Commercial

Airplane

Group

767

Service Bulletin

Number: 767-28-0034 Revision Transmittal Sheet Date: July 1, 1993

Revision 3: March 14, 1996

ATA System: 2822

SUBJECT: FUEL - DISTRIBUTION - DUAL CROSSFEED VALVE INSTALLATION

This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

Federal Aviation Administration (FAA) Airworthiness Directive 88-21-03, Amendment 39-6077, is related to

this service bulletin.

No more work is necessary on airplanes changed as shown in Revision 2 of this service bulletin.

SUMMARY

This revision is sent to make these changes:

- Change statement "airplanes with EICAS computers S242N701-408 or previous dash number" on page

104 to "airplanes with EICAS computers S242N701-408 or previous 400 series dash number" for

clarification.

- Add instructions to cover the right fuel jettison nomenclature on the filler patch for airplanes without fuel

jettison system on page 86.

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

of important changes.

Pages with a revision number and date, but no vertical lines, have no important changes.

REVISION HISTORY

Initial Release: July 1, 1993

Revision 1: February 24, 1994

Revision 2: May 4, 1995

Revision 3: March 14, 1996

BOEING COMMERCIAL AIRPLANE GROUP P.O. BOX 3707 SEATTLE, WASHINGTON 98124-2207

Commercial

Airplane

Group

767

Service Bulletin

Number: 767-28-0034 Summary Date: July 1, 1993

Revision 3: March 14, 1996

ATA System: 2822

SUBJECT: FUEL - DISTRIBUTION - DUAL CROSSFEED VALVE INSTALLATION

BACKGROUND

This service bulletin will improve airplane reliability

and provide an alternative means of compliance with

Airworthiness Directive 88-21-03, Amendment

39-6077 requirement to recycle the crossfeed valve

at the end of the Extended Range Operations

(EROPS) flight.

A second fuel crossfeed valve is added to provide a

redundant path of fuel from a main fuel tank to an

opposite engine. In addition, the DC pump/N2 logic

system is deleted to reduce the circuit complexity.

In-service experience has shown that the system is

not necessary.

ACTION (PRR B12221 and PRR B12221-1)

3 On Groups 1-9, 12, 15, 16, 20 airplanes, do these

steps:

- Remove the fuel crossfeed valve, fuel isolation

valve in the left auxiliary tank and install cover

plates

- Install support brackets and two fuel crossfeed

valves in the center wing tank.

3 On Groups 10, 11, 13, 14, 17-19 airplanes, do

these steps:

- Remove the isolation valve in the left auxiliary

tank and install a cover plate

- Install support bracket and a second fuel

crossfeed valve in the center wing tank.

3 Replace the crossfeed fuel tubes and APU fuel

tubes

3 Install relays in the P33 panel

3 Install circuit breakers in P11 panel

3 Make a modification to the E8 rack, P5, P11, P33,

P36, P37 panel wiring and interconnection wiring

between panels

3 Replace the fuel management panel in P5 Panel.

COMPLIANCE

No compliance time is specified.

EFFECTIVITY

All 767 airplanes line position 1 through 430

MANPOWER

Airplanes

Total

Man-hours

Elapsed Time

(Hours)

Groups 1-9, 12,

15-16, 20

302 77

Groups 10,11, 13,

14, 17-19

274 70

MATERIAL INFORMATION

See the service bulletin.

BOEING COMMERCIAL AIRPLANE GROUP P.O. BOX 3707 SEATTLE, WASHINGTON 98124-2207 Summary Page 1 of 2
BOEING SERVICE BULLETIN 767-28-0034

COVER PLATE

VALVE AND INSTALL A

REMOVE THE APU ISOLATION

WIRING

INTERCONNECTING

MODIFY THE

AND TWO FUEL CROSSFEED VALVES

ONE FUEL CROSSFEED VALVE

-INSTALL SUPPORT BRACKETS

- INSTALL A COVER PLATE

- REMOVE THE FUEL CROSSFEED VALVE

ON GROUPS 1-9, 12, 15, 16,

18-20 AIRPLANES:

BREAKERS MANAGEMENT PANEL

-INSTALL CIRCUIT

P11 PANEL:

-MODIFY WIRING

E8 RACK:

P37 PANEL:

-MODIFY WIRING

ON GROUPS 10,11,13,14, 17-19 AIRPLANES:

-INSTALL A SUPPORT BRACKET AND

AIRPLANES:

-MODIFY WIRING

P36 PANEL:

-MODIFY WIRING

-REPLACE THE FUEL

P5 PANEL:

P33 PANEL:

-MODIFY WIRING

-INSTALL RELAYS

FUEL TUBES

FUEL TUBES AND APU

REPLACE THE CROSSFEED

ON GROUPS 1-9, 12, 15, 16, 20

A73832

Jul 1/93

REV 3: Mar 14/96 Summary Page 2 of 2
Commercial

Airplane

Group

767

Service Bulletin

Number: 767-28-0034

Date: July 1, 1993

Revision 3: March 14, 1996

ATA System: 2822

SUBJECT: FUEL - DISTRIBUTION - DUAL CROSSFEED VALVE INSTALLATION

I. PLANNING INFORMATION

A. Effectivity

1. Airplanes

Refer to Service Bulletin Index Document D6-24T001, Part 3 for Airplane Variable Number,

Line Number, and Serial Number data.

An equivalent change is on subsequent production airplanes. Refer to PRR B12221 and

PRR B12221-1 for data about these changes.

IDENTIFICATION BY CUSTOMER, CUSTOMER CODE, GROUP AND VARIABLE NUMBER

AIR ALGERIE (ALG)

3 VK131-VK133

AIR CANADA (ACN)

1 VA701-VA702 VB201

2 VA703-VA717 VB202

3 VA718-VA719

AIR CHINA GROUP (BEJ)

2 VE064-VE065 VE083-VE084

4 VK161

6 VE085

7 VE086

AIR EUROPE ITALY SPA (EIY)

14 VN682

AIR FRANCE (AFA)

13 VF101-VF102 VN631 VN632 VN633

AIR MAURITIUS LTD. (MAU)

2 VF001-VF002

AIR NEW ZEALAND, LTD. (ANZ)

1 VB001

2 VB002 VB323-VB324 VE101-VE103

13 VN651-VN652

AIR SEYCHELLES LTD. (ASY)

3 VF051

Jul 1/93 767-28-0034

REV 3: Mar 14/96 Page 1 of 132
BOEING SERVICE BULLETIN 767-28-0034

AIR ZIMBABWE (ZMB)

7 VF061

13 VF062

ALL NIPPON AIRWAYS CO. LTD. (ANA)

2 VB101-VB125 VK081-VK090

3 VK091-VK097 VN191-VN192

13 VN193

20 VK098-VK099

AMERICAN AIRLINES, INC. (AAL)

1 VA501-VA505

2 VA506-VA530 VN001-VN015

13 VN016-VN020

ANSETT AUSTRALIA (ANS)

1 VB051-VB054

2 VB055 VB322

ANSETT WORLDWIDE AVIATION SERVICES (AWW)

13 VF092

ASIANA AIRLINES (AAR)

3 VK141-VK142

13 VN751-VN753

AVIANCA (AVI)

5 VN152

7 VE171-VE172

BIRGENAIR (BIR)

2 VE041

BRITANNIA AIRWAYS, INC. (BRI)

2 VB321 VB325-VB327

3 VB328-VB330

20 VB331-VB332

BRITISH AIRWAYS (BAB)

3 VN111-VN115

13 VN116-VN124 VN130-VN132

CANADIAN AIRLINES INTERNATIONAL LTD. (CDI)

15 VN051-VN056

16 VN057-VN058

17 VN059-VN061

CHINA SOUTHERN AIR GROUP (GUN)

17 VN062-VN064

CONDOR/CARGO TECHNIK GMBH (CDF)

14 VN683

Jul 1/93 767-28-0034

REV 3: Mar 14/96 2
BOEING SERVICE BULLETIN 767-28-0034

DELTA AIR LINES, INC. (DAL)

1 VA301-VA308

2 VA309-VA315 VK031-VK045

3 VK046-VK048

11 VN251-VN260

20 VK049-VK054

EGYPTAIR (EGP)

2 VE021-VE023

7 VN211-VN212

EL AL ISRAEL AIRLINES, LTD. (ELA)

2 VB281-VB284

ETHIOPIAN AIRLINES, CORP. (ETH)

2 VE001-VE003

EVA AIRWAYS CORPORATION (EVA)

13 VN471-VN472

GE CAPITAL AVIATION SERVICES, INC. (GEH)

12 VL002

13 VN551

GULF AIR (GUL)

7 VL003-VL006

13 VN301-VN306

JAPAN AIRLINES (JAL)

2 VB372-VB373 VK021-VK022

3 VK010-VK011

15 VK001-VK008

16 VK009

JAPAN TRANSOCEAN AIR CO., LTD. (SWL)

2 VB371

LAN-CHILE S.A. (LAN)

3 VE118

13 VF093 VN376 VN531

18 VF091

LAUDA AIR LUFTFAHRT AG (LAL)

9 VL011

LAUDA AIR S.P.A. (LDI)

14 VN671

LINHAS AEREAS DE MOZAMBIQUE (LAM)

11 VF161

LOT POLISH AIRLINES (LOT)

3 VF041-VF042

13 VN291

Jul 1/93 767-28-0034

REV 3: Mar 14/96 3
BOEING SERVICE BULLETIN 767-28-0034

LUFTTRANSPORT SUED AG AND CO. (LTS)

6 VN171

7 VN172-VN173

13 VN381

MARTINAIR HOLLAND N.V. (MTH)

8 VN221

14 VN223-VN224 VN672

19 VN222

QANTAS AIRWAYS, LTD. (QAN)

2 VE061-VE063 VE066-VE069

15 VN081-VN084

16 VN085

17 VN086-VN092

ROYAL BRUNEI (RBA)

13 VN371-VN372

SCANDINAVIAN AIRLINES SYSTEM (SAS)

5 VN151 VN153-VN155

10 VF071 VN156-VN158 VN163-VN168

SPANAIR (SPP)

13 VN541-VN542

TACA INTERNATIONAL AIRLINES, INC. (TAC)

2 VB401 VE116

13 VN731

TRANS WORLD AIRLINES, INC. (TWA)

1 VA801-VA805

2 VA806-VA810 VB301-VB302

13 VN536-VN537

14 VN681

TRANSBRASIL AIRLINES INC. (TBL)

2 VB251-VB253 VE104 VE117

10 VF072

12 VL001

13 VN532

UNITED AIR LINES, INC. (UAL)

1 VA002-VA012

2 VA013-VA020

13 VN491-VN497

USAIR, INC. (USA)

2 VE141-VE146

3 VE147-VE149

20 VE150-VE151

VARIG AIRLINES (VAR)

2 VE121-VE126

13 VN233-VN234

18 VN231-VN232

Jul 1/93 767-28-0034

REV 3: Mar 14/96 4
BOEING SERVICE BULLETIN 767-28-0034

IDENTIFICATION BY VARIABLE NUMBER

GROUP 1

VA002-VA012 VA301-VA308 VA501-VA505 VA701-VA702 VA801-VA805 VB001

VB051-VB054 VB201

GROUP 2

VA013-VA020 VA309-VA315 VA506-VA530 VA703-VA717 VA806-VA810 VB002

VB055 VB101-VB125 VB202 VB251-VB253 VB281-VB284 VB301-VB302

VB321-VB327 VB371-VB373 VB401 VE001-VE003 VE021-VE023 VE041-VE043

VE061-VE069 VE083-VE084 VE101-VE104 VE116-VE117 VE121-VE126 VE141-VE146

VF001-VF002 VK021-VK022 VK031-VK045 VK081-VK090 VN001-VN015

GROUP 3

VA718-VA719 VB328-VB330 VE118 VE147-VE149 VF041-VF042 VF051

VK010-VK011 VK046-VK048 VK091-VK097 VK131-VK133 VK141-VK142 VN111-VN115

VN191-VN192 VN241

GROUP 4

VK161

GROUP 5

VN151-VN155

GROUP 6

VE085 VN171

GROUP 7

VE086 VE171-VE172 VF061 VL003-VL006 VN172-VN173 VN211-VN212

GROUP 8

VN221

GROUP 9

VL011

GROUP 10

VF071-VF072 VN156-VN158 VN163-VN168

GROUP 11

VF161 VN251-VN260

GROUP 12

VL001-VL002

GROUP 13

VF062 VF092-VF093 VF101-VF102 VN016-VN020 VN116-VN124 VN130-VN132

VN193 VN233-VN234 VN291 VN301-VN306 VN371-VN372 VN376

VN381 VN471-VN472 VN491-VN497 VN531-VN532 VN536-VN537 VN541-VN542

VN551 VN631-VN633 VN651-VN652 VN731 VN751-VN753

GROUP 14

VN223-VN224 VN671-VN672 VN681-VN683

GROUP 15

VK001-VK008 VN051-VN056 VN081-VN084

Jul 1/93 767-28-0034

REV 3: Mar 14/96 5
BOEING SERVICE BULLETIN 767-28-0034

GROUP 16

VK009 VN057-VN058 VN085

GROUP 17

VN059-VN064 VN086-VN092

GROUP 18

VF091 VN231-VN232

GROUP 19

VN222

GROUP 20

VB331-VB332 VE150-VE151 VK049-VK054 VK098-VK099

2. Spares

None

Jul 1/93 767-28-0034

REV 3: Mar 14/96 6
BOEING SERVICE BULLETIN 767-28-0034

B. Reason

This service bulletin will improve airplane reliability and provide an alternative means of compliance

with Airworthiness Directive 88-21-03, Amendment 39-6077 requirement to recycle the crossfeed

valve at the end of the Extended Range Operations (EROPS) flight.

A second fuel crossfeed valve is added to provide a redundant path of fuel from a main fuel tank to

an opposite engine. In addition, the DC pump/N2 logic system is deleted to reduce the circuit

complexity. In-service experience has shown that the system is not necessary.

Revision 1 is sent to show removal of wire W198-504-22 in P37 panel and correct name of the fuel

pump pressure switches.

Revision 2 is sent to make these changes:

- Add supplemental kit and instruction to install bracket to support APU fuel tube for airplanes in

Groups 1-9, 12, 15-16, 18-19.

- Add new figure for the crossfeed valve support bracket installation for airplanes in Groups 4

and 20.

- Add instructions to remove/install bulkhead fitting in the side-of-body rib for installation of tube

assembly 343T0010-65 for all airplanes.

- Move airplanes VL003-VL006 from Group 13 to Group 7 and airplanes VB331-VB332,

VE150-VE151, VK049-VK054, VK098-VK099 to new added Group 20.

- Add instructions to cap and stow wire W142-10S-22 in P33 panel for airplanes with EICAS

computer S242N701-408 or previous dash number.

- Add new functional test for airplanes with upgraded EICAS computers.

Revision 3 is sent to clarify EICAS computer usage statement and to add instructions to cover the

right fuel jettison nomenclature on the filler patch for airplanes without fuel jettison system.

Jul 1/93 767-28-0034

REV 3: Mar 14/96 7
BOEING SERVICE BULLETIN 767-28-0034

C. Description

- On Groups 1-9, 12, 15, 16, 20 airplanes,

+ The existing fuel crossfeed valve, fuel isolation valve in the left auxiliary tank are removed and

cover plates are installed

+ Support brackets and two fuel crossfeed valves are installed in the center wing tank

- On Groups 10, 11, 13, 14, 17-19 airplanes,

+ The existing isolation valve in the left auxiliary tank is removed and a cover plate is installed

+ Support bracket and a second fuel crossfeed valve are installed in the center wing tank.

- The crossfeed fuel tubes and APU fuel tubes are replaced

- Relays are installed in the P33 panel

- Circuit breakers are installed in P11 panel

- A modification is made to the E8 rack, P5, P11, P33, P36, P37 panel wiring and interconnection

wiring between panels

- The fuel management panel is replaced in P5 Panel.

Revision 1 - No more work is necessary on airplanes changed by the initial release of this

servicebulletin.

Revision 2 - More work is necessary to install bracket to support APU fuel tube on airplanes in

Groups 1-9, 12, 15-16, 18-19 changed by the Revision 1 of this service bulletin.

Revision 3 - No more work is necessary on airplanes changed by Revision 2 of this service

bulletin.

Airplane effectivity is divided into 20 groups because of the differences in airplane configuration.

D. Compliance

No compliance time is specified.

E. Approval

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

specified in this service bulletin comply with the applicable Federal Aviation Regulations (FAR) and

are FAA approved. The service bulletin and the FAA approval were based on the airplane in its

original Boeing delivery configuration or as modified by other FAA 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.

The FAA has approved the changes as an alternative to those specified in Airworthiness Directive

(AD) 88-21-03, Amendment 39-6077.

Jul 1/93 767-28-0034

REV 3: Mar 14/96 8
BOEING SERVICE BULLETIN 767-28-0034

F. Manpower

The data below shows an estimate of the man-hours necessary to do this modification for each

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

with operator man-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.

Airplanes Task Number of Persons Man-Hours

Elapsed Time

(Hours)

Groups 1-9,

12, 15, 16, 20

Prepare 4 24 6

Open Access 4 20 5

Change 4 220 55

Close Access 4 20 5

Test 3 18 6

TOTAL FOR AIRPLANE 302 77

Groups 10,

11, 13, 14,

17-19

Prepare 4 24 6

Open Access 4 20 5

Change 4 192 48

Close Access 4 20 5

Test 3 18 6

TOTAL FOR AIRPLANE 274 70

Jul 1/93 767-28-0034

REV 3: Mar 14/96 9
BOEING SERVICE BULLETIN 767-28-0034

G. Material - Price and Availability

Boeing can supply the kits shown in Paragraph II.A., Parts Necessary For Each Airplane, as

shown below. If there is a limit to the quantity of available kits, a supply sequence is given by

Spares. More kits become available as shown in the Reorder Lead Time (ROLT). ROLT is

calculated from the date Boeing gets the purchase order.

Kit Number Name Date

Available

Quantity ROLT

Weeks

Unit Price thru

Jan 7/94

015T1353-1 (a) Top Kit, Dual Crossfeed Valve

Installation

Jul 2/93 7 43 $ 32,814

Jul 28/93 3

Aug 4/93 5

Aug 11/93 9

015T1353-2 (a) Replacement Kit for -1 - - 57 $ 33,844

015T1353-3 (b) Top Kit, Dual Crossfeed Valve

Installation

Jul 2/93 12 43 $ 30,443

Jul 28/93 3

Agu 4/93 5

Agu 11/93 1

015T1353-4 (c) Top Kit, Dual Crossfeed Valve

Installation

Jul 2/93 2 43 $ 32,814

015T1353-5 (d) Top Kit, Dual Crossfeed Valve

Installation

Jul 2/93 2 43 $ 30,443

015T1353-6 (b) Replacement Kit for -3 - - 47 $ 29,606

015T1353-7 (e) Top Kit, Dual Crossfeed Valve

Installation

Jul 2/93 1 43 $ 30,838

015T1353-8 (a) Supplemental Kit - - 47 $ 245

015T1353-9 (b) Supplemental Wire Kit - - 39 $ 171

Date: July 1, 1993

(a) Use for Groups 1-9, 12, 20 airplanes. Supplemental kit 015T1353-8 should be ordered in

addition to top kit 015T1353-1 if operator already has top kit 015T1353-1. Replacement kit

015T1353-2 should be ordered if operator has not ordered top kit 015T1353-1.

(b) Use for Groups 10, 11, 13, 14 airplanes. Supplemental wire kit 015T1353-9 should be ordered

in addition to top kit 015T1353-3 if operator already has top kit 015T1353-3. Replacement kit

015T1353-6 should be ordered if operator has not ordered top kit 015T1353-3.

Jul 1/93 767-28-0034

REV 3: Mar 14/96 10
BOEING SERVICE BULLETIN 767-28-0034

G. (Continued)

(c) Use for Groups 15, 16 airplanes

(d) Use for Groups 17 airplanes

(e) Use for Groups 18, 19 airplanes.

The kits are subject to the terms and conditions of the Boeing standard purchase order

acknowledgment. After the Unit Price date, new price and ROLT data is applicable. Prices are in

United States Dollars. Terms: Net 30 days.

Send purchase orders and letters about the supply data to the Director of Spares and refer to this

service bulletin number.

H. Special Tools - Price and Availability

The 767 Structural Repair Manual Subject 51-40-09 specifies cold working tools and sleeves

necessary to do the work identified in this service bulletin. These tools are available from industry

sources as necessary.

Engineering, service, and a kit of cold working tools made for this change are available from

Fatigue Technology, Inc. or West Coast Industries, Inc.

Refer To:

FTI Kit Number: FTI-767-28-0034-1

Fatigue Technology, Inc.

P.O. Box C-88388

Seattle, WA 98188

Phone Number (206) 246-2010

Fax (206) 244-988

Refer To:

WCI Kit Number: WCI-767-28-0034

West Coast Industries, Inc.

14900 Whitman Avenue North

Seattle, WA 98133-6532

Phone Number (206) 365-7513

Fax (206) 365-7483

I. Weight and Balance

Change in Weight

(Pounds)

Airplane

Model

Change in Moment

(Pound-Inches)

+8

767-200 +4800

767-300 +3832

Jul 1/93 767-28-0034

REV 3: Mar 14/96 11
BOEING SERVICE BULLETIN 767-28-0034

J. References

1. Existing Data:

- Engineering Change Memos PRR B12221 and PRR B12221-1

- 767 Maintenance Manual Subjects 24-22-00, 28-00-00, 28-11-00, 28-22-02, 28-22-07,

28-22-12, 28-25-04, 32-00-15, 51-20-01, 51-31-01

- 767 Structural Repair Manual Subject 51-40-09

- 767 Wiring Diagrams 24-54-71, 28-22-11, 28-22-31, 28-25-11, 28-25-31, 28-42-12, 28-42-31

- Boeing Standard Wiring Practices Manual 20-10-11, 20-10-14, 20-10-15, 20-10-19, 20-20-00,

20-90-11

- Boeing Standard Overhaul Practices Manual 20-50-05, 20-50-10, 20-50-12

- FAA Airworthiness Directive 88-21-03, Amendment 39-6077

2. Data supplied with this service bulletin:

None

K. Publications Changed

Publication Chapter-Section

767 Maintenance Manual 12-11, 28-22, 28-25, 31-41

767 Operations Manual 02.02, 02.15, 03.11, 04.11, 05.20, 15.10, 15.20

767 Wiring Diagram Manual 24-54, 28-22, 28-25, 28-42

767 Ramp Maintenance Manual 28-22, 31-41

767 Illustrated Parts Catalog 28-22

767 Fault Isolation Manual 31-01, 31-41

767 Fault Reporting Manual 28, 31

Component Maintenance Manual 28-22

L. Electrical Load Data

Not changed

Jul 1/93 767-28-0034

REV 3: Mar 14/96 12
BOEING SERVICE BULLETIN 767-28-0034

II. MATERIAL INFORMATION

A. Parts Necessary For Each Airplane

1. To get the kits shown below, refer to Paragraph I.G., Material - Price and Availability.

NOTE: The top kit is divided into subkits. One top kit and operator supplied materials specified

in Paragraph II.A.2., Parts and Materials Supplied by the Operator, are necessary for

each airplane. Supplemental kit 015T1353-8 should be ordered in addition to top kit

015T1353-1 if operator already has top kit 015T1353-1. Replacement kit 015T1353-2

should be ordered if operator has not ordered top kit 015T1353-1. Supplemental wire kit

015T1353-9 should be ordered in addition to top kit 015T1353-3 if operator already has

top kit 015T1353-3. Replacement kit 015T1353-6 should be ordered if operator has not

ordered top kit 015T1353-3.

015T1353 - TOP KIT, DUAL CROSSFEED VALVE INSTALLATION

-1 -2 -3 -4 -5 -6 -7

Quantity Part Number Name

- . . . . . . 015T1353-1 (a) Top Kit, Dual Crossfeed Valve

Installation

. - . . . . . 015T1353-2 (a) Replacement Kit for -1

. . - . . . . 015T1353-3 (b) Top Kit, Dual Crossfeed Valve

Installation

. . . - . . . 015T1353-4 (c) Top Kit, Dual Crossfeed Valve

Installation

. . . . - . . 015T1353-5 (d) Top Kit, Dual Crossfeed Valve

Installation

. . . . . - . 015T1353-6 (b) Replacement Kit for -3

. . . . . . - 015T1353-7 (e) Top Kit, Dual Crossfeed Valve

Installation

1 1 . 1 . . . 111T1016-6 Kit, Rear Spar Rework

1 1 1 1 1 1 1 111T1016-8 Kit, Rear Spar Rework

1 1 1 . . 1 1 233T0027-1 Kit, Dual Crossfeed Panel Installation

. . . 1 1 . . 233T0027-2 Kit, Dual Crossfeed Panel Installation

1 1 1 1 1 1 1 233T5103-111 Kit, P11 Circuit Breaker Installation

1 1 1 1 1 1 1 284T1351-116 Kit, P33 Panel Equipment Installation

1 1 . 1 . . . 289T0202-1 Kit, Wire

. . 1 . 1 1 1 289T0202-2 Kit, Wire

1 1 1 1 1 1 1 289T0256-1 Kit, Supplemental Wire

1 1 1 1 1 1 1 287T0110-16 Kit, Seal Replacement

1 1 1 1 1 1 1 287T0011-2 Clamp

1 1 1 1 1 1 1 287T0011-4 Clamp

1 1 . 1 . . . 343T0005-1 Kit, Dual Crossfeed Valve Installation

. . . . . . 1 343T0005-2 Kit, Dual Crossfeed Valve Installation

. . 1 . 1 1 . 343T0005-3 Kit, Dual Crossfeed Valve Installation

Jul 1/93 767-28-0034

REV 3: Mar 14/96 13
BOEING SERVICE BULLETIN 767-28-0034

015T1353 - TOP KIT, DUAL CROSSFEED VALVE INSTALLATION

-1 -2 -3 -4 -5 -6 -7

Quantity Part Number Name

. 1 . 1 . . 1 MS29513-235 O-Ring

. 1 . 1 . . 1 344T0076-1 Bracket

. 1 . 1 . . 1 BACB30MY10K15X Bolt

. 2 . 2 . . 2 BACB30MY10K25X Bolt

. 3 . 3 . . 3 BACN10WM5 Seal Nut

1 1 . 1 . . 1 343T0062-1 Kit, Tubing Installation

1 1 1 1 1 1 1 343T0062-2 Kit, Tubing Installation

1 1 1 1 1 1 1 343T0062-4 Kit, Tubing Installation

. 1 . 1 1 1 1 BACM15C3B Terminal Block

. 1 . 1 1 1 1 015T1353-10 Wire

. 1 . 1 . 1 1 MS29513-235 O-ring

015T1353 - TOP KIT, DUAL CROSSFEED VALVE INSTALLATION

-8 -9

Quantity Part Number Name

- . 015T1353-8 Kit, Supplemental

. - 015T1353-9 Kit, Wire Supplemental

1 . MS29513-235 O-Ring

1 . 344T0076-1 Bracket

1 . BACB30MY10K15X Bolt

2 . BACB30MY10K25X Bolt

3 . BACN10WM5 Seal Nut

1 1 015T1353-10 Wire

1 1 BACM15C3B Terminal Block

1 . MS29513-235 O-ring

Jul 1/93 767-28-0034

REV 3: Mar 14/96 14
BOEING SERVICE BULLETIN 767-28-0034

111T1016 - KIT, REAR SPAR REWORK

-6 -8

Quantity Part Number Name

- . 111T1016-6 Kit, Rear Spar Rework

. - 111T1016-8 Kit, Rear Spar Rework

1 1 111T1016-7 Mylar Template

1 1 111T1016-2 Doubler

1 1 111T1016-3 Doubler

1 1 343T0021-19 Bracket

1 1 343T0021-20 Bracket

1 1 343T0046-2 Bracket

7 8 BACB30MY12K10Y Bolt

3 4 BACB30MY12K12Y Bolt

1 . BACB30MY10K10Y Bolt

1 . BACB30MY10K12Y Bolt

27 27 BACB30VT6K4 Bolt

11 11 BACB30VT6K6 Bolt

3 3 BACR15FT3AD5 Rivet

38 38 BACW10BP3P Washer

2 . BACW10BP52P Washer

10 12 BACW10BP62P Washer

38 38 MS21042L3 Nut

2 . MS21042L5 Nut

10 12 MS21042L6 Nut

Jul 1/93 767-28-0034

REV 3: Mar 14/96 15
BOEING SERVICE BULLETIN 767-28-0034

233T0027 - KIT, DUAL CROSSFEED PANEL INSTALLATION

-1 -2

Quantity Part Number Name

- . 233T0027-1 Kit, Dual Crossfeed Panel Installation

. - 233T0027-2 Kit, Dual Crossfeed Panel Installation

1 . 233T3100-438 Fuel Management Panel Assembly

. 1 233T3100-439 Fuel Management Panel Assembly

233T3100 - KIT, FUEL MANAGEMENT PANEL ASSEMBLY

-438 -439

Quantity Part Number Name

- . 233T3100-438 Fuel Management Panel Assembly

. - 233T3100-439 Fuel Management Panel Assembly

1 1 S233T100-1106 Lightplate

1 . 233T3235-21 Fuel Management Panel

. 1 233T3235-23 Fuel Management Panel

233T5103 - KIT, P11 CIRCUIT BREAKER INSTALLATION

-111

Quantity Part Number Name

- 233T5103-111 Kit, P11 Circuit Breaker Installation

1 233T5103-109 Filler Patch

1 233T5103-110 Filler Patch

1 BACB29B7S2 Bus Bar Assembly

2 BACC18Z02R Circuit Breaker

1 BACC18Z1R Circuit Breaker

284T1351 - KIT, P33 PANEL EQUIPMENT INSTALLATION

-116

Quantity Part Number Name

- 284T1351-116 Kit, P33 Panel Equipment Installation

1 284T0378-176 Bracket Assembly

2 BACR13CE2 Relay

1 BAC27TEX4891 Marker

4 NAS1738E4-2 Rivet

Jul 1/93 767-28-0034

REV 3: Mar 14/96 16
BOEING SERVICE BULLETIN 767-28-0034

343T0005 - KIT, DUAL CROSSFEED VALVE INSTALLATION

-1 -2 -3

Quantity Part Number Name

- . . 343T0005-1 Kit, Dual Crossfeed Valve Installation

. - . 343T0005-2 Kit, Dual Crossfeed Valve Installation

. . - 343T0005-3 Kit, Dual Crossfeed Valve Installation

1 1 1 S343T003-40

(optional

S343T003-15)

Valve Body

2 2 1 S343T003-26 Adapter Shaft

1 . . 112T1081-1 Cover Plate

1 1 1 112T1081-8 Cover Plate

1 1 . 343T0046-15 Fuel Feed Bracket

1 1 . 69B92447-5 Spacer

10 10 4 AN960D10L Washer

8 8 4 AN960JD10L Washer

16 8 8 AN960JD416L Washer

8 8 4 BACB30NM4K5 Bolt

1 1 . BACC10EW32A Clamp Strap

1 1 . BACC10EW32B Clamp Saddle

2 2 1 BACJ40A20-3 Bonding Jumper

8 8 . BACR15FT6KE7C Rivet

6 6 2 MS21042L3 Nut

8 4 4 MS21042L4 Nut

8 8 4 MS24677-15 Screw

2 2 1 MS29513-151 O-Ring

4 4 2 NAS1801-3-8 Screw

2 2 . NAS1801-3-32 Screw

8 8 4 NAS620-8 Washer

8 4 4 NAS6603-8 Screw

4 4 1 NAS6604-12 Screw

4 4 . NAS6604-13 Screw

Jul 1/93 767-28-0034

REV 3: Mar 14/96 17
BOEING SERVICE BULLETIN 767-28-0034

343T0062 - KIT, TUBING INSTALLATION

-1 -2 -4

Quantity Part Number Name

- . . 343T0062-1 Kit, Tubing Installation

. - . 343T0062-2 Kit, Tubing Installation

. . - 343T0062-4 Kit, Tubing Installation

. 1 . 343T0004-1 Tube Assembly

. 1 . 343T0004-5 Tube Assembly

1 . . 343T0010-65 Tube Assembly

. 1 . 343T0010-86 Tube Assembly

. 1 . 343T0010-87 Tube Assembly

. . 1 346T0010-12 Tube Assembly

1 5 . AN735D32 Bonding Clamp

. . 2 AN735D12 Bonding Clamp

6 22 8 AN960D10L Washer

4 12 . AN960JD10L washer

1 4 . AS1712D32 Coupling

1 5 . BACC10EW32A Clamp Strap

1 5 . BACC10EW32B Clamp Saddle

. . 1 BACJ40A20-8 Bonding Jumper

1 4 . BACJ40A20-6 Bonding Jumper

6 22 5 BACN10JC3 Nut

. . 4 MS29513-212 O-Ring

. . 2 MS29513-216 O-Ring

3 14 . MS29513-330 O-Ring

5 12 . NAS1801-3-7 Screw

. . 5 NAS1801-3-9 Screw

3 12 . NAS1801-3-10 Screw

. . 1 73511-12 Elbow

Jul 1/93 767-28-0034

REV 3: Mar 14/96 18
BOEING SERVICE BULLETIN 767-28-0034

289T0202 - KIT, WIRE

-1 -2

Quantity Part Number Name

- . 289T0202-1 Kit, Wire

. - 289T0202-2 Kit, Wire

1 1 289T0202-101 Wire (W0042)

1 1 289T0202-102 Wire (W0044)

1 1 289T0202-103 Wire (W0062)

1 1 289T0202-104 Wire (W0066)

1 1 289T0202-105 Wire (W0070)

1 1 289T0202-106 Wire (W0142)

1 1 289T0202-107 Wire (W0144)

1 1 289T0202-108 Wire (W0176)

1 1 289T0202-109 Wire (W0184)

1 1 289T0202-110 Wire (W0192)

1 1 289T0202-111 Wire (W0198)

1 1 289T0202-112 Wire (W0452)

1 . 289T0202-113 Wire (W0454)

. 1 289T0202-114 Wire (W0454)

1 1 289T0202-115 Wire (W0460)

1 1 289T0202-116 Wire (W0464)

1 1 289T0202-117 Wire (W0482)

1 1 289T0202-118 Wire (W0590)

1 . 289T0202-119 Wire (W0596)

1 1 289T0202-120 Wire (W0620)

1 1 289T0202-121 Wire (W0624)

1 1 289T0202-122 Wire (W0656)

1 1 289T0202-123 Wire (W0756)

1 1 289T0202-124 Wire (W1114)

1 1 289T0202-125 Wire (W1274)

1 1 289T0202-126 Wire (W0596)

1 1 289T0202-128 Wire (W1722)

1 1 289T0202-129 Wire (W1730)

1 1 289T0202-130 Wire (W2000)

1 1 289T0202-131 Wire (W2002)

1 1 289T0202-132 Wire (W0032)

1 1 289T0202-133 (f) Sleeve

1 . 289T0202-134 (g) Sleeve

2 1 289T0202-135 (h) Convoluted Tubing

4 2 MS27488-16 Seal Plug

Jul 1/93 767-28-0034

REV 3: Mar 14/96 19
BOEING SERVICE BULLETIN 767-28-0034

289T0202 - KIT, WIRE

-101 -103 -104 -105 -106

Quantity Part Number Name

-.... 289T0202-101 Kit, Wire (W0042)

. - . . . 289T0202-103 Kit, Wire (W0062)

. . - . . 289T0202-104 Kit, Wire (W0066)

. . . - . 289T0202-105 Kit, Wire (W0070)

....- 289T0202-106 Kit, Wire (W0142)

1.... 289T0202-101W Wire (W0042)

. 1 . . . 289T0202-103W Wire (W0062)

. . 1 . . 289T0202-104W Wire (W0066)

. . . 1 . 289T0202-105W Wire (W0070)

. . . .1 289T0202-106W Wire (W0142)

. . . .1 BACC45FN14-12S9 Receptacle (D05890)

. 1 . . . BACM15C3A Terminal Block

. . . .1 BACS16AF1 Relay Socket

. . 2 . . BACC47CN1A Pin Contact

2 10 5 3 7 BACC47CP1A Socket Contact

. . . 1 . BACC47CP3T Socket Contact

. . . .3 BACC47DE7 Terminal Block Contact

.6767 M39029/11-145 Terminal Block Contact

. . . .8 BACC47ER1 Relay Socket Contact

2.... BACT12AR203 Lug

. . . .1 289T0202-10601 Identification Tape

. . . .1 289T0202-10602 Identification Tape

Jul 1/93 767-28-0034

REV 3: Mar 14/96 20
BOEING SERVICE BULLETIN 767-28-0034

289T0202 - KIT, WIRE

-107 -109 -110 -111 -113

Quantity Part Number Name

-.... 289T0202-107 Kit, Wire (W0144)

. - . . . 289T0202-109 Kit, Wire (W0184)

. . - . . 289T0202-110 Kit, Wire (W0192)

. . . - . 289T0202-111 Kit, Wire (W0198)

....- 289T0202-113 Kit, Wire (W0454)

1.... 289T0202-107W Wire

. 1 . . . 289T0202-109W Wire

. . . 1 . 289T0202-111W Wire

. . . .1 289T0202-113W Wire

. . . .1 BACC45FN14-12S9 Receptacle (D05890)

1 . . . BACS16AF1 Relay Socket

. . . .1 710AS011M-1412-62A Adapter

4 2 . 1 . BACC47CN1A Pin Contact

. . . .4 BACC47CN2 Pin Contact

. 2 . 1 . BACC47CP1A Socket Contact

. . . 2 5 BACC47CP2T Socket Contact

. . . 1 . BACC47DE4 Terminal Block Contact

3.... BACC47DE7 Terminal Block Contact

9.... M39029/11-145 Terminal Block Contact

8.... BACC47ER1 Relay Socket Contact

. . . 1 . BACC47DJ1 Relay Socket Contact

. . . .1 BACT12M-4 Lug

. . . 1 BACC10HF14 Clamp

1.... 289T0202-10701 Identification Tape

. 1 . . . 289T0202-10901 Identification Tape

. 1 . . . 289T0202-10902 Identification Tape

. 1 . . . 289T0202-10903 Identification Tape

. . 1 . . 289T0202-11001 Identification Tape

. . 1 . . 289T0202-11002 Identification Tape

. . . 1 . 289T0202-11101 Identification Tape

. . . 1 . 289T0202-11102 Identification Tape

. . . 1 . 289T0202-11103 Identification Tape

. . . 1 . 289T0202-11104 Identification Tape

. . . 1 . 289T0202-11105 Identification Tape

. . . 1 . 289T0202-11105 Identification Tape

. . . .1 289T0202-11301 Identification Tape

Jul 1/93 767-28-0034

REV 3: Mar 14/96 21
BOEING SERVICE BULLETIN 767-28-0034

289T0202 - KIT, WIRE

-114 -115 -119 -121 -123

Quantity Part Number Name

-.... 289T0202-114 Kit, Wire (W0454)

. - . . . 289T0202-115 Kit, Wire (W0460)

. . - . . 289T0202-119 Kit, Wire (W0596)

. . . - . 289T0202-121 Kit, Wire (W0624)

....- 289T0202-123 Kit, Wire (W0756)

. 1 . . . 289T0202-115W Wire

. . 1 . 289T0202-121W Wire

. . . .1 289T0202-123W Wire

. 1 . . . BACC63BP14A7SNL Plug (D20058)

. 1 . . . 710AS011M-1412-62A Adapter

. 10 4 BACC47CN1A Pin Contact

. 4 . . BACC47CN2 Pin Contact

. . . 4 BACC47CP1A Socket Contact

. . 1 . . BACC47CP2T Socket Contact

. 1 . . BACC47DE7 Terminal Block Contact

. 1 . . . BACT12M-4 Lug

. . . 1 . 324484 End Cap

1.... 289T0202-11401 Identification Tape

. 1 . . . 289T0202-11501 Identification Tape

Jul 1/93 767-28-0034

REV 3: Mar 14/96 22
BOEING SERVICE BULLETIN 767-28-0034

289T0202 - KIT, WIRE

-125 -129 -130 -132

Quantity Part Number Name

- . . . 289T0202-125 Kit, Wire (W1274)

. - . . 289T0202-129 Kit, Wire (W1730)

. . - . 289T0202-130 Kit, Wire (W2000)

. . . - 289T0202-132 Kit, Wire (W0032)

.... 289T0202-113 Kit, Wire (W0454)

1 . . . 289T0202-125W Wire

. 1 . . 289T0202-129W Wire

. . 1 289T0202-130W Wire

. . . 1 289T0202-132W Wire

. 1 . . MTC100-JB2-S11-T16 Wafer-Insert B (D6230PR)

. 2 . . D-436-36 Splice Insulation Sleeving

. . 1 . 284T1015-2 Cable Assembly - Insert B

. 2 . . BACC47CN1A Pin Contact

. . 38 . BACC47EF1 Pin Contact

4 . . . BACC47CP2T Socket Contact

. . 4 . BACC47DE4 Terminal Block Contact

1 . . . BACC47DE7 Terminal Block Contact

. . . 1 BACT12AC15 Lug

. . . 1 BACT12AL15 Lug

1 . . . 324485 End Cap

1 . . . 289T0202-12501 Identification Tape

Jul 1/93 767-28-0034

REV 3: Mar 14/96 23
BOEING SERVICE BULLETIN 767-28-0034

289T0256 - KIT, SUPPLEMENTAL WIRE

-1 -101 -102

Quantity Part Number Name

- . . 289T0256-1 Kit, Supplemental Wire

1 - . 289T0256-101 Kit, Wire (W0044)

1 . - 289T0256-102 Kit, Wire (W0070)

1 . . 289T0256-103 (i) Sleeve

. 1 . 289T0256-101W Wire

. . 1 289T0256-102W Wire

. 1 1 BACC47CP1A Socket Contact

. 1 . BACT12AR223 Lug

. . 1 289T0256-10201 Identification Tape (D01384)

. . 1 289T0256-10202 Identification Tape (D05010P)

. 1 BACC47CN1A Pin Contact

287T0110 - KIT, SEAL REPLACEMENT

-16

Quantity Part Number Name

- 287T0110-16 (k) Kit, Seal Replacement

1 287T0110-20 Tape

1 BACS45A18 Coiled Spacer

1 BACS45A20 Coiled Spacer

2 BACS45A213 Seal Fitting - Half

1 BACS45A221 Coiled Spacer

1 BACS45A23 Coiled Spacer

1 BACS45A24 Coiled Spacer

2 NAS1801-3-10 Screw

Jul 1/93 767-28-0034

REV 3: Mar 14/96 24
BOEING SERVICE BULLETIN 767-28-0034

A. (Continued)

2. Parts and Materials Supplied by the Operator:

Quantity Part Number (Specification) Name

10 Ounces BAC5719 TYPEII (j) Chemical Coating

10 Ounces BMS10-20 TYPE2 (j) Resistant Finish

20 Ounces BMS5-26 (j) Sealant

20 Ounces BMS5-95 (j) Sealant

10 Feet MS20995NC32 (j) Lockwire

1 S242N701-409 EICAS Computer

1 BACT12AC15 Lug

(a) Use for Groups 1-9, 12, 20 airplanes. Replacement kit 015T1353-2 is equivalent to the

combination of top kit 015T1353-1 and supplemental kit 015T1353-8.

(b) Use for Groups 10, 11, 13, 14 airplanes. Replacement kit 015T1353-6 is equivalent to the

combination of top kit 015T1353-3 and supplemental wire kit 015T1353-9.

(c) Use for Groups 15, 16 airplanes

(d) Use for Groups 17 airplanes

(e) Use for Group 18, 19 airplanes

(f) Sleeve RT876 , 0.125 inch diameter, yellow, 15 feet long

(g) Sleeve TFE-2X, size 8, 15 feet long

(h) Convoluted tubing MS48-3-8, 15 feet long

(i) Sleeve RT876 , 0.125 inch diameter, yellow, 8 feet long

(j) See Qualified Parts List (QPL) in the Boeing Material Specification (BMS) manual for supplier

data.

(k) Kit has more part than are necessary for installation. Discard parts that are not used or keep

the parts for spares.

Jul 1/93 767-28-0034

REV 3: Mar 14/96 25
BOEING SERVICE BULLETIN 767-28-0034

B. Parts Necessary to Change Spares

None

C. Special Tools and Equipment

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

and overhaul tools in manuals shown in Paragraph I.J., References, may be necessary. Examine

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

D. Existing Parts Accountability

The parts shown below are changed by this service bulletin. The Quantity is the number of parts

changed on each airplane. Components or subassembly parts are indented. The Quantity of the

indented part is the number of parts used on the next higher assembly.

Existing Part Number Name Quantity RUC New Part Number PNC RC

S343T003-4 or -17 (a)(b) Adapter Shaft 2 DIS S343T003-26 S A

S343T003-4 or -17 (c) Adapter Shaft 1 DIS S343T003-26 S A

S343T003-6 or -10 Valve Body 1 DIS S343T003-15 S A

343T0010-31 (a) Fuel Tube Assembly 1 DIS 343T0010-65 S A

343T0010-29 or -53 Fuel Tube Assembly 1 DIS 343T0010-87 S A

343T0010-26 or -54 Fuel Tube Assembly 1 DIS 343T0004-1 and -5 S A

343T0010-30 Fuel Tube Assembly 1 DIS 343T0010-86 S A

346T0010-5 Fuel Tube Assembly 1 DIS - S B

346T0047-1 Fuel Tube Assembly 1 DIS 346T0010-12 S A

233T3100-148 Fuel Control Panel

Assembly

- - 233T3100-438 - -

.S233T100-1060 or

-6043

Lightplate 1 DIS .S233T100-1106 S A

.233T3235-7 Fuel Management

Panel

1 DIS .233T3235-21 S A

or

233T3100-189 Fuel Control Panel

Assembly

- - 233T3100-438 - -

.S233T100-1060 or

-6043

Lightplate 1 DIS .S233T100-1106 S A

.233T3235-10 Fuel Management

Panel

1 DIS .233T3235-21 S A

Jul 1/93 767-28-0034

REV 3: Mar 14/96 26
BOEING SERVICE BULLETIN 767-28-0034

(Continued)

Existing Part Number Name Quantity RUC New Part Number PNC RC

or

233T3100-251 Fuel Control Panel

Assembly

- - 233T3100-438 - -

.S233T100-6043 Lightplate 1 DIS .S233T100-1106 S A

.233T3235-12 Fuel Management

Panel

1 DIS .233T3235-21 S A

or

233T3100-277 Fuel Control Panel

Assembly

- - 233T3100-438 - -

.S233T100-6043 Lightplate 1 DIS .S233T100-1106 S A

.233T3235-15 Fuel Management

Panel

1 DIS .233T3235-21 S A

or

233T3100-293 Fuel Control Panel

Assembly

- - 233T3100-439 - -

.S233T100-6043 Lightplate 1 DIS .S233T100-1106 S A

.233T3235-13 Fuel Management

Panel

1 DIS .233T3235-23 S A

(a) Applicable to Groups 1-9, 12, 15, 16, 20 airplanes

(b) Applicable to Groups 18, 19 airplanes

(c) Applicable to Groups 10, 11, 13, 14, 17 airplanes

RUC Recommend Use Code

DIS - Discard the part.

- Keep the part if there are other uses for it.

PNC Part Number Code

S - This is the new equivalent or replacement part number.

- To get a new part, use this part number in your order.

RC Replacement Code

A - Do not use the existing part to replace the new or changed part.

B - This part is removed from the airplane. This part has no replacement.

Jul 1/93 767-28-0034

REV 3: Mar 14/96 27
BOEING SERVICE BULLETIN 767-28-0034

BLANK PAGE

Jul 1/93 767-28-0034

REV 3: Mar 14/96 28
BOEING SERVICE BULLETIN 767-28-0034

III. ACCOMPLISHMENT INSTRUCTIONS

NOTES:

1. The paragraphs identified with a letter give the general work instructions and the necessary

tests. The instructions identified with numbers on the figures give the recommended sequence

of steps.

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

- All 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

- The hole dimensions for standard solid rivets are given in 767 Structural Repair Manual

Chapter 51

- The torque limits to tighten nuts and bolts are given in 767 Structural Repair Manual Chapter

51.

3. Refer to 767 Structural Repair Manual Chapter 51 for alternative fasteners.

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

5. Install all wiring as specified in Boeing Standard Wiring Practices Manual, Chapter 20, Section

20-10-11.

A. Remove the electrical power from the airplane circuits as specified in the 767 Maintenance Manual

Subject 24-22-00.

B. Empty and purge the left and center auxiliary tank as shown in 767 Maintenance Manual Subject

28-11-00.

C. Open the landing gear doors and install the door locks as specified in 767 Maintenance Manual

Subject 32-00-15.

D. Remove the engine fuel crossfeed valve as follows:

- On Groups 1-9, 12, 15, 16, 18-20 airplanes, use Figure 1.

- On Groups 10, 11, 13, 14, 17 airplanes, use Figure 2.

E. Remove the APU isolation valve as shown in Figure 3.

Jul 1/93 767-28-0034

REV 3: Mar 14/96 29
BOEING SERVICE BULLETIN 767-28-0034

F. Install the valve support brackets as follows:

1. On Groups 1-3, 5-9, 12, 15, 16 airplanes, use Figure 4.

2. On Groups 10, 11, 13, 14, 17-19 airplanes, use Figure 5.

3. On Groups 4, 20 airplanes, use Figure 6.

G. Install the cover plate as shown in Figure 7.

H. On Groups 1-9, 12, 15-16, 18-20, install bracket as shown in Figure 8.

I. Replace the crossfeed fuel tubes as shown in Figure 9.

J. Install the APU fuel tubes as shown in Figure 10.

K. Install the crossfeed valves as shown in Figure 11.

L. Clean and examine the fuel tank as specified in the 767 Maintenance Manual Subject 28-11-00.

M. Install the circuit breaker in P11 panel as shown in Figure 12.

N. Make a modification to the P33 panel as shown in Figure 13.

O. Make a modification to P5 panel wiring and interconnection wiring as shown in Figure 14.

P. Make a modification to the E8 rack wiring as follows:

- On Groups 1-4, 6-9, 12-20 airplanes, use Figure 15

- On Groups 5, 10, 11 airplanes, use Figure 16.

Q. Make a modification to P11 panel wiring and interconnection wiring as shown in Figure 17.

R. Make a modification to P33 panel wiring as shown in Figure 18.

S. Make a modification to P36 panel wiring as shown in Figure 19.

T. Make a modification to P37 panel wiring as shown in Figure 20.

U. On Groups 1-3, 5-7, 9, 11-13, 15-18, 20, make a modification to P50 panel wiring as shown in

Figure 21.

Jul 1/93 767-28-0034

REV 3: Mar 14/96 30
BOEING SERVICE BULLETIN 767-28-0034

V. Make a modification to E8 and P33, P37 panels interconnection wiring as shown in Figure 22.

W. Make a modification to P33 panel and wheel well area interconnection wiring as follows:

- On Group 1 airplanes, use Figure 23.

- On Groups 2, 6, 9, 12, 15 airplanes, use Figure 24.

- On Groups 3-5, 7, 8, 10, 11, 13, 14, 16-20, use Figure 25.

X. Make a modification to P33 and P61 panels interconnection wiring as shown in Figure 26.

Y. Make a modification to P36, P37, and P61 panels interconnection wiring as shown in Figure 27.

Z. Make a modification to wheel well area wiring as follows:

- On all airplanes, use Figure 28.

- On Groups 1-9, 12, 15, 16, 18-20 airplanes, use Figure 29.

- On Groups 10, 11,13, 14, 17 airplanes, use Figure 30.

AA. Make a wiring installation as shown in Figure 31.

AB. Replace the fuel control panel as shown in Figure 32.

AC. Do a pressure leak check of the fuel lines and fitting as specified in the 767 Maintenance Manual

Subject 28-22-07.

AD. Do the fuel tank leak check as specified in the 767 Maintenance Manual Subject 28-11-00.

Jul 1/93 767-28-0034

REV 3: Mar 14/96 31
BOEING SERVICE BULLETIN 767-28-0034

AE. Do the fuel crossfeed valve/fuel system pressure verification functional test as follows:

Use this test procedure if airplane has EICAS computers S242N701-408, -603, -703, -801, or

previous dash number.

1. Make sure that both the AFT and FWD crossfeed valves are closed and no flow bars appear on

P5 panel.

2. Make sure that these circuit breakers are open:

Circuit

Breaker

Number

Grid Name Panel

C1069 M20 BATTERY POWER FUEL FWD CROSSFEED VLV P11

C1070 M21 BATTERY POWER FUEL AFT CROSSFEED VLV P11

C1071 D36 CROSSFEED IND P11

3. Close the circuit breaker C1069 and make sure that the forward crossfeed valve light goes off.

4. Close the circuit breaker C1070 make sure that the aft crossfeed valve light goes off and the

"FUEL CROSSFEED" message disappears on EICAS display.

5. Close circuit breaker C1071 and make sure that these messages are shown on EICAS display.

"L FUEL SYS PRESS"

"R FUEL SYS PRESS"

6. Open circuit breaker C1071.

7. Disconnect the R CTR pump pressure switch connector (D2808) located at right wing rear spar

station R257. Make sure the followings:

- These messages are shown on EICAS display.

"R AFT FUEL PUMP"

"R FWD FUEL PUMP"

"L AFT FUEL PUMP"

"L FWD FUEL PUMP"

- These messages are not shown on EICAS display.

"R FUEL SYS PRESS"

"L FUEL SYS PRESS"

Jul 1/93 767-28-0034

REV 3: Mar 14/96 32
BOEING SERVICE BULLETIN 767-28-0034

8. Close circuit breaker C1071. Make sure the followings:

- These messages are shown on EICAS display.

"L FUEL SYS PRESS"

"R FWD FUEL PUMP"

"R AFT FUEL PUMP"

- These messages are not shown on EICAS display.

"R FUEL SYS PRESS"

"L FWD FUEL PUMP"

"L AFT FUEL PUMP"

9. Push the FWD crossfeed valve switch (flow bar appears) and make sure the followings:

- These actions occur:

+ The forward valve manual override handle moves from CLOSED to OPEN position

+ The flow bar on the switch comes on

+ Disagreement light on the switch is on while the valve is in transit.

- These messages are shown on EICAS display.

"R FWD FUEL PUMP"

"R AFT FUEL PUMP"

"L FWD FUEL PUMP"

"L AFT FUEL PUMP"

- These messages are not shown on EICAS display.

"L FUEL SYS PRESS"

"R FUEL SYS PRESS"

10. Push the AFT crossfeed valve switch (flow bar appears) and make sure these actions occur:

+ The aft valve manual override handle moves from CLOSED to OPEN position

+ The flow bar on the switch comes on

+ Disagreement light on the switch is on while the valve is in transit.

Jul 1/93 767-28-0034

REV 3: Mar 14/96 33
BOEING SERVICE BULLETIN 767-28-0034

11. Push the FWD crossfeed valve switch (flow bar disappears) and make sure the followings:

- These actions occur:

+ The forward valve manual override handle moves from OPEN to CLOSED position

+ The flow bar on the switch goes off

+ Disagreement light on the switch is on while the valve is in transit.

- These messages are shown on EICAS display.

"R FWD FUEL PUMP"

"R AFT FUEL PUMP"

"L FWD FUEL PUMP"

"L AFT FUEL PUMP"

- These messages are not shown on EICAS display.

"L FUEL SYS PRESS"

"R FUEL SYS PRESS"

12. Push the AFT crossfeed valve switch (flow bar disappears) and make sure these actions occur:

+ The aft valve manual override handle moves from OPEN to CLOSED position

+ The flow bar on the switch goes off

+ Disagreement light on the switch is on while the valve is in transit.

13. Connect the R CTR pump pressure switch connector (D2808).

14. Disconnect the L CTR pump pressure switch connector (D2806) located at left wing rear spar

station L258. Make sure the followings:

- These messages are shown on EICAS display.

"R FUEL SYS PRESS"

"L AFT FUEL PUMP"

"L FWD FUEL PUMP"

- These messages are not shown on EICAS display.

"L FUEL SYS PRESS"

"R AFT FUEL PUMP"

"R FWD FUEL PUMP"

Jul 1/93 767-28-0034

REV 3: Mar 14/96 34
BOEING SERVICE BULLETIN 767-28-0034

15. Push the FWD fuel crossfeed switch (flow bar appears). Make sure the followings:

- These messages are shown on EICAS display.

"R AFT FUEL PUMP"

"R FWD FUEL PUMP"

"L AFT FUEL PUMP"

"L FWD FUEL PUMP"

- These messages are not shown on EICAS display.

"R FUEL SYS PRESS"

"L FUEL SYS PRESS"

16. Push the AFT fuel crossfeed switch (flow bar appears).

17. Push the FWD fuel crossfeed switch (flow bar disappears). Make sure the followings:

- These messages are shown on EICAS display.

"R AFT FUEL PUMP"

"R FWD FUEL PUMP"

"L AFT FUEL PUMP"

"L FWD FUEL PUMP"

- These messages are not shown on EICAS display.

"R FUEL SYS PRESS"

"L FUEL SYS PRESS"

18. Push the AFT fuel crossfeed switch (flow bar disappears).

19. Connect the L CTR pump pressure switch connector (D2806).

20. Open circuit breaker C1070.

21. Disconnect the R CTR pump pressure switch connector (D2808). Make sure the followings:

- These messages are shown on EICAS display.

"L FUEL SYS PRESS"

"R FWD FUEL PUMP"

"R AFT FUEL PUMP"

"FUEL CROSSFEED"

- These messages are not shown on EICAS display.

"R FUEL SYS PRESS"

"L FWD FUEL PUMP"

"L AFT FUEL PUMP"

Jul 1/93 767-28-0034

REV 3: Mar 14/96 35
BOEING SERVICE BULLETIN 767-28-0034

22. Connect the R CTR pump pressure switch connector (D2808).

23. Disconnect the L CTR pump pressure switch connector (D2806). Make sure the followings:

- These messages are shown on EICAS display.

"R FUEL SYS PRESS"

"FUEL CROSSFEED"

"L FWD FUEL PUMP"

"L AFT FUEL PUMP"

- These messages are not shown on EICAS display.

"L FUEL SYS PRESS"

"R FWD FUEL PUMP"

"R AFT FUEL PUMP"

24. Open circuit breaker C1071. Make sure the followings:

- These messages are shown on EICAS display.

"R FUEL SYS PRESS"

"FUEL CROSSFEED"

"L FWD FUEL PUMP"

"L AFT FUEL PUMP"

- These messages are not shown on EICAS display.

"L FUEL SYS PRESS"

"R FWD FUEL PUMP"

"R AFT FUEL PUMP"

25. Close circuit breaker C1071.

26. Connect the L CTR pump pressure switch connector (D2806).

27. Push the FWD fuel crossfeed switch (flow bar appears).

28. Close circuit breaker C1070.

29. Open circuit breaker C1069.

Jul 1/93 767-28-0034

REV 3: Mar 14/96 36
BOEING SERVICE BULLETIN 767-28-0034

30. Disconnect the R CTR pump pressure switch connector (D2808). Make sure the followings:

- These messages are shown on EICAS display.

"L FUEL SYS PRESS"

"R FWD FUEL PUMP"

"R AFT FUEL PUMP"

"FUEL CROSSFEED"

- These messages are not shown on EICAS display.

"R FUEL SYS PRESS"

"L FWD FUEL PUMP"

"L AFT FUEL PUMP"

31. Connect the R CTR pump pressure switch connector (D2808).

32. Disconnect the L CTR pump pressure switch connector (D2806). Make sure the followings:

- These messages are shown on EICAS display.

"R FUEL SYS PRESS"

"L FWD FUEL PUMP"

"L AFT FUEL PUMP"

"FUEL CROSSFEED"

- These messages are not shown on EICAS display.

"R FWD FUEL PUMP"

"R AFT FUEL PUMP"

"L FUEL SYS PRESS"

33. Open circuit breaker C1071. Make sure the followings:

- These messages are shown on EICAS display.

"R FUEL SYS PRESS"

"FUEL CROSSFEED"

"L FWD FUEL PUMP"

"L AFT FUEL PUMP"

- These messages are not shown on EICAS display.

"L FUEL SYS PRESS"

"R FWD FUEL PUMP"

"R AFT FUEL PUMP"

34. Close circuit breaker C1071.

35. Connect the L CTR pump pressure switch connector (D2806).

36. Close circuit breaker C1069.

Jul 1/93 767-28-0034

REV 3: Mar 14/96 37
BOEING SERVICE BULLETIN 767-28-0034

Use this test procedure if airplane has upgraded EICAS computers S242N701-409, -604, -704, or

-802.

1. Make sure that both the AFT and FWD crossfeed valves are closed and no flow bars appear on

P5 panel.

2. Make sure that these circuit breakers are open:

Circuit

Breaker

Number

Grid Name Panel

C1069 M20 BATTERY POWER FUEL FWD CROSSFEED VLV P11

C1070 M21 BATTERY POWER FUEL AFT CROSSFEED VLV P11

C1071 D36 CROSSFEED IND P11

3. Close the circuit breaker C1069 and make sure that the forward crossfeed valve light goes off

and the "FWD FUEL X-FEED" message disappears on EICAS display.

4. Close the circuit breaker C1070 make sure that the aft crossfeed valve light goes off and the

"AFT FUEL X-FEED" message disappears on EICAS display.

5. Close circuit breaker C1071 and make sure that these messages are shown on EICAS display.

"L FUEL SYS PRESS"

"R FUEL SYS PRESS"

6. Open circuit breaker C1071.

7. Disconnect the R CTR pump pressure switch connector (D2808) located at right wing rear spar

station R257. Make sure the followings:

- These messages are shown on EICAS display.

"R AFT FUEL PUMP"

"R FWD FUEL PUMP"

"L AFT FUEL PUMP"

"L FWD FUEL PUMP"

- These messages are not shown on EICAS display.

"R FUEL SYS PRESS"

"L FUEL SYS PRESS"

Jul 1/93 767-28-0034

REV 3: Mar 14/96 38
BOEING SERVICE BULLETIN 767-28-0034

8. Close circuit breaker C1071. Make sure the followings:

- These messages are shown on EICAS display.

"L FUEL SYS PRESS"

"R FWD FUEL PUMP"

"R AFT FUEL PUMP"

- These messages are not shown on EICAS display.

"R FUEL SYS PRESS"

"L FWD FUEL PUMP"

"L AFT FUEL PUMP"

9. Push the FWD crossfeed valve switch (flow bar appears) and make sure the followings:

- These actions occur:

+ The forward valve manual override handle moves from CLOSED to OPEN position

+ The flow bar on the switch comes on

+ Disagreement light on the switch is on while the valve is in transit.

- These messages are shown on EICAS display.

"R FWD FUEL PUMP"

"R AFT FUEL PUMP"

"L FWD FUEL PUMP"

"L AFT FUEL PUMP"

- These messages are not shown on EICAS display.

"L FUEL SYS PRESS"

"R FUEL SYS PRESS"

10. Push the AFT crossfeed valve switch (flow bar appears) and make sure these actions occur:

+ The aft valve manual override handle moves from CLOSED to OPEN position

+ The flow bar on the switch comes on

+ Disagreement light on the switch is on while the valve is in transit.

Jul 1/93 767-28-0034

REV 3: Mar 14/96 39
BOEING SERVICE BULLETIN 767-28-0034

11. Push the FWD crossfeed valve switch (flow bar disappears) and make sure the followings:

- These actions occur:

+ The forward valve manual override handle moves from OPEN to CLOSED position

+ The flow bar on the switch goes off

+ Disagreement light on the switch is on while the valve is in transit.

- These messages are shown on EICAS display.

"R FWD FUEL PUMP"

"R AFT FUEL PUMP"

"L FWD FUEL PUMP"

"L AFT FUEL PUMP"

- These messages are not shown on EICAS display.

"L FUEL SYS PRESS"

"R FUEL SYS PRESS"

12. Push the AFT crossfeed valve switch (flow bar disappears) and make sure these actions occur:

+ The aft valve manual override handle moves from OPEN to CLOSED position

+ The flow bar on the switch goes off

+ Disagreement light on the switch is on while the valve is in transit.

13. Connect the R CTR pump pressure switch connector (D2808).

14. Disconnect the L CTR pump pressure switch connector (D2806) located at left wing rear spar

station L258. Make sure the followings:

- These messages are shown on EICAS display.

"R FUEL SYS PRESS"

"L AFT FUEL PUMP"

"L FWD FUEL PUMP"

- These messages are not shown on EICAS display.

"L FUEL SYS PRESS"

"R AFT FUEL PUMP"

"R FWD FUEL PUMP"

Jul 1/93 767-28-0034

REV 3: Mar 14/96 40
BOEING SERVICE BULLETIN 767-28-0034

15. Push the FWD fuel crossfeed switch (flow bar appears). Make sure the followings:

- These messages are shown on EICAS display.

"R AFT FUEL PUMP"

"R FWD FUEL PUMP"

"L AFT FUEL PUMP"

"L FWD FUEL PUMP"

- These messages are not shown on EICAS display.

"R FUEL SYS PRESS"

"L FUEL SYS PRESS"

16. Push the AFT fuel crossfeed switch (flow bar appears).

17. Push the FWD fuel crossfeed switch (flow bar disappears). Make sure the followings:

- These messages are shown on EICAS display.

"R AFT FUEL PUMP"

"R FWD FUEL PUMP"

"L AFT FUEL PUMP"

"L FWD FUEL PUMP"

- These messages are not shown on EICAS display.

"R FUEL SYS PRESS"

"L FUEL SYS PRESS"

18. Push the AFT fuel crossfeed switch (flow bar disappears).

19. Connect the L CTR pump pressure switch connector (D2806).

20. Open circuit breaker C1070.

21. Disconnect the R CTR pump pressure switch connector (D2808). Make sure the followings:

- These messages are shown on EICAS display.

"L FUEL SYS PRESS"

"R FWD FUEL PUMP"

"R AFT FUEL PUMP"

"AFT FUEL X-FEED"

- These messages are not shown on EICAS display.

"R FUEL SYS PRESS"

"L FWD FUEL PUMP"

"L AFT FUEL PUMP"

"FWD FUEL X-FEED"

22. Connect the R CTR pump pressure switch connector (D2808).

Jul 1/93 767-28-0034

REV 3: Mar 14/96 41
BOEING SERVICE BULLETIN 767-28-0034

23. Disconnect the L CTR pump pressure switch connector (D2806). Make sure the followings:

- These messages are shown on EICAS display.

"R FUEL SYS PRESS"

"L AFT FUEL PUMP"

"L FWD FUEL PUMP"

"AFT FUEL X-FEED"

- These messages are not shown on EICAS display.

"L FUEL SYS PRESS"

"FWD FUEL X-FEED"

"R FWD FUEL PUMP"

"R AFT FUEL PUMP"

24. Open circuit breaker C1071. Make sure the followings:

- These messages are shown on EICAS display.

"R FWD FUEL PUMP"

"R AFT FUEL PUMP"

"L FWD FUEL PUMP"

"L AFT FUEL PUMP"

"AFT FUEL X-FEED"

- These messages are not shown on EICAS display.

"R FUEL SYS PRESS"

"L FUEL SYS PRESS"

"FWD FUEL X-FEED"

25. Close circuit breaker C1071.

26. Connect the L CTR pump pressure switch connector (D2806).

27. Push the FWD fuel crossfeed switch (flow bar appear).

28. Disconnect the R CTR pump pressure switch connector (D2808). Make sure the followings:

- These messages are shown on EICAS display.

"R FWD FUEL PUMP"

"R AFT FUEL PUMP"

"L FWD FUEL PUMP"

"L AFT FUEL PUMP"

"AFT FUEL X-FEED"

- These messages are not shown on EICAS display.

"L FUEL SYS PRESS"

"R FUEL SYS PRESS"

"FWD FUEL X-FEED"

29. Connect the R CTR pump pressure switch connector (D2808).

Jul 1/93 767-28-0034

REV 3: Mar 14/96 42
BOEING SERVICE BULLETIN 767-28-0034

30. Disconnect the L CTR pump pressure switch connector (D2806). Make sure the followings:

- These messages are shown on EICAS display.

"L FWD FUEL PUMP"

"L AFT FUEL PUMP"

"R FWD FUEL PUMP"

"R AFT FUEL PUMP"

"AFT FUEL X-FEED"

- These messages are not shown on EICAS display.

"L FUEL SYS PRESS"

"R FUEL SYS PRESS"

"FWD FUEL X-FEED"

31. Connect the L CTR pump pressure switch connector (D2806).

32. Push the FWD fuel crossfeed switch (flow bar disappears).

33. Close circuit breaker C1070.

34. Open circuit breaker C1069.

35. Disconnect the R CTR pump pressure switch connector (D2808). Make sure the followings:

- These messages are shown on EICAS display.

"L FUEL SYS PRESS"

"R FWD FUEL PUMP"

"R AFT FUEL PUMP"

"FWD FUEL X-FEED"

- These messages are not shown on EICAS display.

"R FUEL SYS PRESS"

"L FWD FUEL PUMP"

"L AFT FUEL PUMP"

"AFT FUEL X-FEED"

36. Connect the R CTR pump pressure switch connector (D2808).

37. Disconnect the L CTR pump pressure switch connector (D2806). Make sure the followings:

- These messages are shown on EICAS display.

"R FUEL SYS PRESS"

"L FWD FUEL PUMP"

"L AFT FUEL PUMP"

"FWD FUEL X-FEED"

- These messages are not shown on EICAS display.

"R FWD FUEL PUMP"

"R AFT FUEL PUMP"

"L FUEL SYS PRESS"

"AFT FUEL X-FEED"

Jul 1/93 767-28-0034

REV 3: Mar 14/96 43
BOEING SERVICE BULLETIN 767-28-0034

38. Open circuit breaker C1071. Make sure the followings:

- These messages are shown on EICAS display.

"FWD FUEL X-FEED"

"R FWD FUEL PUMP"

"R AFT FUEL PUMP"

"L FWD FUEL PUMP"

"L AFT FUEL PUMP"

- These messages are not shown on EICAS display.

"R FUEL SYS PRESS"

"L FUEL SYS PRESS"

"AFT FUEL X-FEED"

39. Close circuit breaker C1071.

40. Connect the L CTR pump pressure switch connector (D2806).

41. Push the AFT fuel crossfeed switch (flow bar appears).

42. Disconnect the R CTR pump pressure switch connector (D2808). Make sure the followings:

- These messages are shown on EICAS display.

"R FWD FUEL PUMP"

"R AFT FUEL PUMP"

"L FWD FUEL PUMP"

"L AFT FUEL PUMP"

"FWD FUEL X-FEED"

- These messages are not shown on EICAS display.

"L FUEL SYS PRESS"

"R FUEL SYS PRESS"

"AFT FUEL X-FEED"

43. Connect the R CTR pump pressure switch connector (D2808).

44. Disconnect the L CTR pump pressure switch connector (D2806). Make sure the followings:

- These messages are shown on EICAS display.

"L FWD FUEL PUMP"

"L AFT FUEL PUMP"

"R FWD FUEL PUMP"

"R AFT FUEL PUMP"

"FWD FUEL X-FEED"

- These messages are not shown on EICAS display.

"L FUEL SYS PRESS"

"R FUEL SYS PRESS"

"AFT FUEL X-FEED"

45. Connect the L CTR pump pressure switch connector (D2806).

Jul 1/93 767-28-0034

REV 3: Mar 14/96 44
BOEING SERVICE BULLETIN 767-28-0034

46. Push the AFT fuel crossfeed switch (flow bar disappears).

47. Close circuit breaker C1069.

AF. Do the operational test for the fuel pump and APU shutoff valves as follows:

1. Make sure that these circuit breakers are open:

Circuit Breaker

Number

Grid Name Panel

C0020 C4 APU START E6

C0372 G24 FUEL BOOST PUMP L FWD P6

C1052 D35 BATTERY POWER FUEL DC PUMP CONT P11

C1058 D34 BATTERY POWER FUEL DC PUMP PWR P11

C1063 E3 FUEL VALVE APU P6

C1391 B35 BATTERY POWER APU ALTN CONT P11

2. Push the BAT switch to the ON position

3. Rotate the STBY power switch to the AUTO position and make sure that the fault light on the M1

APU panel comes on

4. Close the circuit breaker C1063 and make sure that the fault light and the "APU FUEL VAL"

message on EICAS display goes off

5. Close the circuit breakers C0020, C1052, C1058, and C1391

CAUTION: DO NOT TURN THE APU CONTROL SWITCH TO THE "START" POSITION.

THE APU COULD START AND CAUSE DAMAGE.

DO NOT RUN THE DC PUMP AND L FWD PUMP FOR MORE THAN FIVE

MINUTES ON ANY 15 MINUTE PERIOD.

6. Rotate the APU control switch to ON position and make sure that these actions occur:

- DC fuel pump runs

- APU shutoff valve opens

- The fault light on the M1 panel is on while the valve is in transit

- The valve manual override handle moves from CLOSE to OPEN position

Jul 1/93 767-28-0034

REV 3: Mar 14/96 45
BOEING SERVICE BULLETIN 767-28-0034

7. Make sure that the L FWD pump switch is in the OFF position

8. Close the circuit breaker C0372 and make sure that the left forward boost pump runs and the

DC fuel pump stops

9. Open circuit breakers C1052, C0372 and make sure that the DC pump stops

10. Disconnect the connector D1566 on the DC pump pressure switch and connect a jumper wire

between pins 1 and 2. Make sure that the maintenance message "DC FUEL PUMP ON" is

shown on EICAS display.

11. Connect the connector D1566.

AG. Put the airplane back into the serviceable condition.

Jul 1/93 767-28-0034

REV 3: Mar 14/96 46
BOEING SERVICE BULLETIN 767-28-0034

FIGURE TABLE OF CONTENTS

Title Page

FIGURE 1. FUEL CROSSFEED VALVE REMOVAL - GROUPS 1-9, 12, 15,

16,18-20 AIRPLANES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49

FIGURE 2. FUEL CROSSFEED VALVE REMOVAL - GROUPS 10, 11, 13, 14,

17 AIRPLANES. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50

FIGURE 3. APU ISOLATION VALVE REMOVAL - ALL AIRPLANES. . . . . . . . . . . . . . 51

FIGURE 4. VALVE SUPPORT BRACKET INSTALLATION - GROUPS 1-3, 5-9,

12, 15, 16 AIRPLANES. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52

FIGURE 5. VALVE SUPPORT BRACKET INSTALLATION - GROUPS 10, 11,

13, 14, 17-19 AIRPLANES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57

FIGURE 6. VALVE SUPPORT BRACKET INSTALLATION - GROUPS 4, 20

AIRPLANES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 62

FIGURE 7. COVER PLATE INSTALLATION - ALL AIRPLANES . . . . . . . . . . . . . . . . . 69

FIGURE 8. APU FUEL TUBE SUPPORT BRACKET INSTALLATION -

GROUPS 1-9, 12, 15, 16, 18-20 AIRPLANES . . . . . . . . . . . . . . . . . . . . . . 71

FIGURE 9. CROSSFEED FUEL TUBE REPLACEMENT - ALL AIRPLANES . . . . . . . 74

FIGURE 10. APU FUEL TUBE INSTALLATION - ALL AIRPLANES. . . . . . . . . . . . . . . 80

FIGURE 11. CROSSFEED VALVE INSTALLATION - ALL AIRPLANES . . . . . . . . . . . 82

FIGURE 12. P11 PANEL MODIFICATION - ALL AIRPLANES . . . . . . . . . . . . . . . . . . . 84

FIGURE 13. P33 PANEL MODIFICATION - ALL AIRPLANES . . . . . . . . . . . . . . . . . . . 87

FIGURE 14. P5 PANEL WIRING AND INTERCONNECTION WIRING

MODIFICATION - ALL AIRPLANES. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 90

FIGURE 15. E8 RACK WIRING MODIFICATION - GROUPS 1-4, 6-9, 12-20

AIRPLANES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 94

FIGURE 16. E8 RACK WIRING MODIFICATION - GROUPS 5, 10, 11

AIRPLANES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 96

FIGURE 17. P11 PANEL WIRING AND INTERCONNECTION WIRING

MODIFICATION - ALL AIRPLANES. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 98

FIGURE 18. P33 PANEL WIRING MODIFICATION - ALL AIRPLANES. . . . . . . . . . . . 100

FIGURE 19. P36 PANEL WIRING MODIFICATION - ALL AIRPLANES. . . . . . . . . . . . 105

FIGURE 20. P37 PANEL WIRING MODIFICATION - ALL AIRPLANES. . . . . . . . . . . . 107

FIGURE 21. P50 PANEL WIRING MODIFICATION - GROUPS 1-3, 5-7, 9,

11-13, 15-18, 20 AIRPLANES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 110

FIGURE 22. E8 AND P33, P37 PANELS INTERCONNECTION WIRING

MODIFICATION - ALL AIRPLANES. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 111

Jul 1/93 767-28-0034

REV 3: Mar 14/96 47
BOEING SERVICE BULLETIN 767-28-0034

FIGURE TABLE OF CONTENTS (Continued)

Title Page

FIGURE 23. P33 PANEL AND WHEEL WELL AREA INTERCONNECTION

WIRING MODIFICATION - GROUP 1 AIRPLANES. . . . . . . . . . . . . . . . . . 112

FIGURE 24. P33 PANEL AND WHEEL WELL AREA INTERCONNECTION

WIRING MODIFICATION - GROUPS 2, 6, 9, 12, 15 AIRPLANES . . . . . . 114

FIGURE 25. P33 PANEL AND WHEEL WELL AREA INTERCONNECTION

WIRING MODIFICATION - GROUPS 3-5, 7, 8, 10, 11, 13, 14, 16-20

AIRPLANES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 116

FIGURE 26. P33 AND P61 PANEL INTERCONNECTION WIRING

MODIFICATION - ALL AIRPLANES. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 118

FIGURE 27. P36, P37 AND P61 PANELS INTERCONNECTION WIRING

MODIFICATION - ALL AIRPLANES. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 120

FIGURE 28. WHEEL WELL AREA WIRING MODIFICATION - ALL AIRPLANES . . . . 122

FIGURE 29. WHEEL WELL AREA WIRING MODIFICATION - GROUPS 1-9,

12, 15, 16, 18-20 AIRPLANES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 125

FIGURE 30. WHEEL WELL AREA WIRING MODIFICATION - GROUPS 10, 11,

13, 14, 17 AIRPLANES. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 127

FIGURE 31. WIRING INSTALLATION - ALL AIRPLANES . . . . . . . . . . . . . . . . . . . . . . 128

FIGURE 32. FUEL MANAGEMENT PANEL REPLACEMENT - ALL

AIRPLANES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 131

Jul 1/93 767-28-0034

REV 3: Mar 14/96 48
BOEING SERVICE BULLETIN 767-28-0034

1

2

3

IN THE FUEL TANK

REAR SPAR

INBD

UP

FWD

ENGINE FUEL CROSSFEED VALVE (TYPICAL)

A66967

The instruction numbers shown below agree with the numbers shown inside the circle symbols in the

figure.

1 Remove and keep the valve actuator S343T003-1, -14, -39, or -111 as specified in the 767 Maintenance

Manual Subject 28-22-12.

2 Remove valve body and adapter shaft as specified in the 767 Maintenance Manual Subject 28-22-02.

Keep the valve body S343T003-2 or -15 and hardwares.

3 Remove and discard the valve support bracket.

FIGURE 1. FUEL CROSSFEED VALVE REMOVAL - GROUPS 1-9, 12, 15, 16,18-20 AIRPLANES

Jul 1/93 SHEET 1 OF 1 767-28-0034

REV 3: Mar 14/96 49
BOEING SERVICE BULLETIN 767-28-0034

ENGINE FUEL CROSSFEED VALVE (TYPICAL)

REAR SPAR

CENTER WING

FWD

UP

INBD

1

REAR SPAR

A66999

The instruction numbers shown below agree with the numbers shown inside the circle symbols in the

figure.

1 Remove the valve body S343T003-15 from the fuel tube as specified in the 767 Maintenance

Manual Subject 28-22-02. Keep the valve body and hardwares.

FIGURE 2. FUEL CROSSFEED VALVE REMOVAL - GROUPS 10, 11, 13, 14, 17 AIRPLANES

Jul 1/93 SHEET 1 OF 1 767-28-0034

REV 3: Mar 14/96 50
BOEING SERVICE BULLETIN 767-28-0034

APU ISOLATION VALVE (TYPICAL)

OUTBD

UP

FWD

1

A67016

The instruction numbers shown below agree with the numbers shown inside the circle symbols in the

figure.

1 Remove the actuator and valve body as specified in the 767 Maintenance Manual Subject 28-25-04.

Keep the valve actuator S343T003-1, -14, -39, or -111 and hardwares.

FIGURE 3. APU ISOLATION VALVE REMOVAL - ALL AIRPLANES

Jul 1/93 SHEET 1 OF 1 767-28-0034

REV 3: Mar 14/96 51
BOEING SERVICE BULLETIN 767-28-0034

10.06

20.96

FROM LOWER

EDGE OF WEB

LBBL LBBL

32.94 25.63

SEE DETAIL I

FOR UPPER AND

LOWER LOCATION

AND NOTE THE

DIFFERENCES

CENTER WING

REAR SPAR

A67307

FIGURE 4. VALVE SUPPORT BRACKET INSTALLATION - GROUPS 1-3, 5-9, 12, 15, 16 AIRPLANES

Jul 1/93 SHEET 1 OF 5 767-28-0034

REV 3: Mar 14/96 52
BOEING SERVICE BULLETIN 767-28-0034

C

C

C

C

C

C

C

C

C

C

C

C

C

R

D

R

B

A

A

B

A

A

A

A

A

A

A

A

INBD

UP

12

12

10

10

10

10

10

12

12 12

10

10

LOCATION

LOWER

LOCATION

UPPER

LOCATION

UPPER

LOCATION

LOWER

2 8

2 (27 PLACES)

N

(11 PLACES)

3

A

A

B

DETAIL I

B

1 6

6 8

SEE

3 9

7 10

1 6

1 2

1 2

1 6

1 6

DETAIL II

A67381

FIGURE 4. VALVE SUPPORT BRACKET INSTALLATION - GROUPS 1-3, 5-9, 12, 15, 16 AIRPLANES

Jul 1/93 SHEET 2 OF 5 767-28-0034

REV 3: Mar 14/96 53
BOEING SERVICE BULLETIN 767-28-0034

11

SYM

C/L

5

0.750

0.921

0.840

4 (4 PLACES)

0.839

WEB

VALVE SUPPORT

BRACKET

343T0021-20 DOUBLER

111T1016-3

0.30

RIVET

BACR15FT3AD5

DOUBLER

111T1016-2

6

INBD

FWD VIEW B-B

VIEW A-A

DETAIL II

A67598

FIGURE 4. VALVE SUPPORT BRACKET INSTALLATION - GROUPS 1-3, 5-9, 12, 15, 16 AIRPLANES

Jul 1/93 SHEET 3 OF 5 767-28-0034

REV 3: Mar 14/96 54
BOEING SERVICE BULLETIN 767-28-0034

The instruction numbers shown below agree with the numbers shown inside the circle symbols in the

figure.

1 Remove existing fasteners (10 places) common to doubler and stiffener location.

2 Install doubler 111T1016-3 as follows:

a. Locate the doubler on forward surface of the rear spar web as shown

b. Use the template 111T1016-7 to layout the hole pattern

c. Drill the indicated holes to the final diameter as shown

d. Apply sealant BMS 5-26 Class C on the faying surfaces between the doubler and rear spar web as

specified in the 767 Maintenance Manual Subject 51-31-01.

e. Install the indicated fasteners.

3 Install doubler 111T1016-2 as follows:

a. Locate the doubler on aft surface of the rear spar web as shown

b. Use the template 111T1016-7 to layout the hole pattern

c. Drill the indicated holes to the final diameter as shown

d. Apply sealant BMS 5-26 Class C on the faying surfaces between the doubler and rear spar web as

specified in the 767 Maintenance Manual Subject 51-31-01.

e. Install the indicated fasteners.

4 Drill and cold work the hole using the high interference cold working procedure as specified in the 767

Structure Repair Manual 51-40-09. The final hole size is 0.2802 - 0.2822 inch diameter.

5 Drill and ream the hole through the doublers and web to the final size 0.998 to 1.003 inch diameter with

a surface finish of 63 microinches.

6 Install mounting bracket 343T0021-20 as follows:

a. Locate the bracket on forward surface of the rear spar web as shown

b. Drill the indicated holes to the final diameter as shown

c. Apply sealant BMS 5-26 Class C on the faying surfaces between the bracket and rear spar web as

specified in the 767 Maintenance Manual Subject 51-31-01.

d. Install the indicated fasteners.

7 Finish bared surfaces of rear spar web as specified in the 767 Maintenance Manual Subject 51-20-01.

8 Apply the fillet seal around the edge of doubler 111T1016-3 and bracket 343T0021-20 with sealant BMS

5-26 Class B as specified in the 767 Maintenance Manual Subject 51-31-01.

9 Apply the fillet seal around the edge of doubler 111T0116-2 with sealant BMS 5-26 Class B as specified

in the 767 Maintenance Manual Subject 51-31-01.

10 Apply the fillet seal on all fasteners in the forward surface of the web with sealant BMS 5-26 and aft

surface with sealant BMS 5-95. Refer to the 767 Maintenance Manual Subject 51-31-01.

11 Locate and install support bracket 343T0021-19 with rivet BACR15FT3AD5 (3 places).

The instructions given below agree with the letter shown in the upper left corner of the fastener

symbols in the figure. A letter N in the upper right corner shows that the head of the fastener should

be on the near side. A number in the lower right corner shows the grip length of the fasteners. A letter

C in the lower left corner shows that hole cold working is necessary using the high interference cold

working procedure as specified in the 767 Structure Repair Manual 51-40-09. A letter R in the lower

FIGURE 4. VALVE SUPPORT BRACKET INSTALLATION - GROUPS 1-3, 5-9, 12, 15, 16 AIRPLANES

Jul 1/93 SHEET 4 OF 5 767-28-0034

REV 3: Mar 14/96 55
BOEING SERVICE BULLETIN 767-28-0034

left corner shows that the hole is drill and ream to the final diameter.

FASTENER TABLE

Fastener

Symbol

Fastener Part Number Name Final Hole Diameter

A BACB30MY12K*Y Bolt 0.4022 - 0.4042

BACW10BP62P Washer

MS21042L6 Nut

B BACB30MY10K*Y Bolt 0.3397 - 0.3417

BACW10BP52P Washer

MS21042L5 Nut

C BACB30VT6K4 Bolt 0.186 - 0.188

BACW10BP3P Washer

MS21042L3 Nut

D BACB30VT6K6 Bolt 0.186 - 0.188

BACW10BP3P Washer

MS21042L3 Nut

NOTE: Replace the * with the number shown in the lower right corner of the fasteners

symbols.

FIGURE 4. VALVE SUPPORT BRACKET INSTALLATION - GROUPS 1-3, 5-9, 12, 15, 16 AIRPLANES

Jul 1/93 SHEET 5 OF 5 767-28-0034

REV 3: Mar 14/96 56
BOEING SERVICE BULLETIN 767-28-0034

GROUPS 18, 19

COVERPLATE FOR

AIRPLANES

12

VALVE

CROSSFEED

EXISTING

SEE DETAIL I

LBBL

32.94 29.30

LBBL

CENTER WING

REAR SPAR

10.06

LBBL

25.63

A67637

FIGURE 5. VALVE SUPPORT BRACKET INSTALLATION - GROUPS 10, 11, 13, 14, 17-19 AIRPLANES

Jul 1/93 SHEET 1 OF 5 767-28-0034

REV 3: Mar 14/96 57
BOEING SERVICE BULLETIN 767-28-0034

R

D

C

C

C

C

C

C

C

C

C

C

R

C

A

A

A

A

A

A

A

A

A

A

UP

INBD

(11 PLACES)

N 3

10

10

12

10

12

12

10

10

10

12

1 6

1 2

2 (27 PLACES)

2 8

1 6

1 6

1 2

1 6

7 10

3 9

SEE

6 8

B

DETAIL I

B

A

A

DETAIL II

A67642

FIGURE 5. VALVE SUPPORT BRACKET INSTALLATION - GROUPS 10, 11, 13, 14, 17-19 AIRPLANES

Jul 1/93 SHEET 2 OF 5 767-28-0034

REV 3: Mar 14/96 58
BOEING SERVICE BULLETIN 767-28-0034

FWD

INBD

C/L

SYM

WEB

VALVE SUPPORT

343T0021-20

6 BRACKET

DOUBLER

111T1016-3

DOUBLER

111T1016-2

VIEW B-B

DETAIL II

4 (4 PLACES)

0.30

RIVET

BACR15FT3AD5

0.839

0.840

0.921

0.750

5

11

VIEW A-A

A67643

FIGURE 5. VALVE SUPPORT BRACKET INSTALLATION - GROUPS 10, 11, 13, 14, 17-19 AIRPLANES

Jul 1/93 SHEET 3 OF 5 767-28-0034

REV 3: Mar 14/96 59
BOEING SERVICE BULLETIN 767-28-0034

The instruction numbers shown below agree with the numbers shown inside the circle symbols in the

figure.

1 Remove existing fasteners (10 places) common to doubler and stiffener location.

2 Install doubler 111T1016-3 as follows:

a. Locate the doubler on forward surface of the rear spar web as shown

b. Use the template 111T1016-7 to layout the hole pattern

c. Drill the indicated holes to the final diameter as shown

d. Apply sealant BMS 5-26 Class C on the faying surfaces between the doubler and rear spar web as

specified in the 767 Maintenance Manual Subject 51-31-01.

e. Install the indicated fasteners.

3 Install doubler 111T1016-2 as follows:

a. Locate the doubler on aft surface of the rear spar web as shown

b. Use the template 111T1016-7 to layout the hole pattern

c. Drill the indicated holes to the final diameter as shown

d. Apply sealant BMS 5-26 Class C on the faying surfaces between the doubler and rear spar web as

specified in the 767 Maintenance Manual Subject 51-31-01.

e. Install the indicated fasteners.

4 Drill and cold work the hole using the high interference cold working procedure as specified in the 767

Structure Repair Manual 51-40-09. The final hole size is 0.2802 - 0.2822 inch diameter.

5 Drill and ream the hole through the doublers and web to the final size 0.998 to 1.003 inch diameter with

a surface finish of 63 microinches.

6 Install mounting bracket 343T0021-20 as follows:

a. Locate the doubler on forward surface of the rear spar web as shown

b. Drill the indicated holes to the final diameter as shown

c. Apply sealant BMS 5-26 Class C on the faying surfaces between the bracket and rear spar web as

specified in the 767 Maintenance Manual Subject 51-31-01.

d. Install the indicated fasteners.

7 Finish bared surfaces of rear spar web as specified in the 767 Maintenance Manual Subject 51-20-01

8 Apply the fillet seal around the edge of doubler 111T1016-3 and bracket 343T0021-20 with sealant BMS

5-26 Class B as specified in the 767 Maintenance Manual Subject 51-31-01.

9 Apply the fillet seal around the edge of doubler 111T0116-2 with sealant BMS 5-26 Class B as specified

in the 767 Maintenance Manual Subject 51-31-01.

10 Apply the fillet seal on all fasteners in the forward surface of the web with sealant BMS 5-26 and aft

surface with sealant BMS 5-95. Refer to the 767 Maintenance Manual Subject 51-31-01.

11 Locate and install support bracket 343T0021-19 with rivet BACR15FT3AD5 (3 places).

12 For Groups 18, 19 airplanes, remove coverplate 112T1801-1. Keep the coverplate and all hardwares.

The instructions given below agree with the letter shown in the upper left corner of the fastener

symbols in the figure. A letter N in the upper right corner shows that the head of the fastener should

be on the near side. A number in the lower right corner shows the grip length of the fasteners. A letter

FIGURE 5. VALVE SUPPORT BRACKET INSTALLATION - GROUPS 10, 11, 13, 14, 17-19 AIRPLANES

Jul 1/93 SHEET 4 OF 5 767-28-0034

REV 3: Mar 14/96 60
BOEING SERVICE BULLETIN 767-28-0034

C in the lower left corner shows that hole cold working is necessary using the high interference cold

working procedure as specified in the 767 Structure Repair Manual 51-40-09. A letter R in the lower

left corner shows that the hole is drill and ream to the final diameter.

FASTENER TABLE

Fastener

Symbol

Fastener Part Number Name Final Hole Diameter

A BACB30MY12K*Y Bolt 0.4022 - 0.4042

BACW10BP62P Washer

MS21042L6 Nut

C BACB30VT6K4 Bolt 0.186 - 0.188

BACW10BP52P Washer

MS21042L5 Nut

D BACB30VT6K6 Bolt 0.186 - 0.188

BACW10BP52P Washer

MS21042L5 Nut

NOTE: Replace the * with the number shown in the lower right corner of the fasteners

symbols.

FIGURE 5. VALVE SUPPORT BRACKET INSTALLATION - GROUPS 10, 11, 13, 14, 17-19 AIRPLANES

Jul 1/93 SHEET 5 OF 5 767-28-0034

REV 3: Mar 14/96 61
BOEING SERVICE BULLETIN 767-28-0034

REAR SPAR

CENTER WING

SEE DETAIL I

32.94 25.63

LBBL LBBL

10.06

SEE

DETAIL III

R29019

FIGURE 6. VALVE SUPPORT BRACKET INSTALLATION - GROUPS 4, 20 AIRPLANES

Jul 1/93 SHEET 1 OF 7 767-28-0034

REV 3: Mar 14/96 62
BOEING SERVICE BULLETIN 767-28-0034

C

C

C

C

C

C

C

C

C

C

C

R

D

R

A

A

A

A

A

A

A

A

A

A

INBD

UP

10

12

10

10

12

12

10

10

10

12

3 9

3 (27 PLACES)

N

(11 PLACES)

4

A

A

B

DETAIL I

B

1 7

7 9

SEE

4

8 12

1 3

1 3

1 7

1 7

DETAIL II

1 7

11

R29020

FIGURE 6. VALVE SUPPORT BRACKET INSTALLATION - GROUPS 4, 20 AIRPLANES

Jul 1/93 SHEET 2 OF 7 767-28-0034

REV 3: Mar 14/96 63
BOEING SERVICE BULLETIN 767-28-0034

13

0.840

0.921

DETAIL II

5 (4 PLACES)

0.750

0.30

RIVET

BACR15FT3AD5

DOUBLER

111T1016-3

VALVE SUPPORT

BRACKET

343T0021-20

WEB

DOUBLER

111T1016-2

7

INBD

FWD VIEW B-B

VIEW A-A

0.839

SYM

C/L

6

R29022

FIGURE 6. VALVE SUPPORT BRACKET INSTALLATION - GROUPS 4, 20 AIRPLANES

Jul 1/93 SHEET 3 OF 7 767-28-0034

REV 3: Mar 14/96 64
BOEING SERVICE BULLETIN 767-28-0034

C 12

A

C 12

A

C 12

B

C 12

A

7 10 1 7 12 1 7 12

7 12 1 7 12

2

1

DETAIL III

INBD

UP

C C

A

A

R29023

FIGURE 6. VALVE SUPPORT BRACKET INSTALLATION - GROUPS 4, 20 AIRPLANES

Jul 1/93 SHEET 4 OF 7 767-28-0034

REV 3: Mar 14/96 65
BOEING SERVICE BULLETIN 767-28-0034

VALVE SUPPORT

BRACKET

343T0021-20

WEB

INBD

FWD VIEW C-C

2 7

R29058

FIGURE 6. VALVE SUPPORT BRACKET INSTALLATION - GROUPS 4, 20 AIRPLANES

Jul 1/93 SHEET 5 OF 7 767-28-0034

REV 3: Mar 14/96 66
BOEING SERVICE BULLETIN 767-28-0034

The instruction numbers shown below agree with the numbers shown inside the circle symbols in the

figure.

1 Remove existing fasteners common to doubler and stiffener location.

2 Remove fasteners (4 places) and coverplate 112T1081-1.

3 Install doubler 111T1016-3 as follows:

a. Locate the doubler on forward surface of the rear spar web as shown

b. Use the template 111T1016-7 to layout the hole pattern

c. Drill the indicated holes to the final diameter as shown

d. Apply sealant BMS 5-26 Class C on the faying surfaces between the doubler and rear spar web as

specified in the 767 Maintenance Manual Subject 51-31-01.

e. Install the indicated fasteners.

4 Install doubler 111T1016-2 as follows:

a. Locate the doubler on aft surface of the rear spar web as shown

b. Use the template 111T1016-7 to layout the hole pattern

c. Drill the indicated holes to the final diameter as shown

d. Apply sealant BMS 5-26 Class C on the faying surfaces between the doubler and rear spar web as

specified in the 767 Maintenance Manual Subject 51-31-01.

e. Install the indicated fasteners.

5 Drill and cold work the hole using the high interference cold working procedure as specified in the 767

Structure Repair Manual 51-40-09. The final hole size is 0.2802 - 0.2822 inch diameter.

6 Drill and ream the hole through the doublers and web to the final size 0.998 to 1.003 inch diameter with

a surface finish of 63 microinches.

7 Install mounting bracket 343T0021-20 as follows:

a. Locate the bracket on forward surface of the rear spar web as shown

b. Drill the indicated holes to the final diameter as shown

c. Apply sealant BMS 5-26 Class C on the faying surfaces between the bracket and rear spar web as

specified in the 767 Maintenance Manual Subject 51-31-01.

d. Install the indicated fasteners.

8 Finish bared surfaces of rear spar web as specified in the 767 Maintenance Manual Subject 51-20-01.

9 Apply the fillet seal around the edge of doubler 111T1016-3 and bracket 343T0021-20 with sealant BMS

5-26 Class B as specified in the 767 Maintenance Manual Subject 51-31-01.

10 Apply the fillet seal around the edge of bracket 343T0021-20 with sealant BMS 5-26 Class B as

specified in the 767 Maintenance Manual Subject 51-31-01.

11 Apply the fillet seal around the edge of doubler 111T0116-2 with sealant BMS 5-26 Class B as specified

in the 767 Maintenance Manual Subject 51-31-01.

12 Apply the fillet seal on all fasteners in the forward surface of the web with sealant BMS 5-26 and aft

surface with sealant BMS 5-95. Refer to the 767 Maintenance Manual Subject 51-31-01.

13 Locate and install support bracket 343T0021-19 with rivet BACR15FT3AD5 (3 places).

FIGURE 6. VALVE SUPPORT BRACKET INSTALLATION - GROUPS 4, 20 AIRPLANES

Jul 1/93 SHEET 6 OF 7 767-28-0034

REV 3: Mar 14/96 67
BOEING SERVICE BULLETIN 767-28-0034

The instructions given below agree with the letter shown in the upper left corner of the fastener

symbols in the figure. A letter N in the upper right corner shows that the head of the fastener should

be on the near side. A number in the lower right corner shows the grip length of the fasteners. A letter

C in the lower left corner shows that hole cold working is necessary using the high interference cold

working procedure as specified in the 767 Structure Repair Manual 51-40-09. A letter R in the lower

left corner shows that the hole is drill and ream to the final diameter.

FASTENER TABLE

Fastener

Symbol

Fastener Part Number Name Final Hole Diameter

A BACB30MY12K*Y Bolt 0.4022 - 0.4042

BACW10BP62P Washer

MS21042L6 Nut

B BACB30MY10K*Y Bolt 0.3397 - 0.3417

BACW10BP52P Washer

MS21042L5 Nut

C BACB30VT6K4 Bolt 0.186 - 0.188

BACW10BP3P Washer

MS21042L3 Nut

D BACB30VT6K6 Bolt 0.186 - 0.188

BACW10BP3P Washer

MS21042L3 Nut

NOTE: Replace the * with the number shown in the lower right corner of the fasteners

symbols.

FIGURE 6. VALVE SUPPORT BRACKET INSTALLATION - GROUPS 4, 20 AIRPLANES

Jul 1/93 SHEET 7 OF 7 767-28-0034

REV 3: Mar 14/96 68
BOEING SERVICE BULLETIN 767-28-0034

3

4

2

1

4

3

INBD

UP

REAR SPAR

A67266

FIGURE 7. COVER PLATE INSTALLATION - ALL AIRPLANES

Jul 1/93 SHEET 1 OF 2 767-28-0034

REV 3: Mar 14/96 69
BOEING SERVICE BULLETIN 767-28-0034

The instruction numbers shown below agree with the numbers shown inside the circle symbols in the

figure.

1 For Groups 1-9, 12, 15, 16, 18-20 airplanes only, install the coverplate 112T1081-1 as follows:

NOTE: For Groups 18, 19 airplanes, use the coverplate and hardwares that you kept in Figure 5.

a. Finish the bared area on rear spar web using chemical coating BAC5719, Type II and resistant

finish BMS10-20, Type 2 as specified in the 767 Maintenance Manual Subject 51-20-01.

b. Locate the coverplate on the forward surface of the rear spar web.

c. Apply sealant BMS 5-26 Class C on faying surfaces between the coverplate and rear spar web as

specified in the 767 Maintenance Manual Subject 51-31-01.

d. Secure the coverplate with screw NAS6604-13 (4 places), washer AN960JD416L (4 places), and

nut MS21042L4 (4 places).

2 Install the coverplate 112T1081-8 as follows:

a. Finish the bared area on rear spar web using chemical coating BAC5719, Type II and resistant

finish BMS10-20, Type 2 as specified in the 767 Maintenance Manual Subject 51-20-01.

b. Locate the coverplate on the forward surface of the rear spar web.

c. Apply sealant BMS 5-26 Class C on faying surfaces between the coverplate and rear spar web as

specified in the 767 Maintenance Manual Subject 51-31-01.

d. Secure the coverplate with screw NAS6604-12 (4 places), washer AN960JD416L (4 places), and

nut MS21042L4 (4 places).

3 Apply the fillet seal around the edge of the coverplate with sealant BMS 5-26 Class B as specified in the

767 Maintenance Manual Subject 51-31-01.

4 Apply the fillet seal on all fasteners in the forward surface of the web with sealant BMS 5-26 and aft

surface with sealant BMS 5-95. Refer to the 767 Maintenance Manual Subject 51-31-01.

FIGURE 7. COVER PLATE INSTALLATION - ALL AIRPLANES

Jul 1/93 SHEET 2 OF 2 767-28-0034

REV 3: Mar 14/96 70
BOEING SERVICE BULLETIN 767-28-0034

2

1 4 6

1 3 6

DETAIL I

SEE

INBD

UP

REAR SPAR

WRP

R26725

FIGURE 8. APU FUEL TUBE SUPPORT BRACKET INSTALLATION - GROUPS 1-9, 12, 15, 16, 18-20

AIRPLANES

Jul 1/93 SHEET 1 OF 3 767-28-0034

REV 3: Mar 14/96 71
BOEING SERVICE BULLETIN 767-28-0034

UP

RSS

1 4 6

2

1 3 6

5

250.00

FWD

INBD

0.65

0.65

DETAIL I

REAR

SPAR

WRP

R26728

FIGURE 8. APU FUEL TUBE SUPPORT BRACKET INSTALLATION - GROUPS 1-9, 12, 15, 16, 18-20

AIRPLANES

Jul 1/93 SHEET 2 OF 3 767-28-0034

REV 3: Mar 14/96 72
BOEING SERVICE BULLETIN 767-28-0034

The instruction numbers shown below agree with the numbers shown inside the circle symbols in the

figure.

1 Remove existing fasteners (3 places). Be careful not to damage holes in the rear spar.

2 Install bracket 344T0076-1 as follows:

a. Locate the bracket and use the existing holes in the rear spar to mark holes (3 places) on the

bracket.

b. Remove the bracket and drill 0.3280 - 0.3320 inch diameter holes (3 places) on the bracket and

ream existing hole in rear spar to 0.3245 - 0.3265 inch diameter (3 places).

c. Install the bracket.

3 Install bolt BACB30MY10K15X and seal nut BACN10WM5. Bolt head should be installed on the aft

surface of the rear spar.

4 Install bolt BACB30MY10K25X (2 places) and seal nut BACN10WM5 (2 places). Bolt head should be

installed on the aft surface of the rear spar.

5 Apply the fillet seal around the edge of the bracket with sealant BMS 5-26 Class B as specified in the

767 Maintenance Manual Subject 51-31-01.

6 Apply the fillet seal on all fasteners in the forward surface of the web with sealant BMS 5-26 and aft

surface with sealant BMS 5-95. Refer to the 767 Maintenance Manual Subject 51-31-01.

FIGURE 8. APU FUEL TUBE SUPPORT BRACKET INSTALLATION - GROUPS 1-9, 12, 15, 16, 18-20

AIRPLANES

Jul 1/93 SHEET 3 OF 3 767-28-0034

REV 3: Mar 14/96 73
BOEING SERVICE BULLETIN 767-28-0034

A

A

REAR SPAR

1

2 3 4

RBL

97.96 LBL

97.96 0

BL

RBL

97.96

LBL

97.96 0

BL

SEE

DETAIL III

SEE

DETAIL I

SEE

DETAIL II

SEE

DETAIL III

VIEW A-A

VIEW A-A

NEW CONFIGURATION

EXISTING CONFIGURATION

FWD

FWD

SEE

DETAIL I

B B

8

9

DETAIL IV

SEE

CENTER COMPARTMENT

SEE

DETAIL I

6

6

7

10

A67845

FIGURE 9. CROSSFEED FUEL TUBE REPLACEMENT - ALL AIRPLANES

Jul 1/93 SHEET 1 OF 6 767-28-0034

REV 3: Mar 14/96 74
BOEING SERVICE BULLETIN 767-28-0034

W.R.P.

343T0004-1

FUEL TUBE 8

SEE

DETAIL IV

FUEL TUBE

343T0004-5 8

VIEW B-B

0

BL

UP

10

A67829

FIGURE 9. CROSSFEED FUEL TUBE REPLACEMENT - ALL AIRPLANES

Jul 1/93 SHEET 2 OF 6 767-28-0034

REV 3: Mar 14/96 75
BOEING SERVICE BULLETIN 767-28-0034

MS29513-330

(2 PLACES)

BACC42R32

MS20995NC32

0.12

FERRULES

BETWEEN

DETAIL I

(2 PLACES)

NUT MS21042L3

WASHER AN960D10L

SCREW NAS1801-3-32

BRACKET

343T0046-15

BACC10EW32A

CLAMP

BACC10EW32B

69B92447-5

SPACER

NAS1801-3-10

BACN10JC3

AN960PD10L(2)

(2 PLACES)

BACC10EW32A

BACC10EW32B

AN960D10L(2)

NAS1801-3-7

AN735D32

BACN10JC3

BACJ40A20-6

RIB NO.2

INBD

FWD

FWD

INBD

BACN10JC3

NAS1801-3-7

AN960D10L(2)

DETAIL II

CROSSFEED

FUEL TUBE

D

D

A67862

FIGURE 9. CROSSFEED FUEL TUBE REPLACEMENT - ALL AIRPLANES

Jul 1/93 SHEET 3 OF 6 767-28-0034

REV 3: Mar 14/96 76
BOEING SERVICE BULLETIN 767-28-0034

5

BACC10EW32B

BACC10EW32A

BACJ40A-20-6

BODY RIB

SIDE OF

MS29513-235

(2 PLACES)

MS29513-330(2)

(2 PLACES)

BACN10JC3

AN960PD10L

NAS1801-3-10 NAS1801-3-7

NAS1801-3-7

INBD

FWD

BACN10JC3

AN960D10L(2)

AN735D32

BACN10JC3

AN960D10L(2)

DETAIL IV

DETAIL III

WASHER BULKHEAD

FITTING

A68029

FIGURE 9. CROSSFEED FUEL TUBE REPLACEMENT - ALL AIRPLANES

Jul 1/93 SHEET 4 OF 6 767-28-0034

REV 3: Mar 14/96 77
BOEING SERVICE BULLETIN 767-28-0034

VIEW D-D

RIB NO. 2

6

343T0046-15

BRACKET

(4 PLACES)

BACR15FT6KE7C

RIVET

DOUBLER CROSSFEED

FUEL

TUBE

UP

FWD

B97446

FIGURE 9. CROSSFEED FUEL TUBE REPLACEMENT - ALL AIRPLANES

Jul 1/93 SHEET 5 OF 6 767-28-0034

REV 3: Mar 14/96 78
BOEING SERVICE BULLETIN 767-28-0034

The instruction numbers shown below agree with the numbers shown inside the circle symbols in the

figure.

1 For Groups 1-9, 12, 15-16, 18-20 airplanes only, remove the clamp to release the fuel tube and remove

the fuel tube 343T0010-31 as specified in 767 Maintenance Manual Subject 28-22-07. Keep the

coupling nuts.

2 Remove the clamp to release the fuel tube and remove the fuel tube 343T0010-29 or -53 as specified in

767 Maintenance Manual Subject 28-22-07. Keep the coupling nuts.

3 Remove the clamp to release the fuel tube and remove the fuel tube 343T0010-26 or -54 as specified in

767 Maintenance Manual Subject 28-22-07. Keep the coupling nuts.

4 Remove the clamp to release the fuel tube and remove the fuel tube 343T0010-30 as specified in 767

Maintenance Manual Subject 28-22-07. Keep the coupling nuts.

5 For Groups 1-9, 12, 15, 16, 18-20 airplanes only, do these steps:

a. Remove and keep the bulkhead fitting in the side-of-body (SOB) rib.

b. Insert fuel tube 343T0010-65 outboard through SOB rib and rib 1 from center wing section.

c. Install the bulkhead fitting in the SOB rib. Use the kept fitting and new o-ring as shown in

Detail III.

d. Apply fillet seal around edges of bulkhead fitting with sealant BMS 5-95. Refer to the 767

Maintenance Manual 51-31-01.

6 For Groups 1-9, 12, 15, 16, 18-20 airplanes only, do these steps:

a. Install fuel tube 343T0010-65 as specified in 767 Maintenance Manual Subject 28-22-07. Use the

kept coupling nuts and o-ring as shown in the details to connect the fuel tubes.

NOTE: Make sure that the couplings are assembled correctly and the lockwire is installed on the

couplings as specified in the 767 Maintenance Manual Subject 28-00-00.

b. Install support bracket 343T0046-15 as shown in Detail I and View D-D.

c. Install the clamps, bonding jumper with screws, washers, and nuts as shown in Detail II. Refer to

Boeing Standard Wiring Practices Manual, Chapter 20, Section 20-20-00. The bonding resistance

should not exceed 0.010 ohm.

7 Install fuel tube 343T0010-87 as specified in the 767 Maintenance Manual Subject 28-22-07. Use the

kept coupling nuts and o-ring as shown in the details to connect the fuel tubes.

NOTE: Make sure that the couplings are assembled correctly and the lockwire is installed on the

couplings as specified in the 767 Maintenance Manual Subject 28-00-00.

8 Install fuel tube 343T0004-1 and 343T0004-5 as specified in the 767 Maintenance Manual Subject

28-22-07. Use the kept coupling nuts and o-ring as shown in the indicated details to connect the fuel

tubes.

9 Install fuel tube 343T0010-86 as specified in the 767 Maintenance Manual Subject 28-22-07. Use the

kept coupling nuts and o-ring as shown in the indicated details to connect the fuel tubes.

10 Install the clamps, bonding jumper with screws, washers, and nuts as shown in Detail IV. Refer to

Boeing Standard Wiring Practices Manual, Chapter 20, Section 20-20-00. The bonding resistance

should not exceed 0.010 ohm.

FIGURE 9. CROSSFEED FUEL TUBE REPLACEMENT - ALL AIRPLANES

Jul 1/93 SHEET 6 OF 6 767-28-0034

REV 3: Mar 14/96 79
BOEING SERVICE BULLETIN 767-28-0034

FUEL TUBE

346T0010-12

INBD

UP

EXISTING CONFIGURATION

3

249.75

4 WS

1

2

MS29513-212(2)

AS1712D12

6

VIEW A-A

VIEW C-C

SECTION B-B

UP 7

FWD

INBD

C C

7

8

FWD

9

6

A A

B B MS29513-216(2)

AS1712D16

249.75

WS

NEW CONFIGURATION

INBD

UP

5

A68090

FIGURE 10. APU FUEL TUBE INSTALLATION - ALL AIRPLANES

Jul 1/93 SHEET 1 OF 2 767-28-0034

REV 3: Mar 14/96 80
BOEING SERVICE BULLETIN 767-28-0034

The instruction numbers shown below agree with the numbers shown inside the circle symbols in the

figure.

1 Remove the bonding clamp and jumper.

2 Remove fuel tube 346T0010-5 as specified in the Boeing Maintenance Manual Subject 28-22-07.

3 Disconnect the bonding jumper and remove fuel tube 346T0047-1.

4 Disconnect the fuel tubes and remove the tee assembly.

5 Install elbow 73511-12 to connect the fuel tubes using one o-ring MS29513-12 at each connection.

6 Install fuel tube 346T0010-12 as shown. Connect the bonding jumper as specified in the Boeing

Standard Wiring Practices Manual, Chapter 20, Section 20-20-00. The bonding resistance should not

exceed 0.010 ohm.

7 Use the existing hole location on the existing bracket to locate the bracket 346T0051-3 approximately

as shown. Install the bracket with screw NAS1801-3-9 (2 places), washer AN960JD10L (2 places) and

nut BACN10JC3 (2 places).

8 Install clamp BACC10DK12 to secure the fuel tube with screw NAS1801-3-9, washer AN960JD10L and

nut MS21042L3.

9 Install bonding jumper BACJ40A20-8 with bonding clamp AN735D12 (2 places), screw NAS1801-3-9 (2

places), washer AN960D10L (4 places), and nut MS21042L3 (2 places). Refer to the Boeing Standard

Wiring Practices Manual, Chapter 20, Section 20-20-00. The bonding resistance should not exceed

0.010 ohm.

FIGURE 10. APU FUEL TUBE INSTALLATION - ALL AIRPLANES

Jul 1/93 SHEET 2 OF 2 767-28-0034

REV 3: Mar 14/96 81
BOEING SERVICE BULLETIN 767-28-0034

ENGINE FUEL CROSSFEED VALVE (TYPICAL)

5

4

2

3 REAR SPAR

1

FWD

UP

INBD

REAR SPAR

CENTER WING

A68422

FIGURE 11. CROSSFEED VALVE INSTALLATION - ALL AIRPLANES

Jul 1/93 SHEET 1 OF 2 767-28-0034

REV 3: Mar 14/96 82
BOEING SERVICE BULLETIN 767-28-0034

The instruction numbers shown below agree with the numbers shown inside the circle symbols in the

figure.

1 Install the applicable valve body with screw NAS6603-8 (4 places), washer AN960PD10L (4 places),

o-ring MS29513-330 (4 places) as specified in the 767 Maintenance Manual 28-22-02.

- On Groups 1-9, 12, 15, 16, 18-20, 19 airplanes, install kept valve body S343T003-2 or -15

- On Groups 10, 11, 13, -14, 17 airplanes, install new valve body S343T003-40 (optional

S343T003-15)

2 Install adapter shaft S343T003-26 with BACB30NM4K5 (4 places), washer AN960JD416L (4 places) as

specified in the 767 Maintenance Manual 28-22-02.

3 Install kept valve actuator S343T003-1, -14, -39, or -111with screw MS24677-15 (4 places), washer

AN960PD10L (4 places), as specified in the 767 Maintenance Manual 28-22-12.

4 Install the applicable valve body as specified in the 767 Maintenance Manual 28-22-02.

- On Groups 1-9, 12, 15, 16, 18-20, 19 airplanes, install new valve body S343T003-40 (optional

S343T003-15) with screw NAS6603-8 (4 places), washer AN960PD10L (4 places), o-ring

MS29513-330 (4 places).

- On Groups 10, 11, 13, -14, 17 airplanes, install kept valve body S343T003-15 with these kept

fasteners: screw NAS6603-8 (4 places), washer AN960PD10L (4 places), new o-ring

MS29513-330 (4 places).

5 On Groups 1-9, 12, 15, 16, 18-20, 19 airplanes only, install the these components:

- Install adapter shaft S343T003-26 with BACB30NM4K5 (4 places), washer AN960JD416L (4

places) as specified in the 767 Maintenance Manual 28-22-02.

- Install kept valve actuator S343T003-1, -14, -39, or -111 with screw MS24677-15 (4 places),

washer AN960PD10L (4 places), as specified in the 767 Maintenance Manual 28-22-12.

FIGURE 11. CROSSFEED VALVE INSTALLATION - ALL AIRPLANES

Jul 1/93 SHEET 2 OF 2 767-28-0034

REV 3: Mar 14/96 83
BOEING SERVICE BULLETIN 767-28-0034

SEE DETAIL II

SEE DETAIL I

FWD

BL

0 20.5

RBL

20.5

LBL

P11-1 P11-4

P11-2 P11-5

P11-3 P11-6

FLIGHT COMPARTMENT

A68451

FIGURE 12. P11 PANEL MODIFICATION - ALL AIRPLANES

Jul 1/93 SHEET 1 OF 3 767-28-0034

REV 3: Mar 14/96 84
BOEING SERVICE BULLETIN 767-28-0034

C1071 IND

FEED

CROSS

CONT

C1071

C1052 C1058

D

36 35 34

C1066 C1070 C1069

22 21 20

M

M

19 20 21 22 23 24 25

C1069 C1070

2 2

VALVE R CTR NOZZLE CONT 2

QTY M R AFT

L FWD

RIGHT JETT PUMPS

FUEL

FWD AFT

CROSSFEED VLV

34 35 36

FUEL DC PUMP

PWR D

D

DETAIL IV

1 1 1

1.12

1

5

7

4

3

DETAIL III

0.94

DETAIL I

2

1

5.35

FOR BACK SIDE

SEE DETAIL III

6

1.54

FOR BACK SIDE

SEE DETAIL IV

DETAIL II

A68656

FIGURE 12. P11 PANEL MODIFICATION - ALL AIRPLANES

Jul 1/93 SHEET 2 OF 3 767-28-0034

REV 3: Mar 14/96 85
BOEING SERVICE BULLETIN 767-28-0034

The instruction numbers shown below agree with the numbers shown inside the circle symbols in the

figure.

1 Remove plug button and install circuit breaker BACC18Z02R (2 places).

2 Cut the existing indicia strip to dimension as shown. Center the cutout over circuit breakers as close as

possible. Cut filler patch 233T5103-109 to fit the cutout section with approximately 0.06 inch overlap on

both sides and line up the top edge with the existing indicia strip. For Group 1 and 2 airplanes, cover the

right fuel jettison nomenclature on the filler patch as shown. Install the filler patch as specified in the

Boeing Standard Overhaul Practices Manual 20-50-05.

3 Install bus bar BACB29B7S2 as shown.

4 Rubber stamp or silk-screen circuit breaker identification with 12-point characters in approximate

location as shown. Refer to the Boeing Standard Overhaul Practices Manual 20-50-10.

5 Remove existing circuit breaker BACC18Z02R and install circuit breaker BACC18Z1R.

6 Cut the existing indicia strip to dimension as shown. Center the cutout over circuit breakers as close as

possible. Cut filler patch 233T5103-110 to fit the cutout section with approximately 0.06 inch overlap on

two sides and line up the existing indicia strip. Install the filler patch as specified in the Boeing Standard

Overhaul Practices Manual 20-50-05.

7 Remove existing circuit breaker identification. Rubber stamp, silk-screen or hand letter (abrasion

resistant) circuit breaker identification with 12-point characters in approximate location as shown. Refer

to the Boeing Standard Overhaul Practices Manual 20-50-10.

FIGURE 12. P11 PANEL MODIFICATION - ALL AIRPLANES

Jul 1/93 SHEET 3 OF 3 767-28-0034

REV 3: Mar 14/96 86
BOEING SERVICE BULLETIN 767-28-0034

A A

MAIN EQUIPMENT CENTER

FWD

P33 PANEL

(DOORS REMOVED) INBD

UP

A68674

FIGURE 13. P33 PANEL MODIFICATION - ALL AIRPLANES

Jul 1/93 SHEET 1 OF 3 767-28-0034

REV 3: Mar 14/96 87
BOEING SERVICE BULLETIN 767-28-0034

(ROTATED 180 DEGREES)

VIEW C-C VIEW B-B

VIEW A-A

1

2

3 3

1

INBD

FWD

RIVET NAS1738E4-2

(4 PLACES)

2.00

1.25 C C

B B

C22631

FIGURE 13. P33 PANEL MODIFICATION - ALL AIRPLANES

Jul 1/93 SHEET 2 OF 3 767-28-0034

REV 3: Mar 14/96 88
BOEING SERVICE BULLETIN 767-28-0034

The instruction numbers shown below agree with the numbers shown inside the circle symbols in the

figure.

1 Do these steps to install bracket 284T0378-176

a. Locate the bracket 284T0378-176 approximately as shown. Make sure that the clearance between

the bracket and adjacent light L575 and its associated wires is sufficient for relay installation. If

necessary, tie light L575 wires to avoid inteference.

b. Install the bracket with rivet NAS1738E4-2 (4places).

c. Seal the rivet blind side head (4 places) on the other side as specified in the Boeing Standard

Overhaul Practices Manual 20-50-12, Type 70.

2 Install relay socket BACS16AF1 (2 places) and identification tapes 289T0202-10601 and

289T0202-10701. Install relay BACR13CE2 (2 places). Get the relay sockets and the identification

tapes from the wire kit 289T0202-106 and -107.

3 Install the relay numbers as shown (4 places). Get the relay number from marker BAC27TEX4891.

FIGURE 13. P33 PANEL MODIFICATION - ALL AIRPLANES

Jul 1/93 SHEET 3 OF 3 767-28-0034

REV 3: Mar 14/96 89
BOEING SERVICE BULLETIN 767-28-0034

6 5 2

7

4

1

(4 PLACES)

W044 3

AF0203

POS 02

J D5012P

P61 RIGHT SIDE PNL

POS 7

AF201

D5010P J

1

(6 PLACES)

W062 XD38

TB104

POS 76

D5410P

4 W1716

J

604-20 GD110-DC

TB104

W590

W590

510-22 W062 YC36 4

AF0204

POS 85

W070

W066 31 XB37 591-22

J D4854P

XD37

509-22 XC37

587-22 XA37 W066

W066

W066

587-22

604-22

022-22 W044

(4 PLACES)

P5 PLT OVHD PNL

FUEL MANAGEMENT PNL

M10055(YCL)

J3 D1384

5

21

2

11

7

24

10

585-22

A69946

FIGURE 14. P5 PANEL WIRING AND INTERCONNECTION WIRING MODIFICATION - ALL AIRPLANES

Jul 1/93 SHEET 1 OF 4 767-28-0034

REV 3: Mar 14/96 90
BOEING SERVICE BULLETIN 767-28-0034

1 6

5 4

1

P5 PLT OVHD PNL P61 RIGHT SIDE PNL

W070

543-22

TB104

XD38

M10055(YCL)

FUEL MANAGEMENT PNL

8

W062

J1 D1374

W066-608-22

(16 PLACES)

500-22 XA38

21

20

19

POS 34 W070

544-22 53

54

55

56

540-22

541-22

542-22

D1330

W756

538-22

539-22

XB38

XC38

YC36

(6 PLACES)

(6 PLACES)

J D4714P

(4 PLACES)

7

28

29

J2

W066

J

W620

AF0204

21

POS 54

D4286P

A69969

FIGURE 14. P5 PANEL WIRING AND INTERCONNECTION WIRING MODIFICATION - ALL AIRPLANES

Jul 1/93 SHEET 2 OF 4 767-28-0034

REV 3: Mar 14/96 91
BOEING SERVICE BULLETIN 767-28-0034

29

30

8

11

1

12

13

8 4

6 1

3

P61 RIGHT SIDE PNL

W042

AF0204

POS 04

J D7972P

W070 XA37 521-22

W062 XA38 536-22

XB38 537-20

POS 71

J D5356P

W624

W062

W070

XC38

XD37

XC37

XB37

TB104

535-22

538-20

528-22

530-22

(5 PLACES)

W066

(7 PLACES)

(2 PLACES)

(14 PLACES)

B71641

FIGURE 14. P5 PANEL WIRING AND INTERCONNECTION WIRING MODIFICATION - ALL AIRPLANES

Jul 1/93 SHEET 3 OF 4 767-28-0034

REV 3: Mar 14/96 92
BOEING SERVICE BULLETIN 767-28-0034

The instruction numbers shown below agree with the numbers shown inside the flag symbols in the

figure.

1 Socket Contact BACC47CP1A

2 Socket Contact BACC47CP3T

3 Pin Contact BACC47CN1A

4 Terminal Block Contact M39029/11-145

5 TB104 XA37 is TB098 YC30 for Group 1 airplanes VB051-VB054 and Group 2 airplane VB055.

6 Dead-end the shield with sleeve cut from 289T0202-133 as specified in the Boeing Standard Wiring

Practices Manual, Chapter 20, Sections 20-10-14 and 20-10-15.

7 Pin Contact BACC47CN1A

8 Install terminal block BACM15C3A. Refer to Boeing Standard Wiring Practices Manual, Chapter 20,

Section 20-90-11.

REFERENCE: 767 WIRING DIAGRAMS 28-22-31, 28-41-21

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

989752

FIGURE 14. P5 PANEL WIRING AND INTERCONNECTION WIRING MODIFICATION - ALL AIRPLANES

Jul 1/93 SHEET 4 OF 4 767-28-0034

REV 3: Mar 14/96 93
BOEING SERVICE BULLETIN 767-28-0034

5

1

3

3

6

6

5

7

7

4

2

AFT

FWD

FWD

AFT

J D6230P

(2 PLACES)

(2 PLACES)

(16 PLACES)

QNXX-24

(16 PLACES)

QLXX-24

QN01-24

QN04-24

QN05-24

QL04-24

QL05-24

GD157-S

E8 EICAS RACK

W1730

POS 16

POS 20

AE0219

AE0219

W1722

D6222P

B5

J

B01

BXX

B05

D883A

D6

D883F

D881A

D883D

D881F

D6

D881D

C14

M10181 L EICAS

M10182 R EICAS COMPUTER

M10182 R EICAS COMPUTER

COMPUTER

VALVE

FUEL CROSSFEED C14

VALVE

FUEL CROSSFEED

E6 W2002

DISAGREEMENT HN05-24

APU ISO VALVE

D883F

D883A

M10181 L EICAS COMPUTER

W2002

HL05-24

W2000

D881A

D881F

E6

DISAGREEMENT

APU ISO VALVE

B04

A70331

FIGURE 15. E8 RACK WIRING MODIFICATION - GROUPS 1-4, 6-9, 12-20 AIRPLANES

Jul 1/93 SHEET 1 OF 2 767-28-0034

REV 3: Mar 14/96 94
BOEING SERVICE BULLETIN 767-28-0034

The instruction numbers shown below agree with the numbers shown inside the flag symbols in the

figure.

1 Remove insert blank D-659-0004 at insert B of connector D6230J.

2 Install flat cable assembly 284T1015-2.

3 Pin Contact BACC47EF1

4 Terminal Block Contact BACC47DE4

5 Install pin contact BACC47EF1 on wires. Cap and stow wires at the connector as specified in the

Boeing Standard Wiring Practices Manual, Chapter 20, Section 20-10-15.

6 Represents all spare wires in the flat cable assembly.

7 Cap and stow wire as specified in the Boeing Standard Wiring Practices Manual, Chapter 20, Section

20-10-15.

REFERENCE: 767 WIRING DIAGRAM 28-22-31

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

989752

FIGURE 15. E8 RACK WIRING MODIFICATION - GROUPS 1-4, 6-9, 12-20 AIRPLANES

Jul 1/93 SHEET 2 OF 2 767-28-0034

REV 3: Mar 14/96 95
BOEING SERVICE BULLETIN 767-28-0034

2

1

1

3

3

POS 16

AE0219

QN01-24

GD157-S

M10182 R EICAS COMPUTER

(4 PLACES)

J D6230P

QN04-24

QN05-24

QL04-24

QL05-24

E8 EICAS RACK

W1730

POS 20

AE0219

W1722

D6222P

B5

J

B01

B05

D6

D883F

D883D

D881F

D6

D881D

C14

M10181 L EICAS

M10182 R EICAS COMPUTER

COMPUTER

VALVE

FUEL CROSSFEED C14

VALVE

FUEL CROSSFEED

E6 W2002

DISAGREEMENT HN05-24

APU ISO VALVE

D883F

D883A

M10181 L EICAS COMPUTER

W2002

HL05-24

W2000

D881A

D881F

E6

DISAGREEMENT

APU ISO VALVE

B04

FWD

FWD

AFT

AFT

A70373

FIGURE 16. E8 RACK WIRING MODIFICATION - GROUPS 5, 10, 11 AIRPLANES

Jul 1/93 SHEET 1 OF 2 767-28-0034

REV 3: Mar 14/96 96
BOEING SERVICE BULLETIN 767-28-0034

The instruction numbers shown below agree with the numbers shown inside the flag symbols in the

figure.

1 Pin Contact BACC47EF1

2 Terminal Block Contact BACC47DE4

3 Cap and stow wire as specified in the Boeing Standard Wiring Practices Manual, Chapter 20, Section

20-10-15.

REFERENCE: 767 WIRING DIAGRAM 28-22-31

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

989752

FIGURE 16. E8 RACK WIRING MODIFICATION - GROUPS 5, 10, 11 AIRPLANES

Jul 1/93 SHEET 2 OF 2 767-28-0034

REV 3: Mar 14/96 97
BOEING SERVICE BULLETIN 767-28-0034

1

AF203

AFT FUEL

VALVE CB

CROSSFEED

C1070

2

2

1

1

5

POS 4

4 D7972P J

P11-4 CIRCUIT BREAKER PNL ASSY

P11-5 CIRCUIT BREAKER PNL ASSY

29

30

C1069

2

2

1

W042

POS 2 FUEL

546-20

547-20

2 1

VALVE CB

CROSSFEED

FWD FUEL

W032-031-8 2

D5012J P

020-22 3

C1051

2 1

2

W044

13

TB5022

P

2 1

510-22

C1071

1

D5010J

W070

W070

AF201

VALVE CB

CROSSFEED

CROSSFEED

IND. CB

1

6

W066

(6 PLACES)

4

A70433

FIGURE 17. P11 PANEL WIRING AND INTERCONNECTION WIRING MODIFICATION - ALL AIRPLANES

Jul 1/93 SHEET 1 OF 2 767-28-0034

REV 3: Mar 14/96 98
BOEING SERVICE BULLETIN 767-28-0034

The instruction numbers shown below agree with the numbers shown inside the flag symbols in the

figure.

1 Contact Socket BACC47CP1A

2 Lug BACT12AR203

3 Not Used

4 Lug BACT12AC15

5 Dead-end the shield with sleeve cut from 289T0202-133 as specified in the Boeing Standard Wiring

Practices Manual, Chapter 20, Sections 20-10-14 and 20-10-15.

6 Lug BACT12AR223

REFERENCE: 767 WIRING DIAGRAMS 28-22-31, 24-54-71,

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

989752

FIGURE 17. P11 PANEL WIRING AND INTERCONNECTION WIRING MODIFICATION - ALL AIRPLANES

Jul 1/93 SHEET 2 OF 2 767-28-0034

REV 3: Mar 14/96 99
BOEING SERVICE BULLETIN 767-28-0034

1

PUMP CONT RELAY

FUEL BOOST

K188 L FWD

P33 FWD MISC ELEC EQUIP PNL

09D-16

09C-16

7

2

1

4

P

POS 10

D5890J

11

10

5

6

3

8

W1274

W142

786-24

2B-22

A1 09B-16

TB186

YA11 790-24

AE0207

B1

C1

A70461

FIGURE 18. P33 PANEL WIRING MODIFICATION - ALL AIRPLANES

Jul 1/93 SHEET 1 OF 5 767-28-0034

REV 3: Mar 14/96 100
BOEING SERVICE BULLETIN 767-28-0034

15

5

2

S2B

S2B

S2B

S2B

10 9

12

13

TB268

14 XC2 W144

(7 PLACES)

(8 PLACES)

(28 PLACES)

10P-22

10S-22

38

8

10D-22

3

14

4

13

2

GDX4-DC 10J-20

NC

NC

NC

10G-22

GDX4-DC 10R-20

39 6

12

(5 PLACES)

10K-20

3 2

4

4

YA12

TB90

7

5

D5334J

POS 22

P

3

2

1

10L-22

10M-22

W144

TB268

10T-22 XD2

GDX4-DC 10N-20 1

DISAGREE RELAY

D2985

TB268

YC9 W144

YA5 W144

AE207

D5890J

POS 10

P

W1274

23

24

W142

10I-20

36 10H-20

37

AE0203

AE0203

P D5744J

POS 17

15 10F-22

W624

P33-FWD MISC ELEC EQUIP PNL

K2151 AFT CROSSFEED

W1730

7

13

4

A70650

FIGURE 18. P33 PANEL WIRING MODIFICATION - ALL AIRPLANES

Jul 1/93 SHEET 2 OF 5 767-28-0034

REV 3: Mar 14/96 101
BOEING SERVICE BULLETIN 767-28-0034

12

5

S2B

S2B

S2B

S2B

S2B

S2B

S2B

S2B

S2B S2B

S2B S2B

6

5

3

5 8

5

TB092

DISAGREE RELAY

K2152 FWD CROSSFEED

12

6

TB268

W142 XD2

GDX7-DC

P D5664J

POS 6

W756

54

53 7

14

8

649-22

5

4

3

NC

GDX7-DC

GDX7-DC 1

55

2

13

NC

653-22

W142

TB268

YA3

XC2

654-22

651-22

29

W142

TB268

647-22

W142

655-22

TB268

YA5

648-22 YC9 656-22

P33-FWD MISC ELEC EQUIP PNL

W144

(4 PLACES)

657-20

652-20

658-22

659-20

AE0207

NC

(8 PLACES)

D2987

(9 PLACES)

A70920

FIGURE 18. P33 PANEL WIRING MODIFICATION - ALL AIRPLANES

Jul 1/93 SHEET 3 OF 5 767-28-0034

REV 3: Mar 14/96 102
BOEING SERVICE BULLETIN 767-28-0034

The instruction numbers shown below agree with the numbers shown inside the flag symbols in the

figure.

NOTE: Code "S2B" shown in the diagram is a wire seperation code. Code "S2B" wires should route

with other blue colored lacing tape bundle or as seperate bundle. Refer to Boeing Standard

Wiring Practices Manual 20-10-19.

1 Remove receptacle BACC45FN14-7S. Reterminate wires from the removed receptacle to the same pin

number in the new receptacle BACC45FN14-12S9. Install receptacle BACC45FN14-12S9 and

identification tape 289T0202-10602.

2 Socket Contact BACC47CP1A

3 Relay Socket Contact BACC47ER1

4 Terminal Block Contact BACC47DE7

5 Terminal Block Contact M39029/11-145

6 Pin Contact BACC47CN1A

7 TB90 YA12 is TB90 YC14 for these airplanes:

Group 1: VA701-VA702

Group 2: VA703-VA717, VB281-VB284, VE001-VE003, VE041-VE043, VE061-VE069

Group 3: VA718-VA719

8 GDX7-DC is GDX5-DC for these airplanes:

Group 2: VK031-VK045, VN001-VN015

Group 3: VK046-VK048, VK131-VK133, VN111-VN115

Group 4: VK161

Group 6: VN171

Group 7: VN172-VN173, VN211-VN212, VL003-VL006

Group 11: VN251-VN260

Group 12: VL001-VL002

Group 13: VN016-VN020, VN116-VN124, VN130-VN132, VN233-VN234, VN291,

VN301-VN306, VN371, VN372, VN376, VN381, VN471-VN472, VN531-VN532,

VN536-VN537, VN541-VN542, VN551, VN631-VN633, VN731, VN751-VN753

Group 15: VN051-VN056, VN081-VN084

Group 16: VN057, VN058, VN085

Group 17: VN059-VN064, VN086-VN092

Group 18: VN231-VN232

Group 20: K049-VK054

9 Dead-end the shield with sleeve cut from 289T0202-133 as specified in the Boeing Standard Wiring

Practices Manual, Chapter 20, Sections 20-10-14 and 20-10-15.

10 Use the pin contact included with the new receptacle.

11 Wires 09B-16, 09C-16, 09D-16 are 302B-18, 302R-18, 302Y-18 respectively for Group 1 airplanes

VA002-VA012, VA301-VA308, VA501-VA505, VA801-VA805, VB051-VB054, VB201.

12 Install terminal block BACM15C3B if not installed. Refer to Boeing Standard Wiring Practices Manual,

Chapter 20, Section 20-90-11. Get terminal block from applicable top kit or supplemental kit 289T1353.

13 Use the wires included in supplemental wire kit 015T1353-10. Discard the wires in wire kit

289T0202-106.

14 Connect wire only if airplane does not have EICAS computers S242N701-408, or previous 400 series

dash number.

FIGURE 18. P33 PANEL WIRING MODIFICATION - ALL AIRPLANES

Jul 1/93 SHEET 4 OF 5 767-28-0034

REV 3: Mar 14/96 103
BOEING SERVICE BULLETIN 767-28-0034

15 Cap and stow wire only if airplane has EICAS computers S242N701-408, or previous 400 series dash

number.

REFERENCE: 767 WIRING DIAGRAMS 28-22-11, 28-22-31

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

989752

FIGURE 18. P33 PANEL WIRING MODIFICATION - ALL AIRPLANES

Jul 1/93 SHEET 5 OF 5 767-28-0034

REV 3: Mar 14/96 104
BOEING SERVICE BULLETIN 767-28-0034

2

7

8

6

5 4

1

9

6

W1718 3

D5366J

POS 14

4

W598 6

POS 03

D4942J

P36 LEFT MISC ELEC EQUIP PNL

(2 PLACES)

502-20

P

P

759-20

760-24

YC11

TB302

760-24

759-20

P D4856J

POS 9

W590

18

W176-04P-24

D12246

ENG SPEED RLY

K1274 L HIGH

6

W596

P

POS 15

D4992J

43

44

AE0209

AIR/GND RLY

XC11

XD11

TB218

W176-81U-24

W176-81V-24

20

14

6

NC 1

8

>75%

<67%

W176-04N-24 A2

TB218

XA1

NC

W184-811-24 XB3

TB218

A1

A3

D2910

AIR

7

9

W184

812-24

813-24

812-24

813-24

810-24

K167 SYS NO.1

A71024

FIGURE 19. P36 PANEL WIRING MODIFICATION - ALL AIRPLANES

Jul 1/93 SHEET 1 OF 2 767-28-0034

REV 3: Mar 14/96 105
BOEING SERVICE BULLETIN 767-28-0034

The instruction numbers shown below agree with the numbers shown inside the flag symbols in the

figure.

1 Delete the wires for these airplanes only:

Group 4: VK161

Group 5: VN151-VN155

Group 8: VN221

Group 10: VN156-VN158, VF071-VF072, VN163-VN168

Group 11: VN252-VN260

Group 14: VN223, VN224, VN671-VN672, VN681-VN683

Group 19: VN222

2 The wire is 22 gage on some airplanes

3 The wire is 24 gage on some airplanes

4 TB302 YC11 is TB216 YC05 for these airplanes:

Group 1: All airplanes

Group 2: VA013-VA020, VA309-VA310, VA506, VA703-VA705, VA806-VA809, VB002, VB101-VB104,

VB202, VB251-VB253, VB281

TB302 YC11 is splice SM4 for these airplanes

Group 10: VN156-VN157

Group 16: VK009

5 Pin Contact BACC47CN1A

6 Socket Contact BACC47CP1A

7 Install identification tape 289T0202-10901 on the added wire adjacent to the connector.

8 Install identification tape 289T0202-10902 on the added wire adjacent to the connector.

9 Install identification tape 289T0202-10903 on the added wire adjacent to the connector.

REFERENCE: 767 WIRING DIAGRAMS 28-22-31, 28-25-31

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

989752

FIGURE 19. P36 PANEL WIRING MODIFICATION - ALL AIRPLANES

Jul 1/93 SHEET 2 OF 2 767-28-0034

REV 3: Mar 14/96 106
BOEING SERVICE BULLETIN 767-28-0034

1

5

10 7

6

2

2

9

3

8

NC

4

NC

P37 RIGHT MISC ELEC EQUIP PNL

W614

D19

A C

113-20

P

POS 7

D5052J

W192-634-24

P

P

W656 34

POS 24

D4346J

2

D4284J

POS 26

W620

C2

D3708

K175 APU FUEL

CONTROL RLY

Z9

AE0218

P D5270J

POS 12

16

YC1 087-24

TB86

K632 C PUMP

AUTO ON RLY

D10066

D3

D1

D2

K191 DC FUEL

PUMP CONT RLY

X1

D3726

TB274 R39

APU DC PUMP

CONT DIODE

X2

W198

21 YA7 506-24

TB86

090-24

090-24

AE0224

W0590

088-24

088-24

113-20

089-24

503-22

C3

C1

504-22

A71167

FIGURE 20. P37 PANEL WIRING MODIFICATION - ALL AIRPLANES

Jul 1/93 SHEET 1 OF 3 767-28-0034

REV 3: Mar 14/96 107
BOEING SERVICE BULLETIN 767-28-0034

4

4

4

NC

508-24 Z9

TB86

W0590

X1

X2

512-24

513-24

K632 DC PUMP

AUTO ON RLY

D10066

20

22

3

098-20

097-20

509-20

YA8

TB86

POS 7

P D5052J

B1

B2

B3

13

D3708

K175 APU FUEL

CONTROL RLY

D2

D3

D1

14 100-20

099-24

RLY

VALVE DISAGREE

K523 APU ISLN

3

7

2

5

4

D00442

W198

16 514-24 YA7

TB86

GDX6-DC

105-22

103-20

104-20

29

P

POS 9

D5378J

W1722 5

AE0224

P37 RIGHT MISC ELEC EQUIP PNL

102-22 101-22

A71404

FIGURE 20. P37 PANEL WIRING MODIFICATION - ALL AIRPLANES

Jul 1/93 SHEET 2 OF 3 767-28-0034

REV 3: Mar 14/96 108
BOEING SERVICE BULLETIN 767-28-0034

The instruction numbers shown below agree with the numbers shown inside the flag symbols in the

figure.

1 Terminal Block Contact BACC47DE4

2 Socket Contact BACC47CP2T

3 Socket Contact BACC47CP1A

4 The wire is 22 gage in some airplanes.

5 Pin Contact BACC47CN1A

6 Relay Socket Contact BACC47DJ1

7 Install identification tape 289T0202-11101 on the added wire adjacent to the connector.

8 Install identification tape 289T0202-11102 on the added wire adjacent to the connector.

9 Install identification tape 289T0202-11103 on the added wire adjacent to the connector.

10 Install identification tape 289T0202-11104 on the added wire adjacent to the connector.

REFERENCE: 767 WIRING DIAGRAMS 28-25-11, 28-25-31, 28-41-31

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

989752

FIGURE 20. P37 PANEL WIRING MODIFICATION - ALL AIRPLANES

Jul 1/93 SHEET 3 OF 3 767-28-0034

REV 3: Mar 14/96 109
BOEING SERVICE BULLETIN 767-28-0034

1

P50 ELEC SYSTEM CARD FILE

D10064

SPEED CARD

N2 ENGINE

M1093 LEFT

054-24

46

14

47

W1114

14

AE0202

D8036J

POS 3

P

15 056-24

W596

A71409

The instruction numbers shown below agree with the numbers shown inside the flag symbols in the

figure.

1 D10064 is D13600 for these airplanes:

Group 3: VN111-VN115

Group 13: VN116-VN124, VN130-VN132

REFERENCE: 767 WIRING DIAGRAM 28-25-31

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

989752

FIGURE 21. P50 PANEL WIRING MODIFICATION - GROUPS 1-3, 5-7, 9, 11-13, 15-18, 20 AIRPLANES

Jul 1/93 SHEET 1 OF 1 767-28-0034

REV 3: Mar 14/96 110
BOEING SERVICE BULLETIN 767-28-0034

3

4

2

1

W1722-025-24

24

W1730-024-24

W2000

B4

B5

AE0219

J D5334P

POS 22

23

W142

P33 FWD MISC ELEC

EQUIP PNL

5

AE0224

W198

D5378P

POS 9

J

W1730-025-24

E8 EICAS RACK

W2002

(4 PLACES)

AE0203

D6230P J

POS 16

J

B5

D6222P

POS 20

P37 RIGHT MISC

ELEC EQUIP PNL

A71458

The instruction numbers shown below agree with the numbers shown inside the flag symbols in the

figure.

1 Remove insert blank D-659-0004 at insert B of connector D6230P and install wafer

MTC100-JB2-S11-T16.

2 Pin Contact BACC47CN1A

3 Use splice D-436-36 to connect the wire to stub wire at the connector.

4 Dead-end the shield with sleeve cut from 289T0202-133 as specified in the Boeing Standard Wiring

Practices Manual, Chapter 20, Sections 20-10-14 and 20-10-15.

REFERENCE: 767 WIRING DIAGRAMS 28-22-31, 28-25-31

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

989752

FIGURE 22. E8 AND P33, P37 PANELS INTERCONNECTION WIRING MODIFICATION - ALL AIRPLANES

Jul 1/93 SHEET 1 OF 1 767-28-0034

REV 3: Mar 14/96 111
BOEING SERVICE BULLETIN 767-28-0034

1 4

2

5

3

12

11

10

4

1

6

7

3

5

2

9

(2 PLACES)

J

POS 10

D5890P

PRESSURE SEAL

BL L45

WL 197

STA 1031

GD432-DC

POS 18

101-20

P33 FWD MISC ELEC

EQUIP PNL

(8 PLACES)

(7 PLACES)

W1274

W/W DISC

AL1003

DISC.

LEFT SIDE

AE0207

W460

003-22

002-22

301Y-18

103-20

10

3

5

6

010-20

301R-18

102-20

7

2

001-22

100-20

301B-18

8

4

1

W142

D4600J P

A71663

FIGURE 23. P33 PANEL AND WHEEL WELL AREA INTERCONNECTION WIRING MODIFICATION -

GROUP 1 AIRPLANES

Jul 1/93 SHEET 1 OF 2 767-28-0034

REV 3: Mar 14/96 112
BOEING SERVICE BULLETIN 767-28-0034

The instruction numbers shown below agree with the numbers shown inside the flag symbols in the

figure.

1 Remove plug BACC45FT14-7P. Reterminate wires from the removed plug to the same pin number in

the new plug BACC45FT14-12P9. Install plug BACC45FT14-12P9 and identification tape

289T0202-12501.

2 Socket Contact BACC47CP2T

3 Use the pin contact included with the connector.

4 Terminal Block Contact BACC47DE7

5 Dead-end the shield with sleeve cut from 289T0202-133 as specified in the Boeing Standard Wiring

Practices Manual, Chapter 20, Sections 20-10-14 and 20-10-15.

REFERENCE: 767 WIRING DIAGRAMS 28-22-11, 28-22-31, 28-42-12

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

989752

FIGURE 23. P33 PANEL AND WHEEL WELL AREA INTERCONNECTION WIRING MODIFICATION -

GROUP 1 AIRPLANES

Jul 1/93 SHEET 2 OF 2 767-28-0034

REV 3: Mar 14/96 113
BOEING SERVICE BULLETIN 767-28-0034

1

4

2

5

3

004-16

005-16

006-16 SM6

SM5

SM4

PRESSURE SEAL

12

11

10

1

6

7

5

9

(2 PLACES)

J

POS 10

D5890P

BL L45

WL 197

STA 1031

GD432-DC

POS 18

101-20

P33 FWD MISC ELEC

EQUIP PNL

(8 PLACES)

(7 PLACES)

W1274

W/W DISC

AL1003

DISC.

LEFT SIDE

AE0207

W460

003-22

002-22

103-20

10

3

5

6

010-20

102-20

7

2

001-22

100-20

8

4

1

W142

D4600J P

A71673

FIGURE 24. P33 PANEL AND WHEEL WELL AREA INTERCONNECTION WIRING MODIFICATION -

GROUPS 2, 6, 9, 12, 15 AIRPLANES

Jul 1/93 SHEET 1 OF 2 767-28-0034

REV 3: Mar 14/96 114
BOEING SERVICE BULLETIN 767-28-0034

The instruction numbers shown below agree with the numbers shown inside the flag symbols in the

figure.

1 Remove plug BACC45FT14-7P. Reterminate wires from the removed plug to the same pin number in

the new plug BACC45FT14-12P9. Install plug BACC45FT14-12P9 and identification tape

289T0202-12501.

2 Socket Contact BACC47CP2T

3 Use the pin contact included with the connector.

4 Terminal Block Contact BACC47DE7

5 Dead-end the shield with sleeve cut from 289T0202-133 as specified in the Boeing Standard Wiring

Practices Manual, Chapter 20, Sections 20-10-14 and 20-10-15.

REFERENCE: 767 WIRING DIAGRAMS 28-22-11, 28-22-31, 28-42-12

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

989752

FIGURE 24. P33 PANEL AND WHEEL WELL AREA INTERCONNECTION WIRING MODIFICATION -

GROUPS 2, 6, 9, 12, 15 AIRPLANES

Jul 1/93 SHEET 2 OF 2 767-28-0034

REV 3: Mar 14/96 115
BOEING SERVICE BULLETIN 767-28-0034

1 4

2

5

3

4

3

D4600J P

009-14

008-14

007-14

PRESSURE SEAL

12

11

10

1

6

7

5

9

J

POS 10

D5890P

BL L45

WL 197

STA 1031

GD432-DC

POS 18

101-20

P33 FWD MISC ELEC

EQUIP PNL

(8 PLACES)

(7 PLACES)

W1274

W/W DISC

AL1003

DISC.

LEFT SIDE

AE0207

W460

003-22

002-22

103-20

10

3

5

6

010-20

102-20

7

2

001-22

100-20

8

4

1

W142

(4 PLACES)

A71676

FIGURE 25. P33 PANEL AND WHEEL WELL AREA INTERCONNECTION WIRING MODIFICATION -

GROUPS 3-5, 7, 8, 10, 11, 13, 14, 16-20 AIRPLANES

Jul 1/93 SHEET 1 OF 2 767-28-0034

REV 3: Mar 14/96 116
BOEING SERVICE BULLETIN 767-28-0034

The instruction numbers shown below agree with the numbers shown inside the flag symbols in the

figure.

1 Remove plug BACC45FT14-7P. Reterminate wires from the removed plug to the same pin number in

the new plug BACC45FT14-12P9. Install plug BACC45FT14-12P9 and identification tape

289T0202-12501.

2 Socket Contact BACC47CP2T

3 Use the pin contact included with the connector.

4 Terminal Block Contact BACC47DE7

5 Dead-end the shield with sleeve cut from 289T0202-133 as specified in the Boeing Standard Wiring

Practices Manual, Chapter 20, Sections 20-10-14 and 20-10-15.

REFERENCE: 767 WIRING DIAGRAMS 28-22-11, 28-22-31, 28-42-12

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

989752

FIGURE 25. P33 PANEL AND WHEEL WELL AREA INTERCONNECTION WIRING MODIFICATION -

GROUPS 3-5, 7, 8, 10, 11, 13, 14, 16-20 AIRPLANES

Jul 1/93 SHEET 2 OF 2 767-28-0034

REV 3: Mar 14/96 117
BOEING SERVICE BULLETIN 767-28-0034

12 W624-109-22 38

1 1

3

2

1

3

4

POS 17

D5744P J

W142

POS 71

P33 DISC

AE0203

P33 DISC

AE0207

P61 DISC

AF204

(5 PLACES) (5 PLACES)

13

J D5356P

(10 PLACES)

W624-110-22 39

W066

W624-107-20

W624-106-20

W062 W144

(4 PLACES)

(4 PLACES)

(8 PLACES)

56 W756-645-22 29

55 W756-644-22 55

54 W756-643-22 54

D5664P J

POS 06 POS 34

J D4714P

53 W756-642-22 53

1

11

8 36

37

W624-108-22 15

W624-070-24

A71704

FIGURE 26. P33 AND P61 PANEL INTERCONNECTION WIRING MODIFICATION - ALL AIRPLANES

Jul 1/93 SHEET 1 OF 2 767-28-0034

REV 3: Mar 14/96 118
BOEING SERVICE BULLETIN 767-28-0034

The instruction numbers shown below agree with the numbers shown inside the flag symbols in the

figure.

1 Pin Contact BACC47CN1A

2 Socket Contact BACC47CP1A

3 Dead-end the shield with sleeve cut from 289T0202-133 as specified in the Boeing Standard Wiring

Practices Manual, Chapter 20, Sections 20-10-14 and 20-10-15.

4 Cap and stow wire with end cap 324484 as specified in the Boeing Standard Wiring Practices Manual,

Chapter 20, Section 20-10-15.

REFERENCE: 767 WIRING DIAGRAM 28-22-31

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

989752

FIGURE 26. P33 AND P61 PANEL INTERCONNECTION WIRING MODIFICATION - ALL AIRPLANES

Jul 1/93 SHEET 2 OF 2 767-28-0034

REV 3: Mar 14/96 119
BOEING SERVICE BULLETIN 767-28-0034

1

W184

W590

8

2

3

068-18

039-18

14

13

29

AE0209

P36 DISC.

J

042-18

050-24

049-24

048-24

047-24

16

22

3

20

14

20

9

7

D5052P

POS 7

AE0224

W198

AL1005

W482

P61 DISC.

AF0204

W070 4

J

POS 09

D4856P

009-18 18

P

POS 08

D5698J

D4854P

POS 85

J

P37 DISC.

A71722

FIGURE 27. P36, P37 AND P61 PANELS INTERCONNECTION WIRING MODIFICATION - ALL

AIRPLANES

Jul 1/93 SHEET 1 OF 2 767-28-0034

REV 3: Mar 14/96 120
BOEING SERVICE BULLETIN 767-28-0034

The instruction numbers shown below agree with the numbers shown inside the flag symbols in the

figure.

1 The wire is 22 gage for some airplanes

REFERENCE: 767 WIRING DIAGRAMS 28-22-31, 28-25-31

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

989752

FIGURE 27. P36, P37 AND P61 PANELS INTERCONNECTION WIRING MODIFICATION - ALL

AIRPLANES

Jul 1/93 SHEET 2 OF 2 767-28-0034

REV 3: Mar 14/96 121
BOEING SERVICE BULLETIN 767-28-0034

2

5 7

4

6

3

8

1

9

10

11

12

5

4

2

3

D20058

STA 954

WL 170

BL L29

(J1)

W460-100-18

J

V388 FWD FUEL

CROSSFEED VALVE

W1274

D4600P

POS 18

W460-101-18

W460-102-18

W460-103-18

7

GD4050-S

STA 1015

WL 191

BL L38

W460-104-18

W/W DISC.

AL1003

(10 PLACES)

(4 PLACES)

(5 PLACES)

W482-301Y-18

W482-301B-18

W482-301R-18

3

5

2

W482-004-18 4

7

(J1)

W482-013-18

8

2

3

W590

J

POS 08

D5698P

STA L0253

WL 14

BL RS

AL1005

GD4070-S

GD3440-DC

STA LO246

WL 14

BL RS

BL RS

WL 14

GD4038-S GD4070-S

STA 1047 STA LO253

WL 191

BL L64

D1258

STA L0250

WL 14

BL RS V97 APU FUEL

ISOLATION VALVE

A71789

FIGURE 28. WHEEL WELL AREA WIRING MODIFICATION - ALL AIRPLANES

Jul 1/93 SHEET 1 OF 3 767-28-0034

REV 3: Mar 14/96 122
BOEING SERVICE BULLETIN 767-28-0034

19

STA R0291

SP 1952

SP 772

BL RS

WL 14

STA R0272

AL1002

W/W DISC.

W452-011-20

POS 5

J D4278P

W656

D1532

1

3

2

BL R064

WL 191

STA 1007

GD4044-S

GD4120-S STA R0300

WL 14

BL RS

W452-007-20

S72 R FWD

SW

PUMP PRESS.

FUEL BOOST

BL RS

WL 14

PUMP PRESS.

FUEL BOOST

1

BL RS

WL 14

1

SW

W464-023-20

(J1)

(J1)

D2808

STA R0257

FUEL OVRD PUMP

PRESS. SW

WL 14

BL RS

STA R0261

GD4108-S

W464-024-20

GD4120-S

STA R0300

WL 14

BL RS

S73 R AFT

S424 R AUX TANK

STA R0294

BL RS

WL 14

D2822

A71922

FIGURE 28. WHEEL WELL AREA WIRING MODIFICATION - ALL AIRPLANES

Jul 1/93 SHEET 2 OF 3 767-28-0034

REV 3: Mar 14/96 123
BOEING SERVICE BULLETIN 767-28-0034

The instruction numbers shown below agree with the numbers shown inside the flag symbols in the

figure.

1 Install plug BACC63BP14A7SNL, adapter 710AS011M-1412-62A, and identification tape

289T0202-11501.

2 Install convoluted tubing 289T0202-135 as follows:

a. Cut the convoluted tubing to the length that the convoluted tubing covers the wire bundle to

first breakout approximately 13 feet from connector D20058.

b. Install the tubing over all wires of wire bundle assembly 286T0460 (W460)

c. Attach the convoluted tubing to the adapter of connector D20058.

3 Use contacts included with the new connector

4 Pin Contact BACC47CN2

5 Lug BACT12M-4

6 Dead-end the shield with sleeve cut from 289T0202-133 as specified in the Boeing Standard

Wiring Practices Manual, Chapter 20, Sections 20-10-14 and 20-10-15.

7 Do the bonding resistance check between the valve body and the ground as specified in the

Boeing Standard Wiring Practices Manual, Chapter 20, Section 20-20-00. The bonding resistance

should not exceed 0.001 ohm.

8 Remove the existing plug and clamp.

REFERENCE: 767 WIRING DIAGRAMS 28-22-31, 28-25-31, 28-42-31

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

989752

FIGURE 28. WHEEL WELL AREA WIRING MODIFICATION - ALL AIRPLANES

Jul 1/93 SHEET 3 OF 3 767-28-0034

REV 3: Mar 14/96 124
BOEING SERVICE BULLETIN 767-28-0034

2

4

5

3

7

4

W596

1

6 8

(4 PLACES)

16

15

3

4

J

W454-033-18

W454-034-18

W454-012-18

STA 999

WL 193

BL L64

D4602P

POS 7

W454-027-18

GD4134-S

5

2

3

4

7

V389 AFT FUEL

CROSSFEED VLV.

STA 954

WL 170

BL L29

W454-032-18

5

2

3

4

7

CROSSFEED VLV.

V24 FUEL

STA L0246

WL 14

BL RS

GD 4134-S

D1544 (J1)

(J1)

AL1001

PRESSURE

SEAL

GD432-DC

STA 1031

WL 197

BL L45

W596-199-20

W454-301B-20

W454-301R-20

W454-301Y-20

GD4056-S

STA L0259

WL 12

BL RS

BL RS

STA L0253

WL 14

W454-012-18

BL RS

STA L0253

GD 3388-DC

WL 12 GD 4070-S

D1544

W454-027-18

(5 PLACES)

A72267

FIGURE 29. WHEEL WELL AREA WIRING MODIFICATION - GROUPS 1-9, 12, 15, 16, 18-20 AIRPLANES

Jul 1/93 SHEET 1 OF 2 767-28-0034

REV 3: Mar 14/96 125
BOEING SERVICE BULLETIN 767-28-0034

The instruction numbers shown below agree with the numbers shown inside the flag symbols in the

figure.

1 Remove plug BACC63BP14R7SNL and clamp BACC10HF14. Keep plug

BACC63BP14R7SNL.

2 Install kept plug BACC63BP14R7SNL, adapter 710AS011M-1412-62A, and identification

tape 289T0202-11301.

3 Install convoluted tubing 289T0202-135 as follows:

a. Cut the convoluted tubing to the length that the convoluted tubing covers the wire bundle

to first breakout approximately 13 feet from connector D1544.

b. Install the tubing over all wires of wire bundle assembly 286T0454 (W454)

c. Attach the convoluted tubing to the adapter of connector D1544.

4 Socket Contact BACC47CP2T

5 Pin Contact BACC47CN2

6 Lug BACT12M-4

7 Terminal Block Contact BACC47DE7

8 Do the bonding resistance check between the valve body and the ground as specified in the

Boeing Standard Wiring Practices Manual, Chapter 20, Section 20-20-00. The bonding

resistance should not exceed 0.001 ohm.

REFERENCE: 767 WIRING DIAGRAM 28-22-31

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

989752

FIGURE 29. WHEEL WELL AREA WIRING MODIFICATION - GROUPS 1-9, 12, 15, 16, 18-20 AIRPLANES

Jul 1/93 SHEET 2 OF 2 767-28-0034

REV 3: Mar 14/96 126
BOEING SERVICE BULLETIN 767-28-0034

1

BL L29

AL1001

D1544 (J1)

W454-032-18

WL 170

STA 954

CROSSFEED VLV.

V389 AFT FUEL

7

4

3

2

5

GD4134-S

W454-027-18

POS 7

D4602P

W454-012-18

W454-034-18

W454-033-18

J

4

3

15

16

W596

W454

A72301

The instruction numbers shown below agree with the numbers shown inside the flag symbols in the

figure.

1 Remove the existing identification tape and install new identification tape 289T0202-11401.

REFERENCE: 767 WIRING DIAGRAMS 28-22-31

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

989752

FIGURE 30. WHEEL WELL AREA WIRING MODIFICATION - GROUPS 10, 11, 13, 14, 17 AIRPLANES

Jul 1/93 SHEET 1 OF 1 767-28-0034

REV 3: Mar 14/96 127
BOEING SERVICE BULLETIN 767-28-0034

W1274 5

W1730 4

PRESSURE

SEAL 6

P11 PANEL

DISCONNECT

PANEL

AL1003

SEE

DETAIL I

P61

PANEL

W624

W756

3

W066

W070

1

W042 2 P5 PANEL

A72325

FIGURE 31. WIRING INSTALLATION - ALL AIRPLANES

Jul 1/93 SHEET 1 OF 3 767-28-0034

REV 3: Mar 14/96 128
BOEING SERVICE BULLETIN 767-28-0034

7

7

287T0011-2

287T0011-4

CLAMP

CLAMP

LEFT WHEEL WELL AREA

DETAIL I

FUEL

CROSSFEED

VALVE V388

FUEL

CROSSFEED

VALVE V389

7

FWD

UP

EXISTING WIRE

BUNDLE ROUTING

A73027

FIGURE 31. WIRING INSTALLATION - ALL AIRPLANES

Jul 1/93 SHEET 2 OF 3 767-28-0034

REV 3: Mar 14/96 129
BOEING SERVICE BULLETIN 767-28-0034

The instruction numbers shown below agree with the numbers shown inside the circle symbols in the

figure.

NOTE: Route new wires with the existing wire bundles as specified in the Boeing Standard Wiring

Practices Manual, Chapter 20, Section 20-10-11.

1 Route the new wires from P61 panel to P5 panel with the existing wire bundle routing.

2 Route the new wires from P61 panel to P11 panel with the existing wire bundle routing.

3 Route the new wires from P61 panel to P33 panel with the existing wire bundle routing.

4 Route the new wires from P8 panel to P33 panel with the existing wire bundle routing.

5 Route the new wires from P33 panel to wheel well disconnect panel AL1003 with the existing

wire bundle routing.

6 To route new wires through the seals, replace the pressure seal using parts contained in seal

replacement kit 287T0110-16. Refer to 767 Maintenance Manual Subject 51-31-01.

7 Do the applicable steps:

a. For Groups 10, 11, 13, 14, 17 airplanes, route the new wires to the crossfeed valves with

the existing wire bundle routing.

b. For Groups 1-9, 12, 15, 16, 18-20 airplanes, route the new wires to the crossfeed valves

as shown and secure the wire with clamps 287T0011-2 and 287T0011-4.

FIGURE 31. WIRING INSTALLATION - ALL AIRPLANES

Jul 1/93 SHEET 3 OF 3 767-28-0034

REV 3: Mar 14/96 130
BOEING SERVICE BULLETIN 767-28-0034

M10055

C PUMPS

a

P

R

E

S

S

ON

a

P

R

E

S

S

ON

w w

w

VALVE a

w

VALVE a

CROSSFEED

ON

a

PRESS

ON

a

PRESS

LEFT RIGHT

L PUMPS

FUEL

R PUMPS

AFT

FWD

AFT

FWD

ON

PRESS

ON

a

PRESS

w

w

w

w

a

P5

PILOT

OVERHEAD

PANEL

1

A73047

FIGURE 32. FUEL MANAGEMENT PANEL REPLACEMENT - ALL AIRPLANES

Jul 1/93 SHEET 1 OF 2 767-28-0034

REV 3: Mar 14/96 131
BOEING SERVICE BULLETIN 767-28-0034

The instruction numbers shown below agree with the numbers shown inside the circle symbols in the

figure.

1 Install new fuel management panel as follows:

a. Remove and discard the existing light plate assembly

b. Disconnect the electrical connector and remove existing fuel management panel

c. Connect the electrical connector and install the applicable fuel management panel.

Airplanes Fuel Management Panel

Groups 1-14, 18-20 233T3235-21

Groups 15-17 233T3235-23

d. Install light plate assembly S233T100-1106.

FIGURE 32. FUEL MANAGEMENT PANEL REPLACEMENT - ALL AIRPLANES

Jul 1/93 SHEET 2 OF 2 767-28-0034

REV 3: Mar 14/96 132
Commercial

Airplane

Group

767

Service Bulletin

Number: 767-28-0034 Evaluation Form Date: July 1, 1993

Revision 3: March 14, 1996

ATA System: 2822

Prepared By: Tuan Lam

SUBJECT: FUEL - DISTRIBUTION - DUAL CROSSFEED VALVE INSTALLATION

Use this evaluation form to tell us what you think of the quality of this service bulletin. We will use the data

that you give us to improve the quality of our service bulletins. Please include data about these or other

items:

- Did this service bulletin meet your estimate of quality?

- How easy is this service bulletin to understand?

- Are the Planning Information, Material Information and Accomplishment Instructions satisfactory?

- Will you do this service bulletin fully? If not, please tell us why.

- Is the Manpower estimate satisfactory?

NOTE: Please do not use this evaluation form to tell us to make changes to your manuals. To make these

changes, please use a Publication Change Request (PCR) form.

Please give us this data:

OPERATOR: TODAY'S DATE:

PREPARED BY: TITLE:

ORGANIZATION: TELEX CODE:

TELEPHONE NUMBER:

COMMENTS:

If you have other comments please use the other side. Thank you for the time you used to complete this

form.

Give the completed evaluation form to your Boeing Field Service Representative or send the evaluation form

directly to this address:

T.J. Taylor, Manager

Service Bulletin Engineering

Boeing Commercial Airplane Group

P.O. Box 3707, Mail Stop 20-85

Seattle, WA 98124-2207

BOEING COMMERCIAL AIRPLANE GROUP P.O. BOX 3707 SEATTLE, WASHINGTON 98124-2207