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.

ECCN: 9E991

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Unpublished Work.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

3.0
Export 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PROPRIETARY - Copyright © Unpublished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 56
Boeing 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.

Planning Data Affected Reference

Spares Affected No Paragraph 1.A.2., Spares Affected

Paragraph 1.E., Compliance and Paragraph

1.F., Approval

AD Related Yes

Weight and Balance Change Yes Paragraph 1.H., Weight and Balance Changes

Electrical Load Changed No Paragraph 1.I., Electrical Load Data

Publications Affected Yes Paragraph 1.K., Publications Affected

Airplane Flight Operations Affected (Flight Crew No Paragraph 1.K., Publications Affected

Operations Manual and/or FAA Approved Airplane Flight Manual)

Kits/Parts Required Yes Paragraph 2.C.1., Kits/Parts

Paragraph 2.C.2., Parts and Materials Supplied

by the Operator

Operator Supplied Parts/Material Yes

Paragraph 2.F., Special Tooling Necessary to

do this Service Bulletin

Special Tooling Required Yes

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.

GROUP CONFIGURATION DESCRIPTION

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
Variable Number Group

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 1

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

Model Zone

747-8, 747-8F 451, 452, 481, 482

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

Number of Task Hours

Persons

Task

Open Access 4 13.00 3.25

Remove Access Panels

...FIGURE 1: Strut No. 1 1 1.00 1.00

...FIGURE 2: Strut No. 4 1 1.00 1.00

Depressurize hydraulic system 1 0.15 0.15

Remove Air Drive Unit 4 18.00 4.50

Replace Fuse Pins

...FIGURE 3: Strut No. 1, Outboard Side 2 8.00 4.00

...FIGURE 4: Strut No. 1, Inboard Side 2 5.50 2.75

...FIGURE 5: Strut No. 4, Inboard Side 2 5.50 2.75

...FIGURE 6: Strut No. 4, Outboard Side 2 8.00 4.00

Install Air Drive Unit 4 18.00 4.50

Pressurize hydraulic system 1 0.15 0.15

Install Access Panels

...FIGURE 7: Strut No. 1 1 1.00 1.00

...FIGURE 8: Strut No. 4 1 1.00 1.00

Close Access 4 13.00 3.25

Test 4 4.00 1.00

TOTAL FOR EACH AIRPLANE 97.30 34.30

H. Weight and Balance Changes

Change in Moment

(Pound-Inches)

Change in Weight

Airplane (Pounds)

All +5.2 lb. +8320.9 lb.-in.

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:

Drawing No Title Sheet DCN/REV ADCN

MIT321U8047 747 Hydraulic Bracket Trim Tool 1 - -

2 - -

3 - -

MIT321U8047_- 747 Hydraulic Bracket Trim Tool - - -

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

Drawing Number Title

321U8046 REWORK - BRACKET INSTL, TRAS, HYD, FUEL

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:

Publication Chapter-Section

747 Aircraft Maintenance Manual 54-51

747 Illustrated Parts Catalog 54-51

Component Maintenance Manual 54-00

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 Service Bulletin (US

Dollars)

ROLT as of the

Original Issue

date of this Service Bulletin (Calendar Days)

Kit Number Name Date QTY

December 13, 2 578 $31,036.00

2013

TOP KIT - OUTBOARD

STRUT R3 FUSE PIN

AND ACCESS DOOR

- REPLACEMENT

015U1954-1

January 24, 10

2014

February 27, 18

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

Top Kit 3 4 5 6 7 8

015U1954-1 1 1 1 1 1 1

ALL

KIT 015U1954-1

Notes

Existing Part

Name Number

Figure

New Part Number

3 4 5 6 7 8

Qty

(a) (b)

(c)

FUSE PIN - AFT 311U8092-2

UPPER SPAR NACELLE STRUT

311U8092-3 1 1 1 1 . .

(a) (b)

(c)

THROUGH BOLT 311U8098-9

- AFT UPPER

SPAR NACELLE

STRUT

311U8098-10 1 1 1 1 . .

(a) (b)

(c)

ACCESS COVER 323U8215-3

ASSY, OUTBD

SIDE, LH OUTBD

ENGINE

323U8215-5 . . . . 1 .

(a) (b)

(c)

ACCESS COVER 323U8215-4

ASSY, OUTBD

SIDE, RH OUTBD

ENGINE

323U8215-6 . . . . . 1

BACB30NN4K11 . . . . 15 15 BOLT (d)

(BACB30NN4K11G

optional)

SELF-LOCKING

NUT

BACN10HR14CS 1 1 1 1 . .

BACN11N114CS 1 1 1 1 . . NUT

BACP18BC04A14P 1 1 1 1 . . PIN

(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
Part Number / QTY Name Notes

Specification

8 PRIMER (a)

ounces

BMS 10-11, TYPE

1

1 GREASE (a) (e)

quart

AEROSHELL

GREASE 33MS

8 HYDRAULIC FLUID (a)

ounces

BMS 3-11

(MCS0352 optional)

1 GREASE (a)

quart

BMS 3-33, TYPE I

8 ANTI-SEIZE THREAD COMPOUND (b)

ounces

-

BACC13AT4K18 4 CABLE ASSEMBLY, SAFETY (c)

2 MARKING LACQUER (d)

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 Service Bulletin (US

Dollars)

Tool Kit Number Name

MIT321U8047 747 Hydraulic Bracket Trim Tool $53,760.00

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 service bulletin (US

Dollars)

Tool Kit Number Name

MIT321U8047 747 Hydraulic Bracket Trim Tool $360.00

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.

Tool Kit Number Name

MIT321U8047 747 Hydraulic Bracket Trim Tool

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. 1 Engine Strut No. 4 Engine Strut Forward Fairing Access Panel No.

1 451AT 481AT

2 451BT 481BT

3 451DL and 451DR 481DL and 481DR

4 451EL and 451ER 481EL and 481ER

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
Engine Strut Figure

Strut No. 1 FIGURE 1

Strut No. 4 FIGURE 2

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.

Engine Strut Location Figure

Strut No. 1, Outboard Side FIGURE 3

Strut No. 1, Inboard Side FIGURE 4

Strut No. 4, Inboard Side FIGURE 5

Strut No. 4, Outboard Side FIGURE 6

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

Engine Strut Figure

Strut No. 1 FIGURE 7

Strut No. 4 FIGURE 8

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. 1 Engine Strut No. 4 Engine Strut Forward Fairing Access Panel No.

1 451AT 481AT

2 451BT 481BT

3 451DL and 451DR 481DL and 481DR

4 451EL and 451ER 481EL and 481ER

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.

Step Task Name Identification Qty More Data

1 Remove / Keep BOLT - 13 (a)

ACCESS COVER AS- 323U8215-3 1

SY, OUTBD SIDE, LH

OUTBD ENGINE

Remove

2 Remove / Keep BOLT - 11 (a)

ACCESS COVER AS- 323U8225-3 1

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.

Step Task Name Identification Qty More Data

1 Remove / Keep BOLT - 13 (a)

ACCESS COVER AS- 323U8215-4 1

SY, OUTBD SIDE, RH

OUTBD ENGINE

Remove

2 Remove / Keep BOLT - 11 (a)

ACCESS COVER AS- 323U8225-4 1

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.

Step Task Name Identification Qty More Data

and attach fuse pins.

Refer to 747-8 AMM

54-51-02 as an accepted procedure.

1 Remove / Keep SIDE LINK ASSEMBLY 321U8740-1 2

CABLE ASSEMBLY, - 1

SAFETY

Remove

CLAMPBLOCK - HY- - 1 and fasteners.

DRAULIC TUBE SUPPRT BRACKET

2 Remove / Keep

and lift hydraulic

tube to provide

clearance for installation of new fuse pin.

3 Disconnect HYDRAULIC TUBE - 1

by loosening or removing clamp

screws, as required,

to move the conduit.

Keep all clamp

screws, if removed.

4 Move CONDUIT - -

Refer to 747-8 AMM

54-51-02 as an accepted procedure.

5 Remove PIN - 1

Remove NUT - 1

Remove SELF-LOCKING NUT - 1

THROUGH BOLT - 311U8098-9 1

AFT UPPER SPAR

NACELLE STRUT

Remove

Refer to 747-8 AMM

54-51-02 as an accepted procedure.

END CAP - AFT UP- 311U8095-9 2

PER SPAR NACELLE

STRUT

6 Remove / Keep

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
Step Task Name Identification Qty More Data

to provide clearance

for new fuse pin.

Refer to tool

MIT321U8047 instructions.

7 Machine BRACKET ASSY 321U8047-40 1

two coats to bare

metal areas. Refer

to SOPM 20-41-02

as an accepted procedure.

Apply PRIMER BMS 10-11, TYPE 1 -

Refer to tool

MIT321U8047 instructions.

FUSE PIN - AFT UP- - 1

PER SPAR NACELLE

STRUT

8 Remove

with the flanged end

on the inboard side.

Apply thin film of

Aeroshell Grease

33MS 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 SOPM

20-50-07 as an accepted procedure.

FUSE PIN - AFT UP- 311U8092-3 1

PER SPAR NACELLE

STRUT

Install (New)

After installation, inject grease into

grease fitting until

grease appears at

other side of the

joint. Refer to SOPM

20-50-07 as accepted procedure.

AEROSHELL GREASE -

33MS

Apply GREASE

One End Cap is installed on the

Through Bolt head

side and one End

Cap is installed on

the Through Bolt

thread side.

END CAP - AFT UP- 311U8095-9 2

PER SPAR NACELLE

STRUT

9 Install (Kept)

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
Step Task Name Identification Qty More Data

with bolt head facing

the outboard side.

(a)

THROUGH BOLT - 311U8098-10 1

AFT UPPER SPAR

NACELLE STRUT

10 Install (New)

Install (New) SELF-LOCKING NUT BACN10HR14CS 1 (a) (c)

Apply a torque stripe

to End Cap and SelfLocking Nut on inboard side. Refer to

Paragraph 2.C.2.,

Parts and Materials

Supplied by the Operator for acceptable

material.

11 Apply MARKING LACQUER - -

Tighten Nut 70 to

750 inch-pounds.

Replace Nut if Nut

cannot be tighten

between 70 to 750

inch-pounds. Increase torque, to

align with Pin hole in

Through Bolt, to not

exceed 1500 inchpounds. (a)

12 Install (New) NUT BACN11N114CS 1

Install (New) PIN BACP18BC04A14P 1 (b) (d)

back to previous position. Install clamp

screws, if removed.

13 Move CONDUIT - -

14 Connect HYDRAULIC TUBE - 1

to seal surface of

sleeve before seating B-nut, to external

fitting threads, and

to shoulder of

sleeve. Torque B-nut

to 855 to 945 inchpounds. Refer to

SOPM 20-50-00 as

an accepted procedure.

BMS 3-11 (MCS-352 -

optional)

Apply HYDRAULIC FLUID

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
Step Task Name Identification Qty More Data

and fasteners.

Torque nut to 3.5 to

30.0 inch-pounds.

Refer to SOPM 20-

50-01 as an accepted procedure.

CLAMPBLOCK - HY- - 1

DRAULIC TUBE SUPPRT BRACKET

15 Install (Kept)

and attach fuse pins.

Torque nuts on

through bolts to

1500 to 2500 inchpounds. Ensure that

all parts are firmly

seated. Refer to

747-8 AMM 54-51-

02 as an accepted

procedure.

16 Install (Kept) SIDE LINK ASSEMBLY 321U8740-1 2

Refer to SOPM 20-

50-02 as an accepted procedure.

CABLE ASSEMBLY, BACC13AT4K18 1

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.

Step Task Name Identification Qty More Data

and attach fuse pins.

Refer to 747-8 AMM

54-51-02 as an accepted procedure.

1 Remove / Keep SIDE LINK ASSEMBLY 321U8740-1 2

CABLE ASSEMBLY, - 1

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
Step Task Name Identification Qty More Data

Refer to 747-8 AMM

54-51-02 as an accepted procedure.

2 Remove PIN - 1

Remove NUT - 1

Remove SELF-LOCKING NUT - 1

THROUGH BOLT - 311U8098-9 1

AFT UPPER SPAR

NACELLE STRUT

Remove

Refer to 747-8 AMM

54-51-02 as an accepted procedure.

END CAP - AFT UP- 311U8095-9 2

PER SPAR NACELLE

STRUT

3 Remove / Keep

Refer to tool

MIT321U8047 instructions.

FUSE PIN - AFT UP- - 1

PER SPAR NACELLE

STRUT

4 Remove

with the flanged end

on the outboard

side. Apply thin film

of Aeroshell Grease

33MS 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 SOPM

20-50-07 as an accepted procedure.

FUSE PIN - AFT UP- 311U8092-3 1

PER SPAR NACELLE

STRUT

Install (New)

After installation, inject grease into

grease fitting until

grease appears at

other side of the

joint. Refer to SOPM

20-50-07 as accepted procedure.

AEROSHELL GREASE -

33MS

Apply GREASE

One End Cap is installed on the

Through Bolt head

side and one End

Cap is installed on

the Through Bolt

thread side.

END CAP - AFT UP- 311U8095-9 2

PER SPAR NACELLE

STRUT

5 Install (Kept)

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
Step Task Name Identification Qty More Data

with bolt head facing

the inboard side. (a)

THROUGH BOLT - 311U8098-10 1

AFT UPPER SPAR

NACELLE STRUT

6 Install (New)

Install (New) SELF-LOCKING NUT BACN10HR14CS 1 (a) (c)

Apply a torque stripe

to End Cap and SelfLocking Nut on outboard side. Refer to

Paragraph 2.C.2.,

Parts and Materials

Supplied by the Operator for acceptable

material.

7 Apply MARKING LACQUER - -

Tighten Nut 70 to

750 inch-pounds.

Replace Nut if Nut

cannot be tighten

between 70 to 750

inch-pounds. Increase torque, to

align with Pin hole in

Through Bolt, to not

exceed 1500 inchpounds. (a)

8 Install (New) NUT BACN11N114CS 1

Install (New) PIN BACP18BC04A14P 1 (b) (d)

and attach fuse pins.

Torque nuts on

through bolts to

1500 to 2500 inchpounds. Ensure that

all parts are firmly

seated. Refer to

747-8 AMM 54-51-

02 as an accepted

procedure.

9 Install (Kept) SIDE LINK ASSEMBLY 321U8740-1 2

Refer to SOPM 20-

50-02 as an accepted procedure.

CABLE ASSEMBLY, BACC13AT4K18 1

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
Step Task Name Identification Qty More Data

(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.

Step Task Name Identification Qty More Data

and attach fuse pins.

Refer to 747-8 AMM

54-51-02 as an accepted procedure.

1 Remove / Keep SIDE LINK ASSEMBLY 321U8740-1 2

CABLE ASSEMBLY, - 1

SAFETY

Remove

CLAMPBLOCK - HY- - 1 and fasteners.

DRAULIC TUBE SUPPRT BRACKET

2 Remove / Keep

and lift hydraulic

tube to provide

clearance for installation of new fuse pin.

3 Disconnect HYDRAULIC TUBE - 1

by loosening or removing clamp

screws, as required,

to move the conduit.

Keep all clamp

screws, if removed.

4 Move CONDUIT - -

Refer to 747-8 AMM

54-51-02 as an accepted procedure.

5 Remove PIN - 1

Remove NUT - 1

Remove SELF-LOCKING NUT - 1

THROUGH BOLT - 311U8098-9 1

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.

END CAP - AFT UP- 311U8095-9 2

PER SPAR NACELLE

STRUT

6 Remove / Keep

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
Step Task Name Identification Qty More Data

to provide clearance

for new fuse pin.

Refer to tool

MIT321U8047 instructions.

7 Machine BRACKET ASSY 321U8047-40 1

two coats to bare

metal areas. Refer

to SOPM 20-41-02

as an accepted procedure.

Apply PRIMER BMS 10-11, TYPE 1 -

Refer to tool

MIT321U8047 instructions.

FUSE PIN - AFT UP- - 1

PER SPAR NACELLE

STRUT

8 Remove

with the flanged end

on the outboard

side. Apply thin film

of Aeroshell Grease

33MS 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 SOPM

20-50-07 as an accepted procedure.

FUSE PIN - AFT UP- 311U8092-3 1

PER SPAR NACELLE

STRUT

Install (New)

After installation, inject grease into

grease fitting until

grease appears at

other side of the

joint. Refer to SOPM

20-50-07 as an accepted procedure.

AEROSHELL GREASE -

33MS

Apply GREASE

One End Cap is installed on the

Through Bolt head

side and one End

Cap is installed on

the Through Bolt

thread side.

END CAP - AFT UP- 311U8095-9 2

PER SPAR NACELLE

STRUT

9 Install (Kept)

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
Step Task Name Identification Qty More Data

with bolt head facing

the inboard side. (a)

THROUGH BOLT - 311U8098-10 1

AFT UPPER SPAR

NACELLE STRUT

10 Install (New)

Install (New) SELF-LOCKING NUT BACN10HR14CS 1 (a) (c)

Apply a torque stripe

to End Cap and SelfLocking Nut on outboard side. Refer to

Paragraph 2.C.2.,

Parts and Materials

Supplied by the Operator for acceptable

material.

11 Apply MARKING LACQUER - -

Tighten Nut 70 to

750 inch-pounds.

Replace Nut if Nut

cannot be tighten

between 70 to 750

inch-pounds. Increase torque, to

align with Pin hole in

Through Bolt, to not

exceed 1500 inchpounds. (a)

12 Install (New) NUT BACN11N114CS 1

Install (New) PIN BACP18BC04A14P 1 (b) (d)

back to previous position. Install clamp

screws, if removed.

13 Move CONDUIT - -

14 Connect HYDRAULIC TUBE - 1

to seal surface of

sleeve before seating B-nut, to external

fitting threads, and

to shoulder of

sleeve. Torque B-nut

to 855 to 945 inchpounds. Refer to

SOPM 20-50-00 as

an accepted procedure.

BMS 3-11 (MCS-352 -

optional)

Apply HYDRAULIC FLUID

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
Step Task Name Identification Qty More Data

and fasteners.

Torque nut to 3.5 to

30.0 inch-pounds.

Refer to SOPM 20-

50-01 as an accepted procedure.

CLAMPBLOCK - HY- - 1

DRAULIC TUBE SUPPRT BRACKET

15 Install (Kept)

and attach fuse pins.

Torque nuts on

through bolts to

1500 to 2500 inchpounds. Ensure that

all parts are firmly

seated. Refer to

747-8 AMM 54-51-

02 as an accepted

procedure.

16 Install (Kept) SIDE LINK ASSEMBLY 321U8740-1 2

Refer to SOPM 20-

50-02 as an accepted procedure.

CABLE ASSEMBLY, BACC13AT4K18 1

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.

Step Task Name Identification Qty More Data

and attach fuse pins.

Refer to 747-8 AMM

54-51-02 as an accepted procedure.

1 Remove / Keep SIDE LINK ASSEMBLY 321U8740-1 2

CABLE ASSEMBLY, - 1

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
Step Task Name Identification Qty More Data

Refer to 747-8 AMM

54-51-02 as an accepted procedure.

2 Remove PIN - 1

Remove NUT - 1

Remove SELF-LOCKING NUT - 1

THROUGH BOLT - 311U8098-9 1

AFT UPPER SPAR

NACELLE STRUT

Remove

END CAP - AFT UP- 311U8095-9 2

PER SPAR NACELLE

STRUT

3 Remove / Keep

Refer to tool

MIT321U8047 instructions.

FUSE PIN - AFT UP- - 1

PER SPAR NACELLE

STRUT

4 Remove

with the flanged end

on the inboard side.

Apply thin film of

Aeroshell Grease

33MS 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 SOPM

20-50-07 as an accepted procedure.

FUSE PIN - AFT UP- 311U8092-3 1

PER SPAR NACELLE

STRUT

Install (New)

After installation, inject grease into

grease fitting until

grease appears at

other side of the

joint. Refer to SOPM

20-50-07 as an accepted procedure.

AEROSHELL GREASE -

33MS

Apply GREASE

One End Cap is installed on the

Through Bolt head

side and one End

Cap is installed on

the Through Bolt

thread side.

END CAP - AFT UP- 311U8095-9 2

PER SPAR NACELLE

STRUT

5 Install (Kept)

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
Step Task Name Identification Qty More Data

with bolt head facing

the outboard side.

(a)

THROUGH BOLT - 311U8098-10 1

AFT UPPER SPAR

NACELLE STRUT

6 Install (New)

Install (New) SELF-LOCKING NUT BACN10HR14CS 1 (a) (c)

Apply a torque stripe

to End Cap and SelfLocking Nut on inboard side. Refer to

Paragraph 2.C.2.,

Parts and Materials

Supplied by the Operator for acceptable

material.

7 Apply MARKING LACQUER - -

Tighten Nut 70 to

750 inch-pounds.

Replace Nut if Nut

cannot be tighten

between 70 to 750

inch-pounds. Increase torque, to

align with Pin hole in

Through Bolt, to not

exceed 1500 inchpounds. (a)

8 Install (New) NUT BACN11N114CS 1

Install (New) PIN BACP18BC04A14P 1 (b) (d)

and attach fuse pins.

Torque nuts on

through bolts to

1500 to 2500 inchpounds. Ensure that

all parts are firmly

seated. Refer to

747-8 AMM 54-51-

02 as an accepted

procedure.

9 Install (Kept) SIDE LINK ASSEMBLY 321U8740-1 2

Refer to SOPM 20-

50-02 as an accepted procedure.

CABLE ASSEMBLY, BACC13AT4K18 1

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
Step Task Name Identification Qty More Data

(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.

Step Task Name Identification Qty More Data

ACCESS COVER AS- 323U8215-5 1

SY, OUTBD SIDE, LH

OUTBD ENGINE

1 Install (New)

with BMS 3-33, Type

1 grease on bolt

shank. Torque to 60

to 80 inch-pounds.

Install (Kept) BOLT - 13

ACCESS COVER AS- 323U8225-3 1

SY, INBD SIDE, LH

OUTBD ENGINE

2 Install (Kept)

with BMS 3-33, Type

I grease on bolt

shank. Torque to 60

to 80 inch-pounds.

Install (Kept) BOLT - 11

The parts shown in the table below are provided as extra parts for this figure.

Name Identification Qty More Data

These parts are not required for

installing Access Cover Assemblies. These parts can be used to

replace kept parts if grip length

meets installation requirements.

BACB30NN4K11 15

(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.

Step Task Name Identification Qty More Data

ACCESS COVER AS- 323U8215-6 1

SY, OUTBD SIDE, RH

OUTBD ENGINE

1 Install (New)

with BMS 3-33, Type

1 grease on bolt

shank. Torque to 60

to 80 inch-pounds.

Install (Kept) BOLT - 13

ACCESS COVER AS- 323U8225-4 1

SY, INBD SIDE, RH

OUTBD ENGINE

2 Install (Kept)

with BMS 3-33, Type

I grease on bolt

shank. Torque to 60

to 80 inch-pounds.

Install (Kept) BOLT - 11

The parts shown in the table below are provided as extra parts for this figure.

Name Identification Qty More Data

These parts are not required for

installing Access Cover Assemblies. These parts can be used to

replace kept parts if grip length

meets installation requirements.

BACB30NN4K11 15

(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