Commercial

Airplanes 757

Service Bulletin

SPECIAL ATTENTION

Number: 757-57-0071

Original Issue: September 12, 2012

ATA System: 5750

SUBJECT: WINGS - Trailing Edge and Trailing Edge Devices - Inboard Flap, Inboard Track -

Forward Support Fitting Inspection and 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 © 2012 Boeing.

Unpublished Work. All Rights Reserved.

Treatment of this document and its content is governed by contract with Boeing. Rights to use this document

are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The

Boeing Company.

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BLANK PAGE
Table of Contents

Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5

1. PLANNING INFORMATION ........................................ 9

A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9

1. Airplanes ............................................. 9

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

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

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

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

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

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 24

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 27

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 28

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

FIGURE 1: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

INSPECTION [Group 1] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

FIGURE 2: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

INSPECTION [Group 2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37

FIGURE 3: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

REPLACEMENT [Group 1] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40

FIGURE 4: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

REPLACEMENT [Group 2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46

FIGURE 5: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING

ASSEMBLY INSPECTION [Group 1] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52

FIGURE 6: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING

ASSEMBLY INSPECTION [Group 2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55

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BOEING SERVICE BULLETIN 757-57-0071
FIGURE 7: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING

ASSEMBLY REPLACEMENT [Group 1] . . . . . . . . . . . . . . . . . . . . . . . . . . . 58

FIGURE 8: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING

ASSEMBLY REPLACEMENT [Group 2] . . . . . . . . . . . . . . . . . . . . . . . . . . . 64

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BOEING SERVICE BULLETIN 757-57-0071
Commercial

Airplanes 757

Service Bulletin

SPECIAL ATTENTION

Summary Number: 757-57-0071

Original Issue: September 12, 2012

ATA System: 5750

SUBJECT: WINGS - Trailing Edge and Trailing Edge Devices - Inboard Flap, Inboard Track -

Forward Support Fitting Inspection and Replacement

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

CONCURRENT REQUIREMENTS

None.

BACKGROUND

This service bulletin gives instructions to inspect and if necessary replace the forward support fitting assembly

at the inboard flap, inboard track. The forward support fitting assembly consists of two back-to-back machined

components that attach the forward end of the inboard track of the inboard flap to the Main Landing Gear (MLG)

beam. If the work in this service bulletin is not done, a broken forward support fitting could lead to loss of inboard

flap control and subsequent inability to fly the airplane safely.

One operator reported a broken forward support fitting assembly at the inboard flap, inboard track. During a

post flight taxi, the pilots noticed a FLAP TE DISAGREE message on the Engine Indication and Crew Alerting

System (EICAS). On examination, the ground maintenance personnel discovered that both components of the

forward support fitting assembly had broken causing the inboard track and transmission to drop about eight

inches into the wheel well. The incident occurred at 22,328 flight cycles and is the only reported incident of this

type.

Metallurgical analysis determined that cracks had initiated at a compound radius in each component flange

common to the MLG beam. Each crack propagated by fatigue and was followed by final ductile rupture.

Accomplishment of the work in this service bulletin will make sure that any cracked forward support fitting

assembly at the inboard flap, inboard track is found and replaced.

Boeing Service Related Problem (SRP) 757-SRP-57-0245 is related to this service bulletin.

Boeing Fleet Team Digest (FTD) 757 FTD 57-10004 is related to this service bulletin.

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

information.

Planning Data Affected Reference

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

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Planning Data Affected Reference

AD Related No Paragraph 1.E., Compliance

Weight and Balance Change No Paragraph 1.H., Weight and Balance Changes

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

Publications Affected No 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 No Paragraph 2.C.1., Kits/Parts

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

by the Operator

Operator Supplied Material Yes

Paragraph 2.F., Special Tooling Necessary to

do this Service Bulletin

Special Tooling Required No

ACTION

Get access to the inboard flap, inboard track of the left wing and the right wing. Do a High Frequency Eddy

Current (HFEC) inspection for cracking in the flanges of the forward support fitting assembly common to the

MLG beam. If any crack is found, replace the forward support fitting assembly in accordance with this service

bulletin. If no cracking is found, do repeat inspections at the interval given in Paragraph 1.E., Compliance.

EFFECTIVITY

All 757 Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s).

COMPLIANCE

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

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

mandatory.

Refer to Paragraph 1.E., Compliance.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the inspection and/or replacement given in this service bulletin.

MANPOWER

Refer to Paragraph 1.G., Manpower.

Airplanes Total Task Hours Elapsed Hours

All Groups 10.20 (a) 5.80 (a)

(a) This estimate is for inspection only.

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BOEING SERVICE BULLETIN 757-57-0071
MATERIAL INFORMATION

Operator Supplied Parts/Materials.

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

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BOEING SERVICE BULLETIN 757-57-0071

BLANK PAGE
Commercial

Airplanes 757

Service Bulletin

SPECIAL ATTENTION

Number: 757-57-0071

Original Issue: September 12, 2012

ATA System: 5750

SUBJECT: WINGS - Trailing Edge and Trailing Edge Devices - Inboard Flap, Inboard Track -

Forward Support Fitting Inspection and Replacement

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

This service bulletin is for the airplanes shown below.

Refer to Service Bulletin Index D624N001 Part 3 for Airplane Variable Number, Line Number, and

Serial Number data.

GROUP CONFIGURATION DESCRIPTION

1 - All 757-300 airplanes.

2 - All 757-200, -200CB, 200PF airplanes.

Airplane Models:

757-200, 757-200CB, 757-200PF, 757-300

Variable Number Group

NA001 - NA028 2

NA191 - NA199 2

NA201 - NA239 2

NA301 - NA305 2

NA341 - NA352 2

NA391 - NA399 2

NA401 - NA408 2

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Variable Number Group

NA441 - NA447 2

NA501 - NA586 2

NB001 - NB004 2

NB021 - NB023 2

NB036 - NB041 2

NB051 - NB053 2

NB061 - NB073 2

NB079 2

NB131 - NB148 2

NB161 - NB162 2

NB166 - NB168 2

NB201 - NB204 2

NB221 - NB228 2

NB230 2

NB236 2

NB239 2

NB261 - NB267 2

NB291 - NB299 2

NB301 - NB302 2

NB311 - NB312 2

NB321 - NB331 2

NB421 - NB438 2

NB446 2

NB451 - NB454 2

NB501 - NB523 2

NB561 2

NB571 2

NB581 - NB583 2

NC001 - NC033 2

NC041 - NC042 2

NC051 - NC052 2

NC056 - NC062 2

NC066 - NC084 2

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Variable Number Group

NC091 - NC094 2

NC151 2

NC161 2

NC901 - NC951 2

NC971 - NC974 2

ND001 - ND007 2

ND011 - ND059 2

ND111 - ND113 2

ND161 - ND199 2

ND201 - ND203 2

ND221 - ND225 2

ND241 - ND248 2

ND301 - ND322 2

ND401 2

ND891 2

ND895 2

NE001 - NE008 2

NE011 - NE088 2

NE091 - NE094 2

NE141 - NE150 2

NE161 - NE177 2

NE201 - NE204 2

NE301 - NE302 2

NE311 - NE325 2

NJ001 - NJ004 2

NJ031 - NJ032 2

NJ551 - NJ555 2

NL001 - NL002 1

NL006 - NL017 1

NL101 - NL109 1

NL141 1

NL601 - NL616 1

NN001 - NN002 2

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Variable Number Group

NN051 - NN052 2

NP901 - NP904 2

NS601 - NS616 2

NT001 - NT009 2

NT201 - NT202 2

NT231 - NT234 2

NT237 - NT240 2

NT242 2

NT245 - NT248 2

NT281 - NT289 2

NT341 - NT347 2

NT351 - NT360 2

NT371 - NT373 2

NT375 - NT379 2

NT381 - NT386 2

NT401 - NT409 2

NT411 - NT412 2

NT426 - NT427 2

NT431 - NT432 2

NT436 - NT438 2

NT441 - NT442 2

NT446 2

NT701 - NT769 2

NT791 - NT796 2

NT861 - NT862 2

NT881 - NT885 2

NT901 - NT916 2

NT971 - NT985 2

NU031 - NU038 2

NU701 - NU705 1

NU721 - NU728 1

NU731 - NU732 1

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BOEING SERVICE BULLETIN 757-57-0071
2. Spares Affected

None.

B. Concurrent Requirements

None.

C. Reason

This service bulletin gives instructions to inspect and if necessary replace the forward support fitting

assembly at the inboard flap, inboard track. The forward support fitting assembly consists of two

back-to-back machined components that attach the forward end of the inboard track of the inboard flap

to the Main Landing Gear (MLG) beam. If the work in this service bulletin is not done, a broken forward

support fitting could lead to loss of inboard flap control and subsequent inability to fly the airplane safely.

One operator reported a broken forward support fitting assembly at the inboard flap, inboard track.

During a post flight taxi, the pilots noticed a FLAP TE DISAGREE message on the Engine Indication

and Crew Alerting System (EICAS). On examination, the ground maintenance personnel discovered

that both components of the forward support fitting assembly had broken causing the inboard track

and transmission to drop about eight inches into the wheel well. The incident occurred at 22,328 flight

cycles and is the only reported incident of this type.

Metallurgical analysis determined that cracks had initiated at a compound radius in each component

flange common to the MLG beam. Each crack propagated by fatigue and was followed by final ductile

rupture.

Accomplishment of the work in this service bulletin will make sure that any cracked forward support

fitting assembly at the inboard flap, inboard track is found and replaced.

Boeing Service Related Problem (SRP) 757-SRP-57-0245 is related to this service bulletin.

Boeing Fleet Team Digest (FTD) 757 FTD 57-10004 is related to this service bulletin.

D. Description

Get access to the inboard flap, inboard track of the left wing and the right wing. Do a High Frequency

Eddy Current (HFEC) inspection for cracking in the flanges of the forward support fitting assembly

common to the MLG beam. If any crack is found, replace the forward support fitting assembly in

accordance with this service bulletin. If no cracking is found, do repeat inspections at the interval given

in Paragraph 1.E., Compliance.

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

Group 1:

Affected Maintenance Zones

Model Zone

757-300 143, 144

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Group 2:

Affected Maintenance Zones

Model Zone

757-200, 757-200CB, 757- 143, 144

200PF

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.

Group 1:

Table 1: Left Wing - Inboard Flap, Inboard Track - Forward Support Fitting Assembly Inspection and

Replacement

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs First)

Condition Action

6,000 flight cycles.

(a)

Before 15,000 -

total flight cycles.

Do a High Frequency Eddy Current (HFEC) inspection for cracking in the

forward support fitting assembly of the left wing inboard flap, inboard track

in accordance with Accomplishment Instructions paragraph

3.B.2.a.(1)

Airplanes with less than

12,000 total flight cycles at

the original issue date of

this service bulletin and

(1) have not replaced the

forward support fitting assembly on the left wing

OR

(2) have replaced the forward support fitting assembly on the left wing but the

forward support fitting assembly flight cycles are

unknown.

6,000 flight cycles.

(a)

Within 36

months from the

original issue

date of this service bulletin.

Within 3,000

flight cycles

from the original

issue date of

this service bulletin.

Do a HFEC inspection for

cracking in the forward

support fitting assembly

of the left wing inboard

flap, inboard track in accordance with Accomplishment Instructions

paragraph 3.B.2.a.(1)

Airplanes with 12,000 or

more total flight cycles at

the original issue date of

this service bulletin and

(1) have not replaced the

forward support fitting assembly on the left wing

OR

(2) have replaced the forward support fitting assembly on the left wing but the

forward support fitting assembly flight cycles are

unknown.

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Group 1:

Table 1: Left Wing - Inboard Flap, Inboard Track - Forward Support Fitting Assembly Inspection and

Replacement

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs First)

Condition Action

6,000 flight cycles.

(a)

Within 48

months from the

original issue

date of this service bulletin.

Within 15,000

flight cycles

from the replacement of the left

wing forward

support fitting

assembly.

Do a HFEC inspection for

cracking in the forward

support fitting assembly

of the left wing inboard

flap, inboard track in accordance with Accomplishment Instructions

paragraph 3.B.2.a.(1)

Airplanes that have replaced the forward support

fitting assembly on the left

wing and the forward support fitting assembly flight

cycles are less than 12,000

at the original issue date of

this service bulletin.

6,000 flight cycles.

(a)

Within 36

months from the

original issue

date of this service bulletin.

Within 3,000

flight cycles

from the original

issue date of

this service bulletin.

Do a HFEC inspection for

cracking in the forward

support fitting assembly

of the left wing inboard

flap, inboard track in accordance with Accomplishment Instructions

paragraph 3.B.2.a.(1)

Airplanes that have replaced the forward support

fitting assembly on the left

wing and the forward support fitting assembly flight

cycles are 12,000 or more

at the original issue date of

this service bulletin.

6,000 flight cycles.

(a)

Within 15,000 -

flight cycles

from the replacement of the forward support fitting assembly

on the left wing.

Do a HFEC inspection for

cracking in the forward

support fitting assembly

of the left wing inboard

flap, inboard track in accordance with the Accomplishment Instructions

Paragraph 3.B.2.a.(1).

Airplanes that have replaced the forward support

fitting assembly on the left

wing as a result of any inspection accomplished by

this service bulletin.

Before further - -

flight.

Replace the forward support fitting assembly at

the left wing inboard flap,

inboard track in accordance with Accomplishment Instructions paragraph 3.B.2.a.(1)(a).

Any crack found in the left

wing forward support fitting

assembly.

(a) Replacement of the forward support fitting assembly at the left wing inboard flap, inboard track in accordance with Accomplishment Instructions paragraph 3.B.2.a.(1)(a) terminates the 6,000 flight cycle repeat

inspections for the fitting that was removed. After the replacement of the forward support fitting assembly,

refer to the applicable description in the Condition column for the appropriate compliance time and repeat

inspections.

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BOEING SERVICE BULLETIN 757-57-0071
Group 1:

Table 2: Right Wing - Inboard Flap, Inboard Track - Forward Support Fitting Assembly Inspection and

Replacement

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs First)

Condition Action

6,000 flight cycles.

(a)

Before 15,000 -

total flight cycles.

Do a High Frequency Eddy Current (HFEC) inspection for cracking in the

forward support fitting assembly of the right wing

inboard flap, inboard

track in accordance with

Accomplishment Instructions paragraph

3.B.2.a.(2).

Airplanes with less than

12,000 total flight cycles at

the original issue date of

this service bulletin and

(1) have not replaced the

forward support fitting assembly on the right wing

OR

(2) have replaced the forward support fitting assembly on the right wing but the

forward support fitting assembly flight cycles are

unknown.

6,000 flight cycles.

(a)

Within 36

months from the

original issue

date of this service bulletin.

Within 3,000

flight cycles

from the original

issue date of

this service bulletin.

Do a HFEC inspection for

cracking in the forward

support fitting assembly

of the right wing inboard

flap, inboard track in accordance with Accomplishment Instructions

paragraph 3.B.2.a.(2).

Airplanes with 12,000 or

more total flight cycles at

the original issue date of

this service bulletin and

(1) have not replaced the

forward support fitting assembly on the right wing

OR

(2) have replaced the forward support fitting assembly on the right wing but the

forward support fitting assembly flight cycles are

unknown.

6,000 flight cycles.

(a)

Within 48

months from the

original issue

date of this service bulletin.

Within 15,000

flight cycles

from the replacement of the right

wing forward

support fitting

assembly.

Do a HFEC inspection for

cracking in the forward

support fitting assembly

of the right wing inboard

flap, inboard track in accordance with Accomplishment Instructions

paragraph 3.B.2.a.(2).

Airplanes that have replaced the forward support

fitting assembly on the right

wing and the forward support fitting assembly flight

cycles are less than 12,000

at the original issue date of

this service bulletin.

6,000 flight cycles.

(a)

Within 36

months from the

original issue

date of this service bulletin.

Within 3,000

flight cycles

from the original

issue date of

this service bulletin.

Do a HFEC inspection for

cracking in the forward

support fitting assembly

of the right wing inboard

flap, inboard track in accordance with Accomplishment Instructions

paragraph 3.B.2.a.(2).

Airplanes that have replaced the forward support

fitting assembly on the right

wing and the forward support fitting assembly flight

cycles are 12,000 or more

at the original issue date of

this service bulletin.

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BOEING SERVICE BULLETIN 757-57-0071
Group 1:

Table 2: Right Wing - Inboard Flap, Inboard Track - Forward Support Fitting Assembly Inspection and

Replacement

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs First)

Condition Action

6,000 flight cycles.

(a)

Within 15,000 -

flight cycles

from the replacement of the forward support fitting assembly

on the right

wing.

Do a HFEC inspection for

cracking in the forward

support fitting assembly

of the right wing inboard

flap, inboard track in accordance with the Accomplishment Instructions

Paragraph 3.B.2.a.(2).

Airplanes that have replaced the forward support

fitting assembly on the right

wing as a result of any inspection accomplished by

this service bulletin.

Before further - -

flight.

Replace the forward support fitting assembly at

the right wing inboard

flap, inboard track in accordance with Accomplishment Instructions

paragraph 3.B.2.a.(2)(a).

Any crack found in the right

wing forward support fitting

assembly.

(a) Replacement of the forward support fitting assembly at the right wing inboard flap, inboard track in accordance with Accomplishment Instructions paragraph 3.B.2.a.(2)(a) terminates the 6,000 flight cycle repeat

inspections for the fitting that was removed. After the replacement of the forward support fitting assembly,

refer to the applicable description in the Condition column for the appropriate compliance time and repeat

inspections.

Group 2:

Table 3: Left Wing - Inboard Flap, Inboard Track - Forward Support Fitting Assembly Inspection and

Replacement

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs First)

Condition Action

6,000 flight cycles.

(a)

Before 18,000 -

total flight cycles.

Do a High Frequency Eddy Current (HFEC) inspection for cracking in the

forward support fitting assembly of the left wing inboard flap, inboard track

in accordance with Accomplishment Instructions paragraph

3.B.2.b.(1)

Airplanes with less than

15,000 total flight cycles at

the original issue date of

this service bulletin and

(1) have not replaced the

forward support fitting assembly on the left wing

OR

(2) have replaced the forward support fitting assembly on the left wing but the

forward support fitting assembly flight cycles are

unknown.

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BOEING SERVICE BULLETIN 757-57-0071
Group 2:

Table 3: Left Wing - Inboard Flap, Inboard Track - Forward Support Fitting Assembly Inspection and

Replacement

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs First)

Condition Action

6,000 flight cycles.

(a)

Within 36

months from the

original issue

date of this service bulletin.

Within 3,000

flight cycles

from the original

issue date of

this service bulletin.

Do a HFEC inspection for

cracking in the forward

support fitting assembly

of the left wing inboard

flap, inboard track in accordance with Accomplishment Instructions

paragraph 3.B.2.b.(1)

Airplanes with 15,000 or

more total flight cycles and

30,000 or less total flight

cycles at the original issue

date of this service bulletin

and

(1) have not replaced the

forward support fitting assembly on the left wing

OR

(2) have replaced the forward support fitting assembly on the left wing but the

forward support fitting assembly flight cycles are

unknown.

6,000 flight cycles.

(a)

Within 12

months from the

original issue

date of this service bulletin.

Within 1,000

flight cycles

from the original

issue date of

this service bulletin.

Do a HFEC inspection for

cracking in the forward

support fitting assembly

of the left wing inboard

flap, inboard track in accordance with Accomplishment Instructions

paragraph 3.B.2.b.(1)

Airplanes with more than

30,000 total flight cycles at

the original issue date of

this service bulletin and

(1) have not replaced the

forward support fitting assembly on the left wing

OR

(2) have replaced the forward support fitting assembly on the left wing but the

forward support fitting assembly flight cycles are

unknown.

6,000 flight cycles.

(a)

Within 48

months from the

original issue

date of this service bulletin.

Within 18,000

flight cycles

from the replacement of the left

wing forward

support fitting

assembly.

Do a HFEC inspection for

cracking in the forward

support fitting assembly

of the left wing inboard

flap, inboard track in accordance with Accomplishment Instructions

paragraph 3.B.2.b.(1)

Airplanes that have replaced the forward support

fitting assembly on the left

wing and the forward support fitting assembly flight

cycles are less than 15,000

at the original issue date of

this service bulletin.

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BOEING SERVICE BULLETIN 757-57-0071
Group 2:

Table 3: Left Wing - Inboard Flap, Inboard Track - Forward Support Fitting Assembly Inspection and

Replacement

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs First)

Condition Action

6,000 flight cycles.

(a)

Within 36

months from the

original issue

date of this service bulletin.

Within 3,000

flight cycles

from the original

issue date of

this service bulletin.

Do a HFEC inspection for

cracking in the forward

support fitting assembly

of the left wing inboard

flap, inboard track in accordance with Accomplishment Instructions

paragraph 3.B.2.b.(1)

Airplanes that have replaced the forward support

fitting assembly on the left

wing and the forward support fitting assembly flight

cycles are 15,000 or more

and 30,000 or less at the

original issue date of this

service bulletin.

6,000 flight cycles.

(a)

Within 12

months from the

original issue

date of this service bulletin.

Within 1,000

flight cycles

from the original

issue date of

this service bulletin.

Do a HFEC inspection for

cracking in the forward

support fitting assembly

of the left wing inboard

flap, inboard track in accordance with Accomplishment Instructions

paragraph 3.B.2.b.(1)

Airplanes that have replaced the forward support

fitting assembly on the left

wing and the forward support fitting assembly flight

cycles are more than

30,000 at the original issue

date of this service bulletin.

6,000 flight cycles.

(a)

Within 18,000 -

flight cycles

from the replacement of the forward support fitting assembly

on the left wing.

Do a HFEC inspection for

cracking in the forward

support fitting assembly

of the left wing inboard

flap, inboard track in accordance with the Accomplishment Instructions

Paragraph 3.B.2.b.(1).

Airplanes that have replaced the forward support

fitting assembly on the left

wing as a result of any inspection accomplished by

this service bulletin.

Before further - -

flight.

Replace the forward support fitting assembly at

the left wing inboard flap,

inboard track in accordance with Accomplishment Instructions paragraph 3.B.2.b.(1)(a).

Any crack found in the left

wing forward support fitting

assembly.

(a) Replacement of the forward support fitting assembly at the left wing inboard flap, inboard track in accordance with Accomplishment Instructions paragraph 3.B.2.b.(1)(a) terminates the 6,000 flight cycle repeat

inspections for the fitting that was removed. After the replacement of the forward support fitting assembly,

refer to the applicable description in the Condition column for the appropriate compliance time and repeat

inspections.

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BOEING SERVICE BULLETIN 757-57-0071
Group 2:

Table 4: Right Wing - Inboard Flap, Inboard Track - Forward Support Fitting Assembly Inspection and

Replacement

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs First)

Condition Action

6,000 flight cycles.

(a)

Before 18,000 -

total flight cycles.

Do a High Frequency Eddy Current (HFEC) inspection for cracking in the

forward support fitting assembly of the right wing

inboard flap, inboard

track in accordance with

Accomplishment Instructions paragraph

3.B.2.b.(2).

Airplanes with less than

15,000 total flight cycles at

the original issue date of

this service bulletin and

(1) have not replaced the

forward support fitting assembly on the right wing

OR

(2) have replaced the forward support fitting assembly on the right wing but the

forward support fitting assembly flight cycles are

unknown.

6,000 flight cycles.

(a)

Within 36

months from the

original issue

date of this service bulletin.

Within 3,000

flight cycles

from the original

issue date of

this service bulletin.

Do a HFEC inspection for

cracking in the forward

support fitting assembly

of the right wing inboard

flap, inboard track in accordance with Accomplishment Instructions

paragraph 3.B.2.b.(2).

Airplanes with 15,000 or

more total flight cycles and

30,000 or less total flight

cycles at the original issue

date of this service bulletin

and

(1) have not replaced the

forward support fitting assembly on the right wing

OR

(2) have replaced the forward support fitting assembly on the right wing but the

forward support fitting assembly flight cycles are

unknown.

6,000 flight cycles.

(a)

Within 12

months from the

original issue

date of this service bulletin.

Within 1,000

flight cycles

from the original

issue date of

this service bulletin.

Do a HFEC inspection for

cracking in the forward

support fitting assembly

of the right wing inboard

flap, inboard track in accordance with Accomplishment Instructions

paragraph 3.B.2.b.(2).

Airplanes with more than

30,000 total flight cycles at

the original issue date of

this service bulletin and

(1) have not replaced the

forward support fitting assembly on the right wing

OR

(2) have replaced the forward support fitting assembly on the right wing but the

forward support fitting assembly flight cycles are

unknown.

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BOEING SERVICE BULLETIN 757-57-0071
Group 2:

Table 4: Right Wing - Inboard Flap, Inboard Track - Forward Support Fitting Assembly Inspection and

Replacement

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs First)

Condition Action

6,000 flight cycles.

(a)

Within 48

months from the

original issue

date of this service bulletin.

Within 18,000

flight cycles

from the replacement of the right

wing forward

support fitting

assembly.

Do a HFEC inspection for

cracking in the forward

support fitting assembly

of the right wing inboard

flap, inboard track in accordance with Accomplishment Instructions

paragraph 3.B.2.b.(2).

Airplanes that have replaced the forward support

fitting assembly on the right

wing and the forward support fitting assembly flight

cycles are less than 15,000

at the original issue date of

this service bulletin.

6,000 flight cycles.

(a)

Within 36

months from the

original issue

date of this service bulletin.

Within 3,000

flight cycles

from the original

issue date of

this service bulletin.

Do a HFEC inspection for

cracking in the forward

support fitting assembly

of the right wing inboard

flap, inboard track in accordance with Accomplishment Instructions

paragraph 3.B.2.b.(2).

Airplanes that have replaced the forward support

fitting assembly on the right

wing and the forward support fitting assembly flight

cycles are 15,000 or more

and 30,000 or less at the

original issue date of this

service bulletin.

6,000 flight cycles.

(a)

Within 12

months from the

original issue

date of this service bulletin.

Within 1,000

flight cycles

from the original

issue date of

this service bulletin.

Do a HFEC inspection for

cracking in the forward

support fitting assembly

of the right wing inboard

flap, inboard track in accordance with Accomplishment Instructions

paragraph 3.B.2.b.(2).

Airplanes that have replaced the forward support

fitting assembly on the right

wing and the forward support fitting assembly flight

cycles are more than

30,000 at the original issue

date of this service bulletin.

6,000 flight cycles.

(a)

Within 18,000 -

flight cycles

from the replacement of the forward support fitting assembly

on the right

wing.

Do a HFEC inspection for

cracking in the forward

support fitting assembly

of the right wing inboard

flap, inboard track in accordance with the Accomplishment Instructions

Paragraph 3.B.2.b.(2).

Airplanes that have replaced the forward support

fitting assembly on the right

wing as a result of any inspection accomplished by

this service bulletin.

Before further - -

flight.

Replace the forward support fitting assembly at

the right wing inboard

flap, inboard track in accordance with Accomplishment Instructions

paragraph 3.B.2.b.(2)(a).

Any crack found in the right

wing forward support fitting

assembly.

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BOEING SERVICE BULLETIN 757-57-0071
Group 2:

Table 4: Right Wing - Inboard Flap, Inboard Track - Forward Support Fitting Assembly Inspection and

Replacement

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs First)

Condition Action

(a) Replacement of the forward support fitting assembly at the right wing inboard flap, inboard track in accordance with Accomplishment Instructions paragraph 3.B.2.b.(2)(a) terminates the 6,000 flight cycle repeat

inspections for the fitting that was removed. After the replacement of the forward support fitting assembly,

refer to the applicable description in the Condition column for the appropriate compliance time and repeat

inspections.

F. Approval

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

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

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

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

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

changes.

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

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

before incorporating this service bulletin.

G. Manpower

The table below shows an estimate of the task hours necessary to do this service bulletin for each side

of the 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 inspect the work

• Time to cure the materials

• Time to make the parts

• Time to find the tools.

Group 1:

LEFT WING

Task Number of Persons Task Hours Elapsed Hours

Open Access and 2 2.20 1.10

Preparation

FIGURE 1 1 0.70 0.70

FIGURE 3 1 2.25 2.25

Close Access and 2 2.20 1.10

Restoration

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BOEING SERVICE BULLETIN 757-57-0071
Group 1:

LEFT WING

Task Number of Persons Task Hours Elapsed Hours

TOTAL - INSPECTION ONLY, LEFT WING 5.10 2.90

TOTAL - INSPECTION AND REPLACE- 7.35 5.15

MENT, LEFT WING

Group 1:

RIGHT WING

Task Number of Persons Task Hours Elapsed Hours

Open Access and 2 2.20 1.10

Preparation

FIGURE 5 1 0.70 0.70

FIGURE 7 1 2.25 2.25

Close Access and 2 2.20 1.10

Restoration

TOTAL - INSPECTION ONLY, RIGHT WING 5.10 2.90

TOTAL - INSPECTION AND REPLACE- 7.35 5.15

MENT, RIGHT WING

Group 2:

LEFT WING

Task Number of Persons Task Hours Elapsed Hours

Open Access and 2 2.20 1.10

Preparation

FIGURE 2 1 0.70 0.70

FIGURE 4 1 2.10 2.10

Close Access and 2 2.20 1.10

Restoration

TOTAL - INSPECTION ONLY, LEFT WING 5.10 2.90

TOTAL - INSPECTION AND REPLACE- 7.20 5.00

MENT, LEFT WING

Group 2:

RIGHT WING

Task Number of Persons Task Hours Elapsed Hours

Open Access and 2 2.20 1.10

Preparation

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BOEING SERVICE BULLETIN 757-57-0071
Group 2:

RIGHT WING

Task Number of Persons Task Hours Elapsed Hours

FIGURE 6 1 0.70 0.70

FIGURE 8 1 2.10 2.10

Close Access and 2 2.20 1.10

Restoration

TOTAL - INSPECTION ONLY, RIGHT WING 5.10 2.90

TOTAL - INSPECTION AND REPLACE- 7.20 5.00

MENT, RIGHT WING

H. Weight and Balance Changes

None.

I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. Boeing Service Related Problem (SRP) 757-SRP-57-0245.

b. Service Bulletin Index D624N001.

c. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-41-02, 20-43-03, 20-50-19.

d. 757 Aircraft Maintenance Manual (AMM) 27-51-02, 27-51-03, 29-11-00, 32-00-15, 32-00-20.

e. 757 Fleet Team Digest (FTD) 57-10004.

f. 757 Non-Destructive Testing (NDT) Manual Part 6, 51-00-01, Part 6, 51-00-19.

2. Data Supplied with this Service Bulletin:

None.

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

Drawing Number Title

113N1201 Support Instl - Inbd Track, Inbd Main Flap

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.

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BOEING SERVICE BULLETIN 757-57-0071
K. Publications Affected

1. Publications:

None.

2. Damage Tolerance Based Structural Inspections:

Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue

Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the

Maintenance Program. This service bulletin affects FCS. DTI requirements for the structure affected

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

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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BOEING SERVICE BULLETIN 757-57-0071

BLANK PAGE
2. MATERIAL INFORMATION

A. Material - Price and Availability

The operator can supply the parts and materials shown in Paragraph 2.C., Parts Necessary for Each

Airplane. As an alternative, operators can purchase the parts from Boeing Spares. This service bulletin

does not show the Boeing price and supply data.

B. Industry Support Information

Boeing warranty remedies are not available for the inspection and replacement procedures given in

this service bulletin.

C. Parts Necessary for Each Airplane

1. Kits/Parts

None.

2. Parts and Materials Supplied by the Operator

Group 1:

Part Number / Speci- QTY Name Notes

fication

113N1242-7 1 Fwd Support Fitting Assy Left wing. (a)

113N1242-8 1 Fwd Support Fitting Assy Right wing. (a)

BACB30US5K19 12 Bolt (b)

BACN10HR5CS 12 Nut (b)

BACW10BP5APU 12 Washer (b)

BACW10BP5CD 12 Washer (b)

TYPE 2, CLASS A 2 Oz Chemical Conversion Coating (c)

BMS 10-11, TYPE I 2 Oz Primer (d)

BMS 5-95, TYPE 1, 2 Oz Sealant (d)

CLASS B-1/2

BMS 3-33 3 Oz Grease (d)

(a) Required only if the forward support fitting assembly is cracked.

(b) Required only if the removed part is unserviceable or is different to the one required for

installation in accordance with this service bulletin.

(c) Refer to SOPM 20-43-03 for material sources.

(d) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS)

for supplier data.

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BOEING SERVICE BULLETIN 757-57-0071
Group 2:

Part Number / Speci- QTY Name Notes

fication

654N0244-697 1 Fwd Support Fitting Assy Left wing. (a)

654N0244-698 1 Fwd Support Fitting Assy Right wing. (a)

BACB30US5K19 12 Bolt (b)

BACN10HR5CS 12 Nut (b)

BACW10BP5APU 12 Washer (b)

BACW10BP5CD 12 Washer (b)

TYPE 2, CLASS A 2 Oz Chemical Conversion Coating (c)

BMS 10-11, TYPE I 2 Oz Primer (d)

BMS 5-95, TYPE 1, 2 Oz Sealant (d)

CLASS B-1/2

BMS 3-33 3 Oz Grease (d)

(a) Required only if the forward support fitting assembly is cracked.

(b) Required only if the removed part is unserviceable or is different to the one required for

installation in accordance with this service bulletin.

(c) Refer to SOPM 20-43-03 for material sources.

(d) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS)

for supplier data.

3. Parts Modified and Reidentified

None.

4. Parts Removed and Not Replaced

None.

D. Parts Necessary to Change Spares

None.

E. Special Tooling - Price and Availability

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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BOEING SERVICE BULLETIN 757-57-0071
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

– 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. 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.

7. Boeing Service Letter 757-SL-51-022, 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.

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.

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.

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BOEING SERVICE BULLETIN 757-57-0071
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. Shaded areas in Figures are reference only. Shaded areas in Figures may look

different than your airplane.

B. WORK INSTRUCTIONS

1. ACCESS AND PREPARATION

a. Put the flaps in the fully down position and install a DO-NOT-OPERATE tag on the flap control

lever.

b. Make sure the main and nose gear downlocks are installed on the nose and Main Landing

Gear (MLG). Refer to 757 AMM 32-00-20 as an accepted procedure.

c. Open the doors for the landing gear and install the door locks. Refer to 757 AMM 32-00-15

as an accepted procedure.

d. Remove the power from the left hydraulic system. Refer to 757 AMM 29-11-00 as an accepted

procedure.

e. Open the following circuit breakers and install safety tags:

Main Power Distribution Panel, P6

Row Column Number Name

D 20 C03014 ALTN SLAT PWR

D 23 C00323 ALTN FLAP PWR

Overhead Circuit Breaker Panel, P11

Row Column Number Name

B 18 C00566 WARN ELEX B

D 31 C04054 HYDRAULICS PTU CONT

H 10 C01022 FLAP LOAD RELIEF

H 23 C04212 FLAP/SLAT ALTN DR ARM

J 33 C00565 WARN ELEX A

f. Install a trailing edge flap power drive lock on the trailing edge flap Power Drive Unit (PDU).

Refer to 757 AMM 27-51-03 as an accepted procedure.

2. FORWARD SUPPORT FITTING ASSEMBLY INSPECTION AND REPLACEMENT

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BOEING SERVICE BULLETIN 757-57-0071
a. Group 1:

(1) Do a High Frequency Eddy Current (HFEC) inspection for cracking in the forward support

fitting assembly of the left wing inboard flap, inboard track in accordance with FIGURE

1.

(a) If any crack is found, do the following:

1) Support the left wing inboard flap. Refer to 757 AMM 27-51-02 as an accepted

procedure.

2) Replace the forward support fitting assembly at the left wing inboard flap, inboard

track in accordance with FIGURE 3.

3) Remove the support equipment from the left wing inboard flap. Refer to 757

AMM 27-51-02 as an accepted procedure.

4) Do repeat inspections at the interval given in Paragraph 1.E., Compliance.

(b) If no cracking is found, do repeat inspections at the interval given in Paragraph 1.E.,

Compliance.

(2) Do a HFEC inspection for cracking in the forward support fitting assembly of the right

wing inboard flap, inboard track in accordance with FIGURE 5.

(a) If any crack is found, do the following:

1) Support the right wing inboard flap. Refer to 757 AMM 27-51-02 as an accepted

procedure.

2) Replace the forward support fitting assembly at the right wing inboard flap,

inboard track in accordance with FIGURE 7.

3) Remove the support equipment from the right wing inboard flap. Refer to 757

AMM 27-51-02 as an accepted procedure.

4) Do repeat inspections at the interval given in Paragraph 1.E., Compliance.

(b) If no cracking is found, do repeat inspections at the interval given in Paragraph 1.E.,

Compliance.

b. Group 2:

(1) Do a High Frequency Eddy Current (HFEC) inspection for cracking in the forward support

fitting assembly of the left wing inboard flap, inboard track in accordance with FIGURE

2.

(a) If any crack is found, do the following:

1) Support the left wing inboard flap. Refer to 757 AMM 27-51-02 as an accepted

procedure.

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BOEING SERVICE BULLETIN 757-57-0071
2) Replace the forward support fitting assembly at the left wing inboard flap, inboard

track in accordance with FIGURE 4.

3) Remove the support equipment from the left wing inboard flap. Refer to 757

AMM 27-51-02 as an accepted procedure.

4) Do repeat inspections at the interval given in Paragraph 1.E., Compliance.

(b) If no cracking is found, do repeat inspections at the interval given in Paragraph 1.E.,

Compliance.

(2) Do a HFEC inspection for cracking in the forward support fitting assembly of the right

wing inboard flap, inboard track in accordance with FIGURE 6.

(a) If any crack is found, do the following:

1) Support the right wing inboard flap. Refer to 757 AMM 27-51-02 as an accepted

procedure.

2) Replace the forward support fitting assembly at the right wing inboard flap,

inboard track in accordance with FIGURE 8.

3) Remove the support equipment from the right wing inboard flap. Refer to 757

AMM 27-51-02 as an accepted procedure.

4) Do repeat inspections at the interval given in Paragraph 1.E., Compliance.

(b) If no cracking is found, do repeat inspections at the interval given in Paragraph 1.E.,

Compliance.

3. CLOSE ACCESS AND RESTORATION

a. Remove the trailing edge flap power drive lock from the trailing edge flap PDU. Refer to 757

AMM 27-51-03 as an accepted procedure.

b. Remove safety tags and close the following circuit breakers:

Main Power Distribution Panel, P6

Row Column Number Name

D 20 C03014 ALTN SLAT PWR

D 23 C00323 ALTN FLAP PWR

Overhead Circuit Breaker Panel, P11

Row Column Number Name

B 18 C00566 WARN ELEX B

D 31 C04054 HYDRAULICS PTU CONT

H 10 C01022 FLAP LOAD RELIEF

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BOEING SERVICE BULLETIN 757-57-0071
Overhead Circuit Breaker Panel, P11

Row Column Number Name

H 23 C04212 FLAP/SLAT ALTN DR ARM

J 33 C00565 WARN ELEX A

c. Restore power to the left hydraulic system. Refer to 757 AMM 29-11-00 as an accepted

procedure.

d. Remove the door locks and close the doors for the landing gear. Refer to 757 AMM 32-00-15

as an accepted procedure.

e. Remove the main and nose gear downlocks from the nose and MLG. Refer to 757 AMM

32-00-20 as an accepted procedure.

f. Retract the flaps to the fully up position.

g. Put the airplane back to a serviceable condition.

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BOEING SERVICE BULLETIN 757-57-0071
This Figure applies only to: Group 1.

FIGURE 1: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

INSPECTION

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 757-57-0071
FIGURE 1: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

INSPECTION

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 757-57-0071
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

1 Inspect Fwd Support Fitting Assy - 1 (a)

(a) Do a High Frequency Eddy Current (HFEC) inspection for cracking in the forward support fitting assembly

in accordance with 757 NDT Part 6, 51-00-01 or 757 NDT Part 6, 51-00-19.

FIGURE 1: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

INSPECTION

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 757-57-0071
This Figure applies only to: Group 2.

FIGURE 2: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

INSPECTION

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 757-57-0071
FIGURE 2: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

INSPECTION

(SHEET 2 OF 3)

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38 of 69

BOEING SERVICE BULLETIN 757-57-0071
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

1 Inspect Fwd Support Fitting Assy - 1 (a)

(a) Do a High Frequency Eddy Current (HFEC) inspection for cracking in the forward support fitting assembly

in accordance with 757 NDT Part 6, 51-00-01 or 757 NDT Part 6, 51-00-19.

FIGURE 2: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

INSPECTION

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 757-57-0071
This Figure applies only to: Group 1.

FIGURE 3: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

REPLACEMENT

(SHEET 1 OF 6)

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BOEING SERVICE BULLETIN 757-57-0071
FIGURE 3: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

REPLACEMENT

(SHEET 2 OF 6)

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41 of 69

BOEING SERVICE BULLETIN 757-57-0071
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

1 Remove / Keep Nut - 1 -

Remove / Keep Bolt - 1 -

Remove / Keep Washer - 1 -

Remove / Keep Bolt Retainer - 2 -

2 Remove / Keep Nut - 1 -

Remove / Keep Bolt - 1 -

Remove / Keep Washer - 2 -

3 Remove / Keep Bushing BACB28AK08-064 1 -

4 Remove / Keep Bolt - 6 -

Remove / Keep Nut - 6 -

Remove / Keep Washer - 12 -

Fwd Support Fitting As- - 1 -

sy

5 Remove

6 Inspect Hole - 5 (a)

7 Inspect Hole - 1 (b)

8 Drill / Ream Hole - 5 (c) (d)

9 Drill / Ream Hole - 1 (c) (e)

Main Landing Gear - - (f)

Beam

10 Clean

BMS 5-95, TYPE 1, - (g)

CLASS B-1/2

11 Apply Sealant

Fwd Support Fitting As- 113N1242-7 1 -

sy

12 Install (New)

(h) Refer to the fastener table.13 Install (New) Fastener - 5

Refer to the fastener

table.

14 Torque Nut - 5

BMS 5-95, TYPE 1, - (i)

CLASS B-1/2

Apply Sealant

(h) Refer to the fastener table.15 Install (New) Fastener - 1

FIGURE 3: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

REPLACEMENT

(SHEET 3 OF 6)

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BOEING SERVICE BULLETIN 757-57-0071
Step Task Name Identification Qty More Data

Refer to the fastener

table.

16 Torque Nut - 1

BMS 5-95, TYPE 1, - (i)

CLASS B-1/2

Apply Sealant

17 Install (Kept) Bushing BACB28AK08-064 1 (j)

18 Install (Kept) Bolt - 1 (k)

One under the bolt

head and one under

the nut.

Install (Kept) Washer - 2

Install (Kept) Nut - 1 Finger tight.

Torque the nut to

375 - 450 in-lb.

19 Torque Nut - 1

20 Install (Kept) Bolt Retainer - 2 -

Install (Kept) Bolt - 1 -

Install (Kept) Washer - 1 -

Install (Kept) Nut - 1 -

(a) Inspect the holes in the main landing gear beam to make sure that they are round and undamaged. For

any hole which is distorted or damaged, ream that hole in 1/64 inch increments until it is round and undamaged. Maximum diameter is 0.354 inches. Minimum edge margin is 0.530

(b) Inspect the holes in the main landing gear beam to make sure that they are round and undamaged. For

any hole which is distorted or damaged, ream that hole in 1/64 inch increments until it is round and undamaged. Maximum diameter is 0.316 inches. Minimum edge margin is 0.530 inches

(c) Locate and hold the new forward support fitting assembly where the old one was located.

(d) Match-drill holes in the forward support fitting assembly through the existing holes in the Main Landing

Gear (MLG) beam. Maximum hole diameter is 0.354 inches. Minimum edge margin in forward support

fitting assembly is 0.470 inches. Break sharp edges.

(e) Match-drill hole in the forward support fitting assembly through the existing hole in the MLG beam. Maximum

hole diameter is 0.316 inches. Minimum edge margin in forward support fitting assembly is 0.470 inches.

Break sharp edges.

(f) Clean the mating surface of the MLG beam. Refer to SOPM 20-30-03 as an accepted procedure.

(g) Apply a fay seal to the mating surfaces of the forward support fitting and the MLG beam. Refer to SOPM

20-50-19 as an accepted procedure.

(h) Install wet with BMS 5-95, Type 1, Class B-1/2 sealant. Refer to SOPM 20-50-19 as an accepted procedure.

(i) Fillet seal the nuts with BMS 5-95, Type 1, Class B-1/2 sealant. Refer to SOPM 20-50-19 as an accepted

procedure.

(j) Install the bushing with BMS 3-33 grease. Apply the grease on the outside diameter and inside diameter

of the bushing.

FIGURE 3: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

REPLACEMENT

(SHEET 4 OF 6)

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BOEING SERVICE BULLETIN 757-57-0071
Step Task Name Identification Qty More Data

(k) Install the bolt with BMS 3-33 grease. Apply the grease on the outside diameter of the bolt. Remove excess

grease from the threads prior to nut installation.

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.

Code Name Identification Qty Hole Dia More Data

A Bolt BACB30US4K19 1 0.250 - 0.254 (a) (b)

(a) Torque the nut to 90 -

125 in-lb.

Nut BACN10HR4CS 1 -

Washer BACW10BP4APU 1 - (a) Install under the nut.

(a) Install under the bolt

head.

Washer BACW10BP4CD 1 -

A (Optional) Bolt BACB30US5K19 1 0.312 - 0.316 (a) (c)

(a) Torque the nut to 180

- 250 in-lb.

Nut BACN10HR5CS 1 -

Washer BACW10BP5APU 1 - (a) Install under the nut.

(a) Install under the bolt

head.

Washer BACW10BP5CD 1 -

FIGURE 3: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

REPLACEMENT

(SHEET 5 OF 6)

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BOEING SERVICE BULLETIN 757-57-0071
Code Name Identification Qty Hole Dia More Data

B Bolt BACB30US4K19 5 0.279 - .291 (a) (b)

(a) Torque the nut to 90 -

125 in-lb.

Nut BACN10HR4CS 5 -

Washer BACW10BP4APU 5 - (a) Install under the nut.

(a) Install under the bolt

head.

Washer BACW10BP4CD 5 -

B (Optional) Bolt BACB30US5K19 5 0.342 - 0.354 (a) (c)

(a) Torque the nut to 180

- 250 in-lb.

Nut BACN10HR5CS 5 -

Washer BACW10BP5APU 5 - (a) Install under the nut.

(a) Install under the bolt

head.

Washer BACW10BP5CD 5 -

(a) It is acceptable to install serviceable parts that were previously removed if they meet the requirements in

this table.

(b) For the hole sizes that are between the final diameter shown, ream to the appropriate oversize hole as

required. Refer to 757-300 SRM 51-40-05 as an accepted procedure. Use oversize bolt BACB30US4K19X

or BACB30US4K19Y as required.

(c) For the hole sizes that are between the final diameter shown, ream to the appropriate oversize hole as

required. Refer to 757-300 SRM 51-40-05 as an accepted procedure. Use oversize bolt BACB30US5K19X

or BACB30US5K19Y as required.

FIGURE 3: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

REPLACEMENT

(SHEET 6 OF 6)

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BOEING SERVICE BULLETIN 757-57-0071
This Figure applies only to: Group 2.

FIGURE 4: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

REPLACEMENT

(SHEET 1 OF 6)

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BOEING SERVICE BULLETIN 757-57-0071
FIGURE 4: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

REPLACEMENT

(SHEET 2 OF 6)

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47 of 69

BOEING SERVICE BULLETIN 757-57-0071
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

1 Remove / Keep Nut - 1 -

Remove / Keep Bolt - 1 -

Remove / Keep Washer - 1 -

Remove / Keep Bolt Retainer - 2 -

2 Remove / Keep Nut - 1 -

Remove / Keep Bolt - 1 -

Remove / Keep Washer - 2 -

3 Remove / Keep Bushing BACB28AK08-064 1 -

4 Remove / Keep Bolt - 6 -

Remove / Keep Nut - 6 -

Remove / Keep Washer - 12 -

Fwd Support Fitting As- - 1 -

sy

5 Remove

6 Inspect Hole - 5 (a)

7 Inspect Hole - 1 (b)

8 Drill / Ream Hole - 5 (c) (d)

9 Drill / Ream Hole - 1 (c) (e)

Main Landing Gear - - (f)

Beam

10 Clean

BMS 5-95, TYPE 1, - (g)

CLASS B-1/2

11 Apply Sealant

Fwd Support Fitting As- 654N0244-697 1 -

sy

12 Install (New)

(h) Refer to the fastener table.13 Install (New) Fastener - 5

Refer to the fastener

table.

14 Torque Nut - 5

BMS 5-95, TYPE 1, - (i)

CLASS B-1/2

Apply Sealant

(h) Refer to the fastener table.15 Install (New) Fastener - 1

FIGURE 4: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

REPLACEMENT

(SHEET 3 OF 6)

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BOEING SERVICE BULLETIN 757-57-0071
Step Task Name Identification Qty More Data

Refer to the fastener

table.

16 Torque Nut - 1

BMS 5-95, TYPE 1, - (i)

CLASS B-1/2

Apply Sealant

17 Install (Kept) Bushing BACB28AK08-064 1 (j)

18 Install (Kept) Bolt - 1 (k)

One under the bolt

head and one under

the nut.

Install (Kept) Washer - 2

Install (Kept) Nut - 1 Finger tight.

Torque the nut to

375 - 450 in-lb.

19 Torque Nut - 1

20 Install (Kept) Bolt Retainer - 2 -

Install (Kept) Bolt - 1 -

Install (Kept) Washer - 1 -

Install (Kept) Nut - 1 -

(a) Inspect the holes in the main landing gear beam to make sure that they are round and undamaged. For

any hole which is distorted or damaged, ream that hole in 1/64 inch increments until it is round and undamaged. Maximum diameter is 0.354 inches. Minimum edge margin is 0.530

(b) Inspect the holes in the main landing gear beam to make sure that they are round and undamaged. For

any hole which is distorted or damaged, ream that hole in 1/64 inch increments until it is round and undamaged. Maximum diameter is 0.316 inches. Minimum edge margin is 0.530 inches

(c) Locate and hold the new forward support fitting assembly where the old one was located.

(d) Match-drill holes in the forward support fitting assembly through the existing holes in the Main Landing

Gear (MLG) beam. Maximum hole diameter is 0.354 inches. Minimum edge margin in forward support

fitting assembly is 0.470 inches. Break sharp edges.

(e) Match-drill hole in the forward support fitting assembly through the existing hole in the MLG beam. Maximum

hole diameter is 0.316 inches. Minimum edge margin in forward support fitting assembly is 0.470 inches.

Break sharp edges.

(f) Clean the mating surface of the MLG beam. Refer to SOPM 20-30-03 as an accepted procedure.

(g) Apply a fay seal to the mating surfaces of the forward support fitting and the MLG beam. Refer to SOPM

20-50-19 as an accepted procedure.

(h) Install wet with BMS 5-95, Type 1, Class B-1/2 sealant. Refer to SOPM 20-50-19 as an accepted procedure.

(i) Fillet seal the nuts with BMS 5-95, Type 1, Class B-1/2 sealant. Refer to SOPM 20-50-19 as an accepted

procedure.

(j) Install the bushing with BMS 3-33 grease. Apply the grease on the outside diameter and inside diameter

of the bushing.

FIGURE 4: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

REPLACEMENT

(SHEET 4 OF 6)

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BOEING SERVICE BULLETIN 757-57-0071
Step Task Name Identification Qty More Data

(k) Install the bolt with BMS 3-33 grease. Apply the grease on the outside diameter of the bolt. Remove excess

grease from the threads prior to nut installation.

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.

Code Name Identification Qty Hole Dia More Data

A Bolt BACB30US4K19 1 0.250 - 0.254 (a) (b)

(a) Torque the nut to 90 -

125 in-lb.

Nut BACN10HR4CS 1 -

Washer BACW10BP4APU 1 - (a) Install under the nut.

(a) Install under the bolt

head.

Washer BACW10BP4CD 1 -

A (Optional) Bolt BACB30US5K19 1 0.312 - 0.316 (a) (c)

(a) Torque the nut to 180

- 250 in-lb.

Nut BACN10HR5CS 1 -

Washer BACW10BP5APU 1 - (a) Install under the nut.

(a) Install under the bolt

head.

Washer BACW10BP5CD 1 -

FIGURE 4: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

REPLACEMENT

(SHEET 5 OF 6)

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BOEING SERVICE BULLETIN 757-57-0071
Code Name Identification Qty Hole Dia More Data

B Bolt BACB30US4K19 5 0.279 - .291 (a) (b)

(a) Torque the nut to 90 -

125 in-lb.

Nut BACN10HR4CS 5 -

Washer BACW10BP4APU 5 - (a) Install under the nut.

(a) Install under the bolt

head.

Washer BACW10BP4CD 5 -

B (Optional) Bolt BACB30US5K19 5 0.342 - 0.354 (a) (c)

(a) Torque the nut to 180

- 250 in-lb.

Nut BACN10HR5CS 5 -

Washer BACW10BP5APU 5 - (a) Install under the nut.

(a) Install under the bolt

head.

Washer BACW10BP5CD 5 -

(a) It is acceptable to install serviceable parts that were previously removed if they meet the requirements in

this table.

(b) For the hole sizes that are between the final diameter shown, ream to the appropriate oversize hole as

required. Refer to 757-300 SRM 51-40-05 as an accepted procedure. Use oversize bolt BACB30US4K19X

or BACB30US4K19Y as required.

(c) For the hole sizes that are between the final diameter shown, ream to the appropriate oversize hole as

required. Refer to 757-300 SRM 51-40-05 as an accepted procedure. Use oversize bolt BACB30US5K19X

or BACB30US5K19Y as required.

FIGURE 4: LEFT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

REPLACEMENT

(SHEET 6 OF 6)

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BOEING SERVICE BULLETIN 757-57-0071
This Figure applies only to: Group 1.

FIGURE 5: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

INSPECTION

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 757-57-0071
FIGURE 5: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

INSPECTION

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 757-57-0071
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

1 Inspect Fwd Support Fitting Assy - 1 (a)

(a) Do a High Frequency Eddy Current (HFEC) inspection for cracking in the forward support fitting assembly

in accordance with 757 NDT Part 6, 51-00-01 or 757 NDT Part 6, 51-00-19.

FIGURE 5: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

INSPECTION

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 757-57-0071
This Figure applies only to: Group 2.

FIGURE 6: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

INSPECTION

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 757-57-0071
FIGURE 6: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

INSPECTION

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 757-57-0071
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

1 Inspect Fwd Support Fitting Assy - 1 (a)

(a) Do a High Frequency Eddy Current (HFEC) inspection for cracking in the forward support fitting assembly

in accordance with 757 NDT Part 6, 51-00-01 or 757 NDT Part 6, 51-00-19.

FIGURE 6: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

INSPECTION

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 757-57-0071
This Figure applies only to: Group 1.

FIGURE 7: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

REPLACEMENT

(SHEET 1 OF 6)

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BOEING SERVICE BULLETIN 757-57-0071
FIGURE 7: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

REPLACEMENT

(SHEET 2 OF 6)

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BOEING SERVICE BULLETIN 757-57-0071
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

1 Remove / Keep Nut - 1 -

Remove / Keep Bolt - 1 -

Remove / Keep Washer - 1 -

Remove / Keep Bolt Retainer - 2 -

2 Remove / Keep Nut - 1 -

Remove / Keep Bolt - 1 -

Remove / Keep Washer - 2 -

3 Remove / Keep Bushing BACB28AK08-064 1 -

4 Remove / Keep Bolt - 6 -

Remove / Keep Nut - 6 -

Remove / Keep Washer - 12 -

Fwd Support Fitting As- - 1 -

sy

5 Remove

6 Inspect Hole - 5 (a)

7 Inspect Hole - 1 (b)

8 Drill / Ream Hole - 5 (c) (d)

9 Drill / Ream Hole - 1 (c) (e)

Main Landing Gear - - (f)

Beam

10 Clean

BMS 5-95, TYPE 1, - (g)

CLASS B-1/2

11 Apply Sealant

Fwd Support Fitting As- 113N1242-8 1 -

sy

12 Install (New)

(h) Refer to the fastener table.13 Install (New) Fastener - 5

Refer to the fastener

table.

14 Torque Nut - 5

BMS 5-95, TYPE 1, - (i)

CLASS B-1/2

Apply Sealant

(h) Refer to the fastener table.15 Install (New) Fastener - 1

FIGURE 7: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

REPLACEMENT

(SHEET 3 OF 6)

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BOEING SERVICE BULLETIN 757-57-0071
Step Task Name Identification Qty More Data

Refer to the fastener

table.

16 Torque Nut - 1

BMS 5-95, TYPE 1, - (i)

CLASS B-1/2

Apply Sealant

17 Install (Kept) Bushing BACB28AK08-064 1 (j)

18 Install (Kept) Bolt - 1 (k)

One under the bolt

head and one under

the nut.

Install (Kept) Washer - 2

Install (Kept) Nut - 1 Finger tight.

Torque the nut to

375 - 450 in-lb.

19 Torque Nut - 1

20 Install (Kept) Bolt Retainer - 2 -

Install (Kept) Bolt - 1 -

Install (Kept) Washer - 1 -

Install (Kept) Nut - 1 -

(a) Inspect the holes in the main landing gear beam to make sure that they are round and undamaged. For

any hole which is distorted or damaged, ream that hole in 1/64 inch increments until it is round and undamaged. Maximum diameter is 0.354 inches. Minimum edge margin is 0.530

(b) Inspect the holes in the main landing gear beam to make sure that they are round and undamaged. For

any hole which is distorted or damaged, ream that hole in 1/64 inch increments until it is round and undamaged. Maximum diameter is 0.316 inches. Minimum edge margin is 0.530 inches

(c) Locate and hold the new forward support fitting assembly where the old one was located.

(d) Match-drill holes in the forward support fitting assembly through the existing holes in the Main Landing

Gear (MLG) beam. Maximum hole diameter is 0.354 inches. Minimum edge margin in forward support

fitting assembly is 0.470 inches. Break sharp edges.

(e) Match-drill hole in the forward support fitting assembly through the existing hole in the MLG beam. Maximum

hole diameter is 0.316 inches. Minimum edge margin in forward support fitting assembly is 0.470 inches.

Break sharp edges.

(f) Clean the mating surface of the MLG beam. Refer to SOPM 20-30-03 as an accepted procedure.

(g) Apply a fay seal to the mating surfaces of the forward support fitting and the MLG beam. Refer to SOPM

20-50-19 as an accepted procedure.

(h) Install wet with BMS 5-95, Type 1, Class B-1/2 sealant. Refer to SOPM 20-50-19 as an accepted procedure.

(i) Fillet seal the nuts with BMS 5-95, Type 1, Class B-1/2 sealant. Refer to SOPM 20-50-19 as an accepted

procedure.

(j) Install the bushing with BMS 3-33 grease. Apply the grease on the outside diameter and inside diameter

of the bushing.

FIGURE 7: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

REPLACEMENT

(SHEET 4 OF 6)

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BOEING SERVICE BULLETIN 757-57-0071
Step Task Name Identification Qty More Data

(k) Install the bolt with BMS 3-33 grease. Apply the grease on the outside diameter of the bolt. Remove excess

grease from the threads prior to nut installation.

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.

Code Name Identification Qty Hole Dia More Data

A Bolt BACB30US4K19 1 0.250 - 0.254 (a) (b)

(a) Torque the nut to 90 -

125 in-lb.

Nut BACN10HR4CS 1 -

Washer BACW10BP4APU 1 - (a) Install under the nut.

(a) Install under the bolt

head.

Washer BACW10BP4CD 1 -

A (Optional) Bolt BACB30US5K19 1 0.312 - 0.316 (a) (c)

(a) Torque the nut to 180

- 250 in-lb.

Nut BACN10HR5CS 1 -

Washer BACW10BP5APU 1 - (a) Install under the nut.

(a) Install under the bolt

head.

Washer BACW10BP5CD 1 -

FIGURE 7: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

REPLACEMENT

(SHEET 5 OF 6)

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BOEING SERVICE BULLETIN 757-57-0071
Code Name Identification Qty Hole Dia More Data

B Bolt BACB30US4K19 5 0.279 - .291 (a) (b)

(a) Torque the nut to 90 -

125 in-lb.

Nut BACN10HR4CS 5 -

Washer BACW10BP4APU 5 - (a) Install under the nut.

(a) Install under the bolt

head.

Washer BACW10BP4CD 5 -

B (Optional) Bolt BACB30US5K19 5 0.342 - 0.354 (a) (c)

(a) Torque the nut to 180

- 250 in-lb.

Nut BACN10HR5CS 5 -

Washer BACW10BP5APU 5 - (a) Install under the nut.

(a) Install under the bolt

head.

Washer BACW10BP5CD 5 -

(a) It is acceptable to install serviceable parts that were previously removed if they meet the requirements in

this table.

(b) For the hole sizes that are between the final diameter shown, ream to the appropriate oversize hole as

required. Refer to 757-300 SRM 51-40-05 as an accepted procedure. Use oversize bolt BACB30US4K19X

or BACB30US4K19Y as required.

(c) For the hole sizes that are between the final diameter shown, ream to the appropriate oversize hole as

required. Refer to 757-300 SRM 51-40-05 as an accepted procedure. Use oversize bolt BACB30US5K19X

or BACB30US5K19Y as required.

FIGURE 7: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

REPLACEMENT

(SHEET 6 OF 6)

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BOEING SERVICE BULLETIN 757-57-0071
This Figure applies only to: Group 2.

FIGURE 8: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

REPLACEMENT

(SHEET 1 OF 6)

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BOEING SERVICE BULLETIN 757-57-0071
FIGURE 8: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

REPLACEMENT

(SHEET 2 OF 6)

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65 of 69

BOEING SERVICE BULLETIN 757-57-0071
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

1 Remove / Keep Nut - 1 -

Remove / Keep Bolt - 1 -

Remove / Keep Washer - 1 -

Remove / Keep Bolt Retainer - 2 -

2 Remove / Keep Nut - 1 -

Remove / Keep Bolt - 1 -

Remove / Keep Washer - 2 -

3 Remove / Keep Bushing BACB28AK08-064 1 -

4 Remove / Keep Bolt - 6 -

Remove / Keep Nut - 6 -

Remove / Keep Washer - 12 -

Fwd Support Fitting As- - 1 -

sy

5 Remove

6 Inspect Hole - 5 (a)

7 Inspect Hole - 1 (b)

8 Drill / Ream Hole - 5 (c) (d)

9 Drill / Ream Hole - 1 (c) (e)

Main Landing Gear - - (f)

Beam

10 Clean

BMS 5-95, TYPE 1, - (g)

CLASS B-1/2

11 Apply Sealant

Fwd Support Fitting As- 654N0244-698 1 -

sy

12 Install (New)

(h) Refer to the fastener table.13 Install (New) Fastener - 5

Refer to the fastener

table.

14 Torque Nut - 5

BMS 5-95, TYPE 1, - (i)

CLASS B-1/2

Apply Sealant

(h) Refer to the fastener table.15 Install (New) Fastener - 1

FIGURE 8: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

REPLACEMENT

(SHEET 3 OF 6)

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BOEING SERVICE BULLETIN 757-57-0071
Step Task Name Identification Qty More Data

Refer to the fastener

table.

16 Torque Nut - 1

BMS 5-95, TYPE 1, - (i)

CLASS B-1/2

Apply Sealant

17 Install (Kept) Bushing BACB28AK08-064 1 (j)

18 Install (Kept) Bolt - 1 (k)

One under the bolt

head and one under

the nut.

Install (Kept) Washer - 2

Install (Kept) Nut - 1 Finger tight.

Torque the nut to

375 - 450 in-lb.

19 Torque Nut - 1

20 Install (Kept) Bolt Retainer - 2 -

Install (Kept) Bolt - 1 -

Install (Kept) Washer - 1 -

Install (Kept) Nut - 1 -

(a) Inspect the holes in the main landing gear beam to make sure that they are round and undamaged. For

any hole which is distorted or damaged, ream that hole in 1/64 inch increments until it is round and undamaged. Maximum diameter is 0.354 inches. Minimum edge margin is 0.530

(b) Inspect the holes in the main landing gear beam to make sure that they are round and undamaged. For

any hole which is distorted or damaged, ream that hole in 1/64 inch increments until it is round and undamaged. Maximum diameter is 0.316 inches. Minimum edge margin is 0.530 inches

(c) Locate and hold the new forward support fitting assembly where the old one was located.

(d) Match-drill holes in the forward support fitting assembly through the existing holes in the Main Landing

Gear (MLG) beam. Maximum hole diameter is 0.354 inches. Minimum edge margin in forward support

fitting assembly is 0.470 inches. Break sharp edges.

(e) Match-drill hole in the forward support fitting assembly through the existing hole in the MLG beam. Maximum

hole diameter is 0.316 inches. Minimum edge margin in forward support fitting assembly is 0.470 inches.

Break sharp edges.

(f) Clean the mating surface of the MLG beam. Refer to SOPM 20-30-03 as an accepted procedure.

(g) Apply a fay seal to the mating surfaces of the forward support fitting and the MLG beam. Refer to SOPM

20-50-19 as an accepted procedure.

(h) Install wet with BMS 5-95, Type 1, Class B-1/2 sealant. Refer to SOPM 20-50-19 as an accepted procedure.

(i) Fillet seal the nuts with BMS 5-95, Type 1, Class B-1/2 sealant. Refer to SOPM 20-50-19 as an accepted

procedure.

(j) Install the bushing with BMS 3-33 grease. Apply the grease on the outside diameter and inside diameter

of the bushing.

FIGURE 8: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

REPLACEMENT

(SHEET 4 OF 6)

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BOEING SERVICE BULLETIN 757-57-0071
Step Task Name Identification Qty More Data

(k) Install the bolt with BMS 3-33 grease. Apply the grease on the outside diameter of the bolt. Remove excess

grease from the threads prior to nut installation.

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.

Code Name Identification Qty Hole Dia More Data

A Bolt BACB30US4K19 1 0.250 - 0.254 (a) (b)

(a) Torque the nut to 90 -

125 in-lb.

Nut BACN10HR4CS 1 -

Washer BACW10BP4APU 1 - (a) Install under the nut.

(a) Install under the bolt

head.

Washer BACW10BP4CD 1 -

A (Optional) Bolt BACB30US5K19 1 0.312 - 0.316 (a) (c)

(a) Torque the nut to 180

- 250 in-lb.

Nut BACN10HR5CS 1 -

Washer BACW10BP5APU 1 - (a) Install under the nut.

(a) Install under the bolt

head.

Washer BACW10BP5CD 1 -

FIGURE 8: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

REPLACEMENT

(SHEET 5 OF 6)

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BOEING SERVICE BULLETIN 757-57-0071
Code Name Identification Qty Hole Dia More Data

B Bolt BACB30US4K19 5 0.279 - .291 (a) (b)

(a) Torque the nut to 90 -

125 in-lb.

Nut BACN10HR4CS 5 -

Washer BACW10BP4APU 5 - (a) Install under the nut.

(a) Install under the bolt

head.

Washer BACW10BP4CD 5 -

B (Optional) Bolt BACB30US5K19 5 0.342 - 0.354 (a) (c)

(a) Torque the nut to 180

- 250 in-lb.

Nut BACN10HR5CS 5 -

Washer BACW10BP5APU 5 - (a) Install under the nut.

(a) Install under the bolt

head.

Washer BACW10BP5CD 5 -

(a) It is acceptable to install serviceable parts that were previously removed if they meet the requirements in

this table.

(b) For the hole sizes that are between the final diameter shown, ream to the appropriate oversize hole as

required. Refer to 757-300 SRM 51-40-05 as an accepted procedure. Use oversize bolt BACB30US4K19X

or BACB30US4K19Y as required.

(c) For the hole sizes that are between the final diameter shown, ream to the appropriate oversize hole as

required. Refer to 757-300 SRM 51-40-05 as an accepted procedure. Use oversize bolt BACB30US5K19X

or BACB30US5K19Y as required.

FIGURE 8: RIGHT WING - INBOARD FLAP, INBOARD TRACK - FORWARD SUPPORT FITTING ASSEMBLY

REPLACEMENT

(SHEET 6 OF 6)

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BOEING SERVICE BULLETIN 757-57-0071