AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
MODEL FA2100 CVR
COCKPIT VOICE RECORDER
RECORDER PART NUMBERS:
2100−1010−00
2100−1020−02
2100−1025−12
2100−1027−02
2100−1225−24
2100−1010−50
2100−1010−51
2100−1020−50
2100−1020−51
2100−1025−22
2100−1025−24
2100−1220−00
2100−1220−02
2100−1226−02
2100−1227−02
NOTE:
For FA2100CVR P/N:
2100−1020−90/−91/−93
Contact L−3AR Product Support
2100−1020−00
2100−1025−02
2100−1026−02
2100−1225−22
2100−1925−22
COMPONENT MAINTENANCE MANUAL
WITH
ILLUSTRATED PARTS LIST
P/N: 165E1689−00
IN ACCORDANCE WITH
FAA TSO−C123a
FAA TSO−C123b
EUROCAE ED−56A
EUROCAE ED−112
ARINC CHARACTERISTIC NO. 557
ARINC CHARACTERISTIC NO. 757, 757A
VENDOR CODE: 06141
WARNING: THIS TECHNICAL DATA IS CONTROLLED UNDER THE EXPORT
ADMINISTRATION REGULATIONS (EAR) ECCN 7E994, AND MAY NOT BE EXPORTED TO
A FOREIGN PERSON, EITHER IN THE U.S. OR ABROAD, WITHOUT A LICENSE OR
EXCEPTION FROM THE U.S. DEPARTMENT OF COMMERCE.
DISTRIBUTION STATEMENT: THIS DOCUMENT CONTAINS L-3 AVIATION RECORDERS
PRIVILEGED INFORMATION AND MUST NOT, WITHOUT THE PRIOR WRITTEN CONSENT
OF L-3 AVIATION RECORDERS, BE USED OR REPRODUCED IN WHOLE OR IN PART, OR
COMMUNICATED TO ANY PERSON EXCEPT AS AUTHORIZED BY L-3 AVIATION
RECORDERS.
This manual contains date sensitive information. To verify the latest revision level of this manual, visit our document
download site at http://www.L-3ar.net.
23−70−04
Rev. 15
Apr. 14/16
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
Model FA2100 CVR
Rev. 15
Apr. 14/16
ECopyright 2016 by L-3 Communications.
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
Aviation Recorders Publications
Vendor Code: 06141
P. O. Box 3041
Sarasota, Florida 34230
Phone: (941) 371–0811
FAX: (941) 377–5591
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23–70–04
Title
Rev. 15 Page ii
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
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 (electro–static 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 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 those 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 available line voltage and the correct
fuse is 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.
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
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23–70–04
Title
Rev.
Rev. 15
14 Page
Page iii
iii
Apr.
14/16
Jul. 13/15
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
THIS PAGE IS INTENTIONALLY LEFT BLANK
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23–70–04
Title
Rev. 15 Page iv
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
RECORD OF HIGHLIGHTS
Issue
Revision
Date of
Change
Comments
Revision
15
Apr. 14/16
Page headers updated. Updated unit weights.
Added obsolete unit notes. Removed A860, Calibrated Sound Source, and ROC/5. Added PI/2.
Removed Auto Test section. Updated Software
tables.
Revision
14
Jul. 13/15
Updated to include legal reference in footer.
Moved legal statements from inside front cover
to front cover. Removed 2100−1020−91,
2100−1020−93, and 2100−1020−90. Added
2100−1220−00, 2100−1220−02, 2100−1225−22,
2100−1226−02, 2100−1225−24, 2100−1227−02,
and 2100−1925−22. Added 90 Day ULB.
Revision
13
Dec. 09/13
Assembly, Dissassembly, and IPL updated to reflect MOD DOT 13. ROSE/ROC/ADLP version
numbers updated. Software checksums updated.
Model configuration tables added for clarity. Automatic Test Section revised
Revision
12
Jul. 03/13
Corrected page number errors and updated the
LOEP and Table of Contents.
Revision
11
May 21/13
Added automatic testing section. Added p/n
2100−1027−02. Revised IPL.
Revision
10
Jun. 15/12
Added configuration
Updated Numerical Parts Index to reflect
changes in service bulletins.
Changed output levels for PI MOD DOT #8
Updated the IPL to reflect p/n 2100−1025−24.
Revision
09
Apr. 30/10
Added TSO−C123b. Added Onboard Maintenance System interface and CVR Datalink Input
Interface descriptions. Added software FDP
checksum list for P/Ns 2100−1025/6−XX. updated ROSE software to 4.X
Revision
08
Jul. 30/09
Revised set up figures with Support Equipment in
both Test and Special tools sections.. Updated
procedures in Section 200 Automatic Testing.
added new software for the CVR P/N
2100−1025−22 and 2100−1026−02
Use or disclosure of information on this sheet is subject
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23–70–04
Highlights
Rev. 15 Page v
Apr. 14/16
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
RECORD OF HIGHLIGHTS (Continued)
Issue
Revision
Date of
Change
Comments
Revision
07
Dec. 01/08
Updated for Revision. Added SB011, SB012,
SB013, SB014, SB015, SB 016. Changed the
List of Effective Pages to reflect the Revision 07,
added divider to Table of Contents. Added reference to ROC/6, updated date for Autotest confirmation. Added Beacon Test note, changed content per SB013, corrected reference to Data Link
(ATC) Interface. Added Beacon Test note, added
Acquisition Processor configuration, added reference to ROC/6. Updated part numbers, corrected test setup diagram, added RIU power cautions, verified ROC/6 part list. Added configuration. Updated Test Equipment lists, corrected test
diagram. Updated Numerical Parts Index to reflect changes in service bulletins. Updated the
IPL to reflect p/n 21001026−02.
Revision
06
May 01/07
Added new Section 200, Automatic Testing for
operational testing of CVR to include the ROC6
/w CATS software. Revised Disassembly & Assembly sections to include p/n’s: 2100−1025−12
& −22, Audio Compressor and Crash Survivable
Memory Unit. Revised Description Section for
new p/n: 2100−1025−12 & −22, Audio Compressor and Crash Survivable Memory Unit. Updated
Test Procedures and Checksum Information for
Revisions 5 software and ROC6 /w CATS software. Revised Figure 104 to include all Acquistion Processor configurations. Added new Table
105, CVR fault code corrective actions. Added
ROC6 /w Cats software to Special Tools and Test
Equipment Section. Updated the IPL to reflect
p/n: 2100−1025−12 & −22 CVR, Audio Compressor and Crash Survivable Memory Unit. This includes all Temporary Revisions, including TR6
and Service Bulletins SB008, SB009 and SB010.
Revised Description and Test Procedures to include pre and post MOD−DOT #7 units. Revised
beacon battery replacement date.
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
23–70–04
Highlights
Rev. 15 Page vi
Apr. 14/16
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
RECORD OF HIGHLIGHTS (Continued)
Issue
Revision
Date of
Change
Comments
Revision
05
Oct. 01/04
Revised Disassembly & Assembly sections to include p/n: 2100−1025−02 and associated parts.
Added OMS and Data Link information in the Description Section for p/n: 2100−1025−02. Updated Test Procedures and Checksum Information for Revision 4 software. Added Audio Data
Link Player Software information to Special Tools
and Test Equipment Section. Updated the IPL to
reflect p/n: 2100−1025−02 and associated parts,
along with new Acquisition Processor Board.
Revision
03
Mar. 01/01
Included GACVR changes: All GACVR are DC
only w/ RTV. Incorporated 24−month cleaning requirement for Underwater Locator Device. Added
new CVR label and change of location. Added
2100−1020−90 version.
Revision
04
Jan. 01/03
Revised Disassembly & Assembly sections to include the moisture resistant seals introduced in
SB004. Identified an approved ATA300 shipping
container in the Assembly section. Added the
CICC/2 upgraded cable assembly to the Test &
Troubleshooting sections. Updated the IPL to reflect these additions. Added corrections & comments from Boeing Supplier Data Transmittal
CD01−0348.
Revision
02
June 01/00
Added 2100−1020−93 configuration and S161
control unit information.
Revision
01
Feb. 01/00
Includes changes to the IPL Section 1000 to incorporate a new Audio Compressor PWA for
FSK capability. Added the FA2100 GACVRs to
the manual. Incorporated the Acquisition Processor, p/n: 205E1931−00, turbo PWA changes
along with the Revision 01 Software changes.
Nov. 01/98
Initial issue of CMM. Includes all sections, Pre
ATA100. Includes: FA2100CVR - FSB001.
Initial
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to the restrictions on the cover page of this document.
23–70–04
Highlights
Rev. 15 Page vii
Apr. 14/16
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
THIS PAGE IS INTENTIONALLY LEFT BLANK
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23–70–04
Highlights
Rev. 15 Page viii
Apr. 14/16
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
HIGHLIGHTS
REVISION 15 DATED Apr. 14, 2016
Pages which have been added or revised are outlined below, together with the highlights
of Revision 15, dated Apr. 14, 2016.
Section
Page
Description
Title
All
Page headers updated.
List of FSB’s
All
Page headers updated. Service Bulletin 023 added.
Front Matter
All
Page headers updated.
Introduction
All
Page headers updated. Removed A860.
Description &
Operation
All
Page headers updated. Updated unit weights. Added obsolete notes.
Removed A860.
Testing & Fault
Isolation
All
Page headers updated. Removed A860. Updated Software tables.
Automatic
Testing
All
Page headers updated. Removed section.
Disassembly
All
Page headers updated. ULB information updated.
Cleaning
All
Page headers updated.
Check
All
Page headers updated.
Repair
All
Page headers updated.
Assembly
All
Page headers updated. ULB information updated.
Fit and Clear- All
ances
Page headers updated.
Special Tools All
and Test Equipment
Page headers updated. Removed A860, Calibrated Sound Source,
and ROC/5. Added PI/2.
Illustrated Parts All
List and Schematic Diagrams
Page headers updated. Updated ULB information. Added obsolete
notes. New CSMU assemblies added.
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to the restrictions on the cover page of this document.
23–70–04
Highlights
Rev. 15 Page ix
Apr. 14/16
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
HIGHLIGHTS
REVISION 14 DATED Jul. 13, 2015
Pages which have been added or revised are outlined below, together with the highlights
of Revision 14, dated Jul. 14, 2015.
Section
Page
Description
Title
All
Updated to include legal reference in footer. Moved legal statements
from inside front cover to front cover. Removed 2100−1020−91,
2100−1020−93, and 2100−1020−90. Added 2100−1220−00,
2100−1220−02, 2100−1225−22, 2100−1226−02, 2100−1225−24,
2100−1227−02, and 2100−1925−22.
List of FSB’s
All
Updated to include legal reference in footer. Added Service Bulletins
21 and 22.
Front Matter
All
Updated to include legal reference in footer. Updated to reflect Rev.
14 changes.
Introduction
All
Updated to include legal reference in footer. Added 2100−1220−00,
2100−1220−02, 2100−1225−22, 2100−1226−02, 2100−1225−24,
2100−1227−02, and 2100−1925−22. Added 90 Day ULB.
Description &
Operation
All
Updated to include legal reference in footer. Added 2100−1220−00,
2100−1220−02, 2100−1225−22, 2100−1226−02, 2100−1225−24,
2100−1227−02, and 2100−1925−22. Added 90 Day ULB.
Testing & Fault
Isolation
All
Updated to include legal reference in footer. Added 2100−1220−00,
2100−1220−02, 2100−1225−22, 2100−1226−02, 2100−1225−24,
2100−1227−02, and 2100−1925−22. Added 90 Day ULB.
Automatic
Testing
All
Updated to include legal reference in footer.
Disassembly
All
Updated to include legal reference in footer. Added 90 Day ULB.
Cleaning
All
Updated to include legal reference in footer. Added 90 Day ULB.
Check
All
Updated to include legal reference in footer. Added 90 Day ULB.
Repair
All
Updated to include legal reference in footer.
Assembly
All
Updated to include legal reference in footer. Added 90 Day ULB.
Fit and Clear- All
ances
Updated to include legal reference in footer.
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
23–70–04
Highlights
Rev. 15 Page x
Apr. 14/16
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
Special Tools All
and Test Equipment
Updated to include legal reference in footer.
Illustrated Parts All
List and Schematic Diagrams
Updated to include legal reference in footer. Removed
2100−1020−91, 2100−1020−93, and 2100−1020−90. Added
2100−1220−00, 2100−1220−02, 2100−1225−22, 2100−1226−02,
2100−1225−24, 2100−1227−02, and 2100−1925−22. Added 90 Day
ULB.
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
23–70–04
Highlights
Rev. 15 Page xi
Apr. 14/16
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
HIGHLIGHTS
REVISION 13 DATED December 9, 2013
Pages which have been added or revised are outlined below, together with the highlights
of Revision 13, dated December 9, 2013.
Section
Page
Description
Front Matter
LOEP & TOC
Changed the List of Effective Pages to reflect Revision 13 changes.
Changed the Table of Contents to reflect the Revision 13 changes.
Introduction
3,5
Removed ROC/6 reference. Added Datalink reference.
Description &
Operation
2,4,17,31,36,38
Part number matrix and block diagram updated. ROSE version updated. Model configuration tables added.
Testing & Fault 105,142-145,147- ROSE version updated. ADLP added. Software and directory labels
Isolation
150
updated. Updated setup diagram. Software checksums updated.
Automatic
Testing
201-209,211-212, Reformatted section, updated figure labels, removed redundant
220-255,264-269, steps, corrected test sequences, and streamlined procedure.
271-278
Disassembly
304-310,312
Assembly
701,703-704,708- Updated for differences in MOD DOT 6 and MOD DOT 13.
711,716-721
Updated for differences in MOD DOT 6 and MOD DOT 13.
Special Tools 902-904,918,928
and
Test
Equipment
Updated software versions and optional speakers.
Illustrated
1005-1009,1011Parts List and 1012,1014,1016Schematic
1018,1021-1023
Diagrams
Updated for differences in MOD DOT 13.
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
23–70–04
Highlights
Rev. 15 Page xii
Apr. 14/16
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
HIGHLIGHTS
REVISION 12 DATED July 3, 2013
Pages which have been added or revised are outlined below, together with the highlights
of Revision 12, dated July 3, 2013.
Section
Page
Description
Front Matter
LOEP &
TOC
Changed the List of Effective Pages to reflect Revision 12 changes.
Changed the Table of Contents to reflect the Revision 12 changes.
Automatic Test
201−290
Reformatted section to include figure labels and removed redundant
steps.
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
23–70–04
Highlights
Rev. 15 Page xiii
Apr. 14/16
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
HIGHLIGHTS
REVISION 11 DATED May 21, 2013
Pages which have been added or revised are outlined below, together with the highlights
of Revision 11, dated May 21, 2013.
Section
Page
Description
Title
i
Added part number 2100−1027−02 (ARINC 757A compliant) to cover
page.
List of FSB’s
xxiii
Updated for FSB019 (23−70−04−19) and FSB020 (23−70−04−20)
Front Matter
LOEP &
TOC
Changed the List of Effective Pages to reflect Revision 11 changes.
Changed the Table of Contents to reflect the Revision 11 changes.
Introduction
1
Added part number 2100−1027−02 (ARINC 757A compliant).
Description &
Operation
Section
1, 2, 4, 6, 8,
9, 10, 12,
13−16, 21,
22, 23, 25,
29, 30−34,
35, 36, 43,
48−56, 64,
67
Added part number 2100−1027−02 (ARINC 757A compliant). Added
NAND memory to part number matrix. Adds description of PI/2. Added
description of acquisition processor 205E2502−34. Removed description of FA2100 CVR p/n: S2100−1020−91
Testing & Fault
Isolation
Section
101, 102,
140−145,
148, 149,
151, 152
Added notes about ROC/6, ROC/6 and ROC/7 concerning compatibility with CATS 2.0 Added note about return−to−service procedure. Modified Table 105. Added instruction concerning matching part number
and check sum. Modified Table 106 and Table 107
Automatic Test
201−288
Added new section describing the automatic testing procedure.
Special Tools
903−905,
and Test Equip- 931, 932
ment Section
Updated Table 901 and Table 902. Revised hardware requirements for
ADLP player software.
Illustrated Parts 1004,
List
1009−1020
Updated the Configuration Matrix to include p/n 2100−1027−02. Updated the drawings in the IPL.
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23–70–04
Highlights
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Apr. 14/16
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
HIGHLIGHTS
REVISION 10 DATED Jun. 15, 2012
Pages which have been added or revised are outlined below, together with the highlights
of Revision 10, dated Jun. 15, 2012.
Section
Page
Description
List of FSB’s
n/a
Front Matter
xix − xxxiv
Changed the List of Effective Pages to reflect the Revision 10
changes. Changed the Table of Contents to reflect the Revision 10
changes.
Testing
118−120
Updated procedure to accommodate PI MOD DOT #8
Illustrated Parts n/a
List and Schematic Diagrams
Added 2100−1025−24 configuration
Added 742E1619−03
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23–70–04
Highlights
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Apr. 14/16
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
HIGHLIGHTS
REVISION 09 DATED Apr. 30, 2010
Pages which have been added or revised are outlined below, together with the highlights
of Revision 09, dated Apr. 30, 2010.
Section
Page
Description
Title
i − ii
List of FSB’s
n/a
Front Matter
xix − xxxiv
Changed the List of Effective Pages to reflect the Revision 09
changes. Changed the Table of Contents to reflect the Revision 09
changes.
Introduction
2, 5, 6
Added Rose 4.0. Updated L−3 Address. Updated shop verication
dates.
Description &
Operation
9, 19 − 21, 45,
54−66
Added note on test tones for P/N 2100−1025/6−02. Added BIT and
Fault Detection paragraph. Added TSO C123b.
Testing & Fault
Isolation
105, 150
Revised P/N for the Variac. Added Table 107 Software FDP checksum. Added Section 9. Onboard Maintenance System interface and
Section 10 CVR Datalink Input Interface.
Automatic
Testing
233
Added Rose 4.0
Disassembly
n/a
Assembly
n/a
Updated for Revision 9. Added TSO C123b.
Fit and Clear- n/a
ances
Special Tools n/a
and Test Equipment
Illustrated Parts 1017
List and Schematic Diagrams
Corrected Effective codes for 165B and 165C
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23–70–04
Highlights
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Apr. 14/16
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
HIGHLIGHTS
REVISION 08 DATED Jul. 30, 2009
Pages which have been added or revised are outlined below, together with the highlights
of Revision 08, dated Jul. 30, 2009
Section
Page
Title
i − ii
List of FSB’s
n/a
Front Matter
xix − xxxiv
Introduction
n/a
Description &
Operation
n/a
Testing & Fault
Isolation
143−146, 150
Description
Updated for Revision 8.
Changed the List of Effective Pages to reflect the Revision 08
changes. Changed the Table of Contents to reflect the Revision 08
changes.
Added ROC/6 to note. Revised Figures 105 and 106 for set−up with
support equipment. Updated Table 106 with new software P/N’s for
the CVR P/N 2100−1025−22 and 2100−1026−02. Added note
for the CICC/3
Automatic
Testing
201, 203, 207, Added Caution on power input select switch. Revised Figure 201
212, 213, 216, showing the back of the ROC/6. Updated and added to Section 3, the
218, 219, 221
CATS auto test procedures
Disassembly
Assembly
Fit and Clearances
Special Tools 902, 918, 919, Revised Table 901 in the ROC/5and ROC/6 Lists. Revised Figures
and Test Equip- 921, 926
911 (Sheets 1 and 2) , 913 and 916 for set−up with support equipment
ment.
Illustrated Parts 1005, 1006,
List and Schem- 1010, 1012−
atic Diagrams
1014
Corrected stand−offs effective code per Revision 1 of Service Bulletin
15. Change the callouts for the Front Panel Assembly. Added new
PWA’s 205E2502−24 and 205E3977−29 for the 2100−1026−02
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23–70–04
Highlights
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Apr. 14/16
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
HIGHLIGHTS
REVISION 07 DATED DECEMBER 01, 2008
Pages which have been added or revised are outlined below, together with the highlights
of Revision 07, dated December 01, 2008
Section
Page
Description
Title
i − ii
Updated for Revision.
List of FSB’s
1
Added SB011, SB012, SB013, SB014, SB015, SB 016.
Front Matter
xix−xxii
xxii, xxxvi
Changed the List of Effective Pages to reflect the Revision 07, added
divider to Table of Contents.
Introduction
1, 5, 6
Added p/n: 2100−1026−02. Added reference to ROC/6, updated date
for Autotest confirmation.
Description &
Operation
1−4, 10, 12, 13,
15, 16 19, 20,
22, 23, 27−29,
31−35, 41,
45−47,49−52
Added Beacon Test note, changed content per SB013, corrected reference to Data Link (ATC) Interface. Added RIPs monitoring status
and p/n: 2100−1026−02. Removed p/n: 2100−1020−91/93.
Testing & Fault
Isolation
105−107, 114,
126, 131, 137,
148, 150
Added Beacon Test note, added Acquisition Processor configuration,
added reference to ROC/6. Updated Software Checksums. Added
p/n: 2100−1026−02. Removed p/n: 2100−1020−91/93
Automatic
Testing
201, 203, 205, Updated part numbers, corrected test setup diagram, added RIU
216
power cautions, verified ROC/6 part list. Revised the Auto testing procedure to separate tests using DC, AC or DC and AC power.
Disassembly
305, 308, 309
Added new Capacitor bracket configuration and new part. Removed
p/n: 2100−1020−91/93.
Assembly
705−707, 709,
711
Added new Capacitor bracket configuration and new parts. Removed
p/n: 2100−1020−91/93.
Fit and Clearances
Special Tools 902−904,
and Test Equip- 926, 932
ment
Illustrated Parts 1004−1012,
List and Schem- 1014−1018,
atic Diagrams
1020
Removed p/n: 2100−1020−93 in Audio output.
913, Updated Test Equipment lists, corrected test diagram. Added new
CVR download Cable p/n: 17TES0078.
Updated Numerical Parts Index to reflect changes in service bulletins
and added new CVR p/n: 2100−1026−02. Removed p/n:
2100−1020−91/93.
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
23–70–04
Highlights
Rev. 15 Page xviii
Apr. 14/16
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
HIGHLIGHTS
REVISION 06 DATED May 01, 2007
Pages which have been added or revised are outlined below, together with the highlights
of Revision 06, dated May 01/2007.
Section
Page
Description
Title
i − ii
Updated for Revision. Corrected part numbers on title page (editoral
correction), FA is part of the model number and not part of the P/N.
Added “EUROCAE ED−112”. Revised Export Control Statement IAW
CTR 760 Rev. R.
List of FSB’s
1
Added SB008, SB009 and SB010.
Front Matter
xix−xxii
xxii−xxxiv
Changed the List of Effective Pages to reflect the Revision 06
changes. Changed the Table of Contents to reflect the Revision 06
changes.
Introduction
1−4, 6, 7
Added Paragraph 8 “Part Number Formatting”. Added new items to
the list of acronyms and abbreviations. Added note: verify CMM information when developing other documentation.
Description &
Operation
1−4, 6−16,18−
20, 22, 23 27,
29, 31, 32, 35,
38, 44−49
Added “refer to Figure 6, Audio block diagram”. Updated new Audio
Compressor and Crash Survivable Memory Unit (CSMU) p/ns.
Changed 2100−1025−02 to 2100− 1025−( ) or− XX. Added “EUROCAE ED−112”. Revised text for Per and Post MOD−DOT #7 configurations of P/N 2100−1020−XX. Revised beacon battery replacement
date.
Testing & Fault
Isolation
101−103,
105−107,
110−112,
115−120, 123,
125−132,
139−146,
148−150
Changed 2100−1025−02 to 2100−1025−( ) or− XX. Updated Test
Procedures and Checksum Information for Revsions 5 software. Revised testing for Pre and Post MOD−DOT #7 configurations of P/N
2100−1020−XX. Revised Figure 104, Acquisition Processor PWA
(AP) Test Point Locations to included all AP configurations.
Added new Table 105, CVR fault code corrective actions.
Automatic
Testing
200−216
Added new Section 200 to the CMM. Operational level testing the
CVR using Read-Out Center/6 (ROC/6) Test Station with CVR Automated Test Station (CATS) software.
Disassembly
302−309
Updated procedures and drawings to include new Audio Compressor
board and Crash Survivable Memory Unit (CSMU) for the FA2100
CVR. Changed 2100−1025−02 to 2100−1025−( ) or− XX. Revised
beacon battery replacement date.
Cleaning
402, 403
Updated Figure 401 to include new CSMU p/n callouts. Revised beacon battery replacement date.
Check
502
Revised beacon battery replacement date.
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to the restrictions on the cover page of this document.
23–70–04
Highlights
Rev. 15 Page xix
Apr. 14/16
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
HIGHLIGHTS
REVISION 05 DATED OCT. 01, 2004
Pages which have been added or revised are outlined below, together with the highlights
of Revision 05, dated Oct. 01/2004.
Section
Page
Description
Title
1−2
Updated for Revision.
List of FSB’s
1
Added SB006 and SB007
Front Matter
xv-xvii
xix-xxviii
Changed the List of Effective Pages to reflect the Revision 05
changes. Changed the Table of Contents to reflect the Revision 05
changes.
Introduction
1
Updated to include p/n: 2100−1025−02.
Description &
Operation
4, 7−8, 10−16,
18, 22−23,
32−33
Added information for the 2100−1025−02. Updated Figure 3. FA2100
Block Diagram to include OMS and Data Link. Updated Figure 5.
FA2100 Audio Monitoring Scheme to include the 2100−1025−02,
2−hour HQ only recorder. Updated Figure 6. FA2100 Recording
Schemes to include the 2100−1025−02.Updated Table 1. FA2100
Recording Specifications to include the 2100−1025−02. Added OMS
and Data link information. Added Control Unit information on the
S161−1390−00. Updated Figure 8. Interwiring Diagram to include
OMS and Data LInk pins.
Testing & Fault
Isolation
101, 105, 112
114−118, 122,
124−127,
141−142
Updated test section/procedure to include p/n: 2100−1025−02,
2−hour HQ only recorder. Updated FA2100 CVR test bench setup requirements and Table 1. Recommeded Standard Test Equipment.
Added Data Link Check to Table 102. Operational Test Procedure.
Updated Table 103. Test Procedure Data Record Chart to include p/n:
2100−1025−02. Updated Table 105. FA2100 CVR Software Checksums for Revision 4 software.
Disassembly
302−305,
307−309
Updated Disassembly procedures and drawings to include p/n:
2100−1025−02 and associated parts.
Cleaning
403
Updated Figure 401. to include parts for the 2100−1025−02 CVR.
Assembly
702−709,
711−715
Updated Assembly procedures and drawings to include p/n:
2100−1025−02 and associated parts.
Fits &
Clearances
804−805
Updated Figure 801. FA2100 CVR O&D drawing to include p/n:
2100−1025−02.
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
23–70–04
Highlights
Rev. 15 Page xx
Apr. 14/16
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
Special Tools
and Test
Equipment
902, 914,
924−926
Illustrated Parts 1004−1015
List &
Schematic
Diagrams
Updated Software Library Disk information. Modified Figure 910 CVR
Menu Structures to include p/n: 2100−1025−02. Added Audio Data
Link Player Software information.
Updated the Configuration Matrix, Numerical Index, Figure 1., and
the IPL to include p/n: 2100−1025−02 and associated parts. Added
new Acquistion Processor board for the FA2100 CVR.
Use or disclosure of information on this sheet is subject
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23–70–04
Highlights
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Apr. 14/16
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
HIGHLIGHTS
REVISION 04 DATED JAN. 01, 2003
Pages which have been added or revised are outlined below, together with the highlights
of Revision 04, dated Feb. 01/2003.
Section
Page
Description
Title
1−2
Updated for Revision.
List of FSB’s
1
Added SB003, SB004, and SB005
Front Matter
1-4
1-8
Changed the List of Effective Pages to reflect the Revision 04
changes. Changed the Table of Contents to reflect the Revision 04
changes.
Introduction
4-5
Added Document Verification Section.
Description &
Operation
1-6, 8, 11-12,
15-16, 18-20,
22, 24-26, 37
Added S161, S261, S162, S160 & S056 Control Units, Preamplifier,
and Microphone information. Identified Benthos as new ULB vendor
for ELP−362D beacon. Added channel sensitivity levels and more
RSE signal detail.
Testing & Fault
Isolation
101-103,
105-106, 112,
114, 116 − 123,
136-142.
Corrected testing procedural errors. Incorporated CICC/2 information for Uploading Software changes for 2100−1010−( ) and added
2100−1020−90 along with new checksums in Table 105 for SW Rev.
02 Per SB005.
Disassembly
302-309
Corrected nomenclature inconsistancies with IPL. Changed removal
procedure for Acquisition Processor PWA.
Cleaning
402-403
Changed beacon manufacturer information.
Check
501-502
Changed beacon manufacturer information.
Assembly
701-716
Modified procedure to include installation of the moisture resistant
seals for the CSMU and Chassis Cover per SB004 (MOD−DOT#4).
Added shipping container information.
Fits &
Clearances
802
Added torque values for the chassis, Aircraft Interface, Acquisition
Processor boards. RSE input impedance value added.
Special Tools
and Test
Equipment
901-904,
917-923
911, Added S161, S261, S162, S160 & S056 Control Units, Preamplifier,
and Microphone information. Updated recorder software revisions.
Added CICC & CICC/2 cable information.
Illustrated Parts 1001,
Added abbreviations. Corrected Fig. 1 call-outs. Added moisture reList &
1005-1009,
sistant seals and sealing screws for the CSMU and chassis cover.
Schematic
1011, 1013-1015 Added new Audio Compressor PWA & shipment kit.
Diagrams
Use or disclosure of information on this sheet is subject
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23–70–04
Highlights
Rev. 15 Page xxii
Apr. 14/16
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
HIGHLIGHTS
REVISION 03 DATED MAR. 01, 2001
Pages which have been added or revised are outlined below, together with the highlights
of Revision 03, dated Mar. 01/2001.
Section
Page
Description
Title
1−2
Updated for Revision.
Front Matter
LOEP & TOC
Changed the List of Effective Pages to reflect the Revision 03
changes. Changed the Table of Contents to reflect the Revision 03
changes.
Description &
Operation
Section
1−5, 13, 19−22, Incorporated new label and updated label position. Updated Part
24
Number Matrix. Corrected ULD cleaning requirements. Incorporated
all GACVR’s are DC only. Added −90 version to Figure 3. Updated Aircraft Interface PWA used in GACVRs.
Testing & Fault
Isolation
Section
108, 110, 112,
113, 115−118,
120, 138, 140
Incorporated new label and updated label position. Incorporated all
GACVR’s are DC only. Incorporated Software changes for
2100−1010−( ) and added 2100−1020−90 along with new checksums
in Table 105.
Disassembly
Section
302
Corrected ULD cleaning requirements.
Cleaning
Section
402
Corrected ULD cleaning requirements.
Assembly
Section
709, 710
Added steps and figure to include the assembly of the −99 version
(customer supplied ULD).
Fits &
Clearances
Section
804, 805
Incorporated new label and updated label position.
Special Tools
and Test
Equipment
Section
902, 911, 915
Updated recorder software revisions. Incorporated new label and updated label position.
Illustrated Parts 1004 − 1014
List &
Schematic
Diagrams
Updated configuration matrix to add that all GACVRs are DC only,
and to incluse the−90 configuration. Updated numerical index and
part number list to include 2100−1020−90. Incorporated new label
and updated label position. Updated item numbers for GACVRs to reflect DC only along with GACVR Aircraft Interface PWA
205E−1763−01.
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
23–70–04
Highlights
Rev. 15 Page xxiii
Apr. 14/16
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
HIGHLIGHTS
REVISION 02 DATED JUNE 01, 2000
Pages which have been added or revised are outlined below, together with the highlights
of Revision 02, dated June 01/2000.
Section
Page
Description
Title
1−2
Updated for Revision.
Front Matter
LOEP, TOC
Changed the List of Effective Pages & Table of Contents to reflect the
Revision 02 changes.
Introduction
4
Updated to reflect multiple configurations for the FA2100.
Description &
Operation
Section
1−6, 8, 12−13,
15, 18−19,
21−22, 24−29,
37
Updated to include −93 configuration. Updated manufacturer information for ULDs. Updated to include S161 Control Unit. Updated interwiring diagrams to differentiate GACVR wiring.
Testing & Fault
Isolation
Section
101−107,
111−113, 115,
122−123, 126,
134, 136−137,
140
Updated to include S161 Control Unit. Updated to include −93 configuration. Updated ULD test procedure and manufacturer information.
Disassembly
Section
302−303,
306−307
Updated information for ULDs. Updated the beacon removal procedure. Added IPL Tag for 205E1849−04 Audio Compressor PWA.
Cleaning
Section
402−403
Updated cleaning and manufacturer information for ULD.
Check Section
502
Updated manufacturer information for ULDs.
Assembly
Section
705, 707−708
Added IPL Tag for Audio Compressor PWA. Updated assembly and
installation procedure for ULD.
Fits &
Clearances
Section
802
Updated audio output level to reflect −93 configuration.
Special Tools
and Test
Equipment
Section
901−903, 906,
910, 915
Updated to include Model S161 Control Unit.
Illustrated Parts 1004, 1006,
List &
1008 − 1014
Schematic
Diagrams
Updated configuration matrix to include −93 configuration. Updated
numerical index and part number list to include 205E1849−04 Audio
Compressor PWA. Updated numerical index and part number list to
reflect shift in item numbers for all FA2100 CVR models. Updated numerical index to include ULDs. Updated item numbers for Audio Compressor PWA and ULDs. Updated include correct RTCA / DO−178B
level. Updated part number list to reflect FSB002.
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
23–70–04
Highlights
Rev. 15 Page xxiv
Apr. 14/16
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
HIGHLIGHTS
REVISION 01 DATED FEB. 01, 2000
Pages which have been added or revised are outlined below, together with the highlights
of Revision 01, dated Feb. 01/2000.
Section
Page
Description
Title
1−2
Updated for the Revision and the Copyright year.
List of FSB’s
1
Updated for FSB002 (23−70−04−02).
Front Matter
LOEP &
TOC
Changed the List of Effective Pages to reflect Revision 01 changes.
Changed the Table of Contents to reflect the Revision 01 changes.
Introduction
1
Clarified the cockpit voice and area microphone statement.
Description &
Operation
Section
2−3, 5−13,
16−21,
24, 27, 29,
35, 36, 40
Updated number of CVR configurations. Updated and changed the order of several system component descriptions. Updated CVR recording schemes figure. Added Figure 6 GACVR Fault Circuit for Pin 23.
Removed microphone information. Updated Interwiring diagrams.
Added GMT and Rotor Speed to ARINC 557/757 Aircraft interface Signals table. Introduced the 205E1849−( ) Audio Compressor boards.
Introduced the 205E1931−00 Acquisition Processor board.
Testing & Fault
Isolation
Section
101−140,
Added the GACVR Fault Circuitry for Pin 23. Modified testing procedure for GACVRs, p/ns: 2100−1010−51 and 2100−1020−51. Updated
the Acquisition Processor test point locations. Added new CVR software upload procedure along with Rose utility software upload procedure. Added Table 105 CVR Software Checksums.
Disassembly
Section
303−309
Added steps necessary to disassemble the GACVRs, p/ns:
2100−1010−51 & 2100−1020−51. Updated part item numbers.
Cleaning
Section
Page: 403
Updated part item numbers.
Assembly
Section
701−709
Added 2 new items to the Required Assembly Materials table.
Added steps necessary to assemble the GACVRs, p/ns:
2100−1010−51 & 2100−1020−51. Updated part item numbers.
Fits & Clearances Section
801−802,
804−806
Updated Physical and Electrical Characteristics. Add CSMU torque requirements. Updated O&D drawing.
Special Tools
901− 902,
and Test Equip- 907,
ment Section
909−910,
912−916
Updated Table 901. Updated S150/CAM test Panel Cable Assembly
description and wiring diagram. Added requirements for Acquisition
Processor replacement. Updated Portable Interface figure and menu
structures.
Illustrated Parts 1004−1014
List
Update the Configuration Matrix. Updated the Numerical Index. Added the new Audio Compressor PWA for FSK capability. Added the
FA2100 GACVRs to the IPL.
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Apr. 14/16
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
THIS PAGE IS INTENTIONALLY LEFT BLANK
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23–70–04
Highlights
Rev. 15 Page xxvi
Apr. 14/16
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
RECORD OF REVISIONS
REV. INSERTION
NO. DATE
BY
15
Apr. 14/16
JG
14
Jul. 13/15
JG
13
Dec. 09/13
JG
12
Jul. 03/13
JG
11
May 21/13
DN
10
Jun. 15/12
JM
09
Apr. 30/10
GM
08
Jul. 30/09
GM
07
Dec. 01/08
GM
06
May 01/07
GM
05
Oct. 01/04
GW
04
Jan. 01/03
JG
03
Mar. 01/01
GW
02
Jun. 01/00
JG
01
Feb. 01/00
GW
REV.
NO.
INSERTION
DATE
BY
REV.
NO
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INSERTION
DATE
BY
23–70–04
Record of Revisions
Rev. 15 Page xxvii
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
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23–70–04
Record of Revisions
Rev. 15 Page xxviii
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
SERVICE BULLETIN LIST
SERVICE
BULLETIN
DATE
EFFECTIVITY
DESCRIPTION
FA2100 CVR
FSB001
23−70−04−01
Sep. 08/98 P/N: 2100-1010-00 Modification of Aircraft Interface PWA,
P/N: 2100-1020-00 p/n: 205E1593-00 to prevent erroneous
test tone activation due excessive noise
environment. MOD-DOT #1
FA2100 CVR
FSB002
23−70−04−02
Apr. 30/00
FA2100 CVR
FSB003
23−70−04−03
Aug. 15/01 P/N: 2100-1020-02 Modified Audio Compressor PWA, p/n:
P/N: 2100-1020-98 205E1849−03 to ensure compatibility with
FA2100 CVR
FSB004
Rev. 01
23−70−04−04
Sep. 15/01 P/N: 2100-1010-( ) Introduce Moisture Resistant Seals & self−
P/N: 2100-1020-( ) sealing Chassis Cover & CSMU screws to protect against excessive moisture intrusion.
Sep. 30/02
MOD-DOT #4.
FA2100 CVR
FSB005
23−70−04−05
Apr. 16/02
FA2100 CVR
FSB006
23−70−04−06
Sep. 22/04 P/N: 2100-1020-( )
P/N: 2100-1020-( )
FA2100 CVR
FSB007
23−70−04−07
Sep. 09/04 P/N: 2100-1010-( ) This modification upgrades the recorder unit
P/N: 2100-1020-( ) software to Software Revision 04.
FA2100 CVR
FSB008
23−70−04−08
Dec. 15/05
P/N: 2100-1010-( ) Introduction of Turbo Acquisition Processor
P/N: 2100-1020-( ) PWA, p/n: 205E1931−00, and the reworked
205E1591−01, and Software Revision 01.
MOD-DOT #2
ARINC−429 GMT on Boeing 747−400s.
MOD-DOT #3
P/N: 2100-1010-00 Corrects Software Download problem with
2100-1010-50/−51 30−min. recorders. Software Revision 02.
This modification includes replacing the existing Acquisition Processor PWAs, p/n:
205E1591−00 or 205E1931−00 with a replacement Acquisition Processor PWA, p/n:
205E2502−10 or 205E2502−11.
MOD−DOT #5.
P/N: 2100-1020-( ) This modification includes replacing the existP/N: 2100-1020-( ) ing Crash Survivable Memory Unit (CMSU),
p/n: 253E1568−00, 253E1568−01,
253E1568−07, or 253E1568−07 with a replacement Crash Survivable Memory Unit
(CMSU), p/n: 253E1568−38, 253E1568−39,
253E1568−40 or 253E1568−41. MOD−DOT
#6.
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to the restrictions on the cover page of this document.
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23–70–04
Service Bulletin
Rev. 15 Page xxix
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
SERVICE BULLETIN LIST
FA2100 CVR
FSB009
23−70−04−09
Dec. 15/05 P/N: 2100-1020-( )
P/N: 2100-1020-( )
This modification includes replacing the existing Audio Compressor PWA, p/n:
205E1596−00, 205E1849−00, 205E1849−10,
205E1849−02, 205E1849−03, 205E1849−13,
205E1849−04 or 205E1849−14 with a replacement Audio Compressor PWA, p/n:
205E3977−10, 205E3977−12, 205E3977−13
or 205E3977−14 MOD−DOT #7.
FA2100 CVR
FSB010
23−70−04−10
Dec. 15/05 P/N: 2100-1020-( )
P/N: 2100-1020-( )
This modification upgrades the recorder unit
software to Software Revision 05.
FA2100 CVR
FSB011
23−70−04−11
Sep. 20/07 P/N: 2100-1025−02
This modification upgrades the recorder unit
software to Software Revision 03.
FA2100 CVR
FSB012
23−70−04−12
Oct. 17/07
Factory modification to track internal production processes for new recorders
MOD−DOT #8
FA2100 CVR
FSB013
23−70−04−13
Dec. 14/07 P/N: 2100-1010−5()
P/N: 2100-1020−5()
Introducing a replacement Acquisition Processor PWA, p/n 205E2502−52, with a coating
that protects conductive surfaces from condensation. MOD−DOT #9
FA2100 CVR
FSB014
23−70−04−14
Nov.. 26/07 P/N: 2100-1025−02
This modification upgrades the recorder unit
software to Software Revision 04.
FA2100 CVR
FSB015
23−70−04−15
Sep. 01/08 P/N:
P/N:
P/N:
P/N:
P/N:
P/N:
P/N:
P/N:
P/N:
P/N:
P/N:
P/N:
Replacing the previous Aircraft Interface (AI)
PWA, Acquisition Processor (AP) PWA, Audio
Compressor PWA, and AP to AI W001 ribbon
cables with the new Aircraft Interface PWA,
and AP to AI W001 ribbon cables
MOD−DOT #10
FA2100 CVR
FSB016
23−70−04−16
Sep. 04/08 P/N: 2100−1010−( )
P/N: 2100−102X−( )
P/N: 2100-1010-( )
P/N: 2100-1020-( )
P/N: 2100-1025-( )
2100−1010−00
2100−1010−50
2100−1010−51
2100−1020−00
2100−1020−02
2100−1020−50
2100−1020−51
2100−1020−90
2100−1020−91
2100−1020−93
2100−1020−98
2100−1020−99
Installation of the Capacitor Support Bracket
MOD−DOT #11
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23–70–04
Service Bulletin
Rev. 15 Page xxx
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
SERVICE BULLETIN LIST
FA2100 CVR
FSB017
23−70−04−17
Nov. 09/10
P/N: 2100−1010−( )
P/N: 2100−102X−( )
Introduction of Improved Storage Capacitor
MOD−DOT #13
FA2100 CVR
FSB018
23−70−04−18
Jan. 14/11
P/N:
P/N:
P/N:
P/N:
P/N:
P/N:
P/N:
P/N:
P/N:
P/N:
Replacement of Non−Conforming Hardware
MOD−DOT N/A
FA2100 CVR
FSB019
23−70−04−19
Feb. 13/13 NAND Memory
change
NAND Memory change
Introduction of New Crash Survivable Memory
Unit (CSMU)
MOD−DOT 14
FA2100 CVR
FSB020
23−70−04−020
Jan. 10/13 Released
Intro of SW Rev 06
Introduction
Software Revision 06
FA2100 CVR
FSB021
23−70−04−021
Jan. 22/14 All P/Ns
Introduction
Software Revision (Various)
FA2100 CVR
FSB022
23−70−04−022
Jul. 01/15
Introduction of the new 90−Day Beacon
MOD−DOT 15
FA2100 CVR
FSB023
23−70−04−023
Mar. 22/16 P/N: 2100−1020−00
2100−1020−02
2100−1020−50
2100−1020−51
2100−1020−90
2100−1020−93
2100−1020−98
2100−1020−99
2100−1025−22
2100−1220−00
2100−1220−02
2100−1225−22
2100−1225−24
2100−1925−22
2100−1010−00
2100−1010−51
2100−1020−00
2100−1020−02
2100−1020−51
2100−1025−02
2100−1025−12
2100−1025−22
2100−1026−02
2100−2043−01
All P/Ns
Introduction
Software Revision (Various)
New CSMU Part Number
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
The document reference is online, please check the correspondence between the online documentation and the printed version.
23–70–04
Service Bulletin
Rev. 15 Page xxxi
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
THIS PAGE IS INTENTIONALLY LEFT BLANK
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
The document reference is online, please check the correspondence between the online documentation and the printed version.
23–70–04
Service Bulletin
Rev. 15 Page xxxii
Apr. 14/16
AVIATION RECORDERS
L–3 COMMUNICATIONS, AVIATION RECORDERS
FIELD SERVICE BULLETIN / SERVICE INFORMATION LETTER
EXPORT CONTROL STATEMENT
The technical information about recorder products/software are being exported from the
United States in accordance with the Export Administration Regulations ECCN 9E991, No
License Required. Diversion contrary to U.S. law is prohibited. In accordance with U.S.
Law (31 CFR Part 746, and Supplement No.1 to Part 774, and CFR Part 550) resale/re–export or transfer to the countries identified therein is prohibited without the prior written consent of the U.S. Department of Commerce.
HTSUS, Sch. B: 4901.10.0040, 4901.10.0000
LIMITED RIGHTS LEGEND
Notice to persons receiving this document and/or data: This document and/or data contains information in which L–3 Communications Corporation, Aviation Recorders Division,
has a protectable interest and is subject to change without notice. The use, duplication,
and/or disclosure, by persons receiving this document and/or data may be subject to restrictions. No part of this document and/or data contained herein may be reproduced and/
or used in any form to design, manufacture, and/or test, anything without written permission from L–3 Communications Corporation, Aviation Recorders Division.
The document reference is online, please check the correspondence between the online documentation and the printed version.
AVIATION RECORDERS
100 Cattlemen Rd., Sarasota, FL 34232
Telephone: 941-371-0811 Facsimile: 941-377-5591
SERVICE BULLETIN
MODEL FA2100 COCKPIT VOICE AND DATA RECORDER
INTRODUCTION OF SOFTWARE REVISION 07 & 08
Date: May 02, 2013
I.
BULLETIN NO. FA2100CVDR SB017 R1
PLANNING INFORMATION
A.
Effectivity
L−3 Communications, Aviation Recorders, Model FA2100 Cockpit Voice &
Data Recorder, Part Numbers: 2100−3083−00, 2100−3083−10, and
2100−3083−50.
All affected FA2100CVDR part numbers manufactured after November 2012
will have this modification incorporated. The table below identifies the beginning serial numbers for this production cut-in.
Table 1. Serial Number Effectivity
Beginning Serial
Number
Part Number
New Software
Version
Audio Compressor
PWA P/N
2100−3083−00
000840345 and greater
840E2261−07
205E3977−19
2100−3083−10
000849079 and greater
840E3565−08
205E3977−19
2100−3083−50
000846290 and greater
840E3555−07
205E3977−25
B.
Concurrent Requirements
None.
C.
Reason
A product improvement has been made to the CVDR which enhances the
software. The improvement minimizes the effects of external cockpit noise
through the recorder’s audio input, providing a reliable Push−to−Test function.
This is a Product Improvement that is recommended for existing recorders in
the field.
D.
Description
This modification upgrades the recorder unit software and Audio Compressor
PWA per Table 1.
23‐70‐07-017 R1
Page 1 of 11
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AVIATION RECORDERS
100 Cattlemen Rd., Sarasota, FL 24232
Telephone: 941-371-0811 Facsimile: 941-377-5591
SERVICE BULLETIN
FA2100CVDR
E.
BULLETIN NO. FA2100CVDR SB017 R1
Compliance
This is a recommended modification for units in the field and may be incorporated the next time the recorder is in the shop.
F.
Approval
This service bulletin contains no modification information that revises the approved configuration and therefore does not require governmental or other
regulatory agency approval. Operators are not required to apply for modification approval for this change as it does not affect the form, fit, or function of
the top level LRU, nor the FA2100CVDR TSO.
G.
Manpower
3.0 hours with testing.
H.
Weight and Balance
Not affected.
I.
Electrical Load Data
Not changed.
J.
Software Accomplishment Summary
Model FA2100CVR
Document No: 818−E1436−20, Revision: K
K.
Reference
L−3AR Notifications of Change: NOC #15224
L−3AR Engineering Change Orders: ECO #15323
L.
Other Publications Affected
Model FA2100 Cockpit Voice and Flight Data Recorder Component Maintenance Manual, (23–70–07), P/N 165E1690−00.
23‐70‐07-017 R1
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AVIATION RECORDERS
100 Cattlemen Rd., Sarasota, FL 24232
Telephone: 941-371-0811 Facsimile: 941-377-5591
SERVICE BULLETIN
FA2100CVDR
II.
BULLETIN NO. FA2100CVDR SB017 R1
MATERIAL INFORMATION
A.
Material Price and Availability
This modification can be completed in one of the following ways:
1) An L-3AR Product Support Engineer can provide on−site support; or
2) The FA2100CVDR may be shipped to the L-3AR repair station; or
3) In the field by Operators or Authorized Repair Facilities that have the necessary Model FA2100CVDR test equipment and factory training.
For the 2100−3083−00/−10, the current 205E3997−17 Audio Compression
Circuit Board must be sent to the Factory Repair Station for exchange. Customers will be sent P/N 205E3997−19, ready for installation into the CVDR.
Customers must specify their request for the new part number on the Repair/
Exchange order.
For the 2100−3083−50, the current 205E3997−22 Audio Compression Circuit
Board must be sent to the Factory Repair Station for exchange. Customers
will be sent P/N 205E3997−25, ready for installation into the CVDR. Customers must specify their request for the new part number on the Repair/Exchange order.
The Software Revision is ordered through L-3AR Sales; see Table 2 below for
specific part numbers. One Software CD may be utilized on multiple CVDRs
with the same part number. The Software CD part number must match the
software part number located on the CVDR name label.
Software Revision 07 and 08 available from L-3AR Sales:
L-3 Communications
Aviation Recorders
P.O. Box 3041
Sarasota, FL 34230–3041 USA
Telephone: (941) 371–0811
Fax: (941) 377–5591
SITA: SRQLFCR
23‐70‐07-017 R1
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AVIATION RECORDERS
100 Cattlemen Rd., Sarasota, FL 24232
Telephone: 941-371-0811 Facsimile: 941-377-5591
SERVICE BULLETIN
FA2100CVDR
BULLETIN NO. FA2100CVDR SB017 R1
Table 2. Material Information/Pricing List
Keyword
Quantity
Part
Number
Price
U.S.D.
Delivery
2100-3083−00 Recorder Software
1 ea.
840E2261−07
250
30 Days
2100-3083−10 Recorder Software
1 ea.
840E3565−08
250
30 Days
2100-3083−50 Recorder Software
1 ea.
840E3555−07
250
30 Days
CICC Loader Utility Software Ver. 3.0
1 ea.
883E1893-12
No Charge
30 Days
CICC Interface Utility Software Ver. 3.7
1 ea.
883E1827-18
No Charge
30 Days
For 2100-3083-00/-10, Audio Com­
pression Circuit Board
1 ea.
205E3977-19
1,746 New
90 Days
For 2100-3083-00/-10, Audio Com­
pression Circuit Board
1 ea.
205E3977-19
1,222 Exchange
30 Days
For 2100-3083-50, Audio Compres­
sion Circuit Board
1 ea.
205E3977-25
1,746 New
90 Days
For 2100-3083-50, Audio Compres­
sion Circuit Board
1 ea.
205E3977-25
1,222 Exchange
30 Days
B.
Tooling
For those ROC/6 and ROC/7 test stations operating Microsoft XP and with the internal 17TES0046 RECORDER INTERFACE ADAPTER circuit board, L−3AR recommends an update to the Recorder Interface. ROC/6 and ROC/7 users should
remove the 17TES0046 circuit board, and obtain the 17TES0076 USB
RECORDER INTERFACE. See the illustration in Figure 1 for more detail. ROSE
software version 4.0 (or higher) is required for all applications of the 17TES0076
USB RECORDER INTERFACE.
The 17TES0057 CVDR RECORDER INTERFACE CABLE connects between the
CVDR and the 17TES0076 USB RECORDER INTERFACE, and is included with
the 17TES0400 ROC/6 or the 17TES0700 ROC/7 test station.
23‐70‐07-017 R1
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AVIATION RECORDERS
100 Cattlemen Rd., Sarasota, FL 24232
Telephone: 941-371-0811 Facsimile: 941-377-5591
SERVICE BULLETIN
FA2100CVDR
BULLETIN NO. FA2100CVDR SB017 R1
Table 3. Required Tooling and Availability
Keyword
Quantity
Part Number
Price
U.S.D.
Delivery
Read Out Center 7 (ROC/7)
1 ea.
17TES0700
48,000
90 Days
Read Out Center 6 (ROC/6)
1 ea.
17TES0400
N/A
90 Days
CVDR Recorder Interface (RI)
Cable Assembly
1 ea.
17TES0057
2,243
90 Days
USB Recorder Interface
1 ea.
17TES0076
2,060
90 Days
23‐70‐07-017 R1
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AVIATION RECORDERS
100 Cattlemen Rd., Sarasota, FL 24232
Telephone: 941-371-0811 Facsimile: 941-377-5591
SERVICE BULLETIN
FA2100CVDR
BULLETIN NO. FA2100CVDR SB017 R1
Power
Input
Select
AC
INPUT
CICC LOADER
SOFTWARE
(CDROM)
CICC INTERFACE
SOFTWARE
(CDROM)
TO
ENHANCED
PARALLEL PORT
(EPP)
RECORDER USB FDAU
SIMULATOR (RUFS)
(RI) ADAPTER
17TES0076
FA2100CVDR
RECORDER INTERFACE
(RI) CABLE ASSY.
17TES0057
RECORDER
SOFTWARE
(CDROM)
READ-OUT CENTER /6 or /7
17TES0400 or 17TES0700
FA2100 COMPUTER INTERFACE
COMMUNICATIONS CABLE
CICC/2 17TES0070
and 17TES0072
DC
INPUT
CVDR
The 17TES0058 cable assembly must only
be attached during an upload process and FA2100 SOFTWARE UPLOAD
not used when downloading data or
CABLE ASSEMBLY 17TES0058
getting recorder status.
Typical Bench Setup For FA2100CVDR Recorder and ROC/6 and ROC/7
Figure 1.
23‐70‐07-017 R1
Page 6 of 11
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AVIATION RECORDERS
100 Cattlemen Rd., Sarasota, FL 24232
Telephone: 941-371-0811 Facsimile: 941-377-5591
SERVICE BULLETIN
FA2100CVDR
BULLETIN NO. FA2100CVDR SB017 R1
III. ACCOMPLISHMENT INSTRUCTIONS
CAUTION:
A.
ELECTROSTATIC DISCHARGE (ESD) WARNING: Since the FA2100CVDR
contains electrostatic sensitive devices, it must be modified at a workstation
equipped for such devices. Before handling printed wiring assemblies, ensure that proper personal ESD grounding techniques are used.
Installing CICC Loader and CICC Interface Utility Programs into the
ROC/6 or ROC/7.
The CICC Loader and CICC Interface utility executable programs are needed
to upload the recorder software and to verify that the upload process has been
achieved without any errors. To load these programs onto the ROC perform
the following steps:
(1) Turn ON the power to the ROC.
(2) Insert the CICC Loader CDROM into the ROC.
(3) At the Windows desktop, shut down the Recorder Interface (RI) by right
clicking on the RI Icon in the Windows System Tray at the bottom right of
the screen. Select “shutdown.”
(4) To install the CICC Loader from the Windows Start Menu, use the Browse
button to locate the setup.exe file on the CDROM and click the OK button.
(5) Follow the instructions on the Install Wizard and accept all defaults. The
Install Wizard will create a folder located at c:\Program Files\L-3
Com\CICC Loader. Left click and hold the CICC Loader (CICCLdr) icon
and drag it on to the desktop to create a short-cut.
(6) Insert the CICC Interface CDROM. Use the Browse button to locate the
setup.exe file on the CDROM and click the OK button.
(7) Follow the instructions on the Install Wizard and accept all defaults. The
Install Wizard will create a folder located at c:\Program Files\L-3
Com\CICC Interface. Left click and hold the CICC Interface (CICCIfc)
Icon and drag it on to the desktop to create a short-cut.
23‐70‐07-017 R1
Page 7 of 11
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AVIATION RECORDERS
100 Cattlemen Rd., Sarasota, FL 24232
Telephone: 941-371-0811 Facsimile: 941-377-5591
SERVICE BULLETIN
FA2100CVDR
B.
BULLETIN NO. FA2100CVDR SB017 R1
FA2100 Software Upload Procedure
(1) Connect the J1A rear connector of the FA2100CVDR to the ROC/6 or
ROC/7 using the Recorder Interface (RI) Cable Assy, P/N 17TES0057.
(2) Connect either 115 Vac/400 Hz, or +28 Vdc to the pig−tail connections of
the Recorder Interface (RI) Cable Assy. (Do Not connect both power input types at the same time).
(3) Connect the Computer Interface Communications Cable/2 (CICC/2),
P/N17TES0070 and 17TES0072, to the EPP port of the ROC/6 or ROC/7.
(4) Connect the FA2100 Software Upload Cable Assembly, P/N 17TES0058,
to the FA2100 Recorder front panel GSE connector and the opposite end
to the Computer Interface Communications Cable/2 (CICC/2) Interface
Cable P/N: 17TES0072.
(5) Apply power to the FA2100CVDR Recorder under test.
(6) Turn ON the power to the ROC.
(7) Shut down the Recorder Interface (RI) by right clicking on the RI Icon in
the Windows System Tray at the bottom right of the screen. Select “shutdown.”
NOTE:
You can not use RI and CICC Loader at the same time.
(8) Note the FDP & SMP version and checksum values listed on the label of
the FA2100CVDR Software Distribution CD.
(9) Insert the FA2100CVDR Software Distribution CD into the ROC.
(10) From the Windows desktop double click on the CICC Loader Icon.
(11) When the CICC Loader window appears, refer to Figure 2, select the
Browse button at the Load Directory and set the source to “D:\.” (If it is
not already present).
(12) Select the software load type by choosing the Recorder part number listed
that matches the part number found on the recorder identification label.
(13) Left click the Load button.
23‐70‐07-017 R1
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AVIATION RECORDERS
100 Cattlemen Rd., Sarasota, FL 24232
Telephone: 941-371-0811 Facsimile: 941-377-5591
SERVICE BULLETIN
FA2100CVDR
BULLETIN NO. FA2100CVDR SB017 R1
(14) Observe the progress window and verify that a status pop−up window appears stating that the FA2100 loaded successfully.
Note:
If the load procedure was unsuccessful, remove the CD from the D:\
drive, exit the CICC loader program, turn OFF power to the FA2100
CVDR Recorder, and repeat steps (5) − (15).
D:\
Figure 2. CICC Loader Window
(15) Remove power from the recorder and Exit the CICC Loader utility program.
(16) Disconnect the Software Upload Cable 17TES0058 from the FA2100 front
panel GSE connector and CICC Cable Assembly.
C.
To Verify the Software Upload
Once the FA2100 software has been loaded, it needs to be verified using the
CICC Interface utility program on the ROC/6 or ROC/7 Ground Station:
(1) Connect Computer Interface Communications Cable/2 (CICC/2) (P/N:
17TES0072 and 17TES0070) to FA2100CVDR front panel GSE connector.
(2) Apply power to the FA2100CVDR Recorder and to the ROC/6 or ROC/7.
23‐70‐07-017 R1
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AVIATION RECORDERS
100 Cattlemen Rd., Sarasota, FL 24232
Telephone: 941-371-0811 Facsimile: 941-377-5591
SERVICE BULLETIN
FA2100CVDR
BULLETIN NO. FA2100CVDR SB017 R1
(3) At the Windows desktop, shut down the Recorder Interface (RI) if not
already shutdown from previous steps by right clicking on the RI Icon in
the Windows System Icon Tray at the bottom right of the screen. Select
“shutdown.”
(4) Also shut down the FTP program by right clicking on the FTP Icon in the
Windows System Tray at the bottom right of the screen. Select “Exit”.
(5) From the Windows desktop, activate the CICC Interface utility program by
double−clicking on the CICCIfc Icon.
(6) From the CICC Interface Menu, select the “Version” Command from the
list and left click the “Send” Command button. Observe that a pop-up
window appears showing the recorder software Part Number and SMP &
FDP Checksums.
(7) Match the listed SW Part Number and SMP & FDP Checksums with the
ones listed on the recorder software CD.
(8) Left click the OK button and left click the “Exit” button on the CICC Loader
Menu to exit the utility and return to the Windows desktop.
(9) Once the Software upload versions are validated, perform a full Return To
Service test procedure as listed in Sections 100 & 200 of the
FA2100CVDR CMM, ATA 23−70−07, P/N 165E1690−00.
D.
Modification Information
Incorporation of this Field Service Bulletin will be identified by marking in the
software revision section of the recorder’s name plate with black paint.
23‐70‐07-017 R1
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AVIATION RECORDERS
100 Cattlemen Rd., Sarasota, FL 24232
Telephone: 941-371-0811 Facsimile: 941-377-5591
SERVICE BULLETIN
FA2100CVDR
BULLETIN NO. FA2100CVDR SB017 R1
Table 4. Software Revision Marking
Software Revision
Recorder
E.
2100−3083−00
07
2100−3083−10
08
2100−3083−50
07
Material Information
Table 5. Material Information/Pricing List
Keyword
Quantity
Part
Number
Price
U.S.D.
Delivery
2100-3083−00 Recorder Software
1 ea.
840E2261−07
250
30 Days
2100-3083−10 Recorder Software
1 ea.
840E3565−08
250
30 Days
2100-3083−50 Recorder Software
1 ea.
840E3555−07
250
30 Days
CICC Loader Utility Software Ver. 3.0
1 ea.
883E1893-12
No Charge
30 Days
CICC Interface Utility Software Ver. 3.7
1 ea.
883E1827-18
No Charge
30 Days
For 2100-3083-00/-10, Audio Com­
pression Circuit Board
1 ea.
205E3977-19
1,746 New
90 Days
For 2100-3083-00/-10, Audio Com­
pression Circuit Board
1 ea.
205E3977-19
1,222 Exchange
30 Days
For 2100-3083-50, Audio Compres­
sion Circuit Board
1 ea.
205E3977-25
1,746 New
90 Days
For 2100-3083-50, Audio Compres­
sion Circuit Board
1 ea.
205E3977-25
1,222 Exchange
30 Days
L‐3 Communications, Aviation Recorders
David D. Dowding
Product Support Manager
SB Issue Date: November 12, 2012
SB Revision : May 3, 2013
23‐70‐07-017 R1
Page 11 of 11
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AVIATION RECORDERS
L–3 COMMUNICATIONS, AVIATION RECORDERS
FIELD SERVICE BULLETIN / SERVICE INFORMATION LETTER
EXPORT CONTROL STATEMENT
The technical information about recorder products/software are being exported from the
United States in accordance with the Export Administration Regulations ECCN 9E991, No
License Required. Diversion contrary to U.S. law is prohibited. In accordance with U.S.
Law (31 CFR Part 746, and Supplement No.1 to Part 774, and CFR Part 550) resale/re–export or transfer to the countries identified therein is prohibited without the prior written consent of the U.S. Department of Commerce.
HTSUS, Sch. B: 4901.10.0040, 4901.10.0000
LIMITED RIGHTS LEGEND
Notice to persons receiving this document and/or data: This document and/or data contains information in which L–3 Communications Corporation, Aviation Recorders Division,
has a protectable interest and is subject to change without notice. The use, duplication,
and/or disclosure, by persons receiving this document and/or data may be subject to restrictions. No part of this document and/or data contained herein may be reproduced and/
or used in any form to design, manufacture, and/or test, anything without written permission from L–3 Communications Corporation, Aviation Recorders Division.
The document reference is online, please check the correspondence between the online documentation and the printed version.
100 Cattlemen Road, Sarasota, Florida 34232
Telephone: 941−371−0811 Facsimile: 941−377−5591
SERVICE INFORMATION LETTER
DATE: March 11, 2015
Letter No. FA2100CVR 037
TO:
USERS OF THE MODEL FA2100CVR COCKPIT VOICE RECORDER
SUBJECT:
NEW CONFORMAL COATING PROCESS FOR ACQUISITION PROCESSOR CIRCUIT CARD ASSEMBLY (CCA)
To Whom It May Concern,
As of January 2015, all part numbers of L−3 Communications Model FA2100 Cockpit Voice
Recorders manufactured will contain a new conformal coating process on the Acquisition
Processor CCA.
L-3 Communications has introduced this new conformal coating process on all configurations of the Acquisition Processor Circuit Card Assemblies (CCA’s) to improve their moisture resistance and mitigate pending obsolescence of the incumbent coating.
As this is a process change only, not affecting any form, fit or function aspects of the Model
FA2100 CVR, no external modification identification will be implemented. However,
through L-3 AR’s internal serialization and as built manufacturing system, we are tracking
all Serial Numbers that have the new process CCA’s incorporated.
Sincerely
L‐3 Communications, Aviation Recorders
Mike Phillips
Product Support Manager
Issue Date:
March 11, 2015
1 of 1
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AVIATION RECORDERS
L–3 COMMUNICATIONS, AVIATION RECORDERS
FIELD SERVICE BULLETIN / SERVICE INFORMATION LETTER
EXPORT CONTROL STATEMENT
The technical information about recorder products/software are being exported from the
United States in accordance with the Export Administration Regulations ECCN 9E991, No
License Required. Diversion contrary to U.S. law is prohibited. In accordance with U.S.
Law (31 CFR Part 746, and Supplement No.1 to Part 774, and CFR Part 550) resale/re–export or transfer to the countries identified therein is prohibited without the prior written consent of the U.S. Department of Commerce.
HTSUS, Sch. B: 4901.10.0040, 4901.10.0000
LIMITED RIGHTS LEGEND
Notice to persons receiving this document and/or data: This document and/or data contains information in which L–3 Communications Corporation, Aviation Recorders Division,
has a protectable interest and is subject to change without notice. The use, duplication,
and/or disclosure, by persons receiving this document and/or data may be subject to restrictions. No part of this document and/or data contained herein may be reproduced and/
or used in any form to design, manufacture, and/or test, anything without written permission from L–3 Communications Corporation, Aviation Recorders Division.
The document reference is online, please check the correspondence between the online documentation and the printed version.
AVIATION RECORDERS
100 Cattlemen Road, Sarasota, Florida 34232
Telephone: 941-371-0811 Facsimile: 941-377-5591
SERVICE BULLETIN
PORTABLE INTERFACE (PI) UNIT
MOD DOT 9 REQUIRED FOR NAND RECORDERS
Date: September 19, 2013
I.
BULLETIN NO. PI SB005 Rev. 1
PLANNING INFORMATION
A.
Effectivity
Portable Interface (PI) Unit, manufactured by L-3 Communications, part number
17TES0043.
All Portable Interface Units bearing serial number 917791 or higher will have this
Service Bulletin incorporated from the factory.
B.
Reason
Portable Interface (PI) Unit Mod Dot 9 is required for compatibility with recorders
model number FA2100, FA2200, and FA2300 assembled with the NAND memory.
C.
Description
L−3 Aviation Recorders is now manufacturing model FA2100, FA2200, and FA2300
products with NAND memory devices in the Crash Survivable Memory Unit (CSMU).
Recorders equipped with NAND memory can be identified by their Mod Dot status as
shown in Table 1. Additionally, NAND recorders will feature the L−3 logo on top of the
CSMU as shown in Figure 1.
Figure 1
In order to be compatible with the NAND recorders, the 17TES0043 Portable
Interface (PI) Unit must contain Mod Dot 9. A modified Portable Interface will still be
compatible with older recorders which do not contain NAND memory.
PI SB005 R1
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AVIATION RECORDERS
100 Cattlemen Road, Sarasota, Florida 34232
Telephone: 941-371-0811 Facsimile: 941-377-5591
SERVICE BULLETIN
PORTABLE INTERFACE (PI) UNIT
MOD DOT 9 REQUIRED FOR NAND RECORDERS
Date: September 19, 2013
BULLETIN NO. PI SB005 Rev. 1
Table 1. Recorder Mod Dot Status with NAND Memory
Recorder Type
Mod Dot Number
CVR
Mod Dot 14
CVDR
Mod Dot 13
FDR
Mod Dot 13
For CVR and CVDR applications with NAND memory, the audio data file extensions
in the Portable Interface (PI) Unit have been modified for partial and full audio download. When the NAND CVR is partially downloaded (34 minutes or less), the CVR
file extension in the Portable Interface (PI) Unit will be .cvr. When the NAND CVR is
fully downloaded (35 minutes or more), the CVR file extensions in the Portable Interface (PI) Unit will be .crr.
The file extension for non−modified CVRs (older units with NOR memory), remains
as .cvr for all audio downloads.
Downloaded files with the .crr extension may be converted into .wav files in the
same manner as the .cvr files. The following are three L−3 AR software products
that include the file conversion utilities:
1.
ROSE (Read Out Support Equipment) software p/n 17TES0321, Version 4.7
and higher.
2.
ADLP (Audio Data Link Player) software p/n 17TES0436, Version 3.3 and higher.
3.
CVR Audio Utility (CVRUtil.exe), Version 1.1 and higher. Contained on ROSE
Utility CD Bundle p/n 883E1894-01.
Contact L-3 AR Product Support for details on obtaining the software items listed
above.
D.
Approval
This Service Bulletin contains no modification information that revises the approved
configuration and therefore does not require governmental or other regulatory
agency approval.
PI SB005 R1
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AVIATION RECORDERS
100 Cattlemen Road, Sarasota, Florida 34232
Telephone: 941-371-0811 Facsimile: 941-377-5591
SERVICE BULLETIN
PORTABLE INTERFACE (PI) UNIT
MOD DOT 9 REQUIRED FOR NAND RECORDERS
Date: September 4, 2013
E.
BULLETIN NO. PI SB005
Manpower
Not applicable.
F.
Material Cost and Availability
Mod Dot 9 can be installed by L−3AR Product Support Engineers, or at the factory
repair station. The cost for the update is $435.00 USD.
G.
Tooling
Not applicable.
H.
Weight and Balance
Not affected.
I.
Reference
Portable Interface (PI) Unit Operator’s Manual, part number 165E1630-00,
and ECN−015750.
II.
MODIFICATION INFORMATION
Incorporation of this Service Bulletin shall be identified by marking Modification 9 on
the Portable Interface name label as shown in Figure 2.
Figure 2
PI SB005 R1
Page 3 of 4
The document reference is online, please check the correspondence between the online documentation and the printed version.
AVIATION RECORDERS
100 Cattlemen Road, Sarasota, Florida 34232
Telephone: 941-371-0811 Facsimile: 941-377-5591
SERVICE BULLETIN
PORTABLE INTERFACE (PI) UNIT
MOD DOT 9 REQUIRED FOR NAND RECORDERS
Date: September 4, 2013
BULLETIN NO. PI SB005
III. MATERIAL INFORMATION
L−3 Aviation Recorders will install this Service Bulletin (Portable Interface
Mod. Dot 9) for $435. The Portable Interface (PI) Unit must be returned to the
Aviation Recorder factory Repair Station for modification.
Shipping Address:
L−3 Communications
Aviation Recorders
100 Cattlemen Road
Sarasota, FL 34232 USA
Attn: Aviation Recorders Repair Department
Tel: (941) 377−5558
L-3 Communications, Aviation Recorders
Dave Dowding
Product Support Manager
SB Issue Date:
Rev. 1 Issue Date:
Sep. 04, 2013
Sep. 19, 2013
PI SB005 R1
Page 4 of 4
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The document reference is online, please check the correspondence between the online documentation and the printed version.
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
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COMPONENT MAINTENANCE MANUAL
FA2100CVR
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COMPONENT MAINTENANCE MANUAL
FA2100CVR
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FA2100CVR
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
TABLE OF CONTENTS
SUBJECT/DESCRIPTION
Page
INTRODUCTION
1.
GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1
2.
ACRONYMS AND ABBREVIATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1
3.
DOCUMENT REQUIREMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2
4.
RECORDER DEFINITIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2
5.
MAINTENANCE PHILOSOPHY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3
6.
COMPONENT MAINTENANCE MANUAL (CMM) DESCRIPTION . . . . . . . . . . . . . . . . .
3
A.
FRONT MATTER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3
B.
DESCRIPTION AND OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3
C.
TESTING AND TROUBLESHOOTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4
D.
DISASSEMBLY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4
E.
CLEANING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4
F.
CHECK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4
G.
REPAIR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4
H.
ASSEMBLY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4
I.
SPECIAL TOOLS AND TEST FIXTURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5
J.
ILLUSTRATED PARTS LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5
7.
DOCUMENT VERIFICATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5
8.
COMPONENT MAINTENANCE MANUAL (CMM) EFFECTIVITY . . . . . . . . . . . . . . . . .
6
9.
PART NUMBER FORMATTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6
DESCRIPTION AND OPERATION
1.
GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1
2.
FA2100 CONFIGURATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2
3.
SYSTEM DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4
A.
Underwater Acoustic Beacon . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4
B.
Circuit Boards . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5
C.
Power, Control and Monitor Signal Interface Characteristics . . . . . . . . . . . . . . .
5
D.
Voice Data Interface Characteristics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
11
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23–70–04
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
TABLE OF CONTENTS (Cont.)
4.
E.
Data Recording Storage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
12
F.
Audio Monitoring . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
17
G.
Storage Capacity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
17
H.
Data Retrieval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
18
I.
Data Reproduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
19
J.
Built-In-Test (BIT) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
19
K.
Crash Survivable Memory Unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
20
L.
Crash and Fire Protection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
20
M.
Control Unit, Microphone & Preamplifier Equipment . . . . . . . . . . . . . . . . . . . . . .
20
N.
Remote Microphone Module . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
21
O.
Ground Support Equipment Interface . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
22
P.
BIT and Fault Detection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
22
FA2100 CVR SPECIFICATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
23
A.
Applicable Documents . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
23
B.
Physical Characteristics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
24
C.
Electrical Characteristics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
24
D.
Environmental Characteristics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
24
E.
Crash and Fire Protection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
24
F.
CSMU Torque Requirement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
24
5.
INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
24
6.
THEORY OF OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
32
A.
MODEL FA2100 CVR SYSTEM THEORY OF OPERATION . . . . . . . . . . . . . . .
32
B.
Aircraft Interface (AI) PWA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
33
C.
Audio Compressor (AC) PWA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
37
D.
Acquisition Processor (AP) PWA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
40
7.
SOFTWARE CONSIDERATIONS (ALL P/NS EXCEPT 2100−1X25/1X26/1X27−( ) and
2100−1X20−( ) MOD−DOT #7) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43
A.
Store Manager Processor Software Organization . . . . . . . . . . . . . . . . . . . . . . . .
43
B.
Software Operating States . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
44
C.
Data Structures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
49
D.
Fault Processing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
51
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
The document reference is online, please check the correspondence between the online documentation and the printed version.
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Table of Contents
Rev. 15 Page xxxix
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
TABLE OF CONTENTS (Cont.)
8.
9.
SOFTWARE CONSIDERATIONS (P/NS: 2100−1X25/1X26/1X27−( ) and 2100−1X20−( )
MOD−DOT#7) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53
A.
Equipment Environment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
53
B.
Software Partitioning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
53
C.
Memory Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
53
D.
Interfaces . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
53
E.
Push−to−Test (PTT) Functionality . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
56
F.
Bulk Erase . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
56
G.
Recorder Synchronization . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
57
H.
Data downloading (P/N: 2100−1X25/1X26/1X27−( ) only) . . . . . . . . . . . . . . . . .
57
I.
CVR RIPS status monitoring (P/N: 2100−1X25−22/−24, 2100−1X26−( ), and
2100−1X27−( ) only) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
58
On board Maintenance System Interface . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
60
A.
Label 350 Status Word Output . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
61
B.
Label 354 LRU Identification Output . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
64
C.
Label 377 ARINC 429 Equipment Identification Word Output . . . . . . . . . . . . . .
67
D.
OMS Input . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
67
10. CVR DATALINK INPUT INTERFACE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
67
A.
Data Link Input and Encapsulation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
68
B.
DataLink Heartbeat . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
70
C.
Williamsburg Bit−Oriented Protocol Version Support . . . . . . . . . . . . . . . . . . . . . .
70
D.
DataLink Memory Capacity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
71
E.
DataLink Retrieval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
71
TESTING
1.
GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 101
2.
MAINTENANCE PHILOSOPHY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 102
A.
Model FA2100CVR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
102
B.
Model S151/S161, S152/S162, and S251/S261 Control Units . . . . . . . . . . . . .
103
C.
MODEL S150/S160 MICROPHONE PREAMPLIFIER MODULES . . . . . . . . . .
103
D.
MODEL S055 AND S056 ELECTRET CONDENSER MICROPHONES . . . . .
103
3.
MODEL FA2100CVR RECORDER IN-SERVICE CHECKOUT . . . . . . . . . . . . . . . . . . . . 103
4.
TEST EQUIPMENT REQUIRED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 105
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
The document reference is online, please check the correspondence between the online documentation and the printed version.
23–70–04
Table of Contents
Rev. 15 Page xl
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
TABLE OF CONTENTS (Cont.)
5.
6.
READ−OUT CENTER/6 (ROC/6), WINDOWS XP, AUTO−TESTING . . . . . . . . . . . . . . 106
A.
READ−OUT CENTER/6 (ROC/6) Interconnects . . . . . . . . . . . . . . . . . . . . . . . . . .
106
B.
READ−OUT CENTER/6 (ROC/6) Sound Card Setup . . . . . . . . . . . . . . . . . . . . .
109
C.
READ−OUT CENTER/6 (ROC/6) − CATS AUTOTEST . . . . . . . . . . . . . . . . . . . .
112
D.
READ−OUT CENTER/6 (ROC/6) − Autotest Descriptions . . . . . . . . . . . . . . . . .
118
E.
ROC/6 − Audio Setup Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
125
F.
ROC/6 − AUDIO DOWNLOAD & PLAYBACK . . . . . . . . . . . . . . . . . . . . . . . . . . . .
133
READ−OUT CENTER/7 (ROC/7), WINDOWS 7, AUTO−TESTING . . . . . . . . . . . . . . . 135
A.
READ−OUT CENTER/7 (ROC/7) Interconnects . . . . . . . . . . . . . . . . . . . . . . . . . .
135
B.
READ−OUT CENTER/7 (ROC/7) − Sound Card Setup . . . . . . . . . . . . . . . . . . . .
139
C.
READ−OUT CENTER/7 (ROC/7) − CATS Autotest . . . . . . . . . . . . . . . . . . . . . . .
145
D.
READ OUT CENTER/7 (ROC/7) − Autotest Descriptions . . . . . . . . . . . . . . . . . .
162
7.
READ−OUT CENTER/7 (ROC/7) − AUDIO DOWNLOAD & PLAYBACK . . . . . . . . . . . 170
8.
Underwater Locator Beacon Testing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 171
9.
MODEL FA2100CVR TROUBLESHOOTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 174
10. FA2100CVR SOFTWARE UPLOAD PROCEDURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 178
A.
Installing Software Upload Utility and CICC Interface Programs . . . . . . . . . . . .
178
B.
To upload the FA2100 Software perform the following steps: . . . . . . . . . . . . . .
181
C.
To Verify the Software Upload . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
182
AUTOMATIC TESTING
1.
GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201
DISASSEMBLY
1.
GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 301
2.
MODEL FA2100CVR DISASSEMBLY INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . 301
A.
B.
C.
Underwater Locator Beacon Removal
(See Figure 301 or IPL Figure 1, Item 80) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
302
Crash Survivable Memory Unit (CSMU) Removal
(See Figure 305 or IPL Figure 1, Item 185) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
304
Acquisition Processor (AP) PWA Removal
(See Figure 306 or IPL Figure 1, Item 175) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
307
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Table of Contents
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Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
TABLE OF CONTENTS (Cont.)
D.
E.
Audio Compressor PWA (AC) Removal
(See Figure 307 or IPL Figure 1, Item 155) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
309
Aircraft Interface PWA (AI) Removal
(See Figure 307 or IPL Figure 1, Item 105) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
312
CLEANING
1.
GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 401
2.
MATERIALS REQUIRED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 401
3.
CLEANING PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 401
A.
Printed Wiring Assembly Cleaning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
402
B.
Connector Cleaning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
402
C.
Underwater Locator Device (Beacon) Cleaning . . . . . . . . . . . . . . . . . . . . . . . . . .
402
CHECK
1.
GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 501
2.
CHECKS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 501
A.
Main Recorder Assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
501
B.
Mechanical Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
501
C.
Electrical Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
502
D.
Underwater Locator Device (ULD) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
502
REPAIR
1.
GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 601
ASSEMBLY
1.
GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 701
2.
REQUIRED MATERIALS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 701
3.
ASSEMBLY INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 702
A.
General Assembly Techniques . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
702
B.
Acquisition Processor (AP) PWA Installation
(See Figure 701 or IPL Figure 1, Item 175) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
702
Aircraft Interface PWA (AI) Installation
(See Figure 703 or IPL Figure 1, Item 105) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
704
C.
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23–70–04
Table of Contents
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Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
TABLE OF CONTENTS (Cont.)
D.
E.
F.
G.
4.
Audio Compressor PWA (AC) Installation
(See Figure 703 or IPL Figure 1, Item 155) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
706
Chassis Cover Installation
(See Figure 704 and Figure 706 or IPL Figure 1, Item 20A/B) . . . . . . . . . . . . . .
709
Crash Survivable Memory Unit (CSMU) Installation
(See Figure 710 or IPL Figure 1, Item 185) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
714
Underwater Acoustic Beacon Assembly & Installation
(See Figure 713 and IPL Figure 1, Item 80) . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
721
STORAGE INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 723
A.
Storage in Original Containers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
723
B.
Storage Without Original Containers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
723
C.
Shipment Container Kit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
723
FITS AND CLEARANCES
1.
GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 801
2.
SYSTEM SPECIFICATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 801
A.
Physical Characteristics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
801
B.
Electrical Characteristics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
802
C.
Environmental Characteristics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
802
D.
Crash and Fire Protection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
802
E.
Torque Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
802
SPECIAL TOOLS, FIXTURES AND EQUIPMENT
1.
GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 901
2.
GROUND SUPPORT EQUIPMENT (GSE) DESCRIPTIONS . . . . . . . . . . . . . . . . . . . . . 905
A.
Portable Interface Unit, p/n: 17TES0043 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
905
B.
FA2100 Software Upload Cable Assembly & Distribution Diskettes . . . . . . . . .
905
C.
Audio Data Link Player Software . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
917
D.
CVR Download Cable . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
919
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Table of Contents
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Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
TABLE OF CONTENTS (Cont.)
ILLUSTRATED PARTS LIST
1.
GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1001
2.
PURPOSE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1001
3.
ABBREVIATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1001
4.
EQUIPMENT DESIGNATOR INDEX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1001
5.
NUMERICAL INDEX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1002
6.
DETAIL PARTS LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1002
7.
PART NUMBERING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1004
8.
MANUFACTURER’S CODE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1004
9.
L−3 AVIATION RECORDERS (L−3AR) AUTHORIZED PARTS . . . . . . . . . . . . . . . . . . . 1004
10. CONFIGURATION MATRIX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1006
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
The document reference is online, please check the correspondence between the online documentation and the printed version.
23–70–04
Table of Contents
Rev. 15 Page xliv
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
LIST OF FIGURES
FIGURE TITLE
PAGE
1. Model FA2100 Cockpit Voice Recorder (FA2100CVR) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2
2. Model FA2100 CVR, (2100-1010-00, 2100-1X20-00/02, 2100-1X25-XX, 2100-1X26-XX and
2100-1X27-XX) Functional System Block Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . 6
3. Model FA2100 GACVR (2100-1010-50/-51 and 2100-1020-50/-51)
Functional System Block Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7
4. Model FA2100 CVR, 30-Minute and 120-Minute Audio Monitor Schemes . . . . . . . . . . . . . . . 9
5. Model FA2100 CVR, 30-Minute and 120-Minute Recording Schemes . . . . . . . . . . . . . . . . . . 13
6. GACVR Fault Circuit for Pin 23 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20
7. Interwiring Diagram, Recorder FA2100 CVR
(2100-1010-00, 2100-1X20-00/-02, & 2100-1X25/1X26-XX) . . . . . . . . . . . . . . . . . . 26
8. ARINC 757A Interwiring Diagram, Recorder FA2100 CVR (2100-1X27-XX) . . . . . . . . . . . . 28
9. Interwiring Diagram, Recorder FA2100 GACVR (2100-10X0-50/-51)
with Customer−Furnished Control Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30
10. FA2100 CVR Overall Function Block Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32
11. 2–Hr FA2100 CVR (pre MOD−DOT #7) Word Partition Structure Streams . . . . . . . . . . . . . 46
12. 2–Hr FA2100 CVR Memory Structure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50
13. Generic DataLink Message Encapsulation Structure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 69
101. CVR Fault Circuit for Pin 23 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 104
102. ROC/6 w/CVR Automated Test Station Software (CATS) FA2100CVR TEST SETUP . 108
103. Volume Control Properties . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 109
104. Line In Input Level . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 110
105. Sound Card Properties . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 110
106. Playback Control, Volume Levels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 111
107. CVR Test, Start Toggle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 113
108. CVR Test, Warning Message . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 113
109. CVR Test, Instruction Message . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 113
110. CVR Test, Power Consumption Entry . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 114
111. CVR Test, Power Consumption Entry . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 114
112. CVR Test, Instruction Message . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 114
113. CVR Test, Proceed Message . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 115
114. CVR Test, Instruction Message . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 116
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
The document reference is online, please check the correspondence between the online documentation and the printed version.
23–70–04
Table of Contents
Rev. 15 Page xlv
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
LIST OF FIGURES (Cont.)
115. CVR Test, Warning Message . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 116
116. CVR Test, Instruction Message . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 116
117. CVR Test, Power Consumption Entry . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 117
118. CVR Test, Power Consumption Entry . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 117
119. CVR Test, Instruction Message . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 117
120. CVR Test, Proceed Message . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 118
121. Audio Setup Cable Assembly, 17TES0417 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 125
122. Audio Reference Level Utility, Warning Message . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 126
123. Audio Reference Level Utility, Menu . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 127
124. Audio Reference Level Utility, File Open Menu . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 127
125. Audio Reference Level Utility, Play Sound . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 128
126. Audio Reference Level Utility, Play Sound . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 128
127. Audio Reference Level Utility, Confirmation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 129
128. Audio Reference Level Utility, Warning Message . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 129
129. Audio Reference Level Utility, Menu . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 130
130. Audio Reference Level Utility, File Open Menu . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 130
131. Audio Reference Level Utility, Play Sound . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 131
132. Sound Card Input Results . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 131
133. CVR Tester, Update Reference Level . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 132
134. ROC/7 with CVR Automated Test Station Software (CATS 2.0)
FA2100CVR TEST SETUP − ROC/7’s DMF: Pre Jul. 2014. . . . . . . . . . . . . . . . . . 137
135. ROC/7 with CVR Automated Test Station Software (CATS 2.0)
FA2100CVR TEST SETUP − ROC/7’s DMF: Post Feb. 2015. . . . . . . . . . . . . . . . 138
136. CATS, Channels Control Screen . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 139
137. Volume Control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 140
138. Sound Control, Recording . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 140
139. Line−In Properties, Line−In Level . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 141
140. Sound, Playback Devices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 142
141. Speaker Properties, Levels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 143
142. Volume Mixer, Speaker Levels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 144
143. CATS, Connecting Pop-Up . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 146
144. CATS, Power Toggle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 146
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
The document reference is online, please check the correspondence between the online documentation and the printed version.
23–70–04
Table of Contents
Rev. 15 Page xlvi
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
LIST OF FIGURES (Cont.)
145. CATS, Start Test Toggle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 147
146. CATS, Test Mode and Options Screen . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 147
147. CATS, CVDR Test Confirmation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 148
148. CATS, CVDR Warning Message . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 148
149. CATS, CVDR Instruction Window . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 149
150. CATS, Power Test Input . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 149
151. CATS, Power Test Input . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 149
152. CATS, CVDR Instruction Window . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 150
153. CATS, CVDR Fault History Log . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 150
154. CATS, CVDR Clear Fault Log Confirmation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 151
155. CATS, CVDR Clear Latched Faults and Log Confirmation . . . . . . . . . . . . . . . . . . . . . . . . 151
156. CATS, CVDR Clear Latched Faults and Log Successful . . . . . . . . . . . . . . . . . . . . . . . . . . 151
157. CATS, CVDR Fault History Log . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 152
158. CATS, Continue Test Confirmation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 152
159. CATS, Test Results Screen . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 153
160. CATS, Connecting Pop-Up . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 154
161. CATS, Power Toggle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 154
162. CATS, Start Test Toggle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 155
163. CATS, Test Mode and Options Screen . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 155
164. CATS, CVDR Test Confirmation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 156
165. CATS, CVDR Warning Message . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 156
166. CATS, CVDR Instruction Window . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 157
167. CATS, Power Test Input . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 157
168. CATS, Power Test Input . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 157
169. CATS, CVDR Instruction Window . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 158
170. CATS, CVDR Fault History Log . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 158
171. CATS, CVDR Clear Fault Log Confirmation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 159
172. CATS, CVDR Clear Fault Log Confirmation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 159
173. CATS, CVDR Clear Latched Faults and Log Successful . . . . . . . . . . . . . . . . . . . . . . . . . . 159
174. CATS, CVDR Fault History Log . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 160
175. CATS, Continue Test Confirmation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 160
176. CATS, Test Results Screen . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 161
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
The document reference is online, please check the correspondence between the online documentation and the printed version.
23–70–04
Table of Contents
Rev. 15 Page xlvii
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
LIST OF FIGURES (Cont.)
177. Typical Software Upload Setup For FA2100 Recorder with CICC/2 Cable . . . . . . . . . . . 180
301. Underwater Locator Beacon Removal Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 303
302. CSMU Memory Sealing Screw Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 304
303. CSMU Memory Assembly Removal Diagram (PRE-MOD DOT 6) . . . . . . . . . . . . . . . . . . 305
304. CSMU Memory Assembly Removal Diagram (POST-MOD DOT 6
& PRE-MOD DOT 13) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 306
305. CSMU Memory Assembly Removal Diagram (POST-MOD DOT 13) . . . . . . . . . . . . . . . . 307
306. Acquisition Processor PWA Removal Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 309
307. Aircraft Interface & Audio Compressor PWA Removal Diagram . . . . . . . . . . . . . . . . . . . . 311
701. Acquisition Processor (AP) Installation Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 703
702. Aircraft Interface & Audio Compressor PWA Installation Diagram (PRE-MOD DOT 6) 707
703. Aircraft Interface & Audio Compressor PWA Installation Diagram (POST MOD DOT 6) 709
704. FA2100CVR Chassis Cover Seal Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 712
705. FA2100 GACVR Chassis RTV Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 713
706. FA2100CVR Chassis Cover Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 714
707. Crash Survivable Memory Unit (CSMU) Seal Application (Pre-MOD DOT 13) . . . . . . . . 715
708. Crash Survivable Memory Unit (CSMU) Seal Application (Post-MOD DOT 13) . . . . . . 716
709. Crash Survivable Memory Unit (CSMU) Seal Application (Post-MOD DOT 13) . . . . . . . 716
710. Crash Survivable Memory Unit (CSMU) Assembly (PRE-MOD DOT 6) . . . . . . . . . . . . . 718
711. Crash Survivable Memory Unit (CSMU) Assembly (POST-MOD DOT 6 &
PRE-MOD DOT 13) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 719
712. Crash Survivable Memory Unit (CSMU) Assembly (POST-MOD DOT 13) . . . . . . . . . . . 720
713. Underwater Locator Beacon Assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 722
714. Shipping Container, Short Box, p/n: 197E1746-00,
part of Shipment Package Kit: p/n: 147E1679-00. . . . . . . . . . . . . . . . . . . . . . . . . . . 724
801. Outline & Dimension Drawing
Model FA2100 CVR Recorder P/N: 2100-1010-( ) & 2100-102X-( ) . . . . . . . . . . . 804
901. Portable Interface Unit, p/n: 17TES0043 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 906
902. Portable Interface (PI) Unit, CVR Menu Structures. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 908
903. FA2100CVR Software Upload Connections
Using Computer Interface & Communications Cable (CICC) . . . . . . . . . . . . . . . . . 909
904. Recorder Interface Cable Assembly P/N: 17TES0057 . . . . . . . . . . . . . . . . . . . . . . . . . . . . 910
905. Computer Interface Communications Cable/2 (CICC/2) P/N: 17TES0070 . . . . . . . . . . . 911
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
The document reference is online, please check the correspondence between the online documentation and the printed version.
23–70–04
Table of Contents
Rev. 15 Page xlviii
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
LIST OF FIGURES (Cont.)
906. Programmers Adapter Cable Assembly P/N: 17TES0058 . . . . . . . . . . . . . . . . . . . . . . . . . 913
907. ROC/6 w/CVR Automated Test Station Software (CATS)
FA2100CVR TEST SETUP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 914
908. Recorder Interface Cable Assembly, 17TES0416 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 915
909. AC 115 VAC/400Hz Power Input Cable Assembly P/N: 17TES0411 . . . . . . . . . . . . . . . . 916
910. DC +28VDC Power Input Cable Assembly P/N: 17TES0412 . . . . . . . . . . . . . . . . . . . . . . 916
911. Audio Setup Cable Assembly, 17TES0417 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 917
912. ULD Test Set-Up . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 917
913. FA2100CVR Download Cable, p/n 17TES0078, Wiring Diagram . . . . . . . . . . . . . . . . . . . 920
1. Model FA2100 Cockpit Voice Recorder PN: 2100-1010-( ) & 2100-1X2X-( ) . . . . . . . . . . 1011
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
The document reference is online, please check the correspondence between the online documentation and the printed version.
23–70–04
Table of Contents
Rev. 15 Page xlix
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
LIST OF TABLES
TABLE TITLE
PAGE
1. Shop Verification . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6
2. FA2100 CVR Descriptions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3
1 Model FA2100 CVR Recording Specifications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15
2. Aircraft Interface (AI) PWA Current Configuration Where Used . . . . . . . . . . . . . . . . . . . . . . . . 33
3. ARINC 557/757/757A Aircraft Interface Signals . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34
4. Aircraft Interface PWA to Audio Compressor PWA Interface Signals . . . . . . . . . . . . . . . . . . . 36
5. Aircraft Interface PWA to Acquisition Processor PWA Interface Signals . . . . . . . . . . . . . . . . 37
6. Audio Compressor (AC) PWA Current Configuration Where Used . . . . . . . . . . . . . . . . . . . . . 39
7. Acquisition Processor (AP) PWA Current Configuration Where Used . . . . . . . . . . . . . . . . . . 41
8. Fault Processing Event Types and Descriptions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52
9. P/N 2100−1X25/1X26/1X27−( ) Software Fault Warning Failures . . . . . . . . . . . . . . . . . . . . . . 55
10. CVR RIPS Pin Assignment for P/N: 2100−1X25−22/−24 & 2100−1X26/1X27−( ) . . . . . . . 58
11. CVR OMS Output Words . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 60
12. CVR Pins Assigned to RIPS Status Monitoring . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 61
13. CVR Label 350 Output Format . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 61
14. CVR Fault Reporting Interactions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 62
15. CVR Status Word Fault Reporting Criteria . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 63
101. 17TES0400 READOUT CENTER/6 (ROC/6) − Parts List . . . . . . . . . . . . . . . . . . . . . . . . . 134
102. 17TES0700 READOUT CENTER/7 (ROC/7) − Parts List . . . . . . . . . . . . . . . . . . . . . . . . . 171
103. Underwater Locator Beacon Test Using L−3AR Test Set P/N: 17TES0015 . . . . . . . . . . 172
104. Underwater Locator Beacon Test Using Test Set P/N: 42A12( )
and 10 Mohm High Impedance Voltmeter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 173
105. FA2100 CVR Fault Code Corrective Actions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 174
106. FA2100CVR Software SMP Checksums . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 183
107. FA2100CVR Software FDP Checksums . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 185
401. Cleaning Materials Required . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 401
701. Required Assembly Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 701
801. FA2100 CVR Environmental Characteristics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 803
901. of Special Tools, Fixtures, and Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 901
902. Specification Control Drawing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 918
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23–70–04
Table of Contents
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
THIS PAGE IS INTENTIONALLY LEFT BLANK
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23–70–04
Table of Contents
Rev. 15 Page li
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
INTRODUCTION
1. GENERAL
This Component Maintenance Manual (CMM) documents the operation of and suggested
maintenance for the Model FA2100 Cockpit Voice Recorder, herein after referred to as the
FA2100CVR.
The FA2100CVR meets the performance requirements of ED-56A, while complying with
the interface requirements of ARINC 557/757 cockpit voice input data including Rotor
Speed and GMT interfaces. The only exception is P/N: 2100−1027−02 which complies
with the interface requirements of ARINC 757A only. In addition, the FA2100CVR, p/n:
2100−1025/1026/1027−XX, meets the performance requirements of ED−112. The cockpit
voice and area microphone channels are lowpass filtered, sampled, digitized, compressed, and stored in solid-state, crash protected memory. This CMM covers both the
30-minute and 2-hour memory storage versions of the FA2100CVR.
The FA2100CVR is designed as maintenance-free recorder. No periodic adjustments,
calibration, or maintenance is required to maintain this unit. The Model FA2100CVR is
considered an “ON CONDITION LRU.”
2. ACRONYMS AND ABBREVIATIONS
The following list defines the acronyms and abbreviations used throughout this CMM:
AC
ADLP
ARINC
ATA
ATC
ATE
ATR
BITE
CAA
CATS
CMM
CICC
CSMU
CVR
DC
EUROCAE
FAA
FDAU
GA
GMT
GND
GSE
IPL
Alternating Current
Audio and Data Link Playback
Aeronautical Radio, Inc.
Air Transport Association
Air Traffic Control
Automated Test Equipment
Air Transport Racking
Built−In Test Equipment
Civil Aviation Authority (United Kingdom)
CVR Automatic Test Software
Component Maintenance Manual
Computer Interface Communication Cable
Crash Survivable Memory Unit
Cockpit Voice Recorder
Direct Current
European Organization for Civil Aviation Equipment
Federal Aviation Administration
Flight Data Acquisition Unit
General Aviation
Greenwich Mean Time
Ground
Ground Support Equipment
Illustrated Parts List
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23–70–04
Introduction
Rev. 15 Page 1
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
LRU
MTBF
OMS
PC
PCMCIA
PI
PWA
PWR
REC LVL
RIU
ROC
ROSE
RSE
RTCA
RUFS
SMT
TSO
ULB
Line Replaceable Unit
Mean Time Between Failures
Onboard Maintenance System
Personal Computer
Personal Computer Memory Card International Association (now
known as PC Card)
Portable Interface
printed wiring assembly
power
Record Level
Recorder Interface Unit
Read−Out Center
Read Out Support Equipment
Rotor Speed Encoder
Radio Technical Commission for Aeronautics
Recorder USB FDAU Simulator
Surface Mount Technology
Technical Standard Order
Underwater Locator Beacon
3. DOCUMENT REQUIREMENTS
The following equipment and documents are, or may be, required for on-aircraft installation
and check out of the FA2100CVRs:
F
This Component Maintenance Manual.
F
Portable Interface Operator’s Manual, Part Number 165E1630–00
F
Portable Interface/2 Operator’s Manual, Part Number 165E1630–01
F
Installation and Operation Manual, Cockpit Voice Recorder, Model FA2100CVR, Part
Number 165E1846-00.
F
Component Maintenance Manual, ED−56A Control Units, Preamplifier, & Microphone Modules , ATA 23–70–05, Part Number 165E1747-00.
F
FA2100CVR Audio & Data Link Player Software Operator’s Manual, Part Number
165E3596−00.
F
Read−Out Support Equipment/Recorder Interface Software Version 3.0 or 4.0 Operator’s Manual, Part Number 165E1696−02 or−03 .
4. RECORDER DEFINITIONS
The Model FA2100CVR P/N’s: 2100-1010-( ) and 2100-102X-( ) meet the requirements
of ARINC 557/757 with a voice memory storage capacity of 30-minutes and 2-hours, respectively with the exception of 2100−1027−02 meets the ARINC 757A requirement. A
Rotor Speed Encoder (RSE) and Greenwich Mean Time (GMT) interface is provided. For
all part numbers, an On-Board Maintenance (OMS) interface is implemented in hardware,
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23–70–04
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
however only the FA2100CVR P/Ns:2100−1025/1026/1027−XX, supports OMS in software. Only FA2100 CVR P/N: 2100−1025/1026/1027−XX, supports RIPS Monitoring status and Datalink.
5. MAINTENANCE PHILOSOPHY
The Model FA2100 Solid-State CVR Recorder is considered an “ON CONDITION LRU”
and is designed as maintenance-free unit which makes extensive use of surface mount
technology (SMT).
The repair of printed wiring assemblies (PWAs) containing SMT devices requires specialized factory equipment, training, and techniques, therefore, such PWAs are not field-repairable while the unit is under the warranty period. As a result, during the unit’s warranty
period, the FA2100’s CVR maintenance philosophy is replacement of failed level 2 assemblies.
The field replaceable assemblies identified for the FA2100CVR are the Aircraft Interface
PWA, the Audio Compressor PWA, the Acquisition Processor PWA, and the Crash Survivable Memory Unit (CSMU).
When it has been determined that one or more of these assemblies is faulty, the assembly(ies) should be removed and returned to L-3 Aviation Recorders for repair or replacement.
Attempts to repair any discrete components of these assemblies will void the warranty.
6. COMPONENT MAINTENANCE MANUAL (CMM) DESCRIPTION
This CMM consists of a single volume. The manual conforms to the intent and form of Air
Transport Association of America (ATA) Specification 100. The manual is written for an
audience of operators and both intermediate− and depot−Level maintenance technicians.
Functional, electrical and mechanical aspects of the Model FA2100CVR are documented;
that is, description, specifications, operation, testing, removal and replacement, etc. are
contained in this manual. The CMM content is summarized as follows:
A.
FRONT MATTER
Front Matter material consists of a title page, service bulletin list, record of revisions,
record of changes, list of effective pages, table of contents, and this introduction.
B.
DESCRIPTION AND OPERATION
This section contains the description and operation information for the Model
FA2100 Cockpit Voice Recorder. Line art is used to illustrate the unit, its interconnections and functionality. This section also contains the Model FA2100CVR Theory
of Operation.
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23–70–04
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
C.
TESTING AND TROUBLESHOOTING
Sections 100 and 200 contains specific checks and tests required to determine the
operational condition of a unit that has been removed from service. Also included in
the section are tables of required test equipment, test set-up data, procedures, and
test parameters. Troubleshooting data is presented in a tabular form with each
entry related to a specific test and fault isolation task. Fault isolation is provided to a
Level-2 maintenance, or circuit board removal and replacement level.
No calibration of circuit boards within the Model FA2100CVR is required. The Model
FA2100 Solid-State Cockpit Voice Recorder is considered an “ON CONDITION
LRU”.
D.
DISASSEMBLY
This section provides all the information required to completely disassemble the
FA2100CVR to its Lowest Replaceable Unit (LRU) defined by the maintenance philosophy as the circuit board assemblies. The steps of each procedure are coordinated with the TESTING AND TROUBLESHOOTING Section. Access to subassemblies within the FA2100CVR is described such that there is minimal disturbance to
other subassemblies.
Each major disassembly task is accompanied with a line art exploded-view of the
subassembly area which is cross referenced to the applicable Illustrated Parts List
(IPL) drawing for ordering replacement parts.
E.
CLEANING
This section contains a listing of all required cleaning materials, procedures for
cleaning material use, and applicable warnings and cautions related to the use of
prescribed cleaning solvents.
F.
CHECK
This section contains the check procedures that may be required during shop maintenance. It covers Mechanical Inspection, Electrical Inspection and ULD Inspection
procedures.
G.
REPAIR
This section contains the Model FA2100CVR maintenance philosophy, which provides for Level-2 removal and replacement of failed circuit board assemblies only.
H.
ASSEMBLY
This section contains detailed step-by-step procedures describing the complete assembly of the Model FA2100 Solid-State Cockpit Voice Recorder. Each major as-
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23–70–04
Introduction
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Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
sembly procedure is accompanied with a line art exploded-view of the subassembly
area which is cross referenced to the applicable Illustrated Parts List (IPL) drawing
for ordering replacement parts.
I.
SPECIAL TOOLS AND TEST FIXTURES
This section provides a listing of all required tools, fixtures, and equipment which are
not common maintenance tools. It also provides a description of the Portable Interface (PI) used to download voice data from the recorder. It also provides a description of the Read−Out Center (ROC)/CVR Automated Test Station (CATS) as used
with the Recorder Interface Unit (RIU) to test and download from the FA2100CVR.
J.
ILLUSTRATED PARTS LIST
This section contains parts location diagrams and parts listings for all versions of the
Model FA2100 CVR, p/n: 2100-1010-( ) (30-minute) and p/n: 2100-102X-( )
(2-hour) currently produced.
7. DOCUMENT VERIFICATION
All CMM drawings, illustrations, wiring diagrams, and block diagrams were validated
against existing engineering source material. All Testing & Fault Isolation, Disassembly
and Assembly procedures have been verified against the actual performance of the unit
under test conditions as indicated in Table 1 below.
Table 1 identifies the sections of the CMM that underwent a Shop Verification process
and the date of the verification. In addition, a Component Maintenance Manual Verification Report that identifies the technician who performed the procedure and Engineer/
Technical Writer who verified the procedure along with a Quality Assurance Engineer approval signature is kept on file with the CMM sign off release form. For a copy of the
Component Maintenance Manual Verification Report for this version of the CMM, please
address inquiries to the following:
L-3 Aviation Recorders Publications
100 Cattlemen Rd.
Sarasota, Florida 34230
Phone: (941) 371–0811
FAX: (941) 377–5591
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23–70–04
Introduction
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Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
Table 1. Shop Verification
Procedure
Chapter
Date of Verification
Testing & Fault Isolation
100
Mar. 25/13
Automatic Testing
200
Mar. 25/13
Disassembly
300
Mar. 18/13
Assembly
700
Mar. 18/13
Note:
Contact L-3 Aviation Recorders, to verify this date sensitive information
when using this manual to develop other documentation. The L−3AR Publication index may be located at www.L−3.com or L−3ar.net.
8. COMPONENT MAINTENANCE MANUAL (CMM) EFFECTIVITY
Effectivity of the CMM is based on effectivity dates and product serial number. Effectivity
of the manual is identified by a list of effective pages in the front of the manual.
9. PART NUMBER FORMATTING
L−3AR does not delineate its part numbers by special characters, such as the “−” dash
character. L−3AR considers its part numbers with or without the use of special characters
to be the same, for example, there is no difference between part number 266−E0305−00,
266E0305−00, or 266E030500. To be in compliance with ARINC Specifications 100 and
200 the part numbers listed in this manual use the following format: 266E0305−00.
L−3AR typically identifies its part numbers on other documents such as internal engineering drawings, purchase orders, component labels, shipping orders, Form 8130’s, and certification documents with the format: 266−E0305−00.
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23–70–04
Introduction
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Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
DESCRIPTION AND OPERATION
1. GENERAL
This Component Maintenance Manual describes the Model FA2100/757A, Cockpit Voice
Recorder, FA2100CVR, p/n’s: 2100-1010-( ), 2100-102X-( ), and 2100-122X-( ). The
FA2100CVR is a highly reliable recorder that is designed to meet the performance requirements of ED-56A or ED−112 and to accept requirements of ARINC 557/757A Characteristics including Rotor Speed Encoder (RSE) and Greenwich Mean Time (GMT) interface. The FA2100 CVR recorder is designed as a maintenance free recorder. There is no
periodic or scheduled maintenance required for this recorder. It is considered an “install
and forget it box.”
NOTE:
The CVDR has a time−in−can circuit that is used to date/
time stamp the downloaded voice or flight data files. This
is not a function of the readout time displayed for voice or
data. The GMT inputs are the true time of the recording.
Data can also be displayed during readout as relative time,
based on file size.
If the file date time stamp is not displaying the proper time
of the download, this is not a fault condition that will impede the normal recording operation of the recorder. The
unit should not be pulled from service for a faulty time in a
can date/time stamp error. This condition should be noted
and fixed at the next shop visit.
The FA2100CVR Recorder is an ARINC 404, 1/2 ATR short box which performs the cockpit voice recorder function of an ED-56A, or in the case of 2100−1X25/1X27−XX, ED112,
compliant Recorder. The FA2100CVR uses solid state Flash Memory technology as the
recording medium with two recording capabilities available p/n: 2100-1010-( ) for 30-minutes, or p/n: 2100-1X2X-( ) for 2-hours.
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23–70–04
Description and Operation
Rev. 15 Page 1
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
HARDWARE AND
SOFTWARE
MODIFICATIONS
CSMU
ULD
GSE CONNECTOR
(BEHIND DUST COVER)
Figure 1.
Model FA2100 Cockpit Voice Recorder (FA2100CVR)
2. FA2100 CONFIGURATIONS
The current configurations of the FA2100CVR’s are listed in Table 2 below, and with its
specific part number in the IPL Section Figure 1, Item 1A through Item 1AB.
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23–70–04
Description and Operation
Rev. 15 Page 2
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
Table 2. FA2100 CVR Descriptions
Part Number
Description
Weight!
(lbs)
Figure
Reference
2100-1010-00
ARINC 757, 30 MIN. CVR, 1/2 ATR SHORT *
10.0.5
Figure 1
2100-1010-50
ARINC 757, 30 MIN. GA CVR, 1/2 ATR SHORT, 28 VDC ONLY *
9.5.5
Figure 1
2100-1010-51
ARINC 757, 30 MIN. GA CVR, 1/2 ATR SHORT, TITANIUM
CSMU W/ RTV, 28 VDC ONLY *
7.7.5
Figure 1
2100-1020-00
ARINC 757, 2−HR. CVR, 1/2 ATR SHORT
10.6 max.
Figure 1
2100-1020-02
ARINC 757, 2−HR. CVR W/ FSK
10.6 max.
Figure 1
2100-1020-50
ARINC 757, 2−HR. GA CVR, 1/2 ATR SHORT, 28 VDC ONLY *
9.5.5
Figure 1
2100-1020-51
ARINC 757, 2−HR. GA CVR, 1/2 ATR SHORT, TITANIUM CSMU
W/ RTV, 28 VDC ONLY
8.3 max.
Figure 1
2100-1025-02
ARINC 757, 2−HR. CVR W/ OMS, 4 CHANNEL HIGH QUALITY
10.6 max.
Figure 1
2100-1025-12
ARINC 757, 2−HR. CVR W/ OMS, 4 CHANNEL HIGH QUALITY
(CYRILLIC)
10.6 max.
Figure 1
2100-1025-22
ARINC 757, 2−HR. CVR W/ OMS, 4 CHANNEL HIGH QUALITY
W/ RIPS
10.6 max.
Figure 1
2100-1025-24
ARINC 757, 2−HR. CVR W/ OMS, 4 CHANNEL HIGH QUALITY
W/ RIPS S/W
10.6 max.
Figure 1
2100-1026-02
ARINC 757, 2−HR. CVR W/ OMS, 4 CHANNEL HIGH QUALITY
W/ RIPS
10.6 max.
Figure 1
2100-1027-02
ARINC 757, 2−HR. CVR W/ OMS, 4 CHANNEL HIGH QUALITY
W/ RIPS
10.6 max.
Figure 1
2100-1220-00
ARINC 757, 2−HR. CVR, 1/2 ATR SHORT, 90−DAY BEACON
10.6 max.
Figure 1
2100-1220-02
ARINC 757, 2−HR. CVR W/ FSK, 90−DAY BEACON
10.6 max.
Figure 1
2100-1225-22
ARINC 757, 2−HR. CVR W/ OMS, 4 CHANNEL HIGH QUALITY
W/ RIPS, 90−DAY BEACON
10.6 max.
Figure 1
2100-1225-24
ARINC 757, 2−HR. CVR W/ OMS, 4 CHANNEL HIGH QUALITY
W/ RIPS S/W, 90−DAY BEACON
10.6 max.
Figure 1
2100-1226-02
ARINC 757, 2−HR. CVR W/ OMS, 4 CHANNEL HIGH QUALITY
W/ RIPS, 90−DAY BEACON
10.1.5
Figure 1
2100-1227-02
ARINC 757, 2−HR. CVR W/ OMS, 4 CHANNEL HIGH QUALITY
W/ RIPS, 90−DAY BEACON
10.1.5
Figure 1
2100-1925-22
ARINC 757, 2−HR. CVR W/ OMS, 4 CHANNEL HIGH QUALITY,
90−DAY BEACON
10.6 max.
Figure 1
* Obsolete models.
The standard configurations provide for a 600−ohm audio output monitor to an associated
Control.
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23–70–04
Description and Operation
Rev. 15 Page 3
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
3. SYSTEM DESCRIPTION
Refer to Figure 2. The Model FA2100 Cockpit Voice Recorder System consists of the recorder and an externally mounted control unit or externally mounted preamplifier with remote microphone. Interconnection between the recorder and the control unit is accomplished using aircraft wiring. The FA2100 CVR is connected to the aircraft wiring via a
57-pin, DPXB-style connector. The Aircraft Interface PWA provides for all input and output signals.
The Model FA2100CVR is housed in a 1/2-ATR, Short, ARINC 404A-style case. It has an
aluminum chassis cover painted international orange with two reflective stripes located on
a stainless steel or titanium Crash Survivable Memory Unit (CSMU). The recorder weighs
a maximum of 10.6-pounds with an underwater locator device mounted on the front of the
CSMU. The FA2100CVR does not require external shock mounting.
The Model FA2100CVR consists of an Underwater Locating Device, chassis and front
panel, four internal level-2 replaceable assemblies: the Aircraft Interface PWA, Audio
Compressor PWA, Acquisition Processor PWA, and the Crash Survivable Memory Unit
(CSMU) which contains the solid-state flash memory used as the recording medium.
A.
Underwater Acoustic Beacon
The Model FA2100 FDR has an underwater acoustic beacon mount located on its front
panel which also acts as the recorders carrying handle. The ULB mount will accept either a 30−day or a 90−day underwater locator beacon. The ULB meets or exceeds the
requirements of the Federal Aviation Administration technical standard order TSOC121 for 30−day beacons, or TSO−C121b for 90−day beacons.
FAA TSO−C121 will be revoked as of March 1, 2015. After this date, the manufacture of
30−day beacons in accordance with TSO−C121 will be prohibited. 30−day beacons already in service may still be used, and a kit is available for battery replacement. A
90−day beacon conversion kit is also available for the retrofit of a 90 day beacon to an
existing recorder. All new recorder production will incorporate the 90−day underwater
locator beacon.
The beacon is located on the front panel for ease of reading the battery replacement
date and for quick removal and replacement of the beacon. The ULB is equipped
with a battery that has an expected life of six years. The ULB requires cleaning and
functional testing every 24−months. The batteries in the beacons are field serviceable and and may be ordered from L−3AR.
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Description and Operation
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Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
B.
Circuit Boards
The FA2100CVR electronics contain all the necessary power supplies and circuitry
to input, record, monitor and playback data. In addition, circuitry to perform self–
test functions and provide signals to the appropriate status indicators is also integrated into the FA2100CVR electronics. The removable circuit boards include the
Aircraft Interface PWA, Audio Compressor PWA, and Acquisition Processor PWA.
C.
Power, Control and Monitor Signal Interface Characteristics
Input power may be 115 Vac, 400 Hz or 28 Vdc (PN 2100−10X0−5X units are 28
Vdc only). At normal power level, an interruption equal to or less than 200 milliseconds will not affect the Model FA2100CVR’s function. Upon application or re-application, or normal, abnormal, or emergency power, the FA2100CVR will begin storing data in memory within 250 milliseconds.
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23–70–04
Description and Operation
Rev. 15 Page 5
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
COCKPIT
AREA
MICROPHONE
(CAM)
*
MONITOR
AUDIO TO
HEADSET
JACK
ERASE A
ERASE C
CONTROL
UNIT
AIRCRAFT WIRING INTERLOCKS
(LANDING GEAR MUST BE DOWN
AND BRAKE LOCKED TO ALLOW
MEMORY TO BE ERASED)
PUSH TO TEST
GEAR
AREA MICROPHONE
BRAKE
+18 VDC
OPERATING
POWER
28 VDC OR 115 VAC 400 Hz
2
RECORD ON
+5 V FOR
LIGHTED PANEL
CHANNEL 4
2
CHANNEL 3
PILOT AUDIO
FA2100 CVR
AUDIO OUT
2
2
CHANNEL 2
CO‐PILOT AUDIO
+18 VDC
2
SPARE AUDIO
(TO 3RD CREW MEMBER
OR PA SYSTEM)
2
CHANNEL 1
TEST INDICATOR
2
2
GMT_IN_B (429)
AIRCRAFT
INTERFACE
PWA
GMT_IN_A (429)
ROTOR_SPEED_IN_HI
ROTOR_SPEED_IN_LO
**OMS IN A
**OMS IN B
**DATA LINK IN A 429
**DATA LINK IN B 429
***RIPS FAULT INPUT
***RIPS MAINTENANCE INPUT
***RIPS PRESENT INPUT
STOP RECORDING/
***RIPS ACTIVE INPUT
CHASSIS
GROUND
* S055 Mics have 4 Lines to the C.U.
CVR FAULT
TO AIRCRAFT
FAULT MONITORING
SYSTEM
**OMS OUTPUT A 429
**OMS OUTPUT B 429
**DATA LINK VALID
AUDIO
COMPRESSOR
PWA
ACQUISITION
PROCESSOR
PWA
GSE OUTPUT
TO GROUND STATION
TEST EQUIPMENT
S056 MICS have 3 Lines to the C.U.
For GA versions refer to Figure 4.
** OMS & Data Link are applicable to the
2100‐1025‐XX, ‐1026‐XX, and ‐1027‐XX only.
*** RIPS Status Monitoring. 2100-1025-22/-24
CSMU
(Crash Survivable Memory Unit)
ASSEMBLY
(CRASH PROTECTED SOLID STATE MEMORY)
& 2100-1026-XX only.
Figure 2. Model FA2100 CVR, (2100‐1010‐00, 2100‐1X20‐00/02, 2100‐1X25‐XX,
2100‐1X26‐XX and 2100‐1X27‐XX) Functional System Block Diagram
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23–70–04
Description and Operation
Rev. 15 Page 6
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
2
ERASE A
ERASE C
AIRCRAFT WIRING INTERLOCKS
(LANDING GEAR MUST BE DOWN
AND BRAKE LOCKED TO ALLOW
MEMORY TO BE ERASED)
PUSH TO TEST
GEAR
COCKPIT
AREA
MICROPHONE
(CAM)
BRAKE
3
3
RECORD ON
CHANNEL 4
FA2100 GACVR
3
CHANNEL 3
PILOT AUDIO
AUDIO OUT
2
2
CHANNEL 2
CO‐PILOT AUDIO
2
SPARE AUDIO
(TO 3RD CREW MEMBER
OR PA SYSTEM)
TEST INDICATOR
CHANNEL 1
2
2
CVR FAULT
AIRCRAFT
INTERFACE
PWA
GMT_IN_B (429)
GMT_IN_A (429)
ROTOR_SPEED_IN_HI
TO AIRCRAFT
FAULT MONITORING
SYSTEM
ROTOR_SPEED_IN_LO
(Input Z = 100 Kohms)
1
28 VDC
ATTENUATION
4
STOP
RECORDING
CHASSIS
GROUND
1
2
All GACVR's operate only with a
28Vdc input source.
Used for GA versions only. The GA versions do not use a
control unit; however, the other input and output signals indi­
cated are still utilized allowing for an optional customer fur­
nished control panel.
AUDIO
COMPRESSOR
PWA
ACQUISITION
PROCESSOR
PWA
CSMU
(Crash Survivable Memory Unit)
ASSEMBLY
(CRASH PROTECTED SOLID STATE MEMORY)
GSE OUTPUT
3
TO GROUND STATION
TEST EQUIPMENT
All GACVR's only use
the Model S056 Remote Mic.
Figure 3. Model FA2100 GACVR (2100‐1010‐50/‐51 and 2100‐1020‐50/‐51)
Functional System Block Diagram
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23–70–04
Description and Operation
Rev. 15 Page 7
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
(1)
Stop Recording Command
Assertion of the “Stop Recording” command stops the FA2100 CVR recording within
ten minutes. Removal of the “Stop Recording” command or “Push-To-Test” resumes
the recording. If the recording is resumed due to the “Push-To-Test” function being
activated, the recording will again cease within 10 minutes if the “Stop Recording”
signal is still active.
(2)
Control Unit Operating Power and Monitor Audio Signals
The FA2100 CVR provides the control unit with +18 Vdc operating power, monitor
audio to the headset jack, and a TEST indicator signal.
Refer to Figure 4, an Audio Output channel for test monitoring provides a combination of four High Quality (for 30-minute recorders) or two Standard Quality (for
120-minute recorders and 2100−1020−XX pre MOD−DOT #7) or four High Quality
(for P/N: 2100−1X25/1X26/1X27−XX and 2100−1X20−XX MOD−DOT #7) reprocessed ADPCM data channels. This monitored Audio Output signal is accessible at
the front panel of the control unit via a 600-ohm headset. The monitor audio signal
has a reference input level of 2.55 Vrms into 600 ohms applied to one input channel.
In the 2100-1010-( ), 30-minute recorders, the monitored Audio Output signal to the
control unit is developed by summing together the High Quality Voice for Channels
1, 2, 3, and the Cockpit Area Microphone (CAM) Channel 4. In the 2100-1020-( )
pre MOD−DOT #7, 120-minute recorders, the Audio Output signal consists of the
same High Quality Voice and CAM channels and Test signal as found in the 30-minute recorder, in addition to a Standard Quality Voice and Standard Quality CAM output for up to 120 minutes. In the 2100−1X25/1X26/1X27−( ) and 2100−1X20−( )
MOD−DOT #7 the monitored audio is a combination of Channel 1 through Channel 4
High Quality audio. There are no Standard Quality audio channels in the full 2−hour
High Quality Recorder. This monitored Audio Output is the Adaptive Differential
Pulse Code Modulated (ADPCM) digital data which is reprocessed back to PCM and
converted from digital to analog audio prior to being recorded into flash memory. It
should not to be confused with the downloaded digital audio retrieved from memory
with the Portable Interface Unit, from the front panel ATE connector.
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23–70–04
Description and Operation
Rev. 15 Page 8
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
3rd Crew Member/
Spare Audio
CH 1
CH 1 (HQ)
(150‐3500 Hz)
Co‐Pilot Audio
CH 2
HQ CH1 ,
HQ CH2,
HQ CH3 ,
HQ CAM
CH 2 (HQ)
(150‐3500 Hz)
Pilot Audio
CH 3

CH 3 (HQ)
(150‐3500 Hz)
Cockpit Area Mic
(CAM) Audio CH 4
AUDIO OUT
TO
CONTROL UNIT
HEADSET JACK
ERASE
CH 4 (HQ)
(150‐6000 Hz)
PUSH‐TO‐TEST
620 Hz - 660 Hz
BULK ERASE
400 Hz
ERASE “A” + “C”
FA2100 CVR
P/N 2100–1010–XX, 30‐Minute Audio Monitor Scheme
CH1 (SQ)
CH2 (SQ)
CH3 (SQ)

SQV
CAM (SQ)
3rd Crew Member/
Spare Audio
CH 1
Co‐Pilot Audio
CH 2
Pilot Audio
CH 3
Cockpit Area Mic
(CAM) Audio CH 4
PUSH‐TO‐TEST
CH 1
(150‐3500 Hz)
CH1 (HQ)
CH 2 (HQ)
(150‐3500 Hz)
CH 2 (HQ)
CH 3 (HQ)
(150‐3500 Hz)
CH 3 (HQ)
CH 4 (HQ)
(150‐6000 Hz)

SQV
SQC
HQ CH1 ,
HQ CH2,
HQ CH3 ,
HQ CAM
TEST
AUDIO OUT
TO
CONTROL UNIT
HEADSET JACK
ERASE
CAM (HQ)
620 Hz - 660 Hz
BULK ERASE
400 Hz
ERASE “A” + “C”
FA2100 CVR
P/N 2100-1020-XX, 120‐Minute (pre MOD-DOT #7) Audio Monitor Scheme
Legend:
CAM – Cockpit Area Microphone
CH – Channel
HQ – High Quality
SQ – Standard Quality
Figure 4. (Sheet 1 of 2)
Model FA2100 CVR, 30‐Minute and 120‐Minute Audio Monitor Schemes
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Description and Operation
Rev. 15 Page 9
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
3rd Crew Member/
Spare Audio
CH 1
Co‐Pilot Audio
CH 2
Pilot Audio
CH 3
Cockpit Area Mic
(CAM) Audio CH 4
PUSH‐TO‐TEST
CH 1
(150‐3500 Hz)
CH1 (HQ)
CH 2 (HQ)
(150‐3500 Hz)
CH 2 (HQ)
CH 3 (HQ)
(150‐3500 Hz)
CH 3 (HQ)
CH 4 (HQ)
(150‐6000 Hz)
HQ CH1 ,
HQ CH2,
HQ CH3 ,
HQ CAM

TEST
AUDIO OUT
TO
CONTROL UNIT
HEADSET JACK
ERASE
CAM (HQ)
620 Hz - 660 Hz
BULK ERASE
400 Hz
ERASE “A” + “C”
FA2100 CVR
P/N 2100-1X25/1X26/1X27-XX and 2100-1X20-XX (MOD-DOT #7)
120‐Minute Audio Monitor Scheme
Legend:
CAM – Cockpit Area Microphone
CH – Channel
HQ – High Quality
Figure 4. (Sheet 2 of 2)
Model FA2100 CVR, 30‐Minute and 120‐Minute Audio Monitor Schemes
(3)
Control Unit Test and Bulk Erase Signals
The indicator signal is used to drive the TEST indicator in the Model S151/S161,
Model S152/S162, and Model S251/S261 Control Units. Refer to the Component
Maintenance Manual, ED−56A Control Units, Preamplifier, & Microphone Modules ,
ATA 23–70–05, Part Number 165E1747-00. The +18 Vdc is a short-circuit protected
30 mA line.
All control units provide the FA2100 CVR with three control signals: Erase “A”, Erase
“C”, and Push-To-Test. The Erase “A” and Erase “C” signals are used to initiate a
bulk erasure of the crash protected solid-state memory. The ERASE pushbutton
must be pressed for more than two seconds and then released to initiate the bulk
erase function. Landing gear and brake interlocks are provided in the aircraft wiring
to prevent memory erasures during flight conditions.
The Bulk Erase function will not be activated if Voice Erase “A” is grounded or connected to Voice Erase “C” for 0.5 seconds or less. The function will be activated if
Voice Erase “A” is connected to Voice Erase “C” for 2 seconds or more then
grounded.
The Push-To-Test signal is activated when the TEST pushbutton on the associated
control unit is pressed. During this time, a 620 Hz to 660 Hz signal is generated
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23–70–04
Description and Operation
Rev. 15 Page 10
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
within the FA2100 which is used to test the circuitry of all the audio channels. In a
successful test, the FA2100 Recorder provides a TEST INDICATOR signal which
lights the green TEST indicator mounted on the front panel of the S151/S161,
S152/S162, and S251/261 Control Units.
D.
NOTE:
For all P/N: 2100−1025−02/−22/−24, 2100−1X26−02,
2100−1X27−02, no test tone will be heard and the Monitor
Output will be muted during the test. After the test, if the
−Test Good− tone is not heard, then the 2100CVR has failed
and the test. Monitor Output will resumes in both a passed
and failed test.
NOTE:
The Model 2100−1X25−XX, when used with the S161−1390−01
Control Unit, does not have a LED test indicator present. However, the audible test tone is still present.
Voice Data Interface Characteristics
The FA2100 CVR is used in an ARINC 557/757A configuration, with interface to the aircraft provided through a 57-pin DPXB rear panel connector. The Reference Signal, as
required by ED-56A & ED−112, is defined as an input signal with a frequency of 1 kHz at
an input level of 3 Vrms for Channels 1, 2, and 3, and 2 Vrms for Channel 4. The Audio
input sensitivity level is .05 Vrms − 3 Vrms for Channels 1, 2, and 3, and .02 − 2 Vrms for
Channel 4.
The Model FA2100 CVR provides for four audio inputs which are connected as follows:
Channel 1 – Cockpit Spare Audio Input (3rd crew member − CAA)
Channel 2 – Co-Pilot’s Audio, Boom, Mask, and Hand-Held Microphone Input
Channel 3 – Pilot’s Audio, Boom, Mask and Hand-Held Microphone Input
Channel 4 – Cockpit Area Microphone (CAM) Input
These audio signals are applied through the rear connector to the Aircraft Interface
PWA, then are digitally converted into 16−Bit words, compressed and stored in
memory. Refer to Paragraph 5 for detailed pin-outs of the rear interface connector.
In the −02 FSK version of the FA2100 CVR, CH 1 or CH 3 may have an FSK GMT
input applied along with the standard audio signal.
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23–70–04
Description and Operation
Rev. 15 Page 11
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
E.
Data Recording Storage
Refer to Figure 5 for a diagram of the FA2100CVR recording schemes used in the
30-minute and 120-minute recorders and Table 1 for a breakdown of the recording
durations for each of the High Quality and Standard Quality combined channels.
The audio received from the cockpit area microphone (CAM) is applied to the CAM
input channel (CH4). The recorded CAM audio has a bandwidth of 150 to 6000
Hertz. The other three channels receive audio from the pilot audio selectors and
have a bandwidth of 150 to 3500 Hertz. The spare audio input applied to Channel 1
may be from a third crew member or PA system.
The four audio input signals are applied to separate input circuits located on the Audio Compressor PWA for amplification and shaping with equalization performed as
necessary. These four streams are then converted to a digital pulse code modulation (PCM) 16-Bit word format on the Audio Compressor PWA and then routed to the
Acquisition Processor PWA. The PCM data for each channel is then encoded for
storage using an adaptive differential pulse code modulation (ADPCM) processor.
These four streams are recorded as high quality (HQ) audio for a 30-minute duration. In the case of P/N: 2100−1X25/1X26/1X27−XX and 2100−1X20−XX MOD−
DOT #7, these HQ Channels are recorded for 120−minutes. The rate of the data
stream recorded varies with the type of audio as follows:
F
24 kbps for CH 1, 2, and 3 HQV
F
48 kbps for CH 4 HQC
In the 120−minute FA2100CVR (2100−1020−XX pre MOD−DOT #7), three of these
audio streams (pilot, co-pilot, and spare CH1, 2, and 3) are combined to provide a
fifth audio stream, designated Standard Quality Voice (SQV), to be recorded in standard quality audio. In the 120-minute FA2100CVR version (2100−1020−XX pre
MOD−DOT #7), a sixth audio stream is formed using using the Standard Quality
Cockpit Area Microphone (SQC) input. All six digital-encoded ADPCM signals are
applied to the CSMU for storage in the solid-state flash memory. In this case, the
rate of the data stream recorded varies with the type of audio as follows:
F
24 kbps for CH 1, 2, and 3 HQV
F
48 kbps for CH 4 HQC (CAM)
F
16 kbps for SQV and SQC (CAM)
In both versions of the Model FA2100CVR, the four primary audio streams are always recorded as high quality audio (HQV) for 30 minutes. In the 120-minute Model
(2100−1020−XX pre MOD−DOT #7), the Standard Quality Voice (SQV) and Cockpit
Area Microphone channels (SQC) are recorded for a minimum of 120 minutes.
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23–70–04
Description and Operation
Rev. 15 Page 12
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
(CSMU)
FLASH MEMORY
3rd Crew Member/
Spare Audio
CH1
CH 1 (HQV)
(150‐3500 Hz)
Co‐Pilot Audio
CH2
CH 2 (HQV)
(150‐3500 Hz)
Pilot Audio
CH3
CH 3 (HQV)
(150‐3500 Hz)
CH 1 (24 kbps)
30 minutes
CH 2 (24 kbps)
30 minutes
CH 3 (24 kbps)
30 minutes
CH 4 (HQC)
(150‐6000 Hz)
Cockpit Area Mic
(CAM) Audio CH 4
CH 4 (48 kbps)
30 minutes
Low Speed
ARINC 429 GMT
(12.5 kbps)
429 GMT
Time Code
GMT
(2 Wds per 1 Sec.)
RSE
(7‐6000 Hz)
Rotor Speed
RSE
(2 Wds per 1/2 Sec
FA2100 CVR
P/N 2100–1010–XX, 30‐Minute Recording Scheme
(CSMU)
FLASH MEMORY
3rd Crew Member/
Spare Audio
CH1
CH 1 (HQV)
(150‐3500 Hz)
Co‐Pilot Audio
CH2
CH 2 (HQV)
(150‐3500 Hz)
Pilot Audio
CH3
CH 3 (HQV)
(150‐3500 Hz)
Cockpit Area Mic
(CAM) Audio CH 4
CH 1 (24 kbps)
30 minutes
CH 2 (24 kbps)
30 minutes
CH 3 (24 kbps)
30 minutes
CH 4 (HQC)
(150‐6000 Hz)
CH 4 (48 kbps)
30 minutes

429 GMT
Time Code
CH1 + CH2
+ CH3
Low Speed
ARINC 429 GMT
(12.5 kbps)
GMT
(2 Wds per 1 Sec.)
120 minutes
RSE
(7‐6000 Hz)
Rotor Speed
Internal Channel (SQV)
(16 kbps)
120 minutes
RSE
(2 Wds per 1/2 Sec)
120 minutes
CAM
FA2100 CVR
Internal Channel (SQC)
(16 kbps)
120 minutes
P/N 2100-1020-XX (pre MOD-DOT #7) 120‐Minute Recording Scheme
Legend:
CAM – Cockpit Area Microphone
CH – Channel
HQ – High Quality
SQ – Standard Quality
Figure 5. (Sheet 1 of 2)
Model FA2100 CVR, 30-Minute and 120-Minute Recording Schemes
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23–70–04
Description and Operation
Rev. 15 Page 13
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
(CSMU)
FLASH MEMORY
3rd Crew Member/
Spare Audio
CH1
CH 1 (HQV)
(150‐3500 Hz)
Co‐Pilot Audio
CH2
CH 2 (HQV)
(150‐3500 Hz)
Pilot Audio
CH3
CH 3 (HQV)
(150‐3500 Hz)
Cockpit Area Mic
(CAM) Audio CH 4
429 GMT
Time Code
Rotor Speed
CH 4 (HQC)
(150‐6000 Hz)
Low Speed
ARINC 429 GMT
(12.5 kbps)
RSE
(7‐6000 Hz)
CH 1 (24 kbps)
120 minutes
CH 2 (24 kbps)
120 minutes
CH 3 (24 kbps)
120 minutes
CH 4 (48 kbps)
120 minutes
GMT
(2 Wds per 1 Sec.)
120 minutes
RSE
(2 Wds per 1/2 Sec)
120 minutes
Data Link*
Data Link
120 minutes
OMS*
OMS
120 minutes
FA2100 CVR
P/N 2100-1X25/1X26/1X27-XX and 1200-1X20-XX (MOD-DOT #7)
120‐Minute Recording Scheme
Legend:
CAM – Cockpit Area Microphone
CH – Channel
HQ – High Quality
OMS − On board Maintenance System*
* P/N 2100−1025/1026−XX only
Figure 5. (Sheet 2 of 2)
Model FA2100 CVR, 30-Minute and 120-Minute Recording Schemes
(1)
Output Audio Quality
The FA2100CVR’s audio quality meets or exceeds the audio quality specified in
Chapter 3 of ED–56A and Part I of ED−112. Specifically, the Reference Signal is
1-kHz at 3 Vrms for the voice channels, and 1-kHz at 2 Vrms for the CAM channel.
The signal-to-noise plus distortion ratio (SINAD) of this signal when reproduced exceeds 24 dB (6 percent distortion) for the most recent 30 minutes of recording and
exceeds 20 dB (10 percent distortion) otherwise.
NOTE:
Refer to Table 3.1 of ED–56A and I−3.1 of ED−112 for other
applicable audio quality specifications including the
Speech Transmission Index requirement for various channels and segments of recording.
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23–70–04
Description and Operation
Rev. 15 Page 14
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
Table 1
Model FA2100 CVR Recording Specifications
Cockpit Audio Inputs
Model FA2100
Part Number
Channel 1
Channel 2
Combined Channels
Channel 3
Channel 4
Combined
Audio SQ
CAM–SQ
3rd Crew
Member/
Spare Audio
Input for
High Quality
Recording
Co-Pilot
Audio Input
for High
Quality
Recording
Pilot Audio
Input for
High Quality
Recording
Cockpit Area
Microphone
(CAM) Input
for High
Quality
Recording
Summation of
CH 1, 2, & 3
audio inputs
for Standard
Quality
Recording
Standard
Quality
Recording of
Cockpit Area
Microphone
(CAM) (CH 4)
Input
2100–1010–XX
30 minutes
30 minutes
30 minutes
30 minutes
Not available
Not available
2100–1020–XX
pre MOD−DOT #
7
30 minutes
30 minutes
30 minutes
30 minutes
120 minutes
120 minutes
2100–1X20–XX
MOD−DOT # 7
120 minutes
120 minutes
120 minutes
120 minutes
Not available
Not available
2100–1X25–XX
2100–1X26–XX
2100–1X27–XX
120 minutes
120 minutes
120 minutes
120 minutes
Not available
Not available
NOTE: All of the times indicated in the above chart are minimum recording times.
(2)
GMT/FSK Output Signals
In addition to the voice channel inputs, in the 2100−1010−( ) and 2100−1X2X−( )
configurations, GMT is applied as low speed (12.5 kbps) ARINC-429 to pins 25 and
26; with the exception of 2100−1X20−02 configurations (FSK option). In the
2100−1X20−02 version, GMT may either be applied as low speed ARINC 429, or alternatively as an FSK signal combined with the audio input on either Channel 1 or
Channel 3.
(3)
Rotor Speed Signals
Rotor Speed Encoded (RSE) input signals are applied to the rear connector pins 48
and 49 as an analog frequency varying between 7−6000 Hz. The input impedance
of the RSE signal is 100 Kohms. The GMT/RSE input signals are then digitally converted and compressed in the Acquisition Processor PWA. This data is then stored
in a memory partition separate from the Audio data. In the case of the 30-minute
Model FA2100 CVR, p/n: 2100–1010–( ), 30 minutes of GMT/RSE data is stored. In
the case of the 120-minute Model FA2100 CVR, p/n: 2100–1X2X–( ), a full 120 minutes of GMT/RSE data is stored.
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23–70–04
Description and Operation
Rev. 15 Page 15
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
The Rotor Speed input is recorded as two words every 1/2 second. Rotor Speed
Word 1 (8-bits) provides the number of 400-Hz reference pulses counted during the
sample period. Word 2 (12-bits) contains the integer number of rotor pulse cycles
counted during the sample period. The average rotor pulse frequency is determined
from the word values with better than 1% accuracy using the following formula:
Rotor Pulse Frequency = (400 Hz) x (Rotor Pulse Count) / (Reference Count),
or Rotor Pulse Frequency = 400 x Word 2 / Word 1.
For displaying rotor speed the user must be able to select the display to be frequency or calculated revolutions per minute (RPM). To allow the conversion from frequency to RPM the user must provide a matching frequency to RPM ratio. For example,
6 kHz = 300 RPM. To determine the calculated RPM use the following formula:
RPM = Rotor Pulse Frequency x (Rotor RPM/Tach Frequency).
In the case of helicopter installations of the FA2100CVR, the Bulk Erase function is
inhibited until the rotors stop.
(4)
On board Maintenance System (OMS)
The OMS input signals are applied to the rear connector pins 39 and 40 as a low
speed ARINC 429 signal. The OMS output signal is sent out on pins 50 and 51 as a
high speed ARINC 429 signal, along with the Data Link output signal. The Recorder
records the FA2100 CVR OMS status word only, but is also used to send status
messages to the aircraft’s OMS computer.
Basically, there are two modes for sending messages to the OMS computer, Normal
and Interactive. When the aircraft’s recorder is in Normal mode, the CVR sends a
status message to the OMS computer four times per second. When the recorder is
in Interactive mode, the OMS computer can request the status of the recorder
through a series of menus. The OMS feature can be found on the FA2100 CVR p/n:
2100−1X25/1X26/1X27−( ) only.
(5)
Data Link
The Data Link input signals are applied to the rear connector pins 33 and 34 as a
high speed ARINC 429 signal. The Data Link output signal is sent out on pins 50
and 51 as a high speed ARINC 429 signal, along with the OMS output signal. The
Data Link Valid input signal is applied to pin 56. The Data Link Valid input signal notifies the recorder to expect Data Link input signals.
When the Data Link system is energized, it sends an Aloha response message to
the recorder. If the recorder is in place and operational, the recorder records the
Aloha response message and returns a response message to inform the Data Link
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23–70–04
Description and Operation
Rev. 15 Page 16
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
system that the recorder is in place and operational. Once the Data Link system receives a response from the recorder, it will send all messages received by the Data
Link system to the recorder to be stored in the CSMU. If the recorder is not in
installed or not operational, the Data Link system will continue to send Aloha messages until the recorder’s status changes. The Data Link feature can be found on
the FA2100 CVR p/n: 2100−1X25/1X26/1X27−( ) only. For p/n
2100−1X25/1X26/1X27−XX CVRs, the Audio and Data Link Playback (ADPL) software may be used to download and analyze the audio data. Refer to the
FA2100CVR Audio and Data Link Player Software Operator’s Manual, Part Number
165E3596−00.
F.
Audio Monitoring
For TSO compliant FA2100CVRs mounted in the aircraft, previously recorded data
cannot be monitored from the FA2100CVR. This is a security feature implemented
to protect the rights of pilots and other flight crew members.
The Cockpit Area Microphone (CAM), pilot, co-pilot, and spare audio can be monitored during recording using a headset plugged into the 1/4-inch, 600-ohm phone
jack mounted on the front panel of the associated control unit.
G.
Storage Capacity
The Model FA2100CVR storage media is designated as the Crash Survivable Memory Unit (CSMU). The CSMU in the Model FA2100, p/n 2100–1010–( ), contains
flash memory with enough storage capacity to allow continuous recording of the four
high quality audio channels for a minimum of 30 minutes. The CSMU Flash memory
in the Model FA2100, p/n 2100–1020–( ) pre MOD−DOT #7, provides enough storage capacity to allow continuous recording of the four high quality audio channels for
a minimum of 30 minutes, and the standard quality combined and cockpit microphone channels for a minimum of 120 minutes. The CSMU Flash memory in the
Model FA2100, p/n 2100–1X25/1X26/1X27–( ) and p/n 2100−1X20−( ) post MOD−
DOT #7, provides enough storage capacity to allow continuous recording of the four
high quality audio channels for a minimum of 120 minutes.
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23–70–04
Description and Operation
Rev. 15 Page 17
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
H.
Data Retrieval
Incorporated into the FA2100CVR aircraft installation is a “Record On” jumper. During bench test of the FA2100CVR, removal of the jumper disables the record function of the recorder, thereby allowing playback of the recorded data. While in the
Playback mode, replaying of recorded data is controlled by the Portable Interface
(PI) Unit p/n: 17TES0043 or Portable Interface/2 (PI/2) Unit P/N: 17TES0062. Detailed operation of the PI is contained in the PI Operation Manual, P/N:
165E1630−00 or PI/2 Operation Manual, P/N: 16521630−01.
To retrieve data from the recorder, the recorder must be removed from the aircraft,
connected to appropriate AC or DC power (DC power only for FA2100CVR Models
2100−1010−5X and 2100−1020−5X), and the Portable Interface Unit (PI) p/n:
17TES0043 or Portable Interface/2 (PI/2) Unit P/N: 17TES0062 must be connected
to the recorder’s front panel GSE connector.
The PI or PI/2 Unit allows a user to replay, using a 600-ohm headset and a
600−ohm boomset microphone headset in the case of the
2100−1X25/1X26/1X27−( ) model, any one of the high quality audio channels, or
the cockpit area microphone channel. The PI or PI/2 Unit also has the capability to
search through the stored data using the fast forward and fast reverse command
keys. The fidelity of the FA2100CVR audio data output at the PI or PI/2 Unit is such
that its internal speaker allows quality analysis of the recorded data. The PI or PI/2
Unit also simplifies connection to standard commercial recording equipment for duplicating any of the monitored audio streams.
Additionally, the audio data can be down-loaded through the GSE connector, stored
on Type III PCMICA portable hard disks inserted in the PI Unit for later playback.
The Portable Interface Unit must have MOD-DOT 1 and the FA2100CVR must have
MOD-DOT 2 for Audio data downloading capability to be activated. For the PI/2 refer
to the PI/2 Operation Manual, P/N: 16521630−01on how audio data can be downloaded and the different ways to store data.
For operators using Rose 4.0 or higher software on a ROC or RAU, audio data along
with the flight data may be downloaded directly from a CVR and played back through
Rose. The audio and flight data will be time synchronized through the Rose software. Refer to the Read−Out Support Equipment/Recorder Interface Software Version 4.0 or Higher Operator’s Manual, Part Number 165E1696−03.
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23–70–04
Description and Operation
Rev. 15 Page 18
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
I.
Data Reproduction
A standard cassette, reel-to-reel tape, or digital audio tape recorder can be used to
produce a high fidelity copy of the Model FA2100CVR recorded data. To do so, the
inputs of the copy recorder are connected to any one of the output RCA phono jacks
located on the Portable Interface (PI) Unit’s PI Audio Read-out Cable, p/n
17TES0051. Depending upon the type of recorder used for copying, the
FA2100CVR audio can be copied one channel at a time, or all individual channels
can be copied simultaneously. Reconstructed GMT/RSE output signals may also be
reproduced using the PI’s Aux Read-out Cable, p/n: 17TES0052.
J.
Built-In-Test (BIT)
A continuous Built-In-Test (BIT) capability is provided at power up to establish and
monitor the mission fitness of the hardware. The built-in-test feature has been designed to perform a continuous test of all bits within the solid-state memory located
in the Crash Survivable Memory Unit (CSMU).
An additional built-in-test is initiated by pressing a green TEST pushbutton located
on the front panel of the control unit (Models S151/S161, S152/S162 or
S251/S261). A green TEST indicator is located on the front panel of the Model
S151/S161/S152/S162 and S251/S261 Control Units to indicate successful completion of the manual test. (Note: The S161−1390−01 Control Unit does not have a LED
Test Indicator.) The TEST pushbutton is used to generate the 620- to 660-Hertz test
tone used for unit verification. This test tone is developed on the Audio Compressor
PWA and applied to each channel individually where it is processed, stored in
memory, read from memory, and checked for expected frequency and amplitude.
In the GACVR, a continuous Bite Status Output or Recorder Fault is indicated on pin
23. A ground at pin 23 represents a no fault, while an open indicates a fault or that
a CVR is not installed. The CVR test indicator wires, pins 15 and 16 (1mA) may be
omitted in installations where ARINC 557 compatibility is not needed.
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23–70–04
Description and Operation
Rev. 15 Page 19
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
CVR FAULT LIGHT
REAL TIME
OPEN = FAULT
GND = NO FAULT
ANNUNCIATOR
PANEL
CVR
23
RELAY
+V
ENERGIZE = OPEN (NO CVR FAULT)
DE-ENGERIZED = GRN (CVR FAULT)
Figure 6.
GACVR Fault Circuit for Pin 23
K.
Crash Survivable Memory Unit
The Crash Survivable Memory Unit (CSMU) is the environmentally hardened
memory storage assembly of the Model FA2100. Electrical interface to the CSMU is
made by the Acquisition Processor PWA via a single 16-contact connector at connector J1.
L.
Crash and Fire Protection
The Crash Survivable Memory Unit (CSMU) construction enables the Model
FA2100CVR to meet or exceed the rigorous crash protection requirements of
EUROCAE ED–56A, ED−112 and TSO-123a.
M. Control Unit, Microphone & Preamplifier Equipment
Refer to Aviation Recorders ED-56A Compliant Control Unit, Preamplifier and Microphone CMM, ATA No. 23-70-05, Part Number 165E1747-00, for more detailed information of these ancillary recorder components.
A Control Unit or Preamplifier is a required component of a CVR installation and
functions as the FA2100CVR cockpit user interface; however, this is not required for
GACVR recorders. Control Units contain a preamplifier for interfacing the cockpit
area microphone with the CVR, and provide a means for activating the test function,
by pressing a green TEST push button and observing an green TEST indicator.
Bulk erasure of the FA2100CVR storage media is also accomplished by pressing the
Control Unit’s red ERASE push button. All Control Units contain a headset jack for
verifying system operation.
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23–70–04
Description and Operation
Rev. 15 Page 20
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
The Model S151/S161, Model S152/S162, and the Model S251/S261 Control Units
are for use in FA2100CVR System installations that comply with ARINC Characteristic 757, TSO−C123a and EUROCAE ED–56A. The Model S151/S161, and Model
S251/S261 Control Units house the Microphone Preamplifier PWA, and the TEST
and Bulk ERASE switches. The S151/S251 Control Units are used with remote microphone Model S055, whereas the S161/S261 Control Units are used with the remote microphone Model S056. The Model S152/S162 contains a built-in electret
condenser-type microphone, Microphone Preamplifier PWA, and TEST and Bulk
ERASE switches. All three of these Control Units also contain a TEST indicator
lamp and a 600-ohm HEADSET jack, with the exception of the Model S161 Control
Unit P/N: S161−1390−01, which does not have a test lamp.
The Model S150/S160 Preamplifiers are available for FA2100CVR System installations that do not require a Control Unit but that are required to comply with TSO−
C123a and EUROCAE ED–56A. However, because ARINC Characteristic 757 does
not address microphone preamplifiers, the Model S150/S160 Preamplifiers are not
considered ARINC 557/757 compliant. The S150/S160 provides the same preamplifier circuit for the cockpit area microphone as the Model S151/S161, Model
S152/S162, and Model S251/S261 Control Units.
The FA2100CVR is compatible with installations using the Model A151B and A152B
Control Units; however, such installations do not comply with EUROCAE ED–56A.
The Model A151B houses the Microphone Preamplifier PWA, and the TEST and
Bulk ERASE switches. This Control Unit is used with an externally-mounted condenser microphone (Model A055B). The Model A152B contains a built-in condenser
microphone, Microphone Preamplifier PWA, and TEST and Bulk ERASE switches.
Both the A151B and A152B Control Units contain an analog TEST meter compatible
with the FA2100CVR.
N.
Remote Microphone Module
The Model S055/S056 Remote Microphone Modules are available to complete a
TSO−C123a and ED–56A-compatible installation. The Model S055 Microphone is
required with the S151 and S251 Control Units, and with the S150 Preamplifier Module. The Model S056 Microphone is required with the S161 and S261, and with the
S160 Preamplifier Module.
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23–70–04
Description and Operation
Rev. 15 Page 21
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
O.
Ground Support Equipment Interface
The interface to the Ground Support Equipment (GSE) is via a bi-directional highspeed serial link available at the front-panel GSE connector.
A facility for retrieving the stored data from the CSMU to Ground Support Equipment, GSE, is provided for high-speed downloading of the voice data. The GSE Interface serves two purposes:
P.
(1)
As a connector for use with portable or bench test equipment for recorder
checkout.
(2)
As a connector for use in downloading data into a storage device while on the
aircraft or bench.
BIT and Fault Detection
The FA2100 incorporates multiple overlapping methods of built−in−test (BIT) to ensure proper reporting of the recorder faults. At the most basic level the fault driver
outputs default to the FAULT state (even with no power applied to the recorder) and
must be actively cleared by a properly operating Store Manager Processor (SMP) as
the recorder powers up.
Next, a watchdog circuit monitors the operation of the SMP and associated circuitry.
This assures that a fault is asserted in the event of a processor failure (including partial failures such as arithmetic errors, inordinate increments, and logic errors.) The
watchdog circuit will also be activated in the event of a failure of the SMP’s program
Flash memory.
If the SMP is operating properly it performs the task of monitoring the above listed
faults in the other FA2100 processors. It detects errors in the Flight Data Processor
(FDP) and Audio Compressor Processor (ACP) by checking for protocol errors and
unexpected data values.
The SMP checks the non−volatile random access memory (NVRAM) for operation
and data integrity using a cyclic redundancy check (CRC) on the contents. A failure
to read or write this device properly will be flagged by a CRC mismatch and a BIT
fault will be asserted.
Finally, the SMP verifies the function of the crash−survivable memory unit (CSMU)
by performing a read after each write to ensure the data written to CSMU can be retrieved.
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Description and Operation
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
In summary each processor, RAM and programmable memory device in the FA2100
is monitored by BIT. They are checked at power−up and continuously monitored
during operation of the recorder. Failures are reported using the FAULT output signals.
4. FA2100 CVR SPECIFICATIONS
Specifications for the Model FA2100CVR have been developed in close coordination with
Aerospace Industry regulatory agencies. As such, the FA2100CVR meets or exceeds the
requirements of technical standard order TSO–C123a, TSO–C123b, EUROCAE ED–55,
EUROCAE ED–56A, and EUROCAE ED−112.
A.
Applicable Documents
The following documents form a part of, or are referenced, within this CMM:
(1)
TSO–C123a
Federal Aviation Agency
Technical Standard Order TSO–C123a Technical Standard Order for Cockpit Voice
Recorder Systems.
Federal Aviation Agency
Technical Standard Order TSO–C123b Technical Standard Order for Cockpit Voice
Recorder Equipment.
(1)
TSO–C123b
(2)
EUROCAE MOPS ED–55
European Organization for Civil Aviation
Electronics Minimum Operational Performance
Specification for Flight Data Recorder Systems
(3)
EUROCAE MOPS ED–56A
European Organization for Civil Aviation
Electronics Minimum Operational Performance
Specification for CVR Systems, December
1993
(4)
EUROCAE MOPS ED–112
European Organization for Civil Aviation
Electronics Minimum Operational Performance
Specification for Crash Protected Airborne Recorder Systems, March 2003
(5)
ARINC 404A
Air Transport Equipment Cases and Racking
Characteristic
(6)
ARINC Report 604–1
Guidance for Design and Use of
Built-In-Test-Equipment
(7)
ARINC Report 624
Design Guidance for On-board Maintenance
System
(8) ARINC Characteristic 557
(9) ARINC Characteristic 757
(10) ARINC Characteristic 757A
Cockpit Voice Recorder
Cockpit Voice Recorder
Cockpit Voice Recorder
(11) ARINC Characteristic 777−1
Recorder Independent Power Supply (RIPS)
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23–70–04
Description and Operation
Rev. 15 Page 23
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
(12) RTCA DO–160C
Environmental Conditions and Test
Procedures for Airborne Equipment
(13) RTCA DO–178B
Software Considerations in Airborne Systems
and Equipment Certification to Level D
The Model FA2100CVR meets the performance requirements of ED-56A, chapters 2, 3,
4, and 5, ED–55 chapter 7 and ED−112, chapter 2, and Part I, while conforming to the input interface required in ARINC 557/757/757A. When the software detects a fault a CVR
FAULT will be asserted immediately with no artificial delay.
B.
Physical Characteristics
For specific physical characteristic, refer to Section 800, Fits and Clearances.
C.
Electrical Characteristics
For specific electrical characteristics, refer to Section 800, Fits and Clearances.
D.
Environmental Characteristics
For specific environmental characteristics, refer to Section 800, Fits and Clearances.
E.
Crash and Fire Protection
For specific crash and fire protection specifications, refer to Section 800, Fits and
Clearances.
F.
CSMU Torque Requirement
For specific CSMU torque requirements, refer to Section 800, Fits and Clearances.
5. INSTALLATION
The information provided in this section is for general knowledge use only. For authorized
detailed installation instructions, refer to the Model FA2100CVR Installation and Operation
Instruction Manual, p/n: 165E1846-00.
The Model FA2100CVR is an environmentally hardened unit housed in an ARINC 404A
1/2-ATR short box painted international orange. The FA2100 does not require external
shock mounting for installation into the aircraft. However, the Model FA2100CVR requires
mounting in an approved mount system for installation into the aircraft. FA2100CVR
Mount, Part Number 178E0919–00, is a mount used for this purpose. The FA2100CVR is
fully compatible with ARINC Specification 757 and is directly interchangeable with all existing cockpit voice recorder installations.
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23–70–04
Description and Operation
Rev. 15 Page 24
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
The FA2100CVR is connected to its control unit or preamplifier module by means of the
aircraft wiring. Refer to Figure 7 and Figure 9 for the Standard ARINC−757 and GACVR
Interface Wiring Diagrams used when installing the FA2100CVR into an aircraft. The Control Unit & Microphone information can be found in CMM, ATA No. 23−70−05, p/n:
165E1747−00 for ED−56A installations or the FA2100CVR Installation & Operation
manual, p/n: 165E1846−00.
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23–70–04
Description and Operation
Rev. 15 Page 25
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
STANDARD INTERWIRING PER ARINC SPEC 757
1A
TO 115 Vac HOT
(400Hz)
TO AC COLD
*5
TO
C.U. GND
*1, 2, 7
*3
OR
*4
5A
TO 28 Vdc
*7
PUSH TO TEST
*14
C
*3
ERASE
(MOMENTARY
PUSH BUTTON)
NC
*8
NO
TO ANNUNCIATOR PANEL
FROM CAPTAIN'S
CLOCK
*10
SPARE MICROPHONE
−TO 3RD CREW
MEMBER OR
PA SYSTEM
*9, 11
TO CO-PILOT
MICROPHONE
*10
TO PILOT
MICROPHONE
*16
*9, 11
AREA
MICROPHONE
FROM ROTOR
SPEED SENSOR
*3, 6
* Refer to Notes for
Figure 7.
BRAKE
GEAR
BULK ERASE INTERLOCK (TYPICAL)
OPEN = IN FLIGHT CLOSED = WEIGHT
ON WHEELS
For GACVR versions refer to Figure 9.
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
27
28
29
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, 400 Hz (HOT)
115 Vac, 400 Hz (COLD)
AUDIO OUT LO
AUDIO OUT HI
RECORD ON B
RECORD ON A
+28 Vdc POWER IN
STOP RECORDING
/RIPS ACTIVE INPUT
*7
PUSH_TO_TEST
PREAMP POWER OUT
PREAMP GND
POWER OUT HOT
TEST INDICATOR +
TEST INDICATOR –
CHASSIS GROUND
CVR FAULT OUT
*8
GMT IN B (429) LO
*12
GMT IN A (429) HI
*7
RIPS FAULT INPUT
CHANNEL 1 AUDIO IN LO
DATA LINK FAULT
*15
CHANNEL 1 AUDIO IN HI
DATA LINK IN (429) B
*15
DATA LINK IN (429) A
CHANNEL 2 AUDIO IN LO
CHANNEL 2 AUDIO IN HI
RIPS MAINTENANCE IN­ *7
PUT
OMS IN (429) B
*15
OMS IN (429) A
CHANNEL 3 AUDIO IN LO
RIPS PRESENT INPUT
*7
CHANNEL 3 AUDIO IN HI
CVR REPLAY INHIBIT/FDR
INHIBIT
CHANNEL 4 AUDIO IN LO
CHANNEL 4 AUDIO IN HI
ROTOR SPEED IN LO
*15
ROTOR SPEED IN HI
DATA LINK V1/OMS B OUT
DATA LINK V1/OMS A OUT
*13
VOICE ERASE A
DATA LINK VALID
VOICE ERASE C
*15
Wiring for all CVR's except for 2100-1025-XX and 2100-1026-XX, are compliant to ARINC 757-3.
Figure 7. Interwiring Diagram, Recorder FA2100 CVR
(2100-1010-00, 2100-1X20-00/-02, & 2100-1X25/1X26-XX)
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23–70–04
Description and Operation
Rev. 15 Page 26
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
Notes for Figure 7:
1.
Recommended minimum wire size is #22: #24 is electrically permissible except for power
leads, where #18 wire is desirable on long-runs (pins 2, 3, 9, & 17). Wire resistance
should not exceed 1 ohm for power leads and should not exceed 5 ohms for signal leads.
All wiring should be MIL–W–22759 or MIL–C–27500.
2.
Only one power source to be wired per aircraft. If 115 Vac, 400 Hz is supplied, connection
is to be made to pins 2 & 3. If 28 Vdc is supplied, connection is to be made to pin 9.
Shorting pins 1 & 2 is optional.
3.
Recorder ground connection to be within 1 foot of pin 17, heavy gauge wire. Shields to be
grounded at the recorder using short connections. Pin 17 is used as a +28vdc return. Control unit may be grounded in the cockpit to a chassis ground.
4.
Jumper in aircraft connector. Without this jumper, the unit will not record or erase previously recorded information, bulk erase will not activate, and test will indicate NO–GO.
5.
Pin 3 is not a DC return and is not grounded in the recorder. (see Note 3)
6.
Twisted shielded cable. Shields to be grounded at the airframe using short connections.
Tie shields to existing single point GND use for Pin 17. (see Note 3)
7.
Using the the Stop Recording function, the grounded pin 10 terminates recording within 10
minutes. When using the RIPS Active function the CVR has a backup power source or
RIPS available, pins 10, 29, 38 and 42 will be used for the RIPS Status Monitoring.
8.
BITE status output: ground = no fault, open = fault or CVR not installed.
9.
Audio input 3 Vrms maximum.
10.
In 2100−1010−( ) and 2100−1X20−( ) configurations GMT is inputted as low speed (12.5
kbps) ARINC 429 to pins 25 and 26; with the exception of 2100−1X20−02 configurations
(FSK option). In the −02 versions, GMT is input either as an FSK signal combined with the
audio input signals on either Channel 1 or Channel 3, or as an ARINC 429 input on pins
25 and 26. This recorder has Auto−Sense and will process the GMT input type.
11.
The Control Unit & Microphone information can be found in CMM, ATA No. 23−70−05, p/n:
165E1747−00 for ED−56A installations or the FA2100CVR Installation & Operation manual, p/n: 165E1846−00.
12.
The 205E1849−( ) and 205E3977−( ) Audio Compressor cards provide for both ARINC
429 Label150 (1 sec resolution) and 125 (0.1 min. resolution) Low Speed GMT inputs.
13.
If no Erase function is desired, ground “ERASE A” on pin 55 and leave open “ERASE C”
on pin 57.
14.
Test Indicator +/− lines (pins 15 & 16) only provide +28 Vdc, 1ma output to illuminate the
Control Unit TEST lamp. (This is not sufficient to light an external annunciator lamp).
15.
Data Link and OMS input and output signals are applicable only to p/n: 2100−1X25−( ).
Data Link wiring is in accordance with ARINC 757−4, paragraph 3.9.
16.
Pin 44 may be used to inhibit audio replay when pins 7 and 8 are not jumpered and is applicable only to p/n: 2100−1X25−( ). For further details , refer to ARINC 757−4, Attachment 6, Item 21. (see Note 4)
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23–70–04
Description and Operation
Rev. 15 Page 27
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
STANDARD INTERWIRING PER ARINC SPEC 757A
(Data Link wiring IAW ARINC Spec 757A Paragraph 3.9)
VOICE RECORDER UNIT
(2100−1027−02 wiring shown for
reference)
1
AMP
TO 115 VAC, 400 HZ
TO AC COLD
2, 8
5
OR
TO DC POWER IN
28 VDC
5
AMPS
3
28 VDC RETURN
4
CONTROL UNIT
PUSH TO TEST
PREAMP PWR GND
PREAMP PWR HOT (+18 VDC REG)
CHASSIS GND
VOICE ERASE ”A”
VOICE ERASE ”C”
OUTPUT LO
OUTPUT HI
MIC INPUT LO
MIC INPUT HI
MIC BIAS
AUDIO MONITOR LO
AUDIO MONITOR HI
15
15
LIGHTING COMMON
LIGHTING 28V
8
A
B
C
D
E
F
G
H
J
K
L
M
N
P
R
S
T
U
V
W
X
Y
Z
a
b
c
d
e
f
g
h
i
j
k
m
n
p
q
r
s
9
3
TO ANNUNCIATOR
OR MAINT.
COMPUTER
FROM CAPTAIN’S
CLOCK
SPARE MICROPHONE
TO 3RD CREW
MEMBER OR
PA SYSTEM
10, 11
TO COPILOT
MICROPHONE
10
TO PILOT
MICROPHONE
10, 11
6
COCKPIT AREA MICROPHONE
FROM ROTOR
SPEED
SENSOR
t
3, 7
MICROPHONE
MIC BIAS (WHITE)
MIC HIGH (BLACK)
MIC LOW (SHEILD))
13
BRAKE
GEAR
1 115 VAC POWER IN COLD
5
2 115 VAC POWER IN HOT
28 VDC RETURN/SIGNAL GROUND
3
4
5
AUDIO OUT LO
AUDIO OUT HI
6
RECORD ON B
7
RECORD ON A
8
9 +28 VDC POWER IN
10 STOP RECORDING/RIPS ACTIVE INPUT
11
12 PUSH TO TEST
13 PREAMP PWR OUT GND
14 PREAMP PWR OUT HOT (+18 VDC REG)
15
16
17 CHASSIS GND
3
18
19
20
21
22
23 CVR FAULT
24
25 GMT IN B (ARINC 429) LO
12
26 GMT IN A (ARINC 429) HI
27
28
16
29 RIPS FAULT INPUT
30 CHANNEL 1 LO
INPUT
CHANNEL
31 DATA LINK FAULT
1
32 CHANNEL 1 HI
33 DATA LINK IN (429) B
14
34 DATA LINK IN (429) A
35 CHANNEL 2 LO
INPUT
CHANNEL
36
2
37 CHANNEL 2 HI
RIPS MAINTENANCE INPUT
38
OMS IN (429) B
39
14
OMS IN (429) A
40
41 CHANNEL 3 LO
INPUT
42 RIPS PRESENT INPUT
CHANNEL
3
43 CHANNEL 3 HI
RES - CVR REPLAY INHIBIT/
17
44 PLAYBACK INHIBIT
45 CHANNEL 4 LO
INPUT
CHANNEL
46
4
47 CHANNEL 4 HI
48 ROTOR SPEED IN LO
49 ROTOR SPEED IN HI
50 DATA LINK V1/OMS B OUT
14
51 DATA LINK V1/OMS A OUT
52
53
54
VOICE ERASE ”A”
55
56 DATA LINK VALID
14
57 VOICE ERASE ”C”
BULK ERASE INTERLOCK (TYPICAL)
Figure 8. ARINC 757A Interwiring Diagram, Recorder FA2100 CVR
(2100-1X27-XX)
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
Notes for Figure 9:
1.
Recommended minimum wire size is #22; however, wire size #24 is electrically permissible except for long−run power leads where #18 wire is recommended (pins 3, 9, & 17).
Wire resistance should not exceed 1 ohm for DC power leads and should not exceed 5
ohms for other leads. All wiring should be MIL−W−22759 or MIL−C−27500.
2.
If 115 VAC, 400 Hz is supplied, connection is to be made to pins 2 & 1. If 28 VDC is supplied, connection is to be made to pins 9 and 3.
3.
Recorder Chassis ground connection to be within 1 foot of pin 17, with heavy gauge wire.
Shields to be grounded at the recorder using short connections. Note that Pin 3 is used as
+28 VDC return. Control unit may be grounded in the cockpit to a local chassis ground.
4.
Record enable jumper in aircraft connector. Without this jumper, the unit will not record or
erase previously recorded information, bulk erase will not activate, and test will indicate
NO-GO.
5.
Pin 3 is used for DC power return and is not connected to chassis ground within the recorder. (see Note 3). Pin 1 is used for AC power return and is not connected to chassis
ground within the recorder. All power input and return pins (2 & 1, 9 & 3), are galvanically
insulated from the conductive chassis ground connection.
6.
The Control Unit pre-amp attenuation program pins are not used.
7.
Twisted shielded cable. Shields to be grounded at the airframe using short connections.
Tie shields to existing single point GND used for Pin 17. (see Note 3)
8.
If the power source has battery back-up, a means for terminating recording after a crash
should be included in the aircraft wiring. Grounding pin 10 terminates recording within 10
minutes.
9.
BITE status output: ground = no fault, open = fault or CVR not installed.
10.
Audio input .05 Vrms − 3 Vrms maximum. (1Vrms nominal).
11.
Per FAA Action Notice A8300.56 dated Jan. 24, 1990, the wiring to Channels 1 and 3 may
be transposed; that is, Channel 1 will be Pilot and Channel 3 will be Third Crew Member
or PA System.
12.
In the Model 2100−1X27−( ) configurations GMT is inputted as low speed (12.5 kbps)
ARINC-429 to pins 25 and 26. In addition, the −02 versions can also accept GMT as an
FSK signal combined with the audio input signals on either Channel 1 or Channel 3. In all
CVR configurations, the recorder accepts both label 150 (1 sec resolution) and label 125
(0.1 min. resolution) for 429 GMT inputs. If both are present, label 150 will be used. Any
FSK input will be used only if there is no valid ARINC 429 GMT input.
13.
External microphone connections to control unit.
14.
Data Link and OMS input and output signals are applicable to p/n: 2100−1X27−( ). When
data link valid (pin 56) is grounded and data link communications (pins 32 and 34) are receiving data, then ARINC−429 label 350/352 Bit 16 will be set at zero = good
15.
Control Unit front panel illumination control.
16.
Data Link Fault = Open/Ground discrete, Asserted is Open.
17.
Pin 44 may be used to inhibit audio download when pins 7 and 8 are not jumpered and is
applicable to p/n: 2100-1X27-( ).
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AVIATION RECORDERS
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FA2100CVR
STANDARD INTERWIRING FOR GACVR INSTALLATIONS
6
TO DC POWER IN
28 VDC
5
AMPS
3
CONTROL PANEL*
AUDIO JACK LO
AUDIO JACK HI
6
PUSH TO TEST
NC
ERASE
C
(MOMENTARY
PUSH BUTTON)
8
2, 4
NO
TO ANNUNCIATOR PANEL
TEST LAMP
28 V, 40 mA
INCANDESCENT
FROM CAPTAIN'S
CLOCK
10
TO
3RD
CREW
MEMBER
OR PA SYSTEM
5, 7, 9
TO
COPILOT
5, 7
TO
PILOT
5, 7, 9
MODEL S056
MICROPHONE
FROM ROTOR
SPEED SENSOR
2, 5
MIC BIAS (WHITE)
MIC LO
MIC HI (BLACK)
* Optional Control Panel is custom­
er-furnished.
Refer to Notes on the Following
Page.
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
AUDIO OUT LO
AUDIO OUT HI
RECORD ON B
RECORD ON A
+28 VDC POWER IN
STOP RECORDING
ATTENUATION COMMON
PUSH TO TEST
PREAMP PWR OUT GND
PREAMP PWR OUT HOT (+18 VDC REG
TEST INDICATOR – (TEST LAMP Return)
CHASSIS GND
6dB ATTENUATION
12dB ATTENUATION
24dB ATTENUATION
CVR FAULT
10, 11
GMT IN B (429) LO
GMT IN A (429) HI
CHANNEL 1 LO
CHANNEL 1 HI
CHANNEL 2 LO
CHANNEL 2 HI
INPUT
CHANNEL
1
INPUT
CHANNEL
2
CHANNEL 3 LO
CHANNEL 3 HI
TEST LAMP
INPUT
CHANNEL
3
ROTOR SPEED IN LO
ROTOR SPEED IN HI
MIC. SUPPLY
MIC. GND (SHIELD)
MIC. IN
INPUT
CHANNEL
4
VOICE ERASE ”A”
VOICE ERASE ”C”
GEAR
BULK ERASE INTERLOCK (TYPICAL)
OPEN = IN FLIGHT CLOSED = WEIGHT
ON WHEELS
Figure 9. Interwiring Diagram, Recorder FA2100 GACVR (2100-10X0-50/-51)
with Customer−Furnished Control Panel
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
Notes for Figure 9
1.
Recommended minimum wire size is #22; however, wire size #24 is electrically permissible except for long-run power leads where #18 wire is recommended (pins 9 &
17). Wire resistance should not exceed 1 ohm for power leads and should not exceed 5 ohms for signal leads. All wiring should be MIL–W–22759 or MIL–C–27500.
2.
Single point ground.
3.
Jumper in aircraft connector. Without this jumper, the unit will not record or erase
previously recorded information, bulk erase will not activate, and test will indicate
NO-GO.
4.
Ground connection to be within 1 foot of pin 17. Shields to be grounded at the recorder using short wires. Pin 17 is used as a dc return.
5.
Twisted shielded cable. Shields to be grounded at the airframe using short connections. Tie shields to existing single point GND use for Pin 17. (see Note 4).
6.
If the power source has battery back-up, a means for terminating recording after a
crash should be included in the aircraft wiring. Grounding pin 10 terminates recording within 10 minutes.
7.
Audio input 3V rms maximum.
8.
Wiring shown for fixed attenuation of 18 dB.
9.
Per FAA Action Notice A8300.56 dated Jan. 24, 1990, the wiring to Channels 1 and
3 may be transposed; that is, Channel 1 will be Pilot and Channel 3 will be Third
Crew Member or PA System.
10. If the Solid State GACVR replaces an existing tape-based GA100 Cockpit Voice Recorder installation, the Test Lamp wire connected to pin 23 in the connector that
mates with the GACVR’s J1 connector must be moved to pin 44 with the return connected to pin 16.
11. BITE status output: ground = no fault, open = fault or CVR not installed.
12. The Control Unit & Microphone information can be found in CMM, ATA No.
23−70−05, p/n: 165E1747−00 for ED−56A installations or the FA2100GACVR Installation & Operation manual, p/n: 165E1848−00.
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
6. THEORY OF OPERATION
The theory of operation provided for the Model FA2100CVR describes the function of the
recorder both at the system level, PWA level and software operational level. System level
theory of operation describes the general operation of the system as a whole. Refer to
the Model FA2100CVR System Block Diagram during the following discussion. The
theory of operation for each PWA describes the electrical circuitry of the major functional
groupings contained on the individual PWAs. The software level theory describes the
modes of operation of the recorder software.
A.
MODEL FA2100 CVR SYSTEM THEORY OF OPERATION
The ARINC 557/757/757A, Model FA2100CVR consists of four subassemblies, the
Aircraft Interface Printed Wiring Assembly (PWA), the Audio Compressor PWA, the
Acquisition Processor PWA, and Crash Survivable Memory Unit (CSMU). The recorder interfaces with the aircraft’s cockpit recorder control unit and microphone
through the rear panel connector J1 and with the Ground Station Equipment through
the front panel GSE connector. The descriptions and block diagrams of these subassemblies are provided in this section to support level two maintenance coverage
of this unit.
Rear
J1
Aircraft
Signals &
Power
Front
Aircraft
Interface
(AI)
Analog
Audio
Signals
Audio
Compressor
(AC)
TDM
Crash Survivable
Memory Unit
Processor
(CSMU)
– ADPCM Encoding
– GMT Merging
– Signal Conditioning
– Power Supply
Power
Signals
Acquisition
Processor
(AP)
HSS
– CVR Control
– Fault Processing
– Logic Power Supply
– Digitized Audio Storage
TDM/HSS
GSE –> PI
Figure 10.
FA2100 CVR Overall Function Block Diagram
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AVIATION RECORDERS
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FA2100CVR
B.
Aircraft Interface (AI) PWA
The Aircraft Interface (AI) PWA mounts within the rear of the Cockpit Voice Recorder
chassis and provides the interface between the aircraft and the Cockpit Voice Recorder’s Audio Compressor (AC) and Acquisition Processor (AP) functions. The Aircraft Interface PWA also includes the storage power supply and provides RF filtering
and lightning protection for all input and output signals that interface with the aircraft.
Input and output signal conditioning is also provided for some signals.
Table 2. Aircraft Interface (AI) PWA Current Configuration Where Used
Aircraft Interface PWA
P/N
205E250305
205E250301
205E250308
205E176311
Model Effectivity
2100−1010−00
2100−1020−00
2100−1020−02
2100−1220−00
2100−1220−02
2100−1025−02
2100−1025−12
2100−1025−22
2100−1025−24
2100−1026−02
2100−1225−22
2100−1225−24
2100−1226−02
2100−1027−02
2100−1227−02
Notes
Data Link
On−board Maintenance
System (OMS)
2100−1010−50
2100−1010−51
2100−1020−50
2100−1020−51
Specifically, the Aircraft Interface RF Barrier function provides RF suppression on all
input and output signals needed to meet the requirements of RTCA/DO-160C Sections 20 and 21; while it provides for lightning protection on all input and output signals needed to meet the requirements of RTCA/DO–160C Section 22.
The ARINC 557/757A Aircraft Interface provides input signal conditioning for:
Audio Channel Inputs
Push-To-Test
Voice Erase
Record
Stop Recording
Rotor Speed
GMT
*Datal Link
*OMS
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FA2100CVR
* Only for P/N 205E2503−01 and 205E1763−08.
The ARINC 557/757 Aircraft Interface provides output signal conditioning for:
CVR Fault
Audio Out for Monitoring at the Control Unit headset.
Data Link and OMS (Only for P/N: 205E2503−01 and 205E1763−08)
The Aircraft Interface also includes the storage supply portion of the power supply.
This supply conditions the applied ac or dc input power and charges the 39 Vdc storage capacitor to provide the energy required to operate the Cockpit Voice Recorder
during power outages up to 200 milliseconds in duration.
(1)
ARINC 557/757/757A Aircraft Interface Signals to Aircraft Interface PWA
Table 3 lists the ARINC 557/757/757A aircraft interfaces to the FA2100CVR Aircraft
Interface PWA.
Table 3. ARINC 557/757/757A Aircraft Interface Signals
Signal Name
115 AC IN (HOT, COLD)
AUDIO OUT (HI, LO)
RECORD ON
(A, B)
28 VDC POWER IN
STOP RECORDING
PUSH TO TEST
PRE AMP PWR OUT
(HOT, GND)
TEST INDICATOR
(P,N)
CHASSIS GND
CVR FAULT OUT
Description
Ac input power as defined in RTCA/DO–160C, Section 16.
Combined high quality voice and CAM channels to provide audio monitor output. With the reference signal applied to one
channel, the output level is 2.45 Vrms$30% into a 600 ohm
load (350−400 mVrms into an 8 ohm load for the −93 configuration).
CVR is in Record Mode when A and B are jumpered. A is
grounded internally.
DC input power as defined in RTCA/DO–160C, Section 16.
Recorder stops recording voice and flight data within 10 minutes after this pin is grounded. Recording resumes when
ground is removed.
A ground of this input initiates the BIT test tone sequence.
+18 $2 Vdc output for control unit. Maximum operating current
is 25 ma. Short circuit limited at approximately 30 ma.
Provides 1 ma output into 100 ohms if the PUSH TO TEST
function passed (+12 V $5% through 11.94 kohms $1%).
TEST INDICATOR N is grounded internally. (Not used in
GACVR models.)
Chassis, power, and signal ground.
CVR fault output signal. Open indicates fault, ground indicates
no fault.
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AVIATION RECORDERS
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FA2100CVR
Table 3. (Cont.) ARINC 557/757/757A Aircraft Interface Signals
Signal Name
GMT IN
(A, B) (429)
CHANNEL 1 AUDIO IN
(HI, LO)
CHANNEL 2 AUDIO IN
(HI, LO)
CHANNEL 3 AUDIO IN
(HI, LO)
CHANNEL 4 AUDIO IN
(HI, LO)
ROTOR SPEED IN
(HI, LO)
VOICE ERASE
(A, C)
*Data Link In (A,B)
Out (A,B)
*OMS
In (A,B)
Out (A,B)
Description
GMT input signal. ARINC 429 format. Low Speed (12.5 kbps).
The 205E1849−00 and 205E1849−03 Audio Compressor cards
provide both 150 (1 sec resolution) and 125 (0.1 min. resolution) for 429 GMT inputs.
3rd crew member or extra audio input. Reference signal is 1
kHz at 3 Vrms. Input impedance is greater than 10 kohms.
Co–pilot’s audio input. Reference signal is 1 kHz at 3 Vrms. Input impedance is greater than 10 kohms.
Pilot’s audio input. Reference signal is 1 kHz at 3 Vrms. Input
impedance is greater than 10 kohms.
CAM audio input. Reference signal is 1 kHz at 2 Vrms. Input
impedance is greater than 10 kohms.
Rotor speed input data as defined in ARINC 557/757.
7−6000 Hz Analog Frequency Input.
No Bulk Erase if “A” is grounded or connected to “C” for less
than 0.5 seconds. Bulk Erase occurs if “A” is connected to “C”
for 2 or more seconds and then grounded.
ARINC 429, Labels 156 & 157, Message for displaying ATC
Data Link messaging IAW Williamsburg V3 protocol
On−board Maintenance System, ARINC−429, Label 350, For
monitoring recorder system status including, CVR, CMC Bus,
Control Unit, FDR, and Data Link.
* Only used in 2100−1X25/1X26/1X27−( ) Models of CVR.
(2)
ARINC 557/757/757A Aircraft Interface Signals Between Aircraft Interface
and Audio Compressor PWAs
Table 4 lists the signal interfaces between the FA2100 Aircraft Interface PWA and
Audio Compressor PWA.
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Table 4. Aircraft Interface PWA to Audio Compressor PWA Interface Signals
Signal Name
CH 1 IN HI
CH 2 IN HI
CH 3 IN HI
CH 4 IN HI
CH IN RTN
STOP L
RECORD L
TEST L
AUDIO OUT
AUDIO OUT RTN
TEST GOOD L
VOICE ERASE L
ROTOR SPEED IN
CVR FAULT L
GMT IN
(A, B)
PREAMP PWR FAIL L
Description
Single ended, Channel 1 audio output to Audio Compressor. Signal
level is 2 Vrms $10% with reference signal applied to CVR Channel
1 input.
Single ended, Channel 2 audio output to Audio Compressor. Signal
level is 2 Vrms $10% with reference signal applied to CVR Channel
2 input.
Single ended, Channel 3 audio output to Audio Compressor. Signal
level is 2 Vrms $10% with reference signal applied to CVR Channel
3 input.
Single ended, Channel 4 audio output to Audio Compressor. Signal
level is 1.33 Vrms $10% with reference signal applied to CVR
Channel 4 input.
Return signal for channel 1, 2, 3, and 4 audio signals. Not connected to ground on Aircraft Interface.
Conditioned STOP RECORDING signal output. +5 V through 10
kohms for not asserted. Less than 0.4 V sinking 3.5 ma when asserted.
Conditioned RECORD ON signal output. +5 V through 15 kohms
when not asserted. Ground through 10 kohms when asserted.
Conditioned PUSH TO TEST signal output. +5 V through 10 kohms
for not asserted. Less than 0.4 V sinking 3.5 ma when asserted.
Audio monitor data input from Audio Compressor. Signal level is
2.55 Vrms $30% into 622 ohms when Reference Signal is applied
to one CVR audio input.
Return signal for AUDIO OUT. Grounded on Audio Compressor and
Aircraft Interface.
Push-to-test BIT result input from Audio Compressor. Low indicates
test passed. DS1 on the Audio Compressor Board.
Conditioned voice erase signal output. +5 V through 10 kohms
when high. Less than 0.4 V sinking 3.5 ma when low.
Single ended rotor speed signal output. In phase with ROTOR SPEED IN HI. +5 V through 10 kohms when high. Less than
0.4 V sinking 3.5 ma when low.
CVR fault indicator input from Audio Compressor. Low indicates
fault. DS2 on the Audio Compressor Board.
Provides conditioned, differential GMT input signal to Audio Compressor.
Preamp power fail indication output to Audio Compressor. High is
+5V from 10 kohms and indicates no fault. When preamp power is
less than +15 V output goes low and sinks 3.5 ma at less than 0.4 V.
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(3)
ARINC 557/757A Aircraft Interface Signals
Table 5 lists the signal interfaces between the FA2100 Aircraft Interface PWA and
Acquisition Processor PWA.
Table 5. Aircraft Interface PWA to Acquisition Processor PWA Interface Signals
Signal Name
39VDC
39VDC RTN
+5VDC
+12VDC
−12VDC
PREAMP PWR
(+18VDC)
+15VDC
+ 5VDC (S)
Data Link & OMS*
* Used with
2100− 1025/1026/
1027−XX only
C.
Description
36.6 $2 volt dc output provides up to 16 watts, maximum, to the
main power supply. Up to an additional 4 watts can be supplied to
external test equipment with nominal input voltages and room temperature.
Return path for 39 Vdc current. Tied to ground on both PWAs.
+5 volt input from main power supply. Required tolerance is $5%.
Current required is less than 40 ma.
+12 volt input from main power supply. Required tolerance is $10%.
Current required is not more than 35 ma.
–12 volt input from main power supply. Required tolerance is $10%.
Current required is not more than 25 ma.
+18 volt input from the main power supply, current limited on Acquisition Processor. Required tolerance is $2 volts.
Current requirement is less than 25 ma.
+15 volt output made from Storage Supply input voltage. Tracks the
unregulated input below about 15 volts and then regulates at that level. +18VDC of the main supply is diode coupled to this signal and
provides the power after the main supply is running. Maximum current required by Aircraft Interface is 20 ma. The Aircraft Interface can
supply 100 ma to the Acquisition Processor until the main supply
starts running.
+5 $0.1 volt output made by Storage Supply to provide power to the
main power supply control circuits. The external current must be less
than 10 ma.
Inputs (A, B) − Conditioned, differential Data Link/OMS input to AP
PWA [only used with 205E2502−10/11 AP boards. (MOD−DOT 5
Units.)]
Outputs (A, B) − Data Link/OMS output signal for Acquisition Processor, which drives the ARINC−429 output buffer.
Audio Compressor (AC) PWA
The Audio Compressor (AC) provides a data interface between the Aircraft Interface
(AI) and the Acquisition Processor (AP). The AC digitizes, compresses, and packages four audio channels for subsequent processing by the AP. The AC provides interfaces between the AI and the AP for Greenwich Mean Time (GMT) Data, Rotor
Speed (RSE) Data, and Discrete Data.
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The Audio Compressor PWA receives conditioned audio, GMT, rotor speed, and
discrete command/control data from the AI concurrently. Audio and ARINC 429 input data are processed by the AC and formatted into 16–bit wide words for serial
Time Division Multiplexed (TDM) Bus transmission to the AP. Discrete data from the
AI are consolidated into word format prior to TDM transmission.
Discrete data received over the TDM Bus from the Acquisition Processor provide the
Audio Compressor with Built–In Test (BIT) control and with BIT fault status; fault status data are output to the Aircraft interface PWA. Additionally, audio data reprocessed on the Audio Compressor are output to the Aircraft Interface for audio monitoring. Power/ground and a master reset for the Audio Compressor are derived
from the Acquisition Processor PWA.
The Audio Compressor PWA interfaces with the Aircraft Interface and the Acquisition
Processor. The AC/AI interface comprises four audio input channels: an audio
monitoring output channel, a serial ARINC 429 GMT data input channel, and inputs
for rotor speed frequency and discrete control data. The AC/AP Interface consists of
a serial TDM bus, a master clock signal, a master reset, a test mode control bit, and
power/ground interconnections.
The information transmitted by the AC over the serial TDM bus includes audio, GMT,
rotor speed, and discrete data. Information received by the AC over the serial TDM
bus includes discrete data for status and control.
The AI/AC Interface includes the Audio Interface, the GMT Interface, the Rotor
Speed Interface, and the Discrete Data Interface.
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Table 6. Audio Compressor (AC) PWA Current Configuration Where Used
Audio Compressor PWA
P/N
205E397720
205E397723
205E397717
205E397729
205E397737
205E397722
(1)
Model Effectivity
2100−1010−00
2100−1020−00
2100−1220−00
2100−1020−02
2100−1220−02
2100−1025−02
2100−1025−12
2100−1025−22
2100−1025−24
2100−1225−22
2100−1225−24
2100−1026−02
2100−1226−02
2100−1027−02
2100−1227−02
2100−1010−50
2100−1010−51
2100−1020−50
2100−1020−51
Notes
FSK Function
2−hour Voice
2−hour Voice
AGC Function
Audio Interface
The Audio Interface consists of four audio input channels. Input Channels 1–3
correspond to one of three crew member voice inputs. The ED–56A and
ED−112 reference voltage input to the AC for Channels 1–3 is 2.0 Vrms into a
10 kohm load and a specified bandwidth of 150–3500 Hz. Input Channel 4 corresponds to the Cockpit Area Microphone (CAM) audio input. This channel has
an ED–56A and ED−112 reference voltage input of 1.33 Vrms input into a
10–kohm load with a specified bandwidth of 150–6000 Hz. An audio channel
return ground is included in this interface. Attenuated microphone (AMIC_IN) is
received for the Aircraft Interface.
(2)
ARINC 429 GMT Interface
The ARINC 429 GMT Interface is responsible for receiving serial TTL/CMOS
ARINC 429 Low Speed (12.5 kbps) data from the Aircraft Interface PWA.
(3)
Rotor Speed Interface
The Rotor Speed Interface consists of a single input representing rotor speed
frequency ranging from 7 to 6000 Hz with measurement error less than 2%.
The output signal is 0 – 5 V, with a 10–kohm pull–up resistor on an open collector output.
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(4)
Discrete Data Interface
The Discrete Data Interface includes Aircraft Interface output signals:
RECORD L, TEST L, VOICE ERASE L, STOP L, and PREAMP PWR FAIL L.
Each output signal is 0 – 5 V, with a 10–kohm pull–up resistor on an open collector output. The Discrete Data Interface Audio Compressor output signals
are CVR FAULT L and TEST GOOD L.
(5)
Audio Monitor Interface
An audio output channel for test monitoring provides a combination of six reprocessed Adaptive Differential Pulse Code Modulations (ADPCM) data channels,
with or without a 640 Hz test tone, or a 400 Hz tone indicating bulk erase to a
listener. The output level is 2.55 Vrms into a 622–ohm load with respect to any
input reference level. An audio return ground is included in this interface.
(6)
Audio Compressor/Acquisition Processor Interface
The AC/AP Interface includes the following signals:
(a)
Serial TDM Bus signals TCLK, TFRM, TADD, and TDAT
(b)
Master Clock Input F8.192 MHz
(c)
Master Reset AC RESET L
(d)
BIT Control Input TEST MODE L
(e)
Power/Ground Signals V5N, V5P, and GND
The TCLK and TFRM signals are generated by the Acquisition Processor and
provide bit and TDM frame synchronization, respectively. TADD and TDAT are
bidirectional signals; receiver specific port identification is furnished by TADD
bits [7...0], and the data associated with the targeted receiver occur as TDAT
bits [15...0].
D.
Acquisition Processor (AP) PWA
The Acquisition Processor PWA performs data management of audio data as a
Cockpit Voice Recorder (CVR). It also provides various command and control functions for the recorder, as well as power management.
The Acquisition Processor PWA actually consists of two separate processors: the
Store Manager Processor (SMP) and the Flight Data Processor (FDP). However, in
the FA2100 CVR configuration the SMP is the only processor functioning, with the
exception of p/n: 205E2502−14 since the Data Link signals utilize the FDP proces-
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sor. The Store Manager Processor gathers audio data from the Audio Compressor,
packetizes the data, and saves the data into the flash memory contained in the
Crash Survivable Memory Unit (CSMU).
Table 7. Acquisition Processor (AP) PWA Current Configuration Where Used
Acquisition Processor
PWA P/N
205E250221
205E250214
205E250224
205E250234
205E250238
Model Effectivity
Notes
2100−1010−00
2100−1020−00
2100−1020−02
2100−1220−00
2100−1220−02
2100−1025−02
2100−1025−12
2100−1025−22
2100−1025−24
2100−1225−22
2100−1225−24
2100−1026−02
2100−1226−02
2100−1027−02
2100−1227−02
2100−1010−50
2100−1010−51
2100−1020−50
2100−1020−51
Compatible with 3V Intel
Memory
Data Link
Compatible with 3V Intel
Memory
The Acquisition Processor interfaces with three internal functional modules: Aircraft
Interface, Audio Compressor, and CSMU. Additionally, is an external interface to the
Ground Support Equipment (GSE).
(1)
Aircraft Interface
The Aircraft Interface (AI) Interface involves the following external power inputs
and outputs:
(2)
(a)
External power input +39 Vdc storage supply, +15 V, and +5 V (storage)
from the Aircraft Interface PWA.
(b)
External power output +18 V preamp power, +5 V, and $12 V to the Aircraft Interface PWA.
Audio Compressor
The Audio Compressor (AC) Interface consists mainly of the Time Division Multiplexing (TDM) bus. Audio data is transmitted by the AC via the TDM bus to
the Store Manager Processor (SMP). Additionally, an 8.192 MHz clock is output to the AC to be used as the time base for audio sampling. AC Reset and
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Test mode as well as operating voltages of $5 V are also routed through this
interface.
(3)
Crash Survivable Memory Unit
The Crash Survivable Memory Unit (CSMU) Interface consists mainly of the
buffered high speed serial bus of the SMP. Command and data messages are
transmitted by the Acquisition Processor (AP) to the CSMU. These messages
involve the various data types to be stored in the flash memory of the CSMU.
The CSMU transmits data messages to the AP only in response to commands
issued by the AP. Additionally, +5 V and +12 V power for the CSMU and
CSMU reset are routed through this interface.
(4)
Ground Support Equipment Interface
The Ground Support Equipment (GSE) Interface consists of the buffered TDM
bus, the multiplexed/buffered high–speed serial buses, multiplexer control input, test mode control input, program flash power/control input, and 39 Vdc current limited (GSE pwr, 4–watt available), and +5 V (prgm vpp ap). This interface allows external equipment to monitor microprocessor data transfers within
the recorder, copy the contents of flash memory from the CSMU, download/
upload application software to/from the SMP, and perform functional testing of
the recorders.
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7. SOFTWARE CONSIDERATIONS (ALL P/NS EXCEPT
2100−1X25/1X26/1X27−( ) and 2100−1X20−( ) MOD−DOT #7)
Two sets of software run on the FA2100CVR Recorder. One is the high–level system
software and the other is the low–level processor software. The high–level software consists of a real–time embedded operating system that controls several tasks. Each task is
dedicated to a certain function, such as the recorder controller task. The main purpose of
the system software is to process commands received on the front panel GSE interface
and to coordinate the storing of flight data and voice data. The low–level software is dedicated to the data processing module. The main purpose of this software is to help the
hardware to process the audio data. This software is self–contained and runs separately
from the system software.
As defined in RTCA/DO–178B, the Criticality Category of the Model FA2100CVR is classified as Minor. Accordingly, the software in the FA2100 CVR will comply with the Level D
requirements of RTCA/DO–178B.
A.
Store Manager Processor Software Organization
The SMP software is organized as a multi−tasking environment with individual modules executing as tasks under control of an operating system kernel. The kernel
provides preemptive, priority based multi−tasking of the various modules which satisfy the CVR functionality. The kernel also includes an intertask communications facility which allows the tasks to transmit and receive data. The modules which run as
tasks under software kernel include:
F
CVR Executive
F
Flash Manager
F
NVRAM Manager
F
Fault Manager
F
Mode Executive
F
Audio Channelizer
F
Audio Reconstructer
The SMP software also includes interrupt service routines for the timer, TDM transmit, and TDM receive interrupt handling.
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B.
Software Operating States
The FA2100 CVR software operates in several states which include initialization, recording, power down, data playback, bulk erase, and push to test. Of these states,
the CVR operates in the record state for most of its power on time. Each of the
states will be discussed in the following sections.
(1)
Initialization State
The SMP goes through the initialization sequence when reset is asserted as a
result of power up or watchdog timeout. The power up hardware reset interrupt is connected directly to the SMP. Initialization consists of setting up the
run time environment and starting the software kernel. After the software kernel is initialized, all of the required SMP tasks needed for CVR operation are
started. These include the Mode Executive, CVR Executive, NVRAM Manager,
Flash Manager, Fault Manager, Audio Channelizer, and Audio Reconstructer.
The Mode Executive provides the interface to the GSE if it is connected to the
recorder. It controls whether the CVR will progress into the record state or playback state for recovery of recorded audio.
The CVR Executive processes the input digital audio channel data and manages the actual record or playback operations.
The Flash Manager acts as a server task supporting all accesses to the crash
protected flash memory devices. Likewise, the NVRAM Manager task provides
a similar interface function to the non−volatile RAM used for memory index and
configuration information storage.
The Fault Manager provides common processing for all fault conditions and notable events that are detected by the other software tasks.
The Audio Channelizer task “demultiplexes” mixed audio data from the TDM
bus interface and builds packets of channel specific audio data for storage in
the CSMU. The Audio Reconstructer task processes the individual audio channel streams, either in real time (using the read−after write CSMU data) or as
part of the audio data playback state back into a single stream for transmission
to the GSE via the TDM bus.
Once all the SMP tasks are running, record state initialization is controlled by
the CVR Executive task. It retrieves the record−location indices from NVRAM,
then performs a CRC and additional validation steps. If the indices cannot be
validated, the CSMU memory is scanned to find an appropriate record starting
point as evidenced by an erase gap. In the case where no erase gap can be
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found, the indices are set to a pre−determined top of memory location. Once
the indices are restored, the CVR is ready to transition to the record state.
(2)
Record State
Figure 11 shows the word partition structure for the 2-Hr FA2100CVR, refer to
this figure for the following description. Once the FA2100CVR has been initialized, recording will commence with the first digitized audio data received from
the Audio Compressor board. The CVR Executive task enables the TDM receive routine to begin collecting data form the Audio Compressor stream sent
over the TDM bus. The SMP software is responsible for all of the processing
needed to format the received audio data streams into a form ready for storage
into the CSMU. The complete sequential process is described in the steps below:
(a)
The TDM interrupt handler receives the audio data stream from the Audio
Compressor hardware and buffers it into 8 ms blocks of data. Each of
these blocks contains four, 2 ms frames of interleaved digital samples of
the HQV, HQC, SQV, and SQC audio channels. Each 2 ms frame also
contains samples of GMT, rotor speed, and discrete inputs (push−to−test,
bulk erase).
(b)
The 8 ms blocks of audio data are split by the Audio Channelizer task.
This task “demultiplexes” the audio sample stream into the individual
streams that will be stored in the CSMU. The Audio Channelizer builds 36
word packets of data for each of the four stream types, HQV, HQC, SQV,
and SQC, along with 36 word packets of “special” data (GMT, rotor speed,
discretes). As each packet is filled, it is forwarded to the CVR Executive
task. Special packets containing GMT and rotor speed data are also built
and forwarded.
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HQV
HQC
36‐Wd
HQV
SF
SQV
SQV
HQV
SF
HQC
SF
HQC
HQV
HQC
HQC
HQV
HQC
HQV
SF
X
SQC
SQC
SF
SQC
SQV
SQC
SF
SQC
SPCL
SQC
SF
SQV
HQC
SF
HQV
SQV
SQC
SQC
SQV
SF
HQV
SQV
36‐Wd
SF
SQV
HQC
HQV
SF
SQV
HQC
SF
SQC
36‐Wd
SF
HQC
HQV
HQV
36‐Wd
HQC
SQC
SQV
SQC
SF
HQV
SQV
HQC
SF
HQV
SF
HQC
SQV
SQV
HQV
SF
HQV
SQC
SQC
SF
SQV
SQC
SQC
SF
SQV
HQV
HQV
HQV
HQV
(9) 36‐Word Frames per
72‐ms Superframe
HQC
(6) 36‐Word Frames
per
72‐ms Superframe
SF
SQC
SQV
SQC
SF
X
SPCL
SQV
Special Frame
Rotor Speed, GMT, (2) 36‐Word Frames per
72‐ms Superframe
Discretes, FDR
+
Sync Mark
(1) 36‐Word Special Frame per
4 Superframes
SQC
SQC
(2) 36‐Word
Frames per
72‐ms Superframe
* Block headers & Block boundaries Not Shown
Figure 11.
2–Hr FA2100 CVR (pre MOD−DOT #7)
Word Partition Structure Streams
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(c)
The CVR Executive manages the storage of received channel specific audio data packets to the CSMU. The CVR Executive examines the packet,
determines which memory partition should be addressed, and sends the
complete packet to the Flash Manager for storage in the CSMU. The CVR
Executive task also manages the erase look−ahead function to insure that
there is always a new erased block of flash memory available for impending memory write operations.
(d)
The Flash Manager stores the packet in the CSMU and performs a read−
after−write for each word stored. The read−after−write data packet along
with error count is returned to the CVR Executive.
(e)
The CVR Executive checks for any CSMU access errors, logs error as appropriate, and sends the 36 word read−after−write packet to the Audio Reconstructer task.
(f)
The Audio Reconstructer task accumulates the channel specific audio
data packets and multiplexes them into the 2 ms. audio data frame format.
The reconstructed audio stream is transmitted via the TDM bus to the
GSE connector. If attached, this allows the GSE to monitor real time audio that has been completely processed through the CSMU.
While in the record state, the Mode Executive monitors the delayed shutdown
input to the CVR. If asserted, and held, this will cause the Mode Executive to
start a shutdown timer. If the timeout occurs (within 10 minutes), Mode Executive will set a shutdown flag which is polled by the CVR Executive. This results
in a shutdown of record operation until the delayed shutdown input is de-asserted, or the timer is reset by an assertion of the “push−to−test” input.
(3)
Power Down State
Power down is initiated when the hardware detects an imminent power failure.
The hardware design is such that a power fail signal will be provided to the
SMP at least 50 milliseconds before reset will occur. This input to the SMP is
detected by the CVR executive task. This task then proceeds to effect an orderly shutdown of record operations within the CVR. The shutdown sequence
is as follows:
(a)
After sensing the power fail input, the CVR executive sends a “stop recording” message to the Audio Channelizer task. The Audio Compressor
hardware is disabled to stop the flow of audio data into the SMP. The
CVR executive then starts a timer while waiting for the Audio Channelizer
task to respond to the shutdown message. During this time, all processed
audio data will continue to be received from the Audio Channelizer and
sent to crash protected flash memory as in normal record mode. The Au-
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dio Reconstructer task is also shutdown to free resources and CPU bandwidth.
(b)
The Audio Channelizer task receives the shutdown message, but continues to process any 8 ms blocks of audio data that may be in its input
queue.
(c)
When it has processed all pending data, the Audio Channelizer zero fills
any remaining partial 36 work channel specific packets. The last packets
are sent to the CVR Executive along with a “shutdown complete” indication.
(d)
Upon receiving the shutdown complete indicator from the Audio Channelizer task, the CVR executive knows that it has processed the last of the
audio channel packets. Record position indices are then stored in
NVRAM (via the NVRAM manager task). If the “shutdown complete” indication is not received from the Audio Channelizer task within the prescribed timeout limit, the CVR Executive will proceed with the shutdown
sequence. This prevents an Audio Channelizer anomaly from inhibiting an
orderly storage of pointer indices and other data before the power fail reset occurs.
(e)
(4)
After the NVRAM values have been updated, the CVR executive enters
an idle loop waiting for power to drop. If the power fail indicator relents,
the CVR executive will perform a re-initialization and re-enter the record
state.
Data Playback State
Data Playback state is enabled when the SMP Mode Executive task detects a
playback request command from the GSE via the TDM bus. Playback of audio
data is inhibited if the recorder is installed in an aircraft through sensing of the
record bias input signal.
Requests for audio data playback from the GSE are forwarded to the CVR
Executive task. The CVR Executive will calculate the physical memory indices
for the playback start point based on playback positioning commands (rewind,
forward, fast rewind, fast forward) received from the GSE. Audio data output
starts when the “play” command is received. At that point, the CVR Executive
will start to retrieve 36 word packets of channel specific audio data from the appropriate memory partitions. The packets are passed to the Audio Reconstructer task which, in turn, multiplexes the 2 ms. frames of audio data and transmits
it to the GSE over the TDM bus. This process continues until the end of the recording is reached or a stop command is received from the GSE.
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(5)
Bulk Erase State
The bulk erase operation is initiated by assertion of the bulk erase discrete input to the recorder. After this input has been detected by the Mode Executive
task for at least two seconds (usually by depressing a push button on the control unit in the cockpit), the bulk erase command is sent to the CVR Executive.
The CVR Executive task will cycle through each erase block in the CSMU and
set the bulked erased flag which is part of the eight word block header. The
CVR Executive will prevent the playback of any CSMU memory block which
has been marked as bulk erased. The bulk erase flag in each block is reset
during normal record state operation. During the bulk erase operation the CVR
Executive controls a 400 Hz tone which is inserted on the monitor audio channel to confirm bulk erase state operation.
(6)
Push to Test State
The built in test capability includes the push to test state which is initiated and
controlled by the push to test discrete input to the CVR. Assertion of the push
to test input (usually by depressing a push button on the control unit in the
cockpit) is detected by the Mode Executive task.
Once this input is detected, the Mode Executive will start the test sequence
which takes about two seconds to complete. A 640 Hz analog tone of about
200 ms duration is inserted sequentially into each of the audio input channels
and recorded. The tone is detected on the Audio Compressor board in the
monitored audio channel. Proper detection is checked by the Mode Executive
and, if detected correctly on all inputs, and no other fault condition exists, a
“good” or “passed” indication is asserted and held for about one second. Such
an indication is usually displayed on the control panel in the cockpit.
C.
Data Structures
The primary data structure utilized in the FA2100 CVR is the organization of the
crash protected flash memory contained in the CSMU. The partitioning of the
2-Mwords chips (32 Mb) of the CSMU memory provides for the physical separation
of the individual audio partitions needed for the storage of the HQV, HQC, SQV, and
SQC channels (per ED−56A).
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The memory model for the two hour CVR is physically constructed as illustrated in
Figure 12. There are a total of 15 X 32 Mb memory devices allocated to the four
partitions as shown. The 30 minute CVR contains a total of 7 X 32 Mb memory
devices allocated to just the first two partitions, for the HQV and HQC channels.
Due to the amount of sampling required for high quality channels, it takes almost as
many memory devices for 30 minutes of high quality recording as it does for 120
minutes of standard quality recording. For 30 minute recorders the total amount of
physical memory capacity is 24 megabytes. For 120 minute recorders the memory
capacity is 60 megabytes.
2M
Words
2M
Words
2M
Words
2M
Words
2M
Words
2M
Words
2M
Words
2M
Words
2M
Words
2M
Words
2M
Words
2M
Words
2M
Words
2M
Words
HQV = High Quality Voice
HQC = High Quality CAM
SQV = Standard Quality Voice
SQC = Standard Quality CAM
2M
Words
HQV = 4 Chips
30 Min.
HQC = 3 Chips
30 Min.
SQV = 4 Chips
120 Min.
SQC = 4 Chips
120 Min.
NOTE: This representation does not
include p/n: 2100-1025-( ), which is a
2-hour HQ only recorder.
Figure 12.
2–Hr FA2100 CVR Memory Structure
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Each 32 Mb flash memory device in the CSMU contains 2 Mwords (16 bits per word)
of storage capacity. This 2 Mwords consists of 64 “Erase” Blocks which are each 32
Kwords long. An erase block is the smallest physical block of a flash memory device
that can be erased at one time.
The FA2100 CVR software partitions each 32 Mb Erase Block into an eight word header
followed by 910 logical packets of 36 words each. These packets are the fundamental
units which are built and stored into the CSMU. The header data includes partition,
channel, block number and other information that can be used to re-align and
re-assemble the physical memory devices should they become detached from the
printed wiring board during impact.
D.
Fault Processing
The Model FA2100 CVR software monitors virtually every internal data transaction
for anomalies. This includes all messaging between tasks, SMP to CSMU, and SMP
to GSE. The digitized audio data input stream from the Audio Compressor board is
also monitored for integrity.
The software also monitors itself for illegal or unexpected operations. Fault information is stored in the NVRAM fault history log. The log can contain about 275 entries.
Of these, the first 255 entries are considered as “primary” events. If this portion of
the log fills, the remaining 20 “secondary” entries are used and overwritten as required. The log records the power up sequence number and the following information for each event:
F
time (in seconds) from last power up
F
event class
F
task ID of event source
F
type of event
F
specific event code
F
event count (within this power up sequence)
The event class identifies the severity of the event detected. This allows the fault
log to be used for recording non−fault conditions that may help in determining subsequent failure modes. The event classes reported by the software are:
F
EV − No fault, event recording only
F
NN − Fault, not latched, not fatal
F
LN − Fault, latched, not fatal
F
LF − Fault, latched fatal
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Any detected fault condition asserts the fault output from the CVR. Some faults are
“latched’ meaning that the fault indication will continue to be asserted (regardless of
power cycling) until it is cleared by maintenance action. Other faults may relent, allowing normal CVR operation to continue. In such a case, the fault condition is not
“latched“ and the fault output from the CVR will be de−asserted. Of the latched
faults, some may be severe enough to halt and then restart recorder operation.
Such faults are considered fatal. Any active or latched fault condition is also reported by a “not passed” indication in response to the push−to−test command.
The task ID indicates which module within the software organization detected the reported condition. The “type of event“ field categorizes the general nature of the fault
conditions. Reported categories include:
Table 8.
Fault Processing Event Types and Descriptions
Type of Event
Description
Internal Faults
illegal or unexpected software errors
CSMU flash memory errors
flash memory write or erase errors
BITE errors
detected power supply faults
Communications errors
illegal or unexpected GSE messages
While fault conditions are detected throughout the CVR software modules, the conditions are all reported and logged through the Fault Manager task which executes on
the SMP. It provides the common interface for fault output control and fault history
log management. The fault history log is accessed via GSE commands for downloading and analysis of the fault log entries. Likewise, the latched fault condition and
the fault log itself are cleared by GSE commands by using the Portable Interface
Unit. Refer to the Testing and Troubleshooting, Section 100, for the corrective action
to be taken if any of these fault codes should appear in the status report.
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8. SOFTWARE CONSIDERATIONS (P/NS: 2100−1X25/1X26/1X27−( )
and 2100−1X20−( ) MOD−DOT#7)
A.
Equipment Environment
The hardware environment for the 2100−1X25/1X26/1X27−( ) and 2100−1X20−( )
MOD−DOT #7 Solid State Cockpit Voice Recorder is composed of a pair of
TMS320C50 Digital Signal Processors (DSPs), an external program memory for
each DSP that contains the executable program code, one external NVRAM for
non−crash critical data storage and a flash memory array located in a Crash Survivable Memory Unit (CSMU). In addition there are external interfaces attached to
each DSP to allow external communication for testing purposes, interfaces to allow
the system to gather data for storage, and interfaces used to send and receive external control/state information.
B.
Software Partitioning
Software for the Model FA2100 Solid State Flight Recorders will be partitioned into
two parts. This is to accommodate the use of two DSPs. One DSP, called the Flight
Data Processor (FDP), is responsible for the collection, processing, and forwarding
of Data Link messages. The other processor, called the Storage Management Processor (SMP), is responsible for the collection of audio data, the management of the
CSMU, and other ancillary functions. Communication between the two processors
will be over the device−specific TDM (time division multiplexing) serial link.
C.
Memory Requirements
The memory requirements for the Model FA2100 Cockpit Voice Recorders varies depending on the specifics of the part number produced. The types of memory present in the recorders are: RAM, which is built into the DSP chip; ROM, containing the
program image; NVRAM, which is used to store fault and start−up information; and
Flash memory within the CSMU, that is used to store Data Link and audio data.
Each DSP has a total of 10k words of built−in RAM. Each DSP has access to 64k of
ROM for the executable program image. The system contains one NVRAM with a
minimum of 2k words being required.
D.
Interfaces
The system level inputs dedicated to the CVR functions are:
F
Audio Data Input
F
Audio Frame Synch Input
F
Bulk Erase Input
F
Channel Tone Select Output
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COMPONENT MAINTENANCE MANUAL
FA2100CVR
F
Channel Monitor/Test Select Output
F
CVR Fault Output
F
GMT Input
F
Push−To−Test Input
F
Record On Input
F
Rotor Speed Input
F
Stop Record Input
F
Test Good Output
The system level interfaces used by all configurations are:
F
Power In
F
Power Return
F
GSE Input
F
GSE Output
Data Link interfaces (P/N 2100−1X25/1X26/1X27−( ) only) are:
F
Data Link Input
F
Data Link/OMS Output
F
Data Link Valid
F
CVR Indent Pin
(1)
On−Board Maintenance System (OMS) Interface (P/N
2100−1X25/1X26/1X27−( ) only)
The CVR is identified as a BITE Standard A equipment so as to be portable to
other AIRBUS programs.
The CVR interfaces with the OMS through a system BITE such that the CVR
will pass fault information to the OMS (via SCI) and receive test request based
on two ARINC 429 buses (as per a BITE Type 1 principle):
(2)
F
Use of one ARINC 429 High Speed (HS) output bus for continuous fault
reporting by means of the CVR output pins 50/51 (Data Link / OMS Out).
F
Use of one ARINC 429 Low Speed (LS) input bus for test request by
means of CVR input pins 39/40 (OMS IN).
Fault Warning System (FWS) Interface
As per ARINC 757A, the CVR transmits its status at a 1 Hz rate. The status is
transmitted on Label 350 per ARINC 429 in the format depicted in Attachment
19 of ARINC 757A (CVR STATUS WORD).
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FA2100CVR
The fault signal is indicated for any of the following (as per ED112 §2−1.4.2):
F
failure of the audio or digital interface and processing equipment.
F
failure of the recording medium and/or drive mechanism.
F
failure of the recorder to store the information in the storage medium as
shown by checks fo the recorded material including, if reasonably practicable, correct correspondence with the inputs.
The following list explains system failures intended to be displayed with the
message: “CVR SYSTEM FAULT”
Table 9.
P/N 2100−1X25/1X26/1X27−( ) Software Fault Warning Failures
SSCVR label 350 bit 11
Failure of the audio circuit
CVR CU label 350 bit 13
DataLink Recording label
350 bit 16
Control Unit loads Its powFailure of the recording
er supply below 15.5 Volts.
medium
Failure of the recording
medium
Failure of the recorder to
store Information In the
storage medium
Insufficient audio or UTC
time record duration
CVR Inhibited (pin 10 activated)
(3)
Failure of the recorder to
store Information In the
storage medium
Insufficient datalink record
duration
CVR Inhibited (pin 10 activated)
Data Link (ATC) Interface (p/ns: 2100−1X25/1X26/1X27−( ) only)
The FA2100CVR, p/n: 2100−1X25/1X26/1X27−( ) only can interface with the
Data Link Systems from other aircraft programs (ATSU on SA/LR or even
CMU).
The FA2100CVR is designed to support V3 Williamsburg Protocol high and V1
Williamsburg hardware provision.
The “data link recording” information status is taken into account by the A429
CVR output through the label 350 bit 16. (0 = ok and 1=failure), as per ARINC
757.
The CVR receives all data link messages on pins 33/34 (DATALINK IN 429) as
per ARINC 757 characteristics.
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FA2100CVR
E.
Push−to−Test (PTT) Functionality
The Push−to−Test functionality (already implemented on existing aircraft and standardized in ARINC 757A specification) is used to provide the flight crew with the ability to quickly confirm good serviceability of the CVR before flight as required by the
applicable regulation.
Upon test activation, the CVR tests the front end audio inputs (each of the four audios inputs channels) and initiates Built−In−Test functions of the CVR.
When used with the FA2100CVR, p/n: 2100−1X25−( ) and the S161−1390−01 control unit, the push−to−test action must be a minimum of one (1) second. During the
test, the monitor output (pin 5/6) will be muted (no sound). If the test passes, a .5
second 600−660 Hz tone is activated on the monitor output. For a failure the output
remains muted.
Upon initiation of the Push−To−Test (PTT) function, the CVR sends status indication
on dedicated outputs, particularly on CVR fault discrete output pin 23 (not used) and
on label 350 (CVR STATUS WORD bit 11 on pins 50/51).
CVR Test activation (PTT switch) is allowed at any time during the flight so that the
crew can re−initiate the test after a fault is detected in the hope of recovering the recorder (test is specified to act as a reset of the recorder).
F.
Bulk Erase
As per ARINC 757A, the CVR provides a Bulk erase function. In order to ensure reliable operation, the function is inhibited to prevent inadvertent or untimely erasure
while the aircraft is capable of moving under its own power. In addition to the means
already provided at A/C level (interlock devices monitored with the aircraft on−
ground information and effective park brake locked), the CVR provides a timed interlock for erase. The erase starts by connecting CVR pin 55 to pin 57 for a minimum of
2 seconds and then connecting pin 55 to ground (pin17) before erasing the previously recorded data. This action is initiated by pressing the Bulk Erase push−button on the applicable Control Unit.
The erase is indicated by a 400Hz tone activated during the erase process on Control Unit Headphone or Boomset to validate bulk erasure. The erasure is activated
once per depression (no cycling).
As per ED112 IV−2.2.3 (Data Link part), recorded digital messages shall not be
erased, re−written or altered during the process of downloading. In addition, also per
ED112 IV−2.1.12 (Data Link part), no means for the erasure of the record shall be
provided in the recorder, except for the overwriting of the oldest data by new information.
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FA2100CVR
G.
Recorder Synchronization
The FA2100CVR equipment is designed to be able to record time code from an
ARINC 429 in priority and later FSK source (the frequencies used are 3607Hz +/−
30Hz and 4193Hz +/− 30Hz), depending on the source used on the aircraft. For
Models FA2100CVR, p/n: 2100−1X20−02/2100−1X25−( ), 2100−1X26−( ), and
2100−1X27−( ) the recorder automatically detects which source is received, acquires the time data, and stores it into memory.
The A429 clock refresh time is to one (1) second; if after this time, the CVR is capable of acquiring and to recording the FSK Frequency necessary for synchronization.
The ARINC GMT word (either label 125 UTC BCD or 150 UTC BNR) is transmitted
at a rate of one (1) second, the FA2100CVR recorder is designed to recognize and
record GMT word sent at this transmit rate.
The CVR is capable of recording both label 150 or 125 with a priority for Label 150 if
both labels are present.
The CVR equipment contains an internal time reference in the event FSK or ARINC
429 time reference is not available.
Label 350, Bit 17 indicates the status of the clock as the following: 0=ok and 1=failure.
H.
Data downloading (P/N: 2100−1X25/1X26/1X27−( ) only)
It is possible to download the Data Link message data from the crash protected medium, while the recorder is installed on the aircraft (as per ED112 Part IV § IV−2.2.3).
The L−3AR Portable Interface, 17TES0043 PI/1; 17TES0062 PI/2, provides a
means to download the Data Link message data at the CVR on-aircraft so that an
operator can easily and quickly download previously recorded Data Link information
without removing the recorder from its mounting.
The downloading may be performed by means a ground PC personal computer on
and in laboratory with the L−3AR Audio Data Link Playback software, ADLP software. Refer to the L−3AR Audio Data Link Player Operators manual, p/n:
165E3596−01 for more details.
For operators using ROSE 4.0 or higher software on a ROC or RAU, audio data
along with the flight data may be downloaded directly from a CVR and played back
through ROSE. The audio and flight data will be time synchronized through the
ROSE software. Refer to the Read−Out Support Equipment/Recorder Interface Software Version 4.0 or Higher Operator’s Manual, Part Number 165E1696−03.
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COMPONENT MAINTENANCE MANUAL
FA2100CVR
I.
CVR RIPS status monitoring (P/N: 2100−1X25−22/−24, 2100−1X26−( ),
and 2100−1X27−( ) only)
The Recorder Independent Power Supply (RIPS) is an ON−CONDITION LRU designed to provide 10 minutes CVR backup power as per ARINC Characteristic
777−1. The CVR RIPS status monitoring provides a way to monitor the function
status of RIPS within the CVR. There is no change in CVR hardware except for the
pin assignments to the rear connector. Listed in Table 7 are the difference in the pin
assignments of the CVR rear connector for both prior to RIPS and RIPS installation.
RIPS status will be received and transmitted using Fault Warning Label 350, Label
351 and Label 352 as part of the OMS. RIPS status will also be stored within the
CSMU memory and the data will be able to be retrieved using the existing support
equipment for analysis.
Table 10.
CVR RIPS Pin Assignment for P/N: 2100−1X25−22/−24 & 2100−1X26/1X27−( )
Pin Number
10
29
38
42
(1)
Pre RIPS Pin
Assignment
CVR Stop Recording
FDR Rate A
FDR Rate B
CVR Ident Pin Program
RIPS Pin
Assignment
RIPS Active Input
RIPS Fault Input
RIPS Maintenance Input
RIPS Present Pin Program
RIPS Active
The CVR will use Pin 10 to receive the RIPS Active Status Discrete output. In
addition to reporting the RIPS Active status on this input, the assertion of this
input will start the CVR Stop Recording10 minute timer in order to retain this
standard CVR functionality. Since the RIPS is only active for up to 10 minutes
maximum, the function will be correct if either the RIPS or the CVR shuts down
first.
This status will be received and transmitted in the Label 350, Label 351, and
new Label 352 outputs as follows:
RIPS Active
Status
CVR Discrete input (Pin 10)
SSCVR Label 350 SSCVR Label 351
and 352(Bit 21)
(Bit 12)
Not active
Open
0
1
Active
Ground
1
0
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FA2100CVR
(2)
RIPS Fault
The CVR will use Pin 29 to receive the RIPS Failure Status Discrete output.
This discrete input is presently assigned in ARINC 757A as FDR Rate A for
combination recorder applications. This discrete input is not presently utilized
by the pre RIPS CVR software. This RIPS status will be received and transmitted in the Label 350, Label 351, and new Label 352 outputs as follows:
(3)
RIPS Failure
Status
CVR Discrete input (Pin 29)
SSCVR Label 350 SSCVR Label 351
and 352(Bit 15)
(Bit 18)
Not Failure
Ground
0
1
Fault
Open
1
0
RIPS Maintenance
The CVR will use Pin 38 to receive the RIPS Maintenance Status Discrete output. This discrete input is presently assigned in ARINC 757A as FDR Rate B
for combination recorder applications. This discrete input is not presently utilized by the pre RIPS CVR software. This RIPS status will be received and
transmitted in the Label 350, Label 351, and new Label 352 outputs as follows:
(4)
RIPS Maintenance Status
CVR Discrete input (Pin 38)
SSCVR Label 350 SSCVR Label 351
and 352(Bit 20)
(Bit 19)
No Maintenance required
Open
0
1
Maintenance
required
Ground
1
0
RIPS Present
Use of CVR Pin 42, ”CVR Ident” is being used for the RIPS Present Pin Program. Since we do not anticipate more than one CVR installed on any current
aircraft type, the CVR Ident will be defaulted to the first CVR installed (0) in the
software for BITE reporting purposes instead of reading this through Pin 42.
This will free Pin 42 for use as the RIPS Present Pin Program. The status of
this discrete input will be used to modulate the Label 350, Label 351, and Label
352 reporting of RIPS status. If RIPS is not present, then all of the associated
RIPS status bits (Fault, Maintenance, Active, and Present) will be set to zero
(0) in the Label 350/352 output. Likewise, RIPS Fault and RIPS Maintenance
will default to zero (0) in the Label 351 output if the RIPS is not present.
If the RIPS is not present, then any reference to RIPS in the Interactive OMS
output pages will be suppressed. However, in the case where the CVR is re-
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FA2100CVR
moved from an aircraft with RIPS and re−installed on an aircraft without RIPS, it
is possible that previous flight leg RIPS fault information, stored in the CVR
fault log while installed on the aircraft with RIPS, will be displayed. This is not
considered a likely event since when a CVR is removed from an aircraft it is required to pass a ”return to service” test performed on a repair bench, before re−
installation. This procedure usually includes clearing the fault log that may
have had RIPS faults recorded.
This RIPS Present status will be received and transmitted in the Label 350, Label 351, and new Label 352 outputs as follows:
RIPS Presence CVR Discrete inStatus
put (Pin 42)
SSCVR Label 350 SSCVR Label 351
and 352 (Bit 22)
(Bit 20)
Not present
Open
0
1
Present
Ground
1
0
For more information on the RIPS, see P/N:165E4900−00, Installation and
Operation Instruction Manual for Recorder Independent Power Supply (RIPS).
9. On board Maintenance System Interface
The 2100−1025−22/−24 CVR includes an ARINC 429, high speed, On board Maintenance System (OMS) output interface (Pins 50/51) and an ARINC 429, low speed,
OMS input interface (Pins 39/40). The OMS input interface is only used for OMS
heartbeat detection and is discussed further in section 1.4 below.
The OMS output interface is used for transmission of CVR status information to a
Centralized Maintenance Computer (CMC). The OMS outputs are listed in Table
1.1.
Table 11. CVR OMS Output Words
Label
350
354
377
Parameter
Format
CVR Status Word
BNR
LRU identification (P/N and S/N)
ISO 5
ARINC 429 equipment identification
BCD
Rate
1s
0.5 s
1s
The Label 350 status word can be used to supplement or replace the discrete status
outputs that are otherwise available from the CVR (e.g. CVR Fault discrete, DataLink
Fault Discrete, and Test Good Indicator). The CVR software provides the Label 350
status output word, per ARINC 757A, once per second.
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FA2100CVR
As an additional capability, this CVR also monitors the status of an attached Recorder Independent Power Supply, if present, and includes that status with the OMS output reporting. The RIPS status is monitored using the CVR input pins listed in Table
1.2:
Table 12. CVR Pins Assigned to RIPS Status Monitoring
Pin
Number
10
29
38
42
A.
RIPS Monitoring Function
State
CVR Stop Recording / RIPS Active
Open = Not Active
Closed = RIPS Active or Stop Recording
RIPS Fault
Open = RIPS Fault
Ground = RIPS OK
RIPS Maintenance
Open = No RIPS Maintenance Needed
Ground = RIPS Maintenance Required
RIPS Present Pin Program
Open = No RIPS Installed
Ground = RIPS Present
If the RIPS is not present, then the CVR will not monitor the RIPS status inputs, and
they will not be reported (default to “0’’ in Label 350 output).
Label 350 Status Word Output
The CVR will report status using Label 350 on the OMS ARINC 429 output word as
shown in Table 1.3 below:
Table 13. CVR Label 350 Output Format
BIT
N°
FUNCTION
STATUS
1­8
Label 350
9­10
SDI
1 2
1 1
10 9
0 0
0 1
1 0
1 1
0: OK
11
12
13
14
15
16
17
18
CVR Audio Recording Failure
CMC Bus Status
CVR Control Unit Failure
FDR Status (not used)
RIPS Fault Status (pin 29)
CVR DataLink Recording Failure
Clock Status
Data Link Input Interface
0: OK
3
1
4
0
5
1
6
0
7
0
8
0
Normal (CVR1)
Not used (CVR2)
Not used
Not used
1 : Failure
0: OK
1 : Failure
0: OK
1 : Failure
0: OK
1 : Failure
1 : RIPS Fault
0: OK
1 : Failure
0: OK
1 : Failure
0: OK
1 : Failure
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FA2100CVR
19
20
21
22
23­29
30­31
CVR Recording Failure (Record Enable)
RIPS Maintenance Status (Battery) (pin 38)
RIPS Active Status (pin 10)
RIPS Presence Status (Pin 42)
Spare
SSM 350
0: OK
1 : Failure
0: No Maint. 1 : Maint. Req.
0: Not Active 1 : RIPS Active
0: Not Pres. 1 : RIPS Present
32
Parity
In general, the Label 350 Status Word bits operate as outlined in ARINC 757−4, Attachment 20. There is some interaction among the status bits in Label 350 with regard to Bit 11 (CVR Status), the CVR Fault Status discrete output, and with the results of the CVR Push−to−Test function. These interactions are summarized in Table
1.4 below:
31
1
1
0
0
30
1 Normal Operation (NO)
0 Functional Test (FT)
1 Non Computed Data (Not Used)
0 Fault Warning (Not Used)
Table 14. CVR Fault Reporting Interactions
L350
BIT
N°
11
12
13
14
15
16
17
18
19
20
21
22
FUNCTION
CVR Status (Audio Recording
Failure)
CMC Bus Status (OMS Input)
CVR Control Unit Failure
FDR Status (not used)
RIPS Fault Status (Pin 29)
CVR DataLink Recording Failure
Clock Status
Data Link Input Interface
CVR Record Enable (Pins 7/8)
RIPS Maintenance Status (Battery) (Pin 38)
RIPS Active Status (Pin 10)
RIPS Presence Status (Pin 42)
REPORTED
WITH L350
BIT 11
REPORTED
WITH PUSH
TO TEST
YES
YES
REPORTED
WITH CVR
FAULT DIS­
CRETE
YES
NO
YES
NO
NO
NO
NO
NO
NO
NO
NO
YES
NO
NO
NO
NO
NO
YES
NO
NO
YES
NO
NO
NO
NO
NO
YES
NO
NO
NO
NO
NO
NO
NO
It is important to note that certain CVR faults can only be detected through the
“Push−to−Test” function. This commanded BITE provides the only test of the CVR
audio input circuits. During the Push−to−Test operation, the CVR generates a test
tone and sequentially injects it into each of the four audio input channels. A CVR
fault will be asserted if the tone amplitude or frequency is not correctly detected.
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FA2100CVR
Like any other internal CVR fault, this audio circuit failure will be reported using: the
Label 350 output Bit 11, the CVR Fault Status discrete output, and the Push−to−Test
results. If an audio input circuit failure occurs after a successful Push−to−Test operation, it will not be detected, or reported, until the next Push−to−Test is initiated.
This audio input circuit failure is the only fault that would not otherwise be detected
and reported by the CVR continuous BITE. Push−to−Test results are reported, during the test, using the CVR Test Indicator output (Pins 15/16) which is usually connected to an indicator lamp or meter on the CVR Control Unit. In addition, CVR failures reported through the Push−to−Test operation will be indicated by muting of the
CVR Monitor Audio output (Pins 5/6).
The fault criteria used to determine the reporting status associated with the CVR Label 350 Status Word bits are summarized in Table 1.5.
Table 15. CVR Status Word Fault Reporting Criteria
L350
BIT
N°
11
FUNCTION
FAILURE CRITERIA
CVR Status (Audio Recording Failure)
Any internal CVR failure that prevents correct recording of the audio inputs (including CU failure and
Push−to−Test audio input circuit failure). May relent
depending on fault severity.
Loss of OMS input Heartbeat (valid Label 227 input)
for more than 3 seconds. Relents if OMS Heartbeat is
restored.
Loss of 18 VDC Control Unit supply voltage. Relents if
voltage level returns.
Always reported as “Failed” in CVR only recorder.
RIPS Fault as reported on pin 29 input (if present).
Any internal CVR failure that prevents correct recording of the DataLink input.
Loss of the ARINC 429 GMT input (Label 125 or 150)
for more than 40 seconds. Relents if clock input is
restored.
Loss of the DataLink Heartbeat (valid Label 270) for
more than 3 seconds (only if DataLink Valid, Pin 56, is
asserted). Relents if DataLink Heartbeat is restored
or DataLink Valid removed.
Or
Presence of DataLink Heartbeat (valid Label 270) if
DataLink Valid, Pin 56, is not asserted. Relents if
DataLink Valid is asserted or DataLink Heartbeat is
removed.
12
CMC Bus Status (OMS Input)
13
CVR Control Unit Failure
14
15
16
17
FDR Status (not used)
RIPS Fault Status (Pin 29)
CVR DataLink Recording
Failure
Clock Status
18
Data Link Input Interface
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FA2100CVR
19
CVR Record Enable
(Pins 7/8)
RIPS Maintenance Status
(Battery) (Pin 38)
RIPS Active Status (Pin 10)
20
21
22
RIPS Presence Status
(Pin 42)
CVR “Record Enable” jumper status (pins 7/8).
RIPS Maintenance Status as reported on pin 38 input
(if present).
RIPS Active Status as reported on pin 10 input (if
present).
RIPS Presence as reported on pin 42 input.
Any and all faults detected by the CVR, even if they relent, are recorded in a
non−volatile fault log memory. This fault log can be retrieved using appropriate
ground support equipment for review and analysis.
B.
Label 354 LRU Identification Output
The CVR LRU IDENTIFICATION consists of multiple ARINC 429 words for the transmission of the CVR part number and serial number. The group of eleven ARINC 429
words defined below is transmitted twice per second.
a. Start of Transmission Word
Bit No
1­8
9­16
17­24
25­31
32
Function
Label 354
Number of words in transmission (11)
Not used
STX
Parity
Status
11101100
00001011
00000000
00000010
b. LRU Name
Bit No
1­8
9­15
16
17­23
24
25­31
32
Function
Label 354
‘C’
Not used
‘V’
Not used
‘R’
Parity
Status
11101100
1000011
0
1010110
0
1010010
c. End of LRU Name, Start of Part Number
Bit No
1­8
9­15
16
17­23
Function
Label 354
Carriage return
Not used
First character of part number
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Status
11101100
0001101
0
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FA2100CVR
24
25­31
32
Not used
Second character of part number
Parity
0
d. Part Number (continued)
Bit No
1­8
9­15
16
17­23
24
25­31
32
Function
Label 354
Third character of part number
Not used
Fourth character of part number
Not used
Fifth character of part number
Parity
Status
11101100
0
0
e. Part Number (continued)
Bit No
1­8
9­15
16
Function
Label 354
Sixth character of part number
Not used
17­23
24
25­31
32
Seventh character of part number
Not used
Eighth character of part number
Parity
f.
Status
11101100
0
0
Part Number (continued)
Bit No
1­8
9­15
16
17­23
24
25­31
32
Function
Label 354
Ninth character of part number
Not used
Tenth character of part number
Not used
Eleventh character of part number
Parity
Status
11101100
0
0
g. End of Part Number, Start of Serial Number
Bit No
1­8
9­15
16
17­23
24
25­31
32
Function
Label 354
Twelfth character of part number
Not used
Carriage return
Not used
First character of serial number
Parity
Status
11101100
0
0001101
0
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COMPONENT MAINTENANCE MANUAL
FA2100CVR
h. Serial Number (continued)
Bit No
1­8
9­15
16
17­23
24
25­31
32
i.
Status
11101100
0
0
Serial Number (continued)
Bit No
1­8
9­15
16
17­23
24
25­31
j.
Function
Label 354
Second character of serial number
Not used
Third character of serial number
Not used
Fourth character of serial number
Parity
Function
Label 354
Fifth character of serial number
Not used
Sixth character of serial number
Not used
Seventh character of serial number
Status
11101100
0
0
Serial Number (continued)
Bit No
1­8
9­15
16
17­23
24­31
32
Function
Label 354
Eighth character of serial number
Not used
Ninth character of serial number
Not used
Parity
Status
11101100
0
00000000
k. End of Transmission Word
Bit No
1­8
9­24
25­31
32
Function
Label 354
Not used
EOT
Parity
Status
11101100
0000000000000000
0000100
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Description and Operation
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
C.
Label 377 ARINC 429 Equipment Identification Word Output
The CVR outputs a Label 377 equipment identification word on the OMS bus once
per second. The word structure is defined below:
Bit No
1­8
9­10
11­18
19­29
30­31
32
D.
Function
Label 377
SDI
Equipment ID (CVR = 0x57)
Not Used
SSM
Parity
Status
11111111
00
11101010
00
OMS Input
For the purpose of reporting the OMS input bus status in the Label 350 CVR Status
Word output, the CVR expects a valid OMS input “heartbeat” once per second on
the low speed OMS ARINC 429 input. The heartbeat is detected through the presence of a valid Label 227 input (including good parity) to the CVR. This Label 227 is
used only for heartbeat detection and is not otherwise processed by the CVR. If the
heartbeat is not detected during three consecutive seconds, the CVR will report the
CMS Bus (OMS input) status as “failed” in the Label 350 CVR Status Word output. If
the OMS input bus is not connected, then the associated Label 350 Status Word bit
12 can be ignored.
10. CVR DATALINK INPUT INTERFACE
The FA2100 CVR, part numbers 2100−1X25−02/−22/−24 and 2100−1X26−02, was
developed specifically to satisfy recent requirements for Controller Pilot DataLink
Communications (CPDLC or “DataLink”) recording in addition to the two hour audio
recording capability. The DataLink recording function of the CVR is generally compatible with ARINC 429, ARINC /757A, ARINC 758, and ARINC 619. The interface
is characterized by the following specifications:
F
Single, ARINC 429, High Speed, physical layer input interface (Pins 33/34)
F
Williamsburg Version 3, Bit−Oriented Protocol for link layer interface
F
Includes support for ALOHA exchange (but not required)
F
Records all System Address Label (SAL) 157 and/or 156 full word inputs
F
Recording of all Label 270 and Label 276 DataLink status word inputs
F
Recording of all Label 350 CVR OMS status word outputs
F
32 Mbytes of crash survivable memory reserved for DataLink message recording
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
F
DataLink Valid Discrete input (Pin 56)
F
DataLink Fault Discrete output (Pin 31)
All Label 270, 276, 157, and 156 words input on the CVR DataLink interface will be
recorded to crash protected memory regardless of the parity (good or bad). Likewise, these inputs, if present, will be recorded regardless of the state of the DataLink
Valid discrete input (Pin 56).
A.
Data Link Input and Encapsulation
It is generally recognized that the Williamsburg Version 3 CVR input will utilize only
Command frames containing the encapsulated DataLink message information.
These Command frames then include the ARINC 619 formatting which provides the
Network layer interface. However, the FA2100CVR records data at the link layer interface level and is unaffected by any link layer, or above, data content. This means
that the CVR will record all 32 bits of each and every SAL 157 or 156 word received
on the DataLink input.
As a result, the CVR will not be impacted by any changes or additions to the approved DataLink message set. Likewise, the CVR DataLink recording function is not
affected by the ARINC 619 General Format Identifier (GFI) coding or by the Extended GFI header encoding currently defined for message encapsulation. This technique provides the maximum flexibility in DataLink recording without the need for future CVR changes as the approved message set or associated encapsulation protocols continue to evolve.
A generic DataLink encapsulation structure is illustrated in Figure 2.1 below.
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
Williamsburg V3
protocol
payload
protocol
ARINC 619
Header
payload
Common Header
Header
Payload = one of the following styles
CPDLC
0
Header Length
ASCII or Unaligned PER Message
ADS−C
1
Header Length
ASCII or Bit Encoded Message
AFN, ARINC 623 DC and ARINC 623 OC
2,3,5
Length
ASCII Message
ARINC 623 ATIS & Display Server
4,6
Area
Length
ASCII Message
Figure 13.
Generic DataLink Message Encapsulation Structure
As indicated in Section 1 above, the FA2100 DataLink CVR also includes an ARINC
429 OMS output interface (Pins 50/51) that provides a Label 350 CVR status word
output once per second. This word, in its entirety, along with any DataLink Label 270
or 276 input status words are also recorded as part of the DataLink stream. This
provides a complete representation of the CVR DataLink input, and overall CVR
status, within the recorded DataLink stream.
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
B.
DataLink Heartbeat
In addition to providing the originating system status (e.g. CMU), the Label 270 input
word is also used for DataLink “heartbeat” detection by the CVR. A valid Label 270
input (including good parity) must be received once per second by the CVR. If this
heartbeat is not detected for 40 consecutive seconds for the 2100−1025−02,
2100−1X26−02, 2100−1X27−02 or three consecutive seconds for the
2100−1X25−22/−24, and the DataLink Valid discrete input (Pin 56) is asserted, a
DataLink Interface fault will be asserted (as reported in the Label 350 CVR Status
Word output). Likewise, a DataLink Interface fault will also be reported if the Label
270 heartbeat is detected, and DataLink Valid (Pin 56) is not asserted.
C.
Williamsburg Bit−Oriented Protocol Version Support
It should be noted that the FA2100 CVR does not currently support Williamsburg
Version 1 protocol or a low speed ARINC 429 interface for input of DataLink information.
However, the CVR does support the Williamsburg ALOHA exchange, even though it
is not required for Williamsburg Version 3 DataLink input. In the event that the CVR
receives a valid ALO input on the SAL Label 157 (or 156), it will respond with a valid
Label 304 ALR output indicating support for the Version 3 protocol.
The format of the Label 157 or 156 ALO input is as follows:
Label 157 0r 156 ALO Input
Bit No
Function
Status
1-8
System Address Label 157 or 156
01101111 or 01101110
9-24
Don’t Care (not used by CVR)
xxxxxxxxxxxxxxxx
25-28
ALO
1110
29-31
Protocol
001
32
Parity
The format of the Label 304 ALR response word from the CVR, indicating support
for Version 3 only, is shown below.
CVR Label 304 ALR Output (in response to ALO input)
Bit No
Function
Status
1­8
System Address Label 304
11000100
9­12
Version Supported (3)
1100
13­24
Reserved
000000000000
25­28
ALR
0001
29­31
Protocol
001
32
Parity
As noted above, this ALOHA exchange is not necessary to initiate Williamsburg Version 3 DataLink input to the CVR.
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
D.
DataLink Memory Capacity
The CVR is currently configured with 32 Mbytes of dedicated DataLink recording
memory. This provides for a recording duration far in excess of the existing two hour
requirement.
E.
DataLink Retrieval
Recorded DataLink information is retrieved from the CVR in much the same way as
audio data. All, or a portion, of the DataLink recording can be downloaded from the
CVR using Ground Support Equipment supplied by L−3, Aviation Recorders. The
Portable Interface can be used to download the DataLink recording to a PCMCIA
memory card. The DataLink recording can also be downloaded using the CICC/2 or
CICC/3 interface cable connected to a PC. The downloaded DataLink file can then
be displayed using the Audio DataLink Playback software utility. can also output
the recorded DataLink stream as a Hex ASCII file or Binary ASCII file for more extended user processing and display.
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
THIS PAGE IS INTENTIONALLY LEFT BLANK
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
TESTING
1. GENERAL
NOTE:
The 17TES0400 ROC/6 was manufactured from 2006 to 2011.
Support for the PC operating system (Microsoft Windows XP)
has been discontinued by Microsoft. L−3AR continues to provide technical support and repair; however operators are encouraged to upgrade to the current production 17TES0700
ROC/7. Technical support and documentation for the ROC/6 will
not be available beyond revision 14 of this CMM.
NOTE:
The ROC/6 and ROC/7 will be referred to as “ROC” when the
context and information apply equally to both of them.
NOTE:
If using the ROC/6, begin the testing procedure with Section 2. If
using the ROC/7, begin the testing procedure with Section 3.
NOTE:
ROC/5 and ROC/6 will not run CATS 2.0 and higher. Auto Testing
Part Numbers 2100−1X25−XX, 2100−1X26−XX and
2100−1X27−XX require the ROC/7 and CATS 2.0.
This section provides operational level testing procedures for the Model FA2100 Cockpit
Voice Recorder when using the CVR Automated Test Station (CATS) software, p/n:
17TES0420.
The CATS software v1.0 or 1.1 is contained on the L−3AR Read-Out Center/6 (ROC/6),
p/n: 17TES0400 and is used in conjunction with the L−3AR Recorder Interface Unit (RIU),
p/n: 17TES0410.
The CATS software v2.0 or higher is contained on the L−3AR Read-Out Center/7
(ROC/7), p/n: 17TES0700 and is used in conjunction with the L−3AR Recorder Interface
Unit (RIU), p/n: 17TES0710.
Associated Model S151/S161, S152/S162, and S251/S261 Control Units, S150/S160 Microphone Preamplifier Module, and S055 Remote Microphone testing and troubleshooting procedures are located in the ED-56A Control Unit and Microphone CMM, p/n:
165E1747- 00.
Testing for the Model FA2100CVR is based upon an automated operational test procedure. The automated test procedure may serve as an acceptance criteria for the unit, as
well as provide pointers to probable malfunctioning assemblies in the event that the unit is
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
not functioning properly. For troubleshooting failures, refer to Section 100, Paragraph 7.
To upload the FA2100CVR software, use the ROC/6 without the RIU or an compatible
PC. Refer to Section 100, Paragraph 8.
2. MAINTENANCE PHILOSOPHY
A.
Model FA2100CVR
NOTE:
L-3AR Repair Station has been given authority by L-3AR Factory to
perform board and memory module level, disassembly, repair, assembly and return−to−service testing using factory procedures for all
FA2100 CVRs. L-3AR Repair Station is the only authorized Repair
Station to use the L−3AR factory procedures, all other repair stations
must use the return−to−service testing procedure in this CMM.
The EUROCAE ED−56A and ED−112 compliant Model FA2100CVR has been designed as a maintenance-free unit. The Model FA2100CVR is considered an “ON
CONDITION LRU.” Each of its printed wiring assemblies (PWAs) makes extensive
use of surface mount technology (SMT). The repair of a PWA containing SMT devices requires specialized training and factory equipment, along with special troubleshooting and soldering techniques; therefore, L-3 Communications, Aviation Recorders has deemed that PWAs containing SMT devices are not to be repaired in the
field. As a result, the Model FA2100CVR’s maintenance philosophy is to level-2
board replacement.
The FA2100CVR, has four field replaceable assemblies: (1) the Aircraft Interface
PWA, which contains the power and input circuits; (2) the Audio Compressor PWA,
which conditions the audio streams into digital formats for recording; (3) the Acquisition Processor PWA, which contains the processing and control circuits; and (4) the
Crash Survivable Memory Unit (CSMU), which is used to digitally store and crash
protect the cockpit voice communications. When it has been determined that an assembly is faulty, it should be removed from service, properly packaged, and returned
to L3 Communications, Aviation Recorders for repair or replacement. No troubleshooting procedure is provided for any of these assemblies. Attempting field repair
on any of these assemblies will void their warranty.
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
B.
Model S151/S161, S152/S162, and S251/S261 Control Units
The Model S151/S161, S152/S162, and S251/S261 Control Units have been designed for use with the Model FA2100CVR’s in ED−56A compatible systems and
contain a Microphone Preamplifier PWA manufactured with SMT devices. Refer to
ED-56A Control Unit and Microphone CMM, p/n: 165E1747-00 for detail Testing Procedures for these units.
C.
MODEL S150/S160 MICROPHONE PREAMPLIFIER MODULES
The Model S150/S160 Preamplifiers have also been designed for use with the Model FA2100CVR’s in ED−56A compatible systems that do not require a control unit.
Refer to ED-56A Control Unit and Microphone CMM, p/n: 165E1747-00 for detail
Testing Procedures for these units.
D.
MODEL S055 AND S056 ELECTRET CONDENSER MICROPHONES
The Model S055 and Model S056 Microphones have also been designed for use
with the Model FA2100CVR’s in ED−56A compatible systems. Refer to ED-56A
Control Unit and Microphone CMM, p/n: 165E1747-00 for detail Testing Procedures
for these units.
3. MODEL FA2100CVR RECORDER IN-SERVICE CHECKOUT
A continuous Built-In-Test (BIT) capability is provided at power up to establish and monitor the mission fitness of the hardware. The built-in-test feature has been designed to
perform a continuous test of all bits within the solid-state memory located in the Crash
Survivable Memory Unit (CSMU). Any faults with the unit are stored in non−volatile RAM
as a fault history log to aid in troubleshooting.
An additional built-in-test is initiated by pressing a green TEST pushbutton located on the
front panel of the control units (Model S151/S161 or Model S251/S261). A green TEST
indicator is located on the front panel of the Model S151/S161 and Model S251/S261
Control Units to indicate successful completion of the manual test.
The TEST pushbutton is used to generate the 620- to 660-Hertz test tone used for unit
verification. This test tone is developed on the Audio Compressor PWA and applied to
each channel individually where it is processed, stored in memory, read from memory,
and checked for expected frequency and amplitude.
The Model FA2100CVR’s built-in-test (BIT) philosophy is in accordance with guidelines
set forth in ARINC Reports 604−1 and 624. Activating the BIT test is sufficient to determine the mission readiness of the Model FA2100 Cockpit Voice Recorder System. This
operational test is performed as a pre-flight functional checkout of the Model FA2100CVR
and is activated using front panel controls on its associated control unit.
In the GACVR, a continuous Bite Status Output or Recorder Fault is indicated on pin 23.
A ground at pin 23 represents a no fault, while an open equals fault or CVR not installed.
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COMPONENT MAINTENANCE MANUAL
FA2100CVR
The CVR test indicator wires, pins 15 and 16 (1mA) may be omitted in installations where
ARINC 557 compatibility is not needed.
CVR FAULT LIGHT
REAL TIME
OPEN = FAULT
GND = NO FAULT
ANNUNCIATOR
PANEL
CVR
23
RELAY
+V
ENERGIZE = OPEN (NO CVR FAULT)
DE-ENERGIZED = GRN (CVR FAULT)
Figure 101.
CVR Fault Circuit for Pin 23
To checkout the operation of the Model FA2100CVR, its associated control unit, microphone preamplifier PWA, and cockpit area microphone, connect a headset to the control
unit and, at a distance of approximately 6-inches, speak into the microphone at a normal
voice level. You should be able to hear your words without any significant distortion.
Bulk erasure of the Model FA2100CVR storage medium is accomplished using the
associated control unit red ERASE pushbutton switch. Aircraft wiring interlocks must be
set (that is, landing gear must be down and brakes locked) to allow the CSMU (solid-state
flash memory) to be erased. To erase the information stored in the flash memory, press
the ERASE pushbutton for more than 2 seconds and release. A 400-Hertz tone should
be heard via the headset for less than 10 seconds.
Should a problem be detected with the Model FA2100CVR and its associated control unit,
remove the units from the aircraft. To determine the fault, place the units on the test
bench for complete testing as listed in the procedures in the Testing Section.
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
4. TEST EQUIPMENT REQUIRED
The Model FA2100CVR has been designed as a direct line replaceable unit (LRU) for the
existing Cockpit Voice Recorders, Models A100, A100A, A100S and A200S. As such, the
Model FA2100CVR is to be tested using the same special test equipment built for the
earlier model recorders with the exception of the Model A860 Test Panel which is no
longer supported.
The special test equipment required for use at a FA2100CVR test bench setup consists of
the following units:
L-3AR Read-Out Center/6 (ROC/6)
P/N17TES0400
L-3AR Read-Out Center/7 (ROC/7)
P/N17TES0700
CVR Automated Test Station Software (CATS)
P/N 17TES0420
L−3AR Beacon Test Set
P/N 17TES0015
Dukane Beacon Test Set
Dukane 42A12( )
10 Mohm High Impedance Voltmeter
Commercially Available
Audio Data Link Player (ADLP) Software
P/N 17TES0423
(ADLP Software is only required for FA2100CVR P/N: 2100−1X25/1X26/1X27−( )
for playback only, CATS 2.0+ for Return to Service.)
Note: The Dukane Beacon Test Set may be used as an alternate to the L−3AR Beacon Test Set,
and must be purchased directly from Dukane. A 10 Mohm high impedance voltmeter is
required when using the test equipment below, but it is not included in the test set.
For additional information on the special test equipment, refer to the Special Tools And
Test Fixtures Section 900.
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
5. READ−OUT CENTER/6 (ROC/6), WINDOWS XP, AUTO−TESTING
This section provides instructions for connecting the Recorder Interface Unit to the ROC/6
and FA2100CVR under test. Refer to Figure 201 for the ROC/6 w/CVR Automated Test
Station Software (CATS) FA2100CVR test setup diagram.
NOTE:
The 17TES0400 ROC/6 was manufactured from 2006 to 2011.
Support for the PC operating system (Microsoft Windows XP)
has been discontinued by Microsoft. L−3AR continues to provide technical support and repair; however operators are encouraged to upgrade to the current production 17TES0700
ROC/7. Technical support and documentation for the ROC/6 will
not be available beyond revision 14 of this CMM.
CAUTION:Before proceeding, ensure that the power input select switch on the ROC/6 is
in the proper electrical setting: 115 Vac or 230 Vac. If power input select switch
is not in the proper setting, this will lead to failure in the ROC/6.
A.
READ−OUT CENTER/6 (ROC/6) Interconnects
CAUTION:Make certain that all power is turned off before attaching cables. Failure to
turn off power before attaching cables will result in immediate and serious
damage to the unit.
CAUTION:Only connect DC OR AC input voltage. Do not connect both input voltages at
the same time.
(1)
Connect input power as detailed below, depending on the type of input power
used.
(a)
For DC power, connect the DC power cable (17TES0412) from the DC
Power connector (J8) on the rear of the RIU to a DC power supply that
can generate 28 Volts 1 Amp.
(b)
For AC power, connect the AC power cable (17TES0411) from the AC
Power connector (J7) into a watt meter that handles 115Vac, 400 Hz. Plug
the watt meter into a 115 Vac 400Hz AC power supply
(2)
Plug the cable (17TES0416 for ROC/6) into the rear of the recorder to be
tested. Plug the SCSI connector into “Rear Connector Intfc” (J1) and plug the
blue connector into the blue “AC RCDR Power Test” (J9) connector. Both of
these connectors are on the RIU front panel.
(3)
Connect the cable (17TES0072) between the recorder front ATE connector and
the connector on the front of the RIU labeled “GSE Intfc” (J2).
(4)
Connect the USB Interface cable (17TES0415) between the RIU rear panel
connector (J4) and a USB connector on the ROC/6.
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
NOTE:
Note: Make the following audio connections from the RIU to Sound
Blaster sound card. Note that the sound card is located in an expansion slot not on the motherboard.
(5)
Attach the RIU Sound Card In (SND IN (J3)) cable to the Sound Card Line−In
(or Microphone−In) which is the blue connector.
(6)
Attach the RIU Sound Card Out (SND OUT (J5)) cable to the Sound Card
Line−Out which is the green connector.
(7)
Connect the DIN CABLE from the speakers to the middle Speaker Out (SPKRS
OUT (J6)) connector on the front panel of the RIU.
(8)
After all connections are made to the RIU, apply power to the RIU. This can be
either 28 Vdc or 115 Vac, 400 Hz.
(9)
Apply power to the PC or ROC/6 and observe that the PC boots to the Windows desktop.
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
CVR AUTOMATED TEST
SOFTWARE (CATS)
17TES0420
J4 USB 4‐PIN
RIU UNIVERSAL SERIAL
BUS INTERFACE
17TES0415
POWER
INPUT
SELECT
RIU DC POWER INPUT
17TES0412 (DC)- J8
RIU AC POWER INPUT
17TES0411 (AC)- J7
DC
AC 5A
1A
RECORDER INTERFACE
UNIT (RIU)
J4
17TES0410 USB
R-SPKR *
GREEN
REAR
CONNECTOR
INTFC
GSE
INTFC
J9
RCDR AC
PWR TEST
J1
SPKRS SND
OUT OUT
BLUE
SOUND CARD
DC
RED
LIGHT
YELLOW
LIGHT
AC
SND
IN
J2
J6
J5
J3
L-SPKR *
SND OUT - GREEN
17TES0413
SND IN - BLUE
17TES0413
J6
RIU AUDIO OUTPUT
(SPKRS)
ROC/6
17TES0400
FA2100
SOFTWARE UPLOAD
CABLE ASSEMBLY
17TES0058
(use for software
uploading only)
RECORDER INTERFACE
CABLE ASSY.
17TES0416
(FA2100‐CICC/2) COMPUTER
INTERFACE COMMUNICATIONS CABLE
ASSY.
17TES0072
* Note: Speakers are optional and not incld
with ROC/6
To order speakers from L-3AR use: p/n:
17TES0425 (110V) or 17TES00426 (220V).
FA2100 CVR RECORDER
Figure 102. ROC/6 w/CVR Automated Test Station Software (CATS)
FA2100CVR TEST SETUP
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
B.
READ−OUT CENTER/6 (ROC/6) Sound Card Setup
(1)
Double−click the CATS (CVR Tester) icon on the ROC/6 to start the software
then follow this procedure.
(2)
Click the Speaker button (Volume Control) to display the Playback Control
menu.
(3)
Click on the Options pull down and then click on Properties.
(4)
Click the Recording radio button.
(5)
Select the Line−In check box. (all other boxes should not be checked)
(6)
Click Ok.
Figure 103. Volume Control Properties
(7)
At the Record Control menu under Line−In check the Select box
(8)
Move the Line−In “Volume” control to full volume.
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Figure 104. Line In Input Level
(9)
Click on the Options pull down and then click on Properties.
(10) Select the Playback radio button.
(11) Select the following check boxes: Play Control, Wave and Line−In. All other
boxes should not be checked.
(12) Click Ok.
Figure 105. Sound Card Properties
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(13) Move the Playback and the Wave Volume Controls to full volume and check
the Mute box on the Line in (Mute should not be checked for all others).
Figure 106. Playback Control, Volume Levels
(14) Close the Play Control menu by clicking on the “X” in the upper right corner.
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C.
READ−OUT CENTER/6 (ROC/6) − CATS AUTOTEST
CAUTION:Ensure power is removed from the the RIU before proceeding. If the cable, p/n:
17TES0416 is connected to rear of the unit with the power applied to the RIU,
the RIU may be damaged.
CAUTION:Only connect DC OR AC input voltage. Do not connect both input voltages at
the same time. Connecting both types of input voltages simultaneously will
result in damage to the RIU.
NOTE: The autotest can be performed using DC or AC applied to the RIU.
When autotesting using DC power, proceed to CATS Autotest using DC power paragraph C.(1). when autotesting using AC power,
proceed to CATS Autotest using AC power paragraph C.(2).
(1)
CATS Autotest using DC Power
To perform the CATS Autotest using DC power only, follow the procedures below:
(a)
Ensure that the RIU has no power applied. Connect a CVR to the RIU using the cable, p/n:17TES0416 for the recorder rear connector and cable ,
p/n:17TES0072 for the recorder front connector.
(b)
Setup an in line RMS multimeter. Set to DC amps
(c)
Apply power to the RIU using 28 Vdc.
(d)
If the CATS test page is not shown, Click the L−3 CVR Test Icon on the
Window desktop. Click the Ok button on the Monitor Audio Channel Pop−
up menu.
(e)
From the pull down menu, click on Power at the top of the window and
select Recorder Interface Reset.
NOTE: This will load the Altera chip in the RIU unit. Observe the “connecting to recorder” status window appears.
(f)
From the pull down menu, click on Power => DC Power On.
NOTE: Observe the “connecting to recorder” status window appears.
(g)
Verify that the DC LED on the front of the RIU is on.
(h)
Click on the Information tab in the test section of the menu.
(i)
Enter appropriate information into Department, Part Number and Serial
Number fields.
(j)
From the pull down menu , click on Test=>Test Mode => Return−to−Service Test. Ensure that the Return−to−Service is checked.
(k)
From the pull down menu, click on Test=>Start Test.
NOTE: Follow the instructions below as it appears presented by the software.
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(l)
Read and click on Yes.
Figure 107. CVR Test, Start Toggle
(m) Read and click on OK.
Figure 108. CVR Test, Warning Message
(n)
Remove front cable and click on OK.
Figure 109. CVR Test, Instruction Message
(o)
Enter in the current value in amps (typically .17) in window and click on
OK.
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Figure 110. CVR Test, Power Consumption Entry
(p)
Verify that the DC LED on the front of the RIU is on.
(q)
Enter the current value in amps (typically .52) in window and click on OK.
Figure 111. CVR Test, Power Consumption Entry
(r)
Connect the recorder front cable and click on OK.
Figure 112. CVR Test, Instruction Message
(s)
Verify that the DC LED on the front of the RIU is on.
(t)
Observe the Fault History Log window appears. Select Print if you want to
save the fault history or Close to continue.
(u)
Click on Yes. The autotest will now proceed in completing the autotest
which will take approximately 30 minutes or less.
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Figure 113. CVR Test, Proceed Message
(v)
At the end of the test, save the report by selecting File => Test Report =>
Save Report.
NOTE: The test report is named with the part number of the Unit Under
Test and the serial number provided in the Information section
of the test. The test report is located in the following default location: C:\Program Files\L−3Com\CVR Tester\Reports. This file is
in an ASCII text file format.
(w) If the autotest is successful, clear the fault history log by the pull down
menu, click on Test=>Clear Fault History.
(2)
ROC/6 − CATS Autotest using AC Power
To perform the CATS Autotest using AC power only, follow the procedures below:
(a)
Ensure that the RIU has no power applied. Power is removed. Connect a
CVR to the RIU using the 17TES0416 for the recorder rear connector and
17TES0072 for the recorder front connector.
(b)
Setup an in line RMS multimeter. Set to AC amps
(c)
Apply power to the RIU using 115Vac.
(d)
If the CATS test page is not shown, Click the L−3 CVR Test Icon on the
Window desktop. Click the OK button on the Monitor Audio Channel Pop−
up menu.
(e)
From the pull down menu, click on Power at the top of the window and
select Recorder Interface Reset.
NOTE: This will load the Altera chip in the RIU unit. Observe the “connecting to recorder” status window appears.
(f)
From the pull down menu, click on Power => AC Power On.
NOTE: Observe the “connecting to recorder” status window appears.
(g)
Verify that the AC LED on the front of the RIU is on.
(h)
Click on the Information tab in the test section of the menu.
(i)
Enter appropriate information into Department, Part Number and Serial
Number fields.
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(j)
From the pull down menu , click on Test=> Test Mode=> Return−to−Service Test. Ensure that the Return−to−Service is checked.
(k)
From the pull down menu, click on Test=>Start Test.
(l)
Follow the instructions below as it appears presented by the software.
(m) Read and click on Yes.
Figure 114. CVR Test, Instruction Message
(n)
Read and click on OK.
Figure 115. CVR Test, Warning Message
(o)
Remove front cable and click on OK.
Figure 116. CVR Test, Instruction Message
(p)
Enter in the current value in amps (typically .085) in window and click on
OK.
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Figure 117. CVR Test, Power Consumption Entry
(q)
Verify that the AC LED on the front of the RIU is on.
(r)
Enter the current value in amps (typically .21) in window and click on OK.
Figure 118. CVR Test, Power Consumption Entry
(s)
Connect the recorder front cable and click on OK.
Figure 119. CVR Test, Instruction Message
(t)
Verify that the AC LED on the front of the RIU is on.
(u)
Observe the Fault History Log window appears. Select Print if you want to
save the fault history or Close to continue.
(v)
Click on Yes. The autotest will now proceed in completing the autotest
which will take approximately 30 minutes or less.
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Figure 120. CVR Test, Proceed Message
(w) At the end of the test, save the report by selecting File => Test Report =>
Save Report.
NOTE:
The test report is named with the part number of the Unit Under
Test and the serial number provided in the Information section
of the test. The test report is located in the following default location: C:\Program Files\L−3Com\CVR Tester\Reports. This file is
in an ASCII text file format.
(x)
D.
If the autotest is successful, clear the fault history log by the pull down
menu, click on Test=>Clear Fault History.
READ−OUT CENTER/6 (ROC/6) − Autotest Descriptions
The following provides detailed descriptions of the test performed during the autotest
function.
(1)
Power Test
Prompts the user for AC/DC power usage as in the following AC example:
Please remove the front panel cable from the recorder now and click the ”OK” button.
Please enter the AC power consumption (in amps or watts)
Please enter the AC power consumption (in amps or watts)
Please connect the recorder front panel cable and press the ”OK” button.
Example report message(s):
08:02:13 PASSED Power(AC) (Expected <= 12 watts) Results = (12 watts − 4
watts) = 8 watts
08:02:23 PASSED Power(DC) (Expected <= 11 watts) Results = (12.375 watts
– 2.2 watts) = 10.175 watts
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(2)
Fault Log
Displays the current recorder fault log for user review and prompts the user:
Continue CVR Tests?
Example report message(s):
08:02:32 PASSED Fault History
(3)
Bulk Erase
Part 1 – record audio out and verify 400 Hz bulk erase tone.
Part 2 – record audio out and verify absence of bulk erase tone during rotor data
output.
Part 3 – record audio out and verify absence of bulk erase with recording disabled.
Example report message(s):
08:02:42 PASSED Bulk Erase #1 (Expected 400 Hz) Results = 400.0 Hz
08:02:50 PASSED Bulk Erase #2 with active Rotor Speed (Expected <> 400
Hz) Results = 123.0 Hz
08:02:58 PASSED Bulk Erase #3 with No Recording (Expected <> 400 Hz)
Results = 3334.6 Hz
(4)
Test Tone
Enable push to test and verify push to test indicator is set.
Example report message(s):
08:03:06 PASSED Test Tone (Expected Push−To−Test indicator) Results =
Push−To−Test indicator set
(5)
GMT 429
Record simulated GMT−429 data (label 125 first and label 150 second) and verify 10
good patterns are recorded for each label.
Example report message(s):
08:03:22 PASSED GMT 429 (Label 125) (Expected 10 patterns) Results = 10
good patterns08:03:42 PASSED GMT 429 (Label 150) (Expected 10 patterns)
Results = 10 good patterns
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(6)
Rotor Speed
Part 1 – Record simulated 6000 Hz rotor speed data and verify data is within 2% of
sent frequency.
Part 2 – Record simulated 7 Hz rotor speed data and verify data is within 2% of sent
frequency.
Example report message(s):
08:03:52 PASSED Rotor Speed 6000 Hz (Expected 4 patterns > 5880.0 Hz <
6120.0 Hz) Results = 5998.0 Hz, 6026.4 Hz, 6026.4 Hz, 6026.4 Hz
08:04:03 PASSED Rotor Speed 7 Hz (Expected 4 patterns > 6.9 Hz < 7.1 Hz)
Results = 7.0 Hz, 7.0 Hz, 7.0 Hz, 7.0 Hz
(7)
Channel Balance
Record simulated 1000 Hz ½ reference level data for each channel 1,2,3 and 4 and
verify amplitude all within 3 dB.
Record simulated 1000 Hz 1/10 reference level data for each channel 1,2,3 and 4
and verify amplitude all within 3 dB.
Example report message(s):
08:04:52 PASSED Channel Bal 1000 Hz 0.5 ref (All within 3 dB) Results = HQ1
5.2 /HQ2 5.3 /HQ3 5.1 /HQC 5.1 /SQV1 5.0 /SQV2 5.4 /SQV3 5.4 /SQC 5.5
dBV
08:05:40 PASSED Channel Bal 1000 Hz 0.1 ref (All within 3 dB) Results = HQ1
−8.3 /HQ2 −8.2 /HQ3 −8.4 /HQC −9.4 /SQV1 −8.0 /SQV2 −8.1 /SQV3 −8.1
/SQC −9.1 dBV
(8)
Frequency Response
Record simulated 150 Hz ½ reference data for each channel 1,2,3 and 4.
Record simulated 1000 Hz ½ reference data for each channel 1,2,3 and 4.
Record simulated 3500 Hz ½ reference data for each channel 1,2,3 and 4.
Record simulated 5000 Hz ½ reference data for channel 4.
Record simulated 6000 Hz ½ reference data for channel 4.
Verify amplitude all within 6 dB.
Example report message(s):
08:06:28 Frequency Resp 150 Hz 0.5 ref Results = HQ1 3.6 /HQ2 3.8 /HQ3 3.5
/HQC 1.4 /SQV1 3.9 /SQV2 3.9 /SQV3 3.9 /SQC 3.9 dBV
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08:07:15 Frequency Resp 1000 Hz 0.5 ref Results = HQ1 5.2 /HQ2 5.3 /HQ3
5.1 /HQC 5.1 /SQV1 5.4 /SQV2 5.4 /SQV3 5.4 /SQC 5.4 dBV
08:08:02 Frequency Resp 3500 Hz 0.5 ref Results = HQ1 3.3 /HQ2 2.9 /HQ3
2.5 /HQC 5.1 /SQV1 3.7 /SQV2 3.7 /SQV3 3.8 /SQC 3.5 dBV
08:08:12 Frequency Resp 5000 Hz 0.5 ref Results = HQC 4.9 dBV
08:08:23 Frequency Resp 6000 Hz 0.5 ref Results = HQC 4.9 dBV
08:08:23 PASSED Frequency Resp (All within 6 dB)
(9)
Signal to Noise and Distortion
Record simulated data at each of the following frequencies once at 0 reference level
and again at 1/10 reference).
Frequencies for HQ1, HQ2, HQ3, HQCAM, SQV1, and SQCAM are:
206, 282, 386, 529, 724, 993, 1360, 1864, 2554 and 3500 Hz.
Frequencies for HQCAM and SQCAM are:
217, 314, 454, 656, 949, 1372, 1984 and 2869 Hz.
Frequencies for HQCAM only are:
4148 and 6000 Hz.
Verify HQ > 24.0 dB and SQ > 20.0 dB.
Example report message(s):
08:09:38 PASSED SN+D 150 Hz 1.0 ref (Expected HQ > 24.0 dB SQ > 20.0
dB) Results = HQ1 35.0 /HQ2 34.6 /HQ3 35.3 /HQC 36.9 /SQV1 32.1 /SQV2
31.6 /SQV3 32.0 /SQC 31.6 dB
08:35:07 PASSED SN+D 150 Hz 1.0 ref (Expected HQC > 24.0 dB SQC > 20.0
dB) Results = HQC 30.7 /SQC 25.9 dB
(10) Crosstalk Audio
Record simulated 1000 Hz data for each channel 1,2,3 and 4 and calculate difference between driven and non−driven channels. Verify difference is less than −40
dB.
Example report message(s):
08:41:34 PASSED Crosstalk (Audio) 1000 Hz 1.0 ref (Expected Driven − Non−
Driven < −40 dB) Results = HQ1 11.2 /HQ2 −101.0 /HQ3 −109.9 /HQC −128.1
/SQV 11.4 /SQC −84.4 dBV
08:41:49 PASSED Crosstalk (Audio) 1000 Hz 1.0 ref (Expected Driven − Non−
Driven < −40 dB) Results = HQ1 −101.3 /HQ2 11.2 /HQ3 −115.3 /HQC −107.5
/SQV 11.4 /SQC −72.3 dBV
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08:42:04 PASSED Crosstalk (Audio) 1000 Hz 1.0 ref (Expected Driven − Non−
Driven < −40 dB) Results = HQ1 −304.8 /HQ2 −127.4 /HQ3 11.1 /HQC −104.4
/SQV 11.4 /SQC −72.0 dBV
08:42:19 PASSED Crosstalk (Audio) 1000 Hz 1.0 ref (Expected Driven − Non−
Driven < −40 dB) Results = HQ1 −304.9 /HQ2 −304.9 /HQ3 −111.7 /HQC 11.1
/SQV −72.4 /SQC 11.4 dBV
(11) Crosstalk Data
NOTE:
Test for combination recorders where both flight data and voice data
are being recorded.
Perform a Channel Balance to determine and store results for each channel 1,2,3
and 4.
Record 6000 Hz simulated rotor data and simulated GMT 429 and calculate channel
results minus channel balance results. Verify difference is less than −34 dB
Example report message(s):
08:43:07 PASSED Channel Bal 1000 Hz 1.0 ref (All within 3 dB) Results = HQ1
11.2 /HQ2 11.2 /HQ3 11.0 /HQC 11.1 /SQV1 11.0 /SQV2 11.3 /SQV3 11.4
/SQC 11.5 dBV
08:43:23 PASSED Crosstalk (Data) 6000 Hz 1.0 ref (Expected Crosstalk −
Channel Bal < −34 dB) Results = HQ1 −304.9 /HQ2 −125.7 /HQ3 −304.8 /HQC
−49.8 /SQV −83.4 /SQC −82.8 dB
(12) Audio Out Monitor
Record simulated 1000 Hz data for each channel 1,2,3 and 4 and verify amplitudes
by part number:
Part# 2100−10X0
= 2.45 +/−20%
Audio Out level (VRMS)
Part# 2100−30X3−00
= 2.45 +/−20%
Audio Out level (VRMS)
Part# S200−XXX−XX
= 4.6 − 8.4
Audio Out level (VRMS)
Example report message(s):
08:45:17 PASSED Audio Out Monitor 1000 Hz (Expected 0.358 +/−20 percent
VRMS) Results = HQ1 0.322 /HQ2 0.323 /HQ3 0.321 /HQC 0.319 VRMS
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(13) Signal To No Signal
Record simulated 1000 Hz data for each channel 1,2,3 and 4 and store results then
record no data for channels 1,2,3 and 4 and compare differences between signal
data results and no signal data results. Verify difference is less than −48 dB.
Example report message(s):
08:47:12 PASSED Sig To No Sig 0 Hz 1.0 ref (Expected HQ < −48 dB SQ <
−40 dB) Results = HQ1 −304.9 /HQ2 −122.6 /HQ3 −108.4 /HQC −115.4 /SQV1
−82.7 /SQV2 −82.2 /SQV3 −80.7 /SQC −85.0 dB
(14) Shutdown
Part 1 – enable delayed shutdown.
Part 2 – verify shutdown is detected (CVR fault set) after > 9 and < 10 minutes.
Part 3 – verify shutdown is terminated following a push to test and recording is resumed.
Example report message(s):
08:47:13 PASSED Shutdown Initialization (Shutdown issued − Please wait
9−10 minutes...)
08:56:14 PASSED Shutdown CVR Fault (Expected CVR fault to occur) Result
= CVR Fault
08:56:27 PASSED Shutdown Push−to−Test (Expected 1000 Hz frequency)
Results = 999.9 Hz
(15) Capacitor
Power off recorder and verify recorder is still powered after 200 milliseconds but not
powered after 2 seconds.
Example report message(s):
08:56:32 PASSED Capacitor − GSE powered after 200 milliseconds but not
after 2 seconds
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(16) FSK Time (V1.1 BETA)
Cycle power to recorder to reset for FSK input then record simulated 16000 sps FSK
data and then simulated GMT 429 data (label 150) first with channel 1 output and
again with channel 3 output. Verify 9 good FSK data patterns and a switch to 9 good
GMT 429 data patterns for each channel 1 and channel 3.
Example report message(s):
14:50:07 PASSED FSK Time HQ1 (Playback)(Expected 9 patterns) Results = 9
good patterns
14:50:07 PASSED FSK Time HQ1 (GMT Switch) (Expected 9 patterns) Results
= 9 good patterns
14:50:53 PASSED FSK Time HQ3 (Playback)(Expected 9 patterns) Results = 9
good patterns
14:50:53 PASSED FSK Time HQ3 (GMT Switch) (Expected 9 patterns) Results
= 9 good patterns
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E.
ROC/6 − Audio Setup Procedure
NOTE:
L−3AR recommends that an Audio Setup check be performed
every two years, or if the Sound Blaster Audio card is replaced
on the ROC/6−CATS RIU System.
The Sound Blaster Audio Card in the ROC/6 must be set up to ensure that the proper reference voltage levels of the audio test signals are sent to the RIU for testing
the FA2100CVR. The Audio Setup is only required when the RIU or Sound Blaster
Audio Adapter card is removed or replace by a new one or when the autotest results
indicate that the Audio Adapter Card is not outputting the proper signal levels. Indication of this is when a known good CVR is failing all of the the autotest audio test
functions.
The audio setup process requires the use of the Audio Setup Cable Assembly, p/n:
17TES0417, refer to Figure 121.
LOOP BACK
CONNECTOR
Figure 121. Audio Setup Cable Assembly, 17TES0417
NOTE:
(1)
Selections on the toggle switches of the Audio Setup Cable Assembly, pn
17TES0417, override channel selections made in the CATS software. For
example, if the user selects channels 1,2,3,4 in the Audio Reference Setup
Utility, but selects CH1 on the cable toggle switches, the Audio Reference
Level will be calculated for Channel 1. Reference values calculated for
Channel 1 are functionally equivalent to reference values for channels 2−3.
Sound Card Input/Output Setup
CAUTION: Remove power from the the RIU before proceeding. If the connector is disconnected with power applied to the RIU, the RIU may be damaged.
(a)
Attach the loop−back connector of the Audio Setup Cable, p/n:
17TES0417, to the Recorder Interface cable, p/n: 17TES0416, coming
from the RIU. Connect the Audio Setup Cable, p/n 17TES0417, to multimeter set to “Volts AC”.
(b)
Ensure that the RIU Sound Card In (SND IN (J3)) cable is connected to
the Sound Card Line−In (blue connector).
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(c)
Ensure that the RIU Sound Card Out (SND OUT (J5)) cable is connected
to the Sound Card Line−Out (green connector).
(d)
Apply DC or AC power to the RIU.
(e)
If the CATS test page is not shown, Click the L−3 CVR Test Icon on the
Window desktop. Click the OK button on the Monitor Audio Channel Pop−
up menu.
(f)
From the pull down menu, click on Power at the top of the window and
select Recorder Interface Reset.
NOTE: This will load the Altera chip in the RIU unit. Observe the “connecting to recorder” status window appears.
(g)
From the pull down menu, click on Power => DC Power On or AC Power
On.
NOTE: Observe the “connecting to recorder” status window appears.
(2)
(h)
Verify that the DC LED or AC LED on the front of the RIU is on.
(i)
Click the Speaker button (Volume Control) to display the Playback Control
menu.
(j)
Please refer to and perform steps (2) through (14) of Section 5.B.
“Read-Out Center/7 (ROC/7) - Sound Card Setup.”
Part 1 – Sound Card Output Adjustment
(a)
Select Utilities => Audio Reference Level Utility to run the Audio Reference Utility from the CVR Tester menu. At the CVR Tester Pop−up menu,
select the OK button
Figure 122. Audio Reference Level Utility, Warning Message
(b)
Select Channel 1 check box ion the Audio Reference Level Menu.
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Figure 123. Audio Reference Level Utility, Menu
(c)
Load 1000Hz full amplitude .wav file by selecting File => Open File on the
Audio Reference Utility. Select Setup_1000Hz.wav. and click on Open.
Figure 124. Audio Reference Level Utility, File Open Menu
(d)
Ensure the MultiMeter is connected to the Audio Setup Loop−back cable.
Set the toggle switches to the following settings: (Switch Settings: Channel 1 and No Audio Out).
(e)
At the Audio Reference Level menu, ensure that the Channel 1 check box
is selected. Select Sound => Play Sound to output the 1000 Hz wave file
to the sound card.
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Figure 125. Audio Reference Level Utility, Play Sound
(f)
Adjust the Audio Reference Level menu volume slider so that the meter
reads 3 Volts RMS or as close as possible to this voltage (without going
over 3 Volts RMS).
(g)
From the Audio Reference Level Menu select Sound => Stop Play to
stop audio output to the sound card.
(h)
Set the toggle switches on the loop−back connector to the following settings: (Switch Settings: Channel 4 and No Audio Out).
(i)
At the Audio Reference Level menu, ensure that the Channel 4 check box
is selected and Channel 1 is deselected. Select Sound => Play Sound to
output the 1000 Hz wave file to the sound card.
Figure 126. Audio Reference Level Utility, Play Sound
(j)
Adjust the Audio Reference Level menu volume slider so that the meter
reads 2 Volts RMS or as close as possible to this voltage (without going
over 2 Volts RMS).
(k)
From the Audio Reference Level menu select Sound => Stop Play to
stop audio output to the sound card.
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(l)
Select Store Result =>Output Results. A pop−up window will appear displaying the current REFERENCE, and the new VOICE VOLUME and CAM
VOLUME values.
Figure 127. Audio Reference Level Utility, Confirmation
(m) Select Yes to update the Setup reference level file with the values displayed, or select No to cancel the update of the Setup reference level file.
(n)
NOTE:
(3)
Close the Audio Reference Level menu by selecting the Close button.
The Audio Reference Utility volume value is used to define the VOICE
VOLUME for channels 1,2,3 and the CAM VOLUME for channel 4, for
output to the recorder during CVR tests.
Part 2 – Sound Card Input Adjustment
(a)
Set the toggle switches on the Loop−Back Connector to the following settings: (Switch Settings: Channel 1 and Audio Out).
(b)
Select Utilities => Audio Reference Level Utility to run the Audio Reference Utility from the CVR Tester menu. At the CVR Tester Pop−up menu,
select the OK button
Figure 128. Audio Reference Level Utility, Warning Message
(c)
Select Channel 1 check box ion the Audio Reference Level Menu.
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Figure 129. Audio Reference Level Utility, Menu
(d)
Load 1000Hz full amplitude .wav file by selecting File => Open File on the
Audio Reference Utility. Select Setup_1000Hz.wav. and click on Open.
Figure 130. Audio Reference Level Utility, File Open Menu
(e)
From the menu bar under Utilities, select Audio Reference Utility. Select
the check box next to Channel 1 and deselect Channel 4 check box. Select Sound => Play Sound to output the 1000 Hz wave file to the sound
card.
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Figure 131. Audio Reference Level Utility, Play Sound
(f)
Adjust the Audio Reference Level volume slider so that the meter reads
2.45 Volts RMS or as close as possible to this voltage.
(g)
From the Audio Reference Level menu select Sound => Record Sound
to record the input sound.
(h)
From the Audio Reference Level menu select Sound => Stop Record to
stop recording.
(i)
From the Audio Reference Level menu select Sound => Stop Play to
stop audio output from the sound card.
(j)
From the Audio Reference Level menu select Store Results => Input
Results to calculate and display the REFERENCE value or Correction
Factor (CF).
Figure 132. Sound Card Input Results
(k)
Click OK to continue with the update or Cancel to stop the update. Following an OK click a pop−up window will appear displaying the new REFERENCE, and current VOICE VOLUME and CAM VOLUME values.
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Figure 133. CVR Tester, Update Reference Level
(l)
Select Yes to update the audio setup reference level file with the values
displayed, or select No to cancel the update of the audio setup reference
level file.
(m) Close the Audio Reference Level menu by selecting the Close button.
(n)
Remove power from the RIU
CAUTION: Remove power from the the RIU before proceeding to the next step.
If the connector is disconnected with power applied to the RIU, the
RIU may be damaged.
(o)
Remove the Audio Setup Loop−Back Connector, p/n: 17TES0417.
NOTE:
This reference value will be used to adjust the audio voltages
read from the audio output of a 600 ohm recorder during CVR
tests. For example, if 1.952 Volts RMS is read from the sound
card then Correction Factor = 2.45 VRMS / 1.952 VRMS. If the
Volts RMS value read is less than 1 Volt RMS then and error
message will be displayed. In this case, verify that all of the
cables are working and are installed correctly.
NOTE:
The setup reference level file is named ri_Ref_Level.txt and is
located in the CVR Tester local subdirectory.
Sample ri_Ref_Level.txt file:
; RI Sound Card reference level
;
; REFERENCE value equals 2.45 VRMS / X VRMS read from sound card.
; Example: 1.255 VRMS REFERENCE = (2.45 VRMS/ 1.952 VRMS read from sound
; card)
; VOICE VOLUME value for Full Reference or 3 Volts RMS input to recorder
; CAM VOLUME value for Full Reference or 2 Volts RMS input to recorder
REFERENCE = 1.255
VOICE VOLUME = 9509
CAM VOLUME = 6168
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F.
ROC/6 − AUDIO DOWNLOAD & PLAYBACK
NOTE:
ROSE 4.0 or higher on a ROC or RAU is recommended to download
directly from a CVR and convert audio into a .WAV for playback. Refer to the Read-Out Support Equipment / Recorder Interface Software
version 4.0 or Higher Operator’s Manual, p/n 165E1696-03, to Retrieve Flight Data and / or Audio Data from a Recorder.
NOTE:
When decompressing Standard Quality Audio from a 2−Hr.
FA2100CVR, p/n: 2100−1020−XX, pre Hardware MOD−DOT #7, you
must have the RIU powered and the Altera chip reset using the Power
−> RIU Interface Reset command.
This is required because hardware inside the RIU is used for converting of the 2−bit compressed Standard Quality Combined (SQV)
and Standard Quality CAM (SQC) channels.
This is not a requirement for the High Quality Channels (HQV & HQC)
because this 3−bit compression is converted using the CATS software. The FA2100CVRs that have Hardware MOD−DOT #7 installed
have full two hour High−Quality for all four audio channels as does
all 30−Minute FA2100CVRs.
(1)
Click on the Copy button. Set the File Name to Filename.cvr (the system will
use a default file name with the part number of the recorder and serial number
that was entered in the information fields of the test section).
(2)
Click on the Save button.
(3)
Select either Full Audio Data Download or Copy data from last XX Hrs. XX
Min. Click OK. Copying of the data will start.
(4)
When the “Copy Data is Complete” box is shown click on Yes. On the Decompression Options menu select HQV1 through HQV3 and HQC. If using an
FA2100CVR, p/n: 2100−1020−XX, pre MOD−DOT #7 unit also select the
Standard Quality Audio data SQV & SQC. Click OK.
(5)
Click on the Microphone button. Select the Left Channel to be HQV1 and the
Right Channel to be HQC. Click OK to exit the dialog box.
(6)
Click on the Play button. Confirm that the display changes and that the speakers output the audio. Click on the Stop button when satisfied that the data is
being played back properly.
(7)
Click on File => Exit to leave CVR Tester.
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Table 101. 17TES0400
Part Number
READOUT CENTER/6 (ROC/6) − Parts List
Description
Mfg.
17TES0400
Read-Out Center/6 − Full CVR/FDR Configuration
(The following items are included with the ROC/6).
L-3 Com
17TES0410
Recorder Interface Unit (RIU)
L-3 Com
17TES0411
Cable, RIU to AC Power In
L-3 Com
17TES0412
Cable, RIU to DC Power In
L-3 Com
17TES0413
Cable, RIU to Sound Card (2ea.)
L-3 Com
17TES0415
Cable, RIU to USB
L-3 Com
17TES0416
Cable, RIU to CVR
L-3 Com
17TES0417
Cable Assembly, Audio Setup
L-3 Com
17TES0420
CATS Software, FA2100
L-3 Com
17TES0070
CICC/2 Assembly
L-3 Com
17TES0072
Cable Assembly, FA2100−CICC/2
L-3 Com
17TES0321
Read-Out System Equipment Software (ROSE 4.X)
L-3 Com
17TES0058
FA2100 Software Upload Cable Assembly
L-3 Com
883E4557−00
CD, Soundblaster Audigy
Obsolete
w/ROC−7s
mnf. After
07/14.
17TES0076
RUFS Recorder Interface, USB
L-3 Com
17TES0425
Speakers (2), 110 Vac (U.S. − Standard)
Optional
17TES0426
Speakers (2), 220 Vac (Non−U.S. − Standard)
Optional
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6. READ−OUT CENTER/7 (ROC/7), WINDOWS 7, AUTO−TESTING
This section provides instructions for connecting the Recorder Interface Unit to the ROC
and FA2100 under test. Refer to Figure 134 for the ROC/7 w/CVR Automated Test Station Software (CATS) FA2100CVR test setup diagram.
CAUTION:Before proceeding, ensure that the power input select switch on the ROC is in
the proper electrical setting: 115 Vac or 230 Vac. If power input select switch is
not in the proper setting, this will cause failure or damage in the units.
A.
READ−OUT CENTER/7 (ROC/7) Interconnects
CAUTION:Make certain that all power is turned off before attaching cables. Failure to
turn off power before attaching cables will result in immediate and serious
damage to the unit.
CAUTION:Only connect DC OR AC input voltage. Do not connect both input voltages at
the same time.
(1)
Connect input power as detailed below, depending on the type of input power
used.
(a)
For DC power, connect the DC power cable (17TES0412) from the DC
Power connector (J8) on the rear of the RIU to a DC power supply that
can generate 28 Volts 1 Amp.
(b)
For AC power, connect the AC power cable (17TES0411) from the AC
Power connector (J7) into a watt meter that handles 115Vac, 400 Hz. Plug
the watt meter into a 115 Vac 400Hz AC power supply
(2)
Plug the cable (17TES0418 for ROC/7) into the rear of the recorder to be
tested. Plug the SCSI connector into “Rear Connector Intfc” (J1) and plug the
blue connector into the blue “AC RCDR Power Test” (J9) connector. Both of
these connectors are on the RIU front panel.
(3)
Connect the cable (17TES0072) between the recorder front ATE connector and
the connector on the front of the RIU labeled “GSE Intfc” (J2).
(4)
Connect the USB Interface cable (17TES0415) between the RIU rear panel
connector (J4) and a USB connector on the ROC.
NOTE:
Make the following audio connections from the RIU to Sound Blaster
sound card or to the motherboard sound system depending on the
serial number of the ROC/7. Newer ROC/7 manufactured after Jun.
2014 do not contain the Sound Blaster auxiliary card.
(5)
Attach the RIU Sound Card In (SND IN (J3)) cable 17TES0413 to the Sound
Card Line−In (or Microphone−In) which is the blue connector.
(6)
Attach the RIU Sound Card Out (SND OUT (J5)) 17TES0413 cable to the
Sound Card Line−Out which is the green connector.
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(7)
Connect the DIN CABLE from the speakers to the middle Speaker Out (SPKRS
OUT (J6)) connector on the front panel of the RIU.
(8)
After all connections are made to the RIU, apply power to the RIU. This can be
either 28 Vdc or 115 Vac, 400 Hz.
(9)
Apply power to the PC; the ROC and observe that the PC boots to the Windows desktop.
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CVR AUTOMATED TEST
SOFTWARE (CATS 2.0)
17TES0420
J4 USB 4‐PIN
RIU UNIVERSAL SERIAL
BUS INTERFACE
17TES0415
POWER
INPUT
SELECT
RIU DC POWER INPUT
17TES0412 (DC)- J8
RIU AC POWER INPUT
17TES0411 (AC)- J7
DC
AC 5A
1A
RECORDER INTERFACE
UNIT (RIU)
17TES0710
R-SPKR *
J4
USB
GREEN
REAR
CONNECTOR
INTFC
GSE
INTFC
SND
SPKRS
OUT
OUT
SND
PWR
IND IN
J5
BLUE
J9
RCDR AC
PWR TEST
J1
SOUND CARD
DC
RED
LIGHT
YELLOW
LIGHT
AC
J2
J3
J6
SND OUT - GREEN
17TES0413
SND IN - BLUE
17TES0413
L-SPKR *
J6
RIU AUDIO OUTPUT
(SPKRS)
ROC/7
17TES0700
FA2100
SOFTWARE UPLOAD
CABLE ASSEMBLY
17TES0058
(use for software
uploading only)
RECORDER INTERFACE
CABLE ASSY. 17TES0418
(FA2100‐CICC/2) COMPUTER
INTERFACE COMMUNICATIONS CABLE
ASSY. 17TES0072
* Note: Speakers are optional for ROC/7.
To order speakers from L-3AR use: p/n:
17TES0425 (110V) or 17TES0426 (220V)
CVR RECORDER
Figure 134. ROC/7 with CVR Automated Test Station Software (CATS 2.0)
FA2100CVR TEST SETUP − ROC/7’s DMF: Pre Jul. 2014.
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CVR AUTOMATED TEST
SOFTWARE (CATS 2.0)
17TES0420
J4 USB 4‐PIN
RIU UNIVERSAL SERIAL
BUS INTERFACE
17TES0415
POWER
INPUT
SELECT
RIU DC POWER INPUT
17TES0412 (DC)- J8
RIU AC POWER INPUT
17TES0411 (AC)- J7
DC
AC 5A
1A
RECORDER INTERFACE
UNIT (RIU)
17TES0710
GREEN
R-SPKR *
J4
USB
REAR
CONNECTOR
INTFC
GSE
INTFC
SND
SPKRS OUT
SND OUT
J1
DC
PWR
IND IN
SND OUT - GREEN
17TES0413
RED
LIGHT
YELLOW
LIGHT
AC
J5
BLUE
J9
RCDR AC
PWR TEST
J2
J6
J3
ROC/7
17TES0700
SND IN - BLUE
17TES0413
FA2100
SOFTWARE UPLOAD
CABLE ASSEMBLY
17TES0058
(use for software
uploading only)
L-SPKR *
J6
RIU AUDIO OUTPUT
(SPKRS)
RECORDER INTERFACE
CABLE ASSY. 17TES0418
(FA2100‐CICC/2) COMPUTER
INTERFACE COMMUNICATIONS CABLE
ASSY. 17TES0072
* Note: Speakers are optional for ROC/7.
To order speakers from L-3AR use: p/n:
17TES0425 (110V) or 17TES0426 (220V)
CVR RECORDER
Figure 135. ROC/7 with CVR Automated Test Station Software (CATS 2.0)
FA2100CVR TEST SETUP − ROC/7’s DMF: Post Feb. 2015.
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B.
READ−OUT CENTER/7 (ROC/7) − Sound Card Setup
(1)
Double−click the CVDR Test icon on the ROC to start the software. The application will launch with the Channels control screen displayed, as illustrated in
Figure 136.
Figure 136. CATS, Channels Control Screen
(2)
In the Channels control screen, click OK. The Channels control screen will disappear.
(3)
Click the Volume control icon (it is the icon that looks like a speaker). The
Volume Mixer − Speakers (SB Audigy) control displays, see Figure 137.
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Figure 137. Volume Control
(4)
Under Applications, click Sound Systems, then click the Recording tab. This
will display the Sound control window illustrated on the following page.
Figure 138. Sound Control, Recording
(5)
Select the Recording tab.
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(6)
Highlight and select Line−in.
(7)
Click on Properties.
Figure 139. Line−In Properties, Line−In Level
(8)
Select the Levels tab.
(9)
Make sure that the Line−In level is set at 100 (move the Line−In slider to
maximum.)
(c)
Click on OK.
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Figure 140. Sound, Playback Devices
(10) Click on the Playback tab.
(11) Highlight Speakers.
(12) Click on Properties.
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Figure 141. Speaker Properties, Levels
(13) Select the Levels tab.
(14) Make sure Playback Control is set at 100. (move the Playback Control slider
to its maximum setting)
(15) Make sure that the four remaining controls, Microphone, Line−In, Auxiliary,
and S/PDIF−In are all muted. Volume slider levels do not need modification
since these input volumes have been muted.
(16) Click OK.
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Figure 142. Volume Mixer, Speaker Levels
(17) In the Volume Mixer, make sure both sliders are all the way up.
(18) Close the Volume Mixer.
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C.
READ−OUT CENTER/7 (ROC/7) − CATS Autotest
CAUTION:Ensure power is removed from the the RIU before proceeding. If the cable, p/n:
17TES0418 is connected to rear of the unit with the power applied to the RIU,
the RIU may be damaged.
CAUTION:Only connect DC OR AC input voltage. Do not connect both input voltages at
the same time. Connecting both types of input voltages simultaneously will
result in damage to the RIU.
NOTE: The autotest can be performed using DC or AC applied to the RIU.
When autotesting using DC power, proceed to CATS Autotest using DC power paragraph C.(1). when autotesting using AC power,
proceed to CATS Autotest using AC power paragraph C.(2). When
autotesting using both DC and AC power,to CATS Autotest using
AC and DC power paragraph C.(2).
(1)
ROC/7 − CATS Autotest using DC power
To perform the CATS Autotest using DC power only, follow the procedures below:
NOTE:
(a)
Ensure that the RIU has no power applied, power is removed if not already done. Connect a CVR to the RIU using the cable, p/n:17TES0418
(ROC/7) for the recorder rear connector and cable, p/n:17TES0072 for the
recorder front connector.
(b)
If the power supply does not include a built−in multimeter, set up an inline
RMS multimeter. Set to DC amps
(c)
Apply power to the RIU using 28 Vdc.
(d)
If the CATS test page is not shown, click the L-3 CVDR Test icon on the
Windows desktop.
(e)
Click the Ok button on the Monitor Audio Channel pop-up menu.
(f)
From the Menu bar, click on Power and select Recorder Interface Reset
from the drop down menus.
This will load the Altera chip in the RIU unit. Observe the “connecting to the recorder” status window appears.
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Observe
Figure 143. CATS, Connecting Pop-Up
(g)
On the tool bar, select Power.
Figure 144. CATS, Power Toggle
NOTE:
When DC power is applied verify the appropriate LED is lit up on
the RIU.
(h)
Click on the Information tab in the Test section of the menu.
(i)
Enter appropriate information into Department, Part Number, and Serial
Number fields.
(j)
On the tool bar, select Start Test.
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Figure 145. CATS, Start Test Toggle
(k)
In the “Test Mode and Options” dialog box, select either Return−to−Service or Selectable Test Options, then click on OK.
Figure 146. CATS, Test Mode and Options Screen
NOTE:
If a full return to service test is not desired then select the “Selectable Test Options” radio button and choose the test options
desired. Figure 147 will appear as confirmation.
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NOTE:
Figure 147 is only displayed if “Selectable Test Option” is chosen from the CATS, Test Mode and Options Screen.
Figure 147. CATS, CVDR Test Confirmation
NOTE:
Follow the instructions displayed in the confirmation window.
(l)
Read and click on Yes.
Figure 148. CATS, CVDR Warning Message
(m) Remove front cable and click on OK.
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Figure 149. CATS, CVDR Instruction Window
(n)
Read the current DC amps value from the built-in multimeter on the power
supply or from the inline RMS multimeter. And enter in the value in amps
in window and click on OK.
Figure 150. CATS, Power Test Input
(o)
Read the current DC amps value from the built-in multimeter on the power
supply or from the inline RMS multimeter. And enter in the value in amps
in window and click on OK.
Figure 151. CATS, Power Test Input
(p)
Connect the recorder front cable and click on OK.
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Figure 152. CATS, CVDR Instruction Window
(q)
Observe the Fault History Log window appears. Select Print if you want to
save the fault history or Close to continue.
Figure 153. CATS, CVDR Fault History Log
(r)
Click on Yes on the dialog box to clear the fault logs.
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Figure 154. CATS, CVDR Clear Fault Log Confirmation
(s)
Click on Yes on the dialog box to clear the latched faults and fault history
log.
Figure 155. CATS, CVDR Clear Latched Faults and Log Confirmation
(t)
Click on Ok.
Figure 156. CATS, CVDR Clear Latched Faults and Log Successful
(u)
Observe the Fault History Log window appears. Select Print if you want to
save the fault history or Close to continue.
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Figure 157. CATS, CVDR Fault History Log
(v)
Click on Yes. The autotest will now proceed in completing the autotest
which will take approximately 30 minutes or less.
Figure 158. CATS, Continue Test Confirmation
(w) At the end of the test, save the report by selecting File => Test Report =>
Save Report.
NOTE: The test report is named with the part number of the Unit Under Test and
the serial number provided in the Information section of the test. The test
report is located in the following default location: C:\Program
Files\L−3Com\CVRTester\Reports. This file is in an ASCII text file format.
(x)
If the autotest is successful, clear the fault history log by the pull down
menu, click on Test=>Clear Fault History.
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Figure 159. CATS, Test Results Screen
CAUTION:Ensure power is removed from the the RIU before proceeding. If the cable, p/n:
17TES0418 is connected to rear of the unit with the power applied to the RIU,
the RIU may be damaged.
CAUTION:Only connect DC OR AC input voltage. Do not connect both input voltages at
the same time. Connecting both types of input voltages simultaneously will
result in damage to the RIU.
(2)
ROC/7 − CATS Autotest using AC power
To perform the CATS Autotest using AC power only, follow the procedures below:
(a)
Ensure that the RIU has no power applied, power is removed. If not already done. Connect a CVR to the RIU using the cable, p/n:17TES0418
(ROC/7) for the recorder rear connector and cable , p/n:17TES0072 for
the recorder front connector.
(b)
If the power supply does not include a built−in multimeter, set up an inline
RMS multimeter. Set to AC amps
(c)
Apply power to the RIU using 115 Vac, 400Hz.
(d)
If the CATS test page is not shown, Click the L-3 CVDR Test Icon on the
Window desktop.
(e)
Click the Ok button on the Monitor Audio Channel Pop-up menu.
(f)
From the Menu Bar, click on Power and select Recorder Interface Reset
from the drop down menus.
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Observe
Figure 160. CATS, Connecting Pop-Up
(g)
NOTE:
From the menu bar, select Power ==> Recorder Interface Reset.
This will load the Altera chip in the RIU unit. Observe the “connecting to the recorder” status window appears.
(h)
On the tool bar, select Power.
Figure 161. CATS, Power Toggle
NOTE:
When AC power is applied verify the appropriate LED is lit up on
the RIU.
(i)
Click on the Information tab in the test section of the menu.
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(j)
Enter appropriate information into Department, Part Number and Serial
Number fields.
(k)
On the tool bar, select Start Test.
Figure 162. CATS, Start Test Toggle
(l)
In the “Test Mode and Options” dialog box, select either Return-to-Service or Selectable Test Options, and then click on OK.
Figure 163. CATS, Test Mode and Options Screen
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NOTE:
If a full return to service test is not desired then select the “Selectable Test Options” radio button and choose the test options
desired.
NOTE:
Figure 164 is only displayed if you select “Selectable Test Option” from the CATS, Test Mode and Options Screen.
Figure 164. CATS, CVDR Test Confirmation
NOTE: Follow the instructions in Figure 165 as displayed by the software.
(m) Read and click on Yes.
Figure 165. CATS, CVDR Warning Message
(n)
Remove front cable and click on OK.
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Figure 166. CATS, CVDR Instruction Window
(o)
Read the current AC amps value from the built-in multimeter on the power
supply or from the inline RMS multimeter. And enter in the value in amps
in window and click on OK.
Figure 167. CATS, Power Test Input
(p)
Read the current AC amps value from the built-in multimeter on the power
supply or from the inline RMS multimeter. And enter in the value in amps
in window and click on OK.
Figure 168. CATS, Power Test Input
(q)
Connect the recorder front cable and click on OK.
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Figure 169. CATS, CVDR Instruction Window
(r)
Observe the Fault History Log window appears. Select Print if you want to
save the fault history or Close to continue.
Figure 170. CATS, CVDR Fault History Log
(s)
Click on Yes on the dialog box to clear the fault logs.
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Figure 171. CATS, CVDR Clear Fault Log Confirmation
(t)
Click on Yes on the dialog box to clear the latched faults and fault history
log.
Figure 172. CATS, CVDR Clear Fault Log Confirmation
(u)
Click on Ok.
Figure 173. CATS, CVDR Clear Latched Faults and Log Successful
(v)
Observe the Fault History Log window appears. Select Print if you want to
save the fault history or Close to continue.
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Figure 174. CATS, CVDR Fault History Log
(w) Click on Yes. The autotest will now proceed in completing the autotest
which will take approximately 30 minutes or less.
Figure 175. CATS, Continue Test Confirmation
(x)
At the end of the test, save the report by selecting File => Test Report =>
Save Report.
NOTE: The test report is named with the part number of the Unit Under Test and
the serial number provided in the Information section of the test. The test
report is located in the following default location: C:\Program
Files\L−3Com\CVRTester\Reports. This file is in an ASCII text file format.
(y)
If the autotest is successful, clear the fault history log by the pull down
menu, click on Test=>Clear Fault History.
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Figure 176. CATS, Test Results Screen
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D.
READ OUT CENTER/7 (ROC/7) − Autotest Descriptions
The following provides detailed descriptions of the test performed during the autotest
function.
(1)
Power Test
Test Prompts the user for AC/DC power usage as in the following AC example:
Please remove the front panel cable from the recorder now and click ”OK”.
Please enter the AC power consumption (in amps or watts)
Please enter the AC power consumption (in amps or watts)
Please connect the recorder front panel cable and press the ”OK” button.
Example report message(s):
08:02:13 PASSED Power(AC) (Expected <= 12 watts) Results = (12 watts − 4
watts) = 8 watts
08:02:23 PASSED Power(DC) (Expected <= 11 watts) Results = (12.375 watts
– 2.2 watts) = 10.175 watts
(2)
Fault Log
Displays the current recorder fault log for user review and prompts the user:
“Clear fault log?”
Select “yes” when testing the FA2100 recorder and the full fault log is NOT to be
written to the test report.
Continue CVDR Tests?
Select “yes” to continue or “no” to stop testing.
Example report message(s)
08:02:32 PASSED Fault History
(3)
Bulk Erase
Part 1 – record audio out and verify 400 Hz bulk erase tone.
Part 2 – record audio out and verify absence of bulk erase tone during rotor data
output.
Part 3 – record audio out and verify absence of bulk erase with recording disabled.
Example report message(s):
08:02:42 PASSED Bulk Erase #1 (Expected 400 Hz) Results = 400.0 Hz
08:02:50 PASSED Bulk Erase #2 with active Rotor Speed (Expected <> 400
Hz) Results = 123.0 Hz
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08:02:58 PASSED Bulk Erase #3 with No Recording (Expected <> 400 Hz)
Results = 3334.6 Hz
(4)
Test Tone
Enable push to test and verify push to test indicator is set.
Example report message(s):
08:03:06 PASSED Test Tone (Expected Push−To−Test indicator) Results =
Push−To−Test indicator set
(5)
GMT 429
Record simulated GMT−429 data (label 125 first and label 150 second) and verify 10
good patterns are recorded for each label.
Example report message(s):
08:03:22 PASSED GMT 429 (Label 125) (Expected 10 patterns) Results = 10
good patterns 08:03:42 PASSED GMT 429 (Label 150) (Expected 10 patterns)
Results = 10 good patterns
(6)
Rotor Speed
Part 1 – Record simulated 6000 Hz rotor speed data and verify data is within 2% of
sent frequency.
Part 2 – Record simulated 7 Hz rotor speed data and verify data is within 2% of sent
frequency.
Example report message(s):
08:03:52 PASSED Rotor Speed 6000 Hz (Expected 4 patterns > 5880.0 Hz <
6120.0 Hz) Results = 5998.0 Hz, 6026.4 Hz, 6026.4 Hz, 6026.4 Hz
08:04:03 PASSED Rotor Speed 7 Hz (Expected 4 patterns > 6.9 Hz < 7.1 Hz)
Results = 7.0 Hz, 7.0 Hz, 7.0 Hz, 7.0 Hz
(7)
Channel Balance
Record simulated 1000 Hz ½ reference level data for each channel 1,2,3 and 4 and
verify amplitude all within 3 dB.
Record simulated 1000 Hz 1/10 reference level data for each channel 1,2,3 and 4
and verify amplitude all within 3 dB.
Example report message(s):
08:04:52 PASSED Channel Bal 1000 Hz 0.5 ref (All within 3 dB except HQC)
Results = HQ1 5.2 /HQ2 5.3 /HQ3 5.1 /HQC 5.1 /SQV1 5.0 /SQV2 5.4 /SQV3
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5.4 /SQC −56.6 dBV
08:05:40 PASSED Channel Bal 1000 Hz 0.1 ref (All within 3 dB except HQC)
Results = HQ1 −8.3 /HQ2 −8.2 /HQ3 −8.4 /HQC −9.4 /SQV1 −8.0 /SQV2 −8.1
/SQV3 −8.1 /SQC −293.8 dBV
(8)
Frequency Response
Record simulated 150 Hz ½ reference data for each channel 1,2,3 and 4.
Record simulated 1000 Hz ½ reference data for each channel 1,2,3 and 4.
Record simulated 3500 Hz ½ reference data for each channel 1,2,3 and 4.
Record simulated 5000 Hz ½ reference data for channel 4.
Record simulated 6000 Hz ½ reference data for channel 4.
Verify amplitude all within 6 dB.
Example report message(s):
08:06:28 Frequency Resp 150 Hz 0.5 ref Results = HQ1 3.6 /HQ2 3.8 /HQ3 3.5
/HQC 1.4 /SQV1 3.9 /SQV2 3.9 /SQV3 3.9 /SQC 3.9 dBV
08:07:15 Frequency Resp 1000 Hz 0.5 ref Results = HQ1 5.2 /HQ2 5.3 /HQ3
5.1 /HQC 5.1 /SQV1 5.4 /SQV2 5.4 /SQV3 5.4 /SQC 5.4 dBV
08:08:02 Frequency Resp 3500 Hz 0.5 ref Results = HQ1 3.3 /HQ2 2.9 /HQ3
2.5 /HQC 5.1 /SQV1 3.7 /SQV2 3.7 /SQV3 3.8 /SQC 3.5 dBV
08:08:12 Frequency Resp 5000 Hz 0.5 ref Results = HQC 4.9 dBV
08:08:23 Frequency Resp 6000 Hz 0.5 ref Results = HQC 4.9 dBV
08:08:23 PASSED Frequency Resp (All within 6 dB)
(9)
Signal to Noise and Distortion
Record simulated data at each of the following frequencies once at 1.0 reference
level and again at 1/10 reference). Verify HQ data is > 24.0 dB and SQ data is >
20.0 dB.
Return To Service Frequencies:
Frequencies for HQ1, HQ2, HQ3, HQCAM, SQV1, and SQCAM are:
150, 1000 and 3500 Hz.
Frequencies for HQCAM only are: 5000 and 6000 Hz.
Selectable Test Options Frequencies:
Frequencies for HQ1, HQ2, HQ3, HQCAM, SQV1, and SQCAM are:
150, 200, 250, 315, 400, 500, 630, 800, 1000, 1250, 1600, 2000, 2500
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and 3500 Hz.
Frequencies for HQCAM and SQCAM only is 3150 Hz.
Frequencies for HQCAM only are:
4148 and 6000 Hz.
Example Return to Service report message(s):
11:24:20 PASSED SN+D 150 Hz 1.0 ref (Expected HQ > 24.0 dB SQ > 20.0 dB)
Results = HQ1 34.6 /HQ2 34.4 /HQ3 34.8 /HQC 36.4 /SQV1 30.9 /SQV2 31.0
/SQV3 30.6 /SQC 31.4 dB
11:26:44 PASSED SN+D 1000 Hz 1.0 ref (Expected HQ > 24.0 dB SQ > 20.0 dB)
Results = HQ1 27.0 /HQ2 26.9 /HQ3 26.7 /HQC 32.4 /SQV1 23.3 /SQV2 23.0
/SQV3 23.3 /SQC 23.3 dB
11:29:09 PASSED SN+D 3500 Hz 1.0 ref (Expected HQ > 24.0 dB SQ > 20.0 dB)
Results = HQ1 30.6 /HQ2 30.2 /HQ3 30.4 /HQC 30.3 /SQV1 25.0 /SQV2 25.2
/SQV3 24.9 /SQC 25.5 dB
11:30:35 PASSED SN+D 5000 Hz 1.0 ref (Expected HQC > 24.0 dB) Results = HQC
30.6 dB
11:31:07 PASSED SN+D 6000 Hz 1.0 ref (Expected HQC > 24.0 dB) Results = HQC
27.7 dB
NOTE:
Running the Signal to Noise and Distortion test in the Selectable
Test mode will perform additional tests at 200, 250, 315, 400,
500, 630, 800, 1250, 1600, 2000, 3150 and 4000 Hz.
(10) Crosstalk Audio
Record simulated 1000 Hz data for each channel 1,2,3 & 4 and calculate difference
between driven and non−driven channels. Verify difference is less than −40 dB.
Example report message(s):
08:41:34 PASSED Crosstalk (Audio) 1000 Hz 1.0 ref (Expected Driven − Non−
Driven < −40 dB) Results = HQ1 11.2 /HQ2 −101.0 /HQ3 −109.9 /HQC −128.1
/SQV 11.4 /SQC −84.4 dBV
08:41:49 PASSED Crosstalk (Audio) 1000 Hz 1.0 ref (Expected Driven − Non−
Driven < −40 dB) Results = HQ1 −101.3 /HQ2 11.2 /HQ3 −115.3 /HQC −107.5
/SQV 11.4 /SQC −72.3 dBV
08:42:04 PASSED Crosstalk (Audio) 1000 Hz 1.0 ref (Expected Driven − Non−
Driven < −40 dB) Results = HQ1 −304.8 /HQ2 −127.4 /HQ3 11.1 /HQC −104.4
/SQV 11.4 /SQC −72.0 dBV
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08:42:19 PASSED Crosstalk (Audio) 1000 Hz 1.0 ref (Expected Driven − Non−
Driven < −40 dB) Results = HQ1 −304.9 /HQ2 −304.9 /HQ3 −111.7 /HQC 11.1
/SQV −72.4 /SQC 11.4 dBV
(11) Crosstalk Data
This is a test for CVDR recorders where both flight data and voice data are being
recorded.
A Channel Balance is performed prior to the cross talk data test to determine and
store results for each channel 1,2,3 and 4.
Record 6000 Hz simulated rotor data and simulated GMT 429 and calculate channel results minus channel balance results. Verify difference is less than −34 dB
Example report message(s):
08:43:07 PASSED Channel Bal 1000 Hz 1.0 ref (All within 3 dB) Results = HQ1
11.2 /HQ2 11.2 /HQ3 11.0 /HQC 11.1 /SQV1 11.0 /SQV2 11.3 /SQV3 11.4
/SQC 11.5 dBV
08:43:23 PASSED Crosstalk (Data) 6000 Hz 1.0 ref (Expected Crosstalk −
Channel Bal < −34 dB) Results = HQ1 −304.9 /HQ2 −125.7 /HQ3 −304.8 /HQC
−49.8 /SQV −83.4 /SQC −82.8 dB
(12) FSK Time
This test cycles power to recorder to reset for FSK input then records simulated
16000 sps FSK data and then simulated GMT 429 data (label 150) first with channel
1 output and again with channel 3 output. It verifies 9 good FSK data patterns and a
switch to 9 good GMT 429 data patterns for each channel 1 and channel 3.
Example report message(s):
14:50:07 PASSED FSK Time HQ1 (Playback)(Expected 9 patterns) Results = 9
good patterns
14:50:07 PASSED FSK Time HQ1 (GMT Switch) (Expected 9 patterns) Results
= 9 good patterns
14:50:53 PASSED FSK Time HQ3 (Playback)(Expected 9 patterns) Results = 9
good patterns
14:50:53 PASSED FSK Time HQ3 (GMT Switch) (Expected 9 patterns) Results
= 9 good patterns
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(13) Audio Out Monitor
Record simulated 1000 Hz data for each channel 1,2,3 and 4 and verify amplitudes
by part number:
Example report message(s):
08:26:43 PASSED Audio Out Monitor 1000 Hz (Expected 2.45 +/−20 percent
VRMS) Results = HQ1 2.319 /HQ2 2.338 /HQ3 2.317 /HQC 2.355 VRMS
(14) Signal To No Signal
Record simulated 1000 Hz data for each channel 1,2,3 and 4 and store results; then
record no data for channels 1,2,3 and 4 and compare differences between signal
data results and no signal data results. Verify difference is less than −48 dB.
Example report message(s):
08:47:12 PASSED Sig To No Sig 0 Hz 1.0 ref (Expected HQ < −48 dB SQ <
−40 dB) Results = HQ1 −304.9 /HQ2 −122.6 /HQ3 −108.4 /HQC −115.4 /SQV1
−82.7 /SQV2 −82.2 /SQV3 −80.7 /SQC −85.0 dB
(15) Shutdown
Remove recorder power and verify recorder continues to operate for > 9 and < 10
minutes after power is removed and shutdown is terminated following a push to test.
Part 1 – enable delayed shutdown.
Part 2 – verify shutdown is detected (CVR fault set) after > 9 and < 10 minutes.
Part 3 – verify shutdown is terminated following a push to test and recording is resumed.
Example report message(s):
08:47:13 PASSED Shutdown Initialization (Shutdown issued − Please wait
9−10 minutes)
08:56:14 PASSED Shutdown CVDR Fault (Expected CVDR fault to occur) Result = CVDR Fault
08:56:27 PASSED Shutdown Push−to−Test (Expected 1000 Hz frequency)
Results = 999.9 Hz
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(16) Capacitor
Power off recorder and verify recorder is still powered after 200 milliseconds but not
powered after 2 seconds.
Example report message(s):
08:56:32 PASSED Capacitor − GSE powered after 200 milliseconds but not
after 2 seconds
(17) Data Link
Record simulated data link messages and verify 10 good data link messages.
Example report message(s):
08:58:00 PASSED DLR (Expected 10 patterns) Results = 10 good patterns
NOTE:
If the L−3 DL_RTS software utility was previously used to write an
incrementing patterns into recorder memory then the Data Link test
will fail until this incrementing pattern is overwritten with simulated
data link messages.
(18) OMS
Read the OMS status words and verify CVR fault status and CVR part number and
serial number.
Example report message(s):
08:59:00 PASSED OMS Part 1 (Expected OMS Status to match)
08:59:10 PASSED OMS Part 2 (Expected OMS Part and Serial Numbers to match)
Results = pn2100−1025−22 sn000000000
(19) RIPS
Clear the FA2100 fault log and existing faults that might prevent RIPS test success.
Remove FA2100 recorder power and verify the recorder continues to operate for
over 9 minutes after power is removed.
Example report message(s):
09:00:02 RIPS Initialization (Power has been removed. Please wait 9 minutes)
09:09:15 PASSED RIPS (Expected no CVR Fault for over 9 minutes) Results =
No CVR Fault after power removed for over 9 minutes
(20) FRED
Verify FA2100 Flight Recorder Electronic Documentation (FRED) file exists or can be
written.
Example report message(s):
09:09:30 PASSED FRED – Engineering Units File CRC Verified
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(21) FDR
Clear the FA2100 fault log and existing faults that might prevent FDR test success.
Record simulated flight data and verify good flight data was recorded.
Example report message(s):
09:11:00 PASSED FDR Test Results = 1 minute(s) of good data
NOTE:
The Data Link test, OMS test and FDR tests requires a CATS V2 RIU
and rear panel cable.
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7. READ−OUT CENTER/7 (ROC/7) − AUDIO DOWNLOAD & PLAYBACK
NOTE:
ROSE 4.0 or higher on a ROC or RAU is recommended to download
directly from a CVR and convert audio into a .WAV for playback. Refer to the Read-Out Support Equipment / Recorder Interface Software
version 4.0 or Higher Operator’s Manual, p/n 165E1696-03, to Retrieve Flight Data and / or Audio Data from a Recorder.
NOTE:
When decompressing Standard Quality Audio from a 2−Hr.
FA2100CVR, p/n: 2100−1020−XX, pre Hardware MOD−DOT #7, you
must have the RIU powered and the Altera chip reset using the Power
−> RIU Interface Reset command.
This is required because hardware inside the RIU is used for converting of the 2−bit compressed Standard Quality Combined (SQV)
and Standard Quality CAM (SQC) channels.
This is not a requirement for the High Quality Channels (HQV & HQC)
because this 3−bit compression is converted using the CATS software. The FA2100CVRs that have Hardware MOD−DOT #7 installed
have full two hour High−Quality for all four audio channels as does
all 30−Minute FA2100CVRs.
(1)
Click on the Copy button. Set the File Name to Filename.cvdr (the system will
use a default file name with the part number of the recorder and serial number
that was entered in the information fields of the test section).
(2)
Click on the Save button.
(3)
Select either Full Audio Data Download or Copy data from last XX Hrs. XX
Mins. Click OK. Copying of the data will start.
(4)
When the “Copy Data is Complete” box is shown click on Yes. On the Decompression Options menu select HQV1 through HQV3 and HQC. If using an
FA2100CVDR, p/n: 2100−1020−XX, pre MOD−DOT #7 unit also select the
Standard Quality Audio data SQV & SQC. Click OK.
(5)
Click on the Microphone button. Select the Left Channel to be HQV1 and the
Right Channel to be HQC. Click OK to exit the dialog box.
(6)
Click on the Play button. Confirm that the display changes and that the speakers output the audio. Click on the Stop button when satisfied that the data is
being played back properly.
(7)
Click on File => Exit to leave CVR Tester.
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to the restrictions on the cover page of this document.
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FA2100CVR
Table 102. 17TES0700
Part Number
READOUT CENTER/7 (ROC/7) − Parts List
Description
Mfg.
17TES0700
Read-Out Center/7 − Full CVDR/FDR Configuration
(The following items are included with the ROC/7).
L-3 Com
17TES0710
Recorder Interface Unit (RIU)
L-3 Com
17TES0411
Cable, RIU to AC Power In
L-3 Com
17TES0412
Cable, RIU to DC Power In
L-3 Com
17TES0413
Cable, RIU to Sound Card (2 ea.)
L-3 Com
17TES0415
Cable, RIU to USB
L-3 Com
17TES0417
Cable Assembly, Audio Setup
L-3 Com
17TES0418
Cable, RIU to CVR
L-3 Com
17TES0420
CATS Software, FA2100, V. 2.0
L-3 Com
17TES0070
CICC/2 Assembly
L-3 Com
17TES0072
Cable Assembly, FA2100−CICC/2 (2 ea.)
L-3 Com
17TES0042
Cable Assembly, Recorder Interface
L−3 Com
17TES0057
Cable Assembly, CVDR Interface
L−3 Com
17TES0071
Cable Assembly, F1000−CICC/2
L−3 Com
17TES0321
Read-Out System Equipment Software (ROSE 4.5)
L-3 Com
17TES0058
FA2100 Software Upload Cable Assembly
L-3 Com
883E4557−00
CD, Soundblaster Audigy
L-3 Com
17TES0076
RUFS Recorder Interface, USB
L−3 Com
17TES0425
Speakers (2), 110 Vac (U.S. − Standard)
Optional
17TES0426
Speakers (2), 220 Vac (Non−U.S. − Standard)
Optional
8. Underwater Locator Beacon Testing
Recommended Method to Test the 90-Day Underwater Locator Beacon
The 17TES0015 is a battery operated heterodyne type receiver that operates at an ultrasonic frequency of 37.5 kHz. The test set is a self-contained, hand held functional
tester for testing 90−Day and 30−Day Underwater Locator Beacons. Use the internal
microphone and loudspeaker to perform an operational test on a beacon without removing it from the recorder’s CSMU Mount. The test set can also be used to perform a
voltage measurement for testing the replacement battery within a Beacon.
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Table 103. Underwater Locator Beacon Test Using L−3AR Test Set P/N:
17TES0015
PROCEDURE
This test should be performed after the 90−Day Beacon is installed. It verifies the proper
operation of the Beacon after mounting on the CSMU.
1) Turn the test set ON using the small slide switch located on the left side of the housing.
2) If the display reads LB, the test set battery voltage has fallen below the level required for
operation, and the 9−Volt battery should be replaced.
3) To test the Beacon battery voltage, attach the test probe clip to the Beacon case. The clip
has a spring action that will allow it to slip over the housing on the Beacon. Place the tip
of the probe in contact with the metal pad at the center of the water switch.
4) Read the battery voltage from the test set display. If the battery voltage is at or above
2.97 volts, the battery is operable. If the battery voltage is below 2.97 volts, remove the
Beacon from service.
5) To perform an operational test of the Beacon, place the probes on the Beacon as
described above and press the red button on the test set (the display will be blank during
this operation).
6) If the Beacon is operating properly, a pinging sound will be audible from the test set
speakers. If hearing is difficult due to background noise, repeat the test in a quieter area.
7) Turn off the test set, and remove the Beacon from the test probe clip.
8) If required, record the Beacon’s serial number and expiration date on the appropriate
recorder data record.
Alternate Method to Test the 90-Day Underwater Locator Beacon
Note that using this method requires the use of a 10 Mohm impedance voltmeter that is
not included in the test set.
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FA2100CVR
Table 104. Underwater Locator Beacon Test Using Test Set P/N: 42A12( )
and 10 Mohm High Impedance Voltmeter
PROCEDURE
This test should be performed after the 90−Day Beacon is installed. It verifies the proper
operation of the Underwater Locator Beacon after mounting on the CSMU.
1) To test the Beacon battery voltage, place the negative lead of the high impedance
voltmeter on the metal pad at the center of the water switch and the positive lead on the
Beacon case.
2) Measure the battery voltage. If the battery voltage is at or above 2.97 volts, the battery is
operable. If the battery voltage is below 2.97 volts, remove the Beacon from service.
3) To perform an operational test of the Beacon, turn on the test set by rotating the front
panel GAIN control clockwise until it clicks.
4) On the front panel of the test set, set the INT.-EXT. switch to INT.
5) Rotate TUNING control to a setting between 35 and 40 kHz.
6) Use a metal braid, or other flexible metal conductor, to temporarily short the metal pad at
the center of the water switch to the Beacon case, and activate the unit.
7) Make sure that the test set’s microphone and the Beacon are in close proximity of each
other with unobstructed, line−of−sight between them. This will ensure that the test set will
detect the proper output of the Beacon.
8) If the Underwater Locator Beacon is functioning properly, it will emit inaudible, ultrasonic
sound waves that the test set will receive and reproduce as repetitive beeps through the
test set’s speakers.
9) Remove the metal conductor to stop the short and turn off the test set.
10) If required, record the Beacon’s serial number and expiration date on the appropriate
recorder data record.
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COMPONENT MAINTENANCE MANUAL
FA2100CVR
9. MODEL FA2100CVR TROUBLESHOOTING
WARNING: VOLTAGES CAPABLE OF FATAL INJURY ARE PRESENT AT THE RECORDER
INPUT CONNECTOR. ONLY QUALIFIED MAINTENANCE TECHNICIANS SHOULD
PERFORM THE FOLLOWING MAINTENANCE.
CAUTION: THE FA2100CVR’s PRINTED WIRING ASSEMBLIES (PWA) CONTAIN DEVICES
SENSITIVE TO ELECTROSTATIC DISCHARGE (ESD). PERSONNEL HANDLING A
PRINTED WIRING BOARD SHOULD COMPLY WITH PROPER ESD HANDLING
PROCEDURES. FAILURE TO DO SO MAY RESULT IN DAMAGE TO THE ESD
SENSITIVE DEVICES RENDERING THE PRINTED WIRING BOARD USELESS.
PRIOR TO HANDLING A PRINTED WIRING BOARD, ENSURE PROPER
PERSONNEL GROUNDING TECHNIQUES ARE USED. ALSO, ENSURE THAT ALL
PRINTED WIRING ASSEMBLIES BOARDS ARE PLACED INTO STATIC SHIELDING
CONDUCTIVE BAGS WHEN HANDLING OR STORING.
Table 105. FA2100 CVR Fault Code Corrective Actions
Failure Mode
Corrective Action
cde0
An invalid partition map
was found
1) Remove Memory.
09d7
The SMP Check timed out 1) ck cables.
waiting for audio
2) If fault codes persist, then remove and replace
channelizer to shutdown.
Audio Compressor PWA, p/ns: 205E3977-( ).
3) Run autotest & recheck recorder status.
Fault Code
4) Remove and replace Acquisition Processor PWA,
PN: 205E2502‐( ).
89d2
Next power−up will
generate a CVR Bad
Indices (latched fault).
690X, 89d2, Power supply failure
0X0855
combined with CVR bad
indices and read after
write errors
6900
18v Power Supply Failure
1) Remove and replace Acquisition Processor PWA,
PN: 205E2502‐( ).
2) Run autotest & recheck recorder status.
3) If fault codes still present in status report, then
return the recorder to factory for repair.
1) Remove and replace Acquisition Processor PWA,
PN: 205E2502‐( ).
2) Run autotest & recheck recorder status.
3) If fault codes still present in status report, then
return the recorder to factory for repair.
6901, 6902, BITE Error: Negative 12 &
6904
5 volt & 5 Volt (VCC)
power supply failure
6901
Negative 12 volt power
supply failure.
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FA2100CVR
Table 105. FA2100 CVR Fault Code Corrective Actions (Continued)
Fault Code
Failure Mode
6902
Negative 5 volt power
supply failure.
6903
12 volt (VPP) power
supply failure
51d9
An underflow occurred in
the TDM high priority
queue.
Corrective Action
see previous page
1) Remove and replace Acquisition Processor PWA,
PN: 205E3977-XX‐( ).
2) Run autotest & recheck recorder status.
3) If fault codes still present in status report, then
return the recorder to factory for repair.
1) Remove and replace Audio Compressor PWA,
51d9, 85da, TDM Hi−Priority
PN: 205E3977‐( ).
d9c6, 89d7 Underflow, TDM AC RX
Overflow, CVR Audio
2) Run autotest & recheck recorder status.
Packet Timeout, CVR Bad 3) If fault codes still present in status report, then
Indices, Audio Packet
return the recorder to factory for repair.
Shutdown Timeout.
59db
System Error: CVR test
failed. Test tone failed
1) Remove and replace Audio Compressor PWA,
PN: 205E3977‐( ).
2) Run autotest & recheck recorder status.
3) If fault codes still present in status report, then
return the recorder to factory for repair.
1) Remove and replace Acquisition Processor PWA,
85da, 51d9, 85da: An overflow
PN: 205E2502‐( ).
0855, 6900 occurred in the audio
channelizer receive buffer. 2) Run autotest & recheck recorder status.
3) If fault codes still present in status report, then
51d9: An underflow
return the recorder to factory for repair.
occurred in the TDM high
priority queue.
0855: A CVR flash
memory read−after−write
error occurred.
6900: 18 volt power
supply failed.
85da
An overflow occurred in
the audio channelizer
receive buffer.
1) Remove and replace CSMU, p/n: 253E3977‐( ).
2) Run autotest & recheck recorder status.
3) If fault codes still present in status report, then
return the recorder to factory for repair.
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FA2100CVR
Table 105. FA2100 CVR Fault Code Corrective Actions (Continued)
Fault Code
Failure Mode
Corrective Action
885e
The total number of CVR
errors exceeded the
allowable threshold.
8850,
0855
Flash Error: A flesh
memory read−after−write
error occurred
1) Run Memory test.
2) If fault codes persist, then remove and replace
CSMU, p/n: 253E1568‐( ).
3) Run autotest & recheck recorder status.
89d1
The non volatile memory
contains bad CRC.
89d1
The non−volatile memory
on the CVR has a bad
CRC −This problem is
usually related to a bad
chip on the Acquisition
Processor.
89d2
The non volatile memory
contains bad indices.
89d2, 09d4
89d2: System Error: The
non−volatile memory on
the CVR contains bad
indices.
4) If fault codes still present in status report, then
return the recorder to factory for repair.
1) Remove and replace Acquisition Processor PWA,
p/n: 205E2502‐XX.
2) Run autotest & recheck recorder status.
3) If fault codes still present in status report, then
return the recorder to factory for repair.
09d4: System Error : The
CVR had to wait for a
flash memory block to
erase.
89d6
89d6, 09d7
System Error: The SMP
timed out waiting for an
audio packet to arrive
89d6: System Error: The
SMP timed out waiting for
an audio packet to arrive.
09d7: System Error: The
SMP timed out waiting for
audio channelizer to
shutdown.
89d6, 6901, System Error: The SMP
6902, 6904 timed out waiting for an
audio packet to arrive.
690X: BITE Errors: power
supply failures.
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FA2100CVR
Table 105. FA2100 CVR Fault Code Corrective Actions (Continued)
Fault Code
Failure Mode
Corrective Action
89d7
The SMP timed out
waiting for audio
channelizer to shutdown.
1) Remove and replace Acquisition Processor PWA,
p/n: 205E3977‐XX.
2) Run autotest & recheck recorder status.
3) If fault codes still present in status report, then
return the recorder to factory for repair.
8453
1) Remove and replace CSMU, p/n: 253E1568‐( ).
Read After Write Errors,
Too Long Erase Event and 2) Run autotest & recheck recorder status.
Error.
3) If fault codes still present, remove and replace
Acquisition Processor PWA,
p/n: 205E2502-( ).
The unit took too long to
4) Run autotest & recheck recorder status.
erase.
5) If fault codes still present in status report, then
return the recorder to factory for repair.
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FA2100CVR
10. FA2100CVR SOFTWARE UPLOAD PROCEDURE
Computer Interface Communications Cable/2 (CICC/2) is shown in Figure 177. In the
event that the original Acquisition Processor (AP) PWA, p/n: 205E1591−00 or
205E1931−00, is required to be replaced in the FA2100CVR, it will be replaced with the
Acquisition Processor PWA, p/n 205E2502−11, or −14 in the case of the 2100−1025−( ),
and the software that is required to be loaded onto this PWA. To load the software, use
the FA2100 Software Upload cable assembly, p/n: 17TES0058 and the FA2100 Software
Upload Utility software. The Upload Utility software contains a CICCLDR executable file
and a CICCIFC executable file. The CICCLDR and CICCIFC executable files are found
on the FA2100 Utility Bundle CD p/n 883E1894−01.
NOTE:
The CICC/3 with ethernet (P/N 17TES0075) cannot be used to
upload FA2100CVR software.
The Software Upload cable assembly is connected between the front panel GSE connector of the FA2100 and the CICC/2 Cable assembly, which includes the Computer Interface
Communications Cable/2 (p/n: 17TES0070) and the FA2100 to CICC/2 cable (p/n:
17TES0072).
The software upload procedure is also necessary when replacing a faulty Turbo Acquisition Processor PWA, p/n: 205E2502−10/−11 with a known good AP board from the factory, since the factory spare PWA’s are shipped without the recorder firmware preloaded.
The specific recorder software for either the 2100-1010-( ) 2100-1020-( ) or the
2100−1025−( ) CVRs will be loaded from the FA2100CVR Software Distribution CD.
Once installed, a Windows-98/XP short-cut icon linking to the CICCLDR.exe may be
placed on the desktop. To upload the recorder software perform the following procedure:
NOTE:
A.
After installing CICC loader and/or interface on Windows 7, you
must set the properties of CiccLDR.exe and/or the Ciccldr.exe to
run in compatibility mode of “Windows 98/Windows Me.”
Installing Software Upload Utility and CICC Interface Programs
NOTE:
The Software Upload Utility and the CICC Interface Programs may be loaded onto a ROC/5, ROC/6, ROC/7, RAU, or
any PC. Reference to any of these units is herein referred to
as PC.
The Software Upload utility and Interface executable programs are contained on the
CICC Utility Bundle CD. To load these programs onto a PC perform the following
steps:
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(1)
Turn ON the power to the PC.
(2)
Insert the FA2100 Utility Bundle CD 883E1894−01 into the PC. When ask to
select, Click on the “Open folder to view files using Windows Explorer” .
(3)
To install the Upload utility from the CD, click open the CICCLdr folder and then
click on the “Setup” file.
(4)
Follow the instructions on the Install Wizard and accept all defaults. The Install
Wizard will create a folder and Icons within. To check the version level of the
program right−click on the CICCLdr Icon select Properties −> Version and
verify that the version level is 3.0. Left click and hold the CICCLdr Icon and
drag it on to the desktop. There it will remain as a shortcut.
NOTE:
Note: older versions of the CICCIfc.exe program distributed
with ROSE 3.1 or lower will not work with the updated
CICC/2 Interface. Newer versions of the software are backward compatible and will work with the original CICC Interface.
(5)
To load the Interface program and to verify the upload process, perform the
following: Open up the the FA2100 Utility Bundle CD. To install the Interface
utility, click open the CICCIfc folder and then click on the “Setup” file.
(6)
Follow the instructions on the Install Wizard and accept all defaults. The Install
Wizard will create a folder and Icons within. To check the version level of the
program right−click on the CICCIfc Icon select Properties −> Version and
verify that the version level is 3.7. Left click and hold the CICCIfc Icon and drag
it on to the desktop. There it will remain as a shortcut. Remove the CD from
the PC.
(7)
Exit from Windows by selecting the START button and Shut Down. When
prompted that it is safe, turn OFF the power to the PC. (Note: Newer PCs may
automatically remove power without having to press the power switch.)
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COMPONENT MAINTENANCE MANUAL
FA2100CVR
ROSE/RI SOFTWARE
17TES0321 (CDROM)
Power
Input
Select
FA2100 SOFTWARE
DISTRIBUTION DISK
840‐EXXX‐XX
Note:
Firmware Distribution
Diskette P/N will match the
FA2100 Software Part
Number located on the
recorder 's Name Plate Label.
TO
ENHANCED
PARALLEL PORT
(EPP)
RECORDER USB FDAU
SIMULATOR (RUFS)
(RI) ADAPTER
17TES0076
CICC/2
COMPUTER INTERFACE
COMMUNICATIONS CABLE/2
17TES0070
FA2100 TO CICC/2
COMPUTER INTERFACE
COMMUNICATIONS CABLE
17TES0072
RECORDER INTERFACE (RI)
CABLE ASSY.
17TES0057
READ-OUT CENTER/5, /6 or /7
17TES0300/17TES0400/17TES0700
AC
INPUT
FA2100
SOFTWARE UPLOAD
(BOOTLOAD) CABLE ASSEMBLY
17TES0058
(use for software
uploading only)
DC
INPUT
Note:
RI = Recorder Interface.
ROSE = Read‐Out Support Equipment.
ROC = Read‐Out Center (ROC/5, /6 or /7)
Note:
The ROC rear connections shown in this diagram are for
general reference and may not reflect the exact connector
location or configuration your ROC system computer.
Note:
The 17TES0058 cable assembly should only be attached
during upload process. Not used when downloading data
or getting recorder status.
FA2100 CVR
RECORDER
Figure 177.
Typical Software Upload Setup For FA2100 Recorder with CICC/2 Cable
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FA2100CVR
B.
To upload the FA2100 Software perform the following steps:
(1)
If using the CICC/2 Cable refer to Figure 177 and perform the following steps:
(a)
Connect the FA2100 Software Upload Cable Assembly (p/n: 17TES0058)
to the FA2100 Recorder front panel GSE connector and the opposite end
to the FA2100 to Computer Interface Communications Cable/2 (CICC/2),
(p/n: 17TES0072).
(b)
Connect the opposite end of the FA2100 to CICC/2 cable to the CICC/2
(p/n: 17TES0070).
(c)
Connect the opposite end of the CICC/2 to the PC EPP parallel connector.
CAUTION:
NOTE:
(2)
Do not connect both DC and AC input voltages simultaneously or dam
age to the recorder will result.
Both the Computer Interface Communications Cable/2, p/n:
17TES0070, and the FA2100 to Computer Interface Communications Cable/2, p/n: 17TES0072, are required to upload
FA2100 software to the recorder when using the CICC/2.
At the FA2100 J1A connector, use the Recorder Interface (RI) Cable Assy, P/N
17TES0057, to connect either 115 Vac/400 Hz, or +28 Vdc to the pig−tail connectors.
Alternatively, +28Vdc power may be directly applied to J1A−9 and Ground to
J1A−17, or connect 115Vac, 400Hz to J1A pins 2 & 3.
(3)
Apply power to the FA2100CVR Recorder.
(4)
Note the SMP version and checksum value listed on the label of the FA2100
CD and ensure that the software part number is the software needed to be
loaded into the FA2100CVR recorder. If the FA2100 Software CD is unavailable, refer to Table 106.
(5)
Turn ON the power to the PC, RAU or ROC/5−ROC/6 −ROC/7 Ground Station.
NOTE:
If using a PC, proceed to step (8). If using an RAU or ROC/5
Ground Station, perform steps (6) and (7) prior to performing step (8).
(6)
At the Windows 98 or XP desktop shut down the Recorder Interface (RI) by right
clicking on the RI Icon in the Windows System Tray at the bottom right of the
screen. Select “shutdown.”
(7)
At the Windows 98 or XP desktop also shut down the FTP protocol program by
right clicking on the FTP Icon in the Windows System Tray at the bottom right of
the screen. Select “Exit”.
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FA2100CVR
(8)
Insert the FA2100 CD into the PC, RAU, or ROC/5−ROC/6−ROC−7 Ground
Station system CD.
(9)
From the Windows 98 or XP desktop, activate the (put in new PC & SW)
CICC Loader utility program by double−clicking on the CICCLdr Icon.
(10) When the CICC Loader window appears select the Browse button at the Load
Directory and set the source to “D:\.” (If it is not already present).
(11) Select the software load type by choosing the Recorder part number listed that
matches the part number found on the recorder identification label.
(12) Left click the Load button.
(13) Observe the progress window and verify that a status pop−up window appears
stating that the FA2100 loaded successfully. Note: if the load procedure was
unsuccessful, recycle power to the FA2100CVR and repeat steps (4) − (9).
NOTE:
If still unsuccessful, make sure that the address of the parallel port specified in the CICCLDR.ini file matches the address of the parallel port connected to the CICC.
(14) Turn off power from the recorder and Exit the CICC Loader utility program.
(15) Disconnect the 17TES0058 Upload Cable from the FA2100CVR Front Panel
ATE connector and the 17TES0072 CICC/2 Cable Assembly.
(16) Reconnect the 17TES0072 CICC/2 Cable Assembly to the ATE connector.
(17) Proceed to paragraph C. to verify the software upload.
C.
To Verify the Software Upload
Once the FA2100 software has been loaded it needs to be verified using the CICC
Interface Software Utility as follows:
(1)
Apply power to the FA2100CVR Recorder.
(2)
From the Windows 98 or XP desktop, activate the CICC Interface utility program by double−clicking on the CICCIfc Icon.
(3)
From the CICC Interface Menu, select the Version Command from the list and
left click the Send Command button. Observe that a pop-up window appears
showing the recorder software Part Number and SMP Checksum.
NOTE:
If the “FA2100 Command” window is disabled, make
sure that the address of the parallel port specified in
the CICCIFC.ini file is that same as the address of the
parallel port connected to the CICC.
Use or disclosure of information on this sheet is subject
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COMPONENT MAINTENANCE MANUAL
FA2100CVR
(4)
Match the listed Software Part Number and SMP Checksum with the one listed
on the recorder software distribution CD. If the software distribution CD is unavailable, refer to Table 106 for a list of checksums.
(5)
Left click the OK button and left click the X button in the upper right corner of
the CICC Loader Menu to exit the utility and return to the Windows 98 or XP
desktop.
(6)
Download fault history with PI and verify no faults.
(7)
Once the Software upload versions are validated, perform a full Return To Service test procedure as listed in Section 100 of this manual.
Table 106. FA2100CVR Software SMP Checksums
Software P/N
Recorder P/N
SMP Checksum
SMP Ver.
840-E1657-01
2100-1020-00
2100-1020-02
0X5609
6.1
840-E1657-03
2100-1020-00
2100-1020-02
0X67EE
7.4
840-E1657-04
2100-1020-00
2100-1020-02
0X313B
7.5
840-E1657-05
2100-1020-00
2100-1020-02
0XAD9F
7.9
840-E1657-06
2100-1020-00
2100-1020-02
0XA84B
8.7
840-E1657-07
2100-1020-00
2100-1020-02
0XAEF6
8.8
840-E1657-08
2100-1020-00
2100-1020-02
2100-1220-00
2100-1220-02
0XA96F
9.0
840-E1657-09
2100-1020-00
2100-1020-02
2100-1220-00
2100-1220-02
0XC62C
9.1
840-E1658-02
840-E1658-03
840-E1658-04
840-E1658-05
2100-1010-00
2100-1010-00
2100-1010-00
2100-1010-00
0X6B52
0XB9C7
0X8314
0X8F17
6.7
7.4
7.5
840-E1658-06
2100-1010-00
0X89C3
8.7
840-E1658-07
2100-1010-00
0X28E2
8.9
840-E1658-08
2100-1010-00
0X8AE7
9.0
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7.9
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
Software P/N
Recorder P/N
SMP Checksum
SMP Ver.
840-E1663-02
2100-1010-50
2100-1010-51
0X6B67
6.7
840-E1663-04
2100-1010-50
2100-1010-51
0X8329
7.5
840-E1663-05
2100-1010-50
2100-1010-51
0X8F2C
7.9
840-E1663-06
2100-1010-50
2100-1010-51
0X89D8
8.7
840-E1664-01
2100-1020-50
2100-1020-51
0X5620
6.1
840-E1664-04
2100-1020-50
2100-1020-51
0X3152
7.5
840-E1664-05
2100-1020-50
2100-1020-51
0XADB6
7.9
840-E1664-06
2100-1020-50
2100-1020-51
0X8A62
8.7
840-E1664-09
2100-1020-50
2100-1020-51
840-E3408-04
2100-1025-12
0XD857
8.1
840-E3408-05
2100-1025-02
0X046A
8.1
840-E4568-06
2100-1025-22
0XD8A2
8.5
840-E4568-09
2100-1025-22
2100-1125-02
0XF168
8.8
840-E4568-10
2100-1025-22
0X8D8E
8.9
840-E4568-11
2100-1025-22
2100-1225-22
0X6118
9.0
840-E4568-12
2100-1025-22
2100-1225-22
2100-1925-22
0X7DD5
9.1
840-E5022-02
2100-1026-02
2100-1026-22
0X6A9D
8.5
840-E5022-03
2100-1026-22
0X6A9E
8.5
840-E5022-04
2100-1026-02
2100-1026-22
0X7152
8.8
840-E5022-05
2100-1026-02
0X6BCB
9.0
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
Software P/N
Recorder P/N
SMP Checksum
SMP Ver.
840-E5022-06
2100-1026-02
2100-1226-02
0X8018
9.0
840-E5634-00
2100-1025-24
0XF6F4
8.7
840-E5634-02
2100-1025-24
0X3D09
8.9
840-E5634-03
2100-1025-24
2100-1225-24
0X9A14
9.0
840-E5634-04
2100-1225-24
0X55D8
9.1
Table 107. FA2100CVR Software FDP Checksums
Software P/N
Recorder P/N
FDP Checksum
FDP Ver.
840-E3408-04
2100-1025-02
2100-1025-12
0X44A9
1.8
840-E3408-05
2100-1025-02
2100-1025-12
0X44A9
1.8
840-E4568-06
2100-1025-22
2100-1125-02
0X486D
2.1
840-E4568-09
2100-1025-22
2100-1125-02
0X5E5E
2.3
840-E4568-11
2100-1025-22
2100-1125-02
2100-1225-22
0X5E5E
2.3
840-E4568-12
2100-1025-22
2100-1225-22
2100-1925-22
0XF9F1
2.5
840-E5022-02
2100-1026−02
0X9834
2.1
840-E5022-03
2100-1026−02
0X8190
2.1
840-E5022-04
2100-1026-02
0XEF55
2.3
840-E5022-05
2100-1026-02
0XEF55
2.3
840-E5022-06
2100-1026-02
2100-1226-02
0X8970
2.3
840-E5634-00
2100-1025-24
0X6E00
2.2
840-E5634-02
2100-1025-24
0X3684
2.3
840-E5634-03
2100-1025-24
2100-1225-24
0XA8E3
2.3
840-E5634-04
2100-1225-24
0X7769
2.5
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
THIS PAGE IS INTENTIONALLY LEFT BLANK
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
AUTOMATIC TESTING
1. GENERAL
There are no Automatic Test Procedures for the FA2100 CVR.
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Automatic Testing
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
DISASSEMBLY
1. GENERAL
This section contains the information required to disassemble the Model FA2100 Cockpit
Voice Recorder (FA2100CVR). Access to the major assemblies within the Model
FA2100CVR is described such that there is minimal disturbance to other assemblies. Extreme care should be exercised when removing these assemblies. To ensure the warranty coverage of a defective circuit board, it must be returned to the factory for repair or replacement.
CAUTION: THE MODEL FA2100’s PRINTED CIRCUIT ASSEMBLIES CONTAIN DEVICES SENSITIVE TO ELECTROSTATIC DISCHARGE (ESD). PERSONNEL HANDLING A PRINTED CIRCUIT BOARD SHOULD COMPLY WITH
PROPER ESD HANDLING PROCEDURES; FAILURE TO DO SO MAY RESULT IN DAMAGE TO THE ESD SENSITIVE DEVICES RENDERING THE
PRINTED CIRCUIT BOARD USELESS. PRIOR TO HANDLING A
PRINTED CIRCUIT BOARD, ENSURE PROPER PERSONNEL GROUNDING TECHNIQUES ARE USED. ALSO, ENSURE THAT ALL CIRCUIT
BOARDS ARE PLACED INTO STATIC SHIELDING CONDUCTIVE BAGS
WHEN HANDLING OR STORING.
ESD
WARNING
SYMBOL
SYMBOL FOR ESD
GROUND
CONNECTING
O
2. MODEL FA2100CVR DISASSEMBLY INSTRUCTIONS
Special tools, fixtures, and equipment that are needed to disassemble and repair the
Model FA2100CVR are listed in Figure 901.
NOTE:
Numbers shown in parentheses in the following text and figures are
the Illustrated Parts List (IPL) figure number followed by the IPL item
number for a particular part; e.g., (1-100) for IPL Figure 1, Item 100.
For items listed in the parts list but not illustrated, the item number is
preceded by a “-”.
In addition to the IPL figure references, each disassembly instruction is accompanied with
an illustration showing specific assemblies or subassemblies to which the steps of the
procedure are related. The figures in this section contain the same figure/item number references identifying the piece parts of the assembly as in the IPL figures; however, different views of the assemblies may be provided to facilitate disassembly tasks.
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
NOTE:
A.
All attaching parts such as cable assemblies, stand−offs, screws,
washers, etc. that are not damaged, should be retained with the
chassis for reinstallation with the repaired LRUs. The FA2100CVR
replaceable PWAs or modules consist of the Acoustic Beacon, Aircraft Interface PWA, Audio Compressor PWA, Acquisition Processor
PWA, and the Crash Survivable Memory Unit (CSMU).
Underwater Locator Beacon Removal
(See Figure 301 or IPL Figure 1, Item 80)
The Underwater Locator Beacon (ULB) is mounted on the Model FA2100’s CSMU
front bracket with the beacon water switch facing to the left (refer to Figure 301,
(1–80)). The ULB is equipped with a battery that has an expected life the same as
the beacon replacement date marked on the beacon label. Upon expiration of expected battery life, contact L-3AR for replacement batteries, installation instructions
and re-certification.
30−Day ULB’s already in service may still be used, and a ULB Battery Kit, p/n:
147E0305−00, is available for battery replacement.
The 30−Day ULB, p/n: 266E0305−00, is no longer manufactured due to the cancellation of TSO−121 and TSO−121a as of Dec. 1, 2015.
A 90−Day ULB Conversion Kit, pn: 068E5542−00, is available for retrofit of a
30−Day ULB to 90−Day beacon to an existing recorder.
When converting from a 30−Day ULB to a 90−Day ULB, the L−3AR ULB Conversion
Kit, P/N 068E5542−00, must be used. This kit contains the 90−Day ULB and four
attaching hex mounting screws. Converted CVR units must be marked with MOD−
DOT #15. Refer to FA2100CVR SB022 for more details.
NOTE:
Once a unit has been changed to a 90−Day ULB, it can not
revert to a 30−Day ULB due to the Hardware MOD−DOT
marking.
NOTE:
Refer to the IPL effectivity column, as some specific
FA2100CVR Part Numbers are allowed only 90−Day ULBs to
be installed.
All new recorder production units will incorporate the 90−Day underwater locator
beacon, p/n: 266E5542−00. For more information, including the testing and cleaning
of the ULB, please see the L−3AR Underwater Locator Beacon CMM, p/n
165E5542−00.
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
BEACON REMOVAL PROCEDURE
(1)
To remove the Underwater Acoustic Beacon (1-80) from the Beacon Mount
Bracket (1-70), use a 3/16” Allen hex-wrench, remove the two left 1/4–20, hexcap screws (1-75) that secures the left Beacon Mount Bracket to the CSMU.
(2)
Loosen the lower right hex−cap screw (1-75) which secures the right Beacon
Mount Bracket to the CSMU and holds the beacon in the bracket.
(3)
The beacon can now be removed from the Beacon Mount Bracket.
(4)
If the CSMU requires removal, then remove the right beacon bracket mount
from the CSMU assembly.
Crash Survivable
Memory Unit
(CSMU)
(1‐185)
Right Beacon
Mount Bracket
(1-70)
Water Switch
Left Beacon
Mount Bracket
(1-70)
1/4” Hex−cap Screw
(1-75)
Underwater
Acoustic Beacon
(1-80)
Figure 301.
Underwater Locator Beacon Removal Diagram
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23–70–04
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
B.
Crash Survivable Memory Unit (CSMU) Removal
(See Figure 305 or IPL Figure 1, Item 185)
The Model FA2100CVRs CSMU is mounted to the top of the recorder chassis by (4)
pan-head sealing screws (MOD−DOT 4). It interfaces to the Acquisition Processor
PWA through the Memory Interface Cable assembly attached to the Acquisition
Processor PWA’s J1 connector. The CSMU is a sealed unit and must be returned to
the factory for repair. If replacement of the CSMU is required, proceed with the following procedure:
CSMU REMOVAL PROCEDURE
(1)
Remove the Underwater Acoustic Beacon (1-80) as described in
paragraph A. above.
(2)
Remove the four 1/4–20, 1” pan−head sealing screws (190) that secure the
CSMU memory assembly (1-185) to the recorder chassis (1-5).
(a)
NOTE:
For Pre-MOD DOT 13 units only, carefully remove the RTV from around
the memory interface cable assembly slot in the chassis.
Pan-head sealing screws (1-190) are one time use items
that should be discarded when removed and replaced with
new screws.
1/4” Pan−Head Sealing
Screws (190)
(Qty. 4)
CSMU
Memory Assembly
(1‐185)
Recorder
Chassis
(1‐5)
Figure 302. CSMU Memory Sealing Screw Removal
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23–70–04
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
(3)
Lift and disconnect the CSMU memory assembly as per the appropriate instructions below.
(a)
For Pre-MOD DOT 6 units only, carefully tilt the CSMU memory assembly
to the left side (same side as cable) to gain access to the J1 connector
located on the Acquisition Processor PWA (1-175).
Carefully unplug P1 of the Memory Interface Cable Assembly from J1 on
the Acquisition Processor PWA. Note the pins of J1 can be easily damaged if handled incorrectly.
CSMU
Memory Assembly
Memory Interface
Cable Assembly
(1‐185)
P1
Acquisition
Processor PWA
(AP)
(1‐175)
J1
Recorder
Chassis
(1‐5)
Figure 303. CSMU Memory Assembly Removal Diagram (PRE-MOD DOT 6)
(b)
For Post-MOD DOT 6 / Pre-MODT DOT 13 units only, carefully tilt the
CSMU memory assembly to the left side (same side as cable) to gain access to the J5 connector located on the Acquisition Processor PWA
(1-175).
Carefully unplug P1 of the Memory Interface Cable Assembly from J5 on
the Acquisition Processor PWA. Note the pins of J5 can be easily damaged if handled incorrectly.
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23–70–04
Disassembly
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
Memory Interface
Cable Assembly
CSMU
Memory Assembly
(1‐185)
P1
Acquisition
Processor PWA
(AP)
(1‐175)
Recorder
Chassis
J5
J1
(1‐5)
Figure 304. CSMU Memory Assembly Removal Diagram (POST-MOD DOT 6 &
PRE-MOD DOT 13)
(c)
For Post-MOD DOT 13 units only, carefully lift the CSMU memory assembly directly up without pulling the memory interface cable to gain access to
the J5 connector located on the Acquisition Processor PWA (1-175).
Carefully unplug P1 of the Memory Interface Cable Assembly from J5 on
the Acquisition Processor PWA. Note the pins of J5 can be easily damaged if handled incorrectly.
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23–70–04
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
Memory Interface
Cable Assembly
CSMU
Memory Assembly
(1‐185)
P1
Acquisition
Processor PWA
(AP)
(1‐175)
Recorder
Chassis
J5
J1
(1‐5)
Figure 305. CSMU Memory Assembly Removal Diagram (POST-MOD DOT 13)
(4)
For GACVR’s, p/ns: 2100−1010−5X and 2100−1020−5X, remove RTV from the
bottom of the CSMU and the Chassis at the seating surface for the CSMU memory
assembly.
(5)
Lift the CSMU away from the chassis.
NOTE:
(6)
C.
Post-MOD DOT 13 CSMU Memory Assemblies have circuitry located
on the bottom (flat) side of the CSMU. Only place the CSMU down oriented so that this circuitry is not underneath the CSMU. Failure to do
this will result in damage to the CSMU Memory Assembly.
Package CSMU memory assembly and return to L-3 Aviation Recorders for repair.
Acquisition Processor (AP) PWA Removal
(See Figure 306 or IPL Figure 1, Item 175)
The Model FA2100’s Acquisition Processor PWA (1-175) is mounted in the bottom
of the recorder chassis just below the CSMU. It provides an interface between the
Aircraft Interface PWA through Cable Assembly W001 connected at J2, the Audio
Compressor PWA through Cable Assembly W003 connected at J4, and the CSMU
via the Memory Interface Cable assembly connected at J1. The Acquisition PWA
also provides an interface between the FA2100 Recorder and Ground Support
Equipment, GSE, directly through front panel connector J3.
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23–70–04
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
(1)
Remove the CSMU memory assembly (1-185) as described in paragraph B.
above.
(2)
To gain full access to the Acquisition Processor PWA (1−175) remove the 10 panhead sealing screws (1-25) and lift chassis cover (1-20) from the recorder chassis.
NOTE:
Pan-head sealing screws (1-25) are one time use items that
should be discarded when removed and replaced with new
screws.
(3)
Disconnect the Aircraft Interface PWA interconnection cable assembly, W001
(1-165), from J2 on the Acquisition Processor PWA.
(4)
Disconnect the Audio Compressor PWA interconnection cable assembly, W003
(1-165), from J4 on the Acquisition Processor PWA.
(5)
Remove 8 flat-head screws (1-95) that secure the rear panel assembly (1-90) with
attached Aircraft Interface PWA and Audio Compressor PWA into the recorder
Chassis (1-5).
NOTE:
Flat-head screws (1-95) are one time use items that should
be discarded when removed and replaced with new screws.
(6)
Lift the rear panel assembly away from the chassis.
(7)
Remove 10 pan-head screws (1-180) that secure the Acquisition Processor PWA
to the recorder chassis.
(8)
Carefully slide the Acquisition Processor PWA from the rear of the recorder chassis
while observing proper ESD handling techniques.
(9)
Package Acquisition Processor PWA in a static-resistant container for shipment to
the factory for repair.
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
(1-180)
Qty. 10
Acquisition
Processor PWA
(AP)
(1‐175)
Chassis Cover
Assy
(1-20)
J3
Rear Panel
Assy
J5
J1
J4
J2
(1-90)
Chassis
(1‐5)
W003
(1-165)
W001
(1-170)
Aircraft Interface Audio Compressor
PWA (AI)
PWA (AC)
(1-105)
(1-95)
Qty. 8
(1-155)
Figure 306. Acquisition Processor PWA Removal Diagram
D.
Audio Compressor PWA (AC) Removal
(See Figure 307 or IPL Figure 1, Item 155)
The Model FA2100’s Audio Compressor PWA is mounted to the Aircraft Interface
PWA located in the rear panel assembly of the recorder chassis. It provides digital
conversion and compression of the input audio stream. It interfaces to the Acquisition Processor PWA via interconnect cable assembly W003 through the J2 connec-
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23–70–04
Disassembly
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
tor; and to the Aircraft Interface PWA via cable assembly W002 through the J1 connector.
(1)
Remove the CSMU memory assembly (1-185) as described in paragraph B.
above.
(2)
Remove the 10 pan-head screws (1-25) which secure the chassis cover (1-20) to
the recorder chassis (1−5).
NOTE:
Pan-head sealing screws (1-25) are one time use items that
should be discarded when removed and replaced with new
screws.
(3)
If the rear panel assembly has not been removed from the chassis perform steps
(4) − (7). If the rear panel assembly has been removed, then skip to step (8).
(4)
Disconnect the Aircraft Interface PWA interconnection cable assembly, W001
(1-165), from J2 on the Acquisition Processor PWA.
(5)
Disconnect the Audio Compressor PWA interconnection cable assembly, W003
(1-165), from J4 on the Acquisition Processor PWA.
(6)
Remove 8 flat-head screws (1-95) that secure the rear panel assembly (1-90) with
attached Aircraft Interface PWA and Audio Compressor PWA into the recorder
Chassis (1-5).
NOTE:
Flat-head screws (1-95) are one time use items that should
be discarded when removed and replaced with new screws.
(7)
Lift the rear panel assembly away from the chassis.
(8)
Disconnect the interconnection cable assembly, W002 (1-170), from J1 on the Audio Compressor PWA (1−155).
(9)
Disconnect the interconnection cable assembly, W003 (1-165), from J2 on the Audio Compressor PWA.
(10) Place the Assembly Support Tool fixture, Table 701: item 5, between the Aircraft
Interface PWA (1-105) and the rear panel assembly (1-90). Position the fixture
such that the inner part of the “U” shape surrounds the J1A connector.
NOTE:
This fixture is used to support the Aircraft Interface PWA
and prevent damage to the circuit board when removing the
two bottom standoff screws that attach to the Audio Compressor PWA.
(11) Remove the 4 pan-head screws (1-160) which mount the Audio Compressor PWA
(1-155) to the 4 standoffs (1-120) on the Aircraft Interface PWA (1-105).
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23–70–04
Disassembly
Rev. 15 Page 310
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
(1-141)
(1-135)
REF
(1-20)
(1-25)
Qty. 10
(1-151)
(1-146)
(Post MOD DOT 11)
Audio Compressor
PWA (AC)
(1-155)
Aircraft Interface
PWA (AI)
(1-160)
Qty. 4
(1-105)
A
(1-135)
(1-140)
Qty. 2
BLACK
(Bottom - J5)
(1-120)
Qty. 4
(1-110)
Qty. 2
RED
(Top - J4)
(1-105)
(1-115)
(1-155)
J1
(1-125)
Qty. 3
J2
(1-125)
W003
(1-165)
J2
J3
(1-145)
(1-150)
Qty. 2
(1-125) W002
Qty. 2 (1-165)
(1-90)
J3
J5
W001
(1-170)
(1-130)
Qty. 4
VIEW
A
J1
Acquisition
Processor PWA
(AP)
(1-95)
Qty. 8
(1-175)
Figure 307. Aircraft Interface & Audio Compressor PWA Removal Diagram
Use or disclosure of information on this sheet is subject
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23–70–04
Disassembly
Rev. 15 Page 311
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
(12) Remove the Assembly Support Tool fixture, Table 701: item 5 from under the Aircraft Interface PWA.
(13) Carefully lift the Audio Compressor PWA from the rear panel assembly observing
proper ESD handling precautions.
(14) If the Audio Compressor PWA is the faulty component, then package it in an staticresistant container for shipment to the factory for repair.
E.
Aircraft Interface PWA (AI) Removal
(See Figure 307 or IPL Figure 1, Item 105)
The Model FA2100CVR Aircraft Interface PWA is mounted in the rear panel assembly of the recorder chassis. It provides the Cockpit Voice Recorder with an interface
to the Aircraft’s power and Cockpit Control Unit, through the rear panel connector,
J1A. It also provides operating voltage to the storage capacitor and routes the input
voice, GMT and RSE signals to the Audio Compressor PWA.
AIRCRAFT INTERFACE PWA REMOVAL PROCEDURE
(1)
Remove the Audio Compressor PWA (1-155) from the rear panel assembly as detailed in Para. D. above.
(2)
Disconnect the interconnection cable assembly, W001 (1-165), from J2 and W002
(1−170) from J3 on the Aircraft Interface PWA. Keep these cables for later use.
(3)
Remove 4 flat-head screws (1-130) that attach the J1A Main connector on the Aircraft Interface PWA to rear panel assembly (1-90).
(4)
Disconnect the storage capacitor red blade connector (39Vdc Hot) from the top,
J4, connector on the Aircraft Interface PWA.
(5)
Disconnect the storage capacitor black blade connector (39Vdc Return) from
the lower, J5, connector on the Aircraft Interface PWA.
(6)
Remove 3 pan-head screws (1-125) which mount the two upper standoffs (1-110),
and center standoff (1-115) between the rear panel assembly and Aircraft Interface PWA.
(7)
If storage capacitor is faulty, remove it by performing step (8), otherwise, skip
step (8).
(8)
On pre MOD DOT 11, remove two flat-head screws (1-140), flat washers
(1-145) and self−locking hex nuts (1-150) that secure the storage capacitor to
the top of the rear panel assembly.
(9)
On post MOD DOT 11, remove two flat-head screws (1-141), from the support
capacitor bracket (1−146) that secure the storage capacitor to the top of the
rear panel assembly.
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23–70–04
Disassembly
Rev. 15 Page 312
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
(10) Carefully lift the Aircraft Interface PWA from the rear panel assembly observing
proper ESD handling precautions.
(11) Remove 2 pan-head screws (1-125) which mount the two lower standoffs (1-120)
on the Aircraft Interface PWA.
(12) Remove the remaining single pan-head screw (1-125) which attaches the center
standoff (1-115) to the Aircraft Interface PWA.
(13) Using a 3/16” hex wrench, unscrew the four top standoff’s (1-110 & 1-120) on the
Aircraft Interface PWA.
(14) Save all Aircraft Interface PWA attaching parts for use with replacement Aircraft Interface PWA.
(15) Package Aircraft Interface PWA in an static-resistant container for shipment to the
factory for repair.
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
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23–70–04
Disassembly
Rev. 15 Page 313
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
THIS PAGE IS INTENTIONALLY LEFT BLANK
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23–70–04
Disassembly
Rev. 15 Page 314
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
CLEANING
1. GENERAL
This section contains a list of all required cleaning materials, general cleaning procedures, applicable cautions and warnings related to the use of any cleaning material, and
instructions for cleaning the Model FA2100 CVR major assemblies.
2. MATERIALS REQUIRED
Refer to Table Table 401 for a listing of required cleaning materials:
Table 401.
Cleaning Materials Required
NOTE:
Material
Specification
Solvent
Soft‐Bristle Brush
Cotton Swabs
Lint‐Free Cotton Cloth
MIL‐PRF‐680
Equivalent substitutes may be used for all cleaning materials. All materials and chemicals may be obtained from any commercial source.
3. CLEANING PROCEDURES
WARNINGS:
1) OBSERVE ALL FIRE PRECAUTIONS WHEN USING FLAMMABLE
MATERIALS FOR CLEANING PURPOSES.
2) PERFORM OPERATIONS INVOLVING CLEANING SOLVENT IN A WELLVENTILATED AREA. AVOID PROLONGED BREATHING OF VAPORS OR
CONTACT WITH SKIN.
CAUTION:
THE FA2100 CIRCUIT BOARDS ARE SUSCEPTIBLE TO ELECTRO–
STATIC DESTRUCTION (ESD). PRIOR TO HANDLING PWAs, ENSURE
PROPER PERSONNEL GROUNDING TECHNIQUES ARE USED.
ENSURE THAT CARDS ARE PLACED INTO STATIC SHIELDING
CONDUCTIVE BAGS WHEN HANDLING OR STORING.
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
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23–70–04
Cleaning
Rev. 15 Page 401
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
CAUTION: DO NOT IMMERSE ANY PRINTED WIRING ASSEMBLY MOUNTED ELECTRONIC
PARTS IN THE CLEANING SOLVENT; OTHERWISE, CIRCUIT BOARD AND/OR
COMPONENT DAMAGE MAY RESULT.
A.
B.
Printed Wiring Assembly Cleaning
(1)
Remove dust, dirt, and foreign matter from all surfaces, using soft-bristle brush.
(2)
Wipe finished surfaces and contacts, using a cloth moistened in solvent.
Connector Cleaning
(1)
C.
Wipe dust and dirt from connectors, using a lint-free cloth, moistened with solvent.
Underwater Locator Device (Beacon) Cleaning
All information for the ULB, including the testing and cleaning, is contained in the
L−3AR Underwater Locator Beacon CMM, p/n 165E5542−00.
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
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23–70–04
Cleaning
Rev. 15 Page 402
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
CHECK
1. GENERAL
This section contains the various checks that should be performed on the Model FA2100
Cockpit Voice Recorder during shop maintenance. Check procedures, when required,
are written in step-by-step procedures wherever practicable, and include specific methods, techniques, and equipment required. Electrical set up and checks are given in the
Testing and Troubleshooting Section 100 of this Component Maintenance Manual.
CAUTION:
THE FA2100 CIRCUIT BOARDS ARE SUSCEPTIBLE TO ELECTRO–
STATIC DESTRUCTION (ESD). PRIOR TO HANDLING PWAs, ENSURE
PROPER PERSONNEL GROUNDING TECHNIQUES ARE USED.
ENSURE THAT CARDS ARE PLACED INTO STATIC SHIELDING
CONDUCTIVE BAGS WHEN HANDLING OR STORING.
2. CHECKS
A.
B.
Main Recorder Assembly
(1)
Check the general physical integrity of the recorder; i.e. front panel ATE connector pins,
Underwater Locator Device (acoustic beacon) and J1A rear panel connector pins.
(2)
Check that dust cover is serviceable, exhibiting no undue deterioration and is properly
painted.
Mechanical Inspection
(1)
Remove the unit dust cover, refer to Section 300 Disassembly Section.
(2)
Inspect all parts for cracks, distortion, excessive wear, and proper finish.
(3)
Inspect all cast parts for cracks, especially at bosses, flanges, and other critical areas.
(4)
Inspect circuit boards and connectors for loose terminals, pins, and screws, and check
for cracks in the boards that may have been brought about by environmental conditions.
(5)
Check all wire leads for broken conductors, burnt or deteriorated installation, and loose
connections.
(6)
Check all flat ribbon cable assemblies and associated connectors for broken conductors,
burnt or deteriorated installation, and loose pin connections.
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23–70–04
Check
Rev. 15 Page 501
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
C.
(7)
Check the circuit boards for broken parts and bad solder joints. Check for burnt parts.
Check the circuit boards for cracks and abrasions.
(8)
Inspect the nameplate for legibility.
(9)
Reassemble recorder in accordance with the steps of procedure outlined in Section 700:
Assembly.
Electrical Inspection
Perform all test set-up and testing per instructions given in the Testing and Troubleshooting Section 100 of this Component Maintenance Manual.
D.
Underwater Locator Device (ULD)
All information for the ULB, including the testing and cleaning, is contained in the
L−3AR Underwater Locator Beacon CMM, p/n 165E5542−00.
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23–70–04
Check
Rev. 15 Page 502
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
REPAIR
1. GENERAL
This section is intended to contain information required to restore a worn or damaged part
to a serviceable condition. However, the Fairchild Model FA2100 Cockpit Voice Recorder
is a completely solid-state device that does not contain any electro-mechanical moving
parts. The Model FA2100CVR has been designed as maintenance-free unit which
makes extensive use of surface mount technology (SMT). The repair of printed wiring
assemblies (PWAs) containing SMT components requires specialized factory equipment,
training, and techniques, therefore, such PWAs are not field-repairable. Only the L−3AR
Repair Station, FAA: LD7R612J; EASA.145.4620 is authorized to repair the FA2100CVR
to component level in accordance with L−3AR Factory test, calibration and repair specifications.
As a result, the Model FA2100CVR’s maintenance philosophy is replacement of failed assemblies. In the case of the Model FA2100CVR, the replaceable assemblies are the Aircraft Interface PWA, the Audio Compressor PWA, the Acquisition Processor PWA, and
the Crash Survivable Memory Unit (CSMU).
When it has been determined that one or more of these assemblies is faulty, the faulty
assembly(ies) should be removed and returned to the Aviation Recorders factory for repair or replacement. Attempts to repair any of these assemblies will void the warranty.
Extreme care should be used when handling these assemblies.
CAUTION:
THE FA2100 CIRCUIT BOARDS ARE SUSCEPTIBLE TO ELECTRO–
STATIC DESTRUCTION (ESD). PRIOR TO HANDLING PWAs, ENSURE
PROPER PERSONNEL GROUNDING TECHNIQUES ARE USED.
ENSURE THAT CARDS ARE PLACED INTO STATIC SHIELDING
CONDUCTIVE BAGS WHEN HANDLING OR STORING.
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to the restrictions on the cover page of this document.
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23–70–04
Repair
Rev. 15 Page 601
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
THIS PAGE IS INTENTIONALLY LEFT BLANK
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23–70–04
Repair
Rev. 15 Page 602
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
ASSEMBLY
1. GENERAL
This section contains procedures describing the assembly of the Model FA2100 Cockpit
Voice Recorder as well as storage instructions after assembly. There is no special testing
necessary during assembly. However, once assembly is completed, the operational test
procedure provided in the Testing and Troubleshooting Section 100 should be performed
to verify proper operation of the Recorder.
2. REQUIRED MATERIALS
Special equipment required for testing and assembly of the recorder can be found in
Table 901 of the Special Tools, Fixtures, and Equipment Section 900 of this CMM.
Table 701 provides a list of the common assembly materials used with the FA2100 Cockpit Voice Recorder.
Table 701. Required Assembly Materials
Item
1. Adhesive
Manufacturing and Specification
Loctite, Grade E, Purple No. 222
Lock/sealant manufactured by Loctite Corp.,
705 N. Mountain Rd.,
Newington, CT 06111 [V05972]
2. Torque Wrench Local tool supplier
Range: 5−6 in/lbs
End Range: 75 in/lbs
3. RTV Adhesive
Dow Corning RTV 3145 (V71984)
L-3 p/n: 0601200006, or equivalent
4. Tape, Polymide MMM (3M) 5413
Use
Retain screw
CSMU & Beacon Bracket mounting screws
(75 in/lbs.); Chassis
Cover screws (9-10 in/
lbs; and Rear Panel &
AP board screws (5-6 in/
lbs.)
Chassis
Chassis
L-3 p/n: 2529800034, or equivalent
5. Tool, Assembly L-3 p/n: 980E2196-00, or equivalent
Support
6. Tool, Seal Align- L-3 p/n: 980E2188-00, or equivalent
ment, Short Chassis
7. Tool, Seal
L-3 p/n: 980E2189-00, or equivalent
Applicator
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Audio Compressor PWA
Installation
Chassis Seal
Installation
Chassis Seal
Installation
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Assembly
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
3. ASSEMBLY INSTRUCTIONS
CAUTION:
A.
THE FA2100 CIRCUIT BOARDS ARE SUSCEPTIBLE TO ELECTRO–
STATIC DESTRUCTION (ESD). PRIOR TO HANDLING PWAs, ENSURE
PROPER PERSONNEL GROUNDING TECHNIQUES ARE USED.
ENSURE THAT CARDS ARE PLACED INTO STATIC SHIELDING
CONDUCTIVE BAGS WHEN HANDLING OR STORING.
General Assembly Techniques
The Model FA2100CVR circuit board components are mounted using Surface Mount
Technology (SMT) and also incorporate extensive software programming to functionally configure the logic circuits. Thus, Level-3 repair of these circuit boards requires
specialized factory equipment, diagnostic software, training, and techniques; therefore, such boards are not field-repairable while the unit is under warranty. Consequently, in accordance with the accepted Level-2 repair philosophy for the FA2100
CVR, a known defective circuit board assembly shall be returned to the factory for
repair or replacement.
NOTE:
Numbers shown in parentheses in the following text are the
Illustrated Parts List (IPL) figure number followed by the IPL
item number for a particular part; e.g., (1-115) for IPL Figure 1,
Item 115. For items listed in the parts list but not illustrated, the
item number is preceded by a “-”.
The Assembly procedures begin with the Acquisition Processor PWA installation
then continue with the Audio Compressor and Aircraft Interface PWA installation,
CSMU installation, and Underwater Acoustic Beacon installation.
B.
Acquisition Processor (AP) PWA Installation
(See Figure 701 or IPL Figure 1, Item 175)
This procedure assumes that the Crash Survivable Memory Unit (CSMU) is removed
from the chassis and that the rear panel chassis assembly with the Aircraft Interface
PWA and Audio Compressor PWA attached is also removed from the recorder chassis. The Model FA2100’s Acquisition Processor (AP) PWA (1-175) is mounted in the
bottom of the recorder chassis just below the CSMU.
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23–70–04
Assembly
Rev. 15 Page 702
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
(1-180)
Qty. 10
Acquisition
Processor PWA
(AP)
(1‐175)
Chassis Cover
Assy
(1-20)
J3
Rear Panel
Assy
J5
J1
J4
J2
(1-90)
Chassis
(1‐5)
W003
(1-165)
W001
(1-170)
Aircraft Interface Audio Compressor
PWA (AI)
PWA (AC)
(1-105)
(1-95)
Qty. 8
(1-155)
Figure 701.
Acquisition Processor (AP) Installation Diagram
The Acquisition Processor PWA provides an interface between the Aircraft Interface
PWA, through W001 Cable Assembly connected at J2 and the Audio Compressor
PWA, through W003 Cable Assembly connected at J4. The Acquisition Processor
PWA connects to the CSMU via the Memory Interface Cable assembly connected at
J1 (Pre-MOD DOT 6 units) or the J5 (Post-MOD DOT 6 units). The Acquisition
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23–70–04
Assembly
Rev. 15 Page 703
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
Processor PWA also provides an interface between the FA2100CVR and Ground
Support Equipment, GSE, directly through front panel GSE connector J3.
C.
(1)
Remove the Acquisition Processor PWA (1-175) from its static-resistant container
ensuring that none of the connector contacts are touched and general ESD handling precautions are observed.
(2)
Slide the Acquisition Processor PWA into the chassis with the GSE (J3) connector
toward the front from the rear and position into place. Refer to Figure 701.
(3)
Apply adhesive, Table 701: item 1, to 10 pan-head screws (1-180) and tighten into
place using a torque wrench set at 5-6 in./lbs. to secure the Acquisition Processor
PWA to the recorder chassis (1-5).
(4)
If the Aircraft Interface PWA (1−105) and Audio Compressor PWA (1−155) are not
attached to the rear panel assembly (1−90), then perform the steps in paragraph
C. and paragraph D.
(5)
If the Aircraft Interface PWA and Audio Compressor PWA are attached to the rear
panel assembly, then continue with paragraph D., Step (9).
(6)
Since the Acquisition Processor requires specifically configured software to operate, refer to the Test and Troubleshooting Section 100, for detailed procedures on
loading the recorder software through the front panel GSE connector.
Aircraft Interface PWA (AI) Installation
(See Figure 703 or IPL Figure 1, Item 105)
The Model FA2100’s Aircraft Interface PWA is mounted in the rear panel assembly
of the recorder chassis. It provides the Flight Recorder with an interface to the Aircraft’s power and Flight Data Acquisition Unit, FDAU, through the rear panel connector, J1A. It also provides operating voltage to the storage capacitor and routes the
input signals to the Audio Compressor PWA through W002 Cable Assembly connected at J3 and to the Acquisition Processor PWA through the W001 Cable Assembly connected at J2.
This procedure assumes that the CSMU is removed from the recorder chassis, that
the dust cover is off, the rear panel assembly is detached from the recorder chassis,
the Audio Compressor PWA is not attached, and that the Acquisition Processor PWA
is installed and secured into the chassis as described in paragraph B.
NOTE:
Front orientation means toward or facing the front of the
unit, whereas rear means toward or facing the rear of the
unit.
To secure the Aircraft Interface PWA to the rear panel assembly (1-90):
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23–70–04
Assembly
Rev. 15 Page 704
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
(1)
For GACVRs, p/n: 2100−1010−51 and 2100−1020−51, verify that the three unused holes on the rear of the chassis (1−5) are filled with RTV. If the unused
holes are not filled with RTV, place polymide tape (Table 701: Item 4) over the
holes on the inside of the chassis (1−5).
(2)
Attach the (2) lower short standoffs (1-120) to the front side of the Aircraft Interface PWA using (2) pan−head screws (1-125), inserted from the rear (J1A)
side of the board and coated with adhesive, Table 701: item 1. Hand tighten
for right now.
(3)
Using a 3/16” hex wrench attach 2 studded upper standoffs (1-110) inserted
from the rear side through the board and attach with the remaining two short
standoffs (1-120) from the front side of the Aircraft Interface PWA (1-105). Hand
tighten for right now.
(4)
Attach the center standoff, (1-115) to the rear side of the Aircraft Interface PWA
using (1) pan-head screw (1-125) inserted from the front side of the AI PWA
and coated with adhesive, Table 701: item 1.
(5)
Tighten all screws and standoffs attached to a torque value of 5-6 in./lbs.
(6)
Position the Aircraft Interface PWA into the rear panel assembly such that the
J1A mounting holes and upper standoffs are aligned properly.
(7)
While holding the J1 connector flush with the bottom of the connector opening
of the rear panel assembly, insert (4) flat-head screws (1-130) and tighten down
in a cross pattern to ensure a proper alignment of the J1 main connector assembly with the rear panel assembly (1-90). Note that these screws do not use
adhesive.
(8)
Insert the (3) pan−head screws (1-125) coated with adhesive, Table 701: item
1, which secure the Aircraft Interface PWA to the rear panel through the standoffs (1-110 & 1-115). Tighten screws to a torque value of 5-6 in./lbs.
(9)
Connect interconnect cable assembly W001 (1-165) to J2 on the Aircraft Interface PWA.
(10) Connect the interconnect cable assembly W002 (1-170) to J3 on the Aircraft Interface PWA.
(11) If the storage capacitor assembly was removed earlier, perform step (12), otherwise skip to step (14).
(12) On pre MOD DOT 11, secure the storage capacitor assembly (1-135) to the top
of the rear panel assembly (1-90) with a pair of flat-head screws (1-140), flat
washers (1-145) and hex nuts (1-150).
(13) On post MOD DOT 11, Apply thread-locking adhesive, Table 701 item 1 to the
two flat-head screws (1-136). Install two flat-head screws to secure the storage
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23–70–04
Assembly
Rev. 15 Page 705
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
capacitor (1−130) to the top of the rear panel assembly using the support capacitor bracket (1−141).
(14) Connect the red blade connector (39 Vdc Hot) to the top, J4, connector on the
front side of the Aircraft Interface PWA.
(15) Connect the black blade connector (39 Vdc Return) to the lower, J5, connector
on the front side of the Aircraft Interface PWA.
D.
Audio Compressor PWA (AC) Installation
(See Figure 703 or IPL Figure 1, Item 155)
The Model FA2100’s Audio Compressor PWA is mounted to the Aircraft Interface
PWA located in the rear panel assembly of the recorder chassis. It provides digital
conversion and compression of the input audio stream. It interfaces to the Acquisition Processor PWA via interconnect cable assembly W003 through the J2 connector; and to the Aircraft Interface PWA via cable assembly W002 through the J1 connector.
(1)
Ensure that the Aircraft Interface PWA (1-105) is installed into rear panel assembly
(1-90) as described in paragraph C. above.
(2)
Lay the rear panel assembly on its back with the Aircraft Interface PWA facing up.
(3)
Place the Assembly Support Tool fixture, Table 701: item 5, between the Aircraft
Interface PWA (1-105) and the rear panel assembly (1-90). Position the fixture
such that the inner part of the “U” shape is around the J1A connector.
NOTE:
This fixture is used to support the Aircraft Interface PWA
and prevent damage to the circuit board when installing the
two bottom standoff screws that attach to the Audio Compressor PWA.
(4)
Secure Audio Compressor PWA (1-155) to the Aircraft Interface PWA standoffs
(1-120) using (4) pan-head screws (1-160) coated with adhesive Table 701: item 1.
Only hand tighten right now.
(5)
Tighten the (4) pan-head screws in a cross pattern and torque to a value of 5-6
in./lbs.
(6)
Remove the Assembly Support Tool fixture, Table 701: item 5 from under the Aircraft Interface PWA.
(7)
Attach W002 (1−170) from the Aircraft Interface PWA to J1 on the Audio Compressor PWA.
(8)
Attach W003 (1−165) to J2 on the Audio Compressor PWA.
Use or disclosure of information on this sheet is subject
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23–70–04
Assembly
Rev. 15 Page 706
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
(1-141)
Qty. 2
(1-25)
Qty. 10
(1-135)
REF
(1-20)
Audio Compressor
PWA (AC)
(1-155)
(1-146)
(1-160)
Qty. 4
Aircraft Interface
PWA (AI)
Torque
Sequence
(5‐6 in/lbs)
(1-105)
A
(1-140)
Qty. 2
(1-135)
4
(1-120)
Qty. 4
(1-110)
Qty. 2
(1-146)
(Post MOD DOT 11)
2
(1-115)
BLACK
(Bottom - J5)
1
(1-105)
3
(1-125)
Qty. 3
RED
(Top - J4)
(1-155)
J1
J2
W003
(1-165)
(1-125)
4
2
J2
J3
1
3
Torque
Sequence
(5‐6 in/lbs)
(1-125) W002
Qty. 2 (1-165)
(1-90)
W001
(1-170)
(1-130)
Qty. 4
(1-145)
Qty. 2
VIEW
A
(1-150)
Qty. 2
3
2
1
Torque
Sequence
9−10 in/lb
(Each Side)
W003
(1-165)
J3
2
J5 (Post MOD DOT 6)
3
J1
1
Acquisition
Processor
PWA (AP)
(1-175)
(1-95)
Qty. 8
Figure 702.
Aircraft Interface & Audio Compressor PWA
Installation Diagram (PRE-MOD DOT 6)
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23–70–04
Assembly
Rev. 15 Page 707
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
(1-141)
(1-135)
REF
(1-25)
Qty. 10
(1-20)
(1-151)
(1-146)
(Post MOD DOT 11)
Audio Compressor
PWA (AC)
(1-155)
Aircraft Interface
PWA (AI)
(1-105)
(1-120)
Qty. 4
(1-110)
Qty. 2
(1-160)
Qty. 4
Torque
Sequence
(5‐6 in/lbs)
(1-135)
(1-140)
Qty. 2
A
BLACK
(Bottom - J5)
4
(1-105)
(1-115)
(1-155)
2
1
(1-125)
Qty. 3
J1
J2
3
W003
(1-165)
(1-125)
J2
J3
(1-145)
(1-150)
Qty. 2
4
2
3
1
3
Torque
Sequence
(5‐6 in/lbs)
(1-130)
Qty. 4
RED
(Top - J4)
(1-125) W002
Qty. 2 (1-165)
(1-90)
W001
(1-170)
Torque
Sequence
9−10 in/lb
(Each Side)
VIEW
A
2
J3
1
2
1
J5
3
J1
Acquisition
Processor PWA
(AP)
(1-95)
Qty. 8
(1-175)
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23–70–04
Assembly
Rev. 15 Page 708
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
Figure 703. Aircraft Interface & Audio Compressor PWA
Installation Diagram (POST MOD DOT 6)
(9)
Insert the rear panel assembly with attached Aircraft Interface PWA and Audio
Compressor PWA into the recorder chassis (1-5).
(10) To secure the rear panel assembly, insert six flat-head screws (1-95) coated with
adhesive, Table 701: item 1, three to each side of the rear panel assembly, but do
not fully tighten down.
NOTE:
Flat-head screws (1-95) are one time use items and should
be replaced during re-assembly. These screws should not
be retained after dis-assembly.
(11) Insert two flat-head screws (1-95) coated with adhesive, Table 701: item 1, into the
bottom of the chassis and tighten them down using a torque wrench set to 9-10
in./lbs.
(12) Hold the rear panel assembly (1-90) securely to the chassis, turn on its side and
tighten three screws inserted in Step (10) to 9−10 in./lbs. in the pattern shown in
Figure 703.
(13) Turn the chassis over to the opposite side and tighten the remaining three screws
to 9-10 in./lbs. in the same pattern as shown in Figure 703.
(14) Connect the Aircraft Interface PWA W001 Cable Assembly (1-165) to J2 on the Acquisition Processor PWA (1-175).
(15) Connect the W003 Cable Assembly (1-165) between J2 on the Audio Compressor
PWA and J4 on the Acquisition Processor PWA.
(16) Check proper alignment of the rear connector J1A by carefully inserting the
FA2100CVR into an SSCVR Mount, Part Number 178E0919–00, (Ref: Model
FA2100CVR Installation and Instruction Manual, p/n: 165E1846-00). If alignment
is skewed, loosen (8) flat-head screws (1-95) and repeat steps (11) − (13).
(17) Secure the Chassis Cover (1−20) as described in Paragraph E.
(18) Secure the CSMU (1-185) to the recorder as described in Paragraph F.
E.
Chassis Cover Installation
(See Figure 704 and Figure 706 or IPL Figure 1, Item 20A/B)
(1)
For GACVR p/ns: 2100−1010−5X and 2100−1020−5X, skip steps (2) − (8) and
proceed with step (9), these units do not have the chassis cover seal.
(2)
If original cover seal material is damaged or seals need to be installed (pre
mod−dot #4 units) perform steps (3) − (8), otherwise skip to step (9).
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23–70–04
Assembly
Rev. 15 Page 709
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
(3)
Position the chassis cover seal (1-28) into place on the Seal Alignment Tool,
Table 701: item 6, (see Figure 704, frame 1).
(4)
Carefully peel the paper backing from the chassis cover seal (1-28) to end of
the alignment tool ensuring that you do not stretch the seal.
(5)
With the seal placed on the alignment tool with the sticky side up, position the
front part of the chassis cover (1-20) down onto the seal and gently press (see
Figure 704, frame 2).
(6)
Carefully turn over the alignment tool with chassis cover and seal so that the
rear of the chassis is nearest to you. Carefully, remove the remaining paper
backing from the seal ensuring that you do not stretch the seal or that it folds
over on itself.
(7)
Using the Seal Applicator Tool, p/n: 980E2189−00, or equivalent (see Figure
702, frame 3), gently smooth down the chassis cover seal (1−28) to form two
90_ bends at the rear of the chassis cover.
(8)
Remove the chassis cover with attached seal from the alignment fixture and ensure that the seal screw holes line up with the chassis cover screw holes.
(9)
Replace the chassis cover (1-20) by inserting the front end of the cover into the
alignment grove and inserting ten attaching pan-head sealing-screws (1-25)
coated with adhesive Table 701: item 1.
NOTE:
Pan-head sealing screws (1-25) are one time use items and
should be replaced during re-assembly. These screws
should not be retained after dis-assembly.
(10) To secure the cover to the chassis, tighten down each of the 10 pan-head
sealing-screws (1-25) in the pattern shown in Figure 706, torque to a value of
9-10 in./lbs.
(11) If needed, apply RTV, DOW Corning, 3145 Adhesive silicone sealant to the two
inside corner bend relieves of the chassis cover and to the two front screw
heads as indicated in Note 1 and Note 2, Figure 706, respectively.
(12) For GACVR p/ns: 2100−1010−5X and 2100−1020−5X, apply RTV (Table 701:
Item 3) to the two front screw heads, and the front seam where the chassis
cover (1−20B) meets the chassis (1−5), as indicated in Note 1, Figure 705.
NOTE:
For GACVR p/ns: 2100−1010−5X and 2100−1020−5X, install
the CSMU in accordance with Step 13, and then perform
Steps 14 through 15. This will ensure that the Chassis Cover will be firmly seated prior to applying RTV around the
Chassis Cover to Chassis seam.
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23–70–04
Assembly
Rev. 15 Page 710
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
(13) Secure the CSMU (1-185) to the recorder as described in
Paragraph F.
(14) For GACVR p/ns: 2100−1010−5X and 2100−1020−5X, apply RTV (Table 701:
Item 3) to the entire seam where the chassis cover (1−20B) meets the chassis
(1−5), as indicated in Note 2, Figure 705.
(15) For GACVR p/ns: 2100−1010−5X and 2100−1020−5X, apply RTV (Table 701:
Item 3) around the connector, including the three keying holes, and the seam
on the back of the CVR, as indicated in Note 3, Figure 705.
(16) For GACVR p/ns: 2100−1010−5X and 2100−1020−5X, if the three unused
holes on the backside of the chassis (1−5) are not filled with RTV, apply RTV
(Table 701: Item 3) to the holes to seal them, as indicated in Note 4,
Figure 705.
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23–70–04
Assembly
Rev. 15 Page 711
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
1
ALIGN CHASSIS
COVER OVER
SEAL & PRESS IN
PLACE
2
ALIGN SEAL OVER
FIXTURE HOLES
REMOVE SEAL BACKING
AND SMOOTH OUT
3
PUSH TOOL FIRMLY
TO AFFIX SEAL TO
SIDE
4
HOLES IN SEAL
SHOULD LINE UP WITH
HOLES IN CHASSIS
COVER ASSEMBLY
DO NOT STRETCH
SEAL MATERIAL
Figure 704.
FA2100CVR Chassis Cover Seal Installation
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23–70–04
Assembly
Rev. 15 Page 712
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
Note 1:
Apply RTV to
Two Front Screw Heads
and the front seam where
the Chassis Cover meets
the Chassis.
Note 2:
Apply RTV to entire seam,
where Chassis Cover meets
the Chassis, after the
CSMU is installed and tightened.
Note: 4
Apply RTV to seal unused
holes on backside of Chassis.
(if present)
Note: 3
Apply RTV to seam on the
back of the CVR and around
the connector and the (3)
keying holes.
Figure 705. FA2100 GACVR Chassis RTV Installation
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23–70–04
Assembly
Rev. 15 Page 713
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
7
8
Torque
Sequence
(9−10 in./lbs.)
5
6
3
Chassis Cover
Seal-Screws
(Qty 10)
1
4
2
9
10
Note 1:
Apply RTV to
two front bend relieves in
Chassis Cover
Note 2:
Apply RTV to
Two Front Screw Heads
Figure 706.
FA2100CVR Chassis Cover Installation
F.
Crash Survivable Memory Unit (CSMU) Installation
(See Figure 710 or IPL Figure 1, Item 185)
The Model FA2100’s Crash Survivable Memory Unit, CSMU, is a sealed unit and
must not be opened in the field. CSMU is mounted to the top of the recorder chassis by (4) pan-head srews. The CSMU interfaces to the Acquisition Processor Board
connector J1 through the Memory Interface Cable assembly.
(1)
For GACVR p/ns: 2100−1010−5X and 2100−1020−5X, apply RTV (Table 701:
Item 3) to the CSMU seating surface on the chassis (1−5).
(2)
If the CSMU Cover Seal is not installed or has been damaged and needs replacing perform the CSMU Cover Seal installation / replacement below.
CSMU COVER SEAL INSTALLATION / REPLACEMENT
(PRE−MOD DOT 13)
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23–70–04
Assembly
Rev. 15 Page 714
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
(a)
Remove the damaged seal, if necessary, by peeling the seal up from the
edge.
(b)
Ensure that the flat underside surface of the CSMU is clean.
CSMU Cover
Seal
Apply RTV to seal
Memory Cable Slit
Figure 707. Crash Survivable Memory Unit (CSMU)
Seal Application (Pre-MOD DOT 13)
(c)
Carefully peel the paper backing from the CSMU Cover Seal (1-200) and
position seal into place on the CSMU memory assembly (1-185), with the
sticky side against the CSMU cover. (See Figure 707.)
(d)
Smooth the seal down onto the CSMU memory assembly, such that the
application is toward the memory interface cable assembly. Carefully work
the cable assembly slit in the seal around the memory interface cable assembly.
(e)
Apply RTV, DOW Corning, 3145 Adhesive silicone sealant between the slit
in the CSMU cover seal where memory interface cable assembly passes
through the seal as shown in Figure 707.
CSMU COVER SEAL INSTALLATION / REPLACEMENT
(POST−MOD DOT 13)
(a)
Disconnect the memory cable from CSMU circuitry by lifting the cable
clasp and sliding the cable free.
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23–70–04
Assembly
Rev. 15 Page 715
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
Location of memory
cable clasp
Figure 708. Crash Survivable Memory Unit (CSMU)
Seal Application (Post-MOD DOT 13)
(b)
Secure the loose cable to the side, ensuring that it is away from the bottom of the CSMU. This will keep the cable out of access while applying the
new CSMU seal.
(c)
If necessary remove the damaged seal by peeling the seal up from the
edge. Take care to not damage the circuitry affixed to the bottom of the
CSMU.
(d)
Ensure that the flat underside surface of the CSMU is clean.
CSMU Cover
Seal
Apply RTV to seal
Memory Cable Slit
Figure 709. Crash Survivable Memory Unit (CSMU)
Seal Application (Post-MOD DOT 13)
(e)
Carefully peel the paper backing from the CSMU Cover Seal (1-200) and
position seal into place on the CSMU memory assembly (1-185). Place the
cut out in the seal around the CSMU circuitry with the notch oriented towards the memory cable. The sticky side of the seal should be against the
CSMU cover. (See Figure 709.)
(f)
Smooth the seal down onto the CSMU memory assembly, such that the
application is toward the memory interface cable assembly. Carefully work
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23–70–04
Assembly
Rev. 15 Page 716
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
the cable assembly slit in the seal around the memory interface cable assembly.
(3)
(4)
(g)
Apply RTV, DOW Corning, 3145 Adhesive silicone sealant between the slit
in the CSMU cover seal where memory interface cable assembly passes
through the seal as shown in Figure 709.
(h)
Reattach the memory cable to the CSMU circuitry by sliding the end of the
cable into the connection slot and pushing the clasp down to secure it.
Carefully reconnect the memory interface cable assembly connector from the
CSMU to the Acquisition Processor PWA.
(a)
For Pre-MOD DOT 6 units, the memory interface cable should be connected to J1 on the Acquisition Processor PWA.
(b)
For Post-MOD DOT 6 units, the memory interface cable should be connected to J5 on the Acquisition Processor PWA.
Apply Locktite 222 to the four pan-head sealing-screws (1−190) and insert
them into the CSMU cover (1-185).
NOTE:
Pan-head sealing screws (1-190) are one time use items
and should be replaced during re-assembly. These screws
should not be retained after dis-assembly.
(5)
While pushing back on the front of the CSMU, partially tighten the rear two panhead screws.
(6)
Use a torque-wrench to tighten the four pan-head sealing-screws to 75 in/lbs in
the cross pattern, shown in Figure 710, to fully secure the CSMU to the recorder chassis.
(7)
Apply RTV, DOW Corning, 3145 Adhesive silicone sealant to the memory interface cable assembly tab to seal the slot through the chassis that the cable
passes through as shown in Figure 710, Figure 711 and Figure 712.
NOTE:
(8)
The GACVRs, p/ns: 2100−1010−5X and 2100−1020−5X, must
be allowed to set for 24 hours to allow the RTV to cure.
Install the Underwater Acoustic Beacon as described in the next paragraph.
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23–70–04
Assembly
Rev. 15 Page 717
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
4
Torque Sequence
75 in/lb
1
3
CSMU Mounting
Seal-Screws
(1−190B)
(Qty 4)
2
Note:
After attached, apply RTV
to seal Memory Cable Slot
P1
Crash Survivable
Memory Unit
(CSMU)
(1‐185)
Memory Interface
Cable Assembly
J1
Recorder Chassis
Assembly
(1-5)
Acquisition
Processor PWA
(AP)
(1‐175)
Figure 710. Crash Survivable Memory Unit (CSMU)
Assembly (PRE-MOD DOT 6)
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23–70–04
Assembly
Rev. 15 Page 718
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
4
Torque Sequence
75 in/lb
1
3
CSMU Mounting
Seal-Screws
(1−190B)
(Qty 4)
2
Note:
Crash Survivable
Memory Unit
(CSMU)
After attached, apply RTV
to seal Memory Cable Slot
(1‐185)
P1
Memory Interface
Cable Assembly
J5
Recorder Chassis
Assembly
(1-5)
J1
Acquisition
Processor PWA
(AP)
(1‐175)
Figure 711. Crash Survivable Memory
Unit (CSMU) Assembly (POST-MOD DOT 6 & PRE-MOD DOT 13)
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23–70–04
Assembly
Rev. 15 Page 719
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
4
Torque Sequence
75 in/lb
1
3
CSMU Mounting
Seal-Screws
(1−190B)
(Qty 4)
2
Note:
Crash Survivable
Memory Unit
(CSMU)
After attached, apply RTV
to seal Memory Cable Slot
(1‐185)
P1
Memory Interface
Cable Assembly
J5
Recorder Chassis
Assembly
(1-5)
J1
Acquisition
Processor PWA
(AP)
(1‐175)
Figure 712. Crash Survivable Memory
Unit (CSMU) Assembly (POST-MOD DOT 13)
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23–70–04
Assembly
Rev. 15 Page 720
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
A.
Underwater Acoustic Beacon Assembly & Installation
(See Figure 713 and IPL Figure 1, Item 80)
The Underwater Acoustic Beacon is mounted on the Model FA2100’s CSMU front
bracket with the beacon’s water switch facing to the left (refer to Figure 713, 1–80).
NOTE:
When replacing the 30−day ULB it is recommended that
new mounting hex screws (MS 16995-54) are used to ensure a secure connection to the CSMU.
NOTE:
When replacing the 90−day ULB it is REQUIRED that four
new mounting hex screws (L-3AR p/n 2290200424) that are
used to secure the ULB brackets to the CSMU.
When converting from a 30−Day ULB to a 90−Day ULB, the L−3AR ULB Conversion
Kit, P/N 068E5542−00, is recommended. This kit contains the 90−Day ULB and the
attaching hex mounting screws. Converted CVR units must be marked with MOD−
DOT #15. Refer to FA2100CVR SB022 for more details.
NOTE:
Once a unit has been changed to a 90−Day ULB, it can not
revert to a 30−Day ULB due to the Hardware MOD−DOT
marking.
NOTE:
Refer to the IPL effectivity column, as some specific
FA2100CVR Part Numbers that only are allowed only
90−Day ULBs to be installed.
NOTE:
For complete testing of the ULB and battery replacement
procedures, refer to the 90−Day Underwater Locator Beacon CMM, L-3 p/n 165-E5542-00.
(1)
Insert the Underwater Acoustic Beacon (1-80) into the right and left beacon
mount bracket (1-70) with the beacon water switch facing left and replacement
date label visible to the front.
(2)
Apply thread-locking adhesive, Table 701 item1, to four 1/4–20, 1” hex-cap
bolts (1-75).
(3)
Insert and tighten secure the right and left beacon mount bracket (1-70) with beacon
to the CSMU. Torque mounting bolts (1-75) in a cross−pattern as shown in Figure 713
to 75 in/lbs.
(4)
For those units with customer installed beacons, p/n’s: 2100-1020−98 and
2100-1020-99, remove the temporary label which covers the standard identity
label.
(5)
Perform a return-to-service test on the recorder in accordance with Section 100
of this CMM.
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23–70–04
Assembly
Temp. Rev. 16 Page 721
Apr. 15/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
Note: - Must use the L-3AR Conversion Kit, PN
068E5542-00 when converting from a 30-Day
ULB to a 90-Day ULB.
Mark Name Plate Hardware MOD-DOT #15
Underwater
Acoustic Beacon
(1-80)
Crash Survivable
Memory Unit
(CSMU)
Right Beacon
Mount Bracket
(1-70)
Water Switch
#2
(1‐185)
Left Beacon
Mount Bracket
(1-70)
#4
1/4” Hex Screw
(1-75)
#1
#3
Cross-Pattern
Torquing Sequence
(75 in./lbs.)
Figure 713.
Underwater Locator Beacon Assembly
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23–70–04
Assembly
Rev. 15 Page 722
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
4. STORAGE INSTRUCTIONS
NOTE:
A.
A Return-To-Service bench test is recommended after storage
of more than one year. Refer to Automatic Test Section 200 for
specific test and check-out procedures.
Storage in Original Containers
When possible, the FA2100 Cockpit Voice Recorder should be stored in its original
container(s). Provide adequate packing to ensure protection from damage during
storage and shipment and ensure that adequate silica gel packages are packed in
the container(s) to protect the equipment from moisture. Seal the container(s) to
provide a moisture–proof package.
B.
Storage Without Original Containers
If the original container(s) are not available, perform the following procedures to
wrap the FA2100CVR system equipment for storage:
C.
(1)
Wrap the recorder unit in plain wrapping paper or newspaper of sufficient thickness to thoroughly cover all sharp corners and protrusions.
(2)
Enclose the unit in a polyethylene bag (3 mils thick, min.) seal the bag.
(3)
Place the recorder unit in a suitably sized heavy construction cardboard box
surrounded with packing material sufficient to protect it on all sides. Arrange
packing material in such a way that the unit is protected and will not move
around within the box.
(4)
Seal box(es) with fiberglass packing tape.
(5)
Mark boxes clearly as to contents.
Shipment Container Kit
A shipment package kit, P/N: 147E1679-00, (IPL Item 1−210) may be ordered from
Aviation Recorders if the original container(s) are not available. This kit contains the
FA2100CVR shipping container, p/n: 197E1746-00, (IPL Item 1−220) shown in
Figure 714.
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23–70–04
Assembly
Rev. 15 Page 723
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
NOTES:
1.
CONTAINER TO MEET ATA SPEC 300 CATEGORY II.
MATERIAL: OUTER SHELL FIBER BOARD TO BE TYPE
1, CLASS 2, PER PPP−8−836 BOUBLE WALL 275 LBS
CONSTRUCTION
MATERIAL PACKING FOAM (1.50 IN. THICK) 1.8 LBS/
CUBIC FOOT WITH A COMPRESSION SET OF 95%.
MATERIAL PACKING FOAM (2.00 IN. THICK) 1.2 LBS/
CUBIC FOOT WITH A COMPRESSION SET OF 40%.
FOAM TO BE BONDED TO CARDBOARD. FLUTED
SINGLE WALL 200 LBS CONSTRUCTION
REF: CONTINOUS STITCHING
STAPLE APPROX 1.0
INCH SPACING, DOUBLE
STAPLE EACH END (.25
IN SPACING)
8.9
8.9
17.1
8.9
8.9
FOAM BONDED TO INSIDE
FLAPS OF CONTAINER FOAM
NOT TO EXTEND BEYOND THE
CUT EDGE OF THE FLAP
SHIPPING CONTAINER,
Short Box
(1-220)
Figure 714.
Shipping Container, Short Box, p/n: 197E1746-00,
part of Shipment Package Kit: p/n: 147E1679-00.
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23–70–04
Assembly
Rev. 15 Page 724
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
FITS AND CLEARANCES
1. GENERAL
This section provides the FA2100CVR recorder’s specifications and outline and dimensions. Since the recorder uses solid−state memory recording technology, there are no internal fits and clearances or tension values normally associated with older technology
electromechanical tape recorder units.
The information contained herein is also in the Description/Operation section of this CMM
and is presented here for the purpose of quick reference.
2. SYSTEM SPECIFICATIONS
The Model FA2100CVR meets the performance requirements of ED-56A, chapters 2, 3,
4, and 5, and 7, ED−112, chapter 2, and Part I, while conforming to the input interface
required in ARINC 557/757. When the software detects a fault an CVR FAULT will be asserted immediately with no artificial delay.
A.
Physical Characteristics
(1)
Size: (Refer to Figure 801. for the FA2100CVR Outline & Dimension Drawing)
Height:
Width:
Depth:
5.5 inches
4.98 inches
12.6 inches (behind front panel)
(2)
Weight:
10.0 ($.5) pounds nominal
7.7 ($.5) pounds (p/ns: 2100−1010−51
and 2100−1020−51)
(3)
Case:
404A–ATR Case, Short. Stainless Steel
CSMU Housing, International Orange,
Reflective Striping, English/French
Markings
(4)
Main (Rear)
Connector:
57–Pin Connector Compatible with
ARINC757, p/n: 063E1072–00 (Cannon
p/n: DPXBMA–36571–59)
(5)
Main (Rear)
Mating Connector:
Crimp: p/n: 063–98–01474 (Cannon p/n:
DPXBMA–57–33S- 0001)
Solder: p/n 9300–435 (Cannon p/n:
DPXB-57-33S-0001)
(6)
Ground Support
Equipment Connector:
p/n: 063–98–01962 (AMP p/n: 748481–6)
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FA2100CVR
B.
C.
Electrical Characteristics
(1)
Power Requirements:
115 Vac @ 400 Hz, or 28 Vdc
Only 28 Vdc for GACVRs
(p/n’s: 2100−1010−−50/51 and
2100−1020−−50/51)
(2)
Power Level:
12W max ac, 10.5W max dc
(3)
Power Factor:
.65
(4)
Recording Time:
2100-1010-( ) = 30 min. minimum
2100-102X-( ) = 120 min. minimum
(5)
Input Signal Format:
ARINC 557/757
(6)
Rotor Speed:
Analog Frequency = 7 to 6,000 Hz
with input impedance of 100 kohms
(7)
Audio Output:
2.55 Vrms into 600−ohms
Environmental Characteristics
Refer to Table 801 for the FA2100 CVR environmental characteristics.
D.
Crash and Fire Protection
The Crash Survivable Memory Unit (CSMU) is designed to fully meet the 5,000
pounds crush test requirement of TSO–123a and provides impact protection for up
to 3400 g’s for 6.5 msec. The inner steel casing assembly protects the memory elements from deep sea pressures to 20,000 ft.
The FA2100’s crash–protected CVR memory survives ED–56A 5.3.2.d. and ED−112
2−4.2.4 High Temperature Fire for one hour per the requirements of TSO-123a, or
ED–56A 5.3.2.e., ED−112 2.4.2.5 Low Temperature Fire for ten hours. Specifically, 1
Hr @ 1100_ C, and 10 Hrs @ 260_ C.
E.
Torque Requirements
The following assembly items have the specified torque requirements:
CSMU & Beacon Bracket mounting screws (75 in./lbs.);
Chassis Cover screws (9-10 in./lbs.); and
Rear Panel, Aircraft Interface & Acquisition Processor attaching screws (5-6 in./lbs.)
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COMPONENT MAINTENANCE MANUAL
FA2100CVR
Table 801. FA2100 CVR Environmental Characteristics
Conditions
Description
Temperature & Altitude
RTCA/
DO–160C
Section
4.0
Ground Survival:
Low Temperature
High Temperature
4.5.1
4.5.2
(–55_C)
(+85_C)
Low Temperature Operating
High Temperature Short–time
Operating High Temperature
4.5.1
4.5.2
4.5.3
(–55_C)
(+70_C)
(+70_C)
Altitude
Decompression
Overpressure
Temperature Variation
Humidity
Shock:
Operational Shock
Crash Safety (Impulse)
4.6.1
4.6.2
4.6.3
5.0
6.0
7.0
7.2.2
7.3.1.1
55,000 ft
55,000 ft
–15,000 ft
Category B
Category A (Standard)
Crash Safety (Sustained)
Vibration (Random)
Crash Survival
7.3.2
8.6.2
12 G – 3 seconds
Categories C Without Shock Mounts
3400 G – 6.5 MS
Categories A2 & F2
6 G – 11 MS
15 G – 11 MS
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COMPONENT MAINTENANCE MANUAL
FA2100CVR
ESD LABEL
C
COCKPIT VOICE RECORDER
MODEL FA2100
B
2.44  .5
B
7.5
A

C
.5
A
5.4  .1
3.0  .5
FARSIDE LABEL READS: ENREGISTREUR DE VOL NE PAS OUVRIR
.2
MAX
12.60

.5
MAX
.04
NOTES:
1. RECORDER COLOR IS INTERNATIONAL ORANGE NO. 12197 PER FED-STD-595. FRONT AND SIDE LABELS ARE REFLECTIVE WHITE
BACKGROUND WITH BLACK LETTERING. NAMEPLATE IN VIEW A-A HAS LIGHT GRAY BACKGROUND WITH BLACK MARKING. A RUSSIAN
TEXT LABEL IS LOCATED ON THE CSMU ON P/N: 2100−1025−12 AS SHOWN IN THE LOWER RIGHT HAND CORNER OF THIS DRAWING
2. ELECTRICAL INTERFACE CONNECTIONS PER APPLICABLE ARINC CHARACTERISTIC.
3. SEE CHART FOR FINAL PART NO. INPUT POWER, AND WEIGHT. POWERS ARE MAXIMUMS AND WEIGHTS ARE NOMINAL WITH
 .5 LBS TOLERANCE.
4. OVERALL EQUIPMENT SIZE AND MOUNTING SCHEME COMPLY WITH ARINC 404 AND 404A.
5. REAR PANEL CONTAINS HOLES TO MATE WITH GUIDE PINS IN ARINC 404 MOUNTING TRAYS.
Figure 801. (Sheet 1 of 2) Outline & Dimension Drawing
Model FA2100 CVR Recorder P/N: 2100-1010-( ) & 2100-102X-( )
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COMPONENT MAINTENANCE MANUAL
FA2100CVR
2.44
 .50
REFERENCE ONLY
POLARIZING KEYS
SHADING DENOTES
SOLID KEY AREA
4
.275
A
View
A
B
B
View
J1 CONNECTOR PART NUMBERS:
PN 063-E1072-00 (CANNON DPBX-36571-59)
MATING CONNECTORS:
(CRIMP) PN 063-98-01474 (CANNON DPXBMA-57-33S-0001)
(SOLDER) PN 9300-435 (CANNON DPXB-57-33S-0001)
4.88
CRASH SURVIVABLE
MEMORY UNIT

.04
UNDERWATER LOCATING
DEVICE
5.5

.2
GROUND SUPPORT
EQUIPMENT CONNECTOR
063-98-01962
(AMP 748481-6)
4.12
4.98
C

.04
View
C
Figure 801. (Sheet 2 of 2) Outline & Dimension Drawing Model
FA2100 CVR Recorder P/N: 2100-1010-( ) & 2100-102X-( )
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FA2100CVR
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
SPECIAL TOOLS, FIXTURES AND EQUIPMENT
1. GENERAL
This section provides a listing of all required tools, fixtures, and equipment which are not
common maintenance tools. Refer to Table 901 for a table listing required FA2100CVR
special test equipment. Refer to the following paragraphs for a synopsis of equipment description and purpose.
Table 901. Table of Special Tools, Fixtures, and Equipment
Portable Interface (PI)
Part Number
17TES0043
Description
Mfg.
Portable Interface (PI)
L-3 Com.
17TES0053
PI Memory Card Module (Obsolete)
L-3 Com.
17TES0054
PI Memory Card Module
L-3 Com.
17TES0051
PI Audio Readout Cable
L-3 Com.
17TES0052
PI Aux Readout Cable
L-3 Com.
Portable Interface/2 (PI/2)
Part Number
17TES0062
Description
Mfg.
Portable Interface (PI/2)
L-3 Com.
024E5002-00
USB 2.0 Cable
L-3 Com.
147E4785-00
USB Adapter
L-3 Com.
253E5106-00
USB Key
L-3 Com.
024E5000-00
FA2XXX FDR Interface Cable
L-3 Com.
FA2100 Software Upload Test Equipment, Cable Assemblies & Software (ROC/6)
Part Number
17TES0400
Description
Mfg.
Read-Out Center/6 − Full CVR/FDR Configuration (The following items are included with the
ROC/6)
L-3 Com.
17TES0410
Recorder Interface Unit (RIU)
L-3 Com.
17TES0411
Cable, RIU to AC Power In
L-3 Com.
17TES0412
Cable, RIU to DC Power In
L-3 Com.
17TES0413
Cable, RIU to Sound Card (2ea.)
L-3 Com.
17TES0414
GSE − Recorder Cable Assy to PC Line In
L-3 Com.
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FA2100CVR
17TES0415
Cable, RIU to USB
L-3 Com.
17TES0416
Cable, RIU to CVR
L-3 Com.
17TES0417
Cable Assembly, Audio Setup
L-3 Com.
17TES0420
CATS Software, FA2100
L-3 Com.
17TES0070
CICC/2 Assembly Dwg.
L-3 Com.
17TES0071
Cable Assembly, F1000−CICC/2
L-3 Com.
17TES0072
Cable Assembly, FA2100−CICC/2
L-3 Com.
17TES0076
Recorder Interface, USB, Top Level
L-3 Com.
17TES0321
Read-Out System Equipment Software
(ROSE 3.4)
L-3 Com.
17TES0057
Recorder Interface Cable Assembly
L-3 Com.
17TES0058
FA2100 Software Upload Cable Assembly
L-3 Com.
883E4557−00
CD, Soundblaster Audigy
L-3 Com.
17TES0425
Speakers (110V)
Optional
17TES0426
Speakers (220V)
Optional
FA2100 Software Upload Test Equipment, Cable Assemblies & Software (ROC/7)
Part Number
17TES0700
Description
Mfg.
Read-Out Center/7 − Full CVR/FDR Configuration (The following items are included with the
ROC/7)
L-3 Com.
17TES0710
Recorder Interface Unit (RIU)
L-3 Com.
17TES0411
Cable, RIU to AC Power In
L-3 Com.
17TES0412
Cable, RIU to DC Power In
L-3 Com.
17TES0413
Cable, RIU to Sound Card (2ea.)
L-3 Com.
17TES0415
Cable, RIU to USB
L-3 Com.
17TES0417
Cable Assembly, Audio Setup
L-3 Com.
17TES0418
Cable, RIU to CVR
L-3 Com.
17TES0420
CATS Software, FA2100, V. 2.0
L-3 Com.
17TES0070
CICC/2 Assembly Dwg.
L-3 Com.
17TES0072
Cable Assembly, FA2100−CICC/2
L-3 Com.
17TES0076
(RUFS) Recorder Interface USB, Top Level
L-3 Com.
17TES0321
Read-Out System Equipment Software
(ROSE 4.5)
L-3 Com.
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FA2100CVR
17TES0057
Recorder Interface Cable Assembly
L-3 Com.
17TES0058
FA2100 Software Upload Cable Assembly
L-3 Com.
883E4557−00
CD, Soundblaster Audigy
L-3 Com.
17TES0426
Speakers (110V)
Optional
17TES0426
Speakers (220V)
Optional
Note:
The FA2100 Software Program P/N, listed below for the specific recorder, is
needed to perform the upload function.
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FA2100CVR
FA2100 CVR Software Disk
Part Number
Description
Mfg.
840E1658-07
FA2100CVR p/n: 2100-1010-00, 30-Min.
Program Software
L-3 Com.
840E1657-07
FA2100CVR, p/n: 2100-1020-00 120-Min.
Program Software
L-3 Com.
840E1663-07
FA2100 GACVR p/n: 2100-1010-50/51,
30-Min. Program Software
L-3 Com.
840E1664-07
FA2100 GACVR, p/n: 2100-1020-50/51
120-Min. Program Software
L-3 Com.
840E3408−07
FA2100CVR, p/n: 2100-1025-02 120-Min.
Data Link
L-3 Com.
840E3408−04
FA2100CVR, p/n: 2100-1025-12 CVR
120-Min. Data Link, (Cyrillic Russian Text))
L-3 Com.
840E4568−09
FA2100CVR, p/n: 2100-1025-22 CVR
120-Min. OMS Data Link
L-3 Com.
804E4568−06
FA2100CVR, p/n: 2100-1025-24 CVR
120−Min. OMS Data Link, Bombardier Global
L-3 Com.
TBD
FA2100CVR, p/n: 2100-1026-02 CVR
120−Min. OMS Data Link, Airbus
L-3 Com.
TBD
FA2100CVR, p/n: 2100-1027-02 CVR
120−Min. OMS Data Link, Airbus
L-3 Com.
Note:
The ADLP Software is only required for playback of the datalink data.
FA2100CVR P/N: 2100−1025−02/−12./−22, 2100−1026−02 and
2100−1027−02.
CATS 2.0 or higher is required for Return to Service.
Audio Data Link Player (ADLP) Software
Part Number
17TES0436
Description
Mfg.
Audio Data Link Player Software, Version 3
L-3 Com.
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FA2100CVR
2. GROUND SUPPORT EQUIPMENT (GSE) DESCRIPTIONS
A.
Portable Interface Unit, p/n: 17TES0043
Refer to Figure 901 and Figure 902. The Portable Interface (PI) Unit, Part Number
17TES0043, can be used to check the recorder status and download FA2100CVR
audio data from the recorder to the PI Memory Module, Part Number 17TES0053,
while installed in the aircraft. On the bench, the PI Unit can also be used to monitor
audio channels, playback audio data, check the recorder status, clear latch faults
and fault history logs. For these procedures, refer to the Portable Interface Unit Operating Manual p/n: 165E1630-00.
B.
FA2100 Software Upload Cable Assembly & Distribution Diskettes
In the event that the Acquisition Processor PWA, p/n: 205E1591-00, p/n
205E1931-00 or p/n: 205E2502-10/-11, requires replacement, the FA2100CVR program software must be loaded into the new board using the FA2100 Software
Upload cable assembly, p/n: 17TES0058, the FA2100 Software Utility Bundle Program, p/n: 883E1894−01 which contains the CICCLDR and CICCIFC executable
files. The Utility Programs are also found on the ROSE Distribution CD, p/n:
17TES0321. The Software Upload cable assembly is connected between the
FA2100 front panel GSE/ATE connector and the Computer Interface and Communications Cable (CICC or CICC/2) cable to an enhanced parallel port of a PC.
For the the procedure to install the Software Upload Utility and CICC Interface Programs into the ROC/5 or ROC/6 Ground Station, and the procedure to upload the
FA2100 Software into the recorder, refer to Test and Troubleshooting Section, 100,
Paragraph 10.
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COMPONENT MAINTENANCE MANUAL
FA2100CVR
CVR: MONITOR
PLAYBACK
TO RECORDER
GSE CONNECTOR
STATUS / CONTROL
SPECIAL FUNCTIONS
GMT/ROTOR
FSK
AUDIO
SELECT
DELETE
MENU
Sarasota, Florida
PI AUX
READOUT CABLE
17TES0052
PI AUDIO
READOUT CABLE
17TES0051
CH 1
HQ
SQ
2
3
COMB
4
CAM
Figure 901.
Portable Interface Unit, p/n: 17TES0043
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COMPONENT MAINTENANCE MANUAL
FA2100CVR
MAIN MENU
CVR: MONITOR
PLAYBACK
MONITOR MENU
PLAYBACK MENU
CVR PLAYBACK
MODE: STOP
POSITION: HRS : MIN : SEC
ROTOR: __HZ
GMT:
(PLAY)
STATUS / CONTROL
(STOP)
KEYPAD
SPECIAL FUNCTIONS
(RWD)
(FFWD)
STATUS / CONTROL MENU
OFF/ON
CH 4
**
SQ VOICE CH 1−3 OFF/ON
**
SQ CAM
CH 4
OFF/ON
MODE: NORM
UP
VOLUME:
DOWN
PLAYBACK CONTROL MENU
VERSION ID:
CVR RUN STATUS
SET / CLEAR TEST CNDTNS
DELETE FILE FROM DISK
(A)
DISPLAY GMT/ROTOR
(B)
(C)
(D)
TRACE MSGS TO FILE
HQ CAM
CTRL MENU
SPECIAL FUNCTIONS MENU
FAULT LOG TO FILE
OFF/ON
OFF/ON
OFF/ON
RED KEY
(END/BEGIN)
(F)
HQ VOICE CH 1
CH 2
CH 3
CVR SUPER FR #: (1 Sec
Samples)
CVR PLBK OFFST: 0:00
CVR FAULT STAT: NODAT
**
**
HQ VOICE CH 1 OFF/ON
CH 2 OFF/ON
CH 3 OFF/ON
HQ CAM CH 4 OFF/ON
SQ VOICE CH 1−3 OFF/ON
SQ CAM CH 4 OFF/ON
FILE
BACK
UP
VOLUME:
VERSION MENU
SET / CLEAR TEST CNDTNS
MENU
CVR FILE CONTROL MENU
PORTABLE INTERFACE
PI S/W VERSION 1.2
CLEAR LATCHED FAULT
FA2100 REV. NO. −OO
CLEAR FAULT LOG
SMP VERSION: X.X.
DOWN
CVR FILE CONTROL
FILE NAME: XXXX.CVR
FILE ID: XXXX
(DATE RECORD MADE)
03−APR−1999
(TIME RECORD MADE)
11: 30:10 (HRS :MIN:SEC)
(FILE SIZE:) XXXXX Kbytes
(RECORD DURATION)
HR:MIN:SECS
BACK
COPY PLAY
CVR FAULT : GSE : ON
CVR FAULT : GSE : OFF
CVR FAULT : GSE :RELEASE
SMP CHECK SUM: XXXX
(E)
CVR COPY MENU
FILE ID
:_ (11CHAR LIMIT)
A B C D E F G H I J
K L M N O P Q R S T
U V W X Y Z . : − /
+ _ # & $ @ < > !
0 1 2 3 4 5 6 7 8 9
CLEAR
START
COPY TIME REMAINING
CVR COPY
FOR CVR DATA COPY
HR:MIN:SEC
** Note: SQ Voice and SQ CAM are
not available for p/n: 2100−1025−02
since it is a two−hour HQ Recorder.
START COPY
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FA2100CVR
Figure 902. Sheet 1 of 2
Portable Interface (PI) Unit, CVR Menu Structures.
(A)
(B)
FILE DELETION MENU
FILE DELETION
(FILE NAME): XXXX.CVR
(FILE ID): XXXX
DATE: 0I−JAN−1999
TIME RECORDED:
HRS : MIN : SEC
FILE SIZE: XXX Kbytes
FILE DURATION:
HRS : MIN : SEC
BACK
DELETE
DISPLAY GMT/ROTOR
DELETE THIS FILE:
ROTOR: XXXX HZ
XXXX.CVR
GMT:: X:XX::XX
ARE YOU SURE?
YES
NO
(F)
(C)
(E)
FAULT LOG TO FILE
FILE ID
:_ (11 CHAR LIMIT)
A B C D E F G H I J
K L M N O P Q R S T
U V W X Y Z . : − /
+ _ # & $ @ < > !
0 1 2 3 4 5 6 7 8 9
FILE PLAYBACK MENU
FILE ID : XXXX
MODE: PLAY
POSITION: 00:00:00
ROTOR: Hz
GMT:: X:XX:XX
(PLAY)
DUMPING FAULT LOG TO:
XXXX.FLT
KEYPAD
(RWD)
This halts recording.
CLEAR
START
(STOP)
(FFWD)
(END/BEGIN)
CTRL MENU
(D)
TRACE MESSAGES
FILE ID
:_ (11 CHAR LIMIT)
A B C D E F G H I J
K L M N O P Q R S T
U V W X Y Z . : − /
+ _ # & $ @ < > !
DUMPING TRACE LOG TO:
XXXX.TRC
Press MENU to end.
0 1 2 3 4 5 6 7 8 9
CLEAR
START
Note: Data enclosed in parentheses does not appear on the PI menus and is
provided in these figures for clarification .
Figure 902. Sheet 2 of 2
Portable Interface (PI) Unit, CVR Menu Structures
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COMPONENT MAINTENANCE MANUAL
FA2100CVR
ROSE/RI SOFTWARE
17TES0321 (CDROM)
FA2100 SOFTWARE
DISTRIBUTION DISK
840‐EXXX‐XX
Power
Input
Select
Note:
TO
ENHANCED
PARALLEL PORT
LPT‐1
(EPP)
RECORDER USB FDAU
SIMULATOR (RUFS)
(RI) ADAPTER
17TES0076
Firmware Distribution
Diskette P/N will match the
FA2100 Software Part
Number located on the
recorder 's Name Plate Label.
CICC/2
COMPUTER INTERFACE
COMMUNICATIONS CABLE/2
17TES0070
FA2100 TO CICC/2
COMPUTER INTERFACE
COMMUNICATIONS CABLE
17TES0072
RECORDER INTERFACE (RI)
CABLE ASSY.
17TES0057
READ-OUT
CENTER/6 or /7
17TES0400 or 17TES0700
Note:
Typical view of the back of
the computer.
Views may vary depending
on the computer
AC
INPUT
FA2100
SOFTWARE UPLOAD
(BOOTLOAD) CABLE ASSEMBLY
17TES0058
(use for software
uploading only)
DC
INPUT
Note:
RI = Recorder Interface.
ROSE = Read‐Out Support Equipment.
ROC = Read‐Out Center (ROC/5, /6 or /7)
Note:
The ROC rear connections shown in this diagram are for
general reference and may not reflect the exact connector
location or configuration your ROC system computer.
Note:
The 17TES0058 cable assembly should only be attached
during upload process. Not used when downloading data
or getting recorder status.
FA2100 CVR
RECORDER
Figure 903. FA2100CVR Software Upload Connections
Using Computer Interface & Communications Cable (CICC)
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COMPONENT MAINTENANCE MANUAL
FA2100CVR
P2
28VDC
115VAC
36.0  .2
P1A
P1
2
3
9
17
18
19
115VAC HOT
115VAC COLD
P2
28VDC
GND
FDR DATA OUT LO *
FDR DATA OUT HI *
MONITOR WIRE A
23
MONITOR WIRE B *
24
27
28
29
38
22
19
15
14
16
17
FDR DATA IN LO *
FDR DATA IN HI *
ACID 6 *
ACID 7 *
13
12
2
1
* These signal lines are not used with the FA2100CVR,
they are used with the Combi Recorder CVDR.
Figure 904.
Recorder Interface Cable Assembly P/N: 17TES0057
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
CICC/2
PNR 17−TES0070
3.3 + .2
SER XXXXXXXXX
MFR 06141
DMF MMYYYY
4.4 + .2
3 fT + 2 IN
1.4 + .2
NOTE:
MUST BE USED WITH VER ROSE 3.2/RI 2.0
OR HIGHER SOFTWARE
Figure 905. (Sheet 1 of 2)
Computer Interface Communications Cable/2 (CICC/2) P/N: 17TES0070
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
P1 − POSITRONICS
MC8122D−1038.0
P2
CONN PN AMP 749210−5
SHELL PN AMP 749193−2
10 FT + 3 IN
PIN−1
50 PIN CICC/2
P2 − SCSI CONN
26 PIN FA2100
P1 − DB CONN
1
GSS_PWR
2
GSE_PWR
GND
2
1
GND
TDM_CLK_HI
3
23
SER_D0_RX_HI
TDM_CLK_LO
4
24
SER_D0_RX_LO
TDM_FRM_HI
5
28
SER_D1_RX_HI
TDM_FRM_LO
6
29
SER_D1_RX_LO
TDM_ADD_HI
7
17
SER_C0_I0_HI
TDM_ADD_LO
8
18
SER_C0_I0_LO
11
12
SER_B0_RX_HI
46
CABLE_0
GND
11
SER_FS_AP_HI
10
SER_FS_AP_LO
19
SER_B0_RX_LO
PRGM_VPP_AP
12
PRGM_VPP_SW
13
SER_CLK_HI
14
15
3
4
SER_A0_I0_HI
SER_CLK_LO
SER_A0_I0_LO
SER_DAT_AP_HI
16
15
SER_B1_RX_HI
SER_DAT_AP_LO
17
16
SER_B1_RX_LO
TDM_DAT_HI
9
19
SER_C1_I0_HI
TDM_DAT_LO
18
20
SER_C1_I0_LO
SER_DAT_PI_HI
20
9
SER_B0_TX_HI
SER_DAT_PI_LO
21
10
SER_B0_TX_LO
SER_FS_PI_HI
22
13
SER_B1_TX_HI
SER_FS_PI_LO
23
14
SER_B1_TX_LO
SEL_SMP/FDP
24
21
SER_D0_TX_HI
TEST_MODE_L
25
47
CABLE_1
GSE_PORT_EN
26
48
CABLE_2
49
CABLE_3
NOTE:
MUST BE USED WITH VER ROSE 3.2/RI 2.0
OR HIGHER SOFTWARE
Figure 905. (Sheet 2 of 2)
FA2100 − CICC/2 Interface Cable Assembly P/N: 17TES0072
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
TO
PI OR CICC
OR CICC/2
INTERFACE
TO
FA2100
P1
AMP
748747-1
P2
AMP
748640-1
4.0

.5
P1
PIN1
P2
GSS_PWR
1
39VDC_RTN
2
TDM_CLK_HI
3
TDM_CLK_LO
4
TDM_FRM_HI
5
1
2
3
4
5
6
TDM_FRM_LO
6
7
TDM_ADD_HI
7
8
TDM_ADD_LO
8
TDM_DAT_HI
9
TDM_DAT_LO
18
SER_FS_AP_HI
10
SER_FS_AP_LO
19
GND
11
SEL_SMP/FDP
24
12
PRGM_REC_L
PIN1
9
18
10
19
11
24
12
PRGM_VPP_SW
13
13
SER_CLK_HI
14
15
16
SER_CLK_LO
SER_DAT_AP_HI
14
15
16
SER_DAT_AP_LO
17
20
21
22
SER_DAT_PI_HI
SER_DAT_PI_LO
SER_FS_PI_HI
SER_FS_PI_LO
23
17
20
21
22
23
TEST_MODE_L
25
26
25
GSE_PORT_EN
26
Figure 906.
Programmers Adapter Cable Assembly P/N: 17TES0058
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COMPONENT MAINTENANCE MANUAL
FA2100CVR
CVR AUTOMATED TEST
SOFTWARE (CATS)
17TES0420
J4 USB 4‐PIN
RIU UNIVERSAL SERIAL
BUS INTERFACE
17TES0415
POWER
INPUT
SELECT
RIU DC POWER INPUT
17TES0412 (DC)- J8
RIU AC POWER INPUT
17TES0411 (AC)- J7
DC
AC 5A
1A
RECORDER INTERFACE
UNIT (RIU)
J4
17TES0410 USB
R-SPKR *
GREEN
REAR
CONNECTOR
INTFC
GSE
INTFC
J9
RCDR AC
PWR TEST
J1
SPKRS SND
OUT OUT
BLUE
SOUND CARD
DC
RED
LIGHT
YELLOW
LIGHT
AC
SND
IN
J2
J6
J5
J3
L-SPKR *
SND OUT - GREEN
17TES0413
SND IN - BLUE
17TES0413
J6
RIU AUDIO OUTPUT
(SPKRS)
ROC/6
17TES0400
FA2100
SOFTWARE UPLOAD
CABLE ASSEMBLY
17TES0058
(use for software
uploading only)
RECORDER INTERFACE
CABLE ASSY.
17TES0416
(FA2100‐CICC/2) COMPUTER
INTERFACE COMMUNICATIONS CABLE
ASSY.
17TES0072
* Note: Speakers are optional and not incld
with ROC/6
To order speakers from L-3AR use: p/n:
17TES0425 (110V) or 17TES00426 (220V).
FA2100 CVR RECORDER
Figure 907. ROC/6 w/CVR Automated Test Station Software (CATS)
FA2100CVR TEST SETUP
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
P2
P1
P3
120
Signal Name
From
To
 6.0
IN
Signal Name
From
To
CHANNEL 1 AUDIO IN LO
P1−30
P2−30
PWR IN 115 VAC (HOT)
P1−2
P3−1
DATA LINK FAULT
P1−31
P2−5
PWR IN 115 VAC (COLD)
P1−3
P3−2
CHANNEL 1 AUDIO IN HI
P1−32
P2−32
INDICATOR PWR
P1−4
P2−22
DATA LINK IN (429) (B)
P1−33
P2−34
AUDIO OUT LO
P1−5
P2−1
DATA LINK IN (429) (A)
P1−34
P2−33
AUDIO OUT HI
P1−6
P2−6
CHANNEL 2 AUDIO IN LO
P1−35
P2−35
RECORD ENABLE B
P1−7
P2−8
FDR STATUS
P1−36
P2−20
RECORD ENABLE A
P1−8
P2−7
CHANNEL 2 AUDIO IN HI
P1−37
P2−37
PWR IN +28 VDC 9HOT0
P1−9
P2−9
FDR WORD RATE B
P1−38
P2−38
STOP CVR RECORDING
P1−10
P2−10
OMS IN B (AIRBUS ONLY)
P1−39
P2−39
PUSH−TO−TEST
P1−12
P2−12
OMS IN A (AIRBUS ONLY)
P1−40
P2−34
PREAMP PWR OUT GND
P1−13
P2−13
CHANNEL 3 AUDIO IN LO
P1−41
P2−41
PREAMP PWR OUT HOT
P1−14
P2−14
CVR IDENT PIN
P1−43
P2−4
RESERVERED TEST IND +
P1−15
P2−15
CHANNEL 3 AUDIO IN HI
P1−43
P2−43
RESERVERED TEST IND −
P1−16
P2−16
CHANNEL 4 AUDIO IN LO
P1−45
P2−45
CHASSIS GND−DC RET
P1−17
P2−17
FDR MAINTENANCE
P1−46
P2−21
FDR DATA OUT B (LO)
P1−18
P2−18
CHANNEL 4 AUDIO IN HI
P1−47
P2−47
FDR DATA OUT B (HI)
P1−19
P2−19
ROTOR SPEED IN (LO)
P1−48
P2−48
INT PREAMP ATTEN (−6 dB)
P1−20
P2−58
ROTOR SPEED IN (HI)
P1−49
P2−49
INT PREAMP ATTEN (−12 dB)
P1−21
P2−59
DATA LINK V1 OUT B
P1−50
P2−50
INT PREAMP ATTEN (−24 dB)
P1−22
P2−60
DATA LINK V1 OUT A
P1−51
P2−51
CVR FAULT OUT
P1−23
P2−23
VOICE ERASE A
P1−55
P2−36
FDR FAULT OUT
P1−24
P2−24
DATA LINK VALID
P1−56
P2−66
GMT IN (429) (B)
P1−25
P2−25
VOICE ERASE A
P1−57
P2−57
GMT IN (429) (A)
P1−26
P2−26
FDR DATA IN B (LO)
P1−27
P2−27
FDR DATA IN B (HI)
P1−28
P2−28
FDR WORD RATE A
P1−29
P2−29
Figure 908. Recorder Interface Cable Assembly, 17TES0416
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
1
3
2
1
CABLE, PWR, AC
2
LABEL, “115V/400Hz”
3
LABEL, “17−TES0411”
Figure 909.
AC 115 VAC/400Hz Power Input Cable Assembly P/N: 17TES0411
4
Strip and Tin
144.0  1.0 IN
2X 2.00  .13 IN
2X 1.00  .13 I
2*
5 (See Note)
* WIRE CHART
BLACK OUTER
WHITE INNER
1
3
Note: TRIM SHIELD EVEN WITH OUTER JACKET.
APPLY SLEEVING ITEM 5 OVER OUTER JACKET TRANSITION
1
WIRE, # 22, STRD, 2 COND, SHLD
2
CONN, DC PWR PLUG
3
LABEL, “DC POWER”
4
LABEL, “17−TES0412”
5
TBG, 3/16, THERMO−FIT, BLK
Figure 910.
DC +28VDC Power Input Cable Assembly P/N: 17TES0412
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
LOOP BACK
CONNECTOR
Figure 911. Audio Setup Cable Assembly, 17TES0417
MICROPHONE
SWITCH
INT
EXT
INPUT
35
40
30
45
KHZ
TUNNING
OFF
GAIN
BAT.
TEST
OK
AUDIO
OUTPUT
ULTRASONIC TEST SET
MODEL 42A12( )
UNDERWATER
LOCATOR
DEVICE
42A12( )
ULTRASONIC
TEST SET
Figure 912. ULD Test Set-Up
C.
Audio Data Link Player Software
The FA2100CVR Audio & Data Link Player (ADLP) software provides a user−friendly
interface for initiating audio and data link message retrieval and playback functions
for the Model FA2100CVR, part number 2100−1025−( ). It also provides the capability to decompress the data into standard waveform audio files (.wav) for playback
using conventional audio media players.
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
All other Model FA2100CVR part numbers can use this utility software to playback
the CVR audio data but will not be able to analyze any data link messages since
these other CVR part number recorders do not support the recording of data link
messages.
(1)
Hardware Requirements for Audio & Data Link Player Software
The ADLP software, p/n: 17TES0436, is designed to operate on an IBM/IBMcompatible computer containing specific required hardware.
Assembly is a standard personal computer with tower case; includes the following standard features and may include features not listed hereon. Upgraded
features are acceptable.
Dual core CPU 2.5 GHz or greater
Motherboard with EPP support, compatible with PCMCIA reader (below)
Four USB 2.0 connections
4 GB or greater memory
17” SVGA Color LCD Monitor and Graphics Adapter
Must support 1024x768 and 1280 x 1024
Samsung SyncMaster 710n is an example of a compliant monitor
300 GB Hard Drive 7200 RPM or better
8x4x32X (or better) CD−RW/DVD−RW
104 Keyboard
Windows 7 Professional 32−bit edition OS
2−Button Mouse
Ethernet 100 MHz or greater
2nd Ethernet (Intel Pro/100m PCI or equivalent)
Audigy sound card
PCMCIA Dual Slot PCI installed in 3.5” External Bay
Must be compatible with motherboard above
Envoy Data EDC−F2PCI is an example of compliant reader
(2)
System must be CE and suitable for export.
(3)
Associated user/installation manuals and CDs are to be included with computer.
Table 902. Specification Control Drawing
Configuration
−00
Next Assy No.
Used On
Audio Data Link Player Software, Version 3
ROC/7
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
(4)
Hardware Requirements for Downloading CVR Data
The FA2100CVR must be removed from the aircraft prior to downloading voice
data. Data Link messages, however, can be downloaded while the recorder is
on the aircraft as this data is accessed in a similar manner to standard flight
data.
There are two methods to download audio and data link information from the
Model FA2100CVR memory:
(a)
Directly download into either a ROC or RAU using the Computer Interface
Control Cable Interface (CICCIfc) utility software in conjunction with the
CICC/2 Interface Cable assembly; p/n: 17TES0070 & 17TES0072.
(b)
Using the Portable Interface (PI) Unit, p/n: 17TES0043 with Mod−Dot #6.
This device is used to download the FA2100CVR voice and data link information to a PCMCIA memory card which then can be transferred into either a ROC or RAU that has the ADLP software installed for playback.
For detailed operational instructions, refer to the Audio Data Link Player Software
Operator’s Manual, P/N: 165E3596−00.
D.
CVR Download Cable
Cable can be used to downloaded data while the recorder is on the aircraft using the Portable Interface Unit. The data in the CVR can not be erase while using the cable. Refer to the Installation and Operation Manual, Cockpit Voice
Recorder, Model FA2100CVR, Part Number 165E1846-00.33
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
60in."6 in.
P1
J1
P1
J1
115 VAC HOT
2
2 115 VAC HOT
AC COMMON COLD
3
3 AC COMMON COLD
5
5
6
6
7
7
8
8
9
9 +27.5 VDC INPUT
+27.5 VDC INPUT
10
10
12
12
13
13
14
14
15
15
16
CHASSIS GND 17
16
57
57
CONNECTS TO
FA2100 CVR
17 CHASSIS GND
CONNECTS TO
CVR TRAY
Figure 913.
FA2100CVR Download Cable, p/n 17TES0078,
Wiring Diagram
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
ILLUSTRATED PARTS LIST
1. GENERAL
This section contains the following sections: introduction, equipment designator list, numerical index, and detailed parts list. The introduction of this section describes usage of
the IPB, a listing of abbreviations, and a list of vendor names, addresses, and codes per
the current issue of “Federal Supply Code for Manufacturers”, catalog handbook H4–1.
The Equipment Designator Index provides a cross reference from manufacture reference
designator to manufacturing part number. The Numerical Index provides a numerical listing of all manufacturing part numbers.
2. PURPOSE
The purpose of this Illustrated Parts List is to assist maintenance and supply personnel in
requisitioning, storing, issuing and identifying parts to maintain the FA2100 Cockpit Voice
Recorder. This Illustrated Parts List is not to be taken as the authority for the procedure
of assembly or disassembly. Overhaul or repair should be done by authorized personnel
only.
3. ABBREVIATIONS
The following abbreviations are used in this section:
Abbreviation
AR
ASSY
EFF
FIG
NHA
NO
RF
Meaning
As Required
Assembly
Effectivity
Figure
Next Higher Assembly
Number
Reference
4. EQUIPMENT DESIGNATOR INDEX
The Equipment Designator Index is an index of designators assigned to electrical parts as
shown in electrical wiring and schematic diagrams. Since Level 2 repair is the maintenance philosophy of the FA2100CVR, there are no Equipment designators listed.
Use or disclosure of information on this sheet is subject
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Illustrated Parts List
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
5. NUMERICAL INDEX
The Numerical Index is a complete listing of parts included in the Detail Parts List, cross–
referenced to the applicable figure and item number, L-3’s part numbers, the manufacturer’s part numbers and total quantity required.
Part numbers are arranged in a alphanumerical sequence beginning at the extreme left–
hand position and continue from left to right, one position at a time. The order to precedence in beginning the part number arrangement is as follows:
A. Letters A through Z (Alphabetical Os are considered as numerical zeros).
B. Numerals 0 through 8.
Part number entry is limited to a single line and does not exceed fifteen characters.
The FIGURE number and ITEM number columns contain the figure and item number(s)
for all parts listed. When more than one figure and item number are shown for the same
part number, the part number is not repeated.
6. DETAIL PARTS LIST
The Detail Parts List consists of illustrations and columnar parts breakdown of the component and all assemblies, subassemblies, and parts that can be disassembled, repaired
and reassembled, or replaced. Items that are riveted, welded or spun over are not listed.
Parts made of bulk stock such as wire, tape or bonding braid are also not listed. Illustrations are each assigned a figure number, commencing with Figure 1 and progressing in
sequence.
The FIGURE AND INDEX NUMBER column reflects the assigned figure number of the illustration in which the item is shown and the item number listed on the illustration. Figure
numbers are shown for the first entry of each figure and at the top of each subsequent
column. When there is more than one type of subassembly for the same function additional figures are included with the same number, but followed by an additional alpha designator (such as A, B, etc.).
Each part number listed in the Detail Parts List is assigned an index number. Index numbers begin with number 1 for each illustration and in broken sequence to facilitate the insertion of new items which are not variants of existing items. Items listed but not illustrated are identified by a dash to the left of the index number.
The PART NUMBER column contains the manufacturer’s part number when the part is
purchased from a source other than Aviation Recorders, or the Aviation Recorders part
number for those parts which must be purchased from Aviation Recorders Division.
When the manufacturer’s part number is used for any parts, the Aviation Recorders num-
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Illustrated Parts List
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
ber is also shown enclosed in parentheses in the NOMENCLATURE column. When standard parts (such as MS, AN, RC, CP, etc.) are used, vendor codes are not assigned to
these parts. However, for non–standard parts the vendor code is assigned in the NOMENCLATURE column and is preceded by the letter “V.” It corresponds to the Federal
Supply Code for Manufacturers, (FSCM) now known as Commercial and Government Entity (CAGE) as listed in Cataloging Handbook H4/H8.
When a part has multiple vendors, all part numbers are listed in the PART NUMBER column. The first vendor will be assigned an item number and each subsequent part number is assigned the same item number with an alpha variant.
The NOMENCLATURE column describes the part or assembly. Nomenclature wording is
arranged so that the identifying noun or key word is always the first part of the description; this is followed by modifying words. Standard abbreviations are used as necessary.
Assemblies which are not broken down within a listing but which are covered by a separate figure will carry the notation “(SEE FIG. – FOR DETAIL BREAKDOWN).” The listing
of the assembly in the breakdown figure will carry the reference “(SEE FIG. – FOR NHA)”.
If the vendor is not L−3 Aviation Recorders, the manufacturer’s vendor code may be included in parentheses in this column.
The indenture system, provided by the numbers “1” through “6” in the heading, shows the
relationship of one part to another; for example, a part listed under indenture “3” is a component of the assembly listed under indenture “2” immediately above it. Items used to attach parts or assemblies to each other are designated “ATTACHING PARTS” and are
listed immediately following the item or items they attach. The symbol “* * *” denotes the
end of attaching parts.
The EFFECTIVITY CODE column establishes parts’ relationship with units or assemblies
which are essentially the same but have variations. These units or assemblies are the
lead times on each figure. These units or assemblies are assigned reference letters such
as A, B, C, D, etc. Parts which are not common to all configurations but are associated
with one or more of the coded lead items carry the letter or letters assigned to the lead
item with which it is associated. If a part is common to all lead items, the EFFECTIVITY
CODE column is blank.
The UNITS PER ASSY column lists the quantity of the item required in one assembly in
which it is a component. It is, therefore, not necessarily the total quantity of the part required in the complete equipment; the equipment total can be found in the Numerical Index. The term “RF” denotes that the assembly has been previously listed in the parts
breakdown.
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23–70–04
Illustrated Parts List
Rev. 15 Page 1003
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AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
7. PART NUMBERING
L−3AR does not delineate its part numbers by special characters, such as the “−” dash character.
L−3AR considers its part numbers with or without the use of special characters to be the same, for
example, there is no difference between part number 266−E0305−00, 266E0305−00, or
266E030500. To be in compliance with ARINC Specifications 100 and 200 the part numbers listed
in this manual use the following format: 266E0305−00. L−3AR typically identifies its part numbers
on other documents such as internal engineering drawings, purchase orders, component labels,
shipping orders, Form 8130’s, and certification documents with the format: 266−E0305−00.
8. MANUFACTURER’S CODE
Due to the Level−2 maintenance philosophy used with the FA2100 CVR, all spare parts
will be ordered through L−3 Communications. L3AR Vendor Code, manufacturer name
and address, as listed in the “Federal Supply Codes for Manufacturers” Cataloging Handbook H4/H8, Commercial and Government Entity (CAGE) codes, (formerly FSCM), and/or
the NATO Code as applicable (Ref. ATA Spec. 200), is listed below. The CAGE code is
the vendor (V) code listed in parentheses in the NOMENCLATUE column of the Detailed
Parts List.
Code
V06141
Manufacturer
L-3 Aviation Recorders
100 Cattlemen Road
Sarasota, FL 34232
9. L−3 AVIATION RECORDERS (L−3AR) AUTHORIZED PARTS
L−3AR has performed additional environmental testing on the Stainless and Titanium
Crash−Survivable Memory Units (CSMU) for all Models of recorders using the L−3AR
90−Day Underwater Locator Beacon, PN 266E5542−00, and mounting screws that make
up the ULB Conversion Kit, p/n: 068E5542−00. These tests were conducted to ensure
that the transition from the 30−day ULB to 90−Day ULB for CSMUs used on all Models of
L−3AR Recorders meet the requirements of DO−160G Vibration and ED−112A Beacon
Shear and Tensile Test.
The results of these tests are contained in the following L−3AR Environmental Test
Reports, Document Numbers:
F
ENV284 − MODELS FA2100 Style CSMUs: All Part Numbers: FA2100CVR,
FDR, CVDR, MADRAS, DASU & APR2500.
F
ENV285 − Models FA5000 − Titanium CSMUs: All Part Numbers: FA5000CVR,
FDR, CVDR & MADRAS
F
ENV286 − SRVIVR Style CSMUs: All Part Numbers: SRVIVRCVR, FDR &
CVDR
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
The document reference is online, please check the correspondence between the online documentation and the printed version.
23–70–04
Illustrated Parts List
Rev. 15 Page 1004
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
To ensure integrity of the locating device function and the FAA Manufacturing Inspection
District Office (MIDO) approved installation and assembly of all L−3AR Recorder models,
it is required that only the L-3AR ULB Conversion Kit, p/n: 068E5542−00 be used when
converting from a 30−Day ULB to a 90−Day ULB.
Also the four attaching ULB hex−screws (1−75) must be replaced when the 90−Day ULB
is removed or replaced.
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
The document reference is online, please check the correspondence between the online documentation and the printed version.
23–70–04
Illustrated Parts List
Rev. 15 Page 1005
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
10. CONFIGURATION MATRIX
Listed below are the current configurations for the FA2100 Cockpit Voice Recorder (CVR).
Part Number 2100-1010-( ) is capable of storing 30 minutes of voice data while p/n:
2100-1020-( ) is capable of storing 2 hours of voice data, p/n: 2100−1020−02 has FSK
capability, p/n: 2100−1025/1026/1027−( ) has OMS capability.
2100−1010−00
ARINC 757, 30 MIN. CVR, 1/2 ATR SHORT
2100−1010−50
ARINC 757, 30 MIN. GA CVR, 1/2 ATR SHORT, 28 VDC ONLY
2100−1010−51
ARINC 757, 30 MIN. GA CVR, 1/2 ATR SHORT, TITANIUM CSMU W/ RTV, 28
VDC ONLY
2100−1020−00
ARINC 757, 2−HR. CVR, 1/2 ATR SHORT
2100−1020−02
ARINC 757, 2−HR. CVR W/ FSK
2100−1020−50
ARINC 757, 2−HR. GA CVR, 1/2 ATR SHORT, 28 VDC ONLY
2100−1020−51
ARINC 757, 2−HR. GA CVR, 1/2 ATR SHORT, TITANIUM CSMU W/ RTV, 28
VDC ONLY
2100−1025−02
ARINC 757, 2−HR. CVR W/ OMS, 4 CHANNEL HIGH QUALITY
2100−1025−12
ARINC 757, 2−HR. CVR W/ OMS, 4 CHANNEL HIGH QUALITY (CYRILLIC)
2100−1025−22
ARINC 757, 2−HR. CVR W/ OMS, 4 CHANNEL HIGH QUALITY W/ RIPS
2100−1025−24
ARINC 757, 2−HR. CVR W/ OMS, 4 CHANNEL HIGH QUALITY W/ RIPS S/W
2100−1026−02
ARINC 757, 2−HR. CVR W/ OMS, 4 CHANNEL HIGH QUALITY W/ RIPS
2100−1027−02
ARINC 757, 2−HR. CVR W/ OMS, 4 CHANNEL HIGH QUALITY W/ RIPS
2100−1220−00
ARINC 757, 2−HR. CVR, 1/2 ATR SHORT, 90−DAY BEACON
2100−1220−02
ARINC 757, 2−HR. CVR W/ FSK, 90−DAY BEACON
2100−1225−22
ARINC 757, 2−HR. CVR W/ OMS, 4 CHANNEL HIGH QUALITY W/ RIPS,
90−DAY BEACON
2100−1225−24
ARINC 757, 2−HR. CVR W/ OMS, 4 CHANNEL HIGH QUALITY W/ RIPS S/W,
90−DAY BEACON
2100−1226−02
ARINC 757, 2−HR. CVR W/ OMS, 4 CHANNEL HIGH QUALITY W/ RIPS,
90−DAY BEACON
2100−1227−02
ARINC 757, 2−HR. CVR W/ OMS, 4 CHANNEL HIGH QUALITY W/ RIPS,
90−DAY BEACON
2100−1925−22
ARINC 757, 2−HR. CVR W/ OMS, 4 CHANNEL HIGH QUALITY W/ RIPS
90−DAY BEACON
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
The document reference is online, please check the correspondence between the online documentation and the printed version.
23–70–04
Illustrated Parts List
Rev. 15 Page 1006
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
NUMERICAL INDEX
PART NUMBER
BB1P061H05
BB1P141H16
MS15795−803
MS16995−52
MS16995*54
MS21044C04
MS24693−C26
MS24693−C4
MS24693−C4
MS24693−C6
MS24693−C7
MS51957−14
MS51957−14
MS51957−14
MS51957−14
MS51957*28
MS51957*45
279800024
2290200365
2529800107
2739800201
9030100047
9030100047
9030100049
9030100075
016E1589−00
016E4797*00
016E5352−00
024E1620−00
024E1620−01
024E2659*01
024E3424*00
024E3424*03
027E1590*00
042E1597*00
042E1597*01
075E1598*00
AIRLINE
PART NO.
FIG.
ITEM
TTL
REQ
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
25B
190B
145
190A
75
150
95
130
140
141A
141B
160
180
125A
125B
25A
60
225
127
235
152
205
245
240A
240B
70
146A
146B
165A
170A
165B
170B
165C
35
5A
5B
20A
10
4
2
4
4
2
8
4
2
2
2
4
10
6
7
10
4
1
1
1
1
1
1
1
1
2
1
1
2
1
1
2
1
1
1
1
1
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
The document reference is online, please check the correspondence between the online documentation and the printed version.
23–70–04
Illustrated Parts List
Rev. 15 Page 1007
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
PART NUMBER
075E1806*00
111*98*00097
1256 (DEL.)
140E4207*00
147E1679−00
166*98*00359 (DEL.)
166*98*00361 (DEL.)
166E1594*00
166E1595*00
166E1647*00
191E1603−00
191E1603−01
192E1599*00
197E1746−00
205E1591−00
205E1593−00
205E1596−00
205E1763−00
205E1763−01
205E1763−11
205E1849−00
205E1849−02
205E1849−03
205E1849−04 (DEL.)
205E1849−10
205E1849−13
205E1849−14 (DEL.)
205E1849−17
205E1931−00
205E2502−10
205E2502−11
205E2502*14
205E2502−21
205E2502*24
205E2502*34
205E2502−38
205E2502−52
205E2503−01
AIRLINE
PART NO.
FIG.
ITEM
TTL
REQ
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
20B
55
45
151
210
65
66
10
15
50
90A
90B
30
220
175A
105A
155A
105B
105C
105F
155B
155D
155C
155E
155F
155G
155H
155J
175B
175C
175D
175E
175G
175J
175K
175H
175F
105D
1
2
1
1
1
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
The document reference is online, please check the correspondence between the online documentation and the printed version.
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
23–70–04
Illustrated Parts List
Rev. 15 Page 1008
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
PART NUMBER
205E2503−05
205E2503−08
205E3977*10
205E3977*12
205E3977*13
205E3977*14 (DEL.)
205E3977*17
205E3977*20
205E3977*22
205E3977*23
205E3977*24 (DEL.)
205E3977*29
205E3977*37
2100*1010*00
2100*1010*50
2100*1010*51
2100*1020*00
2100*1020*02
2100*1020*50
2100*1020*51
2100*1020*90 (DEL.)
2100*1020*91 (DEL.)
2100*1020*93 (DEL.)
2100*1025*02
2100*1025*12
2100*1025*22
2100*1025*24
2100*1026*02
2100*1027*02
2100*1220*00
2100*1220*02
2100*1225*22
2100*1225*24
2100*1226*02
2100*1227*02
2100*1925*22
229E0574*00
230E2520−00
AIRLINE
PART NO.
FIG.
ITEM
TTL
REQ
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
105E
105G
155K
155L
155M
155N
155P
155R
155S
155T
155U
155V
155W
1A
1E
1F
1B
1C
1G
1H
1K
1D
1J
1L
1M
1N
1R
1P
1T
1U
1V
1W
1AA
1Y
1AB
1AC
40
200A
1
1
1
1
1
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
The document reference is online, please check the correspondence between the online documentation and the printed version.
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
23–70–04
Illustrated Parts List
Rev. 15 Page 1009
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
PART NUMBER
230E2521*00
230E5675*00
253E1568−00
253E1568−01
253E1568−06
253E1568−07
253E1568−33
253E1568−38
253E1568−39
253E1568−40
253E1568−41
253E4427-33
253E5675-00
253E5675-11
253E5675-20
266E0305−00
266E0305−01
266E0305−02 (DEL.)
266E5542−00
297−98−00087
297−98−00257
297−98−00283
297−98−00319
3M#7201 (DEL.)
742E1619−00
742E1619−03
9300−388
AIRLINE
PART NO.
FIG.
ITEM
TTL
REQ
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
28
200B
185B
185A
185C
185D
185E
185F
185G
185H
185J
185K
185L
185M
185N
80A
80B
80C
80D
120A
115
110
120B
100
135A
135B
85
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
4
1
2
4
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
The document reference is online, please check the correspondence between the online documentation and the printed version.
1
1
1
23–70–04
Illustrated Parts List
Rev. 15 Page 1010
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
25
20
A
B
80A
80B
80C
80D
185
A
B
205
120
110
C
190
135
141
146
151
185
C
160
125
155
A
B
115
200
165
(W2)
105
B
A
170
(W1)
120
160
165
(W3)
180
5
175
10
15*
(farside)
Figure 1. (Sheet 1 of 2)
Model FA2100 Cockpit Voice Recorder
PN: 2100-1010-( ) & 2100-1X2X-( )
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
The document reference is online, please check the correspondence between the online documentation and the printed version.
23–70–04
Illustrated Parts List
Rev. 15 Page 1011
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
125
151
141
146
141
141
90
130
B
B
View
95
80A/B/C
REFERENCE ONLY
70
75
REPLACEMENT DATE
85
C
60
40
30
A
50
View
View
C
45
55
A
Figure 1. (Sheet 2 of 2)
Model FA2100 Cockpit Voice Recorder
PN: 2100-1010-( ) & 2100-1X2X-( )
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
The document reference is online, please check the correspondence between the online documentation and the printed version.
23–70–04
Illustrated Parts List
Rev. 15 Page 1012
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
FIG.
ITEM
PART
NUMBER
UNITS
PER
EFF
CODE ASSY
AIRLINE NOMENCLATURE
PART NO. 1234567
1
1A
2100−1010−00
COCKPIT VOICE RECORDER
FA2100 CVR, ARINC 757, 30 MIN. CVR,
1/2 ATR SHORT (OBSOLETE)
A
RF
1B
2100−1020−00
COCKPIT VOICE RECORDER
FA2100 CVR, ARINC 757, 2−HR. CVR,
1/2 ATR SHORT
B
RF
1C
2100−1020−02
COCKPIT VOICE RECORDER
FA2100 CVR, ARINC 757, 2−HR. CVR
W/ FSK, 1/2 ATR SHORT
C
RF
1D
2100−1020−91
DELETED
1E
2100−1010−50
COCKPIT VOICE RECORDER
FA2100 CVR, ARINC 757, 30 MIN. GA
CVR, 1/2 ATR SHORT, 28 VDC ONLY
(OBSOLETE)
E
RF
1F
2100−1010−51
COCKPIT VOICE RECORDER
FA2100 CVR, ARINC 757, 30 MIN. GA
CVR, 1/2 ATR SHORT, 28 VDC ONLY,
TITANIUM CSMU, W/ RTV
F
RF
1G
2100−1020−50
COCKPIT VOICE RECORDER
FA2100 CVR, ARINC 757, 2−HR. GA CVR,
1/2 ATR SHORT, 28 VDC ONLY
(OBSOLETE)
G
RF
1H
2100−1020−51
COCKPIT VOICE RECORDER
FA2100 CVR, ARINC 757, 2−HR. GA CVR,
1/2 ATR SHORT, 28 VDC ONLY, TITANIUM
CSMU, W/ RTV (OBSOLETE)
H
RF
1J
2100−1020−93
DELETED
1K
2100−1020−90
DELETED
1L
2100−1025−02
COCKPIT VOICE RECORDER
FA2100 CVR, ARINC 757, 2−HR. CVR,
1/2 ATR SHORT, OMS
L
RF
1M
2100−1025−12
COCKPIT VOICE RECORDER
FA2100 CVR, ARINC 757, 2−HR. CVR,
1/2 ATR SHORT, OMS (CYRILLIC)
(RUSSIAN TEXT)
M
RF
Use or disclosure of information on this sheet is subject
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23–70–04
Illustrated Parts List
Rev. 15 Page 1013
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
FIG.
ITEM
PART
NUMBER
UNITS
PER
EFF
CODE ASSY
AIRLINE NOMENCLATURE
PART NO. 1234567
1
1N
2100−1025−22
COCKPIT VOICE RECORDER
FA2100 CVR, ARINC 757, 2−HR. CVR,
1/2 ATR SHORT, OMS
N
RF
1P
2100−1026−02
COCKPIT VOICE RECORDER
FA2100 CVR, ARINC 757, 2−HR. CVR,
1/2 ATR SHORT, OMS
P
RF
1R
2100−1025−24
COCKPIT VOICE RECORDER
FA2100 CVR, ARINC 757, 2−HR. CVR,
1/2 ATR SHORT, OMS , RIPS S/W
R
RF
1T
2100−1027−02
COCKPIT VOICE RECORDER
FA2100 CVR, ARINC 757A, 2−HR. CVR,
1/2 ATR SHORT, OMS
T
RF
1U
2100−1220−00
COCKPIT VOICE RECORDER
FA2100 CVR, ARINC 757, 2−HR. CVR,
1/2 ATR SHORT, 90−DAY BEACON
U
RF
1V
2100−1220−02
COCKPIT VOICE RECORDER
FA2100 CVR, ARINC 757, 2−HR. CVR
W/ FSK, 1/2 ATR SHORT, 90−DAY
BEACON
V
RF
1W
2100−1225−22
COCKPIT VOICE RECORDER
FA2100 CVR, ARINC 757, 2−HR. CVR,
1/2 ATR SHORT, OMS, 90−DAY BEACON
W
RF
1Y
2100−1226−02
COCKPIT VOICE RECORDER
FA2100 CVR, ARINC 757, 2−HR. CVR,
1/2 ATR SHORT, OMS, 90−DAY BEACON
Y
RF
1AA
2100−1225−24
COCKPIT VOICE RECORDER
FA2100 CVR, ARINC 757, 2−HR. CVR,
1/2 ATR SHORT, OMS , RIPS S/W,
90−DAY BEACON
AA
RF
1AB
2100−1227−02
COCKPIT VOICE RECORDER
FA2100 CVR, ARINC 757A, 2−HR. CVR,
1/2 ATR SHORT, OMS, 90−DAY BEACON
AB
RF
1AC
2100−1925−22
COCKPIT VOICE RECORDER
FA2100 CVR, ARINC 757, 2−HR. CVR,
1/2 ATR SHORT, OMS, 90−DAY BEACON
AC
RF
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
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23–70–04
Illustrated Parts List
Rev. 15 Page 1014
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
FIG.
ITEM
PART
NUMBER
UNITS
PER
EFF
CODE ASSY
AIRLINE NOMENCLATURE
PART NO. 1234567
1
5A
042E1597−00
.CHASSIS, SHORT 1/2 ATR ARINC
A, B, C,
E, F, G,
H, L, M,
N, P, R,
U, V,
W, Y,
AA, AC
1
5B
042E1597−01
.CHASSIS, SHORT 1/2 ATR ARINC, AP
T, AB
1
10
166E1594−00
.TAPE, REFLECTIVE, ENGLISH
FLIGHT RECORDER DO NOT OPEN
1
15
166E1595−00
.TAPE, REFLECTIVE, FRENCH
ENREGISTREUR DE VOL NE PAS OUVRIR
1
20A
075E1598−00
.COVER, CHASSIS, SHORT
A, B, C,
L, M, N,
P, R, T,
U, V,
W, Y,
AA, AB,
AC
1
20B
075E1806−00
.COVER, CHASSIS, SHORT, LIGHTWEIGHT
E, F, G,
H
1
ATTACHING PARTS
−
25A
MS51957−28
.SCREW, PAN HEAD, 6−32 x 3/8
(V06141) (2290200085) (SUPSD BY
25B PER SB004)
10
25B
BB1P061H05
.SCREW, PAN HEAD, SEALING 6−32 x 5/16
(V06141) (2299800465) (SUPSDS 25A
PER SB004)
10
28
230E2521−00
.SEAL, CHASSIS COVER, SHORT-BOX
***
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
The document reference is online, please check the correspondence between the online documentation and the printed version.
A, B, C,
L, M, N,
P, R, T,
U, V,
W, Y,
AA, AB,
AC
23–70–04
Illustrated Parts List
Rev. 15 Page 1015
Apr. 14/16
1
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
FIG.
ITEM
PART
NUMBER
UNITS
PER
EFF
CODE ASSY
AIRLINE NOMENCLATURE
PART NO. 1234567
1
30
192E1599−00
.FRONT PANEL ASSEMBLY
1
35
027E1590−00
.CAP,PROTECTIVE METAL
1
ATTACHING PARTS
40
229E0574−00
.SCREW, JACK, KNURLED
***
1
−
45
1256
.DELETED
1
−
50
166E1647−00
.LABEL, IDENT, COCKPIT VOICE RECORDER
55
111−98−00097
.FASTENER, HOOK, NAS622
(V94867) (MFG. NO. HDH-4)
2
ATTACHING PARTS
60
MS51957−45
.SCREW, PAN HEAD, 8−32 X 1/2
(V06141) (2290200102)
***
−
65
166−98−00359
.DELETED
−
66
166−98−00361
.DELETED
70
016E1589-00
.BRACKET, BEACON, MOUNT
4
2
ATTACHING PARTS
75
MS16995−54
.SCREW, SCHCAP, 1/4−20 X 1−1/2
(V06141) (2290200424)
***
80A
266E0305-00
BEACON, ACOUSTIC, UNDERWATER
(SUPSD BY 80D PER SB022)
DUKANE (V94970) (DK-120)
FOR BATTERY REPLACEMENT ORDER
30−DAY BATTERY KIT (147E0305−00)
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
The document reference is online, please check the correspondence between the online documentation and the printed version.
4
A, B, C,
E, F, G,
H, L, M,
N, P, R,
T
23–70–04
Illustrated Parts List
Rev. 15 Page 1016
Apr. 14/16
1
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
FIG.
ITEM
PART
NUMBER
UNITS
PER
EFF
CODE ASSY
AIRLINE NOMENCLATURE
PART NO. 1234567
1
80B
266E0305-01
.BEACON, ACOUSTIC, UNDERWATER
(SUPSD BY 80D PER SB022)
DUKANE (V94970) (DK-120)
FOR BATTERY REPLACEMENT ORDER
30−DAY BATTERY KIT (147E0305−00)
A, B, C,
E, F, G,
H, L, M,
N, P, R,
T
1
80C
266E0305-02
.BEACON, ACOUSTIC, UNDERWATER,
(SUPSD BY 80D PER SB022)
DUKANE (V94970) (ELP−362D)
FOR BATTERY REPLACEMENT ORDER
30−DAY BATTERY KIT (147E0305−00)
A, B, C,
E, F, G,
H, L, M,
N, P, R,
T
1
80D
266E5542-00
.BEACON, LOCATOR, UNDERWATER,
90−DAY (SUPSDS ITEM 80A, 80B, 80C,
PER SB022 (CODE F) (HAZMAT CLS9)
1
FOR BATTERY REPLACEMENT, ORDER
90−DAY ULB BATTERY KIT
(147E5542−00)
85
9300-388
.PLUG
1
90A
191E1603-00
.REAR PANEL ASSEMBLY, ARINC 757
90B
191E1603-01
.REAR PANEL ASSEMBLY, ARINC 757A
A, B, C,
E, F, G,
H, L, M,
N, P, R,
U, V,
W, Y,
AA, AC
1
T, AB
1
ATTACHING PARTS
−
95
MS24693-C26
.SCREW, FLAT HEAD, 6−32 X 3/8
(V06141) (2290200361)
***
100
3M#7201
DELETED
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
The document reference is online, please check the correspondence between the online documentation and the printed version.
8
23–70–04
Illustrated Parts List
Rev. 15 Page 1017
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
FIG.
ITEM
PART
NUMBER
UNITS
PER
EFF
CODE ASSY
AIRLINE NOMENCLATURE
PART NO. 1234567
1
105A
205E1593-00
.PWA, AIRCRAFT INTERFACE, ARINC 757
(SUPSD BY 105E, PER SB015)
A, B, C
1
105B
205E1763-00
.PWA, AIRCRAFT INTERFACE, GA,
ARINC 757 (OBS, SUPSD BY 105C,
PER ECO 9432)
E, F, G,
H
1
105C
205E1763-01
.PWA, AIRCRAFT INTERFACE, GA,
DC, ARINC 757 (SUPSDS ITEM 105B PER
ECO 9432) (SUPSD BY 105F PER SB015)
E, F, G,
H
1
105D
205E2503-01
.PWA, AIRCRAFT INTERFACE,
ARINC 757−4
L, M, N,
P, R,W,
Y, AA,
AC
1
105E
205E2503-05
.PWA, AIRCRAFT INTERFACE,
ARINC 757−4 (SUPSDS ITEM 105A, PER
SB015)
A, B, C,
U, V
1
105F
205E1763-11
.PWA, AIRCRAFT INTERFACE, GA,
DC, ARINC 757 (SUPSDS ITEM 105C,
PER SB015)
E, F, G,
H
1
105G
205E2503-08
.PWA, AIRCRAFT INTERFACE
T, AB
1
ATTACHING PARTS
4
110
297-98-00283
.STANDOFF, 3/16 HEX, M-F4-40 X 1.03
2
115
297-98-00257
.STANDOFF, 3/16 HEX, 4-40 X 1-1/32
1
120A
297-98-00087
.STANDOFF, 3/16 HEX, M-F4-40 X 3/4 SST
(SUPSD BY 120B, PER SB 015)
4
120B
297-98-00319
.STANDOFF, 3/16 HEX, M-F4-40 X 7/8
(SUPSDS ITEM 120A, PER SB 015)
4
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
The document reference is online, please check the correspondence between the online documentation and the printed version.
23–70–04
Illustrated Parts List
Rev. 15 Page 1018
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
FIG.
ITEM
PART
NUMBER
UNITS
PER
EFF
CODE ASSY
AIRLINE NOMENCLATURE
PART NO. 1234567
1
125A
MS51957-14
.SCREW, PAN HEAD, 4-40 X 5/16
(V06141) (2290200074)
A, B, C,
E, F, G,
H, L, M,
N, P, R,
U, V,
W, Y,
AA, AC
6
125B
MS51957-14
.SCREW, PAN HEAD, 4-40 X 5/16
(V06141) (2290200074)
T, AB
7
127
2290200365
.SCR,FLH ,8−32 X1/4
T, AB
1
130
MS24693-C4
.SCREW, FLAT HEAD, 4-40 X 3/8
(V06141) (2290200356)
4
***
135A
742E1619-00
.CAPACITOR ASSEMBLY, STORAGE
(SUPSD BY 135B, PER SB017)
1
135B
742E1619-03
.CAPACITOR ASSEMBLY, STORAGE
(SUPSDS ITEM 135A, PER SB 017)
1
ATTACHING PARTS
140
MS24693-C4
.SCREW, FLAT HEAD, 4-40 X 3/8
(V06141) (2290200356)
(SUPSD BY 141A, PER SB016)
141A
MS24693-C6
.SCREW, FLAT HEAD, 4−40 X 1/2
(V06141) (2290200357)
(SUPSDS ITEM 140, PER SB016)
A, B, C,
E, F, G,
H, L, M,
N, P, R,
U, V,
W, Y,
AA, AC
2
141B
MS24693-C7
.SCREW, FLAT HEAD, 4−40 X 5/8
(V06141) (2290200357)
(SUPSDS ITEM 140, PER SB016)
T, AB
2
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
The document reference is online, please check the correspondence between the online documentation and the printed version.
2
23–70–04
Illustrated Parts List
Rev. 15 Page 1019
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
FIG.
ITEM
PART
NUMBER
UNITS
PER
EFF
CODE ASSY
AIRLINE NOMENCLATURE
PART NO. 1234567
1
145
MS15795-803
.WASHER, #4, FLAT, STAINLESS STEEL
(V06141) (2730200004)
(SUPSD BY 146, PER SB016)
146A
016E4797−00
.BRACKET, CAPACITOR
(SUPSDS ITEM 145, PER SB016)
146B
016E5352-00
.BRACKET, PLASTIC CAPACITOR
150
MS21044C04
.NUT, HEX, SELF-LOCKING, 4-40
(V06141) (2870200019)
(SUPSD BY 151, PER SB016)
151
140E4207−00
.INSULATOR, LATCH, FC
(SUPSDS ITEM 150, PER SB016)
152
2739800201
.WASHER,SHOULDER,.115ID
***
155A
205E1596-00
.PWA, AUDIO COMPRESSOR
(SUPSD BY 155B, PER ECO 8824)
155B
205E1849-00
.PWA, AUDIO COMPRESSOR
(SUPSDS 155A, SN377 PER ECO 8824)
(SUPSD BY 155F, PER ECO 10320)
A, B
1
155C
205E1849-03
.PWA, AUDIO COMPRESSOR w/ FSK
(SUPSDS 155A, SN377 PER ECO 8893,
(SUPSD BY 155G, PER ECO 10365)
C
1
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
The document reference is online, please check the correspondence between the online documentation and the printed version.
2
A, B, C,
E, F, G,
H, L, M,
N, P, R,
U, V,
W, Y,
AA, AC
1
T, AB
1
2
A, B, C,
E, F, G,
H, L, M,
N, P, R,
U, V,
W, Y,
AA, AC
1
T, AB
1
1
23–70–04
Illustrated Parts List
Rev. 15 Page 1020
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
FIG.
ITEM
PART
NUMBER
UNITS
PER
EFF
CODE ASSY
AIRLINE NOMENCLATURE
PART NO. 1234567
1
155D
205E1849-02
.PWA, AUDIO COMPRESSOR, w/ AGC
(SUPSDS 155A, SN377 PER ECO 8893)
(SUPSD BY 155L, PER SB009)
E, F
G, H
1
155E
205E1849-04
.Deleted
155F
205E1849-10
.PWA, AUDIO COMPRESSOR
(SUPSDS 155B, SN377 PER ECO 10320)
(SUPSD BY 155K, PER SB009)
A, B
1
155G
205E1849-13
.PWA, AUDIO COMPRESSOR, W/ FSK
(SUPSDS 155C, SN377 PER ECO 10365)
(SUPSD BY 155M, PER SB009)
C
1
155H
205E1849-14
.Deleted
155J
205E1849-17
.PWA, AUDIO COMPRESSOR, HIGH
QUALITY ONLY (SUPSD BY 155P PER
SB009)
L
1
155K
205E3977−10
.PWA, AUDIO COMPRESSOR
(SUPSDS 155F, PER SB009) (SUPSD BY
ITEM 155R, PER SB015)
A, B
1
155L
205E3977−12
.PWA, AUDIO COMPRESSOR, w/ AGC
(SUPSDS 155D, PER SB009) (SUPSD BY
ITEM 155S, PER SB015)
E, F
G, H
1
155M
205E3977−13
.PWA, AUDIO COMPRESSOR, W/ FSK
(SUPSDS 155G, PER SB009) (SUPSD BY
ITEM 155T, PER SB015)
C
1
155N
205E3977−14
.Deleted
155P
205E3977−17
.PWA, AUDIO COMPRESSOR, HIGH
QUALITY ONLY (SUPSDS 155J, PER
SB009)
L, M, N,
R, W,
AA, AC
1
155R
205E3977−20
.PWA, AUDIO COMPRESSOR (SUPSDS
ITEM 155K, PER SB015)
A, B, U
1
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
The document reference is online, please check the correspondence between the online documentation and the printed version.
23–70–04
Illustrated Parts List
Rev. 15 Page 1021
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
FIG.
ITEM
PART
NUMBER
UNITS
PER
EFF
CODE ASSY
AIRLINE NOMENCLATURE
PART NO. 1234567
1
155S
205E3977−22
.PWA, AUDIO COMPRESSOR, w/ AGC
(SUPSDS 155L, PER SB015)
E, F
G, H
1
155T
205E3977−23
.PWA, AUDIO COMPRESSOR (SUPSDS
ITEM 155M, PER SB015)
C, V
1
155U
205E3977−24
.Deleted
155V
205E3977−29
.PWA, AUDIO COMPRESSOR, HIGH
QUALITY ONLY
P, Y
1
155W
205E3977−37
.PWA, AUDIO COMPRESSOR, HIGH
QUALITY ONLY
T, AB
1
160
MS51957-14
.SCREW, PAN HEAD, 4-40 X 5/16
(V06141) (2290200074)
***
4
165A
024E1620-00
.CABLE ASSEMBLY, FA2100, W001 & W003
(SUPSD BY ITEM 165B for W001
and
170B for W003, PER SB015)
2
165B
024E2659−01
.CABLE ASSEMBLY, FA2100, W001
(SUPSDS ITEM 165A (W001 only) (EFF
A,B,C,L,M,N) PER SB015)
A, B, C,
L, M, N,
P, R, T,
U, V,
W, Y,
AA, AB,
AC
1
165C
024E3424−03
.CABLE ASSEMBLY, FA2100, W001
(SUPSDS ITEM 165A (W001 only)(EFF
E,F,G,H) PER SB015)
E, F, G,
H
1
170A
024E1620-01
.CABLE ASSEMBLY, FA2100, W002
(SUPSD BY ITEM 170B, PER SB015)
1
170B
024E3424−00
.CABLE ASSEMBLY, FA2100, W002 & W003
(SUPSDS ITEM 165A (W003 only) & 170A,
PER SB015)
2
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
The document reference is online, please check the correspondence between the online documentation and the printed version.
1
23–70–04
Illustrated Parts List
Rev. 15 Page 1022
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
FIG.
ITEM
PART
NUMBER
UNITS
PER
EFF
CODE ASSY
AIRLINE NOMENCLATURE
PART NO. 1234567
1
175A
205E1591-00
.PWA, ACQUISITION PROCESSOR
(SUPSD BY 175B, PER SB002)
175B
205E1931-00
.PWA, ACQUISITION PROCESSOR
(SUPSDS 175A, PER SB002)
(SUPSD BY 175D, PER SB006)
A, B, C,
E, F, G,
H
1
175C
205E2502-10
.PWA, ACQUISITION PROCESSOR
(SUPSDS 175B, PER SB006)
(SUPSD BY 175D PER SB006)
A, B, C,
E, F, G,
H
1
175D
205E2502-11
.PWA, ACQUISITION PROCESSOR
(SUPSDS 175B & 175C, PER SB006)
(CONFIGS E, F, G, H SUPSD BY ITEM
175F, PER SB013) (CONFIGS A, B, C
SUPSD BY ITEM 175G, PER SB015)
A, B, C,
E, F, G,
H
1
175E
205E2502−14
.PWA, ADV ACQUISITION PROCESSOR
W/ OMS
L, M, N,
R, W,
AA, AC
1
175F
205E2502-52
.PWA, ACQUISITION PROCESSOR
(SUPSDS 175D PER SB013) (SUPSD BY
ITEM 175H, PER SB015)
E, F, G,
H
1
175G
205E2502-21
.PWA, ACQUISITION PROCESSOR
(SUPSDS 175D PER SB015)
A, B, C,
U, V
1
175H
205E2502-38
.PWA, ACQUISITION PROCESSOR
(SUPSDS 175F PER SB015)
E, F, G,
H
1
175J
205E2502−24
.PWA, ADV ACQUISITION PROCESSOR
W/ OMS
P, Y
1
175K
205E2502−34
.PWA, ADV ACQUISITION PROCESSOR
W/ OMS
T, AB
1
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
The document reference is online, please check the correspondence between the online documentation and the printed version.
1
23–70–04
Illustrated Parts List
Rev. 15 Page 1023
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
FIG.
ITEM
PART
NUMBER
UNITS
PER
EFF
CODE ASSY
AIRLINE NOMENCLATURE
PART NO. 1234567
1
ATTACHING PARTS
180
MS51957-14
.SCREW, PAN HEAD, 4–40 X 5/16
(V06141) (2290200074)
***
185A
253E1568-01
.MEMORY (CSMU) ASSEMBLY, 7X32 MEG
(SUPSD BY 185G PER SB008)
A, E
1
185B
253E1568-00
.MEMORY(CSMU) ASSEMBLY, 15X32 MEG
(SUPSD BY 185F PER SB008)
B, C, G
1
185C
253E1568-06
.MEMORY (CSMU) ASSEMBLY, 7X32 MEG,
TITANIUM (SUPSD BY 185H PER SB008)
F
1
185D
253E1568-07
.MEMORY (CSMU) ASSEMBLY, 15X32 MEG,
TITANIUM (SUPSD BY 185J PER SB008)
H
1
185E
253E1568-33
.MEMORY (CSMU) ASSEMBLY, 9X128 MEG
3V STRATA FLASH
(SUPSD BY 185L PER SB019)
L, N, P,
R, T
1
185F
253E1568-38
.MEMORY (CSMU) ASSEMBLY, 7X128 MEG
3V STRATA FLASH (SUPSDS 185B, PER
SB008)
(SUPSD BY 185L PER SB019)
B, C, G
1
185G
253E1568-39
.MEMORY (CSMU) ASSEMBLY, 4X128 MEG
3V STRATA FLASH (SUPSDS 185A, PER
SB008)
(SUPSD BY 185L PER SB019)
A, E
1
185H
253E1568-40
.MEMORY (CSMU) ASSEMBLY, 7X128 MEG
3V STRATA FLASH, TITANIUM (SUPSDS
185C, PER SB008)
(SUPSD BY 185M PER SB019)
F
1
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
The document reference is online, please check the correspondence between the online documentation and the printed version.
10
23–70–04
Illustrated Parts List
Rev. 15 Page 1024
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
FIG.
ITEM
PART
NUMBER
UNITS
PER
EFF
CODE ASSY
AIRLINE NOMENCLATURE
PART NO. 1234567
1
185J
253E1568-41
.MEMORY (CSMU) ASSEMBLY, 7X128 MEG
3V STRATA FLASH, TITANIUM (SUPSDS
185D, PER SB008)
(SUPSD BY 185M PER SB019)
H
1
185K
253E4427-33
.MEMORY (CSMU) ASSEMBLY, 9X128 MEG
3V STRATA FLASH MEG, CYRILLIC
(RUSSIAN TEXT)
(SUPSD BY 185N PER SB019)
M
1
185L
253E5675-00
.MEMORY (CSMU) ASSEMBLY, 2 GB
NAND MEMORY MODULE
(SUPSDS 185E-185G, PER SB019)
(SUPSD BY 185P FOR B, C, N, U, V, W,
AA, AC PER SB023)
A, B, C,
E, G, L,
N, P, R,
T, U, V,
W, Y,
AA, AB,
AC
1
185M
253E5675-11
.MEMORY (CSMU) ASSEMBLY, 2 GB
NAND MEMORY MODULE, TITANIUM
(SUPSDS 185H & 185J, PER SB019)
(SUPSD BY 185R FOR H PER SB023)
F, H
1
185N
253E5675-20
.MEMORY (CSMU) 2GB NAND, CYRILLIC,
NON EMI (SUPSDS 185K, PER SB019)
M
1
185P
253E5675-02
.MEMORY (CSMU) 2GB NAND
(SUPSDS 185L, PER SB023)
B, C, N,
U, V, W,
AA, AC
1
185R
253E5675-13
.MEMORY (CSMU) 2GB NAND, TITANIUM
(SUPSDS 185M, PER SB023)
H
1
ATTACHING PARTS
190A
MS16995-52
.SCREW, SCHCAP, 1/4-20 X 1
(V06141) (2290200325) (SUPSD BY 190B
PER SB004)
4
190B
BB1P141H16
.SCREW, SCHCAP, 1/4-20 X 1
(V06141) (2299800464) (SUPSDS 190A
PER SB004)
4
200A
230E2520-00
.SEAL, CSMU COVER, SHORT-BOX
(SUPSD BY 200B, PER SB019)
1
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
The document reference is online, please check the correspondence between the online documentation and the printed version.
23–70–04
Illustrated Parts List
Rev. 15 Page 1025
Apr. 14/16
AVIATION RECORDERS
COMPONENT MAINTENANCE MANUAL
FA2100CVR
FIG.
ITEM
PART
NUMBER
UNITS
PER
EFF
CODE ASSY
AIRLINE NOMENCLATURE
PART NO. 1234567
1
200B
230E5675−00
.SEAL, CSMU COVER, SHORT-BOX
(SUPSDS 200A, PER SB019)
***
1
205
9030100047
.LABEL, ESD
1
−
210
147E1679-00
SHIPPING PACKAGE KIT
1
−
220
197E1746-00
.CONTAINER, SHIPPING, SHORT
1
−
225
0279800024
.CAP, DUST, DPX SERIES CONN, 1
1
−
235
2529800107
.TAPE, WATERPROOF, WOVEN BACKED
1
−
240A
9030100049
.BAG, PINK ZIPLOCK, 9 X 12
(SUPSD BY 240B)
1
−
240B
9030100075
.BAG, 14X24, TRANSPARENT PINK
(SUPSDS 240A)
1
−
245
9030100047
.STATIC AWARENESS LABEL
1
− ITEM NOT ILLUSTRATED
Use or disclosure of information on this sheet is subject
to the restrictions on the cover page of this document.
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23–70–04
Illustrated Parts List
Rev. 15 Page 1026
Apr. 14/16
The document reference is online, please check the correspondence between the online documentation and the printed version.