Genesys S-TEC 3100 Owner's manual

S-TEC 3100 Digital and Analog
Flight Control System
S-TEC 3100
Digital and Analog
Flight Control System
Pilot Guide
PRECISE PERFORMANCE.
PROVEN EXPERIENCE.
PERSONALIZED ATTENTION.

S-TEC 3100 Digital and Analog
i2nd Ed Aug 2019 S-TEC 3100 Digital and Analog
Pilot Operating Guide
and Reference
Digital Flight Control System
S-TEC 3100 Digital and Analog
Doc No 87325
This pilot guide must be carried in the aircraft and available to the
pilot at all times. It can only be used in conjunction with the Federal
Aviation Administration (FAA) approved Aircraft Flight Manual (AFM)
or Aircraft Flight Manual Supplement (AFMS). Refer to the applicable
AFM or AFMS for aircraft specic information, such as unique ground
tests, limitations, and emergency procedures.
© 2019 Genesys Aerosystems. All Rights Reserved.
Information contained in this document is subject to change without notice.
No part of this document may be reproduced in any form, or by any means,
without prior written consent of Genesys Aerosystems.
Printed in the United States of America. Genesys Aerosystems and S-TEC
logo are registered trademarks of Genesys Aerosystems. All other brand
names and trademarks are the property of their respective holders.
For service or repairs, contact an authorized Genesys Aerosystems
dealer. For product support, contact Genesys Aerosystems.
One S-TEC Way, Municipal Airport, Mineral Wells TX 76067
Phone: [phone] Fax: [phone]
www.genesys-aerosystems.com

S-TEC 3100 Digital and Analog
2nd Ed Aug 2019
S-TEC 3100 Digital and Analog
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Revision Record
Retain this record in front of guide.
Revision
Number Revision Date Notes/Pages changed, added, or deleted by current revision
1st Ed. February 2018
Rev A November 2018
2nd Ed. August 2019

S-TEC 3100 Digital and Analog
iii2nd Ed Aug 2019 S-TEC 3100 Digital and Analog
Table of Contents
Section 1 Overview
1.1. Document Organization.................................................................. 1-1
1.2. Purpose .......................................................................................... 1-1
1.3. General Control Theory .................................................................. 1-1
1.4. Limitations ...................................................................................... 1-2
1.4.1. Altitude Pre-Select Limitations .............................................. 1-2
1.4.2. Indicated Airspeed Mode (IAS) and Envelope Protection
Limitations........................................................................................ 1-2
1.4.3. Optional Yaw Damper (YD)................................................... 1-2
1.5. Autopilot Modes.............................................................................. 1-3
1.6. System Components ...................................................................... 1-4
1.6.1. S-TEC 3100 Flight Guidance Computer (FGC) .................... 1-4
1.6.2. Aircraft Conguration ............................................................ 1-4
1.6.3. Interface Conguration.......................................................... 1-5
1.6.4. Servo Assemblies ................................................................. 1-5
1.6.5. Sandia Air Data Computer .................................................... 1-5
1.6.6. GPS 1/2 Selector Switch....................................................... 1-5
1.7. Interfaced Avionics ......................................................................... 1-6
1.7.1. Garmin G500/G600/TXi EFIS ............................................... 1-6
1.7.2. Aspen EFD 500/1000/MAX ................................................... 1-6
1.7.3. Avidyne EXP5000 and Meggitt EFIS .................................... 1-7
1.7.4. Analog DG/HSI...................................................................... 1-7
1.8. Display Legend............................................................................... 1-8
Section 2 Pre-Flight Procedures
2.1. Power-Up Test ................................................................................ 2-1
2.2. Pre-Flight Checks........................................................................... 2-2
Section 3 In-Flight Procedures
3.1. Engaging the Autopilot.................................................................... 3-1
3.1.1. Roll Attitude (ROLL) Mode .................................................... 3-1
3.2. Disconnecting the Autopilot ............................................................ 3-1
3.3. Autopilot (AP) Operation................................................................. 3-2
3.4. Flight Director (FD) Operation ........................................................ 3-2
3.5. Yaw Damper (YD) Operation.......................................................... 3-3
3.6. Envelope Protection ....................................................................... 3-3
3.6.1. Envelope Speeds for FIKI Aircraft......................................... 3-4
3.6.2. Passive Envelope Protection ................................................ 3-4
3.6.2.1. Passive Envelope Protection on Approach.................. 3-4
3.6.3. Active Envelope Protection ................................................... 3-4
3.6.3.1. Active Envelope Protection on Approach..................... 3-5
3.6.4. “AP ICE SPEED” (FIKI Aircraft Only) .................................... 3-6

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3.7. Lateral Modes................................................................................. 3-6
3.7.1. Roll Hold (ROLL) Mode......................................................... 3-7
3.7.2. Heading (HDG) Mode ........................................................... 3-7
3.7.3. Navigation (NAV) Mode ........................................................ 3-7
3.7.3.1. Tracking a VOR (NAV)................................................. 3-8
3.7.3.2. GPS Steering (NAVGPSS) Mode .................................... 3-9
3.7.4. Approach (APR) Mode .......................................................... 3-9
3.7.4.1. VOR Approach (APR)................................................ 3-10
3.7.4.2. ILS Approach (APRLOC)...............................................3-11
3.7.4.3. GPS RNAV Approach (APRGPSS/APRGPSL)................. 3-12
3.8. Vertical Modes.............................................................................. 3-14
3.8.1. Pitch Attitude (PITCH) Mode............................................... 3-14
3.8.2. Indicated Airspeed (IAS) Mode ........................................... 3-15
3.8.3. Vertical Speed (VS) Mode................................................... 3-15
3.8.4. Altitude Hold (ALT HOLD) Mode ......................................... 3-16
3.8.5. Altitude Pre-Select .............................................................. 3-16
3.8.5.1. No Altitude Pre-Select (Manual Altitude Capture)...... 3-17
3.8.5.2. S-TEC 3100 Internal Altitude Pre-Select ................... 3-18
3.8.5.3. S-TEC ST 360 Altitude Selector/Alerter..................... 3-19
3.8.5.4. Garmin G500/G600/TXi Pre-Select ........................... 3-19
3.9. Additional Modes .......................................................................... 3-20
3.9.1. Control Wheel Steering (CWS) Mode ................................. 3-20
3.9.2. Go-Around (GA) Button ...................................................... 3-21
3.9.3. Take-O󰀨-Go-Around (TOGA) .............................................. 3-21
3.9.4. Level (LVL) Mode ................................................................ 3-22
3.9.4.1. Emergency Level Mode............................................. 3-22
3.9.5. Half Bank (HB) Mode .......................................................... 3-23
3.9.6. Menu (MNU) Button ............................................................ 3-23
3.9.7. Maintenance Mode ............................................................. 3-24
3.10. Trim............................................................................................. 3-24
3.10.1. Automatic Trim Annunciations........................................... 3-24
3.10.2. Manual Trim Annunciations............................................... 3-25
3.10.3. Manual Electric Trim ......................................................... 3-25
3.10.4. Automatic Trim Disable ..................................................... 3-25
Section 4 Emergency Procedures
Section 5 Operating Parameters
5.1. Roll Axis Limits ............................................................................... 5-1
5.2. Pitch Axis Limits.............................................................................. 5-1
5.3. Level Mode Recovery..................................................................... 5-1
5.4. Envelope Speed Limits................................................................... 5-1
Section 6 Glossary

S-TEC 3100 Digital and Analog
v2nd Ed Aug 2019 S-TEC 3100 Digital and Analog
List of Figures and Tables
Figure 1-1: S-TEC 3100 Without Optional Yaw Damper ........................ 1-2
Figure 1-2: S-TEC 3100 Flight Guidance Computer (FGC) ................... 1-4
Figure 1-3: S-TEC 3100 Servos ............................................................. 1-5
Figure 1-4: Sandia SAC7-35 .................................................................. 1-5
Figure 1-5: Display Legend .................................................................... 1-8
Figure 3-1: Roll Attitude (ROLL) Mode ................................................... 3-1
Figure 3-2: Without Optional Yaw Damper Installed............................... 3-3
Figure 3-3: ALERT.................................................................................. 3-5
Figure 3-4: Roll Attitude (ROLL) Mode ................................................... 3-7
Figure 3-5: Heading (HDG) Mode .......................................................... 3-7
Figure 3-6: VOR Approach ....................................................................3-11
Figure 3-7: Straight-In ILS Approach.....................................................3-11
Figure 3-8: RNAV Approach Procedure................................................ 3-13
Figure 3-9: Pitch Attitude (PITCH) Mode.............................................. 3-14
Figure 3-10: Indicated Airspeed (IAS) Mode ........................................ 3-15
Figure 3-11: Vertical Speed (VS) Mode ................................................ 3-15
Figure 3-12: Altitude Hold (ALT HOLD) Mode ...................................... 3-16
Figure 3-13: Altitude Pre-Select............................................................ 3-16
Figure 3-14: No Altitude Pre-Select...................................................... 3-17
Figure 3-15: Target Altitude in ft. with ALT HOLD Mode Armed............ 3-18
Figure 3-16: S-TEC ST 360 Altitude Selector/Alerter, 3100 Display..... 3-19
Figure 3-17: Target Altitude Not Displayed ........................................... 3-19
Figure 3-18: Control Wheel Steering (CWS) Mode .............................. 3-20
Figure 3-19: Go-Around (GA)............................................................... 3-21
Figure 3-20: Level Mode, Roll and Pitch Hold Modes .......................... 3-22
Figure 3-21: Emergency Level Mode; Servos Engaged, No AP........... 3-23
Figure 3-22: HB Mode Switch/Annunciator .......................................... 3-23
Figure 3-23: Mute Icons........................................................................ 3-24
Figure 3-24: Unmute Icon on 3100 Display.......................................... 3-24
Figure 3-25: Pitch Trim Annunciations.................................................. 3-25
Figure 3-26: Manual Electric Trim......................................................... 3-25

Section 1 Overview
1-12nd Ed Aug 2019 S-TEC 3100 Digital and Analog
Section 1 Overview
1.1. DOCUMENT ORGANIZATION
Section 1 Overview
Section 2 Pre-Flight Procedures
Section 3 In-Flight Procedures
Section 4 Emergency Procedures
Section 5 Operating Parameters
Section 6 Glossary
1.2. PURPOSE
This pilot guide provides pre-ight and in-ight operating procedures for the
S-TEC 3100 autopilot (3100) for both digital and analog interfaced systems.
NOTE:
The S-TEC 3100 is designed to assist pilots with cockpit workload
management. The ability of the 3100 to provide optimum assistance
and performance is directly proportional to the pilot’s knowledge of its
operating procedures. Therefore, it is highly recommended that the pilot
develop a thorough understanding of the 3100, its modes, and operating
procedures in visual meteorological conditions (VMC) prior to using it
under instrument ight rules (IFR).
1.3. GENERAL CONTROL THEORY
The S-TEC 3100 is capable of being a two- or three-axis attitude-based
digital ight control system. It is comprised of a computer/programmer,
which performs input/output processing and control laws, and an integrated
bezel/display for mode selection and display, including trim annunciations.
S-TEC servos are coupled to the control system:
Roll Servo: Coupled to the ailerons. The 3100 senses roll attitude, roll rate,
heading error, and course deviation to control the roll servo.

Section 1 Overview
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S-TEC 3100 Digital and Analog
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Pitch Servo: Coupled to the elevator. The 3100 senses pitch attitude,
pitch rate, pressure altitude, indicated airspeed (IAS), vertical speed (VS),
vertical acceleration, and glideslope deviation to control the pitch servo.
Trim Servo: Coupled to the elevator trim. The 3100 senses an out of
trim condition whenever the trim sensor in the pitch servo is activated. In
response, the 3100 drives the trim servo in the proper direction until the
aircraft is in trim.
Yaw Servo (optional): Coupled to the rudder. The 3100 senses yaw rate
and acceleration to control the yaw servo.
The 3100 also includes an altitude pre-select function, if enabled.
1.4. LIMITATIONS
1.4.1. Altitude Pre-Select Limitations
The S-TEC 3100 relies on digital air data information for altitude pre-select.
Some congurations may not have altitude pre-select if the baro-correction
cannot be provided to the autopilot system.
1.4.2. Indicated Airspeed Mode (IAS) and Envelope Protection
Limitations
The S-TEC 3100 relies on digital air data information for indicated air
speed hold (IAS). Some congurations may not have IAS mode if indicated
airspeed data is not provided to the autopilot system.
Overspeed and underspeed protection is not be available for systems
without indicated airspeed.
1.4.3. Optional Yaw Damper (YD)
Some aircraft congurations do not have a yaw damper system installed.
In these cases, the yaw damper button is blank and the YD LED does not
illuminate under any circumstances.
Figure 1-1: S-TEC 3100 Without Optional Yaw Damper

Section 1 Overview
1-32nd Ed Aug 2019 S-TEC 3100 Digital and Analog
1.5. AUTOPILOT MODES
Autopilot (AP) Mode: Engages autopilot servos
Flight Director (FD) Mode: Drives steering command bars (ight director
or electronic ight instrument system (EFIS) required)
Yaw Damper (YD) Mode: Dampens excessive adverse yaw and coordinates
turns (if installed)
Roll Attitude (ROLL) Mode: Holds roll attitude
Pitch Attitude (PITCH) Mode: Holds pitch attitude
Heading (HDG) Mode: Turns onto a selected heading and holds it
Navigation (NAV) Mode: Intercepts and tracks a VOR course
Approach (APR) Mode: Intercepts and tracks a LOC front course or GPS
approach inbound
Glideslope (GS) Mode: Intercepts and tracks glideslope
Level (LVL) Mode: Returns aircraft to level ight and a congured pitch
angle for the aircraft (refer to AFMS for pitch angle value)
Indicated Airspeed (IAS) Mode: Holds indicated airspeed
Vertical Speed (VS) Mode: Holds vertical speed
Altitude Hold (ALT HOLD) Mode: Holds altitude
GPS Steering (GPSS) Mode: Laterally steers along a ight plan course
dened by GPS/FMS
GPS Lateral Navigation (GPSL) Mode: Laterally steers along an approach
course dened by GPS/FMS approach
GPS Vertical Navigation (GPSV) Mode: Vertically steers along a glidepath
dened by a GPS/FMS approach
Reverse (REV) Mode: Intercepts and tracks a LOC back course (BC)
inbound or tracks a LOC front course outbound
Control Wheel Steering (CWS) Mode: Used to temporarily disengage
servos and manually maneuver the aircraft or set new targets
Go-Around Mode (GA) Mode: Disengages AP and/or engages FD in pitch
hold mode with a pre-set nose-up command

Section 1 Overview
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S-TEC 3100 Digital and Analog
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Half Bank (HB) Mode: Reduces commands in HDG and GPS/FMS steering
by half (if installed)
Automatic Trim Mode: Automatically drives pitch trim servo.
1.6. SYSTEM COMPONENTS
1.6.1. S-TEC 3100 Flight Guidance Computer (FGC)
The S-TEC 3100 FGC is the main processing unit for the autopilot system.
It controls all of the input/output processing, control law calculation, and
drives up to four servos (pitch, roll, yaw and pitch trim).
Figure 1-2: S-TEC 3100 Flight Guidance Computer (FGC)
The FGC requires navigational and target data to provide the correct servo
drive signals. Mode selection may be controlled through the front panel.
The S-TEC 3100 has an on-board MEMS device that calculates attitude
angles and rates in the pitch, roll, and yaw axis. This may be congured
to act as the primary or single source of attitude on certain interface
congurations.
NOTE:
Each S-TEC 3100 is loaded with a single conguration le, which
contains aircraft and interface conguration data to match the
installation. Any future avionic upgrades on equipment interfaced to the
autopilot may require a new conguration le to be uploaded.
1.6.2. Aircraft Conguration
The aircraft conguration contains specic gains and servo drive values
to match the aircraft ight characteristics. Gain values are specically
setup during STC ight testing and are calculated for the optimum ight
performance of each aircraft model/type.