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

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ECCN: 9E991

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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Unpublished Work - All Rights Reserved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.

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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,

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3.0
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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

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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

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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

Original Issue: April 17, 2003

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Revision 1: May 29, 2003

Revision 2: March 15, 2007

Revision 3: December 04, 2008

Revision 4: April 06, 2011

Revision 5: July 27, 2011

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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.

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Refer 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.

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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.

GROUP CONFIGURATION DESCRIPTION

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:

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737-600, 737-700, 737-700C, 737-800, 737-900

Variable Number Group

YA001 - YA099 2

YA101 - YA118 2

YA119 - YA124 4

YA201 - YA211 4

YA221 4

YA231 - YA242 4

YA251 - YA256 4

YA271 - YA272 2

YA291 4

YA301 - YA302 4

YA311 - YA314 4

YA321 - YA322 4

YA323 2

YA336 - YA345 4

YA351 4

YA356 - YA357 4

YA366 - YA367 4

YA501 - YA536 4

YA541 - YA552 4

YA571 - YA578 4

YA601 - YA608 4

YA609 - YA610 2

YA611 - YA615 4

YA621 - YA622 4

YA626 4

YA627 - YA629 1

YA635 2

YA636 4

YA645 - YA648 4

YA656 - YA659 4

YA671 - YA672 4

YA681 - YA691 4

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BOEING SERVICE BULLETIN 737-53-1244
Variable Number Group

YA701 - YA706 4

YA721 - YA722 4

YA731 - YA734 1

YA751 - YA756 4

YA801 - YA803 2

YA809 2

YA811 - YA814 2

YA831 - YA834 4

YA841 - YA856 4

YA881 - YA882 2

YA891 - YA892 4

YA961 - YA969 4

YB001 - YB006 4

YB101 - YB118 1

YB151 - YB153 4

YB161 - YB162 4

YB171 - YB172 4

YB181 - YB183 4

YB201 - YB207 4

YB271 4

YB276 4

YB301 - YB309 4

YB501 - YB502 2

YB521 4

YB551 4

YB561 - YB562 4

YC001 - YC030 4

YC051 - YC082 4

YC091 - YC094 4

YC101 - YC104 4

YC111 - YC113 4

YC121 1

YC126 - YC127 4

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BOEING SERVICE BULLETIN 737-53-1244
Variable Number Group

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 4

YC426 2

YC427 - YC428 4

YC436 - YC437 4

YC441 - YC448 4

YC451 - YC455 4

YC459 4

YC461 - YC467 4

YC471 - YC493 4

YC501 - YC515 4

YC516 - YC526 1

YC571 - YC583 1

YC587 - YC589 4

YC591 - YC593 4

YC601 - YC655 4

YC681 - YC696 2

YC701 - YC707 4

YC708 - YC715 2

YC720 - YC725 2

YC727 2

YC728 - YC740 4

YC751 - YC752 4

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BOEING SERVICE BULLETIN 737-53-1244
Variable Number Group

YC761 - YC770 4

YC781 - YC793 4

YC801 - YC836 4

YC837 - YC880 2

YC881 - YC892 4

YC901 - YC907 4

YC921 4

YC931 - YC932 4

YC941 - YC950 4

YC971 - YC978 4

YC981 - YC983 4

YD001 - YD006 4

YD021 - YD022 1

YD023 - YD024 2

YD025 4

YD041 - YD055 4

YD081 - YD084 2

YD101 - YD107 4

YD121 - YD126 4

YD151 - YD154 4

YD171 - YD172 4

YD201 - YD203 4

YD206 - YD208 4

YD216 1

YD251 - YD254 4

YD256 4

YD301 - YD330 4

YD391 4

YD401 - YD410 4

YD481 - YD482 4

YD501 - YD507 1

YD531 - YD534 4

YD541 - YD547 4

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BOEING SERVICE BULLETIN 737-53-1244
Variable Number Group

YD601 - YD612 4

YE001 - YE020 4

YE051 1

YE101 - YE109 4

YE151 - YE157 4

YE171 - YE172 2

YE201 - YE203 2

YE301 - YE305 4

YG001 - YG044 4

YG061 - YG064 4

YG066 - YG087 4

YG501 - YG504 3

YG505 - YG506 5

YG601 - YG602 5

YJ471 - YJ477 4

YJ501 - YJ517 4

YJ631 - YJ632 4

YJ671 - YJ673 4

YJ871 4

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.

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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.

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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.

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— 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.

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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

Model Zone

737-600, 737-700, 737-800, 231, 232

737-900

Group 2:

Affected Maintenance Zones

Model Zone

737-600, 737-700, 737-800 231, 232

Group 3, 5:

Affected Maintenance Zones

Model Zone

737-700C 231, 232

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.

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BOEING SERVICE BULLETIN 737-53-1244
TABLE 1. PIVOT LINK REPAIR OR REPLACEMENT TIMES

CONDITION OPTIONAL ACTIONS COMPLIANCE TIME FOLLOW ON ACTION

Within 12 months after None

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 Revision

5 date of this service bulletin.

Within 12 months after

the original issue date

of this service bulletin.

Move the seats (a)

Within 12 months after None

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. Within 12 months after (b) and

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 Revision

5 date of this service bulletin.

Install new pivot link within

60 months after the Revision

5 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 Revision

5 date of this service bulletin.

Within 12 months after

the original issue date

of this service bulletin.

Move the seats (a)

Within 60 months after None

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. Within 12 months after (b) and

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 Revision

5 date of this service bulletin.

Install new pivot link within

60 months after the Revision

5 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)

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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

Task Number of Persons Task-Hours Elapsed Hours

Open Access 2 4 2

Remove Old Pivot Link 2 6 3

Install New Pivot Link 2 21 10.5 (a)

Close Access 2 4 2

TOTAL FOR EACH AIRPLANE 35 17.5 (a)

(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

Task Number of Persons Task-Hours Elapsed Hours

Open Access 2 4 2

Remove Old Pivot Link 2 7 3.5

Install New Pivot Link 2 26 13 (a)

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Group 3, 5:

Pivot Link Installation

Task Number of Persons Task-Hours Elapsed Hours

Close Access 2 4 2

TOTAL FOR EACH AIRPLANE 41 20.5 (a)

(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

Task Number of Persons Task-Hours Elapsed Hours

Open Access 2 4 2

Install Fasteners 2 10 5

Close Access 2 4 2

TOTAL FOR EACH AIRPLANE 18 9

Group 3, 5:

Centerline Fastener Installation

Centerline Fastener Installation - Group 3 and 5 Airplanes

Task Number of Persons Task-Hours Elapsed Hours

Open Access 2 4 2

Install Fasteners 2 12 6

Close Access 2 4 2

TOTAL FOR EACH AIRPLANE 20 10

H. Weight and Balance Changes

Group 1-5:

Pivot Link Installation

Change in Moment

(Pound-Inches)

Change in Weight

(Pounds)

Airplane

737-600 +0.4 +200

737-700 +0.4 +200

737-700C +0.4 +200

737-800 +0.4 +200

737-900 +0.4 +200

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BOEING SERVICE BULLETIN 737-53-1244
Group 2-5:

Centerline Fastener Installation

Change in Moment

(Pound-Inches)

Change in Weight

(Pounds)

Airplane

737-600 +0.2 +100

737-700 +0.2 +100

737-700C +0.2 +100

737-800 +0.2 +100

737-900 +0.2 +100

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.

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BOEING SERVICE BULLETIN 737-53-1244
3. Installation Drawings Used in the Preparation of this Service Bulletin:

Drawing Number Title

143A0060 Section 43 / 44 Lower Lobe Integration

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:

Publication Chapter-Section

737 Illustrated Parts Catalog 53-31

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.

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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)

Kit Number Name

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

002A0018-2 (b) TOP KIT - PIVOT LINK - -

002A0018-3 KIT - PIVOT LINK 88 $23,210.00

002A0018-4 KIT - PIVOT LINK 88 $20,689.00

(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.

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BOEING SERVICE BULLETIN 737-53-1244
Airplane Group Use Kit Use Kit

1, 2 and 4 002A0018-1 (a)(b) 002A0018-3

3 and 5 002A0018-2 (c)(d) 002A0018-4

(a) Kit not available. Replaced by 002A0018-3.

(b) To change a 002A0018-1 top kit to a 002A0018-3 top kit, rework the 143A5595-15

pivot 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 143A5595-15

pivot link, 143A5595-22 bushing strap and 143A5595-23 bushing strap as given in Accomplishment Instructions paragraph 3.B. Part IV., 2. b.

Kit 002A0018

Existing Part Num- Notes

ber

New Part Number QTY Name

-2 -1

002A0018-1 . - Top Kit, Pivot Link - (a)(b)

002A0018-2 - . Top Kit, Pivot Link - (d)(e)

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

100A5001-2 1 - Pivot Link Kit - (f)

100A5001-3 1 . Foam - -

143A5595-4 and 65- (g) (h) (i)

46813-137

143A5595-15 5 4 Pivot Link Assy

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

143A5595-23 5 4 Pivot Link Assy, Bushing Strap - -

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

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

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

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

143A5240-2 2 2 Plate 143A5240-2 (g) (i)

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

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

BACB28Y4C178 5 4 Bushing BACB28Y4C138 (i)

BACB30LH3DK4 4 . Bolt - (j)

BACB30US4K29D 5 4 Bolt BACB30NR4DK23 (i) (j)

BACB30VT8K5 22 18 Bolt - (j) (k)

BACB30YP8K2 11 14 Bolt - (j) (k)

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Kit 002A0018

Existing Part Num- Notes

ber

New Part Number QTY Name

-2 -1

BACB30YP8K3 . 3 Bolt - (j)

BACB30YP8K4 . 3 Bolt - (j)

BACC30BL8 32 37 Collar - (k)

BACN10JD103CD 4 . Nut -

BACN10VR1CG 20 20 Clipnut - (k)

BACN10VR3CG 33 27 Clipnut - (k)

BACP18BC02A06P 9 4 Cotter Pin MS24665-134 (l)

BACP18BC02A08P 5 4 Cotter Pin MS24665-155 (l)

BACR15GF4D3 66 66 Rivet - (k)

BACS12GP3L16 60 57 Screw - (k)

NAS1149D0363J 4 . Washer - -

143A5240U31 2 2 Panel Break Detail 143A5240-6 (g) (i) (m)

143A5240U33 . 1 Panel Break Detail 143A5240-9 (g) (i) (m)

143A5240U34 . 1 Panel Break Detail 143A5240-10 (g) (i) (m)

143A5240U37 . 1 Panel Break Detail 143A5240-15 (g) (i) (m)

143A5240U38 . 1 Panel Break Detail 143A5240-16 (g) (i) (m)

143A5240U41 1 . Panel Break Detail 143A5240-23 (g) (i) (m)

143A5240U42 1 . Panel Break Detail 143A5240-24 (g) (i) (m)

143A5240U45 2 . Panel Break Detail 143A5240-29 (g) (i) (m)

(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

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Kit 002A0018

Existing Part Num- Notes

ber

New Part Number QTY Name

-2 -1

(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

Existing Part Num- Notes

ber

New Part Number QTY Name

-4 -3

002A0018-3 . - TOP KIT - PIVOT LINK - (a)

002A0018-4 - . TOP KIT - PIVOT LINK - (b)

100A5001-4 . 1 KIT - PIVOT LINK - (c)

100A5001-5 1 . KIT - PIVOT LINK - (d)

(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

New Part Number QTY Name Existing Part Number Notes

-5 -4

100A5001-3 1 . KIT-PIVOT LINK - -

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

143A5240-11 . 1 PLATE - (a) (b)

143A5240-12 . 1 PLATE - (a) (b)

143A5240-13 . 1 PLATE - (a) (b)

143A5240-14 . 1 PLATE - (a) (b)

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BOEING SERVICE BULLETIN 737-53-1244
Kit 100A5001

New Part Number QTY Name Existing Part Number Notes

-5 -4

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

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

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

143A5240U33 . 1 PANEL BREAK DETAIL - (a) (b) (c)

143A5240U34 . 1 PANEL BREAK DETAIL - (a) (b) (c)

143A5240U37 . 1 PANEL BREAK DETAIL - (a) (b) (c)

143A5240U38 . 1 PANEL BREAK DETAIL - (a) (b) (c)

143A5240U41 1 . PANEL BREAK DETAIL - (a) (b) (c)

143A5240U42 1 . PANEL BREAK DETAIL - (a) (b) (c)

143A5240U45 2 . PANEL BREAK DETAIL - (a) (b) (c)

143A5595-15, (a) (b) (d)

143A5595-4 and 65-

46813-137

143A5595-27 5 4 PIVOT LINK ASSY STA 520-540

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

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

BACB28AK05-170 5 4 BUSHING, PLAIN - -

BACB28Y4C178 5 4 BUSHING, PLAIN BACB28Y4C138 (b)

BACB30LH3DK4 4 . BOLT - (e)

BACB30NR5DK29 5 4 BOLT - -

BACB30US4K29D 5 4 BOLT BACB30NR4DK23 (b) (e)

BACB30VT8K5 22 18 BOLT - (e) (f)

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

BACB30YP8K3 . 3 BOLT, 100 DEG HEX DR - (e)

BACB30YP8K4 . 3 BOLT, 100 DEG HEX DR - (e)

BACC30BL8 32 37 COLLAR - (f)

BACN10JD103CD 4 . NUT, CASTELLATED - -

BACN10JD4CD 5 4 NUT, CASTELLATED - -

BACN10VR1CG 20 20 CLIP NUT - (f)

BACN10VR3CG 33 27 CLIP NUT - (f)

BACP18BC02A06P 9 4 PIN, COTTER MS24665-134 (g)

BACP18BC02A08P 5 4 PIN MS24665-155 (g)

BACR15GF4D3 66 66 RIVET, 100 DEG - (f)

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BOEING SERVICE BULLETIN 737-53-1244
Kit 100A5001

New Part Number QTY Name Existing Part Number Notes

-5 -4

BACS12GP3L16 60 57 FLOOR PANEL SCREWS - (f)

NAS1149D0363J 4 . WASHER, FLAT - -

(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:

Part Number / Specification QTY Name Notes

BACB30NN5K6 (a) Bolt (b)

NAS1149D0563J (a) Washer (b)

NAS1149C0663R or equivalent CRES (h) Washer (h)

material

NAS1805-5L (a) Nut (b)

MS21140 - Blind Fastener (g)

(Alodine 1200S) MIL-C-5541 16 ounces Chemical Conversion Coating (c)(d)

BMS 10-11, Type 1 16 ounces Primer (c)(e)

BMS 5-95, Class B -1/2, -2, -4 16 ounces Sealant (c)(e)

BAC 5010 TYPE 79 or TYPE 60 8 ounces Adhesive (c)(f)

(a) For Group 2 and 4 airplanes quantity of 28 bolts, washers and nuts are needed.

For Group 3 and 5 airplanes quantity of 35 bolts, washers and nuts are needed.

(b) Refer to 737 Structural Repair Manual Chapter 51 for alternative fasteners.

(c) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data.

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BOEING SERVICE BULLETIN 737-53-1244
Part Number / Specification QTY Name Notes

(d) Also refer to SOPM 20-43-03 for supplier data.

(e) Also refer to SOPM 20-30-11 for supplier data.

(f) Also refer to SOPM 20-50-12 for supplier data.

MS21140 blind fastener is optional to BACB30NN5K6 Bolt, NAS1149D0563J Washer, and NAS1805-

5L Nut.

(g)

(h) Used for Bushing Strap 143A5595-30 rework. Quantity as needed, one for each pivot link.

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:

Tool Kit Number Name Daily Price Monthly Price

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)

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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.

Tool Kit Number Name

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.

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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.

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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

Location of Forward Stud Description of Location See Section 1.E Compliance For

BS 521.95 to BS 533.95 - Group 2 and 3

BS 534.95 Third to last lip on the seat track Group 1

BS 535.95 Second to last lip on the seat track Group 1

BS 536.95 Last lip on the seat track Group 1

Aft of BS 536.95 - Group 4 and 5

TABLE 2. PASSENGER SEATS WITH THREE STUDS ON THE AFT LEG

Location of Forward Stud Description of Location See Section 1.E Compliance For

BS 521.95 to BS 533.95 - Group 2 and 3

BS 534.95 Third to last lip on the seat track Group 1

BS 535.95 Second to last lip on the seat track Group 1

BS 536.95 Last lip on the seat track Group 4 and 5

Aft of BS 536.95 - Group 4 and 5

b. If the location of the passenger seats have not been moved since delivery of the airplane then

continue to PART II - ACCESS.

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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.

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(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.

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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.

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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)

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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.

STEP TASK NAME PART NUMBER QTY NOTES

1 Drill Fastener Holes - 7 Four Locations (a)

2 Countersink Fastener Holes - 7 - Four Locations

- 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 Coating3 Apply

Apply one coat to countersink and

fastener hole. (d)

(Reference BMS 10- -

11, Type 1)

4 Apply Primer

SEE FASTENER 7 Four Locations (e)

CODE TABLE

5 Install Fasteners

6 Check Gap 1 - Four Locations

- Minimum Gap of 0.20 inch between

pivot 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 737-600 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)

(c) Refer to SOPM 20-43-03 for procedures to apply chemical conversion coating.

(d) Refer to SOPM 20-41-02 for procedures to apply primer.

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.

CODE NAME PART NUMBER HOLE DIA. NOTES

A Bolt BACB30NN5K6 0.313 - 0.327 (a)

Washer NAS1149D0563J -

Nut NAS1805-5L -

FIGURE 1: CENTERLINE FASTENER INSTALLATION - GROUP 2 AND 4

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 737-53-1244
CODE NAME PART NUMBER HOLE DIA. NOTES

(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)

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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)

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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.

STEP TASK NAME PART NUMBER QTY NOTE

1 Drill Fastener Holes - 7 Five Locations (a)

2 Countersink Fastener Holes - 7 - Five locations

- 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 Coating3 Apply

Apply one coat to countersink and

fastener hole. (d)

(Reference BMS 10- -

11, Type 1)

4 Apply Primer

SEE FASTENER 7 Five Locations (e)

CODE TABLE

5 Install Fasteners

6 Check Gap 1 - Five Locations

- Minimum Gap of 0.20 inch between

pivot 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)

(c) Refer to SOPM 20-43-03 for procedures to apply chemical conversion coating.

(d) Refer to SOPM 20-41-02 for procedures to apply primer.

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

CODE NAME PART NUMBER HOLE DIA. NOTES

A Bolt BACB30NN5K6 0.313 - 0.327 (a)

Washer NAS1149D0563J -

Nut NAS1805-5L -

(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)

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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)

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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)

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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.

STEP TASK NAME PART NUMBER QTY NOTES

Twelve fasteners for each Seat

Track

1 Remove / Discard Seat Track 65-46813-137 4

Floor Beams and - - -

Crease Beams

2 Mark

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.

3 Remove / Discard Break Panel 143A5240-( ) 6 -

The Fillers are between the

Pivot Link and the Break Panels at Body Line 0.0 only.

4 Remove / Keep Fillers 143A5240-17 2

One for each Pivot link at forward end of Pivot link.5 Remove / Discard Cotter Pin - 4

Remove / Keep Nut BACN10JD5CD 4

Remove / Keep Washer NAS1149E0563P 4

Remove / Keep Bolt BACB30NR5DK29 4

Remove / Keep Bushing BACB28AK05-170 4

One for each Pivot link at aft

end of pivot link.

6 Remove / Discard Cotter Pin - 4

Remove / Keep Nut BACN10JD4CD 4

Remove / Keep Washer NAS1149E0463P 4

Remove / Discard Bolt - 4

Remove / Discard Bushing - 4

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

FIGURE 3: BREAK PANEL, SEAT TRACK AND PIVOT LINK REMOVAL - GROUP 1, 2 AND 4

(SHEET 3 OF 3)

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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)

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BOEING SERVICE BULLETIN 737-53-1244
FIGURE 4: PIVOT LINK INSTALLATION - GROUP 1, 2 AND 4

(SHEET 2 OF 4)

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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.

STEP TASK NAME PART NUMBER QTY NOTES

1 Align Pivot Link 143A5595-27 1 4 Locations (a)

2 Position Bushing Strap 143A5595-31 1 4 Locations (b) (c)

3 Position Bushing Strap 143A5595-30 1 4 Locations (b) (c)

4 Locations - Assemble the

Bushing, Bolt, Washer and

Nut. Do not tighten the Bolt

and Nut.

4 Insert New Bushing BACB28Y4C178 1

5 Insert New Bolt BACB30US4K29D 1

6 Install Kept Washer NAS1149E0463P 1

7 Install Kept Nut BACN10JD4CD 1

4 Locations - Assemble the

Bushing, Bolt, Washer and

Nut. Do not tighten. the Bolt

and Nut.

8 Insert Kept Bushing BACB28AK05-170 1

9 Insert Kept Bolt BACB30NR5DK29 1

10 Install Kept Washer NAS1149E0563P 1

11 Install Kept Nut BACN10JD5CD 1

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

13 Clamp Bushing Straps 143A5595-30 and -31 - 4 Locations (c)

14 Inspect Pivot link 143A5595-27 1 4 Locations (f)

Through the Bushing Straps

into the Pivot Link (4 Locations) (d)

15 Match Drill Holes - 4

SEE FASTENER 4 4 Locations

CODE TABLE

Bolts

Collars

16 Install

4

17 Tighten Kept Nut BACN10JD4CD 1 4 Locations

18 Install New Cotter Pin BACP18BC02A08P 1 4 Locations (e)

19 Tighten Kept Nut BACN10JD5CD 1 4 Locations

20 Install New Cotter Pin BACP18BC02A06P 1 4 Locations (e)

(a) Align the Pivot Link with the section 44 seat track crown using MIT002A0018-1 Locating Jig.

(b) Locate by aligning with bolt and bushing shown in steps 4 and 5.

(c) Make sure the Bushing Straps are up against the lower side of the top flange of the Pivot Link.

(d) Drill holes 0.250 - 0.254 for the bolt. Install the collar on outer edge of the pivot link.

(e) Refer to SOPM 20-50-02 for procedures to install cotter pin.

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)

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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.

CODE NAME PART NUMBER HOLE DIA. NOTES

Install collar against bushing

strap.

A Bolt BACB30VT8K5 0.250 - 0.254

Collar BACC30BL8

FIGURE 4: PIVOT LINK INSTALLATION - GROUP 1, 2 AND 4

(SHEET 4 OF 4)

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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)

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BOEING SERVICE BULLETIN 737-53-1244
FIGURE 5: BREAK PANEL INSTALLATION - GROUP 1, 2 AND 4

(SHEET 2 OF 4)

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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.

STEP TASK NAME PART NUMBER QTY NOTES

RBL 60 - RBL 45.5

1 Position Break Panel 143A5240U38 1 (a)

Match Drill Fastener Holes - (e) (f) (g)

2 Position Plate 143A5240-14 1 (b)

Match Drill Fastener Holes - (e) (f) (g)

RBL 45.5 - RBL 24.75

3 Position Break Panel 143A5240U31 1 (c)

Match Drill Fastener Holes - (e) (f) (g)

4 Position Plate 143A5240-2 1 (d)

Match Drill Fastener Holes - (e) (f) (g)

RBL 24.75 - BL 0.0

5 Position / Kept Filler 143A5240-17 1 -

6 Position Break Panel 143A5240U34 (c)

Match Drill Fastener Holes - (e) (f) (g)

7 Position Plate 143A5240-12 1

Match Drill Fastener Holes - (e) (f) (g)

BL 0.0 - LBL 24.75

8 Position / Kept Filler 143A5240-17 1 -

9 Position Break Panel 143A5240U33 1 (c)

Match Drill Fastener Holes - (e) (f) (g)

10 Position Plate 143A5240-11 1

Match Drill Fastener Holes - (e) (f) (g)

LBL 24.75 - LBL 45.5

11 Position Break Panel 143A5240U31 1 (c)

Match Drill Fastener Holes - (e) (f) (g)

12 Position Plate 143A5240-2 1 (d)

Match Drill Fastener Holes - (e) (f) (g)

LBL 45.5 - LBL 60

13 Position Break Panel 143A5240U37 1 (a)

FIGURE 5: BREAK PANEL INSTALLATION - GROUP 1, 2 AND 4

(SHEET 3 OF 4)

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BOEING SERVICE BULLETIN 737-53-1244
STEP TASK NAME PART NUMBER QTY NOTES

Match Drill Fastener Holes - (e) (f) (g)

14 Position Plate 143A5240-13 1 (b)

Match Drill Fastener Holes - (e) (f) (g)

RBL 60 - LBL 60

15 Apply Sealant BMS 5-95 - (h)

16 Install Parts - - See Fastener Codes

(a) Position to match original position of the old break panel on the crease beam.

(b) Position to match contour of new Break Panel at end in common with crease beam.

(c) Position to match original position of the old break panel on the floor beams.

(d) Position the Plate so DISTANCE A and DISTANCE B are equal.

(e) Apply one coat of Alodine 1200S on cut surfaces of fastener holes (Ref. SOPM 20-43-03).

(f) Apply one coat of BMS 10-11, Type 1 primer to cut surfaces of fastener holes (Ref. SOPM 20-41-02).

(g) Maintain an edge margin of 1.6D to 1.8D.

(h) Apply sealant on faying surface between the Break Panels and Floor Beams (Ref. SOPM 20-50-19)

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.

CODE NAME PART NUMBER HOLE DIA. NOTES

A Bolt BACB30YP8K( ) 0.247 - 0.250 100 Degree countersink on top side.

Collar BACC30BL8 - -

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

FIGURE 5: BREAK PANEL INSTALLATION - GROUP 1, 2 AND 4

(SHEET 4 OF 4)

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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.

STEP TASK NAME PART NUMBER QTY NOTES

1 Locate / Kept Floor Panels 143A5810-( ) 3 (a)

2 Install / Kept Nutclips and Screws - 9 -

3 Align / Kept Floor Panels 143A5810-( ) 2 (b)

4 Mark Location Fastener Holes - - (c)

5 Remove Floor Panels 143A5810-( ) 5 -

6 Drill Fastener Holes - - (d)(e)

7 Install Floor Panels 143A5810-( ) 5 Temporarily Install

Into new Break Panels

(d)(e)

8 Match Drill Fastener Holes - -

Locate 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)

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BOEING SERVICE BULLETIN 737-53-1244
STEP TASK NAME PART NUMBER QTY NOTES

(b) Center the floor panels between the pivot links, floor beams and attached floor panels in STEP 1.

Mark the fastener hole locations onto the pivot links and break panels from the existing fastener locations

on the floor panels.

(c)

(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).

FIGURE 6: DRILL HOLES FOR FLOOR PANEL FASTENERS - GROUP 1, 2 AND 4

(SHEET 2 OF 2)

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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)

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BOEING SERVICE BULLETIN 737-53-1244
FIGURE 7: BREAK PANEL, SEAT TRACK AND PIVOT LINK REMOVAL - GROUP 3 AND 5

(SHEET 2 OF 3)

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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.

STEP TASK NAME PART NUMBER QTY NOTES

Twelve fasteners for each

Seat Track

1 Remove / Discard Seat Track 65-46813-137 5

Floor Beams and - - -

Crease Beams

2 Mark

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.

3 Remove / Discard Break Panels 143A5240-( ) 6 -

One for each Pivot link at

forward end of Pivot link.

4 Remove / Discard Cotter Pin - 5

Remove / Keep Nut BACN10JD5CD 5

Remove / Keep Washer NAS1149E0563P 5

Remove / Keep Bolt BACB30NR5DK29 5

Remove / Keep Bushing BACB28AK05-170 5

One for each Pivot link at

aft end of Pivot link.

5 Remove / Discard Cotter Pin - 5

Remove / Keep Nut BACN10JD4CD 5

Remove / Keep Washer NAS1149E0463P 5

Remove / Discard Bolt - 5

Remove / Discard Bushing - 5

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

FIGURE 7: BREAK PANEL, SEAT TRACK AND PIVOT LINK REMOVAL - GROUP 3 AND 5

(SHEET 3 OF 3)

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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)

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BOEING SERVICE BULLETIN 737-53-1244
FIGURE 8: PIVOT LINK INSTALLATION - GROUP 3 AND 5

(SHEET 2 OF 4)

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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.

STEP TASK NAME PART NUMBER QTY NOTES

1 Align Pivot Link 143A5595-27 1 5 Locations (a)

2 Position Bushing Strap 143A5595-31 1 5 Locations (b)

3 Position Bushing Strap 143A5595-30 1 5 Locations (b)

4 Insert New Bushing BACB28Y4C178 1 5 Locations

5 Insert New Bolt BACB30US4K29D 1 5 Locations

6 Install Kept Washer NAS1149E0463P 1 5 Locations

7 Install Kept Nut BACN10JD4CD 1 5 Locations

8 Install Kept Bushing BACB28AK05-170 1 5 Locations

9 Install Kept Bolt BACB30NR5DK29 1 5 Locations

10 Install Kept Washer NAS1149E0563P 1 5 Locations

11 Install Kept Nut BACN10JD5CD 1 5 Locations

FIGURE 8: PIVOT LINK INSTALLATION - GROUP 3 AND 5

(SHEET 3 OF 4)

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BOEING SERVICE BULLETIN 737-53-1244
STEP TASK NAME PART NUMBER QTY NOTES

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

13 Clamp Bushing Strap 143A5595-30 and -31 - 5 Locations (c)

14 Inspect Pivot link 143A5595-27 1 5 Locations (h)

Through the Bushing

Straps into the Pivot Link

(5 Locations) (d)

15 Match Drill Holes - 4

SEE FASTENER 4 5 Locations

CODE TABLE

Bolts

Collars

16 Install

4

17 Tighten Kept Nut BACN10JD4CD 1 5 Locations

18 Install New Cotter Pin BACP18BC02A08P 1 5 Locations (e)

19 Tighten Kept Nut BACN10JD5CD 1 5 Locations

20 Install New Cotter Pin BACP18BC02A06P 1 5 Locations (e)

21 Install Foam 100A5001-3 1 5 Locations (f) (g)

(a) Align the Pivot Link with the seat track crown using MIT002A0018-1 Locating Jig.

(b) Locate by aligning with bolt and bushing shown in steps 4 and 5.

(c) Make sure the Bushing Straps are nested against lower side of seat track flange.

(d) Drill holes 0.250 - 0.254 for the bolt. Install the collar on outer edge of the pivot link.

(e) See SOPM 20-50-02 for procedures to install cotter pin.

(f) Trim foam strip 0.5 inch wide and 3.3 inches long to fit the gap.

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.

CODE NAME PART NUMBER HOLE DIA. NOTES

A Bolt BACB30VT8K5 0.250 - 0.254 Install collar against bushing strap.

Collar BACC30BL8

FIGURE 8: PIVOT LINK INSTALLATION - GROUP 3 AND 5

(SHEET 4 OF 4)

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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)

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BOEING SERVICE BULLETIN 737-53-1244
FIGURE 9: BREAK PANEL INSTALLATION - GROUP 3 AND 5

(SHEET 2 OF 4)

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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.

STEP TASK NAME PART NUMBER QTY NOTES

RBL 60 - RBL 45.5

1 Position Break Panel 143A5240U42 1 (a)

Match Drill Fastener Holes - (e) (f) (g)

2 Position Plate 143A5240-21 1 (b)

Match Drill Fastener Holes - (e) (f) (g)

RBL 45.5 - RBL 24.75 and LBL 45.5 - LBL 24.75

3 Position Break Panel 143A5240U31 1 (c)

Match Drill Fastener Holes - (e) (f) (g)

4 Position Plate 143A5240-2 1 (d)

Match Drill Fastener Holes - (e) (f) (g)

RBL 24.75 - LBL 24.75

5 Position Break Panel 143A5240U45 (c)

Match Drill Fastener Holes - (e) (f) (g)

6 Position Plate 143A5240-27 1 (d)

Match Drill Fastener Holes - (e) (f) (g)

LBL 45.5 - LBL 60

7 Position Break Panel 143A5240U41 1 (a)

Match Drill Fastener Holes - (e) (f) (g)

8 Position Plate 143A5240-21 1 (b)

Match Drill Fastener Holes - (e) (f) (g)

RBL 60 - LBL 60

9 Apply Sealant BMS 5-95 - (h)

10 Install Parts - - See Fastener Codes

NOTE:

See note (b) for Code A in Fastener Code Table for special instructions to install fasteners in common with

the crease beam.

(a) Position to match original position of the old break panel on the outboard seat track.

(b) Position to match contour of new Break Panel at end in common with the outboard seat track.

(c) Position to match original position of the old break panel on the floor beams.

(d) Position the Plate so distance A and DISTANCE B are equal.

FIGURE 9: BREAK PANEL INSTALLATION - GROUP 3 AND 5

(SHEET 3 OF 4)

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BOEING SERVICE BULLETIN 737-53-1244
STEP TASK NAME PART NUMBER QTY NOTES

(e) Apply one coat of Alodine 1200S on cut surfaces fastener holes (Ref. SOPM 20-43-03).

(f) Apply one coat of BMS 10-11, Type 1 primer to surfaces of fastener holes (Ref. SOPM 20-41-02).

(g) Maintain an edge margin of 1.6D to 1.8D.

(h) Apply sealant on faying surface between the Break Panels and Floor Beams (Ref. SOPM 20-50-19).

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

CODE NAME PART NUMBER HOLE DIA. NOTES

A Bolt BACB30LH3DK4 0.190 - 0.194 100 Degree countersink on top side.(a)

Washer NAS1149D0363J - -

Nut BACN10JD103CD - (b)

Cotter Pin BACP18BC02A06P - (b)

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

Collar BACC30BL8 -

C Rivet BACR15GF4D3 0.128 - 0.134 100 Degree countersink on top side.

(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)

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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.

STEP TASK NAME PART NUMBER QTY NOTES

1 Locate / Kept Floor Panels 143A5810-( ) 2 (a)

2 Install / Kept Nutclips and Screws - - -

3 Align / Kept Floor Panels 143A5810-( ) 4 (b)

4 Mark Location Fastener Holes - - (c)

5 Remove Floor Panels 143A5810-( ) 6 -

6 Drill Fastener Holes - - (d) (e)

7 Install Floor Panels 143A5810-( ) 5 Temporarily install

Into new Break Panels (d)

(e)

8 Match Drill Fastener Holes - -

Locate 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)

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BOEING SERVICE BULLETIN 737-53-1244
STEP TASK NAME PART NUMBER QTY NOTES

(b) Center the floor panels between floor beams and the temporarily installed floor panels in STEP 1.

Mark the fastener hole locations onto the pivot links and break panels from the existing fastener locations

on the floor panels.

(c)

(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).

FIGURE 10: DRILL HOLES FOR FLOOR PANEL FASTENERS - GROUP 3 AND 5

(SHEET 2 OF 2)

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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.

STEP TASK NAME PART NUMBER QTY NOTES

1 Machine Bushing Strap 143A5595-30 1 (a)

2 Apply Cad-Plate - - (b)

3 Install Filler-Washer NAS1149C0663R - (c) (d)

Machine 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)

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BOEING SERVICE BULLETIN 737-53-1244
STEP TASK NAME PART NUMBER QTY NOTES

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)

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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)

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Mark Pivot Link 143A5595-15 1 To the dimensions shown.

2 Cut Pivot Link 143A5595-15 1

3 Deburr Pivot Link 143A5595-15 1 Break all sharp edges.

To the cut surfaces. Refer

to SOPM 20-43-03 as an

accepted procedure.

Chemical Conver- Alodine 1200S -

sion Coating

4 Apply

FIGURE 12: PIVOT LINK AND BUSHING PLATE MODIFICATION - GROUP 1, 2, 3, 4 AND 5

(SHEET 2 OF 4)

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BOEING SERVICE BULLETIN 737-53-1244
STEP TASK NAME IDENTIFICATION QTY MORE DATA

To cut surfaces. Refer to

SOPM 20-41-02 as an accepted procedure.

5 Apply Primer BMS 10-11, Type 1 -

6 Mark Pivot Link 143A5595-15 1 To the dimensions shown.

7 Cut Pivot Link 143A5595-15 1

8 Deburr Pivot Link 143A5595-15 1 Break all sharp edges.

To the cut surfaces. Refer

to SOPM 20-43-03 as an

accepted procedure.

Chemical Conver- Alodine 1200S -

sion Coating

9 Apply

To cut surfaces. Refer to

SOPM 20-41-02 as an accepted procedure.

10 Apply Primer BMS 10-11, Type 1 -

Refer to SOPM 20-50-10

rubber stamp method as an

accepted procedure.

11 Identify Pivot Link 143A5595-27 1

12 Mark Bushing Plate 143A5595-22 1 To the dimensions shown.

13 Cut Bushing Plate 143A5595-22 1

14 Deburr Bushing Plate 143A5595-22 1 Break all sharp edges.

To the cut surfaces. Refer

to SOPM 20-43-03 as an

accepted procedure.

Chemical Conver- Alodine 1200S -

sion Coating

15 Apply

To cut surfaces. Refer to

SOPM 20-41-02 as an accepted procedure.

16 Apply Primer BMS 10-11, Type 1 -

Refer to SOPM 20-50-10

rubber stamp method as an

accepted procedure.

17 Identify Bushing Plate 143A5595-31 1

18 Mark Bushing Plate 143A5595-23 1 To the dimensions shown.

19 Cut Bushing Plate 143A5595-23 1

20 Deburr Bushing Plate 143A5595-23 1 Break all sharp edges.

To the cut surfaces. Refer

to SOPM 20-43-03 as an

accepted procedure.

Chemical Conver- Alodine 1200S -

sion Coating

21 Apply

To cut surfaces. Refer to

SOPM 20-41-02 as an accepted procedure.

22 Apply Primer BMS 10-11, Type 1 -

FIGURE 12: PIVOT LINK AND BUSHING PLATE MODIFICATION - GROUP 1, 2, 3, 4 AND 5

(SHEET 3 OF 4)

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BOEING SERVICE BULLETIN 737-53-1244
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Refer to SOPM 20-50-10

rubber stamp method as an

accepted procedure.

23 Identify Bushing Plate 143A5595-30 1

FIGURE 12: PIVOT LINK AND BUSHING PLATE MODIFICATION - GROUP 1, 2, 3, 4 AND 5

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