### Commercial **Airplanes** 

# 747 Service Bulletin **ALERT Number: 747-54A2238**  Original Issue: January 31, 2014 ATA System: 5451 **SUBJECT:** NACELLES/PYLONS - Nacelle Strut Attach Pin - Outboard Struts Aft Upper Spar Fuse Pin Replacement Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 300-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws. 9E991 ECCN: 

## BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET Copyright © 2014 Boeing. Unpublished Work. All Rights Reserved. Treatment of this document and its content is governed by contract with Boeing. Rights to use this document are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The Boeing Company. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and Boeing liveries 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.

Original Issue: January 31, 2014 747-54A2238 1 of 56 3.0Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 2 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT**

BLANK PAGE**Table of Contents** Summary...................................................... 5 1. PLANNING INFORMATION ........................................ 9 A. Effectivity................................................ 9 1. Airplanes............................................. 9 2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 2. Data Supplied with this Service Bulletin:. . . . . . . . . . . . . . . . . . . . . . . . . . . 13 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 13 K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 14 M. Software Accomplishment Summary. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 C. Parts Necessary for Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 1. Kits/Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 16 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 4. Parts Removed and Not Replaced. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 18 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 FIGURE 1: STRUT NO. 1 - ACCESS COVER ASSEMBLY REMOVAL. . . . . . . . . . . . . . . . . 23 FIGURE 2: STRUT NO. 4 - ACCESS COVER ASSEMBLY REMOVAL. . . . . . . . . . . . . . . . . 25 FIGURE 3: STRUT NO. 1 - OUTBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT . . 27 FIGURE 4: STRUT NO. 1 - INBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT. . . . 35 FIGURE 5: STRUT NO. 4 - INBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT. . . . 40 FIGURE 6: STRUT NO. 4 - OUTBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT . . 48 FIGURE 7: STRUT NO. 1 - ACCESS COVER ASSEMBLY INSTALLATION. . . . . . . . . . . . . . 53 FIGURE 8: STRUT NO. 4 - ACCESS COVER ASSEMBLY INSTALLATION. . . . . . . . . . . . . . 55

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 3 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 4 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT**

BLANK PAGE

### Commercial **Airplanes** 

# 747 Service Bulletin **ALERT Summary**  **Number: 747-54A2238** Original Issue: January 31, 2014 ATA System: 5451 **SUBJECT:** NACELLES/PYLONS - Nacelle Strut Attach Pin - Outboard Struts Aft Upper Spar Fuse Pin Replacement THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. **CONCURRENT REQUIREMENTS** None. **BACKGROUND** Accomplishment of this service bulletin will prevent outboard migration of the outboard aft upper spar strut-to-wing attachment fuse pins on struts No. 1 and No. 4 that could result in the complete disconnect and loss of the outboard aft upper spar strut-to-wing attachment load path. The complete loss of the No. 1 or No. 4 outboard aft upper spar strut-to-wing attachment load path could result in divergent flutter in certain parts of the flight envelope, which can result in loss of control of the airplane. Boeing analysis determined that the existing outboard aft upper spar strut-to-wing attachment fuse pins on struts No. 1 and No. 4 are susceptible to migration in the event of a failed fuse pin through bolt. To prevent the outboard aft upper spar strut-to-wing attachment fuse pins migrating outboard, the outboard aft upper spar strut-to-wing attachment fuse pin design was changed to add a flange. The outboard fuse pin access cover assemblies were changed to add interference ribs to only allow the fuse pin to be installed with the flanged end of the fuse pin on the inboard side of the outboard aft upper spar fitting. To prevent incorrect installation of the outboard aft upper spar strut-to-wing attachment fuse pins, the inboard aft upper spar strut-to-wing attachment fuse pin incorporated the same flanged fuse pin design. This service bulletin provides instructions to replace the outboard aft upper spar strut-to-wing attachment fuse pins and access covers on struts No. 1 and No. 4 with the new flanged fuse pins and ribbed access cover assemblies. Installation of the new flanged fuse pins at the outboard aft upper spar strut-to-wing attachment will prevent outboard migration of the fuse pins and possible loss of the outboard aft upper spar strut-to-wing attach load path. Installation of the new ribbed fuse pin access cover assembly will prevent incorrect installation of the outboard aft upper spar strut-to-wing attachment fuse pins. This service bulletin also provides instructions to replace the inboard aft upper spar strut-to-wing attachment fuse pins on struts No. 1 and No. 4 with the new flanged fuse pins. Installation of the new flanged fuse pins at the inboard aft upper spar strut-to-wing attachment will prevent incorrect installation of the non-flanged fuse pins at the outboard and inboard aft upper spar strut-to-wing attachment.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 5 of 56Boeing Service Related Problem (SRP) 747-8-SRP-51-0016 is related to this service bulletin. This table is provided to operators for planning purposes only. Refer to the applicable sections for more information.
**Reference Affected**  **Planning Data** Paragraph 1.A.2., Spares Affected No Spares Affected Paragraph 1.E., Compliance and Paragraph 1.F., Approval Yes AD Related Paragraph 1.H., Weight and Balance Changes Yes Weight and Balance Change Paragraph 1.I., Electrical Load Data No Electrical Load Changed Paragraph 1.K., Publications Affected Yes Publications Affected Paragraph 1.K., Publications Affected No Airplane Flight Operations Affected (Flight CrewOperations Manual and/or FAA Approved Airplane Flight Manual) Paragraph 2.C.1., Kits/Parts Yes Kits/Parts Required Paragraph 2.C.2., Parts and Materials Supplied by the Operator Yes Operator Supplied Parts/Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin Yes Special Tooling Required

**ACTION (PRR 86601-4)** Get access to the Aft Upper Spar Fuse Pins and remove Access Cover Assemblies. Depressurize hydraulic system. Remove Air Drive Units and replace Fuse Pins. Install Air Drive Units and pressurize hydraulic system. Install new Access Cover Assemblies and close access to the Aft Upper Spar Fuse Pins. **EFFECTIVITY** 747-8 and 747-8F Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s). **COMPLIANCE** The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Boeing recommends that the change given in this service bulletin be done within 48 months after the Original Issue date of this service bulletin. **INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are available for airplanes in warranty as of July 25, 2012. Please refer to Paragraph 2.B., Industry Support Information. The warranty remedies will expire eight years from the original issue date of this service bulletin.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 6 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT MANPOWER**  Refer to Paragraph 1.G., Manpower. **MATERIAL INFORMATION** Boeing Supplied Kits/Parts. Refer to Paragraph 2.A., Material - Price and Availability.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 7 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 8 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT**

### Commercial **Airplanes** 

# 747 Service Bulletin **ALERT Number: 747-54A2238**  Original Issue: January 31, 2014 ATA System: 5451 **SUBJECT:** NACELLES/PYLONS - Nacelle Strut Attach Pin - Outboard Struts Aft Upper Spar Fuse Pin Replacement THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. **1. PLANNING INFORMATION A. Effectivity**  1. Airplanes This service bulletin is for the airplane(s) shown below. An equivalent change is on subsequent production airplanes. Refer to PRR 86601-4 for data about this change. Refer to Service Bulletin Index D6-30300 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. **NOTE:** Variable numbers for airplanes scheduled to be delivered more than a year after the Original Issue date of this service bulletin are not listed in the table below. MyBoeingFleet (MBF) will show current listing of the affected airplanes. **NOTE:** This service bulletin is for the airplanes shown in the effectivity list below. The effectivity list includes all affected airplanes scheduled to be delivered before DEC 02, 2014. In addition, at least one airplane scheduled to be delivered after DEC 02, 2014 is affected by this service bulletin and is in Group(s) 1 as described in the Group Configuration table. Affected airplanes will be added to the service bulletin's MyBoeingFleet.com (MBF) "get effectivity" result when they are added to the MBF Fleet Profile Page.
**DESCRIPTION CONFIGURATION**  **GROUP** 747-8 and 747-8F Airplanes line number 1420 through 1434, 1436 through 1491 - 1

Airplane Models: 747-8, 747-8F

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 9 of 56**Group Variable Number**  1 RC001 - RC008 1 RC022 - RC030 1 RC501 - RC511 1 RC521 - RC528 1 RC541 1 RC546 - RC549 1 RC551 - RC563 1 RC571 - RC572 1 RC574 - RC582 1 RC601 - RC605 2. Spares Affected None. **B. Concurrent Requirements** None. **C. Reason** Accomplishment of this service bulletin will prevent outboard migration of the outboard aft upper spar strut-to-wing attachment fuse pins on struts No. 1 and No. 4 that could result in the complete disconnect and loss of the outboard aft upper spar strut-to-wing attachment load path. The complete loss of the No. 1 or No. 4 outboard aft upper spar strut-to-wing attachment load path could result in divergent flutter in certain parts of the flight envelope, which can result in loss of control of the airplane. Boeing analysis determined that the existing outboard aft upper spar strut-to-wing attachment fuse pins on struts No. 1 and No. 4 are susceptible to migration in the event of a failed fuse pin through bolt. To prevent the outboard aft upper spar strut-to-wing attachment fuse pins migrating outboard, the outboard aft upper spar strut-to-wing attachment fuse pin design was changed to add a flange. The outboard fuse pin access cover assemblies were changed to add interference ribs to only allow the fuse pin to be installed with the flanged end of the fuse pin on the inboard side of the outboard aft upper spar fitting. To prevent incorrect installation of the outboard aft upper spar strut-to-wing attachment fuse pins, the inboard aft upper spar strut-to-wing attachment fuse pin incorporated the same flanged fuse pin design. This service bulletin provides instructions to replace the outboard aft upper spar strut-to-wing attachment fuse pins and access covers on struts No. 1 and No. 4 with the new flanged fuse pins and ribbed access cover assemblies. Installation of the new flanged fuse pins at the outboard aft upper spar strut-to-wing attachment will prevent outboard migration of the fuse pins and possible loss of the outboard aft upper spar strut-to-wing attach load path. Installation of the new ribbed fuse pin access cover assembly will prevent incorrect installation of the outboard aft upper spar strut-to-wing attachment fuse pins.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 10 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT**This service bulletin also provides instructions to replace the inboard aft upper spar strut-to-wing attachment fuse pins on struts No. 1 and No. 4 with the new flanged fuse pins. Installation of the new flanged fuse pins at the inboard aft upper spar strut-to-wing attachment will prevent incorrect installation of the non-flanged fuse pins at the outboard and inboard aft upper spar strut-to-wing attachment. Boeing Service Related Problem (SRP) 747-8-SRP-51-0016 is related to this service bulletin. **D. Description** Get access to the Aft Upper Spar Fuse Pins and remove Access Cover Assemblies. Depressurize hydraulic system. Remove Air Drive Units and replace Fuse Pins. Install Air Drive Units and pressurize hydraulic system. Install new Access Cover Assemblies and close access to the Aft Upper Spar Fuse Pins. The work in this service bulletin is done in the maintenance zone(s) given below.
**Affected Maintenance Zones Zone**  **Model** 451, 452, 481, 482 747-8, 747-8F **E. Compliance** The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Boeing recommends that the change given in this service bulletin be done within 48 months after the Original Issue date of 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 regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin. **G. Manpower** The table below shows an estimate of the task hours necessary to do this replacement for each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator task hour data if necessary. The estimate does not include lost time. These are some examples of lost time: • Time to adjust to the workplace • Time to schedule the work

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 11 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT**• Time to inspect the work • Time to cure the materials • Time to make the parts • Time to find the tools. **Elapsed Hours**  **Task Hours Number of**  **Persons Task** 

3.25 13.00 4 Open Access Remove Access Panels 1.00 1.00 1 ...FIGURE 1: Strut No. 1 1.00 1.00 1 ...FIGURE 2: Strut No. 4 0.15 0.15 1 Depressurize hydraulic system 4.50 18.00 4 Remove Air Drive Unit Replace Fuse Pins 4.00 8.00 2 ...FIGURE 3: Strut No. 1, Outboard Side 2.75 5.50 2 ...FIGURE 4: Strut No. 1, Inboard Side 2.75 5.50 2 ...FIGURE 5: Strut No. 4, Inboard Side 4.00 8.00 2 ...FIGURE 6: Strut No. 4, Outboard Side 4.50 18.00 4 Install Air Drive Unit 0.15 0.15 1 Pressurize hydraulic system Install Access Panels 1.00 1.00 1 ...FIGURE 7: Strut No. 1 1.00 1.00 1 ...FIGURE 8: Strut No. 4 3.25 13.00 4 Close Access 1.00 4.00 4 Test 34.30 97.30 TOTAL FOR EACH AIRPLANE **H. Weight and Balance Changes Change in Moment**  **(Pound-Inches) Change in Weight**  **(Pounds) Airplane**  +8320.9 lb.-in. +5.2 lb. All
**I. Electrical Load Data** Not changed.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 12 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT J. References**  1. Existing Data: a. Engineering Change Memo PRR 86601-4 b. Boeing Service Related Problem (SRP) 747-8-SRP-51-0016 c. Service Bulletin Index D6-30300 d. Standard Overhaul Practices Manual (SOPM) 20-41-02, 20-50-00, 20-50-01, 20-50-01, 20-50-02, 20-50-07, 20-60-03 e. 747-8 Aircraft Maintenance Manual (AMM) 27-81-00, 29-11-00, 29-11-08, 54-51-02, 54-62-04, 71-11-04 2. Data Supplied with this Service Bulletin: a. Drawings:
**ADCN DCN/REV**  **Sheet Title**  **Drawing No**

- - 1 747 Hydraulic Bracket Trim Tool MIT321U8047

- - 2

- - 3

- - - 747 Hydraulic Bracket Trim Tool MIT321U8047_- 3. Installation Drawings Used in the Preparation of this Service Bulletin:
**Title Drawing Number**  REWORK - BRACKET INSTL, TRAS, HYD, FUEL 321U8046 The table above lists applicable drawings used to prepare this service bulletin. The drawings are not necessary to make the specified changes, and are not supplied with this service bulletin. The drawings may not be applicable to all airplane configurations or operators. **K. Publications Affected** 1. Publications: **Chapter-Section Publication**  54-51 747 Aircraft Maintenance Manual 54-51 747 Illustrated Parts Catalog 54-00 Component Maintenance Manual 1. Damage Tolerance Based Structural Inspections:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 13 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT**Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This service bulletin affects FCS but no new DTIs are necessary. **L. Interchangeability and Intermixability of Parts** Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts. **M. Software Accomplishment Summary** Not affected.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 14 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT 2. MATERIAL INFORMATION**  **A. Material - Price and Availability** Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin. The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. Prices are in United States Dollars. Terms: Net 30 days. Reference this service bulletin and submit your purchase order by one of these methods: 1. Order on-line via ATA Spec 2000 or The Boeing PART Page 2. Fax to (206) 662-7145 **REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION** 
**Unit Price as of the Original Issue** 

**date of this Ser vice Bulletin (US**  **Dollars) ROLT as of the**  **Original Issue date of this Ser** **vice Bulletin (Cal endar Days)**  **QTY Date**  **Name Kit Number** 

$31,036.00 578 2 December 13, 2013 TOP KIT - OUTBOARD STRUT R3 FUSE PIN AND ACCESS DOOR - REPLACEMENT 015U1954-1

10 January 24, 2014 18 February 27, 2014 **B. Industry Support Information** Boeing warranty remedies are available for 747 airplanes in warranty as of July 25, 2012. For task hour reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing Warranty & Product Assurance Contracts. The kits for airplanes in warranty as of that date will be supplied at no charge. Send a purchase order for the kits to Boeing Material Management. Please refer to this service bulletin number and reference the airplane variable numbers in your purchase order. The warranty remedies will expire eight years from the original issue date of this service bulletin. **C. Parts Necessary for Each Airplane** 1. Kits/Parts To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability. **NOTE:** One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane. The Top Kit is divided into Figure kits for each installation figure shown in the table below.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 15 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT Figure Kit**  **8 7**  **6 5**  **4 3**  **Top Kit** 1 1 1 1 1 1 015U1954-1
**ALL**
**KIT 015U1954-1**

**Notes Existing Part**  **Number Name**  **Figure**

**New Part Number 8**  **7 6**  **5 4**  **3 Qty**  (a) (b) (c) 311U8092-2 FUSE PIN - AFTUPPER SPAR NACELLE STRUT . . 1 1 1 1 311U8092-3

(a) (b) (c) 311U8098-9 THROUGH BOLT - AFT UPPER SPAR NACELLE STRUT . . 1 1 1 1 311U8098-10

(a) (b) (c) 323U8215-3 ACCESS COVER ASSY, OUTBD SIDE, LH OUTBD ENGINE . 1

. . . . 323U8215-5

(a) (b) (c) 323U8215-4 ACCESS COVER ASSY, OUTBD SIDE, RH OUTBD ENGINE 1

. . . . . 323U8215-6

(d) BOLT 15 15

. . . . BACB30NN4K11 (BACB30NN4K11G optional) SELF-LOCKING NUT . . 1 1 1 1 BACN10HR14CS

NUT

. . 1 1 1 1 BACN11N114CS PIN

. . 1 1 1 1 BACP18BC04A14P (a) Discard the existing part. Keep the existing part if there are other uses for it. (b) This part is used in production. (c) You cannot use the existing part to replace the new or changed part. (d) There are more parts than are necessary. 2. Parts and Materials Supplied by the Operator The following parts or materials are necessary to do the change in this service bulletin. Parts and materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine operator part and material supply to make sure all necessary parts and materials are available.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 16 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT Notes**  **Name QTY**  **Part Number / Specification**  (a) PRIMER 8 ounces BMS 10-11, TYPE 1 (a) (e) GREASE 1 quart AEROSHELL GREASE 33MS (a) HYDRAULIC FLUID 8 ounces BMS 3-11(MCS0352 optional) (a) GREASE 1 quart BMS 3-33, TYPE I (b) ANTI-SEIZE THREAD COMPOUND 8 ounces - (c) CABLE ASSEMBLY, SAFETY 4 BACC13AT4K18 (d) MARKING LACQUER 2 ounces - (a) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. (b) Refer to SOPM 20-60-03 for a list of applicable anti-seize thread compounds. (c) Part is used when installing Side Link Assembly. (d) F-925, Skydrol Resistant Torque Seal, Organic Products Company, PO Box 560625, Dallas, TX 75356-0625 (MSDS41617). (e) Aeroshell Grease 33MS is qualified to MIL-G-21164.
3. Parts Modified and Reidentified None. 4. Parts Removed and Not Replaced None. **D. Parts Necessary to Change Spares** None. **E. Special Tooling - Price and Availability** Boeing can supply the tool(s) shown in Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin. Operators are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin. The tool(s) are subject to the terms and conditions of the Boeing standard purchase order acknowledgement. Prices are in United States Dollars. Terms: Net 30 days. Reference this service bulletin number and submit your purchase order by one of these methods: 1. Order on-line via ATA Spec 2000 or Boeing Part Page

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 17 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT**2. Fax to (206) 662-7145 **REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT)**  **AND PRICE INFORMATION**
**Purchase Data: Unit Price as of**  **the Original Issue date of this Ser**  **vice Bulletin (US Dollars)**  **Name Tool Kit Number** 

$53,760.00 747 Hydraulic Bracket Trim Tool MIT321U8047 Boeing can supply the tool(s) shown in Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin. Operators are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin by e-mail to ServiceBulletinRentalLoanTools@boeing.com. The tool(s) are subject to the terms and conditions of the Boeing standard purchase order acknowledgement. Prices are in United States dollars. Terms: Net 30 days. Reference this service bulletin and submit your purchase order by one of these methods: 1. Order on-line via ATA Spec 2000 or Boeing Part Page 2. Fax to (425) 965-8237 **Rental Data: Daily Price as of**  **the Original Issue date of this ser**  **vice bulletin (US Dollars)**  **Name Tool Kit Number** 

$360.00 747 Hydraulic Bracket Trim Tool MIT321U8047 **F. Special Tooling Necessary to do this Service Bulletin** To get the 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 tool supply to make sure all necessary tools are available.
**Name Tool Kit Number**  747 Hydraulic Bracket Trim Tool MIT321U8047

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 18 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT 3. ACCOMPLISHMENT INSTRUCTIONS**  **A. GENERAL INFORMATION CAUTION:**  KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE. **NOTE:** 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 2. Obey all of the warnings and cautions given in the specified manual sections. 3. 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 and fasteners are in Structural Repair Manual (SRM) Chapter 51 – Torque Values: — Values for structural fasteners are given in 747-8F or 747-8P Structural Repair Manual, Chapter 51. — Values for airframe maintenance tasks are included in Chapter 20 of 747-8 Airplane Maintenance Manual (AMM). — Values for electrical maintenance tasks are included in Chapter 20 of Standard Wiring Practices Manual (SWPM). — Values for engine maintenance tasks are included in Chapter 70 of 747-8 Airplane Maintenance Manual (AMM). — Non-standard torque values for maintenance tasks are included in the applicable installation step.
4. Use the approved fastener and process material substitutions in accordance with SRM Chapter 51. 5. If the length of any fastener specified in this service bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. Refer to SOPM 20-50-01 for alternate full threaded fasteners (screws) needed for installation in this service bulletin. 6. These work instructions refer to procedures included in other Boeing documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "in accordance with" are included in the instruction, the procedure in the Boeing document must be used.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 19 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT**7. The instructions in Paragraph 3.B., Work Instructions and the figures can include operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing Index contain data on versions of the tools or test equipment that you can use. It is permitted to use replaced tools. It is not permitted to use superseded tools. 8. If it is necessary to remove more parts for access, you can remove those parts. If you can get access without removing identified parts, it is not necessary to remove all of the identified parts. Jacking and shoring limitations must be observed. 9. Where the work instructions include installation of a kept part, a new or serviceable part with the same part number can be installed as an alternative to the kept part. 10. If shading is used, shaded areas in Figures are to separate the non-critical and non-authoritative information from the critical and authoritative information. 11. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS are in Paragraph 1.E., Compliance. 12. Some steps in the Work Instructions are identified as Required for Compliance (RC). If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps identified as RC must be done to comply with the AD. Alternative procedures for steps not identified with RC can be used if the RC steps can still be done as specified, and the airplane can be put back in a serviceable condition. An Alternative Method of Compliance (AMOC) is not necessary for deviations to steps that are not identified as RC. **B. WORK INSTRUCTIONS** 1. Retract leading edge flaps and install leading edge flap drive unit lock. Refer to 747-8 AMM 27-81-00 as an accepted procedure. 2. Remove and keep Forward Fairing Access Panels shown below from Strut No. 1 and No. 4. Refer to 747-8 AMM 54-62-04 as an accepted procedure.
**No. 4 Engine Strut No. 1 Engine Strut** **Forward Fairing Ac cess Panel No.**  481AT 451AT 1 481BT 451BT 2 481DL and 481DR 451DL and 451DR 3 481EL and 481ER 451EL and 451ER 4 3. Remove and keep Fan Cowl Panels from Engine No. 1 and No. 4. Refer to 747-8 AMM 71-11-04 as an accepted procedure. 4. Prepare for the removal of the Strut No. 1 and No. 4 Aft Upper Spar Fuse Pins. Refer to 747-8 AMM 54-51-02, Prepare for the Removal (Engine Removed) or 747-8 AMM 54-51-02, Prepare for Removal (Engine Supported) as accepted procedures. 5. Remove Access Cover Assemblies in accordance with the figures below.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 20 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT Figure**  **Engine Strut** FIGURE 1 Strut No. 1 FIGURE 2 Strut No. 4 6. Depressurize the hydraulic system. Refer to 747-8 AMM 29-11-00 as an accepted procedure. 7. Remove Air Drive Unit (ADU) on Strut No. 1 and No. 4. Refer to 747-8 AMM 29-11-08 as an accepted procedure. 8. RC - Replace Aft Upper Spar Fuse Pins in accordance with the figures below. **Figure Engine Strut Location**  FIGURE 3 Strut No. 1, Outboard Side FIGURE 4 Strut No. 1, Inboard Side FIGURE 5 Strut No. 4, Inboard Side FIGURE 6 Strut No. 4, Outboard Side 9. Install and test ADU on Strut No. 1 and No. 4. Refer to 747-8 AMM 29-11-08 as an accepted procedure. 10. Pressurize the hydraulic system. Refer to 747-8 AMM 29-11-00 as an accepted procedure. 11. RC - Install Access Cover Assemblies in accordance with the figures below **Figure Engine Strut**  FIGURE 7 Strut No. 1 FIGURE 8 Strut No. 4 12. Restore access to the Strut No. 1 and No. 4 Aft Upper Spar Fuse Pins. Refer to 747-8 AMM 54-51-02, Restore the Airplane to Normal (Engine Removed) or 747-8 AMM 54-51-02, Restore the Airplane to Normal (Engine Supported) as accepted procedures. 13. Install kept Fan Cowl Panels from Strut No. 1 and No. 4. Refer to 747-8 AMM 71-11-04 as an accepted procedure. 14. Install kept Forward Fairing Access Panels shown below on to Strut No. 1 and No. 4. Refer to 747-8 AMM 54-62-04 as an accepted procedure.
**No. 4 Engine Strut No. 1 Engine Strut** **Forward Fairing Ac cess Panel No.**  481AT 451AT 1 481BT 451BT 2 481DL and 481DR 451DL and 451DR 3 481EL and 481ER 451EL and 451ER 4

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 21 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT**15. Remove safety locks from leading edge flaps. Refer to 747-8 AMM 27-81-00 as an accepted procedure. 16. Put the airplane back to a serviceable condition.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 22 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT FIGURE 1: STRUT NO. 1 - ACCESS COVER ASSEMBLY REMOVAL**  **(SHEET 1 OF 2)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 23 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT**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 engine strut.
**More Data Qty**  **Identification Name**  **Task Step**  (a) 13

- BOLT Remove / Keep 1 1 323U8215-3 ACCESS COVER AS- SY, OUTBD SIDE, LH OUTBD ENGINE Remove

(a) 11

- BOLT Remove / Keep 2 1 323U8225-3 ACCESS COVER AS- SY, INBD SIDE, LH OUTBD ENGINE Remove / Keep

(a) Make note of Bolt location for Access Cover Assembly installation.

**FIGURE 1: STRUT NO. 1 - ACCESS COVER ASSEMBLY REMOVAL (SHEET 2 OF 2)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 24 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT FIGURE 2: STRUT NO. 4 - ACCESS COVER ASSEMBLY REMOVAL**  **(SHEET 1 OF 2)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 25 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT**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 engine strut.
**More Data Qty**  **Identification Name**  **Task Step**  (a) 13

- BOLT Remove / Keep 1 1 323U8215-4 ACCESS COVER AS- SY, OUTBD SIDE, RH OUTBD ENGINE Remove

(a) 11

- BOLT Remove / Keep 2 1 323U8225-4 ACCESS COVER AS- SY, INBD SIDE, RH OUTBD ENGINE Remove / Keep

(a) Make note of Bolt location for Access Cover Assembly installation.

**FIGURE 2: STRUT NO. 4 - ACCESS COVER ASSEMBLY REMOVAL (SHEET 2 OF 2)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 26 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT FIGURE 3: STRUT NO. 1 - OUTBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT**  **(SHEET 1 OF 8)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 27 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT FIGURE 3: STRUT NO. 1 - OUTBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT**  **(SHEET 2 OF 8)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 28 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT FIGURE 3: STRUT NO. 1 - OUTBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT**  **(SHEET 3 OF 8)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 29 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT FIGURE 3: STRUT NO. 1 - OUTBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT**  **(SHEET 4 OF 8)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 30 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT**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 engine strut outboard side.
**More Data Qty**  **Identification Name**  **Task Step**  and attach fuse pins. Refer to 747-8 AMM54-51-02 as an accepted procedure. 2 321U8740-1 SIDE LINK ASSEMBLY Remove / Keep 1

1

- CABLE ASSEMBLY, SAFETY Remove
and fasteners. 1

- CLAMPBLOCK - HY-DRAULIC TUBE SUPPRT BRACKET Remove / Keep 2

and lift hydraulic tube to provideclearance for installation of new fuse pin. 1

- HYDRAULIC TUBE Disconnect 3

by loosening or removing clamp screws, as required, to move the conduit. Keep all clamp screws, if removed. - - CONDUIT Move 4

Refer to 747-8 AMM54-51-02 as an accepted procedure. 1

- PIN Remove 5

1

- NUT Remove 1

- SELF-LOCKING NUT Remove 1 311U8098-9 THROUGH BOLT - AFT UPPER SPAR NACELLE STRUT Remove

Refer to 747-8 AMM54-51-02 as an accepted procedure. 2 311U8095-9 END CAP - AFT UP- PER SPAR NACELLE STRUT Remove / Keep 6

**FIGURE 3: STRUT NO. 1 - OUTBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT (SHEET 5 OF 8)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 31 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT More Data**  **Qty Identification**  **Name Task**  **Step** to provide clearance for new fuse pin. Refer to toolMIT321U8047 instructions. 1 321U8047-40 BRACKET ASSY Machine 7

two coats to bare metal areas. Refer to SOPM 20-41-02as an accepted procedure. - BMS 10-11, TYPE 1 PRIMER Apply

Refer to toolMIT321U8047 instructions. 1

- FUSE PIN - AFT UP- PER SPAR NACELLE STRUT Remove 8

with the flanged end on the inboard side. Apply thin film of Aeroshell Grease33MS to outer diameter of the fuse pin. Fuse pin may need to be rotated up to 40 degrees in order to clear Side Link lug. Refer to SOPM20-50-07 as an accepted procedure. 1 311U8092-3 FUSE PIN - AFT UP- PER SPAR NACELLE STRUT Install (New)

After installation, inject grease into grease fitting until grease appears at other side of the joint. Refer to SOPM20-50-07 as accepted procedure. - AEROSHELL GREASE 33MS GREASE Apply

One End Cap is installed on the Through Bolt head side and one End Cap is installed on the Through Bolt thread side. 2 311U8095-9 END CAP - AFT UP- PER SPAR NACELLE STRUT Install (Kept) 9

**FIGURE 3: STRUT NO. 1 - OUTBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT (SHEET 6 OF 8)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 32 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT More Data**  **Qty Identification**  **Name Task**  **Step** with bolt head facing the outboard side. (a) 1 311U8098-10 THROUGH BOLT - AFT UPPER SPAR NACELLE STRUT Install (New) 10

(a) (c) 1 BACN10HR14CS SELF-LOCKING NUT Install (New) Apply a torque stripeto End Cap and SelfLocking Nut on inboard side. Refer to Paragraph 2.C.2., Parts and MaterialsSupplied by the Operator for acceptable material. - - MARKING LACQUER Apply 11

Tighten Nut 70 to 750 inch-pounds. Replace Nut if Nut cannot be tighten between 70 to 750inch-pounds. Increase torque, to align with Pin hole in Through Bolt, to notexceed 1500 inchpounds. (a) 1 BACN11N114CS NUT Install (New) 12

(b) (d) 1 BACP18BC04A14P PIN Install (New) back to previous position. Install clamp screws, if removed. - - CONDUIT Move 13

1

- HYDRAULIC TUBE Connect 14 to seal surface ofsleeve before seating B-nut, to external fitting threads, and to shoulder of sleeve. Torque B-nutto 855 to 945 inchpounds. Refer to SOPM 20-50-00 asan accepted procedure. - BMS 3-11 (MCS-352 optional) HYDRAULIC FLUID Apply

**FIGURE 3: STRUT NO. 1 - OUTBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT (SHEET 7 OF 8)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 33 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT More Data**  **Qty Identification**  **Name Task**  **Step** and fasteners. Torque nut to 3.5 to 30.0 inch-pounds. Refer to SOPM 20-50-01 as an accepted procedure. 1

- CLAMPBLOCK - HY-DRAULIC TUBE SUPPRT BRACKET Install (Kept) 15

and attach fuse pins. Torque nuts on through bolts to1500 to 2500 inchpounds. Ensure that all parts are firmly seated. Refer to 747-8 AMM 54-51- 02 as an accepted procedure. 2 321U8740-1 SIDE LINK ASSEMBLY Install (Kept) 16

Refer to SOPM 20-50-02 as an accepted procedure. 1 BACC13AT4K18 CABLE ASSEMBLY, SAFETY Install (New)

(a) Apply anti-seize thread compound to threads before installation. Refer to SOPM 20-50-07 and SOPM 20- 60-03 as accepted procedures. (b) If Pin can not be installed, then back off the Nut minimum amount to align pin hole in Through Bolt. (c) To install Self-Locking Nut, use the following procedure. Tighten until the Self-Locking Nut is fully engaged. Tighten Self-Locking Nut to run-on torque of 70 to 600 inch-pounds. The torque wrench must be installed on the Self-Locking Nut and not the head of the Through Bolt. Replace Self-Locking Nut if Self-Locking Nut cannot be tighten to run-on torque range. Tighten Self-Locking Nut to 2800 to 3200 inch-pounds. Do a check to make sure that the torque vale is correct. (d) Make sure to check that the Through Bolt, End Caps, Self Locking Nut, Nut, and Pin are installed correctly. Make sure that the joint is not clamped.

**FIGURE 3: STRUT NO. 1 - OUTBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT (SHEET 8 OF 8)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 34 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT FIGURE 4: STRUT NO. 1 - INBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT**  **(SHEET 1 OF 5)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 35 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT**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 engine strut inboard side.
**More Data Qty**  **Identification Name**  **Task Step**  and attach fuse pins. Refer to 747-8 AMM54-51-02 as an accepted procedure. 2 321U8740-1 SIDE LINK ASSEMBLY Remove / Keep 1

1

- CABLE ASSEMBLY, SAFETY Remove

**FIGURE 4: STRUT NO. 1 - INBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT (SHEET 2 OF 5)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 36 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT More Data**  **Qty Identification**  **Name Task**  **Step** Refer to 747-8 AMM54-51-02 as an accepted procedure. 1

- PIN Remove 2

1

- NUT Remove 1

- SELF-LOCKING NUT Remove 1 311U8098-9 THROUGH BOLT - AFT UPPER SPAR NACELLE STRUT Remove

Refer to 747-8 AMM54-51-02 as an accepted procedure. 2 311U8095-9 END CAP - AFT UP- PER SPAR NACELLE STRUT Remove / Keep 3

Refer to toolMIT321U8047 instructions. 1

- FUSE PIN - AFT UP- PER SPAR NACELLE STRUT Remove 4

with the flanged end on the outboard side. Apply thin film of Aeroshell Grease33MS to outer diameter of the fuse pin. Fuse pin may need to be rotated up to 40 degrees in order to clear Side Link lug. Refer to SOPM20-50-07 as an accepted procedure. 1 311U8092-3 FUSE PIN - AFT UP- PER SPAR NACELLE STRUT Install (New)

After installation, inject grease into grease fitting until grease appears at other side of the joint. Refer to SOPM20-50-07 as accepted procedure. - AEROSHELL GREASE 33MS GREASE Apply

One End Cap is installed on the Through Bolt head side and one End Cap is installed on the Through Bolt thread side. 2 311U8095-9 END CAP - AFT UP- PER SPAR NACELLE STRUT Install (Kept) 5

**FIGURE 4: STRUT NO. 1 - INBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT (SHEET 3 OF 5)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 37 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT More Data**  **Qty Identification**  **Name Task**  **Step** with bolt head facing the inboard side. (a) 1 311U8098-10 THROUGH BOLT - AFT UPPER SPAR NACELLE STRUT Install (New) 6

(a) (c) 1 BACN10HR14CS SELF-LOCKING NUT Install (New) Apply a torque stripeto End Cap and SelfLocking Nut on outboard side. Refer to Paragraph 2.C.2., Parts and MaterialsSupplied by the Operator for acceptable material. - - MARKING LACQUER Apply 7

Tighten Nut 70 to 750 inch-pounds. Replace Nut if Nut cannot be tighten between 70 to 750inch-pounds. Increase torque, to align with Pin hole in Through Bolt, to notexceed 1500 inchpounds. (a) 1 BACN11N114CS NUT Install (New) 8

(b) (d) 1 BACP18BC04A14P PIN Install (New) and attach fuse pins. Torque nuts on through bolts to1500 to 2500 inchpounds. Ensure that all parts are firmly seated. Refer to 747-8 AMM 54-51- 02 as an accepted procedure. 2 321U8740-1 SIDE LINK ASSEMBLY Install (Kept) 9

Refer to SOPM 20-50-02 as an accepted procedure. 1 BACC13AT4K18 CABLE ASSEMBLY, SAFETY Install (New)

(a) Apply anti-seize thread compound to threads before installation. Refer to SOPM 20-50-07 and SOPM 20- 60-03 as accepted procedures. (b) If Pin can not be installed, then back off the Nut minimum amount to align pin hole in Through Bolt.

**FIGURE 4: STRUT NO. 1 - INBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT (SHEET 4 OF 5)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 38 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT More Data**  **Qty Identification**  **Name Task**  **Step** (c) To install Self-Locking Nut, use the following procedure. Tighten until the Self-Locking Nut is fully engaged. Tighten Self-Locking Nut to run-on torque of 70 to 600 inch-pounds. The torque wrench must be installed on the Self-Locking Nut and not the head of the Through Bolt. Replace Self-Locking Nut if Self-Locking Nut cannot be tighten to run-on torque range. Tighten Self-Locking Nut to 2800 to 3200 inch-pounds. Do a check to make sure that the torque vale is correct. (d) Make sure to check that the Through Bolt, End Caps, Self Locking Nut, Nut, and Pin are installed correctly. Make sure that the joint is not clamped.

**FIGURE 4: STRUT NO. 1 - INBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT (SHEET 5 OF 5)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 39 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT FIGURE 5: STRUT NO. 4 - INBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT**  **(SHEET 1 OF 8)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 40 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT FIGURE 5: STRUT NO. 4 - INBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT**  **(SHEET 2 OF 8)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 41 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT FIGURE 5: STRUT NO. 4 - INBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT**  **(SHEET 3 OF 8)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 42 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT FIGURE 5: STRUT NO. 4 - INBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT**  **(SHEET 4 OF 8)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 43 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT**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 engine strut outboard side.
**More Data Qty**  **Identification Name**  **Task Step**  and attach fuse pins. Refer to 747-8 AMM54-51-02 as an accepted procedure. 2 321U8740-1 SIDE LINK ASSEMBLY Remove / Keep 1

1

- CABLE ASSEMBLY, SAFETY Remove
and fasteners. 1

- CLAMPBLOCK - HY-DRAULIC TUBE SUPPRT BRACKET Remove / Keep 2

and lift hydraulic tube to provideclearance for installation of new fuse pin. 1

- HYDRAULIC TUBE Disconnect 3

by loosening or removing clamp screws, as required, to move the conduit. Keep all clamp screws, if removed. - - CONDUIT Move 4

Refer to 747-8 AMM54-51-02 as an accepted procedure. 1

- PIN Remove 5

1

- NUT Remove 1

- SELF-LOCKING NUT Remove 1 311U8098-9 THROUGH BOLT - AFT UPPER SPAR NACELLE STRUT Remove

One End Cap is installed on the Through Bolt head side and one End Cap is installed on the Through Bold thread side. 2 311U8095-9 END CAP - AFT UP- PER SPAR NACELLE STRUT Remove / Keep 6

**FIGURE 5: STRUT NO. 4 - INBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT (SHEET 5 OF 8)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 44 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT More Data**  **Qty Identification**  **Name Task**  **Step** to provide clearance for new fuse pin. Refer to toolMIT321U8047 instructions. 1 321U8047-40 BRACKET ASSY Machine 7

two coats to bare metal areas. Refer to SOPM 20-41-02as an accepted procedure. - BMS 10-11, TYPE 1 PRIMER Apply

Refer to toolMIT321U8047 instructions. 1

- FUSE PIN - AFT UP- PER SPAR NACELLE STRUT Remove 8

with the flanged end on the outboard side. Apply thin film of Aeroshell Grease33MS to outer diameter of the fuse pin. Fuse pin may need to be rotated up to 40 degrees in order to clear Side Link lug. Refer to SOPM20-50-07 as an accepted procedure. 1 311U8092-3 FUSE PIN - AFT UP- PER SPAR NACELLE STRUT Install (New)

After installation, inject grease into grease fitting until grease appears at other side of the joint. Refer to SOPM20-50-07 as an accepted procedure. - AEROSHELL GREASE 33MS GREASE Apply

One End Cap is installed on the Through Bolt head side and one End Cap is installed on the Through Bolt thread side. 2 311U8095-9 END CAP - AFT UP- PER SPAR NACELLE STRUT Install (Kept) 9

**FIGURE 5: STRUT NO. 4 - INBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT (SHEET 6 OF 8)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 45 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT More Data**  **Qty Identification**  **Name Task**  **Step** with bolt head facing the inboard side. (a) 1 311U8098-10 THROUGH BOLT - AFT UPPER SPAR NACELLE STRUT Install (New) 10

(a) (c) 1 BACN10HR14CS SELF-LOCKING NUT Install (New) Apply a torque stripeto End Cap and SelfLocking Nut on outboard side. Refer to Paragraph 2.C.2., Parts and MaterialsSupplied by the Operator for acceptable material. - - MARKING LACQUER Apply 11

Tighten Nut 70 to 750 inch-pounds. Replace Nut if Nut cannot be tighten between 70 to 750inch-pounds. Increase torque, to align with Pin hole in Through Bolt, to notexceed 1500 inchpounds. (a) 1 BACN11N114CS NUT Install (New) 12

(b) (d) 1 BACP18BC04A14P PIN Install (New) back to previous position. Install clamp screws, if removed. - - CONDUIT Move 13

1

- HYDRAULIC TUBE Connect 14 to seal surface ofsleeve before seating B-nut, to external fitting threads, and to shoulder of sleeve. Torque B-nutto 855 to 945 inchpounds. Refer to SOPM 20-50-00 asan accepted procedure. - BMS 3-11 (MCS-352 optional) HYDRAULIC FLUID Apply

**FIGURE 5: STRUT NO. 4 - INBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT (SHEET 7 OF 8)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 46 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT More Data**  **Qty Identification**  **Name Task**  **Step** and fasteners. Torque nut to 3.5 to 30.0 inch-pounds. Refer to SOPM 20-50-01 as an accepted procedure. 1

- CLAMPBLOCK - HY-DRAULIC TUBE SUPPRT BRACKET Install (Kept) 15

and attach fuse pins. Torque nuts on through bolts to1500 to 2500 inchpounds. Ensure that all parts are firmly seated. Refer to 747-8 AMM 54-51- 02 as an accepted procedure. 2 321U8740-1 SIDE LINK ASSEMBLY Install (Kept) 16

Refer to SOPM 20-50-02 as an accepted procedure. 1 BACC13AT4K18 CABLE ASSEMBLY, SAFETY Install (New)

(a) Apply anti-seize thread compound to threads before installation. Refer to SOPM 20-50-07 and SOPM 20- 60-03 as accepted procedures. (b) If Pin can not be installed, then back off the Nut a minimum amount to align pin hole in Through Bolt. (c) To install Self-Locking Nut, use the following procedure. Tighten until the Self-Locking Nut is fully engaged. Tighten Self-Locking Nut to run-on torque of 70 to 600 inch-pounds. The torque wrench must be installed on the Self-Locking Nut and not the head of the Through Bolt. Replace Self-Locking Nut if Self-Locking Nut cannot be tighten to run-on torque range. Tighten Self-Locking Nut to 2800 to 3200 inch-pounds. Do a check to make sure that the torque vale is correct. (d) Make sure to check that the Through Bolt, End Caps, Self Locking Nut, Nut, and Pin are installed correctly. Make sure that the joint is not clamped.

**FIGURE 5: STRUT NO. 4 - INBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT (SHEET 8 OF 8)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 47 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT FIGURE 6: STRUT NO. 4 - OUTBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT**  **(SHEET 1 OF 5)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 48 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT**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 engine strut inboard side.
**More Data Qty**  **Identification Name**  **Task Step**  and attach fuse pins. Refer to 747-8 AMM54-51-02 as an accepted procedure. 2 321U8740-1 SIDE LINK ASSEMBLY Remove / Keep 1

1

- CABLE ASSEMBLY, SAFETY Remove

**FIGURE 6: STRUT NO. 4 - OUTBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT (SHEET 2 OF 5)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 49 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT More Data**  **Qty Identification**  **Name Task**  **Step** Refer to 747-8 AMM54-51-02 as an accepted procedure. 1

- PIN Remove 2

1

- NUT Remove 1

- SELF-LOCKING NUT Remove 1 311U8098-9 THROUGH BOLT - AFT UPPER SPAR NACELLE STRUT Remove

2 311U8095-9 END CAP - AFT UP- PER SPAR NACELLE STRUT Remove / Keep 3

Refer to toolMIT321U8047 instructions. 1

- FUSE PIN - AFT UP- PER SPAR NACELLE STRUT Remove 4

with the flanged end on the inboard side. Apply thin film of Aeroshell Grease33MS to outer diameter of the fuse pin. Fuse pin may need to be rotated up to 40 degrees in order to clear Side Link lug. Refer to SOPM20-50-07 as an accepted procedure. 1 311U8092-3 FUSE PIN - AFT UP- PER SPAR NACELLE STRUT Install (New)

After installation, inject grease into grease fitting until grease appears at other side of the joint. Refer to SOPM20-50-07 as an accepted procedure. - AEROSHELL GREASE 33MS GREASE Apply

One End Cap is installed on the Through Bolt head side and one End Cap is installed on the Through Bolt thread side. 2 311U8095-9 END CAP - AFT UP- PER SPAR NACELLE STRUT Install (Kept) 5

**FIGURE 6: STRUT NO. 4 - OUTBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT (SHEET 3 OF 5)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 50 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT More Data**  **Qty Identification**  **Name Task**  **Step** with bolt head facing the outboard side. (a) 1 311U8098-10 THROUGH BOLT - AFT UPPER SPAR NACELLE STRUT Install (New) 6

(a) (c) 1 BACN10HR14CS SELF-LOCKING NUT Install (New) Apply a torque stripeto End Cap and SelfLocking Nut on inboard side. Refer to Paragraph 2.C.2., Parts and MaterialsSupplied by the Operator for acceptable material. - - MARKING LACQUER Apply 7

Tighten Nut 70 to 750 inch-pounds. Replace Nut if Nut cannot be tighten between 70 to 750inch-pounds. Increase torque, to align with Pin hole in Through Bolt, to notexceed 1500 inchpounds. (a) 1 BACN11N114CS NUT Install (New) 8

(b) (d) 1 BACP18BC04A14P PIN Install (New) and attach fuse pins. Torque nuts on through bolts to1500 to 2500 inchpounds. Ensure that all parts are firmly seated. Refer to 747-8 AMM 54-51- 02 as an accepted procedure. 2 321U8740-1 SIDE LINK ASSEMBLY Install (Kept) 9

Refer to SOPM 20-50-02 as an accepted procedure. 1 BACC13AT4K18 CABLE ASSEMBLY, SAFETY Install (New)

(a) Apply anti-seize thread compound to threads before installation. Refer to SOPM 20-50-07 and SOPM 20- 60-03 as accepted procedures. (b) If Pin can not be installed, then back off the Nut minimum amount to align pin hole in Through Bolt.

**FIGURE 6: STRUT NO. 4 - OUTBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT (SHEET 4 OF 5)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 51 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT More Data**  **Qty Identification**  **Name Task**  **Step** (c) To install Self-Locking Nut, use the following procedure. Tighten until the Self-Locking Nut is fully engaged. Tighten Self-Locking Nut to run-on torque of 70 to 600 inch-pounds. The torque wrench must be installed on the Self-Locking Nut and not the head of the Through Bolt. Replace Self-Locking Nut if Self-Locking Nut cannot be tighten to run-on torque range. Tighten Self-Locking Nut to 2800 to 3200 inch-pounds. Do a check to make sure that the torque vale is correct. (d) Make sure to check that the Through Bolt, End Caps, Self Locking Nut, Nut, and Pin are installed correctly. Make sure that the joint is not clamped.

**FIGURE 6: STRUT NO. 4 - OUTBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT (SHEET 5 OF 5)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 52 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT FIGURE 7: STRUT NO. 1 - ACCESS COVER ASSEMBLY INSTALLATION**  **(SHEET 1 OF 2)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 53 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT**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 engine strut.
**More Data Qty**  **Identification Name**  **Task Step**  1 323U8215-5 ACCESS COVER AS- SY, OUTBD SIDE, LH OUTBD ENGINE Install (New) 1

with BMS 3-33, Type 1 grease on bolt shank. Torque to 60 to 80 inch-pounds. 13

- BOLT Install (Kept)

1 323U8225-3 ACCESS COVER AS- SY, INBD SIDE, LH OUTBD ENGINE Install (Kept) 2

with BMS 3-33, Type I grease on bolt shank. Torque to 60 to 80 inch-pounds. 11

- BOLT Install (Kept)

The parts shown in the table below are provided as extra parts for this figure.
**More Data Qty**  **Identification Name**  These parts are not required forinstalling Access Cover Assemblies. These parts can be used to replace kept parts if grip length meets installation requirements. 15 BACB30NN4K11(BACB30NN4K11G optional) BOLT

**FIGURE 7: STRUT NO. 1 - ACCESS COVER ASSEMBLY INSTALLATION (SHEET 2 OF 2)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 54 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT FIGURE 8: STRUT NO. 4 - ACCESS COVER ASSEMBLY INSTALLATION**  **(SHEET 1 OF 2)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 55 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT**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 engine strut.
**More Data Qty**  **Identification Name**  **Task Step**  1 323U8215-6 ACCESS COVER AS- SY, OUTBD SIDE, RH OUTBD ENGINE Install (New) 1

with BMS 3-33, Type 1 grease on bolt shank. Torque to 60 to 80 inch-pounds. 13

- BOLT Install (Kept)

1 323U8225-4 ACCESS COVER AS- SY, INBD SIDE, RH OUTBD ENGINE Install (Kept) 2

with BMS 3-33, Type I grease on bolt shank. Torque to 60 to 80 inch-pounds. 11

- BOLT Install (Kept)

The parts shown in the table below are provided as extra parts for this figure.
**More Data Qty**  **Identification Name**  These parts are not required forinstalling Access Cover Assemblies. These parts can be used to replace kept parts if grip length meets installation requirements. 15 BACB30NN4K11(BACB30NN4K11G optional) BOLT

**FIGURE 8: STRUT NO. 4 - ACCESS COVER ASSEMBLY INSTALLATION (SHEET 2 OF 2)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 31, 2014 747-54A2238 56 of 56 **BOEING SERVICE BULLETIN 747-54A2238 ALERT**  **ALERT**