Mid-Continent MD200-706, MD200-707 Installation Guide

Installation Manual and Operating Instructions

Model MD200-706/707 Series

Course Deviation Indicator

Mid-Continent Instrument Co., Inc.
dba Mid-Continent Instruments and Avionics
9400 E. 34th Street N.
Wichita, KS 67226 Manual Number 9018582
ph [phone] fx [phone] Revision A, January 26, 2016

®

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.

Manual Number 9018582

© Copyright 2016

Mid-Continent Instrument Co., Inc.

2 Revision A, January 26, 2016

REVISION HISTORY

Revision Date Approved Detail

A 01/26/2016 BAW Initial Release;

MD200-7XX series supersedes MD200-3XX series

Manual Number 9018582

3 Revision A, January 26, 2016

TABLE OF CONTENTS

FORWARD ...................................................................................................................... 2

REVISION HISTORY .................................................................................................................... 3

FORWARD 2........................................................................................................................................ 4

REVISION HISTORY3 .......................................................................................................................... 4

SECTION 1 GENERAL DESCRIPTION ........................................................................... 5

1.1Introduction ...................................................................................................................................... 5

1.2Technical specifications ................................................................................................................... 6

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Electrical Attributes ............................................................................................................... 6

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Physical Attributes ................................................................................................................. 6



Qualifications ......................................................................................................................... 6

SECTION 2 PRE-INSTALLATION ................................................................................... 7

2.1General Information ......................................................................................................................... 7

2.2Unpacking and inspecting equipment .............................................................................................. 7

2.3Equipment Location ......................................................................................................................... 7

2.4Cable Harness ................................................................................................................................. 8

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Wire Gauge Selection ........................................................................................................... 8

2.5Limitations ........................................................................................................................................ 9

SECTION 3 INSTALLATION .......................................................................................... 10 

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3.1General .......................................................................................................................................... 10

3.2Mounting ........................................................................................................................................ 10

3.3Installation Completion ................................................................................................................... 10

SECTION 4 OPERATION .............................................................................................. 12

4.1Pre-Installation Tests ..................................................................................................................... 12

4.2Annunciator Dimming Adjustment .................................................................................................. 12

4.3Operating Instructions .................................................................................................................... 12

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VOR Operation .................................................................................................................... 12

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Localizer Operation ............................................................................................................. 13

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Glideslope Operation .......................................................................................................... 13

SECTION 5 CONFORMANCE ....................................................................................... 13

5.1Instructions for Continued Airworthiness ....................................................................................... 13

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Maintenance ........................................................................................................................ 13

5.2ENVIRONMENTAL QUALIFICATION STATEMENT .................................................................... 14

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Manual Number 9018582

4 Revision A, January 26, 2016

SECTION 1 GENERAL DESCRIPTION

1.1 INTRODUCTION

The Mid-Continent Instruments and Avionics MD200-706 and MD200-707 Course Deviation Indicator is
designed to operate with VHF and GPS navigational equipment to provide OMNI (VOR), GPS, Localizer
(VLOC), and Glideslope (GS) information.

The MD200-706/707 is designed to accept DC signals for Left/Right and Up/Down pointer deviation and
Valid/Invalid (“flag”) status from a remote mounted VOR converter. It also provides annunciations for NAV,
VLOC, and GPS indication of the incoming source or mode and a TO or FR (from) annunciation to indicate
direction of the ground signal or course waypoint from the aircraft.

When GPS is selected for display, the MD200-( ) receives inputs from compatible GPS/Navigation receivers
or Flight Management Systems to provide a visual presentation to the pilot. All information presented on
the navigation indicator is generated from this external receiver.

The omni bearing selector (OBS) course resolver provides the compass card position as an el ectrical output
(a phase reference signal which is ORZ zeroed to an industry standard 300°). Additional course datum
output information is offered on the MD200-707 version as well, with the electrical zero defined when the
compass card is set to 090°.

The MD200 CDI uses white LED unit lighting to illuminate the dial and pointers. It can be brightened or
dimmed with an external lighting bus voltage for 5, 14 or 28V systems. Additionally, the backlit LED
annunciators are automatically adjusted for appropriate brightness using a built-in photocell sensor which
can be calibrated at the time of installation.

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1.2 TECHNICAL SPECIFICATIONS

ELECTRICAL ATTRIBUTES

Characteristics:

Input Voltage: 12-32 VDC
Input Current: (maximum) 0.2 amps
Unit Lighting Input: 5, 14, or 28VDC
Annunciator Lighting: Automatic dimming control via internal photocell (adjustable)

Interface Specifications:

OBS Resolver Electrical zero: 300° ±1° ORZ
Pointer Deviation:

Input impedance: 1k
Deflection sensitivity: 150mV ±10% full scale deflection

Valid Signal:

Input impedance: 1k
Valid sensitivity: 260 mV ±10% to display pointers

To/From Indicator:

Input impedance: 200
Annunciator sensitivity: 40mV ±15%

Course Datum Output: Standard ARINC X, Y, Z; 11.8V

PHYSICAL ATTRIBUTES

Characteristics:
Dimensions:

(without connectors, mates & knob)

Bezel: 3-1/8” diameter
Chassis: 3.25” x 3.25” x 4.75” (HxWxD)

Weight: MD200-706: 1.3 pounds (0.59 kg)

MD200-707: 1.4 pounds (0.64 kg)
Cover Glass: HEA (anti-reflective) coated per MIL-C-14806
Mating Connectors: 25-pin D-Sub, MCIA p/n 7014517

9-pin D-Sub, MCIA p/n 8017287 (-707 only)
Mounting: Rear mount, see panel cutout; Figure 3.1 and Figure 3.2
Lighting: Light emitting diodes (LEDs)

QUALIFICATIONS

Specifications:
Qualification: FAA TSO-C34e, C36e, C40c

EASA ETSO C34e, C36e, 2C40c

Environmental Qualification: RTCA DO-160B/G

(details listed in Section 5.2)

±10%

±10%

±10%

RMS

(400 Hz)

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SECTION 2 PRE-INSTALLATION

2.1 GENERAL INFORMATION

This section contains information and considerations required to prepare for the MD200 CDI installation,
including provided equipment, panel location, wiring and other information.

2.2 UNPACKING AND INSPECTING EQUIPMENT

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:

a. Course Deviation Indicator MCIA P/N MD200-7XX
b. Connector Kit MCIA P/N 7014517
c. Connector Kit (-707 only) MCIA P/N 8017287
d. Installation Manual MCIA P/N 9018582

Equipment Not Provided
a. Wire, 22AWG (see 2.4.1)
b. Mounting Hardware (3) #6 UNC screws, 1.0” max length

2.3 EQUIPMENT LOCATION

The MD200-( ) course deviation indicator should be mounted as close to the pilot’s field of view as possible.
Consideration should be given to the depth behind the panel where the unit will be installed. Clearance

for the unit as well as its electrical connections and routing must be allowed. Be aware of routing cables
near other electronics or with other wire bundles that may contain high energy flow. Examples of these
sources could include 400 Hz AC, COM, DME, HF, and transponder transmitter coax. Use of shielded
wire may be useful in isolating the low-level signals that drive the CDI from other interference. Avoid
sharp bends in cabling and routing near aircraft control cables. Also, avoid proximity and cont act with
aircraft structures, avionics equipment, heat sources or other obstructions that could chafe or damage
wires during flight and cause undesirable effects.

No direct cooling is required. As with any electronic equipment, overall reliability may be increased if the
MD200-( ) is not located near any high heat source or crowded next to other equipment.

The MD200 CDI 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.

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2.4 CABLE HARNESS

Construct the cable harness in accordance with the instructions/diagrams locate d within this
document and using industry-accepted practices regarding aircraft wiring and applicable
regulatory requirements and guidance.

See Tables 2.1 and 2.2 for connector pinout.
Refer to Section 2.3: Equipment Location for routing precautions.

WIRE GAUGE SELECTION

Wire gauge should be 24 AWG or larger (smaller AWG; 22, 20, etc). Use of PTFE, ETFE, TFE,
Teflon, or Tefzel insulated wire is recommended for aircraft use per MIL-DTL-16 878 or
equivalent. Shielded twisted pair wiring per M27500 or equivalent is recommended for any signal
wires which may be exposed to sources interfering with the integrity of the signal.

Pin Pin Description Pin Pin Description

1 OB S Res olver H 14 + Do wn (GS common ref)
2 OBS Resolver C 15 + Gli de S l ope V al i d
3 OBS Resolver D 16 - Glide Slope Vali d (GS common ref)
4 OBS Resolver F 17 GP S Annunciator (gnd = active)
5 OBS Resolver E (NAV common ref) 18 VLOC A nnunciat or (gnd = acti ve)
6 OBS Resolver G (NAV common ref) 19 +12-32 V DC (or pin 20)*
7 + V OR/LOC Val id 20 + 12-32 VDC (or pin 19)*
8 - VOR/LO C V ali d (NAV common ref) 21 Power Ground

9 + To 22 + 28 V Light i ng
10 + F rom (NAV common ref) 23 +14 V Li ghting
11 + Left 24 NA V Annunci ator (gnd = acti ve)
12 + Ri ght (NAV common ref) 25 +5 V Li ghting
13 + Up

* only one power input l ine required on either pin 19 or 20

J2 (9 PIN D-SUB) Pinout

MD200-707 only

Pin Pin Description

1 Cours e Datum H

2 Cours e Datum C

3 Cours e Datum X

4 Cours e Datum Y

5 Cours e Datum Z

6 Spare

7 Spare

8 Spare

9 Spare

Tables 2.1 and 2.2 Figure 2.1
Connector Pinout Connector Views; J1 and J2

Manual Number 9018582

J1 (25 PIN D-SUB) Pinout

8 Revision A, January 26, 2016

2.5 LIMITATIONS

The conditions and tests for TSO approval of this article are minimum performan ce 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.

REQUIREMENTS FOR TSO’D VOR/ILS SYSTEM:

1. The navigation receiver shall be certified to FAA TSO C40a/b/c or TSO C36c/d/e or later.

2. VOR phase error shall not exceed 1.5°.

3. Variation in VOR composite output not to exceed ±3 dB from .500 VRMS as the RF input level
of a standard VOR test signal to the receiver is varied from 10 µV to 10,000 µV.

4. Variation in the LOC composite output not to exceed ±2 dB from .333 VRMS as the RF input
level of a standard localizer test signal to the receiver is varied from 50 µV to 10,000 µV.

5. A control line (ILS Energize) must be provided as a low impedance to ground when an ILS
frequency is selected.

REQUIREMENTS FOR TSO’D GLIDESLOPE SYSTEM:

1. The glideslope receiver/converter shall be certified to the standards of TSO C34c/d/e or later.

2. Deviation current with a 700 µV standard glideslope deviation signal applied to the receiver
input shall be 78 µA ±10% into a 1000 ohm load. Deviation current shall not change more than
15% as the RF level of a standard glideslope deviation signal is varied from 100 µA to 10,000
µA. Deviation current shall be proportional within 5% to the difference in depth of modulation
of the 90 Hz and 150 Hz tones.

3. Warning signal output shall be a DC current less than 125 µA into a 1000 ohm load in order to
drive the pointer out of the viewing area. For the pointer to be fully in view and operational, the
warning/valid signal shall be a DC current of 260 µA minimum into a 1000 ohm load.

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3.1 GENERAL

This section contains interconnect diagrams, mounting dimensions and other information
pertaining to the installation of the MD200 Course Deviation Indicator. After installation of cabling
and before installation of the equipment, ensure that power is applied only to the pins specified in
the interconnect diagram.

3.2 MOUNTING

Install the MD200 CDI within the aircraft in accordance with the aircraft manufacturer’s
instructions and the following steps:

1. Verify that the instrument panel cutout meets the requirements of Figure 3.1

2. Secure the indicator to the instrument panel using the proper mounting hardware

3. Connect the electrical connector(s) to the connector on the back of the unit.

SECTION 3 INSTALLATION

unit outline
(ref)

3.156

Ø

1.152

0.408

1.152

Figure 3.1

Panel Cutout

2.480

TYP

1.240 TYP

1.240
TYP

Ø

2.480
TYP

0.156

(3X)

3.3 INSTALLATION COMPLETION

Prior to flight, verify the basic operation of the unit, interface with other equipment, lighting
performance in various conditions, and general expected performance.

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3X 6-32 UNC -2B
on Ø3.500 B.C.,
equally spaced

Ø3.120

(Ø2.800)

(1.670 CG)

0.125 4.584 MAX

Manual Number 9018582

1.625

(1.910 CG)

3.250

Figure 3.2

Outline Drawings

11 Revision A, January 26, 2016

1.625

0.206

3.250

J2, 9-Pin
D-sub Male
(-707 only)

0.765

1.217

J1, 25-Pin
D-sub Male

SECTION 4 OPERATION

4.1 PRE-INSTALLATION TESTS

With the MD200-( ) indicator disconnected, turn on the avionics master switch and verify that aircraft
power on J1 pin 19 or pin 20 is 12-32 VDC. Using an ohmmeter, verify pin 21 is aircraft ground.

4.2 ANNUNCIATOR DIMMING ADJUSTMENT

Following installation of the MD200-( ) CDI, check the brightness of the annunciations (GPS, NAV,
VLOC, TO, FR) as necessary with the ambient and aircraft panel lighting levels set to simulate
minimum-light operations. If required, the dimming adjustment is located on the side of the MD200­( ) unit, and is labeled “ANNUN DIM ADJ”.

4.3 OPERATING INSTRUCTIONS

All controls required to operate the MD200-( ) course deviation indicator are located on the unit’s
front panel and on the front panel of the related navigation receiver.

VOR OPERATION

Channel the NAV receiver to the desired VOR frequency and positively identify the station by
listening to received audio. Determine the NAV/VOR (vertical) pointer is in the viewing area of the
dial.

Flying inbound to a VOR station is accomplished by first rotating the OBS knob to center the
deviation indicator, and determining the TO annunciator is lit. The aircraft is then turned to a
magnetic heading, which is the same as the selected course with proper allowance for wind
correction. When the aircraft is on course, the vertical pointer will be centered. If the aircraft moves
off course, the deviation indicator will move away from the center position and flying in the direction
of pointer deflection (left or right) is required to intercept the appropriate course.

The procedure for flying outbound from a VOR station is the same as flying inbound, except the
OBS knob is first rotated to cause a FR (“From”) annunciator to be active/lit.

To intercept a selected VOR radial (from the station) and fly outbound, turn the OBS control to set
the desired radial under the top indicator index. Maneuver the aircraft to fly the selected radial
magnetic heading plus 45° intercept angle which will provide a sufficient intercept angle. The
intercept angle should be reduced as the deviation pointer approaches an on course condition
(center) to prevent excessive course bracketing.

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LOCALIZER OPERATION

Select the desired localizer frequency and observe that the localizer (vertical) pointer is fully in view.
The To/From annunciator is not functional for localizer operation. When flying on the front course
or outbound on the back course make corrections toward the localizer pointer deflection. The
localizer path narrows as the approach end of the runway becomes closer. When flying inbound
on the back course or outbound on the front course, the corrections are made away from the
direction of pointer deflection. A helpful hint when flying the localizer is to set the localizer heading
on the OBS dial under the lubber line for quick reference.

GLIDESLOPE OPERATION

The glideslope (horizontal) pointer provides the pilot with vertical steering information during ILS,
LPV, or GLS approaches. The glideslope circuitry is energized when the associated localizer
frequency is selected on the navigation receiver. Observe that the glideslope pointer is in view. The
glideslope pointer deflects towards the direction the pil ot must fly to remain on the glide path.

If the glideslope pointer deflects upward the aircraft is below the glide path and the pilot must climb
to again intercept the glide path and center the pointer. If the pointer deflects downward the aircraft
is above the glide path and the pilot must descend to again intercept the glide path and center the
pointer. When the pointer is centered the aircraft is on the glide path.

SECTION 5 CONFORMANCE

5.1 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS

MAINTENANCE

There is no scheduled maintenance required for the MD200 CDI. If the unit fails to perform within
operational specifications, the unit must be removed and serviced by Mid-Continent Instrument s
and Avionics.

The MD200 contains no field replaceable parts.

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5.2 ENVIRONMENTAL QUALIFICATION STATEMENT

NOMENCLATURE: 3-inch Course Deviation Indicator
MODEL NUMBER: MD200 Series PART NUMBER: MD200-( )
TSO NUMBERS: C34e, C36 e, C40c ETSO NUMBERS: C34e, C36e, 2C40c

MANUFACTURERS SPECIFICATIONS: Minimum Performance Specifications: TS361
MANUFACTURER: Mid-Continent Instrument Co., Inc.
ADDRESS: 9400 E. 34th St. North, Wichita, KS 67226, USA
RTCA DO-160: Rev G, dtd 12/08/10 DATES TESTED: 09/2015 – 11/2015

CONDITIONS SECTION DESCRIPTION OF TEST

Temperature and Altitude
Low Temperature
High Temperature
Altitude
Overpressure
Temperature Variation 5 Category B
Humidity 6 Category A
Operational Shock and
Crash Safety
Vibration 8 Category S, Curves M

Explosion 9 Category X
Waterproofness 10 Category X
Fluids 11 Category X
Sand and Dust 12 Category X
Fungus 13 Category X
Salt Spray 14 Category X
Magnetic Effect 15 Category Z
Power Input 16 Category B(XX)
Voltage Spike 17 Category B
Audio Frequency Conducted
Susceptibility
Induced Signal Susceptibility 19 Category BC(X)
Radio Frequency Susceptibility 20

Emission of Radio Freq Energy 21 Category B*
Lightning Induced Transient
Susceptibility
Lightning Direct Effects 23 Category X
Icing 24 Category X
ESD 25 Category X
Fire, Flammability 26 Category X

REMARKS:
* Per RTCA DO-160B

4

Short-time and Normal Operating Low Temp = -55C

Category F2

Short-time and Normal Operating High Temp = +70C

Altitude = 55K

-15,000 ft

7 Category B

Category S, Curve N*

18 Category B

Category B*

22 Category X

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