Commercial 

Airplanes 747

Service Bulletin

ALERT

Number: 747-57A2348

Original Issue: June 12, 2015

Revision 1: February 26, 2016

ATA System: 5752

SUBJECT: WINGS - Trailing Edge Flaps - Transmission Aft Bearing Plate Assembly Replacement

Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15

CFR 300-774). An export license may be required before it is used for development, production or use by foreign

persons from specific countries. The controller of this data has the individual responsibility to abide by all export

laws.

ECCN: 9E991

BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET

Copyright © 2015 Boeing.

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2.0
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BOEING SERVICE BULLETIN 747-57A2348

ALERT ALERT

BLANK PAGE
Table of Contents

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

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

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

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

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

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 19

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 24

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 35

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38

FIGURE 1: FLAP TRACK 1 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - REMOVAL . . . 45

FIGURE 2: FLAP TRACK 2 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - REMOVAL . . . 47

FIGURE 3: FLAP TRACK 3 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - REMOVAL . . . 49

FIGURE 4: FLAP TRACK 4 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - REMOVAL . . . 51

FIGURE 5: FLAP TRACK 5 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - REMOVAL . . . 53

FIGURE 6: FLAP TRACK 6 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - REMOVAL . . . 55

FIGURE 7: FLAP TRACK 7 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - REMOVAL . . . 57

FIGURE 8: FLAP TRACK 8 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - REMOVAL . . . 59

FIGURE 9: FLAP TRACK 1 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - INSTALLATION . 61

FIGURE 10: FLAP TRACK 2 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - INSTALLATION . 63

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BOEING SERVICE BULLETIN 747-57A2348

ALERT ALERT
FIGURE 11: FLAP TRACK 3 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - INSTALLATION . 65

FIGURE 12: FLAP TRACK 4 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - INSTALLATION . 67

FIGURE 13: FLAP TRACK 5 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - INSTALLATION . 69

FIGURE 14: FLAP TRACK 6 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - INSTALLATION . 71

FIGURE 15: FLAP TRACK 7 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - INSTALLATION . 73

FIGURE 16: FLAP TRACK 8 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - INSTALLATION . 75

APPENDIX A: DELETED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 77

APPENDIX B: PART DEMAND INTENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 78

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BOEING SERVICE BULLETIN 747-57A2348

ALERT ALERT
Commercial 

Airplanes 747

Service Bulletin

ALERT

Revision Transmittal Sheet Number: 747-57A2348

Original Issue: June 12, 2015

Revision 1: February 26, 2016

ATA System: 5752

SUBJECT: WINGS - Trailing Edge Flaps - Transmission Aft Bearing Plate Assembly Replacement

This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service

bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin

mandatory.

Effects of this Revision on airplanes on which Original Issue was previously done:

None.

REASON FOR REVISION

This revision is sent to incorporate changes to the access requirements and kit found to be necessary during

the validation of the original issue.

As a part of a service bulletin validation program, this change was completed on airplane RC504 by Service

Bulletin 747-57A2348 Original Issue before the release of Revision 1 of this service bulletin. The change

completed on airplane RC504 by Service Bulletin 747-57A2348 Original Issue is equivalent to the release of

Revision 1 of this service bulletin. Airplane RC504 has the configuration of a Group 4 airplane.

These sections were changed:

1. In Summary, Background, cost benefit analysis statement removed, validation paragraph added and

summary evaluation table updated.

2. In Section 1.A.1., Airplanes, corrected the number of groups and removed airplanes, RC021, RC051

and RC052, from effectivity.

3. In Section 1.C., Reason, reason for revision added, validation paragraph added and cost benefit analysis

statement removed.

4. In Section 1.D., Description, effects of this revision paragraph added.

5. In Section 1.G., Manpower, estimates revised to include revised access steps.

6. In Section 1.J., References, AMM references added for revised access steps.

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7. In Section 2.A., Material - Price and Availability, note added to clarify the relationship between

015U2129-1 and 015U2129-2 Top Kits.

8. In Section 2.C.1., Kits/Parts, new kit added.

9. In Section 2.C.2., Parts and Materials Supplied by the Operator, parts removed and revised to 'None.'

10. In Section 3.B., Work Instructions, revised the access steps in PART 1, PART 2, PART 3 and PART

4.

11. Figures 9 thru 16, specific part marking code added.

12. Figures 12 and 13, washer quantity increased and cotter pin part number revised.

13. Appendix A: Cost Benefit Analysis deleted.

Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes,

to show the location of all content changes.

Pages with no vertical lines have no changes.

REVISION HISTORY

Original Issue: June 12, 2015

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BOEING SERVICE BULLETIN 747-57A2348

ALERT ALERT
Commercial 

Airplanes 747

Service Bulletin

ALERT

Summary Number: 747-57A2348

Original Issue: June 12, 2015

Revision 1: February 26, 2016

ATA System: 5752

SUBJECT: WINGS - Trailing Edge Flaps - Transmission Aft Bearing Plate Assembly Replacement

THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH

1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OWNER.

CONCURRENT REQUIREMENTS

None.

BACKGROUND

This service bulletin is sent to provide instruction to replace the aluminum Transmission Aft Bearing Plate

Assemblies with new titanium Transmission Aft Bearing Plate Assemblies. If the work given in this bulletin is

not completed, then the aluminum Transmission Aft Bearing Plate Assemblies could be damaged in extreme

loading conditions such as flap jams or skews. Under these conditions, damaged Transmission Bearing Plate

Assemblies could stop the flap transmission from working correctly and could result in loss of flap control.

Alternatively, if failure of one of the other components in the flap attachment or flap drive system were to occur,

the resulting redistribution of loads could result in damage to the aft bearing plate assemblies, potentially causing

detachment of the flap transmission from its flap track and possible flap departure, resulting in loss of controllability

of the airplane.

Boeing has done an analysis of the aluminum Transmission Aft Bearing Plate Assemblies. Each airplane has

eight Transmission Aft Bearing Plate Assemblies, one at each of the eight flap track locations. Static strength

analysis has shown that the aluminum Transmission Aft Bearing Plate Assemblies have inadequate strength

for one or more of the required load cases, including cases for drive system jam, flap skew, and structural

damage tolerance. These types of load cases can cause a flap transmission torque brake trip, which will then

cause additional loading on the Transmission Aft Bearing Plate Assemblies common to that flap. This could

cause damage to the Transmission Aft Bearing Plate Assemblies. The new titanium Transmission Aft Bearing

Plate Assemblies have increased strength to prevent any potential damage caused in these high load cases.

Boeing has determined this scenario by analysis and has not yet received any reports of damaged Transmission

Aft Bearing Plate Assemblies from operators.

NOTE: The work given in this service bulletin is a terminating action for the repeat inspections in Boeing Service

Bulletin (SB) 747-57-2347. Each work package in this SB can be completed independently and is

considered a terminating action for inspections in SB 747-57-2347 at that flap track only. Repeat

inspections given in SB 747-57-2347 must continue at all flap tracks where the modification given in

this SB has not been completed.

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Boeing Service Related Problem (SRP) 747-8-SRP-57-0269 is related to this service bulletin.

As a part of a service bulletin validation program, this change was completed on airplane RC504 by Service

Bulletin 747-57A2348 Original Issue before the release of Revision 1 of this service bulletin. The change

completed on airplane RC504 by Service Bulletin 747-57A2348 Original Issue is equivalent to the release of

Revision 1 of this service bulletin. Airplane RC504 has the configuration of a Group 4 airplane.

This table is provided to operators for planning purposes only. Refer to the applicable sections for more

information.

Planning Data Affected Reference

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

Paragraph 1.E., Compliance and Paragraph

1.F., Approval

AD Related Yes

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

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

Publications Affected Yes Paragraph 1.K., Publications Affected

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

Operations Manual and/or FAA Approved Airplane Flight Manual)

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

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

by the Operator

Operator Supplied Parts/Material No

Paragraph 2.F., Special Tooling Necessary to

do this Service Bulletin

Special Tooling Required No

ACTION (PRR 85901-140S)

Get access to the Transmission Aft Bearing Plate Assemblies located at each flap track. Remove and keep the

inboard and outboard flap track fairings. Remove and discard the eight existing aluminum Transmission Aft

Bearing Plate Assemblies. Install eight new titanium Transmission Aft Bearing Plate Assemblies and install kept

inboard and outboard flap track fairings. Do an inboard and outboard flap adjustment, a check of the flap position

and a trailing edge flap system test.

EFFECTIVITY

747-8, 747-8F Airplane(s). Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s).

COMPLIANCE

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service

bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin

mandatory.

Boeing recommends that the change given in this service bulletin be done within 48 months after the original

issue date of this service bulletin.

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 747-57A2348

ALERT ALERT
INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are available for airplanes in warranty as of March 12, 2014. Please refer to Paragraph

2.B., Industry Support Information. The warranty remedies will expire eight years from the original issue date of

this service bulletin.

MANPOWER

Refer to Paragraph 1.G., Manpower.

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

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

Operators are encouraged to complete the survey provided in APPENDIX B of this service bulletin to help Boeing

predict the quantity and timing of the Boeing Supplied Kits/Parts.

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ALERT ALERT
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BOEING SERVICE BULLETIN 747-57A2348

ALERT ALERT
Commercial 

Airplanes 747

Service Bulletin

ALERT

Number: 747-57A2348

Original Issue: June 12, 2015

Revision 1: February 26, 2016

ATA System: 5752

SUBJECT: WINGS - Trailing Edge Flaps - Transmission Aft Bearing Plate Assembly Replacement

THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH

1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OWNER.

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

This service bulletin is applicable to 747-8 and 747-8F Airplanes, line numbers 1420-1434,

1436-1505, 1507, 1508, and 1510-1514 in 10 Groups. The Variable Numbers and Group Information

for the applicable airplanes is given below. An equivalent change is on subsequent production

airplanes. Refer to PRR 85901-140S for data about this change.

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

Serial Number data.

GROUP CONFIGURATION DESCRIPTION

747-8F airplanes, line numbers 1420-1421 with unique track assembly

part numbers

1 -

747-8F airplanes, line numbers 1422-1423 with unique track assembly

part numbers

2 -

747-8F airplanes, line numbers 1424-1433 with unique track assembly

part numbers

3 -

747-8F airplanes, line numbers 1436-1450 with unique track assembly

part numbers

4 -

747-8 airplanes, line numbers 1434-1451 with unique track assembly

part numbers

5 -

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GROUP CONFIGURATION DESCRIPTION

747-8F airplanes, line numbers 1452-1496 with unique track assembly

part numbers

6 -

747-8 airplanes, line numbers 1453-1499 with unique track assembly

part numbers

7 -

747-8F airplanes, line numbers 1501-1505 with unique track assembly

part numbers

8 -

747-8 airplanes, line numbers 1500-1503 with unique track assembly

part numbers

9 -

747-8 airplanes, line numbers 1505-1514 with unique track assembly

part numbers

10 -

Airplane Models:

747-8, 747-8F

Variable Number Group

RC001 - RC005 5

RC006 - RC009 7

RC022 - RC023 5

RC024 - RC034 7

RC035 - RC036 9

RC037 - RC040 10

RC066 7

RC067 - RC069 10

RC501 1

RC502 2

RC503 3

RC504 4

RC505 - RC511 6

RC512 8

RC521 1

RC522 2

RC523 3

RC524 - RC528 6

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BOEING SERVICE BULLETIN 747-57A2348

ALERT ALERT
Variable Number Group

RC541 3

RC546 3

RC547 - RC549 6

RC551 - RC553 3

RC554 - RC557 4

RC558 - RC563 6

RC564 8

RC571 - RC572 3

RC573 - RC576 4

RC577 - RC582 6

RC601 3

RC602 4

RC603 - RC605 6

RC641 - RC642 6

RC671 - RC672 8

2. Spares Affected

None.

B. Concurrent Requirements

None.

C. Reason

This service bulletin is sent to provide instruction to replace the aluminum Transmission Aft Bearing

Plate Assemblies with new titanium Transmission Aft Bearing Plate Assemblies. If the work given in

this bulletin is not completed, then the aluminum Transmission Aft Bearing Plate Assemblies could be

damaged in extreme loading conditions such as flap jams or skews. Under these conditions, damaged

Transmission Bearing Plate Assemblies could stop the flap transmission from working correctly and

could result in loss of flap control. Alternatively, if failure of one of the other components in the flap

attachment or flap drive system were to occur, the resulting redistribution of loads could result in damage

to the aft bearing plate assemblies, potentially causing detachment of the flap transmission from its

flap track and possible flap departure, resulting in loss of controllability of the airplane.

Boeing has done an analysis of the aluminum Transmission Aft Bearing Plate Assemblies. Each airplane

has eight Transmission Aft Bearing Plate Assemblies, one at each of the eight flap track locations.

Static strength analysis has shown that the aluminum Transmission Aft Bearing Plate Assemblies have

inadequate strength for one or more of the required load cases, including cases for drive system jam,

flap skew, and structural damage tolerance. These types of load cases can cause a flap transmission

torque brake trip, which will then cause additional loading on the Transmission Aft Bearing Plate

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BOEING SERVICE BULLETIN 747-57A2348

ALERT ALERT
Assemblies common to that flap. This could cause damage to the Transmission Aft Bearing Plate

Assemblies. The new titanium Transmission Aft Bearing Plate Assemblies have increased strength to

prevent any potential damage caused in these high load cases. Boeing has determined this scenario

by analysis and has not yet received any reports of damaged Transmission Aft Bearing Plate Assemblies

from operators.

NOTE: The work given in this service bulletin is a terminating action for the repeat inspections in

Boeing Service Bulletin (SB) 747-57-2347. Each work package in this SB can be completed

independently and is considered a terminating action for inspections in SB 747-57-2347 at

that flap track only. Repeat inspections given in SB 747-57-2347 must continue at all flap

tracks where the modification given in this SB has not been completed.

Boeing Service Related Problem (SRP) 747-8-SRP-57-0269 is related to this service bulletin.

As a part of a service bulletin validation program, this change was completed on airplane RC504 by

Service Bulletin 747-57A2348 Original Issue before the release of Revision 1 of this service bulletin.

The change completed on airplane RC504 by Service Bulletin 747-57A2348 Original Issue is equivalent

to the release of Revision 1 of this service bulletin. Airplane RC504 has the configuration of a Group

4 airplane.

Revision 1 is sent to incorporate changes to the access requirements and kit found to be necessary

during the validation of the original issue.

D. Description

Get access to the Transmission Aft Bearing Plate Assemblies located at each flap track. Remove and

keep the inboard and outboard flap track fairings. Remove and discard the eight existing aluminum

Transmission Aft Bearing Plate Assemblies. Install eight new titanium Transmission Aft Bearing Plate

Assemblies and install kept inboard and outboard flap track fairings. Do an inboard and outboard flap

adjustment, a check of the flap position and a trailing edge flap system test.

Effects of this Revision on airplanes on which Original Issue was previously done:

None.

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

Group 1-4, 6, 8:

Affected Maintenance Zones

Model Zone

747-8F 561, 563, 565, 567, 661, 663, 665, 667

Group 5, 7, 9-10:

Affected Maintenance Zones

Model Zone

747-8 561, 563, 565, 567, 661, 663, 665, 667

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BOEING SERVICE BULLETIN 747-57A2348

ALERT ALERT
E. Compliance

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to

this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this

service bulletin mandatory.

Boeing recommends that the change given in this service bulletin be done within 48 months after the

original issue date of this service bulletin.

F. Approval

This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified

in this service bulletin comply with the applicable regulations and are FAA approved, as well as European

Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved

airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on

the airplane in its original Boeing delivery configuration or as modified by other approved Boeing

changes.

If an airplane has a non-Boeing modification or repair that affects a component or system also affected

by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval

before incorporating this service bulletin.

G. Manpower

The tables below show an estimate of the task hours necessary to do this modification for each flap

track. 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

• Time to inspect the work

• Time to cure the materials

• Time to make the parts

• Time to find the tools.

Work Package 1 - Flap Track 1 Transmission Aft Bearing Plate Assembly Replacement

Task Number of Persons Task Hours Elapsed Hours

Access 3 6.60 2.20

Disconnect Actuator 2 2.00 (a) 1.00 (a)

Ball Screw Nut

FIGURE 1 1 0.75 0.75

FIGURE 9 1 1.00 1.00

Connect Actuator Ball 2 2.00 (a) 1.00 (a)

Screw Nut

Close Access 3 8.10 2.70

TOTAL FOR EACH FLAP TRACK 16.45 6.65

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ALERT ALERT
Work Package 1 - Flap Track 1 Transmission Aft Bearing Plate Assembly Replacement

Task Number of Persons Task Hours Elapsed Hours

(a) These tasks are optional and are not included in the total given. If these tasks are accomplished, the time shown must be added to the total given.

Work Package Number 1 can be done at the same time as Work Packages 2, 3, 4, 5, 6, 7, and 8

Work Package 2 - Flap Track 2 Transmission Aft Bearing Plate Assembly Replacement

Task Number of Persons Task Hours Elapsed Hours

Access 3 6.60 2.20

Disconnect Actuator 2 2.00 (a) 1.00 (a)

Ball Screw Nut

FIGURE 2 1 0.75 0.75

FIGURE 10 1 1.00 1.00

Connect Actuator Ball 2 2.00 (a) 1.00 (a)

Screw Nut

Close Access 3 8.10 2.70

TOTAL FOR EACH FLAP TRACK 16.45 6.65

(a) These tasks are optional and are not included in the total given. If these tasks are accomplished, the time shown must be added to the total given.

Work Package Number 2 can be done at the same time as Work Packages 1, 3, 4, 5, 6, 7, and 8

Work Package 3 - Flap Track 3 Transmission Aft Bearing Plate Assembly Replacement

Task Number of Persons Task Hours Elapsed Hours

Access 3 6.60 2.20

Disconnect Actuator 2 2.00 (a) 1.00 (a)

Ball Screw Nut

FIGURE 3 1 0.75 0.75

FIGURE 11 1 1.00 1.00

Connect Actuator Ball 2 2.00 (a) 1.00 (a)

Screw Nut

Close Access 3 8.10 2.70

TOTAL FOR EACH FLAP TRACK 16.45 6.65

(a) These tasks are optional and are not included in the total given. If these tasks are accomplished, the time shown must be added to the total given.

Work Package Number 3 can be done at the same time as Work Packages 1, 2, 4, 5, 6, 7, and 8

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ALERT ALERT
Work Package 4 - Flap Track 4 Transmission Aft Bearing Plate Assembly Replacement

Task Number of Persons Task Hours Elapsed Hours

Access 3 6.60 2.20

Disconnect Actuator 2 2.00 (a) 1.00 (a)

Ball Screw Nut

FIGURE 4 1 0.75 0.75

FIGURE 12 1 1.00 1.00

Connect Actuator Ball 2 2.00 (a) 1.00 (a)

Screw Nut

Close Access 3 8.10 2.70

TOTAL FOR EACH FLAP TRACK 16.45 6.65

(a) These tasks are optional and are not included in the total given. If these tasks are accomplished, the time shown must be added to the total given.

Work Package Number 4 can be done at the same time as Work Packages 1, 2, 3, 5, 6, 7, and 8

Work Package 5 - Flap Track 5 Transmission Aft Bearing Plate Assembly Replacement

Task Number of Persons Task Hours Elapsed Hours

Access 3 6.60 2.20

Disconnect Actuator 2 2.00 (a) 1.00 (a)

Ball Screw Nut

FIGURE 5 1 0.75 0.75

FIGURE 13 1 1.00 1.00

Connect Actuator Ball 2 2.00 (a) 1.00 (a)

Screw Nut

Close Access 3 8.10 2.70

TOTAL FOR EACH FLAP TRACK 16.45 6.65

(a) These tasks are optional and are not included in the total given. If these tasks are accomplished, the time shown must be added to the total given.

Work Package Number 5 can be done at the same time as Work Packages 1, 2, 3, 4, 6, 7, and 8

Work Package 6 - Flap Track 6 Transmission Aft Bearing Plate Assembly Replacement

Task Number of Persons Task Hours Elapsed Hours

Access 3 6.60 2.20

Disconnect Actuator 2 2.00 (a) 1.00 (a)

Ball Screw Nut

FIGURE 6 1 0.75 0.75

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ALERT ALERT
Work Package 6 - Flap Track 6 Transmission Aft Bearing Plate Assembly Replacement

Task Number of Persons Task Hours Elapsed Hours

FIGURE 14 1 1.00 1.00

Connect Actuator Ball 2 2.00 (a) 1.00 (a)

Screw Nut

Close Access 3 8.10 2.70

TOTAL FOR EACH FLAP TRACK 16.45 6.65

(a) These tasks are optional and are not included in the total given. If these tasks are accomplished, the time shown must be added to the total given.

Work Package Number 6 can be done at the same time as Work Packages 1, 2, 3, 4, 5, 7, and 8

Work Package 7 - Flap Track 7 Transmission Aft Bearing Plate Assembly Replacement

Task Number of Persons Task Hours Elapsed Hours

Access 3 6.60 2.20

Disconnect Actuator 2 2.00 (a) 1.00 (a)

Ball Screw Nut

FIGURE 7 1 0.75 0.75

FIGURE 15 1 1.00 1.00

Connect Actuator Ball 2 2.00 (a) 1.00 (a)

Screw Nut

Close Access 3 8.10 2.70

TOTAL FOR EACH FLAP TRACK 16.45 6.65

(a) These tasks are optional and are not included in the total given. If these tasks are accomplished, the time shown must be added to the total given.

Work Package Number 7 can be done at the same time as Work Packages 1, 2, 3, 4, 5, 6, and 8

Work Package 8 - Flap Track 8 Transmission Aft Bearing Plate Assembly Replacement

Task Number of Persons Task Hours Elapsed Hours

Access 3 6.60 2.20

Disconnect Actuator 2 2.00 (a) 1.00 (a)

Ball Screw Nut

FIGURE 8 1 0.75 0.75

FIGURE 16 1 1.00 1.00

Connect Actuator Ball 2 2.00 (a) 1.00 (a)

Screw Nut

Close Access 3 8.10 2.70

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ALERT ALERT
Work Package 8 - Flap Track 8 Transmission Aft Bearing Plate Assembly Replacement

Task Number of Persons Task Hours Elapsed Hours

TOTAL FOR EACH FLAP TRACK 16.45 6.65

(a) These tasks are optional and are not included in the total given. If these tasks are accomplished, the time shown must be added to the total given.

Work Package Number 8 can be done at the same time as Work Packages 1, 2, 3, 4, 5, 6, and 7

H. Weight and Balance Changes

Change in Moment

(Pound-Inches)

Change in Weight

Airplane (Pounds)

All +8.50 +12,945.50

I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. Engineering Change Memo PRR 85901-140S

b. Boeing Service Bulletin 747-57-2347

c. Boeing Service Letter 747-SL-51-048

d. Boeing Service Related Problem (SRP) 747-8-SRP-57-0269

e. Service Bulletin Index D6-30300

f. Standard Overhaul Practices Manual (SOPM) 20-50-01, 20-50-10

g. 747-8 Aircraft Maintenance Manual (AMM) 27-51-00, 27-51-01, 27-51-04, 27-51-26, 27-51-31,

27-51-33, 27-51-46

2. Data Supplied with this Service Bulletin:

None.

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

Drawing Number Title

113U1150 TRACK INSTL - OUTBOARD FLAP, TRACK NO. 1 AND NO. 8

113U1250 TRACK INSTL - OUTBOARD FLAP, TRACK NO. 2 AND NO. 7

113U1350 TRACK INSTL - INBOARD FLAP, TRACK NO. 3 AND NO. 6

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ALERT ALERT
Drawing Number Title

113U1450 TRACK INSTL - INBOARD FLAP, TRACK NO. 4 AND NO. 5

TRANSMISSION INSTL OUTBD - OUTBD T.E. FLAPS, DRIVE

NO. 1 AND 8

256U5100

TRANSMISSION INSTL INBD - OUTBD T.E. FLAPS, DRIVE NO.

2 AND 7

256U5200

TRANSMISSION INSTL OUTBD - INBD T.E. FLAPS, DRIVE NO.

3 AND 6

256U5300

TRANSMISSION INSTL INBD - INBD T.E. FLAPS DRIVE, NO. 4

AND 5

256U5400

The table above lists applicable drawings used to prepare this service bulletin. The drawings are

not necessary to make the specified changes, and are not supplied with this service bulletin. The

drawings may not be applicable to all airplane configurations or operators.

K. Publications Affected

1. Publications:

Publication Chapter-Section

747 Fault Isolation Manual 27-51, 27-50

747 Illustrated Parts Catalog 27-51

Component Maintenance Manual 57-52

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 but no new DTIs are necessary.

L. Interchangeability and Intermixability of Parts

Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.

M. Software Accomplishment Summary

Not affected.

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ALERT ALERT
2. MATERIAL INFORMATION

A. Material - Price and Availability

Boeing can supply the kit shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators are

encouraged to share schedule requirements with Boeing for incorporation of the service bulletin. The

kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.

Prices are in United States Dollars. Terms: Net 30 days.

Reference this service bulletin and submit your purchase order by one of these methods:

1. Order on-line via ATA Spec 2000 or The Boeing PART Page

2. Fax to (206) 662-7145

REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER

AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION

Unit Price as of

the original issue

date of this Service Bulletin (US

Dollars)

ROLT as of the

original issue

date of this Service Bulletin (Calendar Days)

Kit Number Name Date QTY

TOP KIT, RETROFIT - 03/07/16 20 545 43,787.00

WING TE FLAP

TRANSMISSION AFT

ATTACH FITTINGS

REPLACEMENT

015U2129-2

TOP KIT, RETROFIT - 04/04/16 20 545 43,787.00

WING TE FLAP

TRANSMISSION AFT

ATTACH FITTINGS

REPLACEMENT

015U2129-2

TOP KIT, RETROFIT - 05/02/16 20 545 43,787.00

WING TE FLAP

TRANSMISSION AFT

ATTACH FITTINGS

REPLACEMENT

015U2129-2

TOP KIT, RETROFIT - 05/31/16 7 545 43,787.00

WING TE FLAP

TRANSMISSION AFT

ATTACH FITTINGS

REPLACEMENT

015U2129-2

NOTE: The 015U2129-1 Top Kit is no longer available. Operators that have a 015U2129-1 Top Kit

can complete the work given in this service bulletin by providing four additional

BACP18BC04A10P pins and four additional BACW10BP9APU washers.

Operators are encouraged to complete the survey provided in APPENDIX B of this service bulletin to

help Boeing predict the quantity and timing of the Boeing Supplied Kits/Parts.

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ALERT ALERT
B. Industry Support Information

Boeing warranty remedies are available for 747-8 and 747-8F airplanes in warranty as of March 12,

2014. For task hour reimbursement for airplanes in warranty as of that date, send a warranty claim to

Boeing Fleet Support Contracts - Warranty. The kits for airplanes in warranty as of that date will be

supplied at no charge. Send a purchase order for the kits to Boeing Material Management. Please refer

to this service bulletin number and reference the airplane variable numbers in your purchase order.

The warranty remedies will expire eight years from the original issue date of this service bulletin.

C. Parts Necessary for Each Airplane

1. Kits/Parts

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

NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by

the Operator, are necessary for each airplane. The Top Kit is divided into Figure kits for

each installation figure shown in the table below.

Figure Kit

Top Kit 9 10 11 12 13 14

015U2129-2 1 1 1 1 1 1

Figure Kit

Top Kit 15 16

015U2129-2 1 1

ALL

KIT 015U2129-2

Notes

Existing Part

Name Number

Figure

New Part Number

9 10 11 12 13 14

Qty

TRANSMISSION -

AFT BEARING

PLATE ASSY

113U1192-5 1 . . . . .

TRANSMISSION -

AFT BEARING

PLATE ASSY

113U1292-5 . 1 . . . .

TRANSMISSION -

AFT BEARING

PLATE ASSY

113U1392-5 . . 1 . . .

TRANSMISSION -

AFT BEARING

PLATE ASSY

113U1392-6 . . . . . 1

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ALERT ALERT
ALL

KIT 015U2129-2

Notes

Existing Part

Name Number

Figure

New Part Number

9 10 11 12 13 14

Qty

TRANSMISSION -

AFT BEARING

PLATE ASSY

113U1492-7 . . . 1 . .

TRANSMISSION -

AFT BEARING

PLATE ASSY

113U1492-8 . . . . 1 .

NUT, CASTELLAT- -

ED

BACN11N107CS . . 2 . . 2

BACN11N108CS 2 2 . . . . NUT -

NUT, CASTELLAT- -

ED

BACN11N110CS . . . 2 2 .

NUT, CASTELLAT- -

ED

BACN11N7CS 2 2 2 . . 2

NUT, CASTELLAT- -

ED

BACN11N9CS . . . 2 2 .

BACP18BC03A08P 4 4 4 . . 4 PIN -

BACP18BC04A10P . . . 4 4 . PIN -

BACW10BP10APU . . . 6 6 . WASHER -

BACW10BP7APU 4 4 12 . . 12 WASHER -

BACW10BP8APU 6 4 . . . . WASHER -

BACW10BP9APU . . . 4 4 . WASHER -

ALL

KIT 015U2129-2

Notes

Existing Part

Name Number

Figure

New Part Number

15 16

Qty

TRANSMISSION -

AFT BEARING

PLATE ASSY

113U1192-6 . 1

TRANSMISSION -

AFT BEARING

PLATE ASSY

113U1292-6 1 .

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ALERT ALERT
ALL

KIT 015U2129-2

Notes

Existing Part

Name Number

Figure

New Part Number

15 16

Qty

BACN11N108CS 2 2 NUT -

NUT, CASTELLAT- -

ED

BACN11N7CS 2 2

BACP18BC03A08P 4 4 PIN -

BACW10BP7APU 4 4 WASHER -

BACW10BP8APU 4 6 WASHER -

2. Parts and Materials Supplied by the Operator

None.

3. Parts Modified and Reidentified

The parts shown below are changed as shown in this service bulletin. The quantity (QTY) is the

number of parts changed on each airplane.

Group 1:

Existing Part QTY Name New Part Number Notes

Number

TRACK ASSY - OUT- - (a)

BOARD FLAP, TRACK

NO. 1

113U1151-1 1

TRACK ASSY - OUT- - (a)

BOARD FLAP, TRACK

NO. 8

113U1151-2 1

TRACK ASSY - OUT- - (a)

BOARD FLAP, TRACK

NO. 2

113U1251-5 1

TRACK ASSY - OUT- - (a)

BOARD FLAP, TRACK

NO. 7

113U1251-6 1

TRACK ASSY - IN- - (a)

BOARD FLAP, TRACK

NO. 3

113U1351-1 1

TRACK ASSY - IN- - (a)

BOARD FLAP, TRACK

NO. 6

113U1351-2 1

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Group 1:

Existing Part QTY Name New Part Number Notes

Number

TRACK ASSY - IN- - (a)

BOARD FLAP, TRACK

NO. 4

113U1451-1 1

TRACK ASSY - IN- - (a)

BOARD FLAP, TRACK

NO. 5

113U1451-2 1

(a) There is no equivalent Boeing part number for the changed part. Identify on the part that

the change done in accordance with this service bulletin was made.

Group 2:

Existing Part QTY Name New Part Number Notes

Number

TRACK ASSY - OUT- - (a)

BOARD FLAP, TRACK

NO. 1

113U1151-3 1

TRACK ASSY - OUT- - (a)

BOARD FLAP, TRACK

NO. 8

113U1151-4 1

TRACK ASSY - OUT- - (a)

BOARD FLAP, TRACK

NO. 2

113U1251-5 1

TRACK ASSY - OUT- - (a)

BOARD FLAP, TRACK

NO. 7

113U1251-6 1

TRACK ASSY - IN- - (a)

BOARD FLAP, TRACK

NO. 3

113U1351-1 1

TRACK ASSY - IN- - (a)

BOARD FLAP, TRACK

NO. 6

113U1351-2 1

TRACK ASSY - IN- - (a)

BOARD FLAP, TRACK

NO. 4

113U1451-1 1

TRACK ASSY - IN- - (a)

BOARD FLAP, TRACK

NO. 5

113U1451-2 1

(a) There is no equivalent Boeing part number for the changed part. Identify on the part that

the change done in accordance with this service bulletin was made.

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Group 3:

Existing Part QTY Name New Part Number Notes

Number

TRACK ASSY - OUT- 113U1151-13 -

BOARD FLAP, TRACK

NO. 1

113U1151-5 1

TRACK ASSY - OUT- 113U1151-14 -

BOARD FLAP, TRACK

NO. 8

113U1151-6 1

TRACK ASSY - OUT- 113U1251-15 -

BOARD FLAP, TRACK

NO. 2

113U1251-7 1

TRACK ASSY - OUT- 113U1251-16 -

BOARD FLAP, TRACK

NO. 7

113U1251-8 1

TRACK ASSY - IN- - (a)

BOARD FLAP, TRACK

NO. 3

113U1351-3 1

TRACK ASSY - IN- - (a)

BOARD FLAP, TRACK

NO. 6

113U1351-4 1

TRACK ASSY - IN- - (a)

BOARD FLAP, TRACK

NO. 4

113U1451-1 1

TRACK ASSY - IN- - (a)

BOARD FLAP, TRACK

NO. 5

113U1451-2 1

(a) There is no equivalent Boeing part number for the changed part. Identify on the part that

the change done in accordance with this service bulletin was made.

Group 4:

Existing Part QTY Name New Part Number Notes

Number

TRACK ASSY - OUT- 113U1151-13 -

BOARD FLAP, TRACK

NO. 1

113U1151-5 1

TRACK ASSY - OUT- 113U1151-14 -

BOARD FLAP, TRACK

NO. 8

113U1151-6 1

TRACK ASSY - OUT- 113U1251-15 -

BOARD FLAP, TRACK

NO. 2

113U1251-7 1

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Group 4:

Existing Part QTY Name New Part Number Notes

Number

TRACK ASSY - OUT- 113U1251-16 -

BOARD FLAP, TRACK

NO. 7

113U1251-8 1

TRACK ASSY - IN- - (a)

BOARD FLAP, TRACK

NO. 3

113U1351-5 1

TRACK ASSY - IN- - (a)

BOARD FLAP, TRACK

NO. 6

113U1351-6 1

TRACK ASSY - IN- - (a)

BOARD FLAP, TRACK

NO. 4

113U1451-1 1

TRACK ASSY - IN- - (a)

BOARD FLAP, TRACK

NO. 5

113U1451-2 1

(a) There is no equivalent Boeing part number for the changed part. Identify on the part that

the change done in accordance with this service bulletin was made.

Group 5:

Existing Part QTY Name New Part Number Notes

Number

TRACK ASSY - OUT- 113U1151-13 -

BOARD FLAP, TRACK

NO. 1

113U1151-5 1

TRACK ASSY - OUT- 113U1151-14 -

BOARD FLAP, TRACK

NO. 8

113U1151-6 1

TRACK ASSY - OUT- 113U1251-15 -

BOARD FLAP, TRACK

NO. 2

113U1251-7 1

TRACK ASSY - OUT- 113U1251-16 -

BOARD FLAP, TRACK

NO. 7

113U1251-8 1

TRACK ASSY - IN- - (a)

BOARD FLAP, TRACK

NO. 3

113U1351-101 1

TRACK ASSY - IN- - (a)

BOARD FLAP, TRACK

NO. 6

113U1351-102 1

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Group 5:

Existing Part QTY Name New Part Number Notes

Number

TRACK ASSY - IN- - (a)

BOARD FLAP, TRACK

NO. 4

113U1451-101 1

TRACK ASSY - IN- - (a)

BOARD FLAP, TRACK

NO. 5

113U1451-102 1

(a) There is no equivalent Boeing part number for the changed part. Identify on the part that

the change done in accordance with this service bulletin was made.

Group 6:

Existing Part QTY Name New Part Number Notes

Number

INTEGRATED TRACK - (a)

ASSY - OUTBOARD

FLAP, TRACK NO. 1

113U1151-7 1

INTEGRATED TRACK - (a)

ASSY - OUTBOARD

FLAP, TRACK NO. 8

113U1151-8 1

INTEGRATED TRACK - (a)

ASSY - OUTBOARD

FLAP, TRACK NO. 2

113U1251-9 1

INTEGRATED TRACK - (a)

ASSY - OUTBOARD

FLAP, TRACK NO. 7

113U1251-10 1

INTEGRATED TRACK - (a)

ASSY - OUTBOARD

FLAP, TRACK NO. 3

113U1351-7 1

INTEGRATED TRACK - (a)

ASSY - INBOARD

FLAP, TRACK NO. 6

113U1351-8 1

INTEGRATED TRACK - (a)

ASSY - OUTBOARD

FLAP, TRACK NO. 4

113U1451-3 1

INTEGRATED TRACK - (a)

ASSY - INBOARD

FLAP, TRACK NO. 5

113U1451-4 1

TRACK ASSY - OUT- 113U1151-13 -

BOARD FLAP, TRACK

NO. 1

113U1151-5 1

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Group 6:

Existing Part QTY Name New Part Number Notes

Number

TRACK ASSY - OUT- 113U1151-14 -

BOARD FLAP, TRACK

NO. 8

113U1151-6 1

TRACK ASSY - OUT- 113U1251-15 -

BOARD FLAP, TRACK

NO. 2

113U1251-7 1

TRACK ASSY - OUT- 113U1251-16 -

BOARD FLAP, TRACK

NO. 7

113U1251-8 1

TRACK ASSY - IN- - (a)

BOARD FLAP, TRACK

NO. 3

113U1351-5 1

TRACK ASSY - IN- - (a)

BOARD FLAP, TRACK

NO. 6

113U1351-6 1

TRACK ASSY - IN- - (a)

BOARD FLAP, TRACK

NO. 4

113U1451-5 1

TRACK ASSY - IN- - (a)

BOARD FLAP, TRACK

NO. 5

113U1451-6 1

(a) There is no equivalent Boeing part number for the changed part. Identify on the part that

the change done in accordance with this service bulletin was made.

Group 7:

Existing Part QTY Name New Part Number Notes

Number

INTEGRATED TRACK - (a)

ASSY - OUTBOARD

FLAP, TRACK NO. 1

113U1151-7 1

INTEGRATED TRACK - (a)

ASSY - OUTBOARD

FLAP, TRACK NO. 8

113U1151-8 1

INTEGRATED TRACK - (a)

ASSY - OUTBOARD

FLAP, TRACK NO. 2

113U1251-9 1

INTEGRATED TRACK - (a)

ASSY - OUTBOARD

FLAP, TRACK NO. 7

113U1251-10 1

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ALERT ALERT
Group 7:

Existing Part QTY Name New Part Number Notes

Number

INTEGRATED TRACK - (a)

ASSY - OUTBOARD

FLAP, TRACK NO. 3

113U1351-103 1

INTEGRATED TRACK - (a)

ASSY - INBOARD

FLAP, TRACK NO. 6

113U1351-104 1

INTEGRATED TRACK - (a)

ASSY - OUTBOARD

FLAP, TRACK NO. 4

113U1451-103 1

INTEGRATED TRACK - (a)

ASSY - INBOARD

FLAP, TRACK NO. 5

113U1451-104 1

TRACK ASSY - OUT- 113U1151-13 -

BOARD FLAP, TRACK

NO. 1

113U1151-5 1

TRACK ASSY - OUT- 113U1151-14 -

BOARD FLAP, TRACK

NO. 8

113U1151-6 1

TRACK ASSY - OUT- 113U1251-15 -

BOARD FLAP, TRACK

NO. 2

113U1251-7 1

TRACK ASSY - OUT- 113U1251-16 -

BOARD FLAP, TRACK

NO. 7

113U1251-8 1

TRACK ASSY - IN- - (a)

BOARD FLAP, TRACK

NO. 3

113U1351-101 1

TRACK ASSY - IN- - (a)

BOARD FLAP, TRACK

NO. 6

113U1351-102 1

TRACK ASSY - IN- - (a)

BOARD FLAP, TRACK

NO. 4

113U1451-105 1

TRACK ASSY - IN- - (a)

BOARD FLAP, TRACK

NO. 5

113U1451-106 1

(a) There is no equivalent Boeing part number for the changed part. Identify on the part that

the change done in accordance with this service bulletin was made.

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ALERT ALERT
Group 8:

Existing Part QTY Name New Part Number Notes

Number

INTEGRATED TRACK 113U1151-11 -

ASSY - OUTBOARD

FLAP, TRACK NO. 1

113U1151-9 1

INTEGRATED TRACK 113U1151-12 -

ASSY - OUTBOARD

FLAP, TRACK NO. 8

113U1151-10 1

INTEGRATED TRACK 113U1251-13 -

ASSY - OUTBOARD

FLAP, TRACK NO. 2

113U1251-11 1

INTEGRATED TRACK 113U1251-14 -

ASSY - OUTBOARD

FLAP, TRACK NO. 7

113U1251-12 1

INTEGRATED TRACK 113U1351-21 -

ASSY - OUTBOARD

FLAP, TRACK NO. 3

113U1351-9 1

INTEGRATED TRACK 113U1351-22 -

ASSY - INBOARD

FLAP, TRACK NO. 6

113U1351-10 1

INTEGRATED TRACK 113U1451-19 -

ASSY - OUTBOARD

FLAP, TRACK NO. 4

113U1451-7 1

INTEGRATED TRACK 113U1451-20 -

ASSY - INBOARD

FLAP, TRACK NO. 5

113U1451-8 1

TRACK ASSY - OUT- 113U1151-13 -

BOARD FLAP, TRACK

NO. 1

113U1151-5 1

TRACK ASSY - OUT- 113U1151-14 -

BOARD FLAP, TRACK

NO. 8

113U1151-6 1

TRACK ASSY - OUT- 113U1251-15 -

BOARD FLAP, TRACK

NO. 2

113U1251-7 1

TRACK ASSY - OUT- 113U1251-16 -

BOARD FLAP, TRACK

NO. 7

113U1251-8 1

TRACK ASSY - IN- 113U1351-23 -

BOARD FLAP, TRACK

NO. 3

113U1351-11 1

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ALERT ALERT
Group 8:

Existing Part QTY Name New Part Number Notes

Number

TRACK ASSY - IN- 113U1351-24 -

BOARD FLAP, TRACK

NO. 6

113U1351-12 1

TRACK ASSY - IN- 113U1451-21 -

BOARD FLAP, TRACK

NO. 4

113U1451-9 1

TRACK ASSY - IN- 113U1451-22 -

BOARD FLAP, TRACK

NO. 5

113U1451-10 1

(a) There is no equivalent Boeing part number for the changed part. Identify on the part that

the change done in accordance with this service bulletin was made.

Group 9:

Existing Part QTY Name New Part Number Notes

Number

INTEGRATED TRACK 113U1151-11 -

ASSY - OUTBOARD

FLAP, TRACK NO. 1

113U1151-9 1

INTEGRATED TRACK 113U1151-12 -

ASSY - OUTBOARD

FLAP, TRACK NO. 8

113U1151-10 1

INTEGRATED TRACK 113U1251-13 -

ASSY - OUTBOARD

FLAP, TRACK NO. 2

113U1251-11 1

INTEGRATED TRACK 113U1251-14 -

ASSY - OUTBOARD

FLAP, TRACK NO. 7

113U1251-12 1

INTEGRATED TRACK 113U1351-109 -

ASSY - OUTBOARD

FLAP, TRACK NO. 3

113U1351-105 1

INTEGRATED TRACK 113U1351-110 -

ASSY - INBOARD

FLAP, TRACK NO. 6

113U1351-106 1

INTEGRATED TRACK 113U1451-111 -

ASSY - OUTBOARD

FLAP, TRACK NO. 4

113U1451-107 1

INTEGRATED TRACK 1131451-112 -

ASSY - INBOARD

FLAP, TRACK NO. 5

113U1451-108 1

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ALERT ALERT
Group 9:

Existing Part QTY Name New Part Number Notes

Number

TRACK ASSY - OUT- 113U1151-13 -

BOARD FLAP, TRACK

NO. 1

113U1151-5 1

TRACK ASSY - OUT- 113U1151-14 -

BOARD FLAP, TRACK

NO. 8

113U1151-6 1

TRACK ASSY - OUT- 113U1251-15 -

BOARD FLAP, TRACK

NO. 2

113U1251-7 1

TRACK ASSY - OUT- 113U1251-16 -

BOARD FLAP, TRACK

NO. 7

113U1251-8 1

TRACK ASSY - IN- 113U1351-111 -

BOARD FLAP, TRACK

NO. 3

113U1351-107 1

TRACK ASSY - IN- 113U1351-112 -

BOARD FLAP, TRACK

NO. 6

113U1351-108 1

TRACK ASSY - IN- - (a)

BOARD FLAP, TRACK

NO. 4

113U1451-105 1

TRACK ASSY - IN- - (a)

BOARD FLAP, TRACK

NO. 5

113U1451-106 1

(a) There is no equivalent Boeing part number for the changed part. Identify on the part that

the change done in accordance with this service bulletin was made.

Group 10:

Existing Part QTY Name New Part Number Notes

Number

INTEGRATED TRACK 113U1151-11 -

ASSY - OUTBOARD

FLAP, TRACK NO. 1

113U1151-9 1

INTEGRATED TRACK 113U1151-12 -

ASSY - OUTBOARD

FLAP, TRACK NO. 8

113U1151-10 1

INTEGRATED TRACK 113U1251-13 -

ASSY - OUTBOARD

FLAP, TRACK NO. 2

113U1251-11 1

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ALERT ALERT
Group 10:

Existing Part QTY Name New Part Number Notes

Number

INTEGRATED TRACK 113U1251-14 -

ASSY - OUTBOARD

FLAP, TRACK NO. 7

113U1251-12 1

INTEGRATED TRACK 113U1351-109 -

ASSY - OUTBOARD

FLAP, TRACK NO. 3

113U1351-105 1

INTEGRATED TRACK 113U1351-110 -

ASSY - INBOARD

FLAP, TRACK NO. 6

113U1351-106 1

INTEGRATED TRACK 113U1451-111 -

ASSY - OUTBOARD

FLAP, TRACK NO. 4

113U1451-107 1

INTEGRATED TRACK 113U1451-112 -

ASSY - INBOARD

FLAP, TRACK NO. 5

113U1451-108 1

TRACK ASSY - OUT- 113U1151-13 -

BOARD FLAP, TRACK

NO. 1

113U1151-5 1

TRACK ASSY - OUT- 113U1151-14 -

BOARD FLAP, TRACK

NO. 8

113U1151-6 1

TRACK ASSY - OUT- 113U1251-15 -

BOARD FLAP, TRACK

NO. 2

113U1251-7 1

TRACK ASSY - OUT- 113U1251-16 -

BOARD FLAP, TRACK

NO. 7

113U1251-8 1

TRACK ASSY - IN- 113U1351-111 -

BOARD FLAP, TRACK

NO. 3

113U1351-107 1

TRACK ASSY - IN- 113U1351-112 -

BOARD FLAP, TRACK

NO. 6

113U1351-108 1

TRACK ASSY - IN- 113U1451-113 -

BOARD FLAP, TRACK

NO. 4

113U1451-109 1

TRACK ASSY - IN- 113U1451-114 -

BOARD FLAP, TRACK

NO. 5

113U1451-110 1

(a) There is no equivalent Boeing part number for the changed part. Identify on the part that

the change done in accordance with this service bulletin was made.

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ALERT ALERT
4. Parts Removed and Not Replaced

None.

D. Parts Necessary to Change Spares

None.

E. Special Tooling - Price and Availability

None.

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.

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ALERT ALERT

BLANK PAGE
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. The work instructions are divided into work packages. Task Hours and Elapsed Hours

for each package are given in Paragraph 1.G., Manpower. You can do each work

package independently.

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

– Linear dimensions are in inches

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

or minus 0.03 inch

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

– Angular tolerance is plus or minus 2 degrees

– Hole dimensions for standard solid rivets and fasteners are in Structural Repair

Manual (SRM) Chapter 51

– Torque Values:

— Values for structural fasteners are given in 747 Structural Repair Manual,

Chapter 51.

— Values for airframe maintenance tasks are included in Chapter 20 of 747

Aircraft Maintenance Manual (AMM).

— Values for electrical maintenance tasks are included in Chapter 20 of

Standard Wiring Practices Manual (SWPM).

— Values for engine maintenance tasks are included in Chapter 70 of 747

Aircraft Maintenance Manual (AMM).

— Non-standard torque values for maintenance tasks are included in the

applicable installation step.

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

SRM Chapter 51.

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

standards given in SRM Chapter 51, then a fastener of the same specification, or

an approved substitute, with a length which meets the installation standards given

in SRM Chapter 51 may be used. In addition, washers may be installed for fastener

grip length in accordance with SRM Chapter 51. Refer to SOPM 20-50-01 for alternate

full threaded fasteners (screws) needed for installation in this service bulletin.

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ALERT ALERT
7. These work instructions refer to procedures included in other Boeing documents.

When the words "refer to" are used and the operator has an accepted alternative

procedure, the accepted alternative procedure can be used. When the words "in

accordance with" are included in the instruction, the procedure in the Boeing document

must be used.

8. 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.

9. 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.

10. 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.

11. Where the work instructions include installation of a kept part, a new or serviceable

part with the same part number can be installed as an alternative to the kept part.

12. This service bulletin includes functional test procedures for the systems changed by

this service bulletin. More functional tests can possibly be necessary in accordance

with standard maintenance practices because of interruption to other airplane systems.

13. Use of colors in Figures is based on guidance from the ATA e-Business Program

(ATA) iSpec 2200.

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

are in Paragraph 1.E., Compliance.

15. Some steps in the Work Instructions are labeled as Required for Compliance (RC).

If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps

labeled as RC, including sub-steps under an RC step and any figures identified in

an RC step, must be done to comply with the AD. An Alternative Method of

Compliance (AMOC) is required for any deviations to RC steps, including sub-steps

and identified figures. Steps not labeled as RC may be deviated from using accepted

methods in accordance with the operator's maintenance or inspection program without

obtaining approval of an AMOC. This is provided that the RC steps, including

sub-steps and identified figures, can still be done as specified, and the airplane can

be put back in an airworthy condition.

B. WORK INSTRUCTIONS

WORK PACKAGE 1: FLAP TRACK 1 TRANSMISSION AFT BEARING PLATE ASSEMBLY

REPLACEMENT

1. Do PART 1: OUTBOARD ACCESS.

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ALERT ALERT
2. RC- Remove the Transmission Aft Bearing Plate Assembly from Flap Track 1 in accordance with

FIGURE 1.

3. RC- Install the new Transmission Aft Bearing Plate Assembly at Flap Track 1 in accordance with

FIGURE 9.

4. Do PART 3: CLOSE OUTBOARD ACCESS.

5. Put the airplane back to a serviceable condition.

WORK PACKAGE 2: FLAP TRACK 2 TRANSMISSION AFT BEARING PLATE ASSEMBLY

REPLACEMENT

1. Do PART 1: OUTBOARD ACCESS.

2. RC- Remove the Transmission Aft Bearing Plate Assembly from Flap Track 2 in accordance with

FIGURE 2.

3. RC- Install the new Transmission Aft Bearing Plate Assembly at Flap Track 2 in accordance with

FIGURE 10.

4. Do PART 3: CLOSE OUTBOARD ACCESS.

5. Put the airplane back to a serviceable condition.

WORK PACKAGE 3: FLAP TRACK 3 TRANSMISSION AFT BEARING PLATE ASSEMBLY

REPLACEMENT

1. Do PART 2: INBOARD ACCESS.

2. RC- Remove the Transmission Aft Bearing Plate Assembly from Flap Track 3 in accordance with

FIGURE 3.

3. RC- Install the new Transmission Aft Bearing Plate Assembly at Flap Track 3 in accordance with

FIGURE 11.

4. Do PART 4: CLOSE INBOARD ACCESS.

5. Put the airplane back to a serviceable condition.

WORK PACKAGE 4: FLAP TRACK 4 TRANSMISSION AFT BEARING PLATE ASSEMBLY

REPLACEMENT

1. Do PART 2: INBOARD ACCESS.

2. RC- Remove the Transmission Aft Bearing Plate Assembly from Flap Track 4 in accordance with

FIGURE 4.

3. RC- Install the new Transmission Aft Bearing Plate Assembly at Flap Track 4 in accordance with

FIGURE 12.

4. Do PART 4: CLOSE INBOARD ACCESS.

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ALERT ALERT
5. Put the airplane back to a serviceable condition.

WORK PACKAGE 5: FLAP TRACK 5 TRANSMISSION AFT BEARING PLATE ASSEMBLY

REPLACEMENT

1. Do PART 2: INBOARD ACCESS.

2. RC- Remove the Transmission Aft Bearing Plate Assembly from Flap Track 5 in accordance with

FIGURE 5.

3. RC- Install the new Transmission Aft Bearing Plate Assembly at Flap Track 5 in accordance with

FIGURE 13.

4. Do PART 4: CLOSE INBOARD ACCESS.

5. Put the airplane back to a serviceable condition.

WORK PACKAGE 6: FLAP TRACK 6 TRANSMISSION AFT BEARING PLATE ASSEMBLY

REPLACEMENT

1. Do PART 2: INBOARD ACCESS.

2. RC- Remove the Transmission Aft Bearing Plate Assembly from Flap Track 6 in accordance with

FIGURE 6.

3. RC- Install the new Transmission Aft Bearing Plate Assembly at Flap Track 6 in accordance with

FIGURE 14.

4. Do PART 4: CLOSE INBOARD ACCESS.

5. Put the airplane back to a serviceable condition.

WORK PACKAGE 7: FLAP TRACK 7 TRANSMISSION AFT BEARING PLATE ASSEMBLY

REPLACEMENT

1. Do PART 1: OUTBOARD ACCESS.

2. RC- Remove the Transmission Aft Bearing Plate Assembly from Flap Track 7 in accordance with

FIGURE 7.

3. RC- Install the new Transmission Aft Bearing Plate Assembly at Flap Track 7 in accordance with

FIGURE 15.

4. Do PART 3: CLOSE OUTBOARD ACCESS.

5. Put the airplane back to a serviceable condition.

WORK PACKAGE 8: FLAP TRACK 8 TRANSMISSION AFT BEARING PLATE ASSEMBLY

REPLACEMENT

1. Do PART 1: OUTBOARD ACCESS.

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ALERT ALERT
2. RC- Remove the Transmission Aft Bearing Plate Assembly from Flap Track 8 in accordance with

FIGURE 8.

3. RC- Install the new Transmission Aft Bearing Plate Assembly at Flap Track 8 in accordance with

FIGURE 16.

4. Do PART 3: CLOSE OUTBOARD ACCESS.

5. Put the airplane back to a serviceable condition.

PART 1: OUTBOARD ACCESS

1. Do one of the following options:

NOTE: OPTION 2: Disconnect the Flap Transmission will involve significantly more work and

risk possible damage to the Flap Transmission.

a. OPTION 1: Secure the Flap Transmission as follows:

(1) Extend and deactivate all trailing edge flaps. Refer to 747-8 AMM 27-51-00 as an accepted

procedure.

(2) Remove the Outboard Flap Track Forward Fairing. Refer to 747-8 AMM 27-51-31 as

an accepted procedure.

(3) Remove the Outboard Flap Track Aft Fairing. Refer to 747-8 AMM 27-51-31 as an

accepted procedure.

(4) Install the transmission removal and installation equipment. Refer to 747-8 AMM 27-51-33

as an accepted procedure.

(5) If necessary, disconnect the ball screw from the actuator attach gimbal fitting to get

sufficient access. Refer to 747-8 AMM 27-51-46 as an accepted procedure.

b. OPTION 2: Disconnect the Flap Transmission as follows:

(1) Extend and deactivate all trailing edge flaps. Refer to 747-8 AMM 27-51-00 as an accepted

procedure.

(2) Prepare for the Removal of the Flap Transmission. Refer to 747-8 AMM 27-51-33 as an

accepted procedure.

NOTE: For flap tracks 1 and 8, the position transmitter must be removed.

(3) Disconnect the applicable torque tubes from the transmission. Refer to 747-8 AMM

27-51-33 as an accepted procedure.

(4) Disconnect the ball screw from the transmission. Refer to 747-8 AMM 27-51-33 as an

accepted procedure.

(5) Install the transmission removal and installation equipment. Refer to 747-8 AMM 27-51-33

as an accepted procedure.

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ALERT ALERT
PART 2: INBOARD ACCESS

1. Do one of the following options:

NOTE: OPTION 2: Disconnect the Flap Transmission will involve significantly more work and

risk possible damage to the Flap Transmission.

a. OPTION 1: Secure the Flap Transmission as follows:

(1) Extend and deactivate all trailing edge flaps. Refer to 747-8 AMM 27-51-00 as an accepted

procedure.

(2) Remove the Inboard Flap Track Forward Fairing. Refer to 747-8 AMM 27-51-26 as an

accepted procedure.

(3) Remove the Inboard Flap Track Aft Fairing. Refer to 747-8 AMM 27-51-26 as an accepted

procedure.

(4) Install the transmission removal and installation equipment. Refer to 747-8 AMM 27-51-33

as an accepted procedure.

(5) If necessary, disconnect the ball screw from the actuator attach gimbal fitting to get

sufficient access. Refer to 747-8 AMM 27-51-46 as an accepted procedure.

b. OPTION 2: Disconnect the Flap Transmission as follows:

(1) Extend and deactivate all trailing edge flaps. Refer to 747-8 AMM 27-51-00 as an accepted

procedure.

(2) Prepare for the Removal of the Flap Transmission. Refer to 747-8 AMM 27-51-33 as an

accepted procedure.

NOTE: For flap tracks 3 and 6, the position transmitter must be removed.

(3) Disconnect the applicable torque tubes from the transmission. Refer to 747-8 AMM

27-51-33 as an accepted procedure.

(4) Disconnect the ball screw from the transmission. Refer to 747-8 AMM 27-51-33 as an

accepted procedure.

(5) Install the transmission removal and installation equipment. Refer to 747-8 AMM 27-51-33

as an accepted procedure.

PART 3: CLOSE OUTBOARD ACCESS

1. If OPTION 1 was used for PART 1: OUTBOARD ACCESS, do the following:

a. If the ball screw was disconnected during access, re-connect the ball screw to the actuator

attach gimbal fitting. Refer to 747-8 AMM 27-51-46 as an accepted procedure.

b. Remove the transmission removal and installation equipment. Refer to 747-8 AMM 27-51-33

as an accepted procedure.

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c. Install the Outboard Flap Track Aft Fairing. Refer to 747-8 AMM 27-51-31 as an accepted

procedure.

d. Install the Outboard Flap Track Forward Fairing. Refer to 747-8 AMM 27-51-31 as an accepted

procedure.

e. Do a Check of the Flap Position. Refer to 747-8 AMM 27-51-04 as an accepted procedure.

f. Do a Trailing Edge Flap System - System Test. Refer to 747-8 AMM 27-51-00 as an accepted

procedure.

2. If OPTION 2 was used for PART 1 - OUTBOARD ACCESS, do the following:

a. Remove the transmission removal and installation equipment. Refer to 747-8 AMM 27-51-33

as an accepted procedure.

b. Attach the ball screw to the transmission. Refer to 747-8 AMM 27-51-33 as an accepted

procedure.

c. Connect the applicable torque tubes to the transmission. Refer to 747-8 AMM 27-51-33 as

an accepted procedure.

d. Install the Outboard Flap Track Forward Fairing. Refer to 747-8 AMM 27-51-31 as an accepted

procedure.

e. Do the Outboard Trailing Edge Flap - Adjustment. Refer to 747-8 AMM 27-51-04 as an accepted

procedure.

f. Do a Check of the Flap Position. Refer to 747-8 AMM 27-51-04 as an accepted procedure.

g. Do a Trailing Edge Flap System - System Test. Refer to 747-8 AMM 27-51-00 as an accepted

procedure.

PART 4: CLOSE INBOARD ACCESS

1. If OPTION 1 was used for PART 2: INBOARD ACCESS, do the following:

a. If the ball screw was disconnected during access, re-connect the ball screw to the actuator

attach gimbal fitting. Refer to 747-8 AMM 27-51-46 as an accepted procedure.

b. Remove the transmission removal and installation equipment. Refer to 747-8 AMM 27-51-33

as an accepted procedure.

c. Install the Inboard Flap Track Aft Fairing. Refer to 747-8 AMM 27-51-26 as an accepted

procedure.

d. Install the Inboard Flap Track Forward Fairing. Refer to 747-8 AMM 27-51-26 as an accepted

procedure.

e. Do a Check of the Flap Position. Refer to 747-8 AMM 27-51-01 as an accepted procedure.

f. Do a Trailing Edge Flap System - System Test. Refer to 747-8 AMM 27-51-00 as an accepted

procedure.

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BOEING SERVICE BULLETIN 747-57A2348

ALERT ALERT
2. If OPTION 2 was used for PART 2: INBOARD ACCESS, do the following:

a. Remove the transmission removal and installation equipment. Refer to 747-8 AMM 27-51-33

as an accepted procedure.

b. Attach the ball screw to the transmission. Refer to 747-8 AMM 27-51-33 as an accepted

procedure.

c. Connect the applicable torque tubes to the transmission. Refer to 747-8 AMM 27-51-33 as

an accepted procedure.

d. Install the Inboard Flap Track Forward Fairing. Refer to 747-8 AMM 27-51-26 as an accepted

procedure.

e. Do the Inboard Trailing Edge Flap - Adjustment. Refer to 747-8 AMM 27-51-01 as an accepted

procedure.

f. Do a Check of the Flap Position. Refer to 747-8 AMM 27-51-01 as an accepted procedure.

g. Do a Trailing Edge Flap System - System Test. Refer to 747-8 AMM 27-51-00 as an accepted

procedure.

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BOEING SERVICE BULLETIN 747-57A2348

ALERT ALERT
FIGURE 1: FLAP TRACK 1 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - REMOVAL

(SHEET 1 OF 2)

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45 of 78

BOEING SERVICE BULLETIN 747-57A2348

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

numbers shown below are the number of parts necessary for this figure.

Step Task Name Identification Qty More Data

1 Remove Cotter Pin - 2 -

Remove Nut - 2 -

Remove Washer - 6 Under nut.

Remove / Keep Washer BACW10BP8CD 2 Under head.

Remove / Keep Bolt BACB30NR8DK21 2 -

Remove / Keep Bushing BACB28AK08-039 2 Head side.

2 Remove Cotter Pin - 2 -

Remove Nut - 2 -

Under nut. 1 washer

is used for

BACB30NR7DK20.

2 washers are used

for

BACB30LE7DK20.

Remove Washer - 4

Remove / Keep Washer BACW10BP7ACU 2 Under head.

BACB30NR7DK20 OR 2 -

BACB30LE7DK20

Remove / Keep Bolt

Remove / Keep Bushing BACB28AK07-039 2 Head side.

TRANSMISSION AFT - - -

BEARING PLATE ASSEMBLY

3 Remove

FIGURE 1: FLAP TRACK 1 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - REMOVAL

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 747-57A2348

ALERT ALERT
FIGURE 2: FLAP TRACK 2 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - REMOVAL

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 747-57A2348

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

numbers shown below are the number of parts necessary for this figure.

Step Task Name Identification Qty More Data

1 Remove Cotter Pin - 2 -

Remove Nut - 2 -

Remove Washer - 4 Under nut.

Remove / Keep Washer BACW10BP8CD 2 Under head.

Remove / Keep Bolt BACB30LT8DK22 2 -

Remove / Keep Bushing BACB28AK08-042 2 Head side.

2 Remove Cotter Pin - 2 -

Remove Nut - 2 -

Under nut. 1 washer

is used for

BACB30LT7DK22.

2 washers are used

for

BACB30LE7DK22.

Remove Washer - 4

Remove / Keep Washer BACW10BP7ACU 2 Under head.

BACB30LT7DK22 OR 2 -

BACB30LE7DK22

Remove / Keep Bolt

Remove / Keep Bushing BACB28AK07-044 2 Head side.

TRANSMISSION AFT - - -

BEARING PLATE ASSEMBLY

3 Remove

FIGURE 2: FLAP TRACK 2 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - REMOVAL

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 747-57A2348

ALERT ALERT
FIGURE 3: FLAP TRACK 3 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - REMOVAL

(SHEET 1 OF 2)

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49 of 78

BOEING SERVICE BULLETIN 747-57A2348

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

numbers shown below are the number of parts necessary for this figure.

Step Task Name Identification Qty More Data

1 Remove Cotter Pin - 2 -

Remove Nut - 2 -

Remove Washer - 8 Under nut.

Remove / Keep Washer BACW10BP7CD 2 Under head.

Remove / Keep Bolt BACB30NR7DK21 2 -

Remove / Keep Bushing BACB28AK07-041 2 Head side.

2 Remove Cotter Pin - 2 -

Remove Nut - 2 -

Under nut. 1 washer

is used for

BACB30NR7DK20.

2 washers are used

for

BACB30LE7BD20.

Remove Washer - 4

Remove / Keep Washer BACW10BP7ACU 2 Under head.

BACB30NR7DK20 OR 2 -

BACB30LE7BD20

Remove / Keep Bolt

Remove / Keep Bushing BACB28AK07-040 2 Head side.

TRANSMISSION AFT - - -

BEARING PLATE ASSEMBLY

3 Remove

FIGURE 3: FLAP TRACK 3 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - REMOVAL

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 747-57A2348

ALERT ALERT
FIGURE 4: FLAP TRACK 4 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - REMOVAL

(SHEET 1 OF 2)

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51 of 78

BOEING SERVICE BULLETIN 747-57A2348

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

numbers shown below are the number of parts necessary for this figure.

Step Task Name Identification Qty More Data

1 Remove Cotter Pin - 2 -

Remove Nut - 2 -

Remove Washer - 6 Under nut.

Remove / Keep Washer BACW10BP10CD 2 Under head.

Remove / Keep Bolt BACB30NR10DK27 2 -

Remove / Keep Bushing BACB28AK10-053 2 Head side.

2 Remove Cotter Pin - 2 -

Remove Nut - 2 -

Under nut. 1 washer

is used for

BACB30NR9DK24.

2 washers are used

for

BACB30LE9BD24.

Remove Washer - 4

Remove / Keep Washer BACW10BP9ACU 2 Under head.

BACB30NR9DK24 OR 2 -

BACB30LE9BD24

Remove / Keep Bolt

Remove / Keep Bushing BACB28AK09-042 2 Head side.

TRANSMISSION AFT - - -

BEARING PLATE ASSEMBLY

3 Remove

FIGURE 4: FLAP TRACK 4 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - REMOVAL

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 747-57A2348

ALERT ALERT
FIGURE 5: FLAP TRACK 5 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - REMOVAL

(SHEET 1 OF 2)

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53 of 78

BOEING SERVICE BULLETIN 747-57A2348

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

numbers shown below are the number of parts necessary for this figure.

Step Task Name Identification Qty More Data

1 Remove Cotter Pin - 2 -

Remove Nut - 2 -

Remove Washer - 6 Under nut.

Remove / Keep Washer BACW10BP10CD 2 Under head.

Remove / Keep Bolt BACB30NR10DK27 2 -

Remove / Keep Bushing BACB28AK10-053 2 Head side.

2 Remove Cotter Pin - 2 -

Remove Nut - 2 -

Under nut. 1 washer

is used for

BACB30NR9DK24.

2 washers are used

for

BACB30LE9BD24.

Remove Washer - 4

Remove / Keep Washer BACW10BP9ACU 2 Under head.

BACB30NR9DK24 OR 2 -

BACB30LE9BD24

Remove / Keep Bolt

Remove / Keep Bushing BACB28AK09-042 2 Head side.

TRANSMISSION AFT - - -

BEARING PLATE ASSEMBLY

3 Remove

FIGURE 5: FLAP TRACK 5 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - REMOVAL

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 747-57A2348

ALERT ALERT
FIGURE 6: FLAP TRACK 6 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - REMOVAL

(SHEET 1 OF 2)

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55 of 78

BOEING SERVICE BULLETIN 747-57A2348

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

numbers shown below are the number of parts necessary for this figure.

Step Task Name Identification Qty More Data

1 Remove Cotter Pin - 2 -

Remove Nut - 2 -

Remove Washer - 8 Under nut.

Remove / Keep Washer BACW10BP7CD 2 Under head.

Remove / Keep Bolt BACB30NR7DK21 2 -

Remove / Keep Bushing BACB28AK07-041 2 Head side.

2 Remove Cotter Pin - 2 -

Remove Nut - 2 -

Under nut. 1 washer

is used for

BACB30NR7DK20.

2 washers are used

for

BACB30LE7BD20.

Remove Washer - 4

Remove / Keep Washer BACW10BP7ACU 2 Under head.

BACB30NR7DK20 OR 2 -

BACB30LE7BD20

Remove / Keep Bolt

Remove / Keep Bushing BACB28AK07-040 2 Head side.

TRANSMISSION AFT - - -

BEARING PLATE ASSEMBLY

3 Remove

FIGURE 6: FLAP TRACK 6 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - REMOVAL

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 747-57A2348

ALERT ALERT
FIGURE 7: FLAP TRACK 7 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - REMOVAL

(SHEET 1 OF 2)

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57 of 78

BOEING SERVICE BULLETIN 747-57A2348

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

numbers shown below are the number of parts necessary for this figure.

Step Task Name Identification Qty More Data

1 Remove Cotter Pin - 2 -

Remove Nut - 2 -

Remove Washer - 4 Under nut.

Remove / Keep Washer BACW10BP8CD 2 Under head.

Remove / Keep Bolt BACB30LT8DK22 2 -

Remove / Keep Bushing BACB28AK08-042 2 Head side.

2 Remove Cotter Pin - 2 -

Remove Nut - 2 -

Under nut. 1 washer

is used for

BACB30LT7DK22.

2 washers are used

for

BACB30LE7DK22.

Remove Washer - 4

Remove / Keep Washer BACW10BP7ACU 2 Under head.

BACB30LT7DK22 OR 2 -

BACB30LE7DK22

Remove / Keep Bolt

Remove / Keep Bushing BACB28AK07-044 2 Head side.

TRANSMISSION AFT - - -

BEARING PLATE ASSEMBLY

3 Remove

FIGURE 7: FLAP TRACK 7 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - REMOVAL

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 747-57A2348

ALERT ALERT
FIGURE 8: FLAP TRACK 8 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - REMOVAL

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 747-57A2348

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

numbers shown below are the number of parts necessary for this figure.

Step Task Name Identification Qty More Data

1 Remove Cotter Pin - 2 -

Remove Nut - 2 -

Remove Washer - 6 Under nut.

Remove / Keep Washer BACW10BP8CD 2 Under head.

Remove / Keep Bolt BACB30NR8DK21 2 -

Remove / Keep Bushing BACB28AK08-039 2 Head side.

2 Remove Cotter Pin - 2 -

Remove Nut - 2 -

Under nut. 1 washer

is used for

BACB30NR7DK20.

2 washers are used

for

BACB30LE7DK20.

Remove Washer - 4

Remove / Keep Washer BACW10BP7ACU 2 Under head.

BACB30NR7DK20 OR 2 -

BACB30LE7DK20

Remove / Keep Bolt

Remove / Keep Bushing BACB28AK07-039 2 Head side.

TRANSMISSION AFT - - -

BEARING PLATE ASSEMBLY

3 Remove

FIGURE 8: FLAP TRACK 8 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - REMOVAL

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 747-57A2348

ALERT ALERT
FIGURE 9: FLAP TRACK 1 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - INSTALLATION

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 747-57A2348

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

numbers shown below are the number of parts necessary for this figure.

Step Task Name Identification Qty More Data

TRANSMISSION AFT 113U1192-5 1 -

BEARING PLATE ASSY

1 Install (New)

Install (Kept) Bushing BACB28AK07-039 2 Head side.

Install (Kept) Bolt BACB30NR8DK21 2 -

Install (Kept) Washer BACW10BP8CD 2 Under head.

Install (New) WASHER BACW10BP8APU 6 Under nut.

Install (New) NUT BACN11N108CS 2 -

Install (New) PIN BACP18BC03A08P 2 -

2 Install (Kept) Bushing BACB28AK07-039 2 Head side.

BACB30NR7DK20 OR 2 -

BACB30LE7DK20

Install (Kept) Bolt

Install (Kept) Washer BACW10BP7ACU 2 Under head.

Under nut. 1 washer

is required for

BACB30NR7DK20.

2 washers are required for

BACB30LE7DK20.

Install (New) WASHER BACW10BP7APU 4

Install (New) NUT, CASTELLATED BACN11N7CS 2 -

Install (New) PIN BACP18BC03A08P 2 -

INTEGRATED TRACK - - (a)

ASSY - OUTBOARD

FLAP, TRACK NO. 1

3 Identify

TRACK ASSY - OUT- - - (a)

BOARD FLAP, TRACK

NO. 1

Identify

(a) Mark the new part number. Refer to Paragraph 2.C.3., Parts Modified and Reidentified for new part

numbers. Refer to SOPM 20-50-10, Code RH, as an accepted procedure.

FIGURE 9: FLAP TRACK 1 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - INSTALLATION

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 747-57A2348

ALERT ALERT
FIGURE 10: FLAP TRACK 2 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - INSTALLATION

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 747-57A2348

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

numbers shown below are the number of parts necessary for this figure.

Step Task Name Identification Qty More Data

TRANSMISSION AFT 113U1292-5 1 -

BEARING PLATE ASSY

1 Install (New)

Install (Kept) Bushing BACB28AK08-042 2 Head side.

Install (Kept) Bolt BACB30LT8DK22 2 -

Install (Kept) Washer BACW10BP8CD 2 Under head.

Install (New) WASHER BACW10BP8APU 4 Under nut.

Install (New) NUT BACN11N108CS 2 -

Install (New) PIN BACP18BC03A08P 2 -

2 Install (Kept) Bushing BACB28AK07-044 2 Head side.

BACB30LT7DK22 OR 2 -

BACB30LE7DK22

Install (Kept) Bolt

Install (Kept) Washer BACW10BP7ACU 2 Under head.

Under nut. 1 washer

is required for

BACB30LT7DK22.

2 washers are required for

BACB30LE7DK22.

Install (New) WASHER BACW10BP7APU 4

Install (New) NUT, CASTELLATED BACN11N7CS 2 -

Install (New) PIN BACP18BC03A08P 2 -

INTEGRATED TRACK - - (a)

ASSY - OUTBOARD

FLAP, TRACK NO. 2

3 Identify

TRACK ASSY - OUT- - - (a)

BOARD FLAP, TRACK

NO. 2

Identify

(a) Mark the new part number. Refer to Paragraph 2.C.3., Parts Modified and Reidentified for new part

numbers. Refer to SOPM 20-50-10, Code RH, as an accepted procedure.

FIGURE 10: FLAP TRACK 2 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - INSTALLATION

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 747-57A2348

ALERT ALERT
FIGURE 11: FLAP TRACK 3 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - INSTALLATION

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 747-57A2348

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

numbers shown below are the number of parts necessary for this figure.

Step Task Name Identification Qty More Data

TRANSMISSION AFT 113U1392-5 1 -

BEARING PLATE ASSY

1 Install (New)

Install (Kept) Bushing BACB28AK07-041 2 Head side.

Install (Kept) Bolt BACB30NR7DK21 2 -

Install (Kept) Washer BACW10BP7CD 2 Under head.

Install (New) WASHER BACW10BP7APU 8 Under nut.

Install (New) NUT, CASTELLATED BACN11N107CS 2 -

Install (New) PIN BACP18BC03A08P 2 -

2 Install (Kept) Bushing BACB28AK07-040 2 Head side.

BACB30NR7DK20 OR 2 -

BACB30LE7BD20

Install (Kept) Bolt

Install (Kept) Washer BACW10BP7ACU 2 Under head.

Under nut. 1 washer

is required for

BACB30NR7DK20.

2 washers are required for

BACB30LE7BD20.

Install (New) WASHER BACW10BP7APU 4

Install (New) NUT, CASTELLATED BACN11N7CS 2 -

Install (New) PIN BACP18BC03A08P 2 -

INTEGRATED TRACK - - (a)

ASSY - OUTBOARD

FLAP, TRACK NO. 3

3 Identify

TRACK ASSY - OUT- - - (a)

BOARD FLAP, TRACK

NO. 3

Identify

(a) Mark the new part number. Refer to Paragraph 2.C.3., Parts Modified and Reidentified for new part

numbers. Refer to SOPM 20-50-10, Code RH, as an accepted procedure.

FIGURE 11: FLAP TRACK 3 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - INSTALLATION

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 747-57A2348

ALERT ALERT
FIGURE 12: FLAP TRACK 4 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - INSTALLATION

(SHEET 1 OF 2)

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67 of 78

BOEING SERVICE BULLETIN 747-57A2348

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

numbers shown below are the number of parts necessary for this figure.

Step Task Name Identification Qty More Data

TRANSMISSION AFT 113U1492-7 1 -

BEARING PLATE ASSY

1 Install (New)

Install (Kept) Bushing BACB28AK10-053 2 Head side.

Install (Kept) Bolt BACB30NR10DK27 2 -

Install (Kept) Washer BACW10BP10CD 2 Under head.

Install (New) WASHER BACW10BP10APU 6 Under nut.

Install (New) NUT, CASTELLATED BACN11N110CS 2 -

Install (New) PIN BACP18BC04A10P 2 -

2 Install (Kept) Bushing BACB28AK09-042 2 Head side.

BACB30NR9DK24 OR 2 -

BACB30LE9BD24

Install (Kept) Bolt

Install (Kept) Washer BACW10BP9ACU 2 Under head.

Under nut. 1 washer

is required for

BACB30NR9DK24.

2 washers are required for

BACB30LE9BD24.

Install (New) WASHER BACW10BP9APU 4

Install (New) NUT, CASTELLATED BACN11N9CS 2 -

Install (New) PIN BACP18BC04A10P 2 -

INTEGRATED TRACK - - (a)

ASSY - OUTBOARD

FLAP, TRACK NO. 4

3 Identify

TRACK ASSY - OUT- - - (a)

BOARD FLAP, TRACK

NO. 4

Identify

(a) Mark the new part number. Refer to Paragraph 2.C.3., Parts Modified and Reidentified for new part

numbers. Refer to SOPM 20-50-10, Code RH, as an accepted procedure.

FIGURE 12: FLAP TRACK 4 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - INSTALLATION

(SHEET 2 OF 2)

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FIGURE 13: FLAP TRACK 5 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - INSTALLATION

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 747-57A2348

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

numbers shown below are the number of parts necessary for this figure.

Step Task Name Identification Qty More Data

TRANSMISSION AFT 113U1492-8 1 -

BEARING PLATE ASSY

1 Install (New)

Install (Kept) Bushing BACB28AK10-053 2 Head side.

Install (Kept) Bolt BACB30NR10DK27 2 -

Install (Kept) Washer BACW10BP10CD 2 Under head.

Install (New) WASHER BACW10BP10APU 6 Under nut.

Install (New) NUT, CASTELLATED BACN11N110CS 2 -

Install (New) PIN BACP18BC04A10P 2 -

2 Install (Kept) Bushing BACB28AK09-042 2 Head side.

BACB30NR9DK24 OR 2 -

BACB30LE9BD24

Install (Kept) Bolt

Install (Kept) Washer BACW10BP9ACU 2 Under head.

Under nut. 1 washer

is required for

BACB30NR9DK24.

2 washers are required for

BACB30LE9BD24.

Install (New) WASHER BACW10BP9APU 4

Install (New) NUT, CASTELLATED BACN11N9CS 2 -

Install (New) PIN BACP18BC04A10P 2 -

INTEGRATED TRACK - - (a)

ASSY - OUTBOARD

FLAP, TRACK NO. 4

3 Identify

TRACK ASSY - OUT- - - (a)

BOARD FLAP, TRACK

NO. 4

Identify

(a) Mark the new part number. Refer to Paragraph 2.C.3., Parts Modified and Reidentified for new part

numbers. Refer to SOPM 20-50-10, Code RH, as an accepted procedure.

FIGURE 13: FLAP TRACK 5 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - INSTALLATION

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 747-57A2348

ALERT ALERT
FIGURE 14: FLAP TRACK 6 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - INSTALLATION

(SHEET 1 OF 2)

Export Controlled ECCN: 9E991 - BOEING

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Work - See page 1 for details.

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71 of 78

BOEING SERVICE BULLETIN 747-57A2348

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

numbers shown below are the number of parts necessary for this figure.

Step Task Name Identification Qty More Data

TRANSMISSION AFT 113U1392-6 1 -

BEARING PLATE ASSY

1 Install (New)

Install (Kept) Bushing BACB28AK07-041 2 Head side.

Install (Kept) Bolt BACB30NR7DK21 2 -

Install (Kept) Washer BACW10BP7CD 2 Under head.

Install (New) WASHER BACW10BP7APU 8 Under nut.

Install (New) NUT, CASTELLATED BACN11N107CS 2 -

Install (New) PIN BACP18BC03A08P 2 -

2 Install (Kept) Bushing BACB28AK07-040 2 Head side.

BACB30NR7DK20 OR 2 -

BACB30LE7BD20

Install (Kept) Bolt

Install (Kept) Washer BACW10BP7ACU 2 Under head.

Under nut. 1 washer

is required for

BACB30NR7DK20.

2 washers are required for

BACB30LE7BD20.

Install (New) WASHER BACW10BP7APU 4

Install (New) NUT, CASTELLATED BACN11N7CS 2 -

Install (New) PIN BACP18BC03A08P 2 -

INTEGRATED TRACK - - (a)

ASSY - OUTBOARD

FLAP, TRACK NO. 3

3 Identify

TRACK ASSY - OUT- - - (a)

BOARD FLAP, TRACK

NO. 3

Identify

(a) Mark the new part number. Refer to Paragraph 2.C.3., Parts Modified and Reidentified for new part

numbers. Refer to SOPM 20-50-10, Code RH, as an accepted procedure.

FIGURE 14: FLAP TRACK 6 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - INSTALLATION

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 747-57A2348

ALERT ALERT
FIGURE 15: FLAP TRACK 7 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - INSTALLATION

(SHEET 1 OF 2)

Export Controlled ECCN: 9E991 - BOEING

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73 of 78

BOEING SERVICE BULLETIN 747-57A2348

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

numbers shown below are the number of parts necessary for this figure.

Step Task Name Identification Qty More Data

TRANSMISSION AFT 113U1292-6 1 -

BEARING PLATE ASSY

1 Install (New)

Install (Kept) Bushing BACB28AK08-042 2 Head side.

Install (Kept) Bolt BACB30LT8DK22 2 -

Install (Kept) Washer BACW10BP8CD 2 Under head.

Install (New) WASHER BACW10BP8APU 4 Under nut.

Install (New) NUT BACN11N108CS 2 -

Install (New) PIN BACP18BC03A08P 2 -

2 Install (Kept) Bushing BACB28AK07-044 2 Head side.

BACB30LT7DK22 OR 2 -

BACB30LE7DK22

Install (Kept) Bolt

Install (Kept) Washer BACW10BP7ACU 2 Under head.

Under nut. 1 washer

is required for

BACB30LT7DK22.

2 washers are required for

BACB30LE7DK22.

Install (New) WASHER BACW10BP7APU 4

Install (New) NUT, CASTELLATED BACN11N7CS 2 -

Install (New) PIN BACP18BC03A08P 2 -

INTEGRATED TRACK - - (a)

ASSY - OUTBOARD

FLAP, TRACK NO. 2

3 Identify

TRACK ASSY - OUT- - - (a)

BOARD FLAP, TRACK

NO. 2

Identify

(a) Mark the new part number. Refer to Paragraph 2.C.3., Parts Modified and Reidentified for new part

numbers. Refer to SOPM 20-50-10, Code RH, as an accepted procedure.

FIGURE 15: FLAP TRACK 7 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - INSTALLATION

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 747-57A2348

ALERT ALERT
FIGURE 16: FLAP TRACK 8 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - INSTALLATION

(SHEET 1 OF 2)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

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75 of 78

BOEING SERVICE BULLETIN 747-57A2348

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

numbers shown below are the number of parts necessary for this figure.

Step Task Name Identification Qty More Data

TRANSMISSION AFT 113U1192-6 1 -

BEARING PLATE ASSY

1 Install (New)

Install (Kept) Bushing BACB28AK07-039 2 Head side.

Install (Kept) Bolt BACB30NR8DK21 2 -

Install (Kept) Washer BACW10BP8CD 2 Under head.

Install (New) WASHER BACW10BP8APU 6 Under nut.

Install (New) NUT BACN11N108CS 2 -

Install (New) PIN BACP18BC03A08P 2 -

2 Install (Kept) Bushing BACB28AK07-039 2 Head side.

BACB30NR7DK20 OR 2 -

BACB30LE7DK20

Install (Kept) Bolt

Install (Kept) Washer BACW10BP7ACU 2 Under head.

Under nut. 1 washer

is required for

BACB30NR7DK20.

2 washers are required for

BACB30LE7DK20.

Install (New) WASHER BACW10BP7APU 4

Install (New) NUT, CASTELLATED BACN11N7CS 2 -

Install (New) PIN BACP18BC03A08P 2 -

INTEGRATED TRACK - - (a)

ASSY - OUTBOARD

FLAP, TRACK NO. 1

3 Identify

TRACK ASSY - OUT- - - (a)

BOARD FLAP, TRACK

NO. 1

Identify

(a) Mark the new part number. Refer to Paragraph 2.C.3., Parts Modified and Reidentified for new part

numbers. Refer to SOPM 20-50-10, Code RH, as an accepted procedure.

FIGURE 16: FLAP TRACK 8 - TRANSMISSION AFT BEARING PLATE ASSEMBLY - INSTALLATION

(SHEET 2 OF 2)

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ALERT ALERT
APPENDIX A: DELETED

(SHEET 1 OF 1)

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ALERT ALERT
APPENDIX B: PART DEMAND INTENT

(SHEET 1 OF 1)

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BOEING SERVICE BULLETIN 747-57A2348

ALERT ALERT