Commercial 

Airplanes 767

Service Bulletin

ALERT

Number: 767-57A0079

Original Issue: June 20, 2002

Revision 2: March 23, 2012

ATA System: 5750

SUBJECT: WINGS - Trailing Edge and Trailing Edge Devices - Inboard Main Flap - Hinge Fitting

Assembly Inspection and Replacement

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

CFR 730-774). 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 © 2002 The Boeing Company

Unpublished Work - All Rights Reserved

Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable

subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.

This document includes proprietary information owned by The Boeing Company and/or one or more third parties.

Treatment of the document and the information it contains is governed by contract with Boeing. For more

information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.

Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,

BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the

Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in

connection with this document unless provided in writing by Boeing.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2: March 23, 2012 767-57A0079

1 of 38

3.0
BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2: March 23, 2012 767-57A0079

2 of 38

BOEING SERVICE BULLETIN 767-57A0079

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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

2. Data supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 16

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . . . 18

3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 19

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

FIGURE 1: LOGIC DIAGRAM OF INSPECTION AND MAINTENANCE ALTERNATIVES . . . . . . . 25

FIGURE 2: OUTBOARD HINGE FITTING - DETAILED INSPECTION . . . . . . . . . . . . . . . . . 26

FIGURE 3: OUTBOARD HINGE FITTING - DETAILED AND EDDY CURRENT INSPECTION . . . . 29

FIGURE 4: HINGE FITTING ASSEMBLY - REPLACEMENT . . . . . . . . . . . . . . . . . . . . . . 33

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2: March 23, 2012 767-57A0079

3 of 38

BOEING SERVICE BULLETIN 767-57A0079

ALERT ALERT
BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2: March 23, 2012 767-57A0079

4 of 38

BOEING SERVICE BULLETIN 767-57A0079

ALERT ALERT

BLANK PAGE
Commercial 

Airplanes 767

Service Bulletin

ALERT

Revision Transmittal Sheet Number: 767-57A0079

Original Issue: June 20, 2002

Revision 2: March 23, 2012

ATA System: 5750

SUBJECT: WINGS - Trailing Edge and Trailing Edge Devices - Inboard Main Flap - Hinge Fitting

Assembly Inspection and Replacement

This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

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

service bulletin. However, operators must continue to do the repetitive inspections of the hinge fittings, at the

times in accordance with Paragraph 1.E., Compliance until new hinge fitting assemblies 113T2271-419 (Left)

and 113T2271-420 (Right) are installed.

REASON FOR REVISION

This revision is sent to change the inspection requirements in Figure 2 and Figure 3 of this service bulletin. The

inspection area on the trailing edge main flap hinge fitting is changed and limited to the outboard half only.

Subsequent to the release of Revision 1 of this service bulletin, one operator reported finding a fractured hinge

fitting assembly. The fracture occurred on a hinge fitting assembly at approximately 780 flight-cycles after its

last inspection on a 767-300 airplane. An examination of the fractured hinge fitting assembly showed that the

crack started at the edge of the current inspection area. The service bulletin illustrations have been updated to

clearly show the expected crack location and direction. The latest service bulletin format standards have also

been updated where applicable.

These sections are changed:

1. Service Bulletin Title updated.

2. Summary - Illustration - Illustration updated to show the expected crack location and direction.

3. Paragraph 1.F., Approval - AMOC statement updated.

4. Paragraph 1.G., Manpower - Table updated.

5. Paragraph 1.K.1., Publications - CMM reference added.

6. Paragraph 1.K.2., Damage Tolerance Based Structural Inspections - Damage Tolerance Inspections (DTI)

statement added.

7. Paragraph 3.A., General Information - General notes updated.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2: March 23, 2012 767-57A0079

5 of 38
8. Paragraph 3.B., Work Instructions - Titles updated and Part 3, Steps 3 and 5 updated to correct the access

panel numbers. Also the latest service bulletin format standards have also been updated where applicable.

9. Figure 1 - Illustration updated to revise the data in compliance Logic Diagram.

10. Figure 2 - Illustration updated to incorporate the new inspection requirements.

11. Figure 3 - Illustration updated to incorporate the new inspection requirements.

12. Figure 4 - Step table updated to remove the QTY for shims.

The data given in Alternative Method of Compliance Notice 767-57A0079-AMOC-01 is included in this revision.

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: June 20, 2002

Revision 1: May 06, 2010

Revision 2: March 23, 2012

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2: March 23, 2012 767-57A0079

6 of 38

BOEING SERVICE BULLETIN 767-57A0079

ALERT ALERT
Commercial 

Airplanes 767

Service Bulletin

ALERT

Summary Number: 767-57A0079

Original Issue: June 20, 2002

Revision 2: March 23, 2012

ATA System: 5750

SUBJECT: WINGS - Trailing Edge and Trailing Edge Devices - Inboard Main Flap - Hinge Fitting

Assembly Inspection and Replacement

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

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

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

THE NEW OWNER.

CONCURRENT REQUIREMENTS

None.

BACKGROUND

Accomplishment of this service bulletin will detect cracks, prevent fractures and ensure the structural integrity

of the inboard trailing edge main flap outboard hinge fittings. Fracture of the hinge fitting assemblies could result

in the inboard aft flap becoming unrestrained potentially striking the aircraft upon departure, resulting in significant

damage to the surrounding structure and could cause potential personal injury.

One operator of a 767-300 reported lug fractures on both the inboard and outboard hinge fittings of the outboard

hinge assembly mounted to the main flap. The hinge assembly provides one of two primary attachment points

of the inboard trailing edge aft flap assembly. The outboard hinge fitting was fractured just above the lug hole.

The fractured hinge fittings were found during a routine maintenance inspection. The airplane had accumulated

9,598 flight-hours and 5,393 flight cycles.

During root cause analysis of the fractured hinge fitting it was discovered that an optional tool runout was not

present on the damaged fitting assemblies. The tool runout option allows the part to be machined thicker within

the area reported to be fractured. Boeing has received no reports of cracks or fractures on fitting that have the

additional material area of the optional tool runout. Service bulletin 767-57A0076 was released to inspect and

replace the suspect hinge fittings if and as required on all 767-200, 767-300 and 767-300F airplanes line numbers

1 through 825. The inboard trailing edge main flap outboard hinge fittings on the 767-400ER are similar in design

to the 767-200, 767-300 and 767-300F fittings. The 767-400ER fittings are wider and thicker; however, higher

fatigue loads are associated with the 767-400ER in this area. Analysis indicates the 767-400ER fittings could

be susceptible to early fatigue cracking and/or fractures as a result of these higher loads.

Subsequent to the original issue of this service bulletin, 3 reports of hinge fitting assembly fracture have been

received. The fractures all occurred at approximately 9,100 flight-cycles and in 1 case fracture at approximately

1,400 flight-cycles after the last detailed - eddy current inspection. Based on the reports of the fractured hinge

fitting assemblies prior to the initial threshold and the repeat interval, revision 1 reduced the initial threshold and

repeat interval. Revision 2 changed the inspection area to show clearly the expected crack location and direction.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2: March 23, 2012 767-57A0079

7 of 38
Replacement of the hinge fitting assembly with a more robust designed fitting will ensure the structural integrity

of the aft flap, prevent damage to the surrounding structure and stop the potential for personal injury.

Boeing Service Related Problem (SRP) 767-SRP-57-0119 is related to this service bulletin.

Boeing Service Related Problem (SRP) 767-SRP-57-0233 is related to this service bulletin.

ACTION

Inspect the inboard trailing edge main flap outboard hinge fittings on the left and right wing for cracks or fractures.

If any cracks or fractures are found, complete terminating action. If cracks or fractures are not found, repeat the

inspections at the intervals in accordance with FIGURE 1 until terminating action is completed.

EFFECTIVITY

767-400ER Airplanes. Refer to Paragraph 1.A., Effectivity, for the list of affected airplanes.

COMPLIANCE

Federal Aviation Administration (FAA) Airworthiness Directive AD 2003-13-01 is related to this service bulletin.

Refer to FIGURE 1 Logic Diagram for Inspection and Maintenance Alternatives.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the configuration changes, inspection and/or repair procedures

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.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2: March 23, 2012 767-57A0079

8 of 38

BOEING SERVICE BULLETIN 767-57A0079

ALERT ALERT
BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2: March 23, 2012 767-57A0079

9 of 38

BOEING SERVICE BULLETIN 767-57A0079

ALERT ALERT
BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2: March 23, 2012 767-57A0079

10 of 38

BOEING SERVICE BULLETIN 767-57A0079

ALERT ALERT

BLANK PAGE
Commercial 

Airplanes 767

Service Bulletin

ALERT

Number: 767-57A0079

Original Issue: June 20, 2002

Revision 2: March 23, 2012

ATA System: 5750

SUBJECT: WINGS - Trailing Edge and Trailing Edge Devices - Inboard Main Flap - Hinge Fitting

Assembly Inspection and 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

Refer to Service Bulletin Index Document D6-24T001 Part 3 for Airplane Variable Number, Line

Number, and Serial Number data.

This service bulletin is for the airplanes shown below. An equivalent change is on subsequent

production airplanes. Refer to PRR12901-9S for data about this change.

GROUP CONFIGURATION DESCRIPTION

1 - 767-400ER airplanes line numbers 758 through 877.

Airplane Models:

767-400ER

Variable Number Group

VQ001 - VQ021 1

VQ071 - VQ085 1

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2: March 23, 2012 767-57A0079

11 of 38
2. Spares Affected

Examine your 767-400ER inboard trailing edge main flap spares supply for the 113T2271-401 and

113T2271-402 outboard hinge fitting assemblies. If any parts are found, refer to Paragraph 2.C.,

Parts Necessary for Each Airplane and Paragraph 2.D., Parts Necessary to Change Spares for

the recommended use.

B. Concurrent Requirements

None.

C. Reason

Accomplishment of this service bulletin will detect cracks, prevent fractures and ensure the structural

integrity of the inboard trailing edge main flap outboard hinge fittings. Fracture of the hinge fittings could

result in the inboard aft flap becoming unrestrained potentially striking the aircraft upon departure,

resulting in significant damage to the surrounding structure and could cause potential personal injury.

One operator of a 767-300 reported lug fractures on both the inboard and outboard hinge fittings of

the outboard hinge assembly mounted to the main flap. The hinge assembly provides one of two primary

attachment points of the inboard trailing edge aft flap assembly. The outboard fitting was fractured just

above the lug hole. The fractured fittings were found during a routine maintenance inspection. The

airplane had accumulated 9,598 flight-hours and 5,393 flight cycles.

During root cause analysis of the fractured hinge fitting it was discovered that an optional tool runout

was not present on the damaged fitting assemblies. The tool runout option allows the part to be machined

thicker within the area reported to be fractured. Boeing has received no reports of cracks or fractures

on fitting that have the additional material area of the optional tool runout. Service bulletin 767-57A0076

was released to inspect and replace the suspect hinge fittings if and as required on all 767-200, 767-300

and 767-300F airplanes line numbers 1 through 825. The inboard trailing edge main flap outboard

hinge fittings on the 767-400ER are similar in design to the 767-200, 767-300 and 767-300F fittings.

The 767-400ER fittings are wider and thicker; however, higher fatigue loads are associated with the

767-400ER in this area. Analysis indicates the 767-400ER fittings could be susceptible to early fatigue

cracking and/or fractures as a result of these higher loads.

Subsequent to the original issue of this service bulletin, 3 reports of hinge assembly fracture have been

received. The fractures all occurred at approximately 9,100 flight-cycles and in 1 case fracture at

approximately 1,400 flight-cycles after the last detailed - eddy current inspection. Based on the reports

of the fractured hinge fitting assemblies prior to the initial threshold and the repeat interval, revision 1

reduced the initial threshold and repeat interval. Revision 2 changed the inspection area to show clearly

the expected crack location and direction.

Replacement of the outboard hinge fitting with a more robust designed fitting will ensure the structural

integrity of the aft flap, prevent damage to the surrounding structure and stop the potential for personal

injury.

Boeing Service Related Problem (SRP) 767-SRP-57-0119 is related to this service bulletin.

Boeing Service Related Problem (SRP) 767-SRP-57-0233 is related to this service bulletin.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2: March 23, 2012 767-57A0079

12 of 38

BOEING SERVICE BULLETIN 767-57A0079

ALERT ALERT
Revision 1 was sent to

1. To reduce the initial compliance time and repeat interval based on service reports. Subsequent

to the original issue of this service bulletin, operators have reported finding 3 fractured hinge fitting

assemblies. The fractured hinge fitting assemblies had accumulated less flight-cycles than the

initial compliance threshold and in 1 case, the hinge fitting assembly fractured after the original

inspection and prior to the next repeat inspection. Boeing Service Related Problem (SRP)

767-SRP-57-0233 was issued to address this issue.

2. Add instructions to transfer the stainless steel filler and the shims for the mid fairing roller from the

old hinge fitting assembly to the new hinge fitting assembly.

3. Revise inspection area to show inspection from the center of the lug forward, not the end of the

lug forward. This moves the inspection forward to inspect additional area where cracking has been

found, not the lug bore where cracking has not been found.

4. Add reference to the existing AD, add an AMOC to the existing AD, and reference the possible

new AD which would make the compliance tasks and times in Revision 1 of this service bulletin

mandatory.

5. Update the format of the service bulletin to meet current service bulletin standards.

Revision 2 is sent to change the inspection requirements in Figure 2 and Figure 3 of this service bulletin.

The inspection area on the trailing edge main flap hinge fitting is changed and limited to the outboard

half only. Subsequent to the release of Revision 1 of this service bulletin, one operator reported finding

a fractured hinge fitting. The fracture occurred on a hinge fitting at approximately 780 flight-cycles after

its last inspection on a 767-300 airplane. An examination of the fractured hinge fitting assembly showed

that the crack started at the edge of the current inspection area. The service bulletin illustrations have

been updated to clearly show the expected crack location and direction. The latest service bulletin

format standards have also been updated where applicable.

D. Description

Inspect the inboard trailing edge main flap outboard hinge fittings on the left and right wing for cracks

or fractures. If any cracks or fractures are found, complete terminating action. If cracks or fractures are

not found, repeat the inspections at the intervals in accordance with FIGURE 1 until terminating action

is completed.

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 the airplanes changed in accordance with the original issue

or Revision 1 of this service bulletin. However, operators must continue to do the repetitive inspections

of the hinge fittings, at the times in accordance with Paragraph 1.E., Compliance until new hinge fitting

assemblies 113T2271-419 (Left) and 113T2271-420 (Right) are installed.

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

Affected Maintenance Zones

Model Zone

767-400ER 555, 655

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2: March 23, 2012 767-57A0079

13 of 38

BOEING SERVICE BULLETIN 767-57A0079

ALERT ALERT
E. Compliance

Federal Aviation Administration (FAA) Airworthiness Directive AD 2003-13-01 is related to this service

bulletin.

Refer to FIGURE 1 Logic Diagram for Inspection and Maintenance Alternatives.

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 service bulletin has been approved by the FAA. In addition, the Manager of the FAA Seattle Aircraft

Certification Office approves the inspections, follow-on and corrective actions, and terminating action

in this service bulletin as an alternative method of compliance to the requirements of paragraph (a)(2),

(b), and (f) of AD 2003-13-01. All provisions of AD 2003-13-01 that are not specifically referenced in

the above statement 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 fitting inspections and

replacement for each airplane. This estimate is for direct labor only, done by an experienced crew.

Adjust the estimate with operator task-hour data if necessary. The estimate does not include lost time.

These are some examples of lost time:

— Time to adjust to the workplace

— Time to schedule the work

— Time to examine the work

— Time to cure the materials

— Time to make the parts

— Time to find the tools.

Part 1 - Detailed Inspection

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 2 2.0 1.0

Detailed Inspection 1 1.0 1.0

Close Access 2 2.0 1.0

TOTAL FOR EACH WING 5.0 3.0

TOTAL FOR EACH AIRPLANE 10.0 6.0

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2: March 23, 2012 767-57A0079

14 of 38

BOEING SERVICE BULLETIN 767-57A0079

ALERT ALERT
Part 2 - Detailed and Eddy Current Inspection

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 2 2.0 1.0

Detailed Inspection 1 1.0 1.0

Eddy Current In- 1 1.5 1.5

spection

Close Access 2 2.0 1.0

TOTAL FOR EACH WING 6.5 4.5

TOTAL FOR EACH AIRPLANE 13.0 9.0

(a) The total task hours and elapsed hours are not given as the work necessary

for each airplane is variable.

Part 3 - Terminating Action

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 2 2.0 1.0

Replace Fitting 2 12.0 6.0

Close Access 2 2.0 1.0

TOTAL FOR EACH WING 16.0 8.0

TOTAL FOR EACH AIRPLANE 32.0 16.0

H. Weight and Balance Changes

None.

I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. Boeing Service Bulletin 767-57A0076

b. Boeing Service Related Problem (SRP) 767-SRP-57-0119, 767-SRP-57-0233

c. Component Maintenance Manual (CMM) 57-53-27

d. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2003-13-01

e. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-41-02, 20-50-10, 20-50-19

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2: March 23, 2012 767-57A0079

15 of 38

BOEING SERVICE BULLETIN 767-57A0079

ALERT ALERT
f. 767 Aircraft Maintenance Manual (AMM) 06-44-00, 27-51-00

g. 767 Non-Destructive Testing (NDT) Manual Part 6, 51-00-01, Part 6, 51-00-19

h. Engineering Change Memo PRR 12901-9S

2. Data supplied with this Service Bulletin:

None.

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

Drawing Number Title

113T2000 Flap Instl - Inbd T.E. Flap

This drawing was used to prepare this service bulletin. This drawing is not necessary to make the

specified changes, and is not supplied with this service bulletin. This drawing may not be applicable

to all airplane configurations or operators.

K. Publications Affected

1. Publications:

Publication Chapter-Section

767 Illustrated Parts Catalog 27-51

Component Maintenance Manual 57-53

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

Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for interchangeability and intermixability

information.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2: March 23, 2012 767-57A0079

16 of 38

BOEING SERVICE BULLETIN 767-57A0079

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, and Paragraph

2.D., Parts Necessary to Change Spares. 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 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

015T1689-1 Top Kit May 06/02 1 367 $46,390.00

Jun 27/02 2

Nov 15/02 8

B. Industry Support Information

Boeing warranty remedies are not available for the configuration changes, inspection and/or repair

procedures given in this service bulletin.

C. Parts Necessary For Each Airplane

1. Kits/Parts:

Kit 015T1689

Existing Part Notes

Number

New Part Number QTY Name

-3 -2 -1

015T1689-1 . . - Subkit, Top Kit

015T1689-2 . - 1 Subkit, Hinge Fitting

015T1689-3 - . 1 Subkit, Hinge Fitting

113T2271-419 1 . . Hinge Fitting Assembly - Left 113T2271-401 (a) (b) (c) (f)

(a) (b) (c)

(g)

113T2271-420 . 1 . Hinge Fitting Assembly - Right 113T2271-402

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2: March 23, 2012 767-57A0079

17 of 38

BOEING SERVICE BULLETIN 767-57A0079

ALERT ALERT
Kit 015T1689

Existing Part Notes

Number

New Part Number QTY Name

-3 -2 -1

BACB30LE5K19 2 2 . Bolt (d)

BACB30LE5K19X 2 2 . Bolt (optional 1/64 oversize) (d)

BACB30LE5K20 2 2 . Bolt (d)

BACB30LE5K20X 2 2 . Bolt (optional 1/64 oversize) (d)

BACS40R015D015F 2 2 . Shim (e)

BACS40R015D017F 2 2 . Shim (e)

BACW10BP5CD 4 4 . Washer

BACW10BP51CD 4 4 . Washer (optional 1/64 oversize)

BACW10BP5DP 4 4 . Washer

BACW10BP51DP 4 4 . Washer (optional 1/64 oversize)

NAS1805-5L 4 4 . Nut

(a) Discard the existing part.

(b) This part is used in production.

(c) You cannot use the existing part to replace the new or changed part.

(d) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer

than indicated. Also, if any fasteners part numbers listed are not available or have been superseded,

substitute fasteners may be supplied in kits.

(e) Use original shims located between the fitting assembly and the flap skin to maintain the original

hinge line geometry of the fittings. However, if the original shims are damaged, replace shims.

Maintain the thickness and location of the original shims.

(f) The 113T2271-419 hinge fitting assembly is composed of a matched set of hinge fittings. The

113T2271-415 and the 113T2271-417.

(g) The 113T2271-420 hinge fitting assembly is composed of a matched set of hinge fittings. The

113T2271-416 and the 113T2271-418.

2. Parts and Materials Supplied by the Operator:

Part Number / QTY Name Notes

Specification

BMS 5-95 8 ounces Sealant (a)

BMS 10-11, Type I 4 ounces Primer (a)

MIL-G-23827 4 ounces Grease (a)

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

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2: March 23, 2012 767-57A0079

18 of 38

BOEING SERVICE BULLETIN 767-57A0079

ALERT ALERT
3. Parts Modified and Reidentified:

None.

4. Parts Removed and Not Replaced:

None.

D. Parts Necessary to Change Spares

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

Part Number Name QTY Notes

015T1689-1 Top Kit 1 (a)

(a) The 015T1689-1 top kit consists of two 015T1689 hinge fitting sub kits. The

015T1689-2 subkit contains the parts required to rework a right inboard

trailing edge main flap assembly. The 015T1689-3 subkit contains the parts

required to rework a left inboard trailing edge main flap assembly.

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.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2: March 23, 2012 767-57A0079

19 of 38

BOEING SERVICE BULLETIN 767-57A0079

ALERT ALERT
BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2: March 23, 2012 767-57A0079

20 of 38

BOEING SERVICE BULLETIN 767-57A0079

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. 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 limits to tighten nuts and bolts are in SRM Chapter 51

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

SRM Chapter 51.

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

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

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

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

grip length in accordance with SRM Chapter 51.

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 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. 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.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2: March 23, 2012 767-57A0079

21 of 38

BOEING SERVICE BULLETIN 767-57A0079

ALERT ALERT
9. 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.

10. 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.

11. 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.

B. WORK INSTRUCTIONS

PART 1 - DETAILED INSPECTION

1. Extend and deactivate the trailing edge flaps. Refer to 767 AMM 27-51-00 as an accepted

procedure.

2. Remove the number 3 and 6 trailing edge aft flap adjustment access panels listed below. Refer

to 767 AMM 06-44-00 for location of these panels.

Left Wing Right Wing

571GL 671GL

571GR 671GR

3. On the left and right wing, do a Detailed Inspection of the inboard trailing edge main flap outboard

hinge fittings for cracks and or fractures in accordance with FIGURE 2.

4. If cracked or fractured fittings are found, do Part 3 - Terminating action.

5. If no cracks or fractures are found, repeat the inspections at the intervals in accordance with

FIGURE 1 until terminating action is completed.

6. Install the number 3 and 6 trailing edge aft flap adjustment access panels listed below. Refer to

767 AMM 06-44-00 for location of these panels.

Left Wing Right Wing

571GL 671GL

571GR 671GR

7. Activate and retract the trailing edge flaps. Refer to 767 AMM 27-51-00 as an accepted procedure.

8. Put the airplane back to a serviceable condition.

PART 2 - DETAILED AND EDDY CURRENT INSPECTION

1. Extend and deactivate the trailing edge flaps. Refer to 767 AMM 27-51-00 as an accepted

procedure.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2: March 23, 2012 767-57A0079

22 of 38

BOEING SERVICE BULLETIN 767-57A0079

ALERT ALERT
2. Remove the number 3 and 6 trailing edge aft flap adjustment access panels listed below. Refer

to 767 AMM 06-44-00 for location of these panels.

Left Wing Right Wing

571GL 671GL

571GR 671GR

3. On the left and right wing, do a Detailed Inspection and an eddy current inspection of the inboard

trailing edge main flap outboard hinge fittings for cracks and or fractures in accordance with FIGURE

3.

4. If cracked or fractured fittings are found, do Part 3 - Terminating action.

5. If no cracks or fractures are found, repeat the inspections at the intervals in accordance with

FIGURE 1 until terminating action is completed.

6. Install the number 3 and 6 trailing edge aft flap adjustment access panels listed below. Refer to

767 AMM 06-44-00 for location of these panels.

Left Wing Right Wing

571GL 671GL

571GR 671GR

7. Activate and retract the trailing edge flaps. Refer to 767 AMM 27-51-00 as an accepted procedure.

8. Put the airplane back to a serviceable condition.

PART 3 - TERMINATING ACTION

1. Extend and deactivate the trailing edge flaps. Refer to 767 AMM 27-51-00 as an accepted

procedure.

2. Remove the number 3 and 6 trailing edge main flap fairing mid sections listed below. Refer to 767

AMM 06-44-00 for location of these fairings.

Left Wing Right Wing

571DB 671DB

3. Remove the number 3 and 6 trailing edge main flap fairing upper skin access panels listed below.

Refer to 767 AMM 06-44-00 for location of these panels.

Left Wing Right Wing

555JT 655JT

4. On the left and right wing, replace the inboard trailing edge main flap outboard hinge fittings in

accordance with FIGURE 4.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2: March 23, 2012 767-57A0079

23 of 38

BOEING SERVICE BULLETIN 767-57A0079

ALERT ALERT
NOTE: The outboard hinge fitting and the inboard hinge fitting are attached together to make the

hinge fitting assembly. If cracks or fractures are found on the outboard hinge fitting, it is

necessary to change both (inboard and outboard) hinge fittings.

5. Install the number 3 and 6 trailing edge main flap fairing upper skin access panels listed below.

Refer to 767 AMM 06-44-00 for location of these panels.

Left Wing Right Wing

555JT 655JT

6. Install the number 3 and 6 trailing edge main flap fairing mid sections listed below. Refer to 767

AMM 06-44-00 for location of these fairings.

Left Wing Right Wing

571DB 671DB

7. Activate and retract the trailing edge flaps. Refer to 767 AMM 27-51-00 as an accepted procedure.

8. Put the airplane back to a serviceable condition.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2: March 23, 2012 767-57A0079

24 of 38

BOEING SERVICE BULLETIN 767-57A0079

ALERT ALERT
FIGURE 1: LOGIC DIAGRAM OF INSPECTION AND MAINTENANCE ALTERNATIVES

(SHEET 1 OF 1)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2 March 23, 2012 767-57A0079

25 of 38

BOEING SERVICE BULLETIN 767-57A0079

ALERT ALERT
FIGURE 2: OUTBOARD HINGE FITTING - DETAILED INSPECTION

(SHEET 1 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2 March 23, 2012 767-57A0079

26 of 38

BOEING SERVICE BULLETIN 767-57A0079

ALERT ALERT
FIGURE 2: OUTBOARD HINGE FITTING - DETAILED INSPECTION

(SHEET 2 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2 March 23, 2012 767-57A0079

27 of 38

BOEING SERVICE BULLETIN 767-57A0079

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

numbers shown below are the number of parts necessary for one side of the airplane.

Step Task Name Identification Qty More Data

to remove loose dirt,

grease and oil. Refer

to SOPM 20-30-03

as an accepted procedure.

1 Clean Outboard Hinge Fittings - 1

Do a Detailed Inspection for cracks or

fractures within the

indicated area. (a)

2 Inspect Outboard Hinge Fittings - 1

(a) On outboard hinge fitting only. Both faces on the outboard hinge fitting require inspection in the area

shown.

FIGURE 2: OUTBOARD HINGE FITTING - DETAILED INSPECTION

(SHEET 3 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2 March 23, 2012 767-57A0079

28 of 38

BOEING SERVICE BULLETIN 767-57A0079

ALERT ALERT
FIGURE 3: OUTBOARD HINGE FITTING - DETAILED AND EDDY CURRENT INSPECTION

(SHEET 1 OF 4)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2 March 23, 2012 767-57A0079

29 of 38

BOEING SERVICE BULLETIN 767-57A0079

ALERT ALERT
FIGURE 3: OUTBOARD HINGE FITTING - DETAILED AND EDDY CURRENT INSPECTION

(SHEET 2 OF 4)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2 March 23, 2012 767-57A0079

30 of 38

BOEING SERVICE BULLETIN 767-57A0079

ALERT ALERT
FIGURE 3: OUTBOARD HINGE FITTING - DETAILED AND EDDY CURRENT INSPECTION

(SHEET 3 OF 4)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2 March 23, 2012 767-57A0079

31 of 38

BOEING SERVICE BULLETIN 767-57A0079

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

numbers shown below are the number of parts necessary for one side of the airplane.

Step Task Name Identification Qty More Data

to remove loose dirt,

grease and oil. Refer

to SOPM 20-30-03

as an accepted procedure.

1 Clean Outboard Hinge Fittings - 1

Do a Detailed Inspection for cracks or

fractures within the

indicated area. (a)

2 Inspect Outboard Hinge Fittings - 1

Do an Eddy Current

inspection for cracks

within the indicated

area in accordance

with 767 NDT Part

6, 51-00-01 or 767

NDT Part 6, 51-00-

19. Use a right angle

pencil probe with a

maximum drop of

0.1 inch. (a)

3 Inspect Outboard Hinge Fittings - 1

(a) On outboard hinge fitting only. Both faces on the outboard hinge fitting require inspection in the area

shown.

FIGURE 3: OUTBOARD HINGE FITTING - DETAILED AND EDDY CURRENT INSPECTION

(SHEET 4 OF 4)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2 March 23, 2012 767-57A0079

32 of 38

BOEING SERVICE BULLETIN 767-57A0079

ALERT ALERT
FIGURE 4: HINGE FITTING ASSEMBLY - REPLACEMENT

(SHEET 1 OF 6)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2 March 23, 2012 767-57A0079

33 of 38

BOEING SERVICE BULLETIN 767-57A0079

ALERT ALERT
FIGURE 4: HINGE FITTING ASSEMBLY - REPLACEMENT

(SHEET 2 OF 6)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2 March 23, 2012 767-57A0079

34 of 38

BOEING SERVICE BULLETIN 767-57A0079

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

numbers shown below are the number of parts necessary for one of the airplane.

Step Task Name Identification Qty More Data

Maintain fasteners

location and stackup

for later installation.

Refer to CMM 57-

53-27 as an accepted procedure.

1 Remove / Keep Fasteners - 4

2 Remove Fasteners - 4

3 Remove Hinge Fitting Assembly 113T2271-() 1

4 Remove / Keep Shims "A" BACS40R015D015F - (a)

Remove / Keep Shims "B" BACS40R015D017F - (a)

FIGURE 4: HINGE FITTING ASSEMBLY - REPLACEMENT

(SHEET 3 OF 6)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2 March 23, 2012 767-57A0079

35 of 38

BOEING SERVICE BULLETIN 767-57A0079

ALERT ALERT
Step Task Name Identification Qty More Data

5 Install (New) Hinge Fitting Assembly 113T2271-419 (LEFT) 1 (b)

Install (New) Hinge Fitting Assembly 113T2271-420 (RIGHT) 1 (b)

Install (Kept) Shims "A" BACS40R015D015F -

Install (Kept) Shims "B" BACS40R015D017F -

Install (New) Fasteners - 4

Install (Kept) Fasteners - 4

the incorporation of

this service bulletin

on each hinge fitting

assembly. Refer to

SOPM 20-50-10 as

an accepted procedure.

Rubber Stamp or Sten- - -

cil

6 Identify

BACB30LU3-20 OR 1

BACB30LH3-20

7 Remove / Keep Bolt "A"

BACB30LU3-13 OR 1

BACB30LH3-13

Remove / Keep Bolt "B"

BACW10BP3AP OR 2

BACW10BP3DP

Remove / Keep Washer

BACN10JC3 OR 2

BACN10JC3CD

Remove / Keep Nut

Remove / Keep Shim "C" BACS40R008A026F -

Remove / Keep Shim "D" BACS40R008E026F -

Remove / Keep Filler 113T1700-9 1

FIGURE 4: HINGE FITTING ASSEMBLY - REPLACEMENT

(SHEET 4 OF 6)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2 March 23, 2012 767-57A0079

36 of 38

BOEING SERVICE BULLETIN 767-57A0079

ALERT ALERT
Step Task Name Identification Qty More Data

8 Install (Kept) Filler 113T1700-9 1

Install (Kept) Shim "D" BACS40R008E026F -

Install (Kept) Shim "C" BACS40R008A026F -

BACB30LU3-13 OR 1

BACB30LH3-13

Install (Kept) Bolt "B"

BACB30LU3-20 OR 1

BACB30LH3-20

Install (Kept) Bolt "A"

BACW10BP3AP is

used with

BACB30LU3-() fasteners.

BACW10BP3DP is

used with

BACB30LH3-() fasteners.

BACW10BP3AP OR 2

BACW10BP3DP

Install (Kept) Washer

Tighten to 19-21

inch-pounds (20 target). BACN10JC3 is

used with

BACB30LU3-() fasteners.

BACN10JC3CD is

used with

BACB30LH3-() fasteners.

BACN10JC3 OR 2

BACN10JC3CD

Install (Kept) Nut

(a) Maintain original location of shims. If shims are damaged, replace shims maintaining the original thickness.

Apply BMS 10-11 Type I primer to the replacement shims and any bare surfaces of the original shims.

Refer to SOPM 20-41-02 as an accepted procedure.

(b) Locate and install hinge fitting with kept or identical replacement shims in the same location to maintain

the original hinge line geometry of the fitting. Refer to CMM 57-53-27 as an accepted procedure. Fay seal

shims and install fasteners wet with BMS 5-95 common to the fitting assembly and the main flap. Refer

to SOPM 20-50-19 as an accepted procedure. Install kept fasteners common to the flap linkage and hinge

fittings with MIL-G-23827 grease. Refer to CMM 57-53-27 as an accepted procedure.

FIGURE 4: HINGE FITTING ASSEMBLY - REPLACEMENT

(SHEET 5 OF 6)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2 March 23, 2012 767-57A0079

37 of 38

BOEING SERVICE BULLETIN 767-57A0079

ALERT ALERT
The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure.

A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the

number of fasteners necessary for this figure.

IDENTIFICA- QTY HOLE DIA MORE DATA

TION

CODE NAME

A Bolt BACB30LE5K * - - (a)

BACB30LE5K * - - (a)

X

Opt 1/64 Oversize

Washer BACW10BP5CD - - (a)

Opt 1/64 Over- BACW10BP51CD - - (a)

size

Washer BACW10BP5DP - - (a)

Opt 1/64 Over- BACW10BP51DP - - (a)

size

Nut NAS1805-5L - - (a)

(a) Install bolts wet with BMS 5-95 sealant. Refer to SOPM 20-50-19 as an accepted procedure.

FIGURE 4: HINGE FITTING ASSEMBLY - REPLACEMENT

(SHEET 6 OF 6)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 20, 2002

Revision 2 March 23, 2012 767-57A0079

38 of 38

BOEING SERVICE BULLETIN 767-57A0079

ALERT ALERT