Midcontinent MD41 Series Documento tecnico

INSTALLATION MANUAL AND

OPERATING INSTRUCTIONS

MD41-( ) Series GPS Annunciation Control Unit

For Garmin GNS 480 and Garmin AT CNX80 VHF

Communication and Navigation Management System

MD41-1748 28vdc Horizontal Mount

MD41-1748(5V) 28vdc Horizontal Mount with 5 volt lighting

MD41-1758 28vdc Vertical Mount (shown on page 11)

MD41-1758(5V) 28vdc Vertical Mount with 5 volt lighting

MD41-1744 14vdc Horizontal Mount

MD41-1754 14vdc Vertical Mount (shown on page 11)

Mid-Continent Instruments and Avionics Manual Number 9015669

9400 E. 34th Street N., Wichita, KS 67226 USA REV. 1 August 17, 2004

Phone 316-630-0101 Fax 316-630-0723

REV. 1 August 17, 2004 2

Revision Detail

Rev. Date Detail

N/R 06/05/03 Complete issue

1 08/17/04 Added Garmin GNS 480

REV. 1 August 17, 2004 3

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

4.3 CONTINUED AIRWORTHINESS

FIGURE N0. LIST OF ILLUSTRATIONS

3.1 SCHEMATIC PINOUT, 25 PIN DSUB

3.2 OUTLINE DRAWING

3.3 WIRING DIAGRAM, MD41-1744/1754 (14Volt),

MD41-1748/1758/1748(5V)/1758(5V) (28volt)

APPENDIX

ENVIRONMENTAL QUALIFICATION FORM

REV. 1 August 17, 2004 4

SECTION 1 GENERAL DESCRIPTION

1.1 INTRODUCTION

The MD41-( ) is a compact, self -contained GPS Annunciation and Control unit. It meets all

requirements for external (remote) mode selection and status annunciation for the Garmin GNS

480 VHF and Garmin AT CNX80 Communication, Navigation Management System.

Features include dual 20,000 hour lamps used for all annunciations, internally lighted

selection switches and 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

Mounting: Panel

Width: 3.25 Inches

Height: .80 Inches

Depth: 3.20 Inches

Weight: 0.50 lbs.

1.2.2 ENVIRONMENTAL CHARACTERISTICS

TSO Compliance: TSO C129

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

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

Humidity: 95% Non-Condensing

Altitude Range: 0 to 55,000 ft.

Vibration: Cat. U and S

Operational Shock: Rigid Mounting, 6 G Operational

15GCrashSafety

1.2.3 SPECIFICATIONS, ELECTRICAL

Design AllSolidState

MD41-1744/1754 (14VDC) 0.40 Amps

MD41-1748/1758 (28VDC) 0.30 Amps

MD41-1748(5V)/1758(5V) (28DC) 0.30 Amps

REV. 1 August 17, 2004 5

1.2.4 FRONT PANEL CONTROLS AND ANNUNCIATIONS

1.2.4.1 CONTROLS

CDI Momentary action switch, when pressed, will select VOR/ILS

(NAV) or GPS presentation on HSI/CDI.

SUSP Momentary action switch, when pressed, will suspend automatic

waypoint sequencing in the active flight plan.

1.2.4.2 ANNUNCIATIONS

NAV VOR or ILS information presented on the HSI or CDI.

GPS GPS information presented on the HSI or CDI.

MSG Flashing indicates new status message(s) available

WPT Flashing indicates aircraft is 10 to 20 seconds of reaching the

turning point for course change. Steady indicates aircraft in

course change turn.

SUSP Automatic sequencing of waypoints has been suspended.

LOI Loss of Integrity. WAAS/GPS detects a position error or unable

to calculate integrity of position.

PTK Parallel track mode is selected.

ALT Altitude Alert. Indicates the estimated altitude is lower than the

alarm limits.

TERM On indicates aircraft is navigating within 30 miles of the

departure or arrival airport or on a SID or STAR.

APR On indicates the approach is active.

1.2.5 INTERFACE

CDI (select)

J1 Pin 4 Provides a momentary low to the GNS 480 (CNX80)

SUSP (select)

J1 Pin 12 Provides a momentary logic low to the GNS 480 (CNX80)

when Suspend is selected.

NAV annunciation

J1 Pin 2 Receives ground from GNS 480 (CNX80) when in

VOR/ILS mode.

NAV annunciation

output, J1 Pin 16. Logic low when NAV annunciation is turned on. May be

connected to MD200 NAV annunciation input.

GPS annunciation

J1 Pin 1 Receives ground from GNS 480 (CNX80) when in GPS

mode.

REV. 1 August 17, 2004 6

1.2.5 INTERFACE (cont.)

GPS annunciation

output, J1 pin 14 Logic low when GPS annunciation is turned on. May be

connected to MD200 GPS annunciation input.

SUSP annunciation

J1 Pin 24 Requires a logic low to annunciate

TERM annunciation

J1 Pin 15 Requires a logic low to annunciate

APPR annunciation

J1 Pin 3 Requires a logic low to annunciate

WPT annunciation

J1 Pin 8 Requires a logic low to annunciate

MSG annunciation

J1 Pin 6 Requires a logic low to annunciate

PTK annunciation

J1 Pin 11 Requires a logic low to annunciate

ALT annunciation

J1 Pin 10 Requires a logic low to annunciate

LOI annunciation

J1 Pin 9 Requires a logic low to annunciate

Lamp Test

J1 Pin 7 Receives ground from remote test switch to light all

annunciations. (optional connection)

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.

REV. 1 August 17, 2004 7

The MD41-1744/1754/1748/1758/1748(5V)/1758(5V) is TSO’D and certified for use with the

Garmin GNS 480 and Garmin AT CNX80 system. Any attempts to install the listed units in an

installation other than these two systems 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 GNS 480 or CNX80.

1.2.7 MAJOR COMPONENTS

This system is comprised of one major component, the MD41-174X/175X series GPS

Annunciation Control Unit.

REV. 1 August 17, 2004 8

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 air flow 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/NAV 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 as all switching

between GPS, VOR and ILS is handled by the GNS 480 or CNX80.This has allowed a for a

smaller size ACU which 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. 1 August 17, 2004 9

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. MD41-1744 (14volt) or MD41-1748 (28 volt) Horiz. Mount

MD41-1754 (14volt) or MD41-1758 (28volt) Vert. Mount

MD41-1748(5V) (28volt) 5 volt button lighting Horiz. Mount

MD41-1758(5V) (28volt) 5 volt button lighting Vert. Mount

2. J1 Connector Kit (25 pin). MCI PN 7014517

3. Installation Manual. MCI PN 9015669

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 navigation

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.

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

phillips screws.

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.

REV. 1 August 17, 2004 10

REAR VIEW OF J1 CONNECTOR

PIN NO.

1 ---------------------------- GPS ANNUNCIATION

2 ---------------------------- NAV ANNNCIATION

3 ---------------------------- APPR ANNUNCIATION

4 ---------------------------- CDI SOURCE SELECT (momentary logic low sent to receiver)

5 ---------------------------- DIMMER IN (from aircraft dimming bus for push-button lighting)

6 ---------------------------- MSG ANNUNCIATION

7 ---------------------------- LAMP TEST (receives ground from remote test switch)(optional conn.)

8 ---------------------------- WPT ANNUNCIATION

9 ---------------------------- LOI ANNUNCIATION

10 -------------------------- ALT ANNUNCIATION

11 -------------------------- PTK ANNUNCIATION

12 -------------------------- SUSP MODE SELECT (momentary logic low sent to the receiver)

13 -------------------------- 14 or 28 VDC UNIT POWER (depends on dash number)

14 -------------------------- GPS ANNUNCIATION OUTPUT

15 -------------------------- TERM ANNUNCIATION

16 -------------------------- NAV ANNUNCIATION OUTPUT

17 -------------------------- SPARE

18 -------------------------- SPARE

19 -------------------------- SPARE

20 -------------------------- SPARE

21 -------------------------- SPARE

22 -------------------------- SPARE

23 -------------------------- SPARE

24 -------------------------- SUSP ANNUNCIATION

25 -------------------------- POWER GROUND

FIGURE 3-1 SCHEMATIC PINOUT, 25 PIN DSUB

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