Midcontinent MD23 Series Technical Document

Manual Number
9019161
Revision A
September 9, 2020

Manual Number 9019161 Revision A, September 9, 2020 2
FOREWORD
This manual provides information intended for use by persons who, in accordance with current
regulatory requirements, are qualified to install this equipment. If further information is required,
please contact:
Mid-Continent Instruments and Avionics
Attn: Customer Service Dept.
9400 E. 34th St. N.
Wichita, KS 67226 USA
Phone [phone]
Fax [phone]
ks.customerse[email protected]m
www.mcico.com
We welcome your comments concerning this manual. Although every effort has been made to keep
it free of errors, some may occur. When reporting a specific problem, please describe it briefly and
include the manual part number, the paragraph/figure/table number, and the page number. Send
your comments to:
Mid-Continent Instruments and Avionics
Attn: Customer Service Dept.
9400 E. 34th St. N.
Wichita, KS 67226 USA
Phone [phone]
Fax [phone]
ks.customerse[email protected]m
© Copyright 2020
Mid-Continent Instrument Co., Inc.

Manual Number 9019161 Revision A, September 9, 2020 3
REVISION HISTORY
Rev
Date
Detail
Approved
A
09/09/2020
Production release.
BAW

Manual Number 9019161 Revision A, September 9, 2020 4
TABLE OF CONTENTS
SECTION 1 GENERAL DESCRIPTION 5
INTRODUCTION 5
TECHNICAL SPECIFICATIONS 6
SECTION 2 PRE-INSTALLATION CONSIDERATIONS 7
COOLING 7
EQUIPMENT LOCATION 7
ROUTING OF CABLES 7
LIMITATIONS 7
MODIFICATION 8
SECTION 3 INSTALLATION PROCEDURES 9
GENERAL INFORMATION 9
PARTS LIST 9
CABLE HARNESS 9
PNEUMATIC PRESSURE CONNECTIONS 13
MOUNTING 13
INSTALLATION COMPLETION 14
SECTION 4 OPERATION 16
GENERAL FUNCTION 16
USER INTERFACE 17
PRE-FLIGHT MODE 18
FLIGHT MODE 19
CONFIGURATION MODE 22
SECTION 5 CONFORMANCE 28
INSTRUCTIONS FOR CONTINUED AIRWORTHINESS 28
ENVIRONAMENTAL QUALIFICATION STATEMENT 30

Manual Number 9019161 Revision A, September 9, 2020 5
SECTION 1 GENERAL DESCRIPTION
INTRODUCTION
The model MD23 series FLEX Custom Function Display (“CFD”) is a panel-mounted instrument
capable of displaying various inputs in a configurable graphical presentation. FLEX is an off-the-
shelf solution that is FAA and EASA TSO-approved with Level A design assurance software
certification. The power of FLEX is its ability to become exactly what your application requires
without the time and cost of a product development and certification effort. This unique new
breakthrough in avionics uses a Patent Pending software concept that allows it to be quickly
customized to your requirements by Mid-Continent Instruments and Avionics without re-certification.
With the ability to receive and send multiple types of inputs and outputs, allow user interface, and
display custom designed graphics, FLEX is as flexible as it gets.
The MD23 is a general purpose CFD indicator in a standard 2-inch (2-¼”) rear-mounted form-factor
with a daylight readable color IPS-LCD display and a push-and-turn knob. The model series comes
in two hardware platforms, both with a 26-pin electrical connector and one with quick-disconnect
pitot and static pneumatic inputs. A USB port is accessible behind a cover on the rear of the unit for
field-loadable software updates and installation of a Custom Instrument Definition (CID) file.
The unique Multi-I/O (MIO) feature allows twelve of the unit’s electrical inputs to be configured per
the CID file to either accept or output various types of signals and information. MIO pins can be
defined to be an analog input, a discrete on/off input, an analog output, or a discrete output. In the
indicator version of the unit (non-pitot/static), the unit is also capable of accepting up to three
independent frequency inputs for tachometer or related use. There are two ARINC 429 serial inputs
and one output. The ARINC labels can be defined as needed for each application. The ARINC
output can combine both ARINC inputs, user selections, and translate MIO (analog/discrete) inputs
into a single ARINC data stream. The remaining interface options include a thermocouple input,
RS-232, an external dimming control, and 10-32VDC power.
The MD23 FLEX can add a new function to your panel, combine multiple data sources into a single
display, or control external equipment. The FLEX is a great tool for any panel upgrade, STC, or
forward-fit challenge. It brings a cost effective and certified product together with the flexibility to
configure it to your custom requirements, making it the perfect value and solution for your specific
cockpit display and control needs.

Manual Number 9019161 Revision A, September 9, 2020 6
TECHNICAL SPECIFICATIONS
Electrical Attributes
Input Voltage:
10-32 VDC
Input Power:
4 watts (0.14A @ 28VDC)
Lighting Input:
5, 14, or 28VDC or automatic photocell control
Battery Backup: (memory only)
(1) Rechargeable coin cell
Table 1.1
Data Inputs and Outputs
Analog input
output
0-27.5VDC, ±0.050V accuracy, input impedance >50Kohms
0-5VDC, ±0.050V accuracy, input impedance >50Kohms
Discrete input
output
Sensing of open or ground
Open, Ground, Pullup to 5V
Frequency input
(-1 only)
0.5-100VDC pk-pk, input impedance >50K ohms
10-2000 Hz (2 input pairs; differential or single point to ground)
10-20,000 Hz (1 input pair; differential or single point to ground)
ARINC 429 input
output
Low/High Speed input; 2 pair
High Speed output; 1 pair
RS-232
Protocol per RS-232 specification; data format per CID; 1 pair
Thermocouple
Type K; 1 pair; cannot be grounded
Pressure Static
(-2 only) Pitot
0-15 psi absolute
±15 psi differential
Table 1.2
Physical Attributes
Weight:
0.4 pounds (0.17 kg)
Dimensions:
2.43” x 2.43” x 1.0” (HxWxD)
Mating Connectors:
26-pin D-Sub and backshell MCIA p/n 9019162-1
Pneumatic fittings MCIA p/n 9019162-2
Mounting:
Rear Panel Mount with (4) #6-32 screws;
2.25 inch round bezel
Table 1.3
Qualifications
Certifications:
FAA/EASA TSO-C2d (Type B), C10c, C106, C113b
Environmental Qualification:
RTCA DO-160G (details listed in Section 5.2)
Software Qualification:
RTCA DO-178C, Design Assurance Level A
Lithium-ion Qualification:
UL 1642
Table 1.4
Exclusivity Rights
Rights:
U.S. Patent Pending
Table 1.5

Manual Number 9019161 Revision A, September 9, 2020 7
SECTION 2 PRE-INSTALLATION CONSIDERATIONS
COOLING
No external cooling is required. The unit will generate some heat as a function of normal operation.
Installation in an area that is exposed to extreme heat or restricted airflow can reduce the expected
life of the product. Mounting the unit to a metal surface can help reduce the effects of temperature
on the unit but is not required.
EQUIPMENT LOCATION
The MD23 FLEX is designed primarily to be installed in the instrument panel of the aircraft. The unit
has an extra-wide viewing angle allowing for flexible installation location. When selecting a panel
location for the MD23, be sure to consider appropriate field-of-view with regard to pilot and/or co-
pilot visibility and accessibility. Other locations may be acceptable if the environmental qualifications
are considered with respect to the installation approval.
Additionally, consider what equipment is behind the panel that could impede the installation.
Clearance for the unit as well as its electrical and pneumatic connections (if present) and routing
must be allowed.
ROUTING OF CABLES
Be aware of routing cables near other electronics or with other wire bundles that may be
susceptible to high energy flow. Avoid sharp bends in cabling and routing near aircraft control
cables. Also avoid proximity and contact with aircraft structures, avionics equipment, or other
obstructions that could chafe wires or hoses during flight and cause undesirable effects.
LIMITATIONS
The MD23 FLEX series of CFDs is certified to multiple FAA/EASA TSOs with the following
limitations identified:
environmental qualification conditions and requirements of each TSO are replaced with the
current and applicable procedures of RTCA/DO-160, revision G, and the equivalent or
better levels as identified within this manual
Applicable TSOs:
Technical Standard Order Authorization to FAA TSO C113b applies to all versions of the MD23.
TSOs C2d, C10c, and 106 only apply to the version(s) of the MD23 with pneumatic inputs. Further,
those TSOs are only applicable to customized configurations of the unit that represent the major
functions of each TSO. See the individual User Guide associated with each customized
configuration (CID) as to whether a particular TSO applies.
The MD23 contains a rechargeable manganese lithium coin cell for the purpose of maintaining non-
volatile memory. Per RTCA/DO-311A, the cell is an Energy Category 1 (0.051Wh < 2 Wh) and is
certified to UL 1642, thus certification to RTCA/DO-311A is not required. Specific STC limitations or
ACO coordination is not required for product or installation qualification.

Manual Number 9019161 Revision A, September 9, 2020 8
The conditions and tests for TSO approvals of this article are minimum performance standards.
Those installing this article, on or in a specific type or class of aircraft, must determine that the
aircraft installation conditions are within the TSO standards, specification of the article, and
deviations as listed above. TSO articles must have separate approval for installation in an aircraft.
The article may be installed only according to 14 CFR part 43 or the applicable airworthiness
requirements.
MODIFICATION
This product has a nameplate that identifies the manufacturer, part number, description,
certification(s) and technical specifications of the unit. It also includes the “MOD” or modification
number representing notable changes in the hardware design of the unit.
Modification (MOD) 0 is the initial release of the product and is identified on the nameplate by the
lack of marking on the MOD numbers 1 through 9 (i.e. 1-9 are visible). All subsequent
modifications are identified on the nameplate by the marking/blacking out of that particular MOD
number (i.e. for MOD 1, the number 1 is not visible and 2-9 are visible - see Figure 2.1 for
examples). MODs do not have to be sequentially inclusive and may be applied independent of each
other.
For additional details regarding specific changes associated with each MOD status refer to the
product published Service Bulletins at www.mcico.com.
Figure 2.1 Nameplate and MOD Status Example
MOD 0
MOD 1
MOD 1 & MOD 2

Manual Number 9019161 Revision A, September 9, 2020 9
SECTION 3 INSTALLATION PROCEDURES
GENERAL INFORMATION
IMPORTANT: READ THIS ENTIRE SECTION PRIOR TO STARTING INSTALLATION!
This section contains interconnect diagrams, mounting dimensions and other information pertaining
to the installation of the MD23 FLEXCustom Function Display. After installation of cabling and
before installation of the equipment, ensure that power is applied only to the pins specified in the
interconnect diagram.
PARTS LIST
When unpacking this equipment, make a visual inspection and notify the sender if there is any
evidence that damage may have incurred during shipment. The following parts are included:
Item Description MCIA Part Number
a. MD23 FLEX Custom Function Display 6420023-( )
b. Installation Manual 9019161
c. Electrical Connector Kit 9019162-1
i. 26-pin d-sub
ii. Size 22 contacts/sockets
iii. Backshell kit, quick-disconnect
iv. (4) #6-32 mounting screws
d. Pneumatic Connector Kit * 9019162-2
v. Pneumatic Connector, quick-disconnect (2)
* pneumatic connector kit only included with the pitot/static version
CABLE HARNESS
Construct the cable harness in accordance with the instructions below, including the Connector
Pinout of Table 3.1 and Figure 3.1 and Harness Assembly per Figure 3.2. Installers should follow
industry-accepted practices regarding aircraft wiring and applicable regulatory requirements and
guidance. The instructions for constructing the cable harness as listed within this manual were also
used to construct the harness during environmental and electrical testing. Alterations may invalidate
environmental qualification and/or performance results.
Refer to Section 2.2 and 2.3 for planning unit location and cable routing guidelines.
3.3.1 WIRE GAUGE SELECTION
Wire gauge should be 22 AWG. Use of PTFE, ETFE, TFE, Teflon, or Tefzel insulated wire is
recommended for aircraft use per MIL-DTL-16878 or equivalent. Additionally, for data
signals associated with ARINC 429 inputs and outputs, all MIO signals, and RS-232,
shielded twisted pair wiring per M27500 or equivalent is recommended (and required to
meet the qualifications associated with the product certification.)

Manual Number 9019161 Revision A, September 9, 2020 10
3.3.2 CONNECTOR PINOUT
The supplied connector and backshell is required for proper installation and operation of the
unit. The functions associated with the 26-pin high density D-subminiature connector are
identified in Table 3.1 below.
Note that for the -1 Indicator version of the unit (non-pitot/static), six of the MIO pins have
different capabilities. These are referred to as “Frequency Inputs” and are identified as three
separate pairs on pins 23/15, 24/25, and 17/26. Also described below as MIO #7/8, #9/10,
and #11/12. The functions of these pins are detailed further in Section 4.
Connector Pinout
Pin
Description
Pin
Description
1
Ground
14
ARINC In #1 B
2
ARINC Out A
15
Multi I/O #8
3
ARINC Out B
16
ARINC In #2 B
4
Dim Input
17
Multi I/O #11
5
ARINC In #1 A
18
Thermocouple +
6
ARINC In #2 A
19
+10-32VDC In
7
RS 232 In
20
Multi I/O #2
8
RS 232 Out
21
Multi I/O #4
9
Thermocouple -
22
Multi I/O #6
10
Reserved
23
Multi I/O #7
11
Multi I/O #1
24
Multi I/O #9
12
Multi I/O #3
25
Multi I/O #10
13
Multi I/O #5
26
Multi I/O #12
Table 3.1 Unit Connector Pin Identification
Figure 3.1 View from Rear of Mating Connector

Manual Number 9019161 Revision A, September 9, 2020 11
3.3.3 CABLE HARNESS ASSEMBLY
To assemble the aircraft cable harness, refer to the following instructions and Figure 3.2:
1) Install a pin/socket as supplied in the Connector Kit using an appropriate crimping tool for
each wire in the aircraft cable harness. Be sure to make the harness long enough to remove
the unit from the panel without stressing the harness.
a. Crimp and insertion/removal tool references can be found in
b. Table 3.2.
c. NOTE: Additional chafe protection, such as heat shrink or nylon wire braid is
recommended over the bundle (not including the shields) to prevent wear when installed in
the cable clamp.
2) Braids from shielded wires should be separated from the wire conductors and pulled back
from the pin/socket termination approximately 2” and gathered together.
a. A ring terminal, not included, may be used to gather the braids into a single attachment
point for connecting the shields to the ground point inside the Backshell later.
3) Insert the pins of the cable harness into the rear of the 26-pin D-Sub connector (Item 1) per
Table 3.1 and Figure 3.1 using an appropriate pin insertion tool per Table 3.2 or similar.
4) Select one (recommended), two or three locations for routing the wire harness bundle into the
Backshell (Item 2) and slide the Blanking Plates (Item 3) into the unused entry points.
5) Install the Backshell Spring Clip (Item 4) into the thin slot of the backshell as shown.
6) Place the Backshell Slide Lock (Item 5) over the D-Sub connector.
7) Install the D-Sub connector with Slide Lock and cable harness attached into the Backshell and
secure with (2) screws (Item 6). Verify that the Backshell Leaf Spring is between the Slide
Lock and Backshell. Move the Slide Lock back and forth to verify free movement.
8) Bundle the exposed shield braids and secure them to the hollow boss inside the Backshell
using a screw. A wire that is common to aircraft chassis ground shall also be electrically
connected to the Backshell here or in some other manner.
9) Route the aircraft wire harness bundle between the two halves of the Cable Strain Relief
Clamp (Item 7).
10) Connect the two halves of the Cable Strain Relief Clamp with (2) screws (Item 8).
a. If the wire bundle is loose, wrap electrical tape or similar material around the bundle until
the clamp securely holds the bundle without movement.
11) Place the Cable Strain Relief Clamp in the Backshell as shown.
12) Secure the Backshell Cover (Item 9) onto the Backshell using (4) Screws (Item 10).
13) The completed assembly should look as shown. Verify that the Slide Lock operates freely and
that no wires are pinched, nicked, or otherwise damaged.
14) Verify that power and ground signals are installed properly before connecting power.
Contact Tooling Reference
Tool
Positronic P/N
Daniels P/N
Mil P/N
Hand Crimp
9507-0-0-0
AFM8
M22520/2-01
Positioner
9502-3-0-0
K-41
M22520/2-06
Insert/Removal
4811-2-0-0
91067-1
M81969/1-04
Table 3.2 Contact Tooling Reference

Manual Number 9019161 Revision A, September 9, 2020 12
Figure 3.2 Mating Cable Harness Assembly
Cable Harness Kit Parts
Item
Qty
Description
1
1
DSub, 26pin HD, with #22 contacts
2
1
Backshell
3
2
Backshell blanking plate
4
1
Spring Clip
5
1
Slide Lock
6
2
Screw, Pan-head Phillips
7
2
Cable Clamp
8
2
Screw, Flat-head Phillips, Long
9
1
Backshell Cover
10
4
Screw, Flat-head Phillips, Short
1
8
9
3
5
2
7
4
6
10
shields

Manual Number 9019161 Revision A, September 9, 2020 13
PNEUMATIC PRESSURE CONNECTIONS
For the MD23 versions with pneumatic inputs, the connector kit supplied with the unit contains two
(2) pneumatic quick disconnect fittings. These fittings are specific to the connections on the rear of
the unit and are required for proper operation. The two fittings are marked with “S” and “P” on the
case. The “S” fitting, or Static, is for absolute pressure. The “P” fitting, or Pitot, is for positive
pressure and provides a differential pressure in relation to the Static input.
Aircraft tubing that connects to the unit must be ¼” OD with an approximate 0.17” ID. When
determining tubing length, be sure to include sufficient service length for insertion and removal
without stressing the tubing.
NOTE: It is helpful to identify/label each tube (pitot or static) so that it can be connected to the
correct port on the back of the unit during installation and so they do not get switched during
maintenance or reconnection in the future.
WARNING: Engage the Lock by pressing the metal tab on the quick disconnect before connecting
to the unit to avoid damaging the o-rings. The connectors will ‘snap’/lock into place once they are
fully engaged.
MOUNTING
The MD23 FLEX is designed primarily to be rear mounted in an aircraft instrument panel. Refer to
Section 2.2 for Equipment Location information. To install the unit in the instrument panel, follow the
instructions below and refer to Figure 3.3 and Figure 3.4.
Notes:
If using flat-head screws, minimum panel thickness is 0.050 inches (1.3mm). Thinner
panels require a pan-head screw, or a spacer/washer between the unit and the rear surface
of the panel to properly secure the unit.
If using screws other than those provided, ensure that they do not protrude more than ½-
inch into the unit.
Remove burrs around the cutout and holes to allow the unit to mount flush with the panel.
Electrical bonding between the aircraft and the unit chassis is NOT required.
1. Once a location is selected, cut the panel per the dimensions in Figure 3.4.
Either through-holes for pan-head or cap screws, or countersink holes for flat-head
screws can be used. The installation kit includes flat-head screws.
2. Route the prepared cable harness and pneumatic tubing (if applicable) behind the panel
and to the panel cutout.
3. VERIFY THAT AIRCRAFT POWER IS TURNED OFF.
4. Connect the cable harness and pneumatic fittings (if applicable) to the rear of the unit.
5. Insert the unit into the panel cutout and secure with four (4) #6-32 screws (provided).

Manual Number 9019161 Revision A, September 9, 2020 14
INSTALLATION COMPLETION
Prior to operating the unit in the aircraft, verify the basic operation of the unit and conduct a
standard leak check of the pitot/static system per the aircraft maintenance manual or industry
practice. Verify the proper CID number is installed for the application.
Table 3.3 MD23 Unit Versions
Figure 3.3 MD23 Outline Drawing
all dimensions apply to all versions
Unit Versions
Part Number
Pneumatic Inputs
Frequency Inputs
6420023-1
No
Yes
6420023-2
Yes
No
FIGURE 3.3
MD23 OUTLINE DRAWING
-1
-2

Manual Number 9019161 Revision A, September 9, 2020 15
Figure 3.4 Panel Cutout

Manual Number 9019161 Revision A, September 9, 2020 16
SECTION 4 OPERATION
IMPORTANT: READ THIS ENTIRE SECTION PRIOR TO OPERATING THE UNIT IN FLIGHT!
The MD23 FLEX Custom Function Display is a unique new type of avionics equipment with a Patent
Pending software concept. It utilizes a highly capable and certified hardware and software platform
that can be customized to receive, output, and display a wide array of information. Because FLEX
can become almost anything, this section is designed to explain the functional capabilities, standard
operation, and configurable defaults. Operational details of specific custom applications are
provided separately as a User Guide that serves as a compliment to this manual.
GENERAL FUNCTION
4.1.1 CUSTOM INSTRUMENT DEFINITION (CID)
The Custom Instrument Definition, or CID, is a data file that describes the definition of the
inputs, outputs, and graphical display for a specific application. The CID utilizes the certified
functions of the MD23 and provides settings and variables to parameterize them to meet the
requirements as requested.
The CID is provided as a single file that can be loaded onto the MD23 through the USB
Type A data port on the rear of the unit. Each unique CID file is assigned an identification
number and revision – typically in the format of 1###X, where # is a three-digit number and
X is the revision, starting with “A”. The currently loaded CID version can be found on the
startup screen during Pre-Flight Mode and in the Options Menu on the Info screen during
Flight Mode.
Contact Mid-Continent Instruments and Avionics to inquire about the purchase and creation
of a CID file to meet your specific application requirements.
4.1.2 SYSTEM NAVIGATION
All standard MD23 units have the same basic system structure. The system navigation map
in the figure below demonstrates the basic functions and relationships between the various
modes and menus. The user interface on how to maneuver between modes and menus is
described in Section 4.2. The details associated with each mode and menu can be found
further in Section 4.3, 4.4, and 4.5. (Figure 4.1)
4.1.3 USB FUNCTION
The MD23 CFD includes a USB Type-A Programming Port connector on the rear of the unit
that is used for loading unit software and CID files. This feature makes it easy and
convenient to perform updates with any standard USB flash drive. The Programming Port is
only accessible when not in flight and shall only be used by authorized personnel in
accordance with the instructions found within this manual.

Manual Number 9019161 Revision A, September 9, 2020 17
Figure 4.1 System Navigation Map
USER INTERFACE
The MD23 FLEX CFD is designed for simple, intuitive operation for ease of use for all custom
applications. The Control Knob and Menu Operation are standard for all MD23 installations.
4.2.1 CONTROL KNOB
The central Control Knob is located at the bottom-center of the unit bezel. This is the only
user interface on the unit.
The Control Knob has two functions: push and turn.
The knob provides 16-detents per revolution and typically increments whatever element it is
controlling on the display one unit per detent. It can also be used to scroll between
controllable elements, menu options, or pages.
The push function is typically used to select the highlighted option in a menu, on the display,
and/or to enter and exit menus and control functions. The push function can also perform
certain operations with a push-and-hold action as described herein.
Hold
Knob
Introduction
Screen
Hold
Knob
Options Menu
User Options
Menu*
Normal
Operation
Config
Menu
User Config
Menu*
YES
NO
FLIGHT MODE
CONFIG MODE
PRE-FLIGHT MODE
Power On

Manual Number 9019161 Revision A, September 9, 2020 18
4.2.2 MENU OPERATION
The menu parts are defined below:
Menu title
white text on a blue background at the top of each menu
Current item cursor
highlighted by a white box and green background
Selectable items
any selectable item on the menu is indicated with white text
Unavailable items
information only / unavailable options are indicated with gray text
Menu operation throughout the MD23 is simple and intuitive:
Turning the Control Knob will scroll the cursor over the available options within each menu.
For items that can be changed without opening another page, the currently set value is
displayed in gray directly to the right of each setting. Pressing the Control Knob for one of
these items will make its options available to the right. Scroll to the desired option and press
the Control Knob to select it. The green highlight will return to the menu options on the left
and the new value will be displayed in gray to the right.
After confirming any setting by selecting it, that setting will become immediately active and
be saved in memory, regardless of whether the EXIT command is selected or it times out
and automatically reverts to the active display.
PRE-FLIGHT MODE
In Pre-flight Mode, power is applied to the unit and the introduction screen appears during startup.
The startup screen will display the manufacturer’s logo, model name and number, unit software
version and CID version. It may also include additional graphics (such as a logo) or other
information specific to the custom application.
During Pre-flight Mode, the introduction screen will be displayed while the unit conducts an initial
power-up built-in test (PBIT) of the system to validate operational readiness. This includes, among
others, an internal test to verify software and memory, and a check that the loaded CID file is valid.
Inputs and outputs are not enabled during Pre-flight Mode.
The introduction screen will be displayed for approximately five (5) seconds and will transition to
Flight Mode when complete. (Figure 4.2)
Figure 4.2 Pre-Flight Mode
manufacturer’s logo
model number/name
software version
CID version
customer info
(optional)

Manual Number 9019161 Revision A, September 9, 2020 19
FLIGHT MODE
In Flight Mode, the unit operates normally according to the function of the CID and displays the
primary graphical presentation. Operational details of specific custom applications are provided
separately as a User Guide that serves as a compliment to this manual. The Options Menu, with
manual brightness adjustment and the User Options Menu, is accessible in Flight Mode.
4.4.1 OPTIONS MENU
While in Flight Mode, the Options Menu can be accessed at any time with a press-and-hold
of the Control Knob for approximately three (3) seconds. The Options Menu offers
selections that are available during flight but do not affect the aircraft specific configuration
of the unit (these must be set in Configuration Mode by authorized personnel during
installation and/or maintenance).
The Options Menu contains up to four standard options: Brightness, User Options, Info, and
Exit. Any setting changed when navigating within the Option Menu or sub-menus will
become active and saved to memory immediately upon selection. (Figure 4.3)
Figure 4.3 Options Menu Example

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4.4.1.1 BRIGHTNESS
The display brightness can be controlled with either an external voltage or automatically
using the integrated photocell. See Section 4.4 for further details. The Brightness feature in
the Options Menu allows the user to manually adjust or offset the display brightness up or
down regardless of the current level set by the External or Internal (automatic) brightness
control method.
The Brightness adjust bar has the following elements: (Figure 4.4)
Full Box: 0-100% brightness range
Left Marker: Minimum brightness*
Center Marker: Current unadjusted brightness level;
per the external input or photocell response, as configured
Right Marker: Maximum brightness*
Green bar: Current brightness per manual adjustment/offset
* as determined by the Dimming Curve in Configuration Mode
Figure 4.4 Manual Brightness Adjustment
After selecting the Brightness menu option, the Brightness adjust bar will appear. Turning
the Control Knob will adjust/offset the display brightness (green bar) above or below the
current brightness level (center marker). Once set, the brightness will continue to be
controlled up or down with the preset control method, but with the adjusted offset applied. At
no time can the brightness exceed the minimum or maximum values programmed into the
Dimming Curve within Configuration Mode, regardless of the manual adjustment. The
manual brightness adjustment will be saved into memory, even after a power cycle.
Pressing the Control Knob will revert to the active display. Inactivity for approximately five
(5) seconds will also revert to the active display.
4.4.1.2 USER OPTIONS
The User Options menu is only available if the specific design of the loaded CID includes it.
This menu will include user selectable options that can be changed by the pilot or crew
during Flight Mode. See the applicable User Guide of the loaded CID for specific details.