Commercial 

Airplanes 757

Service Bulletin

SPECIAL ATTENTION

Number: 757-57-0066

Original Issue: April 05, 2011

ATA System: 5740

SUBJECT: WINGS - Leading Edge and Leading Edge Devices - Slat Trailing Edge Wedge

Inspection

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

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Copyright © 2011 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Unpublished Work - All Rights Reserved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,

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7.0
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BOEING SERVICE BULLETIN 757-57-0066

BLANK PAGE
Table of Contents

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

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

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

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

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

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

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

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

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

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

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

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

1. Existing Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

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 . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 19

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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

FIGURE 1: INSPECTION OF LEFT WING LEADING EDGE SLAT TRAILING EDGE WEDGES . . . 23

FIGURE 2: INSPECTION OF RIGHT WING LEADING EDGE SLAT TRAILING EDGE WEDGES . . . 26

APPENDIX A: DETERMINATION OF LEADING EDGE SLAT TRAILING EDGE WEDGE TYPE . . . . . 29

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Commercial 

Airplanes 757

Service Bulletin

SPECIAL ATTENTION

Summary Number: 757-57-0066

Original Issue: April 05, 2011

ATA System: 5740

SUBJECT: WINGS - Leading Edge and Leading Edge Devices - Slat Trailing Edge Wedge

Inspection

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

CONCURRENT REQUIREMENTS

None.

BACKGROUND

This service bulletin gives instructions for the inspection, monitoring, repair and replacement of disbonded leading

edge slat trailing edge wedges. Failure to repair this damage could result in the loss of a trailing edge wedge

during flight, with subsequent damage to the fuselage and empennage and reduced controllability of the airplane.

The leading edge slat trailing edge wedges may disbond on 757-200 airplanes. This condition was originally

addressed for certain airplanes by Service Bulletin 757-57A0038. However, there have been several operators

who have reported wedge skin-to-core disbonds after completion of the terminating action specified in Service

Bulletin 757-57A0038. Inspection of the submitted damaged wedges indicated that the panels had been

contaminated with moisture ingression as there was evidence of aluminum oxide powder on the core and the

adhesive had failed at the skin-to-core bondline. It is suspected that there was incomplete removal of moisture

and honeycomb core corrosion during the repair of the wedges or that moisture had previously migrated into

the panel and was subsequently sealed in during accomplishment of Service Bulletin 757-57A0038. There have

also been reports of wedge skin-to-core disbonds on airplanes not in the effectivity of Service Bulletin

757-57A0038.

One operator reported major skin-to-core disbonding of a wedge after the airplane had accumulated 42,603

total flight hours and 9,808 total flight cycles. Another operator reported the departure of a wedge during flight

after the airplane had accumulated 47,470 total flight hours and 17,579 total flight cycles.

This service bulletin supersedes Boeing Service Bulletins 757-57A0038, 757-57A0045 and 757-57A0063 which

give instructions to inspect and repair or replace leading edge slat trailing edge wedges on airplanes up to line

number 348.

Boeing Service Related Problem (SRP) 757-SRP-57-0192 is related to this service bulletin.

ACTION

Do an ultrasonic (preferred) or tap test inspection on all applicable leading edge slat trailing edge wedges to

search for areas of skin-to-core disbonding. Monitor, repair or replace all disbonded parts according to the

location and size of the disbond. Do the inspections again at the time given in Paragraph 1.E., Compliance

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EFFECTIVITY

All 757-200,-200CB,-200PF airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes.

COMPLIANCE

Federal Aviation Administration (FAA) Airworthiness Directives 90-23-06, 91-22-51 and 2005-07-08 are related

to this service bulletin.

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 repair procedures given in this service

bulletin.

MANPOWER

Total Task Hours Elapsed Hours

20.00 10.00

MATERIAL INFORMATION

None.

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BLANK PAGE
Commercial 

Airplanes 757

Service Bulletin

SPECIAL ATTENTION

Number: 757-57-0066

Original Issue: April 05, 2011

ATA System: 5740

SUBJECT: WINGS - Leading Edge and Leading Edge Devices - Slat Trailing Edge Wedge

Inspection

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.

GROUP CONFIGURATION DESCRIPTION

1 - All 757-200,-200CB,-200PF series airplanes.

Airplane Models:

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

Variable Number Group

NA001 - NA028 1

NA191 - NA199 1

NA201 - NA239 1

NA301 - NA305 1

NA341 - NA352 1

NA391 - NA399 1

NA401 - NA408 1

NA441 - NA447 1

NA501 - NA586 1

NB001 - NB004 1

NB021 - NB023 1

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Variable Number Group

NB036 - NB041 1

NB051 - NB053 1

NB061 - NB073 1

NB079 1

NB131 - NB148 1

NB161 - NB162 1

NB166 - NB168 1

NB201 - NB204 1

NB221 - NB228 1

NB230 1

NB236 1

NB239 1

NB261 - NB267 1

NB291 - NB299 1

NB301 - NB302 1

NB311 - NB312 1

NB321 - NB331 1

NB421 - NB438 1

NB446 1

NB451 - NB454 1

NB501 - NB523 1

NB561 1

NB571 1

NB581 - NB583 1

NC001 - NC033 1

NC041 - NC042 1

NC051 - NC052 1

NC056 - NC062 1

NC066 - NC084 1

NC091 - NC094 1

NC151 1

NC161 1

NC901 - NC951 1

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BOEING SERVICE BULLETIN 757-57-0066
Variable Number Group

NC971 - NC974 1

ND001 - ND007 1

ND011 - ND059 1

ND111 - ND113 1

ND161 - ND199 1

ND201 - ND203 1

ND221 - ND225 1

ND241 - ND248 1

ND301 - ND322 1

ND401 1

ND891 1

ND895 1

NE001 - NE008 1

NE011 - NE088 1

NE091 - NE094 1

NE141 - NE150 1

NE161 - NE177 1

NE201 - NE204 1

NE301 - NE302 1

NE311 - NE325 1

NJ001 - NJ004 1

NJ031 - NJ032 1

NJ551 - NJ555 1

NN001 - NN002 1

NN051 - NN052 1

NP901 - NP904 1

NS601 - NS616 1

NT001 - NT009 1

NT201 - NT202 1

NT231 - NT234 1

NT237 - NT240 1

NT242 1

NT245 - NT248 1

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BOEING SERVICE BULLETIN 757-57-0066
Variable Number Group

NT281 - NT289 1

NT341 - NT347 1

NT351 - NT360 1

NT371 - NT373 1

NT375 - NT379 1

NT381 - NT386 1

NT401 - NT409 1

NT411 - NT412 1

NT426 - NT427 1

NT431 - NT432 1

NT436 - NT438 1

NT441 - NT442 1

NT446 1

NT701 - NT769 1

NT791 - NT796 1

NT861 - NT862 1

NT881 - NT885 1

NT901 - NT916 1

NT971 - NT985 1

NU031 - NU038 1

2. Spares Affected

Examine your spares supply for the parts identified in APPENDIX A. If any part is found, the work

given in this service bulletin will become necessary if the part is installed on an airplane.

B. Concurrent Requirements

None.

C. Reason

This service bulletin gives instructions for the inspection, monitoring, repair and replacement of disbonded

leading edge slat trailing edge wedges. Failure to repair this damage could result in the loss of a trailing

edge wedge during flight, with subsequent damage to the fuselage and empennage and reduced

controllability of the airplane.

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BOEING SERVICE BULLETIN 757-57-0066
The leading edge slat trailing edge wedges may disbond on 757-200 airplanes. This condition was

originally addressed for certain airplanes by Service Bulletin 757-57A0038. However, there have been

several operators who have reported wedge skin-to-core disbonds after completion of the terminating

action specified in Service Bulletin 757-57A0038. Inspection of the submitted damaged wedges indicated

that the panels had been contaminated with moisture ingression as there was evidence of aluminum

oxide powder on the core and the adhesive had failed at the skin-to-core bondline. It is suspected that

there was incomplete removal of moisture and honeycomb core corrosion during the repair of the

wedges or that moisture had previously migrated into the panel and was subsequently sealed in during

accomplishment of Service Bulletin 757-57A0038. There have also been reports of wedge skin-to-core

disbonds on airplanes not in the effectivity of Service Bulletin 757-57A0038.

One operator reported major skin-to-core disbonding of a wedge after the airplane had accumulated

42,603 total flight hours and 9,808 total flight cycles. Another operator reported the departure of a

wedge during flight after the airplane had accumulated 47,470 total flight hours and 17,579 total flight

cycles.

This service bulletin supersedes Boeing Service Bulletins 757-57A0038, 757-57A0045 and 757-57A0063

which give instructions to inspect and repair or replace leading edge slat trailing edge wedges on

airplanes up to line number 348.

Boeing Service Related Problem (SRP) 757-SRP-57-0192 is related to this service bulletin.

D. Description

Do an ultrasonic (preferred) or tap test inspection on all applicable leading edge slat trailing edge

wedges to search for areas of skin-to-core disbonding. Monitor, repair or replace all disbonded parts

according to the location and size of the disbond. Do the inspections again at the time given in Paragraph

1.E., Compliance.

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

Affected Maintenance Zones

Model Zone

757-200, 757-200CB, 757- 512, 522, 523, 524, 525, 612, 622, 623, 624, 625

200PF

E. Compliance

Federal Aviation Administration (FAA) Airworthiness Directives 90-23-06, 91-22-51 and 2005-07-08

are related to this service bulletin.

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

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

service bulletin mandatory.

Boeing recommends that the inspections given in this Service Bulletin are done according to Table 1.

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BOEING SERVICE BULLETIN 757-57-0066
Table 1: Inspection and repair/replacement of leading edge slat trailing edge wedges

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs First)

Condition Action

Within 24 -

months after

the original issue date of this

service bulletin

Within 3000

flight cycles after the original

issue date of

this service

bulletin

For each leading edge slat

trailing edge wedge, check

maintenance records or do

an inspection of the slat

wedge to determine the assembly number in accordance with Work Instructions, Paragraph 3.B.1.

All airplanes

For each Type B leading No action is required - -

edge slat trailing edge

wedge (a)

3000 flight cycles

or 24 months,

whichever occurs

first (b)

Within 24

months after

the original issue date of this

service bulletin

Within 3000

flight cycles after the original

issue date of

this service

bulletin

Do an ultrasonic (preferred)

or tap test inspection of the

wedge for disbonds in accordance with Work Instructions, Paragraph 3.B.2.

For each Type A leading

edge slat trailing edge

wedge (a)

Within 3000 flight cycles after -

this condition was found

Repair the disbond or replace the wedge in accordance with Work Instructions, Paragraph 3.B.2.a.(1)

For each disbond that is less

than or equal to 1.50 inches

in maximum dimension AND

is located more than or equal

to 1.0 inch from the edge of

the panel AND is located

more than or equal to 4

times the disbond maximum

dimension, measured edge

to edge, from adjacent damage.

600 flight cycles

(c)

Within 600 flight cycles after this

condition was found (c)

Repeat the ultrasonic (preferred) or tap test inspection

of the disbond area or repaired area in accordance

with Work Instructions,

Paragraph 3.B.2.

Contact Boeing for instruc- Before further flight -

tions and do the work instructed by Boeing or replace the wedge in accordance with Work Instructions, Paragraph 3.B.2.b.(1)

For each disbond that is

more than 1.50 inches in

maximum dimension or is

located less than 1.0 inch

from the edge of the panel

or is located less than 4

times the disbond maximum

dimension, measured edge

to edge, from adjacent damage.

(a) Refer to APPENDIX A for determination of wedge type.

(b) Inspection of a Type A wedge is terminated when the wedge is replaced with a Type B wedge.

(c) Repair of a disbond on a Type A wedge does not terminate inspections of the repaired area. Inspections

of the disbond area or the repaired area are terminated when the Type A wedge is replaced with a Type

B wedge.

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BOEING SERVICE BULLETIN 757-57-0066
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.

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

and investigative and corrective actions, at the times specified Table 1, of SB 757-57-0066, at each

applicable slat location, as an AMOC to the inspections, and investigative and corrective actions required

by paragraphs (a), (b), (c), and (d) of AD 90-23-06. All provisions of AD 90-23-06 that are not specifically

referenced above remain fully applicable and must be complied with accordingly.

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

and investigative and corrective actions, at the times specified in Table 1, of SB 757-57-0066, at each

applicable slat location, as an AMOC to the inspections, and investigative and corrective actions required

by paragraphs (a), (b), and (c) of AD 91-22-51. All provisions of AD AD 91-22-51 that are not specifically

referenced above remain fully applicable and must be complied with accordingly.

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

and investigative and corrective actions, at the times specified in Table 1 of SB 757-57-0066, at each

applicable slat location, as an AMOC to the inspections, and investigative and corrective actions required

by paragraphs (f) and (g) of AD 2005-07-08. All provisions of AD 2005-07-08 that are not specifically

referenced above remain fully applicable and must be complied with accordingly.

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 inspection and

repair/replacement for each leading edge slat trailing edge wedge. 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.

Number of Per- Task Hours (a) Elapsed Hours

sons

Task

FIGURE 1 2 10.00 (b) 5.00

FIGURE 2 2 10.00 (b) 5.00

TOTAL FOR EACH AIRPLANE 20.00 10.00

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BOEING SERVICE BULLETIN 757-57-0066
Number of Per- Task Hours (a) Elapsed Hours

sons

Task

(a) The task hours given assume that all trailing edge wedges are Type A and

require inspection.

(b) The task hours given assume that the ultrasonic inspection method is used.

H. Weight and Balance Changes

None.

I. Electrical Load Data

Not changed.

J. References

1. Existing Data

a. Boeing Service Bulletin 757-57A0038, 757-57A0045, 757-57A0063

b. Boeing Service Related Problem (SRP) 757-SRP-57-0192

c. Federal Aviation Administration (FAA) Airworthiness Directive 2005-07-08, 90-23-06, 91-22-51

d. 757 Non-Destructive Testing (NDT) Manual PART 1, 51-05-01, PART 4, 57-40-01

e. 757-200 Structural Repair Manual (SRM) 51-70-10

f. 757-200CB Structural Repair Manual (SRM) 51-70-10

g. 757-200PF Structural Repair Manual (SRM) 51-70-10

2. Data supplied with this Service Bulletin

None.

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

None.

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 does not affect FCS, therefore DTIs are not necessary.

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BOEING SERVICE BULLETIN 757-57-0066
L. Interchangeability and Intermixability of Parts

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

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BLANK PAGE
2. MATERIAL INFORMATION

A. Material - Price and Availability

None.

B. Industry Support Information

Boeing warranty remedies are not available for the inspection and/or repair procedures given in this

service bulletin.

C. Parts Necessary For Each Airplane

1. Kits/Parts

None.

2. Parts and Materials Supplied by the Operator

None.

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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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. The instructions identified in Paragraph 3.B., Work Instructions and the Figure(s)

give the recommended sequence of steps. The sequence of steps to do this service

bulletin can be changed.

2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for

definition of the acronyms.

3. Obey all of the warnings and cautions given in the specified manual sections.

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

– Linear dimensions are in inches

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

or minus 0.03 inch

5. 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.

B. WORK INSTRUCTIONS

1. For each leading edge slat trailing edge wedge, check maintenance records or do an inspection

of the slat wedge to determine the assembly number and refer to APPENDIX A to determine

whether it is a Type A or a Type B wedge.

2. For each Type A wedge, do an ultrasonic (preferred) or tap test inspection of the wedge for disbonds

in accordance with FIGURE 1 and FIGURE 2.

a. For each disbond that is less than or equal to 1.50 inches in maximum dimension AND is

located more than or equal to 1.0 inch from the edge of the panel AND is located more than

or equal to 4 times the disbond maximum dimension, measured edge to edge, from adjacent

damage:

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BOEING SERVICE BULLETIN 757-57-0066
(1) Repair the disbond in accordance with 757-200 SRM 51-70-10, Rev 97, 20 May 2009 or

later, 757-200CB SRM 51-70-10, Rev 71, 20 May 2009 or later, or 757-200PF SRM

51-70-10, Rev 75, 20 May 2009 or later, or replace the wedge at the time given in

Paragraph 1.E., Compliance.

(2) Repeat the ultrasonic (preferred) or tap test inspection of the disbond area or repaired

area in accordance with Work Instructions, Paragraph 3.B.2. at the time given in Paragraph

1.E., Compliance.

b. For each disbond that is more than 1.50 inches in maximum dimension or is located less than

1.0 inch from the edge of the panel or is located less than 4 times the disbond maximum

dimension, measured edge to edge, from adjacent damage:

(1) Contact Boeing for instruction and do the work instructed by Boeing or replace the wedge

at the time given in Paragraph 1.E., Compliance.

3. For each Type A wedge, repeat the ultrasonic (preferred) or tap test inspection of the wedge for

disbonds in accordance with Work Instructions, Paragraph 3.B.2. at the time given in Paragraph

1.E., Compliance.

4. For each Type B wedge, no work is required.

5. Put the airplane back to a serviceable condition.

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BOEING SERVICE BULLETIN 757-57-0066
FIGURE 1: INSPECTION OF LEFT WING LEADING EDGE SLAT TRAILING EDGE WEDGES

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 757-57-0066
FIGURE 1: INSPECTION OF LEFT WING LEADING EDGE SLAT TRAILING EDGE WEDGES

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 757-57-0066
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

shown below are the number of leading edge slat trailing edge wedges on the left wing that require inspection.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Inspect for skin-tocore disbonds. (b)

(c)

Leading edge slat trail- - (a)

ing edge wedge

1 Inspect

(a) Inspect all Type A wedges. Refer to APPENDIX A for determination of wedge type.

(b) Do an ultrasonic inspection in accordance with 757 NDT PART 4, 57-40-01 or a tap test inspection in accordance with 757 NDT PART 1, 51-05-01. Ultrasonic inspection is the preferred method.

(c) If the tap test inspection in accordance with 757 NDT PART 1, 51-05-01 is used, use a scan increment of

1/3 inch.

FIGURE 1: INSPECTION OF LEFT WING LEADING EDGE SLAT TRAILING EDGE WEDGES

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 757-57-0066
FIGURE 2: INSPECTION OF RIGHT WING LEADING EDGE SLAT TRAILING EDGE WEDGES

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 757-57-0066
FIGURE 2: INSPECTION OF RIGHT WING LEADING EDGE SLAT TRAILING EDGE WEDGES

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 757-57-0066
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

shown below are the number of leading edge slat trailing edge wedges on the right wing that require inspection.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Inspect for skin-tocore disbonds. (b)

(c)

Leading edge slat trail- - (a)

ing edge wedge

1 Inspect

(a) Inspect all Type A wedges. Refer to APPENDIX A for determination of wedge type.

(b) Do an ultrasonic inspection in accordance with 757 NDT PART 4, 57-40-01 or a tap test inspection in accordance with 757 NDT PART 1, 51-05-01. Ultrasonic inspection is the preferred method.

(c) If the tap test inspection in accordance with 757 NDT PART 1, 51-05-01 is used, use a scan increment of

1/3 inch.

FIGURE 2: INSPECTION OF RIGHT WING LEADING EDGE SLAT TRAILING EDGE WEDGES

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 757-57-0066
It is necessary to determine the type of each leading edge slat trailing edge wedge that is installed on the airplane

or owned as a spare.

Find the assembly number of each trailing edge wedge and use the figure and Table A1 on the following pages

to determine whether the wedge is Type A or Type B.

NOTE: Table A1 lists slat-wedge configurations from production. If either the wedge or the slat has

been changed since production, use only the wedge assembly number to determine the wedge

type.

1.

2. If there is insufficient evidence to determine a wedge as Type B, it should be assumed that it

is Type A.

APPENDIX A: DETERMINATION OF LEADING EDGE SLAT TRAILING EDGE WEDGE TYPE

(SHEET 1 OF 5)

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BOEING SERVICE BULLETIN 757-57-0066
APPENDIX A: DETERMINATION OF LEADING EDGE SLAT TRAILING EDGE WEDGE TYPE

(SHEET 2 OF 5)

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BOEING SERVICE BULLETIN 757-57-0066
TABLE A1: WEDGE TYPE DETERMINATION FROM ASSEMBLY NUMBERS

Slat Number Slat Assembly Number Wedge Assembly Number Wedge Type

A

114N4057-1 or

114N4002-1 thru

1

114N4057-45 or

114N4002-159, or 114N4057-57 or

114N4002-165 or 114N4057-81 or

114N4002-171 114N4057-97 or

114N4057-105

B

114N4057-137 114N4002-163 or

114N4002-169

114N4002-187 114N4057-181

A

114N4057-3 or

114N4003-1 thru

2

114N4057-47 or

114N4003-191, or 114N4057-59 or

114N4003-195 or 114N4057-83 or

114N4003-203 114N4057-99 or

114N4057-107

B

114N4057-139 114N4003-193 or

114N4003-201

114N4003-221 114N4057-183

A

114N4057-5 or 114N4004-1 thru

3

114N4057-49 or 114N4004-177, or 114N4057-61 or 114N4004-181 or 114N4057-85 or 114N4004-185 or 114N4057-101 or 114N4004-195 114N4057-109

B

114N4057-141

114N4004-179 or

114N4004-183 or

114N4004-191

114N4004-215 114N4057-185

A

114N4057-7 or 114N4005-1 thru

4

114N4057-51 or 114N4005-191, or 114N4057-63 or 114N4005-195 or 114N4057-87 or 114N4005-199 or 114N4057-103 or 114N4005-205 114N4057-111

B

114N4057-143

114N4005-193 or

114N4005-203 or

114N4005-213

114N4005-229 114N4057-187

APPENDIX A: DETERMINATION OF LEADING EDGE SLAT TRAILING EDGE WEDGE TYPE

(SHEET 3 OF 5)

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BOEING SERVICE BULLETIN 757-57-0066
TABLE A1: WEDGE TYPE DETERMINATION FROM ASSEMBLY NUMBERS

Slat Number Slat Assembly Number Wedge Assembly Number Wedge Type

A

114N3003-1 or

114N3002-1 thru

5

114N3003-19 or

114N3002-141, or 114N3003-23 or

114N3002-147 or 114N3003-25 or

114N3002-149 114N3003-27 or

114N3003-31 or

114N3003-33

B

114N3003-35

114N3002-135 or

114N3002-137 or

114N3002-143 or

114N3002-153

114N3003-57

114N3002-145 or

114N3002-155 or

114N3002-163

114N3002-151 114N3056-1

114N3056-13

114N3002-161 or

114N3002-165 or

114N3002-167

A

114N3003-2 or

114N3002-2 thru

6

114N3003-20 or

114N3002-142, or 114N3003-24 or

114N3002-148 or 114N3003-26 or

114N3002-150 114N3003-28 or

114N3003-32 or

114N3003-34

B

114N3003-36

114N3002-136 or

114N3002-138 or

114N3002-144 or

114N3002-154

114N3003-58

114N3002-146 or

114N3002-156 or

114N3002-164

114N3002-152 114N3056-2

114N3056-14

114N3002-162 or

114N3002-166 or

114N3002-168

A

114N4005-2 thru 114N4057-8 or

7 114N4005-192, or 114N4057-52 or

114N4005-196 or 114N4057-64 or

114N4005-200 or 114N4057-88 or

APPENDIX A: DETERMINATION OF LEADING EDGE SLAT TRAILING EDGE WEDGE TYPE

(SHEET 4 OF 5)

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BOEING SERVICE BULLETIN 757-57-0066
TABLE A1: WEDGE TYPE DETERMINATION FROM ASSEMBLY NUMBERS

Slat Number Slat Assembly Number Wedge Assembly Number Wedge Type

114N4005-206 114N4057-104 or

114N4057-112

B

114N4057-144

114N4005-194 or

114N4005-204 or

114N4005-214

114N4005-230 114N4057-188

A

114N4057-6 or 114N4004-2 thru

8

114N4057-50 or 114N4004-178, or 114N4057-62 or 114N4004-182 or 114N4057-86 or 114N4004-186 or 114N4057-102 or 114N4004-196 114N4057-110

B

114N4057-142

114N4004-180 or

114N4004-184 or

114N4004-192

114N4004-216 114N4057-186

A

114N4057-4 or

114N4003-2 thru

9

114N4057-48 or

114N4003-192, or 114N4057-60 or

114N4003-196 or 114N4057-84 or

114N4003-204 114N4057-100 or

114N4057-108

B

114N4057-140 114N4003-194 or

114N4003-202

114N4003-222 114N4057-184

A

114N4057-2 or

114N4002-2 thru

10

114N4057-46 or

114N4002-160, or 114N4057-58 or

114N4002-166 or 114N4057-82 or

114N4002-172 114N4057-98 or

114N4057-106

B

114N4057-138 114N4002-164 or

114N4002-170

114N4002-188 114N4057-182

APPENDIX A: DETERMINATION OF LEADING EDGE SLAT TRAILING EDGE WEDGE TYPE

(SHEET 5 OF 5)

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BOEING SERVICE BULLETIN 757-57-0066