INSTALLATION & OPERATIONINSTRUCTION MANUAL

MODEL A100 / A100ACOCKPIT VOICE RECORDER

(SUPERSEDES FAR 02213189)

Rev. 02July 01/02

RECORDER PART NUMBERS:93A10010 93A10011 93A1001193A10030 93A10031 93A1003293A10033 93A10080 93A1008193A10082 93A10083 93A1008493A10085

CONTROL UNIT MODEL NUMBERS:93A15100 93A15101 93A1512093A15130 93A15140 93A1515093A15200 93A15201 93A1520493A15220 93A15225 93A1523093A15235 93A15240 93A1525093A15260 93A15270

MICROPHONE MODULE MODEL NUMBERS:93A05500 93A05510 93A0552093A05530 93A05540 93A0554593A05550 93A05555 93A0556093A05565 93A05566 93A0556793A05595

EXTERNAL PREAMPLIFIERS MODEL NUMBERS:93A15020

Manufactured in Accordance withTSOC84/ARINC 557

P/N: 165E280700

Part Number 165E280700Rev. 01

July 01/02

Copyright 2002 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 install re-corders in aircraft. Contact L-3 Communications, Aviation Recorders,to verify this date sensitive information prior to using this manual to de-velop other documentation.

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.

THIS PAGE IS INTENTIONALLY LEFT BLANK

TABLE OF CONTENTS

Section Page

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

1.1 Purpose 1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1.2 System Description and Limitations 1. . . . . . . . . . . . . . . . . . . . . . . . . . .

1.3 Recorder Unit 3. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1.4 Control Unit 3. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1.5 Remote Microphone Module 3. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1.6 Installation Accessories 3. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

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

2.1 Leading Particulars Model A100 and A100A Recorders 7. . . . . . . . . .

2.2 Leading Particulars Model A151, A151B, A152, A152BControl Units 8. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2.3 Leading Particulars Model A55 Remote Microphone Module 8. . . . .

2.4 Leading Particulars Model A55B Remote Microphone Module 9. . . .

3.0 INSTALLATION INSTRUCTIONS 10. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3.1 General Information 10. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3.2 Audio System Interface 11. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3.3 Recorder Location 11. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3.4 Microphone Installation Criteria 12. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3.5 Cessation of Recording 12. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3.6 Installation in Rotorcraft 13. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3.7 Installation Procedure for Inverter, P/N 9300A14001 14. . . . . . . . . .

3.8 PostInstallation Checkout Procedures 15. . . . . . . . . . . . . . . . . . . . . . . .

4.0 OPERATION TESTS 16. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4.1 Pre-Flight Functional Check 16. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4.2 Complete Audio System Test 16. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5.0 INSTALLATION ACCEPTANCE BY FIELD APPROVAL METHOD 17. . . .

6.0 MAINTENANCE 18. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

6.1 Underwater Locator Beacon 18. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

6.2 Product Support 18. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

6.3 Authorized Repair Facilities 18. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

6.4 Loaner / Rental Program 19. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

TABLE OF CONTENTS (Contd)

Appendixes

Appendix Page

A OUTLINE & DIMENSION DRAWINGS A1. . . . . . . . . . . . . . . . . . . . . . . . . .

B ACCESSORY EQUIPMENT B1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CALIBRATED SOUND SOURCE, Model A870 B3. . . . . . . . . . . . . . . . . . . .

INERTIA / IMPACT SWITCH, Inertia Switch Inc. Model 3LO453 B7. . . .

CVR AUDIO MIXER, Avtech Model 502011 B9. . . . . . . . . . . . . . . . . . . .

C ENVIRONMENTAL QUALIFICATION FORMS C1. . . . . . . . . . . . . . . . . . .

TABLE OF CONTENTS (Contd)

List of Illustrations

Figure Page

1. Cockpit Voice Recorder, Model A100 2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2. Rotor Speed Encoder, P/N 253E087300 5. . . . . . . . . . . . . . . . . . . . . . . . . . . .

3. Rotor Speed Encoder Typical Mounting Installations 6. . . . . . . . . . . . . . . . . . .

4. Recommended Cockpit Area Microphone Mounting Locations 12. . . . . . . . . .

5. Inverter Installation 14. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

6. Cockpit Voice Recorder System Control Unit A151B, Functional BlockDiagram 20. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7. Cockpit Voice Recorder A100 and Control Unit A152B, Functional BlockDiagram 21. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

8. Channel Allocation in CVRs 22. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

9. Interwiring Diagram, Recorders A100, A100A, Control Units A151, A151B, Remote Microphones A55, A55B 23. . . . . . . . . . . . . . . . . . . . . . . . . .

10. Interwiring Diagram, Recorders A100, A100A, Control Units A152, A152B 24. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

11. Interwiring Diagram, Recorders A100, A100A, Control Units A150 25. . . . . .

A1. Outline & Dimension Drawing, Model A100, P/N 93A10010, 11 A3. . . .

A2. Outline & Dimension Drawing, Model A100 with Beacon andBeacon Mount, P/N 93A10030, 31, 32, 33 A4. . . . . . . . . . . . . . . . . . . .

A3. Outline & Dimension Drawing, Model A100A, P/N 93A10081 A5. . . . . . .

A4. Outline & Dimension Drawing, Model A100A with Beacon, andBeacon Mount, P/N 93A10080, 82, 83, 84, 85 A6. . . . . . . . . . . . . . . .

A5. Outline & Dimension Drawing, CVR Vibration Mount, P/N 9300343 A7. .

A6. Outline & Dimension Drawing, Heavy Duty CVR VibrationMount, P/N 93955 A8. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

TABLE OF CONTENTS (Contd)

List of Illustrations (Contd)

Figure Page

A7. Outline and Dimension Drawing, Model A151 Control Unit, P/N 93A15100 A9. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A8. Outline and Dimension Drawing, Model A151B Control Unit, P/N 93A15120, 30, 40, 50 A10. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A9. Outline and Dimension Drawing, Model A152 Control Unit, P/N93A1520020 A11. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A10. Outline and Dimension Drawing, Model A152B Control UnitP/N 93A15220, 30, 40, 50, 70 A12. . . . . . . . . . . . . . . . . . . . . . . . . . . .

A11. Outline and Dimension Drawing, Model A150 Preamplifier, P/N 93A15020 A13. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A12. Outline and Dimension Drawing, Model A55 Microphone, P/N 93A05500 A14. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A13. Outline and Dimension Drawing, Model A55B Microphone, P/N 93A05510, 30, 50 A15. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A14. Outline and Dimension Drawing, Model A55B Microphone, P/N 93A05520, 55 A16. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A15. Outline and Dimension Drawing, Model A55B Microphone, P/N 93A05540, 45 A17. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A16. Outline and Dimension Drawing, Model A55B Microphone P/N 93A05560, 65, 67 A18. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A17. Outline and Dimension Drawing, Model A55B Microphone, P/N 93A05566 A19. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A18. Outline and Dimension Drawing, Model A55B Microphone, P/N 93A05595 A20. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

B1. Calibrated Sound Source, P/N 9300A870 B3. . . . . . . . . . . . . . . . . . . . . . . . .

B2. Cockpit Voice Recorder System Test Panel, P/N 9300A860 B3. . . . . . . . . . .

B3. Condenser Remote Microphone Test Setup B4. . . . . . . . . . . . . . . . . . . . . . . .

1.0 INTRODUCTION

1.1 Purpose

The information contained within this Installation Manual describes the administrative andtechnical aspects, features, functions, components, and operation of the A100/A100A Cock-pit Voice Recorder (CVR) system and its accessories and components. Any and all com-ments or recommendations regarding the installation, acceptance, or operation of the CVR orits accessories and components should be directed to the Product Support Department of L3Communications Aviation Recorders.

The following L3 Aviation Recorders are covered in this Installation & Operation Instruc-tion Manual:

Part Number Model Mount ULB Inverter Installed93A10010 A100 No No No93A10011 A100 No No Yes93A10030 A100 Yes Yes No93A10031 A100 Yes Yes Yes93A10032 A100 Yes No Yes93A10033 A100 Yes No No93A10080 A100A Yes Yes No93A10081 A100A No No No93A10082 A100A Yes No No93A10083 A100A Yes Yes Yes93A10084 A100A Yes No Yes93A10085 A100A No No Yes

1.2 System Description and Limitations

The Cockpit Voice Recorder system has been designed to meet or exceed those requirementsspecified within and is approved under Federal Aviation Administration Technical StandardOrder C84 or C111.

The Cockpit Voice Recorder system is composed of three essential components: the RecorderUnit, Control Unit Components with area microphone module, and Vibration Mount. AHeavyDuty Vibration Mount is available for rotorcraft installations.

The CVR simultaneously records four separate voice inputs. These inputs may be eithertransmitted or received signals originating from the following recommended stations: Pilot,CoPilot, Public Address or Third Crew Member, and Cockpit Area Microphone.

Cockpit Voice Recorder, Model A100Figure 1

Approval of the Cockpit Voice Recorder system is not authorized by this Installation Manual.Acceptance for the installation and use of the CVR and its associated components must besought through the appropriate offices of the Federal Aviation Administration or other certi-fying agency. Aprovals may be accomplished on a Field Approval basis if the installation isdetermined to meet the criteria of the appropriate Postinstallation, Preflight, and Flight testspecificed for evaluation within this Installation Manual. It is recommended that all proposedinstallations be coordinated with the local jurisdiction of the Federal Aviation Administrationor other certifying agency prior to performing the installation.

1.3 Recorder Unit

The recorder is housed in an inertnational orange, 1/2 ATR short case. It contains the record-er assembly and associated electronics. (See Section 2.1 for leading particulars.) RecorderModels A100 and A100A can be used in any system configuration and are totally inter-changeable. An Underwater Locator Beacon is available as required by regulations.

1.4 Control Unit

The control units are standard ARINC characteristic 306 panel format. Models A152 andA152B house microphone preamplifier, microphone, test switch, erase switch, and meter.Models A151 and A151B house microphone preamplifier, test switch, erase switch, and me-ter. (Refer to Sections 2.2 for leading particulars.)

1.5 Remote Microphone Module

Remote microphone modules, Models A55 and A55B are used when cockpit space limita-tions exist. Remote microphone modules are used in conjunction with control unit ModelsA151 and A151B. (Refer to Sections 2.3 through 2.4 for leading particulars.)

1.6 Installation Accessories

A. Vibration Mount P/N 9300343Standard mount equipped with four (4) vibration isolators. (See Figure 18.)

Isolator load range:Rear: 2.50 5.50 lbs.Front: 5.00 10.00 lbs.

Spring loaded pins guide the CVR connector to mate with the mount connector. Two(2) holddown screws on the front of the mount lock the Recorder Unit into postion.

B. Heavy Duty Vibration Mount P/N 93955Mount for use in aircraft environments where excessive vibration may occur, such asin rotorcraft or test aircraft. (See Figure 19.)

Isolator load range:Rear: 3.00 6.00 lbs.Front: 9.00 15.00 lbs.

C. Connector P/N 9300435Connector attaches to Vibration Mount and mates with connector on rear panel ofCVR. Aircraft wiring is soldered to the pins of the connector.

D. Inverter P/N 9300A14001 (Supersedes P/N 9300A140)Optional 28 VDC to 115 VAC 400 Hertz inverters are available. Inverter may beplugged into available connector internal to the recorder. See Section 3.7 for Installa-tion procedure. Jumper must be added accross Pins 1 & 2 of the mount connector(P/N 9300435, Cannon P/N DPXB5733S0001). When DC power is used, ameans should be provided to stop recording after powered flight has been terminated.

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Rotor Speed Encoder, P/N 253E087300Figure 2

E. Rotor Speed Encoder P/N 93A289An optional Rotor Speed Encoder is available for use in rotorcraft. The Rotor SpeedEncoder module meets CAA requirements for CVR rotor speed recording. The RotorSpeed Encoder allows for simultaneous recording of rotor speed data and voice on thesame audio channel. It uses a subcarrier at 4600 Hz which is phase modulated. (SeeFigure 2 for description.)

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Rotor Speed Encoder Typical Mounting InstallationsFigure 3

F. Rotor Speed Encoder Mount P/N 93A291An optional Rotor Speed Encoder mount is available to directly mount the RotorSpeed Encoder to the Vibration Mount. (See Figure 3 for description.)

F. Rotor Speed Encoder Bracket P/N 93A324An optional Rotor Speed Encoder bracket is available to mount the Rotor Speed En-coder to the airframe, a bulkhead, etc. A 15pin connector is attached to provide in-terconnection with the CVR. (See Figure 3 for description.)

2.0 EQUIPMENT LIMITATIONS / SPECIFICATIONS

2.1 Leading Particulars Model A100 and A100A Recorders

Designed to TSOC84 and ARINC Characteristic 557.

Size: 1/2 ATR Short4 7/8 Width by 12 9/16 Length by 7 5/8 Height

Color: International Orange

Weight (Max): 23.9 lbs.

Power: 115 VAC +/ 10%, 400 Hz +/ 5%20 Watts max normal operation50 Watts max bulk erase

Connections: See Interwiring Diagram

Mating Connector: DPXB5733S001 (L3 P/N 9300435)

Tape (Endless Loop): 1/4 preconditioned recording tape, mylar base

Transport Drive: Direct No clutches

Tape Speed: Standard NARTB; 17/8 ips

Channels: 4 inline coincident recording

Recording Duration: 30 minutes minimum

Head Assembly: Precision aligned 3 heads

Bulk Erase: Failsafe, double electrical interlock. Total erase inexcess of 35 dB

Operational Testing: Automatic four channels sequential600 Hz audio signal recorded and reproduced to trig-ger a gonogo gate controlled meter indicator.

Frequency Response: 150 to 5000 Hz + 3 dB

Recorded Signal to NoiseRatio:

45 dB min

Monitor System: Composite 4 channel playback

Monitor Output: Headphone jack, 600 Ohms, 10 mW

Harmonic Distortion: Less than 5%

Flutter: 1.5% RMS maximum

Audio Input Impedance: 5000 Ohms each channel

Basic Subassemblies: 10 plugin boardsTape transportEnvironmental protection

2.2 Leading Particulars Model A151, A151B, A152, A152B Control Units

Size: ATA Panel5.75 Width by 2.25 Height by 2.5 Depth

Color: Grey, Black, or Brown

Weight (Max): 1.2 lbs.

Connector: MS31122041P

Mating Connector: P/N 9300458Cannon P/N MS3116F2041S

Front Panel: MeterTest Switches (2)Headset JackMicrophone (Models A152 & A152B only)

AGC: Fast reacting 30 dB rangeLow distortionTrue AC attenuation

Audio Input Impedance: 20K Ohms

Audio Input Level: 3 mV

Ouput Impedance: 300 Ohms

Output Level: 500 Millivolts

Audio FrequencyResponse:

150 5000 Hz

Audio Gain: Pin selected 6, 12, 24, dB steps

DC Supply: Plus 18 Volts

2.3 Leading Particulars Model A55 Remote Microphone Module

Size: Side Connector Models:3.56 Length by 2 Width by 2.25 Height

Back Connector Models:3.87 Length by 2 Width by 2 Height

Weight: 0.5 lbs.

Color: Black

Connector: Cannon Twinax #TM RB1M0

Mating Connector: P/N 9300457Cannon P/N 1509000303

Mounting: Front or Rear Panel

Microphone: Dynamic Type

2.4 Leading Particulars Model A55B Remote Microphone Module

For all Model A55B Part Numbers, except 93A05540 and 93A05545 Remote Micro-phones.

Size: Side Connector Models:3.76 Length by 2 Width by 2.25 Height

Back Connector Models:4.07 Length by 2 Width by 2 Height

Weight: 0.5 lbs.

Color: Black or Brown

Connector: Cannon Twinax #TM RB1M0

Mating Connector: P/N 9300457Cannon P/N 1509000303

Mounting: Front or Rear Panel

Microphone: Condenser Type

For only the Model A55B Part Numbers 93A05540 and 93A05545 Remote Micro-phones.

Size: 2.5 Length by 1.1 Width by 1.2 Height

Weight: 4 oz.

Color: Grey, Brown, or Black

Connector: Shield twisted pair pigtail

Microphone: Condenser Type

3.0 INSTALLATION INSTRUCTIONS

Installation of the recorder, control unit, and remote microphone module is based on ARINCCharacteristic 557, dated January 10, 1964.

3.1 General Information

This section contains considerations and recommendations for installation of the CockpitVoice Recorder and associated system components. Interconnect harness wiring, physicalmounting, optional components (preamplifiers and summing amplifiers) must be consideredwhen requirwed to satisfy all applicable regulations. The conditions and tests required forTSO approval of this article are minimum performance standard. It is the responsibility ofthose desiring to install this article either on or within a specific type or class of aircraft todetermine that the aircraft installation conditions are within TSO standards. If not withinTSO standard, the article may be installed only if the applicant documents further evaluationfor an acceptable installation and it is approved by the Administrator of the Federal AviationAdministration or other certifying agency.

The Federal Aviation Administration has issued several Advisory Circulars which may bereferred to in the approval processes. Advisory Circular 25.14571a specifically addressesone 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, and29.1457 appropriate to the category of operation under FAR Parts 91, 135, and 121 (Air Car-rier).

The CVR system is powered by 115 VAC. It may also be powered by 28 VDC from the es-sential aircraft bus source, when the optional DV inverter is installed.

To ensure optimal performance from the Cockpit Voice Recorder System, the following wiresizes and types are recommended as acceptable:

A. All wires except pins 2, 3, 9, and 17: Use #24 AWG or larger, for maximum 500 ft.length if shielded pairs are used. All wiring should be MILW22759 orMILC27500.

B. For pins 2, 3, 9 (power leads), and 17 (ground), use the following as a minimum:#24 AWG, shielded pairs 240 ft. max.#22 AWG, shielded pairs 375 ft. max.

C. Ground connection to be within one foot of pin 17.

D. Single point ground. Reasons for specifying single point ground for pin 17 are tominimize random noise pcikup.

E. Normal power requirements are:20 Watts maximum during normal operation.50 Watts maximum during bulk erase.

The BULK ERASE connection is not mandated by the FAA and, therefore, it is an installa-tion option. The circuitry required for BULK ERASE includes the installation of interlockdevices aboard the aircraft. If the BULK ERASE feature is installed, then at least one (1) in-terlock is required to prevent accidental erasure of the CVR tape. If the BULK ERASE fea-ture is not desired, Pin 55 (ERASE A) must be grounded to Pin 17. Pin 57 remains open.

3.2 Audio System Interface

The range of acceptable audio input levels for the CVR is from 50 mV RMS to 500 mVRMS.

Earlier aircraft audio systems may require rework of their audio system to ensure recordingof ATC, Intercom, Mask Microphone, and Sidetone audio, independant of mode selection onthe audio control panel. In some cases, selection of the Loud Speaker function disables sidetone output and, therefore, transmissions to ATC may not be recorded. Such condition mustbe remedied to provide continous received audio from the communications radios.

Old Systems Rework the audio control panel or system to provide a CVR output or installan external summing amplifier. Summing amplifiers can be obtained from Avtec, BakerElectronics, Racal, and others. (See Appendix B & C for examples.) The addition of a sum-ming amplifier provides existing audio systems with the hot boom microphone capability.No changes to the CVR are required. (See Figure 7 for typical summing amplifier installa-tion.)

New Systems Some later generation audio control panels have a CVR signal output alreadyprovided. A summing amplifier may be required to provide hot boom microphone opera-tion. It is the responsibility of the Installer to determine the means of interfacing to complywith the regulations.

Future Systems Those audio control panels and systems designed to meet or exceed thecharacteristics found in Radio Technical Commission for Aeronautics (RTCA), DO170 forhot boom microphone capability, may be determined to be acceptable.

3.3 Recorder Location

The Cockpit Voice Recorder is certified and approved for installation in any combination ofthe following conditions: Heated/unheated, pressurized/unpressurized, hard mounted/shockmounted.

For long term reliability it is recommended that recorders be mounted within the vibrationmount in an upright position (vertical as viewed from the front) in a heated, pressurized areain a fuselage location, as far aft as practical. Refer to FAA Advisory Circular 25.14571Afor further details.

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RECOMMENDED MICROPHONE LOCATIONSARE NUMBERED IN ORDER OF PREFERENCE

Recommended Cockpit Area Microphone Mounting LocationsFigure 4

3.4 Microphone Installation Criteria

The most desirable location for the cockpit area microphone is forward of a vertical planeoriented laterally through the pilots and copilots normal head position. The area micro-phone must face the crew members. (Refer to Figure 4.)

3.5 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 andprevent each erasure feature from functioning, within 10 minutes after crash impact. TheInstaller must demonstrate this function.

Since the CVR system can be powered by either 115 VAC, 400 Hz or 28 VDC (with optionalinverter), the following methods are acceptable to ensure automatic cessation of recording:

1. IMPACT SWITCH Interrupts CVR power upon exposure to a predertimed level ofgforce. Such switches have limitations, but are effective in high gforce accidents.This item is not available through L3 Communications. (See Appendix A and F formanufacturers specifications for models available.)

2. If power input is derived directly from the enginedriven 115 VAC, 400 HZ source,(not derived from AC Inverter), no other external circuitry is necessary. It is assumedthat the engine(s) will stop upon crash impact.

3.6 Installation in Rotorcraft

The Heavy Duty Dibration Mount P/N 93955 is recommedned for rotorcraft installations. Ithas larger isolators to dampen vibration to the CVR.

A Rotor Speed Encoder (RSE) may be required for the installation in accordance with CAA(U.K.) regulations. There are two configurations for mounting the Rotor Speed Encoder withthe CVR system. (See Figure 3.) The first configuration affixes the Encoder module directlyonto a heavyduty vibration mount, P/N 93A291. The second configuration mounts theRSE module on a small bracket, P/N 93A324, away from the CVR. This bracket must beattached to a bulkhead or a similar rigid surface.

The Rotor Speed Encoder has interlock circuitry which will prevent the CVR Bulk Erasurewhile the main rotor(s) is rotating. If the rotorcraft CVR system is not equipped with a RSEor another suitable interlock, the Bulk Erase feature must be disabled.

If the Bulk Erase feature is not used, Pin 55 (Erase A) must be grounded to Pin 17, and Pin57 remains open to satisify appropriate Federal Aviation Regulations.

INVERTER RAILSTUDS (4 PLACES)

CHASSISJOINT

440X5/16BINDING HEAD

SCREWS

CABLE GUARDP/N 9300428

DETAIL A DETAIL B

CONNECTORP.N 9300232

INVERTER

DETAIL C

Inverter InstallationFigure 5

3.7 Installation Procedure for Inverter, P/N 9300A14001

This procedure applies only to the optional installation of the Inverter into Model A100 andA100A Cockpit Voice Recorders. See Figure 5.

1. Remove dust cover by removing two phillips head screws, exposing chassis wiringassembly.

2. Remove two 440 by 5/16 binding head screws located on the rear of the chasis. (SeeDetail A.) Discard attaching lock nuts.

3. Insert cable guard, P/N 9300428, as shown in Details A and B, ensuring the slottedend is fitted over the rear chassis joint. Fold cable guard over connector and harness.

4. Insert Inverter over chassis wiring assembly engaging it in the four inverter rail studs(Detail B) and connector (Detail C).

5. Reinsert and tighten the two 440 by 5/16 binding head screws removed in Step 2, se-curing the Inverter.

6. Replace the dust cover using two phillips head screws.

7. Refer to the CVR Component Maintenance Manual, P/N 165E010100, for ElectricalTest of Inverter.

3.8 PostInstallation Checkout Procedures

The following tests and procedural results must be documented in the CVR InstallationChecklist and submitted with the date package for field approval consideration.

A. Before applying power to the CVR system and associated components, verify that allconnections are secure and that a continunity or other interconnect assurance test hasbeen conducted.

B. Apply power to the system and activate the Cockpit Voice Recorder selftest. To acti-vate, push and hold the green TEST button for a minimum of five seconds. An in-ternal 600 Hz test tone generator is keyed and sequentially switches through the fourchannels of the recorder. Each channel receives the test tone for approximately .8 sec-onds.

C. Monitor circuitry receives the test tone signals and drives the meter, a GONOGOindicating device, located on the Cockpit Control Unit. The meter needle rises andcomes to rest in the GO (green) section of the meter scale.

Because of the short time interval between each channel being fed the test tone, themeter needle rises to an indication but does not completely fall to a zero indication be-tween signals, giving more of an oscillating action or a slight dithering action. In theevent of a channel failure, the meter needle will fall out of the green section of the me-ter scale or return to zero and give a definite NOGO indication.

D. Aural monitoring of the 600 hertz test tone and channel switching can be accom-plished with a 600 ohm headset inserted into the Jack located on the Cockpit ControlUnit.

With the headset inserted into the Jack located on the Cockpit Control Unit, speak in anormal voice 6 away from the Cockpit Control Unit microphone and note that youcan hear what you speak with approximately a 1/2 second delay without any signifi-cant distortion. This test ensures the microphone is operating.

E. Verify that the following microphone inputs are recorded on their appropriate CVRchannels, regardless of Audio Control Panel mode or audio (communications radio)selection, for Cockpit Voice Recorder installations within aircraft or rotorcraft in-tended for service within the National Airspace Systems:

CHANNEL 1: Third Crewmember Station or Public Address Systems.CHANNEL 2: Primary CoPilots Boom, Mask, and Hand Microphone Input.CHANNEL 3: Primary Pilots Boom, Mask, and Hand Microphone Input.CHANNEL 4: Cockpit Mounted Area Microphone.

F. The Bulk Erase function can occur only when the aircraft is resting on its landing gear.After depressing the bulk erase button (must be pushed in and held for a minimum of2 seconds), verify function by listening for loud 400 Hz tone through the HEADSETjack. Tone duration is approximately 5 12 seconds.

4.0 OPERATION TESTS

4.1 Pre-Flight Functional Check

The Pre-flight Functional Check assures the operator that the equipment is servicable. There-fore, it is to be performed before every flight or whenever maintenance has been performedon the aircraft or rotorcraft which may have affected the performance of the Cockpit VoiceRecorder or its associated Audio System interface, accessories, or components..

Push and hold Test button located on the Cockpit Control Unit for a minimum of five se-conds. A 600 hertz generator is keyed and sequentially switched through the four channels ofthe recorder. Each channel receives the test tone for approximately 0.8 seconds. The metercircuit receives these signals and drives the meter, a GONOGO indicating device, locatedon the Cockpit Control Unit. The meter needle rises and comes to a rest in the GO (green)section of the meter scale.

Because of the short time interval between each channel being fed the test tone, the meterneedle rises to an indication but does not completely fall to a zero indication between signals,giving more of an oscillating action or a slight dithering action. In the event of a channelfailure, the meter needle will fall out of the green section of the meter scale or return to zeroand give a definite NOGO indication.

4.2 Complete Audio System Test

A test of the Cockpit Area Microphone can be accomplished with a 600 Ohm headset in-serted into the remote HEADSET jack or into the HEADSET jack on the Control Unit.Speak in a normal voice 6 away from the Cockpit Area Microphone, and determine audibleclarity after approximately a 1/2 second delay without any significant distortion. This testensures that the Cockpit Area Microphone is operating.

A complete Audio System Interface test must be completed during each annualinspection orspecified maintenance period on the aircraft or rotorcraft and whenever unscheduled mainte-nance is performed on the aircraft or rotorcraft which may have affected the performance ofthe Cockpit Voice Recorder system. To accomplish this test, the Pilots, Co-pilots, CockpitArea Microphone, and Third Crewmember or Public Address System inputs must be individ-ually checked for their operational integrity with the Cockpit Voice Recorder. Upon satisfac-tory achievement of this test, an entry shall be made in the maintenance records of the aircraftor rotorcraft.

5.0 INSTALLATION ACCEPTANCE BY FIELD APPROVAL METHOD

An applicant for Field Approval of a CVR installation must be properly certificated and ap-propriately rated, qualified, and equipped to accomplish the installation and approve the air-craft or rotorcraft for returntoservice. The CVR should be installed in accordance with theinstructions and limitations contained within this Installation Manual.

Drawings and other information, such as structural related data to show the method of attach-ment of the CVR components to the airframe, wiring diagrams, appropriate weight and bal-ance data, identification of all CVR system components used in the installation should bemade available to the Inspector conducting the Field Approval.

The CVR Installation Manual containing Operating Instructions and System descriptionsmust 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 airframeto accomplish the installation of the CVR system. The Form 337 must also include a state-ment that a complete Audio System Interface test was performed as required.

The applicant must make a statement on Form 337 that the Cockpit Area Microphone isinstalled within the recommended locations identified within FAA Advisory Circular25.14571A and in accordance with the instructions contained within this Installation Manu-al.

The applicant should submit all appropriate data and drawings to the Inspector prior to begin-ing the installation of the Cockpit Voice Recorder.

Any deviations to the installation instructions contained within this Installation Manual mustbe brought to the attention of the Inspector and so stated on 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 Micro-phone and the individual Pilot, Copilot, and appropriate Third Crewmember or Public Ad-dress stations. The CVR System must be found to be free of any objectionable audio inter-ference and other unwanted noise in order to ensure discernible recordings. Anydiscrepancies identified during the ground and flight tests must be brought to the attention ofthe Inspector and corrected before the aircraft can be returned to service.

If required, L3 can reproduce the CVR tape contents onto a cassette for channel seperationand evaluation. Contact the Product Support department to coordinate this process.

6.0 MAINTENANCE

6.1 Underwater Locator Beacon

The CVR carries the Dukane Model N15F210B or Model DK 100 Underwater Locator Bea-con (ULB). Both units are manufacturered under a Parts Manufacturer Approval. The bea-con is attached on the front panel for easy removal for replacement of the battery, and foreasy viewing of the battery expiration date.

The Model DK 100 contains a battery life of 6 years prior to its actual operating life of atleast 30 days. The battery must be replaced by Dukane upon expiration.

6.2 Product Support

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

Telephone: (941) 3710811

Telefax: (941) 3775591

SITA: SRQLFCR

Web Site: www.L3AR.com

6.3 Authorized Repair Facilities

L3 Communications Aviation Recorders performs repair, overhaul, and readout services forthe A100 / A100A Cockpit Voice Recorder System. Items should be shipped to the followingaddress:

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

Questions concerning SSFDR repair or readout service may be answered by calling the Avi-ation Recorders Repair Station at (941) 3775554 or (941) 3775579, or by calling the Prod-uct Support Department at (941) 3710811. Readout Service is performed by the Repair Sta-tion.

L3 Communications Aviation Recorders has factory trained technicians at each AuthorizedRepair Facility located worldwide, who are capable of performing repair, overhaul, readout,and loaner / rental services. Contact the Product Support Department for names and loca-tions.

6.4 Loaner / Rental Program

L3 Communications Aviation Recorders Authorized Repair Facilities are capable of pro-viding loaner / rental CVRs. Some facilities may not charge for loaner CVRs if the repair /overhaul work is performed by that repair facility.

Aviation Recorders Product Support Department maintains a limited supply of Rental Cock-pit Voice Recorders. Please contact the Product Support Department for availability and pric-ing.

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