FA2100 CVR Install Rev 16

Aviation Recorders P.O. Box 3041 Sarasota, Florida 34230 CAGE Code 06141

INSTALLATION & OPERATION INSTRUCTION MANUAL MODEL FA2100CVR COCKPIT VOICE RECORDER 1/2-ATR SHORT CASE (SUPERSEDES FAR 08337220) RECORDER PART NUMBERS:

Rev. 16 June 13/12

2100–1010–00 2100–1020–00 2100–1020–02 2100–1020–90 2100–1025–02 2100–1025–12 2100–1025–22 2100−1025−24 2100–1026–02 2100−1027−02

CONTROL UNIT MODEL NUMBERS: S151 S152 S251 A151B

S161 S162 S261 A152B

MICROPHONE PREAMPLIFIER MODULE MODEL NUMBERS:

S150 A150

S160

REMOTE MICROPHONE MODEL NUMBERS:

S055 A55B

S056

Manufactured in Accordance with FAA TSO–C123a FAA TSO−C123b EUROCAE ED–56A EUROCAE ED–112 ARINC 757

P/N: 165E1846−00

Installation & Operation Instruction Manual

Model FA2100CVR

Part Number 165E1846−00 Rev. 16 June 13/12

EXPORT CONTROL STATEMENT SSCVR TECHNOLOGY / DATA: “This Solid State Fight Data/Cockpit Voice Recorder Technical Data is being exported from the United States in accordance with the Export Administration Regulations (ECCN #7E994), No License Required (NLR). Diversion contrary to U.S. law is prohibited. In accordance with U.S. Law (Title 15 CFR Part 746 and Supplement No. 1 to Part 774; and Title 31 CFR) resale/reexport or transfer to certain designated countries is prohibited without the prior written consent of the U.S. Department of Commerce.”

HTSUS/Schedule B: 4901.10.0040 This manual contains date sensitive information. To verify the latest revision level of this manual, visit our document download site at http://www.L−3ar.net.

ECopyright 2012 by L-3 Communications Corporation Aviation Recorders All rights reserved. No part of this manual may be reproduced or utilized in any form or by any means, electronic or mechanical, including photocopying, recording, or by information storage and retrieval system, without permission in writing. Inquiries should be addressed to: L-3 Communications Corporation Aviation Recorders Technical Publications P. O. Box 3041 Sarasota, Florida 34230 (941) 371–0811 FAX: (941) 377–5591 CAGE Code 06141

Page ii

Rev. 16

Installation & Operation Instruction Manual

Model FA2100CVR

IMPORTANT CAUTIONS Installing ARINC 757A type CVR recorders connection wiring: Damage will occur if power is applied on 2100−1027−02 recorder only if the interconnect wiring are not to ARINC 757A requirements. This is because of the power pins are different in the ARINC 757A from the ARINC 757. The mating keys on the connector are rotated different (Refer to Figure 5, sheet 2 of 2 of this manual) as a safe guard to prevent mating a ARINC 757 type recorder. Do not remove or rotate the keys.

Rev. 16

165E1846-00 Page iii

Installation & Operation Instruction Manual

Model FA2100CVR

THE CONTENTS OF THE EQUIPMENT CAN BE DAMAGED BY STATIC ELECTRICITY.PROPER HANDLING IS REQUIRED.

GENERAL This product and related documentation must be reviewed for familiarization with safety markings and instructions before operation. This instrument was constructed in an ESD (electrostatic discharge) protected environment. This is because most of the semiconductor devices used in this instrument are susceptible to damage by static discharge. Depending on the magnitude of the charge, device substrates can be punctured or destroyed by contact or the mere proximity of a static charge. The results can cause degradation of device performance, early failure, or immediate destruction. These charges are generated in numerous ways such as simple contact, separation of materials, and normal motions of persons working with static sensitive devices. When handling or servicing equipment containing static sensitive devices, adequate precautions must be taken to prevent device damage or destruction. Only personnel who are thoroughly familiar with industry-accepted techniques for handling static sensitive devices should attempt to service circuitry with these devices. In all instances, measures must be taken to prevent static charge build-up on work surfaces and persons handling the devices.

BEFORE APPLYING POWER Verify that the product is set to match the line voltage and that the correct fuses are installed. Servicing instructions are for use by service-trained personnel only. To avoid dangerous electric shock, do not perform any servicing unless qualified to do so. Adjustments described in the manual are performed with power supplied to the instrument while protective covers are removed. Energy available at many points may, if contacted, result in personal injury.

165E1846-00 Page iv

Rev. 16

Installation & Operation Instruction Manual

Model FA2100CVR

RECORD OF CHANGES

ISSUE

REVISION

DATE OF CHANGE

COMMENTS

Initial

—

Mar. 15/99

Initial issue of Installation & Operation Instruction Manual. Supersedes FAR 08337220 Rev. Preliminary & FAR 08337220 Rev. Preliminary 01.

01

Feb. 01/00

Specified that this manual is not intended for GACVRs. Updated maximum power requirements as per the latest revision of the drawings. Consolidated the Appendixes.

02

May 01/00

Added 2100−1020−93 configuration and S160, S161, and S161 Control Units.

03

Oct. 01/00

Added 2100−1020−90 and S056 Microphone.

04

Mar. 01/01

Clarified when the Audio System Check is re­ quired.

05

Aug. 15/01

Fixed Control Unit drawings to separate the S151 drawing from the S161 drawing, and the S152 drawing from the S162 drawing in Appen­ dix A. Clarified GMT/FSK operation for -02 configurations.

06

Jan. 20/02

Corrected S261 Control Unit Wire Diagram in Appendix A to show 37 pin connector vs 41 pin connector interface. Added S056 Mic Spec

07

Jan. 01/03

Updated Control Unit information. Changed recommended microphone cabling.

08

Oct. 15/04

Updated S055 connector information. Added new Control Units and associated data. In­ cluded p/n: 2100-1025-02 to the manual.

09

May. 01/07

Revised Export Control Statement IAW CTR 760, Rev. R. Added new “EUROCAE ED-112” specification. Included new p/ns: 2100-1025-12 -22, S161-0090-20, S161-1390-01 & S056-0048-15 to the manu­ al. Revised text for Pre and Post MOD−DOT #7 configurations of P/N 2100−1020−( ). Revised outlines of the S056 microphones.

10

Mar. 31/08

Revised section 3.0

11

Dec. 01.08

Revised Export Control Statement IAW CTR 760, Rev. V. Included new p/ns: 2100-1026-02 and S261-1122-00. Added maintenance pro­ cedure to download data from CVR using the new 17TES0048 cable.

Rev. 16

165E1846-00 Page v

Installation & Operation Instruction Manual

Model FA2100CVR

RECORD OF CHANGES (Continued)

ISSUE

165E1846-00 Page vi

REVISION

DATE OF CHANGE

COMMENTS

12

Mar. 31/09

Added 2100-1025-22 EQF. Changed L-3AR address to 100 Cattleman Road.

13

Jul. 30/09

Correct pin call out under Notes for number 14 for figure A-5, A-9, A-13.

14

Mar. 31/10

Added FAA TSO-C123b and 2100-1025-22 EQF. Added OMS and Datalink data. Deleted FAA Action Notice A8300.56 in all figure notes in Appendix A.

15

Feb. 24/12

New: CAUTION for 757A type recorders inter­ connect wiring. Added new part numbers: 2100-1025-24 and 2100-1027-02.

16

June 13/12

Updated Tables 4, 5, and 6.

Rev. 16

Model FA2100CVR

Installation & Operation Instruction Manual

TABLE OF CONTENTS Section 1.0

Page INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 1.1

Purpose of Manual . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

1.2

Equipment and Document Requirements . . . . . . . . . . . . . . . . . . . . . . . 1

1.3

System Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2

1.4

System Overview . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 1.4.1 Recorder Unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3

1.5

Onboard Maintenance System Interface . . . . . . . . . . . . . . . . . . . . . . . . 5 1.5.1 Label 350 Status Word Output . . . . . . . . . . . . . . . . . . . . . . . . . 6 1.5.2 Label 354 LRU Identification Output . . . . . . . . . . . . . . . . . . . . 9 1.5.3 Label 377 ARINC 429 Equipment Identification Word Output 12

1.6

1.5.4 OMS Input . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 CVR DATALINK INPUT INTERFACE . . . . . . . . . . . . . . . . . . . . . . 12 1.6.1 Data Link Input and Encapsulation . . . . . . . . . . . . . . . . . . . . . 13 1.6.2 DataLink Heartbeat . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 1.6.3 Williamsburg Bit−Oriented Protocol Version Support . . . . . . 15 1.6.4 DataLink Memory Capacity . . . . . . . . . . . . . . . . . . . . . . . . . . 15 1.6.5 DataLink Retrieval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 1.6.6 Control Units and External Preamplifier . . . . . . . . . . . . . . . . . 17 1.6.7 Remote Microphone Module . . . . . . . . . . . . . . . . . . . . . . . . . . 18 1.6.8 CVR Mounting Racks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

1.7 2.0

3.0

Rev. 16

Abbreviations and Acronyms . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

EQUIPMENT LIMITATIONS/SPECIFICATIONS . . . . . . . . . . . . . . . . . . . . 19 2.1

Applicable Documents . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

2.2

Physical Characteristics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

2.3

Electrical Characteristics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

2.4

Environmental Characteristics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

2.5

Crash- and Fire-Survival Characteristics . . . . . . . . . . . . . . . . . . . . . . 25

INSTALLATION PROCEDURES AND LIMITATIONS . . . . . . . . . . . . . . . 25 3.1

Installation Precautions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

3.2

General Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

3.3

Installation Acceptance by Field Approval Method . . . . . . . . . . . . . . 26 165E1846-00 Page vii

Installation & Operation Instruction Manual

Model FA2100CVR

3.4

Recorder Location . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

3.5

Mounting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

3.6

Power Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

3.7

Wiring Connections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

3.8

Audio System Interface . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

3.9

Microphone Installation Criteria . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

3.10 Cessation of Recording . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 4.0

POST-INSTALLATION CHECKOUT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

5.0

OPERATIONAL TESTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 5.1

Preflight Functional Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

5.2

Complete Audio System Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

5.3

Flight Checkout Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

6.0

FA2100CVR READOUT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

7.0

OPERATING INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

8.0

FLIGHT CHECKOUT PROCEDURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

9.0

8.1

Operational Notes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

8.2

Flight Checkout . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

MAINTENANCE AND CALIBRATION . . . . . . . . . . . . . . . . . . . . . . . . . . . 36 9.1

Recorder . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36

9.2

Data Download Using P/N: 17TES0078 Cable . . . . . . . . . . . . . . . . . 36

9.3

Underwater Locator Device . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38

9.4

Product Support . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39

9.5

Authorized Repair Facilities . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39

9.6

Loaner/Rental Program . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39

Appendixes A − OUTLINE & DIMENSIONS MICROPHONES, CONTROL UNITS, & EXTERNAL PREAMPLIFIERS . . . . . . . . . . . . . . . . . . . . . . . . A−1 A − OUTLINE & DIMENSIONS MICROPHONES, CONTROL UNITS, & EXTERNAL PREAMPLIFIERS . . . . . . . . . . . . . . . . . . . . . . . . A−1 B − ENVIRONMENTAL QUALIFICATION FORMS (EQFs) ED–56A AND RTCA/DO–160C . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . B−1 C − ACCESSORY EQUIPMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . C−1 D − ABBREVIATIONS AND ACRONYMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . D−1 165E1846-00 Page viii

Rev. 16

Model FA2100CVR

Installation & Operation Instruction Manual

List of Illustrations Figure

Page

Figure 1. Model FA2100CVR Cockpit Voice Recorder . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 Figure 2. Functional System Block Diagram Model FA2100CVR Cockpit Voice Recorder . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 Figure 3. Generic DataLink Message Encapsulation Structure . . . . . . . . . . . . . . . . . . . . . . . . . . 14 Figure 4. Functional System Block Diagram Model FA2100CVR Cockpit Voice Recorder . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 Figure 5. Outline and Dimensions FA2100CVR Cockpit Voice Recorder, PN 2100–1010–( ) & PN 2100–102X–( ) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 Figure 6. Outline and Dimensions, CVR Mount, Part Number 178E0919-00 . . . . . . . . . . . . . 24 Figure 7. Recommended Cockpit Area Microphone Mounting Location . . . . . . . . . . . . . . . . . . 29 Figure 8. On‐Aircraft Setup for Checking Out FA2100CVRs using a Portable Interface . . . . . 32 Figure 9. On‐Aircraft Setup for Data Download FA2100CVRs using a Portable Interface . . . 38 Figure A-1. Part Number Definition, Model S151/S161, Model S152/S162, and Model S251/S261 Control Units . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A-3 Figure A-2. Outline and Dimensions, Model S151 Control Unit . . . . . . . . . . . . . . . . . . . . . . A-5 Figure A-3. Interwiring Diagram, Voice Recorder Unit, S151 Control Unit, S055 Remote Microphone . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A-6 Figure A-4. Outline and Dimensions, Model S161 Control Unit . . . . . . . . . . . . . . . . . . . . . . A-8 Figure A-5. Interwiring Diagram, Voice Recorder Unit, S161 Control Unit, S056 Remote Microphone . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A-10 Figure A-6. Interwiring Diagram, Voice Recorder Unit, S161 Control Unit, S056 Remote Microphone . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A-12 Figure A-7. Outline and Dimensions, Model S251 Control Unit . . . . . . . . . . . . . . . . . . . . . A-14 Figure A-8. Interwiring Diagram, Voice Recorder Unit, S251 Control Unit, S055 Remote Microphone . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A-15 Figure A-9. Outline and Dimensions, Model S261 Control Unit . . . . . . . . . . . . . . . . . . . . . A-17 Rev. 16

165E1846-00 Page ix

Installation & Operation Instruction Manual

Model FA2100CVR

List of Illustrations (Continued) Figure

Page

Figure A-10. Interwiring Diagram, Voice Recorder Unit, S261 Control Unit, S056 Remote Microphone . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A-18 Figure A-11. Interwiring Diagram, Voice Recorder Unit, S261 Control Unit, S056 Remote Microphone . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A-20 Figure A-12. Outline and Dimensions, Model S152 Control Unit . . . . . . . . . . . . . . . . . . . . A-22 Figure A-13. Outline and Dimensions, Model S162 Control Unit . . . . . . . . . . . . . . . . . . . . A-23 Figure A-14. Interwiring Diagram, Voice Recorder Unit, S152/S162 Control Unit with Internal Microphone . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A-24 Figure A-15. Interwiring Diagram, P/N: 2100-1026-02 Cockpit Voice Recorder with RIPS, Customer Furnished Control Unit and Microphone . . . . . . . . . A-26 Figure A-16. Interwiring Diagram, Cockpit Voice Recorder Unit S161 Control Unit and S056 Microphone For Airbus A350 Aircraft . . . . . . . A-28 Figure A-17. Outline and Dimensions, Model S150 External Preamplifier Module . . . . . A-30 Figure A-18. Interwiring Diagram, Voice Recorder Unit, S150 External Preamplifier, S055 Remote Microphone . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A-31 Figure A-19. Outline and Dimensions, Model S160 External Preamplifier Module . . . . . A-33 Figure A-20. Interwiring Diagram, Voice Recorder Unit, S160 External Preamplifier, S056 Remote Microphone . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A-34 Figure A-21. Outline and Dimensions, Model S055 Surface‐Mount Microphone Module . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A-36 Figure A-22. Outline and Dimensions, Model S055 Panel‐Mount Microphone Module . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A-37 Figure A-23. Outline and Dimensions, Model S056 Surface‐Mount Microphone Module . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A-38 Figure A-24. Outline and Dimensions, Model S056 Panel‐Mount Microphone Module - Small . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A-40 Figure A-25. Outline and Dimensions, Model S056 Panel‐Mount Microphone Module - Large . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A-41 165E1846-00 Page x

Rev. 16

Model FA2100CVR

Installation & Operation Instruction Manual

List of Illustrations (Continued) Figure

Page

Figure A-26. Model S055 Microphone Element Specifications and Response Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A-42 Figure A-27. Model S056 Microphone Element Specifications and Response Diagram . . A-43 Figure A-28. Outline and Dimensions, Model A151B Control Unit Does Not Comply with ED-56A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A-44 Figure A-29. Interwiring Diagram, Voice Recorder Unit, A151B Control Unit, A55B Remote Microphone Does Not Comply with ED-56A . . . . . . . . . . . . A-45 Figure A-30. Outline and Dimensions, Model A152B Control Unit Does Not Comply with ED-56A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A-47 Figure A-31. Interwiring Diagram, Voice Recorder Unit, A152B Control Unit with Internal Microphone Does Not Comply with ED-56A . . . . . . . . . . . . . . . . . . . . . . . . A-48 Figure A-32. Outline and Dimensions, Model A150 External Preamplifier Module Does Not Comply with ED-56A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A-50 Figure A-33. Interwiring Diagram, Voice Recorder Unit, A150 External Preamplifier, A55B Remote Microphone Does Not Comply with ED-56A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A-51 Figure A-34. Outline and Dimensions, Model A55B Surface‐Mount Microphone Module, Directional Microphone Does Not Comply with ED-56A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A-53 Figure A-35. Outline and Dimensions, Model A55B Surface‐Mount Microphone Module, Mini‐Condenser Microphone Does Not Comply with ED-56A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A-54 Figure A-36. Outline and Dimensions, Model A55B Panel‐Mount Microphone Module, Rear Connector Does Not Comply with ED-56A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A-55 Figure A-37.Outline and Dimensions, Model A55B Panel‐Mount Microphone Module, Top Connector Does Not Comply with ED-56A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A-56

Rev. 16

165E1846-00 Page xi

Installation & Operation Instruction Manual

Model FA2100CVR

List of Tables Table

Page

Table 1. FA2100CVR Descriptions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 Table 2. CVR OMS Output Words . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 Table 3. CVR Pins Assigned to RIPS Status Monitoring . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 Table 4. CVR Label 350 Output format . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 Table 5. CVR Fault Reporting Interactions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 Table 6. CVR Status Word Fault Reporting Criteria . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8 Table 7. Model FA2100CVR Recording Specifications . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

165E1846-00 Page xii

Rev. 16

Installation & Operation Instruction Manual

Model FA2100CVR

1.0

INTRODUCTION

1.1

Purpose of Manual

This Installation and Operation Instruction Manual applies to the following Model FA2100CVR Cockpit Voice Recorders: 2100−1010−00

2100−1020−90

2100−1020−00

2100−1020−02

2100−1025−02

2100−1025−12

2100−1025−22

2100−1025−24

2100−1026−02

2100−1027−02

In this manual, these recorders are referred to as FA2100CVR, or CVR’s. Refer to FA2100GACVR Installation Manual (p/n: 165E1848−00) for the installation of the FA2100 General Aviation Cockpit Voice Recorders. This manual contains date sensitive information necessary to install these CVRs in the aircraft, to operate them, and to verify that the installed units are operating properly. This manual also describes the features and functions of the FA2100CVR System and associated accessories. Note:

Contact L-3 Communications, Aviation Recorders, to verify this date sensitive information when using this manual to develop other documentation. The L−3AR Publication index may be located at www.L−3.com or L−3ar.net.

Comments or recommendations about the installation, operation, and check out of the FA2100CVR should be sent to L-3 Communications, Aviation Recorders, Product Support Department, at the address shown in section 9.4.

1.2

Equipment and Document Requirements

The following equipment and documents are, or may be, required for on-aircraft installation and check out of the FA2100CVRs: S

This Installation & Operation Instruction Manual.

S

Portable Interface (PI), Part Number 17TES0043 (includes PI Memory Card Module, Part Number 17TES0054; PI Audio Readout Cable, Part Number 17TES0051; and PI Auxiliary Readout Cable, Part Number 17TES0052).

S

Portable Interface Operator’s Manual, Part Number 165E1630–00

S

Cockpit Voice Recorder System Test Panel, Part Number 9300A860; and Cable Assembly, Part Number 024E1122–00 (for FA2100CVR Readout, see paragraph 6.0). Instead of the Test Panel, the PI and a customer-fabricated cable to provide power to the FA2100CVR’s main (rear) connector can be used.

S

Ultrasonic Test Set (Underwater Locator Device (ULD) Tester), Part Number 15977 (if functional testing of ULD is required).

S

Component Maintenance Manual, Cockpit Voice Recorder, Model FA2100CVR, ATA 23–70–04, Part Number 165E1689-00.

Rev. 16

165E1846-00 Page 1

Installation & Operation Instruction Manual

1.3

Model FA2100CVR

S

Component Maintenance Manual, ED−56A Control Units & Microphones, ATA 23–70–05, Part Number 165E1747-00.

S

FA2100CVR Audio & Data Link Player Software Operator’s Manual, Part Number 165E3596−00.

S

Installation & Operation Instruction Manual for Recorder Independent Power Supply (RIPS), Part Number 165E4900−00. System Description

The FA2100CVR Systems meet or exceed the requirements of Federal Aviation Administration (FAA) Technical Standard Order TSO–C123a/C123b*, Cockpit Voice Recorder Systems; European Organization for Civilian Aviation Equipment (EUROCAE) Minimum Operational Performance Specification (MOPS) ED–56A, Cockpit Voice Recorder System and ED−112, Crash Protected Airborne Recorder Systems; and ARINC Characteristic 757 and 757A(P/N: 2100−1027−02 only), Aeronautical Radio, Inc., Cockpit Voice Recorder (CVR). The FA2100CVRs may also be used to replace existing ARINC Characteristic 557 installations. The FA2100CVR System consists of the Recorder Unit, the Control Unit, a Preamplifier Module for installations that do not require a Control Unit, an Area Microphone, and a Mounting Tray. Interconnection between the recorder and control unit or external preamplifier is accomplished using aircraft wiring.

1.4

System Overview

Table 1 contains a summary description of the FA2100CVRs covered in this manual.

Table 1. FA2100CVR Descriptions Part Number

Description

Weight ( 0.5 lbs.)

2100–1010–00

ARINC 404A 1/2-ATR Short Case; ARINC 757, 30 Minutes

10.0 lbs.

2100–1020–00

ARINC 404A 1/2-ATR Short Case; ARINC 757, 120 Minutes

10.0 lbs.

2100–1020–02

ARINC 404A 1/2-ATR Short Case; ARINC 757, 120 Minutes w/FSK

10.0 lbs.

2100–1020–90

ARINC 404A 1/2-ATR Short Case; ARINC 757, 120 Minutes, Military

10.0 lbs.

2100–1025–02

ARINC 404A 1/2-ATR Short Case; ARINC 757, 120 Minutes w/OMS and Data Link.

10.0 lbs.

2100–1025–12

ARINC 404A 1/2-ATR Short Case; ARINC 757, 120 Minutes w/OMS and Data Link. CYRILLIC (Russian Text)

10.0 lbs.

*2100–1025–22

ARINC 404A 1/2-ATR Short Case; ARINC 757, 120 Minutes w/OMS and Data Link and RIPS status monitoring.

10.0 lbs.

*2100–1025–24

ARINC 404A 1/2-ATR Short Case; ARINC 757, 120 Minutes w/OMS and Data Link and RIPS status monitoring.

10.0 lbs.

2100–1026−02

ARINC 404A 1/2-ATR Short Case; ARINC 757, 120 Minutes w/OMS, Data Link and RIPS status monitoring .

10.0 lbs.

*2100–1027−02

ARINC 404A 1/2-ATR Short Case; ARINC 757A, 120 Minutes w/OMS, Data Link and RIPS status monitoring .

10.0 lbs.

*NOTE: Meets or exceeds FAA TSO−C123b 165E1846-00 Page 2

Rev. 16

Installation & Operation Instruction Manual

Model FA2100CVR

1.4.1 Recorder Unit The FA2100CVRs are housed in ARINC 404A, 1/2-ATR short cases (refer to Figure 1). The chassis and Crash Survivable Memory Unit (CSMU) are painted international orange. Two reflective stripes are located on the CSMU. The FA2100CVR consists of a chassis and front panel, three Printed Wiring Assemblies (Aircraft Interface PWA, Audio Compressor PWA, and Acquisition Processor PWA), and the Crash Survivable Memory Unit (CSMU). The CSMU contains the solid state flash memory used as the recording medium. An Underwater Locator Device (ULD), also referred to as an underwater acoustic beacon, is mounted horizontally on the front of the CSMU and is also used as a the recorder’s carrying handle. The ULD is equipped with a battery that has an expected life of more then six years. The ULD meets or exceeds the requirements of FAA TSO–C121. The Ground Support Equipment (GSE) connector is located on the front of the FA2100CVR. This connector provides the interface from the recorder to GSE for checkout of the recorder, or to transfer data to a readout device. The FA2100CVR is connected to aircraft wiring via a 57-pin, DPXB-style connector. HARDWARE AND SOFTWARE MODIFICATIONS CSMU

ULD

GSE CONNECTOR (BEHIND DUST COVER)

Figure 1. Model FA2100CVR Cockpit Voice Recorder Refer to Figure 4 for this discussion. The FA2100CVR is a Line Replaceable Unit (LRU) that simultaneously records four separate channels of cockpit audio, converts the audio to a digital format, and stores the data in a solid state memory. The following are the four cockpit audio inputs: Channel 1: Channel 2: Channel 3: Channel 4: Rev. 16

Cockpit Spare Audio Input (3rd Crew Member, Public Address System) Co-Pilot’s Audio, Boom, Mask, and Hand-Held Microphone Input Pilot’s Audio, Boom, Mask and Hand-Held Microphone Input Cockpit Area Microphone (CAM) Input 165E1846-00 Page 3

Installation & Operation Instruction Manual

Model FA2100CVR

COCKPIT AREA MICROPHONE (CAM)

*

MONITOR AUDIO TO HEADSET JACK

ERASE A

ERASE C

CONTROL UNIT

AIRCRAFT WIRING INTERLOCKS (LANDING GEAR MUST BE DOWN AND BRAKE LOCKED TO ALLOW MEMORY TO BE ERASED)

PUSH TO TEST

GEAR

AREA MICROPHONE

BRAKE +18 VDC OPERATING POWER

28 VDC OR 115 VAC 400 Hz

2

RECORD ON +5 V FOR LIGHTED PANEL

CHANNEL 4 2 CHANNEL 3

PILOT AUDIO

FA2100 CVR

2

2 CHANNEL 2

CO‐PILOT AUDIO

+18 VDC

2

SPARE AUDIO (TO 3RD CREW MEMBER OR PA SYSTEM)

2

CHANNEL 1

TEST INDICATOR

2

2

GMT_IN_B (429) GMT_IN_A (429) ROTOR_SPEED_IN_HI ROTOR_SPEED_IN_LO **OMS IN A **OMS IN B

AIRCRAFT INTERFACE PWA

***RIPS FAULT INPUT ***RIPS MAINTENANCE INPUT ***RIPS PRESENT INPUT STOP RECORDING/ ***RIPS ACTIVE INPUT CHASSIS GROUND

* S055 Mics have 4 Lines to the C.U. S056 MICS have 3 Lines to the C.U. For GA versions refer to Figure 4.

OMS & Data Link are applicable to the 2100-1025-XX & 2100-1026-XX only.

*** RIPS Status Monitoring. 2100-1025-22 &

CVR FAULT

TO AIRCRAFT FAULT MONITORING SYSTEM

**OMS OUTPUT A 429 **OMS OUTPUT B 429

**DATA LINK IN A 429 **DATA LINK IN B 429 **DATA LINK VALID

**

AUDIO OUT

**DATA LINK FAULT

AUDIO COMPRESSOR PWA ACQUISITION PROCESSOR PWA

GSE OUTPUT

TO GROUND STATION TEST EQUIPMENT

CSMU (Crash Survivable Memory Unit) ASSEMBLY (CRASH PROTECTED SOLID STATE MEMORY)

2100-1026-XX only.

Figure 2. Functional System Block Diagram Model FA2100CVR Cockpit Voice Recorder The FA2100CVR is available in two recording configurations: the first records a minimum of 30 minutes of high quality audio, Part Number 2100–1010–( ), The second records a 120 minutes of high quality audio and are Part Number 2100−1025/26/27−( ) and Part Number 2100–1020–( ) MOD−DOT #7. 165E1846-00 Page 4

Rev. 16

Installation & Operation Instruction Manual

Model FA2100CVR

Part Number 2100–1020–( ) pre MOD−DOT #7 records a fifth internal audio stream 30 mins of HQ audio along with 120 mins of standard quality (SQ) audio. This fifth internal audio stream is a standard quality recording of the combination of the Pilot, Co-Pilot, and Public Address or Third Crew Member audio inputs. Part Number 2100−1020−( ) pre MOD−DOT #7 also records a sixth audio stream, a standard quality recording of the Cockpit Area Microphone (CAM) audio input, for a minimum of 120 minutes. (Table 7 illustrates the recording specifications for the cockpit audio input and combined channels.) The audio inputs are conditioned, amplified, and equalized as necessary. The resulting signals are converted to digital pulse code modulation (PCM) data. Part Numbers 2100−1025/26/27−( ) and 2100−1020−( ) MOD−DOT #7 only records a minimum of 120 minutes of high quality recording on all four audio channels. Onboard Maintenance System (OMS) and Data Link are applicable to the 2100−1025−( ) and 2100−1026/27−02 configurations only. The Part Numbers 2100−1025−22/24 and 2100−1026/27−02 have the Onboard Maintenance System (OMS) and Data Link that includes RIPS monitoring status. The FA2100 FA2100CVR can record Greenwich Mean Time (GMT) Time via the ARINC 429 GMT input and can record rotor speed data via the Rotor Speed input. In ARINC 757 installations, the CVR Fault Line provides continuous status of FA2100CVR operation. It may be connected to an annunciator or to an aircraft central maintenance computer. At start−up, the FA2100CVR initiates a Built-in-Test (BIT) and then continuously monitors itself for fault conditions. Previously recorded information cannot be read from the Model FA2100CVR while it is installed in the aircraft. (Refer to paragraph 6.0 for additional information).

1.5

Onboard Maintenance System Interface

The 2100−1025−( ), 2100−1026/27−02 CVR includes an ARINC 429, high speed, Onboard Maintenance System (OMS) output interface (Pins 50/51) and an ARINC 429, low speed, OMS input interface (Pins 39/40). The 2100−1025/26/27−02 CVR supports a comprehensive OMS input/output protocol. Contact L−3AR for further information. The 2100−1025−22/24 supports the OMS interface as defined below. The OMS output interface is used for transmission of CVR status information to a Centralized Maintenance Computer (CMC). The OMS outputs are listed in Table 2.

Table 2. CVR OMS Output Words Label Parameter Format Rate 350 CVR Status Word BNR 1s 354 LRU identification (P/N and S/N) ISO 5 0.5 s 377 ARINC 429 equipment identification BCD 1s The Label 350 status word can be used to supplement or replace the discrete status outputs that are otherwise available from the CVR (e.g. CVR Fault discrete, DataLink Fault Discrete, and Test Good Indicator). The CVR software provides the Label 350 status output word, per ARINC 757, once per second. As an additional capability, this CVR also monitors the status of an attached Recorder Independent Power Supply, if present, and includes that status with the OMS output reporting. The RIPS status is monitored using the CVR input pins listed in Table 3: Rev. 16

165E1846-00 Page 5

Installation & Operation Instruction Manual

Model FA2100CVR

Table 3. CVR Pins Assigned to RIPS Status Monitoring Pin Number 10

RIPS Monitoring Function

State

CVR Stop Recording / RIPS Active

Open = Not Active Closed = RIPS Active or Stop Recording 29 RIPS Fault Open = RIPS Fault Ground = RIPS OK 38 RIPS Maintenance Open = No RIPS Maintenance Needed Ground = RIPS Maintenance Required 42 RIPS Present Pin Program Open = No RIPS Installed Ground = RIPS Present If the RIPS is not present, then the CVR will not monitor the RIPS status inputs, and they will not be reported (default to “0’’ in Label 350 output).

1.5.1 Label 350 Status Word Output The CVR will report status using Label 350 on the OMS ARINC 429 output word as shown in Table 4 below:

Table 4. CVR LABEL 350 OUTPUT FORMAT BIT N° 1­8

FUNCTION Label 350

9­10

SDI

11 12 13 14 15** 16 17 18 19 20** 21 22 26* 27* 23­29

CVR Status (Audio Recording Failure) CMC Bus Status (OMS Input) CVR Control Unit Failure FDR Status (always set to ‘1’) RIPS Fault Status (Pin 29) CVR DataLink Recording Failure Clock Status Data Link Input Interface CVR Record Enable (Pins 7/8) RIPS Maintenance Status (Battery) (Pin 38) RIPS Active Status (Pin 10) RIPS Presence Status (Pin 42) RIPS Maintenance Status (Battery) (Pin 38) RIPS Fault Status (Pin 29) Spare

STATUS 1 2 3 4 5 6 7 8 1 1 1 0 1 0 0 0 10 9 0 0 Normal (CVR1) 0 1 Not used (CVR2) 1 0 Not used 1 1 Not used 0: OK 1 : Failure 0: OK 1 : Failure 0: OK 1 : Failure 0: OK 1 : Failure 0: OK 1 : RIPS Fault 0: OK 1 : Failure 0: OK 1 : Failure 0: OK 1 : Failure 0: OK 1 : Failure (open) 0: No Maint. 1 : Maint. Req. 0: Not Active 1 : RIPS Active 0: Not Pres. 1 : RIPS Present 0: No Maint. 1 : Maint. Req. 0: Fault 1 : No Fault

* Applicable to the Model 2100-1025-24 only. For all other models these pins are designated Spares. ** Not applicable to the Model 2100-1025-24 only. 165E1846-00 Page 6

Rev. 16

Installation & Operation Instruction Manual

Model FA2100CVR

Table 4. CVR LABEL 350 OUTPUT FORMAT (CONTINUED) 30­31

32

SSM 350

31 1 1 0 0

30 1 Normal Operation (NO) 0 Functional Test (FT) 1 Non Computed Data (Not Used) 0 Fault Warning (Not Used)

Parity

In general, the Label 350 Status Word bits operate as outlined in ARINC 757−4, Attachment 20. There is some interaction among the status bits in Label 350 with regard to Bit 11 (CVR Status), the CVR Fault Status discrete output, and with the results of the CVR Push−to−Test function. These interactions are summarized in Table 5 below: The RIPS Status reporting is unique for the P/N: 2100−1025−24. RIPS Maintenance Status (Battery) is indicated in bit 26 and RIPS Fault Status is indicated in bit 27. The CVR provides this data as received from the RIPS in near real time over this OMS link. Upon power interruption or loss to the RIPS/CVR system, the CVR would ensure that the RIPS supplies the CVR with the required backup power. Specifically, if the system was powered for at least 10 minutes but less than 15 minutes, a hold up time of at least 5 minutes would be expected, and if powered for 15 minutes or more, a hold up time of at least 9 minutes would be expected. If the RIPS meets this requirement, which ensures it is operating in accordance with its intended function, on the next power up the OMS discrete bits would indicate a no Maintenance and a no Fault condition regardless of the information the RIPS provides to the CVR. This no Maintenance and no Fault reporting would also occur if the previous recorder power cycle was less than 10 minutes in duration. In the event the RIPS does not provide for its intended function on the previous power cycle, as described above, the CVR would report actual real time status of the Maintenance and Fault signals it receives from the RIPS in bits 20 and 15. Reporting of RIPS Present would always provide real time status on bit 22 and RIPS Active would always provide real time status on bit 21. To provide for comprehensive troubleshooting, real time status of RIPS Maintenance and Fault will be provided on OMS label 350 bits 26 and 27 respectively. In all scenarios, the status of the RIPS as reported to the recorder will be recorded in the Cockpit Voice Recorder fault log.

Table 5. CVR FAULT REPORTING INTERACTIONS L350 BIT N° 11 12 13 14 15** Rev. 16

FUNCTION

CVR Status (Audio Recording Fail­ ure) CMC Bus Status (OMS Input) CVR Control Unit Failure FDR Status (not used) RIPS Fault Status (Pin 29)

REPORTED WITH L350 BIT 11

REPORTED WITH PUSH TO TEST

YES

YES

REPORTED WITH CVR FAULT DIS­ CRETE YES

NO YES NO NO

NO YES NO NO

NO YES NO NO 165E1846-00 Page 7

Installation & Operation Instruction Manual

16 17 18 19 20** 21 22 26* 27*

Model FA2100CVR

CVR DataLink Recording Failure Clock Status Data Link Input Interface CVR Record Enable (Pins 7/8) RIPS Maintenance Status (Battery) (Pin 38) RIPS Active Status (Pin 10) RIPS Presence Status (Pin 42) RIPS Maintenance Status (Battery) (Pin 38) RIPS Fault Status (Pin 29)

NO NO NO NO NO

NO NO NO YES NO

NO NO NO YES NO

NO NO NO

NO NO NO

NO NO NO

NO

NO

NO

* Applicable to the Model 2100-1025-24 only. ** Not applicable to the Model 2100-1025-24. It is important to note that certain CVR faults can only be detected through the “Push−to−Test” function. This commanded BITE provides the only test of the CVR audio input circuits. During the Push−to−Test operation, the CVR generates a test tone and sequentially injects it into each of the four audio input channels. A CVR fault will be asserted if the tone amplitude or frequency is not correctly detected. Like any other internal CVR fault, this audio circuit failure will be reported using: the Label 350 output Bit 11, the CVR Fault Status discrete output, and the Push−to−Test results. If an audio input circuit failure occurs after a successful Push−to−Test operation, it will not be detected, or reported, until the next Push−to−Test is initiated. This audio input circuit failure is the only fault that would not otherwise be detected and reported by the CVR continuous BITE. Push−to−Test results are reported, during the test, using the CVR Test Indicator output (Pins 15/16) which is usually connected to an indicator lamp or meter on the CVR Control Unit. In addition, CVR failures reported through the Push−to−Test operation will be indicated by muting of the CVR Monitor Audio output (Pins 5/6). The fault criteria used to determine the reporting status associated with the CVR Label 350 Status Word bits are summarized in Table 6.

Table 6. CVR STATUS WORD FAULT REPORTING CRITERIA

L350 BIT N° 11

TABLE 6 CVR STATUS WORD FAULT REPORTING CRITERIA FUNCTION FAILURE CRITERIA

CVR Status (Audio Recording Failure)

12

CMC Bus Status (OMS Input)

13

CVR Control Unit Failure

14 15**

FDR Status (not used) RIPS Fault Status (Pin 29)

165E1846-00 Page 8

Any internal CVR failure that prevents correct recording of the audio inputs (including CU failure and Push-to-Test au­ dio input circuit failure). May relent depending on fault severity. Loss of OMS input Heartbeat (valid Label 227 input) for more than 3 seconds. Relents if OMS Heartbeat is restored. Loss of 18 VDC Control Unit supply voltage. Relents if voltage level returns. Always reported as ‘Failed’ in CVR only recorder. RIPS Fault as reported on pin 29 input (if present). Rev. 16

Installation & Operation Instruction Manual

Model FA2100CVR

16 17

CVR DataLink Recording Fail­ ure Clock Status

18

Data Link Input Interface

19

CVR Record Enable (Pins 7/8) RIPS Maintenance Status (Bat­ tery) (Pin 38) RIPS Active Status (Pin 10) RIPS Presence Status (Pin 42) RIPS Maintenance Status (Bat­ tery) (Pin 38) RIPS Fault Status (Pin 29)

20** 21 22 26* 27*

Any internal CVR failure that prevents correct recording of the DataLink input. Loss of the ARINC 429 GMT input (Label 125 or 150) for more than 40 seconds. Relents if clock input is restored. Loss of the DataLink Heartbeat (valid Label 270) for more than 3 seconds (only if DataLink Valid, Pin 56, is asserted). Relents if DataLink Heartbeat is restored or DataLink Valid removed. Or Presence of DataLink Heartbeat (valid Label 270) if DataLink Valid, Pin 56, is not asserted. Relents if DataLink Valid is asserted or DataLink Heartbeat is removed. CVR ‘Record Enable’ jumper status (pins 7/8). RIPS Maintenance Status as reported on pin 38 input (if present). RIPS Active Status as reported on pin 10 input (if present). RIPS Presence as reported on pin 42 input. RIPS Maintenance Status as reported on pin 38 input (if present). RIPS Fault as reported on pin 29 input (if present).

* Applicable to the Model 2100-1025-24 only. ** Not applicable to the Model 2100-1025-24. Any and all faults detected by the CVR, even if they relent, are recorded in a non−volatile fault log memory. This fault log can be retrieved using appropriate ground support equipment for review and analysis.

1.5.2 Label 354 LRU Identification Output The CVR LRU IDENTIFICATION consists of multiple ARINC 429 words for the transmission of the CVR part number and serial number. The group of eleven ARINC 429 words defined below is transmitted twice per second.

Rev. 16

165E1846-00 Page 9

Installation & Operation Instruction Manual

Model FA2100CVR

a. Start of Transmission Word Bit No Function 1­8 Label 354 9­16 Number of words in transmission (11) 17­24 Not used 25­31 STX 32 Parity b. LRU Name Bit No Function 1­8 Label 354 9­15 ‘C’ 16 Not used 17­23 ‘V’ 24 Not used 25­31 ‘R’ 32 Parity c. End of LRU Name, Start of Part Number Bit No Function 1­8 Label 354 9­15 Carriage return 16 Not used 17­23 First character of part number 24 Not used 25­31 Second character of part number 32 Parity d. Part Number (continued) Bit No Function 1­8 Label 354 9­15 Third character of part number 16 Not used 17­23 Fourth character of part number 24 Not used 25­31 Fifth character of part number 32 Parity e. Part Number (continued) Bit No 1­8 9­15 16 17­23 24 25­31 32 165E1846-00 Page 10

Function Label 354 Sixth character of part number Not used Seventh character of part number Not used Eighth character of part number Parity

Status 11101100 00001011 00000000 00000010

Status 11101100 1000011 0 1010110 0 1010010

Status 11101100 0001101 0 0

Status 11101100 0 0

Status 11101100 0 0

Rev. 16

Installation & Operation Instruction Manual

Model FA2100CVR

f.

Part Number (continued)

Bit No Function 1­8 Label 354 9­15 Ninth character of part number 16 Not used 17­23 Tenth character of part number 24 Not used 25­31 Eleventh character of part number 32 Parity g. End of Part Number, Start of Serial Number Bit No Function 1­8 Label 354 9­15 Twelfth character of part number 16 Not used 17­23 Carriage return 24 Not used 25­31 First character of serial number 32 Parity h. Serial Number (continued) Bit No Function 1­8 Label 354 9­15 Second character of serial number 16 Not used 17­23 Third character of serial number 24 Not used 25­31 Fourth character of serial number 32 Parity i. Serial Number (continued) Bit No Function 1­8 Label 354 9­15 Fifth character of serial number 16 Not used 17­23 Sixth character of serial number 24 Not used 25­31 Seventh character of serial number 32 Parity j. Serial Number (continued) Bit No 1­8 9­15 16 17­23 24­31 32 Rev. 16

Function Label 354 Eighth character of serial number Not used Ninth character of serial number Not used Parity

Status 11101100 0 0

Status 11101100 0 0001101 0

Status 11101100 0 0

Status 11101100 0 0

Status 11101100 0 00000000

165E1846-00 Page 11

Installation & Operation Instruction Manual

Model FA2100CVR

k. End of Transmission Word Bit No 1­8 9­24 25­31 32

Function Label 354 Not used EOT Parity

Status 11101100 0000000000000000 0000100

1.5.3 Label 377 ARINC 429 Equipment Identification Word Output The CVR outputs a Label 377 equipment identification word on the OMS bus once per second. The word structure is defined below: Bit No 1­8 9­10 11­18 19­29 30­31 32

Function Label 377 SDI Equipment ID (CVR = 0x57) Not Used SSM Parity

Status 11111111 00 11101010 00

1.5.4 OMS Input For the purpose of reporting the OMS input bus status in the Label 350 CVR Status Word output, the CVR expects a valid OMS input “heartbeat” once per second on the low speed OMS ARINC 429 input. The heartbeat is detected through the presence of a valid Label 227 input (including good parity) to the CVR. This Label 227 is used only for heartbeat detection and is not otherwise processed by the CVR. If the heartbeat is not detected during three consecutive seconds, the CVR will report the CMS Bus (OMS input) status as “failed” in the Label 350 CVR Status Word output. If the OMS input bus is not connected, then the associated Label 350 Status Word bit 12 can be ignored.

1.6

CVR DATALINK INPUT INTERFACE

The FA2100 CVR, part numbers 2100−1025−( ) and 2100−1026/27−02, was developed specifically to satisfy recent requirements for Controller Pilot DataLink Communications (CPDLC or “DataLink”) recording in addition to the two hour audio recording capability. The DataLink recording function of the CVR is generally compatible with ARINC 429, ARINC 757, ARINC 758, and ARINC 619. The interface is characterized by the following specifications: S

Single, ARINC 429, High Speed, physical layer input interface (Pins 33/34)

S

Williamsburg Version 3, Bit−Oriented Protocol for link layer interface

S

Includes support for ALOHA exchange (but not required)

S

Records all System Address Label (SAL) 157 and/or 156 full word inputs

S

Recording of all Label 270 and Label 276 DataLink status word inputs

S

Recording of all Label 350 CVR OMS status word outputs

S

32 Mbytes of crash survivable memory reserved for DataLink message recording

S

DataLink Valid Discrete input (Pin 56)

165E1846-00 Page 12

Rev. 16

Model FA2100CVR

S

Installation & Operation Instruction Manual

DataLink Fault Discrete output (Pin 31)

All Label 270, 276, 157, and 156 words input on the CVR DataLink interface will be recorded to crash protected memory regardless of the parity (good or bad). Likewise, these inputs, if present, will be recorded regardless of the state of the DataLink Valid discrete input (Pin 56).

1.6.1 Data Link Input and Encapsulation It is generally recognized that the Williamsburg Version 3 CVR input will utilize only Command frames containing the encapsulated DataLink message information. These Command frames then include the ARINC 619 formatting which provides the Network layer interface. However, the FA2100CVR records data at the link layer interface level and is unaffected by any link layer, or above, data content. This means that the CVR will record all 32 bits of each and every SAL 157 or 156 word received on the DataLink input. As a result, the CVR will not be impacted by any changes or additions to the approved DataLink message set. Likewise, the CVR DataLink recording function is not affected by the ARINC 619 General Format Identifier (GFI) coding or by the Extended GFI header encoding currently defined for message encapsulation. This technique provides the maximum flexibility in DataLink recording without the need for future CVR changes as the approved message set or associated encapsulation protocols continue to evolve. A generic DataLink encapsulation structure is illustrated in Figure 2.1 below.

Rev. 16

165E1846-00 Page 13

Installation & Operation Instruction Manual

Model FA2100CVR

Williamsburg V3 protocol

payload

protocol

ARINC 619 Header

payload

Common Header Header

Payload = one of the following styles

CPDLC 0

Header Length

ASCII or Unaligned PER Message

ADS−C 1

Header Length

ASCII or Bit Encoded Message

AFN, ARINC 623 DC and ARINC 623 OC 2,3,5

Length

ASCII Message

ARINC 623 ATIS & Display Server 4,6

Area

Length

ASCII Message

Figure 3. Generic DataLink Message Encapsulation Structure As indicated in Section 1 above, the FA2100 DataLink CVR also includes an ARINC 429 OMS output interface (Pins 50/51) that provides a Label 350 CVR status word output once per second. This word, in its entirety, along with any DataLink Label 270 or 276 input status words are also recorded as part of the DataLink stream. This provides a complete representation of the CVR DataLink input, and overall CVR status, within the recorded DataLink stream.

1.6.2 DataLink Heartbeat In addition to providing the originating system status (e.g. CMU), the Label 270 input word is also used for DataLink “heartbeat” detection by the CVR. A valid Label 270 input (including good parity) must be received once per second by the CVR. If this heartbeat is not detected for 40 consecutive seconds for the 2100−1025/26/27−02 or three consecutive seconds for the 2100−1025−22/24, and the DataLink Valid discrete input (Pin 56) is asserted, a DataLink Interface fault will be asserted (as reported in the Label 350 165E1846-00 Page 14

Rev. 16

Model FA2100CVR

Installation & Operation Instruction Manual

CVR Status Word output). Likewise, a DataLink Interface fault will also be reported if the Label 270 heartbeat is detected, and DataLink Valid (Pin 56) is not asserted.

1.6.3 Williamsburg Bit−Oriented Protocol Version Support It should be noted that the FA2100 CVR does not currently support Williamsburg Version 1 protocol or a low speed ARINC 429 interface for input of DataLink information. However, the CVR does support the Williamsburg ALOHA exchange, even though it is not required for Williamsburg Version 3 DataLink input. In the event that the CVR receives a valid ALO input on the SAL Label 157 (or 156), it will respond with a valid Label 304 ALR output indicating support for the Version 3 protocol. The format of the Label 157 or 156 ALO input is as follows: Label 157 0r 156 ALO Input Bit No Function Status 1­8 System Address Label 157 or 156 01101111 or 01101110 9­24 (Not used by CVR) 25­28 ALO 1110 29­31 Protocol 001 32 Parity The format of the Label 304 ALR response word from the CVR, indicating support for Version 3 only, is shown below. CVR Label 304 ALR Output (in response to ALO input) Bit No Function Status 1­8 System Address Label 304 11000100 9­12 Version Supported (3) 1100 13­24 Reserved 000000000000 25­28 ALR 0001 29­31 Protocol 001 32 Parity As noted above, this ALOHA exchange is not necessary to initiate Williamsburg Version 3 DataLink input to the CVR.

1.6.4 DataLink Memory Capacity The CVR is currently configured with 32 Mbytes of dedicated DataLink recording memory. This provides for a recording duration far in excess of the existing two hour requirement.

1.6.5 DataLink Retrieval Recorded DataLink information is retrieved from the CVR in much the same way as audio data. All, or a portion, of the DataLink recording can be downloaded from the CVR using Ground Support Equipment supplied by L−3, Aviation Recorders. The Portable Interface can be used to download the DataLink recording to a PCMCIA memory card. The DataLink recording can also be downloaded using the CICC/2 or CICC/3 interface cable connected to a PC. The downloaded DataLink file can then be displayed using the Audio DataLink Playback (ADLP) software utility. ADLP can also output the recorded DataLink stream as a Hex ASCII file or Binary ASCII file for more extended user processing and display. Rev. 16

165E1846-00 Page 15

Installation & Operation Instruction Manual

Model FA2100CVR

COCKPIT AREA MICROPHONE (CAM)

*

MONITOR AUDIO TO HEADSET JACK

ERASE A

ERASE C

CONTROL UNIT

AIRCRAFT WIRING INTERLOCKS (LANDING GEAR MUST BE DOWN AND BRAKE LOCKED TO ALLOW MEMORY TO BE ERASED)

PUSH TO TEST

GEAR

AREA MICROPHONE

BRAKE +18 VDC OPERATING POWER

28 VDC OR 115 VAC 400 Hz

2

RECORD ON +5 V FOR LIGHTED PANEL

CHANNEL 4 2 CHANNEL 3

PILOT AUDIO

FA2100 CVR

2

2 CHANNEL 2

CO‐PILOT AUDIO

+18 VDC

2

SPARE AUDIO (TO 3RD CREW MEMBER OR PA SYSTEM)

2

CHANNEL 1

TEST INDICATOR

2

2

GMT_IN_B (429) GMT_IN_A (429) ROTOR_SPEED_IN_HI ROTOR_SPEED_IN_LO **OMS IN A **OMS IN B

AIRCRAFT INTERFACE PWA

***RIPS FAULT INPUT ***RIPS MAINTENANCE INPUT ***RIPS PRESENT INPUT STOP RECORDING/ ***RIPS ACTIVE INPUT CHASSIS GROUND

* S055 Mics have 4 Lines to the C.U. S056 MICS have 3 Lines to the C.U. For GA versions refer to Figure 4.

OMS & Data Link are applicable to the 2100-1025-XX & 2100-1026-XX only.

*** RIPS Status Monitoring. 2100-1025-22 &

CVR FAULT

TO AIRCRAFT FAULT MONITORING SYSTEM

**OMS OUTPUT A 429 **OMS OUTPUT B 429

**DATA LINK IN A 429 **DATA LINK IN B 429 **DATA LINK VALID

**

AUDIO OUT

**DATA LINK FAULT

AUDIO COMPRESSOR PWA ACQUISITION PROCESSOR PWA

GSE OUTPUT

TO GROUND STATION TEST EQUIPMENT

CSMU (Crash Survivable Memory Unit) ASSEMBLY (CRASH PROTECTED SOLID STATE MEMORY)

2100-1026-XX only.

Figure 4. Functional System Block Diagram Model FA2100CVR Cockpit Voice Recorder 165E1846-00 Page 16

Rev. 16

Installation & Operation Instruction Manual

Model FA2100CVR

Table 7. Model FA2100CVR Recording Specifications Cockpit Audio Inputs FA100CVR Part Number

Channel 1

Channel 3

Channel 4

Combined Audio SQ

CAM SQ

Co-Pilot Audio Input for High Quality Recording

Pilot Audio Input for High Quality Recording

Cockpit Area Microphone (CAM) Input for High Quality Recording

Summation of CH 1, 2, & 3 Audio Inputs for Standard Quality Recording

Cockpit Area Microphone (CAM) (CH 4) Input for Standard Quality Recording

2100−1010−( ) 30 minutes

30 minutes

30 minutes

30 minutes

Not Available

Not Available

2100–1020–( ) 30 minutes pre MOD− DOT # 7

30 minutes

30 minutes

30 minutes

120 minutes

120 minutes

2100–1020–( ) 120 minutes MOD−DOT #7

120 minutes

120 minutes

120 minutes

Not Available

Not Available

2100–1025–( ) 120 minutes 2100−1026−02 2100−1027−02

120 minutes

120 minutes

120 minutes

Not Available

Not Available

3rd Crew Member/Spare Audio Input for High Quality Recording

Note:

Channel 2

Combined Channels

All of the times in the above table are minimum recording times. Unit can record input audio levels from .05Vrms − 3.0Vrms. Nominal input level is 1.0 Vrms.

1.6.6 Control Units and External Preamplifier The Control Unit or External Preamplifier is a required component of a CVR installation and functions as the FA2100CVR cockpit user interface. Control Units contain a preamplifier printed wiring assembly (PWA) for interfacing the cockpit area microphone with the FA2100CVR, and provide a means for activating the test function via a green push button and an indicator. Bulk Erasure of the FA2100CVR storage media is also accomplished by pressing the Control Unit’s red Bulk ERASE push button. All Control Units contain a headset jack for verifying system operation. Refer to Component Maintenance Manual, ED−56A Control Units & Microphones, ATA 23–70–05, Part Number 165E1747-00. The Model S151/S161, Model S152/S162, and the Model S251/S261 Control Units are for use in FA2100CVR ARINC−757 / ED–56A System installations. The Model S151 and Model S251 Control Units house the Microphone Preamplifier PWA, and have front panel TEST and Bulk ERASE switches. The Model S151/S251 Control Units are used with an externally-mounted electret condenser-type microphone (Model S055, see paragraph 1.6.7). The Model S161/S261 Controls Units are used with remote microphone modules with internal amplifiers for reducing RF interference (Model S056, see paragraph 1.6.7). These control units also have front panel TEST and Bulk ERASE switches (with the exception of p/n: S161−0030−07), TEST indicator lamp (with the exception of p/n: S161−1390−01) and a HEADSET jack. However, there are two Control Units that do not contain all of the hardware listed, p/n: S161−1390−01 does not have a Test Indicator lamp, and p/n: S161−0030−70 does not have a Bulk Erase switch. Rev. 16

165E1846-00 Page 17

Installation & Operation Instruction Manual

Model FA2100CVR

The Model S152/S162 contains a built-in electret condenser-type microphone, Microphone Preamplifier PWA, TEST and Bulk ERASE switches, TEST indicator lamp and a HEADSET jack. The Model S150/S160 Preamplifier is available for FA2100CVR ED–56A System installations that do not require a Control Unit. However, because ARINC Characteristic 757 does not address microphone preamplifiers, the Model S150/S160 Preamplifier is not considered ARINC−757 compliant. The S150 is designed to be used with the S055 remote microphone. The S160 is used with the S056 remote microphone. The FA2100CVR is compatible with installations using the Model A151B and A152B Control Units; however, such installations do not comply with ARINC Characteristic 757 or EUROCAE ED–56A. The Model A151B houses the Microphone Preamplifier PWA, and the TEST and Bulk ERASE switches. This Control Unit is used with an externally-mounted condenser microphone (Model A55B). The Model A152B contains a built-in condenser microphone, Microphone Preamplifier PWA, and TEST and Bulk ERASE switches. Both the A151B and A152B Control Units contain an analog TEST meter compatible with the FA2100CVR. Refer to Appendix A for Control Unit and External Preamplifier outline and dimension illustrations. Refer to Appendix B for RTCA/DO−160C environmental test conditions and description of environmental tests conducted.

1.6.6.1

Mating Connector, Control Units and External Preamplifiers

For Model S151/S161, S152/S162, A151B, and A152B Control Units. Solder – Part Number MS3116F−20−41S Crimp – Part Number MS3126F−20−41S For Model S251/S261 Control Unit Solder – Part Number 147E1262−00 Crimp – Part Number 147E1263−00 For Model S150 External Preamplifier 19 Pin, Solder – Part Number MS3111F–14–19P 3 Pin, Solder – Part Number MS3111F–8–3P For Model S160 and A150 External Preamplifier 19 Pin, Solder – Part Number 063−98−01897 3 Pin, Solder – Part Number 063−98−01898

1.6.7 Remote Microphone Module The Model S055 and Model S056 Remote Microphone Modules are available to complete an ED–56A-compatible installation. The Model S055 Microphone is required with the S151 and S251 Control Units and with the S150 Preamplifier Module. The Model S056 Microphone is required with the S161 and S261 Control Units and with the S160 Preamplifier Module. Refer to Appendix A for outline and dimensions illustrations and for a definition of the Model S055 and Model S056 Remote Microphone Module part numbers. Also refer to Appendix A for S055 and S056 microphone element specifications and response diagram. Refer to Appendix B for RTCA/DO−160C environmental test conditions and description of environmental tests conducted. 165E1846-00 Page 18

Rev. 16

Installation & Operation Instruction Manual

Model FA2100CVR

1.6.8 CVR Mounting Racks A.

CVR Mount, Part Number 178E0919–00

CVR mount with no vibration isolators used to install the FA2100CVR in the aircraft. Refer to Figure 6 for outline and dimensions. B.

Vibration Mount, Part Number 9300−343

CVR mount equipped with four vibration isolators. Contact Aviation Recorders Product Support for Full Sway Envelope and Outline and Dimension Drawings. C.

Heavy Duty Vibration Mount, Part Number 93−955

CVR mount for use in aircraft environments where excessive vibration may occur, such as in rotor−craft or test aircraft. Contact Aviation Recorders Product Support for Full Sway Envelope and Outline and Dimension Drawings. D.

Connector for CVR Mount

Connector attaches to mount, and mates with the connector on the FA2100CVR’s rear panel. Aircraft wiring is soldered or crimped to the connector pins. Solder – Part Number 9300–435 Crimp – Part Number 063–98–01474

1.7

Abbreviations and Acronyms

For definition of abbreviations and acronyms used in this document, refer to Appendix D.

2.0

EQUIPMENT LIMITATIONS/SPECIFICATIONS

2.1

Applicable Documents

ARINC Characteristic 404A ARINC Characteristic 757 ARINC Characteristic 757A ARINC Characteristic 777−1 ARINC Report 604–1 ARINC Report 624–1 EUROCAE MOPS ED–56A EUROCAE MOPS ED–112 FED–STD–595 Rev. 16

Aeronautical Radio, Inc., Air Transport Equipment Cases and Racking Aeronautical Radio, Inc., Cockpit Voice Recorder Aeronautical Radio, Inc., Cockpit Voice Recorder Aeronautical Radio, Inc., Recorder Independent Power Supply Aeronautical Radio, Inc., Design Guidance for Design and Use of Built-In Test Equipment Aeronautical Radio, Inc., Design Guidance for Onboard Maintenance System European Organization for Civil Aviation Equipment Minimum Operational Performance Specification for Cockpit Voice Recorder Systems European Organization for Civil Aviation Equipment Minimum Operational Performance Specification for Crash Protected Airborne Recorder Systems Federal Standard, Colors 165E1846-00 Page 19

Installation & Operation Instruction Manual

Model FA2100CVR

RTCA/DO–160C

Radio Technical Commission for Aeronautics, Environmental Conditions and Test Procedures for Airborne Equipment Radio Technical Commission for Aeronautics, Software Considerations in Airborne Systems and Equipment Certification Federal Aviation Administration Technical Standard Order Cockpit Voice Recorder Systems Federal Aviation Administration Technical Standard Order Cockpit Voice Recorder Systems

RTCA/DO–178B TSO–C123a TSO–C123b

2.2

Physical Characteristics

The Model FA2100CVRs fit within the envelope of an ARINC 404A 1/2-ATR short case. (Refer to for Figure 5 outline and dimension illustration.) Following are the physical characteristics of the Model FA2100CVRs: Size: Height: Width: Depth:

5.4 inches nominal Chassis: 4.88 inches nominal Front Panel: 4.98 inches nominal 12.6 inches nominal (behind front panel) 13.1 inches nominal (including hold-down hooks)

Weight1:

10.0  0.5 pounds

Markings:

International Orange (FED–STD–595 Color No. 12197), Reflective Striping on Crash Survivable Memory Unit, English Markings on One Side of Chassis and French Markings on Other Side of Chassis

Main (Rear) Connector:

57-Pin Connector Compatible with ARINC 757, Part Number 063E1072–00 (Cannon Part Number DPXB–36571–59)

Main (Rear) Mating Connectors:

Crimp: Part Number 063–98–01474 (Cannon Part Number DPXBMA–57–33S–0001) Solder: Part Number 9300–435 (Cannon Part Number DPXB–57–33S–0001)

Ground Support Equipment Connector: 1

Part Number 063−98−01962 (AMP Part Number 748481–6)

Weight is with Underwater Locator Device installed.

2.3

Electrical Characteristics

Power Requirements:

115 Volts AC @ 400 Hz, or 28 Volts DC

Power Level:

10.5 watts maximum when powered by 28 Volts DC 12 watts maximum when powered by 115 Volts AC @ 400 Hz

Power Factor:

0.65

Output Power:

+18 Vdc, 25 mA short-circuit protected, to Control Unit

165E1846-00 Page 20

Rev. 16

Installation & Operation Instruction Manual

Model FA2100CVR

Recording Time:

PN 2100–1010–( ) = 30 minutes minimum PN 2100–102X–( ) = 120 minutes minimum

Input Signal Format:

ARINC 757/757A

Audio Input Impedance:

> 5000 ohms each channel

Audio Inputs:

3 crew microphones (150 − 3500 Hz bandwidth) 1 cockpit area microphone (150 − 6000 Hz bandwidth)

Audio Input Level:

50 mVrms to 3 Vrms; 1 Vrms nominal.

Audio Quality:

Meets ED−56A Chapter 3 and ED−112 Part I specifications. Signal-to-noise plus distortion ratio (SINAD) of the signal when reproduced > 24 dB (6 % distortion) for the most recent 30 minutes of recording, > 20 dB (10 % distortion) otherwise

Greenwich Mean Time Input Data:

ARINC 429 Format

Rotor Speed Input Signal:

2 Vrms to 122 Vrms from 7 to 6000 Hz per ARINC 757

Discrete Inputs:

Bulk Erase − 2 discrete inputs Erase A Erase C Push-to-Test − 1 discrete Record On − 2 discrete inputs Stop Recording − 1 discrete

Digital Outputs:

CVR Fault − 1 discrete

Rev. 16

165E1846-00 Page 21

Installation & Operation Instruction Manual

Model FA2100CVR

ESD LABEL

C

COCKPIT VOICE RECORDER MODEL FA2100

B

2.44 ± .5

B 7.5

A

±

C

.5

A

5.4 ± .1 3.0 ± .5

FARSIDE LABEL READS: ENREGISTREUR DE VOL NE PAS OUVRIR .2 MAX

12.60

±

.04

.5 MAX

NOTES: 1. RECORDER COLOR IS INTERNATIONAL ORANGE NO. 12197 PER FED-STD-595. FRONT AND SIDE LABELS ARE REFLECTIVE WHITE BACKGROUND WITH BLACK LETTERING. NAMEPLATE IN VIEW A-A HAS LIGHT GRAY BACKGROUND WITH BLACK MARKING. A RUSSIAN TEXT LABEL IS LOCATED ON THE CSMU ON P/N: 2100−1025−12 AS SHOWN IN THE LOWER RIGHT HAND CORNER OF THIS DRAWING

2. ELECTRICAL INTERFACE CONNECTIONS PER APPLICABLE ARINC CHARACTERISTIC. 3. SEE CHART FOR FINAL PART NO. INPUT POWER, AND WEIGHT. POWERS ARE MAXIMUMS AND WEIGHTS ARE NOMINAL WITH ± .5 LBS TOLERANCE. 2100-1010-00 H 4. OVERALL EQUIPMENT SIZE AND MOUNTING SCHEME COMPLY WITH ARINC 404 AND 404A. 2100-1020-00 G 5. REAR PANEL CONTAINS HOLES TO MATE WITH GUIDE PINS IN ARINC 404 MOUNTING TRAYS.

Figure 5. (Sheet 1 of 2) Outline and Dimensions FA2100CVR Cockpit Voice Recorder, PN 2100–1010–( ) & PN 2100–102X–( )

165E1846-00 Page 22

Rev. 16

Installation & Operation Instruction Manual

Model FA2100CVR

2.44 ± .50

REFERENCE ONLY COCKPIT VOICE RECORDER MODEL FA2100

A

POLARIZING KEYS SHADING DENOTES SOLID KEY AREA

.995 ± .01

View

A B

For P/N: 2100−1027−02 With ARINC 757A Connector Only

B

View

J1 CONNECTOR PART NUMBERS: PN 063-E1072-00 (CANNON DPBX-36571-59) MATING CONNECTORS: (CRIMP) PN 063-98-01474 (CANNON DPXBMA-57-33S-0001) (SOLDER) PN 9300-435 (CANNON DPXB-57-33S-0001)

4.88

CRASH SURVIVABLE MEMORY UNIT

UNDERWATER LOCATING DEVICE

±

.04

REPLACEMENT DATE

5.5

±

.2

GROUND SUPPORT EQUIPMENT CONNECTOR 063-98-01962 (AMP 748481-6)

4.12

± View

4.98

C

.04

C

2100-1010-00 H 2100-1020-00 R

Figure 5. (Sheet 2 of 2) Outline & Dimensions FA2100CVR Cockpit Voice Recorder, PN 2100–1010–( ) & PN 2100–102X–( )

Rev. 16

165E1846-00 Page 23

Installation & Operation Instruction Manual

Model FA2100CVR

NAMEPLATE INFO: NAME: MOUNT, HARD, CVR PN: 178−E0919−00 REV [X] SN: XXXXX DATE: MM/YY

5.60 $ .50

3.50

(CG)

CL

COMPANY LOGO

5.38 MAX OUTSIDE

4X 0.182 $ .010 100° CSK

4.12 5.02 $ .02 INSIDE

2.38

9.06

4.00 MAX (CG)

1.00 MAX

.75 $ .50 .80 MAX

16.41 MAX

3.500 $.005 CLEARANCE HOLES FOR #8 SCREWS

9.062 $ .005 SUGGESTED MOUNTING HOLE PATTERN NOTES: 1. UNDIMENSIONED FEATURES (SUCH AS SIDE RAILS, TABS, FLANGES, AND WEIGHT-REDUCING HOLES) MAY VARY PICTORIALLY FROM THIS DRAWING. 2. WEIGHT 1.3 LBS. MAX. 3. CONNECTOR MOUNTING HOLE IS DESIGNED FOR: (CRIMP) PN 063−98−01474 (CANNON DPXBMA−57−33S−0001) (SOLDER) PN 9300−435 (CANNON DPXB−57−33S−0001) 4. SUGGESTED MOUNTING HARDWARE: TO ATTACH CONNECTOR TO MOUNT: 8 EACH 4−40 X 7/16 PAN HEAD SCREWS PN 229−02−00076 (MS51957−16) OR EQUIV, AND 4−40 SELF-LOCKING NUTS, PN 16165 (ESNA PN 68−1660−40) OR EQUIV. TO ATTACH MOUNT TO AIRCRAFT: 4 EACH FLAT HEAD SCREWS MS24693−( ) OR EQUIV (LENGTH AS REQD), AND SELF-LOCKING NUTS MS21044−C08 OR EQUIV.

905−E0919−18H

Figure 6. Outline and Dimensions, CVR Mount, Part Number 178E0919−00 165E1846-00 Page 24

Rev. 16

Installation & Operation Instruction Manual

Model FA2100CVR

2.4

Environmental Characteristics

Refer to the FA2100CVR Environmental Qualification Forms (EQFs) in Appendix B for environmental characteristics.

2.5

Crash- and Fire-Survival Characteristics

Penetration:

ED–56A/ED−112 – 500 lbs./10 feet/!@4” probe

Static Crush:

ED–56A/ED−112 – 5,000 lbs.

Fire Protection:

TSO–C123a/ED–56A/ED−112 – 50,000 BTU/sq. feet/hour, 60 minutes @ 1100_C and 10 hours @ 260_C

Impact:

ED–56A/ED−112 – 3400 g’s, 6 ms, half-sine shock wave

3.0

INSTALLATION PROCEDURES AND LIMITATIONS

3.1

Installation Precautions

Approval of the Model FA2100CVR installation is not authorized by this Installation and Operating Instruction Manual. Approval for initial installation and operational use of the FA2100CVR and its associated components must be sought from the cognizant Federal Aviation Administration (FAA) Flight Standards District Office or other certifying authority using the processes identified within FAA Order 8900.1, Volume 4, Chapter 9 “Selected Field Approvals” or Supplemental Type Certification (STC), as applicable. Generally, retrofit installation of an FA2100CVR may be accomplished as a minor alteration, using approved data from the original installation or other sources of approved data, if such installation is determined to meet the criteria with no limitations, identified during the Post−Installation, Preflight, and Flight checks specified for evaluation in this Installation Manual. (Refer to paragraph 3.3.) Before beginning the recorder installation the installer must determined that such installation does not appreciably affect the certificated properties of weight, balance, structural strength, performance, powerplant operation, flight characteristics, or other qualities affecting airworthiness. If any of the certificated properties are appreciably affected, an STC must be sought for installation and operational use of the Model FA2100CVR. For all CVR Installations except P/N: 2100−1025−22/24 and 2100−1027−02, refer to the following statement which was excerpted from FAA TSO−C123a: The conditions and tests required for TSO approval of this article are minimum performance standards. It is the responsibility of those desiring to install this article either on or within a specific type or class of aircraft to determine that the aircraft installation conditions are within the TSO standards. The article may be installed only if further evaluation by the applicant documents an acceptable installation and is approved by the Administrator. For CVR P/N: 2100-1025-22/24 and 2100−1027−02, refer to the following statement which was extracted from FAA TSO–C124b: The conditions and tests for TSO approval of this article are minimum performance standards. Those installing this article, on or in a specific type or class of aircraft, must determRev. 16

165E1846-00 Page 25

Installation & Operation Instruction Manual

Model FA2100CVR

ine that the aircraft installation conditions are within the TSO standards. TSO articles must have separate approval for installation in an aircraft. The article may be installed only according to 14 CFR part 43 or the applicable airworthiness requirements.

3.2

General Information

Installation of the Recorder, Control Unit, and Remote Microphone Module is per ARINC Characteristic 757 dated December 29, 1993. The Federal Aviation Administration has issued several Advisory Circulars which may be referred to in the approval processes. Advisory Circular 25.1457−1a specifically addresses one acceptable means of compliance with the Code of Federal Aviation Regulations, 14 CFR § 25.1457 (b), (e), and (f). Installations must conform to the Operating Rules in 14 CFR §§ 23.1457, 25.1457, 27.1457, and 29.1457 appropriate to the category of operation under 14 CFR parts 91, 135, and 121. The Bulk ERASE connection is not mandated by the FAA, therefore, it is an installation option. The circuitry required for Bulk ERASE includes the installation of interlock devices on board the aircraft. If the Bulk ERASE feature is installed, at least one interlock is required to prevent accidental erasure of the FA2100CVR. If the BULK ERASE feature is not desired, pin 55 (ERASE A) of the FA2100CVR must be grounded to pin 17. Pin 57 remains open.

3.3

Installation Acceptance by Field Approval Method

Initial installation of the Model FA2100CVR must be accomplished by an appropriately certificated repair station which is qualified, and equipped to accomplish such installation and approve the aircraft for return−to−service. The CVR should be installed in accordance with the instructions and limitations contained in this Installation Manual. Installation drawings and other information, such as structural data showing the method of attachment of the CVR components to the airframe, wiring diagrams, appropriate weight and balance data, and identification of all CVR system components used in the installation should be made available to the to the Principal Inspector, who would be responsible for performing the Field Approval should one be deemed appropriate. Otherwise, if an STC is deemed necessary, the installer should contact the geographic Aircraft Certification Office (ACO) nearest to his or her location. In the instance of a Field Approval, the installer (applicant) must make available the CVR Installation Manual containing Operating Instructions and System Description to the FAA Principal Inspector for review and evaluation of the CVR System. The applicant must submit an FAA Form 337, describing the work performed to the airframe in order to accomplish the major alteration of the initially installed CVR System. The FAA Form 337 must also include a statement that a complete Audio System Interface Test (reference paragraph 5.2) was performed as required. The applicant must indicate that the Cockpit Area Microphone is installed in the recommended locations identified in FAA Advisory Circular 25.1457−1A and in accordance with the instructions contained within this Installation Manual. For initial installations, the applicant should submit all appropriate data and drawings to the FAA Principal Inspector or the ACO, as appropriate, before beginning the installation of the Cockpit Voice Recorder. Any deviations to the installation instructions contained in this Installation Manual must be brought to the Inspector’s attention and be so identified on the FAA Form 337. Finally, ground and flight checks must be conducted to verify that the Audio System Interface is satisfactory and that “normal” conversation can be discerned from the Cockpit Area Microphone and the indi165E1846-00 Page 26

Rev. 16

Installation & Operation Instruction Manual

Model FA2100CVR

vidual Pilot, Co−Pilot, and appropriate Third Crew Member or Public Address stations. The CVR System must be verified to be free of any objectionable audio interference and other unwanted noise. Any discrepancies identified during the ground and flight checks must be brought to the Principal Inspector’s attention and corrected before the aircraft can be returned−to−service. If required, L3 Aviation Recorders can reproduce the CVR memory contents into .wav files for channel separation and evaluation. Contact the L−3AR Factory Repair Station Department to coordinate this process. If you prefer to make your own reproduction, refer to section 6.0.

3.4

Recorder Location

The Model FA2100CVR should be installed in the aircraft fuselage location provided for this purpose by the airframe manufacturer, as far aft as practicable. The recommended orientation is mounted in an upright position (vertical as viewed from the front).

3.5

Mounting

The Model FA2100CVR is has been tested and is acceptable for installation in aircraft environments within the limits of RTCA/DO−160C, Curve C. Installation accessories (CVR Mount and Mount Connectors) are described in paragraph 1.4.4. On aircraft with an existing CVR Vibration Mount such as Part Number 9300−343 or equivalent, or with an existing Heavy Duty CVR Vibration Mount such as Part Number 93−955 or equivalent, it is not necessary to retrofit this mounting tray with a hard−mounted tray. Refer to Figure 4 for CVR Mount outline and dimension illustration.

3.6

Power Requirements

Unless impractical, the FA2100CVR should be powered from a bus other than the bus used to provide power to the Flight Data Recorder. Each bus will need to meet the supply reliability requirements appropriate for the recorders being powered. The FA2100CVR operates with input voltages of either 115 Vac at 400 Hz, or 28 Vdc. The FA2100CVRs draw a maximum of 12 watts ac or 10.5 watts dc. The electrical connector is a 57−pin DPXB connector that is compatible with ARINC 757/757A (Part Number is 063E1072−00, Cannon Part Number DPXB−36571−59). This connector mates with the connector on the aircraft wiring harness.

CAUTION Damage will occur if power is applied on 2100−1027−02 recorder only if the interconnect wiring are not to ARINC 757A requirements. This is because of the power pins are different in the ARINC 757A from the ARINC 757. The mating keys on the connector are rotated different (Refer to Figure 5, sheet 2 of 2) as a safe guard to prevent mating a ARINC 757 type recorder. Do not remove or rotate the keys.

3.7

Wiring Connections

The typical electrical interconnect wiring between the recorder and the aircraft is specified in ARINC Characteristic 757and ARINC 757A (2100−1027−02 only). Connections to the FA2100CVR J1 connector depend on the installation configuration. Refer to Appendix A for appropriate Interwiring Diagram.

3.8

Audio System Interface

The FA2100CVR is used in an ARINC 757and ARINC 757A (2100−1027−02 only) configurations, with interface to the aircraft provided through a 57−pin DPXB rear panel connector. Rev. 16

165E1846-00 Page 27

Installation & Operation Instruction Manual

Model FA2100CVR

The range of acceptable audio input levels for the Model FA2100CVR is from 50 mVrms to 3 Vrms. Nominal audio level input is 1 Vrms. The Model FA2100CVR provides for four audio inputs which are connected as follows: Channel 1: Cockpit Spare Audio Input (3rd Crew Member, Public Address System) Channel 2: Co-Pilot's Audio, Boom, Mask, and Hand-Held Microphone Input Channel 3: Pilot's Audio, Boom, Mask and Hand-Held Microphone Input Channel 4: Cockpit Area Microphone (CAM) Input Older aircraft audio systems may require rework to ensure recording of ATC (Air Traffic Control), Intercom, Mask Microphone, and Sidetone audio, independent of mode selection on the audio control panel. In some cases, selection of the loudspeaker function disables side tone output; therefore, transmissions from ATC may not be recorded. Such conditions must be remedied to assure continuous reception of audio from the communications radios. Old Systems: Rework the audio control panel or system to provide a CVR output or install an external summing amplifier. Summing amplifiers can be obtained from Avtec, Baker Electronics, Racal, and others. No changes to the CVR are required. New Systems: Some later−generation audio control panels have a CVR signal output already provided. A summing amplifier may be required to provide recording of the boom microphone. The Installer is responsible for determining the means of interfacing to comply with the regulations. Future Systems: Audio control panels and systems designed to meet or exceed the characteristics of Radio Technical Commission for Aeronautics RTCA/DO−170 for “hot” boom microphone capability may be determined to be acceptable.

3.9

Microphone Installation Criteria

The most desirable location for the Cockpit Area Microphone is forward of a vertical plane oriented laterally through the pilot’s and co−pilot’s normal head position. The Cockpit Area Microphone must face the crew members. Refer to Figure 5 for an illustration of the preferred placement for the Cockpit Area Microphone. Ensure that the microphone is mounted such that the exposed portion of the microphone element is unobstructed.

165E1846-00 Page 28

Rev. 16

Installation & Operation Instruction Manual

Model FA2100CVR

3

1

2 2

3 RECOMMENDED MICROPHONE LOCATIONS ARE NUMBERED IN ORDER OF PREFERENCE

Figure 7. Recommended Cockpit Area Microphone Mounting Location 3.10 Cessation of Recording Code of Federal Aviation Regulations, 14 CFR §§ 23.1457 (d)(2), 25.1457 (d)(2), 27.1457 (d)(2), and 29.1457 (d)(2) state that “There [must be] an automatic means to simultaneously stop the recorder and prevent each erasure feature from functioning, within 10 minutes after crash impact.” The Installer must demonstrate this function. Since the FA2100CVR System can be powered by either 115 Vac at 400 Hz, or 28 Vdc, the following methods are acceptable to ensure automatic cessation of recording: A.

Engine-driven 115 Vac, 400 Hz Source: If power input is derived directly from an enginedriven 115 Vac, 400-Hz source, (not derived from an AC Inverter), no other external cir­ cuitry is necessary. It is assumed that the engine(s) will stop upon crash impact.

B.

ARINC 757 Shutdown Signal: The FA2100CVR continuously monitors the ARINC 757 shut­ down signal that can be supplied to the recorder via pin 10 of the rear panel connector. If the aircraft can no longer sustain flight under its own power, a ground would be applied to pin 10. If this signal remains “active” for approximately 10 consecutive minutes, recording of data will cease. The recording will resume if the shutdown signal goes inactive or upon activation of the “Push-to-Test” function. If the recording is resumed due to execution of the “Push-toTest,” the recording will again cease within 10 minutes if the shutdown signal is still active. Refer to section 3.11 of ARINC 757 for further information.

Rev. 16

165E1846-00 Page 29

Installation & Operation Instruction Manual

4.0

Model FA2100CVR

POST-INSTALLATION CHECKOUT

The following tests and results must be documented in the CVR Installation Checklist and submitted with the data package for field approval consideration: 1.

Before applying power to the FA2100CVR System and associated components, verify that all connections are secure and that a continuity or other interconnect assurance test has been con­ ducted.

2.

Apply power to the system and activate the FA2100CVR's self‐test. To activate self‐test, press and hold the green TEST button for a minimum of five seconds.

3.

For installations containing a Model S151/S161, Model S152/S162, or Model S251/S261 Control Unit, the cockpit‐mounted TEST lamp illuminates when the FA2100CVR has passed the test. (The TEST lamp stays on as long as the TEST button is pressed.)

NOTE:

The Model S161−1390−01 does not have a Test Indicator lamp; therefore, the user must monitor the test tone through the headset.

For installations containing a Model A151B or Model A152B Control Unit, the meter needle rises and comes to rest in the ‘GO’ (green) section of the meter scale when the FA2100CVR has passed the test. (The meter stays in the ‘GO’ section of the meter scale as long as the TEST button is pressed.) 4.

Speak in a normal voice 6‐inches away from the Control Unit microphone while listening in the headset. Note that you can hear what you say without any delay or significant distortion. This test ensures that the microphone is operating.

5.

The Portable Interface (PI), Part Number 17TES0043, can be used to individually monitor the four audio channels as they are being recorded by the FA2100CVR. The PI is connected to the FA2100CVR via a 10‐foot cable that is plugged into the FA2100CVR's front panel GSE con­ nector (refer to Figure 8). The PI receives power from the FA2100CVR. For a description of the PI, descriptions of the menu functions, and PI operation, refer to the Portable Interface Operator's Manual (Part Number 165E1630–00).

NOTE:

Previously recorded information cannot be played back from the FA2100CVR while it is installed in the aircraft.

Using the following procedure, verify that the four following channels inputs are recording correctly, regardless of Audio Control Panel mode or audio (communications radio) selection: Channel 1: Channel 2: Channel 3: Channel 4: l.

Cockpit Spare Audio Input (3rd Crew Member, Public Address System) Co-Pilot’s Audio, Boom, Mask, and Hand-Held Microphone Input Pilot’s Audio, Boom, Mask and Hand-Held Microphone Input Cockpit Area Microphone (CAM) Input

Connect the PI to the FA2100CVR’s GSE connector as shown in Figure 8.

m. Using the PI’s SELECT button, activate the Monitor Menu and turn HQ VOICE CH 1 ON. While someone is speaking into the Channel 1 source, verify that the audio is clear and distortion-free. Monitor the audio with the PI’s internal speaker or with a 600-ohm headset connected to the PI’s phone jack. n. Repeat this process for CH 2, CH 3, and HQ CAM CH 4. o. For 2100−1020−( ), 2−hour recorders, check the combined standard quality channels by placing the SQ VOICE CH 1−3 to ON and the SQ CAM CH 4 to ON with the Portable Interface 165E1846-00 Page 30

Rev. 16

Model FA2100CVR

Installation & Operation Instruction Manual

unit and perform the following check: (This test is not required for p/n: 2100−1025−( ), which is a two hour high quality only recorder.) 1) Select a clear, audible radio channel on the Pilots’ headset (CH 3). 2) Select the same radio channel on the Co−pilots’ headset (CH2) and adjust the volume level to match the Pilots level. 3) Monitor the Pilots’ (CH 3) audio channel to determine if the audio level has degraded in any manner. If so, there is a possibility that one of the audio channels may have a reverse polarity wiring situation. Recheck the control panel to CVR wiring. p. If the GMT input has been connected to the recorder, confirm proper operation by using the real time GMT display function of the PI. This is found under the Special Functions menu. GMT is supplied to the recorder as a low speed ARINC 429 input using Label 125 or Label 150. GMT can also be supplied as FSK audio mixed with channel 1 or 3 with the 2100−1020−( ) recorder. NOTE: 6.

The PI does not display ARINC 429 GMT or rotor speed in the Monitor Mode. This can only be done with the PI in the Playback Mode.

The Bulk Erase function can occur only when the aircraft is resting on its landing gear. After pressing and holding the Control Unit’s bulk ERASE push button for a minimum of 2 seconds, release it and verify Bulk Erase function by listening for a 400-Hz tone at the HEADSET jack. Tone duration is approximately 4 seconds.

5.0

OPERATIONAL TESTS

5.1

Preflight Functional Check

The Preflight Functional Check assures the operator of FA2100CVR System integrity. Therefore, it must be performed before every flight or whenever maintenance has been performed on the aircraft which may have affected the performance of the FA2100CVR System. Press and hold the Cockpit Control Unit’s TEST push button for a minimum of five seconds. The Control Unit TEST lamp illuminates when the FA2100CVR has passed the testing. For installations containing Model A151B or Model A152B Control Units, the meter is used as a ‘GONO-GO’ indicating device. The meter needle rises to and remains within, the ‘GO’ (green) section of the meter scale when the FA2100CVR has passed the testing. (The meter needle stays in the ‘GO’ section of the meter scale as long as the TEST button is pressed.) For recorder P/Ns:2100-1025/26/27-02 with S161−1390−01/02 Control Units, the CVR functionality can be verified by listening for a 640 Hz “test good” tone which is inserted into the monitor audio output at the completion of a successful “push-to-test” operation.

Rev. 16

165E1846-00 Page 31

Installation & Operation Instruction Manual

Model FA2100CVR

PORTABLE INTERFACE (PI) 17TES0043

FA2100CVR

GMT PI AUX READOUT CABLE 17TES0052 1, 2 ROTOR

PI AUDIO READOUT CABLE 17TES0051 1, 3 CH 1 2 3 4 HQ SQ COMB

CAM

TO RECORDER GSE CONNECTOR DATA FROM RECORDER NOTES: 1. Male phono (RCA) plugs for connection to standard cassette, reel-to-reel tape, or digital audio tape recorder to produce high fidelity copy of FA2100CVR’s recorded data for later playback. Depending on type of recorder used, the FA2100CVR’s recorded data can be copied one channel at a time, or all of the individual channels can be copied simultaneously. 2. FSK output for recorded GMT and/or Rotor Speed audio signal. 3. Analog outputs for recorded voice data.

Figure 8. On-Aircraft Setup for Checking Out FA2100CVRs using a Portable Interface

165E1846-00 Page 32

Rev. 16

Installation & Operation Instruction Manual

Model FA2100CVR

5.2

Complete Audio System Check

A complete Audio System Test must be completed under the following conditions; during operator schedule aircraft inspection or specified maintenance, and whenever unscheduled maintenance is performed which may affect the performance of the Cockpit Voice Recorder System. To accomplish this test, the Pilot’s, Co-Pilot’s, Cockpit Area Microphone, and Third Crew Member or Public Address System inputs must be individually checked for their operational integrity with the FA2100CVR. Upon satisfactory completion of this test, an entry shall be made in the aircraft or rotor−craft maintenance records. Using the PI, Part Number 17TES0043, conduct the following audio system check: NOTE:

For a description of the PI, descriptions of the menu functions, and PI operation, refer to the Portable Interface Operator’s Manual (Part Number 165E1630–00).

NOTE:

Previously recorded information cannot be played back from the FA2100CVR while it is installed in the aircraft.

Using the following procedure, verify that the four following channels inputs are recording correctly, regardless of Audio Control Panel mode or audio (communications radio) selection: Channel 1: Channel 2: Channel 3: Channel 4: (1)

Connect the PI to the FA2100CVR’s GSE connector as shown in Figure 8.

(2)

Using the PI’s SELECT button, activate the Monitor Menu and turn HQ VOICE CH 1 ON. While someone is speaking into the Channel 1 source, verify that the audio is clear and distortion-free. Monitor the audio with the PI’s internal speaker or with a 600-ohm headset connected to the PI’s phone jack (an 8−ohm headset must be used for the 2100−1020−93 configuration).

(3)

Repeat this process for CH 2, CH 3, and HQ CAM CH 4.

NOTE:

5.3

Cockpit Spare Audio Input (3rd Crew Member, Public Address System) Co-Pilot’s Audio, Boom, Mask, and Hand-Held Microphone Input Pilot’s Audio, Boom, Mask and Hand-Held Microphone Input Cockpit Area Microphone (CAM) Input

The PI does not display ARINC 429 GMT or rotor speed in the Monitor Mode. This can only be done with the PI in the Playback Mode.

Flight Checkout Procedure

For flight checkout procedure, refer to section 8.0.

6.0

FA2100CVR READOUT

Previously recorded information cannot be read (played back) from the Model FA2100CVR while it is installed in the aircraft. This requirement is noted in ARINC Characteristic 757 and EUROCAE ED–56A, and is a security feature to protect the privacy rights of pilots and other crew members. The FA2100CVR must be removed from the aircraft, connected to an AC or DC source as appropriate, and connected to a Portable Interface (PI), Part Number 17TES0043, to play back previously recorded data. The following items are needed for FA2100CVR readout: PI, Part Number 17TES0043; Portable Interface Operator’s Manual, Part Number 165E1630–00; Cockpit Voice Recorder System Test Panel, Part Rev. 16

165E1846-00 Page 33

Installation & Operation Instruction Manual

Model FA2100CVR

Number 9300A860; Cable Assembly, Part Number 024E1122–00; and Component Maintenance Manual, Cockpit Voice Recorder, Model FA2100CVR, ATA 23–70–04. Instead of the 9300A860 Test Panel, the PI and a customer-fabricated cable to provide appropriate power to the FA2100CVR’s main (rear) connector can be used to play back previously recorded data. The Portable Interface Operator’s Manual, Part Number 165E1630–00, contains the procedures for using the PI to play back previously recorded FA2100CVR data.

7.0

OPERATING INSTRUCTIONS

The Model FA2100CVR has no controls or switches and its operation is completely automatic upon power-up. When the recorder is installed and wired in accordance with section 3.0 of this document, the recorder is ready for operation. The recorder will operate automatically until power is removed.

8.0

FLIGHT CHECKOUT PROCEDURE

Execution of a flight test may be required to approve/certify the FA2100CVR installation. A predetermined list of words and phrases used during normal pre-flight and in-flight operations should be prepared for use by the cockpit crew. It is important for participants to bear in mind that, to obtain a satisfactory recording on the area microphone channel, clear enunciation in a natural voice is essential.

8.1

Operational Notes

Depending on its part number, the FA2100CVR will preserve 30- or 120-minutes of recorded information. A test program not exceeding 30- or 120-minutes of recording time, depending on recorder version, should be planned prior to the test flight. The FA2100CVR circuit breaker may be pulled and reset as required to preserve the test recording on longer flights. The Test Director shall announce time and condition into the area microphone at the start of each condition, identify any significant events or warnings, and encourage conversation between crew members. CAUTION: If the aircraft is involved in an incident, do not attempt to remove or download data from the CVR at this time. Wait until the proper governing authorities arrive on scene and follow their instruction.

8.2 1.

Flight Checkout Pre‐ and Post‐Engine Start

a. Close FA2100CVR circuit breaker about three minutes before engine start. b. Perform the pilot’s “PRE-FLIGHT FUNCTIONAL CHECK” contained in section 5.1. c. Check and identify, by speaking into the area microphone and listening for playback at the headset jack, the airplane identification, date, and time. d. Check and identify the fire warning bell. Also, record a short excerpt of the pre-start checklist called out by the crew. e. Record the normal cockpit conversations for one minute after one engine has started. Each crew member shall identify himself by name. The Test Director shall announce airplane status and identify any warning sounds. 165E1846-00 Page 34

Rev. 16

Model FA2100CVR

f. 2.

Installation & Operation Instruction Manual

Open FA2100CVR circuit breaker.

Taxi, Takeoff, and Climb

a. Close FA2100CVR circuit breaker. Before releasing the brake, apply takeoff engine power and actuate the stick shaker with the test switch. The Test Director shall identify the event. b. Record normal crew conversations during takeoff. When airborne, identify Bulk Erase Test. Press ERASE button, demonstrating that FA2100CVR will not erase in flight. Verify by monitoring at FA2100CVR output jack. c. Open FA2100CVR circuit breaker. 3.

Cruise, Vmo or Mmo

a. Select cruise altitude. Close FA2100CVR circuit breaker. Disconnect auto-pilot and verify aural disconnect sound. Using the flight inter−phone facilities, each crew member shall identify himself and note that he is listening on his headset at a comfortable listening level. b. Select an ADF or VOR signal and identify these signals when they are being produced by the cockpit speakers at proper listening level. c. Climb to 25,000 feet. Each crew member will don his oxygen mask and will say “This is the pilot/co-pilot speaking through his oxygen mask microphone.” Repeat this test for the headset microphone and the hand-held microphone. d. Open FA2100CVR circuit breaker. 4.

Descent, Touchdown, and Rollout

a. Close FA2100CVR circuit breaker. b. At an appropriate altitude, accelerate until Mmo or Vmo clacker sounds and identify; reduce speed approximately 5 knots so that clacker stops. Hold this speed and have crew member identify flight status via the area microphone, to acquire a reasonable amount of recorded speed. c. Reduce thrust until landing gear warning horn sounds. The pilot will identify himself and warning device sounding. d. Reduce thrust until stall warning horn sounds. The pilot will identify himself and warning device sounding. e. Make a flight crew member announcement on the aircraft public address system advising cabin emergency descent. Conduct emergency descent to 12,000 feet. During this time, the co-pilot will give altitude and airspeed or mach number every 1,000 feet. The pilot will acknowledge and read-back the values given by the co-pilot. f.

Any audio signals identifying navigation and approach aids which are audible to in-flight crew headsets, (including the marker beacon signal) should be recorded for post-flight playback.

g. Open FA2100CVR circuit breaker. 5.

Post‐Flight

Remove FA2100CVR from aircraft and play stored data back via the Portable Interface (PI). Record flight data onto a format usable by the examiner/inspector, such as on a cassette. Rev. 16

165E1846-00 Page 35

Installation & Operation Instruction Manual

9.0

MAINTENANCE AND CALIBRATION

9.1

Recorder

Model FA2100CVR

The Model FA2100CVR does not require scheduled maintenance or calibration, except for periodic inspection/servicing of the Underwater Locator Device (see paragraph 9.3).

9.2

Data Download Using P/N: 17TES0078 Cable

CVR Download Cable, P/N: 17TES0078 can be used to download data while the recorder is on the aircraft using the Portable Interface Unit. The data in the CVR cannot be erase while using the cable. Refer to Figure 7 on setting up the cable between the CVR and the CVR Tray. To connect the Cable between the CVR and CVR Tray: 1) Ensure that aircraft power is removed from the CVR. 2) Disconnect and slide CVR from CVR Tray. 3) Connect the P1 side of the cable to the rear connector of the CVR (J1). 4) Connect the J1 side of the cable to the CVR Tray connector (P1). To download data from the CVR: 1)

Connect the Portable Interface Unit (PI), P/N:17TES0043 to the CVR GSE ATE Connector.

NOTE: The PI is connected to the CVR via a 10-foot cable that is plugged into the FA2100CVR’s front panel GSE ATE connector (refer to Figure 7). The PI receives power from the CVR when power is applied. 2) APPLY power to the system and activate the CVR. 3) ENSURE that the CVR Main Menu is present on the PI. 4) SELECT the CVR Playback Menu from the PI Main Menu. NOTE: The CVR data download can be a complete or partial download by rewinding back into the CVR memory. A complete download depends on the recorder: − A 30 minute recorder must be rewound to 30 minutes. − A 120 minute recorder must be rewound to 120 minutes. − A partial data download, rewind as far back as you need to go within the 30 or 120 minute recorder. 5) USE the Rewind button on the PI keypad and when the desired spot is reached, press the middle Select button on the PI keypad to stop rewind. 6) PRESS the red (Delete) button on the PI keypad to activate the channel monitor menu. 7) NAVIGATE to the File option using the Navigation keys on the PI keypad. 8) SELECT the File option to bring up the CVR File Control Menu and select the Copy function. 9) ENTER a new file name using the Navigation and Select buttons on the PI keypad. 165E1846-00 Page 36

Rev. 16

Model FA2100CVR

Installation & Operation Instruction Manual

10) SELECT Start option to open the CVR Copy Menu. 11) SELECT Start Copy to write the data to the new file on the memory disk. 12) OBSERVE that the Copy time is being displayed in seconds. 13) OBSERVE at the end of the Copy function that the PI returns to the Main Menu. After the data is downloaded to the PI the CVR must be reinstall into the CVR Tray as follows:

1) Remove power to the system to de-activate the CVR. 2) Remove the PI by removing the PI cable from the CVR front panel GSE ATE connector. 3) Remove the CVR Download Cable, P/N: 17TES0078 between the CVR and the CVR Tray. 4) Slide the CVR into the CVR Tray. 5) Perform Post−Installation Checkout according to Paragraph 4.0 of this manual.

Rev. 16

165E1846-00 Page 37

Installation & Operation Instruction Manual

NOTE: CVR Tray still installed in aircraft

Model FA2100CVR

J1 CVR TRAY

(View looking down)

CVR DOWNLOAD CABLE 17TES0078 (ARINC 757 installation only)

PORTABLE INTERFACE (PI) 17TES0043

P1

FA2100CVR

TO RECORDER GSE CONNECTOR DATA FROM RECORDER

Figure 9. On-Aircraft Setup for Data Download FA2100CVRs using a Portable Interface 9.3

Underwater Locator Device

The Model FA2100CVR is equipped with an Underwater Locator Device (ULD) that is approved to FAA TSO–C121. The ULD is mounted horizontally on the front of the CSMU for easy removal and for easy 165E1846-00 Page 38

Rev. 16

Installation & Operation Instruction Manual

Model FA2100CVR

viewing of the battery expiration date. The ULD requires functional testing and cleaning every 24 months. (Refer to Appendix C for information about the ULD Tester.) The ULD is equipped with a battery that has an expected life the same as of the beacon replacement date marked on the beacon label. Upon expiration of expected battery life, contact ULD manufacturer for replacement batteries, installation instructions, and re−certification.

9.4

Product Support

Mailing/Contact Information: L–3 Communications Aviation Recorders P.O. Box 3041 Sarasota, Florida 34230–3041 Attention: Product Support, Mail Stop 20

9.5

Telephone: Telefax: SITA: Web Site:

(941) 371–0811 (941) 377–5591 SRQLFCR www.L-3ar.com

Authorized Repair Facilities

Aviation Recorders performs repair and readout services for the Model FA2100CVR System. Items needing repair should be shipped to the following address: L-3 Communications Aviation Recorders 100 Cattleman Road Sarasota, Florida 34232 Attention: Repair Station Questions concerning FA2100CVR repair may be answered by calling the Aviation Recorders’ Repair Station at (941) 377–5517 or (941) 377–5579, or by calling the Product Support Department at (941) 371–0811. Readout Service is performed by the Repair Station. Aviation Recorders’ Authorized Repair Facilities have factory trained technicians who provide repair, readout, and loaner/rental services. Contact the Product Support Department for names and locations, or visit our web site at www.L-3AR.com for this and much more information.

9.6

Loaner/Rental Program

Aviation Recorders’ Authorized Repair Facilities are capable of providing loaner/rental FA2100CVRs. Also, the Aviation Recorders’ Product Support Group maintains a limited supply of FA2100CVRs available for rental.

Rev. 16

165E1846-00 Page 39

Installation & Operation Instruction Manual

Model FA2100CVR

THIS PAGE IS INTENTIONALLY LEFT BLANK

165E1846-00 Page 40

Rev. 16

Installation & Operation Instruction Manual

Model FA2100CVR

APPENDIX A − OUTLINE & DIMENSIONS MICROPHONES, CONTROL UNITS, & EXTERNAL PREAMPLIFIERS

Rev. 16

165E1846-00 Page A-1

Installation & Operation Instruction Manual

Model FA2100CVR

THIS PAGE IS INTENTIONALLY LEFT BLANK

165E1846-00 Page A-2

Rev. 16

S151–0020–00 S151–0030−00 S151–0040−00 S151–0050−00 S151–0060−00 S152–0020−00

(1)

S152–0030–00 S152–0030–01

(1, 2)

S152–0040–00 S161–0020–00 S161–0020–10 S161–0030–00 S161–0030–70 S161–0040–00 S161–0050–00 S161–0060–00 S161–0080–00 S161–1090−20 S161–1120–10 S161–1390–01 S162–0020–00 S162–0030–00 S162–0030–70 S162–0040–00

(1) (1)

(5) (3)

(5, 7) (4) (8) (1) (1) (1, 6) (1)

S251–1120–00

(7)

S251–1130–00 S251–1170–00

(7) (7)

S261–1120–00 S261–1130–00 S261–0050−00

(7)

S261–1121−00

(7)

(7) (7)

Figure A−1. Part Number Definition, Model S151/S161, Model S152/S162, and Model S251/S261 Control Units Rev. 16

165E1846-00 Page A-3

Attenuated Output

Filtered Connector Non−Filtered Connector

D− type Connector Circular Connector

Gray Black Brown (Boeing) Brown (ATR) Blue (DO328) Gray (BD100) Gray−Blue (Airbus) Embraer

Illuminated Non−Illuminated

Panel Height 1.125 Panel Height 2.25

Panel Thickness .25 Panel Thickness .125

COLOR

Reqs. S055 Microphone Reqs. S056 Microphone

Installation & Operation Instruction Manual

Model FA2100CVR

Installation & Operation Instruction Manual

Model FA2100CVR

Notes for Figure A-1: 1.

Model S152 and S162 Control Units are designed with a built‐in microphone.

2.

SXXX-XXXX-01 model Control Units are used with an 8‐Ohm, 0.21 inch Headphone Jack (J2).

3.

S161-XXXX-70 model Control Units contact L-3AR Product Support.

4.

S161-1390-01 model Control Unit is used with a Boomset Jack and has no Test Indicator Lamp.

5.

SXXX-XXXX-10 model Control Units are designed for use with dual recorder installations.

6.

S162-XXXX-70 model Control Units contact L-3AR Product Support.

7.

Requires 7 volts for illumination.

8.

S161-1390-01 replaces S161-1390-00 (obsolete). Requires 7 or 28 volts for illumination.

165E1846-00 Page A-4

Rev. 16

Installation & Operation Instruction Manual

Model FA2100CVR

5.00 MAX

.37 2.87

NAME PLATE AND MODIFICATIONS CONTROL UNIT MODEL S151 PNR: S151−XXXX−XX SER: XXXXXXXXX MFR: 06141 DATE: MMYYYY communications Sarasota, Florida

SWITCH

MODIFICATIONS 1 4 7 10 13

2D BAR CODE

2 5 8 11 14

3 6 9 12 15

TSO−C123a ED−56A

GREEN LAMP

SWITCH

COCKPIT VOICE RECORDER 2.250 +.000 –.030

HOLD 5 SEC

TEST

1.125  .002

HEADSET ERASE .56

5.375  .015

.18

+.000 5.750 –.020

41‐PIN, CIRCULAR, MS3112E20-41P FILTERED RECEPTACLE KEYWAY

2.11 1.05

.12 NOTES: 1. WEIGHT = 1.1 LBS.  0.1 LBS. 2. DIMENSIONS ARE IN INCHES

2.50

.07

3.00

905−E1019−18K

Figure A−2. Outline and Dimensions, Model S151 Control Unit Rev. 16

165E1846-00 Page A-5

Installation & Operation Instruction Manual

Model FA2100CVR

STANDARD INTERWIRING PER ARINC SPEC 757 VOICE RECORDER UNIT

2, 8

1 AMP

TO 115 VAC, 400 HZ TO AC COLD

5

OR TO DC POWER IN 28 VDC

5 AMPS

3

MODEL S151 CONTROL UNIT PUSH TO TEST PREAMP PWR GND PREAMP PWR HOT (+18 VDC REG) TEST INDICATOR + TEST INDICATOR – CHASSIS GND VOICE ERASE ”A” VOICE ERASE ”C” OUTPUT LO OUTPUT HI MIC INPUT LO MIC INPUT HI MIC BIAS MIC INPUT SHIELD

AUDIO MONITOR LO AUDIO MONITOR HI

4 A B C D E F G H J K L M N P R S T U V W X Y Z a b c d e f g h i j k m n p q r s

TO ANNUNCIATOR OR MAINT. COMPUTER FROM CAPTAIN’S CLOCK

SPARE MICROPHONE TO 3RD CREW MEMBER OR PA SYSTEM

10, 11 TO COPILOT MICROPHONE

10 TO PILOT MICROPHONE

6

10, 11 COCKPIT AREA MICROPHONE

10

t

MODEL S055 MICROPHONE MIC BIAS (WHITE) MIC HIGH (BLACK) MIC LOW (GREEN)

13

9

3

FROM ROTOR SPEED SENSOR

3, 7

BRAKE

GEAR

8

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57

115 VAC POWER IN HOT 115 VAC POWER IN COLD AUDIO OUT LO AUDIO OUT HI RECORD ON B RECORD ON A +28 VDC POWER IN STOP RECORDING PUSH TO TEST PREAMP PWR OUT GND PREAMP PWR OUT HOT (+18 VDC REG) TEST INDICATOR + TEST INDICATOR – CHASSIS GND

CVR FAULT GMT IN B (ARINC 429) LO GMT IN A (ARINC 429) HI

CHANNEL 1 LO CHANNEL 1 HI

CHANNEL 2 LO CHANNEL 2 HI

CHANNEL 3 LO CHANNEL 3 HI CHANNEL 4 LO CHANNEL 4 HI ROTOR SPEED IN LO ROTOR SPEED IN HI

12

INPUT CHANNEL 1

INPUT CHANNEL 2

INPUT CHANNEL 3 INPUT CHANNEL 4

VOICE ERASE ”A” VOICE ERASE ”C”

BULK ERASE INTERLOCK (TYPICAL)

Figure A−3. Interwiring Diagram, Voice Recorder Unit, S151 Control Unit, S055 Remote Microphone

165E1846-00 Page A-6

Rev. 16

Model FA2100CVR

Installation & Operation Instruction Manual

Notes for Figure A−3.: 1.

Recommended minimum wire size is #22; however, wire size #24 is electrically permissible ex­ cept for long‐run power leads where #18 wire is recommended (pins 2, 3, 9, & 17). Wire resist­ ance should not exceed 1 ohm for power leads and should not exceed 5 ohms for signal leads. All wiring should be MIL–W–22759 or MIL–C–27500.

2.

Only one power source is to be wired per aircraft. If 115 Vac, 400 Hz is supplied, connection is to be made to pin 2 & 3. If 28 Vdc is supplied, connection is to be made to pins 9. Shorting pins 1 & 2 is optional.

3.

Recorder ground connection to be within 1 foot of pin 17, heavy gauge wire. Shields to be grounded at the recorder using short connections. Pin 17 is used as +28 VDC return. Control unit may be grounded in the cockpit to a chassis ground.

4.

Jumper in aircraft connector. Without this jumper, the unit will not record or erase previously recorded information, bulk erase will not activate, and test will indicate NO–GO.

5.

Pin 3 is not a DC return and is not grounded in the recorder. (see Note 3)

6.

Pins p, q, and r may be jumpered. The control unit does not use these pins.

7.

Twisted shielded cable. Shields to be grounded at the airframe using short connections. Tie shields to existing single point GND use for Pin 17. (see Note 3)

8.

If the power source has battery back‐up, a means for terminating recording after a crash should be included in the aircraft wiring. Grounding pin 10 terminates recording within 10 minutes.

9.

BITE status output: ground = no fault, open = fault or CVR not installed.

10.

Audio input .05 Vrms - 3 Vrms maximum. (1Vrms nominal).

11.

Deleted

12.

In the Model FA2100, 2100-1010-( ) and 2100-102X-( ) configurations GMT is inputted as low speed (12.5 kbps) ARINC‐429 to pins 25 and 26. In addition, the -02 versions can also ac­ cept GMT as an FSK signal combined with the audio input signals on either Channel 1 or Chan­ nel 3. In all CVR configurations, the Audio Compressor card provides both 150 (1 sec resolu­ tion) and 125 (0.1 min. resolution) for 429 GMT inputs.

13.

S055 Panel‐mount microphones are equipped with a Cannon 150949-1002 Twinax receptacle. Mating connector is a Cannon 150900-0303. Recommended cable is WTWC 2CE2419.2SJ, L-3 P/N: 024-98-00294.

Rev. 16

165E1846-00 Page A-7

Installation & Operation Instruction Manual

Model FA2100CVR

4.88 MAX

.45 2.88

NAME PLATE AND MODIFICATIONS CONTROL UNIT MODEL S161

MODIFICATIONS

PNR: S161−XXXX−XX SER: XXXXXXXXX MFR: 06141 DATE: MMYYYY

SWITCH

1 4 7 10 13

2D BAR CODE

communications Sarasota, Florida

STATIC ALERT LABEL FARSIDE

2 5 8 11 14

3 6 9 12 15

TSO−C123a ED−56A

SWITCH

GREEN LAMP COCKPIT VOICE RECORDER

2.250 +.000 –.030

1.125  .005

TEST

ERASE

HOLD 5 SEC

HEADSET

.56

5.365  .005 +.000 5.750 –.020 41‐PIN, CIRCULAR, MS3112E20-41P FILTERED RECEPTACLE

.19

S161−0090−20

COCKPIT VOICE RECORDER

TEST 2.10 MAX

HOLD 5 SEC

B O O M S E T

ERASE

1.04

.12

2.50 3.00

NOTES: 1. WEIGHT = 1.1 LBS.  0.1 LBS. 2. DIMENSIONS ARE IN INCHES 3. The dimensions for the S161 Control Units are the same except for S161−1390−01 (see sheet 2 of 2). 4. The additional faceplate provide a representation of the S161−0090−20. 905−E2367−18F

Figure A−4. (Sheet 1 of 2) Outline and Dimensions, Model S161 Control Unit 165E1846-00 Page A-8

Rev. 16

Installation & Operation Instruction Manual

Model FA2100CVR

S161−1390−01 CONTROL UNIT MODEL S161 PNR: S161−1390−01 SER: XXXXXXXXX MFR: 06141 DATE: MMYYYY communications Sarasota, Florida

MODIFICATIONS

2D BAR CODE

1 4 7 10 13

2 5 8 11 14

3 6 9 12 15

TSO−C123a ED−56A

NAME PLATE AND MODIFICATIONS

NOTES: 1. DIMENSIONS ARE IN INCHES 2. The dimensions for S161−1390−01 only

Figure A‐4. (Sheet 2 of 2) Outline and Dimensions, Model S161 Control Unit Rev. 16

165E1846-00 Page A-9

Installation & Operation Instruction Manual

Model FA2100CVR

STANDARD INTERWIRING PER ARINC SPEC 757

(Data Link wiring IAW ARINC Spec 757−4 Paragraph 3.9) VOICE RECORDER UNIT (2100−1025−02, 12 wiring shown for reference)

2, 8

1 AMP

TO 115 VAC, 400 HZ TO AC COLD

5

OR TO DC POWER IN 28 VDC

5 AMPS

3

MODEL S161 CONTROL UNIT PUSH TO TEST PREAMP PWR GND PREAMP PWR HOT (+18 VDC REG) TEST INDICATOR + TEST INDICATOR – CHASSIS GND VOICE ERASE ”A” VOICE ERASE ”C” OUTPUT LO OUTPUT HI MIC INPUT LO MIC INPUT HI MIC BIAS

AUDIO MONITOR LO AUDIO MONITOR HI

16

LIGHTING COMMON

16

LIGHTING 28V

4 A B C D E F G H J K L M N P R S T U V W X Y Z a b c d e f g h i j k m n p q r s

TO ANNUNCIATOR OR MAINT. COMPUTER FROM CAPTAIN’S CLOCK

SPARE MICROPHONE TO 3RD CREW MEMBER OR PA SYSTEM

10, 11 TO COPILOT MICROPHONE

10 TO PILOT MICROPHONE

6

10, 11 COCKPIT AREA MICROPHONE

10

t

MODEL S056 MICROPHONE MIC BIAS (WHITE) MIC HIGH (BLACK) MIC LOW (SHEILD))

13

9

3

FROM ROTOR SPEED SENSOR

3, 7

BRAKE

GEAR

8

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57

115 VAC POWER IN HOT 115 VAC POWER IN COLD AUDIO OUT LO AUDIO OUT HI RECORD ON B RECORD ON A +28 VDC POWER IN STOP RECORDING PUSH TO TEST PREAMP PWR OUT GND PREAMP PWR OUT HOT (+18 VDC REG) TEST INDICATOR + TEST INDICATOR – CHASSIS GND

CVR FAULT GMT IN B (ARINC 429) LO GMT IN A (ARINC 429) HI

12

14 17 CHANNEL 1 LO DATA LINK FAULT CHANNEL 1 HI DATA LINK IN (429) B DATA LINK IN (429) A CHANNEL 2 LO CHANNEL 2 HI OMS IN (429) B OMS IN (429) A

INPUT CHANNEL 1

14 INPUT CHANNEL 2

14

CHANNEL 3 LO

INPUT CHANNEL CHANNEL 3 HI 3 RES - CVR REPLAY INHIBIT/ 18 FDR INHIBIT CHANNEL 4 LO INPUT CHANNEL 4 CHANNEL 4 HI ROTOR SPEED IN LO ROTOR SPEED IN HI DATA LINK V1/OMS B OUT 14 DATA LINK V1/OMS A OUT

VOICE ERASE ”A” DATA LINK VALID VOICE ERASE ”C”

15 14 15

BULK ERASE INTERLOCK (TYPICAL)

Figure A−5. Interwiring Diagram, Voice Recorder Unit, S161 Control Unit, S056 Remote Microphone

165E1846-00 Page A-10

Rev. 16

Model FA2100CVR

Installation & Operation Instruction Manual

Notes for Figure A−5.: 1.

Recommended minimum wire size is #22; however, wire size #24 is electrically permissible ex­ cept for long‐run power leads where #18 wire is recommended (pins 2, 3, 9, & 17). Wire resist­ ance should not exceed 1 ohm for power leads and should not exceed 5 ohms for signal leads. All wiring should be MIL–W–22759 or MIL–C–27500.

2.

Only one power source is to be wired per aircraft. If 115 Vac, 400 Hz is supplied, connection is to be made to pin 2 & 3. If 28 Vdc is supplied, connection is to be made to pins 9. Shorting pins 1 & 2 is optional.

3.

Recorder ground connection to be within 1 foot of pin 17, heavy gauge wire. Shields to be grounded at the recorder using short connections. Pin 17 is used as +28 VDC return. Control unit may be grounded in the cockpit to a chassis ground.

4.

Jumper in aircraft connector. Without this jumper, the unit will not record or erase previously recorded information, bulk erase will not activate, and test will indicate NO–GO.

5.

Pin 3 is not a DC return and is not grounded in the recorder. (see Note 3)

6.

Pins p, q, and r may be jumpered. The control unit does not use these pins.

7.

Twisted shielded cable. Shields to be grounded at the airframe using short connections. Tie shields to existing single point GND use for Pin 17. (see Note 3)

8.

If the power source has battery back‐up, a means for terminating recording after a crash should be included in the aircraft wiring. Grounding pin 10 terminates recording within 10 minutes.

9.

BITE status output: ground = no fault, open = fault or CVR not installed.

10.

Audio input .05 Vrms - 3 Vrms maximum. (1Vrms nominal).

11.

Deleted

12.

In the Model FA2100, 2100-1010-( ) and 2100-102X-( ) configurations GMT is inputted as low speed (12.5 kbps) ARINC‐429 to pins 25 and 26. In addition, the -02 versions can also ac­ cept GMT as an FSK signal combined with the audio input signals on either Channel 1 or Chan­ nel 3. In all CVR configurations, the Audio Compressor card provides both 150 (1 sec resolu­ tion) and 125 (0.1 min. resolution) for 429 GMT inputs.

13.

S055 microphone installations required double shielding. For S056 installations, double shield­ ing is not required for new installations, however, it may be left in place for retrofit installations.

14.

Data Link and OMS input and out put signals are applicable only to p/n: 2100-1025-( ) and it is used in conjunction with the S161-1390-00 installations. When data link valid (pin 56) is grounded and data link communications (pins 33 and 34) are receiving data, then ARINC-429 label 350 Bit 16 will be set at zero = good

15.

The S161-0030-70 Control Unit contact L-3AR Product Support.

16.

Only used on S161-1390-01 with the Illuminated Panel.

17.

Data Link Fault = Open/Ground discrete, Asserted is Open.

18.

Pin 44 may be used to inhibit audio download when pins 7 and 8 are not jumpered and is appli­ cable only to p/n: 2100-1025-( ). For further details , refer to ARINC 757-4, Attachment 6, Item 21. (see Note 4)

Rev. 16

165E1846-00 Page A-11

Installation & Operation Instruction Manual

Model FA2100CVR

STANDARD INTERWIRING PER ARINC SPEC 757 VOICE RECORDER UNIT (2100−1010/1020−( ) wiring shown for reference)

2, 8

1 AMP

TO 115 VAC, 400 HZ TO AC COLD

5

OR TO DC POWER IN 28 VDC

5 AMPS

3

MODEL S161 CONTROL UNIT PUSH TO TEST PREAMP PWR GND PREAMP PWR HOT (+18 VDC REG) TEST INDICATOR + TEST INDICATOR – CHASSIS GND VOICE ERASE ”A” VOICE ERASE ”C” OUTPUT LO OUTPUT HI MIC INPUT LO MIC INPUT HI MIC BIAS

AUDIO MONITOR LO AUDIO MONITOR HI

4 A B C D E F G H J K L M N P R S T U V W X Y Z a b c d e f g h i j k m n p q r s

TO ANNUNCIATOR OR MAINT. COMPUTER FROM CAPTAIN’S CLOCK

SPARE MICROPHONE TO 3RD CREW MEMBER OR PA SYSTEM

10, 11 TO COPILOT MICROPHONE

10 TO PILOT MICROPHONE

6

10, 11 COCKPIT AREA MICROPHONE

10

t

MODEL S056 MICROPHONE MIC BIAS (WHITE) MIC HIGH (BLACK) MIC LOW (SHEILD))

13

9

3

FROM ROTOR SPEED SENSOR

3, 7

BRAKE

GEAR

8

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57

115 VAC POWER IN HOT 115 VAC POWER IN COLD AUDIO OUT LO AUDIO OUT HI RECORD ON B RECORD ON A +28 VDC POWER IN STOP RECORDING PUSH TO TEST PREAMP PWR OUT GND PREAMP PWR OUT HOT (+18 VDC REG) TEST INDICATOR + TEST INDICATOR – CHASSIS GND

CVR FAULT GMT IN B (ARINC 429) LO GMT IN A (ARINC 429) HI

CHANNEL 1 LO CHANNEL 1 HI DATA LINK IN (429) B DATA LINK IN (429) A CHANNEL 2 LO CHANNEL 2 HI OMS IN (429) B OMS IN (429) A CHANNEL 3 LO CHANNEL 3 HI CHANNEL 4 LO CHANNEL 4 HI ROTOR SPEED IN LO ROTOR SPEED IN HI DATA LINK V1/OMS B OUT DATA LINK V1/OMS A OUT

VOICE ERASE ”A” DATA LINK VALID VOICE ERASE ”C”

12

INPUT CHANNEL 1

14 INPUT CHANNEL 2

14 INPUT CHANNEL 3 INPUT CHANNEL 4

14

15 14 15

BULK ERASE INTERLOCK (TYPICAL)

Figure A−6. Interwiring Diagram, Voice Recorder Unit, S161 Control Unit, S056 Remote Microphone

165E1846-00 Page A-12

Rev. 16

Model FA2100CVR

Installation & Operation Instruction Manual

Notes for Figure A−6: 1.Recommended minimum wire size is #22; however, wire size #24 is electrically permissible except for long-run power leads where #18 wire is recommended (pins 2, 3, 9, & 17). Wire resistance should not exceed 1 ohm for power leads and should not exceed 5 ohms for signal leads. All wiring should be MIL–W–22759 or MIL–C–27500. 2.Only one power source is to be wired per aircraft. If 115 Vac, 400 Hz is supplied, no connection is to be made to pin 9. If 28 Vdc is supplied, no connection is to be made to pins 2 & 3. Shorting pins 1 & 2 is optional. 3.Single ground point. Ground connection to be within 1 foot of pin 17, heavy gauge wire. 4.Jumper in aircraft connector. Without this jumper, the unit will not record or erase previously recorded information, bulk erase will not activate, and test will indicate NO–GO. 5.Pin 3 is not a DC return and is not grounded in the recorder. 6.Pins p, q, and r may be jumpered. The control unit does not use these pins. 7.Twisted shielded cable. Shields to be grounded at the recorder using short connections. 8.If the power source has battery back-up, a means for terminating recording after a crash should be included in the aircraft wiring. Grounding pin 10 terminates recording within 10 minutes. 9.BITE status output: ground = no fault, open = fault or CVR not installed. 10.Audio input .05 Vrms − 3 Vrms maximum. (1Vrms nominal). 11.Per FAA Action Notice A8300.56 dated Jan. 24, 1990, the wiring to Channels 1 and 3 may be transposed; that is, Channel 1 will be Pilot and Channel 3 will be Third Crew Member or PA System. 12.In the Model A200S, this option is not available. In the Model FA2100, 2100−1010−( ) and 2100−1020−( ) configurations GMT is inputted as low speed (12.5 kbps) ARINC-429 to pins 25 and 26. In addition, the −02 versions can also accept GMT as an FSK signal combined with the audio input signals on either Channel 1 or Channel 3. In all CVR configurations, the 205E1849−( ) Audio Compressor card provides both 150 (1 sec resolution) and 125 (0.1 min. resolution) for 429 GMT inputs. 13.S055 microphone installations required double shielding. For S056 installations, double shielding is not required for new installations, however, it may be left in place for retrofit installations. 14.Data Link and OMS input and out put signals are applicable to p/n: 2100-1025-02 only, and it is used in conjunction with the S161-1390-00 for Airbus installations. 15.The S161-0030-70 does not use Bulk Erase. This Control Unit is used with the FA2100CVR P/N: 2100-1020-93.

Rev. 16

165E1846-00 Page A-13

Installation & Operation Instruction Manual

Model FA2100CVR

5.00 MAX

.37 2.88

NAME PLATE AND MODIFICATIONS CONTROL UNIT MODEL S251 PNR: S251−XXXX−XX SER: XXXXXXXXX MFR: 06141 DATE: MMYYYY communications Sarasota, Florida

MODIFICATIONS 1 4 7 10 13

2D BAR CODE

3 6 9 12 15

TSO−C123a ED−56A

GREEN LAMP

SWITCH

1.125

2 5 8 11 14

HOLD 5 SEC

SWITCH

STATIC ALERT LABEL FARSIDE

COCKPIT VOICE RECORDER

TEST

HEADSET ERASE

.562

5.375

.188

5.75 37 PIN ‐SUB DC37P‐TYPE FILTERED CONNECTOR.

.971 MAX. .47 2.50 .28

2.68

.062 MIN.

NOTES: 1. WEIGHT = 0.8 LBS MAX. 2. DIMENSIONS ARE IN INCHES. 905−E1120−18L

Figure A−7. Outline and Dimensions, Model S251 Control Unit 165E1846-00 Page A-14

Rev. 16

Installation & Operation Instruction Manual

Model FA2100CVR

STANDARD INTERWIRING PER ARINC SPEC 757 VOICE RECORDER UNIT 1 AMP

TO 115 VAC, 400 HZ TO AC COLD

2, 7

5

OR TO DC POWER IN 28 VDC

5 AMPS

3

MODEL S251 CONTROL UNIT PUSH TO TEST PREAMP PWR GND PREAMP PWR HOT (+18 VDC REG) TEST INDICATOR + TEST INDICATOR – CHASSIS GND VOICE ERASE ”A” VOICE ERASE ”C”

12

4

OUTPUT LO OUTPUT HI

9 10

MIC NO.1 INPUT LO

22

MIC NO.1 INPUT HI MIC NO.1 BIAS MIC NO.1 INPUT SHIELD

4

AUDIO MONITOR LO AUDIO MONITOR HI

27 28 1 2 6 7 8 13 14 15 19 20 21 23 24 25 26 29 33 34 35 36 37

LIGHTING COMMON LIGHTING 5V

7

30 17 18 12 11 16 32 31

3

8 TO ANNUNCIATOR OR MAINT. COMPUTER

3 5

FROM CAPTAIN’S CLOCK

SPARE MICROPHONE TO 3RD CREW MEMBER OR PA SYSTEM

9, 10 TO COPILOT MICROPHONE

9 TO PILOT MICROPHONE

9, 10 FROM ROTOR SPEED SENSOR

3, 6 MODEL S055 MICROPHONE BRAKE

MIC BIAS (WHITE) MIC HIGH (BLACK) MIC LOW (GREEN)

115 VAC POWER IN HOT 115 VAC POWER IN COLD AUDIO OUT LO AUDIO OUT HI RECORD ON B RECORD ON A +28 VDC POWER IN STOP RECORDING PUSH TO TEST PREAMP PWR OUT GND PREAMP PWR OUT HOT (+18 VDC REG) TEST INDICATOR + TEST INDICATOR – CHASSIS GND

CVR FAULT GMT IN B (ARINC 429) LO GMT IN A (ARINC 429) HI

30 CHANNEL 1 LO 31 32 CHANNEL 1 HI 33 34 35 CHANNEL 2 LO 36 37 CHANNEL 2 HI 38 39

INPUT CHANNEL 2

40 41 CHANNEL 3 LO 42

GEAR

45 46 47 48 49 50 51 52 53 54 55 56 57

11

INPUT CHANNEL 1

INPUT CHANNEL 3

43 CHANNEL 3 HI 44

COCKPIT AREA MICROPHONE

9

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29

CHANNEL 4 LO CHANNEL 4 HI ROTOR SPEED IN LO ROTOR SPEED IN HI

INPUT CHANNEL 4

VOICE ERASE ”A” VOICE ERASE ”C”

BULK ERASE INTERLOCK (TYPICAL)

13

Figure A−8. Interwiring Diagram, Voice Recorder Unit, S251 Control Unit, S055 Remote Microphone Rev. 16

165E1846-00 Page A-15

Installation & Operation Instruction Manual

Model FA2100CVR

Notes for Figure A−8.: 1.

Recommended minimum wire size is #22; however, wire size #24 is electrically permissible ex­ cept for long‐run power leads where #18 wire is recommended (pins 2, 3, 9, & 17). Wire resist­ ance should not exceed 1 ohm for power leads and should not exceed 5 ohms for signal leads. All wiring should be MIL–W–22759 or MIL–C–27500.

2.

Only one power source is to be wired per aircraft. If 115 Vac, 400 Hz is supplied, connection is to be made to pin 2 & 3. If 28 Vdc is supplied, connection is to be made to pins 9. Shorting pins 1 & 2 is optional.

3.

Recorder ground connection to be within 1 foot of pin 17, heavy gauge wire. Shields to be grounded at the recorder using short connections. Pin 17 is used as +28 VDC return. Control unit may be grounded in the cockpit to a chassis ground.

4.

Jumper in aircraft connector. Without this jumper, the unit will not record or erase previously recorded information, bulk erase will not activate, and test will indicate NO–GO.

5.

Pin 3 is not a DC return and is not grounded in the recorder. (see Note 3)

6.

Twisted shielded cable. Shields to be grounded at the airframe using short connections. Tie shields to existing single point GND use for Pin 17. (see Note 3)

7.

If the power source has battery back‐up, a means for terminating recording after a crash should be included in the aircraft wiring. Grounding pin 10 terminates recording within 10 minutes.

8.

BITE status output: ground = no fault, open = fault or CVR not installed.

9.

Audio input .05 Vrms - 3 Vrms maximum. (1Vrms nominal).

10.

Deleted

11.

In the Model FA2100, 2100-1010-( ) and 2100-102X-( ) configurations GMT is inputted as low speed (12.5 kbps) ARINC‐429 to pins 25 and 26. In addition, the -02 versions can also ac­ cept GMT as an FSK signal combined with the audio input signals on either Channel 1 or Chan­ nel 3. In all CVR configurations, the Audio Compressor card provides both 150 (1 sec resolu­ tion) and 125 (0.1 min. resolution) for 429 GMT inputs.

12.

Use pins 35 (+) and 36 (-) for optional 5V lighting. Incandescent illumination is to be inte­ grated into panel and is to provide even lighting of all graphics. Lighting color is to have CZE chromaticity values of: x =.420 ± .020, y = .395 ± .020 using 5.0 Vdc ± .2 vdc, 600ma Max.

13.

S055 Panel‐mount microphones are equipped with a Cannon 150949-1002 Twinax receptacle. Mating connector is a Cannon 150900-0303. Recommended cable is WTWC 2CE2419.2SJ, L-3 P/N: 024-98-00294.

165E1846-00 Page A-16

Rev. 16

Installation & Operation Instruction Manual

Model FA2100CVR

NAME PLATE AND MODIFICATIONS CONTROL UNIT MODEL S261 PNR: S261−1120−00 SER: XXXXXXXXX MFR: 06141 DATE: MMYYYY communications Sarasota, Florida

MODIFICATIONS 1 4 7 10 13

2D BAR CODE

PNR: S261−1130−00 SER: XXXXXXXXX MFR: 06141 DATE: MMYYYY

MODIFICATIONS 1 4 7 10 13

2D BAR CODE

communications Sarasota, Florida

SWITCH

2 5 8 11 14

3.75

3 6 9 12 15

TSO−C123a ED−56A

CONTROL UNIT MODEL S261 PNR: S261−1121−00 SER: XXXXXXXXX MFR: 06141 DATE: MMYYYY

3 6 9 12 15

TSO−C123a ED−56A

CONTROL UNIT MODEL S261

communications Sarasota, Florida

2 5 8 11 14

MODIFICATIONS 1 4 7 10 13

2D BAR CODE

2 5 8 11 14

3 6 9 12 15

STATIC ALERT LABE FARSIDE

TSO−C123a ED−56A

GREEN LAMP SWITCH

1.13

HOLD 5 SEC

COCKPIT VOICE RECORDER

HEADSET ERASE

TEST

37 PIN ‐SUB DC37P‐TYPE FILTERED CONNECTOR.

5.75

1.03 ± 0.04

2.26 .29 NOTES: 1. WEIGHT = 0.5 LBS MAX. 2. DIMENSIONS ARE IN INCHES. S261-1120-00A S261-1130-00A

Figure A−9. Outline and Dimensions, Model S261 Control Unit Rev. 16

165E1846-00 Page A-17

Installation & Operation Instruction Manual

Model FA2100CVR

STANDARD INTERWIRING PER ARINC SPEC 757

(Data Link wiring IAW ARINC Spec 757−4 Paragraph 3.9) VOICE RECORDER UNIT (2100−1025−02, −12, −22 & −24 wiring shown for reference) 1 AMP

TO 115 VAC, 400 HZ TO AC COLD

5

OR

2, 7

TO DC POWER IN 28 VDC

5 AMPS

3

MODEL S261 CONTROL UNIT PUSH TO TEST PREAMP PWR GND PREAMP PWR HOT (+18 VDC REG) TEST INDICATOR + TEST INDICATOR – CHASSIS GND VOICE ERASE ”A” VOICE ERASE ”C”

12

4 30 17 18 12 11 16 32 31

OUTPUT LO OUTPUT HI

9 10

MIC NO.1 INPUT LO

22

MIC NO.1 INPUT HI MIC NO.1 BIAS

4

AUDIO MONITOR LO AUDIO MONITOR HI

27 28 1 2 6 7 8 13 14 15 19 20 21 23 24 25 26 29 33 34 35 36 37

LIGHTING COMMON LIGHTING 5V

7

3

8 TO ANNUNCIATOR OR MAINT. COMPUTER

3 5

FROM CAPTAIN’S CLOCK

SPARE MICROPHONE TO 3RD CREW MEMBER OR PA SYSTEM

9, 10 TO COPILOT MICROPHONE

9 TO PILOT MICROPHONE

COCKPIT AREA MICROPHONE FROM ROTOR SPEED SENSOR

3, 6 MODEL S056 MICROPHONE BRAKE

MIC BIAS (WHITE) MIC HIGH (BLACK) MIC LOW (SHIELD)

30 31 32 33 34 35 36 37 38 39 40 41 42 43 44

9, 10

9

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29

GEAR

115 VAC POWER IN HOT 115 VAC POWER IN COLD AUDIO OUT LO AUDIO OUT HI RECORD ON B RECORD ON A +28 VDC POWER IN STOP RECORDING/RIPS ACTIVE INPUT PUSH TO TEST PREAMP PWR OUT GND PREAMP PWR OUT HOT (+18 VDC REG) TEST INDICATOR + TEST INDICATOR – CHASSIS GND

CVR FAULT GMT IN B (ARINC 429) LO GMT IN A (ARINC 429) HI

RIPS FAULT INPUT CHANNEL 1 LO DATA LINK FAULT CHANNEL 1 HI DATA LINK IN (429) B DATA LINK IN (429) A CHANNEL 2 LO

11 7

14

INPUT CHANNEL 1

14

INPUT CHANNEL CHANNEL 2 HI 2 7 RIPS MAINTENANCE INPUT OMS IN (429) B 14 OMS IN (429) A 7 CHANNEL 3 LO INPUT RIPS PRESENT INPUT CHANNEL CHANNEL 3 HI 3 CVR REPLAY INHIBIT/FDR IN­ 15 HIBIT CHANNEL 4 LO INPUT CHANNEL CHANNEL 4 HI 4 ROTOR SPEED IN LO ROTOR SPEED IN HI DATA LINK V1/OMS B OUT 14 DATA LINK V1/OMS A OUT

45 46 47 48 49 50 51 52 53 54 55 VOICE ERASE ”A” 56 DATA LINK VALID 57 VOICE ERASE ”C”

14

BULK ERASE INTERLOCK (TYPICAL)

13

Figure A−10. Interwiring Diagram, Voice Recorder Unit, S261 Control Unit, S056 Remote Microphone 165E1846-00 Page A-18

Rev. 16

Model FA2100CVR

Installation & Operation Instruction Manual

Notes for Figure A−10.: 1.

Recommended minimum wire size is #22; however, wire size #24 is electrically permissible ex­ cept for long‐run power leads where #18 wire is recommended (pins 2, 3, 9, & 17). Wire resist­ ance should not exceed 1 ohm for power leads and should not exceed 5 ohms for signal leads. All wiring should be MIL–W–22759 or MIL–C–27500.

2.

Only one power source is to be wired per aircraft. If 115 Vac, 400 Hz is supplied, connection is to be made to pin 2 & 3. If 28 Vdc is supplied, connection is to be made to pins 9. Shorting pins 1 & 2 is optional.

3.

Recorder ground connection to be within 1 foot of pin 17, heavy gauge wire. Shields to be grounded at the recorder using short connections. Pin 17 is used as +28 VDC return. Control unit may be grounded in the cockpit to a chassis ground.

4.

Jumper in aircraft connector. Without this jumper, the unit will not record or erase previously recorded information, bulk erase will not activate, and test will indicate NO–GO.

5.

Pin 3 is not a DC return and is not grounded in the recorder. (see Note 3)

6.

Twisted shielded cable. Shields to be grounded at the airframe using short connections. Tie shields to existing single point GND use for Pin 17. (see Note 3)

7.

Using the the Stop Recording function, the grounded pin 10 terminates recording within 10 minutes. When using the RIPS Active function the CVR has a backup power source or RIPS available, pins 10, 29, 38 and 42 will be used for the RIPS Status Monitoring.

8.

BITE status output: ground = no fault, open = fault or CVR not installed.

9.

Audio input .05 Vrms - 3 Vrms maximum. (1Vrms nominal).

10.

Deleted

11.

In the Model FA2100, 2100-1010-( ) and 2100-102X-( ) configurations GMT is inputted as low speed (12.5 kbps) ARINC‐429 to pins 25 and 26. In addition, the -02 versions can also ac­ cept GMT as an FSK signal combined with the audio input signals on either Channel 1 or Chan­ nel 3. In all CVR configurations, the Audio Compressor card provides both 150 (1 sec resolu­ tion) and 125 (0.1 min. resolution) for 429 GMT inputs.

12.

Use pins 35 (-) and 36 (+) for optional 5V lighting. Incandescent illumination is to be inte­ grated into panel and is to provide even lighting of all graphics. Lighting color is to have CZE chromaticity values of: x =.420 ± .020, y = .395 ± .020 using 5.0 Vdc ± .2 vdc, 600ma Max.

13.

S055 microphone installations required double shielding. For S056 installations, double shield­ ing is not required for new installations, however, it may be left in place for retrofit installations.

14.

Data Link and OMS input and out put signals are applicable only to p/n: 2100-1025-( ).When data link valid (pin 56) is grounded and data link communications (pins 33 and 34) are receiving data, then ARINC-429 label 350 Bit 16 will be set at zero = good.

15.

Pin 44 may be used to inhibit audio download when pins 7 and 8 are not jumpered and is appli­ cable only to p/n: 2100-1025-( ). For further details , refer to ARINC 757-4, Attachment 6, Item 21. (see Note 4)

Rev. 16

165E1846-00 Page A-19

Installation & Operation Instruction Manual

Model FA2100CVR

STANDARD INTERWIRING PER ARINC SPEC 757 VOICE RECORDER UNIT (2100−1010/1020−( ) wiring shown for reference) 1 AMP

TO 115 VAC, 400 HZ TO AC COLD

5

OR

2, 7

TO DC POWER IN 28 VDC

5 AMPS

3

MODEL S261 CONTROL UNIT PUSH TO TEST PREAMP PWR GND PREAMP PWR HOT (+18 VDC REG) TEST INDICATOR + TEST INDICATOR – CHASSIS GND VOICE ERASE ”A” VOICE ERASE ”C”

4

OUTPUT LO OUTPUT HI

9 10

MIC NO.1 INPUT LO

22

MIC NO.1 INPUT HI MIC NO.1 BIAS

4

AUDIO MONITOR LO AUDIO MONITOR HI

27 28 1 2 6 7 8 13 14 15 19 20 21 23 24 25 26 29 33 34 35 36 37

12

7

30 17 18 12 11 16 32 31

3

TO ANNUNCIATOR OR MAINT. COMPUTER FROM CAPTAIN’S CLOCK

3 5

SPARE MICROPHONE TO 3RD CREW MEMBER OR PA SYSTEM

9, 10

TO COPILOT MICROPHONE

9 TO PILOT MICROPHONE

9, 10

9 3, 6 MODEL S056 MICROPHONE BRAKE

115 VAC POWER IN HOT 115 VAC POWER IN COLD AUDIO OUT LO AUDIO OUT HI RECORD ON B RECORD ON A +28 VDC POWER IN STOP RECORDING

PUSH TO TEST PREAMP PWR OUT GND PREAMP PWR OUT HOT (+18 VDC REG) 15 TEST INDICATOR + 16 TEST INDICATOR – 17 CHASSIS GND 18 19 20 21 22 23 CVR FAULT 24 25 GMT IN B (ARINC 429) LO 11 26 GMT IN A (ARINC 429) HI 27 28 29 30 CHANNEL 1 LO 31 32 CHANNEL 1 HI 33 34 35 CHANNEL 2 LO 36 37 CHANNEL 2 HI 38 39 40 41 CHANNEL 3 LO 42 43 CHANNEL 3 HI 44

COCKPIT AREA MICROPHONE FROM ROTOR SPEED SENSOR

MIC BIAS (WHITE) MIC HIGH (BLACK) MIC LOW (SHIELD)

8

1 2 3 4 5 6 7 8 9 10 11 12 13 14

45 46 47 48 49 50 51 52 53 54 55 56 57

CHANNEL 4 LO CHANNEL 4 HI ROTOR SPEED IN LO ROTOR SPEED IN HI

INPUT CHANNEL 1

INPUT CHANNEL 2

INPUT CHANNEL 3 INPUT CHANNEL 4

VOICE ERASE ”A” VOICE ERASE ”C”

GEAR

BULK ERASE INTERLOCK (TYPICAL)

13

Figure A−11. Interwiring Diagram, Voice Recorder Unit, S261 Control Unit, S056 Remote Microphone 165E1846-00 Page A-20

Rev. 16

Model FA2100CVR

Installation & Operation Instruction Manual

Notes for Figure A−11.: 1.Recommended minimum wire size is #22; however, wire size #24 is electrically permissible except for long-run power leads where #18 wire is recommended (pins 2, 3, 9, & 17). Wire resistance should not exceed 1 ohm for power leads and should not exceed 5 ohms for signal leads. All wiring should be MIL–W–22759 or MIL–C–27500. 2.Only one power source is to be wired per aircraft. If 115 Vac, 400 Hz is supplied, no connection is to be made to pin 9. If 28 Vdc is supplied, no connection is to be made to pins 2 & 3. Shorting pins 1 & 2 is optional. 3.Single ground point. Ground connection to be within 1 foot of pin 17, heavy gauge wire. 4.Jumper in aircraft connector. Without this jumper, the unit will not record or erase previously recorded information, bulk erase will not activate, and test will indicate NO–GO. 5.Pin 3 is not a DC return and is not grounded in the recorder. 6.Twisted shielded cable. Shields to be grounded at the recorder using short connections. 7.If the power source has battery back-up, a means for terminating recording after a crash should be included in the aircraft wiring. Grounding pin 10 terminates recording within 10 minutes. 8.BITE status output: ground = no fault, open = fault or CVR not installed. 9.Audio input .05 Vrms − 3 Vrms maximum. (1Vrms nominal). 10.Per FAA Action Notice A8300.56 dated Jan. 24, 1990, the wiring to Channels 1 and 3 may be transposed; that is, Channel 1 will be Pilot and Channel 3 will be Third Crew Member or PA System. 11.In the Model A200S, this option is not available. In the Model FA2100, 2100−1010−( ) and 2100−1020−( ) configurations GMT is inputted as low speed (12.5 kbps) ARINC-429 to pins 25 and 26. In addition, the −02 versions can also accept GMT as an FSK signal combined with the audio input signals on either Channel 1 or Channel 3. In all CVR configurations, the 205E1849−( ) Audio Compressor card provides both 150 (1 sec resolution) and 125 (0.1 min. resolution) for 429 GMT inputs. 12.Use pins 35 (+) and 36 (−) for optional 5V lighting. 13.S055 microphone installations required double shielding. For S056 installations, double shielding is not required for new installations, however, it may be left in place for retrofit installations.

Rev. 16

165E1846-00 Page A-21

Installation & Operation Instruction Manual

Model FA2100CVR

4.88 MAX

.45 2.88

NAME PLATE AND MODIFICATIONS CONTROL UNIT MODEL S152 PNR: S152−00X0−X0 SER: XXXXXXXXX MFR: 06141 DATE: MMYYYY communications Sarasota, Florida

MODIFICATIONS 1 4 7 10 13

2D BAR CODE

2 5 8 11 14

3 6 9 12 15

TSO−C123a ED−56A

SWITCH

SWITCH

STATIC ALERT LABEL FARSIDE

GREEN LAMP

ÍÍÍ ÍÍÍ ÍÍÍ

COCKPIT VOICE RECORDER

2.250 +.000 –.030

TEST HOLD 5 SEC

1.125  .005

ERASE

HEADSET

.56

MICROPHONE 5.365  .005

.19

+.000 5.750 –.020

41‐PIN, CIRCULAR, MS3112E20-41P FILTERED RECEPTACLE

2.10 MAX 1.04

.12 NOTES: 1. WEIGHT = 1.1 LBS.  0.1 LBS. 2. DIMENSIONS ARE IN INCHES

2.50 3.00

905−E1926−18B

Figure A−12. Outline and Dimensions, Model S152 Control Unit 165E1846-00 Page A-22

Rev. 16

Installation & Operation Instruction Manual

Model FA2100CVR

4.88 MAX

.45 2.88

NAME PLATE AND MODIFICATIONS CONTROL UNIT MODEL S162 PNR: S162−00X0−X0 SER: XXXXXXXXX MFR: 06141 DATE: MMYYYY

MODIFICATIONS 1 4 7 10 13

2D BAR CODE

communications Sarasota, Florida

2 5 8 11 14

3 6 9 12 15

TSO−C123a ED−56A

SWITCH

SWITCH STATIC ALERT LABEL FARSIDE

GREEN LAMP

ÍÍÍ ÍÍÍ ÍÍÍ

COCKPIT VOICE RECORDER

2.250 +.000 –.030

TEST HOLD 5 SEC

1.125  .005

ERASE

HEADSET

.56

MICROPHONE 5.365  .005

.19

+.000 5.750 –.020

41‐PIN, CIRCULAR, MS3112E20-41P FILTERED RECEPTACLE

2.10 MAX 1.04

.12

2.50 3.00

NOTES: 1. WEIGHT = 1.1 LBS.  0.1 LBS. 2. DIMENSIONS ARE IN INCHES 3. The dimensions for the S162 Control Units are the same.

905−E2387−18A

Figure A−13. Outline and Dimensions, Model S162 Control Unit Rev. 16

165E1846-00 Page A-23

Installation & Operation Instruction Manual

Model FA2100CVR

STANDARD INTERWIRING PER ARINC SPEC 757 VOICE RECORDER UNIT

2, 8

1 AMP

TO 115 VAC, 400 HZ TO AC COLD

5

OR TO DC POWER IN 28 VDC

5 AMPS

3

MODEL S152/S162 CONTROL UNIT 13

4

PUSH TO TEST PREAMP PWR GND PREAMP PWR HOT (+18 VDC REG) TEST INDICATOR + TEST INDICATOR – CHASSIS GND

A B C D E F

VOICE ERASE “A” VOICE ERASE “C”

G H J K L M N P R S T U V W X Y Z a b c d e f g h i j k m n p q r s

OUTPUT LO OUTPUT HI MIC INPUT LO MIC INPUT HI MIC BIAS MIC INPUT SHIELD

AUDIO MONITOR LO AUDIO MONITOR HI

INTERNAL MIC HI INTERNAL MIC BIAS

8

9 3

TO ANNUNCIATOR OR MAINT. COMPUTER FROM CAPTAIN’S CLOCK

SPARE MICROPHONE TO 3RD CREW MEMBER OR PA SYSTEM

10, 11 TO COPILOT MICROPHONE

10 TO PILOT MICROPHONE

10, 11

6

COCKPIT AREA MICROPHONE

10

t

FROM ROTOR SPEED SENSOR

3, 7 BRAKE

GEAR

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57

115 VAC POWER IN HOT 115 VAC POWER IN COLD AUDIO OUT LO AUDIO OUT HI RECORD ON B RECORD ON A +28 VDC POWER IN STOP RECORDING PUSH TO TEST 13 PREAMP PWR OUT GND PREAMP PWR OUT HOT (+18 VDC REG) TEST INDICATOR + TEST INDICATOR – CHASSIS GND

CVR FAULT GMT IN B (ARINC 429) LO GMT IN A (ARINC 429) HI

CHANNEL 1 LO CHANNEL 1 HI

CHANNEL 2 LO CHANNEL 2 HI

CHANNEL 3 LO CHANNEL 3 HI CHANNEL 4 LO CHANNEL 4 HI ROTOR SPEED IN LO ROTOR SPEED IN HI

12

INPUT CHANNEL 1

INPUT CHANNEL 2

INPUT CHANNEL 3 INPUT CHANNEL 4

VOICE ERASE “A”

13

VOICE ERASE “C”

13

BULK ERASE INTERLOCK (TYPICAL)

Figure A−14. Interwiring Diagram, Voice Recorder Unit, S152/S162 Control Unit with Internal Microphone 165E1846-00 Page A-24

Rev. 16

Model FA2100CVR

Installation & Operation Instruction Manual

Notes for Figure A−14.: 1.

Recommended minimum wire size is #22; however, wire size #24 is electrically permissible ex­ cept for long‐run power leads where #18 wire is recommended (pins 2, 3, 9, & 17). Wire resist­ ance should not exceed 1 ohm for power leads and should not exceed 5 ohms for signal leads. All wiring should be MIL–W–22759 or MIL–C–27500.

2.

Only one power source is to be wired per aircraft. If 115 Vac, 400 Hz is supplied, connection is to be made to pin 2 & 3. If 28 Vdc is supplied, connection is to be made to pins 9. Shorting pins 1 & 2 is optional.

3.

Recorder ground connection to be within 1 foot of pin 17, heavy gauge wire. Shields to be grounded at the recorder using short connections. Pin 17 is used as +28 VDC return. Control unit may be grounded in the cockpit to a chassis ground.

4.

Jumper in aircraft connector. Without this jumper, the unit will not record or erase previously recorded information, bulk erase will not activate, and test will indicate NO–GO.

5.

Pin 3 is not a DC return and is not grounded in the recorder. (see Note 3)

6.

Pins p, q, and r may be jumpered. The control unit does not use these pins.

7.

Twisted shielded cable. Shields to be grounded at the airframe using short connections. Tie shields to existing single point GND use for Pin 17. (see Note 3)

8.

If the power source has battery back‐up, a means for terminating recording after a crash should be included in the aircraft wiring. Grounding pin 10 terminates recording within 10 minutes.

9.

BITE status output: ground = no fault, open = fault or CVR not installed.

10.

Audio input .05 Vrms - 3 Vrms maximum. (1Vrms nominal).

11.

Deleted

12.

In the Model FA2100, 2100-1010-( ) and 2100-102X-( ) configurations GMT is inputted as low speed (12.5 kbps) ARINC‐429 to pins 25 and 26. In addition, the -02 versions can also ac­ cept GMT as an FSK signal combined with the audio input signals on either Channel 1 or Chan­ nel 3. In all CVR configurations, the Audio Compressor card provides both 150 (1 sec resolu­ tion) and 125 (0.1 min. resolution) for 429 GMT inputs.

13.

S162-XXXX-70 model Control Units are used with an 8‐Ohm, Headphone Jack, have no Bulk Erase Switch, Test Switch and Test Indicator Lamp.

Rev. 16

165E1846-00 Page A-25

Installation & Operation Instruction Manual

Model FA2100CVR

STANDARD INTERWIRING PER ARINC SPEC 757

(Data Link wiring IAW ARINC Spec 757−4 Paragraph 3.9) VOICE RECORDER UNIT (2100−1026−02 wiring shown for reference)

2, 8

TO 115 VAC, 400 HZ TO AC COLD

1 AMP

5

OR TO DC POWER IN 28 VDC

5 AMPS

3

CONTROL UNIT* 4 PUSH TO TEST PREAMP PWR GND PREAMP PWR HOT (+18 VDC REG) TEST INDICATOR + TEST INDICATOR – CHASSIS GND VOICE ERASE ”A” VOICE ERASE ”C”

TO ANNUNCIATOR OR MAINT. COMPUTER FROM CAPTAIN’S CLOCK

SPARE MICROPHONE TO 3RD CREW MEMBER OR PA SYSTEM

AUDIO MONITOR LO AUDIO MONITOR HI

16 16

9

3

OUTPUT LO OUTPUT HI MIC INPUT LO MIC INPUT HI MIC BIAS

LIGHTING COMMON

10, 11 TO COPILOT MICROPHONE

LIGHTING 28V

10 TO PILOT MICROPHONE

* Customer − Furnished

6

10, 11 COCKPIT AREA MICROPHONE

10

FROM ROTOR SPEED SENSOR

3, 7 MICROPHONE* MIC BIAS (WHITE) MIC HIGH (BLACK) MIC LOW (SHEILD))

13

BRAKE

GEAR

8

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57

115 VAC POWER IN HOT 115 VAC POWER IN COLD AUDIO OUT LO AUDIO OUT HI RECORD ON B RECORD ON A +28 VDC POWER IN STOP RECORDING/RIPS ACTIVE INPUT PUSH TO TEST PREAMP PWR OUT GND PREAMP PWR OUT HOT (+18 VDC REG) TEST INDICATOR + TEST INDICATOR – CHASSIS GND

CVR FAULT GMT IN B (ARINC 429) LO GMT IN A (ARINC 429) HI

12

14 RIPS FAULT INPUT CHANNEL 1 LO DATA LINK FAULT CHANNEL 1 HI DATA LINK IN (429) B DATA LINK IN (429) A CHANNEL 2 LO

17 INPUT CHANNEL 1

14

CHANNEL 2 HI RIPS MAINTENANCE INPUT OMS IN (429) B OMS IN (429) A

INPUT CHANNEL 2

14

CHANNEL 3 LO INPUT RIPS PRESENT INPUT CHANNEL CHANNEL 3 HI 3 RES - CVR REPLAY INHIBIT/ PLAYBACK INHIBIT CHANNEL 4 LO INPUT CHANNEL 4 CHANNEL 4 HI ROTOR SPEED IN LO ROTOR SPEED IN HI DATA LINK V1/OMS B OUT DATA LINK V1/OMS A OUT

VOICE ERASE ”A” DATA LINK VALID VOICE ERASE ”C”

18

14

15 14 15

BULK ERASE INTERLOCK (TYPICAL)

Figure A−15. Interwiring Diagram, P/N: 2100−1026−02 Cockpit Voice Recorder with RIPS, Customer Furnished Control Unit and Microphone

165E1846-00 Page A-26

Rev. 16

Model FA2100CVR

Installation & Operation Instruction Manual

Notes for Figure A−13.: 1.

Recommended minimum wire size is #22; however, wire size #24 is electrically permissible ex­ cept for long‐run power leads where #18 wire is recommended (pins 2, 3, 9, & 17). Wire resist­ ance should not exceed 1 ohm for power leads and should not exceed 5 ohms for signal leads. All wiring should be MIL–W–22759 or MIL–C–27500.

2.

Only one power source is to be wired per aircraft. If 115 Vac, 400 Hz is supplied, connection is to be made to pin 2 & 3. If 28 Vdc is supplied, connection is to be made to pins 9. Shorting pins 1 & 2 is optional.

3.

Recorder ground connection to be within 1 foot of pin 17, heavy gauge wire. Shields to be grounded at the recorder using short connections. Pin 17 is used as +28 VDC return. Control unit may be grounded in the cockpit to a chassis ground.

4.

Jumper in aircraft connector. Without this jumper, the unit will not record or erase previously recorded information, bulk erase will not activate, and test will indicate NO–GO.

5.

Pin 3 is not a DC return and is not grounded in the recorder. (see Note 3)

6.

Pins p, q, and r may be jumpered. The control unit does not use these pins.

7.

Twisted shielded cable. Shields to be grounded at the airframe using short connections. Tie shields to existing single point GND use for Pin 17. (see Note 3)

8.

Using the the Stop Recording function, the grounded pin 10 terminates recording within 10 minutes. When using the RIPS Active function the CVR has a backup power source or RIPS available, pins 10, 29, 38 and 42 will be used for the RIPS Status Monitoring.

9.

BITE status output: ground = no fault, open = fault or CVR not installed.

10.

Audio input .05 Vrms - 3 Vrms maximum. (1Vrms nominal).

11.

Deleted

12.

GMT is inputted as low speed (12.5 kbps) ARINC‐429 to pins 25 and 26. In addition, the GMT FSK signal is combined with the audio input signals on either Channel 1 or Channel 3. The Au­ dio Compressor card provides both 150 (1 sec resolution) and 125 (0.1 min. resolution) for 429 GMT inputs.

13.

S055 microphone installations required double shielding. For S056 installations, double shield­ ing is not required for new installations, however, it may be left in place for retrofit installations.

14.

Data Link and OMS input and out put signals are applicable only. When data link valid (pin 56) is grounded and data link communications (pins 33 and 34) are receiving data, then ARINC-429 label 350 Bit 16 will be set at zero = good

15.

The S161-0030-70 does not use Bulk Erase if used.

16.

Only used with the Illuminated Panel.

17.

Data Link Fault = Open/Ground discrete, Asserted is Open.

18.

Pin 44 may be used to inhibit audio download when pins 7 and 8 are not jumpered and is appli­ cable only to p/n: 2100-1026-( ). For further details , refer to ARINC 757-4, Attachment 6, Item 21. (see Note 4)

Rev. 16

165E1846-00 Page A-27

Installation & Operation Instruction Manual

Model FA2100CVR

STANDARD INTERWIRING PER ARINC SPEC 757A

(Data Link wiring IAW ARINC Spec 757A Paragraph 3.9)

VOICE RECORDER UNIT (2100−1027−02 wiring shown for reference)

2, 8

1 AMP

TO 115 VAC, 400 HZ TO AC COLD

5

OR TO DC POWER IN 28 VDC

5 AMPS

3

28 VDC RETURN

4

CONTROL UNIT PUSH TO TEST PREAMP PWR GND PREAMP PWR HOT (+18 VDC REG)

CHASSIS GND VOICE ERASE ”A” VOICE ERASE ”C” OUTPUT LO OUTPUT HI MIC INPUT LO MIC INPUT HI MIC BIAS

AUDIO MONITOR LO AUDIO MONITOR HI

15 15

LIGHTING COMMON LIGHTING 28V

8

A B C D E F G H J K L M N P R S T U V W X Y Z a b c d e f g h i j k m n p q r s

9 3 TO ANNUNCIATOR OR MAINT. COMPUTER FROM CAPTAIN’S CLOCK

SPARE MICROPHONE TO 3RD CREW MEMBER OR PA SYSTEM

10, 11 TO COPILOT MICROPHONE

10 TO PILOT MICROPHONE

10, 11

6

COCKPIT AREA MICROPHONE FROM ROTOR SPEED SENSOR

t

3, 7 MICROPHONE MIC BIAS (WHITE) MIC HIGH (BLACK) MIC LOW (SHEILD))

13

BRAKE

GEAR

1 115 VAC POWER IN COLD 5 2 115 VAC POWER IN HOT 28 VDC RETURN/SIGNAL GROUND 3 4 5 AUDIO OUT LO AUDIO OUT HI 6 RECORD ON B 7 RECORD ON A 8 9 +28 VDC POWER IN 10 STOP RECORDING/RIPS ACTIVE INPUT 11 12 PUSH TO TEST 13 PREAMP PWR OUT GND 14 PREAMP PWR OUT HOT (+18 VDC REG) 15 16 17 CHASSIS GND 3 18 19 20 21 22 23 CVR FAULT 24 25 GMT IN B (ARINC 429) LO 12 26 GMT IN A (ARINC 429) HI 27 28 16 29 RIPS FAULT INPUT 30 CHANNEL 1 LO INPUT CHANNEL 31 DATA LINK FAULT 1 32 CHANNEL 1 HI 33 DATA LINK IN (429) B 14 34 DATA LINK IN (429) A 35 CHANNEL 2 LO INPUT CHANNEL 36 2 37 CHANNEL 2 HI RIPS MAINTENANCE INPUT 38 OMS IN (429) B 39 14 OMS IN (429) A 40 41 CHANNEL 3 LO INPUT 42 RIPS PRESENT INPUT CHANNEL 3 43 CHANNEL 3 HI RES - CVR REPLAY INHIBIT/ 17 44 PLAYBACK INHIBIT 45 CHANNEL 4 LO INPUT CHANNEL 46 4 47 CHANNEL 4 HI 48 ROTOR SPEED IN LO 49 ROTOR SPEED IN HI 50 DATA LINK V1/OMS B OUT 14 51 DATA LINK V1/OMS A OUT 52 53 54 VOICE ERASE ”A” 55 56 DATA LINK VALID 14 57 VOICE ERASE ”C”

BULK ERASE INTERLOCK (TYPICAL)

Figure A−16. Interwiring Diagram, Cockpit Voice Recorder Unit S161 Control Unit and S056 Microphone For Airbus A350 Aircraft

165E1846-00 Page A-28

Rev. 16

Model FA2100CVR

Installation & Operation Instruction Manual

Notes for Figure A−14: 1.

Recommended minimum wire size is #22; however, wire size #24 is electrically permissible ex­ cept for long-run power leads where #18 wire is recommended (pins 3, 9, & 17). Wire resist­ ance should not exceed 1 ohm for DC power leads and should not exceed 5 ohms for other leads. All wiring should be MIL-W-22759 or MIL-C-27500.

2.

If 115 VAC, 400 Hz is supplied, connection is to be made to pins 2 & 1. If 28 VDC is supplied, connection is to be made to pins 9 and 3.

3.

Recorder Chassis ground connection to be within 1 foot of pin 17, with heavy gauge wire. Shields to be grounded at the recorder using short connections. Note that Pin 3 is used as +28 VDC return. Control unit may be grounded in the cockpit to a local chassis ground.

4.

Record enable jumper in aircraft connector. Without this jumper, the unit will not record or erase previously recorded information, bulk erase will not activate, and test will indicate NO­GO..

5.

Pin 3 is used for DC power return and is not connected to chassis ground within the recorder. (see Note 3). Pin 1 is used for AC power return and is not connected to chassis ground within the recorder. All power input and return pins (2 & 1, 9 & 3), are galvanically insulated from the conductive chassis ground connection.

6.

The Control Unit pre­amp attenuation program pins are not used..

7.

Twisted shielded cable. Shields to be grounded at the airframe using short connections. Tie shields to existing single point GND used for Pin 17. (see Note 3)

8.

If the power source has battery back‐up, a means for terminating recording after a crash should be included in the aircraft wiring. Grounding pin 10 terminates recording within 10 minutes.

9.

BITE status output: ground = no fault, open = fault or CVR not installed.

10.

Audio input .05 Vrms - 3 Vrms maximum. (1Vrms nominal).

11.

Per FAA Action Notice A8300.56 dated Jan. 24, 1990, the wiring to Channels 1 and 3 may be transposed; that is, Channel 1 will be Pilot and Channel 3 will be Third Crew Member or PA System.

12.

In the Model 2100-1027-( ) configurations GMT is inputted as low speed (12.5 kbps) ARINC‐429 to pins 25 and 26. In addition, the -02 versions can also accept GMT as an FSK signal combined with the audio input signals on either Channel 1 or Channel 3. In all CVR con­ figurations, the recorder accepts both label 150 (1 sec resolution) and label 125 (0.1 min. resolu­ tion) for 429 GMT inputs. If both are present, label 150 will be used. Any FSK input will be used only if there is no valid ARINC 429 GMT input..

13.

External microphone connections to control unit.

14.

Data Link and OMS input and output signals are applicable to p/n: 2100-1027-( ). When data link valid (pin 56) is grounded and data link communications (pins 32 and 34) are receiving data, then ARINC-429 label 350/352 Bit 16 will be set at zero = good

15.

Control Unit front panel illumination control..

16.

Data Link Fault = Open/Ground discrete, Asserted is Open.

17.

Pin 44 may be used to inhibit audio download when pins 7 and 8 are not jumpered and is applic­ able to p/n: 2100­1027­( ).

Rev. 16

165E1846-00 Page A-29

Installation & Operation Instruction Manual

Model FA2100CVR

5.000  .030

4.528  .020

.236  .020

.236  .020 .201‐.195 DIA. 4 HOLES

2.746  .030

C.G.

1.968  .020

1.20  .06

NAMEPLATE AND MODIFICATIONS

.374  .030 .389  .020

PREAMPLIFIER MODEL S150 PNR: S150−0020−00 SER: XXXXXXXXX MFR: 06141 DATE: MMYYYY

2D BAR CODE

communications Sarasota, Florida

MS3112E8‐3S OR EQUIVALENT

MODIFICATIONS 1 4 7 10 13

2 5 8 11 14

3 6 9 12 15

MS3112E14‐19S OR EQUIVALENT

TSO−C123a ED−56A

3.937  .030

.531  .020

1.727  .030 .860  .020

C.G.

.55  .06

1.778  .020 2X .125  .020

2.45  .06 3.378  .020

Part Number S150−0020−00

Housing Color

Weight (+ 0.1 lbs.)

Black

0.7 lbs.

NOTES: 1. DIMENSIONS ARE IN INCHES.

905−E0986−18D

Figure A−17. Outline and Dimensions, Model S150 External Preamplifier Module 165E1846-00 Page A-30

Rev. 16

Installation & Operation Instruction Manual

Model FA2100CVR

STANDARD INTERWIRING (No Control Unit) VOICE RECORDER UNIT 1 AMP

TO 115 VAC 400HZ TO AC COLD

2. 7

OR TO DC POWER IN 28 VDC

5

5 AMPS

3

MODEL S150 EXTERNAL PREAMPLIFIER PREAMPLIFIER J2 PREAMP PWR GND PREAMP PWR (+18 VDC REGULATED)

4 7 B A

CHASSIS GND

F

OUTPUT LOW

D

OUTPUT HIGH

C

8

3 TO ANNUNCIATOR OR MAINT. COMPUTER

PREAMPLIFIER J1 MICROPHONE INPUT LO

C

MICROPHONE INPUT HI

A

MICROPHONE BIAS

B

FROM CAPTAIN’S CLOCK

SPARE MICROPHONE TO 3RD CREW MEMEBER OR PA SYSTEM

NOTE: CONNECT OUTER SHIELD TO CONNECTOR SHELL

9, 10 TO COPILOT MICROPHONE

9 TO PILOT MICROPHONE

9, 10 COCKPIT AREA MICROPHONE

9 MODEL S055 MICROPHONE

FROM ROTOR SPEED SENSOR

3, 6

MIC. BIAS(WHITE) MIC HIGH (BLACK) MIC. LOW (GREEN)

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57

115 VAC POWER IN HOT 115 VAC POWER IN COLD AUDIO OUT LO AUDIO OUT HI RECORD ON B RECORD ON A +28 VDC POWER IN STOP RECORDING PUSH TO TEST PREAMP PWR OUT GND PREAMP PWR OUT HOT (+18 VDC REG) TEST INDICATOR + 11 TEST INDICATOR – CHASSIS GND

CVR FAULT GMT IN B (ARINC 429) LO GMT IN A (ARINC 429) HI

CHANNEL 1 LO

12

INPUT CHANNEL 1

CHANNEL 1 HI

CHANNEL 2 LO

INPUT CHANNEL 2

CHANNEL 2 HI

CHANNEL 3 LO

INPUT CHANNEL 3

CHANNEL 3 HI CHANNEL 4 LO CHANNEL 4 HI ROTOR SPEED IN LO ROTOR SPEED IN HI

INPUT CHANNEL 4

VOICE ERASE ”A” VOICE ERASE ”C”

13

Figure A−18. Interwiring Diagram, Voice Recorder Unit, S150 External Preamplifier, S055 Remote Microphone Rev. 16

165E1846-00 Page A-31

Installation & Operation Instruction Manual

Model FA2100CVR

Notes for Figure A−18.: 1.

Recommended minimum wire size is #22; however, wire size #24 is electrically permissible ex­ cept for long‐run power leads where #18 wire is recommended (pins 2, 3, 9, & 17). Wire resist­ ance should not exceed 1 ohm for power leads and should not exceed 5 ohms for signal leads. All wiring should be MIL–W–22759 or MIL–C–27500.

2.

Only one power source is to be wired per aircraft. If 115 Vac, 400 Hz is supplied, connection is to be made to pin 2 & 3. If 28 Vdc is supplied, connection is to be made to pins 9. Shorting pins 1 & 2 is optional.

3.

Recorder ground connection to be within 1 foot of pin 17, heavy gauge wire. Shields to be grounded at the recorder using short connections. Pin 17 is used as +28 VDC return. Control unit may be grounded in the cockpit to a chassis ground.

4.

Jumper in aircraft connector. Without this jumper, the unit will not record or erase previously recorded information, bulk erase will not activate, and test will indicate NO‐GO.

5.

Pin 3 is not a DC return and is not grounded in the recorder. (see Note 3)

6.

Twisted shielded cable. Shields to be grounded at the airframe using short connections. Tie shields to existing single point GND use for Pin 17. (see Note 3)

7.

If the power source has battery back‐up, a means for terminating recording after a crash should be included in the aircraft wiring. Grounding pin 10 terminates recording within 10 minutes.

8.

BITE status output: Ground = no fault, Open = fault or CVR not installed.

9.

Audio input .05 Vrms - 3 Vrms maximum. (1Vrms nominal).

10.

Deleted

11.

Test Indicator +/- lines (pins 15 & 16) only provide +12 Vdc, 1ma output to illuminate the Control Unit Test Lamp. (This is not sufficient to light an external Annunciator lamp.)

12.

In the Model FA2100, 2100-1010-( ) and 2100-102X-( ) configurations GMT is inputted as low speed (12.5 kbps) ARINC‐429 to pins 25 and 26. In addition, the -02 versions can also ac­ cept GMT as an FSK signal combined with the audio input signals on either Channel 1 or Chan­ nel 3. In all CVR configurations, the Audio Compressor card provides both 150 (1 sec resolu­ tion) and 125 (0.1 min. resolution) for 429 GMT inputs.

13.

S055 Panel‐mount microphones are equipped with a Cannon 150949-1002 Twinax receptacle. Mating connector is a Cannon 150900-0303. Recommended cable is WTWC 2CE2419.2SJ, L-3 P/N: 024-98-00294.

165E1846-00 Page A-32

Rev. 16

Installation & Operation Instruction Manual

Model FA2100CVR

4.99

4.53

.23

.23 0.196 DIA. 4 HOLES

2.74 1.97

NAMEPLATE AND MODIFICATIONS PREAMPLIFIER MODEL S160 PNR: S160−0020−00 SER: XXXXXXXXX MFR: 06141 DATE: MMYYYY communications Sarasota, Florida

MODIFICATIONS 1 4 7 10 13

2D BAR CODE

2 5 8 11 14

.39

3 6 9 12 15

SOURIAU 8525-10R-8B-3ASN009 SOURIAU 825-10R-14B-19SN009

TSO−C123a ED−56A

3.92

.54  .020

1.75

2X 1.00

1.78  .05 .06 3.38  .05

Part Number

Housing Color

Weight (+ 0.1 lbs.)

S160−0020−00

Black

0.65 lbs.

NOTES: 1. DIMENSIONS ARE IN INCHES. S160−0020−00A

Figure A−19. Outline and Dimensions, Model S160 External Preamplifier Module Rev. 16

165E1846-00 Page A-33

Installation & Operation Instruction Manual

Model FA2100CVR

STANDARD INTERWIRING (No Control Unit) VOICE RECORDER UNIT 1 AMP

TO 115 VAC 400HZ TO AC COLD OR

2. 7

TO DC POWER IN 28 VDC

5

5 AMPS

3

MODEL S160 EXTERNAL PREAMPLIFIER PREAMPLIFIER J2 PREAMP PWR GND PREAMP PWR (+18 VDC REGULATED)

4 7 B A

CHASSIS GND

F

OUTPUT LOW

D

OUTPUT HIGH

C

8

3 TO ANNUNCIATOR OR MAINT. COMPUTER

PREAMPLIFIER J1 MICROPHONE INPUT LO

C

MICROPHONE INPUT HI

A

MICROPHONE BIAS

B

FROM CAPTAIN’S CLOCK

SPARE MICROPHONE TO 3RD CREW MEMEBER OR PA SYSTEM

9, 10 TO COPILOT MICROPHONE

9 TO PILOT MICROPHONE

9, 10 COCKPIT AREA MICROPHONE

9 MODEL S056 MICROPHONE

FROM ROTOR SPEED SENSOR

3, 6

MIC. BIAS(WHITE) MIC HIGH (BLACK) MIC. LOW (GREEN)

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57

115 VAC POWER IN HOT 115 VAC POWER IN COLD AUDIO OUT LO AUDIO OUT HI RECORD ON B RECORD ON A +28 VDC POWER IN STOP RECORDING PUSH TO TEST PREAMP PWR OUT GND PREAMP PWR OUT HOT (+18 VDC REG) TEST INDICATOR + 11 TEST INDICATOR – CHASSIS GND

CVR FAULT GMT IN B (ARINC 429) LO GMT IN A (ARINC 429) HI

CHANNEL 1 LO CHANNEL 1 HI

CHANNEL 2 LO CHANNEL 2 HI

CHANNEL 3 LO CHANNEL 3 HI CHANNEL 4 LO CHANNEL 4 HI ROTOR SPEED IN LO ROTOR SPEED IN HI

12

INPUT CHANNEL 1

INPUT CHANNEL 2

INPUT CHANNEL 3 INPUT CHANNEL 4

VOICE ERASE ”A” VOICE ERASE ”C”

13

Figure A−20. Interwiring Diagram, Voice Recorder Unit, S160 External Preamplifier, S056 Remote Microphone 165E1846-00 Page A-34

Rev. 16

Model FA2100CVR

Installation & Operation Instruction Manual

Notes for Figure A−20.: 1.

Recommended minimum wire size is #22; however, wire size #24 is electrically permissible ex­ cept for long‐run power leads where #18 wire is recommended (pins 2, 3, 9, & 17). Wire resist­ ance should not exceed 1 ohm for power leads and should not exceed 5 ohms for signal leads. All wiring should be MIL–W–22759 or MIL–C–27500.

2.

Only one power source is to be wired per aircraft. If 115 Vac, 400 Hz is supplied, connection is to be made to pin 2 & 3. If 28 Vdc is supplied, connection is to be made to pins 9. Shorting pins 1 & 2 is optional.

3.

Recorder ground connection to be within 1 foot of pin 17, heavy gauge wire. Shields to be grounded at the recorder using short connections. Pin 17 is used as +28 VDC return. Control unit may be grounded in the cockpit to a chassis ground.

4.

Jumper in aircraft connector. Without this jumper, the unit will not record or erase previously recorded information, bulk erase will not activate, and test will indicate NO‐GO.

5.

Pin 3 is not a DC return and is not grounded in the recorder. (see Note 3)

6.

Twisted shielded cable. Shields to be grounded at the airframe using short connections. Tie shields to existing single point GND use for Pin 17. (see Note 3)

7.

If the power source has battery back‐up, a means for terminating recording after a crash should be included in the aircraft wiring. Grounding pin 10 terminates recording within 10 minutes.

8.

BITE status output: Ground = no fault, Open = fault or CVR not installed.

9.

Audio input .05 Vrms - 3 Vrms maximum. (1Vrms nominal).

10.

Deleted

11.

Test Indicator +/- lines (pins 15 & 16) only provide +12 Vdc, 1ma output to illuminate the Control Unit Test Lamp. (This is not sufficient to light an external Annunciator lamp.)

12.

In the Model FA2100, 2100-1010-( ) and 2100-102X-( ) configurations GMT is inputted as low speed (12.5 kbps) ARINC‐429 to pins 25 and 26. In addition, the -02 versions can also ac­ cept GMT as an FSK signal combined with the audio input signals on either Channel 1 or Chan­ nel 3. In all CVR configurations, the Audio Compressor card provides both 150 (1 sec resolu­ tion) and 125 (0.1 min. resolution) for 429 GMT inputs.

13.

S055 microphone installations required double shielding. For S056 installations, double shield­ ing is not required for new installations, however, it may be left in place for retrofit installations.

Rev. 16

165E1846-00 Page A-35

Installation & Operation Instruction Manual

.50

Model FA2100CVR

1.09

ÉÉÉÉ ÉÉÉÉ ÉÉÉ ÅÅ ÉÉÉÉ ÉÉÉ ÅÅ ÉÉÉÉ ÉÉÉ ÅÅ ÉÉÉÉ

1.12 30 1.19 .84 DIA

.42 DIA 1

2.25

cL

FOAM DAMPER

.92 15

.64

SHIELDED WIRE, 22 AWG TWISTED PAIR, SEE CHART FOR LENGTH MINIUM

MIC LOW (INNER SHIELD) PIGTAIL (GREEN) MIC HI (BLACK)

.700

cL MIC BIAS +6V (WHITE) MIC SHIELD (OUTER SHIELD) PIGTAIL (YELLOW)

NAMEPLATE 6–32 THD X .22 DEEP (2 PLACES)

MICROPHONE MODEL S055 PNR S055−00XX−00 SER XXXXXXXXXX MFR 06141 DMF MMYYYY

NOTES: 1 2.

communications Sarasota, Florida, USA

INDICATED PORTION OF MICROPHONE MUST BE UNOBSTUCTED FOR PROPER OPERATION. DIMENSIONS ARE IN INCHES.

Part Number

Housing Color

2D BAR CODE TSO−C123a ED−56A

905−E1300−18K

Weight (+/−0.1 lbs.)

Minimum Cable Length

S055−0065−00

Gray − No. 36116*

0.2 lbs

17”

S055−0066−00

Brown, ATR−42

0.2 lbs

17”

S055−0067−00

Black − No. 37038*

0.2 lbs

17”

S055−0067−01

Black − No. 37038*

0.2 lbs

70”

S055−0068−00

Brown, Medium (Boeing)

0.2 lbs

17”

* PER MIL-STD-595

Figure A−21. Outline and Dimensions, Model S055 Surface-Mount Microphone Module

165E1846-00 Page A-36

Rev. 16

Installation & Operation Instruction Manual

Model FA2100CVR

MICROPHONE MODEL S055 PNR S055−0030−00 SER XXXXXXXXXX MFR 06141 DMF MMYYYY communications Sarasota, Florida, USA

2D BAR CODE TSO−C123a ED−56A

CANNON 150949−1002 TWINAX RECEPTACLE

1

NAMEPLATE

COMPANY LOGO

2

3

1.625

2.00 DIA.

1.625 0.25 2.56

0.50 MAX.

2.87

ÉÉÉÉ ÉÉÉ ÉÉÉÉ ÉÉÉ ÅÅÅ ÉÉÉÉ ÉÉÉ ÅÅÅ ÉÉÉÉ

2.00

4X 6−32 TAPPED HOLES

2.00

NOTES: 1

MATING PLUGS FOR SPECIFIED RECEPTACLE IS CANNON 150900−0303

3

INDICATED PORTION OF MICROPHONE MUST BE UNOBSTRUCTED FOR PROPER OPERATION.

2

RECOMMENDED CABLE: MIL−W−22759 OR MIL−C−27500.

4.

DIMENSIONS ARE IN INCHES.

Part Number

Panel Color

Weight (+ 0.1 lbs.)

S055−0030−00

Brown, Medium (Boeing)

0.4 lbs.

905−E1780−18E

Figure A−22. Outline and Dimensions, Model S055 Panel-Mount Microphone Module

Rev. 16

165E1846-00 Page A-37

Installation & Operation Instruction Manual

0.50

Model FA2100CVR

1

ÉÉÉÉ ÉÉÉÉ ÉÉÉ ÅÅ ÉÉÉÉ ÉÉÉ ÅÅ ÉÉÉÉ ÉÉÉ ÅÅ ÉÉÉÉ 1.09

.18 +/- .05

0.42 DIA

1.19

2.25 2.93 +/- .12

FOAM DAMPER (BLUE COLOR)

.64

cL

24 MIN. DC SUPPLY 18V (WHITE) SIGNAL OUTPUT (BLACK)

0.700 cL

SHIELDED WIRE 22 GAUGE TWISTED PAIR NAMEPLATE

1

.92

2 X # 6–32 THD

Indicated portion of microphone must be unobstucted for proper operation. 2. Dimensions are in inches. 3. All outlines are typical for the S056 −00XX−00 microphones. The exceptions are S056−0048−10 and −15. See Figure A−19 sheet 2 of 2 for those differences.

SIGNAL GND (SHIELD)

MICROPHONE MODEL S056 PNR S056−00XX−00 SER XXXXXXXXXX MFR 06141 DMF MMYYYY communications Sarasota, Florida, USA

2D BAR CODE TSO−C123a ED−56A 905−E1771−18K

Part Number

Housing Color

Weight (+ 0.1 lbs.)

S056−0047−00

Gray − No. 36118 per MIL−STD−595

0.2 lbs.

S056−0048−00

Black − No. 37038 per MIL−STD−595

0.2 lbs.

S056−0048−10

Black − No. 37038 per MIL−STD−595

0.2 lbs.

S056−0048−15

Black − No. 37038 per MIL−STD−595

0.2 lbs.

S056−0049−00

Brown, ATR−42 − No. 20059 per MIL−STD−595

0.2 lbs.

S056−0050−00

Boeing Brown − No. 36118 per L3AR Chip

0.2 lbs.

S056−0051−00

Embraer Gray − No. 36173 per MIL−STD−595

0.2 lbs.

Figure A−23. (Sheet 1 of 2) Outline and Dimensions, Model S056 Surface-Mount Microphone Module

165E1846-00 Page A-38

Rev. 16

Installation & Operation Instruction Manual

Model FA2100CVR

0.50 (ref.)

1 .40 +/- .05

0.42 DIA (ref.)

2.25 (ref.) 3.15

S056-0048-10 ONLY

24 MIN. CONNECTOR

SIGNAL OUTPUT

0.700 cL (ref.) SHIELDED WIRE 22 GAUGE TWISTED PAIR NAMEPLATE

RED DOT SIGNAL GND (SHIELD)

.92 (ref.)

DC SUPPLY 18V

CONNECTOR SHELL IS ALSO CONNECTED TO SIGNAL GROUND

2 X # 6–32 THD (ref.)

S056-0048-15 ONLY MICROPHONE MODEL S056

1

Indicated portion of microphone must be unobstucted for proper operation. 2. Dimensions are in inches. 3. Mating Connector: L3AR P/N 063−98−03224 (LEMO P/N PHG.OB.303.LLLD35T)

PNR S056−00XX−00 SER XXXXXXXXXX MFR 06141 DMF MMYYYY communications Sarasota, Florida, USA

2D BAR CODE TSO−C123a ED−56A 905−E1771−18K

Figure A−19. (Sheet 2 of 2) Outline and Dimensions, Model S056 Surface-Mount Microphone Module

Rev. 16

165E1846-00 Page A-39

Installation & Operation Instruction Manual

Model FA2100CVR

MICROPHONE MODEL S056 PNR S056−1048−00 SER XXXXXXXXXX MFR 06141 DMF MMYYYY communications Sarasota, Florida, USA

1

Indicated portion of microphone must be unobstructed for proper operation. 2. Dimensions are in inches.

Part Number S056−1048−00

Panel Color Black

2D BAR CODE TSO−C123a ED−56A

905−E1838−18D

Weight (+ 0.1 lbs.) 0.2 lbs.

Figure A−24. Outline and Dimensions, Model S056 Panel-Mount Microphone Module − Small

165E1846-00 Page A-40

Rev. 16

Installation & Operation Instruction Manual

Model FA2100CVR

MICROPHONE MODEL S056 PNR S056−0030−00 SER XXXXXXXXXX MFR 06141 DMF MMYYYY communications Sarasota, Florida, USA

2D BAR CODE TSO−C123a ED−56A

CANNON 150949−1002 TWINAX RECEPTACLE

1

NAMEPLATE

COMPANY LOGO

2

3

1.625

2.02 DIA.

1.625 0.25 2.56

0.50 MAX.

2.88

ÉÉÉÉ ÉÉÉ ÉÉÉÉ ÉÉÉ ÅÅÅ ÉÉÉÉ ÉÉÉ ÅÅÅ ÉÉÉÉ

2.02

4X 6−32 TAPPED HOLES

2.02

NOTES: 1

MATING PLUG FOR SPECIFIED RECEPTACLE IS ARE CANNON 150900−0303

3

INDICATED PORTION OF MICROPHONE MUST BE UNOBSTRUCTED FOR PROPER OPERATION.

2

RECOMMENDED CABLE: L3 P/N: 024−98−00294

4.

DIMENSIONS ARE IN INCHES.

Part Number S056−0030−00

Panel Color Brown (Boeing)

S056−0030−00 Rev. B

Weight (+ 0.2 lbs.) 0.4 lbs.

Figure A−25. Outline and Dimensions, Model S056 Panel-Mount Microphone Module − Large

Rev. 16

165E1846-00 Page A-41

Installation & Operation Instruction Manual

Model FA2100CVR

SIGNAL OUTPUT (BLACK)

+6 VDC INPUT MIC BIAS (WHITE)

.423 .005 

.53

.882 .020

.50 +6 VDC INPUT

SIGNAL GROUND (GREEN)

SIGNAL OUTPUT

MIC

0 330

16.9 K

30

SIGNAL GROUND

300

SPECIFICATIONS:

TEST CIRCUIT FREQ RESP: REFER TO CHART.

60

ELEMENT CAPACITANCE: 17pF @ 1 kHz CAPACITANCE (PI–FILTER): 4000pF  20%, 100 WVDC 270

WORKING VOLTAGE: