# Boeing Alert Service Bulletin 767-27A0229: No revision named - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2014-0430; AD 2014-22-09 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Alert Service Bulletin 767-27A0229](https://openairdocs.org/service-documents/boeing/767-27a0229.md) - Title as filed: Boeing Commercial Airplanes - Service Bulletin - Pages: 121 - PDF: https://openairdocs.org/files/sha256/19/87/1987ffdf3401f268646f4c90518d9c5c522b324b88d46e10cc071a71c7948859 - Page: https://openairdocs.org/service-documents/boeing/767-27a0229/file/1987ffdf3401 ## Text Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 Commercial Airplanes 767 Service Bulletin ALERT Number: 767-27A0229 Original Issue: March 04, 2014 ATA System: 2751 SUBJECT: FLIGHT CONTROLS - Trailing Edge Flap System - TE Flap Rotary Actuator and Reaction Ring Inspection, Rework and Replacement Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 300-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws. 9E991ECCN: BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET Copyright © 2014 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 Unpublished Work.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: March 04, 2014 767-27A0229 1 of 121 9.0 ### Page 2 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 2 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT BLANK PAGE ### Page 3 Table of Contents Summary ...................................................... 5 1. PLANNING INFORMATION ........................................ 9 A. Effectivity ................................................ 9 1. Airplanes ............................................. 9 2. Spares Affected ........................................ 1 5 B. Concurrent Requirements ...................................... 1 5 C. Reason ................................................ 1 5 D. Description .............................................. 1 6 E. Compliance .............................................. 1 7 F. Approval ............................................... 2 0 G. Manpower .............................................. 2 0 H. Weight and Balance Changes .................................... 2 2 I. Electrical Load Data ......................................... 2 2 J. References .............................................. 2 2 1. Existing Data: ......................................... 2 2 2. Data Supplied with this Service Bulletin: ........................... 2 2 3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 2 3 K. Publications Affected ........................................ 2 3 L. Interchangeability and Intermixability of Parts ........................... 2 3 M. Software Accomplishment Summary ................................ 2 4 2. MATERIAL INFORMATION ........................................ 2 5 A. Material - Price and Availability ................................... 2 5 B. Industry Support Information .................................... 2 5 C. Parts Necessary for Each Airplane ................................. 2 5 1. Kits/Parts ............................................ 2 5 2. Parts and Materials Supplied by the Operator ........................ 2 5 3. Parts Modified and Reidentified ................................ 2 8 4. Parts Removed and Not Replaced .............................. 2 8 D. Parts Necessary to Change Spares ................................. 2 9 E. Special Tooling - Price and Availability ............................... 2 9 F. Special Tooling Necessary to do this Service Bulletin ....................... 2 9 3. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 1 A. GENERAL INFORMATION ..................................... 3 1 B. WORK INSTRUCTIONS ....................................... 3 3 FIGURE 1: OUTBOARD TRAILING EDGE FLAP SUPPORT POSITION #1, #2, #7 AND #8 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING REMOVAL [Group 1-2] ......... 4 0 FIGURE 2: OUTBOARD TRAILING EDGE FLAP SUPPORT POSITION #1, #2, #7 AND #8 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING INSTALLATION [Group 1-2] ...... 4 5 FIGURE 3: INBOARD TRAILING EDGE FLAP SUPPORT POSITION #3 AND #6 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING REMOVAL [Group 1-2] ................ 4 9 FIGURE 4: INBOARD TRAILING EDGE FLAP SUPPORT POSITION #3 AND #6 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING INSTALLATION [Group 1-2] .............. 5 3 FIGURE 5: INBOARD TRAILING EDGE FLAP SUPPORT POSITION #4 AND #5 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING REMOVAL [Group 1-2] ................ 5 7 FIGURE 6: INBOARD TRAILING EDGE FLAP SUPPORT POSITION #4 AND #5 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING INSTALLATION [Group 1-2] .............. 6 1 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 3 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 4 FIGURE 7: OUTBOARD TRAILING EDGE FLAP SUPPORT POSITION #1, #2, #7 AND #8 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING REMOVAL [Group 3] .......... 6 5 FIGURE 8: OUTBOARD TRAILING EDGE FLAP SUPPORT POSITION #1, #2, #7 AND #8 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING INSTALLATION [Group 3] ....... 6 9 FIGURE 9: INBOARD TRAILING EDGE FLAP SUPPORT POSITION #3 AND #6 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING REMOVAL [Group 3] ................. 7 3 FIGURE 10: INBOARD TRAILING EDGE FLAP SUPPORT POSITION #3 AND #6 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING INSTALLATION [Group 3] ............... 7 7 FIGURE 11: INBOARD TRAILING EDGE FLAP SUPPORT POSITION #4 AND #5 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING REMOVAL [Group 3] ................. 8 0 FIGURE 12: INBOARD TRAILING EDGE FLAP SUPPORT POSITION #4 AND #5 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING INSTALLATION [Group 3] ............... 8 4 FIGURE 13: TRAILING EDGE ROTARY ACTUATOR ASSEMBLY FIXED RING GEAR DETAILED INSPECTION .......................................... 8 7 FIGURE 14: TRAILING EDGE REACTION RING DETAILED INSPECTION ............... 9 3 FIGURE 15: CORROSION AND PITTING REWORK FOR TITANIUM-CADMIUM PLATED (4340M) ROTARY ACTUATOR ASSEMBLY FIXED RING GEAR AND (4330M) REACTION RING SPLINES . 97 FIGURE 16: CORROSION AND PITTING REWORK FOR CADMIUM PLATED (15-5PH) REACTION RING SPLINES ........................................... 1 0 4 FIGURE 17: LIGHT SURFACE DAMAGE REWORK FOR TITANIUM-CADMIUM PLATED (4340M) ROTARY ACTUATOR ASSEMBLY FIXED RING GEAR AND (4330M) REACTION RING SPLINES . 110 FIGURE 18: LIGHT SURFACE DAMAGE REWORK FOR CADMIUM PLATED (15-5PH) REACTION RING SPLINES ........................................... 1 1 3 FIGURE 19: SPLINE BLENDOUT AND LIMIT GUIDE .......................... 1 1 7 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 4 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 5 Commercial Airplanes 767 Service Bulletin ALERT SummaryNumber: 767-27A0229Original Issue: March 04, 2014 ATA System: 2751 SUBJECT: FLIGHT CONTROLS - Trailing Edge Flap System - TE Flap Rotary Actuator and Reaction Ring 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 Accomplishment of this service bulletin will provide operators with a repetitive inspection to check the outboard and inboard trailing edge flap rotary actuator joints, replace the rotary actuator or reaction ring if necessary and update the grease to a corrosion inhibiting compound. If this service bulletin is not done, flaps could separate from the airplane, which could lead to loss of airplane control during takeoff or landing. Boeing recently received a report of an unexpected roll on a 767-300ER. The control input required to offset the condition was 0.5 to 1.5 units of aileron trim and was ultimately traced to an Outboard TE flap skew condition. This was the first report of this condition in the fleet. Investigation by the operator revealed that the #7 TE flap rotary actuator had slipped relative to its mating reaction ring that is attached to the flap support rib. Removal of the reaction ring and actuator revealed that the mating splines were severely corroded. The noted airplane was delivered in June 1997 and had accumulated approximately 79,000 hours and 14,000 cycles in service. The potential for the subject condition exists on all 767-200/-300/-300F airplanes prior to L/N 922. The early design of this interface utilized MIL-PRF-23827 grease to lubricate the mating splines of the actuator and reaction ring. The 767-400ER installation utilized BMS 3-27 corrosion inhibiting compound(CIC). Boeing later revised the actuator / reaction ring interface to be assembled using BMS 3-38, also a CIC material, for all other 767 models, from L/N 922 and on. The MIL-PRF-23827 grease must not be used on the mating splines of the actuator and reaction ring. After further evaluation of the joint design for the 767-400ER, and for all other model 767's, from L/N 922 and on, it was determined that periodic teardown inspections and reapplication of the BMS 3-38 was required to prevent significant corrosion of this joint over the life of the airplane. Boeing recommends checking 767-200/-300/-300F airplanes from L/N 922 and on and 767-400ER airplanes from L/N 758 and on, for the subject condition as recommended by the Compliance Table. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 5 of 121 ### Page 6 Boeing worked with the operator to gather more information after the initial report and performed a safety analysis of the event and potential cascading implications beyond that which was reported. It was found that if the corrosion were to affect the mating splines on either surface (actuator or ring) to the point where they could no longer effectively engage, the actuator would be prone to possible slippage. Due to the similarity of the design, the potential condition could develop at multiple flap supports. Should degradation reach the point where both actuators on a single flap were unable to react the torsion created by air loads, a flap blowback could occur. The condition of uncommanded roll with flaps extended, due to flap blowback or loss, could potentially degrade handling performance and preclude continued safe flight and landing. Boeing Service Related Problem (SRP) 767-SRP-27-0238 is related to this service bulletin. Boeing Fleet Team Digest Article 767 FTD FTD-27-13001 is related to this service bulletin. This table is provided to operators for planning purposes only. Refer to the applicable sections for more information. ReferenceAffectedPlanning Data Paragraph 1.A.2., Spares AffectedNoSpares Affected Paragraph 1.E., Compliance and Paragraph 1.F., Approval YesAD Related Paragraph 1.H., Weight and Balance ChangesNoWeight and Balance Change Paragraph 1.I., Electrical Load DataNoElectrical Load Changed Paragraph 1.K., Publications AffectedYesPublications Affected Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew Operations Manual and/or FAA Approved Air- plane Flight Manual) Paragraph 2.C.1., Kits/PartsNoKits/Parts Required Paragraph 2.C.2., Parts and Materials Supplied by the Operator YesOperator Supplied Parts/Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin NoSpecial Tooling Required ACTION PART 1: AIRPLANE WORK - TRAILING EDGE FLAP - SUPPORT POSITIONS 1, 2, 3, 4, 5, 6, 7 AND 8 - ROTARY ACTUATOR ASSEMBLY FIXED RING GEAR AND REACTION RING SPLINE INSPECTION – Prepare the access in accordance with PART 3. – Remove the rotary actuator assembly and the reaction ring if necessary in accordance with PART 4. – Do a Detailed Inspection of the rotary actuator assembly fixed ring gear splines and reaction ring splines. – If there is no corrosion on the rotary actuator assembly fixed ring gear splines or reaction ring splines, then no rework is required and the parts are ready to be reinstalled onto the airplane in accordance with PART 5. – If there is corrosion on the rotary actuator assembly fixed ring gear splines, replace the rotary actuator assembly with a new rotary actuator assembly, or with a rotary actuator assembly that has been repaired in accordance with PART 2. Install rotary actuator assembly in accordance with PART 5. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 6 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 7 – If there is corrosion on the reaction ring splines, replace the reaction ring with a new reaction ring, or a reaction ring that has been repaired in accordance with PART 2. Install the reaction ring in accordance with PART 5. PART 2: COMPONENT WORK - TRAILING EDGE FLAP - SUPPORT POSITIONS 1, 2, 3, 4, 5, 6, 7 AND 8 - ROTARY ACTUATOR ASSEMBLY FIXED RING GEAR AND REACTION RING SPLINE REPAIR – Do a Detailed Inspection of the rotary actuator assembly fixed ring gear splines and reaction ring splines in accordance with PART 1. – Repair the rotary actuator assembly fixed ring gear splines and reaction ring splines in accordance with PART 2. EFFECTIVITY 767-200, -300, -300F, -400ER Airplanes. Refer to Paragraph 1.A., Effectivity for the list of affected airplanes. COMPLIANCE The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Refer to Paragraph 1.E., Compliance. INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the inspections and repair procedures given in this service bulletin. MANPOWER Refer to Paragraph 1.G., Manpower. MATERIAL INFORMATION None. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 7 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 8 (OCR) BOEING SERVICE BULLETIN 767-27A0229 ALERT ALERT ROTARY ACTUATOR ASSEMBLY NO. 6 ROTARY ROTARY ACTUATOR ACTUATOR ROTARY ACTUATOR NO. 7 ASSEMBLY ASSEMBLY NO. 8 ASSEMBLY NO. 5 ROTARY ACTUATOR ASSEMBLY ROTARY NO. 3 ACTUATOR ASSEMBLY NO. 4 OUTBOARD ROTARY FLAP ACTUATOR ASSEMBLY NO. 2 INBOARD ROTARY FLAP ACTUATOR ASSEMBLY NO. 1 AT ROTARY ACTUATOR ASSEMBLY LOCATIONS, DO A GENERAL HE VISUAL INSPECTION (GVI) FOR CORROSION ON THE MATING SPLINE SURFACES OF THE ROTARY ACTUATOR ASSEMBLY FIXED RING GEAR AND THE RE ACTION RING. IF THERE IS CORROSION ON THE ROTARY ACT OR ASSEMBLY FIXED RING GEAR SPLINES, REPLACE THE ROTARY ACTUATOR ASSEMBLY WITH A NEW ROTARY ACTUATOR ASSEMBLY, OR WITH A ROTARY ACTUATOR ASSEMBLY FIXED RING GEAR THAT HAS BEEN REPAIRED. IF THERE IS CORROSION ON THE REACTION RING SPLINES, REPLACE THE REACTION RING WITH A NEW REACTION RING, OR WITH A REACTION RING THAT HAS BEEN REPAIRED. COMPONENT WORK: REPAIR MATING SPLINE SURFACES OF THE ROTARY ACTUATOR ASSEMBLY FIXED RING GEAR AND REACTION RING. TRAILING EDGE FLAP ROTARY ACTUATOR LOCATIONS 2267964 Original Issue: March 04, 2014 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 767-27A0229 Work - See page 1 for details. 8 of 121 ### Page 9 Commercial Airplanes 767 Service Bulletin ALERT Number: 767-27A0229 Original Issue: March 04, 2014 ATA System: 2751 SUBJECT: FLIGHT CONTROLS - Trailing Edge Flap System - TE Flap Rotary Actuator and Reaction Ring 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 Service Bulletin Index D624T001 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. NOTE: The Variable Number table below includes all affected airplanes up to Line Number 1083. Affected airplanes after Line Number 1083 will be added to the service bulletin's MyBoeingFleet.com (MBF) "get effectivity" result when they are added to the MBF Fleet Profile Page. DESCRIPTIONCONFIGURATIONGROUP 767-200, -300, -300F Airplanes from Line Number 1 through 921.-1 767-200, -300, -300F Airplanes from Line Number 922 and on.-2 767-400ER Airplanes from Line Number 758 and on.-3 Airplane Models: 767-200, 767-300, 767-300F, 767-400ER GroupVariable Number 1VA001 - VA020 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 9 of 121 ### Page 10 GroupVariable Number 1VA301 - VA315 1VA501 - VA530 1VA701 - VA719 1VA801 - VA810 1VB001 - VB002 1VB051 - VB055 1VB101 - VB125 1VB201 - VB202 1VB251 - VB253 1VB281 - VB284 1VB301 - VB302 1VB321 - VB332 1VB371 - VB373 1VB401 1VB441 - VB444 1VE001 - VE003 1VE021 - VE023 1VE041 - VE043 1VE061 - VE069 1VE083 - VE086 1VE101 - VE104 1VE116 - VE118 1VE121 - VE126 1VE141 - VE152 1VE171 - VE172 1VF001 - VF002 1VF041 - VF042 1VF051 1VF061 - VF062 1VF071 - VF072 1VF091 - VF093 1VF101 - VF102 1VF161 - VF162 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 10 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 11 GroupVariable Number 1VF171 - VF172 1VF180 - VF184 1VF251 1VK001 - VK016 1VK021 - VK022 1VK031 - VK056 1VK081 - VK113 1VK131 - VK133 1VK141 - VK148 1VK161 - VK164 1VK171 1VK181 1VK186 1VL001 - VL006 1VL011 1VL701 - VL703 1VL751 - VL755 1VL806 - VL807 1VL871 - VL873 1VL891 - VL900 1VL911 - VL914 1VL931 - VL932 1VL941 1VN001 - VN041 1VN051 - VN064 1VN081 - VN099 1VN111 - VN127 1VN130 - VN137 1VN151 - VN158 1VN163 - VN168 1VN171 - VN174 1VN191 - VN198 1VN211 - VN212 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 11 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 12 GroupVariable Number 1VN221 - VN225 1VN231 - VN234 1VN241 - VN243 1VN251 - VN276 1VN291 - VN293 1VN301 - VN314 1VN371 - VN372 1VN376 1VN381 - VN388 1VN421 - VN427 1VN436 1VN471 - VN472 1VN491 - VN513 1VN531 - VN532 1VN536 - VN537 1VN541 - VN542 1VN546 - VN547 1VN551 1VN556 - VN557 1VN561 - VN562 1VN631 - VN638 1VN651 - VN658 1VN671 - VN672 1VN676 1VN681 - VN691 1VN731 - VN732 1VN751 - VN753 1VN791 - VN792 1VN811 - VN813 1VN921 - VN922 1VN931 - VN936 1VN951 - VN953 1VN966 - VN972 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 12 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 13 GroupVariable Number 3VQ001 - VQ021 3VQ071 - VQ086 3VQ111 1VR051 - VR060 1VR081 1VR084 1VR086 2VR087 - VR089 2VR106 - VR109 1VR201 - VR211 1VR251 1VR256 - VR260 2VR266 - VR292 1VR401 1VR421 - VR423 1VR426 1VR441 1VR461 1VR471 - VR472 1VS051 - VS056 1VS061 1VS066 - VS070 1VS073 - VS078 1VS091 - VS104 1VS111 - VS113 1VS131 - VS133 1VS136 - VS137 1VS176 - VS177 1VS186 - VS187 1VS196 - VS203 1VS206 - VS208 1VS211 1VS216 - VS217 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 13 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 14 GroupVariable Number 1VS231 1VS246 - VS248 1VS261 - VS263 1VS266 - VS274 1VS291 - VS293 1VS301 - VS303 1VS306 - VS311 1VS316 1VS321 - VS324 1VS331 - VS333 1VS336 - VS337 1VS366 - VS367 1VS381 - VS382 1VS391 - VS392 1VS401 1VS426 - VS428 1VS466 - VS472 1VS486 1VS496 - VS497 1VS506 - VS507 1VS526 1VS546 - VS549 1VS701 - VS709 2VS710 - VS720 1VS721 - VS730 2VS731 - VS736 1VS751 - VS759 1VS821 - VS825 1VS841 - VS844 1VS861 1VS881 2VS882 - VS883 2VS891 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 14 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 15 GroupVariable Number 2VS896 2VS901 - VS912 2VS916 2VS921 - VS928 2VS931 - VS933 2VS941 2VS951 - VS954 2VS961 - VS969 2VS971 - VS977 2VS981 - VS984 2VT001 - VT013 2VT021 2VT031 - VT033 1VT501 2VT511 - VT513 2VT521 - VT523 2VT531 - VT533 2VT541 - VT546 2VT551 - VT552 2VT556 - VT573 2VV001 1VW701 - VW721 1VW851 2. Spares Affected None. B. Concurrent Requirements None. C. Reason Accomplishment of this service bulletin will provide operators with a repetitive inspection, to check the outboard and inboard trailing edge flap rotary actuator joints, replace the rotary actuator or reaction ring if necessary and update the grease to a corrosion inhibiting compound. If this service bulletin is not done, flaps could separate from the airplane, which could lead to loss of airplane control during takeoff or landing. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 15 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 16 Boeing recently received a report of an unexpected roll on a 767-300ER. The control input required to offset the condition was 0.5 to 1.5 units of aileron trim and was ultimately traced to an Outboard TE flap skew condition. This was the first report of this condition in the fleet. Investigation by the operator revealed that the #7 TE flap rotary actuator had slipped relative to its mating reaction ring that is attached to the flap support rib. Removal of the reaction ring and actuator revealed that the mating splines were severely corroded. The noted airplane was delivered in June 1997 and had accumulated approximately 79,000 hours and 14,000 cycles in service. The potential for the subject condition exists on all 767-200/-300/-300F airplanes prior to L/N 922. The early design of this interface utilized MIL-PRF-23827 grease to lubricate the mating splines of the actuator and reaction ring. The 767-400ER installation utilized BMS 3-27 corrosion inhibiting compound(CIC). Boeing later revised the actuator / reaction ring interface to be assembled using BMS 3-38, also a CIC material, for all other 767 models, from L/N 922 and on. The MIL-PRF-23827 grease must not be used on the mating splines of the actuator and reaction ring. After further evaluation of the joint design for the 767-400ER, and for all other model 767's, from L/N 922 and on, it was determined that periodic teardown inspections and reapplication of the BMS 3-38 was required to prevent significant corrosion of this joint over the life of the airplane. Boeing recommends checking 767-200/-300/-300F airplanes from L/N 922 and on and 767-400ER airplanes from L/N 758 and on, for the subject condition as recommended by the Compliance Table. Boeing worked with the operator to gather more information after the initial report and performed a safety analysis of the event and potential cascading implications beyond that which was reported. It was found that if the corrosion were to affect the mating splines on either surface (actuator or ring) to the point where they could no longer effectively engage, the actuator would be prone to possible slippage. Due to the similarity of the design, the potential condition could develop at multiple flap supports. Should degradation reach the point where both actuators on a single flap were unable to react the torsion created by air loads, a flap blowback could occur. The condition of uncommanded roll with flaps extended, due to flap blowback or loss, could potentially degrade handling performance and preclude continued safe flight and landing. Boeing Service Related Problem (SRP) 767-SRP-27-0238 is related to this service bulletin. Boeing Fleet Team Digest Article 767 FTD FTD-27-13001 is related to this service bulletin. D. Description PART 1: AIRPLANE WORK - TRAILING EDGE FLAP - SUPPORT POSITIONS 1, 2, 3, 4, 5, 6, 7 AND 8 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING SPLINE INSPECTION – Prepare the access in accordance with PART 3. – Remove the rotary actuator assembly and the reaction ring if necessary in accordance with PART 4. – Do a Detailed Inspection of the rotary actuator assembly fixed ring gear splines and reaction ring splines. – If there is no corrosion on the rotary actuator assembly fixed ring gear splines or reaction ring splines, then no rework is required and the parts are ready to be reinstalled onto the airplane in accordance with PART 5. – If there is corrosion on the rotary actuator assembly fixed ring gear splines, replace the rotary actuator assembly with a new rotary actuator assembly, or with a rotary actuator assembly that has been repaired in accordance with PART 2. Install rotary actuator assembly in accordance with PART 5. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 16 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 17 – If there is corrosion on the reaction ring splines, replace the reaction ring with a new reaction ring, or a reaction ring that has been repaired in accordance with PART 2. Install the reaction ring in accordance with PART 5. PART 2: COMPONENT WORK - TRAILING EDGE FLAP - SUPPORT POSITIONS 1, 2, 3, 4, 5, 6, 7 AND 8 - ROTARY ACTUATOR ASSEMBLY FIXED RING GEAR AND REACTION RING SPLINE REPAIR – Do a Detailed Inspection of the rotary actuator assembly fixed ring gear splines and reaction ring splines in accordance with PART 1. – Repair the rotary actuator assembly fixed ring gear splines and reaction ring splines in accordance with PART 2. The work in this service bulletin is done in the maintenance zone(s) given below. Group 1-2: Affected Maintenance Zones ZoneModel 566, 666767-200, 767-300, 767-300F Group 3: Affected Maintenance Zones ZoneModel 566, 666767-400ER E. Compliance The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 17 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 18 Group 1: Table 1: INSPECTION, REPAIRS OF THE ACTUATOR/REACTION RING SUPPORT POSITIONS #1, #2, #3, #4, #5, #6, #7 and #8 Repeat Interval (Not to Exceed) Compliance TimeActionCondition Within 12 years.Within 30 months after the original is- sue date of this Service Bulletin. Do a Detailed Inspection, in accordance with the Accomplishment Instruc- tions PART 1. All GROUP 1 Airplanes, Trailing Edge Actuator/Re- action Ring joints at sup- port positions #1, #2, #3, #4, #5, #6, #7 and #8 that have not been disassem- bled within 6 years prior to the original issue date of this Service Bulletin. Within 12 years.Within 6 years after the original issue date of this Service Bulletin. Do a Detailed Inspection, in accordance with the Accomplishment Instruc- tions PART 1. All GROUP 1 Airplanes, Trailing Edge Actuator/Re- action Ring joints at sup- port positions #1, #2, #3, #4, #5, #6, #7 and #8 that have been disassembled within 6 years prior to the original issue date of this Service Bulletin. --The rotary actuator as- sembly fixed ring gear and reaction ring do not need to be replaced. The rotary actuator assembly and reaction ring are ready to reinstall onto the airplane in accordance with PART 5. PART 1, CONDITION 1: NO CORROSION ON THE TE ROTARY ACTUATOR FIXED RING GEAR AND REACTION RING SPLINES. PART 1, CONDITION 2: -Before Further flight. Replace the rotary actua- tor assembly with a new rotary actuator assembly, or with a rotary actuator assembly that has been repaired in accordance with PART 2. CORROSION ON THE TE ROTARY ACTUATOR FIXED RING GEAR SPLINES. Replace the reaction ring with a new reaction ring, or a reaction ring that has been repaired in accor- dance with PART 2. CORROSION ON THE REACTION RING SPLINES Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 18 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 19 Group 2-3: Table 2: INSPECTION, REPAIRS OF THE ACTUATOR/REACTION RING SUPPORT POSITIONS #1, #2, #3, #4, #5, #6, #7 and #8 Repeat Interval (Not to Exceed) Compliance TimeActionCondition Within 12 years.Within 6 years after the original issue date of this Service Bulletin, within 12 years from the date of issuance of the original certificate of airworthiness or the original export certificate of airwor- thiness, whichever occurs later. Do a Detailed Inspection, in accordance with the Accomplishment Instruc- tions PART 1. All GROUP 2 and GROUP 3 Airplanes, Trailing Edge Actuator/Reaction Ring joints at support positions #1, #2, #3, #4, #5, #6, #7 and #8 that have not been disassembled within 6 years prior to the original issue date of this Service Bulletin. Within 12 years.Within 12 years af- ter the original is- sue date of this Service Bulletin. Do a Detailed Inspection, in accordance with the Accomplishment Instruc- tions PART 1. All GROUP 2 and GROUP 3 Airplanes, Trailing Edge Actuator/Reaction Ring joints at support positions #1, #2, #3, #4, #5, #6, #7 and #8 that have been dis- assembled within 6 years prior to the original issue date of this Service Bul- letin. --The rotary actuator as- sembly fixed ring gear and reaction ring do not need to be replaced. The rotary actuator assembly and reaction ring are ready to reinstall onto the airplane in accordance with PART 5. PART 1, CONDITION 1: NO CORROSION ON THE TE ROTARY ACTUATOR FIXED RING GEAR AND REACTION RING SPLINES. PART 1, CONDITION 2: Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 19 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 20 Group 2-3: Table 2: INSPECTION, REPAIRS OF THE ACTUATOR/REACTION RING SUPPORT POSITIONS #1, #2, #3, #4, #5, #6, #7 and #8 Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Before Further flight. Replace the rotary actua- tor assembly with a new rotary actuator assembly, or with a rotary actuator assembly that has been repaired in accordance with PART 2. CORROSION ON THE TE ROTARY ACTUATOR FIXED RING GEAR SPLINES. Replace the reaction ring with a new reaction ring, or a reaction ring that has been repaired in accor- dance with PART 2. CORROSION ON THE REACTION RING SPLINES 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/repair/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 inspect 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: March 04, 2014 767-27A0229 20 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 21 TABLE 1: AIRPLANE WORK - TRAILING EDGE FLAP - SUPPORT POSITIONS #1, #2, #3, #4, #5, #6, #7 AND #8 - ROTARY ACTUATOR ASSEMBLY FIXED RING GEAR AND REACTION RING SPLINE INSPECTION Elapsed HoursTask HoursNumber of Per- sons Task 2.004.002PART 3: PREPARE ACCESS 4.0024.006PART 4: TRAILING EDGE FLAP - SUP- PORT POSITIONS #1, #2, #3, #4, #5, #6, #7 and #8 - RO- TARY ACTUATOR ASSEMBLY AND REACTION RING REMOVAL 2.004.002PART 1: AIRPLANE WORK - TRAILING EDGE FLAP - SUP- PORT POSITIONS #1, #2, #3, #4, #5, #6, #7 and #8 - RO- TARY ACTUATOR ASSEMBLY FIXED RING GEAR AND REACTION RING SPLINE INSPEC- TION 4.0024.006PART 5: TRAILING EDGE FLAP - SUP- PORT POSITIONS #1, #2, #3, #4, #5, #6, #7 and #8 - RO- TARY ACTUATOR ASSEMBLY AND REACTION RING INSTALLATION 2.004.002Close Access 14.0060.00TOTAL FOR EACH AIRPLANE TABLE 2 - COMPONENT WORK - TRAILING EDGE FLAP - SUPPORT POSITIONS #1, #2, #3, #4, #5, #6, #7, and #8 - ROTARY ACTUATOR ASSEMBLY FIXED RING GEAR AND REACTION RING SPLINE REPAIR Elapsed HoursTask HoursNumber of Per- sons Task 4.004.001FIGURE 13 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 21 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 22 TABLE 2 - COMPONENT WORK - TRAILING EDGE FLAP - SUPPORT POSITIONS #1, #2, #3, #4, #5, #6, #7, and #8 - ROTARY ACTUATOR ASSEMBLY FIXED RING GEAR AND REACTION RING SPLINE REPAIR Elapsed HoursTask HoursNumber of Per- sons Task 4.004.001FIGURE 14 (a)(a)FIGURE 15 (a)(a)FIGURE 16 (a)(a)FIGURE 17 (a)(a)FIGURE 18 (a)(a)FIGURE 19 8.008.00TOTAL FOR EACH AIRPLANE (a) Estimated time for the tasks are variable, depending upon number of parts affected and extent of repairs required. H. Weight and Balance Changes None. I. Electrical Load Data Not changed. J. References 1. Existing Data: a. Boeing Service Related Problem (SRP) 767-SRP-27-0238 b. Component Maintenance Manual (CMM) 27-51-08, 27-51-10, 27-51-48, 27-51-49 c. Standard Overhaul Practices Manual (SOPM) 20-10-01, 20-10-02, 20-10-03, 20-20-01, 20-30-02, 20-30-03, 20-41-02, 20-42-02, 20-42-05, 20-42-10, 20-50-01 d. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19 e. 767 Aircraft Maintenance Manual (AMM) 27-51-00, 27-51-05, 27-51-11, 27-51-22 f. 767 Fleet Team Digest (FTD) FTD-27-13001 g. 767 Illustrated Parts Catalog (IPC) 27-51 2. Data Supplied with this Service Bulletin: None. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 22 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 23 3. Installation Drawings Used in the Preparation of this Service Bulletin: TitleDrawing Number Flap Instl Pos. 1 and 8, Flap Actuation (a)113T3000 Rib Assy Pos. 1 and 8, Flap Actuation (b)113T1328 Flap Instl Pos. 2 and 7, Flap Actuation (a)113T3000 Rib Assy Pos. 2 and 7, Flap Actuation (b)113T1329 Flap Instl Pos. 3 and 6, Flap Actuation (a)113T2000 Rib Assy Pos. 3 and 6, Flap Actuation (b)113T1200 Flap Instl Pos. 4 and 5, Flap Actuation (a)113T2000 Rib Assy Pos. 4 and 5, Flap Actuation (b)113T1200 Actuator Instl Pos. 1 and 8, Flap Actuation (a)256T3240 Actuator Instl Pos. 1 and 8, Flap Actuation (b)256T6100 Actuator Instl Pos. 2 and 7, Flap Actuation (a)256T3280 Actuator Instl Pos. 2 and 7, Flap Actuation (b)256T6200 Actuator Instl Pos. 3 and 6, Flap Actuation (a)256T3200 Actuator Instl Pos. 3 and 6, Flap Actuation (b)256T6300 Actuator Instl Pos. 4 and 5, Flap Actuation (a)256T3290 Actuator Instl Pos. 4 and 5, Flap Actuation (b)256T6400 (a) For 767-200, -300, -300F. (b) For 767-400ER. K. Publications Affected 1. Publications: Chapter-SectionPublication 767 IPC 27-51767 Illustrated Parts Catalog 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. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 23 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 24 M. Software Accomplishment Summary Not affected. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 24 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 25 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 inspections and 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 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. Group 1-2: NotesNameQTYPart Number / Specification (a)Reaction Ring, Outboard Flap - Sup No. 1 and 2. 1113T1342-1 (a)Reaction Ring, Outboard Flap - Sup No. 1 and 2. 1113T1342-7 Reaction Ring, Outboard Flap - Sup No. 1 and 2. 1113T1342-9 (b)Reaction Ring, Outboard Flap - Sup No. 7 and 8. 1113T1342-2 (b)Reaction Ring, Outboard Flap - Sup No. 7 and 8. 1113T1342-8 Reaction Ring, Outboard Flap - Sup No. 7 and 8. 1113T1342-10 (c)Reaction Ring, Inboard Flap - Sup No. 3. 1113T1251-1 Reaction Ring, Inboard Flap - Sup No. 3. 1113T1251-7 (d)Reaction Ring, Inboard Flap - Sup No. 6. 1113T1251-2 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 25 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 26 Group 1-2: NotesNameQTYPart Number / Specification Reaction Ring, Inboard Flap - Sup No. 6. 1113T1251-8 (e)Reaction Ring, Inboard Flap - Sup No. 4. 1113T1269-3 Reaction Ring, Inboard Flap - Sup No. 4. 1113T1269-9 (f)Reaction Ring, Inboard Flap - Sup No. 5. 1113T1269-4 Reaction Ring, Inboard Flap - Sup No. 5. 1113T1269-10 Rotary Actuator Assembly, Outboard Flap Sup No. 1, 2, 7 and 8. 1256T3250-2 (g)Rotary Actuator Assembly, Outboard Flap Sup No. 1, 2, 7 and 8. 1256T3250-4 Rotary Actuator Assembly, Inboard Flap Sup No. 3 and 6. 1256T3210-2 Rotary Actuator Assembly, Inboard Flap Sup No. 3 and 6. 1256T3210-4 Rotary Actuator Assembly, Inboard Flap Sup No. 4 and 5. 1256T3250-2 (g)Rotary Actuator Assembly, Inboard Flap Sup No. 4 and 5. 1256T3250-4 To be installed into the Re- action Rings located at Sup No. 1, 2, 4, 5, 7 and 8. One seal per one reaction ring. Reaction Ring Seal6113T1256-31 To be installed into the Re- action Rings located at Sup No. 3 and 6. One seal per one reaction ring. Reaction Ring Seal2113T1256-29 (h)Shim1113T1361-2 (i)Shim1113T1361-3 (j)Shim1113T1361-4 Shim1113T1361-5 Shim1113T1361-13 Shim1113T1361-14 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 26 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 27 Group 1-2: NotesNameQTYPart Number / Specification Use for installation of Reac- tion Ring Seal. (k) Primer-BMS 10-11 Use on rotary actuator and reaction ring splines. (k) Corrosion Inhibiting Compound-BMS 3-38 (a) Optional replacement part is 113T1342-9. (b) Optional replacement part is 113T1342-10. (c) Optional replacement part is 113T1251-7. (d) Optional replacement part is 113T1251-8. (e) Optional replacement part is 113T1269-9. (f) Optional replacement part is 113T1269-10. (g) Optional replacement part is 256T3250-2. (h) Optional replacement part is 113T11361-5. (i) Optional replacement part is 113T11361-13. (j) Optional replacement part is 113T11361-14. (k) See the Qualified Products List at the end of Boeing Material Specification (BMS) for supplier data. Group 3: NotesNameQTYPart Number / Specification Reaction Ring, Outboard Flap - Sup No. 1 and 2. 1113T1342-5 Reaction Ring, Outboard Flap - Sup No. 7 and 8. 1113T1342-6 Reaction Ring, Inboard Flap - Sup No. 3. 1113T1251-5 Reaction Ring, Inboard Flap - Sup No. 6. 1113T1251-6 Reaction Ring, Inboard Flap - Sup No. 4. 1113T1269-7 Reaction Ring, Inboard Flap - Sup No. 5. 1113T1269-8 (a)Rotary Actuator Assembly, Outboard Flap Sup No. 1, 2, 7 and 8. 1256T6110-2 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 27 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 28 Group 3: NotesNameQTYPart Number / Specification (a)Rotary Actuator Assembly, Outboard Flap Sup No. 1, 2, 7 and 8. 1256T6110-3 (b)Rotary Actuator Assembly, Inboard Flap Sup No. 3 and 6. 1256T6310-2 (b)Rotary Actuator Assembly, Inboard Flap Sup No. 3 and 6. 1256T6310-3 (a)Rotary Actuator Assembly, Inboard Flap Sup No. 4 and 5. 1256T6110-2 (a)Rotary Actuator Assembly, Inboard Flap Sup No. 4 and 5. 1256T6110-3 To be installed into the Re- action Rings located at Sup No. 1, 2, 4, 5, 7 and 8. One seal per one reaction ring. Reaction Ring Seal6113T1256-31 To be installed into the Re- action Rings located at Sup No. 3 and 6. One seal per one reaction ring. Reaction Ring Seal2113T1256-29 To be installed at Sup No. 1 and 8. Shim2113T1361-11 To be installed at Sup No. 2 and 7. Shim2113T1361-12 To be installed at Sup No. 4 and 5. Shim2113T1361-14 Use for installation of Reac- tion Ring Seal. Primer-BMS 10-11 Use on rotary actuator and reaction ring splines. Corrosion Inhibiting Compound-BMS 3-38 (a) The 256T6110-2 and 256T6110-3 are interchangeable with one another. (b) The 256T6310-2 and 256T6310-3 are interchangeable with one another. 3. Parts Modified and Reidentified None. 4. Parts Removed and Not Replaced None. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 28 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 29 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: March 04, 2014 767-27A0229 29 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 30 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 30 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT BLANK PAGE ### Page 31 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 – Torque Values: — Values for structural fasteners are given in Structural Repair Manual, Chapter 51. 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. 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 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. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 31 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 32 9. A General Visual Inspection is defined as: A visual examination of an interior or exterior area, installation or assembly to detect obvious damage, failure or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight or drop-light and may require removal or opening of access panels or doors. Stands, ladders or platforms may be required to gain proximity to the area being checked. 10. 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. 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. 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. 15. If shading is used, shaded areas in Figures are to separate the non-critical and non-authoritative information from the critical and authoritative information. 16. 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. 17. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS are in Paragraph 1.E., Compliance. 18. 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: March 04, 2014 767-27A0229 32 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 33 B. WORK INSTRUCTIONS PART 1: AIRPLANE WORK - TRAILING EDGE FLAP - SUPPORT POSITIONS #1, #2, #3, #4, #5, #6, #7 and #8 - ROTARY ACTUATOR ASSEMBLY FIXED RING GEAR AND REACTION RING SPLINE INSPECTION 1. Prepare for access in accordance with PART 3. 2. Remove the rotary actuator assembly and the reaction ring in accordance with PART 4. 3. Clean the spline mating surfaces of the TE rotary actuator assembly fixed ring gear and the reaction ring. Refer to SOPM 20-30-03 as an accepted procedure. a. The reaction ring does not need to be removed from the rib structure if a Detailed Inspection for corrosion of the reaction ring is done and no corrosion is found. 4. RC - Do a Detailed Inspection, for corrosion, of the rotary actuator assembly fixed ring gear and reaction ring splines for each support position. CONDITION 1 - NO CORROSION ON THE TE ROTARY ACTUATOR ASSEMBLY FIXED RING GEAR AND REACTION RING SPLINES a. RC - If there is no corrosion on the TE rotary actuator assembly fixed ring gear splines, then the rotary actuator assembly does not need to be replaced or reworked. b. RC - If there is no corrosion on the reaction ring splines, then the reaction ring does not need to be removed from the rib support and replaced. c. RC - Surface wear is acceptable on the surfaces of the spline teeth where contact is made between the Rotary Actuator Ring Gear and the Reaction Ring. Surface wear is defined as a change in color or a local loss of finishes, provided there is no surface corrosion or pitting. d. RC - Install the rotary actuator assembly in accordance with PART 5. CONDITION 2 - CORROSION ON THE TE ROTARY ACTUATOR ASSEMBLY FIXED RING GEAR SPLINES OR REACTION RING SPLINES a. RC - If there is corrosion on the rotary actuator assembly fixed ring gear splines, replace the rotary actuator assembly with a new rotary actuator assembly, or with a rotary actuator assembly that has been repaired in accordance with PART 2. b. RC - If there is corrosion on the reaction ring splines, then replace the reaction ring with a new reaction ring, or with a reaction ring that has been repaired in accordance with PART 2. c. RC - Install the rotary actuator assembly and reaction ring in accordance with PART 5. PART 2: COMPONENT WORK - TRAILING EDGE FLAP - SUPPORT POSITIONS #1, #2, #3, #4, #5, #6, #7 and #8 - ROTARY ACTUATOR ASSEMBLY FIXED RING GEAR AND REACTION RING SPLINE REPAIR 1. Disassemble the rotary actuator assembly to isolate the fixed ring gear that contains the splines before reworking the splines. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 33 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 34 a. Group 1-2: For rotary actuator assemblies at support positions #1, #2, #4, #5, #7 and #8, refer to CMM 27-51-10. b. Group 1-2: For rotary actuator assemblies at support positions #3 and #6, refer to CMM 27-51-08. c. Group 3: For rotary actuator assemblies at support positions #1, #2, #4, #5, #7 and #8, refer to CMM 27-51-49. d. Group 3: For rotary actuator assemblies at support positions #3 and #6, refer to CMM 27-51-48. 2. RC - Do a Detailed Inspection, for corrosion, of the rotary actuator assembly fixed ring gear in accordance with FIGURE 13 a. Repair the rotary actuator assembly fixed ring gear in accordance with CONDITION 3. 3. RC - Do a Detailed Inspection, for corrosion, of the reaction ring in accordance with FIGURE 14. a. Repair the reaction rings made of 4330M steel Titanium-Cadmium plated in accordance with CONDITION 4. b. Repair the reaction rings made of 15-5PH CRES CADMIUM plated in accordance with CONDITION 5. CONDITION 3 - CORROSION ON THE TE ROTARY ACTUATOR ASSEMBLY FIXED RING GEAR MADE OF 4340M TITANIUM-CADMIUM PLATED a. RC - ACTION 1: Do the repair for Light Surface Damage in accordance with FIGURE 17. NOTE: Before doing any plating, baking and refinish work, make sure to measure and evaluate the reworked parts in accordance with FIGURE 19. (1) Measure and evaluate the repaired parts in accordance with FIGURE 19. (a) If the reworked rotary actuator assembly fixed ring gear is within limits, then the rotary actuator assembly can be installed onto the airplane in accordance with PART 5. (b) If the reworked rotary actuator assembly fixed ring gear is not within limits, then the rotary actuator assembly must be replaced with a new rotary actuator assembly, or a rotary actuator assembly that has been repaired in accordance with PART 2. b. RC - ACTION 2: Do the repair for moderate corrosion pitting and heavy corrosion pitting in accordance with FIGURE 15. NOTE: Before doing any plating, baking and refinish work, make sure to measure and evaluate the reworked parts in accordance with FIGURE 19. (1) Measure and evaluate the repaired parts in accordance with FIGURE 19. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 34 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 35 (a) If the reworked rotary actuator assembly fixed ring gear is within limits, then the rotary actuator assembly can be installed onto the airplane in accordance with PART 5. (b) If the reworked rotary actuator assembly fixed ring gear is not within limits, then the rotary actuator assembly must be replaced with a new rotary actuator assembly, or a rotary actuator assembly that has been repaired in accordance with PART 2. CONDITION 4 - CORROSION PITTING ON THE REACTION RING MADE OF 4330M TITANIUM-CADMIUM PLATED a. RC - ACTION 3: Do the repair for Light Surface Damage in accordance with FIGURE 17. NOTE: Before doing any plating, baking and refinish work, make sure to measure and evaluate the reworked parts in accordance with FIGURE 19. (1) Measure and evaluate the repaired parts in accordance with FIGURE 19. (a) If the reworked reaction ring is within limits, it can be installed onto the airplane as shown in PART 5. (b) If the reworked reaction ring is not within limits, it must be replaced with a new reaction ring or a reaction ring that has been repaired in accordance with PART 2. b. RC - ACTION 4: Do the repair for moderate corrosion pitting and heavy corrosion pitting, in accordance with FIGURE 15. NOTE: Before doing any plating, baking and refinish work, make sure to measure and evaluate the reworked parts in accordance with FIGURE 19. (1) Measure and evaluate the repaired parts in accordance with FIGURE 19. (a) If the reworked reaction ring is within limits, it can be installed onto the airplane as shown in PART 5. (b) If the reworked reaction ring is not within limits, it must be replaced with a new reaction ring or a reaction ring that has been repaired in accordance with PART 2. CONDITION 5 - CORROSION PITTING ON THE REACTION RING MADE OF 15-5PH CADMIUM PLATED a. RC - ACTION 5: Do the repair for Light Surface Damage in accordance with FIGURE 18. NOTE: Before doing any plating, baking and refinish work, make sure to measure and evaluate the reworked parts in accordance with FIGURE 19. (1) Measure and evaluate the repaired parts in accordance with FIGURE 19. (a) If the reworked reaction ring is within limits, it can be installed onto the airplane as shown in PART 5. (b) If the reworked reaction ring is not within limits, it must be replaced with a new reaction ring or a reaction ring that has been repaired in accordance with PART 2. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 35 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 36 b. RC - ACTION 6: Do the repair for moderate corrosion pitting and heavy corrosion pitting, in accordance with FIGURE 16. NOTE: Before doing any plating, baking and refinish work, make sure to measure and evaluate the reworked parts in accordance with FIGURE 19. (1) Measure and evaluate the repaired parts in accordance with FIGURE 19. (a) If the reworked reaction ring is within limits, it can be installed onto the airplane as shown in PART 5. (b) If the reworked reaction ring is not within limits, it must be replaced with a new reaction ring or a reaction ring that has been repaired in accordance with PART 2. PART 3: PREPARE ACCESS 1. Prepare for access as follows. a. For support positions #1, #2, #7 and #8 rotary actuator assembly removal. Refer to 767 AMM 27-51-22. b. For support positions #3 and #6 rotary actuator assembly removal. Refer to 767 AMM 27-51-11. c. For support positions #4 and #5 rotary actuator assembly removal. Refer to 767 AMM 27-51-05. PART 4: TRAILING EDGE FLAP - SUPPORT POSITIONS #1, #2, #3, #4, #5, #6, #7 and #8 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING REMOVAL 1. Do PART 3 - PREPARE ACCESS. 2. Remove the TE rotary actuator assembly as follows. a. For support positions #1, #2, #7 and #8 rotary actuator assembly removal: (1) Group 1-2: Refer to 767 AMM 27-51-22 and in accordance with FIGURE 1. (2) Group 3: Refer to 767 AMM 27-51-22 and in accordance with FIGURE 7. b. For support positions #3 and #6 rotary actuator assembly removal: (1) Group 1-2: Refer to 767 AMM 27-51-11 and in accordance with FIGURE 3. (2) Group 3: Refer to 767 AMM 27-51-11 and in accordance with FIGURE 9. c. For support positions #4 and #5 rotary actuator assembly removal: (1) Group 1-2: Refer to 767 AMM 27-51-05 and in accordance with FIGURE 5. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 36 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 37 (2) Group 3: Refer to 767 AMM 27-51-05 and in accordance with FIGURE 11. 3. Remove the reaction rings as followings. NOTE: Before removing the reaction ring from the rib support, see PART 1 - INSPECTION, CONDITION 1, because the reaction ring does not need to be removed from the rib structure, if reaction ring corrosion is not found. a. For support positions #1, #2, #7 and #8 reaction ring removal: (1) Group 1-2: In accordance with FIGURE 1. (2) Group 3: In accordance with FIGURE 7. b. For support positions #3 and #6 reaction ring removal: (1) Group 1-2: In accordance with FIGURE 3. (2) Group 3: In accordance with FIGURE 9. c. For support positions #4 and #5 reaction ring removal: (1) Group 1-2: In accordance with FIGURE 5. (2) Group 3: In accordance with FIGURE 11. PART 5: TRAILING EDGE FLAP - SUPPORT POSITIONS #1, #2, #3, #4, #5, #6, #7 and #8 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING INSTALLATION 1. Install the reaction ring as follows. NOTE: Make sure to use BMS 3-38 corrosion inhibiting compound to cover the splines after installation of the reaction ring. a. Make sure to install the grease seal into the reaction ring, before installing the reaction ring on the rib support. (1) For support positions #1, #2, #7 and #8, install the grease seal into the reaction ring: (a) Group 1-2: In accordance with FIGURE 2. (b) Group 3: In accordance with FIGURE 8 (2) For support positions #3 and #6 install the grease seal into the reaction ring: Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 37 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 38 (a) Group 1-2: In accordance with FIGURE 4 (b) Group 3: In accordance with FIGURE 10 (3) For support positions #4 and #5 install the grease seal into the reaction ring: (a) Group 1-2: In accordance with FIGURE 6 (b) Group 3: In accordance with FIGURE 12 b. For support positions #1, #2, #7 and #8 install the reaction ring: (1) Group 1-2: In accordance with FIGURE 2. (2) Group 3: In accordance with FIGURE 8. c. For support positions #3 and #6 install the reaction ring: (1) Group 1-2: In accordance with FIGURE 4. (2) Group 3: In accordance with FIGURE 10. d. For support positions #4 and #5 install the reaction ring: (1) Group 1-2: In accordance with FIGURE 6. (2) Group 3: In accordance with FIGURE 12. 2. Install the TE rotary actuator assembly as follows. NOTE: Make sure to use BMS 3-38 corrosion inhibiting compound to cover the splines prior to installation of the rotary actuator. a. For support positions #1, #2, #7 and #8 rotary actuator assembly installation: (1) Group 1-2: Refer to 767 AMM 27-51-22 and in accordance with FIGURE 2. (2) Group 3: Refer to 767 AMM 27-51-22 and in accordance with FIGURE 8. b. For support positions #3 and #6 rotary actuator assembly installation: Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 38 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 39 (1) Group 1-2: Refer to 767 AMM 27-51-11 and in accordance with FIGURE 4 (2) Group 3: Refer to 767 AMM 27-51-11 and in accordance with FIGURE 10 c. For support positions #4 and #5 rotary actuator assembly installation: (1) Group 1-2: Refer to 767 AMM 27-51-05 and in accordance with FIGURE 6. (2) Group 3: Refer to 767 AMM 27-51-05 and in accordance with FIGURE 12. 3. Put the airplane back to a serviceable condition. Refer to 767 AMM 27-51-22. 4. Do the Trailing Edge Flap System - Adjustment/Test, refer to 767 AMM 27-51-00. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 39 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 40 (OCR) BOEING SERVICE BULLETIN 767-27A0229 ALERT ALERT This Figure applies only to: Group 1-2. WING REAR SPAR HOLD-DOWN CLAMP (3 LOCATIONS) TORQUE TUBE REFERENCE ALIGN MARK ROTARY ACTUATOR ASSEMBLY ROTARY ACTUATOR ASSEMBLY 2267931 FIGURE 1: OUTBOARD TRAILING EDGE FLAP SUPPORT POSITION #1, #2, #7 AND #8 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING REMOVAL (SHEET 1 OF 5) Original Issue: March 04, 2014 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 767-27A0229 Work - See page 1 for details. 40 of 121 ### Page 41 (OCR) BOEING SERVICE BULLETIN 767-27A0229 ALERT ALERT 8) RING \ REACTION (6) SEAL SHIM TRAILING EDGE (TE) FLAP SUPPORT RIB POSITION 1 SHOWN. TE FLAP SUPPORT RIB POSITION 2, 7 AND 8 SIMILAR. 2267932 FIGURE 1: OUTBOARD TRAILING EDGE FLAP SUPPORT POSITION #1, #2, #7 AND #8 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING REMOVAL (SHEET 2 OF 5) Original Issue: March 04, 2014 Export Controlled ECCN: 9E991 - BOEING 767-27 A0229 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 41 of 121 ### Page 42 More DataQtyIdentificationNameTaskStep Remove the rotary actuator. Refer to 767 AMM 27-51-22 as an accepted pro- cedure. 1256T3250-2Rotary Actuator Assem- bly Remove1 Remove the rotary actuator. Refer to 767 AMM 27-51-22 as an accepted pro- cedure. 1256T3250-4Rotary Actuator Assem- bly Remove 2NAS1805-7LNutRemove2 2BACW10BP7PWasherRemove 3NAS1805-6LNutRemove3 3BACW10BP6PWasherRemove 3NAS1805-6LNutRemove4 3BACW10BP6PWasherRemove 8NAS1805-7LNutRemove5 8BACW10BP7PWasherRemove FIGURE 1: OUTBOARD TRAILING EDGE FLAP SUPPORT POSITION #1, #2, #7 AND #8 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING REMOVAL (SHEET 3 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 42 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 43 More DataQtyIdentificationNameTaskStep Remove seal from the reaction ring be- fore temperature stress relieving. Dis- card the removed seal. (a) 1113T1342-1Reaction RingRemove6 Remove seal from the reaction ring be- fore temperature stress relieving. Dis- card the removed seal. (a) 1113T1342-2Reaction RingRemove Remove seal from the reaction ring be- fore temperature stress relieving. Dis- card the removed seal. (a) 1113T1342-7Reaction RingRemove Remove seal from the reaction ring be- fore temperature stress relieving. Dis- card the removed seal. (a) 1113T1342-8Reaction RingRemove Remove seal from the reaction ring be- fore temperature stress relieving. Dis- card the removed seal. (a) 1113T1342-9Reaction RingRemove Remove seal from the reaction ring be- fore temperature stress relieving. Dis- card the removed seal. (a) 1113T1342-10Reaction RingRemove Remove seal from the reaction ring be- fore temperature stress relieving. Dis- card the removed seal. (a) 1113T1256-31SealRemove FIGURE 1: OUTBOARD TRAILING EDGE FLAP SUPPORT POSITION #1, #2, #7 AND #8 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING REMOVAL (SHEET 4 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 43 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 44 More DataQtyIdentificationNameTaskStep 1113T1361-2ShimRemove / Keep7 1113T1361-5ShimRemove / Keep (b)1113T1342-1Reaction RingClean8 (b)1113T1342-2Reaction RingClean (b)1113T1342-7Reaction RingClean (b)1113T1342-8Reaction RingClean (b)1113T1342-9Reaction RingClean (b)1113T1342-10Reaction RingClean (b)1113T1361-2ShimClean9 (b)1113T1361-5ShimClean (a) Make sure to identify how the seal is oriented in the installed position, before removing the seal prior to temperature stress relieving. In the assembly section, the new seal must be installed into the reaction ring with the same orientation. Failure to do so will result in bearing damage, due to lack of lubrication. (b) Use a piece of cloth damped with BMS11-9 or similar solvent. Refer also to SOPM 20-30-03 as an accepted procedure. FIGURE 1: OUTBOARD TRAILING EDGE FLAP SUPPORT POSITION #1, #2, #7 AND #8 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING REMOVAL (SHEET 5 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 44 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 45 (OCR) BOEING SERVICE BULLETIN 767-27A0229 ALERT ALERT This Figure applies only to: Group 1-2. O SHIM → REACTIO < RIN D SEAL ) 9 LOCATIONS 2273182 FIGURE 2: OUTBOARD TRAILING EDGE FLAP SUPPORT POSITION #1, #2, #7 AND #8 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING INSTALLATION (SHEET 1 OF 4) Original Issue: March 04, 2014 Export Controlled ECCN: 9E991 - BOEING 767-27 A0229 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 45 of 121 ### Page 46 (OCR) BOEING SERVICE BULLETIN 767-27A0229 ALERT ALERT 2) SEAL C .- SEAL PRFACTIO - REACTION 2 RIN RING A-A WING REAR SPAR HOLD-DOWN CLAMP (3 LOCATIONS) TORQUE TUBE REFERENCE ALIGN MARK ROTARY ACTUATOR ASSEMBLY 6 ACTUATOR ROTARY ASSEMBLY 2273181 FIGURE 2: OUTBOARD TRAILING EDGE FLAP SUPPORT POSITION #1, #2, #7 AND #8 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING INSTALLATION (SHEET 2 OF 4) Original Issue: March 04, 2014 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 767-27A0229 Work - See page 1 for details. 46 of 121 ### Page 47 More DataQtyIdentificationNameTaskStep 1113T1361-2ShimInstall (Kept)1 1113T1361-5ShimInstall (Kept) Install new seal into the reaction ring with wet BMS 10-11, Type 1 primer, refer to SOPM 20-41- 02.(a) 1113T1256-31SealAssemble2 Apply BMS3-38 Cor- rosion Inhibiting Compound to mating surfaces including splines. (a) (b) 1113T1342-1Reaction RingAssemble Apply BMS3-38 Cor- rosion Inhibiting Compound to mating surfaces including splines. (a) (c) 1113T1342-2Reaction RingAssemble Apply BMS3-38 Cor- rosion Inhibiting Compound to mating surfaces including splines. (a) (b) 1113T1342-7Reaction RingAssemble Apply BMS3-38 Cor- rosion Inhibiting Compound to mating surfaces including splines. (a) (c) 1113T1342-8Reaction RingAssemble Apply BMS3-38 Cor- rosion Inhibiting Compound to mating surfaces including splines. (a) 1113T1342-9Reaction RingAssemble Apply BMS3-38 Cor- rosion Inhibiting Compound to mating surfaces including splines. (a) 1113T1342-10Reaction RingAssemble 6BACW10BP6DPWasherAssemble3 Tighten nut to torque range of 220-410 Inch-Pounds. 6BACN11Z6CDNutAssemble FIGURE 2: OUTBOARD TRAILING EDGE FLAP SUPPORT POSITION #1, #2, #7 AND #8 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING INSTALLATION (SHEET 3 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 47 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 48 More DataQtyIdentificationNameTaskStep 9BACW10BP7DPWasherAssemble4 Tighten nut to torque range of 370-690 Inch-Pounds. 9BACN11Z7CDNutAssemble 1NAS1149D0763JWasherAssemble5 Tighten nut to torque range of 150-170 Inch-Pounds. 1BACN10YR7CDNutAssemble Install the rotary ac- tuator. Refer to 767 AMM 27-51-22 as an accepted proce- dure. 1256T3250-2Rotary Actuator Assem- bly Assemble6 Install the rotary ac- tuator. Refer to 767 AMM 27-51-22 as an accepted proce- dure. 1256T3250-4Rotary Actuator Assem- bly Assemble (a) Make sure to install the new seal, oriented to the reaction ring, the same way as when the old seal was removed. Failure to do so will result in bearing damage, due to lack of lubrication. (b) Optional preferred part 113T1342-9. (c) Optional preferred part 113T1342-10. FIGURE 2: OUTBOARD TRAILING EDGE FLAP SUPPORT POSITION #1, #2, #7 AND #8 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING INSTALLATION (SHEET 4 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 48 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 49 (OCR) BOEING SERVICE BULLETIN 767-27A0229 ALERT ALERT This Figure applies only to: Group 1-2. , WING REAR SPAR HOLD-DOWN CLAMP (3 LOCATIONS) TORQUE TUBE REFERENCE ALIGN MARK ROTARY ACTUATOR ASSEMBLY ROTARY ACTUATOR ASSEMBLY 2273661 FIGURE 3: INBOARD TRAILING EDGE FLAP SUPPORT POSITION #3 AND #6 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING REMOVAL (SHEET 1 OF 4) Original Issue: March 04, 2014 Export Controlled ECCN: 9E991 - BOEING 767-27 A0229 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 49 of 121 ### Page 50 (OCR) BOEING SERVICE BULLETIN 767-27A0229 ALERT ALERT (2 14 LOCATIONS 35 RING REACTION 3 SEAL SHIM 4 TRAILING EDGE (TE) FLAP SUPPORT RIB POSITION 3 SHOWN. TE FLAP SUPPORT RIB POSITION 6 SIMILAR. 2273664 FIGURE 3: INBOARD TRAILING EDGE FLAP SUPPORT POSITION #3 AND #6 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING REMOVAL (SHEET 2 OF 4) Original Issue: March 04, 2014 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 767-27A0229 Work - See page 1 for details. 50 of 121 ### Page 51 More DataQtyIdentificationNameTaskStep Remove the rotary actuator. Refer to 767 AMM 27-51-11 as an accepted pro- cedure. 1256T3210-2Rotary Actuator Assem- bly Remove1 Remove the rotary actuator. Refer to 767 AMM 27-51-11 as an accepted pro- cedure. 1256T3210-4Rotary Actuator Assem- bly Remove 14NAS1805-7NutRemove2 14BACW10BP7APWasherRemove Remove seal from the reaction ring be- fore temperature stress relieving. Dis- card the removed seal. (a) 1113T1251-1Reaction RingRemove3 Remove seal from the reaction ring be- fore temperature stress relieving. Dis- card the removed seal. (a) 1113T1251-2Reaction RingRemove Remove seal from the reaction ring be- fore temperature stress relieving. Dis- card the removed seal. (a) 1113T1251-7Reaction RingRemove Remove seal from the reaction ring be- fore temperature stress relieving. Dis- card the removed seal. (a) 1113T1251-8Reaction RingRemove Remove seal from the reaction ring be- fore temperature stress relieving. Dis- card the removed seal. (a) 1113T1256-29SealRemove FIGURE 3: INBOARD TRAILING EDGE FLAP SUPPORT POSITION #3 AND #6 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING REMOVAL (SHEET 3 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 51 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 52 More DataQtyIdentificationNameTaskStep 1113T1361-3ShimRemove / Keep4 1113T1361-13ShimRemove / Keep (b)1113T1251-1Reaction RingClean5 (b)1113T1251-2Reaction RingClean (b)1113T1251-7Reaction RingClean (b)1113T1251-8Reaction RingClean (b)1113T1361-3ShimClean6 (b)1113T1361-13ShimClean (a) Make sure to identify how the seal is oriented in the installed position, before removing the seal prior to temperature stress relieving. In the assembly section, the new seal must be installed into the reaction ring with the same orientation. Failure to do so will result in bearing damage, due to lack of lubrication. (b) Use a piece of cloth damped with BMS11-9 or similar solvent. Refer to SOPM 20-30-03 as an accepted procedure. FIGURE 3: INBOARD TRAILING EDGE FLAP SUPPORT POSITION #3 AND #6 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING REMOVAL (SHEET 4 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 52 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 53 (OCR) BOEING SERVICE BULLETIN 767-27A0229 ALERT ALERT This Figure applies only to: Group 1-2. © SHIM · d 200 REACTIOI 2 RIN 2 SEAL 3) 14 LOCATIONS A 2273665 FIGURE 4: INBOARD TRAILING EDGE FLAP SUPPORT POSITION #3 AND #6 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING INSTALLATION (SHEET 1 OF 4) Original Issue: March 04, 2014 Export Controlled ECCN: 9E991 - BOEING 767-27 A0229 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 53 of 121 ### Page 54 (OCR) BOEING SERVICE BULLETIN 767-27A0229 ALERT ALERT (2) SEAL C .- SEAL REACTION 3) REACTION RING RING A-A WING REAR SPAR HOLD-DOWN CLAMP (3 LOCATIONS) TORQUE TUBE REFERENCE ALIGN MARK ROTARY ACTUATOR ASSEMBLY ROTARY ACTUATOR ASSEMBLY 2273667 FIGURE 4: INBOARD TRAILING EDGE FLAP SUPPORT POSITION #3 AND #6 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING INSTALLATION (SHEET 2 OF 4) Original Issue: March 04, 2014 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 767-27A0229 Work - See page 1 for details. 54 of 121 ### Page 55 More DataQtyIdentificationNameTaskStep 1113T1361-3ShimInstall (Kept)1 1113T1361-13ShimInstall (Kept) Install new seal into the reaction ring with wet BMS 10-11, Type 1 primer, refer to SOPM 20-41- 02.(a) 1113T1256-29SealAssemble2 Apply BMS3-38 Cor- rosion Inhibiting Compound to mating surfaces including splines. (a) (b) 1113T1251-1Reaction RingAssemble Apply BMS3-38 Cor- rosion Inhibiting Compound to mating surfaces including splines. (a) (c) 1113T1251-2Reaction RingAssemble Apply BMS3-38 Cor- rosion Inhibiting Compound to mating surfaces including splines. (b) 1113T1251-7Reaction RingAssemble Apply BMS3-38 Cor- rosion Inhibiting Compound to mating surfaces including splines. (c) 1113T1251-8Reaction RingAssemble 14BACW10BP7APWasherAssemble3 Tighten nut to torque range of 260-425 Inch-Pounds. 14BACN11Z7CDNutAssemble Install the rotary ac- tuator. Refer to 767 AMM 27-51-11 as an accepted proce- dure. 1256T3210-2Rotary Actuator Assem- bly Assemble4 Install the rotary ac- tuator. Refer to 767 AMM 27-51-11 as an accepted proce- dure. 1256T3210-4Rotary Actuator Assem- bly Assemble FIGURE 4: INBOARD TRAILING EDGE FLAP SUPPORT POSITION #3 AND #6 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING INSTALLATION (SHEET 3 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 55 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 56 More DataQtyIdentificationNameTaskStep (a) Make sure to install the new seal, oriented to the reaction ring, the same way as when the old seal was removed. Failure to do so will result in bearing damage, due to lack of lubrication. (b) Optional preferred part 113T1257-7. (c) Optional preferred part 113T1257-8. FIGURE 4: INBOARD TRAILING EDGE FLAP SUPPORT POSITION #3 AND #6 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING INSTALLATION (SHEET 4 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 56 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 57 (OCR) BOEING SERVICE BULLETIN 767-27A0229 ALERT ALERT This Figure applies only to: Group 1-2. SIDE-OF-BODY ROTARY ACTUATOR ASSEMBLY TORQUE WING-BODY-FAIRING TUBE SUPPORT STRUCTURE HOLD-DOWN CLAMP (3 LOCATIONS) ROTARY ACTUATOR ASSEMBLY 2273669 FIGURE 5: INBOARD TRAILING EDGE FLAP SUPPORT POSITION #4 AND #5 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING REMOVAL (SHEET 1 OF 4) Original Issue: March 04, 2014 Export Controlled ECCN: 9E991 - BOEING 767-27 A0229 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 57 of 121 ### Page 58 (OCR) BOEING SERVICE BULLETIN 767-27A0229 ALERT ALERT (2) 6 LOCATIONS 39 RING TION 3 SEAL SHIM 4 TRAILING EDGE (TE) FLAP SUPPORT RIB POSITION 4 SHOWN. TE FLAP SUPPORT RIB POSITION 5 SIMILAR. B 2273672 FIGURE 5: INBOARD TRAILING EDGE FLAP SUPPORT POSITION #4 AND #5 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING REMOVAL (SHEET 2 OF 4) Original Issue: March 04, 2014 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 767-27A0229 Work - See page 1 for details. 58 of 121 ### Page 59 More DataQtyIdentificationNameTaskStep Remove the rotary actuator. Refer to 767 AMM 27-51-05 as an accepted pro- cedure. 1256T3250-2Rotary Actuator Assem- bly Remove1 Remove the rotary actuator. Refer to 767 AMM 27-51-05 as an accepted pro- cedure. 1256T3250-4Rotary Actuator Assem- bly Remove 6BACN10JC7NutRemove2 6BACW10BP7APWasherRemove Remove seal from the reaction ring be- fore temperature stress relieving. Dis- card the removed seal. (a) 1113T1269-3Reaction RingRemove3 Remove seal from the reaction ring be- fore temperature stress relieving. Dis- card the removed seal. (a) 1113T1269-4Reaction RingRemove Remove seal from the reaction ring be- fore temperature stress relieving. Dis- card the removed seal. (a) 1113T1269-9Reaction RingRemove Remove seal from the reaction ring be- fore temperature stress relieving. Dis- card the removed seal. (a) 1113T1269-10Reaction RingRemove Remove seal from the reaction ring be- fore temperature stress relieving. Dis- card the removed seal. (a) 1113T1256-31SealRemove FIGURE 5: INBOARD TRAILING EDGE FLAP SUPPORT POSITION #4 AND #5 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING REMOVAL (SHEET 3 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 59 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT ### Page 60 More DataQtyIdentificationNameTaskStep 1113T1361-4ShimRemove / Keep4 1113T1361-14ShimRemove / Keep (b)1113T1269-3Reaction RingClean5 (b)1113T1269-4Reaction RingClean (b)1113T1269-9Reaction RingClean (b)1113T1269-10Reaction RingClean (b)1113T1361-4ShimClean6 (a) Make sure to identify how the seal is oriented in the installed position, before removing the seal prior to temperature stress relieving. In the assembly section, the new seal must be installed into the reaction ring with the same orientation. Failure to do so will result in bearing damage, due to lack of lubrication. (b) Use a piece of cloth damped with BMS11-9 or similar solvent. Refer SOPM 20-30-03 as an accepted procedure. FIGURE 5: INBOARD TRAILING EDGE FLAP SUPPORT POSITION #4 AND #5 - ROTARY ACTUATOR ASSEMBLY AND REACTION RING REMOVAL (SHEET 4 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 04, 2014 767-27A0229 60 of 121 BOEING SERVICE BULLETIN 767-27A0229 ALERTALERT The text continues at https://openairdocs.org/service-documents/boeing/767-27a0229/file/1987ffdf3401.md?from=61 --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.