulation

The following stipulation as presented is required by the Federal Aviation Administration for articles approved under Technical Standard Order. This statement does not preclude multiple installation and operational approvals in regard to specific aircraft make, model, or type:

The conditions and tests required for TSO approval of this article are minimum performance standards. It is the responsibility of those desiring to install this article either on or within a specific type or class of aircraft to determine that the aircraft installation conditions are within TSO standards. If not within TSO standards, the article may be installed only if the applicant documents further evaluation for an acceptable installation and it is approved by the Administrator of the Federal Aviation

Administration or by other certifying agency.

2.11 Installation and Operational Approval Procedures

For the purpose of seeking installation approval, declarations should be made in the

“Description of Work Accomplished” section of a Federal Aviation Administration (FAA)

Form 337 or other field approval, or other limited supplemented type certification form.

A sample Form 337 is included in Appendix C. The basis of approval is for use as a primary navigation display for the functions of basic directional and navigational information. Moving map operations of the SN3308 is to be approved as supplemental means for VFR or IFR navigation, consistent with the approval of the long-range



Installation Manual navigation system. See appropriate FAA Advisory Circular (AC) or other guidance on

Loran-C, GPS, FMS, or INS for approval methods of such equipment. Applicable

Federal Aviation Regulations (FAR) must be adhered to.

Flight Standards Information Bulletin, FSAW 95-09( )(Amended), titled: “Electronic

Horizontal Situation Indicator (EHSI) Approvals” was originally published for the purpose of assisting Aviation Safety Inspectors with approval authority and methods for conducting a field approval for the SN3308. This FSIB describes the qualification of displays intended for use as essential, not critical, to preclude the need to conducting additional testing to substantiate immunity to high intensity radiated fields (HIRF) requirements. FSAW 95-09A has been superseded by a Flight Standards

Memorandum dated 11/10/1998, making the SN3308 eligible for follow-on approval. A copy of this memorandum has been attached in the Appendix F.

The Environmental Qualification Form for the SN3308 is included within this Installation

Manual, as Appendix B, and should be referenced to the categories appropriate to the aircraft type and environment into which the SN3308 is to be installed. The environmental category for the SN3308 should be stipulated on the FAA Form 337, or other approval form.

A “Functional Ground Test Procedures/Report” and an “Operational Flight Check

Procedures/Report” is also included as Appendix D, and should be used as a basis for validating the SN3308 equipment configuration and for verifying proper installation and functional performance. A copy of this form should be submitted along with the FAA

Form 337, or other approval or certification form. A permanent copy must be filed and maintained by the installing agency. Another copy must be presented to the aircraft owner for entry into the aircraft maintenance records, as well as a copy forwarded to

Sandel Avionics along with the Warranty Registration Form, Part Number 10129, to be filed after completion and installation acceptance. If any difficulty is experienced with the functionality or operational performance of the SN3308, contact Sandel Avionics for assistance.




3 Installation

3.1 General

This section provides general suggestions and information to consider before installing the SN3308 including interconnect diagrams, mounting dimensions and information pertaining to installation. Close adherence to these suggestions will assure optimum performance.

3.1.1 Unpacking and Inspecting Equipment

Exercise extreme care when unpacking the equipment. Make a visual inspection of the unit for evidence of damage incurred during shipment. If a claim for damage is to be made, save the shipping container to substantiate the claim. The claim should be promptly filed with the carrier. It would be advisable to retain the container and packaging material after all equipment has been removed in the event that equipment storage or reshipment should become necessary.

3.2 Installation Considerations

3.2.1 General Considerations

The SN3308 should be installed in accordance with standards established by the customer’s installing agency, and existing conditions as to unit location and type of installation. However, the following considerations should be heeded before installing the SN3308. Close adherence to these considerations will assure a more satisfactory performance from the equipment. The installing agency will supply and fabricate all external cables. The connectors and associated hardware required are supplied by Sandel Avionics.

3.2.2 Cooling Considerations

The SN3308 Navigation Display contains its own ventilation fan for internal component cooling and therefore, does not require a forced air cooling system.

However, it is extremely important that the mounting area below the Clamp Tray

Fixture opening and the adjacent area above the SN3308 when inserted be kept clear of any objects which would restrict the inflow of air at cabin ambient temperature. In a helicopter installation where the entire installation is shrouded ambient air must be provided to the cooling fan inlet area. Cooling can be verified in the post-installation checkout by monitoring the temperature on the System maintenance page.

3.2.3 Mechanical Installation Considerations

The SN3308 installation should conform to customer requirements and airworthiness standards affecting the location and type of installation. §25.1321(a) stipulates that:




“Each flight, navigation, and powerplant instrument for use by any pilot must be plainly visible to him from his station with the minimum practicable deviation from his normal position and line of vision when he is looking forward along the flight path.”

§ 25.1321(b) stipulates: “The flight instruments required by § 25.1303 must be grouped on the instrument panel and centered as nearly as practicable about the vertical plane of the pilot’s forward vision.” In addition - § 25.1321(b)(4) states: “The instrument that most effectively indicates direction of flight must be adjacent to and directly below the instrument in the top center position.” Similar regulations apply to

FAR Part 29 Transport Category Rotorcraft and to Part 23 Small Airplanes.

Refer to Sandel Avionics, Drawing No. 90106-07-( ) titled, “Layout - SN3308

Installation” for specific assembly and mounting instructions.

The chassis has four #4 holes with nut plates at the rear on both sides for purpose of mounting customer supplied harness strain relief. The strain relief may be attached to the rear of the tray utilizing an adel clamp mounted to the side of the chassis or with an adel clamp and a bracket for strain relief of the harness.

3.2.4 Electrical Installation Considerations

Connections and functions of the SN3308 are described in this section. Refer to the

SN3308 Interconnect Wiring Diagrams for detailed wiring information and appropriate notes. Refer to the Functional Pinout Descriptions for explanations of pin functions.

A. The installing agency will supply and fabricate all wiring harnesses. The length and routing of wires must be carefully measured and planned before the actual installation is attempted. Avoid sharp bends in the harness or locating the harness near aircraft controls. Observe all recommended wire sizes and types and subscribe to appropriate FAR Parts 23, 25, 27, and 29, as well as AC 43.13-1( ) and -2( ).

B. The use of MIL-C-27500 shielded wire and MIL-W-22759 single conductor wire is recommended. The use of ferrules or grounding blocks for signal ground and digital ground returns is satisfactory; however, each ground return must be electrically separated.

C. When an existing installation of a navigation source selection relay unit is installed to provide mode control switching and annunciation for a GPS or other long-range navigation system, the SN3308 may not perform these functions simultaneously. This does not preclude the SN3308 from annunciating such mode control functions.

D. In order to ensure optimum performance the SN3308 and associated wiring must be kept at least a minimum of three feet from high noise sources and not routed with cables from high power sources.




E. Prior to installing the SN3308, a point-to-point continuity check of the wiring harness should be accomplished to verify proper wiring. See Appendix D,

FUNCTIONAL GROUND TEST PROCEDURES/REPORT for verification of this step and other checks.

F. The Functional Pinout Descriptions on the following pages will assist you in determining installation requirements. Adhere to all notes within these

descriptions and on installation wiring diagrams.

G. Special caution must be taken to observe 30 Hz OBS resolver connections in order to prevent possible damage to the installed VOR/localizer converter.

See Installation Wiring Diagrams and the MAINTENANCE MENU,

Configuration Instructions for notes pertaining to these considerations.

H. Ground Bonding. In order to assure installation characteristics match the

DO-160 RF and Lightning test conditions, ensure that two ground wires of at least the recommended size are installed in accordance with the installation drawings and these wires are connected to a bonded aircraft ground. Ensure that shielded wiring is used to the Flux Gate (if installed), Gyro Reference, and

Gyro XYZ (if installed).

I. Power Wiring. To assure that the SN3308 will operate properly down to its rated minimum input voltage of 11Vdc, ensure that two power wires of at least the recommended size are connected from the EHSI circuit breaker to the

SN3308 in accordance with the installation drawings.


3.3 Connector P-1 Pinout Description



P1-1, P1-20: Display Primary Power Input

P1-2: Keep alive power

Pins 1 and 20 are the aircraft DC power input (11-33VDC). Connection to both pins is required using two 20AWG wires and a 5 ampere circuit breaker.

Maximum power required is 35 watts when the SN3308 is operating at maximum brightness. Connection to the Avionics bus is recommended to reduce voltage fluctuations during engine start.

Pin 2 is keep alive power. Connection to this pin is not required, but a voltage over 6.5VDC on this pin when the main power falls below 11VDC will reduce the re-boot time of the SN3308 after a power interruption to approximately 1.5 seconds instead of the typical 6 seconds for power interruptions under two minutes.

For all serial numbers the supply current on this pin may be as much as 20 milliamperes at extremes in ambient temperature so this pin should be connected to the main power bus not the battery bus.

P1-3, P1-22: Display Power Return Input

Pins 3 and 22 are the aircraft ground input connections. Connection to both pins is required using two 20 AWG wires. Either pin should also be used for the digital signal ground (shields) return, as required. The number of shields will vary depending upon the functions wired to Connector P3.

P1-4: Signal Ground Return Input

This common Signal Ground Return is used for analog signal grounds such as the Z lead of synchros, and analog signal shield grounds. See the installation wiring diagrams for details. Do not use this pin to connect digital signal ground return shields or use this for power ground return. Otherwise damage to the unit will occur.

P1-5: DME Distance Analog HI Input

P1-23: DME Distance Analog LO Input

This differential input is for connection with DME equipment furnishing 40 mVDC/nm. The maximum displayed distance is 200 nm. or 8 VDC. 24 AWG twisted shielded pair wire is recommended for this function. This input is associated with P2-3 “Analog DME Valid”.




P1-6: Flux Gate Y Input

P1-24: Flux Gate Z Input

P1-25: Flux Gate X Input

Connections to these pins are made directly from the heading system flux gate if internal slaving is selected on the compass maintenance page. If a

Bendix/King KI-525 PNI or Rockwell/Collins 331A-3( ) HSI is being removed, the respective slaving accessory, should be bypassed. See the installation drawings for details. 24 AWG twisted shielded triple conductor is recommended for these signals.

P1-7: Flux Gate Excitation Input

This connection is made to the 400 Hz AC flux gate excitation source voltage. a 24 AWG shielded wire is recommended for this function. Note: the phase of this excitation voltage is not required to be the same as that supplied to the

Primary AC Excitation input on P2-4, if used.

P1-26: Display Brightness

Input from the pilots display brightness control. 0Vdc – Acft. Power

P1-8: VHF Nav-2 ILS Energize Input

P1-27: VHF Nav-1 ILS Energize Input

These pins control the enabling of the Glideslope pointer. They are not related to the bearing pointer operation.

These signals also control the ILS Lockout logic so the SN3308 can sense when a GPS receiver is inappropriately selected as the primary nav source when ILS Lockout is not disabled on the NAV maintenance page.

Connections to these pins are from the respective VHF navigation receiver and optionally by the GPS receiver. The logic level of these inputs are selected on the NAV maintenance page, and are normally active-low.

NOTE: If ILS Lockout is disabled, NAV1/GPS1 vertical guidance is enabled by P1-27 and NAV2/GPS2 vertical guidance is enabled by P1-8.

NOTE: The ILS Energize inputs are pulled up to one-half aircraft power. In 12 volt aircraft this will make logic high 6Vdc. This many not be satisfactory as the non-energized state of an associated NAV converter or indicator. To increase the inactive high voltage, a 4.7K pullup resistor to aircraft power may be used externally to the SN3308 for 12v aircraft.

P1-9: Directional Gyro Valid Input

Connect to the (DG) valid output if available. Selection of the logic level of this pin is in the Compass maintenance page.

P1-10: VHF Nav 2 VOR Composite Input

P1-29: VHF Nav 1 VOR Composite Input




These pins supply bearing to the VOR bearing pointers. Connection to these pins is from the respective VHF navigation receiver and is normally .5v

ARINC. For 3V inputs a series resistor is required, see the installation drawings. Calibration, including 0° or 180° phase angles for inverted inputs, is in the NAV maintenance page. 24 AWG shielded wire is recommended for these connections.

P1-11: KG 102 DG Stepper C Input

P1-30: KG 102 DG Stepper A Input

These quadrature DC inputs are used exclusively for connections to the

Bendix/King KG-102 series Directional Gyro when selected in the Compass maintenance page. For slaved operation see descriptions of pin-6, pin-7, pin-

24, pin-25. 24 AWG twisted shielded pair wire is recommended for this connection.

P1-12: DG Synchro Y input

P1-31: DG Synchro X input

Connect these pins to an XYZ type directional gyro, ground the Z leg to signal ground P1-4. This input is referenced to the 26VAC/400Hz reference on P2-4.

This function is selected on the Compass maintenance page.

P1-13: OBS Resolver H Input

P1-28: OBS Resolver DC ref Input

P1-14: OBS Resolver SIN Output

P1-32: OBS Resolver COS Output

OBS resolver connections for NAV or GPS receivers. The input frequency range is 20Hz to 500Hz, and calibration is done on the NAV maintenance page. The resolver is electrically zeroed at zero degrees plus the calibration value in the NAV maintenance page. For normal use this calibration value will be –60 degrees (equaling 300 degrees electrical zero). This is the factory default. A different calibration value setting is used for each possible NAV source selectable on the SN3308. 24 AWG twisted shielded pair conductor is recommended for these functions. Please see the warnings on the installation drawings concerning the connection to P1-28.

P1-15: Glideslope +FLAG

P1-33: Glideslope -FLAG

Low level GS receiver flag inputs. Superflags can be supported with a series resistor, see the installation drawings.

P1-16: Glideslope +UP Deviation Input

P1-34: Glideslope +DOWN Deviation Input

GS deviation input. Two-dot deflection is

±150 mVDC. Note that a 24 AWG twisted shielded pair wire is recommended for these functions.

P1-17: VOR +TO Pointer Input

P1-35: VOR +FROM Pointer Input




Differential input supports VHF NAV or long-range navigation +TO pointer and

+FROM pointer outputs. In-view is greater than 40 mVDC (to) and –40mVDC

(from). Note that a 24 AWG twisted shielded pair wire is recommended functions.

P1-18: VOR-LOC +FLAG

P1-36: VOR-LOC -FLAG

Differential Low level Nav Flag inputs. Superflags are supported with a series resistor, see the installation drawings. Flag out of view requires greater than

215 mVDC on +FLAG with respect to -FLAG input. 24 AWG twisted shielded pair wire is recommended for these functions.

P1-19: VOR-LOC +RIGHT Deviation Input

P1-37: VOR-LOC +LEFT Deviation Input

Analog lateral deviation from the VHF navigation receiver or long-range navigation receiver +LEFT and +RIGHT deviation outputs. Two-dot deflection is

±150 mVDC. 24 AWG twisted shielded pair wire is recommended for these functions.

3.4 Connector P-2 Pinout Descriptions

P2-1: Vertical Superflag Output

Reserved for future use.

P2-20: Lateral Superflag Output


P2-2: Vertical Deviation Output


P2-21: Lateral Deviation Output


P2-3: DME-2 HOLD / Analog DME Valid / DME-1 Nav-2 Sense

Multi-function pin setup on the DME setup page. When an analog DME is used this must be used as Analog DME Valid.

P2-22: External Switch 1 In

Used for pilot controlled switching. This has no function in current software version but it is recommended that wiring to a yoke switch be reserved for future functions.

P2-4: Primary AC Excitation Input

Connection to this pin is required only if functions of ARINC 407 synchro or

400Hz AC sine and cosine inputs or outputs are used. The input requirements are 26VAC nominal 400Hz. Input frequency is 440 Hz.




Maximum and 360 Hz. minimum. Input impedance is 220K

Ω. 24 AWG shielded wire is recommended for this function.

P2-23: Hdg/Crs Datum Excitation

This is a 5Khz ground referenced excitation input which is associated with the

HDG Datum and CRS Datum outputs. It is intended for use with older

Century autopilots and can potentially eliminate the need for a King KA52 autopilot adapter to be used. Contact Sandel for details of the use of this pin.

It must be externally transformer isolated.

P2-5: Audio Out


P2-24: AFCS Back Course Discrete Output (DARLINGTON)

Used to feed the back course sensing input of an AFCS. When the Course

Select rotates either direction passing 90º clockwise or counterclockwise from the lubber line of the SN3308 will generate a darlington closure. An external relay is be required to make this signal active-high.

P2-6: HDG Bootstrap Y out

P2-25: HDG Bootstrap X out

Z is Ground. This function may be used to provide “bootstrap” output to an

RMI or other directional instrument in the form of ARINC 407 synchro 24 AWG twisted shielded pair wire is recommended for these functions. Drive only electronic loads with this output – limited to 60ma max.

P2-7: Course Datum Output

P2-26: Heading Datum Output

These function are either AC or DC Course Datum and Heading Datum for the flight control system. Selection of AC/DC, gain, and direction of rotation are accomplished on the FCS maintenance page. 24 AWG single conductor shielded wire is recommended for each of these functions.

P2-8: Reserved for Future Use


P2-9: Spare Y Output

P2-28: Spare X Output

XY (Z ground) output reserved for future use.

P2-10: DME-1 Hold Input

DME-1 Hold annunciator input.

P2-11: MSG Annunciator input

P2-12: ACT (Approach Active) Annunciator Input

P2-29: WPT Annunciator input

P2-31: ARM (Approach Arm) Annunciator Input

Active-low inputs for GPS/LRN on-screen annunciators.




P2-30: GPS SELECTED Input

This input is used when the SN3308 is set up for slave mode so an external

GPS switch can be used to switch to an external GPS receiver. Causes proper mode switching and annunciation on the SN3308 display. This input is active only when enabled in the System maintenance page.


P2-32: OBS-/LEG, HLD-/AUTO or PAR TRK- Annunciator Input

For selected GPS-1 receiver with OBS/LEG mode (or HOLD/AUTO), this input when low senses and annunciates OBS or HOLD on the SN3308 display and changes the mode of the course pointer from auto-slew to manual control.

Otherwise, this is used as a PAR TRK input for other types of receivers, based on the selection in the LNAV maintenance page.

P2-14: External Switch 2 In.

See P2-22.

P2-33: Spare Input 1


P2-15: Inner Marker Beacon Input

P2-16: Outer Marker Beacon Input

P2-34: Middle Marker Beacon Input

Marker beacon receiver inputs. Normally connected to the external lamp drivers on the marker beacon receiver, see the installation drawings. Most marker beacon receivers use “DC” ground referenced outputs driven by transistor drivers. All such receivers are compatible as shown on the installation drawings. Some very old designs may use transformer outputs which are AC coupled. In such an instance call Sandel for installation guidance.

P2-17: ADF-1 AC-X or DC-SIN Input

P2-35: ADF-1 AC-Y or DC-COS Input

Inputs from ADF-1 Receiver. Selection of AC/DC operation is on the ADF maintenance page. For DC use P2-18 as the DC reference input. For AC inputs Z is grounded. 24 AWG twisted shielded pair wire is recommended for these functions.

P2-18: ADF-2 AC-X or ADF-1 DC Ref

P2-36: ADF-2 AC-Y or ADF-2 DC Ref

Used as DC REF inputs when DC Sin/Cos ADF is used as ADF-1 or ADF-2.

Used as AC X/Y if ADF-2 is AC. The DC function is activated when ADF-1 is selected as a DC receiver in the ADF-1 maintenance page. For AC inputs Z is grounded.

P2-19: ADF-2 DC-SIN or 400Hz Diff. Resolver SIN

P2-37: ADF-2 DC-COS or 400Hz Diff. Resolver COS




The selection of the function for these inputs is in the ADF-2 Maintenance

Page and the NAV maintenance page. When 400Hz differential resolver operation is required ADF-2 operation cannot be used. For AC inputs Z is grounded. 24 AWG twisted shielded pair wire is recommended for these functions.




3.5 Connector P-3 Pinout Descriptions

P3-1: Auxiliary Power Output

This output is filtered DC which is nearly the same as the DC potential supplied to the SN3308 but is restricted to 250 ma loads. It is provided to support future accessories.

P3-20: Spare1 Discrete Out (DARLINGTON)


P3-2: GPS OBS- or HOLD- Command Discrete Output (DARLINGTON)

Open Collector active-low output used to operate the OBS function of

Bendix/King KLN-90 GPS receivers or the HOLD function of the II Morrow and

Garmin GPS receivers. Accessible during normal use from the pilots GPS

MODE soft key.

P3-21: GPS-2 Switching Relay Discrete Output (DARLINGTON)

Can be used to operate a switching relay whenever GPS-2 (or Loran-2) is selected by the NAV pushbutton. The receiver type is selected on the LNAV-2 maintenance page.

P3-3: GPS-1 Switching Relay Discrete Output (DARLINGTON)

Can be used to operate a switching relay whenever GPS-1 (or Loran-1) is selected by the NAV pushbutton. The receiver type is selected on the LNAV-1 maintenance page.

P3-22: Spare2 Discrete Out (DARLINGTON)


P3-4: Spare 3 Discrete Output (DARLINGTON)


P3-23: GPS APPR ARM Discrete Output (DARLINGTON)

Open Collector active-low output used to select APPR ARM mode of the external GPS receiver. Accessible during normal use from the pilots SHFT-

NAV operation.

P3-5: VHF NAV-2 Switching Relay Discrete Output (DARLINGTON)

Can be used to operate a switching relay whenever VHF NAV-2 is selected by the NAV pushbutton. VHF NAV-2 is enabled on the NAV-2 maintenance page.



P3-26: Ch3 ARINC 429-A / 568 Data / King Serial Data

P3-7: Ch3 ARINC 429-B / 568 / King DME -REQ Input

P3-25: Ch3 ARINC 568 DME Sync / KING Serial Clock Input




P3-9: Ch2 ARINC 429-A / 568 Data / King Serial Data

P3-27 Ch2 ARINC 429-B / 568 / King DME-REQ Input

P3-8: Ch2 ARINC 568 DME Sync / KING Serial Clock Input

Serial data inputs for either ARINC 429 / 568 serial protocols to support

ARINC DME’s as selected within the DME Maintenance page (Low speed only), Bendix/King DME’s using King Serial Digital protocol, or long range navigation receivers. See the installation drawings. 24 AWG twisted shielded triple conductor is required for these functions.

P3-10: Ch1 ARINC 429-A Input

P3-28: Ch1 ARINC 429-B Input

Used to support ARINC 429 long range navigation receivers as selected in the

LNAV maintenance pages. 24 AWG twisted shielded pair wire is required for these functions.

P3-11: ARINC 429-A Output

P3-29: ARINC 429-B Output

Low speed ARINC 429 output which transmits selected course and selected heading for ARINC 429 Long Range NAV receivers. 24 AWG twisted shielded pair wire is required for these functions.

P3-12: Ch1 RS-232 TX Output

P3-30: Ch2 RS-232 TX Output

RS-232 serial data outputs. TXD-2 is used to communicate with WX-500

Stormscope® when connected to RXD-2 and is also used for program uploads from an external PC. TXD-1 is normally not used. Note that a 24

AWG shielded wire is required for each of these functions.

P3-13: Ch2 RS-422 TX+ Output

P3-31: Ch2 RS-422 TX- Output

P3-15: Ch1 RS-422 TX+ Output

P3-33: Ch1 RS-422 TX- Output

RS422 outputs with the same data as RS232 TXD1 and TXD2. Reserved for future use.

P3-14: Ch2 RS-422+ In or RS-232 Ground

P3-32: Ch2 RS-422- In or RS-232 Signal

P3-16: Ch1 RS-422+ In or RS-232 Ground

P3-34: Ch1 RS-422- In or RS-232 Signal

These inputs are used to connect to Long Range Navigation receivers selected in the LNAV maintenance pages. See the installation drawings. Ch2 is used to communicate with the WX-500 Stormscope®.

P3-17:TTL Low Speed Clock

P3-35: TTL Low Speed Data



P3-18: High Speed Clock+

P3-36: High Speed Clock-

P3-19: High Speed Data+

P3-37: High Speed Data-







4 Setup Procedures

4.1 General

Setup procedures for the SN3308 are described along with the Maintenance Menu below. The Maintenance Menu is accessed and addressed through the use of pushbuttons and the Selected Heading knob. No external connector pin programming is required.

4.2 Accessing The Maintenance Menus

To access the Maintenance Menus perform the following operations:

A. Prior to applying power to the SN3308, depress and hold the SHFT and the A-

B pushbuttons, then apply power to the unit. Continue to hold until the first maintenance menu appears. This protocol insures than maintenance menus cannot be called up accidentally during flight.

B. Once the Maintenance Menu is entered, press the NEXT or LAST softkeys to cycle the MAINTENANCE MENU pages. Use the UP/DOWN arrow keys for selections, and rotate the right knob to adjust and select. On some menus additional soft key legends will appear as prompts.

C. Escape the maintenance menus by pressing the 360 softkey. This will allow normal operation of the unit to test the effects of settings. Re-enter the maintenance pages by the sequence SHFT-MAINT softkey. (Note that this softkey does not appear during normal operation, only after step “A” has been accomplished).

D. To disable maintenance menu operation, power down and restart normally.

All configured items will be stored in non-volatile memory.

4.3 Equipment/Configuration Selections

The choices of compatible equipment contained in the SN3308 menus are listed in Appendix A. For types not listed, consult the factory.




5 Operating Details

For an explanation of the operating controls of the SN3308, refer to the Pilot’s Guide for the SN3308, Sandel Avionics P/N 90106-PG, or to the Airplane Flight Manual

Supplement.


6 Instructions For Continued Airworthiness



6.1 General

The following is a summary of the Instructions for Continued Airworthiness prepared under the guidelines of FAA Advisory Circulars 23.1309-1( ) and 25.1309-1( ) which identifies potential failure modes of the Sandel Avionics Model SN3308 Navigation

Display. The assumption made is that all functions of the SN3308 will be used in an essential (primary) navigation function.

The SN3308 employ a halogen lamp as the singular primary display projection light source. Lamp power is not supplied by a redundant power source. Display lamp life will vary upon the brightness level used to view the display and accumulative age and gradual degradation is likely to occur. Therefore, it is considered that a malfunction will prevent continued use. This failure condition is likely to be an inoperative display.

Sandel recommends the following practice:

Projection lamp failure within the SN3308 is considered similar to the failure of a compass card servo mechanism of an electromagnetic horizontal situation indicator or a CRT or power supply failure within an electronic horizontal situation indicator. Sandel Avionics will demonstrate through service experience that the projection lamp will function beyond

225 hours at full brightness. However, because of its currently predicted life, maintenance personnel are advised to replace the lamp as a precautionary measure within the first 225 hours and every 225 hours thereafter, or calendar 1 year, whichever comes first. This maintenance action will prevent probable failures of the SN3308 functionality and thus meet the safety objectives.

Installers of the SN3308 are advised to take maintenance actions as required to comply with Instructions for Continued Airworthiness in accordance with the Federal Aviation Regulations, or other requirements.

Flight crews and ground maintenance personnel should periodically assess the lamp life and replace the lamp if required. The appropriate maintenance entry must be documented in the aircraft maintenance records. Sandel Avionics requests a copy of the maintenance record of every replacement so that reliability of the display lamp can be tracked.

6.2 Projection Lamp Replacement Procedures

The following tools will be required to remove and replace the SN3308 projection lamp:

1 ea. Phillips Screwdriver, #0 point






1 ea. Allen Key, 7/64”

1ea. ¼” Nut Driver

1ea Sandel Lamp Replacement Kit (90122)

To remove the SN3308 loosen the top two 8-32 screws above the SN3308 to remove tension from the clamp tray. Then remove the single size 8-32 screw at the lower-left of the SN3308. Insert a 7/64” Allen key into this hole approximately ¾” and you will engage a removal jackscrew. This jackscrew is used to assist in removing the

SN3308 but cannot extract the SN3308 alone. Rotate the jack screw clockwise while simultaneously pulling on the front bezel of the SN3308 to provide additional extraction force. Continue to assist the jackscrew in this manner turn ½ a turn at a time. If you have difficulty in removing the SN3308 the upper two clamp screws may not have been loosened sufficiently. DO NOT apply excessive torque on the jackscrew at any time.

Place the SN3308 unit firmly on a clean table or work bench. Carefully remove the two each, 2-56 screws from the top of the bezel using the #0 screwdriver Remove the four 4-40 x ¼” flat-head Phillips screws at the top of both sides of the main enclosure chassis using the #1 screwdriver and the single (encircled) 4-40 taper pin at the top of the rear connector plate. Once removed, carefully lift the top cover from the chassis by lifting up at the rear and pulling slowly backwards.

You will clearly see the projection lamp at the rear top of the unit. Press tubing from the lamp kit firmly over the lamp and pull lamp straight out. Retain the defective lamp for return to the SN3308 owner for their disposition.




Remove the new projection lamp from its box but do not touch the new lamp glass envelope with bare fingers. Instead, touch the lamp using supplied finger cots or the lamps plastic bag. Slide the lamp out far enough to expose the leads. It is permissible to touch the leads of the lamp. Use the rubber tubing in such a manner that will enable you to guide the lamp leads into the lamp socket. Once the leads are in the socket holes apply downward force to the top of the lamp envelope (touching only with the plastic shipping bag or finger cots) and seat the lamp into the socket until it stops. Move the lamp fore-and-aft slightly to seat it in position. Please note that the seated position of the lamp is approximately 10 degrees from vertical. The filament of the lamp will line up with two small V notches in the two sides of the lamp housing, which can be used as a visual reference.

Reinstall the top cover using the original screws and taper pin. Do not apply excessive torque on the small 2-56 screws in the upper bezel.

Either with an appropriate bench harness to apply power or by reinserting the unit into the clamp tray apply power to confirm operation of the replacement lamp and verify proper operation.

Changing the projection lamp requires re-initializing the system’s internal lamp-test data. This is accomplished by holding both LAMP and CHG softkeys simultaneously in Maintenance Page 21. Initiating a Lamp Change cycle will store the prior lamp operational data for reference and reset current measurement values to zero. (See

Maintenance Page 21).

This operation must be performed when the input power is at normal level – either

13.75v or 27.5v. Do not perform this procedure unless the input power is either

13.75v or 27.5v.




If your unit and chassis combination matches Figures A and B below follow

Step A if your unit and chassis combination does not match Figures A and B follow Step B to reinstall the unit.

TRAY HAS PART NUMBER

AND REVISION “G” OR

HIGHER STAMPED IN THIS

AREA

Figure A

JACKSCREW BEHIND

MOUNTING SCREW

UNIT CHASSIS HAS A

CUTOUT AT THIS

LOCATION

TIGHTEN FIRST

Figure B

STEP A Reinstall the SN3308. Tighten the bottom right mounting screw in the panel. Insert a 7/64” Allen key into the lower left mounting hole approximately ¾” and you will engage a jackscrew. Rotate the jackscrew fully clockwise until finger tight.

Insert the SN3308 in the clamp tray, continue rotating the jackscrew counterclockwise until the SN3308 is fully engaged in the tray connectors. Reinstall the single size 8-32 screw in the lower-left of the SN3308. Tighten the two upper screws.

STEP B Rotate the jack screw fully counter-clockwise to return the ejector mechanism to its initial position, otherwise the SN3308 will not seat in its connectors on re-installation. Reinstall the SN3308. Insert the SN3308 in the clamptray, and fully tighten the two bottom screws in the panel. Make absolutely sure the SN3308 is fully engaged in its tray connectors, and tighten the two upper screws. Do this while continuing to apply a slight force on the SN3308 bezel to keep the unit fully engaged with its connectors.




Retest by verifying proper operation of the SN3308 and all associated avionics equipment. Enter the change of the projection lamp, and inspection and test record into the aircraft maintenance records and present a copy of the description of work accomplished to the aircraft owner or operator.

Calibration: To calibrate the newly installed lamp, see the procedure in the postinstallation checkout procedure for “Page 21 Brightness”.


7 Appendix A: Post-Installation Procedures



After all wiring has been verified and the SN3308 has been installed into the panel, the maintenance pages must be accessed to properly configure the SN3308 for the installed equipment. Prior to applying power to the SN3308, depress and hold the

SHFT and the A-B pushbuttons, then apply power to the unit. Continue to hold until the first maintenance menu appears. This protocol insures than maintenance menus cannot be called up accidentally during flight.

Once the Maintenance Menu is entered, press the NEXT or LAST softkeys to cycle the MAINTENANCE MENU pages. Use the UP/DOWN arrow keys for selections, and rotate the right knob to adjust and select. On some menus additional soft key legends will appear as prompts.

Escape the maintenance menus by pressing NEXT repeatedly to step through any remaining maintenance pages until the normal 360-degree view is displayed. This will allow normal operation of the unit to test the effects of settings. Re-enter the maintenance pages by pressing VUE to switch to ARC mode, and then again to access the first maintenance page.

To disable maintenance menu operation, power down and restart normally. All configured items will be stored in non-volatile memory.

Each maintenance page, the options for each, and a brief description of each option are detailed below:

2: COMPASS SYSTEM

GYRO TYPE >

GYRO VALID

KG-102

P1 – 9 LOW

SLAVING NO

Gyro Type: Selects KG102, XYZ NORM, XYZ –180, 429 PORT 1 , 429

PORT 2 OR 429 PORT 3.

Gyro Valid: Selects presence of Gyro Valid signal from Gyro; either disabled, active-high, or active-low.

90106-IM-J Installation Manual.doc Appendix-A Page 1



Turns slaving On and Off. When turned on, the following additional Slaving: information will display:

Cont’d

.

.

.

.

FLUX GATE KMT-112

QUADRANT

(ITEM)

(CALIBRATION)

FG X SIG

FG Y SIG

EXC. LOCK

EXC. VALID

XXX

YYY

00

00

Notes:

Use

↑ and ↓ to select the item and the HDG control knob to adjust.

When a flux gate is first selected the Quadrant and Peaking adjustments will automatically preset.

Upon power-up, the flux gate should show a heading (on page-3) which is within

±20° of true heading (prior to calibration) and the compass card on page

3 should turn in the correct direction as the aircraft turns or the fluxgate is turned manually. If this is not the case, the following troubleshooting procedure can be used to diagnose fluxgate problems.

It is sometimes difficult to determine wiring errors because it is difficult to determine the correct fluxgate terminals which actually represent XYZ since this information may not be supplied with the fluxgate. The following procedure can be used to make this determination. a) Align the aircraft to North. Turn the system on and step the “quadrant” adjustment to align the SN3308 display to North

±20°. (Ensure the adjustments on Page-3 are set to zero). If you can’t get closer than 30 or 40 degrees, your “xyz” may actually be “yzx” or “zxy”. Take all three wires off the fluxgate and move them one terminal “clockwise” and try again. You may have to do this a second time. Once the system achieves correct “North” seeking, the “Z” terminal has been correctly identified and should not be changed.




Note: When installing to existing wiring, ensure that the fluxgate center tap which exists on some Honeywell (Sperry) and Collins fluxgates is not connected. b) Ensure the compass card rotation is correct by observing that the displayed heading increases/decreases properly as the aircraft heading is changed or the fluxgate is rotated by hand. If increasing the heading of the fluxgate yields

decreasing heading card indication, reverse the X/Y leads. This will not affect

North as identified in step ‘a’ above. c) Proceed to the calibration adjustment.

Use of Signal indicators (with Quadrant set to 0):

300

° X=100-250 Y=0

0

°

X =150-350 Y=identical but opposite to X.

60

° X=0

Y=100-200

These readings are informational and approximate. The maximum X/Y signal is dependent on the fluxgate and is not critical as long as it falls within the above ranges.

Use of Peaking adjustment:

At a heading of North where X and Y are numerically equal but opposite, changing the Peaking adjustment should not allow increasing the X or Y level more than 10%. This does not normally require adjustment but can be used to verify proper operation. The larger ARINC style Sperry, Honeywell, Collins fluxgates use setting “0”, and the smaller King, STEC (Humphrey) fluxgates use setting “6”.

Use of Excitation Lock indicators:

The EXC LOCK indicator shows the lock status of the internal fluxgate demodulator and is shown for troubleshooting. When in normal operation, the

EXC LOCK will be a low number, ‘00’ being closer to perfect lock. Any number 30 or above is considered out of lock and will after a three second timeout cause a “Fluxgate Failed” error message to the pilot. If no fluxgate excitation is present at all, the value will be ‘77’. It is normal for this number to flicker from zero to a non-zero number during operation, and will depend on the inverter/gyro used.

EXC VALID is the counter which counts up to 30 (three seconds) to trigger the

“Fluxgate Failed” error message to the pilot. If in the failed state the word

“INVALID” will show on the maintenance page.




3: COMPASS

CALIBRATION

North: > 0.00

°

East:

South:

West:

0.00

°

0.00

°

0.00

°

Instructions: Use the

↑ and ↓ to select the item and the HDG control knob to adjust.

Align the aircraft at each cardinal heading and adjust the corresponding calibration item to the exact heading.

4: BRG PTR SETUP

Sets up sources for the bearing pointers. Purpose: the value.

Notes:

NAV-1 / NAV-2: Allows selections as follows:

DISABLED: Disables this bearing pointer.

COMPOSITE: Enables and forces the source to be the composite input.


ADF 1/2:

429:



Enables and forces the source to be the 429 port as selected for this receiver in the NAV setup page.

429+COMP Uses the 429 port (as described above) unless the cross-side receiver is the pilot’s current nav source, in which case defaults this pointer to the composite input. This selection is used when two 429 NAV receivers are connected which share the same port.

Selects DISABLED, DC SIN/COS, DC -SIN/COS (for Collins receivers), Synchro Normal, and Synchro –180 (to reverse bearing 180 degrees).

5:DME-1 SELECT

CURRENT SELECTION

- - NOT INSTALLED

- - NOT INSTALLED

ANALOG > 40MV/MILE

Purpose: Selects DME-1.

Note: softkey to select. When the SET softkey is depressed, the active selection will appear to the top under “current selection”.

Select the appropriate DME receiver type. Note that the ARINC

568 setting is used for Collins DME40 DME’s.

Analog 40mv/mile DME can only be assigned to DME 1 or DME

2 but not both.

Selection of Serial King Digital automatically selects 429 Port 2




6:DME-2 SELECT

CURRENT SELECTION

- - NOT INSTALLED

- - NOT INSTALLED

ANALOG 40MV/MILE

Purpose: Selects DME-2.

Note: softkey to select. When the SET softkey is depressed, the active selection will appear to the top under “current selection”.

Analog 40mv/mile DME can only be assigned to DME 1 or DME

2 but not both.

Selection of Serial King Digital automatically selects 429 Port 3




7: DME 1 / 2 CHANGE

DME1: > NOT INSTALLED

DME2: NOT INSTALLED

DME-1 HOLD

DME-2 HOLD

DME-2 HOLD

ANALOG 0mi

90mi

ANALOG DIST

ACTIVE HIGH

ACTIVE HIGH

DME2 HOLD

00

000

00.0 nm

Purpose: DME 1 HOLD

Allows setting the logic level of P2-10, DME HOLD input,

ACTIVE HIGH or ACTIVE LOW signals for the DME’s selected on page 5 and 6.

DME 2 HOLD

Allows setting the logic level of P2-3,

DME HOLD input, ACTIVE HIGH or ACTIVE LOW signals for the DME’s selected on page 5 and 6. (See drawing “DME KING

SERIAL AND ANALOG” for interface when wiring P2-3 as

DME1-NAV2)

DME 2 HOLD Allows the DME-2 HOLD to be used instead for

DME-1 NAV-2 (cross side) selection.

Allows calibration of Analog DME’s adjust.

To calibrate analog DME’s, first using a DME test set: a) setting the test set to 0.0 miles, calibrate 0.0miles using the 0mi calibration. Note that the adjustment scale factor is arbitrary. b) setting the test set to 90.0 miles, calibrate 90.0 miles using the 90mi adjustment. Note that the adjustment scale factor is arbitrary.


8: FCS EMULATION

CURRENT SELECTION

BENDIX IN-831

KING > KI-525

COLLINS

CENTURY

CENTURY

PN-101

NSD360

CENTURY

CENTURY II OR III

CENTURY IV

CESSNA

CESSNA

SPERRY

400B AC

400B DC

SPZ-500



Purpose: Changes the output of the heading/course datum signals for the flight control system to DC (KI-525 or NSD360 emulation) or AC

(IN-831/PN101 emulation). The selections by manufacturer name select default settings for the items when on the next page. If an autopilot type is listed, use this to select the closest default settings otherwise select an HSI type which is the closest choice for your autopilot input and strapping. the SET softkey to select.




KING KI-525

SIGNAL DC DC

HDG DATUM +RIGHT +RIGHT

CRS DATUM +RIGHT +RIGHT

HDG 00.550 00.550

MAX 09.996 09.996

Purpose:

Instructions:

Trims the factory defaults for the emulation selected on page 8.

HDG V/DEG and CRS V/DEG increase or decrease the gain of the course or heading error relative to the lubber line, and normally match the Volts/Degree input of the associated autopilot computer. These values default when the FCS selection is initially set, but can be adjusted in-flight if necessary, in VFR conditions, as follows: (Note that prior to Software 1.33 these values were shown in arbitrary units, not in volts/deg). a) Engage the autopilot in HDG mode. After the aircraft is established on the desired heading, move the heading bug a large amount and ensure that the aircraft turns to the heading bug and rolls out normally without instability, overshooting or undershooting the desired heading.

To correct for overshooting or instability, reduce the HDG

GAIN appropriately.

To correct for undershooting, increase the HDG V/DEG appropriately. b) Engage the autopilot in NAV mode and turn OFF the NAV receiver to provide a zero course error. Repeat the tests and adjustments in item ‘a’ above using the course pointer and

CRS V/DEG for adjustment. c) Use the “offset” adjustment to center the heading rollout if not precisely on the lubber line. This will rarely be required.

HDG DATUM and CRS DATUM allow the direction sensing to be reversed during installation. Changing these settings is identical to reversing H/C on a synchro control transformer.




(Note prior to software 1.34 CRS and HDG were a single item and have been separated in software 1.34 to support the Sperry

SPZ-500 and similar autopilots which use opposite phase on

CRS and HDG).

The other settings in this menu are not for installer adjustment except on advice of the factory, service bulletin, or service information letter. These values are defaulted when an item is selected in page 8 with the SET softkey.


GARMIN

GARMIN

GARMIN

GARMIN

GARMIN

GARMIN

GARMIN

GARMIN

GARMIN

KING

KING

KING

KING

KING

KING

MAGELLAN

TRIMBLE

TRIMBLE

TRIMBLE

TRIMBLE

TRIMBLE

CURRENT SELECTION

NONE

NONE

AERO COMP LE-2004

ARNAV R-50

II MORROW

II MORROW

II MORROW

604

612

618

II MORROW

II MORROW

II MORROW

II MORROW

2001 (RS-232)

2101 (RS-232)

2001 (ARINC)

2101 (ARINC)

II MORROW GX (RS-232)

II MORROW GX (RS-232 ENH)

GARMIN 150 (RS-232)

GARMIN

GARMIN

GARMIN

250 (RS-232)

150XL(RS-232)

250XL(RS-232)

GARMIN

GARMIN

GARMIN

GARMIN

155 (RS-232)

165 (RS-232)

155XL(RS-232)

300 (RS-232)

300XL(RS-232)

150 (ARINC)

250 (ARINC)

250XL(ARINC)

155 (ARINC)

165 (ARINC)

155XL(ARINC)

300 (ARINC)

430 (ARINC)

KLN-35 (RS-232)

KLN-88 (RS-232)

KLN-89 (RS-232ENH)

KLN-90 (RS-232)

KLN-90 (ARINC)

KLN-900 (ARINC)

5000

1000 (RS-232)

2000 (RS-232)

2101 (RS-232)

3000 (RS-232)

3100 (RS-232)




Appendix-A Page 11



Purpose: Changes selection of primary NAV LNAV-1. If none installed select NONE.

Note the SET softkey to select.

Selection of LNAV 1 selects 429 Port 1 or #1 RS232

Maintenance Page 11 is identical and sets LNAV-2.

Selection of LNAV 2 automatically assigns 429 Port 3 or #2

RS232

The Maintenance Screen pictured above is for illustration purposes only. To view all the choices of LNAV receiver, scroll through the list using the right knob.

12: LNAV 1 / 2 CHANGE

NONE

ANNUN DISCRETE

COURSE KNOB

OBS ROT NORMAL

OBS CAL 000.0

NONE

ANNUN DISCRETE

COURSE KNOB

OBS ROT NORMAL

OBS CAL 000.0

Maintenance Pages 10 and 11. the value.

Note:In normal use only the OBS CAL is adjusted during installation. This adjusts the calibration of the OBS for each receiver. It is only required if the GPS receiver uses an RS-232 interface and has a resolver connected. When a receiver uses


an ARINC-429 interface the OBS information is transmitted to the receiver via the

ARINC-429 interface.






13: MKR SELECT

CURRENT SELECTION

NONE

NONE

COLLINS AMR-350

KING KMA-20

KING KMA-24

KING

KING

KING

KING

KMR-675

KNR-634

KR-21

KR-22

TRIMBLE TMA-340

TRIMBLE TMS-350

Purpose: Changes selection of the marker beacon receiver. If none is installed select NONE. the SET softkey to select.

14: MKR CHANGE

NONE

MKR VALID > DISABLED

THRESH Volts

Purpose: Changes default settings for the marker beacon receiver selected on page 13.

Notes: the value.

These settings should be changed only on instructions from the factory, service bulletin, or service information letter.




15: NAV CHANGE

ILS VALID LOW

NAV-2 OBS NORM

OBS CAL 000.0

COMPOSITE-1 012.0

-2 003.2

Purpose: Sets up functions associated with VHF NAV 1 & 2 and ILS. the value.

Notes:

NAV-1 / NAV-2: Select installed / not-installed status. A single receiver should be installed as NAV-1.

PORT: Selects Analog if a conventional receiver or the appropriate

ARINC port 1-2-3 as wired (for GNS430 installations).

RELAY MODE: See description in pinout specifications. Normally set to

MASTER.

ILS LOCKOUT: Enables/disables ILS Lockout feature of the ILS Energize input pins. Disabling lockout will allow total manual control by the pilot.

See NAV Interface description. Normally set to NO.

COMPOSITE: Calibrates the composite NAV demodulator for the bearing pointers set up on page 4 BRG POINTERS.

ILS-1 and ILS-2: Select logic level of “ILS Energize” associated with each NAV receiver. Note that these inputs are used ONLY to energize the

VDI display and may apply to either NAV or GPS receivers. If used with GPS2 when no NAV2 is enabled, temporarily enable

NAV2 to access the ILS setting, and then deselect NAV2. The

ILS setting will be retained.

OBS ROTATION: If the OBS control rotates backwards when connected to the associated NAV receiver, change this setting and recalibrate.

OBS CAL:

See chart below.

OBS calibration for each VHF NAV receiver. When this is selected the OBS course will appear on the display and a lateral deviation scale will display. Note: changing the OBS CAL 180

°


COMPOSITE:


Installation Manual is identical to reversing the H/C leads on a standard resolver.

See chart below.

Calibrates the composite NAV demodulator for the BRG pointers. When this is selected the received bearing will display.

SN3308 NAV Page Resolver Troubleshooting

No resolver action at all

No ‘Vref’ signal to SN3308

No Sin/Cos return to receiver

Ensure that you have connected the SN3308 resolver input to the correct pin on the navigation receiver. This is NOT always the ‘Rotor H’ – it might be ‘Rotor

C’. Check the receiver schematic

Check the receiver schematic to determine whether ‘D’ or ‘E’ is the appropriate connection.

Check the receiver schematic to ensure the SN3308 outputs are connected to the appropriate active pins D/E/F/G of the receiver, not the grounded pins.

See steps below Calibration problems

SN3308 NAV Page Resolver Calibration (does not apply to VIR-30 or KNR-634)

STEP COMMENTS

1. Set nav test set to zero degrees and SN3308 course pointer (OBS) to zero degrees.

2. Go to the NAV maintenance page on the

SN3308 and adjust the NAV-1 OBS calibration to center the deviation needle.

3. Step to the compass rose display on the

SN3308.

4. Turn the test set to 45 degrees. Set the

SN3308 OBS to re-null the deviation pointer. If this is within a few degrees to a course angle of

45 degrees, proceed. Otherwise if it is –90 degrees out, step to the SN3308 NAV page and change the OBS ROTATION to “REVERSE” and go back to step 1.

5. Step the SN3308 to the compass rose display

(after the last maintenance page) and check the to/from flag and course pointer rotation. If to/from is reversed (and the wiring is correct) step back to the NAV maintenance page and renull the OBS calibration 180 degrees from the current calibration setting with the test set and the OBS set to the same course.

6. Check the OBS at 30 degree increments and verify calibration.

This step is identical to reversing the H/C leads on a standard resolver. NOTE: If you are using a

NAV401 test set from the rear-panel TONE OUT, to/from are backwards out of the generator and should be expected.




16: RELAY SENSE

CDI SRC SEL OFF

Purpose: Enables/disables relay sense from any relays which are driven from SN3308 relay control outputs. When a ground closure is not detected on the appropriate relay sense terminal (indicating that the relay did not close) the pilot’s NAV source selection will be redlined on the pilot’s display. For example if a NAV2 relay is used and doesn’t close, the pilot’s display will show ”NAV2”.

NAV-2 GPS-1 GPS-2:

Associated with the relay outputs on connector P3.

CDI SRC SEL:

This sense input enables/disables the automatic CDI function for Garmin GNS receivers when grounded/ungrounded. This is only used in a dual

SN3308 installation which has Pilot/Copilot select for the autopilot. See installation drawings. In a typical pilotonly installation this sense pin is not assigned (OFF) and the SN3308 will control / be-controlled from the GNS CDI

Select function.

RCVR 1 / 2:

This is the sense input for a relay which is wired to both the Nav-2 and Gps-2 relay outputs. This is specific to installations with dual Garmin GNS receivers where both receivers (all four nav sources) are made available as nav sources. See installation drawings. the value.

Notes: Each selection allows assigning the appropriate relay sense function to one of the following 12 input pins. These pins represent the probable pins left-over (unassigned) after all the installed equipment has been wired/assigned to the required pins. Normally there will be at least 3-4 of these pins remaining in any installation.




P2-3

P2-10

P2-14

P2-19 *

P2-22

P2-30

DME-2 Hold In

DME-1 Hold In

Ext. Sw 2 In

400 Hz Diff Resolver SIN

Ext. Sw 1 In

GPS Selected In

P2-33

P2-37 *

Spare input 1

400 Hz Diff Resolver COS

All these inputs are ACTIVE LOW, meaning a ground closure is required to activate.

* All the pins EXCEPT P2-19 and P2-37 have internal pullup resistors. If you use P2-19 or P2-37 an EXTERNAL pullup resistor must be tied to aircraft power. 10K Ohms is sufficient.

NAV-1

GPS-1

GPS-2

CDI SRC SEL

RCVR 1 / 2

Enable for any relay when a single relay is operated from the

NAV-1, GPS-1 or GPS-2 relay outputs. The effect of the relay not closing the appropriate sense input will be that the navigation source will be redlined on the pilot’s display after the source is selected. When the relay properly operates the redline will not appear.

A special input related to Garmin GNS430 installations. When enabled, allows the SN3308 to control (ground) or not control

(ungrounded) the CDI source select on the GNS 430. When turned off, the CDI select is always enabled.

A special input related to dual Garmin GNS430 installations which drive autopilots. A ground closure to this input indicates that receiver 1 (ungrounded) or 2 (grounded) is active.




17: SYSTEM LCD SETUPS

CONSULT FACTORY

SET LEFT POS

SET TOP POS

TRIM BOT POS

TRIM RT POS

000

198

541

458

TRIM T/B CENT

TRIM L/R CENT

LCD SHP

LCD PLL

LCD TC1

314

232

003

065

050

Notes:

18: SYSTEM

These settings should be changed only on instructions from the factory, service bulletin, or service information letter.

I/O Rev 1

TEMP

° C

85

° F

INVERTER INPUT 400 Hz

WX DETECTION OFF

Purpose: Shows some helpful system diagnostics.

IO/CPU Rev: These are informational showing the revision level of the internal circuit boards. These numbers are NOT the same as the MOD

LEVEL information on the data plate.

Temp: Internal temperature is displayed for determination of proper installation cooling. The internal temperature should run approximately 10

° C or 18°F above ambient temperature after operating for 30 minutes at maximum brightness. If due to



Installation Manual installation considerations it is necessary to increase cooling airflow:

1) bring additional cooling air to the fan inlet via a hose from an external avionics blower; or

2) it is permissible to remove the foam fan filter in the clamptray to increase cooling air if needed. This may be done by pulling the filter through the slots.

FAN: Displays the cooling fan RPM for proper operation. Normally approximately 6300RPM or greater

INVERTER: Displays the aircraft master inverter input frequency and voltage

(if used). This can be used to test master inverter operation at normal and low bus voltage. The inverter should be between

320Hz and 480Hz. The inverter frequency is shown on the display. Check the inverter at low and high battery voltage for correct tolerance. The displayed voltage is peak voltage which for a sine wave inverter will be approximately 36v and for a square wave inverter will be approximately 26v.

The inverter may be enabled/disabled. Note: if no master inverter is used the master inverter MUST be set to DISABLED to prevent getting a spurious error message on the pilots display.

COLOR SEL: Used to select either the PILOT or COPILOT color scheme for cross-side receiver indications in a dual-SN3308 installation.

BOOTSTRAP: Used to select OFF, NORMAL, or –180 for the RMI bootstrap output signals. This output may be used to provide a heading to an external RMI, moving map or weather detection equipment.

NOTE: Bootstrap selected to OFF, when providing Serial

Heading for WX 500.

WX DETECT: The WX-500 functions are enabled/disabled here. Note: if

Stormscope is enabled it must be connected to RS-232 port #2, which will preclude the use of a 2 nd

RS-232 GPS receiver on this port.




WX-500 DISABLED

IN SYSTEM PAGE.

Purpose: Displays setup data used in WX-500 installations. Refer to the

BFG WX-500 installation manual for instructions on the information contained in this page.

WX-500 DISABLED

IN SYSTEM PAGE.

Purpose: Displays text data from the BFG WX-500. Refer to the BFG

WX-500 installation manual for instructions on the information contained in this page.




21: BRIGHTNESS

Button Lo Bright

Button Hi Bright

LAMP DATA

000

045

Lamp Init Ma 2010 2009

Lamp Peak Ma 2100 2100

Lamp Hrs Tot 002:06 123:23

Lamp Hrs HB 001:10 50:03

Purpose:

Button Lo:

Allows adjustment of LED buttons and viewing of lamp data.

Adjusts the minimum brightness of the pilot’s buttons when the brightness control is at minimum. Adjust this at night.

Button Hi: Adjusts the maximum brightness of the pilot’s buttons when the brightness control is turned up. Adjust at dusk.

V-Cal 14:

I-Cal 14:

I-Cal 28: Factory adjustments. Do not change unless on instruction of the factory. To prevent inadvertently change these adjustments they are locked out unless the CAL button is held while the right knob is turned.

Lamp Ma:

Other:

This items shows the current lamp current in milliamps.

The two-column information is data on the current bulb vs the last bulb. This information is updated when a LAMP CHG operation is performed.

LAMP CHG: Changing the projection lamp requires re-initializing the lamp data. This is accomplished by holding both LAMP and CHG softkeys simultaneously. This operation must be performed when the aircraft bus voltage is at normal level – either 13.75v or 27.5v – either by running the engines or running from ground


power. Do not perform this calibration if the aircraft is on battery only (i.e. at 12.0v or 24.0v).



During this operation the lamp will automatically be brought to maximum brightness and measured over a period of 30 seconds. If you want to abort this operation after selecting it, remove the SN3308 power early in the test cycle.

22-25:

Various

DVM Groups







Purpose: Shows the actual measured input voltages (AC or DC as appropriate) at the SN3308 input pins as well as power supply voltages. This may be helpful in diagnosing installation wiring problems. Please note that AC signals are shown peak so a 26 volt sine wave input will show as approximately 36 volts, while a

26 volt square wave will show as 26 volts.

These values are not smoothed as in a normal DVM so a certain amount of jitter in the readings is normal.

DVM GROUP 1 also shows the internal pulse counter for the

KG102 gyro interface which may be used to diagnose problems with this gyro.




26: Diagnostics

Port 1 2 3

Break 000 000

Overrun 000 000

Framing 000 000

Parity 000 000

LNAV 000 000

429/568 000 000 000

Purpose:

RS232/RS422 Data:

Helps diagnose problems with internal systems such as serial port error counts showing error counts.

PFI: Counts occurrences of power fail sensing. Should normally always be 000000.

Serial Ports

Break:

Overrun:

Framing:

Usually indicates +/- inputs to SN3308 are wired backwards. If also associated with framing errors may indicate the wrong baud rate selected from the sender.

Usually indicates baud rate of sending unit is too high.

Caused by a break error or by baud rate of sending unit too low.

(i.e. 1200 baud GPS sending to 9600 baud Sandel)

LNAV:

429/568:

Indicates internal error decoding information from Loran or GPS.

ARINC 429 or DME communication errors (as appropriate selected/wired).

CLR SOFTKEY: Clears all the error counts

Note: It is NORMAL for some errors to occur during power up sequencing, but errors should not accumulate during normal operation.


8 Appendix B: Environmental Qualification Form



RTCA/DO-160C Environmental Qualification Form

Product nomenclature: SN3308 ColorMap Navigation Display

Vista, CA 92083

Conditions

Section/

Paragraph

4.0

Description of Conducted Tests

Temperature and altitude

Low temperature operating

Low temperature survival

High short-time operating

High temperature survival

4.5.1

4.5.1

4.5.2

4.5.2

Equipment tested to category F1

(-55

°C to +70°C to 55,000’ MSL)

Equipment tested to Table 4-1




High temperature operating

In-flight loss of cooling

4.5.3

4.5.4



Altitude 4.6.1

Decompression 4.6.2 Not required for equipment

Temperature variation

Operational shock

Crash safety

Explosion

Fluids susceptibility

Sand and dust

5.0

7.0

7.0

9.0

11.0

12.0

Equipment tested to Category C

Equipment tested IAW Para. 7.2.1

Equipment tested IAW 7.3.1

Equipment identified as ‘X’



90106-IM-J Installation Manual.doc Appendix-B Page 1



Conditions

Fungus

Salt spray

Magnetic effect

Power input

Voltage spike conducted

Audio frequency conducted

Induced signal susceptibility

Radio frequency susceptibility

Radio frequency emission

Lightning-induced transient susceptibility

Lightning direct effects

Icing

Section/

Paragraph

13.0

14.0

15.0

16.0

17.0

18.0

19.0

20.0

21.0

22.0

Description of Conducted Tests




Equipment tested to Category B

Equipment tested to Category A



Equipment tested to Category W

Equipment tested to Category A/Z

Equipment tested to DO-160D,

Waveform sets E/F, Level 2



23.0

24.0

Remarks:

Tests described in Sections 4,5,7, and 8 were conducted by Bell Technologies, Wayne, NJ.

Tests described in Sections 15, 16, 17, 18, 19, 20, 21, and 22 were conducted by Chomerics,

Radiation Test Services, Woburn, MA.

Tests described in Section 6 were conducted by National Technical Systems, Boxborough, MA.

All test reports are on file at Sandel Avionics.

90106-IM-J Installation Manual.doc Appendix-B Page 2

9 Appendix C: Sample FAA Form 337



NOTICE

Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.

8. Description of Work Accomplished

(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)

1. Sandel Avionics LLC, SN3308 Navigation Display (or as appropriate), Part

Number SN3308-00-BL (or as appropriate)

2. Sandel Avionics LLC, Clamp Tray Fixture 3ATI, Part Number 61013.

B. The Sandel Avionics SN3308 is interfaced to the following equipment:

1. Garmin International, GPS 165, GPS Navigation Receiver (Approved for En route,

Terminal, and Non-precision

Approach).

2. AlliedSignal Electronics and Avionics, KX 165 Communications and Navigation

Receiver. (or as appropriate)

3. AlliedSignal Electronics and Avionics, KX 155 Communications and Navigation

Receiver. (or as appropriate)

4. AlliedSignal Electronics and Avionics, KRA 10A Radar Altimeter System. (or as

appropriate)

5. AlliedSignal Electronics and Avionics, KR 22 Marker Receiver. (or as

appropriate)

6. AlliedSignal Electronics and Avionics, KG 102A Directional Gyro. (or as

appropriate)

7. AlliedSignal Electronics and Avionics, KMT 112 Magnetic Azimuth Transmitter.

(or as appropriate)

(By example state the following functional interface properties)...

C. The SN3308 receives and processes GPS navigation information for digital and waypoint display from the GPS 165. These

D. The SN3308 receives and processes VOR, localizer, and glideslope deviation and

90106-IM-J Installation Manual.doc Appendix-C Page 1


Installation Manual composite audio for bearing display

from the KX 165. These operations are considered primary means of navigation.

E. The SN3308 receives and processes glideslope deviation and composite audio for bearing display from the KX 155.

F. The SN3308 receives and processes radar (radio) altimeter information for digital and virtual display from the KRA 10A.

G. The SN3308 receives and processes marker beacon receiver information for illumination from the KR 22.

H. The SN3308 receives and processes magnetic heading for digital and graphic display from the KG 102A and KMT 112.

Interference functional tests and inspections were accomplished with reference to Advisory Circular 23.1311. (or as appropriate).

J. A system design and analysis was conducted with reference to Advisory Circular

2X.1309-1( ). (or as appropriate).

K. Federal Aviation Regulations, 2X.1301, 2X.1309(a), (b) and (d), 23.1311,

2X.1321(a), (b) and (d), 2X.1322, 2X.1327(a), 2X.1331, 2X1351, 2X.1357(a)-(d),

23.1365, 2X.1381, 2X.1529, and 2X.1581 (or as appropriate), were the basis of compliance.

L. Installation approval is sought with reference to Flight Standards Information Bulletin,

FSAW 95-09( ) (Amended), titled "Electronic Horizontal Situation Indicator (EHSI)

Approvals".

M. Instructions for Continued Airworthiness include the requirement to replace the projection lamp within the first 225 hours and every 225 hours thereafter, or every calendar year, whichever comes first.

N. The aircraft equipment list, and weight and balance were revised and recorded within the aircraft maintenance records.

O. All pertinent records of this alteration are on file at (State your repair station name

and number).

-------------------------------------------------------- End ------------------------------------------------

90106-IM-J Installation Manual.doc Appendix-C Page 2



10 Appendix D: Sample Airplane Flight Manual Supplement

The following is being provided for installations in which the local FSDO requires an Airplane Flight Manual Supplement. This sample is from a Sandel STC in a

Bonanza F33. It is simply being provided for the convenience of the installer.

Note that the cover page, table of contents and log of revisions has not been included here, and will be specific to your installation. The text is specific to the installed equipment, and also specifies ILS LOCKOUT operation.

SECTION I - GENERAL

The Sandel Avionics SN3308 Navigation Display is a compact three-inch instrument which performs the functions of a traditional Horizontal Situation

Indicator combined with a two-pointer RMI. The SN3308 Navigation Display also displays a moving map, Stormscope

® data, and marker beacon and GPS annunciators if the aircraft is appropriately equipped and configured.

SECTION II LIMITATIONS

The SN3308 Navigation Display Pilots Guide, SPN 90106-PG (applicable revision) must be immediately available to the flight crew.

The “CRC Self Test Failed” message must not appear on power-up if flight operations are predicated on the use of the SN3308 Navigation Display.

SECTION III EMERGENCY PROCEDURES

If the SN3308 Navigation Display fails to operate, use the magnetic compass as a heading source.

If the remote directional gyro (DG) becomes inoperative the magnetic fluxgate will provide the heading, and the resulting heading display will respond much more slowly than normal. The compass rose changes color from white to amber, and digital heading numbers will be redlined.

If the fluxgate fails, the SN3308 Navigation Display will continue to display heading based on the directional gyro (DG) input. The compass rose changes color from white to amber, heading numbers will be redlined.

If the remote directional gyro (DG) fails and the fluxgate fails or the SN3308 is a slaved gyro repeater, the compass rose will change from white to amber and continue to be displayed and the digital heading numbers will be redlined. Use the magnetic compass as a heading source.

90106-IM-J Installation Manual.doc Appendix-D Page 1

The circuit breaker for the SN3308 Navigation Display is located on the lower right circuit breaker panel labeled EHSI.



Refer to the SN3308 Navigation Display Pilots Guide for other error messages and alerts.

SECTION IV NORMAL PROCEDURES

VOR-LOC-ILS 1

GPS1

VOR 1

VOR 2

GPS 1

ADF

Sandel Avionics SN3308 Navigation Display

The selection of the primary navigation source between VOR-LOC-ILS 1 and

GPS 1 is accomplished by the use of the NAV switch and will connect the source to the HSI course pointer and the autopilot.

ILS override will prevent selection of the GPS as long as an ILS frequency is tuned on VOR-ILS 1. This will be annunciated on the SN3308 Navigation

Display.

The selection of the bearing pointer source between VOR 1, VOR 2, GPS1,

GPS2 or ADF is accomplished by the use of the BRG switch.

Annunciation of all GPS modes is accomplished by discrete annunciator lamps as well as on-screen annunciation on the SN3308 Navigation Display.

[If installed as a heading repeater (no direct fluxgate connection).]




When manually slewing the remote compass system, the compass rose will change from white to amber and the digital heading numbers will be relined.

[End heading repeater language.]

SECTION V PERFORMANCE DATA

No Change to AFM.


11 Appendix E: Checkout Procedures



11.1 Functional Ground Test Procedures/Report

The “Functional Ground Test Procedures/Report” below is for the purpose of simplifying ground tests of the SN3308. A copy of this report (and the “Operational

Flight Check Procedures/ Report in Section C-2) must be retained by the installing agency and a copy must be installed in the aircraft maintenance records. A copy must also be forwarded to Sandel Avionics along with the Warranty Registration

Form, Part Number 10129, which should be mailed after operational acceptance.

Repair Station Name:

________________________________________________ Number:

_____________

Address or Location: ____________________________ City

__________________ ST _____ ZIP _______

A/C Make: ________________________ A/C Model: _____________________

A/C Serial No: __________

Work Order No.: ___________ Technician: __________________________

Date Performed: ___________

90106-IM-J Installation Manual.doc Appendix-E Page 1



COMPANY NAME

COMPANY ADDRESS

TELEPHONE/FAX


Ground Test Procedures/Report for

Sandel Avionics SN3308

Installed in

{aircraft make and model}

Registration No. ________

SN3308 Serial No. ______________

Document No. ____________

Rev. - , Date

Appendix-E Page 2



11.1.1 Introduction

The following ground test procedures are to be performed after the SN3308 has been properly configured in the “Post-Installation Procedures”, but prior to performing flight test procedures. Successful completion of both the Ground Test and Flight Test procedures is necessary to support the claim that the SN3308, as installed, performs its intended function and is compatible with all aircraft systems.

The ground test procedures contained herein will include testing of interfaces to other systems. Therefore, this ground test must be conducted in conjunction with, or subsequent to ground testing of other systems.

The following external system interfaces will be tested:

- Compass input from fluxgate sensor (if installed)

- Navigation data inputs: VOR/ILS/GS, ADF, DME, GPS and FMS (if installed)

- Annunciator inputs from a marker beacon receiver (if installed)

- Annunciator inputs from a GPS receiver (if installed)

- Lightning-strike inputs from a WX-500 Stormscope® sensor (if installed)

- Remote NAV source switching relays and/or indicators (if installed)

11.1.2 Test Procedures and Results

11.1.3 Physical Installation

Verify that the SN3308 clamp tray has been properly installed in accordance with the manufacturer’s instructions, that any external switches affecting SN3308 operation have been clearly labeled, and that a trip-free resettable circuit breaker labeled “EHSI” is clearly visible.

Ensure that cooling air intake is not obstructed.

Completed _______ Comment __________________________________

11.1.4 Wiring Verification and Initial Power-Up

Perform a 100% continuity check of all aircraft wiring to verify in accordance with installation wiring diagrams.





Power check all wiring to ensure that 28 VDC and 26 VAC (if applicable) are applied to the proper pins and nowhere else.


Install the SN3308 into the clamp tray and verify full connector mating and that the unit installs without obstruction.


Activate the aircraft master switch and avionics master switch, if installed.

Verify that the SN3308 display illuminates within 12 seconds. It may be necessary to adjust the externally-mounted SN3308 dimmer control to obtain satisfactory brightness level.

CHECK SOFTWARE OPERATING VERSION NUMBER AS DISPLAYED

ON TOP OF SCREEN, CHECK WEBSITE OR WITH TECH SUPPORT

THAT UNIT AS LATEST REVISION. INSTALL DATABASE AT THIS TIME

OR AT DELIVERY.

Software revision # ___________Database Expiration Date____________

Switch on all equipment interfaced to the SN3308 such as NAV receivers, gyros, and marker beacon receivers.


11.1.5 System Configuration

If not previously accomplished, perform the “Post-Installation Procedures” included in Appendix A of the SN3308 Installation Guide. These procedures describe how to configure the SN3308 for compatibility with installed systems.


11.1.6 System Functions

11.1.7 Compass System Interface

Power up the system and verify that within 1 minute the compass card is displayed in white and agrees with the heading on a magnetic compass.





Disable the fluxgate excitation to the SN3308. Verify that within 10 seconds the compass digital heading is flagged. Restore the fluxgate excitation and verify that within 10 seconds the display is fully restored. Note: If fluxgate excitation and gyro are interconnected, remove both signals simultaneously and look for simultaneous failure indications.)


Remove power to (or otherwise disable) the remote directional gyro. Verify that the compass card is displayed in amber AND that a warning message is displayed on the SN3308 which requires operator acknowledgement.


If the SN3308 is installed as a heading repeater (no direct fluxgate connection) and interfaced with a Directional Gyro (DG) that “Flags Invalid” when operated in “Free

Gyro Mode”. Verify that the SN3308 continues to display the compass rose while the gyro compass is manually slewed left and right. This test must be performed after the

SN3308 has been powered for a minimum of 2 minutes.


11.1.8 NAV Source Selection

If the SN3308 is configured in “master” mode (no external NAV/GPS switch):

Press the [NAV] button repeatedly and verify that the screen legend next to the button cycles correctly through the configured NAV sources, i.e. NAV1, NAV2, GPS1, GPS2

(or as configured). For each NAV source, create valid and invalid NAV conditions and verify correct display of the SN3308 NAV flag for each receiver (the large red “X” through the CDI). For each VOR/LOC source, verify that tuning an ILS frequency causes the glideslope (vertical deviation) scale to display on the screen, even if it is flagged.


Press the [NAV] button and select a source other than NAV1, such as GPS or NAV2

(if configured). Tune NAV1 to an ILS frequency, and verify that after a one-second delay, the selected NAV source automatically reverts to NAV1. Verify that as long as

NAV1 is tuned to an ILS frequency, pressing the [NAV] button will not change the




NAV source, but instead will display the message “NAV1 TUNED TO LOC”. Verify that upon de-tuning the ILS frequency from NAV1, the NAV source selection returns to its original state.


If NAV2 is configured, tune both NAV1 and NAV2 to an ILS frequency and verify that

NAV1 remains selected. Detune the ILS frequency on NAV1 and verify that the display reverts to NAV2.


If the SN3308 is configured in “slave” mode (using external NAV/GPS switch):

Verify that pressing NAV does not change the selected NAV source, but instead displays a warning message.


Verify that the external NAV/GPS switch arrangement correctly controls the selected

NAV source on the SN3308, including any ILS lockout scheme, if implemented.


11.1.9 BRG Source Selection

Press SHFT>BRG on the SN3308 and verify that all installed NAV sources are presented for each bearing pointer (NAV1, NAV2, ADF1, ADF2, GPS1, GPS2 as installed). In addition, bearing pointer 1 will have “AUTO” listed as a choice.


Select each available NAV source for each pointer, and verify in turn that the depicted bearing corresponds to the actual bearing shown on the NAV source.


DME Selection 11.1.10

If two DME receivers are installed and configured:

Verify that pushing NAV to select between NAV1 and NAV2 also switches the appropriate DME readout on the SN3308 distance display. Press




SHFT>BRG to configure bearing pointer 1 to be NAV1 and bearing pointer 2 to be NAV2. Press BRG to display both pointers simultaneously. Verify that the correct DME data is displayed in each bearing pointer data block.


If a single DME receiver is installed and is not switchable between NAV1 and NAV2:

Verify that pushing NAV to select between NAV1 and NAV2 causes the DME readout to be displayed when NAV1 is selected, and the DME readout to be removed when NAV2 is selected. Press SHFT>BRG to configure bearing pointer 1 to be NAV1 and bearing pointer 2 to be NAV2. Press BRG to display both pointers simultaneously. Verify that DME data is displayed in the bearing pointer 1 data block, and that no distance data is displayed in the bearing pointer 2 data block.


If a single DME receiver is installed and is switchable between NAV1 and NAV2:

Verify that pushing NAV to select between NAV1 and NAV2 causes either the correct DME readout to be displayed or a “none” indication, depending on the position of the external DME select switch (if installed). Press SHFT>BRG to configure bearing pointer 1 to be NAV1 and bearing pointer 2 to be NAV2.

Press BRG to display both pointers simultaneously. Verify that DME data is displayed in the bearing pointer 1 data block when DME is externally switched to NAV1. Verify that when DME is externally switched to NAV2, an arrow

(“ Æ”) appears in the DME portion of the pointer 1 data block, and that DME distance data is displayed in the bearing pointer 2 data block. Press BRG to deselect pointer 1 and only display pointer 2. Verify that proper DME data is now displayed in the bearing pointer 2 data block.


If an external DME HOLD control is configured:

Verify that enabling DME HOLD displays the “H” symbol for each installed

DME receiver so equipped.


11.1.11 GPS Interface and Control

For each GPS receiver installed and configured:




Allow the receiver to acquire a valid position fix, and press NAV on the SN3308 to select that receiver as a NAV source. Enter either a single destination waypoint or a flight plan on the GPS receiver and select normal (LEG) navigation mode. Verify that the course pointer automatically rotates to the desired track, and that groundspeed and waypoint ID are displayed on the SN3308.


Press SHFT>BRG and assign either bearing pointer to the selected GPS receiver.

Verify that the bearing pointer corresponds to the bearing-to-waypoint, and that the distance displayed matches the display on the actual receiver.


If the GPS is equipped with an OBS mode (Bendix/King) or a HOLD mode which enables course resolver input (Garmin), select the OBS or HOLD mode and verify that rotating the course select knob turns the course pointer. Verify that the needle centers on the correct bearing to waypoint.


Enter the “CDI and Annunciator Test” mode of the GPS if available. Verify proper response of the GPS annunciators, if configured to display on the SN3308. If external mode selection is enabled on the SN3308, verify that the GPS pushbutton softkeys accessed in SHFT>NAV control the proper GPS functions.


Marker Beacon Interface 11.1.12

If a marker beacon receiver is interfaced to the SN3308:

With a marker beacon test set, generate outer, middle, and inner marker signals respectively. Verify that the appropriate annunciation appears on the SN3308.


Press “TEST” mode on the marker beacon receiver, and verify that the “MT” symbol appears on the SN3308.



11.1.13



Flight Control System Interface

If the SN3308 is interfaced to a flight control system (FCS):

Place the FCS mode selector in heading (HDG) mode. Verify that the aircraft controls respond correctly as the heading knob is turned and the heading bug moves around the SN3308 display.


Place the FCS mode selector in NAV-coupled (NAV) mode. Verify that the aircraft controls respond correctly as the course select knob is turned and the course pointer moves around the SN3308 display.


Stormscope ® Interface 11.1.14

If the SN3308 is interfaced to a WX-500 remote lightning sensor:

Enable the Stormscope® display by pressing the “WX” softkey in the SHFT>NAV submenu. Verify that “WX” is annunciated on the SN3308 display.


Press SHFT>NAV and select “WX TEST”. Verify that the word “TEST” is annunciated on the SN3308 display for approximately 10 seconds, and is then replaced by “WX”.


11.1.15 Additional Testing

Perform any additional tests deemed necessary.





11.2 EMI/RFI Test Procedures

11.2.1 Nav/Com Testing

Apply power to the avionics bus and ensure that all electrical equipment, including the

SN3308, is operating normally. Open the squelch on the primary communications radio and tune the radio to each whole megahertz frequency sequentially. Attempt to discern any interference caused by the SN3308. Pull the SN3308 breaker if interference is noted, to verify that the SN3308 is the source.


Repeat for the secondary communications radio.


Tune the primary navigation radio to 112 MHz and enable the audio output. Attempt to discern any audible interference cause by the SN3308.


Repeat for the secondary navigation radio.


Transmit on the frequencies 118.000 MHz, 126.975 MHz, and 135.975 MHz on the primary communications radio and attempt to discern any changes in the SN3308 display.


Repeat for the secondary communications radio.


11.2.2 General Testing




Observe any unusual interaction between the transponder, DME, ADF or Marker

Beacon receivers, and the SN3308 when switching power to any equipment.



Perform any additional EMI/RFI-related tests deemed necessary.



11.3 Operational Flight Test Procedures/Report



The “Operational Flight Check Procedures/Report” below is for the purpose of simplifying the in-flight operational check of the SN3308. A copy of this report (and the “Functional Ground Test Procedures/ Report” in Section C-1) must be retained by the installing agency and a copy must be installed in the aircraft maintenance records. A copy must also be forwarded to Sandel Avionics along with the Warranty

Registration Form, Part Number 10129, which should be mailed after operational acceptance.




COMPANY NAME

COMPANY ADDRESS

TELEPHONE/FAX

Flight Test Procedures/Report for

Sandel Avionics SN3308

Installed in

{aircraft make and model}

Registration No. ________

Serial No. ______________

Document No. ____________

Rev. - , Date




11.4 Introduction

The Flight Test Procedures described below are to be performed after both the

Post-Install Procedures and the Ground Test Procedures are performed.

Successful completion of the Flight Test Procedures will then satisfy the criteria for operational acceptance of the SN3308 installation.

Specific procedures are not provided for many of the tests herein, due to differences in installed options and aircraft configurations. Refer to the SN3308

Pilot’s Guide and the proposed Airplane Flight Manual Supplement for operational details of the equipment.

Each test item is followed by a space for the initials of the person performing the procedure, and a space for a description of any observations or anomalies.

Determination of a successful flight test is made after analysis of these observations.

11.5 Test Procedures

11.5.1 Pre-Departure Operations

Apply power to the SN3308 and all associated equipment. Determine that all equipment initializes and functions normally.

Verify that either the SN3308 external brightness control or the aircraft dimming bus control (as installed) can control the brightness of the SN3308 and that a satisfactory brightness level can be attained.


Evaluate the display of the SN3308 for readability.


Evaluate the intensity properties of the SN3308 display under both direct and indirect sunlight conditions, and in nighttime operation conditions.



Check the function of all nine buttons and both knobs, and confirm that all controls are operational.




11.5.2 Enroute Operations

Cycle various aircraft electrical equipment such as lights, landing gear, radar, pitot/windscreen heat, and anti-icing boots. Verify that none causes interference on the SN3308 display.


Verify proper operation of one or both VHF NAV receivers (as installed), both as

NAV sources and as bearing pointer sources. Simultaneously verify proper channeling and display of one or both DME sources, as installed.


Verify proper operation of one or both long-range NAV receivers (as installed), both as NAV sources and as bearing pointer sources. Include verification of map display of waypoints.


Verify proper operation of one or both ADF sources as bearing pointers.


Verify proper operation of the flight control system, both in NAV (coupled) mode and in heading mode.


Verify proper operation of the WX-500 Stormscope® sensor, if installed.


11.5.3 GPS Approach Operations

If installed, configure each approach-capable GPS receiver for a non-precision approach. Conduct the approach and evaluate proper operation of:

• CDI sensitivity and deflection




• Resolver interface in OBS or HOLD mode

• GPS annunciator display on the SN3308 (as installed)

• External GPS mode control switches on the SN3308 (as installed)

• Waypoint display when map is enabled on the SN3308

11.5.4 ILS Approach Operations

Conduct at least one fully coupled ILS approach (in VFR conditions) for each VHF

NAV receiver installed. During the approach, verify proper operation of:

• Lateral deviation display (CDI) in both ARC and 360 modes

• Vertical deviation display in both ARC and 360 modes

• Marker beacon annunciation on the SN3308, if installed

• Flight control system operation.



Perform any additional flight testing deemed necessary.





12 Appendix F: List of Effective Drawings and Attachments

Drawing Rev Title

- FSAW 95-09 FAA MEMORANDUM

90106-07

90106-10 pp 1

90106-10 pp 2

90106-10 pp 3

90106-10 pp 4

90106-10 pp 5

90106-10 pp 6

C Layout, SN3308 INSTALLATION

G2 KING KG102A SIMPLIFIED BLOCK DIAGRAM

G2 S-TEC GYRO SIMPLIFIED BLOCK DIAGRAM

G2 XYZ GYRO SIMPLIFIED BLOCK DIAGRAM

G2 MID-CONTINENT SIMPLIFIED BLOCK DIAGRAM

G2 NAV-1 AND RS-232 GPS

G2 NAV-1 AND ARINC-429 GPS

90106-10 pp 7

90106-10 pp 8

G2 NAV-2, GPS-1, DATA LOAD (RS422) GPS2

G2 WX-500

90106-10 pp 9 G2 RESOLVER INTERCONNECT

90106-10 pp 10 G2 GPS SWITCH / ANNUNCIATORS

90106-10 pp 11 G2 GYROS: XYZ AND KG-102

90106-10 pp 12 G2 GYROS: 328-A3G AND XYZ

90106-10 pp 13 G2 GYROS, MID CONTINENT & S-TEC, BOOTSTRAP

90106-10 pp 14 G2 GYROS: KCS-55 UPGRADE

90106-10 pp 15 G2 ADF

90106-10 pp 16 G2 MARKER BEACON

90106-10 pp 17 G4 DME: KING SERIAL AND ANALOG

90106-10 pp 18 G2 DME: ARINC 568

90106-10 pp 19 G2 SYSTEM

90106-10 pp 20 G2 FCS INTERCONNECT

90106-10 pp 21 G2 CENTURY 1C388 COUPLERS

90106-10 pp 22 G2 BENDIX/KING AUTOPILOTS

90106-10 pp 23 G2 S-TEC AUTOPILOTS

90106-10pp 24 G2 BENDIX AUTOPILOTS

90106-10 pp 25 G4 SINGLE SN3308 / GNS430/530

90106-10 pp 26 G4 SINGLE SN3308 / DUAL GNS430/530

90106-10 pp 27 G4 SINGLE SN3308 / GNS430/530 / #2 VHF NAV

90106-10 pp 28 G4 DUAL SN3308 / GNS430/530, FCS PILOT ONLY

90106-10 pp 29 G4 DUAL SN3308 / GNS430/530, FCS SELECTABLE

90112-08 B MOUNTING, SN3308 BRIGHTNESS POT AND DATA

UPLOAD JACK

90106-IM-J Installation Manual.doc Appendix-F Page 1

A

2

1

4

3

A

B

B

C

C

D E

DATE REV COMMENTS

10/23/00 G INITIAL RELEASE

04/03/01 G1 A/R 360 PAGE COUNT


COMPUTER CONTROLLED DRAWING

DO NOT REVISE MANUALLY

DOES NOT SHOW NAV 1, NAV 2, GPS 1, GPS 2,

DME OR STORMSCOPE INTERFACE.

PLEASE SEE SPECIFIC DRAWINGS FOR

INTERCONNECT

MAYBE USED AS TEMPLATE+

3

4

D

NOTES:

1. THESE LOAD RESISTORS ARE REQUIRED FOR PS ENGINEERING MARKER

RECEIVERS. RECOMMENDED FOR OTHER RECEIVERS TO PREVENT FAILURE

OF THE SN3308 INDICATION IF THE ASSOCIATED MARKER LIGHT BULB FAILS.

2. SELECT THE APPROPRIATE MARKER BEACON RECEIVER ON THE SN3308

MARKER BEACON INSTALLATION PAGE. IF SPECIFIC RECEIVER NOT SHOWN

USE KMA-24 SETTING.

Category

Title

KING KG102A SIMPLIFIED BLOCK DIAGRAM

Size

B

Document Number

Create: Friday, September 22, 2000 Mod:

90106-10

E

Rev

G2

29

1

2

A

2

1

4

3

A

B

B

C

C

D E

DATE REV COMMENTS









INTERCONNECT


3

4

D

NOTES:






USE KMA-24 SETTING.

SANDEL

Vista, Ca.

1

90106-10 G2

E

2

A

2

1

4

3

A

B C

B C

D E

DATE REV COMMENTS









INTERCONNECT


3

4

D

NOTES:






USE KMA-24 SETTING.

Category

Title

Size

B

Document Number

Create: Friday, September 22, 2000 Mod:

90106-10

Rev

G2

29

E

1

2

A

2

1

4

3

A

B

B

C

C

D

10/04/02 G2

E

DATE REV COMMENTS



A/R 573 PAGE COUNT






INTERCONNECT


3

4

D

NOTES:






USE KMA-24 SETTING.

1

90106-10 G2

E

2

4

3

2

1

A

FROM VHF NAV RECEIVER

B

TO AUTOPILOT

C

GPS/LORAN RECEIVER.

KLN89-B SHOWN FOR

REFERENCE.

P892

FCS LOC ENGAGE

VERT +FLAG

17

P891

12

VERT -FLAG

VERT +UP

13

P892

13

VERT +DOWN

LAT +FLAG

14

P891

10

LAT -FLAG

LAT +LEFT

11

P892

11

LAT +RIGHT 12

+TO 32

+FROM

KLN89-B SHOWN

SEE NOTE 3

33

OBS OUT 34

OBS RETURN 37

OBS SIN 35

OBS COS 36

GPS DISPLAYED 31

P891

MSG- ANNUN 16

ARM- ANNUN

APPR- ANNUN

18

17

WPT- ANNUN 15

P892

APPR ARM IN 8

RS232-TX

P891

2

C

TO VHF NAV

RECEIVER

NOTE 1

!

H

E

G

F

N/C

D

K1

ACFT PWR

IN SLAVE MODE THE

RELAY DRIVE IS PART

OF THE EXTERNAL

SWITCH/ANNUNCIATOR

UNIT

2699 AND BELOW 35ma MAX

2700 AND ABOVE 250ma MAX

A

GPS ENABLED FROM

SWITCH/ANNUNCIATOR UNIT.

(SLAVE MODE ONLY)

B

MASTER MODE

SLAVE MODE

GPS SWITCHING RELAY CONNECTIONS (SEE NOTE 4)

CONNECT P3-3 OR P2-30 BUT NOT BOTH.

C

AC POWER SEE NOTE 7

NOTE 6

SN3308

P1

29 Composite 1 In

27 ILS1 ENERGIZE

15 GS + Flag

33 GS - Flag

16 GS + Up

34 GS + Down

18 Nav + Flag

36 Nav - Flag

37 Nav + Left

19 Nav + Right

17 +TO

35 +FROM

RELAY SENSE NOTE 8

13 OBS RESOLVER H (IN)

28 OBS RESOLVER E (VREF) (IN)

14 OBS RESOLVER SIN OUT

32 OBS RESOLVER COS OUT

P2

X GPS1 SENSE

11 LRN MSG IN

12 LRN APPR IN

31 LRN APPR ARM IN

29 LRN WPT IN

P3

23 APPR ARM OUT

16 RS422-1 IN+

34 RS422-1 IN-

21 GPS2 RELAY

3 GPS1 RELAY

P2

30 GPS SELECTED

D

D 6/9/98

DATE

6/9/98

A

REV COMMENTS

A FIRST RELEASE

E

7/10/98 B NO CHANGE TO THIS PAGE

9/10/98 C PAGE COUNT.

12/8/98 E RESOLVER AND NOTE 1

5/26/99 F RELAY SENSE AND NOTE 8. TOTAL SHEETS

CHANGED TO 21

10/23/00 G MOVED GPS1 SENSE TO P2 ADDED RELAY

TO FCS LOC ENGAGE

TOTAL SHEETS CHANGED TO 29

04/03/01 G1

A/R 360 PAGE COUNT




NAV-1 AND RS-232 GPS INTERCONNECT

KLN89-B SHOWN FOR REFERENCE

KX165 / KNS80 / KNS81 SWITCHING, SEE NOTE 2

ROTOR C

KX165

ONLY

STATOR F

GROUND

KNS80, KNS81

ONLY

ROTOR H

STATOR D

K1

NOTES:

1. CONNECT OBS "H" FROM RECEIVER "H" or "C" WHICHEVER IS THE

ACTIVE OUTPUT. CHECK APPROPRIATE NAV RECEIVER SCHEMATICS.

CONNECT "SIN OUT" and "COS OUT" TO THE ACTIVE RETURN PINS,

USUALLY D/F. CONNECT "OBS VREF" TO EITHER STATOR RETURN PIN

(REF OR GROUND) USUALLY E or G. THE LOAD RESISTOR SIMULATES

A SYNCHRO.

2. THESE CONNECTIONS FOR KX165 OR KNX80/81 PREVENT THE RECEIVER

FROM FLAGGING THE NAV SIGNAL WHEN THE RESOLVER IS BEING USED BY

THE GPS. CONSULT THE APPROPRIATE KING DOCUMENTATION FOR

FURTHER INFORMATION.

3. SEE ARINC-429 INSTALLATION PAGE WHICH DOES NOT REQUIRE THE

RESOLVER SWITCHING RELAY (WHERE APPLICABLE)..

4. THE PREFERRED INSTALLATION IS THE SN3308 P3-3 CONTROLLING AN

EXTERNAL SWITCHING RELAY. IF AN EXISTING SWITCH CONTROL BOX IS

INSTALLED AND IT IS DESIRED TO LEAVE IT OPERATIONAL, USE SN3308 P2-30

TO SENSE GPS MODE. THIS WILL DISABLE THE NAV SOURCE SWITCH AND

CHANGE THE SN3308 MODE TO GPS-1 WHEN ACTIVE. YOU MUST ENABLE

P2-30 AS THE GPS SENSE INPUT IN THE SN3308 SYSTEM SETUP PAGE.

1 MASTER: SN3308 CONTROLS THE GPS (PREFERRED)

2 SLAVE: EXTERNAL GPS SWITCHING CONTROLS THE SN3308.

5. CHECK MANUFACTURERS DOCUMENTATION FOR ANY ADDITIONAL

INSTALLATION SPECIFIC RELAY POLES WHICH MAY ALSO BE

NEEDED.

6. FOR 3V COMPOSITE NAV SOURCES INSERT A 470K SERIES RESISTOR

LOCATED AT THE SN3308 CONNECTOR. NOT REQUIRED FOR .5V

SOURCE.

7. FOR 14V AIRCRAFT A PULLUP RESISTOR MAY BE REQUIRED TO

ALLOW VOR OPERATION.

8. SENSE PINS SELECTED IN SOFTWARE SEE "RELAY SENSE" MAINTENANCE

PAGE DESCRIPTION IN APPENDIX A FOR LIST OF SPECIFIC PINS..

SANDEL

Vista, Ca.

Category

Title

Size

B

Document Number

Create: Tuesday, April 28, 1998 Mod:

90106-10

Rev

G2

29

E

3

2

1

4

4

3

2

1

A

GPS/LORAN RECEIVER.

KLN-90B SHOWN FOR

REFERENCE

P901

APPR ACTIVE

SEE NOTE 2

VERT +FLAG

16

VERT -FLAG

VERT +UP

VERT +DOWN

LAT +FLAG 19

LAT -FLAG 25

LAT +LEFT 25

LAT +RIGHT 22

KLN90-B SHOWN

SEE NOTE 5

APPR ACTIVE 16

APPR ARM

GPS DISPLAYED

17

1

ARINC 429 RX-A

ARINC 429 RX-B

ARINC 429 TX-A

ARINC 429 TX-B

ARINC 429 RX-A

ARINC 429 RX-B

5

4

ARM SELECT 30

LEG/OBS- CTRL 33

9

8

24

23

A

FROM VHF NAV RECEIVER

TO VHF NAV

RECEIVER

RESOLVER

INTERCONNECT

NOTE 1 !

C

H

E

G

F

N/C

D

JUMPERS REQUIRED IF NO

AIRDATA COMPUTER

INSTALLED.

IN SLAVE MODE THE

RELAY DRIVE IS PART

OF THE EXTERNAL

SWITCH/ANNUNCIATOR

UNIT

GPS ENABLED FROM

SWITCH/ANNUNCIATOR UNIT.

(SLAVE MODE ONLY)

B

ACFT PWR

GPS SWITCHING RELAY CONNECTIONS (SEE NOTE 3)

CONNECT P3-3 OR P2-30 BUT NOT BOTH.

B

NOTE 6

TO AUTOPILOT


2700 AND ABOVE 250ma MAX

C

AC POWER SEE NOTE 8

NOTE 7

SN3308

P1

29 Composite 1 In

27 ILS1 ENERGIZE

15 GS + Flag

33 GS - Flag

16 GS + Up

34 GS + Down

18 Nav + Flag

36 Nav - Flag

37 Nav + Left

19 Nav + Right

17 +TO

35 +FROM


28 OBS RESOLVER E/F (VREF) (IN)



P2

12 LRN APPR IN

31 LRN APPR ARM IN

RELAY SENSE NOTE 9

D

X GPS1 SENSE

P3

10

28

11

29

429-1 RX-A

429-1 RX-B

429-1 TX-A

429-1 TX-B

23 APPR ARM OUT

2 OBS CMND OUT

MASTER MODE

SLAVE MODE

C

21 GPS2 RELAY

3 GPS1 RELAY

P2

32 OBS- SENSE

30 GPS SELECTED

D

Title

E

DATE REV COMMENTS

6/9/98 A FIRST RELEASE

7/10/98

9/10/98

B

C

KLN90 AIRDATA JUMPERS SHOWN FOR REF.

PAGE COUNT.

12/8/98 E RESOLVER AND NOTE 1.

5/26/99 F TOTAL SHEETS CHANGED TO 21

RELAY SENSE AND NOTE 9.

10/23/00 G MOVE GPS1 SENSE TO P2

ADDED MAX AMPERAGE TO K1






NAV-1 AND ARINC 429 GPS INTERCONNECT.

KLN90-B SHOWN FOR REFERENCE

NOTES:

1. CONNECT OBS "H" FROM RECEIVER "H" or "C" WHICHEVER IS THE ACTIVE

OUTPUT. CHECK APPROPRIATE NAV RECEIVER SCHEMATICS. CONNECT

"SIN OUT" and "COS OUT" TO THE ACTIVE RETURN PINS, USUALLY D/F.

CONNECT "OBS VREF" TO EITHER STATOR RETURN PIN (REF OR GROUND)

USUALLY E or G. THE LOAD RESISTOR SIMULATES A SYNCHRO.

2. THE APPROACH ACTIVE OUTPUT FROM THE GPS TO THE AUTOPILOT MAY

HAVE TO BE AN ADDITIONAL RELAY. SEE THE MANUFACTURERS

INSTALLATION DIAGRAMS.

3. THE PREFERRED INSTALLATION IS THE SN3308 P3-3 CONTROLLING AN

EXTERNAL SWITCHING RELAY. IF AN EXISTING SWITCH CONTROL BOX IS

INSTALLED AND IT IS DESIRED TO LEAVE IT OPERATIONAL, USE SN3308 P2-30

TO SENSE GPS MODE. THIS WILL DISABLE THE NAV SOURCE SWITCH AND

CHANGE THE SN3308 MODE TO GPS-1 WHEN ACTIVE. YOU MUST ENABLE

P2-30 AS THE GPS SENSE INPUT IN THE SN3308 SYSTEM SETUP PAGE.

1 MASTER: SN3308 CONTROLS THE GPS (PREFERRED)

2 SLAVE: EXTERNAL GPS SWITCHING CONTROLS THE

SN3308.

4. CHECK MANUFACTURERS DOCUMENTATION FOR ANY ADDITIONAL

INSTALLATION SPECIFIC RELAY POLES WHICH MAY ALSO BE

NEEDED.

5. KLN-90B PINOUTS SHOWN. CERTAIN CONNECTIONS SUCH AS

GPS_DISPLAYED AND OBS/LEG ARE SPECIFIC TO KLN-90B.

6. MSG AND WPT ANNUNCIATORS ARE COMMUNICATED ON THE ARINC 429

SERIAL CHANNEL.



SOURCE.

8. ON 14V AIRCRAFT A PULLUP RESISTOR MAY BE REQUIRED TO


9. SENSE PINS SELECTED IN SOFTWARE SEE "RELAY SENSE" MAINTENANCE

PAGE DESCRIPTION IN APPENDIX A FOR LIST OF SPECIFIC PINS.

SANDEL

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Category

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B

Document Number


90106-10

Rev

G2

29

E

4

3

2

1

4

3

2

1

A

NAV #2

VHF NAV #2

COMP. NAV OUT

ILS ENERGIZE

NOTE 3

TO SWITCHING RELAY COIL NOTE 3

B

AC POWER SEE

NOTE 4

NOTE 1

SN3308

P1

10 COMP. NAV #2 IN

8 NAV-2 ILS ENERG.

P3

5 NAV2 RELAY

GPS #1 (RS422)

TNL2000

9600 Bd

NORTHSTAR

M3

1200 Bd

(+) 15

(-) 3

(B) 11

(A) 6

SN3308

P3

16 RS422-2 IN+

34 RS422-2 IN-

C

NOTE 3

TNL2000

9600 Bd

NORTHSTAR

M3

1200 Bd

(+) 15 (B) 11

(-) 3 (A) 6

GPS #2 (RS422)

NOTE 5

GPS

UPDATE

SN3308

P3

14 RS 422-2 IN

32

30

RS 232 RX(GPS 2)

RS 232 TX(GPS 2)

(RS-232) GPS-2 OR LORAN-2.

NOTE 5

GPS-2

RS232-TX

A

SEE NOTE 2

B

SEE NOTE 2

SN3308

P3

14 RS422-2 IN+

32 RS422-2 IN-

30 RS-232-2 TX

C

D

DATE REV COMMENTS

6/9/98

7/10/98

A

B

FIRST RELEASE

E

COMPOSITE NAV-2 CHANGED TO P1-10. NOTE 7

ADDED.

9/10/98

12/10/98

3/19/99

C

E

F

NOTE 7 CHANGED. PAGE COUNT.

PAGE COUNT

INCORPORATED A/R 126 ADDED SHEETS 17-21

8/13/99 F1 A/R 161 ADDED RS-422 TO GPS CONNECTION

10/23/00 G TOTAL SHEETS CHANGED TO 29

04/03/01 G1 A/R 360 ADDED 1/4" TO STEREO PHONE PLUG

PAGE COUNT




AIRCRAFT PC-TO-SN3308 DATA LOADER CABLE

GROUND

1/4 Inch

DATA

DATA 2

6

3

7

1

4

8

5

9

4

SN3308

GROUND

P1

4

BENCH PC-TO-SN3308 CABLE

GROUND

RS422-2 IN+

P3

14

DATA

RS422-2 IN-

RS-232-2 TX

32

30

AIRCRAFT DATA LOADER JACK

SN3308

P3

14 RS422-2 IN+

32 RS422-2 IN-

30 RS-232-2 TX

DATA LOADER

SEE NOTE 2

D

DATA

2

6

3

7

1

4

8

5

9

NOTES:



SOURCE.

2. MOUNT SOFTWARE DOWNLOAD JACK IN AN ACCESSIBLE LOCATION.

JACK IS SWITCHCRAFT TYPE 14B OR EQUIVALENT. DATALOAD JACK

MUST BE INSTALLED TO ALLOW FUTURE DOWNLOADS

3. ILS ENERGIZE AND RELAY SWITCHING OUTPUT ARE ONLY REQUIRED IF

NAV-2 IS TO BE USED AS A SECOND PRIMARY VHF NAV RECEIVER. IN THIS

CONFIGURATION A 2ND SWITCHING RELAY IS ADDED TO SWITCH THE DBAR

AND FLAG INPUTS FROM THE 2ND RECEIVER IN THE SAME MANNER AS THE

GPS SWITCHING RELAY SHOWN FOR NAV-1 ON THE PREVIOUS PAGE.

4. ON 14V AIRCRAFT A PULLUP RESISTOR MAY BE REQUIRED TO


5. AN RS-232 GPS-2 CANNOT BE USED IN COMBINATION WITH A WX-500

STORMSCOPE ON THE SAME PORT.

SANDEL

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Category

Title

Size

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Document Number

Create: Sunday, May 03, 1998 Mod:

90106-10

E

Rev

G2

29

3

2

1

1

2

3

WX500

RS232-TX

J3

20

RS232-RX 8

REMOTE CLEAR 6

HDG CONFIG

HDG CONFIG

1

4

CONFIG GND

CONFIG GND

RS232 GND

J2

6

7

5

Sync X

Sync Y

Sync Z

10

23

11

Hdg + Flag

Hdg - Flag

Sync Ref Hi

Sync Ref Lo

24

25

13

12

A

4

A

WX500

J3

RS232-TX 20

RS232-RX 8

REMOTE CLEAR

HDG CONFIG

HDG CONFIG

CONFIG GND

CONFIG GND

RS232 GND

J2

6

7

5

6

1

2

SERIAL HEADING

NOTES 1,2&3

B C

NOTE 4

OPTIONAL

REMOTE

CLEAR

NOTES 5

DATA LOADER

SN3308

P3

14

32

RS422-2 IN+

RS422-2 IN-

30 RS-232-2 TX

P1

3 PWR GND

SYNCHRO HEADING

(REQUIRED FOR GNS430)

NOTES 1&2

NOTE 4

OPTIONAL

REMOTE

CLEAR

P4001

#1 GARMIN 430

RS232 Rx

P4001

#2 GARMIN 430

RS232 Rx

SN3308

P3

14

32

RS422-2 IN+

RS422-2 IN-

30 RS-232-2 TX

NOTES 5

SEE MFG'S INSTALL MANUAL FOR

HEADING FLAG INTERCONNECT

DATA LOADER

P1

3 PWR GND

P2

25

6

4

Sync X

Sync Y

400 Hz Reference

INVERTER

26 VAC Hi

26 VAC Lo

B C

WX500

RS422-TX+

RS422-TX-

J3

25

13

RS232-TX 20

RS232-RX 8

REMOTE CLEAR

HDG CONFIG

HDG CONFIG

CONFIG GND

CONFIG GND

RS232 GND

J2

6

7

5

6

1

2

D E

DATE REV COMMENTS






SERIAL HEADING W/ UPSAT MX 20

NOTE 4

OPTIONAL

REMOTE

CLEAR

NOTES 1,2&3

NOTES 5

UPSAT

MX20

11

26

RS422-RX +

RS422-RX -

SN3308

P3

14

32

RS422-2 IN+

RS422-2 IN-

30 RS-232-2 TX

DATA LOADER

P1

3 PWR GND

D

NOTES:

1. WX500 ALLOWS ONLY ONE UNIT TO BE MASTER. THE"MASTER"

CONTROLS CELL/STRIKE MODE AND REMOTE CLEAR THROUGH THE

SERIAL PORT.

2. AN RS-232 GPS-2 CANNOT BE USED IN COMBINATION WITH A WX-500

STORMSCOPE ON SANDEL RS232 PORT 2.

3. WX-500 HEADING CONFIGURATION IS SET TO "SERIAL" (HEADING

RECEIVED FROM SN3308)

4. A REMOTE-CLEAR SWITCH CONNECTED TO THE WX-500 CAN BE USED

TO CLEAR THE CELL/STRIKE DISPLAY. THIS FUNCTION IS ALSO AVAILABLE ON

THE FRONT PANEL OF THE SN3308 VIA SOFTKEYS.

5. MOUNT SOFTWARE DOWNLOAD JACK IN AN ACCESSIBLE LOCATION.

JACK IS SWITCHCRAFT TYPE 14B OR EQUIVALENT. DATALOAD JACK

MUST BE INSTALLED TO ALLOW FUTURE DOWNLOADS

SANDEL

Vista, Ca.

90106-10

E

G2

2

1

4

3

4

3

2

1

A B

COMMON NAV CONVERTER INTERCONNECTS

C

ROTOR DRIVE

ROTOR RET

STATOR REF

COS RET

SIN RET

10

2

8.

5

B

J

20

2

3

22

21

13

5

4

I

K

27

11

28

12

29

B

C

M

F

L

10

H

J

B

D

F

11

12

X

R

2

11

10

C

3

KK v

B y

JJ

21

25

20

24

19

41

44

47

46

48

5

3

1

2

4

CONNECTION TO OLDER RECEIVERS SUCH AS COLLINS 51R8, 51RV-1,

KING KNR660 AND SIMILAR RECEIVERS. SEE NOTE 1.

NAV RECEIVER

GS +FLAG

GS -FLAG

NAV +FLAG

NAV -FLAG

+TO

+FROM

TO SN3308

2200uF 2200uF

United LXF10VB222M or equivalent.

ARINC NAV RECEIVERS KNR634 AND COLLINS VIR-30A

(FOR VIR-30M SEE ABOVE) SEE NOTE 2.

OBS 'E' COS OUT

OBS 'F' SIN OUT

OBS 'B' DEV

OBS 'A' TO/FROM

VIR-30A

P2

KNR634

P6342

46

47

43

42

37

21

24

22

SN3308

P2

19

37

9

28

400HZ DIFF RES. SIN IN

400HZ DIFF RES. COS IN

400HZ DIFF RES. SIN OUT

400HZ DIFF RES. COS OUT

RESOLVER DRIVE

D

SN3308

P1


28 OBS RESOLVER VREF (IN)



E

DATE REV COMMENTS

12/4/98 E FIRST RELEASE

1/4/99 E1 Corrected KNS81 label, added KX165, ARC, 51R-8.

A/R 107

5/26/99 F RESOLVER INTERCONNECTS AND KNR634, VIR-30A AND M.

SHEET TOTAL CHANGED TO 21.

10/23/00 G ADDED KNR630,VIR350, KN74, KNS-80 ADDED

NARCO MK12D/E. TOTAL SHEETS CHANGED TO 29.





4

3

NOTES:

1. THE SN3308 REQUIRES DC FLAG SIGNALS. SOME VERY OLD RECEIVER

DESIGNS OUTPUT UNSMOOTHED DC DUE TO A LACK OF FILTERING

CAPACITORS. THE SN3308 WILL SHOW UNSTABLE FLAG OPERATION

UNLESS SMOOTHING CAPACITORS ARE ADDED AS SHOWN. THE

CAPACITORS CAN BE MOUNTED ON A TERMINAL BLOCK NEAR THE

RECEIVERS. CONSULT THE RECEIVER SERVICE MANUAL SCHEMATICS AS

REQUIRED.

2. FOR ARINC NAV RECEIVER USING 400HZ DIFFERENTIAL RESOLVER: a) THE NAV RCVR AND SN3308 MUST BE ON THE SAME INVERTER.

b) ON NAV MAINTENANCE PAGE SET OBS TYPE TO "DIFF A".

c) ON SYS MAINTENANCE PAGE ENABLE MASTER INVERTER.

3. VIR-30A AND KNR634 DIFFERENTIAL RESOLVER IS SUPPORTED ON

SOFTWARE 1.33 AND LATER.

2

1

90106-10 G2

E A B C D

2

1

A B C

4

3

GPS SWITCH ANNUNCIATOR MATRIX

II

MORROW

GARMIN

150/250

150XL/250XL

GARMIN

155/165

MSG

PTK

APPR

ACTV

HOLD

MSG

WPT

GARMIN

155XL/300/

300XL

MSG

WPT

MSG

WPT

ACTV ACTV

ARM ARM

HOLD/AUTO HOLD/AUTO

KING

KLN89

MSG

WPT

ACTV

ARM

KING

KLN90

MSG

WPT

ACTV

ARM

OBS/LEG

MAGELLAN

GPS

WPT

N'STAR

MSG

WPT

APCH

NAV PTK

HOLD CMD

ARM CMD ARM CMD

HOLD CMD HOLD CMD

ARM CMD ARM CMD

OBS CMD

TRIMBLE

MSG

WPT

APR

* NOTE 4

* NOTE 4

NOTE 1 NOTE 2

SN3308

P2

11

29

31

12

32

MSG

WPT

ANNUNCIATORS

APPR ARM

APPR ACTIVE

OBS/HOLD/PTK

P3

COMMANDS

23 APPR ARM

2 OBS or HOLD

D

A B C

E

DATE

6/9/98

7/10/98

9/10/98

REV

A

B

C

COMMENTS

FIRST RELEASE

NOTE 4 ADDED.

PAGE COUNT.

12/10/98 E PAGE COUNT.

5/26/99 F TOTAL SHEETS CHANGED TO 21.

NOTE 5 ADDED.

10/23/00 G UPDATED TITLE BLOCK. TOTAL SHEETS CHANGED

TO 29.





4

D

NOTES:

1: USED ONLY ON GARMIN 155/165 WHICH REQUIRED LATCHED ARM

COMMANDS.

2. USED ON GARMIN AND KING RECEIVERS WHICH REQUIRE

LATCHED MODE COMMANDS BUT NOT ON II-MORROW

RECEIVERS.

3. SELECT APPROPRIATE RECEIVER ON THE SN3308 LNAV

MAINTENANCE PAGE. IF INSTALLED RECEIVER IS NOT SHOWN ON

THIS MATRIX USE NEAREST COMPATIBLE SETTING OF THE SAME

MANUFACTURER AND INSURE THE TEXT AND COLORS OF THE

ON-SCREEN ANNUNCIATORS ARE ACCEPTABLE.

4. MSG AND WPT ANNUNCIATOR DISCRETES ARE NOT REQUIRED

WITH ARINC-429 RECEIVERS.

5. GARMIN GNS-430 (NOT SHOWN) DOES NOT REQUIRE ANY DISCRETE ANNUNCIATOR

WIRING.

2

Category

Title

Size

B

Document Number

Create: Thursday, June 18, 1998 Mod:

90106-10

Rev

G2

29

E

1

3

2

1

4

3

A B

SN3308

NEW KG-102 AND KMT112 INSTALLATION.

NOTE 1& 4.

P1

Fluxgate X

Fluxgate Y

Fluxgate Z

25

6

24

B

A

D

H

E

KMT112

Fluxgate X

Fluxgate Y

Fluxgate Z

Exc H

Exc C

Fluxgate Excitation 7

STEPPER A

STEPPER C

GYRO VALID

GROUND

30

11

9

3

AVIONICS BUS

PER KCS 55

INSTALL MANUAL

KG102 GYRO j n

Y c

P

L

Z t a

FV DRIVE

GND

MOTOR A

MOTOR C

GYRO VALID

GND

AUTO

MAN CW

MAN CCW

POWER

GND

C D

BENDIX/KING KI525A BOOTSTRAP MASTER DRIVING

SN3308 WITH NO INTERNAL SN3308 SLAVING.

(NOTES 2 AND 3).

SN3308

DG X

DG Y

SIGNAL GND

P1

31

12

4

P2 s v t

DATE

6/9/98

7/10/98

REV

A

B

E

COMMENTS

FIRST RELEASE

KA51-A "CW" E NOW L. KA51-B A/H REVERSED. NOTE 6 CHANGED.

9/10/98 C NOTE ON BOOTSTRAP OUTPUT. PAGE COUNT. NOTE 7 ADDED.

10/08/98

5/26/99

10/23/00

E

F

G

SHIELD ADDED ON 400HZ


ADDED KMT-112 FLUX GATE




COMPUER CONTROLLED DRAWING


KI-525A

X

Y

Z

4

GROUND 3 r u

EXCITATION

GROUND

3 c

GYRO VALID GYRO VALID 9

400HZ REF

P2

4 A/C 26VAC 400HZ HI

A/C 26VAC 400HZ LO

SN3308

USING KMT-112 FLUX GATE WITH 26VAC INVERTER

NOTE XYZ GYRO ALSO REQUIRED

KMT112

FLUXGATE

P1

FG X

FG Y

FG Z

25

6

24

B

A

D

FG X

FG Y

FG Z

7.2v RMS NOMINAL

H

E

FG Ext Hi

FG Ext Lo

0.5uF

35V NP*

FG Excitation 7 A/C 26VAC 400HZ HI

A/C 26VAC 400HZ LO

*May be 2ea 1uF

35v Electrolytic back-to-back

KA-51 SLAVING ACCESSORY REMOVAL.

NOTE 5.

KA51 SLAVING

ACCESSORY

(NOT USED)

FV EXT HI

FV EXT LO

FV X

FV Y

FV Z

3

4

6

5

2

METER DRV

GROUND

+5V

SLAVE

CW

CCW

E

F

B

C

D

A

N

R

F

J

L

B

E

K

C

H

M

P51B1

E

B

A

H

D

N/C

F

J

C

D

E

B

P51B2

JUMPER AS SHOWN

SN3308

P1

7

3

FG EXCITATION

GROUND

NOTES:

1. SELECT GYRO, FLUX GATE, AND VALID LOGIC ON COMPASS

SYSTEM MAINTENANCE PAGE.

2. TURN OFF SLAVING IN COMPASS MAINTENANCE PAGE.

3. THIS CONFIGURATION IS USED WHEN BOOTSTRAPPED FROM AN

EXISTING SLAVED COMPASS SYSTEM. THIS MIGHT BE DESIRED WHERE AN

EXISTING COMPASS SYSTEM SUCH AS A KI525A IS MOVED TO THE COPILOTS

SIDE AND AN SN3308 IS INSTALLED ON THE PILOTS SIDE. UNDER THIS

CONDITION THE SN3308 CAN BE DRIVEN BY THE BOOTSTRAP OUTPUT OF

THE COPILOTS HSI. THE BOOTSTRAP OUTPUT OF THE HSI MUST BE DRIVEN

BY THE SAME INVERTER THAT SUPPLIES THE SN3308 REFERENCE INPUT.

4. TO UPGRADE AN EXISTING KCS-55 INSTALLATION SEE THE APPROPRIATE

DRAWING IN THIS MANUAL.

5. WHEN CONVERTING KCS-55 SYSTEM INSTALLATIONS THE KA-51 SLAVING

ACCESSORY IS NOT USED. THE FLUXGATE EXCITATION SIGNAL CAN BE

PICKED UP FROM THE EXISTING KA-51 CONNECTORS AS SHOWN. SEE THE

COMPLETE DRAWING ON SEPARATE PAGE IN THIS MANUAL. INSURE THAT

WHEN COMPLETE THE FLUXGATE WIRING IS CORRECT AS SHOWN FROM

THE FLUXGATE TERMINALS TO THE 3308 REGARDLESS OF THE PIN

NUMBERS OF THE INTERMEDIATE CONNECTORS.

SANDEL

Vista, Ca.

Category

2

1

Title

Size

B

Document Number


90106-10

Rev

G2

29

E C D A B

4

3

2

1

A B

LEAVING INSTALLED BUT BYPASSING COLLINS 328A-3G

SLAVING ACCESSORY WHEN UPGRADING A PN101

SYSTEM. SEE NOTE 1 & 2

SN3308

P1

REF PINOUTS

OF 331A

INDICATOR

NOTE 7

TB1

FLUXGATE

NOTE 8

FG X 25

L

1 FG X

M

FG Y

FG Z

6

24

N

2

3

FG Y

FG Z

4

FG Excitation 7

5

FG Ext Hi

FG Ext Lo

NOTE 7

328A-3G

DG X

DG Y

SIGNAL GND

GROUND

400HZ REF

SN3308

FG X

FG Y

FG Z

P1

25

6

24

31

12

4

3

P2

4

F

G

H

HH

P

GG

J

AA

JUMPER THESE PINS AS SHOWN

SEE NOTE 2

TYPICAL XYZ DG AND FLUX GATE

USING THE SN3308 INTERNAL SLAVING.

NOTE 3.

19 GROUND

13

14

15

X

Y

Z

7 GROUND

11

9

SLAVING

SERVO

6 SERVO

5 EXCITATION

FLUXGATE

NOTE 8

FG X

FG Y

FG Z

FG Excitation 7 FG Ext Hi

FG Ext Lo

DG X

DG Y

SIGNAL GND

GYRO VALID

31

12

4

9

GROUND 3

400HZ REF

P2

4

XYZ GYRO

X

Y

Z

GYRO VALID

EXCITATION

GROUND

A/C 26VAC 400HZ HI

A/C 26VAC 400HZ LO

A B

C

C

D E

DATE REV COMMENTS

10/23/00 G INITITAL RELEASE





SN3308

P1

DG X

DG Y

SIGNAL GND

GYRO VALID

31

12

4

9

GROUND 3

400HZ REF

P2

4

XYZ DG WITHOUT FLUXGATE WITH

NO INTERNAL SN3308 SLAVING.

(NOTES 4, 5 & 6).

SLAVED HSI

BOOTSTRAP

OUTPUT

XYZ GYRO

X

Y

Z

GYRO VALID

EXCITATION

GROUND

A/C 26VAC 400HZ HI

A/C 26VAC 400HZ LO

4

3

NOTES

1. THIS CONFIGURATION DOES NOT ALLOW FOR AN ADDITIONAL

INVERTER DRIVING THE SN3308. EITHER USE THE 328A-3G AS THE

INVERTER SOURCE, OR IF A DIFFERENT MASTER INVERTER IS

USED THEN THE 328A-3G MUST BE REMOVED.

2. THIS CONFIGURATION DISABLES THE 328A-3G SLAVING ACTION.

SLAVING IS PERFORMED INSIDE THE SN3308.

3. THIS INTERCONNECT ALLOWS THE USE OF A COLLINS 332-E4 WITHOUT

USE OF 328A-3G SLAVING ACCESSORY.

4. SELECT GYRO, FLUX GATE, AND VALID LOGIC ON COMPASS

SYSTEM MAINTENANCE PAGE.

5. TURN OFF SLAVING IN COMPASS MAINTENANCE PAGE.

6. IF AN EXISTING COMPASS SYSTEM IS LEFT INSTALLED (FOR

INSTANCE ON RIGHT SIDE) THE SN3308 CAN BE BOOTSTRAPPED

TO THE INDICATOR WITH EITHER INTERNAL OR EXTERNAL

EXCITATION. THIS USES THE EXISTING COMPASS SYSTEM IN

SLAVED MODE AND THE SN3308 IN UNSLAVED MODE.

7. THE 2200 OHM RESISTORS ARE RECOMMENDED (NOT REQUIRED) TO

REDUCE RINGING FROM THE INTERNAL INVERTER. THE SN3308 APPLIES

NO LOAD TO THE GYRO.

8. ANY TSO'D XYZ FLUX GATE IS PERMISSABLE, INSTALL ACCORDING TO

MANUFACTURERS RECOMMENDATION. IF FLUX GATE REQUIRES LESS

THAN 26VAC USE A PAIR OF SERIES RESISTORS (2 WATT) ONE IN EACH

DRIVE LEAD TO PROVIDE THE CORRECT DRIVE VOLTAGE.

SANDEL

Vista, Ca.

Category

Title

Size

B

Document Number


90106-10

Rev

G2

29

E

2

1

D

4

3

2

1

A B

SN3308

Fluxgate X

Fluxgate Y

Fluxgate Z

P1

25

6

24

MID-CONTINENT INST CO 4305-100

HUMPHREY FLUXVALVE

B

A

D

H

E

Fluxgate X

Fluxgate Y

Fluxgate Z

Exc H

Exc C

Fluxgate Excitation

STEPPER A

STEPPER C

GYRO VALID

Ground

7

30

11

9

3

AVIONICS BUS

PER MFG'S

INSTALL

MANUAL

ONLY

ONE

4305-100

3

15

1

2

4

17

6

7

8

14

FV DRIVE

GND

5 FV DRIVE

ENCODER A

ENCODER B

GYRO VALID

POWER GND

26 VAC OUTPUT

26 VAC GROUND

28 VDC

14 VDC

STEC (AERONETICS) 8100 GYRO AND 8140 FLUX GATE

WITHOUT 8130 HSI. SEE NOTES 1, 2, & 3.

SN3308

P1

NOTE 2

6444/8140

FLUXGATE

Fluxgate X 25 B Fluxgate X

Fluxgate Y

Fluxgate Z

6

24

A Fluxgate Y

D

E

Fluxgate Z

Exc H

H Exc C

J1

4

5

10

Exc H

6444/8100

Exc C

GYRO

PHASE 1 Fluxgate Excitation 7

DG X

DG Y

Signal Ground

Ground

31

12

4

3

400 Hz Excitation

P2

4

NOTE 2

AVIONICS

BUS

PER MFG'S INSTALL

MANUAL

26VAC 400HZ EXCITATION FOR EXTERNAL USE.

1 SYNCHRO LOAD MAXIMUM.

14

13

12

17

18

2

DG X

DG Y

DG Z

SLAVING

SLAVING

POWER

GROUND

A B C

C D E

DATE

10/23/00

REV

G

COMMENTS

INITIAL RELEASE





SN3308

Sync X

Sync Y

P2

25

6

400 Hz Reference 4

INVERTER

26 VAC Out HI

26 VAC Out LO

Page 18 Setup

Inverter "Enable"

Bootstrap "Normal or 180"

COMPASS BOOTSTRAP

OUTPUT FROM SN3308

Sync X

Sync Y

Sync Z

Sync Ref Hi

Sync Ref Lo

Hdg + Flag

Hdg - Flag

TO BOOTSTRAP SYNCHRO IN.

(ELECTRONIC LOADS ONLY).

429 COMPASS BOOTSTRAP

OUTPUT FROM SN3308

NOTE: HEADING STABILZATION OUTPUT ONLY

SN3308

429 OUT A

429 OUT B

P3

11

29

HEADING LABEL

429 (320)

NOTES

1. THE STEC/AERONETICS GYRO DOES NOT ALLOW THE USE OF

AN EXTERNAL 400HZ INVERTER FOR ITS XYZ OUTPUTS. IF AN

EXTERNAL INVERTER IS NEEDED TO DRIVE OTHER SYSTEMS

WHICH ARE CONNECTED TO THE SN3308, THIS GYRO IS NOT

COMPATIBLE.

2. THE 2200 OHM RESISTORS ARE RECOMMENDED (NOT REQUIRED) TO

REDUCE RINGING FROM THE INTERNAL INVERTER. THE SN3308 APPLIES

NO LOAD TO THE GYRO.

3. EARLY MODELS OF AERONETICS GYROS OPERATE AT 600HZ AND ARE

NOT COMPATIBLE WITH THIS SYSTEM. CONTACT STEC FOR S/N

INFORMATION.

SANDEL

Vista, Ca.

1

2

4

3

D

90106-10 G2

E

4

3

2

1

A

KG102

DIRECTIONAL

GYRO

+15v

-15v

+5v

+15v UNREG

SIGNAL GND

DIGITAL GND

PWR GROUND

T

HDG VALIDa

DRIVE MOTOR 1

DRIVE MOTOR 2

DRIVE MOTOR 3

DRIVE MOTOR 4

P

S

L

N

SLAVING CT H

SLAVING CT C v

W

FV EXT HI

FV EXT LO t

Z

SLAVE METER k

+5v

SLAVE

CW

CCW

T c j n

FROM VHF NAV

NOTE 2 TO FCS

(DC)

DC COURSE

DC HEADING

CRS/HDG REF (GND)

FROM VHF NAV

FROM VHF NAV

30HZ ONLY

FROM INVERTER

BOOTSTRAP

OUTPUT TO

SYNCHRO

26VAC

ACFT GND

X

Y

Z

KMT112 FG

FV EXT HI

FV EXT LO

H

E

FV X B

FV Y

FV Z

A

D

B C

KI-525 INDICATOR

P101

+RIGHT

+LEFT b

V

+TO

+FROM

Z

T

LIGHTING HI

LIGHTING CT

LIGHTING HI

+14v NAV PWR

+28v NAV PWR

+15v

-15v

+5v

+15v UNREG

SIGNAL GND

DIGITAL GND

PWR GROUND s v j n k f

Y t

L

N

D

H

N/C

N/C

N/C

N/C

N/C

N/C

N/C

N/C

N/C

DOTTED AREA REPRESENTS THE SN3308 INTERCONNECT. THE

BALANCE OF THE DATA IS SHOWN FOR REFERENCE

SN3308

P1

19

37

17

35

+RIGHT

+LEFT

+TO

+FROM

3

22

GND

GND

+NAV FLAG

-NAV FLAG

NAV FLAG GND

K

F c

CRS ERROR

HDG ERROR

HDG/CRS REF e

P

S

GS FLAG -

GS FLAG +

W

P102

J

NOTE 5

GS DEV +-UP

GS DEV +DOWN

HDG VALID

HDG VALID c

P

E

B

RESOLVER H

RESOLVER C

RESOLVER D

RESOLVER E

RESOLVER F

RESOLVER G b e

X a

V

Y

SEE NOTE 6

SEE NOTE 3

18

36

NAV FLAG+

NAV FLAG-

HDG CT H

HDG CT C

HDG CT X

HDG CT Y

HDG CT Z t s v r u

DRIVE MOTOR 1

DRIVE MOTOR 2

DRIVE MOTOR 3

DRIVE MOTOR 4

A

D

H

L

SLAVING CT H

SLAVING CT C

SLAVING CT X

SLAVING CT Y

SLAVING CT Z j n m h d

400HZ

N/C

N/C

SEE NOTE 1

4

33

SIGNAL GND

GS FLAG -

15 GS FLAG +

16

34

9

GS DEV +UP

GS DEV +DOWN

GYRO VALID

13 OBS 'H'

14 OBS SIN OUT

32 OBS COS OUT

28 OBS DC REF

P2

7 COURSE DATUM

26 HDG DATUM

4 400HZ REF.

25

6

P1

30

SYNC X OUT

SYNC Y OUT

STEPPER A

11 STEPPER C

25

6

24

FV X

FV Y

FV Z

KA51

FV EXT HI

FV EXT LO

FV X

FV Y

FV Z

2

4

6

3

5

E

K

C

H

M

E

B

A

H

D

P101

METER DRV

GROUND

+5V

SLAVE

CW

CCW

E

F

B

C

D

A

N

R

F

J

L

B

F

J

C

D

E

B

P102

N/C

N/C

SEE NOTE 4

7 FG EXCITATION

A B C

D E

DATE

6/9/98

7/10/98

9/10/98

9/10/98

REV

A

B

C

D

COMMENTS

FIRST RELEASE

PAGE NUMBER CHANGED.

PAGE COUNT.

NO CHANGE.

9/23/98 E KI525-S AND NOTE 7. SHIELDS ADDED 400HZ.


MOVED RESOLVER INTERCONNECT AND NOTES 4

AND 5 TO PAGE 4. KG102 FG H/C CORRECTED.

KA51-A CHANGED 'E' TO 'L'

10/23/00 G ADDED PINS P2-25 AND 6

ADDED NOTE 6. TOTAL SHEETS CHANGED TO 29.





4

NOTES:

1: THE SYSTEM 400HZ INVERTER WILL NORMALLY BE CONNECTED TO THE HEADING

SYNCHRO 'H' TERMINAL. THIS WIRE CAN BE USED TO DRIVE THE SN3308 REFERENCE INPUT.

IN AN UNUSUAL CASE THE SYNCHRO MIGHT HAVE BEEN WIRED IN UPSIDE DOWN AND THE

400HZ REFERENCE MAY BE ON THE 'C' TERMINAL.

2: IF AN EXISTING CONVERTER IS INSTALLED SUCH AS A KA 52 OR KA 57, LEAVE UNIT

INSTALLED AND SELECT KI525 ON FCS EMULATION PAGE.

3. SHOWN IS THE 30HZ RESOLVER INTERCONNECT. CHECK APPROPRIATE NAV RECEIVER

SCHEMATICS BEFORE APPLYING POWER. TYING PINS E/G TOGETHER AS SHOWN ASSUMES THEM

TO BE THE NAV RECEIVER VREF. THESE ARE NORMALLY TIED TOGETHER INSIDE THE NAV

RECEIVER AND GO TO SIGNAL GROUND OR AN INTERNAL DC REFERENCE VOLTAGE. IF THESE DO

NOT TIE INTERNALLY PLEASE CALL SANDEL FOR ASSISTANCE.

4. WHEN CONVERTING KCS-55 SYSTEM INSTALLATIONS THE KA-51 SLAVING ACCESSORY IS NOT

USED. THE FLUXGATE EXCITATION SIGNAL CAN BE PICKED UP FROM THE EXISTING KA-51

CONNECTORS AS SHOWN.

5. PRIOR TO INSTALLING THE SN3308, ENSURE THAT THIS WIRE IS COMING FROM THE FLIGHT

CONTROL SYSTEM GROUND AND THAT NO VOLTAGE IS PRESENT ON THIS PIN WITH POWER

APPLIED TO ALL AVIONICS. IF VOLTAGE IS PRESENT, CONNECT SN3308 P1-4 TO FCS GROUND

AT THE ROLL COMPUTER WITH A NEW WIRE. IF PRIMARY POWER IS APPLIED TO SN3308 P1-4

DAMAGE MAY OCCUR TO THE SN3308 RESULTING IN AN OPEN CIRCUIT AT P1-4. THIS CAN BE

CHECKED WITH AN OHM METER.

6. RESISTOR MAY BE REQUIRED. SEE RESOLVER INTERCONNECT SHEET TO DETERMINE PROPER

CONNECTION.

SANDEL

Vista, Ca.

Category

Title

Size

B

Document Number

Create: Saturday, May 02, 1998 Mod:

90106-10

Rev

G2

29

E D

2

1

3

4

A B

ADF RECEIVER 1/2 INTERCONNECT

SN3308

P2

DC SIN

DC COS

DC REF

17

35

18

ADF-1

DC SIN

DC COS

DC REF

ADF-2

DC SIN

DC COS

DC REF

3

SN3308

DC SIN

DC COS

DC REF

P2

19

37

36

SN3308

400 Hz Ref

P2

4

X

Y

17

35

SIGNAL

GROUND

P1

4

SEE NOTE 1

400HZ ADF RECEIVERS 1&2

2

1

SN3308

400 Hz Ref IN

P2

4

X

Y

18

36

SIGNAL

GROUND

P1

4

ADF 1

400 Hz Ref Hi

400 Hz Ref Lo

X

Y

Z

AC INVERTER

26 VAC 400 Hi

26 VAC 400 Lo

ADF 2

400 Hz Ref Hi

400 Hz Ref Lo

X

Y

Z

AC INVERTER

26 VAC 400 Hi

26 VAC 400 Lo

A B

C

C

SN3308

DC SIN

DC COS

DC REF

P2

17

35

18

D E

DATE

6/9/98

7/10/98

9/10/98

12/11/98

REV

A

B

COMMENTS

FIRST RELEASE


C PAGE COUNT.

E PAGE COUNT


10/23/00 G ADDED INVERTERS TO ADF RECEIVERS ADDED

COLLINS ADF 650/650A AND BENDIX/KING KR 87.

TOTAL SHEETS CHANGED TO 29.





4

12

11

10

14

3

15

A

B

D

DC SIN

DC COS

DC REF

D

NOTES:

1. THE SN3308 WILL NOT SUPPORT THE #2 DC ADF RECEIVER WHEN ALSO

USED WITH A 400HZ #1 VHF NAV AS THE DIFFERENTIAL RESOLVER 400HZ

INPUT AND THE SIN/COS ADF INPUT SHARE THE SAME PINS.

2. SELECT APPROPRIATE SETUP DATA ON ADF INSTALLATION PAGE.

SANDEL

Vista, Ca.

Category

Title

Size

B

Document Number


90106-10

Rev

G2

29

E

1

2

3

1

4

3

2

A B C

EXTERNAL MARKER

LAMPS IF

INSTALLED

MARKER RECEIVER

OM

MM

IM

LAMP COM

NOTE 1

(THESE LOAD RESISTORS ARE REQUIRED FOR

PS ENGINEERING MARKER RECEIVERS)

EXTERNAL MARKER

LAMPS IF INSTALLED

MARKER RECEIVER

KING KR22

OM

MM

IM

LAMP COM

P2

SANDEL SN3308

16

34

15

OM

MM

IM

NOTE 2

P2

SANDEL SN3308

16

34

15

OM

MM

IM

NOTE 2

A B C

D E

DATE

6/9/98

7/10/98

REV

A

B

COMMENTS

FIRST RELEASE

NOTE 2 CHANGED.

8/20/98 C PS ENGINEERING NOTE. PAGE COUNT.

12/8/98 E LOAD RESISTOR VALUES.


10/23/00 G ADDED KING KR22. TOTAL SHEETS CHANGED TO

29.

04/03/01 G1

10/04/02 G2

A/R 360 PAGE COUNT

A/R 573 PAGE COUNT

1.2k ON KR22 TO INNER MARKER



4

3

D

NOTES:






USE KMA-24 SETTING.

SANDEL

Vista, Ca.

Category

Title

Size

B

Document Number


90106-10

Rev

G2

29

E

1

2

4

3

2

1

Data Buss 6

Clock Buss F

DME Request D

9

8

24

DME Hold E 12

DME

KDI 572

A

Data Buss

Clock Buss

11

12

DME Request 15

DME Hold

RNAV Request

2

17

NAV 1 Common 48

NAV 2 Common 49

B

SINGLE KING SERIAL DIGITAL DME USING KDI572

(ANY KING SERIAL DME PERMISSABLE)

(NOTE 5)

P3

SANDEL SN3308

9

8

27

Data Buss

Clock Buss

DME Request

P2

10 DME 1 Hold

3 DME 1 Nav 2

(NOTE 1)

NAV 1

Data Buss

Clock Buss

RNAV Request

DME Common

NAV 2

Data Buss

Clock Buss

RNAV Request

DME Common

DME1

DME2

DUAL KING SERIAL DIGITAL DME'S.

P3

SANDEL SN3308

DATA

DME REQ

CLK

9

27

8

DATA

DME REQ

CLK

P2

DME

HOLD

NOTE 2

10 DME1 HOLD

DATA

DME REQ

CLK

P3

26

7

25

DATA

DME REQ

CLK

DME

HOLD

NOTE 2

P2

3

DME1 HOLD

A B

C D

SINGLE KING SERIAL DIGITAL DME WITH SELF CONTAINED CONTROLLER

(KN64 SHOWN FOR REFERENCE, KN62/KN62A PERMISSABLE)

(NOTE 4 & 5)

KN 64 DME

P3

SANDEL SN3308

Data Buss 13

Clock Buss 14

DME Request N

9

8

27

Data Buss

Clock Buss

DME Request

ADDED KN 64 DME . ADDED NOTE 5.

ADDED NAV1 & NAV2. TOTAL SHEETS CHANGED

TO 29.

E

DATE

6/9/98

7/10/98

REV

A

B

COMMENTS

FIRST RELEASE

DME HOLD SHOWN TO KDI572. DME-1 NAV-2

SHOWN TO NAV-2.

9/10/98

12/11/98

C

E

PAGE COUNT.

PAGE COUNT


10/23/00 G

04/03/01 G1 A/R 360 KN 63 DME NAV1 & NAV 2 WERE CONN

TO SN3308 P3-27 & P3-8. PAGE COUNT

10/04/02 G2

9/25/03 G4

A/R 573 PAGE COUNT

A/R661: Pinout for KDM706 added. Note on permissibility added

RNAV Request L

DME

1 or 2

Nav 1

P2

3 DME 1 Nav 2

(NOTE 1)

NAV 1



DME Common C

Nav 2

Data Buss

Clock Buss

RNAV Request

DME Common

4

3

NAV 2

Data Buss

Clock Buss

RNAV Request

DME Common

ANALOG DME

40MV/MILE

SIGNAL COM

VALID

ANALOG DME AS ONLY DME

P1

5

23

P2

3

10

SANDEL SN3308

DME ANALOG +

DME ANALOG -

DME ANALOG VALID

DME1 HOLD

DME

HOLD

RELAY

ANALOG DME

40MV/MILE

SIGNAL COM

ANALOG DME AS SECOND DME

SANDEL SN3308

P1

5

23

DME ANALOG +

DME ANALOG -

VALID

NOTE 3

P2

3 DME ANALOG VALID

C D

NOTES:

1. IN A SINGLE DME CONFIGURATION THE SN3308 DETECTS BOTH DME

HOLD AND NAV-1/NAV-2 ASSIGNMENT. WHEN NAV-2 IS CHANNELED THE

DME READOUT WILL ASSOCIATE WITH THE BEARING POINTER NAV-2

SELECTION. IF THE DME IS NOT ASSIGNABLE LEAVE THE CORRESPONDING

PIN UNCONNECTED.

2. IN A DUAL DME CONFIGURATION THE SN3308 CAN ONLY DETECT DME

HOLD. IT ALWAYS ASSOCIATES DME-1 WITH NAV-1 AND DME-2 WITH

NAV-2.

3. THE SN3308 WILL NOT SUPPORT HOLD ANNUNCIATION ON ANALOG DME

USED AS DME-2.

4. THE SN3308 WILL SUPPORT REMOTE DISPLAY OF KN62/64 DME'S.

CONNECT AS SHOWN, TAKING "DME REQ" FROM REAR CONNECTOR PIN-N.

THE KN62/64 DO NOT HAVE A HOLD OUTPUT THEREFORE NO HOLD

ANNUNCIATION IS POSSIBLE.

5.

MAINTENANCE PAGE SETUP FOR KING SERIAL DME

DME 1/2 CHANGE

DME1: KING DIGITAL

DME2: NONE

DME-1 HOLD ACTIVE LOW

DME-2 HOLD ACTIVE LOW

DME-2 HOLD DME 1 NAV2

2

SANDEL

Vista, Ca.

Category

Title

Size

B

Document Number


90106-10

Rev

G4

29

E

1

1

4

3

2

A B C

SINGLE ARINC 568 DME. COLLINS DME-40

SHOWN FOR REFERENCE.

DME-40 SANDEL SN3308

P3

DATA

SYNC

CLK

9

27

8

DATA

SYNC

CLK

DME1 HOLD RELAY

DME NAV-2 RELAY

NOTE 1

P2

10 DME1 HOLD

3 DME1 NAV 2

DME-40

DATA

SYNC

CLK

DUAL ARINC 568 DME'S. COLLINS DME-40

SHOWN FOR REFERENCE

SANDEL SN3308

P3

9

27

8

DATA

SYNC

CLK

DME1 HOLD RELAY

DATA

SYNC

CLK

P2

10 DME1 HOLD

P3

26

7

25

DATA

SYNC

CLK

DME2 HOLD RELAY

NOTE 1

P2

3 DME2 HOLD

A B C

D E

DATE

6/9/98

7/10/98

REV

A

B

COMMENTS

FIRST RELEASE


9/10/98 C PAGE COUNT.

12/11/98 E PAGE COUNT

5/26/99 F TOTAL SHEETS CHANGED TO 21.

NOTE ON DME-40 SOFTWARE


TO 29.



4



3

D

1. IN A SINGLE DME CONFIGURATION THE SN3308 DETECTS BOTH DME

HOLD AND NAV-1/NAV-2 ASSIGNMENT FROM THE INSTALLED SWITCHING

RELAYS. WHEN NAV-2 IS CHANNELED THE DME READOUT WILL ASSOCIATE

WITH THE BEARING POINTER NAV-2 SELECTION. IF THE DME IS NOT

ASSIGNABLE LEAVE THE CORRESPONDING PIN UNCONNECTED.

2. IN A DUAL DME CONFIGURATION THE SN3308 CAN ONLY DETECT DME

HOLD. IT ALWAYS ASSOCIATES DME-1 WITH NAV-1 AND DME-2 WITH

NAV-2.

3. DME-40 (ARINC 568) DME SUPPORTED IN SOFTWARE 1.32 AND LATER.

SANDEL

Vista, Ca.

Category

Title

Size

B

Document Number


90106-10

Rev

G2

29

E

1

2

1

2

4

3

A B

ACFT BUS

AVIONICS BUS

5 AMP

NOTE 6/7

NOTE 1

ACFT GROUND

LOW LEVEL SIGNALS

NOTE 2

26VAC 400HZ

NOTE 5

NOTE 4

CW

SANDEL SN3308

P1

2 KEEP ALIVE POWER

1

20

ACFT POWER

ACFT POWER

3

22

POWER GROUND

POWER GROUND

4 SIGNAL GROUND

26 BRIGHTNESS

NOTE 3

P2

4 400HZ REF

22 EXTERNAL SWITCH 1

14 EXTERNAL SWITCH 2

C

A B C

D E

DATE

6/9/98

REV

A

COMMENTS

FIRST RELEASE

7/10/98 B PAGE NUMBER CHANGED.

9/10/98 C NOTE 1 CHANGED. PAGE COUNT.

12/11/98 E MAIN POWER, PAGE COUNT

5/26/99 F REMOVED FUSE. CHANGED NOTES 6/7.

TOTAL SHEETS NOW 21.


TO 29.



4



D

1. USE 20AWG WIRE. BOTH GROUNDS AND BOTH POWER LEADS

REQUIRED.

2. USE THIS GROUND PIN ONLY FOR LOW LEVEL RETURNS OF

ANALOG SIGNALS SUCH AS SYNCHRO 'Z' LEGS. DO NOT USE

FOR DIGITAL SIGNALS OR POWER.

3. MOUNT DIMMER CONTROL NEAR INSTRUMENT WITHIN REACH OF

THE PILOT. 'CW' INDICATES CLOCKWISE ROTATION. THE DIMMER

INPUT GOES TO FULL BRIGHTNESS BELOW .5VDC. THE DIODE

FORCES THE LOWEST SETTING OF THE BRIGHTNESS POT TO .6V OR

ABOVE.

4. WITH THE EXCEPTION OF THE OBS RESOLVER ON PINS P1-13, P1-14,

P1-28 AND P1-32, THE SN3308 REFERENCES ALL 400HZ INPUTS AND

OUTPUTS TO THE SIGNAL ON THIS PIN. SEE ADDITIONAL NOTES ON

OTHER SHEETS OF THIS MANUAL.

5. OPTIONAL YOKE OR PANEL MOUNTED SWITCHES FOR ASSIGNABLE

FUNCTIONS SUCH AS REMOTE SYNC, ARC/360, ETC. SEE SETUP

INFORMATION IN SN3308 INSTALLATION MENUS.

6. FOR ALL SERIAL NUMBERS KEEP ALIVE POWER P1-2 MAY DRAW AS MUCH AS

20MA AT EXTREMES OF TEMPERATURE. THEREFORE DO NOT CONNECT TO

BATTERY BUS BUT CONNECT AS SHOWN TO ACFT PWR.

7. PIN 2 IS KEEP ALIVE POWER. CONNECTION TO THIS PIN IS OPTIONAL. WHEN A PRIMARY POWER INTERRUPTION OCCURS OF LESS THAN TWO MINUTES DURATION, A VOLTAGE OVER 6.5VDC ON THIS PIN WILL REDUCE THE RE-BOOT TIME OF THE SN3308 TO APPROXIMATELY 1.5 SECONDS.

UNIT HAS INTERNAL RESISTOR/FUSE

2

SANDEL

Vista, Ca.

Category

Title

Size

B

Document Number


90106-10

Rev

G2

29

E

1

3

4

3

2

1

A

AUTOPILOT OR

INTERFACE

ADAPTER

CRS DATUM HI

CRS DATUM LO

HDG DATUM HI

HDG DATUM LO

DC AUTOPILOT TYPICAL INTERCONNECT

SEE NOTE 1 CONCERNING KING KA52/57

SN3308

P2

7 DC CRS DATUM

NOTE 2

26 DC HDG DATUM

P1

4 SIGNAL GND

AUTOPILOT

400HZ AC AUTOPILOT TYPICAL INTERCONNECT

SN3308

P2

CRS DATUM X or H

CRS DATUM Y or C

7 DC CRS DATUM

HDG DATUM X or H

HDG DATUM Y or C

26 DC HDG DATUM


2700 AND ABOVE250ma MAX

ACFT PWR

NOTE 3

NOTE 4

24 BACK COURSE

ACFT PWR

BACK COURSE

NOTE 6

FROM SYSTEM

400HZ INVERTER.

4 400HZ REF

P1

4 SIGNAL GND

A

B

B

5Khz

EXCITATION

FROM

CENTURY IV

C

HDG DATUM

P2

26

D

CENTURY IV INTERCONNECT (5KHZ AC VERSION)

SN3308

HDG DATUM

E

DATE

6/9/98

7/10/98

REV

A

B

COMMENTS

FIRST RELEASE

CENTURY IV ADDED.

8/20/98 C CENTURY IV CHANGED, CENTURY 2/3 MOVED

OFF PAGE. NOTES CHANGED. PAGE COUNT.

12/11/98 E PAGE COUNT

5/26/99 F RELAY CURRENT. TOTAL SHEETS CHANGED TO 21

10/23/00 G ADDED MAX AMPERAGE TO BACK COURSE. TOTAL

SHEETS CHANGED TO 29.

04/03/01 G1

10/04/02 G2

A/R 360 PAGE COUNT

A/R 573 PAGE COUNT



P2

23

DATUM

EXCITATION

4

CRS DATUM 7 CRS DATUM

NOTES 7/8

C

N/C

CENTURY IV INTERCONNECT (DC VERSION)

SN3308

P2

P2

HDG DATUM 26 HDG DATUM

23

DATUM

EXCITATION

CRS DATUM 7 CRS DATUM

NOTES 7/8

NOTES:

1. IF INSTALLATION ALREADY CONTAINS A KING KA52/57 AUTOPILOT

ADAPTER IT MAY REMAIN IN THE SYSTEM. TREAT THE SN3308 AS A

KI525.

2. DATUM OUTPUTS ARE REFERENCED TO GROUND.

3. CHECK AUTOPILOT INTERNAL SCHEMATIC TO INSURE THAT THE SN3308 IS

DRIVING THE SIGNAL INPUTS AND THAT IT IS PERMISSABLE TO GROUND 'C'

OR 'Y' AS SHOWN. IN SOME CASES 'C' MAY BE SIGNAL AND 'H' MAY BE

GROUND. CALL FACTORY WITH ANY QUESTIONS.

4. WHEN BC OUTPUT NOT REQUIRED LEAVE UNCONNECTED.

2

5. SELECT THE CORRECT HSI EMULATION ON THE FCS MAINTENANCE PAGE.

6. BC OUTPUT IS AN OPEN COLLECTOR. RELAY REQUIRED IF BACK

COURSE INPUT TO AUTOPILOT REQUIRES +28V TO ACTIVATE.

OTHERWISE CONNECT SN3308 BC OUTPUT DIRECTLY TO AUTOPILOT

BC INPUT.

7. SOFTWARE ABOVE 1.04 SELECT NDS-360DC, OTHERWISE SELECT KI-525

ON THE FCS MENU.

8. ON FCS-CHANGE MENU, ADJUST HDG-GRADIENT (AND CRS-GRADIENT IF

USED) TO HIGHEST VALUE THAT DOES NOT OVER-SHOOT THE LUBBER LINE

DURING HDG-MODE AND NAV-MODE COURSE CHANGES RESPECTIVELY. EXCEPT FOR KI-525 THESE VALUES WILL BE IDENTICAL.

9. IF CRS/HDG WORK BACKWARDS, EITHER a) USE OPPOSITE PHASE OF

AC EXCITATION SOURCE; b) ON SOFTWARE 1.05 OR LATER

SELECT "REVERSE" ON FCS-CHANGE MAINTENANCE PAGE.

SANDEL

Vista, Ca.

Category

Title

1

Size

B

Document Number

Create: Monday, May 04, 1998 Mod:

E

Rev

90106-10 G2

29

D

3

1

2

A B

3

4

CENTURY 1C-388 & 1C388-M RADIO COUPLERS

PARALLEL

WITH

EXISTING

WIRES

CD33 TO AMP

C

ROLL EXC

F

ROLL EXC

CD33 TO DG

A

HDG SIG

(5Khz)

SN3308

P2

23 DATUM EXCITATION

26 HDG DATUM

B

ROLL COM n/c 7 CRS DATUM

D

E

JW Miller PN:9250-276 or Equiv

CENTURY 1C-388-C, 1C388-MC RADIO COUPLERS

CD33 TO DG

D

ROLL EXC

SN3308

P2

23 DATUM EXCITATION

(5Khz)

ROLL EXC

E

A

HDG SIG

B

ROLL COM

(ABOVE COUPLERS DO NOT

SUPPORT COURSE DATUM.) n/c

26 HDG DATUM

7 CRS DATUM

C D

CENTURY 1C-388-2 RADIO COUPLER

CD33 TO DG

ROLL EXC

D

SN3308

P2

23 DATUM EXCITATION

(5Khz)

E

ROLL EXC

A

HDG SIG

26 HDG DATUM

CRS SIG

B

CD33 TO AMP

B

ROLL COM

7 CRS DATUM

CENTURY 1C-388-3 RADIO COUPLER

CD33 TO DG

E

ROLL EXC

P2

23

SN3308

DATUM EXCITATION

(5Khz)

ROLL EXC

D

A

HDG SIG

F

B

ROLL COM

CRS SIG

C

ROLL COM

26 HDG DATUM

7 CRS DATUM

C D

E

DATE REV

9/10/98 C

COMMENTS

FIRST RELEASE THIS PAGE.

12/11/98

5/26/99

E

F

F2

TRANSFORMER P/N, PAGE COUNT


8/20/99 2:1 STEPUP OF CRS/HDG BY DRIVING TRANS. CT.

10/23/00 G ADDED NOTE PARALLEL WITH EXISTING WIRES.


04/03/01 G1 A/R 360 NOTE 5 DELETED SA-330. PAGE COUNT




4

NOTES:

1. SOFTWARE ABOVE 1.04 SELECT NDS-360DC, OTHERWISE SELECT KI-525

ON THE FCS MENU.

2. ON FCS-CHANGE MENU, ADJUST HDG-GRADIENT (AND CRS-GRADIENT IF

USED) TO HIGHEST VALUE THAT DOES NOT OVER-SHOOT THE LUBBER LINE

DURING HDG-MODE AND NAV-MODE COURSE CHANGES RESPECTIVELY.

NORMALLY THESE VALUES WILL BE THE SAME.

3. GROUND CONNECTIONS TO SN3308 SIGNAL GROUND.

4. DO NOT GROUND ANY CENTURY II/III SIGNALS EVEN DURING

TROUBLESHOOTING. THIS COULD DAMAGE THE AUTOPILOT. SEE THE

CENTURY INSTALLATION MANUAL FOR DETAILS.

5. ANY COMMERCIAL 75MW OR GREATER AUDIO TRANSFORMERS

MAY BE USED.

6. TRANSFORMERS ARE MAGNA-TEK TY-141P OR EQUIVALENT.

SANDEL

Vista, Ca.

Category

Title

Size

B

Document Number

Create: Monday, May 04, 1998 Mod:

90106-10

Rev

G2

29

E

1

2

3

A B

A

4

SN3308

DC CRS DATUM

P2

7

DC HDG DATUM 26

SIGNAL GND

P1

4

3

SN3308

DC HDG DATUM

P2

26

DC CRS DATUM

SIGNAL GND

7

P1

4

2

SN3308

DC HDG DATUM

P2

26

DC CRS DATUM

SIGNAL GND

7

P1

4

1

SN3308

DC CRS DATUM

P2

7

DC HDG DATUM 26

SIGNAL GND

P1

4

A

B

P1402

50 PIN

17

P1401

37 PIN

2

HONEYWELL

KAP 140

CRS DATUM HI

HDG DATUM HI

27

CRS/HDG

DATUM LO

(AS AVAILABLE FROM GYRO) 11 HDG VALID

KFC 150

KC190/KC191/KC192

P1901

X DC HDG SIG

W DC CRS SIG

20

19

HDG DATUM LO

CRS DATUM LO

KFC 200

KC 295

P2952

H DC HDG SIG

W DC CRS SIG

M

HDG/CRS

DATUM LO

C

SN3308

AC HDG DATUM

P2

26

AC CRS DATUM 7

ACFT

PWR

BACK COURSE

400HZ REF

24

4

SIGNAL GND

P1

4

PN101 "FCS Emulation" selected in setup

D E

DATE REV

10/23/00 G

COMMENTS

INITIAL RELEASE

04/03/01 G1

10/04/02 G2

A/R 360 PAGE COUNT

A/R 573 PAGE COUNT

ADDED HDG DATUM LOW TO KFC150




2700 AND ABOVE250ma MAX

KFC 300

KCP 320

J1

12

13

14

15

HDG DATUM H

HDG DATUM C

CRS DATUM H

CRS DATUM C

17 BACK COURSE -

16 BACK COURSE +

FROM SYSTEM

400HZ INVERTER.

4

3

2

KFC 225

J2252

16 CRS DATUM HI

J2251

2 HDG DATUM HI

28

CRS/HDG

DATUM LO

(AS AVAILABLE FROM GYRO) 11 HDG VALID

B C D

NOTES

1. SELECT KI525 FOR HSI EMULATION ON THE FCS MAINTENANCE PAGE.

SANDEL

Vista, Ca.

90106-10

E

G2

1

A

4

SN3308

DC HDG DATUM

P2

26

SIGNAL GND

P1

4

3

SN3308

DC HDG DATUM

P2

26

SIGNAL GND

P1

4

2

SN3308

DC HDG DATUM

DC CRS DATUM

P2

26

7

SIGNAL GND

P1

4

1

SN3308

DC HDG DATUM

DC CRS DATUM

P2

26

7

SIGNAL GND

P1

4

A

S-TEC AUTOPILOTS

B

B

C D E

DATE REV COMMENTS






S-TEC 20/30 T/C-R/C

P1

8

7

DC HDG HI

DC HDG LO

35 SIGNAL GROUND

S-TEC 40/50 PROG/COMP

P1

31 DC HDG HI

29 DC HDG LO

46 SIGNAL GROUND

S-TEC 55

P1

28

11

HDG DATUM HI

CRS DATUM HI

29

12

44

CRS/HDG

RETURN

SIGNAL GROUND

S-TEC 60/65/60-2 RFGC

P1

19

20

DC HDG SIG

DC CRS SIG

13

HDG / CRS

RETURN

37 GROUND

SN3308

P2

DC HDG DATUM 26

SIGNAL GND

P1

4

SN3308

P2

DC HDG DATUM

DC CRS DATUM

26

7

SIGNAL GND

P1

4

S-TEC GPSS HEADING SYSTEM'S

S-TEC 20/30/40/50

J3

429 CONVERTER

2

3

23

DC HDG SIG

HDG / CRS

RETURN

SIGNAL GROUND

3

S-TEC 55/60/65/60-2

429 CONVERTER

J3

2 DC HDG SIG

4 DC CRS SIG

3

5

HDG / CRS

RETURN

23 GROUND

2

D

NOTES

1. SELECT KI525 FOR HSI EMULATION ON THE FCS MAINTENANCE PAGE.

SANDEL

Vista, Ca.

1

90106-10 G2

E C

4

4

3

2

1

A B C D E

DATE REV COMMENTS

10/04/02 G2 A/R 573 INITIAL RELEASE



A

SN3308

P2

AC HDG DATUM 26

AC CRS DATUM 7

400 Hz Excitation 4 400 HZ from Inverter

SEE NOTE 3&4

HDG SIG

ROLL COM

CRS SIG

ROLL COM

SN3308

P2

AC HDG DATUM 26

AC CRS DATUM 7

400 HZ INPUT 4

M4D AUTOPILOT

SEE NOTE 1

P3

6

P2

HDG DATUM HI

34 HDG DATUM LO

8 CRS DATUM HI

27 CRS DATUM LO

B

SEE NOTE 3&4

HDG SIG

ROLL COM

CRS SIG

ROLL COM

C

FCS-810 AUTOPILOT SEE NOTE 2

P1 z

HDG DATUM HI t

C

HDG DATUM LO

CRS DATUM HI

D

CRS DATUM LO

P6

X

BENDIX POWER SUPPLY

NOTES

1. SELECT PN101 FOR HSI EMULATION ON THE FCS MAINTENANCE PAGE.

2. SELECT IN831 FOR HSI EMULATION ON THE FCS MAINTENANCE PAGE.

3. ANY COMMERCIAL 75MW OR GREATER AUDIO TRANSFORMERS

MAY BE USED.

4. TRANSFORMERS ARE MAGNA-TEK TY-141P OR EQUIVALENT.

5. THE AUTOPILOT 400HZ IS THE MASTER INVERTER FOR THE SN3308.

2

SANDEL

Vista, Ca.

1

90106-10 G2

E D

3

4

A B C D

1

E

DATE REV COMMENTS

5/26/99 F INCORPORATED A/R 126 INITIAL RELEASE

10/23/00 G ADDED CONNECTION TO ONE PORT ONLY.



10/04/02 G2

9/24/03 G4

A/R 573 PAGE COUNT

A/R 661 ADDED GARMIN GNS 530



4

2

4

3

Connection to One

Port ONLY!

(9/27) OR (26/7)

SN3308

P3

Nav 429 In A Port 2/3

Nav 429 In B Port 2/3

9/26

27/7

429 Out A

429 Out B

11

29

GPS 429 In A Port 1

GPS 429 In B Port 1

10

28

THIS 6-WIRE INTERCONNECT PERFORMS THE FOLLOWING

GPS/VLOC AUTOPILOT SWITCHING

COURSE RESOLVER

DEVIATION

TO/FROM

FLAGS

ANNUNCIATORS

MODE SWITCHING

TO AUTOPILOT

GNS

430

P4006

GNS

530

P5006

24

23

24

23

GARMIN

VLOC 429 Out A

VLOC 429 Out B

P4001 P5001

48/50

49/51

48/50 GPS 429 In A 1/2

49/51 GPS 429 In B 1/2

46

47

46

47

GPS 429 Out A

GPS 429 Out B

MAIN PORT

ANALOG


Port ONLY!

(48/49) OR (50/51)

Notes:

1.

AUXILIARY MECHANICAL RESOLVER MAY BE USED ON THE 430

MAIN PORT.

2.

UNUSED ARINC PORT MAY BE USED FOR DME OR OTHER

ARINC 429 GPS.

3. MAINTENANCE PAGE ITEMS:

LNAV-1: GNS430 (ARINC)

NAV-1: ARINC 429 PORT 2 OR 3 AS WIRED

BRG NAV-1: 429

RELAY SENSE: NOT USED

4.

GARMIN SETUP ITEMS

SOFTWARE MAIN 2.07 OR LATER

MAIN ARINC-429 CONFIGURATION:

IN 1: LOW, SANDEL EHSI

OUT: LOW, GAMA 429 Graphics w/Int

SDI: LNAV 1 (SDI1)

VOR/LOC/GS ARINC-429 CONFIGURATION:

SPD RX: LOW

SPD TX: LOW

SDI: VOR/ILS 1 (SDI1)

Category

Title

Size

B

Document Number

Create: Thursday, January 07, 1999 Mod:

90106-10

Rev

G4

29

E

1

2

A B C D

3

3

4

A

SANDEL SN3308

429 OUT A

429 OUT B

P3

11

29

COMPOSITE IN 1

P1

29

GPS 429 IN A PORT 1

GPS 429 IN B PORT 1

P3

10

28

NAV 429 IN A PORT 2 9

NAV 429 IN B PORT 2 27

B

AUTOPILOT

P2

RCVR1/2 SENSE 12

P1

COMPOSITE IN 2 10

2

1

GPS 429 IN A PORT 3

GPS 429 IN B PORT 3

P3

26

7

GPS-2 RELAY 21

NAV-2 RELAY 5

RELAY

POWER

RCVR 1/2

PORT

SELECT


2700 AND ABOVE 250 ma MAX

A B

C

C

D

GNS

430

P4006

GNS

530

P5006

24

23

GARMIN #1

24

23

VLOC 429 OUT A

VLOC 429 OUT B

8 8 COMPOSITE OUT

P4001 P5001

46

47

46

47

GPS 429 OUT A

GPS 429 OUT B

48/50

49/51

48/50 GPS 429 In A 1/2

49/51 GPS 429 In B 1/2


Port ONLY!

(48/49) OR (50/51)

DATE

5/26/99

10/23/00

E

REV

F

COMMENTS

INCORPORATED A/R 126 INITIAL RELEASE

G ADDED CONNECTION TO ONE PORT ONLY. ADDED

MAX VOLTAGE FOR RELAY. MOVED RCVR1/2

SENSE TO P2. TOTAL SHEETS CHANGED TO 29.

A/R 360 PAGE COUNT 04/03/01 G1

10/04/02

9/24/03

G2

G4

A/R 573 PAGE COUNT




4

MAIN PORT

ANALOG

GNS

430

P4006

GNS

530

P5006

24

23

8

24

23

8

GARMIN #2

VLOC 429 OUT A

VLOC 429 OUT B

COMPOSITE OUT

P4001 P5001

48/50 48/50

49/51 49/51

GPS 429 In A 1/2

GPS 429 In B 1/2

46

47

46

47

GPS 429 OUT A

GPS 429 OUT B

MAIN PORT

ANALOG


Port ONLY!

(48/49) OR (50/51)

Notes:

1. AUXILIARY MECHANICAL RESOLVER MAY BE USED ON THE 430

MAIN PORT.

2. MAINTENANCE PAGE ITEMS:



NAV-1: 429 PORT-2

NAV-2: 429 PORT-2

BRG NAV-1: 429+COMP

BRG NAV-2: 429+COMP

RCVR 1/2 SENSE: ENABLED, SEE NOTE 3

3.

SENSE PINS SELECTED IN SOFTWARE SEE "RELAY SENSE"

MAINTENANCE PAGE DESCRIPTION IN APPENDIX A FOR LIST

OF SPECIFIC PINS.

4.

GARMIN SETUP ITEMS


MAIN ARINC-429 CONFIGURATION RECEIVER 1:



SDI: LNAV 1 (SDI1)


SPD RX: LOW

SPD TX: LOW





SDI: LNAV 2 (SDI2)


SPD RX: LOW

SPD TX: LOW


3

2

Category

Title

Size

B

Document Number


90106-10

Rev

G4

29

E

1

D

3

2

1

4

A/R 6XX ADDED GARMIN GNS 530

A


Port ONLY!

(9/27) OR (26/7)

SANDEL SN3308

P3

Nav 429 In A Port 2/3 9/26

Nav 429 In B Port 2/3 27/7

429 Out A

429 Out B

11

29

GPS 429 In A Port 1

GPS 429 In B Port 1

10

28

B

A

TO

AUTOPILOT

P1

COMPOSITE 2

ILS2 ENERGIZE

10

8

GS + Flag 15

GS - Flag 33

GS + Up 16

GS + Down 34

Nav + Flag 18

Nav - Flag 36

Nav + Left 37

Nav + Right 19

+TO

+FROM

17

35

NOTE 3

OBS Resolver (H) In 13

OBS Resolver (E)VREF In 28

OBS Resolver SIN Out 14

OBS Resolver COS Out 32

P2

NAV-2 SENSE X

P3

NAV-2 RELAY 5

PWR

B

C

GNS

430

P4006

GNS

530

P5006

24

23

24

23

GARMIN

VLOC 429 Out A

VLOC 429 Out B

P4001 P5001

48/50

49/51

48/50 GPS 429 In A 1/2

49/51 GPS 429 In B 1/2

46

47

46

47

GPS 429 Out A

GPS 429 Out B

MAIN PORT

ANALOG

D


Port ONLY!

(48/49) OR (50/51)

E

DATE REV COMMENTS


6/25/99 F(1) INCORPORATED A/R 151 SN3308 P3 PORT 1

AND PORT 2/3 REVERSED

10/23/00 G ADDED MAX VOLTAGE FOR RELAY. P1 16 AND 34

REVERSED ILS2 WAS ILS1. ADDED 220 OHM

RESISTOR. TOTAL SHEETS CHANGED TO 29.



9/24/03 G4 A/R 661 ADDED GARMIN GNS 530



4

TO AUTOPILOT

TO NAV-2

CONVERTER AS

REQ'D

NAV/GS

RECEIVER/CONVERTER

Composite Out

ILS 1

GS + Flag

GS - Flag

GS + Up

GS + Down

Nav + Flag

Nav - Flag

Nav + Left

Nav + Right

+TO

+FROM

SEE RESOLVER

INTERCONNECT FOR

DETAILS

3

NOTES

1. AUXILIARY MECHANICAL RESOLVER MAY BE USED ON THE 430

MAIN PORT.

2.

MAINTENANCE PAGE SETTINGS:


LNAV-2: (AS REQUIRED)

NAV-1: 429 PORT-2 OR PORT-3

NAV-2: ANALOG

BRG NAV-1: 429

BRG NAV-2: COMPOSITE

RELAY SENSE: NAV2 SENSE, SEE NOTE 3

3.

SENSE PINS SELECTED IN SOFTWARE SEE "RELAY SENSE" MAINTENANCE


4.

UNUSED ARINC PORT MAY BE USED FOR DME OR OTHER ARINC

429 GPS.

5.

GARMIN SETUP ITEMS





SDI: LNAV 1 (SDI1)


SPD RX: LOW

SPD TX: LOW


2

NAV-2 RELAY



C D

Category

Title

Size

B

Document Number


E

Rev

90106-10 G4

29

1

A B

1

2

4

3

SANDEL SN3308

429 OUT A

429 OUT B

P3

11

29

COMPOSITE IN 1

P1

29

P1

29

GPS 429 IN A PORT 1

GPS 429 IN B PORT 1

P3 P3

10

28

10

28

NAV 429 IN A PORT 2

NAV 429 IN A PORT 2

NAV 429 IN B PORT 2

NAV 429 IN B PORT 2

9

27

9

27

NOTE 3

NOTE 3

P2 P2

RCVR1/2 SENSE X

NAV-2 SENSE X

P1 P1

COMPOSITE IN 2 10 10

GPS 429 IN A PORT 3

GPS 429 IN B PORT 3

P3 P3

26

7

26

7

GPS-2 RELAY

NAV-2 RELAY

21

5

NAV-2 RELAY 5

AUTOPILOT

RELAY POWER

1-2 (PILOT) 1-2 (COPILOT)



C

C

D E

DATE REV COMMENTS


10/23/00 G ADDED MAX AMPERAGE TO RELAYS. RCVR1/2

SENSE AND NAV-2 SENSE WERE P3.




CORRECTED 430 MISLABELED

9/24/03 G4 A/R 661 ADDED GARMIN GNS 530



4

GNS

430

P4006

GNS

530

P5006

24

23

8

24

23

8

GARMIN #1

VLOC 429 OUT A

VLOC 429 OUT B

COMPOSITE OUT

P4001 P5001

48/50

49/51

48/50 GPS 429 In A 1/2

49/51 GPS 429 In B 1/2

46

47

46

47

GPS 429 OUT A

GPS 429 OUT B

MAIN PORT

ANALOG

GARMIN #2

P4006 P5006

24

23

24

23

VLOC 429 OUT A

VLOC 429 OUT B

8 8 COMPOSITE OUT

P4001 P5001

48/50 48/50

49/51 49/51

GPS 429 In A 1/2

GPS 429 In B 1/2

46

47

46

47

GPS 429 OUT A

GPS 429 OUT B

MAIN PORT

ANALOG


Port ONLY!

(48/49) OR (50/51)


Port ONLY!

(48/49) OR (50/51)

3

NOTES:

1.


MAIN PORT.

2. PILOT'S MP ITEMS:



NAV-1: 429 PORT-2

NAV-2: 429 PORT-2

BRG NAV-1 429+COMP

BRG NAV-2: 429+COMP

RELAY SENSE: RCVR 1/2 SENSE,

SEE NOTE 3

3.

3. COPILOT'S MP ITEMS:



NAV-1: 429 PORT-2

NAV-2: 429 PORT-2

BRG NAV1 : 429+COMP

BRG NAV2: 429+COMP

RELAY SENSE: NAV 2 SENSE,

SEE NOTE 3



4.

GARMIN SETUP ITEMS





SDI: LNAV 1 (SDI1)


SPD RX: LOW

SPD TX: LOW





SDI: LNAV 2 (SDI2)


SPD RX: LOW

SPD TX: LOW


2

Category

Title

Size

B

Document Number


90106-10

Rev

G4

29

E

1

D A B

4

A

SANDEL SN3308

429 OUT A

429 OUT A

429 OUT B

429 OUT B

P3

11

29

P3

11

29

COMPOSITE IN 1

P1

29

P1

29

GPS 429 IN A PORT 1

GPS 429 IN B PORT 1

P3 P3

10

28

10

28

1

3

2

NAV 429 IN A PORT 2

NAV 429 IN A PORT 2

NAV 429 IN B PORT 2

NAV 429 IN B PORT 2

9

27

9

27

CDI SRC SEL

CDI SRC SEL

P2 P2

X

X

NOTE 3

NAV-2 SENSE

NAV-2 SENSE

X

X

RCVR1/2 SENSE

X X

P1 P1

COMPOSITE IN 2 10 10

GPS 429 IN A PORT 3

GPS 429 IN B PORT 3

P3

26

7

P3

26

7

GPS-2 RELAY

NAV-2 RELAY

21

5

GPS-2 RELAY

NAV-2 RELAY

21

5

RELAY POWER

A

B C D

GNS

430

P4006

GNS

530

P5006

24

23

8

24

23

8

GARMIN #1

VLOC 429 OUT A

VLOC 429 OUT B

COMPOSITE OUT

E

DATE REV COMMENTS


10/23/00 G ALL P2 CONNECTIONS WERE P3. ADDED

CONNECTION TO ONE PORT ONLY. ADDED MAX

AMPERAGE TO RELAYS. TOTAL SHEETS CHANGED

TO 29.

04/03/01

10/04/02

9/24/03

G1 A/R 360 PAGE COUNT

G2 A/R 573 PAGE COUNT

G4

CORRECTED 430 MISLABELED


4



P4001 P5001

48/50

49/51

48/50 GPS 429 In A 1/2

49/51 GPS 429 In B 1/2

46

47

46

47

GPS 429 OUT A

GPS 429 OUT B

MAIN PORT

ANALOG

1-2 (PILOT) 1-2 (COPILOT) FCS PILOT /

COPILOT

AUTOPILOT

GNS

430

P4006

GNS

530

P5006

24

23

24

23

GARMIN #2

VLOC 429 OUT A

VLOC 429 OUT B



8 8

P4001 P5001

COMPOSITE OUT

48/50

49/51

48/50

49/51

GPS 429 In A 1/2

GPS 429 In B 1/2

46

47

46

47

GPS 429 OUT A

GPS 429 OUT B

MAIN PORT

ANALOG


Port ONLY!

(48/49) OR (50/51)

RCVR 1/2

SELECT


Port ONLY!

(48/49) OR (50/51)

NOTES:

1.


MAIN PORT.

2. PILOT'S MP ITEMS:



NAV-1: 429 PORT-2

NAV-2: 429 PORT-2

RMI1: 429+COMP

RMI2: 429+COMP

NAV2 SENSE: ENABLED

RCVR 1/2 SENSE: ENABLED

CDI SRC SEL: ENABLED

3. COPILOT'S MP ITEMS:



NAV-1: 429 PORT-2

NAV-2: 429 PORT-2

RMI1: 429+COMP

RMI2: 429+COMP

NAV2 SENSE: ENABLED

RCVR 1/2 SENSE: ENABLED

CDI SRC SEL: ENABLED

3.



2

Category

Title

Size

B

Document Number

Create: Saturday, January 09, 1999 Mod:

90106-10

Rev

G4

29

E

3

1

B C D

Sandel SN3308 Installation manual

SN3308 Navigation Display

Installation Manual

Document No. 90106-IM

Revision J

10-JUL-2008

Revision History

RTCA/DO-160C Environmental Qualification Form

Product nomenclature: SN3308 ColorMap Navigation Display

Vista, CA 92083

COMPANY NAME

COMPANY ADDRESS

TELEPHONE/FAX

Ground Test Procedures/Report for

Sandel Avionics SN3308

Installed in

{aircraft make and model}

Registration No. ________

SN3308 Serial No. ______________

Document No. ____________

Rev. - , Date

COMPANY NAME

COMPANY ADDRESS

TELEPHONE/FAX

Flight Test Procedures/Report for

Sandel Avionics SN3308

Installed in

{aircraft make and model}

Registration No. ________

Serial No. ______________

Document No. ____________

Rev. - , Date

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