FA2100 CVR Install Manual

Aviation RecordersP.O. Box 3041 Sarasota, Florida 34230 CAGE Code 06141 INSTALLATION & OPERATION INSTRUCTION MANUAL MODEL FA2100 CVR COCKPIT VOICE RECORDER 1/2-ATR SHORT CASE (SUPERSEDES FAR 08337220) RECORDER PART NUMBERS: 2100–1010–00 2100–1020–00 2100–1020–02 2100–1020–90 2100–1020–91 2100–1020–93 CONTROL UNIT MODEL NUMBERS: S151 S152 S251 A151B S161 S162 S261 A152B MICROPHONE PREAMPLIFIER MODULE MODEL NUMBERS: S150 A150 S160 REMOTE MICROPHONE MODEL NUMBERS: S055 A55B S056 Manufactured in Accordance with FAA TSO–C123a/EUROCAE ED–56A/ARINC 757 Rev. 07 January 01/03 P/N: 165E1846–00 Model FA2100 CVR Installation & Operation Instruction Manual Part Number 165E1846–00 Rev. 07 Jan. 01/03 This manual contains date sensitive information necessary to install recorders in aircraft. Contact L-3 Communications, Aviation Recorders, to verify this date sensitive information prior to using this manual to develop other documentation. The recorder products/software are being exported from the United States in accordance with the Export Administration Regulations ECCN 4D994, No License Required. Diversion contrary to U.S. law is prohibited. In accordance with U.S. Law (31 CFR Part 746, and Supplement No.1 to Part 774, and CFR Part 550) resale/re–export or transfer to the countries identified therein is prohibited without the prior written consent of the U.S. Department of Commerce. ECopyright 2003 by L-3 Communications Corporation Aviation Recorders All rights reserved. No part of this manual may be reproduced or utilized in any form or by any means, electronic or mechanical, including photocopying, recording, or by information storage and retrieval system, without permission in writing. Inquiries should be addressed to: L-3 Communications Corporation Aviation Recorders Technical Publications P. O. Box 3041 Sarasota, Florida 34230 (941) 371–0811 FAX: (941) 377–5591 CAGE Code 06141 Model FA2100 CVR Installation & Operation Instruction Manual THE CONTENTS OF THE EQUIPMENT CAN BE DAMAGED BY STATIC ELECTRICITY.PROPER HANDLING IS REQUIRED. GENERAL This product and related documentation must be reviewed for familiarization with safety markings and instructions before operation. This instrument was constructed in an ESD (electrostatic discharge) protected environment. This is because most of the semiconductor devices used in this instrument are susceptible to damage by static discharge. Depending on the magnitude of the charge, device substrates can be punctured or destroyed by contact or the mere proximity of a static charge. The results can cause degradation of device performance, early failure, or immediate destruction. These charges are generated in numerous ways such as simple contact, separation of materials, and normal motions of persons working with static sensitive devices. When handling or servicing equipment containing static sensitive devices, adequate precautions must be taken to prevent device damage or destruction. Only personnel who are thoroughly familiar with industry-accepted techniques for handling static sensitive devices should attempt to service circuitry with these devices. In all instances, measures must be taken to prevent static charge build-up on work surfaces and persons handling the devices. BEFORE APPLYING POWER Verify that the product is set to match the line voltage and that the correct fuses are installed. Servicing instructions are for use by service-trained personnel only. To avoid dangerous electric shock, do not perform any servicing unless qualified to do so. Adjustments described in the manual are performed with power supplied to the instrument while protective covers are removed. Energy available at many points may, if contacted, result in personal injury. Rev. 07 Jan. 01/03 165E1846–00 Page iii Installation & Operation Instruction Manual Model FA2100 CVR THIS PAGE IS INTENTIONALLY LEFT BLANK 165E1846–00 Page iv Rev. 07 Jan. 01/03 Model FA2100 CVR Installation & Operation Instruction Manual RECORD OF CHANGES ISSUE REVISION DATE OF CHANGE COMMENTS Initial — Mar. 15/99 Initial issue of Installation & Operation Instruction Manual. Supersedes FAR 08337220 Rev. Preliminary & FAR 08337220 Rev. Preliminary 01. 01 Feb. 01/00 Specified that this manual is not intended for GACVRs. Updated maximum power requirements as per the latest revision of the drawings. Consolidated the Appendixes. 02 May 01/00 Added 2100–1020–93 configuration and S160, S161, and S161 Control Units. 03 Oct. 01/00 Added 2100–1020–90 and S056 Microphone. 04 Mar. 01/01 Clarified when the Audio System Check is reĆ quired. 05 Aug. 15/01 Fixed Control Unit drawings to seperate the S151 drawing from the S161 drawing, and the S152 drawing from the S162 drawing in AppenĆ dix A. Clarified GMT/FSK operation for -02 configurations. 06 Jan. 20/02 Corrected S261 Control Unit Wire Diagram in Appendix A to show 37 pin connector vs 41 pin connector interface. Added S056 Mic Spec 07 Jan. 01/03 Updated Control Unit information. Changed recommended microphone cabling. Rev. 07 Jan. 01/03 165E1846–00 Page v Installation & Operation Instruction Manual Model FA2100 CVR THIS PAGE IS INTENTIONALLY LEFT BLANK 165E1846–00 Page vi Rev. 07 Jan. 01/03 . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 EQUIPMENT LIMITATIONS/SPECIFICATIONS . . 2 1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4 Installation Acceptance by Field Approval Method . . . . . . . . . . . . . . . . . . . . . . . .0 1. . .3 Remote Microphone Module . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Purpose of Manual . . . . . . . . . . . . . . . . . .3 Electrical Characteristics . . . . 13 Crash. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 3. . . . .2 Physical Characteristics . 6 1. . . . . . . . . . . . . 07 Jan. . . . . . . . 13 3. . . . . . . . . . . . . . . . . . . . . . . . . . .6 Power Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 1. . . . . . . . . . . . . . . . . 13 3. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .7 Wiring Connections . . . .5 Environmental Characteristics . . . . . 8 2. .4. . . 7 2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .0 3. .4 CVR Mounting Racks . . . . . . . 14 Recorder Location . .9 Audio System Interface . . .0 Page INTRODUCTION . . . . . . . . .8 3. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 1. . . . .3 3. . . . . . . . . . . . . . . . . . . . . . . . . . .1 Installation Precautions . . . . . . .4. . . . . .2 Equipment and Document Requirements . . . 15 Microphone Installation Criteria .1 Applicable Documents . . . . . . . . . . . . . .4 System Description . . . . . . . . . . . . . . . . . . . . .5 2. . . . . . . . . . . . . . 6 Abbreviations and Acronyms . . . . . . . .2 Control Units and External Preamplifier . . .10 Cessation of Recording . . . 2 System Overview . . .0 Rev. . . . . . . . . . . .4. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 01/03 POST-INSTALLATION CHECKOUT . . . . . . . . . . . . . . . . . . . . . . .3 1. . . . . . . . . . . . . . . . . . . . . . . . . . 13 INSTALLATION PROCEDURES AND LIMITATIONS . . . . . 17 165E1846–00 Page vii . . . . . . . 5 1. . . . . . . . . . . . . . . . . . .5 Mounting . . . . . . . . . . . . . . . . . . 2 1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 4. . . . . . . . . .4. . . . . . . . . . . . . . . . . . . .4 2. . . 1 1. . . . . . . . . . . .2 General Information . . . . . . . . . . . . 8 2. . 14 3. . . . . . . . . . . . . . . . . . . . .Model FA2100CVR Installation & Operation Instruction Manual TABLE OF CONTENTS Section 1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 2. . 16 3. . . . . . . . . . . . . . .and Fire-Survival Characteristics . . . . . . . . . . 15 3. . . . . . . . . . . . . . 15 3. . . . . . . . . . . . . . . . . . . .1 Recorder Unit . . . . . . . . . . 14 3. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 8. . . . . . . 21 8. . . . B–1 C ACCESSORY EQUIPMENT . . . . . . . 21 9. . . . . . . . .4 Authorized Repair Facilities . . . . . . . . . . . . . . . . . . . . . . . . . . . .0 OPERATING INSTRUCTIONS . . . . . . . . . . . .0 8. . . . . . . . . . . . . . . . . . . 20 6. . . . . . . . . . . . . . . .0 FLIGHT CHECKOUT PROCEDURE . . . . . . . . . . . . . . . . . . . . . 18 5. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Recorder . . . .0 Page OPERATIONAL TESTS . . . . . . . .3 Product Support . . . . . . . . . . . 23 9. . . . . . . .5 Loaner/Rental Program . 21 MAINTENANCE AND CALIBRATION .Installation & Operation Instruction Manual Model FA2100 CVR TABLE OF CONTENTS (Cont’d) Section 5. . . . . . . . . . . . . . . 23 9. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 9. . . . . . . . . . . . . . . . . . . 20 7. . . . . . . . . . . . . . . . . . . . . . . .0 FA2100 CVR READOUT . . . . . . . . . 20 5. . . . . . CONTROL UNITS. . . . . . . . 23 9. . . . . . . . . . . . . . . . . . . . . . . . . . . C–1 D ABBREVIATIONS AND ACRONYMS . . . . . . . . . . . . . . . . . . . . . . . . .1 Operational Notes . . . . . 23 Appendixes Appendix Page A OUTLINE & DIMENSIONS MICROPHONES. . . . . . . .2 Underwater Locator Device . . . . . . . 07 Jan. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A–1 B ENVIRONMENTAL QUALIFICATION FORMS (EQFs) ED–56A AND RTCA/DO–160C . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Preflight Functional Check . . & EXTERNAL PREAMPLIFIERS . . . . . . . . 23 9. . . . . 18 5. . 01/03 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3 Flight Checkout Procedure . .2 Complete Audio System Check . . . . . . . . . . . . . . . . . . . . . . . . .2 Flight Checkout . . . . . . . . . . . . . . D–1 165E1846-00 Page viii Rev. . . . . . . Part Number 178E0919–00 . . . . . . . . CVR Mount. . . . . S055 Remote Microphone . . . . . Model S162 Control Unit . . . . . . A–23 A–16. . . . . . Model S152 Control Unit . . . . . . . . Interwiring Diagram. . S152/S162 Control Unit with Internal Microphone . . . . . . Interwiring Diagram. . . . . . . A–16 A–11. . Part Number Definition. . . . . . . . . . . . . . . . A–13 A–9. . . . . . . Outline and Dimensions. . . . . . . . . . . . . . . Model S055 Surface-Mount Microphone Module . . . . . . . . . . A–8 A–6. . . . . . . . . . PN 2100–1010–( ) & PN 2100–1020–( ) . . . . . Model S150 External Preamplifier Module . . . . . . . . . . A–26 Rev. . . . . . . . . . . . . . . Model S261 Control Unit . . . . . . . . . S151 Control Unit. . . . . . . . . . A–11 A–8. . . . . 4 3. FA2100 Recorder. . . A–21 A–15. . . Outline and Dimensions. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Interwiring Diagram. . A–17 A–12. . . . . . . . . . . . . . A–7 A–5. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Outline and Dimensions. . . . . . Interwiring Diagram. . . . . . . . . . . . . . . . . . . A–24 A–17. . . . . . . . . Model S251 Control Unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . S261 Control Unit. . . . . . . . FA2100 Recorder. 3 2. . . . . FA2100 Recorder. . . Model FA2100 CVR Cockpit Voice Recorder . . . Outline and Dimensions. . S056 Remote Microphone . . . . . . . . . Outline and Dimensions FA2100 CVR Cockpit Voice Recorder. . . . . . . . . . . . . . . . . . . . 12 5. . . . . . . . . . . . . . Outline and Dimensions. . . . . . . . . . . . . . . . . . . . . . . . . . . . . Outline and Dimensions. . . . Functional System Block Diagram Model FA2100 CVR Cockpit Voice Recorder . . . . . . . . . Outline and Dimensions. . A–3 A–2. . . . . . . . . . . . . . . . . Outline and Dimensions. . . . . . . . . . . . . . . . . . . . . . . . . . . . . Interwiring Diagram. . . A–5 A–4. . . . . . . . . . . . . . . . . . . . . . . . . . . . FA2100 Recorder. . . .Model FA2100CVR Installation & Operation Instruction Manual TABLE OF CONTENTS (Cont’d) List of Illustrations Figure Page 1. . . Model S161 Control Unit . . . . . . . . 10 4. Interwiring Diagram. . . . . . . S056 Remote Microphone . . . . . . . . . . . . . . . . Recommended Cockpit Area Microphone Mounting Location . . . . . . Model S151 Control Unit . . . . . . . . . . . . . . . . A–14 A–10. . . . . 01/03 165E1846–00 Page ix . . . . . A–20 A–14. . . . . . . . . . . . . . . . . . . . . . On-Aircraft Setup for Checking Out FA2100 CVRs using a Portable Interface . FA2100 Recorder. . . A–18 A–13. . . . . . Outline and Dimensions. S251 Control Unit. . . . . . S161 Control Unit. . . . . . . . . . . . . . . . . . . . . . . . . . . . . FA2100 Recorder. . . . . . . . . . . . . . . . . FA2100 Recorder. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Model S160 External Preamplifier Module . . . A–10 A–7. S150 External Preamplifier. . . . . . . . . . . . S056 Remote Microphone . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Model S151/S161. S055 Remote Microphone . Interwiring Diagram. . . . . . 07 Jan. A–4 A–3. . . . . . . . . S055 Remote Microphone . . . . . . . . 19 A–1. . . . . . . . . . . . . . . . . . . and Model S251/S261 Control Units . . 16 6. . . . . . . . . . . . . . Model S152/S162. . . . . . . . Outline and Dimensions. . . . S160 External Preamplifier. Aerodyne Controls Corp. . . . . . . . . . . A–36 A–27. . . . . 07 Jan. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Model A152B Control Unit Does Not Comply with ED–56A . . . . . . A150 External Preamplifier. . . . . . . . . . . . . A–31 A–23. . . FA2100 CVR Descriptions . . . Does Not Comply with ED–56A . . Interwiring Diagram. . . Aviation Recorders’ Part Number 15977 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Model S055 Microphone Element Specifications and Response Diagram . . . FA2100 Recorder. . . . . . . . . . . . . . Outline and Dimensions. . . Model A151B Control Unit Does Not Comply with ED–56A . . . . Dukane ULD Tester. A–27 A–19. . . . . . . . . . . . . . . . . . . . . . . . . . A–44 C–1. Model A55B Panel-Mount Microphone Module. . . . . . A55B Remote Microphone Such Installations Do Not Comply with ED–56A . Top Connector Does Not Comply with ED–56A . . . . . Model A55B Surface-Mount Directional Microphone Module. . Inertia/Impact Switch Model 3LO–453/3 . . . . . Rear Connector Does Not Comply with ED–56A . . . . . . . . . . . . Model A150 External Preamplifier Module Does Not Comply with ED–56A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Environmentally Sealed Impact Switch Assembly . Outline and Dimensions. . . . Outline and Dimensions. . A–43 A–32. . . . . . . . A–29 A–21. . . . . . . . . . . . . . . . . . . FA2100 Recorder. . . . A–28 A–20. . . . . Outline and Dimensions. . . . . . . . . . . . . . . . A55B Remote Microphone Such Installations Do Not Comply with ED–56A . . . . . . . . . A–42 A–31. . . . . . . . . . Model S056 Panel-Mount Microphone Module . A–39 A–29. . . . . . . . . . . . . A–41 A–30. . . . . . . . . . . . . . . . . . . . C–7 List of Tables Table Page 1. 2 2. . . . Interwiring Diagram. . A151B Control Unit. . 01/03 . . . . . . . . Outline and Dimensions. . . . . . . . . . . . . . . . . . . Does Not Comply with ED–56A . . . Outline and Dimensions. . . . . . A–33 A–25. . . . . . . . . . . . . . . . . . . . . . . . Model S055 Panel-Mount Microphone Module . . A–30 A–22. . . . . . . . . . . . . C–5 C–3. . . Outline and Dimensions. . . . . . . . . . . . . . . Outline and Dimensions. . . . . . . . . . . . . . . . . . . . A–35 A–26. . . 5 165E1846-00 Page x Rev. Model S056 Microphone Element Specifications and Response Diagram . . . . Interwiring Diagram. . . . FA2100 Recorder. . . . . . . . . Model A55B Panel-Mount Microphone Module. . . . . . . .Installation & Operation Instruction Manual Model FA2100 CVR TABLE OF CONTENTS (Cont’d) List of Illustrations (Cont’d) Figure Page A–18. . . . . . . . . A152B Control Unit with Internal Microphone Such Installations Do Not Comply with ED–56A . . . . . C–4 C–2. . Model A55B Surface-Mount Mini–Condensor Microphone Module. . . . . . . . . Outline and Dimensions. A–32 A–24. . . Model FA2100 CVR Recording Specifications . . . . . . . . . . . . . Model S056 Surface-Mount Microphone Module . . . . . . . . . . . . . . . . . . . . . . . . . A–38 A–28. . . . . . . . Outline and Dimensions. Part Number 15977 (if functional testing of ULD is required). Model FA2100 CVR. Part Number 17TES0043 (includes PI Memory Card Module. Part Number 9300A860.Model FA2100 CVR 1. see paragraph 6. Part Number 165E1689-00. Part Number 17TES0051. 1. Refer to FA2100 GACVR Installation Manual (p/n: 165E1848–00) for the installation of the FA2100 General Aviation Cockpit Voice Recorders. the PI and a customer-fabricated cable to provide power to the FA2100 CVR’s main (rear) connector can be used. or CVR’s. or may be. Aviation Recorders. Part Number 165E1630–00 F Cockpit Voice Recorder System Test Panel. and PI Auxiliary Readout Cable. at the address shown in section 9. Part Number 17TES0052).0 INTRODUCTION 1. and to verify that the installed units are operating properly. PI Audio Readout Cable. Aviation Recorders.2 Equipment and Document Requirements The following equipment and documents are. Instead of the Test Panel. and Cable Assembly. Comments or recommendations about the installation. Part Number 024E1122–00 (for FA2100 CVR Readout. Note: Contact L-3 Communications.1 Purpose of Manual Installation & Operation Instruction Manual This Installation and Operation Instruction Manual applies to the following Model FA2100 CVR Cockpit Voice Recorders: 2100–1010–00 2100–1020–90 2100–1020–00 2100–1020–91 2100–1020–02 2100–1020–93 In this manual. to operate them.3. required for on-aircraft installation and check out of these FA2100 CVRs: F This Installation & Operation Instruction Manual.0). and check out of the FA2100 CVR should be sent to L-3 Communications. F Component Maintenance Manual. Rev. F Portable Interface Operator’s Manual. This manual also describes the features and functions of the FA2100 CVR System and associated accessories. Cockpit Voice Recorder. operation. Part Number 17TES0053. to verify this date sensitive information when using this manual to develop other documentation. F Portable Interface (PI). ATA 23–70–04. 01/03 165E1846–00 Page 1 . This manual contains date sensitive information necessary to install these CVRs in the aircraft. these recorders are referred to as FA2100 CVR. 07 Jan. F Ultrasonic Test Set (Underwater Locator Device (ULD) Tester). Product Support Department. The FA2100 CVR is connected to aircraft wiring via a 57-pin. Cockpit Voice Recorder (CVR). The FA2100 CVR consists of a chassis and front panel.) 2100–1010–00 ARINC 404A 1/2-ATR Short Case. The ULD meets or exceeds the requirements of FAA TSO–C121. 07 Jan. three Printed Wiring Assemblies (Aircraft Interface PWA.0 lbs. or to transfer data to a readout device. ARINC 757. the Control Unit. 120 Minutes. 2100–1020–00 ARINC 404A 1/2-ATR Short Case. also referred to as an underwater acoustic beacon. is mounted horizontally on the front of the CSMU and is also used as a the recorder’s carrying handle. 30 Minutes 10. 2100–1020–02 ARINC 404A 1/2-ATR Short Case. 165E1846–00 Page 2 Rev.0 lbs. FA2100 CVR Descriptions Part Number 1 Description Weight 1 (
0.4 System Overview Table 1 contains a summary description of the FA2100 CVRs covered in this manual. 2100–1020–93 ARINC 404A 1/2-ATR Short Case. Interconnection between the recorder and control unit or external preamplifier is accomplished using aircraft wiring. DPXB-style connector.1 Recorder Unit The FA2100 CVRs are housed in ARINC 404A. The ULD is equipped with a battery that has an expected life of six years. and Acquisition Processor PWA). The Ground Support Equipment (GSE) connector is located on the front of the FA2100 CVR. 1.4. 2100–1020–91 ARINC 404A 1/2-ATR Short Case.5 lbs. 10. Weight is with Underwater Locator Device installed. The chassis and Crash Survivable Memory Unit (CSMU) are painted international orange. and ARINC Characteristic 757. 1.3 Model FA2100 CVR System Description The FA2100 CVR Systems meet or exceed the requirements of Federal Aviation Administration (FAA) Technical Standard Order TSO–C123a. 120 Minutes 10. and the Crash Survivable Memory Unit (CSMU).. ARINC 757. European Organization for Civilian Aviation Equipment (EUROCAE) Minimum Operational Performance Specification (MOPS) ED–56A. 120 Minutes w/8–ohm output and no Bulk Erase (when used with 93A152-16 Control Unit). 120 Minutes w/INSITU Playback 10. ARINC 757. Military 10.0 lbs. 120 Minutes w/FSK 10. Cockpit Voice Recorder System. ARINC 757. Aeronautical Radio.Installation & Operation Instruction Manual 1. The FA2100 CVR System consists of the Recorder Unit. ARINC 757. an Area Microphone. This connector provides the interface from the recorder to GSE for checkout of the recorder. Cockpit Voice Recorder Systems. a Preamplifier Module for installations that do not require a Control Unit. 2100–1020–90 ARINC 404A 1/2-ATR Short Case. Two reflective stripes are located on the CSMU. The FA2100 CVRs may also be used to replace existing ARINC Characteristic 557 installations. Audio Compressor PWA.0 lbs. and a Mounting Tray.0 lbs. The CSMU contains the solid state flash memory used as the recording medium. ARINC 757. 01/03 . Inc. An Underwater Locator Device (ULD).0 lbs. 1/2-ATR short cases (refer to Figure 1). Table 1. The FA2100 FA2100 CVR can record Greenwich Mean Time (GMT) Time via the ARINC 429 GMT input and can record rotor speed data via the Rotor Speed input. Both configurations record a minimum of 30 minutes of high quality audio from the following four cockpit audio inputs: Channel 1: Channel 2: Channel 3: Channel 4: Cockpit Spare Audio Input (3rd Crew Member. Public Address System) Co-Pilot’s Audio. and Public Address or Third Crew Member audio inputs. At startup. and stores the data in a solid state memory. This fifth internal audio stream is a standard quality recording of the combination of the Pilot. The FA2100 CVR is available in two recording configurations: 30-minute. 07 Jan. the CVR Fault Line provides continuous status of FA2100 CVR operation. a standard quality recording of the Cockpit Area Microphone (CAM) audio input. It may be connected to an annunciator or to an aircraft central maintenance computer. Boom. and equalized as necessary. Model FA2100 CVR Cockpit Voice Recorder Refer to Figure 2 for this discussion. The resulting signals are converted to digital pulse code modulation (PCM) data. the FA2100 CVR initiates a Built-in-Test (BIT) and then continuously monitors itself for fault conditions. Rev. Mask. converts the audio to a digital format. Co-Pilot. for a minimum of 120 minutes. and 120-minute.Model FA2100 CVR Installation & Operation Instruction Manual HARDWARE AND SOFTWARE MODIFICATIONS CSMU ULD GSE CONNECTOR (BEHIND DUST COVER) Figure 1. Part Number 2100–1020–( ). Part Number 2100–1020–( ) also records a sixth audio stream. Boom. amplified. 01/03 165E1846–00 Page 3 . In ARINC 757 installations. and Hand-Held Microphone Input Pilot’s Audio.) The audio inputs are conditioned. (Table 2 illustrates the recording specifications for the cockpit audio input and combined channels. Mask and Hand-Held Microphone Input Cockpit Area Microphone (CAM) Input Part Number 2100–1020–( ) records a fifth internal audio stream for a minimum of 120 minutes. Part Number 2100–1010–( ). The FA2100 CVR is a Line Replaceable Unit (LRU) that simultaneously records four separate channels of cockpit audio. Installation & Operation Instruction Manual Model FA2100 CVR COCKPIT AREA MICROPHONE (CAM) 1 4 MONITOR AUDIO TO HEADSET JACK ERASE A ERASE C CONTROL UNIT AIRCRAFT WIRING INTERLOCKS (LANDING GEAR MUST BE DOWN AND BRAKE LOCKED TO ALLOW MEMORY TO BE ERASED) PUSH TO TEST GEAR AREA MICROPHONE BRAKE +18 VDC OPERATING POWER 2 RECORD ON +5 V FOR LIGHTED PANEL CHANNEL 4 2 CHANNEL 3 FA2100 CVR AUDIO OUT PILOT AUDIO 2 2 CHANNEL 2 +18 VDC CO-PILOT AUDIO 2 2 SPARE AUDIO (TO 3RD CREW MEMBER OR PA SYSTEM) TEST INDICATOR CHANNEL 1 AIRCRAFT INTERFACE PWA 2 GMT_IN_A (429) GMT_IN_B (429) 2 CVR FAULT TO AIRCRAFT FAULT MONITORING SYSTEM ROTOR_SPEED_IN_HI ROTOR_SPEED_IN_LO 28 VDC OR 115 VAC 400 Hz STOP RECORDING CHASSIS GROUND AUDIO COMPRESSOR PWA ACQUISITION PROCESSOR PWA GSE OUTPUT TO GROUND STATION TEST EQUIPMENT CSMU (Crash Survival Memory Unit) ASSEMBLY (CRASH PROTECTED SOLID STATE MEMORY) Figure 2. 07 Jan. Functional System Block Diagram Model FA2100 CVR Cockpit Voice Recorder 165E1846–00 Page 4 Rev. 01/03 . The S150 is designed to be used with the S055 remote microphone. The FA2100 CVR is compatible with installations using the Model A151B and A152B Control Units. and provide a means for activating the test function via a green push button and an indicator.2 Control Units and External Preamplifier The Control Unit or External Preamplifier is a required component of a CVR installation and functions as the FA2100 CVR cockpit user interface. TEST indicator lamp and a HEADSET jack. The Rev. Nominal input level is 1. because ARINC Characteristic 757 does not address microphone preamplifiers. and the Model S251/S261 Control Units are for use in FA2100 CVR ARINC–757 / ED–56A System installations. The Model S151 and Model S251 Control Units house the Microphone Preamplifier PWA. The Model S150/S160 Preamplifier is available for FA2100 CVR ED–56A System installations that do not require a Control Unit.3). Model FA2100 CVR Recording Specifications Cockpit Audio Inputs FA100CVR Part Number Channel 1 Channel 3 Channel 4 Combined Audio SQ CAM SQ Co-Pilot Audio Input for High Quality Recording Pilot Audio Input for High Quality Recording Cockpit Area Microphone (CAM) Input for High Quality Recording Summation of CH 1. Control Units contain a preamplifier printed wiring assembly (PWA) for interfacing the cockpit area microphone with the FA2100 CVR. 2. and have front panel TEST and Bulk ERASE switches.0 for additional information.Model FA2100 CVR Installation & Operation Instruction Manual Previously recorded information cannot be read from the Model FA2100 CVR while it is installed in the aircraft. Microphone Preamplifier PWA. Unit can record input audio levels from .) Table 2. such installations do not comply with ARINC Characteristic 757 or EUROCAE ED–56A.3).0 Vrms. & 3 Audio Inputs for Standard Quality Recording Cockpit Area Microphone (CAM) (CH 4) Input for Standard Quality Recording 2100–1010–( ) 30 minutes 30 minutes 30 minutes Not Available Not Available 2100–1020–( ) 30 minutes 30 minutes 30 minutes 120 minutes 120 minutes 3rd Crew Member/Spare Audio Input for High Quality Recording Note: Channel 2 Combined Channels 30 minutes All of the times in the above table are minimum recording times. The Model S152/S162 contains a built-in electret condenser-type microphone. 07 Jan. see paragraph 1. The Model S151/S161. The Model S161/S261 Controls Units are used with remote microphone modules with internal amplifiers for reducing RF interference (Model S056.4. TEST and Bulk ERASE switches. see paragraph 1.4. However. (Refer to paragraph 6. Bulk Erasure of the FA2100 CVR storage media is also accomplished by pressing the Control Unit’s red Bulk ERASE push button. Model S152/S162. These control units also have front panel TEST and Bulk ERASE switches. 1. All Control Units contain a headset jack for verifying system operation. TEST indicator lamp and a HEADSET jack. The S160 is used with the S056 remote microphone. however. the Model S150/S160 Preamplifier is not considered ARINC–757 compliant.0Vrms. The Model S151/S251 Control Units are used with an externally-mounted electret condenser-type microphone (Model S055.4. 01/03 165E1846–00 Page 5 .05Vrms – 3. 2. and TEST and Bulk ERASE switches. Both the A151B and A152B Control Units contain an analog TEST meter compatible with the FA2100 CVR. Control Units and External Preamplifiers For Model S151/S161.3 Remote Microphone Module The Model S055 and Model S056 Remote Microphone Modules are available to complete an ED–56A-compatible installation. Solder – Part Number 063–98–01897 3 Pin. and A152B Control Units.Installation & Operation Instruction Manual Model FA2100 CVR Model A151B houses the Microphone Preamplifier PWA. Solder – Part Number MS3111F–8–3P For Model S160 and A150 External Preamplifier 19 Pin.1 Mating Connector. and the TEST and Bulk ERASE switches. Microphone Preamplifier PWA. The Model S055 Microphone is required with the S151 and S251 Control Units and with the S150 Preamplifier Module. 1. Refer to Appendix B for RTCA/DO–160C environmental test conditions and description of environmental tests conducted. S152/S162. Vibration Mount. B. Solder – Part Number 9300–458 Crimp – Part Number 063–98–00577 For Model S251/S261 Control Unit Solder – Kit Part Number 147E1262–00 Crimp – Kit Part Number 147E1263–00 For Model S150 External Preamplifier 19 Pin. The Model S056 Microphone is required with the S161 and S261 Control Units and with the S160 Preamplifier Module. Contact Aviation Recorders Product Support for Full Sway Envelope and Outline and Dimension Drawings. 01/03 . The Model A152B contains a built-in condenser microphone. Refer to Appendix A for outline and dimensions illustrations and for a definition of the Model S055 and Model S056 Remote Microphone Module part numbers. This Control Unit is used with an externally-mounted condenser microphone (Model A55B).4. 07 Jan. Part Number 9300–343 CVR mount equipped with four vibration isolators. Refer to Figure 4 for outline and dimensions. Refer to Appendix B for RTCA/DO–160C environmental test conditions and description of environmental tests conducted.4. 165E1846–00 Page 6 Rev.4. A151B. Refer to Appendix A for Control Unit and External Preamplifier outline and dimension illustrations. Also refer to Appendix A for S055 and S056 microphone element specifications and response diagram. Solder – Part Number MS3111F–14–19P 3 Pin.4 CVR Mounting Racks A. 1. CVR Mount. Solder – Part Number 063–98–01898 1. Part Number 178E0919–00 CVR mount with no vibration isolators used to install the FA2100 CVR in the aircraft. Air Transport Equipment Cases and Racking ARINC Characteristic 757 Aeronautical Radio. such as in rotorcraft or test aircraft.. Aircraft wiring is soldered or crimped to the connector pins.0 EQUIPMENT LIMITATIONS/SPECIFICATIONS 2.1 Applicable Documents ARINC Characteristic 404A Aeronautical Radio. Cockpit Voice Recorder ARINC Report 604–1 Aeronautical Radio. Contact Aviation Recorders Product Support for Full Sway Envelope and Outline and Dimension Drawings. Environmental Conditions and Test Procedures for Airborne Equipment RTCA/DO–178B Radio Technical Commission for Aeronautics. Design Guidance for Design and Use of Built-In Test Equipment ARINC Report 624–1 Aeronautical Radio. Software Considerations in Airborne Systems and Equipment Certification TSO–C123a Federal Aviation Administration Technical Standard Order Cockpit Voice Recorder Systems Rev. Part Number 93–955 CVR mount for use in aircraft environments where excessive vibration may occur.Model FA2100 CVR C. 07 Jan. 01/03 165E1846–00 Page 7 . Inc. and mates with the connector on the FA2100 CVR’s rear panel. Colors RTCA/DO–160C Radio Technical Commission for Aeronautics. Installation & Operation Instruction Manual Heavy Duty Vibration Mount.5 Abbreviations and Acronyms For definition of abbreviations and acronyms used in this document.. D. 2. refer to Appendix D.. Design Guidance for Onboard Maintenance System EUROCAE MOPS ED–55 European Organization for Civil Aviation Equipment Minimum Performance Specification for Flight Data Recorder Systems EUROCAE MOPS ED–56A European Organization for Civil Aviation Equipment Minimum Performance Specification for Cockpit Voice Recorder System FED–STD–595 Federal Standard. Inc.. Inc. Solder – Part Number 9300–435 Crimp – Part Number 063–98–01474 1. Inc. Connector for CVR Mount Connector attaches to mount. Installation & Operation Instruction Manual 2. 1 Vrms nominal. to Control Unit Recording Time: PN 2100–1010–( ) = 30 minutes minimum PN 2100–1020–( ) = 120 minutes minimum Input Signal Format: ARINC 757 Audio Input Impedance: > 5000 ohms each channel Audio Inputs: 3 crew microphones (150 – 3500 Hz bandwidth) 1 cockpit area microphone (150 – 6000 Hz bandwidth) Audio Input Level: 50 mVrms to 3 Vrms.5 watts maximum when powered by 28 Volts DC 12 watts maximum when powered by 115 Volts AC @ 400 Hz Power Factor: 0. 07 Jan.2 Model FA2100 CVR Physical Characteristics The Model FA2100 CVRs fit within the envelope of an ARINC 404A 1/2-ATR short case. 2.3 Electrical Characteristics Power Requirements: 115 Volts AC @ 400 Hz.0  0. 01/03 .98 inches nominal 12.6 inches nominal (behind front panel) 13.) Following are the physical characteristics of the Model FA2100 CVRs: Size: Height: Width: Depth: 5.5 pounds Markings: International Orange (FED–STD–595 Color No. 165E1846–00 Page 8 Rev. or 28 Volts DC Power Level: 10. (Refer to for Figure 3 outline and dimension illustration. 12197). Reflective Striping on Crash Survivable Memory Unit.5 inches nominal Chassis: 4.88 inches nominal Front Panel: 4.65 Output Power: +18 Vdc. Part Number 063E1072–00 (Cannon Part Number DPXB–36571–59) Main (Rear) Mating Connectors: Crimp: Part Number 063–98–01474 (Cannon Part Number DPXBMA–57–33S–0001) Solder: Part Number 9300–435 (Cannon Part Number DPXB–57–33S–0001) Ground Support Equipment Connector: 1 Part Number 063–98–01962 (AMP Part Number 748481–6) Weight is with Underwater Locator Device installed. English Markings on One Side of Chassis and French Markings on Other Side of Chassis Main (Rear) Connector: 57-Pin Connector Compatible with ARINC 757.1 inches nominal (including hold-down hooks) Weight1: 10. 25 mA short-circuit protected. Model FA2100 CVR Installation & Operation Instruction Manual Audio Quality: Meets ED–56A Chapter 3 specifications. > 20 dB (10 % distortion) otherwise Greenwich Mean Time Input Data: ARINC 429 Format Rotor Speed Input Signal: 2 Vrms to 122 Vrms from 7 to 6000 Hz per ARINC 757 Discrete Inputs: Bulk Erase – 2 discrete inputs Erase A Erase C Push-to-Test – 1 discrete Record On – 2 discrete inputs Stop Recording – 1 discrete Digital Outputs: CVR Fault – 1 discrete Rev. 07 Jan. Signal-to-noise plus distortion ratio (SINAD) of the signal when reproduced > 24 dB (6 % distortion) for the most recent 30 minutes of recording. 01/03 165E1846–00 Page 9 . 4. 12197 PER FED-STD-595. OVERALL EQUIPMENT SIZE AND MOUNTING SCHEME COMPLY WITH ARINC 404 AND 404A.1 3. NAMEPLATE IN VIEW A-A HAS LIGHT GRAY BACKGROUND WITH BLACK MARKING.2 MAX 12. 07 Jan. 2100-1010-00 H 2100-1020-00 G Figure 3. (Sheet 1 of 2) Outline and Dimensions FA2100 CVR Cockpit Voice Recorder.0 ± . 01/03 .5 FARSIDE LABEL READS: ENREGISTRUER DE VOL NE PAS OUVRIR . SEE CHART FOR FINAL PART NO. 5.5 A 5.5 LBS TOLERANCE. REAR PANEL CONTAINS HOLES TO MATE WITH GUIDE PINS IN ARINC 404 MOUNTING TRAYS.5 MAX NOTES: 1.5 A ± C . ELECTRICAL INTERFACE CONNECTIONS PER APPLICABLE ARINC CHARACTERISTIC. INPUT POWER. RECORDER COLOR IS INTERNATIONAL ORANGE NO. FRONT AND SIDE LABELS ARE REFLECTIVE WHITE BACKGROUND WITH BLACK LETTERING.44 ± . 2. 3. POWERS ARE MAXIMUMS AND WEIGHTS ARE NOMINAL WITH ± .5 B 7. PN 2100–1010–( ) & PN 2100–1020–( ) 165E1846–00 Page 10 Rev.4 ± .Installation & Operation Instruction Manual Model FA2100 CVR ESD LABEL C COCKPIT VOICE RECORDER MODEL FA2100 B 2. AND WEIGHT.60 ± .04 . 5 ± .2 GROUND SUPPORT EQUIPMENT CONNECTOR 063-98-01962 (AMP 748481-6) 4.98 C .04 UNDERWATER LOCATING DEVICE REPLACEMENT DATE 5.04 C 2100-1010-00 H 2100-1020-00 G Figure 3.88 CRASH SURVIVABLE MEMORY UNIT B View ± . PN 2100–1010–( ) & PN 2100–1020–( ) Rev.995 ± . (Sheet 2 of 2) Outline & Dimensions FA2100 CVR Cockpit Voice Recorder. 07 Jan.50 REFERENCE ONLY POLARIZING KEYS SHADING DENOTES SOLID KEY AREA COCKPIT VOICE RECORDER MODEL FA2100 4 . 01/03 165E1846–00 Page 11 .01 B A View A J1 CONNECTOR PART NUMBERS: PN 063-E1072-00 (CANNON DPBX-36571-59) MATING CONNECTORS: (CRIMP) PN 063-98-01474 (CANNON DPXBMA-57-33S-0001) (SOLDER) PN 9300-435 (CANNON DPXB-57-33S-0001) 4.Model FA2100 CVR Installation & Operation Instruction Manual 2.44 ± .12 ± View 4. 07 Jan.06 4. CVR Mount. Outline and Dimensions.00 MAX (CG) .182 $ . PN 16165 (ESNA PN 68–1660–40) OR EQUIV. 3.02 $ . 905–E0919–18H Figure 4. AND WEIGHT-REDUCING HOLES) MAY VARY PICTORIALLY FROM THIS DRAWING. TO ATTACH MOUNT TO AIRCRAFT: 4 EACH #8 100 T HEAD SCREWS MS24693–( ) OR EQUIV (LENGTH AS REQD). Part Number 178E0919–00 165E1846–00 Page 12 Rev. FLANGES. WEIGHT 1.00 MAX .38 MAX OUTSIDE 4X 0.3 LBS.062 $ .500 $.010 100° CSK 4. CONNECTOR MOUNTING HOLE IS DESIGNED FOR: (CRIMP) PN 063–98–01474 (CANNON DPXBMA–57–33S–0001) (SOLDER) PN 9300–435 (CANNON DPXB–57–33S–0001) 4. HARD.50 3. SUGGESTED MOUNTING HARDWARE: TO ATTACH CONNECTOR TO MOUNT: 8 EACH 4–40 X 7/16 PAN HEAD SCREWS PN 229–02–00076 (MS51957–16) OR EQUIV. 01/03 . AND 4–40 SELF-LOCKING NUTS.50 (CG) CL COMPANY LOGO 5. AND SELF-LOCKING NUTS MS21044–C08 OR EQUIV.12 5. MAX. TABS. 2.80 MAX 16.005 CLEARANCE HOLES FOR #8 SCREWS 9. CVR PN: 178–E0919–00 REV [X] SN: XXXXX DATE: MM/YY 5.50 1.41 MAX 3.02 INSIDE 2.75 $ .38 9.Installation & Operation Instruction Manual Model FA2100 CVR NAMEPLATE INFO: NAME: MOUNT. UNDIMENSIONED FEATURES (SUCH AS SIDE RAILS.005 SUGGESTED MOUNTING HOLE PATTERN NOTES: 1.60 $ . Refer to the following statement which was extracted from FAA TSO–C123a: The conditions and tests required for TSO approval of this article are minimum performance standards. 07 Jan.1457. Preflight. 60 minutes @ 1100_C and 10 hours @ 260_C Impact: ED–56A – 3400 g’s. If Rev./10 feet/!@4” probe Static Crush: ED–55/ED–56A – 5.) Proposed installations should be coordinated with the local jurisdiction of the FAA or other certifying authority before beginning recorder installation. 135.000 lbs. and Flight tests specified for evaluation in this Installation Manual. (e). Control Unit. and (f). feet/hour.4 Installation & Operation Instruction Manual Environmental Characteristics Refer to the FA2100 CVR Environmental Qualification Forms (EQFs) in Appendix B for environmental characteristics. and 121 (Air Carrier). The circuitry required for Bulk ERASE includes the installation of interlock devices on board the aircraft.1457 appropriate to the category of operation under FAR Parts 91. therefore. 25.1457 (b). (Refer to paragraph 3. It is the responsibility of those desiring to install this article either on or within a specific type or class of aircraft to determine that the aircraft installation conditions are within the TSO standards.1457. and Remote Microphone Module is per ARINC Characteristic 757 dated December 29.1457. it is an installation option. and 29. 27. 3.5 Crash.Model FA2100 CVR 2. half-sine shock wave 3. The article may be installed only if further evaluation by the applicant documents an acceptable installation and is approved by the Administrator.2 General Information Installation of the Recorder. Advisory Circular 25. Fire Protection: TSO–C123a/ED–56A – 50. The Federal Aviation Administration has issued several Advisory Circulars which may be referred to in the approval processes. Acceptance of the installation and use of the FA2100 CVR and its associated components must be sought from the cognizant Federal Aviation Administration (FAA) office or other certifying authority. 2.3.0 INSTALLATION PROCEDURES AND LIMITATIONS 3. 1993. 01/03 165E1846–00 Page 13 . 6 ms.1 Installation Precautions Approval of the Model FA2100 CVR installation is not authorized by this Installation and Operating Instruction Manual.1457–1a specifically addresses one acceptable means of compliance with Federal Aviation Regulation (FAR) 25.000 BTU/sq. The Bulk ERASE connection is not mandated by the FAA.and Fire-Survival Characteristics Penetration: ED–55/ED–56A – 500 lbs. Installations must conform to the Operating Rules in FAR23. Approvals may be accomplished on a Field Approval basis if the installation is determined to meet the criteria of the appropriate Post-Installation. pin 55 (ERASE A) of the FA2100 CVR must be grounded to pin 17. 3. ground and flight tests must be conducted to verify that the Audio System Interface is satisfactory and that “normal” conversation can be discerned from the Cockpit Area Microphone and the individual Pilot. Any deviations to the installation instructions contained in this Installation Manual must be brought to the inspector’s attention and be so identified on the Form 337. The Form 337 must also include a statement that a complete Audio System Interface Test (reference paragraph 5. Co-Pilot. The applicant must submit an FAA Form 337. Aviation Recorders can reproduce the CVR memory contents onto cassettes for channel separation and evaluation. and equipped to accomplish the installation and approve the aircraft for return-to-service. The applicant should submit all appropriate data and drawings to the inspector before the installation of the Cockpit Voice Recorder. appropriate weight and balance data.0. If you prefer to make your own reproduction.4. 165E1846–00 Page 14 Rev. Contact the Product Support Department to coordinate this process. The applicant must indicate that the Cockpit Area Microphone is installed in the recommended locations identified in FAA Advisory Circular 25. 07 Jan. 3.1457–1A and in accordance with the instructions contained in this Installation Manual.3 Installation Acceptance by Field Approval Method An applicant for Field Approval of a CVR installation must be properly certified and appropriately rated. The CVR System must be verified to be free of any objectionable audio interference and other unwanted noise.4.4 Recorder Location The Model FA2100 CVR should be installed in the aircraft fuselage location provided for this purpose by the airframe manufacturer. and identification of all CVR system components used in the installation should be made available to the Inspector conducting the Field Approval. 3.2) was performed as required. refer to section 6. Finally. such as structural data showing the method of attachment of the CVR components to the airframe. as far aft as practicable.5 Mounting The Model FA2100 CVR is certified and approved for installation in aircraft environments within the limits of RTCA/DO–160C Curve C.Installation & Operation Instruction Manual Model FA2100 CVR the Bulk ERASE feature is installed. Pin 57 remains open. describing the work performed to the airframe to accomplish the installation of the CVR System. at least one interlock is required to prevent accidental erasure of the FA2100 CVR. Installation accessories (CVR Mount and Mount Connectors) are described in paragraph 1. and appropriate Third Crew Member or Public Address stations. The CVR should be installed in accordance with the instructions and limitations contained in this Installation Manual. The recommended orientation is mounted in an upright position (vertical as viewed from the front). Installation drawings and other information. 01/03 . The CVR Installation Manual containing Operating Instructions and System Description must be made available to the inspector for review and evaluation of the CVR System. If the BULK ERASE feature is not desired. Any discrepancies identified during the ground and flight tests must be brought to the inspector’s attention and corrected before the aircraft can be returned to service. qualified. wiring diagrams. If required. or 28 Vdc. This connector mates with the connector on the aircraft wiring harness. independent of mode selection on the audio control panel. The range of acceptable audio input levels for the Model FA2100 CVR is from 50 mVrms to 3 Vrms. In some cases. The Model FA2100 CVR provides for four audio inputs which are connected as follows: Channel 1: Channel 2: Channel 3: Channel 4: Cockpit Spare Audio Input (3rd Crew Member. The Installer is responsible for determining the means of interfacing to comply with the regulations. Refer to Appendix A for appropriate Interwiring Diagram. Rev. transmissions from ATC may not be recorded.Model FA2100 CVR Installation & Operation Instruction Manual On aircraft with an existing CVR Vibration Mount such as Part Number 9300-343 or equivalent.8 Audio System Interface The FA2100 CVR is used in an ARINC 757 configuration. or with an existing Heavy Duty CVR Vibration Mount such as Part Number 93–955 or equivalent. Cannon Part Number DPXB–36571–59). Nominal audio level input is 1 Vrms.6 Power Requirements Unless impractical. and Sidetone audio. and others. Connections to the FA2100 CVR J1 connector depend on the installation configuration. the FA2100 CVR should be powered from a bus other than the bus used to provide power to the Flight Data Recorder. Summing amplifiers can be obtained from Avtec. 3. Old Systems: Rework the audio control panel or system to provide a CVR output or install an external summing amplifier. Mask and Hand-Held Microphone Input Cockpit Area Microphone (CAM) Input Older aircraft audio systems may require rework to ensure recording of ATC (Air Traffic Control). Mask Microphone. The FA2100 CVRs draw a maximum of 12 watts ac or 10. 3. Mask. Racal. New Systems: Some later-generation audio control panels have a CVR signal output already provided. Baker Electronics. 07 Jan.5 watts dc. therefore. Each bus will need to meet the supply reliability requirements appropriate for the recorders being powered. Public Address System) Co-Pilot’s Audio. The electrical connector is a 57-pin DPXB connector that is compatible with ARINC 757 (Part Number is 063E1072–00. Boom.7 Wiring Connections The typical electrical interconnect wiring between the recorder and the aircraft is specified in ARINC Characteristic 757. Boom. it is not necessary to retrofit this mounting tray with a hard-mounted tray. A summing amplifier may be required to provide recording of the boom microphone. 01/03 165E1846–00 Page 15 . 3. The FA2100 CVR operates with input voltages of either 115 Vac at 400 Hz. Refer to Figure 4 for CVR Mount outline and dimension illustration. and Hand-Held Microphone Input Pilot’s Audio. No changes to the CVR are required. Intercom. with interface to the aircraft provided through a 57-pin DPXB rear panel connector. Such conditions must be remedied to assure continuous reception of audio from the communications radios. selection of the loudspeaker function disables side tone output. (2). or 28 Vdc.9 Microphone Installation Criteria The most desirable location for the Cockpit Area Microphone is forward of a vertical plane oriented laterally through the pilot’s and co-pilot’s normal head position.10 Cessation of Recording Federal Air Regulations 23.1457 (d).1457 (d). 27. and 29.” The Installer must demonstrate this function. (2). within 10 minutes after crash impact. (2). (2) state that “There [must be] an automatic means to simultaneously stop the recorder and prevent each erasure feature from functioning. Ensure that the microphone is mounted such that the exposed portion of the microphone element is unobstructed. 07 Jan. The Cockpit Area Microphone must face the crew members.1457 (d). 3. Recommended Cockpit Area Microphone Mounting Location 3. Since the FA2100 CVR System can be powered by either 115 Vac at 400 Hz.1457 (d).Installation & Operation Instruction Manual Model FA2100 CVR Future Systems: Audio control panels and systems designed to meet or exceed the characteristics of Radio Technical Commission for Aeronautics RTCA/DO–170 for “hot” boom microphone capability may be determined to be acceptable. the following methods are acceptable to ensure automatic cessation of recording: 165E1846–00 Page 16 Rev. 01/03 . 25. Refer to Figure 5 for an illustration of the preferred placement for the Cockpit Area Microphone. 3 1 2 2 3 RECOMMENDED MICROPHONE LOCATIONS ARE NUMBERED IN ORDER OF PREFERENCE Figure 5. Note that you can hear what you say without any delay or significant distortion. Impact Switch: An impact switch interrupts FA2100 CVR power upon exposure to a predetermined level of g-force. Apply power to the system and activate the FA2100 CVR’s self-test. recording of data will cease. Such switches have limitations. 2. 01/03 Previously recorded information cannot be played back from the FA2100 CVR while it is installed in the aircraft. 4. NOTE: Rev. verify that all connections are secure and that a continuity or other interconnect assurance test has been conducted. no other external circuitry is necessary. B. Speak in a normal voice 6-inches away from the Control Unit microphone while listening in the headset. 5. descriptions of the menu functions.Model FA2100 CVR Installation & Operation Instruction Manual A. press and hold the green TEST button for a minimum of five seconds. ARINC 757 Shutdown Signal: The FA2100 CVR continuously monitors the ARINC 757 shutdown signal that can be supplied to the recorder via pin 10 of the rear panel connector. The recording will resume if the shutdown signal goes inactive or upon activation of the “Push-toTest” function. the meter needle rises and comes to rest in the ‘GO’ (green) section of the meter scale when the FA2100 CVR has passed the test. a ground would be applied to pin 10. To activate self-test. It is assumed that the engine(s) will stop upon crash impact. 3. refer to the Portable Interface Operator’s Manual (Part Number 165E1630–00). If the aircraft can no longer sustain flight under its own power. or Model S251/S261 Control Unit. Part Number 17TES0043. (not derived from an AC Inverter). The PI receives power from the FA2100 CVR. For installations containing a Model S151/S161. Before applying power to the FA2100 CVR System and associated components. The Portable Interface (PI). This test ensures that the microphone is operating. 400 Hz Source: If power input is derived directly from an engine-driven 115 Vac. This item is not available through Aviation Recorders. If the recording is resumed due to execution of the “Push-to-Test.0 POST-INSTALLATION CHECKOUT The following tests and results must be documented in the CVR Installation Checklist and submitted with the data package for field approval consideration: 1. Model S152/S162. Refer to section 3.) C.) For installations containing a Model A151B or Model A152B Control Unit. For a description of the PI. (The TEST lamp stays on as long as the TEST button is pressed. 400-Hz source. and PI operation.11 of ARINC 757 for further information. 07 Jan.” the recording will again cease within 10 minutes if the shutdown signal is still active. (The meter stays in the ‘GO’ section of the meter scale as long as the TEST button is pressed. (Refer to Appendix C for manufacturer’s specifications for available models. Engine-driven 115 Vac. If this signal remains “active” for approximately 10 consecutive minutes. the cockpit-mounted TEST lamp illuminates when the FA2100 CVR has passed the test. can be used to individually monitor the four audio channels as they are being recorded by the FA2100 CVR. but are effective in high g-force accidents.) 4. 165E1846–00 Page 17 . The PI is connected to the FA2100 CVR via a 10-foot cable that is plugged into the FA2100 CVR’s front panel GSE connector (refer to Figure 6). and Hand-Held Microphone Input Pilot’s Audio. c.Installation & Operation Instruction Manual Model FA2100 CVR Using the following procedure. Mask. GMT can also be supplied as FSK audio mixed with channel 1 or 3 with the 2100–1020–02 recorder. confirm proper operation by using the real time GMT display function of the PI.) 165E1846–00 Page 18 Rev. the meter is used as a ‘GO-NO-GO’ indicating device. GMT is supplied to the recorder as a low speed ARINC 429 input using Label 125 or Label 150. Monitor the audio with the PI’s internal speaker or with a 600-ohm headset connected to the PI’s phone jack (an 8–ohm headset must be used for the 2100–1020–93 configuration). d. the panel-mounted TEST lamp illuminates when the FA2100 CVR has passed the testing. This is found under the Special Functions menu. regardless of Audio Control Panel mode or audio (communications radio) selection: Channel 1: Channel 2: Channel 3: Channel 4: Cockpit Spare Audio Input (3rd Crew Member. 01/03 . Press and hold the Cockpit Control Unit’s TEST push button for a minimum of five seconds. Mask and Hand-Held Microphone Input Cockpit Area Microphone (CAM) Input a. Repeat this process for CH 2. Using the PI’s SELECT button. Connect the PI to the FA2100 CVR’s GSE connector as shown in Figure 6. This can only be done with the PI in the Playback Mode. and HQ CAM CH 4. Therefore. Boom. verify that the four following channnels inputs are recording correctly.1 Preflight Functional Check The Preflight Functional Check assures the operator of FA2100 CVR System integrity. While someone is speaking into the Channel 1 source. Tone duration is approximately 4 seconds. The Bulk Erase function can occur only when the aircraft is resting on its landing gear. The meter needle rises to and remains within.) For installations containing Model A151B or Model A152B Control Units. the ‘GO’ (green) section of the meter scale when the FA2100 CVR has passed the testing. Boom. Public Address System) Co-Pilot’s Audio. 5. b. or Model S251/S261 Control Units. (The meter needle stays in the ‘GO’ section of the meter scale as long as the TEST button is pressed. NOTE: 6. verify that the audio is clear and distortion-free. For installations containing Model S151/S161. (The TEST lamp stays on as long as the TEST button is pressed. activate the Monitor Menu and turn HQ VOICE CH 1 ON. The PI does not display ARINC 429 GMT or rotor speed in the Monitor Mode. If the GMT input has been connected to the recorder. CH 3. After pressing and holding the Control Unit’s bulk ERASE push button for a minimum of 2 seconds. it must be performed before every flight or whenever maintenance has been performed on the aircraft which may have affected the performance of the FA2100 CVR System. 07 Jan. release it and verify Bulk Erase function by listening for a 400-Hz tone at the HEADSET jack. Model S152/S162.0 OPERATIONAL TESTS 5. 2. 01/03 165E1846–00 Page 19 . 3. 2 ROTOR PI AUDIO READOUT CABLE 17TES0051 1.Model FA2100 CVR Installation & Operation Instruction Manual PORTABLE INTERFACE (PI) 17TES0043 GMT FA2100CVR PI AUX READOUT CABLE 17TES0052 1. FSK output for recorded GMT and/or Rotor Speed audio signal. 3 CH 1 HQ SQ 2 3 4 COMB CAM TO RECORDER GSE CONNECTOR DATA FROM RECORDER NOTES: 1. Depending on type of recorder used. reel-to-reel tape. Analog outputs for recorded voice data. Male phono (RCA) plugs for connection to standard cassette. 07 Jan. or digital audio tape recorder to produce high fidelity copy of FA2100CVR’s recorded data for later playback. or all of the individual channels can be copied simultaneously. On-Aircraft Setup for Checking Out FA2100 CVRs using a Portable Interface Rev. Figure 6. the FA2100CVR’s recorded data can be copied one channel at a time. descriptions of the menu functions. connected to an AC or DC source as appropriate. refer to section 8. Boom. conduct the following audio system check: NOTE: For a description of the PI. and PI operation.0. and connected to a Portable Interface (PI). (2) Using the PI’s SELECT button. verify that the audio is clear and distortion-free. Boom. and HQ CAM CH 4. 07 Jan. This can only be done with the PI in the Playback Mode. specified maintenance period.0 FA2100 CVR READOUT Previously recorded information cannot be read (played back) from the Model FA2100 CVR while it is installed in the aircraft. Flight Checkout Procedure For flight checkout procedure.Installation & Operation Instruction Manual 5. regardless of Audio Control Panel mode or audio (communications radio) selection: Channel 1: Channel 2: Channel 3: Channel 4: (1) Connect the PI to the FA2100 CVR’s GSE connector as shown in Figure 6. Part Number 165E1630–00. The following items are needed for FA2100 CVR readout: PI. activate the Monitor Menu and turn HQ VOICE CH 1 ON. To accomplish this test. Public Address System) Co-Pilot’s Audio. during each annual inspection. Mask. Mask and Hand-Held Microphone Input Cockpit Area Microphone (CAM) Input The PI does not display ARINC 429 GMT or rotor speed in the Monitor Mode. Part Number 17TES0043. refer to the Portable Interface Operator’s Manual (Part Number 165E1630–00). Cockpit Voice Recorder System Test Panel. and Hand-Held Microphone Input Pilot’s Audio. an entry shall be made in the aircraft or rotorcraft maintenance records.2 Model FA2100 CVR Complete Audio System Check A complete Audio System Test must be completed under the following three conditions. NOTE: Previously recorded information cannot be played back from the FA2100 CVR while it is installed in the aircraft. and is a security feature to protect the privacy rights of pilots and other crew members. and whenever unscheduled maintenance is performed which may affect the performance of the Cockpit Voice Recorder System. This requirement is noted in ARINC Characteristic 757 and EUROCAE ED–56A. to play back previously recorded data. CH 3. Using the PI. Cockpit Area Microphone. Using the following procedure. (3) Repeat this process for CH 2. Monitor the audio with the PI’s internal speaker or with a 600-ohm headset connected to the PI’s phone jack (an 8–ohm headset must be used for the 2100–1020–93 configuration).3 Cockpit Spare Audio Input (3rd Crew Member. Upon satisfactory completion of this test. Part Number 17TES0043. Portable Interface Operator’s Manual. 6. 01/03 . and Third Crew Member or Public Address System inputs must be individually checked for their operational integrity with the FA2100 CVR. verify that the four following channnels inputs are recording correctly. The FA2100 CVR must be removed from the aircraft. While someone is speaking into the Channel 1 source. Part Number 17TES0043. the Pilot’s. NOTE: 5. Co-Pilot’s. 165E1846–00 Page 20 Rev. 0 FLIGHT CHECKOUT PROCEDURE Execution of a flight test may be required to approve/certify the FA2100 CVR installation. the recorder is ready for operation. Part Number 165E1630–00. depending on recorder version. Each crew member shall identify himself by name. Pre. Model FA2100 CVR. Check and identify. Close FA2100 CVR circuit breaker about three minutes before engine start. 7.1 Operational Notes Depending on its part number. Rev. the FA2100 CVR will preserve 30. identify any significant events or warnings. and time. e.or 120-minutes of recording time. The FA2100 CVR circuit breaker may be pulled and reset as required to preserve the test recording on longer flights. 01/03 Open FA2100 CVR circuit breaker. Also. c.2 Flight Checkout 1. clear enunciation in a natural voice is essential. Perform the pilot’s “PRE-FLIGHT FUNCTIONAL CHECK” contained in this manual. 07 Jan. The Portable Interface Operator’s Manual. Cable Assembly. b. 8. and Component Maintenance Manual. date.Model FA2100 CVR Installation & Operation Instruction Manual Part Number 9300A860. The Test Director shall announce airplane status and identify any warning sounds. 8. record a short excerpt of the pre-start checklist called out by the crew. Record the normal cockpit conversations for one minute after one engine has started. f. Cockpit Voice Recorder. A test program not exceeding 30. Part Number 024E1122–00. should be planned prior to the test flight.and Post-Engine Start a. Check and identify the fire warning bell. The Test Director shall announce time and condition into the area microphone at the start of each condition. A predetermined list of words and phrases used during normal pre-flight and in-flight operations should be prepared for use by the cockpit crew. and encourage conversation between crew members. contains the procedures for using the PI to play back previously recorded FA2100 CVR data. to obtain a satisfactory recording on the area microphone channel. Instead of the 9300A860 Test Panel.0 of this document. the airplane identification. The recorder will operate automatically until power is removed. the PI and a customer-fabricated cable to provide appropriate power to the FA2100 CVR’s main (rear) connector can be used to play back previously recorded data. 165E1846–00 Page 21 . d. 8. by speaking into the area microphone and listening for playback at the headset jack.or 120-minutes of recorded information. ATA 23–70–04. It is important for participants to bear in mind that.0 OPERATING INSTRUCTIONS The Model FA2100 CVR has no controls or switches and its operation is completely automatic upon power-up. When the recorder is installed and wired in accordance with section 3. Using the flight interphone facilities. such as on a cassette. The Test Director shall identify the event. Touchdown. Vmo or Mmo a. 07 Jan. Open FA2100 CVR circuit breaker. 3. and Climb a. (including the marker beacon signal) should be recorded for post-flight playback. b.Installation & Operation Instruction Manual Model FA2100 CVR 2. Climb to 25. d.” Repeat this test for the headset microphone and the hand-held microphone. Taxi. accelerate until Mmo or Vmo clacker sounds and identify. each crew member shall identify himself and note that he is listening on his headset at a comfortable listening level. During this time. Verify by monitoring at FA2100 CVR output jack. and Rollout a. 165E1846–00 Page 22 Rev. 01/03 . Conduct emergency descent to 12. Before releasing the brake. Close FA2100 CVR circuit breaker. 5. Select an ADF or VOR signal and identify these signals when they are being produced by the cockpit speakers at proper listening level. Disconnect auto-pilot and verify aural disconnect sound. Hold this speed and have crew member identify flight status via the area microphone.000 feet. Cruise. Record flight data onto a format usable by the examiner/inspector. At an appropriate altitude. The pilot will identify himself and warning device sounding. Close FA2100 CVR circuit breaker. Select cruise altitude. Any audio signals identifying navigation and approach aids which are audible to in-flight crew headsets. Takeoff. c. Each crew member will don his oxygen mask and will say “This is the pilot/co-pilot speaking through his oxygen mask microphone. to acquire a reasonable amount of recorded speed. g. apply takeoff engine power and actuate the stick shaker with the test switch. c. Reduce thrust until stall warning horn sounds. Make a flight crew member announcement on the aircraft public address system advising cabin emergency descent. d. Record normal crew conversations during takeoff. the co-pilot will give altitude and airspeed or mach number every 1. b. Press ERASE button. b. The pilot will identify himself and warning device sounding. Close FA2100 CVR circuit breaker. When airborne. reduce speed approximately 5 knots so that clacker stops. Descent. demonstrating that FA2100 CVR will not erase in flight.000 feet. c. Reduce thrust until landing gear warning horn sounds.000 feet. identify Bulk Erase Test. e. The pilot will acknowledge and read-back the values given by the co-pilot. Post-Flight Remove FA2100 CVR from aircraft and play stored data back via the Portable Interface (PI). Open FA2100 CVR circuit breaker. f. Open FA2100 CVR circuit breaker. 4. readout. The ULD is mounted horizontally on the front of the CSMU for easy removal and for easy viewing of the battery expiration date. Aviation Recorders’ Authorized Repair Facilities have factory trained technicians who provide repair. or visit our web site at www. Mail Stop 20 9. installation instructions.1 Recorder Installation & Operation Instruction Manual The Model FA2100 CVR does not require scheduled maintenance or calibration. 9.2). and recertification. Upon expiration of expected battery life.com for this and much more information. 9. Readout Service is performed by the Repair Station. Items needing repair should be shipped to the following address: L-3 Communications Aviation Recorders 6000 East Fruitville Road Sarasota.Model FA2100 CVR 9.0 MAINTENANCE AND CALIBRATION 9.O. 07 Jan. Contact the Product Support Department for names and locations. The ULD requires functional testing and cleaning every 24 months. 01/03 165E1846–00 Page 23 . 9. (Refer to Appendix C for information about the ULD Tester. Box 3041 Sarasota. and loaner/rental services. Also. except for periodic inspection/servicing of the Underwater Locator Device (see paragraph 9. Florida 34230–3041 Attention: Product Support.5 Loaner/Rental Program Aviation Recorders’ Authorized Repair Facilities are capable of providing loaner/rental FA2100 CVRs. the Aviation Recorders’ Product Support Group maintains a limited supply of FA2100 CVRs available for rental.) The ULD is equipped with a battery that has an expected life of six years.L-3ar.3 Product Support Mailing/Contact Information: L–3 Communications Aviation Recorders P.4 Telephone: Telefax: SITA: Web Site: (941) 371–0811 (941) 377–5591 SRQLFCR www. Florida 34232 Attention: Repair Station Questions concerning FA2100 CVR repair may be answered by calling the Aviation Recorders’ Repair Station at (941) 377–5517 or (941) 377–5579.2 Underwater Locator Device The Model FA2100 CVR is equipped with an Underwater Locator Device (ULD) that is approved to FAA TSO–C121.com Authorized Repair Facilities Aviation Recorders performs repair and readout services for the Model FA2100 CVR System. or by calling the Product Support Department at (941) 371–0811. contact ULD manufacturer for replacement batteries.L-3AR. Rev. Installation & Operation Instruction Manual Model FA2100 CVR THIS PAGE IS INTENTIONALLY LEFT BLANK 165E1846–00 Page 24 Rev. 07 Jan. 01/03 Model FA2100 CVR Installation & Operation Instruction Manual APPENDIX A OUTLINE & DIMENSIONS MICROPHONES, CONTROL UNITS, & EXTERNAL PREAMPLIFIERS Rev. 07 Jan. 01/03 165E1846–00 Page A–1 Installation & Operation Instruction Manual Model FA2100 CVR THIS PAGE IS INTENTIONALLY LEFT BLANK 165E1846–00 Page A–2 Rev. 07 Jan. 01/03 Part Number Definition. Model S151/S161.25 Panel Thickness . S056 Microphone Installation & Operation Instruction Manual Panel Thickness . and Model S251/S261 Control Units Rev.125 Model FA2100 CVR S151–0020–00 S151–0030–00 S151–0040–00 S151–0050–00 S151–0060–00 S152–0020–00 S152–0030–00 S152–0030–01 * S152–0040–00 S161–0020–00 S161–0020–10 S161–0030–00 S161–0040–00 S161–0050–00 S161–0060–00 S162–0020–00 S162–0030–00 S162–0040–00 S251–1120–00 S251–1130–00 S251–1170–00 S261–1120–00 S261–1130–00 * Note: -01 version is used with 8ĆOhm.25 COLOR Reqs.125 Panel Height 2. 07 Jan. S055 Microphone Reqs.Attenuated Output Filtered Connector Non–Filtered Connector D– type Connector Circular Connector Gray Black Brown (Boeing) Brown (ATR) Blue (DO328) Gray (BD100) Illuminated Non–Illuminated Panel Height 1. 0. 01/03 165E1846–00 Page A–3 .21 inch Headphone Jack (J2) Figure A–1. Model S152/S162. 56 . DIMENSIONS ARE IN INCHES 905–E1019–18K Figure A–2.000 –.000 5.1 LBS. Florida MODIFICATIONS 1 4 7 10 13 2D BAR CODE 2 5 8 11 14 3 6 9 12 15 TSO–C123a ED–56A SWITCH GREEN LAMP SWITCH COCKPIT VOICE RECORDER 2.50 . Outline and Dimensions. 2.375
.11 1.05 .Installation & Operation Instruction Manual Model FA2100 CVR 5. 07 Jan.12 2.002 HEADSET ERASE . Model S151 Control Unit 165E1846–00 Page A–4 Rev.00 MAX .125
. CIRCULAR.1 LBS.250 +.015 +.18 5. WEIGHT = 1. MS3112E20-41P FILTERED RECEPTACLE KEYWAY 2.87 NAME PLATE AND MODIFICATIONS CONTROL UNIT MODEL S151 PNR: S151–XXXX–XX SER: XXXXXXXXX MFR: 06141 DATE: MMYYYY communications Sarasota.020 41ĆPIN.37 2.030 HOLD 5 SEC TEST 1.750 –.
0. 01/03 .07 3.00 NOTES: 1. 07 Jan. 8 5 OR TO DC POWER IN 28 VDC 5 AMPS 3 MODEL S151 CONTROL UNIT PUSH TO TEST PREAMP PWR GND PREAMP PWR HOT (+18 VDC REG) TEST INDICATOR + TEST INDICATOR – CHASSIS GND VOICE ERASE ”A” VOICE ERASE ”C” OUTPUT LO OUTPUT HI MIC INPUT LO MIC INPUT HI MIC BIAS MIC INPUT SHIELD AUDIO MONITOR LO AUDIO MONITOR HI 4 8 A B C D E F G H J K L M N P R S T U V W X Y Z a b c d e f g h i j k m n p q r s TO ANNUNCIATOR OR MAINT. COMPUTER FROM CAPTAIN’S CLOCK SPARE MICROPHONE TO 3RD CREW MEMBER OR PA SYSTEM 10. 400 HZ TO AC COLD 2. S151 Control Unit. 01/03 165E1846–00 Page A–5 . Voice Recorder Unit. 11 6 COCKPIT AREA MICROPHONE 10 t MODEL S055 MICROPHONE MIC BIAS (WHITE) MIC HIGH (BLACK) MIC LOW (GREEN) 13 9 3 FROM ROTOR SPEED SENSOR 3. Interwiring Diagram.Model FA2100 CVR Installation & Operation Instruction Manual STANDARD INTERWIRING PER ARINC SPEC 757 VOICE RECORDER UNIT 1 AMP TO 115 VAC. S055 Remote Microphone Rev. 7 BRAKE GEAR 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 115 VAC POWER IN HOT 115 VAC POWER IN COLD AUDIO OUT LO AUDIO OUT HI RECORD ON B RECORD ON A +28 VDC POWER IN STOP RECORDING PUSH TO TEST PREAMP PWR OUT GND PREAMP PWR OUT HOT (+18 VDC REG) TEST INDICATOR + TEST INDICATOR – CHASSIS GND CVR FAULT GMT IN B (ARINC 429) LO GMT IN A (ARINC 429) HI CHANNEL 1 LO CHANNEL 1 HI CHANNEL 2 LO CHANNEL 2 HI CHANNEL 3 LO CHANNEL 3 HI CHANNEL 4 LO CHANNEL 4 HI ROTOR SPEED IN LO ROTOR SPEED IN HI 12 INPUT CHANNEL 1 INPUT CHANNEL 2 INPUT CHANNEL 3 INPUT CHANNEL 4 VOICE ERASE ”A” VOICE ERASE ”C” BULK ERASE INTERLOCK (TYPICAL) Figure A–3. 11 TO COPILOT MICROPHONE 10 TO PILOT MICROPHONE 10. resolution) for 429 GMT inputs. 13. q. Jumper in aircraft connector. Recommended minimum wire size is #22. wire size #24 is electrically permissible except for long-run power leads where #18 wire is recommended (pins 2. and r may be jumpered. If 115 Vac. 01/03 . 8. 10. open = fault or CVR not installed. Twisted shielded cable. no connection is to be made to pins 2 & 3. Only one power source is to be wired per aircraft. All wiring should be MIL–W–22759 or MIL–C–27500. 400 Hz is supplied. If 28 Vdc is supplied. 9. 4. that is. Mating connectors are Cannon TM–PL–30 or TM–PL2–F–39. In the Model FA2100. 12. BITE status output: ground = no fault. Single ground point. 07 Jan. the unit will not record or erase previously recorded information. Shorting pins 1 & 2 is optional. Ground connection to be within 1 foot of pin 17. 6. L–3 P/N: 024–98–00294. Recommended cable is WTWC 2CE2419. Channel 1 will be Pilot and Channel 3 will be Third Crew Member or PA System. the 205E1849–( ) Audio Compressor card provides both 150 (1 sec resolution) and 125 (0. 3. Pins p.05 Vrms – 3 Vrms maximum. 2100–1010–( ) and 2100–1020–( ) configurations GMT is inputted as low speed (12.Installation & Operation Instruction Manual Model FA2100 CVR Notes for Figure A–3: 1. Audio input . (1Vrms nominal). If the power source has battery back-up. no connection is to be made to pin 9. Pin 3 is not a DC return and is not grounded in the recorder. 5. 24. the wiring to Channels 1 and 3 may be transposed. bulk erase will not activate. Per FAA Action Notice A8300. heavy gauge wire.1 min. 7. the –02 versions can also accept GMT as an FSK signal combined with the audio input signals on either Channel 1 or Channel 3. The control unit does not use these pins. In the Model A200S. 2. 11. and test will indicate NO–GO. S055 Panel-mount microphones are equipped with a Cannon TM–RBI–M–0 Twinax receptacle. a means for terminating recording after a crash should be included in the aircraft wiring.56 dated Jan.5 kbps) ARINC-429 to pins 25 and 26. 9. Wire resistance should not exceed 1 ohm for power leads and should not exceed 5 ohms for signal leads. Shields to be grounded at the recorder using short connections. Grounding pin 10 terminates recording within 10 minutes. Without this jumper.2SJ. 3. In all CVR configurations. 1990. however. & 17). 165E1846–00 Page A–6 Rev. this option is not available. In addition. MS3112E20-41P FILTERED RECEPTACLE 2.125
.10 MAX 1.005 TEST ERASE HOLD 5 SEC HEADSET .005 +. Model S161 Control Unit Rev.000 –.00 NOTES: 1.88 NAME PLATE AND MODIFICATIONS CONTROL UNIT MODEL S161 PNR: S161–XXXX–XX SER: XXXXXXXXX MFR: 06141 DATE: MMYYYY communications Sarasota.000 5.Model FA2100 CVR Installation & Operation Instruction Manual 4.365
. WEIGHT = 1.750 –.250 +.04 . Florida .88 MAX 2. 01/03 165E1846–00 Page A–7 .45 MODIFICATIONS 2D BAR CODE 1 4 7 10 13 2 5 8 11 14 3 6 9 12 15 TSO–C123a ED–56A STATIC ALERT LABEL FARSIDE SWITCH SWITCH GREEN LAMP COCKPIT VOICE RECORDER 2.030 1. 2.
0. DIMENSIONS ARE IN INCHES 905–E2367–18A Figure A–4.1 LBS.12 2.020 41ĆPIN. Outline and Dimensions. 07 Jan.1 LBS.50 3. CIRCULAR.19 5.56 . Interwiring Diagram. 8 5 OR TO DC POWER IN 28 VDC 5 AMPS 3 MODEL S161 CONTROL UNIT PUSH TO TEST PREAMP PWR GND PREAMP PWR HOT (+18 VDC REG) TEST INDICATOR + TEST INDICATOR – CHASSIS GND VOICE ERASE ”A” VOICE ERASE ”C” OUTPUT LO OUTPUT HI MIC INPUT LO MIC INPUT HI MIC BIAS AUDIO MONITOR LO AUDIO MONITOR HI 4 8 A B C D E F G H J K L M N P R S T U V W X Y Z a b c d e f g h i j k m n p q r s TO ANNUNCIATOR OR MAINT. 400 HZ TO AC COLD 2. 11 6 COCKPIT AREA MICROPHONE 10 t MODEL S056 MICROPHONE MIC BIAS (WHITE) MIC HIGH (BLACK) MIC LOW (SHEILD)) 13 9 3 FROM ROTOR SPEED SENSOR 3.Installation & Operation Instruction Manual Model FA2100 CVR STANDARD INTERWIRING PER ARINC SPEC 757 VOICE RECORDER UNIT 1 AMP TO 115 VAC. 7 BRAKE GEAR 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 115 VAC POWER IN HOT 115 VAC POWER IN COLD AUDIO OUT LO AUDIO OUT HI RECORD ON B RECORD ON A +28 VDC POWER IN STOP RECORDING PUSH TO TEST PREAMP PWR OUT GND PREAMP PWR OUT HOT (+18 VDC REG) TEST INDICATOR + TEST INDICATOR – CHASSIS GND CVR FAULT GMT IN B (ARINC 429) LO GMT IN A (ARINC 429) HI CHANNEL 1 LO CHANNEL 1 HI CHANNEL 2 LO CHANNEL 2 HI CHANNEL 3 LO CHANNEL 3 HI CHANNEL 4 LO CHANNEL 4 HI ROTOR SPEED IN LO ROTOR SPEED IN HI 12 INPUT CHANNEL 1 INPUT CHANNEL 2 INPUT CHANNEL 3 INPUT CHANNEL 4 VOICE ERASE ”A” VOICE ERASE ”C” BULK ERASE INTERLOCK (TYPICAL) Figure A–5. 01/03 . 07 Jan. 11 TO COPILOT MICROPHONE 10 TO PILOT MICROPHONE 10. Voice Recorder Unit. S161 Control Unit. S056 Remote Microphone 165E1846–00 Page A–8 Rev. COMPUTER FROM CAPTAIN’S CLOCK SPARE MICROPHONE TO 3RD CREW MEMBER OR PA SYSTEM 10. Model FA2100 CVR Installation & Operation Instruction Manual Notes for Figure A–5: 1. Recommended minimum wire size is #22; however, wire size #24 is electrically permissible except for long-run power leads where #18 wire is recommended (pins 2, 3, 9, & 17). Wire resistance should not exceed 1 ohm for power leads and should not exceed 5 ohms for signal leads. All wiring should be MIL–W–22759 or MIL–C–27500. 2. Only one power source is to be wired per aircraft. If 115 Vac, 400 Hz is supplied, no connection is to be made to pin 9. If 28 Vdc is supplied, no connection is to be made to pins 2 & 3. Shorting pins 1 & 2 is optional. 3. Single ground point. Ground connection to be within 1 foot of pin 17, heavy gauge wire. 4. Jumper in aircraft connector. Without this jumper, the unit will not record or erase previously recorded information, bulk erase will not activate, and test will indicate NO–GO. 5. Pin 3 is not a DC return and is not grounded in the recorder. 6. Pins p, q, and r may be jumpered. The control unit does not use these pins. 7. Twisted shielded cable. Shields to be grounded at the recorder using short connections. 8. If the power source has battery back-up, a means for terminating recording after a crash should be included in the aircraft wiring. Grounding pin 10 terminates recording within 10 minutes. 9. BITE status output: ground = no fault, open = fault or CVR not installed. 10. Audio input .05 Vrms – 3 Vrms maximum. (1Vrms nominal). 11. Per FAA Action Notice A8300.56 dated Jan. 24, 1990, the wiring to Channels 1 and 3 may be transposed; that is, Channel 1 will be Pilot and Channel 3 will be Third Crew Member or PA System. 12. In the Model A200S, this option is not available. In the Model FA2100, 2100–1010–( ) and 2100–1020–( ) configurations GMT is inputted as low speed (12.5 kbps) ARINC-429 to pins 25 and 26. In addition, the –02 versions can also accept GMT as an FSK signal combined with the audio input signals on either Channel 1 or Channel 3. In all CVR configurations, the 205E1849–( ) Audio Compressor card provides both 150 (1 sec resolution) and 125 (0.1 min. resolution) for 429 GMT inputs. 13. Rev. 07 Jan. 01/03 S055 microphone installations required double shielding. For S056 installations, double shielding is not required for new installations, however, it may be left in place for retrofit installations. 165E1846–00 Page A–9 Installation & Operation Instruction Manual Model FA2100 CVR 5.00 MAX .37 2.88 NAME PLATE AND MODIFICATIONS CONTROL UNIT MODEL S251 PNR: S251–XXXX–XX SER: XXXXXXXXX MFR: 06141 DATE: MMYYYY communications Sarasota, Florida MODIFICATIONS 1 4 7 10 13 2D BAR CODE 2 5 8 11 14 3 6 9 12 15 TSO–C123a ED–56A STATIC ALERT LABEL FARSIDE GREEN LAMP SWITCH HOLD 5 SEC 1.125 SWITCH COCKPIT VOICE RECORDER TEST HEADSET ERASE 5.375 .562 .188 5.75 37 PIN ĆSUB DC37PĆTYPE FILTERED CONNECTOR. .47 2.50 .28 2.68 .971 MAX. .062 MIN. NOTES: 1. WEIGHT = 0.8 LBS MAX. 2. DIMENSIONS ARE IN INCHES. 905–E1120–18L Figure A–6. Outline and Dimensions, Model S251 Control Unit 165E1846–00 Page A–10 Rev. 07 Jan. 01/03 Model FA2100 CVR Installation & Operation Instruction Manual STANDARD INTERWIRING PER ARINC SPEC 757 VOICE RECORDER UNIT 1 AMP TO 115 VAC, 400 HZ TO AC COLD OR 2, 7 5 TO DC POWER IN 28 VDC 5 AMPS 3 MODEL S251 CONTROL UNIT PUSH TO TEST PREAMP PWR GND PREAMP PWR HOT (+18 VDC REG) TEST INDICATOR + TEST INDICATOR – CHASSIS GND VOICE ERASE ”A” VOICE ERASE ”C” 4 OUTPUT LO OUTPUT HI 9 10 MIC NO.1 INPUT LO 22 MIC NO.1 INPUT HI MIC NO.1 BIAS MIC NO.1 INPUT SHIELD 4 AUDIO MONITOR LO AUDIO MONITOR HI 27 28 1 2 6 7 8 13 14 15 19 20 21 23 24 25 26 29 33 34 35 36 37 12 7 30 17 18 12 11 16 32 31 3 8 TO ANNUNCIATOR OR MAINT. COMPUTER 3 5 FROM CAPTAIN’S CLOCK SPARE MICROPHONE TO 3RD CREW MEMBER OR PA SYSTEM 9, 10 TO COPILOT MICROPHONE 9 TO PILOT MICROPHONE COCKPIT AREA MICROPHONE FROM ROTOR SPEED SENSOR 3, 6 MODEL S055 MICROPHONE BRAKE MIC BIAS (WHITE) MIC HIGH (BLACK) MIC LOW (GREEN) 115 VAC POWER IN HOT 115 VAC POWER IN COLD AUDIO OUT LO AUDIO OUT HI RECORD ON B RECORD ON A +28 VDC POWER IN STOP RECORDING PUSH TO TEST PREAMP PWR OUT GND PREAMP PWR OUT HOT (+18 VDC REG) TEST INDICATOR + TEST INDICATOR – CHASSIS GND CVR FAULT GMT IN B (ARINC 429) LO GMT IN A (ARINC 429) HI 30 CHANNEL 1 LO 31 32 CHANNEL 1 HI 33 34 35 CHANNEL 2 LO 36 37 CHANNEL 2 HI 38 39 INPUT CHANNEL 2 40 41 CHANNEL 3 LO 42 GEAR 45 46 47 48 49 50 51 52 53 54 55 56 57 11 INPUT CHANNEL 1 INPUT CHANNEL 3 43 CHANNEL 3 HI 44 9, 10 9 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 CHANNEL 4 LO CHANNEL 4 HI ROTOR SPEED IN LO ROTOR SPEED IN HI INPUT CHANNEL 4 VOICE ERASE ”A” VOICE ERASE ”C” BULK ERASE INTERLOCK (TYPICAL) 13 Figure A–7. Interwiring Diagram, Voice Recorder Unit, S251 Control Unit, S055 Remote Microphone Rev. 07 Jan. 01/03 165E1846–00 Page A–11 If the power source has battery back-up. 400 Hz is supplied. Recommended cable is WTWC 2CE2419. In addition. BITE status output: ground = no fault. Pin 3 is not a DC return and is not grounded in the recorder. 2100–1010–( ) and 2100–1020–( ) configurations GMT is inputted as low speed (12.05 Vrms – 3 Vrms maximum. Grounding pin 10 terminates recording within 10 minutes. 3. Single ground point. no connection is to be made to pin 9. a means for terminating recording after a crash should be included in the aircraft wiring. 9. 3. Audio input . S055 Panel-mount microphones are equipped with a Cannon TM–RBI–M–0 Twinax receptacle. 13. 7. heavy gauge wire. open = fault or CVR not installed. 11. In the Model FA2100.56 dated Jan. Channel 1 will be Pilot and Channel 3 will be Third Crew Member or PA System. this option is not available. (1Vrms nominal). 07 Jan.Installation & Operation Instruction Manual Model FA2100 CVR Notes for Figure A–7: 1. 24. however. Ground connection to be within 1 foot of pin 17. Mating connectors are Cannon TM–PL–30 or TM–PL2–F–39. 2. no connection is to be made to pins 2 & 3. resolution) for 429 GMT inputs. Use pins 35 (+) and 36 (–) for optional
5V lighting. 5. 8. Per FAA Action Notice A8300. and test will indicate NO–GO. All wiring should be MIL–W–22759 or MIL–C–27500. 12. the 205E1849–( ) Audio Compressor card provides both 150 (1 sec resolution) and 125 (0.1 min. 1990. the –02 versions can also accept GMT as an FSK signal combined with the audio input signals on either Channel 1 or Channel 3.2SJ. 9. Twisted shielded cable. Without this jumper. the unit will not record or erase previously recorded information. & 17). 01/03 . Shields to be grounded at the recorder using short connections. 165E1846–00 Page A–12 Rev. Shorting pins 1 & 2 is optional. 4.5 kbps) ARINC-429 to pins 25 and 26. If 115 Vac. L–3 P/N: 024–98–00294. 6. Only one power source is to be wired per aircraft. bulk erase will not activate. If 28 Vdc is supplied. In the Model A200S. Jumper in aircraft connector. In all CVR configurations. that is. Recommended minimum wire size is #22. wire size #24 is electrically permissible except for long-run power leads where #18 wire is recommended (pins 2. the wiring to Channels 1 and 3 may be transposed. 10. Wire resistance should not exceed 1 ohm for power leads and should not exceed 5 ohms for signal leads. Florida 3.26 . 01/03 165E1846–00 Page A–13 . Florida MODIFICATIONS 2D BAR CODE 1 4 7 10 13 2 5 8 11 14 3 6 9 12 15 TSO–C123a ED–56A STATIC ALERT LABEL FARSIDE SWITCH 1. 1. WEIGHT = 0.75 37 PIN ĆSUB DC37PĆTYPE FILTERED CONNECTOR. 2. S261-1120-00A S261-1130-00A Figure A–8. Outline and Dimensions. 07 Jan.5 LBS MAX.29 NOTES: 1.03 ± 0.Model FA2100 CVR Installation & Operation Instruction Manual NAME PLATE AND MODIFICATIONS CONTROL UNIT MODEL S261 PNR: S261–1120–00 SER: XXXXXXXXX MFR: 06141 DATE: MMYYYY communications Sarasota.75 MODIFICATIONS 1 4 7 10 13 2D BAR CODE 2 5 8 11 14 3 6 9 12 15 TSO–C123a ED–56A OR CONTROL UNIT MODEL S261 PNR: S261–1130–00 SER: XXXXXXXXX MFR: 06141 DATE: MMYYYY communications Sarasota.13 GREEN LAMP HOLD 5 SEC SWITCH COCKPIT VOICE RECORDER HEADSET ERASE TEST 5.04 2. DIMENSIONS ARE IN INCHES. Model S261 Control Unit Rev. 10 TO COPILOT MICROPHONE 9 TO PILOT MICROPHONE COCKPIT AREA MICROPHONE FROM ROTOR SPEED SENSOR 3. Interwiring Diagram.Installation & Operation Instruction Manual Model FA2100 CVR STANDARD INTERWIRING PER ARINC SPEC 757 VOICE RECORDER UNIT 1 AMP TO 115 VAC. 10 9 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 GEAR 45 46 47 48 49 50 51 52 53 54 55 56 57 CHANNEL 4 LO CHANNEL 4 HI ROTOR SPEED IN LO ROTOR SPEED IN HI 11 INPUT CHANNEL 1 INPUT CHANNEL 2 INPUT CHANNEL 3 INPUT CHANNEL 4 VOICE ERASE ”A” VOICE ERASE ”C” BULK ERASE INTERLOCK (TYPICAL) 13 Figure A–9.1 INPUT LO 22 MIC NO. 400 HZ TO AC COLD OR 2.1 BIAS 4 AUDIO MONITOR LO AUDIO MONITOR HI 27 28 1 2 6 7 8 13 14 15 19 20 21 23 24 25 26 29 33 34 35 36 37 12 7 30 17 18 12 11 16 32 31 3 8 TO ANNUNCIATOR OR MAINT. 7 5 TO DC POWER IN 28 VDC 5 AMPS 3 MODEL S261 CONTROL UNIT PUSH TO TEST PREAMP PWR GND PREAMP PWR HOT (+18 VDC REG) TEST INDICATOR + TEST INDICATOR – CHASSIS GND VOICE ERASE ”A” VOICE ERASE ”C” 4 OUTPUT LO OUTPUT HI 9 10 MIC NO. S261 Control Unit. 07 Jan. 01/03 . 6 MODEL S056 MICROPHONE BRAKE MIC BIAS (WHITE) MIC HIGH (BLACK) MIC LOW (SHIELD) 115 VAC POWER IN HOT 115 VAC POWER IN COLD AUDIO OUT LO AUDIO OUT HI RECORD ON B RECORD ON A +28 VDC POWER IN STOP RECORDING PUSH TO TEST PREAMP PWR OUT GND PREAMP PWR OUT HOT (+18 VDC REG) TEST INDICATOR + TEST INDICATOR – CHASSIS GND CVR FAULT GMT IN B (ARINC 429) LO GMT IN A (ARINC 429) HI 30 CHANNEL 1 LO 31 32 CHANNEL 1 HI 33 34 35 CHANNEL 2 LO 36 37 CHANNEL 2 HI 38 39 40 41 CHANNEL 3 LO 42 43 CHANNEL 3 HI 44 9. S056 Remote Microphone 165E1846–00 Page A–14 Rev. Voice Recorder Unit. COMPUTER 3 5 FROM CAPTAIN’S CLOCK SPARE MICROPHONE TO 3RD CREW MEMBER OR PA SYSTEM 9.1 INPUT HI MIC NO. If 28 Vdc is supplied. 5. Single ground point. Without this jumper. 01/03 165E1846–00 Page A–15 . 3. Jumper in aircraft connector. open = fault or CVR not installed. 6. 07 Jan. the unit will not record or erase previously recorded information. 9. If 115 Vac. If the power source has battery back-up.56 dated Jan. Rev. it may be left in place for retrofit installations. 4. no connection is to be made to pin 9. (1Vrms nominal). For S056 installations. wire size #24 is electrically permissible except for long-run power leads where #18 wire is recommended (pins 2. a means for terminating recording after a crash should be included in the aircraft wiring. BITE status output: ground = no fault. 13.1 min. Wire resistance should not exceed 1 ohm for power leads and should not exceed 5 ohms for signal leads. In the Model FA2100. In addition. 2100–1010–( ) and 2100–1020–( ) configurations GMT is inputted as low speed (12. that is. Recommended minimum wire size is #22. heavy gauge wire. however. Ground connection to be within 1 foot of pin 17. 9. however. this option is not available. the wiring to Channels 1 and 3 may be transposed. 10. no connection is to be made to pins 2 & 3. 7. Use pins 35 (+) and 36 (–) for optional
5V lighting. Audio input . double shielding is not required for new installations.Model FA2100 CVR Installation & Operation Instruction Manual Notes for Figure A–9: 1. the 205E1849–( ) Audio Compressor card provides both 150 (1 sec resolution) and 125 (0. In the Model A200S. All wiring should be MIL–W–22759 or MIL–C–27500. and test will indicate NO–GO. 2. Grounding pin 10 terminates recording within 10 minutes. resolution) for 429 GMT inputs. 8. In all CVR configurations.5 kbps) ARINC-429 to pins 25 and 26. Channel 1 will be Pilot and Channel 3 will be Third Crew Member or PA System. bulk erase will not activate. Pin 3 is not a DC return and is not grounded in the recorder. Only one power source is to be wired per aircraft. Per FAA Action Notice A8300. 400 Hz is supplied. Twisted shielded cable. & 17). 11. 24. the –02 versions can also accept GMT as an FSK signal combined with the audio input signals on either Channel 1 or Channel 3. 1990. Shields to be grounded at the recorder using short connections. Shorting pins 1 & 2 is optional. 12.05 Vrms – 3 Vrms maximum. 3. S055 microphone installations required double shielding. DIMENSIONS ARE IN INCHES 905–E1926–18B Figure A–10.365
. 01/03 .88 NAME PLATE AND MODIFICATIONS CONTROL UNIT MODEL S152 PNR: S152–00X0–X0 SER: XXXXXXXXX MFR: 06141 DATE: MMYYYY communications Sarasota. 07 Jan. MS3112E20-41P FILTERED RECEPTACLE 2.Installation & Operation Instruction Manual Model FA2100 CVR 4.1 LBS.56 MICROPHONE . Outline and Dimensions. WEIGHT = 1.50 3.020 41ĆPIN.00 NOTES: 1.12 2. Florida MODIFICATIONS 1 4 7 10 13 2D BAR CODE 2 5 8 11 14 3 6 9 12 15 TSO–C123a ED–56A STATIC ALERT LABEL FARSIDE SWITCH SWITCH GREEN LAMP ÍÍÍ ÍÍÍ ÍÍÍ COCKPIT VOICE RECORDER 2. 2. CIRCULAR.005 +.000 5.750 –.
0.250 +.88 MAX . Model S152 Control Unit 165E1846–00 Page A–16 Rev.10 MAX 1.125
.19 5.005 ERASE HEADSET .1 LBS.04 .000 –.030 TEST HOLD 5 SEC 1.45 2. 19 5.005 ERASE HEADSET .005 +. WEIGHT = 1. Florida MODIFICATIONS 1 4 7 10 13 2D BAR CODE 2 5 8 11 14 3 6 9 12 15 TSO–C123a ED–56A STATIC ALERT LABEL FARSIDE SWITCH SWITCH GREEN LAMP ÍÍÍ ÍÍÍ ÍÍÍ COCKPIT VOICE RECORDER 2.750 –.88 NAME PLATE AND MODIFICATIONS CONTROL UNIT MODEL S162 PNR: S162–00XX–00 SER: XXXXXXXXX MFR: 06141 DATE: MMYYYY communications Sarasota.04 .88 MAX .12 2. Outline and Dimensions.250 +. DIMENSIONS ARE IN INCHES 905–E2387–18A Figure A–11. 2. CIRCULAR.125
.
0.1 LBS.45 2.56 MICROPHONE .1 LBS.10 MAX 1.50 3.365
. MS3112E20-41P FILTERED RECEPTACLE 2. 07 Jan. Model S162 Control Unit Rev.00 NOTES: 1.000 –.030 TEST HOLD 5 SEC 1.Model FA2100 CVR Installation & Operation Instruction Manual 4.020 41ĆPIN.000 5. 01/03 165E1846–00 Page A–17 . 8 5 OR TO DC POWER IN 28 VDC 5 AMPS 3 MODEL S152/S162 CONTROL UNIT 4 PUSH TO TEST PREAMP PWR GND PREAMP PWR HOT (+18 VDC REG) TEST INDICATOR + TEST INDICATOR – CHASSIS GND A B C D E F VOICE ERASE “A” VOICE ERASE “C” G H J K L M N P R S T U V W X Y Z a b c d e f g h i j k m n p q r s OUTPUT LO OUTPUT HI MIC INPUT LO MIC INPUT HI MIC BIAS MIC INPUT SHIELD AUDIO MONITOR LO AUDIO MONITOR HI INTERNAL MIC HI INTERNAL MIC BIAS 8 9 3 TO ANNUNCIATOR OR MAINT.Installation & Operation Instruction Manual Model FA2100 CVR STANDARD INTERWIRING PER ARINC SPEC 757 VOICE RECORDER UNIT 1 AMP TO 115 VAC. 7 BRAKE GEAR 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 115 VAC POWER IN HOT 115 VAC POWER IN COLD AUDIO OUT LO AUDIO OUT HI RECORD ON B RECORD ON A +28 VDC POWER IN STOP RECORDING PUSH TO TEST PREAMP PWR OUT GND PREAMP PWR OUT HOT (+18 VDC REG) TEST INDICATOR + TEST INDICATOR – CHASSIS GND CVR FAULT GMT IN B (ARINC 429) LO GMT IN A (ARINC 429) HI CHANNEL 1 LO CHANNEL 1 HI CHANNEL 2 LO CHANNEL 2 HI CHANNEL 3 LO CHANNEL 3 HI CHANNEL 4 LO CHANNEL 4 HI ROTOR SPEED IN LO ROTOR SPEED IN HI 12 INPUT CHANNEL 1 INPUT CHANNEL 2 INPUT CHANNEL 3 INPUT CHANNEL 4 VOICE ERASE “A” VOICE ERASE “C” BULK ERASE INTERLOCK (TYPICAL) Figure A–12. COMPUTER FROM CAPTAIN’S CLOCK SPARE MICROPHONE TO 3RD CREW MEMBER OR PA SYSTEM 10. S152/S162 Control Unit with Internal Microphone 165E1846–00 Page A–18 Rev. 07 Jan. Voice Recorder Unit. 11 6 COCKPIT AREA MICROPHONE 10 t FROM ROTOR SPEED SENSOR 3. 01/03 . 11 TO COPILOT MICROPHONE 10 TO PILOT MICROPHONE 10. 400 HZ TO AC COLD 2. Interwiring Diagram. Single ground point.56 dated Jan. wire size #24 is electrically permissible except for long-run power leads where #18 wire is recommended (pins 2. The control unit does not use these pins. Twisted shielded cable. 12. 4. Recommended minimum wire size is #22. the –02 versions can also accept GMT as an FSK signal combined with the audio input signals on either Channel 1 or Channel 3. Channel 1 will be Pilot and Channel 3 will be Third Crew Member or PA System. Without this jumper. Pin 3 is not a DC return and is not grounded in the recorder. 10.Model FA2100 CVR Installation & Operation Instruction Manual Notes for Figure A–12: 1. Shields to be grounded at the recorder using short connections. In the Model FA2100. 3. (1Vrms nominal). 3. In addition. If 28 Vdc is supplied. however. this option is not available. If 115 Vac. & 17). 07 Jan.1 min. Only one power source is to be wired per aircraft. 9. 6.05 Vrms – 3 Vrms maximum. Jumper in aircraft connector. bulk erase will not activate. 5. Rev. 9. Pins p. Grounding pin 10 terminates recording within 10 minutes. In all CVR configurations. 24. 2. that is. resolution) for 429 GMT inputs. 01/03 165E1846–00 Page A–19 . Wire resistance should not exceed 1 ohm for power leads and should not exceed 5 ohms for signal leads. Ground connection to be within 1 foot of pin 17. and test will indicate NO–GO. If the power source has battery back-up. heavy gauge wire. BITE status output: ground = no fault. open = fault or CVR not installed. and r may be jumpered. the 205E1849–( ) Audio Compressor card provides both 150 (1 sec resolution) and 125 (0. All wiring should be MIL–W–22759 or MIL–C–27500. In the Model A200S. no connection is to be made to pin 9. the wiring to Channels 1 and 3 may be transposed. 7. no connection is to be made to pins 2 & 3. q. 11. Shorting pins 1 & 2 is optional. 2100–1010–( ) and 2100–1020–( ) configurations GMT is inputted as low speed (12. Per FAA Action Notice A8300. 8. Audio input . the unit will not record or erase previously recorded information. 400 Hz is supplied. 1990.5 kbps) ARINC-429 to pins 25 and 26. a means for terminating recording after a crash should be included in the aircraft wiring. 236
.236
.746
.778
.020 . .G.06 1.389
.528
.020 .45
.030 .) Black 0. 4 HOLES 2.937
.020 .20
.374
. 905–E0986–18D Figure A–13.020 1.968
.020 2X .020 C. Florida MS3112E8Ć3S OR EQUIVALENT MODIFICATIONS 1 4 7 10 13 2D BAR CODE 2 5 8 11 14 3 6 9 12 15 MS3112E14Ć19S OR EQUIVALENT TSO–C123a ED–56A 3.7 lbs. 01/03 .020 2.020 PREAMPLIFIER MODEL S150 PNR: S150–0020–00 SER: XXXXXXXXX MFR: 06141 DATE: MMYYYY communications Sarasota.030 .030 .860
.727
.06 NAMEPLATE AND MODIFICATIONS .Installation & Operation Instruction Manual Model FA2100 CVR 5.020 Part Number S150–0020–00 NOTES: 1.201Ć.030 4.55
. Model S150 External Preamplifier Module 165E1846–00 Page A–20 Rev. 1.030 C.06 3.531
.125
.378
. DIMENSIONS ARE IN INCHES. Housing Color Weight (+ 0.020 1.000
. 07 Jan.G.1 lbs.195 DIA. Outline and Dimensions. Voice Recorder Unit. 7 TO DC POWER IN 28 VDC 5 5 AMPS 3 MODEL S150 EXTERNAL PREAMPLIFIER PREAMPLIFIER J2 PREAMP PWR GND PREAMP PWR (+18 VDC REGULATED) 4 7 B A CHASSIS GND F OUTPUT LOW D OUTPUT HIGH C 8 3 TO ANNUNCIATOR OR MAINT. 6 MIC. S055 Remote Microphone Rev. BIAS(WHITE) MIC HIGH (BLACK) MIC. 10 TO COPILOT MICROPHONE 9 TO PILOT MICROPHONE 9. Interwiring Diagram.Model FA2100 CVR Installation & Operation Instruction Manual STANDARD INTERWIRING (No Control Unit) VOICE RECORDER UNIT 1 AMP TO 115 VAC 400HZ TO AC COLD OR 2. LOW (GREEN) 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 115 VAC POWER IN HOT 115 VAC POWER IN COLD AUDIO OUT LO AUDIO OUT HI RECORD ON B RECORD ON A +28 VDC POWER IN STOP RECORDING PUSH TO TEST PREAMP PWR OUT GND PREAMP PWR OUT HOT (+18 VDC REG) TEST INDICATOR + 11 TEST INDICATOR – CHASSIS GND CVR FAULT GMT IN B (ARINC 429) LO GMT IN A (ARINC 429) HI CHANNEL 1 LO 12 INPUT CHANNEL 1 CHANNEL 1 HI CHANNEL 2 LO INPUT CHANNEL 2 CHANNEL 2 HI CHANNEL 3 LO INPUT CHANNEL 3 CHANNEL 3 HI CHANNEL 4 LO INPUT CHANNEL 4 CHANNEL 4 HI ROTOR SPEED IN LO ROTOR SPEED IN HI VOICE ERASE ”A” VOICE ERASE ”C” 13 Figure A–14. 01/03 165E1846–00 Page A–21 . 10 COCKPIT AREA MICROPHONE 9 MODEL S055 MICROPHONE FROM ROTOR SPEED SENSOR 3. 07 Jan. COMPUTER PREAMPLIFIER J1 MICROPHONE INPUT LO C MICROPHONE INPUT HI A MICROPHONE BIAS B FROM CAPTAIN’S CLOCK SPARE MICROPHONE TO 3RD CREW MEMEBER OR PA SYSTEM NOTE: CONNECT OUTER SHIELD TO CONNECTOR SHELL 9. S150 External Preamplifier. 3. All wiring should be MIL–W–22759 or MIL–C–27500. 4. no connection is to be made to pin 9. this option is not available. If 28 Vdc is supplied.1 min. 5. Grounding pin 10 terminates recording within 10 minutes. Without this jumper. heavy gauge wire. Only one power source is to be wired per aircraft. Pin 3 is not a DC return and is not grounded in the recorder.) 12. a means for terminating recording after a crash should be included in the aircraft wiring. 8. Audio input . that is. Single ground point. Twisted shielded cable. Ground connection to be within 1 foot of pin 17. (This is not sufficient to light an external Annunciator lamp. In the Model A200S. 01/03 . Channel 1 will be Pilot and Channel 3 will be Third Crew Member or PA System. Shields to be grounded at the recorder using short connections. 24. (1Vrms nominal). In the Model FA2100. If the power source has battery back-up. Mating connectors are Cannon TM–PL–30 or TM–PL2–F–39. resolution) for 429 GMT inputs. Test Indicator +/. 13. the unit will not record or erase previously recorded information. & 17). 1ma output to illuminate the Control Unit Test Lamp. BITE status output: Ground = no fault. 2100–1010–( ) and 2100–1020–( ) configurations GMT is inputted as low speed (12. 7.5 kbps) ARINC-429 to pins 25 and 26. Wire resistance should not exceed 1 ohm for power leads and should not exceed 5 ohms for signal leads. 07 Jan. In all CVR configurations. and test will indicate NO-GO. 1990. 3. bulk erase will not activate. the wiring to Channels 1 and 3 may be transposed. Recommended cable is WTWC 2CE2419. 11. 9. the –02 versions can also accept GMT as an FSK signal combined with the audio input signals on either Channel 1 or Channel 3.Installation & Operation Instruction Manual Model FA2100 CVR Notes for Figure A–14: 1. If 115 Vac. Jumper in aircraft connector. 400 Hz is supplied. however. no connection is to be made to pins 2 & 3. 2. Shorting pins 1 & 2 is optional. Per FAA Action Notice A8300. the 205E1849–( ) Audio Compressor card provides both 150 (1 sec resolution) and 125 (0. 10.05 Vrms – 3 Vrms maximum. wire size #24 is electrically permissible except for long-run power leads where #18 wire is recommended (pins 2. S055 Panel-mount microphones are equipped with a Cannon TM–RBI–M–0 Twinax receptacle. Recommended minimum wire size is #22. 6.56 dated Jan. In addition.lines (pins 15 & 16) only provide +12 Vdc. L–3 P/N: 024–98–00294. Open = fault or CVR not installed. 9. 165E1846–00 Page A–22 Rev.2SJ. ) S160–0020–00 Black 0. 07 Jan.74 1. Outline and Dimensions.39 PREAMPLIFIER MODEL S160 PNR: S160–0020–00 SER: XXXXXXXXX MFR: 06141 DATE: MMYYYY communications Sarasota. NOTES: 1.1 lbs.020 3. Model S160 External Preamplifier Module Rev.05 .Model FA2100 CVR Installation & Operation Instruction Manual 4.23 . DIMENSIONS ARE IN INCHES.78
.00 1.38
.65 lbs.97 NAMEPLATE AND MODIFICATIONS .92 1. 01/03 165E1846–00 Page A–23 .23 0.06 3.53 . 4 HOLES 2.54
.99 4. S160–0020–00A Figure A–15.196 DIA.75 2X 1.05 Part Number Housing Color Weight (+ 0. Florida MODIFICATIONS 1 4 7 10 13 2D BAR CODE 2 5 8 11 14 SOURIAU 8525-10R-8B-3ASN009 3 6 9 12 15 SOURIAU 825-10R-14B-19SN009 TSO–C123a ED–56A . 7 TO DC POWER IN 28 VDC 5 5 AMPS 3 MODEL S160 EXTERNAL PREAMPLIFIER PREAMPLIFIER J2 PREAMP PWR GND PREAMP PWR (+18 VDC REGULATED) 4 7 B A CHASSIS GND F OUTPUT LOW D OUTPUT HIGH C 8 3 TO ANNUNCIATOR OR MAINT. 6 MIC. 07 Jan.Installation & Operation Instruction Manual Model FA2100 CVR STANDARD INTERWIRING (No Control Unit) VOICE RECORDER UNIT 1 AMP TO 115 VAC 400HZ TO AC COLD OR 2. Interwiring Diagram. COMPUTER PREAMPLIFIER J1 MICROPHONE INPUT LO C MICROPHONE INPUT HI A MICROPHONE BIAS B FROM CAPTAIN’S CLOCK SPARE MICROPHONE TO 3RD CREW MEMEBER OR PA SYSTEM 9. S056 Remote Microphone 165E1846–00 Page A–24 Rev. 10 TO COPILOT MICROPHONE 9 TO PILOT MICROPHONE 9. LOW (GREEN) 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 115 VAC POWER IN HOT 115 VAC POWER IN COLD AUDIO OUT LO AUDIO OUT HI RECORD ON B RECORD ON A +28 VDC POWER IN STOP RECORDING PUSH TO TEST PREAMP PWR OUT GND PREAMP PWR OUT HOT (+18 VDC REG) TEST INDICATOR + 11 TEST INDICATOR – CHASSIS GND CVR FAULT GMT IN B (ARINC 429) LO GMT IN A (ARINC 429) HI CHANNEL 1 LO CHANNEL 1 HI CHANNEL 2 LO CHANNEL 2 HI CHANNEL 3 LO CHANNEL 3 HI CHANNEL 4 LO CHANNEL 4 HI ROTOR SPEED IN LO ROTOR SPEED IN HI 12 INPUT CHANNEL 1 INPUT CHANNEL 2 INPUT CHANNEL 3 INPUT CHANNEL 4 VOICE ERASE ”A” VOICE ERASE ”C” 13 Figure A–16. Voice Recorder Unit. 10 COCKPIT AREA MICROPHONE 9 MODEL S056 MICROPHONE FROM ROTOR SPEED SENSOR 3. BIAS(WHITE) MIC HIGH (BLACK) MIC. 01/03 . S160 External Preamplifier. Ground connection to be within 1 foot of pin 17. 1990. Recommended minimum wire size is #22. that is. 3.1 min. Shields to be grounded at the recorder using short connections. 3. this option is not available. 11. however.) 12. resolution) for 429 GMT inputs. In the Model FA2100. 9. the unit will not record or erase previously recorded information. Jumper in aircraft connector. Audio input . 2. All wiring should be MIL–W–22759 or MIL–C–27500. no connection is to be made to pin 9. Open = fault or CVR not installed. bulk erase will not activate. For S056 installations. the –02 versions can also accept GMT as an FSK signal combined with the audio input signals on either Channel 1 or Channel 3. If 28 Vdc is supplied. Test Indicator +/. 6. 10. 9. 24. Without this jumper. the 205E1849–( ) Audio Compressor card provides both 150 (1 sec resolution) and 125 (0. Rev. 400 Hz is supplied.Model FA2100 CVR Installation & Operation Instruction Manual Notes for Figure A–16: 1. BITE status output: Ground = no fault. Only one power source is to be wired per aircraft. 7. 07 Jan. 165E1846–00 Page A–25 . 2100–1010–( ) and 2100–1020–( ) configurations GMT is inputted as low speed (12. Channel 1 will be Pilot and Channel 3 will be Third Crew Member or PA System. a means for terminating recording after a crash should be included in the aircraft wiring. In all CVR configurations. If 115 Vac. (1Vrms nominal). If the power source has battery back-up.5 kbps) ARINC-429 to pins 25 and 26. (This is not sufficient to light an external Annunciator lamp. 4. Per FAA Action Notice A8300. 13. the wiring to Channels 1 and 3 may be transposed. Wire resistance should not exceed 1 ohm for power leads and should not exceed 5 ohms for signal leads. 01/03 S055 microphone installations required double shielding.56 dated Jan. no connection is to be made to pins 2 & 3.lines (pins 15 & 16) only provide +12 Vdc. Single ground point.05 Vrms – 3 Vrms maximum. 1ma output to illuminate the Control Unit Test Lamp. Grounding pin 10 terminates recording within 10 minutes. In the Model A200S. & 17). wire size #24 is electrically permissible except for long-run power leads where #18 wire is recommended (pins 2. double shielding is not required for new installations. In addition. heavy gauge wire. 5. however. Pin 3 is not a DC return and is not grounded in the recorder. Twisted shielded cable. and test will indicate NO-GO. 8. it may be left in place for retrofit installations. Shorting pins 1 & 2 is optional. 01/03 .2 lbs 17" * PER MIL-STD-595 Figure A–17.50 Model FA2100 CVR 1. 37038* 0.2 lbs 17" S055–0066–00 Brown. 22 AWG TWISTED PAIR. Model S055 Surface-Mount Microphone Module 165E1846–00 Page A–26 Rev. Outline and Dimensions. Florida.84 DIA . ATR–42 0.1 lbs. 2.2 lbs 70" S055–0068–00 Brown. USA 2D BAR CODE TSO–C123a ED–56A NAMPLATE INFORMATION 905–E1300–18K Part Number Housing Color Weight (+/–0.2 lbs 17" S055–0067–01 Black – No.700 cL MIC BIAS +6V (WHITE) MIC SHIELD (OUTER SHIELD) PIGTAIL (YELLOW) NAMEPLATE 6–32 THD X .) Minimum Cable Lenght S055–0064–00 Gray (BD–100) 0. SEE CHART FOR LENGTH MINIUM MIC LOW (INNER SHIELD) PIGTAIL (GREEN) MIC HI (BLACK) .2 lbs 17" S055–0065–00 Gray – No.19 .09 1.42 DIA 1 2.2 lbs 17" S055–0067–00 Black – No.Installation & Operation Instruction Manual . 37038* 0. 36116* 0.64 cL FOAM DAMPER . DIMENSIONS ARE IN INCHES. Medium (Boeing) 0.25 15
. MICROPHONE MODEL S055 PNR S055–00XX–00 SER XXXXXXXXXX MFR 06141 DMF MMYYYY communications Sarasota.22 DEEP (2 PLACES) NOTES: 1 INDICATED PORTION OF MICROPHONE MUST BE UNOBSTUCTED FOR PROPER OPERATION.92 ÉÉÉÉ ÉÉÉÉ ÉÉÉ ÅÅ ÉÉÉÉ ÉÉÉ ÅÅ ÉÉÉÉ ÉÉÉ SHIELDED WIRE.12 30
1. 07 Jan. INDICATED PORTION OF MICROPHONE MUST BE UNOBSTRUCTED FOR PROPER OPERATION. 1. USA 2D BAR CODE NAMEPLATE COMPANY LOGO TSO–C123a ED–56A NAMPLATE INFORMATION CANNON TM–RB1–M–0 TWINAX RECEPTACLE 1 1.50 MAX.00 DIA. 07 Jan. Medium (Boeing) 0.625 2 2.1 lbs. 01/03 165E1846–00 Page A–27 . Outline and Dimensions.87 NOTES: 1 2 3 MATING PLUGS FOR SPECIFIED RECEPTACLE ARE CANNON TM–PL–F–39 OR TM–PL2–F–39. 2.625 0.25 ÉÉÉÉ ÉÉÉ ÉÉÉÉ ÉÉÉ ÉÉ ÅÅ ÉÉÉÉ ÉÉÉ ÉÉ ÅÅ ÉÉÉÉ 2.56 4X 6–32 TAPPED HOLES 0.Model FA2100 CVR Installation & Operation Instruction Manual MICROPHONE MODEL S055 PNR S055–0030–00 SER XXXXXXXXXX MFR 06141 DMF MMYYYY communications Sarasota. Model S055 Panel-Mount Microphone Module Rev. DIMENSIONS ARE IN INCHES. Florida.) S055–0030–00 Brown. 905–E1780–18E Part Number Panel Color Weight (+ 0.00 2.4 lbs. Figure A–18.00 2. USA 2D BAR CODE TSO–C123a ED–56A NAMPLATE INFORMATION 905–E1771–18G Part Number Housing Color Weight (+ 0. communications Sarasota. Dimensions are in inches. 20059 0. 01/03 . Outline and Dimensions.46 MAX 3.700 cL SIGNAL GND (SHIELD) SHIELDED WIRE 22 GAUGE TWISTED PAIR 2 X # 6ć32 THD NAMEPLATE MICROPHONE MODEL S056 PNR S056–00XX–00 SER XXXXXXXXXX MFR 06141 DMF MMYYYY 1 Indicated portion of microphone must be unobstucted for proper operation.2 lbs.) S056–0047–00 Gray – No. 2.3 17 DC SUPPLY 18V (WHITE) SIGNAL OUTPUT (BLACK) 0. * PER MIL-STD-595 Figure A–19. Florida. S056–0050–00 Boeing Brown – No.50 0. S056–0048–00 Black – No.42 DIA 1.2 lbs.1 lbs. 36116* 0. 36118* 0.2 lbs.Installation & Operation Instruction Manual Model FA2100 CVR 0. ATR–42 – No.09 ÉÉÉÉ ÉÉÉÉ ÉÉÉ ÅÅ ÉÉÉÉ ÉÉÉ ÅÅ ÉÉÉÉ ÉÉÉ ÅÅ ÉÉÉÉ 1 1.15 MAX .2 lbs.64 cL FOAM DAMPER 1. 07 Jan. S056–0049–00 Brown. Model S056 Surface-Mount Microphone Module 165E1846–00 Page A–28 Rev. 37038* 0. 2 lbs. 01/03 165E1846–00 Page A–29 . Florida.Model FA2100 CVR 1 Installation & Operation Instruction Manual MICROPHONE MODEL S056 Indicated portion of microphone must be unobstructed for proper operation. Model S056 Panel-Mount Microphone Module Rev. 2.) 0. USA 2D BAR CODE TSO–C123a ED–56A NAMPLATE INFORMATION 905–E1838–18D Part Number S056–1048–00 Panel Color Black Weight (+ 0. Dimensions are in inches. Figure A–20.1 lbs. 07 Jan. PNR S056–1048–00 SER XXXXXXXXXX MFR 06141 DMF MMYYYY communications Sarasota. Outline and Dimensions. 9 K 30 SIGNAL GROUND 300 TEST CIRCUIT SPECIFICATIONS: 60 FREQ RESP: REFER TO CHART. ELEMENT CAPACITANCE: 17pF @ 1 kHz CAPACITANCE (PIćFILTER): 4000pF
20%.9 kOHM LOAD RESISTOR @ 1 kHz.53 . 01/03 .423
. DIMENSIONS: SEE DRAWING SPECIAL FEATURE: CARDIOID POLAR RESPONSE 120 240 SHELL: BRASS COLOR: BLACK. 100 WVDC 270 90 WORKING VOLTAGE: <10 VDC MAX.005
. 07 Jan.) @ 100dB SPL WITH A 16. OUTPUT LEVEL (1 kHz SENSITIVITY): 7 TO 17.882
.Installation & Operation Instruction Manual Model FA2100 CVR SIGNAL OUTPUT (BLACK) +6 VDC INPUT MIC BIAS (WHITE) .020 .50 +6 VDC INPUT SIGNAL GROUND (GREEN) SIGNAL OUTPUT MIC 0 330 16.5 mV (11 mV NOM. 5 FEET. Model S055 Microphone Element Specifications and Response Diagram 165E1846–00 Page A–30 Rev. COLOR 27038 PER FEDĆSTDĆ595 Used On Remote Mic Part Numbers: S055-0065-00 S055-0066-00 S055-0067-00 S055-0068-00 S055-0030-00 5 dB 210 180 SCALE IS 5 DECIBELS PER DIVISION 100 Hz 2000 Hz POLAR RESONSE RESPONSE IN dB 1/4" 5' 180 20 30 50 100 200 500 OFF AXIS 1K 2K 5K 10K 20K Figure A–21. 423
. 120 240 MICROPHONE COLOR: BLACK. WITH A WHITE OUTER JACKET.32 .50 1.84 +18 VDC INPUT SIGNAL OUTPUT MIC . #22 GAGE STRANDED.Model FA2100 CVR Installation & Operation Instruction Manual SIGNAL OUTPUT (BLACK) . Used On Remote Mic Part Numbers: S056-0047-00 S056-0048-00 S056-0049-00 S056-0050-00 S056-1048-00 5 dB 210 SCALE IS 5 DECIBELS PER DIVISION 100 Hz 180 2000 Hz POLAR RESPONSE RESPONSE IN dB 1/4" 1M 180 20 30 50 100 200 500 OFF AXIS 1K 2K 5K 10K 20K Figure A–22. 01/03 165E1846–00 Page A–31 . 270 90 DIMENSIONS: SEE DRAWING ABOVE.005
. AT 1 METER. CABLE: TEFLON INSULATED SHIELDED 2 COND.53 DC SUPPLY 18V (WHITE) . ONE BLACK. SPECIAL FEATURE: CARDIOID POLAR RESPONSE. OUTPUT LEVEL: 155mV NOMINAL
4dB AT 1KHz 94dB SPL.01uF 0 330 1K SIGNAL GROUND SIGNAL GROUND (SHIELD) 30 300 60 TEST CIRCUIT SPECIFICATIONS: FREQ RESP: REFER TO CHART . ONE WHITE. 07 Jan. Model S056 Microphone Element Specifications and Response Diagram Rev. 37 5.50 3.13 1. 01/03 .1 lbs.002 HEADSET 600 OHMS .250 +.37 NAMEPLATE AND MODIFICATIONS (WITH CONFIG.000 Ć . MS3112Ć20Ć41P RECEPTACLE METER ILLUMINATION None None None None 28V None KEYWAY 2.125
.020 PANEL COLOR Gray Black Brown (Boeing) Brown (ATR–42) DO328 BLUE DO328 BLUE NOTES: 1.9 LBS.87 .00 MAX 2.56 COCKPIT VOICE RECORDER . Model A151B Control Unit Does Not Comply with ED–56A 165E1846–00 Page A–32 Rev. AS REQ'D) PLUG BUTTON SWITCHES METER TEST 2.18 PART NUMBER 93A151–20 93A151–30 93A151–40 93A151–50 93A151–60 93A151–70 5. Outline and Dimensions.12 2. WEIGHT = 0.Installation & Operation Instruction Manual Model FA2100 CVR 5.00 MAX 93–CVR120C Figure A–23.030 ERASE 1. DIMENSIONS ARE IN INCHES. 07 Jan. 2.12 .
0.000 Ć .750 + . 51.Model FA2100 CVR Installation & Operation Instruction Manual STANDARD INTERWIRING PER ARINC SPEC 557 VOICE RECORDER UNIT TO 115 VAC HOT (400HZ) TO AC COLD 2. 8. 12. COMPUTER FROM CAPTAIN’S CLOCK SPARE MICROPHONE TO 3RD CREW MEMBER OR PA SYSTEM 10. 26. 37. 11. 28. 55. 46. 31. 33. 6. 36. 3.000 HZ 12 AUDIO JACK – LO AUDIO JACK – HI 6 DB ATTENUATION ATTENUATOR_ COMMON 12 DB ATTENUATION 24 DB ATTENUATION A B C D E F G H J K L M N P R S T U V W X Y Z a b c d e f g h i j k p q r s t 8 3 9 TO ANNUNCIATOR OR MAINT. 5. 15. 7 MODEL A55B MICROPHONE MIC OUTPUT HI (AUDIO) MIC OUTPUT LO ( DC IN ) MIC SHIELD (CONNECTOR SHELL) 1 2 BRAKE GEAR 1. 23. 32. 29. 10. A55B Remote Microphone Such Installations Do Not Comply with ED–56A Rev. 41. 34. 50. 49. 07 Jan. 30. 38. 47. 45. 56.5VDC 5 AMPS 5 3 MODEL A151B CONTROL UNIT 4 PUSH_TO_TEST PRE–AMP POWER GND PRE–AMP POWER +18 VDC INDICATOR + INDICATOR – CHASSIS GROUND ERASE SWITCH “A” ERASE SWITCH “C” OUTPUT – LOW OUTPUT – HIGH MIKE CABLE SHIELD MIKE INPUT – HI MIKE INPUT – LO FILTER COMMON FILTER 1. Voice Recorder Unit. 4. 7. 11 TO COPILOT MICROPHONE 10 TO PILOT MICROPHONE 6 10. 115 VAC HOT OUT 115 VAC HOT IN AC COMMON COLD AUDIO OUT LO AUDIO OUT HI BIAS JUMPER BIAS JUMPER +27. 21. 24. 48. 43. 25. 22. 53. 52. 35. 40. 44. 54. 19. 2. 39. Interwiring Diagram. 16. 42. 8 OR 1 AMP TO 27. 17. 20.5 Vdc INPUT STOP RECORDING PUSH_TO_TEST PREAMP POWER OUT GND PREAMP POWER +18 Vdc REG INDICATOR + INDICATOR – CHASSIS GROUND CVR FAULT GMT IN B (ARINC 429) LO GMT IN A (ARINC 429) HI 13 LO CHANNEL 1 HI LO CHANNEL 2 HI LO CHANNEL 3 HI LO CHANNEL 4 HI ROTOR SPEED IN LO ROTOR SPEED IN HI ERASE A ERASE C 14 Figure A–24. 9. 01/03 165E1846–00 Page A–33 . 57. 18. A151B Control Unit. 13. 11 COCKPIT AREA MICROPHONE 10 FROM ROTOR SPEED SENSOR 3. 14. 27. 6. 4. Per FAA Action Notice A8300. resolution) for 429 GMT inputs. 165E1846–00 Page A–34 Rev.56 dated Jan. & 17). the wiring to Channels 1 and 3 may be transposed. 14. Without this jumper. Grounding pin 10 terminates recording within 10 minutes. this option is not available. Recommended cable is MIL–W–16878/21. 12. 01/03 . 5.1 min. 9. Channel 1 will be Pilot and Channel 3 will be Third Crew Member or PA System. no connection is to be made to pin 9. A55B Panel-mount microphones are equipped with a Cannon TM–RBI–M–0 Twinax receptacle. bulk erase will not activate. heavy gauge wire. the unit will not record or erase previously recorded information. Wire resistance should not exceed 1 ohm for power leads and should not exceed 5 ohms for signal leads. no connection is to be made to pin 3. Audio input . Jumper in aircraft connector. and test will indicate NO–GO. Ground connection to be within 1 foot of pin 17. If 115 Vac. wire size #24 is electrically permissible except for long-run power leads where #18 wire is recommended (pins 2. Recommended minimum wire size is #22. In the Model FA2100. 9. 8. a means for terminating recording after a crash should be included in the aircraft wiring. 3. In all CVR configurations. 11. 3.5 kbps) ARINC-429 to pins 25 and 26. Shorting pins 1 & 2 is optional. Short pins S & T for piston aircraft only. Only one power source is to be wired per aircraft. Mating connectors are Cannon TM–PL–30 or TM–PL2–F–39. open = fault or CVR not installed. 400 Hz is supplied. 07 Jan. Twisted shielded cable. (1Vrms nominal). In the Model A200S. that is. the 205E1849–( ) Audio Compressor card provides both 150 (1 sec resolution) and 125 (0. In addition. Single ground point. If 27. 2. If the power source has battery back-up. BITE status output: ground = no fault. Pin 3 is not a DC return and is not grounded in the recorder. 13. 10. Wiring shown for fixed attenuation of 18 dB. the –02 versions can also accept GMT as an FSK signal combined with the audio input signals on either Channel 1 or Channel 3. 1990. 24.05 Vrms – 3 Vrms maximum. however. All wiring should be MIL–W–22759 or MIL–C–27500.5 Vdc is supplied.Installation & Operation Instruction Manual Model FA2100 CVR Notes for Figure A–24: 1. 7. Shields to be grounded at the recorder using short connections. 2100–1010–( ) and 2100–1020–( ) configurations GMT is inputted as low speed (12. 37 5. Model A152B Control Unit Does Not Comply with ED–56A Rev.020 PART NUMBER 93A152–20 93A152–25 93A152–30 93A152–35 93A152–40 93A152–50 93A152–60 93A152–70 PANEL COLOR Gray Gray Black Gray Gray Brown (ATR–42) Brown (ATR–42) Black NOTES: 1.50 3.87 .20 MAX.750 +.15 LBS.030 SWITCHES ÎÎ ÎÎ TEST ERASE 1.12 .00 93–CVR119B Figure A–25.56 COCKPIT VOICE RECORDER .250 +.
0.18 5.2 LBS.13 1. WEIGHT = 1. MS3112Ć20Ć41P RECEPTACLE METER ILLUMINATION None None 28V 28V 5V None 5V None KEYWAY 2. DIMENSIONS ARE IN INCHES.125
. AS REQ'D) 1. 2. 07 Jan.000 Ć .000 Ć .Model FA2100 CVR Installation & Operation Instruction Manual 5. 01/03 165E1846–00 Page A–35 .12 2. MICROPHONE METER 2.00 2. Outline and Dimensions.002 HEADSET 600 OHMS .37 NAMEPLATE AND MODIFICATIONS (WITH CONFIG. 11 6 COCKPIT AREA MICROPHONE 10 FROM ROTOR SPEED SENSOR 3. 6. 10. 7. 21. 07 Jan. 01/03 . 15. 57. 55. 27. 36. 19. 56. 8 OR 5 TO 27. 49. 50. COMPUTER FROM CAPTAIN’S CLOCK SPARE MICROPHONE TO 3RD CREW MEMBER OR PA SYSTEM 13 14 10. 42. 18. 45. 34. 13. 9. 32. 48. 5. 20. 11 TO COPILOT MICROPHONE 10 TO PILOT MICROPHONE 10. 12. 46. 115 VAC HOT OUT 115 VAC HOT IN AC COMMON COLD AUDIO OUT LO AUDIO OUT HI BIAS JUMPER BIAS JUMPER +27. 52.5 Vdc INPUT STOP RECORDING PUSH_TO_TEST PREAMP POWER GND PREAMP POWER +18 Vdc REG INDICATOR + INDICATOR – CHASSIS GROUND CVR FAULT GMT IN B (ARINC 429) LO GMT IN A (ARINC 429) HI 15 LO CHANNEL 1 HI LO CHANNEL 2 HI DATA RATE B LO CHANNEL 3 HI LO CHANNEL 4 HI ROTOR SPEED IN LO ROTOR SPEED IN HI ERASE A ERASE C Figure A–26. 47. 39. 53. 29. 26. 7 BRAKE GEAR 1. 16. 11. 24. 22. 51. 31.Installation & Operation Instruction Manual Model FA2100 CVR STANDARD INTERWIRING PER ARINC SPEC 557 VOICE RECORDER UNIT 1 AMP TO 115 VAC HOT (400HZ) TO AC COLD 2. A152B Control Unit with Internal Microphone Such Installations Do Not Comply with ED–56A 165E1846–00 Page A–36 Rev. 28. 35. 41. 2. 3. 43. 44. 14. 8.5VDC 5 AMPS 3 MODEL A152B CONTROL UNIT PUSH_TO_TEST PRE–AMP POWER GND PRE–AMP POWER +18 VDC INDICATOR + INDICATOR – CHASSIS GROUND ERASE SWITCH “A” ERASE SWITCH “C” OUTPUT – LOW OUTPUT – HIGH MIKE INPUT – HI MIKE INPUT – LO FILTER COMMON FILTER 1. 17. 30. Interwiring Diagram. 54. 33. 23. Voice Recorder Unit. 38. 4. 25. 37. 40.000 HZ 12 AUDIO JACK – LO AUDIO JACK – HI 5V LAMP – HOT LAMP – COMMON/COLD 28V LAMP – HOT INTERNAL MIKE – HIGH INTERNAL MIKE – LOW 6 DB ATTENUATION ATTENUATOR COMMON 12 DB ATTENUATION 24 DB ATTENUATION 4 A B C D E F G H J K L M N P R S T U V W X Y Z a b c d e f g h i j k m n p q r s t 8 3 9 TO ANNUNCIATOR OR MAINT. Short pins S & T for piston aircraft only. and test will indicate NO–GO.05 Vrms – 3 Vrms maximum. the 205E1849–( ) Audio Compressor card provides both 150 (1 sec resolution) and 125 (0. Audio input . 12.5 kbps) ARINC-429 to pins 25 and 26. Shorting pins 1 & 2 is optional. 2. Single ground point. Twisted shielded cable. 07 Jan. the –02 versions can also accept GMT as an FSK signal combined with the audio input signals on either Channel 1 or Channel 3. & 17). 15. Wiring shown for fixed attenuation of 18 dB. no connection is to be made to pin 9. Pin 3 is not a DC return and is not grounded in the recorder. 7. Channel 1 will be Pilot and Channel 3 will be Third Crew Member or PA System. Per FAA Action Notice A8300. no connection is to be made to pins 2 & 3. If the power source has battery back-up. bulk erase will not activate. 3. 24. In all CVR configurations. 6. Recommended minimum wire size is #22. Only one power source is to be wired per aircraft. In addition.Model FA2100 CVR Installation & Operation Instruction Manual Notes for Figure A–26: 1. 8.5 Vdc is supplied. 9. Grounding pin 10 terminates recording within 10 minutes. If 115 Vac. this option is not available. If meter illumination is included in Control Unit. Jumper wires per ARINC 557. All wiring should be MIL–W–22759 or MIL–C–27500. If 27. Wire resistance should not exceed 1 ohm for power leads and should not exceed 5 ohms for signal leads.56 dated Jan. Shields to be grounded at the recorder using short connections. 9. 13. (1Vrms nominal).1 min. 01/03 165E1846–00 Page A–37 . 3. BITE status output: ground = no fault. 1990. supply voltage from lighting bus to proper pins. Jumper in aircraft connector. Ground connection to be within 1 foot of pin 17. 2100–1010–( ) and 2100–1020–( ) configurations GMT is inputted as low speed (12. resolution) for 429 GMT inputs. open = fault or CVR not installed. 5. however. a means for terminating recording after a crash should be included in the aircraft wiring. wire size #24 is electrically permissible except for long-run power leads where #18 wire is recommended (pins 2. In the Model A200S. 14. Rev. the unit will not record or erase previously recorded information. 4. 11. In the Model FA2100. 10. 1/2-inch maximum length. heavy gauge wire. that is. 400 Hz is supplied. Without this jumper. the wiring to Channels 1 and 3 may be transposed. 0. NOTES: 1. DIMENSIONS ARE IN INCHES.947 MAX.1 lbs.24 4. 93–CVR104D Figure A–27. Outline and Dimensions.97 2.00 0. Model A150 External Preamplifier Module Does Not Comply with ED–56A 165E1846–00 Page A–38 Rev.75 .39 SOURIAU 8525-10R-8B-3ASN SOURIAU 8525-10R-14B-19SN 3.Installation & Operation Instruction Manual Model FA2100 CVR 5.53 0.) Black 0.05 Part Number 93A150–20 Housing Color Weight (+ 0. 01/03 . 07 Jan.05 1.24 NAMEPLATE AND MODIFICATIONS 1.38
.12 3.05 2X 0.75 1.78
.54
.04 1.65 lbs. Interwiring Diagram. 42. A55B Remote Microphone Such Installations Do Not Comply with ED–56A Rev. 19. 07 Jan. 37. COMPUTER PREAMPLIFIER J1 MIC SIGNAL INPUT MIC SUPPLY (+6. 11. 5. 01/03 165E1846–00 Page A–39 . 17. A150 External Preamplifier. 15. 7 MODEL A55B MICROPHONE MIC 6 VDC SUPPLY MIC GND (SHIELD) MIC OUTPUT FROM ROTOR SPEED SENSOR 1 2 1. 16. 38. 55. 53. 21. 43. 31. 56. 51. 13. 7. 4. 8 OR 1 AMP TO 27. 48.2 VDC) MIC SHIELD (GND) 9 FROM CAPTAIN’S CLOCK A B C SPARE MICROPHONE TO 3RD CREW MEMBER OR PA SYSTEM 10.Model FA2100 CVR Installation & Operation Instruction Manual STANDARD INTERWIRING PER ARINC SPEC 557 VOICE RECORDER UNIT TO 115 VAC HOT (400HZ) TO AC COLD 2. 32. 40. 9. 41. 26. 47. 46. 22. 24. 33. 11 TO COPILOT MICROPHONE 10 TO PILOT MICROPHONE 10. 45. 6. 18. 29. 44. 23. 34. 25. 2. 49. 115 VAC HOT OUT 115 VAC HOT IN AC COMMON COLD AUDIO OUT LO AUDIO OUT HI BIAS JUMPER BIAS JUMPER +27. 11 COCKPIT AREA MICROPHONE 10 3. 20.5VDC 5 AMPS 5 3 MODEL A150 EXTERNAL PREAMPLIFIER 4 PREAMPLIFIER J2 PRE–AMP POWER (+18 VDC) PRE–AMP POWER GND PRE-AMP OUT – HI PRE-AMP OUT – LO ATTENUATION MASTER CHASSIS GROUND 24 DB ATTENUATION 12 DB ATTENUATION 6 DB ATTENUATION 8 A B C D E F G H J K L M 6 3 TO ANNUNCIATOR OR MAINT. 35. 8. 10. 39. 54. 3. 27. Voice Recorder Unit. 57. 30. 14.5 Vdc INPUT (with inverter) STOP RECORDING PUSH_TO_TEST PREAMP POWER GND PREAMP POWER +18 Vdc REG INDICATOR + INDICATOR – CHASSIS GROUND CVR FAULT GMT IN B (ARINC 429) LO GMT IN A (ARINC 429) HI 12 LO CHANNEL 1 HI LO CHANNEL 2 HI LO CHANNEL 3 HI LO CHANNEL 4 HI ROTOR SPEED IN LO ROTOR SPEED IN HI ERASE A ERASE C 13 Figure A–28. 28. 12. 36. 52. 50. 2. 6. Mating connectors are Cannon TM–PL–30 or TM–PL2–F–39. All wiring should be MIL–W–22759 or MIL–C–27500. If 27. no connection is to be made to pin 9. Recommended cable is MIL–W–16878/21.5 kbps) ARINC-429 to pins 25 and 26. the 205E1849–( ) Audio Compressor card provides both 150 (1 sec resolution) and 125 (0. 3. no connection is to be made to pin 3. In addition.5 Vdc is supplied. A55B Panel-mount microphones are equipped with a Cannon TM–RBI–M–0 Twinax receptacle. In the Model A200S. wire size #24 is electrically permissible except for long-run power leads where #18 wire is recommended (pins 2. Open = fault or CVR not installed. Jumper in aircraft connector. 9. (1Vrms nominal). If the power source has battery back-up. Pin 3 is not a DC return and is not grounded in the recorder. 11. this option is not available. In the Model FA2100. 7. 12. that is. Grounding pin 10 terminates recording within 10 minutes. 3. Channel 1 will be Pilot and Channel 3 will be Third Crew Member or PA System. Wire resistance should not exceed 1 ohm for power leads and should not exceed 5 ohms for signal leads.56 dated Jan. BITE status output: Ground = no fault. & 17). In all CVR configurations. 1990. Ground connection to be within 1 foot of pin 17.1 min. heavy gauge wire. 24. the wiring to Channels 1 and 3 may be transposed. resolution) for 429 GMT inputs. the –02 versions can also accept GMT as an FSK signal combined with the audio input signals on either Channel 1 or Channel 3. Recommended minimum wire size is #22. bulk erase will not activate.Installation & Operation Instruction Manual Model FA2100 CVR Notes for Figure A–28: 1.05 Vrms – 3 Vrms maximum. 8. 400 Hz is supplied. 5. 10. 13. 4. Single ground point. and test will indicate NO-GO. 01/03 . 07 Jan. If 115 Vac. Per FAA Action Notice A8300. Shorting pins 1 & 2 is optional. Wiring shown for fixed attenuation of 18 dB. Audio input . 165E1846–00 Page A–40 Rev. the unit will not record or erase previously recorded information. 9. Only one power source is to be wired per aircraft. Twisted shielded cable. a means for terminating recording after a crash should be included in the aircraft wiring. Without this jumper. however. 2100–1010–( ) and 2100–1020–( ) configurations GMT is inputted as low speed (12. Shields to be grounded at the recorder using short connections. DIMENSIONS ARE IN INCHES.19 . Model A55B SurfaceĆMount Microphone Module.2 lbs.92 15
. Part Number Housing Color Microphone Type Weight 93A055-60 Gray Directional 0. 1 0.700 DC SUPPLY 6V (WHITE) SIGNAL OUTPUT (BLACK) cL SIGNAL GND (SHIELD) SHIELDED WIRE. 93A055-66 Gray Directional 0. & 93A055–67.84 DIA LEVEL ÉÉÉÉÉÉ ÉÉÉÉÉÉ ÉÉÉÉ ÉÉÉ ÉÉÉÉÉÉ ÉÉÉÉ ÉÉÉ ÅÅÅ ÉÉÉÉÉÉ ÉÉÉÉ ÉÉÉ ÅÅÅ ÉÉÉÉÉÉ ÉÉÉÉ ÉÉÉ ÅÅÅ ÉÉÉÉÉÉ . 93A055–66. 2. 01/03 165E1846–00 Page A–41 . Outline and Dimensions. 93–CVR107C 93–CVR113C Figure A-29.25 cL FOAM DAMPER .50 FOR PART NOS.Model FA2100 CVR Installation & Operation Instruction Manual 1.2 lbs.09 1. 93A055–60.12 1 30
1. 93A055-65 Brown. ATR-42 Directional 0. Directional Microphone Does Not Comply with ED-56A Rev. LENGTH 17 INCHES NAMEPLATE 6ć32 THD X .2 lbs.89 FOR PART NO. 22 AWG TWISTED PAIR. CONFIG.2 lbs. P/N .22 DEEP (2 PLACES) NOTES: 0.64 2. 07 Jan. 93A055–65. 93A055-67 Black Directional 0.415 DIA. P/N . ATR-42 MiniĆCondenser 0.700 DC SUPPLY 6V (BLACK) SIGNAL OUTPUT (WHITE) cL SIGNAL GND (SHIELD) SHIELDED WIRE.38 Model FA2100 CVR 1.22 DEEP (2 PLACES) NOTES: 1. Model A55B SurfaceĆMount Microphone Module. DIMENSIONS ARE IN INCHES.2 lbs.84 DIA LEVEL 2.92 15
. 07 Jan. MiniĆCondenser Microphone Does Not Comply with ED-56A 165E1846–00 Page A–42 Rev. Figure A-30.19 CONFIG. 22 AWG TWISTED PAIR. 93A055-45 Brown. 01/03 .64 cL .2 lbs. 93–CVR114C Part Number Housing Color Microphone Type Weight 93A055-40 Gray MiniĆCondenser 0.Installation & Operation Instruction Manual .12 30
1. Outline and Dimensions.09 1.25 ÉÉÉÉÉÉ ÉÉÉÉÉÉ ÉÉÉÉ ÅÅÅ ÉÉÉÉÉÉ ÉÉÉÉ ÅÅÅ ÉÉÉÉÉÉ ÉÉÉÉ ÅÅÅ ÉÉÉÉÉÉ ÉÉÉÉ ÉÉÉÉÉÉ FOAM DAMPER . LENGTH 17 INCHES NAMEPLATE 6ć32 THD X . 25 2. 2. Rear Connector Does Not Comply with ED–56A Rev. Model A55B Panel-Mount Microphone Module. Boeing Condenser 0.02 2.87 NOTES: 1 MATING PLUGS FOR SPECIFIED RECEPTACLE ARE CANNON TM–PL–F–39 OR TM–PL2–F–39.5 lbs.1 lbs. 93A055–30 Brown. 93–CVR117B Part Number Panel Color Microphone Type Weight (+ 0.56 6–32 TAPPED HOLE 4 PLACES 1.625 ÉÉÉÉ ÉÉÉ ÉÉÉÉ ÉÉÉ ÅÅ ÉÉÉÉ ÉÉÉ ÅÅ ÉÉÉÉ 0. 93A055–50 Black Non-Magnetic 0. 07 Jan.) 93A055–10 Black Condenser 0. 01/03 165E1846–00 Page A–43 . 2.00 DIA. Outline and Dimensions.5 lbs Figure A–31. DIMENSIONS ARE IN INCHES. 1.02 2.625 2.5 lbs.20 MAX.Model FA2100 CVR Installation & Operation Instruction Manual COMPANY LOGO CANNON TM–RB1–M–0 TWINAX RECEPTACLE CONFIGURATION/ NAMEPLATE 1 1. 93A055–55 Black Non-Magnetic 0. Model A55B Panel-Mount Microphone Module. Outline and Dimensions.02 6–32 TAPPED HOLE 4 PLACES 2.625 1. NOTES: MATING PLUGS FOR SPECIFIED RECEPTACLE ARE 1 CANNON TM–PL–F–39 OR TM–PL2–F–39.25 1. Figure A–32. 2.56 1.20 MAX.55 lbs.1 lbs.) 93A055–20 Black Condenser 0.625 ÉÉÉÉ ÉÉÉ ÉÉÉÉ ÉÉÉ ÅÅ ÉÉÉÉ ÉÉÉ ÅÅ ÉÉÉÉ 0. 93–CVR115B Part Number Housing Color Mic Element Type Weight (+ 0.00 DIA. DIMENSIONS ARE IN INCHES.02 2. 01/03 .55 lbs. Top Connector Does Not Comply with ED–56A 165E1846–00 Page A–44 Rev.Installation & Operation Instruction Manual Model FA2100 CVR COMPANY LOGO CANNON TM–RB1–M–0 TWINAX RECEPTACLE 1 0. CONFIGURATION/ NAMEPLATE 0. 07 Jan.47 2.25 2. 07 Jan.Model FA2100 CVR Installation & Operation Instruction Manual APPENDIX B ENVIRONMENTAL QUALIFICATION FORMS (EQFs) ED–56A AND RTCA/DO–160C Rev. 01/03 165E1846–00 Page B–1 . Installation & Operation Instruction Manual Model FA2100 CVR THIS PAGE IS INTENTIONALLY LEFT BLANK 165E1846–00 Page B–2 Rev. 07 Jan. 01/03 . 2.2 +55.O.3 +85°C +70°C Altitude 4. 905–E1750–63 Rev.5.0 Equipment tested to Categories A2 & F2.1 –55°C –55°C High Temperature Ground Survival Operating 4.5. 30-Minute Part Number: 2100–1010–00 Manufacturer: L-3 Communications. 2 Low Temperature Ground Survival Operating 4. Rev.2. Sarasota. 3 seconds Vibration 1 8. 01/03 165E1846–00 Page B–3 . Zip Code 34230-3041 TSO Number: C123a Manufacturer’s Specification and/or Other Applicable Specification: Aviation Recorders Document 905–E1436–07. Document No.000 feet Temperature Variation 1 5. Box 3041. Aviation Recorders 6000 Fruitville Road.0 Equipment tested to Category E1.6. RTCA/DO–160C Conditions RTCA/DO–160C Section Description of Conducted Tests Temperature and Altitude 1 4.2 6 g. Waterproofness 10. no test required.1 7. FL 34232 P. 11 milliseconds 12g.0 Equipment tested to Category B.000 feet Overpressure 4.1.1 4. 11 milliseconds 15 g. B) Model: FA2100 CVR Product: Solid State Cockpit Voice Recorder (SSCVR).2 4.6.Model FA2100 CVR Installation & Operation Instruction Manual Environmental Qualification Form (EQF) for the Model FA2100 CVR Part Number 2100–1010–00 (Ref.5.0 Equipment tested without vibration isolators to Category C using Curve C.5.1 +55. Humidity 1 6.000 feet Decompression 4. 07 Jan. 3 Standard 8.0 Equipment identified as Category X.2 Random Explosion Proofness 1 9.0 Equipment tested to Category A (Standard).3. EUROCAE ED–56A.3 –15.3.0 7. Operational Shocks & Crash Safety 1 Operational Shock Crash Safety (Impulse) Crash Safety (Sustained) 7. standard procedure.5.6.2 7. 0 21.3 19.1 19.0 Equipment tested to Category U.0 Equipment tested to Class A. Magnetic Effect 1 15. Lightning Direct Effects 23. Icing 24. Current probe method Lightning Induced Transient Susceptibility 1 22. no test required.3.0 Identified as Category F. 165E1846–00 Page B–4 Rev. Salt Spray 14.4 Equipment tested to Category Z. Tested to Normal and Emergency Conditions. no test required. Composed of nonnutrient materials or materials that are treated in a manner that renders them non-nutrient.5. Voltage Spike 1 17. no test required. Tested to Normal and Emergency Conditions. Tested with AC and DC source power. Emission of Radio Frequency Energy 1 Conducted Radiated 21.0 Normal Operating Conditions (AC) Normal Operating Conditions (DC) 16.0 Equipment identified as Category X.5.3.0 19.4 Equipment tested to Category Z.2 19. Fungus Resistance 13.0 Equipment identified as Category X.0 Equipment identified as Category X.0 Equipment identified as Category X. 07 Jan. no test required.0 Equipment tested to Category A.3b 21. no test required.0 Equipment identified as Category X. Induced Signal Susceptibility 1 Magnetic Fields Magnetic Fields Electric Fields Spikes 19. Tested with AC and DC source power.0 Equipment tested to Category XXZ2.Installation & Operation Instruction Manual Conditions Model FA2100 CVR RTCA/DO–160C Section Description of Conducted Tests Fluids Susceptibility 11.3. 01/03 .0 Equipment tested to Category Z.3. Sand and Dust 12.1 16. Power Input 1 16.2 Equipment tested to Category Z. Equipment Cables Cables Cables Radio Frequency Susceptibility 1 (Conducted and Radiated) 20. Tested with AC and DC source power. Audio Frequency Susceptibility 1 18. Model FA2100 CVR Conditions Crash Survival Notes: Installation & Operation Instruction Manual RTCA/DO–160C Section NA Description of Conducted Tests Crash survival tests were performed in accordance with EUROCAE ED–56A. vibration mount Part Number 9300–343 or equivalent. Remarks: Rev. sections 2. Category A2 is used for decompression and overpressure tests because these tests are not specified by Category F2. RTCA/DO–160C paragraph 9. and Impact Shock. Decompression from Category A2 is performed at the F2 altitude. St. or heavy duty vibration mount Part Number 93–955 or equivalent. Ohio.3/ED–55..0.2. 120 Minute. ECI Division. 165E1846–00 Page B–5 . Sarasota.2a. were conducted at the University of Dayton Research Institute. For helicopter installations and other severe environments. section 7. Impact Shock tests.8 & 5. Sarasota. are recommended. 01/03 All tests except Crash Safety (Sustained). Dayton. 2. 3. Tested for certification of Part Number 2100–1020–00 SSCVR. Explosion Proofness. EUROCAE ED-56A paragraph 5.1.3.3. Overpressure is performed at the Category A2 specified pressure. Inc. Florida. RTCA/DO-160C paragraph 7. EUROCAE ED–56A paragraph 5. Crash Safety (Sustained) tests were conducted at Baker Electronics. Florida. Petersburg.2. Florida. 1.3. were conducted at L-3 Communications. Explosion Proofness tests were conducted at E-Systems. Aviation Recorders. EQF 905–E1751–63.2a. 07 Jan. Installation & Operation Instruction Manual Model FA2100 CVR THIS PAGE IS INTENTIONALLY LEFT BLANK 165E1846–00 Page B–6 Rev. 07 Jan. 01/03 . Rev. Humidity 6.5. 3 seconds Vibration 8. Operational Shocks & Crash Safety Operational Shock Crash Safety (Impulse) Crash Safety (Sustained) 7. 01/03 165E1846–00 Page B–7 . Sarasota.6.1 4. RTCA/DO–160C Conditions RTCA/DO–160C Section Description of Conducted Tests Temperature and Altitude 4.3. Document No.0 Equipment identified as Category X.1 +55. Aviation Recorders 6000 Fruitville Road.0 Equipment tested to Category E1.0 Equipment tested to Category A (Standard).2.000 feet Decompression 4.3 –15. 07 Jan.0 Equipment tested to Category B. Zip Code 34230-3041 TSO Number: C123a Manufacturer’s Specification and/or Other Applicable Specification: Aviation Recorders Document 905–E1436–07.2 7. Fluids Susceptibility 11.1 Low Temperature Ground Survival Operating 4. Standard 8. no test required.5.3. Waterproofness 10. EUROCAE ED–56A.2 6 g.6.1. 905–E1751–63 Rev. Box 3041.000 feet Temperature Variation 5. standard procedure. 11 milliseconds 12 g. 11 milliseconds 15 g.6.O.0 Equipment identified as Category X.Model FA2100 CVR Installation & Operation Instruction Manual Environmental Qualification Form (EQF) for the Model FA2100 CVR Part Number 2100–1020–00 (Ref. no test required.2 4.2 Random Explosion Proofness 9.5.2. 120 Minute Part Number: 2100–1020–00 2100–1020–90 2100–1020–93 Manufacturer: L-3 Communications.5.0 Equipment tested to Categories A2 & F2.2 +55.1 –55°C –55°C High Temperature Ground Survival Operating 4.0 7.1 7.000 feet Overpressure 4.3 +85°C +70°C Altitude 4.5. C) Model: FA2100 CVR Product: Solid State Cockpit Voice Recorder (SSCVR). FL 34232 P.0 Equipment tested without vibration isolators to Category C using Curve C. 0 Identified as Category F. Composed of nonnutrient materials or materials that are treated in a manner that renders them non-nutrient.0 Equipment tested to Category A.2 19. Icing 24. Crash Survival NA Crash survival tests were performed in accordance with EUROCAE ED–56A.0 Equipment identified as Category X. Equipment Cables Cables Cables Radio Frequency Susceptibility (Conducted and Radiated) 20.0 Equipment tested to Category U. no test required. Tested with AC and DC source power.3b 21.2 Equipment tested to Category Z.Installation & Operation Instruction Manual Conditions Model FA2100 CVR RTCA/DO–160C Section Description of Conducted Tests Sand and Dust 12. Lightning Direct Effects 23.3.4 Equipment tested to Category Z. Decompression from Category A2 is performed at the F2 altitude.3. Notes: 165E1846–00 Page B–8 1.0 Normal Operating Conditions (AC) Normal Operating Conditions (DC) 16.0 Equipment tested to Class A. Tested to Normal and Emergency Conditions. Tested with AC and DC source power. Section 7.1.3.0 Equipment tested to Category XXZ2. Tested with AC and DC source power. Current probe method Lightning Induced Transient Susceptibility 22.4 Equipment tested to Category Z.1 19.3. Emission of Radio Frequency Energy Conducted Radiated 21. 01/03 . 07 Jan. Category A2 is used for decompression and overpressure tests because these tests are not specified by Category F2. Power Input 16.5. Audio Frequency Susceptibility 18.0 19. no test required.0 21. Salt Spray 14.0 Equipment identified as Category X. sections 2.0 Equipment tested to Category Z.8 & 5. Fungus Resistance 13.3 19. Induced Signal Susceptibility Magnetic Fields Magnetic Fields Electric Fields Spikes 19. Tested to Normal and Emergency Conditions. Rev. no test required.1 16. Magnetic Effect 15.0 Equipment identified as Category X. Overpressure is performed at the Category A2 specified pressure. Voltage Spike 17.3/ED–55. no test required.0 Equipment identified as Category X.5. 11 milliseconds 12 g. Humidity 6. 01/03 165E1846–00 Page B–9 . 905–E1795–63 Rev.5. Explosion Proofness 9.5.3.5. Waterproofness 10. FL 34232 P.1 –55°C –15°C High Temperature Ground Survival Operating 4. Sarasota. Box 3041.6.2 +50. (Altitude & Decompression tested to Category D2.0 7.2 4. RTCA/DO–160C Conditions RTCA/DO–160C Section Description of Conducted Tests Temperature and Altitude 4.0 Equipment tested to Category C.1 7.2 6 g.2.) Low Temperature Ground Survival Operating 4.2 7.3 +85°C +70°C Altitude 4.2.0 Equipment identified as Category X. Fluids Susceptibility 11.0 Equipment identified as Category X.000 feet Temperature Variation 5.3 –15.1 +50.000 feet Overpressure 4.5.0 Equipment tested to Category A2.0 Equipment tested to Category A (Standard). Zip Code 34230-3041 TSO Number: C123a Manufacturer’s Specification and/or Other Applicable Specification: EUROCAE ED–56A. 07 Jan.Model FA2100 CVR Installation & Operation Instruction Manual Environmental Qualification Form (EQF) for the Model S055 Microphones (Ref.0 Equipment tested to Category E1.1. Rev.O.3.6. no test required. B) Model: S055 Product: Microphone Part Number: S055–0030–00 S055–0065–00 S055–0066–00 S055–0067–00 S055–0067–01 S055–0068–00 Manufacturer: L-3 Communications.6. Aviation Recorders 6000 Fruitville Road.1 4. no test required. no test required.0 Equipment identified as Category X. 11 milliseconds 15 g. 3 seconds Vibration 8. Document No. Operational Shocks & Crash Safety Operational Shock Crash Safety (Impulse) Crash Safety (Sustained) 7.000 feet Decompression 4. 3b 21. no test required. no test required. Fungus Resistance 13.3.0 Equipment tested to Category T.1 19. Audio Frequency Susceptibility 18.Installation & Operation Instruction Manual Conditions Model FA2100 CVR RTCA/DO–160C Section Description of Conducted Tests Sand and Dust 12.3.0 Equipment tested to Category XXXX. Equipment Cables Cables Cables Radio Frequency Susceptibility (Conducted and Radiated) 20. Voltage Spike 17.0 Equipment identified as Category X. Emission of Radio Frequency Energy Conducted Radiated 21. Induced Signal Susceptibility Magnetic Fields Magnetic Fields Electric Fields Spikes 19.3 19.0 Equipment identified as Category X. Salt Spray 14.2 19.3.0 Equipment tested to Category Z.3.0 Equipment identified as Category X. no test required. 07 Jan. no test required. no test required.0 Equipment identified as Category X. no test required. 01/03 . no test required.0 Equipment identified as Category X. Current probe method Lightning Induced Transient Susceptibility 22. Power Input 16.4 Equipment tested to Category Z. Magnetic Effect 15. no test required.0 Equipment identified as Category X.4 Equipment tested to Category Z. Lightning Direct Effects 23.0 Equipment identified as Category X.0 19.0 Identified as Category F.0 21. Composed of nonnutrient materials or materials that are treated in a manner that renders them non-nutrient. 165E1846–00 Page B–10 Rev. Icing 24. 0 Equipment identified as Category X. FL 34232 P.5.6.1 7. 3 seconds Vibration 8.000 feet Overpressure 4.000 feet.0 Equipment tested to Category C. standard random.2 7.000 feet Decompression 4.1 +15. Operational Shocks & Crash Safety Operational Shock Crash Safety (Impulse) Crash Safety (Sustained) 7.3 +85°C +70°C +70°C Altitude 4.6. Aviation Recorders 6000 Fruitville Road. no test required.0 Equipment tested to Category A (Standard). (Decompression tested to 55.2. 07 Jan.3.2 4. Humidity 6.1 –55°C –15°C High Temperature Ground Survival Short Time Operating 4.0 7.2 6 g.5.3 –15. 905–E1869–63 Rev.5.2 +55.Model FA2100 CVR Installation & Operation Instruction Manual Environmental Qualification Form (EQF) for the Model S056 Microphones (Ref. C) Model: S056 Product: Remote Microphone Part Number: S056–0047–00 S056–0048–00 S056–0049–00 S056–0050–00 S056–1048–00 Manufacturer: L-3 Communications. Curve B.0 Equipment tested to Category B. 11 milliseconds 12 g. Document No.O.0 Equipment identified as Category X.6.1 4. Sarasota.5.1. Zip Code 34230-3041 TSO Number: C123a Manufacturer’s Specification and/or Other Applicable Specification: EUROCAE ED–56A.) Low Temperature Ground Survival Operating 4. Fluids Susceptibility 11. Waterproofness 10.000 feet Temperature Variation 5.2 4.3. RTCA/DO–160C Conditions RTCA/DO–160C Section Description of Conducted Tests Temperature and Altitude 4. Explosion Proofness 9.0 Equipment tested to Category E1.5. Rev. 01/03 165E1846–00 Page B–11 . 11 milliseconds 15 g. Box 3041.2. no test required.0 Equipment tested to Category A2. 0 Equipment identified as Category X. Fungus Resistance 13.0 Category X Equipment tested to 3ma (2V/m) and 2V/m per ED–56A. Power Input 16. Icing 24. no test required.Installation & Operation Instruction Manual Conditions Model FA2100 CVR RTCA/DO–160C Section Description of Conducted Tests Sand and Dust 12. Magnetic Effect 15. The Explosion Proofness tests.0 Equipment identified as Category X. no test required.0 Equipment identified as Category X.3. RTCA/DO-160C paragraph 9. Sevierville.0 Equipment identified as Category X.4 Equipment tested to Category Z. no test required. Sarasota.0. Inc. Audio Frequency Susceptibility 18. Florida. Salt Spray 14. Equipment Cables Cables Cables Radio Frequency Susceptibility (Conducted and Radiated) 20. RTCA/DO-160C paragraph 5. no test required. Exception 2.0. Voltage Spike 17.4 Equipment tested to Category Z. Lightning Direct Effects 23.0 21. were conducted at Raytheon E-Systems. no test required.3. no test required.0.0 Equipment identified as Category X. Petersburg.0 Equipment identified as Category X. no test required. Aviation Recorders. TN: Temperature and Altitude.2 19.3 19.0 19.0 Equipment identified as Category X. RTCA/DO–160C paragraph 6. 165E1846–00 Page B–12 Rev.0 Identified as Category F. St. Remarks: The following tests were conducted at Electro-Voice.. Temperature Variation. 07 Jan. Emission of Radio Frequency Energy Conducted Radiated 21. and Humidity. Composed of nonnutrient materials or materials that are treated in a manner that renders them non-nutrient.0 Equipment tested to Category XXC2. All other tests were conducted at L-3 Communications.3.0 Equipment tested to Category Z.3b 21. FL.0.3. 01/03 .1 19. paragraph 420. RTCA/DO-160C paragraph 4. Induced Signal Susceptibility Magnetic Fields Magnetic Fields Electric Fields Spikes 19. Current probe method Lightning Induced Transient Susceptibility 22. 5.1. 07 Jan.6. Aviation Recorders 6000 Fruitville Road.000 feet Decompression 4. Humidity 6.0 7. 11 milliseconds 12 g.6.0 Equipment tested to Category E1.2.O.Model FA2100 CVR Installation & Operation Instruction Manual Environmental Qualification Form (EQF) for the Model S150 Preamplifier (Ref. Waterproofness 10.1 7.0 Equipment tested to Category B.0 Equipment tested to Category A (Standard). FL 34232 P. Operational Shocks & Crash Safety Operational Shock Crash Safety (Impulse) Crash Safety (Sustained) 7.3. Document No.3 +85°C +70°C Altitude 4.6. Sarasota. Rev. 01/03 165E1846–00 Page B–13 . Robust 8. no test required.2 7.3.3 –15.000 feet Overpressure 4. robust procedure.0 Equipment tested to category C’ using Curves C and C’.2.5. Zip Code 34230-3041 TSO Number: C123a Manufacturer’s Specification and/or Other Applicable Specification: Aviation Recorders Document 905–E0986–07.5.000 feet Temperature Variation 5.1 –55°C –55°C High Temperature Ground Survival Operating 4.5. 11 milliseconds 15 g.1 4.6.2 Random Explosion Proofness 9. 3 seconds Vibration 8.0 Equipment identified as Category X.1 +55. 905–E1802–63 Rev. 1 Low Temperature Ground Survival Operating 4.2 4.2 +55.0 Equipment tested to Categories A2 & F2. A) Model: S150 Product: Preamplifier Part Number: S150–0020–00 Manufacturer: L-3 Communications. EUROCAE ED–56A.0 Equipment identified as Category X. RTCA/DO–160C Conditions RTCA/DO–160C Section Description of Conducted Tests Temperature and Altitude 4. no test required. Fluids Susceptibility 11. Box 3041.2 6 g. and Explosion Proofness.3. Rev.2 19. Explosion Proofness tests were conducted at E-Systems.1 19.Installation & Operation Instruction Manual Conditions Model FA2100 CVR RTCA/DO–160C Section Description of Conducted Tests Sand and Dust 12.3.2. Notes: 2 1. Composed of nonnutrient materials or materials that are treated in a manner that renders them non-nutrient. Audio Frequency Susceptibility 18. Magnetic Effect 15. were conducted at L-3 Communications. Florida. Category A2 is used for the decompression and overpressure tests because these tests are not specified by Category F2. Icing 24. St. Salt Spray 14.0 Equipment tested to Category Z. Sarasota. Power Input 16.0. Current probe method Lightning Induced Transient Susceptibility 22.0 Equipment tested to Category T. Induced Signal Susceptibility Magnetic Fields Magnetic Fields Electric Fields Spikes 19.4 Equipment tested to Category Z. Petersburg. A double-shielded microphone cable is required to achieve this category. ECI Division. Tested with DC and AC power.0 Equipment identified as Category X.2. Lightning Direct Effects 23.0 Equipment tested to Category Z. Sarasota.0 Equipment tested to Category A.0 19.3 19. no test required. Tested with DC and AC power. Voltage Spike 17. Aviation Recorders. Overpressure is performed at the Category A2 specified pressure.3b 21.0 Equipment tested to Category XXZ2.3.3. Remarks: 165E1846–00 Page B–14 All tests except Crash Safety (Sustained).0 Equipment identified as Category X. 2 Equipment Cables Cables Cables Radio Frequency Susceptibility (Conducted and Radiated) 20. Decompression from Category A2 is performed at the F2 altitude. no test required.0 Equipment identified as Category X. Emission of Radio Frequency Energy Conducted Radiated 21.4 Equipment tested to Category Z. RTCA/DO–160C paragraph 9. 07 Jan. no test required. RTCA/DO-160C paragraph 7. Florida.0 Equipment identified as Category X. Florida. Fungus Resistance 13. 01/03 .3. no test required.0 Identified as Category F.0 Equipment identified as Category X. 2. Crash Safety (Sustained) tests were conducted at Baker Electronics. no test required.0 21. 2. Fluids Susceptibility 11. 01/03 165E1846–00 Page B–15 .1 4. 3 seconds Vibration 8.5.6. Rev.3.0 Equipment tested to Category F2.2 7.6. Waterproofness 10. RTCA/DO–160C Conditions RTCA/DO–160C Section Description of Conducted Tests Temperature and Altitude 4. no test required.0 Equipment tested to Category A (Standard).1 7.6.0 7.0 Equipment tested without vibration isolators to category C using Curves C.1.000 feet Temperature Variation 5.0 Equipment tested to Category B. Low Temperature Ground Survival Operating 4.3 –15.3.2 4. 07 Jan. Zip Code 34230-3041 TSO Number: C123a Manufacturer’s Specification and/or Other Applicable Specification: Aviation Recorders Document 905–E0984–07. EUROCAE ED–56A.Model FA2100 CVR Installation & Operation Instruction Manual Environmental Qualification Form (EQF) for the Model S160 Preamplifier (Ref. 11 milliseconds 15 g.5.3 +85°C +70°C Altitude 4.1 +55. Box 3041.000 feet Overpressure 4. 905–E2689–63 Rev. FL 34232 P.2 6 g. Document No. no test required. Operational Shocks & Crash Safety Operational Shock Crash Safety (Impulse) Crash Safety (Sustained) 7. Explosion Proofness 9.0 Equipment tested to Category E1.2.1 –55°C –55°C High Temperature Ground Survival Operating 4. 11 milliseconds 12 g. Humidity 6. Aviation Recorders 6000 Fruitville Road. –) Model: S160 Product: Control Unit with Preamplifier only.5. Part Number: S160–0020–00 Manufacturer: L-3 Communications.O.0 Equipment identified as Category X. Sarasota. standard procedure.5.000 feet Decompression 4.0 Equipment identified as Category X.2 +55. 0 Equipment identified as Category X.0 Equipment tested to Category XXZ2. Audio Frequency Susceptibility 18. Magnetic Effect 15.3. no test required. 07 Jan.0 19. Icing 24.3. Lightning Direct Effects 23.0 Equipment identified as Category X.Installation & Operation Instruction Manual Conditions Model FA2100 CVR RTCA/DO–160C Section Description of Conducted Tests Sand and Dust 12.0 Identified as Category F. no test required.0 Equipment identified as Category X.0 Equipment tested to Category T. Composed of nonnutrient materials or materials that are treated in a manner that renders them non-nutrient.3 19. no test required.4 Equipment tested to Category Z.3. Equipment Cables Cables Cables Radio Frequency Susceptibility (Conducted and Radiated) 20.0 Equipment tested to Category Z.3b 21. Salt Spray 14.2 19. 165E1846–00 Page B–16 Rev.0 Equipment identified as Category X. no test required. no test required. Induced Signal Susceptibility Magnetic Fields Magnetic Fields Electric Fields Spikes 19. no test required. Voltage Spike 17. Power Input 16. Fungus Resistance 13. Current probe method Lightning Induced Transient Susceptibility 22.4 Equipment tested to Category Z.0 Equipment identified as Category X. no test required. Emission of Radio Frequency Energy Conducted Radiated 21.0 21.0 Equipment identified as Category X.3. 01/03 .1 19.0 Equipment identified as Category X. 5.2 +55. 01/03 165E1846–00 Page B–17 . 905–E1803–63 Rev.6.3 +85°C +70°C Altitude 4.2 4. RTCA/DO–160C Conditions RTCA/DO–160C Section Description of Conducted Tests Temperature and Altitude 4.2.Model FA2100 CVR Installation & Operation Instruction Manual Environmental Qualification Form (EQF) for the Model S151 Control Unit (Ref.) Low Temperature Ground Survival Operating 4.0) Humidity 6. Operational Shocks & Crash Safety Operational Shock Crash Safety (Impulse) Crash Safety (Sustained) 7. Zip Code 34230-3041 TSO Number: C123a Manufacturer’s Specification and/or Other Applicable Specification: Aviation Recorders Document 905–E0984–07.0 Equipment tested to Category B. 11 milliseconds 15 g. EUROCAE ED–56A.1.0 7.2 6 g.6.5.1 +55.0 Equipment tested to Category C’ using Curves C and C’. 1 (Temperature Tests combined with Temperature Vibration Test. Section 5. Section 4.2. Robust 8.0 Equipment tested to Category A (Standard).0.5.000 feet Overpressure 4. (This test combined with Temperature Test. There were no changes in the performance or vibration resonances. Aviation Recorders 6000 Fruitville Road.1 4.O.2 Random Explosion Proofness 9. FL 34232 P.1 7. 3 seconds Vibration 8.1 –55°C –55°C High Temperature Ground Survival Operating 4. Rev. Document No.3. 07 Jan. 11 milliseconds 12 g .6.6.0 Equipment tested to Categories A2 & F2.2 7.000 feet Decompression 4. Sarasota.3 –15.5.0 Equipment tested to Category E1.3.000 feet Temperature Variation 5. Box 3041. robust procedure. A) Model: S151 Product: Control Unit Part Number: S151–0020–00 S151–0030–00 S151–0040–00 S151–0050–00 S151–0060–00 Manufacturer: L-3 Communications. Tested with DC and AC source power.0 Equipment identified as Category X. Lightning Direct Effects 23.Installation & Operation Instruction Manual Conditions Model FA2100 CVR RTCA/DO–160C Section Description of Conducted Tests Waterproofness 10. Fungus Resistance 13. no test required. Salt Spray 14. Sand and Dust 12. no test required.0 Equipment identified as Category X.3.0 Equipment tested to Category XXZ2.0 Identified as Category F.0 Equipment tested to Category A. no test required. 2 Equipment Cables Cables Cables Radio Frequency Susceptibility (Conducted and Radiated) 20.0 Equipment identified as Category X. Emission of Radio Frequency Energy Conducted Radiated 21. Power Input 16. no test required.0 Equipment identified as Category X.3 19.2 19.0 Equipment tested to Category Z.3.0 Equipment identified as Category X.3.0 Equipment tested to Category Z. 07 Jan.0 19.3. 01/03 .4 Equipment tested to Category Z. Voltage Spike 17. Fluids Susceptibility 11.4 Equipment tested to Category Z. Current probe method Lightning Induced Transient Susceptibility 22. Composed of nonnutrient materials or materials that are treated in a manner that renders them non-nutrient.1 19. 165E1846–00 Page B–18 2 Rev.3b 21. Audio Frequency Susceptibility 18. Magnetic Effect 15. no test required. Induced Signal Susceptibility Magnetic Fields Magnetic Fields Electric Fields Spikes 19. Tested with DC and AC source power.0 Equipment tested to Category T.0 21.0 Equipment identified as Category X. no test required. Overpressure is performed at the Category A2 specified pressure. A double-shielded microphone cable is required to achieve this category.3. Florida. Aviation Recorders. 165E1846–00 Page B–19 .0 Description of Conducted Tests Equipment identified as Category X.2. 07 Jan. no test required.0. St.Model FA2100 CVR Conditions Icing Notes: Installation & Operation Instruction Manual RTCA/DO–160C Section 24. Explosion Proofness tests were conducted at E-Systems. 01/03 All tests except Crash Safety (Sustained). ECI Division. 1. Florida. and Explosion Proofness. Crash Safety (Sustained) tests were conducted at Baker Electronics. were conducted at L-3 Communications. Petersburg. RTCA/DO-160C paragraph 7. Florida. Decompression from Category A2 is performed at the F2 altitude. Sarasota.2. Category A2 is used for the decompression and overpressure tests because these tests are not specified by Category F2. RTCA/DO–160C paragraph 9. Remarks: Rev. 2. Sarasota. Installation & Operation Instruction Manual Model FA2100 CVR THIS PAGE IS INTENTIONALLY LEFT BLANK. 165E1846–00 Page B–20 Rev. 01/03 . 07 Jan. 3. standard procedure.000 feet Decompression 4.000 feet Temperature Variation 5.Model FA2100 CVR Installation & Operation Instruction Manual Environmental Qualification Form (EQF) for the Model S152 Control Unit (Ref.0 Equipment identified as Category X. Operational Shocks & Crash Safety Operational Shock Crash Safety (Impulse) Crash Safety (Sustained) 7. EUROCAE ED–56A. Explosion Proofness 9. Temperature Tests combined with Temperature Variation Test.0 Equipment tested to Categories A2. Document No.2 4.2 +55.6.0 Equipment tested to Category E1.0 Equipment tested to Category B’ using Curve B. Rev. (This test combined with Temperature Test. 11 milliseconds 12 g.5.6.000 feet Overpressure 4.) Low Temperature Ground Survival Operating 4.2 7. no test required.0. Aviation Recorders 6000 Fruitville Road.2 6 g.6. Section 5.5. Zip Code 34230-3041 TSO Number: C123a Conditions Manufacturer’s Specification and/or Other Applicable Specification: Aviation Recorders Document 905–E0984–07.0 Equipment tested to Category A (Standard). 3 seconds Vibration 8.1 4.0 Equipment tested to Category C. (Altitude and Decompression tested to Category D2. 905–E1804–63 Rev. 07 Jan.1 7. Waterproofness 10.3 –15. Sarasota.5. 01/03 165E1846–00 Page B–21 . RTCA/DO–160C RTCA/DO–160C Section Description of Conducted Tests Temperature and Altitude 4.0) Humidity 6.O.0 7. FL 34232 P. 11 milliseconds 15 g.3 +85°C +70°C Altitude 4.2. There were no changes in the performance or vibration resonances.2. Section 4.1.3.5. Box 3041.1 –55°C –15°C High Temperature Ground Survival Operating 4. D) Model: S152/S162 Product: Control Unit Part Number: S152–0020–00 S152–0030–00 S152–0030–01 S152–0040–00 Manufacturer: L-3 Communications.1 +15. Emission of Radio Frequency Energy Conducted Radiated 21. Current probe method Lightning Induced Transient Susceptibility 22. and Explosion Proofness. no test required.2.0 Equipment tested to 2 V/m. Explosion Proofness tests were conducted at E-Systems. Sand and Dust 12. Magnetic Effect 15.0 19.0 Equipment identified as Category X. Lightning Direct Effects 23.3. no test required. Rev. Sarasota. 01/03 .3. no test required.0.3b 21.3.0 Equipment identified as Category X.0 Equipment identified as Category X.0 Equipment identified as Category X. no test required. Fungus Resistance 13. Petersburg.2. RTCA/DO–160C paragraph 9. Florida. Florida.0 Equipment tested to Category Z. Salt Spray 14.4 Equipment tested to Category Z.3.2 19.4 Equipment tested to Category Z.0 Equipment identified as Category X.1 19. Audio Frequency Susceptibility 18. were conducted at L-3 Communications. Power Input 16. Icing 24.0 Equipment identified as Category X.0 Equipment identified as Category X.0 Equipment tested to Category XXZ2. Sarasota. no test required. no test required. Composed of nonnutrient materials or materials that are treated in a manner that renders them non-nutrient. Induced Signal Susceptibility Magnetic Fields Magnetic Fields Electric Fields Spikes 19.Installation & Operation Instruction Manual Conditions Model FA2100 CVR RTCA/DO–160C Section Description of Conducted Tests Fluids Susceptibility 11.3 19. no test required. Aviation Recorders. RTCA/DO-160C paragraph 7.3. no test required. St. 07 Jan. Florida. ÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁÁ Remarks: 165E1846–00 Page B–22 All tests except Crash Safety (Sustained). Crash Safety (Sustained) tests were conducted at Baker Electronics. ECI Division.0 Equipment identified as Category X. Equipment Cables Cables Cables Radio Frequency Susceptibility (Conducted and Radiated) 20. Voltage Spike 17.0 Identified as Category F.0 21. 5. 01/03 165E1846–00 Page B–23 . 905–E2396–63 Rev.000 feet Overpressure 4.1.6.0 Equipment tested to Category E1.2 6 g.0 Equipment tested to Category B.5.1 –55°C –55°C High Temperature Ground Survival Operating 4.1 4. Sarasota.1 7.2. Waterproofness 10. Humidity 6.3 –15.2 +55.000 feet Decompression 4. Operational Shocks & Crash Safety Operational Shock Crash Safety (Impulse) Crash Safety (Sustained) 7.3.O.5.5. 3 seconds Vibration 8. 11 milliseconds 12 g . standard procedure. EUROCAE ED–56A.1 +55. FL 34232 P. 11 milliseconds 15 g. Zip Code 34230-3041 TSO Number: C123a Manufacturer’s Specification and/or Other Applicable Specification: Aviation Recorders Document 905–E0984–07.0 Equipment tested to Category A (Standard). Box 3041.0 Equipment identified as Category X. Rev. Aviation Recorders 6000 Fruitville Road.0 7. 07 Jan.3 +85°C +70°C Altitude 4.6. –) Model: S161 Product: Control Unit Part Number: S161–0020–00 S161–0030–00 S161–0040–00 S161–0050–00 S161–0060–00 Manufacturer: L-3 Communications. Document No.2.3.Model FA2100 CVR Installation & Operation Instruction Manual Environmental Qualification Form (EQF) for the Model S161 Control Unit (Ref. 1 ) Low Temperature Ground Survival Operating 4.2 7.0 Equipment tested without vibration isolators to to Category C’ using Curve C.0 Equipment tested to Categories A2 & F2. Explosion Proofness 9. RTCA/DO–160C Conditions RTCA/DO–160C Section Description of Conducted Tests Temperature and Altitude 4. no test required.000 feet Temperature Variation 5.6.2 4. Power Input 16. Composed of nonnutrient materials or materials that are treated in a manner that renders them non-nutrient.0 Equipment identified as Category X.0 Equipment identified as Category X.0 Equipment tested to Category T.0 Identified as Category F. Lightning Direct Effects 23. Induced Signal Susceptibility Magnetic Fields Magnetic Fields Electric Fields Spikes 19. Salt Spray 14. Fungus Resistance 13. no test required. Magnetic Effect 15.0 Equipment identified as Category X. no test required.0 Equipment tested to Category XXZ2. 07 Jan.0 Equipment identified as Category X. no test required. Equipment Cables Cables Cables Radio Frequency Susceptibility (Conducted and Radiated) 20.3. 01/03 . Voltage Spike 17.0 Equipment identified as Category X. while Category A2 does.3b 21. L3AR has elected to perform Category A2 decompression at Category F2 altitude parameters and Category A2 overpressure.4 Equipment tested to Category Z. no test required.0 Equipment identified as Category X.3.3 19.0 Equipment identified as Category X.2 19. Sand and Dust 12. Rev. no test required. no test required. Current probe method Lightning Induced Transient Susceptibility 22.0 Equipment tested to Category Z.3.Installation & Operation Instruction Manual Conditions Model FA2100 CVR RTCA/DO–160C Section Description of Conducted Tests Fluids Susceptibility 11. Icing 24. Emission of Radio Frequency Energy Conducted Radiated 21.4 Equipment tested to Category Z.0 19. Notes: 165E1846–00 Page B–24 1. Audio Frequency Susceptibility 18.0 Equipment identified as Category X.1 19.0 21. no test required. Category F2 does not contation decompression and overpressure requirements.3. no test required. 2.5. Waterproofness 10. standard procedure. 11 milliseconds 12 g.2 7. no test required.3 +85°C +70°C Altitude 4. Low Temperature Ground Survival Operating 4. no test required. Box 3041.1 7. FL 34232 P. Humidity 6.000 feet Temperature Variation 5.2 6 g. Operational Shocks & Crash Safety Operational Shock Crash Safety (Impulse) Crash Safety (Sustained) 7. Sarasota.0 Equipment tested to Category C. RTCA/DO–160C Conditions RTCA/DO–160C Section Description of Conducted Tests Temperature and Altitude 4.0 Equipment identified as Category X.000 feet Overpressure 4. 905–E2388–63 Rev.0 Equipment tested without vibration isolators to to Category B’ using Curve B.6. Zip Code 34230-3041 TSO Number: C123a Manufacturer’s Specification and/or Other Applicable Specification: Aviation Recorders Document 905–E0984–07.0 Equipment tested to Category A (Standard).000 feet).5.5.0 7.1 –55°C –15°C High Temperature Ground Survival Operating 4. Aviation Recorders 6000 Fruitville Road.5.Model FA2100 CVR Installation & Operation Instruction Manual Environmental Qualification Form (EQF) for the Model S162 Control Unit (Ref.2 +55.3.3.000 feet Decompression 4. 11 milliseconds 15 g. Fluids Susceptibility 11.6.2.0 Equipment identified as Category X. 07 Jan. Rev. 3 seconds Vibration 8.3 –15. 01/03 165E1846–00 Page B–25 .O. EUROCAE ED–56A. Document No.6. –) Model: S162 Product: Control Unit Part Number: S162–0020–00 S162–0030–00 S162–0040–00 Manufacturer: L-3 Communications.1.0 Equipment tested to Categories A2 (except decompression @ 55.0 Equipment tested to Category E1.1 +15.2 4.1 4. Explosion Proofness 9. Fungus Resistance 13.3 19.0 Equipment tested to Category XXZ2. Composed of nonnutrient materials or materials that are treated in a manner that renders them non-nutrient.0 Equipment identified as Category X.0 Equipment identified as Category X.0 Equipment identified as Category X. no test required.0 Equipment identified as Category X. Equipment Cables Cables Cables Radio Frequency Susceptibility (Conducted and Radiated) 20. 07 Jan. no test required.0 Equipment identified as Category X.3. no test required. 165E1846–00 Page B–26 Rev.0 Identified as Category F.0 Equipment tested to 2 v/m. Emission of Radio Frequency Energy Conducted Radiated 21.0 Equipment tested to Category Z.3b 21. Lightning Direct Effects 23. no test required.0 Equipment identified as Category X. Magnetic Effect 15.0 Equipment identified as Category X. Induced Signal Susceptibility Magnetic Fields Magnetic Fields Electric Fields Spikes 19. Current probe method Lightning Induced Transient Susceptibility 22.2 19. Salt Spray 14.3. Power Input 16.4 Equipment tested to Category Z.3. Voltage Spike 17. 01/03 .4 Equipment tested to Category Z. no test required.1 19. Icing 24. no test required.0 19.Installation & Operation Instruction Manual Conditions Model FA2100 CVR RTCA/DO–160C Section Description of Conducted Tests Sand and Dust 12.3. Audio Frequency Susceptibility 18. no test required.0 21. 1.5. There were no changes in the performance or vibration resonances. Aviation Recorders 6000 Fruitville Road. Waterproofness 10.0 Equipment tested to Category C’ using Curve C.2. 1 Low Temperature Ground Survival Operating 4. Box 3041.000 feet Decompression 4.6.5. standard procedure. Operational Shocks & Crash Safety Operational Shock Crash Safety (Impulse) Crash Safety (Sustained) 7.3.1 +55. 11 milliseconds 12 g. Humidity 6.0 Equipment tested to Category A (Standard).1 7. 11 milliseconds 15 g. Robust 8.6. FL 34232 P.3 –15. Sarasota. 07 Jan. 3 seconds Vibration 8. Document No. C) Model: S251 Product: Control Unit Part Number: S251–1120–00 S251–1130–00 S251–1170–00 Manufacturer: L-3 Communications.0 Equipment tested to Category E1. 01/03 165E1846–00 Page B–27 . Rev.0 7.3 +85°C +70°C Altitude 4.000 feet Overpressure 4.Model FA2100 CVR Installation & Operation Instruction Manual Environmental Qualification Form (EQF) for the Model S251 Control Unit (Ref.O.2 +55. Zip Code 34230-3041 TSO Number: C123a Manufacturer’s Specification and/or Other Applicable Specification: Aviation Recorders Document 905–E0984–07.000 feet Temperature Variation 5.2 7.6.2 6 g. EUROCAE ED–56A.0 Equipment tested to Categories A2 & F2.5.1 4. no test required.0 Equipment tested to Category B.2.2 Standard Explosion Proofness 9. RTCA/DO–160C Conditions RTCA/DO–160C Section Description of Conducted Tests Temperature and Altitude 4.6.2 4.1 –55°C –55°C High Temperature Ground Survival Operating 4.5.0 Equipment identified as Category X. 905–E1805–63 Rev.3. Voltage Spike 17. Overpressure is performed at the Category A2 specified pressure. Category A2 is used for the decompression and overpressure tests because these tests are not specified by Category F2. Notes: 1. 01/03 . Tested with DC and AC power.0 Equipment tested to Category XXZ2. no test required.3.1 19.0 Equipment identified as Category X. Magnetic Effect 15.0 Equipment tested to Category Z. Lightning Direct Effects 23. Tested with DC and AC power.0 Equipment identified as Category X.3. Sand and Dust 12. 165E1846–00 Page B–28 Rev.3b 21. 07 Jan.0 Equipment identified as Category X. A double-shielded cable is required to achieve this category.2 19.0 Equipment tested to Category T.0 Equipment identified as Category X. no test required.4 Equipment tested to Category Z.Installation & Operation Instruction Manual Conditions Model FA2100 CVR RTCA/DO–160C Section Description of Conducted Tests Fluids Susceptibility 11. Power Input 16.0 Equipment tested to Category A. no test required. Induced Signal Susceptibility Magnetic Fields Magnetic Fields Electric Fields Spikes 19.3. Fungus Resistance 13. 2.3 19. no test required. no test required.3.4 Equipment tested to Category Z. Salt Spray 14. Audio Frequency Susceptibility 18. Current probe method Lightning Induced Transient Susceptibility 22. Decompression from Category A2 is performed at the F2 altitude. Icing 24.0 Equipment tested to Category Z.0 Identified as Category F. Composed of nonnutrient materials or materials that are treated in a manner that renders them non-nutrient.0 Equipment identified as Category X.0 Equipment identified as Category X. 2 Radio Frequency Emissions Conducted Radiated 21.0 19. no test required.0 21. 2 Equipment Cables Cables Cables Radio Frequency Susceptibility (Conducted and Radiated) 20. 905–E2731–63 Rev.0 Equipment tested to Category E1.3 +85°C +70°C Altitude 4.0 Equipment identified as Category X.000 feet Overpressure 4. Sarasota.000 feet Temperature Variation 5. 3 seconds Vibration 8.3 –15.0 Equipment tested to Category A. Explosion Proofness 9.2 4.5. RTCA/DO–160C Conditions RTCA/DO–160C Section Description of Conducted Tests Temperature and Altitude 4.3. 11 milliseconds 12 g . Humidity 6. Document No.5.2 6 g.6.3. Aviation Recorders 6000 Fruitville Road.2 7.5.1 +55. –) Model: S261 Product: Control Unit Part Number: S261–1120–00 Manufacturer: L-3 Communications.1. 01/03 165E1846–00 Page B–29 .6. Waterproofness 10.1 –55°C –55°C High Temperature Ground Survival Operating 4. Fluids Susceptibility 11.2 +55. Rev.2.1 4.O. 11 milliseconds 15 g. FL 34232 P.1 7.0 Equipment tested to Category A (Standard).0 Equipment tested to Categories F2 Low Temperature Ground Survival Operating 4. Operational Shocks & Crash Safety Operational Shock Crash Safety (Impulse) Crash Safety (Sustained) 7. Zip Code 34230-3041 TSO Number: C123a Manufacturer’s Specification and/or Other Applicable Specification: Aviation Recorders Document 905–E0984–07.0 7.6.Model FA2100 CVR Installation & Operation Instruction Manual Environmental Qualification Form (EQF) for the Model S261 Control Unit (Ref. no test required. standard procedure. EUROCAE ED–56A.5.0 Equipment tested without vibration isolators to to Category C using Curve C. Box 3041. 07 Jan.000 feet Decompression 4. no test required.0 Equipment identified as Category X.2. 2 19. 07 Jan. no test required. Lightning Direct Effects 23.0 19.4 Equipment tested to Category Z.0 Equipment identified as Category X.0 Equipment identified as Category X.0 Equipment tested to Category XXZ2.3.0 Equipment identified as Category X.0 Equipment identified as Category X.3.0 Category T. no test required.Installation & Operation Instruction Manual Conditions Model FA2100 CVR RTCA/DO–160C Section Description of Conducted Tests Sand and Dust 12.0 Equipment identified as Category X. Salt Spray 14. Composed of nonnutrient materials or materials that are treated in a manner that renders them non-nutrient. Voltage Spike 17.0 Equipment identified as Category X. Equipment Cables Cables Cables Radio Frequency Susceptibility (Conducted and Radiated) 20.0 Equipment identified as Category X. no test required. Induced Signal Susceptibility Magnetic Fields Magnetic Fields Electric Fields Spikes 19. Magnetic Effect 15.3 19.3b 21.0 Identified as Category F.3. Icing 24. no test required. 01/03 .3. Audio Frequency Susceptibility 18.0 Equipment assigned to Class Z.4 Equipment tested to Category Z. Fungus Resistance 13. no test required. no test required. Emission of Radio Frequency Energy Conducted Radiated 21. Power Input 16. 165E1846–00 Page B–30 Rev. Current probe method Lightning Induced Transient Susceptibility 22.0 21. no test required.1 19. 20/02 165E1846–00 Page C–1 .Model FA2100 CVR Installation & Operation Instruction Manual APPENDIX C ACCESSORY EQUIPMENT Rev. 07 Jan. 01/03 . 07 Jan.Installation & Operation Instruction Manual Model FA2100 CVR THIS PAGE IS INTENTIONALLY LEFT BLANK 165E1846–00 Page C–2 Rev. 1.Model FA2100 CVR Installation & Operation Instruction Manual MODEL 3LO–453/3 INERTIA / IMPACT SWITCH C. 07 Jan. 165E1846–00 Page C–3 . 20/02 certain g-levels. When predetermined g-levels are exceeded by the aircraft.0 GENERAL The Model 3LO–453/3 Inertia Switch is a highly reliable latching inertia/impact switch used in various military and commercial aviation applications. certain systems such as voice/data recording. emergency lighting. and fire control can be automatically turned on and off. These units are factory preset at Rev. 260 NORTH ROUTE 303 WEST NYACK.00 2.125 RESET BUTTON 1. Figure C–1. 9 oz.38 1.19 1. 3.187 DIA.G.625 TERMINALS . 01/03 .50 .750 ACCELERATION .Installation & Operation Instruction Manual Model FA2100 CVR 2. 07 Jan.37 C.187 45_ RESET BUTTON POINTING TOWARD GROUND INERTIA SWITCH INC. Inertia/Impact Switch Model 3LO–453/3 165E1846–00 Page C–4 Rev. NEW YORK 10994 PHONE: (914) 358Ć9070 FAX: (914) 358Ć1014 SPECIFICATIONS: RANGE: CURRENT: SHOCK: WEIGHT: 1 to 10 g’s 5 Amps @ 28 V dc 5 Amps @ 125 V ac 100 g’s 11ms. . (Sheet 1 of 2) Aerodyne Controls Corp. 20/02 165E1846–00 Page C–5 .Model FA2100 CVR Installation & Operation Instruction Manual Figure C–2. Environmentally Sealed Impact Switch Assembly Rev. 07 Jan. Installation & Operation Instruction Manual Model FA2100 CVR Figure C–2. 01/03 . 07 Jan. Environmentally Sealed Impact Switch Assembly 165E1846–00 Page C–6 Rev. (Sheet 2 of 2) Aerodyne Controls Corp. Model FA2100 CVR Installation & Operation Instruction Manual Specifications Size: Weight: Tuning range: Battery: Ultrasonic Test Set Gain: Noise: Model 42A12 Series MICROPHONE Undistorted Output: Microphone Sensitivity: Input Jack: Audio Output Jack: DUKANE 35 Beacon Operational Tests 40 30 45 kHZ TUNING 3 x 4 1/2 x 2 1/4 inches. battery operating life will be in the 30. Form No. Several optional modes of operation are possible through the use of external pickup devices fed into the accessory INPUT jack. Battery Life and Replacement With intermittent usage. but longer and more reliable service will be obtained by the use of premium batteries such as NEDA Type 1604A.5 kHz. The battery is accessible by removing the screw on the bottom of the case and dropping the chassis free of the case. Less than 1 mW across 10-ohm load. 13 ounces. D Set TUNING control between 35 and 40 kHz. If 5 or more are counted. OFF D GAIN TUNING GAIN CONTROL AUDIO OUTPUT D D ULTRASONIC TEST SET MODEL 42A12D D D General This Test Set is a battery-powered heterodyne type receiver. One 9-volt transistor radio battery. For example. without notice. attachment of any hydrophone of suitable frequency range to the BNC input permits use of the Test Set as a field demonstration and training device with a beacon up to 1000 yards away in the water. tunable in the ultrasonic range of 30 to 45 kHz. Tune Test Set for best audible signal. Permits operation into headphones. therefore. the beacon should operate according to published specifications. depending upon the type and manufacturer of the battery. Short water switch on Beacon. Dukane Corporation / Seacom Division / St. (impedance 10-ohms nominal). Beacon operation will be indicated by a pulsing. producing an output in the audible range. IL 60174 / (630) 584–2300 / Fax: (630) 584–5154 Printed in U. oscilloscope. 10589–C–91 Figure C–3.A. Determine pulse repetition rate by counting pulses for 10 seconds. The 42A12 Series Test Set is not intended to measure actual output signal level. etc. audible tone. The Test Set can detect a beacon signal over an unobstructed distance of approximately 40 feet with the GAIN control wide open. the Test Set can perform an operational test on a beacon without removing the beacon from its mount on the aircraft. Aviation Recorders’ Part Number 15977 Rev.to 40-hour range.S. 20/02 165E1846–00 Page C–7 . Turn GAIN control clockwise and check for operation by jingling keys or coins near microphone. 87 dB minimum at 37. Any 9-volt transistor battery may be used. Dukane ULD Tester. –150 dB re 1 uPa. 250 mW into 10-ohm load. We reserve the right to change the design and specification of goods supplied. self-contained Test Set designed to be used in connection with the installation and maintenance of Underwater Acoustic Beacons. in place of internal loudspeaker. Diode protected BNC connector. Charles. 07 Jan. By utilizing the self-contained microphone and loudspeaker. Snap-type connectors facilitate change of the battery and prevent reversal of polarity. does not require periodic calibration. to incorporate improvements in design and manufacturing techniques. 30 to 45 kHz. This is an indication of normal operation of both components. It is intended primarily for use as a hand-held. 01/03 . 07 Jan.Installation & Operation Instruction Manual Model FA2100 CVR THIS PAGE IS INTENTIONALLY LEFT BLANK 165E1846–00 Page C–8 Rev. 07 Jan. 01/03 165E1846–00 Page D–1 .Model FA2100 CVR Installation & Operation Instruction Manual APPENDIX D ABBREVIATIONS AND ACRONYMS Rev. Installation & Operation Instruction Manual Model FA2100 CVR THIS PAGE IS INTENTIONALLY LEFT BLANK 165E1846–00 Page D–2 Rev. 01/03 . 07 Jan. 01/03 Installation & Operation Instruction Manual alternating current Aeronautical Radio. 07 Jan.Model FA2100 CVR AC ARINC ATC ATR AUX BIT BITE BTU CAGE CAM CH COMB CSMU CVR DC EQF EUROCAE FAA FAR FED–STD FSK GMT GND GSE HQ Hz lbs. Incorporated Air Traffic Control Air Transport Racking auxiliary Built-in-Test Built-in-Test Equipment British Thermal Unit Commercial and Government Entity Code Cockpit Area Microphone channel combined Crash Survivable Memory Unit Cockpit Voice Recorder direct current Environmental Qualification Form European Organization for Civil Aviation Equipment Federal Aviation Administration Federal Aviation Regulation Federal Standard frequency shift keyed. frequency shift keying Greenwich Mean Time ground Ground Support Equipment high quality Hertz (cycles per second) pounds Line Replaceable Unit milliamperes microphone milliseconds millivolts route mean squared Minimum Operational Performance Specification Pulse Code Modulation Portable Interface Part Number Printed Wiring Assembly quantity Radio Technical Commission for Aeronautics serial signal-to-noise plus distortion (ratio) standard quality Technical Standard Order Underwater Locator Device volts route mean squared 165E1846–00 Page D–3 . LRU mA Mic ms mVrms MOPS PCM PI PN PWA QTY RTCA SER SINAD SQ TSO ULD Vrms Rev. Installation & Operation Instruction Manual Model FA2100 CVR THIS PAGE IS INTENTIONALLY LEFT BLANK 165E1846–00 Page D–4 Rev. 07 Jan. 01/03 .