Commercial 

Airplanes 777

Service Bulletin

Number: 777-24-0074

Original Issue: June 27, 2002

Revision 4: September 13, 2012

ATA System: 2400

SUBJECT: ELECTRICAL POWER - General - Install the Passenger Compartment Electrical Power

Isolation Switches (Partial)

Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15

CFR 300-774). An export license may be required before it is used for development, production or use by foreign

persons from specific countries. The controller of this data has the individual responsibility to abide by all export

laws.

ECCN: 9E991

BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET

Copyright © 2002 Boeing.

Unpublished Work. All Rights Reserved.

Treatment of this document and its content is governed by contract with Boeing. Rights to use this document

are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The

Boeing Company.

Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, DreamlinerTM,

BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and Boeing

liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in connection

with this document unless provided in writing by Boeing. BOEING is a trademark of Boeing Management

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2.0
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BOEING SERVICE BULLETIN 777-24-0074

BLANK PAGE
Table of Contents

Revision Transmittal Sheet ............................................ 5

Summary ...................................................... 7

1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 18

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . . . 21

3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 22

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

FIGURE 1: FLIGHT COMPARTMENT - INSTALL NEW WIRES [Group 1, Configuration 1] . . . . . . 26

FIGURE 2: FLIGHT COMPARTMENT - CHANGE THE AIRPLANE WIRING [Group 1, Configuration 1] . 28

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BOEING SERVICE BULLETIN 777-24-0074

BLANK PAGE
Commercial 

Airplanes 777

Service Bulletin

Revision Transmittal Sheet Number: 777-24-0074

Original Issue: June 27, 2002

Revision 4: September 13, 2012

ATA System: 2400

SUBJECT: ELECTRICAL POWER - General - Install the Passenger Compartment Electrical Power

Isolation Switches (Partial)

This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

No more work is necessary on the airplanes changed in accordance with Revision 3 of this service bulletin.

REASON FOR REVISION

This revision is sent to give more data to change an Electrical Power Control Panel, part number 233W3202-8

to the new part number 233W3202-22, and an Electrical Power Control Panel, part number 233W3202-9 to the

new part number 233W3202-18.

These sections were changed:

1. In Paragraph 1.A., Effectivity, removed Group 1, Configuration 3 and Group 1, Configuration 4.

2. In Summary, Background, Summary Manpower, Paragraph 1.C., Reason, Paragraph 1.G., Manpower

and Paragraph 1.J.1., Existing Data, added BAE Systems SB 233W3202-24-03 reference.

3. In Paragraph 1.K., Publications Affected, changed the publications data.

4. In Paragraph 2.C.2., Parts and Materials Supplied by the Operator, added a table.

5. In Paragraph 2.C.3., Parts Modified and Reidentified, parts table, changed the notes.

6. In Paragraph 3.B., Work Instructions, step 4, changed the notes.

Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location

of important changes.

Pages with no vertical lines have no important changes.

REVISION HISTORY

Original Issue: June 27, 2002

Revision 1: October 05, 2006

Revision 2: May 20, 2010

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Revision 3: February 20, 2012

Revision 4: September 13, 2012

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BOEING SERVICE BULLETIN 777-24-0074
Commercial 

Airplanes 777

Service Bulletin

Summary Number: 777-24-0074

Original Issue: June 27, 2002

Revision 4: September 13, 2012

ATA System: 2400

SUBJECT: ELECTRICAL POWER - General - Install the Passenger Compartment Electrical Power

Isolation Switches (Partial)

CONCURRENT REQUIREMENTS

Refer to Paragraph 1.B., Concurrent Requirements.

BACKGROUND

The change described in this service bulletin will provide new switches on the flight deck that can remove power

from the cabin systems if smoke or flames occur. Smoke and flames in the passenger cabin can cause injury

to the passenger and damage the safety critical cabin equipments.

We have received numerous reports of smoke or flames in the passenger cabin related to the wiring for the

passenger cabin in-flight entertainment system, cabin lighting and passenger seats. It is not easy to remove the

electrical power to these systems to stop the smoke or flames.

Two switches can be installed to remove power from some of the passenger cabin electrical systems. When

selected OFF, the IFE/PASS SEATS switch will remove power from the systems connected to the following

circuit breakers (if installed):

Circuit Breaker Panel and Position Nomenclature

C21332 P110, B021 IFE COOLING FAN

C23355 P110, D021 VOD

C23356 P210, A005 IFE ZIA 1

C23357 P110, A024 IFE ZIA 2

C23358 P110, A027 IFE ZIA 3

C23359 P210, B002 IFE ZIA 4

C23403 P210, E005 VIDEO PGMS & CTRL

C23405 P210, C013 CABIN PRINTER

C23471 P210, E008 VIDEO PGMS & CTRL B

When selected OFF, the CABIN/UTILITY switch will remove power from all galleys, the left and right utility buses,

and systems connected to the following circuit breakers (if installed):

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Circuit Breaker Panel and Position Nomenclature

C21308 P210, A010 BULK CGO VENT FAN

C21330 P110, F023 FWD CGO EXHAUST FAN

C33486 P210, E009 RED ANTI-COLL LTS

Boeing Service Related Problem (SRP) 777-SRP-24-0091 is related to this service bulletin.

BAE Systems SB 233W3202-24-03 Original Issue and BAE Systems SB 233W3202-24-04 Revision 2 are related

to this service bulletin.

ACTION (PRR 61887)

Group 1, Configuration 1:

Remove the Electrical Power Control Panel. Change the airplane wiring to install 8 new wires and remove 2

wires between the P5 panel and the P61 overhead panel card file. Install a new Electrical Power Control Panel

with the two new cabin power control switches. Do a test of the new cabin power switches.

Group 1, Configuration 2:

More work is necessary. In the flight compartment, get access to the electrical power control panel. Do an

inspection on the electrical power control panel for the part number. If the electrical power control panel has the

part number 233W3202-18, and does have lockwire provisions on the switch guards at switches S6 and S10,

then change the part number to 233W3202-19. If the electrical power control panel has the part number

233W3202-19, and does not have lockwire provisions on the switch guards at switches S6 and S10, then change

the part number to 233W3202-18.

EFFECTIVITY

777-200, 777-300 Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.

COMPLIANCE

Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2010-NM-022-AD, is related to

this service bulletin.

Boeing recommends that this service bulletin to be done within 60 months after the effective date of an applicable

Airworthiness Directive.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the configuration changes given in this service bulletin.

MANPOWER

Group 1, Configuration 1:

Airplanes Total Task Hours Elapsed Hours

777-200, 777-300 5.0 5.0

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BOEING SERVICE BULLETIN 777-24-0074
Group 1, Configuration 1:

The time to make the change to the electrical power control panel in accordance with the Boeing SB 777-31-0038

or BAE Systems SB 233W3202-24-03 Original Issue, and/or BAE Systems SB 233W3202-24-04 Revision 2 is

not included.

Group 1, Configuration 1:

This estimate does not include the task hour data given in the service bulletins in Paragraph 1.B., Concurrent

Requirements.

Group 1, Configuration 2:

Airplanes Total Task Hours Elapsed Hours

More Work 1.00 1.00

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

Refer to Paragraph 2.A., Material - Price and Availability.

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BOEING SERVICE BULLETIN 777-24-0074
Commercial 

Airplanes 777

Service Bulletin

Number: 777-24-0074

Original Issue: June 27, 2002

Revision 4: September 13, 2012

ATA System: 2400

SUBJECT: ELECTRICAL POWER - General - Install the Passenger Compartment Electrical Power

Isolation Switches (Partial)

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

Refer to Service Bulletin Index D624W001 Part 3 for Airplane Variable Number, Line Number, and

Serial Number data.

This service bulletin is for the airplanes shown below. An equivalent change is on subsequent

production airplanes. Refer to PRR 61887 for data about this change.

GROUP CONFIGURATION DESCRIPTION

1 - 777-200/-300 airplanes that require flight deck switch installation.

777-200/-300 airplanes that have not accomplished BAE Systems

service bulletin 233W3202-24-04 Original Issue or Revision 1.

1

777-200/-300 airplanes that have accomplished BAE Systems service

bulletin 233W3202-24-04 Original Issue or Revision 1.

2

Airplane Models:

777-200, 777-300

Variable Number Group

WA001 1

WA101 - WA104 1

WA210 - WA212 1

WA221 - WA223 1

WA231 - WA232 1

WA241 - WA250 1

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Variable Number Group

WB016 - WB021 1

WB031 - WB044 1

WB105 - WB106 1

WB133 - WB135 1

WB151 - WB153 1

WB161 - WB173 1

WB181 - WB188 1

WB231 - WB239 1

WB271 - WB272 1

WB276 - WB286 1

WB291 - WB301 1

WB306 - WB307 1

WB311 - WB327 1

WB336 - WB337 1

WB366 - WB367 1

WB371 - WB386 1

WB406 1

WB411 - WB413 1

WB416 - WB433 1

WB446 - WB452 1

WB476 1

WB481 - WB484 1

WB501 - WB507 1

WB531 - WB535 1

WB551 - WB554 1

WB591 - WB595 1

WB601 - WB606 1

WB611 - WB615 1

WB631 - WB632 1

WB636 - WB637 1

WC051 - WC067 1

WC101 - WC103 1

WC111 1

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BOEING SERVICE BULLETIN 777-24-0074
2. Spares Affected

Examine your spares supply for the parts or components identified in Paragraph 2.C., Parts

Necessary for Each Airplane. If any parts or components are found, refer to Paragraph 2.C. for

the recommended use.

B. Concurrent Requirements

The service bulletins listed below must be done before or at the same time as this service bulletin:

Group 1, Configuration 1:

Applicable for all airplanes except WB181-WB188, WB231-WB239, WB611-WB615.

Company Service Bulletin Description

Changes the ELMS OPS and OPC software to

change the oxygen mask inhibit to a fail-toground logic. (a)

Boeing 777-24-0070 Original Issue.

Changes the ELMS OPS and OPC software to

decrease the number of ELMS P110 Panel,

ELMS P210 Panel and ELMS P310 Panel EICAS

status messages. (a)

777-24-0087 Original Issue

thru Revision 2.

Boeing

Changes the ELMS OPS and OPC software to

help make sure that the risk of an ignition source

in the fuel tank is kept to a minimum. (a)

777-28A0039 Original Issue

thru Revision 2.

Boeing

(a) Boeing Service Bulletin 777-24-0070 or 777-24-0087 or 777-28A0039 must be done before

or at the same time as this service bulletin 777-24-0074.

Group 1, Configuration 1:

Applicable only for airplanes WB181-WB188, WB231-WB239, WB611-WB615.

Company Service Bulletin Description

Changes the ELMS OPS and OPC software to

change the oxygen mask inhibit to a fail-toground logic. (a)

Boeing 777-24-0079 Original Issue.

Changes the ELMS OPS and OPC software to

decrease the number of ELMS P110 Panel,

ELMS P210 Panel and ELMS P310 Panel EICAS

status messages. (a)

777-24-0087 Original Issue

thru Revision 2.

Boeing

Changes the ELMS OPS and OPC software to

help make sure that the risk of an ignition source

in the fuel tank is kept to a minimum. (a)

777-28A0039 Original Issue

thru Revision 2.

Boeing

(a) Boeing Service Bulletin 777-24-0079 or 777-24-0087 or 777-28A0039 must be done before

or at the same time as this service bulletin 777-24-0074.

Group 1, Configuration 2:

None.

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BOEING SERVICE BULLETIN 777-24-0074
C. Reason

The change described in this service bulletin will provide new switches on the flight deck that can

remove power from the cabin systems if smoke or flames occur. Smoke and flames in the passenger

cabin can cause injury to the passenger and damage the safety critical cabin equipments.

We have received numerous reports of smoke or flames in the passenger cabin related to the wiring

for the passenger cabin in-flight entertainment system, cabin lighting and passenger seats. It is not

easy to remove the electrical power to these systems to stop the smoke or flames.

Two switches can be installed to remove power from some of the passenger cabin electrical systems.

When selected OFF, the IFE/PASS SEATS switch will remove power from the systems connected to

the following circuit breakers (if installed):

Circuit Breaker Panel and Position Nomenclature

C21332 P110, B021 IFE COOLING FAN

C23355 P110, D021 VOD

C23356 P210, A005 IFE ZIA 1

C23357 P110, A024 IFE ZIA 2

C23358 P110, A027 IFE ZIA 3

C23359 P210, B002 IFE ZIA 4

C23403 P210, E005 VIDEO PGMS & CTRL

C23405 P210, C013 CABIN PRINTER

C23471 P210, E008 VIDEO PGMS & CTRL B

When selected OFF, the CABIN/UTILITY switch will remove power from all galleys, the left and right

utility buses, and systems connected to the following circuit breakers (if installed):

Circuit Breaker Panel and Position Nomenclature

C21308 P210, A010 BULK CGO VENT FAN

C21330 P110, F023 FWD CGO EXHAUST FAN

C33486 P210, E009 RED ANTI-COLL LTS

Boeing Service Related Problem (SRP) 777-SRP-24-0091 is related to this service bulletin.

BAE Systems SB 233W3202-24-03 Original Issue and BAE Systems SB 233W3202-24-04 Revision

2 are related to this service bulletin.

Revision 1 was sent to add airplanes WB406 and WB476 to Group 1 of this service bulletin effectivity.

Revision 2 was sent to add Boeing Service Bulletins to the Concurrent Requirements. Electrical Load

Management System (ELMS) software changes are necessary for the changes in accordance with this

service bulletin to operate.

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BOEING SERVICE BULLETIN 777-24-0074
Revision 3 was sent to allow an Electrical Power Control Panel 233W3202-8, to be changed to a

233W3202-22 and 233W3202-9, to be changed to a 233W3202-18.

Revision 4 is sent to give more data to change an Electrical Power Control Panel, part number

233W3202-8 to the new part number 233W3202-22, and an Electrical Power Control Panel, part number

233W3202-9 to the new part number 233W3202-18.

D. Description

Group 1, Configuration 1:

Remove the electrical system control panel. Change the airplane wiring to install 8 new wires and

remove 2 wires between the P5 panel and the P61 overhead panel card file. Install a new electrical

system control panel with the two new cabin power control switches. Do a test of the new cabin power

switches.

Group 1, Configuration 2:

More work is necessary. In the flight compartment, get access to the electrical power control panel.

Do an inspection on the electrical power control panel for the part number. If the electrical power control

panel has the part number 233W3202-18, and does have lockwire provisions on the switch guards at

switches S6 and S10, then change the part number to 233W3202-19. If the electrical power control

panel has the part number 233W3202-19, and does not have lockwire provisions on the switch guards

at switches S6 and S10, then change the part number to 233W3202-18.

Revision 1 - No more work is necessary on airplanes changed as shown in the Original Issue of this

service bulletin.

Revision 2 - No more work is necessary on airplanes changed in accordance with the Original Issue

or Revision 1 of this service bulletin.

Revision 3 - More work is necessary on the airplanes changed in accordance with BAE Systems Service

Bulletin 233W3202-24-04 Original Issue or Revision 1. The Electrical Power Control Panels

233W3202-12 and 233W3202-13 were incorrectly identified. The correct part number for the changed

233W3202-12 panel is 233W3202-18, and for the changed 233W3202-13 panel is 233W3202-19 then

check lockwire provision on the S6 and S10 switch guards and the marked part number, to decide if

the part number needs changing.

Revision 4 - No more work is necessary on the airplanes changed in accordance with Revision 3 of

this service bulletin.

The work in this service bulletin is done in the maintenance zone(s) given below.

Affected Maintenance Zones

Model Zone

777-200, 777-300 211, 212

E. Compliance

Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2010-NM-022-AD, is

related to this service bulletin.

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BOEING SERVICE BULLETIN 777-24-0074
Boeing recommends that this service bulletin to be done within 60 months after the effective date of

an applicable Airworthiness Directive.

F. Approval

This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified

in this service bulletin comply with the applicable regulations and are FAA approved, as well as European

Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved

airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on

the airplane in its original Boeing delivery configuration or as modified by other approved Boeing

changes.

If an airplane has a non-Boeing modification or repair that affects a component or system also affected

by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval

before incorporating this service bulletin.

G. Manpower

The table below shows an estimate of the task-hours necessary to do this change for each airplane.

This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator

task-hour data if necessary. The estimate does not include lost time. These are some examples of lost

time:

— Time to adjust to the workplace

— Time to schedule the work

— Time to examine the work

— Time to cure the materials

— Time to make the parts

— Time to find the tools

Group 1, Configuration 1:

Task Number of Persons Task-Hours Elapsed Hours

Open Access 1 0.25 0.25

Change 1 4.00 4.00

Close Access 1 0.25 0.25

Test 1 0.50 0.50

TOTAL FOR EACH AIRPLANE 5.00 5.00

Group 1, Configuration 1:

The time to make the change to the electrical power control panel in accordance with the Boeing SB

777-31-0038 or BAE Systems SB 233W3202-24-03 Original Issue, and/or BAE Systems SB

233W3202-24-04 Revision 2 is not included.

Group 1, Configuration 1:

This estimate does not include the task hour data given in the service bulletins in Paragraph 1.B.,

Concurrent Requirements.

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BOEING SERVICE BULLETIN 777-24-0074
Group 1, Configuration 2:

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 0.25 0.25

Inspect 1 0.25 0.25

Change 1 0.25 0.25

Close Access 1 0.25 0.25

TOTAL FOR EACH AIRPLANE 1.00 1.00

H. Weight and Balance Changes

Group 1, Configuration 1:

Change in Moment

(Pound-Inches)

Change in Weight

(Pounds)

Airplane

777-200 +0.1 +26.8

777-300 +0.1 -2.1

Group 1, Configuration 2:

None.

I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. Engineering Change Memo PRR 61887

b. Boeing Service Bulletin 777-24-0070, 777-24-0079, 777-24-0087, 777-28A0039, 777-31-0038

c. Boeing Service Related Problem (SRP) 777-SRP-24-0091

d. Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM)

2010-NM-022-AD

e. Service Bulletin Index D624W001

f. Standard Overhaul Practices Manual (SOPM) 20-50-10

g. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19, 20-61-11, 20-74-11,

20-90-15

h. 777 Aircraft Maintenance Manual (AMM) 24-22-00, 24-22-01, 33-13-00, 33-16-00

i. 777 Wiring Diagram Manual (WDM) 23-93-21, 24-51-24, 25-51-41

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BOEING SERVICE BULLETIN 777-24-0074
j. BAE Systems Service Bulletin 233W3202-24-03, 233W3202-24-04

NOTE: These Service Bulletins were previously issued by Boeing.

2. Data Supplied with this Service Bulletin:

None.

3. Installation Drawings Used in the Preparation of this Service Bulletin:

Drawing Number Title

288W9005 Wire Bundle Installation, Overhead Panels, P11, P5, P61

This drawing was used to prepare this service bulletin. This drawing is not necessary to make the

specified changes, and is not supplied with this service bulletin. This drawing may not be applicable

to all airplane configurations or operators.

K. Publications Affected

1. Publications:

Publication Chapter-Section

777 Operations Manual 6.10, 6.20, 6.30, NNC.6

777 Aircraft Maintenance Manual 24-00, 24-40, 33-20, 33-27

777 Wiring Diagram Manual 23-93, 24-51

24-21, 24-22, 24-25, 24-31, 24-41, 31-10, 31-12,

33-13, 49-42

777 Illustrated Parts Catalog

777 Schematic Diagram Manual 23-93, 24-51

2. Damage Tolerance Based Structural Inspections:

Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue

Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the

Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary.

L. Interchangeability and Intermixability of Parts

Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for interchangeability and intermixability

information.

M. Software Accomplishment Summary

Not Affected.

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BOEING SERVICE BULLETIN 777-24-0074
2. MATERIAL INFORMATION

A. Material - Price and Availability

Boeing can supply the kit shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators are

encouraged to share schedule requirements with Boeing for incorporation of the service bulletin. The

kit are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.

Prices are in United States Dollars. Terms: Net 30 days.

Reference this service bulletin and submit your purchase order by one of these methods:

1. Order on-line via ATA Spec 2000 or The Boeing PART Page

2. Fax to (206) 662-7145

Group 1, Configuration 1:

REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER

AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION

Unit Price as of

the original issue

date of this Service Bulletin (US

Dollars)

ROLT as of the

original issue

date of this Service Bulletin (Calendar Days)

Kit Number Name Date QTY

005W3198-1 Top Kit - 1 149 751.00

Group 1, Configuration 2:

None.

B. Industry Support Information

Boeing warranty remedies are not available for the configuration changes given in this service bulletin.

C. Parts Necessary for Each Airplane

1. Kits/Parts:

Group 1, Configuration 1:

To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.

NOTE: Group 1, Configuration 1:

One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by

the Operator, are necessary for each airplane.

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Group 1, Configuration 1:

Kit 005W3198

Existing Part Notes

Number

New Part Number QTY Name

-1

005W3198-1 - Top Kit (a)

280W5111-1 1 Wire Kit (a)

BACS38K1B 20 Strap

BACS38K2B 10 Strap

(a) There are more parts than are necessary.

Group 1, Configuration 1:

Kit 280W5111

Existing Part Notes

Number

New Part Number QTY Name

-1 -101 -201

280W5111-1 - Wire Kit

280W5111-101 1 - - Kit, W1052

280W5111-101W - 1 - Wire

280W5111-10101 - 1 - Tie Wrap

280W5111-10102 - 1 - Identification Tape

280W5111-10103 - 1 - Identification Tape

280W5111-201 1 - - Kit, Standard (a)

BACC47CP1S - 8 2 Contact, Socket

CTA0165 (CTA- - 6 1 Contact, Socket (b)

0165)

S280W555-920 - 2 1 Contact, Pin

318-01-99-036 - 6 1 Contact, Socket (b)

(a) There are more parts than are necessary.

(b) Contact 318-01-99-036 optional to CTA0165.

Group 1, Configuration 2:

None.

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2. Parts and Materials Supplied by the Operator:

Group 1, Configuration 1:

Part Number / Specifica- QTY Name Existing Part Number Notes

tion

233W3202-19 (a) 1 Electrical Power Control Panel 233W3202-6 (c) (d)

233W3202-18 (a) 1 Electrical Power Control Panel 233W3202-7 (c) (d)

233W3202-22 (b) 1 Electrical Power Control Panel 233W3202-8 (c) (e)

233W3202-18 (a) 1 Electrical Power Control Panel 233W3202-9 (c) (f)

(a) This part is used in production.

(b) This part is not used in production.

(c) You cannot use the existing part to replace the new or changed part.

(d) The existing part number can be changed to the new part number in accordance with BAE Systems SB

233W3202-24-04 Revision 2.

(e) The existing part number can be changed to the new part number in two steps. The part number

233W3202-8 can be changed to part number 233W3202-11 in accordance with Boeing SB 777-31-0038

or BAE Systems SB 233W3202-24-03 Original Issue, and then to the new part number in accordance

with BAE Systems SB 233W3202-24-04 Revision 2.

(f) The existing part number can be changed to the new part number in two steps. The part number

233W3202-9 can be changed to part number 233W3202-12 in accordance with Boeing SB 777-31-0038

or BAE Systems SB 233W3202-24-03 Original Issue, and then to the new part number in accordance

with BAE Systems SB 233W3202-24-04 Revision 2.

Group 1, Configuration 2:

None.

3. Parts Modified and Reidentified:

The parts shown below are changed as shown in this service bulletin. The quantity (QTY) is the

number of parts changed on each airplane.

Group 1, Configuration 1:

Existing Part Number QTY Name New Number Notes

233W3202-6 1 Electrical Power Control Panel 233W3202-19 (a)

233W3202-7 1 Electrical Power Control Panel 233W3202-18 (a)

233W3202-8 1 Electrical Power Control Panel 233W3202-22 (b)

233W3202-9 1 Electrical Power Control Panel 233W3202-18 (c)

(a) Make the change in accordance with BAE Systems SB 233W3202-24-04 Revision 2.

(b) Make the change in two steps. The part number 233W3202-8 is changed to part number 233W3202-11

in accordance with Boeing SB 777-31-0038 or BAE Systems SB 233W3202-24-03 Original Issue, and

then to the new part number in accordance with BAE Systems SB 233W3202-24-04 Revision 2.

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Group 1, Configuration 1:

Existing Part Number QTY Name New Number Notes

(c) Make the change in two steps. The part number 233W3202-9 is changed to part number 233W3202-12

in accordance with Boeing SB 777-31-0038 or BAE Systems SB 233W3202-24-03 Original Issue, and

then to the new part number in accordance with BAE Systems SB 233W3202-24-04 Revision 2.

Group 1, Configuration 2:

None.

4. Parts Removed and Not Replaced:

None.

D. Parts Necessary to Change Spares

None.

E. Special Tooling - Price and Availability

None.

F. Special Tooling Necessary to do this Service Bulletin

No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance

and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine

operator tool supply to make sure all necessary tools are available.

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BOEING SERVICE BULLETIN 777-24-0074
3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL

PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,

METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE

DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR

OTHER ELECTRICAL DAMAGE.

NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for

definition of the acronyms.

2. Obey all of the warnings and cautions given in the specified manual sections.

3. Unless shown differently, these dimensions and tolerances are used:

— Linear dimensions are in inches.

— Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus

or minus 0.03 inch.

— Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch.

— Angular tolerance is plus or minus 2 degrees.

— Hole dimensions for standard solid rivets are given in 777 Structural Repair

Manual, Chapter 51.

— Torque limits to tighten nuts and bolts are given in 777 Structural Repair Manual,

Chapter 51.

4. For approved fastener and process material substitutions, refer to 777 Structural

Repair Manual, Chapter 51, Alternate fasteners are given in 777 Structural Repair

Manual Chapter 51 and Boeing Drawing 012W6100.

5. If the length of fasteners specified in this service bulletin do not meet the installation

standards, fasteners of the same specification, or an approved substitute, one grip

length longer or shorter may be used.

6. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures,

and SWPM 20-10-19 for the wire separation requirements, as accepted procedures.

7. These work instructions refer to procedures included in other Boeing documents.

When the words "refer to" are used and the operator has an accepted alternative

procedure, the accepted alternative procedure can be used. When the words "in

accordance with" are included in the instruction, the procedure in the Boeing document

must be used.

8. This service bulletin includes functional test procedures for the systems changed by

this service bulletin. More functional tests can possibly be necessary in accordance

with standard maintenance practices because of interruption to other airplane systems.

9. If it is necessary to remove more parts for access, you can remove those parts. If

you can get access without removing identified parts, it is not necessary to remove

all of the identified parts. Jacking and shoring limitations must be observed.

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BOEING SERVICE BULLETIN 777-24-0074
B. WORK INSTRUCTIONS

Group 1, Configuration 1:

1. Remove the electrical power from the airplane. Refer to 777 AMM 24-22-00, Remove Electrical

Power as an accepted procedure.

2. Get access to the flight compartment and remove the Electrical Power Control Panel. Refer to 777

AMM 24-22-01, Electrical Module Assembly Removal as an accepted procedure.

3. Make a change to the airplane wiring in accordance with FIGURE 1 and FIGURE 2.

4. Install a new Electrical Power Control Panel 233W3202-18, 233W3202-19 or 233W3202-22. Refer

to 777 AMM 24-22-01, Electrical Module Assembly Installation as an accepted procedure.

NOTE: The removed electrical power control panel, part number 233W3202-6 or 233W3202-7

can be changed to the new part number in accordance with BAE Systems SB

233W3202-24-04 Revision 2.

NOTE: The removed electrical power control panel, part number 233W3202-8 can be changed

to the new part number in two steps. The part number 233W3202-8 can be changed to

part number 233W3202-11 in accordance with Boeing SB 777-31-0038 or BAE Systems

SB 233W3202-24-03 Original Issue, and then to the new part number in accordance with

BAE Systems SB 233W3202-24-04 Revision 2.

NOTE: The removed electrical power control panel, part number 233W3202-9 can be changed

to the new part number in two steps. The part number 233W3202-9 can be changed to

part number 233W3202-12 in accordance with Boeing SB 777-31-0038 or BAE Systems

SB 233W3202-24-03 Original Issue, and then to the new part number in accordance with

BAE Systems SB 233W3202-24-04 Revision 2.

5. Do the Master Dim and Test - Operational Test, and the Integral Panel Lights - Operational Test

for the Electrical Power Control Panel. Refer to 777 AMM 33-16-00, Master Dim and Test -

Operational Test, and 777 AMM 33-13-00 Integral Panel Lights - Operational Test as accepted

procedures.

6. Do this test of the new cabin power switches:

a. Select the IFE/PASS SEATS switch to OFF.

b. See that the bottom part of the switch is lit.

c. See that all video entertainment players and audio entertainment players are off.

d. See that all video monitors and projectors are off.

e. Select the IFE/PASS SEATS switch to ON.

f. See that the top part of the switch is lit.

g. Select the CABIN/UTILITY switch to OFF.

h. See that the bottom part of the switch is lit.

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BOEING SERVICE BULLETIN 777-24-0074
i. On the EICAS, select the Electrical Maintenance page 2/2. See that the UTIL L/R bus is not

powered.

j. See that no electrical power is available in any of the galleys.

k. Select the CABIN/UTILITY switch to ON.

l. See that the top part of the switch is lit.

m. On the EICAS, select the Electrical Maintenance page 2/2. See that the UTIL L/R bus is ON.

NOTE: Depending on the load shed configuration, it can take up to two minutes for the utility

bus to come on line.

n. See that electrical power is available in all of the galleys.

7. Put the airplane back to a serviceable condition.

Group 1, Configuration 2:

CONDITION: MORE WORK IS NECESSARY - ELECTRICAL POWER CONTROL PANEL

INSPECTION

1. In the flight compartment, get access to the Electrical Power Control Panel. Refer to 777 AMM

24-22-01 as an accepted procedure.

2. Do an inspection on the Electrical Power Control Panel for the part number.

3. If the Electrical Power Control Panel does not have the part number 233W3202-18 or 233W3202-19,

then no change is necessary.

4. If the Electrical Power Control Panel has the part number 233W3202-18, and does not have

lockwire provision on the switch guards at switches S6 and S10, then no change is necessary.

5. If the Electrical Power Control Panel has the part number 233W3202-18, and does have lockwire

provision on the switch guards at switches S6 and S10, then change the part number to

233W3202-19. Refer to SOPM 20-50-10 as an accepted procedure.

6. If the electrical power control panel has the part number 233W3202-19, and does have lockwire

provision on the switch guards at switches S6 and S10, then no change is necessary.

7. If the electrical power control panel has the part number 233W3202-19, and does not have lockwire

provision on the switch guards at switches S6 and S10, then change the part number to

233W3202-18. Refer to SOPM 20-50-10 as an accepted procedure.

8. Put back the Electrical Power Control Panel. Refer to 777 AMM 24-22-01 as an accepted procedure.

9. Put the airplane back to a serviceable condition.

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BOEING SERVICE BULLETIN 777-24-0074
This Figure applies only to: Group 1, Configuration 1.

FIGURE 1: FLIGHT COMPARTMENT - INSTALL NEW WIRES

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 777-24-0074
The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME PART NUMBER QTY NOTES

Use the straps as necessary. Wire bundle

W1052 has a separation color of brown and

a separation category of RM2. Refer to

SWPM 20-10-19 as an accepted procedure.

1 Install Wire 280W5111-101W -

Use: Strap BACS38K1B -

Strap BACS38K2B -

FIGURE 1: FLIGHT COMPARTMENT - INSTALL NEW WIRES

(SHEET 2 OF 2)

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This Figure applies only to: Group 1, Configuration 1.

REFERENCE: 777 WDM 23-93-21, 777 WDM 24-51-24, 777 WDM 25-51-41.

FIGURE 2: FLIGHT COMPARTMENT - CHANGE THE AIRPLANE WIRING

(SHEET 1 OF 2)

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The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

FLAG NAME PART NUMBER QTY NOTES

NOTE

Refer to SWPM 20-61-11 as

an accepted procedure.

1 Contact, Socket BACC47CP1S 8

Refer to SWPM 20-74-11 as

an accepted procedure.

318-01-99-036 (or 6

CTA0165)

2 Contact, Socket

Refer to SWPM 20-90-15 as

an accepted procedure.

3 Contact, Pin S280W555-920 2

Refer to SWPM 20-10-11 as

an accepted procedure.

4 ID Tape 280W5111-10102 1

Refer to SWPM 20-10-11 as

an accepted procedure.

5 ID Tape 280W5111-10103 1

FIGURE 2: FLIGHT COMPARTMENT - CHANGE THE AIRPLANE WIRING

(SHEET 2 OF 2)

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