Commercial 

Airplanes 747

Service Bulletin

ALERT

Number: 747-53A2605

Original Issue: October 08, 2009

Revision 3: July 10, 2013

ATA System: 5312

SUBJECT: FUSELAGE - Center Section - Tension Ties and Frames - Modification and Inspection

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laws.

ECCN: 9E991

BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET

Copyright © 2009 Boeing.

Unpublished Work. All Rights Reserved.

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BLANK PAGE
Table of Contents

Revision Transmittal Sheet ............................................ 5

Summary ...................................................... 7

1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 42

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 49

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 50

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 51

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 51

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52

1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52

2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . . 162

3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 163

4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 163

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 163

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 163

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . 164

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 165

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 165

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 166

FIGURE 1: SURFACE HFEC INSPECTION OF TENSION TIE CENTER SECTIONS (STA 760 - STA 940)

[Group 1-3, 13-14] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 177

FIGURE 2: SURFACE HFEC INSPECTION OF TENSION TIE CENTER SECTIONS (STA 800 - STA 940)

[Group 4, 9] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 179

FIGURE 3: SURFACE HFEC INSPECTION OF TENSION TIE CENTER SECTIONS (STA 800 - STA 880,

STA 920, AND STA 940) [Group 5, 16] . . . . . . . . . . . . . . . . . . . . . . . . . . . 181

FIGURE 4: SURFACE HFEC INSPECTION OF TENSION TIE CENTER SECTIONS (STA 840 - STA 940)

[Group 6] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 183

FIGURE 5: SURFACE HFEC INSPECTION OF TENSION TIE CENTER SECTIONS (STA 840 - STA 880,

STA 920, AND STA 940) [Group 7] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 185

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FIGURE 6: SURFACE HFEC INSPECTION OF TENSION TIE CENTER SECTIONS (STA 780 - STA 880,

STA 920, AND STA 940) [Group 8, 11-12, 15] . . . . . . . . . . . . . . . . . . . . . . . 187

FIGURE 7: SURFACE HFEC INSPECTION OF TENSION TIE CENTER SECTIONS (STA 720 - STA 940)

[Group 10] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 189

FIGURE 8: EDDY CURRENT INSPECTIONS OF ALL AREAS OF TENSION TIES - LEFT SIDE [Group

1-16] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 192

FIGURE 9: EDDY CURRENT INSPECTIONS OF ALL AREAS OF TENSION TIES - RIGHT SIDE [Group

1-16] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 197

APPENDIX A: TENSION TIE DISCONNECTION METHODS . . . . . . . . . . . . . . . . . . . . . . . 202

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BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Commercial 

Airplanes 747

Service Bulletin

ALERT

Revision Transmittal Sheet Number: 747-53A2605

Original Issue: October 08, 2009

Revision 3: July 10, 2013

ATA System: 5312

SUBJECT: FUSELAGE - Center Section - Tension Ties and Frames - Modification and Inspection

This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

More work is necessary on airplanes modified in accordance with the original issue, Revision 1, or Revision 2

of this service bulletin. Airplanes previously modified in accordance with this service bulletin will require surface

high frequency eddy current (HFEC) inspection for cracks in the forward and aft tension tie channels around

fasteners in unmodified areas where fastener holes were not zero-timed during modification. Refer to paragraph

1.E., Compliance for the compliance time of this additional inspection. However, no additional modification is

necessary.

Federal Aviation Administration (FAA) Airworthiness Directive AD 2012-13-08 is related to this service bulletin.

Airplanes RG001-RG009, RG091-RG091, RG095-RG095, RG101-RG104, RG121-RG126, RG141-RG142,

RG161-RG164, RG171-RG174, RG191-RG193, RG211-RG213, RG221-RG222, RH111-RH112, RH121-RH122

were added to the service bulletin effectivity as Group 17.

Airplanes RH101 and RH102 were added to the service bulletin effectivity as Group 18.

REASON FOR REVISION

This revision is sent to add the requirement to do surface high frequency eddy current (HFEC) inspection where

fastener holes are not zero-timed during modification on Group 1-16 airplanes. Revision 3 also adds instructions

for post-modification inspection of the entire tension tie for Group 1-16 airplanes, and adds effectivity and

modification instructions for 747SP (Group 17-18) airplanes.

These sections were changed:

1. In the Summary: Updated the Background and Action sections to reflect new inspection requirements.

Also, updated Compliance section with current Airworthiness Directive (AD) information.

2. In Paragraph 1.A., Effectivity: Added 747SP airplanes as Group 17 and Group 18. Also, revised the

Group/Configuration table to specify configurations for airplanes that have and have not already had

the tension tie and frame modification accomplished.

3. In Paragraph 1.C., Reason: Added reason for Revision 3.

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4. In Paragraph 1.D., Description: Updated the description of service bulletin actions and added "more

work" statement related to Revision 3.

5. In Paragraph 1.E., Compliance: Updated Airworthiness Directive information. Revised compliance

Table 1 to apply only to initial inspection and modification. Added new compliance Tables 2, 3, and 4

for Post-Modification inspections. Added new compliance Table 5 for additional (more work) inspection

requirements on airplanes that had the tension tie and frame modification accomplished in accordance

with a previous revision of this service bulletin. Added new compliance Tables 6 and 7 for Group 17

and 18 airplanes.

6. In Paragraph 1.F., Approval: Updated Alternative Method of Compliance (AMOC) statements for AD

2004-07-22 R1, 84-19-01, and 94-13-06. Added new AMOC statements for AD 2012-13-08 (which

superseded AD 2006-01-07).

7. In Paragraph 1.G., Manpower: Added task hour estimates for tension tie center section inspections

and post-modification inspections.

8. In Paragraph 1.J.2., Data Supplied with this Service Bulletin: Added drawings required for

post-modification inspections of Group 1-16 airplanes and added drawings required for modification

of Group 17-18 airplanes. Also added KPL data previously not listed.

9. In Paragraph 3.A., General Information: Added note 15.

10. In Paragraph 3.B., Work Instructions: Added PART 3 to give instructions for new post-modification

inspection requirements, and added PART 4 to give instructions for inspection of the unmodified tension

tie center sections. PART 4 is a "more work" requirement for airplanes that had the tension tie and

frame modification accomplished in accordance with the Original Issue, Revision 1, or Revision 2 of

this service bulletin. Also in the Work Instructions, added PART 5 and PART 6 for modification of Group

17-18 airplanes.

11. In Figures 1 - 7: These new figures have been added to give inspection instructions for the unmodified

tension tie center sections on Group 1-16 airplanes.

12. In Figures 8 and 9: These new figure have been added to give post-modification inspection instructions

not previously included in the service bulletin for Group 1-16 airplanes.

Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location

of important changes.

Pages with no vertical lines have no important changes.

REVISION HISTORY

Original Issue: October 08, 2009

Revision 1: May 27, 2010

Revision 2: December 09, 2011

Revision 3: July 10, 2013

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BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Commercial 

Airplanes 747

Service Bulletin

ALERT

Summary Number: 747-53A2605

Original Issue: October 08, 2009

Revision 3: July 10, 2013

ATA System: 5312

SUBJECT: FUSELAGE - Center Section - Tension Ties and Frames - Modification and Inspection

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

This service bulletin gives instructions for modification of upper deck tension ties and adjacent frame structure

on non stretched upper deck (Non-SUD) airplanes. The tension ties have been determined to be structure that

is susceptible to Widespread Fatigue Damage (WFD). WFD can cause tension ties to become severed or

disconnected from the frames. Severed or disconnected Tension Ties and/or Frames at multiple locations could

result in rapid in-flight decompression.

For more information about WFD, refer to Boeing Service Letter 747-SL-53-088.

Service Bulletin 747-53A2502 recommends initial and repeat inspections of Non-SUD airplane tension ties from

body station (STA) 760 to STA 940 (STA 1040 to STA 1140 for 747SP). Service Bulletin 747-53A2502 was

issued to address multiple reports of cracks found in tension ties and adjacent frame structure.

Group 1-16:

Accomplishment of the modification in this service bulletin terminates the repeat inspection requirement of

Service Bulletin 747-53A2502.

Group 17-18:

Accomplishment of the modification in this service bulletin does not terminate the repeat inspection requirement

of Service Bulletin 747-53A2502, but a new inspection threshold is provided.

Boeing Service Related Problem (SRP) 747-SRP-53-0200 and 747-SRP-53-0438 are related to this service

bulletin.

As a part of a service bulletin validation program, this modification and inspection was completed on airplane

RD041 by Service Bulletin 747-53A2605, Original Issue. The modification and inspection completed on airplane

RD041 by Service Bulletin 747-53A2605, Original Issue is equivalent to the Revision 2 of this service bulletin.

Airplane RD041 has the configuration of a Group 5 airplane.

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Subsequent to the release of Revision 2 of this service bulletin, Boeing has determined that additional inspections

are required in the center sections of the tension ties where the tension tie channels are not replaced and where

fastener holes are not zero-timed during modification.

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

AD Related Yes Paragraph 1.E., Compliance

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 Material Yes

Paragraph 2.F., Special Tooling Necessary to

do this Service Bulletin

Special Tooling Required Yes

ACTION (PRR 85901-68RS)

Get access to the Frame to Tension Tie joints in Section 42. At each station, disconnect and remove a section

of the tension tie between the frame and approximate Buttock Line (BL) 36. For each frame, remove a specified

section of the frame above and below the tension tie attach point. After the existing frame and tension tie structure

has been removed and discarded, install new frame and tension tie structure. Do the modification on both sides

of the airplane.

Group 1-16:

Do surface high frequency eddy current (HFEC) inspection of the tension ties at fastener locations where the

holes were not zero-timed during modification. If cracks are found, contact Boeing for repair instructions and do

the repair.

Group 1-16:

After modification, do initial and repeat detailed, high frequency eddy current (HFEC), and low frequency eddy

current (LFEC) inspections of the tension ties at the compliance time specified in paragraph 1.E., Compliance.

If cracks are found, contact Boeing for repair instructions and do the repair.

Group 17-18:

After modification, do initial and repeat detailed and HFEC inspections for cracks in all tension ties, adjacent

frame structure, and adjacent structure that attaches to the tension ties. If cracks are found, contact Boeing for

repair instructions and do the repair.

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BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
EFFECTIVITY

747-100, 747-100B, 747-200B, 747-200C, 747-200F, 747-400F, 747SR, and 747SP airplanes. Refer to Paragraph

1.A.1., Airplanes, for the list of affected airplanes.

COMPLIANCE

Federal Aviation Administration (FAA) Airworthiness Directives AD 84-19-01, AD 94-13-06, AD 2004-07-22 R1,

and AD 2012-13-08 are related to this service bulletin.

Refer to paragraph 1.E, Compliance.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the modification and inspections given in this service bulletin.

MANPOWER

Refer to paragraph 1.G., Manpower.

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

Refer to Paragraph 2.A., Material - Price and Availability.

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BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Commercial 

Airplanes 747

Service Bulletin

ALERT

Number: 747-53A2605

Original Issue: October 08, 2009

Revision 3: July 10, 2013

ATA System: 5312

SUBJECT: FUSELAGE - Center Section - Tension Ties and Frames - Modification and Inspection

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 airplanes shown below. Refer to PRR 85901-68RS for data about

this change.

Refer to Service Bulletin Index Document D6-30300 Part 3 for Airplane Variable Number, Line

Number, and Serial Number data.

GROUP CONFIGURATION DESCRIPTION

747-100 and -200B airplanes with tension ties from STA 760 to STA

940, and a combination of tension ties at STA 760 and STA 940 that

is unique. The Group 1 tension tie modification is similar to Group 2,

except at STA 760. The Group 1 tension tie modification similar to

Group 13, except at STA 940. This group requires 142U0102-233

tension tie modification kit.

1 -

Group 1 airplanes not modified in accordance with the Original Issue,

Revision 1, or Revision 2 of this service bulletin.

1

Group 1 airplanes that were modified in accordance with the Original

Issue, Revision 1, or Revision 2 of this service bulletin.

2

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GROUP CONFIGURATION DESCRIPTION

747-100 airplanes with tension ties from STA 760 to STA 940, and

a combination of tension ties at STA 760 and STA 940 that is unique.

The Group 2 tension tie modification is similar to Group 1, except at

STA 760. The Group 2 tension tie modification similar to Group 14,

except at STA 940. This group requires 142U0102-233 tension tie

modification kit.

2 -

Group 2 airplanes not modified in accordance with the Original Issue,

Revision 1, or Revision 2 of this service bulletin.

1

Group 2 airplanes that were modified in accordance with the Original

Issue, Revision 1, or Revision 2 of this service bulletin.

2

-100 and -200B airplanes with tension ties from STA 760 to STA 940,

and a unique tension tie configuration at STA 760.

3 -

Group 3 airplanes not modified in accordance with the Original Issue,

Revision 1, or Revision 2 of this service bulletin.

1

Group 3 airplanes that were modified in accordance with the Original

Issue, Revision 1, or Revision 2 of this service bulletin.

2

747-100, -100B, -200B and SR airplanes with tension ties from STA

800 to STA 940, and a unique combination of tension ties at STA

900, 920, and 940.

4 -

Group 4 airplanes not modified in accordance with the Original Issue,

Revision 1, or Revision 2 of this service bulletin.

1

Group 4 airplanes that were modified in accordance with the Original

Issue, Revision 1, or Revision 2 of this service bulletin.

2

747-200B and SR airplanes with tension ties from STA 800 to STA

940, and a unique frame configuration.

5 -

Group 5 airplanes not modified in accordance with the Original Issue,

Revision 1, or Revision 2 of this service bulletin.

1

Group 5 airplanes that were modified in accordance with the Original

Issue, Revision 1, or Revision 2 of this service bulletin.

2

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BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
GROUP CONFIGURATION DESCRIPTION

747-100, -100B, -200B and SR airplanes with tension ties from STA

840 to STA 940 that have a unique configuration.

6 -

Group 6 airplanes not modified in accordance with the Original Issue,

Revision 1, or Revision 2 of this service bulletin.

1

Group 6 airplanes that were modified in accordance with the Original

Issue, Revision 1, or Revision 2 of this service bulletin.

2

747-200B and SR airplanes with tension ties from STA 840 to STA

940 that have a unique configuration.

7 -

Group 7 airplanes not modified in accordance with the Original Issue,

Revision 1, or Revision 2 of this service bulletin.

1

Group 7 airplanes that were modified in accordance with the Original

Issue, Revision 1, or Revision 2 of this service bulletin.

2

747-200F airplanes. These airplanes have tension ties from STA 780

to STA 940, and have a unique configuration at STA 940.

8 -

Group 8 airplanes not modified in accordance with the Original Issue,

Revision 1, or Revision 2 of this service bulletin.

1

Group 8 airplanes that were modified in accordance with the Original

Issue, Revision 1, or Revision 2 of this service bulletin.

2

747-200C airplanes. These airplanes have tension ties from STA

800 to STA 940, and have a unique configuration at STA 900.

9 -

Group 9 airplanes not modified in accordance with the Original Issue,

Revision 1, or Revision 2 of this service bulletin.

1

Group 9 airplanes that were modified in accordance with the Original

Issue, Revision 1, or Revision 2 of this service bulletin.

2

747-400F airplanes. These airplanes have tension ties from STA 720

to STA 940.

10 -

Group 10 airplanes not modified in accordance with the Original

Issue, Revision 1, or Revision 2 of this service bulletin.

1

Group 10 airplanes that were modified in accordance with the Original

Issue, Revision 1, or Revision 2 of this service bulletin.

2

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BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
GROUP CONFIGURATION DESCRIPTION

747-100 airplanes with tension ties from STA 780 to STA 940, and

a unique combination of tension ties at STA 900, 920, and 940. This

group requires 142U0102-233 tension tie modification kit.

11 -

Group 11 airplanes not modified in accordance with the Original

Issue, Revision 1, or Revision 2 of this service bulletin.

1

Group 11 airplanes that were modified in accordance with the Original

Issue, Revision 1, or Revision 2 of this service bulletin.

2

747-100 airplanes with tension ties from STA 780 to STA 940, and

a unique combination of tension ties at STA 900, 920, and 940.

12 -

Group 12 airplanes not modified in accordance with the Original

Issue, Revision 1, or Revision 2 of this service bulletin.

1

Group 12 airplanes that were modified in accordance with the Original

Issue, Revision 1, or Revision 2 of this service bulletin.

2

747-100 airplanes with tension ties from STA 760 to STA 940, and

a combination of tension ties at STA 760 and STA 940 that is unique.

The Group 13 tension tie modification is similar to Group 14, except

at STA 760. The Group 13 tension tie modification similar to Group

1, except at STA 940. This group requires 142U0102-232 tension tie

modification kit.

13 -

Group 13 airplanes not modified in accordance with the Original

Issue, Revision 1, or Revision 2 of this service bulletin.

1

Group 13 airplanes that were modified in accordance with the Original

Issue, Revision 1, or Revision 2 of this service bulletin.

2

747-100 airplanes with tension ties from STA 760 to STA 940, and

a combination of tension ties at STA 760 and STA 940 that is unique.

The Group 14 tension tie modification is similar to Group 13, except

at STA 760. The Group 14 tension tie modification similar to Group

2, except at STA 940. This group requires 142U0102-232 tension tie

modification kit.

14 -

Group 14 airplanes not modified in accordance with the Original

Issue, Revision 1, or Revision 2 of this service bulletin.

1

Group 14 airplanes that were modified in accordance with the Original

Issue, Revision 1, or Revision 2 of this service bulletin.

2

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ALERT ALERT
GROUP CONFIGURATION DESCRIPTION

747-100 airplanes with tension ties from STA 840 to STA 940 that

have a unique configuration. This group requires 142U0102-232

tension tie modification kit.

15 -

Group 15 airplanes not modified in accordance with the Original

Issue, Revision 1, or Revision 2 of this service bulletin.

1

Group 15 airplanes that were modified in accordance with the Original

Issue, Revision 1, or Revision 2 of this service bulletin.

2

747-200C airplanes with tension ties from STA 800 to STA 940, and

a unique frame configuration.

16 -

Group 16 airplanes not modified in accordance with the Original

Issue, Revision 1, or Revision 2 of this service bulletin.

1

Group 16 airplanes that were modified in accordance with the Original

Issue, Revision 1, or Revision 2 of this service bulletin.

2

17 - 747SP airplanes that have tension ties from STA 1040 to STA 1140.

18 - 747SP airplanes that have tension ties from STA 1060 to STA 1140.

Airplane Models:

747-100, 747-100B, 747-200B, 747-200C, 747-200F, 747-400F, 747SP, 747SR

Variable Number Group

RA001 - RA025 13

RA026 11

RA027 - RA028 1

RA029 11

RA030 - RA032 1

RA033 11

RA034 1

RA101 - RA103 15

RA104 - RA110 14

RA111 - RA112 11

RA113 - RA115 2

RA161 - RA162 11

RA163 12

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ALERT ALERT
Variable Number Group

RA164 3

RA201 - RA203 14

RA216 1

RA217 3

RA245 1

RA246 4

RA251 - RA254 13

RA255 1

RA256 - RA266 3

RA301 - RA303 13

RA304 - RA306 1

RA307 - RA313 3

RA314 - RA317 4

RA318 6

RA351 - RA355 13

RA356 - RA360 1

RA369 - RA371 1

RA372 - RA373 3

RA401 - RA403 14

RA404 - RA412 2

RA413 3

RA414 - RA418 4

RA501 - RA502 1

RA521 - RA523 13

RA524 12

RA525 - RA528 3

RA532 - RA534 1

RA535 - RA543 3

RA544 - RA548 4

RA551 - RA552 13

RA559 - RA560 1

RA561 3

RA581 - RA582 1

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ALERT ALERT
Variable Number Group

RA585 3

RA601 - RA602 1

RA631 1

RA632 11

RA633 1

RA634 - RA635 12

RA651 - RA652 1

RA671 - RA674 1

RA675 - RA677 3

RA701 1

RA702 3

RA721 - RA722 1

RA723 - RA724 3

RA725 - RA731 4

RA741 - RA743 1

RA744 - RA745 3

RA749 - RA750 4

RA761 - RA762 1

RA781 1

RA782 - RA783 4

RA784 5

RA901 - RA902 15

RA903 - RA904 14

RA905 - RA909 2

RA910 - RA916 11

RB001 - RB016 4

RB041 15

RB042 14

RB043 15

RB044 2

RB071 - RB075 3

RB101 - RB102 1

RB411 - RB413 6

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ALERT ALERT
Variable Number Group

RB421 4

RB601 - RB603 4

RB604 - RB605 5

RB606 4

RB607 5

RB681 - RB695 6

RB696 7

RB697 6

RB711 6

RB721 - RB723 4

RB741 - RB748 4

RD001 - RD004 4

RD021 - RD022 4

RD041 5

RD042 4

RD043 - RD044 5

RD045 - RD054 4

RD055 5

RD056 - RD059 4

RD071 - RD072 4

RD081 4

RD082 - RD083 7

RD091 - RD092 6

RD101 - RD104 4

RD121 4

RD122 - RD127 6

RD131 - RD141 6

RD142 7

RD143 6

RD144 7

RD166 - RD167 6

RD171 - RD172 4

RD181 - RD183 6

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ALERT ALERT
Variable Number Group

RD201 - RD204 6

RD221 - RD224 6

RD225 7

RD226 6

RD227 7

RD231 - RD232 6

RD233 - RD235 7

RD241 - RD243 6

RD251 - RD262 4

RD271 - RD272 6

RD291 - RD292 6

RD301 - RD302 7

RD311 6

RD351 - RD357 6

RD358 7

RD361 - RD366 7

RD411 - RD412 7

RD413 - RD414 6

RD421 - RD426 6

RD431 - RD435 4

RD441 - RD442 7

RD451 - RD456 6

RD461 7

RD471 - RD475 6

RD513 - RD519 6

RD531 - RD533 6

RD551 5

RD561 6

RD571 4

RD581 - RD583 7

RD591 - RD593 6

RD621 4

RD622 - RD623 5

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ALERT ALERT
Variable Number Group

RD641 - RD643 7

RD644 - RD645 6

RD646 7

RD647 - RD649 6

RD651 - RD659 6

RD661 6

RD671 4

RD681 - RD682 6

RD691 7

RD692 6

RD701 - RD702 6

RD741 - RD742 6

RD751 6

RD752 7

RD753 - RD755 6

RD761 6

RD771 - RD775 6

RD781 - RD783 6

RD791 - RD792 6

RE001 6

RG001 - RG009 17

RG091 17

RG095 17

RG101 - RG104 17

RG121 - RG126 17

RG141 - RG142 17

RG161 - RG164 17

RG171 - RG174 17

RG191 - RG193 17

RG211 - RG213 17

RG221 - RG222 17

RH101 - RH102 18

RH111 - RH112 17

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ALERT ALERT
Variable Number Group

RH121 - RH122 17

RJ131 - RJ133 9

RJ151 - RJ152 9

RJ301 - RJ303 16

RJ321 - RJ322 16

RJ331 - RJ333 16

RL401 - RL403 10

RL411 - RL436 10

RL451 - RL456 10

RL461 - RL462 10

RL471 - RL481 10

RL491 - RL492 10

RL501 - RL502 10

RL511 - RL516 10

RL521 - RL522 10

RL531 - RL534 10

RL551 10

RL561 - RL568 10

RL571 - RL572 10

RL576 - RL577 10

RL579 10

RL581 - RL586 10

RL651 - RL655 10

RL671 - RL675 10

RL681 - RL684 10

RL751 - RL752 10

RM851 - RM859 10

RM861 - RM863 10

RM871 - RM899 10

RM901 - RM906 10

RM911 10

RR001 - RR005 8

RR021 - RR025 8

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ALERT ALERT
Variable Number Group

RR031 8

RR201 - RR206 8

RR221 - RR226 8

RR261 - RR267 8

RR301 - RR310 8

RR331 - RR332 8

RR336 8

RR341 - RR345 8

RR361 - RR362 8

RR421 - RR422 8

RR431 - RR432 8

RR441 - RR442 8

RR451 8

RR501 - RR504 8

RR521 - RR522 8

RR526 8

RR531 8

RR551 - RR556 8

RR561 8

RR566 8

RR701 10

RR721 - RR724 10

RR746 - RR748 10

RR851 - RR856 10

RR861 - RR862 10

RR951 - RR952 10

2. Spares Affected

None.

B. Concurrent Requirements

None.

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BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
C. Reason

This service bulletin gives instructions for modification of upper deck tension ties and adjacent frame

structure on non stretched upper deck (Non-SUD) airplanes. The tension ties have been determined

to be structure that is susceptible to Widespread Fatigue Damage (WFD). WFD can cause tension ties

to become severed or disconnected from the frames. Severed or disconnected Tension Ties and/or

Frames at multiple locations could result in rapid in-flight decompression.

For more information about WFD, refer to Boeing Service Letter 747-SL-53-088.

Service Bulletin 747-53A2502 recommends initial and repeat inspections of Non-SUD airplane tension

ties from body station (STA) 760 to STA 940 (STA 1040 to STA 1140 for 747SP). Service Bulletin

747-53A2502 was issued to address multiple reports of cracks found in tension ties and adjacent frame

structure.

Group 1-16:

Accomplishment of the modification in this service bulletin terminates the repeat inspection requirement

of Service Bulletin 747-53A2502.

Group 17-18:

Accomplishment of the modification in this service bulletin does not terminate the repeat inspection

requirement of Service Bulletin 747-53A2502, but a new inspection threshold is provided.

As a part of a service bulletin validation program, this modification and inspection was completed on

airplane RD041 by Service Bulletin 747-53A2605, Original Issue. The modification and inspection

completed on airplane RD041 by Service Bulletin 747-53A2605, Original Issue is equivalent to the

Revision 2 of this service bulletin. Airplane RD041 has the configuration of a Group 5 airplane.

Boeing Service Related Problem (SRP) 747-SRP-53-0200 and 747-SRP-53-0438 are related to this

service bulletin.

Revision 1 was sent to add more airplanes to the service bulletin effectivity and add Appendix A to give

information on methods for disconnecting tension ties.

Revision 2 was sent to tell operators that new retrofit drawings have been added for airplanes with

barrier net fittings installed under the shear ties located at frame station (STA) 860.

Subsequent to the release of Revision 2 of this service bulletin, Boeing has determined that additional

inspections are required in the center sections of the tension ties where the tension tie channels are

not replaced and where fastener holes are not zero-timed during modification.

Revision 3 is sent to add the requirement to do surface high frequency eddy current (HFEC) inspection

where fastener holes are not zero-timed during modification on Group 1-16 airplanes. Revision 3 also

adds instructions for post-modification inspection of the entire tension tie for Group 1-16 airplanes, and

adds effectivity and modification instructions for 747SP (Group 17-18) airplanes.

D. Description

Get access to the Frame to Tension Tie joints in Section 42. At each station, disconnect and remove

a section of the tension tie between the frame and approximate Buttock Line (BL) 36. For each frame,

remove a specified section of the frame above and below the tension tie attach point. After the existing

frame and tension tie structure has been removed and discarded, install new frame and tension tie

structure. Do the modification on both sides of the airplane.

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BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 1-16:

Do surface high frequency eddy current (HFEC) inspection of the tension ties at fastener locations

where the holes were not zero-timed during modification. If cracks are found, contact Boeing for repair

instructions and do the repair.

Group 1-16:

After modification, do initial and repeat detailed, high frequency eddy current (HFEC), and low frequency

eddy current (LFEC) inspections of the tension ties at the compliance time specified in paragraph 1.E.,

Compliance. If cracks are found, contact Boeing for repair instructions and do the repair.

Group 17-18:

After modification, do initial and repeat detailed and HFEC inspections for cracks in all tension ties,

adjacent frame structure, and adjacent structure that attaches to the tension ties. If cracks are found,

contact Boeing for repair instructions and do the repair.

Revision 1 - No more work is necessary on airplanes changed in accordance with the original issue of

this service bulletin.

Revision 2 - No more work is necessary on airplanes changed in accordance with the original issue or

Revision 1 of this service bulletin.

Revision 3 - More work is necessary on airplanes modified in accordance with the original issue,

Revision 1, or Revision 2 of this service bulletin. Airplanes previously modified in accordance with this

service bulletin will require surface high frequency eddy current (HFEC) inspection for cracks in the

forward and aft tension tie channels around fasteners in unmodified areas where fastener holes were

not zero-timed during modification. Refer to paragraph 1.E., Compliance for the compliance time of

this additional inspection. However, no additional modification is necessary.

The work in this service bulletin is done in the maintenance zone(s) given below.

Group 1, 3:

Affected Maintenance Zones

Model Zone

747-100, 747-200B 233, 234, 243, 244

Group 2, 11-15:

Affected Maintenance Zones

Model Zone

747-100 233, 234, 243, 244

Group 4, 6:

Affected Maintenance Zones

Model Zone

747-100, 747-100B, 747-200B, 233, 234, 243, 244

747SR

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ALERT ALERT
Group 5, 7:

Affected Maintenance Zones

Model Zone

747-200B, 747SR 233, 234, 243, 244

Group 8:

Affected Maintenance Zones

Model Zone

747-200F 233, 234, 243, 244

Group 9, 16:

Affected Maintenance Zones

Model Zone

747-200C 233, 234, 243, 244

Group 10:

Affected Maintenance Zones

Model Zone

747-400F 233, 234, 243, 244

Group 17-18:

Affected Maintenance Zones

Model Zone

747SP 243, 244

E. Compliance

Federal Aviation Administration (FAA) Airworthiness Directives AD 84-19-01, AD 94-13-06, AD

2004-07-22 R1, and AD 2012-13-08 are related to this service bulletin.

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ALERT ALERT
Group 1-16, Configuration 1:

Table 1: Tension Tie and Frame - Inspection and Modification

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Within 3,000 -

flight cycles after August 14,

2012 (the effective date of AD

2012-13-08).

Before 30,000

total flight cycles.

Do tension tie and frame modification in accordance with Paragraph

3.B., Work Instructions, PART 1.

(a)

All airplanes.

AND

Within 3,000 -

flight cycles after the Revision

3 date of this

service bulletin.

Concurrently

with modification in accordance with

Paragraph 3.B.,

Work Instructions, PART 1.

Do surface high frequency eddy

current (HFEC) inspections for

cracks in the tension tie center

sections in accordance with

Paragraph 3.B., Work Instructions, PART 4. (b)

Contact Boeing for repair instruc- Before further flight. -

tions, and do the repair.

Any crack found.

At the times specified in Para- -

graph 1.E., Compliance, Tables

2, 3 and 4, as applicable.

Do post-modification inspections

in accordance with Paragraph

1.E., Compliance, Tables 2, 3 and

4, as applicable.

No crack found.

(a) Due to the post-modification inspection requirements, Boeing does not recommend tension tie modification

prior to 15,000 total flight cycles.

(b) Boeing recommends accomplishment of the HFEC inspection before beginning the modification in case

cracks are found in the center section and repairs are necessary that may affect the modification.

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ALERT ALERT
Group 5, 7-8, 10-12, 15:

Table 2: Post-Modification Detailed Inspection of Unmodified Areas of the Tension Ties

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Within 6,000 flight cycles after -

modification in accordance with

Paragraph 3.B., Work Instructions,

PART 1.

Do a detailed inspection

for cracks in the unmodified areas of the tension

ties in accordance with

Paragraph 3.B., Work Instructions, PART 2.

Modification has been done

in accordance with Paragraph 3.B., Work Instructions, PART 1 of this service bulletin.

Repeat the detailed in- - 3,000 flight cycles.

spection for cracks in the

unmodified areas of the

tension ties in accordance with Paragraph

3.B., Work Instructions,

PART 2.

No crack found during inspection in accordance

with Paragraph 3.B., Work

Instructions, PART 2.

Contact Boeing for repair Before further flight. -

instructions, and do the

repair.

Any crack found during inspection in accordance

with Paragraph 3.B., Work

Instructions, PART 2. AND

Repeat the detailed in- - 3,000 flight cycles.

spection for cracks in the

unmodified areas of the

tension ties in accordance with Paragraph

3.B., Work Instructions,

PART 2.

Group 1-4, 6, 9, 13-14, 16:

Table 3: Post-Modification Detailed Inspection of Unmodified Areas of the Tension Ties

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Within 6,000 flight cycles after -

modification in accordance with

Paragraph 3.B., Work Instructions,

PART 1.

Do a detailed inspection

for cracks in the unmodified areas of the tension

ties in accordance with

Paragraph 3.B., Work Instructions, PART 2.

Modification has been done

in accordance with Paragraph 3.B., Work Instructions, PART 1 of this service bulletin.

Repeat the detailed in- - 4,000 flight cycles.

spection for cracks in the

unmodified areas of the

tension ties in accordance with Paragraph

3.B., Work Instructions,

PART 2.

No crack found during inspection in accordance

with Paragraph 3.B., Work

Instructions, PART 2.

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ALERT ALERT
Group 1-4, 6, 9, 13-14, 16:

Table 3: Post-Modification Detailed Inspection of Unmodified Areas of the Tension Ties

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Contact Boeing for repair Before further flight. -

instructions, and do the

repair.

Any crack found during inspection in accordance

with Paragraph 3.B., Work

Instructions, PART 2. AND

Repeat the detailed in- - 4,000 flight cycles.

spection for cracks in the

unmodified areas of the

tension ties in accordance with Paragraph

3.B., Work Instructions,

PART 2.

Group 1-16:

Table 4: Post-Modification Inspections of the Tension Ties in all Areas (Modified and Unmodified areas)

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Within 20,000 flight cycles after -

modification in accordance with

Paragraph 3.B., Work Instructions,

PART 1.

Do eddy current inspections for cracks in all areas of the tension ties in

accordance with Paragraph 3.B., Work Instructions, PART 3.

Modification has been done

in accordance with Paragraph 3.B., Work Instructions, PART 1 of this service bulletin.

Repeat the eddy current - 3,000 flight cycles.

inspections for cracks in

all areas of the tension

ties in accordance with

Paragraph 3.B., Work Instructions, PART 3.

No crack found during inspection in accordance

with Paragraph 3.B., Work

Instructions, PART 3.

Contact Boeing for repair Before further flight. -

instructions, and do the

repair.

Any crack found during inspection in accordance

with Paragraph 3.B., Work

Instructions, PART 3. AND

Repeat the eddy current - 3,000 flight cycles.

inspections for cracks in

all areas of the tension

ties in accordance with

Paragraph 3.B., Work Instructions, PART 3.

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ALERT ALERT
Group 1-16, Configuration 2:

Table 5: Surface HFEC Inspection of Unmodified Tension Tie Center Sections (More Work)

Condition Action Compliance Time (Whichever Occurs Later)

Within 1,000 flight cycles

after the Revision 3 date

of this service bulletin.

Within 3,000 flight cycles

after accomplishment of

the modification in accordance with Paragraph

3.B., Work Instructions,

PART 1.

Do a surface HFEC inspection for

cracks in unmodified center sections of the tension tie channels

in accordance with Paragraph

3.B., Work Instructions, PART 4.

All airplanes.

Contact Boeing for repair instruc- Before further flight. -

tions, and do the repair.

Any crack found.

No further action is required until - -

you begin inspections in accordance with Paragraph 1.E., Compliance, Tables 2, 3, and 4, as

applicable.

No crack found.

Group 17:

Table 6: Modification and Post-Modification Inspection of Tension Ties and Frame Segments

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Within 3,000 -

flight cycles after

August 14, 2012

(the effective

date of AD 2012-

13-08).

Before 30,000

total flight cycles.

At each station location

from STA 1040 to STA

1140, remove and replace

existing tension tie and

frame structure with new

structure which is the

same as the original production parts in accordance with Paragraph 3.B.,

Work Instructions, PART

5.

All airplanes.

4,000 flight cycles.Within 20,000 -

flight cycles after

the tension tie

and frame structure was replaced in accordance with Paragraph 3.B., Work

Instructions,

PART 5.

Do inspections of the replaced tension tie and

frame structure in accordance with Service Bulletin

747-53A2502.

Tension tie and frame

structure has been removed and replaced

with new parts in accordance with Paragraph

3.B., Work Instructions,

PART 5.

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ALERT ALERT
Group 18:

Table 7: Modification and Post-Modification Inspection of Tension Ties and Frame Segments

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Within 3,000 -

flight cycles after

August 14, 2012

(the effective

date of AD 2012-

13-08).

Before 30,000

total flight cycles.

At each station location

from STA 1060 to STA

1140, remove and replace

existing tension tie and

frame structure with new

structure which is the

same as the original production parts in accordance with Paragraph 3.B.,

Work Instructions, PART

6.

All airplanes.

4,000 flight cycles.Within 20,000 -

flight cycles after

the tension tie

and frame structure was replaced in accordance with Paragraph 3.B., Work

Instructions,

PART 6.

Do inspections of the replaced tension tie and

frame structure in accordance with Service Bulletin

747-53A2502.

Tension tie and frame

structure has been removed and replaced

with new parts in accordance with Paragraph

3.B., Work Instructions,

PART 6.

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.

This SB has been approved by the FAA. In addition, the Manager of the Seattle Aircraft Certification

Office (ACO) approves the accomplishment of the modification, post modification inspection and

corrective action with the corresponding compliance times specified in Table 1, under paragraph 1.E.,

"Compliance," of SB 747-53A2605, Revision 3, as an AMOC to the inspections and corrective action

required by paragraphs (h) and (i) of AD 2004-07-22 R1, for the inspection of Structural Significant

Item (SSI) F-19A of the Supplemental Structural Inspection Document (SSID) D6-35022, Revision G.

This AMOC only applies to the areas inspected by this service bulletin. When this SB specifies contacting

Boeing for repair instructions and post modification inspections, the repair instructions and post

modification inspections must be approved by the FAA in accordance with paragraph (I) of the AD. All

provisions of AD 2004-07-22 R1 that are not specifically referenced in this paragraph remain fully

applicable and must be complied with accordingly.

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Group 1-16:

In addition, the Manager of the Seattle ACO approves the accomplishment of the inspections,

modification, post-modification inspections, and related corrective actions with corresponding compliance

times specified in Tables 1, 2, 3, 4, and 5 (as applicable) under paragraph 1.E., "Compliance," of Service

Bulletin 747-53A2605, Revision 3 as an AMOC to the inspections, investigative actions, modification,

post-modification, and repair actions with corresponding compliance times required by paragraphs (g),

(h), (i), (j)(1), (k), and (l) of AD 2012-13-08. When this service bulletin specifies contacting Boeing for

repair instructions, the repair instructions must be approved by the FAA in accordance with paragraph

(n) of the AD. All provisions of AD 2012-13-08 that are not specifically referenced in this paragraph

remain fully applicable and must be complied with accordingly.

Group 17-18:

In addition, the Manager of the Seattle ACO approves the accomplishment of the modification and

post-modification inspections with corresponding compliance times specified in Table 6 or 7 (as

applicable) under paragraph 1.E., "Compliance," of Service Bulletin 747-53A2605, Revision 3 as an

AMOC to the inspections, investigative actions, corrective actions, modification, and post-modification

actions with corresponding compliance times required by paragraphs (g) and (j)(2) of AD 2012-13-08.

When this service bulletin specifies contacting Boeing for repair instructions, the repair instructions

must be approved by the FAA in accordance with paragraph (n) of the AD. All provisions of AD

2012-13-08 that are not specifically referenced in this paragraph remain fully applicable and must be

complied with accordingly.

In addition, the Manager of the Seattle ACO approves the accomplishment of the modification,

inspections and repair with the corresponding compliance times specified in Tables 1, 2, 3, 4, and 5

under paragraph 1.E., "Compliance," of Service Bulletin 747-53A2605, Revision 3 as an AMOC to the

inspections, repair and modification with the corresponding compliance times required by paragraphs

A. and B. of AD 84-19-01. When this service bulletin specifies contacting Boeing for repair instructions,

the repair instructions must be approved by the FAA in accordance with paragraph C. of the AD. All

provisions of AD 84-19-01 that are not specifically referenced in this paragraph, including but not limited

to repeat inspections in accordance with paragraphs A. and B. until the modification in accordance with

Service Bulletin 747-53A2605, Revision 3 is installed, remain fully applicable and must be complied

with accordingly.

In addition, the Manager of the Seattle ACO approves the accomplishment of the modification,

inspections and repair with the corresponding compliance times specified in Tables 1, 2, 3, 4, and 5

under paragraph 1.E., "Compliance," of Service Bulletin 747-53A2605, Revision 3 as an AMOC to the

inspections, repair and modification with the corresponding compliance times required by paragraphs

(a) and (b) of AD 94-13-06. When this service bulletin specifies contacting Boeing for repair instructions,

the repair instructions must be approved by the FAA in accordance with paragraph (c) of the AD. All

provisions of AD 94-13-06 that are not specifically referenced in this paragraph, including but not limited

to repeat inspections in accordance with paragraphs (a) and (b) until the modification in accordance

with Service Bulletin 747-53A2605, Revision 3 is installed, remain fully applicable and must be complied

with accordingly.

G. Manpower

The table below shows an estimate of the task hours necessary to do the modification 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

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— Time to inspect the work

— Time to cure the materials

— Time to make the parts

— Time to find the tools.

Task Number of Persons Task Hours Elapsed Hours

Access 4 24.00 6.00

Restoration 4 30.00 7.50

TOTAL FOR EACH AIRPLANE 54.00 13.50

Group 1-5, 8-9, 11-16:

Shear Panel Removal/Installation

Task Number of Persons Task Hours Elapsed Hours

Remove 2 10.00 5.00

Install 2 10.00 5.00

TOTAL FOR EACH AIRPLANE 20.00 10.00

Group 6-7:

Shear Panel Removal/Installation

Task Number of Persons Task Hours Elapsed Hours

Remove 2 10.00 5.00

Install 2 10.00 5.00

TOTAL FOR EACH AIRPLANE 20.00 10.00

Group 10:

Shear Panel Removal/Installation

Task Number of Persons Task Hours Elapsed Hours

Remove 2 10.00 5.00

Install 2 10.00 5.00

TOTAL FOR EACH AIRPLANE 20.00 10.00

Group 10:

STA 720 Tension Tie and Frame Modification

Task Number of Persons Task Hours Elapsed Hours

Remove 4 14.00 3.50

Install 4 14.00 3.50

TOTAL FOR EACH AIRPLANE 28.00 7.00

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Group 10:

STA 740 Tension Tie and Frame Modification

Task Number of Persons Task Hours Elapsed Hours

Remove 4 14.00 3.50

Install 4 14.00 3.50

TOTAL FOR EACH AIRPLANE 28.00 7.00

Group 1, 13:

STA 760 Tension Tie and Frame Modification

Task Number of Persons Task Hours Elapsed Hours

Remove 4 15.00 3.75

Install 4 15.00 3.75

TOTAL FOR EACH AIRPLANE 30.00 7.50

Group 2-3, 14:

STA 760 Tension Tie and Frame Modification

Task Number of Persons Task Hours Elapsed Hours

Remove 4 13.00 3.25

Install 4 13.00 3.25

TOTAL FOR EACH AIRPLANE 26.00 6.50

Group 10:

STA 760 Tension Tie and Frame Modification

Task Number of Persons Task Hours Elapsed Hours

Remove 4 12.00 3.00

Install 4 12.00 3.00

TOTAL FOR EACH AIRPLANE 24.00 6.00

Group 1-2, 8, 11, 13-15:

STA 780 Tension Tie and Frame Modification

Task Number of Persons Task Hours Elapsed Hours

Remove 4 14.00 3.50

Install 4 14.00 3.50

TOTAL FOR EACH AIRPLANE 28.00 7.00

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Group 3, 12:

STA 780 Tension Tie and Frame Modification

Task Number of Persons Task Hours Elapsed Hours

Remove 4 13.00 3.25

Install 4 13.00 3.25

TOTAL FOR EACH AIRPLANE 26.00 6.50

Group 10:

STA 780 Tension Tie and Frame Modification

Task Number of Persons Task Hours Elapsed Hours

Remove 4 10.00 2.50

Install 4 10.00 2.50

TOTAL FOR EACH AIRPLANE 20.00 5.00

Group 1-5, 8-9, 11-16:

STA 800 Tension Tie and Frame Modification

Task Number of Persons Task Hours Elapsed Hours

Remove 4 13.00 3.25

Install 4 13.00 3.25

TOTAL FOR EACH AIRPLANE 26.00 6.50

Group 10:

STA 800 Tension Tie and Frame Modification

Task Number of Persons Task Hours Elapsed Hours

Remove 4 10.00 2.50

Install 4 10.00 2.50

TOTAL FOR EACH AIRPLANE 20.00 5.00

Group 1-5, 9, 11-16:

STA 820 Tension Tie and Frame Modification

Task Number of Persons Task Hours Elapsed Hours

Remove 4 52.00 13.00

Install 4 52.00 13.00

TOTAL FOR EACH AIRPLANE 104.00 26.00

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Group 8, 10:

STA 820 Tension Tie and Frame Modification

Task Number of Persons Task Hours Elapsed Hours

Remove 4 55.00 13.75

Install 4 55.00 13.75

TOTAL FOR EACH AIRPLANE 110.00 27.50

Group 1-5, 9-16:

STA 840 Tension Tie and Frame Modification

Task Number of Persons Task Hours Elapsed Hours

Remove 4 48.00 12.00

Install 4 48.00 12.00

TOTAL FOR EACH AIRPLANE 96.00 24.00

Group 6-7:

STA 840 Tension Tie and Frame Modification

Task Number of Persons Task Hours Elapsed Hours

Remove 4 47.00 11.75

Install 4 47.00 11.75

TOTAL FOR EACH AIRPLANE 94.00 23.50

Group 8:

STA 840 Tension Tie and Frame Modification

Task Number of Persons Task Hours Elapsed Hours

Remove 4 52.00 13.00

Install 4 52.00 13.00

TOTAL FOR EACH AIRPLANE 104.00 26.00

Group 1-5, 8, 11-15:

STA 860 Tension Tie and Frame Modification

Task Number of Persons Task Hours Elapsed Hours

Remove 4 55.00 13.75

Install 4 55.00 13.75

TOTAL FOR EACH AIRPLANE 110.00 27.50

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ALERT ALERT
Group 6-7:

STA 860 Tension Tie and Frame Modification

Task Number of Persons Task Hours Elapsed Hours

Remove 4 52.00 13.00

Install 4 52.00 13.00

TOTAL FOR EACH AIRPLANE 104.00 26.00

Group 9, 16:

STA 860 Tension Tie and Frame Modification

Task Number of Persons Task Hours Elapsed Hours

Remove 4 54.00 13.50

Install 4 54.00 13.50

TOTAL FOR EACH AIRPLANE 108.00 27.00

Group 10:

STA 860 Tension Tie and Frame Modification

Task Number of Persons Task Hours Elapsed Hours

Remove 4 51.00 12.75

Install 4 51.00 12.75

TOTAL FOR EACH AIRPLANE 102.00 25.50

Group 1-9, 11-16:

STA 880 Tension Tie and Frame Modification

Task Number of Persons Task Hours Elapsed Hours

Remove 2 56.00 14.00

Install 2 56.00 14.00

TOTAL FOR EACH AIRPLANE 112.00 28.00

Group 10:

STA 880 Tension Tie and Frame Modification

Task Number of Persons Task Hours Elapsed Hours

Remove 4 50.00 12.50

Install 4 50.00 12.50

TOTAL FOR EACH AIRPLANE 100.00 25.00

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Group 1-4, 6, 13-14:

STA 900 Tension Tie and Frame Modification

Task Number of Persons Task Hours Elapsed Hours

Remove 4 52.00 13.00

Install 4 52.00 13.00

TOTAL FOR EACH AIRPLANE 104.00 26.00

Group 5, 7, 16:

STA 900 Tension Tie and Frame Modification

Task Number of Persons Task Hours Elapsed Hours

Remove 4 49.00 12.25

Install 4 49.00 12.25

TOTAL FOR EACH AIRPLANE 98.00 24.50

Group 8:

STA 900 Tension Tie and Frame Modification

Task Number of Persons Task Hours Elapsed Hours

Remove 4 51.00 12.75

Install 4 51.00 12.75

TOTAL FOR EACH AIRPLANE 102.00 25.50

Group 9-10:

STA 900 Tension Tie and Frame Modification

Task Number of Persons Task Hours Elapsed Hours

Remove 4 48.00 12.00

Install 4 48.00 12.00

TOTAL FOR EACH AIRPLANE 96.00 24.00

Group 11-12, 15:

STA 900 Tension Tie and Frame Modification

Task Number of Persons Task Hours Elapsed Hours

Remove 4 52.00 13.00

Install 4 52.00 13.00

TOTAL FOR EACH AIRPLANE 104.00 26.00

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ALERT ALERT
STA 920 Tension Tie and Frame Modification

Task Number of Persons Task Hours Elapsed Hours

Remove 4 50.00 12.50

Install 4 50.00 12.50

TOTAL FOR EACH AIRPLANE 100.00 25.00

Group 1-2, 11:

STA 940 Tension Tie and Frame Modification

Task Number of Persons Task Hours Elapsed Hours

Remove 4 57.00 14.25

Install 4 57.00 14.25

TOTAL FOR EACH AIRPLANE 114.00 28.50

Group 3-4, 6, 12:

STA 940 Tension Tie and Frame Modification

Task Number of Persons Task Hours Elapsed Hours

Remove 4 58.00 14.50

Install 4 58.00 14.50

TOTAL FOR EACH AIRPLANE 116.00 29.00

Group 5, 7, 9, 16:

STA 940 Tension Tie and Frame Modification

Task Number of Persons Task Hours Elapsed Hours

Remove 4 64.00 16.00

Install 4 64.00 16.00

TOTAL FOR EACH AIRPLANE 128.00 32.00

Group 8:

STA 940 Tension Tie and Frame Modification

Task Number of Persons Task Hours Elapsed Hours

Remove 4 56.00 14.00

Install 4 56.00 14.00

TOTAL FOR EACH AIRPLANE 112.00 28.00

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ALERT ALERT
Group 10:

STA 940 Tension Tie and Frame Modification

Task Number of Persons Task Hours Elapsed Hours

Remove 4 65.00 16.25

Install 4 65.00 16.25

TOTAL FOR EACH AIRPLANE 130.00 32.50

Group 13-15:

STA 940 Tension Tie and Frame Modification

Task Number of Persons Task Hours Elapsed Hours

Remove 4 52.00 13.00

Install 4 52.00 13.00

TOTAL FOR EACH AIRPLANE 104.00 26.00

Group 17:

STA 1040 - STA 1140 Tension Tie and Frame Modification

Task Number of Persons Task Hours Elapsed Hours

Remove 4 129.00 32.25

Install 4 258.00 64.50

TOTAL FOR EACH AIRPLANE 387.00 96.75

Group 18:

STA 1060 - STA 1140 Tension Tie and Frame Modification

Task Number of Persons Task Hours Elapsed Hours

Remove 4 108.00 27.00

Install 4 216.00 54.00

TOTAL FOR EACH AIRPLANE 324.00 81.00

Group 1-3, 13-14:

Surface HFEC Inspection of Tension Tie Center Sections

Task Number of Persons Task Hours Elapsed Hours

FIGURE 1 4 100.00 25.00

TOTAL FOR EACH AIRPLANE 100.00 25.00

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Group 4, 9:

Surface HFEC Inspection of Tension Tie Center Sections

Task Number of Persons Task Hours Elapsed Hours

FIGURE 2 4 80.00 20.00

TOTAL FOR EACH AIRPLANE 80.00 20.00

Group 5, 16:

Surface HFEC Inspection of Tension Tie Center Sections

Task Number of Persons Task Hours Elapsed Hours

FIGURE 3 4 70.00 17.50

TOTAL FOR EACH AIRPLANE 70.00 17.50

Group 6:

Surface HFEC Inspection of Tension Tie Center Sections

Task Number of Persons Task Hours Elapsed Hours

FIGURE 4 4 60.00 15.00

TOTAL FOR EACH AIRPLANE 60.00 15.00

Group 7:

Surface HFEC Inspection of Tension Tie Center Sections

Task Number of Persons Task Hours Elapsed Hours

FIGURE 5 4 50.00 12.50

TOTAL FOR EACH AIRPLANE 50.00 12.50

Group 8, 11-12, 15:

Surface HFEC Inspection of Tension Tie Center Sections

Task Number of Persons Task Hours Elapsed Hours

FIGURE 6 4 80.00 20.00

TOTAL FOR EACH AIRPLANE 80.00 20.00

Group 10:

Surface HFEC Inspection of Tension Tie Center Sections

Task Number of Persons Task Hours Elapsed Hours

FIGURE 7 4 120.00 30.00

TOTAL FOR EACH AIRPLANE 120.00 30.00

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Group 1-16:

Post-Modification Inspections of All Areas of the Tension Ties

Task Number of Persons Task Hours Elapsed Hours

FIGURE 8 2 18.00 (a) 9.00 (a)

FIGURE 9 2 18.00 (a) 9.00 (a)

TOTAL FOR EACH TENSION TIE (a) (a)

(a) Estimates given are for each tension tie location. Multiply the estimates by the

number of tension ties to determine the total estimate for the airplane.

H. Weight and Balance Changes

Group 1-2, 13-14:

Change in Moment

(Pound-Inches)

Change in Weight

Airplane (Pounds)

747-100, 747-200B +286.2 +247016.2

Group 3:

Change in Moment

(Pound-Inches)

Change in Weight

Airplane (Pounds)

747-100, 747-200B +280.2 +241382.6

Group 4-5, 9, 16:

Change in Moment

(Pound-Inches)

Change in Weight

Airplane (Pounds)

747-100, 747-100B, +243.8 +213354.9

747-200B, 747SR,

747-200C

Group 6-7:

Change in Moment

(Pound-Inches)

Change in Weight

Airplane (Pounds)

747-100, 747-100B, +193.9 +172879.8

747-200B, 747SR

Group 8, 12:

Change in Moment

(Pound-Inches)

Change in Weight

Airplane (Pounds)

747-100, 747-200F +262.0 +227550.8

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ALERT ALERT
Group 10:

Change in Moment

(Pound-Inches)

Change in Weight

Airplane (Pounds)

747-400F +322.6 +273811.8

Group 11, 15:

Change in Moment

(Pound-Inches)

Change in Weight

Airplane (Pounds)

747-100 +268.0 +233184.4

Group 17-18:

None.

I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. Engineering Change Memo PRR 85901-68RS

b. Boeing Service Bulletin 747-53A2502, 747-53A2605

c. Boeing Service Letter 747-SL-51-048, 747-SL-53-088

d. Boeing Service Related Problem (SRP) 747-SRP-53-0200, 747-SRP-53-0438

e. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2004-07-22 R1, 2012-13-08,

84-19-01, 94-13-06

f. Standard Overhaul Practices Manual (SOPM) 20-41-01, 20-41-05, 20-43-03

g. 747 Non-Destructive Testing (NDT) Manual Part 6, 51-00-00, Part 6, 51-00-26

h. 747-100/200/300 Aircraft Maintenance Manual (AMM) 24-22-00, 25-21-04, 25-22-01, 25-25-01

i. 747-100/200/300 Structural Repair Manual (SRM) 51-10-01, 51-30-09

j. 747-400 Aircraft Maintenance Manual (AMM) 24-22-00, 25-21-04, 25-22-01, 25-25-01

k. 747-400F Structural Repair Manual (SRM) 51-10-02, 51-40-09

2. Data Supplied with this Service Bulletin:

a. Drawings:

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ALERT ALERT
Drawing No Title Sheet DCN/REV ADCN

TOP KIT - FRAME AND TENSION TIE 1 A -

MODIFICATION, STA 720 - STA 940

142U0100

10 - -

11 - -

12 A -

13 A -

14 - -

15 - -

2 - -

3 - -

4 - -

5 - -

6 A -

7 - -

8 A -

9 A -

TOP KIT - FRAME AND TENSION TIE KPL A -

MODIFICATION

142U0100-1001

TOP KIT - FRAME AND TENSION TIE KPL A -

MODIFICATION

142U0100-1002

TOP KIT - FRAME AND TENSION TIE KPL A -

MODIFICATION

142U0100-1003

TOP KIT - FRAME AND TENSION TIE KPL B -

MODIFICATION

142U0100-1004

TOP KIT - FRAME AND TENSION TIE KPL B -

MODIFICATION

142U0100-1005

TOP KIT - FRAME AND TENSION TIE KPL A -

MODIFICATION

142U0100-1006

TOP KIT - FRAME AND TENSION TIE KPL B -

MODIFICATION

142U0100-1007

TOP KIT - FRAME AND TENSION TIE KPL C -

MODIFICATION

142U0100-1008

TOP KIT - FRAME AND TENSION TIE KPL B -

MODIFICATION

142U0100-1009

TOP KIT - FRAME AND TENSION TIE KPL B -

MODIFICATION

142U0100-1010

TOP KIT - FRAME AND TENSION TIE KPL B -

MODIFICATION

142U0100-1011

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ALERT ALERT
Drawing No Title Sheet DCN/REV ADCN

TOP KIT - FRAME AND TENSION TIE KPL B -

MODIFICATION

142U0100-1012

TOP KIT - FRAME AND TENSION TIE KPL A -

MODIFICATION

142U0100-1013

TOP KIT - FRAME AND TENSION TIE KPL A -

MODIFICATION

142U0100-2001

TOP KIT - FRAME AND TENSION TIE KPL A -

MODIFICATION

142U0100-2002

KIT - FRAME MODIFICATION, STA 820 - 1 - -

STA 940

142U0101

10 - -

11 - -

12 - -

13 - -

14 - -

15 - -

16 A -

17 - -

18 A -

19 - -

2 - -

20 - -

21 - -

22 - -

23 - -

24 - -

3 - -

4 - -

5 A -

6 A -

7 - -

8 A -

9 - -

KIT - FRAME MODIFICATION, STA 820 - PSDL C -

STA 940

142U0101#DL

142U0101-101 KIT - FRAME MODIFICATION KPL A -

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ALERT ALERT
Drawing No Title Sheet DCN/REV ADCN

142U0101-102 KIT - FRAME MODIFICATION KPL A -

142U0101-103 KIT - FRAME MODIFICATION KPL A -

142U0101-104 KIT - FRAME MODIFICATION KPL A -

142U0101-105 KIT - FRAME MODIFICATION KPL A -

142U0101-106 KIT - FRAME MODIFICATION KPL A -

142U0101-107 KIT - FRAME MODIFICATION KPL A -

142U0101-108 KIT - FRAME MODIFICATION KPL A -

142U0101-109 KIT - FRAME MODIFICATION KPL A -

142U0101-110 KIT - FRAME MODIFICATION KPL A -

142U0101-111 KIT - FRAME MODIFICATION KPL A -

142U0101-112 KIT - FRAME MODIFICATION KPL A -

142U0101-113 KIT - FRAME MODIFICATION KPL A -

142U0101-114 KIT - FRAME MODIFICATION KPL A -

142U0101-115 KIT - FRAME MODIFICATION KPL A -

142U0101-116 KIT - FRAME MODIFICATION KPL A -

142U0101-117 KIT - FRAME MODIFICATION KPL A -

142U0101-119 KIT - FRAME MODIFICATION KPL A -

142U0101-120 KIT - FRAME MODIFICATION KPL A -

142U0101-121 KIT - FRAME MODIFICATION KPL A -

142U0101-123 KIT - FRAME MODIFICATION KPL A -

142U0101-124 KIT - FRAME MODIFICATION KPL A -

142U0101-125 KIT - FRAME MODIFICATION KPL A -

142U0101-126 KIT - FRAME MODIFICATION KPL A -

142U0101-127 KIT - FRAME MODIFICATION KPL A -

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ALERT ALERT
Drawing No Title Sheet DCN/REV ADCN

KIT - TENSION TIE MODIFICATION, STA 1 A -

720 - STA 940

142U0102

10 A -

11 A -

12 A -

13 A -

14 A -

15 B -

16 B -

17 A -

18 A -

19 A -

2 A -

20 A -

21 A -

22 A -

23 A -

24 A -

25 A -

26 A -

27 A -

28 A -

29 A -

3 A -

30 A -

31 A -

32 A -

33 A -

34 - -

35 - -

36 - -

37 - -

4 A -

5 A -

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BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Drawing No Title Sheet DCN/REV ADCN

6 - A

7 A -

8 A -

9 A -

KIT - TENSION TIE MODIFICATION, STA PSDL A -

720 - STA 940

142U0102#DL

142U0102-201 KIT - TENSION TIE MODIFICATION KPL B -

142U0102-202 KIT - TENSION TIE MODIFICATION KPL B -

142U0102-203 KIT - TENSION TIE MODIFICATION KPL B -

142U0102-204 KIT - TENSION TIE MODIFICATION KPL B -

142U0102-205 KIT - TENSION TIE MODIFICATION KPL B -

142U0102-206 KIT - TENSION TIE MODIFICATION KPL B -

142U0102-207 KIT - TENSION TIE MODIFICATION KPL B -

142U0102-208 KIT - TENSION TIE MODIFICATION KPL B -

142U0102-209 KIT - TENSION TIE MODIFICATION KPL B -

142U0102-210 KIT - TENSION TIE MODIFICATION KPL B -

142U0102-211 KIT - TENSION TIE MODIFICATION KPL B -

142U0102-212 KIT - TENSION TIE MODIFICATION KPL B -

142U0102-213 KIT - TENSION TIE MODIFICATION KPL B -

142U0102-214 KIT - TENSION TIE MODIFICATION KPL B -

142U0102-215 KIT - TENSION TIE MODIFICATION KPL B -

142U0102-216 KIT - TENSION TIE MODIFICATION KPL B -

142U0102-217 KIT - TENSION TIE MODIFICATION KPL B -

142U0102-218 KIT - TENSION TIE MODIFICATION KPL B -

142U0102-219 KIT - TENSION TIE MODIFICATION KPL B -

142U0102-220 KIT - TENSION TIE MODIFICATION KPL B -

142U0102-221 KIT - TENSION TIE MODIFICATION KPL B -

142U0102-222 KIT - TENSION TIE MODIFICATION KPL B -

142U0102-223 KIT - TENSION TIE MODIFICATION KPL B -

142U0102-224 KIT - TENSION TIE MODIFICATION KPL B -

142U0102-225 KIT - TENSION TIE MODIFICATION KPL B -

142U0102-226 KIT - TENSION TIE MODIFICATION KPL B -

142U0102-227 KIT - TENSION TIE MODIFICATION KPL B -

Export Controlled ECCN: 9E991 - BOEING

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ALERT ALERT
Drawing No Title Sheet DCN/REV ADCN

142U0102-228 KIT - TENSION TIE MODIFICATION KPL B -

142U0102-229 KIT - TENSION TIE MODIFICATION KPL B -

142U0102-230 KIT - TENSION TIE MODIFICATION KPL B -

142U0102-231 KIT - TENSION TIE MODIFICATION KPL B -

142U0102-232 KIT - TENSION TIE MODIFICATION KPL B -

142U0102-233 KIT - TENSION TIE MODIFICATION KPL B -

142U0102-234 KIT - TENSION TIE MODIFICATION KPL A -

142U0102-235 KIT - TENSION TIE MODIFICATION KPL A -

142U0102-301 KIT - TENSION TIE MODIFICATION KPL A -

142U0102-302 KIT - TENSION TIE MODIFICATION KPL A -

142U0102-303 KIT - TENSION TIE MODIFICATION KPL A -

624U0077 TENSION TIE - INSPECTION 1 - -

2 - -

65B01745 FRAME INSTL - STA 1040 4 F -

6 B -

7 A -

PL Y -

PSDL - -

65B01746 FRAME INSTL - STA 1060 1 H -

4 E -

6 C -

7 A -

8 - -

PL AA -

PSDL - -

65B01747 FRAME INSTL - STA 1080 1 G -

4 E -

6 C -

7 A -

8 - -

PL Y -

PSDL - -

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ALERT ALERT
Drawing No Title Sheet DCN/REV ADCN

65B01748 FRAME INSTL - STA 1100 4 E -

6 B -

7 A -

PL Y -

PSDL - -

65B01749 FRAME INSTL - STA 1120 4 D -

7 C -

8 A -

PL Y -

PSDL - -

TENSION TIE INSTL - AFT OF UPPER 10 C -

DECK FLOOR

65B09631

9 E -

PL AG -

PSDL - -

BULKHEAD INSTL - MID SPAR BODY - 2 C -

STA 1140

65B18703

3 B -

4 A -

PL A -

PSDL - -

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

None.

K. Publications Affected

1. Publications

Publication Chapter-Section

747-100/200/300 Structural Repair Manual 53-11

747-400F Structural Repair Manual 53-20

2. Damage Tolerance Based Structural Inspections:

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. DTI requirements for the structure affected

are contained in Paragraph 1.E., Compliance of this service bulletin.

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ALERT ALERT
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.

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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

Price as of the Revision 02 date of this

Service Bulletin (US

Dollars)

ROLT as of the Revision 02 date of this

Service Bulletin

(Calendar Days)

Kit Number Name Date QTY

TOP KIT - TENSION TIE AND 8/26/09 1 399 635,004.00

FRAME MODIFICATION

142U0100-1001

TOP KIT - TENSION TIE AND (a) - 399 634,277.00

FRAME MODIFICATION

142U0100-1002

TOP KIT - TENSION TIE AND 8/28/09 1 399 655,323.00

FRAME MODIFICATION

142U0100-1003

TOP KIT - TENSION TIE AND 8/31/09 1 399 623,027.00

FRAME MODIFICATION

142U0100-1004

TOP KIT - TENSION TIE AND 9/03/09 1 399 623,719.00

FRAME MODIFICATION

142U0100-1005

TOP KIT - TENSION TIE AND 9/04/09 1 399 535,131.00

FRAME MODIFICATION

142U0100-1006

TOP KIT - TENSION TIE AND 9/08/09 1 399 535,823.00

FRAME MODIFICATION

142U0100-1007

TOP KIT - TENSION TIE AND 9/10/09 1 399 645,067.00

FRAME MODIFICATION

142U0100-1008

TOP KIT - TENSION TIE AND (a) - 399 623,537.00

FRAME MODIFICATION

142U0100-1009

TOP KIT - TENSION TIE AND (a) - 399 658,423.00

FRAME MODIFICATION

142U0100-1010

TOP KIT - TENSION TIE AND 9/11/09 1 399 618,575.00

FRAME MODIFICATION

142U0100-1011

TOP KIT - TENSION TIE AND (a) - 399 639,219.00

FRAME MODIFICATION

142U0100-1012

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ALERT ALERT
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

Price as of the Revision 02 date of this

Service Bulletin (US

Dollars)

ROLT as of the Revision 02 date of this

Service Bulletin

(Calendar Days)

Kit Number Name Date QTY

TOP KIT - FRAME AND TEN- (a) - (a) 623,268.00

SION TIE MODIFICATION

142U0100-1013

TOP KIT - TENSION TIE AND (a) - 399 18,657.00

FRAME MODIFICATION

142U0100-2001

TOP KIT - TENSION TIE AND (a) - 399 21,288.00

FRAME MODIFICATION

142U0100-2002

(a) Contact Boeing Spares for kit availability.

NOTE: Due to the limited number of kits available and the long ROLT, Boeing recommends that

operators submit purchase orders 18 months in advance of performing the modification.

B. Industry Support Information

Boeing warranty remedies are not available for the inspection or modification procedures given in this

service bulletin.

C. Parts Necessary for Each Airplane

1. Kits/Parts:

NOTE: The top kits shown in the table that follows and the items shown in Paragraph 2.C.2.,

Parts and Materials Supplied by the Operator, are necessary for each airplane.

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

Group(s) Top Kit

1 142U0100-1001 and 142U0100-2002

2 142U0100-1002 and 142U0100-2002

3 142U0100-1003

4 142U0100-1004

5 142U0100-1005

6 142U0100-1006

7 142U0100-1007

8 142U0100-1008

9 142U0100-1009

10 142U0100-1010

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ALERT ALERT
Group(s) Top Kit

11 142U0100-1011 and 142U0100-2002

12 142U0100-1012

13 142U0100-1001 and 142U0100-2001

14 142U0100-1002 and 142U0100-2001

15 142U0100-1011 and 142U0100-2001

16 142U0100-1013

17-18 (a)

(a) Only operator supplied parts are needed for Group 17-18.

Group 1, 13:

Kit 142U0100

New Part Number QTY Name Existing Part Number Notes

-1001

KIT - FRAME MODIFICATION, STA 820142U0101-101 1

KIT - FRAME MODIFICATION, STA 840142U0101-104 1

KIT - FRAME MODIFICATION, STA 860142U0101-107 1

KIT - FRAME MODIFICATION, STA 880142U0101-111 1

KIT - FRAME MODIFICATION, STA 900142U0101-113 1

KIT - FRAME MODIFICATION, STA 920142U0101-117 1

KIT - FRAME MODIFICATION, STA 940142U0101-121 1

KIT - TENSION TIE MODIFICATION, STA 760142U0102-203 1

KIT - TENSION TIE MODIFICATION, STA 780142U0102-207 1

KIT - TENSION TIE MODIFICATION, STA 800142U0102-210 1

KIT - TENSION TIE MODIFICATION, STA 820142U0102-212 1

KIT - TENSION TIE MODIFICATION, STA 840142U0102-214 1

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ALERT ALERT
Group 1, 13:

Kit 142U0100

New Part Number QTY Name Existing Part Number Notes

-1001

KIT - TENSION TIE MODIFICATION, STA 860142U0102-217 1

KIT - TENSION TIE MODIFICATION, STA 880142U0102-220 1

KIT - TENSION TIE MODIFICATION, STA 900142U0102-222 1

KIT - TENSION TIE MODIFICATION, STA 920142U0102-225 1

KIT - SHEAR PANEL INSTL

- TENSION TIE MODIFICATION

142U0102-301 1

Group 2, 14:

Kit 142U0100

New Part Number QTY Name Existing Part Number Notes

-1002

KIT - FRAME MODIFICATION, STA 820142U0101-101 1

KIT - FRAME MODIFICATION, STA 840142U0101-104 1

KIT - FRAME MODIFICATION, STA 860142U0101-107 1

KIT - FRAME MODIFICATION, STA 880142U0101-111 1

KIT - FRAME MODIFICATION, STA 900142U0101-113 1

KIT - FRAME MODIFICATION, STA 920142U0101-117 1

KIT - FRAME MODIFICATION, STA 940142U0101-121 1

KIT - TENSION TIE MODIFICATION, STA 760142U0102-204 1

KIT - TENSION TIE MODIFICATION, STA 780142U0102-207 1

KIT - TENSION TIE MODIFICATION, STA 800142U0102-210 1

Export Controlled ECCN: 9E991 - BOEING

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ALERT ALERT
Group 2, 14:

Kit 142U0100

New Part Number QTY Name Existing Part Number Notes

-1002

KIT - TENSION TIE MODIFICATION, STA 820142U0102-212 1

KIT - TENSION TIE MODIFICATION, STA 840142U0102-214 1

KIT - TENSION TIE MODIFICATION, STA 860142U0102-217 1

KIT - TENSION TIE MODIFICATION, STA 880142U0102-220 1

KIT - TENSION TIE MODIFICATION, STA 900142U0102-222 1

KIT - TENSION TIE MODIFICATION, STA 920142U0102-225 1

KIT - SHEAR PANEL INSTL

- TENSION TIE MODIFICATION

142U0102-301 1

Group 3:

Kit 142U0100

New Part Number QTY Name Existing Part Number Notes

-1003

KIT - FRAME MODIFICATION, STA 820142U0101-101 1

KIT - FRAME MODIFICATION, STA 840142U0101-104 1

KIT - FRAME MODIFICATION, STA 860142U0101-107 1

KIT - FRAME MODIFICATION, STA 880142U0101-111 1

KIT - FRAME MODIFICATION, STA 900142U0101-113 1

KIT - FRAME MODIFICATION, STA 920142U0101-117 1

KIT - FRAME MODIFICATION, STA 940142U0101-121 1

KIT - TENSION TIE MODIFICATION, STA 760142U0102-205 1

Export Controlled ECCN: 9E991 - BOEING

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ALERT ALERT
Group 3:

Kit 142U0100

New Part Number QTY Name Existing Part Number Notes

-1003

KIT - TENSION TIE MODIFICATION, STA 780142U0102-208 1

KIT - TENSION TIE MODIFICATION, STA 800142U0102-210 1

KIT - TENSION TIE MODIFICATION, STA 820142U0102-212 1

KIT - TENSION TIE MODIFICATION, STA 840142U0102-214 1

KIT - TENSION TIE MODIFICATION, STA 860142U0102-217 1

KIT - TENSION TIE MODIFICATION, STA 880142U0102-220 1

KIT - TENSION TIE MODIFICATION, STA 900142U0102-222 1

KIT - TENSION TIE MODIFICATION, STA 920142U0102-225 1

KIT - TENSION TIE MODIFICATION, STA 940142U0102-229 1

KIT - SHEAR PANEL INSTL

- TENSION TIE MODIFICATION

142U0102-301 1

Group 4:

Kit 142U0100

New Part Number QTY Name Existing Part Number Notes

-1004

KIT - FRAME MODIFICATION, STA 820142U0101-101 1

KIT - FRAME MODIFICATION, STA 840142U0101-104 1

KIT - FRAME MODIFICATION, STA 860142U0101-107 1

KIT - FRAME MODIFICATION, STA 880142U0101-111 1

KIT - FRAME MODIFICATION, STA 900142U0101-113 1

Export Controlled ECCN: 9E991 - BOEING

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ALERT ALERT
Group 4:

Kit 142U0100

New Part Number QTY Name Existing Part Number Notes

-1004

KIT - FRAME MODIFICATION, STA 920142U0101-117 1

KIT - FRAME MODIFICATION, STA 940142U0101-121 1

KIT - TENSION TIE MODIFICATION, STA 800142U0102-210 1

KIT - TENSION TIE MODIFICATION, STA 820142U0102-212 1

KIT - TENSION TIE MODIFICATION, STA 840142U0102-214 1

KIT - TENSION TIE MODIFICATION, STA 860142U0102-217 1

KIT - TENSION TIE MODIFICATION, STA 880142U0102-220 1

KIT - TENSION TIE MODIFICATION, STA 900142U0102-222 1

KIT - TENSION TIE MODIFICATION, STA 920142U0102-225 1

KIT - TENSION TIE MODIFICATION, STA 940142U0102-229 1

KIT - SHEAR PANEL INSTL

- TENSION TIE MODIFICATION

142U0102-301 1

Group 5:

Kit 142U0100

New Part Number QTY Name Existing Part Number Notes

-1005

KIT - FRAME MODIFICATION, STA 820142U0101-101 1

KIT - FRAME MODIFICATION, STA 840142U0101-104 1

KIT - FRAME MODIFICATION, STA 860142U0101-107 1

Export Controlled ECCN: 9E991 - BOEING

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ALERT ALERT
Group 5:

Kit 142U0100

New Part Number QTY Name Existing Part Number Notes

-1005

KIT - FRAME MODIFICATION, STA 880142U0101-111 1

KIT - FRAME MODIFICATION, STA 900142U0101-125 1

KIT - FRAME MODIFICATION, STA 920142U0101-126 1

KIT - FRAME MODIFICATION, STA 940142U0101-127 1

KIT - TENSION TIE MODIFICATION, STA 800142U0102-210 1

KIT - TENSION TIE MODIFICATION, STA 820142U0102-212 1

KIT - TENSION TIE MODIFICATION, STA 840142U0102-214 1

KIT - TENSION TIE MODIFICATION, STA 860142U0102-217 1

KIT - TENSION TIE MODIFICATION, STA 880142U0102-220 1

KIT - TENSION TIE MODIFICATION, STA 920142U0102-226 1

KIT - TENSION TIE MODIFICATION, STA 940142U0102-230 1

KIT - TENSION TIE MODIFICATION, STA 900142U0102-235 1

KIT - SHEAR PANEL INSTL

- TENSION TIE MODIFICATION

142U0102-301 1

Group 6:

Kit 142U0100

New Part Number QTY Name Existing Part Number Notes

-1006

KIT - FRAME MODIFICATION, STA 840142U0101-104 1

KIT - FRAME MODIFICATION, STA 860142U0101-107 1

Export Controlled ECCN: 9E991 - BOEING

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ALERT ALERT
Group 6:

Kit 142U0100

New Part Number QTY Name Existing Part Number Notes

-1006

KIT - FRAME MODIFICATION, STA 880142U0101-111 1

KIT - FRAME MODIFICATION, STA 900142U0101-113 1

KIT - FRAME MODIFICATION, STA 920142U0101-117 1

KIT - FRAME MODIFICATION, STA 940142U0101-121 1

KIT - TENSION TIE MODIFICATION, STA 840142U0102-215 1

KIT - TENSION TIE MODIFICATION, STA 860142U0102-218 1

KIT - TENSION TIE MODIFICATION, STA 880142U0102-220 1

KIT - TENSION TIE MODIFICATION, STA 900142U0102-222 1

KIT - TENSION TIE MODIFICATION, STA 920142U0102-225 1

KIT - TENSION TIE MODIFICATION, STA 940142U0102-229 1

KIT - SHEAR PANEL INSTL

- TENSION TIE MODIFICATION

142U0102-302 1

Group 7:

Kit 142U0100

New Part Number QTY Name Existing Part Number Notes

-1007

KIT - FRAME MODIFICATION, STA 840142U0101-104 1

KIT - FRAME MODIFICATION, STA 860142U0101-107 1

KIT - FRAME MODIFICATION, STA 880142U0101-111 1

KIT - FRAME MODIFICATION, STA 900142U0101-125 1

Export Controlled ECCN: 9E991 - BOEING

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ALERT ALERT
Group 7:

Kit 142U0100

New Part Number QTY Name Existing Part Number Notes

-1007

KIT - FRAME MODIFICATION, STA 920142U0101-126 1

KIT - FRAME MODIFICATION, STA 940142U0101-127 1

KIT - TENSION TIE MODIFICATION, STA 840142U0102-215 1

KIT - TENSION TIE MODIFICATION, STA 860142U0102-218 1

KIT - TENSION TIE MODIFICATION, STA 880142U0102-220 1

KIT - TENSION TIE MODIFICATION, STA 920142U0102-226 1

KIT - TENSION TIE MODIFICATION, STA 940142U0102-230 1

KIT - TENSION TIE MODIFICATION, STA 900142U0102-235 1

KIT - SHEAR PANEL INSTL

- TENSION TIE MODIFICATION

142U0102-302 1

Group 8:

Kit 142U0100

New Part Number QTY Name Existing Part Number Notes

-1008

KIT - FRAME MODIFICATION, STA 820142U0101-102 1

KIT - FRAME MODIFICATION, STA 840142U0101-105 1

KIT - FRAME MODIFICATION, STA 860142U0101-108 1

KIT - FRAME MODIFICATION, STA 880142U0101-111 1

KIT - FRAME MODIFICATION, STA 900142U0101-114 1

Export Controlled ECCN: 9E991 - BOEING

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ALERT ALERT
Group 8:

Kit 142U0100

New Part Number QTY Name Existing Part Number Notes

-1008

KIT - FRAME MODIFICATION, STA 920142U0101-117 1

KIT - FRAME MODIFICATION, STA 940142U0101-121 1

KIT - TENSION TIE MODIFICATION, STA 780142U0102-207 1

KIT - TENSION TIE MODIFICATION, STA 800142U0102-210 1

KIT - TENSION TIE MODIFICATION, STA 820142U0102-212 1

KIT - TENSION TIE MODIFICATION, STA 840142U0102-214 1

KIT - TENSION TIE MODIFICATION, STA 860142U0102-217 1

KIT - TENSION TIE MODIFICATION, STA 880142U0102-220 1

KIT - TENSION TIE MODIFICATION, STA 920142U0102-225 1

KIT - TENSION TIE MODIFICATION, STA 940142U0102-228 1

KIT - TENSION TIE MODIFICATION, STA 900142U0102-234 1

KIT - SHEAR PANEL INSTL

- TENSION TIE MODIFICATION

142U0102-301 1

Group 9:

Kit 142U0100

New Part Number QTY Name Existing Part Number Notes

-1009

KIT - FRAME MODIFICATION, STA 820142U0101-101 1

KIT - FRAME MODIFICATION, STA 840142U0101-104 1

KIT - FRAME MODIFICATION, STA 860142U0101-109 1

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ALERT ALERT
Group 9:

Kit 142U0100

New Part Number QTY Name Existing Part Number Notes

-1009

KIT - FRAME MODIFICATION, STA 880142U0101-111 1

KIT - FRAME MODIFICATION, STA 900142U0101-115 1

KIT - FRAME MODIFICATION, STA 920142U0101-119 1

KIT - FRAME MODIFICATION, STA 940142U0101-123 1

KIT - TENSION TIE MODIFICATION, STA 800142U0102-210 1

KIT - TENSION TIE MODIFICATION, STA 820142U0102-212 1

KIT - TENSION TIE MODIFICATION, STA 840142U0102-214 1

KIT - TENSION TIE MODIFICATION, STA 860142U0102-217 1

KIT - TENSION TIE MODIFICATION, STA 880142U0102-220 1

KIT - TENSION TIE MODIFICATION, STA 900142U0102-223 1

KIT - TENSION TIE MODIFICATION, STA 920142U0102-226 1

KIT - TENSION TIE MODIFICATION, STA 940142U0102-230 1

KIT - SHEAR PANEL INSTL

- TENSION TIE MODIFICATION

142U0102-301 1

Group 10:

Kit 142U0100

New Part Number QTY Name Existing Part Number Notes

-1010

KIT - FRAME MODIFICATION, STA 820142U0101-103 1

KIT - FRAME MODIFICATION, STA 840142U0101-106 1

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

62 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 10:

Kit 142U0100

New Part Number QTY Name Existing Part Number Notes

-1010

KIT - FRAME MODIFICATION, STA 860142U0101-110 1

KIT - FRAME MODIFICATION, STA 880142U0101-112 1

KIT - FRAME MODIFICATION, STA 900142U0101-116 1

KIT - FRAME MODIFICATION, STA 920142U0101-120 1

KIT - FRAME MODIFICATION, STA 940142U0101-124 1

KIT - TENSION TIE MODIFICATION, STA 720142U0102-201 1

KIT - TENSION TIE MODIFICATION, STA 740142U0102-202 1

KIT - TENSION TIE MODIFICATION, STA 760142U0102-206 1

KIT - TENSION TIE MODIFICATION, STA 780142U0102-209 1

KIT - TENSION TIE MODIFICATION, STA 800142U0102-211 1

KIT - TENSION TIE MODIFICATION, STA 820142U0102-213 1

KIT - TENSION TIE MODIFICATION, STA 840142U0102-216 1

KIT - TENSION TIE MODIFICATION, STA 860142U0102-219 1

KIT - TENSION TIE MODIFICATION, STA 880142U0102-221 1

KIT - TENSION TIE MODIFICATION, STA 900142U0102-224 1

KIT - TENSION TIE MODIFICATION, STA 920142U0102-227 1

KIT - TENSION TIE MODIFICATION, STA 940142U0102-231 1

KIT - SHEAR PANEL INSTL - TENSION TIE MODIFICATION142U0102-303 1

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

63 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 11, 15:

Kit 142U0100

New Part Number QTY Name Existing Part Number Notes

-1011

KIT - FRAME MODIFICATION, STA 820142U0101-101 1

KIT - FRAME MODIFICATION, STA 840142U0101-104 1

KIT - FRAME MODIFICATION, STA 860142U0101-107 1

KIT - FRAME MODIFICATION, STA 880142U0101-111 1

KIT - FRAME MODIFICATION, STA 900142U0101-113 1

KIT - FRAME MODIFICATION, STA 920142U0101-117 1

KIT - FRAME MODIFICATION, STA 940142U0101-121 1

KIT - TENSION TIE MODIFICATION, STA 780142U0102-207 1

KIT - TENSION TIE MODIFICATION, STA 800142U0102-210 1

KIT - TENSION TIE MODIFICATION, STA 820142U0102-212 1

KIT - TENSION TIE MODIFICATION, STA 840142U0102-214 1

KIT - TENSION TIE MODIFICATION, STA 860142U0102-217 1

KIT - TENSION TIE MODIFICATION, STA 880142U0102-220 1

KIT - TENSION TIE MODIFICATION, STA 920142U0102-225 1

KIT - TENSION TIE MODIFICATION, STA 900142U0102-234 1

KIT - SHEAR PANEL INSTL

- TENSION TIE MODIFICATION

142U0102-301 1

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

64 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 12:

Kit 142U0100

New Part Number QTY Name Existing Part Number Notes

-1012

KIT - FRAME MODIFICATION, STA 820142U0101-101 1

KIT - FRAME MODIFICATION, STA 840142U0101-104 1

KIT - FRAME MODIFICATION, STA 860142U0101-107 1

KIT - FRAME MODIFICATION, STA 880142U0101-111 1

KIT - FRAME MODIFICATION, STA 900142U0101-113 1

KIT - FRAME MODIFICATION, STA 920142U0101-117 1

KIT - FRAME MODIFICATION, STA 940142U0101-121 1

KIT - TENSION TIE MODIFICATION, STA 780142U0102-208 1

KIT - TENSION TIE MODIFICATION, STA 800142U0102-210 1

KIT - TENSION TIE MODIFICATION, STA 820142U0102-212 1

KIT - TENSION TIE MODIFICATION, STA 840142U0102-214 1

KIT - TENSION TIE MODIFICATION, STA 860142U0102-217 1

KIT - TENSION TIE MODIFICATION, STA 880142U0102-220 1

KIT - TENSION TIE MODIFICATION, STA 920142U0102-225 1

KIT - TENSION TIE MODIFICATION, STA 940142U0102-229 1

KIT - TENSION TIE MODIFICATION, STA 900142U0102-234 1

KIT - SHEAR PANEL INSTL

- TENSION TIE MODIFICATION

142U0102-301 1

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

65 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 16:

Kit 142U0100

New Part Number QTY Name Existing Part Number Notes

-1013

KIT - FRAME MODIFICATION, STA 820142U0101-101 1

KIT - FRAME MODIFICATION, STA 840142U0101-104 1

KIT - FRAME MODIFICATION, STA 860142U0101-109 1

KIT - FRAME MODIFICATION, STA 880142U0101-111 1

KIT - FRAME MODIFICATION, STA 900142U0101-115 1

KIT - FRAME MODIFICATION, STA 920142U0101-119 1

KIT - FRAME MODIFICATION, STA 940142U0101-123 1

KIT - TENSION TIE MODIFICATION, STA 800142U0102-210 1

KIT - TENSION TIE MODIFICATION, STA 820142U0102-212 1

KIT - TENSION TIE MODIFICATION, STA 840142U0102-214 1

KIT - TENSION TIE MODIFICATION, STA 860142U0102-217 1

KIT - TENSION TIE MODIFICATION, STA 880142U0102-220 1

KIT - TENSION TIE MODIFICATION, STA 920142U0102-226 1

KIT - TENSION TIE MODIFICATION, STA 940142U0102-230 1

KIT - TENSION TIE MODIFICATION, STA 900142U0102-235 1

KIT - SHEAR PANEL INSTL

- TENSION TIE MODIFICATION

142U0102-301 1

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

66 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 13-15:

Kit 142U0100

New Part Number QTY Name Existing Part Number Notes

-2001

KIT - TENSION TIE MODIFICATION, STA 940142U0102-232 1

Group 1-2, 11:

Kit 142U0100

New Part Number QTY Name Existing Part Number Notes

-2002

KIT - TENSION TIE MODIFICATION, STA 940142U0102-233 1

Group 1-5, 9, 11-16:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-101

142U0106-11 2 STRAP

142U0106-19 2 STRAP

142U0106-21 2 STRAP

142U0107-23 1 FRAME SEGMENT

142U0107-24 1 FRAME SEGMENT

142U0107-27 1 TRIPLER

142U0107-28 1 TRIPLER

142U0107-29 1 DOUBLER

142U0107-30 1 DOUBLER

142U0107-55 2 STIFFENER

142U0108-11 2 STRINGER CLIP TEE

142U0108-12 2 STRINGER CLIP TEE

142U0108-47 1 SHEAR TIE TEE, S-11 TO S-12

142U0108-48 1 SHEAR TIE TEE, S-11 TO S-12

142U0108-49 2 SHEAR TIE TEE, S-10A TO S-11

142U0108-50 2 SHEAR TIE TEE, S-10 TO S-10A

142U0108-51 2 SHEAR TIE TEE, S-9 TO S-10

142U0108-53 2 SHEAR TIE, S-8 TO S-9

142U0108-54 2 CHORD SPLICE - UPPER

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

67 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 1-5, 9, 11-16:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-101

142U0108-55 1 CHORD SEGMENT

142U0108-56 1 CHORD SEGMENT

142U0108-115 2 CHORD SPLICE - LOWER

142U0108-117 1 STIFFENER

142U0108-118 1 STIFFENER

142U0108-119 2 STIFFENER

144U0064-6 2 STRINGER CLIP TEE

144U0064-7 2 STRINGER CLIP TEE

144U0064-8 8 STRINGER CLIP TEE

144U0064-9 8 STRINGER CLIP TEE

69B41412-3 2 INSULATOR

BACB2D018B0F0 2 BRACKET, ANGLE

BACB30NW6K5Y 88 BOLT, 100 DEG HEX DR

BACB30NW6K6X 26 BOLT, 100 DEG HEX DR

BACB30NX6K3 139 BOLT, PROTRUDING HD

BACB30NX6K3X 4 BOLT, PROTRUDING HD

BACB30NX6K3Y 48 BOLT, PROTRUDING HD

BACB30NX6K4 238 BOLT, PROTRUDING HD

BACB30NX6K4X 31 BOLT, PROTRUDING HD

BACB30NX6K4Y 27 BOLT, PROTRUDING HD

BACB30NX6K5 201 BOLT

BACB30NX6K5X 2 BOLT, PROTRUDING HD

BACB30NX6K5Y 12 BOLT, PROTRUDING HD

BACB30NX6K6 40 BOLT

BACB30NX6K7 46 HI-LOK

BACB30NX6K7X 18 BOLT, PROTRUDING HD

BACB30NX6K8 112 BOLT, PROTRUDING HD

BACB30NX6K8X 13 BOLT, PROTRUDING HD

BACB30NX6K9X 2 BOLT, PROTRUDING HD

BACC30AC6 83 COLLAR

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

68 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 1-5, 9, 11-16:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-101

BACC30BH6 840 COLLAR

BACC30M6 26 COLLAR

BACC30R6 88 COLLAR

BACF3H05JF008HN 4 RADIUS FILLER

BACF3T01B10-40 8 FILLER, TAPERED

BACN10TL3A12 2 NUT STANDOFF

BACR15BB12AD8C 2 RIVET, UNIVERSAL HD

BACR15BB4AD5C 4 RIVETS

BACR15BB4AD6C 4 RIVET

BACR15BB6AD4C 26 RIVET, UNIVERSAL HD

BACR15BB8AD6C 2 RIVET, UNIVERSAL HD

BACR15GF6D5 26 RIVET

BACS40R005C005F 4 SHIM,LAMINATED

BACS40R008B035F 4 SHIM, LAMINATED

BACS40R008B038F 4 SHIM, LAMINATED

Group 8:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-102

142U0106-23 2 STRAP

142U0106-25 2 STRAP

142U0106-27 2 STRAP

142U0107-23 1 FRAME SEGMENT

142U0107-24 1 FRAME SEGMENT

142U0107-25 1 DOUBLER

142U0107-26 1 DOUBLER

142U0107-27 1 TRIPLER

142U0107-28 1 TRIPLER

142U0107-55 2 STIFFENER

142U0108-11 4 STRINGER CLIP TEE

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

69 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 8:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-102

142U0108-12 4 STRINGER CLIP TEE

142U0108-47 1 SHEAR TIE TEE, S-11 TO S-12

142U0108-48 1 SHEAR TIE TEE, S-11 TO S-12

142U0108-49 2 SHEAR TIE TEE, S-10A TO S-11

142U0108-50 2 SHEAR TIE TEE, S-10 TO S-10A

142U0108-51 2 SHEAR TIE TEE, S-9 TO S-10

142U0108-53 2 SHEAR TIE, S-8 TO S-9

142U0108-54 2 CHORD SPLICE - UPPER

142U0108-55 1 CHORD SEGMENT

142U0108-56 1 CHORD SEGMENT

142U0108-115 2 CHORD SPLICE - LOWER

142U0108-117 1 STIFFENER

142U0108-118 1 STIFFENER

142U0108-119 2 STIFFENER

144U0064-6 2 STRINGER CLIP TEE

144U0064-7 2 STRINGER CLIP TEE

144U0064-8 8 STRINGER CLIP TEE

144U0064-9 8 STRINGER CLIP TEE

BACB2D016B0F0 2 BRACKET, ANGLE

BACB30NW6K5Y 88 BOLT, 100 DEG HEX DR

BACB30NX6K3 113 BOLT, PROTRUDING HD

BACB30NX6K3X 29 BOLT, PROTRUDING HD

BACB30NX6K3Y 136 BOLT, PROTRUDING HD

BACB30NX6K4 222 BOLT, PROTRUDING HD

BACB30NX6K4X 20 BOLT, PROTRUDING HD

BACB30NX6K4Y 86 BOLT, PROTRUDING HD

BACB30NX6K5 196 BOLT

BACB30NX6K5X 6 BOLT, PROTRUDING HD

BACB30NX6K5Y 22 BOLT, PROTRUDING HD

BACB30NX6K6 40 BOLT

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

70 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 8:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-102

BACB30NX6K6Y 6 BOLT, PROTRUDING HD

BACB30NX6K7 42 HI-LOK

BACB30NX6K7X 24 BOLT, PROTRUDING HD

BACB30NX6K7Y 4 BOLT, PROTRUDING HD

BACB30NX6K8 103 BOLT, PROTRUDING HD

BACB30NX6K8X 6 BOLT, PROTRUDING HD

BACB30NX6K8Y 6 BOLT, PROTRUDING HD

BACB30NX6K9X 2 BOLT, PROTRUDING HD

BACC30AC6 262 COLLAR

BACC30BH6 775 COLLAR

BACC30M6 26 COLLAR

BACC30R6 88 COLLAR

BACF3H05JF008HN 2 RADIUS FILLER

BACF3T01B10-40 8 FILLER, TAPERED

BACN10TL3A6 2 SPACER PLATE NUT

BACR15BB12AD8C 2 RIVET, UNIVERSAL HD

BACR15BB4AD5C 4 RIVETS

BACR15BB6AD4C 26 RIVET, UNIVERSAL HD

BACR15BB8AD6C 2 RIVET, UNIVERSAL HD

BACR15GF6D5 26 RIVET

BACS40R005C005F 4 SHIM,LAMINATED

BACS40R008B035F 4 SHIM, LAMINATED

BACS40R008B038F 4 SHIM, LAMINATED

Group 10:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-103

142U0106-3 2 STRAP

142U0106-27 2 STRAP

142U0106-41 2 STRAP

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

71 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 10:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-103

142U0107-23 1 FRAME SEGMENT

142U0107-24 1 FRAME SEGMENT

142U0107-25 1 DOUBLER

142U0107-26 1 DOUBLER

142U0107-27 1 TRIPLER

142U0107-28 1 TRIPLER

142U0107-55 4 STIFFENER

142U0108-11 4 STRINGER CLIP TEE

142U0108-12 4 STRINGER CLIP TEE

142U0108-47 1 SHEAR TIE TEE, S-11 TO S-12

142U0108-48 1 SHEAR TIE TEE, S-11 TO S-12

142U0108-49 2 SHEAR TIE TEE, S-10A TO S-11

142U0108-50 2 SHEAR TIE TEE, S-10 TO S-10A

142U0108-51 2 SHEAR TIE TEE, S-9 TO S-10

142U0108-52 2 SHEAR TIE TEE, S-8 TO S-9

142U0108-54 2 CHORD SPLICE - UPPER

142U0108-77 1 CHORD SEGMENT

142U0108-78 1 CHORD SEGMENT

142U0108-115 2 CHORD SPLICE - LOWER

144U0064-6 10 STRINGER CLIP TEE

144U0064-7 10 STRINGER CLIP TEE

BACB30NW6K6X 26 BOLT, 100 DEG HEX DR

BACB30NW6K6Y 106 BOLT, 100 DEG HEX DR

BACB30NX6K3 189 BOLT, PROTRUDING HD

BACB30NX6K3X 29 BOLT, PROTRUDING HD

BACB30NX6K3Y 29 BOLT, PROTRUDING HD

BACB30NX6K4 209 BOLT, PROTRUDING HD

BACB30NX6K4X 53 BOLT, PROTRUDING HD

BACB30NX6K4Y 62 BOLT, PROTRUDING HD

BACB30NX6K5 196 BOLT

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

72 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 10:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-103

BACB30NX6K5X 20 BOLT, PROTRUDING HD

BACB30NX6K5Y 2 BOLT, PROTRUDING HD

BACB30NX6K6 53 BOLT

BACB30NX6K6Y 6 BOLT, PROTRUDING HD

BACB30NX6K7 42 HI-LOK

BACB30NX6K7X 26 BOLT, PROTRUDING HD

BACB30NX6K8 110 BOLT, PROTRUDING HD

BACB30NX6K8X 13 BOLT, PROTRUDING HD

BACB30NX6K9X 2 BOLT, PROTRUDING HD

BACC30AC6 100 COLLAR

BACC30BH6 941 COLLAR

BACC30M6 26 COLLAR

BACC30R6 106 COLLAR

BACF3T01B10-40 8 FILLER, TAPERED

BACR15BB12AD8C 2 RIVET, UNIVERSAL HD

BACR15BB6AD4C 31 RIVET, UNIVERSAL HD

BACR15BB8AD6C 2 RIVET, UNIVERSAL HD

BACR15GF6D5 31 RIVET

BACS40R005C005F 4 SHIM,LAMINATED

BACS40R008B035F 4 SHIM, LAMINATED

BACS40R008B038F 4 SHIM, LAMINATED

Group 1-7, 9, 11-16:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-104

142U0106-15 2 STRAP

142U0106-29 2 STRAP

142U0106-31 2 STRAP

142U0107-39 4 STIFFENER

142U0107-41 1 FRAME SEGMENT

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

73 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 1-7, 9, 11-16:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-104

142U0107-42 1 FRAME SEGMENT

142U0107-43 1 DOUBLER

142U0107-44 1 DOUBLER

142U0107-45 1 TRIPLER

142U0107-46 1 TRIPLER

142U0108-11 2 STRINGER CLIP TEE

142U0108-12 2 STRINGER CLIP TEE

142U0108-79 2 SHEAR TIE, S-8 TO S-9

142U0108-81 2 SHEAR TIE TEE, S-9 TO S-10

SHEAR TIE TEE, S-10 TO S-10A

/ S-10A TO S-11

142U0108-83 4

142U0108-85 1 SHEAR TIE TEE, S-11 TO S-12

142U0108-86 1 SHEAR TIE TEE, S-11 TO S-12

142U0108-87 2 CHORD SPLICE - UPPER

142U0108-89 2 CHORD SPLICE - LOWER

142U0108-91 1 CHORD SEGMENT

142U0108-92 1 CHORD SEGMENT

144U0064-8 10 STRINGER CLIP TEE

144U0064-9 10 STRINGER CLIP TEE

69B41412-3 2 INSULATOR

BACB2D018B0F0 2 BRACKET, ANGLE

BACB30NW6K5Y 88 BOLT, 100 DEG HEX DR

BACB30NW6K6X 27 BOLT, 100 DEG HEX DR

BACB30NW6K7Y 2 BOLT, 100 DEG HEX DR

BACB30NX6K3 110 BOLT, PROTRUDING HD

BACB30NX6K3X 4 BOLT, PROTRUDING HD

BACB30NX6K3Y 29 BOLT, PROTRUDING HD

BACB30NX6K4 216 BOLT, PROTRUDING HD

BACB30NX6K4X 18 BOLT, PROTRUDING HD

BACB30NX6K4Y 20 BOLT, PROTRUDING HD

BACB30NX6K5 190 BOLT

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

74 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 1-7, 9, 11-16:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-104

BACB30NX6K5X 2 BOLT, PROTRUDING HD

BACB30NX6K5Y 11 BOLT, PROTRUDING HD

BACB30NX6K6 40 BOLT

BACB30NX6K6X 4 BOLT, PROTRUDING HD

BACB30NX6K7 47 HI-LOK

BACB30NX6K7X 14 BOLT, PROTRUDING HD

BACB30NX6K8 104 BOLT, PROTRUDING HD

BACB30NX6K8X 6 BOLT, PROTRUDING HD

BACB30NX6K9X 2 BOLT, PROTRUDING HD

BACC30AC6 60 COLLAR

BACC30BH6 748 COLLAR

BACC30M6 27 COLLAR

BACC30R6 90 COLLAR

BACF3T01B10-40 8 FILLER, TAPERED

BACN10TL3A12 2 NUT STANDOFF

BACR15BB4AD5C 4 RIVETS

BACR15BB4AD6C 4 RIVET

BACR15BB6AD4C 27 RIVET, UNIVERSAL HD

BACR15GF6D5 27 RIVET

BACS40R005C005F 4 SHIM,LAMINATED

BACS40R007B034F 4 SHIM,LAMINATED

BACS40R008B038F 4 SHIM, LAMINATED

Group 8:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-105

142U0106-17 2 STRAP

142U0106-29 2 STRAP

142U0106-31 2 STRAP

142U0107-39 4 STIFFENER

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

75 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 8:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-105

142U0107-41 1 FRAME SEGMENT

142U0107-42 1 FRAME SEGMENT

142U0107-45 1 TRIPLER

142U0107-46 1 TRIPLER

142U0107-47 1 DOUBLER

142U0107-48 1 DOUBLER

142U0108-11 4 STRINGER CLIP TEE

142U0108-12 4 STRINGER CLIP TEE

142U0108-79 2 SHEAR TIE, S-8 TO S-9

142U0108-81 2 SHEAR TIE TEE, S-9 TO S-10

SHEAR TIE TEE, S-10 TO S-10A

/ S-10A TO S-11

142U0108-83 4

142U0108-85 1 SHEAR TIE TEE, S-11 TO S-12

142U0108-86 1 SHEAR TIE TEE, S-11 TO S-12

142U0108-87 2 CHORD SPLICE - UPPER

142U0108-89 2 CHORD SPLICE - LOWER

142U0108-91 1 CHORD SEGMENT

142U0108-92 1 CHORD SEGMENT

144U0064-8 10 STRINGER CLIP TEE

144U0064-9 10 STRINGER CLIP TEE

BACB2D017B0G0 2 BRACKET, ANGLE

BACB30NW6K5Y 88 BOLT, 100 DEG HEX DR

BACB30NW6K6X 27 BOLT, 100 DEG HEX DR

BACB30NX6K3 154 BOLT, PROTRUDING HD

BACB30NX6K3X 4 BOLT, PROTRUDING HD

BACB30NX6K3Y 60 BOLT, PROTRUDING HD

BACB30NX6K4 214 BOLT, PROTRUDING HD

BACB30NX6K4X 29 BOLT, PROTRUDING HD

BACB30NX6K4Y 62 BOLT, PROTRUDING HD

BACB30NX6K5 190 BOLT

BACB30NX6K5X 8 BOLT, PROTRUDING HD

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

76 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 8:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-105

BACB30NX6K5Y 11 BOLT, PROTRUDING HD

BACB30NX6K6 36 BOLT

BACB30NX6K6X 4 BOLT, PROTRUDING HD

BACB30NX6K7 47 HI-LOK

BACB30NX6K7X 16 BOLT, PROTRUDING HD

BACB30NX6K8 106 BOLT, PROTRUDING HD

BACB30NX6K8X 6 BOLT, PROTRUDING HD

BACB30NX6K9X 2 BOLT, PROTRUDING HD

BACB30YP6K7 2 BOLT, 100 DEG HEX DR

BACC30AC6 132 COLLAR

BACC30BH6 805 COLLAR

BACC30M6 27 COLLAR

BACC30R6 88 COLLAR

BACF3T01B10-40 8 FILLER, TAPERED

BACN10TL3A6 2 SPACER PLATE NUT

BACR15BB4AD5C 4 RIVETS

BACR15BB6AD4C 27 RIVET, UNIVERSAL HD

BACR15GF6D5 27 RIVET

BACS40R005C005F 4 SHIM,LAMINATED

BACS40R007B034F 4 SHIM,LAMINATED

BACS40R007B038F 4 SHIM, LAMINATED

Group 10:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-106

142U0106-17 2 STRAP

142U0106-29 2 STRAP

142U0106-31 2 STRAP

142U0107-39 4 STIFFENER

142U0107-41 1 FRAME SEGMENT

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

77 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 10:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-106

142U0107-42 1 FRAME SEGMENT

142U0107-43 1 DOUBLER

142U0107-44 1 DOUBLER

142U0107-45 1 TRIPLER

142U0107-46 1 TRIPLER

142U0108-11 2 STRINGER CLIP TEE

142U0108-12 2 STRINGER CLIP TEE

142U0108-81 2 SHEAR TIE TEE, S-9 TO S-10

SHEAR TIE TEE, S-10 TO S-10A

/ S-10A TO S-11

142U0108-83 4

142U0108-85 1 SHEAR TIE TEE, S-11 TO S-12

142U0108-86 1 SHEAR TIE TEE, S-11 TO S-12

142U0108-87 2 CHORD SPLICE - UPPER

142U0108-89 2 CHORD SPLICE - LOWER

142U0108-91 1 CHORD SEGMENT

142U0108-92 1 CHORD SEGMENT

142U0108-93 2 SHEAR TIE TEE, S-8 TO S-9

144U0064-8 10 STRINGER CLIP TEE

144U0064-9 10 STRINGER CLIP TEE

BACB2C024E0E0 1 BRACKET, ANGLE

BACB30NW6K5Y 106 BOLT, 100 DEG HEX DR

BACB30NW6K6X 27 BOLT, 100 DEG HEX DR

BACB30NX6K3 105 BOLT, PROTRUDING HD

BACB30NX6K3X 18 BOLT, PROTRUDING HD

BACB30NX6K3Y 33 BOLT, PROTRUDING HD

BACB30NX6K4 202 BOLT, PROTRUDING HD

BACB30NX6K4X 18 BOLT, PROTRUDING HD

BACB30NX6K4Y 31 BOLT, PROTRUDING HD

BACB30NX6K5 193 BOLT

BACB30NX6K5X 4 BOLT, PROTRUDING HD

BACB30NX6K5Y 11 BOLT, PROTRUDING HD

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

78 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 10:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-106

BACB30NX6K6 36 BOLT

BACB30NX6K6X 4 BOLT, PROTRUDING HD

BACB30NX6K7 58 HI-LOK

BACB30NX6K7X 16 BOLT, PROTRUDING HD

BACB30NX6K8 104 BOLT, PROTRUDING HD

BACB30NX6K8X 6 BOLT, PROTRUDING HD

BACB30NX6K9X 2 BOLT, PROTRUDING HD

BACC30AC6 75 COLLAR

BACC30BH6 765 COLLAR

BACC30M6 27 COLLAR

BACC30R6 105 COLLAR

BACF3T01B10-40 8 FILLER, TAPERED

BACR15BB6AD4C 27 RIVET, UNIVERSAL HD

BACR15GF6D5 27 RIVET

BACS40R005C005F 4 SHIM,LAMINATED

BACS40R007B034F 4 SHIM,LAMINATED

BACS40R007B038F 4 SHIM, LAMINATED

BACS53B1ES1 2 ELECTRICAL GROUND STUD

Group 1-7, 11-15:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-107

142U0106-5 2 DOUBLER

142U0106-6 2 STRAP

142U0106-7 2 STRAP

142U0106-8 2 STRAP

142U0106-59 2 FILLER

142U0107-13 1 FRAME SEGMENT

142U0107-14 1 FRAME SEGMENT

142U0107-15 1 DOUBLER

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

79 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 1-7, 11-15:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-107

142U0107-16 1 DOUBLER

142U0107-17 1 DOUBLER

142U0107-18 1 DOUBLER

142U0108-13 1 SHEAR TIE, S-7 TO S-8

142U0108-14 1 SHEAR TIE, S-7 TO S-8

142U0108-15 1 SHEAR TIE, S-11 TO S-12

142U0108-16 1 SHEAR TIE, S-11 TO S-12

142U0108-35 4 ANGLE

142U0108-36 4 ANGLE

142U0108-37 2 CHORD SPLICE - UPPER

142U0108-38 2 CHORD SPLICE - LOWER

142U0108-39 1 CHORD SEGMENT

142U0108-40 1 CHORD SEGMENT

142U0108-41 2 SHEAR TIE TEE, S-8 TO S-9

142U0108-42 2 SHEAR TIE TEE, S-9 TO S-10

SHEAR TIE TEE, S-10 TO S-10A

/ S-10A TO S-11

142U0108-43 4

144U0064-6 14 STRINGER CLIP TEE

144U0064-7 14 STRINGER CLIP TEE

69B41412-3 2 INSULATOR

BACB2D018B0F0 2 BRACKET, ANGLE

BACB30NW6K5Y 117 BOLT, 100 DEG HEX DR

BACB30NW6K6X 14 BOLT, 100 DEG HEX DR

BACB30NX6K10X 2 BOLT, PROTRUDING HD

BACB30NX6K2X 2 BOLT, PROTRUDING HD

BACB30NX6K3 91 BOLT, PROTRUDING HD

BACB30NX6K3X 14 BOLT, PROTRUDING HD

BACB30NX6K3Y 31 BOLT, PROTRUDING HD

BACB30NX6K4 20 BOLT, PROTRUDING HD

BACB30NX6K4X 6 BOLT, PROTRUDING HD

BACB30NX6K5 379 BOLT

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

80 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 1-7, 11-15:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-107

BACB30NX6K5X 11 BOLT, PROTRUDING HD

BACB30NX6K5Y 6 BOLT, PROTRUDING HD

BACB30NX6K6 97 BOLT

BACB30NX6K6X 8 BOLT, PROTRUDING HD

BACB30NX6K6Y 2 BOLT, PROTRUDING HD

BACB30NX6K7 31 HI-LOK

BACB30NX6K7X 8 BOLT, PROTRUDING HD

BACB30NX6K8 181 BOLT, PROTRUDING HD

BACB30NX6K8X 29 BOLT, PROTRUDING HD

BACB30NX6K9 14 BOLT

BACB30NX8K3X 6 BOLT, PROTRUDING HD

BACB30NX8K5X 2 BOLT, PROTRUDING HD

BACB30NX8K6X 2 BOLT, PROTRUDING HD

BACB30NX8K8X 4 BOLT, PROTRUDING HD

BACC30AC6 36 COLLAR

BACC30BH6 893 COLLAR

BACC30BH8 14 COLLAR

BACC30M6 131 COLLAR

BACF3T01B10-40 8 FILLER, TAPERED

BACN10TL3A12 2 NUT STANDOFF

BACR15BB4AD5C 4 RIVETS

BACR15BB4AD6C 4 RIVET

BACR15BB6AD4C 31 RIVET, UNIVERSAL HD

BACR15GF6D5 31 RIVET

BACS40R005C005F 4 SHIM,LAMINATED

BACS40R008A043F 4 SHIM, LAMINATED

BACS40R008B038F 4 SHIM, LAMINATED

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

81 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 8:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-108

142U0106-5 2 DOUBLER

142U0106-6 2 STRAP

142U0106-7 2 STRAP

142U0106-8 2 STRAP

142U0106-60 2 FILLER

142U0107-13 1 FRAME SEGMENT

142U0107-14 1 FRAME SEGMENT

142U0107-15 1 DOUBLER

142U0107-16 1 DOUBLER

142U0107-17 1 DOUBLER

142U0107-18 1 DOUBLER

142U0108-13 1 SHEAR TIE, S-7 TO S-8

142U0108-14 1 SHEAR TIE, S-7 TO S-8

142U0108-15 1 SHEAR TIE, S-11 TO S-12

142U0108-16 1 SHEAR TIE, S-11 TO S-12

142U0108-35 4 ANGLE

142U0108-36 4 ANGLE

142U0108-37 2 CHORD SPLICE - UPPER

142U0108-38 2 CHORD SPLICE - LOWER

142U0108-39 1 CHORD SEGMENT

142U0108-40 1 CHORD SEGMENT

142U0108-41 2 SHEAR TIE TEE, S-8 TO S-9

142U0108-42 2 SHEAR TIE TEE, S-9 TO S-10

SHEAR TIE TEE, S-10 TO S-10A

/ S-10A TO S-11

142U0108-43 4

144U0064-6 14 STRINGER CLIP TEE

144U0064-7 14 STRINGER CLIP TEE

69B41412-3 2 INSULATOR

BACB2D018B0F0 2 BRACKET, ANGLE

BACB30NW6K5Y 104 BOLT, 100 DEG HEX DR

BACB30NW6K6X 14 BOLT, 100 DEG HEX DR

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

82 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 8:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-108

BACB30NX6K3 102 BOLT, PROTRUDING HD

BACB30NX6K3X 11 BOLT, PROTRUDING HD

BACB30NX6K3Y 31 BOLT, PROTRUDING HD

BACB30NX6K4 22 BOLT, PROTRUDING HD

BACB30NX6K4X 8 BOLT, PROTRUDING HD

BACB30NX6K5 384 BOLT

BACB30NX6K5X 20 BOLT, PROTRUDING HD

BACB30NX6K6 97 BOLT

BACB30NX6K6X 6 BOLT, PROTRUDING HD

BACB30NX6K7 29 HI-LOK

BACB30NX6K7X 8 BOLT, PROTRUDING HD

BACB30NX6K8 179 BOLT, PROTRUDING HD

BACB30NX6K8X 29 BOLT, PROTRUDING HD

BACB30NX6K9 14 BOLT

BACC30AC6 31 COLLAR

BACC30BH6 902 COLLAR

BACC30M6 117 COLLAR

BACF3T01B10-40 8 FILLER, TAPERED

BACN10TL3A12 2 NUT STANDOFF

BACR15BB4AD5C 4 RIVETS

BACR15BB4AD6C 4 RIVET

BACR15BB6AD4C 31 RIVET, UNIVERSAL HD

BACR15GF6D5 31 RIVET

BACS40R005C005F 4 SHIM,LAMINATED

BACS40R008A043F 4 SHIM, LAMINATED

BACS40R008B038F 4 SHIM, LAMINATED

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

83 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 9, 16:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-109

142U0106-5 2 DOUBLER

142U0106-6 2 STRAP

142U0106-7 2 STRAP

142U0106-8 2 STRAP

142U0107-13 1 FRAME SEGMENT

142U0107-14 1 FRAME SEGMENT

142U0107-15 1 DOUBLER

142U0107-16 1 DOUBLER

142U0107-17 1 DOUBLER

142U0107-18 1 DOUBLER

142U0108-13 1 SHEAR TIE, S-7 TO S-8

142U0108-14 1 SHEAR TIE, S-7 TO S-8

142U0108-15 1 SHEAR TIE, S-11 TO S-12

142U0108-16 1 SHEAR TIE, S-11 TO S-12

142U0108-35 4 ANGLE

142U0108-36 4 ANGLE

142U0108-37 2 CHORD SPLICE - UPPER

142U0108-38 2 CHORD SPLICE - LOWER

142U0108-39 1 CHORD SEGMENT

142U0108-40 1 CHORD SEGMENT

142U0108-41 2 SHEAR TIE TEE, S-8 TO S-9

142U0108-42 2 SHEAR TIE TEE, S-9 TO S-10

SHEAR TIE TEE, S-10 TO S-10A

/ S-10A TO S-11

142U0108-43 4

144U0064-6 14 STRINGER CLIP TEE

144U0064-7 14 STRINGER CLIP TEE

69B41412-3 2 INSULATOR

BACB2D018B0F0 2 BRACKET, ANGLE

BACB30NW6K5Y 104 BOLT, 100 DEG HEX DR

BACB30NW6K6X 14 BOLT, 100 DEG HEX DR

BACB30NX6K10X 2 BOLT, PROTRUDING HD

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

84 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 9, 16:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-109

BACB30NX6K3 73 BOLT, PROTRUDING HD

BACB30NX6K3X 6 BOLT, PROTRUDING HD

BACB30NX6K3Y 31 BOLT, PROTRUDING HD

BACB30NX6K4 18 BOLT, PROTRUDING HD

BACB30NX6K4X 8 BOLT, PROTRUDING HD

BACB30NX6K5 368 BOLT

BACB30NX6K5X 22 BOLT, PROTRUDING HD

BACB30NX6K5Y 6 BOLT, PROTRUDING HD

BACB30NX6K6 97 BOLT

BACB30NX6K6X 8 BOLT, PROTRUDING HD

BACB30NX6K6Y 2 BOLT, PROTRUDING HD

BACB30NX6K7 31 HI-LOK

BACB30NX6K7X 8 BOLT, PROTRUDING HD

BACB30NX6K8 179 BOLT, PROTRUDING HD

BACB30NX6K8X 29 BOLT, PROTRUDING HD

BACB30NX6K9 14 BOLT

BACB30NX8K5X 2 BOLT, PROTRUDING HD

BACB30NX8K6X 2 BOLT, PROTRUDING HD

BACB30NX8K8X 4 BOLT, PROTRUDING HD

BACC30AC6 40 COLLAR

BACC30BH6 863 COLLAR

BACC30BH8 8 COLLAR

BACC30M6 117 COLLAR

BACF3T01B10-40 8 FILLER, TAPERED

BACN10TL3A12 2 NUT STANDOFF

BACR15BB4AD5C 4 RIVETS

BACR15BB4AD6C 4 RIVET

BACR15BB6AD4C 31 RIVET, UNIVERSAL HD

BACR15GF6D5 31 RIVET

BACS40R005C005F 4 SHIM,LAMINATED

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

85 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 9, 16:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-109

BACS40R008A043F 4 SHIM, LAMINATED

BACS40R008B038F 4 SHIM, LAMINATED

Group 10:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-110

142U0106-5 2 DOUBLER

142U0106-6 2 STRAP

142U0106-7 2 STRAP

142U0106-8 2 STRAP

142U0106-60 2 FILLER

142U0107-13 1 FRAME SEGMENT

142U0107-14 1 FRAME SEGMENT

142U0107-15 1 DOUBLER

142U0107-16 1 DOUBLER

142U0107-17 1 DOUBLER

142U0107-18 1 DOUBLER

142U0108-13 1 SHEAR TIE, S-7 TO S-8

142U0108-14 1 SHEAR TIE, S-7 TO S-8

142U0108-15 1 SHEAR TIE, S-11 TO S-12

142U0108-16 1 SHEAR TIE, S-11 TO S-12

142U0108-35 4 ANGLE

142U0108-36 4 ANGLE

142U0108-37 2 CHORD SPLICE - UPPER

142U0108-38 2 CHORD SPLICE - LOWER

142U0108-39 1 CHORD SEGMENT

142U0108-40 1 CHORD SEGMENT

142U0108-41 2 SHEAR TIE TEE, S-8 TO S-9

142U0108-42 2 SHEAR TIE TEE, S-9 TO S-10

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

86 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 10:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-110

SHEAR TIE TEE, S-10 TO S-10A

/ S-10A TO S-11

142U0108-43 4

144U0064-6 14 STRINGER CLIP TEE

144U0064-7 14 STRINGER CLIP TEE

69B41412-3 2 INSULATOR

BACB2D018B0F0 2 BRACKET, ANGLE

BACB30NW6K5Y 104 BOLT, 100 DEG HEX DR

BACB30NW6K6X 14 BOLT, 100 DEG HEX DR

BACB30NX6K10X 2 BOLT, PROTRUDING HD

BACB30NX6K3 102 BOLT, PROTRUDING HD

BACB30NX6K3X 11 BOLT, PROTRUDING HD

BACB30NX6K3Y 31 BOLT, PROTRUDING HD

BACB30NX6K4 22 BOLT, PROTRUDING HD

BACB30NX6K4X 8 BOLT, PROTRUDING HD

BACB30NX6K5 381 BOLT

BACB30NX6K5X 20 BOLT, PROTRUDING HD

BACB30NX6K6 95 BOLT

BACB30NX6K6X 8 BOLT, PROTRUDING HD

BACB30NX6K7 29 HI-LOK

BACB30NX6K7X 8 BOLT, PROTRUDING HD

BACB30NX6K8 176 BOLT, PROTRUDING HD

BACB30NX6K8X 29 BOLT, PROTRUDING HD

BACB30NX6K9 6 BOLT

BACC30AC6 31 COLLAR

BACC30BH6 905 COLLAR

BACC30M6 117 COLLAR

BACF3T01B10-40 8 FILLER, TAPERED

BACN10TL3A12 2 NUT STANDOFF

BACR15BB4AD5C 4 RIVETS

BACR15BB4AD6C 4 RIVET

BACR15BB6AD4C 31 RIVET, UNIVERSAL HD

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

87 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 10:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-110

BACR15GF6D5 31 RIVET

BACS40R005C005F 4 SHIM,LAMINATED

BACS40R008A043F 4 SHIM, LAMINATED

BACS40R008B038F 4 SHIM, LAMINATED

Group 1-9, 11-16:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-111

142U0106-1 2 SPLICE PLATE

142U0106-3 2 STRAP

142U0106-43 2 STRAP

142U0106-45 2 STRAP

142U0107-1 1 FRAME SEGMENT

142U0107-2 1 FRAME SEGMENT

142U0107-3 1 DOUBLER

142U0107-4 1 DOUBLER

142U0107-5 1 TRIPLER

142U0107-6 1 TRIPLER

142U0107-59 4 STIFFENER

142U0108-1 1 CHORD SEGMENT

142U0108-2 1 CHORD SEGMENT

142U0108-3 2 CHORD SPLICE - UPPER

142U0108-4 2 SHEAR TIE, S-7 TO S-8

142U0108-5 2 SHEAR TIE TEE, S-8 TO S-9

142U0108-6 2 SHEAR TIE TEE, S-9 TO S-10

142U0108-7 2 SHEAR TIE TEE, S-10 TO S-10A

142U0108-8 2 SHEAR TIE TEE, S-10A TO S-11

142U0108-9 1 SHEAR TIE, S-11 TO S-12

142U0108-10 1 SHEAR TIE, S-11 TO S-12

142U0108-11 1 STRINGER CLIP TEE

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

88 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 1-9, 11-16:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-111

142U0108-12 1 STRINGER CLIP TEE

144U0064-6 11 STRINGER CLIP TEE

144U0064-7 11 STRINGER CLIP TEE

144U0064-25 1 STRINGER CLIP TEE

144U0064-26 1 STRINGER CLIP TEE

69B41412-3 2 INSULATOR

BACB2D015B0F0 2 BRACKET, ANGLE

BACB2D018B0F0 2 BRACKET, ANGLE

BACB30NW6K5Y 84 BOLT, 100 DEG HEX DR

BACB30NW6K6X 15 BOLT, 100 DEG HEX DR

BACB30NX6K3 110 BOLT, PROTRUDING HD

BACB30NX6K3X 13 BOLT, PROTRUDING HD

BACB30NX6K3Y 59 BOLT, PROTRUDING HD

BACB30NX6K4 271 BOLT, PROTRUDING HD

BACB30NX6K4X 20 BOLT, PROTRUDING HD

BACB30NX6K4Y 59 BOLT, PROTRUDING HD

BACB30NX6K5 167 BOLT

BACB30NX6K5X 33 BOLT, PROTRUDING HD

BACB30NX6K5Y 22 BOLT, PROTRUDING HD

BACB30NX6K6 44 BOLT

BACB30NX6K6X 26 BOLT, PROTRUDING HD

BACB30NX6K7 51 HI-LOK

BACB30NX6K7X 22 BOLT, PROTRUDING HD

BACB30NX6K8 112 BOLT, PROTRUDING HD

BACB30NX6K8X 4 BOLT, PROTRUDING HD

BACB30NX6K8Y 6 BOLT, PROTRUDING HD

BACB30NX8K5X 6 BOLT, PROTRUDING HD

BACB30NX8K7 2 BOLT, HEX DRIVE

BACB30NX8K7X 4 BOLT, PROTRUDING HD

BACC30AC6 147 COLLAR

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

89 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 1-9, 11-16:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-111

BACC30BH6 873 COLLAR

BACC30BH8 13 COLLAR

BACC30M6 15 COLLAR

BACC30R6 84 COLLAR

BACF3T01B10-40 12 FILLER, TAPERED

BACF3T01E07-10 4 TAPERED FILLER

BACN10TL3A12 2 NUT STANDOFF

BACN10TL3A6 2 SPACER PLATE NUT

BACR15BB4AD5C 8 RIVETS

BACR15BB4AD6C 8 RIVET

BACR15BB6AD4C 27 RIVET, UNIVERSAL HD

BACR15GF6D5 27 RIVET

BACS40R005C005F 10 SHIM,LAMINATED

BACS40R008B037F 4 SHIM - LAMINATED

Group 10:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-112

142U0106-1 2 SPLICE PLATE

142U0106-9 2 STRAP

142U0106-45 2 STRAP

142U0106-47 2 STRAP

142U0107-1 1 FRAME SEGMENT

142U0107-2 1 FRAME SEGMENT

142U0107-3 1 DOUBLER

142U0107-4 1 DOUBLER

142U0107-5 1 TRIPLER

142U0107-6 1 TRIPLER

142U0107-59 4 STIFFENER

142U0108-1 1 CHORD SEGMENT

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

90 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 10:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-112

142U0108-2 1 CHORD SEGMENT

142U0108-3 2 CHORD SPLICE - UPPER

142U0108-4 2 SHEAR TIE, S-7 TO S-8

142U0108-5 2 SHEAR TIE TEE, S-8 TO S-9

142U0108-6 2 SHEAR TIE TEE, S-9 TO S-10

142U0108-7 2 SHEAR TIE TEE, S-10 TO S-10A

142U0108-8 2 SHEAR TIE TEE, S-10A TO S-11

142U0108-9 1 SHEAR TIE, S-11 TO S-12

142U0108-10 1 SHEAR TIE, S-11 TO S-12

144U0064-6 10 STRINGER CLIP TEE

144U0064-7 10 STRINGER CLIP TEE

144U0064-8 2 STRINGER CLIP TEE

144U0064-9 2 STRINGER CLIP TEE

BACB2D019C0D0 1 BRACKET, ANGLE

BACB30NW6K5Y 84 BOLT, 100 DEG HEX DR

BACB30NW6K6X 15 BOLT, 100 DEG HEX DR

BACB30NX6K3 64 BOLT, PROTRUDING HD

BACB30NX6K3X 33 BOLT, PROTRUDING HD

BACB30NX6K3Y 40 BOLT, PROTRUDING HD

BACB30NX6K4 255 BOLT, PROTRUDING HD

BACB30NX6K4X 26 BOLT, PROTRUDING HD

BACB30NX6K4Y 37 BOLT, PROTRUDING HD

BACB30NX6K5 165 BOLT

BACB30NX6K5X 29 BOLT, PROTRUDING HD

BACB30NX6K5Y 22 BOLT, PROTRUDING HD

BACB30NX6K6 24 BOLT

BACB30NX6K6X 20 BOLT, PROTRUDING HD

BACB30NX6K7 59 HI-LOK

BACB30NX6K7X 22 BOLT, PROTRUDING HD

BACB30NX6K8 112 BOLT, PROTRUDING HD

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

91 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 10:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-112

BACB30NX6K8X 11 BOLT, PROTRUDING HD

BACC30AC6 99 COLLAR

BACC30BH6 820 COLLAR

BACC30M6 15 COLLAR

BACC30R6 84 COLLAR

BACF3T01B10-40 12 FILLER, TAPERED

BACF3T01E07-10 4 TAPERED FILLER

BACN10TL3A10 1 NUT PLATE

BACR15BB4AD5C 2 RIVETS

BACR15BB6AD4C 27 RIVET, UNIVERSAL HD

BACR15GF6D5 27 RIVET

BACS40R005C005F 10 SHIM,LAMINATED

BACS40R008B037F 4 SHIM - LAMINATED

Group 1-4, 6, 11-15:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-113

142U0106-33 2 STRAP

142U0106-35 2 STRAP

142U0106-37 2 STRAP

142U0107-49 1 FRAME SEGMENT

142U0107-50 1 FRAME SEGMENT

142U0107-51 1 DOUBLER

142U0107-52 1 DOUBLER

142U0107-53 1 TRIPLER

142U0107-54 1 TRIPLER

142U0108-95 1 CHORD SEGMENT

142U0108-96 1 CHORD SEGMENT

142U0108-97 2 CHORD SPLICE - UPPER

142U0108-99 2 CHORD SPLICE - LOWER

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

92 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 1-4, 6, 11-15:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-113

142U0108-101 1 SHEAR TIE, S-7 TO S-8

142U0108-102 1 SHEAR TIE, S-7 TO S-8

142U0108-105 2 SHEAR TIE TEE, S-8 TO S-9

142U0108-107 2 SHEAR TIE TEE, S-9 TO S-10

142U0108-109 2 SHEAR TIE TEE, S-10 TO S-11

142U0108-113 1 SHEAR TIE, S-11 TO S-12

142U0108-114 1 SHEAR TIE, S-11 TO S-12

144U0064-8 10 STRINGER CLIP TEE

144U0064-9 10 STRINGER CLIP TEE

144U0064-25 2 STRINGER CLIP TEE

144U0064-26 2 STRINGER CLIP TEE

69B41412-3 2 INSULATOR

BACB2D019B0F0 2 BRACKET, ANGLE

BACB30NW6K5Y 106 BOLT, 100 DEG HEX DR

BACB30NW6K8X 29 BOLT, 100 DEG HEX DR

BACB30NX6K3 89 BOLT, PROTRUDING HD

BACB30NX6K3X 6 BOLT, PROTRUDING HD

BACB30NX6K3Y 29 BOLT, PROTRUDING HD

BACB30NX6K4 291 BOLT, PROTRUDING HD

BACB30NX6K4X 8 BOLT, PROTRUDING HD

BACB30NX6K4Y 29 BOLT, PROTRUDING HD

BACB30NX6K5 236 BOLT

BACB30NX6K5X 2 BOLT, PROTRUDING HD

BACB30NX6K5Y 14 BOLT, PROTRUDING HD

BACB30NX6K6Y 2 BOLT, PROTRUDING HD

BACB30NX6K7 49 HI-LOK

BACB30NX6K7X 11 BOLT, PROTRUDING HD

BACB30NX6K7Y 6 BOLT, PROTRUDING HD

BACB30NX6K8 130 BOLT, PROTRUDING HD

BACB30NX6K8Y 8 BOLT, PROTRUDING HD

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

93 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 1-4, 6, 11-15:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-113

BACB30NX6K9X 2 BOLT, PROTRUDING HD

BACC30AC6 89 COLLAR

BACC30BH6 824 COLLAR

BACC30M6 135 COLLAR

BACN10TL3A12 2 NUT STANDOFF

BACR15BB4AD5C 4 RIVETS

BACR15BB4AD6C 4 RIVET

BACR15BB6AD4C 27 RIVET, UNIVERSAL HD

BACR15GF6D5 27 RIVET

BACS40R005C005F 4 SHIM,LAMINATED

BACS40R007B036F 4 SHIM, LAMINATED

BACS40R007B045F 4 SHIM, LAMINATED

BACS40R010B061F 2 SHIM, LAMINATED

Group 8:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-114

142U0106-33 2 STRAP

142U0106-35 2 STRAP

142U0106-37 2 STRAP

142U0107-49 1 FRAME SEGMENT

142U0107-50 1 FRAME SEGMENT

142U0107-51 1 DOUBLER

142U0107-52 1 DOUBLER

142U0107-53 1 TRIPLER

142U0107-54 1 TRIPLER

142U0108-95 1 CHORD SEGMENT

142U0108-96 1 CHORD SEGMENT

142U0108-97 2 CHORD SPLICE - UPPER

142U0108-99 2 CHORD SPLICE - LOWER

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

94 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 8:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-114

142U0108-101 1 SHEAR TIE, S-7 TO S-8

142U0108-102 1 SHEAR TIE, S-7 TO S-8

142U0108-105 2 SHEAR TIE TEE, S-8 TO S-9

142U0108-107 2 SHEAR TIE TEE, S-9 TO S-10

142U0108-109 2 SHEAR TIE TEE, S-10 TO S-11

142U0108-113 1 SHEAR TIE, S-11 TO S-12

142U0108-114 1 SHEAR TIE, S-11 TO S-12

144U0064-8 10 STRINGER CLIP TEE

144U0064-9 10 STRINGER CLIP TEE

144U0064-25 2 STRINGER CLIP TEE

144U0064-26 2 STRINGER CLIP TEE

69B41412-3 2 INSULATOR

BACB2D019B0F0 2 BRACKET, ANGLE

BACB30NW6K5Y 108 BOLT, 100 DEG HEX DR

BACB30NW6K8X 16 BOLT, 100 DEG HEX DR

BACB30NX6K3 89 BOLT, PROTRUDING HD

BACB30NX6K3X 6 BOLT, PROTRUDING HD

BACB30NX6K3Y 29 BOLT, PROTRUDING HD

BACB30NX6K4 291 BOLT, PROTRUDING HD

BACB30NX6K4X 8 BOLT, PROTRUDING HD

BACB30NX6K4Y 29 BOLT, PROTRUDING HD

BACB30NX6K5 236 BOLT

BACB30NX6K5X 2 BOLT, PROTRUDING HD

BACB30NX6K5Y 14 BOLT, PROTRUDING HD

BACB30NX6K6Y 2 BOLT, PROTRUDING HD

BACB30NX6K7 49 HI-LOK

BACB30NX6K7X 11 BOLT, PROTRUDING HD

BACB30NX6K7Y 4 BOLT, PROTRUDING HD

BACB30NX6K8 108 BOLT, PROTRUDING HD

BACB30NX6K8Y 8 BOLT, PROTRUDING HD

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

95 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 8:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-114

BACB30NX6K9X 2 BOLT, PROTRUDING HD

BACC30AC6 86 COLLAR

BACC30BH6 802 COLLAR

BACC30M6 124 COLLAR

BACN10TL3A12 2 NUT STANDOFF

BACR15BB4AD5C 4 RIVETS

BACR15BB4AD6C 4 RIVET

BACR15BB6AD4C 27 RIVET, UNIVERSAL HD

BACR15GF6D5 27 RIVET

BACS40R005C005F 4 SHIM,LAMINATED

BACS40R007B036F 4 SHIM, LAMINATED

BACS40R007B045F 4 SHIM, LAMINATED

Group 9, 16:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-115

142U0106-33 2 STRAP

142U0106-35 2 STRAP

142U0106-37 2 STRAP

142U0107-49 1 FRAME SEGMENT

142U0107-50 1 FRAME SEGMENT

142U0107-51 1 DOUBLER

142U0107-52 1 DOUBLER

142U0107-53 1 TRIPLER

142U0107-54 1 TRIPLER

142U0108-95 1 CHORD SEGMENT

142U0108-96 1 CHORD SEGMENT

142U0108-97 2 CHORD SPLICE - UPPER

142U0108-99 2 CHORD SPLICE - LOWER

142U0108-103 1 SHEAR TIE TEE, S-7 TO S-8

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

96 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 9, 16:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-115

142U0108-104 1 SHEAR TIE TEE, S-7 TO S-8

142U0108-105 2 SHEAR TIE TEE, S-8 TO S-9

142U0108-107 2 SHEAR TIE TEE, S-9 TO S-10

142U0108-111 2 SHEAR TIE, S-10 TO S-11

142U0108-113 1 SHEAR TIE, S-11 TO S-12

142U0108-114 1 SHEAR TIE, S-11 TO S-12

144U0064-8 10 STRINGER CLIP TEE

144U0064-9 10 STRINGER CLIP TEE

144U0064-25 2 STRINGER CLIP TEE

144U0064-26 2 STRINGER CLIP TEE

69B41412-3 2 INSULATOR

BACB2D019B0F0 2 BRACKET, ANGLE

BACB30NW6K5Y 124 BOLT, 100 DEG HEX DR

BACB30NX6K3 86 BOLT, PROTRUDING HD

BACB30NX6K3X 4 BOLT, PROTRUDING HD

BACB30NX6K3Y 31 BOLT, PROTRUDING HD

BACB30NX6K4 284 BOLT, PROTRUDING HD

BACB30NX6K4X 8 BOLT, PROTRUDING HD

BACB30NX6K4Y 27 BOLT, PROTRUDING HD

BACB30NX6K5 231 BOLT

BACB30NX6K5X 2 BOLT, PROTRUDING HD

BACB30NX6K5Y 20 BOLT, PROTRUDING HD

BACB30NX6K6Y 2 BOLT, PROTRUDING HD

BACB30NX6K7 40 HI-LOK

BACB30NX6K7X 11 BOLT, PROTRUDING HD

BACB30NX6K7Y 10 BOLT, PROTRUDING HD

BACB30NX6K8 124 BOLT, PROTRUDING HD

BACB30NX6K8Y 15 BOLT, PROTRUDING HD

BACB30NX6K9X 2 BOLT, PROTRUDING HD

BACB30YP6K7 2 BOLT, 100 DEG HEX DR

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

97 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 9, 16:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-115

BACC30AC6 104 COLLAR

BACC30BH6 794 COLLAR

BACC30BL6 2 COLLAR

BACC30M6 124 COLLAR

BACN10TL3A12 2 NUT STANDOFF

BACR15BB4AD5C 4 RIVETS

BACR15BB4AD6C 4 RIVET

BACR15BB6AD4C 27 RIVET, UNIVERSAL HD

BACR15GF6D5 27 RIVET

BACS40R005C005F 4 SHIM,LAMINATED

BACS40R007B036F 4 SHIM, LAMINATED

BACS40R007B045F 4 SHIM, LAMINATED

Group 10:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-116

142U0106-33 2 STRAP

142U0106-35 2 STRAP

142U0106-37 2 STRAP

142U0107-49 1 FRAME SEGMENT

142U0107-50 1 FRAME SEGMENT

142U0107-51 1 DOUBLER

142U0107-52 1 DOUBLER

142U0107-53 1 TRIPLER

142U0107-54 1 TRIPLER

142U0108-95 1 CHORD SEGMENT

142U0108-96 1 CHORD SEGMENT

142U0108-97 2 CHORD SPLICE - UPPER

142U0108-99 2 CHORD SPLICE - LOWER

142U0108-101 1 SHEAR TIE, S-7 TO S-8

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

98 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 10:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-116

142U0108-102 1 SHEAR TIE, S-7 TO S-8

142U0108-105 2 SHEAR TIE TEE, S-8 TO S-9

142U0108-107 2 SHEAR TIE TEE, S-9 TO S-10

142U0108-109 2 SHEAR TIE TEE, S-10 TO S-11

142U0108-113 1 SHEAR TIE, S-11 TO S-12

142U0108-114 1 SHEAR TIE, S-11 TO S-12

144U0064-8 10 STRINGER CLIP TEE

144U0064-9 10 STRINGER CLIP TEE

144U0064-25 2 STRINGER CLIP TEE

144U0064-26 2 STRINGER CLIP TEE

BACB2C028E0E0 1 BRACKET

BACB2D019B0G0 2 BRACKET, ANGLE

BACB30NW6K5Y 108 BOLT, 100 DEG HEX DR

BACB30NW6K8X 16 BOLT, 100 DEG HEX DR

BACB30NX6K3 89 BOLT, PROTRUDING HD

BACB30NX6K3X 6 BOLT, PROTRUDING HD

BACB30NX6K3Y 29 BOLT, PROTRUDING HD

BACB30NX6K4 300 BOLT, PROTRUDING HD

BACB30NX6K4X 4 BOLT, PROTRUDING HD

BACB30NX6K4Y 25 BOLT, PROTRUDING HD

BACB30NX6K5 238 BOLT

BACB30NX6K5X 2 BOLT, PROTRUDING HD

BACB30NX6K5Y 14 BOLT, PROTRUDING HD

BACB30NX6K6Y 2 BOLT, PROTRUDING HD

BACB30NX6K7 44 HI-LOK

BACB30NX6K7X 11 BOLT, PROTRUDING HD

BACB30NX6K7Y 4 BOLT, PROTRUDING HD

BACB30NX6K8 128 BOLT, PROTRUDING HD

BACB30NX6K8Y 8 BOLT, PROTRUDING HD

BACB30NX6K9X 2 BOLT, PROTRUDING HD

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

99 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 10:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-116

BACB30YP6K7 2 BOLT, 100 DEG HEX DR

BACC30AC6 82 COLLAR

BACC30BH6 824 COLLAR

BACC30BL6 2 COLLAR

BACC30M6 124 COLLAR

BACN10TL3A8 2 NUT, SPACER PLATE

BACR15BB4AD6C 4 RIVET

BACR15BB6AD4C 27 RIVET, UNIVERSAL HD

BACR15GF6D5 27 RIVET

BACS40R005C005F 4 SHIM,LAMINATED

BACS40R007B036F 4 SHIM, LAMINATED

BACS40R007B045F 4 SHIM, LAMINATED

BACS53B1ES1 1 ELECTRICAL GROUND STUD

Group 1-4, 6, 8, 11-15:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-117

142U0106-12 2 STRAP

142U0106-51 2 STRAP

142U0106-53 2 STRAP

142U0107-7 1 TRIPLER

142U0107-8 1 TRIPLER

142U0107-9 1 FRAME SEGMENT

142U0107-10 1 FRAME SEGMENT

142U0107-11 1 DOUBLER

142U0107-12 1 DOUBLER

142U0108-21 1 CHORD SEGMENT

142U0108-22 1 CHORD SEGMENT

142U0108-23 2 CHORD SPLICE - UPPER

142U0108-25 2 SHEAR TIE TEE, S-7 TO S-8

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

100 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 1-4, 6, 8, 11-15:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-117

142U0108-27 1 SHEAR TIE, S-11 TO S-12

142U0108-28 1 SHEAR TIE, S-11 TO S-12

142U0108-33 2 SHEAR TIE, S-10 TO S-11

142U0108-45 2 CHORD SPLICE - LOWER

142U0108-57 2 SHEAR TIE TEE, S-8 TO S-9

142U0108-121 2 SHEAR TIE TEE, S-9 TO S-10

144U0064-6 12 STRINGER CLIP TEE

144U0064-7 12 STRINGER CLIP TEE

69B41412-3 2 INSULATOR

BACB2D018A0C0 2 BRACKET, ANGLE

BACB2D018B0F0 2 BRACKET, ANGLE

BACB30NW6K5Y 124 BOLT, 100 DEG HEX DR

BACB30NW6K6Y 16 BOLT, 100 DEG HEX DR

BACB30NX6K3 91 BOLT, PROTRUDING HD

BACB30NX6K3X 6 BOLT, PROTRUDING HD

BACB30NX6K3Y 29 BOLT, PROTRUDING HD

BACB30NX6K4 266 BOLT, PROTRUDING HD

BACB30NX6K4X 17 BOLT, PROTRUDING HD

BACB30NX6K4Y 18 BOLT, PROTRUDING HD

BACB30NX6K5 261 BOLT

BACB30NX6K5X 4 BOLT, PROTRUDING HD

BACB30NX6K5Y 11 BOLT, PROTRUDING HD

BACB30NX6K7 47 HI-LOK

BACB30NX6K7X 22 BOLT, PROTRUDING HD

BACB30NX6K8 117 BOLT, PROTRUDING HD

BACB30NX6K8X 6 BOLT, PROTRUDING HD

BACB30NX6K8Y 6 BOLT, PROTRUDING HD

BACB30NX6K9X 2 BOLT, PROTRUDING HD

BACC30AC6 64 COLLAR

BACC30BH6 838 COLLAR

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

101 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 1-4, 6, 8, 11-15:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-117

BACC30M6 140 COLLAR

BACN10TL3A12 2 NUT STANDOFF

BACN10TL3A6 2 SPACER PLATE NUT

BACR15BB4AD5C 4 RIVETS

BACR15BB6AD4C 27 RIVET, UNIVERSAL HD

BACR15GF6D5 27 RIVET

BACS40R005C005F 4 SHIM,LAMINATED

BACS40R008B036F 2 SHIM - LAMINATED

BACS40R008B037F 2 SHIM - LAMINATED

BACS40R008B044F 4 SHIM - LAMINATED

Group 9, 16:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-119

142U0106-12 2 STRAP

142U0106-51 2 STRAP

142U0106-53 2 STRAP

142U0107-7 1 TRIPLER

142U0107-8 1 TRIPLER

142U0107-9 1 FRAME SEGMENT

142U0107-10 1 FRAME SEGMENT

142U0107-11 1 DOUBLER

142U0107-12 1 DOUBLER

142U0108-21 1 CHORD SEGMENT

142U0108-22 1 CHORD SEGMENT

142U0108-23 2 CHORD SPLICE - UPPER

142U0108-27 1 SHEAR TIE, S-11 TO S-12

142U0108-28 1 SHEAR TIE, S-11 TO S-12

142U0108-29 2 SHEAR TIE, S-7 TO S-8

142U0108-31 2 SHEAR TIE TEE, S-10 TO S-11

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

102 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 9, 16:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-119

142U0108-45 2 CHORD SPLICE - LOWER

142U0108-57 2 SHEAR TIE TEE, S-8 TO S-9

142U0108-121 2 SHEAR TIE TEE, S-9 TO S-10

144U0064-6 12 STRINGER CLIP TEE

144U0064-7 12 STRINGER CLIP TEE

69B41412-3 2 INSULATOR

BACB2D018B0F0 2 BRACKET, ANGLE

BACB30NW6K5Y 141 BOLT, 100 DEG HEX DR

BACB30NW6K6Y 16 BOLT, 100 DEG HEX DR

BACB30NX6K3 91 BOLT, PROTRUDING HD

BACB30NX6K3X 6 BOLT, PROTRUDING HD

BACB30NX6K3Y 29 BOLT, PROTRUDING HD

BACB30NX6K4 266 BOLT, PROTRUDING HD

BACB30NX6K4X 17 BOLT, PROTRUDING HD

BACB30NX6K4Y 18 BOLT, PROTRUDING HD

BACB30NX6K5 258 BOLT

BACB30NX6K5X 4 BOLT, PROTRUDING HD

BACB30NX6K5Y 11 BOLT, PROTRUDING HD

BACB30NX6K7 47 HI-LOK

BACB30NX6K7X 22 BOLT, PROTRUDING HD

BACB30NX6K8 124 BOLT, PROTRUDING HD

BACB30NX6K8X 6 BOLT, PROTRUDING HD

BACB30NX6K9X 2 BOLT, PROTRUDING HD

BACC30AC6 58 COLLAR

BACC30BH6 842 COLLAR

BACC30M6 157 COLLAR

BACN10TL3A12 2 NUT STANDOFF

BACR15BB4AD5C 4 RIVETS

BACR15BB6AD4C 27 RIVET, UNIVERSAL HD

BACR15GF6D5 27 RIVET

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

103 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 9, 16:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-119

BACS40R005C005F 4 SHIM,LAMINATED

BACS40R008B036F 2 SHIM - LAMINATED

BACS40R008B037F 2 SHIM - LAMINATED

BACS40R008B044F 4 SHIM - LAMINATED

Group 10:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-120

142U0106-12 2 STRAP

142U0106-51 2 STRAP

142U0106-53 2 STRAP

142U0107-7 1 TRIPLER

142U0107-8 1 TRIPLER

142U0107-9 1 FRAME SEGMENT

142U0107-10 1 FRAME SEGMENT

142U0107-11 1 DOUBLER

142U0107-12 1 DOUBLER

142U0108-21 1 CHORD SEGMENT

142U0108-22 1 CHORD SEGMENT

142U0108-23 2 CHORD SPLICE - UPPER

142U0108-25 2 SHEAR TIE TEE, S-7 TO S-8

142U0108-27 1 SHEAR TIE, S-11 TO S-12

142U0108-28 1 SHEAR TIE, S-11 TO S-12

142U0108-31 2 SHEAR TIE TEE, S-10 TO S-11

142U0108-45 2 CHORD SPLICE - LOWER

142U0108-57 2 SHEAR TIE TEE, S-8 TO S-9

142U0108-121 2 SHEAR TIE TEE, S-9 TO S-10

144U0064-6 12 STRINGER CLIP TEE

144U0064-7 12 STRINGER CLIP TEE

69B41412-3 2 INSULATOR

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

104 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 10:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-120

BACB2D018B0E0 1 BRACKET, ANGLE

BACB2D018B0F0 2 BRACKET, ANGLE

BACB30NW6K5Y 141 BOLT, 100 DEG HEX DR

BACB30NW6K6Y 16 BOLT, 100 DEG HEX DR

BACB30NX6K3 91 BOLT, PROTRUDING HD

BACB30NX6K3X 11 BOLT, PROTRUDING HD

BACB30NX6K3Y 25 BOLT, PROTRUDING HD

BACB30NX6K4 275 BOLT, PROTRUDING HD

BACB30NX6K4X 17 BOLT, PROTRUDING HD

BACB30NX6K4Y 18 BOLT, PROTRUDING HD

BACB30NX6K5 263 BOLT

BACB30NX6K5X 4 BOLT, PROTRUDING HD

BACB30NX6K5Y 11 BOLT, PROTRUDING HD

BACB30NX6K7 47 HI-LOK

BACB30NX6K7X 22 BOLT, PROTRUDING HD

BACB30NX6K8 115 BOLT, PROTRUDING HD

BACB30NX6K8X 6 BOLT, PROTRUDING HD

BACB30NX6K8Y 6 BOLT, PROTRUDING HD

BACB30NX6K9X 2 BOLT, PROTRUDING HD

BACC30AC6 60 COLLAR

BACC30BH6 852 COLLAR

BACC30M6 157 COLLAR

BACN10TL3A12 2 NUT STANDOFF

BACN10TL3A8 1 NUT, SPACER PLATE

BACR15BB4AD5C 6 RIVETS

BACR15BB6AD4C 27 RIVET, UNIVERSAL HD

BACR15GF6D5 27 RIVET

BACS40R005C005F 4 SHIM,LAMINATED

BACS40R008B036F 2 SHIM - LAMINATED

BACS40R008B037F 2 SHIM - LAMINATED

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

105 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 10:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-120

BACS40R008B044F 4 SHIM - LAMINATED

Group 1-4, 6, 8, 11-15:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-121

142U0106-10 2 STRAP

142U0106-55 2 STRAP

142U0106-57 2 STRAP

142U0107-33 1 FRAME SEGMENT

142U0107-34 1 FRAME SEGMENT

142U0107-35 1 DOUBLER

142U0107-36 1 DOUBLER

142U0107-37 1 TRIPLER

142U0107-38 1 TRIPLER

142U0108-59 1 CHORD SEGMENT

142U0108-60 1 CHORD SEGMENT

142U0108-61 2 CHORD SPLICE - LOWER

142U0108-63 2 CHORD SPLICE - UPPER

142U0108-65 1 SHEAR TIE, S-11 TO S-12

142U0108-66 1 SHEAR TIE, S-11 TO S-12

142U0108-67 2 SHEAR TIE, S-10 TO S-11

142U0108-69 2 SHEAR TIE TEE, S-7 TO S-8

142U0108-71 2 SHEAR TIE TEE, S-6 TO S-7

142U0108-75 2 SHEAR TIE TEE, S-9 TO S-10

142U0108-123 2 SHEAR TIE TEE, S-8 TO S-9

144U0064-6 14 STRINGER CLIP TEE

144U0064-7 14 STRINGER CLIP TEE

69B41412-3 2 INSULATOR

BACB2D018B0F0 2 BRACKET, ANGLE

BACB2D019A0C0 2 BRACKET, ANGLE

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

106 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 1-4, 6, 8, 11-15:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-121

BACB30NW6K3Y 6 BOLT, 100 DEG HEX DR

BACB30NW6K6Y 141 BOLT, 100 DEG HEX DR

BACB30NW6K7Y 16 BOLT, 100 DEG HEX DR

BACB30NX6K3 84 BOLT, PROTRUDING HD

BACB30NX6K3X 14 BOLT, PROTRUDING HD

BACB30NX6K3Y 29 BOLT, PROTRUDING HD

BACB30NX6K4 167 BOLT, PROTRUDING HD

BACB30NX6K4X 15 BOLT, PROTRUDING HD

BACB30NX6K4Y 14 BOLT, PROTRUDING HD

BACB30NX6K5 168 BOLT

BACB30NX6K5X 2 BOLT, PROTRUDING HD

BACB30NX6K5Y 14 BOLT, PROTRUDING HD

BACB30NX6K6X 16 BOLT, PROTRUDING HD

BACB30NX6K6Y 4 BOLT, PROTRUDING HD

BACB30NX6K7 34 HI-LOK

BACB30NX6K7X 11 BOLT, PROTRUDING HD

BACB30NX6K7Y 2 BOLT, PROTRUDING HD

BACB30NX6K8 138 BOLT, PROTRUDING HD

BACB30NX6K8X 6 BOLT, PROTRUDING HD

BACB30NX6K8Y 6 BOLT, PROTRUDING HD

BACB30NX6K9X 2 BOLT, PROTRUDING HD

BACB30YP6K8 18 BOLT, 100 DEG HEX DR

BACC30AC6 589 COLLAR

BACC30BH6 31 COLLAR

BACC30BL6 18 COLLAR

BACC30M6 169 COLLAR

BACN10TL3A12 2 NUT STANDOFF

BACN10TL3A6 2 SPACER PLATE NUT

BACR15BB4AD5C 4 RIVETS

BACR15BB6AD4C 31 RIVET, UNIVERSAL HD

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

107 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 1-4, 6, 8, 11-15:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-121

BACR15GF6D5 31 RIVET

BACS40R005C005F 4 SHIM,LAMINATED

BACS40R008B035F 2 SHIM, LAMINATED

BACS40R008B036F 6 SHIM - LAMINATED

Group 9, 16:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-123

FILLER BETWEEN CLIPS OF

CREASE

142U0103-154 2

142U0104-5 1 BEAM

142U0104-6 1 BEAM

142U0104-7 1 CLIP

142U0104-8 1 CLIP

142U0106-10 2 STRAP

142U0106-55 2 STRAP

142U0106-57 2 STRAP

142U0107-33 1 FRAME SEGMENT

142U0107-34 1 FRAME SEGMENT

142U0107-35 1 DOUBLER

142U0107-36 1 DOUBLER

142U0107-37 1 TRIPLER

142U0107-38 1 TRIPLER

142U0108-59 1 CHORD SEGMENT

142U0108-60 1 CHORD SEGMENT

142U0108-61 2 CHORD SPLICE - LOWER

142U0108-63 2 CHORD SPLICE - UPPER

142U0108-65 1 SHEAR TIE, S-11 TO S-12

142U0108-66 1 SHEAR TIE, S-11 TO S-12

142U0108-67 2 SHEAR TIE, S-10 TO S-11

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

108 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 9, 16:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-123

142U0108-69 2 SHEAR TIE TEE, S-7 TO S-8

142U0108-73 2 SHEAR TIE, S-6 TO S-7

142U0108-75 2 SHEAR TIE TEE, S-9 TO S-10

142U0108-123 2 SHEAR TIE TEE, S-8 TO S-9

144U0064-6 14 STRINGER CLIP TEE

144U0064-7 14 STRINGER CLIP TEE

69B41412-3 2 INSULATOR

BACB2D018B0F0 2 BRACKET, ANGLE

BACB30NW6K5 4 BOLT, HILOK

BACB30NW6K6Y 137 BOLT, 100 DEG HEX DR

BACB30NW6K7Y 16 BOLT, 100 DEG HEX DR

BACB30NX6K20 2 BOLT, PROTRUDING HD

BACB30NX6K2Y 48 BOLT, HEX DRIVE

BACB30NX6K3 101 BOLT, PROTRUDING HD

BACB30NX6K3X 14 BOLT, PROTRUDING HD

BACB30NX6K3Y 126 BOLT, PROTRUDING HD

BACB30NX6K4 310 BOLT, PROTRUDING HD

BACB30NX6K4X 15 BOLT, PROTRUDING HD

BACB30NX6K4Y 12 BOLT, PROTRUDING HD

BACB30NX6K5 310 BOLT

BACB30NX6K5X 4 BOLT, PROTRUDING HD

BACB30NX6K5Y 20 BOLT, PROTRUDING HD

BACB30NX6K6 8 BOLT

BACB30NX6K6X 14 BOLT, PROTRUDING HD

BACB30NX6K7 43 HI-LOK

BACB30NX6K7X 13 BOLT, PROTRUDING HD

BACB30NX6K7Y 4 BOLT, PROTRUDING HD

BACB30NX6K8 142 BOLT, PROTRUDING HD

BACB30NX6K8X 6 BOLT, PROTRUDING HD

BACB30NX6K9X 2 BOLT, PROTRUDING HD

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

109 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 9, 16:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-123

BACC30AC6 210 COLLAR

BACC30BH6 975 COLLAR

BACC30M6 168 COLLAR

BACN10TL3A12 2 NUT STANDOFF

BACR15BB4AD5C 4 RIVETS

BACR15BB6AD4C 31 RIVET, UNIVERSAL HD

BACR15GF6D5 31 RIVET

BACS40R005C005F 4 SHIM,LAMINATED

BACS40R008B035F 2 SHIM, LAMINATED

BACS40R008B036F 6 SHIM - LAMINATED

Group 10:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-124

FILLER BETWEEN CLIPS OF

CREASE

142U0103-154 2

142U0104-5 1 BEAM

142U0104-6 1 BEAM

142U0104-7 1 CLIP

142U0104-8 1 CLIP

142U0106-10 2 STRAP

142U0106-55 2 STRAP

142U0106-57 2 STRAP

142U0107-33 1 FRAME SEGMENT

142U0107-34 1 FRAME SEGMENT

142U0107-35 1 DOUBLER

142U0107-36 1 DOUBLER

142U0107-37 1 TRIPLER

142U0107-38 1 TRIPLER

142U0108-59 1 CHORD SEGMENT

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

110 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 10:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-124

142U0108-60 1 CHORD SEGMENT

142U0108-61 2 CHORD SPLICE - LOWER

142U0108-63 2 CHORD SPLICE - UPPER

142U0108-65 1 SHEAR TIE, S-11 TO S-12

142U0108-66 1 SHEAR TIE, S-11 TO S-12

142U0108-67 2 SHEAR TIE, S-10 TO S-11

142U0108-69 2 SHEAR TIE TEE, S-7 TO S-8

142U0108-71 2 SHEAR TIE TEE, S-6 TO S-7

142U0108-75 2 SHEAR TIE TEE, S-9 TO S-10

142U0108-123 2 SHEAR TIE TEE, S-8 TO S-9

144U0064-6 14 STRINGER CLIP TEE

144U0064-7 14 STRINGER CLIP TEE

255U0281U5 1 CLIP

69B41412-3 2 INSULATOR

BACB2D018B0F0 2 BRACKET, ANGLE

BACB2D020E0H0 1 BRACKET, ANGLE

BACB30NW6K5 6 BOLT, HILOK

BACB30NW6K6Y 159 BOLT, 100 DEG HEX DR

BACB30NW6K7Y 16 BOLT, 100 DEG HEX DR

BACB30NX6K20 2 BOLT, PROTRUDING HD

BACB30NX6K2Y 48 BOLT, HEX DRIVE

BACB30NX6K3 99 BOLT, PROTRUDING HD

BACB30NX6K3X 14 BOLT, PROTRUDING HD

BACB30NX6K3Y 128 BOLT, PROTRUDING HD

BACB30NX6K4 315 BOLT, PROTRUDING HD

BACB30NX6K4X 17 BOLT, PROTRUDING HD

BACB30NX6K4Y 14 BOLT, PROTRUDING HD

BACB30NX6K5 329 BOLT

BACB30NX6K5X 6 BOLT, PROTRUDING HD

BACB30NX6K5Y 22 BOLT, PROTRUDING HD

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

111 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 10:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-124

BACB30NX6K6 8 BOLT

BACB30NX6K6X 14 BOLT, PROTRUDING HD

BACB30NX6K7 43 HI-LOK

BACB30NX6K7X 16 BOLT, PROTRUDING HD

BACB30NX6K7Y 16 BOLT, PROTRUDING HD

BACB30NX6K8 142 BOLT, PROTRUDING HD

BACB30NX6K8X 6 BOLT, PROTRUDING HD

BACB30NX6K8Y 8 BOLT, PROTRUDING HD

BACB30NX6K9X 2 BOLT, PROTRUDING HD

BACC30AC6 237 COLLAR

BACC30BH6 998 COLLAR

BACC30M6 191 COLLAR

BACF3F008L008NN 1 FILLER

BACF3F008V008NN 1 FILLER

BACF3H07RF009HN 1 FILLER, RADIUSED EDGE

BACN10TL3A12 2 NUT STANDOFF

BACN10TL3A4 1 NUT, SPACER PLATE

BACR15BB4AD4C 2 RIVET, UNIVERSAL HD

BACR15BB4AD5C 4 RIVETS

BACR15BB6AD4C 31 RIVET, UNIVERSAL HD

BACR15GF6D5 31 RIVET

BACS40R005C005F 4 SHIM,LAMINATED

BACS40R008B035F 2 SHIM, LAMINATED

BACS40R008B036F 6 SHIM - LAMINATED

Group 5, 7:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-125

142U0106-33 2 STRAP

142U0106-35 2 STRAP

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

112 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 5, 7:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-125

142U0106-37 2 STRAP

142U0107-49 1 FRAME SEGMENT

142U0107-50 1 FRAME SEGMENT

142U0107-51 1 DOUBLER

142U0107-52 1 DOUBLER

142U0107-53 1 TRIPLER

142U0107-54 1 TRIPLER

142U0108-95 1 CHORD SEGMENT

142U0108-96 1 CHORD SEGMENT

142U0108-97 2 CHORD SPLICE - UPPER

142U0108-99 2 CHORD SPLICE - LOWER

142U0108-103 1 SHEAR TIE TEE, S-7 TO S-8

142U0108-104 1 SHEAR TIE TEE, S-7 TO S-8

142U0108-105 2 SHEAR TIE TEE, S-8 TO S-9

142U0108-107 2 SHEAR TIE TEE, S-9 TO S-10

142U0108-111 2 SHEAR TIE, S-10 TO S-11

142U0108-113 1 SHEAR TIE, S-11 TO S-12

142U0108-114 1 SHEAR TIE, S-11 TO S-12

144U0064-8 10 STRINGER CLIP TEE

144U0064-9 10 STRINGER CLIP TEE

144U0064-25 2 STRINGER CLIP TEE

144U0064-26 2 STRINGER CLIP TEE

69B41412-3 2 INSULATOR

BACB2D019B0F0 2 BRACKET, ANGLE

BACB30NW6K5Y 124 BOLT, 100 DEG HEX DR

BACB30NX6K3 95 BOLT, PROTRUDING HD

BACB30NX6K3X 4 BOLT, PROTRUDING HD

BACB30NX6K3Y 38 BOLT, PROTRUDING HD

BACB30NX6K4 284 BOLT, PROTRUDING HD

BACB30NX6K4X 8 BOLT, PROTRUDING HD

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

113 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 5, 7:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-125

BACB30NX6K4Y 29 BOLT, PROTRUDING HD

BACB30NX6K5 231 BOLT

BACB30NX6K5X 2 BOLT, PROTRUDING HD

BACB30NX6K5Y 20 BOLT, PROTRUDING HD

BACB30NX6K6Y 2 BOLT, PROTRUDING HD

BACB30NX6K7 40 HI-LOK

BACB30NX6K7X 11 BOLT, PROTRUDING HD

BACB30NX6K7Y 12 BOLT, PROTRUDING HD

BACB30NX6K8 126 BOLT, PROTRUDING HD

BACB30NX6K8Y 15 BOLT, PROTRUDING HD

BACB30NX6K9X 2 BOLT, PROTRUDING HD

BACB30YP6K7 2 BOLT, 100 DEG HEX DR

BACC30AC6 115 COLLAR

BACC30BH6 805 COLLAR

BACC30BL6 2 COLLAR

BACC30M6 126 COLLAR

BACN10TL3A12 2 NUT STANDOFF

BACR15BB4AD5C 4 RIVETS

BACR15BB4AD6C 4 RIVET

BACR15BB6AD4C 31 RIVET, UNIVERSAL HD

BACR15GF6D5 31 RIVET

BACS40R005C005F 4 SHIM,LAMINATED

BACS40R007B036F 4 SHIM, LAMINATED

BACS40R007B045F 4 SHIM, LAMINATED

Group 5, 7:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-126

142U0106-12 2 STRAP

142U0106-51 2 STRAP

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

114 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 5, 7:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-126

142U0106-53 2 STRAP

142U0107-7 1 TRIPLER

142U0107-8 1 TRIPLER

142U0107-9 1 FRAME SEGMENT

142U0107-10 1 FRAME SEGMENT

142U0107-11 1 DOUBLER

142U0107-12 1 DOUBLER

142U0108-21 1 CHORD SEGMENT

142U0108-22 1 CHORD SEGMENT

142U0108-23 2 CHORD SPLICE - UPPER

142U0108-25 2 SHEAR TIE TEE, S-7 TO S-8

142U0108-27 1 SHEAR TIE, S-11 TO S-12

142U0108-28 1 SHEAR TIE, S-11 TO S-12

142U0108-31 2 SHEAR TIE TEE, S-10 TO S-11

142U0108-45 2 CHORD SPLICE - LOWER

142U0108-57 2 SHEAR TIE TEE, S-8 TO S-9

142U0108-121 2 SHEAR TIE TEE, S-9 TO S-10

144U0064-6 12 STRINGER CLIP TEE

144U0064-7 12 STRINGER CLIP TEE

69B41412-3 2 INSULATOR

BACB2D018B0F0 2 BRACKET, ANGLE

BACB30NW6K5Y 141 BOLT, 100 DEG HEX DR

BACB30NW6K6Y 16 BOLT, 100 DEG HEX DR

BACB30NX6K3 91 BOLT, PROTRUDING HD

BACB30NX6K3X 6 BOLT, PROTRUDING HD

BACB30NX6K3Y 29 BOLT, PROTRUDING HD

BACB30NX6K4 266 BOLT, PROTRUDING HD

BACB30NX6K4X 17 BOLT, PROTRUDING HD

BACB30NX6K4Y 18 BOLT, PROTRUDING HD

BACB30NX6K5 258 BOLT

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

115 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 5, 7:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-126

BACB30NX6K5X 4 BOLT, PROTRUDING HD

BACB30NX6K5Y 11 BOLT, PROTRUDING HD

BACB30NX6K7 47 HI-LOK

BACB30NX6K7X 22 BOLT, PROTRUDING HD

BACB30NX6K8 124 BOLT, PROTRUDING HD

BACB30NX6K8X 6 BOLT, PROTRUDING HD

BACB30NX6K8Y 6 BOLT, PROTRUDING HD

BACB30NX6K9X 2 BOLT, PROTRUDING HD

BACC30AC6 64 COLLAR

BACC30BH6 842 COLLAR

BACC30M6 157 COLLAR

BACN10TL3A12 2 NUT STANDOFF

BACR15BB4AD5C 4 RIVETS

BACR15BB6AD4C 27 RIVET, UNIVERSAL HD

BACR15GF6D5 27 RIVET

BACS40R005C005F 4 SHIM,LAMINATED

BACS40R008B036F 2 SHIM - LAMINATED

BACS40R008B037F 2 SHIM - LAMINATED

BACS40R008B044F 4 SHIM - LAMINATED

Group 5, 7:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-127

FILLER BETWEEN CLIPS OF

CREASE

142U0103-154 2

142U0104-5 1 BEAM

142U0104-6 1 BEAM

142U0104-7 1 CLIP

142U0104-8 1 CLIP

142U0106-10 2 STRAP

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

116 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 5, 7:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-127

142U0106-55 2 STRAP

142U0106-57 2 STRAP

142U0107-33 1 FRAME SEGMENT

142U0107-34 1 FRAME SEGMENT

142U0107-35 1 DOUBLER

142U0107-36 1 DOUBLER

142U0107-37 1 TRIPLER

142U0107-38 1 TRIPLER

142U0108-59 1 CHORD SEGMENT

142U0108-60 1 CHORD SEGMENT

142U0108-61 2 CHORD SPLICE - LOWER

142U0108-63 2 CHORD SPLICE - UPPER

142U0108-65 1 SHEAR TIE, S-11 TO S-12

142U0108-66 1 SHEAR TIE, S-11 TO S-12

142U0108-67 2 SHEAR TIE, S-10 TO S-11

142U0108-69 2 SHEAR TIE TEE, S-7 TO S-8

142U0108-71 2 SHEAR TIE TEE, S-6 TO S-7

142U0108-75 2 SHEAR TIE TEE, S-9 TO S-10

142U0108-123 2 SHEAR TIE TEE, S-8 TO S-9

144U0064-6 14 STRINGER CLIP TEE

144U0064-7 14 STRINGER CLIP TEE

69B41412-3 2 INSULATOR

BACB2D018B0F0 2 BRACKET, ANGLE

BACB30NW6K5 4 BOLT, HILOK

BACB30NW6K6Y 137 BOLT, 100 DEG HEX DR

BACB30NW6K7Y 16 BOLT, 100 DEG HEX DR

BACB30NX6K20 2 BOLT, PROTRUDING HD

BACB30NX6K2Y 48 BOLT, HEX DRIVE

BACB30NX6K3 101 BOLT, PROTRUDING HD

BACB30NX6K3X 14 BOLT, PROTRUDING HD

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

117 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 5, 7:

Kit 142U0101

Existing Part Notes

Number

New Part Number QTY Name

-127

BACB30NX6K3Y 126 BOLT, PROTRUDING HD

BACB30NX6K4 310 BOLT, PROTRUDING HD

BACB30NX6K4X 15 BOLT, PROTRUDING HD

BACB30NX6K4Y 12 BOLT, PROTRUDING HD

BACB30NX6K5 310 BOLT

BACB30NX6K5X 4 BOLT, PROTRUDING HD

BACB30NX6K5Y 20 BOLT, PROTRUDING HD

BACB30NX6K6 8 BOLT

BACB30NX6K6X 14 BOLT, PROTRUDING HD

BACB30NX6K7 43 HI-LOK

BACB30NX6K7X 13 BOLT, PROTRUDING HD

BACB30NX6K7Y 4 BOLT, PROTRUDING HD

BACB30NX6K8 142 BOLT, PROTRUDING HD

BACB30NX6K8X 6 BOLT, PROTRUDING HD

BACB30NX6K9X 2 BOLT, PROTRUDING HD

BACC30AC6 210 COLLAR

BACC30BH6 975 COLLAR

BACC30M6 168 COLLAR

BACN10TL3A12 2 NUT STANDOFF

BACR15BB4AD5C 4 RIVETS

BACR15BB6AD4C 31 RIVET, UNIVERSAL HD

BACR15GF6D5 31 RIVET

BACS40R005C005F 4 SHIM,LAMINATED

BACS40R008B035F 2 SHIM, LAMINATED

BACS40R008B036F 6 SHIM - LAMINATED

Group 10:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-201

142U0103-1 1 ALUMINUM STRAP LEFT

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

118 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 10:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-201

142U0103-2 1 ALUMINUM STRAP RIGHT

142U0103-3 2 STEEL STRAP

142U0103-4 2 STEEL STRAP

142U0103-5 2 STEEL STRAP

142U0104-1 4 TENSION TIE SPLICE

142U0105-1 1 STRINGER CLIP LEFT

142U0105-2 1 STRINGER CLIP RIGHT

142U0105-4 4 TENSION TIE SEGMENT

BACB30NX6K3 2 BOLT, PROTRUDING HD

BACB30NX6K3X 2 BOLT, PROTRUDING HD

BACB30NX8K3 203 HI-LOK

BACB30NX8K4 71 HI-LOK

BACB30NX8K5 49 HI LOK

BACB30NX8K6 14 BOLT

BACB30NX8K7 27 BOLT, HEX DRIVE

BACB30US4K11 8 BOLT, 12 PT HEAD

BACB30US4K9 13 BOLT, 12 PT HEAD

BACC30BH6 4 COLLAR

BACC30BH8 361 COLLAR

BACN10HR4CD 22 NUT

BACR15BB6AD4C 2 RIVET, UNIVERSAL HD

BACR15GF6D5 2 RIVET

BACS40R011B053F 4 SHIM, LAMINATED

BACS40R011B054F 4 SHIM, LAMINATED

BACW10BP4CD 22 WASHER

BACW10BP4DP 22 WASHER

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

119 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 10:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-202

142U0103-6 2 STEEL STRAP

142U0103-7 1 ALUMINUM STRAP LEFT

142U0103-8 1 ALUMINUM STRAP RIGHT

142U0103-9 2 STEEL STRAP

142U0103-10 2 STEEL STRAP

142U0104-1 4 TENSION TIE SPLICE

142U0105-4 4 TENSION TIE SEGMENT

BACB30NX8K3 163 HI-LOK

BACB30NX8K4 71 HI-LOK

BACB30NX8K5 53 HI LOK

BACB30NX8K6 14 BOLT

BACB30NX8K7 27 BOLT, HEX DRIVE

BACB30US4K10 4 BOLT, 12 PT HEAD

BACB30US4K11 14 BOLT, 12 PT HEAD

BACB30US4K9 4 BOLT, 12 PT HEAD

BACC30BH8 328 COLLAR

BACN10HR4CD 22 NUT

BACS40R011B052F 2 SHIM, LAMINATED

BACS40R011B059F 2 SHIM, LAMINATED

BACS40R011B062F 2 SHIM, LAMINATED

BACS40R011B064F 2 SHIM, LAMINATED

BACW10BP4CD 22 WASHER

BACW10BP4DP 22 WASHER

Group 1, 13:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-203

142U0103-11 1 ALUMINUM STRAP LEFT

142U0103-12 1 ALUMINUM STRAP RIGHT

142U0103-13 2 STEEL STRAP

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

120 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 1, 13:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-203

142U0103-14 2 STEEL STRAP

142U0103-15 2 STEEL STRAP

142U0103-16 2 FILLER

142U0103-17 2 DOUBLER

142U0103-18 2 DOUBLER SPLICE

142U0103-19 2 FILLER

142U0104-3 4 TENSION TIE SPLICE

142U0104-24 1 ANGLE

142U0104-25 1 ANGLE

142U0105-5 4 TENSION TIE SEGMENT

BACB30NW6K5X 2 BOLT, 100 DEG HEX DR

BACB30NX6K4Y 14 BOLT, PROTRUDING HD

BACB30NX6K5X 8 BOLT, PROTRUDING HD

BACB30NX6K7X 18 BOLT, PROTRUDING HD

BACB30NX6K8X 2 BOLT, PROTRUDING HD

BACB30NX8K3 185 HI-LOK

BACB30NX8K4 58 HI-LOK

BACB30NX8K5 36 HI LOK

BACB30NX8K6 40 BOLT

BACB30NX8K7 27 BOLT, HEX DRIVE

BACB30US4K10 6 BOLT, 12 PT HEAD

BACB30US5K11 4 BOLT, 12 PT HEAD

BACB30US5K12 8 BOLT, 12 PT HEAD

BACC30AC6 14 COLLAR

BACC30BH6 29 COLLAR

BACC30BH8 346 COLLAR

BACC30M6 2 COLLAR

BACF3F009J051NG 2 FILLER, FLAT

BACN10HR4CD 6 NUT

BACN10HR5CD 14 NUT

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

121 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 1, 13:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-203

BACS40R008B051F 8 SHIM, LAMINATED

BACW10BP4CD 6 WASHER

BACW10BP4DP 6 WASHER

BACW10BP5CD 14 CSK WASHER

BACW10BP5DP 14 WASHER

Group 2, 14:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-204

142U0103-18 2 DOUBLER SPLICE

142U0103-21 1 ALUMINUM STRAP LEFT

142U0103-22 1 ALUMINUM STRAP RIGHT

142U0103-23 2 STEEL STRAP

142U0103-24 2 STEEL STRAP

142U0103-25 2 STEEL STRAP

142U0103-26 2 DOUBLER

142U0103-27 2 FILLER

142U0104-3 4 TENSION TIE SPLICE

142U0105-5 4 TENSION TIE SEGMENT

BACB30NX8K3 168 HI-LOK

BACB30NX8K4 62 HI-LOK

BACB30NX8K5 36 HI LOK

BACB30NX8K6 40 BOLT

BACB30NX8K7 31 BOLT, HEX DRIVE

BACB30US4K9 4 BOLT, 12 PT HEAD

BACB30US5K10 4 BOLT, 12 PT HEAD

BACB30US5K11 8 BOLT, 12 PT HEAD

BACC30BH8 332 COLLAR

BACN10HR4CD 4 NUT

BACN10HR5CD 13 NUT

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

122 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 2, 14:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-204

BACS40R008B052F 8 SHIM,LAMINATED

BACW10BP4CD 4 WASHER

BACW10BP4DP 4 WASHER

BACW10BP5CD 13 CSK WASHER

BACW10BP5DP 13 WASHER

Group 3:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-205

142U0103-18 2 DOUBLER SPLICE

142U0103-28 2 FILLER

142U0103-29 1 ALUMINUM STRAP LEFT

142U0103-30 1 ALUMINUM STRAP RIGHT

142U0103-31 2 STEEL STRAP

142U0103-32 2 STEEL STRAP

142U0103-33 2 STEEL STRAP

142U0103-34 2 DOUBLER

142U0104-3 4 TENSION TIE SPLICE

142U0105-5 4 TENSION TIE SEGMENT

BACB30NX8K3 172 HI-LOK

BACB30NX8K4 62 HI-LOK

BACB30NX8K5 36 HI LOK

BACB30NX8K6 40 BOLT

BACB30NX8K7 31 BOLT, HEX DRIVE

BACB30US4K9 4 BOLT, 12 PT HEAD

BACB30US5K10 4 BOLT, 12 PT HEAD

BACB30US5K11 8 BOLT, 12 PT HEAD

BACC30BH8 337 COLLAR

BACN10HR4CD 4 NUT

BACN10HR5CD 13 NUT

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

123 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 3:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-205

BACS40R008B051F 8 SHIM, LAMINATED

BACW10BP4CD 4 WASHER

BACW10BP4DP 4 WASHER

BACW10BP5CD 13 CSK WASHER

BACW10BP5DP 13 WASHER

Group 10:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-206

142U0103-35 1 ALUMINUM STRAP LEFT

142U0103-36 1 ALUMINUM STRAP RIGHT

142U0103-37 2 STEEL STRAP

142U0103-38 2 STEEL STRAP

142U0103-39 2 STEEL STRAP

142U0104-1 4 TENSION TIE SPLICE

142U0105-4 4 TENSION TIE SEGMENT

BACB30NX8K3 150 HI-LOK

BACB30NX8K4 62 HI-LOK

BACB30NX8K5 47 HI LOK

BACB30NX8K6 14 BOLT

BACB30NX8K7 33 BOLT, HEX DRIVE

BACB30US4K7 4 BOLT, 12 PT HEAD

BACB30US4K8 2 BOLT, 12 PT HEAD

BACB30US4K9 14 BOLT, 12 PT HEAD

BACC30BH8 306 COLLAR

BACN10HR4CD 20 NUT

BACS40R011B052F 2 SHIM, LAMINATED

BACS40R011B055F 2 SHIM, LAMINATED

BACS40R011B057F 4 SHIM LAMINATED

BACW10BP4CD 20 WASHER

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

124 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 10:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-206

BACW10BP4DP 20 WASHER

Group 1-2, 8, 11, 13-15:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-207

142U0103-18 2 DOUBLER SPLICE

142U0103-40 2 FILLER

142U0103-41 1 ALUMINUM STRAP LEFT

142U0103-42 1 ALUMINUM STRAP RIGHT

142U0103-43 2 STEEL STRAP

142U0103-44 2 STEEL STRAP

142U0103-45 2 STEEL STRAP

142U0103-46 2 DOUBLER

142U0103-47 2 FILLER

142U0103-48 2 FILLER

142U0104-3 4 TENSION TIE SPLICE

142U0104-26 1 CHORD

142U0104-27 1 CHORD

142U0105-5 4 TENSION TIE SEGMENT

BACB30NX6K5X 11 BOLT, PROTRUDING HD

BACB30NX6K6X 2 BOLT, PROTRUDING HD

BACB30NX6K7X 22 BOLT, PROTRUDING HD

BACB30NX8K3 172 HI-LOK

BACB30NX8K4 58 HI-LOK

BACB30NX8K5 36 HI LOK

BACB30NX8K6 40 BOLT

BACB30NX8K7 27 BOLT, HEX DRIVE

BACB30US4K10 4 BOLT, 12 PT HEAD

BACB30US4K11 4 BOLT, 12 PT HEAD

BACB30US4K12 8 BOLT, 12 PT HEAD

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

125 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 1-2, 8, 11, 13-15:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-207

BACB30US4K15 4 BOLT, 12 PT HEAD

BACC30BH6 35 COLLAR

BACC30BH8 333 COLLAR

BACF3H10XP010HN 4 FILLER, RECTANGULAR

BACN10HR4CD 22 NUT

BACS40R008B051F 8 SHIM, LAMINATED

BACW10BP4CD 22 WASHER

BACW10BP4DP 22 WASHER

Group 3, 12:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-208

142U0103-18 2 DOUBLER SPLICE

142U0103-49 1 ALUMINUM STRAP LEFT

142U0103-50 1 ALUMINUM STRAP RIGHT

142U0103-51 2 STEEL STRAP

142U0103-52 2 STEEL STRAP

142U0103-53 2 STEEL STRAP

142U0103-54 2 FILLER

142U0103-55 2 DOUBLER

142U0104-3 4 TENSION TIE SPLICE

142U0105-5 4 TENSION TIE SEGMENT

BACB30NX8K3 172 HI-LOK

BACB30NX8K4 58 HI-LOK

BACB30NX8K5 36 HI LOK

BACB30NX8K6 40 BOLT

BACB30NX8K7 27 BOLT, HEX DRIVE

BACB30US4K10 4 BOLT, 12 PT HEAD

BACB30US4K11 8 BOLT, 12 PT HEAD

BACB30US4K14 4 BOLT, 12 PT HEAD

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

126 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 3, 12:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-208

BACB30US4K9 4 BOLT, 12 PT HEAD

BACC30BH8 333 COLLAR

BACF3H10XP010HN 4 FILLER, RECTANGULAR

BACN10HR4CD 22 NUT

BACS40R008B051F 8 SHIM, LAMINATED

BACW10BP4CD 22 WASHER

BACW10BP4DP 22 WASHER

Group 10:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-209

142U0103-56 2 STEEL STRAP

142U0103-57 1 ALUMINUM STRAP LEFT

142U0103-58 1 ALUMINUM STRAP RIGHT

142U0103-59 2 STEEL STRAP

142U0103-60 2 STEEL STRAP

142U0104-3 4 TENSION TIE SPLICE

144U0064-66 4 TENSION TIE STOCK SEGMENT

BACB30NX8K3 108 HI-LOK

BACB30NX8K4 56 HI-LOK

BACB30NX8K5 49 HI LOK

BACB30NX8K6 16 BOLT

BACB30NX8K7 27 BOLT, HEX DRIVE

BACB30US3K8Y 2 BOLT

BACB30US4K10 11 BOLT, 12 PT HEAD

BACB30US4K14 2 BOLT, 12 PT HEAD

BACB30US4K9 4 BOLT, 12 PT HEAD

BACC30BH8 253 COLLAR

BACF3H10XK010HN 2 FILLER, RECTANGULAR

BACN10HR3CD 2 SELF-LOCKING NUT

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

127 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 10:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-209

BACN10HR4CD 17 NUT

BACS40R008B051F 2 SHIM, LAMINATED

BACS40R008B055F 6 SHIM, LAMINATED

BACW10BP32CD 2 WASHER, PLAIN

BACW10BP32DP 2 WASHER

BACW10BP4CD 17 WASHER

BACW10BP4DP 17 WASHER

Group 1-5, 8-9, 11-16:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-210

142U0103-61 1 ALUMINUM STRAP LEFT

142U0103-62 1 ALUMINUM STRAP RIGHT

142U0103-63 2 STEEL STRAP

142U0103-64 2 STEEL STRAP

142U0103-65 2 STEEL STRAP

142U0103-66 2 FILLER

142U0104-3 4 TENSION TIE SPLICE

144U0064-66 4 TENSION TIE STOCK SEGMENT

BACB30NX8K3 185 HI-LOK

BACB30NX8K4 58 HI-LOK

BACB30NX8K5 44 HI LOK

BACB30NX8K6 14 BOLT

BACB30NX8K7 29 BOLT, HEX DRIVE

BACB30US3K10Y 4 BOLT

BACB30US3K8Y 11 BOLT

BACB30US3K9Y 6 BOLT

BACC30BH8 328 COLLAR

BACN10HR3CD 21 SELF-LOCKING NUT

BACS40R008B052F 4 SHIM,LAMINATED

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

128 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 1-5, 8-9, 11-16:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-210

BACS40R008B053F 4 SHIM, LAMINATED

BACS40R018A031F 2 SHIM LAMINATED

BACS40R018A051F 2 SHIM, LAMINATED

BACW10BP32CD 21 WASHER, PLAIN

BACW10BP32DP 21 WASHER

Group 10:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-211

142U0103-67 1 ALUMINUM STRAP LEFT

142U0103-68 1 ALUMINUM STRAP RIGHT

142U0103-69 2 STEEL STRAP

142U0103-70 2 STEEL STRAP

142U0103-71 2 STEEL STRAP

142U0104-3 4 TENSION TIE SPLICE

144U0064-66 4 TENSION TIE STOCK SEGMENT

BACB30NX8K3 104 HI-LOK

BACB30NX8K4 51 HI-LOK

BACB30NX8K5 44 HI LOK

BACB30NX8K6 18 BOLT

BACB30NX8K7 27 BOLT, HEX DRIVE

BACB30US4K7 4 BOLT, 12 PT HEAD

BACB30US4K8 4 BOLT, 12 PT HEAD

BACB30US4K9 14 BOLT, 12 PT HEAD

BACC30BH8 244 COLLAR

BACN10HR4CD 22 NUT

BACS40R008B054F 2 SHIM, LAMINATED

BACS40R008B058F 2 SHIM, LAMINATED

BACS40R008B059F 2 SHIM, LAMINATED

BACS40R008B064F 2 SHIM, LAMINATED

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

129 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 10:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-211

BACW10BP4CD 22 WASHER

BACW10BP4DP 22 WASHER

Group 1-5, 8-9, 11-16:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-212

142U0103-72 2 FILLER

142U0103-73 1 ALUMINUM STRAP LEFT

142U0103-74 1 ALUMINUM STRAP RIGHT

142U0103-75 2 STEEL STRAP

142U0103-76 2 STEEL STRAP

142U0103-77 2 STEEL STRAP

142U0104-3 4 TENSION TIE SPLICE

142U0105-5 4 TENSION TIE SEGMENT

BACB30NX8K3 117 HI-LOK

BACB30NX8K4 66 HI-LOK

BACB30NX8K5 49 HI LOK

BACB30NX8K6 14 BOLT

BACB30NX8K7 27 BOLT, HEX DRIVE

BACB30US4K10 2 BOLT, 12 PT HEAD

BACB30US4K11 2 BOLT, 12 PT HEAD

BACB30US4K12 8 BOLT, 12 PT HEAD

BACB30US4K13 4 BOLT, 12 PT HEAD

BACC30BH8 271 COLLAR

BACN10HR4CD 16 NUT

BACS40R008B052F 2 SHIM,LAMINATED

BACS40R008B053F 4 SHIM, LAMINATED

BACS40R008B054F 2 SHIM, LAMINATED

BACW10BP4CD 16 WASHER

BACW10BP4DP 16 WASHER

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

130 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 10:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-213

142U0103-78 2 FILLER

142U0103-79 1 ALUMINUM STRAP LEFT

142U0103-80 1 ALUMINUM STRAP RIGHT

142U0103-81 2 STEEL STRAP

142U0103-82 2 STEEL STRAP

142U0103-83 2 STEEL STRAP

142U0104-3 4 TENSION TIE SPLICE

144U0064-66 4 TENSION TIE STOCK SEGMENT

BACB30NX8K3 128 HI-LOK

BACB30NX8K4 51 HI-LOK

BACB30NX8K5 49 HI LOK

BACB30NX8K6 16 BOLT

BACB30NX8K7 27 BOLT, HEX DRIVE

BACB30US4K10 4 BOLT, 12 PT HEAD

BACB30US4K11 4 BOLT, 12 PT HEAD

BACB30US4K12 14 BOLT, 12 PT HEAD

BACC30BH8 271 COLLAR

BACN10HR4CD 22 NUT

BACS40R008B051F 6 SHIM, LAMINATED

BACS40R008B052F 2 SHIM,LAMINATED

BACW10BP4CD 22 WASHER

BACW10BP4DP 22 WASHER

Group 1-5, 8-9, 11-16:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-214

142U0103-84 2 FILLER

142U0103-85 1 ALUMINUM STRAP LEFT

142U0103-86 1 ALUMINUM STRAP RIGHT

142U0103-87 2 STEEL STRAP

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

131 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 1-5, 8-9, 11-16:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-214

142U0103-88 2 STEEL STRAP

142U0103-89 2 STEEL STRAP

142U0104-3 4 TENSION TIE SPLICE

144U0064-66 4 TENSION TIE STOCK SEGMENT

BACB30NX6K3 4 BOLT, PROTRUDING HD

BACB30NX8K3 112 HI-LOK

BACB30NX8K4 66 HI-LOK

BACB30NX8K5 49 HI LOK

BACB30NX8K6 14 BOLT

BACB30NX8K7 27 BOLT, HEX DRIVE

BACB30US3K15 2 BOLT

BACB30US4K10 4 BOLT, 12 PT HEAD

BACB30US4K11 4 BOLT, 12 PT HEAD

BACB30US4K12 8 BOLT, 12 PT HEAD

BACC30BH6 4 COLLAR

BACC30BH8 266 COLLAR

BACN10HR3CD 2 SELF-LOCKING NUT

BACN10HR4CD 17 NUT

BACS40R008B050F . SHIM, LAMINATED

BACS40R008B051F 4 SHIM, LAMINATED

BACS40R008B052F 4 SHIM,LAMINATED

BACW10BP3CD 2 WASHER

BACW10BP3DP 2 WASHER

BACW10BP4CD 17 WASHER

BACW10BP4DP 17 WASHER

Group 6-7:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-215

142U0103-84 2 FILLER

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

132 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 6-7:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-215

142U0103-85 1 ALUMINUM STRAP LEFT

142U0103-86 1 ALUMINUM STRAP RIGHT

142U0103-87 2 STEEL STRAP

142U0103-88 2 STEEL STRAP

142U0103-89 2 STEEL STRAP

142U0104-3 4 TENSION TIE SPLICE

144U0064-66 4 TENSION TIE STOCK SEGMENT

BACB30NX8K3 112 HI-LOK

BACB30NX8K4 66 HI-LOK

BACB30NX8K5 49 HI LOK

BACB30NX8K6 14 BOLT

BACB30NX8K7 27 BOLT, HEX DRIVE

BACB30US3K15 2 BOLT

BACB30US4K10 4 BOLT, 12 PT HEAD

BACB30US4K11 4 BOLT, 12 PT HEAD

BACB30US4K12 8 BOLT, 12 PT HEAD

BACC30BH8 266 COLLAR

BACN10HR3CD 2 SELF-LOCKING NUT

BACN10HR4CD 17 NUT

BACS40R008B050F 2 SHIM, LAMINATED

BACS40R008B051F 2 SHIM, LAMINATED

BACS40R008B053F 4 SHIM, LAMINATED

BACW10BP3CD 2 WASHER

BACW10BP3DP 2 WASHER

BACW10BP4CD 17 WASHER

BACW10BP4DP 17 WASHER

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

133 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 10:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-216

142U0103-84 2 FILLER

142U0103-90 2 STEEL STRAP

142U0103-91 1 ALUMINUM STRAP LEFT

142U0103-92 1 ALUMINUM STRAP RIGHT

142U0103-93 2 STEEL STRAP

142U0103-94 2 STEEL STRAP

142U0104-3 4 TENSION TIE SPLICE

144U0064-66 4 TENSION TIE STOCK SEGMENT

BACB30NX8K3 128 HI-LOK

BACB30NX8K4 47 HI-LOK

BACB30NX8K5 44 HI LOK

BACB30NX8K6 16 BOLT

BACB30NX8K7 29 BOLT, HEX DRIVE

BACB30US4K10 4 BOLT, 12 PT HEAD

BACB30US4K11 4 BOLT, 12 PT HEAD

BACB30US4K12 14 BOLT, 12 PT HEAD

BACC30BH8 264 COLLAR

BACN10HR4CD 22 NUT

BACS40R008B053F 6 SHIM, LAMINATED

BACS40R008B054F 2 SHIM, LAMINATED

BACW10BP4CD 22 WASHER

BACW10BP4DP 22 WASHER

Group 1-5, 8-9, 11-16:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-217

142U0103-95 1 ALUMINUM STRAP LEFT

142U0103-96 1 ALUMINUM STRAP RIGHT

142U0103-97 2 STEEL STRAP

142U0103-98 2 STEEL STRAP

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

134 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 1-5, 8-9, 11-16:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-217

142U0103-99 2 STEEL STRAP

142U0103-100 2 FILLER

142U0104-3 4 TENSION TIE SPLICE

144U0064-66 4 TENSION TIE STOCK SEGMENT

BACB30NX6K2 28 BOLT, PROTRUDING HD

BACB30NX6K3 3 BOLT, PROTRUDING HD

BACB30NX6K5 4 BOLT

BACB30NX8K2 82 BOLT, PROTRUDING HD

BACB30NX8K3 83 HI-LOK

BACB30NX8K4 58 HI-LOK

BACB30NX8K5 18 HI LOK

BACB30NX8K6 14 BOLT

BACB30NX8K7 29 BOLT, HEX DRIVE

BACB30US4K11 4 BOLT, 12 PT HEAD

BACB30US4K12 4 BOLT, 12 PT HEAD

BACB30US4K13 14 BOLT, 12 PT HEAD

BACC30BH6 38 COLLAR

BACC30BH8 279 COLLAR

BACN10HR4CD 22 NUT

BACS40R008B052F 4 SHIM,LAMINATED

BACS40R008B053F 4 SHIM, LAMINATED

BACS40R008B054F 1 SHIM, LAMINATED

BACS40R018A031F 2 SHIM LAMINATED

BACS40R018A053F 2 SHIM, LAMINATED

BACW10BP4CD 22 WASHER

BACW10BP4DP 22 WASHER

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

135 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 6-7:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-218

142U0103-95 1 ALUMINUM STRAP LEFT

142U0103-96 1 ALUMINUM STRAP RIGHT

142U0103-97 2 STEEL STRAP

142U0103-98 2 STEEL STRAP

142U0103-99 2 STEEL STRAP

142U0103-100 2 FILLER

142U0105-6 4 TENSION TIE SEGMENT

144U0063-32 4 TENSION TIE SPLICE

BACB30NX8K2 83 BOLT, PROTRUDING HD

BACB30NX8K3 51 HI-LOK

BACB30NX8K4 53 HI-LOK

BACB30NX8K5 18 HI LOK

BACB30NX8K6 14 BOLT

BACB30NX8K7 29 BOLT, HEX DRIVE

BACB30US4K11 4 BOLT, 12 PT HEAD

BACB30US4K12 4 BOLT, 12 PT HEAD

BACB30US4K13 14 BOLT, 12 PT HEAD

BACC30BH8 248 COLLAR

BACN10HR4CD 22 NUT

BACS40R008B052F 4 SHIM,LAMINATED

BACS40R008B053F 4 SHIM, LAMINATED

BACW10BP4CD 22 WASHER

BACW10BP4DP 22 WASHER

Group 10:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-219

142U0103-100 2 FILLER

142U0103-101 1 ALUMINUM STRAP LEFT

142U0103-102 1 ALUMINUM STRAP RIGHT

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

136 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 10:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-219

142U0103-103 2 STEEL STRAP

142U0103-104 2 STEEL STRAP

142U0103-105 2 STEEL STRAP

142U0104-1 4 TENSION TIE SPLICE

142U0105-4 4 TENSION TIE SEGMENT

BACB30NX8K3 124 HI-LOK

BACB30NX8K4 44 HI-LOK

BACB30NX8K5 42 HI LOK

BACB30NX8K6 14 BOLT

BACB30NX8K7 31 BOLT, HEX DRIVE

BACB30US3K16 2 BOLT

BACB30US4K11 4 BOLT, 12 PT HEAD

BACB30US4K12 4 BOLT, 12 PT HEAD

BACB30US4K13 11 BOLT, 12 PT HEAD

BACC30BH8 255 COLLAR

BACN10HR4CD 19 NUT

BACS40R011B051F 2 SHIM, LAMINATED

BACS40R011B055F 2 SHIM, LAMINATED

BACS40R011B057F 4 SHIM LAMINATED

BACW10BP3CD 2 WASHER

BACW10BP3DP 2 WASHER

BACW10BP4CD 19 WASHER

BACW10BP4DP 19 WASHER

Group 1-9, 11-16:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-220

142U0103-106 2 FILLER

142U0103-107 1 ALUMINUM STRAP LEFT

142U0103-108 1 ALUMINUM STRAP RIGHT

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

137 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 1-9, 11-16:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-220

142U0103-109 2 STEEL STRAP

142U0103-110 2 STEEL STRAP

142U0103-111 2 STEEL STRAP

142U0104-3 4 TENSION TIE SPLICE

142U0105-7 2 FITTING

144U0064-66 4 TENSION TIE STOCK SEGMENT

BACB30NX6K2 8 BOLT, PROTRUDING HD

BACB30NX8K2 93 BOLT, PROTRUDING HD

BACB30NX8K3 84 HI-LOK

BACB30NX8K4 59 HI-LOK

BACB30NX8K5 8 HI LOK

BACB30NX8K6 8 BOLT

BACB30NX8K7 29 BOLT, HEX DRIVE

BACB30NX8K8 8 BOLT

BACB30US3K12 2 BOLT, 12 PT HEAD

BACB30US4K10 2 BOLT, 12 PT HEAD

BACB30US4K11 2 BOLT, 12 PT HEAD

BACB30US4K12 14 BOLT, 12 PT HEAD

BACC30BH6 8 COLLAR

BACC30BH8 290 COLLAR

BACF3H06LC007HN 4 FILLER, RECTANGULAR

BACN10HR3CD 2 SELF-LOCKING NUT

BACN10HR4CD 18 NUT

BACS40R008B008F 2 SHIM,LAMINATED

BACS40R008B052F 4 SHIM,LAMINATED

BACS40R008B053F 4 SHIM, LAMINATED

BACS40R018A031F 2 SHIM LAMINATED

BACW10BP3CD 2 WASHER

BACW10BP3DP 2 WASHER

BACW10BP4CD 18 WASHER

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

138 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 1-9, 11-16:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-220

BACW10BP4DP 18 WASHER

Group 10:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-221

142U0103-106 2 FILLER

142U0103-112 2 STEEL STRAP

142U0103-113 1 ALUMINUM STRAP LEFT

142U0103-114 1 ALUMINUM STRAP RIGHT

142U0103-115 2 STEEL STRAP

142U0103-116 2 STEEL STRAP

142U0104-1 4 TENSION TIE SPLICE

142U0105-4 4 TENSION TIE SEGMENT

BACB30NX8K3 119 HI-LOK

BACB30NX8K4 42 HI-LOK

BACB30NX8K5 44 HI LOK

BACB30NX8K6 16 BOLT

BACB30NX8K7 29 BOLT, HEX DRIVE

BACB30US3K15 6 BOLT

BACB30US4K10 4 BOLT, 12 PT HEAD

BACB30US4K11 2 BOLT, 12 PT HEAD

BACB30US4K12 6 BOLT, 12 PT HEAD

BACC30BH8 250 COLLAR

BACN10HR3CD 6 SELF-LOCKING NUT

BACN10HR4CD 14 NUT

BACS40R011B053F 8 SHIM, LAMINATED

BACW10BP3CD 6 WASHER

BACW10BP3DP 6 WASHER

BACW10BP4CD 14 WASHER

BACW10BP4DP 14 WASHER

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

139 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 1-4, 6, 13-14:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-222

142U0103-117 1 ALUMINUM STRAP LEFT

142U0103-118 1 ALUMINUM STRAP RIGHT

142U0103-119 2 STEEL STRAP

142U0103-120 2 STEEL STRAP

142U0103-121 2 STEEL STRAP

142U0103-122 2 FILLER

142U0104-3 4 TENSION TIE SPLICE

142U0105-7 2 FITTING

144U0064-66 4 TENSION TIE STOCK SEGMENT

BACB30NX6K2 25 BOLT, PROTRUDING HD

BACB30NX8K2 8 BOLT, PROTRUDING HD

BACB30NX8K3 137 HI-LOK

BACB30NX8K4 57 HI-LOK

BACB30NX8K5 44 HI LOK

BACB30NX8K6 14 BOLT

BACB30NX8K7 37 BOLT, HEX DRIVE

BACB30US4K11 4 BOLT, 12 PT HEAD

BACB30US4K12 4 BOLT, 12 PT HEAD

BACB30US4K13 14 BOLT, 12 PT HEAD

BACC30BH6 25 COLLAR

BACC30BH8 297 COLLAR

BACF3H06LC007HN 4 FILLER, RECTANGULAR

BACN10HR4CD 22 NUT

BACS40R008B008F 2 SHIM,LAMINATED

BACS40R008B051F 8 SHIM, LAMINATED

BACW10BP4CD 22 WASHER

BACW10BP4DP 22 WASHER

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

140 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 9:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-223

142U0103-122 2 FILLER

142U0103-123 1 ALUMINUM STRAP LEFT

142U0103-124 1 ALUMINUM STRAP RIGHT

142U0103-125 2 STEEL STRAP

142U0103-126 2 STEEL STRAP

142U0103-127 2 STEEL STRAP

142U0104-3 4 TENSION TIE SPLICE

144U0064-66 4 TENSION TIE STOCK SEGMENT

BACB30NX6K2 18 BOLT, PROTRUDING HD

BACB30NX8K2 8 BOLT, PROTRUDING HD

BACB30NX8K3 115 HI-LOK

BACB30NX8K4 49 HI-LOK

BACB30NX8K5 36 HI LOK

BACB30NX8K6 4 BOLT

BACB30NX8K7 29 BOLT, HEX DRIVE

BACB30US3K16 2 BOLT

BACB30US4K11 4 BOLT, 12 PT HEAD

BACB30US4K12 4 BOLT, 12 PT HEAD

BACB30US4K13 8 BOLT, 12 PT HEAD

BACC30BH6 18 COLLAR

BACC30BH8 241 COLLAR

BACN10HR3CD 2 SELF-LOCKING NUT

BACN10HR4CD 18 NUT

BACS40R008B051F 4 SHIM, LAMINATED

BACS40R008B052F 4 SHIM,LAMINATED

BACW10BP3CD 2 WASHER

BACW10BP3DP 2 WASHER

BACW10BP4CD 18 WASHER

BACW10BP4DP 18 WASHER

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

141 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 10:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-224

142U0103-122 2 FILLER

142U0103-128 2 STEEL STRAP

142U0103-129 1 ALUMINUM STRAP LEFT

142U0103-130 1 ALUMINUM STRAP RIGHT

142U0103-131 2 STEEL STRAP

142U0103-132 2 STEEL STRAP

142U0104-1 4 TENSION TIE SPLICE

142U0105-4 4 TENSION TIE SEGMENT

BACB30NX8K3 124 HI-LOK

BACB30NX8K4 42 HI-LOK

BACB30NX8K5 40 HI LOK

BACB30NX8K6 11 BOLT

BACB30NX8K7 29 BOLT, HEX DRIVE

BACB30US3K14 2 BOLT, 12 PT HEAD

BACB30US3K15 2 BOLT

BACB30US4K11 2 BOLT, 12 PT HEAD

BACB30US4K12 2 BOLT, 12 PT HEAD

BACB30US4K13 11 BOLT, 12 PT HEAD

BACC30BH8 246 COLLAR

BACN10HR3CD 4 SELF-LOCKING NUT

BACN10HR4CD 16 NUT

BACS40R011B052F 2 SHIM, LAMINATED

BACS40R011B053F 4 SHIM, LAMINATED

BACS40R011B054F 2 SHIM, LAMINATED

BACW10BP3CD 4 WASHER

BACW10BP3DP 4 WASHER

BACW10BP4CD 16 WASHER

BACW10BP4DP 16 WASHER

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

142 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 1-4, 6, 8, 11-15:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-225

142U0103-133 1 ALUMINUM STRAP LEFT

142U0103-134 1 ALUMINUM STRAP RIGHT

142U0103-135 2 STEEL STRAP

142U0103-136 2 STEEL STRAP

142U0103-137 2 STEEL STRAP

142U0103-138 2 FILLER

142U0104-3 4 TENSION TIE SPLICE

144U0064-66 4 TENSION TIE STOCK SEGMENT

BACB30NX6K3 3 BOLT, PROTRUDING HD

BACB30NX6K4 15 BOLT, PROTRUDING HD

BACB30NX6K5 2 BOLT

BACB30NX6K7 4 HI-LOK

BACB30NX8K2 4 BOLT, PROTRUDING HD

BACB30NX8K3 137 HI-LOK

BACB30NX8K4 44 HI-LOK

BACB30NX8K5 42 HI LOK

BACB30NX8K6 4 BOLT

BACB30NX8K7 33 BOLT, HEX DRIVE

BACB30US3K10 6 BOLT, 12 PT HEAD

BACB30US4K11 4 BOLT, 12 PT HEAD

BACB30US4K12 13 BOLT, 12 PT HEAD

BACC30BH6 24 COLLAR

BACC30BH8 264 COLLAR

BACN10HR3CD 6 SELF-LOCKING NUT

BACN10HR4CD 17 NUT

BACS40R008B050F 2 SHIM, LAMINATED

BACS40R008B051F 4 SHIM, LAMINATED

BACS40R008B052F 4 SHIM,LAMINATED

BACW10BP3CD 6 WASHER

BACW10BP3DP 6 WASHER

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

143 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 1-4, 6, 8, 11-15:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-225

BACW10BP4CD 17 WASHER

BACW10BP4DP 17 WASHER

Group 5, 7, 9, 16:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-226

142U0103-138 2 FILLER

142U0103-139 1 ALUMINUM STRAP LEFT

142U0103-140 1 ALUMINUM STRAP RIGHT

142U0103-141 2 STEEL STRAP

142U0103-142 2 STEEL STRAP

142U0103-143 2 STEEL STRAP

142U0104-3 4 TENSION TIE SPLICE

144U0064-66 4 TENSION TIE STOCK SEGMENT

BACB30NX6K3 2 BOLT, PROTRUDING HD

BACB30NX6K4 14 BOLT, PROTRUDING HD

BACB30NX8K3 134 HI-LOK

BACB30NX8K4 49 HI-LOK

BACB30NX8K5 44 HI LOK

BACB30NX8K6 8 BOLT

BACB30NX8K7 29 BOLT, HEX DRIVE

BACB30US3K10 6 BOLT, 12 PT HEAD

BACB30US4K11 4 BOLT, 12 PT HEAD

BACB30US4K12 14 BOLT, 12 PT HEAD

BACC30BH6 16 COLLAR

BACC30BH8 262 COLLAR

BACN10HR3CD 6 SELF-LOCKING NUT

BACN10HR4CD 17 NUT

BACS40R008B046F 2 SHIM, LAMINATED

BACS40R008B047F 2 SHIM, LAMINATED

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

144 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 5, 7, 9, 16:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-226

BACS40R008B049F 2 SHIM - LAMINATED

BACS40R008B053F 2 SHIM, LAMINATED

BACW10BP3CD 6 WASHER

BACW10BP3DP 6 WASHER

BACW10BP4CD 17 WASHER

BACW10BP4DP 17 WASHER

Group 10:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-227

142U0103-138 2 FILLER

142U0103-144 2 STEEL STRAP

142U0103-145 1 ALUMINUM STRAP LEFT

142U0103-146 1 ALUMINUM STRAP RIGHT

142U0103-147 2 STEEL STRAP

142U0103-148 2 STEEL STRAP

142U0104-1 4 TENSION TIE SPLICE

142U0105-4 4 TENSION TIE SEGMENT

BACB30NX8K3 124 HI-LOK

BACB30NX8K4 38 HI-LOK

BACB30NX8K5 36 HI LOK

BACB30NX8K6 6 BOLT

BACB30NX8K7 29 BOLT, HEX DRIVE

BACB30US3K10 4 BOLT, 12 PT HEAD

BACB30US3K13 2 BOLT

BACB30US4K11 4 BOLT, 12 PT HEAD

BACB30US4K12 14 BOLT, 12 PT HEAD

BACC30BH8 233 COLLAR

BACN10HR3CD 6 SELF-LOCKING NUT

BACN10HR4CD 17 NUT

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

145 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 10:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-227

BACS40R011B054F 6 SHIM, LAMINATED

BACS40R011B055F 2 SHIM, LAMINATED

BACW10BP3CD 6 WASHER

BACW10BP3DP 6 WASHER

BACW10BP4CD 17 WASHER

BACW10BP4DP 17 WASHER

Group 8:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-228

142U0103-149 1 ALUMINUM STRAP LEFT

142U0103-150 1 ALUMINUM STRAP RIGHT

142U0103-151 2 STEEL STRAP

142U0103-152 2 STEEL STRAP

142U0103-153 2 STEEL STRAP

FILLER BETWEEN CLIPS OF

CREASE

142U0103-154 2

FILLER BETWEEN TT AND

FRAME

142U0103-155 2

142U0104-3 4 TENSION TIE SPLICE

142U0104-5 1 BEAM

142U0104-6 1 BEAM

142U0104-7 1 CLIP

142U0104-8 1 CLIP

142U0104-11 1 CHANNEL SEGMENT

142U0104-12 1 CHANNEL SEGMENT

144U0063-123 2 SPLICE CHANNEL

144U0064-66 4 TENSION TIE STOCK SEGMENT

BACB30NW6K5 6 BOLT, HILOK

BACB30NX6K20X 2 BOLT, PROTRUDING HD

BACB30NX6K2Y 49 BOLT, HEX DRIVE

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

146 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 8:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-228

BACB30NX6K3 6 BOLT, PROTRUDING HD

BACB30NX6K3X 8 BOLT, PROTRUDING HD

BACB30NX6K3Y 95 BOLT, PROTRUDING HD

BACB30NX6K4 49 BOLT, PROTRUDING HD

BACB30NX6K5 24 BOLT

BACB30NX6K5Y 8 BOLT, PROTRUDING HD

BACB30NX6K6 4 BOLT

BACB30NX6K7 6 HI-LOK

BACB30NX8K2 86 BOLT, PROTRUDING HD

BACB30NX8K3 93 HI-LOK

BACB30NX8K4 66 HI-LOK

BACB30NX8K5 36 HI LOK

BACB30NX8K6 4 BOLT

BACB30NX8K7 29 BOLT, HEX DRIVE

BACB30US3K10 2 BOLT, 12 PT HEAD

BACB30US3K11 4 BOLT, 12 PT HEAD

BACB30US3K13 2 BOLT

BACB30US4K12 14 BOLT, 12 PT HEAD

BACB30US4K13 2 BOLT, 12 PT HEAD

BACC30AC6 174 COLLAR

BACC30BH6 91 COLLAR

BACC30BH8 314 COLLAR

BACC30M6 18 COLLAR

BACN10HR3CD 8 SELF-LOCKING NUT

BACN10HR4CD 16 NUT

BACS40R008B052F 2 SHIM,LAMINATED

BACS40R008B053F 2 SHIM, LAMINATED

BACS40R008B054F 2 SHIM, LAMINATED

BACS40R008B055F 2 SHIM, LAMINATED

BACW10BP3CD 8 WASHER

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

147 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 8:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-228

BACW10BP3DP 8 WASHER

BACW10BP4CD 16 WASHER

BACW10BP4DP 16 WASHER

Group 3-4, 6, 12:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-229

FILLER BETWEEN CLIPS OF

CREASE

142U0103-154 2

FILLER BETWEEN TT AND

FRAME

142U0103-155 2

142U0103-156 2 STEEL STRAP

142U0103-157 1 ALUMINUM STRAP LEFT

142U0103-158 1 ALUMINUM STRAP RIGHT

142U0103-159 2 STEEL STRAP

142U0103-160 2 STEEL STRAP

142U0104-3 4 TENSION TIE SPLICE

142U0104-13 1 CHANNEL SEGMENT

142U0104-14 1 CHANNEL SEGMENT

142U0104-15 1 BEAM

142U0104-16 1 BEAM

142U0104-17 1 CLIP

142U0104-18 1 CLIP

142U0105-3 2 BRACKET

144U0063-123 2 SPLICE CHANNEL

144U0064-66 4 TENSION TIE STOCK SEGMENT

BACB30NW6K5 6 BOLT, HILOK

BACB30NW6K7 2 BOLT

BACB30NW6K8 2 HI-LOK

BACB30NX6K20X 2 BOLT, PROTRUDING HD

BACB30NX6K2Y 58 BOLT, HEX DRIVE

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

148 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 3-4, 6, 12:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-229

BACB30NX6K3 16 BOLT, PROTRUDING HD

BACB30NX6K3X 8 BOLT, PROTRUDING HD

BACB30NX6K3Y 95 BOLT, PROTRUDING HD

BACB30NX6K4 42 BOLT, PROTRUDING HD

BACB30NX6K5 20 BOLT

BACB30NX6K5Y 31 BOLT, PROTRUDING HD

BACB30NX6K6 6 BOLT

BACB30NX8K2 62 BOLT, PROTRUDING HD

BACB30NX8K3 93 HI-LOK

BACB30NX8K4 80 HI-LOK

BACB30NX8K5 36 HI LOK

BACB30NX8K6 11 BOLT

BACB30NX8K7 29 BOLT, HEX DRIVE

BACB30US3K10 6 BOLT, 12 PT HEAD

BACB30US3K14 2 BOLT, 12 PT HEAD

BACB30US3K15 2 BOLT

BACB30US4K11 4 BOLT, 12 PT HEAD

BACB30US4K12 6 BOLT, 12 PT HEAD

BACB30US4K13 2 BOLT, 12 PT HEAD

BACC30AC6 183 COLLAR

BACC30BH6 84 COLLAR

BACC30BH8 311 COLLAR

BACC30BL6 6 COLLAR

BACC30M6 22 COLLAR

BACN10HR3CD 11 SELF-LOCKING NUT

BACN10HR4CD 13 NUT

BACS40R008B051F 2 SHIM, LAMINATED

BACS40R008B053F 4 SHIM, LAMINATED

BACS40R008B054F 2 SHIM, LAMINATED

BACW10BP3CD 11 WASHER

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

149 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 3-4, 6, 12:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-229

BACW10BP3DP 11 WASHER

BACW10BP4CD 13 WASHER

BACW10BP4DP 13 WASHER

BACW10P168L 22 WASHER, PLAIN

BACW10P4L 8 WASHER, PLAIN

Group 5, 7, 9, 16:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-230

142U0103-161 1 ALUMINUM STRAP LEFT

142U0103-162 1 ALUMINUM STRAP RIGHT

142U0103-163 2 STEEL STRAP

142U0103-164 2 STEEL STRAP

142U0103-165 2 STEEL STRAP

FILLER BETWEEN TT AND

FRAME

142U0103-166 2

142U0104-3 4 TENSION TIE SPLICE

142U0104-19 1 CHANNEL SEGMENT

142U0104-20 1 CHANNEL SEGMENT

142U0105-3 2 BRACKET

142U0105-4 . TENSION TIE SEGMENT

144U0063-123 2 SPLICE CHANNEL

144U0064-66 4 TENSION TIE STOCK SEGMENT

BACB30NX6K2Y 8 BOLT, HEX DRIVE

BACB30NX6K3 8 BOLT, PROTRUDING HD

BACB30NX6K5Y 22 BOLT, PROTRUDING HD

BACB30NX8K2 77 BOLT, PROTRUDING HD

BACB30NX8K3 97 HI-LOK

BACB30NX8K4 75 HI-LOK

BACB30NX8K5 36 HI LOK

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

150 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 5, 7, 9, 16:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-230

BACB30NX8K6 14 BOLT

BACB30NX8K7 38 BOLT, HEX DRIVE

BACB30US3K10 6 BOLT, 12 PT HEAD

BACB30US4K11 11 BOLT, 12 PT HEAD

BACB30US4K12 6 BOLT, 12 PT HEAD

BACC30AC6 30 COLLAR

BACC30BH6 8 COLLAR

BACC30BH8 337 COLLAR

BACN10HR3CD 6 SELF-LOCKING NUT

BACN10HR4CD 18 NUT

BACR15BA5B4C 8 RIVET, 100 DEG

BACS40R008B052F 2 SHIM,LAMINATED

BACS40R008B054F 2 SHIM, LAMINATED

BACS40R008B056F 4 SHIM, LAMINATED

BACW10BP3CD 6 WASHER

BACW10BP3DP 6 WASHER

BACW10BP4CD 18 WASHER

BACW10BP4DP 18 WASHER

BACW10P168L 22 WASHER, PLAIN

BACW10P4L 8 WASHER, PLAIN

Group 10:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-231

FILLER BETWEEN TT AND

FRAME

142U0103-166 2

142U0103-167 1 ALUMINUM STRAP LEFT

142U0103-168 1 ALUMINUM STRAP RIGHT

142U0103-169 2 STEEL STRAP

142U0103-170 2 STEEL STRAP

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

151 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 10:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-231

142U0103-171 2 STEEL STRAP

142U0104-1 4 TENSION TIE SPLICE

142U0104-21 1 CHANNEL SEGMENT

142U0104-22 1 CHANNEL SEGMENT

142U0104-23 2 SPLICE CHANNEL

142U0105-4 4 TENSION TIE SEGMENT

BACB30NX8K2 86 BOLT, PROTRUDING HD

BACB30NX8K3 110 HI-LOK

BACB30NX8K4 82 HI-LOK

BACB30NX8K5 36 HI LOK

BACB30NX8K6 6 BOLT

BACB30NX8K7 29 BOLT, HEX DRIVE

BACB30US3K10 6 BOLT, 12 PT HEAD

BACB30US4K11 6 BOLT, 12 PT HEAD

BACB30US4K12 11 BOLT, 12 PT HEAD

BACC30BH8 349 COLLAR

BACN10HR3CD 6 SELF-LOCKING NUT

BACN10HR4CD 17 NUT

BACS40R011B053F 6 SHIM, LAMINATED

BACS40R011B055F 2 SHIM, LAMINATED

BACW10BP3CD 6 WASHER

BACW10BP3DP 6 WASHER

BACW10BP4CD 17 WASHER

BACW10BP4DP 17 WASHER

Group 13-15:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-232

142U0103-149 1 ALUMINUM STRAP LEFT

142U0103-150 1 ALUMINUM STRAP RIGHT

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

152 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 13-15:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-232

142U0103-151 2 STEEL STRAP

142U0103-152 2 STEEL STRAP

FILLER BETWEEN CLIPS OF

CREASE

142U0103-154 2

FILLER BETWEEN TT AND

FRAME

142U0103-155 2

142U0103-172 2 STEEL STRAP

142U0104-3 4 TENSION TIE SPLICE

142U0104-9 1 CLIP

142U0104-10 1 CLIP

142U0104-11 1 CHANNEL SEGMENT

142U0104-12 1 CHANNEL SEGMENT

142U0105-3 2 BRACKET

144U0063-123 2 SPLICE CHANNEL

144U0064-66 4 TENSION TIE STOCK SEGMENT

BACB30NW6K5 2 BOLT, HILOK

BACB30NX6K3 11 BOLT, PROTRUDING HD

BACB30NX6K3Y 4 BOLT, PROTRUDING HD

BACB30NX6K4 51 BOLT, PROTRUDING HD

BACB30NX6K5 18 BOLT

BACB30NX6K5Y 22 BOLT, PROTRUDING HD

BACB30NX6K6 2 BOLT

BACB30NX6K7 6 HI-LOK

BACB30NX8K2 53 BOLT, PROTRUDING HD

BACB30NX8K3 93 HI-LOK

BACB30NX8K4 75 HI-LOK

BACB30NX8K5 36 HI LOK

BACB30NX8K6 6 BOLT

BACB30NX8K7 29 BOLT, HEX DRIVE

BACB30US3K10 2 BOLT, 12 PT HEAD

BACB30US3K11 4 BOLT, 12 PT HEAD

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

153 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 13-15:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-232

BACB30US3K13 2 BOLT

BACB30US4K11 2 BOLT, 12 PT HEAD

BACB30US4K12 14 BOLT, 12 PT HEAD

BACB30VT6K5 16 BOLT

BACC30AC6 26 COLLAR

BACC30BH6 88 COLLAR

BACC30BH8 292 COLLAR

BACC30BL6 16 COLLAR

BACC30M6 2 COLLAR

BACN10HR3CD 8 SELF-LOCKING NUT

BACN10HR4CD 16 NUT

BACS40R008B052F 2 SHIM,LAMINATED

BACS40R008B053F 2 SHIM, LAMINATED

BACS40R008B054F 2 SHIM, LAMINATED

BACS40R008B055F 2 SHIM, LAMINATED

BACW10BP3CD 8 WASHER

BACW10BP3DP 8 WASHER

BACW10BP4CD 16 WASHER

BACW10BP4DP 16 WASHER

BACW10P168L 22 WASHER, PLAIN

BACW10P4L 8 WASHER, PLAIN

Group 1-2, 11:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-233

142U0103-149 1 ALUMINUM STRAP LEFT

142U0103-150 1 ALUMINUM STRAP RIGHT

142U0103-151 2 STEEL STRAP

142U0103-152 2 STEEL STRAP

142U0103-153 2 STEEL STRAP

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

154 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 1-2, 11:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-233

FILLER BETWEEN CLIPS OF

CREASE

142U0103-154 2

FILLER BETWEEN TT AND

FRAME

142U0103-155 2

142U0104-3 4 TENSION TIE SPLICE

142U0104-5 1 BEAM

142U0104-6 1 BEAM

142U0104-7 1 CLIP

142U0104-8 1 CLIP

142U0104-11 1 CHANNEL SEGMENT

142U0104-12 1 CHANNEL SEGMENT

142U0105-3 2 BRACKET

144U0063-123 2 SPLICE CHANNEL

144U0064-66 4 TENSION TIE STOCK SEGMENT

BACB30NW6K5 6 BOLT, HILOK

BACB30NX6K20X 2 BOLT, PROTRUDING HD

BACB30NX6K2Y 49 BOLT, HEX DRIVE

BACB30NX6K3 16 BOLT, PROTRUDING HD

BACB30NX6K3X 8 BOLT, PROTRUDING HD

BACB30NX6K3Y 95 BOLT, PROTRUDING HD

BACB30NX6K4 49 BOLT, PROTRUDING HD

BACB30NX6K5 24 BOLT

BACB30NX6K5Y 31 BOLT, PROTRUDING HD

BACB30NX6K6 4 BOLT

BACB30NX6K7 6 HI-LOK

BACB30NX8K2 53 BOLT, PROTRUDING HD

BACB30NX8K3 93 HI-LOK

BACB30NX8K4 75 HI-LOK

BACB30NX8K5 36 HI LOK

BACB30NX8K6 6 BOLT

BACB30NX8K7 29 BOLT, HEX DRIVE

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

155 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 1-2, 11:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-233

BACB30US3K10 2 BOLT, 12 PT HEAD

BACB30US3K11 4 BOLT, 12 PT HEAD

BACB30US3K13 2 BOLT

BACB30US4K12 14 BOLT, 12 PT HEAD

BACB30US4K13 2 BOLT, 12 PT HEAD

BACC30AC6 174 COLLAR

BACC30BH6 98 COLLAR

BACC30BH8 290 COLLAR

BACC30M6 18 COLLAR

BACN10HR3CD 8 SELF-LOCKING NUT

BACN10HR4CD 16 NUT

BACS40R008B052F 2 SHIM,LAMINATED

BACS40R008B053F 2 SHIM, LAMINATED

BACS40R008B054F 2 SHIM, LAMINATED

BACS40R008B055F 2 SHIM, LAMINATED

BACW10BP3CD 8 WASHER

BACW10BP3DP 8 WASHER

BACW10BP4CD 16 WASHER

BACW10BP4DP 16 WASHER

BACW10P168L 22 WASHER, PLAIN

BACW10P4L 8 WASHER, PLAIN

Group 8, 11-12, 15:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-234

KIT - TENSION TIE MODIFICATION, STA 900142U0102-234 -

142U0103-117 1 ALUMINUM STRAP LEFT

142U0103-118 1 ALUMINUM STRAP RIGHT

142U0103-119 2 STEEL STRAP

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3: July 10, 2013 747-53A2605

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ALERT ALERT
Group 8, 11-12, 15:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-234

142U0103-120 2 STEEL STRAP

142U0103-121 2 STEEL STRAP

142U0103-122 2 FILLER

142U0104-3 2 TENSION TIE SPLICE

142U0105-7 2 FITTING

144U0064-133 4 TENSION TIE STOCK SEGMENT

BACB30NW6K3X 2 BOLT, 100 DEG HEX DR

BACB30NX6K2 10 BOLT, PROTRUDING HD

BACB30NX6K3Y 31 BOLT, PROTRUDING HD

BACB30NX6K4 12 BOLT, PROTRUDING HD

BACB30NX6K5Y 31 BOLT, PROTRUDING HD

BACB30NX8K2 8 BOLT, PROTRUDING HD

BACB30NX8K3 268 HI-LOK

BACB30NX8K4 42 HI-LOK

BACB30NX8K5 29 HI LOK

BACB30NX8K6 8 BOLT

BACB30NX8K7 33 BOLT, HEX DRIVE

BACB30US4K11 4 BOLT, 12 PT HEAD

BACB30US4K12 4 BOLT, 12 PT HEAD

BACB30US4K13 12 BOLT, 12 PT HEAD

BACC30AC6 62 COLLAR

BACC30BH6 22 COLLAR

BACC30BH8 389 COLLAR

BACC30M6 2 COLLAR

BACF3H06LC007HN 4 FILLER, RECTANGULAR

BACN10HR4CD 20 NUT

BACS40R008B008F 2 SHIM,LAMINATED

BACS40R008B051F 4 SHIM, LAMINATED

BACW10BP4CD 20 WASHER

BACW10BP4DP 20 WASHER

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ALERT ALERT
Group 5, 7, 16:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-235

KIT - TENSION TIE MODIFICATION, STA 900142U0102-235 -

142U0103-122 2 FILLER

142U0103-123 1 ALUMINUM STRAP LEFT

142U0103-124 1 ALUMINUM STRAP RIGHT

142U0103-125 2 STEEL STRAP

142U0103-126 2 STEEL STRAP

142U0103-127 2 STEEL STRAP

142U0104-3 2 TENSION TIE SPLICE

144U0064-133 4 TENSION TIE STOCK SEGMENT

BACB30NW6K3X 2 BOLT, 100 DEG HEX DR

BACB30NX6K2 16 BOLT, PROTRUDING HD

BACB30NX6K3Y 44 BOLT, PROTRUDING HD

BACB30NX6K6X 20 BOLT, PROTRUDING HD

BACB30NX8K2 10 BOLT, PROTRUDING HD

BACB30NX8K3 251 HI-LOK

BACB30NX8K4 37 HI-LOK

BACB30NX8K5 18 HI LOK

BACB30NX8K6 4 BOLT

BACB30NX8K7 29 BOLT, HEX DRIVE

BACB30US3K16 2 BOLT

BACB30US4K11 4 BOLT, 12 PT HEAD

BACB30US4K12 4 BOLT, 12 PT HEAD

BACB30US4K13 8 BOLT, 12 PT HEAD

BACC30AC6 44 COLLAR

BACC30BH6 40 COLLAR

BACC30BH8 352 COLLAR

BACC30M6 2 COLLAR

BACN10HR3CD 2 SELF-LOCKING NUT

BACN10HR4CD 16 NUT

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ALERT ALERT
Group 5, 7, 16:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-235

BACS40R008B051F 2 SHIM, LAMINATED

BACS40R008B052F 2 SHIM,LAMINATED

BACW10BP3CD 2 WASHER

BACW10BP3DP 2 WASHER

BACW10BP4CD 16 WASHER

BACW10BP4DP 16 WASHER

Group 1-5, 8-9, 11-16:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-301

142U0104-40 2 ANGLE

142U0104-41 1 SHEAR PANEL

142U0104-42 1 SHEAR PANEL

142U0104-43 1 PANEL TIE

142U0104-44 1 PANEL TIE

142U0104-45 1 CHANNEL

142U0104-46 1 CHANNEL

142U0104-47 1 CLIP

142U0104-48 1 CLIP

BACB30NX6K2 258 BOLT, PROTRUDING HD

BACB30NX6K3 8 BOLT, PROTRUDING HD

BACB30NX6K5 6 BOLT

BACB30NX6K6 2 BOLT

BACB30NX6K9 6 BOLT

BACB30NX8K2 20 BOLT, PROTRUDING HD

BACB30NX8K3 49 HI-LOK

BACB30NX8K4 4 HI-LOK

BACC30BH6 280 COLLAR

BACC30BH8 75 COLLAR

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ALERT ALERT
Group 1-5, 8-9, 11-16:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-301

BACF3F008L015NN 2 FLAT FILLER

Group 6-7:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-302

142U0104-28 2 ANGLE

142U0104-29 1 SHEAR WEB

142U0104-30 1 SHEAR WEB

142U0104-31 1 PANEL TIE

142U0104-32 1 PANEL TIE

142U0104-33 1 CHANNEL

142U0104-34 1 CHANNEL

142U0104-35 1 ANGLE

142U0104-36 1 ANGLE

142U0104-37 2 ANGLE

142U0104-38 2 ANGLE

142U0104-39 2 ANGLE

BACB30NX6K12 8 BOLT, PROTRUDING HD

BACB30NX6K2 249 BOLT, PROTRUDING HD

BACB30NX6K3 60 BOLT, PROTRUDING HD

BACB30NX6K4 6 BOLT, PROTRUDING HD

BACB30NX6K5 10 BOLT

BACB30NX6K6 4 BOLT

BACB30NX8K2 14 BOLT, PROTRUDING HD

BACB30NX8K3 44 HI-LOK

BACB30NX8K4 2 HI-LOK

BACB30NX8K6 2 BOLT

BACB30NX8K7 2 BOLT, HEX DRIVE

BACC30BH6 339 COLLAR

BACC30BH8 66 COLLAR

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ALERT ALERT
Group 6-7:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-302

BACF3F010L028NN 2 FILLER

BACF3H38RP010HN 2 FILLER, RECTANGULAR

BACF3T01E10-08 2 FILLER,TAPERED

BACF3T01F86-08 2 FILLER, TAPERED

BACF3T02C88-08 2 FILLER, TAPERED

BACF3T02E10-09 4 FILLER, TAPERED

BACF3T05E88-08 2 FILLER, TAPERED

BACF3T10M78-08 2 FILLER, TAPERED

BACF3T14M24-08 2 FILLER, TAPERED

Group 10:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-303

140U0072U1 1 CHANNEL-DETAIL

140U0072U2 1 CHANNEL-DETAIL

142U1023U142 2 STIFFENER

142U1023U153 1 SHEAR PLATE

142U1023U154 1 SHEAR PLATE

142U1023U155 1 GUSSET

142U1023U156 1 GUSSET

142U1023U157 1 GUSSET

142U1023U158 1 GUSSET

142U1023U159 1 SHEAR PANEL

142U1023U160 1 SHEAR PANEL

142U1023U161 1 CHANNEL

142U1023U162 1 CHANNEL

142U1023U165 2 GUSSET

142U1023U166 2 GUSSET

BACB30NX6K2 169 BOLT, PROTRUDING HD

BACB30NX6K2Y 35 BOLT, HEX DRIVE

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BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 10:

Kit 142U0102

Existing Part Notes

Number

New Part Number QTY Name

-303

BACB30NX6K3 37 BOLT, PROTRUDING HD

BACB30NX6K3X 13 BOLT, PROTRUDING HD

BACB30NX6K4 4 BOLT, PROTRUDING HD

BACB30NX6K4X 18 BOLT, PROTRUDING HD

BACB30NX8K2 19 BOLT, PROTRUDING HD

BACB30NX8K3 46 HI-LOK

BACB30NX8K4 2 HI-LOK

BACB30NX8K5 4 HI LOK

BACC30AC6 35 COLLAR

BACC30BH6 241 COLLAR

BACC30BH8 71 COLLAR

2. Parts and Materials Supplied by the Operator:

Group 1-16:

Part Number / Speci- QTY Name Notes

fication

Alodine as required Chemical Conversion Coating (a) (b)

BMS 10-11, Type I as required Primer (b)

BMS 3-23, Type II as required Corrosion Inhibiting Compound (b)

BMS 5-95 as required Sealant (b)

BAC5849 as required Cadmium Plating - Brush (b)

7075-T6 Clad Sheet as required Raw Material - Filler (c)

(QQ-A-250/13)

Optional to 7075-T6

Clad Sheet

2024-T3 Clad Sheet as required Raw Material - Filler

(QQ-A-250/5)

(a) Refer to SOPM 20-43-03 for material alternatives.

(b) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data.

(c) During installation of new frame parts, it may be necessary to install radius fillers at some fastener locations. If necessary, fabricate radius fillers from 7075-T6 Clad sheet per QQ-A-250/13

or 2024-T3 Clad sheet per QQ-A-250/5. See instructions in Frame installation drawings for

details.

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BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
Group 17-18:

Part Number / Speci- QTY Name Notes

fication

65B09631-329 1 Tension Tie Installation (a)

65B01745-330 1 Frame Installation - STA 1040 (a)

65B01746-330 1 Frame Installation - STA 1060 (a) (b)

65B01746-355 1 Frame Installation - STA 1060 (a) (c)

65B01747-330 1 Frame Installation - STA 1080 (a) (b)

65B01747-357 1 Frame Installation - STA 1080 (a) (c)

65B01748-330 1 Frame Installation - STA 1100 (a)

65B01749-330 1 Frame Installation - STA 1120 (a)

65B18703-1 1 Frame Installation - STA 1140 (a)

(a) Refer to the drawings listed in Paragraph 1.J.2., Data Supplied with this Service Bulletin to

determine the detail part numbers for tension ties, shear panels and frame segments to be replaced. Operator that plan to order detail parts from Boeing should contact Boeing Spares two

years before the planned modification.

(b) R3001-R3018, R3031-R3035, R3306-R3310.

(c) R3019-R3030, R3301-R3305.

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

The 747 Structural Repair Manual Subject 747-100/200/300 SRM 51-30-09 or 747-400F SRM 51-40-09

gives data about cold working tools and sleeves necessary to do the work given in this service bulletin.

These tools are available from industry sources.

Engineering, service, and a kit of cold working tools made for this change are available from Fatigue

Technology, Inc. or West Coast Industries, Inc.

— Refer To:

FTI Kit Number: FTI-747-53A2605-1 Fatigue Technology, Inc. P.O. Box C-88388 Seattle, WA

98188 USA Phone Number (206) 246-2010 Fax (206) 244-9886

— Refer To:

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BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
WCI Kit Number: WCI-747-53A-2605 West Coast Industries, Inc. 14900 Whitman Avenue North

Seattle, WA 98133-6532 USA Phone Number (206) 365-7513 Fax (206) 365-7483

F. Special Tooling Necessary to do this Service Bulletin

No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance

and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine

operator tool supply to make sure all necessary tools are available.

Cold working tools are necessary to do the change given in this service bulletin. To get the cold working

tools, refer to Paragraph 2.E, Special Tooling - Price and Availability.

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BOEING SERVICE BULLETIN 747-53A2605

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 are in 747 SRM, Chapter 51

— Torque limits to tighten nuts and bolts are in 747 SRM, Chapter 51.

4. Use the approved fastener and process material substitutions in accordance with

747 SRM, Chapter 51. Alternate fasteners are also listed in 747 SRM, Chapter 51.

5. If the length of any fastener specified in this service bulletin does not meet the

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.

6. A Detailed Inspection is defined as: An intensive examination of a specific item,

installation, or assembly to detect damage, failure, or irregularity. Available lighting

is normally supplemented with a direct source of good lighting at an intensity deemed

appropriate. Inspection aids such as mirrors magnifying lenses, etc. may be

necessary. Surface cleaning and elaborate procedures may be required.

7. These work instructions refer to procedures included on 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.

8. If any of the existing frames or tension ties already have a repair installed which

prevents the modification given in this service bulletin, contact Boeing for instructions

before you accomplish the modification at the affected frame station.

9. Do not remove fasteners from all Tension Tie to Frame joints at the same time. Refer

to Appendix A for allowable methods to disconnect the Tension Ties.

10. Refer to SOPM 20-41-01 for explanations of Boeing finish codes.

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BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
11. Boeing Service Letter 747-SL-51-048 Damage Reporting and Repair Plan/Design

Guidelines, is an acceptable procedure to request information from Boeing for

additional structural repair instructions. The Service Letter describes what information

must be provided to Boeing before a structural repair can be provided.

12. 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.

13. 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.

14. Some Boeing parts are supplied in a temporary configuration. Those parts are

identified with a 'U', 'W', or 'Y' in place of the '-' (dash) in the part number. It is

permitted to install parts identified with a 'U', 'W', or 'Y' as an alternative to the '-'

(dash) part number. Boeing Drawing 005W0900 contains more data.

15. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS

are in Paragraph 1.E., Compliance.

B. WORK INSTRUCTIONS

Group 1-16:

NOTE: Boeing recommends accomplishment of PART 4 - Surface HFEC Inspection of the Tension

Tie Center Sections before beginning the PART 1 - Tension Tie and Frame Modification in case cracks

are found in the center section and repairs are necessary that may affect the modification.

ACCESS

1. Remove electrical power and ground the airplane. Refer to 747-100/200/300 AMM 24-22-00 or

747-400 AMM 24-22-00 as accepted procedures.

2. Get access to the tension ties and frames as follows:

a. Remove/keep seats as necessary between STA 720 and STA 940. Refer to 747-100/200/300

AMM 25-25-01 or 747-400 AMM 25-25-01 as accepted procedures.

b. Remove/keep main deck ceiling panels as necessary between STA 720 and STA 940. Refer

to 747-100/200/300 AMM 25-22-01 or 747-400 AMM 25-22-01 as accepted procedures.

c. Remove/keep insulation as necessary between STA 720 and STA 940. Refer to

747-100/200/300 AMM 25-21-04 or 747-400 AMM 25-21-04 as accepted procedures.

Group 1-16:

PART 1: TENSION TIE AND FRAME MODIFICATION

1. Remove existing shear panels as follows:

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ALERT ALERT
a. Group 1-5, 8-9, 11-16:

Remove left and right side shear panels between STA 820 and 840 in accordance with Drawing

142U0102, Sheet 33.

b. Group 6-7:

Remove left and right side shear panels between STA 840 and 860 in accordance with Drawing

142U0102, Sheet 34.

c. Group 10:

Remove left and right side shear panels between STA 780 and 800 in accordance with Drawing

142U0102, Sheet 35.

2. Group 10:

Modify existing left and right side tension tie structure at STA 720 in accordance with INSTL

142U0102-201 on Drawing 142U0102, Sheet 2. Remove small cracks and fatigue damage material

from the existing holes in the unmodified center section of the tension tie channels in accordance

with the "zero-timing" procedure of 747-400F SRM 51-10-02.

3. Group 10:

Modify existing left and right side tension tie structure at STA 740 in accordance with INSTL

142U0102-202 on Drawing 142U0102, Sheet 3. Remove small cracks and fatigue damage material

from the existing holes in the unmodified center section of the tension tie channels in accordance

with the "zero-timing" procedure of 747-400F SRM 51-10-02.

4. Group 1-3, 10, 13-14:

Modify existing left and right side tension tie structure at STA 760 as follows:

a. Group 1, 13:

Modify left and right side tension tie structure in accordance with INSTL 142U0102-203 on

Drawing 142U0102, Sheet 4. Remove small cracks and fatigue damage material from the

existing holes in the unmodified center section of the tension tie channels in accordance with

the "zero-timing" procedure of 747-100/200/300 SRM 51-10-01.

b. Group 2, 14:

Modify left and right side tension tie structure in accordance with INSTL 142U0102-204 on

Drawing 142U0102, Sheet 5. Remove small cracks and fatigue damage material from the

existing holes in the unmodified center section of the tension tie channels in accordance with

the "zero-timing" procedure of 747-100/200/300 SRM 51-10-01.

c. Group 3:

Modify left and right side tension tie structure in accordance with INSTL 142U0102-205 on

Drawing 142U0102, Sheet 6. Remove small cracks and fatigue damage material from the

existing holes in the unmodified center section of the tension tie channels in accordance with

the "zero-timing" procedure of 747-100/200/300 SRM 51-10-01.

d. Group 10:

Modify left and right side tension tie structure in accordance with INSTL 142U0102-206 on

Drawing 142U0102, Sheet 7. Remove small cracks and fatigue damage material from the

existing holes in the unmodified center section of the tension tie channels in accordance with

the "zero-timing" procedure of 747-400F SRM 51-10-02.

5. Group 1-3, 8, 10-15:

Modify existing left and right side tension tie structure at STA 780 as follows:

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BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT
a. Group 1-2, 8, 11, 13-15:

Modify left and right side tension tie structure in accordance with INSTL 142U0102-207 on

Drawing 142U0102, Sheet 8. Remove small cracks and fatigue damage material from the

existing holes in the unmodified center section of the tension tie channels in accordance with

the "zero-timing" procedure of 747-100/200/300 SRM 51-10-01.

b. Group 3, 12:

Modify left and right side tension tie structure in accordance with INSTL 142U0102-208 on

Drawing 142U0102, Sheet 9. Remove small cracks and fatigue damage material from the

existing holes in the unmodified center section of the tension tie channels in accordance with

the "zero-timing" procedure of 747-100/200/300 SRM 51-10-01.

c. Group 10:

Modify left and right side tension tie structure in accordance with INSTL 142U0102-209 on

Drawing 142U0102, Sheet 10. Remove small cracks and fatigue damage material from the

existing holes in the unmodified center section of the tension tie channels in accordance with

the "zero-timing" procedure of 747-400F SRM 51-10-02.

6. Group 1-5, 8-16:

Modify existing left and right side tension tie structure at STA 800 as follows:

a. Group 1-5, 8-9, 11-16:

Modify left and right side tension tie structure in accordance with INSTL 142U0102-210 on

Drawing 142U0102, Sheet 11. Remove small cracks and fatigue damage material from the

existing holes in the unmodified center section of the tension tie channels in accordance with

the "zero-timing" procedure of 747-100/200/300 SRM 51-10-01.

b. Group 10:

Modify left and right side tension tie structure in accordance with INSTL 142U0102-211 on

Drawing 142U0102, Sheet 12. Remove small cracks and fatigue damage material from the

existing holes in the unmodified center section of the tension tie channels in accordance with

the "zero-timing" procedure of 747-400F SRM 51-10-02.

7. Group 1-5, 8-16:

Modify existing left and right side tension tie and frame structure at STA 820 as follows:

a. Group 1-5, 9, 11-16:

Modify left and right side tension tie and frame structure in accordance with INSTL

142U0102-212 on Drawing 142U0102, Sheet 13 and INSTL 142U0101-101 on Drawing

142U0101, Sheet 2. Remove small cracks and fatigue damage material from the existing

holes in the unmodified center section of the tension tie channels in accordance with the

"zero-timing" procedure of 747-100/200/300 SRM 51-10-01.

b. Group 8:

Modify left and right side tension tie and frame structure in accordance with INSTL

142U0102-212 on Drawing 142U0102, Sheet 13 and INSTL 142U0101-102 on Drawing

142U0101, Sheet 3. Remove small cracks and fatigue damage material from the existing

holes in the unmodified center section of the tension tie channels in accordance with the

"zero-timing" procedure of 747-100/200/300 SRM 51-10-01.

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ALERT ALERT
c. Group 10:

Modify left and right side tension tie and frame structure in accordance with INSTL

142U0102-213 on Drawing 142U0102, Sheet 14 and INSTL 142U0101-103 on Drawing

142U0101, Sheet 4. Remove small cracks and fatigue damage material from the existing

holes in the unmodified center section of the tension tie channels in accordance with the

"zero-timing" procedure of 747-400F SRM 51-10-02.

8. Modify existing left and right side tension tie and frame structure at STA 840 as follows:

a. Group 1-5, 9, 11-16:

Modify left and right side tension tie and frame structure in accordance with INSTL

142U0102-214 on Drawing 142U0102, Sheet 15 and INSTL 142U0101-104 on Drawing

142U0101, Sheet 5. Remove small cracks and fatigue damage material from the existing

holes in the unmodified center section of the tension tie channels in accordance with the

"zero-timing" procedure of 747-100/200/300 SRM 51-10-01.

b. Group 6-7:

Modify left and right side tension tie and frame structure in accordance with INSTL

142U0102-215 on Drawing 142U0102, Sheet 16 and INSTL 142U0101-104 on Drawing

142U0101, Sheet 5. Remove small cracks and fatigue damage material from the existing

holes in the unmodified center section of the tension tie channels in accordance with the

"zero-timing" procedure of 747-100/200/300 SRM 51-10-01.

c. Group 8:

Modify left and right side tension tie and frame structure in accordance with INSTL

142U0102-214 on Drawing 142U0102, Sheet 15 and INSTL 142U0101-105 on Drawing

142U0101, Sheet 6. Remove small cracks and fatigue damage material from the existing

holes in the unmodified center section of the tension tie channels in accordance with the

"zero-timing" procedure of 747-100/200/300 SRM 51-10-01.

d. Group 10:

Modify left and right side tension tie and frame structure in accordance with INSTL

142U0102-216 on Drawing 142U0102, Sheet 17 and INSTL 142U0101-106 on Drawing

142U0101, Sheet 7. Remove small cracks and fatigue damage material from the existing

holes in the unmodified center section of the tension tie channels in accordance with the

"zero-timing" procedure of 747-400F SRM 51-10-02.

9. Modify existing left and right side tension tie and frame structure at STA 860 as follows:

a. Group 1-5, 11-15:

Modify left and right side tension tie and frame structure in accordance with INSTL

142U0102-217 on Drawing 142U0102, Sheet 18 and INSTL 142U0101-107 on Drawing

142U0101, Sheet 8. Remove small cracks and fatigue damage material from the existing

holes in the unmodified center section of the tension tie channels in accordance with the

"zero-timing" procedure of 747-100/200/300 SRM 51-10-01.

b. Group 6-7:

Modify left and right side tension tie and frame structure in accordance with INSTL

142U0102-218 on Drawing 142U0102, Sheet 19 and INSTL 142U0101-107 on Drawing

142U0101, Sheet 8. Remove small cracks and fatigue damage material from the existing

holes in the unmodified center section of the tension tie channels in accordance with the

"zero-timing" procedure of 747-100/200/300 SRM 51-10-01.

Export Controlled ECCN: 9E991 - BOEING

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ALERT ALERT
c. Group 8:

Modify left and right side tension tie and frame structure in accordance with INSTL

142U0102-217 on Drawing 142U0102, Sheet 18 and INSTL 142U0101-108 on Drawing

142U0101, Sheet 9. Remove small cracks and fatigue damage material from the existing

holes in the unmodified center section of the tension tie channels in accordance with the

"zero-timing" procedure of 747-100/200/300 SRM 51-10-01.

d. Group 9, 16:

Modify left and right side tension tie and frame structure in accordance with INSTL

142U0102-217 on Drawing 142U0102, Sheet 18 and INSTL 142U0101-109 on Drawing

142U0101, Sheet 10. Remove small cracks and fatigue damage material from the existing

holes in the unmodified center section of the tension tie channels in accordance with the

"zero-timing" procedure of 747-100/200/300 SRM 51-10-01.

e. Group 10:

Modify left and right side tension tie and frame structure in accordance with INSTL

142U0102-219 on Drawing 142U0102, Sheet 20 and INSTL 142U0101-110 on Drawing

142U0101, Sheet 11. Remove small cracks and fatigue damage material from the existing

holes in the unmodified center section of the tension tie channels in accordance with the

"zero-timing" procedure of 747-400F SRM 51-10-02.

10. Modify existing left and right side tension tie and frame structure at STA 880 as follows:

a. Group 1-9, 11-16:

Modify left and right side tension tie and frame structure in accordance with INSTL

142U0102-220 on Drawing 142U0102, Sheet 21 and INSTL 142U0101-111 on Drawing

142U0101, Sheet 12. Remove small cracks and fatigue damage material from the existing

holes in the unmodified center section of the tension tie channels in accordance with the

"zero-timing" procedure of 747-100/200/300 SRM 51-10-01.

b. Group 10:

Modify left and right side tension tie and frame structure in accordance with INSTL

142U0102-221 on Drawing 142U0102, Sheet 22 and INSTL 142U0101-112 on Drawing

142U0101, Sheet 13. Remove small cracks and fatigue damage material from the existing

holes in the unmodified center section of the tension tie channels in accordance with the

"zero-timing" procedure of 747-400F SRM 51-10-02.

11. Modify existing left and right side tension tie and frame structure at STA 900 as follows:

a. Group 1-4, 6, 13-14:

Modify left and right side tension tie and frame structure in accordance with INSTL

142U0102-222 on Drawing 142U0102, Sheet 23 and INSTL 142U0101-113 on Drawing

142U0101, Sheet 14. Remove small cracks and fatigue damage material from the existing

holes in the unmodified center section of the tension tie channels in accordance with the

"zero-timing" procedure of 747-100/200/300 SRM 51-10-01.

b. Group 5, 7:

Modify left and right side tension tie and frame structure in accordance with INSTL

142U0102-235 on Drawing 142U0102, Sheet 37 and INSTL 142U0101-125 on Drawing

142U0101, Sheet 18. Remove small cracks and fatigue damage material from the existing

holes in the unmodified center section of the tension tie channels in accordance with the

"zero-timing" procedure of 747-100/200/300 SRM 51-10-01.

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ALERT ALERT
c. Group 8:

Modify left and right side tension tie and frame structure in accordance with INSTL

142U0102-234 on Drawing 142U0102, Sheet 36 and INSTL 142U0101-114 on Drawing

142U0101, Sheet 15. Remove small cracks and fatigue damage material from the existing

holes in the unmodified center section of the tension tie channels in accordance with the

"zero-timing" procedure of 747-100/200/300 SRM 51-10-01.

d. Group 9:

Modify left and right side tension tie and frame structure in accordance with INSTL

142U0102-223 on Drawing 142U0102, Sheet 24 and INSTL 142U0101-115 on Drawing

142U0101, Sheet 16. Remove small cracks and fatigue damage material from the existing

holes in the unmodified center section of the tension tie channels in accordance with the

"zero-timing" procedure of 747-100/200/300 SRM 51-10-01.

e. Group 10:

Modify left and right side tension tie and frame structure in accordance with INSTL

142U0102-224 on Drawing 142U0102, Sheet 25 and INSTL 142U0101-116 on Drawing

142U0101, Sheet 17. Remove small cracks and fatigue damage material from the existing

holes in the unmodified center section of the tension tie channels in accordance with the

"zero-timing" procedure of 747-400F SRM 51-10-02.

f. Group 11-12, 15:

Modify left and right side tension tie and frame structure in accordance with INSTL

142U0102-234 on Drawing 142U0102, Sheet 36 and INSTL 142U0101-113 on Drawing

142U0101, Sheet 14. Remove small cracks and fatigue damage material from the existing

holes in the unmodified center section of the tension tie channels in accordance with the

"zero-timing" procedure of 747-100/200/300 SRM 51-10-01.

g. Group 16:

Modify left and right side tension tie and frame structure in accordance with INSTL

142U0102-235 on Drawing 142U0102, Sheet 37 and INSTL 142U0101-115 on Drawing

142U0101, Sheet 16. Remove small cracks and fatigue damage material from the existing

holes in the unmodified center section of the tension tie channels in accordance with the

"zero-timing" procedure of 747-100/200/300 SRM 51-10-01.

12. Modify existing left and right side tension tie and frame structure at STA 920 as follows:

a. Group 1-4, 6, 8, 11-15:

Modify left and right side tension tie and frame structure in accordance with INSTL

142U0102-225 on Drawing 142U0102, Sheet 26 and INSTL 142U0101-117 on Drawing

142U0101, Sheet 19. Remove small cracks and fatigue damage material from the existing

holes in the unmodified center section of the tension tie channels in accordance with the

"zero-timing" procedure of 747-100/200/300 SRM 51-10-01.

b. Group 5, 7:

Modify left and right side tension tie and frame structure in accordance with INSTL

142U0102-226 on Drawing 142U0102, Sheet 27 and INSTL 142U0101-126 on Drawing

142U0101, Sheet 20. Remove small cracks and fatigue damage material from the existing

holes in the unmodified center section of the tension tie channels in accordance with the

"zero-timing" procedure of 747-100/200/300 SRM 51-10-01.

Export Controlled ECCN: 9E991 - BOEING

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ALERT ALERT
c. Group 9, 16:

Modify left and right side tension tie and frame structure in accordance with INSTL

142U0102-226 on Drawing 142U0102, Sheet 27 and INSTL 142U0101-119 on Drawing

142U0101, Sheet 20. Remove small cracks and fatigue damage material from the existing

holes in the unmodified center section of the tension tie channels in accordance with the

"zero-timing" procedure of 747-100/200/300 SRM 51-10-01.

d. Group 10:

Modify left and right side tension tie and frame structure in accordance with INSTL

142U0102-227 on Drawing 142U0102, Sheet 28 and INSTL 142U0101-120 on Drawing

142U0101, Sheet 21. Remove small cracks and fatigue damage material from the existing

holes in the unmodified center section of the tension tie channels in accordance with the

"zero-timing" procedure of 747-400F SRM 51-10-02.

13. Modify existing left and right side tension tie and frame structure at STA 940 as follows:

a. Group 1-2, 11:

Modify left and right side tension tie and frame structure in accordance with INSTL

142U0102-233 on Drawing 142U0102, Sheet 29 and INSTL 142U0101-121 on Drawing

142U0101, Sheet 22. Remove small cracks and fatigue damage material from the existing

holes in the unmodified center section of the tension tie channels in accordance with the

"zero-timing" procedure of 747-100/200/300 SRM 51-10-01.

b. Group 3-4, 6, 12:

Modify left and right side tension tie and frame structure in accordance with INSTL

142U0102-229 on Drawing 142U0102, Sheet 30 and INSTL 142U0101-121 on Drawing

142U0101, Sheet 22. Remove small cracks and fatigue damage material from the existing

holes in the unmodified center section of the tension tie channels in accordance with the

"zero-timing" procedure of 747-100/200/300 SRM 51-10-01.

c. Group 5, 7:

Modify left and right side tension tie and frame structure in accordance with INSTL

142U0102-230 on Drawing 142U0102, Sheet 31 and INSTL 142U0101-127 on Drawing

142U0101, Sheet 23. Remove small cracks and fatigue damage material from the existing

holes in the unmodified center section of the tension tie channels in accordance with the

"zero-timing" procedure of 747-100/200/300 SRM 51-10-01.

d. Group 8:

Modify left and right side tension tie and frame structure in accordance with INSTL

142U0102-228 on Drawing 142U0102, Sheet 29 and INSTL 142U0101-121 on Drawing

142U0101, Sheet 22. Remove small cracks and fatigue damage material from the existing

holes in the unmodified center section of the tension tie channels in accordance with the

"zero-timing" procedure of 747-100/200/300 SRM 51-10-01.

e. Group 9, 16:

Modify left and right side tension tie and frame structure in accordance with INSTL

142U0102-230 on Drawing 142U0102, Sheet 31 and INSTL 142U0101-123 on Drawing

142U0101, Sheet 23. Remove small cracks and fatigue damage material from the existing

holes in the unmodified center section of the tension tie channels in accordance with the

"zero-timing" procedure of 747-100/200/300 SRM 51-10-01.

Export Controlled ECCN: 9E991 - BOEING

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ALERT ALERT
f. Group 10:

Modify left and right side tension tie and frame structure in accordance with INSTL

142U0102-231 on Drawing 142U0102, Sheet 32 and INSTL 142U0101-124 on Drawing

142U0101, Sheet 24. Remove small cracks and fatigue damage material from the existing

holes in the unmodified center section of the tension tie channels in accordance with the

"zero-timing" procedure of 747-400F SRM 51-10-02.

g. Group 13-15:

Modify left and right side tension tie and frame structure in accordance with INSTL

142U0102-232 on Drawing 142U0102, Sheet 29 and INSTL 142U0101-121 on Drawing

142U0101, Sheet 22. Remove small cracks and fatigue damage material from the existing

holes in the unmodified center section of the tension tie channels in accordance with the

"zero-timing" procedure of 747-100/200/300 SRM 51-10-01.

14. Install new shear panels as follows:

a. Group 1-5, 8-9, 11-16:

Install left and right side shear panels between STA 820 and 840 in accordance with INSTL

142U0102-301 on Drawing 142U0102, Sheet 33.

b. Group 6-7:

Install left and right side shear panels between STA 840 and 860 in accordance with INSTL

142U0102-302 on Drawing 142U0102, Sheet 34.

c. Group 10:

Install left and right side shear panels between STA 780 and 800 in accordance with INSTL

142U0102-303 on Drawing 142U0102, Sheet 35.

Group 1-16:

PART 2: POST-MODIFICATION DETAILED INSPECTION OF UNMODIFIED AREAS OF TENSION

TIES

1. At all body stations where modification was previously done in accordance with this service bulletin,

do a detailed inspection of the remaining unmodified area of the tension tie for cracks. The

unmodified area of the tension tie at all body stations will be from approximately LBL 36 to RBL

36. Do the inspection on both sides of the tension tie (FWD and AFT) so that both tension tie

channels are inspected.

2. If no crack is found, repeat the detailed inspection for cracks in the unmodified areas of the tension

ties, at the time specified in paragraph 1.E., Compliance.

3. If any crack is found, contact Boeing for repair instructions and do the repair. Repeat the detailed

inspection for cracks in the unmodified areas of the tension ties, at the time specified in paragraph

1.E., Compliance.

Group 1-16:

PART 3: POST-MODIFICATION INSPECTION OF ALL AREAS OF THE TENSION TIES

1. Do eddy current inspections for cracks in the tension ties on the left side of the airplane in

accordance with FIGURE 8.

2. Do eddy current inspections for cracks in the tension ties on the right side of the airplane in

accordance with FIGURE 9.

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ALERT ALERT
3. If no crack is found, repeat the eddy current inspections for cracks in the tension ties, at the

compliance time specified in paragraph 1.E., Compliance..

4. If any crack is found, contact Boeing for repair instructions and do the repair. Repeat the eddy

current inspections for cracks in the tension ties, at the compliance time specified in paragraph

1.E., Compliance.

Group 1-16:

PART 4: SURFACE HFEC INSPECTION OF UNMODIFIED TENSION TIE CENTER SECTIONS

(MORE WORK for Configuration 2 airplanes)

1. Group 1-3, 13-14:

Do a surface HFEC inspection for cracks in the forward and aft tension tie channels at STA 760

thru STA 940 in accordance with FIGURE 1.

2. Group 4, 9:

Do a surface HFEC inspection for cracks in the forward and aft tension tie channels at STA 800

thru STA 940 in accordance with FIGURE 2.

3. Group 5, 16:

Do a surface HFEC inspection for cracks in the forward and aft tension tie channels at STA 800

thru STA 880, STA 920, and STA 940 in accordance with FIGURE 3.

NOTE: The STA 900 tension does not require inspection because the entire tension tie is replaced

during modification.

4. Group 6:

Do a surface HFEC inspection for cracks in the forward and aft tension tie channels at STA 840

thru STA 940 accordance with FIGURE 4.

5. Group 7:

Do a surface HFEC inspection for cracks in the forward and aft tension tie channels at STA 840

thru STA 880, STA 920, and STA 940 accordance with FIGURE 5.

NOTE: The STA 900 tension does not require inspection because the entire tension tie is replaced

during modification.

6. Group 8, 11-12, 15:

Do a surface HFEC inspection for cracks in the forward and aft tension tie channels at STA 780

thru STA 880, STA 920, and STA 940 accordance with FIGURE 6.

NOTE: The STA 900 tension does not require inspection because the entire tension tie is replaced

during modification.

7. Group 10:

Do a surface HFEC inspection for cracks in the forward and aft tension tie channels at STA 720

thru STA 940 accordance with FIGURE 7.

8. If any crack is found, contact Boeing for repair instructions and do the repair.

9. If no crack is found, no further action is required until you begin post-modification inspections at

the times given in Paragraph 1.E., Compliance.

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ALERT ALERT
Group 17:

PART 5 - MODIFICATION OF TENSION TIE AND FRAME STRUCTURE FOR GROUP 17 AIRPLANES

CAUTION: DO NOT REMOVE FASTENERS FROM ALL TENSION TIE TO FRAME JOINTS AT

THE SAME TIME. REFER TO APPENDIX A FOR THE METHOD TO DISCONNECT

THE TENSION TIES.

1. At each station location from STA 1040 to STA 1140, remove and discard the existing tension tie

channels. Also, remove and discard the existing straps (plates) and fillers at the outboard ends of

the tension ties where the tension ties attach to the frames.

2. At each station location from STA 1040 to STA 1140, remove and discard the existing frame

structure from the nearest production splice above the tension tie attachment to the nearest

production splice below the tension tie attachment. Remove the existing frame structure on both

sides of the airplane. Also, remove and discard, shear ties, stringer clips, chords, and stiffeners

on each side of the airplane where the frame structure is removed.

3. At each station location from STA 1040 to STA 1140, install a new frame structure, shear ties,

stringer clips, chords, and stiffeners on each side of the airplane. Install new structure which is the

same as the original structure in accordance with the production drawings specified in Paragraph

1.J.2., Data Supplied with this Service Bulletin.

4. At each station location from STA 1040 to STA 1140, install new tension tie channels, straps, and

fillers which are the same as the original structure in accordance with the production drawings

specified in Paragraph 1.J.2., Data Supplied with this Service Bulletin.

5. Do inspections of the replaced tension tie and frame structure in accordance with Service Bulletin

747-53A2502 at the times specified in Paragraph 1.E., Compliance.

Group 18:

PART 6 - MODIFICATION OF TENSION TIE AND FRAME STRUCTURE FOR GROUP 18 AIRPLANES

CAUTION: DO NOT REMOVE FASTENERS FROM ALL TENSION TIE TO FRAME JOINTS AT

THE SAME TIME. REFER TO APPENDIX A FOR THE METHOD TO DISCONNECT

THE TENSION TIES.

1. At each station location from STA 1060 to STA 1140, remove and discard the existing tension tie

channels. Also, remove and discard the existing straps (plates) and fillers at the outboard ends of

the tension ties where the tension ties attach to the frames.

2. At each station location from STA 1060 to STA 1140, remove and discard the existing frame

structure from the nearest production splice above the tension tie attachment to the nearest

production splice below the tension tie attachment. Remove the existing frame structure on both

sides of the airplane. Also, remove and discard, shear ties, stringer clips, chords, and stiffeners

on each side of the airplane where the frame structure is removed.

3. At each station location from STA 1060 to STA 1140, install a new frame structure, shear ties,

stringer clips, chords, and stiffeners on each side of the airplane. Install new structure which is the

same as the original structure in accordance with the production drawings specified in Paragraph

1.J.2., Data Supplied with this Service Bulletin.

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ALERT ALERT
4. At each station location from STA 1060 to STA 1140, install new tension tie channels, straps, and

fillers which are the same as the original structure in accordance with the production drawings

specified in Paragraph 1.J.2., Data Supplied with this Service Bulletin.

5. Do inspections of the replaced tension tie and frame structure in accordance with Service Bulletin

747-53A2502 at the times specified in Paragraph 1.E., Compliance.

RESTORATION

1. Apply BMS 3-23, Type II, Corrosion Inhibiting Compound to the modified areas. Refer to SOPM

20-41-05 as an accepted procedure.

2. Install/kept insulation as necessary between STA 720 and STA 940. Refer to 747-100/200/300

AMM 25-21-04 or 747-400 AMM 25-21-04 as an accepted procedure.

3. Install/kept main deck ceiling panels as necessary between STA 720 and STA 940. Refer to

747-100/200/300 AMM 25-22-01 or 747-400 AMM 25-22-01 as an accepted procedure.

4. Install/kept seats as necessary between STA 720 and STA 940. Refer to 747-100/200/300 AMM

25-25-01 or 747-400 AMM 25-25-01 as an accepted procedure.

5. Supply electrical power to the airplane. Refer to 747-100/200/300 AMM 24-22-00 or 747-400 AMM

24-22-00 as an accepted procedure.

6. Return the airplane to a serviceable condition.

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ALERT ALERT
This Figure applies only to: Group 1-3, 13-14.

FIGURE 1: SURFACE HFEC INSPECTION OF TENSION TIE CENTER SECTIONS (STA 760 - STA 940)

(SHEET 1 OF 2)

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

STEP TASK NAME PROCEDURE REFERENCES NOTES

Surface High Fre- - (a)

quency Eddy Current

Forward and Aft

Tension Tie Channels

Inspect

1

(a) Do a surface high frequency eddy current (HFEC) inspection for cracks in the center sections of the

tension ties where fasteners are not replaced and fastener holes are not zero-timed during modification.

The inspection area is approximately LBL 36 to RBL 36. Inspect around all fasteners in the inspection

area, and inspect both the forward and aft tension tie channels. This will require inspection from both the

forward and aft side of the tension tie. Do the surface HFEC inspection in accordance with 747 NDT Part

6, 51-00-00, Procedure 4 or 23.

FIGURE 1: SURFACE HFEC INSPECTION OF TENSION TIE CENTER SECTIONS (STA 760 - STA 940)

(SHEET 2 OF 2)

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ALERT ALERT
This Figure applies only to: Group 4, 9.

FIGURE 2: SURFACE HFEC INSPECTION OF TENSION TIE CENTER SECTIONS (STA 800 - STA 940)

(SHEET 1 OF 2)

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 747-53A2605

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

STEP TASK NAME PROCEDURE REFERENCES NOTES

Surface High Fre- - (a)

quency Eddy Current

Forward and Aft

Tension Tie Channels

Inspect

1

(a) Do a surface high frequency eddy current (HFEC) inspection for cracks in the center sections of the

tension ties where fasteners are not replaced and fastener holes are not zero-timed during modification.

The inspection area is approximately LBL 36 to RBL 36. Inspect around all fasteners in the inspection

area, and inspect both the forward and aft tension tie channels. This will require inspection from both the

forward and aft side of the tension tie. Do the surface HFEC inspection in accordance with 747 NDT Part

6, 51-00-00, Procedure 4 or 23.

FIGURE 2: SURFACE HFEC INSPECTION OF TENSION TIE CENTER SECTIONS (STA 800 - STA 940)

(SHEET 2 OF 2)

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ALERT ALERT
This Figure applies only to: Group 5, 16.

FIGURE 3: SURFACE HFEC INSPECTION OF TENSION TIE CENTER SECTIONS (STA 800 - STA 880, STA

920, AND STA 940)

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 747-53A2605

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

STEP TASK NAME PROCEDURE REFERENCES NOTES

Surface High Fre- - (a)

quency Eddy Current

Forward and Aft

Tension Tie Channels

Inspect

1

(a) Do a surface high frequency eddy current (HFEC) inspection for cracks in the center sections of the

tension ties where fasteners are not replaced and fastener holes are not zero-timed during modification.

The inspection area is approximately LBL 36 to RBL 36. Inspect around all fasteners in the inspection

area, and inspect both the forward and aft tension tie channels. This will require inspection from both the

forward and aft side of the tension tie. Do the surface HFEC inspection in accordance with 747 NDT Part

6, 51-00-00, Procedure 4 or 23.

FIGURE 3: SURFACE HFEC INSPECTION OF TENSION TIE CENTER SECTIONS (STA 800 - STA 880, STA

920, AND STA 940)

(SHEET 2 OF 2)

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ALERT ALERT
This Figure applies only to: Group 6.

FIGURE 4: SURFACE HFEC INSPECTION OF TENSION TIE CENTER SECTIONS (STA 840 - STA 940)

(SHEET 1 OF 2)

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

STEP TASK NAME PROCEDURE REFERENCES NOTES

Surface High Fre- - (a)

quency Eddy Current

Forward and Aft

Tension Tie Channels

Inspect

1

(a) Do a surface high frequency eddy current (HFEC) inspection for cracks in the center sections of the

tension ties where fasteners are not replaced and fastener holes are not zero-timed during modification.

The inspection area is approximately LBL 36 to RBL 36. Inspect around all fasteners in the inspection

area, and inspect both the forward and aft tension tie channels. This will require inspection from both the

forward and aft side of the tension tie. Do the surface HFEC inspection in accordance with 747 NDT Part

6, 51-00-00, Procedure 4 or 23.

FIGURE 4: SURFACE HFEC INSPECTION OF TENSION TIE CENTER SECTIONS (STA 840 - STA 940)

(SHEET 2 OF 2)

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ALERT ALERT
This Figure applies only to: Group 7.

FIGURE 5: SURFACE HFEC INSPECTION OF TENSION TIE CENTER SECTIONS (STA 840 - STA 880, STA

920, AND STA 940)

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

STEP TASK NAME PROCEDURE REFERENCES NOTES

Surface High Fre- - (a)

quency Eddy Current

Forward and Aft

Tension Tie Channels

Inspect

1

(a) Do a surface high frequency eddy current (HFEC) inspection for cracks in the center sections of the

tension ties where fasteners are not replaced and fastener holes are not zero-timed during modification.

The inspection area is approximately LBL 36 to RBL 36. Inspect around all fasteners in the inspection

area, and inspect both the forward and aft tension tie channels. This will require inspection from both the

forward and aft side of the tension tie. Do the surface HFEC inspection in accordance with 747 NDT Part

6, 51-00-00, Procedure 4 or 23.

FIGURE 5: SURFACE HFEC INSPECTION OF TENSION TIE CENTER SECTIONS (STA 840 - STA 880, STA

920, AND STA 940)

(SHEET 2 OF 2)

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ALERT ALERT
This Figure applies only to: Group 8, 11-12, 15.

FIGURE 6: SURFACE HFEC INSPECTION OF TENSION TIE CENTER SECTIONS (STA 780 - STA 880, STA

920, AND STA 940)

(SHEET 1 OF 2)

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

STEP TASK NAME PROCEDURE REFERENCES NOTES

Surface High Fre- - (a)

quency Eddy Current

Forward and Aft

Tension Tie Channels

Inspect

1

(a) Do a surface high frequency eddy current (HFEC) inspection for cracks in the center sections of the

tension ties where fasteners are not replaced and fastener holes are not zero-timed during modification.

The inspection area is approximately LBL 36 to RBL 36. Inspect around all fasteners in the inspection

area, and inspect both the forward and aft tension tie channels. This will require inspection from both the

forward and aft side of the tension tie. Do the surface HFEC inspection in accordance with 747 NDT Part

6, 51-00-00, Procedure 4 or 23.

FIGURE 6: SURFACE HFEC INSPECTION OF TENSION TIE CENTER SECTIONS (STA 780 - STA 880, STA

920, AND STA 940)

(SHEET 2 OF 2)

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This Figure applies only to: Group 10.

FIGURE 7: SURFACE HFEC INSPECTION OF TENSION TIE CENTER SECTIONS (STA 720 - STA 940)

(SHEET 1 OF 3)

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ALERT ALERT
FIGURE 7: SURFACE HFEC INSPECTION OF TENSION TIE CENTER SECTIONS (STA 720 - STA 940)

(SHEET 2 OF 3)

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

STEP TASK NAME PROCEDURE REFERENCES NOTES

Surface High Fre- - (a)

quency Eddy Current

Forward and Aft

Tension Tie Channels

Inspect

1

(a) Do a surface high frequency eddy current (HFEC) inspection for cracks in the center sections of the

tension ties where fasteners are not replaced and fastener holes are not zero-timed during modification.

The inspection area is approximately LBL 36 to RBL 36. Inspect around all fasteners in the inspection

area, and inspect both the forward and aft tension tie channels. This will require inspection from both the

forward and aft side of the tension tie. Do the surface HFEC inspection in accordance with 747 NDT Part

6, 51-00-00, Procedure 4 or 23.

FIGURE 7: SURFACE HFEC INSPECTION OF TENSION TIE CENTER SECTIONS (STA 720 - STA 940)

(SHEET 3 OF 3)

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ALERT ALERT
This Figure applies only to: Group 1-16.

FIGURE 8: EDDY CURRENT INSPECTIONS OF ALL AREAS OF TENSION TIES - LEFT SIDE

(SHEET 1 OF 5)

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

NOTE: The tension tie shown on Drawing 624U0077 is an example of one configuration. However, the number

and locations of straps, locations of tension tie splice channels, and number and location of attached

fittings will vary depending on airplane configuration and station location. If the following steps are not

appropriate for inspection of all configurations and station locations, operators should use change the

inspection methods, as necessary, in order to detect any possible cracks in the tension tie channels,

splice channels, and straps around the fasteners.

STEP TASK NAME PROCEDURE REFERENCES NOTES

Surface High Fre- - AREA A (a) (p)

quency Eddy Current (HFEC)

Inspect Steel Straps

1

Forward Tension Surface HFEC - AREA A (b) (q)

Tie Channel

Inspect 2

3 Inspect Steel Straps Surface HFEC - AREA B (a) (p)

Forward Tension Surface HFEC - AREA B (b) (q)

Tie Channel

Inspect 4

Aft Tension Tie Surface HFEC - AREA B (c) (q)

Channel

Inspect 5

Low Frequency Ed- - AREA B (d) (r)

dy Current (LFEC)

Forward Tension

Tie Channel

Inspect 6

7 Inspect Aluminum Strap Surface HFEC - AREA C (e) (q)

Forward Tension Surface HFEC - AREA C (b) (q)

Tie Channel

Inspect 8

Aft Tension Tie Surface HFEC - AREA C (c) (q)

Channel

Inspect 9

Forward Tension LFEC - AREA C (d) (r)

Tie Channel

Inspect 10

Forward Tension Surface HFEC - AREA D and H (c) (q)

Tie Channel

Inspect 11

Aft Tension Tie Surface HFEC - AREA D and H (c) (q)

Channel

Inspect 12

Forward Tension Surface HFEC - AREA E (c) (q)

Tie Channel

Inspect 13

Aft Tension Tie LFEC - AREA E (f) (r)

Channel

Inspect 14

Aft Tension Tie Surface HFEC - AREA E (b) (q)

Channel

Inspect 15

Aft Tension Tie Surface HFEC - AREA E (g) (q)

Channel

Inspect 16

FIGURE 8: EDDY CURRENT INSPECTIONS OF ALL AREAS OF TENSION TIES - LEFT SIDE

(SHEET 2 OF 5)

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ALERT ALERT
STEP TASK NAME PROCEDURE REFERENCES NOTES

17 Inspect Aft Splice Channel Surface HFEC - AREA E (h) (q)

Forward Splice Surface HFEC - AREA F (h) (q)

Channel

Inspect 18

Forward Tension LFEC - AREA F (i) (r)

Tie Channel

Inspect 19

Forward Tension Surface HFEC - AREA F (g) (q)

Tie Channel

Inspect 20

Forward and Aft Surface HFEC - AREA F (j) (q)

Tension Tie Channels

Inspect

21

Aft Tension Tie Surface HFEC - AREA F (g) (q)

Channel

Inspect 22

23 Inspect Aft Splice Channel Surface HFEC - AREA F (h) (q)

Aft Tension Tie LFEC - AREA F (k) (r)

Channel

Inspect 24

Forward Splice Surface HFEC - AREA G (h) (q)

Channel

Inspect 25

Forward Tension Surface HFEC - AREA G (g) (q)

Tie Channel

Inspect 26

Forward Tension Surface HFEC - AREA G (b) (q)

Tie Channel

Inspect 27

Aft Tension Tie Surface HFEC - AREA G (c) (q)

Channel

Inspect 28

Forward Tension LFEC - AREA G (d) (r)

Tie Channel

Inspect 29

Forward Tension LFEC - (l) (i)

Tie Channel

Inspect 30

Forward and Aft Surface HFEC - (m)

Tension Tie Channel

Inspect

31

Forward and Aft Surface HFEC - (n)

Tension Tie Channels

Inspect

32

Aft Tension Tie LFEC - (l) (o)

Channel

Inspect 33

(a) Do a surface HFEC inspection for cracks in the steel straps. Do the inspection around all fasteners in

the inspection area on the forward side of the tension tie. This inspection will only detect cracks in the

exposed straps. The illustration is an example. The number of straps will vary depending on airplane

configuration, station location, and inboard/outboard location on the tension tie within the inspection area.

FIGURE 8: EDDY CURRENT INSPECTIONS OF ALL AREAS OF TENSION TIES - LEFT SIDE

(SHEET 3 OF 5)

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ALERT ALERT
STEP TASK NAME PROCEDURE REFERENCES NOTES

(b) Do a surface HFEC inspection for cracks along the outside radius on the top and bottom of the tension

tie channel.

(c) Do a surface HFEC inspection for cracks in the tension tie channel around all fasteners in the inspection

area.

(d) Do a LFEC inspection to detect cracks in the forward tension tie channel. Do the inspection around all

fasteners in the inspection area from the aft side of the tension tie. At fastener locations where the inspection probe interferes with a radius or another fastener, inspect around as much of the fastener as possible

(as much as the probe size allows).

(e) Do a surface HFEC inspection for cracks in the aluminum strap around all fasteners in the inspection

area.

(f) Do a LFEC inspection to detect cracks in the aft tension tie channel. Do the inspection around all fasteners

in the inspection area from the forward side of the tension tie. At fastener locations where the inspection

probe interferes with a radius or another fastener, inspect around as much of the fastener as possible

(as much as the probe size allows).

(g) Do a surface HFEC inspection for cracks in the tension tie channel around all fasteners in the inspection

area common to the splice channel in upper and lower surfaces.

(h) Do a surface HFEC inspection for cracks in the splice channel around all fasteners in the inspection area.

(i) Do a LFEC inspection to detect cracks in the forward tension tie channel. Do the inspection around all

fasteners in the inspection area from the forward side of the tension tie. At fastener locations where the

inspection probe interferes with a radius or another fastener, inspect around as much of the fastener as

possible (as much as the probe size allows).

(j) Do a surface HFEC inspection for cracks along the outside radius on the top and bottom of the forward

and aft tension tie channels.

(k) Do a LFEC inspection to detect cracks in the aft tension tie channel. Do the inspection around all fasteners

in the inspection area from the aft side of the tension tie. At fastener locations where the inspection probe

interferes with a radius or another fastener, inspect around as much of the fastener as possible (as much

as the probe size allows).

(l) If the vertical support post fittings shown do not exist, this step is not necessary. If different fittings or fitting

configurations exist on the tension tie, substitute appropriate inspection methods, as necessary, in order

to detect any possible cracks in the tension tie channels around fasteners.

(m) Do a surface HFEC inspection for cracks in the forward and aft tension tie channels around the fasteners

common to the lower vertical post fittings.

(n) Do a surface HFEC inspection for cracks along the outside radius on the bottom of the forward and aft

tension tie channels.

(o) Do a LFEC inspection to detect cracks in the aft tension tie channel. Do the inspection around the fasteners

from the aft side of the tension tie. At fastener locations where the inspection probe interferes with a radius

or another fastener, inspect around as much of the fastener as possible (as much as the probe size allows).

(p) Do the inspection in accordance with 747 NDT Manual Part 6, 51-00-00, Procedure 13 or 24.

(q) Do the inspection in accordance with 747 NDT Manual Part 6, 51-00-00, Procedure 4 or 23.

FIGURE 8: EDDY CURRENT INSPECTIONS OF ALL AREAS OF TENSION TIES - LEFT SIDE

(SHEET 4 OF 5)

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ALERT ALERT
STEP TASK NAME PROCEDURE REFERENCES NOTES

(r) Do the inspection in accordance with 747 NDT Manual Part 6, 51-00-26. Refer to the next table for material thickness information.

MATERIAL THICKNESS FOR LOW FREQUENCY EDDY CURRENT INSPECTIONS

THICKNESS OF

LAYER TO INSPECT

THICKNESS OF

LAYER IN FRONT

OF LAYER TO EXAMINE

TENSION TIE STATIONINSPECTION GROUP

STEP

All, except Group 6-7 All 0.063 0.063

6 Group 6-7 All, except STA 860 0.063 0.063

STA 860 0.056 0.056

All, except Group 6-7 All 0.063 0.063

10 Group 6-7 All, except STA 860 0.063 0.063

STA 860 0.056 0.056

All, except Group 6-7 All 0.063 0.063

14 Group 6-7 All, except STA 860 0.063 0.063

STA 860 0.056 0.056

All, except Group 6-7 All 0.071 0.063

19 Group 6-7 All, except STA 860 0.071 0.063

STA 860 0.063 0.056

All, except Group 6-7 All 0.071 0.063

24 Group 6-7 All, except STA 860 0.071 0.063

STA 860 0.063 0.056

All, except Group 6-7 All 0.063 0.063

29 Group 6-7 All, except STA 860 0.063 0.063

STA 860 0.056 0.056

All, except Group 6-7 All 0.063 0.063

30 Group 6-7 All, except STA 860 0.063 0.063

STA 860 0.056 0.056

All, except Group 6-7 All 0.063 0.063

33 Group 6-7 All, except STA 860 0.063 0.063

STA 860 0.056 0.056

FIGURE 8: EDDY CURRENT INSPECTIONS OF ALL AREAS OF TENSION TIES - LEFT SIDE

(SHEET 5 OF 5)

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ALERT ALERT
This Figure applies only to: Group 1-16.

FIGURE 9: EDDY CURRENT INSPECTIONS OF ALL AREAS OF TENSION TIES - RIGHT SIDE

(SHEET 1 OF 5)

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

NOTE: The tension tie shown on Drawing 624U0077 is an example of one configuration. However, the number

and locations of straps, locations of tension tie splice channels, and number and location of attached

fittings will vary depending on airplane configuration and station location. If the following steps are not

appropriate for inspection of all configurations and station locations, operators should use change the

inspection methods, as necessary, in order to detect any possible cracks in the tension tie channels,

splice channels, and straps around the fasteners.

STEP TASK NAME PROCEDURE REFERENCES NOTES

Surface High Fre- - AREA A (a) (p)

quency Eddy Current (HFEC)

Inspect Steel Straps

1

Forward Tension Surface HFEC - AREA A (b) (q)

Tie Channel

Inspect 2

3 Inspect Steel Straps Surface HFEC - AREA B (a) (p)

Forward Tension Surface HFEC - AREA B (b) (q)

Tie Channel

Inspect 4

Aft Tension Tie Surface HFEC - AREA B (c) (q)

Channel

Inspect 5

Low Frequency Ed- - AREA B (d) (r)

dy Current (LFEC)

Forward Tension

Tie Channel

Inspect 6

7 Inspect Aluminum Strap Surface HFEC - AREA C (e) (q)

Forward Tension Surface HFEC - AREA C (b) (q)

Tie Channel

Inspect 8

Aft Tension Tie Surface HFEC - AREA C (c) (q)

Channel

Inspect 9

Forward Tension LFEC - AREA C (d) (r)

Tie Channel

Inspect 10

Forward Tension Surface HFEC - AREA D and H (c) (q)

Tie Channel

Inspect 11

Aft Tension Tie Surface HFEC - AREA D and H (c) (q)

Channel

Inspect 12

Forward Tension Surface HFEC - AREA E (c) (q)

Tie Channel

Inspect 13

Aft Tension Tie LFEC - AREA E (f) (r)

Channel

Inspect 14

Aft Tension Tie Surface HFEC - AREA E (b) (q)

Channel

Inspect 15

Aft Tension Tie Surface HFEC - AREA E (g) (q)

Channel

Inspect 16

FIGURE 9: EDDY CURRENT INSPECTIONS OF ALL AREAS OF TENSION TIES - RIGHT SIDE

(SHEET 2 OF 5)

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ALERT ALERT
STEP TASK NAME PROCEDURE REFERENCES NOTES

17 Inspect Aft Splice Channel Surface HFEC - AREA E (h) (q)

Forward Splice Surface HFEC - AREA F (h) (q)

Channel

Inspect 18

Forward Tension LFEC - AREA F (i) (r)

Tie Channel

Inspect 19

Forward Tension Surface HFEC - AREA F (g) (q)

Tie Channel

Inspect 20

Forward and Aft Surface HFEC - AREA F (j) (q)

Tension Tie Channels

Inspect

21

Aft Tension Tie Surface HFEC - AREA F (g) (q)

Channel

Inspect 22

23 Inspect Aft Splice Channel Surface HFEC - AREA F (h) (q)

Aft Tension Tie LFEC - AREA F (k) (r)

Channel

Inspect 24

Forward Splice Surface HFEC - AREA G (h) (q)

Channel

Inspect 25

Forward Tension Surface HFEC - AREA G (g) (q)

Tie Channel

Inspect 26

Forward Tension Surface HFEC - AREA G (b) (q)

Tie Channel

Inspect 27

Aft Tension Tie Surface HFEC - AREA G (c) (q)

Channel

Inspect 28

Forward Tension LFEC - AREA G (d) (r)

Tie Channel

Inspect 29

Forward Tension LFEC - (l) (i)

Tie Channel

Inspect 31

Forward and Aft Surface HFEC - (m)

Tension Tie Channel

Inspect

32

Forward and Aft Surface HFEC - (n)

Tension Tie Channels

Inspect

33

Aft Tension Tie LFEC - (l) (o)

Channel

Inspect 35

(a) Do a surface HFEC inspection for cracks in the steel straps. Do the inspection around all fasteners in

the inspection area on the forward side of the tension tie. This inspection will only detect cracks in the

exposed straps. The illustration is an example. The number of straps will vary depending on airplane

configuration, station location, and inboard/outboard location on the tension tie within the inspection area.

FIGURE 9: EDDY CURRENT INSPECTIONS OF ALL AREAS OF TENSION TIES - RIGHT SIDE

(SHEET 3 OF 5)

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ALERT ALERT
STEP TASK NAME PROCEDURE REFERENCES NOTES

(b) Do a surface HFEC inspection for cracks along the outside radius on the top and bottom of the tension

tie channel.

(c) Do a surface HFEC inspection for cracks in the tension tie channel around all fasteners in the inspection

area.

(d) Do a LFEC inspection to detect cracks in the forward tension tie channel. Do the inspection around all

fasteners in the inspection area from the aft side of the tension tie. At fastener locations where the inspection probe interferes with a radius or another fastener, inspect around as much of the fastener as possible

(as much as the probe size allows).

(e) Do a surface HFEC inspection for cracks in the aluminum strap around all fasteners in the inspection

area.

(f) Do a LFEC inspection to detect cracks in the aft tension tie channel. Do the inspection around all fasteners

in the inspection area from the forward side of the tension tie. At fastener locations where the inspection

probe interferes with a radius or another fastener, inspect around as much of the fastener as possible

(as much as the probe size allows).

(g) Do a surface HFEC inspection for cracks in the tension tie channel around all fasteners in the inspection

area common to the splice channel in upper and lower surfaces.

(h) Do a surface HFEC inspection for cracks in the splice channel around all fasteners in the inspection area.

(i) Do a LFEC inspection to detect cracks in the forward tension tie channel. Do the inspection around all

fasteners in the inspection area from the forward side of the tension tie. At fastener locations where the

inspection probe interferes with a radius or another fastener, inspect around as much of the fastener as

possible (as much as the probe size allows).

(j) Do a surface HFEC inspection for cracks along the outside radius on the top and bottom of the forward

and aft tension tie channels.

(k) Do a LFEC inspection to detect cracks in the aft tension tie channel. Do the inspection around all fasteners

in the inspection area from the aft side of the tension tie. At fastener locations where the inspection probe

interferes with a radius or another fastener, inspect around as much of the fastener as possible (as much

as the probe size allows).

(l) If the vertical support post fittings shown do not exist, this step is not necessary. If different fittings or fitting

configurations exist on the tension tie, substitute appropriate inspection methods, as necessary, in order

to detect any possible cracks in the tension tie channels around fasteners.

(m) Do a surface HFEC inspection for cracks in the forward and aft tension tie channels around the fasteners

common to the lower vertical post fittings.

(n) Do a surface HFEC inspection for cracks along the outside radius on the bottom of the forward and aft

tension tie channels.

(o) Do a LFEC inspection to detect cracks in the aft tension tie channel. Do the inspection around the fasteners

from the aft side of the tension tie. At fastener locations where the inspection probe interferes with a radius

or another fastener, inspect around as much of the fastener as possible (as much as the probe size allows).

(p) Do the inspection in accordance with 747 NDT Manual Part 6, 51-00-00, Procedure 13 or 24.

(q) Do the inspection in accordance with 747 NDT Manual Part 6, 51-00-00, Procedure 4 or 23.

FIGURE 9: EDDY CURRENT INSPECTIONS OF ALL AREAS OF TENSION TIES - RIGHT SIDE

(SHEET 4 OF 5)

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ALERT ALERT
STEP TASK NAME PROCEDURE REFERENCES NOTES

(r) Do the inspection in accordance with 747 NDT Manual Part 6, 51-00-26. Refer to the next table for material thickness information.

MATERIAL THICKNESS FOR LOW FREQUENCY EDDY CURRENT INSPECTIONS

THICKNESS OF

LAYER TO INSPECT

THICKNESS OF

LAYER IN FRONT

OF LAYER TO EXAMINE

TENSION TIE STATIONINSPECTION GROUP

STEP

All, except Group 6-7 All 0.063 0.063

6 Group 6-7 All, except STA 860 0.063 0.063

STA 860 0.056 0.056

All, except Group 6-7 All 0.063 0.063

10 Group 6-7 All, except STA 860 0.063 0.063

STA 860 0.056 0.056

All, except Group 6-7 All 0.063 0.063

14 Group 6-7 All, except STA 860 0.063 0.063

STA 860 0.056 0.056

All, except Group 6-7 All 0.071 0.063

19 Group 6-7 All, except STA 860 0.071 0.063

STA 860 0.063 0.056

All, except Group 6-7 All 0.071 0.063

24 Group 6-7 All, except STA 860 0.071 0.063

STA 860 0.063 0.056

All, except Group 6-7 All 0.063 0.063

29 Group 6-7 All, except STA 860 0.063 0.063

STA 860 0.056 0.056

All, except Group 6-7 All 0.063 0.063

30 Group 6-7 All, except STA 860 0.063 0.063

STA 860 0.056 0.056

All, except Group 6-7 All 0.063 0.063

33 Group 6-7 All, except STA 860 0.063 0.063

STA 860 0.056 0.056

FIGURE 9: EDDY CURRENT INSPECTIONS OF ALL AREAS OF TENSION TIES - RIGHT SIDE

(SHEET 5 OF 5)

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APPENDIX A: TENSION TIE DISCONNECTION METHODS

(SHEET 1 OF 2)

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METHOD TASK NOTES

With the airplane on its gear, disconnect every other Tension Tie from -

the Frame at both ends, as shown in the view for Method 1.

1

With the airplane on its gear, remove all but four fasteners at each end -

of each Tension Tie. Do the necessary Work Instructions specified in this

service bulletin, and re-install fasteners. Remove the remaining four fasteners at each end of each Tension Tie and do the necessary Work Instructions at those locations.

2

not

shown

APPENDIX A: TENSION TIE DISCONNECTION METHODS

(SHEET 2 OF 2)

Export Controlled ECCN: 9E991 - BOEING

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Work - See page 1 for details.

Original Issue: October 08, 2009

Revision 3 July 10, 2013 747-53A2605

203 of 203

BOEING SERVICE BULLETIN 747-53A2605

ALERT ALERT