### 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: MANAGEMENT PANEL BREAKERS -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, 20A73832

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

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### 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

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### 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

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### 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

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### 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

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### 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

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### 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.

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### 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.

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### 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

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### 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.

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### 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

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### 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

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### 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

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### 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

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### 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

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### 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

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### 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.

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### 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

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### 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.

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### 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.

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### 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.

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### 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"

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### 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.

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### 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"

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### 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"

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### 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 SPARA66999

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) OUTBDUP FWD 1A67016

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 SPARA67307

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

CC 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 (27 PLACES) 2

N 

### (11 PLACES) 3 

## A A
B

DETAIL I B 6 1 6 8 SEE

3 9 7 10 6 1 1 2 1 2

6 1 6 1 DETAIL IIA67381

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 PLACES) 4 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 IIA67598

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 25.63A67637

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

2 1 (27 PLACES) 2 8 2
1 6

1 6 2 1

1 6
10 7 9 3 SEE 8 6



## B

DETAIL I B A

A DETAIL IIA67642

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 BRACKET 6 DOUBLER 111T1016-3 DOUBLER 111T1016-2



## VIEW B-B DETAIL II (4 PLACES) 4 0.30

RIVET BACR15FT3AD5 0.839 0.840 0.921 0.750

5

11 

## VIEW A-AA67643

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

25.63 32.94 LBBL LBBL 10.06 SEE DETAIL IIIR29019

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 (27 PLACES) 3

N 

### (11 PLACES) 4 

## A A
B

DETAIL I B 7 1 7 9 SEE

4 8 12 1 3 1 3

7 1 7 1 DETAIL II

7 1 11R29020

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 (4 PLACES) 5 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
6R29022

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

12 C A 12 C A

12 C B12 C A 10 7 1 12 7 1 12 7

12 7 1 12 7 2

1



## DETAIL III INBD UP C C A

AR29023

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 7R29058

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 SPARA67266

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

4 6 1 3 6 1 DETAIL I SEE

INBD UP REAR SPAR

WRPR26725

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 WRPR26728

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 4 3

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 10A67845

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 10A67829

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 DA67862

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 FITTINGA68029

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 FWDB97446

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 346T0010-12INBD UP 

## EXISTING CONFIGURATION 3

249.75 WS 4 1 2

MS29513-212(2) AS1712D12

6 

## VIEW A-A

VIEW C-C SECTION B-B

7 UP FWD INBD 

## C C 7 8

FWD 9 6 

## A A
B B MS29513-216(2) AS1712D16

249.75 WS 

## NEW CONFIGURATION INBD UP 5A68090

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 WINGA68422

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

P11-4 P11-1 P11-5 P11-2 P11-6 P11-3 FLIGHT COMPARTMENTA68451

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 C1058 C1052 

### D 35 34 36 C1069 C1070 C1066



### 22 21 20 M M

25 21 22 23 24 20 19 C1070 C1069



### 2 2 VALVE R CTR NOZZLE CONT 2 QTY M R AFT L FWD PUMPS RIGHT JETT FUEL AFT FWD 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 IIA68656

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 UPA68674

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 BC22631

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) 3 W044 AF0203 POS 02
J D5012P

P61 RIGHT SIDE PNL POS 7 AF201

D5010P J 1

(6 PLACES) XD38 W062 TB104 POS 76

D5410P 4 W1716 J 604-20 GD110-DC TB104 W590

W590 510-22 W062 YC36 4 AF0204 POS 85 

# W070

591-22 XB37 W066 31 D4854P J
XD37 XC37 509-22 W066 XA37 587-22

W066 W066 587-22

604-22

022-22 W044 (4 PLACES)

P5 PLT OVHD PNL FUEL MANAGEMENT PNL M10055(YCL) D1384 J3 5 21 2 11 7

24 10

585-22A69946

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



### P61 RIGHT SIDE PNL P5 PLT OVHD 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

D4286PA69969

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 4 8

6 1 3



### P61 RIGHT SIDE PNL W042 AF0204 POS 04

J D7972P 521-22 XA37 W070 W062 XA38 536-22

XB38 537-20 POS 71

J D5356PW624 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 ROUTING989752

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

AE0219W1722

D6222P B5 J

B01 BXX B05

D883A D6D883F

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 HN05-24 DISAGREEMENT APU ISO VALVE D883F D883A COMPUTER M10181 L EICAS W2002 HL05-24

# W2000 D881A
D881F E6 DISAGREEMENT APU ISO VALVE

B04A70331

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 ROUTING989752

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 AE0219W1722

D6222P B5 J

B01 B05

D6D883F
D883D D881F D6

D881D

C14 M10181 L EICAS M10182 R EICAS COMPUTER

COMPUTER VALVE FUEL CROSSFEED C14

VALVE FUEL CROSSFEED E6 W2002 HN05-24 DISAGREEMENT APU ISO VALVE D883F D883A COMPUTER M10181 L EICAS W2002 HL05-24

# W2000 D881A
D881F E6 DISAGREEMENT APU ISO VALVE

B04

FWD FWD

AFT AFTA70373

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 ROUTING989752

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 D7972P J 4 

### 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 1 2

VALVE CB

CROSSFEED FWD FUEL 2 W032-031-8 P D5012J 3 020-22 C1051 1 2 2 

# W044 13 TB5022

P 1 2 510-22

C1071 1 D5010J
W070 W070 AF201

VALVE CB CROSSFEED CROSSFEED IND. CB 1 6



### W066

(6 PLACES) 4A70433

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 ROUTING989752

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
C1A70461

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 9 10

12

13



### TB268 14 

### W144 XC2 (7 PLACES)

(8 PLACES) (28 PLACES)

10P-22 10S-22 38 8 10D-22 3 14

4 13 2 10J-20 GDX4-DC 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

1 10N-20 GDX4-DC

DISAGREE RELAY D2985 TB268

YC9 W144 YA5 W144 AE207

D5890J POS 10 P W1274

23 24 

# W142

10I-20 10H-20 36 37 AE0203

AE0203 P D5744J POS 17 10F-22 15 W624

P33-FWD MISC ELEC EQUIP PNL K2151 AFT CROSSFEED W1730 7

13 4A70650

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

7 53 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

656-22 YC9 648-22

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 ROUTING989752

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 3 

### W1718 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%

A2 W176-04N-24 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.1A71024

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 ROUTING989752

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 

### C A

113-20 P POS 7 D5052J

W192-634-24

P P 34 W656 POS 24 D4346J 2 D4284J POS 26 W620 C2 D3708 K175 APU FUEL CONTROL RLY Z9

AE0218
P D5270J POS 12 16 087-24 YC1 TB86 K632 C PUMP AUTO ON RLY D10066 D3 D1 D2K191 DC FUEL PUMP CONT RLY X1 D3726
TB274 R39 APU DC PUMP CONT DIODE X2 

# W198
506-24 21 YA7 TB86 090-24 090-24 AE0224 W0590

088-24 088-24

113-20 089-24

503-22

C3 C1 504-22A71167

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 D5052J P 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 5 W1722 AE0224

P37 RIGHT MISC ELEC EQUIP PNL 102-22 101-22A71404

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 ROUTING989752

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 W596A71409
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 ROUTING989752

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

J D6230P POS 16

J B5 D6222P POS 20 P37 RIGHT MISC ELEC EQUIP PNLA71458
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 ROUTING989752

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 PA71663

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 ROUTING989752

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 PA71673

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 ROUTING989752

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

P D4600J 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 ROUTING989752

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 D5356P J (10 PLACES) W624-110-22 39 W066 W624-107-20 W624-106-20 W144 W062 (4 PLACES)

(4 PLACES) (8 PLACES) 29 W756-645-22 56 55 W756-644-22 55 54 W756-643-22 54

J D5664P POS 06 POS 34 D4714P J 53 W756-642-22 53

1 11 8 36 37 15 W624-108-22 W624-070-24A71704

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 ROUTING989752

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 4 W070 J POS 09 D4856P 18 009-18 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 ROUTING989752

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 4 W482-004-18

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 LO253 STA 1047 WL 191 BL L64

D1258 STA L0250 WL 14 BL RS V97 APU FUEL ISOLATION VALVEA71789

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 D4278P J 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 D2822A71922

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 ROUTING989752

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

8 6 

### (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 GD 4070-S WL 12

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 ROUTING989752

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

(J1) D1544 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 

# W454A72301The 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 ROUTING989752

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 5W1730 4

PRESSURE 6 SEAL P11 PANEL

DISCONNECT PANEL AL1003 SEE DETAIL I P61 PANEL W624 W756 3 W066 W070 1 W042 2 P5 PANELA72325

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 ROUTINGA73027

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

1A73047

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