INSTALLATION 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 TSOC84/ARINC 557 Rev. 02 July 01/02
P/N: 165E2807–00
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.
Copyright
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
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.
Copyright
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
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 envi- ronment. 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 Servi cing instructions inst ructions 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 instrumen inst rumentt while protective covers are removed. Energy available at many points may, may, if contacted, result in personal injury.
THIS PAGE IS INTENTIONALLY LEFT BLANK
TABLE OF CONTENTS Section
1.0
2.0
3.0
4.0
Page
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
EQUIPMENT LIMITATIONS / SPECIFICATIONS . . . . . . . . . . . . . . . . . . . . 7 2.1
Leading Particulars – Model A100 and A100A Recorders . . . . . . . . . . 7
2.2
Leading Particulars – Model A151, A151B, A152, A152B Control Units . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8
2.3
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
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 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
Underwater Locator Beacon . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18
6.2
Product Support . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18
6.3
Authorized Repair Facilities . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18
6.4
Loaner / Rental Program . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
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
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
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
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.
Cockpit Voice Recorder, Model A100 Figure 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 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.
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.
communications
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.)
Rotor Speed Encoder Typical Mounting Installations Figure 3
F.
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.)
F.
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%
2.2
2.3
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
2.4
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
3.0
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.
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.
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.
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.
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.
3.8
3.
Insert Insert cable cable guard, guard, P/N 9300– 9300–428, 428, as show shown n in Details Details A and B, B, ensuring ensuring the the slotted slotted end is fitted over the rear chassis joint. Fold cable guard over connector and harness.
4.
Insert Insert Inverter Inverter over over chassis chassis wiring wiring assemb assembly ly engaging engaging it in the the four inverte inverterr rail studs studs (Detail B) and connector (Detail C).
5.
Reinsert Reinsert and and tighten tighten the the two 4–40 4–40 by 5/16 5/16 binding binding head head screw screwss removed removed in Step Step 2, sesecuring the Inverter.
6.
Replace Replace the dust cover cover using using two two phill phillips ips head head screws. screws.
7.
Refer Refer to the CVR CVR Compone Component nt Maintena Maintenance nce Manual, Manual, P/N P/N 165E0101 165E0101–00, –00, for for Electric Electrical al Test of Inverter.
Post–I Post–Inst nstall allati ation on Checko Checkout ut Proce Procedur dures es 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 system and and associated associated component components, s, verify that all connections are secure and that a continunity or other interconnect assurance test has been conducted. B. Apply power power to the the system and activate activate the Cockpit Cockpit Voice Voice Recorder Recorder self–test. self–test. To 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. recorder. Each channel receives the test tone for approximately .8 seconds. C. Monitor circuitry receives the test tone signals signals and and drives the meter, meter, a “GO–NO–GO “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 monitoring of the 600 hertz hertz test tone and channel switching switching can be accomaccomplished 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.
E.
Verify that that the following microphone microphone inputs inputs are recorded on their appropriate 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: CHAN CHANNE NEL L 1: CHAN CHANNE NEL L 2: CHAN CHANNE NEL L 3: CHAN CHANNE NEL L 4: 4:
F.
Third Third Crew Crewmem member ber Statio Station n or Publi Publicc Addre Address ss Syst System ems. s. Prima Primary ry Co–P Co–Pilo ilot’ t’ss Boom Boom,, Mask, Mask, and and Hand Hand Micro Micropho phone ne Inpu Input. t. Prima Primary ry Pilot Pilot’’s Boom Boom,, Mask, Mask, and and Han Hand d Micro Microph phone one Input. Input. Cock Cockpi pitt Mou Mount nted ed Area Area Micr Microp opho hone ne..
The Bulk Bulk Erase Erase function function can occur only only when when the aircraft aircraft is resting resting on its its landing landing gear. 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 duration is approximately approximately 5 – 12 12 seconds.
4.0
OPERATION TESTS
4.1 4.1
PrePre-Fl Flig ight ht Func Functi tion onal al Chec Check k 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. 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 4.2
Comp Comple lete te Aud Audio io Sys Syste tem m Tes Test t 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.
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 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 Voice Recorder. Upon satisfactory achievement of this test, an entry shall be made in the maintenance records of the aircraft or rotorcraft.
5.0
INSTALLA INSTALLATION TION ACCEPT ACCEPTANCE ANCE BY FIEL FIELD D APPRO APPROV VAL METHO METHOD D 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.
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.
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.
Cockpit Voice Recorder System Control Unit A151B, Functional Block Diagram Figure 6
Cockpit Voice Recorder A100 and Control Unit A152B, Functional Block Diagram Figure 7
Channel Allocation in CVRs Figure 8
VOICE RECORDER UNIT ALL MODELS A100 OR A100A
STANDARD INTERWIRING PER ARINC SPEC 557
1 AMP
TO 27.5 VAC HOT (400HZ) TO AC COLD TO 27.5VDC
5 AMPS
*4
CONTROL UNIT ALL MODELS A151 OR A151B
*6
*4
TO 3RD CREW MEMBER OR PA *5
*8 TO COPILOT
TO PILOT
AREA MIKE *7
*4
MIICROPHONE MODEL A55 OR A55B
*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
NOTE S: *1 *2 *3
Rec. min. wire size is #22. #24 is acceptable except for long–run power leads where #18 is rec. (pins 2,3,17, & 19) Ground connection to be within 1 ft. of pin 17. 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
VOICE RECORDER UNIT ALL MODELS A100 OR A100A
STANDARD INTERWIRING PER ARINC SPEC 557 RECORDER A100 OR A100A WITH CONTROL UNIT A152 OR A152B
TO 27.5 VAC HOT (400HZ) TO AC COLD
1 AMPS
TO 27.5VDC
5 AMPS
*4
CONTROL UNIT ALL MODELS A152 OR A152B
*6
*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 *2 *3
Rec. min. wire size is #22. #24 is acceptable except for long–run power leads where #18 is rec. (pins 2,3,17, & 19) Ground connection to be within 1 ft. of pin 17. 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
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
J1
*2
TO 3RD CREW MEMBER OR PA
MODEL A55B MICROPHONE (ANY PART MODEL)
*4
TO COPILOT
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 rul e 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
Outline & Dimension Drawing, Model A100, P/N 93A100–10, –11 Figure A–1
Outline & Dimension Drawing, Model A100 with Beacon and Beacon Mount, P/N 93A100–30, –31, –32, –33 Figure A–2
Outline & Dimension Drawing, Model A100A, P/N 93A100–81 Figure A–3
Outline & Dimension Drawing, Model A100A with Beacon, and Beacon Mount, P/N 93A100–80, –82, –83, –84, –85 Figure A–4
CENTER OF GRAVITY LOCATION OF MOUNT ASSY
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
Outline & Dimension Drawing, Heavy Duty CVR Vibration Mount, P/N 93–955 Figure A–6
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
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
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
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
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
Part Number 93A05500
Model A55
Connector Location
Microphone Dynamic
Panel Color Black
Outline and Dimension Drawing, Model A55 Microphone, P/N 93A055–00 Figure A–12
Part Number 93A05510 93A05530 93A05550
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
Part Number 93A05520 93A05555
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
Part Number 93A05540 93A05545
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
Part Number 93A05560 93A05565 93A05567
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
Part Number 93A05566
Model A55B
Connector Location Pigtail
Microphone Condenser
Panel Color Black
Outline and Dimension Drawing, Model A55B Microphone, P/N 93A055–66 Figure A–17
Part Number 93A05595
Model A55B
Connector Location Pigtail
Microphone Condenser
Panel Color Black
Outline and Dimension Drawing, Model A55B Microphone, P/N 93A055–95 Figure A–18
CALIBRATED SOUND SOURCE, Model A870
Calibrated Sound Source, P/N 9300A870 Figure B–1
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.
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.
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.
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.
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.
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/
Inertia / Impact Installation Figure B–4
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/
ENVIRONMENTAL QUALIFICATION FORM A100 & A100A Part Number 93A100–( ) (Ref. Document No. FAR 0380.1)
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ENVIRONMENTAL QUALIFICATION FORM Model A150 Part Number 93A150–( ) (Ref. Document No. FAR 0368)
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