### Commercial **Airplanes** 

# 767 Service Bulletin **ALERT Number: 767-57A0079**  Original Issue: June 20, 2002 Revision 1: May 06, 2010 ATA System: 5750 **SUBJECT:** WINGS - Trailing Edge and Trailing Edge Devices - Inboard Main Flap - Hinge Fitting Lug Inspection and Replacement Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 730-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws. 9E991 ECCN: 

## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2002 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work. This document includes proprietary information owned by The Boeing Company and/or one or more third parties. Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1: May 06, 2010 1 of 39 4.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1: May 06, 2010 2 of 39 **BOEING SERVICE BULLETIN 767-57A0079 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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 2. Data supplied with this Service Bulletin:. . . . . . . . . . . . . . . . . . . . . . . . . . . 18 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 18 K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 18 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 C. Parts Necessary For Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 2. Parts and Materials Supplied by the Operator:. . . . . . . . . . . . . . . . . . . . . . . . 20 3. Parts Modified and Reidentified:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 4. Parts Removed and Not Replaced:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 21 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 FIGURE 1: LOGIC DIAGRAM OF INSPECTION AND MAINTENANCE ALTERNATIVES. . . . . . . 27 FIGURE 2: HINGE FITTING - DETAILED INSPECTION. . . . . . . . . . . . . . . . . . . . . . . . . 28 FIGURE 3: HINGE FITTING - DETAILED - EDDY CURRENT INSPECTION. . . . . . . . . . . . . . 31 FIGURE 4: HINGE FITTING - REPLACEMENT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1: May 06, 2010 3 of 39 **BOEING SERVICE BULLETIN 767-57A0079 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1: May 06, 2010 4 of 39 **BOEING SERVICE BULLETIN 767-57A0079 ALERT**  **ALERT**

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### Commercial **Airplanes** 

# 767 Service Bulletin **ALERT Revision Transmittal Sheet**  **Number: 767-57A0079** Original Issue: June 20, 2002 Revision 1: May 06, 2010 ATA System: 5750 **SUBJECT:** WINGS - Trailing Edge and Trailing Edge Devices - Inboard Main Flap - Hinge Fitting Lug Inspection and Replacement This Revision includes all pages of the service bulletin. **COMPLIANCE INFORMATION RELATED TO THIS REVISION** Federal Aviation Administration (FAA) Airworthiness Directive AD 2003-13-01, is related to this service bulletin. No more work is necessary on airplanes changed in accordance with the original issue of this service bulletin. **REASON FOR REVISION** This revision is sent to: 1. To reduce the initial compliance time and repeat interval based on service reports. Subsequent to the original issue of this service bulletin, operators have reported finding 3 fractured hinge fitting assemblies. The fractured hinge fitting assemblies had accumulated less flight-cycles than the initial compliance threshold and in 1 case, the hinge fitting assembly fractured after the original inspection and prior to the next repeat inspection. Boeing Service Related Problem (SRP) 767-SRP-57-0233 was issued to address this issue. 2. Add instructions to transfer the stainless steel filler and the shims for the mid fairing roller from the old hinge fitting assembly to the new hinge fitting assembly. 3. Revise inspection area to show inspection from the center of the lug forward, not the end of the lug forward. This moves the inspection forward to inspect additional area where cracking has been found, not the lug bore where cracking has not been found. 4. Add reference to the existing AD, add an AMOC to the existing AD, and reference the possible new AD which would make the compliance tasks and times in Revision 1 of this service bulletin mandatory. 5. Update the format of the service bulletin to meet current service bulletin standards.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1: May 06, 2010 5 of 39These sections were changed: 1. Summary: a. Background - Add the new reports of fracture and reference to the new Boeing Service Related Problem (SRP) 767-SRP-57-0233. b. Compliance - Add reference to the existing AD and the possible new AD which would make the compliance tasks and times in Revision 1 of this service bulletin mandatory. 2. 1., Planning: a. C., Reason - Add new reports of fracture and reference to the new Boeing Service Related Problem (SRP) 767-SRP-57-0233. b. D., Description - Add Compliance information related to the revision and Affected Maintenance Zone Table. c. E., Compliance - Add reference to the existing the AD and the possible new AD which would make the compliance tasks and times in Revision 1 of this service bulletin mandatory. d. F., Approval - Add AMOC statement for the existing AD. e. J., References - Add reference to new SRP number. Add Reference to existing FAA AD. 3. 2., Material Information a. A., Material - Price and Availability - Updated price data. 4. 3., Accomplishment Instructions: a. A., General Notes: (1) Note 6 - Revise note to remove the one grip length variance and refer to the SRM for installation standards. Operators have reported grip length variances greater than the 1 grip length. b. B., Work Instructions: c. Figure 1 - Revise the inital threshold and the repeat interval for the Part 2 - Detailed - Eddy Current Inspection due to reports of cracks. d. Figure 3 - Illustration - Revise inspection area to show inspection from the center of the lug forward, not the end of the lug forward. e. Figure 4: (1) Illustration: Revise inspection area to show inspection from the center of the lug forward, not the end of the lug forward. (2) Step Table: Add new steps 7 and 8 to transfer the stainless steel filler and the shims for the mid fairing roller from the old hinge fitting assembly to the new hinge fitting assembly. (3) Fastener Table: Change "reference" to "refer to as an accepted procedure" to meet current service

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1: May 06, 2010 6 of 39 **BOEING SERVICE BULLETIN 767-57A0079 ALERT**  **ALERT**bulletin standards. Paragraph 1.A., Effectivity, shows changes of airplane operators. Each operator should examine the Effectivity paragraph for changes. Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location of important changes. Pages with no vertical lines have no important changes. **REVISION HISTORY** June 20, 2002 Original Issue: May 06, 2010 Revision 1:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1: May 06, 2010 7 of 39 **BOEING SERVICE BULLETIN 767-57A0079 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1: May 06, 2010 8 of 39 **BOEING SERVICE BULLETIN 767-57A0079 ALERT**  **ALERT**

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### Commercial **Airplanes** 

# 767 Service Bulletin **ALERT Summary**  **Number: 767-57A0079** Original Issue: June 20, 2002 Revision 1: May 06, 2010 ATA System: 5750 **SUBJECT:** WINGS - Trailing Edge and Trailing Edge Devices - Inboard Main Flap - Hinge Fitting Lug Inspection 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** Accomplishment of this service bulletin will detect cracks, prevent fractures and ensure the structural integrity of the inboard trailing edge main flap outboard hinge fittings. Fracture of the hinge fittings could result in the inboard aft flap becoming unrestrained potentially striking the aircraft upon departure, resulting in significant damage to the surrounding structure and cause potential personal injury. One operator of a 767-300 reported lug fractures on both the inboard and outboard hinge fittings of the outboard hinge assembly mounted to the main flap. The hinge assembly provides one of two primary attachment points of the inboard trailing edge aft flap assembly. The inboard fitting was fractured through the lug hole. The outboard fitting was fractured just above the lug hole. The fractured fittings were found during a routine maintenance inspection. The airplane had accumulated 9,598 flight-hours and 5,393 flight cycles. During root cause analysis of the fractured hinge fitting it was discovered that an optional tool runout was not present on the damaged fitting assemblies. The tool runout option allows the part to be machined thicker within the area reported to be fractured. Boeing has received no reports of cracks or fractures on fitting that have the additional material area of the optional tool runout. Service bulletin 767-57A0076 was released to inspect and replace the suspect hinge fittings if and as required on all 767-200, 767-300 and 767-300F airplanes line numbers 1 through 825. The inboard trailing edge main flap outboard hinge fittings on the 767-400 are similar in design to the 767-200, 767-300 and 767-300F fittings. The 767-400 fittings are wider and thicker however higher fatigue loads are associated with the 767-400 in this area. Analysis indicates the 767-400 fittings could be susceptible to early fatigue cracking and or fractures as a result of these higher loads. Subsequent to the original issue of this service bulletin, 3 reports of hinge assembly fracture have been received. The fractures all occurred at approximately 9,100 flight-cycles and in 1 case fracture at approximately 1,400 flight-cycles after the last detailed - eddy current inspection. Based on the reports of the fractured hinge fitting assemblies prior to the initial threshold and the repeat interval, the initial threshold and repeat interval have been reduced.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1: May 06, 2010 9 of 39Replacement of the outboard hinge fitting with a more robust designed fitting will ensure the structural integrity of the aft flap, prevent damage to the surrounding structure and the potential for personal injury. Boeing Service Related Problem (SRP) 767-SRP-57-0119 is related to this service bulletin. Boeing Service Related Problem (SRP) 767-SRP-57-0233 is related to this service bulletin. **ACTION** Inspect the inboard trailing edge fitting assemblies for cracks and or fractures. If damaged fittings are found, complete terminating action. If damaged fittings are not found, repeat the inspections at the intervals in accordance with Figure 1 until terminating action is completed. **EFFECTIVITY** 767-400 Airplanes. Refer to Paragraph 1.A., Effectivity, for the list of affected airplanes. **COMPLIANCE** Federal Aviation Administration (FAA) Airworthiness Directive AD 2003-13-01 is related to this service bulletin. The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in Revision 1 of this service bulletin mandatory. Refer to Figure 1 Logic Diagram for Inspection and Maintenance Alternatives. **INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are not available for the configuration changes, inspection and/or repair procedures given in this service bulletin. **MANPOWER** Refer to Paragraph 1.G. Manpower. **MATERIAL INFORMATION** Boeing Supplied Kits/Parts. Refer to Paragraph 2.A., Material - Price and Availability.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1: May 06, 2010 10 of 39 **BOEING SERVICE BULLETIN 767-57A0079 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1: May 06, 2010 11 of 39 **BOEING SERVICE BULLETIN 767-57A0079 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1: May 06, 2010 12 of 39 **BOEING SERVICE BULLETIN 767-57A0079 ALERT**  **ALERT**

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### Commercial **Airplanes** 

# 767 Service Bulletin **ALERT Number: 767-57A0079**  Original Issue: June 20, 2002 Revision 1: May 06, 2010 ATA System: 5750 **SUBJECT:** WINGS - Trailing Edge and Trailing Edge Devices - Inboard Main Flap - Hinge Fitting Lug Inspection 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 Refer to Service Bulletin Index Document D6-24T001 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. This service bulletin is for the airplanes shown below. An equivalent change is on subsequent production airplanes. Refer to PRR12901-9S for data about this change.
**DESCRIPTION CONFIGURATION**  **GROUP** 767-400 airplanes line numbers 758 through 877.

- 1

Airplane Models: 767-400ER **Group Variable Number**  1 VQ001 - VQ021 1 VQ071 - VQ085 2. Spares Affected Examine your 767-400 inboard trailing edge main flap spares supply for the 113T2271-401 and 113T2271-402 outboard hinge fitting assemblies. If any parts are found, refer to Paragraph 2.C. and 2.D. for the recommended use.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1: May 06, 2010 13 of 39**B. Concurrent Requirements** None. **C. Reason** Accomplishment of this service bulletin will detect cracks, prevent fractures and ensure the structural integrity of the inboard trailing edge main flap outboard hinge fittings. Fracture of the hinge fittings could result in the inboard aft flap becoming unrestrained potentially striking the aircraft upon departure, resulting in significant damage to the surrounding structure and cause potential personal injury. One operator of a 767-300 reported lug fractures on both the inboard and outboard hinge fittings of the outboard hinge assembly mounted to the main flap. The hinge assembly provides one of two primary attachment points of the inboard trailing edge aft flap assembly. The inboard fitting was fractured through the lug hole. The outboard fitting was fractured just above the lug hole. The fractured fittings were found during a routine maintenance inspection. The airplane had accumulated 9,598 flight-hours and 5,393 flight cycles. During root cause analysis of the fractured hinge fitting it was discovered that an optional tool runout was not present on the damaged fitting assemblies. The tool runout option allows the part to be machined thicker within the area reported to be fractured. Boeing has received no reports of cracks or fractures on fitting that have the additional material area of the optional tool runout. Service bulletin 767-57A0076 was released to inspect and replace the suspect hinge fittings if and as required on all 767-200, 767-300 and 767-300F airplanes line numbers 1 through 825. The inboard trailing edge main flap outboard hinge fittings on the 767-400 are similar in design to the 767-200, 767-300 and 767-300F fittings. The 767-400 fittings are wider and thicker however higher fatigue loads are associated with the 767-400 in this area. Analysis indicates the 767-400 fittings could be susceptible to early fatigue cracking and or fractures as a result of these higher loads. Subsequent to the original issue of this service bulletin, 3 reports of hinge assembly fracture have been received. The fractures all occurred at approximately 9,100 flight-cycles and in 1 case fracture at approximately 1,400 flight-cycles after the last detailed - eddy current inspection. Based on the reports of the fractured hinge fitting assemblies prior to the initial threshold and the repeat interval, the initial threshold and repeat interval have been reduced. Replacement of the outboard hinge fitting with a more robust designed fitting will ensure the structural integrity of the aft flap, prevent damage to the surrounding structure and the potential for personal injury. Boeing Service Related Problem (SRP) 767-SRP-57-0119 is related to this service bulletin. Boeing Service Related Problem (SRP) 767-SRP-57-0233 is related to this service bulletin.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1: May 06, 2010 14 of 39 **BOEING SERVICE BULLETIN 767-57A0079 ALERT**  **ALERT**Revision 1 is sent to 1. To reduce the initial compliance time and repeat interval based on service reports. Subsequent to the original issue of this service bulletin, operators have reported finding 3 fractured hinge fitting assemblies. The fractured hinge fitting assemblies had accumulated less flight-cycles than the initial compliance threshold and in 1 case, the hinge fitting assembly fractured after the original inspection and prior to the next repeat inspection. Boeing Service Related Problem (SRP) 767-SRP-57-0233 was issued to address this issue. 2. Add instructions to transfer the stainless steel filler and the shims for the mid fairing roller from the old hinge fitting assembly to the new hinge fitting assembly. 3. Revise inspection area to show inspection from the center of the lug forward, not the end of the lug forward. This moves the inspection forward to inspect additional area where cracking has been found, not the lug bore where ctracking has not been found. 4. Add reference to the existing AD, add an AMOC to the existing AD, and reference the possible new AD which would make the compliance tasks and times in Revision 1 of this service bulletin mandatory. 5. Update the format of the service bulletin to meet current service bulletin standards. **D. Description** Inspect the inboard trailing edge fitting assemblies for cracks and or fractures. If damaged fittings are found, complete terminating action. If damaged fittings are not found, repeat the inspections at the intervals in accordance with Figure 1 until terminating action is completed. Revision 1 - No more work is necessary on airplanes changed in accordance with the original issue of this service bulletin. The work in this service bulletin is done in the maintenance zone(s) given below.
**Affected Maintenance Zones Zone**  **Model** 555, 655 767-400ER **E. Compliance** Federal Aviation Administration (FAA) Airworthiness Directive AD 2003-13-01 is related to this service bulletin. The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in Revision 1 of this service bulletin mandatory. Refer to Figure 1 Logic Diagram for Inspection and Maintenance Alternatives.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1: May 06, 2010 15 of 39 **BOEING SERVICE BULLETIN 767-57A0079 ALERT**  **ALERT 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. This service bulletin has been approved by the FAA. In addition, the Manager of the Seattle Aircraft Certification Office approves the inspections, follow-on and corrective actions, and terminating action with the corresponding compliance times specified in paragraph 1.E., "Compliance," of SB 767-57A0079, Revision 1, as an AMOC to the inspections, follow-on and corrective actions, and terminating action with the corresponding compliance times specified in paragraph 1.E., "Compliance," of SB 767-57A0079, Initial Release, dated June 20, 2002, required by paragraphs (a), (b) and (f) of AD 2003-13-01. All provisions of AD 2003-13-01 that are not specifically referenced in this paragraph remain fully applicable and must be complied with. **G. Manpower** The table below shows an estimate of the task-hours necessary to do the fitting inspections and replacement 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 examine the work — Time to cure the materials — Time to make the parts — Time to find the tools. Part 1 - Detailed Inspection **Elapsed Hours Task-Hours**  **Number of Per- sons**  **Task**

1.0 2.0 2 Open Access 1.0 1.0 1 Examine 1.0 2.0 2 Close Access 3.0 5.0 TOTAL FOR EACH WING 6.0 10.0 TOTAL FOR EACH AIRPLANE

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1: May 06, 2010 16 of 39 **BOEING SERVICE BULLETIN 767-57A0079 ALERT**  **ALERT**Part 2 - Detailed Inspection - Eddy Current Inspection **Elapsed Hours Task-Hours**  **Number of Per- sons**  **Task**

1.0 2.0 2 Open Access 2.5 2.5 1 Examine 1.0 2.0 2 Close Access 4.5 6.5 TOTAL FOR EACH WING 9.0 13.0 TOTAL FOR EACH AIRPLANE Part 3 - Terminating Action **Elapsed Hours Task-Hours**  **Number of Per- sons**  **Task**

1.0 2.0 2 Open Access 6.0 12.0 2 Replace Fitting 1.0 2.0 2 Close Access 8.0 16.0 TOTAL FOR EACH WING 16.0 32.0 TOTAL FOR EACH AIRPLANE **H. Weight and Balance Changes** None. **I. Electrical Load Data** Not changed. **J. References** 1. Existing Data: a. Engineering Change Memo PRR12901-9S b. Boeing Service Bulletin 767-57A0076 c. Boeing Service Related Problem (SRP) 767-SRP-57-0119, 767-SRP-57-0233 d. Component Maintenance Manual (CMM) 57-53-27 e. Federal Aviation Administration (FAA) Airworthiness Directive 2003-13-01 f. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-41-02, 20-50-10, 20-50-19

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1: May 06, 2010 17 of 39 **BOEING SERVICE BULLETIN 767-57A0079 ALERT**  **ALERT**g. 767 Aircraft Maintenance Manual (AMM) 06-44-00, 27-51-00 h. 767 Non-Destructive Testing (NDT) Manual Part 6, Subject 51-00-01, Part 6, Subject 51-00-19 i. Boeing Drawing 012W6100 2. Data supplied with this Service Bulletin: None. 3. Installation Drawings Used in the Preparation of this Service Bulletin:
**Title Drawing Number**  Flap Instl - Inbd T.E. Flap 113T2000 This drawing was used to prepare this service bulletin. This drawing is not necessary to make the specified changes, and is not supplied with this service bulletin. This drawing may not be applicable to all airplane configurations or operators. **K. Publications Affected Chapter-Section** 

**Publication** 27-51 767 Illustrated Parts Catalog **L. Interchangeability and Intermixability of Parts** Refer to Paragraph 2.C., Parts Necessary For Each Airplane, for interchangeability and intermixability information.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1: May 06, 2010 18 of 39 **BOEING SERVICE BULLETIN 767-57A0079 ALERT**  **ALERT 2. MATERIAL INFORMATION**  **A. Material - Price and Availability** Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary For Each Airplane and Paragraph 2.D., Parts Necessary to Change Spares, as shown below. If there is a limit to the quantity (QTY) of available kits, a supply sequence is given by Spares. More kits become available as shown in the Reorder Lead Time (ROLT). ROLT is calculated from the date Boeing gets the purchase order.
**Unit Price thru Mar 31/11**  **ROLT (Weeks)**  **QTY Date**  **Name Number**  $ 45,400.00 1 May 06/02 Top Kit 015T1689-1 2 Jun 27/02 19 8 Nov 15/02 The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. After the Unit Price date, new price and ROLT data is applicable. Prices are in United States dollars. Terms: Net 30 days. **REFERENCE THIS SERVICE BULLETIN AND SUBMIT YOUR PURCHASE ORDER BY ONE OF THE METHODS THAT FOLLOW:**  1. Order on-line via ATA Spec 2000 or Boeing Part Page 2. Fax to (206) 662-7145 3. Spares Customer Support - MC 36-65 Boeing Spares Department P.O. Box 3707 Seattle, Washington 98124-2207 **B. Industry Support Information** Boeing warranty remedies are not available for the configuration changes, inspection and/or repair procedures given in this service bulletin. **C. Parts Necessary For Each Airplane** 1. Kits/Parts:
**Kit 015T1689 Notes**  **Existing Part Number**  **Name QTY**  **New Part Number -1**  **-2 -3**  Subkit, Top Kit

- . . 015T1689-1 Subkit, Hinge Fitting 1

- . 015T1689-2 Subkit, Hinge Fitting 1

. - 015T1689-3 (a)(b)(c)(f) 113T2271-401 Hinge Fitting Assembly - Left

. . 1 113T2271-419 (a)(b)(c)(g) 113T2271-402 Hinge Fitting Assembly - Right

. 1

. 113T2271-420

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1: May 06, 2010 19 of 39 **BOEING SERVICE BULLETIN 767-57A0079 ALERT**  **ALERT Kit 015T1689**  **Notes Existing Part**  **Number Name**  **QTY New Part Number**  **-1 -2**  **-3** (d) Bolt

. 2 2 BACB30LE5K19 (d) Bolt (optional 1/64 oversize)

. 2 2 BACB30LE5K19X (d) Bolt

. 2 2 BACB30LE5K20 (d) Bolt (optional 1/64 oversize)

. 2 2 BACB30LE5K20X (e) Shim

. 2 2 BACS40R015D015F (e) Shim

. 2 2 BACS40R015D017F Washer

. 4 4 BACW10BP5CD Washer (optional 1/64 oversize)

. 4 4 BACW10BP51CD Washer

. 4 4 BACW10BP5DP Washer (optional 1/64 oversize)

. 4 4 BACW10BP51DP Nut

. 4 4 NAS1805-5L (a) Discard the existing part. (b) This part is used in production. (c) You cannot use the existing part to replace the new or changed part. (d) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer than indicated. Also, if any fasteners part numbers listed are not available or have been superseded, substitute fasteners may be supplied in kits. Boeing Document D-590 and Boeing Drawing 012W6100 are used to determine the part numbers used as substitutes. (e) Use original shims located between the fitting assembly and the flap skin to maintain the original hinge line geometry of the fittings. However, if the original shims are damaged, replace shims. Maintain the thickness and location of the original shims. (f) The 113T2271-419 hinge fitting assembly is composed of a matched set of hinge fittings. The 113T2271- 415 and the 113T2271-417. (g) The 113T2271-420 hinge fitting assembly is composed of a matched set of hinge fittings. The 113T2271- 416 and the 113T2271-418. 2. Parts and Materials Supplied by the Operator:
**Notes Name**  **QTY Part Number /**  **Specification** (a) Sealant 8 ounces BMS 5-95 (a) Primer 4 ounces BMS 10-11, Type I (a) Grease 4 ounces MIL-G-23827 (a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1: May 06, 2010 20 of 39 **BOEING SERVICE BULLETIN 767-57A0079 ALERT**  **ALERT**3. Parts Modified and Reidentified: None. 4. Parts Removed and Not Replaced: None. **D. Parts Necessary to Change Spares** To get the kit shown below, refer to Paragraph 2.A., Material - Price and Availability.
**Notes QTY**  **Name Part Number**  (a) 1 Top Kit 015T1689-1 (a) The 015T1689-1 top kit consists of two 015T1689 hinge fitting sub kits. The 015T1689-2 subkit contains the parts required to rework a right inboard trailing edge main flap assembly. The 015T1689-3 subkit contains the parts required to rework a left inboard trailing edge main flap assembly. **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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1: May 06, 2010 21 of 39 **BOEING SERVICE BULLETIN 767-57A0079 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1: May 06, 2010 22 of 39 **BOEING SERVICE BULLETIN 767-57A0079 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. The instructions identified in Paragraph 3.B., Work Instructions and the Figure(s) give the recommended sequence of steps. The sequence of steps to do this service bulletin can be changed. 2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 3. Obey all of the warnings and cautions given in the specified manual sections. 4. 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 are in 767-400 SRM, Chapter 51 – Torque limits to tighten nuts and bolts are in 767-400 SRM, Chapter 51. 5. Use the approved fastener and process material substitutions in accordance with 767-400 SRM, Chapter 51, Alternate fasteners are listed in 767-400 SRM, Chapter 51 and Boeing Drawing 012W6100. 6. If the length of any fastener specified in this service bulletin does not meet the installation standards in 767-400 SRM, Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards in 767-400 SRM, Chapter 51 may be used. 7. 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. maybe necessary. Surface cleaning and elaborate procedures may be required. 8. 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. 9. 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. The removed part can be discarded if a new or serviceable part is installed.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1: May 06, 2010 23 of 39 **BOEING SERVICE BULLETIN 767-57A0079 ALERT**  **ALERT B. WORK INSTRUCTIONS**  **PART 1 - DETAILED INSPECTION WARNING:**  TRAILING EDGE FLAPS ARE FAST ACTING. MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF TRAILING EDGE FLAPS AND THE FLAP DRIVE MECHANISMS BEFORE YOU MOVE THE FLAP CONTROL LEVER. ONCE THE TRAILING EDGE FLAPS ARE DEPLOYED LOCKS MUST BE INSTALLED TO PREVENT POSSIBLE INJURY DUE TO INADVERTENT OPERATION OF THE FLAPS. 1. Extend and deactivate the trailing edge flaps. Refer to 767 AMM 27-51-00 as an accepted procedure. 2. Remove the number 3 and 6 trailing edge aft flap adjustment access panels listed below. Refer to 767 AMM 06-44-00 for location of these panels. **Right Wing Left Wing**  671GL 571GL 671GR 571GR 3. Do a Detailed Inspection (DET) of the inboard trailing edge main flap outboard hinge fittings for cracks and or fractures in accordance with Figure 2. 4. If cracked or fractured fittings are found, do Part 3 - Terminating action. 5. If no damage is found, repeat the inspections at the intervals in accordance with Figure 1 until terminating action is completed. 6. Install the number 3 and 6 trailing edge aft flap adjustment access panels listed below. Refer to 767 AMM 06-44-00 for location of these panels. **Right Wing Left Wing**  671GL 571GL 671GR 571GR 7. Activate and retract the trailing edge flaps. Refer to 767 AMM 27-51-00 as an accepted procedure. 8. Put the airplane back to a serviceable condition.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1: May 06, 2010 24 of 39 **BOEING SERVICE BULLETIN 767-57A0079 ALERT**  **ALERT PART 2 - DETAILED - EDDY CURRENT INSPECTION**  **WARNING:** TRAILING EDGE FLAPS ARE FAST ACTING. MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF TRAILING EDGE FLAPS AND THE FLAP DRIVE MECHANISMS BEFORE YOU MOVE THE FLAP CONTROL LEVER. ONCE THE TRAILING EDGE FLAPS ARE DEPLOYED LOCKS MUST BE INSTALLED TO PREVENT POSSIBLE INJURY DUE TO INADVERTENT OPERATION OF THE FLAPS. 1. Extend and deactivate the trailing edge flaps. Refer to 767 AMM 27-51-00 as an accepted procedure. 2. Remove the number 3 and 6 trailing edge aft flap adjustment access panels listed below. Refer to 767 AMM 06-44-00 for location of these panels. **Right Wing Left Wing**  671GL 571GL 671GR 571GR 3. Do a Detailed Inspection (DET) and eddy current inspection of the inboard trailing edge main flap outboard hinge fittings for cracks and or fractures in accordance with Figure 3. 4. If cracked or fractured fittings are found, do Part 3 - Terminating action. 5. If no damage is found, repeat the inspections at the intervals in accordance with Figure 1 until terminating action is completed. 6. Install the number 3 and 6 trailing edge aft flap adjustment access panels listed below. Refer to 767 AMM 06-44-00 for location of these panels. **Right Wing Left Wing**  671GL 571GL 671GR 571GR 7. Activate and retract the trailing edge flaps. Refer to 767 AMM 27-51-00 as an accepted procedure. 8. Put the airplane back to a serviceable condition.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1: May 06, 2010 25 of 39 **BOEING SERVICE BULLETIN 767-57A0079 ALERT**  **ALERT PART 3 - TERMINATING ACTION**  **WARNING:** TRAILING EDGE FLAPS ARE FAST ACTING. MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF TRAILING EDGE FLAPS AND THE FLAP DRIVE MECHANISMS BEFORE YOU MOVE THE FLAP CONTROL LEVER. ONCE THE TRAILING EDGE FLAPS ARE DEPLOYED LOCKS MUST BE INSTALLED TO PREVENT POSSIBLE INJURY DUE TO INADVERTENT OPERATION OF THE FLAPS. 1. Extend and deactivate the trailing edge flaps. Refer to 767 AMM 27-51-00 as an accepted procedure. 2. Remove the number 3 and 6 trailing edge main flap fairing mid sections listed below. Refer to 767 AMM 06-44-00 for location of these fairings. **Right Wing Left Wing**  671DB 571DB 3. Remove the number 3 and 6 trailing edge main flap fairing upper skin access panels listed below. Refer to 767 AMM 06-44-00 for location of these panels. **Right Wing Left Wing**  655HB 555HB 4. Replace the inboard trailing edge main flap outboard hinge fittings in accordance with Figure 4. 5. Install the number 3 and 6 trailing edge main flap fairing upper skin access panels listed below. Refer to 767 AMM 06-44-00 for location of these panels. **Right Wing Left Wing**  655HB 555HB 6. Install the number 3 and 6 trailing edge main flap fairing mid sections listed below. Refer to 767 AMM 06-44-00 for location of these fairings. **Right Wing Left Wing**  671DB 571DB 7. Activate and retract the trailing edge flaps. Refer to 767 AMM 27-51-00 as an accepted procedure. 8. Put the airplane back to a serviceable condition.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1: May 06, 2010 26 of 39 **BOEING SERVICE BULLETIN 767-57A0079 ALERT**  **ALERT FIGURE 1: LOGIC DIAGRAM OF INSPECTION AND MAINTENANCE ALTERNATIVES**  **(SHEET 1 OF 1)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1 May 06, 2010 27 of 39 **BOEING SERVICE BULLETIN 767-57A0079 ALERT**  **ALERT FIGURE 2: HINGE FITTING - DETAILED INSPECTION**  **(SHEET 1 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1 May 06, 2010 28 of 39 **BOEING SERVICE BULLETIN 767-57A0079 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

**FIGURE 2: HINGE FITTING - DETAILED INSPECTION (SHEET 2 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1 May 06, 2010 29 of 39 **BOEING SERVICE BULLETIN 767-57A0079 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** to remove loose dirt, grease and oil. Refer to SOPM 20-30-03 as an accepted procedure. 2

- Hinge Fittings Clean 1

Do a Detailed Inspection (DET) forcracks or fractures within the indicated area. 2

- Hinge Fittings Inspect 2

**FIGURE 2: HINGE FITTING - DETAILED INSPECTION (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1 May 06, 2010 30 of 39 **BOEING SERVICE BULLETIN 767-57A0079 ALERT**  **ALERT FIGURE 3: HINGE FITTING - DETAILED - EDDY CURRENT INSPECTION**  **(SHEET 1 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1 May 06, 2010 31 of 39 **BOEING SERVICE BULLETIN 767-57A0079 ALERT**  **ALERT**The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

**FIGURE 3: HINGE FITTING - DETAILED - EDDY CURRENT INSPECTION (SHEET 2 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1 May 06, 2010 32 of 39 **BOEING SERVICE BULLETIN 767-57A0079 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** to remove loose dirt, grease and oil. Refer to SOPM 20-30-03 as an accepted procedure. 2

- Hinge Fittings Clean 1

Do a Detailed Inspection (DET) for fractures within the indicated area. 2

- Hinge Fittings Inspect 2 Do an Eddy Current inspection for cracks within the indicated area in accordance with 767 NDT Part 6, Subject 51-00-01 or 767 NDT Part 6, Subject 51-00-19. Use a rightangle pencil probe with a maximum drop of 0.1 inch. 2

- Hinge Fittings Inspect 3

**FIGURE 3: HINGE FITTING - DETAILED - EDDY CURRENT INSPECTION (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1 May 06, 2010 33 of 39 **BOEING SERVICE BULLETIN 767-57A0079 ALERT**  **ALERT FIGURE 4: HINGE FITTING - REPLACEMENT**  **(SHEET 1 OF 6)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1 May 06, 2010 34 of 39 **BOEING SERVICE BULLETIN 767-57A0079 ALERT**  **ALERT FIGURE 4: HINGE FITTING - REPLACEMENT**  **(SHEET 2 OF 6)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1 May 06, 2010 35 of 39 **BOEING SERVICE BULLETIN 767-57A0079 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 of the airplane.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Maintain fasteners location and stackup for later installation. Refer to CMM 57-53-27 as an accepted procedure. 4

- Fasteners Remove / Keep 1

4

- Fasteners Remove 2 1 113T2271-() Hinge Fitting Assembly Remove 3 Maintain original location of shims. If shims are damaged, replace shimsmaintaining the original thickness. Apply BMS 10-11 Type I primer to thereplacement shims and any bare surfaces of the original shims. Refer toSOPM 20-41-02 as an accepted procedure. 2 BACS40R015D015F Shims "A" Remove / Keep 4

2 BACS40R015D017F Shims "B" Remove / Keep

**FIGURE 4: HINGE FITTING - REPLACEMENT (SHEET 3 OF 6)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1 May 06, 2010 36 of 39 **BOEING SERVICE BULLETIN 767-57A0079 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Locate and install hinge fitting with kept or identical replacement shims in the same location to maintain the original hinge line geometry of the fitting. Referto CMM 57-53-27 as an accepted procedure. Fay seal shims and install fasteners wet with BMS 5-95 common to the fitting assembly and the main flap. Refer to SOPM 20-50-19 as anaccepted procedure. Install kept fasteners common to the flap linkage and hinge fittings with MIL-G-23827 grease.Refer to CMM 57-53-27 as an accepted procedure. 1 113T2271-419 LEFT Hinge Fitting Assembly Install 5

1 113T2271-420 RIGHT 2 BACS40R015D015F Shims "A" (Kept) 2 BACS40R015D017F Shims "B" (Kept) 4

- Fasteners 4

- Fasteners (Kept) the incorporation of this service bulletin on each hinge fitting assembly. Refer to SOPM 20-50-10 as an accepted procedure. - - Rubber Stamp or Sten- cil Identify 6

1 BACB30LU3-20 OR BACB30LH3-20 Bolt "A" Remove / Keep 7

1 BACB30LU3-13 OR BACB30LH3-13 Bolt "B" Remove / Keep 2 BACW10BP3AP OR BACW10BP3DP Washer Remove / Keep 2 BACN10JC3 OR BACN10JC3CD Nut Remove / Keep 1 BACS40R008A026F Shim "C" Remove / Keep 2 BACS40R008E26F Shim "D" Remove / Keep 1 113T1700-9 Filler Remove / Keep

**FIGURE 4: HINGE FITTING - REPLACEMENT (SHEET 4 OF 6)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1 May 06, 2010 37 of 39 **BOEING SERVICE BULLETIN 767-57A0079 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** 1 113T1700-9 Filler Install (Kept) 8

2 BACS40R008E26F Shim "D" Install (Kept) 1 BACS40R008A026F Shim "C" Install (Kept) 1 BACB30LU3-13 OR BACB30LH3-13 Bolt "B" Install (Kept) 1 BACB30LU3-20 OR BACB30LH3-20 Bolt "A" Install (Kept) BACW10BP3AP is used with BACB30LU3-() fasteners. BACW10BP3DP is used with BACB30LH3-() fasteners. 2 BACW10BP3AP OR BACW10BP3DP Washer Install (Kept)

Tighten to 19-21 inch-pounds (20 target). BACN10JC3 is used with BACB30LU3-() fasteners. BACN10JC3CD is used with BACB30LH3-() fasteners. 2 BACN10JC3 OR BACN10JC3CD Nut Install (Kept)

The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener.

**FIGURE 4: HINGE FITTING - REPLACEMENT (SHEET 5 OF 6)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1 May 06, 2010 38 of 39 **BOEING SERVICE BULLETIN 767-57A0079 ALERT**  **ALERT**If the grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer than indicated. Also, if any of the fastener part numbers are not available or have been superseded, substitute fasteners may be supplied in Boeing kits, Boeing Document D-590 and Boeing drawing 012W6100 are used to determine the part numbers used as substitutes.
**MORE DATA HOLE DIA**  **QTY IDENTIFICATION**  **NAME CODE** 

Install bolts wet with BMS 5-95 sealant. Refer to SOPM 20-50-19 as an accepted procedure.

- - BACB30LE5K * Bolt

A BACB30LE5K * X Opt 1/64 Oversize BACW10BP5CD Washer BACW10BP51CD Opt 1/64 Oversize BACW10BP5DP Washer BACW10BP51DP Opt 1/64 Oversize NAS1805-5L Nut

**FIGURE 4: HINGE FITTING - REPLACEMENT (SHEET 6 OF 6)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 20, 2002 767-57A0079 Revision 1 May 06, 2010 39 of 39 **BOEING SERVICE BULLETIN 767-57A0079 ALERT**  **ALERT**