Midcontinent MD302-3 Technical Document

ManualNumber
9018233
RevisionC
February 21, 2022

Manual Number 9018233 Revision C, February 21, 2022 1
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 Street N.
Wichita, KS 67226 USA
PH [phone]
FX [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 reference and the
page number. Send your comments to:
Mid-Continent Instruments and Avionics
Attn: Technical Publications
9400 E. 34th Street N.
Wichita, KS 67226 USA
PH [phone]
FX [phone]
[email protected]
All products produced by Mid-Continent Instrument Co., Inc., including those identified as
Mid-Continent Instruments and Avionics or True Blue Power, are designed and manufactured
in Wichita, KS, USA.
© Copyright 2019
Mid-Continent Instrument Co., Inc.
Download the current
version of this
installation manual
using your
smartphone or tablet.

Manual Number 9018233 Revision C, February 21, 2022 2
TABLE OF CONTENTS
SECTION 1GENERAL DESCRIPTION 4
1.1INTRODUCTION 4
1.2TECHNICAL SPECIFICATIONS 5
1.3ARINC DATA LABELS 6
1.4IMPORTANT SAFETY INFORMATION 7
SECTION 2PRE-INSTALLATION CONSIDERATIONS 8
2.1EQUIPMENT LOCATION 8
2.2LIMITATIONS 9
2.3MODIFICATION 10
SECTION 3INSTALLATION 11
3.1GENERAL INFORMATION 11
3.2PARTS LIST 11
3.3CABLE HARNESS 11
3.4PITOT / STATIC CONNECTIONS 14
3.5INSTALLATION COMPLETION 16
SECTION 4OPERATION 18
4.1CONFIGURATION 18
4.2CALIBRATION 19
SECTION 5CONFORMANCE 23
5.1INSTRUCTIONS FOR CONTINUED AIRWORTHINESS 23
5.2ENVIRONMENTAL QUALIFICATION STATEMENT 25

Manual Number 9018233 Revision C, February 21, 2022 3
REVISION HISTORY
Rev Date Detail Approved
A
12/22/2014 Production release. BMC
B 05/11/2018 Added TSO C6e and support information for use of MD32
Magnetometer. ARINC pass-through feature. Updated
pinout. Add patent reference.
BAW
C 02/21/2022 Updated style and brand to meet Marketing and
Engineering guidelines. Updated Section 3.2 and 3.4 with
o-ring replacement information.
DLR

Manual Number 9018233 Revision C, February 21, 2022 4
SECTION 1 GENERAL DESCRIPTION
1.1 INTRODUCTION
The model MD302 series SAM® Standby Attitude Module is a self-contained situational awareness
instrument that provides aircraft attitude, altitude, airspeed, and slip indication, plus available
heading data with the optionally installed MD32 Magnetometer. The remote version of the MD302,
part number 6420302-3, is specifically designed as a compact and innovative solution for maximum
flexibility, providing the needed positional awareness for navigation, autopilot function, or related
applications. Its size and remote capability allow it to be installed almost anywhere convenient and
provides critical information to the equipment that needs it.
The MD302 provides critical flight and situational data to the pilot and crew under any
circumstances you are likely to encounter. The design is built around a solid-state electronic sensor
array for high reliability and accuracy.
Regardless of the aircraft you are 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. 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.

Manual Number 9018233 Revision C, February 21, 2022 5
1.2 TECHNICAL SPECIFICATIONS
Electrical Attributes
Input Voltage: 10-32 VDC
Input Power: 4 watts (0.12A @ 28VDC)
Output Power: Reserved for MD32 Remote Magnetometer (pin 11)
Lighting Input: n/a
Input Data: ARINC 429 (see Table 1.1)
Output Data: ARINC 429 (see Table 1.1);
discrete valid signal to ground; invalid signal is open (pin 2)
Physical Attributes
Weight: 1.3 pounds (0.59 kg)
Dimensions:
(without connectors, mates & knob)
Bezel: 2.30” x 5.20” x 0.125” (HxWxD)
Chassis: 2.31” x 3.16” x 4.84” (HxWxD)
Mating Connectors: 15-pin D-Sub with Configuration Module, MCIA p/n 9017275
Pneumatic fittings, MCIA p/n 9017642
Mounting: Mount from front; uses (4) #6-32 screws
Performance Limits
A
ttitude: Pitch Angle No limits (360°+)
Pitch Rate 300° per second max
Roll Angle No limits (360°+)
Roll Rate 300° per second max
A
ltitude: Range -1,500 to +55,000 feet (available in meters)
Baromete
r
28.00 to 31.00 inches of mercury (available in mbar)
A
irspeed: Range 20 to 500 knots (available in mph or kph)
Qualifications
Certifications: FAA TSO-C2d (Type B), C3e, C4c, C6e, C10b, C106, C113a,
C179a
EASA ETSO-C2d, C3d, C4c, C6e, C10b, C106, C113, C179a
Environmental Qualification: RTCA DO-160G (details listed in Section 5.2)
Software Qualification: RTCA DO-178B, Design Assurance Level
A
Complex Hardware Qualification: RTCA DO-254, Design Assurance Level
A
Rights
U.S. Patent No.: 9,739,611

Manual Number 9018233 Revision C, February 21, 2022 6
1.3 ARINC DATA LABELS
All labels are defined as Equipment ID 038 in BNR format. High and Low speed options for ARINC
outputs are configurable.
ARINC 429 Input Speed
Label Description High Low
014 magnetic heading x x
203 altitude (rel 29.92) x x
204 baro altitude x x
234 baro correction (mbar) x x
235 baro correction (inHg) x x
320 magnetic heading x x
ARINC 429 Output Speed
Label Description High Low
203 altitude (rel 29.92) x x
204 baro altitude x x
205 mach numbe
r
x x
206 computed airspeed x x
212 altitude rate x x
215 impact pressure x x
217 static pressure x x
234 baro correction (mbar) x x
235 baro correction (inHg) x x
320 magnetic heading x
324 pitch attitude x x
325 roll angle 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
350 custom label for software version x
351 reserved custom label x
353 SSEC identification x
364 vertical acceleration x
377 specific equipment id x x
TABLE 1.1

Manual Number 9018233 Revision C, February 21, 2022 7
1.4 IMPORTANT SAFETY INFORMATION
Read this safety information BEFORE maintaining or servicing the unit.
Symbol Definition
This section describes the precautions necessary for safe operations. The following safety
symbols have been placed throughout the guide.
Warnings identify conditions or practices that could result in personal injury.
Cautions identify conditions or practices that could result in damage to the equipment.
W
ARNING
CAUTION

Manual Number 9018233 Revision C, February 21, 2022 8
SECTION 2 PRE-INSTALLATION CONSIDERATIONS
2.1 EQUIPMENT LOCATION
The MD302 SAM (-3) Standby Attitude Module is designed to be installed in the instrument panel or
equipment bay 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.
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.
FIGURE 2.1
INSTALLATION ORIENTATION OPTIONS
top
MUST BE INSTALLED IN THE
DIRECTION OF FLIGHT
dir
ect
i
Panel tilt: -90° to +90°
(horizontal shown; also applicable for
strai
ght
sid

Manual Number 9018233 Revision C, February 21, 2022 9
2.2 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 listed below. 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 the approved TSOs which represent outdated requirements or do not
apply to the product. These items are highlighted below and have been submitted to and approved
by the FAA as deviations to the TSO certifications of the product. In the case of FAA TSO and
EASA ETSO-C3e, the MD302 has been approved as an ‘incomplete TSO’. The MD302 meets all
TSO requirements for applicable functions (slip) but does not meet requirements associated with
functionality that is not present in the unit (rate of turn). A note below describes further details
regarding the temperature requirements of FAA TSO-C113a, but does not represent a deviation.
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
 instrument is not labeled with “Altitude” or “ALT”
 graduation increments are every 25 feet instead of 20 feet
FAA TSO-C113a: Airborne Multipurpose Electronic Displays
 display is operable but marginally usable at -30°C. Display is fully functional at
temperatures higher than -30°C.
Heading Display Function
 Does not provide independent heading data, the ARINC data is displayed without
reprocessing; if ARINC data is lost the display will read “---“.

Manual Number 9018233 Revision C, February 21, 2022 10
2.3 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 2.2 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 or www.flysam.com.
Figure 2.2
Nameplate and MOD Status Example
MOD 0
MOD 1
MOD 1
& MOD 2

Manual Number 9018233 Revision C, February 21, 2022 11
SECTION 3 INSTALLATION
3.1 GENERAL INFORMATION
This section contains interconnect diagrams, mounting dimensions and other information pertaining
to the installation of the MD302 SAM Standby Attitude Module. After installation of cabling and
before installation of the equipment, ensure that power is applied only to the pins specified in the
interconnect diagram.
IMPORTANT: READ THIS ENTIRE SECTION PRIOR TO STARTING INSTALLATION!
3.2 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 SAM Standby Attitude Module 6420302-3
i. Internal/Replacement Battery Pack 9017177 (Type 1)
(Installed on select versions) 9019120 (Type 2)
ii. Included/Replacement O-rings 9017146
b. Installation Manual 9018233
c. Connector Kit 9017646-1
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)
3.3 CABLE HARNESS
Construct the cable harness in accordance with the instructions below including the Connector
Pinout of Table 2.1 and Figure 2.3 and Configuration Module Assembly of Figure 2.4. 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 2.1, Equipment Location for routing precautions.

Manual Number 9018233 Revision C, February 21, 2022 12
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, shielded twisted pair wiring per M27500 or
equivalent is recommended (pin pairs 3 & 8 and 12 & 13).
Configuration Module
The supplied custom configuration module is required for proper installation and operation of the
unit. The functions associated with the 15-pin D-subminiature connector are identified as follows:
Unit Connector Pin Identification
Pin No. Description Pin No. Description
1 +10-32VDC Input 9 Reserved
2 Valid Signal Out 10 Config Module Clock
3
A
RINC Out B 11 Reserved
4 Reserved 12
A
RINC In
A
5 Config Module Powe
r
13
A
RINC In B
6 Power Return / Ground 14 Config Module Data
7 Reserved 15 Config Module Return
8
A
RINC Out
A
TABLE 3.1
UNIT CONNECTOR PIN IDENTIFICATION
FIGURE 3.1
VIEW FROM REAR OF MATING CONNECTOR

Manual Number 9018233 Revision C, February 21, 2022 13
To assemble the aircraft cable harness and Configuration Module 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 front of the panel without stressing the harness (approx. 8” longer
than required to reach the unit connector).
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. 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 3.1 and Figure 3.1 using an appropriate pin insertion tool.
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:
 Board TP1 = config return = D-Sub pin 15
 Board TP2 = config data = D-Sub pin 14
 Board TP3 = config clock = D-Sub pin 10
 Board TP4 = config power = D-Sub 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 1) 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).
CAUTION

Manual Number 9018233 Revision C, February 21, 2022 14
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 threaded hole on the rear of
the Backshell using a 2-56 screw (Item 10). A wire that is common to aircraft chassis
ground shall also be connected to one of these two holes on the Backshell. 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.
Verify that power and ground signals are installed appropriately before connecting to the unit.
3.4 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.
If o-rings are worn or damaged, replace with MCIA p/n 9017146 and
install per the drawing as shown.
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.
CAUTION: Lock quick disconnect before connecting to the unit to avoid damaging the O-ring.
CAUTION
MCIA p/n 9017146
(x4)
(rear of unit)

Manual Number 9018233 Revision C, February 21, 2022 15
FIGURE 3.2
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
shield termination

Manual Number 9018233 Revision C, February 21, 2022 16
3.5 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.
Configuration information is stored on the configuration module, allowing easy replacement of the
MD302. Because of this, the configuration module must be installed prior to applying power and
configuring the unit (See Section 4.1.)
Within 10 seconds after power is applied, the STAT (status) light should illuminate solid green. This
indicates normal operation. If the STAT light indicates RED, there is an issue preventing normal
operation. See Section 5.1.3 for details regarding operation and troubleshooting.

Manual Number 9018233 Revision C, February 21, 2022 17
FIGURE 3.3
MD302 OUTLINE DRAWING
TABLE 3.2
MD302 UNIT VERSIONS
Unit Versions
Part Numbe
r
Bezel Batter
y
6420302-1 Black Yes
6420302-2 Black No
6420302-3 None* No
6420302-4 Gra
y
Yes
6420302-5 Gra
y
No
6420302-6* Black No
* remote mounted unit version. Contact manufacturer for details.

Manual Number 9018233 Revision C, February 21, 2022 18
SECTION 4 OPERATION
IMPORTANT: THE UNIT IS NOT APPROVED FOR FLIGHT UNTIL IT HAS BEEN
CONFIGURED FULLY USING THE INSTRUCTIONS IN THIS SECTION!
This section contains information on how to configure the aircraft specific requirements available
with the MD302 SAM Standby Attitude Module. This includes critical flight parameters that
contribute to the safe and certified operation of the unit and the aircraft.
Only authorized installers and trained personnel should access the Configuration Mode during initial
installation or during maintenance, adjustments and updates.
4.1 CONFIGURATION
Configuration is accomplished through the USB interface similarly to a software update, see
Section 5.1.2 for more information regarding software updates.
A specific file must be present in the root drive of the flash drive with the name “mc_conf.dat”.
This file must be formatted as ASCII text with options specified on separate lines as follows:
 “mc_conf.dat”:
 # MD302 configuration settings file
 AIRSPEED_MINIMUM_20_KNOTS
 #AIRSPEED_MINIMUM_30_KNOTS
 #AIRSPEED_MINIMUM_40_KNOTS
 #ARINC_SPEED_LOW
 ARINC_SPEED_HIGH
 ARINC_PASSTHRU_OFF
 #ARINC_PASSTHRU_ON
 BARO_SYNC_ON
 #BARO_SYNC_OFF
 DISPLAY_ORIENTATION_HORIZONTAL
 #DISPLAY_ORIENTATION_VERTICAL_RIGHT
 #DISPLAY_ORIENTATION_VERTICAL_LEFT
 #DISPLAY_ORIENTATION_HORIZONTAL_SWAP
 PANEL_TILT={ 0.0 }
 PANEL_ROLL={ 0.0 }
Any line beginning with “#” is considered a comment. These lines are provided for reference of
the other options.
Display Orientation is configurable, even though the unit has no display. This information is
used along with the items below to determine the direction of flight.
Panel Tilt is specified in units of degrees from { 90.0 } to { -90.0 }. This compensates for pitch
error in the installation, as seen above in figure X.X. Fractions of a degree may be entered,
but will be rounded to 0.5° increments.

Manual Number 9018233 Revision C, February 21, 2022 19
Panel Roll is specified in units of degrees from { 5.0 } to { -5.0 }. This compensates for minor
roll error in the installation. Fractions of a degree may be entered, but will be rounded to 0.5°
increments.
The defaults are shown in the above example. If any parameters are omitted from the file, the
configuration unit will retain its current setting.
The procedure for updating configuration is to:
1. Power off MD302.
2. Uncover the USB port and insert flash drive containing the configuration file.
3. Power on MD302.
4. The STATUS indicator will blink green while settings are processed.
5. The RESULT indicator will illuminate green if the settings were accepted.
6. Remove the USB stick while power remains on.
The MD302 will reboot and illuminate STATUS green to indicate normal operation with the
new settings. Reinstall USB cover.
If the RESULT indicator is not green following Step 5, the config file was not installed. This
could be due to a misspelled entry or improper syntax.
4.2 CALIBRATION
Pressure Calibration
Calibration of the altitude and airspeed functions is possible with a single or dual pressure
tester. The procedure is similar to the configuration process in section 3.1 (above).
Preparation
One or both of the following options may be independently added to the “mc_conf.dat” file to
trigger calibration of airspeed and altitude respectively:
CALIBRATE_AIRSPEED
CALIBRATE_ALTITUDE
If calibrating airspeed, the external tester must be connected to the pitot port of the MD302,
with the test pressure stabilized at 120 knots.
If calibrating altitude, the external tester must be connected to the static port of the MD302,
with the test pressure stabilized at 5,000 feet.
Both calibrations may be done at the same time with a combined P/S tester.