C CRJ200

WIRING DIAGRAM MANUAL

INTRODUCTION

1. General

A. The Wiring Diagram Manual (WDM), for the Canadair Regional Jet, agrees with the Air Transport
Association of America Specification No. 100 (ATA 100), Revision 26, dated Apr 1/87.

The electronic version of the Wiring Diagram Manual (WDM), for the Canadair Regional Jet,
agrees with the Air Transport Association of America Specification No. 2100 (ATA−2100).

B. This WDM has data and procedures that are applicable only to the Bombardier Regional Jet
CRJ100/200/440 Series, Model CL−600−2B19 (CL−601R) aircraft.

C. The Wiring Diagram Manual contains point to point wiring information on all electrically−operated
systems of the Regional Jet Aircraft.

2. Correspondence

A. For requests for changes to the manual, please send the Technical Manual Change Request
(MCR) form contained in this manual.

Send all other correspondence about this manual to the address below:

Bombardier Inc.
Bombardier Aerospace Regional Aircraft
Customer Support
Mailbox Stop N42−25
123 Garratt Blvd., Toronto
Ontario, Canada
M3K 1Y5
Attention: Director, Technical Publications.
or send to the Technical Manual Change Request (MCR) form contained in this
manual.

3. Translation of Manual

A. If all or part of the Canadair Regional Jet WDM is translated, the official version is the English
language version by Bombardier Regional Aircraft Division.

4. Service Life Limits

A. Service Life Limits are given in Section 5 of the MPD and are recognized by the Airworthiness
Authorities.

CSP A−003 − MASTER

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5. Temporary Revisions

A. Bombardier Regional Aircraft Division will supply temporary revision service to this manual as
necessary. The Temporary Revisions supply the configuration differences before the next
scheduled revision.

B. Temporary Revisions are applicable to only one page block. Temporary Revisions are not
revised. If changes are necessary to the Temporary Revision, a new Temporary Revision is
supplied.

6. Statement of Effectivity

A. Effectivity data is given on an Effectivity Sheet located before Sheet 1 of each diagram.

The effectivity block, found on the lower left corner of each sheet within the diagram, will always
refer to Effectivity Sheet 1 of that diagram.

B. When a page applies to all aircraft, the phrase **ON A/C ALL will show on the Effectivity Sheet. If
the information does not apply to all aircraft, the manufacturer serial number of the aircraft is
given.

C. In the master manual, all information applicable to all aircraft is given. The effectivity is derived
from applicable manufacturer modification summaries and Service Bulletins.

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7. Organization of the Manual

A. General

(1) The WDM is organized on four levels as specified by ATA 100/ATA 2100. They are usually
referred to as group, chapter, section, subject. Each page contains the
chapter−section−subject number, the page number, the sheet number, the effectivity code
of the page and the revision date of the page. The groups are divided into chapter/system;
the chapter/system is divided into section/subsystem and the section/subsystem is divided
into subject/unit as follows:

Level 1 Group

Level 2 Chapter/System

Level 3 Section/Subsystem

Level 4 Subject/Unit

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B. Group

(1) Groups give a broad separation of the contents of the manual. The Wiring Diagram Manual
is organized into four groups. Each group contains aircraft systems usually known as
chapters and are divided as follows:

WM

Group 1 Group 2 Group 3 Group 4

Airframe System Structure Power Plant Charts and Lists

Chapters Chapters Chapters Chapter

21 to 49 52 71 to 80 91 and Lists

C. Chapter/System

(1) This level is usually known as the chapter. It has inter−related components arranged to do a
specific function and is further divided into subsystems usually known as sections. Each
chapter is assigned its number and title by ATA 100 and is identified by the first element in
the standard numbering system.

CHAPTER
CHAPTER TITLE
NUMBER

AIRFRAME SYSTEMS

Cross reference to the ELECTRICAL /

ELECTRONIC COMPONENTS −
20
STANDARD PRACTICES MANUAL (SPC)
CSP A−115

Air Conditioning 21

Auto Flight 22

Communications 23

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CHAPTER
CHAPTER TITLE
NUMBER

Electrical Power 24

Equipment/Furnishings 25

Fire Protection 26

Flight Controls 27

Fuel 28

Hydraulic Power 29

Ice and Rain Protection 30

Indicating/Recording Systems 31

Landing Gear 32

Lights 33

Navigation 34

Oxygen 35

Pneumatic 36

Water/Waste 38

Airborne Auxiliary Power 49

STRUCTURE

Doors 52

POWER PLANT

Power Plant 71

Engine Fuel and Control 73

Ignition 74

Engine Controls 76

Engine Indicating 77

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CHAPTER
CHAPTER TITLE
NUMBER

Exhaust 78

Oil 79

Starting 80

CHARTS AND LISTS

Charts 91

Electrical Equipment List (EEL) Lists

Extended Wire List (EWL) Lists

D. Section/Subsystem

(1) This level is usually known as the section. It permits the chapter to be divided into
subsystems and is identified by the second element in the standard numbering system.

E. Subject/Unit

(1) This level is usually known as the subject. It permits the identification of individual units in a
system or section and is identified by the third element in the standard numbering system.

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8. Standard Numbering System

A. Manual Numbering System

(1) The manual numbering system is specified by ATA 100. It is a three−element numbering
system that divides the manual material into chapter/section/subject. Each element has two
digits and is given as follows:

Elements Definition of Element

1 2 3

26 −00 −00 Material applicable to the system as a whole

System 26−00−00 Fire Protection

26 −10 −00 Material applicable to the subsystem as a whole

Subsystem 26−10−00 Detection

26 −11 −00 Material applicable to the sub−subsystem as a whole

Sub−subsystem 26−11−00 Engine Fire Detection System

26 −11 −13 Material applicable to a specific unit of the sub−subsystem

Unit 26−11−13 Fire Warning Lights

B. Page Numbering System

(1) The page numbering system in the Wiring Diagram Manual has a special significance not
applicable to other manuals. The page numbers are used to represent different
configurations of a given system, subsystem, or sub−subsystem within the fleet. For
example: 27−51−00 Page 1, 27−51−00 Page 2, and 27−51−00 Page 3 represent the first,
second and third configurations of 27−51−00 Flaps Control and Monitoring System.

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(2) The effectivity block of each page defines the configuration involved by gouping the tail
numbers of aircraft. The effectivity is expressed in three basic formats. The formats may be
combined to show all the aircraft that are possible for the configuration.

(a) The first format is just a simple list of all the aircraft with the configuration.

(b) The second format is a list of all the aircraft which may have been upgraded to the
configuration with the implementation of a service bulletin (a “POST SB”), or all aircraft
that may not have been upgraded to the configuration (a “PRE SB” condition).

(c) The third format can include a reference to a combination of specific conditions or
options for the configuration.

(d) When these forms are combined the second and third formats are always placed after
the first format of tail numbers and are preceded by “and”.

(3) Starting at revision 23, aircraft effectivity groups (pages) are now split by manufacturing
production configurations. Services bulletins are added in the wiring diagrams by updating
the production wiring diagrams to include the service bulletin changes. The main diagrams
will always show the service bulletin installed. If the pre service bulletin condition is needed,
it will be shown as a circuit detail on the note page.

C. Sheet Numbering System

(1) Electrical Wiring Diagrams whose function cannot be shown on a single sheet are presented
on additional sheets. For example: 26−11−00, Page 1, Sheet 1 of 3 , 26−11−00, Page 1,
Sheet 2 of 3 , 26−11−00 Page 1, Sheet 3 of 3 . These sheets have the necessary
cross−referencing and sheet−to−sheet circuitry interconnecting line information. These lines
are aligned and identified on each side of the break point.

9. Front Matter

A. Manual Front Matter

(1) Title Page

(a) The Title Page contains the Canadair masthead and the identification of the manual.

(2) List of Effective Aircraft

(a) The List of Effective Aircraft follows the Title Page. It provides a listing of
Manufacturer’s Serial Numbers cross−referenced with the operator assigned
Registration Numbers.

(3) Manual Change Request

(a) The Manual Change Request (MCR) form follows the List of Effective Aircraft. This
form must be filled in each time a correction or a clarification is to be made in a
publication.

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(4) Record of Revisions

(a) The Record of Revisions follows the List of Effective Aircraft. This record must be
completed whenever a revision to the WDM is received.

(5) Record of Temporary Revisions

(a) The Record of Temporary Revisions follows the Record of Revisions. The Record of
Temporary Revisions must be updated each time a Temporary Revision is added to or
removed from the WDM.

B. Chapter Front Matter

(1) List of Effective Pages

(a) The List of Effective Pages is located at the beginning of each chapter. It identifies
each chapter/section/subject and page individually and also gives the number and the
date of each page.

(2) List of Effective Temporary Revisions

(a) The List of Effective Temporary Revisions follows the List of Effective Pages for each
chapter. It identifies all effective temporary revisions at the chapter level.

(3) Table of Contents

(a) The Table of Contents, for each chapter, follows the list of effective pages and is
identified by the chapter number and the word CONTENTS. The table of contents
gives an index for the quick location of information in a chapter. All sub−subsystems
are given with the maintenance function indented below each unit. The component
units are arranged in alphabetical order by the key noun of the component. The
chapter/section/subject number, the first page number, and the effectivity information
is adjacent to each section or subject for which information is given. The arrangement
and indentation of the table of contents is as follows:

System ............................... Numerical arrangement

Subsystem ...................... Numerical arrangement

Sub−subsystem .......... Numerical arrangement

Function ................... Numerical arrangement

Component/Unit .... Alphabetical arrangement

Function ............. Numerical arrangement

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10. Definition of Warning, Caution and Note

A. ATA 100 specifies warnings, cautions and notes as follows:

WARNING:

– Calls attention to the use of materials, processes, methods, procedures, or limits that must be
followed precisely to avoid injury to persons.

CAUTION:

– Calls attention to methods and procedures that must be followed to avoid damage to
equipment.

NOTE:

– Calls attention to methods that make the job easier.

11. Note Page

A. Each wiring diagram ends with a note page. The note page provides information specific to the
system and includes added engineering information, service bulletin information and optional
system references.

B. Generally four types of notes will be used, the service bulletin notes, the optional reference notes,
the engineering notes and the configuration notes.

(1) The main drawing always reflects the post service bulletin. The note page shows the pre
service bulletin containing all the pre condition circuit details. A dashed box is used to
identify the affected circuit on the main drawing. A number inserted into a hexagon is placed
outside the dashed box indicating the corresponding note on the note page. Items shown for
reference purposes only are drawn with a dashed line. An asterisk is positioned beside the
items and plain text is added to clarify added, removed or changed wire numbers.

(2) An optional reference note is used on the main drawing when a reference to another
chapter/section/subject is optional. The optional reference note is placed beside the
reference. A number inserted into a hexagon corresponds to the applicable reference on the
note page.

(3) Engineering notes give additional information such as wire type, connector type, wire
preparation, etc.

(4) Configuration notes include a reference to a combination of specific conditions or options for
the configuration.

12. Aircraft State

A. The Wiring Diagrams show the circuits in the aircraft with “weight−on−wheels” and with switch
contacts in a “power off” condition, except where otherwise indicated.

CSP A−003 − MASTER

EFFECTIVITY: **ON A/C ALL
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13. Aircraft Station

A. This section gives information about reference planes and lines. Reference planes divide the
aircraft into stations. Reference lines divide the aircraft into waterlines and buttock lines.

(1) Fuselage Station (FS)

Refer to Figure 1.

(a) The fuselage stations are measured in inches and are perpendicular to the fuselage
centerline. FS0.00 is 144 inches (3657.6 mm) forward of the nose of the aircraft.

(2) Wing Station (WS)

Refer to Figure 2.

(a) The wing stations are measured in inches and are perpendicular to the wing reference
plane and parallel to the centerline of the fuselage.

(3) Nacelle Station (XN)

Refer to Figure 3.

(a) The nacelle stations are measured in inches and are perpendicular to the nacelle
centerline. XN0.00 is 100.72 inches (2558.3 mm) forward of the nacelle nose cowl.

(4) Vertical Stabilizer Station (VSS) and Rudder Station (RS)

Refer to Figures 4 and 5.

(a) The vertical stabilizer stations and rudder stations are measured in inches and are
perpendicular to the centerline of the vertical stabilizer rear spar.

(5) Horizontal Stabilizer Station (HSS) and Elevator Station (ES)

Refer to Figures 6 and 7.

(a) The horizontal stabilizer stations and elevator stations are measured in inches and are
perpendicular to the centerline of the horizontal stabilizer rear spar.

(6) Waterline (WL)

(a) The waterlines are measured in inches and are horizontal lines perpendicular to the
buttock line (BL) and parallel to the fuselage centerline.

(7) Buttock Line (BL)

(a) The buttock lines are measured in inches. The buttock lines are vertical lines
perpendicular to the waterline and fuselage center line. The buttock lines are parallel
to the fuselage vertical centerline.

CSP A−003 − MASTER

EFFECTIVITY: **ON A/C ALL
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(8) Maximum Half−Breadth (MHB)

(a) The maximum half−breadth line is the geometric center of the fuselage from the
forward to aft ends of the aircraft. The line joins the points of maximum half−width and
half−height of the fuselage at specified fuselage stations.

CSP A−003 − MASTER

EFFECTIVITY: **ON A/C ALL
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WIRING DIAGRAM MANUAL

ER
* PRESSURE BULKHEAD
I LIZ AL
AB IC AR FS830.00
ST ERT SP

CONE
TAIL
V AR 5%
. FS816.25
RE 67 FS789.75

FS755.00
FS736.00
FS718.00
FS700.00
FUSELAGE

FS672.20 FS682.00
AFT

FS654.50
FS640.00
FS621.00 * FS625.30
FS605.00
FS589.00
FS574.00
FS559.00 +112
EXTENSION

FS559.00 +96
FS559.00 +80
FS559.00 +64
AFT

FS559.00 +48
FS559.00 +32
FS559.00 +16
FS559.00
FS544.00
FS529.00
FUSELAGE

FS513.00
FS499.00
MID

FS484.00
FS473.15
FS461.00
FS449.85
FS439.00
FS424.00
FS409.00 +128
FS409.00 +112
EXTENSION
FORWARD

FS409.00 +96
WL73.50
WL97.50

FS409.00 +80
FS409.00 +64
FS409.00 +48
FS409.00 +32
FS409.00 +16
FS409.00
/MIDFUSELAGE

FS394.00
FS379.00
FORWARD

FS364.00
FS349.00
FS333.00
FS319.70
FS310.00
ram0631000_001.dg, sw/cs, may21/2014

FS295.00
FS280.00
WL79.50

FS265.00
FS250.00
FUSELAGE
FORWARD

MHB

FS235.00
FS220.00
FS210.00
FS193.00 FS202.75 *
FS169.00
FS144.00

Fuselage Stations
Figure 1

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WIRING DIAGRAM MANUAL

WGLTS
WGLTS 33.00 49.89 WGLTS
WGLTS 26.00
WGLTS 19.00 0.00
WGLTS 12.50
WGLTS 3.25 WGLTS 6.36
WGLTS 0.00
WS 407.08 WS 407.08

LEGEND WS 389.00
WS 377.40 15
BL. Buttock line. TRUE
WS 366.00 FS. Fuselage station.
WGLTS. Winglet station. WS
WS 353.00
WL. Water line. 353.00
WS 341.89 WS 343.50
WS 330.25 WRP. Wing reference plane.
WS 321.32 WS. Wing station.
WS 317.85 WS 314.50 WRP

WS 292.00 WS 294.50
WS 282.00
WS 277.10 WS 274.00
WS 264.00
WS 255.36 WS 260.00
WS 252.8
WS 246.93 WS 247.90
WS 242.00 WL
53.25
WS 226.51
WS 220.00
WS 213.08
WS 199.00
WS 191.44
WS 183.00 WS 178.00
WS 162.49 WS 163.00
WS 149.58 WS 148.019 WS
WS 139.924 WS 143.189 WS 139.54 148.019
WS 137.00
WS 127.25
WS 120.382
WS 104.099 WS 106.40
WS 96.13 WS
WS 97.70 WS 93.00 96.13
WS 85.50
WS 80.50
WS 75.27
WS 66.2
WS 58.50
WS 65.75
WS 56.30 2 20
WS 50.54
WS 47.61
BL 45.00
WS 29.42
ram0634000_001(1).dg, gg/kms, 21/04/95

BL 0.00 WS 0.00
WING
AIRCRAFT FS 511.00 ORIGIN
CENTERLINE (REF) FS 411.00
(REF) (REF)

Wing Stations
Figure 2 (Sheet 1 of 2)

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LEGEND
WS. Wing station.
AS. Aileron station.
WS353.00 FLS. Flap station.
AS308.42
WS282.00

FLS169.46
WS148.02

FLS50.50

ram0634000_002.dg, mg, jul25/2011

WS0.00

Wing Stations
Figure 2 (Sheet 2 of 2)

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XN100.72
XN105.00

FS589.00
XN121.60
FS59600

FS605.00
XN135.845
FS614.00
FS621.00
XN151.40 FS625.30
XN156.62

XN164.73 FS640.00

XN170.00

FS654.50
XN185.00
ZN112.780 AT FS663.40
XN190.59 YN97.750
XN196.18 FBL72.606 AT FS672.20
XN200.00 FWL120.632
XN205.70
XN208.39 FS682.00

XN214.00

XN221.96
FS700.00
XN227.80
XN232.87
XN237.93 FS711.40
XN243.00 FS718.00
XN247.90
ram0635000_002.dc, GL, 02/10/90.
FB123.483
ZN100.00

FS736.00
PBL0.00

Station − Nacelle and Pylon

Figure 3

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++ VERTICAL STABILIZER
FRONT SPAR STATIONS

15
++ VERTICAL STABILIZER

1.
+
+

73
REAR SPAR STATIONS

FS
175.20

160.06
155.06
D RIB
145.35 CANTE RI 158.71
B
NO
136.80 .9
RI
+ B
+

128.25 NO
RI .8
119.70 B 139.20
NO
.7
)
0%

111.16
RI 128.25
(2

B
102.61 NO
AR

)
.6
%
SP

117.75
75

94.06
3.
NT

)
RI

%
(4

86.52 B
O

NO 7.5
AR
FR

78.98 103.11
(6
.5
SP

AR

71.94
ID

RI
SP

+
M

B ++
64.90 NO +
AR

.4 86.11
RE

56.06
RI
B
NO
.3 69.11
RI
B RI
NO B
.1 NO
.2 52.11

23.11 37.11
rsr5500000_004(1).dc, sw/gg ,28/10/00

Vertical Stabilizer Stations

Figure 4

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RS162.96
RUDDER SPAR
CENTERLINE

RS151.50
RS148.85

RS144.86
RS142.63
2.25(REF)
RS136.90
RS133.33
RS131.17

RS125.44

RS121.80
RS119.71

RS113.98
RS110.27
RS108.25

RS102.52
RS98.75
RS95.57
RS92.94
RS90.32
RS87.69
RS85.07

RS81.50
RS78.81

RS72.78
RS71.58
RS66.75

RS61.66 RS60.72

RS54.69
RS52.48
RS51.75
rsr5500000_003.dc, sw ,19/09/90

RS47.75

RS40.45
HINGE
CENTERLINE
(72.5%)

Rudder Stations
Figure 5

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 BL122.00

+
+ HORIZONTAL STABILIZER
FRONT SPAR STATIONS BL102.25

BL95.49 BL96.26
NO.3 HINGE
FS937.13

CSP A−003 − MASTER

BL88.10 WL242.28
BL56.91
BL55.88

EFFECTIVITY: **ON A/C ALL

BL72.51
NO.2 HINGE

BL15.25 BL16.55 BL41.32

NO.1 HINGE
BL25.72 ) BL112.00
WL243.50 ( 65%
AR 118.63
FS903.76 SP
AR 110.63
BL7.37 RE
R 102.06
TO
L E VA 70%) )

Figure 6
E GE( %
(20 93.49
HIN
FS886.00 P AR %)
84.93
T S R (8
(STAB PIVOT) R ON PA 76.36
F
C

E .S
.

Horizontal Stabilizer Stations

L
WIRING DIAGRAM MANUAL

67.79
+

59.22 +
50.65
CRJ200

42.08
FS863.00
31.99
BL0.00 WL242.00
21.91
10.91 WL235.00 FS886.00
STABILIZER
BL6.00 PIVOT POINT

rsr5500000_001(1).dc, sw/gg, 26/10/00

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BL1

HIN
02.
00

GE
RIB NO.13
ES103.419

CE
NT
RIB NO.12

ER
ES94.52

FS897.42
LIN
ES103.41

E7
RIB NO.11 WL242.28
ES86.26

0%
BL95.49 HINGE NO.3
RIB NO.10
ES77.68

RIB NO.9 ES69.10 FS937.13

RIB NO.8A ES62.02

ES60.52
RIB NO.8 ES59.02
ES60.52
RIB NO.7 WL242.88
ES52.42
BL55.88 HINGE NO.2
RIB NO.6
ES44.72

RIB NO.5 ES36.82

RIB NO.4
ES28.92

RIB NO.3 ES16.52

ES21.02 WL243.50
RIB NO.2
ES16.52 BL15.25 HINGE
AIR RIB NO.1 ES12.02 NO.1
FS903.76
CEN CRAF
.42

TER T BL6.00
97

LIN
E
rsr5500000_002(1).dc, sw/gg, 27/10/00
8

AIRCRAFT
FS

REAR SPAR CENTERLINE

ES0.00
(95%)
FRONT SPAR LAYOUT GEOMETRY − HINGES
(73%) HINGE
CENTERLINE
70%

Elevator Stations
Figure 7

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EFFECTIVITY: **ON A/C ALL
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14. Cross−References Between Wiring Diagrams

A. Cross−references between wiring diagrams are identified by a cross−reference designator placed

next to the affected wire or component. The designator gives the location in the WDM which
shows the termination of the wire, or the referenced part of the component. For example, if the
cross−reference designator WDM 26−11−00 is placed adjacent to a partially drawn wire or
component, this indicates that the referenced part of the wire or component is shown on the
wiring diagram WDM 26−11−00 located in this manual. An optional reference note is added
beside the cross−reference designator when a reference to another chapter/section/subject is
optional.

15. Circuit Function Code

A. A circuit function code is assigned to every wire and component. Table 1 lists the codes
alphabetically with the associated circuit.

CIRCUIT
FUNCTION CIRCUIT
CODES

CA Digital Automatic Flight Control System

CB Alternate Flap Control Lever System

CD Horizontal Stabilizer Control and Monitoring System

CE Flaps Control and Monitoring System

CF Control Surface Position Monitoring System

CG Stall Protection System

CH Auto Pitch Trim and Feel Control System

CJ Aileron Trim Control and Monitoring System

CM Rudder Trim Control and Monitoring System

CN Spoilers Control and Monitoring System

CR Flutter Damper Monitoring System

DB Hydraulic Power Control System

DF Digital Clock System

EA Engine Instrumentation System

Circuit Function Codes Table 1

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CIRCUIT
FUNCTION CIRCUIT
CODES

EC Engine Vibration Monitoring System

EZ Engine Nacelle System

FC Standby Airspeed/Altimeter System

FD Standby Artificial Horizon System

FG Digital Air Data Computer System

FH Electronic Flight Instrument System

FJ Head−Up Guidance System

FK Dual Inertial Reference System

FL JAR Certification

FM Global Postioning System

FP Attitude and Heading Reference System

FS Dual Flight Management System

GA Proximity Sensor System

GB Antiskid Control System

GC Nosewheel Steering (Steer−by−Wire) System

GD Brake Pressure Monitoring System

GE Brake Temperature Monitoring System

GH Parking Brake Control and Monitoring System

HA Anti−Ice System

HB Temperature Control System

HC Windshield Heater Control System

Circuit Function Codes Table 1

CSP A−003 − MASTER

EFFECTIVITY: **ON A/C ALL
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CIRCUIT
FUNCTION CIRCUIT
CODES

HD Air Data Sensors Heater Control System

HF 10th−Stage Bleed Air Control System

HG Air Conditioning Control System

HH Cabin Pressurization Control System

HJ 14th−Stage Bleed Air Control System

HK Avionics Cooling System

HL Class C Baggage Compartment System

KB Engine Ignition System

KD APU Control System

KE Thrust Reversers Control System

KG Engine Start Control System

KH Engine Speed Control System

KJ Engine Lubrication Control System

KL Automatic Performance Reserve

KM Automatic Performance Reserve System (3B1 Engine)

LA Cockpit Fluorescent Lighting System

LB Passenger Compartment Lighting System

LC Maintenance Lights System

LD Cockpit Miscellaneous Lighting System

LE Taxi and Landing Lights System

LF Emergency Lighting System

Circuit Function Codes Table 1

CSP A−003 − MASTER

EFFECTIVITY: **ON A/C ALL
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CIRCUIT
FUNCTION CIRCUIT
CODES

LG Ordinance Signs System

LH Integral Lighting System − Center Instrument Panel and Pedestal

LJ Anticollision Lights System

LK Wing Inspection and Navigation Lights System

LL Integral Lighting System − Overhead Panel

LM Integral Lighting System − Pilots Instrument Panel

LN Integral Lighting System − Copilots Instrument Panel

LP Illuminated Chart Holder System

LQ Fwd Cargo Bay Light System

LS Red Strobe Lights System

LT Boarding, Dome and Galley Lights System

LU Logo Lights System

LV Stair Lights System

LW Service Lights System

LX Cargo Bay Door Flood Light System

LY Emergency Lighting System

LZ Passenger Compartment Lighting System

MA Passenger Services Unit System

MB Door Control and Indication System

MC Windshield Wiper System

MD Passenger Services Unit System

Circuit Function Codes Table 1

CSP A−003 − MASTER

EFFECTIVITY: **ON A/C ALL
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CIRCUIT
FUNCTION CIRCUIT
CODES

ME Galley Interface System

MF Lavatory Interface System

MG Galley and Lavatory Water Services System

MH Lavatory Interface System

MJ Galley and Lavatory Water Services System

PA DC Power and Distribution System

QA Fuel Distribution System

QB Fuel Computer System

QC Cockpit Refuel/Defuel Panel System

QD Third Fuel Tank System

QE Metric Indication System

RA VHF Communication System

RB Third VHF Communication System

RC HF Communication System

RD VHF Navigation System

RE Automatic Direction Finding System

RF Air Traffic Control Transponder System

RG Distance Measuring Equipment System

RH Audio Integrating System

RJ Cockpit Voice Recorder System

RK Boarding Music System

Circuit Function Codes Table 1

CSP A−003 − MASTER

EFFECTIVITY: **ON A/C ALL
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CIRCUIT
FUNCTION CIRCUIT
CODES

RL Radio Altimeter System

RM AFT Intercom System

RN Passenger Address System

RP ACARS

RS Selcal System

RT Emergency Locator Transmitter System

RU Passenger Address System

RV Microwave Landing System

RW Radio Tuning System

RX Second Radio Altimeter System

RY HF Communication System (Dual Installation)

SA Weather Radar System

SB Traffic Collision Avoidance System

SC Weather Radar (Split Scan)

UB Integrated Avionics Processing System

UD Onboard Data Loader System

UL Interior Lighting (C&D Interiors)

UM Lavatory System

WA Engine Indication and Crew Alerting System (2 DCU)

WB Third DCU Harness

WC Engine Fire Detection and Warning System

Circuit Function Codes Table 1

CSP A−003 − MASTER

EFFECTIVITY: **ON A/C ALL
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CIRCUIT
FUNCTION CIRCUIT
CODES

WD Ground Proximity Warning System

WE DOT Certification Authority (2DCU) Config Strap

WF Engine Fire Extinguishing System

WG APU Fire Detection, Warning and Extinguishing System

WH Engine Indication and Crew Alerting System (3 DCU)

WK Bleed Leak Detection and Warning System

WL Main Landing Gear Bay Overheat Detection System

WM Certification Authority 2DCU Config Strapping

WN Ice Detection System

WP Crew Oxygen Monitoring System

WQ Passenger Oxygen Deployment System

WR Flight Data Recorder System

WT 2DCU (Engine Control Panel)

WW Aircraft Configuration Strapping

WY Metric Altimeter System

XA Gen 1 and Gen 2 AC Power Generation and Monitoring System

XB External AC and APU Power Control and Monitoring System

XC AC Emergency Power Generation and Monitoring System

XD AC Electrical Load Distribution System

Circuit Function Codes Table 1

CSP A−003 − MASTER

EFFECTIVITY: **ON A/C ALL
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16. Component Class Prefix

A. A component class prefix is assigned to all electrical and electronic parts and equipment. Refer to
Table 2.

PREFIX CLASS OF COMPONENT

A Assembly (separable)

B Blower, motor, synchro

BT Battery

C Capacitor

CB Circuit breaker

CBP Circuit breaker panel

CP Coupler

CR Semiconductor diode

CS Contactor circuit breaker

DS Light (indicator)

E Antenna

F Fuse

FL Filter

FT Feedthrough

G Generator

HP Shutoff valve

HR Static port

HS Handset

J Connector (receptacle)

JB Junction box

Component Class Prefix Table 2

CSP A−003 − MASTER

EFFECTIVITY: **ON A/C ALL
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PREFIX CLASS OF COMPONENT

K Contactor, relay

KJ Socket relay

L Coil

LS Horn, loudspeaker, bell

M Indicator, meter

MK Microphone

MPE Electromechanical assembly

MT Measuring transducer

N Ground stud

P Connector (plug)

PS Inverter, power supply

R Resistor

RT Thermal resistor

RV Symmetrical varistor

S Switch

SDS Push button (illuminated)

SH Shunt

SJ Socket switch

SP Splice

T Transformer

TB Terminal board

TC Thermocouple

Component Class Prefix Table 2

CSP A−003 − MASTER

EFFECTIVITY: **ON A/C ALL
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PREFIX CLASS OF COMPONENT

V Valve (solenoid)

W Cable assembly, conductor

Component Class Prefix Table 2

17. Color Code

A. Indicator Light

A = Amber

G = Green

R = Red

W = White

B. Cable Code

BLK = Black

BLU = Blue

ORN = Orange

RED = Red

WHT = White

18. Wire Separation “W” Code

A. General

(1) Electro magnetic interference and safety considerations dictate that each wire must be
assigned with a wire separation “W” code. These codes are used to determine the bundle
into which the wire is placed.

B. “W” Code

(Refer to Table 3)

(1) Each wire has a “W” code. If none is applied specifically on the wiring diagram then it is W7
by default note. This note is found on the note page of the wiring diagram.

CSP A−003 − MASTER

EFFECTIVITY: **ON A/C ALL
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(2) The “W” code on one section of the wire applies to the complete wire unless otherwise
stated.

(3) Wires with different “W” codes must not be bundled together unless permitted in the bundle
compatibility table. Refer to the following table for wire separation and compatibility:

MAY BE RUN
CODE DESCRIPTION
LOCALLY WITH

W1A Generator No. 1, power

W1B Generator No. 1, control

W1C Generator No. 2, power

W1D Generator No. 2, control

W1E Generator No. 3, power

W1F Generator No. 3, control

W1G TRU No. 1 and ground services

W1H TRU No. 2

W1J ADG power

W1L Essential Tru No. 1

W1M Essential Tru No. 1

W2 Audio No. 1

W3 Audio No. 2

W4 Flux valve No. 1

W5 Flux valve No. 2

W6 Coaxial cables

W7 General (single system) (dc and low power ac) W8, W9

W8 General (system No. 1) (dc and low power ac) W7

W9 General (system No. 2) (dc and low power ac) W7

Wire Separation “W” Codes Table 3

CSP A−003 − MASTER

EFFECTIVITY: **ON A/C ALL
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MAY BE RUN
CODE DESCRIPTION
LOCALLY WITH

W11 AC distribution No. 1, ac power > 3 amperes

W12 AC distribution No. 2, ac power > 3 amperes

W14 Sensitive circuits No. 1 (critical

volts/amperes/frequency)

W15 Sensitive circuits No. 2 (critical

volts/amperes/frequency)

W16 Windshield No. 1, power

W17 Windshield No. 2, power

W18 Data bus No. 1 (ARINC 429)

W19 Data bus No. 2 (ARINC 429)

W20 DC distribution No. 1 dc power > 3 amperes

W21 DC distribution No. 2 dc power > 3 amperes

W22 HGS interconnect

W23 No.1 sensors inputs to HGS

W24 No.2 sensors inputs to HGS

Wire Separation “W” Codes Table 3

19. Wire Identification

A. The example that follows shows the wire identification system used in this manual:

Wire identification 2XD1K10AWHTN

2 System number

XD Circuit function code (refer to Table 1)

1 Wire number

K Letter segment

CSP A−003 − MASTER

EFFECTIVITY: **ON A/C ALL
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10 Wire guage (0,8,10,12,14,16,18,20,22)

A Phase (A,B,C)

WHT Color (WHT,BLU,ORN)

N Ground (N)

NOTE: The Ground, Color, Phase and System number (wire identification elements) are used
if required.

20. Component Identification

A. The example that follows shows the component identification system used in this manual:

Component identification 2A3CA

2 System number

A Component class prefix (refer to Table 2)

3 Component number

CA Circuit function code (refer to Table 1)

NOTE: The System number (component identification element) is used if required.

21. Terminal Block (TB)

A. Terminal blocks are secured onto a module rail which may consist of one or several positions to
accommodate terminal blocks. Numerical designators are assigned on the module rail to every
position.

Terminal Block identification TB43−10E

TB43 Module rail designator

10 Module location on rail

E Pin location on module

CSP A−003 − MASTER

EFFECTIVITY: **ON A/C ALL
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22. Diode Terminal Module

A. For some applications, diodes have been included within terminal blocks. These terminal blocks
are environmentally−sealed devices which have a diode installed between two terminals. A
schematic diagram, representing the internal components interconnection, is shown on the side
of the module.

Diode Terminal Module TB149−3E

TB149 Module rail designator

3 Module location on rail

E Pin location on module

23. Electrical and Electronic Symbols

A. The graphic symbols used in this manual are shown in Figure 8.

CSP A−003 − MASTER

EFFECTIVITY: **ON A/C ALL
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SWITCH ENERGIZING COIL FOR

VALVE/RELAY
SWITCH MOMENTARY

LIMIT SWITCH SOLENOID OPERATED

VALVE
TWO−POLE SWITCH

TWO−POLE SWITCH
(MOMENTARY)
RELAY
TWO−POSITION SWITCH

TWO−POSITION
SWITCH (MOMENTATY)

THREE−POSITION SWITCH
RELAY WITH
THREE−POSITION SWITCH TIME DELAY
(MOMENTARY) TD=5SEC

THREE−POSITION SWITCH
(MOMENTARY)
MOTOR

MULTIPOSITION SWITCH

PUSHBUTTON
SWITCH
POSITION TRANSDUCER

CONTACTS

RESISTOR
TEMPERATURE
ACTUATED SWITCH

PRESSURE VARIABLE
ACTUATED SWITCH RESISTOR
rwm0000000 001.dg, pb, 02/01/94

DIODE
THERMISTOR
ZENER DIODE

THERMISTOR
ZENER DIODE SYMMETRIC NONLINEAR t

Electrical and Electronic Symbols

Figure 8 (Sheet 1 of 3)

CSP A−003 − MASTER

EFFECTIVITY: **ON A/C ALL
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THERMAL OVERLOAD CIRCUIT BREAKER

DEVICE

HEATER ELEMENT CIRCUIT BREAKER

THREE−PHASE

TRANSFORMER
WIRE WITH
FB3A22
IDENTIFICATION
INDUCTANCE
COAXIAL CABLE
VARIABLE INDUCTANCE
STOWED WIRE

THERMOCOUPLE SHIELDED WIRE

SQUIB DOUBLE TWISTED AND

SHIELDED CONDUCTOR

CAPACITOR DOUBLE TWISTED

CONDUCTOR

TEMPERATURE
SENSING TRIAX SHIELDED
ELEMENT/WIRE FIRE CONDUCTOR

INCADESCENT LAMP WIRE GROUP

A= AMBER SP1 SP2

B= BLUE
INDICATOR LIGHT A G= GREEN SPLICE
R= RED CRIMP TYPE SOLDER TYPE
Y= YELLOW

GROUND STUD
FLUORESCENT LIGHT

GROUND CONNECTION
INTEGRAL LIGHTING
CONNECTOR
CHASSIS OR
FRAME GROUND
rwm0000000 002.dg, pb, 07/01/94

BUS BAR CURCUIT BREAKER TB205 TB209

1 1

0A STUD 2 2
BUS BAR WITH TERMINAL BLOC
THREE−PHASE 0B (PARTIAL ASSEMBLY) 3 3
CIRCUIT BREAKER
0C
WITH BUS

Electrical and Electronic Symbols

Figure 8 (Sheet 2 of 3)

CSP A−003 − MASTER

EFFECTIVITY: **ON A/C ALL
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TB145 TB148 J1 P1
TERMINAL BLOC A 12 B A 15 B
CONNECTOR A
MODULE C 12 D C 15 D
WITH BACKSHELL CONNECTION B
E 12 F E 15 F
PARTIAL ASSEMBLY (PARTIAL ASSEMBLY) C
D
WITH BUS
TB149−3
J D
DIODE MODULE CR8 A1
P1
(PARTIAL ASSEMBLY) E K
A
CR5 EQUIPMENT CONNECTION
B
(PLUG IS PART
C
OF EQUIPMENT)
D
A B
GROUND STUD C D
MODULE E F

(PARTIAL ASSEMBLY)
COAX CONNECTOR

FT202−D
COAX CONNECTOR
FEEDTHROUGH WITH BULKHEAD
ADAPTER

J1 P1
ANTENNA (GENERAL)
A
CONNECTOR B
(COMPLETE ASSEMBLY) C
D
SPEAKER

J1 P1
A
CONNECTOR
B
(PARTIAL ASSEMBLY) PHONE JACK
C
D

rwm0000000 003.dg, pb/pr, mar03/2009

Electrical and Electronic Symbols

Figure 8 (Sheet 3 of 3)

CSP A−003 − MASTER

EFFECTIVITY: **ON A/C ALL
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