### Commercial **Airplanes** 

# 737 Service Bulletin **Number: 737-53-1244** Original Issue: April 17, 2003 Revision 5: July 27, 2011 ATA System: 5321 **SUBJECT:** FUSELAGE - Passenger Cabin Floors - Station 520 to 540 - Pivot Link Assembly Repair/Replace Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 730-774). 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## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2003 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work. This document includes proprietary information owned by The Boeing Company and/or one or more third parties. Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124. 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, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 1 of 74 3.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 2 of 74 **BOEING SERVICE BULLETIN 737-53-1244**

BLANK PAGE**Table of Contents** Revision Transmittal Sheet............................................ 5 Summary...................................................... 7 1. PLANNING INFORMATION........................................ 9 A. Effectivity................................................ 9 1. Airplanes............................................. 9 2. Spares Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 F. Approval. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 G. Manpower. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 1. Existing Data:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 2. Data supplied with this Service Bulletin:. . . . . . . . . . . . . . . . . . . . . . . . . . . 22 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 23 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 23 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 C. Parts Necessary For Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 1. Kits/Parts:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 2. Parts and Materials Supplied by the Operator:. . . . . . . . . . . . . . . . . . . . . . . . 30 3. Parts Modified and Reidentified:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 4. Parts Removed and Not Replaced:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 32 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34 FIGURE 1: CENTERLINE FASTENER INSTALLATION - GROUP 2 AND 4 [Group 2, 4]. . . . . . . . 38 FIGURE 2: CENTERLINE FASTENER INSTALLATION - GROUP 3 AND 5 [Group 3, 5]. . . . . . . . 41 FIGURE 3: BREAK PANEL, SEAT TRACK AND PIVOT LINK REMOVAL - GROUP 1, 2 AND 4 [Group 1-2, 4] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43 FIGURE 4: PIVOT LINK INSTALLATION - GROUP 1, 2 AND 4 [Group 1-2, 4]. . . . . . . . . . . . . 46 FIGURE 5: BREAK PANEL INSTALLATION - GROUP 1, 2 AND 4 [Group 1-2, 4]. . . . . . . . . . . 50 FIGURE 6: DRILL HOLES FOR FLOOR PANEL FASTENERS - GROUP 1, 2 AND 4 [Group 1-2, 4] . 54 FIGURE 7: BREAK PANEL, SEAT TRACK AND PIVOT LINK REMOVAL - GROUP 3 AND 5 [Group 3, 5] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 56 FIGURE 8: PIVOT LINK INSTALLATION - GROUP 3 AND 5 [Group 3, 5]. . . . . . . . . . . . . . . . 59 FIGURE 9: BREAK PANEL INSTALLATION - GROUP 3 AND 5 [Group 3, 5]. . . . . . . . . . . . . . 63

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 3 of 74 **BOEING SERVICE BULLETIN 737-53-1244**FIGURE 10: DRILL HOLES FOR FLOOR PANEL FASTENERS - GROUP 3 AND 5 [Group 3, 5]. . . . 67 FIGURE 11: BUSHING STRAP REWORK - GROUP 1, 2, 3, 4 AND 5 [Group 1-5]. . . . . . . . . . . . 69 FIGURE 12: PIVOT LINK AND BUSHING PLATE MODIFICATION - GROUP 1, 2, 3, 4 AND 5 [Group 1-5] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 71

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 4 of 74 **BOEING SERVICE BULLETIN 737-53-1244**

### Commercial **Airplanes** 

# 737 Service Bulletin **Revision Transmittal Sheet Number: 737-53-1244**  Original Issue: April 17, 2003 Revision 5: July 27, 2011 ATA System: 5321 **SUBJECT:** FUSELAGE - Passenger Cabin Floors - Station 520 to 540 - Pivot Link Assembly Repair/Replace This revision includes all pages of the service bulletin. **COMPLIANCE INFORMATION RELATED TO THIS REVISION** No more work is necessary on the airplane(s) changed in accordance with the original issue, Revision 1, Revision 2 or Revision 3 of this service bulletin. No airplanes were removed or added. **REASON FOR REVISION** Revision 4 of the service bulletin 737-53-1244 was removed from MyBoeingFleet.com and must not be used. Operators are advised to destroy existing copies of Revision 4. After release of Service bulletin 737-53-1244 Revision 4, it was discovered that an FAA required change to the service bulletin was not incorporated. The FAA required the removal of references to Boeing drawing 65-88700 from the service bulletin as a condition of approval. The revisions contained in Revision 4 are retained in Revision 5. This revision 5 is sent to change the compliance time for replacement of the pivot link. These sections were changed: 1. Paragraph 1.E., Compliance, Table 1: Compliance time to install the new pivot link is changed. 2. Paragraph 1.K.2., Damage Tolerance Based Structural Inspections section is added. 3. Paragraph 3.A., General Information: Notes are updated. 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** April 17, 2003 Original Issue:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 5 of 74May 29, 2003 Revision 1: March 15, 2007 Revision 2: December 04, 2008 Revision 3: April 06, 2011 Revision 4: July 27, 2011 Revision 5:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 6 of 74 **BOEING SERVICE BULLETIN 737-53-1244**

### Commercial **Airplanes** 

# 737 Service Bulletin **Summary Number: 737-53-1244**  Original Issue: April 17, 2003 Revision 5: July 27, 2011 ATA System: 5321 **SUBJECT:** FUSELAGE - Passenger Cabin Floors - Station 520 to 540 - Pivot Link Assembly Repair/Replace **CONCURRENT REQUIREMENTS** None. **BACKGROUND** Boeing Service Related Problem (SRP) 737-SRP-53-0176 is related to this service bulletin. A review at Boeing of engineering requirements and factory inspections showed that sufficient gap may not have been allowed at the BS 520 pivot link assembly. The gap is required to prevent fatigue cracking in BS 520 floor beam area. Testing of a portion of the seat track revealed a structural anomaly related to the seat track crown attachment to the pivot link assembly. The noncompliance is to FAR/JAR 25.561 emergency landing conditions, specially the 9G forward loading. The changes shown in this service bulletin will prevent floor beam cracks and restore the 9G forward loading condition in the areas around Body Station 520. Installation of the new one piece pivot link will reduce the possibility of gap between the floor beam and the pivot link. **ACTION (PRR 38489)** Check the airplane maintenance records to see if the passenger seats have been moved. If the operator has moved or changed the pivot link, then refer to Paragraph 1.E. Compliance for possible changes in compliance action and time limit. Depending on passenger seat configuration either reposition the seats, install centerline fasteners in the seat track or replace the pivot link with the new one piece pivot link. If the airplane has been or will be modified for installation of something other than a seat, contact Boeing for assistance. **EFFECTIVITY** 737-600 / -700 / -700C / -800 / -900 airplanes line numbers 1 through 1221. **COMPLIANCE** The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 7 of 74Refer to Paragraph 1.E., Compliance. **INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are available for airplanes in warranty as of January 18, 2002. 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 8 of 74 **BOEING SERVICE BULLETIN 737-53-1244**

### Commercial **Airplanes** 

# 737 Service Bulletin **Number: 737-53-1244** Original Issue: April 17, 2003 Revision 5: July 27, 2011 ATA System: 5321 **SUBJECT:** FUSELAGE - Passenger Cabin Floors - Station 520 to 540 - Pivot Link Assembly Repair/Replace **1. PLANNING INFORMATION A. Effectivity**  1. Airplanes This service bulletin is for the airplanes shown below. An equivalent change is on subsequent production airplanes. Refer to PRR 38489 for data about this change. Refer to Service Bulletin Index Document D6-19567 Part 3 for Airplane Variable Number, Line Number, and Serial Number data.
**DESCRIPTION CONFIGURATION**  **GROUP** Passenger airplanes with four pivot links. Airplanes delivered with two studs have the forward stud located at BS 534.95, BS 535.95 or BS 536.95. Airplanes delivered with three studs have the forward stud located at BS 534.95 and BS 535.95. - 1

Passenger airplanes with four pivot links. Airplanes delivered with two studs or three studs have the forward stud located between BS 521.95 and BS 533.95. - 2

737-700 Convertible airplanes with five pivot links. Airplanes delivered with either two studs or three studs have the forward stud located between BS 521.95 and BS 533.95. - 3

Passenger airplanes with four pivot links. Airplanes delivered with two studs have the forward stud located aft of BS 536.95. Airplanes with three studs have the forward stud located aft of BS 535.95. - 4

737-700 Convertible airplanes with five pivot links. Airplanes delivered with two studs have the forward stud located aft of BS 536.95. Airplanes with three studs have the forward stud located aft of BS 535.95. - 5

Airplane Models:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 9 of 74737-600, 737-700, 737-700C, 737-800, 737-900 **Group Variable Number**  2 YA001 - YA099 2 YA101 - YA118 4 YA119 - YA124 4 YA201 - YA211 4 YA221 4 YA231 - YA242 4 YA251 - YA256 2 YA271 - YA272 4 YA291 4 YA301 - YA302 4 YA311 - YA314 4 YA321 - YA322 2 YA323 4 YA336 - YA345 4 YA351 4 YA356 - YA357 4 YA366 - YA367 4 YA501 - YA536 4 YA541 - YA552 4 YA571 - YA578 4 YA601 - YA608 2 YA609 - YA610 4 YA611 - YA615 4 YA621 - YA622 4 YA626 1 YA627 - YA629 2 YA635 4 YA636 4 YA645 - YA648 4 YA656 - YA659 4 YA671 - YA672 4 YA681 - YA691

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 10 of 74 **BOEING SERVICE BULLETIN 737-53-1244 Group**  **Variable Number** 4 YA701 - YA706 4 YA721 - YA722 1 YA731 - YA734 4 YA751 - YA756 2 YA801 - YA803 2 YA809 2 YA811 - YA814 4 YA831 - YA834 4 YA841 - YA856 2 YA881 - YA882 4 YA891 - YA892 4 YA961 - YA969 4 YB001 - YB006 1 YB101 - YB118 4 YB151 - YB153 4 YB161 - YB162 4 YB171 - YB172 4 YB181 - YB183 4 YB201 - YB207 4 YB271 4 YB276 4 YB301 - YB309 2 YB501 - YB502 4 YB521 4 YB551 4 YB561 - YB562 4 YC001 - YC030 4 YC051 - YC082 4 YC091 - YC094 4 YC101 - YC104 4 YC111 - YC113 1 YC121 4 YC126 - YC127

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 11 of 74 **BOEING SERVICE BULLETIN 737-53-1244 Group**  **Variable Number** 4 YC136 - YC141 4 YC146 - YC147 4 YC151 - YC156 4 YC166 - YC169 4 YC171 4 YC176 - YC178 4 YC301 - YC304 4 YC321 - YC383 4 YC391 - YC392 4 YC396 4 YC401 - YC417 4 YC421 - YC422 2 YC426 4 YC427 - YC428 4 YC436 - YC437 4 YC441 - YC448 4 YC451 - YC455 4 YC459 4 YC461 - YC467 4 YC471 - YC493 4 YC501 - YC515 1 YC516 - YC526 1 YC571 - YC583 4 YC587 - YC589 4 YC591 - YC593 4 YC601 - YC655 2 YC681 - YC696 4 YC701 - YC707 2 YC708 - YC715 2 YC720 - YC725 2 YC727 4 YC728 - YC740 4 YC751 - YC752

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 12 of 74 **BOEING SERVICE BULLETIN 737-53-1244 Group**  **Variable Number** 4 YC761 - YC770 4 YC781 - YC793 4 YC801 - YC836 2 YC837 - YC880 4 YC881 - YC892 4 YC901 - YC907 4 YC921 4 YC931 - YC932 4 YC941 - YC950 4 YC971 - YC978 4 YC981 - YC983 4 YD001 - YD006 1 YD021 - YD022 2 YD023 - YD024 4 YD025 4 YD041 - YD055 2 YD081 - YD084 4 YD101 - YD107 4 YD121 - YD126 4 YD151 - YD154 4 YD171 - YD172 4 YD201 - YD203 4 YD206 - YD208 1 YD216 4 YD251 - YD254 4 YD256 4 YD301 - YD330 4 YD391 4 YD401 - YD410 4 YD481 - YD482 1 YD501 - YD507 4 YD531 - YD534 4 YD541 - YD547

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 13 of 74 **BOEING SERVICE BULLETIN 737-53-1244 Group**  **Variable Number** 4 YD601 - YD612 4 YE001 - YE020 1 YE051 4 YE101 - YE109 4 YE151 - YE157 2 YE171 - YE172 2 YE201 - YE203 4 YE301 - YE305 4 YG001 - YG044 4 YG061 - YG064 4 YG066 - YG087 3 YG501 - YG504 5 YG505 - YG506 5 YG601 - YG602 4 YJ471 - YJ477 4 YJ501 - YJ517 4 YJ631 - YJ632 4 YJ671 - YJ673 4 YJ871 2. Spares Affected Examine your spares supply for the parts or components identified in Paragraph 2.C., Parts Necessary for Each Airplane. If any parts or components are found, refer to Paragraph 2.C. for the recommended use. **B. Concurrent Requirements** None. **C. Reason** Boeing Service Related Problem (SRP) 737-SRP-53-0176 is related to this service bulletin. During review of the pivot link installation between BS 520 and BS 540 a loading test of the seat track was performed. Testing of a portion of the seat track revealed a structural anomaly related to the seat track crown attachment to the pivot link assembly. The noncompliance is to FAR/JAR 25.561 emergency landing conditions, specially the 9G forward loading.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 14 of 74 **BOEING SERVICE BULLETIN 737-53-1244**This issue affects passenger seats that are attached to seat tracks at RBL 24.75, RBL 45.5, LBL 24.75 LBL 45.5 or BL 0.0 between BS 521.95 and BS 536.95 for passenger seats with aft legs with two studs and between BS 521.95 and BS 535.95 for passenger seats with aft legs with three studs. Contact Boeing if there are other payload items (i.e. galleys, lavatories, cargo pallets, custom interior furnishing etc.) other than passenger seats attached to the seat track. Current pivot link design has two parts, a pivot link with an attached seat track. The design has been changed so the seat track and pivot link are one piece. Also the new pivot link attaches differently at BS 537. At BS 537 the pivot link is installed using two bushing straps. The two bushing straps make it easier to install and accurately align the pivot link with the adjacent structure. Revision 1 was released for the following reasons: — To add Figure 11 which allows the rework of Bushing Strap 143A5595-23 if needed for seat track alignment. — To change the installation of BACB30US4K29D Bolt so the manufactured head is against the 143A5595-23 Bushing Strap in Figures 4 and 8. — To add notes to alodine and prime drilled and match drilled holes in Figures 6 and 10 which drill holes for the floor panel fasteners. — To remove dimensions C and D to center the plates on the break panels in Figure 5 between LBL 25.75 and RBL 24.75. The position of the plate is set by the joggle down in the plate and the break panel. Revision 2 was sent to add instructions to modify the pivot link assembly and to inspect for correct vertical alignment between the pivot link assembly and the section 44 seat track on installation. Changes to Revision 2 of this service bulletin include: - — Manpower - Group 1, 2 and 4 pivot link installation table has been revised. — Material Information - Add new top kits with a new pivot link assembly and new bushing straps. — Special tooling - A new special tool has been added to accomplish the installation of the pivot links. — Special tooling - The special tool required to install the new pivot links will be supplied as a no charge loan to operators of in-warranty airplanes. — Accomplishment Instructions - Changed to add reference to modify pivot links and bushing straps. — Figure 4 - Changed to include an inspection step. — Figure 8 - Changed to include an inspection step. — Figure 12 - Added to modify the pivot link and bushing straps. Revision 3 was sent to change the special tool required to install the pivot links. The special tool listed in Revision 2 of this service bulletin is no longer available for loan. Changes to the service bulletin include: — Paragraph 1.D., Description: Maintenance zone data is added. — Paragraph 1.J., References: All 737-600,-700,-700CONV,-700IGW,-800,-900 SRM 53-40-08 references are updated to 737-600,-700,-700CONV,-700IGW,-800,-900 SRM 51-40-08. — Paragraph 2.C.2., Parts and Materials Supplied by the Operator: Blind fastener part number is updated. — Paragraph 2.E., Special Tooling - Price and Availability: Tool data is updated. — Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin: Tool data is updated.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 15 of 74 **BOEING SERVICE BULLETIN 737-53-1244**— Paragraph 3.B., Work Instructions: Tool number for locating jig is updated in PART IV. — Figures 1 and 2, Centerline Fastener Installation: Blind fastener part number is updated. All 737-600,-700,-700CONV,-700IGW,-800,-900 SRM 53-40-08 references are updated to 737-600,-700,-700CONV,-700IGW,-800,-900 SRM 51-40-08. — Figures 4 and 8: Tool number for locating jig is updated. Revision 4 of the service bulletin 737-53-1244 was removed from MyBoeingFleet.com and must not be used. Operators are advised to destroy existing copies of Revision 4. Revision 5 is sent to change the compliance time for installation of the new pivot link in Paragraph 1.E., Compliance, Table 1. **D. Description** If the operator moved the seats or changed the pivot link then refer to Paragraph 1.E. Compliance for possible changes in compliance action and time limit. **NOTE:** The groups below are based on airplane configurations with passenger seats with two or three studs on the aft leg of the seat. If none of the two or three stud configurations below apply to the airplane then contact Boeing. Group 1 airplanes are passenger airplanes with four pivot links — Group 1 airplanes with two studs on the aft leg of the seat have the forward stud of the aft leg of the seat located at BS 534.95, BS 535.95 or BS 536.95 on the seat track. — Group 1 airplanes with three studs on the aft leg of the seat have the forward stud of the aft leg of the seat located at BS 534.95 and BS 535.95 on the seat track. Group 2 airplanes are passenger airplanes with four pivot links — Group 2 airplanes with either two studs or three studs on the aft leg of the seat have the forward stud of the aft leg of the seat located between BS 521.95 to BS 533.95 on the seat track. Group 3 airplanes are 737-700 Convertibles with five pivot links — Group 3 airplanes with either two studs or three studs on the aft leg of the seat have the forward stud of the aft leg of the seat located between BS 521.95 to BS 533.95 on the seat track. Group 4 airplanes are passenger airplanes with four pivot links — Group 4 airplanes are airplanes delivered in compliance to FAR/JAR 25.561, 9G emergency landing conditions. — Group 4 airplanes with two studs on the aft leg of the seat have the forward stud of the aft leg of the seat located aft of BS 536.95 on the seat track. — Group 4 airplanes with three studs on the aft leg of the seat have the forward stud of the aft leg of the seat located aft of BS 535.95 on the seat track. Group 5 airplanes are 737-700 Convertible airplanes with five pivot links.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 16 of 74 **BOEING SERVICE BULLETIN 737-53-1244**— Group 5 airplanes are airplanes delivered in compliance to FAR/JAR 25.561, 9G emergency landing conditions. — Group 5 airplanes with two studs on the aft leg of the seat have the forward stud of the aft leg of the seat located aft 536.95 on the seat track. — Group 5 airplanes with three studs on the aft leg of the seat have the forward stud of the aft leg of the seat located aft BS 535.95 on the seat track. On all airplanes check the airplane maintenance records to see if the passenger seats have been moved. Check to see if the forward stud on the aft leg is between stations 521.95 and 536.95 or if the pivot link has been changed after airplane delivery. If the operator moved the seats or changed the pivot link then refer to Paragraph 1.E. Compliance for possible changes in compliance action and time limit. On Group 1 airplanes that did not have seats moved, install one piece pivot links or as an option move the seats. Gain access for pivot link replacement by removing the passenger seats, carpets and floor panels in the area between body stations 520 and 540. Remove the seat tracks, break panels and pivot links. Align the new pivot link with the seat tracks and then install the pivot link. Align and install the break panel detail and plates. Drill holes in the pivot links and break panels for floor panel fasteners. See Paragraph 1.E Compliance for time limits and terminating action. On Group 2 and 3 airplanes that did not have seats moved, install one piece pivot link or as an option either install centerline fasteners in the seat tracks or move the seats. If centerline fasteners are to be installed gain access by removing the seat track covers, carpets, seats and floor panels between body stations 520 and 540. If blind fasteners are used there is no need to remove the floor panels. If solid fasteners are used then the floor panels must be removed. See Paragraph 1.E Compliance for time limits and terminating action. Group 4 and 5 airplanes that did not have seats moved, install the one piece pivot link or as an option install centerline fasteners in the seat tracks. Gain access for pivot link replacement by removing the passenger seats, carpets and floor panels in the area between body stations 520 and 540. Remove the seat tracks, break panels and pivot links. Align the new pivot link with the seat tracks and then install the pivot link. Align and install the break panel detail and plates. Drill holes in the pivot links and break panels for floor panel fasteners. Group 4 and 5 airplanes, if centerline fasteners are installed then gain access by removing the seat track covers, carpets, seats and floor panels between body stations 520 and 540. If blind fasteners are used there is no need to remove the floor panels. If solid fasteners are used then the floor panels must be removed. See Paragraph 1.E Compliance for time limits and terminating action. Installation of the one piece pivot link will make all seating configurations compliant with FAR/JAR 25.561 emergency landing conditions. Revision 1 - No more work is necessary on airplanes changed as shown in the initial release of this service bulletin. If the airplane has been or will be modified for installation of something other than a seat, contact Boeing for assistance. Revision 2 - No more work is necessary on airplanes changed as shown in the initial release or Revision 1 of this service bulletin. Revision 3 - No more work is necessary on airplanes changed as shown in the original issue, Revision 1 or Revision 2 of this service bulletin.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 17 of 74 **BOEING SERVICE BULLETIN 737-53-1244**Revision 4 of the service bulletin 737-53-1244 was removed from MyBoeingFleet.com and must not be used. Operators are advised to destroy existing copies of Revision 4. Revision 5 - No more work is necessary on airplanes changed in accordance with the original issue, Revision 1, Revision 2 or Revision 3 of this service bulletin. The work in this service bulletin is done in the maintenance zone(s) given below. **Group 1, 4:**
**Affected Maintenance Zones Zone**  **Model** 231, 232 737-600, 737-700, 737-800, 737-900 **Group 2:**
**Affected Maintenance Zones Zone**  **Model** 231, 232 737-600, 737-700, 737-800 **Group 3, 5:**
**Affected Maintenance Zones Zone**  **Model** 231, 232 737-700C **E. Compliance** The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Boeing recommends the following actions shown in the table below. **NOTE:** If the pivot link structure has been changed or if the seats moved or the interior configuration has changed since delivery of the airplane, then contact the holder of the STC which changed the pivot link or moved the seats to determine which airplane group to comply to in the table below.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 18 of 74 **BOEING SERVICE BULLETIN 737-53-1244 TABLE 1. PIVOT LINK REPAIR OR REPLACEMENT TIMES** 
**FOLLOW ON ACTION COMPLIANCE TIME**  **OPTIONAL ACTIONS CONDITION**  None Within 12 months after the original issue date of this service bulletin. Install new pivot link as shown in this service bulletin. Group 1 airplanes - No changes to pivot link structure and passenger seats have not been moved after airplane delivery. Install new pivot link within 60 months after the Revision5 date of this service bulletin. Within 12 months after the original issue date of this service bulletin. Move the seats (a)

None Within 12 months after the original issue date of this service bulletin. Install new pivot link as shown in this service bulletin. Group 2 and 3 Airplanes - No changes to pivot link structure and passenger seats have not been moved after airplane delivery. (b) and Within 12 months after the original issue date of this service bulletin. Install blind centerline fasteners in the seat track Install new pivot link within 60 months after the Revision5 date of this service bulletin. Install new pivot link within 60 months after the Revision5 date of this service bulletin. Within 12 months after the original issue date of this service bulletin. Install solid centerline fasteners in the seat track. Install new pivot link within 60 months after the Revision5 date of this service bulletin. Within 12 months after the original issue date of this service bulletin. Move the seats (a)

None Within 60 months after the Revision 4 date of this service bulletin. Install new pivot link as shown in this service bulletin. Group 4 and 5 Airplanes - No changes to pivot link structure and passenger seats have not been moved after airplane delivery. (b) and Within 12 months after the original issue date of this service bulletin. Install blind centerline fasteners in the seat track Install new pivot link within 60 months after the Revision5 date of this service bulletin. Install new pivot link within 60 months after the Revision5 date of this service bulletin. Within 12 months after the original issue date of this service bulletin. Install solid centerline fasteners in the seat track. Move the seats so that the forward stud of the aft legs are not in the BS 521.95 to 536.95 area for two stud configurations or between BS 521.95 to 535.95 for three stud configurations. If seats are moved to optional positions they cannot be moved back to the original position until after the new one piece pivot link has been installed as shown in this service bulletin. (a)

If blind fasteners are installed then inspect for missing or damaged fasteners every 3,000 flight cycles. Replace the blind fasteners with solid fasteners within 10,000 fight cycles. (b)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 19 of 74 **BOEING SERVICE BULLETIN 737-53-1244 F. Approval**  This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin. **G. Manpower** The table below shows an estimate of the task-hours necessary to do this change 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.
**Group 1-2, 4: Pivot Link Installation**  **Elapsed Hours Task-Hours**  **Number of Persons Task**  2 4 2 Open Access 3 6 2 Remove Old Pivot Link 10.5 (a) 21 2 Install New Pivot Link 2 4 2 Close Access 17.5 (a) 35 TOTAL FOR EACH AIRPLANE (a) More time may be required for each bushing strap reworked or modified as given in Figure 11 and Figure 12. **Group 3, 5: Pivot Link Installation**  **Elapsed Hours Task-Hours**  **Number of Persons Task**  2 4 2 Open Access 3.5 7 2 Remove Old Pivot Link 13 (a) 26 2 Install New Pivot Link

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 20 of 74 **BOEING SERVICE BULLETIN 737-53-1244 Group 3, 5:**  **Pivot Link Installation Elapsed Hours**  **Task-Hours Number of Persons**  **Task** 2 4 2 Close Access 20.5 (a) 41 TOTAL FOR EACH AIRPLANE (a) More time may be required for each bushing strap reworked or modified as given in Figure 11 and Figure 12. **Group 2, 4: Centerline Fastener Installation**  **Centerline Fastener Installation - Group 2 and 4 Airplanes Elapsed Hours**  **Task-Hours Number of Persons**  **Task** 2 4 2 Open Access 5 10 2 Install Fasteners 2 4 2 Close Access 9 18 TOTAL FOR EACH AIRPLANE **Group 3, 5: Centerline Fastener Installation**  **Centerline Fastener Installation - Group 3 and 5 Airplanes Elapsed Hours**  **Task-Hours Number of Persons**  **Task** 2 4 2 Open Access 6 12 2 Install Fasteners 2 4 2 Close Access 10 20 TOTAL FOR EACH AIRPLANE **H. Weight and Balance Changes Group 1-5:**  **Pivot Link Installation Change in Moment**  **(Pound-Inches) Change in Weight**  **(Pounds) Airplane** 
+200 +0.4 737-600 +200 +0.4 737-700 +200 +0.4 737-700C +200 +0.4 737-800 +200 +0.4 737-900

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 21 of 74 **BOEING SERVICE BULLETIN 737-53-1244 Group 2-5:**  **Centerline Fastener Installation Change in Moment**  **(Pound-Inches) Change in Weight**  **(Pounds) Airplane** 
+100 +0.2 737-600 +100 +0.2 737-700 +100 +0.2 737-700C +100 +0.2 737-800 +100 +0.2 737-900
**I. Electrical Load Data** Not applicable. **J. References** 1. Existing Data: a. Engineering Change Memo PRR 38489. b. Boeing Document D6-56722, Customer Cost Benefit Methodology Guide. c. Service Related Problem (SRP) 737-SRP-53-0176. d. 737-600/700/800/900 Aircraft Maintenance Manual (AMM) 25-22-00, 25-27-15, 53-21-00. e. 737-600 Structural Repair Manual (SRM) 51-40-08. f. 737-700 Structural Repair Manual (SRM) 51-40-08. g. 737-700CONV Structural Repair Manual (SRM) 51-20-01, 51-40-08. h. 737-700IGW (BBJ) Structural Repair Manual (SRM) 51-40-08. i. 737-800 Structural Repair Manual (SRM) 51-40-08. j. 737-900 Structural Repair Manual (SRM) 51-40-08. k. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-30-11, 20-41-02, 20-42-05, 20-43-03, 20-50-02, 20-50-10, 20-50-12, 20-50-19. l. Boeing Service Letter 737-SL-00-018 m. Boeing Parts Standards Document D-590 2. Data supplied with this Service Bulletin: None.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 22 of 74 **BOEING SERVICE BULLETIN 737-53-1244**3. Installation Drawings Used in the Preparation of this Service Bulletin:
**Title Drawing Number**  Section 43 / 44 Lower Lobe Integration 143A0060 These drawings were used to prepare this service bulletin. These drawings are not necessary to make the specified changes, and are not supplied with this service bulletin. These drawings may not be applicable to all airplane configurations or operators. **K. Publications Affected** 1. Publications: **Chapter-Section Publication**  53-31 737 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 23 of 74 **BOEING SERVICE BULLETIN 737-53-1244**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 24 of 74 **BOEING SERVICE BULLETIN 737-53-1244**

BLANK PAGE**2. MATERIAL INFORMATION A. Material - Price and Availability**  Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary For Each Airplane as shown below. Kits availability is shown in the Reorder Lead Time (ROLT). ROLT is calculated from the date Boeing gets the purchase order.
**Unit Price thru May 31, 2006**  **ROLT (Weeks)**  **Name Kit Number** 

- - TOP KIT - PIVOT LINK 002A0018-1 (a)

- - TOP KIT - PIVOT LINK 002A0018-2 (b) $23,210.00 88 KIT - PIVOT LINK 002A0018-3 $20,689.00 88 KIT - PIVOT LINK 002A0018-4 (a) Kit not available. Replaced by 002A0018-3. (b) Kit not available. Replaced by 002A0018-4. The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. After the Unit Price date, new price and ROLT data is applicable. Prices are in United States dollars. Terms: Net 30 days. **Reference this service bulletin and submit your purchase order by one of the methods that follow:**  1. Order on-line via ATA Spec 2000 or Boeing Part Page 2. Fax to (206) 662-7145 3. Spares Customer Support - MC 36-65 Boeing Spares Department P.O. Box 3707 Seattle, Washington 98124-2207 USA **B. Industry Support Information** Boeing warranty remedies are available for 737 airplanes in warranty as of January 18, 2002. For man-hour reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing Commercial Airplanes Group - Warranties. The kits for airplanes in warranty as of that date will be supplied at no charge. Send a purchase order for the kits to Boeing Spares. Please refer to this service bulletin number and reference the airplane variable number in your purchase order. In addition, the tool required to complete this modification will be supplied as a no charge loan. **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:** One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 25 of 74 **BOEING SERVICE BULLETIN 737-53-1244 Use Kit**  **Use Kit Airplane Group**  002A0018-3 002A0018-1 (a)(b) 1, 2 and 4 002A0018-4 002A0018-2 (c)(d) 3 and 5 (a) Kit not available. Replaced by 002A0018-3. (b) To change a 002A0018-1 top kit to a 002A0018-3 top kit, rework the 143A5595-15pivot link, 143A5595-22 bushing strap and 143A5595-23 bushing strap as given in Accomplishment Instructions paragraph 3.B. Part IV.,1. b. (c) Kit not available. Replaced by 002A0018-4. (d) To change a 002A0018-2 top kit to a 002A0018-4 top kit, rework the 143A5595-15pivot link, 143A5595-22 bushing strap and 143A5595-23 bushing strap as given in Accomplishment Instructions paragraph 3.B. Part IV., 2. b.
**Kit 002A0018 Notes**  **Existing Part Num- ber**  **Name QTY**  **New Part Number -1**  **-2** (a)(b)

- Top Kit, Pivot Link
- . 002A0018-1 (d)(e)

- Top Kit, Pivot Link

. - 002A0018-2 (c)

- Pivot Link Kit 1
- 100A5001-1 (f)

- Pivot Link Kit
- 1 100A5001-2

- - Foam

. 1 100A5001-3 (g) (h) (i) 143A5595-4 and 65- 46813-137 Pivot Link Assy 4 5 143A5595-15

- - Pivot Link Assy, Bushing Strap 4 5 143A5595-22

- - Pivot Link Assy, Bushing Strap 4 5 143A5595-23 (g) (i) 143A5240-11 Plate 1

. 143A5240-11 (g) (i) 143A5240-12 Plate 1

. 143A5240-12 (g) (i) 143A5240-13 Plate 1

. 143A5240-13 (g) (i) 143A5240-14 Plate 1

. 143A5240-14 (g) (i) 143A5240-2 Plate 2 2 143A5240-2 (g) (i) 143A5240-21 Plate

. 2 143A5240-21 (g) (i) 143A5240-27 Plate

. 2 143A5240-27 (i) BACB28Y4C138 Bushing 4 5 BACB28Y4C178 (j)

- Bolt

. 4 BACB30LH3DK4 (i) (j) BACB30NR4DK23 Bolt 4 5 BACB30US4K29D (j) (k)

- Bolt 18 22 BACB30VT8K5 (j) (k)

- Bolt 14 11 BACB30YP8K2

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 26 of 74 **BOEING SERVICE BULLETIN 737-53-1244 Kit 002A0018**  **Notes Existing Part Num-**  **ber Name**  **QTY New Part Number**  **-1 -2**  (j)

- Bolt 3

. BACB30YP8K3 (j)

- Bolt 3

. BACB30YP8K4 (k)

- Collar 37 32 BACC30BL8

- Nut

. 4 BACN10JD103CD (k)

- Clipnut 20 20 BACN10VR1CG (k)

- Clipnut 27 33 BACN10VR3CG (l) MS24665-134 Cotter Pin 4 9 BACP18BC02A06P (l) MS24665-155 Cotter Pin 4 5 BACP18BC02A08P (k)

- Rivet 66 66 BACR15GF4D3 (k)

- Screw 57 60 BACS12GP3L16

- - Washer

. 4 NAS1149D0363J (g) (i) (m) 143A5240-6 Panel Break Detail 2 2 143A5240U31 (g) (i) (m) 143A5240-9 Panel Break Detail 1

. 143A5240U33 (g) (i) (m) 143A5240-10 Panel Break Detail 1

. 143A5240U34 (g) (i) (m) 143A5240-15 Panel Break Detail 1

. 143A5240U37 (g) (i) (m) 143A5240-16 Panel Break Detail 1

. 143A5240U38 (g) (i) (m) 143A5240-23 Panel Break Detail

. 1 143A5240U41 (g) (i) (m) 143A5240-24 Panel Break Detail

. 1 143A5240U42 (g) (i) (m) 143A5240-29 Panel Break Detail

. 2 143A5240U45 (a) Kit not available. Replaced by 002A0018-3. (b) To change a 002A0018-1 top kit to a 002A0018-3 top kit, rework the 100A5001-1 pivot link kit into 100A5001- 4 pivot link kit. (c) To change a 100A5001-1 pivot link kit to a 100A5001-4 pivot link kit, rework the 143A5595-15 pivot link, 143A5595-22 bushing strap and 143A5595-23 bushing strap as given in Accomplishment Instructions paragraph 3.B. Part IV., 1. b. (d) Kit not available. Replaced by 002A0018-4. (e) To change a 002A0018-2 top kit to a 002A0018-4 top kit, rework the 100A5001-2 pivot link kit into 100A5001- 5 pivot link kit. (f) To change a 100A5001-2 pivot link kit to a 100A5001-5 pivot link kit, rework 143A5595-15 pivot link, 143A5595-22 bushing strap and 143A5595-23 bushing strap as given in Accomplishment Instructions paragraph 3.B. Part IV., 2. b. (g) Discard the existing part. (h) The one piece 143A5595-15 Pivot Link Assembly replaces the 143A5595-4 pivot link and 65-46813-137 seat track

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 27 of 74 **BOEING SERVICE BULLETIN 737-53-1244 Kit 002A0018**  **Notes Existing Part Num-**  **ber Name**  **QTY New Part Number**  **-1 -2**  (i) You cannot use the existing part to replace the new or changed part. (j) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer than indicated. Also, if any fasteners part numbers listed are not available or have been superseded, substitute fasteners may be supplied in kits. Boeing Document D-590 is used to determine the part numbers used as substitutes. (k) There are more parts than are necessary. (l) The new part number and existing part number for the cotter pin for group 3 and 5 airplanes are the same. (m) To facilitate installation, some Boeing parts will be sent in an 'interim' configuration. Boeing will identify these interim configurations with a 'U', 'W' or 'Y' in lieu of the '-' (dash) in the part number. Interim parts are changed to the as-designed 'dash' configuration when installed as given in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing 005W0900 "INTERIM PARTS - SPARES" and Service Letter 737-SL-00-018 for more information.
**Kit 002A0018 Notes**  **Existing Part Num- ber**  **Name QTY**  **New Part Number -3**  **-4** (a)

- TOP KIT - PIVOT LINK

- . 002A0018-3 (b)

- TOP KIT - PIVOT LINK

. - 002A0018-4 (c)

- KIT - PIVOT LINK 1

. 100A5001-4 (d)

- KIT - PIVOT LINK

. 1 100A5001-5 (a) Replaces 002A0018-1 top kit - pivot link. (b) Replaces 002A0018-2 top kit - pivot link. (c) Replaces 100A5001-1 kit - pivot link. (d) Replaces 100A5001-2 kit - pivot link.
**Kit 100A5001 Notes**  **Existing Part Number Name**  **QTY New Part Number**  **-4 -5** 

- - KIT-PIVOT LINK

. 1 100A5001-3 (a) (b)

- PLATE 2 2 143A5240-2 (a) (b)

- PLATE 1

. 143A5240-11 (a) (b)

- PLATE 1

. 143A5240-12 (a) (b)

- PLATE 1

. 143A5240-13 (a) (b)

- PLATE 1

. 143A5240-14

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 28 of 74 **BOEING SERVICE BULLETIN 737-53-1244 Kit 100A5001**  **Notes Existing Part Number**  **Name QTY**  **New Part Number -4**  **-5** (a) (b)

- PLATE

. 2 143A5240-21 (a) (b)

- PLATE

. 2 143A5240-27 (a) (b) (c)

- PANEL BREAK DETAIL 2 2 143A5240U31 (a) (b) (c)

- PANEL BREAK DETAIL 1

. 143A5240U33 (a) (b) (c)

- PANEL BREAK DETAIL 1

. 143A5240U34 (a) (b) (c)

- PANEL BREAK DETAIL 1

. 143A5240U37 (a) (b) (c)

- PANEL BREAK DETAIL 1

. 143A5240U38 (a) (b) (c)

- PANEL BREAK DETAIL

. 1 143A5240U41 (a) (b) (c)

- PANEL BREAK DETAIL

. 1 143A5240U42 (a) (b) (c)

- PANEL BREAK DETAIL

. 2 143A5240U45 (a) (b) (d) 143A5595-15, 143A5595-4 and 65- 46813-137 PIVOT LINK ASSY STA 520-540 4 5 143A5595-27

- 143A5595-23 PIVOT LINK ASSY STA 520-540 4 5 143A5595-30

- 143A5595-22 PIVOT LINK ASSY STA 520-540 4 5 143A5595-31

- - BUSHING, PLAIN 4 5 BACB28AK05-170 (b) BACB28Y4C138 BUSHING, PLAIN 4 5 BACB28Y4C178 (e)

- BOLT

. 4 BACB30LH3DK4

- - BOLT 4 5 BACB30NR5DK29 (b) (e) BACB30NR4DK23 BOLT 4 5 BACB30US4K29D (e) (f)

- BOLT 18 22 BACB30VT8K5 (e) (f)

- BOLT, 100 DEG HEX DR 14 11 BACB30YP8K2 (e)

- BOLT, 100 DEG HEX DR 3

. BACB30YP8K3 (e)

- BOLT, 100 DEG HEX DR 3

. BACB30YP8K4 (f)

- COLLAR 37 32 BACC30BL8

- - NUT, CASTELLATED

. 4 BACN10JD103CD

- - NUT, CASTELLATED 4 5 BACN10JD4CD (f)

- CLIP NUT 20 20 BACN10VR1CG (f)

- CLIP NUT 27 33 BACN10VR3CG (g) MS24665-134 PIN, COTTER 4 9 BACP18BC02A06P (g) MS24665-155 PIN 4 5 BACP18BC02A08P (f)

- RIVET, 100 DEG 66 66 BACR15GF4D3

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 29 of 74 **BOEING SERVICE BULLETIN 737-53-1244 Kit 100A5001**  **Notes Existing Part Number**  **Name QTY**  **New Part Number -4**  **-5** (f)

- FLOOR PANEL SCREWS 57 60 BACS12GP3L16

- - WASHER, FLAT

. 4 NAS1149D0363J (a) Discard the existing part. (b) You cannot use the existing part to replace the new or changed part. (c) To facilitate installation, some Boeing parts will be sent in an 'interim' configuration. Boeing will identify these interim configurations with a 'U', 'W' or 'Y' in lieu of the '-' (dash) in the part number. Interim parts are changed to the as-designed 'dash' configuration when installed as given in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing 005W0900 "INTERIM PARTS - SPARES" and Service Letter 737-SL-00-018 for more information. (d) The one piece 143A5595-27 Pivot Link Assembly replaces the 143A5595-15 or 143A5595-4 pivot link and 65-46813-137 seat track. (e) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer than indicated. Also, if any fasteners part numbers listed are not available or have been superseded, substitute fasteners may be supplied in kits. Boeing Document D-590 is used to determine the part numbers used as substitutes. (f) There are more parts than are necessary. (g) The new part number and existing part number for the cotter pin for group 3 and 5 airplanes are the same. 2. Parts and Materials Supplied by the Operator:
**Notes Name**  **QTY Part Number / Specification**  (b) Bolt (a) BACB30NN5K6 (b) Washer (a) NAS1149D0563J (h) Washer (h) NAS1149C0663R or equivalent CRES material (b) Nut (a) NAS1805-5L (g) Blind Fastener
- MS21140 (c)(d) Chemical Conversion Coating 16 ounces (Alodine 1200S) MIL-C-5541 (c)(e) Primer 16 ounces BMS 10-11, Type 1 (c)(e) Sealant 16 ounces BMS 5-95, Class B -1/2, -2, -4 (c)(f) Adhesive 8 ounces BAC 5010 TYPE 79 or TYPE 60 For Group 2 and 4 airplanes quantity of 28 bolts, washers and nuts are needed. (a)For Group 3 and 5 airplanes quantity of 35 bolts, washers and nuts are needed. Refer to 737 Structural Repair Manual Chapter 51 for alternative fasteners. (b)See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. (c)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 30 of 74 **BOEING SERVICE BULLETIN 737-53-1244 Notes**  **Name QTY**  **Part Number / Specification** Also refer to SOPM 20-43-03 for supplier data. (d)Also refer to SOPM 20-30-11 for supplier data. (e)Also refer to SOPM 20-50-12 for supplier data. (f) MS21140 blind fastener is optional to BACB30NN5K6 Bolt, NAS1149D0563J Washer, and NAS1805- 5L Nut. (g)Used for Bushing Strap 143A5595-30 rework. Quantity as needed, one for each pivot link. (h)
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** Boeing can supply the tools shown in Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin. Send a Purchase Order to the Director of Spares. Give this service bulletin number and the date the tools will be used. If there is a limit in the quantity of available rental tools, a supply sequence is given by Spares. **Rental Data: Monthly Price**  **Daily Price Name**  **Tool Kit Number**

- - LOCATING JIG SEAT TRACK PIVOT LINK MIT002A0018-1 NOTE: The special tool required to install the new pivot links will be supplied as a no charge loan. The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgement. After the Price date, new price data is applicable. Prices are in United States dollars. Terms: Net 30 days. **Reference this service bulletin number and submit purchase order by one of the methods that follow:**  1. Order on-line via ATA Spec 2000 or Boeing Part Page 2. Fax to (206) 662-7145 3. Spares Customer Support - MC 36-65 Boeing Spares Department P.O. Box 3707 Seattle, Washington 98124-2207 (Service Bulletin 737-53-1244)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 31 of 74 **BOEING SERVICE BULLETIN 737-53-1244 F. Special Tooling Necessary to do this Service Bulletin**  To get the tools shown below, refer to Paragraph 2.E., Special Tooling - Price and Availability. Maintenance and overhaul tools in the manuals shown in Paragraph 1.J., References, can also be necessary. Examine operator tool supply to make sure all necessary tools are available.
**Name Tool Kit Number**  LOCATING JIG SEAT TRACK PIVOT LINK MIT002A0018-1 NOTE: The special tool required to install the new pivot links will be supplied as a no charge loan.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 32 of 74 **BOEING SERVICE BULLETIN 737-53-1244 3. ACCOMPLISHMENT INSTRUCTIONS**  **A. GENERAL INFORMATION CAUTION:**  KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE. **NOTE:** 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 2. Obey all of the warnings and cautions given in the specified manual sections. 3. Unless shown differently, these dimensions and tolerances are used: – Linear dimensions are in inches – Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or minus 0.03 inch – Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch – Angular tolerance is plus or minus 2 degrees – Hole dimensions for standard solid rivets and fasteners are in Structural Repair Manual (SRM) Chapter 51 – Torque limits to tighten nuts and bolts are in SRM Chapter 51 4. Use the approved fastener and process material substitutions in accordance with SRM Chapter 51. Alternate fasteners are listed in SRM Chapter 51. 5. If the length of any fastener specified in this service bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. 6. These work instructions refer to procedures included in other Boeing documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "as given in" are included in the instruction, the procedure in the Boeing document must be used.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 33 of 74 **BOEING SERVICE BULLETIN 737-53-1244**7. The instructions in Paragraph 3.B., Work Instructions and the figures can include operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing Index contain data on versions of the tools or test equipment that you can use. It is permitted to use replaced tools. It is not permitted to use superseded tools. 8. If it is necessary to remove more parts for access, you can remove those parts. If you can get access without removing identified parts, it is not necessary to remove all of the identified parts. Jacking and shoring limitations must be observed. 9. Where the work instructions include installation of a kept part, a new or serviceable part with the same part number can be installed as an alternative to the kept part. The removed part can be discarded if a new or serviceable part is installed. **B. WORK INSTRUCTIONS PART I - CHECK LOCATION OF THE PASSENGER SEATS**  1. Check the maintenance records for the airplane to see if the passenger seats between Body Stations 521.95 and 536.95 have been moved since delivery of the airplane. a. If the location of the passenger seats have been moved after delivery of the airplane then check the location of the forward stud on the aft leg of the seat. See the tables below to determine which group your airplane belongs to. **TABLE 1. PASSENGER SEATS WITH TWO STUDS ON THE AFT LEG See Section 1.E Compliance For**  **Description of Location Location of Forward Stud**  Group 2 and 3

- BS 521.95 to BS 533.95 Group 1 Third to last lip on the seat track BS 534.95 Group 1 Second to last lip on the seat track BS 535.95 Group 1 Last lip on the seat track BS 536.95 Group 4 and 5

- Aft of BS 536.95
**TABLE 2. PASSENGER SEATS WITH THREE STUDS ON THE AFT LEG See Section 1.E Compliance For**  **Description of Location Location of Forward Stud**  Group 2 and 3

- BS 521.95 to BS 533.95 Group 1 Third to last lip on the seat track BS 534.95 Group 1 Second to last lip on the seat track BS 535.95 Group 4 and 5 Last lip on the seat track BS 536.95 Group 4 and 5

- Aft of BS 536.95 b. If the location of the passenger seats have not been moved since delivery of the airplane then continue to PART II - ACCESS.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 34 of 74 **BOEING SERVICE BULLETIN 737-53-1244 PART II - ACCESS - REPAIR OR PIVOT LINK INSTALLATION**  1. Remove the seat track covers as necessary between body stations 520 and 540. Refer to 737-600/700/800/900 AMM 25-27-15 as an accepted procedure. 2. Remove the passenger seats. Refer to 737-600/700/800/900 AMM 25-22-00 as an accepted procedure. 3. Remove the passenger carpets. Refer to 737-600/700/800/900 AMM 25-27-15 as an accepted procedure. 4. Remove the passenger compartment floor panels. Refer to 737-600/700/800/900 AMM 53-21-00 as an accepted procedure. Keep fasteners for floor panel installation. **NOTE:** Record the hole size and nut clip size for each floor panel fastener in the pivot links and break panels at body station 540. Use this data to drill fastener holes in the new pivot links and break panels for floor panel installation. **PART III - REPAIR - GROUP 2, 3, 4 AND 5** 1. GROUP 2 AND 4 REPAIR (4 Pivots) a. Install centerline fasteners as given in Figure 1, or install new pivot link as given in PART IV - PIVOT LINK INSTALLATION. b. Do the PART VI - CLOSE ACCESS. 2. GROUP 3 AND 5 REPAIR (5 Pivots) a. Install centerline fasteners as given in Figure 2, or install new pivot link as given in PART IV - PIVOT LINK INSTALLATION. b. Do the PART VI - CLOSE ACCESS. **PART IV - PIVOT LINK INSTALLATION - GROUP 1, 2, 3, 4 AND 5** 1. GROUP 1, 2 AND 4 PIVOT LINK INSTALLATION a. Remove the seat tracks, break panels and pivot links as given in Figure 3. **NOTE:** Mark the position of the break panels onto the floor beams forward of the pivot links and onto the crease beams before removal. Use this data to position the new break panels for installation. b. If a 002A0018-1 top kit is to be installed. Do the modification to part numbers 143A5595-15 pivot link, 143A5595-22 bushing strap and 143A5595-23 bushing strap as given in Figure 12. c. Install new pivot links as given in Figure 4. (1) When installing the pivot link, remove the MIT002A0018-1 Locating Jig and check if the pivot link seat track aligns with the seat track aft of Body Station 537.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 35 of 74 **BOEING SERVICE BULLETIN 737-53-1244**(a) If the seat tracks above do not align, then rework the bushing strap as given in Part V - Bushing Strap Rework. Then do steps d and e below. (b) If the seat tracks align at Body Station 537, then continue to steps d and e below. d. Install break panels as given in Figure 5. e. Drill holes for floor panels as given in Figure 6. f. Do the PART VI - CLOSE ACCESS. 2. GROUP 3 AND 5 PIVOT LINK INSTALLATION a. Remove seat track, break panels and pivot link as given in Figure 7. **NOTE:** Mark the position of the break panels onto the floor beams forward of the pivot links and onto the cargo tracks before removal. Use this data to position the new break panels for installation. b. If a 002A0018-2 top kit is to be installed. Do the modification to part numbers 143A5595-15 pivot link, 143A5595-22 bushing strap and 143A5595-23 bushing strap as given in Figure 12. c. Install new pivot links as given in Figure 8. (1) When installing the pivot link, remove the MIT002A0018-1 Locating Jig and check if the pivot link seat track aligns with the seat track aft of Body Station 537. (a) If the seat tracks above do not align, then rework the bushing strap as given in Part V - Bushing Strap Rework. Then do steps d and e below. (b) If the seat tracks align at Body Station 537, then continue to steps d and e below. d. Install break panels as given in Figure 9. e. Drill holes for floor panels as given in Figure 10. f. Do the PART VI - CLOSE ACCESS. **PART V - BUSHING STRAP REWORK** 1. If pivot link seat track does not align with seat track aft of Body Station 537 then rework the 143A5595-30 Bushing Strap and add filler as given in Figure 11. **NOTE:** Maximum amount of material removal from the Bushing Strap is 0.06 inch. If more material needs to be removed then contact the Boeing Company.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 36 of 74 **BOEING SERVICE BULLETIN 737-53-1244 PART VI - CLOSE ACCESS - REPAIR OR PIVOT LINK INSTALLATION**  1. Install the passenger compartment floor panels. Refer to 737-600/700/800/900 AMM 53-21-00 as an accepted procedure. 2. Install the passenger carpets. Refer to 737-600/700/800/900 AMM 25-27-15 as an accepted procedure. 3. Install the passenger seats with kept fasteners. Refer to 737-600/700/800/900 AMM 25-22-00 as an accepted procedure. 4. Install the seat track covers. Refer to737-600/700/800/900 AMM 25-27-15 as an accepted procedure. 5. Put the airplane back to a serviceable condition.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5: July 27, 2011 37 of 74 **BOEING SERVICE BULLETIN 737-53-1244 This Figure applies only to: Group 2, 4.** 

**FIGURE 1: CENTERLINE FASTENER INSTALLATION - GROUP 2 AND 4 (SHEET 1 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 38 of 74 **BOEING SERVICE BULLETIN 737-53-1244**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 each airplane.
**NOTES QTY**  **PART NUMBER NAME**  **TASK STEP**  Four Locations (a) 7
- Fastener Holes Drill 1 - Four Locations 7
- Fastener Holes Countersink 2 - Countersink 100 degrees on upper side of seat track (b) Apply one coat to countersink and fastener hole. (c) - Alodine 1200S (Refer- ence MIL-C-5541)Chemical Conversion Coating Apply 3 Apply one coat to countersink and fastener hole. (d) - (Reference BMS 10- 11, Type 1) Primer Apply 4 Four Locations (e) 7 SEE FASTENER CODE TABLE Fasteners Install 5
- Four Locations 1 Gap Check 6 - Minimum Gap of 0.20 inch between pivot link and seat track at BodyStation 520. Trim pivot link as necessary to get minimum Gap of 0.20 inch. Keep the center of the fastener hole within 0.03 inch from the center of the seat track slot in the inboard / outboard direction and the forward / aft direction. (a)Maintain a countersink depth so fastener will have a flushness of +/- 0.005 on the seat track. Refer to 737-600 SRM 51-40-08, 737-700 SRM 51-40-08, 737-700IGW (BBJ) SRM 51-40-08, 737-800 SRM 51-40-08, 737-900 SRM 51-40-08 for tools and procedures to set countersink depth. (b)
Refer to SOPM 20-43-03 for procedures to apply chemical conversion coating. (c) Refer to SOPM 20-41-02 for procedures to apply primer. (d) Install fasteners wet with BMS 5-95 sealant. Apply sealant under the head of the fastener and on the shank of the fastener (Ref. SOPM 20-50-19, Method 2 of Corrosion Protection Sealing). (e)
The code shown below agrees with the letter shown in the upper left corner of the fastener symbol in the figure. If the grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer than indicated. Also, if any of the fastener part numbers are not available or have been superseded, substitute fasteners may be supplied in Boeing kits, Boeing Document D-590 is used to determine the part numbers used as substitutes.
**NOTES HOLE DIA.**  **PART NUMBER NAME**  **CODE** (a) 0.313 - 0.327 BACB30NN5K6 Bolt A

- NAS1149D0563J Washer

- NAS1805-5L Nut

**FIGURE 1: CENTERLINE FASTENER INSTALLATION - GROUP 2 AND 4 (SHEET 2 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 39 of 74 **BOEING SERVICE BULLETIN 737-53-1244 NOTES**  **HOLE DIA. PART NUMBER**  **NAME CODE**  (a) MS21140 blind fasteners can be used in place of BACB30NN bolts. If blind fasteners are used, then you must obey Paragraph 1.E. Compliance inspection times and time limit for blind fasteners.

**FIGURE 1: CENTERLINE FASTENER INSTALLATION - GROUP 2 AND 4 (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 40 of 74 **BOEING SERVICE BULLETIN 737-53-1244 This Figure applies only to: Group 3, 5.** 

**FIGURE 2: CENTERLINE FASTENER INSTALLATION - GROUP 3 AND 5 (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 41 of 74 **BOEING SERVICE BULLETIN 737-53-1244**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 each airplane.
**NOTE QTY**  **PART NUMBER NAME**  **TASK STEP**  Five Locations (a) 7
- Fastener Holes Drill 1 - Five locations 7
- Fastener Holes Countersink 2 - Countersink 100 degrees on upper side of seat track (b) Apply one coat to countersink and fastener hole. (c) - Alodine 1200S (Ref- erence MIL-C-5541)Chemical Conversion Coating Apply 3 Apply one coat to countersink and fastener hole. (d) - (Reference BMS 10- 11, Type 1) Primer Apply 4 Five Locations (e) 7 SEE FASTENER CODE TABLE Fasteners Install 5
- Five Locations 1 Gap Check 6 - Minimum Gap of 0.20 inch betweenpivot link and seat track at Body Station 520. Trim pivot link as necessary to get minimum Gap of 0.20 inch.Keep the center of the fastener hole within 0.03 inch from the center of the seat track slot in the inboard-outboard direction and the forward-aft direction. (a) Maintain a countersink depth so fastener will have a flushness of +/- 0.005 on the seat track. Refer to 737-700CONV SRM 51-40-08, for tools and procedures to set countersink depth. (b) Refer to SOPM 20-43-03 for procedures to apply chemical conversion coating. (c) Refer to SOPM 20-41-02 for procedures to apply primer. (d) Install fasteners wet with BMS 5-95 sealant. Apply sealant under the head of the fastener and on the shank of the fastener (Ref. SOPM 20-50-19, Method 2 of Corrosion Protection Sealing). (e)
The code shown below agrees with the letter shown in the upper left corner of the fastener symbol in the figure. If the grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer than indicated. Also, if any of the fastener part numbers are not available or have been superseded, substitute fasteners may be supplied in Boeing kits, Boeing Document D-590 is used to determine the part numbers used as substitutes
**NOTES HOLE DIA.**  **PART NUMBER NAME**  **CODE** (a) 0.313 - 0.327 BACB30NN5K6 Bolt A

- NAS1149D0563J Washer

- NAS1805-5L Nut (a) MS21140 blind fasteners can be used in place of BACB30NN bolts. If blind fasteners are used, then you must obey Paragraph 1.E. Compliance inspection times and time limit for blind fasteners.

**FIGURE 2: CENTERLINE FASTENER INSTALLATION - GROUP 3 AND 5 (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 42 of 74 **BOEING SERVICE BULLETIN 737-53-1244 This Figure applies only to: Group 1-2, 4.** 

**FIGURE 3: BREAK PANEL, SEAT TRACK AND PIVOT LINK REMOVAL - GROUP 1, 2 AND 4 (SHEET 1 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 43 of 74 **BOEING SERVICE BULLETIN 737-53-1244 FIGURE 3: BREAK PANEL, SEAT TRACK AND PIVOT LINK REMOVAL - GROUP 1, 2 AND 4**  **(SHEET 2 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 44 of 74 **BOEING SERVICE BULLETIN 737-53-1244**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 each airplane.
**NOTES QTY**  **PART NUMBER NAME**  **TASK STEP**  Twelve fasteners for each Seat Track 4 65-46813-137 Seat Track Remove / Discard 1

- - - Floor Beams and Crease Beams Mark 2
NOTE: Mark the position of the break panels onto the floor beams aft of the pivot links and on to the crease beams before removal. Use this data to position the new break panels during installation.

- 6 143A5240-( ) Break Panel Remove / Discard 3 The Fillers are between thePivot Link and the Break Panels at Body Line 0.0 only. 2 143A5240-17 Fillers Remove / Keep 4

One for each Pivot link at forward end of Pivot link. 4
- Cotter Pin Remove / Discard 5 4 BACN10JD5CD Nut Remove / Keep 4 NAS1149E0563P Washer Remove / Keep 4 BACB30NR5DK29 Bolt Remove / Keep 4 BACB28AK05-170 Bushing Remove / Keep One for each Pivot link at aft end of pivot link. 4
- Cotter Pin Remove / Discard 6 4 BACN10JD4CD Nut Remove / Keep 4 NAS1149E0463P Washer Remove / Keep 4
- Bolt Remove / Discard 4
- Bushing Remove / Discard

- 4 143A5595-4 Pivot Link Remove / Discard 7

**FIGURE 3: BREAK PANEL, SEAT TRACK AND PIVOT LINK REMOVAL - GROUP 1, 2 AND 4 (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 45 of 74 **BOEING SERVICE BULLETIN 737-53-1244 This Figure applies only to: Group 1-2, 4.** 

**FIGURE 4: PIVOT LINK INSTALLATION - GROUP 1, 2 AND 4 (SHEET 1 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 46 of 74 **BOEING SERVICE BULLETIN 737-53-1244 FIGURE 4: PIVOT LINK INSTALLATION - GROUP 1, 2 AND 4**  **(SHEET 2 OF 4)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 47 of 74 **BOEING SERVICE BULLETIN 737-53-1244**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 each pivot link assembly. A total of 4 pivot link assemblies are required for each airplane.
**NOTES QTY**  **PART NUMBER NAME**  **TASK STEP**  4 Locations (a) 1 143A5595-27 Pivot Link Align 1 4 Locations (b) (c) 1 143A5595-31 Bushing Strap Position 2 4 Locations (b) (c) 1 143A5595-30 Bushing Strap Position 3 4 Locations - Assemble the Bushing, Bolt, Washer and Nut. Do not tighten the Bolt and Nut. 1 BACB28Y4C178 Bushing Insert New 4 1 BACB30US4K29D Bolt Insert New 5 1 NAS1149E0463P Washer Install Kept 6 1 BACN10JD4CD Nut Install Kept 7 4 Locations - Assemble the Bushing, Bolt, Washer and Nut. Do not tighten. the Bolt and Nut. 1 BACB28AK05-170 Bushing Insert Kept 8 1 BACB30NR5DK29 Bolt Insert Kept 9 1 NAS1149E0563P Washer Install Kept 10 1 BACN10JD5CD Nut Install Kept 11 4 Locations (c)

- 143A5595-30 and -31 Bushing Straps Check Position 12 4 Locations (c)

- 143A5595-30 and -31 Bushing Straps Clamp 13 4 Locations (f) 1 143A5595-27 Pivot link Inspect 14 Through the Bushing Strapsinto the Pivot Link (4 Locations) (d) 4
- Holes Match Drill 15

4 Locations 4 SEE FASTENER CODE TABLE Bolts Collars Install 16 4 4 Locations 1 BACN10JD4CD Nut Tighten Kept 17 4 Locations (e) 1 BACP18BC02A08P Cotter Pin Install New 18 4 Locations 1 BACN10JD5CD Nut Tighten Kept 19 4 Locations (e) 1 BACP18BC02A06P Cotter Pin Install New 20Align the Pivot Link with the section 44 seat track crown using MIT002A0018-1 Locating Jig. (a)Locate by aligning with bolt and bushing shown in steps 4 and 5. (b)Make sure the Bushing Straps are up against the lower side of the top flange of the Pivot Link. (c)Drill holes 0.250 - 0.254 for the bolt. Install the collar on outer edge of the pivot link. (d)Refer to SOPM 20-50-02 for procedures to install cotter pin. (e)Make sure the pivot link seat track is vertically aligned with the section 44 seat track. The vertical alignment should be within + or - 0.020 inch to make sure correct seat installation. (f)

**FIGURE 4: PIVOT LINK INSTALLATION - GROUP 1, 2 AND 4 (SHEET 3 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 48 of 74 **BOEING SERVICE BULLETIN 737-53-1244**The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener. If the grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer than indicated. Also, if any of the fastener part numbers are not available or have been superseded, substitute fasteners may be supplied in Boeing kits, Boeing Document D-590 is used to determine the part numbers used as substitutes.
**NOTES HOLE DIA.**  **PART NUMBER NAME**  **CODE** Install collar against bushing strap. 0.250 - 0.254 BACB30VT8K5 Bolt A BACC30BL8 Collar

**FIGURE 4: PIVOT LINK INSTALLATION - GROUP 1, 2 AND 4 (SHEET 4 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 49 of 74 **BOEING SERVICE BULLETIN 737-53-1244 This Figure applies only to: Group 1-2, 4.** 

**FIGURE 5: BREAK PANEL INSTALLATION - GROUP 1, 2 AND 4 (SHEET 1 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 50 of 74 **BOEING SERVICE BULLETIN 737-53-1244 FIGURE 5: BREAK PANEL INSTALLATION - GROUP 1, 2 AND 4**  **(SHEET 2 OF 4)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 51 of 74 **BOEING SERVICE BULLETIN 737-53-1244**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 each airplane.
**NOTES QTY**  **PART NUMBER NAME**  **TASK STEP**  RBL 60 - RBL 45.5 (a) 1 143A5240U38 Break Panel Position 1 (e) (f) (g)

- Fastener Holes Match Drill (b) 1 143A5240-14 Plate Position 2 (e) (f) (g)

- Fastener Holes Match Drill RBL 45.5 - RBL 24.75 (c) 1 143A5240U31 Break Panel Position 3 (e) (f) (g)

- Fastener Holes Match Drill (d) 1 143A5240-2 Plate Position 4 (e) (f) (g)

- Fastener Holes Match Drill RBL 24.75 - BL 0.0

- 1 143A5240-17 Filler Position / Kept 5 (c) 143A5240U34 Break Panel Position 6 (e) (f) (g)

- Fastener Holes Match Drill 1 143A5240-12 Plate Position 7 (e) (f) (g)

- Fastener Holes Match Drill BL 0.0 - LBL 24.75

- 1 143A5240-17 Filler Position / Kept 8 (c) 1 143A5240U33 Break Panel Position 9 (e) (f) (g)

- Fastener Holes Match Drill 1 143A5240-11 Plate Position 10 (e) (f) (g)

- Fastener Holes Match Drill LBL 24.75 - LBL 45.5 (c) 1 143A5240U31 Break Panel Position 11 (e) (f) (g)

- Fastener Holes Match Drill (d) 1 143A5240-2 Plate Position 12 (e) (f) (g)

- Fastener Holes Match Drill LBL 45.5 - LBL 60 (a) 1 143A5240U37 Break Panel Position 13

**FIGURE 5: BREAK PANEL INSTALLATION - GROUP 1, 2 AND 4 (SHEET 3 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 52 of 74 **BOEING SERVICE BULLETIN 737-53-1244 NOTES**  **QTY PART NUMBER**  **NAME TASK**  **STEP** (e) (f) (g)

- Fastener Holes Match Drill (b) 1 143A5240-13 Plate Position 14 (e) (f) (g)

- Fastener Holes Match Drill RBL 60 - LBL 60 (h)

- BMS 5-95 Sealant Apply 15 See Fastener Codes

- - Parts Install 16Position to match original position of the old break panel on the crease beam. (a)Position to match contour of new Break Panel at end in common with crease beam. (b)Position to match original position of the old break panel on the floor beams. (c) Position the Plate so DISTANCE A and DISTANCE B are equal. (d)Apply one coat of Alodine 1200S on cut surfaces of fastener holes (Ref. SOPM 20-43-03). (e)Apply one coat of BMS 10-11, Type 1 primer to cut surfaces of fastener holes (Ref. SOPM 20-41-02). (f) Maintain an edge margin of 1.6D to 1.8D. (g)Apply sealant on faying surface between the Break Panels and Floor Beams (Ref. SOPM 20-50-19) (h) The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener. If the grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer than indicated. Also, if any of the fastener part numbers are not available or have been superseded, substitute fasteners may be supplied in Boeing kits, Boeing Document D-590 is used to determine the part numbers used as substitutes.
**NOTES HOLE DIA.**  **PART NUMBER NAME**  **CODE** 100 Degree countersink on top side. 0.247 - 0.250 BACB30YP8K( ) Bolt A

- - BACC30BL8 Collar 100 Degree countersink on top side. 0.128 - 0.134 BACR15GF4D3 Rivet B

**FIGURE 5: BREAK PANEL INSTALLATION - GROUP 1, 2 AND 4 (SHEET 4 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 53 of 74 **BOEING SERVICE BULLETIN 737-53-1244 This Figure applies only to: Group 1-2, 4.** 

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 each airplane.
**NOTES QTY**  **PART NUMBER NAME**  **TASK STEP**  (a) 3 143A5810-( ) Floor Panels Locate / Kept 1

- 9
- Nutclips and Screws Install / Kept 2 (b) 2 143A5810-( ) Floor Panels Align / Kept 3 (c)

- - Fastener Holes Mark Location 4

- 5 143A5810-( ) Floor Panels Remove 5 (d)(e)

- - Fastener Holes Drill 6 Temporarily Install 5 143A5810-( ) Floor Panels Install 7 Into new Break Panels (d)(e) - - Fastener Holes Match Drill 8Locate by temporarily attaching to the floor panels at existing attach locations in the pivot link at BL 0.0

and in the crease beams using kept clipnuts and screws or clipnuts and screw in kit 100A5001-4. (a)

**FIGURE 6: DRILL HOLES FOR FLOOR PANEL FASTENERS - GROUP 1, 2 AND 4 (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 54 of 74 **BOEING SERVICE BULLETIN 737-53-1244 NOTES**  **QTY PART NUMBER**  **NAME TASK**  **STEP** Center the floor panels between the pivot links, floor beams and attached floor panels in STEP 1. (b)Mark the fastener hole locations onto the pivot links and break panels from the existing fastener locations on the floor panels. (c)Apply one coat of Alodine 1200S on cut surfaces of fastener holes (Ref. SOPM 20-43-03). (d)Apply one coat of BMS 10-11, Type 1 primer to cut surfaces of fastener holes (Ref. SOPM 20-41-02). (e)

**FIGURE 6: DRILL HOLES FOR FLOOR PANEL FASTENERS - GROUP 1, 2 AND 4 (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 55 of 74 **BOEING SERVICE BULLETIN 737-53-1244 This Figure applies only to: Group 3, 5.** 

**FIGURE 7: BREAK PANEL, SEAT TRACK AND PIVOT LINK REMOVAL - GROUP 3 AND 5 (SHEET 1 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 56 of 74 **BOEING SERVICE BULLETIN 737-53-1244 FIGURE 7: BREAK PANEL, SEAT TRACK AND PIVOT LINK REMOVAL - GROUP 3 AND 5**  **(SHEET 2 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 57 of 74 **BOEING SERVICE BULLETIN 737-53-1244**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 each airplane.
**NOTES QTY**  **PART NUMBER NAME**  **TASK STEP**  Twelve fasteners for each Seat Track 5 65-46813-137 Seat Track Remove / Discard 1

- - - Floor Beams and Crease Beams Mark 2
NOTE: Mark the position of the break panels onto the floor beams aft of the pivot links and on to the crease beams before removal. Use this data to position the new break panels during installation.

- 6 143A5240-( ) Break Panels Remove / Discard 3 One for each Pivot link at forward end of Pivot link. 5
- Cotter Pin Remove / Discard 4 5 BACN10JD5CD Nut Remove / Keep 5 NAS1149E0563P Washer Remove / Keep 5 BACB30NR5DK29 Bolt Remove / Keep 5 BACB28AK05-170 Bushing Remove / Keep One for each Pivot link at aft end of Pivot link. 5
- Cotter Pin Remove / Discard 5 5 BACN10JD4CD Nut Remove / Keep 5 NAS1149E0463P Washer Remove / Keep 5
- Bolt Remove / Discard 5
- Bushing Remove / Discard

- 5 143A5595-4 Pivot Link Remove / Discard 6

**FIGURE 7: BREAK PANEL, SEAT TRACK AND PIVOT LINK REMOVAL - GROUP 3 AND 5 (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 58 of 74 **BOEING SERVICE BULLETIN 737-53-1244 This Figure applies only to: Group 3, 5.** 

**FIGURE 8: PIVOT LINK INSTALLATION - GROUP 3 AND 5 (SHEET 1 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 59 of 74 **BOEING SERVICE BULLETIN 737-53-1244 FIGURE 8: PIVOT LINK INSTALLATION - GROUP 3 AND 5**  **(SHEET 2 OF 4)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 60 of 74 **BOEING SERVICE BULLETIN 737-53-1244**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 each pivot link assembly. A total of 5 pivot link assemblies are required for each airplane.
**NOTES QTY**  **PART NUMBER NAME**  **TASK STEP**  5 Locations (a) 1 143A5595-27 Pivot Link Align 1 5 Locations (b) 1 143A5595-31 Bushing Strap Position 2 5 Locations (b) 1 143A5595-30 Bushing Strap Position 3 5 Locations 1 BACB28Y4C178 Bushing Insert New 4 5 Locations 1 BACB30US4K29D Bolt Insert New 5 5 Locations 1 NAS1149E0463P Washer Install Kept 6 5 Locations 1 BACN10JD4CD Nut Install Kept 7 5 Locations 1 BACB28AK05-170 Bushing Install Kept 8 5 Locations 1 BACB30NR5DK29 Bolt Install Kept 9 5 Locations 1 NAS1149E0563P Washer Install Kept 10 5 Locations 1 BACN10JD5CD Nut Install Kept 11

**FIGURE 8: PIVOT LINK INSTALLATION - GROUP 3 AND 5 (SHEET 3 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 61 of 74 **BOEING SERVICE BULLETIN 737-53-1244 NOTES**  **QTY PART NUMBER**  **NAME TASK**  **STEP** 5 Locations (c)

- 143A5595-30 and -31 Bushing Strap Check Position 12 5 Locations (c)

- 143A5595-30 and -31 Bushing Strap Clamp 13 5 Locations (h) 1 143A5595-27 Pivot link Inspect 14 Through the Bushing Straps into the Pivot Link (5 Locations) (d) 4
- Holes Match Drill 15

5 Locations 4 SEE FASTENER CODE TABLE Bolts Collars Install 16 4 5 Locations 1 BACN10JD4CD Nut Tighten Kept 17 5 Locations (e) 1 BACP18BC02A08P Cotter Pin Install New 18 5 Locations 1 BACN10JD5CD Nut Tighten Kept 19 5 Locations (e) 1 BACP18BC02A06P Cotter Pin Install New 20 5 Locations (f) (g) 1 100A5001-3 Foam Install 21Align the Pivot Link with the seat track crown using MIT002A0018-1 Locating Jig. (a) Locate by aligning with bolt and bushing shown in steps 4 and 5. (b) Make sure the Bushing Straps are nested against lower side of seat track flange. (c) Drill holes 0.250 - 0.254 for the bolt. Install the collar on outer edge of the pivot link. (d) See SOPM 20-50-02 for procedures to install cotter pin. (e) Trim foam strip 0.5 inch wide and 3.3 inches long to fit the gap. (f) If the gap exceeds 0.20 inch then bond two or more pieces of foam together with BAC 5010 TYPE 79 or TYPE 60 adhesive to obtain the necessary thickness to fill the gap. Refer to SOPM 20-50-12 for procedures to bond the foam with BAC 5010 TYPE 79 or TYPE 60 adhesive. (g)

Make sure the pivot link seat track is vertically aligned with the section 44 seat track. The vertical alignment should be within + or - 0.020 inch to make sure correct seat installation. (h)
The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener. If the grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer than indicated. Also, if any of the fastener part numbers are not available or have been superseded, substitute fasteners may be supplied in Boeing kits, Boeing Document D-590 is used to determine the part numbers used as substitutes.
**NOTES HOLE DIA.**  **PART NUMBER NAME**  **CODE** Install collar against bushing strap. 0.250 - 0.254 BACB30VT8K5 Bolt A BACC30BL8 Collar

**FIGURE 8: PIVOT LINK INSTALLATION - GROUP 3 AND 5 (SHEET 4 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 62 of 74 **BOEING SERVICE BULLETIN 737-53-1244 This Figure applies only to: Group 3, 5.** 

**FIGURE 9: BREAK PANEL INSTALLATION - GROUP 3 AND 5 (SHEET 1 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 63 of 74 **BOEING SERVICE BULLETIN 737-53-1244 FIGURE 9: BREAK PANEL INSTALLATION - GROUP 3 AND 5**  **(SHEET 2 OF 4)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 64 of 74 **BOEING SERVICE BULLETIN 737-53-1244**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 each airplane.
**NOTES QTY**  **PART NUMBER NAME**  **TASK STEP**  RBL 60 - RBL 45.5 (a) 1 143A5240U42 Break Panel Position 1 (e) (f) (g)

- Fastener Holes Match Drill (b) 1 143A5240-21 Plate Position 2 (e) (f) (g)

- Fastener Holes Match Drill RBL 45.5 - RBL 24.75 and LBL 45.5 - LBL 24.75 (c) 1 143A5240U31 Break Panel Position 3 (e) (f) (g)

- Fastener Holes Match Drill (d) 1 143A5240-2 Plate Position 4 (e) (f) (g)

- Fastener Holes Match Drill RBL 24.75 - LBL 24.75 (c) 143A5240U45 Break Panel Position 5 (e) (f) (g)

- Fastener Holes Match Drill (d) 1 143A5240-27 Plate Position 6 (e) (f) (g)

- Fastener Holes Match Drill LBL 45.5 - LBL 60 (a) 1 143A5240U41 Break Panel Position 7 (e) (f) (g)

- Fastener Holes Match Drill (b) 1 143A5240-21 Plate Position 8 (e) (f) (g)

- Fastener Holes Match Drill RBL 60 - LBL 60 (h)

- BMS 5-95 Sealant Apply 9 See Fastener Codes

- - Parts Install 10 NOTE: See note (b) for Code A in Fastener Code Table for special instructions to install fasteners in common with the crease beam. Position to match original position of the old break panel on the outboard seat track. (a)Position to match contour of new Break Panel at end in common with the outboard seat track. (b)Position to match original position of the old break panel on the floor beams. (c) Position the Plate so distance A and DISTANCE B are equal. (d)

**FIGURE 9: BREAK PANEL INSTALLATION - GROUP 3 AND 5 (SHEET 3 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 65 of 74 **BOEING SERVICE BULLETIN 737-53-1244 NOTES**  **QTY PART NUMBER**  **NAME TASK**  **STEP** Apply one coat of Alodine 1200S on cut surfaces fastener holes (Ref. SOPM 20-43-03). (e)Apply one coat of BMS 10-11, Type 1 primer to surfaces of fastener holes (Ref. SOPM 20-41-02). (f) Maintain an edge margin of 1.6D to 1.8D. (g)Apply sealant on faying surface between the Break Panels and Floor Beams (Ref. SOPM 20-50-19). (h) The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener. If the grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer than indicated. Also, if any of the fastener part numbers are not available or have been superseded, substitute fasteners may be supplied in Boeing kits, Boeing Document D-590 is used to determine the part numbers used as substitutes
**NOTES HOLE DIA.**  **PART NUMBER NAME**  **CODE** 100 Degree countersink on top side.(a) 0.190 - 0.194 BACB30LH3DK4 Bolt A

- - NAS1149D0363J Washer (b)

- BACN10JD103CD Nut (b)

- BACP18BC02A06P Cotter Pin 100 Degree countersink on top side. 0.247 - 0.250 BACB30YP8K3 Bolt B

- BACC30BL8 Collar 100 Degree countersink on top side. 0.128 - 0.134 BACR15GF4D3 Rivet C (a) Install bolt wet with BMS 5-95 sealant. Refer to 737-700CONV SRM 51-20-01 for procedures. (b) 1. Torque nut to 10 inch-pounds. 2. Turn the nut counterclockwise to loosen and to align the nut with the hole in the bolt for cotter pin installation. Do not turn the nut more than 1/6th of a turn. 3. Install cotter pin. Refer to Refer to SOPM 20-50-02 for more procedures to install cotter pin.

**FIGURE 9: BREAK PANEL INSTALLATION - GROUP 3 AND 5 (SHEET 4 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 66 of 74 **BOEING SERVICE BULLETIN 737-53-1244 This Figure applies only to: Group 3, 5.** 

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 each airplane.
**NOTES QTY**  **PART NUMBER NAME**  **TASK STEP**  (a) 2 143A5810-( ) Floor Panels Locate / Kept 1

- - - Nutclips and Screws Install / Kept 2 (b) 4 143A5810-( ) Floor Panels Align / Kept 3 (c)

- - Fastener Holes Mark Location 4

- 6 143A5810-( ) Floor Panels Remove 5 (d) (e)

- - Fastener Holes Drill 6 Temporarily install 5 143A5810-( ) Floor Panels Install 7 Into new Break Panels (d) (e) - - Fastener Holes Match Drill 8Locate by temporarily attaching to the floor panels at existing attach locations in the crease beams using

kept clipnuts and screws or clipnuts and screws in kit 100A5001-5. (a)

**FIGURE 10: DRILL HOLES FOR FLOOR PANEL FASTENERS - GROUP 3 AND 5 (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 67 of 74 **BOEING SERVICE BULLETIN 737-53-1244 NOTES**  **QTY PART NUMBER**  **NAME TASK**  **STEP** Center the floor panels between floor beams and the temporarily installed floor panels in STEP 1. (b)Mark the fastener hole locations onto the pivot links and break panels from the existing fastener locations on the floor panels. (c)Apply one coat of Alodine 1200S on cut surfaces of fastener holes (Ref. SOPM 20-43-03). (d)Apply one coat of BMS 10-11, Type 1 primer to cut surfaces of fastener holes (Ref. SOPM 20-41-02). (e)

**FIGURE 10: DRILL HOLES FOR FLOOR PANEL FASTENERS - GROUP 3 AND 5 (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 68 of 74 **BOEING SERVICE BULLETIN 737-53-1244 This Figure applies only to: Group 1-5.** 

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 each pivot link.
**NOTES QTY**  **PART NUMBER NAME**  **TASK STEP**  (a) 1 143A5595-30 Bushing Strap Machine 1 (b)

- - Cad-Plate Apply 2 (c) (d)

- NAS1149C0663R Filler-Washer Install 3Machine the NAS538B6P037 bushing in the 143A5595-30 bushing strap. Maximum material removed is 0.06 inch. Contact the Boeing Company if more material needs to be removed. (a)Machine surface to 63 AA. Apply stylus cad plate. See SOPM 20-42-05 Bright Cadmium Plating for procedures. (b)Machine thickness to match material removed from the bushing in Bushing Strap 143A5595-30 to fill void. (c)

**FIGURE 11: BUSHING STRAP REWORK - GROUP 1, 2, 3, 4 AND 5 (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 69 of 74 **BOEING SERVICE BULLETIN 737-53-1244 NOTES**  **QTY PART NUMBER**  **NAME TASK**  **STEP** If filler-washer is machined then passivate the machined surface. See SOPM 20-30-03 Cleaning, Descaling and Surface Preparation of Ferrous Alloys for passivate procedures. (d)

**FIGURE 11: BUSHING STRAP REWORK - GROUP 1, 2, 3, 4 AND 5 (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 70 of 74 **BOEING SERVICE BULLETIN 737-53-1244 This Figure applies only to: Group 1-5.** 

**FIGURE 12: PIVOT LINK AND BUSHING PLATE MODIFICATION - GROUP 1, 2, 3, 4 AND 5 (SHEET 1 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 71 of 74 **BOEING SERVICE BULLETIN 737-53-1244**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 each pivot link assembly.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  To the dimensions shown. 1 143A5595-15 Pivot Link Mark 1 1 143A5595-15 Pivot Link Cut 2 Break all sharp edges. 1 143A5595-15 Pivot Link Deburr 3 To the cut surfaces. Refer to SOPM 20-43-03 as an accepted procedure. - Alodine 1200S Chemical Conver- sion Coating Apply 4

**FIGURE 12: PIVOT LINK AND BUSHING PLATE MODIFICATION - GROUP 1, 2, 3, 4 AND 5 (SHEET 2 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 72 of 74 **BOEING SERVICE BULLETIN 737-53-1244 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** To cut surfaces. Refer toSOPM 20-41-02 as an accepted procedure. - BMS 10-11, Type 1 Primer Apply 5

To the dimensions shown. 1 143A5595-15 Pivot Link Mark 6 1 143A5595-15 Pivot Link Cut 7 Break all sharp edges. 1 143A5595-15 Pivot Link Deburr 8 To the cut surfaces. Refer to SOPM 20-43-03 as an accepted procedure. - Alodine 1200S Chemical Conver- sion Coating Apply 9

To cut surfaces. Refer toSOPM 20-41-02 as an accepted procedure. - BMS 10-11, Type 1 Primer Apply 10

Refer to SOPM 20-50-10 rubber stamp method as an accepted procedure. 1 143A5595-27 Pivot Link Identify 11

To the dimensions shown. 1 143A5595-22 Bushing Plate Mark 12 1 143A5595-22 Bushing Plate Cut 13 Break all sharp edges. 1 143A5595-22 Bushing Plate Deburr 14 To the cut surfaces. Refer to SOPM 20-43-03 as an accepted procedure. - Alodine 1200S Chemical Conver- sion Coating Apply 15

To cut surfaces. Refer toSOPM 20-41-02 as an accepted procedure. - BMS 10-11, Type 1 Primer Apply 16

Refer to SOPM 20-50-10 rubber stamp method as an accepted procedure. 1 143A5595-31 Bushing Plate Identify 17

To the dimensions shown. 1 143A5595-23 Bushing Plate Mark 18 1 143A5595-23 Bushing Plate Cut 19 Break all sharp edges. 1 143A5595-23 Bushing Plate Deburr 20 To the cut surfaces. Refer to SOPM 20-43-03 as an accepted procedure. - Alodine 1200S Chemical Conver- sion Coating Apply 21

To cut surfaces. Refer toSOPM 20-41-02 as an accepted procedure. - BMS 10-11, Type 1 Primer Apply 22

**FIGURE 12: PIVOT LINK AND BUSHING PLATE MODIFICATION - GROUP 1, 2, 3, 4 AND 5 (SHEET 3 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 73 of 74 **BOEING SERVICE BULLETIN 737-53-1244 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Refer to SOPM 20-50-10 rubber stamp method as an accepted procedure. 1 143A5595-30 Bushing Plate Identify 23

**FIGURE 12: PIVOT LINK AND BUSHING PLATE MODIFICATION - GROUP 1, 2, 3, 4 AND 5 (SHEET 4 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 17, 2003 737-53-1244 Revision 5 July 27, 2011 74 of 74 **BOEING SERVICE BULLETIN 737-53-1244**