Page 1 of 5 DOA017/28.04.2011
EASA Approval: EASA.21J.312
Continued Airworthiness Instructions
CAI No: CAI-757-2320-52 Revision: I
Title: Communications - Data Transmission & Automatic Calling - DLink+ ACARS / CPDLC Installation
Applicable Aircraft: Boeing 757-200/300
Applicable Registrations/Variable Nos: All aircraft listed in CRA-757-2320-52 Rev J or later revision
Affected Airworthiness Documents: Aircraft Flight Manual
Maintenance Manual Illustrated Parts Catalog Wiring Diagram Manual Maintenance Program Electrical Load Analysis MEL Operations Manual Weight and Balance Other
Document References: Boeing 757-200/300 Aircraft Flight Manual. Note AFM-757-2320-52 Rev D or later will be issued as separate document. Boeing 757-200/300 Aircraft Maintenance Manual Boeing 757-200/300 Illustrated Parts Catalog Boeing 757-200/300 Wiring Diagram Manual
The operator is responsible for amending affected manuals with the continued airworthiness instructions contained herein. The technical content of this document is approved under the authority of Icelandair Technical Services Part 21 Subpart J DOA No. EASA.21J.312 - EASA STC: 10044500 Prepared by / Signature / Date:
Approved by Signature / Date: Structures Avionic
EASA Approval: EASA.21J.312
Continued Airworthiness Instructions
CAI No: CAI-757-2320-52 Revision: I
Page 2 of 5 DOA017/28.04.2011
REVISION RECORD SHEET
REVISION REVISION REASON DATE
I/R
N/A
19/10/2012
A Rev A issued to show relocation of the annunciator Panel from P5 overhead panel to P9 forward electronic control panel. Also, to correct revision status on documents.
11/02/2013
B Rev B issued to add reference to DDP-757-2320-52 I/R or later for equipment approval.
25.03.2013
C Rev C issued to add aircraft to effective list and applicable supplements
8.10.2013
D Rev C issued to add NRW/IKARS aircraft to effective list and applicable supplements
12.11.2013
E
Rev E issued to add updated WDM drawings. 02.01.2014
F
Rev F issued to add updated WDM drawings. 01.04.2014
G Rev G issued to add updated WDM drawings and adding new annunciator panels to IPC supplement.
26.06.2014
H Rev H issued to add updated WDM drawings, WDM supplement divided into A and B sections. AMM supplement updated for annunciator panel instructions.
13.10.2014
I Rev I issued to add aircraft ND037 (TF-ISY) 20.01.2015
EASA Approval: EASA.21J.312
Continued Airworthiness Instructions
CAI No: CAI-757-2320-52 Revision: I
Page 3 of 5 DOA017/28.04.2011
Table of Contents
Item Content Page No 1 Description 4 2 Control and Operation 4 3 System Line Replaceable Units (LRU’s) 4 4 Equipment Locations 4 5 Certification Considerations 4 6 Equipment Approvals 5 7 Servicing Information 5 8 Maintenance Instructions 5 9 Troubleshooting Instructions 5 10 Removal and Replacement Information 5 11 Wiring Diagrams Supplements 5 12 Special Inspection Requirements 5 13 Application of Protective Treatments 5 14 Data 5 15 List of Special Tools 5 16 Recommended Overhaul Period 5 17 Airworthiness Limitations 5 18 Assistance 6 APPENDIX I Illustrated Parts Catalogue Supplement APPENDIX II-A Wiring Diagram Manual Supplement (Icelandair) APPENDIX II-B Wiring Diagram Manual Supplement
(Nordwind/Ikar)
APPENDIX III Aircraft Maintenance Manual Supplement
EASA Approval: EASA.21J.312
Continued Airworthiness Instructions
CAI No: CAI-757-2320-52 Revision: I
Page 4 of 5 DOA017/28.04.2011
1. Description: This change installs and activates a Spectralux Dlink+ system which provides Aircraft Communications Addressing and Reporting System (ACARS) / Controller Pilot Data Link Communications (CPDLC) system on the Boeing 757-200/-300 series aircraft. The system provides flight crews with the ability to send and receive messages over Very-High Frequency Digital Link (VDL) Mode A/2 networks.
2. Control and Operation:
Introduced in AMM supplement Appendix III
3. System Line Replaceable Units (LRU’s): Equipment Part Number Description Reference
M9000 14114-1-02 Dlink+ w/ CPDLC ACARS, Brown See Note
M10386 8055515-4502 PTA-45B Data Printer See Note
M9001 12854 Personality Module See Note
M99001 ITS-757-2320-52-007-01 Annunciator Panel Assembly See Note
M99002 PED523252-04-01 Annunciator Panel Assembly See Note
M99003 PED523252-04-02 Annunciator Panel Assembly See Note Note: See Aircraft Maintenance Manual Supplement – Appendix III
4. Equipment Locations: Equipment Location Dlink+ w/ CPDLC ACARS P8 Aft Control Stand Data Printer P8 Aft Control Stand Personality Module P8 Aft Control Stand Annunciator Panel Assembly P9 Forward Electronic Panel or P10 Control Stand.
5. Certification Considerations: The Dlink+ w/CPDLC ACARS and the personality module unit have been approved fit for this installation by DDP-757-2320-52 I/R or later. A functional hazard analysis and system safety assessment was carried out by per document SSA-757-2320-52Rev B or later. Furthermore, the equipment are FAA TSO approved per FAA TSO-C160 and TSO-C113. The annunciator panel is a part of this design change and will be built by an approved production organisation.
EASA Approval: EASA.21J.312
Continued Airworthiness Instructions
CAI No: CAI-757-2320-52 Revision: I
Page 5 of 5 DOA017/28.04.2011
6. Equipment Approvals: Description Part Number Approval Dlink+ w/ CPDLC ACARS, Brown 14114-1-02 DDP-757-2320-52 I/R Data Printer, Brown 8055515-4502 PMA Personality Module 12854 DDP-757-2320-52 I/R Annunciator Panel Assembly ITS-757-2320-52-007-01 EASA Form 1 Release Annunciator Panel Assembly PED523252-04-01 EASA Form 1 Release Annunciator Panel Assembly PED523252-04-02 EASA Form 1 Release
7. Servicing Information: The equipment are considered on-condition items
8. Maintenance Instructions: Introduced in AMM supplement Appendix III
9. Troubleshooting Instructions Introduced in AMM supplement Appendix III
10. Removal and Replacement Information: Introduced in AMM supplement Appendix III
11. Wiring Diagrams: Introduced in WDM supplement Appendix II
12. Special Inspection Requirements: None
13. Application of Protective Treatments: None
14. Data: CRA-757-2320-52 Rev J or later provides reference to all data for this change
15. List of Special Tools:
None
16. Recommended Overhaul Period:
Introduced in AMM supplement Appendix III
17. Airworthiness Limitations:
N/A. There are no airworthiness limitations or any EWIS component that must be replaced at regular intervals due to this modification.
18. Assistance: No special support is needed to carry out the continued airworthiness.
EASA Approval: EASA.21J.312
APPENDIX I
Illustrated Parts Catalog Supplement
CAI No: CAI-757-2320-52 Revision: I
APPENDIX I
Illustrated Parts Catalog Supplement
EASA Approval: EASA.21J.312
APPENDIX I
Illustrated Parts Catalog Supplement
CAI No: CAI-757-2320-52 Revision: I
Title: Communications - Data Transmission & Automatic Calling - DLink+ ACARS / CPDLC Installation
Applicable Aircraft/Components: Boeing 757-200/300
Applicable Registrations/Variable Nos/Component Serial Numbers: All aircraft listed in CRA-757-2320-52 Rev J or later revision
Affected Documentation
Boeing 757-200/300 Illustrated Parts Catalog Front Matter
1.1 Scope
This document provides information related to the change incorporated by CRA-757-2320-52 Rev J or later
1.2 Purpose
Information herein supplements information provided in the existing aircraft IPC with information specific to CRA-757-2320-52 Rev J or later
1.3 Definitions
This document contains no words, terms, expressions, etc. that have varying interpretation throughout the industry.
1.4 Referenced information
Boeing 757, Illustrated Parts Catalog
1.5 Distribution
This documentation is to be distributed to each aircraft that has incorporated change specified in CRA-757-2320-52 Rev J or later as applicable above.
MANUAL SUPPLEMENT TO: Approval Doc:
Boeing B757-200/300 IPC
PAGE 1
Figure 1
Date 20.10.2015
CRA-757-2320-52
Figure 1 - DLINK LOCATION
23-22-06-01The technical content of this document is approved under the authority of Icelandair Technical Services Part 21 Subpart J DOA Nr. EASA.21J.312
MANUAL SUPPLEMENT TO: Approval Doc:
Boeing B757-200/300 IPC
PAGE 2
Figure 2
Date 20.10.2015
Figure 2 -DLINK
The technical content of this document is approved under the authority of Icelandair Technical Services Part 21 Subpart J DOA Nr. EASA.21J.312
23-22-06-01
CRA-757-2320-52
5
MANUAL SUPPLEMENT TO: Approval Doc:Boeing B757-200/300 IPC
FIGITEM Part Number Nomenclature Effect
From To
UnitsPer
Assy
2 ALL
5 14114-1-02 Dlink+ w/ CPDLC ACARS, Brown 1 - Mod 2 incorpurate
V4PUZ9 ELECTRICL EQUIPMENT NUMBER: M9000
-10 12854-4 UNIT - PERSONALITY MODULE 1 SUPPLIER CODE: V4PUZ9 ELECTRICL EQUIPMENT NUMBER: M9001
PAGE 3
Figure 2
Date 20.10.2015
The technical content of this document is approved under the authority of Icelandair Technical Services Part 21 Subpart J DOA Nr. EASA.21J.312
23-22-06-01
CRA-757-2320-52
MANUAL SUPPLEMENT TO: Approval Doc:
Boeing B757-200/300 IPC
PAGE 4
Figure 3
Date 20.10.2015
The technical content of this document is approved under the authority of Icelandair Technical Services Part 21 Subpart J DOA Nr. EASA.21J.312
23-22-06-01
CRA-757-2320-52
Figure 3 - Annunciation Panel Assembly - Config 1
5
A
MANUAL SUPPLEMENT TO: Approval Doc:Boeing B757-200/300 IPC
FIGITEM Part Number Nomenclature Effect
From To
UnitsPer
Assy
3
5 ITS-757-2320-52-007-01 .Annunciator Panel Assembly 1 ELECTRICL EQUIPMENT NUMBER: M99001 - Mod A incorpurated
Note: For aircraft post EO-757-2320-60 satLINK MAX installation P/N PED523260-06-01 is installed.
PAGE 5
Figure 3
Date 20.10.201523-22-06-01
CRA-757-2320-52
The technical content of this document is approved under the authority of Icelandair Technical Services Part 21 Subpart J DOA Nr. EASA.21J.312
NT287 ND177 ND037 ND038 ND039
ND164 NT915 NT914 NB079
ND246 ND247 ND201 ND202
ND203 NT861 NT862 NN001
NN002 ND244 ND245 NC971
NB139 NT913 NT916 NL141
MANUAL SUPPLEMENT TO: Approval Doc:
Boeing B757-200/300 IPC
PAGE 5Figure 4Date 20.10.2015
CRA-757-2320-52
Figure 4 - Annunciation Panel Assembly - Config 2
The technical content of this document is approved under the authority of Icelandair Technical Services Part 21 Subpart J DOA Nr. EASA.21J.312
23-22-06-01
D
10 5
MANUAL SUPPLEMENT TO: Approval Doc:Boeing B757-200/300 IPC
FIGITEM Part Number Nomenclature Effect
From To
UnitsPer
Assy4
5 PED523252-04-01 .Annunciator Panel Assembly (Left-hand) 1 ELECTRICL EQUIPMENT NUMBER: M99002
10 PED523252-04-02 .Annunciator Panel Assembly (Right-hand) 1 ELECTRICL EQUIPMENT NUMBER: M99003
PAGE 6Figure 4Date 20.10.2015
CRA-757-2320-52
The technical content of this document is approved under the authority of Icelandair Technical Services Part 21 Subpart J DOA Nr. EASA.21J.312
23-22-06-01
NC073 NC072 NT377 NT376 NT378 NE301 NT346
NT358
NC073 NC072 NT377 NT376 NT378 NE301 NT346
NT358
MANUAL SUPPLEMENT TO: Approval Doc:
Boeing B757-200/300 IPC
PAGE 1
Figure 1
Date 22.10.2014
CRA-757-2320-52
Figure 1 - PRINTER LOCATION
The technical content of this document is approved under the authority of Icelandair Technical Services Part 21 Subpart J DOA Nr. EASA.21J.312
31-33-01-01
MANUAL SUPPLEMENT TO: Approval Doc:Boeing B757-200/300 IPC
PAGE 2
Figure 2
Date 22.10.2014
CRA-757-2320-52Figure 2 - PRINTER
The technical content of this document is approved under the authority of Icelandair Technical Services Part 21 Subpart J DOA Nr. EASA.21J.312
31-33-01-01
MANUAL SUPPLEMENT TO: Approval Doc:Boeing B757-200/300 IPC
FIGITEM Part Number Nomenclature Effect
From To
UnitsPer
Assy
2 ALL
5 8055515-4502 .PRINTER - DATA (PTA-45B) 1 SUPPLIER CODE: V97896 ELECTRICL EQUIPMENT NUMBER: M10386 OPTIONAL PART: 8055515-4503 8055515-4506 8055515-4507
-10 8050917-0006 ..PAPER ROLL - DATA PRINTER 1 SUPPLIER CODE: V97896
PAGE 3
Figure 2
Date 22.10.2014
CRA-757-2320-52
The technical content of this document is approved under the authority of Icelandair Technical Services Part 21 Subpart J DOA Nr. EASA.21J.312
31-33-01-01
EASA Approval: EASA.21J.312
APPENDIX II-A
Wiring Diagram Manual Supplement
CAI No: CAI-757-2320-52 Revision: I
APPENDIX II-A
Wiring Diagram Manual Supplement Icelandair
EASA Approval: EASA.21J.312
APPENDIX II-A
Wiring Diagram Manual Supplement
CAI No: CAI-757-2320-52 Revision: I
Title: Communications - Data Transmission & Automatic Calling - DLink+ ACARS / CPDLC Installation
Applicable Aircraft/Components: Boeing 757-200/300
Applicable Registrations/Variable Nos/Component Serial Numbers: Aircraft listed in CRA-757-2320-52 Rev J or later (Groups 1-3)
Affected Documentation
Boeing 757-200/300 Wiring Diagram Manual Front Matter
1.1 Scope
This document provides information related to the change incorporated by CRA-757-2320-52 Rev J or later
1.2 Purpose
Information herein supplements information provided in the existing aircraft WDM with information specific to CRA-757-2320-52 Rev J or later
1.3 Definitions
This document contains no words, terms, expressions, etc. that have varying interpretation throughout the industry.
1.4 Referenced information
Boeing 757, Wiring Diagram Manual 1.5 Distribution
This documentation is to be distributed to each aircraft that has incorporated change specified in CRA-757-2320-52 Rev J or later as applicable above.
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92
02
-2
0
W9
00
4-9
20
1-2
2W
01
24
-9
00
1-2
2
3.0
C9
00
1
PR
IN
TE
R
5.0
C5
92
GR
ND
P
RO
X C
MP
TR
90
01
-1
2
=L
=B
=L
=B
FLIG
HT
D
EC
K
M9
00
0 D
LIN
K+
W
/ C
PD
LC
A
CA
RS
D9
00
2
Z-
GN
D
AA
A
BB
B
OU
TPU
T D
ATA
BU
S N
O. 1
M9
00
3 P
RIN
TE
R
115V AC
GD
23
03
-S
T9
20
3-2
0
GD
23
03
-A
C9
20
4-2
0C
CH
AS
SIS
G
ND
FB
EA
PRIN
TER D
ATA
OU
T
DATA FRO
M
DLIN
K+
GD
23
03
-S
T
GD
23
03
-S
T
GG
GN
D
EE
A
FF
B
DATA FRO
M
PRIN
TER
W9
00
2-9
10
4R
-2
4
W9
00
2-9
10
4B
-2
4
W9
00
2-9
10
5R
-2
4
W9
00
2-9
10
5B
-2
4
23
-2
0-0
0
Page 4.C
EFFECTIVITY
NB079
The technical content of this docum
ent is approved under
the authority of Icelandair Technical Services Part 21
Subpart J D
OA N
o. EASA.21J.312
75
7-2
00
W
IR
IN
G D
IA
GR
AM
M
AN
UA
L
SH
EET 4
DL
IN
K A
CA
RS
C
PD
LC
EFFECTIVITY
DLIN
K+
CPD
LC W
IRIN
G
DW
G. N
O.
WD
523252-01D
REV. N
O
D
NB079
10
4C
of
SH
EET
P8
A
FT
C
ON
TR
OL S
TA
ND
P8
P
AN
EL
D7
79
BB
AA
M9
00
0 D
LIN
K+
W
/ C
PD
LC
A
CA
RS
D9
00
2
Z-
GN
D
AA
A
BB
B
OU
TPU
T
DATA BU
S
NO
. 1
M1
03
86
P
RIN
TE
R
FB
EA
PRIN
TER
DATA O
UT
DATA FRO
M
DLIN
K+
GD
23
03
-S
T
GD
23
03
-S
T
GG
GN
D
EE
A
FF
B
DATA FRO
M
PRIN
TER
W9
00
2-9
10
4R
-2
4
W9
00
2-9
10
4B
-2
4
W9
00
2-9
10
5R
-2
4
W9
00
2-9
10
5B
-2
4
1P
rior to connection of new
w
iring to connector D
779, disconnect, cap and stow
the follow
in
g w
ire
s fro
m D
77
9.
- W
2079-5002B
-24 &
W
2079-5002R
-24. R
eference W
DM
23-22-32.
- W
2079-5207B
-24 &
W
2079-5207R
-24. R
eference W
DM
31-33-01.
1
23
-2
0-0
0
Page 4.D
EFFECTIVITY
NT287
The technical content of this docum
ent is approved under
the authority of Icelandair Technical Services Part 21
Subpart J D
OA N
o. EASA.21J.312
75
7-2
00
W
IR
IN
G D
IA
GR
AM
M
AN
UA
L
SH
EET 4
DL
IN
K A
CA
RS
C
PD
LC
EFFECTIVITY
DLIN
K+
CPD
LC W
IRIN
G
DW
G. N
O.
WD
523252-01D
REV. N
O
D
NT287
10
4D
of
SH
EET
P8
A
FT
C
ON
TR
OL S
TA
ND
M9
00
0 D
LIN
K+
W
/ C
PD
LC
A
CA
RS
D9
00
2
99
03
-2
2
W9
00
1-9
90
2-2
2J
P9
FW
D C
ON
TR
OL S
TA
ND
L9
90
1 A
CA
RS
M
ES
SA
GE
LIG
HT
3
P9
P
AN
EL
FLIG
HT
D
EC
K
99
07
-2
2
W9
00
1-9
90
1-2
2H
D9
90
01
P J
7
M9
90
01
M
ES
SA
GE
A
NN
UN
CIA
TO
R M
OD
ULE
B B
G
C B A
D
L9
90
2 C
PD
LC
M
ES
SA
GE
LIG
HT
AN
NU
NC
IA
TO
R P
AN
EL
ACARS
AN
NU
NCIATO
R
(O
PEN
/G
ND
)
CPD
LC
AN
NU
NCIATO
R
(O
PEN
/G
ND
)
99
04
-2
24
99
04
-2
2
B B
G
C B A
D
99
08
-2
28
99
08
-2
2
99
06
-2
2
99
05
-2
2
YA
10
TB
10
0
YA
10
TB
10
0
33
-1
6-5
1W
20
78
-0
03
1-2
2
33
-1
6-5
1W
20
78
-0
03
1-2
2
5 69
90
6-2
2
99
05
-2
2
Z4
TB
58
33
-1
6-6
1W
20
78
-0
03
9-2
2
Z4
TB
58
33
-1
6-6
1W
20
78
-0
03
9-2
2
Z7
TB
10
0
Z7
TB
10
0
1 1
1F
or connection of w
ires W
205
9-9905-22 &
W
2059-9906-22, T
B100 Y
A10 is the source block.
- U
se if free sockets exist in Y
A10
- U
se if free sockets exist in a
ny near by T
B linked to Y
A10 such as Z
7 as show
n
- If needed to accom
modate the
tw
o new
w
ires:
Install new
T
B, preferably T
B100 Z
7/8 . A
dd jum
per w
ire from
Y
A10 to the new
T
B. If need
ed
to
a
cco
mm
od
ate th
e ju
mp
er in
Y
A1
0 re
lo
cate
w
ire
W
42
36
-0
12
5-2
2 fro
m Y
A1
0 to
th
e n
ew
T
B
23
-2
0-0
0
Page 5
EFFECTIVITY
ALL
The technical content of this docum
ent is approved under
the authority of Icelandair Technical Services Part 21
Subpart J D
OA N
o. EASA.21J.312
75
7-2
00
W
IR
IN
G D
IA
GR
AM
M
AN
UA
L
SH
EET 5
DL
IN
K A
CA
RS
C
PD
LC
EFFECTIVITY
DLIN
K+
CPD
LC W
IRIN
G
DW
G. N
O.
WD
523252-01D
REV. N
O
D
ALL
10
5of
SH
EET
P8
A
FT
C
ON
TR
OL S
TA
ND
W9
00
2-9
10
1R
-2
4
M9
00
0 D
LIN
K+
W
/ C
PD
LC
A
CA
RS
D9
00
2
A-
GN
D
UA
VB
YA
ZB
P-
GN
D
WA
XB
I-
GN
D
W9
00
2-9
10
1B
-2
4
W9
00
2-9
10
6B
-2
4
W9
00
2-9
10
6R
-2
4
W9
00
2-9
10
0B
-2
4
W9
00
2-9
10
0R
-2
4
DATA FRO
M
L FM
C
DATA FRO
M
L IRU
DATA FRO
M
L AD
C
D1
73
A
M1
34
L FLT
M
GM
T C
OM
PU
TE
R
E2
-1
S
HE
LF
92
00
R-2
4
92
00
B-2
4
30
31
G9
H9
A B
E2
-1
S
HE
LF
AE
02
01
GE
N O
UT
PU
T B
US
1
D1
73
A
A3
B3
A B
L IR
U IN
PU
T
Z9
4
Z9
3
TB
20
1
GD
18
13
-S
T
51
29
R-2
4
51
29
B-2
4
43
44
29
15
92
02
R-2
4
92
02
B-2
4
Z1
13
Z1
12
TB
20
1
GD
18
15
-S
T
50
82
R-2
4
50
82
B-2
4
34-21-11
34-61-15
34-61-16
22-12-11
22-12-31
22-32-11
34-61-12
92
01
R-2
4
92
01
B-2
4
D4
13
91
P J
23
24
28
M1
00
LE
FT
A
IR
D
AT
A C
OM
PU
TE
R
D2
89
B
A8
B8
A B
DA
TA
B
US
4
50
41
R-2
4
50
41
B-2
4
Z1
22
Z1
21
TB
20
1
GD
18
16
-S
T
34-12-12
ME
C
1W
ires stow
ed w
hen C
RA
-757-2320-60 is accom
plished (W
D523260-01)
1
23
-2
0-0
0
Page 6.A
EFFECTIVITY
ND
177, N
D164, N
T914, N
T915, N
D246, N
D247, N
T287
The technical content of this docum
ent is approved under
the authority of Icelandair Technical Services Part 21
Subpart J D
OA N
o. EASA.21J.312
75
7-2
00
W
IR
IN
G D
IA
GR
AM
M
AN
UA
L
SH
EET 6
DL
IN
K A
CA
RS
C
PD
LC
EFFECTIVITY
DLIN
K+
CPD
LC W
IRIN
G
DW
G. N
O.
WD
523252-01D
REV. N
O
D
ND
177, N
D164, N
T914, N
T915, N
D246, N
D247, N
T287
10
6A
of
SH
EET
P8
A
FT
C
ON
TR
OL S
TA
ND
W9
00
2-9
10
1R
-2
4
M9
00
0 D
LIN
K+
W
/ C
PD
LC
A
CA
RS
D9
00
2
A-
GN
D
UA
VB
YA
ZB
P-
GN
D
WA
XB
I-
GN
D
W9
00
2-9
10
1B
-2
4
W9
00
2-9
10
6B
-2
4
W9
00
2-9
10
6R
-2
4
W9
00
2-9
10
0B
-2
4
W9
00
2-9
10
0R
-2
4
DATA FRO
M
L FM
C
DATA FRO
M
L IRU
DATA FRO
M
L AD
C
D1
73
A
M1
34
L FLT
M
GM
T C
OM
PU
TE
R
E2
-1
S
HE
LF
92
00
R-2
4
92
00
B-2
4
30
31
G9
H9
A B
E2
-1
S
HE
LF
AE
02
01
GE
N O
UT
PU
T B
US
1
D1
73
A
A3
B3
A B
L IR
U IN
PU
T
Z9
4
Z9
3
TB
20
1
GD
18
13
-S
T
51
29
R-2
4
51
29
B-2
4
43
44
29
15
92
02
R-2
4
92
02
B-2
4
Z1
04
Z1
03
TB
20
1
GD
18
15
-S
T
50
82
R-2
4
50
82
B-2
4
34-21-11
34-61-16
22-12-11
22-12-31
22-32-11
34-61-12
92
01
R-2
4
92
01
B-2
4
D4
13
91
P J
23
24
28
M1
00
LE
FT
A
IR
D
AT
A C
OM
PU
TE
R
D2
89
B
A8
B8
A B
DA
TA
B
US
4
50
41
R-2
4
50
41
B-2
4
Z1
22
Z1
21
TB
20
1
GD
18
16
-S
T
34-12-12
ME
C
Z1
07
Z1
06
TB
20
1
34-61-15
1W
ires stow
ed w
hen C
RA
-757-2320-60 is accom
plished (W
D523260-01)
1
23
-2
0-0
0
Page 6.B
EFFECTIVITY
ND
037, N
D038, N
D039, N
B079
The technical content of this docum
ent is approved under
the authority of Icelandair Technical Services Part 21
Subpart J D
OA N
o. EASA.21J.312
75
7-2
00
W
IR
IN
G D
IA
GR
AM
M
AN
UA
L
SH
EET 6
DL
IN
K A
CA
RS
C
PD
LC
EFFECTIVITY
DLIN
K+
CPD
LC W
IRIN
G
DW
G. N
O.
WD
523252-01D
REV. N
O
D
ND
037, N
D038, N
D039, N
B079
10
6B
of
SH
EET
P8
A
FT
C
ON
TR
OL S
TA
ND
M9
00
0 D
LIN
K+
W
/ C
PD
LC
A
CA
RS
D9
00
2
S-
GN
D
D-
A
E-
BW
90
02
-9
90
1B
-2
4
W9
00
2-9
90
1R
-2
4
HI-SPEED
DATA FRO
M
L FM
C
D1
73
A
M1
34
L FLT
M
GM
T C
OM
PU
TE
R
E2
-1
S
HE
LF
99
01
R-2
4
99
01
B-2
4
D4
13
91
P J
53
54
A1
1
B1
1
A B
E2
-1
S
HE
LF
AE
02
01
FM
S O
UT
PU
T (H
I-S
PE
ED
)
55
Z5
0
Z4
9
TB
20
1
GD
18
07
-S
T
50
15
R-2
4
50
15
B-2
4
23-11-16
31-31-42
34-22-18
34-22-38
34-46-12
ME
C
Z1
TB
72
03
70
-2
4W
90
02
-9
90
2-2
2G
P5
1 W
AR
N E
LE
X C
AR
D FILE
P
AN
EL
AP
00
51
D9
03
M1
00
0 A
UR
AL W
AR
NIN
G B
ELL C
HIM
E
49
AC
AR
S
D4
10
59
P J
55
99
01
-2
2
P5
1 P
AN
EL
CPD
LC
BELL-CH
IM
E
(O
PEN
/G
ND
)
AE
03
03
E3
-3
S
HE
LF
E3
-3
S
HE
LF
D4
05
90
P J
41
AE
05
03
E5
-3
S
HE
LF
W9
00
2-9
90
6-2
2
D3
25
8B
M1
03
32
FS
EU
-2
C8
FLA
PS
N
OT
U
P
99
01
-2
2
99
01
R-2
4
99
01
B-2
4
D4
06
70
P J
53
54
55
YA
10
2
YC
10
2
TB
18
1
N-
W9
00
2-9
90
3B
-2
4
W9
00
2-9
90
3R
-2
4
FLAPS N
OT U
P
FG
ND
PA
RB
DATA TO
D
FD
R
E5
-3
S
HE
LF
1If w
ire W
1451-0370-24 and T
B72 is not existing in aircraft as show
n, then obtain w
ire from
sub
kit -1
3 a
nd
in
stall w
ire a
nd
T
B.
1
23
-2
0-0
0
Page 7
EFFECTIVITY
ALL
The technical content of this docum
ent is approved under
the authority of Icelandair Technical Services Part 21
Subpart J D
OA N
o. EASA.21J.312
75
7-2
00
W
IR
IN
G D
IA
GR
AM
M
AN
UA
L
SH
EET 7
DL
IN
K A
CA
RS
C
PD
LC
EFFECTIVITY
DLIN
K+
CPD
LC W
IRIN
G
DW
G. N
O.
WD
523252-01D
REV. N
O
D
ALL
10
7of
SH
EET
P8
A
FT
C
ON
TR
OL S
TA
ND
W9
00
2-9
10
2B
LU
-2
4
M9
00
0 D
LIN
K+
W
/ C
PD
LC
A
CA
RS
D9
00
2
NG
ND
SA
TB
BT
X+
CT
X-
AG
ND
W9
00
2-9
10
2B
BK
-2
4
W9
00
2-9
10
3B
-2
4
W9
00
2-9
10
3R
-2
4
DATA FRO
M
EICAS
ETH
ERN
ET
D1
1D
M1
38
D
FD
AU
P6
1 P
AN
EL
92
00
R-2
4
92
00
B-2
4
D4
06
70
P J
42
43
C1
4
D1
4
A B
P6
1 P
AN
EL
AE
03
03
L/R
E
IC
AS
P
OR
T 1
4
41
YA
67
YC
67
TB
18
1
GD
19
49
-S
T
50
23
R-2
4
50
23
B-2
4
31-31-41
92
00
BLU
-2
4
92
00
BB
K-2
4
D4
00
03
P J
36
40
35
E3
-3
S
HE
LF
E3
-3
S
HE
LF
92
00
RE
D-2
4
92
00
RB
K-2
43
9
38
W9
00
2-9
10
2R
ED
-2
4D
RX
+
ER
X-
W9
00
2-9
10
2R
BK
-2
4
D9
00
7J
6321
ET
HE
RN
ET
ME
C
AP
00
61
KK
GN
D
B-
A
C-
BW
90
02
-9
10
7B
-2
4
W9
00
2-9
10
7R
-2
4
DATA FRO
M
MM
R
92
01
R-2
4
92
01
B-2
4
D4
06
70
P J
51
52
50
D2
51
A
M1
01
41
LE
FT
T
RA
NS
PO
ND
ER
A2
B2
A B
L G
NS
S 4
29
IN
FLIG
HT
D
EC
K
YA
06
YA
05
TB
18
1
W9
00
1-9
00
1R
-2
4
W9
00
1-9
00
1B
-2
4
D4
13
09
P J
34
36
20
52
08
R-2
2
52
08
B-2
2
WD
M 34-58-11
GD
19
49
-S
T
1In order to accom
modate w
ires W
1433-9200R
/B
-24 in T
B181 Y
A67/Y
C67, disconnect, cap and stow
w
ires W
1461-2635R
/B
-24. R
eference W
DM
23-22-38.
1
2
2D
isconnect existing w
ires W
1433-5208R
/B
-22 from
connector D
251A
and reroute to T
B 181 Y
A06/Y
A05 as show
n. R
eference W
DM
34-58-11.
23
-2
0-0
0
Page 8.A
EFFECTIVITY
N
T287
The technical content of this docum
ent is approved under
the authority of Icelandair Technical Services Part 21
Subpart J D
OA N
o. EASA.21J.312
75
7-2
00
W
IR
IN
G D
IA
GR
AM
M
AN
UA
L
SH
EET 8
DL
IN
K A
CA
RS
C
PD
LC
EFFECTIVITY
DLIN
K+
CPD
LC W
IRIN
G
DW
G. N
O.
WD
523252-01D
REV. N
O
D
N
T287
10
8A
of
SH
EET
P8
A
FT
C
ON
TR
OL S
TA
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2-9
10
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LU
-2
4
M9
00
0 D
LIN
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/ C
PD
LC
A
CA
RS
D9
00
2
NG
ND
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TB
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00
2-9
10
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BK
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4
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00
2-9
10
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-2
4
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00
2-9
10
3R
-2
4
DATA FRO
M
EICAS
ETH
ERN
ET
D1
1D
M1
38
D
FD
AU
P6
1 P
AN
EL
92
00
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4
92
00
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4
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06
70
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42
43
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4
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4
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P6
1 P
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EL
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03
03
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E
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OR
T 1
4
41
YA
67
YC
67
TB
18
1
GD
19
49
-S
T
50
23
R-2
4
50
23
B-2
4
92
00
BLU
-2
4
92
00
BB
K-2
4
D4
00
03
P J
36
40
35
E3
-3
S
HE
LF
E3
-3
S
HE
LF
92
00
RE
D-2
4
92
00
RB
K-2
43
9
38
W9
00
2-9
10
2R
ED
-2
4D
RX
+
ER
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W9
00
2-9
10
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BK
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4
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00
7J
6321
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ME
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AP
00
61
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BW
90
02
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7B
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4
W9
00
2-9
10
7R
-2
4
DATA FRO
M
MM
R
92
01
R-2
4
92
01
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4
D4
06
70
P J
51
52
50
D2
51
A
M1
01
41
LE
FT
T
RA
NS
PO
ND
ER
A2
B2
A B
L G
NS
S 4
29
IN
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D
EC
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06
YA
05
TB
18
1
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00
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4
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00
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P J
1 23
92
02
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4
92
02
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4
EO
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DW
G 05306-900
GD
19
49
-S
T
WD
M 31-31-41
31-31-41
1R
em
ove
e
xistin
g w
ire
s W
90
01
-9
00
1W
/B
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2 in
sta
lle
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y E
O-7
57
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45
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r re
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ute
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nd
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nn
ect to
T
B1
81
Y
A0
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5 in
ste
ad
o
f n
ew
w
ire
s. R
efe
re
nce
d
ra
win
g 0
53
06
-9
00
p
re
se
nte
d b
y m
od
7
57
-3
45
0-2
7.
1
23
-2
0-0
0
Page 8.B
EFFECTIVITY
NT914, N
T915
The technical content of this docum
ent is approved under
the authority of Icelandair Technical Services Part 21
Subpart J D
OA N
o. EASA.21J.312
75
7-2
00
W
IR
IN
G D
IA
GR
AM
M
AN
UA
L
SH
EET 8
DL
IN
K A
CA
RS
C
PD
LC
EFFECTIVITY
DLIN
K+
CPD
LC W
IRIN
G
DW
G. N
O.
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523252-01D
REV. N
O
D
NT914, N
T915
10
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of
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LIN
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00
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00
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4
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00
2-9
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4
DATA FRO
M
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ETH
ERN
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D1
1D
M1
38
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FD
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P6
1 P
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EL
92
00
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4
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00
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4
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70
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42
43
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4
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4
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P6
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EL
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03
03
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AS
P
OR
T 1
4
41
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17
SM
16
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19
47
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T
50
20
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4
50
20
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4
92
00
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-2
4
92
00
BB
K-2
4
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00
03
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36
40
35
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-3
S
HE
LF
E3
-3
S
HE
LF
92
00
RE
D-2
4
92
00
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K-2
43
9
38
W9
00
2-9
10
2R
ED
-2
4D
RX
+
ER
X-
W9
00
2-9
10
2R
BK
-2
4
D9
00
7J
6321
ET
HE
RN
ET
ME
C
AP
00
61
KK
GN
D
B-
A
C-
BW
90
02
-9
10
7B
-2
4
W9
00
2-9
10
7R
-2
4
DATA FRO
M
MM
R
92
01
R-2
4
92
01
B-2
4
D4
06
70
P J
51
52
50
D2
51
A
M1
01
41
LE
FT
T
RA
NS
PO
ND
ER
A2
B2
A B
L G
NS
S 4
29
IN
FLIG
HT
D
EC
K
YA
06
YA
05
TB
18
1
W9
00
1-9
00
1R
-2
4
W9
00
1-9
00
1B
-2
4
D9
00
01
P J
1 23
92
02
R-2
4
92
02
B-2
4
EO
-757-3450-27
DW
G 05306-900
GD
19
49
-S
T
51
49
R-2
4
51
49
B-2
4
7 89
D4
14
03
P J
SM
18
WD
M 31-31-41
1R
em
ove existing w
ires W
9001-9001W
/B
-22 installed by E
O-757-3450-27 or reroute and connect to T
B181 Y
A06/Y
A05 in stead of new
w
ires. R
eference draw
ing 05306-900 presented by m
od 757-3450-27.
1
23
-2
0-0
0
Page 8.C
EFFECTIVITY
ND
037, N
D038, N
D039, N
D164, N
D177, N
D246, N
D247
The technical content of this docum
ent is approved under
the authority of Icelandair Technical Services Part 21
Subpart J D
OA N
o. EASA.21J.312
75
7-2
00
W
IR
IN
G D
IA
GR
AM
M
AN
UA
L
SH
EET 8
DL
IN
K A
CA
RS
C
PD
LC
EFFECTIVITY
DLIN
K+
CPD
LC W
IRIN
G
DW
G. N
O.
WD
523252-01D
REV. N
O
D
ND
037, N
D038, N
D039, N
D164, N
D177, N
D246, N
D247
10
8C
of
SH
EET
P8
A
FT
C
ON
TR
OL S
TA
ND
W9
00
2-9
10
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LU
-2
4
M9
00
0 D
LIN
K+
W
/ C
PD
LC
A
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RS
D9
00
2
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ND
SA
TB
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X+
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AG
ND
W9
00
2-9
10
2B
BK
-2
4
W9
00
2-9
10
3B
-2
4
W9
00
2-9
10
3R
-2
4
DATA FRO
M
EICAS
ETH
ERN
ET
D1
1D
M1
38
D
FD
AU
P6
1 P
AN
EL
92
00
R-2
4
92
00
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4
D4
06
70
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42
43
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4
D1
4
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P6
1 P
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EL
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03
03
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IC
AS
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OR
T 1
4
41
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17
SM
16
GD
19
47
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T
50
20
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4
50
20
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4
92
00
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-2
4
92
00
BB
K-2
4
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00
03
P J
36
40
35
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-3
S
HE
LF
E3
-3
S
HE
LF
92
00
RE
D-2
4
92
00
RB
K-2
43
9
38
W9
00
2-9
10
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ED
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RX
+
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00
2-9
10
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00
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6321
ET
HE
RN
ET
ME
C
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00
61
KK
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D
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A
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BW
90
02
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10
7B
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4
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00
2-9
10
7R
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4
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M
MM
R
92
01
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4
92
01
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4
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06
70
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51
52
50
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51
A
M1
01
41
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FT
T
RA
NS
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S 4
29
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YA
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18
1
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00
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00
1-9
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1 23
92
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4
92
02
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4
EO
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DW
G 50306-900
GD
19
49
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T
19
18
20
D4
14
43
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SM
18
WD
M 31-31-22
92
03
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4
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03
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4
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em
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g w
ire
s W
90
01
-9
00
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/B
-2
2 in
sta
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d b
y E
O-7
57
-3
45
0-2
7 o
r re
ro
ute
a
nd
co
nn
ect to
T
B1
81
Y
A0
6/Y
A0
5 in
ste
ad
o
f n
ew
w
ire
s. R
efe
re
nce
d
ra
win
g 0
53
06
-9
00
p
re
se
nte
d b
y m
od
7
57
-3
45
0-2
7.
1
23
-2
0-0
0
Page 8.D
EFFECTIVITY
NB079
The technical content of this docum
ent is approved under
the authority of Icelandair Technical Services Part 21
Subpart J D
OA N
o. EASA.21J.312
75
7-2
00
W
IR
IN
G D
IA
GR
AM
M
AN
UA
L
SH
EET 8
DL
IN
K A
CA
RS
C
PD
LC
EFFECTIVITY
DLIN
K+
CPD
LC W
IRIN
G
DW
G. N
O.
WD
523252-01D
REV. N
O
D
NB079
10
8D
of
SH
EET
P8
A
FT
C
ON
TR
OL S
TA
ND
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C
D7
79
EA
FB
M9
00
0 D
LIN
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W
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A
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00
2
GG
GN
D
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M
PRIN
TER
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86
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RIN
TE
R
AA
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DATA TO
ACARS
GD
23
03
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23
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T
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23
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41
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51
39
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51
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50
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4
50
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1
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19
51
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T
51
41
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4
51
41
B-2
4
31-33-01
AE
03
03
AE
03
03
23
-2
0-0
0
Page 9.A
EFFECTIVITY
NT914, N
T915
The technical content of this docum
ent is approved under
the authority of Icelandair Technical Services Part 21
Subpart J D
OA N
o. EASA.21J.312
75
7-2
00
W
IR
IN
G D
IA
GR
AM
M
AN
UA
L
SH
EET 9
DL
IN
K A
CA
RS
C
PD
LC
EFFECTIVITY
DLIN
K+
CPD
LC W
IRIN
G
DW
G. N
O.
WD
523252-01D
REV. N
O
D
NT914, N
T915
10
9A
of
SH
EET
P8
A
FT
C
ON
TR
OL S
TA
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C
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79
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FB
M9
00
0 D
LIN
K+
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/ C
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LC
A
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00
2
GG
GN
D
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A
DATA FRO
M
PRIN
TER
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03
86
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M
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DATA TO
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23
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00
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10
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00
2-9
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15
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41
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51
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51
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4
50
40
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4
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85
SM
86
51
41
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4
51
41
B-2
4
31-35-02
AE
03
03
AE
03
03
SM
87
23
-2
0-0
0
Page 9.B
EFFECTIVITY
ND
246, N
D247
The technical content of this docum
ent is approved under
the authority of Icelandair Technical Services Part 21
Subpart J D
OA N
o. EASA.21J.312
75
7-2
00
W
IR
IN
G D
IA
GR
AM
M
AN
UA
L
SH
EET 9
DL
IN
K A
CA
RS
C
PD
LC
EFFECTIVITY
DLIN
K+
CPD
LC W
IRIN
G
DW
G. N
O.
WD
523252-01D
REV. N
O
D
ND
246, N
D247
10
9B
of
SH
EET
P8
A
FT
C
ON
TR
OL S
TA
ND
M9
00
0 D
LIN
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D9
00
2
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90
02
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4
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00
2-9
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4
FLIG
HT PLAN
DATA TO
L FM
C
D1
73
B
M1
34
L FLT
M
GM
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OM
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TE
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99
02
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4
99
02
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13
91
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02
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LA
N IN
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T
9
ME
C
W9
00
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00
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4
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44
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21
FU
EL Q
TY
P
RO
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OR
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NIT
99
01
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4
99
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4
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16
20
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27
28
J1
1
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1
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03
04
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TY
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T
29
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11
YC
11
TB
18
2
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18
84
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T
50
02
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4
50
02
B-2
4
34-61-14
E3
-4
S
HE
LF
E3
-4
S
HE
LF
GD
18
16
-S
T
1W
ires stow
ed w
hen C
RA
-757-2320-60 is accom
plished (W
D523260-01)
1
23
-2
0-0
0
Page 10.A
EFFECTIVITY
ND
038, N
D164, N
D177, N
T914
The technical content of this docum
ent is approved under
the authority of Icelandair Technical Services Part 21
Subpart J D
OA N
o. EASA.21J.312
75
7-2
00
W
IR
IN
G D
IA
GR
AM
M
AN
UA
L
SH
EET 10
DL
IN
K A
CA
RS
C
PD
LC
EFFECTIVITY
DLIN
K+
CPD
LC W
IRIN
G
DW
G. N
O.
WD
523252-01D
REV. N
O
D
ND
038, N
D164, N
D177, N
T914
10
10A
of
SH
EET
P8
A
FT
C
ON
TR
OL S
TA
ND
M9
00
0 D
LIN
K+
W
/ C
PD
LC
A
CA
RS
D9
00
2
X-
GN
D
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Page 10.B
EFFECTIVITY
ND
246, N
D247, N
T915, N
D039, N
T287, N
B079, N
D037
The technical content of this docum
ent is approved under
the authority of Icelandair Technical Services Part 21
Subpart J D
OA N
o. EASA.21J.312
75
7-2
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Page
3.A
EFFE
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ITY
ND
201,
ND
202,
ND
203,
NC9
71
The
tech
nica
l con
tent
of
this
doc
umen
t is
app
rove
d un
der
the
auth
ority
of
Icel
anda
ir Te
chni
cal S
ervi
ces
Part
21
Subp
art
J D
OA
No.
EAS
A.21
J.31
275
7-20
0 W
IRIN
G D
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RA
M M
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23-2
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Page
3.B
EFFE
CTIV
ITY
The
tech
nica
l con
tent
of
this
doc
umen
t is
app
rove
d un
der
the
auth
ority
of
Icel
anda
ir Te
chni
cal S
ervi
ces
Part
21
Subp
art
J D
OA
No.
EAS
A.21
J.31
275
7-20
0 W
IRIN
G D
IAG
RA
M M
AN
UA
L
SHEE
T 3
DLI
NK
AC
AR
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23-2
0-00
Page
4.A
EFFE
CTIV
ITY
ND
201,
ND
202,
ND
203,
NB1
39, N
C971
The
tech
nica
l con
tent
of
this
doc
umen
t is
app
rove
d un
der
the
auth
ority
of
Icel
anda
ir Te
chni
cal S
ervi
ces
Part
21
Subp
art
J D
OA
No.
EAS
A.21
J.31
275
7-20
0 W
IRIN
G D
IAG
RA
M M
AN
UA
L
SHEE
T 4
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23-2
0-00
Page
4.B
EFFE
CTIV
ITY
NT8
61, N
T862
, NN
001,
NN
002
The
tech
nica
l con
tent
of
this
doc
umen
t is
app
rove
d un
der
the
auth
ority
of
Icel
anda
ir Te
chni
cal S
ervi
ces
Part
21
Subp
art
J D
OA
No.
EAS
A.21
J.31
275
7-20
0 W
IRIN
G D
IAG
RA
M M
AN
UA
L
SHEE
T 4
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22, T
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YA
10- U
se if
free
soc
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exi
st in
any
nea
r by
TB li
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A10
suc
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Z7
as s
how
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the
two
new
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s: I
nsta
ll ne
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B, p
refe
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100
Z7/8
. A
dd ju
mpe
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from
YA
10 to
the
new
TB
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d to
acc
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mpe
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10 re
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4236
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5-22
from
YA
10 to
the
new
TB
23-2
0-00
Page
5
EFFE
CTIV
ITY
ALL
The
tech
nica
l con
tent
of
this
doc
umen
t is
app
rove
d un
der
the
auth
ority
of
Icel
anda
ir Te
chni
cal S
ervi
ces
Part
21
Subp
art
J D
OA
No.
EAS
A.21
J.31
275
7-20
0 W
IRIN
G D
IAG
RA
M M
AN
UA
L
SHEE
T 5
DLI
NK
AC
AR
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CTIV
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23-2
0-00
Page
6.A
EFFE
CTIV
ITY
The
tech
nica
l con
tent
of
this
doc
umen
t is
app
rove
d un
der
the
auth
ority
of
Icel
anda
ir Te
chni
cal S
ervi
ces
Part
21
Subp
art
J D
OA
No.
EAS
A.21
J.31
275
7-20
0 W
IRIN
G D
IAG
RA
M M
AN
UA
L
SHEE
T 6
DLI
NK
AC
AR
S C
PDLC
EFFE
CTIV
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NK+
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DW
G. N
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5232
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V. N
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f10
SHEE
T
ND
201,
ND
202,
ND
203,
NT8
61, N
T862
, NN
001,
NN
002,
NT9
13, N
T916
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201,
ND
202,
ND
203,
NT8
61, N
T862
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DAT
AFR
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AFR
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AFR
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D17
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4 L
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R
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43 4429 15
9202
R-2
4
9202
B-2
4
Z113
Z112
TB20
1
GD
1815
-ST
5082
R-2
4
5082
B-2
4
34-2
1-11
34-6
1-15
34-6
1-16
34-6
1-12
9201
R-2
4
9201
B-2
4
D41
391P
J
23 2428
M10
0 LE
FT A
IR D
ATA
CO
MP
UTE
RD
289B
A8
B8
A BD
ATA
BU
S 4
5041
R-2
4
5041
B-2
4
Z122
Z121
TB20
1
GD
1816
-ST
34-1
2-12
MEC
23-2
0-00
Page
6.B
EFFE
CTIV
ITY
NB1
39
The
tech
nica
l con
tent
of
this
doc
umen
t is
app
rove
d un
der
the
auth
ority
of
Icel
anda
ir Te
chni
cal S
ervi
ces
Part
21
Subp
art
J D
OA
No.
EAS
A.21
J.31
275
7-20
0 W
IRIN
G D
IAG
RA
M M
AN
UA
L
SHEE
T 6
DLI
NK
AC
AR
S C
PDLC
EFFE
CTIV
ITY
DLI
NK+
CP
DLC
WIR
ING
DW
G. N
O.
WD
5232
52-0
2CRE
V. N
O
C 6B o
f10
SHEE
T
NB1
39
P8
AFT
CO
NTR
OL
STA
ND
W90
02-9
101R
-24
M90
00 D
LIN
K+
W/
CP
DLC
AC
AR
S
D90
02
A-
GN
D
UA
VB
YA
ZB
P-
GN
D
WA
XB
I-G
ND
W90
02-9
101B
-24
W90
02-9
106B
-24
W90
02-9
106R
-24
W90
02-9
100B
-24
W90
02-9
100R
-24
DAT
AFR
OM L
FMC
DAT
AFR
OM L
IRU
DAT
AFR
OM L
ADC
D17
3A
M13
4 L
FLT
MG
MT
CO
MP
UTE
R
E2-1
SH
ELF
9200
R-2
4
9200
B-2
4
30 31
G9
H9
A B
E2-1
SH
ELF
AE0
201
GEN
OU
TPU
T B
US
1
D17
3A
A3
B3
A BL
IRU
IN
PU
TZ9
4
Z93
TB20
1
GD
1813
-ST
5129
R-2
4
5129
B-2
4
54 5529 15
9202
R-2
4
9202
B-2
4
Z104
Z103
TB20
1
GD
1815
-ST
5082
R-2
4
5082
B-2
4
34-2
1-11
34-6
1-15
34-6
1-16
34-6
1-12
9201
R-2
4
9201
B-2
4
D41
391P
J
23 2428
M10
0 LE
FT A
IR D
ATA
CO
MP
UTE
RD
289B
A8
B8
A BD
ATA
BU
S 4
5041
R-2
4
5041
B-2
4
Z122
Z121
TB20
1
GD
1816
-ST
34-1
2-12
MEC
23-2
0-00
Page
6.C
EFFE
CTIV
ITY
NC9
71
The
tech
nica
l con
tent
of
this
doc
umen
t is
app
rove
d un
der
the
auth
ority
of
Icel
anda
ir Te
chni
cal S
ervi
ces
Part
21
Subp
art
J D
OA
No.
EAS
A.21
J.31
275
7-20
0 W
IRIN
G D
IAG
RA
M M
AN
UA
L
SHEE
T 6
DLI
NK
AC
AR
S C
PDLC
EFFE
CTIV
ITY
DLI
NK+
CP
DLC
WIR
ING
DW
G. N
O.
WD
5232
52-0
2CRE
V. N
O
C 6C o
f10
SHEE
T
NC9
71
P8
AFT
CO
NTR
OL
STA
ND
W90
02-9
101R
-24
M90
00 D
LIN
K+
W/
CP
DLC
AC
AR
S
D90
02
A-
GN
D
UA
VB
YA
ZB
P-
GN
D
WA
XB
I-G
ND
W90
02-9
101B
-24
W90
02-9
106B
-24
W90
02-9
106R
-24
W90
02-9
100B
-24
W90
02-9
100R
-24
DAT
AFR
OM L
FMC
DAT
AFR
OM L
IRU
DAT
AFR
OM L
ADC
D17
3A
M13
4 L
FLT
MG
MT
CO
MP
UTE
R
E2-1
SH
ELF
9200
R-2
4
9200
B-2
4
30 31
G9
H9
A B
E2-1
SH
ELF
AE0
201
GEN
OU
TPU
T B
US
1
D17
3A
A3
B3
A BL
IRU
IN
PU
TZ9
4
Z93
TB20
1
GD
1813
-ST
5129
R-2
4
5129
B-2
4
54 5529 15
9202
R-2
4
9202
B-2
4
Z113
Z112
TB20
1
GD
1815
-ST
5082
R-2
4
5082
B-2
4
34-2
1-11
34-6
1-15
34-6
1-16
34-6
1-12
9201
R-2
4
9201
B-2
4
D41
391P
J
23 2428
M10
0 LE
FT A
IR D
ATA
CO
MP
UTE
RD
289B
A8
B8
A BD
ATA
BU
S 4
5041
R-2
4
5041
B-2
4
Z122
Z121
TB20
1
GD
1816
-ST
34-1
2-12
MEC
23-2
0-00
Page
6.D
EFFE
CTIV
ITY
ND
244,
ND
245
The
tech
nica
l con
tent
of
this
doc
umen
t is
app
rove
d un
der
the
auth
ority
of
Icel
anda
ir Te
chni
cal S
ervi
ces
Part
21
Subp
art
J D
OA
No.
EAS
A.21
J.31
275
7-20
0 W
IRIN
G D
IAG
RA
M M
AN
UA
L
SHEE
T 6
DLI
NK
AC
AR
S C
PDLC
EFFE
CTIV
ITY
DLI
NK+
CP
DLC
WIR
ING
DW
G. N
O.
WD
5232
52-0
2CRE
V. N
O
C 6D o
f10
SHEE
T
ND
244,
ND
245
P8
AFT
CO
NTR
OL
STA
ND
M90
00 D
LIN
K+
W/
CP
DLC
AC
AR
SD
9002
S-G
ND
D-
A
E-B
W90
02-9
901B
-24
W90
02-9
901R
-24
HI-
SPEE
DD
ATA
FRO
M LFM
C
D17
3A
M13
4 L
FLT
MG
MT
CO
MP
UTE
R
E2-1
SH
ELF
9901
R-2
4
9901
B-2
4
D41
391P
J
53 54
A11
B11
A B
E2-1
SH
ELF
AE0
201
FMS
OU
TPU
T (H
I-SP
EED
)
55
Z50
Z49
TB20
1
GD
1807
-ST
5015
R-2
4
5015
B-2
423
-11-
1631
-31-
4234
-22-
1834
-22-
3834
-46-
12
MEC
Z1
TB72
0370
-24
W90
02-9
902-
22G
P51
WA
RN
ELE
X C
AR
D F
ILE
PA
NEL
AP
0051
D90
3M
1000
AU
RA
L W
AR
NIN
G B
ELL
CH
IME
49A
CA
RS
D41
059P
J
5599
01-2
2
P51
PA
NEL
CPD
LCBE
LL-C
HIM
E(O
PEN
/GN
D)
AE0
303
E3-3
SH
ELF
E3-3
SH
ELF
D40
590P
J
41
AE0
503
E5-3
SH
ELF
W90
02-9
906-
22
D32
58B
M10
332
FSEU
-2
C8
FLA
PS
NO
T U
P99
01-2
2
9901
R-2
4
9901
B-2
4
D40
670P
J
53 5455
YA
102
YC
102
TB18
1
N-
W90
02-9
903B
-24
W90
02-9
903R
-24
FLAP
SN
OT UP
FG
ND
PA
RB
DAT
ATO
DFD
R
E5-3
SH
ELF
1
1Fo
r airc
raft
ND
245,
ND
203
and
NT9
16. U
se p
ins
43, 4
4 an
d 45
in c
onne
ctor
D41
391
2If
W14
51-0
370-
24 a
nd T
B72
Z1
are
not e
xist
ing
in a
ircra
ft as
sho
wn,
then
obt
ain
wire
from
sub
kit -
13 a
nd in
stal
l wire
and
TB
.
2
23-2
0-00
Page
7
EFFE
CTIV
ITY
ALL
The
tech
nica
l con
tent
of
this
doc
umen
t is
app
rove
d un
der
the
auth
ority
of
Icel
anda
ir Te
chni
cal S
ervi
ces
Part
21
Subp
art
J D
OA
No.
EAS
A.21
J.31
275
7-20
0 W
IRIN
G D
IAG
RA
M M
AN
UA
L
SHEE
T 7
DLI
NK
AC
AR
S C
PDLC
EFFE
CTIV
ITY
DLI
NK+
CP
DLC
WIR
ING
DW
G. N
O.
WD
5232
52-0
2CRE
V. N
O
C 7 o
f10
SHEE
T
ALL
P8
AFT
CO
NTR
OL
STA
ND
W90
02-9
102B
LU-2
4
M90
00 D
LIN
K+
W/
CP
DLC
AC
AR
S
D90
02
NG
ND
SA
TB
BTX
+
CTX
-
AG
ND
W90
02-9
102B
BK
-24
W90
02-9
103B
-24
W90
02-9
103R
-24
DAT
AFR
OM
EICA
S
ETH
ERN
ET
D11
D
M13
8 D
FDA
U
P61
PA
NEL
9200
R-2
4
9200
B-2
4
D40
670P
J
42 43
C14
D14
A B
P61
PA
NEL
AE0
303
L/R
EIC
AS
PO
RT
14
41
YC
67
YA
67
TB18
1
GD
1949
-ST
5020
R-2
4
5020
B-2
4
23-2
2-11
31-3
1-41
9200
BLU
-24
9200
BB
K-2
4
D40
003P
J
36 4035E3-3
SH
ELF
E3-3
SH
ELF
9200
RED
-24
9200
RB
K-2
43938
W90
02-9
102R
ED-2
4D
RX
+
ER
X-
W90
02-9
102R
BK
-24
D90
07J
6321
ETH
ERN
ET
MEC
AP
0061
KK
GN
D
B-
A
C-
BW
9002
-910
7B-2
4
W90
02-9
107R
-24
DAT
AFR
OM
MM
R
9201
R-2
4
9201
B-2
4
D40
670P
J
51 5250
D25
1A
M10
141
LEFT
TR
AN
SPO
ND
ER
A2
B2
A BL
GN
SS 4
29 I
N
FLIG
HT
DEC
K
YA
06
YA
05
TB18
1
W90
01-9
001R
-24
W90
01-9
001B
-24
D90
001P
J1 23
9202
R-2
4
9202
B-2
4
EO-7
57-3
450-
27D
WG
053
06-9
00
GD
1949
-ST
1R
emov
e ex
istin
g w
ires
W90
01-9
001W
/B-2
2 in
stal
led
by E
O-7
57-3
450-
27 o
r rer
oute
and
con
nect
to T
B18
1 Y
A06
/YA
05 in
ste
ad o
f new
wire
s. R
efer
ence
dra
win
g 05
306-
900
pres
ente
d by
mod
757
-345
0-27
.
1
23-2
0-00
Page
8.A
EFFE
CTIV
ITY
The
tech
nica
l con
tent
of
this
doc
umen
t is
app
rove
d un
der
the
auth
ority
of
Icel
anda
ir Te
chni
cal S
ervi
ces
Part
21
Subp
art
J D
OA
No.
EAS
A.21
J.31
275
7-20
0 W
IRIN
G D
IAG
RA
M M
AN
UA
L
SHEE
T 8
DLI
NK
AC
AR
S C
PDLC
EFFE
CTIV
ITY
DLI
NK+
CP
DLC
WIR
ING
DW
G. N
O.
WD
5232
52-0
2CRE
V. N
O
C 8A o
f10
SHEE
TN
D20
1, N
D20
2, N
D20
3, N
T861
, NT8
62, N
N00
1, N
N00
2, N
T913
, NT9
16
ND
201,
ND
202,
ND
203,
NT8
61, N
T862
NN
001,
NN
002,
NT9
13, N
T916
P8
AFT
CO
NTR
OL
STA
ND
W90
02-9
102B
LU-2
4
M90
00 D
LIN
K+
W/
CP
DLC
AC
AR
S
D90
02
NG
ND
SA
TB
BTX
+
CTX
-
AG
ND
W90
02-9
102B
BK
-24
W90
02-9
103B
-24
W90
02-9
103R
-24
DAT
AFR
OM
EICA
S
ETH
ERN
ET
D11
D
M13
8 D
FDA
U
P61
PA
NEL
9200
R-2
4
9200
B-2
4
D40
670P
J
42 43
C14
D14
A B
P61
PA
NEL
AE0
303
L/R
EIC
AS
PO
RT
14
41
YC
111
YA
111
TB18
1
5020
R-2
4
5020
B-2
4
23-2
2-11
31-3
1-41
9200
BLU
-24
9200
BB
K-2
4
D40
003P
J
36 4035E3-3
SH
ELF
E3-3
SH
ELF
9200
RED
-24
9200
RB
K-2
43938
W90
02-9
102R
ED-2
4D
RX
+
ER
X-
W90
02-9
102R
BK
-24
D90
07J
6321
ETH
ERN
ET
MEC
AP
0061
KK
GN
D
B-
A
C-
BW
9002
-910
7B-2
4
W90
02-9
107R
-24
DAT
AFR
OM
MM
R
9201
R-2
4
9201
B-2
4
D40
670P
J
51 5250
D25
1A
M10
141
LEFT
TR
AN
SPO
ND
ER
A2
B2
A BL
GN
SS 4
29 I
N
FLIG
HT
DEC
K
YA
06
YA
05
TB18
1
W90
01-9
001R
-24
W90
01-9
001B
-24
D90
001P
J1 23
9202
R-2
4
9202
B-2
4
EO-7
57-3
450-
27D
WG
053
06-9
00
GD
1949
-ST
YA
112
31-3
1-22
1R
emov
e ex
istin
g w
ires
W90
01-9
001W
/B-2
2 in
stal
led
by E
O-7
57-3
450-
27 o
r rer
oute
and
con
nect
to T
B18
1 Y
A06
/YA
05 in
ste
ad o
f new
wire
s. R
efer
ence
dra
win
g 05
306-
900
pres
ente
d by
mod
757
-345
0-27
.
1
23-2
0-00
Page
8.B
EFFE
CTIV
ITY
NB1
39
The
tech
nica
l con
tent
of
this
doc
umen
t is
app
rove
d un
der
the
auth
ority
of
Icel
anda
ir Te
chni
cal S
ervi
ces
Part
21
Subp
art
J D
OA
No.
EAS
A.21
J.31
275
7-20
0 W
IRIN
G D
IAG
RA
M M
AN
UA
L
SHEE
T 8
DLI
NK
AC
AR
S C
PDLC
EFFE
CTIV
ITY
DLI
NK+
CP
DLC
WIR
ING
DW
G. N
O.
WD
5232
52-0
2CRE
V. N
O
C 8B o
f10
SHEE
TN
B139
P8
AFT
CO
NTR
OL
STA
ND
W90
02-9
102B
LU-2
4
M90
00 D
LIN
K+
W/
CP
DLC
AC
AR
S
D90
02
NG
ND
SA
TB
BTX
+
CTX
-
AG
ND
W90
02-9
102B
BK
-24
W90
02-9
103B
-24
W90
02-9
103R
-24
DAT
AFR
OM
EICA
S
ETH
ERN
ET
D11
D
M13
8 D
FDA
U
P61
PA
NEL
9200
R-2
4
9200
B-2
4
D40
670P
J
42 43
C14
D14
A B
P61
PA
NEL
AE0
303
L/R
EIC
AS
PO
RT
14
41
YC
109
YA
109
TB18
1
5020
R-2
4
5020
B-2
4
23-2
2-11
31-3
1-41
9200
BLU
-24
9200
BB
K-2
4
D40
003P
J
36 4035E3-3
SH
ELF
E3-3
SH
ELF
9200
RED
-24
9200
RB
K-2
43938
W90
02-9
102R
ED-2
4D
RX
+
ER
X-
W90
02-9
102R
BK
-24
D90
07J
6321
ETH
ERN
ET
MEC
AP
0061
KK
GN
D
B-
A
C-
BW
9002
-910
7B-2
4
W90
02-9
107R
-24
DAT
AFR
OM
MM
R
9201
R-2
4
9201
B-2
4
D40
670P
J
51 5250
D25
1A
M10
141
LEFT
TR
AN
SPO
ND
ER
A2
B2
A BL
GN
SS 4
29 I
N
FLIG
HT
DEC
K
YA
06
YA
05
TB18
1
W90
01-9
001R
-24
W90
01-9
001B
-24
D90
001P
J1 23
9202
R-2
4
9202
B-2
4
GD
1949
-ST
YA
110
31-3
1-22
1
1R
emov
e ex
istin
g w
ires
W90
01-9
001W
/B-2
2 in
stal
led
by E
O-7
57-3
450-
27 o
r rer
oute
and
con
nect
to T
B18
1 Y
A06
/YA
05 in
ste
ad o
f new
wire
s. R
efer
ence
dra
win
g 05
306-
900
pres
ente
d by
mod
757
-345
0-27
.
EO-7
57-3
450-
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The
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Icel
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ervi
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Part
21
Subp
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J D
OA
No.
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A.21
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275
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57-3
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00
23-2
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8.D
EFFE
CTIV
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ND
244,
ND
245
The
tech
nica
l con
tent
of
this
doc
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t is
app
rove
d un
der
the
auth
ority
of
Icel
anda
ir Te
chni
cal S
ervi
ces
Part
21
Subp
art
J D
OA
No.
EAS
A.21
J.31
275
7-20
0 W
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RA
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9.A
EFFE
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ND
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ND
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The
tech
nica
l con
tent
of
this
doc
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t is
app
rove
d un
der
the
auth
ority
of
Icel
anda
ir Te
chni
cal S
ervi
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Part
21
Subp
art
J D
OA
No.
EAS
A.21
J.31
275
7-20
0 W
IRIN
G D
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RA
M M
AN
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9.B
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The
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Part
21
Subp
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J D
OA
No.
EAS
A.21
J.31
275
7-20
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10
EFFE
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The
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Part
21
Subp
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J D
OA
No.
EAS
A.21
J.31
275
7-20
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Part
21
Subp
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J D
OA
No.
EAS
A.21
J.31
275
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Part
21
Subp
art
J D
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No.
EAS
A.21
J.31
275
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0 W
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the
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of
Icel
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cal S
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Part
21
Subp
art
J D
OA
No.
EAS
A.21
J.31
275
7-30
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Part
21
Subp
art
J D
OA
No.
EAS
A.21
J.31
275
7-30
0 W
IRIN
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RA
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The
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umen
t is
app
rove
d un
der
the
auth
ority
of
Icel
anda
ir Te
chni
cal S
ervi
ces
Part
21
Subp
art
J D
OA
No.
EAS
A.21
J.31
275
7-30
0 W
IRIN
G D
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RA
M M
AN
UA
L
EFFE
CTIV
ITY
DLI
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CP
DLC
WIR
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G. N
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WD
5232
52-0
3ARE
V. N
O
A
NL1
419
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SHEE
T
P8
AFT
CO
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STA
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M90
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LIN
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DAT
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BB
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app
rove
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der
the
auth
ority
of
Icel
anda
ir Te
chni
cal S
ervi
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Part
21
Subp
art
J D
OA
No.
EAS
A.21
J.31
275
7-30
0 W
IRIN
G D
IAG
RA
M M
AN
UA
L
EFFE
CTIV
ITY
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NK+
CP
DLC
WIR
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DW
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O.
WD
5232
52-0
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A
NL1
419
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T
P8
AFT
CO
NTR
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LIN
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umen
t is
app
rove
d un
der
the
auth
ority
of
Icel
anda
ir Te
chni
cal S
ervi
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Part
21
Subp
art
J D
OA
No.
EAS
A.21
J.31
275
7-30
0 W
IRIN
G D
IAG
RA
M M
AN
UA
L
EFFE
CTIV
ITY
DLI
NK+
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DLC
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5232
52-0
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V. N
O
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NL1
419
9of
SHEE
T
EASA Approval: EASA.21J.312
APPENDIX II-B
Wiring Diagram Manual Supplement
CAI No: CAI-757-2320-52 Revision: I
APPENDIX II-B
Wiring Diagram Manual Supplement Nordwind/Ikar
EASA Approval: EASA.21J.312
APPENDIX II-B
Wiring Diagram Manual Supplement
CAI No: CAI-757-2320-52 Revision: I
Title: Communications - Data Transmission & Automatic Calling - DLink+ ACARS / CPDLC Installation
Applicable Aircraft/Components: Boeing 757-200/300
Applicable Registrations/Variable Nos/Component Serial Numbers: Aircraft listed in CRA-757-2320-52 Rev J or later (Group 4)
Affected Documentation
Boeing 757-200/300 Wiring Diagram Manual Front Matter
1.1 Scope
This document provides information related to the change incorporated by CRA-757-2320-52 Rev J or later
1.2 Purpose
Information herein supplements information provided in the existing aircraft WDM with information specific to CRA-757-2320-52 Rev J or later
1.3 Definitions
This document contains no words, terms, expressions, etc. that have varying interpretation throughout the industry.
1.4 Referenced information
Boeing 757, Wiring Diagram Manual 1.5 Distribution
This documentation is to be distributed to each aircraft that has incorporated change specified in CRA-757-2320-52 Rev J or later as applicable above.
33
-1
3-5
2
23
-2
1-1
1
24
-5
4-1
1
P1
1-1
P
AN
EL
D4
19
70
J P
P1
1 O
VE
RH
EA
D C
IR
CU
IT
B
RE
AK
ER
P
AN
EL
P1
1-1
P
AN
EL
7
P8
A
FT
C
ON
TR
OL S
TA
ND
P8
P
AN
EL
Z3
TB
58
W2
06
6-0
00
9-2
09
00
2-2
0
GD
23
03
-D
C
M9
00
0 D
LIN
K+
W
/ C
PD
LC
A
CA
RS
D9
00
1
A2
8V
D
C
D9
00
3
1V
HF A
NT
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NA
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3.3
V
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HC
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03
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PERSO
NALITY
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Page 3
EFFECTIVITY
ALL
The technical content of this docum
ent is approved under
the authority of Icelandair Technical Services Part 21
Subpart J D
OA N
o. EASA.21J.312
75
7-2
00
W
IR
IN
G D
IA
GR
AM
M
AN
UA
L
SH
EET 3
DL
IN
K A
CA
RS
C
PD
LC
EFFECTIVITY
DLIN
K+
CPD
LC W
IRIN
G
DW
G. N
O.
WD
523252-04D
REV. N
O
D
ALL
93
of
SH
EET
33
-1
3-5
2
34
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6-1
1
24
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2
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11
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ON
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58
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20
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03
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23
-2
0-0
0
Page 4.A
EFFECTIVITY
NE301, N
C072, N
C073, N
T376, N
T377, N
T378
The technical content of this docum
ent is approved under
the authority of Icelandair Technical Services Part 21
Subpart J D
OA N
o. EASA.21J.312
75
7-2
00
W
IR
IN
G D
IA
GR
AM
M
AN
UA
L
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EET 4
DL
IN
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LC
EFFECTIVITY
DLIN
K+
CPD
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IRIN
G
DW
G. N
O.
WD
523252-04D
REV. N
O
D
NE301, N
C072, N
C073, N
T376, N
T377, N
T378
94
of
SH
EET
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A
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TA
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LIN
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99
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2
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90
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ON
TR
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TA
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L9
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1 A
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ES
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LIG
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3
PE
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23
25
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EC
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99
07
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99
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24
98
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06
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99
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33
-1
6-5
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20
78
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1-2
2
33
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78
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1-2
2
5 69
80
4-2
2
98
04
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2
Z4
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58
33
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6-6
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20
78
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9-2
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58
33
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20
78
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03
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10
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1 1
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or co
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98
01
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80
4-2
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W
98
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se
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a
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In
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bly T
B1
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7/8
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42
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99
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99
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92
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7
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01
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ES
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IA
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99
04
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24
B B
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C B A
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99
08
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28
99
06
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2
99
05
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98
02
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2
98
05
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2
98
03
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2
98
06
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2
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11
TB
10
0
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11
TB
10
0
SP
91
01
SP
91
02
98
07
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2
98
08
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2
98
02
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2
98
05
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2
98
03
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2
98
06
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SP
92
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SP
92
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98
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2
98
07
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2
PE
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23
25
2-0
5-0
2
23
-2
0-0
0
Page 5
EFFECTIVITY
ALL
The technical content of this docum
ent is approved under
the authority of Icelandair Technical Services Part 21
Subpart J D
OA N
o. EASA.21J.312
75
7-2
00
W
IR
IN
G D
IA
GR
AM
M
AN
UA
L
SH
EET 5
DL
IN
K A
CA
RS
C
PD
LC
EFFECTIVITY
DLIN
K+
CPD
LC W
IRIN
G
DW
G. N
O.
WD
523252-04D
REV. N
O
D
ALL
95
of
SH
EET
P8
A
FT
C
ON
TR
OL S
TA
ND
W9
00
2-9
10
1R
-2
4
M9
00
0 D
LIN
K+
W
/ C
PD
LC
A
CA
RS
D9
00
2
A-
GN
D
UA
VB
YA
ZB
P-
GN
D
WA
XB
I-
GN
D
W9
00
2-9
10
1B
-2
4
W9
00
2-9
10
6B
-2
4
W9
00
2-9
10
6R
-2
4
W9
00
2-9
10
0B
-2
4
W9
00
2-9
10
0R
-2
4
DATA FRO
M
L FM
C
DATA FRO
M
L IRU
DATA FRO
M
L AD
C
D1
73
A
M1
34
L FLT
M
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PU
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R
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92
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R-2
4
92
00
B-2
4
30
31
G9
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HE
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D1
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T
Z9
4
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TB
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1
GD
18
13
-S
T
51
29
R-2
4
51
29
B-2
4
43
44
29
15
92
02
R-2
4
92
02
B-2
4
Z1
04
Z1
03
TB
20
1
GD
18
15
-S
T
50
82
R-2
4
50
82
B-2
4
34-21-11
34-61-15
34-61-16
22-12-11
22-12-31
22-32-11
34-61-12
92
01
R-2
4
92
01
B-2
4
D4
13
91
P J
23
24
28
M1
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LE
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D2
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50
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50
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TB
20
1
GD
18
16
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34-12-12
ME
C
23
-2
0-0
0
Page 6.A
EFFECTIVITY
NC072, N
C073, N
T376, N
T377, N
T378
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00
W
IR
IN
G D
IA
GR
AM
M
AN
UA
L
SH
EET 6
DL
IN
K A
CA
RS
C
PD
LC
EFFECTIVITY
DLIN
K+
CPD
LC W
IRIN
G
DW
G. N
O.
WD
523252-04D
REV. N
O
D
NC072, N
C073, N
T376, N
T377, N
T378
96A
of
SH
EET
P8
A
FT
C
ON
TR
OL S
TA
ND
W9
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2-9
10
1R
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4
M9
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LIN
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6R
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4
W9
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10
0B
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DATA FRO
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L FM
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DATA FRO
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L IRU
DATA FRO
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L AD
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D1
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A
M1
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L FLT
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GM
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PU
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00
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92
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30
31
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A3
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L IR
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13
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29
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43
44
29
15
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92
02
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TB
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18
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50
82
R-2
4
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82
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34-61-16
22-12-11
22-12-31
22-32-11
34-61-12
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01
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4
92
01
B-2
4
D4
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91
P J
23
24
28
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TB
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18
16
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34-12-12
ME
C
23
-2
0-0
0
Page 6.B
EFFECTIVITY
NE301, N
T346, N
T358
The technical content of this docum
ent is approved under
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W
IR
IN
G D
IA
GR
AM
M
AN
UA
L
SH
EET 6
DL
IN
K A
CA
RS
C
PD
LC
EFFECTIVITY
DLIN
K+
CPD
LC W
IRIN
G
DW
G. N
O.
WD
523252-04D
REV. N
O
D
NE301, N
T346, N
T358
96B
of
SH
EET
P8
A
FT
C
ON
TR
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TA
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M9
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LIN
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HI-SPEED
DATA FRO
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C
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1
23
-2
0-0
0
Page 7
EFFECTIVITY
ALL
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IR
IN
G D
IA
GR
AM
M
AN
UA
L
SH
EET 7
DL
IN
K A
CA
RS
C
PD
LC
EFFECTIVITY
DLIN
K+
CPD
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IRIN
G
DW
G. N
O.
WD
523252-04D
REV. N
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ALL
97
of
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BK
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DATA FRO
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EICAS
ETH
ERN
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D1
1D
M1
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FD
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P6
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AN
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TB
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1
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19
49
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T
50
20
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4
50
20
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31-31-41
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00
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-2
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A
C-
BW
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02
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00
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10
7R
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DATA FRO
M
MM
R
92
03
R-2
4
92
02
B-2
4
D4
13
91
P J
34
35
33
D1
73
B
M1
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LE
FT
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C
A7
B7
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NS
S 4
29
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FLIG
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44
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en
d
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p a
nd
sto
w.
1
23
-2
0-0
0
Page 8.A
EFFECTIVITY
NT346, N
T358, N
T376, N
T377, N
T378
The technical content of this docum
ent is approved under
the authority of Icelandair Technical Services Part 21
Subpart J D
OA N
o. EASA.21J.312
75
7-2
00
W
IR
IN
G D
IA
GR
AM
M
AN
UA
L
SH
EET 8
DL
IN
K A
CA
RS
C
PD
LC
EFFECTIVITY
DLIN
K+
CPD
LC W
IRIN
G
DW
G. N
O.
WD
523252-04D
REV. N
O
D
NT346, N
T358, N
T376, N
T377, N
T378
98A
of
SH
EET
P8
A
FT
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TA
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LU
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LIN
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BK
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DATA FRO
M
EICAS
ETH
ERN
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D1
1D
M1
38
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FD
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P6
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AN
EL
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4
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T
50
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-2
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7B
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2-9
10
7R
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DATA FRO
M
MM
R
FLIG
HT
D
EC
K
51
49
R-2
4
51
49
B-2
4
19
18
20
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P J
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WD
M 31-31-41
E3
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HE
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HE
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91
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34
35
33
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73
B
M1
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LE
FT
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29
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10
7
YC
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8
TB
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1
52
44
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52
44
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63
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10
11
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92
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92
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3 th
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d
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ect it, ca
p a
nd
sto
w.
23
-2
0-0
0
Page 8.B
EFFECTIVITY
NE301
The technical content of this docum
ent is approved under
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Subpart J D
OA N
o. EASA.21J.312
75
7-2
00
W
IR
IN
G D
IA
GR
AM
M
AN
UA
L
SH
EET 8
DL
IN
K A
CA
RS
C
PD
LC
EFFECTIVITY
DLIN
K+
CPD
LC W
IRIN
G
DW
G. N
O.
WD
523252-04D
REV. N
O
D
NE301
98B
of
SH
EET
P8
A
FT
C
ON
TR
OL S
TA
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0 D
LIN
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A
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2
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TB
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2B
BK
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2-9
10
3B
-2
4
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2-9
10
3R
-2
4
DATA FRO
M
EICAS
ETH
ERN
ET
D1
1D
M1
38
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FD
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P6
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AN
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92
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4
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70
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42
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4
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19
49
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T
50
20
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20
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92
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36
40
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92
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4
92
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9
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W9
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RX
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7B
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2-9
10
7R
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4
DATA FRO
M
MM
R
FLIG
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EC
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92
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R-2
4
92
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B-2
4
19
18
20
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P J
34
35
33
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M1
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LE
FT
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B7
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29
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7
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8
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1
52
44
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52
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11
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92
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M 34-58-11
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18
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T
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3 th
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d
isco
nn
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p a
nd
sto
w.
23
-2
0-0
0
Page 8.C
EFFECTIVITY
NC072, N
C073
The technical content of this docum
ent is approved under
the authority of Icelandair Technical Services Part 21
Subpart J D
OA N
o. EASA.21J.312
75
7-2
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W
IR
IN
G D
IA
GR
AM
M
AN
UA
L
SH
EET 8
DL
IN
K A
CA
RS
C
PD
LC
EFFECTIVITY
DLIN
K+
CPD
LC W
IRIN
G
DW
G. N
O.
WD
523252-04D
REV. N
O
D
NC072, N
C073
98C
of
SH
EET
P8
A
FT
C
ON
TR
OL S
TA
ND
ME
C
D7
79
EA
FB
M9
00
0 D
LIN
K+
W
/ C
PD
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EASA Approval: EASA.21J.312
APPENDIX III
Aircraft Maintenance Manual Supplement
CAI No: CAI-757-2320-52 Revision: I
APPENDIX III
Aircraft Maintenance Manual Supplement
EASA Approval: EASA.21J.312
APPENDIX III
Aircraft Maintenance Manual Supplement
CAI No: CAI-757-2320-52 Revision: I
Title: Communications - Data Transmission & Automatic Calling - DLink+ ACARS / CPDLC Installation
Applicable Aircraft/Components:
Boeing 757-200/300
Applicable Registrations/Variable Nos/Component Serial Numbers: Aircraft listed in CRA-757-2320-52 Rev J or later
Affected Documentation
Boeing 757-200/300 Aircraft Maintenance Manual Front Matter
1.1 Scope
This document provides information related to the change incorporated by CRA-757-2320-52 Rev J or later
1.2 Purpose
Information herein supplements information provided in the existing Aircraft Maintenance Manual with information specific to CRA-757-2320-52 Rev J or later
1.3 Definitions
This document contains no words, terms, expressions, etc. that have varying interpretation throughout the industry.
1.4 Referenced information
Boeing 757, Maintenance Manual 1.5 Distribution
This documentation is to be distributed to each aircraft that has incorporated change specified in CRA-757-2320-52 Rev J or later as applicable above.
Boeing 757-200/-300 MAINTENANCE MANUAL SUPPLEMENT
EFFECTIVITY 23-22-00 AIRPLANES WITH DLINK+ W/ CPDLC ACARS PAGE 1 Approval CRA-757-2320-52 Rev F or later
ACARS - DESCRIPTION AND OPERATION
1. General
A. Aircraft Communications Addressing and Reporting System (ACARS) with Controller Pilot Data Link Communications (CPDLC) is a digital data link system that enhances two-way communications between the airplane and a ground station.
B. ACARS enhances air/ground communications by easing the flight compartment work load, and eliminating much of the air/ground voice communications traffic. ACARS enables a high-speed computer controlled digital data link between the airplane and ground facilities using: a VHF transceiver, ARINC data link stations, landlines, a central ARINC control station, and airline terminals. The data link exchanges routine airline operations information. ACARS also enables voice "phone-patch" communications between the airplane and ground telephone circuits via: the VHF transceiver, an ARINC voice station, landlines, the central ARINC control station, and ground telephone systems. The CPDLC feature transmits messages over Very-High Frequency Digital Link (VDL) Mode A/2 networks.
C. ACARS receives data inputs from airplane sensors, external systems, and the pilot inputs. Incoming data communications are displayed to the pilot via the Dlink+ ACARS. Outgoing data communications are sent automatically or manually. Data is sent using ARINC assigned frequencies (primarily 131.550 MHz), in ARINC encoded audio frequency tone modulation. ARINC data link stations provide nearly continuous (but not 100%) air/ground data communications.
D. This installation does not support voice communications via ACARS.
E. ACARS receives power from the left 28V DC bus. The system circuit breaker is on the P11 Overhead Panel.
2. Component Details (Figure 1)
A. Dlink+ w/ CPDLC ACARS Unit
1) The Dlink+ with CPDLC ACARS Unit provides Aircraft Communications Addressing and Reporting System (ACARS) and Controller Pilot Data Link Communications (CPDLC) message functionality by combining three ARINC devices into one flight deck equipment panel mounted device. The three devices are: a) ARINC 724B Communication Management Unit (CMU)
b) ARINC 750 VHF Data Link (VDL) Radio
c) ARINC 739 Multi-purpose Control Display Unit (MCDU)
Dlink+ w/ CPDLC ACARS Unit provides air to ground to air data only communication. The system sends and receives free text messages, ACARS messages and CPDLC messages to support Aircraft Operational Control (AOC) communications over the ACARS VHF data link. The system has a Personality Module (PM) which is a serial EEPROM that houses the units configuration and database. When the unit powers up, it reads the configuration from the PM into its internal Random Access Memory (RAM). This defines the system's hardware configuration and many of its settings.
Boeing 757-200/-300 MAINTENANCE MANUAL SUPPLEMENT
EFFECTIVITY 23-22-00 AIRPLANES WITH DLINK+ W/ CPDLC ACARS PAGE 2 Approval CRA-757-2320-52 Rev F or later
2) The Dlink+ w/ CPDLC ACARS Unit design features are: a) Keyboard and display assembly
b) Display unit/power supply printed circuit assembly (DU/PS PCA)
c) Single board computer printed circuit assembly (SBC PCA)
d) Auxiliary input/output printed circuit assembly (AI/O PCA)
e) Very high frequency data link PCA (VDL PCA) (118MHz - 136.975MHz Receiver and 15W
Transmitter)
f) Electronic assembly
g) Soft keys
Boeing 757-200/-300 MAINTENANCE MANUAL SUPPLEMENT
EFFECTIVITY 23-22-00 AIRPLANES WITH DLINK+ W/ CPDLC ACARS PAGE 3 Approval CRA-757-2320-52 Rev F or later
DLINK+ ACARS CPDLC UNIT - Component Location on Pilots Aft Electronic Control Panel Figure 1
Boeing 757-200/-300 MAINTENANCE MANUAL SUPPLEMENT
EFFECTIVITY 23-22-00 AIRPLANES WITH DLINK+ W/ CPDLC ACARS PAGE 4 Approval CRA-757-2320-52 Rev F or later
B. Personality Module (PM)
1) The Personality Module (PM) stores the database used by the Dlink+ w/ CPDLC ACARS Unit. When the Dlink+ Unit is powered up it reads the configuration from the PM into its internal Random Access Memory (RAM). This defines the system's hardware configuration and many of its settings.
2) The PM is a cable wrapped to one of the Dlink+ w/ CPDLC ACARS Unit mating connector's. The PM has a pigtail of four wires that are inserted into the associated mating connector. These wires are used to load the stored database to the Dlink+ w/ CPDLC ACARS Unit RAM and download new database information.
C. Data Printer
1) The Data Printer is used to print the various Dlink+ w/ CPDLC ACARS Unit screen forms. Additionally, if connected to other compatible subsystems, it will also print the screen forms for that subsystem.
D. Ethernet Maintenance Port
1) The Ethernet Maintenance Port located on the P61 Panel is used for loaded data and software updates to the Dlink+ w/ CPDLC ACARS Unit. The Ethernet Maintenance Port allows for updates to the database and software features of the Dlink+ w/ CPDLC ACARS Unit without having to removed the unit from the airplane.
E. Annunciator Panel Assembly
1) The Annunciator Panel contains call/message lights to provide annunciation for CPDLC and ACARS messages in the pilot‘s primary field of view. Two configuration are offered to opeators:
a) One Annuciator panel located forward most on the P9 FWD Control Stand.
b) Two Annunciator Panels located on P10 Quadrant Control Stand beside the EFIS control
panel on both sides.
3. Operation
A. Functional Description
1) Off mode: a) Dlink+ w/ CPDLC ACARS Unit is off when 28V DC left bus power is removed from the unit.
There is no system activity or indications.
2) Operation: a) When the Dlink+ w/ CPDLC ACARS Unit is powering on, the unit reads the configuration of the
PM into the RAM, internal to the unit. Once powered, the unit can provide the ability to send
and receive free text messages, ACARS messages and CPDLC messages to support end-to-
end AOC communication over VDL.
Boeing 757-200/-300 MAINTENANCE MANUAL SUPPLEMENT
EFFECTIVITY 23-22-00 AIRPLANES WITH DLINK+ W/ CPDLC ACARS PAGE 201 Approval CRA-757-2320-52F or later
ACARS - SOFTWARE INSTALLATION
1. General
A. This procedure contains the task to install the Dlink+ w/ CPDLC ACARS Unit software into the Personality Module using a laptop computer and the Ethernet Maintenance Port located on the P61 Panel.
2. ACARS Software Installation with a Laptop Computer
A. References
1) AMM 24-22-00/201, Electrical Power - Control
B. Access
1) Location Zones 211/212 Flight Compartment
C. Procedure
1) Make sure the following circuit breaker is close: a) 11G6, ACARS
2) On the P61 Panel, connect the laptop computer containing the LaptopLoader Software to the Ethernet Maintenance Port by using a Ethernet cable.
3) Turn the laptop computer ON and start the LaptopLoader Software containing the Dlink+ configuration files for the aircraft.
4) To load the Dlink+ w/ CPDLC ACARS Unit configuration to the PM, click on the Write Config button and select the appropriate file that is provided for the aircraft.
5) Once the file is selected, click OPEN to access the configuration software file.
6) Enter the Tail Number and ICAO address for the aircraft and press OK. NOTE: The laptop loader will close and the Dlink+ w/ CPDLC ACARS Unit will reboot.
7) After the Dlink+ w/ CPDLC ACARS Unit reboot is complete, start the LaptopLoader Software and click the Write DB button.
8) Select the customer or test database file provided for the aircraft and click OPEN. NOTE: The laptop loader will close and the Dlink+ w/ CPDLC ACARS Unit will reboot.
9) Turn off the laptop and disconnect the Ethernet cable from the P61 Panel Ethernet Maintenance Port.
10) Do an ACARS System Test per AMM 23-22-00/501.
Boeing 757-200/-300 MAINTENANCE MANUAL SUPPLEMENT
EFFECTIVITY 23-22-01 AIRPLANES WITH DLINK+ W/ CPDLC ACARS PAGE 401 Approval CRA-757-2320-52F or later
ACARS - REMOVAL/INSTALLATION
1. General
A. There are two tasks in this procedure. The first task is the removal of the Dlink+ w/ CPDLC ACARS Unit. The second task is the installation of the Dlink+ w/ CPDLC ACARS Unit.
B. The Dlink+ w/ CPDLC ACARS Unit is installed in the P8 Aft Electronic Control Panel.
2. Dlink+ w/ CPDLC ACARS Unit - Removal
A. References
1) AMM 24-22-00/201, Electrical Power - Control
B. Access
1) Location Zones 211/212 Flight Compartment
C. References
1) AMM 24-22-00/201, Electrical Power - Control
D. Procedure
1) Open the following circuit breakers and attach DO-NOT-CLOSE tags: a) 11G5, PRINTER
b) 11G6, ACARS
2) Remove the Dlink+ w/ CPDLC ACARS Unit (AMM 20-10-01/401). a) Loosen the four quarter-turn fasteners that attach the Dlink+ w/ CPDLC ACARS Unit to the P8
Panel.
b) Lift the Dlink+ w/ CPDLC ACARS Unit to get access to the electrical connectors.
c) Disconnect the electrical connectors.
d) Put a protective cover on the electrical connector.
3. Dlink+ w/ CPDLC ACARS Unit - Installation
A. References
1) AMM 24-22-00/201, Electrical Power - Control
B. Access
1) Location Zones 211/212 Flight Compartment
Boeing 757-200/-300 MAINTENANCE MANUAL SUPPLEMENT
EFFECTIVITY 23-22-01 AIRPLANES WITH DLINK+ W/ CPDLC ACARS PAGE 402 Approval CRA-757-2320-52F or later
C. Procedure
1) Make sure the following circuit breakers are open: a) 11G5, PRINTER
b) 11G6, ACARS
2) Install the Dlink+ w/ CPDLC ACARS Unit (AMM 20-10-01/401). a) Remove the protective cover from the electrical connector.
b) Examine the electrical connectors for bent or broken pins, dirt and damage.
c) Connect the electrical connector.
d) Put the Dlink+ w/ CPDLC ACARS Unit in its position in the P8 Panel.
e) Tighten the four quarter-turn fasteners.
3) Remove the DO-NOT-CLOSE tags and close these circuit breakers: a) 11G5, PRINTER
b) 11G6, ACARS
4) Perform an ACARS System Test per AMM 23-22-00/501.
Boeing 757-200/-300 MAINTENANCE MANUAL SUPPLEMENT
EFFECTIVITY 23-22-02 AIRPLANES WITH DLINK+ W/ CPDLC ACARS PAGE 401 Approval CRA-757-2320-52F or later
PERSONALITY MODULE - REMOVAL/INSTALLATION
1. General
A. There are two tasks in this procedure. The first task is the removal of the Personality Module. The second task is the installation of the Personality Module.
B. The Personality Module is installed to one of the Dlink+ w/ CPDLC ACARS Unit harnesses located in the P8 Aft Electronic Control Panel.
2. Personality Module - Removal
A. References
1) AMM 24-22-00/201, Electrical Power - Control
B. Access
1) Location Zones 211/212 Flight Compartment
C. Procedure
1) Open the following circuit breakers and attach DO-NOT-CLOSE tags: a) 11G5, PRINTER
b) 11G6, ACARS
2) Remove the Personality Module (AMM 20-10-01/401). a) Remove the Dlink+ w/ CPDLC ACARS Unit from the P8 Panel (AMM 23-22-01/401).
b) Cut the tie wraps that secure the Personality Module to the harness.
c) Disconnect the electrical connector.
d) Put a protective cover on the electrical connector.
3. Personality Module - Installation
A. References
1) AMM 24-22-00/201, Electrical Power - Control
B. Access
1) Location Zones 211/212 Flight Compartment
Boeing 757-200/-300 MAINTENANCE MANUAL SUPPLEMENT
EFFECTIVITY 23-22-02 AIRPLANES WITH DLINK+ W/ CPDLC ACARS PAGE 402 Approval CRA-757-2320-52F or later
C. Procedure
1) Make sure the following circuit breakers are open: a) 11G5, PRINTER
b) 11G6, ACARS
2) Install the Personality Module (AMM 20-10-01/401) a) Remove the protective cover from the electrical connector.
b) Examine the electrical connectors for bent or broken pins, dirt and damage.
c) Connect the electrical connector.
d) Attach the Personality Module to the harness using tie wraps.
e) Install the Dlink+ w/ CPDLC ACARS Unit in the P8 Panel (AMM 23-22-01/401).
3) Remove the DO-NOT-CLOSE tags and close these circuit breakers: a) 11G5, PRINTER
b) 11G6, ACARS
4) Install the Personality Module Configuration and Database software per AMM 23-22-00/201.
5) Perform an ACARS System Test per AMM 23-22-00/501.
Boeing 757-200/-300 MAINTENANCE MANUAL SUPPLEMENT
EFFECTIVITY 23-22-03 AIRPLANES WITH DLINK+ W/ CPDLC ACARS PAGE 401 Approval CRA-757-2320-52F or later
ANNUNCIATIOR PANEL - REMOVAL/INSTALLATION
1. General
A. There are two tasks in this procedure. The first task is the removal of the Annunciator Panel Assembly. The second task is the installation of the Annunciator Panel Assembly.
B. The Annunciator Panel Assembly is installed in the P9 FWD Control Stand or P10 Quadrant Control Stand. See figures 2 & 3 for configuration 1 & 2.
Figure 2 – Annunciator Panel Config 1, One panel on P9 Control stand.
Boeing 757-200/-300 MAINTENANCE MANUAL SUPPLEMENT
EFFECTIVITY 23-22-03 AIRPLANES WITH DLINK+ W/ CPDLC ACARS PAGE 402 Approval CRA-757-2320-52F or later
Figure 3 – Annunciator Panel Config 2, Two panels on P10 Quadrant stand.
Boeing 757-200/-300 MAINTENANCE MANUAL SUPPLEMENT
EFFECTIVITY 23-22-03 AIRPLANES WITH DLINK+ W/ CPDLC ACARS PAGE 403 Approval CRA-757-2320-52F or later
2. Annunciator Panel Assembly - Removal
A. Removal Procedure
1) Open the following circuit breakers and attach DO-NOT-CLOSE tags:
• Indicator Lights, located on P11-2 Panel.
• Indicator Lights Test, located on P11-2 Panel.
• ACARS, located on P11-1 Panel.
2) Ensure Dlink+ and Master Dim and Test systems are completely powered down.
3) Gain access to the Annunciator Panel Assembly ( Reference figure 2 & 3 ).
4) Loosen the two turnlock fasteners on the front of the assembly.
5) Lift the panel assembly and disconnect the D-sub connector from the back of the assembly.
3. Annunciator Panel Assembly - Installation
A. Installation Procedure
1) Open the following circuit breakers and attach DO-NOT-CLOSE tags:
• Indicator Lights, located on P11-2 Panel.
• Indicator Lights Test, located on P11-2 Panel.
• ACARS, located on P11-1 Panel.
2) Ensure Dlink+ and Master Dim and Test systems are completely powered down.
3) Gain access to the Annunciator Panel Assembly location ( Reference figure 2 & 3 ).
4) Locate the Annunciator Panel harness with the D-sub connector.
5) Connect the D-sub connector the receptacle on the back of the Panel Assembly.
6) Insert the Panel Assembly into its position and tighten the two turnlock fasteners on the front of the assembly.
Boeing 757-200/-300 MAINTENANCE MANUAL SUPPLEMENT
EFFECTIVITY 23-22-03 AIRPLANES WITH DLINK+ W/ CPDLC ACARS PAGE 404 Approval CRA-757-2320-52F or later
B. Installation Test
1) Supply electrical power (AMM 24-22-00/201)
2) Remove tags and close the following circuit breakers:
• Indicator Lights, located on P11-2 Panel.
• Indicator Lights Test, located on P11-2 Panel.
• ACARS, located on P11-1 Panel.
3) Push the TEST switch on the right lightning control panel P5 and make sure the annunciators illuminate.
4) Put the airplane back to its usual condition.
• Remove electrical power if it is not necessary (AMM 22-22-00/201)
Boeing 757-200/-300 MAINTENANCE MANUAL SUPPLEMENT
EFFECTIVITY 23-22-00 AIRPLANES WITH DLINK+ W/ CPDLC ACARS PAGE 501 Approval CRA-757-2320-52F or later
ACARS - ADJUSTMENT/TEST
1. General
A. There are two tasks in this procedure. The first task is the operational test of the Dlink+ Aircraft Communications Addressing and Reporting System (ACARS) and Controller Pilot Data Link Communications (CPDLC). The second is the system test of the ACARS and CPDLC.
B. The operational test is a minimum check of the basic ACARS and CPDLC systems.
C. The system test contains checks of all primary ACARS functions. Test includes checks of the OOOI operation and the ACARS interfaces.
D. When the ACARS cannot make a link with the ground station it is not a system failure. This is usually one of the following conditions:
1) The RF path between the VHF antenna and the ground station is blocked. It can help to move the airplane to a better location.
2) The ground station has a problem. Inform the ground station that a link cannot be made.
E. If the airplane is towed, or moved with power on, open the ACARS circuit breaker to avoid a ACARS Out Time transmission.
2. ACARS Operational Test
A. References
1) AMM 23-22-00/201, ACARS Software Installation
2) AMM 24-22-00/201, Electrical Power - Control
B. Prepare for the Operation Test.
1) Supply electrical power (AMM 24-22-00/201)
2) Make sure the following circuit breakers are closed: a) 11G5, PRINTER
b) 11G6, ACARS
C. Procedure
1) Test Setup a) Locate the aircraft on the airfield away from any existing structures that may shadow the
reception from a remote VHF ground station.
b) From the main menu of the Dlink+ w/ CPDLC ACARS Unit, locate the maintenance menu by
navigating through the units menu selection.
NOTE: The menus will look different depending on specific aircraft type and installation. The maintenance menu can be located from a MISC or MAINT selection on the Dlink+ w/ CPDLC ACARS Unit main menu.
Boeing 757-200/-300 MAINTENANCE MANUAL SUPPLEMENT
EFFECTIVITY 23-22-00 AIRPLANES WITH DLINK+ W/ CPDLC ACARS PAGE 502 Approval CRA-757-2320-52F or later
c) From the Dlink+ w/ CPDLC ACARS Unit main menu, select the Line Select Key (LSK) adjacent
to the MISC or MAINT menu optin as required to access the maintenance menu pages.
NOTE: The Dlink+ w/ CPDLC ACARS Maintenance Menu pages will normally contain radio status and OOOI status on the page 1A and typically contain specific system checks on page 1B.
2) ACARS VHF Ping Test a) From the Dlink+ w/ CPDLC ACARS Unit maintenance menu page 1B, select the LSK adjacent
to the PING TEST prompt.
b) From the PING TEST screen, select the LSK adjacent to the TEST CONTROL prompt and
verify that the display changes from STOP to GO.
c) Verify proper VHF connection and that the Ping Test passes by verifying that the TEST
CONTROL display changes to WAIT and the returns to STOP.
NOTE: The DELAY CNT will count the seconds until the response is received. The AVG SEC will show the time it takes to receive a response. If no test response is received after the timeout period the TEST CONTROL will display a FAIL message.
3) Annunciator Light Test a) On the Dlink+ w/ CPDLC ACARS unit, press and hold the A/B LSK.
b) Verify that the Dlink+ w/ CPDLC ACARS unit annunciator lights (MSG, TEMP, CPDLC and
FAIL) come on.
D. Put the airplane back to its usual condition
1) Return the Dlink+ w/ CPDLC ACARS display to the main menu page.
2) Remove electrical power (AMM 24-22-00/201)
Boeing 757-200/-300 MAINTENANCE MANUAL SUPPLEMENT
EFFECTIVITY 23-22-00 AIRPLANES WITH DLINK+ W/ CPDLC ACARS PAGE 503 Approval CRA-757-2320-52F or later
3. ACARS System Test
A. References
1) AMM 24-22-00/201, Electrical Power - Control
2) AMM 31-31-00/501, Flight Data Recorder System
3) AMM 31-41-00/501, EICAS System
4) AMM 32-09-02/501, Air/Ground Relay System
5) AMM 33-13-00/501, Integral Panel Lights
6) AMM 34-12-00/501, Air Data Computer System
7) AMM 34-21-00/501, Inertial Reference System
8) AMM 34-61-00/501, Flight Management System
B. Prepare for the system test
1) Supply electrical power (AMM 24-22-00/201)
2) Make sure the following circuit breakers are closed: a) 11G5, PRINTER
b) 11G6, ACARS
C. Procedure
1) Test Setup a) Locate the aircraft on the airfield away from any existing structures that may shadow the
reception from a remote VHF ground station.
b) From the main menu of the Dlink+ w/ CPDLC ACARS Unit, locate the maintenance menu by
navigating through the units menu selection.
NOTE: The menus will look different depending on specific aircraft type and installation. The maintenance menu can be located from a MISC or MAINT selection on the Dlink+ w/ CPDLC ACARS Unit main menu.
c) From the Dlink+ w/ CPDLC ACARS Unit main menu, select the Line Select Key (LSK) adjacent
to the MISC or MAINT menu optin as required to access the maintenance menu pages.
NOTE: The Dlink+ w/ CPDLC ACARS Maintenance Menu pages will normally contain radio status and OOOI status on the page 1A and typically contain specific system checks on page 1B.
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2) Annunciator Light Test a) On the Dlink+ w/ CPDLC ACARS unit, press and hold the A/B LSK.
b) Verify that the Dlink+ w/ CPDLC ACARS unit annunciator lights (MSG, TEMP, CPDLC and
FAIL) come on.
3) OOOI Interface Test a) From the Dlink+ w/ CPDLC ACARS Unit maintenance page 1A, verify that the OOOI are
operating by changing the discrete states on the aircraft and verifying that they change state on
the OOOI status screen.
CPDLC Chime On/Off ACARS Annunciator On/Off CPDLC Annunciator On/Off
4) Application Software Version Test a) From the Dlink+ w/ CPDLC ACARS Unit maintenance page 1B, select the Line Select Key
(LSK) adjacent to the DLINK CONFIG prompt.
b) From the CONFIG screen, select the LSK adjacent to the VERSION menu option.
c) From the VERSION screen, verify that the following application software is being used:
NOTE: Application Software might vary depending on aircraft type and configuration. SBC 6B70 IO 5D58 DU D849
d) Return to the Dlink+ w/ CPDLC ACARS Unit CONFIG menu screen.
5) Aircraft Registration and ICAO Address Test a) From the CONFIG screen, select the LSK adjacent to the USER EDIT prompt.
NOTE: The USER EDIT option can edit the user's configurations.
b) Verify that the PASSWORD menu screen is displayed.
c) Type in the user password in the proper location and press the ENTER key.
NOTE: The default user password is "USER00"
d) Verify that the EDIT CONFIGURATION 1/3 menu screen is displayed.
e) From the EDIT CONFIGURATION screen page 1, verify that the correct aircraft registration
number and ICAO address is displayed.
f) Return to the Dlink+ w/ CPDLC ACARS Unit maintenance menu screen.
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g) If any changes were made to the EDIT CONFIGURATION screen, follow the steps to return to
the Dlink+ w/ CPDLC ACARS Unit maintenance menu.
i. Select the LSK adjacent to the RETURN prompt and verify that the CONFIRMATION
menu is displayed.
ii. On the CONFIRMATION menu screen, press the LSK until the NO or YES option is
displayed.
NOTE: Pressing the LSK will cycle the selection to NO, CANCEL and YES.
iii. Once the NO or YES option is selected, select the LSK adjacent to the RETURN
prompt to return to the Dlink+ w/ CPDLC ACARS Unit maintenance menu screen.
6) Monitor Bus Status Test a) From the Dlink+ w/ CPDLC ACARS Unit maintenance page 1B, select the LSK adjacent to the
MONITOR prompt.
NOTE: The Monitor menu will display the status of each of the ARINC 429 busses and some of the key variables interfaced to the Dlink+ w/ CPDLC ACARS Unit.
b) From the MONITOR Bus Status screen, verify that each of the following ARINC 429 busses
display a GOOD status:
i. FMC
ii. IRU
iii. ADC
iv. EICAS
v. FQPU
c) Open the following circuit breakers:
i. 11A10, AIR DATA CMPTR L
ii. 11A11, AIR DATA AOA SENSOR L
iii. 11A12, AIR DATA BARO CORRECT L
iv. 11C34, FUEL QTY 1
v. 11E9, FMCS CMPTR LEFT
vi. 11J2, EICAS CMPTR L
vii. 11J29, EICAS CMPTR R
viii. 11L19, FUEL QTY 2
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d) From the MONITOR Bus Status screen, verify that each of the following ARINC 429 busses
display a FAIL status:
i. FMC
ii. IRU
iii. ADC
iv. EICAS
v. FQPU
e) Close the following circuit breakers:
i. 11A10, AIR DATA CMPTR L
ii. 11A11, AIR DATA AOA SENSOR L
iii. 11A12, AIR DATA BARO CORRECT L
iv. 11C34, FUEL QTY 1
v. 11E9, FMCS CMPTR LEFT
vi. 11J2, EICAS CMPTR L
vii. 11J29, EICAS CMPTR R
viii. 11L19, FUEL QTY 2
f) From the MONITOR Bus Status screen, verify that each of the following ARINC 429 busses
display a GOOD status:
i. FMC
ii. IRU
iii. ADC
iv. EICAS
v. FQPU
g) If there are any variables displayed on the MONITOR Bus Status screen, verify that each of the
variables display a value and not XXX.
h) Return the Dlink+ w/ CPDLC ACARS Unit maintenance menu screen.
7) Printer Interface Test a) From the + Dlink+ w/ CPDLC ACARS Unit maintenance menu page 1B, select the LSK
adjacent to the PRINT TEST prompt.
b) From the PRINT TEST screen, select the LSK adjacent to the PRINT prompt and verify that the
Data Printer prints the information select on the Dlink+ w/ CPDLC ACARS Unit screen.
c) Return to the Dlink+ w/ CPDLC ACARS Unit maintenance menu screen.
8) VHF Ping Test a) From the Dlink+ w/ CPDLC ACARS Unit maintenance menu page 1B, select the LSK adjacent
to the PING TEST prompt.
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b) From the PING TEST screen, select the LSK adjacent to the TEST CONTROL prompt and
verify that the display changes from STOP to GO.
c) Verify proper VHF connection and that the Ping Test passes by verifying that the TEST
CONTROL display changes to WAIT and the returns to STOP.
NOTE: The DELAY CNT will count the seconds until the response is received. The AVG SEC will show the time it takes to receive a response. If no test response is received after the timeout period the TEST CONTROL will display a FAIL message.
d) Return to the Dlink+ w/ CPDLC ACARS Unit main menu screen.
9) Free Text Message Test a) From the Return to the Dlink+ w/ CPDLC ACARS Unit main menu screen page 1A, select the
LSK adjacent to the FREE TEXT prompt.
b) From the FREE TEXT screen page 1A, type in a message with a minimum length of 24
characters. The outgoing message should request the recipient to reply with a text message.
c) From the FREE TEXT screen, select page 1B and then select the LSK adjacent to the SEND
option.
d) Verify that the message was transmitted.
e) Return to the Dlink+ w/ CPDLC ACARS Unit main menu screen.
f) Verify that the MSG annunciator on the Dlink+ w/ CPDLC ACARS Unit and ACARS annunciator
on the P9 Forward Electronic Control Panel illuminate when the uplinked message is received.
g) Confirm the received message is in response to the sent message.
10) CPDLC Interoperability Test a) Logon and make a CPDLC connection with an appropriate ATC using the following steps:
i. Aircraft issues a CM logon request
ii. ATC verifies CM logon indication reception
iii. ATC uplinks CM logon response
iv. ATC uplinks CPDLC start request
v. Aircraft verifies CPDLC connection established
vi. Aircraft checks CDA on CPDLC logon status page
vii. ATC verifies CDA message received
viii. ATC uplinks message: CURRENT ATC UNIT CENTER (UM 183)
ix. Aircraft verifies receipt of message: CURRENT ATC UNIT CENTER
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b) Test the altitude change request process by using the following steps:
i. Aircraft downlinks message: REQUEST FL390 (DM 6)
ii. ATC verifies receipt of message: REQUEST FL390
iii. ATC uplinks message: CLIMB TO FL410 (UM 20)
iv. Aircraft verifies message: CLIMB TO FL410
v. Aircraft downlinks message: UNABLE (DM 1)
vi. ATC verifies message: UNABLE
c) Test the direct to request process by using the following steps:
i. Aircraft downlinks message: REQUEST DIRECT TO CVG (DM 22)
ii. ATC verifies receipt of message: REQUEST DIRECT TO CVG
iii. ATC uplinks message: STANDBY (UM 1)
iv. Aircraft verifies receipt of message: STANDBY
v. ATC uplinks message: PROCEED DIRECT TO CVG (UM 74)
vi. Aircraft verifies receipt of message: PROCEED DIRECT TO CVG
vii. Aircraft downlinks message: WILCO (DM 0)
viii. ATC verifies receipt of message: WILCO
d) Test the heading change process by using the following steps:
i. ATC uplinks message: TURN RIGHT 10 DEGREES (UM 215)
ii. Aircraft verifies receipt of message: TURN RIGHT 10 DEGREES
iii. Aircraft downlinks message: WILCO (DM 0)
iv. ATC verifies receipt of message: WILCO
e) Test the altitude change clearance process by using the following steps:
i. ATC uplinks message: CLIMB TO FL350 (UM 20)
ii. Aircraft verifies receipt of message: CLIMB TO FL350
iii. Aircraft downlinks message: UNABLE (DM 1)
iv. ATC verifies receipt of message: UNABLE
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f) Test the altitude change clearance and message expired process by using the following steps:
i. ATC uplinks message: DESCEND TO FL250
ii. Aircraft waits for message to time out.
iii. Aircraft verifies message status is EXPIRED and no response can be sent.
iv. Aircraft automatically downlinks message: ERROR
v. ATC verifies receipt of message: ERROR
vi. ATC verifies message reason: INSUFFICIENT RESOURCES and AIR SYSTEM
TIMEOUT
g) Test the direct to request and heading change clearance process by using the following steps:
i. Aircraft downlinks message: REQUEST DIRECT TO CVG (DM 22)
ii. ATC verifies receipt of message: REQUEST DIRECT TO CVG
iii. ATC uplinks message: FLY HEADING 180 (UM 190)
iv. Aircraft verifies receipt of message: FLY HEADING 180
v. Aircraft downlinks message: STANDBY (DM 2)
vi. ATC verifies receipt of message: STANDBY
vii. Aircraft downlinks message: WILCO (DM 0)
viii. ATC verifies receipt of message: WILCO
h) Test the squawk change clearance process by using the following steps:
i. ATC uplinks message: SQUAWK 1234 (UM 123)
ii. Aircraft verifies receipt of message: SQUAWK 1234
iii. Aircraft downlinks message: WILCO (DM 0)
iv. ATC verifies receipt of message: WILCO
i) Test the check stuck microphone process by using the following steps:
i. ATC uplinks message: CHECK STUCK MICROPHONE 132.085 (UM 157)
ii. Aircraft verifies receipt of message: CHECK STUCK MICROPHONE 132.085
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j) Test the CPDLC connection transfer process by using the following steps:
i. ATC1 uplinks CM contact request for ATC2
ii. Aircraft verifies receipt of CM contact request
iii. Aircraft downlinks CM logon request to ATC2
iv. Aircraft verifies CM logon response from ATC2
v. Aircraft downlinks CM contact response to ATC1
NOTE: The aircraft messages are automatic and transparent to the flight crew.
vi. ATC1 Uplinks message: NDA ATC2
vii. Aircraft verifies receipt of message: NDA ATC2
viii. Aircraft verifies that ATC1 is CDA and ATC2 is NDA
ix. ATC2 establishes CPDLC connection
x. ATC1 uplinks message: CONTACT ATC2 (UM 117)
xi. Aircraft verifies receipt of message: CONTACT ATC2
xii. Aircraft downlinks message: WILCO (DM 0)
xiii. Aircraft downlinks CDA message to ATC2
xiv. ATC2 verifies receipt of CDA
xv. Aircraft verifies that ATC2 is CDA
D. Put the airplane back to its usual condition
1) Return the Dlink+ w/ CPDLC ACARS display to the main menu page.
2) Remove electrical power (AMM 24-22-00/201)
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DATA PRINTER - DESCRIPTION AND OPERATION
1. General
A. The Data Printer is a general purpose airborne message, thermal line printer designed specifically for commercial aircraft.
B. The Data Printer contains a power supply, stepper motor, controller module, print drive module, selector light module, and stationary thermal printer head to produce prints.
C. The Data Printer meets the specifications of ARINC 740 to include the following capabilities:
1) Interfaces with up to 12 ARINC 429 subsystems using prioritized polling.
2) Variable print formats - 40, 64, 80, 80 sideways
3) Up to 80 characters per line and 7 lines per inch
4) Multiple print character sets available (32K byte font memory)
5) Supports paper width of 4.375 inches, 100 feet per roll
6) Print rate of 120 40-character lines per minute
D. The Data Printer receives power from the left 115V AC bus. The system circuit breaker is on the P11 Overhead Panel.
2. Component Details (Figure 1)
A. Data Printer
1) The Data Printer is a single Line Replaceable Unit (LRU) designed to fit standard flight deck instrument rails.
2) All Data Printer processing and control is performed by a single plug in circuit board, the controller module. The controller contains a 32K byte EPROM in which the operational software and character fonts are individually partitioned. Print messages are buffered in two RAMs, which provided data protection from power interrupts by retained data for up to two minutes upon power interruption. Fault diagnostic is provided by a single digit hexadecimal display, viewed when the paper access panel is open.
3) The printer drive module contains all the circuitry for interfacing the print head mechanism as well as the high current drivers for the print head and stepper motor.
4) The stepper motor supplies the mechanical drive to advance the paper during printing operations or paper feeding operations.
5) The sensor light module is a reflective object sensor which deactivates the print head when there is no paper left on the spindle, preventing print head damage.
6) The Data Printer uses thermal printer paper (non-perforated) rolls that are 4.375 inches wide with a maximum diameter of 2.1 inches.
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DATA PRINTER PTA-45B FOR DLINK+ ACARS CPDLC UNIT - Component Location on Pilots Aft Electronic Control Panel
Figure 4
Boeing 757-200/-300 MAINTENANCE MANUAL SUPPLEMENT
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B. Operation
1) The Data Printer is off when the 115V AC left bus power is removed.
2) Message Printing: a) Print message priority is determined by port number allocation. Port #1 has the highest priority.
Print message polling is defined by ARINC 740.
b) When a message has finished printing, the Data Printer will automatically advance the paper
outside the printer.
c) A message being printed will always be completed before polling for subsequent messages.
d) Dual blades allow for two-way paper tear for print removal.
3) Data Printer Switch/Indicator: a) SLEW switch - depress to advance paper
b) TEST switch - performs a functional BITE test and generates a print out of a graphic test
pattern and fault diagnostic messages.
c) ALERT RESET switch - reset the printer's alert relay contacts
d) MSG annunciator - illuminates to indicate receipt of a message. Depress teh RESET button to
extinguish the annunciator.
e) PAPER indicator - illuminates when the printer is out of paper.
f) FAIL indicator - illuminates when a fault is detected by the BITE test.
g) PAPER FULL/EMPTY indicator - mechanical indicator which shows the amount of paper
loaded in the printer.
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DATA PRINTER - PAPER ROLL REPLACEMENT
1. General
A. This procedure contains the task to replace the paper roll in the Data Printer.
B. The Data Printer uses thermal printer paper (non-perforated) rolls that are 4.375 inches wide with a maximum diameter of 2.1 inches.
C. The Data Printer is installed in the P8 Aft Electronic Control Panel.
2. Data Printer - Paper Roll Replacement
A. References
1) AMM 24-22-00/201, Electrical Power - Control
B. Access
1) Location Zones 211/212 Flight Compartment
C. Procedure
1) Open the following circuit breaker and attach DO-NOT-CLOSE tag: a) 11G5, PRINTER
2) Paper Roll Replacement (Figure 5) a) On the face of the Data Printer, turn the thumbscrew counterclockwise to release the front
panel.
b) Open the front panel to the 180° position.
c) Release the hinged paper roll spindle by pushing to the right and pulling straight out to the full
90° position. Remove the empty paper roll.
d) Load new paper roll onto the spindle with the end of the paper facing towards the printer.
e) Close the spindle with the paper roll and lock into place by pushing to the right.
f) Thread the end of the paper through the guide (drag) bar as indicated by the arrows until end of
paper extends under the finger bar and rest on the platen roller. Continue to thread the paper
out of the paper cutter slot at the bottom of the front panel.
g) Close the front panel and secure with the thumbscrew.
3) Remove the DO-NOT-CLOSE tag and close these circuit breaker: a) 11G5, PRINTER
4) Depress the Data Printer SLEW switch. Ensure the paper feeds through the print head properly.
5) Perform a Data Printer Operational Test per AMM 31-33-00/501.
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D. Put the airplane back to its usual condition
1) Remove electrical power (AMM 24-22-00/201)
Data Printer - Paper Replacement
Figure 5
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DATA PRINTER - REMOVAL/INSTALLATION
1. General
A. There are two tasks in this procedure. The first task is the removal of the Data Printer. The second task is the installation of the Data Printer. The installation task includes an operational test of the Data Printer.
B. The Data Printer is installed in the P8 Aft Electronics Control Panel.
2. Data Printer - Removal
A. References
1) AMM 24-22-00/201, Electrical Power - Control
B. Access
1) Location Zones 211/212 Flight Compartment
C. Procedure
1) Open the following circuit breaker and attach DO-NOT-CLOSE tag: a) 11G5, PRINTER
2) Remove the Data Printer: a) Loosen the four quarter-turn fasteners that attach the Data Printer to the P8 Panel.
b) Lift the Data Printer to get access to the electrical connector.
c) Disconnect the electrical connector.
d) Put a protective cover on the electrical connector.
3. Data Printer - Installation
A. References
1) AMM 24-22-00/201, Electrical Power - Control
B. Access
1) Location Zones 211/212 Flight Compartment
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C. Procedure
1) Make sure the following circuit breaker is open: a) 11G5, PRINTER
2) Install the Data Printer a) Remove the protective cover from the electrical connector.
b) Examine the electrical connector for bent or broken pins, dirt and damage.
c) Connect the electrical connector.
d) Put the Data Printer in its position in the P8 Panel.
e) Tighten the four quarter-turn fasteners.
3) Remove the DO-NOT-CLOSE tag and close the following circuit breaker: a) 11G5, PRINTER
4) Perform a Data Printer System Test per AMM 31-33-00/501.
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DATA PRINTER - ADJUSTMENT/TEST
1. General
A. There are two tasks in this procedure. The first task is the operational test of the Data Printer. The second is the system test of the Data Printer.
B. The operational test is a self-test of the Data Printer.
C. The system test contains the operational test and checks the interface between the Data Printer and ACARS.
2. Data Printer Operational Test
A. References
1) AMM 24-22-00/201, Electrical Power - Control
B. Access
1) Location Zones 211/212 Flight Compartment
C. Prepare for the Operation Test.
1) Supply electrical power (AMM 24-22-00/201)
2) Make sure the following circuit breakers are closed: a) 11G5, PRINTER
b) 11G6, ACARS
D. Procedure
1) Data Printer Self-Test: a) On the front panel of the Data Printer, depress the TEST button.
b) Verify that the Data Printer outputs a graphical test pattern (printer fonts) and no fault code
messages.
E. Put the airplane back to its usual condition
1) Remove electrical power (AMM 24-22-00/201)
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3. Data Printer System Test
A. References
1) AMM 24-22-00/201, Electrical Power - Control
2) AMM 23-22-00/501, ACARS
B. Access
1) Location Zones 211/212 Flight Compartment
C. Prepare for the System Test.
1) Supply electrical power (AMM 24-22-00/201)
2) Make sure the following circuit breakers are closed: a) 11G5, PRINTER
b) 11G6, ACARS
D. Procedure
1) Data Printer Self-Test: a) On the front panel of the Data Printer, depress the TEST button.
b) Verify that the Data Printer outputs a graphical test pattern (printer fonts) and no fault code
messages.
2) ACARS/Data Printer Interface Test: a) On the P8 Panel, locate the Dlink+ w/ CPDLC ACARS Unit and navigate to the maintenance
menu.
b) From the Dlink+ w/ CPDLC ACARS Unit maintenance menu page 1B, select the LSK adjacent
to the PRINT TEST prompt.
c) From the PRINT TEST screen, select the LSK adjacent to the PRINT prompt and verify that the
Data Printer prints the information select on the Dlink+ w/ CPDLC ACARS Unit screen.
d) Return to the Dlink+ w/ CPDLC ACARS Unit main menu screen.
E. Put the airplane back to its usual condition
1) Remove electrical power (AMM 24-22-00/201)
