Garmin G3X Touch Technical specifications

FLIGHT MANUAL STEMME S12
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This powered sailplane must be operated in compliance
with the instructions and limitations contained in the
associated Aircraft Flight Manual and this Supplement.
CONTACT
STEMME AG
Flugplatzstrasse F2, Nr. 6-7
D-15344 Strausberg
Phone: [phone]
E-mail: [e-mail]
Web: www.stemme.com
All rights reserved.
Reproduction or disclosure to third parties of this document
or any part thereof is not permitted, except with the prior
and express written permission of STEMME AG.

FLIGHT MANUAL STEMME S12
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0.1 Record of Revisions
The following table documents all revisions for the supplement S06 to the
Flight Manual for the aircraft STEMME S10, variant S12.
Minor revisions to the STEMME S12 Aircraft Flight Manual are approved and
countersigned by the Design Organization DOA EASA.21J.250 based on its
privileges.
All other revisions are approved by the Agency stating the EASA or FAA
approval number (countersigned by DOA EASA.21J.250.)
In the table hereafter only the latest approved revision must be
countersigned.
New or corrected text sections of the revised page(s) will be marked by a
vertical line on the outer side of the page. The newest revision number of
all revisions on the page is mentioned in the feedline-section of the page,
along with the date of the newest revision.
Compliance with the following information and the corresponding aircraft
is documented by the signature of the correcting person in the table.
Rev.
No. Re- moved
Pages
Inserted
Pages Date of Revision Reference Approval Date of Inser-
tation
Signa-
ture
Initial
Issue
Supersede
Issue
Feb 12 2018
REV03 All FEB 21, 2020 CN
2019-027
EASA:
10069765
FAA:
AT01070CE-G

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0.2 List of Effective Pages
This list is only valid for the aircraft serial number mentioned on the title
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FLIGHT MANUAL STEMME S12
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0.3 Contents
0.1 RECORD OF REVISIONS ......................................................................................0-3
0.2 LIST OF EFFECTIVE PAGES....................................................................................0-4
0.3 CONTENTS........................................................................................................0-6
1. GENERAL ......................................................................................................... 1-1
1.3 ABBREVATIONS..................................................................................................1-3
2. OPERATING LIMITATIONS............................................................................... 2-1
2.15 COCKPIT PLACARDS..........................................................................................2-2
3. EMERGENCY PROCEDURES............................................................................ 3-1
3.9 OTHER EMERGENCIES ........................................................................................3-1
3.9.4 System Malfunctions....................................................................................3-1
4. NORMAL OPERATING PROCEDURES ............................................................. 4-1
4.1 INTRODUCTION..................................................................................................4-1
4.1.1 Primary Flight Display...................................................................................4-4
4.1.2 GPS-Map.....................................................................................................4-13
4.1.3 Engine Indicating System..........................................................................4-15
4.1.4 Autopilot .....................................................................................................4-16
4.1.5 Autopilot Modes ........................................................................................4-22
4.4 AUTOPILOT PRE-FLIGHT INSPECTIONS..................................................................4-25
4.5 NORMAL OPERATIONS PROCEDURES AND RECOMMENDED AIRSPEEDS.................4-26
4.5.1 Engine Start, Warm-up and Taxi Procedures..........................................4-26
4.5.3 Cruise and Cross-country Flying...............................................................4-29
5. FLIGHT PERFORMANCE................................................................................... 5-1
6. MASS AND BALANCE ..................................................................................... 6-1
6.5 EQUIPMENT LIST.................................................................................................6-1
7. SYSTEM DESCRIPTION OF THE S12 AND ITS EQUIPMENT............................... 7-1
7.1 GENERAL DESCRIPTION......................................................................................7-1
7.1.1 Line Replaceable Units................................................................................7-1
7.1.2 System Architecture ....................................................................................7-5
7.1.3 Dependency of AHRS data........................................................................7-6
7.1.4 Restrictions....................................................................................................7-7
7.2 OPERATION ......................................................................................................7-8
7.2.1 General Operation......................................................................................7-8
7.2.2 PFD Operation and Control......................................................................7-13
7.2.3 Engine Indicating System Display ............................................................7-13
7.2.4 G3X Autopilot.............................................................................................7-13
7.3 Instrument Panel ........................................................................................7-15
8. HANDLING, MAINTENANCE AND SERVICING .............................................. 8-1

FLIGHT MANUAL STEMME S12
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1. General
This supplement extends the contents of the relevant sections of the basic
flight manual where additional information or instructions are necessary for
safe operation of the aircraft and a G3X system description installed in the
STEMME S12.
The G3X system consists of two main displays (LMFD and RMFD) and several
modular built sub-units. This electronic flight information system (EFIS) offers
4 main capabilities:
The first MFD (LMFD) works as a primary flight display (PFD) and is located
on the left side of the instrument panel. It provides in non-split-mode air
data, attitude and heading information.
The second MFD (RMFD) functions as engine indicating system (EIS) and is
located on the right side of the instrument panel. It provides in full screen
mode engine data, voltmeter and ammeter and fuel management
information.
Each MFD can be operated in individual split-modes, where more than the
initial function is displayed.
The G3X system is also capable to work as a GPS-Map. This function is
available on both displays.
The G3X system contains an integrated two-axis autopilot which is
operated only from the LMFD.
The G3X system is controlled by pushbuttons and rotary knobs located on
the main displays as well as by touch control of the main displays. The
decimal separator for displayed values is a “period”.
The G3X system does not control further electronic equipment.
The operating manual of the Garmin G3X System provides the basic
information for operation of the G3X units.
WARNING
The basic value setting of G3X-Touch-system is approved within the
certification process for the Stemme S12.
The unapproved changing of settings by the pilot is prohibited.
Any changes on basic settings can cause structural damages to the
aircraft, unexpected flight attitudes and/or additional pilot workload.

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The Garmin G3X system is specified for the following environmental
conditions:
Temperature: -30 °C / -22°F up to +50°C / 122 °F OAT
Altitude: up to 4870 m / 16.000 ft MSL
NOTICE
Altitudes in this manual may include a period instead of a comma to
separate the thousands digit. For example, 2.000 ft = 2,000 ft.
NOTICE
The Garmin G3X System is
approved as an additional, supporting
instrument.
Refer to the non-electric flight instruments for primary flight information.
WARNING
The components of the G3X system and its software level must be
approved by STEMME AG before installation (See STE
MME service
Bulletin P062-980024 Rev. 00 or later approved revisions).
WARNING
The installation of software levels not approved by STEMME can cause
malfunction of the autopilot system.

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1.3 Abbrevations
ADAHRS Air Data, Attitude and Heading Reference System
AGL Above Ground Level
CAS Crew Alerting System
EIS Engine Indicating System
GPS Global Positioning System
HSI Horizontal Situation Indicator
IAS
Indicated Airspeed
IMC Instrument Metrological Condition
LMFD Left Multifunction Display
LRU Line Replaceable Unit
MFD Multifunction Display
MSL Mean Sea Level
OAT Outside Air Temperature
PFD Primary Flight Display
RMFD Right Multifunction Display
TCU Turbo Control Unit
VFR Visual Flight Rules
VSI Vertical Speed Indicator

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FLIGHT MANUAL STEMME S12
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2. Operating Limitations
The following limitations apply to the operation of the autopilot:
Speed
(IAS)
Remarks
V
AP+
Maximum speed for
operation of the
autopilot
240 kph
130 kt
Maximum approved
speed for safe use of the
autopilot
V
AP-
Minimum speed for
operation of the
autopilot
130 kph
70 kt
Minimum approved speed
for safe use of the
autopilot
WARNING
The autopilot system is only approved for powered flight operations
under VFR-DAY conditions.
WARNING
Flights under IMC, approach procedures and flights below 600 m /
2.000 ft AGL are prohibited!
Further limitations are:
Maximum Altitude: 4780 m / 16.000 ft MSL
Flap positions: -10° up to +5°

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2.15 Cockpit Placards
Placards Location
Top forward center
console [8]
8

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3. Emergency Procedures
3.9 Other Emergencies
3.9.4 System Malfunctions
3.9.4.1 Fuel Pressure
The fuel pressure indicator features a bar-graph display.
Garmin G3X-System indications are set to the permissible BRP-ROTAX fuel
pressure values:
•Low fuel pressure: <0.15 bar
•Normal fuel pressure: between 0.15 bar and 0.35 bar
•High fuel pressure: >0.35 bar
Refer to Basis Aircraft Flight Manual section 3.9.4.1 fuel pressure for related
emergency procedures.

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3.9.4.21 Abnormal Operation of the G3X Touch System
Red X:
When a line replaceable unit (LRU) or a LRU function fails, a large red ‘X’ is
typically displayed over the instrument(s) or data experiencing the failure.
Upon G3X power-up, certain instruments remain invalid as equipment
begins to initialize. All instruments should be operational within one minute
of power-up. If any instrument remains flagged, the G3X Touch should be
serviced.
Crew Alerting System (CAS):
System malfunctions will also be announced by the Crew Alerting System
(CAS) on the MFD’s in PFD-mode. The CAS Annunciation window location
is depending on screen size.
CAS messages are grouped by criticality (warning, caution, advisory and
safe):
•WARNING (red) Requires immediate attention. Warning
messages will flash until acknowledged by
pressing the BACK Key or touching the on-
screen message.
•CAUTION (yellow): Requires pilot awareness and possible future
corrective action.

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•ADVISORY (white): Provides general information.
•SAFE (green): Indicates a safe condition.
CAS Messages will appear to the right of the Horizontal Situation Indicator.
(HSI) Touch on an active CAS message to acknowledge it.
CAS Annunciation includes exceedance of engine parameters monitored
by the GARMIN Engine Indication System (EIS).
Indication of Unusual Attitudes:
The Attitude Indicator includes permanent red warning chevrons to
indicate extreme pitch angles. A series of downward-pointing chevrons
appear at 50˚ above the horizon line, and upward-pointing chevrons at
30˚ below the horizon line.

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System Status Message Box:
If an abnormal behavior is recognized by the G3X Touch self-test
capability, it will be announced in the System Status Message Box. A yellow
(Messages) alert will flash at the bottom of the display.
To access a message:
•Touch Messages at the bottom of the screen to view messages.
•Touch Messages again to remove the messages.
GPS Status Indication:
The GPS status icon is located on the in left half of the HSI. The GPS status
icon and GPS related data is colored in magenta.
In case of loss of GPS satellite reception, the GPS status icon in the HSI will
disappear and GPS-related data will not be displayed. Persistent loss of
GPS satellite reception and GPS unit malfunctions will be announced in the
System Status Message Box.

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A red X will be displayed over the aircraft icon on the map page
A red X will be displayed over the whole terrain page.
Engine Parameters:
A red flashing engine value indicated exceedance of allowed engine
parameters.

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Autopilot Cautions and Warnings:
Autopilot-related cautions are indicated in black letters in yellow boxes
either in the autopilot status box or above the pitch scale.
Autopilot-related warnings are indicated in black letters in red boxes in the
autopilot status box.
Reversionary Mode:
In the event of a display failure, the G3X Touch System automatically
switches to reversionary (backup) mode. In reversionary mode, the
information is presented on the remaining display in the split-screen
configuration.
In the event of an LMFD failure, the RMFD switches to reversionary mode,
and the autopilot is disengaged.
If the RMFD fails, the LMFD switches to reversionary mode and the autopilot
continues to function.

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3.9.4.22 Loss of One or Both Display Units
In the case of loss of the LMFD the autopilot is automatically disengaged
and the display of navigation data is disabled. The remaining RMFD
switches to reversionary mode and displays the PFD and the engine data
in split screen mode.
If the autopilot is not automatically disengaged, proceed according
section
•3.9.4.23 Loss or Malfunction of autopilot control
If the PFD is not displayed on the RMFD, proceed according sections
•3.9.4.24 Loss or Malfunction of ADAHRS on primary flight display
In the case of loss of the RMFD the LMFD switches to reversionary mode
and displays the engine data and the PFD in split screen mode. If the
engine data are not displayed on the LMFD, proceed according section
• 3.9.4.26 Loss or malfunction of engine indicating system
If both MFD units fail, proceed according the following sections.
3.9.4.23 Loss or Malfunction of Autopilot Control
Loss or malfunction of Autopilot is indicated by:
•The autopilot alert message window
•The autopilot status box
Display of AP alert messages
In each case of a displayed alert message proceed as follows:
•Quick Disengage on stick:PUSH.
•Garmin PFD-screen DISENGAGE autopilot using the AP
control panel if quick disengage fails.
WARNING
By using the “Quick Disengage Button” the aircraft can be mis-trimmed.
Always keep hand on stick while disconnecting.

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Jamming actuator:
The system can be overridden by hand. In the case of a jamming actuator
during a manually controlled flight, proceed as follows:
• Slip Clutch: OVERPOWER actuator by hand and
continue flight manually.
• Landing: PREPARE for a landing at the next suitable
airfield.
In case of a jamming actuator during an autopilot supported flight,
proceed as follows:
•Quick disengage on stick:PUSH.
•Garmin PFD-screen: DISENGAGE autopilot
if controls are still jammed
•LMFD and RMFD: Turn PFD and MFD unit switch OFF
if controls are still jammed.
•PFD circuit breaker: PULL.
•Slip clutch: OVERPOWER actuator by hand and
continue flight manually.
•Landing: PREPARE for a landing at the next suitable
airfield.
WARNING
By using the “Quick Disengage Button” the aircraft can be mis-trimmed.
Always keep hand on stick while disconnecting.
CAUTION
Steering the aircraft while overpowering autopilot actuators requires
distinctly increased hand-forces than normal operation.
NOTICE
The Garmin G3X System is not approved as a primary flight instrument.
Refer to the instruments intended for use as primary flight instruments.