INSTALLATION MANUAL AND

OPERATING INSTRUCTIONS

MD41-( ) Series GPS ANNUNCIATION CONTROL UNIT

FOR ALLIED SIGNAL KLN 90B

MD41-1324 14vdc Horizontal Mount

MD41-1334 14vdc Vertical Mount (shown on page 11)

MD41-1328 28vdc Horizontal Mount

MD41-1338 28vdc Vertical Mount (shown on page 11)

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 7019747

REV. 2 Jan 2, 1998

MANUAL REVISION AND HISTORY

MANUAL:

REVISION: 1

MD41-1324, -1328, -1334, -1338, -1328(5v), -1338(5v)

Oct. 18, 1997

MANUAL NUMBER: 7019747

This revision level of this manual consist of the following changes:

Added AlliedSignal KI 208A/209A Navigation Indicators to be used with the

MD41-1300 series ACU in place of the MD41-244/248 series Relay Units.

REVISION: 2 Jan 2, 1998

Removed KI 208A/209A from install manual due to incapability of OBS resolver

REV. 2 Jan 2, 1998

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SECTION 1

TABLE OF CONTENTS

GENERAL DESCRIPTION

1.2.4 FRONT PANEL CONTROLS AND ANNUNCIATIONS

SECTION 2 INSTALLATION CONSIDERATIONS

SECTION 3

SECTION 4

INSTALLATION PROCEDURE

3.3

UNPACKING INSPECTING

MOUNTING THE MD41-( )

POST INSTALLATION CHECKOUT

FIGURE N0.

3.1

3.3

LIST OF ILLUSTRATIONS

SCHEMATIC PINOUT, 25 PIN DSUB

OUTLINE

WIRING DIAGRAM, MD41-1324/1334 (14Volt),

MD41-244/248

APPENDIX

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SECTION 1 GENERAL DESCRIPTION

1.1 INTRODUCTION

The MD41-( ) is a compact, self -contained GPS Annunciation and Control unit. It combines all the necessary functions required to interface the Allied Signal KLN 90B approach-certified GPS receiver with the MD41-244/248 remote mounted relay transfer system. In addition, the MD41-( ) contains several GPS status annunciations used to indicate modes selected by the front panel switches and various inputs from the GPS receiver.

A special ILS override feature has been incorporated to cause the MD41-( ) to automatically switch to the NAV mode when the NAV (VOR) receiver is tuned to an ILS frequency. Other features include dual 20,000 hour lamps used for all annunciations, internally lighted selection switches and automatic photocell dimming. A external annunciation dimming adjustment is provided for balancing low level light conditions.

The MD41-1300 series annunciation control unit must be installed with the companion

MD41-244/248 series Relay Unit to be approved as a complete TSO’d system.

1.2 SPECIFICATIONS, TECHNICAL

1.2.1 PHYSICAL CHARACTERISTICS

Height:

1.2.2 ENVIRONMENTAL CHARACTERISTICS

Temperature

C to +70C

REV. 2 Jan 2, 1998

Operational Shock: Rigid Mounting, 6 G Operational

15 G Crash Safety

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1.2.3 SPECIFICATIONS, ELECTRICAL

Design

MD41-1328/1338 (28VDC)

All Solid State

MD41-1324/1334 (14VDC) 0.40 Amps

0.30 Amps

(28DC) Amps

1.2.4 FRONT PANEL CONTROLS AND ANNUNCIATIONS

1.2.4.1 CONTROLS

NAV/GPS Alternate action switch, when pressed, will select

NAV (VOR) GPS presentation on HSI/CDI.

GPS/APR Momentary switch, when pressed, will arm GPS

Approach Mode.

OBS/LEG Alternate action switch, when pressed, will select between

1.2.4.2 ANNUNCIATIONS

OBS and LEG modes.

NAV

GPS

ARM

ACTV

OBS

LEG

J1 Pin 1

NAV (VOR) information presented on the HSI or CDI.

GPS information presented on the HSI or CDI.

GPS is armed for automatic transition to approach mode.

GPS is actively engaged in the approach mode.

This will activate the course selector and also disable the automatic GPS waypoint sequencing to the next leg.

This will disable the course selector input to the GPS and will enable automatic GPS waypoint sequencing to the

MSG

WPT next leg of the pre-planned route.

GPS message alert, from the GPS receiver.

GPS waypoint alert, from the GPS receiver.

1.2.5 INTERFACE

NAV annunciation

J1 Pin 2

Receives ground from transfer relay when relays are in NAV mode.

GPS annunciation Receives ground from transfer relay when relays are in GPS mode.

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1.2.5 INTERFACE (cont.) connection)

Lamp Test

J1 Pin 7

APR ARM Select

J1 Pin 6

APR ARM

OBS/LEG Select

FCS LOC ENGAGE

J1 pin 11

Receives ground from remote test switch to light all annunciations.(optional

Provides a momentary logic low to the

GPS receiver when approach arm is selected.

Receives a logic low from the GPS receiver

Provides a logic low to the GPS receiver

GPS APR ACTV

J1 Pin 8

MSG and WPT annunciation

Receives a logic low from the GPS receiver when a transition is made from arm to active.

A logic low will cause the appropriate annunciation to illuminate. GPS receiver must

GPS DISPLAYED

J1 pin 16

Provides a ground to the GPS receiver when

NAV is selected on the MD41-( ).

ILS Override

JI Pin 15

Receives a logic low from the NAV (VOR) receiver when tuned to an ILS frequency.

This will force the MD41-( ) into NAV mode

regardless NAV/GPS

Logic low when GPS is in ACTIVE mode.

Used to provide a ILS ground to the flight active. system GPS

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1.2.6 EQUIPMENT LIMITATIONS

The MD41-( ) series control units contain specific dash numbers to be used with various GPS receivers. The installer must match the correct controller part number with the GPS receiver 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 MD41-1324/1334/1328/1338/1328(5V)/1338(5V) ACU MUST be installed with the

Mid-Continent Instruments and Avionics MD41-244/248 remote transfer relay in order to be approved as a complete TSO system. These items will not be TSO’d if one is installed without the other.

The MD41-1324/1334/1328/1338/1328(5V)/1338(5V) is TSO’D and certified for use with the

AlliedSignal KLN 90B system. Any attempts to install the listed units in an installation other than the AlliedSignal KLN 90B is prohibited. This will void the TSO.

NOTE: Anytime the MD41-( ) is disconnected or removed from the aircraft, the HSI/CDI will default to NAV (VOR) mode.

This system is comprised of two major components, the MD41-1300 series GPS Annunciation

Control Unit and the MD41-244/248 Remote Relay.

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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.

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 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 have been removed and are now remotely mounted in a separate package designated as the MD41-244/248 Relay Unit.

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.

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SECTION 3 INSTALLATION PROCEDURES

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. MD41-1324 (14volt) or MD41-1328 (28 volt) Horiz. Mount

MD41-1334 (14volt) or MD41-1338 (28volt) Vert. Mount

MD41-1328(5V) (28volt) 5 volt button lighting Horiz. Mount

MD41-1338(5V) (28volt) 5 volt button lighting Vert. Mount

2.

3.

J1 Connector Kit (25 pin). MCI PN 7014517

Installation Manual. MCI PN 7019747

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.

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 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. Normal installation techniques should be applied. Also see equipment limitations, section 1.2.6.

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REAR VIEW OF J1 (bottom) CONNECTOR

J1

PIN NO.

1 ---------------------------- GPS ANNUNCIATION (receives ground from remote transfer relays)

2 ---------------------------- NAV ANNUNCIATION (receives ground from remote transfer relays)

3 ---------------------------- MSG ANNUNCIATION (receives logic low from GPS receiver)

4 ---------------------------- ARM ANNUNCIATION (receives logic low from GPS receiver)

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

6 ---------------------------- GPS APR ARM SELECT (logic low sent to GPS)

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

8 ---------------------------- ACTV ANNUNCIATION (receives logic low from GPS receiver)

9 ---------------------------- WPT ANNUNCIATION (receives logic low from GPS receiver)

10 -------------------------- OBS HOLD ( logic low sent to the GPS receiver)

11 -------------------------- FCS LOC ENGAGE (ground when GPS is in active mode)(for autopilot)

12 -------------------------- TO NAV CIRCUIT BREAKER (for fault monitoring)

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

14 -------------------------- EXTERNAL RELAY ENERGIZE (ground to energize remote transfer relays when GPS is selected)

15 -------------------------- ILS ENERGIZE from NAV/VOR receiver (optional connection)(for ILS override)

16 -------------------------- GPS DISPLAY (ground to GPS receiver in NAV mode)

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

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

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

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

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

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

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

24 -------------------------- SPARE

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

FIGURE 3-1 SCHEMATIC PINOUT, 25 PIN DSUB

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

FIGURE 3-2 OUTLINE DRAWING

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FIGURE 3-3 WIRING DIAGRAM, MD41-1324/1334/1328/1338,

1328(5V)/1338(5V), MD41-244/248 for KLN 90B

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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 25 is aircraft ground.

Turn off the avionics master switch and connect the mating connector to the MD41-( ). Turn on the avionics master switch and the MD41-( ) should come on with the following annunciations.

1.

2.

NAV or GPS

OBS or LEG

3. MSG and/or WPT may be flashing depending on the status of the GPS

receiver.

Press the lamp test button, (if installed) all annunciations should light. Continue pressing the lamp test button and cover the photocell window located in the center of the front panel. All annunciations should dim.

Annunciation brightness at the minimum dimming level may be adjusted by rotation of the dimmer control located on the bottom of the MD41-( ) case. CW rotation lowers the dimming level.

Select NAV using the NAV/GPS button. The presentation on the HSI/CDI will now be information from the VOR receiver. Using a VOR test generator or equivalent VOR signal, verify that the presentation and operation of the HSI/CDI is correct. This will include course resolver, left-right meter, to-from meter and nav warn flag. Now select GPS on the MD41-( ) and tune the VOR receiver to an ILS frequency. The MD41-( ) will be forced to NAV mode and ILS information will be displayed on the HSI/CDI. NOTE, this feature will not work if

“ILS Energize” (J1 pin 15) was not connected at the time of installation.

Next, verify that OBS and LEG annunciations will cycle alternately when pressing the

OBS/LEG button two times. Press the GPS/APR button and the ARM annunciation will illuminate. ARM can be canceled by pressing the GPS/APR button a second time, or by

ACTV input from the GPS receiver. GPS/APR test will not work without a valid GPS signal.

Please refer to section 2.4 of the KLN 90B installation manual for the remaining system tests.

No periodic maintenance or calibration is necessary for continued airworthiness of the

MD41-( ).

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ENVIRONMENTAL QUALIFICATION FORM

RTCA / DO160C

NOMENCLATURE: MD41-( ) GPS ANNUNCIATION CONTROL UNIT

MODEL NO: MD41-( ) TSO NO: C129

CLASS A1

MANUFACTURER TEST SPECIFICATION: MPS 7015613

MANUFACTURER: Mid-Continent Instruments and Avionics

9400 E. 34 th

Street N.

Wichita, KS 672226

Phone (316) 630-0101

Conditions Section Description of Conducted Tests

Temperature and Altitude

Low Temperature

High Temperature

In-Flight Loss of Cooling

Altitude

Decompression

Overpressure

Temperature Variation

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 Categories A1 & F2 except as noted

Cooling air not required

Not Tested

Equipment tested to Category B 5.0

6.0 Equipment tested to Category A Humidity

Shock

Operational

Crash Safety

Vibration

7.0

7.2

7.3

8.0

Equipment tested per DO-160C

Par. 7.2.1

Explosion

Waterproofness

Fluids Susceptibility

9.0

10.0

11.0

Equipment tested without shockmounts to Categories M and N

(Table 8-1)

Equipment identified as Category X, no test required

Equipment identified as Category X , no test required

Equipment identified as Category X, no test required

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Icing

Environmental Qualification (cont.)

Conditions

Sand and Dust

Fungus

Salt Spray

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

Section

12.0

13.0

14.0

15.0

16.0

17.0

18.0

19.0

20.0

21.0

22.0

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 tested to Class Z

Equipment tested to Category B

Equipment tested to Category A

Equipment tested to Category B

Equipment tested to Category A

Equipment tested to Category T

Equipment tested to Category Z

Equipment identified as Category X, no tests required

23.0

24.0

Equipment identified as Category X, no tests required

Equipment identified as Category X, no test required

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