ALT-1000 Radio Altimeter System · 2017-05-23 · 1/2 July 18, 2012 TO: HOLDERS OF ROCKWELL...

installation manual

ALT-1000 Radio Altimeter System

Export Control Classification Notice (ECCN) for this document is 7E994.

© 2012 Rockwell Collins. All rights reserved.

1/2

July 18, 2012

TO: HOLDERS OF ROCKWELL COLLINS® ALT-1000 RADIO ALTIMETER SYSTEM INSTALLATION MANUAL (CPN 523-0806452)

DESCRIPTION OF REVISION NO 2

This page shows all pages of the manual that are added, changed, or removed. Replace the specified pages of the manual with the new pages supplied. Record the applicable data on the Record of Revisions page.

All changed pages keep data necessary to do maintenance on all equipment models. Black bars on the side of the page identify changes.

PAGE NUMBER DESCRIPTION OF REVISION AND REASON FOR CHANGE

SERVICE BULLETIN EFFECTIVITY

A, B, i thru ix/ (x Blank)

Revised to reflect current revision.

1-1 thru 1-19/(1-20 Blank), 2-1 thru 2-69/(2-70 Blank)

Replaced Chapter 1, General Information and Chapter 2, Installation. Pages that have changed are listed below.

1-1, 1-2 Revised Equipment Covered Table 1-1 to add new top level CPNs.

1-5 Revised Table 1-2, 339H-4/4A Radio Altimeter Indicator, Description.

1-8 Revised Table 1-6 ALT Radio Altimeter Receiver-Transmitter, Equipment Specifications. For Height and Length.

1-19/(1-20 Blank) Revised Table 1-12 Related Publications.

2-10 Revised paragraph 2.6.6.2 Mounting instructions.

2-31/(2-32 Blank), 2-33/(2-34 Blank)

Revised Figure 2-10 to current released revision.

T-1

installation manual

Rockwell CollinsCedar Rapids, Iowa 52498

Printed in the United States of America © 2012 Rockwell Collins. All rights reserved.

523-0806452-201116

(ALT-1000_IM_JUL_18/2012)1st Edition, Jan 29/2005

2nd Revision, Jul 18/2012


This manual includes coverage of the following equipment:

Unit Model No Collins Part No Radio Altimeter ALT-1000 822-1939-001, -002, -005, -006, -021, -025

Radio Altimeter Indicator 339H-4 622-1204-001, thru -008, -010

Radio Altimeter Indicator 339H-4A 622-1205-001, thru -006

Radio Altimeter Indicator ALI-55 622-2937-001, thru -005, -008, -009

Radio Altimeter Indicator ALI-55A 622-2938-001, thru -004

Radio Altimeter Indicator ALI-55B 622-5367-001

Radio Altimeter Indicator DRI-55 622-4160-001, thru -008, -011 thru -018

Radio Altimeter Antenna 437X-1 522-4140-001, thru -004, -006, -007

Radio Altimeter Antenna 437X-1A 522-4255-001, thru -004, -006, -007

Radio Altimeter Antenna 437X-1B 622-0954-001, -002

Radio Altimeter Antenna ANT-50A 622-3698-001

Radio Altimeter Antenna ANT-51A 622-4550-001

Radio Altimeter Antenna ANT-52 622-6793-001

Universal Mount UMT-12 622-5212-004

Universal Mount 390R-19 622-1195-301

ROCKWELL COLLINS INSTALLATION MANUAL

T-2 Jul 18/2012

PROPRIETARY NOTICE NOTICE: FREEDOM OF INFORMATION ACT (5 USC 552) AND DISCLOSURE OF CONFIDENTIAL INFORMATION GENERALLY (18 USC 1905) This document and the information disclosed herein are proprietary data of Rockwell Collins. Neither this document nor the information contained herein shall be used, reproduced, or disclosed to others without the written authorization of Rockwell Collins except to the extent required for installation or maintenance of recipient’s equipment. This document is being furnished in confidence by Rockwell Collins. The information disclosed herein falls within exemption (b) (4) of 5 USC 552 and the prohibitions of 18 USC 1905. SOFTWARE COPYRIGHT NOTICE © 2004 - 2005 ROCKWELL COLLINS. ALL RIGHTS RESERVED. All software resident in this equipment is protected by copyright.

We try to supply manuals that are free of errors, but some can occur. If a problem is found with this manual, you can send the necessary data to Rockwell Collins. When you report a specified problem, give short instructions. Include the manual part number, the paragraph or figure number, and the page number. To send data to Rockwell Collins about this manual: Address: Rockwell Collins 350 Collins Road NE, M/S 153-250 Cedar Rapids, IA 52498-0001 Email: [email protected] To get more manuals: Address: Rockwell Collins Customer Response Center 400 Collins Road NE, M/S 133-100 Cedar Rapids, IA 52498-0001 TELEPHONE: 1.888.265.5467 INTERNATIONAL: 1.319.265.5467 FAX: 319.295.4941 Email: [email protected]

Export Control Classification Notice (ECCN) for this document is 7E994.

523-0806452

INSERT LATEST CHANGED PAGES. DESTROY SUPERSEDED PAGES.

LIST OF EFFECTIVE PAGES NOTE: The portion of the text affected by the changes is indicated by a vertical linein the outer margins of the page. Changes to illustrations are indicated byshaded or screened areas, or by miniature pointing hands.

Dates of issue for original and changed pages are:

Original . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .January 29, 2004Change 1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . July 18, 2005Change 2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . July 18, 2012

TOTAL NUMBER OF PAGES IN THIS PUBLICATION IS 126 CONSISTING OF THE FOLLOWING:

Page No. *Change No. Page No. *Change No.

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INSERT LATEST CHANGED PAGES. DESTROY SUPERSEDED PAGES.

LIST OF EFFECTIVE PAGES NOTE: The portion of the text affected by the changes is indicated by a vertical linein the outer margins of the page. Changes to illustrations are indicated byshaded or screened areas, or by miniature pointing hands.

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2-49 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .22-50 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .22-51 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .22-52 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .22-53 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .22-54 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .22-55 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .22-56 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .22-57 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .22-58 Blank. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .22-59 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .22-60 Blank. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .22-61 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .22-62 Blank. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .22-63 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .22-64 Blank. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .22-65 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .22-66 Blank. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .22-67 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .22-68 Blank. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .22-69 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .22-70 Blank. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2

3-1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .03-2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .03-3. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .03-4. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .03-5. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .03-6. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .04-1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .04-2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .04-3. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .04-4 Blank . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .04-5. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .04-6 Blank . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .05-1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .05-2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .05-3. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .05-4. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .05-5. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .05-6. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .05-7. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .05-8. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .05-9. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .05-10 Blank. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .0

*Zero in this column indicates an original page.B July 18, 2012

523-0806452

TABLE OF CONTENTS

Chapter Page

LIST OF ILLUSTRATIONS .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . iii

LIST OF TABLES .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . iv

INTRODUCTION .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . vGeneral . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . v

SAFETY SUMMARY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .viiiGeneral Advisories for All Units . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .viii

1 General Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1-11.1 INTRODUCTION .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1-11.2 PURPOSE OF EQUIPMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1-11.3 RELATED PUBLICATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1-11.4 STORAGE .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1-1

2 Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-12.1 GENERAL .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-12.2 UNPACKING AND INSPECTING EQUIPMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-12.3 PREINSTALLATION CHECK .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-12.4 SPECIAL INSTRUCTIONS .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-12.4.1 Connector Contact Assembly and Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-22.5 PLANNING .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-22.5.1 Installation Configurations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-22.5.2 Strapping Options . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-32.5.3 Cooling Considerations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-72.6 INSTALLATION AND REMOVAL PROCEDURES .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-72.6.1 UMT-12 (Preferred) or 390R-19 (Alternate) Mounting Tray . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-72.6.2 ALT-1000 Radio Altimeter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-82.6.3 ALI-55/55A/55B Radio Altitude Indicator (Used With ALT-1000 (-00X Status) System) . . . . . . . . . . . . . . . . . . . . . . .2-82.6.4 DRI-55 Digital Radio Altitude Indicator (Used With ALT-1000 (-00X or -02X Status) System) . . . . . . . . . . . . . . . .2-82.6.5 339H-4/4A Radio Altitude Indicator (Used With ALT-1000 (-02X Status) System) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-92.6.6 437X-1/1A/1B or ANT-50A/51A/52 Antenna . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-92.7 TESTING .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-122.7.1 Post Installation Test, Systems with ALI-55/55A/55B or 334H-4/4A Indicators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-122.7.2 Post Installation Test, Systems with DRI-55 Indicators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-13

3 Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-13.1 GENERAL .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-13.2 ALI-55/55A/55B RADIO ALTITUDE INDICATORS, DISPLAYS, AND CONTROLS . . . . . . . . . . . . . . . . . . . . . . . .3-13.2.1 Pointer and Dial Scale . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-13.2.2 Decision Height (DH) Index and DH Adjustment Knob . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-23.2.3 DH Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-23.2.4 Warning Flag . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-23.2.5 TEST Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-23.3 339H-4/4A RADIO ALTITUDE INDICATORS, DISPLAYS, AND CONTROLS .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-33.3.1 Pointer and Dial Scale . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-33.3.2 Other Features . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-43.4 DRI-55 DIGITAL RADIO ALTITUDE INDICATOR, DISPLAYS, AND CONTROLS .. . . . . . . . . . . . . . . . . . . . . . . .3-43.4.1 Radio Altitude Display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-43.4.2 Decision Height (DH) Display and DH/PUSH TEST Knob . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-53.4.3 DH Annunciator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-53.4.4 DH/PUSH TEST Knob . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-53.5 OPERATING PROCEDURES .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-63.5.1 Preflight Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-6

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table of contents 523-0806452

Chapter Page3.5.2 Flight Operations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-63.5.3 Points to Remember . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-7

4 Theory of Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-14.1 INTRODUCTION .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-14.2 OVERVIEW .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-14.2.1 Installation Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-14.3 FUNCTIONAL THEORY .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-14.3.1 ALT-1000 Radio Altimeter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-14.3.2 437X-1/1A/1B Radio Altimeter Antenna . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-34.3.3 ANT-50A/51A Radio Altimeter Antenna . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-34.3.4 ANT-52 Radio Altimeter Antenna . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-34.3.5 339H-4/4A Radio Altimeter Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-34.3.6 ALI-55/55A/55B and DRI-55 Radio Altimeter Indicators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-3

5 Maintenance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5-15.1 GENERAL .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5-15.2 MAINTENANCE SCHEDULE .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5-15.3 TEST EQUIPMENT AND POWER REQUIREMENTS .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5-15.3.1 Test Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5-15.3.2 Power Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5-15.4 TESTING AND TROUBLESHOOTING .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5-15.4.1 Diagnostic Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5-15.4.2 Analog Diagnostic Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5-15.4.3 Digital Diagnostic Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5-3

ii 18 July 2012

523-0806452

LIST OF ILLUSTRATIONS

Figure Title Page

1-1 ALT-1000 Radio Altimeter System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1-42-1 Aircraft Installation Delay (AID) and RF Cable Requirements Chart . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-62-2 ALT-1000 Radio Altimeter Input/Output Interface Circuits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-152-3 ALT-1000 Radio Altimeter Mating Connector Pin Assignment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-172-4 ALT-1000 Radio Altimeter BITE Mating Connector Pin Assignment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-182-5 ALI-55/55A/55B Radio Altimeter Indicator Mating Connector Pin Assignment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-192-6 DRI-55 Digital Radio Altimeter Indicator Mating Connector Pin Assignment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-202-7 ALT-1000 Radio Altimeter System, Typical Interconnect Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-212-8 ALT-1000 (-02X Status Units) Radio Altimeter System for 2000-Foot Operation, Interconnect Wiring Diagram . 2-272-9 ALT-1000 (-00X Status Units) Radio Altimeter System for 2500-Foot Operation, Interconnect Wiring Diagram . 2-292-10 ALT-1000 Altimeter System, Outline and Mounting Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-312-11 ALI-55/55A/55B Radio Altimeter Indicator, Outline and Mounting Diagram .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-352-12 DRI-55 Digital Radio Altitude Indicator, Outline and Mounting Dimensions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-372-13 DRI-55 Digital Radio Altitude Indicator, Typical Installations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-392-14 339H-4/4A Radio Altimeter Indicator, Outline and Mounting Diagram .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-412-15 437X-1/1A/1B and ANT-50A/51A/55 Antenna, Typical Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-432-16 ANT-50A Antenna (CPN 622-3698-001), Outline and Mounting Diagram .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-452-17 ANT-51A Antenna (CPN 622-4550-001), Outline and Mounting Diagram .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-472-18 ANT-52 Antenna (CPN 622-6793-001), Outline and Mounting Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-482-19 437X-1 Antenna (CPN 522-4140-001/-006), Outline and Mounting Diagram .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-492-20 437X-1 Antenna (CPN 522-4140-002/-004), Outline and Mounting Diagram .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-502-21 437X-1 Antenna (CPN 522-4140-003), Outline and Mounting Diagram .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-512-22 437X-1 Antenna (CPN 522-4140-001/-007), Outline and Mounting Diagram .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-522-23 437X-1A Antenna (CPN 522-4255-001/-007), Outline and Mounting Diagram .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-532-24 437X-1A Antenna (CPN 522-4255-002), Outline and Mounting Diagram .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-542-25 437X-1A Antenna (CPN 522-4255-003), Outline and Mounting Diagram .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-542-26 437X-1A Antenna (CPN 522-4255-004), Outline and Mounting Diagram .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-552-27 437X-1B Antenna (CPN 622-0954-001), Outline and Mounting Diagram .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-562-28 437X-1B Antenna (CPN 622-0954-002), Outline and Mounting Diagram .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-572-29 UMT-10/11/12/13 Universal Mount, Outline and Mounting Diagram .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-592-30 390R-18/19/20 Universal Mount, Outline and Mounting Diagram .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-652-31 AEA Wire Marking Standard . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-693-1 ALI-55/55A/55B Radio Altitude Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-13-2 ALI-55/55A/55B Radio Altitude Indicator, Controls and Indicators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-23-3 339H-4/4A Radio Altimeter Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-43-4 DRI-55 Digital Radio Altitude Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-53-5 DRI-55 Digital Radio Altitude Indicator, Controls and Indicators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-64-1 ALT-1000 Radio Altimeter, Functional Block Diagram .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-5

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LIST OF TABLES

Table Title Page

1-1 Equipment Covered . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1-11-2 339H-4/4A Radio Altimeter Indicator, Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1-51-3 ALI-55/55A/55B Radio Altimeter Indicator, Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1-51-4 DRI-55 Digital Altitude Indicator, Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1-61-5 437X-1/1A/1B and ANT-50A/51A/52 Radio Altimeter Antenna, Descriptions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1-71-6 ALT-1000 Radio Altimeter Receiver-Transmitter, Equipment Specifications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1-81-7 339H-4/4A and ALI-55/55A/55B Radio Altimeter Indicator, Equipment Specifications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-121-8 DRI-55 Digital Radio Altitude Indicator, Equipment Specifications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-141-9 437X-1/1A/1B Radio Altimeter Antenna, Equipment Specifications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-151-10 ANT-50A/51A Radio Altimeter Antenna, Equipment Specifications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-171-11 ANT-52 Radio Altimeter Antenna, Equipment Specifications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-181-12 Related Publications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-192-1 AID Strapping Definitions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-32-2 Mod Freq/Source Ident Definitions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-72-3 Radio Altimeter Antenna Gaskets Available . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-112-4 Equipment Mounting Options . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-112-5 Connector Kit Contents . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-122-6 Mating Connector Contacts and Special Tools . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-125-1 Self-Test Pass/Fail Indication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5-15-2 Reported Fault Definitions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5-25-3 ARINC 429 Data Bus Word 270 Definitions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5-45-4 ARINC 429 Data Bus Word 350 Definitions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5-65-5 Diagnostic Codes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5-8

iv 18 July 2012

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INTRODUCTIONGENERAL

THE MATERIAL IN THIS MANUAL IS SUBJECT TO CHANGE. BEFORE ATTEMPTING ANYMAINTENANCE OPERATION ON THE EQUIPMENT COVERED IN THIS MANUAL, VERIFYTHAT YOU HAVE COMPLETE AND UP-TO-DATE PUBLICATIONS BY REFERRING TO THEAPPLICABLE PUBLICATIONS AND SERVICE BULLETINS INDEXES.

This Installation Manual includes installation instructions for the Collins ® ALT-1000 Radio Altimeter System.

The installation instructions are presented in the following chapters: General Information, Installation, Operation, Theory ofOperation, Maintenance, and Service Bulletins and Service Information Letters.

This installation manual provides shop verified procedures that will enable a mechanic unfamiliar with the system to isolate afault to the unit level. The procedures are prepared for the aircraft mechanic, not for the mechanic that performs shop work.Abbrev/Acronym DefinitionACK/NAK Acknowledgement/negative acknowledgementAID Aircraft Installation DelayARINC Aeronautical Radio, Incorporated.ATA Air Transport AssociationATE Automatic Test EquipmentATR Air Transport RackingBCD Binary Coded DecimalBIT Built-In TestBITE Built-In Test EquipmentBNR Binary Numeral RepresentationC CentigradeCMOS Complementary Metal SemiconductorCMU Collins Modular UnitCPCI Computer Program Configuration IdentifierCPN Collins Part NumberCPU Central Processing UnitdB Decibel (s)dBm Decibel (s) Below 1 Milliwattdc direct currentDMA Direct Memory AccessDSP Digital Signal ProcessorEEPROM Electrically Erasable, Programmable Read-Only MemoryEFIS Electronic Flight Instrument SystemESDS Electrostatic Discharge Sensitive DeviceEUROCAE European Organization for Civil Aviation Electronics. A regulatory agency for avionics

certification in Europe.F FahrenheitFAA Federal Aviation Administration (U.S.)FAR Federal Acquisition RegulationFCS Flight Control SystemFET Field Effect TransmitterFPGA Field Programmable Gate ArrayFT Functional TestFW Failure Warning

18 July 2012 v

introduction 523-0806452

Abbrev/Acronym DefinitionGaAs Gallium Arsenide Metal Semiconductor Field Effect TransmitterGHz GigahertzGND GroundGPWS Ground Proximity Warning SystemIF Intermediate FrequencyIN-LBS Inch Poundskg Kilogramslb poundsLNA Low Noise AmplifierLO LowLRU Line Replaceable UnitM MetersMAX MaximumMOS Metal Oxide Semiconductormm millimeterms millisecondmsl Mean Sea LevelN/A Not ApplicableNVM Nonvolatile MemoryPA Power Amplifierp-p Peak to PeakRAM Random Access MemoryRF Radio FrequencyROM Read Only MemoryRX Receive or ReceiverSCSI Small Computer System InterfaceSDI Source Destination IdentifierSSM Sign Status MatrixTNC Threaded Neill-Concelman connectorTSO Technical Standard OrderTTL Transistor – Transistor LogicTX Transmit or TransmitterUART Universal Asynchronous Receiver/TransmitterVCO Voltage Controlled OscillatorVSWR Voltage Standing Wave RatioWDI Wind Direction InstrumentXMIT Transmit or Transmitter

vi 18 July 2012

introduction 523-0806452

To submit comments regarding this manual, please contact:

Rockwell Collins ServicesRockwell Collins400 Collins Rd NECedar Rapids, IA 52498-0001

Attn: Technical Operations M/S 153-250

or send email to: [email protected]

18 July 2012 vii

523-0806452

SAFETY SUMMARYGENERAL ADVISORIES FOR ALL UNITS

Service personnel are to obey standard safety precautions, such as wearing safety glasses, to prevent per-sonal injury while installing or doing maintenance on this unit.

Use care when using sealants, solvents and other chemical compounds. Do not expose to excessive heat oropen flame. Use only with adequate ventilation. Avoid prolonged breathing of vapors and avoid prolongedcontact with skin. Observe all cautions and warnings given by the manufacturer.

Remove all power to the unit before disassembling it. Disassembling the unit with power connected isdangerous to life and may cause voltage transients that can damage the unit.

This unit may have components that contain materials (such as beryllium oxide, acids, lithium, radioactivematerial, mercury, etc) that can be hazardous to your health. If the component enclosure is broken, han-dle the component in accordance with OSHA requirements 29CFR 1910.1000 or superseding documentsto prevent personal contact with or inhalation of hazardous materials. Since it is virtually impossible todetermine which components do or do not contain such hazardous materials, do not open or disassemblecomponents for any reason.

This unit exhibits a high degree of functional reliability. Nevertheless, users must know that it is not practicalto monitor for all conceivable system failures and, however unlikely, it is possible that erroneous operationcould occur without a fault indication. The pilot has the responsibility to find such an occurrence by meansof cross checks with redundant or correlated data available in the cockpit.

Before handling any unit or unit component, ground the repair operator through a conductive wrist strap orother device that uses a 470kΩ or 1mΩ series resistor to prevent operator injury.

Turn off power before disconnecting any unit from wiring. Disconnecting the unit without turning poweroff may cause voltage transients that can damage the unit.

viii 18 July 2012

safety summary 523-0806452

This unit contains electrostatic discharge sensitive (ESDS) components and ESDS assemblies that can bedamaged by static voltages. Although most ESDS components contain internal protection circuits, goodprocedures dictate careful handling of all ESDS components and ESDS assemblies.

Obey the precautions given below when moving, touching, or repairing all ESDS components and units containing ESDS com-ponents.

a. Deenergize or remove all power, signal sources, and loads used with the unit.

b. Place the unit on a work surface that can conduct electricity (is grounded).

c. Ground the repair operator through a conductive wrist strap or other device using a 470-kΩ or 1-MΩ series resistor to preventunit or unit component damage.

d. Ground any tools (and soldering equipment) that will contact the unit. Contact with the operator’s hand is a sufficient groundfor hand tools that are electrically isolated.

e. All ESDS replacement components are shipped in conductive foam or tubes and must be stored in their shipping containersuntil installed.

f. ESDS devices and assemblies that are removed from a unit must immediately be put on the conductive work surface or inconductive containers.

g. Place repaired or disconnected circuit cards in aluminum foil or in plastic bags that have a layer of, or are made with, con-ductive material.

h. Do not touch ESDS devices/assemblies or remove them from their containers until they are needed.

Failure to handle ESDS devices as described above can permanently damage them. This damage can cause immediate or pre-mature device failure.

The radio altitude trip outputs of the ALT-1000 are not monitored. The specific trip levels for each versionor status of the ALT-1000 are reflected in the last three digits of the part number of the unit. On initialinstallation or any subsequent replacement of the ALT-1000, the installer is to verify that the correct statusunit for the airplane in being stalled by cross-checking the enitre part number of the unit with that of thecertification documented of the airplane.

18 July 2012 ix/(x Blank)

523-0806452

CHAPTER 1General Information

1.1 INTRODUCTIONThis publication provides the descriptions, specifications, principles of operation, and information necessary to install, test,and troubleshoot the ALT-1000 Radio Altimeter System. Refer to Table 1-1 for a list of equipment, Tables 1-2 through 1-5for descriptions, Tables 1-6 through 1–11 for equipment specifications, and Table 1-12 for publications related to equipmentcovered in this manual. An overall view of the ALT-1000 Radio Altimeter System is shown in Figure 1-1.

1.2 PURPOSE OF EQUIPMENTThe ALT-1000 system (Figure 1-1) provides the pilot with altitude information during the approach phase of the flight. Twoantennas, one for transmitting and one for receiving, are used. An indicator provides the pilot with a visual display of the aircraftheight above the terrain and annunciates when the aircraft descends below the selected decision height (DH). The ALT-1000is also compatible with Ground Proximity Warning Systems (GPWS) and the 2500 feet version is also compatible with TrafficAlert and Collision Avoidance Systems (TCAS). The following tables provide detailed information on each of the units that arepart of this system:

• Table 1-1. Equipment Covered• Table 1-2. 339H-4/4A Radio Altimeter Indicator, Description• Table 1-3. ALI-55/55A/55B Radio Altimeter Indicator, Description• Table 1-4. DRI-55 Digital Radio Altimeter Indicator, Description• Table 1-5. 437X-1/1A/1B and ANT-50A/51A/52 Radio Altimeter Antenna, Description• Table 1-6. ALT-1000 Radio Altimeter Receiver-Transmitter, Equipment Specifications• Table 1-7. 339H-4/4A and ALI-55/55A/55B Radio Altimeter Indicator, Equipment Specifications• Table 1-8. DRI-55 Radio Altimeter Indicator, Equipment Specifications• Table 1-9. 437X-1/1A/1B Radio Altimeter Antenna, Equipment Specifications• Table 1-10. ANT-50A/51A Radio Altimeter Antenna, Equipment Specifications• Table 1-11. ANT-52 Radio Altimeter Antenna, Equipment Specifications

1.3 RELATED PUBLICATIONSTable 1-12 lists publications related to ALT-1000 Radio Altimeter System operation.

1.4 STORAGEThe ALT-1000 and associated equipment should be stored in its original packing materials and shipping container. If the unit isto be stored for a long time put the unit in an airtight plastic bag with sufficient desiccant to absorb moisture. At no time shouldthe ambient temperature of the storage area fall below –55 °C (–67 °F) or rise above +85 °C (+185°F). The relative humidityshould never exceed 95 percent. If the unit is stored for an extended time, retest the unit prior to returning it to service to ensurethat possible component degradation has not affected performance.

Table 1-1. Equipment Covered

COLLINSEQUIPMENT DESCRIPTION

COLLINSPART

NUMBER

ALT-1000 Radio Altimeter - Used to replace the ALT-55B Radio Altimeter, CPN622-2855-001/-011. The altitude trips (200, 500, 1000, and 1500 feet) are factory setbut may be reset in the shop.

822-1939-001

ALT-1000 Radio Altimeter - Used to replace the ALT-55B Radio Altimeter, CPN622-2855-002/-012. The altitude trips (200, 250, 1000, and 1200 feet) are factory set.

822-1939-002


822-1939-005


822-1939-006

18 July 2012 1-1

General Information 523-0806452

Table 1-1. Equipment Covered - Continued


COLLINSPART

NUMBER

ALT-1000 Radio Altimeter - Used to replace the ALT-50A Radio Altimeter, CPN622-3201-001/-002/-011. The altitude trips (200, 500, 1000, and 1500 feet) arefactory set but may be reset in the shop.

822-1939-021

ALT-1000 Radio Altimeter - Used to replace the ALT-50A Radio Altimeter, CPN622-3201-001/-011. The altitude trips (200, 500, 1000, and 1500 feet) are factory set.

822-1939-025

339H-4 Indicator, Radio Altimeter (Refer to Table 1-2 for a description of each status).

NOTEUse with -02X status ALT-1000 Radio Altimeter.

622-1204-0XX

339H-4A Indicator, Radio Altimeter (Refer to Table 1-2 for a description of each status).

NOTEUse with -02X status ALT-1000 Radio Altimeter.

622-1205-00X

ALI-55 Indicator, Radio Altimeter (Refer to Table 1-3 for a description of each status).

NOTEUse with -00X status ALT-1000 Radio Altimeters.

622-2937-00X

ALI-55A Indicator, Radio Altimeter (Refer to Table 1-3 for a description of each status).


622-2938-00X

ALI-55B Indicator, Radio Altimeter (Refer to Table 1-3 for a description of each status).


622-5367-001

DRI-55 Indicator, Radio Altimeter (Refer to Table 1-4 for a description of each status). 622-4160-0XX

437X-1 Antenna, Radio Altimeter (Refer to Table 1-5 for a description of each status).

NOTEUse of this antenna requires that the ALT-1000 antenna monitoring function notbe enabled.

522-4140-00X

437X-1A Antenna, Radio Altimeter (Refer to Table 1-5 for a description of each status).


522-4255-00X

437X-1B Antenna, Radio Altimeter (Refer to Table 1-5 for a description of each status).


622-0954-00X

1-2 18 July 2012


Table 1-1. Equipment Covered - Continued


COLLINSPART

NUMBER

ANT-50A Antenna, Radio Altimeter (Refer to Table 1-5 for a description of each status).


622-3698-001

ANT-51A Antenna, Radio Altimeter (Refer to Table 1-5 for a description of each status).


622-4550-001

ANT-52 Antenna, Radio Altimeter (Refer to Table 1-5 for a description of each status).

NOTEEnhanced monitoring can be obtained by enabling the ALT-1000 antenna mon-itoring function.

622-6793-001

UMT-12 Mount, Universal 622-5212-004

390R-19 Mount, Universal 622-1195-301

18 July 2012 1-3


Figure 1-1. ALT-1000 Radio Altimeter System

1-4 18 July 2012


Table 1-2. 339H-4/4A Radio Altimeter Indicator, Description

PARTNUMBER

ALTITUDESCALE

AIRCRAFTTYPE LIGHTING BEZEL

DESCRIPTION

339H-4

622-1204-001622-1204-002622-1204-003622-1204-004622-1204-005622-1204-006622-1204-007622-1204-008622-1204-010

0 to +2000 ft0 to +2000 ft0 to +2000 ft0 to +2000 ft0 to +2000 ft0 to +2000 ft0 to +2000 ft0 to +2000 ft0 to +2000 ft

Fixed-wingFixed-wingFixed-wingFixed-wingFixed-wingFixed-wingFixed-wingFixed-wingFixed-wing

28 V blue-white5 V blue-white28 V blue-white5 V blue-white28 V blue-white5 V blue-white5 V blue-white5 V blue-white5 V blue-white

Flat grayFlat grayBlack (with raised bright metal ring)Black (with raised bright metal ring)Gray (with raised bright metal ring)Gray (with raised bright metal ring)Gray (with raised painted metal ring)Black (with raised bright metal ring)Black (with raised bright metal ring andsloping portion of bezel painted gray)

339H-4A

622-1205-001622-1205-002622-1205-003622-1205-004622-1205-005622-1205-006

0 to +2000 ft0 to +2000 ft0 to +2000 ft0 to +2000 ft0 to +2000 ft0 to +2000 ft

Rotary-wingRotary-wingRotary-wingRotary-wingRotary-wingRotary-wing

28 V blue-white5 V blue-white28 V blue-white5 V blue-white28 V blue-white5 V blue-white

Flat grayFlat grayBlack (with raised bright metal ring)Black (with raised bright metal ring)Gray (with raised bright metal ring)Gray (with raised bright metal ring)

Table 1-3. ALI-55/55A/55B Radio Altimeter Indicator, Description

PARTNUMBER

ALTITUDESCALE

AIRCRAFTTYPE LIGHTING BEZEL

DESCRIPTION

ALI-55

622-2937-001622-2937-002622-2937-003622-2937-004622-2937-005622-2937-008622-2937-009

0 to +2500 ft0 to +2500 ft0 to +2500 ft0 to +2500 ft0 to +2500 ft0 to +2500 ft0 to +2500 ft

Fixed-wingFixed-wingFixed-wingFixed-wingFixed-wingFixed-wingFixed-wing

28 V blue-white5 V blue-white28 V blue-white5 V blue-white5 V white5 V white5 V blue-white

BlackBlackGrayGrayBlackGray

Black-gray

ALI-55A

622-2938–001622-2938–002622-2938–003622-2938–004

0 to +2500 ft0 to +2500 ft0 to +2500 ft0 to +2500 ft

Rotary-wingRotary-wingRotary-wingRotary-wing

28 V blue-white5 V blue-white28 V blue-white5 V blue-white

BlackBlackGrayGray

ALI-55B

622-5367-001 0 to +750 metres Fixed-wing 28 V blue-white Black

18 July 2012 1-5


Table 1-4. DRI-55 Digital Altitude Indicator, Description

PARTNUMBER

CASECOLOR LIGHTING

DECISIONHEIGHT

ANNUNCIATOR

LINEARLIGHTINGCURVE

622-4160-001622-4160-002622-4160-003622-4160-004622-4160-005622-4160-006622-4160-007622-4160-008622-4160-011622-4160-012622-4160-013622-4160-014622-4160-015622-4160-016622-4160-017622-4160-018

GrayGrayBlackBlackGrayGrayBlackBlackGrayGrayBlackBlackGrayGrayBlackBlack

5 V white28 V white5 V white28 V white5 V white28 V white5 V white28 V white5 V white28 V white5 V white28 V white5 V white28 V white5 V white28 V white

NoNoNoNoYesYesYesYesNoNoNoNoYesYesYesYes

YesYesYesYesYesYesYesYesNoNoNoNoNoNoNoNo

1-6 18 July 2012


Table 1-5. 437X-1/1A/1B and ANT-50A/51A/52 Radio Altimeter Antenna, Descriptions

HALF-POWER BEAMWIDTH (DEGREES)PART

NUMBERE-PLANE H-PLANE

GAIN(MIN)

VSWR(MAX)

MOUNTINGSURFACE

437X-1

522-4140-001522-4140-002522-4140-003522-4140-004522-4140-006 (1)522-4140-007 (2)

50 ±560 ±545 ±560 ±560 ±560 ±5

40 +10, –545 ±540 ±545 ±540 +10, –540 +10, –5

11.5 dB11.0 dB12.0 dB11.0 dB11.5 dB11.0 dB

1.5:11.4:11.5:11.4:11.5:11.5:1

FlatFlatFlatFlatFlatFlat

(1) Manufactured by UB Corp(2) Manufactured by Dorne-Margolin

437X-1A

522-4255-001522-4255-002522-4255-003522-4255-004522-4255-006 (1)522-4255-007 (2)

50 ±560 ±545 ±545 ±550 ±550 ±5

40 +10, -545 ±540 ±540 +10, -540 +10, -540 +10, -5

11.5 dB11.0 dB12.0 dB11.0 dB11.5 dB11.0 dB

1.5:11.4:11.5:11.5:11.5:11.5:1

CurvedCurvedCurvedCurved (3)CurvedCurved

(1) Manufactured by UB Corp(2) Manufactured by Dorne-Margolin(3) Mounting holes offset 22.5 deg

437X-1B

622-0954-001

622-0954-002

50 ±5

50 ±5

55 ±5

55 ±5

9.0 dB

9.0 dB

1.4:1

1.4:1

Curved, 81.28-cm(32-in) radiusCurved, 81.28-cm(32-in) radius (1)

(1) Outer mounting holes (on flat side) are in line

ANT-50A

622-3698-001 35 min. 35 min. 13.0 dB 1.3:1 Flat

ANT-51A

622-4550-001 55 max 50 max 1.5 dB 1.5:1 Flat

ANT-52

622-6793-001 60 +5, -10 50 +5, -10 10.0 dB 1.5:1 Flat or curved

18 July 2012 1-7


Table 1-6. ALT-1000 Radio Altimeter Receiver-Transmitter, Equipment Specifications

CHARACTERISTIC SPECIFICATION

Certification

FAA TSO C87

RTCA documents DO-155, DO-160C, and DO-178B

ARINC 429–13, Mark 33

FAR Parts 23 and 25

FAA Part 87

EUROCAE ED-30

Environmental Categories DO-160C [A2F2]BB[CLMNY]E1XXXXSZ[BZ]AZ[AZ]Y*[AZ][Z3Z3]XA

NOTE*Unit meets DO-160D, Section 20, Cat YYP

Physical Size 3/8-ATR, short, dwarf

Height 85.09 mm (3.35 in)

Width 90.47 mm (3.56 in)

Length 353.70 mm (13.92 in)

Weight 2.04 kg (4.5 lb.) nominal

Mounting: Preferred: UMT-12 (622–5212–004) and connector kit; 3/8-ATR, short, dwarfOptional: 390R-19 (622–1195–301) and connector kit; 3/8-ATR, short, dwarf

Connectors: Electrical: Collins Thinline II (CPN 634-1112-001), Qty 1RF: TNC (CPN 857-1511-010), Qty 2

Environmental

Temperature range Operating: –55 to +70 °C (–67 to +158 °F)Storage: –55 to +85 °C (–67 to +185 °F)

Altitude Continuous operation: –1000 to +70 000 ft (-305 to +21 336 m)Overpressure: –15 000 ft (-4575 m)Decompression: +70 000 ft (+21 336 m)

Cooling Convection or forced air. Estimated thermal load is 18watts.

Relative humidity 85 to 95 %, 65 to 38 °C, 240 hours

Shock Operational: 6 g, 11 msCrash safety: 15 g, 11 ms

Vibration:DO-138, cat JN

5 to 17 Hz: 0.1 in da17 to 39 Hz: 1.5 g39 to 55 Hz: 0.02 in da55 to 2000 Hz: 3 g da

DO-138, cat J 0.02 in da, 5 to 2000 Hz, 3 g max

DO-138, cat N 0.1 in da, 5 to 55 Hz, 1.5 g max55 to 2000 Hz, 1 g max

Electrical

1-8 18 July 2012


Table 1-6. ALT-1000 Radio Altimeter Receiver-Transmitter, Equipment Specifications - Continued


Input power:-02X status (P1-1)-00X status (P1-9)

30 W nom, while driving one indicator30 W nom, while driving one indicator

Power gnd (P1-3)

Overall limit +16 V dc (after initial power-up) to +33 V dc

RF center frequency 4.3 GHGz

RF output power 450 mW nominal

Modulation strap:50 Hz (P1-38)51 Hz (P1-40)

Selectable 50 or 51 Hz modulation frequency and linear FM deviation of 100 MHznominal p-p centered around ALT-1000 RF frequency of 4.3 GHz nominal.

Maintenance requirements On condition

Altitude output:+dc analog (P1-57)–dc analog (P1-59)

Dc analog

Analog 0 to +18 V dc, piece-wise linear

ALT-1000 (–02X status):

Scale 20 mV/ft from –20 to +500 ft+10.4 V dc + 3 mV/ft from +500 to +2000ft

Accuracy, display ±5 ft or ±5% (whichever is greater) from 0 to +500 ft±7% from +500 to +2000 ft

Accuracy, analog output ±2 ft or ±2% (whichever is greater) from 0 to +500 ft±3% from +500 to +2000 ft

ALT-1000 (–00X status):

Scale 20 mV/ft from –20 to +500 ft+10.4 V dc + 3 mV/ft from +500 to +2500ft

Accuracy, display ±5 ft or ±5% (whichever is greater) from 0 to +500 ft±7% from +500 to +2500 ft

Accuracy, analog output ±2 ft or ±2% (whichever is greater) from 0 to +500 ft±3% from +500 to +2500 ft

Off-scale voltage +18 ±0.5 V dc

Output loading 1 millimho max or 1 kΩ

Time Constant 0.09 ± 0.01 s

Reference voltages:+22 V dc (P1-49)-15 V dc (P1-51)

+22 V dc ± 0.5% regulated @ 125 mA max–15 V dc ± 0.3% regulated @ 60 mA max

FCS warn output (P1-8) No warn: +20 to +33 V dc at 100 mA maxWarn: less than 1 V dc (less than 20 ma)

ALT-1000 factory set trip points: Tripped: less than 1.5 V dc at 100 mA maxUntripped: less than 20 μA at 30 V dc max

18 July 2012 1-9




-001 status(adjustable)

Trip No.1 = 200 ftTrip No.2 = 500 ftTrip No.3 = 1000 ftTrip No.4 = 1500 ft

-002 status(non-adjustable)


-021 status(adjustable)


Built In Test Equipment (BITE) I/O Specifications

Input label 164 Parameter = BNR altitudeRange = 8192 feetSig Digits = 16Resolution = 0.125 feetUpdate interval = 25 to 80 ms

Input label 227 Parameter = Command wordRange = NASig Digits = NAResolution = NAUpdate interval = NA

Output label 164 Parameter = BNR altitudeRange = 8192 feetSig Digits = 16Resolution = 0.125 feetUpdate interval = 25 to 50 ms

Output label 165 Parameter = BCD altitudeRange = ±7999.9 feetSig Digits = 5Resolution = 0.1 feetUpdate interval = 25 to 50 ms

Output label 270 Parameter = ALT discreteRange = NASig Digits = NAResolution = NAUpdate interval = 100 to 200 ms

1-10 18 July 2012




Output label 350 Parameter = Maint word 1Range = NASig Digits = NAResolution = NAUpdate interval = 100 to 200 ms

Output label 355 Parameter = Character dataRange = NASig Digits = NAResolution = NAUpdate interval = As required

Built-in Test Equipment (BITE)Connector P12

P12-1 = NCP12-2 = BITE TX AP12-3 = BITE TX BP12-4 = BITE RX AP12-5 = BITE RX BP12-6 = GROUNDP12-7 = IF TEST FREQP12-8 = WRAP AROUND OUTP12-9 = NCP12-10 = WRAP AROUND INP12-11 through 26 = NC

NOTEThe BITE interface uses ARINC 429 serial input and output buses to provide ac-cess to fault log information, altitude trip setting, and various other parameters ofthe ALT-1000. The interface is designed to interact with external test equipmentwith bi-directional, low-speed ARINC 429 capabilities. The data transfers are con-trolled via a handshake protocol.

The WRAP AROUND OUT (P12-8) is a low frequency square wave output that isrouted to the BITE interface connector. The wrap around input allows the processorto determine if the BITE interface connector is mated.

Two modes of operation are available, the In Aircraft Test (IAT) mode and the shopmode.

When in the IAT mode, the ALT-1000 will condition all altitude and status outputsbased on the contents of ARINC 429 words received via the BITE connector. TheIAT mode is identified by bit 26 set to 1 in Label 270 ARINC 429 discrete outputword.

When in the shop mode, the ALT-1000 will allow ARINC 429 data to be outputproviding diagnostic fault information and various other parameters of the ALT-1000. Shop mode is defined by attaching the BITE connector and sending a 227word with a command of 20 (Label 227 bits 32–1: D0 00 01 E9).

18 July 2012 1-11


Table 1-7. 339H-4/4A and ALI-55/55A/55B Radio Altimeter Indicator, Equipment Specifications


Certification

FAA TSO C87

RTCA documents DO-123 and DO-138

FCC rules Part 87

ARINC 408

Environmental DO-138cat DAPAAAXXXXXX

Physical Size

Height 85.73 cm (3.375 in)

Width 85.73 cm (3.375 in)

Length 142.87 cm (5.625 in)


Mounting:Front panel mounted or

Requires front mounting mooring plate (CPN 553-6588-004) and frontmounting clamp (CPN 139-3156-000)

Rear panel mounted Requires rear mounting mooring plate (CPN 553-6588-004)

Unit connector:339H-4/4A

Cannon PTO6A-14-19S(SR) (CPN 371-8087-000)

ALI-55A Bendix 21-209214-200 (CPN 371-9036-010)

ALI-55/55B Cannon PTO2A-14-19P (CPN 371-2051-000)

Mating connector Cannon PTO6A-14-19S(SR) (CPN 371-8087-000)

Maintenance requirement On condition

Environmental

Temperature:OperatingStorage

-15 to +55 °C (+5 to +131 °F)-65 to +71 °C (-85 to +160 °F)

Altitude 15 240 m (50 000 ft) max

Cooling Convection

Relative humidity:HighLow

95% min. at +50 °C ±3 °C (+122 °F ±5 °F )85% min. at +38 °C (+100 °F) max

Vibration: Conforms to DO-138, cat P5 to 17 Hz: 2.54 mm (0.1 in) da max17 to 55 Hz: ±1.5 g max acceleration55 to 2000 Hz: ±0.25 g max acceleration

Magnetic 5° max deflection of 3.81 cm (1.5 in) bar magnet at a distance of 30.48 cm(12 in)

Electrical

Positive reference +21.890 to +22.110 V dc at 55 mA max

1-12 18 July 2012


Table 1-7. 339H-4/4A and ALI-55/55A/55B Radio Altimeter Indicator, Equipment Specifications - Continued


Negative reference –14.925 to –15.075 V dc at 25 mA max

Input power (P1-T) +24.5 to +30.0 V dc at 250 mA max (supplied by the ALT–1000)

Power ground (P1-N)

DH annunciator internal lamp (P1-U) 25.2 to 30.8 V ac or Vdc at 50 mA continuous

Lighting voltage:+28 V dc units (P1-L)+5 V dc ac/dc units (P1-C)Indicator lighting low (P1–M)

0.120 A max0.460 A maxConnect to dim power low

Altitude signal input:+dc analog alt (P1-A)–dc analog alt (P1-B)

339H-4/4A units are compatible with ALT-1000 (–02X status) and ALI-55()units are compatible with ALT-1000 (–00X status)

External decision height (P1-R and P1-V) Isolated relay contacts, closed (P1-R is connected to P1-V) at DH and below

Inst flag:+ (P1-D)– (P1–E)

0.02 A load capability for the flight director system and/or other externalsystem

18 July 2012 1-13


Table 1-8. DRI-55 Digital Radio Altitude Indicator, Equipment Specifications


Certification

FAA TSO C87

RTCA document DO-160

ARINC 408

Environmental Categories DO-160, cat /A2C1/B/PKS/EXXXXXZBAZZ

Physical Size

Height 20.95 cm (0.825 in)

Width 85.73 cm (3.375 in)

Length 153.41 cm (6.04 in)


Mounting: Front or rear panel mounted

Integral turnlock Front mounted in panels 1.27 mm (0.05 in) to 3.18 mm (0.125 in) thick

Front mounted Requires front adapter plate (CPN 629-8671-001 for gray or CPN629-8671-002 for black)

Rear mounted Requires rear mounting mooring plate (CPN 629-8672-001)

Unit connector Cannon DBU-25PAD (CPN 371–0385–030)

Mating connectors:Crimp connectorCrimp contactsSolder connector

Cannon DBMA25S-A183–FO (CPN 371-0213-030)Cannon 031-1007-067 (CPN 371-0213-110)Cannon DBM-25S (CPN 371-0221-000)

Maintenance requirement On condition

Environmental Specifications

Temperature Operating: –20 to +70 °C (–4 to +158 °F)Storage: -55 to +85 °C (–67 to +185 °F)

Altitude 0 to 12 192 m (0 to 40 000 ft) max

Cooling Convection

Relative humidity 95% min. at +50 °C (+122 °F)

Vibration Conforms to DO-160, cat PKS

Operational shock 6 g

Crash safety shock 15 g

Electrical

Positive reference (P1-20) +21.89 to +22.11 V dc at 55 mA max

Negative reference –14.925 to –15.075 V dc at 25 mA max

Input power (P1-25) +24.5 to +30.0 V dc at 250 mA max (supplied by the ALT-1000

Power ground (P1-14)

DH annunciator internal lamp dimmerpower (P1-15)

25.2 to 30.8 V ac or V dc at 50 mA continuous

1-14 18 July 2012


Table 1-8. DRI-55 Digital Radio Altitude Indicator, Equipment Specifications - Continued


+28 V dc lighting voltage (P1-4) 0.120 A max

+5 V dc/5 V ac lighting power (P1-5) 0.460 A max

Indicator lighting low Connect to dimmer power low

ALT-50A/55B and ARINC PGM straps(P1-10 and P1-9)

Open=greater than 100 kohm; ground = less than 1.0 V dcFor input from -02X status ALT-1000, straps P1-10 and P1-9 are both openFor input from -00X status ALT-1000, strapP1-10 is ground and strap P1-9 is openFor input from ARINC ALT, strap P1-10 is open and strapP1-9 is ground

DH PGM (only on DRI-55 with SB 6installed) (P1-12)

Open = greater than 100 kohm; ground = less than 1.0 V dcOpen for DRI-55 display disable at 00 feet

Altitude signal input:+dc analog altitude (P1-23)–dc analog altitude (P1-22)

Compatible with ALT-1000Accuracy is ±2 feet or ±2 percent, whichever isgreater

NOTEOnly 10-ft increments are displayed (50-ft increments when above 1000ft) to present a quick, easy-to-read altitude indication for the pilot.

External decision height (P1-2 and P1-3) Isolated relay contacts, closed at DH and below (P1-2 is connected to P1-3 atDH and below)

Table 1-9. 437X-1/1A/1B Radio Altimeter Antenna, Equipment Specifications


Certification

FAA TSO C87

RTCA documents DO-123 and DO-138

FCC rules Part 87

EUROCAE MPS1/WG6/74 and ED-30

ARINC 552

Environmental categories

437X-1/1A TSO–C87, AAAAAE

437X-1B TSO–C87, AAAAAX

Physical Size

Flange diameter 17.78 cm (7.00 in)

Body diameter 13.21 cm (5.20 in)

Height 6.99 cm (2.75 in)

Weight 0.45 kg (1.0 lb.) nom

Environmental

18 July 2012 1-15


Table 1-9. 437X-1/1A/1B Radio Altimeter Antenna, Equipment Specifications - Continued


Temperature Operating: –54 to +55 °C (–65 to +131 °F)Storage: –62 to +85 °C (–80 to +185 °F)

Humidity 0 to 100 percent with condensation at 50 °C (+122 °F)

Altitude 0 to 18 288 m (0 to 60 000 ft)

Vibration

437X-1/1A 5 to 10 Hz: 0.1016 cm (0.040) da10 to 55 Hz: 0.0762 cm (0.030) da55 to 500 Hz: 10 g500 to 1000 Hz: 6 g

437X-1B 5 to 10 Hz: 0.2032 cm (0.080) da10 to 55 Hz: 0.1520 cm (0.060) da55 to 500 Hz: 10 g500 to 1000 Hz: 6 g

Shock 15 g for 10 ms

Pressure differential 0.907 kg/cm2 (12.9 lb./in2)

Electrical:

437X-1 (-001 status) Gain: 11.5 dB min.Half-power beam width, E plane: 50 ±5°Half-power beam width, H plane: 40 +10°, –5°VSWR: 1.5:1 max

437X-1A (-001 status) Gain: 11.5 dB min.Half-power beam width, E plane: 50 ±5°Half-power beam width, H plane: 40 +10°, –5°VSWR: 1.5:1 max

437X-1B (all status) Gain: 9 dB min.Half-power beam width, E plane: 50 ±5°Half-power beam width, H plane: 55 ±5°VSWR: 1.4:1 max

Isolation

437X-1 -001, -006, -007: 40.64 cm (16 in) spacing, 80 dB min.-002, -003, -004: 50.80 cm (20 in) spacing, 80 dB min.

437X-1A -001, -004, 006, -007: 40.64 cm (16 in) spacing, 80 dB min.-002, -003: 91.44 cm (36 in) spacing, 90 dB min.

437X-1B 50.80 cm (20 in) spacing, 80 dB min. and76.20 cm (30 in) spacing, 85 dB min.

Squint angle 6° max

Input impedance 50 Ω nom

Mounting:

437X-1 Flat surfaces, in-line or side-by-side

437X-1A Curved surfaces, in-line only, 181.61 cm (71.5 in) nom radius

437X-1B Curved surfaces, in-line only, 81.28 cm (32.0 in) nom radius

1-16 18 July 2012


Table 1-9. 437X-1/1A/1B Radio Altimeter Antenna, Equipment Specifications - Continued


Minimum spacing 50.8 cm (20 in)

Mating connector TNC CPN 857-1511-010

Orientation Must be perpendicular to a line between the antennas for minimumcross-coupling

Gaskets:

437X-1 -002 status: CPN 018-1394-040All except -002 status: CPN 018-1394-020

437X-1A CPN 018-1394-020

437X-1B CPN 018-1394-030

Table 1-10. ANT-50A/51A Radio Altimeter Antenna, Equipment Specifications


Certification

FAA TSO C87

Environmental categories AAAAAX

Physical Size

ANT-50A Flange (rectangular): 15.87 x 14.17 cm (6.2 x 5.6 in)Body: 14.66 x 12.96 cm (5.8 x 5.1 in)Height: 6.35 cm (2.5 in)Weight: 0.45 kg (1.0 lb.)

ANT-51A Flange (round): 17.78 cm (7.0 in) diaHeight: 4.65 cm (1.8 in)Weight: 0.36 kg (0.8 lb.) nom

Environmental

Temperature: Operating: –54 to +71 °C (–65 to +160 °F)Storage: –62 to +71 °C (–80 to +160 °F)

Humidity 0 to 100 percent with condensation at 50 °C (+122 °F)

Altitude: ANT-50A: 0 to 13 716 m (0 to 45 000 ft)ANT-51A: 0 to 18 288 m (0 to 60 000 ft)

Vibration: 5 to 10 Hz: 0.1016 cm (0.040 in) da10 to 55 Hz: 0.0762 cm (0.030 in) da55 to 500 Hz: 10 g500 to 1000 Hz: 6 g

Electrical:

ANT-50A Gain: 13.0 dB min.Half-power beam width, E plane: 35°Half-power beam width, H plane: 35°VSWR: 1.4:1 max

18 July 2012 1-17


Table 1-10. ANT-50A/51A Radio Altimeter Antenna, Equipment Specifications - Continued


ANT-51A Gain: 11.5 dB min.Half-power beam width, E plane: 50°Half-power beam width, H plane: 40°VSWR: 1.5:1 max

Isolation:

ANT-50A 91.44 cm (36 in) spacing: 90 dB min.50.80 cm (20 in) spacing: 80 dB min.

ANT-51A 76.20 cm (30 in) spacing: 85 dB min.

Squint angle 6° max


Mounting Flat surfaces, in line or side by side



Orientation Must be perpendicular to a line between the antennas for minimumcross-coupling

Gaskets:

ANT-50A CPN 018-1394-060

ANT-51A CPN 018-1394-020

Table 1-11. ANT-52 Radio Altimeter Antenna, Equipment Specifications


Certification

FAA TSO C87

RTCA document DO-160B

FCC rules Part 87

Environmental categories D2AXJXWXDFXXXXXXXX

Physical Size

Flange (rectangular)BodyHeightWeight

9.27 x 8.89 cm (3.65 x 3.5 in)2.54 x 2.54 cm (1.0 x 1.0 in)1.85 cm (0.73 in)0.098 kg (3.5 oz.)

Environmental

Temperature: Operating (continuous): –54 to +55 °C (–65 to +131 °F)Operating (short term): Up to +71 °C (+160 °F)Storage: –62 to +71 °C (–80 to +160 °F)

Humidity 0 to 100 percent with condensation at +50 °C (+122 °F)

Altitude 0 to 16 764 m (0 to 55 000 ft)

Vibration: 10 to 80 Hz: 0.0762 cm (0.030 in) da80 to 500 Hz: 10 g peak

1-18 18 July 2012


Table 1-11. ANT-52 Radio Altimeter Antenna, Equipment Specifications - Continued


Electrical:

ANT-52 Gain: 10.0 dB min.Half-power beam width, E plane: 60 +5°,-10°Half-power beam width, H plane: 50 +5°,-10°VSWR:4200 to 4400 MHz: 2.0:14210 to 4390 MHz: 1.9:14240 to 4360 MHz: 1.5:1

Isolation: 91.44 cm (36 in) spacing: 95 dB min.76.20 cm (30 in) spacing: 90 dB min.50.80 cm (20 in) spacing: 88 dB min.40.64 cm (16 in) spacing: 80 dB min.


Mounting Flat or curved surfaces, in-line or side-by-side, mounting screwssupplied

Gasket (optional) CPN 018–1394–100



Table 1-12. Related Publications

PUBLICATION COLLINSPART NUMBER

UMT- ( ) Mount and Thinline II Connectors Instruction Book 523-0772277

Pro Line II Comm/Nav/Pulse System Installation Manual, ALT-50/55 Radio AltimeterSystem Installation Section

523-0772719

ALT-1000 Radio Altimeter Component Maintenance Manual with Illustrated Parts List 523-0806454

ALT-55 Radio Altimeter System (with ALT-55B for 2500-Ft Operation and ALI-55/55A/55B)Instruction Book (Installation and Repair) (covers ALI-55( ) Radio Altitude Indicators)

523-0766793

DRI-55 Digital Radio Altitude Indicator Instruction Book (Installation and Repair) 523-0768424

Installation Practices Manual 523-0775254

General Aviation Antennas, Instruction Book 523-0769091

ALT-50 Radio Altimeter System, ALT-50A with 339H-4/4A, Instruction Book 523-0766818

Rockwell Collins ALT-1000 and ALI-55/55A Operating Instructions 523-0806488

18 July 2012 1-19/(1-20 Blank)

523-0806452

CHAPTER 2Installation

2.1 GENERALThis section provides all of the information needed to install the ALT-1000 Radio Altimeter System. The following topics areincluded in this section: mounting, mating connectors and contacts, cabling, and system interconnect.

An aircraft station radio license is required to operate the ALT-1000 Radio Altimeter System. In the United States, use FCCForm 404 to apply for this license.

2.2 UNPACKING AND INSPECTING EQUIPMENTUnpack equipment carefully and make a careful visual inspection of the units for possible shipping damage. All claims fordamage should be filed with the transportation company involved. If claims for damage are to be filed, save the original shippingcontainer andmaterials. If no damage can be detected, replace the packingmaterials in the shipping container and save for futureuse (such as storage or reshipment).

2.3 PREINSTALLATION CHECKBefore installing the equipment in an aircraft, perform the final performance (customer acceptance) test (in the maintenancesection of this manual) or connect the unit in a system mock up to verify proper operation.

2.4 SPECIAL INSTRUCTIONSThe following instructions must be followed to ensure proper installation of the ALT-1000 Radio Altimeter System.

Interconnect cables should be prepared in accordancewith Figures 2-7 through 2-9, Interconnect Diagrams. Since these intercon-nects are typical, variations or modifications to meet customer requirements are inevitable. Refer to paragraph 2.5, PLANNING,for information on some of the options that can affect the interconnecting cabling. The mounts, mating connectors, and contactsrequired to install an ALT-1000 are listed in Tables 2-4 and 2-5. Table 2-6 lists the special tools required for installation. Figure2-3 shows the mating connector (P1) pin assignments. Figure 2-4 shows the BITE mating connector (P12) pin assignments.

Ensure that the aircraft battery master switch is turned off before installing any of the interconnect cabling.

Improper operation may occur if the following instructions are not followed.

a. The minimum wire size for power lines is #20 AWG. #22 AWG wire can be used for all other lines.

NOTEAircraft approved wire must always be used and extra care must be taken when selecting any wire smallerthan #22 AWG.

b. Read all notes on drawings, interconnects, and the planning paragraph before installing any units or cabling.

c. Keep the interconnect cables away from circuits carrying heavy current, pulse transmitting equipment, and othersources of interference.

d. Make all external connections of the equipment through the designated connectors listed on the outline and mountingdiagrams.

e. For balanced connections, use twisted pair shielded wiring for minimum pickup of electrostatic and magnetic fields.Avoid long runs of wire and keep input and output circuits separated as much as possible.

f. All interconnect wires and cables should be marked in accordance with the Aircraft Electronics Association WireMarking Standard (refer to Figure 2-31).

g. Avoid excessive cable lengths, but allow sufficient slack for movement due to vibration.

18 July 2012 2-1

Installation 523-0806452

h. After installation of the cables in the aircraft and before installation of the equipment, check to ensure that aircraftpower is applied only to the pins specified on the interconnect diagrams, and that all other wires and shields areproperly terminated.

2.4.1 Connector Contact Assembly and Installation For more detailed instructions on contact crimping, contact in-sertion, and contact extraction, refer to Collins UMT ( ) Mount and Thinline II Connectors manual (523-0772277).

NOTEEach connecting wire must be crimped in the contact so the crimped portion of the contact can enter theconnector shell. The crimped portion must enter the shell to provide positive locking of contact in the shell.

a. Contact Crimping Instructions

(1) Strip approximately 3.2 mm (0.125 in) of insulation from each interconnect wire.

(2) Place the contact into crimp tool (refer to Table 2-6 for part number) and gently close handles until the contactis held in place without deforming either the wire or insulation barrels.

(3) Hold wire straight and insert stripped portion as far as possible into wire barrel of contact pin. Bare wire shouldextend beyond the front of the wire barrel, but no more than 0.8 mm (1/32 in). Insulation should be aligned withthe insulation barrel.

(4) Hold the wire in place and complete the crimp by closing the crimping tool handles until the ratchet releases.

(5) Remove the crimped contact from the crimping tool.

NOTEBe sure that the wire insulation has not been crimped into the wire barrel. The end portions of the insulationbarrel should meet after crimping to form a complete loop. The wire barrel section of the contact should becompletely closed after crimping.

b. Contact Insertion Instructions

(1) Use insertion tool (refer to Table 2-6 for part number) and insert each wired contact into the proper connectorhole from the rear and press until locked.

(2) Pull gently on each wire to ensure that the pin is properly locked into the connector. Refer to Figure 2-3 for theALT-1000 pin locations and functions.

c. Contact Extraction Instructions

(1) From the mating side of the connector, insert the extraction tool (refer to Table 2-6 for part number) as far aspossible into the cavity containing the contact to be removed.

(2) Push the ejector plunger of the extraction tool forward, holding the handle in position to keep the tool frombacking out of the connector.

(3) Holding the tool in position, grasp the wire and gently pull the contact free from the connector.

2.5 PLANNINGProper and careful planning prior to installation is essential for reliable performance and easy maintenance. The following listis a sample of the points to be considered in planning an installation:

a. Single or dual installation.

b. Installation location has adequate airflow for cooling, good bonding to aircraft ground, ease of cable routing, room for singleor dual mounting (piggyback or side by side).

c. Compatibility with other equipment loading considerations.

2.5.1 Installation Configurations There are two basic configurations for the ALT-1000 Radio Altimeter System:

• The first configuration is a single ALT-1000 installation where the altimeter data is displayed on one or two 339H-4/4A,ALI-55/55A/55B, or DRI-55 Indicator(s).

• The second configuration is a dual ALT-1000 installation where the altimeter data from each ALT-1000 is displayed on itsown dedicated 339H-4/4A, ALI-55/55A/55B, or DRI-55 Indicator.

2-2 18 July 2012


In either case, the ALT-1000 altitude trips may be factory set (-002) or set to customer specifications (-001 and -021).

2.5.2 Strapping Options

All connector straps should be kept as short as possible, preferably under 75-mm (3-in).

Figure 2-2 shows the circuits connected to the ALT-1000 rear pins permitting evaluation of loading anddrive considerations.

2.5.2.1 Antenna Monitor Enable The ALT-1000 antenna monitor function is enabled when ANT MON ENABLE pin(P1-21) of the ALT-1000 rear connector is grounded. The function can only be used with antennas that have a DC resistancepath to the coax shell not exceeding a nominal 100 ohms. When the ALT-1000 is used with the ANT-52 type antennas, theDC conductivity of the antennas and coaxial transmission lines are monitored continuously when the antenna monitor enablediscrete is grounded.

• For an ANT-52 Antenna, ground P1-21 to enable the antenna monitor.• For a 437X-1/1A/1B or ANT-50A/51A Antenna, leave P1-21 open to disable the antenna monitor.

2.5.2.2 Aircraft Installation Delay The radio altimeter system must be adjusted to read 0-foot altitude at the point oftouchdown. Therefore, compensation for the antenna cable lengths and the antenna height above ground at the point of touch-down must be made by applying AID bias. AID bias is selected on the ALT-1000 by jumpering a connector pin to aircraftground on new installations. The AID COMMON pin (P1-19) is an acceptable ground for existing installations.

NOTEIn determining the height of the antenna, do not measure the antenna height of the parked aircraft. Thelanding gear of a parked aircraft is loaded, and the antenna height is not the same as at the point of touch-down. A simulated touchdown position can be obtained by jacking up the aircraft until the landing gear isunloaded; however, aircraft pitch at touchdown must also be taken into account.

The ALT-1000 provides three possible AID selections to reduce the amount of excess cable that must be stored in the aircraft.To increase the safety margin, odd parity is set by strapping one option pin to aircraft ground. The Altimeter can detect a singlefailure of this strapping configuration. The AID strapping is designed for an individual strap from the appropriate pin directlyto aircraft ground on new installations. The AID COMMON pin (P1-19) is an acceptable ground for existing installations. Thebit assignments are as follows:

Table 2-1. AID Strapping Definitions

AID 20 FT(P1-22)

AID 40 FT(P1-24)

AID 57 FT(P1-27) DEFINITION

P1-19 (Gnd)OpenOpen

OpenP1-19 (Gnd)

Open

OpenOpen

P1-19 (Gnd)

20 feet AID40 feet AID57 feet AID

For new installations; the AID 20 FT, AID 40 FT, or AID 57 FT strap pin should be connected to aircraft ground.For existing installations; the AID COMMON pin (P1-19) may be used for ground.

NOTEAll other combinations are invalid. AID parity is set by connecting only one (1) of the following pins:P1-22, P1-24, or P1-27 to aircraft ground. AID COMMON (P1-19) is internally connected to ground inthe ALT-1000. For plug in replacement of an ALT-50A/55B, the existing jumper strap for aid selection pinto AID COMMON can be retained. Definitions are such that 20, 40, and 57 feet selections are the samewhen the ALT-1000 uses existing ALT-50A/55B wiring. After aircraft antenna height has been determined,antenna cable length must be determined.

18 July 2012 2-3


2.5.2.3 Antenna Cable Approved Types and Lengths The required antenna cable length depends on the AID usedand the antenna height. Cable lengths are critical and must be measured accurately. The AID and cable requirement formula is:

AIDfeet = P + (Ct + Cr) / Vp

Where:

AIDfeet = Aircraft installation delay in feet

P = Total minimum path length (in feet) from the transmitting antenna to the ground and back to the receiving antenna, whenthe aircraft is in the touchdown attitude and configuration.

Ct = Transmitter cable length in feet from the ALT-1000 to the transmit antenna. Does not include any cable or delay within thereceiver - transmitter or the antenna.

Cr = Receiver cable length in feet from the ALT-1000 to the receive antenna. Does not include any cable or delay within thereceiver - transmitter or the antenna.

Vp = Velocity of propagation factor (velocity factor) of the transmission line used between the antenna and the ALT-1000,specified as either a percentage or numerical factor with a range of 0 to 1.000.

Receiver and transmitter cables are assumed to be the same length. However, if installation problems require unequal lengthcables, the length required for the transmitter, and receiver cables should be added and the total length of both cables shouldequal this amount. The length of either individual cable should not exceed a nominal 18 feet.

To find the total cable length for a known AID, minimum path length, and coaxial cable velocity of propagation, use the formula:

(Ct+ Cr) = (AIDfeet – P)Vp

Excess cable should be rolled up and secured to the aircraft. The antenna cables must be continuous without any interveningconnectors or breaks.

2.5.2.4 Coaxial Cable Parameters Parameters for five (5) coaxial cables are listed in the following paragraphs.

2.5.2.5 RG-393/U Coaxial CableNOTE

Use of cable that does not conform to military standards may affect the ALT-1000 system performance,resulting in erratic readings and intermittent operation.

• Velocity Factor = 0.694• Outside Diameter = 0.390 in• Temperature Range = -55 to +200 °C• Loss/Ft = 0.210 dB @ 5 GHz• Characteristic Impedance = 50• Mating Connector = CPN 857-1511-010

2.5.2.6 ECS 311201 Coaxial CableNOTE

ECS cable with crimped connector can be ordered from Electronic Cable Specialist, 5300W. Franklin Drive,Franklin, WI 53132, Telephone (414) 421-5300.

• Velocity Factor = 0.800• Outside Diameter = 0.317• Temperature Range = -55 to +200 °C• Loss/Ft = 0.127 dB @ 5 GHz• Characteristic Impedance = 50• Mating Connector = CTS 122 (Crimp type)

2-4 18 July 2012


2.5.2.7 PIC S55122 Coaxial CableNOTE

PIC cable with crimped connector can be ordered from PIC Wire and Cable Supply, P.O. Box 330, Susan,WI 53089-0330, Telephone (414) 246-0500.

• Velocity Factor = 0.840• Outside Diameter = 0.300• Temperature Range = -55 to + 200 °C• Loss/Ft = 0.142 dB @ 5 GHz• Characteristic Impedance = 50• Mating Connector = 190609 (Crimp type)


Use of cable that does not conform to military standards may affect the ALT-1000 system performance,resulting in erratic readings and intermittent operation.

Mating connector vendor type number of listed is for Automatic Connector, Inc., 400Moreland Road, Com-mack, NY 11725.

• Velocity Factor = 0.870• Outside Diameter = 0.465• Temperature Range = -55 to +80 °C• Loss/Ft = 0.141 dB @ 5 GHz• Characteristic Impedance = 50• Mating Connector = 258-T1800B


RG-214/U coaxial cable is not recommended for new installations. Use RG-393/U or equivalent coaxialcable. The PVC jacket does not meet FAR 23.1365 and FAR 25.831. Refer to Rockwell Collins All AvionicsInformation Letter 2-92 for further information.

• Velocity Factor = 0.660• Outside Diameter = 0.425• Temperature Range = -40 to +80 °C• Loss/Ft = 0.215 dB @ 5 GHz• Characteristic Impedance = 50• Mating Connector = 357-7204-010

18 July 2012 2-5


Figure 2-1. Aircraft Installation Delay (AID) and RF Cable Requirements Chart

2-6 18 July 2012


2.5.2.10 Source Identification and Modulation Selection The ALT-1000 uses the existing discrete input for modu-lation frequency selection to accomplish source identification selection to save pins on the rear connector. The source identi-fication strapping is designed for individual straps from the appropriate pins directly to aircraft ground for new installations.The modulation frequency selection and source identification selection are coupled. Source identification/modulation frequencydefinitions are as follows:

Table 2-2. Mod Freq/Source Ident Definitions

MOD FREQ 50 Hz(P1-38)

MOD FREQ 51 Hz(P1-40) DEFINITION MOD

FREQ

P1-35 (Gnd)Open

OpenP1-35 (Gnd)

No. 1 (left side)No. 2 (right side)

50 Hz51 Hz

For new installations; the MOD FREQ 50 HZ or MOD FREQ 51 HZ strap pin should be connected to aircraft ground.For existing installations; the MOD FREQ COMMON pin (P1-35) may be used for ground.

NOTEAll other combinations are invalid. Mod frequency parity is set by connecting only one (1) of the followingpins: P1-38 or P1-40 to aircraft ground. MOD FREQ COMMON (P1-35) is internally connected to groundin the ALT-1000. For plug in replacement of an ALT-50A/55B, the existing jumper strap for mod freq se-lection pin to MOD FREQ COMMON can be retained. Definitions are such that the ALT-1000 will operatewhen installed in existing ALT-50A/55B installations.

2.5.2.11 Maintenance Mode Selection (P1-53) This discrete input is for maintenance only and is not to be connectedto the aircraft wiring. This discrete input is used with the BITE (built-in test equipment) connector to perform various shopfunctions.

2.5.2.12 Self-Test (P1-25) This pin is normally open (not in self-test). The ALT-1000 enters self-test when a ground isapplied to this pin.

2.5.2.13 BITE Wrap Around I/O (P12-10/8) This is a discrete used by the BITE. When used, a wrap around signal fromWRPNDOUT (P1-8) to WPRNDIN (P12-10) is present to check the mating of the BITE connectors.

NOTEThis signal may not be active unless in shop mode.

2.5.3 Cooling Considerations The ALT-1000 performs properly with convection cooling at ambient air temperaturesup to +55 °C (+131 °F). However, as with all electronic equipment, lower operating temperatures extend equipment life. Onthe average, reducing the operating temperature by 15 to 20 °C (25 to 35°F) doubles the mean time between failure (MTBF).Units tightly packed in the radio rack heat each other through radiation, convection, and sometimes by direct conduction. Ifspace permits, separate the units from each other to significantly improve reliability. Even a single unit operates at a muchhigher temperature in still air than in moving air. Fans or some other means of moving the air around electronic equipment areusually a worthwhile investment. If a form of ram air-cooling is installed, make certain that rainwater cannot enter spray on theequipment.

2.6 INSTALLATION AND REMOVAL PROCEDURESThe following paragraphs provide instructions for installing and removing the ALT-1000. If other associated equipment is tobe installed or removed, refer to the applicable equipment manual for procedures.

Ensure that the aircraft battery master switch is turned off before installing any equipment, mounts, or in-terconnect cables.

2.6.1 UMT-12 (Preferred) or 390R-19 (Alternate) Mounting Tray The UMT-12 or 390R-19 is mounted in the locationdetermined for the ALT-1000 radio altimeter. Refer to Collins UMT-( ) Mount and Thinline II Connectors Instruction Book orto 390R-18/19/20 Universal Mount Assembly Instructions for additional information.

a. Install the UMT-12 or 390R-19 and connector kit according to the procedures printed in the UMT-( ) Mount or390R-19 reference manuals.

18 July 2012 2-7


b. Verify all interconnect wiring before proceeding. Make sure +28 V dc input power is applied only to pin P1-1 for-02X status of ALT-1000 or only to pin P1-9 for -00X status of ALT-1000.

2.6.2 ALT-1000 Radio Altimeter2.6.2.1 Location The radio altimeter is normally mounted in the UMT 12 Universal Mount. The 390R-19 Mounting Trayused with the ALT-50/55 may also be used in retrofit installations of the ALT-1000. Refer to the 390R-18/19/20 UniversalMount Assembly Instructions for additional information. The location of the mount is dependent upon the length of the antennacables. The length of the antenna cables is defined in a previous paragraph. Refer to Tables 2-4 and 2-5 for specific mount,mating connector, and associated parts information. Refer to Figures 2-10, 2-29, and 2-30 for outline and mounting diagramsof the equipment and mounts.

2.6.2.2 Installationa. Remove electrical power from the aircraft and slide unit into mount until mating connectors are fully engaged.

b. Position knurled knobs on front of mount to engage unit mounting projections and tighten knurled knobs.

c. Press on front panel to ensure that the unit is fully seated in the mount. Retighten knurled knobs until unit is securein mount.

d. Ensure that a good electrical bond exists between the unit and mount.

e. Attach safety wire to knurled knobs.

f. Connect receive and transmit antenna cables to two TNC connectors on front of radio altimeter.

2.6.2.3 Removala. Remove electrical power from the aircraft.

b. Disconnect TNC connectors on receive and transmit antenna cables at front of unit. Tag cables to ensure correctreinstallation.

c. Remove safety wire from two knurled knobs that secure unit to mounting tray.

d. Loosen two knurled knobs and disengage from retainer brackets on unit.

e. Slide unit forward until rear connector is disengaged and clear of mounting tray connector.

f. Remove radio altimeter from mounting tray.

2.6.3 ALI-55/55A/55B Radio Altitude Indicator (Used With ALT-1000 (-00X Status) System)2.6.3.1 Location TheALI-55/55A/55B Radio Altitude Indicator can be front or rear mounted in the instrument panel. Referto Figure 2-11 for outline and mounting dimensions.

2.6.3.2 Installationa. Connect ALI-55/55A/55B rear connector to mating connector on wiring harness.

b. Install ALI-55/55A/55B in instrument panel recess and secure with four screws.

2.6.3.3 Removala. Remove four screws that secure ALI-55/55A/55B to instrument panel.

b. Pull ALI-55/55A/55B out of panel recess and disconnect rear connector from mating connector.

c. Remove ALI-55/55A/55B from control panel.

2.6.4 DRI-55 Digital Radio Altitude Indicator (Used With ALT-1000 (-00X or -02X Status) System) The DRI-55can be front or rear mounted using one of the following three methods:

a. The DRI-55 may be front mounted using integral turnlock fasteners. This method uses the least space and adds no extraweight.

b. The DRI-55 may be front mounted using an adapter plate, CPN 659-8671-XXX. This method requires that the four holes inthe panel be tapped or that mooring plate, CPN 629-8672-001, be used.

c. The DRI-55 may be rear mounted using a mooring plate, CPN 629-8672-001.

2-8 18 July 2012


All of the above methods use the same panel cutout. Refer to Figure 2-12 for the outline and mounting dimensions and also thepanel cutout dimensions. Refer Figure 2-13 for typical installations. Select a mounting position that is convenient for pilot orcopilot view and control. Make the instrument panel cutout at this time.

a. Front Mounting Using Integral Turnlock Fasteners:• Use this method to install the DRI-55 in instrument panels 1.27 mm (0.050 in) to 3.18 (0.125 in) thick Turn the integralturnlock actuation screws counterclockwise until they will no longer turn. This moves the integral clamp out of the wayso that the DRI-55 may be inserted in the instrument panel. From the front, slide the DRI-55 into the panel and hookup the mating connector. Install the screw locks to secure the mating connector to the rear connector. Push the DRI-55tight against the instrument panel (do not push on the glass window) while turning the integral turnlock actuating screwsclockwise. Tighten the actuating screws until the DRI-55 is held firmly in place.

b. Front Mounting Using Adapter Plate, CPN 629-8671-XXX• This method requires the use of an adapter plate, CPN-8671-XXX. CPN 629-8671-001 is the gray adapter plate and CPN629-8671-002 is the black adapter plate. This method requires that the four holes in the panel cutout be tapped or that themooring plate, CPN 629-8672-001, be used. Either the tapped holes or the mooring plate is required so that screws can beused to hold the adapter plate in place. From the front, place the DRI-55 into the panel cutout. If the mooring plate is tobe used, slide this into place from behind the instrument panel at this time and retain using the integral turnlock fastenersif necessary. Hook up the mating connector and install the screw locks. Secure the mating connector firmly to the rearconnector. Push the DRI-55 into place against the instrument panel and put the adapter plate in place. Use four screwsinserted from the front to secure the adapter plate and DRI-55 in place.

c. Rear Mounting Using Mooring Plate, CPN 629-8672-001

NOTEThe DRI-55 may be rear mounted so as to be flush with the instrument panel, or it may be rear mountedto extend approximately 3/8 inch from the instrument panel. For flush mounting, place space plate, CPN629-8672-002, between the instrument panel and the bezel of the DRI-55.

• Slide the DRI-55 into place from behind the instrument panel. Slide the mooring plate over the DRI-55 and retain usingthe integral turnlock fasteners. Hook up the mating connector to the rear connector and install the screw locks. Install fourscrews from the front of the DRI-55 and tighten.

2.6.5 339H-4/4A Radio Altitude Indicator (Used With ALT-1000 (-02X Status) System)2.6.5.1 Location The 339H-4/4A Radio Altitude Indicator may be front or rear mounted in the instrument panel. Refer toFigure 2-14 for outline and mounting dimensions.

2.6.5.2 Installationa. Connect 339H-A/4A rear connector to mating connector on wiring harness.

b. Install 339H-4/4A in instrument panel recess and secure with four screws.

2.6.5.3 Removala. Remove four screws that secure 339H-4/4A to instrument panel.

b. Pull 339H-4/4A out of panel recess and disconnect rear connector from mating connector.

c. Remove 339H-4/4A from control panel.

2.6.6 437X-1/1A/1B or ANT-50A/51A/52 Antenna

Do not paint the surface of any radio altimeter antenna.

Refer to Figures 2-19 through 2-28 for radio altimeter antenna outline and mounting dimensions.

18 July 2012 2-9


Six types of antennas are available for installation in the ALT-1000 Radio Altimeter System. The 437X-1, ANT-50A, or ANT-51A is used when the mounting surface is relatively flat. The 437X-1A or 437X-1B is used when the mounting surface iscurved. The 437X-1A fits a curved surface with a radius of 180.34 cm (71 in); the 437X-1B fits a radius of 81.23 cm (32 in).The ANT-52, because of its relatively small size can be used on either flat or curved surface. The altimeter system requires twoantennas, one for transmit and one for receive. The ALT-1000 also provides monitoring of the ANT-52 antennas.

2.6.6.1 Location The antennas should be mounted on the underside of the aircraft, positioned as near the point of rotationas possible. Mounting the antenna near the point of rotation reduces the change in altitude readings due to aircraft pitch attitudeduring approach and landing. The location must provide a clearance cone from the antenna of not less than 120 degrees.

2.6.6.2 Mounting The 437X-1, ANT-50A, ANT-51A, and ANT-52 antennas can be mounted either side by side or in line.The 437X-1A and 437X-1B antennas can be mounted only in line. Refer to Figure 2-15 for typical mounting placement. Theantennas must be separated by no more than the antenna height above the terrain at touchdown, but should be separated by atleast 50.8 cm (20 in) (measured between antenna center lines). The antennas should always be installed as far apart as possiblebut not more than the antenna height above the terrain at touchdown. Otherwise, insufficient terrain area is illuminated forground level operation. If a dual system is installed, the transit antenna from one system must be located as far as possiblefrom the receive antenna of the other system. Except for the ANT-52, the antennas should be mounted with the connectorsperpendicular to a line between the transmit and receive antennas to minimize antenna to antenna signal leakage. The signalleakage should be at least 6 dB below the signal level required for operation. The surface area between the transmit and receiveantennas must be smooth and free from discontinuities.

The combined squint angle of both transmit and receive antennas must not exceed 6 degrees. This angle is measured from thephysical axis of the antenna to a vertical line from the aircraft to the reflecting terrain. In the case of antennas mounted sideby side and on either side of the aircraft centerline, and depending on the symmetry and curvature of the fuselage, the antennascan be pointing in opposite directions, each by some angle. In this case, the angle by which one antenna is tilted away from thevertical cannot exceed 3 degrees (6 degrees from the other antenna). In the case of in-line mounting, the antennas will (mostlikely) be pointing in the same direction, left or right (if not straight down), so that the squint angle of one will be nearly thesame as that of the other in magnitude and direction. In this case, the angle from the vertical can be as much as 6 degrees foreither or both antennas.

For all antennas except the ANT-52, the mounting hole in line with the connector should be marked with black paint on the faceof the antenna before installation. This facilitates orientation of the antenna on the aircraft. These antennas should be orientedso that the antenna connectors are pointed in the same direction and at 90 degrees to the center line between the antennas. TheANT-52 antenna has a small arrow painted on the face. These antennas should be mounted so that the arrow are in line, pointingdirectly toward or away from each other. For installations with the antennas mounted fore and aft the arrows need to be pointingforward of aft. For installations with antennas side by side the arrows should be pointing either right or left.

The antenna mating flange and aircraft surface must be free of paint or other insulation materials to provide a continuous groundpath. Improper grounding results in side-lobe radiation. Do not remove the chromate finish from the antennas or the aircraftstructure, as it provides adequate grounding and protects the aluminum from corrosion.

In certain aircraft installations, the possibility of undesirable side-lobe radiation effects may necessitate that the antennas beinstalled with rf bonding gaskets between the aircraft fuselage and the antenna. An rf gasket constructed of aluminumwire cloth,impregnated with silicone rubber and made of type 40-8520 material, from Metex Electronic Corporation, or equivalent, maybe used. Precut antenna ground gaskets are also available from the Collins General Aviation Division of Rockwell Internationalunder the part numbers shown in Table 2-3.

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Table 2-3. Radio Altimeter Antenna Gaskets Available

ANTENNA GASKET CPN

437X-1437X-1A

437X-1B (CPN 622-0954-001)437X-1B (CPN 622-0954-002)

ANT-50AANT-51AANT-52

018-1394-020018-1394-020018-1394-030018-1394-040018-1394-060018-1394-020018-1394-100

2.6.6.3 Installationa. Install antenna ground gasket on 437X-1/1A/1B or ANT-50A/51A/52 Antenna

b. Install antenna in airframe with TNC connector facing antenna cable, and secure with eight (8) screws for the 437X-1/1A/1B or ANT-51A Antenna, twelve (12) screws for the ANT-50A Antenna, and four (4) screws for the ANT-52Antenna.

c. Connect the antenna cable TNC connector to the antenna connector and safety wire.

d. Repeat the previous steps for the second antenna.

2.6.6.4 Removala. Remove the safety wire from the TNC connector and disconnect the antenna cable from the antenna.

b. Remove the four (4), eight (8), or twelve (12) screws and antenna from the airframe. Do not disturb the groundinggasket unless the gasket on the antenna is being replaced.

c. Repeat the previous steps for the second antenna.

Table 2-4. Equipment Mounting Options

DESCRIPTION COLLINS PART NUMBER QTY

UMT-12 Mount (Preferred)Connector Kit** orConnector Kit with groundingbracket**

622-5212-004634-4192-017 or634-4192-018

11 or1

390R-19 Mount (Alternate)Connector Kit**

622-1195-301634-4193-012

11

* Quantity required for typical installation.** Refer to CROSS REFERENCE. For a complete listing of the components included in each kit.

18 July 2012 2-11


Table 2-5. Connector Kit Contents

CONNECTOR KITPART NUMBER

PARTDESCRIPTION

COLLINSPART NUMBER QTY

634-4192-017 Connector, Male - TLIIContactKeyway, ConnectorRing, Captive - KeywayInsert, FastenerScrew, 4-40 x 3/8”Connector, Male - TNC

634-1112-001372-2514-110634-1116-001634-1117-001334-2117-010324-2604-000857-1511-010

14623222

634-4192-018 Connector, Male – TLIIContactKeyway, ConnectorRing, Captive – KeywayInsert, FastenerScrew, 4-40 x 3/8”Bracket, GroundingScrew, 6-32 x 1/2”

634-1112-001372-2514-110634-1116-001634-1117-001334-2117-010324-2604-000992-3477-004343-0171-000

146232212

634-4193-012 Connector, Male - TLIIContactKeyway, ConnectorRing, Captive - KeywayWasher, Flat - No. 4Screw, 4-40 x 1/2”Connector Plate AssyConnector, Male - TNC

634-1112-001372-2514-110634-1116-001634-1117-001310-0779-030324-2605-000634-1130-018857-1511-010

146222212

Table 2-6. Mating Connector Contacts and Special Tools

CONTACTDESCRIPTION

CONTACTPART NUMBER

CRIMPINGTOOL

INSERTIONTOOL

EXTRACTIONTOOL

Snap in tuning fork(wire with insulation upto 0.050 in. dia).

372-2514-110 359-0697-010 or623-8579-001(* Daniels GMT-221)

359-0697-050(* Daniels DAK-188)

359-0697-020(*Daniels DRK-230)

Snap in tuning fork (wirewith insulation 0.050 to0.080 in. dia).

372-2514-180 359-0697-010(*Daniels GMT-221)

359-0697-050(*Daniels DAK-188)

359-0697-020(*Daniels DRK-230)

* Special tools are available in connector kit 359-0697-080 (Daniels DMC-593) or can be ordered from: Daniels Manufac-turing Corp., 2266 Franklin Road, Bloomfield Hills, Michigan 48013.

2.7 TESTING

2.7.1 Post Installation Test, Systems with ALI-55/55A/55B or 334H-4/4A IndicatorsNOTE

The ALI-55B Radio Altimeter Indicator altitude scale is calibrated in meters. The metric altitudes shownin ( ) apply to an ALT-1000 Radio Altitude System with an ALI-55B installed.

a. Turn on the aircraft primary electrical power.

2-12 18 July 2012


b. Adjust the DH knob on the indicator to set the DH index to 25 ft (7.6 m). The indicated altitude should be at a nominal0 ft (0 m), the red flag should be out of view, and the DH lamp should be on. If the indicated altitude is off scale (>2500ft or >762 m); the pointer will be out of view, the system is not operating properly, and diagnostic testing is required(see Paragraph 2.7.1.1).

c. Push and hold the TEST button on the indicator. The indicated altitude should be 50 ft (15.2 m), the red instrumentflag should be in view, and the DH lamp should be off.

d. With the TEST button still being held, slowly increase the DH index towards 50 ft. The DH lamp should go out at a50 ±5 ft (15.2 ±1.52 m).

e. Release the TEST button. The indicated altitude reading should return to the nominal 0 ft (0 ±5 ft or 0 ±1.5 m) level.

2.7.1.1 Post Installation Troubleshooting With electrical power applied to the system, push and hold the TEST buttonon the indicator until the instrument pointer is no longer out of view (takes a nominal 10 seconds) and goes to an altitude readingof between 100 and 1500 ft. This altitude reading relates to a specific single or multiple faults that have been detected by themonitoring system of the ALT-1000. Each major fault has an equivalent altitude reading in the binary indications of 100, 200,400, and 800 ft with multiple faults being indicated by sums of these basic values. Refer to the Maintenance section, Chapter 5for the diagnostic meaning of the observed altitude reading.

2.7.2 Post Installation Test, Systems with DRI-55 IndicatorsNOTE

Due to the test sequence provided by this instrument, the display of any diagnostic altitude values after a10 second hold of the DH/TEST knob is masked by the instruments display test which produces all 8s onthe altitude display units. As a result of this, the diagnostic altitudes presented by the ALT-1000 after 10seconds can not be observed. An accurate DC meter across the analog altitude output of the ALT-1000 canbe used to establish what altitude value is being produced by the ALT-1000. See the table of voltage valuesvs indicated altitudes in the Maintenance section of this manual.

a. Turn on the aircraft primary electrical power.

b. Adjust the DH/TEST knob on the indicator to set the DH index to 25 ft. The indicated altitude should be at a nominal0 ft, the red flag over the DH readout should be out of view, and for DRI-55 Indicators with the optional DH indicatorlamp the DH lamp should be on. If the indicated altitude is blank the monitoring system of the ALT-1000 has detecteda fault and diagnostic testing is required.

c. Push and hold the DH/TEST knob on the indicator. The following sequence takes place:

(1) The DH index value (to a one foot level) is displayed for a nominal 2 seconds.

(2) After that an altitude of 50 ft is displayed for the next two seconds, indicating that no faults have been detectedby the monitoring system. For DRI-55 indicators with the optional DH indicator lamp, this lamp should not beon. If a fault was detected, the display would be blank during this 2 second period.

(3) After this, the altitude display shows the number 8 on each of the four display units. This verifies that all segmentsof the display units are active. The display will remain in this configuration for as long as the DH/TEST knob isheld in the test position.

d. For DRI-55 indicators with the optional DH lamp, after the display goes to 50 ft in Step c.2 above with the DH/TESTknob still being held in the test mode, slowly increase the DH index towards 50 ft. The DH lamp should extinguishat a nominal 50 ft as read on the DH window of the instrument.

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Figure 2-2. ALT-1000 Radio Altimeter Input/Output Interface Circuits

18 July 2012 2-15/(2-16 Blank)

.


Figure 2-3. ALT-1000 Radio Altimeter Mating Connector Pin Assignment

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Figure 2-4. ALT-1000 Radio Altimeter BITE Mating Connector Pin Assignment

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Figure 2-5. ALI-55/55A/55B Radio Altimeter Indicator Mating Connector Pin Assignment

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Figure 2-6. DRI-55 Digital Radio Altimeter Indicator Mating Connector Pin Assignment

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Figure 2-7. ALT-1000 Radio Altimeter System, Typical Interconnect Diagram (Sheet 1 of 3)

18 July 2012 2-21/(2-22 Blank)



18 July 2012 2-23/(2-24 Blank)



18 July 2012 2-25/(2-26 Blank)

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Figure 2-8. ALT-1000 (-02X Status Units) Radio Altimeter System for 2000-Foot Operation, Interconnect Wiring Diagram

18 July 2012 2-27/(2-28 Blank)

.


Figure 2-9. ALT-1000 (-00X Status Units) Radio Altimeter System for 2500-Foot Operation, Interconnect Wiring Diagram

18 July 2012 2-29/(2-30 Blank)

.


Figure 2-10. ALT-1000 Altimeter System, Outline and Mounting Diagram (Sheet 1 of 2)

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Figure 2-10. ALT-1000 Altimeter System, Outline and Mounting Diagram (Sheet 2 of 2)

18 July 2012 2-33/(2-34 Blank)

.


Figure 2-11. ALI-55/55A/55B Radio Altimeter Indicator, Outline and Mounting Diagram

18 July 2012 2-35/(2-36 Blank)

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Figure 2-12. DRI-55 Digital Radio Altitude Indicator, Outline and Mounting Dimensions

18 July 2012 2-37/(2-38 Blank)

.


Figure 2-13. DRI-55 Digital Radio Altitude Indicator, Typical Installations

18 July 2012 2-39/(2-40 Blank)


Figure 2-14. 339H-4/4A Radio Altimeter Indicator, Outline and Mounting Diagram

18 July 2012 2-41/(2-42 Blank)

.


Figure 2-15. 437X-1/1A/1B and ANT-50A/51A/55 Antenna, Typical Installation

18 July 2012 2-43/(2-44 Blank)


Figure 2-16. ANT-50A Antenna (CPN 622-3698-001), Outline and Mounting Diagram

18 July 2012 2-45/(2-46 Blank)

.


Figure 2-17. ANT-51A Antenna (CPN 622-4550-001), Outline and Mounting Diagram

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Figure 2-18. ANT-52 Antenna (CPN 622-6793-001), Outline and Mounting Diagram

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Figure 2-19. 437X-1 Antenna (CPN 522-4140-001/-006), Outline and Mounting Diagram

18 July 2012 2-49



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Figure 2-21. 437X-1 Antenna (CPN 522-4140-003), Outline and Mounting Diagram

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Figure 2-23. 437X-1A Antenna (CPN 522-4255-001/-007), Outline and Mounting Diagram

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Figure 2-24. 437X-1A Antenna (CPN 522-4255-002), Outline and Mounting Diagram


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Figure 2-27. 437X-1B Antenna (CPN 622-0954-001), Outline and Mounting Diagram

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Figure 2-28. 437X-1B Antenna (CPN 622-0954-002), Outline and Mounting Diagram

18 July 2012 2-57/(2-58 Blank)


Figure 2-29. UMT-10/11/12/13 Universal Mount, Outline and Mounting Diagram (Sheet 1 of 3)

18 July 2012 2-59/(2-60 Blank)



18 July 2012 2-61/(2-62 Blank)



18 July 2012 2-63/(2-64 Blank)

.


Figure 2-30. 390R-18/19/20 Universal Mount, Outline and Mounting Diagram (Sheet 1 of 2)

18 July 2012 2-65/(2-66 Blank)


Figure 2-30. 390R-18/19/20 Universal Mount, Outline and Mounting Diagram (Sheet 2 of 2)

18 July 2012 2-67/(2-68 Blank)

.


Figure 2-31. AEA Wire Marking Standard

18 July 2012 2-69/(2-70 Blank)

.

523-0806452

CHAPTER 3Operation

3.1 GENERALThis chapter describes the operation of the ALT-1000 Radio Altimeter System. Descriptions of the displays and controls arepresented as follows:

• Figure 3-1 shows the controls and indicators of the ALI-55/55A/55B indicators.• Figure 3-2 also describes the controls and indicators of the ALI-55/55A/55B indicators.• Figure 3-3 shows the controls and indicators of the 339H-4/4A indicators.• Figure 3-4 shows the controls and indicators of the DRI-55 indicator.• Figure 3-5 also describes the controls and indicators of the DRI-55 indicator.The variety of combinations of control features using electronic flight displays and remote control units in any given installationprecludes their coverage in this publication. Refer to the specific publications covering the aircraft avionics system for thoseinstallations.

The ALT-1000 Radio Altimeter System provides radio altitude data from 2500 feet above the terrain through touchdown. TheALI-55 is primarily used in fixed-wing aircraft. The ALI-55A is primarily used in helicopters. The ALI-55B comes with anindicator scaled in meters rather than feet.

Figure 3-1. ALI-55/55A/55B Radio Altitude Indicator

3.2 ALI-55/55A/55B RADIO ALTITUDE INDICATORS, DISPLAYS, AND CONTROLS

Although the Altimeter System has a very high degree of functional integrity, the user must recognize thatit is not practical to provide monitoring and/or self-test for all conceivable system failures and, howeverunlikely, it is possible that erroneous operation could occur without a fault indication. It is the responsibilityof the pilot to detect such an occurrence by means of cross-checks with redundant or correlated informationavailable in the cockpit.

3.2.1 Pointer and Dial Scale The pointer indicates aircraft height above the terrain during the approach phase of the flight.The scale of the indicators displays altitude between -20 and +2500 feet or -6.1 to +750 meters.

The ALI-55 Radio Altitude Indicator is used primarily in fixed wing aircraft. The display of the ALI-55 is linear from 0 to 500feet, with major scale division every 50 feet and minor scale divisions every 10 feet. The scale is compressed and linear from500 to 2500 feet, with major scale marks every 500 feet and minor scale marks every 100 feet.

29 January 2004 3-1

Operation 523-0806452

The ALI-55A Radio Altitude Indicator is used primarily in helicopters. The display scale of the ALI-55A is linear from 0 to100 feet, with major scale divisions every 10 feet and minor divisions every 5 feet. The scale is compressed and linear from 100to 500 feet, with scale marks every 50 feet. The scale is compressed from 500 to 2500 feet, with scale marks every 500 feet.

The ALI-55B is used primarily in fixed-wing aircraft. The display scale of the ALI-55B is linear from 0 to 152.4 meters, withmajor scale divisions every 10 meters and minor divisions every 5 meters. The scale is compressed and linear from 152.4 to750 meters, with major scale divisions every 100 meters and minor divisions every 50 meters.

Since the indicators are calibrated to read 0-foot at the point of touchdown and landing gear extended, below 0-foot indicationsoccur when the aircraft is on the ground with the aircraft weight on the landing gear. The scale mark to the left of the 0-footaltitude indication is approximately -20 feet or -6.1 meters.

3.2.2 Decision Height (DH) Index and DH Adjustment Knob The DH knob selects the decision height. The DHIndex indicates the selected decision height on the edge of the dial scale.

3.2.3 DH Indicator The DH Indicator lights when the aircraft descends below the selected decision height indicated by theDH Index. The DH indicator remains lit at all altitudes below the selected decision height. Once on the ground, the decisionheight light may be turned off by setting the decision height below the indicated altitude.

During ascent, the DH indicator remains lit until the altitude pointer is above the DH index or selected decision height. The DHindicator turnoff point varies with the selected decision height. When the DH index is set at any altitude between 0 and 500 feet,the DH indicator turns off at 0 to 10 feet above the selected decision height for the ALI-55A and 10 to 30 feet for the ALI-55.With the DH index set at any altitude between 500 and 2500 feet, the DH indicator turns off at 70 to 190 feet above the selecteddecision height.

3.2.4 Warning Flag The warning flag comes into view when the system loses power, when the altitude pointer does nottrack the altitude signal from the radio altimeter or during self-test of the system. The ALI-55/55A/55B Radio Altitude Indica-tors also provide an instrument flag output for an external system (such as a flight director). When the aircraft is above 2500feet, the flag remains out of view unless a malfunction occurs.

Figure 3-2. ALI-55/55A/55B Radio Altitude Indicator, Controls and Indicators

3.2.5 TEST Switch In normal operation, pushing the TEST switch on the ALI-55/55A/55B indicator starts a functional testof the ALT-1000 Radio Altimeter System. When the ALT-1000 system is functioning properly, the pointer indicates a self-testaltitude of 50 ± 5 feet (15.2 ± 1.52 meters), the flag comes into view, and the DH indicator lights if the DH index is set above50 feet (15.2 meters).

3-2 29 January 2004


When the ALT-1000 is not operating properly, the altitude pointer indicates 2600 feet for 10 seconds if the TEST switch is heldin the pushed position. After 10 seconds, the altitude will change to read an altitude value that signifies what fault or faults aredetected. See Chapter 5, Maintenance for the altitude reading diagnostic values.

Installations may have a provision to inhibit self-test during the approach when radio altitude data is being used by the flightcontrol system.

3.3 339H-4/4A RADIO ALTITUDE INDICATORS, DISPLAYS, AND CONTROLS

Although the altimeter system has a very high degree of functional integrity, the user must recognize thatit is not practical to provide monitoring and/or self-test for all conceivable system failures, and, howeverunlikely, it is possible that erroneous operation could occur without a fault indication. It is the responsibilityof the pilot to detect such and occurrence by means of cross-checks with redundant or correlated informationavailable in the cockpit.

3.3.1 Pointer and Dial Scale The pointer and dial scale display indicates aircraft height above the terrain during the ap-proach phase of the flight.

The 339H-4 has a 0 to 2000 foot altitude scale calibrated for fixed wing aircraft. The display of the 339H-4 is linear from 0 to500 feet, with major scale divisions every 50 feet and minor divisions every 10 feet. The scale is compressed and linear from500 to 2000 feet, with major scale divisions every 500 feet and minor divisions every 100 feet.

The 339H-4A has a 0 to 2000 foot altitude scale calibrated for helicopters. The display of the 339H-4A is linear from 0 to 100feet, with major divisions every 10 feet and minor divisions every 5 feet. The scale is compressed and linear from 100 to 500feet, with major scale divisions every 100 feet and minor divisions every 50 feet. The scale is compressed and linear from 500to 2000 feet, with scale divisions every 500 feet.

Figure 3-3. 339H-4/4A Radio Altimeter Indicator

3.3.2 Other Features The Decision Height (DH) Index, DH Adjustment Knob, Warning Flag, and TEST switch all operatethe same as previously described for the ALI-55/55A/55B Indicators with the exception that the maximum display altitude is2000 feet instead of 2500 feet.

29 January 2004 3-3


3.4 DRI-55 DIGITAL RADIO ALTITUDE INDICATOR, DISPLAYS, AND CONTROLS

Although the Altimeter System has a very high degree of functional integrity, the user must recognize thatit is not practical to provide monitoring and/or self-test for all conceivable system failures and, howeverunlikely, it is possible that erroneous operation could occur without a fault indication. It is the responsibilityof the pilot to detect such an occurrence by means of cross-checks with redundant or correlated informationavailable in the cockpit.

3.4.1 Radio Altitude Display The radio altitude display indicates aircraft height above the terrain during the approachphase of the flight. The display increments are 10 feet below 1000 feet and 50 feet above 1000 feet. The display range is from0 to 2500 feet. Above 2500 feet, the display is blanked.

Figure 3-4. DRI-55 Digital Radio Altitude Indicator

3.4.2 Decision Height (DH) Display and DH/PUSH TEST Knob The DH/PUSH TEST knob selects the decisionheight, which is displayed by the DH display. The decision height is selected by turning the DH/PUSH TEST knob clockwiseor counterclockwise until the DH display indicates the desired decision height. The user may set the decision height anywherebetween the 10-foot increments by interpolating or by using the DH altitude display during the test function. The decision heightrange is from 0 to 980 feet.

3.4.3 DH Annunciator DRI-55 Indicators CPN 622-4160-005, -006, -007, -008, -015, -016, -017, and -018 have DH an-nunciators on their front panels. The DH annunciator lights when the aircraft descends below the selected decision height, asindicated by the DH display.

DRI-55 Indicators CPN 622-4160-001, -002, -003, -004, -011, -012, -013, and -014 do not have DH annunciators.

3.4.4 DH/PUSH TEST Knob Pushing the DH/PUSH TEST knob on the DRI-55 indicator initiates a function self-test rou-tine of the radio altimeter system. The following sequence occurs when the DH/PUSH TEST knob is pushed and held.

a. Decision height is displayed in the RAD ALT display window for a nominal 2 seconds (to the nearest foot) and maybe adjusted during the first 2 seconds the knob is pushed.

b. The system test altitude of 50 feet is displayed for a nominal 2 seconds for a system that is functioning properly,otherwise the display goes blank (altitude reading = 2600 ft).

c. After 2 seconds the lamp test (8888) is displayed until the DH/PUSH TEST is released.

3-4 29 January 2004


Figure 3-5. DRI-55 Digital Radio Altitude Indicator, Controls and Indicators

3.5 OPERATING PROCEDURESNOTE

On the DRI-55 the DH set and TEST functions are combined into one control knob. Rotation of the knobwithout pushing sets the DH value. Pushing the knob invokes the TEST function (DH lamp should be on).

3.5.1 Preflight Checka. Apply electrical power to the ALT-1000 Radio Altimeter System.b. Adjust the DH knob on the indicator to set the DH index to 20 feet (6.1 meters).c. Push and hold the PUSH TEST knob on the indicator and observe indicator for the following indications:

• Pointer indicates 50 ±5 feet (15.2 ±1.52 meters).• DH indicator is off.• Flag is in view.

d. With the TEST switch pushed, slowly adjust DH knob to increase DH index altitude indication, and verify the DHindicator light when the DH index is between 45 and 55 feet (13.7 and 16.7 meters).

e. Release TEST switch and observe indicator. Warning flag should be out of view and altitude indication should be 0foot nominal.

3.5.2 Flight Operations3.5.2.1 Cruise Altitude Operation For ALT-1000 (-00X status) units; the indicator pointer is in view when the aircraftis within 2500 feet (760 meters) of the terrain. For ALT-1000 (-02X status) units; the indicator is in view when the aircraft iswithin 2000 feet (608 meters) of the terrain. When the aircraft is higher than these values, the indicator pointer is behind themask and the indicator flag is out of view.

An FCS WARN output (P1-8) is applied to the flight control system (flight director/autopilot) to indicate that the radio altitudeinformation is not usable.

29 January 2004 3-5


3.5.2.2 Approach Phase Operation

ALT-1000 Radio Altimeter Systems that use the DRI-55 Digital Radio Altitude Indicator should not havea functional self-test performed during the approach phase of aircraft operation. The functional self-test,initiated by pushing the PUSH TEST switch on the DRI-55, causes the DRI-55 to display self-test informa-tion for a minimum of four seconds. During the DRI-55 four seconds (minimum) self-test time period, theALT-1000 Radio Altimeter System altitude information is not displayed on the DRI-55.

Before initiating an approach, the pilot should check the radio altimeter system using the self-test feature and adjust the DHknob to set the DH index on the published decision height for the facility being used. When the aircraft descends to the selecteddecision height, the DH indicator lights to alert the pilot that a continue-approach or go-around decision must be made.

Although the Altimeter System has a very high degree of functional integrity, the user must recognize thatit is not practical to provide monitoring and/or self-test for all conceivable system failure and, howeverunlikely, it is possible that erroneous operation could occur without a fault indication. It is the responsibilityof the pilot to detect such an occurrence by means of cross-checks with redundant or correlated informationavailable in the cockpit.

NOTEDetection of possible in-flight radio altimeter malfunctions should be maximized by using the self-test func-tion immediately prior to the approach phase of the flight. Cross-referencing the radio altimeters shouldoccur below 2500 feet (760 meters) for -00X statuses or below 2000 feet (608 meters) for -02X statuses ofthe ALT-1000.

During the descent, the radio altimeter system provides altitude and altitude trip information to the flight control system (flightdirector/autopilot) and the Ground Proximity Warning System (GPWS).

After landing, the DH indicator can be turned off by adjusting the DH knob fully counterclockwise.

3.5.3 Points to Remembera. In some installations, the altimeter may read less than zero altitude on the ramp. This is a normal phenomenon in

aircraft whose altimeter antennas are nearer the ground on the ramp than at touchdown.b. The radio altimeter is intended to give accurate altitude information over a wide variety of terrain characteristics.

Altimeter accuracy may be affected, however, under exceptional circumstances. The dominant reflecting surface maynot coincide with treetop level when flying over triple-tier jungle or with the top of the snow when flying over verydeep, fluffy snow.

c. The time-constant of the radio altimeter is about 100 milliseconds. While this allows the altimeter output to followmost terrain accurately, the altimeter will not respond to extremely rapid fluctuations in terrain.

d. At extreme pitch or roll, altimeter accuracy may be impaired.e. Frequent use of the self-test feature, especially before take-off and at the beginning of the approach, will enhance

probability of detecting possible altimeter system malfunctions.

3-6 29 January 2004

523-0806452

CHAPTER 4Theory of Operation

4.1 INTRODUCTIONThis chapter presents the theory of operation for the Collins ALT-1000 Radio Altimeter. The theory is presented as an overviewof the entire system and as a functional theory for each system unit in the paragraphs that follow.

4.2 OVERVIEWA single Collins ALT-1000 Radio Altimeter System consists of an ALT-1000 Radio Altimeter (and mount), two antennas, andan indicator. This ALT-1000 is normally installed as a single system, but may also be installed as a dual system. The ALT-1000 Radio Altimeter was designed for use in new installations and also as a drop-in replacement in an existing ALT-50A andALT-55B Radio Altimeter installations. As such, the ALT-1000 will operate with a number of different antennas and indicators.These antennas and indicators are listed and described in more detail in the following paragraphs.

4.2.1 Installation Configuration The ALT-1000 Radio Altimeter may be installed in one of the following configurations:

• The ALT-1000 (-00X status) may be installed as part of a new installation. This configuration normally uses ANT-52 RadioAltimeter Antennas and a DRI-55 Radio Altitude Indicator.

• The ALT-1000 (-00X status) may be installed as a drop-in replacement in an existing ALT-55B installation. This config-uration normally uses ANT-50A/51A/52 Radio Altimeter Antennas and an ALI-55/55A/55B or DRI–55 Radio AltimeterIndicator.

• The ALT-1000 (-02X status) may be installed as a drop-in replacement in an existing ALT-50A installation. This configura-tion normally uses 437X-1/1A/1B Radio Altimeter Antennas and a 339H-4/4A Radio Altimeter Indicator.

4.3 FUNCTIONAL THEORYThe functional theory of operation will briefly describe the functions of each unit and provide signal flow information. TheALT-1000 Radio Altitude System includes:

4.3.1 ALT-1000 Radio Altimeter The ALT-1000 Radio Altimeter is an FMCW transceiver that measures the aircraft radioaltitude (up to 2500 feet) above the terrain during approach mode. The ALT-1000 transmits a reference signal on one antenna,receives the reflected signal on another antenna, and then computes the aircraft altitude.

4.3.1.1 Power The ALT-1000 consists of a power supply, a digital section, transmitter, and receiver. Operating power isprovided by the +28-V dc aircraft supply; an internal power supply converts this voltage into required supply levels for theALT-1000.

4.3.1.2 Digital Section The digital section consists of the microprocessor, the field programmable gate array (FPGA),the power monitor, the system watchdog, the signal presence detector, the fault log non-volatile memory, the analog channelmonitor, several strap inputs, the voltage and temperature references, modulation generator and control, and variable low-passfilter.

4.3.1.3 Microprocessor/FPGA The microprocessor and FPGA share processing responsibilities using the ADDRESSBUS A(0-15). The microprocessor is an 80188 processor running at 12 MHz. Program memory is stored in the EEPROM andin the RAM. The FPGA contains the altitude processor and ARINC 429 UARTs for BITE/IAT/Shop functions.

4.3.1.4 Power Monitor / System Watchdog The power monitor and system watchdog reset the ALT-1000 circuits asrequired to ensure proper operation. The power monitor causes a reset if the supply voltage falls below 4.65 V dc for more thanone second. The system watchdog causes a reset if the WDI WATCHDOG input line has been high or low for more than 1.6seconds.

4.3.1.5 Signal Presence Detector The signal presence detector filters and tests the output signal to determine if the signalis valid. Altitude is reported with the sign/status matrix bits set to normal operation or FCS warn flag set to No Warn only ifthe detector state is true.

4.3.1.6 Fault LogMemory The fault logmemory is a serially controlled, electrically erasable and programmable, read-onlymemory (EEPROM). The FPGA controls the memory and writes fault information into the EEPROM. The fault log memorycan be read or erased using the BITE interface and an external computer.

4.3.1.7 Analog Channel Monitor The analog channel monitor multiplexes several signals into a single analog-to-digitalconverter so the signals can be monitored for proper operation of the ALT-1000. The analog channel monitor is controlled byserial data from the FPGA. The signals monitored are: DC analog output, ground, the signal presence detector, the temperatureof the voltage reference circuit, and the internal power supply levels.

29 January 2004 4-1

Theory of Operation 523-0806452

4.3.1.8 Aircraft Installation Delay The aircraft installation delay (AID) value in feet is determined during certificationand is set by strapping one of the following rear connector pins; AID 20 FT, AID 40 FT, or AID 57 FT to aircraft ground orAID COMMON as required. These three discrete inputs are tied to pullup resistors and applied to the FPGA. This strappingprovides a customized airplane offset to ensure accurate altitude indications when the airplane is in a touchdown attitude. ThisAID compensation is applied to an AID/self-test switch. The AID normally is switched to both discriminators, but it is removedin self-test mode since the test function is internally generated and not related to airplane characteristics.

4.3.1.9 Modulation Frequency The modulation frequency (MOD FREQ) is set by strapping rear connector pin MODFREQ 50Hz or MOD FREQ 51 Hz to aircraft ground or MOD FREQ COMMON as required. These two discrete inputs aretied to pullup resistors and applied to the FPGA. The left ALT-1000 is strapped (as shown) for a 50 Hz modulation frequency.The right ALT-1000 is strapped for a 51 HZ modulation frequency.

4.3.1.10 Self Test The SELF TEST pin is set by the remote RADIO ALTIMETER TEST button. This discrete input isdiode isolated, tied to a pullup resistor, and input to the FGPA. A ground on this pin selects the ALT-1000 self-test function.When test mode is selected, a 50-foot altitude test signal is switched to the preamplifier instead of the altitude input from themixer. This test signal is an IF frequency corresponding to a 50-foot above terrain altitude input.

4.3.1.11 Antenna Continuity Circuit the ALT-1000 has an antenna continuity test circuit that tests for the presence ofproperly connected ANT-52 Radio Altimeter Antennas. The ANTENNAMONITOR ENABLE pin must be grounded to enablethis function. The antenna continuity test circuit provides dc voltages that pass through the XMT ANTENNA to the TRANS-MITTER and through the RCV ANTENNA to the RECEIVER.

4.3.1.12 Attitude Trips One or more of the four transistor switches may be programmed to provide a discrete RAD ALTTRIP output to optional non-Collins airplane equipment.

4.3.1.13 Transmitter The transmitter generates a 4250- to 4350-MHz swept deviation output to the transmit antenna. Thetransmitter consists of a voltage controlled oscillator (VCO), power amplifier (PA), frequency detector, isolator, antenna conti-nuity test circuit (described above), and low pass filter.

4.3.1.14 VCO The VCO is a common collector transistor that operates at 4.3 GHz. The MODULATION INPUT causes thetransmit frequency to sweep ±50 MHz. The PA buffers and amplifies the VCO output signal. Frequency detectors follow thePA and detect when the signal is at the low, center, and high frequency points. The isolator prevents other signals from enteringthe transmitter through the antenna.

4.3.1.15 Receiver The receiver consists of an isolator, bandpass/low pass filter, low noise amplifier, mixer, self test inputswitch (described above), intermediate frequency amplifiers, and filtering. The isolator performs two functions. First, the iso-lator prevents the mixer LO from leaking out of the receiver antenna port, reflecting from the antenna, and returning as a falsealtitude signal. Second, the isolator provides a constant 50 ohm impedance to the low noise amplifier. The bandpass and lowpass filter combine to prevent unwanted RF energy from entering the receiver.

4.3.1.16 Low Noise Amplifier The low noise amplifier reduces the receiver noise floor and allows operation of the ALT-1000 at high altitude with minimal transmitter power. The mixer combines the low noise amplifier output with a sample of thecurrent transmitted signal producing an output signal with a frequency proportional to the airplane altitude (approximately 20Hz/foot). This output signal is applied to the first and second intermediate frequency amplifiers. The intermediate frequencyamplifier gains are sensitive to frequency and provide more gain at higher frequencies to compensate for losses due to the longertransmission path of the signal. The filtering reduces interference between altimeters at altitudes below 250 feet.

4.3.2 437X-1/1A/1B Radio Altimeter Antenna The 437X-1/1A/1B Radio Altimeter Antennas were designed to operatewith the ALT-50A Radio Altimeter System. These antennas will also function with the ALT-1000. The antenna monitoringfunction must not be enabled (P1-21 ANT MON ENABLE must be left open). Refer to the ALT-50A Radio Altimeter SystemInstruction Book, CPN 523-0764281 for further information on these antennas.

4.3.3 ANT-50A/51A Radio Altimeter Antenna The ANT-50A/51A Radio Altimeter Antennas were designed to operatewith the ALT-55B Radio Altimeter System. These antennas will also function with the ALT-1000. The antenna monitoringfunction is must not be enabled (P1-21 ANTMON ENABLE must be left open). Refer to the ALT-55B Radio Altimeter SystemInstruction Book, CPN 523-0766793 for further information on these antennas.

4.3.4 ANT-52 Radio Altimeter Antenna The ANT-52 Radio Altimeter Antennas were designed to operate with the ALT-55B Radio Altimeter System. These antennas will also function with the ALT-1000. The antenna monitoring function must beenabled (P1-21 ANT MON ENABLE must be grounded) in order to provide antenna monitoring. Refer to the ALT-55B RadioAltimeter System Instruction Book, CPN 523-0766793 for further information on this antenna.

4-2 29 January 2004


4.3.5 339H-4/4A Radio Altimeter Indicator The 339H-4/4A Radio Altimeter Indicators were designed to operate withthe ALT-50A Radio Altimeter System. These indicators will also function with the ALT-1000. Refer to the ALT-50A RadioAltimeter System Instruction Book, CPN 523–0764281 for further information on these indicators.

4.3.6 ALI-55/55A/55B and DRI-55 Radio Altimeter Indicators The ALI-55/55A/55B and DRI-55 Radio AltimeterIndicators were designed to operate with the ALT-55B Radio Altimeter System. These indicators will also function with theALT-1000. Refer to the ALT-55B Radio Altimeter System Instruction Book, CPN 523-0766793 for further information onthese indicators.

29 January 2004 4-3/(4-4 Blank)


Figure 4-1. ALT-1000 Radio Altimeter, Functional Block Diagram

29 January 2004 4-5/(4-6 Blank)

.

523-0806452

CHAPTER 5Maintenance

5.1 GENERALThis section provides a procedure for testing and troubleshooting the ALT-1000 Radio Altimeter System. The test procedureprovides fault isolation down to the line replaceable unit (LRU) while the system is installed in the aircraft. Faulty units canthen be tested and repaired with the bench procedures given in the associated unit repair manual.

5.2 MAINTENANCE SCHEDULENo periodic maintenance is required on the ALT-1000. Units should not be removed from the aircraft unless repair is required.

5.3 TEST EQUIPMENT AND POWER REQUIREMENTS

5.3.1 Test Equipment The analog test procedure of Section 5.4.2 is performed without the use of any test equipment. Thedigital test procedure of Section 5.4.3 requires the use of test equipment that can transmit and receive ARINC 429 data. Apersonal computer with a Collins CTC-429 interface card and cable with the appropriate software is required. This interfacesystem is not available at the time of this publication release and will be added later.

5.3.2 Power Requirements All power required to perform the system test and troubleshooting is provided by the aircraftin which the system is installed.

5.4 TESTING AND TROUBLESHOOTING

5.4.1 Diagnostic Information Both analog and digital diagnostic information is available on the ALT-1000 outputs. Theanalog diagnostic information is present on the DC ANALOG ALT output connector pins (P1-57/59) upon activation of theunits test mode. The digital diagnostic information is present on the BITE connector TX A/B output pins (P12-2/3) when theunit is commanded into the shop test mode. Shop test mode is commanded by the transmission of the appropriate ARINC 429word (see below) to the RX A/B input pins (P12-4/5). The P12 connector is located under the top fold down portion of the unitsfront panel.

5.4.2 Analog Diagnostic Information For systems that use indicators such as the 339H-4/4A and ALI-55/55A/55Bseries, diagnostic information can be read in terms of an altitude value during the test mode of operation (see Tables 5-1 and5-2). When the TEST button is pushed and held on the display instrument, if no faults are detected by the units monitoring, a 50±5 foot altitude level and an altitude warn flag will be present and will remain present until the TEST button is released. If a faultis present, the indicator pointer will be out of view (2600 feet analog output). Pushing and holding the TEST button initiallycauses the flag to appear and remain present during the entire test sequence (the instrument pointer is already out of view). Aftera nominal 10 seconds of holding the TEST button depressed, the instrument will display an altitude value indicating the faultor faults detected. Multiple faults provide an altitude reading that equals the sum of the individual fault values. As an example:an antenna fault (100 ft) plus an invalid strap fault (400 ft) provides an altitude reading of 500 feet.

For systems that use DRI-55 indicators, the ALT-1000 produces the same analog diagnostic information to the display instru-ment but after a nominal 4 seconds with the PUSH TEST knob held in the test position. While the TEST button is being held,the unit will display all 8’s on the display readout of the instrument. The only diagnostic information that can be displayed inthe first 2 seconds will be 50 feet for no faults detected or a blank display if a system fault or faults are detected. The DC analogvoltage values of the detected faults can be read on the DC ANALOG ALT output pins (P1-57/59). Voltage output levels foreach fault are listed in Table 5-2.

29 January 2004 5-1

Maintenance 523-0806452

Table 5-1. Self-Test Pass/Fail Indication

SELF TESTRESULTS FCS WARN INDICATED ALTITUDE

Pass No Warn 50 feet

Fail Warn 2600 feet for 10 seconds followed by an indicated altitude that represents thedetected fault or faults. See Table 5-2 for descriptions of each of these faults.

Table 5-2. Reported Fault Definitions

OUTPUTVOLTAGE(P1–57/59)

INDICATEDALTITUDE

FAULTREPORTED

ALT-1000 antenna monitoring function enabled (P1-21 ground) with ANT-52 antenna

+2.4 V dc+4.4 V dc+6.4 V dc+8.4 V dc+10.4 V dc+10.7 V dc+11.0 V dc+11.3 V dc+11.6 V dc+11.9 V dc+12.2 V dc+12.5 V dc+12.8 V dc+13.1 V dc+13.4 V dc

100 feet200 feet300 feet400 feet500 feet600 feet700 feet800 feet900 feet1000 feet1100 feet1200 feet1300 feet1400 feet1500 feet

Antenna FaultPower Supply FaultAntenna Fault + Power Supply FaultInvalid StrapAntenna Fault + Invalid StrapPower Supply Fault + Invalid StrapAntenna Fault + Power Supply Fault + Invalid StrapInternal FaultAntenna Fault + Internal FaultPower Supply Fault + Internal FaultAntenna Fault + Power Supply Fault + Internal FaultInvalid Strap + Internal FaultAntenna Fault + Invalid Strap + Internal FaultPower Supply Fault + Invalid Strap + Internal FaultAntenna Fault + Power Supply Fault + Invalid Strap + Internal Fault

ALT-1000 antenna monitoring function left disabled (P1-21 open)

+4.4 V dc+8.4 V dc+10.7 V dc+11.3 V dc+11.9 V dc+12.5 V dc+13.1 V dc

200 feet400 feet600 feet800 feet1000 feet1200 feet1400 feet

Power Supply FaultInvalid StrapPower Supply Fault + Invalid StrapInternal FaultPower Supply Fault + Internal FaultInvalid Strap + Internal FaultPower Supply Fault + Invalid Strap + Internal Fault

NOTEThe output voltages and indicated altitude readings shown in bold represent the four basic monitored functions de-scribed below:

• TheAntenna Faultmonitoring function only exists when the ANTMON ENABLE discrete pin (P1-21) is groundedand the antennas are ANT-52’s.

• The Power Supply Fault monitoring detects an out of tolerance voltage level from the power supply.• The Invalid Strapmonitoring detects an invalid strap configuration with either the Aircraft Installation Delay (AID)or the Modulation Frequency strapping.

• The Internal Fault monitoring detects an internal failure.

5-2 29 January 2004


5.4.3 Digital Diagnostic Information The ALT-1000 must be in the shop mode of operation in order to receive the digitalARINC output information from the BITE connector TX A/B output pins (P12-2/3). To receive the ARINC output information,external test equipment must be connected to the BITE RXA/B input pins (P12-4/5). In order for this function to work, a jumpermust also be connected between the BITE connector pins WRAP AROUND OUT (P12-8) and WRAP AROUND IN (P12-10).Refer to the BITE software instructions to access the diagnostic information of the ALT-1000.

Refer to Tables 5-3, 5-4, and 5-5 for descriptions of the ALT-1000 diagnostic codes and to Table 5-5 for the recommendedtroubleshooting procedures. Due to the amount of very high integration ICs used in the ALT-1000, the failure of a single partmay produce more than one diagnostic code value. For example: the EEPROM could have input/output errors (codes 36-38)or internal data corruption (codes 53-61).

NOTEThe ALT-1000 must be in shop mode in order to receive ARINC outputs through the BITE connector. Toreceive the ARINC outputs, connect the external test equipment to the BITE connector and send a 227 wordwith a command of 20.

29 January 2004 5-3


Table 5-3. ARINC 429 Data Bus Word 270 Definitions

BIT Definition

12

Octal 2:10

345

Octal 7:111

678

Octal 0:000

910

Source/Destination Identifier (Bit 10 is MSB and Bit 9 is LSB):Bit 10 = 0 and Bit 9 = 0 for Not UsedBit 10 = 0 and Bit 9 = 1 for Left Unit (Modulation strapped for 50 Hz)Bit 10 = 1 and Bit 9 = 0 for Right Unit (Modulation strapped for 51 Hz)Bit 10 = 1 and Bit 9 = 1 for Not Used

11 Reserved

12 Reserved

13 0 = AID 20 Foot Strap Input Grounded, 1 = AID 20 Foot Strap Input Open.



16 Reserved

17 0 = Antenna Monitor Disabled, 1 = Antenna Monitor Enabled.

18 0 = FCS No Warn, 1 = FCS Warn

19 Reserved

20 0 = Altitude Trip #1 Untripped, 1 = Altitude Trip #1 Tripped.




24 0 = BITE connector not installed, 1 = BITE connector installed.

25 0 = BITE mode disabled, 1 = BITE mode enabled.

26 0 = In Aircraft Test mode disabled, 1 = In Aircraft Test mode enabled.

27 0 = Maintenance strap disabled, 1 = Maintenance strap enabled.

28 Reserved

29 Reserved

5-4 29 January 2004


Table 5-3. ARINC 429 Data Bus Word 270 Definitions - Continued

BIT Definition

3031

Sign/Status Matrix (Bit 31 is MSB and Bit 30 is LSB:Bit 31 = 0 and Bit 30 = 0 for Failure WarningBit 31 = 0 and Bit 30 = 1 for No Computed DataBit 31 = 1 and Bit 30 = 0 for Functional TestBit 31 = 1 and Bit 30 = 1 for Normal Operation

32 Parity Bit (UART sets for odd parity).

29 January 2004 5-5


Table 5-4. ARINC 429 Data Bus Word 350 Definitions

BIT Definition

12

Octal 3:11

345

Octal 5: 1011

678

Octal 0:000

910

Source/Destination Identifier - (Bit 10 is MSB and Bit 9 is LSB):Bit 10 = 0 and Bit 9 = 0 for Not UsedBit 10 = 0 and Bit 9 = 1 for Left Unit (Modulation strapped for 50 Hz)Bit 10 = 1 and Bit 9 = 0 for Right Unit (Modulation strapped for 51 Hz)Bit 10 = 1 and Bit 9 = 1 for Not Used

11 0 = Altimeter OK, 1 = Altimeter Error.

12 0 = RAM OK, 1 = RAM Error.

13 0 = ROM OK, 1 = ROM Error.

14 Reserved

15 Reserved

16 Reserved

17 Fault code, See Table 5-5 for description.








25 Reserved

26 Reserved

27 0 = Maintenance log not full, 1 = Maintenance log full.

28 0 = Maintenance log has no data, 1 = Maintenance log has data.

29 Reserved

5-6 29 January 2004


Table 5-4. ARINC 429 Data Bus Word 350 Definitions - Continued

BIT Definition

3031

Sign/Status Matrix - (Bit 31 is MSB and Bit 30 is LSB):Bit 31 = 0 and Bit 30 = 0 for Failure WarningBit 31 = 0 and Bit 30 = 1 for No Computed DataBit 31 = 1 and Bit 30 = 0 for Functional TestBit 31 = 1 and Bit 30 = 1 for Normal Operation

32 Parity Bit (UART sets for odd parity).

29 January 2004 5-7


Table 5-5. Diagnostic Codes

CODE HEX DESCRIPTION TROUBLESHOOTING PROCEDURES

00 00 No fault found No troubleshooting required, test passed.

01 - 20 01 - 14 Reserved These diagnostic codes are reserved as spares forfuture use.

21 15 ARINC-429 RX no data

22 16 ARINC-429 received parity error

23 17 ARINC-429 transmitter not ready

Indicates a problem with the FGPA on the digitalcircuit card.

24 18 Altitude counter altitude data not ready

25 19 Altitude counter beat frequency hardwareoverflow

26 1A Altitude counter frequency range

27 1B Altitude counter interval error

28 1C Altitude counter missing pulse limit

Indicates a problem with the digital circuit card.

29 1D Analog output error

30 1E Reserved

31 1F Reserved

32 20 Reserved

Indicates a problem with the analog output.

33 21 Antenna TX disconnected

34 22 Antenna RX disconnected

35 23 Antenna TX and RX disconnected

Antenna monitoring must be enabled by turningon the ANT MON switch on the test fixture orconnecting P1-21 to ground. Check antenna,antenna cable, and antenna connections.

36 24 EEPROM no acknowledge data

37 25 EEPROM no acknowledge slave address

38 26 EEPROM no acknowledge word address

Indicates the EEPROM is not following the datatransfer protocol properly.

39 27 Modulator deviation control limit

40 28 Modulator center control limit

41 29 Modulator period error

42 2A Modulator linearity error

43 2B Modulator clock stopped

44 2C Modulator slope error

45 2D Modulator pulse width error

46 2E Modulator center error

47 2F Modulator monitor clear error

48 30 Modulator pulse missing error

Indicates the modulator is not working properly.

49 31 State machine sequence error

50 32 State machine interval error

51 33 State machine results error

52 34 State machine initial error

Indicates the internal state machine is not workingproperly.

5-8 29 January 2004


Table 5-5. Diagnostic Codes - Continued

CODE HEX DESCRIPTION TROUBLESHOOTING PROCEDURES

53 35 NVM header record checksum error

54 36 NVM maintenance record checksum error

55 37 NVM power cycle record checksum error

56 38 NVM trips checksum error

57 39 NVM trips backup checksum error

58 3A NVM calibration checksum error

59 3B NVM calibration backup checksum error

60 3C NVM reserved checksum error

61 3D NVM fault record checksum error

These codes indicate the EEPROM containscorrupted data.

62 3E Soft reset watchdog armed 63 3F strapAID complement

63 3F Strap AID complement Indicates a FGPA problem on the digital circuitcard.

64 40 Strap AID select invalid Indicates the AID strapping and parity are notcorrect. There must be an odd number of groundstraps connected to P1-22, P1-24. P1-27, andP1-37.

65 41 Reserved

66 42 Strap modulation frequency complement Indicates a FGPA problem on the digital circuitcard.

67 43 Strap modulation frequency select invalid Indicates more than one ground strap is connectedto ALT-1000 P1-38, P1-40, or P1-47; or that noneof the three pins are grounded. Only one pin maybe grounded to select the modulation frequency.

68 44 Voltages -15/+12 high

69 45 Voltages -15/+12 low

70 46 Voltages -5/+12 high

71 47 Voltages -5/+12 low

72 48 Voltages +22 high

73 49 Voltages +22 low

74 4A Voltages +30 high

75 4B Voltages +30 low

76 4C Voltages half full scale low

77 4D Voltages half full scale high

78 4E Voltages ground high

79 4F Voltages full scale low

Indicates a power supply problem.

29 January 2004 5-9/(5-10 Blank)

523-00806452-001116 1st Edition, 29 January 2004


Service Bulletins and Service Information Letters (Refer to latest edition/addendum of the Business and Regional Systems Equipment Service Bulletin/Information Letter Index 523-0766944 for up-to-date listing.)

SB/SIL Number Unit Title Date

Page No Issue

Title ............................................29 Jan 04 List of Effective Pages ...............29 Jan 04

Record of Revisions

RETAIN THIS RECORD IN THE FRONT OF THE MANUAL. ON RECEIPT OF REVISIONS, INSERT REVISED PAGES IN THE MANUAL, AND ENTER DATE INSERTED AND INITIALS.

REV NO

REVISION DATE

INSERTION DATE/BY

SB NUMBER INCLUDED

REV NO

REVISION DATE

INSERTION DATE/BY

SB NUMBER INCLUDED

1st Ed 29 Jan 04

List of Effective Pages *The asterisk indicates pages changed, added, or deleted by the current change.

523-0806452 © 2012, Rockwell Collins All Rights Reserved, Printed in USA

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