Commercial 

Airplanes 777

Service Bulletin

Number: 777-24-0077

Original Issue: August 21, 2003

Revision 4: October 17, 2012

ATA System: 2400

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

Isolation Switches

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 © 2003 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Unpublished Work.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.

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2.0
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BOEING SERVICE BULLETIN 777-24-0077

BLANK PAGE
Table of Contents

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

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

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

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

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

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

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

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

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 20

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . . . 23

3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 25

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

FIGURE 1: CHANGE THE AIRPLANE WIRING - GROUP 1 [Group 1, Configuration 1] . . . . . . . . 40

FIGURE 2: FLIGHT DECK - AIRPLANE WIRE ROUTING [Group 1, Configuration 1] . . . . . . . . . 44

FIGURE 3: MAIN EQUIPMENT CENTER - AIRPLANE WIRE ROUTING [Group 1, Configuration 1] . 46

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BOEING SERVICE BULLETIN 777-24-0077

BLANK PAGE
Commercial 

Airplanes 777

Service Bulletin

Revision Transmittal Sheet Number: 777-24-0077

Original Issue: August 21, 2003

Revision 4: October 17, 2012

ATA System: 2400

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

Isolation Switches

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 tell operators that GE Aviation Service Bulletin 4000ELM-24-435 has been revised, and

to give data to change an Electrical Power Control Panel, part number 233W3202-9 to the new part number

233W3202-18.

These sections were changed:

1. In Paragraph 1.B., Concurrent Requirements, changed the GE Aviation service bulletin data.

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:

a. Added an Electrical Power Control Panel part number.

b. Added a note.

5. In Paragraph 2.C.3., Parts Modified and Reidentified, added a table.

6. In Paragraph 3.B., Work Instructions:

a. Step 3, added a note.

b. Step 5, changed the GE Aviation service bulletin data.

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.

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REVISION HISTORY

Original Issue: August 21, 2003

Revision 1: May 24, 2007

Revision 2: December 17, 2009

Revision 3: December 06, 2011

Revision 4: October 17, 2012

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BOEING SERVICE BULLETIN 777-24-0077
Commercial 

Airplanes 777

Service Bulletin

Summary Number: 777-24-0077

Original Issue: August 21, 2003

Revision 4: October 17, 2012

ATA System: 2400

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

Isolation Switches

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.

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 all the components of the IFE (in-flight

entertainment) system and the passenger seats (seat motor power, personal computer power outlets and

telephones).

When selected OFF, the CABIN/UTILITY switch will remove power from all the galleys, the ground service bus

(except the main and APU battery chargers and left forward fuel pump), the utility busses, the gasper air fan,

the fluorescent cabin lighting and the beacon, wing and logo lights. While the switch is off, the night lights, the

supplemental night lights, the reading lights, the attendant work lights and some of the galley and crew rest

lights will be turned on.

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:

On the P5 panel, replace the electrical power control panel. Install eight new wires and remove two wires between

the P5 panel and the P61 overhead panel. Install 13 new wires between the P110 panel and the P210 panel.

Remove one wire between the P210 panel and the P101 panel. Install four new wires between the P210 panel

and the P320 panel. Make the changes to the P110, P210 and P320 panels in accordance with the Smiths/GE

Aviation service bulletins. Do a test of the passenger cabin systems, including the IFE/PASS SEATS switch.

Do a test of the CABIN UTILITY switch.

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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 Airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes.

COMPLIANCE

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive (AD) related to this

service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service

bulletin mandatory.

Boeing recommends that the change given in this service bulletin be done 60 months after the Revision 1 date

of this service bulletin.

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 27.00 13.50

Group 1, Configuration 1:

The time to make the change to the P110, P210 and P320 panels in accordance with the Smiths/GE Aviation

Service Bulletins is not included.

Group 1, Configuration 1:

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

Concurrent Requirements.

Group 1, Configuration 1:

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

233W3202-24-03 Original Issue and/or BAE Systems SB 233W3202-24-04 Revision 2 is not included.

Group 1, Configuration 2:

Airplanes Total Task Hours Elapsed Hours

More Work 1.00 1.00

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BOEING SERVICE BULLETIN 777-24-0077
MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

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

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BOEING SERVICE BULLETIN 777-24-0077
Commercial 

Airplanes 777

Service Bulletin

Number: 777-24-0077

Original Issue: August 21, 2003

Revision 4: October 17, 2012

ATA System: 2400

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

Isolation Switches

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

Refer to Service Bulletin Index Document D6-24W001 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 Airplanes with classic core IFE interface.

777-200 Airplanes that have not accomplished BAE Systems Service

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

1

777-200 Airplanes that have accomplished BAE Systems Service

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

2

Airplane Models:

777-200

Variable Number Group

WA002 - WA017 1

WA076 - WA080 1

WA086 - WA093 1

WA116 - WA119 1

WA131 - WA137 1

WA171 - WA175 1

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Variable Number Group

WA196 - WA198 1

WA206 - WA209 1

WA261 - WA266 1

WB001 - WB015 1

WB051 - WB082 1

WB101 - WB104 1

WB121 - WB125 1

WB131 - WB132 1

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

Group 1, Configuration 1:

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

Group 1, Configuration 1:

Company Service Bulletin Description

Installs new OPS in the Cabin Area Control Panel

(CACP) to change the operation of the cabin

lighting system when the CABIN/UTILITY switch

is installed.

777-23-0176 Original Issue thru

Revision 2.

Boeing

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

(a) The changes in accordance with Boeing Service Bulletin 777-24-0087 can only be done at the same

time as the changes in accordance with this service bulletin.

Group 1, Configuration 1:

The Smiths/GE Aviation Service Bulletins listed below must be done to complete the changes in

accordance with this service bulletin.

Group 1, Configuration 1:

Description

(Power Panel)

Company Service Bulletin

GE Aviation 4000ELM-24-435 Revision 8, Dated March 26, 2012 P320

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BOEING SERVICE BULLETIN 777-24-0077
Group 1, Configuration 1:

Description

(Power Panel)

Company Service Bulletin

GE Aviation 4000ELM-24-556 Revision 1, Dated December 21, 2009 P320

Smiths 4000ELM-24-619 Original Issue, Dated May 9, 2003 P320

Smiths 4000ELM-24-625 Original Issue, Dated May 9, 2003 P320

Smiths 5000ELM-24-450 Original Issue, Dated April 11, 2003 P110

Smiths 5000ELM-24-454 Original Issue, Dated April 11, 2003 P110

Smiths 5000ELM-24-554 Original Issue, Dated April 15, 2003 P110

Smiths 5000ELM-24-559 Revision 2, Dated August 12, 2005 P110

GE Aviation 5000ELM-24-560 Revision 2, Dated April 10, 2006 P110

Smiths 5000ELM-24-562 Revision 1, Dated March 3, 2005 P110

GE Aviation 5000ELM-24-565 Revision 2, Dated December 14, 2009 P110

Smiths 5000ELM-24-617 Original Issue, Dated May 9, 2003 P110

GE Aviation 5000ELM-24-451 Original Issue, Dated April 22, 2003 P110

GE Aviation 5000ELM-24-514 Revision 2, Dated December 12, 2005 P110

Smiths 5200ELM-24-566 Original Issue, Dated April 24, 2003 P110

GE Aviation 6000ELM-24-461 Revision 1, Dated June 12, 2006 P210

Smiths 6000ELM-24-555 Original Issue, Dated April 15, 2003 P210

GE Aviation 6000ELM-24-571 Revision 6, Dated December 14, 2009 P210

GE Aviation 6000ELM-24-572 Revision 3, Dated July 03, 2008 P210

GE Aviation 6000ELM-24-573 Revision 1, Dated December 12, 2005 P210

Smiths 6000ELM-24-575 Original Issue, Dated April 29, 2003 P210

GE Aviation 6000ELM-24-588 Revision 1, Dated June 12, 2006 P210

Smiths 6000ELM-24-590 Original Issue, Dated April 16, 2003 P210

GE Aviation 6000ELM-24-597 Revision 1, Dated December 14, 2009 P210

Smiths 6000ELM-24-601 Original Issue, Dated May 1, 2003 P210

Smiths 6000ELM-24-604 Revision 1, Dated June 14, 2005 P210

GE Aviation 6000ELM-24-614 Revision 1, Dated November 9, 2009 P210

Smiths 6000ELM-24-618 Original Issue, Dated May 9, 2003 P210

GE Aviation 6000ELM-24-624 Revision 5, Dated December 14, 2009 P210

Smiths 6053ELM1-24-613 Original Issue, Dated July 8, 2003 P210

GE Aviation 6060ELM1-24-587 Revision 1, Dated May 24, 2010 P210

Smiths 6064ELM1-24-576 Original Issue, Dated May 6, 2003 P210

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BOEING SERVICE BULLETIN 777-24-0077
Group 1, Configuration 1:

Description

(Power Panel)

Company Service Bulletin

Smiths 6064ELM1-24-603 Original Issue, Dated May 1, 2003 P210

Smiths 6087ELM1-24-615 Original Issue, Dated July 8, 2003 P210

GE Aviation 6000ELM-24-440 Revision 1, Dated December 21, 2005 P210

Smiths 6000ELM-24-456 Revision 1, Dated February 17, 2005 P210

Smiths 6000ELM-24-457 Original Issue, Dated April 11, 2003 P210

GE Aviation 6000ELM-24-460 Revision 3, Dated December 2, 2009 P210

GE Aviation 6000ELM-24-545 Revision 3, Dated December 22, 2005 P210

GE Aviation 6200ELM-24-581 Revision 1, Dated March 5, 2010 P210

GE Aviation 6200ELM-24-616 Revision 1, Dated March 5, 2010 P210

Smiths 6205ELM6-24-605 Original Issue, Dated May 2, 2003 P210

GE Aviation 6087ELM1-24-703 Original Issue, Dated January 26, 2009 P210

The Smiths/GE Aviation service bulletins listed below are for reference and give the specific service

bulletins applicable for each airplane.

Group 1, Configuration 1:

Smiths/GE Aviation Service Revision and Date Notes

Bulletins

ELMS-24-ANA Revision 2, Dated January 20, 2006 Reference Only

ELMS-24-BAB Revision 1, Dated February 19, 2004 Reference Only

ELMS-24-EAD Revision 1, Dated January 16, 2004 Reference Only

ELMS-24-GUN Revision 1, Dated March 1, 2004 Reference Only

ELMS-24-JAL Revision 1, Dated March 1, 2004 Reference Only

ELMS-24-JAS Revision 3, Dated May 23, 2004 Reference Only

ELMS-24-KAL Revision 3, Dated December 14, 2009 Reference Only

ELMS-24-TII Revision 1, Dated March 1, 2004 Reference Only

ELMS-24-UAL Revision 2, Dated February 16, 2009 Reference Only

Group 1, Configuration 2:

None.

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.

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BOEING SERVICE BULLETIN 777-24-0077
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 all the components of the

IFE (in-flight entertainment) system and the passenger seats (seat motor power, personal computer

power outlets and telephones).

When selected OFF, the CABIN/UTILITY switch will remove power from all the galleys, the ground

service bus (except the main and APU battery chargers and left forward fuel pump), the utility busses,

the gasper air fan, the fluorescent cabin lighting and the beacon, wing and logo lights. While the switch

is off, the night lights, the supplemental night lights, the reading lights, the attendant work lights and

some of the galley and crew rest lights will be turned on.

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 three new wires to the wire changes in Figure 1. Reference to

6000ELM1-24-461 were revised to 6000ELM-24-461 due to typographical error. References to Smiths

service bulletin 6000ELM-24-459, 6000ELM-24-567, 5600ELM-24-558, 5000ELM-24-477, and

5000ELM-24-564 were removed because they are not applicable to airplanes with classic core IFE.

Revision 2 was sent to include reference to GE Aviation Service Bulletin 6087ELM1-24-703 in the

service bulletin. GE Aviation Service Bulletin 6087ELM1-24-703 gives instructions to change the wiring

in the Electrical Load Management System (ELMS) P210 panel for airplanes WA261-WA266. Also,

GE Aviation Service Bulletin ELMS-24-UAL which gives airplane applicability data, has been revised

to add reference to GE Aviation Service Bulletin 6087ELM1-24-703.

Revision 3 was sent to tell operators that the wire kit 280W5110-101 included in the top kit 005W3206-1

contains a wire 280W5110-101W of incorrect length. A new supplemental kit 280W5110-105W is added

to this service bulletin which contains an equivalent wire with the correct length. Also, this revision is

sent to tell operators that BAE Systems Service Bulletin 233W3202-24-04, and some GE Aviation

service bulletins have been revised.

The data given in Information Notice 777-24-0077 IN01 and 777-24-0077 IN02 is included in this

revision.

Revision 4 is sent to tell operators that GE Aviation Service Bulletin 4000ELM-24-435 has been revised,

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

part number 233W3202-18.

D. Description

Group 1, Configuration 1:

On the P5 panel, replace the electrical power control panel. Install eight new wires and remove two

wires between the P5 panel and the P61 overhead panel. Install 13 new wires between the P110 panel

and the P210 panel. Remove one wire between the P210 panel and the P101 panel. Install four new

wires between the P210 panel and the P320 panel. Make the changes to the P110, P210 and P320

panels in accordance with the Smiths/GE Aviation service bulletins. Do a test of the passenger cabin

systems, including the IFE/PASS SEATS switch. Do a test of the CABIN UTILITY switch.

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BOEING SERVICE BULLETIN 777-24-0077
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 - More work may be necessary on airplanes changed as shown in the Original Issue of this

service bulletin. Operators can install the three new wires W6220-0071-20, W6220-072-20 and

W6220-073-20 as shown in Figure 1.

Revision 2 - More work is necessary on airplanes WA261-WA266 changed in accordance with the

Original Issue or Revision 1 of this service bulletin. For airplanes WA261-WA266 do GE Aviation Service

Bulletin 6087ELM1-24-703 Original Issue to change the wiring in the ELMS P210 panel.

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.

Revision 3 - More work is necessary on the airplanes changed in accordance with GE Aviation Service

Bulletin 6000ELM-24-614 Original Issue or GE Aviation SB 6200ELM-24-616 Original Issue. Do GE

Aviation SB 6000ELM-24-614 Revision 1 or GE Aviation SB 6200ELM-24-616 Revision 1 to put back

the P210 power panel to the correct standard.

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

777-200 117, 118

E. Compliance

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive (AD) related

to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in

this service bulletin mandatory.

Boeing recommends that the change given in this service bulletin be done 60 months after the Revision

1 date of this service bulletin.

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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 2 1.5 0.75

Change 2 16.0 8.00

Close Access 2 1.5 0.75

Test 2 8.0 4.00

TOTAL FOR EACH AIRPLANE 27.00 13.50

Group 1, Configuration 1:

The time to make the change to the P110, P210 and P320 panels in accordance with the Smiths/GE

Aviation Service Bulletins is not included.

Group 1, Configuration 1:

This estimate does not include the task hour data given in the Boeing service bulletins in Paragraph

1.B., Concurrent Requirements.

Group 1, Configuration 1:

The time to make the change to the electrical power control panel in accordance with the BAE Systems

SB 233W3202-24-03 Original Issue and/or BAE Systems SB 233W3202-24-04 Revision 2 is not

included.

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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 +2.6 +951.6

Group 1, Configuration 2:

None.

I. Electrical Load Data

Group 1, Configuration 1:

The electrical loads for these circuit breakers do not change. These circuit breakers change electrical

busses as shown in the last two columns of the following table. The actual electrical loads for these

circuit breakers can be found in the current copy of the electrical load analysis for the airplane. Some

airplanes will not have all of these circuit breakers. Change the electrical buss data only for the circuit

breakers installed on the airplane.

Group 1, Configuration 1:

Circuit Breaker Nomenclature Pre S/B Bus Location Post S/B Bus Location

C23423 Landscape Camera L MAIN AC Sec 1, Phase A L MAIN AC Sec 2, Phase A

C23430 CTU L MAIN AC Sec 1, Phase A L MAIN AC Sec 2, Phase A

C23432 UHF R L MAIN AC Sec 1, Phase B L MAIN AC Sec 2, Phase A

C23434 UHF L L MAIN AC Sec 1, Phase C L MAIN AC Sec 2, Phase A

C23450 M1/M2 Galley Handsets R Utility, Phase C R Utility, Phase B

C23454 Cabin File Server L MAIN AC Sec 1, Phase A L MAIN AC Sec 2, Phase A

C23455 Fax Machine R Utility, Phase C R Utility, Phase B

C23460 Cabin Unit/Holster R Utility, Phase A R Utility, Phase B

C23468 Phones F/C R Utility, Phase A R Utility, Phase B

C23473 BCC Printer L MAIN AC Sec 1, Phase B L MAIN AC Sec 2, Phase A

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Group 1, Configuration 1:

Circuit Breaker Nomenclature Pre S/B Bus Location Post S/B Bus Location

C25429 Crew Rest Powered Seats L MAIN AC Sec 1, Phase B L MAIN AC Sec 2, Phase A

Group 1, Configuration 2:

Not changed.

J. References

1. Existing Data:

a. Engineering Change Memo PRR 61887

b. Boeing Service Bulletin 777-23-0125, 777-23-0176, 777-24-0087

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

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

e. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19, 20-30-11, 20-30-12,

20-30-16, 20-61-11, 20-74-11

f. 777 Aircraft Maintenance Manual (AMM) 12-11-01, 23-18-00, 23-18-05, 23-32-00, 24-22-00,

24-22-01, 24-31-02, 24-31-06, 33-13-00, 33-16-00, 33-21-00, 33-31-00, 33-44-00

g. 777 Wiring Diagram Manual (WDM) 23-32-02, 23-93-21, 24-51-24, 24-51-41, 46-01-11

h. BAE Systems Service Bulletin 233W3202-24-03, 233W3202-24-04

NOTE: These Service Bulletins were previously issued by Boeing.

i. GE Aviation Service Bulletin 4000ELM-24-435, 5000ELM-24-451, 5000ELM-24-514,

5000ELM-24-560, 5000ELM-24-565, 5200ELM-24-566, 6000ELM-24-440, 6000ELM-24-460,

6000ELM-24-461, 6000ELM-24-545, 6000ELM-24-571, 6000ELM-24-572, 6000ELM-24-573,

6000ELM-24-588, 6000ELM-24-597, 6000ELM-24-614, 6000ELM-24-624, 6060ELM1-24-587,

6087ELM1-24-703, ELMS-24-UAL

j. Smiths Service Bulletin 4000ELM-24-556, 4000ELM-24-619, 4000ELM-24-625,

5000ELM-24-450, 5000ELM-24-454, 5000ELM-24-554, 5000ELM-24-559, 5000ELM-24-562,

5000ELM-24-617, 6000ELM-24-456, 6000ELM-24-457, 6000ELM-24-555, 6000ELM-24-575,

6000ELM-24-590, 6000ELM-24-601, 6000ELM-24-604, 6000ELM-24-618, 6053ELM1-24-613,

6064ELM1-24-576, 6064ELM1-24-603, 6087ELM1-24-615, 6200ELM-24-581,

6200ELM-24-616, 6205ELM6-24-605, ELMS-24-ANA, ELMS-24-BAB, ELMS-24-EAD,

ELMS-24-GUN, ELMS-24-JAL, ELMS-24-JAS, ELMS-24-KAL, ELMS-24-TII

NOTE: The supplier was told to send copies of the service bulletin to each operator.

2. Data Supplied with this Service Bulletin:

None.

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BOEING SERVICE BULLETIN 777-24-0077
3. Installation Drawings Used in the Preparation of this Service Bulletin:

Drawing Number Title

288W4106 Wire Bundle Installation - Bulkhead (STA 332.5)

288W4111 Wire Bundle Installation - L.S. Passenger Floor (STA 379-469)

Wire Bundle Installation - L.S. Cab Floor and Forward Passenger

Floor (STA 209.5-379.0)

288W4115

Wire Bundle Installation - R.S. Cab Floor and Forward Passenger

Floor (STA 209.5-379.0)

288W4116

These drawings were used to prepare this service bulletin. These drawings are not necessary to

make the specified changes, and are not supplied with this service bulletin. These drawings may

not be applicable to all airplane configurations or operators.

K. Publications Affected

1. Publications:

Publication Chapter-Section

777 Operations Manual 1.21, 6.10, 6.20, 6.30, NNC.6

777 Maintenance Manual 23-32

777 Wiring Diagram Manual Equipment List, 23-32, 23-93, 24-51, 46-01

777 Schematic Diagram Manual 23-32, 23-93, 24-51

777 Illustrated Parts Catalog 24-11, 24-21, 24-31, 24-41, 31-12, 33-13

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 777-24-0077
2. MATERIAL INFORMATION

A. Material - Price and Availability

Boeing can supply the kits 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 kits 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

Revision 3 date of this

Service Bulletin (US

Dollars)

ROLT as of Revision

3 date of this Service

Bulletin (Calendar

Days)

Kit Number Name

TOP KIT - CABIN POWER ISOLATION 182 1,346.00

SWITCH INSTALLATION

005W3206-1

280W5110-105W WIRE 149 90.00 (a)

(a) Wire 280W5110-105W is a supplemental kit to the top kit 005W3206-1.

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.

Group 1, Configuration 1:

NOTE: 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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BOEING SERVICE BULLETIN 777-24-0077
Group 1, Configuration 1:

Kit 005W3206

Existing Part Notes

Number

New Part Number QTY Name

-1

005W3206-1 - Top Kit (a)

280W5110-1 1 Wire Kit

BACS38K1 45 Strap

BACS38K1B 70 Strap

BACS38K1E 25 Strap

BACS38K2B 10 Strap

(a) There are more parts than are necessary.

Group 1, Configuration 1:

Kit 280W5110

Existing Part Notes

Number

New Part Number QTY Name

-201 -104 -103 -102 -101 -1

280W5110-1 . . . . . - Wire Kit (a)

280W5110-101 . . . . - 1 Kit (W4236)

280W5110-101W . . . . 1 . Wire

280W5110-10101 . . . . 1 . Tie Wrap

280W5110-102 . . . - . 1 Kit (W1052)

280W5110-102W . . . 1 . . Wire

280W5110-10201 . . . 1 . . Tie Wrap

280W5110-10202 . . . 1 . . Identification Tape

280W5110-10203 . . . 1 . . Identification Tape

280W5110-103 . . - . . 1 Kit (W6120)

280W5110-103W . . 1 . . . Wire

280W5110-10301 . . 1 . . . Tie Wrap

280W5110-10302 . . 1 . . . Identification Tape

280W5110-104 . - . . . 1 Kit (W6220)

280W5110-104W . 1 . . . . Wire

280W5110-10401 . 1 . . . . Tie Wrap

280W5110-10402 . 1 . . . . Identification Tape

280W5110-10403 . 1 . . . . Identification Tape

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Group 1, Configuration 1:

Kit 280W5110

Existing Part Notes

Number

New Part Number QTY Name

-201 -104 -103 -102 -101 -1

280W5110-10404 . 1 . . . . Identification Tape

280W5110-10405 . 1 . . . . Identification Tape

280W5110-201 - . . . . 1 Kit (Spares)

BACC47CN1S 2 12 6 . . . Contact, Socket

BACC47CN2A 1 3 . . . . Contact, Pin

BACC47CP1S . . . 8 . . Contact, Socket

BACT12C12 2 1 1 . . . Splice

CTA0165 (CTA- . . . 6 . . Contact, Socket

0165)

D436-39 2 1 1 . . . Sleeve

M39029-1-101 . . . 2 . . Contact, Pin

(M39029/1-101)

324485 1 1 . . . . End Cap

(a) There are more parts than are necessary.

Group 1, Configuration 1:

Kit 280W5110

Existing Part Num- Notes

ber

New Part Number QTY Name

-105W

280W5110-105W 1 Wire (a)

(a) Wire 280W5110-105W is a replacement for wire 280W5110-101W of incorrect length. Wire 280W5110-

101W is included in the wire kit 280W5110-101.

Group 1, Configuration 2:

None.

2. Parts and Materials Supplied by the Operator:

Group 1, Configuration 1:

Part Number / Specifica- QTY Name Existing Part Number Notes

tion

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

233W3202-18 (a) 1 Electrical Power Control Panel 233W3202-12 (c) (d)

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Group 1, Configuration 1:

Part Number / Specifica- QTY Name Existing Part Number Notes

tion

233W3202-19 (a) 1 Electrical Power Control Panel 233W3202-13 (c) (d)

233W3202-22 (b) 1 Electrical Power Control Panel 233W3202-11 (c) (d)

BACC47CN2A 2 Contact, Pin - (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

233W3202-9 can be changed to part number 233W3202-12 in accordance with 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) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data.

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 Part Number Notes

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

233W3202-12 1 Electrical Power Control Panel 233W3202-18 (a)

233W3202-13 1 Electrical Power Control Panel 233W3202-19 (a)

233W3202-11 1 Electrical Power Control Panel 233W3202-22 (a)

(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 233W3202-9 is changed to part number 233W3202-12

in accordance with 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.

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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 777-24-0077

BLANK PAGE
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. Refer to the Boeing Standard Wiring Practices Manuals SWPM 20-10-11, SWPM

20-10-12, SWPM 20-30-11, SWPM 20-30-12, SWPM 20-30-16 and SWPM 20-61-11

for the wire installation procedures. Refer to SWPM 20-10-19 for the wire separation

requirements.

4. 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.

5. Where the work instructions include installation of a kept part, a new or serviceable

part with the same part number can be installed as an alternative to the kept part.

6. 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.

7. These work instructions refer to procedures included on 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.

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. Remove the electrical power control panel. Refer to 777 AMM 24-22-01, Electrical Module Assembly

Removal, as an accepted procedure.

3. 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 233W3202-11, 233W3202-12

or 233W3202-13, can be changed to the new part number in accordance with BAE

Systems SB 233W3202-24-04 Revision 2.

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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 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.

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

5. Make the changes to the ELMS panels P110, P210 and P320 in accordance with the Smiths/GE

Aviation Service Bulletins that follow:

Description

(Power Panel)

Company Service Bulletin

GE Aviation 4000ELM-24-435 Revision 8, Dated March 26, 2012 P320

GE Aviation 4000ELM-24-556 Revision 1, Dated December 21, 2009 P320

Smiths 4000ELM-24-619 Original Issue, Dated May 9, 2003 P320

Smiths 4000ELM-24-625 Original Issue, Dated May 9, 2003 P320

Smiths 5000ELM-24-450 Original Issue, Dated April 11, 2003 P110

Smiths 5000ELM-24-454 Original Issue, Dated April 11, 2003 P110

Smiths 5000ELM-24-554 Original Issue, Dated April 15, 2003 P110

Smiths 5000ELM-24-559 Revision 2, Dated August 12, 2005 P110

GE Aviation 5000ELM-24-560 Revision 2, Dated April 10, 2006 P110

Smiths 5000ELM-24-562 Revision 1, Dated March 3, 2005 P110

GE Aviation 5000ELM-24-565 Revision 2, Dated December 14, 2009 P110

Smiths 5000ELM-24-617 Original Issue, Dated May 9, 2003 P110

GE Aviation 5000ELM-24-451 Original Issue, Dated April 22, 2003 P110

GE Aviation 5000ELM-24-514 Revision 2, Dated December 12, 2005 P110

Smiths 5200ELM-24-566 Original Issue, Dated April 24, 2003 P110

GE Aviation 6000ELM-24-461 Revision 1, Dated June 12, 2006 P210

Smiths 6000ELM-24-555 Original Issue, Dated April 15, 2003 P210

GE Aviation 6000ELM-24-571 Revision 6, Dated December 14, 2009 P210

GE Aviation 6000ELM-24-572 Revision 3, Dated July 03, 2008 P210

GE Aviation 6000ELM-24-573 Revision 1, Dated December 12, 2005 P210

Smiths 6000ELM-24-575 Original Issue, Dated April 29, 2003 P210

GE Aviation 6000ELM-24-588 Revision 1, Dated June 12, 2006 P210

Smiths 6000ELM-24-590 Original Issue, Dated April 16, 2003 P210

GE Aviation 6000ELM-24-597 Revision 1, Dated December 14, 2009 P210

Smiths 6000ELM-24-601 Original Issue, Dated May 1, 2003 P210

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Description

(Power Panel)

Company Service Bulletin

Smiths 6000ELM-24-604 Revision 1, Dated June 14, 2005 P210

GE Aviation 6000ELM-24-614 Revision 1, Dated November 9, 2009 P210

Smiths 6000ELM-24-618 Original Issue, Dated May 9, 2003 P210

GE Aviation 6000ELM-24-624 Revision 5, Dated December 14, 2009 P210

Smiths 6053ELM1-24-613 Original Issue, Dated July 8, 2003 P210

GE Aviation 6060ELM1-24-587 Revision 1, Dated May 24, 2010 P210

Smiths 6064ELM1-24-576 Original Issue, Dated May 6, 2003 P210

Smiths 6064ELM1-24-603 Original Issue, Dated May 1, 2003 P210

Smiths 6087ELM1-24-615 Original Issue, Dated July 8, 2003 P210

GE Aviation 6000ELM-24-440 Revision 1, Dated December 21, 2005 P210

Smiths 6000ELM-24-456 Revision 1, Dated February 17, 2005 P210

Smiths 6000ELM-24-457 Original Issue, Dated April 11, 2003 P210

GE Aviation 6000ELM-24-460 Revision 3, Dated December 2, 2009 P210

GE Aviation 6000ELM-24-545 Revision 3, Dated December 22, 2005 P210

GE Aviation 6200ELM-24-581 Revision 1, Dated March 5, 2010 P210

GE Aviation 6200ELM-24-616 Revision 1, Dated March 5, 2010 P210

Smiths 6205ELM6-24-605 Original Issue, Dated May 2, 2003 P210

GE Aviation 6087ELM1-24-703 Original Issue, Dated January 26, 2009 P210

The Smiths/GE Aviation service bulletins that follow are for reference and give the specific service

bulletins applicable for each airplane.

Smiths/GE Aviation Service Revision and Date Notes

Bulletins

ELMS-24-ANA Revision 2, Dated January 20, 2006 Reference Only

ELMS-24-BAB Revision 1, Dated February 19, 2004 Reference Only

ELMS-24-EAD Revision 1, Dated January 16, 2004 Reference Only

ELMS-24-GUN Revision 1, Dated March 1, 2004 Reference Only

ELMS-24-JAL Revision 1, Dated March 1, 2004 Reference Only

ELMS-24-JAS Revision 3, Dated May 23, 2004 Reference Only

ELMS-24-KAL Revision 3, Dated December 14, 2009 Reference Only

ELMS-24-TII Revision 1, Dated March 1, 2004 Reference Only

ELMS-24-UAL Revision 2, Dated February 16, 2009 Reference Only

6. Do this continuity check:

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Connector Pin Panel Connector Pin Panel Result Airplanes

From To

D21021P 6 P210 D21037P 24 P210 Continuity All

26 Continuity All

28 Continuity All

29 Continuity All

30 Continuity All

31 Continuity All

D21021P 6 P210 D11037P 19 P110 Continuity All

D11037P 19 P110 D11037P 7 P110 Continuity All

11 Continuity All

15 Continuity All

18 Continuity All

D21021P 42 P210 D32012P 9 P320 Continuity WA261-WA266, WB051-WB082

D21027P 28 10 Continuity

D21027P 29 11 Continuity

D21027P 30 12 Continuity

DM24023B 46 P5 DM23217G A2 P61 Continuity All

DM24023B 47 A3 Continuity All

DM24023B 48 A1 Continuity All

DM24023B 49 A19 Continuity All

DM24023B 50 A20 Continuity All

DM24023B 51 A18 Continuity All

DM24023B 45 Ground Continuity All

DM24023B 52 Ground Continuity All

7. Supply the electrical power to the airplane. Refer to 777 AMM 24-22-00, Supply Electrical Power,

as an accepted procedure.

8. 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 for the Master Dim and Test -

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

accepted procedures.

9. Do this test of the passenger cabin systems:

a. Prepare for the test.

(1) Make sure that the circuit breakers that follow on the P210 panel are closed:

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NOTE: This list is all inclusive. Operators should compare this list to the Wiring Diagram

Manual Equipment List (ELI) to find the circuit breakers installed on a specific

airplane.

Number, Location, Name Notes

C21608, G2, R LAV/GLY FAN CTRL

C23302, D13, CTU

C23303, A2, SVU ZONE 1 L-C-R

C23309, A5, SVU ZONE 3 R-C

WA002-WA017 if Boeing Service

Bulletin 777-23-0125 has been done.

C23309, A5, BUFFER BOX 2

C23310, B2, SVU ZONE 3 L-C

WA002-WA017 if Boeing Service

Bulletin 777-23-0125 has been done.

C23310, B2, BUFFER BOX 3

C23354, C27, NATS PWR

C23403, C1, VIDEO PGMS & CTRL

C23404, D14, VIDEO PGMS & CTRL 2

C23405, C13, CABIN PRINTER

C23410, D3, VIDEO DISTR 1

C23411, C14, VIDEO DISTR 2

C23412, E6, VIDEO DISTR 3

C23413, E8, VIDEO DISTR 4

C23430, C6, CABIN TELECOMMUNICATION UNIT

C23432, D3, UHF - R

C23434, E5, UHF - L

C23448, C2, ZNC/ZNTU

C23450, D23, M1/M2 GALLEY HANDSETS

C23452, D22, FAX/F5 GALLEY HANDSET

C23454, E7, CABIN FILE SERVER

C23455, D23, FAX MACHINE

C23460, A23, CABIN UNIT/HOLSTER

C23461, D22, TFTS MPU & XMTR/RCRV

C23462 , C7 , VIDEO DISTR 1A

C23616, H8, ENTMT CTRL R

C23644, H7, PASSENGER TELEPHONE 2

C23650, J10, CTM/HOLSTER

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Number, Location, Name Notes

C23658, G12, IFE MASTER CTRL

C24451, B19, FLT DK SW PWR DISTR 1

C24452, D14, FLT DK SW PWR DISTR 2

C24688, G13, IFE SEATS DECK SW

C25312, F10, PAX SEAT R

C25314, F13, PAX SEAR C

C25315, F7, PAX SEAT 2R

C25316, F4, PAX SEAR 2C

C25320, A21, IN-SEAT POWER OUTLETS ZONE 1

(2) Make sure that the circuit breakers that follow on the P110 panel are closed:

NOTE: This list is all inclusive. Operators should compare this list to the Wiring Diagram

Manual Equipment List (ELI) to find the circuit breakers installed on a specific

airplane.

Number, Location, Name Notes

C23305, A24, SVU ZONE 2 R-C

C23307, A27, SVU ZONE 2 L-C

WA002-WA017 if Boeing Service

Bulletin 777-23-0125 has been done.

C23307, A27, BUFFER BOX 1

C23401, D27, MULTP AUDIO ENTMT CTRL

C23407, F28, VIDEO DISTR 1

C23408, E23, VIDEO DISTR 2

C23409, C21, VIDEO DISTR 3

C23641, G23, ENTMT CTRL L

C23643, H15, PASSENGER TELEPHONE 1

C25311, F16, PAX SEAT L

C25317, F19, PAX SEAT 2L

(3) Make sure that the circuit breaker that follows on the P320 panel is closed:

NOTE: This list is all inclusive. Operators should compare this list to the Wiring Diagram

Manual Equipment List (ELI) to find the circuit breakers installed on a specific

airplane.

Number, Location, Name Notes

C23475, K6, VEP AC

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(4) On the P5 panel, select the IFE/PASS SEATS switch to the ON position.

(5) On the CSCP, select these menu items, Cabin Controls, Seat Control and Audio Monitor,

Seat/Audio Player Power Control, Seat Power "ON", Audio Entertainment Player "ON".

b. Do this test of the IFE electrical power.

(1) For airplanes WA002-WA017, WA076-WA080, WA086-WA093, WA116-WA119,

WA196-WA198, WA206-WA209, WB001-WB015, WB101-WB104, WB121-WB125 and

WB131-WB132, on the seat rows aft of door 1, see that the passenger control units (PCU)

are powered (LEDs are on). This step does a check that circuit breaker C23303 is

connected to the electrical power.

NOTE: For airplanes WA002-WA017, circuit breaker C23303 is collared if Boeing Service

Bulletin 777-23-0125 has been done. If the circuit breaker is collared, it is not

necessary to do this step.

(2) For airplanes WA002-WA017, WA076-WA080, WA196-WA198, WA207-WA209,

WB001-WB015, WB101-WB104 and WB121-WB125, on the seat rows aft of door 2, see

that the passenger control units (PCU) are powered (LEDs are on). This step does a

check that circuit breakers C23305 and C23307 are connected to the electrical power.

NOTE: For airplanes WA002-WA017, if Boeing Service Bulletin 777-23-0125 has been

done, check to see that buffer box 1 is powered (C23307).

(3) For airplanes WA002-WA017, WA076-WA080, WA196-WA198, WA207-WA209,

WB001-WB015, WB101-WB104 and WB121-WB125, on the seat rows aft of door 3, see

that the passenger control units (PCU) are powered (LEDs are on). This step does a

check that circuit breakers C23309 and C23310 are connected to the electrical power.

NOTE: For airplanes WA002-WA017, if Boeing Service Bulletin 777-23-0125 has been

done, check to see that buffer box 2 (C23309) and buffer box 3 (C23310) are

powered.

(4) See that the video entertainment player 1 (in the purser work station/video control center)

has power (LED is on). For all airplanes except WB074-WB082, this step does a check

that circuit breaker C23403 is connected to the electrical power. For all airplanes

WB074-WB082, this step does a check that circuit breaker C23475 is connected to the

electrical power.

(5) On the E2-4 shelf, see that the Audio Entertainment Player(s) are powered (at least one

LED is on). This step does a check that circuit breaker C23401 is connected to the

electrical power.

(6) For all airplanes except WA002-WA017, WB068-WB082 and WB121-WB125, turn on

the passenger video entertainment system. Refer to 777 AMM 23-32-00, Power On the

Video Entertainment System, as an accepted procedure. See that all the projectors and

monitors are on. This step checks that circuit breakers C23462, C23407, C23408, C23409,

C234010, C23411, C23412, C23413, C23421 and C23422, if applicable, are connected

to the electrical power.

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c. For airplanes WA002-WA017, WA076-WA080, WA196-WA198, WA206-WA209,

WB001-WB015, WB051-WB082, WB101-WB104, WB121-WB125 and WB 131-WB132, do

this passenger seat power test.

(1) On the seat rows aft of door 1 left, use the seat switches to see that the seats are powered.

This step checks that circuit breaker C25311 is connected to electrical power.

NOTE: Airplanes WB051-WB082 have this circuit breaker installed. If the circuit breaker

has a collar installed, it is not necessary to do this step.

(2) On the center seat rows aft of door 1, use the seat switches to see that the seats are

powered. This step checks that circuit breaker C25314 is connected to electrical power.

NOTE: Airplanes WB051-WB082 have this circuit breaker installed. If the circuit breaker

has a collar installed, it is not necessary to do this step.

(3) On the seat rows aft of door 1 right, use the seat switches to see that the seats are

powered. This step checks that circuit breaker C25312 is connected to electrical power.

NOTE: Airplanes WB051-WB082 have this circuit breaker installed. If the circuit breaker

has a collar installed, it is not necessary to do this step.

d. For airplanes WA261-WA266 do this test of the in seat power outlets.

(1) On the seat rows aft of door 1, see that the PC power outlets have electrical power. See

that LED is illuminated. This step checks that the circuit breaker C25320 is connected to

electrical power.

e. For all airplanes except WA131-WA137, WA171-WA175, WA206-WA209, WA261-WA266

and WB051-WB082 do this test of the passenger telephones.

(1) Try to make a phone call from either a wall mount telephone or an in-seat telephone.

Refer to 777 AMM 23-18-00 as an accepted procedure. If a call can be made, or a busy

signal is heard, the system is serviceable. This step checks that circuit breaker C23430

is connected to electrical power. Circuit breaker C23430 powers the cabin

telecommunications unit.

NOTE: Airplanes WB051-WB082 have this circuit breaker installed. The circuit breaker

is for provisions only and has a collar and an INOP label installed.

f. Do this test of the IFE/PASS SEATS switch.

(1) On the P5 panel, select the IFE/PASS SEATS switch to OFF.

(2) Make sure that all the IFE equipment in the purser work station or video control center

no longer has electrical power. Some components may have battery backup units. For

these components it may take several minutes before the electrical power is removed.

(3) Make sure that the overhead video system is off (no video signal, monitor may still be

powered).

(4) Make sure that all the passenger control units on the passenger seats are off (electrical

power is removed).

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(5) For all airplanes with PC power outlets, make sure that all the PC power outlets do not

have electrical power. See that LEDs are not illuminated.

(6) For airplanes with powered seats, make sure the powered seats do not operate (electrical

power is removed).

(7) For airplanes with wall mounted telephones, make sure that the telephone does not

operate. Swipe a valid credit card through the card reader. Make sure that no dial tone

can be heard.

(8) On the P5 panel, select the IFE/PASS SEATS switch to ON.

g. Do this test of the passenger seat/audio player power control system.

(1) See that the overhead video system is on. Refer to 777 AMM 23-32-00, Power On the

Video Entertainment System, as an accepted procedure to get the recommended

instructions.

(2) On the CSCP, select these menu items, Cabin Controls, Seat Control and Audio Monitor,

Seat/Audio Player Power Control, Seat Power "OFF", Audio Entertainment Player "OFF".

(3) See that the overhead video system is on.

(4) Make sure that all the passenger control units on the passenger seats are off (electrical

power is removed).

(5) For all airplanes with PC power outlets, make sure that all the PC power outlets have

electrical power. See that LEDs are illuminated.

(6) For airplanes with powered seats, make sure the powered seats operate (electrical power

is available).

(7) For airplanes with wall mounted telephones, make sure that the telephones operate.

Swipe a valid credit card through the card reader. Make sure that a dial tone can be

heard.

(8) For airplanes WB037-WB044, see that these switches are serviceable (the switch is

illuminated).

— PC/SEAT POWER ISOLATION SWITCH MCU 1

— PC/SEAT POWER ISOLATION SWITCH MCU 2

— PC/SEAT POWER ISOLATION

— SEAT/PC PWR FAULT

(9) Select the IFE master power switch to the ON position.

10. Do this test of the CABIN/UTIL switch:

a. Make sure that the circuit breakers that follow on the P110 panel are closed:

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Number, Location, Name Notes

C21444, A07, L DR 1 HTR

C21446, B07, L DR 2 HTR

C21448, C07, L DR 3 HTR

C21450, C08, L DR 4 HTR

C28307, E05, L FWD FUEL BOOST PUMP

b. Make sure that the circuit breakers that follow on the P210 panel are closed:

Number, Location, Name Notes

C21445, A25, R DR 1 HTR

C21447, A24, R DR 2 HTR

C21449, D28, R DR 3 HTR

C21451, B25, R DR 4 HTR

C33486, E09, RED ANTI-COLL LTS

C33636, M11, RED ANTI-COLL LTS CTRL

c. Make sure that the circuit breakers that follow on the P310 panel are closed:

Number, Location, Name Notes

C24620, M02, MN BAT CHARGER

d. Make sure that the circuit breakers that follow on the P320 panel are closed:

Number, Location, Name Notes

C24300, K09, MN BAT CHARGER PWR

C24301, K12, APU BAT CHARGER PWR

C33416, G02, CABIN LTS FWD R

C28301, G09, L FWD FUEL BOOST PUMP GND SVCE

C33417, L02, CABIN LTS FWD L

C33418, H04, CABIN LTS MID FWD R

C33419, L06, CABIN LTS MID FWD L

C33420, H09, CABIN LTS MID AFT R

C33421, L10, CABIN LTS MID AFT L

C33422, G03, CABIN LTS AFT R

C33423, L07, CABIN LTS AFT L

C33518, J12, E/E EQUIP CTR LTS

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e. Make sure that the circuit breakers that follow on the P49 panel are closed:

Number, Location, Name Notes

C24622, A01, APU BAT CHARGER

f. On the P5 panel, see that the CABIN/UTIL switch is selected to the ON position.

g. For airplanes with an airborne fax machine, see that the fax machine has electrical power.

Refer to 777 AMM 23-18-05 as an accepted procedure to get more data about the location

of the fax machine.

h. Do a test of the sidewall lights and indirect ceiling lights. Refer to 777 AMM 33-21-00,

Passenger Compartment Illumination - Operational Test, as an accepted procedure. This step

makes sure that all phases of the ground service bus, sections 1 and 2, have electrical power.

It is not necessary to do the test for the night lights.

i. Do a test of the forward equipment center lights. Refer to 777 AMM 33-31-00, Service and

Cargo Loading Lights - Operational Test of the Forward and Main Equipment Center Lights,

as an accepted procedure. This step makes sure the 28V AC ground service bus has electrical

power.

j. Do a test of the red anti-collision lights on the upper and lower body. Refer to 777 AMM

33-44-00, Anti-Collision Lights - Operational Test, as an accepted procedure. It is only

necessary to do a test of the upper and lower anti-collision lights. This step makes sure there

is electrical power on the right main AC bus.

k. On the P5 panel, select the CABIN/UTIL switch to the OFF position.

l. For airplanes with an airborne fax machine, see that the fax machine does not have electrical

power.

m. Do a test of the sidewall lights and indirect ceiling lights. Refer to 777 AMM 33-21-00,

Passenger Compartment Illumination - Operational Test, as an accepted procedure. The lights

should not come on. This step makes sure that all phases of the ground service bus, sections

1 and 2, do not have electrical power. It is not necessary to do the test for the night lights.

n. See that the passenger seat reading lights, attendant work lights, night lights and supplemental

night lights are all on. This step does a check of the new cabin management system (CMS)

database (refer to Boeing Service Bulletin 777-23-0176).

o. Do a test of the forward equipment center lights. Refer to 777 AMM 33-31-00, Service and

Cargo Loading Lights - Operational Test of the Forward and Main Equipment Center Lights,

as an accepted procedure. The lights should not come on. This step makes sure the 28V AC

ground service bus does not have electrical power.

p. Do a test of the red anti-collision lights on the upper and lower body. Refer to 777 AMM

33-44-00, Anti-Collision Lights - Operational Test, as an accepted procedure. It is only

necessary to do a test of the upper and lower anti-collision lights. The lights should not come

on. This step makes sure there is no electrical power on the right main AC bus.

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q. Do a test of the main battery charger operation. Refer to 777 AMM 24-31-02, Main Battery

Charger Installation Test, as an accepted procedure.

r. Do a test of the APU battery charger operation. Refer to 777 AMM 24-31-06, APU Battery

Charger Installation Test, as an accepted procedure.

s. Do this test of the left forward fuel boost pump operation:

WARNING: DO NOT OPERATE ANY FUEL PUMP IF THE AMBER PRESS LIGHT COMES

ON AND STAYS ON. FUEL VAPORS IN THE TANK MAY IGNITE AND CAUSE

A FIRE OR EXPLOSION.

(1) To operate any of the fuel pumps, you must be in the flight compartment to continuously

monitor the fuel quantity and the low pressure indication in the applicable tank.

Immediately set the applicable fuel pump switch-light to OFF if the amber PRESS light

comes on and stays on.

(2) Make sure there is a minimum of 6,000 LB (2,700 KGS) in the left main fuel tank.

NOTE: This fuel quantity is necessary to prevent dry operation of the fuel pump.

If it necessary to refuel the fuel tanks, refer to the 777 AMM 12-11-01 as an accepted

procedure.

(3) On the P5 panel, push the L FWD PUMP switch-light to the ON position.

(4) On the P5 panel, make sure the left forward fuel boost pump PRESS light goes off. The

PRESS light can take up to 20 seconds to go off.

(5) On the EICAS display, see that the FUEL PUMP L FWD message is not displayed.

(6) On the P5 panel, push the L FWD PUMP switch-light to the OFF position.

(7) On the P5 panel, make sure the left forward fuel boost pump PRESS light comes on. The

PRESS light can take up to 20 seconds to come on.

t. On the P5 panel, see that the CABIN/UTIL switch is selected to the ON position.

11. 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.

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4. If the electrical power control panel has the part number 233W3202-18, and does not have lockwire

provisions 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

provisions 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

provisions 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

provisions 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 777-24-0077
This Figure applies only to: Group 1, Configuration 1.

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

FIGURE 1: CHANGE THE AIRPLANE WIRING - GROUP 1

(SHEET 1 OF 4)

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BOEING SERVICE BULLETIN 777-24-0077
REFERENCE: 777 WDM 23-32-02

FIGURE 1: CHANGE THE AIRPLANE WIRING - GROUP 1

(SHEET 2 OF 4)

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BOEING SERVICE BULLETIN 777-24-0077
REFERENCE: 777 WDM 23-32-02, 777 WDM 46-01-11

FIGURE 1: CHANGE THE AIRPLANE WIRING - GROUP 1

(SHEET 3 OF 4)

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BOEING SERVICE BULLETIN 777-24-0077
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

1 Contact, Socket BACC47CP1S 8

Refer to SWPM 20-74-11 as an

accepted procedure.

2 Contact, Socket CTA0165 (CTA-0165) 6

M39029-1-101 2

(M39029/1-101)

3 Contact, Pin

4 Contact, Socket BACC47CN1S 15

5 Splice BACT12C12 2

Sleeve D436-39 2

6 Airplanes WA261-WA266, WB051-WB082.

7 End Cap 324485 1

8 Contact, Pin BACC47CN2A 5

Refer to SWPM 20-10-11 as an

accepted procedure.

9 Identification Tape 280W5110-10202 1

Refer to SWPM 20-10-11 as an

accepted procedure.

10 Identification Tape 280W5110-10203 1

Refer to SWPM 20-10-11 as an

accepted procedure.

11 Identification Tape 280W5110-10302 1

Refer to SWPM 20-10-11 as an

accepted procedure.

12 Identification Tape 280W5110-10404 1

Refer to SWPM 20-10-11 as an

accepted procedure.

13 Identification Tape 280W5110-10405 1

Refer to SWPM 20-10-11 as an

accepted procedure.

14 Identification Tape 280W5110-10403 1

Refer to SWPM 20-10-11 as an

accepted procedure.

15 Identification Tape 280W5110-10402 1

FIGURE 1: CHANGE THE AIRPLANE WIRING - GROUP 1

(SHEET 4 OF 4)

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BOEING SERVICE BULLETIN 777-24-0077
This Figure applies only to: Group 1, Configuration 1.

FIGURE 2: FLIGHT DECK - AIRPLANE WIRE ROUTING

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 777-24-0077
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for each airplane.

STEP TASK NAME PART NUMBER QTY NOTES

Make the changes to wire bundle W1052

in accordance with FIGURE 1. Use the

straps as necessary. Wire bundle

W1052 has a separation code RM2 and

a tie color brown. Refer to SWPM 20-10-

19 as an accepted procedure.

1 Install Wires 280W5110-102W 1

Use: Strap BACS38K1B -

Strap BACS38K2B -

FIGURE 2: FLIGHT DECK - AIRPLANE WIRE ROUTING

(SHEET 2 OF 2)

Export Controlled ECCN: 9E991 - BOEING

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Original Issue: August 21, 2003

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BOEING SERVICE BULLETIN 777-24-0077
This Figure applies only to: Group 1, Configuration 1.

FIGURE 3: MAIN EQUIPMENT CENTER - AIRPLANE WIRE ROUTING

(SHEET 1 OF 6)

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 777-24-0077
FIGURE 3: MAIN EQUIPMENT CENTER - AIRPLANE WIRE ROUTING

(SHEET 2 OF 6)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: August 21, 2003

Revision 4 October 17, 2012 777-24-0077

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BOEING SERVICE BULLETIN 777-24-0077
FIGURE 3: MAIN EQUIPMENT CENTER - AIRPLANE WIRE ROUTING

(SHEET 3 OF 6)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: August 21, 2003

Revision 4 October 17, 2012 777-24-0077

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BOEING SERVICE BULLETIN 777-24-0077
FIGURE 3: MAIN EQUIPMENT CENTER - AIRPLANE WIRE ROUTING

(SHEET 4 OF 6)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: August 21, 2003

Revision 4 October 17, 2012 777-24-0077

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BOEING SERVICE BULLETIN 777-24-0077
FIGURE 3: MAIN EQUIPMENT CENTER - AIRPLANE WIRE ROUTING

(SHEET 5 OF 6)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: August 21, 2003

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BOEING SERVICE BULLETIN 777-24-0077
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for each airplane.

STEP TASK NAME PART NUMBER QTY NOTES

Make the changes to wire bundle

W4236 in accordance with FIGURE 1.

Use the straps as necessary. Wire

bundle W4236 has a separation code

NN2 and a tie color white. Refer to

SWPM 20-10-19 as an accepted procedure.

1 Install Wires 280W5110-105W 1

Use: Strap BACS38K1 -

Make the changes to wire bundle

W6120 in accordance with FIGURE 1.

Use the straps as necessary. Wire

bundle W6120 has a separation code

LM2 and a tie color yellow. Refer to

SWPM 20-10-19 as an accepted procedure.

2 Install Wires 280W5110-103W 1

Use: Strap BACS38K1E -

Make the changes to wire bundle

W6220 in accordance with FIGURE 1.

Use the straps as necessary. Wire

bundle W6220 has a separation code

RM1 and a tie color brown. Refer to

SWPM 20-10-19 as an accepted procedure.

3 Install Wires 280W5110-104W 1

Use: Strap BACS38K1B -

Strap BACS38K2B -

FIGURE 3: MAIN EQUIPMENT CENTER - AIRPLANE WIRE ROUTING

(SHEET 6 OF 6)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: August 21, 2003

Revision 4 October 17, 2012 777-24-0077

51 of 51

BOEING SERVICE BULLETIN 777-24-0077