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Commercial Airplanes 747 Service Bulletin ALERT Number: 747-57A2343 Original Issue: September 12, 2013 ATA System: 5752 2751 SUBJECT: WINGS - Trailing Edge Flaps - Outboard Flap Inboard Actuator Attach Fittings (Gimbals No.s 2 and 7) - Inspection, Rework, and Replacement 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.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET Copyright © 2013 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Unpublished Work.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: September 12, 2013 747-57A2343 1 of 54
3.0
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: September 12, 2013 747-57A2343 2 of 54 BOEING SERVICE BULLETIN 747-57A2343
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BLANK PAGE
Table of Contents
Summary5
1. PLANNING INFORMATION9
A. Effectivity9
1. Airplanes9
2. Spares Affected ........................................ 1 8 B. Concurrent Requirements ...................................... 1 8 C. Reason ................................................ 1 8 D. Description .............................................. 1 9 E. Compliance .............................................. 2 0 F. Approval ............................................... 2 2 G. Manpower .............................................. 2 2 H. Weight and Balance Changes .................................... 2 4 I. Electrical Load Data ......................................... 2 4 J. References .............................................. 2 4
1. Existing Data: ......................................... 2 4
2. Data Supplied with this Service Bulletin: ........................... 2 5
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 2 5 K. Publications Affected ........................................ 2 5 L. Interchangeability and Intermixability of Parts ........................... 2 5 M. Software Accomplishment Summary ................................ 2 6
2. MATERIAL INFORMATION ........................................ 2 7 A. Material - Price and Availability ................................... 2 7 B. Industry Support Information .................................... 2 7 C. Parts Necessary for Each Airplane ................................. 2 7
1. Kits/Parts ............................................ 2 7
2. Parts and Materials Supplied by the Operator ........................ 2 7
3. Parts Modified and Reidentified ................................ 2 8
4. Parts Removed and Not Replaced .............................. 2 8 D. Parts Necessary to Change Spares ................................. 2 8 E. Special Tooling - Price and Availability ............................... 2 8 F. Special Tooling Necessary to do this Service Bulletin ....................... 2 8
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 9 A. GENERAL INFORMATION ..................................... 2 9 B. WORK INSTRUCTIONS ....................................... 3 1 FIGURE 1: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - PART NUMBER INSPECTION . . 35 FIGURE 2: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - DET INSPECTION ......... 3 7 FIGURE 3: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - MINIMUM WALL THICKNESS INSPECTION .......................................... 4 0 FIGURE 4: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - PART NUMBER INSPECTION . 44 FIGURE 5: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - DET INSPECTION ........ 4 6 FIGURE 6: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - MINIMUM WALL THICKNESS INSPECTION .......................................... 4 9 APPENDIX A: LOGIC DIAGRAM ....................................... 5 3 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: September 12, 2013 747-57A2343 3 of 54 BOEING SERVICE BULLETIN 747-57A2343
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Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: September 12, 2013 747-57A2343 4 of 54 BOEING SERVICE BULLETIN 747-57A2343
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Commercial Airplanes 747 Service Bulletin ALERT SummaryNumber: 747-57A2343Original Issue: September 12, 2013 ATA System: 5752 2751 SUBJECT: WINGS - Trailing Edge Flaps - Outboard Flap Inboard Actuator Attach Fittings (Gimbals No.s 2 and 7) - Inspection, Rework, and Replacement
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 The inspections and replacement in this service bulletin will help prevent fracture of the outboard flap, inboard actuator support fitting assembly (no. 2 or no. 7 gimbal). A fractured inboard actuator fitting combined with the loss of the outboard actuator load path could result in the uncontrolled retraction of the outboard flap and subsequent damage to flight control systems at the rear spar. Uncontrolled retraction of the flap or damage to flight control systems could lead to reduced controllability of the airplane.
One operator reported the fracture of a 65B08564-7 actuator attach fitting. The actuator attach fitting had approximately 5,500 flight-cycles and 20,600 flight-hours. The actuator attach fitting was installed by service bulletin 747-57A2316. The actuator attach fitting fractured in the internal conical machined area. Inspection of the actuator attach fitting revealed that a portion of the interior surface was machined with a cylindrical profile instead of a conical profile. This results in reduced wall thickness. The thickness of the fitting in the cylindrical area was approximately half the design wall thickness. The operator inspected the remaining airplanes in their fleet and found another actuator attach fitting with the cylindrical defect with a wall thickness below design requirements. An inspection of spare 65B08564-7 actuator attach fittings at Boeing revealed some actuator attach fittings with the cylindrical defect with reduced wall thicknesses. In addition, some actuator attach fittings which did not have the cylindrical defect had wall thicknesses which were below design requirements. Reduced wall thickness results in the inability of the actuator attach fitting to carry required loads.
This service bulletin provides instructions to inspect and replace 65B08564-7 no. 2 and no. 7 actuator attach fittings which could have insufficient wall thickness.
Boeing Service Related Problem (SRP) 747-SRP-57-0264 is related to this service bulletin.
Boeing Fleet Team Digest (FTD) 747 FTD 57-13003 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: September 12, 2013 747-57A2343 5 of 54
ReferenceAffectedPlanning Data Paragraph 1.A.2., Spares AffectedYesSpares Affected Paragraph 1.E., Compliance and Paragraph
1.F., Approval YesAD Related Paragraph 1.H., Weight and Balance ChangesNoWeight and Balance Change Paragraph 1.I., Electrical Load DataNoElectrical Load Changed Paragraph 1.K., Publications AffectedYesPublications Affected Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew Operations Manual and/or FAA Approved Airplane Flight Manual) Paragraph 2.C.1., Kits/PartsNoKits/Parts Required Paragraph 2.C.2., Parts and Materials Supplied by the Operator YesOperator Supplied Parts/Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin NoSpecial Tooling Required ACTION (PRR 85901-129RS) Part 1: Outboard Flap, Inboard Actuator Attach Fitting - Part Number Inspection Extend the trailing edge flaps to detent 30 and deactivate. Disconnect actuator ball screw nut from the actuator attach fitting. Do an inspection of the actuator attach fitting to determine if a 65B08564-7 Actuator Attach Fitting is installed. Attach actuator ball screw to the actuator attach fitting. Activate and retract the trailing edge flaps.
Part 2: Outboard Flap, Inboard Actuator Attach Fitting - DET Inspection Extend the trailing edge flaps to detent 30 and deactivate. Disconnect actuator ball screw nut from the actuator attach fitting. Do a Detailed (DET) inspection of the Actuator Attach Fitting to determine if it has the cylindrical defect. Attach actuator ball screw to the actuator attach fitting. Activate and retract the trailing edge flaps.
Part 3: Outboard Flap, Inboard Actuator Attach Fitting - Minimum Thickness Inspection Extend the trailing edge flaps to detent 30 and deactivate. Remove the Actuator Attach Fitting. Do an Ultrasonic (UT) inspection or mechanically determine the thickness of the Actuator Attach Fitting. Install the Actuator Attach Fitting. Activate and retract the trailing edge flaps.
Part 4: Outboard Flap, Inboard Actuator Attach Fitting - Replacement Extend the trailing edge flaps to detent 30 and deactivate. Remove the Actuator Attach Fitting. Install actuator attach fitting assemblies not affected by this service bulletin. Activate and retract the trailing edge flaps.
EFFECTIVITY 747-100, -100B, -100B SUD, -200B, -200C, -200F, -300, -400, -400D, -400F,and 747SR Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: September 12, 2013 747-57A2343 6 of 54 BOEING SERVICE BULLETIN 747-57A2343
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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.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are available for airplanes in warranty as of June 5, 2013. Please refer to Paragraph
2.B., Industry Support Information. The warranty remedies will expire eight years from the original issue date of this service bulletin.
MANPOWER Elapsed HoursTotal Task Hours
4.007.00Part 1: Outboard Flap, Inboard Actuator Attach Fitting - Part Number Inspection
4.007.00Part 2: Outboard Flap, Inboard Actuator Attach Fitting - DET Inspection
5.008.00Part 3: Outboard Flap, Inboard Actuator Attach Fitting - Minimum Thickness Inspection
6.006.00Part 4: Outboard Flap, Inboard Actuator Attach Fitting - Replacement
MATERIAL INFORMATION Operator Supplied Parts/Materials.
Refer to Paragraph 2.A., Material - Price and Availability.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: September 12, 2013 747-57A2343 7 of 54 BOEING SERVICE BULLETIN 747-57A2343
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BOEING SERVICE BULLETIN 747-57A2343
ALERT ALERT PART 1:
DO AN INSPECTION TO DETERMINE IF A 65B08564-7 IS INSTALLED PART 2:
DO A DET TO DETERMINE IF ACTUATOR
ATTACH FITTING HAS THE CYLINDRICAL DEFECT PART 3:
RIGHT WING OPPOSITE LEFT WING SHOWN, DO A UT INSPECTION OR MECHANICALLY DETERMINE THE MINIMUM WALL
THICKNESS OF THE ACTUATOR ATTACH
FITTING PART 4:
REPLACE ACTUATOR ATTACH FITTING
WITH FITTING NOT AFFECTED BY THIS
SERVICE BULLETIN
ACTUATOR
• ATTACH FITTING → PART NUMBER
LOCATION A-A 2267858 Original Issue: September 12, 2013 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 747-57A2343 Work - See page 1 for details. 8 of 54
Commercial Airplanes 747 Service Bulletin ALERT Number: 747-57A2343 Original Issue: September 12, 2013 ATA System: 5752 2751 SUBJECT: WINGS - Trailing Edge Flaps - Outboard Flap Inboard Actuator Attach Fittings (Gimbals No.s 2 and 7) - Inspection, Rework, and Replacement
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 for the airplane(s) shown below. Refer to PRR 85901-129RS for data about this change.
Refer to Service Bulletin Index D6-30300 Part 3 for Airplane Variable Number, Line Number, and Serial Number data.
DESCRIPTIONCONFIGURATIONGROUP 747-100, -100B, -100B SUD, -200B, -200C, -200F, -300, -400, -400D, -400F, 747SR Airplanes line numbers 1 through 1263. These airplanes were not delivered with a 65B08564-7 Actuator Attach Fitting, but could have had a 65B08564-7 Actuator Attach Fitting installed by service bulletin 747-57A2316.
-1 747-400 and -400F Airplanes line numbers 1264 through 1419. These airplanes were delivered with a 65B08564-7 Actuator Attach Fitting and could have replaced the 65B08564-7 Actuator Attach Fitting by service bulletin 747-57A2316 with an Actuator Attach Fitting not affected by this service bulletin.
-2 Airplane Models:
747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: September 12, 2013 747-57A2343 9 of 54
GroupVariable Number 1RA001 - RA034 1RA101 - RA115 1RA161 - RA164 1RA201 - RA203 1RA216 - RA217 1RA245 - RA246 1RA251 - RA266 1RA301 - RA318 1RA351 - RA360 1RA369 - RA373 1RA401 - RA418 1RA501 - RA502 1RA521 - RA528 1RA532 - RA548 1RA551 - RA552 1RA559 - RA561 1RA581 - RA582 1RA585 1RA601 - RA602 1RA631 - RA635 1RA651 - RA652 1RA671 - RA677 1RA701 - RA702 1RA721 - RA731 1RA741 - RA745 1RA749 - RA750 1RA761 - RA762 1RA781 - RA784 1RA901 - RA916 1RB001 - RB016 1RB041 - RB044 1RB071 - RB075 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: September 12, 2013 747-57A2343 10 of 54 BOEING SERVICE BULLETIN 747-57A2343
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GroupVariable Number 1RB101 - RB102 1RB411 - RB413 1RB421 1RB601 - RB607 1RB681 - RB697 1RB711 1RB721 - RB723 1RB741 - RB748 1RD001 - RD004 1RD021 - RD022 1RD041 - RD059 1RD071 - RD072 1RD081 - RD083 1RD091 - RD092 1RD101 - RD104 1RD121 - RD127 1RD131 - RD144 1RD166 - RD167 1RD171 - RD172 1RD181 - RD183 1RD201 - RD204 1RD221 - RD227 1RD231 - RD235 1RD241 - RD243 1RD251 - RD262 1RD271 - RD272 1RD291 - RD292 1RD301 - RD302 1RD311 1RD351 - RD358 1RD361 - RD366 1RD381 - RD383 1RD411 - RD414 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: September 12, 2013 747-57A2343 11 of 54 BOEING SERVICE BULLETIN 747-57A2343
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GroupVariable Number 1RD421 - RD426 1RD431 - RD435 1RD441 - RD442 1RD451 - RD456 1RD461 1RD471 - RD475 1RD513 - RD519 1RD531 - RD533 1RD551 1RD561 1RD571 1RD581 - RD583 1RD591 - RD593 1RD601 - RD607 1RD621 - RD623 1RD641 - RD649 1RD651 - RD659 1RD661 1RD671 1RD681 - RD682 1RD691 - RD692 1RD701 - RD702 1RD721 - RD722 1RD741 - RD742 1RD751 - RD755 1RD761 1RD771 - RD775 1RD781 - RD783 1RD791 - RD792 1RE001 2RF001 - RF006 1RJ131 - RJ133 1RJ151 - RJ152 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: September 12, 2013 747-57A2343 12 of 54 BOEING SERVICE BULLETIN 747-57A2343