Mid-Continent Instrument MD41-1514 Installation manual

INSTALLATION MANUAL AND

OPERATING INSTRUCTIONS

MD41-151X Series

GPS Annunciation Control Unit

For Garmin GTN 6XX/7XX Systems

Horizontal

MD41-1512 14vdc

MD41-1514 28vdc

Vertical

MD41-1513 14vdc

MD41-1515

Horizontal Mount, 5vdc lighting

Mount

28vdc Vertical Mount, 5vdc lighting

REV. A February 21, 2011 MANUAL NUMBER 9017211

Mid-Continent Instruments and Avionics

9400 E. 34

th

Street N., Wichita, KS 67226 USA phone 316-630-0101

 fax 316-630-0723  web www.mcico.com

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. 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 [email protected] www.mcico.com

 Copyright 2011

Mid-Continent Instruments and Avionics

REV. A February 21, 2011 2 Manual Number 9017211

Rev. Date

REVISION DETAIL

Detail

REV. A February 21, 2011 3 Manual Number 9017211

TABLE OF CONTENTS

SECTION 1 GENERAL DESCRIPTION

1.1 INTRODUCTION

1.2 TECHNICAL SPECIFICATIONS

1.2.1 MODELS

1.2.2 PHYSICAL ATTRIBUTES

1.2.3 PERFORMANCE

SECTION 2 INSTALLATION CONSIDERATIONS

2.1 COOLING

2.2 EQUIPMENT LOCATION

2.3 ROUTING OF CABLES

2.4 LIMITATIONS

SECTION 3 INSTALLATION PROCEDURE

3.1 GENERAL INFORMATION

3.2 UNPACKING AND INSPECTING

3.3 CABLE HARNESS

3.3.1 LIGHTING CONTROLS

3.3.2 SIGNALS AND POWER

3.3.3 HARNESS VERIFICATION

3.4 MOUNTING

SECTION 4 OPERATION

4.1 FRONT PANEL CONTROLS AND ANNUNCIATIONS

4.1.1 CONTROLS

4.1.2 ANNUCIATIONS

SECTION 5 CONFORMANCE

5.1 OPERATING INSTRUCTIONS

5.2 CONTINUED AIRWORTHINESS STATEMENT

5.3 ENVIRONMENTAL QUALIFICATION STATEMENT

NUMBER LIST OF TABLES AND FIGURES

TABLE

1.2 PHYSICAL ATTRIBUTES TABLE

TABLE

3.3 CONNECTOR FIGURE

3.3 SCHEMATIC PIONOUT TABLE

DRAWING

DIAGRAM

4.1 FRONT PANEL FIGURE

REV. A February 21, 2011 4 Manual Number 9017211

SECTION 1 GENERAL DESCRIPTION

1.1 INTRODUCTION

The MD41-151X series products are compact, self-contained Annunciation and Control Units (ACUs). The fully integrated control unit provides annunciation and mode selection for Global Positioning System

(GPS) / Satellite-Based Augmentation System (SBAS) navigators. This series of the MD41 product family is specifically designed to work with the Garmin GTN 6XX/7XX series WAAS navigator systems and derivatives with equivalent functionality. It combines the necessary functions and annunciations required to interface with an approved system and provide regulatory compliance with GPS/SBAS minimum performance specifications.

Highlighted features include long-life LEDs used for all lighting, internally backlit selection switches, deadfront inactive annunciations, and the installation option for manual or automatic dimming. An external annunciation dimming adjustment is provided for balancing low-level light conditions.

1.2 TECHNICAL SPECIFICATIONS

1.2.1 MODELS

Unit Configurations

MD41-1510 MD41-1512 MD41-1514

Horizontal Horizontal Horizontal

Power Input

Lighting Input

28VDC

28VDC

14VDC

14VDC

28VDC

5VDC

MD41-1511 MD41-1513 MD41-1515

Power Input

Lighting Input

28VDC

28VDC

1.2.2 PHYSICAL ATTRIBUTES

Characteristics:

Dimensions:

(not including connector or mate)

Mating Connector:

Instrument Panel Mounting:

1.2.3 PERFORMANCE

Specifications:

Table 1.1

14VDC

14VDC

28VDC

5VDC

3.2 inches long

3.25 inches wide

0.8 inches high

Positronic RD25F10JVL0 or equivalent (MCI P/N 7014517)

Rear mount

Table 1.2

Environmental Qualification:

Power Requirement:

REV. A February 21, 2011

RTCA DO-160D Environmental Category

F2CAB(SM/UG)XXXXXXZBABA(TT)M[A3C3]XXA*

* Sections 16, 20, 21, and 22 comply with DO-160C, Section 8

(UG) complies with DO-160F

0.20 A max

5 Manual Number 9017211

Table 1.3

SECTION 2 PRE-INSTALLATION CONSIDERATIONS

2.1 COOLING

No direct cooling is required. As with any electronic equipment, overall reliability may be increased if the unit is not located near a high heat source or crowded next to other equipment. Means of providing some airflow would be considered beneficial.

2.2 EQUIPMENT LOCATION

The MD41-151X series ACU must be mounted as close to the pilot’s field of view as possible. Please reference the GPS/SBAS installation manual for approved locations. The unit depth, with connector attached, must also be taken into consideration when selecting an appropriate location. Allow at least 3 inches of space behind the unit for connector attachment and removal.

2.3 ROUTING OF CABLES

Care must be taken not to bundle the MD41 series ACU 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 coaxial cables. Always use shielded wire when shown on the installation print.

Avoid sharp bends in cabling and routing near aircraft control cables. Also avoid proximity and contact with aircraft structures, avionics equipment, or other obstructions that could chafe wires during flight and cause undesirable effects.

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. 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.

Note that this product is part of an incomplete system. It is designed to be installed with other applicable equipment to provide functionality for global positioning /satellite-based augmentation systems.

REV. A February 21, 2011 6 Manual Number 9017211

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 series ACU. 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 this equipment, make a visual inspection for evidence of any damage that may have incurred during shipment. The following parts should be included: a. GPS ACU – b. J1 Connector Kit (25 pin) –

MCI P/N MD41-151X series

MCI P/N 7014517 c. Installation Manual –

3.3 CABLE HARNESS

MCI P/N 9017211

The MD41 cable harness should be made using 24 AWG wire or larger for all connections. Construct the cable harness with regards to the instructions below and using the Connector Pinout of Figure 3.3,

Schematic Pinout of Table 3.3, and Wiring Diagram of Figure 3.5.

Refer to Section 2: Pre-Installation Considerations in regards to routing precautions.

3.3.1 LIGHTING CONTROL

Button backlighting (pin 5) is powered (5vdc, 14vdc, or 28vdc) from the aircraft’s panel lighting bus. This will allow manual dimming control of the button brightness using the aircraft’s panel lighting control dimmer.

There are three options for annunciation brightness control. The annunciations options can be configured in the following ways:

 Full bright when active o connect aircraft power (same as pin 13 input) to pin 6

 Manual control using the aircraft’s panel lighting control o connect the aircraft lighting bus power output (same as pin 5 input) to pin 6 o (not available for aircraft with 5V lighting bus)

 Automatically dimming using the internal photocell of the unit o connect pin 23 (“Annun Bright/Dim Output”) to pin 6

3.3.2 POWER AND SIGNALS

Wire aircraft power and aircraft ground according to the associated ACU pins in the Pinout

Diagram. Annunciation signals should be wired from the appropriate system inputs and outputs to the associated ACU pins in the Pinout Diagram.

3.3.3 HARNESS VERIFICATION

With the MD41 ACU disconnected, turn on the avionics master switch and use an ohm-meter to verify that aircraft power and panel lighting bus power is on the appropriate pin(s) with appropriate voltage. Also verify that aircraft ground is applied to the appropriate pins.

REV. A February 21, 2011 7 Manual Number 9017211

3.4 MOUNTING

Refer to Section 2: Pre-Installation Considerations in regards to equipment location.

The MD41 ACU is designed for rear panel mounting only. A cutout should be made in the panel in accordance with Figure 3.4 for the unit bezel and two mounting holes. A cutout template is available from

Mid-Continent Instruments and Avionics (reference p/n 8014458) upon request.

Prior to completing the mounting of the unit in the aircraft, make sure to set the Annunciator Dim

Adjustment if automatic dimming is configured for the annunciations. Ideally this procedure is best performed in a dark cockpit to simulate low-light/night time conditions. Connect the unit to the cable harness and turn on master power to the instrument panel and lighting bus. Use a small flat-bladed screwdriver to access the adjustment screw inside the hole on the bottom of the unit. Adjust the screw to increase or decrease the annunciator lighting brightness to a level appropriate with the rest of the panel instrument lighting.

Secure the indicator to the panel with two #4-40 x 3/8 flat head phillips screws.

FIGURE 3.3

REAR VIEW OF 25-PIN D-SUB CONNECTOR (J1)

Connector Pinout

Pin #

1 Annun. GPS input

2 Annun. VLOC input

3 Annun. TERM input

4 CDI Switch output

5 Bright/Dim Button Backlight input

6 Annun. Bright/Dim input

7 Light Test

8 Annun. WPT input

9 Annun. APR input

10 Annun. MSG input

11 OBS input

12 OBS/SUSP Switch output

13 Aircraft Power (+14V/+28V)

Pin #

14 Reserved

15 Reserved

16 Reserved

17 Reserved

18 Reserved

19 Reserved

20 Annun. LOI input

21 Reserved

22 Reserved

23 Annun. Bright/Dim output

24 Annun. SUSP input

25 Ground

TABLE 3.3

SCHEMATIC PINOUT

REV. A February 21, 2011 8 Manual Number 9017211

3.20 MAX

0.125

0.156 typ

0.80

2.73

3.00

3.25

MD41-1510

MD41-1512

MD41-1514

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

FIGURE 3.4

OUTLINE DRAWING

MD41-1511

MD41-1513

MD41-1515

REV. A February 21, 2011 9 Manual Number 9017211

MD41-151X Series ACU

J1

5

13

25

24

14

8

10

2

1

4

20

12

9

3

11

17

7

22

19

18

23

15

6

16

21

5,14 or 28VDC

14 OR 28VDC AIRCRAFT PWR

POWER GND

SUSP ANNUN

RESERVED

OBS/SUSP MODE SELECT

APR ANNUN

TERM ANNUN

WPT ANNUN

MSG ANNUN

VLOC ANNUN

GPS ANNUN

CDI SOURCE SELECT

LOI ANNUN

2A

OBS ANNUN

RESERVED

LAMP TEST

RESERVED

RESERVED

RESERVED

TEST

AUTOMATIC INTERNAL DIMMING ONLY

RESERVED

ANNUN BRIGHT/DIM (3 OPTIONS)

SPARE

SPARE

FROM LIGHTING BUS (for pushbutton lighting, see note 4)

USE 2A CIRCUIT BREAKER

P1002

3

P1001

16

55

34

33

54

52

15

39

GTN 6XX/7XX

53

14

(note 3)

INTERNAL DIMMING

EXTERNAL DIMMING; (EXCEPT -1514/1515) FROM LIGHTING BUS

FULL BRIGHT; FROM MD41-ACU CIRUIT BREAKER (14 OR 28VDC)

NOTES:

1) REFER TO GARMIN GTN 6XX/7XX INSTALLATION MANUAL FOR ACTUAL INSTALLATION.

2) ALL WIRING SHALL BE 24 AWG UNLESS OTHERWISE NOTED.

3) MOMENTARY SWITCH FOR TEST. (optional connection)

4) 5 VOLT FOR MD41-1514/1515, 14 VOLT FOR MD41-1512/1513, AND 28 VOLT FOR MD41-1510/1511.

FIGURE 3.5

WIRING DIAGRAM

REV. A February 21, 2011 10 Manual Number 9017211

SECTION 4 OPERATION

4.1 FRONT PANEL CONTROLS AND ANNUNCIATIONS

4.1.1 CONTROLS

CDI Momentary Switch, when pressed, will select VLOC, or GPS presentation on

HSI/CDI

OBS/SUSP Momentary switch, when pressed, will select OBS, or SUSP.

In OBS MODE, this will enable OBS selection input from a remote HSI/CDI indicator. In SUSP mode, this will suspend automatic waypoint sequencing in the active flight plan.

All button/switch controls are white backlit. Refer to the operation manual of the GPS/SBAS

System equipment manufacturer for additional operational and functional interface details.

4.1.2 ANNUNCIATIONS

LOI

TERM

(AMBER) Loss of Integrity: WAAS/GPS detects a position error or unable to calculate integrity of position

(GREEN) Terminal: Indicates aircraft is navigating within 30 miles of the departure or arrival airport

APR (GREEN)

MSG

VLOC

GPS

(WHITE) Message: Indicates message(s) is active

(GREEN) VOR/Localizer: NAV/ILS information presented on the HSI or CDI

(WHITE) GPS information presented on the HSI or CDI

WPT (WHITE)

AUTO

SUSP

(WHITE) Automatic sequencing of waypoints is active

(WHITE) Suspended: Automatic sequencing of waypoints has been suspended

FIGURE 4.1 FRONT PANEL

4.2 LIGHTING BEHAVIOR

Lighting behavior can be controlled in multiple ways. Button lighting is controlled manually using the aircraft’s panel lighting bus controller. Annunciations can be configured to automatically dim using the internal photocell, configured to be on full bright, or controlled manually with external dimming

(excluding -1514, -1515) using the aircraft’s panel lighting bus controller when activated.

If using the internal dimming feature for the annunciations, the Annunciator Dim Adjust on the outside of the unit can be used to set the brightness at their dimmest level for best night-time viewing.

REV. A February 21, 2011 11 Manual Number 9017211

SECTION 5 CONFORMANCE

5.1 CONTINUED AIRWORTHINESS STATEMENT

No periodic scheduled maintenance or calibration is necessary for continued airworthiness of the MD41 series ACU. If the unit fails to perform to specifications, the unit must be removed and serviced by Mid-

Continent Instruments and Avionics or their authorized designee.

5.2 ENVIRONMENTAL QUALIFICATION STATEMENT

NOMENCLATURE: GPS Annunciator Control Unit (ACU)

MODEL NUMBER: MD41-151X series

MANUFACTURERS SPECIFICATIONS:

TSO NUMBER: C129

Minimum Performance Specifications: Test Specification (TS) 187, Test Data Sheet (TDS) 444

QUALIFICATION STANDARD: RTCA DO-160D (* denotes qualification to RTCA DO-160C)

(** denotes qualification to RTCA DO-160F)

CONDITIONS SECTION

Temperature and Altitude

Low

Temperature

Decompression

4

4.5.1

4.5.2

4.6.2

Overpressure

Temperature Variation

4.6.3

5

DESCRIPTION OF TEST

Category F2

Operating Low Temp = -55C

Operating High Temp = +70C

Altitude = 55K

-15,000 ft

Category C

Operational Shock and

Crash Safety

Vibration 8 Category S, Curve M

Category U, Curve G**

(SM/UG)

Waterproofness 10

Sand and Dust

Salt Spray

Magnetic Effect

Power Input*

Voltage Spike

Audio Frequency Conducted

Susceptibility

Induced Signal Susceptibility

Radio Frequency Susceptibility*

Emission of Radio Freq Energy*

Lightning Induced Transient

Susceptibility*

Lightning Direct Effects

19

20

21

22

12

14

15

16

17

23

Category X

Category X

Category Z

Category B

Category A

Category A

Category T (conducted)

Category T (radiated)

[TT]

M

Category A3 (pin injection)

Category C3 (cable bundle)

[A3C3]

Category X

REV. A February 21, 2011 12 Manual Number 9017211