### Commercial **Airplanes** 

# 767 Service Bulletin
**Number: 767-27A0183** Original Issue: May 09, 2002 Revision 2: September 25, 2014 ATA System: 2751 5751 **SUBJECT:** FLIGHT CONTROLS - Flaps - Outboard Flap - Deflection Control Track - Inspection/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 © 2002 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 Unpublished Work.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: May 09, 2002 767-27A0183 Revision 2: September 25, 2014 1 of 23 3.0Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 09, 2002 767-27A0183 Revision 2: September 25, 2014 2 of 23 **BOEING SERVICE BULLETIN 767-27A0183**

BLANK PAGE**Table of Contents** Revision Transmittal Sheet ............................................ 5 Summary...................................................... 7 1. PLANNING INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 2. Data Supplied with this Service Bulletin:. . . . . . . . . . . . . . . . . . . . . . . . . . . 15 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 15 K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 2. Parts and Materials Supplied by the Operator:. . . . . . . . . . . . . . . . . . . . . . . . 17 3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 4. Parts Removed and Not Replaced:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 17 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 FIGURE 1: LOGIC DIAGRAM OF INSPECTION AND MAINTENANCE ALTERNATIVES . . . . . . . 21 FIGURE 2: OUTBOARD FLAP DETECTION CONTROL TRACK - AFT LOWER LUG INSPECTION . 22

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 09, 2002 767-27A0183 Revision 2: September 25, 2014 3 of 23 **BOEING SERVICE BULLETIN 767-27A0183**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 09, 2002 767-27A0183 Revision 2: September 25, 2014 4 of 23 **BOEING SERVICE BULLETIN 767-27A0183**

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### Commercial **Airplanes** 

# 767 Service Bulletin **Revision Transmittal Sheet Number: 767-27A0183**  Original Issue: May 09, 2002 Revision 2: September 25, 2014 ATA System: 2751 5751 **SUBJECT:** FLIGHT CONTROLS - Flaps - Outboard Flap - Deflection Control Track - Inspection/Replacement This revision includes all pages of the service bulletin. **COMPLIANCE INFORMATION RELATED TO THIS REVISION** Federal Aviation Administration (FAA) Airworthiness Directive AD 2004-07-11 is related to this service bulletin. No more work is necessary on the airplanes changed or inspected in accordance with the Revision 1 of this service bulletin. **REASON FOR REVISION** This revision is sent to: 1. Revise the compliance time for airplanes VR087, VR106, VS710, VS711, VS712, VS731, VS732, VS882, VS883, VS891, and VS896 which were added to this service bulletin in Revision 1 to be the same as the original airplanes in the service bulletin. The initial compliance time for these airplanes was 1,200 flight cycles from Revision 1 date. One operator noted that the compliance time for the original airplanes in the service bulletin was before the accumulation of 12,000 total flight cycles, or within 1,200 flight cycles after the effective date of FAA AD 2004-07-11, whichever occurs later, and believes that it should be the same as the airplanes added in Revision 1. We agreed that the initial compliance time for the airplanes added in Revision 1 should be the same as the original airplanes in the service bulletin. This results in the effectivity being split into two groups to clarify the different compliance times for the airplanes in the Original Issue and the airplanes added in Revision 1. 2. Clarify summary page illustration and work instructions to match changes in logic diagram made in Revision 1. 3. Clarify the compliance time for Group 1 Airplanes in the logic diagram to add: whichever occurs later. Add Effective date of AD 2004-07-11 to Compliance section. These sections were changed: 1. Summary a. Illustration - Revised text to match Action paragraph. 2. Planning Information a. Paragraph 1.C., Reason - Added reason for Revision 2.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 09, 2002 767-27A0183 Revision 2: September 25, 2014 5 of 23b. Paragraph 1.D., Description - Added compliance information for Revision 2. c. Paragraph 1.E., Compliance - Add effective date of AD 2004-07-11. d. Paragraph 1.F., Approval - Added Revision 2 to AMOC Statement. 3. Material Information a. No Changes. 4. Accomplishment Instructions a. Paragraph 3.B., Work Instructions (1) Step 3.B.2. - Added part number of track assembly requiring inspection to match logic diagram. (2) Figure 1 (a) Added compliance time for Group 2 Airplanes. (b) Corrected the compliance time for Group 1 airplane by adding, whichever occurs later. 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** May 09, 2002 Original Issue: April 04, 2014 Revision 1: September 25, 2014 Revision 2:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 09, 2002 767-27A0183 Revision 2: September 25, 2014 6 of 23 **BOEING SERVICE BULLETIN 767-27A0183**

### Commercial **Airplanes** 

# 767 Service Bulletin **Summary Number: 767-27A0183**  Original Issue: May 09, 2002 Revision 2: September 25, 2014 ATA System: 2751 5751 **SUBJECT:** FLIGHT CONTROLS - Flaps - Outboard Flap - Deflection Control Track - Inspection/Replacement **CONCURRENT REQUIREMENTS** None. **BACKGROUND** The related 767-200, -300, and -300F service bulletin is 767-27-0184 for line numbers 1 through 921. Accomplishment of this service bulletin will detect cracking of the outboard flap deflection control track. A fractured deflection control track could result in the loss of an outboard flap in the event there is a loss of the primary flap support. The outboard flap deflection control track is located at the outboard end of the outboard flap. The track reduces the deflection of the outboard flap and provides an alternate load path to retain the flap in the event there is a loss of the primary flap support. Two operators have reported cracked or fractured deflection control tracks on three airplanes with approximately 35,700 to 54,400 flight-hours and 6,550 to 14,100 flight-cycles. The cracks all initiated in the aft lower lug run-out region. In one case the crack initiated at inclusions that is typical of the slag products that are a result of the casting process. After a crack initiates it is propagated by fatigue until the track fractures. The three cases of cracking all occurred on 767-300 airplanes. However the tracks on the 767-400ER airplane are similar in design and cracking could occur on these airplanes at the same location. Inspection of the track will detect cracking before the track fractures. Installation of the new outboard flap deflection control track assembly with thicker aft lug run-out will help prevent cracks and terminates the repeat inspections. Boeing Service Related Problem (SRP) 767-SRP-57-0154 and 767-SRP-57-0156 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 No 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

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 09, 2002 767-27A0183 Revision 2: September 25, 2014 7 of 23**Reference Affected**  **Planning Data** Paragraph 1.I., Electrical Load Data No Electrical Load Changed Paragraph 1.K., Publications Affected No 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 Yes 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 B12901-31S)** Extend the trailing edge flaps and deactivate. Do a High Frequency Eddy Current (HFEC) inspection of the aft lower lug of the outboard flap deflection control track for cracks. If no cracks are found, repeat the inspections at the interval shown in Figure 1. If cracks are found, replace the track assembly with a 113T8333-9 track assembly and terminate the repeat inspections. Retract the flaps. **EFFECTIVITY** 767-200, -300, and 400ER Airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes. **COMPLIANCE** Federal Aviation Administration (FAA) Airworthiness Directive 2004-07-11 is related to this service bulletin. See Figure 1 Logic Diagram of Inspection and Maintenance Alternatives. **INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are not available for the inspection given in this service bulletin. **MANPOWER Elapsed Hours**  **Total Task Hours** 5.50 17.00
**MATERIAL INFORMATION** Operator Supplied Parts/Materials. Refer to Paragraph 2.A., Material - Price and Availability.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 09, 2002 767-27A0183 Revision 2: September 25, 2014 8 of 23 **BOEING SERVICE BULLETIN 767-27A0183**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 09, 2002 767-27A0183 Revision 2: September 25, 2014 9 of 23 **BOEING SERVICE BULLETIN 767-27A0183**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 09, 2002 767-27A0183 Revision 2: September 25, 2014 10 of 23 **BOEING SERVICE BULLETIN 767-27A0183**

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### Commercial **Airplanes** 

# 767 Service Bulletin
**Number: 767-27A0183** Original Issue: May 09, 2002 Revision 2: September 25, 2014 ATA System: 2751 5751 **SUBJECT:** FLIGHT CONTROLS - Flaps - Outboard Flap - Deflection Control Track - Inspection/Replacement
**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. Refer to PRR-B 12901-31S (PART D) for data about this change.
**DESCRIPTION CONFIGURATION**  **GROUP** 767-400ER Airplanes line number 758 through 878.

- 1 767-200 and -300 airplanes 922 through 933

- 2

Airplane Models: 767-200, 767-300, 767-400ER **Group Variable Number**  1 VQ001 - VQ021 1 VQ071 - VQ086 2 VR087 2 VR106 2 VS710 - VS712 2 VS731 - VS732 2 VS882 - VS883 2 VS891 2 VS896

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 09, 2002 767-27A0183 Revision 2: September 25, 2014 11 of 232. Spares Affected None. **B. Concurrent Requirements** None. **C. Reason** The related 767-200, -300, and -300F service bulletin is 767-27-0184 for line numbers 1 through 921. Accomplishment of this service bulletin will detect cracking of the outboard flap deflection control track. A fractured deflection control track could result in the loss of an outboard flap in the event there is a loss of the primary flap support. The outboard flap deflection control track is located at the outboard end of the outboard flap. The track reduces the deflection of the outboard flap and provides an alternate load path to retain the flap in the event there is a loss of the primary flap support. Two operators have reported cracked or fractured deflection control tracks on three airplanes with approximately 35,700 to 54,400 flight-hours and 6,550 to 14,100 flight-cycles. The cracks all initiated in the aft lower lug run-out region. In one case the crack initiated at inclusions that is typical of the slag products that are a result of the casting process. After a crack initiates it is propagated by fatigue until the track fractures. The three cases of cracking all occurred on 767-300 airplanes. However the tracks on the 767-400ER airplane are similar in design and cracking could occur on these airplanes at the same location. Inspection of the track will detect cracking before the track fractures. Installation of the new outboard flap deflection control track assembly with thicker aft lug run-out will help prevent cracks and terminates the repeat inspections. Boeing Service Related Problem (SRP) 767-SRP-57-0154 and 767-SRP-57-0156 is related to this service bulletin. Revision 1 is sent to: 1. This revision is sent to update the logic diagram in Figure 1 and add new outboard flap deflection control track assembly with thicker aft lug run-out as terminating action to the repeat inspections. After Installing the new outboard flap deflection control track assembly with thicker aft lug run-out, it is not necessary to do the repeat inspections of the outboard flap deflection control track. 2. Add 767-200 and -300 Airplanes VR087, VR106, VS710, VS711, VS712, VS731, VS732, VS882, VS883, VS891, and VS896 to the service bulletin. These airplanes were delivered with the same flap installation as the 767-400ER airplanes and therefore should have been in this service bulletin. 3. The latest service bulletin format standards have also been updated where applicable. 4. Terminology has been changed in the Work Instructions to agree with the terminology defined in Paragraph 3.A., General Information - Notes. Revision 2 is sent to:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 09, 2002 767-27A0183 Revision 2: September 25, 2014 12 of 23 **BOEING SERVICE BULLETIN 767-27A0183**1. Revise the compliance time for airplanes VR087, VR106, VS710, VS711, VS712, VS731, VS732, VS882, VS883, VS891, and VS896 which were added to this service bulletin in Revision 1 to be the same as the original airplanes in the service bulletin. The initial compliance time for these airplanes was 1,200 flight cycles from Revision 1 date. One operator noted that the compliance time for the original airplanes in the service bulletin was before the accumulation of 12,000 total flight cycles, or within 1,200 flight cycles after the effective date of FAA AD 2004-07-11, whichever occurs later, and believes that it should be the same as the airplanes added in Revision 1. We agreed that the initial compliance time for the airplanes added in Revision 1 should be the same as the original airplanes in the service bulletin. This results in the effectivity being split into two groups to clarify the different compliance times for the airplanes in the Original Issue and the airplanes added in Revision 1. 2. Clarify summary page illustration and work instructions to match changes in logic diagram made in Revision 1. 3. Clarify the compliance time for Group 1 Airplanes in the logic diagram to add: whichever occurs later. Add Effective date of AD 2004-07-11 to Compliance section. **D. Description** Extend the trailing edge flaps and deactivate. Do a High Frequency Eddy Current (HFEC) inspection of the aft lower lug of the outboard flap deflection control track for cracks. If no cracks are found, repeat the inspections at the interval shown in Figure 1. If cracks are found, replace the track assembly with a 113T8333-9 track assembly and terminate the repeat inspections. Retract the flaps. Revision 1: 1. No more work is necessary on airplanes changed as shown in the original issue of this service bulletin. However, operators must continue to do the inspection detailed at the times given in Paragraph 1.E., Compliance until new improved outboard flap deflection control track is installed. After the installation of the new outboard flap deflection control track assembly with thicker aft lug run-out, it is not necessary to do the repeat inspections of the outboard flap deflection control track assembly. 2. Airplanes VR087, VR106, VS710, VS711, VS712, VS731, VS732, VS882, VS883, VS891, and VS896 were added to this service bulletin effectivity. These airplanes should be inspected in accordance with this service bulletin within 1,200 flight-cycles after the Revision 1 date of this service bulletin. Continue to do the repeat inspection detailed at the times given in Paragraph 1.E., Compliance until new outboard flap deflection control track assembly with thicker aft lug run-out is installed. After the installation of the new outboard flap deflection control track assembly with thicker aft lug run-out, it is not necessary to do the repeat inspections of the outboard flap deflection control track assembly. Revision 2: 1. No more work is necessary on the airplanes changed or inspected in accordance with the Revision 1 of this service bulletin. The work in this service bulletin is done in the maintenance zone(s) given below.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 09, 2002 767-27A0183 Revision 2: September 25, 2014 13 of 23 **BOEING SERVICE BULLETIN 767-27A0183 Group 1:** 
**Affected Maintenance Zones Zone**  **Model** 566, 666 767-400ER **Group 2:**
**Affected Maintenance Zones Zone**  **Model** 566, 666 767-200, 767-300 **E. Compliance** See Figure 1 Logic Diagram of Inspection and Maintenance Alternatives. Federal Aviation Administration (FAA) Airworthiness Directive 2004-07-11 is related to this service bulletin. Federal Aviation Administration (FAA) Airworthiness Directive AD 2004-07-11 is related to this service bulletin. The effective date of AD 2004-07-11 is May 11, 2004. **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. **G. Manpower** The table below shows an estimate of the task-hours necessary to do this inspection 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 09, 2002 767-27A0183 Revision 2: September 25, 2014 14 of 23 **BOEING SERVICE BULLETIN 767-27A0183 Elapsed Hours**  **Task-Hours Number of Per-**  **sons Task** 

0.50 1.00 2 Open Access 1.50 3.00 2 Inspect 3.00 12.00 4 Replace 0.50 1.00 2 Close Access 5.50 17.00 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 PRR B12901-31S (PART D), PRR B12901-31S b. Boeing Service Bulletin 767-27-0184 c. Boeing Service Related Problem (SRP) 767-SRP-57-0154, 767-SRP-57-0156 d. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2004-07-11 e. 767 Aircraft Maintenance Manual (AMM) 27-51-00, 27-51-23 f. 767 Non-Destructive Testing (NDT) Manual Part 6, 57-50-01 g. 767-400 Aircraft Maintenance Manual (AMM) 27-51-00, 27-51-23 2. Data Supplied with this Service Bulletin: None. 3. Installation Drawings Used in the Preparation of this Service Bulletin:
**Title Drawing Number**  Deflection Control and Aux. Track Installations, Outbd T.E. Flap 113T1346 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 09, 2002 767-27A0183 Revision 2: September 25, 2014 15 of 23 **BOEING SERVICE BULLETIN 767-27A0183 K. Publications Affected**  1. Publications: None. 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: May 09, 2002 767-27A0183 Revision 2: September 25, 2014 16 of 23 **BOEING SERVICE BULLETIN 767-27A0183 2. MATERIAL INFORMATION**  **A. Material - Price and Availability** 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 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: None. 2. Parts and Materials Supplied by the Operator: QTY column shows parts and materials required per airplane.
**Notes Name**  **QTY Part Number / Specifi-**  **cation** (a) TRACK ASSEMBLY 2 113T8333-9 (a) Install new outboard flap deflection control track assembly 113T8333-9 as Terminating Action to the repeat inspections.
3. Parts Modified and Reidentified: None. 4. Parts Removed and Not Replaced: None. **D. Parts Necessary to Change Spares** None. **E. Special Tooling - Price and Availability** None. **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: May 09, 2002 767-27A0183 Revision 2: September 25, 2014 17 of 23 **BOEING SERVICE BULLETIN 767-27A0183**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 09, 2002 767-27A0183 Revision 2: September 25, 2014 18 of 23 **BOEING SERVICE BULLETIN 767-27A0183**

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 limits to tighten nuts and bolts are in SRM Chapter 51 4. Use the approved fastener and process material substitutions in accordance with SRM Chapter 51. 5. If the length of any fastener specified in this service bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. 6. These work instructions refer to procedures included in other Boeing documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "in accordance with" are included in the instruction, the procedure in the Boeing document must be used. 7. 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. 8. 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. 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 09, 2002 767-27A0183 Revision 2: September 25, 2014 19 of 23 **BOEING SERVICE BULLETIN 767-27A0183**10. This service bulletin includes functional test procedures for the systems changed by this service bulletin. More functional tests can possibly be necessary in accordance with standard maintenance practices because of interruption to other airplane systems. 11. FIGURE 1 is a logic diagram of Inspection and Maintenance Alternatives. **B. WORK INSTRUCTIONS** 1. Extend the trailing edge flaps to detent 20 or greater and deactivate. Refer to 767 AMM 27-51-00 or 767-400 AMM 27-51-00 as accepted procedures. 2. Do a High Frequency Eddy Current (HFEC) inspection of the outboard flap deflection control track, 113T8333-3 or -7, aft lower lug in accordance with FIGURE 2. 3. If no cracks are found, repeat the inspections at the interval in accordance with FIGURE 1. If cracks are found, replace the track assembly with a 113T8333-9 track assembly and terminate the repeat inspections. Refer to 767 AMM 27-51-23 or 767-400 AMM 27-51-23 as accepted procedures to replace tracks. 4. Activate and retract the trailing edge flaps. Refer to 767 AMM 27-51-00 or 767-400 AMM 27-51-00 as accepted procedures. 5. Put the airplane back to a serviceable condition.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 09, 2002 767-27A0183 Revision 2: September 25, 2014 20 of 23 **BOEING SERVICE BULLETIN 767-27A0183 FIGURE 1: LOGIC DIAGRAM OF INSPECTION AND MAINTENANCE ALTERNATIVES**  **(SHEET 1 OF 1)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 09, 2002 767-27A0183 Revision 2 September 25, 2014 21 of 23 **BOEING SERVICE BULLETIN 767-27A0183 FIGURE 2: OUTBOARD FLAP DETECTION CONTROL TRACK - AFT LOWER LUG INSPECTION**  **(SHEET 1 OF 2)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 09, 2002 767-27A0183 Revision 2 September 25, 2014 22 of 23 **BOEING SERVICE BULLETIN 767-27A0183**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 High Frequency Eddy Current Inspection for cracks in the aft lower lug run-out area in accordance with 767 NDT Part 6, 57-50-01. 1 113T8333-3 OR -7 TRACK ASSEMBLY Inspect 1

**FIGURE 2: OUTBOARD FLAP DETECTION CONTROL TRACK - AFT LOWER LUG INSPECTION (SHEET 2 OF 2)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 09, 2002 767-27A0183 Revision 2 September 25, 2014 23 of 23 **BOEING SERVICE BULLETIN 767-27A0183**