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

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Show pages 13–24

Page 25Open in PDF

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 The following parts or materials are necessary to do the change in this service bulletin. Parts and materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine operator part and material supply to make sure all necessary parts and materials are available.

Group 2, Configuration 1; Group 3:

NotesNameQTYPart Number / Specification -Rivet18BACR15FT6D8C Group 1; Group 2, Configuration 2; Group 4:

NotesNameQTYPart Number / Specification -Rivet24BACR15FT6D8C

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.

Original Issue: April 20, 2015 767-53A0266 25 of 41 BOEING SERVICE BULLETIN 767-53A0266

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Page 26Open in PDF

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.

Original Issue: April 20, 2015 767-53A0266 26 of 41 BOEING SERVICE BULLETIN 767-53A0266

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Page 27Open in PDF

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).

4. Use the approved fastener, process and material substitutions in accordance with SRM Chapter 51.

5. If the length of any fastener specified in this service bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. Refer to SOPM 20-50-01 for alternate full threaded fasteners (screws) needed for installation in this service bulletin.

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.

7. 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.

Original Issue: April 20, 2015 767-53A0266 27 of 41 BOEING SERVICE BULLETIN 767-53A0266

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Page 28Open in PDF

8. Refer to Appendices A and B for logic diagrams. 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.

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. Use of colors in Figures is based on guidance from the ATA e-Business Program (ATA) iSpec 2200.

13. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS are in Paragraph 1.E., Compliance.

14. 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.

B. WORK INSTRUCTIONS

1. Do PART 1: OPEN ACCESS.

2. RC - Do PART 2: FASTENER REMOVAL AND OPEN HOLE HFEC INSPECTION.

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

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

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

(1) RC - Repeat PART 2: FASTENER REMOVAL AND OPEN HOLE HFEC INSPECTION.

3. Do PART 3: FASTENER INSTALLATION.

4. Do PART 4: CLOSE ACCESS.

5. Put the airplane back to a serviceable condition.

Original Issue: April 20, 2015 767-53A0266 28 of 41 BOEING SERVICE BULLETIN 767-53A0266

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Page 29Open in PDF

PART 1: OPEN ACCESS

1. For passenger airplanes only:

a. Remove and keep the aft galley. Refer to 767 AMM 25-31-04 as an accepted procedure.

2. For freighter airplanes (including Boeing Converted Freighters) only:

a. Remove and keep the cargo lining panels from the aft pressure bulkhead in the main deck cargo compartment. Refer to 767 AMM 25-59-01 as an accepted procedure.

3. Remove and keep insulation from around splice plates that splice pressure chords on the aft pressure bulkhead in the main deck cargo compartment. Refer to 767 AMM 25-59-05 as an accepted procedure.

4. Remove and keep the end wall in the bulk cargo compartment. Refer to 767 AMM 25-52-01 as an accepted procedure.

5. For passenger airplanes only:

a. 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.

b. 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.

WARNING: MAKE SURE THAT PERSONNEL AND EQUIPMENT ARE CLEAR OF THE HORIZONTAL STABILIZER AND ELEVATOR SURFACES BEFORE MOVING THE STABILIZER.

INJURY TO PERSONNEL AND DAMAGE TO EQUIPMENT COULD OCCUR.

7. Position the horizontal stabilizer to neutral and deactivate controls. Refer to 767 AMM 27-41-00 as an accepted procedure.

WARNING: DO NOT STAND ON ACCESS DOOR 312AR. THE WEIGHT OF PERSONNEL COULD

CAUSE THE SPRING LOADED LATCH TO RELEASE, AND PERSONNEL MAY BE INJURED BY FALLING THROUGH THE OPENING.

8. Open access door 312AR for access to the aft side of the aft pressure bulkhead. Use a suitable platform or cover over the access door while working inside the tail section.

PART 2: FASTENER REMOVAL AND OPEN HOLE HFEC INSPECTION CAUTION: TO PREVENT ANY MOVEMENT OF THE PRESSURE DOME, PERFORM PART 2 ON ONE SPLICE PLATE AT A TIME.

Original Issue: April 20, 2015 767-53A0266 29 of 41 BOEING SERVICE BULLETIN 767-53A0266

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Page 30Open in PDF

IF DRILLING OF FASTENERS IS REQUIRED, HOLD STEEL SHEETS TO THOSE FASTENERS ON THE AFT SIDE OF THE AFT PRESSURE BULKHEAD.

1. Group 2, Configuration 1; Group 3:

Remove the aft row of fasteners from splice plates that splice pressure chords and do open hole HFEC inspections for any crack in the aft pressure bulkhead web in accordance with FIGURE 1.

2. Group 1; Group 2, Configuration 2; Group 4:

Remove the aft row of fasteners from splice plates that splice pressure chords and do open hole HFEC inspections for any crack in the aft pressure bulkhead web in accordance with FIGURE 2.

PART 3: FASTENER INSTALLATION

1. Group 2, Configuration 1; Group 3:

Install the aft row of fasteners on splice plates that splice pressure chords in accordance with FIGURE 3.

2. Group 1; Group 2, Configuration 2; Group 4:

Install the aft row of fasteners on splice plates that splice pressure chords in accordance with FIGURE 4.

PART 4: CLOSE ACCESS WARNING: DO NOT STAND ON ACCESS DOOR 312AR. THE WEIGHT OF PERSONNEL COULD

CAUSE THE SPRING LOADED LATCH TO RELEASE, AND PERSONNEL MAY BE INJURED BY FALLING THROUGH THE OPENING.

1. Remove any platforms or covers that were used to cover access door 312AR and close the access door.

WARNING: MAKE SURE THAT PERSONNEL AND EQUIPMENT ARE CLEAR OF THE HORIZONTAL STABILIZER AND ELEVATOR SURFACES BEFORE MOVING THE STABILIZER.

INJURY TO PERSONNEL AND DAMAGE TO EQUIPMENT COULD OCCUR.

2. Reactivate controls for the horizontal stabilizer. Refer to 767 AMM 27-41-00 as an accepted procedure.

3. 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.

4. For passenger airplanes only:

a. If removed, install the waste tank. Refer to 767 AMM 38-32-11 as an accepted procedure.

b. Install the right side potable water tank. If removed, install the left side potable water tank.

Refer to 767 AMM 38-11-01 as an accepted procedure.

5. Install the end wall in the bulk cargo compartment. Refer to 767 AMM 25-55-01 as an accepted procedure.

6. Install insulation to splice plates that splice pressure chords on the aft pressure bulkhead in the main deck compartment. Refer to 767 AMM 25-59-05 as an accepted procedure.

Original Issue: April 20, 2015 767-53A0266 30 of 41 BOEING SERVICE BULLETIN 767-53A0266

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Page 31Open in PDF

7. For passenger airplanes only:

a. Install the aft galley. Refer to 767 AMM 25-31-04 as an accepted procedure.

8. For freighter airplanes (including Boeing Converted Freighters) only:

a. Install the cargo lining panels to the aft pressure bulkhead in the main deck cargo compartment.

Refer to 767 AMM 25-59-01 as an accepted procedure.

Original Issue: April 20, 2015 767-53A0266 31 of 41 BOEING SERVICE BULLETIN 767-53A0266

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Page 32OCROpen in PDF

BOEING SERVICE BULLETIN 767-53A0266

ALERT ALERT This Figure applies only to: Group 2, Configuration 1; Group 3.

BULKHEAD WEB 6 LOCATIONS STA 1582 S-12R SKIN INBD

SPLICE PLATE (TYPICAL) S-39L TO S-39R

SOME AFFECTED AIRPLANE CONFIGURATIONS HAVE SHORT STIFFENERS AT THE AFT PRESSURE BULKHEAD TO PRESSURE CHORD JOINT. 2385797 SHORT STIFFENERS ARE NOT SHOWN FOR CLARITY.

FIGURE 1: AFT PRESSURE BULKHEAD WEB COMMON TO PRESSURE CHORD SPLICE PLATE -

FASTENER REMOVAL AND WEB INSPECTION (SHEET 1 OF 2) Original Issue: April 20, 2015 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 767-53A0266 Work - See page 1 for details. 32 of 41

Page 33Open 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 fasteners on aft row of each of three splice plates. (a) (b) 18-FastenerRemove1 Do a HFEC inspection of open holes for any crack in accordance with 767 NDT Manual Part 6, 51-00-04 or 767 NDT Manual Part 6, 51-00-11. (b) 3-Aft Pressure Bulkhead Web Inspect2

(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.

(b) 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 form 8100-9 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 in accordance with this service bulletin.

FIGURE 1: AFT PRESSURE BULKHEAD WEB COMMON TO PRESSURE CHORD SPLICE PLATE -

Original Issue: April 20, 2015 767-53A0266 33 of 41 BOEING SERVICE BULLETIN 767-53A0266

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Page 34OCROpen 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)2 6 LOCATIONS

INBD STA 1582 S-11L TO S-12L S-11R

SKIN TO S-12R

SPLICE PLATE (TYPICAL) S-23R NOTE:

SOME AFFECTED AIRPLANE CONFIGURATIONS HAVE SHORT STIFFENERS AT THE AFT PRESSURE 2385802 BULKHEAD TO PRESSURE CHORD JOINT.

SHORT STIFFENERS ARE NOT SHOWN FOR CLARITY. S-24L FIGURE 2: AFT PRESSURE BULKHEAD WEB COMMON TO PRESSURE CHORD SPLICE PLATE -

Page 35Open 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 fasteners on aft row of each of four splice plates. (a) (b) 24-FastenerRemove1 Do a HFEC inspection of open holes for any crack in accordance with 767 NDT Manual Part 6, 51-00-04 or 767 NDT Manual Part 6, 51-00-11. (b) 4-Aft Pressure Bulkhead Web Inspect2

(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.

FIGURE 2: AFT PRESSURE BULKHEAD WEB COMMON TO PRESSURE CHORD SPLICE PLATE -

Original Issue: April 20, 2015 767-53A0266 35 of 41 BOEING SERVICE BULLETIN 767-53A0266

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Page 36OCROpen in PDF

BOEING SERVICE BULLETIN 767-53A0266

ALERT ALERT This Figure applies only to: Group 2, Configuration 1; Group 3.

BULKHEAD WEB STA 1582 6 LOCATIONS 00 INBD SKIN S-11R

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

SOME AFFECTED AIRPLANE CONFIGURATIONS HAVE SHORT STIFFENERS AT THE AFT PRESSURE BULKHEAD TO PRESSURE CHORD JOINT. 2385803 SHORT STIFFENERS ARE NOT SHOWN FOR CLARITY. S-39L TO S-39R FIGURE 3: AFT PRESSURE BULKHEAD - PRESSURE CHORD SPLICE PLATES - FASTENER

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