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.

ECCN: 9E991

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Unpublished Work.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.

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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

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BLANK PAGE
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.

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Terminology 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.

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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

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BLANK PAGE
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.

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Boeing 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.

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BLANK PAGE
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.

GROUP CONFIGURATION DESCRIPTION

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

Variable Number Group

YA146 - YA199 1

YA373 - YA377 1

YA631 1

YA666 - YA667 1

YA973 - YA978 1

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Variable Number Group

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 1

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BOEING SERVICE BULLETIN 737-32-1402
Variable Number Group

YD158 - YD159 1

YD333 - YD334 1

YD412 - YD417 2

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 1

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BOEING SERVICE BULLETIN 737-32-1402
Variable Number Group

YG091 - YG099 2

YG101 - YG104 2

YG111 - YG114 2

YG116 - YG128 2

YG202 - YG205 1

YG211 - YG214 1

YG221 - YG224 1

YG251 - YG252 1

YG507 - YG511 1

YG701 2

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 1

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BOEING SERVICE BULLETIN 737-32-1402
Variable Number Group

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 1

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BOEING SERVICE BULLETIN 737-32-1402
Variable Number Group

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 1

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BOEING SERVICE BULLETIN 737-32-1402
Variable Number Group

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 1

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Variable Number Group

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 1

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Variable Number Group

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 1

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.

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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

Model Zone

737-600, 737-700, 737-700C, 551, 661, 734, 744

737-800, 737-900

Group 2:

Affected Maintenance Zones

Model Zone

737-700, 737-700C, 737-800 551, 661, 734, 744

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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)

Condition Action

Within 30 days 30 days (a)

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 Forward

Trunnion Pin - Lubrication"

All airplanes that were included in the effectivity of

the Original Issue of this

service bulletin.

Within 30 days 30 days (a)

from the date of

Revision 1 of

this service bulletin

Lubricate the MLG For- -

ward Trunnion Pin in accordance with Accomplishment Instruction 3.B.,

PART IV, "MLG Forward

Trunnion 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 since

the date of issuance of the

original standard airworthiness certificate

or date of issuance of the

original export

certificate of airworthiness.

Detailed Inspection of the

Transition Radius location

(In-Situ) in accordance

with Accomplishment Instruction, paragraph 3.B.,

PART I, "MLG Forward

Trunnion Pin - Inspection

of the Transition Radius

with the MLG Not Removed (in-situ)".

All airplanes that were included in the effectivity of

the Original Issue of this

service bulletin.

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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)

Condition Action

Within 6 months -

from the date of

Revision 1 of

this service bulletin

Within 60

months since

the date of issuance of the

original standard airworthiness certificate

or date of issuance of the

original export

certificate of airworthiness

Detailed Inspection of the

Transition Radius location

(In-Situ) in accordance

with Accomplishment Instruction, paragraph 3.B.,

PART I, "MLG Forward

Trunnion Pin - Inspection

of the Transition Radius

with 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 in

the Transition Radius location, and no corrosion, no

pitting, and no base metal

scratches. And

Within 24 24 Months (b)

Months after the

finish damage is

repaired

Detailed Inspection of the -

Transition Radius location

(In-Situ) in accordance

with Accomplishment Instruction, paragraph 3.B.,

PART I, "MLG Forward

Trunnion Pin - Inspection

of the Transition Radius

with the MLG Not Removed (in-situ)".

Before further -

flight (c)

Do Accomplishment In- -

struction, paragraph 3.B.,

PART II, "MLG Forward

Trunnion Pin - Replacement".

Airplanes with corrosion, or

pitting, or base metal

scratches in the base material, found at the Transition

Radius location.

Before further -

flight.

Do Accomplishment In- -

struction paragraph 3.B.,

PART IV, "MLG Forward

Trunnion Pin - Lubrication".

Airplanes with no corrosion, no pitting , no base

metal scratches, and no

finish damage at the Transition Radius location.

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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)

Condition Action

(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)

Condition Action

Within 30 days 30 days (a)

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 Forward

Trunnion Pin - Lubrication"

All airplanes that were included in the effectivity of

the Original Issue of this

service bulletin.

Within 30 days 30 days (a)

from the date of

Revision 1 of

this service bulletin

Lubricate the MLG For- -

ward Trunnion Pin in accordance with Accomplishment Instruction 3.B.,

PART IV, "MLG Forward

Trunnion 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 since

the date of issuance of the

original standard airworthiness certificate

or date of issuance of the

original export

certificate of airworthiness.

Detailed Inspection of the

Transition Radius location

(In-Situ) in accordance

with Accomplishment Instruction, paragraph 3.B.,

PART I, "MLG Forward

Trunnion Pin - Inspection

of the Transition Radius

with the MLG Not Removed (in-situ)".

All airplanes that were included in the effectivity of

the Original Issue of this

service bulletin.

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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)

Condition Action

Within 6 months -

from the date of

Revision 1 of

this service bulletin

Within 60

months since

the date of issuance of the

original standard airworthiness certificate

or date of issuance of the

original export

certificate of airworthiness

Detailed Inspection of the

Transition Radius location

(In-Situ) in accordance

with Accomplishment Instruction, paragraph 3.B.,

PART I, "MLG Forward

Trunnion Pin - Inspection

of the Transition Radius

with 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 in

the Transition Radius location and no corrosion, no

pitting, and no base metal

scratches And

Within 24 24 Months (b)

Months after the

finish damage is

repaired.

Detailed Inspection of the

Transition Radius location

(In-Situ) in accordance

with Accomplishment Instruction, paragraph 3.B.,

PART I, "MLG Forward

Trunnion Pin - Inspection

of the Transition Radius

with the MLG Not Removed (in-situ)".

Before further -

flight (c)

Do Accomplishment In- -

struction, paragraph 3.B.,

PART II, "MLG Forward

Trunnion Pin - Replacement".

Airplanes with corrosion, or

pitting, or base metal

scratches in the base material, found at the Transition

Radius location.

Before further -

flight.

Do Accomplishment In- -

struction paragraph 3.B.,

PART IV, "MLG Forward

Trunnion Pin - Lubrication".

Airplanes with no corrosion, no pitting , no base

metal scratches, and no

finish damage at the Transition Radius location.

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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)

Condition Action

(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.

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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)

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 2 2.00 (b) 1.00 (b)

FIGURE 1 1 2.00 2.00

FIGURE 2 1 2.00 2.00

Close Access 2 2.00 (b) 1.00 (b)

TOTAL FOR EACH AIRPLANE FOR 8.00 (a) (b) 6.00 (a) (b)

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

Number of Per- Task-Hours Elapsed Hours

sons

Task

Remove Trunnion 4 36.00 9.00

Bearing Assy

Remove FWD 2 2.00 1.00

Trunnion Pins

Install FWD Trun- 2 2.00 1.00

nion Pins

Install Trunnion 4 36.00 9.00

Bearing Assy

TOTAL FOR EACH AIRPLANE FOR 76.00 20.00

PART II

TABLE 3: PART III - MLG FORWARD TRUNNION PIN - BLENDING AND REPAIR OF THE

PROTECTIVE FINISH

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 3 (a) (a) (a)

FIGURE 4 (a) (a) (a)

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BOEING SERVICE BULLETIN 737-32-1402
TABLE 3: PART III - MLG FORWARD TRUNNION PIN - BLENDING AND REPAIR OF THE

PROTECTIVE FINISH

Number of Per- Task-Hours Elapsed Hours

sons

Task

TOTAL FOR EACH AIRPLANE FOR (a) (a)

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

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 5 1 0.25 0.25

FIGURE 6 1 0.25 0.25

TOTAL FOR EACH AIRPLANE FOR 0.50 0.50

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.

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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:

Publication Chapter-Section

737 Illustrated Parts Catalog 32-11

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.

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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 Service Bulletin

(US Dollars)

ROLT as

of the Revision 01

date of

this Service Bulletin (Calendar

Days)

Part Number Name Date QTY

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

161A1188-3 (b) (g) Forward Trunnion Pin - 1 - $4,271.00

161A1188-5 (c) (g) Forward Trunnion Pin - 1 - $4,271.00

161A1188-9 (d) (g) Forward Trunnion Pin - 1 - $4,271.00

161A1188-13 (e) (g) Forward Trunnion Pin - 1 - $12,084.00

161A1188-15 (f) (g) Forward Trunnion Pin - 1 - $12,084.00

161A1188-17 (g) (h) (l) Forward Trunnion Pin - 1 - $12,084.00

161A1188-19 (g) (i) (l) Forward Trunnion Pin - 1 - $12,084.00

161A1188-21 (g) (j) (l) Forward Trunnion Pin - 1 - $12,084.00

161A1188-23 (g) (k) (l) Forward Trunnion Pin - 1 - $12,084.00

(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.

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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 Service Bulletin

(US Dollars)

ROLT as

of the Revision 01

date of

this Service Bulletin (Calendar

Days)

Part Number Name Date QTY

(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.

New Part Number QTY Name Existing Part Number Notes

161A1188-1 or (a) (f) (g) (h)

161A1188-5 (optional)

161A1188-1 1 Forward Trunnion Pin

161A1188-3 or (b) (f) (g) (h)

161A1188-9 (optional)

161A1188-3 or 1 Forward Trunnion Pin

161A1188-9 (optional)

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New Part Number QTY Name Existing Part Number Notes

161A1188-5 or (c) (f) (g)

161A1188-23 (optional)

161A1188-5 1 Forward Trunnion Pin

161A1188-1 or (d) (f)

161A1188-5 (optional)

161A1188-13 1 Forward Trunnion Pin

161A1188-1 or (e) (f)

161A1188-5 (optional)

161A1188-15 1 Forward Trunnion Pin

161A1188-17 1 Forward Trunnion Pin 161A1188-1 (f) (h) (j) (n)

161A1188-19 1 Forward Trunnion Pin 161A1188-13 (f) (i) (k) (n)

161A1188-21 1 Forward Trunnion Pin 161A1188-15 (f) (i) (l) (n)

161A1188-23 1 Forward Trunnion Pin 161A1188-5 (f) (i) (m) (n)

(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:

Part Number / Specifi- QTY Name Notes

cation

BMS 3-38 or BMS 3-26, 16 oz. Corrosion Inhibiting Compound (a)

Type II

BMS 3-33 32oz. Grease - Aircraft General Purpose (a)

Urethane Compatible Corrosion Re- (a)

sistant Primer

BMS 10-79 Type III 4 oz.

Grade A or Grade D

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Part Number / Specifi- QTY Name Notes

cation

MS20995NC32 10 feet Lockwire

BMS 11-7 1 pint Cleaning Solvent (a)

Scotch-Brite, Type A, very fine or (b)

equivalent material

Abrasive 3 feet

Aluminum Oxide Abrasive Pad, 320 (c)

grit or finer or equivalent material

As NecessaryAbrasive

Ultrachromate 300, or 4 oz. Chromate Conversion Coating (d)

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., 10th

Ave. 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.

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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.

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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.

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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.

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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.

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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.

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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.

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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.

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41 of 55

BOEING SERVICE BULLETIN 737-32-1402
FIGURE 1: LEFT MLG FORWARD TRUNNION PIN TRANSITION RADIUS - INSPECTION

(SHEET 1 OF 2)

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Surface of excess grease and dirt. Refer

to SOPM 20-30-03 as an accepted procedure.

Forward 161A1188-( ) 1

Trunnion

Pin

1 Clean

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.

Forward 161A1188-( ) 1

Trunnion

Pin

2 Inspect

FIGURE 1: LEFT MLG FORWARD TRUNNION PIN TRANSITION RADIUS - INSPECTION

(SHEET 2 OF 2)

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43 of 55

BOEING SERVICE BULLETIN 737-32-1402
FIGURE 2: RIGHT MLG FORWARD TRUNNION PIN TRANSITION RADIUS - INSPECTION

(SHEET 1 OF 2)

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Original Issue: August 06, 2008

Revision 1 February 07, 2013 737-32-1402

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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Surface of excess grease and dirt. Refer to

SOPM 20-30-03 as an accepted procedure.

Forward 161A1188-( ) 1

Trunnion

Pin

1 Clean

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.

Forward 161A1188-( ) 1

Trunnion

Pin

2 Inspect

FIGURE 2: RIGHT MLG FORWARD TRUNNION PIN TRANSITION RADIUS - INSPECTION

(SHEET 2 OF 2)

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45 of 55

BOEING SERVICE BULLETIN 737-32-1402
FIGURE 3: LEFT MLG FORWARD TRUNNION PIN - PROTECTIVE FINISH APPLICATION

(SHEET 1 OF 3)

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Revision 1 February 07, 2013 737-32-1402

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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

With solvent where areas of finish damage

or bare metal exist. Refer to SOPM 20-30-

03 as an accepted procedure.

1 Clean Transition Radius - -

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)

Abrasive Transition Radius

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.

3 Clean Transition Radius - -

With cotton swabs or gauze. Apply as little

solution as possible to prevent contamination of the surrounding areas. Refer to

SOPM 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 Coating4 Apply

FIGURE 3: LEFT MLG FORWARD TRUNNION PIN - PROTECTIVE FINISH APPLICATION

(SHEET 2 OF 3)

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47 of 55

BOEING SERVICE BULLETIN 737-32-1402
STEP TASK NAME IDENTIFICATION QTY MORE DATA

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

Apply Primer

(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)

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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

Revision 1 February 07, 2013 737-32-1402

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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

With solvent where areas of finish damage

or bare metal exist. Refer to SOPM 20-30-

03 as an accepted procedure.

1 Clean Transition Radius - -

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)

Abrasive Transition Radius

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.

3 Clean Transition Radius - -

With cotton swabs or gauze. Apply as little

solution as possible to prevent contamination of the surrounding areas. Refer to

SOPM 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 Coating4 Apply

FIGURE 4: RIGHT MLG FORWARD TRUNNION PIN - PROTECTIVE FINISH APPLICATION

(SHEET 2 OF 3)

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Original Issue: August 06, 2008

Revision 1 February 07, 2013 737-32-1402

50 of 55

BOEING SERVICE BULLETIN 737-32-1402
STEP TASK NAME IDENTIFICATION QTY MORE DATA

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

Apply Primer

(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)

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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

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Revision 1 February 07, 2013 737-32-1402

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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

With BMS 3-33 at the

times in accordance with

Paragraph 1.E., Compliance. (a) (b)

Left Forward Trun- 161A1188-( ) 1

nion Pin

1 Lubricate

With BMS 3-33 at the

times in accordance with

Paragraph 1.E., Compliance. (a)

Left Forward Trun- 115A5240-( ) 1

nion Bearing

Housing

2 Lubricate

(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)

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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

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Work - See page 1 for details.

Original Issue: August 06, 2008

Revision 1 February 07, 2013 737-32-1402

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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

With BMS 3-33 at the

times in accordance with

Paragraph 1.E., Compliance. (a) (b)

Right Forward 161A1188-( ) 1

Trunnion Pin

1 Lubricate

With BMS 3-33 at the

times in accordance with

Paragraph 1.E., Compliance. (a)

Right Forward 115A5240-( ) 1

Trunnion Bearing

Housing

2 Lubricate

(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

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55 of 55

BOEING SERVICE BULLETIN 737-32-1402