# Boeing Alert Service Bulletin 737-28A1216: Revision 2

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- Document: [Boeing Alert Service Bulletin 737-28A1216](https://openairdocs.org/service-documents/boeing/737-28a1216.md)
- Title as filed: SB-737-28A1216-02--BOEING
- Pages: 439
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### Page 1

Commercial
Airplanes
737
Service Bulletin
Number: 737-28A1216
Original Issue: July 29, 2010
Revision 2: November 12, 2012
ATA System: 2822
SUBJECT: FUEL - Engine Fuel Feed System - Installation of the Auto Shutoff Protection for the
Center and Auxiliary Fuel Tank Boost Pumps
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 300-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET
Copyright © 2010 Boeing.
Unpublished Work. All Rights Reserved.
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document
are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The
Boeing Company.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner™,
BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and Boeing
liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in connection
with this document unless provided in writing by Boeing. BOEING is a trademark of Boeing Management
Company.
Original Issue: July 29, 2010
737-28A1216Revision 2: November 12, 2012
1 of 439
7.0

### Page 2

Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: July 29, 2010
737-28A1216Revision 2: November 12, 2012
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BOEING SERVICE BULLETIN 737-28A1216
BLANK PAGE

### Page 3

Table of Contents
Revision Transmittal Sheet ............................................ 7
S u m m a r y..................................................... 1 1
1. PLANNING INFORMATION ........................................ 1 9
A . E f f e c t i v i t y  ............................................... 1 9
1. Airplanes ............................................ 1 9
2 . S p a r e s  A f f e c t e d  ........................................ 3 0
B. Concurrent Requirements ...................................... 3 0
C. Reason ................................................ 3 0
D . D e s c r i p t i o n  .............................................. 3 2
E. Compliance .............................................. 3 8
F . A p p r o v a l  ............................................... 3 8
G. Manpower .............................................. 3 9
H. Weight and Balance Changes .................................... 8 5
I. Electrical Load Data ......................................... 8 5
J . R e f e r e n c e s  .............................................. 8 6
1. Existing Data: ......................................... 8 6
2. Data Supplied with this Service Bulletin: ........................... 8 6
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 8 6
K. Publications Affected ........................................ 8 7
L. Interchangeability and Intermixability of Parts ........................... 8 7
M. Software Accomplishment Summary ................................ 8 7
2. MATERIAL INFORMATION ........................................ 8 9
A. Material - Price and Availability ................................... 8 9
B. Industry Support Information .................................... 9 2
C . P a r t s  N e c e s s a r y  f o r  E a c h  A i r p l a n e  ................................. 9 2
1 . K i t s / P a r t s :  ........................................... 9 2
2. Parts and Materials Supplied by the Operator: ....................... 1 1 8
3. Parts Modified and Reidentified: ............................... 1 1 9
4. Parts Removed and Not Replaced: ............................. 1 1 9
D. Parts Necessary to Change Spares ................................ 1 1 9
E. Special Tooling - Price and Availability .............................. 1 1 9
F. Special Tooling Necessary to do this Service Bulletin ...................... 1 1 9
3. ACCOMPLISHMENT INSTRUCTIONS ................................. 1 2 1
A. GENERAL INFORMATION .................................... 1 2 1
B. WORK INSTRUCTIONS ...................................... 1 2 2
FIGURE 1: REMOVAL OF THE J2802 BOX ASSEMBLY COVER [Group 1-13, 15-16] ........ 1 4 9
FIGURE 2: REMOVAL OF THE J2802 BOX ASSEMBLY COVER [Group 19-20] ........... 1 5 0
FIGURE 3: LABELS INSTALLATION, AND WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802
BOX ASSEMBLY [Group 1-13, 15-16] ............................ 1 5 1
FIGURE 4: CONNECTION OF THE WIRE BUNDLE W1760 [Group 1-16, 21-29, 31] ......... 1 5 4
FIGURE 5: CONNECTION OF THE WIRE BUNDLE W1770 [Group 1-16, 21-29, 31] ......... 1 5 7
FIGURE 6: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY [Group 19-20]
................................................. 1 6 0
FIGURE 7: CONNECTION OF THE WIRE BUNDLE W1760 [Group 17-20, 30] ............ 1 6 3
FIGURE 8: CONNECTION OF THE WIRE BUNDLE W1760 [Group 17-20, 30] ............ 1 6 5
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### Page 4

FIGURE 9: CONNECTION OF THE WIRE BUNDLE W1770 [Group 17-20, 30] ............ 1 6 8
FIGURE 10: CONNECTION OF THE WIRE BUNDLE W1770 [Group 17-20, 30] ............ 1 7 0
FIGURE 11: INSTALLATION OF THE J2802 BOX ASSEMBLY COVER [Group 1-13, 15-16, 19-20] . 173
FIGURE 12: ATTACHMENT OF THE J2802 BOX ASSEMBLY [Group 1-13, 15-16] .......... 1 7 4
FIGURE 13: ATTACHMENT OF THE J2802 BOX ASSEMBLY [Group 19-20] ............. 1 7 7
FIGURE 14: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND E3 SUPPORT POST [Group
1 - 1 3 ,  1 5 - 1 6 ,  1 9 - 2 0 ]  ...................................... 1 8 0
FIGURE 15: PREPARATION OF THE J2802 BOX ASSEMBLY, E2 AND E3 SUPPORT POSTS [Group 1-13,
1 5 - 1 6 ,  1 9 - 2 0 ]  ......................................... 1 8 3
FIGURE 16: INSTALLATION THE J2802 BOX ASSEMBLY ON THE E2 AND E3 SUPPORT POSTS [Group
1 - 1 3 ,  1 5 - 1 6 ]  .......................................... 1 8 5
FIGURE 17: INSTALLATION THE J2802 BOX ASSEMBLY ON THE E2 AND E3 SUPPORT POSTS [Group
1 9 - 2 0 ]............................................. 1 8 7
FIGURE 18: INSTALLATION THE BONDING JUMPER AND CLAMPS [Group 1-13, 15-16, 19-20] . . 189
FIGURE 19: REMOVAL OF THE RELAYS FROM THE P6 PANEL [Group 1-16, 21-29, 31] ...... 1 9 2
FIGURE 20: INSTALLATION OF THE P5 PANEL WIRE BUNDLE W036 [Group 1-16, 21-29, 31] . . . 194
FIGURE 21: CONNECTION OF THE WIRE BUNDLE W036 [Group 1, 21] ............... 1 9 5
FIGURE 22: CONNECTION OF THE WIRE BUNDLE W036 [Group 2-3, 22-23] ............ 1 9 8
FIGURE 23: CONNECTION OF THE WIRE BUNDLE W036 [Group 4-5, 24] .............. 2 0 1
FIGURE 24: CONNECTION OF THE WIRE BUNDLE W036 [Group 6-7, 25] .............. 2 0 4
FIGURE 25: CONNECTION OF THE WIRE BUNDLE W036 [Group 8, 26] ............... 2 0 7
FIGURE 26: CONNECTION OF THE WIRE BUNDLE W036 [Group 9, 31] ............... 2 1 0
FIGURE 27: CONNECTION OF THE WIRE BUNDLE W036 [Group 10-11, 27-28] ........... 2 1 3
FIGURE 28: CONNECTION OF THE WIRE BUNDLE W036 [Group 12, 29] .............. 2 1 6
FIGURE 29: CONNECTION OF THE WIRE BUNDLE W036 [Group 13] ................ 2 1 9
FIGURE 30: CONNECTION OF THE WIRE BUNDLE W036 [Group 14] ................ 2 2 2
FIGURE 31: CONNECTION OF THE WIRE BUNDLE W036 [Group 15] ................ 2 2 5
FIGURE 32: CONNECTION OF THE WIRE BUNDLE W036 [Group 16] ................ 2 2 8
FIGURE 33: REMOVAL OF THE RELAYS FROM THE P6 PANEL [Group 17-20, 30] ......... 2 3 1
FIGURE 34: INSTALLATION OF THE P5 PANEL WIRE BUNDLE W036 [Group 17-20, 30] ...... 2 3 3
FIGURE 35: CONNECTION OF THE WIRE BUNDLE W036 [Group 19, 30] .............. 2 3 4
FIGURE 36: CONNECTION OF THE WIRE BUNDLE W036 [Group 19, 30] .............. 2 3 7
FIGURE 37: CONNECTION OF THE WIRE BUNDLE W036 [Group 19, 30] .............. 2 4 0
FIGURE 38: CONNECTION OF THE WIRE BUNDLE W036 [Group 17] ................ 2 4 3
FIGURE 39: CONNECTION OF THE WIRE BUNDLE W036 [Group 17] ................ 2 4 6
FIGURE 40: CONNECTION OF THE WIRE BUNDLE W036 [Group 17] ................ 2 4 9
FIGURE 41: CONNECTION OF THE WIRE BUNDLE W036 [Group 18, 20] .............. 2 5 2
FIGURE 42: CONNECTION OF THE WIRE BUNDLE W036 [Group 18, 20] .............. 2 5 5
FIGURE 43: CONNECTION OF THE WIRE BUNDLE W036 [Group 18, 20] .............. 2 5 8
FIGURE 44: INSTALLATION OF THE P6 PANEL WIRE BUNDLE W044 [Group 1-16, 21-29, 31] . . . 261
FIGURE 45: CONNECTION OF THE WIRE BUNDLE W044 [Group 1, 21] ............... 2 6 2
FIGURE 46: CONNECTION OF THE WIRE BUNDLE W044 [Group 2, 22, Configuration 1] ...... 2 6 4
FIGURE 47: CONNECTION OF THE WIRE BUNDLE W044 [Group 2, 22, Configuration 2] ...... 2 6 6
FIGURE 48: CONNECTION OF THE WIRE BUNDLE W044 [Group 3, 16, 23] ............. 2 6 8
FIGURE 49: CONNECTION OF THE WIRE BUNDLE W044 [Group 4, Configuration 1] ........ 2 7 0
FIGURE 50: CONNECTION OF THE WIRE BUNDLE W044 [Group 4, Configuration 2] ........ 2 7 2
FIGURE 51: CONNECTION OF THE WIRE BUNDLE W044 [Group 5, 8, 24, 26] ............ 2 7 4
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### Page 5

FIGURE 52: CONNECTION OF THE WIRE BUNDLE W044 [Group 6, 25, Configuration 1] ...... 2 7 6
FIGURE 53: CONNECTION OF THE WIRE BUNDLE W044 [Group 6, 25, Configuration 2] ...... 2 7 8
FIGURE 54: CONNECTION OF THE WIRE BUNDLE W044 [Group 9, 31] ............... 2 8 0
FIGURE 55: CONNECTION OF THE WIRE BUNDLE W044 [Group 10, 27] .............. 2 8 2
FIGURE 56: CONNECTION OF THE WIRE BUNDLE W044 [Group 12, 29, Configuration 1] ..... 2 8 4
FIGURE 57: CONNECTION OF THE WIRE BUNDLE W044 [Group 12, 29, Configuration 2] ..... 2 8 6
FIGURE 58: CONNECTION OF THE WIRE BUNDLE W044 [Group 13] ................ 2 8 8
FIGURE 59: CONNECTION OF THE WIRE BUNDLE W044 [Group 7] ................. 2 9 0
FIGURE 60: CONNECTION OF THE WIRE BUNDLE W044 [Group 14, Configuration 1] ....... 2 9 2
FIGURE 61: CONNECTION OF THE WIRE BUNDLE W044 [Group 14, Configuration 2] ....... 2 9 4
FIGURE 62: CONNECTION OF THE WIRE BUNDLE W044 [Group 11, 28, Configuration 1] ..... 2 9 6
FIGURE 63: CONNECTION OF THE WIRE BUNDLE W044 [Group 11, 28, Configuration 2] ..... 2 9 8
FIGURE 64: CONNECTION OF THE WIRE BUNDLE W044 [Group 15, Configuration 1] ....... 3 0 0
FIGURE 65: CONNECTION OF THE WIRE BUNDLE W044 [Group 15, Configuration 2] ....... 3 0 2
FIGURE 66: INSTALLATION OF THE P6 PANEL WIRE BUNDLE W044 [Group 17-20, 30] ...... 3 0 4
FIGURE 67: CONNECTION OF THE WIRE BUNDLE W044 [Group 17, Configuration 1] ....... 3 0 5
FIGURE 68: CONNECTION OF THE WIRE BUNDLE W044 [Group 17, Configuration 2] ....... 3 0 8
FIGURE 69: CONNECTION OF WIRE BUNDLE W044 [Group 17, Configuration 1] .......... 3 1 1
FIGURE 70: CONNECTION OF THE WIRE BUNDLE W044 [Group 17, Configuration 2] ....... 3 1 4
FIGURE 71: CONNECTION OF THE WIRE BUNDLE W044 [Group 18, Configuration 1] ....... 3 1 7
FIGURE 72: CONNECTION OF THE WIRE BUNDLE W044 [Group 18, Configuration 2] ....... 3 2 0
FIGURE 73: CONNECTION OF THE WIRE BUNDLE W044 [Group 18, Configuration 1] ....... 3 2 3
FIGURE 74: CONNECTION OF THE WIRE BUNDLE W044 [Group 18, Configuration 2] ....... 3 2 6
FIGURE 75: CONNECTION OF THE WIRE BUNDLE W044 [Group 19, 30] .............. 3 2 9
FIGURE 76: CONNECTION OF WIRE BUNDLE W044 [Group 19, 30, Configuration 1] ........ 3 3 2
FIGURE 77: CONNECTION OF THE WIRE BUNDLE W044 [Group 19, 30, Configuration 2] ..... 3 3 5
FIGURE 78: CONNECTION OF THE WIRE BUNDLE W044 [Group 20, Configuration 1] ....... 3 3 8
FIGURE 79: CONNECTION OF THE WIRE BUNDLE W044 [Group 20, Configuration 2] ....... 3 4 1
FIGURE 80: CONNECTION OF THE WIRE BUNDLE W044 [Group 20, Configuration 1] ....... 3 4 4
FIGURE 81: CONNECTION OF THE WIRE BUNDLE W044 [Group 20, Configuration 2] ....... 3 4 7
FIGURE 82: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774 [Group 1-16, 19-20]
................................................. 3 5 0
FIGURE 83: CONNECTION OF WIRE BUNDLE W368 AND W1764 [Group 1-16, 21-29, 31] ..... 3 5 4
FIGURE 84: CONNECTION OF WIRE BUNDLE W368 AND W1764 [Group 17-20, 30] ........ 3 5 7
FIGURE 85: CONNECTION OF WIRE BUNDLE W386 / W1774 [Group 8, 16, 26] ........... 3 6 0
FIGURE 86: CONNECTION OF WIRE BUNDLE W386 / W1774 [Group 1-7, 9-15, 21-25, 27-29, 31] . 362
FIGURE 87: CONNECTION OF WIRE BUNDLE W386 / W1774 [Group 17-20, 30] .......... 3 6 4
FIGURE 88: INSTALLATION OF THE RELAYS AND STRAPS ON THE J2802 BOX ASSEMBLY [Group
1 - 1 6 ].............................................. 3 6 7
FIGURE 89: INSTALLATION OF THE RELAYS AND STRAPS ON THE J2802 BOX ASSEMBLY [Group
1 9 - 2 0 ]............................................. 3 7 0
FIGURE 90: INSTALLATION OF THE RELAYS IN THE P6 PANEL [Group 1-16, 21-29, 31] ...... 3 7 3
FIGURE 91: INSTALLATION OF THE RELAYS IN THE P6 PANEL [Group 17-20, 30] ......... 3 7 5
FIGURE 92: CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS [Group 14,
2 1 - 2 9 ,  3 1 ]  ........................................... 3 7 7
FIGURE 93: CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS [Group 17-18,
3 0 ]............................................... 3 8 0
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FIGURE 94: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS [Group 14,
2 1 - 2 9 ,  3 1 ]  ........................................... 3 8 4
FIGURE 95: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS [Group 17-18,
3 0 ]............................................... 3 9 0
FIGURE 96: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY FOR
AIRPLANES WITH AIRSTAIRS [Group 14, 21-29, 31] ................... 3 9 6
FIGURE 97: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY FOR
AIRPLANES WITH AIRSTAIRS [Group 17-18, 30] ..................... 4 0 0
FIGURE 98: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND E3 SUPPORT POST FOR
AIRPLANES WITH AIRSTAIRS [Group 14, 21-29, 31] ................... 4 0 4
FIGURE 99: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND E3 SUPPORT POST FOR
AIRPLANES WITH AIRSTAIRS [Group 17-18, 30] ..................... 4 1 0
FIGURE 100: PREPARATION OF THE J2802 BOX ASSEMBLY, E2 AND E3 SUPPORT POSTS FOR
AIRPLANE WITH AIRSTAIRS [Group 14, 21-29, 31] .................... 4 1 6
FIGURE 101: PREPARATION OF THE J2802 BOX ASSEMBLY, E2 AND E3 SUPPORT POSTS FOR
AIRPLANES WITH AIRSTAIRS [Group 17-18, 30] ..................... 4 1 8
FIGURE 102: INSTALLATION THE J2802 BOX ASSEMBLY ON THE E2 AND E3 SUPPORT POSTS FOR
AIRPLANES WITH AIRSTAIRS [Group 14, 21-29, 31] ................... 4 2 0
FIGURE 103: INSTALLATION THE J2802 BOX ASSEMBLY ON THE E2 AND E3 SUPPORT POSTS FOR
AIRPLANES WITH AIRSTAIRS [Group 17-18, 30] ..................... 4 2 2
FIGURE 104: INSTALLATION THE BONDING JUMPER AND CLAMPS FOR AIRPLANES WITH AIRSTAIRS
[Group 14, 17-18, 21-31] ................................... 4 2 4
FIGURE 105: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774 FOR AIRPLANES WITH
AIRSTAIRS [Group 14, 17-18, 21-31] ............................ 4 3 0
FIGURE 106: INSTALLATION OF THE RELAYS ON THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH
AIRSTAIRS [Group 14, 21-29, 31] .............................. 4 3 6
FIGURE 107: INSTALLATION OF THE RELAYS ON THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH
AIRSTAIRS [Group 17-18, 30] ................................ 4 3 8
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### Page 7

Commercial
Airplanes
737
Service Bulletin
Revision Transmittal SheetNumber: 737-28A1216Original Issue: July 29, 2010
Revision 2: November 12, 2012
ATA System: 2822
SUBJECT: FUEL - Engine Fuel Feed System - Installation of the Auto Shutoff Protection for the
Center and Auxiliary Fuel Tank Boost Pumps
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2010-NM-189-AD, is related to
this service bulletin.
No more work is necessary on the airplane(s) Groups 1-16, 19-31 changed in accordance with Revision 1 of
this service bulletin, dated March 26, 2012. More work is necessary for airplanes Group 17-18 that changed the
airplanes in accordance with Part 7 of Revision 1 of this service bulletin dated March 26, 2012. These airplanes
need to do also the Auxiliary Fuel Boost Pump Auto Shutoff Functional Test in accordance with PART 8 if the
Auxiliary Tank is installed.
REASON FOR REVISION
This revision is sent to tell the operators that Figures 8, 10, 84, 87, 94, 95, 98, 99, 100, 101, 102, 103 have been
revised to incorporate minor typographical changes. This revision also changes the Weight and Moments table,
that are based on airplanes with and without AUX Tank. Also the Electrical Load Data tables are identified with
titles, and missing airplane groups are added to the applicability of the tables. This revision also changes
supplemental kit 65C37854-16 for manufacturing purpose. The quantity of the labels in drawing 65C38484-30
is changed from 2 to 1 and, the quantity of 65C38484-30 is changed from 1 to 2 in the supplemental kit
65C37854-16. Also PART 7, PART 8, and PART 9 are added to Summary page, Action paragraph, and to
Planning section, Description paragraph.
These sections were changed:
1. Summary:
a. Action: added the descriptions of PART 7, PART 8, and PART 9.
b. Compliance: changed the compliance time from the date of Revision 2 of this service bulletin.
2. Planning Information:
a. Paragraph 1. B., Concurrent Requirements: changed the revision level and date of the concurrent
BAE service bulletin, and changed the revision level of the concurrent Boeing service bulletin.
b. Paragraph 1. D., Description: added the descriptions of PART 7, PART 8, and PART 9.
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### Page 8

c. Paragraph 1.E., Compliance: changed the compliance time from the date of Revision 2 of this
service bulletin.
d. Paragraph 1.H., Weight and Balance Changes, page 81: Changed the titles of the tables, changed
the weight and moments tables for airplanes with and without AUX Tank.
e. Paragraph 1.I, Electrical Load Data: Added titles to the tables and added missing airplane groups
to the tables.
3. Material Section:
a. Paragraph 2.A., Material and Price Availability: Added supplemental kit 65C37854-16 to the table
applicable to airplane groups 17-20, changed footnote (a), and added new footnote (c). Added a
new table with the new top kit 65C38471-12 for groups 17-18.
b. Paragraph 2.C.1., Kits/Parts: The quantity of the 65C38484-30 is changed from 1 to 2 in the
supplemental kit 65C37854-16.
c. Paragraph 2.C.1., Kits/Parts: Removed duplicate lines from tables.
d. Paragraph 2.C.2., Parts and Materials Supplied by the Operator: Added Seal Plugs.
4. Accomplishment Instructions:
a. Paragraph 3.B.8., PART 8: Added the Auxiliary Tank Fuel Boost Pump Auto Shutoff Functional
test that needs to be done for airplanes that have an AUX Tank Installed.
b. Figure 8, Figure 10, Figure 84, and Figure 87: Added footnote related to additional seal plugs
necessary for airplanes with wire provisions for AUX Tank and with no AUX Tank installed.
c. Figure 94 and Figure 95: moved call-outs for View "A" and view "B" to a different location, changed
the reference lines for two dimensions, corrected step instructions, changed the quantity of fasteners
and holes in step instructions table.
d. Figure 98 and Figure 99: replaced the word "Shim" with "Filler", deleted one hole related to step
instruction 1 that was shown in error, added the filler in section C-C and revised section D-D, added
a footnote to step 1, added fillers to step instruction 2, re-numbered the footnotes, changed step
instruction 9.
e. Figure 100 and Figure 101: Showed the filler between the J2802 relay box and the stanchion.
f. Figure 102 and Figure 103 sheet 1 of 2, cross sections A-A and B-B: Showed the fillers between
the J2802 relay box and the stanchion, corrected fastener size location.
g. Figure 104: Corrected number of holes and fasteners in the step instruction table.
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.
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### Page 9

REVISION HISTORY
July 29, 2010Original Issue:
March 26, 2012Revision 1:
November 12, 2012Revision 2:
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Export Controlled ECCN: 9E991 - BOEING
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BLANK PAGE

### Page 11

Commercial
Airplanes
737
Service Bulletin
SummaryNumber: 737-28A1216Original Issue: July 29, 2010
Revision 2: November 12, 2012
ATA System: 2822
SUBJECT: FUEL - Engine Fuel Feed System - Installation of the Auto Shutoff Protection for the
Center and Auxiliary Fuel Tank Boost Pumps
CONCURRENT REQUIREMENTS
Refer to Paragraph 1.B., Concurrent Requirements.
BACKGROUND
This service bulletin is the result of the safety analysis done by Boeing under SFAR 88, "Fuel Tank System Fault
Tolerance Evaluation Requirements." Initial results from the fuel system safety analysis shows that fuel boost
pumps that run dry could cause an overheat condition external of the fuel pump explosion resistance area that
is open to the fuel pump inlet. An overheat condition in this area could possibly cause an unwanted ignition
source for the fuel vapors in the fuel tank and could cause a fire or explosion.
This service bulletin gives the instructions and a kit of parts to install an automatic (auto) shut-off system for the
fuel boost pumps. The fuel boost pumps are installed in the center fuel tank and if equipped, also in the auxiliary
fuel tank. Time delay relays are installed in the new J2802 box assembly that will shut off the fuel boost pumps
if the pumps operate with continuous low pressure for 15 seconds. The 15 second time delay relay prevents
extended dry operation of the fuel boost pumps and allows for sufficient time for fuel pump inlet reprime to
prevent nuisance automatic shutoff. The flight crew stays in primary control, with the auto shutoff system as a
backup, to stop the fuel boost pumps after a low pressure indication.
The change installs an automatic shut off system that gives fuel boost pump inlet protection in the fuel tank
against sparks possibly caused by friction overheat damage.
This change affects the Fuel Systems Airworthiness Limitations section of Boeing document
"737-100/200/200C/300/400/500 Airworthiness Limitations (AWLs) and Certification Maintenance Requirements
(CMRs), D6-38278-CMR." New AWL "28-AWL-20" will be added to include an operational check of the boost
pump automatic shutoff system for the center fuel tank. AWL "28-AWL-21" will be added to include an operational
check of the fuel boost pump automatic shutoff system for the auxiliary fuel tank, if installed by Boeing. This
change also affects Section 1 and Section 3 of the FAA Approved Airplane Flight Manual (AFM).
ACTION (PRR 35442-RS)
The work instructions are divided into 31 airplane groups, 9 parts.
PART 1, PART 2, PART 3, PART 4, and PART 5 work instructions are divided into 3 work packages because
of the different wire bundle changes and airplanes without and with Airstairs
PART 6 work instructions are for Operators that already ordered the kit from the original release, and want to
re-work the kit for airplanes with Airstairs.
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11 of 439

### Page 12

PART 7, PART 8, PART 9 provide instructions to change the J2802 relay box for airplanes that incorporated
the original release of the service bulletin.
NOTE: When submitting a Publication Change Request (PCR) to Boeing to incorporate this service bulletin in
the affected manuals, please notify Boeing if Auxiliary Tanks are installed on these airplanes. If Boeing
is not notified about the Auxiliary Tanks, Boeing will assume that the airplanes in these groups do not
have Auxiliary (AUX) tanks and no AUX Tank changes to the affected manuals will be done.
Group 1-13, 15-16:
PART 1 - AIRPLANES WITH CENTER FUEL TANKS AND WITHOUT AUXILIARY (AUX) FUEL TANKS
1. Work Package 1:
In the J2802 box assembly, install the wire bundles W1760 and W1770.
2. Work Package 2:
Get access into the main electronics compartment. Between the E2 and E3 rack support posts, install
the J2802 box assembly.
3. Work Package 3:
In the flight compartment, get access to the P5 overhead panel, P6 relay panel or P6 relay modules.
Above the P5 overhead panel, make a change to the wire bundles W36, W368 and W386. Between
the P6 disconnect panel and the fuel boost pump relays R54 and R55, make a change to the wire
bundle W44.
In the flight and main electronics compartments, between the P6 disconnect panel and the J2802 box
assembly, install the new wire bundles W1764 and W1774.
In the main electronics compartment, at the J2802 box assembly, install the time delay relays R3318
and R3321.
Do a functional test of the fuel boost pumps to make sure the changed control system operates correctly.
Group 17-18:
PART 2 - AIRPLANES WITH CENTER TANKS AND WIRE PROVISION FOR AUXILIARY (AUX) FUEL
TANKS, AND AIRSTAIRS
1. Work Package 1:
In the J2802 box assembly, install the wire bundles W1760 and W1770.
2. Work Package 2:
Get access into the main electronics compartment. Between the E2 and E3 rack support posts, install
the J2802 box assembly.
3. Work Package 3:
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### Page 13

NOTE: Airplanes in group 17 and 18 have been delivered with provisional wires for future Auxiliary
Tank installation. Operators that installed AUX tanks with Fuel Boost Pumps on these airplanes
need to install an Auto Shutoff system. FAA may release an AD to require that all airplanes
that have AUX tanks with Fuel Boost Pumps should install an Auto Shutoff system.
In the flight compartment, get access to the P5 overhead panel, P6 relay panel or P6 relay modules.
Above the P5 overhead panel, make a change to the wire bundles W36, W368 and W386. Between
the P6 disconnect panel and the fuel boost pump relays R54 and R55, make a change to the wire
bundle W44. For the airplanes that have an auxiliary fuel tank, between the P6 disconnect panel and
the fuel boost pump relays R146 and R147, make a change to the wire bundle W44.
In the flight and main electronics compartments, between the P6 disconnect panel and the J2802 box
assembly, install the new wire bundles W1764 and W1774.
In the main electronics compartment, at the J2802 box assembly, install the time delay relays R3318
and R3321. For the airplanes that have auxiliary fuel tank, at the J2802 box assembly, install the time
delay relays R3327 and R3329.
Do a functional test of the fuel boost pumps to make sure the changed control system operates correctly.
Group 19-20:
PART 3 - AIRPLANES WITH CENTER AND AUXILIARY (AUX) FUEL TANKS
1. Work Package 1:
In the J2802 box assembly, install the wire bundles W1760 and W1770.
2. Work Package 2:
Get access into the main electronics compartment. Between the E2 and E3 rack support posts, install
the J2802 box assembly.
3. Work Package 3:
In the flight compartment, get access to the P5 overhead panel, P6 relay panel or P6 relay modules.
Above the P5 overhead panel, make a change to the wire bundles W36, W368 and W386. Between
the P6 disconnect panel and the fuel boost pump relays R54 and R55, make a change to the wire
bundle W44. Between the P6 disconnect panel and the fuel boost pump relays R146 and R147, make
a change to the wire bundle W44.
In the flight and main electronics compartments, between the P6 disconnect panel and the J2802 box
assembly, install the new wire bundles W1764 and W1774.
In the main electronics compartment, at the J2802 box assembly, install the time delay relays R3318
and R3321. At the J2802 box assembly, install the time delay relays R3327 and R3329.
Do a functional test of the fuel boost pumps to make sure the changed control system operates correctly.
Group 14, 21-29, 31:
PART 4 - AIRPLANES WITH CENTER FUEL TANKS AND WITHOUT AUXILIARY (AUX) FUEL TANKS,
AND AIRSTAIRS
1. Work Package 1:
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### Page 14

Change J2802 Box Assy in accordance with PART 6 if necessary.
In the J2802 box assembly, install the wire bundles W1760 and W1770.
2. Work Package 2:
Get access into the main electronics compartment. Between the E2 and E3 rack support posts, install
the J2802 box assembly.
3. Work Package 3:
In the flight compartment, get access to the P5 overhead panel, P6 relay panel or P6 relay modules.
Above the P5 overhead panel, make a change to the wire bundles W36, W368 and W386. Between
the P6 disconnect panel and the fuel boost pump relays R54 and R55, make a change to the wire
bundle W44.
In the flight and main electronics compartments, between the P6 disconnect panel and the J2802 box
assembly, install the new wire bundles W1764 and W1774.
In the main electronics compartment, at the J2802 box assembly, install the time delay relays R3318
and R3321.
Do a functional test of the fuel boost pumps to make sure the changed control system operates correctly.
Group 30:
PART 5 - AIRPLANES WITH CENTER AND AUXILIARY (AUX) FUEL TANKS, AND AIRSTAIRS
1. Work Package 1:
Change J2802 Box Assy in accordance with PART 6 if necessary.
In the J2802 box assembly, install the wire bundles W1760 and W1770.
2. Work Package 2:
Get access into the main electronics compartment. Between the E2 and E3 rack support posts, install
the J2802 box assembly.
3. Work Package 3:
In the flight compartment, get access to the P5 overhead panel, P6 relay panel or P6 relay modules.
Above the P5 overhead panel, make a change to the wire bundles W36, W368 and W386. Between
the P6 disconnect panel and the fuel boost pump relays R54 and R55, make a change to the wire
bundle W44. Between the P6 disconnect panel and the fuel boost pump relays R146 and R147, make
a change to the wire bundle W44.
In the flight and main electronics compartments, between the P6 disconnect panel and the J2802 box
assembly, install the new wire bundles W1764 and W1774.
In the main electronics compartment, at the J2802 box assembly, install the time delay relays R3318
and R3321. At the J2802 box assembly, install the time delay relays R3327 and R3329.
Do a functional test of the fuel boost pumps to make sure the changed control system operates correctly.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: July 29, 2010
737-28A1216Revision 2: November 12, 2012
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BOEING SERVICE BULLETIN 737-28A1216

### Page 15

Group 14, 17-18, 21-31:
PART 6 - AIRPLANES WITH CENTER AND AUXILIARY (AUX) FUEL TANKS, AND AIRSTAIRS
1. Change J2802 Box Assy for airplanes with Airstairs.
NOTE: Operators that have airplanes with Airstairs that ordered and received the Top Kits given in
the original release of this service bulletin can use the J2802 Box assembly received in the
kit but they need to change the J2802 Box for airplanes with airstairs.
Group 1-16, 21-29, 31:
PART 7- CHANGE OF THE J2802 RELAY BOX FOR AIRPLANES THAT INCORPORATED THE ORIGINAL
RELEASE OF THE SERVICE BULLETIN
1. Install Labels on the J2802 Box Assy, change wire W1760 termination at switch S3318, change wire
W1770 termination at switch S3321, inspect the imprinted text on the ID tape of wire W368-031-20,
and Do the Center Fuel Boost Pump Auto Shutoff Functional Test.
NOTE: Only airplanes that were in Group 1 through 16 of the Original Release of this service bulletin
and incorporated the changes provided in the Original Release of the service bulletin have to
do the work provided in PART 7.
Group 17-18:
PART 8- CHANGE OF THE J2802 RELAY BOX FOR AIRPLANES THAT INCORPORATED THE ORIGINAL
RELEASE OF THE SERVICE BULLETIN
1. Install the Labels on the J2802 Box Assy, change wire W1760 termination at switch S3318, change
wire W1770 termination at switch S3321, Inspect the imprinted text on the ID tape of wire W368-031-20,
Do the Center Fuel Boost Pump Auto Shutoff Functional Test, Do the Auxiliary Fuel Boost Pump Auto
Shutoff Functional Test for airplanes with Auxiliary Tank installed.
NOTE: Only airplanes that were in Group 17 and 18 of the Original Release of this service bulletin
and incorporated the changes provided in the Original Release of the service bulletin have to
do the work provided in PART 8.
NOTE: Airplanes in Group 17 and 18 have been delivered without Auxiliary Tanks but with wire
provisions for Auxiliary Tank Installation. It was necessary to do the change given in Figure
7 of the Original Release of the service bulletin only if Auxiliary Tank with Fuel Boost Pumps
were installed on the airplane. If Auxiliary Tank is not installed, it is not necessary to do the
changes of wire W1760 in accordance with Figure 7 of this revision.
Group 19-20, 30:
PART 9- CHANGE OF THE J2802 RELAY BOX FOR AIRPLANES THAT INCORPORATED THE ORIGINAL
RELEASE OF THE SERVICE BULLETIN
1. Install the Labels on the J2802 Box Assy, change wire W1760 termination at switch S3318, change
wire W1770 termination at switch S3321, Inspect the imprinted text on the ID tape of wire W368-031-20,
Do the Center Fuel Boost Pump Auto Shutoff Functional Test, Do the Auxiliary Fuel Boost Pump Auto
Shutoff Functional Test.
NOTE: Only airplanes that were in Group 19 through 20 of the Original Release of this service bulletin
and incorporated the changes provided in the Original Release of the service bulletin have to
do the work provided in PART 9.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: July 29, 2010
737-28A1216Revision 2: November 12, 2012
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### Page 16

EFFECTIVITY
737-300/400/500 airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes.
COMPLIANCE
Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2010-NM-189-AD, is related to
this service bulletin.
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service
bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin
mandatory.
Boeing recommends that the change given in this service bulletin be done within 36 months after the Revision
2 date of this service bulletin.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
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 737-28A1216

### Page 17 (OCR)

BOEING SERVICE BULLETIN 737-28A1216
CHANGE WIRE BUNDLES
W036/W368/W386
CHANGE WIRE BUNDLE WO44
INSTALL WIRE BUNDLES
W1764/W1774
P6 RELAY
PANEL
INSTALL WIRE BUNDLES W1760/W1770
INSTALL J2802 BOX ASSEMBLY
INSTALL RELAYS
AIRPLANES WITH NO AIRSTAIRS
CHANGE WIRE BUNDLES
CHANGE WIRE BUNDLE WO44  W036/W368/W386
INSTALL WIRE BUNDLES
W1764/W1774
P6 RELAY
PANEL
INSTALL WIRE BUNDLES W1760/W1770
INSTALL J2802 BOX ASSEMBLY
INSTALL RELAYS
AIRPLANES WITH AIRSTAIRS  D31390
Original Issue: July 29, 2010
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PROPRIETARY - Copyright © Unpublished  Work - See page 1 for details.  17 of 439

### Page 18

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PROPRIETARY - Copyright © Unpublished
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18 of 439
BOEING SERVICE BULLETIN 737-28A1216
BLANK PAGE

### Page 19

Commercial
Airplanes
737
Service Bulletin
Number: 737-28A1216
Original Issue: July 29, 2010
Revision 2: November 12, 2012
ATA System: 2822
SUBJECT: FUEL - Engine Fuel Feed System - Installation of the Auto Shutoff Protection for the
Center and Auxiliary Fuel Tank Boost Pumps
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 35442-RS 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.
NOTE: Airplanes in group 17 and 18 have been delivered with provisional wires for future Auxiliary
Tank installation. Operators that installed AUX tanks with Fuel Boost Pumps on these
airplanes need to install an Auto Shutoff system. FAA may release an AD to require that
all airplanes that have AUX tanks with Fuel Boost Pumps should install an Auto Shutoff
system.
DESCRIPTIONCONFIGURATIONGROUP
Airplanes that do not have the auxiliary fuel tanks and have different
wiring configurations at the P5 and P6 panels, and with or without
SB 737-28A1212 R0 or R1 incorporated.
-1
Airplanes that do not have the auxiliary fuel tanks and have different
wiring configurations at the P5 and P6 panels.
-2
Airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
Airplanes with SB 737-28A1212 R0 or R1 incorporated.2
Airplanes that do not have the auxiliary fuel tanks and have different
wiring configurations at the P5 and P6 panels, and with or without
SB 737-28A1212 R0 or R1 incorporated.
-3
Export Controlled ECCN: 9E991 - BOEING
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### Page 20

DESCRIPTIONCONFIGURATIONGROUP
Airplanes that do not have the auxiliary fuel tanks and have different
wiring configurations at the P5 and P6 panels.
-4
Airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
Airplanes with SB 737-28A1212 R0 or R1 incorporated.2
Airplanes that do not have the auxiliary fuel tanks and have different
wiring configurations at the P5 and P6 panels, and with or without
SB 737-28A1212 R0 or R1 incorporated.
-5
Airplanes that do not have the auxiliary fuel tanks and have different
wiring configurations at the P5 and P6 panels.
-6
Airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
Airplanes with SB 737-28A1212 R0 or R1 incorporated.2
Airplanes that do not have the auxiliary fuel tanks and have different
wiring configurations at the P5 and P6 panels, and with or without
SB 737-28A1212 R0 or R1 incorporated.
-7
Airplanes that do not have the auxiliary fuel tanks and have different
wiring configurations at the P5 and P6 panels, and with or without
SB 737-28A1212 R0 or R1 incorporated.
-8
Airplanes that do not have the auxiliary fuel tanks and have different
wiring configurations at the P5 and P6 panels, and with or without
SB 737-28A1212 R0 or R1 incorporated.
-9
Airplanes that do not have the auxiliary fuel tanks and have different
wiring configurations at the P5 and P6 panels, and with or without
SB 737-28A1212 R0 or R1 incorporated.
-10
Airplanes that do not have the auxiliary fuel tanks and have different
wiring configurations at the P5 and P6 panels.
-11
Airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
Airplanes with SB 737-28A1212 R0 or R1 incorporated.2
Airplanes that do not have the auxiliary fuel tanks and have different
wiring configurations at the P5 and P6 panels.
-12
Airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
Airplanes with SB 737-28A1212 R0 or R1 incorporated.2
Export Controlled ECCN: 9E991 - BOEING
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### Page 21

DESCRIPTIONCONFIGURATIONGROUP
Airplanes that do not have the auxiliary fuel tanks and have different
wiring configurations at the P5 and P6 panels, and with or without
SB 737-28A1212 R0 or R1 incorporated.
-13
Airplanes with Airstairs that do not have the auxiliary fuel tanks and
have different wiring configurations at the P5 and P6 panels.
-14
Airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
Airplanes with SB 737-28A1212 R0 or R1 incorporated.2
Airplanes that do not have the auxiliary fuel tanks and have different
wiring configurations at the P5 and P6 panels.
-15
Airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
Airplanes with SB 737-28A1212 R0 or R1 incorporated.2
Airplanes that do not have the auxiliary fuel tanks and have different
wiring configurations at the P5 and P6 panels, and with or without
SB 737-28A1212 R0 or R1 incorporated.
-16
Airplanes with Airstairs, delivered with wire provision for Auxiliary
Tank installation and have different wiring configurations at the P5
and P6 panels.
-17
Airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
Airplanes with SB 737-28A1212 R0 or R1 incorporated.2
Airplanes with Airstairs, delivered with wire provision for Auxiliary
Tank installation and have different wiring configurations at the P5
and P6 panels.
-18
Airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
Airplanes with SB 737-28A1212 R0 or R1 incorporated.2
Airplanes that have the auxiliary fuel tanks and have different wiring
configurations at the P5 and P6 panels.
-19
Airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
Airplanes with SB 737-28A1212 R0 or R1 incorporated.2
Export Controlled ECCN: 9E991 - BOEING
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BOEING SERVICE BULLETIN 737-28A1216

### Page 22

DESCRIPTIONCONFIGURATIONGROUP
Airplanes that have the auxiliary fuel tanks and have different wiring
configurations at the P5 and P6 panels.
-20
Airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
Airplanes with SB 737-28A1212 R0 or R1 incorporated.2
Airplanes with Airstairs, that do not have the auxiliary fuel tanks and
have different wiring configurations at the P5 and P6 panels, and
with or without SB 737-28A1212 R0 or R1 incorporated.
-21
Airplanes with Airstairs, that do not have the auxiliary fuel tanks and
have different wiring configurations at the P5 and P6 panels.
-22
Airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
Airplanes with SB 737-28A1212 R0 or R1 incorporated.2
Airplanes with Airstairs, that do not have the auxiliary fuel tanks and
have different wiring configurations at the P5 and P6 panels, and
with or without SB 737-28A1212 R0 or R1 incorporated.
-23
Airplanes with Airstairs, that do not have the auxiliary fuel tanks and
have different wiring configurations at the P5 and P6 panels, and
with or without SB 737-28A1212 R0 or R1 incorporated.
-24
Airplanes with Airstairs, that do not have the auxiliary fuel tanks and
have different wiring configurations at the P5 and P6 panels.
-25
Airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
Airplanes with SB 737-28A1212 R0 or R1 incorporated.2
Airplanes with Airstairs, that do not have the auxiliary fuel tanks and
have different wiring configurations at the P5 and P6 panels, and
with or without SB 737-28A1212 R0 or R1 incorporated.
-26
Airplanes with Airstairs, that do not have the auxiliary fuel tanks and
have different wiring configurations at the P5 and P6 panels, and
with or without SB 737-28A1212 R0 or R1 incorporated.
-27
Airplanes with Airstairs, that do not have the auxiliary fuel tanks and
have different wiring configurations at the P5 and P6 panels.
-28
Airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
Airplanes with SB 737-28A1212 R0 or R1 incorporated.2
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### Page 23

DESCRIPTIONCONFIGURATIONGROUP
Airplanes with Airstairs, that do not have the auxiliary fuel tanks and
have different wiring configurations at the P5 and P6 panels.
-29
Airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
Airplanes with SB 737-28A1212 R0 or R1 incorporated.2
Airplanes with Airstairs, that have the auxiliary fuel tanks and have
different wiring configurations at the P5 and P6 panels.
-30
Airplanes with SB 737-28A1212 R0 or R1 not incorporated.1
Airplanes with SB 737-28A1212 R0 or R1 incorporated.2
Airplanes with Airstairs, that do not have the auxiliary fuel tanks and
have different wiring configurations at the P5 and P6 panels, and
with or without SB 737-28A1212 R0 or R1 incorporated.
-31
Airplane Models:
737-300, 737-400, 737-500
GroupVariable Number
1PJ301 - PJ302
1PJ551 - PJ561
1PJ601 - PJ615
19PJ811
21PJ816 - PJ817
22PM381 - PM399
22PM401 - PM417
22PM541 - PM550
23PM551 - PM564
6PP001 - PP054
29PP101
12PP102 - PP169
6PP181 - PP187
7PP188 - PP199
25PP201 - PP205
14PP221
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### Page 24

GroupVariable Number
6PP231 - PP243
6PP281 - PP286
6PP301 - PP305
25PP351 - PP353
25PP376 - PP384
25PP391 - PP393
6PP401 - PP440
20PP471 - PP475
18PP501 - PP520
25PP521 - PP522
6PP631 - PP634
25PP651 - PP652
6PP671 - PP689
20PP690 - PP694
6PP695 - PP699
6PP701 - PP706
20PP707 - PP716
6PP717 - PP733
6PP771 - PP779
25PP801 - PP808
25PP821 - PP827
22PP831 - PP848
28PP851 - PP852
11PP861 - PP877
28PP891 - PP899
28PP901 - PP936
28PP946 - PP948
28PP951 - PP952
11PP961 - PP965
3PP966 - PP967
11PP981 - PP982
3PP983 - PP990
11PP991
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### Page 25

GroupVariable Number
23PP993
11PQ001 - PQ016
11PQ026 - PQ041
11PQ051 - PQ092
11PQ101 - PQ199
11PQ201 - PQ202
23PQ221 - PQ230
11PQ231 - PQ232
10PQ233 - PQ237
28PQ241 - PQ242
27PQ243
27PQ251 - PQ267
27PQ281 - PQ291
10PQ292 - PQ297
27PQ298
10PQ299
10PQ301 - PQ307
10PQ331 - PQ332
10PQ341 - PQ348
27PQ361 - PQ373
27PQ391 - PQ395
27PQ401 - PQ418
27PQ421
10PQ431 - PQ438
27PQ447 - PQ448
10PQ451
10PQ454
10PQ471
27PQ472 - PQ475
10PQ479 - PQ481
10PQ486 - PQ487
10PQ491 - PQ493
10PQ771 - PQ772
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### Page 26

GroupVariable Number
10PQ791 - PQ793
16PQ801 - PQ805
16PQ931 - PQ935
27PQ951
27PQ971 - PQ997
23PR001 - PR017
23PR021 - PR030
3PR031 - PR034
3PR041 - PR045
3PR061 - PR072
3PR077 - PR080
23PR081 - PR082
23PR091 - PR092
23PR096
23PR101
23PR121 - PR122
23PR131 - PR132
23PR141 - PR143
23PR161 - PR172
16PR181
22PS601 - PS631
22PS636 - PS638
22PS641 - PS642
2PS643 - PS644
23PS651 - PS657
10PS666 - PS669
3PS691 - PS692
11PS701 - PS706
12PS751 - PS799
23PS811
23PS836 - PS837
22PS841 - PS846
22PS851 - PS852
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### Page 27

GroupVariable Number
22PS856
17PS861 - PS863
17PS866 - PS868
22PS871 - PS874
22PS896 - PS897
15PS901 - PS941
17PS956 - PS957
23PS961 - PS963
23PS971 - PS978
3PT001 - PT015
3PT021 - PT031
23PT041 - PT064
3PT101 - PT105
23PT121 - PT138
23PT146 - PT148
23PT161 - PT170
31PT181 - PT185
9PT186 - PT188
23PT211 - PT220
23PT295
3PT301 - PT309
10PT331 - PT360
3PT381 - PT399
3PT401 - PT438
27PT501 - PT517
3PT561 - PT565
3PT581 - PT586
10PT611 - PT621
3PT641 - PT644
3PT651 - PT656
27PT671 - PT672
3PT681 - PT685
13PT701 - PT703
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GroupVariable Number
3PT716 - PT717
23PT721 - PT725
10PT801 - PT834
3PT851 - PT854
23PT871 - PT886
10PT901 - PT930
10PT971 - PT973
3PT981 - PT985
23PT996
10PU001 - PU025
23PU301
23PU311 - PU313
4PV001
5PV002 - PV055
1PV201 - PV209
1PV226 - PV229
8PV231 - PV237
1PV271 - PV272
1PV281 - PV287
21PV296
21PV301 - PV302
1PV351
31PV356 - PV357
21PW001 - PW054
21PW061
1PW062 - PW068
21PW072
21PW086 - PW088
21PW091 - PW094
21PW101 - PW102
21PW106
21PW111 - PW120
21PW156 - PW157
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GroupVariable Number
21PW161 - PW171
1PW201 - PW252
21PW261 - PW268
21PW271 - PW276
21PW278
21PW281 - PW293
21PW296
26PW301 - PW327
1PW401 - PW408
1PW411 - PW418
1PW421 - PW424
1PW431 - PW435
8PW441 - PW450
1PW461 - PW467
21PW501 - PW504
19PW511 - PW522
19PW524
1PW525 - PW529
19PW530
5PW531 - PW550
24PW556 - PW557
1PW561 - PW564
1PW571 - PW576
21PW591 - PW596
5PW611 - PW622
5PW631 - PW637
24PW661 - PW662
5PW681 - PW683
30PW701 - PW702
1PW711 - PW717
24PW741 - PW742
5PW761
1PW771
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GroupVariable Number
31PW831
31PW851 - PW856
2. Spares Affected
None.
B. Concurrent Requirements
The service bulletin(s) listed below must be done before or at the same time as this service bulletin:
DescriptionService BulletinCompany
Gives instruction to install a new printed
circuit assembly in the P5-2 fuel system
module assembly to supply Low fuel pres-
sure master caution Annunciation.
BAE Systems SB 69-37335-28-04, Revision
3, dated March 31/2011
BAE
Gives instruction to replace the P5-2 fuel
system module assembly to supply Low fuel
pressure master caution Annunciation.
737-28A1210, Revision 2Boeing
C. Reason
This service bulletin is the result of the safety analysis done by Boeing under SFAR 88, "Fuel Tank
System Fault Tolerance Evaluation Requirements." Initial results from the fuel system safety analysis
shows that fuel boost pumps that run dry could cause an overheat condition external of the fuel pump
explosion resistance area that is open to the fuel pump inlet. An overheat condition in this area could
possibly cause an unwanted ignition source for the fuel vapors in the fuel tank and could cause a fire
or explosion.
This service bulletin gives the instructions and a kit of parts to install an automatic (auto) shut-off system
for the fuel boost pumps. The fuel boost pumps are installed in the center fuel tank and if equipped,
also in the auxiliary fuel tank. Time delay relays are installed in the new J2802 box assembly that will
shut off the fuel boost pumps if the pumps operate with continuous low pressure for 15 seconds. The
15 second time delay relay prevents extended dry operation of the fuel boost pumps and allows for
sufficient time for fuel pump inlet reprime to prevent nuisance automatic shutoffs. The flight crew stays
in primary control, with the auto shut off system as a backup, to stop the fuel boost pumps after a low
pressure indication.
The change installs an automatic shut off system that gives fuel boost pump inlet protection in the fuel
tank against sparks possibly caused by friction overheat damage.
This change affects the Fuel Systems Airworthiness Limitations section of Boeing document
"737-100/200/200C/300/400/500 Airworthiness Limitations (AWLs) and Certification Maintenance
Requirements (CMRs), D6-38278-CMR." New AWL "28-AWL-20" will be added to include an operational
check of the boost pump automatic shutoff system for the center fuel tank. AWL "28-AWL-21" will be
added to include an operational check of the fuel boost pump automatic shutoff system for the auxiliary
fuel tank, if installed by Boeing. This change also affects Section 1 and Section 3 of the FAA Approved
Airplane Flight Manual (AFM).
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Other related airplane service bulletins are Service Bulletin 737-28A1228 for the 737-100/200 airplanes
and Service Bulletin 737-28A1206 for the 737-600/700/800/900 airplanes.
Revision 1:
This revision is sent to tell the operators that for airplanes with Airstairs the J2802 Box provided in the
original release can not be installed in the main equipment compartment on the E2 and E3 support
posts in accordance with Figure 12 or Figure 13. When J2802 Box is installed in accordance with Figure
12 or 13, the forward face of the box interferes with the Airstairs and the Airstairs support structure.
Also there is no good access to the Airstairs relays, and to the wires connected to the Airstairs relays.
A new J2802 Box Assembly was designed and added to this revision that can be installed on airplanes
with Airstairs with no interference with Airstairs and the Airstairs support structure. The airplanes with
Airstairs were moved from the existing groups into new groups based on the wires configuration and
Auxiliary Tank installation. Figures 92 through 107 were added for airplanes with Airstairs.
This revision is also sent to tell the Operators that the switches S03318 and S03321 installed on J2802
box have two positions (for each switch) identified as "POS 1" and "POS 2". POS 1 of the test switch
S03318 is for Left Fuel Boost Pump of the Center Tank. POS 1 of the test switch S03321 is for Right
Fuel Boost Pump of the Center Tank. POS 2 of the test switches S03318 and S03321 are only used
for airplanes with Auxiliary Tanks. POS 2 of the test switch S03318 is for Aft Fuel Boost Pump of the
Auxiliary Tank. POS 2 of the test switch S03321 is for Fwd Fuel Boost Pump of the Auxiliary Tank. The
wires terminated at switches S03318 and S03321 were incorrectly terminated in Figures 4, 5, 7, 8, 9,
10. The wire terminations at switches S03318 and S03321 are changed in order for the switches to
function as indicated.
New steps are added to Figure 3 that instruct the operators to install markers on the J2802 Box that
will identify S03318 and S003321 as "TEST SWITCHES". Also instructions are added to install markers
that will identify the function of the switch S03318 POS 1 as "CTR-L", and the function of the switch
S03321 POS 1 as "CTR-R".
New steps are added to Figure 6 that instruct the operators to install markers on the J2802 Box that
will identify S03318 and S003321 as "TEST SWITCHES". Also instructions are added to install markers
that will identify the functions of the switch S03318 as follows: POS 1 as "CTR-L", and POS 2 as
"AUX-AFT". Also instructions are added to install markers that will identify the functions of the switch
S03321 as follows: POS 1 as "CTR-R", and POS 2 as "AUX-FWD".
Also this revision moves airplanes with airstairs from existing groups in new groups, Group 21 through
31. All airplanes in Groups 14, 17, and 18 have airstairs.
Some wires W368-031-20 delivered in the kits have been identified incorrectly. The wire I.D Tapes
Part Number 61-74478-10906 installed on both ends of the wire W368-031-20 may be imprinted
incorrectly as "W036-031-20". Instructions are added to Figure 83 and Figure 84 to check the imprinted
text on the wire I.D Tapes before installation and correct the text from "W036-031-20" to "W0368-031-20"
if necessary.
The data given in Information Notice 737-28A1216 IN 01, 737-28A1216 IN 02, and 737-28A1216 IN
03 are included in this revision.
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Revision 2:
This revision is sent to tell the operators that Figures 8, 10, 84, 87, 94, 95, 98, 99, 100, 101, 102, 103
have been revised to incorporate minor typographical changes. This revision also changes the Weight
and Moments table based on airplanes with and without AUX Tank. Also the Electrical Load Data tables
are identified with titles, and missing airplane groups are added to the applicability. This revision also
changes supplemental kit 65C37854-16 for manufacturing purpose. The quantity of the labels in the
kit drawing 65C38484-30 is changed from 2 to 1 and, the quantity of the 65C38484-30 is changed from
1 to 2 in the supplemental kit 65C37854-16. Also PART 7, PART 8, and PART 9 are added to Summary,
Action paragraph, and to Planning, Description paragraph.
D. Description
The work instructions are divided into 31 airplane groups and 9 parts.
PART 1, PART 2, PART 3, PART 4, and PART 5 work instructions are divided into 3 work packages
because of the different wire bundle changes and airplanes without and with Airstairs.
PART 6 work instructions are for Operators that already ordered the kit from the original release, and
want to re-work the kit for airplanes with Airstairs.
PART 7, PART 8, PART 9 provide instructions to change the J2802 relay box for airplanes that
incorporated the original release of the service bulletin.
NOTE: When submitting a Publication Change Request (PCR) to Boeing to incorporate this service
bulletin in the affected manuals, please notify Boeing if Auxiliary Tanks are installed on these
airplanes. If Boeing is not notified about the Auxiliary Tanks, Boeing will assume that the
airplanes in these groups do not have Auxiliary (AUX) tanks and no AUX Tank changes to
the affected manuals will be done.
Group 1-13, 15-16:
PART 1 - AIRPLANES WITH CENTER FUEL TANKS AND WITHOUT AUXILIARY (AUX) FUEL
TANKS
1. Work Package 1:
In the J2802 box assembly, install the wire bundles W1760 and W1770.
2. Work Package 2:
Get access into the main electronics compartment. Between the E2 and E3 rack support posts,
install the J2802 box assembly.
3. Work Package 3:
In the flight compartment, get access to the P5 overhead panel, P6 relay panel or P6 relay modules.
Above the P5 overhead panel, make a change to the wire bundles W36, W368 and W386. Between
the P6 disconnect panel and the fuel boost pump relays R54 and R55, make a change to the wire
bundle W44.
In the flight and main electronics compartments, between the P6 disconnect panel and the J2802
box assembly, install the new wire bundles W1764 and W1774.
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In the main electronics compartment, at the J2802 box assembly, install the time delay relays
R3318 and R3321.
Do a functional test of the fuel boost pumps to make sure the changed control system operates
correctly.
Group 17-18:
PART 2 - AIRPLANES WITH CENTER TANKS AND WIRE PROVISION FOR AUXILIARY (AUX)
FUEL TANKS, AND AIRSTAIRS
1. Work Package 1:
In the J2802 box assembly, install the wire bundles W1760 and W1770.
2. Work Package 2:
Get access into the main electronics compartment. Between the E2 and E3 rack support posts,
install the J2802 box assembly.
3. Work Package 3:
NOTE: Airplanes in group 17 and 18 have been delivered with provisional wires for future Auxiliary
Tank installation. Operators that installed AUX tanks with Fuel Boost Pumps on these
airplanes need to install an Auto Shutoff system. FAA may release an AD to require that
all airplanes that have AUX tanks with Fuel Boost Pumps should install an Auto Shutoff
system.
In the flight compartment, get access to the P5 overhead panel, P6 relay panel or P6 relay modules.
Above the P5 overhead panel, make a change to the wire bundles W36, W368 and W386. Between
the P6 disconnect panel and the fuel boost pump relays R54 and R55, make a change to the wire
bundle W44. For the airplanes that have an auxiliary fuel tank, between the P6 disconnect panel
and the fuel boost pump relays R146 and R147, make a change to the wire bundle W44.
In the flight and main electronics compartments, between the P6 disconnect panel and the J2802
box assembly, install the new wire bundles W1764 and W1774.
In the main electronics compartment, at the J2802 box assembly, install the time delay relays
R3318 and R3321. For the airplanes that have auxiliary fuel tank, at the J2802 box assembly,
install the time delay relays R3327 and R3329.
Do a functional test of the fuel boost pumps to make sure the changed control system operates
correctly.
Group 19-20:
PART 3 - AIRPLANES WITH CENTER AND AUXILIARY (AUX) FUEL TANKS
1. Work Package 1:
In the J2802 box assembly, install the wire bundles W1760 and W1770.
2. Work Package 2:
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### Page 34

Get access into the main electronics compartment. Between the E2 and E3 rack support posts,
install the J2802 box assembly.
3. Work Package 3:
In the flight compartment, get access to the P5 overhead panel, P6 relay panel or P6 relay modules.
Above the P5 overhead panel, make a change to the wire bundles W36, W368 and W386. Between
the P6 disconnect panel and the fuel boost pump relays R54 and R55, make a change to the wire
bundle W44. Between the P6 disconnect panel and the fuel boost pump relays R146 and R147,
make a change to the wire bundle W44.
In the flight and main electronics compartments, between the P6 disconnect panel and the J2802
box assembly, install the new wire bundles W1764 and W1774.
In the main electronics compartment, at the J2802 box assembly, install the time delay relays
R3318 and R3321. At the J2802 box assembly, install the time delay relays R3327 and R3329.
Do a functional test of the fuel boost pumps to make sure the changed control system operates
correctly.
Group 14, 21-29, 31:
PART 4 - AIRPLANES WITH CENTER FUEL TANKS AND WITHOUT AUXILIARY (AUX) FUEL
TANKS, AND AIRSTAIRS
1. Work Package 1:
Change J2802 Box Assy if/as necessary.
In the J2802 box assembly, install the wire bundles W1760 and W1770.
2. Work Package 2:
Get access into the main electronics compartment. Between the E2 and E3 rack support posts,
install the J2802 box assembly.
3. Work Package 3:
In the flight compartment, get access to the P5 overhead panel, P6 relay panel or P6 relay modules.
Above the P5 overhead panel, make a change to the wire bundles W36, W368 and W386. Between
the P6 disconnect panel and the fuel boost pump relays R54 and R55, make a change to the wire
bundle W44.
In the flight and main electronics compartments, between the P6 disconnect panel and the J2802
box assembly, install the new wire bundles W1764 and W1774.
In the main electronics compartment, at the J2802 box assembly, install the time delay relays
R3318 and R3321.
Do a functional test of the fuel boost pumps to make sure the changed control system operates
correctly.
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### Page 35

Group 30:
PART 5 - AIRPLANES WITH CENTER AND AUXILIARY (AUX) FUEL TANKS, AND AIRSTAIRS
1. Work Package 1:
Change J2802 Box Assy if/as necessary.
In the J2802 box assembly, install the wire bundles W1760 and W1770.
2. Work Package 2:
Get access into the main electronics compartment. Between the E2 and E3 rack support posts,
install the J2802 box assembly.
3. Work Package 3:
In the flight compartment, get access to the P5 overhead panel, P6 relay panel or P6 relay modules.
Above the P5 overhead panel, make a change to the wire bundles W36, W368 and W386. Between
the P6 disconnect panel and the fuel boost pump relays R54 and R55, make a change to the wire
bundle W44. Between the P6 disconnect panel and the fuel boost pump relays R146 and R147,
make a change to the wire bundle W44.
In the flight and main electronics compartments, between the P6 disconnect panel and the J2802
box assembly, install the new wire bundles W1764 and W1774.
In the main electronics compartment, at the J2802 box assembly, install the time delay relays
R3318 and R3321. At the J2802 box assembly, install the time delay relays R3327 and R3329.
Do a functional test of the fuel boost pumps to make sure the changed control system operates
correctly.```````
Group 14, 17-18, 21-31:
PART 6 - AIRPLANES WITH CENTER AND AUXILIARY (AUX) FUEL TANKS, AND AIRSTAIRS
1. Change J2802 Box Assy for airplanes with Airstairs.
NOTE: Operators that have airplanes with Airstairs that ordered and received the Top Kits given
in the original release of this service bulletin can use the J2802 Box assembly received
in the kit but they need to change the J2802 Box for airplanes with airstairs.
Group 1-16, 21-29, 31:
PART 7- CHANGE OF THE J2802 RELAY BOX FOR AIRPLANES THAT INCORPORATED THE
ORIGINAL RELEASE OF THE SERVICE BULLETIN
1. Install Labels on the J2802 Box Assy, change wire W1760 termination at switch S3318, change
wire W1770 termination at switch S3321, inspect the imprinted text on the ID tape of wire
W368-031-20, and Do the Center Fuel Boost Pump Auto Shutoff Functional Test.
NOTE: Only airplanes that were in Group 1 through 16 of the Original Release of this service
bulletin and incorporated the changes provided in the Original Release of the service
bulletin have to do the work provided in PART 7.
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### Page 36

Group 17-18:
PART 8- CHANGE OF THE J2802 RELAY BOX FOR AIRPLANES THAT INCORPORATED THE
ORIGINAL RELEASE OF THE SERVICE BULLETIN
1. Install the Labels on the J2802 Box Assy, change wire W1760 termination at switch S3318, change
wire W1770 termination at switch S3321, Inspect the imprinted text on the ID tape of wire
W368-031-20, Do the Center Fuel Boost Pump Auto Shutoff Functional Test, Do the Auxiliary Fuel
Boost Pump Auto Shutoff Functional Test for airplanes with Auxiliary Tank installed..
NOTE: Only airplanes that were in Group 17 and 18 of the Original Release of this service bulletin
and incorporated the changes provided in the Original Release of the service bulletin
have to do the work provided in PART 8.
NOTE: Airplanes in Group 17 and 18 have been delivered without Auxiliary Tanks but with wire
provisions for Auxiliary Tank Installation. It was necessary to do the change given in
Figure 7 of the Original Release of the service bulletin only if Auxiliary Tank with Fuel
Boost Pumps were installed on the airplane. If Auxiliary Tank is not installed, it is not
necessary to do the changes of wire W1760 in accordance with Figure 7 of this revision.
Group 19-20, 30:
PART 9- CHANGE OF THE J2802 RELAY BOX FOR AIRPLANES THAT INCORPORATED THE
ORIGINAL RELEASE OF THE SERVICE BULLETIN
1. Install the Labels on the J2802 Box Assy, change wire W1760 termination at switch S3318, change
wire W1770 termination at switch S3321, Inspect the imprinted text on the ID tape of wire
W368-031-20, Do the Center Fuel Boost Pump Auto Shutoff Functional Test, Do the Auxiliary Fuel
Boost Pump Auto Shutoff Functional Test.
NOTE: Only airplanes that were in Group 19 through 20 of the Original Release of this service
bulletin and incorporated the changes provided in the Original Release of the service
bulletin have to do the work provided in PART 9.
Revision 1: More work is necessary on the airplane(s) changed in accordance with the original issue
of this service bulletin. Operators that incorporated the original issue of this SB, have to change the
labels and wire termination in the J2802 relay box assembly in accordance with Figures 3, 4, 5, 6, 7,
8, 9, or 10 as applicable, and do a functional test within the compliance time specified in paragraph 1.
E. Also, operators have to inspect the imprinted text on the ID tape of wire W368-031-20 installed in
accordance with Figures 82 and 83 or Figures 82 and 84 within the compliance time specified in
paragraph 1. E. Some wires W368-031-20 delivered in the kits have been identified incorrectly as
"W036-031-20". If they are imprinted as "W036-031-20", then correct that text of the I.D. tapes to
"W0368-031-20" using a permanent marker.
Revision 2:
No more work is necessary on the airplane(s) Groups 1-16, 19-31 changed in accordance with Revision
1 of this service bulletin, dated March 26, 2012. More work is necessary for airplanes Group 17-18 that
changed the airplanes in accordance with Part 7 of Revision 1 of this service bulletin dated March 26,
2012. These airplanes need to do also the Auxiliary Fuel Boost Pump Auto Shutoff Functional Test in
accordance with PART 8 if the Auxiliary Tank is installed.
The work in this service bulletin is done in the maintenance zone(s) given below.
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Group 1, 4-5, 8, 19, 21, 24, 26, 30:
Affected Maintenance Zones
ZoneModel
102, 205737-400
Group 2, 6-7, 11-12, 14-18, 20, 22, 25, 28-29:
Affected Maintenance Zones
ZoneModel
102, 205737-300
Group 3, 10:
Affected Maintenance Zones
ZoneModel
102, 205737-300, 737-500
Group 9, 13, 31:
Affected Maintenance Zones
ZoneModel
102, 205737-500
Group 23:
Affected Maintenance Zones
ZoneModel
102, 205737-300, 737-400, 737-500
Group 27:
Affected Maintenance Zones
ZoneModel
102, 105, 205737-300
Group 27:
Affected Maintenance Zones
ZoneModel
105, 205737-500
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Group 31:
Affected Maintenance Zones
ZoneModel
105, 205737-400
E. Compliance
Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2010-NM-189-AD, is
related to this service bulletin.
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to
this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this
service bulletin mandatory.
Boeing recommends that the change given in this service bulletin be done within 36 months after the
Revision 2 date of this service bulletin.
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.
This service bulletin has been approved by the FAA. In addition, the Manager of the FAA Seattle Aircraft
Certification Office approves the installation of the automatic shutoff system for the center tank fuel
pumps in accordance with this service bulletin and the installation of a modified P5-2 Fuel System
Module in accordance with Service Bulletin 737-28A1210, Revision 2, as an alternative method of
compliance (AMOC) to the requirements of paragraph (a) of AD 2001-08-24. Compliance with the
conditions of this AMOC approval requires concurrent incorporation of the associated revisions to
Airplane Flight Manual Sections 1 and 3 and incorporation of Airworthiness Limitations (AWL)
28-AWL-20in Boeing document "737-100/200/200C/300/400/500 Airworthiness Limitations (AWLs)
and Certification Maintenance Requirements (CMRs), D6-38278-CMR," into the operator's maintenance
documentation. In order to operate a mixed fleet of airplanes, some having automatic shutoff installed
and others without automatic shutoff, it will be necessary to install a placard in the flight deck of airplanes
that do not have automatic shutoff installed to alert the crew that the procedures required by paragraph(a)
of AD 2001-08-24 must be followed on that airplane. The placard should read as follows (alternative
placard wording may be used if approved by an appropriate FAA Principal Operations Inspector):
'AD 2001-08-24 fuel usage restrictions required"
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If an operator would like to use a different method of placarding their airplanes for operation as a mixed
fleet, a request for approval of an AMOC should be submitted to the Seattle Aircraft Certification Office.
All provisions of AD 2001-08-24 that are not specifically referenced in the above statement remain fully
applicable and must be complied with.
G. Manpower
The table below shows an estimate of the task-hours necessary to do 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 inspect the work
— Time to cure the materials
— Time to find the tools.
Group 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151FIGURE 1
--2FIGURE 3 (a)
3.607.202FIGURE 4
3.607.202FIGURE 5
0.150.151FIGURE 11
1.001.001FIGURE 12
1.001.001FIGURE 14
2.002.001FIGURE 15
0.500.501FIGURE 16
1.001.001FIGURE 18
1.501.501FIGURE 19
--2FIGURE 20 (a)
2.755.502FIGURE 21
--1FIGURE 44 (a)
3.803.801FIGURE 45
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
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Group 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 2, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151FIGURE 1
--2FIGURE 3 (a)
3.607.202FIGURE 4
3.607.202FIGURE 5
0.150.151FIGURE 11
1.001.001FIGURE 12
1.001.001FIGURE 14
2.002.001FIGURE 15
0.500.501FIGURE 16
1.001.001FIGURE 18
1.501.501FIGURE 19
--2FIGURE 20 (a)
2.755.502FIGURE 22
--1FIGURE 44 (a)
3.803.801FIGURE 46
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
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### Page 41

Group 2, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 2, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151FIGURE 1
--2FIGURE 3 (a)
3.607.202FIGURE 4
3.607.202FIGURE 5
0.150.151FIGURE 11
1.001.001FIGURE 12
1.001.001FIGURE 14
2.002.001FIGURE 15
0.500.501FIGURE 16
1.001.001FIGURE 18
1.501.501FIGURE 19
--2FIGURE 20 (a)
2.755.502FIGURE 22
--1FIGURE 44 (a)
3.803.801FIGURE 47
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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### Page 42

Group 3:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151FIGURE 1
--2FIGURE 3 (a)
3.607.202FIGURE 4
3.607.202FIGURE 5
0.150.151FIGURE 11
1.001.001FIGURE 12
1.001.001FIGURE 14
2.002.001FIGURE 15
0.500.501FIGURE 16
1.001.001FIGURE 18
1.501.501FIGURE 19
--2FIGURE 20 (a)
2.755.502FIGURE 22
--1FIGURE 44 (a)
3.803.801FIGURE 48
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 4, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151FIGURE 1
--2FIGURE 3 (a)
3.607.202FIGURE 4
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### Page 43

Group 4, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
3.607.202FIGURE 5
0.150.151FIGURE 11
1.001.001FIGURE 12
1.001.001FIGURE 14
2.002.001FIGURE 15
0.500.501FIGURE 16
1.001.001FIGURE 18
1.501.501FIGURE 19
--2FIGURE 20 (a)
2.755.502FIGURE 23
--1FIGURE 44 (a)
3.803.801FIGURE 49
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 4, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151FIGURE 1
--2FIGURE 3 (a)
3.607.202FIGURE 4
3.607.202FIGURE 5
0.150.151FIGURE 11
1.001.001FIGURE 12
1.001.001FIGURE 14
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### Page 44

Group 4, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
2.002.001FIGURE 15
0.500.501FIGURE 16
1.001.001FIGURE 18
1.501.501FIGURE 19
--2FIGURE 20 (a)
2.755.502FIGURE 23
--1FIGURE 44 (a)
3.803.801FIGURE 50
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 5:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151FIGURE 1
--2FIGURE 3 (a)
3.607.202FIGURE 4
3.607.202FIGURE 5
0.150.151FIGURE 11
1.001.001FIGURE 12
1.001.001FIGURE 14
2.002.001FIGURE 15
0.500.501FIGURE 16
1.001.001FIGURE 18
1.501.501FIGURE 19
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### Page 45

Group 5:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
--2FIGURE 20 (a)
2.755.502FIGURE 23
--1FIGURE 44 (a)
3.803.801FIGURE 51
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 6, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151FIGURE 1
--2FIGURE 3 (a)
3.607.202FIGURE 4
3.607.202FIGURE 5
0.150.151FIGURE 11
1.001.001FIGURE 12
1.001.001FIGURE 14
2.002.001FIGURE 15
0.500.501FIGURE 16
1.001.001FIGURE 18
1.501.501FIGURE 19
--2FIGURE 20 (a)
2.755.502FIGURE 24
--1FIGURE 44 (a)
3.803.801FIGURE 52
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### Page 46

Group 6, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 6, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151FIGURE 1
--2FIGURE 3 (a)
3.607.202FIGURE 4
3.607.202FIGURE 5
0.150.151FIGURE 11
1.001.001FIGURE 12
1.001.001FIGURE 14
2.002.001FIGURE 15
0.500.501FIGURE 16
1.001.001FIGURE 18
1.501.501FIGURE 19
--2FIGURE 20 (a)
2.755.502FIGURE 24
--1FIGURE 44 (a)
3.803.801FIGURE 53
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
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### Page 47

Group 6, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 7:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151FIGURE 1
--2FIGURE 3 (a)
3.607.202FIGURE 4
3.607.202FIGURE 5
0.150.151FIGURE 11
1.001.001FIGURE 12
1.001.001FIGURE 14
2.002.001FIGURE 15
0.500.501FIGURE 16
1.001.001FIGURE 18
1.501.501FIGURE 19
--2FIGURE 20 (a)
2.755.502FIGURE 24
--1FIGURE 44 (a)
3.803.801FIGURE 59
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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### Page 48

Group 7:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 8:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151FIGURE 1
--2FIGURE 3 (a)
3.607.202FIGURE 4
3.607.202FIGURE 5
0.150.151FIGURE 11
1.001.001FIGURE 12
1.001.001FIGURE 14
2.002.001FIGURE 15
0.500.501FIGURE 16
1.001.001FIGURE 18
1.501.501FIGURE 19
--2FIGURE 20 (a)
2.755.502FIGURE 25
--1FIGURE 44 (a)
3.803.801FIGURE 51
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 85
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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### Page 49

Group 9:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151FIGURE 1
--2FIGURE 3 (a)
3.607.202FIGURE 4
3.607.202FIGURE 5
0.150.151FIGURE 11
1.001.001FIGURE 12
1.001.001FIGURE 14
2.002.001FIGURE 15
0.500.501FIGURE 16
1.001.001FIGURE 18
1.501.501FIGURE 19
--2FIGURE 20 (a)
2.755.502FIGURE 26
--1FIGURE 44 (a)
3.803.801FIGURE 54
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 10:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151FIGURE 1
--2FIGURE 3 (a)
3.607.202FIGURE 4
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### Page 50

Group 10:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
3.607.202FIGURE 5
0.150.151FIGURE 11
1.001.001FIGURE 12
1.001.001FIGURE 14
2.002.001FIGURE 15
0.500.501FIGURE 16
1.001.001FIGURE 18
1.501.501FIGURE 19
--2FIGURE 20 (a)
2.755.502FIGURE 27
--1FIGURE 44 (a)
3.803.801FIGURE 55
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 11, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151FIGURE 1
--2FIGURE 3 (a)
3.607.202FIGURE 4
3.607.202FIGURE 5
0.150.151FIGURE 11
1.001.001FIGURE 12
1.001.001FIGURE 14
Export Controlled ECCN: 9E991 - BOEING
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### Page 51

Group 11, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
2.002.001FIGURE 15
0.500.501FIGURE 16
1.001.001FIGURE 18
1.501.501FIGURE 19
--2FIGURE 20 (a)
2.755.502FIGURE 27
--1FIGURE 44 (a)
3.803.801FIGURE 62
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 11, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151FIGURE 1
--2FIGURE 3 (a)
3.607.202FIGURE 4
3.607.202FIGURE 5
0.150.151FIGURE 11
1.001.001FIGURE 12
1.001.001FIGURE 14
2.002.001FIGURE 15
0.500.501FIGURE 16
1.001.001FIGURE 18
1.501.501FIGURE 19
Export Controlled ECCN: 9E991 - BOEING
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### Page 52

Group 11, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
--2FIGURE 20 (a)
2.755.502FIGURE 27
--1FIGURE 44 (a)
3.803.801FIGURE 63
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 12, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151FIGURE 1
--2FIGURE 3 (a)
3.607.202FIGURE 4
3.607.202FIGURE 5
0.150.151FIGURE 11
1.001.001FIGURE 12
1.001.001FIGURE 14
2.002.001FIGURE 15
0.500.501FIGURE 16
1.001.001FIGURE 18
1.501.501FIGURE 19
--2FIGURE 20 (a)
2.755.502FIGURE 28
--1FIGURE 44 (a)
3.803.801FIGURE 56
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Work - See page 1 for details.
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### Page 53

Group 12, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 12, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151FIGURE 1
--2FIGURE 3 (a)
3.607.202FIGURE 4
3.607.202FIGURE 5
0.150.151FIGURE 11
1.001.001FIGURE 12
1.001.001FIGURE 14
2.002.001FIGURE 15
0.500.501FIGURE 16
1.001.001FIGURE 18
1.501.501FIGURE 19
--2FIGURE 20 (a)
2.755.502FIGURE 28
--1FIGURE 44 (a)
3.803.801FIGURE 57
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
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Work - See page 1 for details.
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### Page 54

Group 12, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 13:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151FIGURE 1
--2FIGURE 3 (a)
3.607.202FIGURE 4
3.607.202FIGURE 5
0.150.151FIGURE 11
1.001.001FIGURE 12
1.001.001FIGURE 14
2.002.001FIGURE 15
0.500.501FIGURE 16
1.001.001FIGURE 18
1.501.501FIGURE 19
--2FIGURE 20 (a)
2.755.502FIGURE 29
--1FIGURE 44 (a)
3.803.801FIGURE 58
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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### Page 55

Group 13:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 14, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
3.607.202FIGURE 4
3.607.202FIGURE 5
1.501.501FIGURE 19
--2FIGURE 20 (a)
2.755.502FIGURE 30
--1FIGURE 44 (a)
3.803.801FIGURE 60
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
2.752.751FIGURE 92 (b)
2.802.801FIGURE 94 (b)
0.150.151FIGURE 96 (c)
1.201.201FIGURE 98
0.500.501FIGURE 100
0.600.601FIGURE 102
2.302.301FIGURE 104
--1FIGURE 105 (a)
0.650.651FIGURE 106
4.0012.003Close Access
1.002.002Test
54.0096.75TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
(b) The task hours for this figure to be used only if operators ordered and received the Top
Kits given in the original release of this service bulletin and they need to change the
J2802 Box Assembly.
(c) See related wire connection figure for wire routing task hours.
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Work - See page 1 for details.
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### Page 56

Group 14, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
3.607.202FIGURE 4
3.607.202FIGURE 5
1.501.501FIGURE 19
--2FIGURE 20 (a)
2.755.502FIGURE 30
--1FIGURE 44 (a)
3.803.801FIGURE 61
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
2.752.751FIGURE 92 (b)
2.802.801FIGURE 94 (b)
0.150.151FIGURE 96 (c)
1.201.201FIGURE 98
0.500.501FIGURE 100
0.600.601FIGURE 102
2.302.301FIGURE 104
--1FIGURE 105 (a)
0.650.651FIGURE 106
4.0012.003Close Access
1.002.002Test
54.0096.75TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
(b) The task hours for this figure to be used only if operators ordered and received the Top
Kits given in the original release of this service bulletin and they need to change the
J2802 Box Assembly.
(c) See related wire connection figure for wire routing task hours.
Group 15, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
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### Page 57

Group 15, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
0.150.151FIGURE 1
--2FIGURE 3 (a)
3.607.202FIGURE 4
3.607.202FIGURE 5
0.150.151FIGURE 11
1.001.001FIGURE 12
1.001.001FIGURE 14
2.002.001FIGURE 15
0.500.501FIGURE 16
1.001.001FIGURE 18
1.501.501FIGURE 19
--2FIGURE 20 (a)
2.755.502FIGURE 31
--1FIGURE 44 (a)
3.803.801FIGURE 64
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 15, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151FIGURE 1
--2FIGURE 3 (a)
3.607.202FIGURE 4
3.607.202FIGURE 5
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### Page 58

Group 15, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
0.150.151FIGURE 11
1.001.001FIGURE 12
1.001.001FIGURE 14
2.002.001FIGURE 15
0.500.501FIGURE 16
1.001.001FIGURE 18
1.501.501FIGURE 19
--2FIGURE 20 (a)
2.755.502FIGURE 31
--1FIGURE 44 (a)
3.803.801FIGURE 65
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 86
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 16:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
0.150.151FIGURE 1
--2FIGURE 3 (a)
3.607.202FIGURE 4
3.607.202FIGURE 5
0.150.151FIGURE 11
1.001.001FIGURE 12
1.001.001FIGURE 14
2.002.001FIGURE 15
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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58 of 439
BOEING SERVICE BULLETIN 737-28A1216

### Page 59

Group 16:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
0.500.501FIGURE 16
1.001.001FIGURE 18
1.501.501FIGURE 19
--2FIGURE 20 (a)
2.755.502FIGURE 32
--1FIGURE 44 (a)
3.803.801FIGURE 48
--2FIGURE 82 (a)
8.2016.402FIGURE 83
7.6015.202FIGURE 85
1.501.501FIGURE 88
1.501.501FIGURE 90
4.0012.003Close Access
1.002.002Test
48.8591.60TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
Group 17, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
3.607.202FIGURE 7 (b)
3.607.202FIGURE 8
3.607.202FIGURE 9 (b)
3.607.202FIGURE 10
1.501.501FIGURE 33
--2FIGURE 34 (a)
2.755.502FIGURE 38
2.304.602FIGURE 39 (b)
2.304.602FIGURE 40 (b)
--2FIGURE 66 (a)
3.803.801FIGURE 67
3.803.802FIGURE 69 (b)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: July 29, 2010
737-28A1216Revision 2: November 12, 2012
59 of 439
BOEING SERVICE BULLETIN 737-28A1216

### Page 60

Group 17, Configuration 1:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
16.3032.602FIGURE 84 (c)
15.1030.202FIGURE 87 (d)
3.003.001FIGURE 89
1.501.501FIGURE 91
3.003.001FIGURE 93 (e)
2.802.801FIGURE 95 (e)
0.150.151FIGURE 97 (f)
1.201.201FIGURE 99
0.500.501FIGURE 101
0.600.601FIGURE 103
--1FIGURE 105 (a)
0.750.751FIGURE 107
4.0012.003Close Access
1.002.002Test
84.75154.90TOTAL FOR EACH AIRPLANE
(a) This figure shows wire routes only. See the related wire connection figure for task hours.
(b) This figure is only applicable if Auxiliary Tank is installed. They are not counted in the
total "Task-Hours" and total "Elapsed Hours" time.
(c) It is necessary to install wires W1764-004-20, W1764-005-20, and W1764-006-20 given
in this figure only if Auxiliary Fuel Tanks with Fuel Boost Pumps are installed on the air-
plane.
(d) It is necessary to install wires W1774-004-20, W1774-005-20, and W1774-006-20 given
in this figure only if Auxiliary Fuel Tanks with Fuel Boost Pumps are installed on the air-
plane.
(e) The task hours for this figure to be used only if operators ordered and received the Top
Kits given in the original release of this service bulletin and they need to change the
J2802 Box Assembly.
(f) See related wire connection figure for wire routing task hours.
Group 17, Configuration 2:
Elapsed HoursTask-HoursNumber of Per-
sons
Task
4.0012.003Open Access
3.607.202FIGURE 7 (b)
3.607.202FIGURE 8
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: July 29, 2010
737-28A1216Revision 2: November 12, 2012
60 of 439
BOEING SERVICE BULLETIN 737-28A1216

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