Mid-Continent Instruments MD41 Series Technisches Dokument

INSTALLATION MANUAL AND

OPERATING INSTRUCTIONS

MD41-( ) Series GPS Annunciation Unit

For Garmin GNS 430/430W/530/530W VHF

Communication and Navigation Management System

MD41-1484W 14VDC Horizontal Mount

MD41-1488W 28VDC Horizontal Mount

MD41-1494W 14VDC Vertical Mount

MD41-1498W 28VDC Vertical Mount

MID-CONTINENT INST. CO., INC MANUAL NUMBER 9016478

REV. C 2April 24, 2007

Revision History

ECO Rev. Date Detail

N/R 01/19/07 Initial release.

A 02/15/07 J1 connector was 9016475, now 9016479.

B 03/12/07 Corrected section 4.1 to show proper pins,

corrected mating connector rear view.

4828 C 4/24/07 Correct connector schematic pinout in section

1.2.5. Add –1494W and –1498W versions.

REV. C 3April 24, 2007

TABLE OF CONTENTS

SECTION 1 GENERAL DESCRIPTION

1.1 INTRODUCTION

1.2 SPECIFICATIONS, TECHNICAL

1.2.1 PHYSICAL CHARACTERISTICS

1.2.2 ENVIRONMENTAL CHARACTERISTICS

1.2.3 SPECIFICATIONS, ELECTRICAL

1.2.4 FRONT PANEL CONTROLS AND ANNUNCIATIONS

1.2.4.1 CONTROLS

1.2.4.2 ANNUNCIATIONS

1.2.5 INTERFACE

1.2.6 EQUIPMENT LIMITATIONS

1.2.7 MAJOR COMPONENTS

SECTION 2 INSTALLATION CONSIDERATIONS

2.1 COOLING

2.2 EQUIPMENT LOCATION

2.3 ROUTING OF CABLES

SECTION 3 INSTALLATION PROCEDURE

3.1 GENERAL INFORMATION

3.2 UNPACKING AND INSPECTING

3.3 MOUNTING THE MD41-( )

3.4 INSTALLATION LIMITATIONS

SECTION 4 POST INSTALLATION CHECKOUT

4.1 PRE-INSTALLATION TEST

4.2 OPERATING INSTRUCTIONS

FIGURES LIST OF ILLUSTRATIONS

3.1 SCHEMATIC PINOUT, 15 PIN HIGH DENSITY D-SUB

3.2 OUTLINE DRAWING

3.3 INSTRUMENT PANEL MOUNTING

3.4 WIRING DIAGRAM, MD41-1484W/1488W/1494W/1498W

APPENDIX RTCA DO-160C ENVIRONMENTAL QUALIFICATION FORM

REV. C 4April 24, 2007

SECTION 1 GENERAL DESCRIPTION

1.1 INTRODUCTION

The MD41-( ) is a compact, self-contained GPS Annunciation unit. This unit

displays status annunciation received from the Garmin GNS 430/430W/530/530W

series GPS navigation management systems.

Features include dual 20,000 hour lamps used for all annunciations along with

automatic photocell dimming. An external annunciation dimming adjustment is

provided for balancing low-level light conditions.

1.2 TECHNICAL SPECIFICATIONS

1.2.1 PHYSICAL CHARACTERISTICS

Mounting: Front mount, panel

Width: 2.45 inches

Height: 0.75 inches

Depth: 2.60 inches (max)

Weight: 0.2 pounds

1.2.2 ENVIRONMENTAL CHARACTERISTICS

TSO Compliance: TSO C129

Applicable Documents: RTCA DO-160C, DO-208

Operating Temperature Range: -55°C to +70°C

Humidity: 95% Non-Condensing

Altitude Range: 0 to 55,000 ft.

Vibration: RTCA DO-160C, Cat. M and N

Operational Shock: Rigid Mounting, 6G Operational

15 G Crash Safety

REV. C 5April 24, 2007

1.2.3 ELECTRICAL SPECIFICATIONS

Design All Solid State

MD41-1484W (14VDC) 0.30 Amps

MD41-1488W (28VDC) 0.25 Amps

MD41-1494W (14VDC) 0.30 Amps

MD41-1498W (28VDC) 0.25 Amps

1.2.4 FRONT PANEL CONTROLS AND ANNUNCIATIONS

1.2.4.1 ANNUNCIATIONS

VLOC NAV or ILS information presented on the HSI or CDI

GPS GPS information presented on the HSI or CDI

MSG ON indicates message(s) active.

WPT ON indicates reaching the arrival waypoint.

TERM ON indicates aircraft is within 30 miles of departure or

arrival airport

APR ON indicates the approach is active.

INTG ON indicates GPS receiver detected a position error

or is unable to calculate the integrity of the position

1.2.5 INTERFACE

INTG annunciation Requires a logic low to annunciate

J1 Pin 1

WPT annunciation Requires a logic low to annunciate

J1 Pin 2 when in VOR/ILS mode

MSG annunciation Requires a logic low to annunciate

J1 Pin 3

TERM annunciation Requires a logic low to annunciate

J1 Pin 4

APR annunciation Requires a logic low to annunciate

J1 Pin 6

VLOC annunciation Receives ground from GNS 430/530

J1 Pin 7

GPS annunciation Receives ground from GNS 430/530

J1 Pin 8 when in GPS mode.

Lamp Test Receives ground from remote test switch

J1 Pin 10 to light all annunciations (optional connection)

J1 Pin 15 Ground

REV. C 6April 24, 2007

1.2.6 EQUIPMENT LIMITATIONS

The MD41-( ) series control units contain specific dash numbers to be used with

various GPS receivers or Navigation Management Systems. The installer must match

the correct controller part number with the system being installed.

The conditions and tests required for TSO approval of this article are minimum

performance standards. It is the responsibility of those desiring to install this article

either on or within a specific type or class of aircraft to determine that the aircraft

installation conditions are within the TSO standards. The article may be installed

only if further evaluation by the applicant documents an acceptable installation and

is approved by the Administrator.

The MD41-1484W/1488W/1494W/1498W are TSO certified and approved for use

with the Garmin GNS 430/430W/530/530W system. This includes the (A), (W) and

TAWS system versions of the Garmin equipment. Any attempts to install the listed

units in an installation other than the GNS 430/530 system is prohibited.

This will void the TSO.

NOTE: If the MD41-( ) is disconnected or removed from the aircraft, it will not

affect the operation of the GNS 430/430W/530/530W.

1.2.7 MAJOR COMPONENTS

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

1484W/1488W/1494W/1498W GPS Annunciation Control Units.

REV. C 7April 24, 2007

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-( ) is not located near any high heat source or crowded next

to other equipment. Means of providing a gentle airflow will be a plus.

2.2 EQUIPMENT LOCATION

The MD41-( ) must be mounted as close to the pilot’s field of view as possible. The

preferable location is near the HSI/CDI that will be displaying the GPS/VLOC

information. The unit depth, with connector attached, must also be taken into

consideration. Note: Unlike previous versions of the MD41 Annunciation Control Units

(ACU), the transfer relays are not required since the GNS 430/530 handles all

switching between GPS, VOR and ILS. This has allowed for a smaller size ACU that

now provides more options for panel mounting.

2.3 ROUTING OF CABLES

Care must be taken not to bundle the MD41-( ) 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.

REV. C 8April 24, 2007

SECTION 3: INSTALLATION PROCEDURES

3.1 GENERAL INFORMATION

This section contains interconnect diagrams, mounting dimensions and other

information pertaining to the installation of the MD41-( ). 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. MD41-1484W (14VDC) or MD41-1488W (28VDC) Horiz. Mount

MD41-1494W (14VDC) or MD41-1498W (28VDC) Vertical Mount

2. Installation kit P/N 9016480 consisting of the following items:

A. J1 Connector Kit (15 pin) MCI P/N 9016479

B. 2 ea mounting brackets MCI P/N 8018483

C. 4 ea 4-40x ½ pan Phillips screws MCI P/N 90-416-00011

D. 2 ea 4-40x 9/16 flat Phillips screws MCI P/N 90-418-10011

E. 1 ea panel cutout template MCI P/N 8018954

3. Installation Manual MCI P/N 9016478

3.3 MOUNTING THE MD41-( )

Plan a location in the aircraft for the MD41-( ) to be mounted as close to the pilot’s

field of view as possible. The preferable location is near the HSI/CDI that will be

displaying the GPS information. 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.

Use the dimensions shown in figure 3-3 to prepare opening and screw holes for the

ACU. A file template has been provided to use for these measurements and hole

cutout Carefully measure the locations for the screw holes and mark the drill locations

with a center punch. Drill all six holes. A steel template (P/N 8018954) is supplied to

aid in locating holes and cutting out the panel. The template may be mounted to the

instrument panel to allow a file to be used to complete the cutout area. The front plate

of the ACU has a recessed area on the back so a flat head screw is not absolutely

necessary. Attach the mounting brackets to the rear side of the instrument panel with

four 4-40x1/2 pan-head screws. Insert the ACU through the front of instrument panel

and fasten with two 4-40 x 9/16 flat-head screws.

REV. C 9April 24, 2007

3.4 INSTALLATION LIMITATIONS

Wire the aircraft harness according to figure 3-3. 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. Normal

installation techniques should be applied. Also see equipment limitations, section

1.2.6.

REAR VIEW OF MATING CONNECTOR

Pin # Pin #

1 INTG Annun. 9 Reserved

2 WPT Annun. 10 Lamp Test

3 MSG Annun. 11 Reserved

4 TERM Annun. 12 Reserved

5 28 VDC Power 13 Reserved

6 APR Annun. 14 Reserved

7 VLOC Annun. 15 Ground

8 GPS Annun.

Connector Pinout

FIGURE 3-1 SCHEMATIC PINOUT, 15 PIN HIGH DENSITY D-SUB

REV. C 10 April 24, 2007

FIGURE 3-2 OUTLINE DRAWING

2.450

0.150

2.150

0.375

0.750

2.392 MAX

0.150

15-pin

High Density

D-Sub

2.150

2.450

0.150

0.375 0.750

MD41-1484W, MD41-1488W MD41-1494W, MD41-1498W

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