Boeing ASB 767-53A0266: No revision named, text

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Show pages 25–36

Page 37Open in PDF

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 each airplane.

More DataQtyIdentificationNameTaskStep Six rivets on aft row of each of three splice plates. (a) (b) 18BACR15FT6D8CRivetInstall (New)1

(a) Refer to 767-200 SRM 51-40-02, 767-200SF SRM 51-40-02, 767-300 SRM 51-40-02, 767-300F SRM 51-40-02, 767-300BCF SRM 51-40-02 or 767-400 SRM 51-40-02 as an accepted procedure. Refer to 767-200 SRM 51-40-05, 767-200SF SRM 51-40-05, 767-300 SRM 51-40-05, 767-300F SRM 51-40-05, 767-300BCF SRM 51-40-05 or 767-400 SRM 51-40-05 for hole quality specifications.

(b) Alternative fastener installation in accordance with 767-200 SRM 51-40-03, 767-200SF SRM 51-40-03, 767-300 SRM 51-40-03, 767-300F SRM 51-40-03, 767-300BCF SRM 51-40-03 or 767-400 SRM 51-40- 03 is allowed. Also, installation of BACB30VT6K*X and BACC30BL6 in a transition fit hole is acceptable.

FIGURE 3: AFT PRESSURE BULKHEAD - PRESSURE CHORD SPLICE PLATES - FASTENER

Original Issue: April 20, 2015 767-53A0266 37 of 41 BOEING SERVICE BULLETIN 767-53A0266

ALERTALERT

Page 38OCROpen in PDF

BOEING SERVICE BULLETIN 767-53A0266

ALERT ALERT This Figure applies only to: Group 1; Group 2, Configuration 2; Group 4.

BULKHEAD WEB

1) 6 LOCATIONS STA 1582 B S-11L TO S-12L SKIN INBD

SPLICE PLATE (TYPICAL) S-11R _ TO S-12R FWD NOTE:

SOME AFFECTED AIRPLANE CONFIGURATIONS HAVE

SHORT STIFFENERS AT THE AFT PRESSURE BULKHEAD TO PRESSURE CHORD JOINT. S-24L SHORT STIFFENERS ARE NOT SHOWN FOR CLARITY.

FIGURE 4: AFT PRESSURE BULKHEAD - PRESSURE CHORD SPLICE PLATES - FASTENER

Page 39Open in PDF

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 each airplane.

More DataQtyIdentificationNameTaskStep Six rivets on aft row of each of four splice plates. (a) (b) 24BACR15FT6D8CRivetInstall (New)1

FIGURE 4: AFT PRESSURE BULKHEAD - PRESSURE CHORD SPLICE PLATES - FASTENER

Original Issue: April 20, 2015 767-53A0266 39 of 41 BOEING SERVICE BULLETIN 767-53A0266

ALERTALERT

Page 40Open in PDF

This Appendix applies only to: Group 2, Configuration 1; Group 3-4.

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.

DescriptionTitle FASTENER REMOVAL AND OPEN HOLE HFEC INSPECTION.PART 2 ANY CRACK FOUND IN THE AFT PRESSURE BULKHEAD WEB.CONDITION 1 NO CRACK FOUND IN THE AFT PRESSURE BULKHEAD WEB.CONDITION 2 APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE TABLE 1: AFT PRESSURE BULKHEAD WEB INSPECTIONS AT PRESSURE CHORD JOINT.

Original Issue: April 20, 2015 767-53A0266 40 of 41 BOEING SERVICE BULLETIN 767-53A0266

ALERTALERT

Page 41OCROpen in PDF

BOEING SERVICE BULLETIN 767-53A0266

ALERT ALERT This Appendix applies only to: Group 1; Group 2, Configuration 2.

1. The table below gives the description for the parts and conditions called out in the logic diagrams.

Title Description PART 2 FASTENER REMOVAL AND OPEN HOLE HFEC INSPECTION.

CONDITION 1 ANY CRACK FOUND IN THE AFT PRESSURE BULKHEAD WEB.

CONDITION 2 NO CRACK FOUND IN THE AFT PRESSURE BULKHEAD WEB.

WHICHEVER OCCURS LATER WITHIN 37,500 FLIGHT WITHIN 3,000 FLIGHT

CYCLES AFTER CYCLES AFTER THE

REPLACEMENT OF THE ORIGINAL ISSUE DATE OF

AFT PRESSURE BULKHEAD THIS SERVICE BULLETIN DO PART 2 CONDITION 1 CONDITION 2 NOT TO EXCEED 12,000

BEFORE FURTHER FLIGHT FLIGHT CYCLES

CONTACT THE BOEING COMPANY FOR REPAIR REPEAT PART 2

INSTRUCTIONS AND DO THE REPAIR 2406028 APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE TABLE 2: AFT PRESSURE BULKHEAD WEB INSPECTIONS AT PRESSURE CHORD JOINT.