Midcontinent MD302 Series Technical Document

INSTALLATION MANUAL AND
OPERATING INSTRUCTIONS
MODEL MD302-( ) SERIES
STANDBY ATTITUDE MODULE
Mid-Continent Instrument Co., Inc.
dba Mid-Continent Instruments and Avionics
9400 E. 34
th
Street N.
Wichita, KS USA 67226
[phone] Manual Number 9017782
[phone] Rev B, October 31, 2012

Mid-Continent Instruments and Avionics, Wichita, KS
REV. B, October 31, 2012 2 Manual Number 9017782
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]
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]
©Copyright 2012
Mid-Continent Instrument Co., Inc.

Mid-Continent Instruments and Avionics, Wichita, KS
REV. B, October 31, 2012 3 Manual Number 9017782
REVISION HISTORY
Rev Date Approved Detail
1 09/10/12 BAW Engineering release.
A 10/02/12 BAW Initial release.
B 10/31/12 BAW Updates implemented.

Mid-Continent Instruments and Avionics, Wichita, KS
REV. B, October 31, 2012 4 Manual Number 9017782
Table of Contents
SECTION 1GENERAL DESCRIPTION 6
1.1INTRODUCTION 6
1.2SYSTEM OVERVIEW 7
1.2.1PRE-FLIGHT MODE...................................................................................................7
1.2.2FLIGHT MODE..........................................................................................................7
1.2.3EMERGENCY MODE ..................................................................................................9
1.2.4CONFIGURATION MODE ...........................................................................................9
1.3TECHNICAL SPECIFICATIONS 10
1.3.1ELECTRICAL ATTRIBUTES....................................................................................... 10
1.3.2PHYSICAL ATTRIBUTES .......................................................................................... 10
1.3.3PERFORMANCE LIMITS........................................................................................... 10
1.3.4QUALIFICATIONS................................................................................................... 10
SECTION 2INSTALLATION 12
2.1GENERAL INFORMATION 12
2.2PARTS LIST 12
2.3EQUIPMENT LOCATION 12
2.4LIMITATIONS 14
2.5CABLE HARNESS 15
2.5.1WIRE GAUGE SELECTION ....................................................................................... 15
2.5.2CONFIGURATION MODULE ..................................................................................... 15
2.6PITOT / STATIC CONNECTIONS 18
2.7MOUNTING 18
2.8INSTALLATION COMPLETION 18
SECTION 3OPERATION 21
3.1USER INTERFACE 21
3.2PRE-FLIGHT MODE 21
3.3FLIGHT MODE 22
3.3.1MAJOR FUNCTIONS................................................................................................ 23
3.3.1.1ATTITUDE OPERATION........................................................................................... 23
3.3.1.2ALTITUDE OPERATION........................................................................................... 24
3.3.1.3AIRSPEED OPERATION ........................................................................................... 25
3.3.1.4SLIP OPERATION ................................................................................................... 26
3.3.2OPTION SETTINGS................................................................................................. 27
3.3.2.1MENU OPERATION ................................................................................................. 27
3.3.2.2ALT UNITS............................................................................................................. 28
3.3.2.3BARO UNITS.......................................................................................................... 28
3.3.2.4SYMBOL ................................................................................................................ 28
3.3.2.5ATT MASK ............................................................................................................. 29
3.3.2.6ALT TREND............................................................................................................ 29
3.3.2.7POWER OFF........................................................................................................... 30
3.3.2.8REVIEW CONFIG.................................................................................................... 30
3.3.2.9EXIT MENU............................................................................................................ 31
3.3.3BRIGHTNESS ADJUSTMENT .................................................................................... 31
3.4EMERGENCY OPERATION 31
3.4.1IN FLIGHT............................................................................................................. 31
3.4.2ON THE GROUND................................................................................................... 32

Mid-Continent Instruments and Avionics, Wichita, KS
REV. B, October 31, 2012 5 Manual Number 9017782
SECTION 4CONFIGURATION SETUP 33
4.1CONFIGURATION MODE/MENU 33
4.2CONFIGURE DISPLAY 34
4.2.1ROLL DISPLAY ....................................................................................................... 35
4.2.2AIRSPEED UNITS ................................................................................................... 35
4.2.1DISPLAY ORIENTATION.......................................................................................... 36
4.3CONFIG DIMMING 36
4.3.1DIMMING CONTROL............................................................................................... 37
4.3.2DIMMING CURVE ................................................................................................... 37
4.4CONFIGURE AIRCRAFT 38
4.4.1PANEL TILT ........................................................................................................... 39
4.4.2RANGE MMO.......................................................................................................... 39
4.4.3RANGE MARKINGS ................................................................................................. 40
4.5CONFIGURATION MODE ACTIONS 41
4.5.1UPDATE SOFTWARE............................................................................................... 41
4.5.2ARINC SPEED......................................................................................................... 41
4.5.3ACCEPT CHANGES.................................................................................................. 42
4.5.4CANCEL CHANGES.................................................................................................. 42
SECTION 5CONFORMANCE 43
5.1INSTRUCTIONS FOR CONTINUED AIRWORTHINESS 43
5.1.1PRESSURE SYSTEM AND ALTIMETER VERIFICATION................................................. 43
5.1.2SOFTWARE UPGRADES........................................................................................... 43
5.1.3BATTERY REPLACEMENT ........................................................................................ 43
5.1.4TROUBLESHOOTING............................................................................................... 43
5.2ENVIRONMENTAL QUALIFICATION STATEMENT 47

Mid-Continent Instruments and Avionics, Wichita, KS
REV. B, October 31, 2012 6 Manual Number 9017782
SECTION 1 GENERAL DESCRIPTION
1.1 INTRODUCTION
The model MD302 series Standby Attitude Module is a self-contained situational awareness instrument
that provides aircraft attitude, altitude, airspeed and slip indication. The compact and innovative design
of the MD302 is specifically developed for maximum flexibility for installation in retrofit or modern
instrument panel. Its size, extra-wide viewing angle and AnyWay selectable orientation allows it to be
installed almost anywhere in the instrument panel and in less space than traditional 2-inch mechanical
standby or primary flight instruments.
Regardless of the aircraft you’re flying, the MD302 is a great fit. With a 10 to 32 volt DC input range, the
unit will work with 14 or 28V aircraft electrical buses and the selectable lighting input allows operation
with 5, 14 or 28V lighting systems. The operation and certification of the MD302 make it well suited for
Part 23 and 25 fixed-wing applications as well as Part 27 and 29 rotorcraft.
The MD302 provides critical flight and situational data to the pilot and crew under any circumstances
you’re likely to encounter. The design is built around a solid-state electronic sensor array for high
reliability and contains an integral and rechargeable Nanophosphate® lithium-ion battery that can power
the unit for up to two hours if main aircraft power is lost. The dual, high-resolution LCD display uses
smooth graphics, daylight-readable brightness, and a configurable lighting response curve to ensure
optimal visibility in all conditions.
The user interface of the product allows for simple, intuitive operation using a single push-and-turn knob
that easily navigates through the user options and menu screens. The interactivity of the unit means that
it can receive and transmit ARINC 429 data communications. Functional outputs of attitude, altitude, and
airspeed can be used for monitoring or backup information while baro input data can be received that will
synchronize the baro setting with the primary system to eliminate redundant task loading for the pilot.
The MD302 is an excellent complement to your avionics suite as a reliable and state-of-the-art instrument
that is an essential part of any instrument panel.

Mid-Continent Instruments and Avionics, Wichita, KS
REV. B, October 31, 2012 7 Manual Number 9017782
1.2 SYSTEM OVERVIEW
The MD302 has four specific modes of operation. They are:
Pre-flight Mode
Flight Mode
Emergency Mode
Configuration Mode
The following sections will briefly introduce each mode with further details provide within Sections 3 and
4 of this manual.
1.2.1 PRE-FLIGHT MODE
In Pre-flight Mode, power is applied to the unit and the introduction screen appears
during startup with the information shown in Figure 1.1.
FIGURE 1.1
1.2.2 FLIGHT MODE
manufacturer’s logo
model name/number
software version
total operating time

Mid-Continent Instruments and Avionics, Wichita, KS
REV. B, October 31, 2012 8 Manual Number 9017782
In Flight Mode, the unit operates normally by displaying attitude, altitude, airspeed and
slip information as shown in Figure 1.2.
Figure 1.2
FIGURE 1.2
roll/bank scale
pitch scale
symbolic airplane
slip indicator
barometer value
airspeed window
airspeed units
airspeed tape/scale
altitude trend bar
altitude window
altitude units
altitude tape/scale

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REV. B, October 31, 2012 9 Manual Number 9017782
1.2.3 EMERGENCY MODE
In Emergency Mode, aircraft power to the instrument has been lost and the unit
continues to operate in Flight Mode utilizing power from the internal battery. The battery
icon is displayed as shown in Figure 1.3.
FIGURE 1.3
1.2.4 CONFIGURATION MODE
In Configuration Mode, an authorized installer can change and set the appropriate
configuration values that are specific to the aircraft. These also include user preferences
that are not available during flight and certain maintenance functions as well. The top
level menu in Configuration Mode is shown in Figure 1.4.
FIGURE 1.4
current menu
current selection
unavailable
more options available
battery icon

Mid-Continent Instruments and Avionics, Wichita, KS
REV. B, October 31, 2012 10 Manual Number 9017782
1.3 TECHNICAL SPECIFICATIONS
1.3.1 ELECTRICAL ATTRIBUTES
Characteristics:
Input Voltage: 10-32 VDC
Input Power: (nominal) 4 watts (0.15A @ 28VDC)
(maximum) 25 watts max (when charging and heating battery)
Lighting Input: 5.14, or 28VDC or automatic photocell control
Input Data: barometer synchronization via ARINC 429 (see Table 1.5)
Output Data: attitude, altitude, airspeed via ARINC 429 (see Table 1.5)
discrete valid signal to ground; invalid signal is open (pin 2)
TABLE 1.1
1.3.2 PHYSICAL ATTRIBUTES
Characteristics:
Weight: 1.6 pounds (0.73 kg)
Dimensions:
(without connectors, mates, & knob) Bezel: 2.37” x 5.50” x 0.33” (HxWxD) Chassis: 2.31” x 3.16” x 4.82” (HxWxD)
Mating Connectors: 15-pin D-Sub with Configuration Module, MCIA p/n 9017275
Pneumatic fittings, MCIA p/n 9017642
Mounting: Panel mount from front; uses (4) #6-32 cap screws and
MCIA p/n 9017490-2 Nutplate (included)
TABLE 1.2
1.3.3 PERFORMANCE LIMITS
Characteristics:
Attitude: Pitch Angle No limits (360°+)
Pitch Rate 300° per second max
Roll Angle No limits (360°+)
Roll Rate 300° per second max
Altitude: Range -1,500 to +55,000 feet (available in meters)
Barometer 28.00 to 31.00 inches of mercury (available in inHg/mB/hPa)
Air Speed: Range 20 to 500 knots (available in mph or kph)
TABLE 1.3
1.3.4 QUALIFICATIONS
Specifications:
Certifications: FAA TSO-C2d (Type B), C3e, C4c, C10b, C106, C113a, C179a
Environmental Qualification: RTCA DO-160G Environmental Category
(F1)(S2)AB(RBB1)XXXXXXZ(ZXX)AZ(ZC)[WF]P[B3H33]XXAX
Software Qualification: RTCA DO-178B, Design Assurance Level A
Complex Hardware Qualification: RTCA DO-254, Design Assurance Level A
TABLE 1.4

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REV. B, October 31, 2012 11 Manual Number 9017782
ARINC DATA LABELS
All labels are defined as Equipment ID 038 in BNR format.
High and Low speed options are configurable. See Section 3.4.
ARINC 429 Input Speed
Label Description High Low
203 altitude (rel 29.92) x x
204 baro altitude x x
ARINC 429 Output Speed
Label Description High Low
203 altitude (rel 29.92) x x
204 baro altitude x x
212 altitude rate x x
215 impact pressure x x
217 static pressure x x
324 pitch attitude x x
325 roll attitude x x
326 body pitch rate x
327 body roll rate x
330 body yaw rate x
331 body longitudinal acceleration x
332 body lateral acceleration x
333 body normal acceleration x
336 inertial pitch rate x
337 inertial roll rate x
340 inertial yaw rate x
364 vertical acceleration x
377 specific equipment id x x
TABLE 1.5

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REV. B, October 31, 2012 12 Manual Number 9017782
SECTION 2 INSTALLATION
2.1 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 MD302Digital Flight Instrument. After installation of cabling and before installation
of the equipment, ensure that power is applied only to the pins specified in the interconnect diagram.
2.2 PARTS LIST
When unpacking this equipment, make a visual inspection for evidence of any damage that may have
incurred during shipment. The following parts should be included:
Item Description MCIA Part Number
a. MD302 Digital Flight Instrument 6420302-( )
b. Installation Manual – 9017782
c. Connector Kit – 9017646
i. Nutplate 9017490-2
ii. Pneumatic Connector (x2) 9017642
iii. Screw, Hex, 6-32x5/8 (x4) 90-620-52011
iv. Screw, Flat, 2-56x1/4 (x2) 90-208-10011
v. Configuration Module 9017275
1. 15-pin D-Sub
2. Backshell
3. Backshell Cover
4. Printed Circuit Board Assembly
5. Screw, Flat, 2-56x1/4 (x2)
6. Screw, 4-40x3/16 (x4)
2.3 EQUIPMENT LOCATION
The MD302 Standby Attitude Module is designed primarily to be installed in the instrument panel of the
aircraft. However, within the limitations of the environmental qualifications, other locations may be
acceptable when considered within the context of the specific application and with the appropriate
installation certification.
The MD302 has an extra wide viewing angle and AnyWay™ selectable orientation that allows for flexible
installation locations and options. The unit can be mounted vertically (knob left or knob right) or horizontally.
Once installed, the display orientation can be selected to match the installation. See Figure 2.1. However, be
sure to consider appropriate field-of-view in regards to pilot and/or co-pilot visibility and accessibility when
selecting a location to install the MD302. Note: when installing in vertical orientation, choose the knob
position based on whether or not the pilot’s hand will obscure the display during operation.
Additionally, consider what equipment is behind the panel which may impede the installation of the
MD302. Clearance for the unit as well as its electrical and pneumatic connections and routing must be
allowed. 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 or hoses and routing near aircraft control
cables. Also avoid proximity and contact with aircraft structures, avionics equipment, heat sources or
other obstructions that could chafe or damage wires or hoses during flight and cause undesirable effects.
No external cooling is required.

Mid-Continent Instruments and Avionics, Wichita, KS
REV. B, October 31, 2012 13 Manual Number 9017782
FIGURE 2.1
INSTALLATION ORIENTATION OPTIONS

Mid-Continent Instruments and Avionics, Wichita, KS
REV. B, October 31, 2012 14 Manual Number 9017782
2.4 LIMITATIONS
The conditions and tests for TSO approval 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.
There are some portions of these TSOs which do not apply to our product or represent outdated
requirements. These items are highlighted below and have been submitted to and approved by the FAA
as deviations to the TSO certifications of the product.
FAA TSO-C2d: Airspeed Instruments
instrument is not labeled with “Airspeed” or “IAS”
FAA TSO-C3e: Turn and Slip Instrument
instrument does not provide rate-of-turn functionality
FAA TSO-C4c: Bank and Pitch Instruments
dielectric strength/insulation resistance does not apply due to electronic components between
chassis and connector pins
FAA TSO-C10b: Altimeter, Pressure Actuated, Sensitive Type
graduation increments are every 25 feet instead of 20 feet
FAA TSO-C179a: Permanently Installed Rechargeable Lithium Cells, Batteries and Battery Systems
dielectric strength/insulation resistance does not apply due to electronic components between
chassis and connector pins

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REV. B, October 31, 2012 15 Manual Number 9017782
2.5 CABLE HARNESS
Construct the cable harness with regards to the instructions below and using the Connector Pinout of
Table2.1 and Figure 2.2 and Configuration Module Assembly of Figure 2.3. Installers should follow
industry-accepted practices regarding aircraft wiring and applicable regulatory and advisory requirements
and guidance.
Refer to Section 2.3: Equipment Location in regards to routing precautions.
2.5.1 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 for the connections as
noted below. Additionally, for data signals associated with ARINC 429 inputs and outputs,
shielded twisted pair wiring per M27500 or equivalent is recommended (pin pairs 3/8 and
12/13).
2.5.2 CONFIGURATION MODULE
The supplied custom configuration module is required for proper installation and
operation of the MD302 unit. The functions associated with the 15-pin D-subminiature
connector are identified as follows:
15-pin D-Sub Connector
Pin No. Description Pin No. Description
1 +10-32VDC Input 8 ARINC Out A
2 Valid Signal Out 9 Reserved
3 ARINC Out B 10 Config Module Clock
4 Reserved 11 Reserved
5 Config Module Power 12 ARINC In A
6 Power Return / Ground 13 ARINC In B
7 Lighting Bus Input 14 Config Module Data
15 Config Module Return
TABLE 2.1
FIGURE 2.2
VIEW FROM REAR OF MATING CONNECTOR

Mid-Continent Instruments and Avionics, Wichita, KS
REV. B, October 31, 2012 16 Manual Number 9017782
To assembly the aircraft cable harness and Configuration Module refer to the following
instructions and Figure 2.3:
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 front of the panel without stressing the harness (approx. 8” longer than
required to reach the unit connector).
2) Braids from shielded wires should separate from the wire conductors and pulled back from
the pin/socket termination approximately 2” and gathered together.
a. 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.
3) Insert the pins of the cable harness into the rear of the 15-pin D-Sub connector (Item 4) per
Table 2.1 and Figure 2.2using an appropriate pin insertion tool.
NOTE: The Configuration Module PC Board Assembly contains sensitive electronics that can be
damaged by electrostatic discharge (ESD). Appropriate precautions should be applied prior to
handling this component.
4) Insert the pins of the Configuration Module PC Board Assembly (Item 3) into their
corresponding locations as noted below using an appropriate pin insertion tool.
a. The wires coming from the Configuration Module PC Board Assembly are marked as
follows on the circuit board: TP1, TP2, TP3, TP4.
b. With the D-Sub oriented up (pin locations 1-5 on top), orient the Configuration
Module PC Board Assembly with the electronic parts facing UP prior to pin insertion.
c. Install each pin into the rear of the D-Sub connector as follows:
TP1 = config return = pin 15
TP2 = config data = pin 14
TP3 = config clock = pin 10
TP4 = config power = pin 5
5) Install the D-Sub Backshell Spring (Item 5) as shown.
6) Place the D-Sub Slide Lock (Item 6) over the D-Sub connector.
7) Install the D-Sub connector with Slide Lock and cable harness attached into the Backshell
(Item 9) and secure with (2) screws (Item 8). Verify that the Backshell Spring is between
the Slide Lock and Backshell. Move the Slide Lock back and forth to verify free movement.
8) Route the aircraft wire harness bundle (excluding shield braids) between the two halves of
the Cable Strain Relief Clamp (Item 7). The Clamp should be placed over the chafe
protection installed in Step 2 (if used).
9) Loosely connect the two halves of the Cable Strain Relief Clamp with (2) screws (Item 8).
10) Place the Cable Strain Relief Clamp in the Backshell as shown.
11) Bend the wires of the Configuration Module PC Board Assembly 180 degrees so that the PC
Board has its electrical components facing down as shown. Be careful not to place excess
strain on the solder connections between the wires and the PC Board.
12) Capture the Configuration Module PC Board Assembly into the Backshell by placing the
Backshell Cover (Item 2) on top of the Backshell.
13) Secure the Backshell Cover onto the Backshell using (2) Screws (Item 9).
14) Bundle the exposed shield braids and secure them to either side of the rear of the Backshell,
along with a connection to aircraft chassis ground, in the threaded holes using the one or
both of the remaining two 4-40 screws provided in the connector kit. Use of a ring terminal
(not included) may be useful.
15) The completed assembly should look as shown. Verify that the Slide Lock operates freely
and that no wires are pinched, nicked, or otherwise damaged.
16) Verify that power and ground signals are installed appropriately before connecting to the
unit.

Mid-Continent Instruments and Avionics, Wichita, KS
REV. B, October 31, 2012 17 Manual Number 9017782
FIGURE 2.3
CONFIGURATION MODULE ASSEMBLY
Item Qty Part Number Description
1 1 9017218 Backshell, Size 9
2 1 9017274 Cover, Backshell
3 1 9017184-1 PCB Assy, Config Module
4 1 9016479 Kit, DSub, 15pin HD
5 1 part of 9016479 DSub Backshell Spring Clip
6 1 part of 9016479 DSub Slide Lock, Size 9
7 2 part of 9016479 DSub Backshell Cable Clamp
8 4 90-406-00011 Screw 4-40X3/16 Pan Phil Blk Patch
9 2 90-208-10011 Screw 2-56X1/4 Flat Phil Blk Patch

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REV. B, October 31, 2012 18 Manual Number 9017782
2.6 PITOT / STATIC CONNECTIONS
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 required for proper operation.
Aircraft tubing that connects to the unit must be ¼” OD with an approximate 0.17” ID. When
determining tubing length, be sure that it can extend through the cutout in the panel by approximately 8”
to allow the unit to be installed and removed from the front of the panel.
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.
2.7 MOUNTING
The MD302 is designed primarily to be front mounted in an aircraft instrument panel. Refer to Section
2.5in regards to Equipment Location. To install the unit in the instrument panel, follow the instructions
below and refer to Figures 2.4, 2.5 and 2.6.
1) Once a location is selected, cut the panel per the dimensions in Figure 2.5. Other notes to
consider for panel cutout: (the Nutplate can be used as a basic template for the panel cutout)
For vertical installation, rotate the panel cutout profile 90°.
Be sure to leave space clear on the front of the panel for the bezel of the unit, which will
extend significantly outside the main rectangular cutout.
The dimension of the smaller side of the rectangle is critical for a good finished appearance.
If it is too large, the cutout will be visible outside the unit bezel. The relationship of the holes
to the cutout should be maintained closely to ensure proper installation.
One countersink hole on either side of the rectangular cutout is required. Any of the three
hole locations is acceptable. More than one countersink hole one each side is optional.
Screws for these holes will retain the Nutplate and not support the weight of the unit.
Verify that a flathead screw will sit flush or below the panel surface in the countersink holes.
If not, deepen the countersinks slightly.
Remove burrs around the cutout and holes to allow the unit to mount flush with the panel.
2) Install the Nutplate on the backside of the instrument panel using at least one (1) flathead screw
on each side of the rectangular cutout.
The Nutplate should mount flush to the backside of the instrument panel. The threaded nuts
in corners of the Nutplate should protrude to the rear.
3) Route the prepared cable harness and pitot/static fittings from behind the panel and through the
panel cutout. The length of the cable harness should allow the unit to be connected in front of
the panel.
4) VERIFY THAT AIRCRAFT POWER IS TURNED OFF.
5) Connect the cable harness with configuration module and pitot/static fittings to the rear of the
unit.
6) Insert the unit through the panel cutout and secure with four (4) hex cap screws provided.
Electrical bonding between the aircraft and the unit chassis is NOT required.
2.8 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. When
initially powering the unit, an error may occur if a pre-configured unit is being mated to a Configuration
Module for the first time or if the unit has yet to be configured. Acknowledge this error and either
proceed to configuring the installation settings or cycle the power. The error should not occur for
subsequent startups.

Mid-Continent Instruments and Avionics, Wichita, KS
REV. B, October 31, 2012 19 Manual Number 9017782
5.22
5.50
2.092.37 2.4" diagonal
active area
4X Ø0.150 thru
.33 4.82
3.16
2.30
static port
pitot port USB access
15-pin D-sub
Battery access
FIGURE 2.4
MD302 OUTLINE DRAWING

Mid-Continent Instruments and Avionics, Wichita, KS
REV. B, October 31, 2012 20 Manual Number 9017782
2.34±0.02
.50
.295
.750
.750
.295
3.25±0.05
2.090
5.220 .50
4X Ø.16±0.01 thru
wØ 0.175 X 82° countersink
only 1 of 3 required per side 4X R 0.10 max
FIGURE 2.6
INSTALL ILLUSTRATION
FIGURE 2.5
PANEL CUTOUT
STEP 1
STEP 2