Commercial 

Airplanes 757

Service Bulletin

ALERT

Number: 757-53A0099

Original Issue: September 18, 2014

ATA System: 5363

SUBJECT: FUSELAGE - Section 43 and 46 - Structure - Inspection for Cracks in Fuselage Frames

at Stringer S-24 and S-25, Left and Right

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 © 2014 Boeing.

Unpublished Work. All Rights Reserved.

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

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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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

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

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

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: . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 25

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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 27

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

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

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

FIGURE 1: FUSELAGE FRAME - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)

INSPECTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 54

FIGURE 2: FUSELAGE FRAME - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)

INSPECTIONS - SECTION 43 [Group 1-2, 5-6] . . . . . . . . . . . . . . . . . . . . . . . 59

APPENDIX A: SCOPE OF INSPECTION [Group 1] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 64

APPENDIX B: SCOPE OF INSPECTION [Group 2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 65

APPENDIX C: SCOPE OF INSPECTION [Group 3] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 66

APPENDIX D: SCOPE OF INSPECTION [Group 4] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 67

APPENDIX E: SCOPE OF INSPECTION [Group 5] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 68

APPENDIX F: SCOPE OF INSPECTION [Group 6] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 69

APPENDIX G: SCOPE OF INSPECTION [Group 7] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 70

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Commercial 

Airplanes 757

Service Bulletin

ALERT

Summary Number: 757-53A0099

Original Issue: September 18, 2014

ATA System: 5363

SUBJECT: FUSELAGE - Section 43 and 46 - Structure - Inspection for Cracks in Fuselage Frames

at Stringer S-24 and S-25, Left and Right

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

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

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

THE NEW OWNER.

CONCURRENT REQUIREMENTS

None.

BACKGROUND

One operator has reported a 0.60 inch long crack in the fuselage frame at Station (STA) 1440, stringer S-24L.

The airplane had 36,890 total flight cycles and 78,922 total flight hours. The crack was discovered while doing

unrelated local repairs. An investigation has determined the crack may have been caused by fatigue. The crack

initiated in the fuselage frame at the corner radius of the fuselage frame opening for the stringer. It continued

to the fastener hole common to fuselage frame, splice plate, and fail safe chord. The crack was not visible

because it was completely hidden by the splice plate on one side and the fail safe chord on the other side. If

this service bulletin is not done, such fatigue cracking could adversely affect the structural integrity of the airplane.

Similar design details and stresses exist at multiple fuselage frame stations in Section 43 and Section 46. This

service bulletin gives instructions to inspect for cracks in the fuselage frames at S-24 and S-25, left and right at

multiple fuselage frame stations.

The fuselage frames have been determined to be structure that is susceptible to Widespread Fatigue Damage

(WFD).

Boeing Service Related Problem (SRP) 757-53-0429 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

Paragraph 1.E., Compliance and Paragraph

1.F., Approval

AD Related Yes

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

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Planning Data Affected Reference

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 Parts/Material No

Paragraph 2.F., Special Tooling Necessary to

do this Service Bulletin

Special Tooling Required No

ACTION

This service bulletin gives instructions to do detailed and High Frequency Eddy Current (HFEC) inspections for

cracks in the fuselage frames at the identified Station (STA) locations and Stringer (S) locations.

If any crack is found, contact Boeing for repair instructions and do the repair.

EFFECTIVITY

All 757-200, -200CB, -200PF, -300 Airplane(s). Refer to Paragraph 1.A.1., Airplanes, for the list of affected

airplane(s).

COMPLIANCE

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

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

mandatory.

Refer to Paragraph 1.E., Compliance.

INDUSTRY SUPPORT INFORMATION

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

MANPOWER

Refer to Paragraph 1.G., Manpower.

MATERIAL INFORMATION

None.

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BLANK PAGE
Commercial 

Airplanes 757

Service Bulletin

ALERT

Number: 757-53A0099

Original Issue: September 18, 2014

ATA System: 5363

SUBJECT: FUSELAGE - Section 43 and 46 - Structure - Inspection for Cracks in Fuselage Frames

at Stringer S-24 and S-25, Left and Right

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

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

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

THE NEW OWNER.

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

This service bulletin is for the airplane(s) shown below.

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

Serial Number data.

GROUP CONFIGURATION DESCRIPTION

1 - 757-200 Airplanes with 2 Cargo Doors

2 - 757-200 Airplanes with 3 Cargo Doors

3 - 757-200PF Airplanes (Freighter)

757-200SF Airplanes (Special Freighter Boeing Supplemental Type

Certificate)

4 -

757-300 Airplanes with Cargo Net Support Structure Installation (STA

720-STA 740)

5 -

757-300 Airplanes without Cargo Net Support Structure Installation

(STA 720-STA 740)

6 -

7 - 757-200CB Airplane (Convertible)

Airplane Models:

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

Variable Number Group

NA001 - NA028 1

NA191 - NA199 1

NA201 - NA204 4

NA205 2

NA206 - NA213 4

NA214 2

NA215 - NA236 4

NA237 - NA239 1

NA301 - NA305 1

NA341 - NA352 2

NA391 - NA399 2

NA401 - NA408 1

NA441 - NA447 1

NA501 - NA586 1

NB001 - NB004 1

NB021 - NB023 1

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

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Variable Number Group

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 3

NC971 - NC974 3

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 7

NE001 - NE008 1

NE011 - NE088 1

NE091 - NE094 1

NE141 - NE150 1

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Variable Number Group

NE161 - NE177 1

NE201 - NE204 1

NE301 - NE302 1

NE311 - NE325 1

NJ001 - NJ004 1

NJ031 - NJ032 1

NJ551 - NJ555 1

NL001 - NL002 5

NL006 - NL017 6

NL101 - NL109 6

NL141 6

NL601 - NL616 6

NN001 - NN002 1

NN051 - NN052 1

NP901 - NP904 1

NS601 - NS616 3

NT001 - NT009 3

NT201 - NT202 1

NT231 - NT234 1

NT237 - NT240 1

NT242 1

NT245 - NT248 1

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

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Variable Number Group

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

NU701 - NU705 5

NU721 - NU728 5

NU731 - NU732 5

2. Spares Affected

None.

B. Concurrent Requirements

None.

C. Reason

One operator has reported a 0.60 inch long crack in the fuselage frame at Station (STA) 1440, stringer

S-24L. The airplane had 36,890 total flight cycles and 78,922 total flight hours. The crack was discovered

while doing unrelated local repairs. An investigation has determined the crack may have been caused

by fatigue. The crack initiated in the fuselage frame at the corner radius of the fuselage frame opening

for the stringer. It continued to the fastener hole common to fuselage frame, splice plate, and fail safe

chord. The crack was not visible because it was completely hidden by the splice plate on one side and

the fail safe chord on the other side. If this service bulletin is not done, such fatigue cracking could

adversely affect the structural integrity of the airplane.

Similar design details and stresses exist at multiple fuselage frame stations in Section 43 and Section

46. This service bulletin gives instructions to inspect for cracks in the fuselage frames at S-24 and

S-25, left and right at multiple fuselage frame stations.

The fuselage frames have been determined to be structure that is susceptible to Widespread Fatigue

Damage (WFD).

Boeing Service Related Problem (SRP) 757-53-0429 is related to this service bulletin.

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ALERT ALERT
D. Description

This service bulletin gives instructions to do detailed and High Frequency Eddy Current (HFEC)

inspections for cracks in the fuselage frames at the identified Station (STA) locations and Stringer (S)

locations.

If any crack is found, contact Boeing for repair instructions and do the repair.

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

Group 1-2, 4:

Affected Maintenance Zones

Model Zone

757-200 119, 121, 122, 153, 154, 161, 162, 165, 166

Group 3:

Affected Maintenance Zones

Model Zone

757-200PF 119, 121, 122, 153, 154, 161, 162, 165, 166

Group 5-6:

Affected Maintenance Zones

Model Zone

757-300 119, 121, 122, 153, 154, 161, 162, 165, 166

Group 7:

Affected Maintenance Zones

Model Zone

757-200CB 119, 121, 122, 153, 154, 161, 162, 165, 166

E. Compliance

1. 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.

2. Do the required actions in accordance with Paragraph 3. Accomplishment Instructions.

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ALERT ALERT
3. Previously Approved Boeing Frame Repairs Common To Inspection Areas:

a. If any Boeing Organization Designation Authorization (ODA) approved repair via FAA Form

8100-9 interferes with the frame inspection areas in this service bulletin, the operator must

contact Boeing for alternate inspection instructions and do the alternate inspection instructions

before or at the Compliance time outlined in this Service Bulletin (SB).

b. If any Boeing ODA approved repair via FAA Form 8100-9 in the frame inspection area does

not impede inspections under the frame flange per this SB, the operator shall perform the SB

inspections as described in this SB.

4. Any Repair Installed as a Result of Accomplishing this Service Bulletin:

a. If any repair is installed as a result of accomplishing this service bulletin, do the post repair

requirements for the affected repair area in accordance with the Boeing ODA approved repair.

Any remaining requirements of this service bulletin remain fully applicable and must be complied

with.

5. When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers.

When more than one ACTION is given for a CONDITION number or an OPTION number, do all

of the ACTION numbers for that CONDITION number or OPTION number.

Group 1:

Table 1: Fuselage Frames - Detailed and High Frequency Eddy Current (HFEC) Inspections for Cracks

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs Later)

Condition Action

Within 6,000 flight -

cycles after the

original issue date

of this service bulletin

Before 24,000 total

flight cycles

Do PART 2: FUSELAGE

FRAMES - DETAILED AND

HIGH FREQUENCY EDDY

CURRENT (HFEC) INSPECTIONS for cracks.

All Airplanes

Within 6,000 flight -

cycles after the

original issue date

of this service bulletin

Before 36,000 total

flight cycles

Do PART 3: FUSELAGE

FRAMES - DETAILED AND

HIGH FREQUENCY EDDY

CURRENT (HFEC) INSPECTIONS for cracks.

All Airplanes

Within 6,000 flight -

cycles after the

original issue date

of this service bulletin

Before 50,000 total

flight cycles

Do PART 4: FUSELAGE

FRAMES - DETAILED AND

HIGH FREQUENCY EDDY

CURRENT (HFEC) INSPECTIONS for cracks.

All Airplanes

Repeat PART 2: FUSE- - - 12,000 Flight

LAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for

cracks.

CONDITION 1: NO

CRACK FOUND

DURING PART 2

INSPECTIONS

Cycles

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Group 1:

Table 1: Fuselage Frames - Detailed and High Frequency Eddy Current (HFEC) Inspections for Cracks

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs Later)

Condition Action

Repeat PART 3: FUSE- - - 12,000 Flight

LAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for

cracks.

CONDITION 2: NO

CRACK FOUND

DURING PART 3

INSPECTIONS

Cycles

Repeat PART 4: FUSE- - - 12,000 Flight

LAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for

cracks.

CONDITION 3: NO

CRACK FOUND

DURING PART 4

INSPECTIONS

Cycles

Contact Boeing for repair Before further flight - -

instructions and do the repair.

CONDITION 4:

ANY CRACK

FOUND

Group 2:

Table 2: Fuselage Frames - Detailed and High Frequency Eddy Current (HFEC) Inspections for Cracks

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs Later)

Condition Action

Within 6,000 flight -

cycles after the

original issue date

of this service bulletin

Before 24,000 total

flight cycles

Do PART 5: FUSELAGE

FRAMES - DETAILED AND

HIGH FREQUENCY EDDY

CURRENT (HFEC) INSPECTIONS for cracks.

All Airplanes

Within 6,000 flight -

cycles after the

original issue date

of this service bulletin

Before 36,000 total

flight cycles

Do PART 6: FUSELAGE

FRAMES - DETAILED AND

HIGH FREQUENCY EDDY

CURRENT (HFEC) INSPECTIONS for cracks.

All Airplanes

Within 6,000 flight -

cycles after the

original issue date

of this service bulletin

Before 50,000 total

flight cycles

Do PART 7: FUSELAGE

FRAMES - DETAILED AND

HIGH FREQUENCY EDDY

CURRENT (HFEC) INSPECTIONS for cracks.

All Airplanes

Repeat PART 5: FUSE- - - 12,000 Flight

LAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for

cracks.

CONDITION 5: NO

CRACK FOUND

DURING PART 5

INSPECTIONS

Cycles

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Group 2:

Table 2: Fuselage Frames - Detailed and High Frequency Eddy Current (HFEC) Inspections for Cracks

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs Later)

Condition Action

Repeat PART 6: FUSE- - - 12,000 Flight

LAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for

cracks.

CONDITION 6: NO

CRACK FOUND

DURING PART 6

INSPECTIONS

Cycles

Repeat PART 7: FUSE- - - 12,000 Flight

LAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for

cracks.

CONDITION 7: NO

CRACK FOUND

DURING PART 7

INSPECTIONS

Cycles

Contact Boeing for repair Before further flight - -

instructions and do the repair.

CONDITION 8:

ANY CRACK

FOUND

Group 3:

Table 3: Fuselage Frames - Detailed and High Frequency Eddy Current (HFEC) Inspections for Cracks

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs Later)

Condition Action

Within 6,000 flight -

cycles after the

original issue date

of this service bulletin

Before 36,000 total

flight cycles

Do PART 8: FUSELAGE

FRAMES - DETAILED AND

HIGH FREQUENCY EDDY

CURRENT (HFEC) INSPECTIONS for cracks.

All Airplanes

Within 6,000 flight -

cycles after the

original issue date

of this service bulletin

Before 50,000 total

flight cycles

Do PART 9: FUSELAGE

FRAMES - DETAILED AND

HIGH FREQUENCY EDDY

CURRENT (HFEC) INSPECTIONS for cracks.

All Airplanes

Repeat PART 8: FUSE- - - 12,000 Flight

LAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for

cracks.

CONDITION 9: NO

CRACK FOUND

DURING PART 8

INSPECTIONS

Cycles

Repeat PART 9: FUSE- - - 12,000 Flight

LAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for

cracks.

CONDITION 10:

NO CRACK

FOUND DURING

PART 9 INSPECTIONS

Cycles

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ALERT ALERT
Group 3:

Table 3: Fuselage Frames - Detailed and High Frequency Eddy Current (HFEC) Inspections for Cracks

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs Later)

Condition Action

Contact Boeing for repair Before further flight - -

instructions and do the repair.

CONDITION 11:

ANY CRACK

FOUND

Group 4:

Table 4: Fuselage Frames - Detailed and High Frequency Eddy Current (HFEC) Inspections for Cracks

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs Later)

Condition Action

Within 6,000 flight -

cycles after the

original issue date

of this service bulletin

Before 36,000 total

flight cycles

Do PART 10: FUSELAGE

FRAMES - DETAILED AND

HIGH FREQUENCY EDDY

CURRENT (HFEC) INSPECTIONS for cracks.

All Airplanes

Within 6,000 flight -

cycles after the

original issue date

of this service bulletin

Before 50,000 total

flight cycles

Do PART 11: FUSELAGE

FRAMES - DETAILED AND

HIGH FREQUENCY EDDY

CURRENT (HFEC) INSPECTIONS for cracks.

All Airplanes

Repeat PART 10: FUSE- - - 12,000 Flight

LAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for

cracks.

CONDITION 12:

NO CRACK

FOUND DURING

PART 10 INSPECTIONS

Cycles

Repeat PART 11: FUSE- - - 12,000 Flight

LAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for

cracks.

CONDITION 13:

NO CRACK

FOUND DURING

PART 11 INSPECTIONS

Cycles

Contact Boeing for repair Before further flight - -

instructions and do the repair.

CONDITION 14:

ANY CRACK

FOUND

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Group 5:

Table 5: Fuselage Frames - Detailed and High Frequency Eddy Current (HFEC) Inspections for Cracks

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs Later)

Condition Action

Within 6,000 flight -

cycles after the

original issue date

of this service bulletin

Before 24,000 total

flight cycles

Do PART 12: FUSELAGE

FRAMES - DETAILED AND

HIGH FREQUENCY EDDY

CURRENT (HFEC) INSPECTIONS for cracks.

All Airplanes

Within 6,000 flight -

cycles after the

original issue date

of this service bulletin

Before 36,000 total

flight cycles

Do PART 13: FUSELAGE

FRAMES - DETAILED AND

HIGH FREQUENCY EDDY

CURRENT (HFEC) INSPECTIONS for cracks.

All Airplanes

Within 6,000 flight -

cycles after the

original issue date

of this service bulletin

Before 50,000 total

flight cycles

Do PART 14: FUSELAGE

FRAMES - DETAILED AND

HIGH FREQUENCY EDDY

CURRENT (HFEC) INSPECTIONS for cracks.

All Airplanes

Repeat PART 12: FUSE- - - 12,000 Flight

LAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for

cracks.

CONDITION 15:

NO CRACK

FOUND DURING

PART 12 INSPECTIONS

Cycles

Repeat PART 13: FUSE- - - 12,000 Flight

LAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for

cracks.

CONDITION 16:

NO CRACK

FOUND DURING

PART 13 INSPECTIONS

Cycles

Repeat PART 14: FUSE- - - 12,000 Flight

LAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for

cracks.

CONDITION 17:

NO CRACK

FOUND DURING

PART 14 INSPECTIONS

Cycles

Contact Boeing for repair Before further flight - -

instructions and do the repair.

CONDITION 18:

ANY CRACK

FOUND

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ALERT ALERT
Group 6:

Table 6: Fuselage Frames - Detailed and High Frequency Eddy Current (HFEC) Inspections for Cracks

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs Later)

Condition Action

Within 6,000 flight -

cycles after the

original issue date

of this service bulletin

Before 24,000 total

flight cycles

Do PART 15: FUSELAGE

FRAMES - DETAILED AND

HIGH FREQUENCY EDDY

CURRENT (HFEC) INSPECTIONS for cracks.

All Airplanes

Within 6,000 flight -

cycles after the

original issue date

of this service bulletin

Before 36,000 total

flight cycles

Do PART 16: FUSELAGE

FRAMES - DETAILED AND

HIGH FREQUENCY EDDY

CURRENT (HFEC) INSPECTIONS for cracks.

All Airplanes

Within 6,000 flight -

cycles after the

original issue date

of this service bulletin

Before 50,000 total

flight cycles

Do PART 17: FUSELAGE

FRAMES - DETAILED AND

HIGH FREQUENCY EDDY

CURRENT (HFEC) INSPECTIONS for cracks.

All Airplanes

Repeat PART 15: FUSE- - - 12,000 Flight

LAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for

cracks.

CONDITION 19:

NO CRACK

FOUND DURING

PART 15 INSPECTIONS

Cycles

Repeat PART 16: FUSE- - - 12,000 Flight

LAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for

cracks.

CONDITION 20:

NO CRACK

FOUND DURING

PART 16 INSPECTIONS

Cycles

Repeat PART 17: FUSE- - - 12,000 Flight

LAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for

cracks.

CONDITION 21:

NO CRACK

FOUND DURING

PART 17 INSPECTIONS

Cycles

Contact Boeing for repair Before further flight - -

instructions and do the repair.

CONDITION 22:

ANY CRACK

FOUND

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Group 7:

Table 7: Fuselage Frames - Detailed and High Frequency Eddy Current (HFEC) Inspections for Cracks

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs Later)

Condition Action

Within 6,000 flight -

cycles after the

original issue date

of this service bulletin

Before 36,000 total

flight cycles

Do PART 18: FUSELAGE

FRAMES - DETAILED AND

HIGH FREQUENCY EDDY

CURRENT (HFEC) INSPECTIONS for cracks.

All Airplanes

Within 6,000 flight -

cycles after the

original issue date

of this service bulletin

Before 50,000 total

flight cycles

Do PART 19: FUSELAGE

FRAMES - DETAILED AND

HIGH FREQUENCY EDDY

CURRENT (HFEC) INSPECTIONS for cracks.

All Airplanes

Repeat PART 18: FUSE- - - 12,000 Flight

LAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for

cracks.

CONDITION 23:

NO CRACK

FOUND DURING

PART 18 INSPECTIONS

Cycles

Repeat PART 19: FUSE- - - 12,000 Flight

LAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for

cracks.

CONDITION 24:

NO CRACK

FOUND DURING

PART 19 INSPECTIONS

Cycles

Contact Boeing for repair Before further flight - -

instructions and do the repair.

CONDITION 25:

ANY CRACK

FOUND

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.

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G. Manpower

The table below shows an estimate of the task hours necessary to do this inspection for each airplane.

This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator

task hour data if necessary. The estimate does not include lost time. These are some examples of lost

time:

• Time to adjust to the workplace

• Time to schedule the work

• Time to inspect the work

• Time to cure the materials

• Time to make the parts

• Time to find the tools.

Group 1:

Task Number of Persons Task Hours Elapsed Hours

Part 1 (a) 4 23.00 (a) 5.75 (a)

Part 2 1 2.25 2.25

Part 3 4 15.00 3.75

Part 4 4 19.60 4.90

Part 20 4 23.00 5.75

TOTAL FOR EACH AIRPLANE 82.85 22.40

(a) Refer to Work Instructions, Paragraph 3.B., Part 1 for additional open access

information. More task hours will be required at these locations.

Group 2:

Task Number of Persons Task Hours Elapsed Hours

Part 1 (a) 4 18.60 (a) 4.65 (a)

Part 5 1 2.25 2.25

Part 6 4 19.60 4.90

Part 7 2 9.00 4.50

Part 20 4 18.60 4.65

TOTAL FOR EACH AIRPLANE 68.05 20.95

(a) Refer to Work Instructions, Paragraph 3.B., Part 1 for additional open access

information. More task hours will be required at these locations.

Group 3:

Task Number of Persons Task Hours Elapsed Hours

Part 1 (a) 4 19.00 (a) 4.75 (a)

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Group 3:

Task Number of Persons Task Hours Elapsed Hours

Part 8 4 20.20 5.05

Part 9 4 13.60 3.40

Part 20 4 19.00 4.75

TOTAL FOR EACH AIRPLANE 71.80 17.95

(a) Refer to Work Instructions, Paragraph 3.B., Part 1 for additional open access

information. More task hours will be required at these locations.

Group 4:

Task Number of Persons Task Hours Elapsed Hours

Part 1 (a) 4 19.00 (a) 4.75 (a)

Part 10 4 26.20 6.55

Part 11 1 3.00 3.00

Part 20 4 19.00 4.75

TOTAL FOR EACH AIRPLANE 67.20 19.05

(a) Refer to Work Instructions, Paragraph 3.B., Part 1 for additional open access

information. More task hours will be required at these locations.

Group 5:

Task Number of Persons Task Hours Elapsed Hours

Part 1 (a) 4 22.00 (a) 5.50 (a)

Part 12 1 1.25 1.25

Part 13 4 15.80 3.95

Part 14 4 18.00 4.50

Part 20 4 22.00 5.50

TOTAL FOR EACH AIRPLANE 79.05 20.70

(a) Refer to Work Instructions, Paragraph 3.B., Part 1 for additional open access

information. More task hours will be required at these locations.

Group 6:

Task Number of Persons Task Hours Elapsed Hours

Part 1 (a) 4 22.00 (a) 5.50 (a)

Part 15 1 2.25 2.25

Part 16 4 15.80 3.95

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Group 6:

Task Number of Persons Task Hours Elapsed Hours

Part 17 4 18.00 4.50

Part 20 4 22.00 5.50

TOTAL FOR EACH AIRPLANE 80.05 21.70

(a) Refer to Work Instructions, Paragraph 3.B., Part 1 for additional open access

information. More task hours will be required at these locations.

Group 7:

Task Number of Persons Task Hours Elapsed Hours

Part 1 (a) 4 20.40 (a) 5.10 (a)

Part 18 4 21.00 5.25

Part 19 2 10.50 5.25

Part 20 4 20.40 5.10

TOTAL FOR EACH AIRPLANE 72.30 20.70

(a) Refer to Work Instructions, Paragraph 3.B., Part 1 for additional open access

information. More task hours will be required at these locations.

H. Weight and Balance Changes

None.

I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. Boeing Service Letter 757-SL-51-022

b. Boeing Service Related Problem (SRP) 757-53-0429

c. Service Bulletin Index D624N001

d. 757 Aircraft Maintenance Manual (AMM) 06-41-00, 25-50-02, 25-50-07

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

f. 757-200 Structural Repair Manual (SRM) 53-30-07, 53-60-07

g. 757-200CB Structural Repair Manual (SRM) 53-30-07, 53-60-07

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ALERT ALERT
h. 757-200PF Structural Repair Manual (SRM) 53-30-07, 53-60-07

i. 757-300 Structural Repair Manual (SRM) 53-30-07, 53-60-07

j. Multi Operator Message, MOM-MOM-13-0823-01B

2. Data Supplied with this Service Bulletin:

None.

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

Drawing Number Title

146N1013 Frame Instl Body Station 1440

146N1028 Frame Detail - Body Station 1200 - 1440

451N5130 Net Support Structure Instl - Fwd Cargo Compartment

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

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

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

K. Publications Affected

1. Publications:

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 but no new DTIs are necessary.

L. Interchangeability and Intermixability of Parts

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

M. Software Accomplishment Summary

Not affected.

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ALERT ALERT

BLANK PAGE
2. MATERIAL INFORMATION

A. Material - Price and Availability

None.

B. Industry Support Information

Boeing warranty remedies are not available for the inspections 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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ALERT ALERT

BLANK PAGE
3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL

PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,

METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE

DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR

OTHER ELECTRICAL DAMAGE.

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

definition of the acronyms.

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

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

– Linear dimensions are in inches

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

or minus 0.03 inch

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

– Angular tolerance is plus or minus 2 degrees

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

Manual (SRM) Chapter 51

– Torque Values:

— Values for structural fasteners are given in 757 Structural Repair Manual,

Chapter 51.

— Values for airframe maintenance tasks are included in Chapter 20 of 757

Airplane Maintenance Manual (AMM).

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

Standard Wiring Practices Manual (SWPM).

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

applicable installation step.

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

SRM Chapter 51.

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

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

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

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

necessary. Surface cleaning and elaborate procedures may be required.

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.

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ALERT ALERT
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. Refer to APPENDIX A to APPENDIX G for Scope of Inspection. The diagrams are

provided as aids only. Information contained in Paragraph 1.E., Compliance is the

primary source for compliance times. Information in Paragraph 3.B., Work Instructions

is the primary source for tasks required for compliance.

9. The instructions in Paragraph 3.B., Work Instructions and the figures can include

operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated

Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing

Index contain data on versions of the tools or test equipment that you can use. It is

permitted to use replaced tools. It is not permitted to use superseded tools.

10. If it is necessary to remove more parts for access, you can remove those parts. If

you can get access without removing identified parts, it is not necessary to remove

all of the identified parts. Jacking and shoring limitations must be observed.

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

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

12. If shading is used, shaded areas in Figures are to separate the non-critical and

non-authoritative information from the critical and authoritative information.

13. Some steps in the Work Instructions are identified as Required for Compliance (RC).

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

identified as RC must be done to comply with the AD. Alternative procedures for

steps not identified with RC can be used if the RC steps can still be done as specified,

and the airplane can be put back in a serviceable condition. An Alternative Method

of Compliance (AMOC) is not necessary for deviations to steps that are not identified

as RC.

14. Refer to Multi Operator Message, MOM-MOM-13-0823-01B, for information on the

Retention of Failed/Discrepant Part for Boeing Evaluation. It is requested that an

operator or repair station retain any failed or discrepant parts for possible examination

or analysis by Boeing when doing this Service Bulletin.

15. Previously Approved Boeing Frame Repairs Common To Inspection Areas:

— If any Boeing Organization Designation Authorization (ODA) approved repair

via FAA Form 8100-9 interferes with the frame inspection areas in this service

bulletin, the operator must contact Boeing for alternate inspection instructions

and do the alternate inspection instructions before or at the Compliance time

outlined in this Service Bulletin (SB).

— If any Boeing ODA approved repair via FAA Form 8100-9 in the frame inspection

area does not impede inspections under the frame flange per this SB, the

operator shall perform the SB inspections as described in this SB.

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ALERT ALERT
16. Any Repair Installed as a Result of Accomplishing this Service Bulletin:

– If any repair is installed as a result of accomplishing this service bulletin, do the

post repair requirements for the affected repair area in accordance with the

Boeing ODA approved repair. Any remaining requirements of this service bulletin

remain fully applicable and must be complied with.

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

are in Paragraph 1.E., Compliance.

18. When more than one OPTION is given for a CONDITION, do only one of the OPTION

numbers. When more than one ACTION is given for a CONDITION number or an

OPTION number, do all of the ACTION numbers for that CONDITION number or

OPTION number.

B. WORK INSTRUCTIONS

The table below defines the PART requirements by Group.

Group PART

1 1, 2, 3, 4, 20

2 1, 5, 6, 7, 20

3 1, 8, 9, 20

4 1, 10, 11, 20

5 1, 12, 13, 14, 20

6 1, 15, 16, 17, 20

7 1, 18, 19, 20

Group 1:

1. Do PART 1: OPEN ACCESS.

2. RC - Do PART 2: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for cracks.

3. RC - Do PART 3: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for cracks.

4. RC - Do PART 4: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for cracks.

5. RC - Based upon the detailed and HFEC inspection results from accomplishing PART 2, PART

3, or PART 4, do the following:

a. CONDITION 1: NO CRACK FOUND DURING PART 2 INSPECTIONS

(1) RC - Repeat PART 2: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY

EDDY CURRENT (HFEC) INSPECTIONS for cracks.

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b. CONDITION 2: NO CRACK FOUND DURING PART 3 INSPECTIONS

(1) RC - Repeat PART 3: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY

EDDY CURRENT (HFEC) INSPECTIONS for cracks.

c. CONDITION 3: NO CRACK FOUND DURING PART 4 INSPECTIONS

(1) RC - Repeat PART 4: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY

EDDY CURRENT (HFEC) INSPECTIONS for cracks.

d. CONDITION 4 - ANY CRACK FOUND

(1) RC - Contact Boeing for repair instructions and do the repair.

6. Do PART 20: CLOSE ACCESS.

Group 2:

1. Do PART 1: OPEN ACCESS.

2. RC - Do PART 5: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for cracks.

3. RC - Do PART 6: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for cracks.

4. RC - Do PART 7: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for cracks.

5. RC - Based upon the detailed and HFEC inspection results from accomplishing PART 5, PART

6, or PART 7, do the following:

a. CONDITION 5: NO CRACK FOUND DURING PART 5 INSPECTIONS

(1) RC - Repeat PART 5: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY

EDDY CURRENT (HFEC) INSPECTIONS for cracks.

b. CONDITION 6: NO CRACK FOUND DURING PART 6 INSPECTIONS

(1) RC - Repeat PART 6: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY

EDDY CURRENT (HFEC) INSPECTIONS for cracks.

c. CONDITION 7: NO CRACK FOUND DURING PART 7 INSPECTIONS

(1) RC - Repeat PART 7: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY

EDDY CURRENT (HFEC) INSPECTIONS for cracks.

d. CONDITION 8 - ANY CRACK FOUND

(1) RC - Contact Boeing for repair instructions and do the repair.

6. Do PART 20: CLOSE ACCESS.

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 757-53A0099

ALERT ALERT
Group 3:

1. Do PART 1: OPEN ACCESS.

2. RC - Do PART 8: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for cracks.

3. RC - Do PART 9: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for cracks.

4. RC - Based upon the detailed and HFEC inspection results from accomplishing PART 8 or PART

9, do the following:

a. CONDITION 9: NO CRACK FOUND DURING PART 8 INSPECTIONS

(1) RC - Repeat PART 8: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY

EDDY CURRENT (HFEC) INSPECTIONS for cracks.

b. CONDITION 10: NO CRACK FOUND DURING PART 9 INSPECTIONS

(1) RC - Repeat PART 9: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY

EDDY CURRENT (HFEC) INSPECTIONS for cracks.

c. CONDITION 11 - ANY CRACK FOUND

(1) RC - Contact Boeing for repair instructions and do the repair.

5. Do PART 20: CLOSE ACCESS.

Group 4:

1. Do PART 1: OPEN ACCESS.

2. RC - Do PART 10: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for cracks.

3. RC - Do PART 11: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for cracks.

4. RC - Based upon the inspection results from accomplishing PART 10 or PART 11, do the following:

a. CONDITION 12: NO CRACK FOUND DURING PART 10 INSPECTIONS

(1) RC - Repeat PART 10: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY

EDDY CURRENT (HFEC) INSPECTIONS for cracks.

b. CONDITION 13: NO CRACK FOUND DURING PART 11 INSPECTIONS

(1) RC - Repeat PART 11: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY

EDDY CURRENT (HFEC) INSPECTIONS for cracks.

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ALERT ALERT
c. CONDITION 14 - ANY CRACK FOUND

(1) RC - Contact Boeing for repair instructions and do the repair.

5. Do PART 20: CLOSE ACCESS.

Group 5:

1. Do PART 1: OPEN ACCESS.

2. RC - Do PART 12: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for cracks.

3. RC - Do PART 13: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for cracks.

4. RC - Do PART 14: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for cracks.

5. RC - Based upon the inspection results from accomplishing PART 12, PART 13, or PART 14, do

the following:

a. CONDITION 15: NO CRACK FOUND DURING PART 12 INSPECTIONS

(1) RC - Repeat PART 12: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY

EDDY CURRENT (HFEC) INSPECTIONS for cracks.

b. CONDITION 16: NO CRACK FOUND DURING PART 13 INSPECTIONS

(1) RC - Repeat PART 13: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY

EDDY CURRENT (HFEC) INSPECTIONS for cracks.

c. CONDITION 17: NO CRACK FOUND DURING PART 14 INSPECTIONS

(1) RC - Repeat PART 14: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY

EDDY CURRENT (HFEC) INSPECTIONS for cracks.

d. CONDITION 18 - ANY CRACK FOUND

(1) RC - Contact Boeing for repair instructions and do the repair.

6. Do PART 20: CLOSE ACCESS.

Group 6:

1. Do PART 1: OPEN ACCESS.

2. RC - Do PART 15: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for cracks.

3. RC - Do PART 16: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for cracks.

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ALERT ALERT
4. RC - Do PART 17: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for cracks.

5. RC - Based upon the inspection results from accomplishing PART 15, PART 16, or PART 17, do

the following:

a. CONDITION 19: NO CRACK FOUND DURING PART 15 INSPECTIONS

(1) RC - Repeat PART 15: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY

EDDY CURRENT (HFEC) INSPECTIONS for cracks.

b. CONDITION 20: NO CRACK FOUND DURING PART 16 INSPECTIONS

(1) RC - Repeat PART 16: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY

EDDY CURRENT (HFEC) INSPECTIONS for cracks.

c. CONDITION 21: NO CRACK FOUND DURING PART 17 INSPECTIONS

(1) RC - Repeat PART 17: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY

EDDY CURRENT (HFEC) INSPECTIONS for cracks.

d. CONDITION 22 - ANY CRACK FOUND

(1) RC - Contact Boeing for repair instructions and do the repair.

6. Do PART 20: CLOSE ACCESS.

Group 7:

1. Do PART 1: OPEN ACCESS.

2. RC - Do PART 18: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for cracks.

3. RC - Do PART 19: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT

(HFEC) INSPECTIONS for cracks.

4. RC - Based upon the inspection results from accomplishing PART 18 or PART 19, do the following:

a. CONDITION 23: NO CRACK FOUND DURING PART 18 INSPECTIONS

(1) RC - Repeat PART 18: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY

EDDY CURRENT (HFEC) INSPECTIONS for cracks.

b. CONDITION 24: NO CRACK FOUND DURING PART 19 INSPECTIONS

(1) RC - Repeat PART 19: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY

EDDY CURRENT (HFEC) INSPECTIONS for cracks.

c. CONDITION 25 - ANY CRACK FOUND

(1) RC - Contact Boeing for repair instructions and do the repair.

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ALERT ALERT
5. Do PART 20: CLOSE ACCESS.

PART 1: OPEN ACCESS

1. Get access to the fuselage frame inspection areas as follows:

a. Remove and keep the cargo compartment sidewall linings. Refer to 757 AMM 25-50-02 as

an accepted procedure.

b. Remove and keep the cargo compartment insulation. Refer to 757 AMM 25-50-07 as an

accepted procedure.

c. Open Main Equipment Center (MEC) access door 119BL. Refer to 757 AMM 06-41-00 as an

accepted procedure.

d. An inquiry was done with an operator to obtain additional access information. The results

indicate that operators should consider planning for additional work and time when gaining

access to the following areas:

Threshold Access Issue

(Total Flight Cycles)

Group Location

1-2, 4-7 Right Side, STA 1660 to STA 1701 36,000 Ducts and Hoses

1-3, 5-7 Left Side, STA 500 50,000 Electrical Wire Bundles/Ducts

4 Right Side, STA 440 50,000 Avionics Rack/Equipment

1-2, 4 Right Side, STA 500 to STA 520 50,000 P36 Electrical Panel

1,3, 5-7 Right Side, STA 1480 50,000 E6 Aft Equipment Rack (a)

3 Right Side, STA 1660 to STA 1701 50,000 Ducts and Hoses

(a) Depending on customer configuration, the E6 Aft Equipment Rack may not be installed at this location.

Group 1:

PART 2: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)

INSPECTIONS

1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE

1 at the Station (STA) and Stringer (S) locations that follow:

Station (STA) and Stringer (S) Qty Location

Location

Task Name

Inspect Fuselage Frame STA 560, S-25L 1 Forward Cargo

Compartment, Left Side STA 580, S-25L

STA 600, S-25L

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ALERT ALERT
Group 1:

PART 3: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)

INSPECTIONS

1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE

1 at the Station (STA) and Stringer (S) locations that follow:

Station (STA) and Stringer (S) Qty Location

Location

Task Name

Inspect Fuselage Frame STA 640, S-25L 1 Forward Cargo

Compartment, Left Side STA 660, S-25L

STA 680, S-25L

STA 700, S-25L

STA 720, S-25L

Aft Cargo Compartment,

Left Side

STA 1360, S-24L 1

STA 1380, S-24L

STA 1400, S-24L

STA 1420, S-24L

STA 1440, S-24L

STA 1460, S-24L

STA 1480, S-24L

Bulk Cargo Compartment,

Left Side

STA 1500, S-24L 1

Area Aft of Bulk Cargo

Compartment, Left Side

STA 1661, S-24L 1

STA 660, S-25R 1 Forward Cargo

Compartment, Right Side STA 680, S-25R

STA 700, S-25R

STA 720, S-25R

Area Aft of Bulk Cargo

Compartment, Right Side

STA 1661, S-24R 1

2. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE

2 at the Station (STA) and Stringer (S) locations that follow:

Station (STA) and Stringer (S) Qty Location

Location

Task Name

Inspect Fuselage Frame STA 620, S-25L 1 Forward Cargo

Compartment, Left Side

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ALERT ALERT
Group 1:

PART 4: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)

INSPECTIONS

1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE

1 at the Station (STA) and Stringer (S) locations that follow:

Station (STA) and Stringer (S) Qty Location

Location

Task Name

Main Equipment Center,

Left Side

Inspect Fuselage Frame STA 500, S-25L 1

STA 520, S-25L 1 Forward Cargo

Compartment, Left Side STA 540, S-25L

STA 740, S-25L

STA 760, S-25L

STA 780, S-25L

Bulk Cargo Compartment,

Left Side

STA 1520, S-24L 1

STA 1540, S-24L

STA 1560, S-24L

STA 1580, S-24L

STA 1600, S-24L

STA 1620, S-24L

Main Equipment Center,

Right Side

STA 480, S-25R 1

STA 500, S-25R

STA 520, S-25R 1 Forward Cargo

Compartment, Right Side STA 740, S-25R

STA 760, S-25R

STA 780, S-25R

Aft Cargo Compartment,

Right Side

STA 1480, S-24R 1

Bulk Cargo Compartment,

Right Side

STA 1500, S-24R 1

STA 1520, S-24R

STA 1540, S-24R

STA 1560, S-24R

STA 1580, S-24R

STA 1600, S-24R

STA 1620, S-24R

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ALERT ALERT
Group 2:

PART 5: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)

INSPECTIONS

1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE

1 at the Station (STA) and Stringer (S) locations that follow:

Station (STA) and Stringer (S) Qty Location

Location

Task Name

Inspect Fuselage Frame STA 560, S-25L 1 Forward Cargo

Compartment, Left Side STA 580, S-25L

STA 600, S-25L

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ALERT ALERT
Group 2:

PART 6: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)

INSPECTIONS

1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE

1 at the Station (STA) and Stringer (S) locations that follow:

Station (STA) and Stringer (S) Qty Location

Location

Task Name

Inspect Fuselage Frame STA 640, S-25L 1 Forward Cargo

Compartment, Left Side STA 660, S-25L

STA 680, S-25L

STA 700, S-25L

STA 720, S-25L

Aft Cargo Compartment,

Left Side

STA 1360, S-24L 1

STA 1380, S-24L

STA 1400, S-24L

STA 1420, S-24L

STA 1440, S-24L

STA 1460, S-24L

STA 1480, S-24L

Bulk Cargo Compartment,

Left Side

STA 1500, S-24L 1

STA 1520, S-24L

STA 1540, S-24L

STA 1560, S-24L

STA 1580, S-24L

STA 1600, S-24L

STA 1620, S-24L

Area Aft of Bulk Cargo

Compartment, Left Side

STA 1661, S-24L 1

STA 660, S-25R 1 Forward Cargo

Compartment, Right Side STA 680, S-25R

STA 700, S-25R

STA 720, S-25R

Area Aft of Bulk Cargo

Compartment, Right Side

STA 1661, S-24R 1

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ALERT ALERT
2. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE

2 at the Station (STA) and Stringer (S) locations that follow:

Station (STA) and Stringer (S) Qty Location

Location

Task Name

Inspect Fuselage Frame STA 620, S-25L 1 Forward Cargo

Compartment, Left Side

Group 2:

PART 7: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)

INSPECTIONS

1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE

1 at the Station (STA) and Stringer (S) locations that follow:

Station (STA) and Stringer (S) Qty Location

Location

Task Name

Main Equipment Center,

Left Side

Inspect Fuselage Frame STA 500, S-25L 1

STA 520, S-25L 1 Forward Cargo

Compartment, Left Side STA 540, S-25L

STA 740, S-25L

STA 760, S-25L

STA 780, S-25L

Main Equipment Center,

Right Side

STA 480, S-25R 1

STA 500, S-25R

STA 520, S-25R 1 Forward Cargo

Compartment, Right Side STA 740, S-25R

STA 760, S-25R

STA 780, S-25R

Export Controlled ECCN: 9E991 - BOEING

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ALERT ALERT
Group 3:

PART 8: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)

INSPECTIONS

1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE

1 at the Station (STA) and Stringer (S) locations that follow:

Station (STA) and Stringer (S) Qty Location

Location

Task Name

Main Equipment Center,

Left Side

Inspect Fuselage Frame STA 500, S-25L 1

STA 520, S-25L 1 Forward Cargo

Compartment, Left Side STA 540, S-25L

STA 560, S-25L

STA 580, S-25L

STA 600, S-25L

STA 660, S-25L

STA 680, S-25L

STA 700, S-25L

STA 720, S-25L

STA 740, S-25L

STA 760, S-25L

Aft Cargo Compartment,

Left Side

STA 1360, S-24L 1

STA 1380, S-24L

STA 1400, S-24L

STA 1420, S-24L

STA 1440, S-24L

STA 1460, S-24L

STA 1480, S-24L

Bulk Cargo Compartment,

Left Side

STA 1500, S-24L 1

STA 1520, S-24L

STA 660, S-25R 1 Forward Cargo

Compartment, Right Side STA 680, S-25R

STA 700, S-25R

STA 720, S-25R

STA 740, S-25R

STA 760, S-25R

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ALERT ALERT
Group 3:

PART 9: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)

INSPECTIONS

1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE

1 at the Station (STA) and Stringer (S) locations that follow:

Station (STA) and Stringer (S) Qty Location

Location

Task Name

Bulk Cargo Compartment,

Left Side

Inspect Fuselage Frame STA 1540, S-24L 1

STA 1560, S-24L

STA 1580, S-24L

STA 1600, S-24L

STA 1620, S-24L

Area Aft of Bulk Cargo

Compartment, Left Side

STA 1661, S-24L 1

STA 1701, S-24L

Aft Cargo Compartment,

Right Side

STA 1480, S-24R 1

Bulk Cargo Compartment,

Right Side

STA 1500, S-24R 1

STA 1520, S-24R

STA 1540, S-24R

STA 1560, S-24R

STA 1580, S-24R

STA 1600, S-24R

STA 1620, S-24R

Area Aft of Bulk Cargo

Compartment, Right Side

STA 1661, S-24R 1

STA 1701, S-24R

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ALERT ALERT
Group 4:

PART 10: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)

INSPECTIONS

1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE

1 at the Station (STA) and Stringer (S) locations that follow:

Station (STA) and Stringer (S) Qty Location

Location

Task Name

Inspect Fuselage Frame STA 520, S-25L 1 Forward Cargo

Compartment, Left Side STA 540, S-25L

STA 560, S-25L

STA 580, S-25L

STA 600, S-25L

STA 660, S-25L

STA 680, S-25L

STA 700, S-25L

STA 720, S-25L

STA 740, S-25L

STA 760, S-25L

STA 780, S-25L

Aft Cargo Compartment,

Left Side

STA 1360, S-24L 1

STA 1380, S-24L

STA 1400, S-24L

STA 1420, S-24L

STA 1440, S-24L

STA 1460, S-24L

STA 1480, S-24L

Bulk Cargo Compartment,

Left Side

STA 1500, S-24L 1

STA 1520, S-24L

STA 1540, S-24L

STA 1560, S-24L

STA 1580, S-24L

STA 1600, S-24L

STA 1620, S-24L

Area Aft of Bulk Cargo

Compartment, Left Side

STA 1661, S-24L 1

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ALERT ALERT
Station (STA) and Stringer (S) Qty Location

Location

Task Name

STA 660, S-25R Forward Cargo

Compartment, Right Side

1

STA 680, S-25R

STA 700, S-25R

STA 720, S-25R

STA 740, S-25R

STA 760, S-25R

STA 780, S-25R

Area Aft of Bulk Cargo

Compartment, Right Side

STA 1661, S-24R 1

Group 4:

PART 11: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)

INSPECTIONS

1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE

1 at the Station (STA) and Stringer (S) locations that follow:

Station (STA) and Stringer (S) Qty Location

Location

Task Name

Main Equipment Center,

Right Side

Inspect Fuselage Frame STA 440, S-25R 1

STA 480, S-25R

STA 500, S-25R

STA 520, S-25R 1 Forward Cargo

Compartment, Right Side

Group 5:

PART 12: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)

INSPECTIONS

1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE

1 at the Station (STA) and Stringer (S) locations that follow:

Station (STA) and Stringer (S) Qty Location

Location

Task Name

Inspect Fuselage Frame STA 560, S-25L 1 Forward Cargo

Compartment, Left Side STA 580, S-25L

STA 600, S-25L

Export Controlled ECCN: 9E991 - BOEING

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ALERT ALERT
Group 5:

PART 13: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)

INSPECTIONS

1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE

1 at the Station (STA) and Stringer (S) locations that follow:

Station (STA) and Stringer (S) Qty Location

Location

Task Name

Inspect Fuselage Frame STA 640, S-25L 1 Forward Cargo

Compartment, Left Side STA 660, S-25L

STA 680, S-25L

STA 700, S-25L

Aft Cargo Compartment,

Left Side

STA 1360, S-24L 1

STA 1380, S-24L

STA 1400, S-24L

STA 1420, S-24L

STA 1440, S-24L

STA 1460, S-24L

STA 1480, S-24L

Bulk Cargo Compartment,

Left Side

STA 1500, S-24L 1

STA 1520, S-24L

Area Aft of Bulk Cargo

Compartment, Left Side

STA 1661, S-24L 1

STA 660, S-25R 1 Forward Cargo

Compartment, Right Side STA 680, S-25R

STA 700, S-25R

Area Aft of Bulk Cargo

Compartment, Right Side

STA 1661, S-24R 1

2. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE

2 at the Station (STA) and Stringer (S) locations that follow:

Station (STA) and Stringer (S) Qty Location

Location

Task Name

Inspect Fuselage Frame STA 620, S-25L 1 Forward Cargo

Compartment, Left Side STA 720, S-25L

STA 720, S-25R 1 Forward Cargo

Compartment, Right Side

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ALERT ALERT
Group 5:

PART 14: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)

INSPECTIONS

1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE

1 at the Station (STA) and Stringer (S) locations that follow:

Station (STA) and Stringer (S) Qty Location

Location

Task Name

Main Equipment Center,

Left Side

Inspect Fuselage Frame STA 500, S-25L 1

STA 520, S-25L 1 Forward Cargo

Compartment, Left Side STA 540, S-25L

STA 740, S-25L

STA 760, S-25L

STA 780, S-25L

STA 780+20, S-25L

Bulk Cargo Compartment,

Left Side

STA 1540, S-24L 1

STA 1560, S-24L

STA 1580, S-24L

STA 1600, S-24L

STA 1620, S-24L

STA 740, S-25R 1 Forward Cargo

Compartment, Right Side STA 760, S-25R

STA 780, S-25R

STA 780+20, S-25R

Aft Cargo Compartment,

Right Side

STA 1480, S-24R 1

Bulk Cargo Compartment,

Right Side

STA 1500, S-24R 1

STA 1520, S-24R

STA 1540, S-24R

STA 1560, S-24R

STA 1580, S-24R

STA 1600, S-24R

STA 1620, S-24R

Export Controlled ECCN: 9E991 - BOEING

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Group 6:

PART 15: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)

INSPECTIONS

1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE

1 at the Station (STA) and Stringer (S) locations that follow:

Station (STA) and Stringer (S) Qty Location

Location

Task Name

Inspect Fuselage Frame STA 560, S-25L 1 Forward Cargo

Compartment, Left Side STA 580, S-25L

STA 600, S-25L

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Group 6:

PART 16: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)

INSPECTIONS

1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE

1 at the Station (STA) and Stringer (S) locations that follow:

Station (STA) and Stringer (S) Qty Location

Location

Task Name

Inspect Fuselage Frame STA 640, S-25L 1 Forward Cargo

Compartment, Left Side STA 660, S-25L

STA 680, S-25L

STA 700, S-25L

STA 720, S-25L

Aft Cargo Compartment,

Left Side

STA 1360, S-24L 1

STA 1380, S-24L

STA 1400, S-24L

STA 1420, S-24L

STA 1440, S-24L

STA 1460, S-24L

STA 1480, S-24L

Bulk Cargo Compartment,

Left Side

STA 1500, S-24L 1

STA 1520, S-24L

Area Aft of Bulk Cargo

Compartment, Left Side

STA 1661, S-24L 1

STA 660, S-25R 1 Forward Cargo

Compartment, Right Side STA 680, S-25R

STA 700, S-25R

STA 720, S-25R

Area Aft of Bulk Cargo

Compartment, Right Side

STA 1661, S-24R 1

2. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE

2 at the Station (STA) and Stringer (S) locations that follow:

Station (STA) and Stringer (S) Qty Location

Location

Task Name

Inspect Fuselage Frame STA 620, S-25L 1 Forward Cargo

Compartment, Left Side

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Group 6:

PART 17: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)

INSPECTIONS

1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE

1 at the Station (STA) and Stringer (S) locations that follow:

Station (STA) and Stringer (S) Qty Location

Location

Task Name

Main Equipment Center,

Left Side

Inspect Fuselage Frame STA 500, S-25L 1

STA 520, S-25L 1 Forward Cargo

Compartment, Left Side STA 540, S-25L

STA 740, S-25L

STA 760, S-25L

STA 780, S-25L

STA 780+20, S-25L

Bulk Cargo Compartment,

Left Side

STA 1540, S-24L 1

STA 1560, S-24L

STA 1580, S-24L

STA 1600, S-24L

STA 1620, S-24L

STA 740, S-25R 1 Forward Cargo

Compartment, Right Side STA 760, S-25R

STA 780, S-25R

STA 780+20, S-25R

Aft Cargo Compartment,

Right Side

STA 1480, S-24R 1

Bulk Cargo Compartment,

Right Side

STA 1500, S-24R 1

STA 1520, S-24R

STA 1540, S-24R

STA 1560, S-24R

STA 1580, S-24R

STA 1600, S-24R

STA 1620, S-24R

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Group 7:

PART 18: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)

INSPECTIONS

1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE

1 at the Station (STA) and Stringer (S) locations that follow:

Station (STA) and Stringer (S) Qty Location

Location

Task Name

Main Equipment Center,

Left Side

Inspect Fuselage Frame STA 500, S-25L 1

STA 520, S-25L 1 Forward Cargo

Compartment, Left Side STA 540, S-25L

STA 560, S-25L

STA 580, S-25L

STA 600, S-25L

STA 660, S-25L

STA 680, S-25L

STA 700, S-25L

STA 720, S-25L

STA 740, S-25L

STA 760, S-25L

Aft Cargo Compartment,

Left Side

STA 1360, S-24L 1

STA 1380, S-24L

STA 1400, S-24L

STA 1420, S-24L

STA 1440, S-24L

STA 1460, S-24L

STA 1480, S-24L

Bulk Cargo Compartment,

Left Side

STA 1500, S-24L 1

Area Aft of Bulk Cargo

Compartment, Left Side

STA 1661, S-24L 1

STA 660, S-25R 1 Forward Cargo

Compartment, Right Side STA 680, S-25R

STA 700, S-25R

STA 720, S-25R

STA 740, S-25R

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Station (STA) and Stringer (S) Qty Location

Location

Task Name

STA 760, S-25R

Area Aft of Bulk Cargo

Compartment, Right Side

STA 1661, S-24R 1

Group 7:

PART 19: FUSELAGE FRAMES - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)

INSPECTIONS

1. RC - Do detailed and HFEC inspections for cracks in the fuselage frame in accordance with FIGURE

1 at the Station (STA) and Stringer (S) locations that follow:

Station (STA) and Stringer (S) Qty Location

Location

Task Name

Bulk Cargo Compartment,

Left Side

Inspect Fuselage Frame STA 1520, S-24L 1

STA 1540, S-24L

STA 1560, S-24L

STA 1580, S-24L

STA 1600, S-24L

STA 1620, S-24L

Aft Cargo Compartment,

Right Side

STA 1480, S-24R 1

Bulk Cargo Compartment,

Right Side

STA 1500, S-24R 1

STA 1520, S-24R

STA 1540, S-24R

STA 1560, S-24R

STA 1580, S-24R

STA 1600, S-24R

STA 1620, S-24R

PART 20: CLOSE ACCESS

1. Close access to the fuselage frame inspection areas as follows:

a. Install kept cargo compartment insulation. Refer to 757 AMM 25-50-07 as an accepted

procedure.

b. Install kept cargo compartment sidewall linings. Refer to 757 AMM 25-50-02 as an accepted

procedure.

c. Close Main Equipment Center (MEC) access door 119BL. Refer to 757 AMM 06-41-00 as an

accepted procedure.

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d. Close up any areas that required additional work to gain access.

2. Put the airplane back to a serviceable condition.

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FIGURE 1: FUSELAGE FRAME - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)

INSPECTIONS

(SHEET 1 OF 5)

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FIGURE 1: FUSELAGE FRAME - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)

INSPECTIONS

(SHEET 2 OF 5)

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FIGURE 1: FUSELAGE FRAME - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)

INSPECTIONS

(SHEET 3 OF 5)

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FIGURE 1: FUSELAGE FRAME - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)

INSPECTIONS

(SHEET 4 OF 5)

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

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

Step Task Name Identification Qty More Data

1 Inspect FUSELAGE FRAME - - (a) (b) (c)

(a) Do a Detailed and High Frequency Eddy Current (HFEC) for cracks in accordance with 757 NDT Manual

Part 6, 51-00-01 or 757 NDT Manual Part 6, 51-00-19. HFEC inspection is to be done around the fasteners

and on the fuselage frame along the upper edge of the fail safe chord.

(b) For fuselage frame identification in Section 43, refer to 757-200 SRM 53-30-07, 757-200CB SRM 53-30-

07, 757-200PF SRM 53-30-07, 757-300 SRM 53-30-07.

(c) For fuselage frame identification in Section 46, refer to 757-200 SRM 53-60-07, 757-200CB SRM 53-60-

07, 757-200PF SRM 53-60-07, 757-300 SRM 53-60-07.

FIGURE 1: FUSELAGE FRAME - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)

INSPECTIONS

(SHEET 5 OF 5)

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This Figure applies only to: Group 1-2, 5-6.

FIGURE 2: FUSELAGE FRAME - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)

INSPECTIONS - SECTION 43

(SHEET 1 OF 5)

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FIGURE 2: FUSELAGE FRAME - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)

INSPECTIONS - SECTION 43

(SHEET 2 OF 5)

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FIGURE 2: FUSELAGE FRAME - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)

INSPECTIONS - SECTION 43

(SHEET 3 OF 5)

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FIGURE 2: FUSELAGE FRAME - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)

INSPECTIONS - SECTION 43

(SHEET 4 OF 5)

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

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

Step Task Name Identification Qty More Data

1 Inspect FUSELAGE FRAME - - (a) (b)

(a) Do a Detailed and High Frequency Eddy Current (HFEC) for cracks in accordance with 757 NDT Manual

Part 6, 51-00-01 or 757 NDT Manual Part 6, 51-00-19. HFEC inspection is to be done around the fasteners,

on the fuselage frame along the upper edge of the fail safe chord, and along edge of cargo net support

installation fitting.

(b) For fuselage frame identification in Section 43, refer to 757-200 SRM 53-30-07, 757-200CB SRM 53-30-

07, 757-200PF SRM 53-30-07, 757-300 SRM 53-30-07.

FIGURE 2: FUSELAGE FRAME - DETAILED AND HIGH FREQUENCY EDDY CURRENT (HFEC)

INSPECTIONS - SECTION 43

(SHEET 5 OF 5)

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This Appendix applies only to: Group 1.

APPENDIX A: SCOPE OF INSPECTION

(SHEET 1 OF 1)

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This Appendix applies only to: Group 2.

APPENDIX B: SCOPE OF INSPECTION

(SHEET 1 OF 1)

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This Appendix applies only to: Group 3.

APPENDIX C: SCOPE OF INSPECTION

(SHEET 1 OF 1)

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This Appendix applies only to: Group 4.

APPENDIX D: SCOPE OF INSPECTION

(SHEET 1 OF 1)

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This Appendix applies only to: Group 5.

APPENDIX E: SCOPE OF INSPECTION

(SHEET 1 OF 1)

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This Appendix applies only to: Group 6.

APPENDIX F: SCOPE OF INSPECTION

(SHEET 1 OF 1)

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This Appendix applies only to: Group 7.

APPENDIX G: SCOPE OF INSPECTION

(SHEET 1 OF 1)

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