INSTALLATION MANUAL AND

OPERATING INSTRUCTIONS

MD41-1000 SERIES TERRAIN AWARENESS

ANNUNCIATION CONTROL UNIT

MD41-1038 28vdc Vertical Mount (shown on page 12)

MD41-1038(5V) 28vdc Vertical Mount (shown on page 12)

MD41-1024 14vdc Horizontal Mount

MD41-1034 14vdc Vertical Mount (shown on page 12)

Mid-Continent Instruments and Avionics

9400 E. 34 th

Street N., Wichita, KS 67226 USA

Phone 316-630-0101

 Fax 316-630-0723

Manual Number 9015308

REV A JANUARY 21, 2005

Mid-Continent Instruments and Avionics, Wichita, KS

FOREWORD

This manual provides information intended for use by persons who, in accordance with current regulatory requirements, are qualified to install or repair this equipment. If further information is required, please contact:

Mid-Continent Instruments and Avionics

Attn: Customer Service Dept.

9400 E. 34 th

ST North

Wichita, KS 67226 USA

Phone 316-630-0101 Fax 316-630-0723

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: Technical Publications

9400 E. 34 th

ST North

Wichita, KS 67226 USA

Phone 316-630-0101 Fax 316-630-0723

 Copyright 2003

Mid-Continent Instruments and Avionics

REV A January 21, 2005 Manual Number 9015308 2 of 19

A

Mid-Continent Instruments and Avionics, Wichita, KS

Revision Detail

01/21/05 Added “otherwise connect pin 7 to bright/dim switch on aircraft dimming bus” to note 2 of fig. 3-3 and 3-4.

REV A January 21, 2005 Manual Number 9015308 3 of 19

SECTION 1

Mid-Continent Instruments and Avionics, Wichita, KS

TABLE OF CONTENTS

GENERAL DESCRIPTION

1.2.4

1.2.4.2

1.2.5

SECTION 2

FRONT PANEL CONTROLS AND ANNUNCIATIONS

ANNUNCIATIONS

EQUIPMENT LIMITATIONS

INSTALLATION CONSIDERATIONS

SECTION 3 INSTALLATION PROCEDURE

3.3

UNPACKING INSPECTING

MOUNTING THE MD41-( )

SECTION 4 POST INSTALLATION CHECKOUT

OPERATING INSTRUCTIONS

5.6

5.7

5.8

5.9

4.2

SECTION 5

5.1

5.2

5.3

5.4

5.5

INSTRUCTIONS FOR CONTINUED AIRWORTHINESS

INTRODUCTION

CONTROL, OPERATION INFORMATION

MAINTENANCE INSTRUCTIONS

TROUBLESHOOTING INFORMATION

REMOVAL AND REPLACEMENT INFORMATION

DIAGRAMS

SPECIAL INSPECTION REQUIRMENTS

SPECIAL TOOLS

OVERHAUL PERIOD

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Mid-Continent Instruments and Avionics, Wichita, KS

FIGURE NO.

3.1

LIST OF ILLUSTRATIONS

SCHEMATIC PINOUT, 25 PIN DSUB

OUTLINE

3.3

3.4

3.5

WIRING DIAGRAM, MD41-1024, -1034

WIRING DIAGRAM, MD41-1024, -1034, -1028, -1038,

-1028(5v), -1038(5V)

SCHEMATIC DIAGRAM, MD41-1028, -1038, -1028(5v),

-1038(5V)

APPENDIX

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Mid-Continent Instruments and Avionics, Wichita, KS

SECTION 1: GENERAL DESCRIPTION

1.1 INTRODUCTION

The MD41-1024, -1034, -1028, -1038 is a compact, self -contained Annunciation and

Control unit. The fully integrated, control unit provides annunciation and mode selection for TAWS (Terrain Awareness Warning System). It combines all the necessary functions required to interface a wide range of TAWS systems for FAA approval.

Other features include dual 20,000 hour lamps used for all annunciations, internally lighted selection switches and choice of manual or automatic photocell dimming. An external annunciation dimming adjustment is provided for balancing low level light conditions.

1.2 SPECIFICATIONS, TECHNICAL

1.2.1 PHYSICAL CHARACTERISTICS

1.2.2 ENVIRONMENTAL CHARACTERISTICS

Temperature

C to +70C

Operational Shock: Rigid Mounting, 6 G Operational

20 G Crash Safety

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Mid-Continent Instruments and Avionics, Wichita, KS

1.2.3 SPECIFICATIONS, ELECTRICAL

Design All Solid State

MD41-1028(5V), -1038(5V) 0.42 Amps

1.2.4 FRONT PANEL CONTROLS AND ANNUNCIATIONS

1.2.4.1 CONTROLS

TERR/INHB Momentary switch, when pressed, will toggle the 'Inhibit' mode. When active, the 'Inhibit' mode will inhibit certain

TAWS alerts.

1.2.4.2 ANNUNCIATIONS

TERR/NA Terrain information is not available.

(Amber)

TERR

(Amber)

The current flight trajectory brings the aircraft in close proximity to the terrain. Extreme caution should be exercised.

PULL UP The current flight trajectory brings the aircraft in extremely

(Red) close proximity to the terrain. The aircraft is in imminent danger and actions should be taken to rectify the situation.

TERR/

INHB

(White)

The TAWS system has been placed in the 'Inhibit' mode.

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Mid-Continent Instruments and Avionics, Wichita, KS

1.2.5 EQUIPMENT LIMITATIONS

The MD41-1000 series control units contain specific dash numbers to be used with various

Terrain Awareness Warning Systems. The installer must match the correct controller part number with the system that is being installed.

The MD41-1028, -1028(5V), -1038, -1038(5V), -1024, -1034 is TSO’D and certified for use with the Garmin International GNS 500, 500A, 530, 530A Terrain Awareness Warning

System (TAWS). Any attempts to install the listed units in an installation other than above system is prohibited. This will void the TSO.

NOTE: If the MD41-( ) is disconnected or removed from the aircraft, there will be no effect in the operation of the TAWS system.

This system is comprised of one major component, the MD41-1000 series TAWS

Annunciation Control Unit

SECTION 2 INSTALLATION CONSIDERATIONS

2.1 COOLING

No direct cooling is required. As with any electronic equipment, overall reliability may be increased if the MD41-1024, -1034, -1028, -1038 is not located near any high heat source or crowded next to other equipment. Means of providing a gentle airflow will be a plus.

The MD41-1028 must be mounted as close to the pilot’s field of view as possible. Please reference the TAWS installation manual for approved locations. The unit depth, with connector attached, must also be taken into consideration.

2.3 ROUTING OF CABLES

Care must be taken not to bundle the MD41-1024, -1034, -1028, -1038 logic and low level signal lines with any high energy sources. Examples of these sources include 400 HZ AC,

Comm, DME, HF and transponder transmitter coax. Always use shielded wire when shown on the installation print.

Avoid sharp bends in cabling and routing near aircraft control cables.

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Mid-Continent Instruments and Avionics, Wichita, KS

SECTION 3 INSTALLATION PROCEDURES

This section contains interconnect diagrams, mounting dimensions and other information pertaining to the installation of the MD41-1024, -1034, -1028, -1038. 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 UNPACKING AND INSPECTING EQUIPMENT

When unpacking equipment, make a visual inspection for evidence of damage incurred during shipment. The following parts should be included:

1. MD41-1024 (14V) or MD41-1028 (28V) Horiz. Mount

MD41-1034 (14V) or MD41-1038 (28V) Vert. Mount

MD41-1028(5V), (28volt) 5 volt button lighting Horiz. Mount

MD41-1038(5V), (28volt) 5 volt button lighting Vert. Mount

2.

3.

J1 Connector Kit (25 pin). MCI P/N 7014517

Installation Manual. MCI P/N 9015308

3.3 MOUNTING THE MD41-( )

Avoid mounting close to heater vents or other high heat sources. Allow a clearance of at least

3 inches from back of unit for plug removal.

The indicator is secured in place behind the panel since it is designed for rear mount only.

Make a panel cutout as shown in Figure 3-2. Secure the indicator in place with two 4-40 x

3/8 flat head phillip screws.

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Mid-Continent Instruments and Avionics, Wichita, KS

3.4 INSTALLATION LIMITATIONS

Wire the aircraft harness according to figure 3-3 or 3-4. Use at least 24 AWG wire for all connections. Avoid sharp bends and routing cable near high-energy sources. Care must be taken to tie the harness away from aircraft controls and cables. Also see equipment limitations, section 1.2.5.

“The TSO identifies the minimum performance standards, tests and other conditions applicable for issuance of design and production approval of the article. The TSO does not specifically identify acceptable conditions for installations of the article. The TSO applicant is responsible for documenting all limitations and conditions suitable for installation of the article. An applicant requesting approval for installation of the article within a specific type or class of product is responsible for determining environmental and functional compatibility.”

This Annunciation Control Unit is part of an incomplete system. The intended function is to provide required or optional annunciation and mode selection for Class B TAWS systems.

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Mid-Continent Instruments and Avionics, Wichita, KS

1 ANNUNCIATOR FULL BRIGHT #1

2 ANNUNCIATOR FULL BRIGHT #2

3 TERRAIN WARNING BRT/DIM

4 INTERNAL DIMMING PROGRAM #1

5 TERRAIN CAUTION ANNUNCIATE* IN

6 TERRAIN TEST* IN

7 ANNUNCIATOR DIMMING IN

8 28 V PANEL LIGHTING BUS HI

9 PANEL LIGHTING BUS LO

10 TERRAIN NOT AVAILABLE ANNUNCIATE IN

11 TERRAIN PULL UP ANNUNCIATE* IN

12 INTERNAL DIMMING PROGRAM #2

13 28 V AIRCRAFT POWER

14 SPARE

15 SPARE

16 SPARE

17 SPARE

18 SPARE

19

20

Rear View of J1 Mating Connector

TAWS ANNUNCIATE INHIBIT * IN

TAWS INHIBIT * OUT

* Designates an active low signal.

FIGURE 3-1 SCHEMATIC PINOUT, 25 PIN DSUB

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Out

In

---

---

---

---

---

In

Out

---

---

---

---

---

In

In

In

In

In

In

IO

Out

Out

Out

In

Out

In

Mid-Continent Instruments and Avionics, Wichita, KS

MD41-1024, -1028, -1028(5V) Horizontal

MD41-1034, -1038, -1038(5V) Vertical

Note 1: Use two 4-40 X 3/8” Flat Head Phillips Screws for Mounting

FIGURE 3-2 OUTLINE DRAWING

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(note 1)

(note 1)

(note 1)

(note 2)

(note 2)

18

19

20

21

22

23

24

25

15

16

17

9

10

11

12

13

14

6

7

8

1

2

3

4

5

Mid-Continent Instruments and Avionics, Wichita, KS

ANNUNCIATOR FULL BRIGHT #1

ANNUNCIATOR FULL BRIGHT #2

TERRAIN WARNING BRT/DIM

INTERNAL DIMMING PROGRAM #1

TERRAIN CAUTION ANNUNCIATE* IN

TERRAIN TEST* IN

ANNUNCIATOR DIMMING IN

14V PANEL LIGHTING BUS HI

TEST

11

(note 3)

PANEL LIGHTING BUS LO

TERRAIN NOT AVAILABLE ANNUNCIATE IN

TERRAIN WARNING ANNUNCIATE* IN

INTERNAL DIMMING PROGRAM #2

14V AIRCRAFT POWER

TO MD41-ACU CIRCUIT BREAKER

2A

9

10

SPARE

SPARE

SPARE

SPARE

SPARE

TAWS ANNUNCIATE INHIBIT* IN

TAWS INHIBIT* OUT

POWER GROUND/AIRCRAFT GROUND

AIRCRAFT GROUND

AIRCRAFT GROUND

AIRCRAFT GROUND

AIRCRAFT GROUND

12

1

17

18

19

20

21

NOTES:

1) JUMPER 3 TO 1 FOR FULL BRIGHT TERRAIN WARNING.

JUMPER 3 TO 4 FOR TERRAIN WARNING BRIGHTNESS TO BE CONTROLLED BY INTERNAL PHOTOCELL.

2) JUMPER 7 TO 12 FOR ANNUNCIATION BRIGHTNESS TO BE CONTROLLED BY INTERNAL PHOTOCELL,

OTHERWISE CONNECT PIN 7 TO AIRCRAFT BRIGHT/DIM SWITCH.

3) MOMENTARY SWITCH FOR ANNUNCIATION LAMP TEST. (optional connection)

4) REFER TO GARMIN INSTALLATION MANUAL FOR ACTUAL INSTALLATION.

* DESIGNATES AN ACTIVE LOW SIGNAL.

5) REFER TO ACU SCHEMATIC IN THIS MANUAL FOR DETAILED CIRCUIT.

FIGURE 3-3 WIRING DIAGRAM, MD41-1024, -1034.

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Mid-Continent Instruments and Avionics, Wichita, KS

(note 1)

(note 1)

(note 1)

(note 2)

(note 4)

(note 2)

15

16

17

18

19

20

21

22

23

24

25

9

10

11

12

6

7

8

13

14

1

2

3

4

5

MD41-1028 ANNUNCIATION-CONTROL

J1 28 VOLT

GNS 530

P5050

ANNUNCIATOR FULL BRIGHT #1

ANNUNCIATOR FULL BRIGHT #2

TERRAIN WARNING BRT/DIM

INTERNAL DIMMING PROGRAM #1

TERRAIN CAUTION ANNUNCIATE* IN

TERRAIN TEST* IN

ANNUNCIATOR DIMMING IN

28V PANEL LIGHTING BUS HI

TEST

11

(note 3)

PANEL LIGHTING BUS LO

TERRAIN NOT AVAILABLE ANNUNCIATE IN

TERRAIN WARNING ANNUNCIATE* IN

INTERNAL DIMMING PROGRAM #2

28V AIRCRAFT POWER

9

10

TO MD41-ACU CIRCUIT BREAKER

2A

SPARE

SPARE

SPARE

SPARE

SPARE

TAWS ANNUNCIATE INHIBIT* IN

TAWS INHIBIT* OUT

POWER GROUND/AIRCRAFT GROUND

AIRCRAFT GROUND

AIRCRAFT GROUND

AIRCRAFT GROUND

AIRCRAFT GROUND

12

1

17

18

19

20

21

NOTES:

1) JUMPER 3 TO 1 FOR FULL BRIGHT TERRAIN WARNING.

JUMPER 3 TO 4 FOR TERRAIN WARNING BRIGHTNESS TO BE CONTROLLED BY INTERNAL PHOTOCELL.

2) JUMPER 7 TO 12 FOR ANNUNCIATION BRIGHTNESS TO BE CONTROLLED BY INTERNAL PHOTOCELL,

OTHERWISE CONNECT PIN 7 TO AIRCRAFT BRIGHT/DIM SWITCH.

3) MOMENTARY SWITCH FOR ANNUNCIATION LAMP TEST. (optional connection)

4) 5 VOLT FOR MD41-1028(5V)/1038(5V)

5) REFER TO GARMIN INSTALLATION MANUAL FOR ACTUAL INSTALLATION.

* DESIGNATES AN ACTIVE LOW SIGNAL

6) REFER TO ACU SCHEMATIC IN THIS MANUAL FOR DETAILED CIRCUIT.

FIGURE 3-4 WIRING DIAGRAM, MD41-1028, -1038

-1028(5V), -1038(5V)

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Mid-Continent Instruments and Avionics, Wichita, KS

FIGURE 3-5 SCHEMATIC, MD41-1028, -1038, -1028(5V), -1038(5V)

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Mid-Continent Instruments and Avionics, Wichita, KS

SECTION 4 POST INSTALLATION CHECKOUT

4.1 PRE INSTALLATION TESTS

With the MD41-( ) disconnected, turn on the avionics master switch and verify that aircraft power is on pin 13 for. Using an ohm-meter, verify pin 21 is aircraft ground.

Refer to the TAWS pilots guide or installation manual for final testing of the MD41-( ).

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Mid-Continent Instruments and Avionics, Wichita, KS

SECTION 5: INSTRUCTIONS FOR CONTINUED AIRWORTHINESS

5.1 INTRODUCTION

This document identifies the instructions for Continued Airworthiness for the MD1000 series

TAWS Annunciation Control Unit.

5.2 CONTROL, OPERATION INFORMATION

Refer to the Garmin International GNS 530 Pilots Guide and section 1.2.4 of this manual.

Repair of the MD41-1000 ACU is “on condition only”, periodic maintenance is not required.

Calibration and inspection intervals are not required. Service life will be a minimum of 20,000 hours.

5.4 TROUBLESHOOTING INFORMATION

Refer to the MD41-1000 series Maintenance Manual.

5.5 REMOVAL AND REPLACEMENT INFORMATION

If the unit is removed and reinstalled, a functional check of the equipment should be conducted in accordance with the Garmin International GNS 530 preflight test procedure.

5.6 DIAGRAMS

Refer to figure 3-2, 3-3 and 3-4 of this manual.

5.7 SPECIAL INSPECTION REQUIRMENTS: N/A

5.8 SPECIAL TOOLS: None

5.9

OVERHAUL PERIOD: No overhaul time limitations

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Mid-Continent Instruments and Avionics, Wichita, KS

Temperature and Altitude

Low Temperature

High Temperature

In-Flight Loss of Cooling

Altitude

Decompression

Overpressure

Temperature Variation

Humidity

Shock

Operational

Crash Safety

Vibration

Explosion

Waterproofness

ENVIRONMENTAL QUALIFICATION FORM

RTCA / DO160D

NOMENCLATURE: MD41-( ) TERRAIN AWARENESS ANNUNCIATION CONTROL

UNIT

MODEL NO: MD41-( ) TSO C151a

MANUFACTURER: Mid-Continent Instruments and Avionics

9400 E. 34 th

Street N.

Wichita, KS 67226

Phone (316) 630-0101

Conditions Section Description of Conducted Tests

4.0

4.5.1

4.5.2 & 4.5.3

4.5.4

4.6.1

4.6.2

4.6.3

Equipment tested to Category A1 and F2

Cooling air not required

Not Tested

5.0

6.0

7.0

7.2

7.3

8.0

9.0

10.0

Equipment tested to Category C

Equipment tested to Category A

Equipment tested to Category B

Aircraft type 1 (helicopter) tested to category U

Aircraft type 2 through 6 tested to category S

Equipment identified as Category X, no test required

Equipment identified as Category X , no test required

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Mid-Continent Instruments and Avionics, Wichita, KS

Environmental Qualification (cont.)

Fluids Susceptibility

Sand and Dust

Fungus

Salt Spray

Conditions

Magnetic Effect

Power Input

Voltage Spike

Audio Frequency

Susceptibility

Induced Signal Susceptibility

Radio Frequency

Susceptibility

Radio Frequency Emissions

Lightning Induced Transient

Susceptibility

Lightning Direct Effects

Icing

Section

11.0

12.0

13.0

14.0

15.0

16.0

17.0

18.0

Description of Conducted Tests

Equipment identified as Category X, no test required

Equipment identified as Category X, no test required

Equipment identified as Category X, no test required

Equipment identified as Category X, no test required

Equipment tested to Class Z

Equipment tested to Category B

Equipment tested to Category A

Equipment tested to Category B

19.0

20.0

21.0

22.0

23.0

24.0

Equipment tested to Category A

Equipment tested to Category T

Equipment tested to Category B and M

Equipment tested to Category A3C3

Equipment identified as Category X, no tests required

Equipment identified as Category X, no test required

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