Midcontinent MD302-3 Document technique

ManualNumber

9018233

RevisionC

February 21, 2022

Manual Number 9018233 Revision C, February 21, 2022

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 (316) 630-0101

FX (316) 630-0723

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 (316) 630-0101

FX (316) 630-0723

[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.

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

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

ttitude: Pitch Angle No limits (360°+)

Pitch Rate 300° per second max

Roll Angle No limits (360°+)

Roll Rate 300° per second max

ltitude: Range -1,500 to +55,000 feet (available in meters)

Baromete

28.00 to 31.00 inches of mercury (available in mbar)

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

Complex Hardware Qualification: RTCA DO-254, Design Assurance Level

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

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

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.

ARNING

CAUTION

Manual Number 9018233 Revision C, February 21, 2022

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

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 “---“.

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