### Commercial **Airplanes** 

# 747 Service Bulletin **ALERT Number: 747-57A2343**  Original Issue: September 12, 2013 Revision 1: June 23, 2014 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. 9E991 ECCN: 

## 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 Unpublished Work.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2013 747-57A2343 Revision 1: June 23, 2014 1 of 68 5.0Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 2 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT**

BLANK PAGE**Table of Contents** Revision Transmittal Sheet............................................ 5 Summary...................................................... 9 1. PLANNING INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 A. Effectivity. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 1. Airplanes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 2. Spares Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 F. Approval. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 G. Manpower. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30 1. Existing Data:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30 2. Data Supplied with this Service Bulletin:. . . . . . . . . . . . . . . . . . . . . . . . . . . 30 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 30 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 31 M. Software Accomplishment Summary. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33 C. Parts Necessary for Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34 1. Kits/Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 34 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34 4. Parts Removed and Not Replaced. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 35 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39 FIGURE 1: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - PART NUMBER INSPECTION . . 45 FIGURE 2: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - DET INSPECTION. . . . . . . . . 47 FIGURE 3: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - MINIMUM WALL THICKNESS AND MACHINING DEFECT INSPECTION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50 FIGURE 4: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - PART NUMBER INSPECTION . 55 FIGURE 5: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - DET INSPECTION. . . . . . . . 57 FIGURE 6: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - MINIMUM WALL THICKNESS AND MACHINING DEFECT INSPECTION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 60 APPENDIX A: LOGIC DIAGRAM. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 65 APPENDIX B: INPUT SURVEY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 68

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 3 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 4 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT**

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### Commercial **Airplanes** 

# 747 Service Bulletin **ALERT Revision Transmittal Sheet**  **Number: 747-57A2343** Original Issue: September 12, 2013 Revision 1: June 23, 2014 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 revision includes all pages of the service bulletin. **COMPLIANCE INFORMATION RELATED TO THIS REVISION** Federal Aviation Administration (FAA) Airworthiness Directive AD 2013-23-03 is related to this service bulletin. More work is required on airplanes with an actuator attach fitting 65B08564-7 installed which accomplished PART 3: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - MINIMUM THICKNESS INSPECTION in accordance with the Original Issue of this service bulletin. These airplanes should do PART 3: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - MINIMUM THICKNESS AND MACHINING DEFECT INSPECTION to determine if the machining defect is present and accomplish any required follow-on actions within the compliance time in Paragraph 1.E., Compliance. The Federal Aviation Administration (FAA) will possibly release an additional Airworthiness Directive related to Revision 1 of this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in Revision 1 of this service bulletin mandatory. **REASON FOR REVISION** This revision is sent to: 1. Add an inspection for a machining defect that can reduce the durability of the fitting. During inspection of the actuator fittings, many actuator attach fittings 65B08564-7 were found to have a machining defect, visible under the protective finishes, in the area where the tapered machining transitioned to the hemispherical machining at the top of the inner surface. 2. Limit the compliance time that fitting assemblies with a wall thickness 0.130 inch or greater and less than 0.140 inch and do not have a machining defect can remain in-service, to 48 months or 3,000 flight-cycles after the Original Issue date of this service bulletin, whichever occurs first. These sections were changed: 1. Summary a. Background - Add machining defect. b. Action

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 5 of 68(1) Add inspection for machining defect to Part 3. (2) Part 5 - Overhaul - Add new part for fittings with minimum wall thickness greater than 0.140 inch to allow removal of the machining defect. c. Compliance - Add Reference to AD 2013-23-03. Show that it is expected that additional rule-making is expected against Revision 1 of this service bulletin. d. Manpower (1) Revise title for Part 3 to account for inspection for the machining defect. (2) Add new Part 5 - Overhaul. e. Illustration (1) Revise title for Part 3 to account for inspection for the machining defect. (2) Add new Part 5 - Overhaul. f. Material Information - Reference new Spares Input Survey in APPENDIX B. 2. Planning Information a. Paragraph 1.C., Reason (1) Add machining defect. (2) Add Reason for revision b. Paragraph 1.D., Description (1) Add inspection for machining defect to Part 3. (2) Part 5 - Overhaul - Add new part for fittings with minimum wall thickness greater than 0.140 inch to allow removal of the machining defect. (3) Add compliance information related to the revision. c. Paragraph 1.E., Compliance (1) Add Reference to AD 2013-23-03. Show that it is expected that additional rule-making is expected against Revision 1 of this service bulletin. (2) Add new row for airplanes which accomplished Part 3 - Inspection in accordance with the Original Issue. (3) Add inspection for machining defect to Part 3. (4) Include no machining defect in existing Conditions 5 and 6. Add new Conditions 8 and 9 which are the same as Conditions 5 and 6 with the machining defect. Show that for Condition 7 it does not matter if the machining defect is or is not present.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 6 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT**(5) Add Part 5 - Overhaul for fittings with minimum wall thickness greater than 0.140 inch to allow removal of the machining defect. (6) Revise the compliance time for Condition 6 due to durability concerns. d. Paragraph 1.F., Approval - Add AMOC paragraph for AD 2013-23-03. e. Paragraph 1.G., Manpower (1) Revise title for Part 3. (2) Add new table for Part 5 - Overhaul. f. Paragraph 1.J., References - Add reference to AD 2013-23-03 and to SOPM for storage of fitting assemblies after overhaul or new. 3. Material Information a. Paragraph 2.A., Material - Price and Availability - Add price and availability information for new 65B08564-9 Fitting Assembly and reference new Spares Input Survey in APPENDIX B. b. Paragraph 2.C.2., Parts and Materials Supplied by the Operator (1) Clarify the condition of the spare actuator assemblies sold by Boeing. (2) Clarify what parts are not affected by this service bulletin. c. Paragraph 2.B., Industry Support Information - Correct model number. 4. Accomplishment Instructions a. Paragraph 3.B., Work Instructions (1) General work Flow (a) Add inspection for airplanes which accomplished Part 3 - Inspection in accordance with the Original Issue. (b) Add inspection for machining defect to Part 3. (c) Add Part 5 - Overhaul for fittings with minimum wall thickness greater than 0.140 inch to allow removal of the machining defect. (2) Part 3 - DET Insection - Add inspection for machining defect. (3) Part 4 Overhaul - Add additional Actuator attach fitting options. (4) Part 5 - Overhaul - Add new part for fittings with minimum wall thickness greater than 0.140 inch to allow removal of the machining defect. (5) FIGURE 2 (a) Revise illustration to help clarify cylindrical defect.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 7 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT**(b) Revise Flag Note 1 text to help clarify cylindrical defect. (6) FIGURE 3 (a) General - Revise title to add inspection for machining defect. (b) Illustration - Add new illustration showing a typical machining defect. (c) Step 3 - Add new step to inspect for the machining defect. Note that finish restoration is not required if fitting is being overhauled. (7) FIGURE 5 (a) Revise illustration to help clarify cylindrical defect. (b) Revise Flag Note 1 text to help clarify cylindrical defect. (8) FIGURE 6 (a) General - Revise title to add inspection for machining defect. (b) Illustration - Add new illustration showing a typical machining defect. (c) Step 3 - Add new step to inspect for the machining defect. Note that finish restoration is not required if fitting is being overhauled. (9) APPENDIX A - Revise logic diagram to add inspection for machining defect. This adds new initial compliance time box for airplanes that accomplished Part 3 in accordance with the original issue of this service bulletin. Revise title of Part 3 to add inspection for the machining defect. Add Condition 8 and 9 which are the same as Condition 5 and 6 except with the machining defect. Revise compliance time for fitting replacement for Condition 6 (wall thickness 0.130 or greater and less than 0.140 inch and machining defect is not present). (10) APPENDIX B - Add new appendix with Spares survey. Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes, to show the location of all content changes. Pages with no vertical lines have no changes. **REVISION HISTORY** September 12, 2013 Original Issue: June 23, 2014 Revision 1:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 8 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT**

### Commercial **Airplanes** 

# 747 Service Bulletin **ALERT Summary**  **Number: 747-57A2343** Original Issue: September 12, 2013 Revision 1: June 23, 2014 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. Some of the actuator assemblies inspected at Boeing also were found to have a machining defect at the point where the tapered machining transitioned to the hemispherical machining at the top of the inner surface. This defect was visible under the finishes. This defect could eventually lead to fatigue cracks and subsequent fracture. 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 or the machining defect. Boeing Service Related Problem (SRP) 747-SRP-57-0264 is related to this service bulletin.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 9 of 68Boeing 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.
**Reference Affected**  **Planning Data** Paragraph 1.A.2., Spares Affected Yes 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 Yes 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 Yes Operator Supplied Parts/Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin No Special 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 and Machining Defect 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 minimum wall thickness of the Actuator Attach Fitting. Do a DET to determine if the machining defect is present on the inner wall. 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 10 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT**Part 5: Outboard Flap, Inboard Actuator Attach Fitting - Overhaul Extend the trailing edge flaps to detent 30 and deactivate. Remove the Actuator Attach Fitting. Overhaul the Actuator attach fitting and remove the machining defect. Install the Actuator Attach Fitting. 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. **COMPLIANCE** Federal Aviation Administration (FAA) Airworthiness Directive AD 2013-23-03 is related to this service bulletin. The effective date of AD 2013-23-03 is November 29, 2013. The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to Revision 1 of this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in Revision 1 of 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 Hours**  **Total Task Hours**4.00 7.00 Part 1: Outboard Flap, Inboard Actuator Attach Fitting - Part Number Inspection 4.00 7.00 Part 2: Outboard Flap, Inboard Actuator Attach Fitting - DET Inspection 5.00 8.00 Part 3: Outboard Flap, Inboard Actuator Attach Fitting - Minimum Thickness and Machining Defect Inspection 6.00 6.00 Part 4: Outboard Flap, Inboard Actuator Attach Fitting - Replacement 3.00 6.00 Part 5: Outboard Flap, Inboard Actuator Attach Fitting - Overhaul
**MATERIAL INFORMATION** Boeing Supplied Kits/Parts. 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 Revision 1: June 23, 2014 11 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT**Operators are encouraged to complete the survey provided in the Appendix of this service bulletin to help Boeing predict the quantity and timing of the Boeing Supplied Kits/Parts.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 12 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT**

### Commercial **Airplanes** 

# 747 Service Bulletin **ALERT Number: 747-57A2343**  Original Issue: September 12, 2013 Revision 1: June 23, 2014 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.
**DESCRIPTION CONFIGURATION**  **GROUP** 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 Revision 1: June 23, 2014 13 of 68**Group Variable Number**  1 RA001 - RA034 1 RA101 - RA115 1 RA161 - RA164 1 RA201 - RA203 1 RA216 - RA217 1 RA245 - RA246 1 RA251 - RA266 1 RA301 - RA318 1 RA351 - RA360 1 RA369 - RA373 1 RA401 - RA418 1 RA501 - RA502 1 RA521 - RA528 1 RA532 - RA548 1 RA551 - RA552 1 RA559 - RA561 1 RA581 - RA582 1 RA585 1 RA601 - RA602 1 RA631 - RA635 1 RA651 - RA652 1 RA671 - RA677 1 RA701 - RA702 1 RA721 - RA731 1 RA741 - RA745 1 RA749 - RA750 1 RA761 - RA762 1 RA781 - RA784 1 RA901 - RA916 1 RB001 - RB016 1 RB041 - RB044 1 RB071 - RB075

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 14 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT Group**  **Variable Number** 1 RB101 - RB102 1 RB411 - RB413 1 RB421 1 RB601 - RB607 1 RB681 - RB697 1 RB711 1 RB721 - RB723 1 RB741 - RB748 1 RD001 - RD004 1 RD021 - RD022 1 RD041 - RD059 1 RD071 - RD072 1 RD081 - RD083 1 RD091 - RD092 1 RD101 - RD104 1 RD121 - RD127 1 RD131 - RD144 1 RD166 - RD167 1 RD171 - RD172 1 RD181 - RD183 1 RD201 - RD204 1 RD221 - RD227 1 RD231 - RD235 1 RD241 - RD243 1 RD251 - RD262 1 RD271 - RD272 1 RD291 - RD292 1 RD301 - RD302 1 RD311 1 RD351 - RD358 1 RD361 - RD366 1 RD381 - RD383 1 RD411 - RD414

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 15 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT Group**  **Variable Number** 1 RD421 - RD426 1 RD431 - RD435 1 RD441 - RD442 1 RD451 - RD456 1 RD461 1 RD471 - RD475 1 RD513 - RD519 1 RD531 - RD533 1 RD551 1 RD561 1 RD571 1 RD581 - RD583 1 RD591 - RD593 1 RD601 - RD607 1 RD621 - RD623 1 RD641 - RD649 1 RD651 - RD659 1 RD661 1 RD671 1 RD681 - RD682 1 RD691 - RD692 1 RD701 - RD702 1 RD721 - RD722 1 RD741 - RD742 1 RD751 - RD755 1 RD761 1 RD771 - RD775 1 RD781 - RD783 1 RD791 - RD792 1 RE001 2 RF001 - RF006 1 RJ131 - RJ133 1 RJ151 - RJ152

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 16 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT Group**  **Variable Number** 1 RJ301 - RJ303 1 RJ321 - RJ322 1 RJ331 - RJ333 1 RL401 2 RL402 - RL403 1 RL411 - RL414 2 RL415 - RL436 2 RL451 - RL456 2 RL461 - RL462 2 RL471 - RL481 2 RL491 - RL492 2 RL501 - RL502 2 RL511 - RL516 2 RL521 - RL522 2 RL531 - RL534 2 RL551 2 RL561 - RL568 2 RL571 - RL572 2 RL576 - RL577 2 RL579 2 RL581 - RL586 1 RL651 - RL653 2 RL654 - RL655 2 RL671 - RL675 2 RL681 - RL684 2 RL751 - RL752 1 RM001 - RM004 2 RM005 - RM007 2 RM010 1 RM011 - RM012 2 RM013 1 RM021 - RM024 1 RM026 - RM027

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 17 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT Group**  **Variable Number** 2 RM028 - RM030 1 RM036 - RM039 2 RM040 1 RM041 2 RM042 - RM045 1 RM051 2 RM052 - RM053 1 RM071 1 RM081 - RM084 1 RM091 1 RM096 - RM097 1 RM116 - RM117 1 RM126 - RM131 2 RM132 1 RM136 - RM147 1 RM156 - RM157 2 RM158 1 RM166 - RM177 1 RM191 - RM192 1 RM231 - RM233 1 RM241 - RM244 2 RM245 - RM246 1 RM261 - RM264 1 RM316 - RM318 1 RM331 - RM333 1 RM341 2 RM351 - RM355 2 RM366 - RM367 2 RM401 - RM403 2 RM426 2 RM431 2 RM441 - RM443 2 RM445

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 18 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT Group**  **Variable Number** 1 RM801 - RM802 2 RM803 1 RM811 - RM813 1 RM851 - RM853 2 RM854 - RM855 1 RM856 2 RM857 - RM859 1 RM861 2 RM862 - RM863 1 RM871 - RM873 2 RM874 - RM880 1 RM881 - RM885 2 RM886 - RM890 1 RM891 - RM899 1 RM901 - RM903 2 RM904 - RM906 1 RM911 1 RR001 - RR005 1 RR021 - RR025 1 RR031 1 RR201 - RR206 1 RR221 - RR226 1 RR261 - RR267 1 RR301 - RR310 1 RR331 - RR332 1 RR336 1 RR341 - RR345 1 RR361 - RR362 1 RR421 - RR422 1 RR431 - RR432 1 RR441 - RR442 1 RR451 1 RR501 - RR504

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 19 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT Group**  **Variable Number** 1 RR521 - RR522 1 RR526 1 RR531 1 RR551 - RR556 1 RR561 1 RR566 1 RR701 1 RR721 - RR724 1 RR746 - RR748 1 RR851 - RR856 1 RR861 - RR862 1 RR951 - RR952 1 RS001 - RS002 1 RS201 1 RS211 - RS212 1 RS221 - RS222 1 RS231 - RS241 1 RS251 - RS259 1 RS263 1 RS265 - RS268 1 RS271 - RS276 1 RS291 - RS292 1 RS301 - RS306 1 RS311 - RS320 1 RS331 - RS333 1 RS341 - RS342 1 RS699 1 RS701 - RS703 1 RS711 - RS713 1 RS721 - RS722 1 RS731 - RS732 1 RS741 - RS743 1 RS751 - RS752

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 20 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT Group**  **Variable Number** 1 RS761 - RS762 1 RS771 1 RS781 - RS782 1 RS786 1 RT001 - RT014 1 RT021 - RT022 1 RT031 - RT035 1 RT041 - RT047 1 RT061 1 RT071 - RT075 1 RT101 - RT103 1 RT121 1 RT131 - RT137 1 RT151 - RT152 1 RT161 - RT168 1 RT401 - RT412 1 RT431 - RT447 1 RT451 - RT469 1 RT471 - RT499 1 RT501 - RT535 1 RT551 - RT568 1 RT571 - RT591 1 RT601 - RT657 1 RT671 - RT673 1 RT681 - RT682 1 RT691 - RT699 1 RT701 - RT704 1 RT711 - RT717 1 RT741 - RT757 1 RT776 - RT777 1 RT781 - RT784 1 RT801 - RT803 1 RT811 - RT814

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 21 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT Group**  **Variable Number** 1 RT831 - RT837 1 RT861 - RT864 1 RT876 - RT880 1 RT931 - RT932 1 RT945 - RT949 1 RT951 - RT955 1 RT966 - RT967 1 RU001 - RU006 1 RU016 - RU017 1 RU031 - RU032 1 RU051 - RU052 1 RU059 - RU062 1 RU081 - RU083 1 RU101 - RU102 1 RU121 - RU132 1 RU801 - RU809 1 RU831 - RU841 2. Spares Affected Examine your spares supply for the parts or components identified below. If any parts or components are found, refer to Paragraph 3.B., Work Instructions for the recommended action.
**Part Number** 65B08564-7 **B. Concurrent Requirements** None. **C. Reason** 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 22 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT**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. Some of the actuator assemblies inspected at Boeing also were found to have a machining defect at the point where the tapered machining transitioned to the hemispherical machining at the top of the inner surface. This defect was visible under the finishes. This defect could eventually lead to fatigue cracks and subsequent fracture. 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 or the machining defect. 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. Revision 1 is sent to: 1. Add an inspection for a machining defect that can reduce the durability of the fitting. During inspection of the actuator fittings, many actuators were found to have a machining defect, visible under the protective finishes, in the area where the tapered machining transitioned to the hemispherical machining at the top of the inner surface. 2. Limit the compliance time that fitting assemblies with a wall thickness 0.130 inch or greater and less than 0.140 inch and do not have a machining defect can remain in-service, to 48 months or 3,000 flight-cycles after the original issue date of this service bulletin, whichever occurs first. **D. Description** 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 and Machining Defect Inspection

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 23 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT**Extend the trailing edge flaps to detent 30 and deactivate. Remove the Actuator Attach Fitting. Do an Ultrasonic (UT) inspection or mechanically determine the minimum wall thickness of the Actuator Attach Fitting. Do a DET to determine if the machining defect is present on the inner wall. 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. Part 5: Outboard Flap, Inboard Actuator Attach Fitting - Overhaul Extend the trailing edge flaps to detent 30 and deactivate. Remove the Actuator Attach Fitting. Overhaul the Actuator attach fitting and remove the machining defect. Install the Actuator Attach Fitting. Activate and retract the trailing edge flaps. Revision 1 - More work is required on airplanes with an actuator attach fitting 65B08564-7 installed which accomplished PART 3: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - MINIMUM THICKNESS INSPECTION in accordance with the Original Issue of this service bulletin. These airplanes should do PART 3: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - MINIMUM THICKNESS AND MACHINING DEFECT INSPECTION to determine if the machining defect is present and accomplish any required follow-on actions within the compliance time in Paragraph 1.E., Compliance. The work in this service bulletin is done in the maintenance zone(s) given below. **Group 1:**
**Affected Maintenance Zones Zone**  **Model** 587, 687 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR **Group 2:**
**Affected Maintenance Zones Zone**  **Model** 587, 687 747-400, 747-400F **E. Compliance** Federal Aviation Administration (FAA) Airworthiness Directive AD 2013-23-03 is related to this service bulletin. The effective date of AD 2013-23-03 is November 29, 2013. The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to Revision 1 of this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in Revision 1 of this service bulletin mandatory.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 24 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT**A logic diagram showing compliance tasks and compliance times is included as an aid in Appendix A. The Conditions, Actions and Compliance times shown apply to each Actuator Attach Fitting independently. Do the required actions in accordance with Paragraph 3. Accomplishment Instructions. When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When more than one ACTION is given for a CONDITION number or an OPTION number, do all of the ACTION numbers for that CONDITION number or OPTION number. **Table 1: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING (GIMBAL FITTING NO.S 2 AND 7) – PART NUMBER INSPECTION, MINIMUM THICKNESS INSPECTION, AND DET INSPECTION** **Repeat In terval (Not**  **to Exceed) Compliance Time**  **Action Condition** 

- Within 90 days after the effective date of AD 2013-23-03 Do PART 1: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - PART NUMBER INSPECTION to determine if a65B08564-7 actuator attach fitting is installed All Airplanes

- Within 24 months after the Revision 1 date of this service bulletin OPTION 9: Do PART 3: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - MINIMUM THICKNESS ANDMACHINING DEFECT INSPECTION, except only determine if the machining defect is presentAirplanes with an Actuator Attach Fitting 65B08564-7 installed which accomplished PART 3: OUTBOARD FLAP,INBOARD ACTUATOR ATTACH FITTING - MINIMUM THICKNESS INSPECTION inaccordance with the Original Issue of this service bulletin (c) - Within 24 months after the Revision 1 date of this service bulletin OPTION 10: Do PART 4: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - REPLACEMENT (Terminating Action) (a)

- - No additional work required (Terminating Action) (a) CONDITION 1:65B08564-7 ACTUATOR ATTACH FITTING IS NOT INSTALLED

- Before further flight OPTION 1: Do PART 2: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - DET INSPECTION for cylindrical defect CONDITION 2:65B08564-7 ACTUATOR ATTACH FITTING IS INSTALLED

OPTION 2: Do PART 4: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - REPLACEMENT (Terminating Action) (a)

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 25 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT Table 1: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING (GIMBAL FITTING NO.S 2 AND 7)**  **– PART NUMBER INSPECTION, MINIMUM THICKNESS INSPECTION, AND DET INSPECTION Repeat In**  **terval (Not to Exceed)**  **Compliance Time Action**  **Condition**

- Within 24 monthsafter the original issue date of this service bulletin OPTION 3: Do PART 3: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - MINIMUM THICKNESS AND MACHINING DEFECT INSPECTION to determine minimum wall thickness of theActuator Fitting Assembly and if the machining defect is present CONDITION 3: NO CYLINDRICAL DEFECT FOUND

OPTION 4: Do PART 4: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - REPLACEMENT (Terminating Action) (a)

- Before further flight OPTION 5: Do PART 3: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - MINIMUM THICKNESS AND MACHINING DEFECT INSPECTION to determine minimum wall thickness of theActuator Fitting Assembly and if the machining defect is present CONDITION 4: CYLINDRICAL DEFECT FOUND

OPTION 6: Do PART 4: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - REPLACEMENT (Terminating Action) (a)

- - No additional work required (Terminating Action) (a) CONDITION 5: MINIMUM THICKNESS OF WALL IS 0.140 INCH OR GREATER AND MACHINING DEFECT IS NOT PRESENT Before further flight OPTION 7: Do PART 5: OUTBOARD FLAP, INBOARD ACTUATOR ATTACHFITTING - OVERHAUL (Terminating Action) (a) CONDITION 8: MINIMUM THICKNESS OF WALL IS 0.140 INCH OR GREATER AND MACHINING DEFECT IS PRESENT OPTION 8: Do PART 4: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - REPLACEMENT (Terminating Action) (a)

- Within 48 months or 3,000 flight-cyclesafter the Original Issue date of this service bulletin, whichever occurs first. (a) (b) Do PART 4: OUTBOARD FLAP, INBOARDACTUATOR ATTACH FITTING - REPLACEMENT (Terminating Action) (a) CONDITION 6: MINIMUM THICKNESS OF WALL IS 0.130 INCH OR GREATER AND LESS THAN 0.140 INCH AND MACHINING DEFECT IS NOT PRESENT

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 26 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT Table 1: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING (GIMBAL FITTING NO.S 2 AND 7)**  **– PART NUMBER INSPECTION, MINIMUM THICKNESS INSPECTION, AND DET INSPECTION Repeat In**  **terval (Not to Exceed)**  **Compliance Time Action**  **Condition**

Before further flight Do PART 4: OUTBOARD FLAP, INBOARDACTUATOR ATTACH FITTING - REPLACEMENT (Terminating Action) (a) CONDITION 9: MINIMUM THICKNESS OF WALL IS 0.130 INCH OR GREATER AND LESS THAN 0.140 INCH AND MACHINING DEFECT IS PRESENT

- Before further flight Do PART 4: OUTBOARD FLAP, INBOARDACTUATOR ATTACH FITTING - REPLACEMENT (Terminating Action) (a) CONDITION 7: MINIMUM THICKNESS OF WALL IS LESS THAN 0.130INCH AND MACHINING DEFECT IS OR IS NOT PRESENT (a) Repeat overhauls of the actuator attach fittings are still required in accordance with service bulletin 747- 57A2316. (b) Compliance time for the attach fitting is the in-service time, and does not include storage time if an attach fitting was new, used or was overhauled and subsequently stored. Refer to SOPM 20-44-02 and SOPM 20-70-01 as accepted procedures to prepare attach fittings for storage. (c) This includes Actuator Attach Fittings that were installed that met the requirements of CONDITION 5 or CONDITION 6 in the Original Issue of this service bulletin. **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. In addition, the Manager of the FAA Seattle ACO approves the accomplishment of the inspection, rework and replacement defined in this service bulletin, as an alternative method of compliance to the inspection, rework and replacement requirements of paragraphs (g) and (h) of AD 2013-23-03. All provisions of AD 2013-23-03 that are not specifically referenced in the above statement remain fully applicable and must be complied with accordingly

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 27 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT G. Manpower**  The table below shows an estimate of the task hours necessary to do this inspection and overhaul 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. **Part 1: Outboard Flap, Inboard Actuator Attach Fitting - Part Number Inspection Elapsed Hours**  **Task Hours Number of Persons**  **Task** 0.50 1.00 2 Open Access 1.00 2.00 2 Disconnect Actuator Ball Screw Nut Inspect 0.50 0.50 1 ...Left Wing - FIGURE 1 0.50 0.50 1 ...Right Wing - FIGURE 4 1.00 2.00 2 Connect Actuator Ball Screw Nut 0.50 1.00 2 Close Access 2.00 3.50 TOTAL FOR EACH WING 4.00 7.00 TOTAL FOR EACH AIRPLANE **Part 2: Outboard Flap, Inboard Actuator Attach Fitting - DET Inspection Elapsed Hours**  **Task Hours Number of Persons**  **Task** 0.50 1.00 2 Open Access 1.00 2.00 2 Disconnect Actuator Ball Screw Nut Inspect 0.50 0.50 1 ...Left Wing - FIGURE 2 0.50 0.50 1 ...Right Wing - FIGURE 5 1.00 2.00 2 Connect Actuator Ball Screw Nut 0.50 1.00 2 Close Access 2.00 3.50 TOTAL FOR EACH WING 4.00 7.00 TOTAL FOR EACH AIRPLANE

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 28 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT Part 3: Outboard Flap, Inboard Actuator Attach Fitting - Minimum Thickness** **and Machining Defect In**  **spection Elapsed Hours**  **Task Hours Number of Persons**  **Task** 0.50 1.00 2 Open Access 1.00 2.00 2 Remove the Actuator Attach Fitting Inspect 1.00 1.00 1 ...Left Wing - FIGURE 3 1.00 1.00 1 ...Right Wing - FIGURE 6 1.00 2.00 2 Install the Actuator Attach Fitting 0.50 1.00 2 Close Access 2.50 4.00 TOTAL FOR EACH WING 5.00 8.00 TOTAL FOR EACH AIRPLANE **Part 4: Outboard Flap, Inboard Actuator Attach Fitting - Replacement Elapsed Hours**  **Task Hours Number of Persons**  **Task** 0.50 1.00 2 Open Access 1.00 2.00 2 Remove the Actuator Attach Fitting 1.00 2.00 2 Install the Actuator Attach Fitting 0.50 1.00 2 Close Access 1.50 3.00 TOTAL FOR EACH WING 3.00 6.00 TOTAL FOR EACH AIRPLANE **Part 5: Outboard Flap, Inboard Actuator Attach Fitting - Overhaul Elapsed Hours**  **Task Hours Number of Persons**  **Task** 0.50 1.00 2 Open Access 1.00 2.00 2 Remove the Actuator Attach Fitting (a) (a) Overhaul the Actuator 1.00 2.00 2 Install the Actuator Attach Fitting 0.50 1.00 2 Close Access 1.50 3.00 TOTAL FOR EACH WING 3.00 6.00 TOTAL FOR EACH AIRPLANE (a) Time to overhaul actuator dependent upon condition found during inspection. **H. Weight and Balance Changes** None.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 29 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT I. Electrical Load Data**  Not changed. **J. References** 1. Existing Data: a. Engineering Change Memo PRR 85901-129RS b. Boeing Service Bulletin 747-57A2316 c. Boeing Service Related Problem (SRP) 747-SRP-57-0264 d. Component Maintenance Manual (CMM) 57-52-55 e. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2013-23-03 f. Service Bulletin Index D6-30300 g. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-42-10, 20-44-02 , 20-50-01, 20-70-01 h. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19 i. 747 Fleet Team Digest (FTD) 57-13003 j. 747 Non-Destructive Testing (NDT) Manual Part 4, 51-00-00 k. 747-100/200/300 Aircraft Maintenance Manual (AMM) 27-51-00, 27-51-41, 27-51-46 l. 747-400 Aircraft Maintenance Manual (AMM) 27-51-00, 27-51-41, 27-51-46 2. Data Supplied with this Service Bulletin: None. 3. Installation Drawings Used in the Preparation of this Service Bulletin:
**Title Drawing Number**  Inbd. Transmission Instl Outbd. T.E. Flap Drive No. 2 And 7 65B81115 The table above lists the applicable drawing used to prepare this service bulletin. This drawing is not necessary to make the specified changes, and is not supplied with this service bulletin. The drawing may not be applicable to all airplane configurations or operators. **K. Publications Affected** 1. Publications:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 30 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT Chapter-Section**  **Publication** 57-52 Component Maintenance Manual 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: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 31 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 32 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT**

BLANK PAGE**2. MATERIAL INFORMATION A. Material - Price and Availability**  Boeing can supply the parts shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin. The parts are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. Prices are in United States Dollars. Terms: Net 30 days. Reference this service bulletin and submit your purchase order by one of these methods: 1. Order on-line via ATA Spec 2000 or The Boeing PART Page 2. Fax to (206) 662-7145 **REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION** 
**Unit Price as of the Revision 1** **date of this Ser vice Bulletin (US**  **Dollars) ROLT as of the**  **Revision 1 date of this Service Bul** 

**letin (Calendar Days)**  **QTY Date**  **Name Part Number** 

$ 13,720.00 169 25 Mar 03/14 FITTING ASSY 65B08564-9 25 Mar 31/14 25 Apr 28/14 25 May 27/14 20 Jun23/14 Operators are encouraged to complete the survey provided in the Appendix of this service bulletin to help Boeing predict the quantity and timing of the Boeing Supplied Kits/Parts. The operator can supply the parts and materials shown in Paragraph 2.C., Parts Necessary for Each Airplane . As an alternative, operators can purchase the parts from Boeing Spares. This service bulletin does not show the Boeing price and supply data. **B. Industry Support Information** Boeing warranty remedies are available for 747 airplanes in warranty as of June 5, 2013. For inspection labor task hour reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing Fleet Support Contracts - Warranty. If the condition described in this service bulletin is found during the inspection for airplanes in warranty as of that date and additional task hours and kits, parts, and/or special tools are required, send a warranty claim to Boeing Fleet Support Contracts - Warranty. Please refer to this service bulletin number and reference the airplane variable numbers in your purchase order. The warranty remedies will expire eight years from the original issue date of this service bulletin.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 33 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT 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.
**Notes Name**  **QTY Part Number / Specification**  (a) (b) (c) FITTING ASSY 2 65B08564-9 (65B08564-1 or 65B08564-5 or 65B08564-7 WHICH MEET CONDITION 5 OR CONDITION 8 (AFTER OVERHAUL) IN THIS SERVICE BULLETIN optional) (d) Primer 1 Pt BMS 10-11, TYPE I (d) Enamel 1 Pt BMS 10-60, TYPE I (a) A new Actuator Attach Fittings is only required if the installed 65B08564-7 Assemblies do not meet Condition 5 or Condition 8 (after Overhaul) in this service bulletin. (b) 65B08564-7 Actuator Attach Fittings sold by Boeing Spares after 17 June 2013 meet Condition 3 requirements. These parts will need to accomplish Part 3: Outboard Flap, Inboard Actuator Attach Fitting - Minimum Thickness and Machining Defect Inspectionand any required follow-on actions within the compliance time in Paragraph 1.E., Compliance, if installed. These actuators attach fittings are affected by this service bulletin if installed. (c) 65B08564-1, 65B08564-5, or 65B08564-9 Actuator Attach Fittings are not affected by this service bulletin. The 65B08564-9 is a new Actuator Attach Fitting which is not affected by this service bulletin and will be available at a later date. (d) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data.
3. Parts Modified and Reidentified None. 4. Parts Removed and Not Replaced None. **D. Parts Necessary to Change Spares** None.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 34 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT 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: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 35 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 36 of 68 **BOEING SERVICE BULLETIN 747-57A2343 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 747 Structural Repair Manual, Chapter 51. — Values for airframe maintenance tasks are included in Chapter 20 of 747 Airplane 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 747 Airplane Maintenance Manual (AMM). — Non-standard torque values for maintenance tasks are included in the applicable installation step.

4. Use the approved fastener and process material substitutions in accordance with SRM Chapter 51. 5. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures, and SWPM 20-10-19 for the wire separation requirements, as accepted procedures. 6. The necessary conditions for selection of clamp type and size are included in SWPM 20-10-12. If any wire bundle support clamp specified in this service bulletin does not make a correct fit on the wire bundle, refer to SWPM 20-10-12 as an accepted procedure to select a clamp that fits correctly.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 37 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT**7. 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. 8. A Detailed Inspection (DET) is defined as: An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be necessary. Surface cleaning and elaborate procedures may be required. 9. 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. 10. Refer to Appendix A for logic diagram. 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. 11. 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. 12. 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. 13. 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. 14. If shading is used, shaded areas in Figures are to separate the non-critical and non-authoritative information from the critical and authoritative information. 15. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS are in Paragraph 1.E., Compliance. 16. The CONDITIONS, ACTIONS and OPTIONS shown apply to each actuator attach fitting independently. 17. 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 38 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT B. WORK INSTRUCTIONS**  1. Additional work required for airplanes with an actuator attach fitting 65B08564-7 installed which accomplished PART 3: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - MINIMUM THICKNESS INSPECTION in accordance with the Original Issue of this service bulletin. This includes actuator fittings that were installed that met the requirements of CONDITION 5 or CONDITION 6 in the Original Issue of this service bulletin. a. OPTION 9: Do PART 3: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - MINIMUM THICKNESS AND MACHINING DEFECT INSPECTION, except only determine if the machining defect is present. **CONDITION 5: MINIMUM THICKNESS OF WALL IS 0.140 INCH OR GREATER AND**  **MACHINING DEFECT IS NOT PRESENT** (1) No additional work required (Terminating Action). **NOTE:**Repeat overhaul is still required in accordance with service bulletin 747-57A2316. **CONDITION 8: MINIMUM THICKNESS OF WALL IS 0.140 INCH OR GREATER AND MACHINING DEFECT IS PRESENT**  (1) OPTION 7: Do PART 5: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - OVERHAUL (Terminating Action). **NOTE:**Repeat overhaul is still required in accordance with service bulletin 747-57A2316. (2) OPTION 8: Do PART 4: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - REPLACEMENT (Terminating Action). **NOTE:**Repeat overhaul is still required in accordance with service bulletin 747-57A2316. **CONDITION 6: MINIMUM THICKNESS OF WALL IS 0.130 INCH OR GREATER AND LESS THAN 0.140 INCH** **AND MACHINING DEFECT IS NOT PRESENT** (1) Do PART 4: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - REPLACEMENT (Terminating Action). **NOTE:** 1. Repeat overhaul is still required in accordance with service bulletin 747-57A2316. 2. Compliance time for the attach fitting is the in-service time, and does not include storage time if an attach fitting was new, used or was overhauled and subsequently stored. Refer to SOPM 20-44-02 and SOPM 20-70-01 as accepted procedures to prepare attach fittings for storage. **CONDITION 9: MINIMUM THICKNESS OF WALL IS 0.130 INCH OR GREATER AND LESS THAN 0.140 INCH** **AND MACHINING DEFECT IS PRESENT** (1) Do PART 4: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - REPLACEMENT (Terminating Action).

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 39 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT NOTE:** Repeat overhaul is still required in accordance with service bulletin 747-57A2316. b. OPTION 10: Do PART 4: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - REPLACEMENT (Terminating Action). **NOTE:**Repeat overhaul is still required in accordance with service bulletin 747-57A2316. 2. Do PART 1: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - PART NUMBER INSPECTION to determine if a 65B08564-7 actuator attach fitting is installed. **CONDITION 1: 65B08564-7 ACTUATOR ATTACH FITTING IS NOT INSTALLED** a. No additional work required (Terminating Action). **NOTE:**Repeat overhaul is still required in accordance with service bulletin 747-57A2316. **CONDITION 2: 65B08564-7 ACTUATOR ATTACH FITTING IS INSTALLED** a. OPTION 1: Do PART 2: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - DET INSPECTION for cylindrical defect. b. OPTION 2: Do PART 4: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - REPLACEMENT (Terminating Action). **NOTE:**Repeat overhaul is still required in accordance with service bulletin 747-57A2316. **CONDITION 3: NO CYLINDRICAL DEFECT FOUND** a. OPTION 3: Do PART 3: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - MINIMUM THICKNESS AND MACHINING DEFECT INSPECTION to determine minimum wall thickness of the Actuator Fitting Assembly and if the machining defect is present b. OPTION 4: Do PART 4: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - REPLACEMENT (Terminating Action). **NOTE:**Repeat overhaul is still required in accordance with service bulletin 747-57A2316. **CONDITION 4: CYLINDRICAL DEFECT FOUND** a. OPTION 5: Do PART 3: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - MINIMUM THICKNESS AND MACHINING DEFECT INSPECTION to determine minimum wall thickness of the Actuator Fitting Assembly and if the machining defect is present b. OPTION 6: Do PART 4: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - REPLACEMENT (Terminating Action). **NOTE:**Repeat overhaul is still required in accordance with service bulletin 747-57A2316. **CONDITION 5: MINIMUM THICKNESS OF WALL IS 0.140 INCH OR GREATER AND MACHINING**  **DEFECT IS NOT PRESENT** a. No additional work required (Terminating Action).

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 40 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT NOTE:** Repeat overhaul is still required in accordance with service bulletin 747-57A2316. **CONDITION 8: MINIMUM THICKNESS OF WALL IS 0.140 INCH OR GREATER AND MACHINING DEFECT IS PRESENT**  a. OPTION 7: Do PART 5: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - OVERHAUL (Terminating Action). **NOTE:**Repeat overhaul is still required in accordance with service bulletin 747-57A2316. b. OPTION 8: Do PART 4: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - REPLACEMENT (Terminating Action). **NOTE:**Repeat overhaul is still required in accordance with service bulletin 747-57A2316. **CONDITION 6: MINIMUM THICKNESS OF WALL IS 0.130 INCH OR GREATER AND LESS THAN 0.140 INCH** **AND MACHINING DEFECT IS NOT PRESENT** a. Do PART 4: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - REPLACEMENT (Terminating Action). **NOTE:** 1. Repeat overhaul is still required in accordance with service bulletin 747-57A2316. 2. Compliance time for the attach fitting is the in-service time, and does not include storage time if an attach fitting was new, used or was overhauled and subsequently stored. Refer to SOPM 20-44-02 and SOPM 20-70-01 as accepted procedures to prepare attach fittings for storage. **CONDITION 9: MINIMUM THICKNESS OF WALL IS 0.130 INCH OR GREATER AND LESS THAN 0.140 INCH** **AND MACHINING DEFECT IS PRESENT** a. Do PART 4: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - REPLACEMENT (Terminating Action). **NOTE:**Repeat overhaul is still required in accordance with service bulletin 747-57A2316. **CONDITION 7: MINIMUM THICKNESS OF WALL IS LESS THAN 0.130 INCH AND MACHINING**  **DEFECT IS OR IS NOT PRESENT** a. Do PART 4: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - REPLACEMENT (Terminating Action). **NOTE:**Repeat overhaul is still required in accordance with service bulletin 747-57A2316. **PART 1: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - PART NUMBER INSPECTION**  1. Extend the trailing edge flaps to detent 30 and deactivate. Refer to 747-100/200/300 AMM 27-51-00 or 747-400 AMM 27-51-00 as accepted procedures.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 41 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT**2. Optional. Disconnect actuator ball screw nut from the actuator attach fitting. Refer to 747-100/200/300 AMM 27-51-41 or 747-400 AMM 27-51-41 as accepted procedures. May be required if rubber stamped part number is not visible. 3. RC - Do an inspection of the Actuator Attach Fitting to determine if part number 65B08564-7 is installed in accordance with the figure below. As an alternative, a review of the maintenance or delivery records can be used if the part number of the installed Actuator Attach Fitting can be positively determined. **Right Wing (No. 7 Actuator Attach Fitting)**  **Left Wing (No. 2 Actuator Attach Fitting)**  FIGURE 4 FIGURE 1 4. Attach actuator ball screw to the actuator attach fitting, if disconnected. Refer to 747-100/200/300 AMM 27-51-41 or 747-400 AMM 27-51-41 as accepted procedures. 5. Activate and retract the trailing edge flaps. Refer to 747-100/200/300 AMM 27-51-00 or 747-400 AMM 27-51-00 as accepted procedures. 6. Put the airplane back to a serviceable condition. **PART 2: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - DET INSPECTION** 1. Extend the trailing edge flaps to detent 30 and deactivate. Refer to 747-100/200/300 AMM 27-51-00 or 747-400 AMM 27-51-00 as accepted procedures. 2. Optional. Disconnect actuator ball screw nut from the actuator attach fitting. Refer to 747-100/200/300 AMM 27-51-41 or 747-400 AMM 27-51-41 as accepted procedures. 3. RC - Do a DET inspection of the Actuator Attach Fitting to determine if it has the cylindrical defect in accordance with the figure below. **Right Wing (No. 7 Actuator Attach Fitting)**  **Left Wing (No. 2 Actuator Attach Fitting)**  FIGURE 5 FIGURE 2 4. Attach actuator ball screw to the actuator attach fitting, if disconnected. Refer to 747-100/200/300 AMM 27-51-41 or 747-400 AMM 27-51-41 as accepted procedures. 5. Activate and retract the trailing edge flaps. Refer to 747-100/200/300 AMM 27-51-00 or 747-400 AMM 27-51-00 as accepted procedures. 6. Put the airplane back to a serviceable condition. **PART 3: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - MINIMUM THICKNESS AND MACHINING DEFECT** **INSPECTION** 1. Extend the trailing edge flaps to detent 30 and deactivate. Refer to 747-100/200/300 AMM 27-51-00 or 747-400 AMM 27-51-00 as accepted procedures.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 42 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT**2. Remove the Actuator Attach Fitting. Refer to 747-100/200/300 AMM 27-51-46 or 747-400 AMM 27-51-46 as accepted procedures. 3. RC - Do an Ultrasonic (UT) inspection or mechanically determine the minimum thickness of the Actuator Attach Fitting and a DET of the inner conical section to determine if the machining defect is present in accordance with the figure below. **Right Wing (No. 7 Actuator Attach Fitting)**  **Left Wing (No. 2 Actuator Attach Fitting)**  FIGURE 6 FIGURE 3 4. Install the Actuator Attach Fitting. Refer to 747-100/200/300 AMM 27-51-46 or 747-400 AMM 27-51-46 as accepted procedures. 5. Activate and retract the trailing edge flaps. Refer to 747-100/200/300 AMM 27-51-00 or 747-400 AMM 27-51-00 as accepted procedures. 6. Put the airplane back to a serviceable condition. **PART 4: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - REPLACEMENT** 1. Extend the trailing edge flaps to detent 30 and deactivate. Refer to 747-100/200/300 AMM 27-51-00 or 747-400 AMM 27-51-00 as accepted procedures. 2. Remove the Actuator Attach Fitting. Refer to 747-100/200/300 AMM 27-51-46 or 747-400 AMM 27-51-46 as accepted procedures. 3. RC - Install a replacement Actuator Attach Fitting listed below. Refer to 747-100/200/300 AMM 27-51-46 or 747-400 AMM 27-51-46 as an accepted procedure. a. Actuator Attach Fitting 65B08564-1, 65B08564-5, or 65B08564-9 (Terminating Action) b. Actuator Attach Fitting 65B08564-7 Assembly which meets Condition 5 in Revision 1 of this service bulletin (Terminating Action) c. Actuator Attach Fitting 65B08564-7 Assembly which meets Condition 8 in which PART 5: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - OVERHAUL has been accomplished (Terminating Action) d. Actuator attach fittings that meet the requirements of CONDITION 5 or CONDITION 6 in the Original Issue of this service bulletin. These actuator attach fittings will require additional work. These parts will need to accomplish Part 3: Outboard Flap, Inboard Actuator Attach Fitting - Minimum Thickness and Machining Defect Inspection and any required actions within the compliance times in Paragraph 1.E., Compliance. **NOTE:**Repeat overhaul is still required in accordance with service bulletin 747-57A2316. A new Actuator Attach Fitting is being designed, 65B08564-9, which will meet the terminating action requirements in this service bulletin. These new Actuator Attach Fitting will require repeat inspections and overhaul in accordance with service bulletin 747-57A2316.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 43 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT**4. Activate and retract the trailing edge flaps. Refer to 747-100/200/300 AMM 27-51-00 or 747-400 AMM 27-51-00 as accepted procedures. 5. Put the airplane back to a serviceable condition. **PART 5: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - OVERHAUL** 1. Extend the trailing edge flaps to detent 30 and deactivate. Refer to 747-100/200/300 AMM 27-51-00 or 747-400 AMM 27-51-00 as accepted procedures. 2. Remove the Actuator Attach Fitting. Refer to 747-100/200/300 AMM 27-51-46 or 747-400 AMM 27-51-46 as accepted procedures. 3. RC- Overhaul the Actuator attach fitting and remove the machining defect. Refer to the most recent revision of CMM 57-52-55 as an accepted procedure. 4. Install the Actuator Attach Fitting. Refer to 747-100/200/300 AMM 27-51-46 or 747-400 AMM 27-51-46 as accepted procedures. **NOTE:**Repeat overhaul is still required in accordance with service bulletin 747-57A2316. 5. Activate and retract the trailing edge flaps. Refer to 747-100/200/300 AMM 27-51-00 or 747-400 AMM 27-51-00 as accepted procedures. 6. Put the airplane back to a serviceable condition.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1: June 23, 2014 44 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT FIGURE 1: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - PART NUMBER INSPECTION**  **(SHEET 1 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1 June 23, 2014 45 of 68 **BOEING SERVICE BULLETIN 747-57A2343 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 one side of the airplane.
**More Data Qty**  **Identification Name**  **Task Step**  to determine if a 65B08564-7 is installed. The part number is rubber stamped between the feet on either the inboard or outboard side of the fitting. 1

- Actuator Attach Fit- ting Inspect 1

If the part number is not visible,it can be determined if a 65B08564-7 is installed bymeasuring the internal diameter at the location shown. It may be necessary to disconnect the actuator ball screw nut to gain access. Refer to 747-100/200/300 AMM 27-51- 41 or 747-400 AMM 27-51-41 as accepted procedures. 1

- Actuator Attach Fit- ting Measure 2

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.
**More Data Flag Note**  The diameter of the feature is: 1 1. 2.5 +/- 0.05 inches for the 65B08564-7 2. 2.85 +/- 0.05 inches for the 65B08564-1 or -5.

**FIGURE 1: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - PART NUMBER INSPECTION (SHEET 2 OF 2)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1 June 23, 2014 46 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT FIGURE 2: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - DET INSPECTION**  **(SHEET 1 OF 3)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1 June 23, 2014 47 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT FIGURE 2: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - DET INSPECTION**  **(SHEET 2 OF 3)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1 June 23, 2014 48 of 68 **BOEING SERVICE BULLETIN 747-57A2343 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 one side of the airplane.
**More Data Qty**  **Identification Name**  **Task Step**  Do a DET to determine if the cylindrical defect is present. The Actuator Attach Fitting should only have a conical profile. On some fittings the upper portion of the bore was made with a cylindrical defect perpendicular to the base. A borescope can be used to do this inspection. 1

- Actuator Attach Fit- ting Inspect 1

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.
**More Data Flag Note**  The cylindrical defect results in a circular ridge where the ID transitions from a conical section to a hemispherical section. When looking into the fitting with a bright light, the circular ridge is seen as change in the color, due to the change in angle of the machining. The cylindrical defect, if present, will be seen as a constant diameter feature perpendicular to the base until it transitions into the hemispherical region. 1

**FIGURE 2: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - DET INSPECTION (SHEET 3 OF 3)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1 June 23, 2014 49 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT FIGURE 3: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - MINIMUM WALL THICKNESS AND**  **MACHINING DEFECT INSPECTION (SHEET 1 OF 5)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1 June 23, 2014 50 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT FIGURE 3: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - MINIMUM WALL THICKNESS AND**  **MACHINING DEFECT INSPECTION (SHEET 2 OF 5)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1 June 23, 2014 51 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT FIGURE 3: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - MINIMUM WALL THICKNESS AND**  **MACHINING DEFECT INSPECTION (SHEET 3 OF 5)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1 June 23, 2014 52 of 68 **BOEING SERVICE BULLETIN 747-57A2343 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 one side of the airplane.
**More Data Qty**  **Identification Name**  **Task Step**  Do an Ultrasonic inspection to determine the minimum thickness of the actuator attachfitting wall in the indicated area in accordance with 747 NDT Manual Part 4, 51-00-00, Procedure 2 or Procedure 3. It is recommend the measurements be recorded for future reference. Remove finish if required; refer to SOPM 20-30-03 as an accepted procedure. As an option, mechanicallymeasure the Actuator Attach Fitting to determine the minimum thickness of the Actuator Attach Fitting in the indicated area. Scan the vertical surface every 45 + or - 10 degrees. Mark the minimum thickness location, then scan the entire circumference a minimum of 0.5 inch above and below location of the minimum thickness. 1

- Actuator Attach Fit- ting Inspect 1

**FIGURE 3: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - MINIMUM WALL THICKNESS AND MACHINING DEFECT INSPECTION**  **(SHEET 4 OF 5)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1 June 23, 2014 53 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT More Data**  **Qty Identification**  **Name Task**  **Step** Touch-up bare surfaces. Refer to SOPM 20- 42-10 as an accepted procedure. (a) - - Low Hydrogen Em-brittlement Cadmium Plating Apply 2

Touch-up bare surfaces. 2 coats. (a)

- BMS 10-11, TYPE I Primer Apply Do a DET of the inner surface of the fitting assembly to determine if a machining defectis present. There should be a smooth transition between the conical section and the hemispherical section. A machining defect is present when there is an obvious step, mismatch, gouge, or irregularity that is clearly visible under the protective finish in this area. Finish removal is not required to identify if any of these defects are present. 1

- Actuator Attach Fit- ting Inspect 3

(a) Required only if the actuator attach fitting is not being replaced or overhauled and the existing finish was removed to accomplish the inspection.

**FIGURE 3: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - MINIMUM WALL THICKNESS AND MACHINING DEFECT INSPECTION**  **(SHEET 5 OF 5)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1 June 23, 2014 54 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT FIGURE 4: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - PART NUMBER INSPECTION**  **(SHEET 1 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1 June 23, 2014 55 of 68 **BOEING SERVICE BULLETIN 747-57A2343 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 one side of the airplane.
**More Data Qty**  **Identification Name**  **Task Step**  to determine if a 65B08564-7 is installed. The part number is rubber stamped between the feet on either the inboard or outboard side of the fitting. 1

- Actuator Attach Fit- ting Inspect 1

If the part number is not visible,it can be determined if a 65B08564-7 is installed bymeasuring the internal diameter at the location shown. It may be necessary to disconnect the actuator ball screw nut to gain access. Refer to 747-100/200/300 AMM 27-51- 41 or 747-400 AMM 27-51-41 as accepted procedures. 1

- Actuator Attach Fit- ting Measure 2

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.
**More Data Flag Note**  The diameter of the feature is approximately as follows: 1 1. 2.5 +/- 0.05 inches for the 65B08564-7 2. 2.85 +/- 0.05 inches for the 65B08564-1 or -5.

**FIGURE 4: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - PART NUMBER INSPECTION (SHEET 2 OF 2)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1 June 23, 2014 56 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT FIGURE 5: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - DET INSPECTION**  **(SHEET 1 OF 3)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1 June 23, 2014 57 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT FIGURE 5: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - DET INSPECTION**  **(SHEET 2 OF 3)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1 June 23, 2014 58 of 68 **BOEING SERVICE BULLETIN 747-57A2343 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 one side of the airplane.
**More Data Qty**  **Identification Name**  **Task Step**  Do a DET to determine if the cylindrical defect is present. The Actuator Attach Fitting should only have a conical profile. On some fittings the upper portion of the bore was made with a cylindrical defect perpendicular to the base. 1

- Actuator Attach Fit- ting Inspect 1

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.
**More Data Flag Note**  The cylindrical defect results in a circular ridge where the ID transitions from a conical section to a hemispherical section. When looking into the fitting with a bright light, the circular ridge is seen as change in the color, due to the change in angle of the machining. The cylindrical defect, if present, will be seen as a constant diameter feature perpendicular to the base until it transitions into the hemispherical region. 1

**FIGURE 5: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - DET INSPECTION (SHEET 3 OF 3)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1 June 23, 2014 59 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT FIGURE 6: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - MINIMUM WALL THICKNESS AND**  **MACHINING DEFECT INSPECTION (SHEET 1 OF 5)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1 June 23, 2014 60 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT FIGURE 6: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - MINIMUM WALL THICKNESS AND**  **MACHINING DEFECT INSPECTION (SHEET 2 OF 5)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1 June 23, 2014 61 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT FIGURE 6: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - MINIMUM WALL THICKNESS AND**  **MACHINING DEFECT INSPECTION (SHEET 3 OF 5)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1 June 23, 2014 62 of 68 **BOEING SERVICE BULLETIN 747-57A2343 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 one side of the airplane.
**More Data Qty**  **Identification Name**  **Task Step**  Do an Ultrasonic inspection to determine the minimum thickness of the actuator attachfitting wall in the indicated area in accordance with 747 NDT Manual Part 4, 51-00-00, Procedure 2 or Procedure 3. It is recommend the measurements be recorded for future reference. Remove finish if required; refer to SOPM 20-30-03 as an accepted procedure. As an option, mechanicallymeasure the Actuator Attach Fitting to determine the minimum thickness of the Actuator Attach Fitting in the indicated area. Scan the vertical surface every 45 + or - 10 degrees. Mark the minimum thickness location, then scan the entire circumference a minimum of 0.5 inch above and below location of the minimum thickness. 1

- Actuator Attach Fit- ting Inspect 1

**FIGURE 6: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - MINIMUM WALL THICKNESS AND MACHINING DEFECT INSPECTION**  **(SHEET 4 OF 5)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1 June 23, 2014 63 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT More Data**  **Qty Identification**  **Name Task**  **Step** Touch-up bare surfaces. Refer to SOPM 20- 42-10 as an accepted procedure. (a) - - Low Hydrogen Em-brittlement Cadmium Plating Apply 2

Touch-up bare surfaces. 2 coats. (a)

- BMS 10-11, TYPE I Primer Apply Do a DET of the inner surface of the fitting assembly to determine if a machining defectis present. There should be a smooth transition between the conical section and the hemispherical section. A machining defect is present when there is an obvious step, mismatch, gouge, or irregularity that is clearly visible under the protective finish in this area. Finish removal is not required to identify if any of these defects are present. 1

- Actuator Attach Fit- ting Inspect 3

(a) Required only if the actuator attach fitting is not being replaced and the existing finish was removed to accomplish the inspection.

**FIGURE 6: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - MINIMUM WALL THICKNESS AND MACHINING DEFECT INSPECTION**  **(SHEET 5 OF 5)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1 June 23, 2014 64 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT APPENDIX A: LOGIC DIAGRAM**  **(SHEET 1 OF 3)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1 June 23, 2014 65 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT APPENDIX A: LOGIC DIAGRAM**  **(SHEET 2 OF 3)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1 June 23, 2014 66 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT More Data**  **Flag Note** Repeat overhauls of the actuator attach fittings are still required in accordance with service bulletin 747-57A2316. 1 Compliance time for the attach fitting is the in-service time, and does not include storage time if an attach fitting was new, used or was overhauled and subsequently stored. Refer to SOPM 20-44-02 and SOPM 20-70-01 as accepted procedures to prepare attach fittings for storage. 2

This includes actuator fittings that were installed that met the requirements of CONDITION 5 or CONDITION 6 in the Original Issue of this service bulletin. 3

**APPENDIX A: LOGIC DIAGRAM (SHEET 3 OF 3)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1 June 23, 2014 67 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT APPENDIX B: INPUT SURVEY**  **(SHEET 1 OF 1)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 12, 2013 747-57A2343 Revision 1 June 23, 2014 68 of 68 **BOEING SERVICE BULLETIN 747-57A2343 ALERT**  **ALERT**