# Boeing Alert Service Bulletin 737-31A1325: Boeing - Service Bulletin

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- Document: [Boeing Alert Service Bulletin 737-31A1325](https://openairdocs.org/service-documents/boeing/737-31a1325.md)
- Title as filed: Boeing - Service Bulletin
- Pages: 178
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## Text

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### Page 1

Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-31A1325
Original Issue: January 11, 2010
Revision 1: July 05, 2012
ATA System: 3100
SUBJECT: INDICATING / RECORDING SYSTEMS - Aural Warning System - Installation of the
Cabin Altitude Warning System and Takeoff Configuration Warning System Lights
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Unpublished Work.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: January 11, 2010
737-31A1325Revision 1: July 05, 2012
1 of 178
4.0

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Table of Contents
Revision Transmittal Sheet ............................................ 7
Summary ...................................................... 9
1. PLANNING INFORMATION ........................................ 1 1
A. Effectivity ............................................... 1 1
1. Airplanes ............................................ 1 1
2. Spares Affected ........................................ 2 8
B. Concurrent Requirements ...................................... 2 8
C. Reason ................................................ 2 8
D. Description .............................................. 2 8
E. Compliance .............................................. 3 0
F. Approval ............................................... 3 0
G. Manpower .............................................. 3 0
H. Weight and Balance Changes .................................... 3 1
I. Electrical Load Data ......................................... 3 1
J. References .............................................. 3 1
1. Existing Data: ......................................... 3 1
2. Data Supplied with this Service Bulletin: ........................... 3 2
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 3 2
K. Publications Affected ........................................ 3 2
L. Interchangeability and Intermixability of Parts ........................... 3 2
M. Software Accomplishment Summary ................................ 3 2
2. MATERIAL INFORMATION ........................................ 3 3
A. Material - Price and Availability ................................... 3 3
B. Industry Support Information .................................... 3 3
C. Parts Necessary for Each Airplane ................................. 3 3
1. Kits/Parts: ........................................... 3 3
2. Parts and Materials Supplied by the Operator: ........................ 3 6
3. Parts Modified and Reidentified: ............................... 3 6
4. Parts Removed and Not Replaced: .............................. 4 1
D. Parts Necessary to Change Spares ................................. 4 2
E. Special Tooling - Price and Availability ............................... 4 2
F. Special Tooling Necessary to do this Service Bulletin ....................... 4 2
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 4 3
A. GENERAL INFORMATION ..................................... 4 3
B. WORK INSTRUCTIONS ....................................... 4 3
FIGURE 1: P2-2 CENTER INSTRUMENT PANEL REMOVAL [Group 1-43] .............. 5 2
FIGURE 2: MODIFICATION OF THE P2-2 CENTER INSTRUMENT PANEL [Group 1-43] ....... 5 4
FIGURE 3: LIGHT ASSEMBLY INSTALLATION [Group 1-43] ...................... 5 7
FIGURE 4: WIRE BUNDLE W066 WIRE ROUTING [Group 1-24, 26-30, 40, 42] ............ 6 0
FIGURE 5: WIRE BUNDLE W066 WIRE ROUTING ........................... 6 1
FIGURE 6: WIRE BUNDLE W066 WIRE ROUTING [Group 25, 31-38, 41, 43] ............. 6 2
FIGURE 7: WIRE BUNDLES W002 AND W066 WIRE ROUTING [Group 39] .............. 6 3
FIGURE 8: WIRE BUNDLE W066 WIRING CHANGE .......................... 6 5
FIGURE 9: WIRE BUNDLE W066 WIRING CHANGE [Group 1] ..................... 6 6
FIGURE 10: WIRE BUNDLE W066 WIRING CHANGE [Group 13, 20] .................. 6 8
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FIGURE 11: WIRE BUNDLE W066 WIRING CHANGE [Group 5, 19] ................... 7 0
FIGURE 12: WIRE BUNDLE W066 WIRING CHANGE [Group 6-7] .................... 7 2
FIGURE 13: WIRE BUNDLE W066 WIRING CHANGE [Group 4, 8] ................... 7 4
FIGURE 14: WIRE BUNDLE W066 WIRING CHANGE [Group 9] ..................... 7 6
FIGURE 15: WIRE BUNDLE W066 WIRING CHANGE .......................... 7 8
FIGURE 16: WIRE BUNDLE W066 WIRING CHANGE [Group 3] ..................... 7 9
FIGURE 17: WIRE BUNDLE W066 WIRING CHANGE [Group 14] .................... 8 1
FIGURE 18: WIRE BUNDLE W066 WIRING CHANGE [Group 15] .................... 8 3
FIGURE 19: WIRE BUNDLE W066 WIRING CHANGE [Group 16] .................... 8 5
FIGURE 20: WIRE BUNDLE W066 WIRING CHANGE [Group 17-18] .................. 8 7
FIGURE 21: WIRE BUNDLE W066 WIRING CHANGE [Group 2, 12] ................... 8 9
FIGURE 22: WIRE BUNDLE W066 WIRING CHANGE [Group 10] .................... 9 1
FIGURE 23: WIRE BUNDLE W066 WIRING CHANGE [Group 21, 42] .................. 9 3
FIGURE 24: WIRE BUNDLE W066 WIRING CHANGE [Group 22] .................... 9 5
FIGURE 25: WIRE BUNDLE W066 WIRING CHANGE [Group 23] .................... 9 7
FIGURE 26: WIRE BUNDLE W066 WIRING CHANGE [Group 11, 24] .................. 9 9
FIGURE 27: WIRE BUNDLE W066 WIRING CHANGE [Group 26-27] .................. 1 0 1
FIGURE 28: WIRE BUNDLE W066 WIRING CHANGE .......................... 1 0 3
FIGURE 29: WIRE BUNDLE W066 WIRING CHANGE [Group 28] ................... 1 0 4
FIGURE 30: WIRE BUNDLE W066 WIRING CHANGE [Group 29] ................... 1 0 6
FIGURE 31: WIRE BUNDLE W066 WIRING CHANGE .......................... 1 0 8
FIGURE 32: WIRE BUNDLE W066 WIRING CHANGE .......................... 1 0 9
FIGURE 33: WIRE BUNDLE W066 WIRING CHANGE [Group 30] ................... 1 1 0
FIGURE 34: WIRE BUNDLE W066 WIRING CHANGE [Group 31] ................... 1 1 2
FIGURE 35: WIRE BUNDLE W066 WIRING CHANGE [Group 32] ................... 1 1 4
FIGURE 36: WIRE BUNDLE W066 WIRING CHANGE [Group 33] ................... 1 1 6
FIGURE 37: WIRE BUNDLE W066 WIRING CHANGE [Group 34] ................... 1 1 8
FIGURE 38: WIRE BUNDLE W066 WIRING CHANGE [Group 25] ................... 1 2 0
FIGURE 39: WIRE BUNDLE W066 WIRING CHANGE [Group 35] ................... 1 2 2
FIGURE 40: WIRE BUNDLE W066 WIRING CHANGE [Group 36] ................... 1 2 4
FIGURE 41: WIRE BUNDLE W066 WIRING CHANGE [Group 37] ................... 1 2 6
FIGURE 42: WIRE BUNDLE W066 WIRING CHANGE .......................... 1 2 8
FIGURE 43: WIRE BUNDLE W066 WIRING CHANGE [Group 38] ................... 1 2 9
FIGURE 44: WIRE BUNDLE W066 WIRING CHANGE [Group 39] ................... 1 3 1
FIGURE 45: WIRE BUNDLE W002 WIRE ROUTING [Group 1-24, 26-30, 40] ............. 1 3 3
FIGURE 46: WIRE BUNDLE W002 WIRE ROUTING [Group 25, 31-38, 41] .............. 1 3 4
FIGURE 47: WIRE BUNDLE W002 WIRING CHANGE [Group 1, 3-9, 13-16, 19-20] .......... 1 3 5
FIGURE 48: WIRE BUNDLE W002 WIRING CHANGE [Group 2, 12, 17-18] .............. 1 3 7
FIGURE 49: WIRE BUNDLE W002 WIRING CHANGE [Group 10, 21-23, 40, 42-43] .......... 1 3 9
FIGURE 50: WIRE BUNDLE W002 WIRING CHANGE [Group 11, 24, 26-27] .............. 1 4 1
FIGURE 51: WIRE BUNDLE W002 WIRING CHANGE .......................... 1 4 3
FIGURE 52: WIRE BUNDLE W002 WIRING CHANGE [Group 28] ................... 1 4 4
FIGURE 53: WIRE BUNDLE W002 WIRING CHANGE [Group 29] ................... 1 4 6
FIGURE 54: WIRE BUNDLE W002 WIRING CHANGE .......................... 1 4 8
FIGURE 55: WIRE BUNDLE W002 WIRING CHANGE [Group 30] ................... 1 4 9
FIGURE 56: WIRE BUNDLE W002 WIRING CHANGE .......................... 1 5 1
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FIGURE 57: WIRE BUNDLE W002 WIRING CHANGE .......................... 1 5 2
FIGURE 58: WIRE BUNDLE W002 WIRING CHANGE [Group 25, 31-34] ................ 1 5 3
FIGURE 59: WIRE BUNDLE W002 WIRING CHANGE [Group 35-38] .................. 1 5 5
FIGURE 60: WIRE BUNDLE W002 WIRING CHANGE [Group 39] ................... 1 5 7
FIGURE 61: WIRE BUNDLE W246 WIRE ROUTING [Group 1-43] ................... 1 5 9
FIGURE 62: WIRE BUNDLE W246 WIRING CHANGE [Group 1, 3-4, 7, 9-10, 12-17, 19, 21-26, 28, 30-31,
33-35, 37-39, 41-43] ..................................... 1 6 2
FIGURE 63: WIRE BUNDLE W246 WIRING CHANGE [Group 2, 5-6, 8, 11, 18, 20, 27, 29, 32, 36, 40] . 165
FIGURE 64: WIRE BUNDLE W246 WIRING CHANGE .......................... 1 6 8
FIGURE 65: WIRE BUNDLE W246 WIRING CHANGE .......................... 1 6 9
FIGURE 66: WIRE BUNDLE W246 WIRING CHANGE .......................... 1 7 0
FIGURE 67: P2-2 CENTER INSTRUMENT PANEL INSTALLATION [Group 1-43] ........... 1 7 1
FIGURE 68: WIRE BUNDLE W066 WIRING CHANGE [Group 40] ................... 1 7 3
FIGURE 69: WIRE BUNDLE W066 WIRING CHANGE [Group 41, 43] ................. 1 7 5
FIGURE 70: WIRE BUNDLE W002 WIRING CHANGE [Group 41] ................... 1 7 7
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Commercial 
Airplanes
737
Service Bulletin
ALERT
Revision Transmittal SheetNumber: 737-31A1325Original Issue: January 11, 2010
Revision 1: July 05, 2012
ATA System: 3100
SUBJECT: INDICATING / RECORDING SYSTEMS - Aural Warning System - Installation of the
Cabin Altitude Warning System and Takeoff Configuration Warning System Lights
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
Federal Aviation Administration (FAA) Airworthiness Directive AD 2011-03-14 is related to this service bulletin.
Also, airplanes Line Numbers 1 thru 291 have been moved to Group 44. The affected airplanes were in Groups
4, 14, 16-17, 24, 33, 36-37, 43 and 47 in the original issue of this service bulletin.
No more work is necessary on the airplanes changed in accordance with the original issue of this service bulletin.
REASON FOR REVISION
This revision is sent to add FAA Airworthiness Directive AD 2011-03-14 and correct typographical errors identified
by operators incorporating this change. Also, airplanes Line Numbers 1 thru 291 have been moved to Group
44.
These sections were changed:
1. In Summary Compliance and Paragraph 1.E., Compliance, added the AD 2011-03-14 reference.
2. In Paragraph 1.A.1., Airplanes, moved airplanes Line numbers 1 thru 291 to Group 44, these airplanes
were in Groups 4, 14, 16-17, 24, 33, 36-37, 43 and 47 in the original issue of this service bulletin
3. In Paragraph 1.F., Approval, added the Alternative Method Of Compliance (AMOC) paragraph.
4. In Paragraph 1.J.1., Existing Data, changed Aircraft Maintenance Manual (AMM) references and added
Airworthiness Directive.
5. In Paragraph 2.A., Material - Price and Availability, updated top kit price and ROLT. Also added a
footnote to the table.
6. In Paragraph 2.C.2., Parts and Materials Supplied by the Operator, added part number data.
7. In Paragraph 3.B., Work Instructions,
a. Removed the work instructions for figures 5, 8, 15, 28, 31-32, 42, 51, 54, 56-57 and 64-66.
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b. Moved Group 19 airplanes from Step 7.b to Step 7a.
c. Changed the AMM references in Step 1, 10, 11 and 12.
d. Removed the AMM references from Step 16.c.(2).
8. FIGURE 1, changed the graphic and added a new step.
9. FIGURE 2, step table, added a Standard Overhaul Practices Manual reference for part marking.
10. FIGURE 5, 8, 15, 28, 31-32, 42, 51, 54, 56-57 and 64-66 have been deleted.
11. FIGURE 9, 10 and 40, changed the graphics and part number in flag note table.
12. FIGURE 10-13, 20-21, 26-27,30, 35 and 40 changed the Wiring Diagram Manual (WDM) reference.
13. FIGURE 11-14, 16-27, 29-30, 33-39, 41, 43, 47-50, 52-53, 55 and 58-60 changed a part number in
flag note table.
14. FIGURE 61, changed the graphics.
15. FIGURES 62-63, added a note and changed footnotes.
16. FIGURE 63, changed WDM references.
17. FIGURE 67, changed the graphic and added new step.
18. FIGURE 68-70, added new figures.
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
January 11, 2010Original Issue:
July 05, 2012Revision 1:
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Commercial 
Airplanes
737
Service Bulletin
ALERT
SummaryNumber: 737-31A1325Original Issue: January 11, 2010
Revision 1: July 05, 2012
ATA System: 3100
SUBJECT: INDICATING / RECORDING SYSTEMS - Aural Warning System - Installation of the
Cabin Altitude Warning System and Takeoff Configuration Warning System Lights
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
CONCURRENT REQUIREMENTS
None
BACKGROUND
This service bulletin gives instructions to install two warning level indicator lights on the P2-2 center instrument
panel in the flight compartment. The installation of these lights will provide a visual indication to the flight crew
to be used in conjunction with the existing aural warning horn for cabin altitude and takeoff configuration alerts.
The visual warning lights are intended to provide additional notice to crews to prepare a correct takeoff
configuration, respond to excessive cabin altitude and avoid confusion between the takeoff configuration and
cabin altitude alerts. An unrecognized incorrect takeoff configuration or excessive cabin altitude could prevent
a continued safe flight and landing.
As a part of a service bulletin validation program, this change was completed on airplane PW234 by Service
Bulletin 737-31A1325 Validation Copy 1 and Installation Deviation Records 737-31A1325-001 through
737-31A1325-006 before the initial release of this service bulletin. The change completed on airplane PW234
by Service Bulletin 737-31A1325 Validation Copy 1 and Installation Deviation Records 737-31A1325-001 through
737-31A1325-006 is equivalent to the initial release of this service bulletin. Airplane PW234 has the configuration
of a Group 13 airplane.
Boeing Service Related Problem (SRP) 737-SRP-31-0042 is related to this service bulletin.
ACTION (PRR 35005-277RS)
Get access to the flight compartment. Remove the P2-2 center instrument panel to install two warning level
indicator lights on the panel and change three wire bundles. Reinstall the modified P2-2 center instrument panel.
Do a test of the warning level indicator lights.
On Group 44 airplanes, contact Boeing to get instructions for the change for this service bulletin, 737-31A1325
Revision 1, and do the work instructed by Boeing.
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EFFECTIVITY
All 737-100/-200/-200C/-300/-400/-500 Airplanes. Refer to Paragraph 1.A.1 Airplanes, for the list of affected
airplanes.
COMPLIANCE
Federal Aviation Administration (FAA) Airworthiness Directive AD 2011-03-14 is related to this service bulletin.
On Group 44 airplanes, contact Boeing to get instructions for the change for this service bulletin, 737-31A1325
Revision 1, and do the work instructed by Boeing.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
MANPOWER
Elapsed HoursTotal Task HoursAirplanes
20.5032.50Groups 1-43
MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
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Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-31A1325
Original Issue: January 11, 2010
Revision 1: July 05, 2012
ATA System: 3100
SUBJECT: INDICATING / RECORDING SYSTEMS - Aural Warning System - Installation of the
Cabin Altitude Warning System and Takeoff Configuration Warning System Lights
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
Refer to Service Bulletin Index Document D6-19567 Part 3 for Airplane Variable Number, Line
Number, and Serial Number data.
This service bulletin is for the airplanes shown below. Refer to PRR 35005-277RS for data about
this change.
DESCRIPTIONCONFIGURATIONGROUP
Wiring and P2 panel configuration differences-1
Wiring and P2 panel configuration differences-2
Wiring and P2 panel configuration differences-3
Wiring and P2 panel configuration differences-4
Wiring and P2 panel configuration differences-5
Wiring and P2 panel configuration differences-6
Wiring and P2 panel configuration differences-7
Wiring and P2 panel configuration differences-8
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DESCRIPTIONCONFIGURATIONGROUP
Wiring and P2 panel configuration differences-9
Wiring and P2 panel configuration differences-10
Wiring and P2 panel configuration differences-11
Wiring and P2 panel configuration differences-12
Wiring and P2 panel configuration differences-13
Wiring and P2 panel configuration differences-14
Wiring and P2 panel configuration differences-15
Wiring and P2 panel configuration differences-16
Wiring and P2 panel configuration differences-17
Wiring and P2 panel configuration differences-18
Wiring and P2 panel configuration differences-19
Wiring and P2 panel configuration differences-20
Wiring and P2 panel configuration differences-21
Wiring and P2 panel configuration differences-22
Wiring and P2 panel configuration differences-23
Wiring and P2 panel configuration differences-24
Wiring and P2 panel configuration differences-25
Wiring and P2 panel configuration differences-26
Wiring and P2 panel configuration differences-27
Wiring and P2 panel configuration differences-28
Wiring and P2 panel configuration differences-29
Wiring and P2 panel configuration differences-30
Wiring and P2 panel configuration differences-31
Wiring and P2 panel configuration differences-32
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DESCRIPTIONCONFIGURATIONGROUP
Wiring and P2 panel configuration differences-33
Wiring and P2 panel configuration differences-34
Wiring and P2 panel configuration differences-35
Wiring and P2 panel configuration differences-36
Wiring and P2 panel configuration differences-37
Wiring and P2 panel configuration differences-38
Wiring and P2 panel configuration differences-39
Wiring and P2 panel configuration differences-40
Wiring and P2 panel configuration differences-41
Wiring and P2 panel configuration differences-42
Wiring and P2 panel configuration differences-43
737 Airplanes with line numbers 1-291-44
Airplane Models:
737-100, 737-200, 737-200C, 737-300, 737-400, 737-500
GroupVariable Number
44PA001 - PA022
44PA099
44PA231 - PA232
44PC001 - PC005
44PG001 - PG075
44PG199
44PG201 - PG230
44PG251 - PG255
44PG271 - PG279
44PG301 - PG314
44PG331 - PG332
44PG351 - PG356
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GroupVariable Number
44PG375
44PG401 - PG403
44PG431 - PG442
44PG471 - PG475
44PG501 - PG505
44PG571 - PG583
1PG584 - PG586
44PG621 - PG630
44PG651 - PG652
44PG701 - PG705
1PH001
10PH011 - PH013
3PH021 - PH022
1PH023
3PH024
44PH701 - PH715
44PH731 - PH732
44PH741 - PH742
1PH743
44PJ001 - PJ002
3PJ003 - PJ006
9PJ007 - PJ009
44PJ031 - PJ032
44PJ071 - PJ072
44PJ101 - PJ104
1PJ105 - PJ119
1PJ201 - PJ206
3PJ207
1PJ208 - PJ219
2PJ301 - PJ302
2PJ551 - PJ561
2PJ601 - PJ615
2PJ811
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GroupVariable Number
2PJ816 - PJ817
1PK026 - PK029
1PK041 - PK053
10PK061 - PK067
39PK068 - PK069
10PK070
1PK081 - PK082
1PK091 - PK099
9PK101 - PK103
10PK111 - PK120
10PK141 - PK146
1PK201 - PK203
10PK204
1PK211 - PK215
9PK216 - PK220
10PK221 - PK223
3PK231 - PK240
1PK241
9PK251 - PK258
1PK271 - PK274
3PK281 - PK284
1PK285 - PK289
22PK291
3PK301 - PK304
1PK305 - PK306
3PK307 - PK310
21PK311 - PK318
21PK341
9PK351
1PK352 - PK354
9PK355
1PK356 - PK358
9PK359 - PK360
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GroupVariable Number
1PK361
22PK391
1PK431 - PK433
1PK451 - PK452
9PK461 - PK468
1PK469
9PK495
9PK501 - PK504
9PK511 - PK515
9PK519
9PK521
1PK522
9PK523 - PK524
1PK525
9PK526 - PK528
1PK541 - PK561
9PK562
1PK563 - PK564
14PK565
10PK581
1PK591 - PK599
40PK601 - PK610
1PK611 - PK617
1PK621
9PK622
1PK623
9PK624
1PK625 - PK627
31PK628 - PK630
9PK631
31PK632
9PK633 - PK634
33PK635 - PK637
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GroupVariable Number
3PK641 - PK642
21PK661
34PK662 - PK663
31PK664
34PK665 - PK666
1PK671 - PK680
3PK681
1PK691 - PK694
9PK695 - PK697
1PK711 - PK716
1PK731 - PK749
25PK750 - PK765
1PK771 - PK779
1PK801 - PK804
1PK819 - PK827
1PK830
3PK861 - PK863
9PK871
3PK872 - PK874
10PK881 - PK883
35PK884
25PK901 - PK938
25PK971 - PK974
1PL001 - PL028
1PL061
1PL081
15PL101 - PL113
34PL151
1PL171 - PL172
9PL201 - PL203
1PL221
1PL401 - PL414
10PL415
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GroupVariable Number
1PL416 - PL417
10PL421
9PL441
1PL451 - PL454
9PL455 - PL456
9PL471
31PL491
9PL501 - PL506
1PL551 - PL562
9PL581
33PL601 - PL603
37PL611
9PL621 - PL626
3PL631 - PL632
44PL711 - PL712
44PL716
10PL717
1PL718 - PL724
10PL725
21PL726 - PL735
3PL736 - PL738
1PL739
3PL740 - PL745
9PL746 - PL747
10PL756
10PL758
1PL761 - PL770
3PL781 - PL782
14PL783 - PL788
1PL793
44PL801 - PL803
3PM001 - PM006
3PM016 - PM017
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GroupVariable Number
3PM021 - PM023
1PM051 - PM060
9PM061
1PM062
9PM063 - PM066
1PM101 - PM119
1PM141 - PM142
38PM171
9PM181
33PM251 - PM255
1PM281 - PM283
2PM381 - PM399
2PM401 - PM417
2PM541 - PM564
9PN001 - PN002
3PN021 - PN043
3PN081 - PN086
3PN101 - PN117
3PN131
41PN132
3PN133 - PN149
41PN150 - PN152
3PN153 - PN163
3PN401 - PN420
3PN431 - PN433
3PN451 - PN452
41PN453
3PN454 - PN456
3PN471 - PN474
3PN481
3PN491 - PN493
3PN501 - PN502
33PN511 - PN512
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GroupVariable Number
3PN521
4PP001 - PP054
4PP101 - PP169
4PP181 - PP194
7PP195 - PP199
4PP201 - PP205
4PP221
8PP231 - PP243
8PP281 - PP286
4PP301 - PP305
4PP351 - PP353
4PP376 - PP384
7PP391 - PP393
4PP401 - PP440
4PP471 - PP475
4PP501 - PP502
7PP503 - PP507
12PP508 - PP520
4PP521 - PP522
4PP631 - PP634
4PP651 - PP652
8PP671 - PP699
8PP701 - PP733
4PP771 - PP779
20PP801 - PP804
2PP805 - PP808
4PP821 - PP827
6PP831 - PP844
2PP845
6PP846 - PP848
6PP851 - PP852
24PP861 - PP870
26PP871 - PP873
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GroupVariable Number
27PP874 - PP877
5PP891 - PP899
5PP901 - PP914
2PP915 - PP930
5PP931 - PP936
19PP946 - PP948
6PP951 - PP952
6PP961 - PP965
2PP966 - PP967
6PP981 - PP982
2PP983 - PP990
6PP991
2PP993
6PQ001 - PQ012
5PQ013 - PQ016
6PQ026 - PQ041
11PQ051 - PQ092
6PQ101 - PQ138
5PQ139 - PQ150
2PQ151 - PQ199
2PQ201 - PQ202
2PQ221 - PQ230
6PQ231 - PQ233
2PQ234 - PQ237
6PQ241 - PQ243
2PQ251 - PQ267
12PQ281 - PQ293
2PQ294 - PQ299
12PQ301 - PQ307
2PQ331 - PQ332
2PQ341 - PQ348
2PQ361 - PQ364
12PQ365 - PQ367
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GroupVariable Number
2PQ368 - PQ373
2PQ391 - PQ395
2PQ401 - PQ418
2PQ421
2PQ431
5PQ432 - PQ438
2PQ447 - PQ448
2PQ451
5PQ454
2PQ471 - PQ475
2PQ479 - PQ481
2PQ486 - PQ487
2PQ491 - PQ493
2PQ771 - PQ772
2PQ791 - PQ793
36PQ801 - PQ805
2PQ931 - PQ935
2PQ951
2PQ971 - PQ997
2PR001 - PR017
2PR021 - PR034
2PR041 - PR045
2PR061 - PR072
2PR077 - PR082
2PR091 - PR092
2PR096
2PR101
2PR121 - PR122
2PR131 - PR132
2PR141 - PR143
2PR161 - PR172
2PR181
2PS601 - PS631
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GroupVariable Number
2PS636 - PS638
2PS641 - PS644
2PS651 - PS657
7PS666 - PS668
17PS669
2PS691 - PS692
11PS701 - PS706
4PS751 - PS799
2PS811
2PS836 - PS837
2PS841 - PS846
2PS851 - PS852
2PS856
12PS861 - PS863
12PS866 - PS868
2PS871 - PS874
2PS896 - PS897
4PS901 - PS941
12PS956 - PS957
2PS961 - PS963
2PS971 - PS978
2PT001 - PT015
2PT021 - PT031
2PT041 - PT058
12PT059
2PT060 - PT064
2PT101 - PT105
2PT121 - PT138
2PT146 - PT148
2PT161 - PT170
2PT181 - PT188
2PT211 - PT220
2PT295
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GroupVariable Number
2PT301 - PT309
11PT331 - PT360
2PT381 - PT399
2PT401 - PT438
29PT501 - PT516
11PT517
2PT561 - PT565
2PT581 - PT586
2PT641 - PT644
2PT651 - PT656
2PT681 - PT685
2PT701 - PT703
2PT716 - PT717
2PT721 - PT725
2PT851 - PT854
2PT871 - PT886
2PT981 - PT985
2PT996
8PU001 - PU025
2PU301
2PU311 - PU313
4PV001 - PV008
13PV009 - PV010
20PV011
13PV012 - PV020
8PV021 - PV055
2PV201 - PV209
2PV226 - PV229
11PV231 - PV237
2PV271 - PV272
2PV281 - PV287
32PV296
2PV301 - PV302
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GroupVariable Number
2PV351
2PV356 - PV357
2PW001 - PW054
2PW061 - PW068
2PW072
2PW086 - PW088
2PW091 - PW094
2PW101 - PW102
2PW106
2PW111 - PW120
2PW156 - PW157
32PW161 - PW171
2PW201 - PW230
12PW231 - PW238
2PW239 - PW252
12PW261
2PW262 - PW264
12PW265
2PW266 - PW268
2PW271 - PW276
2PW278
12PW281
2PW282 - PW292
12PW293
12PW296
24PW301 - PW313
11PW314 - PW327
2PW401 - PW408
2PW411 - PW418
2PW421 - PW424
2PW431 - PW435
2PW441 - PW450
2PW461 - PW467
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GroupVariable Number
2PW501 - PW504
2PW511 - PW522
2PW524 - PW530
18PW531 - PW550
18PW556 - PW557
2PW561 - PW564
2PW571 - PW576
2PW591 - PW596
27PW611 - PW622
6PW631 - PW637
6PW661 - PW662
2PW701 - PW702
2PW711 - PW717
2PW771
2PW831
2PW851 - PW856
44PX071
44PX701
44PY001 - PY008
44PY021
3PY022
44PY031
21PY036 - PY037
10PY046 - PY048
1PY051 - PY053
33PY056 - PY057
1PY101
3PY102 - PY103
22PY111 - PY113
21PY131 - PY135
3PY141 - PY143
10PY151 - PY154
21PY156 - PY157
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GroupVariable Number
10PY161
21PY162
21PY166
10PY191
3PY201
1PY221 - PY222
9PY231
23PY241 - PY244
16PY270
1PY271 - PY275
43PY281
10PY286
44PY301 - PY304
44PY321 - PY323
44PY341 - PY346
44PY361 - PY362
44PY381
30PY401
34PY409 - PY410
10PY411
10PY421 - PY422
22PY441
21PY451
28PY461 - PY463
33PY591 - PY595
9PY611
21PY612
3PY621
3PY631
34PY651
42PY671 - PY672
14PY721
9PY741
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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
This service bulletin gives instructions to install two warning level indicator lights on the P2-2 center
instrument panel in the flight compartment. The installation of these lights will provide a visual indication
to the flight crew to be used in conjunction with the existing aural warning horn for cabin altitude and
takeoff configuration alerts. The visual warning lights are intended to provide additional notice to crews
to prepare a correct takeoff configuration, respond to excessive cabin altitude and avoid confusion
between the takeoff configuration and cabin altitude alerts. An unrecognized incorrect takeoff
configuration or excessive cabin altitude could prevent a continued safe flight and landing.
As a part of a service bulletin validation program, this change was completed on airplane PW234 by
Service Bulletin 737-31A1325 Validation Copy 1 and Installation Deviation Records 737-31A1325-001
through 737-31A1325-006 before the initial release of this service bulletin. The change completed on
airplane PW234 by Service Bulletin 737-31A1325 Validation Copy 1 and Installation Deviation Records
737-31A1325-001 through 737-31A1325-006 is equivalent to the initial release of this service bulletin.
Airplane PW234 has the configuration of a Group 13 airplane.
Boeing Service Related Problem (SRP) 737-SRP-31-0042 is related to this service bulletin.
Revision 1 is sent to add FAA Airworthiness Directive AD 2011-03-14 and correct typographical errors
identified by operators incorporating this change. Also, airplanes Line Numbers 1 thru 291 have been
moved to Group 44. The affected airplanes were in Groups 4, 14, 16-17, 24, 33, 36-37, 43 and 47 in
the original issue of this service bulletin.
D. Description
Get access to the flight compartment. Remove the P2-2 center instrument panel to install two warning
level indicator lights on the panel and change three wire bundles. Reinstall the modified P2-2 center
instrument panel. Do a test of the warning level indicator lights.
On Group 44 airplanes, contact Boeing to get instructions for the change for this service bulletin,
737-31A1325 Revision 1, and do the work instructed by Boeing.
Revision 1 - No more work is necessary on airplanes changed in accordance with the original issue of
this service bulletin.
The work in this service bulletin is done in the maintenance zone(s) given below.
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Group 1, 3, 9-10, 14, 21-22, 33-34:
Affected Maintenance Zones
ZoneModel
1-1, 1-2, 2-2737-200, 737-200C
Group 2, 8, 11-12:
Affected Maintenance Zones
ZoneModel
101, 102, 202737-300, 737-400, 737-500
Group 4, 6, 20, 24, 27:
Affected Maintenance Zones
ZoneModel
101, 102, 202737-300, 737-400
Group 5, 7, 17, 19, 26, 36:
Affected Maintenance Zones
ZoneModel
101, 102, 202737-300
Group 13, 18, 32:
Affected Maintenance Zones
ZoneModel
101, 102, 202737-400
Group 15, 25, 31, 35, 37-41:
Affected Maintenance Zones
ZoneModel
1-1, 1-2, 2-2737-200
Group 16, 23, 28, 30, 42-43:
Affected Maintenance Zones
ZoneModel
1-1, 1-2, 2-2737-200C
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Group 29:
Affected Maintenance Zones
ZoneModel
101, 102, 202737-500
Group 44:
Affected Maintenance Zones
ZoneModel
1-1, 1-2, 2-2737-100, 737-200, 737-200C
E. Compliance
Federal Aviation Administration (FAA) Airworthiness Directive AD 2011-03-14 is related to this service
bulletin.
On Group 44 airplanes, contact Boeing to get instructions for the change for this service bulletin,
737-31A1325 Revision 1, and do the work instructed by Boeing.
F. Approval
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified
in this service bulletin comply with the applicable regulations and are FAA approved, as well as European
Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved
airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on
the airplane in its original Boeing delivery configuration or as modified by other approved Boeing
changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
In addition, the Manager of the FAA Seattle Aircraft Certification Office approves the action (i.e. inspection
or modification) defined in this service bulletin as an alternative method of compliance to the requirements
of paragraph (g) of AD 2011-03-14. All provisions of AD 2011-03-14 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 examine the work
— Time to cure the materials
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— Time to make the parts
— Time to find the tools.
Elapsed HoursTask-HoursNumber of Per-
sons
Task
2.252.251Open Access
4.504.501Remove
5.0015.003Change
4.504.501Replace
2.252.251Close Access
2.004.002Test
20.5032.50TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)
Airplane
+ 175+ 0.8737-100
+ 145+ 0.8737-200/200C
+ 110+ 0.8737-300
+ 55+ 0.8737-400
+ 155+ 0.8737-500
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Engineering Change Memo PRR 35005-277RS
b. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2011-03-14
c. Overhaul Manual (OHM) 31-10-01
d. Standard Overhaul Practices Manual (SOPM) 20-50-10
e. Standard Wiring Practices Manual (SWPM) 20-00-13, 20-10-11, 20-10-12, 20-10-18, 20-10-19,
20-30-11, 20-30-12, 20-60-09, 20-61-11, 20-61-19
f. 737-100/200 Aircraft Maintenance Manual (AMM) 21-33-01, 24-22-00, 27-88-11, 32-42-00,
32-43-00, 71-09-100, 78-32-01
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g. 737-100/200 Wiring Diagram Manual (WDM) 21-33-01, 27-43-01, 33-18-03, 33-18-12, 80-11-01
h. 737-300/400/500 Aircraft Maintenance Manual (AMM) 24-22-00, 27-88-00, 32-42-00, 32-43-01,
53-14-01, 71-00-00, 78-31-00
i. 737-300/400/500 Wiring Diagram Manual (WDM) 21-33-01, 27-43-01, 33-18-03, 33-18-18
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
None
K. Publications Affected
1. Publications
Chapter-SectionPublication
Section 2737 FAA Approved Airplane Flight Manual
1.10, 1.20, 15.10, 15.20737 Flight Crew Operations Manual
31-26-00 (737-100/200/200C), 31-26-00 (737-300/400/500)737 Maintenance Manual
21-33-01, 27-43-01, 33-18-03, 33-18-12, 33-18-18, 80-11-11737 Wiring Diagram
31-10 (737-100/200/200C), 31-11 (737-300/400/500)737 Illustrated Parts Catalog
21-30-05, 27-09-00, 31-26-00737 System Schematic Manual
31-36Component Maintenance Manual
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary.
L. Interchangeability and Intermixability of Parts
Refer to Paragraph 2.C., Parts Necessary For Each Airplane, for interchangeability and intermixability
information.
M. Software Accomplishment Summary
Not affected.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators
are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin.
The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.
Prices are in United States Dollars. Terms: Net 30 days.
Reference this service bulletin and submit your purchase order by one of these methods:
1. Order on-line via ATA Spec 2000 or The Boeing PART Page
2. Fax to (206) 662-7145
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the Revision 01
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
Revision 01 date
of this Service
Bulletin (Calendar
Days)
QTYDateNameKit Number
2,902.00150258/31/07Top Kit - Cabin Altitude
Warning Indication
65C38791-1 (a)
(a) 25 top kits are available every 14 days from 8/31/07 to 2/29/08. 10 top kits are available on 3/14/08. 25
top kits are available every 14 days from 5/09/08 to 4/14/09.
B. Industry Support Information
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts:
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.
Kit 65C38791
NotesNameQTYNew Part Number
-1
Top Kit - Cabin Altitude Warning Indication-65C38791-1
Wire Kit - Cabin Altitude Warning Indication161-74487-1
Wire Kit - Cabin Altitude Warning Indication161-74488-1
Kit - Cabin Altitude Warning Indication, P2-2
Modification
165C38242-1
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Kit 61-74487
NotesNameQTYNew Part Number
-1-101
Wire Kit - Cabin Altitude Warning Indication-.61-74487-1
Wire Bundle W066 Assembly.-61-74487-101
Wire Bundle W066 Assembly1.61-74487-101
(a) (d)Wire, Identified as W066-8032-20, Length 6 Feet.1-
(a) (d)Wire, Identified as W066-8033-20, Length 6 Feet.1-
(b) (d)Wire, Identified as W066-8034-22, Length 2 Feet.1-
(b) (d)Wire, Identified as W066-8035-22, Length 2 Feet.1-
(b) (d)Wire, Identified as W066-8036-22, Length 2 Feet.1-
(b) (d)Wire, Identified as W066-8037-22, Length 2 Feet.1-
(c) (d)Wire, Identified as W066-8038-24, Length 2 Feet.1-
(c) (d)Wire, Identified as W066-8039-24, Length 2 Feet.1-
Lacing Tape, White, Length 27 Feet1.61-74487-2001
Lacing Tape, Red, Length 9 Feet1.61-74487-2002
Lacing Tape, Yellow, Length 9 Feet1.61-74487-2003
Connector Identification Tape, Imprinted "D04258J".161-74487-10101
Connector Identification Tape, Imprinted "D04260J".161-74487-10102
Splice Identification Sleeve, Imprinted "SP4016".161-74487-10103
Splice Identification Sleeve, Imprinted "SP4018".161-74487-10104
(e)Pin Contact.3BACC47CN1S
Terminal Lug.2BACT12AC44
Terminal Lug.14BACT12AC48
Terminal Lug.14BACT12AC52
Splice Sleeve.3D-436-58
(a) Make from BMS 13-48, Type 10, Class 1, AWG 20.
(b) Make from BMS 13-48, Type 10, Class 1, AWG 22.
(c) Make from BMS 13-48, Type 11, Class 1, AWG 24.
(d) Refer to SWPM 20-00-13 for alternative wire types.
(e) There are more parts than are necessary.
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Kit 61-74488
NotesNameQTYNew Part Number
-1-111-112
Wire Kit - Cabin Altitude Warning Indication-..61-74488-1
Wire Bundle W002 Assembly1-.61-74488-111
Wire Bundle W246 Assembly1.-61-74488-112
(a) (b)Wire, Identified as W002-8051-20, Length 10 Feet.1.-
(a) (c)Wire, Identified as W002-8052-22, Length 10 Feet.1.-
(a) (b)Wire, Identified as W246-170-20, Length 5 Feet..1-
(a) (b)Wire, Identified as W246-171-20, Length 40 Feet..1-
(a) (c)Wire, Identified as W246-172-22, Length 10 Feet..1-
Lacing Tape, White, Length 100 Feet1..61-74488-2001
Expandable Sleeve - White, 0.250 Inch Inner Diameter,
Length 10 Feet
1..61-74488-2003
Lacing Tape, Red, Length 15 Feet1..61-74488-2007
Lacing Tape, Yellow, Length 30 Feet1..61-74488-2008
Connector Identification (I.D.) Tape - D04258P.1.61-74488-10101
Connector I.D. Tape - D04260P.1.61-74488-10102
Connector I.D. Tape - D04006P.1.61-74488-10103
Connector I.D. Tape - D04006J..161-74488-10201
Connector I.D. Tape - D00776..161-74488-10202
Splice I.D. Sleeve - SM3..161-74488-10203
Splice I.D. Sleeve - SP2218..161-74488-10204
Splice I.D. Sleeve - SM21..161-74488-10205
Splice I.D. Sleeve - SM23..161-74488-10207
Diode I.D. Sleeve - M2592..161-74488-10212
Thermofit Sleeve - 0.093 Inch Inner Diameter, Length 2
Inches
..161-74488-10213
Diode Assembly..169-58806-4
(d)Pin Contact.3.BACC47CN1S
(d)Socket Contact.33BACC47CP1S
(d)Socket Contact..2BACC47DR1
(d)Splice..4D-436-37
(d)Splice..2D-436-38
(a) Make from BMS 13-48, Type 10, Class 1, AWG 20.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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ALERTALERT

### Page 36

Kit 61-74488
NotesNameQTYNew Part Number
-1-111-112
(b) Make from BMS 13-48, Type 10, Class 1, AWG 22.
(c) Refer to SWPM 20-00-13 for alternative wire types.
(d) There are more parts than are necessary.
Kit 65C38242
NotesNameQTYNew Part Number
-1
Kit - Cabin Altitude Warning Indication, P2-2 Modification-65C38242-1
Light Assembly, PRESS-TO-TEST Indicator1318-630-1001-452
Light Assembly, PRESS-TO-TEST Indicator1318-630-1001-460
2. Parts and Materials Supplied by the Operator:
NotesNameQTYPart Number /
Specification
Loctite 222, Thread Lock Compound1222
Adhesive Tape, Permacel P-421 or
equivalent, 0.5 Inch Width
1P-421
Adhesive Tape, Permacel P-440 or
equivalent, 1.0 Inch Width
1P-440
3. Parts Modified and Reidentified:
The parts shown below are changed as shown in this service bulletin. The quantity (QTY) is the
number of parts changed on each airplane.
NotesNew Part NumberNameQTYExisting Part
Number
(a)69-37305-2001P2-2 Center Instrument Module Assembly169-37305-1
(a)69-37305-2101P2-2 Center Instrument Module Assembly169-37305-101
(a)69-37305-2104P2-2 Center Instrument Module Assembly169-37305-104
(a)69-37305-2107P2-2 Center Instrument Module Assembly169-37305-107
(a)69-37305-2011P2-2 Center Instrument Module Assembly169-37305-11
(a)69-37305-2110P2-2 Center Instrument Module Assembly169-37305-110
(a)69-37305-2111P2-2 Center Instrument Module Assembly169-37305-111
(a)69-37305-2114P2-2 Center Instrument Module Assembly169-37305-114
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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ALERTALERT

### Page 37

NotesNew Part NumberNameQTYExisting Part
Number
(a)69-37305-2120P2-2 Center Instrument Module Assembly169-37305-120
(a)69-37305-2123P2-2 Center Instrument Module Assembly169-37305-123
(a)69-37305-2126P2-2 Center Instrument Module Assembly169-37305-126
(a)69-37305-2129P2-2 Center Instrument Module Assembly169-37305-129
(a)69-37305-2135P2-2 Center Instrument Module Assembly169-37305-135
(a)69-37305-2138P2-2 Center Instrument Module Assembly169-37305-138
(a)69-37305-2014P2-2 Center Instrument Module Assembly169-37305-14
(a)69-37305-2141P2-2 Center Instrument Module Assembly169-37305-141
(a)69-37305-2144P2-2 Center Instrument Module Assembly169-37305-144
(a)69-37305-3452P2-2 Center Instrument Module Assembly169-37305-1452
(a)69-37305-2147P2-2 Center Instrument Module Assembly169-37305-147
(a)69-37305-2148P2-2 Center Instrument Module Assembly169-37305-148
(a)69-37305-2151P2-2 Center Instrument Module Assembly169-37305-151
(a)69-37305-2155P2-2 Center Instrument Module Assembly169-37305-155
(a)69-37305-2158P2-2 Center Instrument Module Assembly169-37305-158
(a)69-37305-2163P2-2 Center Instrument Module Assembly169-37305-163
(a)69-37305-2167P2-2 Center Instrument Module Assembly169-37305-167
(a)69-37305-3684P2-2 Center Instrument Module Assembly169-37305-1684
(a)69-37305-3688P2-2 Center Instrument Module Assembly169-37305-1688
(a)69-37305-2170P2-2 Center Instrument Module Assembly169-37305-170
(a)69-37305-2173P2-2 Center Instrument Module Assembly169-37305-173
(a)69-37305-2180P2-2 Center Instrument Module Assembly169-37305-180
(a)69-37305-2184P2-2 Center Instrument Module Assembly169-37305-184
(a)69-37305-2188P2-2 Center Instrument Module Assembly169-37305-188
(a)69-37305-2201P2-2 Center Instrument Module Assembly169-37305-201
(a)69-37305-2205P2-2 Center Instrument Module Assembly169-37305-205
(a)69-37305-2217P2-2 Center Instrument Module Assembly169-37305-217
(a)69-37305-2022P2-2 Center Instrument Module Assembly169-37305-22
(a)69-37305-2233P2-2 Center Instrument Module Assembly169-37305-233
(a)69-37305-2240P2-2 Center Instrument Module Assembly169-37305-240
(a)69-37305-2241P2-2 Center Instrument Module Assembly169-37305-241
(a)69-37305-2245P2-2 Center Instrument Module Assembly169-37305-245
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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ALERTALERT

### Page 38

NotesNew Part NumberNameQTYExisting Part
Number
(a)69-37305-2246P2-2 Center Instrument Module Assembly169-37305-246
(a)69-37305-2247P2-2 Center Instrument Module Assembly169-37305-247
(a)69-37305-2025P2-2 Center Instrument Module Assembly169-37305-25
(a)69-37305-2266P2-2 Center Instrument Module Assembly169-37305-266
(a)69-37305-2270P2-2 Center Instrument Module Assembly169-37305-270
(a)69-37305-2271P2-2 Center Instrument Module Assembly169-37305-271
(a)69-37305-2275P2-2 Center Instrument Module Assembly169-37305-275
(a)69-37305-2279P2-2 Center Instrument Module Assembly169-37305-279
(a)69-37305-2028P2-2 Center Instrument Module Assembly169-37305-28
(a)69-37305-2283P2-2 Center Instrument Module Assembly169-37305-283
(a)69-37305-2290P2-2 Center Instrument Module Assembly169-37305-290
(a)69-37305-2293P2-2 Center Instrument Module Assembly169-37305-293
(a)69-37305-2297P2-2 Center Instrument Module Assembly169-37305-297
(a)69-37305-2301P2-2 Center Instrument Module Assembly169-37305-301
(a)69-37305-2305P2-2 Center Instrument Module Assembly169-37305-305
(a)69-37305-2309P2-2 Center Instrument Module Assembly169-37305-309
(a)69-37305-2031P2-2 Center Instrument Module Assembly169-37305-31
(a)69-37305-2310P2-2 Center Instrument Module Assembly169-37305-310
(a)69-37305-2318P2-2 Center Instrument Module Assembly169-37305-318
(a)69-37305-2323P2-2 Center Instrument Module Assembly169-37305-323
(a)69-37305-2327P2-2 Center Instrument Module Assembly169-37305-327
(a)69-37305-2331P2-2 Center Instrument Module Assembly169-37305-331
(a)69-37305-2335P2-2 Center Instrument Module Assembly169-37305-335
(a)69-37305-2339P2-2 Center Instrument Module Assembly169-37305-339
(a)69-37305-2034P2-2 Center Instrument Module Assembly169-37305-34
(a)69-37305-2343P2-2 Center Instrument Module Assembly169-37305-343
(a)69-37305-2347P2-2 Center Instrument Module Assembly169-37305-347
(a)69-37305-2035P2-2 Center Instrument Module Assembly169-37305-35
(a)69-37305-2351P2-2 Center Instrument Module Assembly169-37305-351
(a)69-37305-2355P2-2 Center Instrument Module Assembly169-37305-355
(a)69-37305-2359P2-2 Center Instrument Module Assembly169-37305-359
(a)69-37305-2036P2-2 Center Instrument Module Assembly169-37305-36
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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ALERTALERT

### Page 39

NotesNew Part NumberNameQTYExisting Part
Number
(a)69-37305-2362P2-2 Center Instrument Module Assembly169-37305-362
(a)69-37305-2363P2-2 Center Instrument Module Assembly169-37305-363
(a)69-37305-2367P2-2 Center Instrument Module Assembly169-37305-367
(a)69-37305-2037P2-2 Center Instrument Module Assembly169-37305-37
(a)69-37305-2371P2-2 Center Instrument Module Assembly169-37305-371
(a)69-37305-2375P2-2 Center Instrument Module Assembly169-37305-375
(a)69-37305-2379P2-2 Center Instrument Module Assembly169-37305-379
(a)69-37305-2038P2-2 Center Instrument Module Assembly169-37305-38
(a)69-37305-2383P2-2 Center Instrument Module Assembly169-37305-383
(a)69-37305-2387P2-2 Center Instrument Module Assembly169-37305-387
(a)69-37305-2039P2-2 Center Instrument Module Assembly169-37305-39
(a)69-37305-2390P2-2 Center Instrument Module Assembly169-37305-390
(a)69-37305-2394P2-2 Center Instrument Module Assembly169-37305-394
(a)69-37305-2398P2-2 Center Instrument Module Assembly169-37305-398
(a)69-37305-2402P2-2 Center Instrument Module Assembly169-37305-402
(a)69-37305-2406P2-2 Center Instrument Module Assembly169-37305-406
(a)69-37305-2410P2-2 Center Instrument Module Assembly169-37305-410
(a)69-37305-2414P2-2 Center Instrument Module Assembly169-37305-414
(a)69-37305-2418P2-2 Center Instrument Module Assembly169-37305-418
(a)69-37305-2422P2-2 Center Instrument Module Assembly169-37305-422
(a)69-37305-2425P2-2 Center Instrument Module Assembly169-37305-425
(a)69-37305-2433P2-2 Center Instrument Module Assembly169-37305-433
(a)69-37305-2437P2-2 Center Instrument Module Assembly169-37305-437
(a)69-37305-2448P2-2 Center Instrument Module Assembly169-37305-448
(a)69-37305-2452P2-2 Center Instrument Module Assembly169-37305-452
(a)69-37305-2456P2-2 Center Instrument Module Assembly169-37305-456
(a)69-37305-2457P2-2 Center Instrument Module Assembly169-37305-457
(a)69-37305-2461P2-2 Center Instrument Module Assembly169-37305-461
(a)69-37305-2463P2-2 Center Instrument Module Assembly169-37305-463
(a)69-37305-2467P2-2 Center Instrument Module Assembly169-37305-467
(a)69-37305-2471P2-2 Center Instrument Module Assembly169-37305-471
(a)69-37305-2475P2-2 Center Instrument Module Assembly169-37305-475
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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ALERTALERT

### Page 40

NotesNew Part NumberNameQTYExisting Part
Number
(a)69-37305-2479P2-2 Center Instrument Module Assembly169-37305-479
(a)69-37305-2483P2-2 Center Instrument Module Assembly169-37305-483
(a)69-37305-2487P2-2 Center Instrument Module Assembly169-37305-487
(a)69-37305-2491P2-2 Center Instrument Module Assembly169-37305-491
(a)69-37305-2495P2-2 Center Instrument Module Assembly169-37305-495
(a)69-37305-2005P2-2 Center Instrument Module Assembly169-37305-5
(a)69-37305-2051P2-2 Center Instrument Module Assembly169-37305-51
(a)69-37305-2055P2-2 Center Instrument Module Assembly169-37305-55
(a)69-37305-2059P2-2 Center Instrument Module Assembly169-37305-59
(a)69-37305-2060P2-2 Center Instrument Module Assembly169-37305-60
(a)69-37305-2600P2-2 Center Instrument Module Assembly169-37305-600
(a)69-37305-2603P2-2 Center Instrument Module Assembly169-37305-603
(a)69-37305-2609P2-2 Center Instrument Module Assembly169-37305-609
(a)69-37305-2061P2-2 Center Instrument Module Assembly169-37305-61
(a)69-37305-2612P2-2 Center Instrument Module Assembly169-37305-612
(a)69-37305-2615P2-2 Center Instrument Module Assembly169-37305-615
(a)69-37305-2062P2-2 Center Instrument Module Assembly169-37305-62
(a)69-37305-2623P2-2 Center Instrument Module Assembly169-37305-623
(a)69-37305-2627P2-2 Center Instrument Module Assembly169-37305-627
(a)69-37305-2063P2-2 Center Instrument Module Assembly169-37305-63
(a)69-37305-2631P2-2 Center Instrument Module Assembly169-37305-631
(a)69-37305-2634P2-2 Center Instrument Module Assembly169-37305-634
(a)69-37305-2064P2-2 Center Instrument Module Assembly169-37305-64
(a)69-37305-2642P2-2 Center Instrument Module Assembly169-37305-642
(a)69-37305-2644P2-2 Center Instrument Module Assembly169-37305-644
(a)69-37305-2648P2-2 Center Instrument Module Assembly169-37305-648
(a)69-37305-2065P2-2 Center Instrument Module Assembly169-37305-65
(a)69-37305-2659P2-2 Center Instrument Module Assembly169-37305-659
(a)69-37305-2663P2-2 Center Instrument Module Assembly169-37305-663
(a)69-37305-2667P2-2 Center Instrument Module Assembly169-37305-667
(a)69-37305-2671P2-2 Center Instrument Module Assembly169-37305-671
(a)69-37305-2675P2-2 Center Instrument Module Assembly169-37305-675
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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ALERTALERT

### Page 41

NotesNew Part NumberNameQTYExisting Part
Number
(a)69-37305-2679P2-2 Center Instrument Module Assembly169-37305-679
(a)69-37305-2068P2-2 Center Instrument Module Assembly169-37305-68
(a)69-37305-2683P2-2 Center Instrument Module Assembly169-37305-683
(a)69-37305-2684P2-2 Center Instrument Module Assembly169-37305-684
(a)69-37305-2685P2-2 Center Instrument Module Assembly169-37305-685
(a)69-37305-2686P2-2 Center Instrument Module Assembly169-37305-686
(a)69-37305-2687P2-2 Center Instrument Module Assembly169-37305-687
(a)69-37305-2688P2-2 Center Instrument Module Assembly169-37305-688
(a)69-37305-2069P2-2 Center Instrument Module Assembly169-37305-69
(a)69-37305-2694P2-2 Center Instrument Module Assembly169-37305-694
(a)69-37305-2698P2-2 Center Instrument Module Assembly169-37305-698
(a)69-37305-2699P2-2 Center Instrument Module Assembly169-37305-699
(a)69-37305-2700P2-2 Center Instrument Module Assembly169-37305-700
(a)69-37305-2701P2-2 Center Instrument Module Assembly169-37305-701
(a)69-37305-2703P2-2 Center Instrument Module Assembly169-37305-703
(a)69-37305-2707P2-2 Center Instrument Module Assembly169-37305-707
(a)69-37305-2709P2-2 Center Instrument Module Assembly169-37305-709
(a)69-37305-2072P2-2 Center Instrument Module Assembly169-37305-72
(a)69-37305-2075P2-2 Center Instrument Module Assembly169-37305-75
(a)69-37305-2078P2-2 Center Instrument Module Assembly169-37305-78
(a)69-37305-2008P2-2 Center Instrument Module Assembly169-37305-8
(a)69-37305-2081P2-2 Center Instrument Module Assembly169-37305-81
(a)69-37305-2082P2-2 Center Instrument Module Assembly169-37305-82
(a)69-37305-2087P2-2 Center Instrument Module Assembly169-37305-87
(a)69-37305-2088P2-2 Center Instrument Module Assembly169-37305-88
(a)69-37305-2091P2-2 Center Instrument Module Assembly169-37305-91
(a)69-37305-2092P2-2 Center Instrument Module Assembly169-37305-92
(a)69-37305-2095P2-2 Center Instrument Module Assembly169-37305-95
(a)69-37305-2098P2-2 Center Instrument Module Assembly169-37305-98
(a) Make the change given in this service bulletin.
4. Parts Removed and Not Replaced:
None.
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### Page 42

D. Parts Necessary to Change Spares
None
E. Special Tooling - Price and Availability
None
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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### Page 43

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. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures,
and SWPM 20-10-19 for the wire separation requirements, as accepted procedures.
4. The necessary conditions for selection of clamp type and size are included in SWPM
20-10-12. If any wire bundle support clamp specified in this service bulletin does not
make a correct fit on the wire bundle, refer to SWPM 20-10-12 as an accepted
procedure to select a clamp that fits correctly.
5. These work instructions refer to procedures included in other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "in
accordance with" are included in the instruction, the procedure in the Boeing document
must be used.
6. 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.
7. 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.
8. This service bulletin includes functional test procedures for the systems changed by
this service bulletin. More functional tests can possibly be necessary in accordance
with standard maintenance practices because of interruption to other airplane systems.
B. WORK INSTRUCTIONS
1. Remove electrical power from the airplane. Refer to 737-100/200 AMM 24-22-00  or
737-300/400/500 AMM 24-22-00 as an accepted procedure.
2. Get access to the flight compartment.
3. Remove the P2-2 center instrument panel in accordance with FIGURE 1.
4. Modify the P2-2 center instrument panel in accordance with FIGURE 2.
5. Install the light assembly in accordance with FIGURE 3.
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### Page 44

6. Change wire bundle W066:
a. Group 1:
In accordance with FIGURE 4 and FIGURE 9.
b. Group 13, 20:
In accordance with FIGURE 4 and FIGURE 10.
c. Group 5, 19:
In accordance with FIGURE 4 and FIGURE 11.
d. Group 6-7:
In accordance with FIGURE 4 and FIGURE 12.
e. Group 4, 8:
In accordance with FIGURE 4 and FIGURE 13.
f. Group 9:
In accordance with FIGURE 4 and FIGURE 14.
g. Group 3:
In accordance with FIGURE 4 and FIGURE 16.
h. Group 14:
In accordance with FIGURE 4 and FIGURE 17.
i. Group 15:
In accordance with FIGURE 4 and FIGURE 18.
j. Group 16:
In accordance with FIGURE 4 and FIGURE 19.
k. Group 17-18:
In accordance with FIGURE 4 and FIGURE 20.
l. Group 2, 12:
In accordance with FIGURE 4 and FIGURE 21.
m. Group 10:
In accordance with FIGURE 4 and FIGURE 22.
n. Group 21, 42:
In accordance with FIGURE 4 and FIGURE 23.
o. Group 22:
In accordance with FIGURE 4 and FIGURE 24.
p. Group 23:
In accordance with FIGURE 4 and FIGURE 25.
q. Group 11, 24:
In accordance with FIGURE 4 and FIGURE 26.
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### Page 45

r. Group 26-27:
In accordance with FIGURE 4 and FIGURE 27.
s. Group 28:
In accordance with FIGURE 4 and FIGURE 29.
t. Group 29:
In accordance with FIGURE 4 and FIGURE 30.
u. Group 30:
In accordance with FIGURE 4 and FIGURE 33.
v. Group 31:
In accordance with FIGURE 6 and FIGURE 34.
w. Group 32:
In accordance with FIGURE 6 and FIGURE 35.
x. Group 33:
In accordance with FIGURE 6 and FIGURE 36.
y. Group 34:
In accordance with FIGURE 6 and FIGURE 37.
z. Group 25:
In accordance with FIGURE 6 and FIGURE 38.
aa. Group 35:
In accordance with FIGURE 6 and FIGURE 39.
ab. Group 36:
In accordance with FIGURE 6 and FIGURE 40.
ac. Group 37:
In accordance with FIGURE 6 and FIGURE 41.
ad. Group 38:
In accordance with FIGURE 6 and FIGURE 43.
ae. Group 39:
In accordance with FIGURE 7 and FIGURE 44.
af. Group 40:
In accordance with FIGURE 4 and FIGURE 68.
ag. Group 41, 43:
In accordance with FIGURE 6 and FIGURE 69.
ah. Group 44:
Contact Boeing to get instructions for the change for this service bulletin, 737-31A1325 R01,
and do the work instructed by Boeing.
7. Change wire bundle W002:
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### Page 46

a. Group 1, 3-9, 13-16, 19-20:
In accordance with FIGURE 45 and FIGURE 47.
b. Group 2, 12, 17-18:
In accordance with FIGURE 45 and FIGURE 48.
c. Group 10, 21-23, 40, 42-43:
In accordance with FIGURE 45 and FIGURE 49.
d. Group 11, 24, 26-27:
In accordance with FIGURE 45 and FIGURE 50.
e. Group 28:
In accordance with FIGURE 45 and FIGURE 52.
f. Group 29:
In accordance with FIGURE 45 and FIGURE 53.
g. Group 30:
In accordance with FIGURE 45 and FIGURE 55.
h. Group 25, 31-34:
In accordance with FIGURE 46 and FIGURE 58.
i. Group 35-38:
In accordance with FIGURE 46 and FIGURE 59.
j. Group 39:
In accordance with FIGURE 7 and FIGURE 60.
k. Group 41:
In accordance with FIGURE 46 and FIGURE 70.
l. Group 44:
Contact Boeing to get instructions for the change for this service bulletin, 737-31A1325 R01,
and do the work instructed by Boeing.
8. Change wire bundle W246:
a. Remove access panels 3103 and 3105 to access to wire bundle W246. Refer to
737-300/400/500 AMM 53-14-01 as an accepted procedure.
a. Group 1, 3-4, 7, 9-10, 12-17, 19, 21-26, 28, 30-31, 33-35, 37-43:
In accordance with FIGURE 61 and FIGURE 62.
b. Group 2, 5-6, 8, 11, 18, 20, 27, 29, 32, 36:
In accordance with FIGURE 61 and FIGURE 63.
c. Group 44:
Contact Boeing to get instructions for the change for this service bulletin, 737-31A1325 R01,
and do the work instructed by Boeing.
9. Install the P2-2 center instrument panel in accordance with FIGURE 67.
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ALERTALERT

### Page 47

10. Restore electrical power removed in Step 1. Refer to 737-100/200 AMM 24-22-00  or
737-300/400/500 AMM 24-22-00 as an accepted procedure.
11. Do the "Antiskid Indication Monitor Function Test". Refer to 737-100/200 AMM 32-42-00  or
737-300/400/500 AMM 32-42-00 as an accepted procedure.
12. Do the "Automatic Braking System Test". Refer to 737-100/200 AMM 32-43-00  or 737-300/400/500
AMM 32-43-01 as an accepted procedure.
13. Do the test of the leading edge flap and slat indicators. Refer to 737-100/200 AMM 27-88-11 or
737-300/400/500 AMM 27-88-00 as an accepted procedure.
14. Do a test of the reverser indicator lights. Refer to 737-100/200 AMM 78-32-01 or 737-300/400/500
AMM 78-31-00 as an accepted procedure.
15. Do a test of the takeoff warning system as follows:
Group 1, 3, 9-10, 14-16, 21-23, 25, 28, 30-31, 33-35, 37-43:
a. Make sure these circuit breakers are closed:
NameCircuit BreakerPanel/Location
LANDING GEAR AIR/GND RELAY LIGHTSC404P6-2 or P6-3
AURAL WARNC451P6-2 or P6-3
ENGINE PRESSURE RATIO WARNINGC552P6-2
b. Do one of these steps:
(1) Make sure the flap control lever is outside of the takeoff range.
(2) Make sure the speedbrake handle is not in the down detent position
(3) Make sure the stabilizer is out of the green band range.
(4) Make sure the leading edge flaps are not extended.
(5) Make sure the parking brake is set.
c. For airplanes that have a engine pressure ratio (EPR) activated takeoff warning, do the
following test.
In the electrical/electronics compartment, at the M528 engine accessory unit (EAU) on the
E3-2 electronics shelf, press and hold the S1 Engine 1 or S2 Engine 2 engine pressure ratio
(EPR) test switch on the front of the M528 EAU.
NOTE: Airplanes that do not have the EPR activated takeoff warning, do not need this step
completed.
d. Move the thrust levers to the takeoff position.
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ALERTALERT

### Page 48

(1) Make sure you hear the warning horn.
(2) Make sure the "Red" TAKE OFF WARNING light on the P2-2 panel is on.
e. Move the thrust levers to the idle position.
(1) Make sure the warning horn stops.
(2) Make sure the "Red" TAKE OFF WARNING light on the P2-2 panel is off.
f. In the electrical/electronics compartment, at the M528 EAU on the E3-2 electronics shelf,
release the S1 Engine 1 or S2 Engine 2 EPR test switch on the front of the M528 EAU.
NOTE: Airplanes that do not have the EPR activated takeoff warning, do not need this step
completed.
(1) Make sure the warning horn stays off.
(2) Make sure the "Red" TAKE OFF WARNING light on the P2-2 panel stays off.
Group 2, 4-8, 11-13, 17-20, 24, 26-27, 29, 32, 36:
a. Make sure these circuit breakers are closed:
NameCircuit BreakerPanel/Location
LANDING GEAR AIR/GND RELAY LIGHTSC404P6-2 or P6-3
AURAL WARNC451P6-2
b. Do one of these steps:
(1) Make sure the flap control lever is outside of the takeoff range.
(2) Make sure the speedbrake handle is not in the down detent position
(3) Make sure the stabilizer is out of the green band range.
(4) Make sure the leading edge flaps are not extended.
(5) Make sure the parking brake is set.
c. Move the thrust levers to the takeoff position.
(1) Make sure you hear the warning horn.
(2) Make sure the "Red" TAKE OFF WARNING light on the P2-2 panel is on.
d. Move the thrust levers to the idle position.
(1) Make sure the warning horn stops.
(2) Make sure the "Red" TAKE OFF WARNING light on the P2-2 panel is off.
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ALERTALERT

### Page 49

16. Do a test of the Cabin Altitude Warning System as follows:
a. Open the forward access door.
b. Make sure these circuit breakers are closed:
NameCircuit BreakerPanel/Location
AURAL WARNC451P6-2 or P6-3
LAND LATCH & PRESS WARNC129P6-2 or P6-3
c. Do a test of the altitude warning horn.
(1) Remove the vent port screen.
(2) Connect the pitot static system tester (No. 4 Union and O-ring) to the vent port of the
warning switch for the cabin altitude.
(3) Operate the system by slowly increasing the vacuum and monitor the altimeter.
(4) Make a record of the altitude at which you hear the warning horn.
(a) Make sure you hear the intermittent warning horn at an altitude between 9,000 and
11,000 feet.
(b) Make sure the "Red" CABIN ALTITUDE light on the P2-2 panel is on.
(5) Push the switch for the ALTITUDE HORN CUTOUT.
(a) Make sure the warning horn stops.
(b) Make sure the "Red" CABIN ALTITUDE light on the P2-2 panel remains on.
(6) Slowly lower the altitude shown to approximately 1,700 feet below the altitude at which
you hear the horn.
(a) Make sure the "Red" CABIN ALTITUDE light on the P2-2 panel goes off.
(7) Increase the altitude.
(a) Make sure the horn is again heard between 9,000 and 11,000 feet.
(b) Make sure the "Red" CABIN ALTITUDE light on the P2-2 panel comes on.
(8) Decrease the altitude to the ground level.
d. Disconnect the pitot static system equipment.
e. Install the vent port screen.
f. Close the forward access panel.
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ALERTALERT

### Page 50

17. Do the Power Plant Operational Test as follows:
a. With the engine stopped:
(1) Make sure the amber LOW OIL PRESSURE light on the pilots center instrument panel,
P2, is on.
(2) Make sure the amber OIL FILTER BYPASS light on the pilots center instrument panel,
P2, is off.
b. Do the Power Plant Operation (Normal) procedure. Refer to 737-100/200 AMM 71-09-100 or
737-300/400/500 AMM 71-00-00 as an accepted procedure.
c. Operate each engine at the same power setting. Refer to 737-100/200 AMM 71-09-100 or
737-300/400/500 AMM 71-00-00 as an accepted procedure.
(1) Make sure the amber START VALVE OPEN light on the pilots center instrument panel,
P2, goes off.
(2) Monitor the LOW OIL PRESSURE light and oil pressure indicator.
(a) The light must go off at or before the oil pressure is 15.25 psi.
(b) The LOW OIL PRESSURE light must stay off during the engine operation.
(3) Make sure the OIL FILTER BYPASS light stays off during the engine operation.
(4) Make sure the oil quantity indicator reads:
For EIS airplanes: 94 - 100%.
For non-EIS airplanes: 4.5 gallons for engine No. 1 or 4.75 gallons for engine No. 2 (on
airplanes with indicators graduated from 0 to 4.5 U.S. gallons) or 17 liters for engine No.
1 or 18 liters for engine No. 2 (on airplanes with indicators graduated from 0 to 18 liters).
(5) Push and hold the ENG OIL QTY TEST switch on the pilots center instrument panel P2-2
(non-EIS airplanes only).
(a) The indicator pointer will start to move to zero.
(b) Release the ENG OIL QTY TEST switch.
1) The indicator pointer will go back to its initial value.
(6) Make sure the oil temperature indication for the two engines is approximately equal.
(7) Make sure the N1 indicators show approximately the same N1% when the N2 indicators
show the same N2%.
(8) Make sure that the EGT for the engine system in test is approximately the same as that
for the other engine.
(9) Make sure the Fuel Flow indication for the two engines is approximately equal.
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ALERTALERT

### Page 51

d. Stop the engines. Refer to 737-100/200 AMM 71-09-100 or 737-300/400/500 AMM 71-00-00
as an accepted procedure.
18. Put the airplane in a serviceable condition.
19. Group 44:
Contact Boeing to get instructions for the change for this service bulletin, 737-31A1325 R01, and
do the work instructed by Boeing.
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ALERTALERT

### Page 52 (OCR)

BOEING SERVICE BULLETIN 737-31A1325
ALERT  ALERT
This Figure applies only to: Group 1-43.
4 LOCATIONS
FLIGHT COMPARTMENT  4 LOCATIONS
•
10
P2-2 CENTER INSTRUMENT PANEL  P2-2 CENTER INSTRUMENT PANEL  1366853
EIS CONFIGURATION  NON-EIS CONFIGURATION
FIGURE 1: P2-2 CENTER INSTRUMENT PANEL REMOVAL
(SHEET 1 OF 2)
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### Page 53

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.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
4-Quick-Release
Fastener
Release1
Refer to OHM 31-10-01 as
an accepted procedure.
169-37305-( )P2-2 PanelRemove/Keep2
FIGURE 1: P2-2 CENTER INSTRUMENT PANEL REMOVAL
(SHEET 2 OF 2)
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ALERTALERT

### Page 54 (OCR)

BOEING SERVICE BULLETIN 737-31A1325
ALERT  ALERT
This Figure applies only to: Group 1-43.
- SEE A
FLIGHT COMPARTMENT
0.55
-1.94
0.45
1.70
1.60
0.44
-o
STIFFENER
P2-2 CENTER INSTRUMENT PANEL
EIS CONFIGURATION
1367051
FIGURE 2: MODIFICATION OF THE P2-2 CENTER INSTRUMENT PANEL
(SHEET 1 OF 3)
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### Page 55 (OCR)

BOEING SERVICE BULLETIN 737-31A1325
ALERT  ALERT
1.05  1.05
1.94  - 0.95  0.94  0.95
1.70
2.30  1.60
2.20
0.44  0.94
P2-2 CENTER INSTRUMENT PANEL  P2-2 CENTER INSTRUMENT PANEL
PREFERRED NON-EIS CONFIGURATION  OPTIONAL NON-EIS CONFIGURATION
1367888
FIGURE 2: MODIFICATION OF THE P2-2 CENTER INSTRUMENT PANEL
(SHEET 2 OF 3)
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### Page 56

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.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a)1-HoleCut1
For NON-EIS airplanes, the two lights can be configured with one on top of the other no less than
1.70 inches from the panel top for visual purposes.
(b)169-37305-( )P2-2 Center Instrument
Panel
Identify2
(a) Lights can be located to the left of location shown if the designated space is already in use for EIS and
NON-EIS configurations.
(b) Refer to Paragraph 2.C.3., Parts Modified and Reidentified. For part marking information refer to SOPM
20-50-10 as an accepted procedure.
FIGURE 2: MODIFICATION OF THE P2-2 CENTER INSTRUMENT PANEL
(SHEET 3 OF 3)
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ALERTALERT

### Page 57 (OCR)

BOEING SERVICE BULLETIN 737-31A1325
ALERT  ALERT
This Figure applies only to: Group 1-43.
- SEE (A
FLIGHT COMPARTMENT
P2-2 CENTER INSTRUMENT PANEL
EIS CONFIGURATION
1368247
FIGURE 3: LIGHT ASSEMBLY INSTALLATION
(SHEET 1 OF 3)
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### Page 58 (OCR)

BOEING SERVICE BULLETIN 737-31A1325
ALERT  ALERT
P2-2 CENTER INSTRUMENT PANEL  P2-2 CENTER INSTRUMENT PANEL
PREFERRED NON-EIS CONFIGURATION  OPTIONAL NON-EIS CONFIGURATION
1368348
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.
FIGURE 3: LIGHT ASSEMBLY INSTALLATION
(SHEET 2 OF 3)
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### Page 59

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
"CABIN ALTITUDE". Refer to
OHM 31-10-01 as an accepted
procedure.
1318-630-1001-452Light AssemblyInstall1
"TAKEOFF CONFIG". Refer to
OHM 31-10-01 as an accepted
procedure.
1318-630-1001-460Light AssemblyInstall2
FIGURE 3: LIGHT ASSEMBLY INSTALLATION
(SHEET 3 OF 3)
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ALERTALERT

### Page 60 (OCR)

BOEING SERVICE BULLETIN 737-31A1325
ALERT  ALERT
This Figure applies only to: Group 1-24, 26-30, 40, 42.
L1316
L1304
W066 -
D4258J
L360
L361
FWD L
FIGURE 4: WIRE BUNDLE W066 WIRE ROUTING
(SHEET 1 OF 1)
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