### 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### © 2006 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent thaI the page contains copyrightable subject matter.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 th e document and th e 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 PROPR I ETA RY . Copyright I!> Unpubiish ed Worl< _ See p.<lg e 1 for detai l s . 747-28-2265 1 of68

### BOEING SERVICE BULLETIN 747-28 -2265

BLANK PAG E



### BLANK PAGE 

### February 22, 2006 BOEING PROPRIETARY. Copynght C Unpubl's.hed WQIic. See Pi'lle 1 for delll" ' _**7~ 28~** **2265** 

### 2 of 

### 68

### BOEI N G S E RVIC E BU LLE TI N 747-28-22 6 5 Summary 1 . PLANNI N G 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 Intercha ngea bility and Intermixabilily of Parts . 2 . MATERIAL INFORMATI ON . 

### A Material- Pri ce and 

### Availabili ty .. B . I nd ustry Support Information ... C . Parts N ecessary For Each Airplane 1 . Kits/Parts : 2 . Parts and Materia ls Supplied by the Operator: 3. Parts M od ified 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 Bull eti n . 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 WI N G REFUELING PANEL P42 MODIFICATI ON . 

### 37 FIGURE 

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

### 39 FIGURE 

### 6 : HOR IZONTALSTABILIZER TRANSFER PUMP MOTOR IMP E LLE R ASSY CHANGE 

### 41 FIGURE 7 : REMOTE ELECTRONIC UNIT CHANGES - E8 EQUIPMENT RACK 

### 44 FIGURE 6 : FUEL SYSTEM CARD F I LE 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 T

ab l e of Contents February 22, 2006 BOEING PROPRIETARY ·**COP1righ~** C' Un p", toishcd Worit - See pasc 1 for det1ln s . 

### 747-28-2265 

### 3 of 68

### BOEING SERVICE BULLETIN 747-28-2265 FIGURE 11 : REWORK OF HORIZONTAL STABILIZER TANK TRANSFER LINE FIG URE 12 : REWORK OF W iRE BUNDLES



### Table of Contents February 22 , 2006 BOEING PROPR I ETARY . Co pyn ght C Unpul>l isil e d W o r\(·**S~** page 1 l o r**de\a~ 1**  

### . 56

. 66



### 747-28-2265 4 of 

### 68

### Number : Date: AT A System : 747-2 8-2265 February 22 , 2006 2811 

### Commerc ial Airplane Group 

# 747 Service Bulletin Summary SUBJECT : CONV ERSION Airplane from a 747-400 Passenger configu rat ion to a 747-400 Spec ial Freighter (SF) Configuration - Horizontal Stabilizer Tank Deactivation CONCURRENT REQUIREMENTS Refer to Paragraph 1 . B . BACKGROUND As part of the special freighter conversion . the ho rizontal stabi l izer fue l tank is to be deactivated and the fuel transfe r lin e removed . This service bullet in provides instructions and kit of parts to do that. ACTION (MC 0300MK4010) On P7-2 overh ead ci rcuit breaker pane!. remove the Horizon ta l Stabiliz er REFUEL 

### & XFR circuit breake rs C10125 and C10126 . Rework the circuit breaker w iring . On P5 overhead pane!. remove th e Fuel Management Control Modu le (M00154) and rewo rk the wiring. At the FWD and AFT fuel isolation valves for the horizontal stabi l izer transfer system , disconnect electrical connector from each va l ve actuato r, co i l and stow wiring. Position manual override lever for affected valves , located an valve actuator, to closed pos ition an d lock wire to secure in place . On the horizontal stabilizer refuel valve control u nit, disconnect electrical connector , cap and stow wi ring. On the P42 left wing refueling panel coil and stow wiring for in dicator , switches and lights. Place " H.STAB TANK DEACTIVATED " placard above H . STAB indicator. On the E8 equipment rack , in the Remote E lectron ic Unit (REU) , M7861 , remove REU cove r p l ate and H . STAB Individu a l Fue l Quantity Channel ( IF OC) card . Re-install REU cover plate . Placard R EU " I NOP ' and rework the wiring . ON the E2 equipment rack, make ch anges to the left , center , and right Electronic Instrument Unit (E IU ) configuration pins to disable the Horizontal Slab Tan k display and associat ed messagi ng on the Integrated Display Unit (lOS) . On P8S pan el. remove HOR STAB XFER/JETT PUMP 

### circuit breakers C031 4 1 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 fo r H.STAB fuel pum p low p ressure switches .

February 22 , 2006 BOEING PROPRIETARY - Copyrignt 

### e Unpublisn e d Work · See P3 \1 e , tor del<ul s 

### 747-28-2265 

### 5 of 68

### BOEING SERVI CE 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 F i le , remove horizonta l stabilizer transfer Single Point Sensor Control (SP SC) card and install cover assembly . Coil and stow SPSC ca rd w iring . I nsert jum per wire in Fuel System Card File. On the Fuel Quantity Indicating System 

### (Fa IS ). reprogram FQIS card fil e for Horizontal Stabilizer absent. On the Wire Interface Unit (WlU ), 

### mOdify affected wire bundles at W1U. On the fuel t ransfer li ne. remove and discard fuel transfer l ine from center wing tank to the horizontal stab ilizer fuel tank , and in stall 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 , Fina l Rule Docket Number 2002·NM·314.AD, Amendment 39·12993 is related to th is service bulletin. INDUSTRY SUPPORT INFORMATION Boeing Industry Support information is p rovided in Master Change 0300MK4010 . MANPOWER Man Hours are not l isted in th is Service Bulleti n they are negotiated separate l y between Boeing and the contracted modification facility. MATER IAL I NFORMATION Negotiated Kits.

February 22, 2006 BOEI N G PROPRIETARY - Copyngh l C Unpo.Jblished Work - See pag e ' ro r dela' s. 

### 747-28-2265 60f68REMOVE SPS CARD FROM FUEL SYSTEM CARD FILE AND INSTALL 

### COVER ASSY

REMOVE FUEL MGMT PANEL**INTHEP5~** 

# L REMOVE REFUEL AND XFR STAB L A ND STAB R CIRCUIT BREAKERS ON P7 PANEL



### February 22, 2006 

### BOEING SER V ICE BULLETIN 747-28-2265



## pas I T ION M ANUAL OVERR I DE LE VER FOR FWD ISOLATION VALVES TO CLOS E POSITIO N AND DISCONNECT ELECTR! CAL CONNECTOR FROM VALVE ACTUATOR RE MOVE 2 M OTOR I MPELLER UNITS. I NS TALL 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 P M

ENT RACK £8 REMOVE I FOC CARD IN REU . PLACARD REU I NOP . REMOVE 2 C I RU IT BREAKERS ON PBS 

### PANEL .

PLACARD " H. STAB TANK DEACT IVATED" ON LEFT WING REFUELING P42 PANEL REMOVE HOR IZONTAl STABILIZER FUEL TRANSFER II NE AND 

### INSTALL P L

UGS REMOVE RELAYS AND CHANGE THE WIRING AT THE P7 , P414 FUEL SYST EM CARD FILE, E2-6 SHELF AND THE P54 PANEL . REV I SE PIN PROGRAMMI NG TO THE LEFT , CENTER AND RIGHT EIU O N SHELF 6 OF E2 - 6.

BO:oING PROPRIETAHY _ Copyright I!:I Unpubli shed Work _ See page 1 for del.) i ls . 

### 747-28-2265 

### 7 of 

### 68

### BOEING SERVICE BULLETIN 747-28-2265

BLANK PAGE



### February 22. 2006

a O E I NG PROPRIETARY· Copyright**~** UnpuDli sl led Wo ft; · See palle 1 fo r deta il s . 

### 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 Stabili ze r Tank Deactivation 1 , PLANNING INFORMATION A. Effe ct ivity 1 . 

### Ai rp lanes Refer to SelVice Bulletin I ndex Docu ment 0 6-30300 Part 3 for A i rp lan e Variable N umber, Li ne N umber , and Serial Number data . This selVice bulletin i s fo r the airplanes shown below. Refer to Mast er Change 0300MK4010 for data about th is change. GROUP CONFIGURATION DESCR I PT I ON 

### 1 

# - 747-400 airplanes RT456 to be modified to a 747-400SF . Airplane models : 747-400 I DE NTIFICATIO N BY 

### CUS TOME R , CUS TOMER CODE, GROUP AND VARIABLE NUM BER CATHAY PACIFIC A IR WAYS (CAT) 1 RT456 IDENTIFICATI ON BY VARIABL E NUMBER 

# I Variable Group RT456 

### 1 2. 

### S pares Affected None .

Februa ry 22 , 2006 BOEING PROPRIETARY - CO pyri g h t**~** UnpUbi lShed 1Nor!<· See page 1 ! Of delab. 

### 747-28-2265 90f68

### BOEI NG SERVICE BUL LET I N 747 -28 - 226 5 B . Conc u r r ent Requ i rements The related 74 7-400SF concu rrent service bulletins are: 

### 747-00-0005,747-00 -0007 .747-00-0014, 747 -21 -2431 , 747-24-2250, 747-25-3362, 747-25-3366, 747-53-2510,747-53-2531.74 7-57-2324. C. Reason As part of the special freighter conversion , the horizontal stab i li zer fue l tank is to be deactivated and the fuel transfer line removed . This service bulleti n provides i nstructions 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 Modu le ( M00154) and rewor1< the wi ring. At the FWD and AFT fuel isolation valves for the horizontal stab i l izer transfer system , disconnect electrica l connector from each valve actuator , coil and stow wiring . Position manual override lever for affected valves , located on va lve actu ator, to dosed position and lock wire to secure i n place . On the horizontal stabi l izer refue l valve control unit, disconnect electrical connector, cap and stow wiring. On the P42 left w i ng refueling panel coil and stow wiring for ind icator , switches and lights . Place " H.STAB TANK DEACTIVATED " placard above H . STAB indicator. On the E8 equipment rack, i n the Remote Electronic Unit (REU) , M7861 , remove REU cover plate and H .5TA B I nd ivid ua l Fue l Quantity Chan net ( I FOC) card . Re- install REU cover plate . Placard REU " INOP · and rework the wiring. O N the E2 equipment rack, make changes to the left, center, and right Electronic Instrument Unit (E I U) configuration pins to disable the Horizontal Stab Tank display and asso ciated messaging on the Integrated Display Unit ( I DS) . On P8S panel , remove H OR 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 p lug s 51884 and S1685 for H.STAB fue l pump low pressure switc hes . On the horizonta l 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 Ca rd File , remove horizontal stabilizer transfer Single Point Sensor Control (SPS C) 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 Wl U . February 22, 2006 BOEING PROPRIETARY _ Copyright**~** Unpu blishe d Wark· See page t lar clcta" . 747-28-2265 100f68

### BOEING SERVICE BULLETIN 747-28-2265 On the fuel transfer line , remove and discard fue l lransfer line from center wing tank to the horizontal stab i lizer fuel tank , and install plugs . 

### E . Compliance Federal Aviat i on Administration (FAA) Airworth iness Directives ; 97-03-17 , 2002-19-52 and 2002 -2 4 - 52 , Final Rule Docket Number 2002-NM-314-AO , Amendment 39-12993 is related to th is service 

### bulletin . 

### F. Approval This service bulletin was exam ined 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 servic e 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 app rova l before incorporating this service bulletin . G. Manpower Man Hours are not listed in this Service Bulletin they are negoti ated separately between Boeing and the contracted modification facility. H . Weight and Balan ce Changes Boe i ng requ i res that , because of the magnitud e and uniqueness of major modificat ion programs , the tota l airp l ane weight and centerof g ravity w ill be determined by actual weighing after all modifications are complete and prior to del ivery . The actual data 

### win be recorded and p laced in Chapter 2 of the Weight and Balance Manua l. I. Electrical Load Data**~T he**  electrical loads of CAT Model 747-4008 airplane (RT4S6) as specified in document 0281 U002-422 have been reviewed and the following load s were deleted . 1 . Direct Current (DC) Loads Ai rpla nes Nomenclature Connected Circuit Load Breaker RT4S6 Refuel and Transfer 1 .40 1 012 5 Stabilizer - left Refuel and Transfer 1.4 0 10126 Stabi l izer - Right

February 22 , 2006 BOEING PROPRIETAR Y _ Copyri g ht ;' U n puOlishlNl 'Abril _See page 1 tor**deta ~s**  

### Bus DC1P7 DC2P 7

747 -2 8-2265 110f68

### BO E ING S E RVI C E BUL L ETI N 747 - 28 -2 265 2. Alternating Cu rrent 

### CAe) Loads A i r planes N ome n c l at ure 

### Co nn ected L oad C i rcuit B us 

### Breaker RT456 Horizontal Stabilizer 4 .600KVA . 76PF 

### 3141 GSB-3 Boost Pump - Fwd Horizontal Stabilizer 4 . 600KVA .76PF 

### 3142 AC2P85P183 Boost Pump - Aft 

### J. Referen ces 

### 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 Manua l ( SRM ) 51 d. 747-400 Wiring Diagrams 24-51-26 , 24·51 ·64 ,2 4-54-13 , 24 -54 -2 3 , 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 ·3 0, 28-21 -3 1 , 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 P ractices Manual (SWPM) 20-10-11, 20-10- 1 2 , 20-20-00 2 . Data supp lied w ith this Service Bulletin :

February 22, 2006 1 . The Modu le Parts List (MPL) drawings l isted below w i ll 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 Maste r Change 0300MK4010 .

BOEI NG PRO P RIETARY· C<>p1nghl C Unpublished Work· See page 1 fO f**deta~l .**  747-28-2265 12 of 68

### MPl 

### BOEING SE RVICE BULLET I N 747-28-2265 2 . Within the MPl is a 

### lis t of the retrofit 

### andlor production drawing p icture sheets required to facilitate installation of the identified part , assembly or in stallation as g ille n in this service bulletin . Table 1 - 

### , Titl e 

### Drawing Sh eet Rev Number 

### 834 80401-1001 FUEL TANK DEACTIVATION· 

### 83480401 

### MPl C HO R I ZONTAL STAB I LIZER 

### 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. I nstallation D rawings Used in the Preparation of this Service Bulletin : Non e. 4. Process Data: 

### Boeing Process specifications refe rred to on the drawings are not given in this service bulletin since these procedures are frequently used as standard shop p ra ctices .

February 22, 2006 BOEING PROP R I ETARY -**Copyng~1** C Un published Wolk - See page ' tor d etail s 

### 747-28-2265 130f68

### B OE ING SERVICE BULLETIN 747 -28-2265 K. Publications Affected



### Pub lication Chapter·Section 747 FAA Approve d Airplane Flight Manual 

### • 747 Operations Manua l 

### 02 .02, 15.10 , and 15 .20 747 Mai ntenance Manua l 

### 11-13 , 28-10 , 28-30 , and 28-40 ( Dual configuration alread y exi sts) 747 Wiring D iagra m Man ual 

### 24-51 , 24 -54 , 28-21 , 28-22 , 28-27 , 28-41 , 28-42 . 28-43 , 28-51, and 31-61 747 Fault Reporting Manua l 

### 28 - 10 747 Fault Isolation Manu al 28 CMCS Index , 28 EICA S In dex 747 Illustrated Parts Catal og 28-22,28-26 , and 28-41 Ramp Maintenance M an u a l 

### 28-00 • This Change affects Section1 and Section 2 of the FAA App roved Airplan e F light M anual.

Operators w ill rece ive ap p licable data 

### L. I nte rchangeabi l ity and Intermixabi li ty of Parts Refer to Paragraph 2 . C ., Parts Necessary For Each A irplane , for interchangeabil ity and intermixab i l ity info rmation ,

Fe b ruary 22 . 2006 BOEI N G PROPRIETARY - Copyright 0; UnJ)\Jbll5hed Wo r1<. - See page 1 I Of**delll~S .**  747 -28-22 65 

### 14 of 68

### BOEING SERVICE BULLETIN 747-28 -2265 2. MATERIAL I NFORMATION 

### A. Material· Price and Availability Boeing supplies the kits shown in Paragraph 2 . C., Parts Necessary For Ea ch Airplane. This was negotiated w ith the operator under Master Change 

## Me 0300MK4Q10 . 

### 8 . Industry Support Infannation Boeing I ndustry Support I nformat ion is provided in Master Change 

## Me 03 00MK401D . 

### C. Parts Necessa ry For Each Airplane 1 . Kits/Parts : To get the kits/parts shown below , refer to Paragraph 2A , Material· Price and Availability . N.QIE.;.O ne lop kit and the items shown in Paragraph 2.C.2 ., Parts and Materials Supplied by the Operator, are necessary for each a i rplane. 

### Kit 83480401 QTY New Part 

## . Existing Part Number 

### 1001 Name Number 

### Notes 

### 83490401-1001 

## - FUEL TANK (a) DEACTIVATION - HORIZONTAL STAB ILI ZER 285U0096-6 1 COVER ASSY 

## I 835BOOO4-1 1 P LUG - CONNECTOR FITTING , H ST FUEL TRANSFER LINE 835UOOO1·1 2 MACHINED PARTS DETAILS· PLUG 835UOOO2 - 1 2 MAC HINED PARTS DETAILSPIN AS5168W32 2 PLUG , FLARED I (b) TUBE BAC27EFS595 1 MARKER 

# I BAC27TFDE0013 

### 1 VINYL DECALI I ( IN OP) MS21913W32 

# I 1 I PLUG , I (b) I FLARE LESS

February 22 , 2006 B OE I NG PROPR I ETA RY . Copyn g ht 

### e U npu bli shed Vlb rl<· See page 1 l or d eta ils 

# i

747-28-2265 150f68

### BOE I NG SERVICE BU L LETIN 747-28 -2265 Kit 826B4260 New Part

# ~ Ex i sting 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 t he forward fitting 344U0014 only. 

### 2. Parts and Materia ls Supplied by 

### the Operator: 

# IPart Number I I Spec i f i cat i o n 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 PRO P RIE TA RY - Copyright Q Un pub lish ed Work· See pag e 1 lor details. 747-28-2265 

### 16 of 

### 68

### BOEING SERVICE BULLETIN 747-28-2265 4. Parts Removed and Not Replaced: 

### Existing 

# I Notes Part Number Name QTY 

### 160-72101-1 

### or 60-72102-4 Molor-Impeller Assembly 

### 2 Refer to AMM 28-17-04 (a) I 

### (Boe ing 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 ( I FOC) 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 344 UOO18-5) 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 

# IRefer 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 

# IRefer to 747 AMM 28 - 17 -06 (b) 344U1022-2 Tube Assy 

### 1 

# IRefer to 747 AMM 28-17-06 (b) 344U1022-25 Tube Assy 

### 1 Refer to 747 AMM 28-17-06 (b) 344U1022-26 T u be 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. Specia l 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

BOElN G PROPRIE TARY - Copyright C> Unpublished Well< _ See page 1 tor deta ils. 747-28-2265 170f68

### BOEING SERVICE BULLETIN 747- 28 -2265 F. Sp ecia l Tooli n g Necess ary t o d o thi s Se rvi ce B u ll eti n To gellhe tools shown be l ow , refer to Paragraph 2.E. , Spec ial Too l ing - Price and Availabi l ity. Maintenance and ove rhau l tools in the manua ls shown i n Paragraph 1 .J ., References , can al so be necessary . Exam i ne ope rator loot supply to make sure aU necessary too ls are avai l able . 

### Tool K it Num be r Nam e Shop Supply ESOS Wrist Strap ( 1 required) Shop Supply Jumper Wire (4 required)



### February 22 , 2006 B OE ING PROPRIETARY _ Cepy n ght 1;1 Unpubli shed Work · See Il age 1 fo r d eta il" 

### 747-28-2265 

### 18 of 

### 68

### BOEI NG SERVI C E BUL L ETI N 747 - 28-22 65 3. ACCOM PLISH M E NT I NSTR U CT I O NS 

### A . GEN E RA L IN FO RMATION CAUTIO N : KEEP THE WORK AREA , WIRES A N D ELECTRICAL BUND L ES CLEAN OF METAL 

### PART I CLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANT E D MATERIAL. METAL PARTIC L ES OR CONTAM I NAT I ON CAUGHT I N WIRE BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES . DAMAGED WIRE BUNDL E S CAN CAUS E SPARKS OR OTHER E L ECTRICAL DAMAGE . 

### 1 . Manual t it les are referred to by acronyms . Refer to Paragraph 1 .J ., References , fo r defin ition of the acronyms. 

### 2 . Obey all of the warnings and cautions g iven in the specified manual sect ions . 3. Un less shown differently , these d i mensions and to l erances are used : Linear dimensions are in inches Tolerance on l i near d i mensio n s, other than rivet and bo lt edge margins , is plus or minus 0 . 03 inch. Tolerance on rivet and bolt edge ma rgin i s p l us or m i nus 0 . 05 inch Angular to le rance is plus or minus 2 degrees Ho le d i mens ions for standard solid rivets are g iven i n 747-400F SRM 51 Torque lim its to ti ghten nuts and bolts are g iven in 747-400F SRM 51 4 . 

### For ap proved fastener and p rocess material subst itutions , refer to 747 Stl1Jctu ral Repa i r Man u al, Chapter 51 , 5 . Refer to the SWPM 20 - 10-11 and SWPM 20 - 10 - 12 for the wire i nstallati on procedures . 

### 6 . Refer to the SWPM 20-20-00 the necessary ground i ng procedures . Th i s is the same as BAC5 1 1 7 which i s used on the drawings . 7. If the l ength of fasteners specified in this service bulleti n do not meet the installation standards , fasteners of the same specificat ion , or an approved substitute, one g rip length longe r or shorter may be used . B . 

### W O RK INS T RUCTION S H orizo nt al Stabili ze r Tank P re p ar ati o n 1. Defuel Horizontal Stab i l izer Tank ( HST) per 747 -400 AMM 28 -26-00 . In addition , def uel Main Tanks 2 and 3 sufficiently to allow the Fill/ J etti son Man ifo ld 

### to dra i n . 2. S u mp HST per AMM 12-11 - 1 0 . 

### 3. Open the following circuit breakers and attach DO- N OT-CLOSE tag on t he P7 Overhead Ci rcuit Breaker Pane l: a . 7H25 REFUEL 

### & XFR STAB L. 

### b . 7H26 REFUEL 

### & XFR STAB 

### R. February 22, 2006 S O EI N G PROPRIETARY _ Co py right 

# = Unpublished Wor1l - See page 1 fer details . 

### 747-28-2265 190f68

### BOEING SERVICE BULLETIN 747-28-2265 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 stab i lizer in the neutral trim pos ition (3 un its of trim) as follows : a. Supply electrical power . Refer to the 74 7-400 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 R E VERSERS CAN MOVE QUICKLY WHEN YOU SUPPLY HYDRAULIC POWER . THIS CAN CAUSE I NJURY TO PERSONS AND DAMAGE TO EQUIPMENT. b . Supply hydraul ic power. Refer to the 747-400 AMM 29 - 11-00. c . Use the STAB TRIM ALTN 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 pane l, 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 F LT 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 February 22, 2006 BOEING PROPRIETARY· Copyright Q Un pu tlhsh ed Won.:· See Pilge 1 f or deta il s. 747-28-2265 20 of 68

### BOEING SERVICE BULLETIN 747-28-2265 13. Install the gear door locks . Refer to the 747-400 AMM 32-00-30. 14. Remove hydraulic power. Refe r to the 747-400 AMM 29-11-00. 15. Remove electrical power. Refer to the 747-400 AMM 24-22-00. 

### Horizontal Stabilizer Tank Deactivat i on 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 PANE L 

### (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 L EFT EIU C10174 E2-6 F10 CENTER EIU C10175 E2-6 F15 RIGHT E I U 

## 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 i solation 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 Fi gure 12 . c. Pos ition manual override l ever for affected valves , located on valve actuator, to closed position and LOCKWIRE. Refer to Figure 2 for location. February 22, 2006 BOEING PROPRIETARY· Copyrighl (C Unpublished 'Nor!<.. See p"g e 1 for deL,ils . 747-28-2265 21 of 68

### BOE IN G SERVICE BULLE TIN 74 7-2 8-226 5 6. Change FWD Horizontal Stabilizer Fuel Isolation Valves as follows : a. Locate two isolation valves on rea r spar of center tank , L fwd valve (\1439), R fwd valve (\1440). Refer to Figure 3 for location , b . Disconnect e lectrical connector from valve actuator. Rework wire bundl e W4611 and W4641 

### as refe renced in F igure 12 . C. Position manual ove rride lev er for affected va lves , located on valve actuator, to closed pos ition and lO CKWIR E . Refe r to F igure 3 for locat ion . 7. Modify w i re bundle W0144 on Pressure F ueling Control Pane l P42 as referenced in Figure 12 . Coil and slow wiring for ind icator, switches, a nd l ights . 8 . Insta ll the " H . STA8 TANK DEACT IVATED " placard (marker) above H . STAS indicator, Part Number BAC27EFS595 as given i n AMM 20-11-06-404-012 A L UMINUM FOIL MARKER INSTALLATION. Refer to Figure 4 . 9 . Re move relay R7391 and rewo rk wire bundle W0076 on Center Equ ipm ent Panel P54 as referenced i n Figure 12 . 10 . Modify wire bundl e W4606 on the Horizontal Stabilizer Refue l Valve Control Unit as referenced in F igure 12 . Refer to Figure 2 for component lo cat io n . 11. Remove " HOR STAB XFER/JETI PUMP L" ci rcuit breaker C03141 and " HOR STAB XFERI JETI R " circuit breaker C03142 . Remove H OR STAB XFERIJETI PUMP LEFT and RIGHT placard as shown in Figure 5 . 12. Modify wire bund l e W2018 on AFT MISC Circuit Breaker Pane l P8S as referenced in Figure 12. 13 . Modify wire bundles W4601 and W4602 on Left AFT Equipment Center E8 as referenced in F igu re 12. Cap and stow pump wiring and p lugs S1884 and 51885 as ind icated. 14 . Remove fuel trans fer line and in stall plugs as shown in F igure 1 1. 15. Change Horizonta l 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 . I nsla lil wo p l ug s nd two associated p i ns and do the fo llowi ng :

February 22, 2006 (1) I nstall new packing MS29513 -007 , lubricated with petro latum , i nto groove on p in , part number 83SU0002-1. (2) Put end of pin with packing inlo housing on top of unit. (3) Install new pack in g M25988- 1-238, lubricated w ith petrolatum into groove on plug , part number 835U0001-1. (4) Carefull y push the plug into h ousi ng . Make sure that smallest h ole is in l ine with p in on ho us ing.

SOEING PROPRIETARY _ copyright CI UnpubliShed Wort<· See pall e 1 1<;1'**debl~5 .**  747 -28-2265 22 of 68

### BOEING SERVICE BULLETI N 747- 28-2 2 65 (5) Put the bonding clip{s) with the bonding jumper(s) attached into position on the plug . 

### CA UTI O N : ENSURE SOCKET HEAD MOUNTING SCREWS ARE 

### P I N MS24674-9 OR EQU IVALENT ALTERNAT IVE (TH READ LENGTH 15MM) . QUANTITY (1) 

### WASHER PI N NAS11490N832J MUS T BE USED AT EACH SCREW LOCATI ON . (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 

### th readed end on pin to secure pin i n housing . 16 . M odify the Remote Electron ic Unit (REU) at M7861 i n Equipme nt Cente r EB as shown in Figu re 7 and as follow s: 

### a . Remove the "H.STAB I N D IVIDUAL FUEL QUANTITY CHANNEL ( I FOC) CARD " , part number 60892018-207 in accordance with AMM 28--41 - 17. b . Install the cover p late on the REU , M786 1 and tighten the four captive screws. c. Placard REU**NOP ~.**  d . Modify w i re bun d le W3851 on 

### AFT Left E quipment Center E8 as referenced i n Figu re 12 . 

### 17 . Modify wire bund l e W3890 as referenced i n Figure 1 2 and " reprogram FQIS card file fo r Horizontal Stabilizer absent ". 18 . Change Fue l System Card Fi l e as follows : a . Remove horizontal stabilizer Sing le Point Sensor Contro l Card (SPSC) A3 , in accordance with AMM 28 - 17-10 and Figure 8. b . Install cover assemb ly , part number 285U0096-6 , at SPSC installation location. Refer to Figure 8 . c. M odify wire bund le W4764 by inserting jumper wire in Fuel System Ca rd File as refe re n ced in Figu re 12. d . Modify w i re bundle W4974 on shelf 6 of Main Right Equipment Center E2-6 as referenced i n Figure 

### 12 . 19. Change P5 F uel Management Control Panel as fo ll ows : a. Remove the Fue l Management Control module (M00154) from the P5 panel as referenced in Fi gure 9. b . Modify wire bund les W4751 and W4 753 on Pil ots Overhead Panel P5 as referenced in Figure 12 . 2 0. Deactivate tai l tank at WlU for th e left , center, and righ t Electronic Inst rument Units (E I U) as fo llows:
February 

### 22 , 2006 BOEING PROPR IETARY _ C"pyrighl 

# = Unpubl lsned Work _ See page 1 f() r**ta~s .**  

### 747 -28-2265 23 of 68

### BOEING SERVICE BULLETIN 747-28-2265

a. Modify w i re 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 EQU IPMENT ARE CLEAR OF ALL CONTROL SURFACES BEFOR E YOU SUPP LY HYDRAULIC POVVER. ALERONS , RUDDERS , ELEVATORS , FLAPS , SPO I LERS , LANDING GEAR , AND THRUST REVERSERS CAN MOVE QUICKLY WHEN YOU SUPPLY HYDRAULIC POWER. THIS CAN CAUSE I NJURY TO PERSONS A N D DAMAG E E Q U IPMENT. 22. Supply e lectrical 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 N ON-X valUes shown in steps c , e, and 9 below. The · X· values in the program p i n codes shown below are not pertinent to th i s change and may be any va l ue . a . D isplay the configuration ma i ntenance page on the CMC d isp l ay un it. 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 Capta in 's and First Officer'S source select switches in th e C p ositi on . e. Make sure that the following is d isp layed : 

### IDS PROGRAM PINS : l/XXXX XOXX/32 33/XXXX XX/56 l /P f. 

### Put the Capta i n's and First Officer's source select switches in the R 

### position . g . Make sure that the follow i ng is disp layed : 

### 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 ai rplane must be in the ground mode for this test: a. Open these circuit breakers on the P6 panel : CBND. LOC 

### Nomencl atu re C10123 

### 005 FUEL QTY 1 

### C 1 0124 

### 006 FUEL QTY 2 

### Fe bruary 22, 2006 BOEI N G PRO PRIE TARY -**CopYJJ9 1**  C UnpYbii$M!d Work· See pa ge 1 f or detaUs . 

### 747-28-2265 24 of 68

### BOEING SERVICE BULLETIN 747-28-2265 b. Open these circuit breakers on t he P414 panel : 

### CBND. LOe Nomenclature 

### COOO90 F17 FUELING VALV E 

### C01142 F22 FUELING PWR C10131 

### M33 HOR STAB SUMP DRA IN VLV 

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

# I CB NO 

# ILOC 

# INomenclature 

### COOO86 M08 FUELING VALVE 2 

### C01143 M09 FUELING LTS - HOT 

### d . Open the P42 fuel ing pane l door. e. On the P42 panel , put the battery switch i n 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 indi cator displays read 888.B. The horizontal stabilizer indicator will remain blank. h . Re l ease the GAUGES TEST switch. i. Set the SELECT QTY value to 222.2. 

### J. Press the PRESELECT SET QTY switch to the TOTA L 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 d i splay switch . n. On the lower E ICAS display, see that the fue l quantities are within +/- 200 Ibs (+/- 100 kgs) of the quantities recorded in Step 

### 6 of the Horizontal Stabilizer Tank Preparation Procedure.**~Horiz onta** **l** Stabilizer tank fuel quantity will not be disp layed. o . On the P414 panel, pos ition F22 , open the circuit breaker C01142, FUELING PWR. p. On the P42 pane l , 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 i nd icator quantities are within +/- 200 Ibs (+/-100 kgs) of the quantities recorded in Step 6 of the Horizontal Stabilizer Tank Preparati o n Procedure. February 22, 2006 BOEING PROP RIETAR Y . Copyright**~** Unpublished Worl<· Se e P<'ge 1 '0 ' detai ls . 

### 747-2 8-2265 

### 25 of 68

### BOEING SERVICE BULLETIN 747 -2 8-2265 NQTE ;Horizontal Stab il izer 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 pane l, see that the refue l indicator displays go blank . V. On the P42 pane l , put the battery switch in t h e NORM pos ition . 3 . Do an e lectrical test of the FQIS display , cente r tank fuel control card , and secondary valves and horizontal stabilizer sump drain va lves as fo llows : a . On the rear spa r of the center tank , disconnect connector DV437 from the left secondary refue l valve . b. On the P42 panel , put the CENTER tank valve positio n control switch in the OPEN position . C. On the P414 panel , position F22 , close the circuit breaker C01142 , FUELING PWR . d . On the rear s par 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 th e CLOSED position. See that the Land R valve position l ights come on. f. On the rear s par of the center tank , make su re there is 0-3 VDC on DV437 , between pins 

### A and B. g . On the rear spar of the center tank, d isco nnect the left secondary refuel va lve pressure switch co nnector D S 1877 . On the P42 pan el, see that t he secondary refue l valve L valve posit ion l igh ts goes off. h . On the P42 pane l , re lease the C . TANK SEC . VAL. switch , I. On the P4 2 panel, pul the CENTER tank valve pos ition contro l switch i n the CLOSED position . j. On the P4 2 panel, put the ALL VALVES switch in the OPEN position . k. On the rear spa r ofthe center tank , make sure there is 23-30 VDC on DV437 , between p i ns A and B . I. On the P42 pane l , put the ALL VALVES switch i n the CLOSED pos iti on . m. On th e rear s par of the center tank , make sure there is 0-3 VDC on DV437, between pins A and B . n . On th e P414 panel, position F22 , open th e circuit breaker C01142 , FUEL IN G PWR . o. On the rea r spar of the center tank , connect conn ectors DV437 and D 5 1877 . p . On the rear spar of th e center lank , d isconnect connector DV438 from the right secondary refuel va lve . February 22 , 2006 BOEI N G PROPRIETARY. Copyright d;I UnpubJished Worl<.· See page' l or**eta~s ,**  747 -28-226 5 26 of 68

### BOEING SE RVICE BUL L ET IN 747-2 8-22 65 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 circu it 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 ho ld 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 rea r spar of the center tank, disconnect the right secondary refuel valve pressure switch connector OS1876. On t he 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 DRA I N 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 VA LVE valve power lights come on . ah . On t he P211 panel , push the SUMP DRAIN MA I NT switch to CLOSED position . a i. On the P211 panel , push the SUMP DRAIN CON T switch to the l OPEN pos ition . On the horizontal stabilizer, hear that the left solenoid valve operates . On the P211 panel , see that L VALVE va lve power light comes on . Put the switch back to the normal position .

February 22 , 2006 BOEING PROPRIETARY. CoPyri ll hl**~ Unp~bli** **d** \No.... - See page 1 fo r delnls . 747-28-2265 270f68

### BOEING SERVICE BULLETI N 747-28- 2265 aj . On the P211 panel , push the SUMP DRAIN CONT switch to the R OPEN position. On the horizontal stabilize r , heartha! the right solenoid va lve operates . On the P211 pane l, see that the R VALVE valve powe r l ight comes on . Put the switch back to the normal position. 4 . Do an elect rica l test of the fuel system management cards as follows : a . On the CMC MCDU , go to the I NPUT 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 , pos ition F7. C

. 

### On the P414 panel, position F22 , open the circuit breaker 

### C01142 , FUELING P\I\IR . d. On the P6 panel, close th e circu it b reaker C1 0129, FUEL SYS MG MT CH 1, pos it ion F6, and apen the circu it b reaker C10130, F U E L SYS MG MT C H 2, pos ition F8. e . I n the fuel system ca rd file ( M 7852), on the A2 card , see that the CH 1 green LE D is on and t he 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 C H 1 green LED goes off. On the CMG MCDU see that bit 27 goes from " 1 " to " 0 ' (main tank num ber 2 si ngle point sensor) . This can take up to 1 m i nute to happen . h . In the fue l system card fi le (M7853), on the A2 card , release the B IT switch . i . On the P6 panel, open the ci rcuit breaker C 1 0 1 28 , FUE L SYS MGMT CARD A , position F5 , open the circuit breaker C10130 , FUE L SYS MGMT GH 2 , pos ition F8 , open the circuit breaker C10129, FUEL SYS MGMT CH 1 , position F6 , and open the circuit breaker C10127 , FUEL SYS M GMT CARD B, position F7 . 

### j . On the P 1 80 panel, close the ci rcuit breaker C10136 , FUEL SYS EICAS INT FC CO NT, positio n H17 . k. O n the G Mt MC D U, p ut th is data in for i nput mon itoring: port" E 10', labe l "274" and sd i "00 : See that this data can be see n . 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 1 18 17 

### 16 1 15 14 13 12 11 Status 

### 0 1 1 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 pane l, push the MAIN 1 A FT 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 . February 22 , 2006 BOEING PROPRIETARY _ Copyright IC Unpublished Wof1l - See pag e 1 tor detai ls . 74 7-28-2265 28 of68

### BOEING SERVICE BULLETIN 747-28-2265

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 b il 14 goes from ' 0" to " 1. " This can take up to 1 minute. q. On the PS pane !, push the MAIN 3 AF T 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 t he 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 ." Th i s can take up to 1 minute. 

### t. On the P5 panel, push the MAIN 4 FWD fuel pump switch to ON. See thai b it 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 m i nute . v . On the P5 panel, push the CTR R fue l pump switch to ON. See thai b it 20 goes from "0" to " 1 ." This can take up to 1 minute. w . On the P5 panel , push the OVRD 2 MA I N 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 b it 24 goes from " 0 " to " 1 ." This can take up to 

### 1 m i nute. 

### y. On the P5 pane l, push the OVRD 

### 3 MAIN AFT fue l pump switch to ON. See that b it 25 goes from '0" to "1." T his 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. " Th i s can take up to 1 minute to happen. ab o 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 numbe r 

### 3 tank FUEL 

### X FEED switch to on (flow bar can be seen). See that b it 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 number 4 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 modu l e to off .

February 22, 2006 BO EING PROPRIETARY - Copyright 11:1 Unp u bl ished VVor!< _ Sec pag e 1 for**d~ ta** **~s .**  747-28 -2265 29 of 68

### BOEING SERVICE BULLETIN 747-28-2265 ago On the P6 panel , close the circuit breakers C10128 , FUEL SYS MGMT CARD A , posi ti on F5 , C10 1 27 , FUEL SYS MGMT CARD B, position F7, C10129 , FUEL SYS MGMT CH 1, posi ti on F6 , and C10130, FUEL SYS MGM T 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 t o be fueled . 6. Do the Wing Surge Tank F loat Switch Operationa l 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 . Refe r to the 74 7 -400 AMM 32-00-30 . 

### 9 . Put the ai rplane back into serviceable condition .

February 22 , 2006 B OE I N G P ROPRIETARY - Copy ri ght Itl U np ubli shed**ork~** See JI'Ig e 1 lo r detaUs, 

### 74 7 -28-2265 30 of 

### 68

### BOEING SERVICE BULLETIN 747-28-2265 FIGURE 1: OVERHEAD CIRCUIT BREAKER PANEL**P7 2**  

### CH A NGE

P7-2 PAN E L



# 10**~3** 0) 0) @ 

# I L

____**"' ~~** **C~"~"~~c.~.~ _'c,** **"=7L~~~~ --:** **"** 

# I ", '**~** 

# , I 1 2

, ! , 

# i O 0 0 0 0 0 0 i**--~ --** **~-** 

## ------ ------ - ------'

FIGURE 1 : OVERHE A D C I RCUIT BREAKER PANEL P7-2 CHANGE February 22 , 2006 (SHEET 1 OF 2) BOEING PROPRIETARY - Copyright e UnJ'ubli!<hed Wori< _See p.oge 1 lor**deta ~s,**  

### 747-28-2265 

### 31 of 

### 68

### BOEING SERVICE BULLETIN 747-28-2265 The step numb ers shown below agree with the numbers shown in the circle symbo ls 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 P l ug Button 

### 2654 2 

## -

FIGURE 1 : OVERHEAD CIRCUIT BREAKER PANEL P7·2 CHANGE 

### February 22 , 2006 (SHEET 2 OF 2) BOEING PROPR I ETARY· Copyright C Unpubl iihed Wort< · See pag e t lor d etaU$ . 

### 747-28-2265 32 of 

### 68

### BOEING SERVICE BULLETIN 747-28-2265 FIGURE 2 : H O RIZONTA L STA B I LIZER TAN K AFT FUEL TRANSFER SY STEM LOCATION

REFUEL VALVE CONTROL UN IT

STAB I

### L! Z£R FRONT SPAR 

### (DRY SIDE)

# ~FWD STABILIZER FRO NT SPAR REFUEL VA L VE



### STABILIZER REAR SPAR 

### AFT ISOLATION VALVE ( IN HOR IZONTAL 

### STABILIZER TANK) 

# e:> FVlD (WET SIDE)



### FIGURE 2 : HORIZONTAL STABILIZE R 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 

### 33 of 

### 68

### BOEING SERVICE BULLETIN 747-28-2265

ACTUATO R FOR THE AFT ISOLATI ON VALVE ( LEFT - UPPER)


### VALVE 

### ADAPTER

MANUAL OVERR IDE LEVER (REf) ACTUATOR FOR THE AFT ISOLATION VALVE 

### (R IG HT -LOY.'ER) 

## l-\-\--_ REAR SPAR (REF)

# ~FWD 

# o VALVE ADAPTER



### MANUAL O V

ERR IDE LE V ER (REf)



# · 

# • • M C



### FIGURE 2: HORIZONTAL ST A BILIZER TANK AFT FUEL TRAN S FER SYSTEM LOCATION 

### Febru a ry 22, 2006 (SHEET 2 OF 2) BOEI N G PROPRIETARY _ Copyngh! C Unpubl is hed Worl<.· Sft! palle 1 for deta,s . 

### 747 -28-2265 34 of 

### 68

### BOEING SERVICE BULLETIN 747-28-2265 FIGURE 3: HORIZONT A L STABILIZER TAN K FWD FU E L TRANSFER SYSTEM LOCATION

CENTER W ING TANK 

### COM PONENTS SEE 

# 0

HORIZO NTA L STABILIZER FWD I SOLAT ION VALVES 

# f?S"C;7" SEE 

# 0 )lr""'O!



# o CENTER WING TANK



### FIGURE 3 : HORIZONTAL ST A BILIZER TANK FWD FUEL TRANSFER SYSTEM LOCATION 

### Februa ry 22, 2006 (SHEET 1 OF 2) BOEING PROPRI ETARY - Copyright C U npu l>i shed Worl< _See "",gel I gr**eta ~s** **.** 

### 747-28-2 265 

### 35 of 

### 68

### "D~ 

### BOEING SERVICE BULLETIN 747-28-2265

VALVE ADAPTER REAR SPAR

MANUAL 

### OVERR IDE LEVER

HORIZONTAL STABILIZER ISOLATION V ALV E VALVE 

### ACTUATOR 

# " o



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

### February 22, 2006 (SHEET 2 OF 2) 

### 747-28-226 5 BOEI NG PROPRIETARY _ Copyright**~ Unp~b** **lis hed**  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 . STA B TANK 

### DEACT I VATED

# I/~~**~,** 

# t Ii 4.0 

# I \ 

# (M \ (\**~** 

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# Ii)**I~/ ~/**  )

# RE5E~VE 3 H 

# STAS 

# I DPEN O 

# 2®

;'

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



### FIGURE 4 : LEFT WING REFUELING PANEL P42 MODIFICATION Feb ru ary 22, 2006 (SHEET 1 OF 2) BOEING PROPRIETARY _ Co pyright**~** Unpubl isl>ed Work· SCI! page 1 for deta i ls . 

# - • • 8



### 747 -28-2265 3 7 of 

### 68

### BOEING SERVICE BULLETIN 747-28-2265 The step numbers shown below agree with t h e numbers shown in t h e circl e symbols in t he figure . The QTY numbers shown below are the number of p a rts n ecessary for one airpl a ne. 

## STEP TASK NAME PART NUMBER QTY NOTES 

### 1 Insta ll Marke r BAC2 7EFS595 

### 1 Refer to A M M 20- 1 1-06.

FIGURE 4 : LEFT WING REFUELING PANEL P42 MODIFI CATION 

### February 22 , 2 006 (SHEET 2 OF 2) BOEING PROPRIETARY - Copyriij hl C Unpu bl ,r,hed Work S ee page' 10' detah . 

### 7 4 7 -2 8 -2265 38 of 

### 68

### BOEING SERVICE BULLETIN 747-28-2265 FIGURE 5: H.STAB FUEL PUMP LOW PRESSURE SWITCHES AND 

### PBS PANEL CHANGE

E8 EQUIPMEN T RACK



# r- lAV WATER HTR ---, FC1-FC2 

# ! FC3.f"C. 

# I FC5-FC6 DOQRNQ , S

# ~===:::-~ .- HOR STAB XFER IJETI PUMP n ,"' ,'" I 

# o LEFT ",on , THE BOEI NG CO . PART tW MSE;;; SERIAl NUMBER 

# o 2 

### SEE 

# (0 PBS PANEL



### FIGURE 5: H . STAB FUEL PUMP LOW PRES S URE SWITCHES AND P8S PANEL CHANGE 

### February 22. 2006 (SHEET 1 OF 2) BOE ING PROPRIETARY - Copyright C Unpul>ished Won.. - See Pl'ge 1 f or**deta~s .**  

### 747-28-2 265 

### 39 of 

### 68

### BOEING SERVICE BULLETIN 747 · 28·2265 The step numbe rs shown below agree with the n umbers shown i n t h e circle symbols in the figu re . STEP TASK NAME PART NUMBER QTY NOTES 1 R emove C i rcuit B reakers BA CC 1 8AE 25 2 . 2 R e m ove M a rker BA C27E E L23764 1 Refer to AMM 2 0 -11 -06 . 

### 3 Install Plug Button 2645 2

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

### Fe b ruary 22, 2 006 (SHEET 2 OF 2) BOE IN G PROP RIET AR Y -**Copy~ght** C Un ....**bli~ed** Work - See page 1 for deta il5 . 

### 7 47 -28 -2265 

### 4 0 of 

### 68

### BOEING SERVICE BULLETIN 747-28-2265 FIGURE 6 : HORIZONTA LSTABILIZER TRANSFER PUMP MOTOR IMPELLER ASS Y CHANGE

# FWO~

PUMP HOUS 1 NG '---STAB I L IZ ER FRONT SPAR

TRANSFER ! JEn I SON PUMP 

# o MOTOR J

### MPEllER

FIGURE 6 : HOR IZONTALSTABILIZER TRANSFER PUMP MOTOR IMPELLER ASSY CHANGE Febru ary 22, 2006 (SHEET 1 OF 3) BOEING PROPRIETARY - Copyright C Unpubl ished Wori< - S ee pa ll e 1 fO(**deta~s _**  

### 747-28 · 2265 41 of 

### 68

### BOEING SERVICE BULLETIN 747-28-2265 

# r: HST FRONT I -/SPA R 

# I

PACKING 4 

### TRANSFER/ JEn iSON PUMP HOUS I NG

PIN 

### 2 PLUG PUMP HOUS I NG**~** N UT

# "t;:~ 6 7 WA SHER 

### ELECTRICAL II I BOND SURFACE II BONDING

## [VMOUNT ING BOLT ( AMM 28 - 17-05) (DO NOT RE M OVE) 

## I, I, 

# r--**j** 

# , - WASH ER (S LOCATIONS) I

## ' _ SOCKE T HEAD SCREW AND

# 1 

# [0 

# '8f HST FRONT 

# l U LBONDING JU MPER BUILD-UP SPAR ---...J1 

## I ( DO NOT 0 I SASSE MB LE FROM 

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

## [VELECTRICAL BOND SURFACE 

### 5 P ACKING



# 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 IMPELLE R ASSY CHANGE Fe bruary 22, 2006 (SHEET 2 OF 3) 

### 747-28 -2265 SOEI N G PROPR IE TARY _ Copyrlgnt**~** Unpublilhed Wor\c· S.... page 1 lor delah . 

### 42 of 

### 68

### BOEING SERVI CE BULLE T IN 747 -2 8-22 65 The step numbers shown be l ow agree with the numbers shown in the ci rcle symbols in the figu re . The QTY numbers shown be l ow are the number of parts necessary for one airp lane . 

## STEP TASK NA ME PART N UM BER QTY i NOTES Remove Motor I mpeller 6 0 -72101 - 1 

### or 60- 72102-4 (Boeing 2 

# IRefer to AMM 1 Assembly Part Number 60S92603 · 22 or 28-17-04 . Keep 608926 0 3-26) fasteners to install plug . I nstall P l ug 

### 835UOOO 1 - 1 2 Use kept 2 fasteners, if usable ( 10 l o cat ions) . 3 I nstall Pin 835UOO02- 1 2 

# I 4 Install 

### Packing MS29513-007 2 

# I 5 I nstal! Packing M25988 - 1-238 2 6 I nstall N ut 8AC N 10J C06C 2 Use with pin 7 I nstall Washe r NAS620C6 2 

# IUse with p i n

FIGUR E 6: HORI Z O NTA LS T ABILI Z E R T RA NSFE R PUMP M OT OR I M PE L LE R A SSY C H AN GE February 22 , 2006 (S HEET 3 OF 3) 747 -28-2265 BOEI N G PROPR I ETARY - Co pyri g ht Q**Unpu bli~n** **d** Wor" _ See pa ge 1 for detai l S 

### 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 IVE 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: RE M OTE ELECTRONIC UNIT CHANGES - EB EQUIPMENT RACK February 22 . 2006 

### (SHEET 1 

### OF 2) BOEING PROPRIETARY _ Copyrigh t 

### e Unpub l Ish e d Worl< _ See page 1 for detai ls 747-28-2265 

### 4 4of68

### BOE I NG SERVICE BULLETIN 747-28-2265 The step numbers shown below agree with the numbern shown i n the circle symbols in the figure . The QTY numbers shown below are the number of parts necessary for one airp l ane . STEP TASK NAME PART NUMBER QTY 

### N OTES 1 Remove lFQC Card 608920 1 8-204 1 Refer to AMM 28-17-10 2 Reinstall COlie r Plate 

## - 

# - 3 Install li ND? Decal BAC27TFDEOO13 1 Refer to AMM 20-11-16

FI G URE 7 : REMOTE ELE CTRONI C UNIT CHANGE S - E8 EQUIPMENT RACK Feb ruary 22 , 2006 (SHEET 2 OF 2) BOEING PROPRIETARY _ Copyright e Unpubli5hed Work . See pag e 1 for deta'5 . 

### 747-28-2265 450f6S

### BOEING SERV I CE BULLETIN 747-28-2265 FIGURE 8 : FUEL SYSTEM CARD FILE CHANGE

FUE L SYSTEM CARD FILE

A3

### FY/o~



### UP 

# {J FWO tt'

Th e step numbers shown below ag ree with the numbers shown in the circle symbol s in the figure. The Q1Y numbers show n be low are the numbe r of parts n ecessary for one a i rpl ane. STEP TASK NAME PART NUMBER QTY 

### 1 Remove S ingle Point Sensor Card S344TQ02-B 

### 1 (S P SC) 

### 2 I nstall Cove r Assembly 

### 285UOO96-6 

### 1 N otes: (a) Install per drawing 284U 1255 , sheet 1, Rev. C, Zone : 812 .

February 22, 2006 FIGURE 8 : FUEL SYSTEM CA RD FILE CHANGE (SHEET 1 OF 11 NOTES Remove Per A M M 

### 28-17- 1 0. (a) 

### • " 

### • • 8

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

### 747-28-2265 46 of 

### 68

### 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.; show n in the circle symbols in the figure. The OTY numbers shown below are the numbe r of parts necessary fo r one ai rpl a n e . 

### STEP TASK Remove 

### 1

February 22, 2006 NAME PART NUMBER 

### QTY NOTES Fuel Man agement 

### 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 Unpublish ed Work _SII!e page 1 for**t.a ~s** **,** 

### 747-28 -2265 47 of 

### 68

### 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 deta b. 

### 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 

## - - DEL ETE QG0584 I RD DQ 2625 C0 7 GDYOO 02 22 0 

## - - DEL ETE QG0591 RD DQ2645 C07 GDYOO04 22 0 

## - 

# - ADD QG1002 RD DQ262 7 813 GDXOO02 13 7 . 3 

## - - ADD QG10 03 RD OQ266 7 813 GDXOO 06 28 10.8 

## - - ADD QG1004 RD OQ2647 813 GDXOO 04 28 10.8 

## - - C hang e th e wire wrap wires i n the sequence shown in thi s table . I nstall the wire along the routing shown an the subsequent pages . Refer to Boeing Standard Wiring Practices Manua I20-72-1B . LEGEND FOR DETAILS 1-6 (a) DELETE Delete this wire from the wire i ntegration unit (W IU ) . ADD Add t his wire to the w i re integration unit (W1 U ) 

### (b) Wire number is shown for reference on ly ; th e number is not printed on wire wrap wires. (e) RD Cut from w i re 82989006-1 4 . This wire i s BM S 1 3-46 , Type 3 , Class 1 , AWG 26 (d ) Th e length of wire is i n inch es . Use th ese length s as aids on ly. C u t th e w i re to th e correct len gth du rin g the i nstallat ion. ( e) N o n e 

### (Q Sleeve Code : N one**e** 

### changes in this figure 

### are from Wire Kit 6268426 0

FIGURE 10 : DEACTIVATION OF TAIL TANK AT LEFT, CENTER , AND RIGHT EIU· E2-6 WIU WIRE CHANGE Feb rua ry 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 747-2 8 -2265



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### DELETE QOO584-2S 

### RD 002625 C07 GOV2 22

DETA I L 1 N.QIE.;.Reference : Wiring Diagram 31-61-12.

FI G URE 10 : DEA CT IVA T I ON OF TAIL TAN K AT LEFT, C ENTER , AND RI G H T EIU - E2 - S WI U WI R E CHANGE February 22, 2006 (SHEET 3 OF 101 SOE IN G PROPRIETARY - Copyright C U n publjsl1ed Work - See pa ge 1**ordela~' ,**  

### 7 47 -28 -2265 50 of 

### 68ACTI ON W IRE ND. -GAGE ADD Q(3 1OO2·26

DETAIL 2 

### BOEING SERVICE BULLETIN 747-28 - 2265

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### LENGTH (It«:HES) 7 .3**~Re fe** **ence :**  

### Wiring Di ag ra m 31-61 - 12 NO TE S

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 deUl b. 

### 747 -2 8-22 65 51 of 

### 68

### BOE IN G SERVI CE B U LL ETIN 747-28 -2265



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FIGURE 1 0 : DE A CTiVATION OF TAI L T ANK AT LE FT, C E NT ER , AND RIGH T E I U - E2 -6 WIU W IRE 

### C HA N GE 

### February 22 , 2006 (SHEE T 5 O F 10) BOEING PROPRIETARY _ CopyriQht C**Unpublj5~ed** Wor1< - See pag e 1 l or details . 

### 747-28-2265 52 of 68

### BOEI N G SE RV IC E BUL L ET I N 747-28 -22 65



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### RD 002647 8 13 GDX4 28 10.8



### DE TA I L.**~R eference** **:** 

### Wiring Dia g ram 31-62-32 . NOTES

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### FIGURE 10 : DEAC T IVATION O F T A IL TANK AT LEFT, C E NTER , AND R I GHT EIU - E2-6 W I U WIRE 

### CHANG E Feb ru ary 22, 2006 (S H EET 6 OF 10) BOEING PRO PRIETARY - Cc pyn;hI**~** Unpublished Work· See**pag~** 1 for**d"ta~s ,**  

### 747-28-2 265 

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### BOEING SERVICE BULLETIN 747-28-2265



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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 Feb ruary 22, 2006 (SHEET 7 OF 10) BOEING PROPRIETARY _ Copyright C Unpu b!i5hed WIlli< - SEe page 1 fer detai ls . 

### 747-28-2265 54 of 

### 68ACTION WIRE NO .- GAGE 

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### BOEING SERVICE BULLETIN 747-28-2265

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### Wiring Diag ram 31-61-22 . NOTES

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

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# l "c7 ! I"" " W i ryyrJ QG058 4-26 111///11. GDYOO02-22

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## W4260 C7 QG059, -2 6 

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### FIGURE 1 0 : DEACTIV ATION OF TAIL TANK AT LEFT, CENTER , AND RIGHT EIU - E 2-6 WIU WIRE CHANGE 

### February 22 , 2006 (SHEET 9 O F 10) 

### 74 7 -2 8-2265 BOEI N G PROPRIETARY - Copyright C lJnpubljshed Work· See page 1 for**de\4l ~I.**  

### 56 of68

### BOEING SERVICE BULLETIN 747-28-2265

AR0426

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### 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 FO R E XI S TING PARTS R EMOVA L SEE 

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SEE A FOR EXISTING P ARTS REMOVA L SEE 

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### FIGURE 11 : REWORK OF HORIZONTAL STABILIZER TANK TRANSFER LINE February 22, 2006 (SHEET 1 OF 8) BOEI N G PROPR I ETARY _ Copy nllht C UnputJIi$hl!d W or!<. - See pa ll" 1 10.**dl!ta~ .**  

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### 747 -2 8-2265 58of6S

### BOEING SERVICE BULLETIN 747-28-2265

UN I ON

## ~h.**--.;>;:-; ~~~"[~**  O-R ING " TOP OF THE CENTER WING TANK



### FIGURE 11 : REWORK OF HORIZONT A L STABILIZER TAN K TRANSFER LINE 

### Feb ruary 22 , 2006 (SHEET 2 OF 8) BOEING PRO PRIETARY - Copyngh! e Unpublis h e d Work - See page 1 lor detaits 

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### 59 of 

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HOR I ZONT AL**'-~** STABILIZER FITT I NG**,-~SHROUD** (FLEX I BLE HOSE)



### ____'-/ / FUEL HOSE 

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### BULKHEAD STA 2598

FIGURE 

### 11 : REWORK OF HORIZONTAL STABILIZER TANK TRANSFER LINE 

### Feb ru ary 22 , 2006 (SHEET 3 OF 8) BOEING PROPRIETARY - CopYrl9hl CI Unpub!ilohed Work - See page 1 for dela's . 

### 74 7-2 8-2265 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 PROPRIE TARY· Copyright I:;l Unpublished IIIobrk _ See page 1 fer detai ls . 

### 747-28-2265 61 of 

### 68

### BOEING SERVICE BULLETIN 747-28-2265

11

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### FIGURE 

### 11 : REWORK OF HORIZONTAL STABILIZER TANK TRANSFER LINE 

### February 22 , 2006 (SHEET 5 OF 8 ) BO EI NG PR OPR I ETARY _ Copyright C Unpubl ished Wtlrk _ S...e page 1 for**deLa l~** **.** 

### 74 7 -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 i n 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 ident ified part , assembly o r installation . 

### STEP TASK NAME IDENTIFICATION QTY 

### REMOVAL REMOVAL PIC INSTALL 

### MORE INSTALL DRAWING SHT REF DATA PIN REF REF REF 1 Remove H ose Assy 

### 1 0-60536-25 (opt 

### 1 344U1022 

### 344U1022 1 (a ) 

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### 344UOOOO-6 1 344U1022 

### 344U1022 1 (a) 

### ·24 Remove Tube Assy 

### 344U 1022-1 0 

### 1 344U1 022 344 U1022 1 (a ) 

### ·24 Remove T ube Assy 344 U1022-11 

### 1 344U1022 344U1022 1 (a)



### · 24 Remove T ube Assy 

### 344U1022-12 

### 1 344U1022 344U1022 

### 1 (a) 

### ·24 Remove Tube Assy 

### 344U1022-13 1 344 U 1022 344U1022 

### 1 (a) 

### ·24 Remove Tube A ssy 344U1022· 1 4 

### 1 344U1022 344U1022 

### 1 (a) 

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### 344U1022·2 1 344U1022 344 U10 22 

### 1 (a) 

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### 344U1022·22 1 344U1022 344U1022 

### 1 (a)



### · 24 Remov e Shroud 344U1022·23 

### 1 344U1022 

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### · 24 Remov e Tube Assy 344U1022·25 

### 1 344U 1 022 344U 1 022 

### 1 (a)



### · 24 Remove Tube Assy 344 U102 2·26 

### 1 344U1022 344U1022 

### 1 (a) 

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### ·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) BO EING PROP RIETARY . Ccpyright C Unpubli shl! d Werle · See page 1 for deta i l ,_ 

### 747 · 28·2265 

### 630f68

### BOEING SE RVICE BULLETI N 747-28-2265 

## STEP TAS K N AME I D E N TIFI CATIO N QTY R EMOVAL REM OVAL 

## PI C IN STALL MORE 

### INSTALL DRAWING 

## SHT REF DATA PIN REF 

## REF REF 1 Remove Spacer 69892447-52 1 

### 344U1022 344 U1022 (allb) -24 Remove Space r 69892447-8 1 344U1022 344U1022 1 (allb) -24 Remove C lamp, AN735D 4 8 20 

### 344U1022 34 4 U1022 1 (a) Loop -24 Remove Coup l i n g AS1712D48 11 344U1022 34 4 U1022 1 (a) -24 Remove Bolt BACB30 N M3HK7 6 344U1022 

### 344U1022 3 (a)

-24 Remove Clamp , U - BACC10CC48 3 344U1022 344U1022 1, 2, (a) style -24 3 Remove C lamp BACC10CC48S 1 344 U1 022 344U 1 Q22 (allb)

-24 Remove C lamp, U- BACC10 EW48A 60 344U1022 344U1022 2 (a) style -2 4 Remove Clamp, U- BACC10EW488 60 344U 1 022 344U 1 022 2 (a) style -24 Remove Bond i ng BACJ 4 0A20-3 2 344U1022 

### 344U1022 2 (a) Jumpe r -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 Sh i m, 

### BACS40ROOB E 048F 1 

### 344U1022 

### 344 U1022 1 (a) Laminated -24 Remove Pin MS 24665-144 4 344U1022 344U1022 1, 2 Cal -24 Remove O-ring MS29513-23 4 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 344U 1 022 344U1022 1,2 , (a) -24 3 Remove a - ring NAS1523AA3R 6 344U1022 344U1022 3 (a) -24 2 Remove Fitt i ng 344UOOOO-2 1 344U 1 022 344U1022 1 (a) a-ri ng MS29513-24 1 1 -24

F I GURE 11 : REWO RK O F H O RI Z ONTA L STABILI Z E R TANK TRA N S F ER LINE Feb ruary 22, 2006 (SHEET 7 O F 8 ) BOEING PRO P RIETARY _ Copyrig ht C Unpublished Work · S ee paS" 1 fordetail s 747-28-2265 64 of 68

### BOEI N G S ERVICE BULLETIN 747-28-226 5 STEP TASK NAM E I D EN T IFICA T ION QTY RE M OVA L REMOVA L P IC I NS T A L L MOR E I NS T ALL D RAW IN G SH T REF DATA 

### PIN REF RE F R E F 3 Remove Union 

### AP7102D32 ·1 (opt 1 344U1022 

### 344U1022 1 (a) AFP720D3232 

### or -2 4 

### AP71 02032 

### o r MS21900D32 ) 

### O - ring MS29512-32 1 4 Install Plug AS5 1 68W32 (Opt 1 834B0401 ( c) MS21913W32) 

### -1 001 O-ring MS29512-32 1 5 Install Plug 83580004-1 1 83480401 (c) O-ring MS29513-24 1 1 

### - 1 001 Lockwi re MS20995NC32 1 6 Remove Tube Assy 344U0018-8 (opt 1 

### 344U1022 344U1022 1 (a) 344UOO18-5) -24 H ose Assy 

### 10-60536-23 1 

### 7 I nsta ll P l ug AS5168W32 1 83480401 (d ) 

### O - ri ng 

### MS2 9S 1 2-32 1 

### ·1001 8 I nstall Cap BACC14AD06D 1 83480401 (e) 

### -1001 NOTE

(a) Refer to 747-400 AMM 28-17-06 for additional i nfo rmation . (b) Quantity used varies . (c) on 344UD014-1 fitt i ng . (d) on 

### 13218 adapter. (e) on MS219 12D6tee .

F IG U RE 11 : REWORK OF HORIZONTAL STA BILI ZER T ANK TRANSF E R LI N E 

### February 22 , 2006 (S HEET 8 O F 8) BOE I NG PROPR IETAR Y . Co pyri g"t e**U~publish d**  WJtI< _ See p ag e 1 t or d eta'l. 

### 747 -28-2265 65 of 68

### BOEING SERVICE BULLETIN 747 -28-2265 FI GU R E 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 fo r all reworked wi re b un d les. Refer to 747.400 Wi ri ng Diagram Manual - WirelEquipment Li st for additional information . See Wire 

### Kil828B6101 and 82886102 

### IDENTIFICATI ON INSTALL REF WIRE DIAGRAM 82680007-1 

### 62886102·100 1 28-21-26 82680076-1 

### 62886102-100 1 28-21-23 82680144-1 

### 82866102-100 1 28-21-24 

### 826 6 2018-1 82886 1 02 - 100 1 

### 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 : REW O RK OF WIRE BUNDLES (SHEET 1 OF 3) BOEING PROPRIETARY _ Copyright C UnpubliShed Work -**~** page liar dela b . 

### 747-28-2265 66 of68

### BOEING SERV I CE BULLETIN 747-28-2265 WIRE BUNDLE I DENTIFI CATION I N STALL REF WIRE DIAGRAM W3851 

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Feb ruary 22, 2006 

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### 82896102-100 1 128-21-21 82683942-1 82886102 - 1 001 

### 28-21-29 82693944 - 1 82896 1 02-1001 28-21-29 82694092-1 182896102- 1 001 24-54-1 3 82684094 - 1 82886102 - 1001 24-54-23 82684260- 1 

### 82886102- 1 001 28-21-29,31-61-12, 

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### 82896102 - 1 0 0 1 28 -2 1 -29 8268 4263-1 

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### 82896102 - 1 00 1 28 -21-23 826944 1 5 -1 82886102- 1 001 28 -2 1-23 

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### 28-2 1- 12 8268444 1 - 1 82886102 - 1001 

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### 82896102 - 1001 28-21 - 13 82684478 -1 82886102-1001 

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### 82896102 - 1001 28-43- 12 82684768- 1 82886102-1001 28-21-29 FIGURE 

### 12 : R EWOR K OF WIRE BUNDLES (SHEET 2 OF 3) BO E I NG PROPR I ETARY -**~n ht**  C Unp ublis h ed Wor!<. - S ee pag e 1 lor deta ils. 

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### BOEING SERVICE BULLETIN 747-28-2265 WIRE BUNDLE IDENTIFICATION INSTALL REF WIRE DIAGRAM 

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February 22, 2006 82684774-1 82886102- 1 001 

### 28-21-29 82684974 - 1 82886102 - 1 00 1 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 d etails . 

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