### Commercial **Airplanes** 

# 737 Service Bulletin **SPECIAL ATTENTION Number: 737-32-1402**  Original Issue: August 06, 2008 Revision 1: February 07, 2013 ATA System: 3211 **SUBJECT:** LANDING GEAR - Main Landing Gear - Forward Trunnion Pin Inspection and Replacement. Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 300-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws. 9E991 ECCN: 

## BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET Copyright © 2008 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 Unpublished Work.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: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 1 of 55 7.0Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 2 of 55 **BOEING SERVICE BULLETIN 737-32-1402**

BLANK PAGE**Table of Contents** Revision Transmittal Sheet............................................ 5 Summary...................................................... 9 1. PLANNING INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 A. Effectivity. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 1. Airplanes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 2. Spares Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 F. Approval. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 G. Manpower. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 1. Existing Data:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 2. Data Supplied with this Service Bulletin:. . . . . . . . . . . . . . . . . . . . . . . . . . . 30 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 30 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 30 M. Software Accomplishment Summary. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32 C. Parts Necessary for Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32 1. Kits/Parts:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32 2. Parts and Materials Supplied by the Operator:. . . . . . . . . . . . . . . . . . . . . . . . 33 3. Parts Modified and Reidentified:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34 4. Parts Removed and Not Replaced:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 34 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36 FIGURE 1: LEFT MLG FORWARD TRUNNION PIN TRANSITION RADIUS - INSPECTION. . . . . 42 FIGURE 2: RIGHT MLG FORWARD TRUNNION PIN TRANSITION RADIUS - INSPECTION. . . . . 44 FIGURE 3: LEFT MLG FORWARD TRUNNION PIN - PROTECTIVE FINISH APPLICATION. . . . . 46 FIGURE 4: RIGHT MLG FORWARD TRUNNION PIN - PROTECTIVE FINISH APPLICATION. . . . 49 FIGURE 5: FORWARD TRUNNION PIN LUBRICATION - LEFT MLG. . . . . . . . . . . . . . . . . . 52 FIGURE 6: FORWARD TRUNNION PIN LUBRICATION - RIGHT MLG. . . . . . . . . . . . . . . . . 54

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 3 of 55 **BOEING SERVICE BULLETIN 737-32-1402**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 4 of 55 **BOEING SERVICE BULLETIN 737-32-1402**

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### Commercial **Airplanes** 

# 737 Service Bulletin **SPECIAL ATTENTION Revision Transmittal Sheet**  **Number: 737-32-1402** Original Issue: August 06, 2008 Revision 1: February 07, 2013 ATA System: 3211 **SUBJECT:** LANDING GEAR - Main Landing Gear - Forward Trunnion Pin Inspection and Replacement. This revision includes all pages of the service bulletin. **COMPLIANCE INFORMATION RELATED TO THIS REVISION** Federal Aviation Administration (FAA) Airworthiness Directive AD 2009-24-07 is related to this service bulletin. No more work is necessary on the airplane(s) changed in accordance with the Original Issue of this service bulletin. 737-600/700/800/900 airplanes, but not 737-700/700C/800 airplanes with a Boeing Business Jet (BBJ) configuration, from Line Number 1423 to 1787 and from Line Number 2091 to 3526, are added to Group 1 of this service bulletin effectivity. These airplanes must start and continue repeat lubrication applications for the forward trunnion pin and do a detailed inspection of the trunnion pin transition radius, of the left and right Main Landing Gear (MLG). 737-700/700C/800 airplanes with a Boeing Business Jet configuration (BBJ) variable numbers YD412, YD415 thru YD417, YG091 thru YG093, YG103, YG104, YG111 thru YG114, YG116 thru YG128 and YG701 are added to Group 2. These airplanes must start and continue repeat lubrication applications for the forward trunnion pin and do a detailed inspection of the trunnion pin transition radius, of the left and right Main Landing Gear (MLG). Airplanes variable numbers YG101 and YG102 are moved from Group 1 to Group 2 of this service bulletin effectivity. **REASON FOR REVISION** This revision is sent to increase the service bulletin effectivity to a larger range of airplanes because of reports of corrosion protection damage to the forward trunnion pin on 737 airplanes outside the original service bulletin effectivity. Airplanes line numbers 1423 thru 1787 and 2091 thru 3526 have therefore been added to Group 1 and Group 2 of the service bulletin effectivity where applicable. From line number 3527 and above a new trunnion pin seal and seal retainer were installed that are less likely to allow damage in this area. Also, a requirement was added to production drawings to do a visual inspection of the protective coating of the forward trunnion pin transition radius, after the MLG is installed. Airplane variable numbers YG101 and YG102 are moved to Group 2, because they were not correctly identified as BBJ before. Material Information and Accomplishment Instructions are changed to show trunnion pin, P/N 161A1188-3, as fully interchangeable with P/N 161A1188-9, also trunnion pins, P/N 161A1188-17, -19, -21 and -23 are added with their related part substitutions. Appendix A and B and related operator inspection report instructions are removed.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 5 of 55Terminology has been changed in the Work Instructions to agree with the terminology defined in Paragraph 3.A., General Information - Notes. These sections are changed: 1. In Summary, Background: Added Boeing Service Related Problem, Boeing Fleet Team Digest, Boeing Service Letter and related Boeing Service Bulletin references. Updated second paragraph. 2. In Summary, Action: Removed inspection report. 3. In Summary, Effectivity: Updated airplane models and statement. 4. In Summary, Compliance: Added FAA AD 2009-24-07. 5. In Paragraph 1.A., Effectivity: Updated airplane models and Group Configuration Table. Added airplanes line numbers 1423 thru 1787 and 2091 thru 3526, as applicable, to effectivity list. Moved airplanes variable numbers YG101 and YG102 from Group 1 to Group 2. 6. In Paragraph 1.C., Reason: Added Boeing Service Related Problem, Boeing Fleet Team Digest and Boeing Service Letter references. Updated second paragraph. 7. In Paragraph 1.D., Description: Removed inspection report. Updated airplane models in maintenance zone table. 8. In Paragraph 1.E., Compliance: Added FAA AD 2009-24-07 and note. Updated compliance times for to refer to this AD and added new rows to Table 1 and 2 to cover airplanes not included in the effectivity of the Original Issue of this service bulletin. 9. In Paragraph 1.F., Approval: Added Alternative Method of Compliance (AMOC) statement. 10. In Paragraph 1.G., Manpower: Added footnote (b) and references to the Manpower table for PART I. Corrected PART IV total. 11. In Paragraph 1.J., References: updated. 12. In Paragraph 1.K., Publications Affected: Added Publications Affected table, with new IPC reference, and note on Damage Tolerance Based Structural Inspections. 13. Added Paragraph 1.M., Software Accomplishment Summary: New service bulletin section - not affected. 14. In Paragraph 2.A., Material - Price and Availability: Changed footnote (b) to show correct part interchangeability. Added P/N's 161A1188-17, -19, -21 and -23 and Footnotes (h) thru (l). Updated prices. 15. In Paragraph 2.B., Industry Support Information: Updated warranty statement. 16. In Paragraph 2.C.1., Kits/Parts: Changed footnote (b) and added optional P/N 161A1188-9 to show correct part interchangeability. Added P/N's 161A1188-17, -19, -21 and -23 and Footnotes (i) thru (n). 17. In Paragraph 2.C.2., Parts and Materials Supplied by the Operator: Corrected Grease Specification and Chromate name. Added equivalent material specifications for Ultrachromate 300. Combined BMS 3-38 and BMS 3-26.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 6 of 55 **BOEING SERVICE BULLETIN 737-32-1402**18. In Paragraph 3.A., General Information: General Notes updated. 19. In Paragraph 3.B., Work Instructions, PART I: Corrected Step 2. Added notes to Step 5.c.2. Removed Step 6 for inspection report. 20. In Paragraph 3.B., Work Instructions, PART II: Changed Step 3.b. and added Steps 3.f. thru 3.i. and note to show part interchangeability. Added Steps 5 thru 9. 21. In Paragraph 3.B., Work Instructions, PART III: Updated paragraph structure. Changed part name in Step 4 to agree with Figures 3 and 4. Added Step 7. 22. In Paragraph 3.B., Work Instructions, PART IV: Added Steps 2 thru 4. 23. In Figure 1 Step Table: Added Inspection Description to Step 2. Removed Footnote (a) and reference. 24. In Figure 2 Step Table: Added Inspection Description to Step 2. Removed Footnote (a) and reference. 25. In Figure 3 Step Table: Added equivalent material specifications. Updated quantity definitions. 26. In Figure 4 Step Table: Added equivalent material specifications. Updated quantity definitions. 27. Removed Appendix A and B. The data given in Information Notices 737-32-1402 IN 01, 737-32-1402 IN 02 is included in this revision. Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location of important changes. Pages with no vertical lines have no important changes. **REVISION HISTORY** August 06, 2008 Original Issue: February 07, 2013 Revision 1:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 7 of 55 **BOEING SERVICE BULLETIN 737-32-1402**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 8 of 55 **BOEING SERVICE BULLETIN 737-32-1402**

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### Commercial **Airplanes** 

# 737 Service Bulletin **SPECIAL ATTENTION Summary**  **Number: 737-32-1402** Original Issue: August 06, 2008 Revision 1: February 07, 2013 ATA System: 3211 **SUBJECT:** LANDING GEAR - Main Landing Gear - Forward Trunnion Pin Inspection and Replacement. BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY. **CONCURRENT REQUIREMENTS** None. **BACKGROUND** This Service Bulletin gives instructions to inspect the Main Landing Gear (MLG) forward trunnion pins for finish damage or corrosion pitting, and if necessary, to replace them. If this Service Bulletin is not done, the corrosion pitting could cause stress cracking of the forward trunnion pin which could result in a MLG collapse due to fracture of the pin. MLG forward trunnion pin protective finishes may have been damaged during final assembly. The protective finish could be damaged at the transition radius between the chrome plated outer diameter and the spherical ball bearing surface, because the pin was not handled correctly. The damage of the protective finish puts the base metal at risk from corrosion pitting. After the release of the Original Issue of this service bulletin, Boeing has received a total of four reports of MLG trunnion pin transition radius finish damage on pins installed on airplanes that are before and after the effectivity of the Original Issue of this service bulletin. In each case, the MLG had not been removed since aircraft delivery and the damage is similar to that described in this service bulletin. Thus, at this revision, the effectivity is being increased to include those airplanes omitted previously, between line numbers 1423 and 3526. From line number 3527 and above a new trunnion pin seal and seal retainer were installed that are less likely to allow damage in this area. Also, a requirement was added to production drawings to do a visual inspection of the protective coating of the forward trunnion pin transition radius, after the MLG is installed. Boeing Service Bulletin 737-32-1376 and 737-32-1448, are related to this service bulletin. Boeing recommends to do this service bulletin at the same time as Boeing Service Bulletin 737-32-1448, if applicable. Boeing Service Related Problem (SRP) 737NG-SRP-32-0175 and 737NG-SRP-32-0157 are related to this service bulletin. Boeing Service Letter 737-SL-32-166 is related to this service bulletin.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 9 of 55Boeing Fleet Team Digest 737NG FTD 32-11005, 737NG FTD 32-07010 and 737NG FTD 32-09004 are related to this service bulletin. **ACTION** Do the lubrication of the MLG Forward Trunnion Pins at the thresholds given in Paragraph 1.E., Compliance, Table 1 or Table 2 as applicable. Do (in-situ) a detailed inspection of the Forward Trunnion Pin Transition Radius area (with the Main Landing Gear not removed) at the thresholds and repeat intervals given in Paragraph 1.E., Compliance, Table 1 or Table 2 as applicable. Repair/Overhaul or replace the MLG Forward Trunnion Pin if finish damage or corrosion is found. **EFFECTIVITY** 737-600, 737-700, 737-700C, 737-800, 737-900 Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s). **COMPLIANCE** Federal Aviation Administration (FAA) Airworthiness Directive AD 2009-24-07 is related to this service bulletin. Refer to Paragraph 1.E., Compliance. **INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are available for airplanes in warranty as of February 22, 2007. Please refer to Paragraph 2.B., Industry Support Information. **MANPOWER** Refer to Paragraph 1.G., Manpower. **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: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 10 of 55 **BOEING SERVICE BULLETIN 737-32-1402**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 11 of 55 **BOEING SERVICE BULLETIN 737-32-1402**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 12 of 55 **BOEING SERVICE BULLETIN 737-32-1402**

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### Commercial **Airplanes** 

# 737 Service Bulletin **SPECIAL ATTENTION Number: 737-32-1402**  Original Issue: August 06, 2008 Revision 1: February 07, 2013 ATA System: 3211 **SUBJECT:** LANDING GEAR - Main Landing Gear - Forward Trunnion Pin Inspection and Replacement. BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY. **1. PLANNING INFORMATION A. Effectivity**  1. Airplanes Refer to Service Bulletin Index D6-19567 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. This service bulletin is for the airplane(s) shown below.
**DESCRIPTION CONFIGURATION**  **GROUP** 737-600, -700, -700C, -800 and -900 airplanes, from Line Number 1423 to 3526, but not 737-700/700C/800 airplanes with a Boeing Business Jet configuration. - 1

737-700, -700C and -800 airplanes, with a Boeing Business Jet (BBJ) configuration, between line number 1423 and 3526. - 2

Airplane Models: 737-600, 737-700, 737-700C, 737-800, 737-900 **Group Variable Number**  1 YA146 - YA199 1 YA373 - YA377 1 YA631 1 YA666 - YA667 1 YA973 - YA978

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 13 of 55**Group Variable Number**  1 YB127 - YB132 1 YB157 - YB158 1 YB371 - YB392 1 YB526 1 YB544 1 YB571 - YB580 1 YB584 - YB598 1 YB616 - YB630 1 YB633 - YB635 1 YB651 1 YB656 1 YB671 - YB672 1 YB857 - YB863 1 YB871 - YB874 1 YB881 - YB893 1 YB901 - YB903 1 YB911 1 YB961 - YB974 1 YB981 1 YB986 - YB996 1 YC083 - YC084 1 YC095 1 YC170 1 YC179 1 YC190 1 YC202 - YC203 1 YC206 - YC207 1 YC385 - YC387 1 YC394 1 YC438 - YC439 1 YC742 - YC750 1 YD056 - YD057 1 YD108 - YD113

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 14 of 55 **BOEING SERVICE BULLETIN 737-32-1402 Group**  **Variable Number** 1 YD158 - YD159 1 YD333 - YD334 2 YD412 - YD417 1 YD491 - YD499 1 YD512 1 YD535 1 YD591 - YD595 1 YD651 - YD655 1 YE324 - YE326 1 YE371 - YE383 1 YF001 - YF011 1 YF021 - YF049 1 YF051 - YF065 1 YF086 - YF087 1 YF106 - YF107 1 YF111 - YF114 1 YF116 - YF119 1 YF121 - YF128 1 YF176 - YF178 1 YF191 - YF192 1 YF201 - YF276 1 YF401 - YF402 1 YF431 - YF432 1 YF441 - YF442 1 YF451 - YF460 1 YF501 - YF599 1 YF701 - YF707 1 YF801 - YF803 1 YF831 - YF832 1 YF836 - YF838 1 YF901 - YF905 1 YF921 - YF927 1 YF951

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 15 of 55 **BOEING SERVICE BULLETIN 737-32-1402 Group**  **Variable Number** 2 YG091 - YG099 2 YG101 - YG104 2 YG111 - YG114 2 YG116 - YG128 1 YG202 - YG205 1 YG211 - YG214 1 YG221 - YG224 1 YG251 - YG252 1 YG507 - YG511 2 YG701 1 YG711 1 YJ003 - YJ013 1 YJ021 1 YJ533 - YJ579 1 YJ593 - YJ599 1 YJ683 - YJ694 1 YJ814 - YJ860 1 YJ872 - YJ880 1 YJ902 - YJ904 1 YJ908 - YJ910 1 YJ917 - YJ929 1 YJ932 - YJ937 1 YJ941 - YJ956 1 YJ961 1 YJ976 - YJ977 1 YK003 - YK007 1 YK111 - YK112 1 YK121 - YK122 1 YK131 - YK133 1 YK136 - YK139 1 YK141 - YK142 1 YK146 - YK148 1 YK151 - YK154

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 16 of 55 **BOEING SERVICE BULLETIN 737-32-1402 Group**  **Variable Number** 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 1 YK456 - YK467 1 YK471 - YK473 1 YK476 1 YK480 - YK487 1 YK491 1 YK495 - YK498 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

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 17 of 55 **BOEING SERVICE BULLETIN 737-32-1402 Group**  **Variable Number** 1 YK691 1 YK701 - YK713 1 YK716 - YK719 1 YK721 - YK741 1 YK751 - YK770 1 YK776 - YK778 1 YK781 - YK785 1 YK792 1 YK796 - YK797 1 YK801 - YK899 1 YK901 - YK912 1 YK918 - YK919 1 YK921 - YK928 1 YK941 - YK959 1 YK961 - YK996 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 - YL136 1 YL201 - YL226 1 YL271 - YL272 1 YL281 - YL284 1 YL302 - YL303 1 YL311 - YL314 1 YL316 - YL321 1 YL351 - YL353 1 YL371 - YL374 1 YL401

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 18 of 55 **BOEING SERVICE BULLETIN 737-32-1402 Group**  **Variable Number** 1 YL421 - YL429 1 YL431 - YL444 1 YL461 - YL478 1 YL501 - YL509 1 YL531 - YL534 1 YL541 - YL544 1 YL561 - YL569 1 YL591 - YL598 1 YL601 - YL606 1 YL611 - YL612 1 YL616 - YL617 1 YL621 1 YL626 1 YL631 - YL634 1 YL636 - YL637 1 YL661 - YL664 1 YL676 - YL681 1 YL691 1 YL696 - YL697 1 YL701 - YL706 1 YL731 1 YL751 - YL752 1 YL756 - YL757 1 YL761 - YL779 1 YL796 - YL797 1 YL801 - YL815 1 YL901 - YL910 1 YL921 - YL940 1 YL951 - YL968 1 YM102 - YM103 1 YM201 - YM242 1 YM251 - YM299 1 YM301 - YM398

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 19 of 55 **BOEING SERVICE BULLETIN 737-32-1402 Group**  **Variable Number** 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 - YM698 1 YM701 - YM710 1 YM761 - YM765 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 YQ001 - YQ003 1 YQ011 - YQ017 1 YQ026 - YQ027 1 YQ036 - YQ042 1 YQ201 1 YQ231

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 20 of 55 **BOEING SERVICE BULLETIN 737-32-1402 Group**  **Variable Number** 1 YQ241 - YQ242 1 YQ291 - YQ295 1 YQ401 - YQ403 1 YR001 - YR005 1 YR051 - YR053 1 YR101 1 YR111 - YR112 1 YR166 1 YR201 - YR203 1 YR231 - YR232 2. Spares Affected None. **B. Concurrent Requirements** None. **C. Reason** This Service Bulletin gives instructions to inspect the Main Landing Gear (MLG) forward trunnion pins for finish damage or corrosion pitting, and if necessary, to replace them. If this Service Bulletin is not done, the corrosion pitting could cause stress cracking of the forward trunnion pin which could result in a MLG collapse due to fracture of the pin. MLG forward trunnion pin protective finishes may have been damaged during final assembly. The protective finish could be damaged at the transition radius between the chrome plated outer diameter and the spherical ball bearing surface, because the pin was not handled correctly. The damage of the protective finish puts the base metal at risk from corrosion pitting. After the release of the Original Issue of this service bulletin, Boeing has received a total of four reports of MLG trunnion pin transition radius finish damage on pins installed on airplanes that are before and after the effectivity of the Original Issue of this service bulletin. In each case, the MLG had not been removed since aircraft delivery and the damage is similar to that described in this service bulletin. Thus, at this revision, the effectivity is being increased to include those airplanes omitted previously, between line numbers 1423 and 3526. From line number 3527 and above a new trunnion pin seal and seal retainer were installed that are less likely to allow damage in this area. Also, a requirement was added to production drawings to do a visual inspection of the protective coating of the forward trunnion pin transition radius, after the MLG is installed. Boeing Service Bulletin 737-32-1376 and 737-32-1448, are related to this service bulletin. Boeing recommends to do this service bulletin at the same time as Boeing Service Bulletin 737-32-1448, if applicable. Boeing Service Related Problem (SRP) 737NG-SRP-32-0175 and 737NG-SRP-32-0157 are related to this service bulletin.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 21 of 55 **BOEING SERVICE BULLETIN 737-32-1402**Boeing Service Letter 737-SL-32-166 is related to this service bulletin. Boeing Fleet Team Digest 737NG FTD 32-11005, 737NG FTD 32-07010 and 737NG FTD 32-09004 are related to this service bulletin. Revision 1 is sent to increase the service bulletin effectivity to a larger range of airplanes because of reports of corrosion protection damage to the forward trunnion pin on 737 airplanes outside the original service bulletin effectivity. Airplanes line numbers 1423 thru 1787 and 2091 thru 3526 have therefore been added to Group 1 and Group 2 of the service bulletin effectivity where applicable. From line number 3527 and above a new trunnion pin seal and seal retainer were installed that are less likely to allow damage in this area. Also, a requirement was added to production drawings to do a visual inspection of the protective coating of the forward trunnion pin transition radius, after the MLG is installed. Airplane variable numbers YG101 and YG102 are moved to Group 2, because they were not correctly identified as BBJ before. Material Information and Accomplishment Instructions are changed to show trunnion pin, P/N 161A1188-3, as fully interchangeable with P/N 161A1188-9, also trunnion pins, P/N 161A1188-17, -19, -21 and -23 are added with their related part substitutions. Appendix A and B and related operator inspection report instructions are removed.. **D. Description** Do the lubrication of the MLG Forward Trunnion Pins at the thresholds in accordance with Paragraph 1.E., Compliance, Table 1 or Table 2 as applicable. Do (in-situ) a detailed inspection of the Forward Trunnion Pin Transition Radius area at the thresholds and repeat intervals in accordance with Paragraph 1.E., Compliance, Table 1 or Table 2 as applicable. **NOTE:** Make sure that you have serviceable Trunnion Pins on hand in case the Trunnion Pins inspected are found with damage and need to be replaced. Repair/Overhaul or replace the MLG Forward Trunnion Pin if damaged finishes or corrosion is found. Revision 1 - No more work is necessary on the airplane(s) changed in accordance with the original issue of this service bulletin. The work in this service bulletin is done in the maintenance zone(s) given below. **Group 1:**
**Affected Maintenance Zones Zone**  **Model** 551, 661, 734, 744 737-600, 737-700, 737-700C, 737-800, 737-900 **Group 2:**
**Affected Maintenance Zones Zone**  **Model** 551, 661, 734, 744 737-700, 737-700C, 737-800

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 22 of 55 **BOEING SERVICE BULLETIN 737-32-1402 E. Compliance**  Accomplish the required action(s), based on the applicable condition(s), in Table(s) 1 and 2, in accordance with Paragraph 3. Accomplishment Instructions. Federal Aviation Administration (FAA) Airworthiness Directive AD 2009-24-07 is related to this service bulletin. **Group 1: Table 1 - MLG Forward Trunnion Pin - Inspection and Lubrication of the Transition Radius with Main**  **Landing Gear not removed (In-Situ) Repeat Interval**  **(Not to Exceed) Compliance Time (Whichever**  **Occurs Later) Action**  **Condition** 30 days (a) Within 30 days from January 4,2010, the effective date of AD 2009-24-07 . - Lubricate the MLG For-ward Trunnion Pin in accordance with Accomplishment Instruction 3.B., PART IV, "MLG ForwardTrunnion Pin - Lubrication"All airplanes that were included in the effectivity of the Original Issue of this service bulletin.

30 days (a) Within 30 days from the date of Revision 1 ofthis service bulletin - Lubricate the MLG For-ward Trunnion Pin in accordance with Accomplishment Instruction 3.B., PART IV, "MLG ForwardTrunnion Pin - Lubrication" All airplanes that were NOT included in the effectivity of the original issue of this service bulletin.

- Within 6 months from January 4,2010, the effective date of AD 2009-24-07 . Within 60 months sincethe date of issuance of theoriginal standard airworthiness certificateor date of issuance of the original exportcertificate of airworthiness. Detailed Inspection of the Transition Radius location (In-Situ) in accordancewith Accomplishment Instruction, paragraph 3.B., PART I, "MLG Forward Trunnion Pin - Inspection of the Transition Radiuswith the MLG Not Removed (in-situ)".All airplanes that were included in the effectivity of the Original Issue of this service bulletin.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 23 of 55 **BOEING SERVICE BULLETIN 737-32-1402 Group 1:**  **Table 1 - MLG Forward Trunnion Pin - Inspection and Lubrication of the Transition Radius with Main Landing Gear not removed (In-Situ)**  **Repeat Interval (Not to Exceed)**  **Compliance Time (Whichever Occurs Later)**  **Action Condition** 

- Within 6 months from the date of Revision 1 ofthis service bulletin Within 60 months sincethe date of issuance of theoriginal standard airworthiness certificateor date of issuance of the original exportcertificate of airworthiness Detailed Inspection of the Transition Radius location (In-Situ) in accordancewith Accomplishment Instruction, paragraph 3.B., PART I, "MLG Forward Trunnion Pin - Inspection of the Transition Radiuswith the MLG Not Removed (in-situ)" All airplanes that were NOT included in the effectivity of the original issue of this service bulletin.

- Before further flight - Repair the finish in accor-dance with Accomplishment Instruction, paragraph 3.B., PART III, "MLG Forward Trunnion Pin - Blending and Repair of the Protective Finish" (in situ).Airplanes with finish damage (scrapes or scratches through the full thickness of the primer or areas of missing primer) found inthe Transition Radius location, and no corrosion, no pitting, and no base metal scratches. And 24 Months (b) Within 24 Months after the finish damage is repaired - Detailed Inspection of the Transition Radius location (In-Situ) in accordancewith Accomplishment Instruction, paragraph 3.B., PART I, "MLG Forward Trunnion Pin - Inspection of the Transition Radiuswith the MLG Not Removed (in-situ)".

- Before further flight (c) - Do Accomplishment In- struction, paragraph 3.B., PART II, "MLG ForwardTrunnion Pin - Replacement". Airplanes with corrosion, or pitting, or base metalscratches in the base material, found at the Transition Radius location.

- Before further flight. - Do Accomplishment In- struction paragraph 3.B., PART IV, "MLG ForwardTrunnion Pin - Lubrication".Airplanes with no corrosion, no pitting , no base metal scratches, and nofinish damage at the Transition Radius location.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 24 of 55 **BOEING SERVICE BULLETIN 737-32-1402 Group 1:**  **Table 1 - MLG Forward Trunnion Pin - Inspection and Lubrication of the Transition Radius with Main Landing Gear not removed (In-Situ)**  **Repeat Interval (Not to Exceed)**  **Compliance Time (Whichever Occurs Later)**  **Action Condition**  (a) Until the inspections of PART I, "MLG Forward Trunnion Pin - Inspection of the Transition Radius with the MLG Not Removed" are completed. (b) Until the Forward Trunnion Pin is Replaced or Overhauled - for that pin only. Refer to CMM 57-15-01 as an accepted procedure. (c) Trunnion pins that are removed from the airplane can be repaired at the operator's approved maintenance facility. Refer to CMM 57-15-01 as an accepted procedure. The repair of the Trunnion Pin, with reference to CMM 57-15-01, will meet all compliance requirements of this service bulletin, for that pin only. **Group 2: Table 2 - MLG Forward Trunnion Pin - Inspection and Lubrication of the Transition Radius with Main**  **Landing Gear not removed (In-Situ) Repeat Interval**  **(Not to Exceed) Compliance Time (Whichever**  **Occurs Later) Action**  **Condition** 30 days (a) Within 30 days from January 4,2010, the effective date of AD 2009-24-07 . - Lubricate the MLG For-ward Trunnion Pin in accordance with Accomplishment Instruction 3.B., PART IV, "MLG ForwardTrunnion Pin - Lubrication"All airplanes that were included in the effectivity of the Original Issue of this service bulletin.

30 days (a) Within 30 days from the date of Revision 1 ofthis service bulletin - Lubricate the MLG For-ward Trunnion Pin in accordance with Accomplishment Instruction 3.B., PART IV, "MLG ForwardTrunnion Pin - Lubrication" All airplanes that were NOT included in the effectivity of the original issue of this service bulletin.

- Within 6 months from January 4,2010, the effective date of AD 2009-24-07 . Within 60 months sincethe date of issuance of theoriginal standard airworthiness certificateor date of issuance of the original exportcertificate of airworthiness. Detailed Inspection of the Transition Radius location (In-Situ) in accordancewith Accomplishment Instruction, paragraph 3.B., PART I, "MLG Forward Trunnion Pin - Inspection of the Transition Radiuswith the MLG Not Removed (in-situ)".All airplanes that were included in the effectivity of the Original Issue of this service bulletin.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 25 of 55 **BOEING SERVICE BULLETIN 737-32-1402 Group 2:**  **Table 2 - MLG Forward Trunnion Pin - Inspection and Lubrication of the Transition Radius with Main Landing Gear not removed (In-Situ)**  **Repeat Interval (Not to Exceed)**  **Compliance Time (Whichever Occurs Later)**  **Action Condition** 

- Within 6 months from the date of Revision 1 ofthis service bulletin Within 60 months sincethe date of issuance of theoriginal standard airworthiness certificateor date of issuance of the original exportcertificate of airworthiness Detailed Inspection of the Transition Radius location (In-Situ) in accordancewith Accomplishment Instruction, paragraph 3.B., PART I, "MLG Forward Trunnion Pin - Inspection of the Transition Radiuswith the MLG Not Removed (in-situ)" All airplanes that were NOT included in the effectivity of the original issue of this service bulletin.

- Before further flight - Repair the finish in accor-dance with Accomplishment Instruction, paragraph 3.B., PART III, "MLG Forward Trunnion Pin - Blending and Repair of the Protective Finish" (In-Situ).Airplanes with finish damage (scrapes or scratches through the full thickness of the primer or areas of missing primer) found inthe Transition Radius location and no corrosion, no pitting, and no base metal scratches And 24 Months (b) Within 24 Months after the finish damage is repaired. Detailed Inspection of the Transition Radius location (In-Situ) in accordancewith Accomplishment Instruction, paragraph 3.B., PART I, "MLG Forward Trunnion Pin - Inspection of the Transition Radiuswith the MLG Not Removed (in-situ)".

- Before further flight (c) - Do Accomplishment In- struction, paragraph 3.B., PART II, "MLG ForwardTrunnion Pin - Replacement". Airplanes with corrosion, or pitting, or base metalscratches in the base material, found at the Transition Radius location.

- Before further flight. - Do Accomplishment In- struction paragraph 3.B., PART IV, "MLG ForwardTrunnion Pin - Lubrication".Airplanes with no corrosion, no pitting , no base metal scratches, and nofinish damage at the Transition Radius location.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 26 of 55 **BOEING SERVICE BULLETIN 737-32-1402 Group 2:**  **Table 2 - MLG Forward Trunnion Pin - Inspection and Lubrication of the Transition Radius with Main Landing Gear not removed (In-Situ)**  **Repeat Interval (Not to Exceed)**  **Compliance Time (Whichever Occurs Later)**  **Action Condition**  (a) Until the inspections of PART I, "MLG Forward Trunnion Pin - Inspection of the Transition Radius with the MLG Not Removed" are completed. (b) Until the Forward Trunnion Pin is Replaced or Overhauled - for that pin only. Refer to CMM 57-15-01 as an accepted procedure. (c) Trunnion pins that are removed from the airplane can be repaired at the operator's approved maintenance facility. Refer to CMM 57-15-01 as an accepted procedure. The repair of the Trunnion Pin, with reference to CMM 57-15-01, will meet all compliance requirements of this service bulletin, for that pin only. **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 accomplishment of the inspection, investigative and corrective actions, and lubrication specified in Section 1.E., Compliance, of Service Bulletin 737-32-1402, Revision 1, as an alternative method of compliance to the inspection, investigative and corrective actions, and lubrication specified in Section 1.E., Compliance, of Service Bulletin 737-32-1402, Original Issue, dated August 6, 2008, and required by paragraphs (g), (h), and (j) of AD 2009-24-07. All provisions of AD 2009-24-07 that are not specifically referenced in this paragraph remain fully applicable and must be complied with accordingly. **G. Manpower** The table below shows an estimate of the task-hours necessary to do this service bulletin for each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator task-hour data if necessary. The estimate does not include lost time. These are some examples of lost time: — Time to adjust to the workplace — Time to schedule the work — Time to examine the work — Time to cure the materials — Time to make the parts — Time to find the tools.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 27 of 55 **BOEING SERVICE BULLETIN 737-32-1402 TABLE 1: PART I - MLG FORWARD TRUNNION PIN - TRANSITION RADIUS INSPECTION**  **WITH MAIN LANDING GEAR NOT REMOVED (IN-SITU) Elapsed Hours**  **Task-Hours Number of Per-**  **sons Task**  1.00 (b) 2.00 (b) 2 Open Access 2.00 2.00 1 FIGURE 1 2.00 2.00 1 FIGURE 2 1.00 (b) 2.00 (b) 2 Close Access 6.00 (a) (b) 8.00 (a) (b) TOTAL FOR EACH AIRPLANE FOR PART I (a) Total assumes no corrosion or finish damages found during the inspections covered in FIGURE 1 and FIGURE 2. If corrosion or finish damage is found more work may be necessary in PART I. (b) Estimates shown do not include time to remove and put back the left and right Main Landing Gear (MLG), if necessary. If it is necessary to remove and put back a MLG, an additional 34.00 hours will be added to the total for each airplane. Add 17.00 hours to the Open Access estimate and 17.00 hours to the Close Access estimate, for each MLG that must be removed and put back.
**TABLE 2: PART II - MLG FORWARD TRUNNION PIN - REPLACEMENT Elapsed Hours**  **Task-Hours Number of Per-**  **sons Task** 

9.00 36.00 4 Remove Trunnion Bearing Assy 1.00 2.00 2 Remove FWD Trunnion Pins 1.00 2.00 2 Install FWD Trun- nion Pins 9.00 36.00 4 Install Trunnion Bearing Assy 20.00 76.00 TOTAL FOR EACH AIRPLANE FOR PART II
**TABLE 3: PART III - MLG FORWARD TRUNNION PIN - BLENDING AND REPAIR OF THE PROTECTIVE FINISH**  **Elapsed Hours Task-Hours**  **Number of Per- sons**  **Task** (a) (a) (a) FIGURE 3 (a) (a) (a) FIGURE 4

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 28 of 55 **BOEING SERVICE BULLETIN 737-32-1402 TABLE 3: PART III - MLG FORWARD TRUNNION PIN - BLENDING AND REPAIR OF THE**  **PROTECTIVE FINISH Elapsed Hours**  **Task-Hours Number of Per-**  **sons Task**  (a) (a) TOTAL FOR EACH AIRPLANE FOR PART III (a) Manpower estimates are not available for FIGURE 3 and FIGURE 4: Left and right MLG Forward Trunnion Pin Protective Finish Restoration. The tasks covered by both figures are covered by Lost Time.
**TABLE 4: PART IV - MLG FORWARD TRUNNION PIN - LUBRICATION Elapsed Hours**  **Task-Hours Number of Per-**  **sons Task** 

0.25 0.25 1 FIGURE 5 0.25 0.25 1 FIGURE 6 0.50 0.50 TOTAL FOR EACH AIRPLANE FOR PART IV **H. Weight and Balance Changes** None. **I. Electrical Load Data** Not changed. **J. References** 1. Existing Data: a. Boeing Service Bulletin 737-32-1376, 737-32-1448. b. Boeing Service Letter 737-SL-32-166. c. Boeing Service Related Problem (SRP) 737NG-SRP-32-0157, 737NG-SRP-32-0175. d. Component Maintenance Manual (CMM) 57-15-01. e. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2009-24-07. f. Service Bulletin Index D6-19567. g. Standard Overhaul Practices Manual (SOPM) 20-00-00, 20-30-03, 20-41-05, 20-42-10, 20-44-04. h. 737-600/700/800/900 Aircraft Maintenance Manual (AMM) 07-11-01, 12-21-11, 32-00-01, 32-11-00, 32-11-83, 57-16-01.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 29 of 55 **BOEING SERVICE BULLETIN 737-32-1402**i. 737-600/700/800/900 Maintenance Planning Data (MPD) Appendix A. j. 737-700/800 Maintenance Planning Data (MPD) Appendix A. k. 737NG Fleet Team Digest (FTD) 32-07010, 32-09004, 32-11005. 2. Data Supplied with this Service Bulletin: None. 3. Installation Drawings Used in the Preparation of this Service Bulletin: None. **K. Publications Affected** 1. Publications: **Chapter-Section Publication**  32-11 737 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 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** Not affected.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 30 of 55 **BOEING SERVICE BULLETIN 737-32-1402 2. MATERIAL INFORMATION**  **A. Material - Price and Availability** Boeing can supply the parts shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin. The parts are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. Prices are in United States Dollars. Terms: Net 30 days. Reference this service bulletin and submit your purchase order by one of these methods: 1. Order on-line via ATA Spec 2000 or The Boeing PART Page 2. Fax to (206) 662-7145 **REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION** 
**Unit Price as of the Revision 01** **date of this Ser vice Bulletin**  **(US Dollars) ROLT as** **of the Re vision 01**  **date of this Ser** **vice Bul letin (Cal**  **endar Days)**  **QTY Date**  **Name Part Number** 

$4,271.00

- 1

- Forward Trunnion Pin 161A1188-1 (a) (g) $4,271.00

- 1

- Forward Trunnion Pin 161A1188-3 (b) (g) $4,271.00

- 1

- Forward Trunnion Pin 161A1188-5 (c) (g) $4,271.00

- 1

- Forward Trunnion Pin 161A1188-9 (d) (g) $12,084.00

- 1

- Forward Trunnion Pin 161A1188-13 (e) (g) $12,084.00

- 1

- Forward Trunnion Pin 161A1188-15 (f) (g) $12,084.00

- 1

- Forward Trunnion Pin 161A1188-17 (g) (h) (l) $12,084.00

- 1

- Forward Trunnion Pin 161A1188-19 (g) (i) (l) $12,084.00

- 1

- Forward Trunnion Pin 161A1188-21 (g) (j) (l) $12,084.00

- 1

- Forward Trunnion Pin 161A1188-23 (g) (k) (l) (a) 161A1188-1 Trunnion Pin may replace 161A1188-1 and 161A1188-5 Trunnion Pins. (b) 161A1188-3 Trunnion Pin may replace 161A1188-3 or 161A1188-9 Trunnion Pins. (c) 161A1188-5 Trunnion Pin replaces only 161A1188-5 Trunnion Pins. (d) 161A1188-9 Trunnion Pin may replace 161A1188-3 and 161A1188-9 Trunnion Pins. (e) 161A1188-13 Trunnion Pin may replace 161A1188-1 and 161A1188-5 Trunnion Pins. (f) 161A1188-15 Trunnion Pin may replace 161A1188-1 and 161A1188-5 Trunnion Pins.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 31 of 55 **BOEING SERVICE BULLETIN 737-32-1402 REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER**  **AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION**
**Unit Price as of the Revision 01** **date of this Ser vice Bulletin**  **(US Dollars) ROLT as** **of the Re vision 01**  **date of this Ser** **vice Bul letin (Cal**  **endar Days)**  **QTY Date**  **Name Part Number** 

(g) The quantity shown is for a single main landing gear strut. (h) 161A1188-17 Trunnion Pin may replace 161A1188-1 Trunnion Pins. (i) 161A1188-19 Trunnion Pin may replace 161A1188-13 Trunnion Pins. (j) 161A1188-21 Trunnion Pin may replace 161A1188-15 Trunnion Pins (k) 161A1188-23 Trunnion Pin may replace 161A1188-5 Trunnion Pins. (l) This part is required for the terminating action given in Boeing Service Bulletin 737-32-1448.
**NOTE:** Operators will need to identify which trunnion pin was initially fitted to each main landing gear strut. This will ensure the correct replacement part is ordered. **B. Industry Support Information** Boeing warranty remedies are available for 737-600/700/800/900 airplanes in warranty as of February 22, 2007. For inspection man-hour reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing Commercial Airplanes Group - Warranties. If the condition described in this service bulletin is found during the inspection for airplanes in warranty as of that date and additional man-hours and kits, parts, and/or special tools are required, send a warranty claim to Boeing Commercial Airplanes Group - Warranties. Please refer to this service bulletin number and reference the airplane variable number(s) in your purchase order. **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. **NOTE:** The items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane.
**Notes Existing Part Number**  **Name QTY**  **New Part Number** (a) (f) (g) (h) 161A1188-1 or 161A1188-5 (optional) Forward Trunnion Pin 1 161A1188-1 (b) (f) (g) (h) 161A1188-3 or 161A1188-9 (optional) Forward Trunnion Pin 1 161A1188-3 or 161A1188-9 (optional)

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 32 of 55 **BOEING SERVICE BULLETIN 737-32-1402 Notes**  **Existing Part Number Name**  **QTY New Part Number**  (c) (f) (g) 161A1188-5 or 161A1188-23 (optional) Forward Trunnion Pin 1 161A1188-5 (d) (f) 161A1188-1 or 161A1188-5 (optional) Forward Trunnion Pin 1 161A1188-13 (e) (f) 161A1188-1 or 161A1188-5 (optional) Forward Trunnion Pin 1 161A1188-15 (f) (h) (j) (n) 161A1188-1 Forward Trunnion Pin 1 161A1188-17 (f) (i) (k) (n) 161A1188-13 Forward Trunnion Pin 1 161A1188-19 (f) (i) (l) (n) 161A1188-15 Forward Trunnion Pin 1 161A1188-21 (f) (i) (m) (n) 161A1188-5 Forward Trunnion Pin 1 161A1188-23 (a) 161A1188-1 Trunnion Pin may replace 161A1188-1 and 161A1188-5 Trunnion Pins. (b) 161A1188-3 or 161A1188-9 Trunnion Pins may replace 161A1188-3 or 161A1188-9 Trunnion Pins. (c) 161A1188-5 Trunnion Pin replaces only 161A1188-5 Trunnion Pins. (d) 161A1188-13 Trunnion Pin may replace 161A1188-1 and 161A1188-5 Trunnion Pins. (e) 161A1188-15 Trunnion Pin may replace 161A1188-1 and 161A1188-5 Trunnion Pins. (f) Quantity shown is for one main landing gear strut. (g) Rework the existing part at an authorized repair center or send the parts that are removed to Boeing at the address given below: Spares Distribution Center Repair Overhaul and Exchange Services The Boeing Company 2201 South 142nd Street Building 2201, Door W-10, SSA 111 SeaTac, Washington 98168 Make sure the parts have tags, with the data that follows: (h) This part is used in production. (i) This part is not used in production. (j) 161A1188-17 Trunnion Pin replaces only 161A1188-1 Trunnion Pins. (k) 161A1188-19 Trunnion Pin replaces only 161A1188-13 Trunnion Pins. (l) 161A1188-21 Trunnion Pin replaces only 161A1188-15 Trunnion Pins. (m) 161A1188-23 Trunnion Pin replaces only 161A1188-5 Trunnion Pins. (n) This part is required for the terminating action given in Boeing Service Bulletin 737-32-1448. 2. Parts and Materials Supplied by the Operator:
**Notes Name**  **QTY Part Number / Specifi-**  **cation** (a) Corrosion Inhibiting Compound 16 oz. BMS 3-38 or BMS 3-26, Type II (a) Grease - Aircraft General Purpose 32oz. BMS 3-33 (a) Urethane Compatible Corrosion Re- sistant Primer 4 oz. BMS 10-79 Type III Grade A or Grade D

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 33 of 55 **BOEING SERVICE BULLETIN 737-32-1402 Notes**  **Name QTY**  **Part Number / Specifi- cation**  Lockwire 10 feet MS20995NC32 (a) Cleaning Solvent 1 pint BMS 11-7 (b) Scotch-Brite, Type A, very fine or equivalent material 3 feet Abrasive (c) Aluminum Oxide Abrasive Pad, 320 grit or finer or equivalent materialAs Necessary Abrasive (d) Chromate Conversion Coating 4 oz. Ultrachromate 300, or equivalent chromate solution per QQ-P-416 or AMS-QQ-P-416, Type II. (a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. (b) Vendor Contact Information: V76381, 3M CO., 3M Center Bldg. 225-3S-20, St. Paul, Minnesota 55144-1000. Refer to SOPM 20-00-00 for vendors. (c) Vendor Contact Information: V06565, Norton Company, Coated Abrasive Div., 10thAve. and 25th St., Watervliet, New York 12189. Refer to SOPM 20-00-00 for vendors. (d) Vendor Contact Information: V64709, Delta Pollution Control, Inc., 30540 S.E. 8th, Preston, Washington, 98050. Refer to SOPM 20-00-00 for vendors.
3. Parts Modified and Reidentified: None. 4. Parts Removed and Not Replaced: None. **D. Parts Necessary to Change Spares** None. **E. Special Tooling - Price and Availability** None. **F. Special Tooling Necessary to do this Service Bulletin** No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine operator tool supply to make sure all necessary tools are available.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 34 of 55 **BOEING SERVICE BULLETIN 737-32-1402 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 work packages. Task-Hours and Elapsed-Hours for each package are given in Paragraph 1.G., Manpower. 4. Unless shown differently, these dimensions and tolerances are used: — Torque limits to tighten nuts and bolts are given in 737 Structural Repair Manual, Chapter 51. 5. 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. 6. 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. 7. 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. 8. 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. 9. 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 35 of 55 **BOEING SERVICE BULLETIN 737-32-1402**10. 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. **B. WORK INSTRUCTIONS PART I - MLG FORWARD TRUNNION PIN - TRANSITION RADIUS INSPECTION WITH MAIN**  **LANDING GEAR NOT REMOVED (IN-SITU) WARNING:** MAKE SURE THE DOWNLOCK PINS ARE INSTALLED ON ALL THE LANDING GEAR. WITHOUT THE DOWNLOCK PINS, THE LANDING GEAR COULD RETRACT AND CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT 1. Install the downlock pins in the nose and main landing gear. Refer to 737-600/700/800/900 AMM 32-00-01 as an accepted procedure. 2. Remove the following access panels, if necessary, for a better accessibility to the inspection area: a. 551BB, Lower Inboard Fixed Trailing Edge, Gear Adjustment Door, for the Left Landing Gear. b. 551CB, Lower Inboard Fixed Trailing Edge, Gear Access Panel, for the Left Landing Gear. c. 651BB, Lower Inboard Fixed Trailing Edge, Gear Adjustment Door, for the Right Landing Gear. d. 651CB, Lower Inboard Fixed Trailing Edge, Gear Access Panel, for the Right Landing Gear. Refer to 737-600/700/800/900 MPD Appendix A or 737-700/800 MPD Appendix A for the panel locations. 3. Open the following access panels: a. 551DB, Lower Inboard Fixed Trailing Edge, Lube Actuator & MLG Beam Outboard Attach Pin Access Panel. b. 651DB, Lower Inboard Fixed Trailing Edge, Lube Actuator & MLG Beam Outboard Attach Pin Access Panel. Refer to 737-600/700/800/900 MPD Appendix A or 737-700/800 MPD Appendix A for the panel locations. 4. Clean the grease and debris from the transition radius area using a clean cloth and solvent. Refer to SOPM 20-30-03 as an accepted procedure. 5. Do a detailed inspection of the transition radius area of the Forward Trunnion Pin, on both the left and right MLG, in accordance with FIGURE 1 and FIGURE 2. Look for finish damage (scrapes and scratches through the full thickness of primer or areas of missing primer), signs of corrosion, and pitting, and base metal scratches in the base material. Minor scrapes and/or scratches that do not fully penetrate the primer layer shall not be considered as finish damage. **NOTE:** It is difficult to inspect the outboard transition radius area using a mirror. There is better visibility of this area if you look from the bottom up. It is recommended that Operators use a 10X magnification boroscope to inspect the outboard area of the Trunnion Pin. Use good light in order to have a good exposure of the transition radius area.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 36 of 55 **BOEING SERVICE BULLETIN 737-32-1402**a. If no corrosion, no pitting, no base metal scratches, and no finish damage are found at the Transition Radius location on the left and/or right forward trunnion pin(s), do PART IV - MLG Forward Trunnion Pin - Lubrication. b. If corrosion, pitting, or base metal scratches is found at the Transition Radius area on the left and/or right forward trunnion pin(s) remove and replace the Trunnion pin in accordance with PART II - MLG Forward Trunnion Pin Replacement. c. If finish damage (scrapes or scratches through the full thickness of the primer, or areas of missing primer) is found at the Transition Radius location on the left and/or right Forward Trunnion Pin(s), and there is no corrosion, no pitting, and no base metal scratches in the base material, continue with step 5.c.(3). If there is damage on the outboard side of the Trunnion Pin you may need to remove the Main Landing Gear in order to perform the inspection and the repair of the protective finish. If it is necessary to remove the Main Landing Gear continue with step 5.c.(1). (1) Lift the airplane on Jacks if/as necessary. Refer to 737-600/700/800/900 AMM 07-11-01 as an accepted procedure. **WARNING:**DO NOT REMOVE THE VALVE BODY UNTIL THE SHOCK STRUT IS FULLY DEFLATED. IF YOU REMOVE THE VALVE BODY WHEN THERE IS PRESSURE, THE PRESSURE CAN BLOW THE VALVE BODY OUT AND CAUSE INJURY TO PERSONS **WARNING:**MAKE SURE THE HYDRAULIC PRESSURE IS BELOW 5000 PSIG WHEN YOU OPERATE THE DOLLY ASSEMBLY AND THE MAIN LANDING GEAR PIVOTS ABOUT THE FORWARD TRUNNION BEARING PIN. IF THE HYDRAULIC PRESSURE IS 5000 PSIG OR HIGHER, A BINDING CONDITION OCCURS. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT. **WARNING:**MAKE SURE THE HYDRAULIC PRESSURE IS BELOW 5000 PSIG WHEN YOU DISCONNECT THE AFT TRUNNION FROM THE AFT TRUNNION BEARING PIN. IF THE HYDRAULIC PRESSURE IS 5000 PSIG OR HIGHER, A BINDING CONDITION OCCURS. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT. **WARNING:**MAKE SURE THE HYDRAULIC PRESSURE IS BELOW 5000 PSIG WHEN YOU DISCONNECT THE FORWARD TRUNNION FROM THE FORWARD TRUNNION BEARING PIN. IF THE HYDRAULIC PRESSURE IS 5000 PSIG OR HIGHER, A BINDING CONDITION OCCURS. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT. **CAUTION:** MAKE SURE THE FORWARD TRUNNION PIN DOES NOT MOVE ON THE PROTECTOR ASSEMBLY (C32034-4) DURING THE REMOVAL OR INSTALLATION OF THE MAIN LANDING GEAR. IF THIS CONDITION OCCURS, IT CAN CAUSE DAMAGE TO THE PIN. THE TOOLS AND EQUIPMENT NECESSARY FOR REMOVING AND INSTALLING THE MAIN LANDING GEAR ARE GIVEN IN 737-600/700/800/900 AMM 32-11-00. (2) Remove the Main Landing Gear (MLG). Refer to 737-600/700/800/900 AMM 32-11-00 as an accepted procedure.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 37 of 55 **BOEING SERVICE BULLETIN 737-32-1402 NOTE:**  Removal of the wheels, tires and brakes, with reference to 737-600/700/800/900 AMM 32-11-00, is recommended, because it will make the MLG easier to handle, but these removals are not necessary to remove or install the MLG. **NOTE:** Operators may use new improved protector tools, P/N C32034-228, which are part of landing gear installation kit, P/N C32034-227, when the MLG is removed. The landing gear installation kit can hold the MLG with the wheels, tires and brakes installed, refer to Boeing Service Letter 737-SL-32-166 for more data. (3) Do PART III - MLG Forward Trunnion Pin - Blending and Repair of the Protective Finish. **PART II - MLG FORWARD TRUNNION PIN - REPLACEMENT WARNING:** USE NITRILE GLOVES FOR SKIN PROTECTION AGAINST COMPOUND C00913 (MASTINOX 6856K). IF MASTINOX GETS ON YOUR SKIN, IMMEDIATELY REMOVE IT WITH WATER. IF THIS MATERIAL GETS IN YOUR EYES, IMMEDIATELY FLUSH YOUR EYES WITH WATER AND GET MEDICAL AID. THIS MATERIAL CONTAINS VERY POISONOUS AND FLAMMABLE AGENTS WHICH CAN CAUSE INJURIES TO PERSONS. 1. Remove the left (MLG) and/or right (MLG) Forward Trunnion Bearing Assembly(ies). Refer to 737-600/700/800/900 AMM 32-11-83 as an accepted procedure. 2. Remove the left (MLG) and/or right (MLG) Forward Trunnion Pin(s). Refer to 737-600/700/800/900 AMM 57-16-01 as an accepted procedure. **NOTE:** The race assembly (161A1187-1) is made of half races (161A1187-2 and 161A1187-3). The half races are matched set and must not be mixed with other race details. Care should be taken during the removal of the race assembly. the half races can easily fall and become damaged. Identify the race details as a matched set using paper tags. **NOTE:** Trunnion Pins that are removed from the airplane can be repaired at the operator's approved maintenance facility. Refer to CMM 57-15-01 as an accepted procedure. 3. Install the replacement left (MLG) and/or right (MLG) Forward Trunnion Pin(s). Refer to 737-600/700/800/900 AMM 57-16-01 as an accepted procedure. **CAUTION:** PROTECT THE TRANSITION RADIUS FINISHES FROM POSSIBLE DAMAGE RESULTING FROM CONTACT WITH THE SEAL RETAINER RING. a. 161A1188-1 Trunnion Pin may replace 161A1188-1 and 161A1188-5 Forward Trunnion Pins. b. 161A1188-3 or 161A1188-9 Trunnion Pins may replace 161A1188-3 or 161A1188-9 Trunnion Pins. c. 161A1188-5 Trunnion Pin replaces only 161A1188-5 Trunnion Pins. d. 161A1188-13 Trunnion Pin may replace 161A1188-1 and 161A1188-5 Trunnion Pins. e. 161A1188-15 Trunnion Pin may replace 161A1188-1 and 161A1188-5 Trunnion Pins. f. 161A1188-17 Trunnion Pin may replace 161A1188-1 Trunnion Pins.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 38 of 55 **BOEING SERVICE BULLETIN 737-32-1402**g. 161A1188-19 Trunnion Pin may replace 161A1188-13 Trunnion Pins. h. 161A1188-21 Trunnion Pin may replace 161A1188-15 Trunnion Pins. i. 161A1188-23 Trunnion Pin may replace 161A1188-5 Trunnion Pins. **NOTE:** Trunnion Pin P/N 161A1188 -17, -19, -21 or -23 is required for the terminating action given in Boeing Service Bulletin 737-32-1448. Refer to Paragraph 2.C.1., Kits/Parts for more data. 4. Install the left (MLG) and/or right (MLG) Forward Trunnion Bearing Assembly(ies). Refer to 737-600/700/800/900 AMM 32-11-83 as an accepted procedure. **NOTE:** Do not force the fuse pin installation if binding occurs. Remove the pins and inspect the bushing inner diameter surfaces for contamination or damage. 5. Do a General Visual Inspection of the transition radius area of the left (MLG) and/or right (MLG) forward trunnion pin. Look for finish damage (scrapes and scratches) in the protective coatings, and repair all damage found. Refer to 737-600/700/800/900 AMM 32-11-00 as an accepted procedure. 6. If not done, close the access panels that follow: a. 551DB, Lower Inboard Fixed Trailing Edge, Lube Actuator & MLG Beam Outboard Attach Pin Access Panel. b. 651DB, Lower Inboard Fixed Trailing Edge, Lube Actuator & MLG Beam Outboard Attach Pin Access Panel. Refer to 737-600/700/800/900 MPD Appendix A or 737-700/800 MPD Appendix A for the panel locations. 7. If not done, install the access panels that follow: a. 551BB, Lower Inboard Fixed Trailing Edge, Gear Adjustment Door, for the Left Landing Gear. b. 551CB, Lower Inboard Fixed Trailing Edge, Gear Access Panel, for the Left Landing Gear. c. 651BB, Lower Inboard Fixed Trailing Edge, Gear Adjustment Door, for the Right Landing Gear. d. 651CB, Lower Inboard Fixed Trailing Edge, Gear Access Panel, for the Right Landing Gear. Refer to 737-600/700/800/900 MPD Appendix A or 737-700/800 MPD Appendix A for the panel locations. 8. If not done, remove the downlock pins in the nose and main landing gear. Refer to 737-600/700/800/900 AMM 32-00-01 as an accepted procedure. 9. Put the airplane back to a serviceable condition.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 39 of 55 **BOEING SERVICE BULLETIN 737-32-1402 PART III - MLG FORWARD TRUNNION PIN - BLENDING AND REPAIR OF THE PROTECTIVE**  **FINISH WARNING:** MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF ALL CONTROL SURFACES BEFORE YOU SUPPLY HYDRAULIC POWER. AILERONS, RUDDERS, ELEVATORS, FLAPS, SLATS, SPOILERS, LANDING GEAR AND THRUST REVERSERS CAN MOVE QUICKLY WHEN YOU SUPPLY HYDRAULIC POWER. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT. **WARNING:**MAKE SURE THE HYDRAULIC PRESSURE IS BELOW 5000 PSIG WHEN YOU CONNECT THE FORWARD TRUNNION TO THE FORWARD TRUNNION BEARING PIN. IF THE HYDRAULIC PRESSURE IS 5000 PSIG OR HIGHER, A BINDING CONDITION OCCURS. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT. **WARNING:**MAKE SURE THE HYDRAULIC PRESSURE IS BELOW 5000 PSIG WHEN YOU OPERATE THE DOLLY ASSEMBLY AND TO LIFT THE AFT TRUNNION INTO ITS POSITION. IF THE HYDRAULIC PRESSURE IS 5000 PSIG OR HIGHER WHEN YOU DO THIS, A BINDING CONDITION OCCURS. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT **CAUTION:** PROTECT THE TRANSITION RADIUS FINISHES FROM DAMAGE BY CONTACT WITH THE SEAL RETAINER RING. 1. Clean areas of damaged finishes and immediate surrounding surfaces with solvent in accordance with FIGURE 3 and FIGURE 4. 2. Abrasive clean the primer in accordance with FIGURE 3 and FIGURE 4. 3. Solvent clean the repair area in accordance with FIGURE 3 and FIGURE 4. 4. Apply Chromate Conversion Coating in accordance with FIGURE 3 and FIGURE 4. 5. Apply primer to the affected area on the Transition Radius in accordance with FIGURE 3 and FIGURE 4. 6. Apply Corrosion Inhibiting Compound (CIC) to the Transition Radius in accordance with FIGURE 3 and FIGURE 4. 7. If the MLG was removed (in PART I): a. Install the MLG. Refer to 737-600/700/800/900 AMM 32-11-00 as an accepted procedure. b. Do a General Visual Inspection of the transition radius area of the left (MLG) and/or right (MLG) forward trunnion pin. Look for finish damage (scrapes and scratches) in the protective coatings, and repair all damage found. Refer to 737-600/700/800/900 AMM 32-11-00 as an accepted procedure. 8. Do PART IV - MLG Trunnion Pin - Lubrication.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 40 of 55 **BOEING SERVICE BULLETIN 737-32-1402 PART IV - MLG FORWARD TRUNNION PIN - LUBRICATION**  **WARNING:**MAKE SURE THE DOWNLOCK PINS ARE INSTALLED ON ALL THE LANDING GEAR. WITHOUT THE DOWNLOCK PINS, THE LANDING GEAR COULD RETRACT AND CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT. **WARNING:**USE GLOVES AND EYE PROTECTION WHEN YOU LUBRICATE WITH THE USE OF A GREASE GUN. LUBRICANT AT HIGH PRESSURE CAN CAUSE INJURY TO PERSONS. 1. Lubricate the Left and Right MLG Forward Trunnion Pins in accordance with FIGURE 5 and FIGURE 6. 2. If not done, close the access panels that follow: a. 551DB, Lower Inboard Fixed Trailing Edge, Lube Actuator & MLG Beam Outboard Attach Pin Access Panel. b. 651DB, Lower Inboard Fixed Trailing Edge, Lube Actuator & MLG Beam Outboard Attach Pin Access Panel. Refer to 737-600/700/800/900 MPD Appendix A or 737-700/800 MPD Appendix A for the panel locations. 3. If not done, install the access panels that follow: a. 551BB, Lower Inboard Fixed Trailing Edge, Gear Adjustment Door, for the Left Landing Gear. b. 551CB, Lower Inboard Fixed Trailing Edge, Gear Access Panel, for the Left Landing Gear. c. 651BB, Lower Inboard Fixed Trailing Edge, Gear Adjustment Door, for the Right Landing Gear. d. 651CB, Lower Inboard Fixed Trailing Edge, Gear Access Panel, for the Right Landing Gear. Refer to 737-600/700/800/900 MPD Appendix A or 737-700/800 MPD Appendix A for the panel locations. 4. If not done, remove the downlock pins in the nose and main landing gear. Refer to 737-600/700/800/900 AMM 32-00-01 as an accepted procedure. 5. Put the airplane back to a serviceable condition.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1: February 07, 2013 41 of 55 **BOEING SERVICE BULLETIN 737-32-1402 FIGURE 1: LEFT MLG FORWARD TRUNNION PIN TRANSITION RADIUS - INSPECTION**  **(SHEET 1 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1 February 07, 2013 42 of 55 **BOEING SERVICE BULLETIN 737-32-1402**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for one side of the airplane.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Surface of excess grease and dirt. Referto SOPM 20-30-03 as an accepted procedure. 1 161A1188-( ) Forward Trunnion Pin Clean 1

Do a detailed inspection of the Transition Radius (cylindrical to spherical transitionarea) for evidence of corrosion, and/or finish damage, and/or scratches in accordance with PART I. 1 161A1188-( ) Forward Trunnion Pin Inspect 2

**FIGURE 1: LEFT MLG FORWARD TRUNNION PIN TRANSITION RADIUS - INSPECTION (SHEET 2 OF 2)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1 February 07, 2013 43 of 55 **BOEING SERVICE BULLETIN 737-32-1402 FIGURE 2: RIGHT MLG FORWARD TRUNNION PIN TRANSITION RADIUS - INSPECTION**  **(SHEET 1 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1 February 07, 2013 44 of 55 **BOEING SERVICE BULLETIN 737-32-1402**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for one side of the airplane.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Surface of excess grease and dirt. Refer to SOPM 20-30-03 as an accepted procedure. 1 161A1188-( ) Forward Trunnion Pin Clean 1

Do a detailed inspection of the Transition Radius (cylindrical to spherical transition area) for evidence of corrosion, and/or finish damage, and/or scratches in accordance with PART I. 1 161A1188-( ) Forward Trunnion Pin Inspect 2

**FIGURE 2: RIGHT MLG FORWARD TRUNNION PIN TRANSITION RADIUS - INSPECTION (SHEET 2 OF 2)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1 February 07, 2013 45 of 55 **BOEING SERVICE BULLETIN 737-32-1402 FIGURE 3: LEFT MLG FORWARD TRUNNION PIN - PROTECTIVE FINISH APPLICATION**  **(SHEET 1 OF 3)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1 February 07, 2013 46 of 55 **BOEING SERVICE BULLETIN 737-32-1402**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for one side of the airplane.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  With solvent where areas of finish damage or bare metal exist. Refer to SOPM 20-30- 03 as an accepted procedure. - - Transition Radius Clean 1

Use light hand pressure to lightly abrade the surface of the primer. Do not abrade the areas where the primer is missing and the cadmium plating is exposed. (a) Transition Radius Abrasive Clean 2

Again with solvent the area that has been abraded in step 2 including the immediate surrounding areas. Refer to SOPM 20-30- 03 as an accepted procedure. - - Transition Radius Clean 3

With cotton swabs or gauze. Apply as littlesolution as possible to prevent contamination of the surrounding areas. Refer toSOPM 20-42-10 as an accepted procedure. (b) up to 1 oz. Ultrachromate 300, or equivalent chromate solution per QQ-P-416 or AMS-QQ-P-416, Type II.Chromate Conversion Coating Apply 4

**FIGURE 3: LEFT MLG FORWARD TRUNNION PIN - PROTECTIVE FINISH APPLICATION (SHEET 2 OF 3)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1 February 07, 2013 47 of 55 **BOEING SERVICE BULLETIN 737-32-1402 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Where the surface protective coating was damaged or disturbed, using a brush. Apply two coats of primer. Refer to SOPM 20-44-04 as an accepted procedure. (c) up to 1 oz. BMS 10-79, Type III Grade A or Grade D Primer Apply(Manually) 5

In a thick layer to the trunnion pin exterior surfaces using a brush. Refer to SOPM 20-41-05 as an accepted procedure. up to 8 oz. BMS 3-26, Type II or BMS 3-38 Corrosion Inhibiting Compound (CIC) Apply(Manually) 6

(a) Use aluminum oxide abrasive pad 320 grit or finer, or a light grade Scotch-Brite type A, very fine. (b) Mask the area with aluminum tape on both sides of the Transition Radius Area, around the perimeter of the Trunnion Pin to prevent debris from going in the spherical or cylindrical area of the Trunnion Pin. (c) Refer to SOPM 20-44-04 as an accepted procedure for curing time and temperature. Allow enough time for drying before handling and grease application.

**FIGURE 3: LEFT MLG FORWARD TRUNNION PIN - PROTECTIVE FINISH APPLICATION (SHEET 3 OF 3)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1 February 07, 2013 48 of 55 **BOEING SERVICE BULLETIN 737-32-1402 FIGURE 4: RIGHT MLG FORWARD TRUNNION PIN - PROTECTIVE FINISH APPLICATION**  **(SHEET 1 OF 3)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1 February 07, 2013 49 of 55 **BOEING SERVICE BULLETIN 737-32-1402**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for one side of the airplane.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  With solvent where areas of finish damage or bare metal exist. Refer to SOPM 20-30- 03 as an accepted procedure. - - Transition Radius Clean 1

Use light hand pressure to lightly abrade the surface of the primer. Do not abrade the areas where the primer is missing and the cadmium plating is exposed. (a) Transition Radius Abrasive Clean 2

Again with solvent the area that has been abraded in step 2 including the immediate surrounding areas. Refer to SOPM 20-30- 03 as an accepted procedure. - - Transition Radius Clean 3

With cotton swabs or gauze. Apply as littlesolution as possible to prevent contamination of the surrounding areas. Refer toSOPM 20-42-10 as an accepted procedure. (b) up to 1 oz. Ultrachromate 300, or equivalent chromate solution per QQ-P-416 or AMS-QQ-P-416, Type II.Chromate Conversion Coating Apply 4

**FIGURE 4: RIGHT MLG FORWARD TRUNNION PIN - PROTECTIVE FINISH APPLICATION (SHEET 2 OF 3)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1 February 07, 2013 50 of 55 **BOEING SERVICE BULLETIN 737-32-1402 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Where the surface protective coating was damaged or disturbed, using a brush. Apply two coats of primer. Refer to SOPM 20-44-04 as an accepted procedure. (c) up to 1 oz. BMS 10-79, Type III Grade A or Grade D Primer Apply(Manually) 5

In a thick layer to the trunnion pin exterior surfaces using a brush. Refer to SOPM 20-41-05 as an accepted procedure. up to 8 oz. BMS 3-26, Type II, or BMS 3-38 Corrosion Inhibiting Compound (CIC) Apply(Manually) 6

(a) Use aluminum oxide abrasive pad 320 grit or finer, or a light grade Scotch-Brite type A, very fine. (b) Mask the area with aluminum tape on both sides of the Transition Radius Area, around the perimeter of the Trunnion Pin to prevent debris from going in the spherical or cylindrical area of the Trunnion Pin. (c) Refer to SOPM 20-44-04 as an accepted procedure for curing time and temperature. Allow enough time for drying before handling and grease application.

**FIGURE 4: RIGHT MLG FORWARD TRUNNION PIN - PROTECTIVE FINISH APPLICATION (SHEET 3 OF 3)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1 February 07, 2013 51 of 55 **BOEING SERVICE BULLETIN 737-32-1402 FIGURE 5: FORWARD TRUNNION PIN LUBRICATION - LEFT MLG**  **(SHEET 1 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1 February 07, 2013 52 of 55 **BOEING SERVICE BULLETIN 737-32-1402**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for one side of the airplane.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  With BMS 3-33 at the times in accordance withParagraph 1.E., Compliance. (a) (b) 1 161A1188-( ) Left Forward Trun- nion Pin Lubricate 1

With BMS 3-33 at the times in accordance withParagraph 1.E., Compliance. (a) 1 115A5240-( ) Left Forward Trun- nion Bearing Housing Lubricate 2

(a) Refer to 737-600/700/800/900 AMM 12-21-11 as an accepted procedure. (b) Lubricate the trunnion pin through the lube fitting on the outer cylinder.

**FIGURE 5: FORWARD TRUNNION PIN LUBRICATION - LEFT MLG (SHEET 2 OF 2)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1 February 07, 2013 53 of 55 **BOEING SERVICE BULLETIN 737-32-1402 FIGURE 6: FORWARD TRUNNION PIN LUBRICATION - RIGHT MLG**  **(SHEET 1 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1 February 07, 2013 54 of 55 **BOEING SERVICE BULLETIN 737-32-1402**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for one side of the airplane.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  With BMS 3-33 at the times in accordance withParagraph 1.E., Compliance. (a) (b) 1 161A1188-( ) Right Forward Trunnion Pin Lubricate 1

With BMS 3-33 at the times in accordance withParagraph 1.E., Compliance. (a) 1 115A5240-( ) Right Forward Trunnion Bearing Housing Lubricate 2

(a) Refer to 737-600/700/800/900 AMM 12-21-11 as an accepted procedure. (b) Lubricate the trunnion pin through the lube fitting on the outer cylinder.

**FIGURE 6: FORWARD TRUNNION PIN LUBRICATION - RIGHT MLG (SHEET 2 OF 2)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 06, 2008 737-32-1402 Revision 1 February 07, 2013 55 of 55 **BOEING SERVICE BULLETIN 737-32-1402**