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INSTALLATION & OPERATIONINSTRUCTION MANUAL
MODEL A100 / A100ACOCKPIT VOICE RECORDER
(SUPERSEDES FAR 02213189)
Rev. 02July 01/02
RECORDER PART NUMBERS:93A10010 93A10011 93A1001193A10030
93A10031 93A1003293A10033 93A10080 93A1008193A10082 93A10083
93A1008493A10085
CONTROL UNIT MODEL NUMBERS:93A15100 93A15101 93A1512093A15130
93A15140 93A1515093A15200 93A15201 93A1520493A15220 93A15225
93A1523093A15235 93A15240 93A1525093A15260 93A15270
MICROPHONE MODULE MODEL NUMBERS:93A05500 93A05510
93A0552093A05530 93A05540 93A0554593A05550 93A05555
93A0556093A05565 93A05566 93A0556793A05595
EXTERNAL PREAMPLIFIERS MODEL NUMBERS:93A15020
Manufactured in Accordance withTSOC84/ARINC 557
P/N: 165E280700
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Part Number 165E280700Rev. 01
July 01/02
Copyright 2002 by L-3 Communications CorporationAviation
Recorders
All rights reserved. No part of this manual may be repro-duced
or utilized in any form or by any means, electronic ormechanical,
including photocopying, recording, or by infor-mation storage and
retrieval system, without permission inwriting.
Inquiries should be addressed to:L-3 Communications
CorporationAviation RecordersTechnical PublicationsP. O. Box
3041Sarasota, Florida 34230(941) 3710811FAX: (941) 3775591CAGE Code
06141
This manual contains date sensitive information necessary to
install re-corders in aircraft. Contact L-3 Communications,
Aviation Recorders,to verify this date sensitive information prior
to using this manual to de-velop other documentation.
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GENERAL
This product and related documentation must be reviewed for
familiarization withsafety markings and instructions before
operation.
This instrument was constructed in an ESD (electrostatic
discharge) protected envi-ronment. This is because most of the
semiconductor devices used in this instrumentare susceptible to
damage by static discharge.
Depending on the magnitude of the charge, device substrates can
be punctured ordestroyed by contact or the mere proximity of a
static charge. The results can causedegradation of device
performance, early failure, or immediate destruction.
These charges are generated in numerous ways such as simple
contact, separation ofmaterials, and normal motions of persons
working with static sensitive devices.
When handling or servicing equipment containing static sensitive
devices, adequateprecautions must be taken to prevent device damage
or destruction.
Only personnel who are thoroughly familiar with
industry-accepted techniques forhandling static sensitive devices
should attempt to service circuitry with these devices.
In all instances, measures must be taken to prevent static
charge build-up on worksurfaces and persons handling the
devices.
BEFORE APPLYING POWER
Verify that the product is set to match the line voltage and
that the correct fusesare installed.
Servicing instructions are for use by service-trained personnel
only. To avoid dangerouselectric shock, do not perform any
servicing unless qualified to do so.
Adjustments described in the manual are performed with power
supplied to theinstrument while protective covers are removed.
Energy available at many points may, ifcontacted, result in
personal injury.
THE CONTENTS OF THEEQUIPMENT CAN BE
DAMAGED BY STATIC ELECTRICITY.PROPER
HANDLING IS REQUIRED.
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THIS PAGE IS INTENTIONALLY LEFT BLANK
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TABLE OF CONTENTS
Section Page
1.0 INTRODUCTION 1. . . . . . . . . . . . . . . . . . . . . . .
. . . . . . . . . . . . . . . . . . . . . . . .
1.1 Purpose 1. . . . . . . . . . . . . . . . . . . . . . . . . .
. . . . . . . . . . . . . . . . . . . . . . .
1.2 System Description and Limitations 1. . . . . . . . . . . .
. . . . . . . . . . . . . . .
1.3 Recorder Unit 3. . . . . . . . . . . . . . . . . . . . . . .
. . . . . . . . . . . . . . . . . . . . .
1.4 Control Unit 3. . . . . . . . . . . . . . . . . . . . . . .
. . . . . . . . . . . . . . . . . . . . . . .
1.5 Remote Microphone Module 3. . . . . . . . . . . . . . . . .
. . . . . . . . . . . . . . . .
1.6 Installation Accessories 3. . . . . . . . . . . . . . . . .
. . . . . . . . . . . . . . . . . . . .
2.0 EQUIPMENT LIMITATIONS / SPECIFICATIONS 7. . . . . . . . . .
. . . . . . . . . .
2.1 Leading Particulars Model A100 and A100A Recorders 7. . . .
. . . . . .
2.2 Leading Particulars Model A151, A151B, A152, A152BControl
Units 8. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
. . . . . . . . . . . . . . .
2.3 Leading Particulars Model A55 Remote Microphone Module 8. .
. . .
2.4 Leading Particulars Model A55B Remote Microphone Module 9. .
. .
3.0 INSTALLATION INSTRUCTIONS 10. . . . . . . . . . . . . . . .
. . . . . . . . . . . . . . . .
3.1 General Information 10. . . . . . . . . . . . . . . . . . .
. . . . . . . . . . . . . . . . . . .
3.2 Audio System Interface 11. . . . . . . . . . . . . . . . . .
. . . . . . . . . . . . . . . . . . .
3.3 Recorder Location 11. . . . . . . . . . . . . . . . . . . .
. . . . . . . . . . . . . . . . . . . . .
3.4 Microphone Installation Criteria 12. . . . . . . . . . . . .
. . . . . . . . . . . . . . . .
3.5 Cessation of Recording 12. . . . . . . . . . . . . . . . . .
. . . . . . . . . . . . . . . . . .
3.6 Installation in Rotorcraft 13. . . . . . . . . . . . . . . .
. . . . . . . . . . . . . . . . . . .
3.7 Installation Procedure for Inverter, P/N 9300A14001 14. . .
. . . . . . .
3.8 PostInstallation Checkout Procedures 15. . . . . . . . . . .
. . . . . . . . . . . . .
4.0 OPERATION TESTS 16. . . . . . . . . . . . . . . . . . . . .
. . . . . . . . . . . . . . . . . . . . . .
4.1 Pre-Flight Functional Check 16. . . . . . . . . . . . . . .
. . . . . . . . . . . . . . . . .
4.2 Complete Audio System Test 16. . . . . . . . . . . . . . . .
. . . . . . . . . . . . . . .
5.0 INSTALLATION ACCEPTANCE BY FIELD APPROVAL METHOD 17. . .
.
6.0 MAINTENANCE 18. . . . . . . . . . . . . . . . . . . . . . .
. . . . . . . . . . . . . . . . . . . . . . .
6.1 Underwater Locator Beacon 18. . . . . . . . . . . . . . . .
. . . . . . . . . . . . . . . .
6.2 Product Support 18. . . . . . . . . . . . . . . . . . . . .
. . . . . . . . . . . . . . . . . . . . .
6.3 Authorized Repair Facilities 18. . . . . . . . . . . . . . .
. . . . . . . . . . . . . . . . .
6.4 Loaner / Rental Program 19. . . . . . . . . . . . . . . . .
. . . . . . . . . . . . . . . . . .
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TABLE OF CONTENTS (Contd)
Appendixes
Appendix Page
A OUTLINE & DIMENSION DRAWINGS A1. . . . . . . . . . . . . .
. . . . . . . . . . . .
B ACCESSORY EQUIPMENT B1. . . . . . . . . . . . . . . . . . . .
. . . . . . . . . . . . . . . .
CALIBRATED SOUND SOURCE, Model A870 B3. . . . . . . . . . . . .
. . . . . . .
INERTIA / IMPACT SWITCH, Inertia Switch Inc. Model 3LO453 B7. .
. .
CVR AUDIO MIXER, Avtech Model 502011 B9. . . . . . . . . . . . .
. . . . . . .
C ENVIRONMENTAL QUALIFICATION FORMS C1. . . . . . . . . . . . .
. . . . . .
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TABLE OF CONTENTS (Contd)
List of Illustrations
Figure Page
1. Cockpit Voice Recorder, Model A100 2. . . . . . . . . . . . .
. . . . . . . . . . . . . . . . . .
2. Rotor Speed Encoder, P/N 253E087300 5. . . . . . . . . . . .
. . . . . . . . . . . . . . . .
3. Rotor Speed Encoder Typical Mounting Installations 6. . . . .
. . . . . . . . . . . . . .
4. Recommended Cockpit Area Microphone Mounting Locations 12. .
. . . . . . . .
5. Inverter Installation 14. . . . . . . . . . . . . . . . . . .
. . . . . . . . . . . . . . . . . . . . . . . . .
6. Cockpit Voice Recorder System Control Unit A151B, Functional
BlockDiagram 20. . . . . . . . . . . . . . . . . . . . . . . . . .
. . . . . . . . . . . . . . . . . . . . . . . . . . .
7. Cockpit Voice Recorder A100 and Control Unit A152B,
Functional BlockDiagram 21. . . . . . . . . . . . . . . . . . . . .
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
8. Channel Allocation in CVRs 22. . . . . . . . . . . . . . . .
. . . . . . . . . . . . . . . . . . . . .
9. Interwiring Diagram, Recorders A100, A100A, Control Units
A151, A151B, Remote Microphones A55, A55B 23. . . . . . . . . . . .
. . . . . . . . . . . . . .
10. Interwiring Diagram, Recorders A100, A100A, Control Units
A152, A152B 24. . . . . . . . . . . . . . . . . . . . . . . . . . .
. . . . . . . . . . . . . . . . . . . . . . . . . . .
11. Interwiring Diagram, Recorders A100, A100A, Control Units
A150 25. . . . . .
A1. Outline & Dimension Drawing, Model A100, P/N 93A10010,
11 A3. . . .
A2. Outline & Dimension Drawing, Model A100 with Beacon
andBeacon Mount, P/N 93A10030, 31, 32, 33 A4. . . . . . . . . . . .
. . . . . . . .
A3. Outline & Dimension Drawing, Model A100A, P/N 93A10081
A5. . . . . . .
A4. Outline & Dimension Drawing, Model A100A with Beacon,
andBeacon Mount, P/N 93A10080, 82, 83, 84, 85 A6. . . . . . . . . .
. . . . . .
A5. Outline & Dimension Drawing, CVR Vibration Mount, P/N
9300343 A7. .
A6. Outline & Dimension Drawing, Heavy Duty CVR
VibrationMount, P/N 93955 A8. . . . . . . . . . . . . . . . . . . .
. . . . . . . . . . . . . . . . . . . . . .
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TABLE OF CONTENTS (Contd)
List of Illustrations (Contd)
Figure Page
A7. Outline and Dimension Drawing, Model A151 Control Unit, P/N
93A15100 A9. . . . . . . . . . . . . . . . . . . . . . . . . . . .
. . . . . . . . . . . . . . . . . .
A8. Outline and Dimension Drawing, Model A151B Control Unit, P/N
93A15120, 30, 40, 50 A10. . . . . . . . . . . . . . . . . . . . . .
. . . . . . . . . .
A9. Outline and Dimension Drawing, Model A152 Control Unit,
P/N93A1520020 A11. . . . . . . . . . . . . . . . . . . . . . . . .
. . . . . . . . . . . . . . . . . . . .
A10. Outline and Dimension Drawing, Model A152B Control UnitP/N
93A15220, 30, 40, 50, 70 A12. . . . . . . . . . . . . . . . . . . .
. . . . . . . .
A11. Outline and Dimension Drawing, Model A150 Preamplifier, P/N
93A15020 A13. . . . . . . . . . . . . . . . . . . . . . . . . . . .
. . . . . . . . . . . . . . . .
A12. Outline and Dimension Drawing, Model A55 Microphone, P/N
93A05500 A14. . . . . . . . . . . . . . . . . . . . . . . . . . . .
. . . . . . . . . . . . . . . .
A13. Outline and Dimension Drawing, Model A55B Microphone, P/N
93A05510, 30, 50 A15. . . . . . . . . . . . . . . . . . . . . . . .
. . . . . . . . . . . .
A14. Outline and Dimension Drawing, Model A55B Microphone, P/N
93A05520, 55 A16. . . . . . . . . . . . . . . . . . . . . . . . . .
. . . . . . . . . . . . . .
A15. Outline and Dimension Drawing, Model A55B Microphone, P/N
93A05540, 45 A17. . . . . . . . . . . . . . . . . . . . . . . . . .
. . . . . . . . . . . . . . .
A16. Outline and Dimension Drawing, Model A55B Microphone P/N
93A05560, 65, 67 A18. . . . . . . . . . . . . . . . . . . . . . . .
. . . . . . . . . . . .
A17. Outline and Dimension Drawing, Model A55B Microphone, P/N
93A05566 A19. . . . . . . . . . . . . . . . . . . . . . . . . . . .
. . . . . . . . . . . . . . . .
A18. Outline and Dimension Drawing, Model A55B Microphone, P/N
93A05595 A20. . . . . . . . . . . . . . . . . . . . . . . . . . . .
. . . . . . . . . . . . . . . .
B1. Calibrated Sound Source, P/N 9300A870 B3. . . . . . . . . .
. . . . . . . . . . . . . . .
B2. Cockpit Voice Recorder System Test Panel, P/N 9300A860 B3. .
. . . . . . . . .
B3. Condenser Remote Microphone Test Setup B4. . . . . . . . . .
. . . . . . . . . . . . . .
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1.0 INTRODUCTION
1.1 Purpose
The information contained within this Installation Manual
describes the administrative andtechnical aspects, features,
functions, components, and operation of the A100/A100A Cock-pit
Voice Recorder (CVR) system and its accessories and components. Any
and all com-ments or recommendations regarding the installation,
acceptance, or operation of the CVR orits accessories and
components should be directed to the Product Support Department of
L3Communications Aviation Recorders.
The following L3 Aviation Recorders are covered in this
Installation & Operation Instruc-tion Manual:
Part Number Model Mount ULB Inverter Installed93A10010 A100 No
No No93A10011 A100 No No Yes93A10030 A100 Yes Yes No93A10031 A100
Yes Yes Yes93A10032 A100 Yes No Yes93A10033 A100 Yes No No93A10080
A100A Yes Yes No93A10081 A100A No No No93A10082 A100A Yes No
No93A10083 A100A Yes Yes Yes93A10084 A100A Yes No Yes93A10085 A100A
No No Yes
1.2 System Description and Limitations
The Cockpit Voice Recorder system has been designed to meet or
exceed those requirementsspecified within and is approved under
Federal Aviation Administration Technical StandardOrder C84 or
C111.
The Cockpit Voice Recorder system is composed of three essential
components: the RecorderUnit, Control Unit Components with area
microphone module, and Vibration Mount. AHeavyDuty Vibration Mount
is available for rotorcraft installations.
The CVR simultaneously records four separate voice inputs. These
inputs may be eithertransmitted or received signals originating
from the following recommended stations: Pilot,CoPilot, Public
Address or Third Crew Member, and Cockpit Area Microphone.
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Cockpit Voice Recorder, Model A100Figure 1
-
Approval of the Cockpit Voice Recorder system is not authorized
by this Installation Manual.Acceptance for the installation and use
of the CVR and its associated components must besought through the
appropriate offices of the Federal Aviation Administration or other
certi-fying agency. Aprovals may be accomplished on a Field
Approval basis if the installation isdetermined to meet the
criteria of the appropriate Postinstallation, Preflight, and Flight
testspecificed for evaluation within this Installation Manual. It
is recommended that all proposedinstallations be coordinated with
the local jurisdiction of the Federal Aviation Administrationor
other certifying agency prior to performing the installation.
1.3 Recorder Unit
The recorder is housed in an inertnational orange, 1/2 ATR short
case. It contains the record-er assembly and associated
electronics. (See Section 2.1 for leading particulars.)
RecorderModels A100 and A100A can be used in any system
configuration and are totally inter-changeable. An Underwater
Locator Beacon is available as required by regulations.
1.4 Control Unit
The control units are standard ARINC characteristic 306 panel
format. Models A152 andA152B house microphone preamplifier,
microphone, test switch, erase switch, and meter.Models A151 and
A151B house microphone preamplifier, test switch, erase switch, and
me-ter. (Refer to Sections 2.2 for leading particulars.)
1.5 Remote Microphone Module
Remote microphone modules, Models A55 and A55B are used when
cockpit space limita-tions exist. Remote microphone modules are
used in conjunction with control unit ModelsA151 and A151B. (Refer
to Sections 2.3 through 2.4 for leading particulars.)
1.6 Installation Accessories
A. Vibration Mount P/N 9300343Standard mount equipped with four
(4) vibration isolators. (See Figure 18.)
Isolator load range:Rear: 2.50 5.50 lbs.Front: 5.00 10.00
lbs.
Spring loaded pins guide the CVR connector to mate with the
mount connector. Two(2) holddown screws on the front of the mount
lock the Recorder Unit into postion.
-
B. Heavy Duty Vibration Mount P/N 93955Mount for use in aircraft
environments where excessive vibration may occur, such asin
rotorcraft or test aircraft. (See Figure 19.)
Isolator load range:Rear: 3.00 6.00 lbs.Front: 9.00 15.00
lbs.
C. Connector P/N 9300435Connector attaches to Vibration Mount
and mates with connector on rear panel ofCVR. Aircraft wiring is
soldered to the pins of the connector.
D. Inverter P/N 9300A14001 (Supersedes P/N 9300A140)Optional 28
VDC to 115 VAC 400 Hertz inverters are available. Inverter may
beplugged into available connector internal to the recorder. See
Section 3.7 for Installa-tion procedure. Jumper must be added
accross Pins 1 & 2 of the mount connector(P/N 9300435, Cannon
P/N DPXB5733S0001). When DC power is used, ameans should be
provided to stop recording after powered flight has been
terminated.
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!"##$
%
%
&%% '&
($)&'$(
)'&&
!*"+*$
,-.
**/(/#
0("
communications
Rotor Speed Encoder, P/N 253E087300Figure 2
E. Rotor Speed Encoder P/N 93A289An optional Rotor Speed Encoder
is available for use in rotorcraft. The Rotor SpeedEncoder module
meets CAA requirements for CVR rotor speed recording. The
RotorSpeed Encoder allows for simultaneous recording of rotor speed
data and voice on thesame audio channel. It uses a subcarrier at
4600 Hz which is phase modulated. (SeeFigure 2 for
description.)
-
'1.-& #*$*!0
& #*$!"#
'.-& #*$!#(
Rotor Speed Encoder Typical Mounting InstallationsFigure 3
-
F. Rotor Speed Encoder Mount P/N 93A291An optional Rotor Speed
Encoder mount is available to directly mount the RotorSpeed Encoder
to the Vibration Mount. (See Figure 3 for description.)
F. Rotor Speed Encoder Bracket P/N 93A324An optional Rotor Speed
Encoder bracket is available to mount the Rotor Speed En-coder to
the airframe, a bulkhead, etc. A 15pin connector is attached to
provide in-terconnection with the CVR. (See Figure 3 for
description.)
2.0 EQUIPMENT LIMITATIONS / SPECIFICATIONS
2.1 Leading Particulars Model A100 and A100A Recorders
Designed to TSOC84 and ARINC Characteristic 557.
Size: 1/2 ATR Short4 7/8 Width by 12 9/16 Length by 7 5/8
Height
Color: International Orange
Weight (Max): 23.9 lbs.
Power: 115 VAC +/ 10%, 400 Hz +/ 5%20 Watts max normal
operation50 Watts max bulk erase
Connections: See Interwiring Diagram
Mating Connector: DPXB5733S001 (L3 P/N 9300435)
Tape (Endless Loop): 1/4 preconditioned recording tape, mylar
base
Transport Drive: Direct No clutches
Tape Speed: Standard NARTB; 17/8 ips
Channels: 4 inline coincident recording
Recording Duration: 30 minutes minimum
Head Assembly: Precision aligned 3 heads
Bulk Erase: Failsafe, double electrical interlock. Total erase
inexcess of 35 dB
Operational Testing: Automatic four channels sequential600 Hz
audio signal recorded and reproduced to trig-ger a gonogo gate
controlled meter indicator.
Frequency Response: 150 to 5000 Hz + 3 dB
Recorded Signal to NoiseRatio:
45 dB min
Monitor System: Composite 4 channel playback
Monitor Output: Headphone jack, 600 Ohms, 10 mW
Harmonic Distortion: Less than 5%
-
Flutter: 1.5% RMS maximum
Audio Input Impedance: 5000 Ohms each channel
Basic Subassemblies: 10 plugin boardsTape transportEnvironmental
protection
2.2 Leading Particulars Model A151, A151B, A152, A152B Control
Units
Size: ATA Panel5.75 Width by 2.25 Height by 2.5 Depth
Color: Grey, Black, or Brown
Weight (Max): 1.2 lbs.
Connector: MS31122041P
Mating Connector: P/N 9300458Cannon P/N MS3116F2041S
Front Panel: MeterTest Switches (2)Headset JackMicrophone
(Models A152 & A152B only)
AGC: Fast reacting 30 dB rangeLow distortionTrue AC
attenuation
Audio Input Impedance: 20K Ohms
Audio Input Level: 3 mV
Ouput Impedance: 300 Ohms
Output Level: 500 Millivolts
Audio FrequencyResponse:
150 5000 Hz
Audio Gain: Pin selected 6, 12, 24, dB steps
DC Supply: Plus 18 Volts
2.3 Leading Particulars Model A55 Remote Microphone Module
Size: Side Connector Models:3.56 Length by 2 Width by 2.25
Height
Back Connector Models:3.87 Length by 2 Width by 2 Height
Weight: 0.5 lbs.
Color: Black
Connector: Cannon Twinax #TM RB1M0
-
Mating Connector: P/N 9300457Cannon P/N 1509000303
Mounting: Front or Rear Panel
Microphone: Dynamic Type
2.4 Leading Particulars Model A55B Remote Microphone Module
For all Model A55B Part Numbers, except 93A05540 and 93A05545
Remote Micro-phones.
Size: Side Connector Models:3.76 Length by 2 Width by 2.25
Height
Back Connector Models:4.07 Length by 2 Width by 2 Height
Weight: 0.5 lbs.
Color: Black or Brown
Connector: Cannon Twinax #TM RB1M0
Mating Connector: P/N 9300457Cannon P/N 1509000303
Mounting: Front or Rear Panel
Microphone: Condenser Type
For only the Model A55B Part Numbers 93A05540 and 93A05545
Remote Micro-phones.
Size: 2.5 Length by 1.1 Width by 1.2 Height
Weight: 4 oz.
Color: Grey, Brown, or Black
Connector: Shield twisted pair pigtail
Microphone: Condenser Type
-
3.0 INSTALLATION INSTRUCTIONS
Installation of the recorder, control unit, and remote
microphone module is based on ARINCCharacteristic 557, dated
January 10, 1964.
3.1 General Information
This section contains considerations and recommendations for
installation of the CockpitVoice Recorder and associated system
components. Interconnect harness wiring, physicalmounting, optional
components (preamplifiers and summing amplifiers) must be
consideredwhen requirwed to satisfy all applicable regulations. The
conditions and tests required forTSO approval of this article are
minimum performance standard. It is the responsibility ofthose
desiring to install this article either on or within a specific
type or class of aircraft todetermine that the aircraft
installation conditions are within TSO standards. If not withinTSO
standard, the article may be installed only if the applicant
documents further evaluationfor an acceptable installation and it
is approved by the Administrator of the Federal
AviationAdministration or other certifying agency.
The Federal Aviation Administration has issued several Advisory
Circulars which may bereferred to in the approval processes.
Advisory Circular 25.14571a specifically addressesone acceptable
means of compliance with Federal Aviation Regulation (FAR) 25.1457
(b),(e), and (f). Installations must conform to the Operating Rules
in FAR23.1457, 25.1457, and29.1457 appropriate to the category of
operation under FAR Parts 91, 135, and 121 (Air Car-rier).
The CVR system is powered by 115 VAC. It may also be powered by
28 VDC from the es-sential aircraft bus source, when the optional
DV inverter is installed.
To ensure optimal performance from the Cockpit Voice Recorder
System, the following wiresizes and types are recommended as
acceptable:
A. All wires except pins 2, 3, 9, and 17: Use #24 AWG or larger,
for maximum 500 ft.length if shielded pairs are used. All wiring
should be MILW22759 orMILC27500.
B. For pins 2, 3, 9 (power leads), and 17 (ground), use the
following as a minimum:#24 AWG, shielded pairs 240 ft. max.#22 AWG,
shielded pairs 375 ft. max.
C. Ground connection to be within one foot of pin 17.
D. Single point ground. Reasons for specifying single point
ground for pin 17 are tominimize random noise pcikup.
E. Normal power requirements are:20 Watts maximum during normal
operation.50 Watts maximum during bulk erase.
-
The BULK ERASE connection is not mandated by the FAA and,
therefore, it is an installa-tion option. The circuitry required
for BULK ERASE includes the installation of interlockdevices aboard
the aircraft. If the BULK ERASE feature is installed, then at least
one (1) in-terlock is required to prevent accidental erasure of the
CVR tape. If the BULK ERASE fea-ture is not desired, Pin 55 (ERASE
A) must be grounded to Pin 17. Pin 57 remains open.
3.2 Audio System Interface
The range of acceptable audio input levels for the CVR is from
50 mV RMS to 500 mVRMS.
Earlier aircraft audio systems may require rework of their audio
system to ensure recordingof ATC, Intercom, Mask Microphone, and
Sidetone audio, independant of mode selection onthe audio control
panel. In some cases, selection of the Loud Speaker function
disables sidetone output and, therefore, transmissions to ATC may
not be recorded. Such condition mustbe remedied to provide
continous received audio from the communications radios.
Old Systems Rework the audio control panel or system to provide
a CVR output or installan external summing amplifier. Summing
amplifiers can be obtained from Avtec, BakerElectronics, Racal, and
others. (See Appendix B & C for examples.) The addition of a
sum-ming amplifier provides existing audio systems with the hot
boom microphone capability.No changes to the CVR are required. (See
Figure 7 for typical summing amplifier installa-tion.)
New Systems Some later generation audio control panels have a
CVR signal output alreadyprovided. A summing amplifier may be
required to provide hot boom microphone opera-tion. It is the
responsibility of the Installer to determine the means of
interfacing to complywith the regulations.
Future Systems Those audio control panels and systems designed
to meet or exceed thecharacteristics found in Radio Technical
Commission for Aeronautics (RTCA), DO170 forhot boom microphone
capability, may be determined to be acceptable.
3.3 Recorder Location
The Cockpit Voice Recorder is certified and approved for
installation in any combination ofthe following conditions:
Heated/unheated, pressurized/unpressurized, hard
mounted/shockmounted.
For long term reliability it is recommended that recorders be
mounted within the vibrationmount in an upright position (vertical
as viewed from the front) in a heated, pressurized areain a
fuselage location, as far aft as practical. Refer to FAA Advisory
Circular 25.14571Afor further details.
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RECOMMENDED MICROPHONE LOCATIONSARE NUMBERED IN ORDER OF
PREFERENCE
Recommended Cockpit Area Microphone Mounting LocationsFigure
4
3.4 Microphone Installation Criteria
The most desirable location for the cockpit area microphone is
forward of a vertical planeoriented laterally through the pilots
and copilots normal head position. The area micro-phone must face
the crew members. (Refer to Figure 4.)
3.5 Cessation of Recording
Federal Air Regulations 23.1457 (d), (2), 25.1457 (d), (2),
27.1457 (d), (2), and 29.1457 (d),(2) state that There [must be] an
automatic means to simultaneously stop the recorder andprevent each
erasure feature from functioning, within 10 minutes after crash
impact. TheInstaller must demonstrate this function.
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Since the CVR system can be powered by either 115 VAC, 400 Hz or
28 VDC (with optionalinverter), the following methods are
acceptable to ensure automatic cessation of recording:
1. IMPACT SWITCH Interrupts CVR power upon exposure to a
predertimed level ofgforce. Such switches have limitations, but are
effective in high gforce accidents.This item is not available
through L3 Communications. (See Appendix A and F formanufacturers
specifications for models available.)
2. If power input is derived directly from the enginedriven 115
VAC, 400 HZ source,(not derived from AC Inverter), no other
external circuitry is necessary. It is assumedthat the engine(s)
will stop upon crash impact.
3.6 Installation in Rotorcraft
The Heavy Duty Dibration Mount P/N 93955 is recommedned for
rotorcraft installations. Ithas larger isolators to dampen
vibration to the CVR.
A Rotor Speed Encoder (RSE) may be required for the installation
in accordance with CAA(U.K.) regulations. There are two
configurations for mounting the Rotor Speed Encoder withthe CVR
system. (See Figure 3.) The first configuration affixes the Encoder
module directlyonto a heavyduty vibration mount, P/N 93A291. The
second configuration mounts theRSE module on a small bracket, P/N
93A324, away from the CVR. This bracket must beattached to a
bulkhead or a similar rigid surface.
The Rotor Speed Encoder has interlock circuitry which will
prevent the CVR Bulk Erasurewhile the main rotor(s) is rotating. If
the rotorcraft CVR system is not equipped with a RSEor another
suitable interlock, the Bulk Erase feature must be disabled.
If the Bulk Erase feature is not used, Pin 55 (Erase A) must be
grounded to Pin 17, and Pin57 remains open to satisify appropriate
Federal Aviation Regulations.
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INVERTER RAILSTUDS (4 PLACES)
CHASSISJOINT
440X5/16BINDING HEAD
SCREWS
CABLE GUARDP/N 9300428
DETAIL A DETAIL B
CONNECTORP.N 9300232
INVERTER
DETAIL C
Inverter InstallationFigure 5
3.7 Installation Procedure for Inverter, P/N 9300A14001
This procedure applies only to the optional installation of the
Inverter into Model A100 andA100A Cockpit Voice Recorders. See
Figure 5.
1. Remove dust cover by removing two phillips head screws,
exposing chassis wiringassembly.
2. Remove two 440 by 5/16 binding head screws located on the
rear of the chasis. (SeeDetail A.) Discard attaching lock nuts.
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3. Insert cable guard, P/N 9300428, as shown in Details A and B,
ensuring the slottedend is fitted over the rear chassis joint. Fold
cable guard over connector and harness.
4. Insert Inverter over chassis wiring assembly engaging it in
the four inverter rail studs(Detail B) and connector (Detail
C).
5. Reinsert and tighten the two 440 by 5/16 binding head screws
removed in Step 2, se-curing the Inverter.
6. Replace the dust cover using two phillips head screws.
7. Refer to the CVR Component Maintenance Manual, P/N
165E010100, for ElectricalTest of Inverter.
3.8 PostInstallation Checkout Procedures
The following tests and procedural results must be documented in
the CVR InstallationChecklist and submitted with the date package
for field approval consideration.
A. Before applying power to the CVR system and associated
components, verify that allconnections are secure and that a
continunity or other interconnect assurance test hasbeen
conducted.
B. Apply power to the system and activate the Cockpit Voice
Recorder selftest. To acti-vate, push and hold the green TEST
button for a minimum of five seconds. An in-ternal 600 Hz test tone
generator is keyed and sequentially switches through the
fourchannels of the recorder. Each channel receives the test tone
for approximately .8 sec-onds.
C. Monitor circuitry receives the test tone signals and drives
the meter, a GONOGOindicating device, located on the Cockpit
Control Unit. The meter needle rises andcomes to rest in the GO
(green) section of the meter scale.
Because of the short time interval between each channel being
fed the test tone, themeter needle rises to an indication but does
not completely fall to a zero indication be-tween signals, giving
more of an oscillating action or a slight dithering action. In
theevent of a channel failure, the meter needle will fall out of
the green section of the me-ter scale or return to zero and give a
definite NOGO indication.
D. Aural monitoring of the 600 hertz test tone and channel
switching can be accom-plished with a 600 ohm headset inserted into
the Jack located on the Cockpit ControlUnit.
With the headset inserted into the Jack located on the Cockpit
Control Unit, speak in anormal voice 6 away from the Cockpit
Control Unit microphone and note that youcan hear what you speak
with approximately a 1/2 second delay without any signifi-cant
distortion. This test ensures the microphone is operating.
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E. Verify that the following microphone inputs are recorded on
their appropriate CVRchannels, regardless of Audio Control Panel
mode or audio (communications radio)selection, for Cockpit Voice
Recorder installations within aircraft or rotorcraft in-tended for
service within the National Airspace Systems:
CHANNEL 1: Third Crewmember Station or Public Address
Systems.CHANNEL 2: Primary CoPilots Boom, Mask, and Hand Microphone
Input.CHANNEL 3: Primary Pilots Boom, Mask, and Hand Microphone
Input.CHANNEL 4: Cockpit Mounted Area Microphone.
F. The Bulk Erase function can occur only when the aircraft is
resting on its landing gear.After depressing the bulk erase button
(must be pushed in and held for a minimum of2 seconds), verify
function by listening for loud 400 Hz tone through the HEADSETjack.
Tone duration is approximately 5 12 seconds.
4.0 OPERATION TESTS
4.1 Pre-Flight Functional Check
The Pre-flight Functional Check assures the operator that the
equipment is servicable. There-fore, it is to be performed before
every flight or whenever maintenance has been performedon the
aircraft or rotorcraft which may have affected the performance of
the Cockpit VoiceRecorder or its associated Audio System interface,
accessories, or components..
Push and hold Test button located on the Cockpit Control Unit
for a minimum of five se-conds. A 600 hertz generator is keyed and
sequentially switched through the four channels ofthe recorder.
Each channel receives the test tone for approximately 0.8 seconds.
The metercircuit receives these signals and drives the meter, a
GONOGO indicating device, locatedon the Cockpit Control Unit. The
meter needle rises and comes to a rest in the GO (green)section of
the meter scale.
Because of the short time interval between each channel being
fed the test tone, the meterneedle rises to an indication but does
not completely fall to a zero indication between signals,giving
more of an oscillating action or a slight dithering action. In the
event of a channelfailure, the meter needle will fall out of the
green section of the meter scale or return to zeroand give a
definite NOGO indication.
4.2 Complete Audio System Test
A test of the Cockpit Area Microphone can be accomplished with a
600 Ohm headset in-serted into the remote HEADSET jack or into the
HEADSET jack on the Control Unit.Speak in a normal voice 6 away
from the Cockpit Area Microphone, and determine audibleclarity
after approximately a 1/2 second delay without any significant
distortion. This testensures that the Cockpit Area Microphone is
operating.
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A complete Audio System Interface test must be completed during
each annualinspection orspecified maintenance period on the
aircraft or rotorcraft and whenever unscheduled mainte-nance is
performed on the aircraft or rotorcraft which may have affected the
performance ofthe Cockpit Voice Recorder system. To accomplish this
test, the Pilots, Co-pilots, CockpitArea Microphone, and Third
Crewmember or Public Address System inputs must be individ-ually
checked for their operational integrity with the Cockpit Voice
Recorder. Upon satisfac-tory achievement of this test, an entry
shall be made in the maintenance records of the aircraftor
rotorcraft.
5.0 INSTALLATION ACCEPTANCE BY FIELD APPROVAL METHOD
An applicant for Field Approval of a CVR installation must be
properly certificated and ap-propriately rated, qualified, and
equipped to accomplish the installation and approve the air-craft
or rotorcraft for returntoservice. The CVR should be installed in
accordance with theinstructions and limitations contained within
this Installation Manual.
Drawings and other information, such as structural related data
to show the method of attach-ment of the CVR components to the
airframe, wiring diagrams, appropriate weight and bal-ance data,
identification of all CVR system components used in the
installation should bemade available to the Inspector conducting
the Field Approval.
The CVR Installation Manual containing Operating Instructions
and System descriptionsmust be made available to the Inspector for
review and evaluation of the CVR system.
The applicant must submit an FAA Form 337, describing the work
performed to the airframeto accomplish the installation of the CVR
system. The Form 337 must also include a state-ment that a complete
Audio System Interface test was performed as required.
The applicant must make a statement on Form 337 that the Cockpit
Area Microphone isinstalled within the recommended locations
identified within FAA Advisory Circular25.14571A and in accordance
with the instructions contained within this Installation
Manu-al.
The applicant should submit all appropriate data and drawings to
the Inspector prior to begin-ing the installation of the Cockpit
Voice Recorder.
Any deviations to the installation instructions contained within
this Installation Manual mustbe brought to the attention of the
Inspector and so stated on Form 337.
Finally, ground and flight tests must be conducted to verify
that the Audio System Interface issatisfactory and that normal
conversation can be discerned from the Cockpit Area Micro-phone and
the individual Pilot, Copilot, and appropriate Third Crewmember or
Public Ad-dress stations. The CVR System must be found to be free
of any objectionable audio inter-ference and other unwanted noise
in order to ensure discernible recordings. Anydiscrepancies
identified during the ground and flight tests must be brought to
the attention ofthe Inspector and corrected before the aircraft can
be returned to service.
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If required, L3 can reproduce the CVR tape contents onto a
cassette for channel seperationand evaluation. Contact the Product
Support department to coordinate this process.
6.0 MAINTENANCE
6.1 Underwater Locator Beacon
The CVR carries the Dukane Model N15F210B or Model DK 100
Underwater Locator Bea-con (ULB). Both units are manufacturered
under a Parts Manufacturer Approval. The bea-con is attached on the
front panel for easy removal for replacement of the battery, and
foreasy viewing of the battery expiration date.
The Model DK 100 contains a battery life of 6 years prior to its
actual operating life of atleast 30 days. The battery must be
replaced by Dukane upon expiration.
6.2 Product Support
Mailing address: L3 CommunicationsAviation RecordersP.O. Box
3041Sarasota, Florida 342303041Attention: Product Support, Mail
Stop 20
Telephone: (941) 3710811
Telefax: (941) 3775591
SITA: SRQLFCR
Web Site: www.L3AR.com
6.3 Authorized Repair Facilities
L3 Communications Aviation Recorders performs repair, overhaul,
and readout services forthe A100 / A100A Cockpit Voice Recorder
System. Items should be shipped to the followingaddress:
L-3 Communications Aviation Recorders6000 Fruitville Road
Sarasota, Florida 34232 Attention: Repair Station
Questions concerning SSFDR repair or readout service may be
answered by calling the Avi-ation Recorders Repair Station at (941)
3775554 or (941) 3775579, or by calling the Prod-uct Support
Department at (941) 3710811. Readout Service is performed by the
Repair Sta-tion.
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L3 Communications Aviation Recorders has factory trained
technicians at each AuthorizedRepair Facility located worldwide,
who are capable of performing repair, overhaul, readout,and loaner
/ rental services. Contact the Product Support Department for names
and loca-tions.
6.4 Loaner / Rental Program
L3 Communications Aviation Recorders Authorized Repair
Facilities are capable of pro-viding loaner / rental CVRs. Some
facilities may not charge for loaner CVRs if the repair /overhaul
work is performed by that repair facility.
Aviation Recorders Product Support Department maintains a
limited supply of Rental Cock-pit Voice Recorders. Please contact
the Product Support Department for availability and pric-ing.
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