### Commercial **Airplanes** 

# 767 Service Bulletin **ALERT Number: 767-53A0268**  Original Issue: April 01, 2015 ATA System: 5363 **SUBJECT:** FUSELAGE - Section 48 - STA 1582 Aft Pressure Bulkhead Web Inspection at Web to Pressure Chord Joint 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. 9E991 ECCN: 

## BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET Copyright © 2015 Boeing. Unpublished Work. All Rights Reserved. Treatment of this document and its content is governed by contract with Boeing. Rights to use this document are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The Boeing Company. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.

Original Issue: April 01, 2015 767-53A0268 1 of 35 3.0Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 01, 2015 767-53A0268 2 of 35 **BOEING SERVICE BULLETIN 767-53A0268 ALERT**  **ALERT**

BLANK PAGE**Table of Contents** Summary...................................................... 5 1. PLANNING INFORMATION........................................ 9 A. Effectivity................................................ 9 1. Airplanes............................................. 9 2. Spares Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 1. Existing Data:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 2. Data Supplied with this Service Bulletin:. . . . . . . . . . . . . . . . . . . . . . . . . . . 22 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 22 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 22 M. Software Accomplishment Summary. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 C. Parts Necessary for Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 1. Kits/Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 23 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 4. Parts Removed and Not Replaced. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 23 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 FIGURE 1: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE AFT PRESSURE BULKHEAD WEB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE TABLE 1: INSPECTION FOR ANY CRACK AT STA 1582 AFT PRESSURE BULKHEAD [Group 2, Configuration 1]. . . . . 30 APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE TABLE 2: INSPECTION FOR ANY CRACK AT STA 1582 AFT PRESSURE BULKHEAD [Group 3, Configuration 1]. . . . . 32 APPENDIX C: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE TABLE 3: INSPECTION FOR ANY CRACK AT STA 1582 AFT PRESSURE BULKHEAD [Group 1; Group 2-3, Configuration 2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 01, 2015 767-53A0268 3 of 35 **BOEING SERVICE BULLETIN 767-53A0268 ALERT**  **ALERT**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 01, 2015 767-53A0268 4 of 35 **BOEING SERVICE BULLETIN 767-53A0268 ALERT**  **ALERT**

BLANK PAGE

### Commercial **Airplanes** 

# 767 Service Bulletin **ALERT Summary**  **Number: 767-53A0268** Original Issue: April 01, 2015 ATA System: 5363 **SUBJECT:** FUSELAGE - Section 48 - STA 1582 Aft Pressure Bulkhead Web Inspection at Web to Pressure Chord Joint 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** Widespread Fatigue Damage (WFD) analysis of the 767, as required by 14 CFR 26.21(b), has resulted in the conclusion that existing MPD Section 9, Airworthiness Limitation Item (ALI) inspection program is not sufficient to preclude the occurrence of WFD in the aft pressure bulkhead to pressure chord joint as the airplane ages. The aft pressure bulkhead web to pressure chord joint has multiple adjacent identical details which have the potential for Multi-Site Damage (MSD) and the potential for WFD. 14 CFR 26.21 requires evaluation of such designs for the potential for WFD and implementation of the appropriate service actions to ensure that WFD is precluded before the Limit of Validity (LOV). Boeing has not received any reports of cracks in the bulkhead web to pressure chord joint. Accomplishment of the inspection described in this service bulletin will enable detection and repair of cracks if they should occur, at the STA 1582 Aft Pressure Bulkhead Web to Pressure Chord joint. If Widespread Fatigue cracking is not found and repaired, the cracks can rapidly link up and can result in possible rapid decompression and loss of structural integrity. The aft pressure bulkhead web to pressure chord joint affected by this service bulletin has been determined to be structure that is susceptible to WFD. Boeing Service Related Problem (SRP) 767-SRP-53-0469 is related to this service bulletin. Boeing 767 MPD 622T001-9 Section 9, SSI 53-80-l01A is related to this service bulletin. Boeing Service Bulletin 767-53A0087 is related to this service bulletin. Boeing Service Bulletin 767-53A0139 is related to this service bulletin. This table is provided to operators for planning purposes only. Refer to the applicable sections for more information.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 01, 2015 767-53A0268 5 of 35**Reference Affected**  **Planning Data** Paragraph 1.A.2., Spares Affected No Spares Affected Paragraph 1.E., Compliance and Paragraph 1.F., Approval Yes AD Related Paragraph 1.H., Weight and Balance Changes No Weight and Balance Change Paragraph 1.I., Electrical Load Data No Electrical Load Changed Paragraph 1.K., Publications Affected No Publications Affected Paragraph 1.K., Publications Affected No Airplane Flight Operations Affected (Flight CrewOperations Manual and/or FAA Approved Airplane Flight Manual) Paragraph 2.C.1., Kits/Parts No Kits/Parts Required Paragraph 2.C.2., Parts and Materials Supplied by the Operator No Operator Supplied Parts/Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin No Special Tooling Required

**ACTION** Get access to the forward side of the aft pressure bulkhead at STA 1582. Remove the aft galley and the main water tank(s) in the lower lobe. Do a Surface High Frequency Eddy Current (HFEC) inspection of all visible locations of the aft pressure bulkhead web at the aft/inboard row of fasteners common to the aft pressure bulkhead web and pressure chord around the entire circumference of the pressure chord for any crack. If any crack is found, contact Boeing to get instructions for the repair for this service bulletin, and do the work instructed by Boeing. If no crack is found, repeat the inspection. **EFFECTIVITY** All 767-200 and 767-300 Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s). **COMPLIANCE** The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Federal Aviation Administration (FAA) Airworthiness Directive AD 2004-05-16 is related to this service bulletin. The effective date of AD 2004-05-16 is April 13, 2004. Federal Aviation Administration (FAA) Airworthiness Directive AD 2012-09-08 is related to this service bulletin. The effective date of AD 2012-09-08 is June 18, 2012. Federal Aviation Administration (FAA) Airworthiness Directive AD 2014-14-04 is related to this service bulletin. The effective date of AD 2014-14-04 is September 5, 2014. This service bulletin affects SSI 53-80-I01A of 767 MPD 622T001-9 Section 9, which is mandated by AD 2014-14-04. All other MPD inspections outside the of the affected area are not affected and must continue.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 01, 2015 767-53A0268 6 of 35 **BOEING SERVICE BULLETIN 767-53A0268 ALERT**  **ALERT**Refer to Paragraph 1.E., Compliance. **INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are not available for the inspection given in this service bulletin. **MANPOWER Elapsed Hours**  **Total Task Hours Airplanes**  17.25 55.00 Group 1, 2 and 3 Airplanes with one water tank removal required 17.75 57.00 Group 1, 2 and 3 Airplanes with two water tank removals required Refer to Paragraph 1.G., Manpower. **MATERIAL INFORMATION** None.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 01, 2015 767-53A0268 7 of 35 **BOEING SERVICE BULLETIN 767-53A0268 ALERT**  **ALERT**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 01, 2015 767-53A0268 8 of 35 **BOEING SERVICE BULLETIN 767-53A0268 ALERT**  **ALERT**

### Commercial **Airplanes** 

# 767 Service Bulletin **ALERT Number: 767-53A0268**  Original Issue: April 01, 2015 ATA System: 5363 **SUBJECT:** FUSELAGE - Section 48 - STA 1582 Aft Pressure Bulkhead Web Inspection at Web to Pressure Chord Joint 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 applicable to all 767-200 and 767-300 Airplanes in 3 Group(s). The Variable Numbers and Group Information for the applicable airplanes is given below. Refer to Service Bulletin Index D624T001 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. **NOTE:** The Variable Number table below includes all affected airplanes up to Line Number 1068. Affected airplanes after Line Number 1068 will be added to the service bulletin's MyBoeingFleet.com (MBF) "get effectivity" result when they are added to the MBF Fleet Profile Page.
**DESCRIPTION CONFIGURATION**  **GROUP** Airplanes Line Numbers 1-175 with replaced aft pressure bulkhead in accordance with SB 767-53A0139. - 1

Airplanes Line Numbers 176-423.

- 2 Airplanes with original production aft pressure bulkhead installed. 1 Airplanes with aft pressure bulkhead replaced in accordance with a Boeing Organization Design Authorization (ODA) approval via FAA Form 8100-9. 2

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 01, 2015 767-53A0268 9 of 35**DESCRIPTION CONFIGURATION**  **GROUP** Airplanes Line Numbers 424 and on (767-200/300 only).

- 3 Airplanes with original production aft pressure bulkhead installed. 1 Airplanes with aft pressure bulkhead replaced in accordance with a Boeing Organization Designation Authorization (ODA) approval via FAA Form 8100-9. 2

Airplane Models: 767-200, 767-300 **Group Variable Number**  1 VA001 - VA020 1 VA301 - VA315 1 VA501 - VA526 2 VA527 - VA530 1 VA701 - VA712 2 VA713 - VA719 1 VA801 - VA810 1 VB001 - VB002 1 VB051 - VB055 1 VB101 - VB125 1 VB201 - VB202 1 VB251 - VB253 1 VB281 - VB284 1 VB301 - VB302 1 VB321 - VB324 2 VB325 - VB332 1 VB371 - VB373 1 VB401 3 VB441 - VB444 1 VE001 - VE002 2 VE003 1 VE021 - VE023 1 VE041 - VE043

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 01, 2015 767-53A0268 10 of 35 **BOEING SERVICE BULLETIN 767-53A0268 ALERT**  **ALERT Group**  **Variable Number** 1 VE061 - VE068 2 VE069 1 VE083 - VE084 2 VE085 - VE086 1 VE101 - VE103 2 VE104 1 VE116 - VE117 2 VE118 1 VE121 - VE123 2 VE124 - VE126 1 VE141 - VE142 2 VE143 - VE151 3 VE152 2 VE171 - VE172 2 VF001 - VF002 2 VF041 - VF042 2 VF051 2 VF061 - VF062 2 VF071 - VF072 2 VF091 - VF093 2 VF101 - VF102 2 VF161 3 VF162 3 VF171 - VF172 3 VF180 - VF184 3 VF251 1 VK001 - VK004 2 VK005 - VK011 3 VK012 - VK016 2 VK021 - VK022 1 VK031 - VK037 2 VK038 - VK053 3 VK054 - VK056

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 01, 2015 767-53A0268 11 of 35 **BOEING SERVICE BULLETIN 767-53A0268 ALERT**  **ALERT Group**  **Variable Number** 2 VK081 - VK099 3 VK100 - VK113 2 VK131 - VK133 2 VK141 - VK142 3 VK143 - VK148 3 VK161 - VK164 3 VK171 3 VK181 3 VK186 1 VL001 2 VL002 - VL006 1 VL011 3 VL701 - VL703 3 VL751 - VL755 3 VL806 - VL807 3 VL871 - VL873 3 VL891 - VL900 3 VL911 - VL914 3 VL931 - VL932 3 VL941 2 VN001 - VN019 3 VN020 - VN041 2 VN051 - VN062 3 VN063 - VN064 2 VN081 - VN092 3 VN093 - VN099 2 VN111 - VN124 3 VN125 - VN127 2 VN130 - VN132 3 VN133 - VN137 2 VN151 - VN158 2 VN163 - VN168 2 VN171 - VN173

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 01, 2015 767-53A0268 12 of 35 **BOEING SERVICE BULLETIN 767-53A0268 ALERT**  **ALERT Group**  **Variable Number** 3 VN174 2 VN191 - VN193 3 VN194 - VN198 2 VN211 - VN212 2 VN221 - VN224 3 VN225 2 VN231 - VN234 2 VN241 3 VN242 - VN243 2 VN251 - VN259 3 VN260 - VN276 2 VN291 3 VN292 - VN293 2 VN301 - VN306 3 VN307 - VN314 2 VN371 - VN372 2 VN376 2 VN381 3 VN382 - VN388 3 VN421 - VN427 3 VN436 2 VN471 - VN472 2 VN491 - VN496 3 VN497 - VN513 2 VN531 - VN532 2 VN536 - VN537 2 VN541 - VN542 3 VN546 - VN547 2 VN551 3 VN556 - VN557 3 VN561 - VN562 2 VN631 - VN633 3 VN634 - VN638

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 01, 2015 767-53A0268 13 of 35 **BOEING SERVICE BULLETIN 767-53A0268 ALERT**  **ALERT Group**  **Variable Number** 2 VN651 - VN652 3 VN653 - VN658 2 VN671 - VN672 3 VN676 2 VN681 - VN683 3 VN684 - VN691 2 VN731 3 VN732 2 VN751 - VN753 3 VN791 - VN792 3 VN811 - VN813 3 VN921 - VN922 3 VN931 - VN936 3 VN951 - VN953 3 VN966 - VN972 3 VR051 - VR060 3 VR081 3 VR084 3 VR086 - VR089 3 VR106 - VR109 3 VR401 3 VR421 - VR423 3 VR426 3 VR441 3 VR461 3 VR471 - VR472 3 VS051 - VS056 3 VS061 3 VS066 - VS070 3 VS073 - VS078 3 VS091 - VS104 3 VS111 - VS113 3 VS131 - VS133

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 01, 2015 767-53A0268 14 of 35 **BOEING SERVICE BULLETIN 767-53A0268 ALERT**  **ALERT Group**  **Variable Number** 3 VS136 - VS137 3 VS176 - VS177 3 VS186 - VS187 3 VS196 - VS203 3 VS206 - VS208 3 VS211 3 VS216 - VS217 3 VS231 3 VS246 - VS248 3 VS261 - VS263 3 VS266 - VS274 3 VS291 - VS293 3 VS301 - VS303 3 VS306 - VS311 3 VS316 3 VS321 - VS324 3 VS331 - VS333 3 VS336 - VS337 3 VS366 - VS367 3 VS381 - VS382 3 VS391 - VS392 3 VS401 3 VS426 - VS428 3 VS466 - VS472 3 VS486 3 VS496 - VS497 3 VS506 - VS507 3 VS526 3 VS546 - VS549 3 VS701 - VS736 3 VS751 - VS759 3 VS821 - VS825 3 VS841 - VS844

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 01, 2015 767-53A0268 15 of 35 **BOEING SERVICE BULLETIN 767-53A0268 ALERT**  **ALERT Group**  **Variable Number** 3 VS861 3 VS881 - VS883 3 VS891 3 VS896 3 VS901 - VS912 3 VS916 3 VS921 - VS928 3 VS931 - VS933 3 VS941 3 VS951 - VS954 3 VS961 - VS969 3 VS971 - VS977 3 VS981 - VS984 3 VT001 - VT013 3 VT021 3 VT031 - VT033 3 VV001 2. Spares Affected None. **B. Concurrent Requirements** None. **C. Reason** Widespread Fatigue Damage (WFD) analysis of the 767, as required by 14 CFR 26.21(b), has resulted in the conclusion that existing MPD Section 9, Airworthiness Limitation Item (ALI) inspection program is not sufficient to preclude the occurrence of WFD in the aft pressure bulkhead to pressure chord joint as the airplane ages. The aft pressure bulkhead web to pressure chord joint has multiple adjacent identical details which have the potential for Multi-Site Damage (MSD) and the potential for WFD. 14 CFR 26.21 requires evaluation of such designs for the potential for WFD and implementation of the appropriate Service Actions to ensure that WFD is precluded before the Limit of Validity (LOV). Boeing has not received any reports of cracks in the bulkhead web to pressure chord joint. Accomplishment of the inspection described in this service bulletin will enable detection and repair of cracks if they should occur, at the STA 1582 Aft Pressure Bulkhead Web to Pressure Chord joint. If Widespread Fatigue cracking is not found and repaired, the cracks can rapidly link up and can result in possible rapid decompression and loss of structural integrity.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 01, 2015 767-53A0268 16 of 35 **BOEING SERVICE BULLETIN 767-53A0268 ALERT**  **ALERT**The aft pressure bulkhead web to pressure chord joint affected by this service bulletin has been determined to be structure that is susceptible to WFD. Boeing Service Related Problem (SRP) 767-SRP-53-0469 is related to this service bulletin. Boeing 767 MPD 622T001-9 Section 9, SSI 53-80-l01A is related to this service bulletin. Boeing Service Bulletin 767-53A0087 is related to this service bulletin. Boeing Service Bulletin 767-53A0139 is related to this service bulletin. **D. Description** Get access to the forward side of the aft pressure bulkhead at STA 1582. Remove the aft galley and the main water tank(s) in the lower lobe. Do a Surface High Frequency Eddy Current (HFEC) inspection of all visible locations of the aft pressure bulkhead web at the aft/inboard row of fasteners common to the aft pressure bulkhead web and pressure chord around the entire circumference of the pressure chord for any crack. If any crack is found, contact Boeing to get instructions for the repair for this service bulletin, and do the work instructed by Boeing. If no crack is found, repeat the inspection. The work in this service bulletin is done in the maintenance zone(s) given below.
**Affected Maintenance Zones Zone**  **Model** 165, 166, 251, 252, 253, 254 767-200, 767-300 **E. Compliance** The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Federal Aviation Administration (FAA) Airworthiness Directive AD 2004-05-16 is related to this service bulletin. The effective date of AD 2004-05-16 is April 13, 2004. Federal Aviation Administration (FAA) Airworthiness Directive AD 2012-09-08 is related to this service bulletin. The effective date of AD 2012-09-08 is June 18, 2012. Federal Aviation Administration (FAA) Airworthiness Directive AD 2014-14-04 is related to this service bulletin. The effective date of AD 2014-14-04 is September 5, 2014. This service bulletin affects SSI 53-80-I01A of 767 MPD 622T001-9 Section 9, which is mandated by AD 2014-14-04. All other MPD inspections outside the of the affected area are not affected and must continue. Logic diagrams showing compliance tasks and compliance times are included as an aid in APPENDIX A, APPENDIX B and APPENDIX C. Do the required actions in accordance with Paragraph 3. Accomplishment Instructions.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 01, 2015 767-53A0268 17 of 35 **BOEING SERVICE BULLETIN 767-53A0268 ALERT**  **ALERT Group 2, Configuration 1:**  **Table 1: Surface High Frequency Eddy Current Inspection for Any Crack at STA 1582 Aft Pressure Bulkhead**  **Repeat Interval (Not to Exceed)**  **Compliance Time (Whichever Occurs Later)**  **Action Condition** 

- Within 3,000flight cycles after the original issue date ofthis service bulletin. Before 50,000total flight cycles. Do PART 2: SURFACEHIGH FREQUENCY EDDY CURRENT INSPECTION OF THE AFT PRESSURE BULKHEAD WEB, for any crack. (a) (b) All Airplanes.

- Before further flight. Contact Boeing to get in- structions for the repair for this service bulletin,and do the work instructed by Boeing. CONDITION 1: ANY CRACK FOUND

3,000 flight cycles.

- Repeat PART 2: HIGH FREQUENCY EDDY CURRENT INSPECTIONOF THE AFT PRESSURE BULKHEAD WEB, for any crack. (a) (b) CONDITION 2: NO CRACK FOUND

(a) It is not necessary to do inspections in accordance with this service bulletin in areas where existing repairs approved by the Boeing ODA via FAA 8100-9 form cover the affected inspection areas. Damage Tolerance Inspection instructions specified in approval for existing repairs must continue. Inspection outside of the repaired area must continue in accordance with this service bulletin. (b) Inspection of the web in accordance with this service bulletin does not require removal of permanently attached structure such as stiffeners, splice plates, or clips. **Group 3, Configuration 1: Table 2: Surface High Frequency Eddy Current Inspection for Any Crack at STA 1582 Aft Pressure**  **Bulkhead Repeat Interval**  **(Not to Exceed) Compliance Time (Whichever**  **Occurs Later) Action**  **Condition**

- Within 3,000flight cycles after the original issue date ofthis service bulletin. Before 62,000total flight cycles. Do PART 2: SURFACEHIGH FREQUENCY EDDY CURRENT INSPECTION OF THE AFT PRESSURE BULKHEAD WEB, for any crack. (a) (b) All Airplanes.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 01, 2015 767-53A0268 18 of 35 **BOEING SERVICE BULLETIN 767-53A0268 ALERT**  **ALERT Group 3, Configuration 1:**  **Table 2: Surface High Frequency Eddy Current Inspection for Any Crack at STA 1582 Aft Pressure Bulkhead**  **Repeat Interval (Not to Exceed)**  **Compliance Time (Whichever Occurs Later)**  **Action Condition** 

- Before further flight. Contact Boeing to get in- structions for the repair for this service bulletin,and do the work instructed by Boeing. CONDITION 1: ANY CRACK FOUND

4,400 flight cycles.

- Repeat PART 2: SUR-FACE HIGH FREQUENCY EDDY CURRENT INSPECTION OF THE AFT PRESSURE BULKHEAD WEB, for any crack. (a) (b) CONDITION 2: NO CRACK FOUND

(a) It is not necessary to do inspections in accordance with this service bulletin in areas where existing repairs approved by the Boeing ODA via FAA 8100-9 form cover the affected inspection areas. Damage Tolerance Inspection instructions specified in approval for existing repairs must continue. Inspections outside of the repaired area must continue in accordance with this service bulletin. (b) Inspection of the web in accordance with this service bulletin does not require removal of permanently attached structure such as stiffeners, splice plates, or clips. **Group 1; Group 2-3, Configuration 2: Table 3: Surface High Frequency Current Inspection for Any Crack at STA 1582 Aft Pressure Bulkhead**  **Repeat Interval (Not to Exceed)**  **Compliance Time (Whichever Occurs Later)**  **Action Condition** 

- Within 3,000flight cycles after the original issue date ofthis service bulletin. Within 37,500flight cycles after aft pressurebulkhead replacement. Do PART 2: SURFACEHIGH FREQUENCY EDDY CURRENT INSPECTION OF THE AFT PRESSURE BULKHEAD WEB, for any crack. (a) (b) All Airplanes.

- Before further flight. Contact Boeing to get in- structions for the repair for this service bulletin,and do the work instructed by Boeing. CONDITION 1: ANY CRACK FOUND

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 01, 2015 767-53A0268 19 of 35 **BOEING SERVICE BULLETIN 767-53A0268 ALERT**  **ALERT Group 1; Group 2-3, Configuration 2:**  **Table 3: Surface High Frequency Current Inspection for Any Crack at STA 1582 Aft Pressure Bulkhead Repeat Interval**  **(Not to Exceed) Compliance Time (Whichever**  **Occurs Later) Action**  **Condition** 4,400 flight cycles.

- Repeat PART 2: SUR-FACE HIGH FREQUENCY EDDY CURRENT INSPECTION OF THE AFT PRESSURE BULKHEAD WEB, for any crack. (a) (b) CONDITION 2: NO CRACK FOUND

(a) It is not necessary to do inspections in accordance with this service bulletin in areas where existing repairs approved by the Boeing ODA via FAA 8100-9 form cover the affected inspection areas. Damage Tolerance Inspection instructions specified in approval for existing repairs must continue. Inspection outside of the repaired region must continue as instructed per this service bulletin (b) Inspection of the web in accordance with this service bulletin does not require removal of permanently attached structure such as stiffeners, splice plates, or clips. **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. The Manager of the FAA Seattle Aircraft Certification Office (SACO) approves the accomplishment of the inspections defined in this Service Bulletin (SB) along with the corresponding compliance times specified in Paragraph 1.E., Compliance of this SB, Original Issue, as an Alternative Method Of Compliance (AMOC) to the inspections defined in D622T001-DTR Structural Significant Item (SSI) 53-80-I01A and Section 9 of the Maintenance Planning Document (MPD) D622T001-9, required by paragraphs (i) and (k) of Airworthiness Directive (AD) 2014-14-04. This AMOC only applies to the areas inspected in accordance with this SB. All other inspections outside of this SB inspection region are not affected and must continue. All provisions of AD 2014-14-04 that are not specifically referenced in this paragraph remain fully applicable and must be complied with. The Manager of the FAA SACO approves the accomplishment of the inspections defined in this SB along with the corresponding compliance times specified in Paragraph 1.E., Compliance of this SB, Original Issue, as an AMOC to the inspections defined in SB 767-53A0087 required by paragraphs (a) and (b) of AD 2004-05-16. This AMOC only applies to the areas inspected in accordance with this SB. All other inspections outside of this SB inspection region are not affected and must continue.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 01, 2015 767-53A0268 20 of 35 **BOEING SERVICE BULLETIN 767-53A0268 ALERT**  **ALERT**In Addition, the Manager of the FAA SACO approves the accomplishment of the inspections defined in this SB along with the corresponding compliance times specified in Paragraph 1.E., Compliance of this SB, Original Issue, as an AMOC to the inspections defined in SB 767-53A0139 required by paragraph (h) of AD 2012-09-08. This AMOC only applies to the areas inspected in accordance with this SB. All other inspections outside of this SB inspection region are not affected and must continue. **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, 2 AND 3 AIRPLANES (WITH ONE WATER TANK REMOVAL REQUIRED): Elapsed Hours**  **Task Hours Number of Persons**  **Task** 4.75 19.00 4 Open Access 7.00 14.00 2 FIGURE 1 5.50 22.00 4 Close Access 17.25 55.00 TOTAL FOR EACH AIRPLANE (a) (a) The manpower estimate does not include repairs, if necessary. **GROUP 1, 2 AND 3 AIRPLANES (WITH TWO WATER TANK REMOVALS REQUIRED): Elapsed Hours**  **Task Hours Number of Persons**  **Task** 5.00 20.00 4 Open Access 7.00 14.00 2 FIGURE 1 5.75 23.00 4 Close Access 17.75 57.00 TOTAL FOR EACH AIRPLANE (a) (a) The manpower estimate does not include repairs, if necessary. **H. Weight and Balance Changes** None. **I. Electrical Load Data** Not changed.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 01, 2015 767-53A0268 21 of 35 **BOEING SERVICE BULLETIN 767-53A0268 ALERT**  **ALERT J. References**  1. Existing Data: a. Boeing Service Bulletin 767-53A0087, 767-53A0139 b. Boeing Service Letter 767-SL-51-036 c. Boeing Service Related Problem (SRP) 767-SRP-53-0469 d. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2004-05-16, 2004-05-16 , 2012-09-08, 2014-14-04 e. Service Bulletin Index D624T001 f. 767 Aircraft Maintenance Manual (AMM) 25-31-04, 25-52-01, 25-52-03, 38-11-01, 38-11-64, 38-32-11 g. 767 Maintenance Planning Data (MPD) 622T001-9Section 9 h. 767 Non-Destructive Testing (NDT) Manual Part 6, 51-00-01, Part 6, 51-00-19, Part 6, 53-80-05 2. Data Supplied with this Service Bulletin: None. 3. Installation Drawings Used in the Preparation of this Service Bulletin: None. **K. Publications Affected** 1. Publications: None. 2. Damage Tolerance Based Structural Inspections: Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This service bulletin 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 01, 2015 767-53A0268 22 of 35 **BOEING SERVICE BULLETIN 767-53A0268 ALERT**  **ALERT 2. MATERIAL INFORMATION**  **A. Material - Price and Availability** None. **B. Industry Support Information** Boeing warranty remedies are not available for the inspection and/or repair procedures given in this service bulletin. **C. Parts Necessary for Each Airplane** 1. Kits/Parts None. 2. Parts and Materials Supplied by the Operator None. 3. Parts Modified and Reidentified None. 4. Parts Removed and Not Replaced None. **D. Parts Necessary to Change Spares** None. **E. Special Tooling - Price and Availability** None. **F. Special Tooling Necessary to do this Service Bulletin** No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine operator tool supply to make sure all necessary tools are available.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 01, 2015 767-53A0268 23 of 35 **BOEING SERVICE BULLETIN 767-53A0268 ALERT**  **ALERT**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 01, 2015 767-53A0268 24 of 35 **BOEING SERVICE BULLETIN 767-53A0268 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 767 Structural Repair Manual, Chapter 51. — Values for airframe maintenance tasks are included in Chapter 20 of 767 Aircraft Maintenance Manual (AMM). — Values for electrical maintenance tasks are included in Chapter 20 of Standard Wiring Practices Manual (SWPM). — Values for engine maintenance tasks are included in Chapter 70 of 767 Aircraft Maintenance Manual (AMM). — Non-standard torque values for maintenance tasks are included in the applicable installation step.

4. 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. 5. Boeing Service Letter 767-SL-51-036, 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. 6. Refer to APPENDIX A, APPENDIX B and APPENDIX C for logic diagram(s). Logic diagrams are provided as an aid 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 01, 2015 767-53A0268 25 of 35 **BOEING SERVICE BULLETIN 767-53A0268 ALERT**  **ALERT**7. 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. 8. 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. 9. 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. 10. Use of colors in Figures is based on guidance from the ATA e-Business Program (ATA) iSpec 2200. 11. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS are in Paragraph 1.E., Compliance. 12. 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 and steps indented under an RC step must be done to comply with the AD. Alternative procedures for steps not identified with RC can be used if the RC steps and indented 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. **B. WORK INSTRUCTIONS** 1. Do PART 1: OPEN ACCESS. 2. RC - Do PART 2: SURFACE HIGH FREQUENCY EDDY CURRENT INSPECTION OF THE AFT PRESSURE BULKHEAD WEB, for any crack. a. CONDITION 1: ANY CRACK FOUND (1) RC - Contact Boeing to get instructions for the repair for this service bulletin and do the work instructed by Boeing. b. CONDITION 2: NO CRACK FOUND (1) RC - Repeat PART 2: SURFACE HIGH FREQUENCY EDDY CURRENT INSPECTION OF THE AFT PRESSURE BULKHEAD WEB, for any crack. 3. Do PART 3: CLOSE ACCESS. 4. Put the airplane back to a serviceable condition. **PART 1: OPEN ACCESS** 1. Remove and keep the aft galley. Refer to 767 AMM 25-31-04 as an accepted procedure.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 01, 2015 767-53A0268 26 of 35 **BOEING SERVICE BULLETIN 767-53A0268 ALERT**  **ALERT**2. Remove and keep insulation from around splice plates that splice pressure chords on the aft pressure bulkhead in the main deck compartment. Refer to 767 AMM 25-52-03 as an accepted procedure. 3. Remove and keep the end wall in the bulk cargo compartment. Refer to 767 AMM 25-52-01 as an accepted procedure. 4. Remove and keep the right side potable water tank. If installed, remove and keep the left side potable water tank. Refer to 767 AMM 38-11-01 as an accepted procedure. 5. If necessary for access, remove and keep the waste tank. On some affected airplanes, the waste tanks are installed forward of the affected area. On these airplanes, waste tank removal is not necessary for access to the aft pressure bulkhead. Refer to 767 AMM 38-32-11 as an accepted procedure. 6. Remove and keep insulation from around splice plates that splice pressure chords on the aft pressure bulkhead in the bulk cargo compartment. Refer to 767 AMM 25-52-03 as an accepted procedure. **PART 2: SURFACE HIGH FREQUENCY EDDY CURRENT INSPECTION OF THE AFT PRESSURE BULKHEAD WEB**  1. Do a surface HFEC Inspection of the aft pressure bulkhead web for any crack at the aft most fastener row at all visible locations common to the pressure chord in accordance with FIGURE 1. **PART 3: CLOSE ACCESS** 1. Install insulation to splice plates that splice pressure chords on the aft pressure bulkhead in the bulk cargo compartment. Refer to 767 AMM 25-52-03 as an accepted procedure. 2. If removed, install the waste tank. Refer to 767 AMM 38-32-11 as an accepted procedure. 3. Install the right side potable water tank. If removed, install the left side potable water tank. Refer to 767 AMM 38-11-64 as an accepted procedure. 4. Install the end wall in the bulk cargo compartment. Refer to 767 AMM 25-52-01 as an accepted procedure. 5. Install insulation to splice plates that splice pressure chords on the aft pressure bulkhead in the main deck compartment. Refer to 767 AMM 25-52-03 as an accepted procedure. 6. Install the aft galley. Refer to 767 AMM 25-31-04 as an accepted procedure.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 01, 2015 767-53A0268 27 of 35 **BOEING SERVICE BULLETIN 767-53A0268 ALERT**  **ALERT FIGURE 1: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE AFT PRESSURE BULKHEAD**  **WEB (SHEET 1 OF 2)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 01, 2015 767-53A0268 28 of 35 **BOEING SERVICE BULLETIN 767-53A0268 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.

**More Data Qty**  **Identification Name**  **Task Step**  (a) (b) (c) (d) (e)

- - Bulkhead Web Inspect 1 (a) Do a Surface HFEC Inspection for any crack in accordance with 767 NDT Manual Part 6, 51-00-01, 767 NDT Manual Part 6, 51-00-19 or 767 NDT Manual Part 6, 53-80-05. (b) Inspect all visible locations of web around the entire bulkhead circumference. (c) Temporarily pull back insulation in area of inspection. (d) It is not necessary to do inspections in accordance with this service bulletin in areas where existing repairs approved by the Boeing ODA via FAA 8100-9 form cover the affected inspection areas. Damage Tolerance Inspection instructions specified in approval for existing repairs must continue. Inspection outside of the repaired region must continue as instructed per this service bulletin. (e) Inspection of the web in accordance with this service bulletin does not require removal of permanently attached structure such as stiffeners, splice plates, or clips.

**FIGURE 1: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE AFT PRESSURE BULKHEAD WEB**  **(SHEET 2 OF 2)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 01, 2015 767-53A0268 29 of 35 **BOEING SERVICE BULLETIN 767-53A0268 ALERT**  **ALERT This Appendix applies only to: Group 2, Configuration 1.**  Logic diagrams are provided as an aid only. Information contained in Paragraph 1.E., Compliance is the primary source for compliance times. Information contained in Paragraph 3.B., Work Instructions is the primary source for tasks required for compliance. 1. The table below gives the description for the parts and conditions called out in the logic diagrams. **Description Table Description**  **Title** SURFACE HIGH FREQUENCY EDDY CURRENT INSPECTION OF AFT PRESSURE BULKHEAD WEB. PART 2

ANY CRACK FOUND. CONDITION 1 NO CRACK FOUND. CONDITION 2 2. The table below gives the description for the flag notes called out in the logic diagram. **Flag Notes Description**  **Flag Note Letter** It is not necessary to do inspections in accordance with this service bulletin in areas where existing repairs approved by the Boeing ODA via FAA 8100- 9 form cover the affected inspection areas. Damage Tolerance Inspection instructions specified in approval for existing repairs must continue. Inspection outside of the repaired area must continue in accordance with this service bulletin. (a)

Inspection of the web in accordance with this service bulletin does not require removal of permanently attached structure such as stiffeners, splice plates, or clips. (b)

**APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE TABLE 1: INSPECTION FOR ANY CRACK AT STA 1582 AFT PRESSURE BULKHEAD**  **(SHEET 1 OF 2)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 01, 2015 767-53A0268 30 of 35 **BOEING SERVICE BULLETIN 767-53A0268 ALERT**  **ALERT APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE TABLE 1: INSPECTION FOR ANY**  **CRACK AT STA 1582 AFT PRESSURE BULKHEAD (SHEET 2 OF 2)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 01, 2015 767-53A0268 31 of 35 **BOEING SERVICE BULLETIN 767-53A0268 ALERT**  **ALERT This Appendix applies only to: Group 3, Configuration 1.**  Logic diagrams are provided as an aid only. Information contained in Paragraph 1.E., Compliance is the primary source for compliance times. Information contained in Paragraph 3.B., Work Instructions is the primary source for tasks required for compliance. 1. The table below gives the description for the parts and conditions called out in the logic diagrams. **Description Table Description**  **Title** SURFACE HIGH FREQUENCY EDDY CURRENT INSPECTION OF AFT PRESSURE BULKHEAD WEB. PART 2

ANY CRACK FOUND. CONDITION 1 NO CRACK FOUND. CONDITION 2 2. The table below gives the description for the flag notes called out in the logic diagram. **Flag Notes Description**  **Flag Note Letter** It is not necessary to do inspections in accordance with this service bulletin in areas where existing repairs approved by the Boeing ODA via FAA 8100- 9 form cover the affected inspection areas. Damage Tolerance Inspection instructions specified in approval for existing repairs must continue. Inspection outside of the repaired area must continue in accordance with this service bulletin. (a)

Inspection of the web in accordance with this service bulletin does not require removal of permanently attached structure such as stiffeners, splice plates, or clips. (b)

**APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE TABLE 2: INSPECTION FOR ANY CRACK AT STA 1582 AFT PRESSURE BULKHEAD**  **(SHEET 1 OF 2)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 01, 2015 767-53A0268 32 of 35 **BOEING SERVICE BULLETIN 767-53A0268 ALERT**  **ALERT APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE TABLE 2: INSPECTION FOR ANY**  **CRACK AT STA 1582 AFT PRESSURE BULKHEAD (SHEET 2 OF 2)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 01, 2015 767-53A0268 33 of 35 **BOEING SERVICE BULLETIN 767-53A0268 ALERT**  **ALERT This Appendix applies only to: Group 1; Group 2-3, Configuration 2.**  Logic diagrams are provided as an aid only. Information contained in Paragraph 1.E., Compliance is the primary source for compliance times. Information contained in Paragraph 3.B., Work Instructions is the primary source for tasks required for compliance. 1. The table below gives the description for the parts and conditions called out in the logic diagrams. **Description Table Description**  **Title** SURFACE HIGH FREQUENCY EDDY CURRENT INSPECTION OF AFT PRESSURE BULKHEAD WEB. PART 2

ANY CRACK FOUND. CONDITION 1 NO CRACK FOUND. CONDITION 2 2. The table below gives the description for the flag notes called out in the logic diagram. **Flag Notes Description**  **Flag Note Letter** It is not necessary to do inspections in accordance with this service bulletin in areas where existing repairs approved by the Boeing ODA via FAA 8100- 9 form cover the affected inspection areas. Damage Tolerance Inspection instructions specified in approval for existing repairs must continue. Inspection outside of the repaired area must continue in accordance with this service bulletin. (a)

Inspection of the web in accordance with this service bulletin does not require removal of permanently attached structure such as stiffeners, splice plates, or clips. (b)

**APPENDIX C: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE TABLE 3: INSPECTION FOR ANY CRACK AT STA 1582 AFT PRESSURE BULKHEAD**  **(SHEET 1 OF 2)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 01, 2015 767-53A0268 34 of 35 **BOEING SERVICE BULLETIN 767-53A0268 ALERT**  **ALERT APPENDIX C: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE TABLE 3: INSPECTION FOR ANY**  **CRACK AT STA 1582 AFT PRESSURE BULKHEAD (SHEET 2 OF 2)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 01, 2015 767-53A0268 35 of 35 **BOEING SERVICE BULLETIN 767-53A0268 ALERT**  **ALERT**