Aviation Recorders
P.O. Box 3041
Sarasota, Florida 34230
CAGE Code 06141
INSTALLATION & OPERATION
INSTRUCTION MANUAL
MODEL A100 / A100A
COCKPIT VOICE RECORDER
(SUPERSEDES FAR 02213189)
RECORDER PART NUMBERS:
93A10010
93A10011
93A10030
93A10031
93A10033
93A10080
93A10082
93A10083
93A10085
93A10011
93A10032
93A10081
93A10084
CONTROL UNIT MODEL NUMBERS:
93A15100
93A15101
93A15130
93A15140
93A15200
93A15201
93A15220
93A15225
93A15235
93A15240
93A15260
93A15270
93A15120
93A15150
93A15204
93A15230
93A15250
MICROPHONE MODULE MODEL NUMBERS:
93A05500
93A05510
93A05520
93A05530
93A05540
93A05545
93A05550
93A05555
93A05560
93A05565
93A05566
93A05567
93A05595
EXTERNAL PREAMPLIFIERS MODEL NUMBERS:
93A15020
Manufactured in Accordance with
TSOC84/ARINC 557
Rev. 02
July 01/02
P/N: 165E2807–00
Model A100 / A100A CVR
Installation & Operation
Instruction Manual
Part Number 165E2807–00
Rev. 01
July 01/02
This manual contains date sensitive information necessary to install recorders in aircraft. Contact L-3 Communications, Aviation Recorders,
to verify this date sensitive information prior to using this manual to develop other documentation.
ECopyright 2002 by L-3 Communications Corporation
Aviation Recorders
All rights reserved. No part of this manual may be reproduced or utilized in any form or by any means, electronic or
mechanical, including photocopying, recording, or by information storage and retrieval system, without permission in
writing.
Inquiries should be addressed to:
L-3 Communications Corporation
Aviation Recorders
Technical Publications
P. O. Box 3041
Sarasota, Florida 34230
(941) 371–0811
FAX: (941) 377–5591
CAGE Code 06141
Installation & Operation
Instruction Manual
Model A100 / A100A CVR
THE CONTENTS OF THE
EQUIPMENT CAN BE
DAMAGED BY
STATIC ELECTRICITY.PROPER
HANDLING IS REQUIRED.
GENERAL
This product and related documentation must be reviewed for familiarization with
safety markings and instructions before operation.
This instrument was constructed in an ESD (electrostatic discharge) protected environment. This is because most of the semiconductor devices used in this instrument
are susceptible to damage by static discharge.
Depending on the magnitude of the charge, device substrates can be punctured or
destroyed by contact or the mere proximity of a static charge. The results can cause
degradation of device performance, early failure, or immediate destruction.
These charges are generated in numerous ways such as simple contact, separation of
materials, and normal motions of persons working with static sensitive devices.
When handling or servicing equipment containing static sensitive devices, adequate
precautions must be taken to prevent device damage or destruction.
Only personnel who are thoroughly familiar with industry-accepted techniques for
handling static sensitive devices should attempt to service circuitry with these devices.
In all instances, measures must be taken to prevent static charge build-up on work
surfaces and persons handling the devices.
BEFORE APPLYING POWER
Verify that the product is set to match the line voltage and that the correct fuses
are installed.
Servicing instructions are for use by service-trained personnel only. To avoid dangerous
electric shock, do not perform any servicing unless qualified to do so.
Adjustments described in the manual are performed with power supplied to the
instrument while protective covers are removed. Energy available at many points may, if
contacted, result in personal injury.
Model A100 / A100A CVR
Installation & Operation
Instruction Manual
THIS PAGE IS INTENTIONALLY LEFT BLANK
Installation & Operation
Instruction Manual
Model A100 / A100A CVR
TABLE OF CONTENTS
Section
1.0
2.0
Page
INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1
1.1
1.2
1.3
Purpose . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1
System Description and Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . 1
Recorder Unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3
1.4
1.5
Control Unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3
Remote Microphone Module . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3
1.6
Installation Accessories . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3
EQUIPMENT LIMITATIONS / SPECIFICATIONS . . . . . . . . . . . . . . . . . . . . 7
2.1
2.2
3.0
4.0
2.3
Leading Particulars – Model A100 and A100A Recorders . . . . . . . . . . 7
Leading Particulars – Model A151, A151B, A152, A152B
Control Units . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8
Leading Particulars – Model A55 Remote Microphone Module . . . . . 8
2.4
Leading Particulars – Model A55B Remote Microphone Module . . . . 9
INSTALLATION INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10
3.1
General Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10
3.2
3.3
Audio System Interface . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11
Recorder Location . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11
3.4
3.5
Microphone Installation Criteria . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12
Cessation of Recording . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12
3.6
3.7
Installation in Rotorcraft . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
Installation Procedure for Inverter, P/N 9300–A140–01 . . . . . . . . . . 14
3.8
Post–Installation Checkout Procedures . . . . . . . . . . . . . . . . . . . . . . . . 15
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
6.2
Underwater Locator Beacon . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18
Product Support . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18
6.3
6.4
Authorized Repair Facilities . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18
Loaner / Rental Program . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
Model A100 / A100A CVR
Installation & Operation
Instruction Manual
TABLE OF CONTENTS (Cont’d)
Appendixes
Appendix
Page
A
OUTLINE & DIMENSION DRAWINGS . . . . . . . . . . . . . . . . . . . . . . . . . . A–1
B
ACCESSORY EQUIPMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . B–1
CALIBRATED SOUND SOURCE, Model A870 . . . . . . . . . . . . . . . . . . . . B–3
INERTIA / IMPACT SWITCH, Inertia Switch Inc. Model 3LO–453 . . . . B–7
CVR AUDIO MIXER, Avtech Model 5020–1–1 . . . . . . . . . . . . . . . . . . . . B–9
C
ENVIRONMENTAL QUALIFICATION FORMS . . . . . . . . . . . . . . . . . . . C–1
Installation & Operation
Instruction Manual
Model A100 / A100A CVR
TABLE OF CONTENTS (Cont’d)
List of Illustrations
Figure
Page
1.
Cockpit Voice Recorder, Model A100 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2
2.
Rotor Speed Encoder, P/N 253E0873–00 . . . . . . . . . . . . . . . . . . . . . . . . . . . . 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 Block
Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20
7.
Cockpit Voice Recorder A100 and Control Unit A152B, Functional Block
Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 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
A–1.
Outline & Dimension Drawing, Model A100, P/N 93A100–10, –11 . . . . A–3
A–2.
Outline & Dimension Drawing, Model A100 with Beacon and
Beacon Mount, P/N 93A100–30, –31, –32, –33 . . . . . . . . . . . . . . . . . . . . A–4
A–3.
Outline & Dimension Drawing, Model A100A, P/N 93A100–81 . . . . . . . A–5
A–4.
Outline & Dimension Drawing, Model A100A with Beacon, and
Beacon Mount, P/N 93A100–80, –82, –83, –84, –85 . . . . . . . . . . . . . . . . A–6
A–5.
Outline & Dimension Drawing, CVR Vibration Mount, P/N 9300–343 . . A–7
A–6.
Outline & Dimension Drawing, Heavy Duty CVR Vibration
Mount, P/N 93–955 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A–8
Model A100 / A100A CVR
Installation & Operation
Instruction Manual
TABLE OF CONTENTS (Cont’d)
List of Illustrations (Cont’d)
Figure
Page
A–7.
Outline and Dimension Drawing, Model A151 Control Unit,
P/N 93A15100 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A–9
A–8.
Outline and Dimension Drawing, Model A151B Control Unit,
P/N 93A151–20, –30, –40, –50 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A–10
A–9.
Outline and Dimension Drawing, Model A152 Control Unit, P/N
93A152–00–20 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A–11
A–10. Outline and Dimension Drawing, Model A152B Control Unit
P/N 93A152–20, –30, –40, –50, –70 . . . . . . . . . . . . . . . . . . . . . . . . . . . . A–12
A–11. Outline and Dimension Drawing, Model A150 Preamplifier,
P/N 93A150–20 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A–13
A–12. Outline and Dimension Drawing, Model A55 Microphone,
P/N 93A055–00 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A–14
A–13. Outline and Dimension Drawing, Model A55B Microphone,
P/N 93A055–10, –30, –50 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A–15
A–14. Outline and Dimension Drawing, Model A55B Microphone,
P/N 93A055–20, –55 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A–16
A–15. Outline and Dimension Drawing, Model A55B Microphone,
P/N 93A05540, –45 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A–17
A–16. Outline and Dimension Drawing, Model A55B Microphone
P/N 93A055–60, –65, –67 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A–18
A–17. Outline and Dimension Drawing, Model A55B Microphone,
P/N 93A055–66 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A–19
A–18. Outline and Dimension Drawing, Model A55B Microphone,
P/N 93A055–95 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A–20
B–1.
Calibrated Sound Source, P/N 9300A870 . . . . . . . . . . . . . . . . . . . . . . . . . B–3
B–2.
Cockpit Voice Recorder System Test Panel, P/N 9300A860 . . . . . . . . . . . B–3
B–3.
Condenser Remote Microphone Test Setup . . . . . . . . . . . . . . . . . . . . . . . . B–4
Installation & Operation
Instruction Manual
Model A100 / A100A CVR
1.0
INTRODUCTION
1.1
Purpose
The information contained within this Installation Manual describes the administrative and
technical aspects, features, functions, components, and operation of the A100/A100A Cockpit Voice Recorder (CVR) system and it’s accessories and components. 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 of L–3
Communications Aviation Recorders.
The following L–3 Aviation Recorders are covered in this Installation & Operation Instruction Manual:
Part Number
93A10010
93A10011
93A10030
93A10031
93A10032
93A10033
93A10080
93A10081
93A10082
93A10083
93A10084
93A10085
1.2
Model
A100
A100
A100
A100
A100
A100
A100A
A100A
A100A
A100A
A100A
A100A
Mount
No
No
Yes
Yes
Yes
Yes
Yes
No
Yes
Yes
Yes
No
ULB
No
No
Yes
Yes
No
No
Yes
No
No
Yes
No
No
Inverter Installed
No
Yes
No
Yes
Yes
No
No
No
No
Yes
Yes
Yes
System Description and Limitations
The Cockpit Voice Recorder system has been designed to meet or exceed those requirements
specified within and is approved under Federal Aviation Administration Technical Standard
Order C84 or C111.
The Cockpit Voice Recorder system is composed of three essential components: the Recorder
Unit, Control Unit Components with area microphone module, and Vibration Mount. A
Heavy–Duty Vibration Mount is available for rotorcraft installations.
The CVR simultaneously records four separate voice inputs. These inputs may be either
transmitted or received signals originating from the following recommended stations: Pilot,
Co–Pilot, Public Address or Third Crew Member, and Cockpit Area Microphone.
Rev. 02
July 01/02
165E2807-00
Page 1
Model A100 / A100A CVR
Installation & Operation
Instruction Manual
EXTERNAL PREAMP
AREA MICROPHONE
INVERTER (OPTIONAL)
CONTROL UNIT
MAIN RECORDER
Cockpit Voice Recorder, Model A100
Figure 1
165E2807-00
Page 2
Rev. 02
July 01/02
Installation & Operation
Instruction Manual
Model A100 / A100A CVR
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 be
sought through the appropriate offices of the Federal Aviation Administration or other certifying agency. Aprovals may be accomplished on a Field Approval basis if the installation is
determined to meet the criteria of the appropriate Post–installation, Pre–flight, and Flight test
specificed 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.
1.3
Recorder Unit
The recorder is housed in an inertnational orange, 1/2 ATR short case. It contains the recorder assembly and associated electronics. (See Section 2.1 for leading particulars.) Recorder
Models A100 and A100A can be used in any system configuration and are totally interchangeable. 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 and
A152B house microphone pre–amplifier, microphone, test switch, erase switch, and meter.
Models A151 and A151B house microphone pre–amplifier, test switch, erase switch, and meter. (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 limitations exist. Remote microphone modules are used in conjunction with control unit Models
A151 and A151B. (Refer to Sections 2.3 through 2.4 for leading particulars.)
1.6
Installation Accessories
A. Vibration Mount P/N 9300–343
Standard 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) hold–down screws on the front of the mount lock the Recorder Unit into postion.
Rev. 02
July 01/02
165E2807-00
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Model A100 / A100A CVR
Installation & Operation
Instruction Manual
B. Heavy Duty Vibration Mount P/N 93–955
Mount for use in aircraft environments where excessive vibration may occur, such as
in 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 9300–435
Connector attaches to Vibration Mount and mates with connector on rear panel of
CVR. Aircraft wiring is soldered to the pins of the connector.
D. Inverter P/N 9300–A140–01 (Supersedes P/N 9300–A140)
Optional 28 VDC to 115 VAC 400 Hertz inverters are available. Inverter may be
plugged into available connector internal to the recorder. See Section 3.7 for Installation procedure. Jumper must be added accross Pins 1 & 2 of the mount connector
(P/N 9300–435, Cannon P/N DPXB–57–33S–0001). When DC power is used, a
means should be provided to stop recording after powered flight has been terminated.
165E2807-00
Page 4
Rev. 02
July 01/02
Installation & Operation
Instruction Manual
Model A100 / A100A CVR
communications
NAME:
PART NO.:
SER. NO.:
MODEL:
INĆBAND S ROTOR SPEED ENCODER
253E0873-00
XXXX
DATE MFG. MO/YR
N/A
0.5
WT.
LBS.
FAIRCHILD MODIFICATIONS
1 O 2 O 3 O 4 O 5 O 6 O 7 O 8 O 9 O 10 O
11 O 12 O 13 O 14 O 15 O 16 O 17 O 18 O 19 O 20 O
21 O 22 O 23 O 24 O 25 O 26 O 27 O 28 O 29 O 30 O
1.69"
4.18"
3.36"
.50"
NAME PLATE
Encoder PWA,
P/N 205E0899-00
15-PIN DĆSUB CONNECTOR, CANNON DA-15P
Rotor Speed Encoder, P/N 253E0873–00
Figure 2
E. Rotor Speed Encoder P/N 93–A289
An optional Rotor Speed Encoder is available for use in rotorcraft. The Rotor Speed
Encoder module meets CAA requirements for CVR rotor speed recording. The Rotor
Speed Encoder allows for simultaneous recording of rotor speed data and voice on the
same audio channel. It uses a subcarrier at 4600 Hz which is phase modulated. (See
Figure 2 for description.)
Rev. 02
July 01/02
165E2807-00
Page 5
Model A100 / A100A CVR
Installation & Operation
Instruction Manual
ROTOR SPEED ENCODER
P/N 93-A289
BULKHEAD MOUNTING OF RSE
P/N 93-A324
VIBRATION MOUNTING OF RSE
P/N 93-A291
fwvib
Rotor Speed Encoder Typical Mounting Installations
Figure 3
165E2807-00
Page 6
Rev. 02
July 01/02
Installation & Operation
Instruction Manual
F.
F.
Model A100 / A100A CVR
Rotor Speed Encoder Mount P/N 93–A291
An optional Rotor Speed Encoder mount is available to directly mount the Rotor
Speed Encoder to the Vibration Mount. (See Figure 3 for description.)
Rotor Speed Encoder Bracket P/N 93–A324
An optional Rotor Speed Encoder bracket is available to mount the Rotor Speed Encoder to the airframe, a bulkhead, etc. A 15–pin connector is attached to provide interconnection with the CVR. (See Figure 3 for description.)
2.0
EQUIPMENT LIMITATIONS / SPECIFICATIONS
2.1
Leading Particulars – Model A100 and A100A Recorders
Designed to TSO–C84 and ARINC Characteristic 557.
Size:
1/2 ATR Short
4 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 operation
50 Watts max bulk erase
Connections:
See Interwiring Diagram
Mating Connector:
DPXB–57–33S–001 (L–3 P/N 9300–435)
Tape (Endless Loop):
1/4” preconditioned recording tape, mylar base
Transport Drive:
Direct – No clutches
Tape Speed:
Standard NARTB; 1–7/8 ips
Channels:
4 in–line – coincident recording
Recording Duration:
30 minutes minimum
Head Assembly:
Precision aligned – 3 heads
Bulk Erase:
Fail–safe, double electrical interlock. Total erase in
excess of 35 dB
Operational Testing:
Automatic four channels sequential
600 Hz audio signal recorded and reproduced to trigger a go–no–go gate controlled meter indicator.
Frequency Response:
150 to 5000 Hz + 3 dB
Recorded Signal to Noise
Ratio:
45 dB min
Monitor System:
Composite 4 channel playback
Monitor Output:
Headphone jack, 600 Ohms, 10 mW
Harmonic Distortion:
Less than 5%
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165E2807-00
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Model A100 / A100A CVR
2.2
2.3
Installation & Operation
Instruction Manual
Flutter:
1.5% RMS maximum
Audio Input Impedance:
5000 Ohms each channel
Basic Subassemblies:
10 plug–in boards
Tape transport
Environmental protection
Leading Particulars – Model A151, A151B, A152, A152B Control Units
Size:
ATA Panel
5.75” Width by 2.25” Height by 2.5” Depth
Color:
Grey, Black, or Brown
Weight (Max):
1.2 lbs.
Connector:
MS3112–20–41P
Mating Connector:
P/N 9300–458
Cannon P/N MS–3116–F20–41S
Front Panel:
Meter
Test Switches (2)
Headset Jack
Microphone (Models A152 & A152B only)
AGC:
Fast reacting 30 dB range
Low distortion
True AC attenuation
Audio Input Impedance:
20K Ohms
Audio Input Level:
3 mV
Ouput Impedance:
300 Ohms
Output Level:
500 Millivolts
Audio Frequency
Response:
150 – 5000 Hz
Audio Gain:
Pin selected 6, 12, 24, dB steps
DC Supply:
Plus 18 Volts
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 RB1–M–0
165E2807-00
Page 8
Rev. 02
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Installation & Operation
Instruction Manual
2.4
Model A100 / A100A CVR
Mating Connector:
P/N 9300–457
Cannon P/N 150–900–0303
Mounting:
Front or Rear Panel
Microphone:
Dynamic Type
Leading Particulars – Model A55B Remote Microphone Module
For all Model A55B Part Numbers, except 93–A055–40 and 93–A055–45 Remote Microphones.
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 RB1–M–0
Mating Connector:
P/N 9300–457
Cannon P/N 150–900–0303
Mounting:
Front or Rear Panel
Microphone:
Condenser Type
For only the Model A55B Part Numbers 93–A055–40 and 93–A055–45 Remote Microphones.
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
Rev. 02
July 01/02
165E2807-00
Page 9
Model A100 / A100A CVR
3.0
Installation & Operation
Instruction Manual
INSTALLATION INSTRUCTIONS
Installation of the recorder, control unit, and remote microphone module is based on ARINC
Characteristic 557, dated January 10, 1964.
3.1
General Information
This section contains considerations and recommendations for installation of the Cockpit
Voice Recorder and associated system components. Interconnect harness wiring, physical
mounting, optional components (preamplifiers and summing amplifiers) must be considered
when requirwed to satisfy all applicable regulations. The conditions and tests required for
TSO approval of this article are minimum performance standard. 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 standard, 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 FAR23.1457, 25.1457, and
29.1457 appropriate to the category of operation under FAR Parts 91, 135, and 121 (Air Carrier).
The CVR system is powered by 115 VAC. It may also be powered by 28 VDC from the essential aircraft bus source, when the optional DV inverter is installed.
To ensure optimal performance from the Cockpit Voice Recorder System, the following wire
sizes 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 MIL–W–22759 or
MIL–C–27500.
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 to
minimize random noise pcikup.
E. Normal power requirements are:
20 Watts maximum during normal operation.
50 Watts maximum during bulk erase.
165E2807-00
Page 10
Rev. 02
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Installation & Operation
Instruction Manual
Model A100 / A100A CVR
The BULK ERASE connection is not mandated by the FAA and, therefore, it is an installation option. The circuitry required for BULK ERASE includes the installation of interlock
devices aboard the aircraft. If the BULK ERASE feature is installed, then at least one (1) interlock is required to prevent accidental erasure of the CVR tape. If the BULK ERASE feature 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 mV
RMS.
Earlier aircraft audio systems may require rework of their audio system to ensure recording
of ATC, Intercom, Mask Microphone, and Sidetone audio, independant of mode selection on
the audio control panel. In some cases, selection of the Loud Speaker function disables side
tone output and, therefore, transmissions to ATC may not be recorded. Such condition must
be 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 install
an external summing amplifier. Summing amplifiers can be obtained from Avtec, Baker
Electronics, Racal, and others. (See Appendix B & C for examples.) The addition of a summing 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 installation.)
New 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.
Future Systems – Those audio control panels and systems designed to meet or exceed the
characteristics found in Radio Technical Commission for Aeronautics (RTCA), DO–170 for
“hot” 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 of
the following conditions: Heated/unheated, pressurized/unpressurized, hard mounted/shock
mounted.
For long term reliability it is recommended that recorders be mounted within the vibration
mount in an upright position (vertical as viewed from the front) in a heated, pressurized area
in a fuselage location, as far aft as practical. Refer to FAA Advisory Circular 25.1457–1A
for further details.
Rev. 02
July 01/02
165E2807-00
Page 11
Model A100 / A100A CVR
Installation & Operation
Instruction Manual
3
1
2
2
3
RECOMMENDED MICROPHONE LOCATIONS
ARE NUMBERED IN ORDER OF PREFERENCE
Recommended Cockpit Area Microphone Mounting Locations
Figure 4
3.4
Microphone Installation Criteria
The most desirable location for the cockpit area microphone is forward of a vertical plane
oriented laterally through the pilot’s and co–pilot’s normal head position. The area microphone 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 and
prevent each erasure feature from functioning, within 10 minutes after crash impact.” The
Installer must demonstrate this function.
165E2807-00
Page 12
Rev. 02
July 01/02
Installation & Operation
Instruction Manual
Model A100 / A100A CVR
Since the CVR system can be powered by either 115 VAC, 400 Hz or 28 VDC (with optional
inverter), the following methods are acceptable to ensure automatic cessation of recording:
3.6
1.
IMPACT SWITCH – Interrupts CVR power upon exposure to a predertimed level of
g–force. Such switches have limitations, but are effective in high g–force accidents.
This item is not available through L–3 Communications. (See Appendix A and F for
manufacturer’s specifications for models available.)
2.
If power input is derived directly from the engine–driven 115 VAC, 400 HZ source,
(not derived from AC Inverter), no other external circuitry is necessary. It is assumed
that the engine(s) will stop upon crash impact.
Installation in Rotorcraft
The Heavy Duty Dibration Mount P/N 93–955 is recommedned for rotorcraft installations. It
has 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 with
the CVR system. (See Figure 3.) The first configuration affixes the Encoder module directly
onto a heavy–duty vibration mount, P/N 93–A291. The second configuration mounts the
RSE module on a small bracket, P/N 93–A324, away from the CVR. This bracket must be
attached to a bulkhead or a similar rigid surface.
The Rotor Speed Encoder has interlock circuitry which will prevent the CVR Bulk Erasure
while the main rotor(s) is rotating. If the rotorcraft CVR system is not equipped with a RSE
or 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 Pin
57 remains open to satisify appropriate Federal Aviation Regulations.
Rev. 02
July 01/02
165E2807-00
Page 13
Model A100 / A100A CVR
Installation & Operation
Instruction Manual
INVERTER RAIL
STUDS (4 PLACES)
4–40X5/16
BINDING HEAD
SCREWS
CHASSIS
JOINT
CABLE GUARD
P/N 9300–428
DETAIL A
DETAIL B
CONNECTOR
P.N 9300–232
INVERTER
DETAIL C
Inverter Installation
Figure 5
3.7
Installation Procedure for Inverter, P/N 9300–A140–01
This procedure applies only to the optional installation of the Inverter into Model A100 and
A100A Cockpit Voice Recorders. See Figure 5.
1.
Remove dust cover by removing two phillips head screws, exposing chassis wiring
assembly.
2.
Remove two 4–40 by 5/16 binding head screws located on the rear of the chasis. (See
Detail A.) Discard attaching lock nuts.
165E2807-00
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Rev. 02
July 01/02
Installation & Operation
Instruction Manual
3.8
Model A100 / A100A CVR
3.
Insert cable guard, P/N 9300–428, as shown in Details A and B, ensuring the slotted
end 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 4–40 by 5/16 binding head screws removed in Step 2, securing the Inverter.
6.
Replace the dust cover using two phillips head screws.
7.
Refer to the CVR Component Maintenance Manual, P/N 165E0101–00, for Electrical
Test of Inverter.
Post–Installation Checkout Procedures
The following tests and procedural results must be documented in the CVR Installation
Checklist and submitted with the date package for field approval consideration.
A. Before applying power to the CVR system and associated components, verify that all
connections are secure and that a continunity or other interconnect assurance test has
been conducted.
B. Apply power to the system and activate the Cockpit Voice Recorder self–test. To activate, push and hold the green “TEST” button for a minimum of five seconds. An internal 600 Hz test tone generator is keyed and sequentially switches through the four
channels of the recorder. Each channel receives the test tone for approximately .8 seconds.
C. Monitor circuitry receives the test tone signals and drives the meter, a “GO–NO–GO”
indicating device, located on the Cockpit Control Unit. The meter needle rises and
comes 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, the
meter needle 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 channel failure, the meter needle will fall out of the green section of the meter scale or return to zero and give a definite “NO–GO” indication.
D. Aural monitoring of the 600 hertz test tone and channel switching can be accomplished with a 600 ohm headset inserted into the Jack located on the Cockpit Control
Unit.
With the headset inserted into the Jack located on the Cockpit Control Unit, speak in a
normal voice 6” away from the Cockpit Control Unit microphone and note that you
can hear what you speak with approximately a 1/2 second delay without any significant distortion. This test ensures the microphone is operating.
Rev. 02
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165E2807-00
Page 15
Model A100 / A100A CVR
Installation & Operation
Instruction Manual
E. Verify that the following microphone inputs are recorded on their appropriate CVR
channels, regardless of Audio Control Panel mode or audio (communications radio)
selection, for Cockpit Voice Recorder installations within aircraft or rotorcraft intended for service within the National Airspace Systems:
CHANNEL 1:
CHANNEL 2:
CHANNEL 3:
CHANNEL 4:
F.
Third Crewmember Station or Public Address Systems.
Primary Co–Pilot’s Boom, Mask, and Hand Microphone Input.
Primary Pilot’s Boom, Mask, and Hand Microphone Input.
Cockpit Mounted Area Microphone.
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 of
2 seconds), verify function by listening for loud 400 Hz tone through the “HEADSET”
jack. 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. Therefore, it is to be performed before every flight or whenever maintenance has been performed
on the aircraft or rotorcraft which may have affected the performance of the Cockpit Voice
Recorder 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 seconds. A 600 hertz generator is keyed and sequentially switched through the four channels of
the recorder. Each channel receives the test tone for approximately 0.8 seconds. The meter
circuit receives these signals and drives the meter, a ’GO–NO–GO” indicating device, located
on 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 meter
needle 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 channel
failure, the meter needle will fall out of the green section of the meter scale or return to zero
and give a definite ’NO–GO’ indication.
4.2
Complete Audio System Test
A test of the Cockpit Area Microphone can be accomplished with a 600 Ohm headset inserted 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 audible
clarity after approximately a 1/2 second delay without any significant distortion. This test
ensures that the Cockpit Area Microphone is operating.
165E2807-00
Page 16
Rev. 02
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Installation & Operation
Instruction Manual
Model A100 / A100A CVR
A complete Audio System Interface test must be completed during each annualinspection or
specified maintenance period on the aircraft or rotorcraft and whenever unscheduled maintenance is performed on the aircraft or rotorcraft which may have affected the performance of
the Cockpit Voice Recorder system. To accomplish this test, the Pilot’s, Co-pilot’s, Cockpit
Area Microphone, and Third Crewmember or Public Address System inputs must be individually checked for their operational integrity with the Cockpit Voice Recorder. Upon satisfactory achievement of this test, an entry shall be made in the maintenance records of the aircraft
or rotorcraft.
5.0
INSTALLATION ACCEPTANCE BY FIELD APPROVAL METHOD
An applicant for Field Approval of a CVR installation must be properly certificated and appropriately rated, qualified, and equipped to accomplish the installation and approve the aircraft or rotorcraft for return–to–service. The CVR should be installed in accordance with the
instructions and limitations contained within this Installation Manual.
Drawings and other information, such as structural related data to show the method of attachment of the CVR components to the airframe, wiring diagrams, appropriate weight and balance data, identification of all CVR system components used in the installation should be
made available to the Inspector conducting the Field Approval.
The CVR Installation Manual containing Operating Instructions and System descriptions
must 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 airframe
to accomplish the installation of the CVR system. The Form 337 must also include a statement 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 is
installed within the recommended locations identified within FAA Advisory Circular
25.1457–1A and in accordance with the instructions contained within this Installation Manual.
The applicant should submit all appropriate data and drawings to the Inspector prior to begining the installation of the Cockpit Voice Recorder.
Any deviations to the installation instructions contained within this Installation Manual must
be 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 is
satisfactory and that “normal” conversation can be discerned from the Cockpit Area Microphone and the individual Pilot, Co–pilot, and appropriate Third Crewmember or Public Address stations. The CVR System must be found to be free of any objectionable audio interference and other unwanted noise in order to ensure discernible recordings. Any
discrepancies identified during the ground and flight tests must be brought to the attention of
the Inspector and corrected before the aircraft can be returned to service.
Rev. 02
July 01/02
165E2807-00
Page 17
Model A100 / A100A CVR
Installation & Operation
Instruction Manual
If required, L–3 can reproduce the CVR tape contents onto a cassette for channel seperation
and 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 Beacon (ULB). Both units are manufacturered under a Parts Manufacturer Approval. The beacon is attached on the front panel for easy removal for replacement of the battery, and for
easy viewing of the battery expiration date.
The Model DK 100 contains a battery life of 6 years prior to its actual operating life of at
least 30 days. The battery must be replaced by Dukane upon expiration.
6.2
6.3
Product Support
Mailing address:
L–3 Communications
Aviation Recorders
P.O. Box 3041
Sarasota, Florida 34230–3041
Attention: Product Support, Mail Stop 20
Telephone:
(941) 371–0811
Telefax:
(941) 377–5591
SITA:
SRQLFCR
Web Site:
www.L–3AR.com
Authorized Repair Facilities
L–3 Communications Aviation Recorders performs repair, overhaul, and readout services for
the A100 / A100A Cockpit Voice Recorder System. Items should be shipped to the following
address:
L-3 Communications
Aviation Recorders
6000 Fruitville Road
Sarasota, Florida 34232
Attention: Repair Station
Questions concerning SSFDR repair or readout service may be answered by calling the Aviation Recorders’ Repair Station at (941) 377–5554 or (941) 377–5579, or by calling the Product Support Department at (941) 371–0811. Readout Service is performed by the Repair Station.
165E2807-00
Page 18
Rev. 02
July 01/02
Installation & Operation
Instruction Manual
Model A100 / A100A CVR
L–3 Communications Aviation Recorders has factory trained technicians at each Authorized
Repair Facility located worldwide, who are capable of performing repair, overhaul, readout,
and loaner / rental services. Contact the Product Support Department for names and locations.
6.4
Loaner / Rental Program
L–3 Communications Aviation Recorders’ Authorized Repair Facilities are capable of providing loaner / rental CVRs. Some facilities may not charge for loaner CVRs if the repair /
overhaul work is performed by that repair facility.
Aviation Recorder’s Product Support Department maintains a limited supply of Rental Cockpit Voice Recorders. Please contact the Product Support Department for availability and pricing.
Rev. 02
July 01/02
165E2807-00
Page 19
Model A100 / A100A CVR
Installation & Operation
Instruction Manual
Bias Gen.
65 kHz
A021
SYSTEM
BLOCK DIAGRAM
Ch No. 1
Extra
RECORD HEAD
SHOWN 90 ROTATED
FOR CLARITY
Ch No. 2
Co Pilot
Record
Record Amp
A020
Ch No. 4
Area Mic
Play
Record Amp
A020
Control Unit A151B
Bulk
Erase
Test
Test
Meter
Bulk Erase
Monitor
Amp
A023-(XX)
DC/AC
Inverter
A140
Optional
(A140-01)
Test 600 Hz
A025-(XX)
Head Phone
Aircraft
Wiring
Erase
Record Amp
A020
A55B
MIC
Tape Transport
Protected
Record Amp
A020
Ch No. 3
Pilot
Remote Mic
MIC
Pre Amp
A266-(XX)
Head Phone
Recorder A100A
Bulk Erase
A024
Power
Supply
A022-(XX)
115V 400Hz
Timer Board
A098
Cockpit Voice Recorder System Control Unit A151B,
Functional Block Diagram
Figure 6
165E2807-00
Page 20
Rev. 02
July 01/02
28VDC
Installation & Operation
Instruction Manual
Model A100 / A100A CVR
Ch No. 1
Extra
SYSTEM
BLOCK DIAGRAM
Recorder A100
Bias Gen.
65 kHz
A021
Tape Transport
Protected
Record Amp
A020
Ch No. 2
Co Pilot
RECORD HEAD
SHOWN 90 ROTATED
FOR CLARITY
Erase
Record Amp
A020
Ch No. 3
Pilot
Record
Record Amp
A020
Ch No. 4
Area Mic
Play
Record Amp
A020
Control Unit A152B
Test
Meter
MIC
Pre Amp
A266-(XX)
MIC
Bulk
Erase
Test
Meter
Monitor
Amp
A023-(XX)
Head Phone
Test
1
2
3
4
all
Test 600 Hz
A025
Head Phone
Aircraft
Wiring
Bulk Erase
Bulk Erase
A024
DC/AC
Inverter
A140
Optional
(A140-01)
Power
Supply
A022-(XX)
115V 400Hz
Timer Board
A098
Cockpit Voice Recorder A100 and Control Unit A152B,
Functional Block Diagram
Figure 7
Rev. 02
July 01/02
165E2807-00
Page 21
28VDC
Model A100 / A100A CVR
Installation & Operation
Instruction Manual
TOP MOUNTING
TAPE
MOTION
0.25"
NOTE: OXIDE VIEW OF TAPE
NOTE:
CH 3
PILOT
CH 1
3rd CREW
CH 4
COCKPIT AREA
CH 2
CO-PILOT
ARINC
FAA
BACK VIEW
OF HEAD
PER FAA ACTION NOTICE A8300.56 DATED JANUARY 24, 1990,
THE WIRING TO CHANNELS 1 AND 3 MUST BE TRANSPOSED; i.e.,
CHANNEL 1 WILL BE PILOT AND CHANNEL 3 WILL BE 3RD
CREWMEMBER OR PA. THIS CONFIGURATION VARIES FROM THE
ARINC 557 WIRING.
Channel Allocation in CVRs
Figure 8
165E2807-00
Page 22
Rev. 02
July 01/02
Installation & Operation
Instruction Manual
Model A100 / A100A CVR
VOICE RECORDER UNIT
ALL MODELS A100 OR A100A
STANDARD INTERWIRING PER ARINC SPEC 557
TO 27.5 VAC HOT (400HZ)
TO AC COLD
1
AMP
TO 27.5VDC
5
AMPS
*4
CONTROL UNIT ALL MODELS A151 OR A151B
PUSHćTOćTEST
PREćAMP POWER GND
PREćAMP POWER +18 VDC
INDICATOR +
INDICATOR ć
CHASSIS GROUND
ERASE SWITCH A"
ERASE SWITCH C"
OUTPUT ć LOW
OUTPUT ć HIGH
MIKE CABLE SHIELD
MIKE INPUT HI
MIKE INPUT LO
FILTER COMMON
FILTER 1.000 HZ
*6
AUDIO JACK LO
AUDIO JACK HI
5V LAMP HOT
LAMP COMMON COLD
28V LAMP HOT
(RESERVED)
(RESERVED)
SUGGESTED SPARE NO. 1
SUGGESTED SPARE NO. 2
SUGGESTED SPARE NO. 3
6 DB ATTENUATION
ATTENUATOR MASTER
12 DB ATTENUATION
24 DB ATTENUATION
A
B
C
D
E
F
G
H
J
K
L
M
N
P
R
S
T
U
V
W
X
Y
Z
a
b
c
d
e
f
g
h
i
j
k
p
q
r
s
t
*4
TO 3RD CREW
MEMBER OR PA
*5
*8
TO COPILOT
TO PILOT
AREA MIKE
*7
*4
MIICROPHONE MODEL
A55 OR A55B
MIKE OUTPUT HI (AUDIO)
MIKE OUTPUT LO ( DC IN )
MIKE SHIELD
(CONNECTOR SHELL)
1
2
*2
*8
*9
BRAKE
GEAR
1. 115 Vac HOT OUT
2. 115 Vac HOT IN
3. AC COMMON COLD
4.
5. AUDIO OUT LO
6. AUDIO OUT HI
7. BIAS JUMPER
8. BIAS JUMPER
9. +27.5 Vdc INPUT (with inverter)
10. (reserved)
11.
12. PUSH–TO–TEST
13. PREAMP POWER GND
14. PREAMP POWER +18 Vdc REG
15. INDICATOR +
16. INDICATOR –
17. CHASSIS GROUND
18. (reserved)
19. (reserved)
20.
21.
22.
23. SUGGESTED SPARE NO. 1
24. SUGGESTED SPARE NO. 2
25. SUGGESTED SPARE NO. 3
26.
27.
28.
29.
30. LO
31.
CHANNEL 1
32. HI
33.
34.
35. LO
36.
CHANNEL 2
37. HI
38.
39.
40.
41. LO
42.
CHANNEL 3
43. HI
44.
45. LO
46.
CHANNEL 4
47. HI
48.
49.
50.
51.
52.
53.
54.
55. ERASE A
56.
57. ERASE C
NOTES: *1 Rec. min. wire size is #22. #24 is acceptable except for long–run power leads where #18 is rec. (pins 2,3,17, & 19)
*2 Ground connection to be within 1 ft. of pin 17.
*3 Only one power source to be wired per aircraft. If 115Vac, 400 Hz is supplied, no connection to be made to
pin #9. If 27.5Vdc is supplied, no connection to be made to pin #3.Short pins 1 & 2, be sure inverter is used.
*4 Single Ground Point
*5 If meter illumination is included in Control Unit, supply voltage from lighting bus to proper pins.
*6 Short S & T for piston aircraft only.
*7 Wiring shown for standard fixed atten. of 18 dB per ARINC 557.
*8 Control Units A151 or A152 to be used with Mike Modules A55 only. Control Units A151B or A152B to be used with Mike
Modules A55B only.
*9 Model 40 Series & Model 60 series’ microphone output cabling colors are reversed: on the ‘40 Series the
white wire is the “high” (audio side), and on the 60 series, the white wire is the “LO” ( dc in ).
Interwiring Diagram, Recorders A100, A100A, Control Units A151, A151B,
Remote Microphones A55, A55B
Figure 9
Rev. 02
July 01/02
165E2807-00
Page 23
Model A100 / A100A CVR
Installation & Operation
Instruction Manual
VOICE RECORDER UNIT
ALL MODELS A100 OR A100A
STANDARD INTERWIRING PER ARINC SPEC 557
RECORDER A100 OR A100A WITH CONTROL UNIT A152 OR A152B
1
AMPS
TO 27.5 VAC HOT (400HZ)
TO AC COLD
TO 27.5VDC
5
AMPS
*4
CONTROL UNIT ALL MODELS A152 OR A152B
PUSHćTOćTEST
PREćAMP POWER GND
PREćAMP POWER +18 Vdc
INDICATOR +
INDICATOR ć
CHASSIS GROUND
ERASE SWITCH A"
ERASE SWITCH C"
OUTPUT ć LOW
OUTPUT ć HIGH
(RESERVED)
MIKE INPUT HI
MIKE INPUT LO
FILTER COMMON
FILTER 1.000 HZ
*6
AUDIO JACK LO
AUDIO JACK HI
5V LAMP HOT
LAMP COMMON COLD
28V LAMP HOT
INTERNAL MIKE HIGH
INTERNAL MIKE LOW
SUGGESTED SPARE NO. 1
SUGGESTED SPARE NO. 2
SUGGESTED SPARE NO. 3
6 DB ATTENUATION
ATTENUATOR MASTER
12 DB ATTENUATION
24 DB ATTENUATION
A
B
C
D
E
F
G
H
J
K
L
M
N
P
R
S
T
U
V
W
X
Y
Z
a
b
c
d
e
f
g
h
i
j
k
m
n
p
q
r
s
t
*4
*2
TO 3RD CREW
MEMBER OR PA
*5
*8
TO COPILOT
TO PILOT
AREA MIKE
*7
*4
BRAKE
GEAR
1.
2.
3.
4.
5.
6.
7.
8.
9.
10.
11.
12.
13.
14.
15.
16.
17.
18.
19.
20.
21.
22.
23.
24.
25.
26.
27.
28.
29.
30.
31.
32.
33.
34.
35.
36.
37.
38.
39.
40.
41.
42.
43.
44.
45.
46.
47.
48.
49.
50.
51.
52.
53.
54.
55.
56.
57.
115 Vac HOT OUT
115 Vac HOT IN
AC COMMON COLD
AUDIO OUT LO
AUDIO OUT HI
BIAS JUMPER
BIAS JUMPER
+27.5 Vdc INPUT (with inverter)
(reserved)
PUSH–TO–TEST
PREAMP POWER GND
PREAMP POWER +18 Vdc REG
INDICATOR +
INDICATOR –
CHASSIS GROUND
(reserved)
(reserved)
SUGGESTED SPARE NO. 1
SUGGESTED SPARE NO. 2
SUGGESTED SPARE NO. 3
LO
CHANNEL 1
HI
LO
CHANNEL 2
HI
LO
CHANNEL 3
HI
LO
CHANNEL 4
HI
ERASE A
ERASE C
NOTES: *1 Rec. min. wire size is #22. #24 is acceptable except for long–run power leads where #18 is rec. (pins 2,3,17, & 19)
*2 Ground connection to be within 1 ft. of pin 17.
*3 Only one power source to be wired per aircraft. If 115VAC, 400 Hz is supplied, no connection to be made to
pin #9. If 27.5VDC is supplied, no connection to be made to pin #3.Short pins 1 & 2, be sure inverter is used.
*4 Single Ground Point
*5 If meter illumination is included in Control Unit, supply voltage from lighting bus to proper pins.
*6 Short S & T for piston aircraft only.
*7 Wiring shown for standard fixed atten. of 18 dB per ARINC 557.
*8 Jumper wires per ARINC 557, 1/2” max. length
Interwiring Diagram, Recorders A100, A100A, Control Units A152, A152B
Figure 10
165E2807-00
Page 24
Rev. 02
July 01/02
Installation & Operation
Instruction Manual
Model A100 / A100A CVR
VOICE RECORDER UNIT
ALL MODELS A100 OR A100A
STANDARD INTERWIRING PER ARINC SPEC 557
EXTERNAL PREAMP A150
1
AMPS
TO 27.5 VAC HOT (400HZ)
TO AC COLD
*3
TO 27.5VDC
5
AMPS
*4
EXTERNAL PREAMP
MODEL A150
J2
PREćAMP POWER
+18 VDC
PREćAMP POWER GND
PREćAMP OUT HI
PREćAMP OUT LO
ATTENUATION MASTER
CHASSIS GROUND
6DB ATTENUATION
B
C
D
E
F
G
H
J
K
L
M
MIC SIGNAL INPUT
MIC SUPPLY (+6.2VDC)
MIC SHIELD (GND)
A
B
C
24DB ATTENUATION
12DB ATTENUATION
J1
A
*2
TO 3RD CREW
MEMBER OR PA
MODEL A55B
MICROPHONE
(ANY PART MODEL)
MIC 6VDC SUPPLY (WHITE)
MIIC GND (SHIELD)
MIC OUTPUT (BLACK)
*4
1
TO COPILOT
2
TO PILOT
*4
1.
2.
3.
4.
5.
6.
7.
8.
9.
10.
11.
12.
13.
14.
15.
16.
17.
18.
19.
20.
21.
22.
23.
24.
25.
26.
27.
28.
29.
30.
31.
32.
33.
34.
35.
36.
37.
38.
39.
40.
41.
42.
43.
44.
45.
46.
47.
48.
49.
50.
51.
52.
53.
54.
55.
56.
57.
115 Vac HOT OUT
115 Vac HOT IN
AC COMMON COLD
AUDIO OUT LO
AUDIO OUT HI
BIAS JUMPER
BIAS JUMPER
+27.5 Vdc INPUT (with inverter)
(reserved)
PUSH–TO–TEST
PREAMP POWER GND
PREAMP POWER +18 Vdc REG
INDICATOR +
INDICATOR –
CHASSIS GROUND
(reserved)
(reserved)
SUGGESTED SPARE NO. 1
SUGGESTED SPARE NO. 2
SUGGESTED SPARE NO. 3
LO
CHANNEL 1
HI
LO
CHANNEL 2
HI
LO
CHANNEL 3
HI
LO
CHANNEL 4
HI
ERASE A
ERASE C
NOTES: *1 Recommended min. wire size is #22. #24 is acceptable except for long–run power leads where #18 is rec.
(pins 2,3,17, & 19)
*2 Ground connection to be within 1 ft. of pin 17.
*3 Only one power source to be wired per aircraft. If 115VAC, 400 Hz is supplied, no connection to be made to
pin #9. If 27.5VDC is supplied, no connection to be made to pin #3.Short pins 1 & 2, be sure inverter is used.
*4 Single Ground Point
NOTICE:
FAA action notice A8300.56, dated January 24, 1990, states that the pilot and area mic will be recorded on the inner two
tracks of the CVR. To conform to the above notice, some CVR installations will have the pilot connected to CVR channel
No. 1 and the third crew member connected to CVR channel no. 3. The channel designations under this new rule are:
Channel 1 = pilot; Channel 2 = co–pilot; Channel 3 = 3rd crew member; Channel 4 = area mic
Interwiring Diagram, Recorders A100, A100A, Control Units A150
Figure 11
Rev. 02
July 01/02
165E2807-00
Page 25
Model A100 / A100A CVR
Installation & Operation
Instruction Manual
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165E2807-00
Page 26
Rev. 02
July 01/02
Installation & Operation
Instruction Manual
Model A100 / A100A CVR
APPENDIX A
OUTLINE & DIMENSION
DRAWINGS
Rev. 02
July 01/02
165E2807-00
Page A-1
Model A100 / A100A CVR
Installation & Operation
Instruction Manual
THIS PAGE IS INTENTIONALLY BLANK.
165E2807-00
Page A-2
Rev. 02
July 01/02
Installation & Operation
Instruction Manual
Model A100 / A100A CVR
Outline & Dimension Drawing, Model A100,
P/N 93A100–10, –11
Figure A–1
Rev. 02
July 01/02
165E2807-00
Page A-3
Model A100 / A100A CVR
Installation & Operation
Instruction Manual
Outline & Dimension Drawing, Model A100 with Beacon
and Beacon Mount, P/N 93A100–30, –31, –32, –33
Figure A–2
165E2807-00
Page A-4
Rev. 02
July 01/02
Installation & Operation
Instruction Manual
Model A100 / A100A CVR
Outline & Dimension Drawing, Model A100A,
P/N 93A100–81
Figure A–3
Rev. 02
July 01/02
165E2807-00
Page A-5
Model A100 / A100A CVR
Installation & Operation
Instruction Manual
Outline & Dimension Drawing, Model A100A with Beacon,
and Beacon Mount, P/N 93A100–80, –82, –83, –84, –85
Figure A–4
165E2807-00
Page A-6
Rev. 02
July 01/02
Installation & Operation
Instruction Manual
Model A100 / A100A CVR
CENTER OF GRAVITY
LOCATION OF MOUNT ASSY
ÇÇÇÇÇÇÇÇÇ
ÇÇÇÇÇÇÇÇÇ
ÇÇÇÇÇÇÇÇÇ
ÇÇÇÇÇÇÇÇÇ
NAMEPLATE
NAME: MOUNT, TRAY
PART NO: 9300–343
SER. NO: XXX
DATE MFG:
MO/YR
MODEL NO: WEIGHT: 1.6 LBS
OPTIONAL REAR
MOUNTING ADAPTER
9300–A075 FOR AC/DC
INVERTER REQUIRES
ADDITION OF 0.166
HOLES
ONE END OF GROUND STRAP
ATTACHED AS SHOWN. OTHER
END ATTACHED AT INSTALLATION BY MOUNTING SCREW
(#8–32 X .88 LONG FHMS.)
1.90 MAX.EXTENDED HEIGHT
1.64 MIN. BOTTOM HEIGHT
DIMENSIONS ARE IN INCHES.
Outline & Dimension Drawing,
CVR Vibration Mount, P/N 9300–343
Figure A–5
Rev. 02
July 01/02
165E2807-00
Page A-7
Model A100 / A100A CVR
Installation & Operation
Instruction Manual
Outline & Dimension Drawing,
Heavy Duty CVR Vibration Mount, P/N 93–955
Figure A–6
165E2807-00
Page A-8
Rev. 02
July 01/02
Installation & Operation
Instruction Manual
Model A100 / A100A CVR
CONTROL UNIT
MODEL A151
PNR 93–A151–XX
SER XXXXXXXXX
MFR 06141
DMF MMYYYY
Part Number
93A15100
93A15101
Model
A151
A151
Meter
Illumination
None
None
Microphone
None
None
Panel Color
Grey
Black
Outline and Dimension Drawing,
Model A151 Control Unit, P/N 93A15100
Figure A–7
Rev. 02
July 01/02
165E2807-00
Page A-9
Model A100 / A100A CVR
Installation & Operation
Instruction Manual
CONTROL UNIT
MODEL A151B
PNR 93–A151–XX
SER XXXXXXXXX
MFR 06141
DMF MMYYYY
communications
Part Number
93A15120
93A15130
93A15140
93A15150
Model
A151B
A151B
A151B
A151B
Meter
Illumination
None
None
None
None
Microphone
None
None
None
None
Panel Color
Grey
Black
Brown (Boeing)
Brown (ATR–42)
Outline and Dimension Drawing, Model A151B Control Unit
P/N 93A151–20, –30, –40, –50
Figure A–8
165E2807-00
Page A-10
Rev. 02
July 01/02
Installation & Operation
Instruction Manual
Model A100 / A100A CVR
CONTROL UNIT
MODEL A152A
PNR 93–A152–XX
SER XXXXXXXXX
MFR 06141
DMF MMYYYY
communications
Part Number
93A15200
93A15201
93A15204
Model
A152
A152
A152
Meter
Illumination
None
28V
5V
Microphone
Dynamic
Dynamic
Dynamic
Panel Color
Grey
Black
Grey
Outline and Dimension Drawing,
Model A152 Control Unit, P/N 93A152–00
Figure A–9
Rev. 02
July 01/02
165E2807-00
Page A-11
Model A100 / A100A CVR
Installation & Operation
Instruction Manual
CONTROL UNIT
MODEL A152B
PNR 93–A152–XX
SER XXXXXXXXX
MFR 06141
DMF MMYYYY
communications
Part Number
93A15220
93A15225
93A15230
93A15235
93A15240
93A15250
93A15260
93A15270
Model
A152B
A152B
A152B
A152B
A152B
A152B
A152B
A152B
Meter
Illumination
None
None
28V
28V
5V
None
5V
None
Microphone
Condenser
Condenser
Condenser
Condenser
Condenser
Condenser
Condenser
Condenser
Panel Color
Grey
Grey
Black
Grey
Grey
Brown (Boeing)
Brown (Boeing)
Black
Outline and Dimension Drawing, Model A152B Control Unit
P/N 93A152–20, –30, –40, –50, –70
Figure A–10
165E2807-00
Page A-12
Rev. 02
July 01/02
Installation & Operation
Instruction Manual
Model A100 / A100A CVR
PREAMPLIFIER
MODEL A150
PNR 93–A150–20
SER XXXXXXXXX
MFR 06141
DMF MMYYYY
Part Number
93A15020
Model
A150
Panel Color
Black
Outline and Dimension Drawing,
Model A150 Preamplifier, P/N 93A150–20
Figure A–11
Rev. 02
July 01/02
165E2807-00
Page A-13
Model A100 / A100A CVR
Part Number
93A05500
Installation & Operation
Instruction Manual
Model
A55
Connector
Location
Microphone
Dynamic
Panel Color
Black
Outline and Dimension Drawing,
Model A55 Microphone, P/N 93A055–00
Figure A–12
165E2807-00
Page A-14
Rev. 02
July 01/02
Installation & Operation
Instruction Manual
Part Number
93A05510
93A05530
93A05550
Model A100 / A100A CVR
Model
A55B
A55B
A55B
Connector
Location
Rear
Rear
Rear
Microphone
Condenser
Condenser
Condenser
Panel Color
Black
Brown (Boeing)
Black
Outline and Dimension Drawing,
Model A55B Microphone, P/N 93A055–10, –30, –50
Figure A–13
Rev. 02
July 01/02
165E2807-00
Page A-15
Model A100 / A100A CVR
Part Number
93A05520
93A05555
Installation & Operation
Instruction Manual
Model
A55B
A55B
Connector
Location
Side
Side
Microphone
Condenser
Condenser
Panel Color
Black
Black
Outline and Dimension Drawing,
Model A55B Microphone, P/N 93A055–20, –55
Figure A–14
165E2807-00
Page A-16
Rev. 02
July 01/02
Installation & Operation
Instruction Manual
Part Number
93A05540
93A05545
Model A100 / A100A CVR
Model
A55B
A55B
Connector
Location
Pigtail
Pigtail
Microphone
Condenser
Condenser
Panel Color
Grey
Brown (ATR–42)
Outline and Dimension Drawing,
Model A55B Microphone, P/N 93A05540, –45
Figure A–15
Rev. 02
July 01/02
165E2807-00
Page A-17
Model A100 / A100A CVR
Part Number
93A05560
93A05565
93A05567
Installation & Operation
Instruction Manual
Model
A55B
A55B
A55B
Connector
Location
Pigtail
Pigtail
Pigtail
Microphone
Condenser
Condenser
Condenser
Panel Color
Grey
Brown (ATR–42)
Black
Outline and Dimension Drawing, Model A55B Microphone
P/N 93A055–60, –65, –67
Figure A–16
165E2807-00
Page A-18
Rev. 02
July 01/02
Installation & Operation
Instruction Manual
Part Number
93A05566
Model A100 / A100A CVR
Model
A55B
Connector
Location
Pigtail
Microphone
Condenser
Panel Color
Black
Outline and Dimension Drawing,
Model A55B Microphone, P/N 93A055–66
Figure A–17
Rev. 02
July 01/02
165E2807-00
Page A-19
Model A100 / A100A CVR
Part Number
93A05595
Installation & Operation
Instruction Manual
Model
A55B
Connector
Location
Pigtail
Microphone
Condenser
Panel Color
Black
Outline and Dimension Drawing,
Model A55B Microphone, P/N 93A055–95
Figure A–18
165E2807-00
Page A-20
Rev. 02
July 01/02
Installation & Operation
Instruction Manual
Model A100 / A100A CVR
APPENDIX B
ACCESSORY EQUIPMENT
Rev. 02
July 01/02
165E2807-00
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Model A100 / A100A CVR
Installation & Operation
Instruction Manual
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165E2807-00
Page B-2
Rev. 02
July 01/02
Installation & Operation
Instruction Manual
Model A100 / A100A CVR
CALIBRATED SOUND SOURCE, Model A870
MICROPHONE
CALIBRATE
CALIBRATED
SOUND SOURCE
P/N 9300-A870
USE 1 kHz
SET TO 0 dB
Calibrated Sound Source, P/N 9300A870
Figure B–1
VOICE RECORDER
FAIRCHILD COCKPIT
SYSTEM TEST PANEL
N
O
R
M
A
L
A
C
T
U
A
T
E
BULK
ERASE
TEST
TEST
BIAS TRAP
ADJUST
SYS UNIT
O
U
T
P
U
T
MODE
GND
FAULT
700
1kHz
ROLL OFF
I
N
P
U
T
GND
SHORT
AII3
BULK
ERASE
-6 dB
A
T
T
E
N
U
A
T
I
O
N
-24 dB
C.U.
EXT
1
A55
MIC
J2
ALL
TEST
REC.
INT
O
U
T
P
U
T
BULK
ERASE
-12 dB
BYPASS
REVERSED
GND
HEADSET
LOCAL AMP
VOLUME
AC
MIC
CAL
DC
2A
DC
OFF
3
4
SHORT
C.U.
CHANNEL
SELECT RECORD
BIAS
ON
POWER
2
I
N
P
U
T
-18VDC +18VDC
2A
AC
J3
CONTROL OFF
UNIT
GTP PROBE(FOR GROUND TEST)
Cockpit Voice Recorder System Test Panel, P/N 9300A860
Figure B–2
The L–3 Communications Aviation Recorders Model A870 Calibrated Sound Source is designed to act as a sound level source for the testing of Remote Microphones. This is accomplished by applying a 1 KHz input to J1 or the “Mic Cal” input of the CVR Test Panel. Increase the voltage until a 0–dB reading is noted on M1, which indicates a 100–dB sound
pressure level is present. Microphone testing can begin from this step.
Rev. 02
July 01/02
165E2807-00
Page B-3
Model A100 / A100A CVR
Installation & Operation
Instruction Manual
Model A55 Dynamic Remote Mic, P/N 93–A055–00
58. Using a DVM, insure that no continunity exists between the microphone shield wire, the
high side of the mic, and the low side of the mic. The microphone case should be tied to
the shield.
59. Connect the microphone to an AC voltmeter and an oscilloscope. Apply a 100 dB sound
pressure level to the microphone and observe that the output is undistorted. Measure the
output voltage, which should be between 3 mV RMS and 9 mV RMS.
60. Speak into the microphone and observe that the output fluctuates.
OSCILLOSCOPE
POWER INPUT
MODEL A55B
MICROPHONE
SIGNAL OUTPUT
6 V +/- 1 V
BATTERY OR
DC POWER
SUPPLY
SOUND LEVEL
SOURCE
P/N 9300-A870
SHIELD
10K
1/4 W
AC
VTVM
Condenser Remote Microphone Test Setup
Figure B–3
Model A55B Condenser Remote Mics, P/N 93–A055–10, –20, –30, –50, –55
1. Using a DVM, check for no continunity between the connector shell and Pin 1, Pin 2, and
the dust cover.
2. Set up for test as shown in Figure B–3, using the Calibrated Sound Source and connecting
the microphone to an oscilloscope and AC voltmeter. Pin 1 = Signal Output and Pin 2 =
6.2 V Power Input.
3. Apply 100 dB sound pressure level to the microphone. Observe that the output is undistorted and the. Measure the output voltage which should be between 7 mV RMS and 17.5
RMS.
4. Speak into the microphone and observe that the output fluctuates on the oscilloscope.
165E2807-00
Page B-4
Rev. 02
July 01/02
Installation & Operation
Instruction Manual
Model A100 / A100A CVR
Model A55B Condenser Remote Mics, P/N 93–A055–40, –45
1. Using a DVM, insure no continunity exists between the microphone shield wire and the
power input wire, as well as between the signal output wire and microphone case.
2. Set up for the test as shown in Figure B–3, using the Calibrated Sound Source and connecting the microphone to an oscilloscope and AC voltmeter.
3. Apply 100 dB sound pressure level to the microphone. Observe that the output is undistorted. Measure the output voltage, which should be between 10 mV RMS and 30 mV
RMS.
4. Speak into the microphone and observe that the output fluctuates on the oscilloscope.
Model A55B Condenser Remote Mics, P/N 93–A055–60, –65, –66, –67, –95
1. Using a DVM, insure no continunity exists between the microphone shield wire and the
power input wire, as well as between the signal output wire and microphone case.
2. Set up for the test as shown in Figure B–3, using the Calibrated Sound Source and connecting the microphone to an oscilloscope and AC voltmeter.
3. Apply 100 dB sound pressure level to the microphone. Monitor the oscilloscope and
verify that the output is undistorted. Measure the output voltage, which should be between 7mV RMS and 17.5 mV RMS.
4. Speak into the the microphone and observe that the output fluctuates on the oscilloscope.
Model A152 Control Units
The Model 860 Test Panel must also be used with the Model A870 Calibrated Sound Source
for testing the Model A152 Control Units. Please refer to the Model A100 / A100A CVR
Component Maintenance Manual, P/N 165E0101–00, for thorough test and calibration procedures of specific models.
Calibration
The Model A870 Calibrated Sound Source has been calibrated at the factory before shipping,
however, periodic checks should be made by the following procedure:
1. Connect audio signal generator of 1 KHz, 10.0 VAC output at 500 Ohms to the “MIC
CAL” input of the Model A860 CVR Test Panel. Adjust AP1 for 0 dB on the front panel
meter (M1) of the A870.
2. Adjust calibrate control AP2 on the front panel for a nominal 100 dB sound pressure level
at test opening. The microphone for this calibration should be no larger in diameter than 1
1/8 inch, such as the unit on the General Radio 1551–C sound level meter. The sound
pressure meter should be centered in the test opening and be touching the perforated metal
grille.
Rev. 02
July 01/02
165E2807-00
Page B-5
Model A100 / A100A CVR
Installation & Operation
Instruction Manual
3. The calibration is now complete and no further adjustment should be made to the controls.
NOTE
The meter calibration control AP1 is set and sealed at the factory for 0 dB reading with 10.0
VAC input at 1000 Hz. This should be checked at the periodic calibrations but would not
normally have to be adjusted unless the meter was subjected to possible damage. The acoustic calibration should be done with the test panel mounted in the same configuration as that
when used during normal operation, since different environments may affect sound pressure
performance.
165E2807-00
Page B-6
Rev. 02
July 01/02
Installation & Operation
Instruction Manual
Model A100 / A100A CVR
INERTIA / IMPACT SWITCH, Inertia Switch Inc. Model 3LO–453
The Inertia Swtich Incorporated Model 3LO–453 is a highly relibable latching inertia / impact switch used in various military / commercial aviation applications. These units are factory preset at certain g levels. When predetermined g levels are exceeded by the aircraft, certain systems such as voice / data recording, emergency lighting, and fire control can be
automatically turned on or off.
Further product information as well as ordering information can be obtained by contacting
Inertia Switch Incorporated through the information below.
Inertia Switch Inc.
Engineering & Laboratory
Administrative & Sales Offices
70 South Greenbush Road
Orangeburg, New York 10962
Phone: (845) 359–8300
Fax: (845) 359–6227
WWW: http://www.inertiaswitch.com/
http://www.avtcorp.com/
45_
RESET BUTTON
POINTING
TOWARD GROUND
Inertia / Impact Installation
Figure B–4
Rev. 02
July 01/02
165E2807-00
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Model A100 / A100A CVR
Installation & Operation
Instruction Manual
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Installation & Operation
Instruction Manual
Model A100 / A100A CVR
CVR AUDIO MIXER, Avtech Model 5020–1–1
Avtech CVR Audio Mixers are designed to comply with new FAA regulations mandating
cockpit voice recorders for all multi–engined turbine–powered aircraft that require two crew
members and seat six or more passengers. Unless audio panels are replaced or modified, Avtech CVR Audio Mixers are needed to sum and route audio signals from microphones, headphones and speakers to the cockpit voice recorder. Proven Avtech audio technology provides
”hot mic” biasing, adjustable channels for balancing audio levels, and paired pins to make
installations easy and economical. Both single– and dual–station units are available. And, of
course, these systems are qualified to TSO C50c requirements.
As CVRs are added to additional classifications of the world’s aircraft, Avtech CVR Audio
Mixers will help ensure that systems comply with FAA Airworthiness Standards.
Installation instructions for the Model 5020–1–1 can be found in Document 5020–23–501.
This document is maintained by and can be obtained directly from the Avtech Corporation.
Further product information as well as ordering information can also be obtained by contacting the Avtech Corporation through the information below.
Avtech Corporation
3400 Wallingford Avenue N.
Seattle WA 98103
Phone: (206) 695–8000
Fax: (206) 695–8011
WWW: http://www.avtcorp.com/
Rev. 02
July 01/02
165E2807-00
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Model A100 / A100A CVR
Installation & Operation
Instruction Manual
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Installation & Operation
Instruction Manual
Rev. 02
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Model A100 / A100A CVR
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Model A100 / A100A CVR
165E2807-00
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Installation & Operation
Instruction Manual
Rev. 02
July 01/02
Installation & Operation
Instruction Manual
Model A100 / A100A CVR
APPENDIX C
ENVIRONMENTAL
QUALIFICATION FORMS
Rev. 02
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Model A100 / A100A CVR
Installation & Operation
Instruction Manual
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July 01/02
Installation & Operation
Instruction Manual
Model A100 / A100A CVR
ENVIRONMENTAL QUALIFICATION FORM
A100 & A100A Part Number 93A100–( )
(Ref. Document No. FAR 0380.1)
Model: A100 & A100A
Product: Fairchild Cockpit Voice Recorder
Part Number: 93A100ć( )
Manufacturer:
TSO Number: C84
Manufacturer's Specification and/or Other Applicable
Specification:
Aviation Recorders Document 905ćE1000ć07
EUROCAE EDć56A, RTCA/DOć160C
Conditions
RTCA/DOć160B
Section
LĆ3 Communications, Aviation Recorders
6000 Fruitville Road, Sarasota, FL 34232
P.O. Box 3041, Zip Code 34230Ć3041
Description of Conducted Tests
Temperature and Altitude
4.0
Low Temperature
High Temperature
4.5.1
4.5.3
Altitude
4.6.1
Decompression
4.6.2
Overpressure
4.6.3
Temperature Variation
5.0
Equipment tested to Category A.
Humidity
6.0
Equipment tested to Category A.
Shock
Operational
Crash Safety
7.0
7.2
7.3
Equipment tested equivalent to DO-160B,
para. 7.1.1..
Vibration
8.0
Equipment tested without shock mounts to
Categories J or C (DO-160B, Table 8-1).
Mounting with isolation mount P/N 9300-343
meets category J', Table 8-2.
Explosion
9.0
Equipment tested equivalent to Category E1.
Waterproofness
10.0
Equipment identified as 'X', no test required.
Fluids Susceptibility
11.0
Equipment identified as 'X', no test required.
Sand and Dust
12.0
Equipment identified as 'X', no test required.
Rev. 02
July 01/02
Equipment tested to Categories A2 & D2
with Altitude extended to 55,000 feet.
Operating High Temperature limited to +55°C
Short Time High Temperature +71°C for 30
Minutes.
165E2807-00
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Model A100 / A100A CVR
Installation & Operation
Instruction Manual
THIS PAGE IS INTENTIONALLY BLANK.
165E2807-00
Page C-4
Rev. 02
July 01/02
Installation & Operation
Instruction Manual
Model A100 / A100A CVR
ENVIRONMENTAL QUALIFICATION FORM
Model A150 Part Number 93A150–( )
(Ref. Document No. FAR 0368)
Model: A150
Product: Control Unit, CVR
Part Number: 93A150ć( )
Manufacturer:
TSO Number: C84
Manufacturer's Specification and/or Other Applicable
Specification:
FAA TSO C84 and Fairchild Weston Systems, Inc.
QC Procedure
Conditions
LĆ3 Communications, Aviation Recorders
6000 Fruitville Road, Sarasota, FL 34232
P.O. Box 3041, Zip Code 34230Ć3041
RTCA/DOć160B
Section
Description of Conducted Tests
Temperature and Altitude
4.0 Rev. 1
Equipment tested to Categories D2
Low Temperature
High Temperature
4.5.1
4.5.3
-55°C
+70°C.
Altitude
4.6.1
Altitude Extended to 55,000 Feet
Decompression
4.6.2
Overpressure
4.6.3
Temperature Variation
5.0
Equipment tested to Category A #.
Humidity
6.0
Equipment tested to Category A.
Shock
Operational
Crash Safety
7.0
7.2
7.3
Equipment tested to TSO C84 meets
DO-160B by analysis.
Vibration
8.0
Equipment tested without shock mounts to
Categories J' (DO-160B). See Test Report
FAR 0360R2 #.
Explosion
9.0
Equipment identified as 'E' based on analysis.
Waterproofness
10.0
Equipment identified as 'X', no test required.
Fluids Susceptibility
11.0
Equipment identified as 'X', no test required.
Sand and Dust
12.0
Equipment identified as 'X', no test required.
Fungus
13.0
Equipment identified as 'F', no test required.
Salt Spray
14.0
Equipment identified as 'X', no test required.
Rev. 02
July 01/02
165E2807-00
Page C-5
Model A100 / A100A CVR
Conditions
Installation & Operation
Instruction Manual
RTCA/DOć160B
Section
Description of Conducted Tests
Magnetic Effect
15.0
Equipment identified as Class 'B' by analysis.
Power Input
16.0
Not applicable; power from CVR Unit.
Voltage Spike Conducted
17.0
Not applicable; power from CVR Unit.
Audio Frequency Conducted
Susceptibility
18.0
Equipment tested to Category A.
Induced Signal Susceptibility
19.0
Equipment tested to Category 'Z'.
Radio Frequency Susceptibility
20.0
Equipment tested to Category 'A'.
Radio Frequency Emissions
21.0
Equipment identified as Category 'Z' by
analysis.
Other Tests
Remarks:
165E2807-00
Page C-6
Crash survival test as defined in TSO C51a is
not applicable to the Cockpit mounted Control
Unit.
Tests were conducted at: Fairchild Weston Systems, Inc., Sarasota, FL. Original test had been
performed to TSO C84 requirements. Equivalent categories in DO-160B are indictaed. Refer to
original TSO dated Febuary 5, 1965.
Rev. 02
July 01/02