Universal CVR 30 IM 23-70-03_Rev_1

CVR-30B and CVR-120 Solid-State

COCKPIT VOICE RECORDER

Installation Manual

© 1996, 1997, 1998 UNIVERSAL AVIONICS SYSTEMS CORPORATION ALL RIGHTS RESERVED

3260 East Lerdo Road Tucson, AZ 85706 (520) 295-2300 • (800) 321-5253

23-70-03

Revised January 20, 1998

CVR-30B and CVR-120 Installation Manual

Record of Revisions R e v. N o .

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Initials

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1/20/98

ARO

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23-70-03

Page 1 January 20, 1998


Record of Revisions R e v. N o .

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23-70-03


CVR-30 CVR-30B B a nd CVR-1 CVR-120 20 Ins Insta ta lla lla tion Ma nua l

Record of Temporary Revisions Rev. No.

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23-70-03



List of Effective Pages For your convenience, this manual has been reprinted in its entirety including Revision 1.

SUBJECT Title Page Record of Revisions Record of Temporary Revisions List of Effective Pages Table of Contents

PAGE 1

DATE Jan 20/98 Jan 20/98

1 1 1 2 3 Introduction 1 Description and Operation 1 2 3 4 5 FAA Approval 1 01 10 2 10 3 10 4 10 5 10 6 10 7 10 8 10 9 11 0 Equi Eq uipm pmen entt Spe Speci cifficat icatio ions ns 20 201 1 20 2 20 3 20 4 20 5 20 6 20 7 20 8 20 9 21 0 21 1 21 2 21 3 21 4 21 5 21 6

Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan Jan 20/9 20/98 8 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98

SUBJECT

PAGE 217 218 Installation and Wiring 30 1 302 303 304 305 306 307 308 309 310 311 312 313 314 315 316 317 318 319 320 Maintenance Ch Checkout 401 And Troubleshooting 402 403 404 405 406 407 408 409 410 411 412 413 414 415 416 417 418

LIST OF EFFECTIVE PAGES

DATE Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98 Jan 20/98



Table of Contents Record of Revisions........................................................................................................ 1 Record of Temporary Revisions..................................................................................... 1 List of Effective Pages.................................................................................................... 1 Table of Contents............................................................................................................ 1 Introduction .................................................................................................................... 1 1. Makeup and Use of This Manual................................................ .............................................. 1 A. Application...................................................................................................................................................... 1 B. Organization.................................................................................................................................................... 1

2. Abbreviations and Terminology ............................................................................................... 1 3. History...................................................... ................................................................................. 1

Description and Operation ............................................................................................. 1 1. Description ................................................... ............................................................................. 1 A. General............................................................................................................................................................ 1 B. Standard Features............................................................................................................................................ 3 C. Error Detection ............................................................................................................................................... 3 D. Recorder Unit.................................................................................................................................................. 3 E.

Control Unit .................................................................................................................................................... 4

F.

Remote Mic Amplifier.................................................................................................................................... 5

G. Annunciator / Switch Kit ................................................................................................................................ 5 H. Area Microphone ............................................................................................................................................ 5

FAA Approval ............................................................................................................ 101 1. General .................................................................................................................................. 101 2. Software Criticality................................................ ............................................................... 101 3. Environmental Qualification Forms................................................................... ................... 101 Cockpit Voice Recorder (CVR-30B & CVR-120)............................................................................................. 102 Control Unit, Remote Mic Amp......................................................................................................................... 104 Microphone ........................................................................................................................................................ 106

4. Airplane Flight Manual Supplement................................................... .................................. 108 5. CVR Operating Instructions.......................................... ........................................................ 108

CONTENTS



Equipment Specifications ........................................................................................... 201 1. Equipment Identification....................................................................................................... 201 A. CVR-30B and CVR-120 ............................................................................................................................. 201 B. Control Unit................................................................................................................................................ 201 C. Remote Mic Amp........................................................................................................................................ 201 D. Area Microphone ........................................................................................................................................ 201

2. Equipment Specification Tables .................................................. ......................................... 202 A. Recorder Unit (P/N 1603-02-30 or 1603-02-12).................. ....................................................................... 202 B. Control Unit (Slimline) (P/N 1634-01 or 1634-02) .................................................................................... 203 C. Control Unit (ARINC) (P/N 1632-01 or 1632-02)................ ...................................................................... 204 D. Control Unit (ARINC) (P/N 1633-01 or 1633-02)................ ...................................................................... 205 E.

Remote Mic Amplifier (P/N 1635-02 or 1637-02) ..................................................................................... 205

3. Installation Kits ................................................... .................................................................. 206 A. CVR Installation Kit - CVR and Slimline Control Unit or Slimline Remote Mic Amplifier (P/N 1338)... 206 B. CVR Installation Kit - CVR and ARINC Control Unit or ARINC Remote Mic Amplifier (P/N 1383)..... 206 C. Remote Switch and Jack Installation Kit (P/N 1341) ........................................................................... ...... 207

4. Drawings ............................................................................................................................... 208 A. CVR-30B/120 (P/N 1603-02-XX) .............................................................................................................. 208 B

Rack (P/N L404A-50-S-1/DPXB-0)... ........................................................................................................ 209

C. Rack Footprint ............................................................................................................................................ 210 D. Control Unit, Slimline (P/N 1634-0X)........................................................................................................ 211 E.

Control Unit, ARINC (P/N 1632-0X)......................................................................................................... 212

F.

Control Unit, ARINC w/Mic (P/N 1633-0X) ............................................................................................. 213

G. Remote Mic Amplifier, ARINC (P/N 1637-02) ......................................................................................... 214 H. Remote Mic Amplifier, Slimline (P/N 1635-02) ........................................................................................ 215 I.

Remote Switch and Jack Kit (P/N 1341) .................................................................................................... 216

J.

Annunciator Switch Detail......................................................................................................... ................. 217

K. Area Microphone (P/N 16301) ................................................................................................................... 218

Installation and Wiring ............................................................................................... 301 1. General .................................................................................................................................. 301 2. Audio System Interface......................................................... ................................................ 302 3. Recorder Location............................. .................................................................................... 302 4. Area Microphone Installation Criteria .................................................................................. 303 5. Cessation of Recording ................................................. ........................................................ 303 A. g-Switch Installation ................................................................................................................................... 303

CONTENTS


CVR-30B and CVR-120 Installation Manual 6. Installation in Rotorcraft ....................................................................................................... 304 7. Wiring Diagrams................................................................................................................... 305 A. CVR/ARINC Control Unit (P/N 1632-0X)/Aircraft Wiring........... ............................................................ 305 B. CVR/ARINC Control Unit (P/N 1633-0X)/Aircraft Wiring........... ............................................................ 307 C. CVR/Slimline Control Unit (P/N 1634-0X)/Aircraft Wiring...................................................................... 309 D. CVR/Remote Mic Amplifier, ARINC (P/N 1637-02)/Aircraft Wiring ...................................................... 311 E.

CVR/Remote Mic Amplifier, Slimline (P/N 1635-02)/Aircraft Wiring ..................................................... 313

8. Pin Out Charts....................................................................................................................... 315 A. CVR Pin Out............................................................................................................................................... 315 B. Control Unit, ARINC P/N 1633-0X Pin Out .............................................................................................. 316 C. Control Unit, ARINC P/N 1632-0X Pin Out .............................................................................................. 317 D. Control Unit, Slimline P/N 1634-0X Pin Out ............................................................................................. 318 E.

Remote Mic Amplifier, ARINC P/N 1637-02 Pin Out............................................................................... 319

F.

Remote Mic Amplifier, Slimline P/N 1635-02 Pin Out.............................................................................. 320

Maintenance, Checkout and Troubleshooting ........................................................... 401 1. Maintenance .......................................................................................................................... 401 A. Periodic Inspections/Overhaul.................................................................................................................... 401 B. Underwater Locator Beacon Servicing/Maintenance ................................................................................. 401

2. Post-Installation Checkout Procedure ................................................................................... 402 3. Preflight Ground Checkout Procedure.................................................................................. 404 A. Checkout Procedures .................................................................................................................................. 405

4. Flight Checkout Procedure....................................... ............................................................. 408 A. Prior To Engine Start .................................................................................................................................. 408 B. Engine Start................................................................................................................................................... 408 C. Take-Off ..................................................................................................................................................... 409 D. Landing....................................................................................................................................................... 409 E.

Postflight..................................................................................................................................................... 410

5. Test Set (P/N 1623-01).......................................................................................................... 411 A. Test Set Features......................................................................................................................................... 412 B. Test Set Panel Layout ................................................................................................................................. 415 C. ANSI Terminal Interface............................................................................................................................... 416

CONTENTS



Introduction 1.

Makeup and Use of This Manual

A.

Application This Installation Manual for the CVR-30B and CVR-120 is applicable to the components noted below;

Component

Part Number

Remarks

CVR-30B

1603-02-03

30 minutes recording

CVR-120

1603-02-12

120 minutes recording

Control Unit

1634-0X

Slimline, non-ARINC

Control Unit

1632-0X

ARINC

Control Unit

1633-0X

ARINC w/ microphone

Microphone

16301-0X

Remote Microphone

Remote Amplifier

1637-02

ARINC remote mounting, used in lieu of control unit

Remote Amplifier

1635-02

Slimline, non-ARINC, remote mounting, used in lieu of control unit

Annunciator/Switch Kit

1341

Used with Remote Amplifier

Installation Kit

1338

For non-ARINC control unit or Remote Amplifier

Installation Kit

1383

For ARINC control unit or Remote Amplifier

Test Set

B.

1623-01

Organization This Installation Manual provides the information about:

2.

(1)

Description and operation of the components of the cockpit voice recorder system.

(2)

FAA Approval including Environmental Qualification Forms.

(3)

Equipment Specifications to support selection of compatible peripherals and planning for the installation of CVR Components.

(4)

Detailed installation and wiring requirements.

(5)

Maintenance, Checkout, and Troubleshooting of the CVR System.

Abbreviations and Terminology This manual contains no abbreviations or terms that have varying interpretations throughout the industry. Throughout this manual you will see part numbers containing X’s. These X’s define variables which, in specific portions of text, do not matter. Refer to the Equipment Specifications Section for full part number definition.

3.

History This is the first revision of this Installation Manual, Report No. 23-70-03. Return to Table of Contents

INTRODUCTION



Description and Operation 1.

Description

A.

General The information contained within this Installation manual describes the administrative and technical aspects, features, functions, components and operation of Universal Avionics Systems Corporation’s CVR-30B and CVR-120 Solid State Cockpit Voice Recorders. Any and all comments or recommendations regarding the installation, acceptance or operation of the CVR or its accessories and components should be directed to the Product Support department at Universal Avionics Systems Corporation. All references and descriptions in this manual refer to both the CVR-30B and CVR-120 unless otherwise noted. The CVR-30B and CVR-120 Systems have been designed to meet or exceed those requirements specified within this Installation Manual and is approved under Federal Aviation Administration Technical Standard Order (TSO) C123a and EUROCAE ED-56A (refer to FAA Approval Section). Three versions of the CVR Control Units are available. There are two ARINC size Control Units with ARINC 557 connectors, one with and one without a microphone. The CVR-30B stores up to thirty minutes of cockpit audio and the CVR-120 stores up to one hundred twenty minutes. The four channels of audio input consist of an area microphone, pilot, copilot and an extra source. The area microphone is fed into two separate audio channels, the first is for high quality audio lasting 30 minutes and the second is lower quality lasting for 120 minutes. All four audio inputs are fed into six CODEC channels, four of which record directly for 30 minutes, the fifth is a combination (mix) of the four channels for a recording duration of 120 minutes, and the area mic channel also recorded for 120 minutes. The CVR-30B has four 30minute recording channels only.

23-70-03


CVR-30B and CVR-120 Installation Manual In addition to storing cockpit audio, the CVR is also capable of storing other data such as; •

Greenwich Mean Time (GMT) from an ARINC 429 bus

•

GMT from a Frequency Shift Keying (FSK) signaling source

•

Rotor speed for helicopter applications

•

CVR internal BITE status

This data is synchronized with the audio during recording and playback. The digital approach to a CVR is made possible by two key new technologies: 1) Adaptive Differential Pulse Code Modulation (ADPCM) Digital Signal Processing (DSP) hardware and 2) flash memory. The ADPCM processor is a hardware engine that compresses and expands digital audio data. A compression of 4:1 is used in the CVR and provides sufficient audio performance to meet existing and proposed MOPS (Minimum Operating Performance Standards). Flash memory is a type of Electrically Erasable Programmable Read Only Memory (EEPROM) which is characterized by fast write timing, high bit density, a high number of erase/write cycles, and data retention at high temperature with no backup power required. The reliability of flash (EEPROM) memory is inherently very high, the memory cell structure of EEPROMs and PROMs are similar, with the added ability to electrically erase the EEPROMs. The normal operating procedures for writing and erasing EEPROMs is also inherently reliable and redundant. To write to a location in the flash device, three operations are performed, 1) the old data is erased, 2) the data is written, and 3) the data is verified. The operation of the CVR is controlled by a microprocessor operating at 24 MHz. The microprocessor is closely coupled to a 68 M-byte flash memory array and performs the memory programming functions. When the CVR is in the record mode, the compressed ADPCM data is read from a hardware interface and stored in the flash memory using special programming algorithms. The process is reversed for the play mode. All other control functions such as self test and bulk erase are performed by the microprocessor.

CVR HARDWARE BLOCK DIAGRAM

23-70-03


CVR-30B and CVR-120 Installation Manual The CVR-30B and CVR-120 are line replaceable units (LRU) and are ARINC 757/557 compatible. An underwater locator beacon (ULB) is mounted on the front. Three models of panel-mounted control units are offered, plus a remote preamp option.

B.

Standard Features •

TSO-C123a (ED-56A)

•

Solid-State Flash Memory Array

•

Input Recording

•

C.

•

5 external source inputs

•

7 recorded channels (6 voice plus rotor speed)

•

Records GMT

Maintenance on Condition Only (excluding ULB) •

No Overhaul Required

•

30,000 hrs. MTBF

•

Diagnostics and Maintenance Alert through Cockpit Control Panel

•

Three Year Warranty

•

Weighs: 30B = 13.0 lbs. & 120 = 13.0 lbs.

•

Complete Onboard Aircraft Testing with Portable Test Set

•

Direct replacement for ARINC 557 Analog Tape Units

•

ARINC 757 compatible

Error Detection CVR errors are detected at three possible times; during power up, during self test and during normal operation. Detected errors are reported via the CVR control unit FAIL Light. Errors are classified as either non-significant (some audio is recorded) or significant (high probability that no audio is recorded). During power up, significant failures only will be reported by steady illumination of the red FAIL light on the CVR control unit. This FAIL Light can be cleared by pressing the SELF TEST button on the control unit if there is no longer an error. A self test should be performed following the report of a significant error to confirm that the error is in fact significant. During the on demand self test, an inspection of a memory array verify error count is performed, if the error count is greater than the allowed tolerance, a flash (or steady) code will be displayed on the red FAIL Light on the CVR control unit.

D.

Recorder Unit The Recorder Unit contains the Recorder Assembly and associated electronics. The enclosure is International Orange to meet requirements of the National Transportation Safety Board (NTSB). An Underwater Locator Beacon (ULB) is attached as required by regulations. The Recorder Unit mounts in an ARINC 404A 1/2 ATR short rack (Kit 1338 or 1383).

23-70-03


CVR-30B and CVR-120 Installation Manual E.

Control Unit The Control Unit (P/N 1632-0X, 1633-0X or 1634-0X) contains an amplifier for the Area Microphone, ERASE Push Button, TEST Push Button, PASS and FAIL Annunciators, SIGNAL LEVEL Indicator and a HEADPHONE Jack. The panel mounted Control Unit mounts with standard DZUS fasteners. The Control Unit is available in either black or gray and will operate with either 5 VDC or 28 VDC lighting. Control Unit P/N 1633-0X has a built in microphone.

SLIMLINE CONTROL UNIT, P/N 1634-0X

UNIVERSAL

ERASE

SIGNALLEVEL

HEADPHONE

PAS S

FA IL

TEST

ARINC CONTROL UNIT, P/N 1632-0X

ARINC CONTROL UNIT, P/N 1633-0X

23-70-03


CVR-30B and CVR-120 Installation Manual F.

Remote Mic Amplifier The Remote Mic Amplifier (P/N 1635-02 or 1637-02) and the Annunciator/Switch Kit (P/N 1341) are used in lieu of the Control Unit when there is not enough space in the cockpit for the panel mounted Control Unit. Refer to Annunciator/Switch Kit below.

G.

Annunciator/Switch Kit The Annunciator/Switch Kit (P/N 1341) provides a CVR TEST/PASS/FAIL Annunciator/Switch, a CVR ERASE Annunciator/Switch, Headphone Jack, a plate and a decal. This Kit is used in conjunction with the Remote Mic Amplifier described above.

CVR CVR TEST

CVR ERASE

PASS FAIL HEADSET

ANNUNCIATOR/SWITCH KIT H.

Area Microphone The CVR utilizes a miniature, cardiod type, directional pattern, remotely mounted Area Microphone (P/N 16301-01 or 16301-02). The P/N 1633-0X Control Unit contains its own internal microphone and, in most cases eliminates the need for a remotely mounted area microphone.

AREA MICROPHONE Return to Table of Contents

23-70-03



FAA Approval 1.

General Approval of the CVR-30B and CVR-120 Recorder System is not authorized by this Installation Manual. Acceptance for the installation and use of the CVR and its associated components must be sought through the appropriate offices of the Federal Aviation Administration or other certifying agency. Approvals may be accomplished on a Field Approval basis if the installation is determined to meet the criteria of the appropriate Post-Installation, Ground Checkout and Flight Checkout Procedures specified for evaluation within this Installation Manual. It is recommended that all proposed installations be coordinated with the local jurisdiction of the Federal Aviation Administration or other certifying agency prior to performing the installation.

2.

Software Criticality The software embedded in the CVR-30B and CVR-120 is categorized as DO-178B Level D. Level D software is defined by DO-178B as “software whose anomalous behavior, as shown by the system safety assessment process, would cause or contribute to a failure of system function resulting in a minor failure condition for the aircraft.” There are no flight regime dependent functions which will change the criticality category and software level.

3.

Environmental Qualification Forms The environmental categories under which the CVR-30B, CVR-120 and all other related components of the CVR system are defined on the following Environmental Qualification Forms.

23-70-03


CVR-30B and CVR-120 Installation Manual UNIVERSAL AVIONICS SYSTEMS CORPORATION ENVIRONMENTAL QUALIFICATION FORM PROCEDURE TSO C123 AND RTCA DO-160C NOMENCLATURE: PART NO.:

COCKPIT VOICE RECORDER (CVR-30B & CVR-120)

1603-02-0X

TSO NUMBER:

C123a & ED-56A

MANUFACTURER’S SPECIFICATION AND/OR OTHER APPLICABLE SPECIFICATION:

Contained in

CVR-30B/CVR-120 Cockpit Voice Recorder Installation Manual Report Number 23-70-03 MANUFACTURER: Universal Avionics Systems Corporation 3260 E. Lerdo Road Tucson, AZ. 85706-5021 CONDITIONS

DO-160C SECTION# PARAGRAPH# 4.0

EQUIPMENT TESTED TO CATEGORY C2E1

4.5.1 4.5.2, 4.5.3

-55°C OPERATING, -55°C SURVIVAL +70°C OPERATING, +85°C SURVIVAL

4.6.1 4.6.2

70,000 FT 70,000 FT

4.6.3

-15,000 FT

TEMPERATURE VARIATION HUMIDITY SHOCK

5.0 6.0 7.0

OPERATIONAL CRASH SAFETY VIBRATION

7.2 7.3 8.0

EXPLOSION WATERPROOFNESS FLUIDS SUSCEPTIBILITY SAND AND DUST FUNGUS

9.0 10.0 11.0 12.0 13.0

EQUIPMENT TESTED TO CATEGORY B EQUIPMENT TESTED TO CATEGORY A EQUIPMENT TESTED PER DO-160C, PARA 7.2.1 6.0 g 15.0 g EQUIPMENT TESTED WITHOUT SHOCK MOUNTS TO CATEGORIES B, M & N EQUIP. CAT "E2" EQUIP. IDENTIFIED AS "W" EQUIP. IDENTIFIED AS "X" NO TEST REQ'D EQUIP. IDENTIFIED AS "X" NO TEST REQ'D EQUIP. IDENTIFIED AS "X" NO TEST REQ'D

TEMPERATURE AND ALTITUDE LOW TEMPERATURE HIGH TEMPERATURE ALTITUDE DECOMPRESSION OVERPRESSURE

DESCRIPTION OF CONDUCTED TESTS

23-70-03


CVR-30B and CVR-120 Installation Manual UASC ENVIRONMENTAL QUALIFICATION FORM (cont.) NOMENCLATURE: PART NO.:

COCKPIT VOICE RECORDER (CVR-30B & CVR-120)

1603-02-0X

CONDITIONS

SALT SPRAY MAGNETIC EFFECT POWER INPUT VOLTAGE SPIKE CONDUCTED AUDIO FREQUENCY SUSCEPTIBILITY INDUCED SIGNAL SUSCEPTIBILITY RADIO FREQUENCY SUSCEPTIBILITY RADIO FREQUENCY EMISSION LIGHTNING INDUCED TRANS SUS LIGHTNING DIRECT EFFECTS ICING CRASH SURVIVABILITY

DO-160C SECTION# PARAGRAPH# 14.0 15.0 16.0 17.0


18.0

EQUIPMENT TESTED TO CATEGORY "Z"

19.0


20.0

EQUIPMENT TESTED TO CATEGORY "T"

21.0


22.0

EQUIPMENT TESTED TO CATEGORY A3E3

23.0

EQUIP. IDENTIFIED AS "X" NO TEST REQ’D

24.0

EQUIP. IDENTIFIED AS "X" NO TEST REQ’D ACCORDING TO TSO C-123 & ED-55, 7.1

EQUIP. IDENTIFIED AS "X" NO TEST REQ’D EQUIPMENT IDENTIFIED AS CLASS "Z" EQUIPMENT TESTED TO CATEGORY "Z" EQUIPMENT TESTED TO CATEGORY "A"

23-70-03



CONTROL UNIT, REMOTE MIC AMP

1632-0X, 1633-0X, 1635-XX, 1637-XX________

TSO NUMBER:

C123a & ED-56A


Contained in


DO-160C SECTION# PARAGRAPH#


TEMPERATURE AND ALTITUDE

4.0

CONTROL UNIT & REMOTE MIC AMPLIFIER TESTED TO CATEGORY A2 MICROPHONE TESTED TO CATEGORY A2

LOW TEMPERATURE HIGH TEMPERATURE ALTITUDE *2 DECOMPRESSION *2 OVERPRESSURE *2

4.5.1 4.5.2, 4.5.3 4.6.1 4.6.2 4.6.3

-55°C OPERATING, -55°C SURVIVAL +70°C OPERATING, +85°C SURVIVAL 70,000 FT 70,000 FT -15,000 FT

TEMPERATURE VARIATION

5.3

EQUIPMENT TESTED TO CATEGORY B

HUMIDITY

6.0

EQUIPMENT TESTED TO CATEGORY A 50°C, 95%, 48 HOURS

7.0

EQUIPMENT TESTED PER DO-160C

7.2 7.3

6.0 g 15.0 g

VIBRATION

8.0

EQUIPMENT TESTED WITHOUT SHOCK MOUNTS TO CATEGORIES B, M & N

EXPLOSION

9.0 of (DO-160C) EQUIP. CAT "X" INTRINSICALLY SAFE

WATERPROOFNESS

10.0

EQUIP. IDENTIFIED AS "X" NO TEST REQ'D

FLUIDS SUSCEPTIBILITY

11.0


SAND AND DUST

12.0


*2

SHOCK OPERATIONAL CRASH SAFETY

See Temporary Change 23.70.03-3

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>=4^=A

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3<=6!G 6@3496>63@ :A gHg 4* 93A9 73
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CONTROL UNIT, REMOTE MIC AMP

1632-0X, 1633-0X, 1635-XX, 1637-XX

________

CONDITIONS

DO-160C SECTION# PARAGRAPH#


FUNGUS

13.0


SALT SPRAY

14.0


MAGNETIC EFFECT

15.0

EQUIPMENT IDENTIFIED AS CLASS "Z"

POWER INPUT

16.0


VOLTAGE SPIKE CONDUCTED

17.0

EQUIPMENT TESTED TO CATEGORY "A"

AUDIO FREQUENCY CONDUCTED SUSCEPTIBILITY

18.0


INDUCED SIGNAL SUSCEPTIBILITY

19.0


RADIO FREQUENCY SUSCEPTIBILITY

20.0

EQUIP. IDENTIFIED AS "X" (MEETS DO-160B CATEGORY Z)

RADIO FREQUENCY EMISSION

21.0


LIGHTNING INDUCED TRANS SUS

22.0

EQUIPMENT TESTED TO CATEGORY "K"

LIGHTNING DIRECT EFFECTS

23.0


ICING

24.0


23-70-03



MICROPHONE

16301-0X

TSO NUMBER:

C123a & ED-56A


Contained in


DO160C SECTION# PARAGRAPH#


TEMPERATURE AND ALTITUDE

4.0

CONTROL UNIT & REMOTE MIC AMPLIFIER TESTED TO CATEGORY A2 MICROPHONE TESTED TO CATEGORY A2

LOW TEMPERATURE HIGH TEMPERATURE ALTITUDE *2 DECOMPRESSION *2 OVERPRESSURE *2

4.5.1 4.5.2, 4.5.3 4.6.1 4.6.2 4.6.3

-55°C OPERATING, -55°C SURVIVAL +70°C OPERATING, +85°C SURVIVAL 70,000 FT 70,000 FT -15,000 FT

TEMPERATURE VARIATION

5.3

EQUIPMENT TESTED TO CATEGORY B

HUMIDITY

6.0

EQUIPMENT TESTED TO CATEGORY A 50°C, 95%, 48 HOURS

7.0

EQUIPMENT TESTED PER DO-160C

7.2 7.3

6.0 g 15.0 g

VIBRATION

8.0

EQUIPMENT TESTED WITHOUT SHOCK MOUNTS TO CATEGORIES B, M & N

EXPLOSION

9.0 of (DO-160C) EQUIP. CAT "X" INTRINSICALLY SAFE

WATERPROOFNESS

10.0


FLUIDS SUSCEPTIBILITY

11.0


SAND AND DUST

12.0


*2

SHOCK OPERATIONAL CRASH SAFETY

23-70-03



MICROPHONE

16301-0X________

CONDITIONS

DO160C SECTION# PARAGRAPH#


FUNGUS

13.0


SALT SPRAY

14.0


MAGNETIC EFFECT

15.0

EQUIPMENT IDENTIFIED AS CLASS "Z"

POWER INPUT

16.0


VOLTAGE SPIKE CONDUCTED

17.0


AUDIO FREQUENCY CONDUCTED SUSCEPTIBILITY

18.0


INDUCED SIGNAL SUSCEPTIBILITY

19.0


RADIO FREQUENCY SUSCEPTIBILITY

20.0


RADIO FREQUENCY EMISSION

21.0


LIGHTNING INDUCED TRANS SUS

22.0

EQUIPMENT TESTED TO CATEGORY "K"

LIGHTNING DIRECT EFFECTS

23.0


ICING

24.0


23-70-03



4.

Airplane Flight Manual Supplement Supplementing the Airplane Flight Manual with CVR Operating instructions can be accomplished several different ways. One method of preparing an AFMS is to include all operational instructions in one supplement. Another method is to merely have a supplement referring to Universal’s Operational Instructions. These Operational instructions as well as the supplement would both go into the Supplements Section of the Airplane Flight Manual. Some local certifying agencies differ on the method of supplementing, so it would be a good idea to check with them first.

5.

CVR Operating Instructions The following CVR operating instructions are provided for insertion into the Supplements Section of the Airplane Flight Manual if so desired. Permission is hereby granted to reproduce these instructions. These instructions are also available from Universal Avionics Systems Corporation upon request. Ask for Operating Instructions, Report No. 23-70-03.01

See Temporary Change 23.70.03-2

23-70-03


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Y4

2$C-++$"=$= D$%)-=)C QC($=?H$= D%$;$"&.&);$ N.)"&$"."C$ *$#&#V0($CW# &- a$&$%+)"$ Q/#&$+ 0-"=)&)-" ."=V-% _.&$"& K.)H?%$#M !"#$M

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3-"$ 2$O?)%$=4

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23-70-03



Return to Table of Contents

23-70-03



Equipment Specifications 1.

Equipment Identification

A.

CVR-30B and CVR-120

B.

Control Unit

C.

Remote Mic Amplifier - ARINC

D.

Remote Mic Amplifier - Slimline

E.

Area Microphone

23-70-03



2.

Equipment Specification Tables

A.

Recorder Unit (P/N 1603-02-30 or 1603-02-12) Characteristic

Specification

Height

6.78”

Width

4.875”

Length

12.56”

Weight

13.0 lbs.

Power Input

28 VDC or 115 VAC

Power Consumption

Approx 14W nominal @ 27.5 VDC Approx 18W nominal @ 115 VAC

Inputs

3 crew microphones 1 area microphone Rotor speed GMT (ARINC 429 or FSK) OMS (Onboard Maintenance System) Data Link (future)

Medium

Solid State Flash Memory array

Erase

Fail Safe; double electrical interlock

Recorded Audio Frequency Response

Crew microphones 150 to 3500 Hz Area microphone 150 to 6000 Hz

Analog Rotor Speed Input

10 to 15,000 Hz rotor tach frequency 200 K Ohms Impedance .2 volts min., 100 volts max.

Headphone Output (Monitor)

600 Ohms, 10 mw

Audio Input Impedance

5000 Ohms, each channel

Recorded SNR

48 dB (Area microphone) 45 dB (minimum)

Harmonic Distortion

10% max THD and noise at 0 dB input 6% max THD and noise at -20 dB input 6.3% max THD for area microphone

Audio Outputs (6 channels)

775 mV RMS into 600 Ohms (with 330 VRMS input)

Underwater Locator Beacon Battery Life

6 years (Dukane Model DK120, replaceable battery)

Mounting

Solid Rack Mount (shock mounting is not required in aircraft or helicopters)

23-70-03


CVR-30B and CVR-120 Installation Manual B.

Control Unit (Slimline) (P/N 1634-01 or 1634-02)

Characteristic

Specification

Height

1.50”

Width

5.75”

Depth

3.88”

Weight

.75 lbs.

Power Input

+15 VDC (from Recorder Unit)

Lighting

210 mA @ 5 VDC (from aircraft bus lighting)

Jack: HEADPHONE output

600 Ohms

Area Mic Input

20 K Ohms impedance audio input 3 mV audio input level 30 dB audio gain control

Area Mic Output

150 Ohms impedance audio input 500 mV rms (max) output level 150 to 10,000 Hz frequency response; frequency selectable 1000 Hz; 18 dB/octave rolloff 6, 12, 24 dB step attenuation strapping

Switches

TEST and ERASE

Indicators

SIGNAL LEVEL, PASS, FAIL

Mounting

Dzus Panel Mount

23-70-03


CVR-30B and CVR-120 Installation Manual C.

Control Unit (ARINC) (P/N 1632-01 or 1632-02)

Characteristic

Specification

Height

2.25”

Width

5.75”

Depth

3.625”

Weight

0.9 lbs.

Power Input


Lighting

210 mA @ 5 VDC (from aircraft bus lighting)


600 Ohms

Area Mic Input


Area Mic Output

150 Ohms impedance audio input 500 mV output level 150 to 10,000 Hz frequency response; frequency selectable 1000 Hz; 18 dB/octave rolloff 1000 Hz; 18 dB/octave rolloff 6, 12, 24 dB step attenuation strapping

Switches

TEST and ERASE

Indicators


Mounting

Dzus Panel Mount

23-70-03


CVR-30B and CVR-120 Installation Manual D.

Control Unit (ARINC) (P/N 1633-01 or 1633-02) Characteristic

Specification

Height

2.25”

Width

5.75”

Depth

3.625”

Weight

0.9 lbs.

Power Input


Lighting

210 mA @ 5 VDC, 77 mA @ 28 VDC (from aircraft bus lighting)


600 Ohms

Area Mic Input


Area Mic Output

150 Ohms impedance audio input 500 mV output level 150 to 10,000 Hz frequency response filter is cutoff frequency selectable 1000 Hz; 18 dB/octave rolloff 6, 12, 24 dB step attenuation strapping

Switches

TEST and ERASE

Indicators


Mounting

Dzus Panel Mount

E.

Remote Mic Amplifier (P/N 1635-02 or 1637-02) Characteristic

Specification

Height

1.50” (1635-02) or 2.50” (1637-02)

Width

6.25” (1635-02) or 5.75” (1637-02)

Depth

3.63” (1635-02) or 2.91” (1637-02)

Weight

0.75 lbs. (1635-02) or .80” (1637-02)

Power Input


Area Mic Input


Area Mic Output

150 Ohms impedance audio input 500 mV output level 150 to 10,000 Hz frequency response filter is cutoff frequency selectable 1000 Hz; 18 dB/octave rolloff 6, 12, 24 dB step attenuation strapping

Switches, Indicators and headphone

Annunciator/Switch Kit P/N 1341 provides the necessary switches, indicators and headphone jack.

Mounting

Remote

23-70-03



3.

Installation Kits

A.

CVR Installation Kit - CVR and Slimline Control Unit or Slimline Remote Mic Amplifier (P/N 1338) Kit No 1338 is used to install the CVR when either the Slimline Control Unit P/N 1634-0X or the Slimline Remote Mic Amplifier P/N 1635-02 is used. If the Slimline Remote Mic Amplifier is used then the CVR Remote Switch and Jack Kit No 1341 should also be used.

Kit No. 1338 Consists of: QTY

B.

P/N

NAME

1

L404A-50-S-1/DPXB-0

1/2 ATR Short Rack

1

DPXBMA-57-33S-00

Rack Connector

1

205561-2

Controller/Remote Amp Connector

1

206478-4

Connector Backshell

1

91067-2

Insertion/Extraction Tool

CVR Installation Kit - CVR and ARINC Control Unit or ARINC Remote Mic Amplifier (P/N 1383) Kit No 1383 is used to install the CVR when either the ARINC Control Unit P/Ns 1632-XX or 1633-XX, or the ARINC Remote Mic Amplifier P/N 1637-02 is used. If the ARINC Remote Mic Amplifier is used then the CVR Remote Switch and Jack Kit No 1341 should also be used.


P/N

NAME

1

L404A-50-S-1/DPXB-0

1/2 ATR Short Rack

1

DPXBNA-57M-33S-00

Rack Connector

1

MS3126F20-41S

Controller/Remote Mic Amp Connector

23-70-03



Remote Switch and Jack Installation Kit (P/N 1341) Kit No 1341 provides the necessary switches, annunciators and headphone jacks which are need when a Remote Mic Amplifier, P/N 1637-02 or 1635-02 is installed.


P/N

NAME

1

95-18-11-E6-55631

Annunciator Switch “CVR TEST / PASS / FAIL”

1

95-18-11-H6-55632

Annunciator Switch “CVR ERASE”

1

39F652

Headphone Jack

1

1341-1

Annunciator Plate

1

L12304

Annunciator Plate Label

23-70-03



4.

Drawings

A.

CVR-30B/120 (P/N 1603-02-XX)

23-70-03



Rack (P/N L404A-50-S-1/DPXB-0)

23-70-03



Rack Foot Print 4.120" TYP

#19 (.166) DRILL (CLEARANCE FOR #8 SCREW) (4 PLCS FOR RACK)

9.000" TYP

23-70-03



Control Unit, Slimline (P/N 1634-0X)

23-70-03



Control Unit, ARINC (P/N 1632-0X)

23-70-03



Control Unit, ARINC w/mic (P/N 1633-0X)

23-70-03


CVR-30B and CVR-120 Installation Manual G.

Remote Mic Amplifier (P/N 1637-02)

23-70-03


CVR-30B and CVR-120 Installation Manual H.

Remote Mic Amplifier, Slimline (P/N 1635-02)

23-70-03


CVR-30B and CVR-120 Installation Manual I.

Remote Switch and Jack Kit (P/N 1341)

1341-3 DECAL

23-70-03


CVR-30B and CVR-120 Installation Manual J.

Annunciator Switch Detail (P/N 1612-0X)

23-70-03


CVR-30B and CVR-120 Installation Manual K.

Area Microphone (P/N 16301)


23-70-03



Installation and Wiring 1.

General This section contains considerations and recommendations for installation of the Cockpit Voice Recorder and associated system components. Interconnect harness wiring, physical mounting and Area Microphone must be considered as required to satisfy all applicable regulations. The conditions and tests required for TSO approval of this article are minimum performance standards. It is the responsibility of those desiring to install this article either on or within a specific type or class of aircraft to determine that the aircraft installation conditions are within TSO standards. If not within TSO standards, the article may be installed only if the applicant documents further evaluation for an acceptable installation and it is approved by the Administrator of the Federal Aviation Administration or other certifying agency. The Federal Aviation Administration has issued several Advisory Circulars which may be referred to in the approval processes. Advisory Circular 25.1457-1A specifically addresses one acceptable means of compliance with Federal Aviation Regulation (FAR) 25.1457 (b), (e) and (f). Installations must conform to the Operating Rules in FAR 23.1457, 25.1457, 27.1457 and 29.1457 appropriate to the category of operation under FAR Parts 91, 135 and 121 (Air Carrier). The CVR System can be powered by either 115 VAC or by 28 VDC from the essential aircraft bus source. To ensure optimal performance from the Cockpit Voice Recorder System, the following wire sizes and types are recommended as acceptable: A.

All wires except 1P1 pins 2,3,9 and 17: Use #22 AWG or larger, for maximum of 500 ft. length if shielded pairs are used. All wiring should be MIL-W-22759 or MIL-C-27500.

B.

For 1P1 pins 2,3,9 (Power leads), and 17 (Ground), use the following as a minimum: #20 AWG,

35 ft. max.

#16 AWG,

70 ft. max.

C.

Ground connections for all shields are to be within one foot of 1P1 pin 17. The reason for specifying single point ground is to minimize random noise pickup on audio inputs. Refer to Wiring Diagram Notes.

D.

Normal power requirements are: 14 watts nominal @ 27.5VDC 18 watts nominal @ 115VAC

The ERASE connection is not mandated by the FAA; therefore, it is an installation option. The circuitry required for ERASE includes the installation of interlock devices on board the aircraft. If the ERASE is installed, then at least one interlock circuit is required to prevent accidental erasure of the CVR recording. The most common interlock circuit is through the squat switch and/or the parking brake switch, however, the installer may choose an alternate type of interlock circuit as long as it is not flight accessible. If the ERASE is not desired, 1P1 pin 55 (ERASE A) must be grounded to single point ground or jumpered to 1P1 pin 17. Pin 57 remains open. If at least one interlock cannot be provided, the ERASE feature may NOT be utilized. NOTE:

The wiring diagrams contained in this manual show both the squat switch and parking brake interlock circuit as an example only.

23-70-03



2.

Audio System Interface The range of acceptable audio input levels for the CVR is approximately from 50 mV RMS to 500 mV RMS. Do not exceed 500 mV RMS. Exceeding 500 mV RMS will overdrive the recorder and result in non-intelligible recording. The overdrive condition is readily identifiable on the Signal Level Indicator on the Control Unit or Test Set. Normal audio inputs will illuminate the first seven LED segments most of the time while the last three LED segments will illuminate momentarily during conversation. If the last three LED segments are illuminated most of the time or continually, then chances are that audio inputs exceed system design. To correct this problem, adjust the aircraft audio system/mixer outputs to an acceptable level. Each audio input, including area mics should be isolated, tested and adjusted separately. NOTE:

Do not attempt to adjust audio level during the first ten seconds of self testing. The CVR is recording a test tone during this time.

Earlier aircraft audio systems may require rework of their audio system to ensure recording of ATC, Intercom, Mask Microphone and Sidetone Audio, independent of mode selection on the audio control panel. In some cases, selection of the Loud Speaker function disables Sidetone output; therefore, transmissions to ATC may not be recorded. Such a condition must be remedied to provide continuous received audio from the communications radios. It is beyond the scope of this manual to show all specific aircraft audio system wiring interconnects. The wiring diagrams shown herein show the required inputs to the CVR. It is the installer’s responsibility to obtain the specific aircraft audio system wiring diagrams for determining the required outputs. Old Audio Systems - Rework the audio control panel or system to provide a CVR output or install an external summing amplifier. Summing amplifiers can be obtained from Avtec, Baker Electronics, Racal, Gables and others. The addition of a summing amplifier provides existing audio systems with the “hot” boom microphone capability. No changes to the CVR are required. New Audio Systems - Some later generation audio control panels have a CVR signal output already provided. A summing amplifier may be required to provide “hot “ boom microphone operation. It is the responsibility of the installer to determine the means of interfacing to comply with the regulations.

3.

Recorder Location It is permissible to install the CVR in unpressurized, unheated areas whenever installation within the pressure vessel is not desired or practical. Refer to FAA Advisory Circular 25.1457-1A for further details. See Temporary Change 23.70.03-1

23-70-03


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4.

Area Microphone Installation Criteria The most desirable location for the cockpit area microphone(s) is forward of a vertical plane oriented laterally through the pilot’s and co-pilot’s normal head position. The microphone should face the crew members. The area microphone wiring should be kept as short and direct as possible. A maximum of 15 feet is allowed. The area microphone wiring must be secured within four inches of the microphone. This helps prevent the wires from vibrating loose in the microphone.

5.

Cessation Of Recording Federal Aviation Regulations 23.1457 (d), (2), 25.1457 (d), (2) 27.1457 (d), (2) and 29.1457 (d), (2) state that “There [must be] is an automatic means to simultaneously stop the recorder and prevent each erasure feature from functioning, within 10 minutes after crash impact.” EUROCAE document ED-56A states “The CVR shall be provided with a means of automatically terminating the recording and erasure functions within 10 minutes after all engines have stopped”. ARINC Characteristics 757 states “Within the installation, a means should be provided to terminate recording after the aircraft is no longer moving under its own power, or after an accident”. It is the installer’s responsibility to assure that these regulations are met. A CVR pin has been reserved for this function; providing a ground to CVR 1P1 pin 10 (STOP RECORD) will start a 10-minute timing cycle, at the end of which both record and erase functions will be inhibited. Removal of this ground will cause the recorder to immediately begin recording

A.

g-Switch Installation When a g-Switch is used as a means of cessation, it should be noted that some certifying agencies are more restrictive than others. Two examples are shown below. •From FAA Action Notice A8300.56 (para. 1.(5)); “NOTE:

....An automatic means which incorporates a “G” Switch must consider nuisance tripping and should be within an activation range of 3.0G to 6.0G.”

•From CAA Specification 11 (para. 3.5); “NOTE:

An acceptable means of compliance would be to install a device which would interrupt the electrical supply to the recorder when the inertial force on the airplane exceeds 3 ‘g’ forwards or, for helicopters, 3 ‘g’ along the axis 45 degrees below the horizontal forward axis. In addition, for helicopters equipped in compliance with the Air Navigation Order for flights over water, a device should be installed so as to interrupt the electrical supply to the recorder following an enforced ditching.”

It is imperative that the installer be familiar with the rules, regulations and recommendations of the certifying agency. Refer to the figure for a typical 45° g-Switch installation. Some acceptable switches are: Inertia Switch, Inc. 269 N Rte. 303 West Nyack, NY 10994

P/N 3LO-453/3 (3-g activation) or P/N 3LO-453/4 (4-g activation)

Aerodyne Controls Corp 30 Haynes Court Ronkonkoma, NY 11779

P/N 6895-D-1-3-5 (3-g) or P/N 6895-D-1-4-4 (4-g)

23-70-03



6.

Installation In Rotorcraft

g-SWITCH

45 DEG

RESET BUTTON (REF)

UP FORWARD VIEW LOOKING FROM RIGHT SIDE OF FUSELAGE

g-SWITCH INSTALLATION On rotorcraft where at least one interlock cannot be provided, the ERASE feature may NOT be utilized. 1P1 pin 55 (ERASE A) must be grounded to single point ground or jumpered to 1P1 pin 17. 1P1 pin 57 remains open. The CVR accepts direct input of rotor speed tachometer signal and can be read out with ground support equipment. The rotor speed encoder, necessary with analog CVRs is not needed. It is important to note that rotor speed input is not compatible with rotorspeed encoders due to the higher frequencies of the encoder. Refer to the wiring diagrams in this manual for rotor speed input specifications.

23-70-03



7.

Wiring Diagrams

A.

CVR / ARINC Control Unit (P/N 1632-0X) / Aircraft Wiring

23-70-03


CVR-30B and CVR-120 Installation Manual NOTES:

1.

ALL WIRES ARE 22 AWG UNLESS SPECIFIED OTHERWISE.

2.

NOT USED.

3.

NOT USED

4.

SINGLE POINT GROUND WITHIN 12" OF 1P1 PIN 17.

5.

ONLY ONE POWER SOURCE CAN BE CONNECTED AT A TIME. CONNECT EITHER 1P1 PIN 2 OR PIN 9, NOT BOTH.

6.

CONNECT EITHER 5V OR 28V, NOT BOTH.

7.

30dB ATTENUATION SHOWN. WIRE ACCORDINGLY. QUIET COCKPITS MAY BE STRAPPED FOR LESS ATTENUATION. ATTENUATION SHOULD BE SUCH THAT THE SIGNAL LEVEL INDICATOR ON THE CONTROL UNIT AND/OR TEST SET ILLUMINATES TWO-THIRDS TO THREE-FOURTHS OF THE LEDS DURING NORMAL CONVERSATIONS.

8.

SQUAT SWITCH CLOSED WITH WEIGHT ON GEAR.

9.

PARK BRAKE SWITCH CLOSED WITH BRAKE SET.

10. WHEN GROUNDED, A 10 MINUTE TIMER IS STARTED. AFTER 10 MINUTES, RECORDING AND ERASURE IS INHIBITED. REMOVAL OF GROUND RESETS TIMER. 11. IF ERASE IS NOT DESIRED, 1P1 PIN 55 MUST BE GROUNDED TO SINGLE POINT GROUND (SEE NOTE 4) OR JUMPERED TO 1P1 PIN 17. 1P1 PIN 57 AND 2P1 PINS G AND H WILL BE LEFT OPEN. 12. WIRING SHOWN IN ACCORDANCE WITH ARINC 757 (SINGLE POINT GROUND WITHIN 12" OF 1P1 PIN 17). HOWEVER, IT IS ACCEPTABLE TO GROUND AUDIO SHIELDS AT THE SOURCE. DO NOT GROUND BOTH ENDS OF SHIELD. 13. SHIELD IS TO BE GROUNDED AT SOURCE. 14. ROTOR SPEED INPUT SPECS; FREQUENCY - 10 TO 15,000 Hz IMPEDANCE = 200 K OHMS .2 VOLTS MIN., 100V MAX. ROTOR SPEED INPUT IS NOT COMPATIBLE WITH ROTOR SPEED ENCODERS DUE TO THEIR HIGH FREQUENCIES. THE CVR ACCEPTS INPUTS DIRECTLY FROM THE ROTOR TACH. 15. INPUT CHAN 1 (EXTRA) CAN BE USED TO ACCEPT FLIGHT DATA RECORDER TONE OUTPUT FOR RECORDER SYNCHRONIZATION. FDR PIN 19 CONNECTS TO CVR PIN 32 AND FDR PIN 20 CONNECTS TO CVR PIN 30. NO STANDARDIZATION OF THE SIGNAL CHARACTERISTICS, LEVELS OR OTHER PARAMETERS OF THE TIMING SIGNAL FROM THE AIRBORNE FLIGHT DATA RECORDER HAS BEEN ADOPTED. IT IS THE INSTALLER’S RESPONSIBILITY TO ASSURE THAT THE FDR TIMING SIGNAL OUTPUT IS COMPATIBLE WITH THE CVR. CVR INPUT LIMITS ARE AS FOLLOWS; LOW FREQ LIMIT = 3607 ± 30 HZ / HIGH FREQ LIMIT = 4193±30 HZ. LEVEL = .5 Vrms TO 2.5 Vrms. TYPE = SINEWAVE OR TRIANGLE

23-70-03



CVR / ARINC Control Unit (P/N 1633-0X) / Aircraft Wiring

23-70-03



1.


2.

NOT USED.

3.

NOT USED.

4.


5.


6.


7.


8.


9.


10. WHEN GROUNDED, A 10 MINUTE TIMER IS STARTED. AFTER 10 MINUTES, RECORDING AND ERASURE IS INHIBITED. REMOVAL OF GROUND RESETS TIMER. 11. IF ERASE IS NOT DESIRED, 1P1 PIN 55 MUST BE GROUNDED TO SINGLE POINT GROUND (SEE NOTE 4) OR JUMPERED TO 1P1 PIN 17. 1P1 PIN 57 AND 2P1 PINS G AND H WILL BE LEFT OPEN. 12. WIRING SHOWN IN ACCORDANCE WITH ARINC 757 (SINGLE POINT GROUND WITHIN 12" OF 1P1 PIN 17). HOWEVER, IT IS ACCEPTABLE TO GROUND AUDIO SHIELDS AT THE SOURCE. DO NOT GROUND BOTH ENDS OF SHIELD. 13. SHIELD IS TO BE GROUNDED AT SOURCE. 14. ROTOR SPEED INPUT SPECS; FREQUENCY - 10 TO 15,000 Hz IMPEDANCE = 200 K OHMS .2 VOLTS MIN., 100V MAX. ROTOR SPEED INPUT IS NOT COMPATIBLE WITH ROTOR SPEED ENCODERS DUE TO THEIR HIGH FREQUENCIES. THE CVR ACCEPTS INPUTS DIRECTLY FROM THE ROTOR TACH. 15. INPUT CHAN 1 (EXTRA) CAN BE USED TO ACCEPT FLIGHT DATA RECORDER TONE OUTPUT FOR RECORDER SYNCHRONIZATION. FDR PIN 19 CONNECTS TO CVR PIN 32 AND FDR PIN 20 CONNECTS TO CVR PIN 30. NO STANDARDIZATION OF THE SIGNAL CHARACTERISTICS, LEVELS OR OTHER PARAMETERS OF THE TIMING SIGNAL FROM THE AIRBORNE FLIGHT DATA RECORDER HAS BEEN ADOPTED. IT IS THE INSTALLER’S RESPONSIBILITY TO ASSURE THAT THE FDR TIMING SIGNAL OUTPUT IS COMPATIBLE WITH THE CVR. CVR INPUT LIMITS ARE AS FOLLOWS; LOW FREQ LIMIT = 3607 ± 30 HZ / HIGH FREQ LIMIT = 4193±30 HZ. LEVEL = .5 Vrms TO 2.5 Vrms. TYPE = SINEWAVE OR TRIANGLE

23-70-03



CVR / Slimline Control Unit (P/N 1634-0X) / Aircraft Wiring

23-70-03



1.


2.

NOT USED.

3.

NOT USED.

4.


5.


6.


7.


8.


9.


10. WHEN GROUNDED, A 10 MINUTE TIMER IS STARTED. AFTER 10 MINUTES, RECORDING AND ERASURE IS INHIBITED. REMOVAL OF GROUND RESETS TIMER. 11. IF ERASE IS NOT DESIRED, 1P1 PIN 55 MUST BE GROUNDED TO SINGLE POINT GROUND (SEE NOTE 4) OR JUMPERED TO 1P1 PIN 17. 1P1 PIN 57 AND 2P1 PINS 32 AND 31 WILL BE LEFT OPEN. 12. WIRING SHOWN IN ACCORDANCE WITH ARINC 757 (SINGLE POINT GROUND WITHIN 12" OF 1P1 PIN 17). HOWEVER, IT IS ACCEPTABLE TO GROUND AUDIO SHIELDS AT THE SOURCE. DO NOT GROUND BOTH ENDS OF SHIELD. 13. SHIELD IS TO BE GROUNDED AT SOURCE. 14. ROTOR SPEED INPUT SPECS; FREQUENCY - 10 TO 15,000 Hz IMPEDANCE = 200 K OHMS .2 VOLTS MIN., 100V MAX. ROTOR SPEED INPUT IS NOT COMPATIBLE WITH ROTOR SPEED ENCODERS DUE TO THEIR HIGH FREQUENCIES. THE CVR ACCEPTS INPUTS DIRECTLY FROM THE ROTOR TACH. 15. INPUT CHAN 1 (EXTRA) CAN BE USED TO ACCEPT FLIGHT DATA RECORDER TONE OUTPUT FOR RECORDER SYNCHRONIZATION. FDR PIN 19 CONNECTS TO CVR PIN 32 AND FDR PIN 20 CONNECTS TO CVR PIN 30. NO STANDARDIZATION OF THE SIGNAL CHARACTERISTICS, LEVELS OR OTHER PARAMETERS OF THE TIMING SIGNAL FROM THE AIRBORNE FLIGHT DATA RECORDER HAS BEEN ADOPTED. IT IS THE INSTALLER’S RESPONSIBILITY TO ASSURE THAT THE FDR TIMING SIGNAL OUTPUT IS COMPATIBLE WITH THE CVR. CVR INPUT LIMITS ARE AS FOLLOWS; LOW FREQ LIMIT = 3607 ± 30 HZ / HIGH FREQ LIMIT = 4193±30 HZ. LEVEL = .5 Vrms TO 2.5 Vrms. TYPE = SINEWAVE OR TRIANGLE

23-70-03


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CVR / Remote Mic Amplifier (P/N 1637-02) / Aircraft Wiring

23-70-03



1.


2.

NOT USED.

3.

NOT USED.

4.


5.


6.

REMOTE MIC AMPLIFIER MUST BE MOUNTED WITHIN THE AIRCRAFT PRESSURE VESSEL (COCKPIT RECOMMENDED) IN A MANNER SUCH THAT AREA MIC WIRES DO NOT EXCEED 15 FEET IN LENGTH. THE SHORTEST WIRE LENGTH POSSIBLE IS DESIRED.

7.


8.

SQUAT SWITCH CLOSED WITH WEIGHT ON GEAR

9.


10. WHEN GROUNDED, A 10 MINUTE TIMER IS STARTED. AFTER 10 MINUTES, RECORDING AND ERASURE IS INHIBITED. REMOVAL OF GROUND RESETS TIMER. 11. IF ERASE IS NOT DESIRED, 1P1 PIN 55 MUST BE GROUNDED TO SINGLE POINT GROUND (SEE NOTE 4) OR JUMPERED TO 1P1 PIN 17. 1P1 PIN 57 WILL BE LEFT OPEN. 12. CVR ERASE AND CVR TEST ANNUNCIATOR SWITCHES AND HEADPHONE JACK ARE PART OF KIT NO 1341. 13. WIRING SHOWN IN ACCORDANCE WITH ARINC 757 (SINGLE POINT GROUND WITHIN 12" OF 1P1 PIN 17). HOWEVER, IT IS ACCEPTABLE TO GROUND AUDIO SHIELDS AT THE SOURCE. DO NOT GROUND BOTH ENDS OF SHIELD. 14. SHIELD IS TO BE GROUNDED AT SOURCE. 15. ROTOR SPEED INPUT SPECS; FREQUENCY - 10 TO 15,000 Hz IMPEDANCE = 200 K OHMS .2 VOLTS MIN., 100V MAX. ROTOR SPEED INPUT IS NOT COMPATIBLE WITH ROTOR SPEED ENCODERS DUE TO THEIR HIGH FREQUENCIES. THE CVR ACCEPTS INPUTS DIRECTLY FROM THE ROTOR TACH. 16. INPUT CHAN 1 (EXTRA) CAN BE USED TO ACCEPT FLIGHT DATA RECORDER TONE OUTPUT FOR RECORDER SYNCHRONIZATION. FDR PIN 19 CONNECTS TO CVR PIN 32 AND FDR PIN 20 CONNECTS TO CVR PIN 30. NO STANDARDIZATION OF THE SIGNAL CHARACTERISTICS, LEVELS OR OTHER PARAMETERS OF THE TIMING SIGNAL FROM THE AIRBORNE FLIGHT DATA RECORDER HAS BEEN ADOPTED. IT IS THE INSTALLER’S RESPONSIBILITY TO ASSURE THAT THE FDR TIMING SIGNAL OUTPUT IS COMPATIBLE WITH THE CVR. CVR INPUT LIMITS ARE AS FOLLOWS; LOW FREQ LIMIT = 3607 ± 30 HZ / HIGH FREQ LIMIT = 4193±30 HZ. LEVEL = .5 Vrms TO 2.5 Vrms. TYPE = SINEWAVE OR TRIANGLE

23-70-03



CVR / Remote Mic Amplifier, Slimline (P/N 1635-02) / Aircraft Wiring

23-70-03



1.


2.

NOT USED.

3.

NOT USED.

4.

SINGLE POINT GROUND WITHIN 12” OF 1P1 PIN 17.

5.

ONLY ONE POWER SOURCE CAN BE CONNECTED AT A TIME. CONNECT EITHER 1P1 PIN 2 OR PIN 9, NOT BOTH. P/N 1601-01-3 USES 28VDC ONLY AND P/N 1601-02-3 USES EITHER 115VAC OR 28VDC.

6.

REMOTE MIC AMPLIFIER MUST BE MOUNTED WITHIN THE AIRCRAFT PRESSURE VESSEL (COCKPIT RECOMMENDED) IN A MANNER SUCH THAT AREA MIC WIRES DO NOT EXCEED 15 FEET IN LENGTH. THE SHORTEST WIRE LENGTH POSSIBLE IS DESIRED.

7.


8.


9.


10. WHEN GROUNDED, A 10 MINUTE TIMER IS STARTED. AFTER 10 MINUTES, RECORDING AND ERASURE IS INHIBITED. REMOVAL OF GROUND RESETS TIMER. 11. IF ERASE IS NOT DESIRED, 1P1 PIN 55 MUST BE GROUNDED TO SINGLE POINT GROUND (SEE NOTE 4) OR JUMPERED TO 1P1 PIN 17. 1P1 PIN 57 WILL BE LEFT OPEN. 12. CVR ERASE AND CVR TEST ANNUNCIATOR SWITCHES AND HEADPHONE JACK ARE PART OF KIT NO. 1341. 13. WIRING SHOWN IN ACCORDANCE WITH ARINC 557 (SINGLE POINT GROUND WITHIN 12” OF 1P1 PIN 17). HOWEVER, IT IS ACCEPTABLE TO GROUND AUDIO SHIELDS AT THE SOURCE. DO NOT GROUND BOTH ENDS OF SHIELD. 14. SHIELD IS TO BE GROUNDED AT SOURCE. 15. ROTOR SPEED INPUT SPECS; FREQUENCY - 10 TO 6000 Hz IMPEDANCE = 200 K OHMS .2 VOLTS MIN., 100V MAX. ROTOR SPEED INPUT IS NOT COMPATIBLE WITH ROTOR SPEED ENCODERS DUE TO THEIR HIGH FREQUENCIES. THE CVR ACCEPTS INPUTS DIRECTLY FROM THE ROTOR TACH. 16. INPUT CHAN 1 (EXTRA) CAN BE USED TO ACCEPT FLIGHT DATA RECORDER TONE OUTPUT FOR RECORDER SYNCHRONIZATION. FDR PIN 19 CONNECTS TO CVR PINS 32 AND FDR PIN 20 CONNECTS TO CVR PIN 30. NO STANDARDIZATION OF THE SIGNAL CHARACTERISTICS, LEVELS OR OTHER PARAMETERS OF THE TIMING SIGNAL FROM THE AIRBORNE FLIGHT DATA RECORDER HAS BEEN ADOPTED. IT IS THE INSTALLER’S RESPONSIBILITY TO ASSURE THAT THE FDR TIMING SIGNAL OUTPUT IS COMPATIBLE WITH THE CVR. CVR INPUT LIMITS ARE AS FOLLOWS; LOW LIMIT = 3607 ± 30 Hz / HIGH LIMIT = 4193 ± 30 Hz. LEVEL = .5 Vrms TO 2.5 Vrms. TYPE = SINEWAVE OR TRIANGLE

23-70-03



8.

Pin Out Charts

A.

CVR Pin Out CVR P/N 1603-02-XX / 1P1

Pin

Function

1

CVR P/N 1603-02-XX / 1P1 - Cont’d Pin

2

115 VAC Input

29

3

Power Ground

30

4

Function INPUT Chan 1 (Extra) - Lo

31

5

Audio Out - Lo

32

6

Audio Out - Hi

33

7

Record On Strap (To Pin 8)

34

8

Record On Strap (To Pin 7)

35

9

+27.5 VDC Input

36

10

Stop Record

37

11

INPUT Chan 1 (Extra) - Hi

INPUT Chan 2 (Copilot) - Lo INPUT Chan 2 (Copilot) - Hi

38

12

Push To Test

39

OMS Input (B)

13

Preamp Power Ground

40

OMS Input (A)

14

Preamp Power - + 15 VDC

41

INPUT Chan 3 (Pilot) - Lo

15

Indicator +

42

16

Indicator -

43

17

Chassis Ground

44

INPUT Chan 3 (Pilot - Hi

18

45

19

46

20

47

INPUT Chan 4 (Area Mic) - Hi

21

48

Rotor Speed - Lo

22

49

Rotor Speed - Hi

INPUT Chan 4 (Area Mic) - Lo

23

Fault CVR (norm low)

50

OMS Out (B)

24

Fault FDR

51

OMS Out (A)

25

GMT Input (B)

52

26

GMT Input (A)

53

27

54

28

55

Continued -

Erase ‘A’

56 57

Erase ‘C’

23-70-03



Control Unit, ARINC P/N 1633-0X Pin Out

Control Unit P/N 1633-0X / 2P1 Pin

Control Unit P/N 1633-0X / 2P1- Cont’d

Function

Pin

Function

A

Push-To-Test

B

Ground

a

Spare

C

+15 VDC

b

Lighting - +28 VDC

D

Indicator +

c

Area Mic 2 Input - Signal

E

Indicator -

d

Area Mic 2 Input - Bias

F

Chassis Ground

e

Area Mic 2 Input - Shield Gnd

G

Erase ‘A’

f

Internal Mic - Lo

H

Erase ‘C’

g

Internal Mic - Hi

h

J K

INPUT Chan 4 Audio Out - Lo

i

L

INPUT Chan 4 Audio Out - Hi

j

M


k

N


l

P


Spare

m

Q

n

R

o

S

p

Attenuation - 6 dB

T

q

Attenuation - COM

U

r

Attenuation - 12 dB

V

Headphone Audio - Lo

s

W

Headphone Audio - Hi

t

X

Spare

Y

Lighting - +5 VDC

Z

Lighting - COM

Attenuation - 24 dB

Continued -

23-70-03



Control Unit, ARINC P/N 1632-0X Pin Out


Control Unit P/N 1632-0X / 2P1- Cont’d

Function

Pin

Function

A

Push-To-Test

B

Ground

a

Spare

C

+15 VDC

b

Lighting - +28 VDC

D

Indicator +

c


E

Indicator -

d


F

Chassis Ground

e


G

Erase ‘A’

f

H

Erase ‘C’

g h

J K

Chan 4 Audio Out - Lo

i

L

Chan 4 Audio Out - Hi

j

M


k

Spare

N

l

P

m

Q

n

R

o

S

p

Attenuation - 6 dB

T

q

Attenuation - COM

U

r

Attenuation - 12 dB

V


s

W


t

X

Spare

Y

Lighting - +5 VDC

Z

Lighting - COM

Attenuation - 24 dB

Continued -

23-70-03



Control Unit, Slimline P/N 1634-0X Pin Out


Function

1 2


3


4


5

Reserved

6

Reserved

7

Pass Lo

8

Fail Lo

9


10


11

Indicator -

12

Indicator +

13

Spare

14 15 16

Chassis Ground

17

Ground

18

+15 VDC

19 Continued -

Control Unit P/N 1634-0X / 2P1- Cont’d Pin

Function

20


21


22


23

Attenuation COM

24

Attenuation 6 dB

25

Attenuation 12 dB

26

Attenuation - 24 dB

27


28


29 30

Push-To-Test

31

Erase ‘C’

32

Erase ‘A’

33

Lighting +28 VDC

34

Spare

35

Lighting COM

36

Lighting +5 VDC

37

Spare

23-70-03


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Remote Mic Amplifier, ARINC P/N 1637-02 Pin Out

Remote Mic Amplifier P/N 1637-02 Pin

Function

Remote Mic Amplifier P/N 1637-02- Cont’d Pin

A B

Ground

a

C

+15 VDC

b

D

Indicator +

c

E

d

F

e

G

f

H

g

J

h

Function

K


i

Pass Lo

L


j

Fail Lo

M


k

N


l

P


m

Q

n

R

o

S

p

Attenuation - 6 dB

T

q

Attenuation - COM

U

r

Attenuation - 12 dB

V

s

5 VDC Output

W

t

Attenuation - 24 dB

X Y Z Continued -

23-70-03



Remote Mic Amplifier, Slimline P/N 1635-02 Pin Out

Remote Mic Amplifier P/N 1635-02 / 2P1 Pin

Function

1

Remote Mic Amp P/N 1635-02 / 2P1- Cont’d Pin

Function

20


2


21


3


22


4


23

Attenuation COM

5

Reserved

24

Attenuation 6 dB

6

Reserved

25

Attenuation 12 dB

7

26

Attenuation - 24 dB

8

27

Headphone Audio - Lo Headphone Audio - Hi

9


28

10


29

11

Indicator -

30

Push-To-Test

12

Indicator +

31

Erase ‘C’

13

Spare

32

Erase ‘A’

14

33

Lighting +28 VDC

15

34

Spare

16

Chassis Ground

35

Lighting COM

17

Ground

36

Lighting +5 VDC

18

+15 VDC

37

Spare

19 Continued -


23-70-03



Maintenance, Checkout and Troubleshooting 1.

Maintenance CVR Maintenance includes Periodic Inspections of the CVR and Underwater Locator Beacon (ULB) as well as Servicing/Maintenance of the ULB.

A.

Periodic Inspections/Overhaul CVR Periodic Inspection consists of the required preflight self test. Only if a self test fails, is maintenance need on the CVR. (1)

CVR Overhaul

Because of the solid state technology used in the CVR, there is no need for periodic overhaul of the CVR. MTBF has been established at 30,000 hours. (2)

Underwater Locator Beacon Periodic Inspection

NOTE:

The following inspections are dictated by the Dukane Technical Manual. INSPECTION INTERVAL

TASK

24 Months

1. Clean ULB Beacon Switch 2. Perform ULB Beacon Test 3. Perform ULB Battery Test

6 Years

B.

1. Replace ULB Beacon Battery

Underwater Locator Beacon Servicing / Maintenance The CVR utilizes the Dukane Model DK120 underwater acoustic beacon which is manufactured under a Parts Manufacturer Approval (PMA) and is authorized by FAA TSO-C121. The beacon is attached to the recorder environmental shell for easy removal and for easy viewing of the battery expiration date. The battery in the Model DK120 has a life of six years. The battery is user replaceable. Refer to Technical Manual, Underwater Acoustic Beacon, DK100/DK120 for maintenance and battery replacement. Contact Dukane for details.

23-70-03



2.

Post-Installation Checkout Procedure NOTE:

•

It will be helpful if the following checkout procedures are copied, filled out and presented along with other supporting documents when applying for approval. Permission is hereby granted to copy this portion of this manual.

•

The following procedures are written for installation with Control Unit P/N 1632-0X, 1633-0X or 1634-0X. On installations utilizing Remote Mic Amplifier P/N 1635-0X or 1637-0X and Annunciator/Switch Kit P/N 1341, disregard all references to SIGNAL LEVEL Indicator.

The CVR Self Test gives an indication of the Pass or Fail condition. During Self Test, the following occurs: (1)

A test tone will be recorded onto all six channels and then followed by a period of silence. Items tested during the self test include; power supply voltages, ARINC 429 Built In Test Equipment (BITE), ARINC 429 Onboard Maintenance System(OMS) receiver, FSK GMT receiver, EPROM checksum and rotor speed receiver.

(2)

The test tone and silence is then automatically played back and read internally.

(3)

The PASS or FAIL LED will then illuminate for 10 seconds. The SIGNAL LEVEL Indicator will also illuminate for 10 seconds with the FAIL LED.

After installation is accomplished and all wiring, power sources and audio interface is verified, apply power to the system. Self Test (1)

Don headset and plug into the control unit headphone jack.

(2)

Press the control unit TEST Button firmly for at least two seconds and release. This initiates the CVR Self Test.

(3)

During self test the PASS and FAIL LEDs will illuminate alternately indicating that self test is in progress. Self test takes approximately 15 seconds to perform. After 10 seconds of self test, cockpit conversation should be heard through the headset and visible on the SIGNAL LEVEL Indicator. The test tone audio will be heard. No audio will be recorded during self test.

NOTE:

Self test will not initiate if the erase feature is in progress. Self test will not function if Stop Record is initiated. When power is removed and then applied to the CVR, if “STOP RECORD” is active, it will be ignored. “STOP RECORD” must go from an inactive to active condition to be properly recognized. This means that the CVR will immediately start to record upon application of power if “RECORD ON” is ON and “GND EQ INTLK” is OFF, regardless of the condition of “STOP RECORD”.

23-70-03


CVR-30B and CVR-120 Installation Manual (4)

Upon completion of a successful self test, the PASS Light will illuminate for approximately ten seconds then go out. A failed self test will be indicated by an illuminated FAIL Light (usually flashing). The flashing FAIL Light indicates the nature of the failure. FAIL will flash a number of times, pause, and then repeat that same number of flashes. The following table shows the fail condition based on the number of FAIL flashes. Number of FAIL flashes

FAIL Light

PASS Light

None

Pass

Off

On

1

Channel 1 fail

On

Off

2

Channel 2 fail

On

Off

3

Channel 3 fail

On

Off

4

Channel 4 fail

On

Off

5

Flash Memory Fail

On

Off

Steady (10 secs)

General failure (Note 1)

On

Off

Alternating

System test in progress

Alternating

Alternating

Simultaneous

Bulk Erase

Simultaneous

Simultaneous

NOTE:

(5)

CVR Condition

1.

General failure is a misc. failure of Ch. 5, 6, FSK, Rotor Speed, ARINC Channels, etc. The BITE Status code indicates which function has failed. Please contact Universal Avionics for assistance with determining a particular BITE Status failure indication.

Should self test fail and it is desired to perform another self test, the TEST Button must be pressed firmly for at least one second to engage self test.

Erase (if applicable) (1)

Open squat switch and parking brake switch (air mode) (and/or any other interlock switches).

NOTE: The ERASE Button is usually interlocked through a weight-on-wheels and/or parking brake circuit to prevent the inadvertent erasure unless the aircraft is on the ground with the parking brake set. (2)

Press ERASE Button for five seconds and then release. Erase shall not occur.

(3)

Close squat switch and parking brake switch (and/or any other interlock switches).

(4)

Press ERASE Button for five seconds and then release to engage erase.

(5)

During the erase process the PASS and FAIL Lights will flash simultaneously and the SIGNAL LEVEL indicator will modulate with cockpit audio. Erase takes approximately 10 seconds.

23-70-03



3.

Preflight Ground Checkout Procedure Ground checkout of the CVR is accomplished using the Test Set (P/N 1623-01) and an RS232C ANSI compatible terminal or any personal computer with a software package capable of emulating a VT100 type terminal. The terminal or computer must be set up to communicate at 9600 baud, 8 data bits, no parity and one stop bit (8N1). The interconnection between the CVR and the computer terminal is through a RS-232 type electrical interface. The Test Set Harness has five connectors; one 25 pin DB-25 connector to connect to the CVR, a nine pin DB-9S (socket) connector for connection to the computer terminal, a 57 pin ARINC Connector to connect to the CVR rear connector, another ARINC connector for future use, a nine pin DB-9S socket for future use, and a connector to connect to the cockpit control unit. If the terminal to be used has a 25 pin connector, then a 9 pin-to 25 pin adapter plug must be used. CVR operation is controlled and monitored from the computer terminal. The ground test set and harness consists of an audio control unit and a wire harness. The computer terminal display is divided into an upper and lower portion. The upper portion of the screen displays status and parameter fields while, the lower portion displays commands available for entry using the terminal keyboard. Read and become familiar with TEST SET AND HARNESS paragraphs before proceeding with the following checkout procedures.

NOTE:

•

It will be helpful if the following checkout procedures are copied, filled out and presented along with other supporting documents when applying for approach.

•

In order to assure easy analysis of the recording, it is important that adequate commentary is provided during testing. Each test shall be clearly announced and the crew members identified.

•

Test time should be limited to less than 30 minutes (the length of the recording capability). Durations longer than 30 minutes will result in the overwriting of the first part of the test on the 30 minute channels.

•

After post installation is found satisfactory, a preflight ground checkout is required.

REAR CONNECTOR

FRONT CONNECTOR

ARINC 404 HARNESS

DB25 HARNESS CVR-30B or CVR-120

9-PIN CONN HARNESS TEST SET (P/N 1623-01)

TERMINAL (RS232 ANSI COMPATIBLE)

28 VDC POWER SOURCE

TAPE RECORDER

POWER SOURCE

1623-01 Test Set Connections

23-70-03


CVR-30B and CVR-120 Installation Manual A.

Checkout Procedures WARNING:

USE ONLY P/N 1623-01 TEST SET AND HARNESS FOR CVR TESTING. FAILURE TO COMPLY COULD DAMAGE THE CVR AND VOID THE WARRANTY.

NOTE:

Refer to the wiring diagrams and information inside the lid on the Test Set, it will be helpful when connecting the Test Set to the CVR. MECH

(1)

With all power removed from the aircraft, gain access to the Cockpit Recorder Unit.

(2)

Verify the following switch positions on the Test Set: a)

TEST SET POWER - Off

b)

CHANNEL SELECT Switches

INSP

PA - Off COPILOT - Off PILOT - Off MIXED - Off AREA MIC - Off HI-FI AREA MIC - Off c)

GND EQ INTLK - On

d)

REC ON - On

e)

24dB, 12dB and 6dB - Off

f)

All other switches - Off

(3)

Connect the test set and harness (P/N 1623-01) to the recorder unit front connector.

(4)

Connect an RS232C compatible terminal to the test set harness nine pin connector.

(5)

Set SPKR/HEADSET VOLUME to approximate mid-range.

(6)

Apply power to the terminal and turn it on, then apply aircraft power to the CVR, then set the TEST SET POWER switch to ON (the Test Set receives power from the CVR).

NOTE:

A three-second delay in screen display change is normal between the CVR and some personal computers.

(7)

On the computer, type in 5 (Self Test) and ENTER to initiate self test.

(8)

Self test will take approximately 15 seconds to perform. During self test, the PASS and FAIL Lights on the CVR controller will alternately illuminate. MODE on the terminal screen will read SELF TEST. OPERATION will read TESTING. No incoming audio will be recorded during self test.

23-70-03



MECH (9)

INSP

At the end of a successful self test, the MODE will read “RECORD” and OPERATION will become “STOP”.

(10) TEST RESULTS will be displayed as follows; a) Audio Ch1, Ch2, Ch3, Ch4, Ch5 and CH 6 will read PASS. b) Flash Memory will read OK. c) Power supply will read PASS. (11) Position a person at each crew station in the aircraft. (12) On the computer, press E. Reset Elapsed Time. (13) Write down (in the space provided below) the Channel 1 number from the screen. RECORD = (14) On the computer, type in 1 (Record) and ENTER to initiate recording. (15) From each crew station, announce “Area Mic Test” as well as the time and date. Announcements should be made looking left, forward and right. (16) From each crew station, announce and test each function of the audio panel/mic jack including comm radios, interphone and crosstalk. (17) Activate and announce aural warnings. (18) Announce end of test and time. (19) On the computer, type in 3 (Stop) and ENTER. (20) Remove CVR from aircraft and connect to Test Set with the DB connector and the 57 pin CVR cable. (21) Assure that CHANNEL SELECT, COPILOT, PILOT, MIXED and AREA MIC switches are set to OFF. (22) Connect 28 VDC to the Test Set. (23) Set the CHANNEL SELECT PA to ON. (24) Set REC ON Switch OFF. (25) Type in 2 (Play) and press ENTER. (26) On the computer, press R (Reverse) to return to the Record Number written down in Step 13 above, then type in 3 (Stop) and press ENTER.

NOTE:

Pressing R on the terminal will cause the Record counter to reverse about 3 seconds per keystroke. Holding R down will accelerate this process. In order to reverse or forward, Mode must be in PLAY.

23-70-03



MECH

INSP

(27) Type in 2 (Play) and press ENTER. (28) Verify that the appropriate announcements and tests are on Channel 1 (PA) and that conversation is intelligible. (29) Press R (Reverse) to return to the beginning of the recording. (30) On the computer, type in 3 (Stop) and press ENTER. (31) Repeat steps 23 thru 30 for Channels 2, 3, 4, 5 and 6 using the appropriate CHANNEL SELECT Switches. (32) On the computer, type 4 (Bulk Erase) and press ENTER. (33) Verify that Bulk Erase process occurs. (34) Type in 3 (Stop) and press ENTER. (35) Remove all power and disconnect Test Set and computer from recorder. (36) Secure all equipment in preparation for flight checkout.

23-70-03



4.

Flight Checkout Procedure It is common practice for local certifying agencies to require a recorded tape of the CVR flight checkout procedure. The P/N 1623-01 CVR Test Set incorporates six high level audio output jacks which can be used to transfer the Flight Checkout onto tape via an audio mixer. The recording is transferred onto tape during the postflight portion of the Flight Checkout procedure. NOTE:

•

It will be helpful if the following checkout procedures are copied, filled out and presented along with other supporting documents when applying for approval.

•

Flight time should be limited to less than 30 minutes. Any duration longer than 30 minutes will result in overwrite of the first part of the checkout.

Once the Ground Checkout Procedure is completed satisfactorily, the following Flight Checkout Procedure is to be performed. NOTE:

A.

B.

In order to assure easy analysis of the recording it is important that adequate commentary is provided during the flight, e.g., crew actions, speed, altitude and equipment operation. Each test shall be clearly announced in a normal speaking voice and the crew member identified. Cockpit speakers should be set to the normal volume.

Prior To Engine Start (1)

Engage cockpit voice recorder circuit breaker.

(2)

Don headsets and boom microphones.

(3)

Perform CVR self test.

(4)

Select boom microphone and interphone ON at all positions

(5)

Announce aircraft type, registration, date, time and crew.

MECH

INSP

MECH

INSP

Engine Start (1)

On rotorcraft only, during rotor spin-up, announce RPM at 50%, 80% and 100%.

(2)

With interphone on, make an announcement from each crew member position.

(3)

With interphone off, make an announcement from each crew member position.

(4)

Repeat steps (2) and (3) using the oxygen mask microphone.

(5)

Test stall warning stick shaker and announce (if applicable).

(6)

Cockpit windows closed (if applicable).

23-70-03



Take-Off (1)

Turn interphone on.

(2)

Announce a normal take-off and initial climb.

(3)

Announce landing gear, flap and other selections.

(4)

With interphone off, activate and announce aural warnings.

(5)

Turn interphone back on.

(6)

Accelerate to normal cruise speed.

(7)

Announce from each crew station, name, altitude, and airspeed. Announcements should be made looking left, forward and right.

(8)

Activate, and announce aural warnings.

(9)

Each crew member should verify selections of comms and navaids on their respective audio control panel and perform a communications check using comms, interphone and P/A.

MECH

INSP

MECH

INSP

(10) Accelerate to maximum cruise speed. (11) Announce from each crew station, name, altitude and airspeed. Announcements should be made looking let, forward and right. (12) Activate and announce aural warnings.

D.

Landing (1)

Announce landing events such as final approach, ILS marker audio ID, landing gear selection, flap selection, etc.

(2)

At the end of taxi, announce the time.

(3)

Using the boom microphone with interphone on at all positions, announce end of test.

CAUTION:

(4)

FAILURE TO PULL CVR CIRCUIT BREAKER COULD RESULT IN A COMPLETE OVERWRITE OF THE FLIGHT TEST RECORDING IF THE CVR IS STILL POWERED AFTER LANDING.

Pull CVR Circuit Breaker (Do not erase).

23-70-03



Postflight Using the Test Set (P/N 1623-01) along with a compatible terminal, perform the following; WARNING:

USE ONLY P/N 1623-01 TEST SET FOR CVR TESTING. FAILURE TO COMPLY COULD DAMAGE THE CVR AND VOID THE WARRANTY.

NOTE:

Test set P/N 1623-01 incorporates six high level audio out jacks. These unswitched outputs can be used to transfer the Flight Checkout onto tape via an audio mixer.

(1)

With all power removed, gain access to the recorder unit and remove it from the aircraft.

(2)

Verify that the test set POWER Switch is OFF.

(3)

Connect +28 VDC and ground leads from power supply to Test Set +28V and GND jacks.

(4)

Connect the test set and harness (P/N 1623-01) to recorder unit front and rear connectors.

(5)

Connect an RS232C compatible terminal to the test set harness nine pin connector.

(6)

Set test set SPKR/HEADSET VOLUME to approximate mid range.

(7)

Set GND EQ INTLK Switch ON.

(8)

Set STOP REC Switch ON.

(9)

Set REC ON Switch ON.

(10) Set EXT CVR-FDR PWR Switch ON. (11) Set the TEST SET POWER switch to ON. (12) Type in 3 (Stop) and press ENTER. (13) Write down (in the space provided below) the Record number from the upper portion of the screen. RECORD = (14) Set CHANNEL SELECT Switches, except PA, to OFF. (15) Verify that CHANNEL SELECT PA Switch is ON. (16) Type in 2 (Play) and press ENTER. (17) On the computer, press R (Reverse) to return to the Record Number recorded in step (9) above, then type in 3 (Stop) and enter. NOTE:

•

Pressing R on the terminal will cause the Record counter to reverse 3 seconds per keystroke. Holding R down will accelerate this process. In order to reverse or forward. Mode must be in PLAY.

•

On rotorcraft, during the following tests, note rotor speed frequency on the computer screen as RPM is announced by the crew. The rotorcraft manufacturer must be contacted for the Hz to RPM conversion factor for RPM verification.

(18) On the computer, type in 2 (Play) and press ENTER. (19) Verify that the appropriate announcements and tests are on the PA Channel and that conversation is intelligible. (20) Press R (Reverse) to return to the beginning of the recording. (21) On the computer type in 3 (Stop) and press ENTER. (22) Repeat step (14) thru (21) for COPILOT, PILOT, MIXED, AREA MIC and HI-FI AREA MIC Channels.

23-70-03


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CVR-30B and CVR-120 Installation Manual (23) Type in 3 (Stop) and press ENTER. (24) Remove all power and disconnect all equipment from the CVR. (25) Reinstall the CVR into the aircraft.

5.

Test Set (P/N 1623-01) The Test Set (P/N 1623-01) is used in conjunction with a computer terminal to accomplish the post installation checkouts. WARNING:

USE ONLY P/N 1623-01 TEST SET FOR CVR TESTING. FAILURE TO COMPLY COULD DAMAGE THE CVR AND VOID THE WARRANTY.

Specific operation of the Test Set is contained in the checkout procedures in this manual. Ground checkout of the CVR is accomplished using the Test Set (P/N 1623-01) and an RS232C ANSI compatible terminal or any PC terminal with a software package capable of emulating a VT100 type terminal. The terminal or computer must be set up to communicate at 9600 baud, 8 data bits, no parity and one stop bit (8N1). The interconnection between the CVR and the computer terminal is through a RS-232 type electrical interface. CVR operation is controlled and monitored from the terminal. The Test Set harness has five connectors; one DB-25 connector to connect to the CVR, a DB-95 connector to connect to the computer terminal (an adapter must be used if the terminal has a 25-pin connector), a 57-pin ARINC connector to connect to rear of the CVR, another ARINC connector for future use, a DB-9S socket for future use, a DB-9S socket for future use, and a connector to connect to the cockpit control unit. All audio heard when using the test set will be playback audio only. No active audio will be heard. Similarly, playback audio will not be heard in the cockpit when using the Test Set. No audio is recorded during self test.

REAR CONNECTOR

FRONT CONNECTOR

ARINC 404 HARNESS

DB25 HARNESS

CVR-30B or CVR-120

9-PIN CONN HARNESS

TEST SET (P/N 1623-01)

TERMINAL (RS232 ANSI COMPATIBLE)

28 VDC POWER SOURCE

TAPE RECORDER

POWER SOURCE

1623-01 Test Set Connections

23-70-03


CVR-30B and CVR-120 Installation Manual A.

Test Set Features (Refer to the Test Set Panel Layout figure) (1)

CHANNEL SELECT Switches - Six channel select switches allow selection or deselection of each of the six channels. This allows selection of playback of individual or any combination of channels to the high level audio output jacks and the speaker.

(2)

SIGNAL LEVEL Indicator - The ten segment bar graph on the Test Set remains active during both record and playback when the CTRL UNIT EXT/OFF/INT slide switch is in the INT position and when the GND EQ INTLK push-button switch is ON. During playback, the bargraph will flash about once per second when playing out previously recorded FSK data, and will indicate the playback audio for a particular channel when selected with the CHANNEL SELECT push-buttons.

(3)

SPKR/HEADSET VOLUME Adjustment - The speaker volume adjusts the level of audio to the Test Set speaker. The CHANNEL SELECT push-buttons determine which channel or channels will be applied to the speaker.

(4)

LO LEVEL AUDIO OUT for Cassette Recorder - This low level (10-20mV) output jack is for connection to a cassette recorder. The jack outputs any of the channels as selected by the CHANNEL SELECT Switches. The six channel output is adjustable by using the LVL ADJUST Potentiometer.

(5)

HI LEVEL AUDIO OUT - This high level (330mV) jack is for connection to the line input of a stereo recorder via an RCA jack. The jack outputs any of the six channels as selected by the CHANNEL SELECT Switches.

(6)

HEADSET Jack - When a headset is used in lieu of the test set integral speaker, plugging the headset into the jack will mute the integral speaker.

(7)

SCOPE OUTPUT - A coaxial connector exists to be used in applications where it is desirable to monitor audio output with an oscilloscope or a voltmeter. This is normally an overhaul facility application.

(8)

HI-LEVEL AUDIO OUTPUTS - These six unswitched jacks provide unswitched outputs for transferring CVR recording onto a tape via an audio mixer. The jacks are labeled PA, COPILOT, PILOT, MIXED, AREA MIC and HI-FI AREA MIC.

(9)

TEST SET POWER Switch - This switch applies power to all of the internal electronics of the Test Set and must be ON when using the Test Set. The Test Set power comes from the CVR-120/30B through the DB25 connector on the front of the CVR. This switch does not effect power to the CVR.

(10)

Speaker - The speaker is provided to listen to playback audio from the CVR. Selection of which channel to listen to is provided by the CHANNEL SELECT push-button switches to the right of the HI LEVEL AUDIO OUT jack on the Test Set.

(11)

GND EQ INTLK Switch - This push-button switch informs the CVR that the Test Set has been connected. This switch must be illuminated (ON) when using the Test Set with the CVR, even when the CVR is installed on an aircraft. When the CVR is installed on an aircraft and connected to the Test Set, this push-button switch, when ON, will inhibit CVR recording after applying power to the CVR.

(12)

REC ON Switch - This switch must also be ON when recording test speech or tones from the Test Set when the CVR is connected to the Test Set and not installed on an aircraft. When this switch is OFF, recording from the Test Set is inhibited, and bulk erase is not allowed. In addition, when this switch is ON, playback is inhibited. Recording and playback of audio to/from the Test Set is always inhibited when the CVR is installed on an aircraft.

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recording, will start a STOP REC Switch Switch - With this switch placed to the ON position, while previously recording, ten minute timer that will terminate recording after the timer expires. This push-button switch setting is ignored when power is first applied applied to the CVR. In other words, the CVR must see this switch go from the inactive to the active position in order to be properly recognized. recognize d. When the CVR is installed on an aircraft, the STOP REC switch on the Test Set has no effect on CVR operation.

(14)

LOOP BACK Switch Switch - This push-button push-button switch, when placed to the ON position with the Test Set connected to the CVR, will indicate to the CVR that external loopback testing of the unit is desired. Individual tests tests can be selected at the terminal. Signals are actually transmitted transmitted out of the CVR through the Test Set and back into the CVR to complete the “loop” test. Signals tested during Loop Back are; all four audio input channels, FSK, rotor speed, and all of the ARINC 429 transmit and receive channels. When the CVR is installed in the aircraft, the LOOP BACK switch has no effect on CVR operation.

(15)

initiates a self test when the CONTROL UNIT INT/OFF/EXT TEST Switch Switch - This momentary switch initiates switch has been set to INT, and is identical to pushing the TEST switch switch on an external control unit. All testing is confined confined within the CVR when the the LOOP BACK switch is OFF. When the LOOP BACK switch is ON the test signals are routed through the Test Set in order to test pin and cable continuity. If an external control unit is connected to the Test Set and properly connected to the CVR and the CTRL UNIT INT/OFF/EXT slide switch has been set to EXT, the TEST switch on the external control unit can be pressed to initiate a test. When the CVR is installed on an aircraft, the TEST switch has no effect effect on CVR operation.

(16)

DELAYED REC INHB Switch Switch - This switch is not used for testing of the CVR-120/30B.

(17)

BULK ERASE Switch Switch - If the CTRL UNIT INT/OFF EXT switch has been set to INT, REC ON is ON and STOP REC has not timed out (10 minutes), this momentary push-button switch will initiate a bulk erase of the entire flash memory memory array, assuming that GND EQ INTLK is ON. This switch emulates the Bulk Erase switch on an external control control unit. If an external control unit unit is connected to the Test Set and the Test Set is properly connected to the CVR, the BULK ERASE switch on the external control unit can be pressed to initiate a bulk erase. erase. When the CVR is installed on an aircraft, aircraft, the BULK ERASE switch has no effect on CVR operation.

(18)

MONITOR Switch Switch - This push-button switch selects mixed audio to be tested on the Test Set’s bar graph from two possible sources; 1) mixed audio that drives the headset jack on an external control unit, or 2) mixed audio that drives the bar graph on an external control unit. When the CVR is installed on an aircraft, the MONITOR switch has no effect on CVR operation.

(19)

24dB, 12dB and 6dB Attenuation Switches Switches - These push-button switches select attenuation settings for the Test Set’s mic amplifier when the CONTROL UNIT INT/OFF/EXT switch has been set to INT, and for an external control unit’s mic amplifier when properly connected to the Test Set with the cable provided and the CTRL UNIT INT/OFF/EXT switch set to E XT.

(20)

CTRL UNIT Switch: INT Position Position - Selects the Test Set’s internal control unit for test recording of speech. control unit. Therefore, audio signals signals picked up by the internal internal OFF Position - No selection of a control microphone in the Test Set will not interfere with any other testing that is being performed. external control unit unit connected to the the Test Set for testing. testing. The external EXT Position - Selects an external control unit must be connected to the Test Set with the cable provided.

(21)

FSK IN/OUT Coax Connector Connector - This jack allows the connection of an external FSK signal for testing purposes. The FSK input signal can be either a sinewave sinewave or triangle wave of 3607 Hz or 4193 Hz. During normal playback of audio during storage retrieval, this jack is used to play back the previously recorded time data in an FSK analog format. The analog output level is approximately 1 Vrms sinewave at a rate of once per second, regardless of the recorded rate. When the CVR is installed installed on an aircraft, the FSK IN/OUT jack has no effect on CVR operation.

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RTR SP IN/OUT Coax Connector Connector - This jack allows the connection of an external rotor speed signal from 10 Hz to 15,000 Hz for testing purposes. The input sinewave can be in the range of 100 mV to 1 Vrms. During normal playback playback of audio during storage storage retrieval, this jack is used to play back back the previously recorded rotor speed data in an analog format. The output level is about 1 Vrms. When the CVR is installed on an aircraft, the RTR SP IN/OUT jack has no effect on CVR operation.

(23)

TEST INPUTS - PA, COPILOT, PILOT and AREA MIC Coax Connectors - These four input jacks provide a means of connecting an external signal to each of the four CVR audio input channels for audio recording test purposes.

(24)

AREA MIC Switch Switch - This push-button switch selects the Lo-Fi Area Mic output audio from the CVR to be connected to the Test Set’s HI LEVEL AUDIO OUT jack, HEA DSET jack, LO LEVEL AUDIO OUT jack, SCOPE jack, and the Test Set’s internal speaker for testing. testing. If any of the other push-button push-button switches (e.g., PA, COPILOT, PILOT, MIXED, AREA MIC) are ON, the audio signal from these channels will be mixed with the Lo-Fi Area Mic audio output from the CVR.

(25)

HI-FI AREA MIC Switch Switch - This push-button selects the Hi-Fi Area Mic audio output from the CVR to be connected to the Test Set’s HI LEVEL AUDIO OUT jack, HEA DSET jack, LO LEVEL AUDIO OUT jack, SCOPE jack, and the Test Set’s internal speaker for testing. testing. If any of the other push-button push-button switches (e.g., PA, COPILOT, PILOT, MIXED, AREA MIC) are on, the audio signal from these channels will be mixed with the Hi-Fi Area Mic audio output from the CVR.

(26)

MIXED Switch Switch - This push-button selects the mixed audio output from the CVR, which consists of PA/Copilot/Pilot PA/Copilot/Pilot audio to be connected to the Test Set’s HI LEVEL AUDIO OUT jack, HEADSET jack, LO LEVEL AUDIO OUT jack, SCOPE jack and the Test Set’s internal internal speaker for for testing. If any of the other push-button push-button switches (e.g., PA, COPILOT, PILOT, MIXED, AREA MIC) are O N, the audio signal from these channels will be mixed with the mixed audio output from the CVR.

(27)

PASS and FAIL Indicators Indicators - These LEDs indicate various test conditions conditions and are identical to the indicators on an external external control unit. The CTRL UNIT INT/OFF/EXT slideswitch must be in the INT position for these indicators to function.

(28)

EXT CVR-FDR PWR Switch Switch - Applies 28 VDC power to the CVR when the CVR is connected to the Test Set via the rear connector. Power is applied to the CVR regardless regardless of the position of the TEST SET PWR switch setting. setting. Power cannot be applied from the Test Set to the CVR when the connector connector on the front panel of the CVR alone is connected to the the Test Set. This switch has no affect when the CVR is installed on an aircraft or receives its power from another source.

(29)

+28VDC and GND Jacks Jacks - These jacks allow an external power supply to power the CVR when the Test Set is connected to the CVR rear connector. connector. The power supply must be able to provide provide about 800mA of continuous current with an initial power on surge of about 1.5 amps. The CVR draws about 400mA and the Test Set and external control unit draw about 200mA each, depending on how many switches and segments on the bar graph are illuminated. A power supply connected to these jacks will not power the CVR when installed on an aircraft because the CVR is receiving its power from the aircraft and not the Test Set.

(30)

FDR DATA Switch Switch - The Flight Data Recorder switch is a future provision however, it must be set to the 64W position.

(31)

INT MIC MIC - The Test Set internal microphone is used to input recorded speech to the CVR via the Test Set.

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Test Set Panel Layout

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ANSI Terminal Interface In addition to the features described above, the test set and harness, when connected to an RS232C ANSI terminal (or any PC with a software package capable of emulating a VT100 type terminal), includes the following features which can be seen and controlled on the terminal. The terminal screen is divided into an upper portion and a lower portion. The upper portion provides information while the lower portion indicates the various modes.

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CVR-30B and CVR-120 Installation Manual Upper Portion of Screen: (1)

MODE - Displays the active mode; record, playback, self test, bulk erase and calibration.

(2)

OPERATION - Displays the current operation; recording, playing, stopped, erasing, testing and calibration.

(3)

ELAPSED TIME - Displays in hours: minutes: seconds. The elapsed timer is reset using ‘R’ command on the keyboard.

(4)

ROTOR SPEED - Rotor speed is displayed in Hz when a valid rotor speed input is provided. When there is no rotor speed input, it will read - - - -Hz.

(5)

RECORD - This number is used to find a specific spot on the recording.

(6)

RECORD HOURS - Displays the total number of hours that the recorder has accumulated. Used for inspection/maintenance purposes.

(7)

SELF TEST RESULTS - Self Test results for CVR Fault, Flash Memory, Power Supply and Audio. CVR FAULT - Will display “ON” or “OFF”. Flash Status - Will display either OK or FAIL. Power Supply Test - Will display either PASS or FAIL as well as power supply voltages for +5V, filtered +5V, -5V, +12V, -12V and Input Voltage. Audio Test - Each of the six channel fields will display either PASS or FAIL. DUART Inputs - Not used by field installation personnel. Para Inputs - Not used by field installation personnel.

(8)

Channel, Record - This field displays the record number for each of the six channels. This gives an indication of the relative position in the audio buffer. 30 min audio buffers may display dashes for the record number if the audio buffer is inactive at the time. This occurs for the first 90 minutes of a 120 minute channel during playback mode.

(9)

ARINC 429 GMT - Displays the current time detected by the ARINC 429 GMT bus during record mode. Field is dashed during recording when GMT is not present. During playback, the display represents GMT as recorded in flash memory.

(10)

FSK GMT - Displays the current time detected by the FSK GMT bus during record mode. Field is dashed during recording when FSK GMT is not present. During playback, the display represents FSK GMT as recorded in flash memory.

(11)

BITE Status - Not used by installation personnel.

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Universal CVR 30 IM 23-70-03_Rev_1

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