fJ-DDEINO·· Commercial 

Airplane 

Group 747 

Number: 

Date: 

ATA System: 

SUBJECT, 

747-28-2265 

February 22, 2006 

2811 

Service Bulletin 

CONVERSION Airplane from a 747-400 Passenger configuration to a 747-400 Special 

Freighter (SF) Configuration - Horizontal Stabilizer Tank Deactivation 

BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET 

Copyright © 2006 The Boeing Company 

Unpublished Work - All Rights Reserved 

Boeing claims copyright in each page of this document only to the extent thaI the page contains copyrightable 

subject matter. Boeing also claims copyright in this document as a compilation andlor collective work. 

This document includes proprietary information owned by The Boeing Company and/or one or more third 

parties. Treatment of the document and the information it contains is governed by contract with Boeing. For 

more information, contact The Boeing Company, P.O. Box 3707. Seattle, Washington 98124. 

Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777. BBJ , DC-B. DC-9, 

OC-10. MO-10, MO-11, MO-80, MO-88. MO-90. and the red-white-and-blue Boeing livery are all trademarks 

owned by The Boeing Company; and no trademark license is granted in connection with this document unless 

provided in writing by Boeing. 

February 22, 2006 

BOEING PROPRIETARY . Copyright I!> Unpubiished Worl< _ See p.<lge 1 for details. 

747-28-2265 

1 of68 
BOEING SERVICE BULLETIN 747-28-2265 

BLANK PAGE 

BLANK PAGE 

February 22, 2006 

BOEING PROPRIETARY. Copynght C Unpubl's.hed WQIic. See Pi'lle 1 for delll"' _ 

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BOEING SERVICE BULLETIN 747-28-2265 

Summary 

1. PLANNING INFORMATION. 

A. Effectivity . 

1. Airplanes 

2. Spares Affected . 

B. Concurrent Requirements 

C. Reason . 

D, Description . 

E. Compliance , 

F. Approval .. 

G, Manpower 

H. Weight and Balance Changes. 

I. Electrical Load Data 

J. References. 

1. Existing Data: , 

Table of Contents 

2. Data supplied with this Service Bulletin: 

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

4. Process Data: 

K. Publications Affected . 

L Interchangeability and Intermixabilily of Parts . 

2. MATERIAL INFORMATION . 

A Material- Price and Availability .. 

B. Industry Support Information ... 

C. Parts Necessary For Each Airplane 

1. Kits/Parts: 

2. Parts and Materials Supplied by the Operator: 

3. Parts Modified and Reidentified: 

4. Parts Removed and Not Replaced: 

D. Parts Necessary to Change Spares . 

E. Special Tooling - Price and Availability. 

F. Special Tooling Necessary to do this Service Bulletin . 

3. ACCOMPLISHMENT INSTRUCTIONS . 

A. GENERAL INFORMATION 

B. WORK INSTRUCTIONS . 

. 5 

. 9 

. 9 

. 9 

. 9 

10 

10 

10 

11 

11 

11 

11 

11 

12 

12 

12 

13 

13 

14 

14 

15 

15 

15 

15 

15 

16 

16 

17 

17 

17 

18 

19 

19 

19 

FIGURE 1: OVERHEAD CIRCUIT BREAKER PANEL P7-2 CHANGE . 31 

FIGURE 2: HORIZONTAL STABILIZER TANK AFT FUEL TRANSFER SYSTEM LOCATION 33 

FIGURE 3: HORIZONTAL STABILIZER TANK FWD FUEL TRANSFER SYSTEM LOCATION 35 

FIGURE 4: LEFT WING REFUELING PANEL P42 MODIFICATION . 37 

FIGURE 5: H.STAB FUEL PUMP LOW PRESSURE SWITCHES AND P85 PANEL CHANGE 39 

FIGURE 6: HORIZONTALSTABILIZER TRANSFER PUMP MOTOR IMPELLER ASSY CHANGE 41 

FIGURE 7: REMOTE ELECTRONIC UNIT CHANGES - E8 EQUIPMENT RACK 44 

FIGURE 6: FUEL SYSTEM CARD FILE CHANGE 46 

FIGURE 9: FUEL MANAGEMENT CONTROL PANEL CHANGE .. 47 

FIGURE 10: DEACTIVATION OF TAIL TANK AT LEFT, CENTER, AND RIGHT EIU - E2-6 WlU WIRE 

CHANGE 46 

Table of Contents 

February 22, 2006 

BOEING PROPRIETARY · COP1righ~ C' Unp",toishcd Worit - See pasc 1 for det1lns. 

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BOEING SERVICE BULLETIN 747-28-2265 

FIGURE 11 : REWORK OF HORIZONTAL STABILIZER TANK TRANSFER LINE 

FIGURE 12: REWORK OF WiRE BUNDLES 

Table of Contents 

February 22, 2006 

BOEING PROPRIETARY . Copynght C Unpul>lisiled Wor\(· S~ page 1 lor de\a~1 

. 56 

. 66 

747-28-2265 

4 of 68 
Number: 

Date: 

ATA System: 

747-28-2265 

February 22, 2006 

2811 

Commercial 

Airplane 

Group 747 

Service Bulletin 

Summary 

SUBJECT: CONVERSION Airplane from a 747-400 Passenger configuration to a 747-400 Special 

Freighter (SF) Configuration - Horizontal Stabilizer Tank Deactivation 

CONCURRENT REQUIREMENTS 

Refer to Paragraph 1.B. 

BACKGROUND 

As part of the special freighter conversion. the horizontal stabilizer fuel tank is to be deactivated and the fuel 

transfer line removed. This service bulletin provides instructions and kit of parts to do that. 

ACTION (MC 0300MK4010) 

On P7-2 overhead circuit breaker pane!. remove the Horizontal Stabilizer REFUEL & XFR circuit breakers 

C10125 and C10126. Rework the circuit breaker wiring. 

On P5 overhead pane!. remove the Fuel Management Control Module (M00154) and rework the wiring. 

At the FWD and AFT fuel isolation valves for the horizontal stabilizer transfer system, disconnect electrical 

connector from each valve actuator, coil and stow wiring. Position manual override lever for affected valves, 

located an valve actuator, to closed position and lock wire to secure in place. 

On the horizontal stabilizer refuel valve control unit, disconnect electrical connector, cap and stow wiring. 

On the P42 left wing refueling panel coil and stow wiring for indicator, switches and lights. Place "H.STAB TANK 

DEACTIVATED" placard above H.STAB indicator. 

On the E8 equipment rack , in the Remote Electronic Unit (REU), M7861 , remove REU cover plate and H.STAB 

Individual Fuel Quantity Channel (IFOC) card. Re-install REU cover plate. Placard REU "INOP' and rework the 

wiring. 

ON the E2 equipment rack, make changes to the left, center, and right Electronic Instrument Unit (EIU) 

configuration pins to disable the Horizontal Slab Tank display and associated messaging on the Integrated 

Display Unit (lOS). 

On P8S panel. remove HOR STAB XFER/JETT PUMP circuit breakers C031 41 and C03142. Remove HOR 

STAB XFER/JETI PUMP placard below the circuit breakers. Rework circuit breaker wire and pump wiring. Cap 

and stow plugs S1884 and S1885 for H.STAB fuel pump low pressure switches. 

February 22, 2006 

BOEING PROPRIETARY - Copyrignt e Unpublisned Work · See P3 \1e , tor del<uls 

747-28-2265 

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BOEING SERVICE BULLETIN 747-28-2265 

On the horizontal stabilizer transfer J jettison pumps, remove two motor impeller assemblies located on the front 

spar of H. Stab tank. Install plugs and associated pins. 

On the Fuel System Card File, remove horizontal stabilizer transfer Single Point Sensor Control (SPSC) card 

and install cover assembly. Coil and stow SPSC card wiring. Insert jumper wire in Fuel System Card File. 

On the Fuel Quantity Indicating System (FaIS). reprogram FQIS card file for Horizontal Stabilizer absent. 

On the Wire Interface Unit (WlU), mOdify affected wire bundles at W1U. 

On the fuel transfer line. remove and discard fuel transfer line from center wing tank to the horizontal stabilizer 

fuel tank, and install plugs. 

EFFECTIVITY 

Operator Airplanes 

CAT· Cathay RT456 

Pacific Airways 

COMPLIANCE 

Federal Aviation Administration (FAA) Airworthiness Directives; 97·03·17, 2002·19·52 and 2002·24·52, Final 

Rule Docket Number 2002·NM·314.AD, Amendment 39·12993 is related to this service bulletin. 

INDUSTRY SUPPORT INFORMATION 

Boeing Industry Support information is provided in Master Change 0300MK4010. 

MANPOWER 

Man Hours are not listed in this Service Bulletin they are negotiated separately between Boeing and the 

contracted modification facility. 

MATERIAL INFORMATION 

Negotiated Kits. 

February 22, 2006 

BOEING PROPRIETARY - Copynghl C Unpo.Jblished Work - See page ' ror dela's. 

747-28-2265 

60f68 
REMOVE SPS CARD FROM 

FUEL SYSTEM CARD FILE 

AND INSTALL COVER ASSY 

REMOVE FUEL 

MGMT PANEL 

INTHEP5~ 

L 

REMOVE REFUEL AND 

XFR STAB L AND 

STAB R CIRCUIT 

BREAKERS ON P7 

PANEL 

February 22, 2006 

BOEING SERVICE BULLETIN 747-28-2265 

pas I T I ON MANUAL OVERR I DE LEVER 

FOR FWD ISOLATION VALVES TO 

CLOSE POSITION AND DISCONNECT 

ELECTR! CAL CONNECTOR FROM 

VALVE ACTUATOR 

REMOVE 2 MOTOR 

IMPELLER UNITS. 

I NSTALL PLUGS 

/ 

pas I T I ON MANUAL OVERR I DE 

LEVER FOR AFT ISOLAT ION 

VALVES TO CLOSE POSITION 

AND 0 I SCONNECT 

ELECTRICAL CONNECTOR FRO~~ VALVE ACTUATOR 

I N AFT EQU j PMENT RACK £8 

REMOVE I FOC CARD IN REU . 

PLACARD REU I NOP . REMOVE 

2 C I RU I T BREAKERS ON PBS 

PANEL . 

PLACARD "H. STAB TANK 

DEACTIVATED" ON LEFT 

WING REFUELING P42 PANEL 

REMOVE HOR I ZONT Al 

STABILIZER FUEL 

TRANSFER II NE AND 

INSTALL PLUGS 

REMOVE RELAYS AND CHANGE THE 

WIRING AT THE P7 , P414 FUEL 

SYSTEM CARD FILE, E2-6 SHELF AND 

THE P54 PANEL . REV I SE PIN 

PROGRAMMI NG TO THE LEFT , CENTER 

AND RIGHT EIU ON SHELF 6 OF E2 - 6. 

BO:oING PROPRIETAHY _ Copyright I!:I Unpublished Work _ See page 1 for del.)ils. 

747-28-2265 

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BOEING SERVICE BULLETIN 747-28-2265 

BLANK PAGE 

February 22. 2006 

a OEING PROPRIETARY· Copyright ~ UnpuDlislled Woft; · See palle 1 for details. 

747-28-2265 

8 of 68 
Commercial 

Airplane 

Group 747 

Service Bulletin 

Number: 747·28-2265 

February 22, 2006 

2811 

Date: 

ATA System: 

SUBJECT: CONVERSION Airplane from a 747-400 Passenger configuration to a 747-400 Special 

Freighter (SF) Configuration· Horizontal Stabilizer Tank Deactivation 

1, PLANNING INFORMATION 

A. Effectivity 

1. Airplanes 

Refer to SelVice Bulletin Index Document 0 6-30300 Part 3 for Airplane Variable Number, Line 

Number, and Serial Number data. 

This selVice bulletin is for the airplanes shown below. Refer to Master Change 0300MK4010 for 

data about this change. 

GROUP CONFIGURATION DESCRIPTION 

1 - 747-400 airplanes RT456 to be modified to a 

747-400SF. 

Airplane models: 

747-400 

IDENTIFICATION BY CUSTOMER, CUSTOMER CODE, GROUP AND VARIABLE NUMBER 

CATHAY PACIFIC AIRWAYS (CAT) 

1 RT456 

IDENTIFICATION BY VARIABLE NUMBER 

I Variable Group 

RT456 1 

2. Spares Affected 

None. 

February 22 , 2006 

BOEING PROPRIETARY - COpyright ~ UnpUbilShed 1Nor!<· See page 1 !Of delab. 

747-28-2265 

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BOEING SERVICE BULLETIN 747-28-2265 

B. Concurrent Requirements 

The related 747-400SF concurrent service bulletins are: 

747-00-0005,747-00-0007.747-00-0014, 747-21 -2431 , 747-24-2250, 747-25-3362, 747-25-3366, 

747-53-2510,747-53-2531.747-57-2324. 

C. Reason 

As part of the special freighter conversion, the horizontal stabilizer fuel tank is to be deactivated and 

the fuel transfer line removed. This service bulletin provides instructions and kit of parts to do that. 

O. Description 

On P7-2 overhead circuit breaker panel, remove the Horizontal Stabilizer REFUEL & XFR circuil 

breakers C10125 and C1 0126. Rework the circuit breaker wiring. 

On P5 overhead panel, remove the Fuel Management Control Module (M00154) and rewor1< the 

wiring. 

At the FWD and AFT fuel isolation valves for the horizontal stabilizer transfer system, disconnect 

electrical connector from each valve actuator, coil and stow wiring. Position manual override lever for 

affected valves, located on valve actuator, to dosed position and lock wire to secure in place. 

On the horizontal stabilizer refuel valve control unit, disconnect electrical connector, cap and stow 

wiring. 

On the P42 left wing refueling panel coil and stow wiring for indicator, switches and lights. Place 

"H.STAB TANK DEACTIVATED" placard above H.STAB indicator. 

On the E8 equipment rack, in the Remote Electronic Unit (REU), M7861 , remove REU cover plate and 

H.5TAB Individual Fuel Quantity Chan net (IFOC) card. Re-install REU cover plate. Placard REU 

"INOP· and rework the wiring. 

ON the E2 equipment rack, make changes to the left, center, and right Electronic Instrument Unit (EIU) 

configuration pins to disable the Horizontal Stab Tank display and associated messaging on the 

Integrated Display Unit (IDS). 

On P8S panel, remove HOR STAB XFER/JETT PUMP circuit breakers C03141 and C03142_ Remove 

HOR STAB XFER/JETI PUMP placard below the circuit breakers. Rework circuit breaker wire and 

pump wiring. Cap and stow plugs 51884 and S1685 for H.STAB fuel pump low pressure switches. 

On the horizontal stabilizer transfer I jettison pumps, remove two motor impeller assemblies located 

on the front spar of H. Stab tank. Install plugs and associated pins. 

On the Fuel System Card File, remove horizontal stabilizer transfer Single Point Sensor Control 

(SPSC) card and install cover assembly. Coil and stow SPSC card wiring. Insert jumper wire in Fuel 

System Card File. 

On the Fuel Quantity Indicating System (FaIS), reprogram FQIS card file for Horizontal Stabilizer 

absent. 

On the Wire Interface Unit (W1U), modify affected wire bundles at WlU. 

February 22, 2006 

BOEING PROPRIETARY _ Copyright ~ Unpublished Wark· See page t lar clcta" . 

747-28-2265 

100f68 
BOEING SERVICE BULLETIN 747-28-2265 

On the fuel transfer line, remove and discard fuel lransfer line from center wing tank to the horizontal 

stabilizer fuel tank, and install plugs. 

E. Compliance 

Federal Aviation Administration (FAA) Airworthiness Directives; 97-03-17, 2002-19-52 and 2002-24-

52, Final Rule Docket Number 2002-NM-314-AO, Amendment 39-12993 is related to this service 

bulletin. 

F. 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. This 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 

approva l before incorporating this service bulletin. 

G. Manpower 

Man Hours are not listed in this Service Bulletin they are negotiated separately between Boeing and 

the contracted modification facility. 

H. Weight and Balance Changes 

Boeing requires that, because of the magnitude and uniqueness of major modification programs, the 

total airplane weight and centerof gravity will be determined by actual weighing after all modifications 

are complete and prior to delivery. The actual data win be recorded and placed in Chapter 2 of the 

Weight and Balance Manual. 

I. Electrical Load Data 

~The electrical loads of CAT Model 747-4008 airplane (RT4S6) as specified in document 

0281 U002-422 have been reviewed and the following loads were deleted . 

1. Direct Current (DC) Loads 

Airpla nes Nomenclature Connected Circuit 

Load Breaker 

RT4S6 Refuel and Transfer 1.40 10125 

Stabilizer - left 

Refuel and Transfer 1.40 10126 

Stabilizer - Right 

February 22 , 2006 

BOEING PROPRIETARY _ Copyright ;' UnpuOlishlNl 'Abril _ See page 1 tor deta~s 

Bus 

DC1P7 

DC2P7 

747-28-2265 

110f68 
BOEING SERVICE BULLETIN 747-28-2265 

2. Alternating Current CAe) Loads 

Airplanes Nomenclature Connected Load Circuit Bus 

Breaker 

RT456 Horizontal Stabilizer 4.600KVA .76PF 3141 GSB-3 

Boost Pump - Fwd 

Horizontal Stabilizer 4.600KVA .76PF 3142 AC2P85P183 

Boost Pump - Aft 

J. References 

1. Existing Data: 

a. Engineering Change Memo Me 0300MK401 0 

b. 747-400 Aircraft Maintenance Manual (AMM) 28-26-00 

c. 747-400F Structural Repair Manual (SRM) 51 

d. 747-400 Wiring Diagrams 24-51-26, 24·51 ·64,24-54-13, 24-54-23, 28-21-11,28-21-12, 28-

21-13, 28-21 -21 ,28-21-23,28-21-24,28-2 1-25, 28-21-26, 28-21-27, 28-21-28, 28-21-29, 

28-21 ·30, 28-21 -31, 28-22-41, 28·26·21 , 28-41-12, 28-41-13,28-21-24, 28-42-15, 28-43-12, 

31-61-12,31 -61·22, and 31-61-32. 

e. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-20-00 

2. Data supplied with this Service Bulletin: 

February 22, 2006 

1. The Module Parts List (MPL) drawings listed below will not be shipped with this 

service bulletin. Drawing access will be given to the modification site through My 

Boeing Fleet (MBF). This was negotiated by the operator and modification facility 

under Master Change 0300MK4010. 

BOEING PROPRIETARY· C<>p1nghl C Unpublished Work· See page 1 fOf deta~l . 

747-28-2265 

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MPl 

BOEING SERVICE BULLETIN 747-28-2265 

2. Within the MPl is a list of the retrofit andlor production drawing picture sheets 

required to facilitate installation of the identified part, assembly or installation as gillen 

in this service bulletin. 

Table 1, -

Title Drawing Sheet Rev Number 

83480401-1001 FUEL TANK DEACTIVATION· 83480401 MPl C 

HORIZONTAL STABILIZER 

344U1D11 Dl -

344U1011 4 -

344U1014 Dl 8 

344U1014 1 8 

344U1 022 Dl A 

344U1022 1 K 

344U1022 2 G 

I 344U1023 Dl -

344U1023 2 A 

284U1255 Dl -

284U1255 1 C 

284U4219 7 -

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

None. 

4. Process Data: 

Boeing Process specifications referred to on the drawings are not given in this service bulletin 

since these procedures are frequently used as standard shop practices. 

February 22, 2006 

BOEING PROPRIETARY - Copyng~1 C Unpublished Wolk - See page ' tor detail s 

747-28-2265 

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BOEING SERVICE BULLETIN 747-28-2265 

K. Publications Affected 

Publication Chapter·Section 

747 FAA Approved Airplane Flight Manual • 

747 Operations Manual 02.02, 15.10, and 15.20 

747 Maintenance Manual 11-13, 28-10, 28-30, and 28-40 (Dual 

configuration already exists) 

747 Wiring Diagram Manual 24-51 , 24-54, 28-21 , 28-22, 28-27, 28-41 , 

28-42. 28-43, 28-51, and 31-61 

747 Fault Reporting Manual 28-10 

747 Fault Isolation Manual 28 CMCS Index, 28 EICAS Index 

747 Illustrated Parts Catalog 28-22,28-26, and 28-41 

Ramp Maintenance Manual 28-00 

• This Change affects Section1 and Section 2 of the FAA Approved Airplane Flight Manual. 

Operators will receive applicable data 

L. Interchangeabi lity and Intermixability of Parts 

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

information , 

February 22 . 2006 

BOEING PROPRIETARY - Copyright 0; UnJ)\Jbll5hed Wor1<. - See page 1 IOf delll~S . 

747-28-2265 

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BOEING SERVICE BULLETIN 747-28-2265 

2. MATERIAL INFORMATION 

A. Material· Price and Availability 

Boeing supplies the kits shown in Paragraph 2. C., Parts Necessary For Each Airplane. This was 

negotiated with the operator under Master Change Me 0300MK4Q10. 

8 . Industry Support Infannation 

Boeing Industry Support Information is provided in Master Change Me 0300MK401D. 

C. Parts Necessary For Each Airplane 

1. Kits/Parts: 

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

N.QIE.;.One lop kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the 

Operator, are necessary for each airplane. 

Kit 83480401 

QTY 

New Part . Existing Part 

Number 1001 Name Number Notes 

83490401-1001 - FUEL TANK (a) 

DEACTIVATION -

HORIZONTAL 

STABILIZER 

285U0096-6 1 COVER ASSY I 

835BOOO4-1 1 PLUG -

CONNECTOR 

FITTING, HST 

FUEL TRANSFER 

LINE 

835UOOO1·1 2 MACHINED 

PARTS DETAILS· 

PLUG 

835UOOO2-1 2 MACHINED 

PARTS DETAILSPIN 

AS5168W32 2 PLUG, FLARED I (b) TUBE 

BAC27EFS595 1 MARKER I 

BAC27TFDE0013 1 VINYL DECALI I (INOP) 

MS21913W32 I 1 IPLUG, I (b) 

I FLARE LESS 

February 22, 2006 

BOEING PROPRIETARY . Copyn ght e Unpublished Vlbrl<· See page 1 lor details 

i 

747-28-2265 

150f68 
BOEING SERVICE BULLETIN 747-28-2265 

Kit 826B4260 

New Part ~ Existing Part 

Number - Name Number Notes 

82989006-14 1 Wire 

!Noles: 

(a) Kit has more parts than necessary. Discard extra parts 

or keep them for other use. 

. (b) Optional to ASS168W32 in the forward fitting 

344U0014 only. 

2. Parts and Materials Supplied by the Operator: 

I Part Number I 

I Specification QTY Name Notes 

2645 4 Plug Button (a) 

(a) PALL AEROPOWER CORP 

5775 RIO VISTA 

CLEARWATER Fl 33760 

727-539-8448 

3. Parts Modified and Reidentified: 

None 

February 22, 2006 

BOEING PROPRIETARY - Copyright Q Unpublished Work· See page 1 lor details. 

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BOEING SERVICE BULLETIN 747-28-2265 

4. Parts Removed and Not Replaced: 

Existing 

Part Number Name QTY I Notes 

160-72101-1 or 60-72102-4 Molor-Impeller Assembly 2 Refer to AMM 28-17-04 (a) 

I (Boeing Part Number 

60892603-22 or 60892603-26) 

S344TOO2-8 Horizontal Stabilizer Transfer 1 Refer to AMM 28-17-10 (al 

, Single Point Sensor Control , Card (SPSC) A3 

60892018-207 Individual Fuel Quantity 1 RefertoAMM 28-41-17 {al 

Channel (IFOC) Card Y5XA 1 

I R7391 Relay 1 Located on P54 panel 

10-60536-25 (opt 10-60536-22) Hose Assy 1 Refer to 747 AMM 28-17-06 (b) 

10-60536-23 Hose Assy 1 Refer to 747 AMM 28-17-06 (b) 

344UD018-8 (opt 344UOO18-5) Tube Assy 1 Refer to 747 AMM 28-17-06 (b) 

344U1022-10 Tube Assy 1 Refer to 747 AMM 28-17-06 (b) 

344U1022-11 Tube Assy 1 Refer to 747 AMM 28-17-06 (b) 

344U1022-12 Tube Assy 1 I Refer to 747 AMM 28-17-06 (b) 

344U1022-13 Tube Assy 1 Refer to 747 AMM 28-17-06 (b) 

344U1022-14 Tube Assy 1 I Refer to 747 AMM 28-17-06 (b) 

344U1022-2 Tube Assy 1 I Refer to 747 AMM 28-17-06 (b) 

344U1022-25 Tube Assy 1 Refer to 747 AMM 28-17-06 (b) 

344U1022-26 Tube Assy 1 Refer to 747 AMM 28-17-06 (b) 

344U1022-5 I Tube Assy 1 Refer to 747 AMM 28-17-06 (b) 

344U1022-8 Tube Assy 1 Refer to 747 AMM 28-17-06 (b) 

344U1022-9 Tube Assy 1 Refer to 747 AMM 28-17-06 (b) 

I 6305B374S48-03 Nut Assy 1 Refer to 747 AMM 28-17-06 (b) 

63211-48 Coupling Assy 1 Refer to 747 AMM 28-17-06 (b) 

(a) Keep the part if there are other uses for it. 

(b) Refer to 747 AMM 28-17-06 for additional information 

D. Parts Necessary to Change Spares 

None. 

E. Special Tooling - Price and Availability 

The operator can supply the tools shown in Paragraph 2.F., Special Tooling Necessary to do this 

Service Bulletin. Tool price and supply data are not given. 

February 22, 2006 

I 

I 

BOElNG PROPRIETARY - Copyright C> Unpublished Well< _ See page 1 tor details. 

747-28-2265 

170f68 
BOEING SERVICE BULLETIN 747-28-2265 

F. Special Tooling Necessary to do this Service Bulletin 

To gellhe tools shown below, refer to Paragraph 2.E., Special Tooling - Price and Availability. 

Maintenance and overhaul tools in the manuals shown in Paragraph 1.J., References , can also be 

necessary. Examine operator loot supply to make sure aU necessary tools are available. 

Tool Kit Numbe r Name 

Shop Supply ESOS Wrist Strap (1 required) 

Shop Supply Jumper Wire (4 required) 

February 22 , 2006 

BOEING PROPRIETARY _ Cepynght 1;1 Unpublished Work · See Ilage 1 for detail" 

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BOEING SERVICE BULLETIN 747-28-2265 

3. ACCOMPLISHMENT INSTRUCTIONS 

A. GENERAL INFORMATION 

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

PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED 

MATERIAL. METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES 

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

SPARKS OR OTHER ELECTRICAL DAMAGE. 

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

definition of the acronyms. 

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

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

Linear dimensions are in inches 

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

minus 0.03 inch. 

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

Angular tolerance is plus or minus 2 degrees 

Hole dimensions for standard solid rivets are given in 747-400F SRM 51 

Torque limits to tighten nuts and bolts are given in 747-400F SRM 51 

4. For approved fastener and process material substitutions, refer to 747 Stl1Jctural Repair 

Manual, Chapter 51 , 

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

6. Refer to the SWPM 20-20-00 the necessary grounding procedures. This is the same as 

BAC5117 which is used on the drawings. 

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

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

longer or shorter may be used. 

B. WORK INSTRUCTIONS 

Horizontal Stabilizer Tank Preparation 

1. Defuel Horizontal Stabilizer Tank (HST) per 747-400 AMM 28-26-00. In addition, defuel Main 

Tanks 2 and 3 sufficiently to allow the Fill/Jettison Manifold to drain. 

2. Sump HST per AMM 12-11 -10. 

3. Open the following circuit breakers and attach DO-NOT-CLOSE tag on the P7 Overhead Circuit 

Breaker Panel: 

a. 7H25 REFUEL & XFR STAB L. 

b. 7H26 REFUEL & XFR STAB R. 

February 22, 2006 

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4. Manually open one oflhe horizonlal stabilizer isolation valves at the rear spar oflhe center wing 

tank. Refer to the 747-400 AMM 28-17-01. 

NOTE:This will lei fuel from the fuel transfer line drain into main tanks 2 and 3. 

5. On the flight deck push FUEL synoptic EICAS display switch. 

6. On the lower EICAS display, record the fuel quantity for all displayed tanks. 

7. After the fuel has drained from the fuel transfer line, manually close the horizonial stabilizer 

isolation valve that was opened. 

8. Close the circuit breakers opened in step 3 above. 

9. Purge the fuel tanks as specified in the 747-400 Maintenance Manual Subject 28-11-00. Prepare 

the horizontal stabilizer for entry. 

10. Clean and corrosion protect HST as necessary to prepare for deactivation in accordance with 

AMM 28-1 1-00. 

11. Close HST (do not put fuel into the HST). 

12. Put the stabilizer in the neutral trim position (3 units of trim) as follows: 

a. Supply electrical power. Refer to the 747-400 AMM 24-22-00. 

WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF ALL 

CONTROL SURFACES BEFORE YOU SUPPLY HYDRAULIC POWER. 

AILERONS, RUDDERS, ELEVATORS, FLAPS, SPOILERS, LANDING GEAR, 

AND THRUST REVERSERS CAN MOVE QUICKLY WHEN YOU SUPPLY 

HYDRAULIC POWER. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE 

TO EQUIPMENT. 

b. Supply hydraulic power. Refer to the 747-400 AMM 29-11-00. 

c. Use the STAB TRIM AL TN switches to set the horizontal stabilizer to the neutral rig position 

(3 units of trim). 

d. Set the STAB TRIM 2 and 3 switches on the control stand to CUTOUT. 

e. On the P7 panel, open the L STAB TRIM SIO VLV circuit breaker (position E7) and the R 

STAB TRIM SIO VLV circuit breaker (position E20) and attach DO-NOT-CLOSE tabs. 

f. Set all FLT CONTROL HYD POWER TAIL switches on the P461 pilots overhead 

maintenance panel to SHUTOFF. 

g. On the P180 panel, open these circuit breakers and attach DO-NOT-CLOSE tags: 

(1 ) ELEV/RUD VLV SYS 2, position E7 

(2) ELEV/RUD VLV SYS 4, position E22 

(3) ELEV/RUD VLV SYS 1, position H8 

(4) ELEV/RUD VLV SYS 3, position H23 

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13. Install the gear door locks. Refer to the 747-400 AMM 32-00-30. 

14. Remove hydraulic power. Refer to the 747-400 AMM 29-11-00. 

15. Remove electrical power. Refer to the 747-400 AMM 24-22-00. 

Horizontal Stabilizer Tank Deactivation Procedure 

1. The following circuit breakers are to be opened and remain open throughout the duration of this 

HST deactivation procedure. 

Location Name Circuit Breaker 

Panel Position 

P-6 DOS FUEL QTY 1 C10123 

P-6 006 FUEL QTY 2 C10124 

P180 M08 FUELING VALVE 2 COOO86 

P180 M09 FUELING LTS-HOT or FUELING PWR-HOT BATH C01143 

P180 C25 FUELING LIGHTS PANEL (if installed) C10746 

P180 C26 FUELING LTS RECP (if installed) C10747 

P414 F17 FUELING VALVE COO090 

P414 F22 LIGHT FUELING or FUELING POWER C01142 

P415 M14 FUEL OVERFILL CONT COO062 

P6 F06 FUEL SYS MGMT CH 1 I C10129 

P6 F08 FUEL SYS MGMT CH 2 I C10130 

E2-6 F9 LEFT EIU C10174 

E2-6 F10 CENTER EIU C10175 

E2-6 F15 RIGHT EIU I C10176 

2. Remove and install plugs for REFUEL & XFR STAB L circuit breaker C1 0125 and REFUEL & 

XFR STAB R circuit breaker C10126. Refer to Figure 1. 

3. Modify wire bundle W0007 on P7 Overhead Circuit Breaker Pane! as referenced in Figure 12. 

4. Modify wire bundles W4092 and W4094 on Overhead Circuit Breaker Panel P7 as referenced in 

Figure 12. 

5. Change AFT Horizontal Stabilizer Fuel Isolation Valves as follows: 

a. Locate two isolation valves on rear spar of H. Stab tank, L aft valve (V435), R aft valve 

(V436). Refer to Figure 5. 

b. Disconnect electrical connector from valve actuator. Rework wire bundle W4607 and 

W4618 as referenced in Figure 12. 

c. Position manual override lever for affected valves , located on valve actuator, to closed 

position and LOCKWIRE. Refer to Figure 2 for location. 

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6. Change FWD Horizontal Stabilizer Fuel Isolation Valves as follows: 

a. Locate two isolation valves on rear spar of center tank, L fwd valve (\1439), R fwd valve 

(\1440). Refer to Figure 3 for location, 

b. Disconnect electrical connector from valve actuator. Rework wire bundle W4611 and 

W4641 as referenced in Figure 12. 

C. Position manual override lever for affected valves, located on valve actuator, to closed 

position and lOCKWIRE. Refer to Figure 3 for location. 

7. Modify wire bundle W0144 on Pressure Fueling Control Panel P42 as referenced in Figure 12. 

Coil and slow wiring for indicator, switches, and lights. 

8. Install the "H.STA8 TANK DEACTIVATED" placard (marker) above H.STAS indicator, Part 

Number BAC27EFS595 as given in AMM 20-11-06-404-012 ALUMINUM FOIL MARKER 

INSTALLATION. Refer to Figure 4. 

9. Remove relay R7391 and rework wire bundle W0076 on Center Equipment Panel P54 as 

referenced in Figure 12. 

10. Modify wire bundle W4606 on the Horizontal Stabilizer Refuel Valve Control Unit as referenced 

in Figure 12. Refer to Figure 2 for component location. 

11. Remove "HOR STAB XFER/JETI PUMP L" circuit breaker C03141 and "HOR STAB XFERI 

JETI R" circuit breaker C03142. Remove HOR STAB XFERIJETI PUMP LEFT and RIGHT 

placard as shown in Figure 5. 

12. Modify wire bundle W2018 on AFT MISC Circuit Breaker Panel P8S as referenced in Figure 12. 

13. Modify wire bundles W4601 and W4602 on Left AFT Equipment Center E8 as referenced in 

Figure 12. Cap and stow pump wiring and plugs S1884 and 51885 as indicated. 

14. Remove fuel transfer line and install plugs as shown in Figure 11. 

15. Change Horizontal Stabilizer Motor Impeller Assemblies as shown in Figure 6 and as follows: 

a. Remove two motor impeller assemblies located on the front spar of HST. Refer to AMM 28-

17-04. 

b. Inslalilwo plugs nd two associated pins and do the following: 

February 22, 2006 

(1) Install new packing MS29513-007, lubricated with petrolatum, into groove on pin, part 

number 83SU0002-1. 

(2) Put end of pin with packing inlo housing on top of unit. 

(3) Install new packing M25988-1-238, lubricated w ith petrolatum into groove on plug, part 

number 835U0001-1. 

(4) Carefully push the plug into housing. Make sure that smallest hole is in line with pin on 

housing. 

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(5) Put the bonding clip{s) with the bonding jumper(s) attached into position on the plug. 

CAUTION: ENSURE SOCKET HEAD MOUNTING SCREWS ARE PIN MS24674-9 OR 

EQUIVALENT ALTERNATIVE (THREAD LENGTH 15MM). QUANTITY (1) 

WASHER PIN NAS11490N832J MUST BE USED AT EACH SCREW 

LOCATION. 

(6) Install socket head screws and washers at five locations to fasten the bonding clips and 

plug, part number 835U0001-1, to the pump housing. 

(7) Install nut, part number BACN10JC06C, and washer, part number NAS620C6 to the 

threaded end on pin to secure pin in housing. 

16. Modify the Remote Electronic Unit (REU) at M7861 in Equipment Center EB as shown in Figure 

7 and as follows: 

a. Remove the "H.STAB INDIVIDUAL FUEL QUANTITY CHANNEL (IFOC) CARD", part 

number 60892018-207 in accordance with AMM 28--41 -17. 

b. Install the cover plate on the REU, M7861 and tighten the four captive screws. 

c. Placard REU NOP~. 

d. Modify wire bundle W3851 on AFT Left Equipment Center E8 as referenced in Figure 12. 

17. Modify wire bundle W3890 as referenced in Figure 12 and "reprogram FQIS card file for 

Horizontal Stabilizer absent". 

18. Change Fuel System Card File as follows: 

a. Remove horizontal stabilizer Single Point Sensor Control Card (SPSC) A3, in accordance 

with AMM 28-17-10 and Figure 8. 

b. Install cover assembly, part number 285U0096-6, at SPSC installation location. Refer to 

Figure 8. 

c. Modify wire bundle W4764 by inserting jumper wire in Fuel System Card File as referenced 

in Figure 12. 

d. Modify wire bundle W4974 on shelf 6 of Main Right Equipment Center E2-6 as referenced 

in Figure 12. 

19. Change P5 Fuel Management Control Panel as follows: 

a. Remove the Fuel Management Control module (M00154) from the P5 panel as referenced 

in Figure 9. 

b. Modify wire bundles W4751 and W4753 on Pilots Overhead Panel P5 as referenced in 

Figure 12. 

20. Deactivate tail tank at WlU for the left, center, and right Electronic Instrument Units (EIU) as 

follows: 

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a. Modify wire bundle W4260 on shelf 6 of the Main Righi Equipment Center E2-6 for the left, 

center, and right EJUs as shown in Figure 10. 

21 . Close all circuit breakers thai were opened in step 1 above. 

WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF ALL CONTROL 

SURFACES BEFORE YOU SUPPLY HYDRAULIC POVVER. ALERONS, RUDDERS, 

ELEVATORS, FLAPS, SPOILERS, LANDING GEAR, AND THRUST REVERSERS 

CAN MOVE QUICKLY WHEN YOU SUPPLY HYDRAULIC POWER. THIS CAN CAUSE 

INJURY TO PERSONS AND DAMAGE EQUIPMENT. 

22. Supply electrical power to airplane. Refer to the 747-400 AMM 24-22-00. 

Horizontal Stabilizer Tank Functional Check 

1. Do the following steps to check the IDS program pin configuration: 

Onty check the NON-X valUes shown in steps c, e, and 9 below. The ·X· values in the 

program pin codes shown below are not pertinent to this change and may be any value. 

a. Display the configuration maintenance page on the CMC display unit. 

b. Put the Captain's and First Officer's source select switches in the L position. 

c, Make sure that the following is displayed: 

IDS PROGRAM PINS : 

l/XXXX XOXX/32 

33/XXXX XX/56 l/P 

d. Put the Captain's and First Officer'S source select switches in the C position. 

e. Make sure that the following is displayed: 

IDS PROGRAM PINS : 

l/XXXX XOXX/32 

33/XXXX XX/56 l /P 

f. Put the Captain's and First Officer's source select switches in the R position. 

g. Make sure that the following is displayed: 

IDS PROGRAl1 PIN : 

l/XXXX xaxx/32 

33/XXXX XX/56 l/p 

2. Do an electrical test of the P42 panel as follows. The airplane must be in the ground mode for 

this test: 

a. Open these circuit breakers on the P6 panel: 

CBND. LOC Nomenclature 

C10123 005 FUEL QTY 1 

C10124 006 FUEL QTY 2 

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b. Open these circuit breakers on the P414 panel: 

CBND. LOe Nomenclature 

COOO90 F17 FUELING VALVE 

C01142 F22 FUELING PWR 

C10131 M33 HOR STAB SUMP DRAIN VLV 

c. Open these circuil breakers on the P180-1 panel: 

I CB NO I LOC I Nomenclature 

COOO86 M08 FUELING VALVE 2 

C01143 M09 FUELING LTS - HOT 

d. Open the P42 fueling panel door. 

e. On the P42 panel, put the battery switch in the NORM position. 

f. On the P414 panel, position F22, close the circuit breaker C01142, FUELING PWR. 

g. On the P42 panel, push and hold the GAUGES TEST switch. See that all the fuel quantity 

indicator displays read 888.B. The horizontal stabilizer indicator will remain blank. 

h. Release the GAUGES TEST switch. 

i. Set the SELECT QTY value to 222.2. 

J. Press the PRESELECT SET QTY switch to the TOTAL position and hold for more than 2 

seconds. 

k. Release the PRESELECT SET QTY switch. 

I. See that the quantity 222.2 can be seen in the bottom display of the TOTAL FUEL indicator. 

m. On the flight deck, push the FUEL synoptic EICAS display switch. 

n. On the lower EICAS display, see that the fuel quantities are within +/- 200 Ibs (+/- 100 kgs) 

of the quantities recorded in Step 6 of the Horizontal Stabilizer Tank Preparation Procedure. 

~Horizonta l Stabilizer tank fuel quantity will not be displayed. 

o. On the P414 panel, position F22, open the circuit breaker C01142, FUELING PWR. 

p. On the P42 panel, see that the refuel indicator displays go blank. 

q. On the P42 panel, put the battery switch in the BATT position. 

r. On the P180-1 panel, position M09, close the circuit breaker C01143, FUELING PWR-HOT 

BAT. 

s. On the P42 panel, see that the refuel indicator quantities are within +/- 200 Ibs (+/-100 kgs) 

of the quantities recorded in Step 6 of the Horizontal Stabilizer Tank Preparation Procedure. 

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NQTE;Horizontal Stabilizer tank fuel quantity will not be displayed, 

t. On the P180·1 panel, position M09, open the circuit breaker C01143, FUELING PWR-HOT 

BAT. 

u. On the P42 panel, see that the refuel indicator displays go blank. 

V. On the P42 panel, put the battery switch in the NORM position. 

3. Do an electrical test of the FQIS display, center tank fuel control card, and secondary valves and 

horizontal stabilizer sump drain valves as follows: 

a. On the rear spar of the center tank, disconnect connector DV437 from the left secondary 

refuel valve. 

b. On the P42 panel, put the CENTER tank valve position control switch in the OPEN position. 

C. On the P414 panel, position F22, close the circuit breaker C01142, FUELING PWR. 

d. On the rear spar of the center tank, make sure there is 23-30 VDC on DV437, between pins 

Aand B. 

e. On the P42 panel, push and hold the C. TANK SEC. VAL. switch to the CLOSED position. 

See that the Land R valve position lights come on. 

f. On the rear spar of the center tank, make sure there is 0-3 VDC on DV437, between pins A 

and B. 

g. On the rear spar of the center tank, disconnect the left secondary refuel valve pressure 

switch connector DS 1877. On the P42 panel, see that the secondary refuel valve L valve 

position lights goes off. 

h. On the P42 panel, release the C. TANK SEC. VAL. switch, 

I. On the P42 panel, pul the CENTER tank valve position control switch in the CLOSED 

position. 

j. On the P42 panel, put the ALL VALVES switch in the OPEN position. 

k. On the rear spar ofthe center tank, make sure there is 23-30 VDC on DV437, between pins 

A and B. 

I. On the P42 panel, put the ALL VALVES switch in the CLOSED position. 

m. On the rear spar of the center tank, make sure there is 0-3 VDC on DV437, between pins A 

and B. 

n. On the P414 panel, position F22, open the circuit breaker C01142, FUELING PWR. 

o. On the rear spar of the center tank , connect conn ectors DV437 and D5 1877. 

p. On the rear spar of the center lank, disconnect connector DV438 from the right secondary 

refuel valve. 

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q. On the P42 panel, put the CENTER tank valve position control switch in the OPEN position. 

r. On the P414 panel, position F22, close the circuit breaker C01142, FUELING PWR. 

s. On the rear spar of the cenler lank, make sure there is 23-30 VDC on DV438, between pins 

A and B. 

1. On the P42 panel, push and hold the C. TANK SEC. VAL. switch to the CLOSED position. 

See that the Land R valve posltion lights come on. 

U. On the rear spar oflhe center lank, make sure there is 0-3 VDC on DV436, between pins A 

and B. 

v. On the rear spar of the center tank, disconnect the right secondary refuel valve pressure 

switch connector OS1876. On the P42 panel, see that the secondary refuel valve R valve 

position lights goes off. 

W. On the P42 panel, release the C. TANK SEC. VAl. switch. 

x. On the P42 panel, put the CENTER tank valve position control switch in the CLOSED 

position. 

y. On the P42 panel, put the ALL VALVES switch in the OPEN position. 

z . On the rear spar of the center tank, make sure there is 23· 30 VDC on DV438, between pins 

A and B. 

aa. On the P42 panel, put the ALL VALVES switch in the CLOSED position. 

abo On the rear spar of the center tank, make sure there is 0-3 VDC on DV438, between pins A 

and B. 

ac. On the P414 panel, position F22, open the circuit breaker C01142, FUELING PWR. 

ad. On the rear spar of the center tank, connect connectors DV438 and DS1876. 

ae. On the P414 panel, close the circuit breakers C090, FUELING VALVE, position F17 and 

C10131, HIS SUMP DRAIN VALVE, position M33. 

af. On the P211 panel, push the L VALVE (L3666) and R VALVE (L3667) valve power lights. 

See that the lights come on when they are pushed. 

ag o On the P211 panel, push the SUMP DRAIN MAINT switch to the open position. On the 

horizontal stabilizer, hear that each solenoid valve operates. On the P211 panel, see that 

the l VALVE and R VALVE valve power lights come on. 

ah. On the P211 panel, push the SUMP DRAIN MAINT switch to CLOSED position. 

ai. On the P211 panel, push the SUMP DRAIN CONT switch to the l OPEN position. On the 

horizontal stabilizer, hear that the left solenoid valve operates. On the P211 panel, see that 

L VALVE valve power light comes on. Put the switch back to the normal position. 

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aj. On the P211 panel, push the SUMP DRAIN CONT switch to the R OPEN position. On the 

horizontal stabilizer, heartha! the right solenoid valve operates. On the P211 panel, see that 

the R VALVE valve power light comes on. Put the switch back to the normal position. 

4. Do an electrical test of the fuel system management cards as follows: 

a. On the CMC MCDU, go to the INPUT MONITORING screen. 

b. On the P6 panel, close the circuit breaker C1 0128, FUEL SYS MGMT CARD A, position F5, 

and open the circuit breaker C10127, FUEL $Y$ MGMT CARD S, position F7. 

C. On the P414 panel, position F22, open the circuit breaker C01142, FUELING P\I\IR. 

d. On the P6 panel, close the circuit breaker C1 0129, FUEL SYS MGMT CH 1, position F6, 

and apen the circuit breaker C10130, FUEL SYS MGMT CH 2, position F8. 

e. In the fuel system card file (M7852), on the A2 card, see that the CH 1 green LED is on and 

the CH 2 green LED is not on. 

f. On the CMC MCDU, put this data in for input monitoring: port "EGg,' label "270' and sdi ' 00." 

g. In the fuel system card file (M7852), on the A2 card, push and hold the BIT switch to the CH 

1 position. See that the CH 1 green LED goes off. On the CMG MCDU see that bit 27 goes 

from "1" to "0' (main tank number 2 single point sensor). This can take up to 1 minute to 

happen. 

h. In the fuel system card file (M7853), on the A2 card, release the BIT switch. 

i. On the P6 panel, open the circuit breaker C10128, FUEL SYS MGMT CARD A, position F5, 

open the circuit breaker C10130, FUEL SYS MGMT GH 2, position F8, open the circuit 

breaker C10129, FUEL SYS MGMT CH 1, position F6, and open the circuit breaker C10127, 

FUEL SYS MGMT CARD B, position F7. 

j. On the P180 panel, close the circuit breaker C10136, FUEL SYS EICAS INTFC CONT, 

position H17. 

k. On the GMt MCDU, put this data in for input monitoring: port"E 10', label "274" and sdi "00: 

See that this data can be seen. This can take up to 1 minute to happen. 

Position 29 28 27 26 25 24 23 22 21 20 

Status 0 1 1 1 1 1 1 0 0 0 

Position 19 118 17 16 115 14 13 12 11 

Status 0 11 1 1 1 1 0 0 1 

I. On the CMC MCDU, put this data in for input monitoring:"E 10', label "270' and sdi '00: 

m. On the p5 panel, push the MAIN 1 AFT fuel pump switch to ON. See that bit 11 goes from 

' 0" to ·1." This can take up to 1 minute. 

n. On the P5 panel, push the MAIN 1 FWD fuel pump switch to ON. See that bil12 goes from 

' 0' to ·1." This can take up to 1 minute to happen. 

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o. On the P5 panel, push the MAIN 2 AFT fuel pump switch to ON. See that bit 13 goes from 

"0' to ' 1". This can take up to 1 minute to happen. 

p. On the P5 panel, push the MAIN 2 FWD fuel pump switch to ON. See that bil 14 goes from 

' 0" to "1." This can take up to 1 minute. 

q. On the PS pane!, push the MAIN 3 AFT fuel pump switch to ON. See that bit 15 goes from 

' 0' to "1: This can take up to 1 minute. 

r. On the PS panel, push the MAIN 3 FWD fuel pump switch to ON. See that bit 16 goes from 

"a" to "1." This can take up to 1 minute. 

s. On the P5 panel, push the MAIN 4 AFT fuel pump switch to ON. See that bit 17 goes from 

'0' to "1." This can take up to 1 minute. 

t. On the P5 panel, push the MAIN 4 FWD fuel pump switch to ON. See thai bit 18 goes from 

"0' to "e This can take up to 1 minute. 

u. On the P5 pane!, push the CTR L fuel pump switch to ON. See that bit 19 goes from ·0" to 

"1." This can take up to 1 minute. 

v. On the P5 panel, push the CTR R fuel pump switch to ON. See thai bit 20 goes from "0" to 

"1." This can take up to 1 minute. 

w. On the P5 panel, push the OVRD 2 MAIN AFT fuel pump switch to ON. See that bit 23 goes 

from "0" to "1." This can take up to 1 minute. 

x. On the P5 panel, push the OVRD 2 MAIN FWD fuel pump switch to ON. See that bit 24 goes 

from "0" to "1." This can take up to 1 minute. 

y. On the P5 panel, push the OVRD 3 MAIN AFT fuel pump switch to ON. See that bit 25 goes 

from '0" to "1." This can take up to 1 minute. 

z. On the P5 panel, push the OVRD 3 MAIN FWD fuel pump switch to ON. See that bit 26 goes 

from ' 0· to "1." This can take up to 1 minute. 

aa. On the P5 panel, push the number 1 tank FUEL X FEED switch to on (flow bar can be seen). 

See that bit 27 goes from "0" to ' 1." This can take up to 1 minute to happen. 

abo On the P5 panel, push the number 2 tank FUEL X FEED switch to on (flow bar can be seen). 

See that bit 28 goes from "0" to "1." This can take up to 1 minute to happen. 

ac. On the P5 panel, push the number 3 tank FUEL X FEED switch to on (flow bar can be seen). 

See that bit 29 goes from ' 0' to "1." This can take up to 1 minute to happen. 

ad. On the CMC MCDU, put this data in for input monitoring: port "E 10", label "270' and sdi "10." 

ae. On the PS panel, push the number4 tank FUEL X FEED switch to on (flow ban can be seen). 

See that bit 11 goes from "0" to "1." This can take up to 1 minute. 

af. On the PS pane!, push all the switches on the M154 module to off. 

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ago On the P6 panel, close the circuit breakers C10128, FUEL SYS MGMT CARD A, position 

F5, C10127, FUEL SYS MGMT CARD B, position F7, C10129, FUEL SYS MGMT CH 1, 

position F6, and C10130, FUEL SYS MGMT CH 2, position F8. 

5. Do the Fuel Quantity indication System Ground test as specified in the 747-400 AMM 28-41 ·00. 

NOTE:Horizonlal Stabilizer is now deactivated and NOT to be fueled . 

6. Do the Wing Surge Tank Float Switch Operational Test as specified in the 747-400 AMM 28-21-

12. 

7. Restore hydraulic power. Refer to the 747-400 AMM 29-11-00. 

8. Remove the gear door locks. Refer to the 747-400 AMM 32-00-30. 

9. Put the airplane back into serviceable condition. 

February 22, 2006 

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FIGURE 1: OVERHEAD CIRCUIT BREAKER PANEL P7 2 CHANGE 

P7-2 PANEL 

10 ~3 0) 0) @ I L ____ "'~~C~"~"~~c.~.~_'c,"=7L~~~~--:" 

I 

, I ",' ~ 1 2 

, ! , 

iO 0 0 0 0 0 0 i --~ -- ~- ------------- ------' 

FIGURE 1: OVERHEAD CIRCUIT BREAKER PANEL P7-2 CHANGE 

February 22, 2006 (SHEET 1 OF 2) 

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BOEING SERVICE BULLETIN 747-28-2265 

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY 

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

STEP TASK NAME PART NUMBER QTY NOTES 

1 Remove Circuit Breaker BACC18AD7 2 - 2 Install Plug Button 2654 2 -

FIGURE 1: OVERHEAD CIRCUIT BREAKER PANEL P7·2 CHANGE 

February 22, 2006 (SHEET 2 OF 2) 

BOEING PROPRIETARY· Copyright C Unpubliihed Wort< · See page t lor detaU$. 

747-28-2265 

32 of 68 
BOEING SERVICE BULLETIN 747-28-2265 

FIGURE 2: HORIZONTAL STABILIZER TANK AFT FUEL TRANSFER SYSTEM LOCATION 

REFUEL VALVE 

CONTROL UN I T 

STAB I L! Z£R 

FRONT SPAR 

(DRY SIDE) 

~FWD 

STABILIZER 

FRONT SPAR 

REFUEL VALVE 

STABILIZER 

REAR SPAR 

AFT ISOLATION VALVE 

( I N HOR I ZONTAL 

STABILIZER TANK) 

e:> FVlD 

(WET SIDE) 

FIGURE 2: HORIZONTAL STABILIZER TANK AFT FUEL TRANSFER SYSTEM LOCATION 

February 22, 2006 (SHEET 1 OF 2) 

BOEING PROPRIETARY . Copyright C Unpubl sh~d 'Nork _ See pIIge , lor !a~5 . 

747-28-2265 

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BOEING SERVICE BULLETIN 747-28-2265 

ACTUATOR FOR THE 

AFT ISOLATI ON VALVE 

(LEFT -UPPER) 

VALVE 

ADAPTER 

MANUAL OVERR I DE LEVER 

(REf) 

ACTUATOR FOR THE 

AFT ISOLATION VALVE 

(R IGHT -LOY.'ER) 

l-\-\--_ REAR SPAR 

(REF) 

~FWD 

o 

VALVE 

ADAPTER 

MANUAL OVERR I DE 

LEVER (REf) 

· • • M 

C 

FIGURE 2: HORIZONTAL STABILIZER TANK AFT FUEL TRANSFER SYSTEM LOCATION 

February 22, 2006 (SHEET 2 OF 2) 

BOEI NG PROPRIETARY _ Copyngh! C Unpublished Worl<.· Sft! palle 1 for deta,s. 

747-28-2265 

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BOEING SERVICE BULLETIN 747-28-2265 

FIGURE 3: HORIZONTAL STABILIZER TANK FWD FUEL TRANSFER SYSTEM LOCATION 

CENTER WING TANK 

COMPONENTS 

SEE 0 

HORIZONTAL STABILIZER 

FWD ISOLATION VALVES 

f?S"C;7" SEE 0 

)lr""'O! 

o 

CENTER 

WING TANK 

FIGURE 3: HORIZONTAL STABILIZER TANK FWD FUEL TRANSFER SYSTEM LOCATION 

February 22, 2006 (SHEET 1 OF 2) 

BOEING PROPRIETARY - Copyright C Unpul>ished Worl< _ See "",gel Igr eta ~s . 

747-28-2265 

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"D~ 

BOEING SERVICE BULLETIN 747-28-2265 

VALVE 

ADAPTER 

REAR SPAR 

MANUAL 

OVERR I DE LEVER 

HORIZONTAL STABILIZER ISOLATION VALVE 

VALVE 

ACTUATOR 

" o 

FIGURE 3: HORIZONTAL STABILIZER TANK FWD FUEL TRANSFER SYSTEM LOCATION 

February 22, 2006 (SHEET 2 OF 2) 

747-28-2265 

BOEING PROPRIETARY _ Copyright ~ Unp~blished Worll- See page 1 lor deta~ . 36 of 68 
BOEING SERVICE BULLETIN 747-28-2265 

FIGURE 4: LEFT WING REFUELING PANEL P42 MODIFICATION 

FWDt' 

, I 

FWD 

~ 

H. STAB TANK 

DEACT IVATED 

I/~~ ~, t Ii 4.0 I \ (M \ (\ ~ I,) \ i: 3 5 Ii) I~/ ~/ 

) RE5E~VE 3 H ST AS 

I DPEN O 2® 

;' CLOSED ~; \..'1 'V \:( ~,'0"10 V '---./ I '>.J '-..-/ 

FIGURE 4: LEFT WING REFUELING PANEL P42 MODIFICATION 

February 22, 2006 (SHEET 1 OF 2) 

BOEING PROPRIETARY _ Copyright ~ Unpublisl>ed Work· SCI! page 1 for details. 

-

• • 8 

747-28-2265 

37 of 68 
BOEING SERVICE BULLETIN 747-28-2265 

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY 

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

STEP TASK NAME PART NUMBER QTY NOTES 

1 Install Marker BAC27EFS595 1 Refer to AMM 20-11-06. 

FIGURE 4: LEFT WING REFUELING PANEL P42 MODIFICATION 

February 22, 2006 (SHEET 2 OF 2) 

BOEING PROPRIETARY - Copyriijhl C Unpu bl,r,hed Work S ee page' 10' detah. 

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BOEING SERVICE BULLETIN 747-28-2265 

FIGURE 5: H.STAB FUEL PUMP LOW PRESSURE SWITCHES AND PBS PANEL CHANGE 

E8 EQUIPMENT RACK 

r-lAV WATER HTR ---, 

FC1-FC2 ! FC3.f"C. I FC5-FC6 

DOQRNQ, S 

~===:::-~ .- HOR STAB XFERIJETI PUMP n,"','" I 

o 

LEFT ",on , 

THE BOEING CO. 

PART tWMSE;;; 

SERIAl NUMBER 

o 2 

SEE (0 

PBS PANEL 

FIGURE 5: H.STAB FUEL PUMP LOW PRESSURE SWITCHES AND P8S PANEL CHANGE 

February 22. 2006 (SHEET 1 OF 2) 

BOEING PROPRIETARY - Copyright C Unpul>ished Won.. - See Pl'ge 1 for deta~s. 

747-28-2265 

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BOEING SERVICE BULLETIN 747·28·2265 

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. 

STEP TASK NAME PART NUMBER QTY NOTES 

1 Remove Circuit Breakers BACC18AE25 2 . 

2 Remove Marker BAC27EEL23764 1 Refer to AMM 20-11 -06. 

3 Install Plug Button 2645 2 

FIGURE 5: H.STAB FUEL PUMP LOW PRESSURE SWITCHES AND P8S PANEL CHANGE 

February 22, 2006 (SHEET 2 OF 2) 

BOEING PROPRIETARY - Copy~ght C Un .... bli~ed Work - See page 1 for detail5. 

747-28-2265 

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BOEING SERVICE BULLETIN 747-28-2265 

FIGURE 6: HORIZONTALSTABILIZER TRANSFER PUMP MOTOR IMPELLER ASSY CHANGE 

FWO~ 

PUMP HOUS 1 NG 

'---STABI LIZER 

FRONT SPAR 

TRANSFER! JEn I SON PUMP 

o 

MOTOR J MPEllER 

FIGURE 6: HORIZONTALSTABILIZER TRANSFER PUMP MOTOR IMPELLER ASSY CHANGE 

February 22, 2006 (SHEET 1 OF 3) 

BOEING PROPRIETARY - Copyright C Unpublished Wori< - See palle 1 fO( deta~s _ 

747-28·2265 

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BOEING SERVICE BULLETIN 747-28-2265 

r: 

HST FRONT 

I -/SPAR 

I 

PACKING 4 

TRANSFER/ 

JEn iSON 

PUMP HOUS I NG 

PIN 

2 PLUG 

PUMP HOUS I NG ~ NUT 

"t;:~ 6 7 WASHER 

ELECTRICAL III 

BOND SURFACE II BONDING 

[VMOUNT I NG BOLT 

(AMM 28 - 17-05) 

(DO NOT REMOVE) 

I, I, 

r-- j ,- WASHER (S LOCATIONS) 

I ' _ SOCKET HEAD SCREW AND 

1 [0 '8f 

HST FRONT l U LBONDING JUMPER BUILD-UP 

SPAR ---...J1 I (DO NOT 0 I SASSEMBLE FROM 

L.......J BOND I NG CLIP) 

[VELECTRICAL 

BOND SURFACE 

5 PACKING 

Q:> PREPARE THE FAY I NG SURFACE OF THE TRANSFER/ JETT I SON PUMP HOUSING AND THE 

MATING SURFACE OF THE PLUG FOR AN ELECTRICAL SURFACE BOND (SWPM 20 - 20 - 00) . 

FIGURE 6: HORIZONTALSTABILIZER TRANSFER PUMP MOTOR IMPELLER ASSY CHANGE 

February 22, 2006 (SHEET 2 OF 3) 

747-28-2265 

SOEING PROPRIETARY _ Copyrlgnt ~ Unpublilhed Wor\c· S .... page 1 lor delah. 42 of 68 
BOEING SERVICE BULLETIN 747-28-2265 

The step numbers shown below agree with the numbers shown in the circle symbols in the figu re. The QTY 

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

STEP TASK NAME PART NUMBER QTY i NOTES 

Remove Motor Impeller 60-72101 -1 or 60-72102-4 (Boeing 2 I Refer to AMM 

1 Assembly Part Number 60S92603·22 or 28-17-04. Keep 

60892603-26) fasteners to 

install plug. 

Install Plug 835UOOO1-1 2 Use kept 

2 fasteners, if 

usable (1 0 

locations). 

3 Install Pin 835UOO02-1 2 I 

4 Install Packing MS29513-007 2 I 

5 Instal! Packing M25988-1-238 2 

6 Install Nut 8ACN10JC06C 2 Use with pin 

7 Install Washer NAS620C6 2 I Use with pin 

FIGURE 6: HORIZONTALSTABILIZER TRANSFER PUMP MOTOR IMPEL LER ASSY CHANGE 

February 22, 2006 (SHEET 3 OF 3) 

747-28-2265 

BOEING PROPRIETARY - Copyright Q Unpu bli~n d Wor" _ See page 1 for detailS 43 of68 
BOEING SERVICE BULLETIN 747-28-2265 

FIGURE 7: REMOTE ELECTRONIC UNIT CHANGES - E8 EQUIPMENT RACK 

AFT EQU I PMENT CENTER 

SEE A 

FWD~ 

3 

o 

Rf\\:lTt flE>' ~IT 

AFT EQU I PMENT 

RACK. E8 

REMOTE ELECTRONICS 

UN I T (REU) . M7861 

SEE CD 

ATIENTION 

ELECTROSTATIC 

GROUND 

o JACK 

~F\'I D 

HOUS I NG FOR THE REMOTE 

ELECTRONICS UNIT AFT EQU' PMENT CENTER 

CAPT I VE SCREWS 

(4 LOCATIONS) 

2 COVER PLATE 

I ND I V IOUAL FUEL QUANT I TY 

CHANNEL CARD. YSCA1 

REMOTE ELECTRONICS 

UN I T (REU). M7861 

® 

o 

FIGURE 7: REMOTE ELECTRONIC UNIT CHANGES - EB EQUIPMENT RACK 

February 22 . 2006 (SHEET 1 OF 2) 

BOEING PROPRIETARY _ Copyright e UnpublIshed Worl< _ See page 1 for details 

747-28-2265 

44of68 
BOEING SERVICE BULLETIN 747-28-2265 

The step numbers shown below agree with the numbern shown in the circle symbols in the figure. The QTY 

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

STEP TASK NAME PART NUMBER QTY NOTES 

1 Remove lFQC Card 60892018-204 1 Refer to AMM 28-17-10 

2 Reinstall COlier Plate - - 3 Install liND? Decal BAC27TFDEOO13 1 Refer to AMM 20-11-16 

FIGURE 7: REMOTE ELECTRONIC UNIT CHANGES - E8 EQUIPMENT RACK 

February 22, 2006 (SHEET 2 OF 2) 

BOEING PROPRIETARY _ Copyright e Unpubli5hed Work . See page 1 for deta'5. 

747-28-2265 

450f6S 
BOEING SERVICE BULLETIN 747-28-2265 

FIGURE 8: FUEL SYSTEM CARD FILE CHANGE 

FUEL SYSTEM 

CARD FILE 

A3 

FY/o~ 

UP 

{J 

FWO tt' 

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The Q1Y 

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

STEP TASK NAME PART NUMBER QTY 

1 Remove Single Point Sensor Card S344TQ02-B 1 

(SPSC) 

2 Install Cover Assembly 285UOO96-6 1 

Notes: 

(a) Install per drawing 284U1255, sheet 1, Rev. C, Zone: 812. 

February 22, 2006 

FIGURE 8: FUEL SYSTEM CA RD FILE CHANGE 

(SHEET 1 OF 11 

NOTES 

Remove Per AMM 

28-17-10. 

(a) 

• 

• " 

• 8 

BOEING PROPRIETARY - Copyright C Ullpublisned Work - ~ palle 1 for detah. 

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BOEING SERVICE BULLETIN 747·28·2265 

FIGURE 9: FUEL MANAGEMENT CONTROL PANEL CHANGE 

o 

FUEL MANAGEMENT 

CONTROL PANEL 

The step numbers shown below agree with the number.; shown in the circle symbols in the figure. The OTY 

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

STEP TASK 

Remove 

1 

February 22, 2006 

NAME PART NUMBER QTY NOTES 

Fuel Management 233u3100-247 1 Refer to Service Bulletin 

Panel Assy 747-24-2250 for new 

(MOO1540) panel assy installation. 

FIGURE 9: FUEL MANAGEMENT CONTROL PANEL CHANGE 

(SHEET 1 OF 1) 

BOEING PROPRIETARY _ Copyri&hl C Unpublished Work _ SII!e page 1 for t.a ~s , 

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BOEING SERVICE BULLETIN 747-28-2265 

FIGURE 10: DEACTIVATION OF TAIL TANK AT LEFT, CENTER, AND RIGHT EIU· E2--6 WIU WIRE 

CHANGE 

1.14260 WI U 

SEE DETAilS 

1 THROUGH 6 

e7 R

" 

MA I N EQU 1 PMENT CENTER 

FIGURE 10: DEACTIVATION OF TAIL TANK AT LEFT, CENTER, AND RIGHT EIU - E2-6 WIU WIRE 

CHANGE 

February 22, 2006 (SHEET 1 OF 10) 

• • • c 

747-28-2265 

BOEING PROPRIETARY - Capyriglll ~ Unpublished Work _ S .... paS" 1 for detab. 48 of 68 
BOEING SERVICE BULLETIN 747-28-2265 

ACTION WIRE NO. TYPE FROM TO LENGTH NOTES SL 

(a) (b) (e) EQUIP. NO. PIN EQUIP. NO. PIN (d) (e) If) 

DELETE QG0534 I RD DQ2665 C07 GDYOO06 22 0 - -

DELETE QG0584 I RD DQ2625 C07 GDYOO02 22 0 - -

DELETE QG0591 RD DQ2645 C07 GDYOO04 22 0 - - ADD QG1002 RD DQ2627 813 GDXOO02 13 7.3 - -

ADD QG1003 RD OQ2667 813 GDXOO06 28 10.8 - -

ADD QG1004 RD OQ2647 813 GDXOO04 28 10.8 - -

Change the wire wrap wires in the sequence shown in this table. Install the wire along the routing shown an the 

subsequent pages. Refer to Boeing Standard Wiring Practices ManuaI20-72-1B. 

LEGEND FOR DETAILS 1-6 

(a) DELETE Delete this wire from the wire integration unit (WIU). 

ADD Add this wire to the wire integration unit (W1U) 

(b) Wire number is shown for reference only; the number is not printed on wire wrap wires. 

(e) RD Cut from wire 82989006-1 4. This wire is BMS 13-46, Type 3, Class 1, AWG 26 

(d) The length of wire is in inches. Use these lengths as aids only. Cut the wire to the correct length 

during the installation. 

(e) None 

(Q Sleeve Code: None 

e changes in this figure are from Wire Kit 62684260 

FIGURE 10: DEACTIVATION OF TAIL TANK AT LEFT, CENTER, AND RIGHT EIU· E2-6 WIU WIRE 

CHANGE 

February 22, 2006 (SHEET 2 OF 10) 

BOEING PROPRIETARY - Copyright C Unpublished Work - See page 1 lor detab, 

747~28-2265 

49 of 68 
BOEING SERVICE BULLETIN 747-28-2265 

, 

0 • • -• --· · · • • • • • -----· · · · : I 0 • • • • • , , , • , • , • "0\112131415 

0 -· -• • • -· · • • • • -- 0 ---• • • -· · • • ---- -· -• -• · · -• • • --- 0 -· ---• · · -• • • --· 0 · · · · · · · · -· · · • • · 

0 · · · · · · · · -· -• • · · 0 · · · · · · · · -· • • · • • 

• • -· · · · -• • • • • • • 

0 • · · · · · · · · • • • • • • 0 · · -· · · • • • • • • • • • 

0 • • • • • • • · • • • • 

• · -· 0 · · · • · · · · • • • · -· • • · • • • · · -• • • • -· 0 · · -· · · · --· -· · -· 0 · · ---· · · ---· · · - 0 -· ---· · · -• • • • • • , ~ 0 -· · --,. . 

· -• • • • • , ~ 

: r: : • --· -- · • • • • • • c 

0 ~ 0 g • -· -- · • • • -• • , 

• -· --· · · · -• • • · - • 

0 -· · · --· · · -· · -· - 0 -· · · -· · · --· · -· - -· · · -· · · · -· · -· - 0 -· · · -· · · · -· · • • • 0 -· · · --· · · -· · · · - 0 -

• · • · · --· · · -• • • • - 0 · · • -· · -• • • • · • 

• · · · • --· · • • • • • - 0 --· ----· · -· ---- 0 -------· · -· ---- • , 

0 ~ 

> -· · --- · · · · ---- 0 8 -· ---· · · · · • • • • • 

RON B (2) 

ACTION WIRE NC.-GAGE TYP LENGTH 

(INCt-ES) f\JOTES 

CONI\ECTOR PIN COI\NECTOA PIN 

DELETE QOO584-2S RD 002625 C07 GOV2 22 

DETAIL 1 

N.QIE.;.Reference: Wiring Diagram 31-61-12. 

FIGURE 10: DEACTIVATION OF TAIL TANK AT LEFT, CENTER, AND RIGHT EIU - E2-S WIU WIRE 

CHANGE 

February 22, 2006 (SHEET 3 OF 101 

SOEING PROPRIETARY - Copyright C Unpubljsl1ed Work - See page 1 ordela~' , 

747-28-2265 

50 of 68 
ACTION WIRE ND.-GAGE 

ADD Q(31OO2·26 

DETAIL 2 

BOEING SERVICE BULLETIN 747-28-2265 

o~ 

o 

o 

o 

o 

o ~ 

Oil 

o 

o 

o 

o 

o 

o 

o 

1.14260 

TVP 

. " · ........ ..... . · . . . . . . . . . .. .. , 2 3 ~ 5 e 7 8 i 10 1112 31~15 

· .... ......... . · .. .. ... ...... . · ............. . · ........ .... . . · ...... ....... . · ............. . · ............. . · .. .... .... .. . . · .. .. ......... . · ....... .... .. . · .... ... ...... . · ............. . : : : : : : : : : : : :'-i : : 

· ... .... ...... . · ............. . · .... .. .. ..... . · .... ........ . . · .... .. .. ..... . · .... .... .... . . · .. .... .... ... . · ............. . · ... .. ......... . · .. ....... .. .. . · ...... ..... .. . · ...... .. ..... . · ............. . · .... ......... . · ... .......... . · .. ........... . · .............. . · ..... ........ . ROW s (2) 

o 

o 

o 

o 

o 

:0 

c !O 

o 

o 

o 

o 

o 

o 

o 

CONNECTOR P'N CONNECTOA P'N 

RD 002:627 B13 GDX2 13 

LENGTH 

(It«:HES) 

7.3 

~Refe ence : Wiring Diagram 31-61-12 

NOTES 

FIGURE 10: DEACTIVATION OF TAIL TANK AT LEFT, CENTER, AND RIGHT EIU· E2-6 WIU WIRE 

CHANGE 

February 22, 2006 (SHEET 4 OF 101 

BOEING PROPRIETARY . Co~yrigh: C Unpublished VVoIk · Sec pa\le 1 tor deUlb. 

747-28-2265 

51 of 68 
BOEING SERVICE BULLETIN 747-28-2265 

• 

0 I : -· · · · · · · • • -• • · -· · · · · · · · · - 0 , , , • • - • , , , , 9101112131415 

0 · -· · · · --• • • • • -· 0 --· · · · · -· • • • • • · 

· -· · · · · · · • · • • • • 

0 · • · · · · · · · • • • • · · 0 · · · · · · · · · • • • • · · 

0 • • • · · · · · · • • • • · · 0 · · · · · · · · · · · · · · · 

· · · · · • • • • • · · · · · 0 · · · · · · · · · · · · · · · 0 · · · · · · · · · · · • • • • 

0 · · · · · · · · · • • • • • • 0 · · · · · · · · · · · • • · • 

· · · · · · · · · • • • • • • 

0 · · · · · · · · · · · • 

• · · · 0 · · · · · · · · • • · · · · 

0 · • · · · · · · · · · · · · · , 0 0 · · · · · · · · · · · · · · · 0 • 

6 8 · · · · · · · · · · · · · · c 

· · · · · · · · · · · • • • • , 0 · · · · · · · · · · · · · · · , 

0 • • · · · · · · · • • • 

• • • · · · 0 · · · • • • • • • · · · • • • · · · · · · • • · · · · 0 • · · · · · · · · · · · · · · 0 · · · · · · · · · • · · · · · 

0 · · · · · · · · · · · · · · · 0 · · · · · · · · · · • • • • • 

· · · · · · · · · · · • • • • 

Q · • • · · · · · · • • • • 

• • • · · 0 · · · · · · • • • • • · 

0 ~ • • • · · : : : • • • • · · : I 0 ~ · · • · · • • • • • • 

"'''' RON 0 (4) 

ACTION WIRE NC.-GAGE 1'IP LENGTH 

(INCHES) NOTES 

CONt\ECTOA P'N CONflE.CTOA P'N 

DELETE QG0591-26 AD 002645 C07 GOY, 22 

" • il 

DETAIL 3 

Reference: Wiring Diagram 31-61-32 

FIGURE 10: DEACTiVATION OF TAIL TANK AT LEFT, CENTER, AND RIGHT EIU - E2-6 WIU WIRE 

CHANGE 

February 22, 2006 (SHEET 5 OF 10) 

BOEING PROPRIETARY _ CopyriQht C Unpublj5~ed Wor1< - See page 1 lor details. 

747-28-2265 

52 of 68 
BOEING SERVICE BULLETIN 747-28-2265 

• , 

0 § I: · · · · · · · · · · · · · 

· · · 0 • · · · · · · · • · • , , , • • • , , 9101112131415 

0 · · · · · • · · · · • · • 

• • • • • • • • • • • • • · • · • 0 

· · · · • • · • · · · · • · • 

0 • • • • • • • • • · • • • • • 0 · · • · · • · · • • • • • • · 

0 · · · · · · · · · · • • · · · 0 · · · · · · • · • • • • · • · 

· · · · · · · · · · • · · · · 0 · · · · · · · · · · · · · · · 0 · · · · · · · · · · · · · · · 

0 • · · · • • · • • • • • • • • , 0 , • • • · · · • • • • • • • • • , , 

· • · · · N • • • • • • • • • • C 

0 a · · · · · · • • • • • · ... • '0 0 

· · · · · · • · • • • • • • • ~ 

0 · · · · · · · · · · · · • • • 0 · · · · · · · · · · · · · • · 

· • • · • • • · • • • • • • • 

0 · · · · · · · · · · · · · · · 0 · · · · · · · · · • · • • · · 

0 · • • • · · • • • • • • • • • 0 · • • · • · · • • · • • • • • 

· · · · • · • · • • • • • • • 

0 · · · · • · • • • • · • • • • 0 · · · · · · · · · · · • · · • 

0 · · · · · · · · · · · • · · · 0 · · · · · · · · · · · · · · • 

· · · · · · · · · · · · · • • 

0 -· -· · - • • • • • • · • · • · • · • · • · • · • · • · • 0 

0 · · · · · · · · · · · • · • • 0 

· · · · · · · · · · · · · · · 

""SO RONQ(4) 

ACTION WIRE NO.-GAGE TYP LENGTH 

CONNECTOR PIN CONNECTOR PIN (1f\CHES) 

ADD 061004-26 RD 002647 813 GDX4 28 10.8 

DETAIL. 

~Reference : Wiring Diagram 31-62-32. 

NOTES 

• " 

3 

FIGURE 10: DEACTIVATION OF TAIL TANK AT LEFT, CENTER, AND RIGHT EIU - E2-6 WIU WIRE 

CHANGE 

February 22, 2006 (SHEET 6 OF 10) 

BOEING PROPRIETARY - Ccpyn;hI ~ Unpublished Work· See pag~ 1 for d"ta~s , 

747-28-2265 

53 of 68 
BOEING SERVICE BULLETIN 747-28-2265 

0 -• • · · · · · • • • • • · • 

· · 0 • · · · · · · • • • • • • , , , • , • , • 5101112131415 

0 • • • • · • • • • • • • • • • 0 · · · · -· · · • • • · • · · • • • · · · • • • • • • • · • 

0 · · · · · · · · • · · · · · · 0 · • · · · • • • • • • • • • • 

0 · · · · • • • • • • • • • · · 0 · · · · · · · · · · · · · · · 

· · · · · · · · · · · · · · · 0 · · · · · · · · · • • • · · · 0 · · · · · · · · · · · · · · · 

0 · · · · · · · · · • • 

• · · · · 0 · · · · · · · · • • • · -• 

· -· · · · · · · · • • • • · 0 • • • • • · · • • • • • · • · 0 · · · · · -· · • · · · · · · 

0 · · · · · · · · · · · · · · · , ~ 0 · · · · · · · · · · · · · · · 0 

" · · · · · · · · · · · · -· , 

0 0 -· · · · · · · · · · • • · · , 0 0 

· · · · · · · · · · · • · -· • 

0 · · --· • · · • • • · • · · 0 · · · · • • • • • • • · · · · 

· · • ---• • • · • · · · · 0 · · · · · · · · · · · · · · · 0 · · · · · · · · · · · · · · · 

0 · · · · · · · · · · · · · · · 0 · · · · · · · · · · • • · · · 

· · · · · · · · · · · · · -· 0 · · • · • • • • • • • · · · · 0 · · • --· • • • • • • · · · 

0 ~ · · · · · · · · · · · · · · 0 8 · · • · · · • • • • • • • · · 

""'''' ROO F (6) 

ACTION WIRE ND.-GAGE TVP LENGTH 

(iNCHES) NOTES 

COf\INECTOA PIN CONNECTOR PIN 

DELETE 000534-26 AD D02SSS C07 GDY6 22 

DETAIL 5 

NQ!E;.Reference: Wiring Diagram 31-61-22. 

FIGURE 10: DEACTIVATION OF TAIL TANK AT LEFT, CENTER, AND RIGHT EIU • E2-6 WIU WIRE 

CHANGE 

February 22, 2006 (SHEET 7 OF 10) 

BOEING PROPRIETARY _ Copyright C Unpub!i5hed WIlli< - SEe page 1 fer details. 

747-28-2265 

54 of 68 
ACTION WIRE NO.-GAGE 

ADD 001003-26 

DETAIL 6 

BOEING SERVICE BULLETIN 747-28-2265 

o~ 

o 

o 

o 

o 

O. ~ 08 

o 

o 

o 

o 

o 

o 

o 

.... 260 

TY' 

• · . . . . . . . . . .. .. · .. .......... . . · ...... ....... . • • • ••• . . . . . . . . . · ............. . · ............ . . · .. ........ ... . · ....... .... . . . · .. ....... .. . . . · ... ... . .... ... · .... .. .. .... . . • •••••• ....... . · ... . . . . . . . . . . . · .. ..... ...... . · . . . . . • • • • • • L " • 

o 

o 

o 

o 

iO 

, 

· ........... ... ~ '0 

· ...... .... ... . · .......... . . . . · . . . . . . . . . . . . . . · ....... . .. .. .. · ..... .. ..... . . · ... ......... .. · . . . . . . . . . . . . . . · .. ........... . · ....... . . . . . . . · .... ......... . · .. · ...... ...... . . · .......... ... . · ....... ... ... . · ........... .. . ROW F (S) 

o 

o 

o 

o 

o 

o 

o 

COt-JIJECTOA PIN CO/'IJ\JECTOR PIN 

AD D02$67 813 GDXB 2B 

LENGTH 

(INCHES) 

10.8 

~Reference : Wiring Diagram 31-61-22. 

NOTES 

FIGURE 10: DEACTIVATION OF TAIL TANK AT LEFT, CENTER, AND RIGHT EIU - E2-6 WIU WIRE 

CHANGE 

February 22, 2006 (SHEET 8 OF 10) 

BOEING PROPRIETARY - Copyright C Unpubl,shed Wot!< - See palle t l or delah. 

747-28-2265 

55 of 68 
BOEING SERVICE BULLETIN 747-28-2265 

AR0426 REFERENCE: IYIRING DIAGRAM 31-61-12 

W4260 

Wi l"c7 ! Ii"" ryyrJ " QG0584-26 111///11. GDYOO02-22 

N2 625A I 002625 

60 ------------------------------" 

AR042 6 REFERENCE· WI RING DIAGRAM 3'-6'-22 

W4260 

C7 I, ' , I , , r 71 rri QGOS34-26 ( ( { , ( 'II, GDYOOO6-22 i) i i ) ) 

D\Y266 5A 002665 

M4260 WIU 

AR0426 REFERENCE" WIRING DIAGRAM 31-61 - 32 

W4260 

C7 QG059, -26 ) ( T/ , ( ( ( ) , i 'II' GDYOOO4-22 

OW264 5A DQ2645 

M4260 WIU 

FIGURE 10: DEACTIVATION OF TAIL TANK AT LEFT, CENTER, AND RIGHT EIU - E2-6 WIU WIRE 

CHANGE 

February 22, 2006 (SHEET 9 OF 10) 

747-2 8-2265 

BOEING PROPRIETARY - Copyright C lJnpubljshed Work· See page 1 for de\4l ~I. 56 of68 
BOEING SERVICE BULLETIN 747-28-2265 

AR0426 

! 1813 1 , __ _

~ 

REFERENCE: WIRING DIAGRAM 31 -51 - 12 

W4260 

QGl002-26 --....,111 GDX0002-13 

DW2627A ILDQ_2_62_7 ___ ________ ____ ~ 

M4260 IVI U 

AR0426 

I 

l 813 

DW2667 A OQ2667 

M4260 WI U 

AR0426 

IJ 8131- 1 -

REFERENCE ' WIRING DIAGRAM 31 -61 -22 

W4260 

QG1003-26 !II GOXOOO6-28 

REFERENCE. WIRING DIAGRAM 31-61-32 

W4260 

001004-26 --""'111 GOXOa04 - 28 

OW2547A I OQ2647 

L-______________________ ~ 

M4260 WI U 

- ADDED WIRE 

++++ DELETED WIRE OR FORMER ROUT I NG 

FIGURE 10: DEACTIVATION OF TAIL TANK AT LEFT, CENTER, AND RIGHT EIU - E2-6 WIU WIRE 

CHANGE 

February 22, 2006 (SHEET 10 OF 10) 

BOEING PROPRIETARY - Copyrighl C Unpublished V'lbr1< _ S .... page' for deta~s_ 

747-28-2265 

57 of 68 
BOEING SERVICE BULLETIN 747-28-2265 

FIGURE 11 : REWORK OF HORIZONTAL STABILIZER TANK TRANSFER LINE 

SEE CD FOR EXI STING 

PARTS REMOVAL 

SEE CD FOR PLUG 

INSTALLATI ON 

FUEL TRANSFER II NE 

FOR THE HOR IZONTAL 

STAB ILIZER TANK 

(liST) 

SEE A FOR EXISTING PARTS REMOVAL 

SEE CD FOR PLUG INSTALLAT ION 

FIGURE 11 : REWORK OF HORIZONTAL STABILIZER TANK TRANSFER LINE 

February 22, 2006 (SHEET 1 OF 8) 

BOEING PROPRIETARY _ Copynllht C UnputJIi$hl!d Wor!<. - See pall" 110. dl!ta~ . 

• 

• " o 

747-28-2265 

58of6S 
BOEING SERVICE BULLETIN 747-28-2265 

UN ION ~h.--.;>;:-;~~~"[~ O-R ING " 

TOP OF THE CENTER 

WING TANK 

FIGURE 11 : REWORK OF HORIZONTAL STABILIZER TANK TRANSFER LINE 

February 22, 2006 (SHEET 2 OF 8) 

BOEING PROPRIETARY - Copyngh! e Unpublished Work - See page 1 lor detaits 

• " il 

747*28-2265 

59 of 68 
, 

, 

, 

I 

j : 

, I 

Ld 

BOEING SERVICE BULLETIN 747-28-2265 

HOR I ZONTAL 

'-~ STABILIZER 

FITT ING 

,-~SHROUD 

(FLEX I BLE HOSE) 

____ '-// FUEL HOSE 

\ 

HOSE AS$EMBL Y 6 

TUBE ASSEMBLY 6 

SHROUD 

DRA IN 

LINE 

BULKHEAD 

STA 2598 

FIGURE 11 : REWORK OF HORIZONTAL STABILIZER TANK TRANSFER LINE 

February 22, 2006 (SHEET 3 OF 8) 

BOEING PROPRIETARY - CopYrl9hl CI Unpub!ilohed Work - See page 1 for dela's. 

747-28-2265 

60 of6S 
BOEING SERVICE BULLETIN 747-28-2265 

WING TANK 

FIGURE 11: REWORK OF HORIZONTAL STABILIZER TANK TRANSFER LINE 

February 22, 2006 (SHEET 4 OF 8) 

BOEING PROPRIETARY· Copyright I:;l Unpublished IIIobrk _ See page 1 fer details. 

747-28-2265 

61 of 68 
BOEING SERVICE BULLETIN 747-28-2265 

11 _ __ HORlZONTAL 

STABILIZER 

FITT ING 

,ret i : , I 

i I~f 

I , 

I ' , I 

Lei 

SHROUD 

DRAIN 

LINE 

o 

PLUG 7 

, __ SHROUD 

(FLEX IBLE HOSE) 

FUEL HOSE 

, __ ~ ___ --"1 

~-

BULKHEAD 

STA 2598 

7 O-RI NG 

FIGURE 11 : REWORK OF HORIZONTAL STABILIZER TANK TRANSFER LINE 

February 22, 2006 (SHEET 5 OF 8) 

BOEING PROPRIETARY _ Copyright C Unpublished Wtlrk _ S...e page 1 for deLa l~ . 

747-28-2265 

62 of 68 
BOEING SERVICE BULLETIN 747·28·2265 

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The OTY 

numbers shown below are the number of parts necessary for each airplane. Each reference drawing listed is a 

Module Parts List (MPL). The MPL lists all the retrofit drawings and/or production drawings picture sheets to 

facilitate installation of the identified part, assembly or installation. 

STEP TASK NAME IDENTIFICATION QTY REMOVAL REMOVAL PIC INSTALL MORE 

INSTALL DRAWING SHT REF DATA 

PIN REF REF REF 

1 Remove Hose Assy 10-60536-25 (opt 1 344U1022 344U1022 1 (a) 

10-60536--22) ·24 

Remove Fitting 344UOOOO-6 1 344U1022 344U1022 1 (a) 

·24 

Remove Tube Assy 344U1 022-1 0 1 344U1 022 344U1022 1 (a) 

·24 

Remove Tube Assy 344U1022-11 1 344U1022 344U1022 1 (a) 

·24 

Remove Tube Assy 344U1022-12 1 344U1022 344U1022 1 (a) 

·24 

Remove Tube Assy 344U1022-13 1 344U1022 344U1022 1 (a) 

·24 

Remove Tube Assy 344U1022·14 1 344U1022 344U1022 1 (a) 

·24 

Remove Tube Assy 344U1022·2 1 344U1022 344U1022 1 (a) 

·24 

Remove Sleeve 344U1022·22 1 344U1022 344U1022 1 (a) 

·24 

Remove Shroud 344U1022·23 1 344U1022 344U1022 2D7 (a) 

·24 

Remove Tube Assy 344U1022·25 1 344U1022 344U1022 1 (a) 

·24 

Remove Tube Assy 344U1022·26 1 344U1022 344U1022 1 (a) 

·24 

Remove Tube Assy 344U1022·5 3 344U1022 344U1022 1 (a) 

·24 

Remove Tube Assy 344U1022·8 1 1 344U1022 344U1022 1 (a) 

·24 

Remove Tube Assy 344U1 022·9 1 344U1022 344U1022 1 (a) 

·24 

Remove Nut Assy 6 3058374S48·03 2 344U1022 344U1022 2C7 (a) 

·24 

Remove Shroud 63058381548·1 1 344U1022 344U1 022 1 (a) 

Connector ·24 

Remove Coupling 63211-48 1 344U1022 344U1022 3A5 (a) 

Assy ·24 

Remove I Spacer 69892447·39 1 344U1022 344U1022 (a)(b) 

·24 

FIGURE 11 : REWORK OF HORIZONTAL STABILIZER TANK TRANSFER LINE 

February 22, 2006 (SHEET 6 OF 8) 

BOEING PROPRIETARY . Ccpyright C Unpublishl!d Werle · See page 1 for detail,_ 

747·28·2265 

630f68 
BOEING SERVICE BULLETIN 747-28-2265 

STEP TASK NAME IDENTIFICATION QTY REMOVAL REMOVAL PIC INSTALL MORE 

INSTALL DRAWING SHT REF DATA 

PIN REF REF REF 

1 Remove Spacer 69892447-52 1 344U1022 344U1022 (allb) 

-24 

Remove Spacer 69892447-8 1 344U1022 344U1022 1 (allb) 

-24 

Remove Clamp, AN735D48 20 344U1022 344U1022 1 (a) 

Loop -24 

Remove Coupling AS1712D48 11 344U1022 344U1022 1 (a) 

-24 

Remove Bolt BACB30NM3HK7 6 344U1022 344U1022 3 (a) 

-24 

Remove Clamp, U- BACC10CC48 3 344U1022 344U1022 1, 2, (a) 

style -24 3 

Remove Clamp BACC10CC48S 1 344U1 022 344U1Q22 (allb) 

-24 

Remove Clamp, U- BACC10EW48A 60 344U1022 344U1022 2 (a) 

style -24 

Remove Clamp, U- BACC10EW488 60 344U1022 344U1022 2 (a) 

style -24 

Remove Bonding BACJ40A20-3 2 344U1022 344U1022 2 (a) 

Jumper -24 

Remove Bonding BACJ40A20-4 4 344U1022 344U1022 " 2 (a) 

Jumper -24 

Remove Bonding BACJ40A20·5 9 344U1022 344U1022 1,2 (a) 

Jumper -24 

Remove Shim, BACS40ROOBE048F 1 344U1022 344U1022 1 (a) 

Laminated -24 

Remove Pin MS24665-144 4 344U1022 344U1022 1, 2 Cal 

-24 

Remove O-ring MS29513-234 2 344U1022 344U1022 1,2 Ca) 

-24 

Remove O-ring MS29513-241 1 344U1022 344U1022 1, 2 (a) 

-24 

Remove a-ring MS29513-338 26 344U1022 344U1022 1,2, (a) 

-24 3 

Remove a -ring NAS1523AA3R 6 344U1022 344U1022 3 (a) 

-24 

2 Remove Fitting 344UOOOO-2 1 344U1022 344U1022 1 (a) 

a-ring MS29513-241 1 -24 

FIGURE 11 : REWORK OF HORIZONTAL STABILIZER TANK TRANSFER LINE 

February 22, 2006 (SHEET 7 OF 8) 

BOEING PROPRIETARY _ Copyright C Unpublished Work · See paS" 1 fordetails 

747-28-2265 

64 of 68 
BOEING SERVICE BULLETIN 747-28-2265 

STEP TASK NAME IDENTIFICATION QTY REMOVAL REMOVAL PIC INSTALL MORE 

INSTALL DRAWING SHT REF DATA 

PIN REF REF REF 

3 Remove Union AP7102D32·1 (opt 1 344U1022 344U1022 1 (a) 

AFP720D3232 or -24 

AP71 02032 or 

MS21900D32) 

O-ring MS29512-32 1 

4 Install Plug AS5168W32 (Opt 1 834B0401 (c) 

MS21913W32) -1 001 

O-ring MS29512-32 1 

5 Install Plug 83580004-1 1 83480401 (c) 

O-ring MS29513-241 1 -1001 

Lockwire MS20995NC32 1 

6 Remove Tube Assy 344U0018-8 (opt 1 344U1022 344U1022 1 (a) 

344UOO18-5) -24 

Hose Assy 10-60536-23 1 

7 Install Plug AS5168W32 1 83480401 (d ) 

O-ri ng MS29S12-32 1 ·1001 

8 Install Cap BACC14AD06D 1 83480401 (e) 

-1001 

NOTE 

(a) Refer to 747-400 AMM 28-17-06 for additional information. 

(b) Quantity used varies. 

(c) on 344UD014-1 fitting. 

(d) on 13218 adapter. 

(e) on MS21912D6tee. 

FIGURE 11 : REWORK OF HORIZONTAL STABILIZER TANK TRANSFER LINE 

February 22, 2006 (SHEET 8 OF 8) 

BOEING PROPRIETARY . Copyri g"t e U~publish d WJtI< _ See page 1 tor deta'l. 

747-28-2265 

65 of 68 
BOEING SERVICE BULLETIN 747-28-2265 

FIGURE 12: REWORK OF WIRE BUNDLES 

fWO~ 

STEP TASK NAME 

1 Rework Wire Bundles 

WIRE BUNDLE 

WOOD? 

WOO76 

W0144 

W2018 

W3842 

W3844 

W3B45 

W3B46 

February 22, 2006 

STA 

STA 

MORE DATA 

STA 

1980 

I 

See Table 1 for all reworked wire bundles. Refer to 747.400 Wiring 

Diagram Manual - WirelEquipment List for additional information. See 

Wire Kil828B6101 and 82886102 

IDENTIFICATION INSTALL REF WIRE DIAGRAM 

82680007-1 62886102·1001 28-21-26 

82680076-1 62886102-1001 28-21-23 

82680144-1 82866102-1001 28-21-24 

82662018-1 82886102-1001 24-51-26,24-51-64 

82663842-1 82886102-1001 28-21-26 

82683844-1 82886102-1001 28-21-26 

82683645-1 82886102-1001 28-21-11 

82683846-1 82866102-1001 28-21-26 

FIGURE 12: REWORK OF WIRE BUNDLES 

(SHEET 1 OF 3) 

BOEING PROPRIETARY _ Copyright C UnpubliShed Work - ~ page liar delab . 

747-28-2265 

66 of68 
BOEING SERVICE BULLETIN 747-28-2265 

WIRE BUNDLE IDENTIFICATION INSTALL REF WIRE DIAGRAM 

W3851 

W3890 

W3942 

W3944 

W4092 

W4094 

W4260 

W4261 

W4262 

W4263 

W4406 

W4415 

W4427 

W4435 

W4437 

W4441 

W4445 

W4478 

W4488 

W4562 

W4588 

W4601 

W4602 

W4606 

W4607 

W4611 

W4616 

W4618 

W4620 

W4641 

W4693 

W4750 

W4751 

W4753 

W4758 

W4760 

W4764 

W4768 

February 22, 2006 

82683851-1 82886102-1001 28-21-12 

8268 3890-1 82896102-1001 128-21-21 

82683942-1 82886102-1001 28-21-29 

82693944-1 82896102-1001 28-21-29 

82694092-1 182896102-1001 24-54-1 3 

82684094-1 82886102-1001 24-54-23 

82684260-1 82886102-1001 28-21-29,31-61-12, 

31-61-22,31-61-32 

82684261-1 828861 02-1 001 28-42-15 

82684262-1 82896102-1001 28-21-29 

82684263-1 828961 02-1001 28-42-15 

82684406-1 82896102-1001 28-21-23 

82694415-1 82886102-1001 28-2 1-23 

82694427-1 82886102-1001 28-21 -29 

82694435-1 82886102-1001 28-21 -25 

82684437-1 82886102-1001 28-21-12 

82684441-1 82886102-1001 28-21 -27 

82684445-1 82896102-1001 28-21 -13 

82684478-1 82886102-1001 28-21-12 

82684488-1 82886102-1001 28-21-13 

82684562-1 82896102-1001 28-2 1-30 

82684588-1 82896102-1001 28-21 -13 

82684601-1 82896102-1001 28-21-28 

82694602-1 82896102-1001 28-42-15 

82684606-1 82886102-1001 28-21-25 

82684607-1 82886102-1001 28-21 -31 

82694611-1 82886102-1001 28-21-28 

82684616-1 82896102-1001 28-2 1-12 

82684618-1 82896102-1001 28-2 1-28 

82694620-1 82886102-1001 28-2 1-12 

82684641 -1 82886102-1001 28-21-31 

82684693-1 828861 02-1001 28-21-12 

82684750-1 82886102-1001 28-42-15 

82684751 -1 82886102-1001 28-21-26 

82684753-1 82886102-1001 28-42-15 

82684758-1 82886102-1001 28-21-26 

82684760-1 82886102-1 001 28-21 -29 

82684764-1 82896102-1001 28-43-12 

82684768-1 82886102-1001 28-21-29 

FIGURE 12: REWORK OF WIRE BUNDLES 

(SHEET 2 OF 3) 

BOEING PROPRIETARY - ~n ht C Unpublished Wor!<. - See page 1 lor details. 

747-28-2265 

67of68 
BOEING SERVICE BULLETIN 747-28-2265 

WIRE BUNDLE IDENTIFICATION INSTALL REF WIRE DIAGRAM 

W4774 

W4974 

W5172 

February 22, 2006 

82684774-1 82886102-1001 28-21-29 

82684974-1 82886102-1001 28-21-21 

82685172-1 82886102-1001 28-21-30 

FIGURE 12: REWORK OF WIRE BUNDLES 

(SHEET 3 OF 3) 

BOEING PROPRIETARY _ Copyright = Unpublished Wort< _ See page 1 for details. 

747-28-2265 

68 of 68