Sandel SG102 AHRS Manual

82011-PG-ERR-E4 SANDEL SG102 PG ERRATA PAGE 1 OF 2
SG102 AHRS
Pilot’s Guide Effectivity and Errata
Insert this update ahead of the cover page of the Pilot’s Guide referenced
below.
Date:
Effectivity:
Errata:
10-MAY-2016
Pilots Guide 82011-PG-E
SG102 Software Version 1.35 for SG102 (Mod 1)
SG102 Software Version 1.62 for SG102 (Mod 2)
SG102 Software Version 1.62 for SG102/D
MT102 Software Version 1.00
With the exception of the superseding information
contained in this document, operation of the SG102 is as
described in the SG102 Pilot’s Guide referenced above.
82011-PG-ERR-E4 SANDEL SG102 PG ERRATA PAGE 2 OF 2
Chapter 1 Limitation #3 regarding aerobatic flight should be updated to
read as follows:
Aerobatics: Permitted, software version 1.25 and later. Aerobatic
maneuvers must be approximately wings level 50% of the time over any 5
minute period.
Chapter 2 “Power Interruptions” statement should be updated to read as
follows:
The SG102 can recover from momentary power interruptions in flight
without losing its initialization. If extended power interruptions are
experienced and the gyro flag remains, it will be necessary to use an
alternate means of primary heading information for the remainder of the
flight.

SG102
Attitude Heading Reference System
Pilot’s Guide
Revision E
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Pilot information
Original Publication Date: 10 APR 2014
This guide provides information on the use and operation of the SG102
Attitude Heading Reference System.
Information in this guide is current as of publication or revision date.
Specifications and operational details are subject to change without notice
at the discretion of Sandel Avionics, Inc.
Copyright
Copyright 2014 Sandel Avionics, Inc.
May be covered by one or more US and foreign patents (pending).
All rights reserved. No part of this manual may be reproduced, stored or
distributed without written permission of Sandel Avionics, Inc. Additional
copies of this manual are available from:
Sandel Avionics, Inc.
2401 Dogwood Way
Vista, CA 92081
USA
Tel: [phone]
Fax: [phone]
www.sandel.com
Revision notice
The “Effectivity, Errata, and Revision History” allow the use of this Pilot
Guide with a specific software release. The “Effectivity, Errata, and
Revision History” specifically lists the software to which this Pilot’s Guide
applies and corrects any errors or omissions in this revision of the Pilot’s
Guide. Document number 82011-PG-ERR, Effectivity, Errata, and
Revision History” can be found on page VI of this Pilot’s Guide.
Operational and legal issues
The information provided by the SG102 is displayed by external
equipment. It is the pilot’s responsibility to ensure the correct
configuration and use of the external equipment. Always refer to your
approved Aircraft Flight Manual Supplement for operation and limitations
on the use of installed equipment.
Note: Because aircraft vary in their installed equipment, it is important to
note that what is displayed by the information provided by the SG102 may
vary depending on the presence or absence of equipment.
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Approvals
The FAA has approved the SG102 under the following TSOs:
TSO-C4c Bank and Pitch Instruments
TSO -C6d Direction Instrument, Magnetic (Gyroscopically Stabilized)
The following RTCA Standards apply to this product:
DO-160E: Environmental (See Installation Manual)
DO-178B Software Level C
Installation of the SG102 Attitude Heading Reference System in a type-
certificated aircraft must be performed in accordance with the Sandel
SG102/MT102 Installation Manual, document number 82011-IM (latest
revision).
Conventions Used in This Manual
This manual uses terms, which should be familiar to aviation-minded
readers, such as “magnetic heading” and “gyro”. Terms, which are
specific to the SG102, will be placed in the glossary.

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Table of Contents
Pilot information iii
Copyright iii
Revision notice iii
Operational and legal issues iii
Approvals iv
Conventions Used in This Manual iv
Table of Contents v
Effectivity, Errata and Revision History vi
CHAPTER 1 WELCOME TO THE SG102 1-1
What is the SG102? 1-1
Limitations 1-1
CHAPTER 2 OPERATION 2-1
NORMAL OPERATION 2-1
ABNORMAL OPERATION 2-2
CHAPTER 3 TECHNICAL SPECIFICATIONS 3-1
CHAPTER 4 INSTALLATION INFORMATION 4-1
CHAPTER 5 GLOSSARY 5-1
CHAPTER 6 AVIONICS ACRONYMS 6-1
82011-PG-E SANDEL SG102 PILOT’S GUIDE PAGE VI
Effectivity, Errata and Revision History
Applies to: SG102/D
SG102 (Mod 1 & Mod 2)
MT102
With the exception of the superseding information contained in this
section, operation of the SG102 is as described in the SG102 Pilot’s Guide
referenced above.
Revision Date Comments
E 10-APR-2014
Effectivity, Errata and Revision History
updated.
Previous Errata incorporated.
Page 1-1: SG102/D and SG102 Mod 2
information added.
Page 2-1: Initialization information
updated.
Page 2-2: Power Interruptions
description updated.
Page 3-1: Operational Specifications
removed.
Page 4-1: Line for Mod level added.
D4 16-FEB-2011 Updated for software release 1.31
D3 03-NOV-2009 Updated for software release 1.30
D2 22-MAY-2009 Updated for software release 1.26
D1 07-MAY-2009 Updated for software release 1.25
D 11-FEB-2009 Updated copyright.
Errata removed.
Updated limitations.
C 06-NOV-2008 Page 2-1 Preflight Initialization period;
Errata updated.
B 31-OCT-2008 Page vi: Updated for software release
1.10 and SG102 Mod 1; Errata updated.
A 18-DEC-2008 Initial Release
Errata
None

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CHAPTER 1 WELCOME TO THE SG102
What is the SG102?
The Sandel model SG102 is a solid-state Attitude Heading Reference
System (AHRS) that combines angular rate, linear acceleration and
magnetic field measurements to provide primary heading information.
Roll and pitch information is provided for stabilization of other equipment
such as weather RADAR or FLIR cameras etc.
Limitations
1. For SG102/D, and SG102 (Mod 1 and Mod 2): The roll and
pitch information provided by the SG102 may not be used to
display primary aircraft attitude to the aircrew. The roll and
pitch information may be used to display reversionary or
backup attitude information to the flight crew in the primary
field of view.
2. For SG102 Mod 0: The roll and pitch information provided
by the SG102 may not be used to display aircraft attitude to
the aircrew.
3. The SG102 is not approved for aerobatic flight.
4. The SG102 may not provide satisfactory heading
performance above 70° north latitude or below 70° south
latitude.
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CHAPTER 2 OPERATION
NORMAL OPERATION
Flying an aircraft equipped with an SG102 does not require any special
piloting skills; however there are a few key points for the pilot:
Preflight:
Refer to the Approved Flight Manual Supplement for the SG102.
Initialization periods (at 15°C):
oMod 0 (S/Ns below 11-2500 - Units shipped prior to
11/28/2008): 4-5 minutes.
oMod 1 (S/Ns 11-2500 to 11-3045): less than 3 minutes.
oMod 2 (S/Ns 11-3100 and above): approximately 1
Minute
oSG102/D: approximately 1 Minute
During the initialization period the aircraft should not be moved.
When the Flag is removed from the heading display, the SG102
initialization is complete.
In Flight:
The SG102 supports two slaving modes: “Slaving ON” and
“Slaving OFF”. The “Slaving OFF” mode requires the installation
of Pilot-operated slaving switches.
Under normal conditions the SG102 should be operated with
“Slaving ON”, by moving the Slaving selector switch to the “ON”
position.
To operate in the “Slaving OFF” mode, move the Slaving selector
switch to the “OFF” position. The heading display can now be
adjusted with the CW or CCW manual slew switches as desired.
All displays driven by the SG102 will track the adjusted heading.
Move the Slaving On switch to the ON position to restore slaving
operation. All indicators will immediately slew to the current
magnetic heading.
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ABNORMAL OPERATION
Outputs Flagged
If the SG102 is inoperative or detects an internal error, all outputs will be
flagged. Reference to an alternate heading source must be made.
Power Interruptions
The SG102 can withstand power interruptions of up to 30 seconds in flight
without losing its initialization. If longer power interruptions are
experienced and the gyro flag appears, it will be necessary to use an
alternate means of primary heading information for the remainder of the
flight.

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CHAPTER 3 TECHNICAL SPECIFICATIONS
TSO Compliance
Technical
Standard Order
(TSO):
TSO-C4c “Bank and Pitch Instruments”
TSO-C6d “Direction Instrument, Magnetic
(Gyroscopically Stabilized)”
Software
Certification: RTCA/DO-178, Level C
Environmental
Category:
RTCA DO-160E
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CHAPTER 4 INSTALLATION INFORMATION
To be completed by installer.
Date of Installation: _____________________________________
Installer Company: _____________________________________
Installer Address:
______________________________________________________
______________________________________________________
______________________________________________________
Installer Phone: ________________________________________
Work Order #: __________________________________________
Installer: ______________________________________________
Notes: ______________________________________________________
______________________________________________________
______________________________________________________
______________________________________________________
Mod level:
______________________________________________________
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CHAPTER 5 GLOSSARY
Magnetometer A device that measures the earth’s magnetic field
Failure The inability of the equipment or any sub-part of that
equipment to perform within specified limits.
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CHAPTER 6 AVIONICS ACRONYMS
AFM Airplane Flight Manual
AFMS Airplane Flight Manual Supplement
AHRS Attitude Heading Reference System
FAA Federal Aviation Administration
HDG Magnetic Heading
POH Pilot’s Operating Handbook
RTCA Radio Technical Commission on Aeronautics (rtca.org)
TSO Technical Standard Order
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