FA2100 CVR Install Manual

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

INSTALLATION & OPERATION INSTRUCTION MANUAL MODEL FA2100 CVR COCKPIT VOICE RECORDER 1/2-ATR SHORT CASE (SUPERSEDES FAR 08337220) RECORDER PART NUMBERS:

2100–1010–00 2100–1020–00 2100–1020–02 2100–1020–90 2100–1020–91 2100–1020–93

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/EUROCAE ED–56A/ARINC 757

Rev. 07 January 01/03

P/N: 165E1846–00

Model FA2100 CVR

Installation & Operation Instruction Manual Part Number 165E1846–00 Rev. 07 Jan. 01/03

This manual contains date sensitive information necessary to install recorders in aircraft. Contact L-3 Communications, Aviation Recorders, to verify this date sensitive information prior to using this manual to develop other documentation. The recorder products/software are being exported from the United States in accordance with the Export Administration Regulations ECCN 4D994, No License Required. Diversion contrary to U.S. law is prohibited. In accordance with U.S. Law (31 CFR Part 746, and Supplement No.1 to Part 774, and CFR Part 550) resale/re–export or transfer to the countries identified therein is prohibited without the prior written consent of the U.S. Department of Commerce.

ECopyright 2003 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

Model FA2100 CVR

Installation & Operation Instruction Manual

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.

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Installation & Operation Instruction Manual

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 reĆ quired.

05

Aug. 15/01

Fixed Control Unit drawings to seperate the S151 drawing from the S161 drawing, and the S152 drawing from the S162 drawing in AppenĆ 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.

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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 1.4

System Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 System Overview . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 1.4.1 Recorder Unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 1.4.2 Control Units and External Preamplifier . . . . . . . . . . . . . . . . . . 5 1.4.3 Remote Microphone Module . . . . . . . . . . . . . . . . . . . . . . . . . . . 6

1.5 2.0

3.0

1.4.4 CVR Mounting Racks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 Abbreviations and Acronyms . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7

EQUIPMENT LIMITATIONS/SPECIFICATIONS . . . . . . . . . . . . . . . . . . . . . 7 2.1

Applicable Documents . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7

2.2

Physical Characteristics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8

2.3

Electrical Characteristics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8

2.4 2.5

Environmental Characteristics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 Crash- and Fire-Survival Characteristics . . . . . . . . . . . . . . . . . . . . . . 13

INSTALLATION PROCEDURES AND LIMITATIONS . . . . . . . . . . . . . . . 13 3.1

Installation Precautions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

3.2

General Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

3.3 3.4

Installation Acceptance by Field Approval Method . . . . . . . . . . . . . . 14 Recorder Location . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

3.5

Mounting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

3.6

Power Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

3.7

Wiring Connections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

3.8 3.9

Audio System Interface . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 Microphone Installation Criteria . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

3.10 Cessation of Recording . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 4.0

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POST-INSTALLATION CHECKOUT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

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TABLE OF CONTENTS (Cont’d) Section 5.0

Page OPERATIONAL TESTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 5.1

Preflight Functional Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

5.2

Complete Audio System Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

5.3

Flight Checkout Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

6.0

FA2100 CVR READOUT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

7.0

OPERATING INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

8.0

FLIGHT CHECKOUT PROCEDURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

9.0

8.1

Operational Notes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

8.2

Flight Checkout . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

MAINTENANCE AND CALIBRATION . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 9.1

Recorder . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

9.2

Underwater Locator Device . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

9.3

Product Support . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

9.4

Authorized Repair Facilities . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

9.5

Loaner/Rental Program . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

Appendixes Appendix

Page

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

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Installation & Operation Instruction Manual

TABLE OF CONTENTS (Cont’d) List of Illustrations Figure

Page

1.

Model FA2100 CVR Cockpit Voice Recorder . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3

2.

Functional System Block Diagram Model FA2100 CVR Cockpit Voice Recorder . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4

3.

Outline and Dimensions FA2100 CVR Cockpit Voice Recorder, PN 2100–1010–( ) & PN 2100–1020–( ) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

4.

Outline and Dimensions, CVR Mount, Part Number 178E0919–00 . . . . . . . . . . . . . . . . . . . 12

5.

Recommended Cockpit Area Microphone Mounting Location . . . . . . . . . . . . . . . . . . . . . . 16

6.

On-Aircraft Setup for Checking Out FA2100 CVRs using a Portable Interface . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

A–1.

Part Number Definition, Model S151/S161, Model S152/S162, and Model S251/S261 Control Units . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A–3

A–2.

Outline and Dimensions, Model S151 Control Unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A–4

A–3.

Interwiring Diagram, FA2100 Recorder, S151 Control Unit, S055 Remote Microphone . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A–5

A–4.

Outline and Dimensions, Model S161 Control Unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A–7

A–5.

Interwiring Diagram, FA2100 Recorder, S161 Control Unit, S056 Remote Microphone . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A–8

A–6.

Outline and Dimensions, Model S251 Control Unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . A–10

A–7.

Interwiring Diagram, FA2100 Recorder, S251 Control Unit, S055 Remote Microphone . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A–11

A–8.

Outline and Dimensions, Model S261 Control Unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . A–13

A–9.

Interwiring Diagram, FA2100 Recorder, S261 Control Unit, S056 Remote Microphone . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A–14

A–10.

Outline and Dimensions, Model S152 Control Unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . A–16

A–11.

Outline and Dimensions, Model S162 Control Unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . A–17

A–12.

Interwiring Diagram, FA2100 Recorder, S152/S162 Control Unit with Internal Microphone . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A–18

A–13.

Outline and Dimensions, Model S150 External Preamplifier Module . . . . . . . . . . . . . . A–20

A–14.

Interwiring Diagram, FA2100 Recorder, S150 External Preamplifier, S055 Remote Microphone . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A–21

A–15.

Outline and Dimensions, Model S160 External Preamplifier Module . . . . . . . . . . . . . . A–23

A–16.

Interwiring Diagram, FA2100 Recorder, S160 External Preamplifier, S056 Remote Microphone . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A–24

A–17.

Outline and Dimensions, Model S055 Surface-Mount Microphone Module . . . . . . . . . A–26

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Model FA2100 CVR

TABLE OF CONTENTS (Cont’d)

List of Illustrations (Cont’d) Figure

Page

A–18.

Outline and Dimensions, Model S055 Panel-Mount Microphone Module . . . . . . . . . . . A–27

A–19.

Outline and Dimensions, Model S056 Surface-Mount Microphone Module . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A–28

A–20.

Outline and Dimensions, Model S056 Panel-Mount Microphone Module . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A–29

A–21.

Model S055 Microphone Element Specifications and Response Diagram . . . . . . . . . . . A–30

A–22.

Model S056 Microphone Element Specifications and Response Diagram . . . . . . . . . . . A–31

A–23.

Outline and Dimensions, Model A151B Control Unit Does Not Comply with ED–56A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A–32

A–24.

Interwiring Diagram, FA2100 Recorder, A151B Control Unit, A55B Remote Microphone Such Installations Do Not Comply with ED–56A . . . . . . . . . . . . . A–33

A–25.

Outline and Dimensions, Model A152B Control Unit Does Not Comply with ED–56A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A–35

A–26.

Interwiring Diagram, FA2100 Recorder, A152B Control Unit with Internal Microphone Such Installations Do Not Comply with ED–56A . . . . . . . . . . . . . . . . . . . A–36

A–27.

Outline and Dimensions, Model A150 External Preamplifier Module Does Not Comply with ED–56A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A–38

A–28.

Interwiring Diagram, FA2100 Recorder, A150 External Preamplifier, A55B Remote Microphone Such Installations Do Not Comply with ED–56A . . . . . . . A–39

A–29.

Outline and Dimensions, Model A55B Surface-Mount Directional Microphone Module, Does Not Comply with ED–56A . . . . . . . . . . . . . . . . A–41

A–30.

Outline and Dimensions, Model A55B Surface-Mount Mini–Condensor Microphone Module, Does Not Comply with ED–56A . . . . . . . . . . . A–42

A–31.

Outline and Dimensions, Model A55B Panel-Mount Microphone Module, Rear Connector Does Not Comply with ED–56A . . . . . . . . . . . . . . . . . . . . . . . A–43

A–32.

Outline and Dimensions, Model A55B Panel-Mount Microphone Module, Top Connector Does Not Comply with ED–56A . . . . . . . . . . . . . . . . . . . . . . . A–44

C–1.

Inertia/Impact Switch Model 3LO–453/3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . C–4

C–2.

Aerodyne Controls Corp. Environmentally Sealed Impact Switch Assembly . . . . . . . . . C–5

C–3.

Dukane ULD Tester, Aviation Recorders’ Part Number 15977 . . . . . . . . . . . . . . . . . . . . . C–7

List of Tables Table

Page

1.

FA2100 CVR Descriptions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2

2.

Model FA2100 CVR Recording Specifications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5

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1.0

INTRODUCTION

1.1

Purpose of Manual

Installation & Operation Instruction Manual

This Installation and Operation Instruction Manual applies to the following Model FA2100 CVR Cockpit Voice Recorders: 2100–1010–00

2100–1020–90

2100–1020–00

2100–1020–91

2100–1020–02

2100–1020–93

In this manual, these recorders are referred to as FA2100 CVR, or CVR’s. Refer to FA2100 GACVR 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 FA2100 CVR 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.

Comments or recommendations about the installation, operation, and check out of the FA2100 CVR should be sent to L-3 Communications, Aviation Recorders, Product Support Department, at the address shown in section 9.3.

1.2

Equipment and Document Requirements

The following equipment and documents are, or may be, required for on-aircraft installation and check out of these FA2100 CVRs: F

This Installation & Operation Instruction Manual.

F

Portable Interface (PI), Part Number 17TES0043 (includes PI Memory Card Module, Part Number 17TES0053; PI Audio Readout Cable, Part Number 17TES0051; and PI Auxiliary Readout Cable, Part Number 17TES0052).

F

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

F

Cockpit Voice Recorder System Test Panel, Part Number 9300A860; and Cable Assembly, Part Number 024E1122–00 (for FA2100 CVR Readout, see paragraph 6.0). Instead of the Test Panel, the PI and a customer-fabricated cable to provide power to the FA2100 CVR’s main (rear) connector can be used.

F

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

F

Component Maintenance Manual, Cockpit Voice Recorder, Model FA2100 CVR, ATA 23–70–04, Part Number 165E1689-00.

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Installation & Operation Instruction Manual

1.3

Model FA2100 CVR

System Description

The FA2100 CVR Systems meet or exceed the requirements of Federal Aviation Administration (FAA) Technical Standard Order TSO–C123a, Cockpit Voice Recorder Systems; European Organization for Civilian Aviation Equipment (EUROCAE) Minimum Operational Performance Specification (MOPS) ED–56A, Cockpit Voice Recorder System; and ARINC Characteristic 757, Aeronautical Radio, Inc., Cockpit Voice Recorder (CVR). The FA2100 CVRs may also be used to replace existing ARINC Characteristic 557 installations. The FA2100 CVR 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 FA2100 CVRs covered in this manual.

Table 1. FA2100 CVR Descriptions Part Number

1

Description

Weight 1 (
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.

2100–1020–91

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

10.0 lbs.

2100–1020–93

ARINC 404A 1/2-ATR Short Case; ARINC 757, 120 Minutes w/8–ohm output and no Bulk Erase (when used with 93A152-16 Control Unit).

10.0 lbs.

Weight is with Underwater Locator Device installed.

1.4.1 Recorder Unit The FA2100 CVRs 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 FA2100 CVR 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 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 FA2100 CVR. This connector provides the interface from the recorder to GSE for checkout of the recorder, or to transfer data to a readout device. The FA2100 CVR is connected to aircraft wiring via a 57-pin, DPXB-style connector. 165E1846–00 Page 2

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HARDWARE AND SOFTWARE MODIFICATIONS CSMU

ULD

GSE CONNECTOR (BEHIND DUST COVER)

Figure 1. Model FA2100 CVR Cockpit Voice Recorder Refer to Figure 2 for this discussion. The FA2100 CVR 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 FA2100 CVR is available in two recording configurations: 30-minute, Part Number 2100–1010–( ), and 120-minute, Part Number 2100–1020–( ). Both configurations record a minimum of 30 minutes of high quality audio from the following four cockpit audio inputs: Channel 1: Channel 2: Channel 3: Channel 4:

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

Part Number 2100–1020–( ) records a fifth internal audio stream for a minimum of 120 minutes. 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–( ) 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 2 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. The FA2100 FA2100 CVR 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 FA2100 CVR operation. It may be connected to an annunciator or to an aircraft central maintenance computer. At startup, the FA2100 CVR initiates a Built-in-Test (BIT) and then continuously monitors itself for fault conditions. Rev. 07 Jan. 01/03

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Model FA2100 CVR

COCKPIT AREA MICROPHONE (CAM) 1 4

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 2

RECORD ON +5 V FOR LIGHTED PANEL CHANNEL 4 2 CHANNEL 3

FA2100 CVR

AUDIO OUT

PILOT AUDIO

2

2 CHANNEL 2

+18 VDC

CO-PILOT AUDIO

2

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

TEST INDICATOR

CHANNEL 1

AIRCRAFT INTERFACE PWA

2

GMT_IN_A (429) GMT_IN_B (429)

2 CVR FAULT

TO AIRCRAFT FAULT MONITORING SYSTEM

ROTOR_SPEED_IN_HI ROTOR_SPEED_IN_LO 28 VDC OR 115 VAC 400 Hz STOP RECORDING

CHASSIS GROUND

AUDIO COMPRESSOR PWA ACQUISITION PROCESSOR PWA

GSE OUTPUT

TO GROUND STATION TEST EQUIPMENT

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

Figure 2. Functional System Block Diagram Model FA2100 CVR Cockpit Voice Recorder

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Previously recorded information cannot be read from the Model FA2100 CVR while it is installed in the aircraft. (Refer to paragraph 6.0 for additional information.)

Table 2. Model FA2100 CVR 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

Not Available

Not Available

2100–1020–( ) 30 minutes

30 minutes

30 minutes

120 minutes

120 minutes

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

Note:

Channel 2

Combined Channels

30 minutes

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.

1.4.2 Control Units and External Preamplifier The Control Unit or External Preamplifier is a required component of a CVR installation and functions as the FA2100 CVR cockpit user interface. Control Units contain a preamplifier printed wiring assembly (PWA) for interfacing the cockpit area microphone with the FA2100 CVR, and provide a means for activating the test function via a green push button and an indicator. Bulk Erasure of the FA2100 CVR 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. The Model S151/S161, Model S152/S162, and the Model S251/S261 Control Units are for use in FA2100 CVR 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 1.4.3). The Model S161/S261 Controls Units are used with remote microphone modules with internal amplifiers for reducing RF interference (Model S056, see paragraph 1.4.3). These control units also have front panel TEST and Bulk ERASE switches, TEST indicator lamp and a HEADSET jack. 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 FA2100 CVR 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 FA2100 CVR 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 Rev. 07 Jan. 01/03

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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 FA2100 CVR. 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.

1.4.2.1

Mating Connector, Control Units and External Preamplifiers

For Model S151/S161, S152/S162, A151B, and A152B Control Units. Solder – Part Number 9300–458 Crimp – Part Number 063–98–00577 For Model S251/S261 Control Unit Solder – Kit Part Number 147E1262–00 Crimp – Kit 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

1.4.3 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.

1.4.4 CVR Mounting Racks A.

CVR Mount, Part Number 178E0919–00

CVR mount with no vibration isolators used to install the FA2100 CVR in the aircraft. Refer to Figure 4 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. 165E1846–00 Page 6

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Model FA2100 CVR

C.

Installation & Operation Instruction Manual

Heavy Duty Vibration Mount, Part Number 93–955

CVR mount for use in aircraft environments where excessive vibration may occur, such as in rotorcraft 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 FA2100 CVR’s rear panel. Aircraft wiring is soldered or crimped to the connector pins. Solder – Part Number 9300–435 Crimp – Part Number 063–98–01474

1.5

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

Aeronautical Radio, Inc., Air Transport Equipment Cases and Racking

ARINC Characteristic 757

Aeronautical Radio, Inc., Cockpit Voice Recorder

ARINC Report 604–1

Aeronautical Radio, Inc., Design Guidance for Design and Use of Built-In Test Equipment

ARINC Report 624–1

Aeronautical Radio, Inc., Design Guidance for Onboard Maintenance System

EUROCAE MOPS ED–55

European Organization for Civil Aviation Equipment Minimum Performance Specification for Flight Data Recorder Systems

EUROCAE MOPS ED–56A

European Organization for Civil Aviation Equipment Minimum Performance Specification for Cockpit Voice Recorder System

FED–STD–595

Federal Standard, Colors

RTCA/DO–160C

Radio Technical Commission for Aeronautics, Environmental Conditions and Test Procedures for Airborne Equipment

RTCA/DO–178B

Radio Technical Commission for Aeronautics, Software Considerations in Airborne Systems and Equipment Certification

TSO–C123a

Federal Aviation Administration Technical Standard Order Cockpit Voice Recorder Systems

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2.2

Model FA2100 CVR

Physical Characteristics

The Model FA2100 CVRs fit within the envelope of an ARINC 404A 1/2-ATR short case. (Refer to for Figure 3 outline and dimension illustration.) Following are the physical characteristics of the Model FA2100 CVRs: Size: Height: Width: Depth:

5.5 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

Recording Time:

PN 2100–1010–( ) = 30 minutes minimum PN 2100–1020–( ) = 120 minutes minimum

Input Signal Format:

ARINC 757

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.

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Installation & Operation Instruction Manual

Audio Quality:

Meets ED–56A Chapter 3 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

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Model FA2100 CVR

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: ENREGISTRUER 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. 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. 4. OVERALL EQUIPMENT SIZE AND MOUNTING SCHEME COMPLY WITH ARINC 404 AND 404A. 5. REAR PANEL CONTAINS HOLES TO MATE WITH GUIDE PINS IN ARINC 404 MOUNTING TRAYS.

2100-1010-00 H 2100-1020-00 G

Figure 3. (Sheet 1 of 2) Outline and Dimensions FA2100 CVR Cockpit Voice Recorder, PN 2100–1010–( ) & PN 2100–1020–( )

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Installation & Operation Instruction Manual

2.44

± .50

REFERENCE ONLY POLARIZING KEYS SHADING DENOTES SOLID KEY AREA

COCKPIT VOICE RECORDER MODEL FA2100

4 .995 ± .01

B A

View

A

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

B

View

±

.04

UNDERWATER LOCATING DEVICE 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 G

Figure 3. (Sheet 2 of 2) Outline & Dimensions FA2100 CVR Cockpit Voice Recorder, PN 2100–1010–( ) & PN 2100–1020–( )

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Installation & Operation Instruction Manual

Model FA2100 CVR

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)

.75 $ .50

1.00 MAX .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 #8 100 T HEAD SCREWS MS24693–( ) OR EQUIV (LENGTH AS REQD), AND SELF-LOCKING NUTS MS21044–C08 OR EQUIV. 905–E0919–18H

Figure 4. Outline and Dimensions, CVR Mount, Part Number 178E0919–00 165E1846–00 Page 12

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2.4

Installation & Operation Instruction Manual

Environmental Characteristics

Refer to the FA2100 CVR Environmental Qualification Forms (EQFs) in Appendix B for environmental characteristics.

2.5

Crash- and Fire-Survival Characteristics

Penetration:

ED–55/ED–56A – 500 lbs./10 feet/!@4” probe

Static Crush:

ED–55/ED–56A – 5,000 lbs.

Fire Protection:

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

Impact:

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

3.0

INSTALLATION PROCEDURES AND LIMITATIONS

3.1

Installation Precautions

Approval of the Model FA2100 CVR installation is not authorized by this Installation and Operating Instruction Manual. Acceptance of the installation and use of the FA2100 CVR and its associated components must be sought from the cognizant Federal Aviation Administration (FAA) office or other certifying authority. Approvals may be accomplished on a Field Approval basis if the installation is determined to meet the criteria of the appropriate Post-Installation, Preflight, and Flight tests specified for evaluation in this Installation Manual. (Refer to paragraph 3.3.) Proposed installations should be coordinated with the local jurisdiction of the FAA or other certifying authority before beginning recorder installation. Refer to the following statement which was extracted 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.

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 Federal Aviation Regulation (FAR) 25.1457 (b), (e), and (f). Installations must conform to the Operating Rules in FAR23.1457, 25.1457, 27.1457, and 29.1457 appropriate to the category of operation under FAR Parts 91, 135, and 121 (Air Carrier). 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 Rev. 07 Jan. 01/03

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Model FA2100 CVR

the Bulk ERASE feature is installed, at least one interlock is required to prevent accidental erasure of the FA2100 CVR. If the BULK ERASE feature is not desired, pin 55 (ERASE A) of the FA2100 CVR must be grounded to pin 17. Pin 57 remains open.

3.3

Installation Acceptance by Field Approval Method

An applicant for Field Approval of a CVR installation must be properly certified and appropriately rated, qualified, and equipped to accomplish the 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 Inspector conducting the Field Approval. The CVR Installation Manual containing Operating Instructions and System Description must be made available to the inspector for review and evaluation of the CVR System. The applicant must submit an FAA Form 337, describing the work performed to the airframe to accomplish the installation of the CVR System. The 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 in this Installation Manual. The applicant should submit all appropriate data and drawings to the inspector before 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 Form 337. Finally, ground and flight tests 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 individual 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 tests must be brought to the inspector’s attention and corrected before the aircraft can be returned to service. If required, Aviation Recorders can reproduce the CVR memory contents onto cassettes for channel separation and evaluation. Contact the Product Support Department to coordinate this process. If you prefer to make your own reproduction, refer to section 6.0.

3.4

Recorder Location

The Model FA2100 CVR 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 FA2100 CVR is certified and approved 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. 165E1846–00 Page 14

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Installation & Operation Instruction Manual

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 FA2100 CVR 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 FA2100 CVR operates with input voltages of either 115 Vac at 400 Hz, or 28 Vdc. The FA2100 CVRs 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 (Part Number is 063E1072–00, Cannon Part Number DPXB–36571–59). This connector mates with the connector on the aircraft wiring harness.

3.7

Wiring Connections

The typical electrical interconnect wiring between the recorder and the aircraft is specified in ARINC Characteristic 757. Connections to the FA2100 CVR J1 connector depend on the installation configuration. Refer to Appendix A for appropriate Interwiring Diagram.

3.8

Audio System Interface

The FA2100 CVR is used in an ARINC 757 configuration, with interface to the aircraft provided through a 57-pin DPXB rear panel connector. The range of acceptable audio input levels for the Model FA2100 CVR is from 50 mVrms to 3 Vrms. Nominal audio level input is 1 Vrms. The Model FA2100 CVR provides for four audio inputs which are connected as follows: Channel 1: Channel 2: Channel 3: Channel 4:

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

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. Rev. 07 Jan. 01/03

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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.

3

1

2 2

3 RECOMMENDED MICROPHONE LOCATIONS ARE NUMBERED IN ORDER OF PREFERENCE

Figure 5. Recommended Cockpit Area Microphone Mounting Location 3.10 Cessation of Recording Federal Air Regulations 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 FA2100 CVR 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: 165E1846–00 Page 16

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Installation & Operation Instruction Manual

A.

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

B.

Impact Switch: An impact switch interrupts FA2100 CVR power upon exposure to a predetermined level of g-force. Such switches have limitations, but are effective in high g-force accidents. This item is not available through Aviation Recorders. (Refer to Appendix C for manufacturer’s specifications for available models.)

C.

ARINC 757 Shutdown Signal: The FA2100 CVR continuously monitors the ARINC 757 shutdown 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-toTest” function. If the recording is resumed due to execution of the “Push-to-Test,” 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.

4.0

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 FA2100 CVR System and associated components, verify that all connections are secure and that a continuity or other interconnect assurance test has been conducted.

2.

Apply power to the system and activate the FA2100 CVR’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 FA2100 CVR has passed the test. (The TEST lamp stays on as long as the TEST button is pressed.) 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 FA2100 CVR 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 FA2100 CVR. The PI is connected to the FA2100 CVR via a 10-foot cable that is plugged into the FA2100 CVR’s front panel GSE connector (refer to Figure 6). The PI receives power from the FA2100 CVR. 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:

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Installation & Operation Instruction Manual

Model FA2100 CVR

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

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

a. Connect the PI to the FA2100 CVR’s GSE connector as shown in Figure 6. b. 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). c. Repeat this process for CH 2, CH 3, and HQ CAM CH 4. d. 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 2100–1020–02 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 FA2100 CVR 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 FA2100 CVR System. Press and hold the Cockpit Control Unit’s TEST push button for a minimum of five seconds. For installations containing Model S151/S161, Model S152/S162, or Model S251/S261 Control Units, the panel-mounted TEST lamp illuminates when the FA2100 CVR has passed the testing. (The TEST lamp stays on as long as the TEST button is pressed.) For installations containing Model A151B or Model A152B Control Units, the meter is used as a ‘GO-NO-GO’ indicating device. The meter needle rises to and remains within, the ‘GO’ (green) section of the meter scale when the FA2100 CVR has passed the testing. (The meter needle stays in the ‘GO’ section of the meter scale as long as the TEST button is pressed.) 165E1846–00 Page 18

Rev. 07 Jan. 01/03

Model FA2100 CVR

Installation & Operation Instruction Manual

PORTABLE INTERFACE (PI) 17TES0043

GMT

FA2100CVR

PI AUX READOUT CABLE 17TES0052 1, 2 ROTOR

PI AUDIO READOUT CABLE 17TES0051 1, 3

CH 1 HQ SQ

2

3

4

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 6. On-Aircraft Setup for Checking Out FA2100 CVRs using a Portable Interface Rev. 07 Jan. 01/03

165E1846–00 Page 19

Installation & Operation Instruction Manual

5.2

Model FA2100 CVR

Complete Audio System Check

A complete Audio System Test must be completed under the following three conditions; during each annual inspection, specified maintenance period, 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 FA2100 CVR. Upon satisfactory completion of this test, an entry shall be made in the aircraft or rotorcraft 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 FA2100 CVR while it is installed in the aircraft. Using the following procedure, verify that the four following channnels 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 FA2100 CVR’s GSE connector as shown in Figure 6.

(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

FA2100 CVR READOUT

Previously recorded information cannot be read (played back) from the Model FA2100 CVR 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 FA2100 CVR 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 FA2100 CVR readout: PI, Part Number 17TES0043; Portable Interface Operator’s Manual, Part Number 165E1630–00; Cockpit Voice Recorder System Test Panel, 165E1846–00 Page 20

Rev. 07 Jan. 01/03

Model FA2100 CVR

Installation & Operation Instruction Manual

Part Number 9300A860; Cable Assembly, Part Number 024E1122–00; and Component Maintenance Manual, Cockpit Voice Recorder, Model FA2100 CVR, ATA 23–70–04. Instead of the 9300A860 Test Panel, the PI and a customer-fabricated cable to provide appropriate power to the FA2100 CVR’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 FA2100 CVR data.

7.0

OPERATING INSTRUCTIONS

The Model FA2100 CVR 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 FA2100 CVR 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 FA2100 CVR 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 FA2100 CVR 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.

8.2

Flight Checkout

1. Pre- and Post-Engine Start a. Close FA2100 CVR circuit breaker about three minutes before engine start. b. Perform the pilot’s “PRE-FLIGHT FUNCTIONAL CHECK” contained in this manual. 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. f. Rev. 07 Jan. 01/03

Open FA2100 CVR circuit breaker. 165E1846–00 Page 21

Installation & Operation Instruction Manual

Model FA2100 CVR

2. Taxi, Takeoff, and Climb a. Close FA2100 CVR 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 FA2100 CVR will not erase in flight. Verify by monitoring at FA2100 CVR output jack. c. Open FA2100 CVR circuit breaker. 3. Cruise, Vmo or Mmo a. Select cruise altitude. Close FA2100 CVR circuit breaker. Disconnect auto-pilot and verify aural disconnect sound. Using the flight interphone 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 FA2100 CVR circuit breaker. 4. Descent, Touchdown, and Rollout a. Close FA2100 CVR 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 FA2100 CVR circuit breaker. 5. Post-Flight

Remove FA2100 CVR 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. 165E1846–00 Page 22

Rev. 07 Jan. 01/03

Model FA2100 CVR

9.0

MAINTENANCE AND CALIBRATION

9.1

Recorder

Installation & Operation Instruction Manual

The Model FA2100 CVR does not require scheduled maintenance or calibration, except for periodic inspection/servicing of the Underwater Locator Device (see paragraph 9.2).

9.2

Underwater Locator Device

The Model FA2100 CVR 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 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 of six years. Upon expiration of expected battery life, contact ULD manufacturer for replacement batteries, installation instructions, and recertification.

9.3

Product Support

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

9.4

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 FA2100 CVR System. Items needing repair should be shipped to the following address: L-3 Communications Aviation Recorders 6000 East Fruitville Road Sarasota, Florida 34232 Attention: Repair Station Questions concerning FA2100 CVR 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.

9.5

Loaner/Rental Program

Aviation Recorders’ Authorized Repair Facilities are capable of providing loaner/rental FA2100 CVRs. Also, the Aviation Recorders’ Product Support Group maintains a limited supply of FA2100 CVRs available for rental. Rev. 07 Jan. 01/03

165E1846–00 Page 23

Installation & Operation Instruction Manual

Model FA2100 CVR

THIS PAGE IS INTENTIONALLY LEFT BLANK

165E1846–00 Page 24

Rev. 07 Jan. 01/03

Model FA2100 CVR

Installation & Operation Instruction Manual

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

Rev. 07 Jan. 01/03

165E1846–00 Page A–1

Installation & Operation Instruction Manual

Model FA2100 CVR

THIS PAGE IS INTENTIONALLY LEFT BLANK

165E1846–00 Page A–2

Rev. 07 Jan. 01/03

Attenuated Output

Filtered Connector Non–Filtered Connector

D– type Connector Circular Connector

Gray Black Brown (Boeing) Brown (ATR) Blue (DO328) Gray (BD100)

Illuminated Non–Illuminated

Panel Height 1.125 Panel Height 2.25

COLOR

Reqs. S055 Microphone Reqs. S056 Microphone

Installation & Operation Instruction Manual

Panel Thickness .25 Panel Thickness .125

Model FA2100 CVR

S151–0020–00 S151–0030–00 S151–0040–00 S151–0050–00 S151–0060–00 S152–0020–00 S152–0030–00 S152–0030–01 * S152–0040–00 S161–0020–00 S161–0020–10 S161–0030–00 S161–0040–00 S161–0050–00 S161–0060–00 S162–0020–00 S162–0030–00 S162–0040–00 S251–1120–00 S251–1130–00 S251–1170–00 S261–1120–00 S261–1130–00 *

Note: -01 version is used with 8ĆOhm, 0.21 inch Headphone Jack (J2)

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

Rev. 07 Jan. 01/03

165E1846–00 Page A–3

Installation & Operation Instruction Manual

Model FA2100 CVR

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

MODIFICATIONS 1 4 7 10 13

2D BAR CODE

2 5 8 11 14

3 6 9 12 15

TSO–C123a ED–56A

SWITCH

GREEN LAMP

SWITCH

COCKPIT VOICE RECORDER 2.250 +.000 –.030

HOLD 5 SEC

TEST

1.125
.002

HEADSET ERASE .56

.18

5.375
.015 +.000 5.750 –.020 41ĆPIN, CIRCULAR, MS3112E20-41P FILTERED RECEPTACLE KEYWAY

2.11 1.05

.12

2.50

.07

3.00 NOTES: 1. WEIGHT = 1.1 LBS.
0.1 LBS. 2. DIMENSIONS ARE IN INCHES 905–E1019–18K

Figure A–2. Outline and Dimensions, Model S151 Control Unit 165E1846–00 Page A–4

Rev. 07 Jan. 01/03

Model FA2100 CVR

Installation & Operation Instruction Manual

STANDARD INTERWIRING PER ARINC SPEC 757 VOICE RECORDER UNIT 1 AMP

TO 115 VAC, 400 HZ TO AC COLD

2, 8

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 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

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

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

13

9

3

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 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

Rev. 07 Jan. 01/03

165E1846–00 Page A–5

Installation & Operation Instruction Manual

Model FA2100 CVR

Notes for Figure A–3: 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 Panel-mount microphones are equipped with a Cannon TM–RBI–M–0 Twinax receptacle. Mating connectors are Cannon TM–PL–30 or TM–PL2–F–39. Recommended cable is WTWC 2CE2419.2SJ, L–3 P/N: 024–98–00294.

165E1846–00 Page A–6

Rev. 07 Jan. 01/03

Model FA2100 CVR

Installation & Operation Instruction Manual

4.88 MAX 2.88

NAME PLATE AND MODIFICATIONS CONTROL UNIT MODEL S161 PNR: S161–XXXX–XX SER: XXXXXXXXX MFR: 06141 DATE: MMYYYY communications Sarasota, Florida

.45

MODIFICATIONS

2D BAR CODE

1 4 7 10 13

2 5 8 11 14

3 6 9 12 15

TSO–C123a ED–56A

STATIC ALERT LABEL FARSIDE SWITCH

SWITCH GREEN LAMP COCKPIT VOICE RECORDER

2.250 +.000 –.030

1.125
.005

TEST

ERASE

HOLD 5 SEC

HEADSET

.56

.19

5.365
.005 +.000 5.750 –.020 41ĆPIN, 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

905–E2367–18A

Figure A–4. Outline and Dimensions, Model S161 Control Unit Rev. 07 Jan. 01/03

165E1846–00 Page A–7

Installation & Operation Instruction Manual

Model FA2100 CVR

STANDARD INTERWIRING PER ARINC SPEC 757 VOICE RECORDER UNIT 1 AMP

TO 115 VAC, 400 HZ TO AC COLD

2, 8

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 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

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

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

13

9

3

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 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–5. Interwiring Diagram, Voice Recorder Unit, S161 Control Unit, S056 Remote Microphone

165E1846–00 Page A–8

Rev. 07 Jan. 01/03

Model FA2100 CVR

Installation & Operation Instruction Manual

Notes for Figure A–5: 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.

Rev. 07 Jan. 01/03

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.

165E1846–00 Page A–9

Installation & Operation Instruction Manual

Model FA2100 CVR

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

2 5 8 11 14

3 6 9 12 15

TSO–C123a ED–56A

STATIC ALERT LABEL FARSIDE

GREEN LAMP

SWITCH

HOLD 5 SEC

1.125

SWITCH

COCKPIT VOICE RECORDER

TEST

HEADSET ERASE

5.375

.562

.188

5.75 37 PIN ĆSUB DC37PĆTYPE FILTERED CONNECTOR.

.47 2.50 .28

2.68

.971 MAX.

.062 MIN.

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

Figure A–6. Outline and Dimensions, Model S251 Control Unit 165E1846–00 Page A–10

Rev. 07 Jan. 01/03

Model FA2100 CVR

Installation & Operation Instruction Manual

STANDARD INTERWIRING PER ARINC SPEC 757 VOICE RECORDER UNIT 1 AMP

TO 115 VAC, 400 HZ TO AC COLD OR

2, 7

5

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”

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

12

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

COCKPIT AREA MICROPHONE 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

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

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–7. Interwiring Diagram, Voice Recorder Unit, S251 Control Unit, S055 Remote Microphone Rev. 07 Jan. 01/03

165E1846–00 Page A–11

Installation & Operation Instruction Manual

Model FA2100 CVR

Notes for Figure A–7: 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 Panel-mount microphones are equipped with a Cannon TM–RBI–M–0 Twinax receptacle. Mating connectors are Cannon TM–PL–30 or TM–PL2–F–39. Recommended cable is WTWC 2CE2419.2SJ, L–3 P/N: 024–98–00294.

165E1846–00 Page A–12

Rev. 07 Jan. 01/03

Model FA2100 CVR

Installation & Operation Instruction Manual

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

3.75

MODIFICATIONS 1 4 7 10 13

2D BAR CODE

2 5 8 11 14

3 6 9 12 15

TSO–C123a ED–56A

OR

CONTROL UNIT MODEL S261 PNR: S261–1130–00 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

STATIC ALERT LABEL FARSIDE SWITCH

1.13

GREEN LAMP

HOLD 5 SEC

SWITCH

COCKPIT VOICE RECORDER

HEADSET ERASE

TEST

5.75 37 PIN ĆSUB DC37PĆTYPE FILTERED CONNECTOR.

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–8. Outline and Dimensions, Model S261 Control Unit Rev. 07 Jan. 01/03

165E1846–00 Page A–13

Installation & Operation Instruction Manual

Model FA2100 CVR

STANDARD INTERWIRING PER ARINC SPEC 757 VOICE RECORDER UNIT 1 AMP

TO 115 VAC, 400 HZ TO AC COLD OR

2, 7

5

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

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)

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 40 41 CHANNEL 3 LO 42 43 CHANNEL 3 HI 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

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

11

INPUT CHANNEL 1

INPUT CHANNEL 2

INPUT CHANNEL 3 INPUT CHANNEL 4

VOICE ERASE ”A” VOICE ERASE ”C”

BULK ERASE INTERLOCK (TYPICAL)

13

Figure A–9. Interwiring Diagram, Voice Recorder Unit, S261 Control Unit, S056 Remote Microphone 165E1846–00 Page A–14

Rev. 07 Jan. 01/03

Model FA2100 CVR

Installation & Operation Instruction Manual

Notes for Figure A–9: 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. 07 Jan. 01/03

165E1846–00 Page A–15

Installation & Operation Instruction Manual

Model FA2100 CVR

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

STATIC ALERT LABEL FARSIDE SWITCH

SWITCH GREEN LAMP

ÍÍÍ ÍÍÍ ÍÍÍ

COCKPIT VOICE RECORDER

2.250 +.000 –.030

TEST

HOLD 5 SEC

1.125
.005

ERASE

HEADSET

.56

MICROPHONE .19

5.365
.005 +.000 5.750 –.020 41ĆPIN, 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

905–E1926–18B

Figure A–10. Outline and Dimensions, Model S152 Control Unit 165E1846–00 Page A–16

Rev. 07 Jan. 01/03

Model FA2100 CVR

Installation & Operation Instruction Manual

4.88 MAX

.45 2.88

NAME PLATE AND MODIFICATIONS CONTROL UNIT MODEL S162 PNR: S162–00XX–00 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

STATIC ALERT LABEL FARSIDE SWITCH

SWITCH GREEN LAMP

ÍÍÍ ÍÍÍ ÍÍÍ

COCKPIT VOICE RECORDER

2.250 +.000 –.030

TEST HOLD 5 SEC

1.125
.005

ERASE

HEADSET

.56

MICROPHONE .19

5.365
.005 +.000 5.750 –.020 41ĆPIN, 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

905–E2387–18A

Figure A–11. Outline and Dimensions, Model S162 Control Unit Rev. 07 Jan. 01/03

165E1846–00 Page A–17

Installation & Operation Instruction Manual

Model FA2100 CVR

STANDARD INTERWIRING PER ARINC SPEC 757 VOICE RECORDER UNIT 1 AMP

TO 115 VAC, 400 HZ TO AC COLD

2, 8

5

OR TO DC POWER IN 28 VDC

5 AMPS

3

MODEL S152/S162 CONTROL UNIT

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 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–12. Interwiring Diagram, Voice Recorder Unit, S152/S162 Control Unit with Internal Microphone 165E1846–00 Page A–18

Rev. 07 Jan. 01/03

Model FA2100 CVR

Installation & Operation Instruction Manual

Notes for Figure A–12: 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.

Rev. 07 Jan. 01/03

165E1846–00 Page A–19

Installation & Operation Instruction Manual

Model FA2100 CVR

5.000
.030

4.528
.020

.236
.020

.236
.020 .201Ć.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 communications Sarasota, Florida

MS3112E8Ć3S OR EQUIVALENT

MODIFICATIONS 1 4 7 10 13

2D BAR CODE

2 5 8 11 14

3 6 9 12 15

MS3112E14Ć19S 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 NOTES: 1. DIMENSIONS ARE IN INCHES.

Housing Color

Weight (+ 0.1 lbs.)

Black

0.7 lbs.

905–E0986–18D

Figure A–13. Outline and Dimensions, Model S150 External Preamplifier Module 165E1846–00 Page A–20

Rev. 07 Jan. 01/03

Model FA2100 CVR

Installation & Operation Instruction Manual

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 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

INPUT CHANNEL 4

CHANNEL 4 HI ROTOR SPEED IN LO ROTOR SPEED IN HI

VOICE ERASE ”A” VOICE ERASE ”C”

13

Figure A–14. Interwiring Diagram, Voice Recorder Unit, S150 External Preamplifier, S055 Remote Microphone Rev. 07 Jan. 01/03

165E1846–00 Page A–21

Installation & Operation Instruction Manual

Model FA2100 CVR

Notes for Figure A–14: 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.

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 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 Panel-mount microphones are equipped with a Cannon TM–RBI–M–0 Twinax receptacle. Mating connectors are Cannon TM–PL–30 or TM–PL2–F–39. Recommended cable is WTWC 2CE2419.2SJ, L–3 P/N: 024–98–00294.

165E1846–00 Page A–22

Rev. 07 Jan. 01/03

Model FA2100 CVR

Installation & Operation Instruction Manual

4.99

4.53

.23

.23 0.196 DIA. 4 HOLES

2.74 1.97

NAMEPLATE AND MODIFICATIONS .39 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

SOURIAU 8525-10R-8B-3ASN009

3 6 9 12 15

SOURIAU 825-10R-14B-19SN009

TSO–C123a ED–56A

.54
.020

3.92

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–15. Outline and Dimensions, Model S160 External Preamplifier Module Rev. 07 Jan. 01/03

165E1846–00 Page A–23

Installation & Operation Instruction Manual

Model FA2100 CVR

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–16. Interwiring Diagram, Voice Recorder Unit, S160 External Preamplifier, S056 Remote Microphone 165E1846–00 Page A–24

Rev. 07 Jan. 01/03

Model FA2100 CVR

Installation & Operation Instruction Manual

Notes for Figure A–16: 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.

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 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.

Rev. 07 Jan. 01/03

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.

165E1846–00 Page A–25

Installation & Operation Instruction Manual

.50

Model FA2100 CVR

1.09

1.12 30
1.19 .84 DIA

.42 DIA 1 2.25

15


.64

cL

FOAM DAMPER

.92

ÉÉÉÉ ÉÉÉÉ ÉÉÉ ÅÅ ÉÉÉÉ ÉÉÉ ÅÅ ÉÉÉÉ ÉÉÉ

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) NOTES: 1 INDICATED PORTION OF MICROPHONE MUST BE UNOBSTUCTED FOR PROPER OPERATION. 2. DIMENSIONS ARE IN INCHES.

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

2D BAR CODE TSO–C123a ED–56A

NAMPLATE INFORMATION 905–E1300–18K

Part Number

Housing Color

Weight (+/–0.1 lbs.)

Minimum Cable Lenght

S055–0064–00

Gray (BD–100)

0.2 lbs

17"

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–17. Outline and Dimensions, Model S055 Surface-Mount Microphone Module 165E1846–00 Page A–26

Rev. 07 Jan. 01/03

Model FA2100 CVR

Installation & Operation Instruction Manual

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

2D BAR CODE

NAMEPLATE

COMPANY LOGO

TSO–C123a ED–56A

NAMPLATE INFORMATION

CANNON TM–RB1–M–0 TWINAX RECEPTACLE

1 1.625

2 2.00 DIA.

1.625

0.25

ÉÉÉÉ ÉÉÉ ÉÉÉÉ ÉÉÉ ÉÉ ÅÅ ÉÉÉÉ ÉÉÉ ÉÉ ÅÅ ÉÉÉÉ

2.00

2.00

2.56 4X 6–32 TAPPED HOLES

0.50 MAX.

2.87

NOTES: 1 2 3

MATING PLUGS FOR SPECIFIED RECEPTACLE ARE CANNON TM–PL–F–39 OR TM–PL2–F–39. INDICATED PORTION OF MICROPHONE MUST BE UNOBSTRUCTED FOR PROPER OPERATION. DIMENSIONS ARE IN INCHES. 905–E1780–18E

Part Number

Panel Color

Weight (+ 0.1 lbs.)

S055–0030–00

Brown, Medium (Boeing)

0.4 lbs.

Figure A–18. Outline and Dimensions, Model S055 Panel-Mount Microphone Module Rev. 07 Jan. 01/03

165E1846–00 Page A–27

Installation & Operation Instruction Manual

Model FA2100 CVR

0.50 0.42 DIA

1.09

ÉÉÉÉ ÉÉÉÉ ÉÉÉ ÅÅ ÉÉÉÉ ÉÉÉ ÅÅ ÉÉÉÉ ÉÉÉ ÅÅ ÉÉÉÉ

1

1.46 MAX

3.15 MAX

.64

cL

FOAM DAMPER 1.3 17

DC SUPPLY 18V (WHITE) SIGNAL OUTPUT (BLACK)

0.700 cL

SIGNAL GND (SHIELD) SHIELDED WIRE 22 GAUGE TWISTED PAIR 2 X # 6ć32 THD NAMEPLATE

MICROPHONE MODEL S056 PNR S056–00XX–00 SER XXXXXXXXXX MFR 06141 DMF MMYYYY

1

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

communications Sarasota, Florida, USA

2D BAR CODE TSO–C123a ED–56A

NAMPLATE INFORMATION

905–E1771–18G

Part Number

Housing Color

Weight (+ 0.1 lbs.)

S056–0047–00

Gray – No. 36118*

0.2 lbs.

S056–0048–00

Black – No. 37038*

0.2 lbs.

S056–0049–00

Brown, ATR–42 – No. 20059

0.2 lbs.

S056–0050–00

Boeing Brown – No. 36116*

0.2 lbs.

* PER MIL-STD-595

Figure A–19. Outline and Dimensions, Model S056 Surface-Mount Microphone Module 165E1846–00 Page A–28

Rev. 07 Jan. 01/03

Model FA2100 CVR

1

Installation & Operation Instruction Manual

MICROPHONE MODEL S056

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

PNR S056–1048–00 SER XXXXXXXXXX MFR 06141 DMF MMYYYY communications Sarasota, Florida, USA

2D BAR CODE TSO–C123a ED–56A

NAMPLATE INFORMATION 905–E1838–18D

Part Number S056–1048–00

Panel Color Black

Weight (+ 0.1 lbs.) 0.2 lbs.

Figure A–20. Outline and Dimensions, Model S056 Panel-Mount Microphone Module

Rev. 07 Jan. 01/03

165E1846–00 Page A–29

Installation & Operation Instruction Manual

Model FA2100 CVR

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

TEST CIRCUIT

SPECIFICATIONS:

60

FREQ RESP: REFER TO CHART. ELEMENT CAPACITANCE: 17pF @ 1 kHz CAPACITANCE (PIćFILTER): 4000pF
20%, 100 WVDC 270

90

WORKING VOLTAGE: