FA2100 CVR Install Manual

INSTALLATION & OPERATIONINSTRUCTION MANUAL

MODEL FA2100 CVRCOCKPIT VOICE RECORDER

1/2-ATR SHORT CASE

(SUPERSEDES FAR 08337220)

Rev. 07January 01/03

RECORDER PART NUMBERS: 210010100021001020002100102002210010209021001020912100102093

CONTROL UNIT MODEL NUMBERS: S151 S161S152 S162S251 S261A151B A152B

MICROPHONE PREAMPLIFIER S150 S160MODULE MODEL NUMBERS: A150

REMOTE MICROPHONE S055 S056MODEL NUMBERS: A55B

Manufactured in Accordance withFAA TSOC123a/EUROCAE ED56A/ARINC 757

P/N: 165E184600

Model FA2100 CVRInstruction Manual

Installation & Operation

Part Number 165E184600Rev. 07

Jan. 01/03

Copyright 2003 by L-3 Communications CorporationAviation Recorders

All rights reserved. No part of this manual may be repro-duced or utilized in any form or by any means, electronic ormechanical, including photocopying, recording, or by infor-mation storage and retrieval system, without permission inwriting.

Inquiries should be addressed to:L-3 Communications CorporationAviation RecordersTechnical PublicationsP. O. Box 3041Sarasota, Florida 34230(941) 3710811FAX: (941) 3775591CAGE Code 06141

This manual contains date sensitive information necessary to installrecorders in aircraft. Contact L-3 Communications, Aviation Recorders,to verify this date sensitive information prior to using this manual todevelop other documentation.

The recorder products/software are being exported from the UnitedStates in accordance with the Export Administration Regulations ECCN4D994, No License Required. Diversion contrary to U.S. law isprohibited. In accordance with U.S. Law (31 CFR Part 746, andSupplement No.1 to Part 774, and CFR Part 550) resale/reexport ortransfer to the countries identified therein is prohibited without theprior written consent of the U.S. Department of Commerce.



Page iiiJan. 01/03165E184600Rev. 07

GENERAL

This product and related documentation must be reviewed for familiarization withsafety markings and instructions before operation.

This instrument was constructed in an ESD (electrostatic discharge) protected envi-ronment. This is because most of the semiconductor devices used in this instrumentare susceptible to damage by static discharge.

Depending on the magnitude of the charge, device substrates can be punctured ordestroyed by contact or the mere proximity of a static charge. The results can causedegradation of device performance, early failure, or immediate destruction.

These charges are generated in numerous ways such as simple contact, separation ofmaterials, and normal motions of persons working with static sensitive devices.

When handling or servicing equipment containing static sensitive devices, adequateprecautions must be taken to prevent device damage or destruction.

Only personnel who are thoroughly familiar with industry-accepted techniques forhandling 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 worksurfaces and persons handling the devices.

BEFORE APPLYING POWER

Verify that the product is set to match the line voltage and that the correct fusesare installed.

Servicing instructions are for use by service-trained personnel only. To avoid dangerouselectric shock, do not perform any servicing unless qualified to do so.

Adjustments described in the manual are performed with power supplied to theinstrument while protective covers are removed. Energy available at many points may, ifcontacted, result in personal injury.

THE CONTENTS OF THEEQUIPMENT CAN BE

DAMAGED BY STATIC ELECTRICITY.PROPER

HANDLING IS REQUIRED.

Model FA2100 CVRInstruction ManualInstallation & Operation

Page iv Jan. 01/03165E184600 Rev. 07

THIS PAGE IS INTENTIONALLY LEFT BLANK



Page vRev. 07Jan. 01/03

165E184600

RECORD OF CHANGES

ISSUE REVISION DATE OF CHANGE COMMENTS

Initial Mar. 15/99 Initial issue of Installation & Operation InstructionManual. Supersedes FAR 08337220 Rev. Prelimi-nary & FAR 08337220 Rev. Preliminary 01.

01 Feb. 01/00 Specified that this manual is not intended forGACVRs. Updated maximum power require-ments as per the latest revision of the drawings.Consolidated the Appendixes.

02 May 01/00 Added 2100102093 configuration and S160,S161, and S161 Control Units.

03 Oct. 01/00 Added 2100102090 and S056 Microphone.

!"# $ % &' %' $$"()!*$+'

06 Jan. 20/02 Corrected S261 Control Unit Wire Diagram inAppendix A to show 37 pin connector vs 41 pinconnector interface. Added S056 Mic Spec

, -. #$# $/


Page viRev. 07

Jan. 01/03165E184600


Model FA2100CVRInstruction Manual


Page vii165E184600Rev. 07

Jan. 01/03

TABLE OF CONTENTS

Section Page

1.0 INTRODUCTION 1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

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

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

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

1.4 System Overview 2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1.4.1 Recorder Unit 2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1.4.2 Control Units and External Preamplifier 5. . . . . . . . . . . . . . . . . .

1.4.3 Remote Microphone Module 6. . . . . . . . . . . . . . . . . . . . . . . . . . .

1.4.4 CVR Mounting Racks 6. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1.5 Abbreviations and Acronyms 7. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2.0 EQUIPMENT LIMITATIONS/SPECIFICATIONS 7. . . . . . . . . . . . . . . . . . . . .

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

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

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

2.4 Environmental Characteristics 13. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

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

3.0 INSTALLATION PROCEDURES AND LIMITATIONS 13. . . . . . . . . . . . . . .

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

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

3.3 Installation Acceptance by Field Approval Method 14. . . . . . . . . . . . . .

3.4 Recorder Location 14. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3.5 Mounting 14. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

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

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

3.8 Audio System Interface 15. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3.9 Microphone Installation Criteria 16. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

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

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

TABLE OF CONTENTS (Contd)

Section Page

5.0 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. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

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

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

9.0 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 A1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

B ENVIRONMENTAL QUALIFICATION FORMS (EQFs) ED56A AND RTCA/DO160C B1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

C ACCESSORY EQUIPMENT C1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

D ABBREVIATIONS AND ACRONYMS D1. . . . . . . . . . . . . . . . . . . . . . . . . . .

Model FA2100CVRInstruction Manual


Page ix165E184600Rev. 07

Jan. 01/03


List of Illustrations

Figure Page

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

2. Functional System Block Diagram Model FA2100 CVRCockpit Voice Recorder 4. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3. Outline and Dimensions FA2100 CVR Cockpit Voice Recorder, PN 21001010( ) & PN 21001020( ) 10. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4. Outline and Dimensions, CVR Mount, Part Number 178E091900 12. . . . . . . . . . . . . . . . . . .

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

6. On-Aircraft Setup for Checking Out FA2100 CVRsusing a Portable Interface 19. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A1. Part Number Definition, Model S151/S161, Model S152/S162,and Model S251/S261 Control Units A3. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A2. Outline and Dimensions, Model S151 Control Unit A4. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A3. Interwiring Diagram, FA2100 Recorder, S151 Control Unit,S055 Remote Microphone A5. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A4. Outline and Dimensions, Model S161 Control Unit A7. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A5. Interwiring Diagram, FA2100 Recorder, S161 Control Unit,S056 Remote Microphone A8. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A6. Outline and Dimensions, Model S251 Control Unit A10. . . . . . . . . . . . . . . . . . . . . . . . . . . .

A7. Interwiring Diagram, FA2100 Recorder, S251 Control Unit,S055 Remote Microphone A11. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .


A9. Interwiring Diagram, FA2100 Recorder, S261 Control Unit,S056 Remote Microphone A14. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .



A12. Interwiring Diagram, FA2100 Recorder, S152/S162 Control Unitwith Internal Microphone A18. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A13. Outline and Dimensions, Model S150 External Preamplifier Module A20. . . . . . . . . . . . . .

A14. Interwiring Diagram, FA2100 Recorder, S150 External Preamplifier,S055 Remote Microphone A21. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A15. Outline and Dimensions, Model S160 External Preamplifier Module A23. . . . . . . . . . . . . .

A16. Interwiring Diagram, FA2100 Recorder, S160 External Preamplifier,S056 Remote Microphone A24. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A17. Outline and Dimensions, Model S055 Surface-Mount Microphone Module A26. . . . . . . . .


List of Illustrations (Contd)

Figure Page

A18. Outline and Dimensions, Model S055 Panel-Mount Microphone Module A27. . . . . . . . . . .

A19. Outline and Dimensions, Model S056 Surface-MountMicrophone Module A28. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A20. Outline and Dimensions, Model S056 Panel-MountMicrophone Module A29. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A21. Model S055 Microphone Element Specifications and Response Diagram A30. . . . . . . . . . .

A22. Model S056 Microphone Element Specifications and Response Diagram A31. . . . . . . . . . .

A23. Outline and Dimensions, Model A151B Control UnitDoes Not Comply with ED56A A32. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A24. Interwiring Diagram, FA2100 Recorder, A151B Control Unit, A55BRemote Microphone Such Installations Do Not Comply with ED56A A33. . . . . . . . . . . . .

A25. Outline and Dimensions, Model A152B Control UnitDoes Not Comply with ED56A A35. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A26. Interwiring Diagram, FA2100 Recorder, A152B Control Unit with InternalMicrophone Such Installations Do Not Comply with ED56A A36. . . . . . . . . . . . . . . . . . .

A27. Outline and Dimensions, Model A150 External Preamplifier ModuleDoes Not Comply with ED56A A38. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A28. Interwiring Diagram, FA2100 Recorder, A150 External Preamplifier, A55B Remote Microphone Such Installations Do Not Comply with ED56A A39. . . . . . .

A29. Outline and Dimensions, Model A55B Surface-MountDirectional Microphone Module, Does Not Comply with ED56A A41. . . . . . . . . . . . . . . .

A30. Outline and Dimensions, Model A55B Surface-MountMiniCondensor Microphone Module, Does Not Comply with ED56A A42. . . . . . . . . . .

A31. Outline and Dimensions, Model A55B Panel-Mount MicrophoneModule, Rear Connector Does Not Comply with ED56A A43. . . . . . . . . . . . . . . . . . . . . . .

A32. Outline and Dimensions, Model A55B Panel-Mount MicrophoneModule, Top Connector Does Not Comply with ED56A A44. . . . . . . . . . . . . . . . . . . . . . .

C1. Inertia/Impact Switch Model 3LO453/3 C4. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

C2. Aerodyne Controls Corp. Environmentally Sealed Impact Switch Assembly C5. . . . . . . . .

C3. Dukane ULD Tester, Aviation Recorders Part Number 15977 C7. . . . . . . . . . . . . . . . . . . . .

List of Tables

Table Page

Instruction ManualInstallation & OperationModel FA2100 CVR

165E184600Jan. 01/03Rev. 07

Page 1

1.0 INTRODUCTION

1.1 Purpose of Manual

This Installation and Operation Instruction Manual applies to the following Model FA2100 CVR CockpitVoice Recorders:

2100101000 2100102090

2100102000 2100102091

2100102002 2100102093

In this manual, these recorders are referred to as FA2100 CVR, or CVRs. Refer to FA2100 GACVRInstallation Manual (p/n: 165E184800) for the installation of the FA2100 General Aviation CockpitVoice Recorders.

This manual contains date sensitive information necessary to install these CVRs in the aircraft, to operatethem, and to verify that the installed units are operating properly. This manual also describes the featuresand functions of the FA2100 CVR System and associated accessories.

Contact L-3 Communications, Aviation Recorders, to verify this date sensitiveinformation when using this manual to develop other documentation.

Comments or recommendations about the installation, operation, and check out of the FA2100 CVRshould be sent to L-3 Communications, Aviation Recorders, Product Support Department, at the addressshown 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 checkout of these FA2100 CVRs:

This Installation & Operation Instruction Manual.

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

Portable Interface Operators Manual, Part Number 165E163000

Cockpit Voice Recorder System Test Panel, Part Number 9300A860; and Cable Assembly, PartNumber 024E112200 (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 CVRs main (rear) con-nector can be used.

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

Component Maintenance Manual, Cockpit Voice Recorder, Model FA2100 CVR, ATA237004, Part Number 165E1689-00.


165E184600Jan. 01/03

Rev. 07Page 2

1.3 System Description

The FA2100 CVR Systems meet or exceed the requirements of Federal Aviation Administration (FAA)Technical Standard Order TSOC123a, Cockpit Voice Recorder Systems; European Organization forCivilian Aviation Equipment (EUROCAE) Minimum Operational Performance Specification (MOPS)ED56A, 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 ARINCCharacteristic 557 installations.

The FA2100 CVR System consists of the Recorder Unit, the Control Unit, a Preamplifier Module forinstallations 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 usingaircraft 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 Description Weight 1

( 0.5 lbs.)

2100101000 ARINC 404A 1/2-ATR Short Case; ARINC 757, 30 Minutes 10.0 lbs.

2100102000 ARINC 404A 1/2-ATR Short Case; ARINC 757, 120 Minutes 10.0 lbs.

2100102002 ARINC 404A 1/2-ATR Short Case; ARINC 757, 120 Minutes w/FSK 10.0 lbs.

2100102090 ARINC 404A 1/2-ATR Short Case; ARINC 757, 120 Minutes, Military 10.0 lbs.

2100102091 ARINC 404A 1/2-ATR Short Case; ARINC 757, 120 Minutes w/INSITUPlayback

10.0 lbs.

2100102093 ARINC 404A 1/2-ATR Short Case; ARINC 757, 120 Minutes w/8ohmoutput and no Bulk Erase (when used with 93A152-16 Control Unit).

10.0 lbs.

1 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 andCrash Survivable Memory Unit (CSMU) are painted international orange. Two reflective stripes arelocated on the CSMU.

The FA2100 CVR consists of a chassis and front panel, three Printed Wiring Assemblies (AircraftInterface PWA, Audio Compressor PWA, and Acquisition Processor PWA), and the Crash SurvivableMemory 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 mountedhorizontally on the front of the CSMU and is also used as a the recorders carrying handle. The ULD isequipped with a battery that has an expected life of six years. The ULD meets or exceeds therequirements of FAA TSOC121. The Ground Support Equipment (GSE) connector is located on thefront of the FA2100 CVR. This connector provides the interface from the recorder to GSE for checkoutof the recorder, or to transfer data to a readout device. The FA2100 CVR is connected to aircraft wiringvia a 57-pin, DPXB-style connector.


165E184600Jan. 01/03Rev. 07

Page 3

Figure 1. Model FA2100 CVR Cockpit Voice Recorder

Refer to Figure 2 for this discussion. The FA2100 CVR is a Line Replaceable Unit (LRU) thatsimultaneously 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 recordingconfigurations: 30-minute, Part Number 21001010( ), and 120-minute, Part Number 21001020( ).Both configurations record a minimum of 30 minutes of high quality audio from the following fourcockpit audio inputs:

Channel 1: Cockpit Spare Audio Input (3rd Crew Member, Public Address System)Channel 2: Co-Pilots Audio, Boom, Mask, and Hand-Held Microphone InputChannel 3: Pilots Audio, Boom, Mask and Hand-Held Microphone InputChannel 4: Cockpit Area Microphone (CAM) Input

Part Number 21001020( ) records a fifth internal audio stream for a minimum of 120 minutes. Thisfifth internal audio stream is a standard quality recording of the combination of the Pilot, Co-Pilot, andPublic Address or Third Crew Member audio inputs. Part Number 21001020( ) also records a sixthaudio stream, a standard quality recording of the Cockpit Area Microphone (CAM) audio input, for aminimum of 120 minutes. (Table 2 illustrates the recording specifications for the cockpit audio input andcombined channels.) The audio inputs are conditioned, amplified, and equalized as necessary. Theresulting 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 GMTinput 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 faultconditions.


165E184600Jan. 01/03

Rev. 07Page 4

ERASE A

ERASE C

PUSH TO TEST

2

+5 V FORLIGHTED PANEL

2PILOT AUDIO

CO-PILOT AUDIO

SPARE AUDIO(TO 3RD CREW MEMBER

OR PA SYSTEM)

28 VDCOR

115 VAC400 Hz

CHASSISGROUND

TEST INDICATOR

RECORD ON

AIRCRAFT WIRING INTER-LOCKS (LANDING GEAR MUST

BE DOWN AND BRAKE LOCKEDTO ALLOW MEMORY TO BE

ERASED)

CONTROLUNIT

CHANNEL 1

CHANNEL 4

CHANNEL 2

CHANNEL 3

AIRCRAFTINTERFACE

PWA

+18 VDCOPERATING

POWER

MONITORAUDIO TOHEADSET

JACK

AREA MICROPHONE

2

2

2

2

2

2

ACQUISITION PROCESSOR

PWA

CSMU (Crash Survival Memory Unit)

ASSEMBLY (CRASH PROTECTED SOLID STATE MEMORY)

TO AIRCRAFT

FAULT MONITORINGSYSTEM

GSE OUTPUT

COCKPITAREA

MICROPHONE(CAM)

4

STOPRECORDING

AUDIO COMPRESSOR

PWA

FA2100 CVR

CVR FAULT

TOGROUND STATIONTEST EQUIPMENT

GMT_IN_B (429)

GMT_IN_A (429)

ROTOR_SPEED_IN_LO

ROTOR_SPEED_IN_HI

GEAR

BRAKE

AUDIO OUT

+18 VDC

1

Figure 2. Functional System Block Diagram

Model FA2100 CVR Cockpit Voice Recorder


165E184600Jan. 01/03Rev. 07

Page 5

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

Table 2. Model FA2100 CVR Recording Specifications

FA100CVRCockpit Audio Inputs Combined Channels

FA100CVRPart Number Channel 1 Channel 2 Channel 3 Channel 4 Combined

Audio SQCAM SQ

3rd CrewMember/SpareAudio Inputfor High Qual-ity Recording

Co-Pilot Au-dio Input forHigh QualityRecording

Pilot AudioInput for HighQualityRecording

Cockpit AreaMicrophone(CAM) Inputfor High Qual-ity Recording

Summation ofCH 1, 2, & 3Audio Inputsfor StandardQuality Re-cording

Cockpit AreaMicrophone(CAM) (CH 4)Input for Stan-dard QualityRecording

21001010( ) 30 minutes 30 minutes 30 minutes Not Available Not Available

21001020( ) 30 minutes 30 minutes 30 minutes 30 minutes 120 minutes 120 minutes

Note: All of the times in the above table are minimum recording times. Unit can recordinput 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 asthe 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 foractivating the test function via a green push button and an indicator. Bulk Erasure of the FA2100 CVRstorage media is also accomplished by pressing the Control Units red Bulk ERASE push button. AllControl 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 inFA2100 CVR ARINC757 / ED56A System installations. The Model S151 and Model S251 ControlUnits 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-typemicrophone (Model S055, see paragraph 1.4.3).

The Model S161/S261 Controls Units are used with remote microphone modules with internal amplifiersfor reducing RF interference (Model S056, see paragraph 1.4.3). These control units also have frontpanel 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 PreamplifierPWA, TEST and Bulk ERASE switches, TEST indicator lamp and a HEADSET jack.

The Model S150/S160 Preamplifier is available for FA2100 CVR ED56A System installations that donot require a Control Unit. However, because ARINC Characteristic 757 does not address microphonepreamplifiers, the Model S150/S160 Preamplifier is not considered ARINC757 compliant. The S150 isdesigned to be used with the S055 remote microphone. The S160 is used with the S056 remotemicrophone.

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 ED56A. The


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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 ModelA152B contains a built-in condenser microphone, Microphone Preamplifier PWA, and TEST and BulkERASE switches. Both the A151B and A152B Control Units contain an analog TEST meter compatiblewith the FA2100 CVR.

Refer to Appendix A for Control Unit and External Preamplifier outline and dimension illustrations.Refer to Appendix B for RTCA/DO160C environmental test conditions and description ofenvironmental tests conducted.

For Model S151/S161, S152/S162, A151B, and A152B Control Units.

Solder Part Number 9300458Crimp Part Number 0639800577

For Model S251/S261 Control Unit

Solder Kit Part Number 147E126200Crimp Kit Part Number 147E126300

For Model S150 External Preamplifier

19 Pin, Solder Part Number MS3111F1419P 3 Pin, Solder Part Number MS3111F83P

For Model S160 and A150 External Preamplifier

19 Pin, Solder Part Number 0639801897 3 Pin, Solder Part Number 0639801898

1.4.3 Remote Microphone Module

The Model S055 and Model S056 Remote Microphone Modules are available to complete anED56A-compatible installation. The Model S055 Microphone is required with the S151 and S251Control Units and with the S150 Preamplifier Module. The Model S056 Microphone is required with theS161 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 andModel S056 Remote Microphone Module part numbers. Also refer to Appendix A for S055 and S056microphone element specifications and response diagram.

Refer to Appendix B for RTCA/DO160C environmental test conditions and description ofenvironmental tests conducted.

1.4.4 CVR Mounting Racks

A. CVR Mount, Part Number 178E091900

CVR mount with no vibration isolators used to install the FA2100 CVR in the aircraft. Refer to Figure 4for outline and dimensions.

B. Vibration Mount, Part Number 9300343

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


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C. Heavy Duty Vibration Mount, Part Number 93955

CVR mount for use in aircraft environments where excessive vibration may occur, such as in rotorcraft ortest aircraft. Contact Aviation Recorders Product Support for Full Sway Envelope and Outline andDimension Drawings.

D. Connector for CVR Mount

Connector attaches to mount, and mates with the connector on the FA2100 CVRs rear panel. Aircraftwiring is soldered or crimped to the connector pins.

Solder Part Number 9300435Crimp Part Number 0639801474

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 andRacking

ARINC Characteristic 757 Aeronautical Radio, Inc., Cockpit Voice Recorder

ARINC Report 6041 Aeronautical Radio, Inc., Design Guidance for Design and Useof Built-In Test Equipment

ARINC Report 6241 Aeronautical Radio, Inc., Design Guidance for Onboard Mainte-nance System

EUROCAE MOPS ED55 European Organization for Civil Aviation Equipment MinimumPerformance Specification for Flight Data Recorder Systems

EUROCAE MOPS ED56A European Organization for Civil Aviation Equipment MinimumPerformance Specification for Cockpit Voice Recorder System

FEDSTD595 Federal Standard, Colors

RTCA/DO160C Radio Technical Commission for Aeronautics, EnvironmentalConditions and Test Procedures for Airborne Equipment

RTCA/DO178B Radio Technical Commission for Aeronautics, Software Consid-erations in Airborne Systems and Equipment Certification

TSOC123a Federal Aviation Administration Technical Standard OrderCockpit Voice Recorder Systems


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2.2 Physical Characteristics

The Model FA2100 CVRs fit within the envelope of an ARINC 404A 1/2-ATR short case. (Refer to forFigure 3 outline and dimension illustration.) Following are the physical characteristics of the ModelFA2100 CVRs:

Size:

Height:Width:

Depth:

5.5 inches nominalChassis: 4.88 inches nominalFront Panel: 4.98 inches nominal12.6 inches nominal (behind front panel)13.1 inches nominal (including hold-down hooks)

Weight1: 10.0 0.5 pounds

Markings: International Orange (FEDSTD595 Color No. 12197),Reflective Striping on Crash Survivable Memory Unit,English Markings on One Side of Chassis and FrenchMarkings on Other Side of Chassis

Main (Rear) Connector: 57-Pin Connector Compatible with ARINC 757, PartNumber 063E107200 (Cannon Part NumberDPXB3657159)

Main (Rear) Mating Connectors:

Crimp: Part Number 0639801474 (Cannon Part Num-ber DPXBMA5733S0001)

Solder: Part Number 9300435 (Cannon Part Number DPXB5733S0001)

Ground Support Equipment Connector:

Part Number 0639801962 (AMP Part Number7484816)

1 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 21001010( ) = 30 minutes minimumPN 21001020( ) = 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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Audio Quality: Meets ED56A Chapter 3 specifications. Signal-to-noiseplus distortion ratio (SINAD) of the signal when repro-duced > 24 dB (6 % distortion) for the most recent 30minutes 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 inputsErase AErase C

Push-to-Test 1 discreteRecord On 2 discrete inputsStop Recording 1 discrete

Digital Outputs: CVR Fault 1 discrete


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CO

CK

PIT

VO

ICE

RE

CO

RD

ER

MO

DE

L F

A21

00

ESD LABEL

7.5 .5

3.0 .5

5.4 .1

12.60 .04

FARSIDE LABEL READS: ENREGISTRUER DE VOL NE PAS OUVRIR

.2MAX

.5MAX

2.44 .5

NOTES:

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

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.

.5 LBS TOLERANCE.4. OVERALL EQUIPMENT SIZE AND MOUNTING SCHEME COMPLY WITH ARINC 404 AND 404A.

REAR PANEL CONTAINS HOLES TO MATE WITH GUIDE PINS IN ARINC 404 MOUNTING TRAYS.5.

2100-1010-00 H2100-1020-00 G

Figure 3. (Sheet 1 of 2) Outline and Dimensions

FA2100 CVR Cockpit Voice Recorder, PN 21001010( ) & PN 21001020( )


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COCKPIT VOICE RECORDERMODEL FA2100

2.44 .50

POLARIZING KEYSSHADING DENOTESSOLID KEY AREA

.995

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 .04

5.5 .2

4.12

4.98 .04

CRASH SURVIVABLEMEMORY UNIT

UNDERWATER LOCATINGDEVICE

GROUND SUPPORTEQUIPMENT CONNECTOR

(AMP 748481-6)

4

063-98-01962

2100-1010-00 H2100-1020-00 G

.01

REPLACEMENT DATE

Figure 3. (Sheet 2 of 2)Outline & Dimensions

FA2100 CVR Cockpit Voice Recorder, PN 21001010( ) & PN 21001020( )


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NAMEPLATE INFO:NAME: MOUNT, HARD, CVRPN: 178E091900 REV [X]SN: XXXXXDATE: MM/YY

5.38 MAXOUTSIDE

4X 0.182 .010100 CSK

(CG)

9.06

5.60 .50

CL

3.504.12

5.02 .02INSIDE

2.38

1.00 MAX

(CG)

.75 .50

.80 MAX16.41 MAX

4.00 MAX

CLEARANCE HOLESFOR #8 SCREWS

3.500.005

SUGGESTED MOUNTING HOLE PATTERN

9.062 .005

CO

MP

AN

Y L

OG

O

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 0639801474 (CANNON DPXBMA5733S0001)(SOLDER) PN 9300435 (CANNON DPXB5733S0001)

4. SUGGESTED MOUNTING HARDWARE:TO ATTACH CONNECTOR TO MOUNT: 8 EACH 440 X 7/16 PAN HEAD SCREWS PN 2290200076 (MS5195716) OR EQUIV, AND 440 SELF-LOCKING NUTS, PN 16165 (ESNA PN 68166040) OR EQUIV.TO ATTACH MOUNT TO AIRCRAFT: 4 EACH #8 100 T HEAD SCREWS MS24693( ) OR EQUIV (LENGTH AS REQD), AND SELF-LOCKING NUTS MS21044C08 OR EQUIV.

905E091918H

Figure 4. Outline and Dimensions, CVR Mount, Part Number 178E091900


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2.4 Environmental Characteristics

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

2.5 Crash- and Fire-Survival Characteristics

Penetration: ED55/ED56A 500 lbs./10 feet/ probe

Static Crush: ED55/ED56A 5,000 lbs.

Fire Protection: TSOC123a/ED56A 50,000 BTU/sq. feet/hour, 60minutes @ 1100C and 10 hours @ 260C

Impact: ED56A 3400 gs, 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 OperatingInstruction Manual. Acceptance of the installation and use of the FA2100 CVR and its associatedcomponents must be sought from the cognizant Federal Aviation Administration (FAA) office or othercertifying authority. Approvals may be accomplished on a Field Approval basis if the installation isdetermined to meet the criteria of the appropriate Post-Installation, Preflight, and Flight tests specified forevaluation in this Installation Manual. (Refer to paragraph 3.3.) Proposed installations should becoordinated with the local jurisdiction of the FAA or other certifying authority before beginning recorderinstallation.

Refer to the following statement which was extracted from FAA TSOC123a:

The conditions and tests required for TSO approval of this article are minimum perfor-mance standards. It is the responsibility of those desiring to install this article either on orwithin a specific type or class of aircraft to determine that the aircraft installation conditionsare within the TSO standards. The article may be installed only if further evaluation by theapplicant 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 Characteristic757 dated December 29, 1993.

The Federal Aviation Administration has issued several Advisory Circulars which may be referred to inthe approval processes. Advisory Circular 25.14571a specifically addresses one acceptable means ofcompliance with Federal Aviation Regulation (FAR) 25.1457 (b), (e), and (f). Installations must conformto the Operating Rules in FAR23.1457, 25.1457, 27.1457, and 29.1457 appropriate to the category ofoperation 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. Thecircuitry required for Bulk ERASE includes the installation of interlock devices on board the aircraft. If


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the Bulk ERASE feature is installed, at least one interlock is required to prevent accidental erasure of theFA2100 CVR. If the BULK ERASE feature is not desired, pin 55 (ERASE A) of the FA2100 CVR mustbe 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. TheCVR should be installed in accordance with the instructions and limitations contained in this InstallationManual. Installation drawings and other information, such as structural data showing the method ofattachment of the CVR components to the airframe, wiring diagrams, appropriate weight and balancedata, and identification of all CVR system components used in the installation should be made availableto the Inspector conducting the Field Approval.

The CVR Installation Manual containing Operating Instructions and System Description must be madeavailable to the inspector for review and evaluation of the CVR System. The applicant must submit anFAA Form 337, describing the work performed to the airframe to accomplish the installation of the CVRSystem. 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 locationsidentified in FAA Advisory Circular 25.14571A and in accordance with the instructions contained inthis Installation Manual. The applicant should submit all appropriate data and drawings to the inspectorbefore the installation of the Cockpit Voice Recorder. Any deviations to the installation instructionscontained in this Installation Manual must be brought to the inspectors attention and be so identified onthe Form 337.

Finally, ground and flight tests must be conducted to verify that the Audio System Interface issatisfactory and that normal conversation can be discerned from the Cockpit Area Microphone and theindividual Pilot, Co-Pilot, and appropriate Third Crew Member or Public Address stations. The CVRSystem 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 inspectorsattention and corrected before the aircraft can be returned to service.

If required, Aviation Recorders can reproduce the CVR memory contents onto cassettes for channelseparation and evaluation. Contact the Product Support Department to coordinate this process. If youprefer 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 bythe airframe manufacturer, as far aft as practicable. The recommended orientation is mounted in anupright position (vertical as viewed from the front).

3.5 Mounting

The Model FA2100 CVR is certified and approved for installation in aircraft environments within thelimits of RTCA/DO160C Curve C. Installation accessories (CVR Mount and Mount Connectors) aredescribed in paragraph 1.4.4.


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On aircraft with an existing CVR Vibration Mount such as Part Number 9300-343 or equivalent, or withan existing Heavy Duty CVR Vibration Mount such as Part Number 93955 or equivalent, it is notnecessary 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 providepower to the Flight Data Recorder. Each bus will need to meet the supply reliability requirementsappropriate for the recorders being powered.

The FA2100 CVR operates with input voltages of either 115 Vac at 400 Hz, or 28 Vdc. The FA2100CVRs draw a maximum of 12 watts ac or 10.5 watts dc. The electrical connector is a 57-pin DPXBconnector that is compatible with ARINC 757 (Part Number is 063E107200, Cannon Part NumberDPXB3657159). 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 ARINCCharacteristic 757. Connections to the FA2100 CVR J1 connector depend on the installationconfiguration. 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 througha 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:


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 controlpanel. 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 continuousreception of audio from the communications radios.

Old Systems: Rework the audio control panel or system to provide a CVR output or install an externalsumming amplifier. Summing amplifiers can be obtained from Avtec, Baker Electronics, Racal, andothers. 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 isresponsible for determining the means of interfacing to comply with the regulations.


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Future Systems: Audio control panels and systems designed to meet or exceed the characteristics ofRadio Technical Commission for Aeronautics RTCA/DO170 for hot boom microphone capabilitymay 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 orientedlaterally through the pilots and co-pilots normal head position. The Cockpit Area Microphone must facethe crew members. Refer to Figure 5 for an illustration of the preferred placement for the Cockpit AreaMicrophone. Ensure that the microphone is mounted such that the exposed portion of the microphoneelement is unobstructed.

RECOMMENDED MICROPHONE LOCATIONSARE 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 thatThere [must be] an automatic means to simultaneously stop the recorder and prevent each erasurefeature from functioning, within 10 minutes after crash impact. The Installer must demonstrate thisfunction.

Since the FA2100 CVR System can be powered by either 115 Vac at 400 Hz, or 28 Vdc, the followingmethods are acceptable to ensure automatic cessation of recording:


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A. Engine-driven 115 Vac, 400 Hz Source: If power input is derived directly from an engine-driven115 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 predeter-mined 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 manufacturersspecifications for available models.)

C. ARINC 757 Shutdown Signal: The FA2100 CVR continuously monitors the ARINC 757 shut-down signal that can be supplied to the recorder via pin 10 of the rear panel connector. If the air-craft can no longer sustain flight under its own power, a ground would be applied to pin 10. If thissignal remains active for approximately 10 consecutive minutes, recording of data will cease.

The recording will resume if the shutdown signal goes inactive or upon activation of the Push-to-Test function. If the recording is resumed due to execution of the Push-to-Test, the recordingwill again cease within 10 minutes if the shutdown signal is still active. Refer to section 3.11 ofARINC 757 for further information.

4.0 POST-INSTALLATION CHECKOUT

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

1. Before applying power to the FA2100 CVR System and associated components, verify that allconnections are secure and that a continuity or other interconnect assurance test has been con-ducted.

2. Apply power to the system and activate the FA2100 CVRs 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/S261Control Unit, the cockpit-mounted TEST lamp illuminates when the FA2100 CVR has passedthe 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 needlerises and comes to rest in the GO (green) section of the meter scale when the FA2100 CVRhas passed the test. (The meter stays in the GO section of the meter scale as long as theTEST button is pressed.)

4. Speak in a normal voice 6-inches away from the Control Unit microphone while listening inthe 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 thefour audio channels as they are being recorded by the FA2100 CVR. The PI is connected tothe FA2100 CVR via a 10-foot cable that is plugged into the FA2100 CVRs front panel GSEconnector (refer to Figure 6). The PI receives power from the FA2100 CVR. For a descrip-tion of the PI, descriptions of the menu functions, and PI operation, refer to the Portable In-terface Operators Manual (Part Number 165E163000).

NOTE: Previously recorded information cannot be played back from the FA2100 CVR while it isinstalled in the aircraft.


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Using the following procedure, verify that the four following channnels inputs are recordingcorrectly, regardless of Audio Control Panel mode or audio (communications radio) selection:

Channel 1: Cockpit Spare Audio Input (3rd Crew Member, Public Address System) Channel 2: Co-Pilots Audio, Boom, Mask, and Hand-Held Microphone InputChannel 3: Pilots Audio, Boom, Mask and Hand-Held Microphone InputChannel 4: Cockpit Area Microphone (CAM) Input

a. Connect the PI to the FA2100 CVRs GSE connector as shown in Figure 6.

b. Using the PIs 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 clearand distortion-free. Monitor the audio with the PIs internal speaker or with a 600-ohm head-set connected to the PIs phone jack (an 8ohm headset must be used for the 2100102093configuration).

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 thereal 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 Label150. GMT can also be supplied as FSK audio mixed with channel 1 or 3 with the2100102002 recorder.

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

6. The Bulk Erase function can occur only when the aircraft is resting on its landing gear. Afterpressing and holding the Control Units bulk ERASE push button for a minimum of 2 se-conds, release it and verify Bulk Erase function by listening for a 400-Hz tone at the HEAD-SET 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, itmust be performed before every flight or whenever maintenance has been performed on the aircraft whichmay have affected the performance of the FA2100 CVR System.

Press and hold the Cockpit Control Units 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 TESTlamp 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 aGO-NO-GO indicating device. The meter needle rises to and remains within, the GO (green) sectionof the meter scale when the FA2100 CVR has passed the testing. (The meter needle stays in the GOsection of the meter scale as long as the TEST button is pressed.)


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FA2100CVR

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 FA2100CVRs recorded data for later playback. Depending on type of recorder used, the FA2100CVRs 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.

PI AUXREADOUT CABLE

17TES0052 1, 2

TO RECORDERGSE CONNECTOR

PI AUDIOREADOUT CABLE

17TES0051 1, 3

DATA FROM RECORDER

ROTOR

GMT

PORTABLE INTERFACE (PI)

17TES0043

HQ

SQ COMB CAM

CH 1 2 3 4

Figure 6. On-Aircraft Setup for Checking Out FA2100 CVRs using a Portable Interface


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5.2 Complete Audio System Check

A complete Audio System Test must be completed under the following three conditions; during eachannual inspection, specified maintenance period, and whenever unscheduled maintenance is performedwhich may affect the performance of the Cockpit Voice Recorder System. To accomplish this test, thePilots, Co-Pilots, Cockpit Area Microphone, and Third Crew Member or Public Address System inputsmust be individually checked for their operational integrity with the FA2100 CVR. Upon satisfactorycompletion of this test, an entry shall be made in the aircraft or rotorcraft maintenance records. Using thePI, 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 thePortable Interface Operators Manual (Part Number 165E163000).

NOTE: Previously recorded information cannot be played back from the FA2100 CVR while it isinstalled 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:


(1) Connect the PI to the FA2100 CVRs GSE connector as shown in Figure 6.

(2) Using the PIs 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 dis-tortion-free. Monitor the audio with the PIs internal speaker or with a 600-ohm headsetconnected to the PIs phone jack (an 8ohm headset must be used for the 2100102093configuration).

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

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

5.3 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 isinstalled in the aircraft. This requirement is noted in ARINC Characteristic 757 and EUROCAEED56A, and is a security feature to protect the privacy rights of pilots and other crew members. TheFA2100 CVR must be removed from the aircraft, connected to an AC or DC source as appropriate, andconnected 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; PortableInterface Operators Manual, Part Number 165E163000; Cockpit Voice Recorder System Test Panel,


165E184600Jan. 01/03Rev. 07

Page 21

Part Number 9300A860; Cable Assembly, Part Number 024E112200; and Component MaintenanceManual, Cockpit Voice Recorder, Model FA2100 CVR, ATA 237004. Instead of the 9300A860 TestPanel, the PI and a customer-fabricated cable to provide appropriate power to the FA2100 CVRs main(rear) connector can be used to play back previously recorded data.

The Portable Interface Operators Manual, Part Number 165E163000, contains the procedures for usingthe 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 uponpower-up. When the recorder is installed and wired in accordance with section 3.0 of this document, therecorder 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 shouldbe prepared for use by the cockpit crew. It is important for participants to bear in mind that, to obtain asatisfactory 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 recordedinformation. A test program not exceeding 30- or 120-minutes of recording time, depending on recorderversion, should be planned prior to the test flight. The FA2100 CVR circuit breaker may be pulled andreset 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 eachcondition, identify any significant events or warnings, and encourage conversation between crewmembers.

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 pilots PRE-FLIGHT FUNCTIONAL CHECK contained in this manual.

c. Check and identify, by speaking into the area microphone and listening for playback at theheadset jack, the airplane identification, date, and time.

d. Check and identify the fire warning bell. Also, record a short excerpt of the pre-start checklistcalled out by the crew.

e. Record the normal cockpit conversations for one minute after one engine has started. Eachcrew member shall identify himself by name. The Test Director shall announce airplane sta-tus and identify any warning sounds.

f. Open FA2100 CVR circuit breaker.


165E184600Jan. 01/03

Rev. 07Page 22

2. Taxi, Takeoff, and Climb

a. Close FA2100 CVR circuit breaker. Before releasing the brake, apply takeoff engine powerand 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 bymonitoring 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 verifyaural disconnect sound. Using the flight interphone facilities, each crew member shall identi-fy 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 thecockpit speakers at proper listening level.

c. Climb to 25,000 feet. Each crew member will don his oxygen mask and will say This is thepilot/co-pilot speaking through his oxygen mask microphone. Repeat this test for the head-set 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; reducespeed approximately 5 knots so that clacker stops. Hold this speed and have crew memberidentify flight status via the area microphone, to acquire a reasonable amount of recordedspeed.

c. Reduce thrust until landing gear warning horn sounds. The pilot will identify himself andwarning device sounding.

d. Reduce thrust until stall warning horn sounds. The pilot will identify himself and warningdevice sounding.

e. Make a flight crew member announcement on the aircraft public address system advising cab-in 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. Thepilot 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-flightcrew headsets, (including the marker beacon signal) should be recorded for post-flight play-back.

g. Open FA2100 CVR circuit breaker.

5. Post-Flight

Remove FA2100 CVR from aircraft and play stored data back via the Portable Inter-face (PI). Record flight data onto a format usable by the examiner/inspector, such ason a cassette.


165E184600Jan. 01/03Rev. 07

Page 23

9.0 MAINTENANCE AND CALIBRATION

9.1 Recorder

The Model FA2100 CVR does not require scheduled maintenance or calibration, except for periodicinspection/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 toFAA TSOC121. The ULD is mounted horizontally on the front of the CSMU for easy removal and foreasy viewing of the battery expiration date. The ULD requires functional testing and cleaning every 24months. (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 expectedbattery life, contact ULD manufacturer for replacement batteries, installation instructions, andrecertification.

9.3 Product Support

Mailing/Contact Information:

L3 CommunicationsAviation RecordersP.O. Box 3041Sarasota, Florida 342303041Attention: Product Support, Mail Stop 20

Telephone: (941) 3710811Telefax: (941) 3775591SITA: SRQLFCRWeb Site: www.L-3ar.com

9.4 Authorized Repair Facilities

Aviation Recorders performs repair and readout services for the Model FA2100 CVR System. Itemsneeding repair should be shipped to the following address:

L-3 Communications Aviation Recorders6000 East Fruitville Road Sarasota, Florida 34232 Attention: Repair Station

Questions concerning FA2100 CVR repair may be answered by calling the Aviation Recorders RepairStation at (941) 3775517 or (941) 3775579, or by calling the Product Support Department at (941)3710811. 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, orvisit 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 CVRsavailable for rental.


165E184600Jan. 01/03

Rev. 07Page 24




Rev. 07Jan. 01/03

165E184600Page A1

APPENDIX A

OUTLINE & DIMENSIONS MICROPHONES, CONTROL UNITS, &

EXTERNAL PREAMPLIFIERS

Jan. 01/03Rev. 07

Page A2165E184600




Rev. 07Jan. 01/03

165E184600Page A3

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S151002000S151003000S151004000S151005000S151006000

S152002000S152003000S152003001 *S152004000

S161002000S161002010 S161003000S161004000S161005000S161006000

S162002000S162003000S162004000

S251112000S251113000S251117000

S261112000S261113000

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Figure A1. Part Number Definition, Model S151/S161, Model S152/S162, and Model S251/S261

Control Units

Jan. 01/03Rev. 07

Page A4165E184600

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

TEST

HOLD5 SEC

HEADSET ERASE

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PNR: S151XXXXXXSER: XXXXXXXXXMFR: 06141

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MODIFICATIONS

1 2 3

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10 11 1213 14 15

DATE: MMYYYY

CONTROL UNITMODEL S151

2DBAR

CODE

Figure A2. Outline and Dimensions, Model S151 Control Unit



Rev. 07Jan. 01/03

165E184600Page A5

AUDIO OUT LOAUDIO OUT HIRECORD ON BRECORD ON A+28 VDC POWER INSTOP RECORDING

PUSH TO TEST

TEST INDICATOR +TEST INDICATOR CHASSIS GND

CVR FAULT

GMT IN B (ARINC 429) LOGMT IN A (ARINC 429) HI

CHANNEL 1 LO

CHANNEL 1 HI

CHANNEL 2 LO

CHANNEL 2 HI

CHANNEL 3 LO

CHANNEL 3 HI

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CHANNEL 4 HIROTOR SPEED IN LOROTOR SPEED IN HI

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FROM CAPTAINSCLOCK

TO ANNUNCIATOROR MAINT.

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TEST INDICATOR +TEST INDICATOR

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OUTPUT LOOUTPUT HI

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MIC LOW (GREEN)

FROM ROTORSPEED

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SPARE MICROPHONETO 3RD CREWMEMBER ORPA SYSTEM

TO COPILOT MICROPHONE

TO PILOTMICROPHONE

MODEL S055MICROPHONE

5

10

13

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Figure A3. Interwiring Diagram, Voice Recorder Unit, S151 Control Unit,

S055 Remote Microphone

Jan. 01/03Rev. 07

Page A6165E184600

Notes for Figure A3:

1. Recommended minimum wire size is #22; however, wire size #24 is electrically permissibleexcept for long-run power leads where #18 wire is recommended (pins 2, 3, 9, & 17). Wireresistance should not exceed 1 ohm for power leads and should not exceed 5 ohms for signalleads. All wiring should be MILW22759 or MILC27500.

2. Only one power source is to be wired per aircraft. If 115 Vac, 400 Hz is supplied, no connec-tion 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 previouslyrecorded information, bulk erase will not activate, and test will indicate NOGO.

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 crashshould be included in the aircraft wiring. Grounding pin 10 terminates recording within 10minutes.

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 betransposed; that is, Channel 1 will be Pilot and Channel 3 will be Third Crew Member or PASystem.

12. In the Model A200S, this option is not available.

In the Model FA2100, 21001010( ) and 21001020( ) configurations GMT is inputted aslow speed (12.5 kbps) ARINC-429 to pins 25 and 26. In addition, the 02 versions can alsoaccept GMT as an FSK signal combined with the audio input signals on either Channel 1 orChannel 3. In all CVR configurations, the 205E1849( ) Audio Compressor card providesboth 150 (1 sec resolution) and 125 (0.1 min. resolution) for 429 GMT inputs.

13. S055 Panel-mount microphones are equipped with a Cannon TMRBIM0 Twinax recep-tacle. Mating connectors are Cannon TMPL30 or TMPL2F39. Recommended cable isWTWC 2CE2419.2SJ, L3 P/N: 0249800294.



Rev. 07Jan. 01/03

165E184600Page A7

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

TESTHOLD 5 SEC HEADSET

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TO ANNUNCIATOR ORMAINT. COMPUTER

SPARE MICROPHONETO 3RD CREWMEMEBER OR

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TO COPILOTMICROPHONE

TO PILOTMICROPHONE


5

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CHANNEL 3 HI

9

13

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Figure A14. Interwiring Diagram, Voice Recorder Unit, S150 External Preamplifier,


Jan. 01/03Rev. 07

Page A22165E184600





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




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



11. !"#$%&%'!%()%*+,$-.'



13. S055 Panel-mount microphones are equipped with a Cannon TMRBIM0 Twinax recep-tacle. Mating connectors are Cannon TMPL30 or TMPL2F39. Recommended cable isWTWC 2CE2419.2SJ, L3 P/N: 0249800294.



Rev. 07Jan. 01/03

165E184600Page A23

Jan. 01/03Rev. 07

Page A24165E184600

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9

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Figure A16. Interwiring Diagram, Voice Recorder Unit, S160 External Preamplifier,




Rev. 07Jan. 01/03

165E184600Page A25





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




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



11. !"#$%&%'!%()%*+,$-.'



13.

Jan. 01/03Rev. 07

Page A26165E184600

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Rev. 07Jan. 01/03

165E184600Page A31

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Jan. 01/03Rev. 07

Page A32165E184600

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PART PANEL METERNUMBER COLOR ILLUMINATION93A15120 Gray None93A15130 Black None93A15140 Brown (Boeing) None93A15150 Brown (ATR42) None93A15160 DO328 BLUE 28V93A15170 DO328 BLUE None

1.125 .002

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Figure A23. Outline and Dimensions, Model A151B Control Unit

Does Not Comply with ED56A



Rev. 07Jan. 01/03

165E184600Page A33

1. 115 VAC HOT OUT2. 115 VAC HOT IN3. AC COMMON COLD4.5. AUDIO OUT LO6. AUDIO OUT HI7. BIAS JUMPER8. BIAS JUMPER9. +27.5 Vdc INPUT10. STOP RECORDING11.12. PUSH_TO_TEST13. PREAMP POWER OUT GND14. PREAMP POWER +18 Vdc REG15. INDICATOR +16. INDICATOR 17. CHASSIS GROUND18.19.20.21.22.23. CVR FAULT24.25. GMT IN B (ARINC 429) LO26. GMT IN A (ARINC 429) HI27.28.29.30. LO31. CHANNEL 132. HI33.34.35. LO36. CHANNEL 237. HI38.39.40.41. LO42. CHANNEL 343. HI44.45. LO46. CHANNEL 447. HI48. ROTOR SPEED IN LO49. ROTOR SPEED IN HI50.51.52.53.54.55. ERASE A56.57. ERASE C

PUSH_TO_TESTPREAMP POWER GNDPREAMP POWER +18 VDCINDICATOR +INDICATOR CHASSIS GROUNDERASE SWITCH AERASE SWITCH C

OUTPUT LOWOUTPUT HIGHMIKE CABLE SHIELDMIKE INPUT HIMIKE INPUT LO

FILTER COMMONFILTER 1.000 HZ

AUDIO JACK LOAUDIO JACK HI

6 DB ATTENUATIONATTENUATOR_ COMMON12 DB ATTENUATION

24 DB ATTENUATION

MIC OUTPUT HI (AUDIO)MIC OUTPUT LO ( DC IN )MIC SHIELD (CONNECTOR SHELL)

1AMP

TO 115 VAC HOT (400HZ)TO AC COLD

5AMPS

3

ABCDEFGHJKLMNPRSTUVWXYZabcdefghijkpqrst

12

12

6

3

3, 7

TO 27.5VDC

MODEL A151BCONTROL UNIT

MODEL A55BMICROPHONE

COCKPIT AREA MICROPHONE

STANDARD INTERWIRING PER ARINC SPEC 557

2, 8

BRAKE GEAR

5

VOICE RECORDER UNIT



9

5

4

10, 11

TO PILOT MICROPHONE


SPARE MICROPHONE TO 3RD CREWMEMBER ORPA SYSTEM

FROM CAPTAINSCLOCK

10

10, 11

10

8

14

13

Figure A24. Interwiring Diagram, Voice Recorder Unit, A151B Control Unit,

A55B Remote MicrophoneSuch Installations Do Not Comply with ED56A

Jan. 01/03Rev. 07

Page A34165E184600



2. Only one power source is to be wired per aircraft. If 115 Vac, 400 Hz is supplied, no connec-tion is to be made to pin 9. If 27.5 Vdc is supplied, no connection is to be made to pin 3.Shorting pins 1 & 2 is optional.


4. Jumper in aircraft connector. Without this jumper, the unit will not record or erase previouslyrecorded information, bulk erase will not activate, and test will indicate NOGO.


6. Wiring shown for fixed attenuation of 18 dB.



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


11. Per FAA Action Notice A8300.56 dated Jan. 24, 1990, the wiring to Channels 1 and 3 may betransp

FA2100 CVR Install Manual

Documents

Transcript of FA2100 CVR Install Manual