Mid-Continent Instrument SAM MD302-3 Document technique
Installation Manual and Operating Instructions
Model MD302-3
Mid-Continent Instruments and Avionics
Mid-Continent Instrument Co., Inc.
dba Mid-Continent Instruments and Avionics
9400 E. 34
th
Street N.
Wichita, KS USA 67226
PH (800) 821-1212 Manual Number 9018233
FX (316) 630-0723 Revision A, December 22, 2014
2 Manual Number 9018233, Revision A
Mid-Continent Instruments and Avionics December 22, 2014
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 316-630-0101
Fax 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 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 316-630-0101
Fax 316-630-0723
© Copyright 2014
Mid-Continent Instrument Co., Inc.
3 Manual Number 9018233, Revision A
Mid-Continent Instruments and Avionics December 22, 2014
REVISION HISTORY
ECO Rev Date Approved Detail
A 12/22/2014 BMC Production release.
4 Manual Number 9018233, Revision A
Mid-Continent Instruments and Avionics December 22, 2014
TABLE OF CONTENTS
SECTION 1GENERAL DESCRIPTION 5
1.1INTRODUCTION .....................................................................................................5
1.2TECHNICAL SPECIFICATIONS................................................................................6
1.2.1ELECTRICAL ATTRIBUTES 6
1.2.2PHYSICAL ATTRIBUTES 6
1.2.3PERFORMANCE LIMITS 6
1.2.4QUALIFICATIONS 6
1.2.5ARINC DATA LABELS 7
SECTION 2INSTALLATION 8
2.1GENERAL INFORMATION.......................................................................................8
2.2PARTS LIST............................................................................................................8
2.3EQUIPMENT LOCATION .........................................................................................9
2.4LIMITATIONS........................................................................................................ 10
2.5MODIFICATIONS .................................................................................................. 11
2.6CABLE HARNESS................................................................................................. 12
2.6.1WIRE GAUGE SELECTION 12
2.6.2CONFIGURATION MODULE 12
2.7PITOT / STATIC CONNECTIONS ........................................................................... 15
2.8INSTALLATION COMPLETION............................................................................... 15
SECTION 3CONFIGURATION 17
3.1CONFIGURATION................................................................................................. 17
SECTION 4CALIBRATION 19
SECTION 5CONFORMANCE 20
5.1INSTRUCTIONS FOR CONTINUED AIRWORTHINESS ........................................... 20
5.1.1PRESSURE SYSTEM AND ALTIMETER VERIFICATION 20
5.1.2SOFTWARE UPDATES 20
5.2ENVIRONMENTAL QUALIFICATION STATEMENT.................................................. 22
5 Manual Number 9018233, Revision A
Mid-Continent Instruments and Avionics December 22, 2014
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. The compact and
innovative design of the MD302 is specifically developed for maximum flexibility for installation in retrofit
or modern instrument panels and equipment bays. Its size and AnyWayTM selectable orientation allows it
to be installed almost anywhere and in less space than traditional 2-inch mechanical standby or primary
flight instruments.
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.
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1.2 TECHNICAL SPECIFICATIONS
1.2.1 ELECTRICAL ATTRIBUTES
Characteristics:
Input Voltage: 10-32 VDC
Input Power: (nominal) 4 watts (0.12A @ 28VDC)
(maximum) 25 watts max (limited to initial startup)
Lighting Input: n/a
Input Data: ARINC 429 (see Table 1.5)
Output Data: ARINC 429 (see Table 1.5);
discrete valid signal to ground; invalid signal is open (pin 2)
TABLE 1.1
1.2.2 PHYSICAL ATTRIBUTES
Characteristics:
Weight: 1.3 pounds (0.73 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 cap screws
TABLE 1.2
1.2.3 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 mbar)
Airspeed: Range 20 to 500 knots (available in mph or kph)
TABLE 1.3
1.2.4 QUALIFICATIONS
Specifications:
Certifications: FAA TSO-C2d (Type B), C3e, C4c, C10b, C106, C113a,
C179a
EASA ETSO-C2d, C3d, C4c, 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
TABLE 1.4
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1.2.5 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
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 number x x
206 computed airspeed x x
212 altitude rate x x
215 impact pressure x x
217 static pressure x 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
364 vertical acceleration x
377 specific equipment id x x
TABLE 1.5
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Mid-Continent Instruments and Avionics December 22, 2014
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 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.
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 SAM Standby Attitude Module 6420302-( )
b. Installation Manual – 9018233
c. Connector Kit – 9017646-1
i. 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)
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2.3 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
to
p
view
MUST BE INSTALLED IN THE DIRECTION OF FLIGHT
(horizontal shown; also applicable for vertical)
direction
of flight
Panel tilt: -90° to +90°
(horizontal shown; also applicable for vertical)
-90°
+90°
straight and
level flight
side view
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Mid-Continent Instruments and Avionics December 22, 2014
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 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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