### Commercial **Airplanes** 

# 737 Service Bulletin **Number: 737-27-1300** Original Issue: April 16, 2012 ATA System: 2731 **SUBJECT:**FLIGHT CONTROLS - Elevator and Tab - Elevator Tab Control Mechanism - Aft Attach Lug Modification 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 © 2012 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 Unpublished Work.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, DreamlinerTM, BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and 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. BOEING is a trademark of Boeing Management Company.

Original Issue: April 16, 2012 737-27-1300 1 of 59 4.0Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 2 of 59 **BOEING SERVICE BULLETIN 737-27-1300**

BLANK PAGE**Table of Contents** Summary...................................................... 5 1. PLANNING INFORMATION........................................ 9 A. Effectivity................................................ 9 1. Airplanes............................................. 9 2. Spares Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 F. Approval. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 G. Manpower. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 1. Existing Data:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 2. Data Supplied with this Service Bulletin:. . . . . . . . . . . . . . . . . . . . . . . . . . . 26 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 26 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 27 M. Software Accomplishment Summary. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 C. Parts Necessary for Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 1. Kits/Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 32 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33 4. Parts Removed and Not Replaced. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 34 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36 FIGURE 1: RIGHT SIDE, ELEVATOR TAB CONTROL MECHANISM MODIFICATION. . . . . . . . 42 FIGURE 2: LEFT SIDE, ELEVATOR TAB CONTROL MECHANISM MODIFICATION. . . . . . . . . 49 FIGURE 3: RIGHT SIDE, ELEVATOR TAB CONTROL MECHANISM INSTALLATION. . . . . . . . 56 FIGURE 4: LEFT SIDE, ELEVATOR TAB CONTROL MECHANISM INSTALLATION. . . . . . . . . 58

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 3 of 59 **BOEING SERVICE BULLETIN 737-27-1300**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 4 of 59 **BOEING SERVICE BULLETIN 737-27-1300**

BLANK PAGE

### Commercial **Airplanes** 

# 737 Service Bulletin **Summary Number: 737-27-1300**  Original Issue: April 16, 2012 ATA System: 2731 **SUBJECT:**FLIGHT CONTROLS - Elevator and Tab - Elevator Tab Control Mechanism - Aft Attach Lug Modification **CONCURRENT REQUIREMENTS** None.

**BACKGROUND** Boeing has received 2 reports from operators where the failure of the aft attach lugs on the left elevator tab control mechanism resulted in unwanted elevator freeplay vibration during flight. Investigation revealed that the bearings installed in the elevator tab control mechanism aft attach lugs were likely installed such that they may become loose and migrate. This service bulletin installs a new or modified elevator tab control mechanism with a new improved machined lug with a new bearing that has an improved retention swage. A secondary retention feature was also added to the lug assemblies to ensure the bearings remain in the load path in the event of a swage failure. This new improved machined lug is more robust than the original and will increase the service life of the lugs and bearings of the elevator tab control mechanism. A loose bearing in the aft attach lug of the elevator tab control mechanism that is allowed to migrate out of the load path could lead to unwanted elevator freeplay and then tab vibration which could lead to structural failure of the elevator or the horizontal stabilizer, which can result in unsafe flight conditions. The related Elevator Tab service bulletins are 737-27A1299 and 737-27A1297. Boeing Service Related Problem (SRP) 737NG-SRP-27-0211 is related to this service bulletin. This table is provided to operators for planning purposes only. Refer to the applicable sections for more information.
**Reference Affected**  **Planning Data** Paragraph 1.A.2., Spares Affected Yes Spares Affected Paragraph 1.F., Approval Yes AD Related Paragraph 1.H., Weight and Balance Changes Yes Weight and Balance Change Paragraph 1.I., Electrical Load Data No Electrical Load Changed Paragraph 1.K., Publications Affected Yes Publications Affected Paragraph 1.K., Publications Affected No Airplane Flight Operations Affected Paragraph 2.C.1., Kits/Parts Yes Kits/Parts Required

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 5 of 59**Reference Affected**  **Planning Data** Paragraph 2.C.2., Parts and Materials Supplied by the Operator Yes Operator Supplied Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin Yes Special Tooling Required

**ACTION (PRR 38964) Airplane Work**  1. Gain access to the elevator tab control mechanism. Remove and replace with a new or previously modified elevator tab control mechanism or remove and modify the elevator tab control mechanism by installing the new machined lug assemblies to the existing frames and applying the part mark, as indicated under Component Work. Perform functional tests, a power-off (manual reversion) flight test and return the airplane to a serviceable condition. **Component Work** 1. Disassemble the elevator tab control mechanism and remove the lugs (bracket) from the frame. 2. Replace the sheet metal lug assemblies with the new machined lug assemblies. 3. Reassemble the elevator tab control mechanism and part mark with the new dash number. **EFFECTIVITY** 737-600, -700, -700C, -800, -900 and -900ER Airplane(s). Refer to Paragraph 1.A., Effectivity, Airplanes, for the list of affected airplanes.

**COMPLIANCE** Federal Aviation Administration (FAA) Airworthiness Directive AD 2010-17-19 is related to this service bulletin. The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Refer to Paragraph 1.E., Compliance. **INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are available for airplanes in warranty as of March 11, 2010. Please refer to Paragraph 2.B., Industry Support Information. **MANPOWER** Refer to Paragraph 1.G., Manpower.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 6 of 59 **BOEING SERVICE BULLETIN 737-27-1300 Elapsed Hours**  **Total Task Hours Airplanes**  11.00 12.00 TOTAL FOREACH INSTALLED ELEVATOR TAB CONTROL MECHANISM 6.00 6.00 TOTAL FORSPARE COMPONENT - ELEVATOR TAB CONTROL MECHANISM
**MATERIAL INFORMATION** Boeing Supplied Kits/Parts. Refer to Paragraph 2.A., Material - Price and Availability.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 7 of 59 **BOEING SERVICE BULLETIN 737-27-1300**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 8 of 59 **BOEING SERVICE BULLETIN 737-27-1300**

### Commercial **Airplanes** 

# 737 Service Bulletin **Number: 737-27-1300** Original Issue: April 16, 2012 ATA System: 2731 **SUBJECT:**FLIGHT CONTROLS - Elevator and Tab - Elevator Tab Control Mechanism - Aft Attach Lug Modification **1. PLANNING INFORMATION A. Effectivity**  1. Airplanes

**DESCRIPTION CONFIGURATION**  **GROUP** Line numbers 1 through 3909

- 1

Airplane Models: 737-600, 737-700, 737-700C, 737-800, 737-900, 737-900ER **Group Variable Number** 1 YA001 - YA099 1 YA101 - YA199 1 YA201 - YA211 1 YA221 1 YA231 - YA242 1 YA251 - YA256 1 YA271 - YA272 1 YA291 1 YA301 - YA302 1 YA311 - YA314 1 YA321 - YA323 1 YA336 - YA345 1 YA351 1 YA356 - YA357

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 9 of 59**Group Variable Number** 1 YA366 - YA367 1 YA371 - YA377 1 YA501 - YA536 1 YA541 - YA552 1 YA571 - YA578 1 YA601 - YA615 1 YA621 - YA622 1 YA626 - YA631 1 YA635 - YA636 1 YA641 - YA642 1 YA645 - YA650 1 YA656 - YA659 1 YA666 - YA667 1 YA671 - YA672 1 YA681 - YA691 1 YA701 - YA710 1 YA721 - YA722 1 YA731 - YA734 1 YA751 - YA756 1 YA801 - YA803 1 YA809 1 YA811 - YA814 1 YA831 - YA835 1 YA841 - YA862 1 YA881 - YA882 1 YA891 - YA892 1 YA961 - YA978 1 YB001 - YB006 1 YB101 - YB132 1 YB151 - YB153 1 YB156 - YB158 1 YB161 - YB164 1 YB171 - YB172

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 10 of 59 **BOEING SERVICE BULLETIN 737-27-1300 Group**  **Variable Number**1 YB181 - YB184 1 YB201 - YB208 1 YB271 1 YB276 1 YB301 - YB310 1 YB371 - YB392 1 YB501 - YB502 1 YB521 - YB526 1 YB541 - YB544 1 YB551 1 YB561 - YB598 1 YB601 - YB635 1 YB651 1 YB656 1 YB671 - YB672 1 YB851 - YB863 1 YB871 - YB874 1 YB881 - YB893 1 YB901 - YB903 1 YB911 1 YB961 - YB975 1 YB981 1 YB986 - YB998 1 YC001 - YC030 1 YC051 - YC084 1 YC091 - YC095 1 YC101 - YC104 1 YC111 - YC113 1 YC121 1 YC126 - YC127 1 YC136 - YC141 1 YC146 - YC147 1 YC151 - YC156

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 11 of 59 **BOEING SERVICE BULLETIN 737-27-1300 Group**  **Variable Number**1 YC166 - YC171 1 YC176 - YC179 1 YC186 - YC190 1 YC201 - YC203 1 YC206 - YC207 1 YC301 - YC305 1 YC321 - YC387 1 YC391 - YC394 1 YC396 1 YC401 - YC417 1 YC421 - YC422 1 YC426 - YC428 1 YC436 - YC439 1 YC441 - YC448 1 YC451 - YC455 1 YC459 1 YC461 - YC467 1 YC471 - YC499 1 YC501 - YC526 1 YC571 - YC583 1 YC587 - YC589 1 YC591 - YC593 1 YC601 - YC655 1 YC681 - YC696 1 YC701 - YC715 1 YC720 - YC725 1 YC727 - YC752 1 YC761 - YC770 1 YC781 - YC793 1 YC801 - YC892 1 YC901 - YC907 1 YC921 - YC922 1 YC931 - YC932

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 12 of 59 **BOEING SERVICE BULLETIN 737-27-1300 Group**  **Variable Number**1 YC941 - YC951 1 YC971 - YC978 1 YC981 - YC983 1 YD001 - YD007 1 YD021 - YD025 1 YD041 - YD057 1 YD081 - YD084 1 YD101 - YD117 1 YD121 - YD126 1 YD151 - YD159 1 YD171 - YD172 1 YD201 - YD203 1 YD206 - YD209 1 YD216 - YD219 1 YD251 - YD254 1 YD256 - YD257 1 YD261 1 YD301 - YD334 1 YD391 1 YD401 - YD410 1 YD412 - YD418 1 YD481 - YD485 1 YD491 - YD499 1 YD501 - YD512 1 YD531 - YD535 1 YD541 - YD547 1 YD561 - YD564 1 YD571 - YD572 1 YD591 - YD595 1 YD601 - YD612 1 YD651 - YD655 1 YE001 - YE020 1 YE051

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 13 of 59 **BOEING SERVICE BULLETIN 737-27-1300 Group**  **Variable Number**1 YE101 - YE109 1 YE151 - YE157 1 YE171 - YE172 1 YE201 - YE206 1 YE301 - YE305 1 YE321 - YE326 1 YE371 - YE383 1 YF001 - YF011 1 YF021 - YF049 1 YF051 - YF067 1 YF086 - YF087 1 YF106 - YF107 1 YF111 - YF114 1 YF116 - YF119 1 YF121 - YF132 1 YF176 - YF178 1 YF191 - YF192 1 YF201 - YF276 1 YF401 - YF402 1 YF431 - YF432 1 YF436 - YF437 1 YF441 - YF442 1 YF451 - YF460 1 YF501 - YF599 1 YF601 - YF638 1 YF701 - YF707 1 YF801 - YF805 1 YF831 - YF832 1 YF836 - YF838 1 YF901 - YF905 1 YF921 - YF928 1 YF951 - YF954 1 YG001 - YG044

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 14 of 59 **BOEING SERVICE BULLETIN 737-27-1300 Group**  **Variable Number**1 YG061 - YG064 1 YG066 - YG089 1 YG091 - YG099 1 YG101 - YG104 1 YG111 - YG114 1 YG116 - YG134 1 YG201 - YG205 1 YG211 - YG214 1 YG221 - YG224 1 YG251 - YG252 1 YG501 - YG512 1 YG601 - YG602 1 YG701 1 YG711 1 YH001 - YH012 1 YH031 - YH055 1 YH071 - YH080 1 YH101 - YH132 1 YH201 - YH202 1 YH206 - YH207 1 YH301 - YH306 1 YH321 - YH322 1 YH501 - YH515 1 YH551 - YH552 1 YH601 - YH602 1 YH611 - YH612 1 YH631 - YH632 1 YH641 1 YJ001 - YJ013 1 YJ021 1 YJ471 - YJ480 1 YJ501 - YJ517 1 YJ531 - YJ579

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 15 of 59 **BOEING SERVICE BULLETIN 737-27-1300 Group**  **Variable Number**1 YJ591 - YJ599 1 YJ631 - YJ632 1 YJ671 - YJ694 1 YJ801 - YJ867 1 YJ871 - YJ880 1 YJ901 - YJ904 1 YJ908 - YJ929 1 YJ931 - YJ937 1 YJ941 - YJ956 1 YJ961 1 YJ976 - YJ977 1 YK001 - YK007 1 YK101 - YK104 1 YK111 - YK112 1 YK121 - YK122 1 YK131 - YK133 1 YK136 - YK139 1 YK141 - YK142 1 YK146 - YK148 1 YK151 - YK154 1 YK161 - YK167 1 YK171 1 YK176 - YK177 1 YK186 1 YK191 1 YK196 1 YK201 - YK202 1 YK301 - YK314 1 YK321 - YK340 1 YK361 - YK378 1 YK401 - YK406 1 YK426 - YK427 1 YK431 - YK450

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 16 of 59 **BOEING SERVICE BULLETIN 737-27-1300 Group**  **Variable Number**1 YK456 - YK467 1 YK471 - YK473 1 YK476 1 YK480 - YK487 1 YK491 - YK492 1 YK495 - YK499 1 YK511 - YK516 1 YK521 - YK530 1 YK551 - YK571 1 YK576 - YK577 1 YK580 - YK585 1 YK601 - YK602 1 YK606 - YK607 1 YK611 - YK616 1 YK621 - YK634 1 YK641 - YK644 1 YK651 - YK665 1 YK671 - YK672 1 YK676 - YK677 1 YK681 - YK686 1 YK691 1 YK701 - YK713 1 YK716 - YK719 1 YK721 - YK741 1 YK751 - YK770 1 YK776 - YK778 1 YK781 - YK785 1 YK791 - YK792 1 YK796 - YK797 1 YK801 - YK899 1 YK901 - YK912 1 YK918 - YK919 1 YK921 - YK929

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 17 of 59 **BOEING SERVICE BULLETIN 737-27-1300 Group**  **Variable Number**1 YK941 - YK998 1 YL001 - YL005 1 YL011 - YL016 1 YL021 - YL024 1 YL051 - YL052 1 YL056 - YL057 1 YL061 1 YL066 - YL069 1 YL076 - YL077 1 YL101 - YL137 1 YL201 - YL232 1 YL241 - YL242 1 YL271 - YL272 1 YL281 - YL284 1 YL301 - YL303 1 YL311 - YL314 1 YL316 - YL321 1 YL351 - YL353 1 YL371 - YL374 1 YL401 1 YL421 - YL429 1 YL431 - YL444 1 YL461 - YL478 1 YL501 - YL509 1 YL531 - YL534 1 YL541 - YL551 1 YL561 - YL579 1 YL591 - YL598 1 YL601 - YL606 1 YL611 - YL612 1 YL616 - YL617 1 YL621 1 YL626

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 18 of 59 **BOEING SERVICE BULLETIN 737-27-1300 Group**  **Variable Number**1 YL631 - YL634 1 YL636 - YL637 1 YL661 - YL664 1 YL676 - YL691 1 YL696 - YL697 1 YL701 - YL707 1 YL731 1 YL751 - YL752 1 YL756 - YL757 1 YL761 - YL780 1 YL796 - YL797 1 YL801 - YL815 1 YL901 - YL910 1 YL921 - YL940 1 YL951 - YL968 1 YM101 - YM103 1 YM201 - YM244 1 YM251 - YM299 1 YM301 - YM399 1 YM401 - YM415 1 YM471 1 YM481 - YM484 1 YM501 - YM515 1 YM521 - YM522 1 YM541 1 YM551 - YM553 1 YM571 - YM572 1 YM581 - YM582 1 YM591 - YM599 1 YM631 - YM634 1 YM641 - YM652 1 YM671 - YM674 1 YM691 - YM699

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 19 of 59 **BOEING SERVICE BULLETIN 737-27-1300 Group**  **Variable Number**1 YM701 - YM710 1 YM761 - YM765 1 YM771 - YM779 1 YN001 - YN016 1 YN021 - YN024 1 YN061 1 YN071 - YN082 1 YN091 - YN092 1 YN101 - YN112 1 YN121 1 YN201 - YN202 1 YN211 - YN219 1 YN231 - YN236 1 YN261 1 YN501 1 YN531 - YN534 1 YN551 - YN552 1 YN601 - YN602 1 YN701 - YN702 1 YQ001 - YQ003 1 YQ011 - YQ019 1 YQ026 - YQ029 1 YQ036 - YQ045 1 YQ201 - YQ202 1 YQ231 1 YQ241 - YQ251 1 YQ281 - YQ282 1 YQ291 - YQ296 1 YQ301 - YQ302 1 YQ401 - YQ403 1 YQ451 - YQ454 1 YQ461 1 YQ471

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 20 of 59 **BOEING SERVICE BULLETIN 737-27-1300 Group**  **Variable Number**1 YR001 - YR015 1 YR051 - YR057 1 YR091 1 YR101 - YR102 1 YR111 - YR116 1 YR126 - YR132 1 YR141 - YR142 1 YR166 - YR174 1 YR201 - YR204 1 YR231 - YR248 1 YR271 - YR278 1 YR286 - YR287 1 YR291 - YR294 1 YR296 - YR297 1 YR301 - YR314 1 YR361 - YR363 1 YR381 - YR382 1 YR401 - YR405 1 YR421 - YR422 1 YR431 1 YR441 1 YR451 - YR455 1 YR501 - YR504 1 YR511 - YR514 1 YR516 - YR520 1 YR526 - YR527 1 YR601 - YR605 1 YR616 - YR617 1 YR651 - YR653 1 YR656 1 YR701 - YR717 1 YR801 - YR808 1 YR831 - YR833

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 21 of 59 **BOEING SERVICE BULLETIN 737-27-1300 Group**  **Variable Number**1 YR851 - YR855 1 YR901 1 YR951 - YR952 1 YR981 - YR984 1 YS001 - YS002 1 YS051 - YS054 1 YS101 1 YS151 2. Spares Affected Examine your spares supply for the parts or components identified in Paragraph 2.C., Parts Necessary for Each Airplane. If any parts or components are found, refer to Paragraph 2.C. for the recommended use.
**B. Concurrent Requirements** None.

**C. Reason** Boeing has received 2 reports from operators where the failure of the aft attach lugs on the left elevator tab control mechanism resulted in unwanted elevator freeplay vibration during flight. Investigation revealed that the bearings installed in the elevator tab control mechanism aft attach lugs were likely installed such that they may become loose and migrate. This service bulletin installs a new or modified elevator tab control mechanism with a new improved machined lug with a new bearing that has an improved retention swage. A secondary retention feature was also added to the lug assemblies to ensure the bearings remain in the load path in the event of a swage failure. This new improved machined lug is more robust than the original and will increase the service life of the lugs and bearings of the elevator tab control mechanism. A loose bearing in the aft attach lug of the elevator tab control mechanism that is allowed to migrate out of the load path could lead to unwanted elevator freeplay and then tab vibration which could lead to structural failure of the elevator or the horizontal stabilizer, which can result in unsafe flight conditions. Boeing Service Related Problem (SRP) 737NG-SRP-27-0211 is related to this service bulletin. Fleet Team Digest 737NG FTD 27-10005 is related to this service bulletin.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 22 of 59 **BOEING SERVICE BULLETIN 737-27-1300 D. Description**  **Airplane Work** 1. Gain access to the elevator tab control mechanism. Remove and replace with a new or previously modified elevator tab control mechanism or remove and modify the elevator tab control mechanism by installing the new machined lug assemblies to the existing frames and applying the part mark, as indicated under Component Work. Perform functional tests, a power-off (manual reversion) flight test and return the airplane to a serviceable condition.. **Component Work** 1. Disassemble the elevator tab control mechanism and remove the lugs (bracket) from the frame. 2. Replace the sheet metal lug assemblies with the new machined lug assemblies. 3. Reassemble the elevator tab control mechanism and part mark with the new dash number. The work in this service bulletin is done in the maintenance zone(s) given below.
**Affected Maintenance Zones Zone**  **Model** 333, 334, 343, 344 737-600, 737-700, 737-700C, 737-800, 737-900, 737-900ER **E. Compliance** Federal Aviation Administration (FAA) Airworthiness Directive AD 2010-17-19 is related to this service bulletin. The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. **Table 1: Elevator Tab Control Mechanism Aft Attach Lug Replacement Repeat Interval**  **(Not to Exceed) Compliance Time**  **Action Condition** 

- Within five years after the date of the original issue of this service bulletin Replace the elevator tab control mechanisms thathave sheet metal aft attach lugs with elevator tab control mechanismsthat have the new machined aft attach lugs inaccordance with work instruction 3.B. All Airplanes

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 23 of 59 **BOEING SERVICE BULLETIN 737-27-1300 F. Approval**  This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin. In addition, the Manager of the FAA Seattle Aircraft Certification Office approves the action (i.e. inspection or modification) defined in this service bulletin as an alternative method of compliance to the requirements of paragraph (g), (h), (i), (j), (k), (l), (m), (n), (o), (p), (q), (r), (s), (t) of AD 2010-17-19. All provisions of AD 2010-17-19 that are not specifically referenced in the above statement remain fully applicable and must be complied with.
**G. Manpower** The table below shows an estimate of the task hours necessary to do tasks required in this service bulletin for one elevator tab control mechanism, there are two on the 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. **Airplane Work Elapsed Hours**  **Task Hours Number of Persons**  **Task** 0.50 0.50 1 Open Access 1.50 1.50 1 Remove the elevatortab control mechanism 1.50 1.50 1 Install the elevatortab control mechanism 0.50 0.50 1 Close Access 1.00 2.00 2 Test (a) (a) 2 Flight Test (a) Flight test hours are not included in estimate.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 24 of 59 **BOEING SERVICE BULLETIN 737-27-1300 Airplane Work**  **Elapsed Hours Task Hours**  **Number of Persons Task**  5.00 6.00 TOTAL FOR EACH INSTALLED ELEVATOR TAB CONTROL MECHANISM **Component Work Elapsed Hours**  **Task Hours Number of Persons**  **Task** 1.60 1.60 1 Disassemble the ele- vator tab control mechanism 2.80 2.80 1 Modify the elevatortab control mechanism 1.60 1.60 1 Reassemble the ele- vator tab control mechanism 6.00 6.00 TOTAL FOR EACH COMPONENT
**H. Weight and Balance Changes Change in Moment**  **(Inches-Pound) Change in Weight**  **(Pounds) Airplane**  + 1,812.0 InchesPounds + 1.5 Pounds 737-600
+ 1,872.0 InchesPounds + 1.5 Pounds 737-700, -700C
+ 2,040.0 InchesPounds + 1.5 Pounds 737-800
+ 2,103.0 InchesPounds + 1.5 Pounds 737-900, -900ER

**I. Electrical Load Data** Not applicable.

**J. References** 1. Existing Data:
a. Engineering Change Memo PRR 38964

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 25 of 59 **BOEING SERVICE BULLETIN 737-27-1300**b. Service Related Problem (SRP) 737NG-SRP-27-0211 c. Fleet Team Digest 737NG FTD 27-10005 d. Boeing Program Letter BPL 6-1151-737-PGM-196, dated July 15, 2011 e. 737 Maintenance Manual (AMM) Subject737-600/700/800/900 AMM 27-31-00 , 737-600/700/800/900 AMM 27-31-34, f. Component Maintenance Manual (CMM) CMM 27-34-03 g. Boeing Standard Wiring Practices Manual (SWPM) SWPM 20-10-11, SWPM 20-10-12, SWPM 20-10-19 h. Boeing Standard Overhaul Practices Manual (SOPM) SOPM 20-43-03, SOPM 20-50-07, SOPM 20-50-10, SOPM 20-50-19 i. Boeing Service Bulletin 737-27A1297, 737-27A1299 j. FAA Airworthiness Directive AD 2010-17-19 k. Boeing Parts Standards Document D-590 2. Data Supplied with this Service Bulletin: None. 3. Installation Drawings Used in the Preparation of this Service Bulletin:
**Title Drawing Number** Tab Mechanism Assy - Elevator Control 251A2430 Frame Assy - Tab Mechanism, Elevator Control 251A2431 Tab Mechanism instl - Elevator Control 251A2401 The table above lists applicable drawings used to prepare this service bulletin. The drawings are not necessary to make the specified changes, and are not supplied with this service bulletin. The drawings may not be applicable to all airplane configurations or operators.

**K. Publications Affected** 1. Publications: **Chapter-Section Publication**  27-31 737 Aircraft Maintenance Manual

- 737 Structural Repair Manual 27-31 737 Illustrated Parts Catalog

- 737 Weight and Balance Manual

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 26 of 59 **BOEING SERVICE BULLETIN 737-27-1300 Chapter-Section**  **Publication** 27-34 Component Maintenance Manual 2. Damage Tolerance Based Structural Inspections: Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary.

**L. Interchangeability and Intermixability of Parts** Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for interchangeability and intermixability information.
**M. Software Accomplishment Summary**

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 27 of 59 **BOEING SERVICE BULLETIN 737-27-1300**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 28 of 59 **BOEING SERVICE BULLETIN 737-27-1300**

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

$2,359.00 222 days

- - Top Kit 002A0001-107 $570.00 242 days

- - Top Kit 002A0001-109
**B. Industry Support Information** Boeing warranty remedies are available for 737 NG airplanes in warranty as of March 11, 2010. For man-hour reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing Warranty & Product Assurance Contracts. The parts for airplanes in warranty as of that date will be supplied at no charge. Send a purchase order for the parts to Boeing Spares. Please refer to this service bulletin number and reference the airplane variable number(s) in your purchase order. Also see Program Letter BPL 6-1151-737-PGM-196, dated July 15,2011 for out of warranty parts support. Additional copies of program letters are available from Boeing Commercial Airplanes Group - Warranties. QTY (1) MIT002A0001-107 will be supplied for each operator with 737NG airplanes in warranty as of March 11, 2010, and are not planning to accomplish modifications at Boeing or a MRO. Please see Program Letter BPL 6-1151-737-PGM-196-R1, for out of warranty tool support. **C. Parts Necessary for Each Airplane** 1. Kits/Parts To get the kits/parts shown below, 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: April 16, 2012 737-27-1300 29 of 59 **BOEING SERVICE BULLETIN 737-27-1300 NOTE:** Two of each top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane. One of the 002A0001-107 kits is necessary to modify each spare. As an option operators may exchange their elevator tab control mechanism for one previously modified or send their elevator tab control mechanism to be modified by a designated MRO. (c) (d)
**Kit 002A0001 Notes**  **Existing Part Number**  **Name QTY**  **New Part Number -109**  **-107** (c) Kit - Retrofit - Elev Tab Control Mech Aft Attach Lug . - 002A0001-107

(d) Kit - Retrofit - Elev Tab Instl - . 002A0001-109
PIN ASSY - DUAL LOAD PATH, TABMECHANISM, ELEVATOR CONTROL 1

. 251A2445-4

PIN ASSY - DUAL LOAD PATH, TABMECHANISM, ELEVATOR CONTROL 1

. 251A2445-5

(a) LUG ASSY - TABMECHANISM, ELEVATOR CONTROLS . 1 251A2455-1

DOUBLER - TABMECHANISM, ELEVATOR CONTROLS . 2 251A2455-10

RADIUS FILLER, UPPER - TABMECHANISM, ELEVATOR CONTROLS . 2 251A2455-11

(a) LUG ASSY - TABMECHANISM, ELEVATOR CONTROLS . 1 251A2455-2

MACHINED SPACER - TAB MECHANISM, ELEVATOR CONTROLS . 2 251A2455-7

RETAINER - TABMECHANISM, ELEVATOR CONTROL . 2 251A2455-8

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 30 of 59 **BOEING SERVICE BULLETIN 737-27-1300 Kit 002A0001**  **Notes Existing Part**  **Number Name**  **QTY New Part Number**  **-109 -107**  RADIUS FILLER, LOWER - TABMECHANISM, ELEVATOR CONTROLS . 2 251A2455-9

(a) (b) BOLT, HEX DRIVE

. 4 BACB30FM5AK7 (a) (b) BOLT, PROTRUD- ING HD . 4 BACB30MB8A10 (a) COLLAR

. 4 BACC30BH8 (a) COLLAR

. 4 BACC30M5 (a) NUT 1

. BACN10HR5CD (a) SELF-LOCKING NUT . 1 BACN10JC12CD (a) NUT,SELF-LOCK- ING 1

. BACN10JC4CD (a) SELF-LOCKING NUT 2 2 BACN10JC5CD (a) SELF-LOCKING NUT . 3 BACN10JC7CD (a) NUT 4 2 BACN10YR3CD (a) NUT 4

. BACN10YR4CD (a) (b) PIN, COTTER 2

. BACP18BC02A12P (a) (b) RIVET, BLIND

. 4 BACR15FP5F3R (a) (b) RIVET, 100 DEG

. 2 BACR15GF5D11 (a) (b) RIVET, 100 DEG

. 2 BACR15GF5D12 (a) (b) RIVET, 100 DEG

. 2 BACR15GF5D9 (a) (b) SCREW, CAP 2

. BACS12GU3K7 (a) SHIM, LAMINAT- ED . 4 BACS40R007Y020P (a) CSK WASHER 1

. BACW10BP5CD (a) WASHER, FLAT 4

. BACW10P475CG (a) WASHER 2

. NAS1149D0332J (a) WASHER, FLAT 4 2 NAS1149D0363J (a) WASHER 1

. NAS1149D0463J (a) WASHER 3 2 NAS1149D0563J

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 31 of 59 **BOEING SERVICE BULLETIN 737-27-1300 Kit 002A0001**  **Notes Existing Part**  **Number Name**  **QTY New Part Number**  **-109 -107**  (a) WASHER

. 3 NAS1149D0763J (a) WASHER, PLAIN

. 1 NAS1149D1290J (a) BUSHING 2

. NAS75-5-021 (a) WASHER

. 2 BACW10P220S (a) Discard the existing part{Keep the existing part if there are other uses for it} (b) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer than indicated. Also, if any fasteners part numbers listed are not available or have been superseded, substitute fasteners may be supplied in kits. Boeing Document D-590 and Boeing Drawing 65-88700 are used to determine the part numbers used as substitutes. (c) One kit is required for each elevator tab control mechanism that the operator plans to modify. (d) One kit is required for each elevator tab control mechanism that is installed on the airplane. 2. Parts and Materials Supplied by the Operator
**Notes Name**  **QTY Part Number /**  **Specification** As an option to modifying your elevator tab control mechanism, you may installa new or previously modified elevator tab control mechanism. Elevator Tab Control Mechanism, Left hand side 1 251A2430-25

As an option to modifying your elevator tab control mechanism, you may installa new or previously modified elevator tab control mechanism. Elevator Tab Control Mechanism, Right hand side 1 251A2430-26

(a) Anti-seize Compound 1 oz BMS 3-28 Clear Skydrol-resistance Topcoating 1 oz Type 41 Chemical conversion coating 1 oz Alodine (a) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. – Part Interchangeability – Left hand side:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 32 of 59 **BOEING SERVICE BULLETIN 737-27-1300**251A2430-23 is a replacement for a 251A2430-17 and -13 or -101 and -103 251A2430-25 is a replacement for a 251A2430-15 – Right hand side: 251A2430-24 is a replacement for a 251A2430-18 and -14 or -102 and -104 251A2430-26 is a replacement for a 251A2430-16

3. Parts Modified and Reidentified
**Notes New Part Number**  **Name QTY**  **Existing Part Number**  (a) (c) 251A2455-1, -2 Lug assembly 4
- (a) (b) (c) 251A2431-15, -17 & -16, -18 Frame assembly 4 251A2431-11, -12 (a) (b) (c) 251A2430-23, -24 Elevator tab control mechanism 2 251A2430-13, -14, -17, -18, -101, - 102, -103, -104 (a) Make the change in accordance with this service bulletin. (b) This is the part number after the change is done in accordance with this service bulletin. (c) This part is used in production.
4. Parts Removed and Not Replaced None. **D. Parts Necessary to Change Spares** To get the kits shown below, refer to Paragraph 2.A., Material - Price and Availability.
**QTY Name**  **Part Number** 1 Top Kit 002A0001-107
**E. Special Tooling - Price and Availability** Boeing can supply the tool(s) shown in Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin. Operators are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin. The tool(s) are subject to the terms and conditions of the Boeing standard purchase order acknowledgement. Prices are in United States Dollars. Terms: Net 30 days. Reference this service bulletin number and submit your purchase order by one of these methods: 1. Order on-line via ATA Spec 2000 or Boeing Part Page 2. Fax to (206) 662-7145

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 33 of 59 **BOEING SERVICE BULLETIN 737-27-1300 REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST**  **RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION** 
**Purchase Data: Unit Price as of**  **the Original Issue date of this Ser**  **vice Bulletin (US Dollars)**  **Name Tool Kit Number** 

$2,145.00 (b) Miscellaneous Tool Tab Mecha- nism Lug Locating Tool MIT002A0001-107

- Removal / Installation EQPT - -TAB Mechanism ASSY, Elevator Control. (a) C27085

(a) This tool is not required to accomplish this service bulletin, but it islisted as an option and recommended to help prevent damage to the elevator tab mechanism bearings when the aft pin assemblies are removed. This tool is GSE (Ground Support Equipment), operators will have access to the drawing, and they will be able to procure it from wherever they want. (b) The daily rate is $90.00 **F. Special Tooling Necessary to do this Service Bulletin** To get the tools shown below, refer to Paragraph 2.E., Special Tooling - Price and Availability. Maintenance and overhaul tools in the manuals shown in Paragraph 1.J., References, can also be necessary. Examine operator tool supply to make sure all necessary tools are available.
**Name Tool Kit Number**  Miscellaneous Tool Tab Mechanism Lug Locating Tool MIT002A0001-107
Removal / Installation EQPT - - TAB Mechanism ASSY, Elevator Control (a) C27085

(a) This tool is not required to accomplish this service bulletin, but it is listed as an option and recommended to help prevent damage to the elevator tab mechanism bearings when the aft pin assemblies are removed. This tool is GSE (Ground Support Equipment), operators will have access to the drawing, and they will be able to procure it from wherever they want.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 34 of 59 **BOEING SERVICE BULLETIN 737-27-1300 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. The work instructions are divided into Airplane Work and Component Work. Task Hours and Elapsed Hours for each section are given in Paragraph 1.G., Manpower. 4. Unless shown differently, these dimensions and tolerances are used: – Linear dimensions are in inches – Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or minus 0.03 inch – Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch – Angular tolerance is plus or minus 2 degrees – Hole dimensions for standard solid rivets and fasteners are in Structural Repair Manual (SRM) Chapter 51 – Torque limits to tighten nuts and bolts are in SRM Chapter 51 5. Use the approved fastener and process material substitutions in accordance with SRM Chapter 51. 6. 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. 7. 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. 8. 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. 9. 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: April 16, 2012 737-27-1300 35 of 59 **BOEING SERVICE BULLETIN 737-27-1300**10. 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. 11. 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. 12. Boeing Service Letter 737-SL-51-042, Damage Reporting and Repair Plan/Design Guidelines, is an acceptable procedure to request information from Boeing for additional structural repair instructions. The Service Letter describes what information must be provided to Boeing before a structural repair can be provided. 13. 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. 14. 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. 15. 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. 16. 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. 17. Some Boeing parts are supplied in a temporary configuration. Those parts are identified with a 'U', 'W', or 'Y' in place of the '-' (dash) in the part number. It is permitted to install parts identified with a 'U', 'W', or 'Y' as an alternative to the '-' (dash) part number. Boeing Drawing 005W0900 contains more data. **B. WORK INSTRUCTIONS Airplane work, right elevator tab control mechanism**  1. Gain access to the Horizontal Stabilizer and the Elevator as required. Refer to 737-600/700/800/900 AMM 27-31-34 as an accepted procedure. 2. Remove the elevator tab control mechanism. Refer to 737-600/700/800/900 AMM 27-31-34 as an accepted procedure.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 36 of 59 **BOEING SERVICE BULLETIN 737-27-1300 NOTE:** As an option the actuator can be removed from the elevator tab control mechanism and left on the airplane, prior to removing the elevator tab control mechanism. 3. Remove the actuator from the elevator tab control mechanism. Refer to CMM 27-34-03 or 737-600/700/800/900 AMM 27-31-34 as an accepted procedure. **NOTE:**It is not required to remove the actuator from the airplane. 4. Modify your elevator tab control mechanism in accordance with the Component Work section. **NOTE:**As an option to modifying your elevator tab control mechanism in accordance with the Component Work section, you may install a new elevator tab control mechanism with the machined lugs or elevator tab control mechanism previously modified in accordance to the requirements of this service bulletin. 5. Install the 251A2430-24 elevator tab control mechanism onto the airplane. If the actuator was left on the airplane install the 251A2430-26 elevator tab control mechanism onto the airplane. Refer to 737-600/700/800/900 AMM 27-31-34 as an accepted procedure. Use the fastener codes in accordance with Figure 3 for the replacement fasteners, otherwise re-use the fasteners removed from the airplane. Installation fasteners, that are to be replaced are provided in kit #002A0001-109. 6. This step is only required if the actuator has not been previously installed in the elevator tab control mechanism. Install the actuator onto the new 251A2430-26 elevator tab control mechanism. Refer to CMM 27-34-03 or 737-600/700/800/900 AMM 27-31-34 as an accepted procedure. Use the fastener codes in accordance with Figure 3 for the replacement fasteners, otherwise reuse the existing fasteners. Installation fasteners that are to be replaced are provided in kit #002A0001-109 7. Part mark the assembly with the actuator to 251A2430 -24 in accordance with Figure 1, if the assembly has not been previously part marked. 8. Close access and restore airplane as required, refer to 737-600/700/800/900 AMM 27-31-34 as an accepted procedure. 9. Perform functional tests and a power-off (manual reversion) flight test. Ref to 737-600/700/800/900 AMM 27-31-34, 737-600/700/800/900 AMM 27-31-00 as an accepted procedure. 10. Put the airplane back into a serviceable condition. 11. Report all tab mechanism retrofit completions to Boeing using the Service Requests application on MyBoeingFleet. Include airplane identification and date the retrofit was completed. **Airplane work, left elevator tab control mechanism** 1. Gain access to the Horizontal Stabilizer and the Elevator as required. Refer to 737-600/700/800/900 AMM 27-31-34 as an accepted procedure. 2. Remove the elevator tab control mechanism. Refer to 737-600/700/800/900 AMM 27-31-34 as an accepted procedure. **NOTE:**As an option the actuator can be removed from the elevator tab control mechanism and left on the airplane, prior to removing the elevator tab control mechanism.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 37 of 59 **BOEING SERVICE BULLETIN 737-27-1300**3. Remove the actuator from the elevator tab control mechanism. Refer to CMM 27-34-03 or 737-600/700/800/900 AMM 27-31-34 as an accepted procedure. **NOTE:**It is not required to remove the actuator from the airplane. 4. Modify your elevator tab control mechanism in accordance with the Component Work section. **NOTE:**As an option to modifying your elevator tab control mechanism in accordance with the Component Work section, you may install a new elevator tab control mechanism with the machined lugs or elevator tab control mechanism previously modified in accordance to the requirements of this service bulletin. 5. Install the 251A2430-23 elevator tab control mechanism onto the airplane. If the actuator was left on the airplane install the 251A2430-25 elevator tab control mechanism onto the airplane. Refer to 737-600/700/800/900 AMM 27-31-34 as an accepted procedure. Use the fastener codes in accordance with Figure 3 for the replacement fasteners, otherwise re-use the fasteners removed from the airplane. Installation fasteners, that are to be replaced are provided in kit #002A0001-109. 6. This step is only required if the actuator has not been previously installed in the elevator tab control mechanism. Install the actuator onto the new 251A2430-25 elevator tab control mechanism. Refer to CMM 27-34-03 or 737-600/700/800/900 AMM 27-31-34 as an accepted procedure. Use the fastener codes in accordance with Figure 4 for the replacement fasteners, otherwise reuse the existing fasteners. Installation fasteners and hardware that are to be replaced are provided in kit #002A0001-109. 7. Part mark the assembly with the actuator to 251A2430-23 in accordance with Figure 2, if the assembly has not been previously part marked. 8. Close access and restore airplane as required, refer to 737-600/700/800/900 AMM 27-31-34 as an accepted procedure. 9. Perform functional tests and a power-off (manual reversion) flight test. Ref to 737-600/700/800/900 AMM 27-31-34, 737-600/700/800/900 AMM 27-31-00 as an accepted procedure. 10. Put the airplane back into a serviceable condition. 11. Report all tab mechanism retrofit completions to Boeing using the Service Requests application on MyBoeingFleet. Include airplane identification and date the retrofit was completed. **Component work, right elevator tab control mechanism** 1. Disassemble the elevator tab control mechanism as required to get access to the left and right frame assemblies. Refer to CMM 27-34-03 as an accepted procedure. 2. Remove the sheet metal lug (bracket) assemblies from the left and right frame assemblies. Refer to CMM 27-34-03 as an accepted procedure. 3. For each frame assembly: Locate the frame assembly on the tool, using the 2 indicated holes in the frame and make the cutout. Refer to the MIT002A0001-107 tool use instructions as an accepted procedure.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 38 of 59 **BOEING SERVICE BULLETIN 737-27-1300**4. For each frame assembly: Locate the new lug assembly onto the close tolerance pin. Refer to the MIT002A0001-107 tool use instructions as an accepted procedure. 5. For each frame assembly: Locate the doubler at the lower flange and the shims at the upper and lower flanges, between the lug assembly and the frame in accordance with Figure 1. Use the shims to center the lug assemble in the frame. 6. For each frame assembly: Clamp the lug assembly against the web of the frame subassembly. Refer to the MIT002A0001-107 tool use instructions as an accepted procedure. 7. For each frame assembly: Locate the upper and lower radius fillers flush with the end of the lug assembly and clamp in place in accordance with Figure 1. 8. For each frame assembly: Match drill fastener holes in lower flange, upper flange and lower part of the frame web through the stack-up using existing hole locations in the frame assemblies in accordance with Figure 1. **NOTE:**Take care not to oversize the existing hole. 9. For each frame assembly: Install 2 fasteners in lower flange and 1 in upper flange and 2 in the lower part of the frame web in accordance with Figure 1. Note, there are two more existing holes in the upper frame flange that will be used when the elevator tab control mechanism is reassembled. 10. For each frame assembly: Locate the spacers/retainers with the MIT002A0001-107 tool. a. For the left frame assembly: Locate the retainers and clamp in place. Refer to the MIT002A0001-107 tool use instructions as an accepted procedure. b. For the right frame assembly: Locate the machined spacers and clamp in place. Refer to the MIT002A0001-107 tool use instructions as an accepted procedure. 11. For each frame assembly: Drill holes through the spacer/retainer stack-up. a. For the left frame assembly: Drill holes through the retainer stack-up. Refer to the MIT002A0001-107 tool use instructions as an accepted procedure. Install double flush fasteners in accordance with Figure 1. b. For the right frame assembly: Drill holes through the machined spacer stack-up. Refer to the MIT002A0001-107 tool use instructions as an accepted procedure. Install double flush fasteners in accordance with Figure 1 12. Reassemble the elevator tab control mechanism. Refer to CMM 27-34-03 as an accepted procedure. Use the fastener codes in accordance with Figure 1 for the replacement fasteners, otherwise reuse the existing fasteners. Installation fasteners that are to be replaced are provided in kit #002A0001-107. 13. Part mark the frame assemblies in accordance with Figure 1. On the right mechanism the 251A2431-11 frame becomes a 251A2431-18 frame and the 251A2431-12 becomes a 251A2431-16. 14. Part mark 251A2430-26 on the elevator tab control mechanism in accordance with Figure 1.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 39 of 59 **BOEING SERVICE BULLETIN 737-27-1300 NOTE:** After installation of the actuator, part mark 251A2430-24 on the elevator tab control mechanism in accordance with Figure 1 **Component work, left elevator tab control mechanism** 1. Disassemble the elevator tab control mechanism as required to get access to the left and right frame assemblies. Refer to CMM 27-34-03 as an accepted procedure. 2. Remove the sheet metal lug (bracket) assemblies from the left and right frame assemblies. Refer to CMM 27-34-03 as an accepted procedure. 3. For each frame assembly: Locate the frame assembly on the tool, using the 2 indicated holes in the frame and make the cutout. Refer to the MIT002A0001-107 tool use instructions as an accepted procedure. 4. For each frame assembly: Locate the new lug assembly onto the close tolerance pin. Refer to the MIT002A0001-107 tool use instructions as an accepted procedure. 5. For each frame assembly: Locate the doubler at the lower flange and the shims at the upper and lower flanges, between the lug assembly and the frame in accordance with Figure 2. Use the shims to center the lug assemble in the frame. 6. For each frame assembly: Clamp the lug assembly against the web of the frame subassembly. Refer to the MIT002A0001-107 tool use instructions as an accepted procedure. 7. For each frame assembly: Locate the upper and lower radius fillers flush with the end of the lug assembly and clamp in place in accordance with Figure 2. 8. For each frame assembly: Match drill fastener holes in lower flange, upper flange and the lower part of the frame web through the stack-up using existing hole locations in the frame assemblies in accordance with Figure 2. **NOTE:**Take care not to oversize the existing hole. 9. For each frame assembly: Install 2 fasteners in lower flange, 1 in upper flange and 2 in the lower part of the frame web in accordance with Figure 2. Note, there are two more existing holes in the upper frame flange that will be used when the elevator tab control mechanism is reassembled. 10. For each frame assembly: Locate the spacers/retainers with the MIT002A0001-107 tool. a. For the left frame assembly: Locate the machined spacers and clamp in place. Refer to the MIT002A0001-107 tool use instructions as an accepted procedure. b. For the right frame assembly: Locate the retainers and clamp in place. Refer to the MIT002A0001-107 tool use instructions as an accepted procedure. 11. For each frame assembly: Drill holes through the bearing retainer stack-up. a. For the left frame assembly: Drill holes through the machined spacer stack-up. Refer to the MIT002A0001-107 tool use instructions as an accepted procedure. Install double flush fasteners in accordance with Figure 2.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 40 of 59 **BOEING SERVICE BULLETIN 737-27-1300**b. For the right frame assembly: Drill holes through the retainer stack-up. Refer to the MIT002A0001-107 tool use instructions as an accepted procedure. Install double flush fasteners in accordance with Figure 2. 12. Reassemble the elevator tab control mechanism. Refer to CMM 27-34-03 as an accepted procedure. Use the fastener codes in accordance with Figure 2 for the replacement fasteners, otherwise reuse the existing fasteners. Installation fasteners that are to be replaced are provided in kit #002A0001-107. 13. Part mark the frame assemblies in accordance with Figure 2. On the left mechanism the 251A2431-11 frame becomes a 251A2431-15 frame and the 251A2431-12 becomes a 251A2431-17. 14. Part mark 251A2430-25 on the elevator tab control mechanism in accordance with Figure 2. **NOTE:**After installation of the actuator, part mark 251A2430-23 on the elevator tab control mechanism in accordance with Figure 2.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 41 of 59 **BOEING SERVICE BULLETIN 737-27-1300 FIGURE 1: RIGHT SIDE, ELEVATOR TAB CONTROL MECHANISM MODIFICATION**  **(SHEET 1 OF 7)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 42 of 59 **BOEING SERVICE BULLETIN 737-27-1300 FIGURE 1: RIGHT SIDE, ELEVATOR TAB CONTROL MECHANISM MODIFICATION**  **(SHEET 2 OF 7)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 43 of 59 **BOEING SERVICE BULLETIN 737-27-1300 FIGURE 1: RIGHT SIDE, ELEVATOR TAB CONTROL MECHANISM MODIFICATION**  **(SHEET 3 OF 7)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 44 of 59 **BOEING SERVICE BULLETIN 737-27-1300 FIGURE 1: RIGHT SIDE, ELEVATOR TAB CONTROL MECHANISM MODIFICATION**  **(SHEET 4 OF 7)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 45 of 59 **BOEING SERVICE BULLETIN 737-27-1300 More Data**  **Qty Identification**  **Name Task**  **Step** Install flush withedge of lug assembly. Shim if/as required. 4 BACS40R007Y020P SHIM, LAMINAT- ED Install (New) 1

Install flush withedge of lug assembly. 2 251A2455-10 DOUBLER - TAB MECHANISM, ELEVATOR CONTROLS Install (New) 2

Install flush withedge of lug assembly. 2 251A2455-11 RADIUS FILLER, UPPER - TAB MECHANISM, ELEVATOR CONTROLS Install (New) 3

Install flush withedge of lug assembly. 2 251A2455-9 RADIUS FILLER, LOWER - TAB MECHANISM, ELEVATOR CONTROLS Install (New)

Match drill 5 holes each side. (a) 10
- Fastener Hole Drill 4

(b) 1 251A2455-1 LUG ASSY -TAB MECHANISM, ELEVATOR CONTROLS Install (New) 5 Left frame assembly

(b) 1 251A2455-2 LUG ASSY -TAB MECHANISM, ELEVATOR CONTROLS Install (New) Right frame assembly

(a) 2 251A2455-7 MACHINED SPACER - TAB MECHANISM, ELEVATOR CONTROLS Install (New) 6 Right frame assembly

(a) 2 251A2455-8 RETAINER -TAB MECHANISM, ELEVATOR CONTROL Install (New) Left frame assembly

**FIGURE 1: RIGHT SIDE, ELEVATOR TAB CONTROL MECHANISM MODIFICATION (SHEET 5 OF 7)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 46 of 59 **BOEING SERVICE BULLETIN 737-27-1300 More Data**  **Qty Identification**  **Name Task**  **Step** On the top of theframe assemblies Part mark 251A2431-16 (right frame assy) & 251A2431-18 (left frame assy) on the251A2430-26 elevator tab control mechanism. (c) 2
- Part Mark Identify 7

On the bottom of the elevator tabcontrol mechanism part mark 251A2430-26. (c) (d) 1
- Part Mark Identify

On the bottom of the elevator tabcontrol mechanism with actuator installed part mark 251A2430- 24. (c) (d) 1
- Part Mark Identify

(a) Touch-up fastener holes with Chemical Conversion Coating. Refer to SOPM 20-43-03 as an accepted procedure. (b) Wet install bolts with BMS 5-95. Refer to SOPM 20-50-19 as an accepted procedure. (c) Rubber stamp part mark. Refer to SOPM 20-50-10 as an accepted procedure. (d) Apply abrasive overcoat.
**More Data Hole Dia**  **Qty Identification**  **Name Code**  Head far side

- 4 BACB30FM5AK7 BOLT, HEX DRIVE C

- 4 BACB30MB8A10 BOLT, PROTRUDING HD D

- 4 BACC30BH8 COLLAR E

- 4 BACC30M5 COLLAR F

- 1 BACN10JC12CD SELF-LOCKING NUT H

- 2 BACN10JC5CD SELF-LOCKING NUT J

- 3 BACN10JC7CD SELF-LOCKING NUT K

- 2 BACN10YR3CD NUT L

**FIGURE 1: RIGHT SIDE, ELEVATOR TAB CONTROL MECHANISM MODIFICATION (SHEET 6 OF 7)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 47 of 59 **BOEING SERVICE BULLETIN 737-27-1300 More Data**  **Hole Dia Qty**  **Identification Name**  **Code** Head near side

- 4 BACR15FP5F3R RIVET, BLIND O Head near side. Grip length may need to be adjusted depending on the amount of shimming, if any. - 2 BACR15GF5D11 RIVET, 100 DEG P

Head near side, double flush - 2 BACR15GF5D12 RIVET, 100 DEG Q
Head near side, double flush - 2 BACR15GF5D9 RIVET, 100 DEG R

- 2 NAS1149D0363J WASHER, FLAT X

- 2 NAS1149D0563J WASHER Z

- 3 NAS1149D0763J WASHER AA

- 1 NAS1149D1290J WASHER, PLAIN AB

- 2 BACW10P220S WASHER AD

**FIGURE 1: RIGHT SIDE, ELEVATOR TAB CONTROL MECHANISM MODIFICATION (SHEET 7 OF 7)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 48 of 59 **BOEING SERVICE BULLETIN 737-27-1300 FIGURE 2: LEFT SIDE, ELEVATOR TAB CONTROL MECHANISM MODIFICATION**  **(SHEET 1 OF 7)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 49 of 59 **BOEING SERVICE BULLETIN 737-27-1300 FIGURE 2: LEFT SIDE, ELEVATOR TAB CONTROL MECHANISM MODIFICATION**  **(SHEET 2 OF 7)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 50 of 59 **BOEING SERVICE BULLETIN 737-27-1300 FIGURE 2: LEFT SIDE, ELEVATOR TAB CONTROL MECHANISM MODIFICATION**  **(SHEET 3 OF 7)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 51 of 59 **BOEING SERVICE BULLETIN 737-27-1300 FIGURE 2: LEFT SIDE, ELEVATOR TAB CONTROL MECHANISM MODIFICATION**  **(SHEET 4 OF 7)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 52 of 59 **BOEING SERVICE BULLETIN 737-27-1300 More Data**  **Qty Identification**  **Name Task**  **Step** Install flush withedge of lug assembly. Shim if/as required. 4 BACS40R007Y020P SHIM, LAMINAT- ED Install (New) 1

Install flush withedge of lug assembly. 2 251A2455-10 DOUBLER - TAB MECHANISM, ELEVATOR CONTROLS Install (New) 2

Install flush withedge of lug assembly. 2 251A2455-11 RADIUS FILLER, UPPER - TAB MECHANISM, ELEVATOR CONTROLS Install (New) 3

Install flush withedge of lug assembly. 2 251A2455-9 RADIUS FILLER, LOWER - TAB MECHANISM, ELEVATOR CONTROLS Install (New)

Match drill 5 holes each side. (a) 10
- Fastener Hole Drill 4

(b) 1 251A2455-1 LUG ASSY -TAB MECHANISM, ELEVATOR CONTROLS Install (New) 5 Left frame assembly

(b) 1 251A2455-2 LUG ASSY -TAB MECHANISM, ELEVATOR CONTROLS Install (New) Right frame assembly

(a) 2 251A2455-7 MACHINED SPACER - TAB MECHANISM, ELEVATOR CONTROLS Install (New) 6 Left frame assembly

(a) 2 251A2455-8 RETAINER -TAB MECHANISM, ELEVATOR CONTROL Install (New) Right frame assembly

**FIGURE 2: LEFT SIDE, ELEVATOR TAB CONTROL MECHANISM MODIFICATION (SHEET 5 OF 7)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 53 of 59 **BOEING SERVICE BULLETIN 737-27-1300 More Data**  **Qty Identification**  **Name Task**  **Step** On the top of theframe assemblies Part mark 251A2431-15 (left frame assy) & 251A2431-17 (right frame assy) on the251A2430-25 elevator tab control mechanism. (c) 2
- Part Mark Identify 7

On the bottom of the elevator tabcontrol mechanism part mark 251A2430-25. (c) (d) 1
- Part Mark Identify

On the bottom of the elevator tabcontrol mechanism with actuator installed part mark 251A2430- 23. (c) (d) 1
- Part Mark Identify

(a) Touch-up fastener holes with Chemical Conversion Coating. Refer to SOPM 20-43-03 as an accepted procedure. (b) Wet install bolts with BMS 5-95. Refer to SOPM 20-50-19 as an accepted procedure. (c) Rubber stamp part mark. Refer to SOPM 20-50-10 as an accepted procedure. (d) apply abrasive overcoat.
**More Data Hole Dia**  **Qty Identification**  **Name Code**  Head far side

- 4 BACB30FM5AK7 BOLT, HEX DRIVE C

- 4 BACB30MB8A10 BOLT, PROTRUDING HD D

- 4 BACC30BH8 COLLAR E

- 4 BACC30M5 COLLAR F

- 1 BACN10JC12CD SELF-LOCKING NUT H

- 2 BACN10JC5CD SELF-LOCKING NUT J

- 3 BACN10JC7CD SELF-LOCKING NUT K

- 2 BACN10YR3CD NUT L

**FIGURE 2: LEFT SIDE, ELEVATOR TAB CONTROL MECHANISM MODIFICATION (SHEET 6 OF 7)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 54 of 59 **BOEING SERVICE BULLETIN 737-27-1300 More Data**  **Hole Dia Qty**  **Identification Name**  **Code** Head near side

- 4 BACR15FP5F3R RIVET, BLIND O Head near side. Grip length may need to be adjusted depending on the amount of shimming, if any. - 2 BACR15GF5D11 RIVET, 100 DEG P

Head near side, double flush - 2 BACR15GF5D12 RIVET, 100 DEG Q
Head near side, double flush - 2 BACR15GF5D9 RIVET, 100 DEG R

- 2 NAS1149D0363J WASHER, FLAT X

- 2 NAS1149D0563J WASHER Z

- 3 NAS1149D0763J WASHER AA

- 1 NAS1149D1290J WASHER, PLAIN AB

- 2 BACW10P220S WASHER AD

**FIGURE 2: LEFT SIDE, ELEVATOR TAB CONTROL MECHANISM MODIFICATION (SHEET 7 OF 7)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 55 of 59 **BOEING SERVICE BULLETIN 737-27-1300 FIGURE 3: RIGHT SIDE, ELEVATOR TAB CONTROL MECHANISM INSTALLATION**  **(SHEET 1 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 56 of 59 **BOEING SERVICE BULLETIN 737-27-1300 More Data**  **Qty Identification**  **Name Task**  **Step** Use the parts/fasteners at the locations shown to replace theexisting parts/fasteners. All other parts/fasteners areto be reused for installation. (a) 1
- Elevator Tab Control Mechanism Install (Changed) 1

(a) Refer to 737-600/700/800/900 AMM 27-31-34 as an accepted procedure.
**More Data Hole Dia**  **Qty Identification**  **Name Code**  (a)

- 1 251A2445-4 PIN ASSY - DUAL LOAD PATH, TABMECHANISM, ELEVATOR CONTROL A

(a)

- 1 251A2445-5 PIN ASSY - DUAL LOAD PATH, TABMECHANISM, ELEVATOR CONTROL B

- 1 BACN10HR5CD NUT G

- 1 BACN10JC4CD NUT,SELF-LOCKING I

- 2 BACN10JC5CD SELF-LOCKING NUT J

- 4 BACN10YR3CD NUT L

- 4 BACN10YR4CD NUT M

- 2 BACP18BC02A12P PIN, COTTER N

- 2 BACS12GU3K7 SCREW, CAP S

- 1 BACW10BP5CD CSK WASHER U

- 4 BACW10P475CG WASHER, FLAT V

- 2 NAS1149D0332J WASHER W

- 4 NAS1149D0363J WASHER, FLAT X

- 1 NAS1149D0463J WASHER Y

- 3 NAS1149D0563J WASHER Z (a)

- 2 NAS75-5-021 BUSHING AC (a) Apply BMS3-28 anti-seize compound to the OD of the fastener or bushing prior to installation. Refer to SOPM 20-50-07 as an acceptable procedure.

**FIGURE 3: RIGHT SIDE, ELEVATOR TAB CONTROL MECHANISM INSTALLATION (SHEET 2 OF 2)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 57 of 59 **BOEING SERVICE BULLETIN 737-27-1300 FIGURE 4: LEFT SIDE, ELEVATOR TAB CONTROL MECHANISM INSTALLATION**  **(SHEET 1 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 58 of 59 **BOEING SERVICE BULLETIN 737-27-1300 More Data**  **Qty Identification**  **Name Task**  **Step** Use the parts/fasteners at the locations shown to replace theexisting parts/fasteners. All other parts/fasteners areto be reused for installation. (a) 1
- Elevator Tab Control Mechanism Install (Changed) 1

(a) Refer to 737-600/700/800/900 AMM 27-31-34 as an accepted procedure.
**More Data Hole Dia**  **Qty Identification**  **Name Code**  (a)

- 1 251A2445-4 PIN ASSY - DUAL LOAD PATH, TABMECHANISM, ELEVATOR CONTROL A

(a)

- 1 251A2445-5 PIN ASSY - DUAL LOAD PATH, TABMECHANISM, ELEVATOR CONTROL B

- 1 BACN10HR5CD NUT G

- 1 BACN10JC4CD NUT,SELF-LOCKING I

- 2 BACN10JC5CD SELF-LOCKING NUT J

- 4 BACN10YR3CD NUT L

- 4 BACN10YR4CD NUT M

- 2 BACP18BC02A12P PIN, COTTER N

- 2 BACS12GU3K7 SCREW, CAP S

- 1 BACW10BP5CD CSK WASHER U

- 4 BACW10P475CG WASHER, FLAT V

- 2 NAS1149D0332J WASHER W

- 4 NAS1149D0363J WASHER, FLAT X

- 1 NAS1149D0463J WASHER Y

- 3 NAS1149D0563J WASHER Z (a)

- 2 NAS75-5-021 BUSHING AC (a) Apply BMS3-28 anti-seize compound to the OD of the fastener or bushing prior to installation. Refer to SOPM 20-50-07 as an acceptable procedure.

**FIGURE 4: LEFT SIDE, ELEVATOR TAB CONTROL MECHANISM INSTALLATION (SHEET 2 OF 2)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 16, 2012 737-27-1300 59 of 59 **BOEING SERVICE BULLETIN 737-27-1300**