Boeing ASB 777-57A0064: Revision 1, text

TextPartly OCR

Some pages are OCR from a scan. OCR can misread letters and numbers.

Query with SQL

duckdb -csv -c "SELECT p.page, p.text_source, p.text, f.rights_holder, f.license
  FROM 'https://openairdocs.org/data/latest/service_document_file_page.parquet' p JOIN 'https://openairdocs.org/data/latest/service_document_file.parquet' f USING (file_sha256)
  WHERE p.file_sha256 = 'c367266f5be7178cc6e0814cc943372ab73bbc8e2ddb9630df07d287f5d0490b'
  ORDER BY p.page"

Prints the whole list as CSV. It reads the release’s Parquet files over HTTPS, so there’s nothing to download first. Install DuckDB to run it.

SELECT p.page, p.text_source, p.text, f.rights_holder, f.license
FROM 'https://openairdocs.org/data/latest/service_document_file_page.parquet' p JOIN 'https://openairdocs.org/data/latest/service_document_file.parquet' f USING (file_sha256)
WHERE p.file_sha256 = 'c367266f5be7178cc6e0814cc943372ab73bbc8e2ddb9630df07d287f5d0490b'
ORDER BY p.page

Run it at the DuckDB prompt, or in any tool that reads Parquet over HTTPS. More ways to query the release are on Use the data.

Page 1Open in PDF

Commercial Airplanes 777 Service Bulletin Number: 777-57A0064 Original Issue: March 26, 2009 Revision 1: May 06, 2010 ATA System: 5741 2781 SUBJECT: WINGS - Leading Edge and Leading Edge Devices - Leading Edge - Outboard Slat Main Track Downstop Assembly and Slat Can - Inspection, Repair And Change Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 730-774). 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.

9E991ECCN:

BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2009 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.

This document includes proprietary information owned by The Boeing Company and/or one or more third parties.

Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.

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, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the Boeing livery 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: March 26, 2009 777-57A0064Revision 1: May 06, 2010 1 of 104

2.0

Page 2Open in PDF

Original Issue: March 26, 2009 777-57A0064Revision 1: May 06, 2010 2 of 104 BOEING SERVICE BULLETIN 777-57A0064

BLANK PAGE

Page 3Open in PDF

Table of Contents

Revision Transmittal Sheet5

Summary9

1. PLANNING INFORMATION ........................................ 1 3 A. Effectivity ............................................... 1 3

1. Airplanes ............................................ 1 3

2. Spares Affected ........................................ 1 6 B. Concurrent Requirements ...................................... 1 6 C. Reason ................................................ 1 6 D. Description .............................................. 1 8 E. Compliance .............................................. 1 9 F. Approval ............................................... 2 2 G. Manpower .............................................. 2 3 H. Weight and Balance Changes .................................... 2 6 I. Electrical Load Data ......................................... 2 7 J. References .............................................. 2 7

1. Existing Data .......................................... 2 7

2. Data supplied with this Service Bulletin ............................ 2 7

3. Installation Drawings Used in the Preparation of this Service Bulletin ............ 2 7 K. Publications Affected ........................................ 2 7 L. Interchangeability and Intermixability of Parts ........................... 2 7

2. MATERIAL INFORMATION ........................................ 2 9 A. Material - Price and Availability ................................... 2 9 B. Industry Support Information .................................... 3 1 C. Parts Necessary For Each Airplane ................................. 3 1

1. Kits/Parts ............................................ 3 1

2. Parts and Materials Supplied by the Operator ........................ 3 1

3. Parts Modified and Reidentified ................................ 3 4

4. Parts Removed and Not Replaced .............................. 3 4 D. Parts Necessary to Change Spares ................................. 3 4 E. Special Tooling - Price and Availability ............................... 3 4 F. Special Tooling Necessary to do this Service Bulletin ....................... 3 4

3. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 5 A. GENERAL INFORMATION ..................................... 3 5 B. WORK INSTRUCTIONS ....................................... 3 6 FIGURE 1: LEFT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP ASSEMBLY - INSPECTION [Group 1] ............................................ 4 7 FIGURE 2: RIGHT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP ASSEMBLY - INSPECTION [Group 1] ............................................ 5 0 FIGURE 3: LEFT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP ASSEMBLY - INSPECTION [Group 2] ............................................ 5 3 FIGURE 4: RIGHT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP ASSEMBLY - INSPECTION [Group 2] ............................................ 5 6 FIGURE 5: LEFT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP ASSEMBLY - TORQUE CHECK [Group 1] ............................................ 5 9 FIGURE 6: RIGHT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP ASSEMBLY - TORQUE CHECK [Group 1] ....................................... 6 2

Original Issue: March 26, 2009 777-57A0064Revision 1: May 06, 2010 3 of 104 BOEING SERVICE BULLETIN 777-57A0064

Page 4Open in PDF

FIGURE 7: LEFT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP ASSEMBLY - TORQUE CHECK [Group 2] ............................................ 6 5 FIGURE 8: RIGHT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP ASSEMBLY - TORQUE CHECK [Group 2] ....................................... 6 8 FIGURE 9: LEFT WING - OUTBOARD SLATS - MAIN TRACK SLAT CAN - INSPECTION [Group 1] . 71 FIGURE 10: RIGHT WING - OUTBOARD SLATS - MAIN TRACK SLAT CAN - INSPECTION [Group 1] . 73 FIGURE 11: LEFT WING - OUTBOARD SLATS - MAIN TRACK SLAT CAN - INSPECTION [Group 2] . 75 FIGURE 12: RIGHT WING - OUTBOARD SLATS - MAIN TRACK SLAT CAN - INSPECTION [Group 2] . 77 FIGURE 13: LEFT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP FITTING HARDWARE - REPLACEMENT [Group 1] .................................. 7 9 FIGURE 14: RIGHT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP FITTING HARDWARE - REPLACEMENT [Group 1] .................................. 8 2 FIGURE 15: LEFT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP FITTING HARDWARE - REPLACEMENT [Group 2] .................................. 8 5 FIGURE 16: RIGHT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP FITTING HARDWARE - REPLACEMENT [Group 2] .................................. 8 8 FIGURE 17: OUTBOARD SLATS - MAIN TRACK SLAT CAN - REPAIR ................. 9 1 FIGURE 18: LEFT WING - OUTBOARD SLAT NUMBER 3 - OUTBOARD MAIN TRACK SLAT CAN - INSPECTION [Group 2] .................................... 9 3 FIGURE 19: RIGHT WING - OUTBOARD SLAT NUMBER 12 - OUTBOARD MAIN TRACK SLAT CAN - INSPECTION [Group 2] .................................... 9 5 FIGURE 20: LEFT WING - OUTBOARD SLAT NUMBER 2 AND 3 - OUTBOARD AND INBOARD MAIN TRACK DOWNSTOP FITTING HARDWARE - REPLACEMENT .............. 9 7 FIGURE 21: RIGHT WING - OUTBOARD SLAT NUMBER 12 AND 13 - OUTBOARD AND INBOARD MAIN TRACK DOWNSTOP FITTING HARDWARE - REPLACEMENT ............. 1 0 0 APPENDIX A: REWORK INSTRUCTIONS - 116W4802-3 AND -4 DOWNSTOP FITTING INTO 116W4802-1 AND -2 DOWNSTOP FITTING ................................ 1 0 3

Original Issue: March 26, 2009 777-57A0064Revision 1: May 06, 2010 4 of 104 BOEING SERVICE BULLETIN 777-57A0064

Page 5Open in PDF

Commercial Airplanes 777 Service Bulletin Revision Transmittal SheetNumber: 777-57A0064Original Issue: March 26, 2009 Revision 1: May 06, 2010 ATA System: 5741 2781 SUBJECT: WINGS - Leading Edge and Leading Edge Devices - Leading Edge - Outboard Slat Main Track Downstop Assembly and Slat Can - Inspection, Repair And Change This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION No more work is necessary on airplanes changed in accordance with the original issue of this service bulletin.

Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2009-NM-100-AD, is related to this service bulletin.

REASON FOR REVISION

1. This revision is sent to:

a. Clarify that the rework limits for weld beads are measured from the slat can surface and do not include the weld bead height. The weld bead can be blended flush with the can surface before rework limits apply.

b. Delete the requirement in Part 7 - Outboard Slat Numbers 3 and 12 Outboard Main Track Slat Can Inspection and Outboard and Inboard Main Track Stop Hardware Replacement that required accomplishment of Part 2 - Slat Main Track Stop Hardware Torque Check. Checking the torque of the fasteners prior to replacement is not necessary. Failure of Part 2 - Slat Main Track Stop Hardware Torque Check requires the hardware to be replaced which is already being accomplished.

c. Add note in the General Information section that allows the installation of a fastener with a different grip length if required to meet SRM requirements. Subsequent to the release of the original issue of this service bulletin, an operator reported that a different grip length bolt was required to meet SRM requirements.

In addition, operators have reported difficulty in obtaining BACB30LR4-35 bolts. Boeing has reviewed and determined that a BACB30LR4-36 bolt with a BACW10BP4APU washer is an acceptable option.

d. Revise incorrect chamfer callout in Appendix A. See Information Notice (IN) IN-01.

e. Verify that a post machining stress relief bake is not required in Appendix A. See Information Notice (IN) IN-02.

f. Correct the Standard Overhaul Practices Manual (SOPM) in Appendix A for the optional part marking.

See Information Notice (IN) IN-02.

Original Issue: March 26, 2009 777-57A0064Revision 1: May 06, 2010 5 of 104

Page 6Open in PDF

g. Add scrubbing part with a scotchbrite pad (or equivalent) as an option to solvent cleaning in Appendix A. See Information Notice (IN) IN-02.

h. Clarify the Part 1 - Slat Track Stop Hardware Installation Inspection action that requires Part 3 - Slat Can Inspection be accomplished does not apply to the outboard main track locations of slats no. 3 and 12 on Group 1 Airplanes. Subsequent to the release of the original issue of this service bulletin, an operator requested this clarification be added.

i. Clarify the areas where the slat can repair is applicable by adding commas inadvertantly missing in the original issue.

j. Clarify in figures 13 through 16 that the downstops can be kept and reinstalled.

k. Clarify the locator in Figure 5 to show the correct locations affected.

l. Add reference to FAA NPRM 2009-NM-100-AD.

m. Updated service bulletin to current requirements.

2. The following sections were changed in this revision:

a. Summary:

(1) Compliance - Add reference to FAA NPRM 2009-NM-100-AD.

b. 1. Planning

(1) Paragraph 1.E., Compliance:

(a) Add reference to FAA NPRM 2009-NM-100-AD.

(b) Table 1 - Clarified that certain main track locations on Group 1 Airplanes do not require Part 3 - Slat Can Inspection.

(2) Paragraph 1.J.1., Existing Data - Added Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2009-NM-100-AD. Revised SOPM Callout.

(3) Paragraph 1.K., Publications Affected - Added Damage Tolerance Based Structural Inspections requirements.

c. 3. Accomplishment Instructions

(1) Paragraph 3.A., General Information:

(a) Note 5 - Added new note allowing installation of a different grip length fastener if required to meet SRM requirements.

(2) Paragraph 3.B., Work Instructions:

(a) Part 7 - Outboard Slat Numbers 3 and 12 Outboard Main Track Slat Can Inspection and Outboard and Inboard Main Track Stop Hardware Replacement

Original Issue: March 26, 2009 777-57A0064Revision 1: May 06, 2010 6 of 104 BOEING SERVICE BULLETIN 777-57A0064

Page 7Open in PDF

1) Step 4 - Deleted requirement to do Part 2 - Slat Main Track Stop Hardware Torque Check.

(b) FIGURE 5:

1) Illustration - Clarified locator to show correct locations affected.

1) Step Table - Clarified that downstop fittings can be kept in step 1.

(d) FIGURE 14:

1) Step Table - Clarified that downstop fittings can be kept in step 1.

(e) FIGURE 15:

1) Step Table - Clarified downstop fittings can be kept in step 1. Clarified that kept downstop fittings can be installed in step 2.

(f) FIGURE 16:

1) Step Table - Clarified downstop fittings can be kept in step 1. Clarified that kept downstop fittings can be installed in step 2.

(g) FIGURE 17:

1) Illustration - Deleted extra circle note 4 not used in step table.

2) Step Table - Clarified the areas where the slat can repair is applicable by adding commas.

Clarify rework limits at weld bead.

(h) FIGURE 20:

1) Step Table - Added optional bolt and washer in step 2.

(i) FIGURE 21:

1) Step Table - added optional bolt and washer in step 2.

d. APPENDIX A:

(1) Illustration - Revised Chamfer callout.

(2) Step Table

(a) Step 1 and 2 - Verified that post machining stress relief bake is not required. Revised SOPM callout to the correct callout for part marking.

(b) Step 3 - Added scrubbing with scotchbrite (or equivalent) as an option to solvent cleaning.

Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location of important changes.

Original Issue: March 26, 2009 777-57A0064Revision 1: May 06, 2010 7 of 104 BOEING SERVICE BULLETIN 777-57A0064

Page 8Open in PDF

Pages with no vertical lines have no important changes.

REVISION HISTORY March 26, 2009Original Issue:

May 06, 2010Revision 1:

Original Issue: March 26, 2009 777-57A0064Revision 1: May 06, 2010 8 of 104 BOEING SERVICE BULLETIN 777-57A0064

Page 9Open in PDF

Commercial Airplanes 777 Service Bulletin SummaryNumber: 777-57A0064Original Issue: March 26, 2009 Revision 1: May 06, 2010 ATA System: 5741 2781 SUBJECT: WINGS - Leading Edge and Leading Edge Devices - Leading Edge - Outboard Slat Main Track Downstop Assembly and Slat Can - Inspection, Repair And Change

CONCURRENT REQUIREMENTS None.

BACKGROUND Paragraph 1.E., Compliance Accomplishment of the inspections and changes in this service bulletin will help detect and prevent damage to the outboard slat main track slat cans. Damage to the outboard slat main track slat cans can allow fuel leakage into the fixed wing leading edge in excess of the capacity of the drainage system. The fuel leakage from the excess fuel could result in an uncontained fire.

Each outboard slat main track has a downstop attached to the aft end of the slat track assembly. The downstop consists of two fittings that are secured to the track with a bolt and nut. The main tracks travel through holes in the front spar web when the slat is retracted. In areas of the wing where fuel is stored, a slat can is installed on the wet side of the spar to surround the main track and contain the fuel. One operator reported finding a hole in the inboard main track slat can for outboard slat number 12. The hole was caused when the bolt securing the downstop migrated out of the fitting and contacted the slat can. It is believed the locking element of the nut was not fully engaged and the nut securing the bolt backed off and allowed the bolt to migrate. In addition, in production it was discovered that a downstop was contacting the weld on a slat can at the outboard main track location on slat numbers 3 and 12. This contact could cause wear damage and eventually a hole in the slat can. Holes in the slat can can allow fuel leakage into the wing fixed leading edge. It is possible that the hole could be large enough to alow fuel leakage in excess of the capacity of the drainage provisions in the fixed leading edge. The excess fuel leakage could result in an uncontained fire.

Inspections of the bolt, nut, and downstop will ensure that parts are correctly installed and prevent the bolt from migrating out and puncturing the slat can. Replacement of the hardware will ensure that parts are correctly installed. Inspection of the slat can will ensure that there are no holes or wear damage that could result in a hole in the slat can.

Boeing Service Related Problem (SRP) 777-SRP-57-0219 is related to this service bulletin.

Original Issue: March 26, 2009 777-57A0064Revision 1: May 06, 2010 9 of 104

Page 10Open in PDF

ACTION (PRR 62777-63S) Part 1 - Slat Track Stop Hardware Installation Inspection Extend the slats. Remove or open the fixed leading edge access panels at each of the affected outboard slat main track locations. Do a Detailed inspection (DET) of the stop hardware at the end of each track to determine if the stop is installed and the thread protrusion from the nut is within limits. Install or close the fixed leading edge access panels. Retract the slats.

Part 2 - Slat Main Track Stop Hardware Torque Check Extend the slats. Remove or open the fixed leading edge access panels at each of the affected outboard slat main track locations. Measure the torque of the nuts to determine if the the nut is shanked out on the bolt. Install or close the fixed leading edge access panels. Retract the slats.

Part 3 - Slat Can Inspection Do a Detailed inspection (DET) of the slat can for holes and gouges.

Part 4 - Stop Hardware Replacement Replace the bolt and nut, and the stop fitting if required.

Part 5 - Slat Can Repair Remove the slat at the affected main track location. Remove the slat main track at the affected main track location. Blend out gouges and wear damage as required. Install the slat main tracks. Install the Slat Part 6 - Slat Can Replacement Drain and purge the outboard main tanks and prepare for entry. Remove the lower wing access panel in the wing rib bay which the affected slat can is located. Remove the slat at the affected main track location. Remove the slat main track at the affected main track location. Replace the slat can. Install the lower wing access panel.

Install the slat main tracks. Install the Slat Part 7 - Outboard Slat Numbers 3 and 12 Outboard Main Track Slat Can Inspection and Outboard and Inboard Main Track Stop Hardware Replacement Extend the slats. Remove or open the fixed leading edge access panels at each of the outboard slats number 3 and 12 outboard and inboard main track locations. Do a DET of the slat cans at the outboard slat number 3 and 12 outboard main track locations for holes and wear damage. Replace the downstop hardware for the outboard slats number 3 and 12 outboard and inboard main track locations. Install or close the fixed leading edge access panels. Retract the slats.

EFFECTIVITY 777-200, -200LR, -300, -300ER Airplanes. Refer to Paragraph 1.A., Effectivity for the list of affected airplanes.

COMPLIANCE Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2009-NM-100-AD, is related to this service bulletin.

Original Issue: March 26, 2009 777-57A0064Revision 1: May 06, 2010 10 of 104 BOEING SERVICE BULLETIN 777-57A0064

Page 11Open in PDF

See Paragraph 1.E., Compliance.

INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are available for airplanes in warranty as of April 9, 2008. Please refer to Paragraph

2.B., Industry Support Information.

MANPOWER Group 1:

Elapsed Hours Total Task Hours

1.7517.50Part 1 - Slat Track Stop Hardware Installation Inspection

4.2014.70Part 2 - Slat Main Track Stop Hardware Torque Check

7.007.00Part 3 - Slat Can Inspection

0.30 (a)0.30 (a)Part 4 - Stop Hardware Replacement

8.00 (b)12.00 (b)Part 5 - Slat Can Repair

14.50 (b)30.50 (b)Part 6 - Slat Can Replacement

(a) Estimate is for hardware replacement for each main track location.

(b) Estimate is for each slat can.

Group 2:

Elapsed Hours Total Task Hours

9.0021.00Part 1 - Slat Track Stop Hardware Installation Inspection

4.9016.90Part 2 - Slat Main Track Stop Hardware Torque Check

9.009.00Part 3 - Slat Can Inspection

0.30 (a)0.30 (a)Part 4 - Stop Hardware Replacement

8.00 (b)12.00 (b)Part 5 - Slat Can Repair

14.50 (b)30.50 (b)Part 6 - Slat Can Replacement

4.508.00Part 7 - Outboard Slat Numbers 3 and 12 Outboard Main Track Slat Can Inspection and Outboard and Inboard Main Track Stop Hardware Replacement

(a) Estimate is for hardware replacement for each main track location.

(b) Estimate is for each slat can

MATERIAL INFORMATION Operator Supplied Parts/Materials.

Original Issue: March 26, 2009 777-57A0064Revision 1: May 06, 2010 11 of 104 BOEING SERVICE BULLETIN 777-57A0064

Page 12OCROpen in PDF

BOEING SERVICE BULLETIN 777-57A0064 Refer to Paragraph 2.A., Material - Price and Availability

SLAT SLAT 7 LOCATIONS 6 5 SLAT 4 SLAT SLAT 2 SLAT GROUP 2

AIRPLANES ONLY SLATS 1-6 SHOWN, SLATS 9-14 OPPOSITE PART 3:

DO A DET OF THE SLAT CAN FOR DAMAGE.

PART 5:

REPAIR GOUGES IN THE SLAT CAN.

PART 6:

REPLACE THE SLAT CAN.

PART 7:

GROUP 2 AIRPLANES: DO A DET OF THE OUT-

BOARD MAIN TRACK SLAT CAN FOR SLATS NUMBERS 3 AND 12 FOR HOLES OR WEAR DAMAGE. REPLACE THE DOWNSTOP HARDWARE AT SLAT NUMBERS 3 AND 12 INBOARD AND OUTBOARD MAIN TRACK LOCATIONS.

PART 1:

DO A DET TO DETERMINE IF THE

DOWNSTOP AND HARDWARE ARE

INSTALLED AND THE BOLT THREAD PROTRUSION IS WITHIN LIMITS.

PART 2:

MEASURE THE TORQUE OF

THE NUT OF THE DOWN STOP ATTACH HARDWARE.

PART 4:

REPLACE THE DOWNSTOP

HARDWARE WD

TYPICAL MAIN TRACK LOCATION FWD A-A 1673711 Original Issue: March 26, 2009 Revision 1: May 06, 2010 777-57A0064

Pages 13–24 of 104