Aviation Partners Boeing Alert Service Bulletin AP757-53-001

AVIATION PARTNERS BOEING SERVICE BULLETIN 2811 S 102nd Street, Suite 200 Seattle, WA 98168

(206) 830-7699

Original Issue: May 22, 2017 AP757-53-001 Revision 2: October 22, 2019 Page i Aviation Partners Boeing Proprietary ALERT NUMBER: AP757-53-001 Revision Transmittal Sheet Original Issue: May 22, 2017 Revision 2 October 22, 2019 ATA SYSTEM: 5360 SUBJECT: FUSELAGE – Section 46 – Body Station 1640 Fuselage Frame Inspection This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION Federal Aviation Administration (FAA) Airworthiness Directive AD 2018-06-07 is related to this service bulletin.

Effects of this Revision on airplanes on which Revision 1 was previously done:

NOTE: PART instructions correspond to the instructions contained in Boeing Service Bulletin 757 -53A0108, Revision 1, or later.

Group Condition Action Groups 1, 3 Airplanes that have accomplished OPTION 1 PART 2 inspections in Service Bulletin AP757-53-001 Revision 1 Issue with no crack found.

Do PART 6 inspection for any crack, nick or gouge.

Do PART 2, PART 7 and PART 8 inspection for any crack.

Airplanes that have accomplished OPTION 2 PART 3 inspections in Service Bulletin AP757-53-001 Revision 1 Issue with no crack found.

Do PART 6 inspection for any crack, nick or gouge.

Do PART 3, PART 7 and PART 8 inspection for any crack.

Airplanes that have accomplished the inspections in accordance with Service Bulletin AP757-53-001 Revision 1 Issue and have installed a repair or local frame replacement that does not contain a reinforcement repair or repair splice member between S-11 and S-16 and the repair or replacement is Boeing Organization Designation Authorization (ODA) approved via an FAA form 8100-9.

Do PART 6 inspection for any crack, nick or gouge.

Do PART 2, PART 7 and PART 8 inspection for any crack.

OR Do PART 3, PART 7 and PART 8 inspection for any crack.

Airplanes that have accomplished the inspections in accordance with Service Bulletin AP757-53-001 Revision 1 Issue and have installed a repair or local frame replacement that contains a reinforcement repair or repair splice member between S-11 and S-16.

Contact The Boeing Company for alternative inspection(s) and do the inspection(s) and any corrective actions as applicable.

Airplanes that have accomplished the inspections in accordance with Service Bulletin AP757-53-001 Revision 1 Issue and have installed a repair or local frame replacement that is not Boeing Organization Designation Authorization (ODA) approved.

Contact The Boeing Company for alternative inspection(s) and do the inspection(s) and any corrective actions as applicable.

AVIATION PARTNERS BOEING SERVICE BULLETIN AP757-53-001 Original Issue: May 22, 2017 AP757-53-001 Revision 2: October 22, 2019 Page ii Aviation Partners Boeing Proprietary

REASON FOR REVISION This revision contains planned administrative changes coordinated with the FAA.

This revision is sent to provide the following:

 Added a reference to Airworthiness Directive AD 2018-06-07  Added new instructions to do a one-time inspection of maintenance records for any repairs or local frame replacements installed as a result of damage found during inspections in Revision 1 of service bulletin AP757-

53-001.

 Added a one-time Detailed Inspection of the frame inner chord forward return flange edge for cracks, nicks and gouges.

 Added initial and repetitive High Frequency Eddy Current (HFEC) inspections around the fasteners of the frame inner chord, and of the inner chord forward return flange radius.

 Changed Low Frequency Eddy Current (LFEC) inspections for six fasteners in the inner chord from LFEC to HFEC inspections, and the inspection direction is changed from the outboard side of the frame inner chord to the inboard side of the frame inner chord.

 Added LFEC inspections of the frame inner chord around the uppermost fastener common to the frame inner chord long strap (Groups 1 and 3) These sections were changed:

1. Summary, added new detailed and HFEC inspections. Reference to stringers S -11 and S -16, was S -11 and S-14.

2. In Paragraph 1.A., Added Group 1 Configuration 3, Added Group 3 Configuration 3 . Revised group description.

3. In Paragraph 1.B., Revised Boeing Service Bulletin revision callout, is Revision 1, was Original Issue.

4. In Paragraph 1.C., Reason, updated paragraph to add new crack information and reason for revision statement added.

5. In Paragraph 1.D., Description, added details on HFEC/LFEC inspections. Added table for effects of revision on airplanes on which revision 1 was previously done.

6. In Paragraph 1.E., Compliance, changed existing compliance Tables and added new compliance Tables to r eflect revised repeat intervals. A dded Part - Title Index table, and added paragraph to reference Airworthiness Directive (AD).

7. In Paragraph 1.F., Revised approval statement, and added new AMOC statement.

8. In Paragraph 1.G., Manpower, revised manpower for figures 1-4. Added manpower for figures 13-18.

9. In Paragraph 1.J., References, Added Airworthiness Directive AD 2018 -06-07, Boeing Service Related Problem 757-SRP-53-0594, and Multi-Operator Message MOM-MOM-17-0037-01C.

10. In Paragraph 3.A., General Information, revised reference to Boeing Service Bulletin revision.

11. In Paragraph 3.B., Work Instructions, revised reference to Boeing Service Bulletin revision . Added Group 1 Configuration 3, Added Group 3 Configuration 3.

(Reference ECR-0001974)

REVISION HISTORY Original Issue: May 22, 2017 Revision 1: June 21, 2017 Revision 2: October 22, 2019

AVIATION PARTNERS BOEING SERVICE BULLETIN 2811 S 102nd Street, Suite 200 Seattle, WA 98168

(206) 830-7699

Original Issue: May 22, 2017 AP757-53-001 Revision 2: October 22, 2019 Page 1 of 41 Aviation Partners Boeing Proprietary ALERT NUMBER: AP757-53-001 Original Issue: May 22, 2017 Revision 2 October 22, 2019 ATA SYSTEM: 5360 SUBJECT: FUSELAGE – Section 46 – Body Station 1640 Fuselage Frame Inspection

PROPRIETARY NOTICE

The data contained hereon and herein is proprietary to Aviation Partners Boeing. Neither this data nor the data contained herein shall be reproduced, used or disclosed to others without the written authorization of Aviation Partners Boeing.

EXPORT CONTROLLED TECHNOLOGY

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AVIATION PARTNERS BOEING SERVICE BULLETIN AP757-53-001

Original Issue: May 22, 2017 AP757-53-001 Revision 2: October 22, 2019 Page 2 of 41 Aviation Partners Boeing Proprietary

APB DOCUMENT FEEDBACK FORM To provide feedback on this document to APB for corrections or improvements, please complete the form below and fax or email to the attention of APB Liaison Engineering at:

Fax: +1 (206) 767-0535 Email: leng@aviationpartners.com Airline Name: ______________________________________________ Contact Name: ______________________________________________ Phone Number: ______________________________________________ Email Address: ______________________________________________ Airplane Model-Type: ______________________________________________ Document Number: ______________________________________________ Document Revision: ______________________________________________ Document Title: ______________________________________________ Chapter-Section- Subject: ______________________________________________ Page: ______________________________________________ Page Date: ______________________________________________ Description of Change:

(Include additional sheets as required)

Attachments: ______________________________________________

AVIATION PARTNERS BOEING SERVICE BULLETIN AP757-53-001

Original Issue: May 22, 2017 AP757-53-001 Revision 2: October 22, 2019 Page 3 of 41 Aviation Partners Boeing Proprietary Table of Contents

Revision Transmittal Sheeti

APB DOCUMENT FEEDBACK FORM2

Table of Contents3

Summary4

1. PLANNING INFORMATION7

A. Effectivity7

1. Airplanes7

2. Spares Affected8

B. Concurrent Requirements8

C. Reason8

D. Description9

E. Compliance10

F. Approval37

G. Manpower37

H. Weight and Balance Changes38

I. Electrical Load Data38

J. References38

1. Existing Data:38

2. Data Supplied with this Service Bulletin:38

3. Installation Drawings Used in the Preparation of this Service Bulletin:38

K. Publications Affected38

1. Publications38

2. Damage Tolerance Based Structural Inspections:39

L. Interchangeability and Intermixability of Parts39

M. Software Accomplishment Summary39

2. MATERIAL INFORMATION40

A. Material - Price and Availability40

B. Industry Support Information40

C. Parts Necessary for Each Airplane40

1. Kits/Parts40

2. Parts and Materials Supplied by the Operator:40

3. Parts Modified and Re-identified40

4. Parts Removed and Not Replaced40

D. Parts Necessary to Change Spares40

E. Special Tooling – Price Availability40

F. Special Tooling Necessary to do this Service Bulletin40

3. ACCOMPLISHMENT INSTRUCTIONS41

A. GENERAL INFORMATION41

B. WORK INSTRUCTIONS41

AVIATION PARTNERS BOEING SERVICE BULLETIN 2811 S 102nd Street, Suite 200 Seattle, WA 98168

(206) 830-7699

Original Issue: May 22, 2017 AP757-53-001 Revision 2: October 22, 2019 Page 4 of 41 Aviation Partners Boeing Proprietary ALERT NUMBER: AP757-53-001 Summary Original Issue: May 22, 2017 Revision 2 October 22, 2019 ATA SYSTEM: 5360 SUBJECT: FUSELAGE – Section 46 – Body Station 1640 Fuselage Frame Inspection

THIS DOCUMENT 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 DOCUMENT TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE NEW OWNER.

CONCURRENT REQUIREMENTS Company Service Bulletin Description The Boeing Company 757-53A0108, Revision 1, or later approved revisions published on myboeingfleet.

Get access to the Body Station (STA) 1640 fuselage frame, between stringers S-11 and S-16, on the left and right side of the airplane. Do High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for any crack in the STA 1640 fuselage frame, between stringers S-11 and S-16, on the left and right side of the airplane.

BACKGROUND This service bulletin is sent to provide instructions to do High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for any crack in the fuselage frame at Body Station (STA) 1640, between stringers S-11 and S-16, on the left and right side of the airplane. If the work given in this service bulletin is not done, such fatigue cracking could adversely affect the structural integrity of the airplane.

One operator reported a crack finding, at 24,607 total fli ght cycles, in the STA 1640 fuselage frame at stringer S - 14R, adjacent to door stop number 5. The crack had fully severed the inner chord and web of the STA 1640 fuselage frame. The cracking is attributed to fatigue caused by flight loads and pressurizatio n of the fuselage.

During inspections in Service Bulletin 757-53A0108 Original Issue an operator found a STA 1640 frame with a crack starting from the third fastener below the S -14 intercostal on the right side. The crack was approximately 3 inches long and had grown into an insulation stud hole in the web near the outer chord. The crack was not in the 757- 53A0108 Original Issue inspection area. There have also been instances of cracks found growing out of the fastener holes in the inner chord in the aft direction, towards the web away from the original inspection areas.

AVIATION PARTNERS BOEING SERVICE BULLETIN AP757-53-001 Original Issue: May 22, 2017 AP757-53-001 Revision 2: October 22, 2019 Page 5 of 41 Aviation Partners Boeing Proprietary In addition, after the original issue of this service bulletin, there have been a total of 23 cracks reported in the STA 1640 frames resulting from SB 757 -53A0108 Original Issue inspections. These reports were from airplanes with 20,500 to 39,850 flight cycles, and with 62,100 to 89,150 flight hours. The crack lengths reported ranged from 0.10 inch to a completely severed frame with some reporting cracking in the outer chord.

Boeing has determined that the existing inspection programs are not sufficient to detect these cracks because most of the STA 1640 fuselage frame is obscured by adjacent structure. Accomplishment of this service bulletin, together with Boeing Service Bulletin 757-53A0108, will improve detection of cracking in the STA 1640 fuselage frame and make sure that any crack is found and repaired before the crack grows to a critical length.

Boeing Fleet Team Digest (FTD) 757 FTD 53-16001 is related to this service bulletin.

Boeing Service Related Problem (SRP) 757-SRP-53-0525 and 757-SRP-53-0594 are related to this service bulletin.

Multi-Operator Message (MOM) MOM-MOM-17-0037-01C 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 AD Related Yes Paragraph 1.E., Compliance and Paragraph

1.F., Approval Weight and Balance Change No Paragraph 1.H., Weight and Balance Changes Electrical Load Changed No Paragraph 1.I., Electrical Load Data Publications Affected No Paragraph 1.K., Publications Affected Airplane Flight Operations Affected (Flight Crew Operations Manual and/or FAA Approved Airplane Flight Manual) No Paragraph 1.K., Publications Affected Kits/Parts Required No Paragraph 2.C.1., Kits/Parts Operator Supplied Parts/Material No Paragraph 2.C.2., Parts and Materials Supplied by the Operator Special Tooling Required No Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin

ACTION Get access to the Body Station (STA) 1640 fuselage frame, between stringers S -11 and S-16, on the left and right side of the airplane. Do the one time general visual inspection for repairs and the one-time detailed inspection for any crack, nick or gouge in the STA 1640 fuselage frame, on the left and right side of the airplane. If any repair, crack, nick or gouge is found, contact The Boeing Company for alternate inspections, repair s and any corrective actions as applicable. If no crack, nick or gouge is found, do the High Frequency Eddy Current (HFEC) inspections and Low Frequency Eddy Current (LFEC) for any crack in the STA 1640 fuselage frame, between stringers S-11 and S-16, on the left and right side of the airplane. If any crack is found, contact The Boeing Company for repair instructions and do the repair, and repeat the HFEC and LFEC inspections in unrepaired areas at the times given in Paragraph 1.E., Compliance. If no crack is found, repeat the HFEC and LFEC inspections at the times given in Paragraph 1.E., Compliance.

AVIATION PARTNERS BOEING SERVICE BULLETIN AP757-53-001 Original Issue: May 22, 2017 AP757-53-001 Revision 2: October 22, 2019 Page 6 of 41 Aviation Partners Boeing Proprietary

EFFECTIVITY All 757-200 and 757-300 Airplane(s) with STC ST01518SE installed APB Blended Winglets or Scimitar Blended Winglets. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s).

COMPLIANCE Federal Aviation Administration (FAA) Airworthiness Directive AD 2018-06-07 is related to this service bulletin.

The effective date of AD 2018-06-07 is May 03, 2018.

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.

AVIATION PARTNERS BOEING SERVICE BULLETIN 2811 S 102nd Street, Suite 200 Seattle, WA 98168

(206) 830-7699

Original Issue: May 22, 2017 AP757-53-001 Revision 2: October 22, 2019 Page 7 of 41 Aviation Partners Boeing Proprietary ALERT NUMBER: AP757-53-001 Original Issue: May 22, 2017 Revision 2 October 22, 2019 ATA SYSTEM: 5360 SUBJECT: FUSELAGE – Section 46 – Body Station 1640 Fuselage Frame Inspection

1. PLANNING INFORMATION A. Effectivity

1. Airplanes This service bulletin is applicable to 757-200 with Blended Winglets or Scimitar Blended Winglets, and 757-300 with Blended Winglets (Refer to STC ST01518SE). The following airplane group, configuration, and description are the same as Boeing service bulletin 757-53A0108.

GROUP CONFIGURATION DESCRIPTION 1 - 757-200 airplanes with APB Blended Winglets or Scimitar Blended Winglets, that have a long inner chord strap at the Body Station (STA) 1640 fuselage frame.

1 757-200 airplanes with less than 32,000 total flight cycles at the revision 1 issue date of this service bulletin, that have not accomplished AP757-53-001 R1 inspections as of the revision 2 date of this service bulletin.

2 757-200 airplanes with 32,000 total flight cycles or more at the revision 1 issue date of this service bulletin, that have not accomplished AP757-53-001 R1 inspections as of the revision 2 date of this service bulletin.

3 757-200 airplanes that have accomplished AP757-53-001 revision 1 as of the revision 2 date of this service bulletin.

3 - 757-300 airplanes with APB Blended Winglets, that have a long inner chord strap at the Body Station (STA) 1640 fuselage frame.

1 757-300 airplanes, with less than 16,000 total flight cycles at the revision 1 issue date of this service bulletin, that have not accomplished AP757-53-001 R1 inspections as of the revision 2 date of this service bulletin.

2 757-300 airplanes, with 16,000 total flight cycles or more at the revision 1 issue date of this service bulletin, that have not

AVIATION PARTNERS BOEING SERVICE BULLETIN AP757-53-001 Original Issue: May 22, 2017 AP757-53-001 Revision 2: October 22, 2019 Page 8 of 41 Aviation Partners Boeing Proprietary

GROUP CONFIGURATION DESCRIPTION accomplished AP757-53-001 R1 inspections as of the revision 2 date of this service bulletin.

3 757-300 airplanes that have accomplished AP757-53-001 revision 1 as of the revision 2 date of this service bulletin.

2. Spares Affected None B. Concurrent Requirements The service bulletin listed below must be done at the same time as this service bulletin:

Company Service Bulletin Description The Boeing Company 757-53A0108, Revision 1, or later approved revisions published on myboeingfleet.

Get access to the Body Station (STA) 1640 fuselage frame, between stringers S-11 and S-16, on the left and right side of the airplane. Do High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for any crack in the STA 1640 fuselage frame, between stringers S-11 and S-16, on the left and right side of the airplane.

C. Reason This service bulletin is sent to provide instructions to do High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for any crack in the fuselage frame at Body Station (STA) 1640, between stringers S -11 and S-16, on the left and right side of the airplane. If the work given in this service bulletin is not done, such fatigue cracking could adversely affect the structural integrity of the airplane.

One operator reported a crack finding, at 24,607 total flight cycles, in the STA 1640 fuselage frame at stringer S-14R, adjacent to door stop number 5. The crack had fully severed the inner chord and web of the STA 1640 fuselage frame. The cracking is attributed to fatigue caused by flight loads and pressurization of the fuselage.

During inspections in Service Bulletin 757-53A0108 Original Issue an operator found the STA 1640 frame with a crack starting from the third fastener below the S -14 intercostal on the right side. The crack was approximately 3 inches long and had grown into an insulation stud hole in the web near the outer chord.

The crack was not in the 757 -53A0108 Original Issue inspection area. There have also been instances of cracks found growing out of the fastener holes in the inner chord in the aft direction, towards the web away from the original inspection areas.

Boeing has determined that the existing inspection programs are not sufficient to detect these cracks because most of the STA 1640 fuselage frame is obscured by adjacent structure. Accomplishment of this service bulletin, together wi th Boeing Service Bulletin 757 -53A0108, will improve detection of cracking in the STA 1640 fuselage frame and make sure that any crack is found and repaired before the crack grows to a critical length.

Boeing Fleet Team Digest (FTD) 757 FTD 53-16001 is related to this service bulletin.

Boeing Service Related Problem (SRP) 757-SRP-53-0525 is related to this service bulletin.

Multi-Operator Message (MOM) MOM-MOM-17-0037-01C is related to this service bulletin.

AVIATION PARTNERS BOEING SERVICE BULLETIN AP757-53-001 Original Issue: May 22, 2017 AP757-53-001 Revision 2: October 22, 2019 Page 9 of 41 Aviation Partners Boeing Proprietary Revision 2 is sent to provide the following:

– Added a reference to Airworthiness Directive AD 2018-06-07 – Added new instructions to do a one time inspection of maintenance records for any repairs or local frame replacements installed as a result of damage found during inspections in the original issue of service bulletin 757-53A0108.

– Added a one time Detailed Inspection of the frame inner chord forward return flange edge for cracks, nicks and gouges.

– Added initial and repetitive High Frequency Eddy Current (HFEC) inspections around the fasteners of the frame inner chord, and of the inner chord forward return flange radius.

– Changed Low Frequency Eddy Current (LFEC) inspections for six fasteners in the inner chord from LFEC to HFEC inspections, and the inspection direction is changed from the outboard side of the frame inner chord to the inboard side of the frame inner chord.

– Added LFEC inspections of the frame inner chord around the uppermost fastener common to the frame inner chord long strap (Groups 1-3) D. Description Get access to the Body Station (STA) 1640 fuselage frame, between stringers S -11 and S-16, on the left and right side of the airplane. Do the one time general visual inspection for repairs and the one-time detailed inspection for any crack, nick or gouge in the STA 1640 fuselage frame, on the left and right side of the airplane. If any repair, crack, nick or gouge is found, contact The Boeing Company for alternate inspections, repairs and any corrective actions as applicable. If no crack, nick or gouge is found, do the High Frequency Eddy Current (HFEC) inspections and Low Frequency Eddy Current (LFEC) for any crack in the STA 1640 fuselage frame, between stringers S -11 and S-16, on the left and right side of the airplane. If any crack is found, contact The Boeing Company for repair instructions and do the repair, and repeat the HFEC and LFEC inspections in unrepaired areas at the times given in Paragraph 1.E., Compliance. If no crack is found, repeat the HFEC and LFEC inspections at the times given in Paragraph 1.E., Compliance.

Effects of this Revision on airplanes on which Revision 1 was previously done:

NOTE: PART instructions correspond to the instructions contained in Boeing Service Bulletin 757- 53A0108, Revision 1, or later.

Group Condition Action Groups 1, 3 Airplanes that have accomplished OPTION 1 PART 2 inspections in Service Bulletin AP757-53- 001 Revision 1 Issue with no crack found.

Do PART 6 inspection for any crack, nick or gouge.

Do PART 2, PART 7 and PART 8 inspection for any crack.

Airplanes that have accomplished OPTION 2 PART 3 inspections in Service Bulletin AP757-53- 001 Revision 1 Issue with no crack found.

Do PART 6 inspection for any crack, nick or gouge.

Do PART 3, PART 7 and PART 8 inspection for any crack.

Airplanes that have accomplished the inspections in accordance with Service Bulletin AP757-53-001 Revision 1 Issue and have installed a repair or local frame replacement that does not contain a reinforcement repair or repair splice member between S-11 and S-16 and the repair or replacement is Boeing Organization Designation Authorization (ODA) approved via an FAA form 8100-9.

Do PART 6 inspection for any crack, nick or gouge.

Do PART 2, PART 7 and PART 8 inspection for any crack.

OR Do PART 3, PART 7 and PART 8 inspection for any crack.

AVIATION PARTNERS BOEING SERVICE BULLETIN AP757-53-001 Original Issue: May 22, 2017 AP757-53-001 Revision 2: October 22, 2019 Page 10 of 41 Aviation Partners Boeing Proprietary Group Condition Action Airplanes that have accomplished the inspections in accordance with Service Bulletin AP757-53-001 Revision 1 Issue and have installed a repair or local frame replacement that contains a reinforcement repair or repair splice member between S-11 and S-16.

Contact The Boeing Company for alternative inspection(s) and do the inspection(s) and any corrective actions as applicable Airplanes that have accomplished the inspections in accordance with Service Bulletin AP757-53-001 Revision 1 Issue and have installed a repair or local frame replacement that is not Boeing Organization Designation Authorization (ODA) approved.

Contact The Boeing Company for alternative inspection(s) and do the inspection(s) and any corrective actions as applicable

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

Group 1:

Affected Maintenance Zones Model Zone 757-200 with APB Blended Winglets or Scimitar Blended Winglets 251, 252 Group 3:

Affected Maintenance Zones Model Zone 757-300 with APB Blended Winglets 251, 252 E. Compliance Federal Aviation Administration (FAA) Airworthiness Directive AD 2018-06-07 is related to this service bulletin. The effective date of AD 2018-06-07 is May 03, 2018.

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

Logic diagrams showing compliance tasks and compliance times are included as an aid in APPENDIX A, APPENDIX B, APPENDIX E, and APPENDIX F of Boeing Service Bulletin 757-53A0108. Compliance tasks, compliance times, and repeat intervals are given in this service bulletin.

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.

CONDITION refers to the STA 1640 frame CONDITION of either or both Left Side and/or Right Side frames. Both side frames must be in compliance but may be under different CONDITIONS at the same time on any given airplane.