# Boeing Alert Service Bulletin 737-24A1148: Revision 2

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2019-1071; AD 2021-07-17 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Alert Service Bulletin 737-24A1148](https://openairdocs.org/service-documents/boeing/737-24a1148.md)
- Title as filed: PUBLISHED - SB 737-24A1148 R02 dated Sept 2020
- Pages: 61
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## Text

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### Page 1

Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-24A1148
Original Issue: December 06, 2001
Revision 2: September 14, 2020
ATA System: 2400 2750 2760 2840 2910
SUBJECT: ELECTRICAL POWER - General - Corrosion Protection of the Electrical Connectors
in the Main Wheel Well
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 © 2001 Boeing.
Unpublished Work. All Rights Reserved.
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document
are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The
Boeing Company.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and
Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in
connection with this document unless provided in writing by Boeing.
Original Issue: December 06, 2001
737-24A1148Revision 2: September 14, 2020
1 of 61
5.0

### Page 2

Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 06, 2001
737-24A1148Revision 2: September 14, 2020
2 of 61
BOEING SERVICE BULLETIN 737-24A1148
ALERTALERT
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Table of Contents
Revision Transmittal Sheet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
2. Spares Aff ected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22
B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22
C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22
D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24
F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24
G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26
J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26
1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26
2. Data Supplied with this Ser vice Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 26
3. Installation Drawings Used in the Prepar ation of this Ser vice Bulletin: . . . . . . . . . . . 26
K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
L. Interchangeability and Inter mixability of P arts . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
M. Software Accomplishment Summar y . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29
A. Material - Pr ice and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29
B. Industry Suppor t Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29
C. Parts Necessary for Each Air plane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29
1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29
2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . . . 30
3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30
4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31
D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31
E. Special Tooling - Pr ice and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31
F. Special Tooling Necessary to do this Ser vice Bulletin . . . . . . . . . . . . . . . . . . . . . . . 31
3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33
A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33
B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33
FIGURE 1: MAIN WHEEL WELL ELECTRICAL CONNECTOR REPLACEMENT [Group 1] . . . . . . 35
FIGURE 2: CIC APPLICATION [Group 2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42
FIGURE 3: REPEAT INSPECTIONS - RESISTANCE MEASUREMENTS . . . . . . . . . . . . . . . . 49
FIGURE 4: REPEAT INSPECTIONS - EXTERIOR CORR OSION INSPECTION . . . . . . . . . . . . 52
FIGURE 5: REPEAT INSPECTIONS - INTERIOR CORROSION OR FLUID CONTAMINATION INSPECTION
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 06, 2001
737-24A1148Revision 2: September 14, 2020
3 of 61
BOEING SERVICE BULLETIN 737-24A1148
ALERTALERT

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Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 06, 2001
737-24A1148Revision 2: September 14, 2020
4 of 61
BOEING SERVICE BULLETIN 737-24A1148
ALERTALERT
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Commercial 
Airplanes
737
Service Bulletin
ALERT
Revision Transmittal SheetNumber: 737-24A1148Original Issue: December 06, 2001
Revision 2: September 14, 2020
ATA System: 2400 2750 2760 2840 2910
SUBJECT: ELECTRICAL POWER - General - Corrosion Protection of the Electrical Connectors
in the Main Wheel Well
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 2019-NM-165-AD is related to
this service bulletin.
Federal Aviation Administration (FAA) Airworthiness Directive AD 2005-18-23 is related to this service bulletin.
Effects of this Revision on airplanes on which Revision 1 was previously done:
None.
REASON FOR REVISION
This revision is sent to
– Add the 737-900ER minor model in the model designation
– Changed resistance for connector D4850 to meet Airworthiness Limitation.
– Add Federal Aviation Administration (FAA) Airworthiness Directive AD 2005-18-23 and NPRM
2019-NM-165-AD
– Change the inspection interval and the connector and backshell replacement requirements
– Change approval statements
– Remove requirement to disconnect the J-side of the connector from the disconnect bracket during the repeat
interval inspection.
– Changes the test titles to agree with the Aircraft Maintenance Manual (AMM),
The data given in Alternative Method of Compliance Notice (AMOC) 737-24A1148-AMOC-01 is included in this
revision.
These sections were changed:
1. In Summary, BACKGROUND, added compliance reference.
2. In Summary, ACTION, added reference to operational tests.
3. In Summary, COMPLIANCE, added NPRM and FAA AD statements, and compliance statements.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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Original Issue: December 06, 2001
737-24A1148Revision 2: September 14, 2020
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4. In Summary, MANPOWER, added minor model designation.
5. In Paragraph 1.C., Reason, added compliance reference, revision statement, and AMOC reference.
6. In Paragraph 1.D., Description, added test reference, revision statement and Maintenance Zone
information.
7. In Paragraph 1.E., Compliance, added NPRM and FAA AD statements, and compliance statements.
8. In Paragraph 1.F., Approval, added approval statement for non-EASA models and AMOC statement.
9. In Paragraph 1.J.1., Existing Data, added and changed references.
10. In Paragraph 1.K., Publications Affected, added publication references and Damage Tolerance Based
Structural Inspections statement.
11. In Paragraph 1.L., Interchangeability and Intermixability of Parts, revised statement.
12. In Paragraph 1.M., Software Accomplishment Summary, added section.
13. In Paragraph 2.A., Material - Price and Availability, added Group 2 and 3 information.
14. In Paragraph 2.C.2., Parts and Materials Supplied by Operator, changed supplier information and
added alternate part number.
15. In Paragraph 3.A., GENERAL INFORMATION, added WARNING, CAUTION and Notes.
16. In Paragraph 3.B., WORK INSTRUCTIONS, corrected statement.
17. In Paragraph 3.B., WORK INSTRUCTIONS, PART 3, added steps to remove and restore electrical
power to the airplane and renumbered steps.
18. In FIGURE 1, corrected bubble steps, changed notes, added alternate material, changed test titles and
added alternate test.
19. In FIGURE 2, Step table, added a row before Step 1 to remove electrical power from the airplane.
20. In FIGURE 2, added connector locator, added WARNING, changed notes, added alternate material,
changed test titles and added alternate test.
21. In FIGURE 3, added connector locator, added WARNING and changed notes.
22. In FIGURE 4, added connector locator and added more data information.
23. In FIGURE 5, added connector locator, added WARNING, changed notes, added alternate material,
changed test titles and added alternate test.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes,
to show the location of all content changes.
Pages with no vertical lines have no changes.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 06, 2001
737-24A1148Revision 2: September 14, 2020
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BOEING SERVICE BULLETIN 737-24A1148
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REVISION HISTORY
December 06, 2001Original Issue:
July 10, 2003Revision 1:
September 14, 2020Revision 2:
Export Controlled ECCN: 9E991 - BOEING
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Work - See page 1 for details.
Original Issue: December 06, 2001
737-24A1148Revision 2: September 14, 2020
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ALERTALERT

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Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 06, 2001
737-24A1148Revision 2: September 14, 2020
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ALERTALERT
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Commercial 
Airplanes
737
Service Bulletin
ALERT
SummaryNumber: 737-24A1148Original Issue: December 06, 2001
Revision 2: September 14, 2020
ATA System: 2400 2750 2760 2840 2910
SUBJECT: ELECTRICAL POWER - General - Corrosion Protection of the Electrical Connectors
in the Main Wheel Well
THIS DOCUMENT 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 DOCUMENT
TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE
NEW OWNER.
CONCURRENT REQUIREMENTS
None.
BACKGROUND
The Federal Aviation Administration (FAA) has issued an Airworthiness Directive (AD) which requires incorporation
of this service bulletin.
Several operators have reported significant corrosion to electrical connectors located in the main wheel well.
The airplanes in these operations land on runways that are treated with deicing fluids that contain potassium
formate or potassium acetate. These deicing fluids are used in multiple locations in the world.
Corrosion is an indicator that the electrical connectors may have been exposed to potassium formate and/or
potassium acetate. Loss of cadmium-plating of the electrical connectors may allow a path for moisture ingress
which may lead to electrical shorting of the connector. Electrical shorting of the electrical connectors in the wheel
well can cause incorrect function of critical systems necessary for safe flight.
Tests conducted at Boeing have demonstrated that corrosion inhibiting compounds (CICs) can be used to form
a shield against the contamination and corrosion caused by the potassium formate or potassium acetate. Tests
conducted at Boeing have also demonstrated that the recommended CICs do not affect the electrical components
or the systems.
The work given in this service bulletin will increase the corrosion resistance of the electrical connectors located
in the main wheel well. This will improve the reliability and maintainability of the electrical components that are
exposed to potassium formate or potassium acetate.
An evaluation of exposure to runway deicing fluids that contain potassium formate or potassium acetate and
repetitive inspections of connectors and application of CICs must be completed at the time intervals given in
Paragraph 1.E., Compliance.
Export Controlled ECCN: 9E991 - BOEING
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### Page 10

Boeing Service Related Problem (SRP) 737NG-SRP-26-0056S is related to this service bulletin. Boeing Service
Bulletins 737-24-1149 and 737-26-1112 are related to this service bulletin. Boeing Service Letter 737-SL-24-171
is related to this service bulletin.
ACTION (PRR 38275-36S)
In Group 1 airplanes, remove the seven wire bundle connectors from the LRU components and the disconnect
brackets.
Examine the LRUs and replace if necessary. Apply the internal avionics CIC to the LRU connectors.
Examine the seven connectors and backshells and replace if necessary. Examine the contacts for corrosion
and replace if necessary. Apply the internal avionics CIC. Mate the connectors. Do an operational test of the
affected systems. Apply the external CIC to the connectors. Return the airplane to service.
In Group 2 airplanes, apply the internal avionics CIC to the LRU connectors. Apply the internal avionics CIC to
the seven connectors. Apply the external CIC to the seven connectors. Mate the connectors. Do an operational
test of the affected systems. Apply the external CIC to the connectors. Return the airplane to service.
In Group 1 through 3 airplanes, examine the connectors and backshells and replace if necessary. Complete
operational tests if the connector has been disconnected or replaced. Apply CICs at the time intervals given in
Paragraph 1.E., Compliance.
EFFECTIVITY
See Effectivity section 1.A.
COMPLIANCE
Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2019-NM-165-AD is related to
this service bulletin.
Federal Aviation Administration (FAA) Airworthiness Directive AD 2005-18-23 is related to this service bulletin.
The effective date of AD 2005-18-23 is October 19, 2005.
Group 1-2:
Boeing recommends that operators accomplish this service bulletin within 12 months of the release date of
Revision 1 of this service bulletin.
Group 3:
Boeing recommends that operators accomplish this service bulletin within 12 months of the release date of
Revision 1 of this service bulletin or 12 months after delivery date of the airplane whichever occurs later.
Connector and backshell replacement is required immediately if the cumulative area of corrosion is greater than
10% of the total backshell area. If the cumulative area of corrosion is less than 10% of the total backshell surface
area, the backshell may be cleaned only.
Boeing recommends that each operator request data about the components of the fluids used to deice the
runways that support their operations. Use this information to determine the applicability of the changes and
inspections given in this service bulletin.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 06, 2001
737-24A1148Revision 2: September 14, 2020
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BOEING SERVICE BULLETIN 737-24A1148
ALERTALERT

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For airplanes which are exposed to runway deicing fluids that contain potassium formate or potassium acetate,
within 90 days of making this determination Boeing recommends the examination of connectors and application
of CICs, with a repeat intervalevery 24 months. For airplanes which are not exposed to runway deicing fluids
that contain potassium formate or potassium acetate, no inspections are required. A re-evaluation of exposure
must be completed at 12 month intervals. If future exposure occurs, complete this service bulletin.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the configuration changes and inspections given in this service
bulletin.
MANPOWER
Elapsed HoursTotal Task HoursAirplanes
5.010.0737-600, -700, -700C,
-800, -900, -900ER
MATERIAL INFORMATION
Boeing Supplied Kits/Parts
Refer to Paragraph 2.A., Material - Price and Availability.
Export Controlled ECCN: 9E991 - BOEING
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737-24A1148Revision 2: September 14, 2020
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Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 06, 2001
737-24A1148Revision 2: September 14, 2020
12 of 61
BOEING SERVICE BULLETIN 737-24A1148
ALERTALERT
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### Page 13

Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-24A1148
Original Issue: December 06, 2001
Revision 2: September 14, 2020
ATA System: 2400 2750 2760 2840 2910
SUBJECT: ELECTRICAL POWER - General - Corrosion Protection of the Electrical Connectors
in the Main Wheel Well
THIS DOCUMENT 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 DOCUMENT
TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE
NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
This bulletin is applicable to 737-600, 737-700, 737-700C, 737-800, 737-900, 737-900ER
Airplane(s), line number(s) 1-2598, 2600-2721, 2723-2813, 2815-2930, 2932-3068, 3070-3323,
3325-3425, 3427-3521, 3523-3611, 3613-3701, 3703-3791, 3793-3878, 3880-3915, 3917-3968,
3970-4013, 4015-4054, 4056-4098, 4100-4140, 4142-4180, 4182-4218, 4220-4255, 4257-4293,
4295-4330, 4332-4365, 4367-4398, 4400-4444, 4446-4480, 4482-4546, 4548-4608, 4610-4672,
4674-4727, 4729-4767, 4769-4812, 4814-4858, 4860-4897, 4899-4937, 4939-4977, 4979-5019,
5021-5057, 5059-5097, 5099-5137, 5139-5177, 5179-5217, 5219-5261, 5263-5297, 5299-5337,
5339-5367, 5369-5397, 5399-5427, 5429-5457, 5459-5477, 5479-5509, 5511-5541, 5543-5566,
5568-5586, 5588-5601, 5603-5622, 5624-5655, 5657-5667, 5669-5679, 5681-5711, 5713-5727,
5729-5739, 5741-5764, 5766-5787, 5789-5795, 5797-5822, 5824-5850, 5853-5879, 5881-5901,
5904-5935, 5937-5947, 5949-5962, 5964-5991, 5994-6019, 6021-6033, 6035-6047, 6049-6073,
6075, 6077-6103, 6105-6113, 6115-6131, 6133-6153, 6155-6159, 6161-6187, 6190-6215,
6217-6221, 6223-6243, 6245-6249, 6251-6271, 6274-6289, 6291-6299, 6301-6307, 6309-6325,
6327, 6329-6343, 6345-6355, 6357-6359, 6361-6371, 6373-6383, 6386-6395, 6397-6407,
6409-6411, 6413-6419, 6421-6429, 6431-6439, 6442-6447, 6449-6455, 6457-6463, 6465-6467,
6469-6471, 6473-6480, 6482-6489, 6491, 6493-6498, 6500-6507, 6509-6514, 6516-6520,
6522-6527, 6529-6531, 6533-6534, 6536-6541, 6543-6547, 6549-6554, 6556-6559, 6561,
6563-6568, 6570-6574, 6576-6581, 6583-6588, 6590-6593, 6596-6597, 6599-6602, 6604-6606,
6608-6611, 6613-6615, 6617-6620, 6622, 6624, 6626-6629, 6631-6633, 6635-6638, 6640-6642,
6644-6647, 6649-6651, 6653-6656, 6659-6660, 6662-6665, 6667-6671, 6673-6676, 6678-6680,
6682-6685, 6688-6689, 6691-6694, 6696-6698, 6700-6703, 6705-6707, 6709-6712, 6714-6716,
6718-6719, 6721, 6723-6725, 6727-6730, 6732-6734, 6736-6739, 6741-6743, 6745-6748,
6751-6752, 6754-6757, 6759-6761, 6763-6766, 6768-6770, 6772-6775, 6777-6779, 6781-6782,
6786-6788, 6790-6791, 6793, 6795, 6797, 6799-6802, 6804, 6806, 6808-6809, 6811, 6813, 6815,
6817-6818, 6820, 6822-6824, 6826-6827, 6829, 6831-6833, 6835-6836, 6838, 6840, 6842,
6844-6845, 6847, 6849, 6851, 6853-6854, 6856-6858, 6860, 6862-6863, 6865, 6867, 6869-6871,
6873-6874, 6878-6880, 6882-6883, 6885, 6887-6889, 6891-6892, 6894, 6896, 6898, 6900-6903,
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### Page 14

6905, 6907, 6910, 6912-6914, 6916, 6918-6919, 6921, 6923-6925, 6927-6928, 6930, 6932-6934,
6936-6937, 6939, 6943, 6945-6948, 6950, 6952, 6954-6955, 6957-6959, 6961-6962, 6964,
6966-6967, 6969, 6971-6972, 6977, 6979, 6981-6982, 6984, 6986-6987, 6989, 6992, 6994,
6996-6997, 6999, 7001-7002, 7007, 7009, 7011-7012, 7014, 7016-7017, 7019, 7021-7022, 7024,
7026, 7029, 7031-7032, 7034, 7036-7037, 7039, 7041, 7046-7047, 7049, 7051-7052, 7054,
7056-7057, 7059, 7061, 7063, 7066-7067, 7069, 7071-7072, 7076, 7078, 7081-7082, 7084,
7086-7087, 7089, 7091-7092, 7094, 7097, 7099, 7101-7102, 7104, 7106-7107, 7109, 7112,
7116-7117, 7119, 7121-7122, 7124, 7126-7127, 7129, 7131, 7134, 7136-7137, 7139, 7141-7142,
7146, 7149, 7151-7152, 7154, 7156-7157, 7159, 7161-7162, 7164, 7167, 7169, 7171-7172, 7174,
7176-7177, 7179, 7182, 7187, 7189, 7191, 7194, 7197, 7199, 7202, 7204, 7206, 7209, 7212,
7214, 7217, 7221, 7224, 7227, 7229, 7232, 7234-7235, 7239, 7242, 7244, 7247, 7249, 7251,
7257, 7259, 7262, 7264, 7266, 7269, 7272, 7274, 7277, 7279-7280, 7284, 7287, 7292, 7294,
7297, 7299, 7302, 7304, 7307, 7309, 7312, 7314, 7317, 7319, 7322, 7327, 7329, 7332, 7334,
7337, 7339, 7342, 7344, 7347, 7349, 7352, 7354, 7357, 7362, 7364, 7367, 7369, 7372, 7374,
7377, 7379, 7382, 7387, 7397, 7402, 7407, 7412, 7417, 7422, 7432, 7437, 7442, 7447, 7452,
7457, 7467, 7472, 7477, 7482, 7487, 7492, 7502, 7507, 7512, 7517, 7522, 7527, 7537, 7542,
7547, 7552, 7557, 7562, 7572, 7577, 7582, 7587, 7592, 7597, 8592, 9103, 9219 in 3 Group(s).
Where the effectivity is presented with hyphens between line numbers, the airplane applicability
means "through" and "inclusive", e.g. line numbers 1-9 means line numbers 1 through 9 inclusive.
Refer to PRR 38275-36 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: The Variable Number table below includes all affected airplanes up to Line Number 9219.
Affected airplanes after Line Number 9219 will be added to the service bulletin's
MyBoeingFleet.com (MBF) "get effectivity" result when they are added to the MBF Fleet
Profile Page.
DESCRIPTIONCONFIGURATIONGROUP
Airplanes that did not receive replacement connectors or corrosion
inhibiting compounds (CIC)s in production.
-1
Airplanes that did not receive CICs in production.-2
Airplanes that received replacement connectors and CICs in
production.
-3
Airplane Models:
737-600, 737-700, 737-700C, 737-800, 737-900, 737-900ER
GroupVariable Number
1YA001 - YA099
1YA101 - YA123
2YA124
3YA125 - YA199
GroupVariable Number
1YA201 - YA210
3YA211
3YA221
1YA231 - YA242
GroupVariable Number
1YA251 - YA256
1YA271 - YA272
1YA291
1YA301 - YA302
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### Page 15

GroupVariable Number
1YA311 - YA314
1YA321 - YA323
1YA336 - YA342
3YA343 - YA345
1YA351
1YA356 - YA357
1YA366
3YA367
3YA371 - YA377
1YA501 - YA536
1YA541 - YA550
3YA551 - YA552
1YA571 - YA578
1YA601 - YA615
1YA621 - YA622
1YA626 - YA629
3YA630 - YA631
1YA635
3YA636
3YA641 - YA642
1YA645 - YA647
3YA648 - YA650
1YA656 - YA658
2YA659
3YA666 - YA667
2YA671 - YA672
1YA681 - YA691
1YA701 - YA706
3YA707 - YA710
1YA721 - YA722
1YA731 - YA734
1YA751 - YA756
1YA801 - YA803
GroupVariable Number
1YA809
1YA811 - YA814
1YA831 - YA834
3YA835
1YA841 - YA856
3YA857 - YA862
1YA881 - YA882
1YA891 - YA892
1YA961 - YA966
3YA967 - YA978
1YB001 - YB006
1YB101 - YB111
3YB112 - YB132
1YB151 - YB153
3YB156 - YB158
1YB161 - YB162
3YB163 - YB164
1YB171 - YB172
1YB181 - YB183
3YB184
1YB201 - YB205
3YB206 - YB208
1YB271
1YB276
1YB301 - YB305
3YB306 - YB310
3YB371 - YB392
1YB501 - YB502
1YB521
3YB522 - YB526
3YB541 - YB544
3YB551
3YB561 - YB598
GroupVariable Number
3YB601 - YB636
3YB651
3YB656
3YB671 - YB672
3YB851 - YB863
3YB871 - YB874
3YB881 - YB893
3YB901 - YB903
3YB911
3YB961 - YB975
3YB981
3YB986 - YB998
1YC001 - YC027
3YC028 - YC030
1YC051 - YC082
3YC083 - YC084
3YC091 - YC095
1YC101 - YC104
1YC111 - YC113
1YC121
1YC126 - YC127
1YC136 - YC141
1YC146 - YC147
1YC151 - YC156
1YC166 - YC168
3YC169 - YC170
1YC171
2YC176
3YC177 - YC179
3YC186 - YC190
3YC201 - YC203
3YC206 - YC207
1YC301 - YC304
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GroupVariable Number
3YC305
1YC321 - YC382
3YC383 - YC387
1YC391 - YC392
3YC393 - YC394
1YC396
1YC401 - YC417
1YC421 - YC422
1YC426
2YC427
3YC428
1YC436
2YC437
3YC438 - YC439
1YC441 - YC448
1YC451 - YC455
1YC459
1YC461 - YC467
1YC471 - YC490
3YC491 - YC499
1YC501 - YC526
1YC571 - YC581
3YC582 - YC583
1YC587 - YC589
1YC591 - YC593
1YC601 - YC655
1YC681 - YC696
1YC701 - YC715
1YC720 - YC725
1YC727 - YC738
3YC739 - YC750
1YC751 - YC752
1YC761 - YC770
GroupVariable Number
1YC781 - YC793
1YC801 - YC884
2YC885
3YC886 - YC892
1YC901 - YC907
3YC921 - YC922
1YC931 - YC932
1YC941 - YC948
3YC949 - YC951
1YC971 - YC976
3YC977 - YC978
1YC981 - YC983
1YD001 - YD005
2YD006
3YD007
1YD021 - YD025
1YD041 - YD053
3YD054 - YD057
1YD081 - YD084
1YD101 - YD107
3YD108 - YD117
1YD121 - YD126
1YD151 - YD152
3YD153 - YD159
1YD171 - YD172
1YD201 - YD203
1YD206 - YD208
3YD209
3YD216 - YD219
1YD251 - YD252
2YD253
3YD254
3YD256 - YD257
GroupVariable Number
3YD261
1YD301 - YD320
2YD321 - YD322
3YD323 - YD334
1YD391
1YD401 - YD408
2YD409
3YD410
3YD412 - YD424
3YD481 - YD485
3YD491 - YD499
3YD501
1YD502 - YD506
3YD507 - YD512
1YD531 - YD534
3YD535
1YD541 - YD543
3YD544 - YD547
3YD561 - YD564
3YD571 - YD572
3YD591 - YD595
1YD601 - YD612
3YD651 - YD655
1YE001 - YE020
1YE051
1YE101 - YE109
1YE151 - YE157
1YE171 - YE172
1YE201 - YE203
3YE204 - YE206
1YE301
2YE302
3YE303 - YE305
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GroupVariable Number
3YE321 - YE326
3YE371 - YE383
3YF001 - YF011
3YF021 - YF049
3YF051 - YF080
3YF086 - YF087
3YF106 - YF107
3YF111 - YF114
3YF116 - YF119
3YF121 - YF132
3YF176 - YF178
3YF191 - YF192
3YF201 - YF276
3YF401 - YF402
3YF431 - YF432
3YF436 - YF437
3YF441 - YF442
3YF451 - YF460
3YF501 - YF599
3YF601 - YF685
3YF691 - YF695
3YF701 - YF707
3YF801 - YF805
3YF831 - YF832
3YF836 - YF838
3YF871 - YF872
3YF901 - YF905
3YF921 - YF928
3YF951 - YF954
1YG001 - YG043
3YG044
1YG061 - YG064
1YG066 - YG084
GroupVariable Number
3YG085 - YG089
3YG091 - YG099
3YG101 - YG104
3YG111 - YG114
3YG116 - YG150
3YG201 - YG205
3YG211 - YG214
3YG221 - YG224
3YG251 - YG252
1YG501 - YG505
3YG506 - YG517
1YG601 - YG602
3YG701
3YG711
3YG721 - YG722
3YH001 - YH012
3YH031 - YH055
3YH071 - YH080
3YH101 - YH132
3YH201 - YH202
3YH206 - YH207
3YH301 - YH307
3YH321 - YH322
3YH501 - YH542
3YH551 - YH594
3YH601 - YH606
3YH611 - YH620
3YH631 - YH632
3YH636 - YH637
3YH641
3YH681 - YH686
3YH701 - YH755
3YH801 - YH899
GroupVariable Number
3YH901 - YH908
3YH911 - YH915
3YH951 - YH952
3YJ001 - YJ013
3YJ021
1YJ471 - YJ473
2YJ474
3YJ475 - YJ480
1YJ501 - YJ517
3YJ531 - YJ579
3YJ591 - YJ599
1YJ631
3YJ632
3YJ671 - YJ694
3YJ801 - YJ867
3YJ871 - YJ880
3YJ901 - YJ904
3YJ908 - YJ929
3YJ931 - YJ937
3YJ941 - YJ956
3YJ961
3YJ976 - YJ977
3YK001 - YK007
3YK101 - YK104
3YK111 - YK112
3YK121 - YK122
3YK131 - YK133
3YK136 - YK139
3YK141 - YK142
3YK146 - YK148
3YK151 - YK154
3YK161 - YK167
3YK171
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### Page 18

GroupVariable Number
3YK176 - YK177
3YK186
3YK191
3YK196
3YK201 - YK202
3YK301 - YK314
3YK321 - YK340
3YK361 - YK378
3YK401 - YK406
3YK426 - YK427
3YK431 - YK450
3YK456 - YK467
3YK471 - YK473
3YK476
3YK478
3YK480 - YK487
3YK491 - YK493
3YK495 - YK499
3YK511 - YK516
3YK521 - YK530
3YK551 - YK571
3YK576 - YK577
3YK580 - YK585
3YK601 - YK602
3YK606 - YK607
3YK611 - YK616
3YK621 - YK634
3YK641 - YK644
3YK651 - YK665
3YK671 - YK672
3YK676 - YK677
3YK681 - YK686
3YK691
GroupVariable Number
3YK695 - YK699
3YK701 - YK713
3YK716 - YK719
3YK721 - YK741
3YK751 - YK770
3YK776 - YK778
3YK781 - YK785
3YK791 - YK792
3YK796 - YK797
3YK801 - YK899
3YK901 - YK912
3YK918 - YK919
3YK921 - YK929
3YK941 - YK999
3YL001 - YL005
3YL011 - YL016
3YL021 - YL024
3YL051 - YL052
3YL056 - YL057
3YL061
3YL066 - YL069
3YL076 - YL077
3YL101 - YL137
3YL201 - YL237
3YL241 - YL242
3YL271 - YL272
3YL281 - YL284
3YL301 - YL303
3YL311 - YL314
3YL316 - YL321
3YL351 - YL353
3YL371 - YL374
3YL401
GroupVariable Number
3YL421 - YL429
3YL431 - YL444
3YL461 - YL478
3YL501 - YL509
3YL531 - YL534
3YL541 - YL551
3YL561 - YL579
3YL591 - YL598
3YL601 - YL606
3YL611 - YL612
3YL616 - YL617
3YL621
3YL626
3YL631 - YL634
3YL636 - YL637
3YL661 - YL664
3YL676 - YL691
3YL696 - YL697
3YL701 - YL707
3YL731
3YL751 - YL752
3YL756 - YL757
3YL761 - YL780
3YL796 - YL797
3YL801 - YL815
3YL901 - YL910
3YL921 - YL940
3YL951 - YL968
3YM101 - YM103
3YM201 - YM244
3YM251 - YM299
3YM301 - YM399
3YM401 - YM415
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GroupVariable Number
3YM471
3YM481 - YM484
3YM501 - YM515
3YM521 - YM522
3YM541
3YM551 - YM553
3YM571 - YM572
3YM581 - YM582
3YM591 - YM599
3YM631 - YM634
3YM641 - YM652
3YM671 - YM674
3YM691 - YM699
3YM701 - YM710
3YM761 - YM765
3YM771 - YM779
3YN001 - YN016
3YN021 - YN024
3YN061
3YN071 - YN082
3YN091 - YN092
3YN101 - YN112
3YN121
3YN126
3YN201 - YN202
3YN211 - YN219
3YN231 - YN236
3YN261
3YN501
3YN531 - YN534
3YN551 - YN566
3YN581 - YN585
3YN591 - YN593
GroupVariable Number
3YN601 - YN606
3YN651 - YN653
3YN661 - YN663
3YN666 - YN667
3YN671 - YN674
3YN701 - YN702
3YN741 - YN746
3YN756 - YN758
3YQ001 - YQ003
3YQ011 - YQ021
3YQ026 - YQ029
3YQ036 - YQ045
3YQ201 - YQ207
3YQ231
3YQ241 - YQ251
3YQ281 - YQ284
3YQ291 - YQ296
3YQ301 - YQ302
3YQ321 - YQ324
3YQ331 - YQ334
3YQ346 - YQ347
3YQ351 - YQ367
3YQ371
3YQ401 - YQ403
3YQ451 - YQ454
3YQ456
3YQ461
3YQ471
3YQ501 - YQ520
3YQ601 - YQ606
3YQ610 - YQ614
3YR001 - YR098
3YR101 - YR105
GroupVariable Number
3YR111 - YR124
3YR126 - YR144
3YR166 - YR182
3YR186 - YR198
3YR201 - YR215
3YR231 - YR294
3YR296 - YR297
3YR301 - YR334
3YR338 - YR341
3YR361 - YR366
3YR371 - YR373
3YR376 - YR377
3YR381 - YR382
3YR386 - YR388
3YR391
3YR396 - YR399
3YR401 - YR405
3YR411 - YR413
3YR416 - YR418
3YR421 - YR424
3YR426 - YR455
3YR457 - YR499
3YR501 - YR506
3YR511 - YR520
3YR526 - YR544
3YR546 - YR551
3YR556 - YR562
3YR571 - YR582
3YR591 - YR592
3YR601 - YR605
3YR616 - YR658
3YR661 - YR663
3YR671 - YR673
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GroupVariable Number
3YR676 - YR678
3YR681 - YR682
3YR701 - YR769
3YR771 - YR799
3YR801 - YR827
3YR831 - YR838
3YR841 - YR899
3YR901 - YR903
3YR931 - YR934
3YR938 - YR944
3YR951 - YR998
3YS001 - YS002
3YS006 - YS009
3YS031 - YS032
3YS051 - YS073
3YS101 - YS120
3YS126 - YS142
3YS146 - YS160
3YS166 - YS194
3YS196 - YS197
3YS201 - YS209
3YS221 - YS225
3YS231 - YS236
3YS271 - YS288
3YS295 - YS296
3YS301 - YS348
3YS351 - YS378
3YS381 - YS386
3YS393 - YS395
3YS401
3YS451
3YS456 - YS457
3YS462 - YS465
GroupVariable Number
3YS467
3YS501 - YS502
3YS506
3YS511 - YS518
3YS531
3YS536 - YS538
3YS541 - YS542
3YS546
3YS551 - YS556
3YS561 - YS578
3YS581 - YS595
3YS601 - YS690
3YS701 - YS716
3YS721 - YS762
3YS771 - YS780
3YS806 - YS810
3YS816 - YS818
3YS823 - YS825
3YS851 - YS863
3YS876
3YS881 - YS884
3YS891 - YS894
3YS896 - YS897
3YS901 - YS909
3YS911 - YS957
3YS961 - YS974
3YS976 - YS977
3YS981 - YS987
3YS991 - YS998
3YT001 - YT004
3YT006
3YT026 - YT027
3YT031 - YT032
GroupVariable Number
3YT036 - YT038
3YT061 - YT068
3YT101 - YT138
3YT176 - YT185
3YT191
3YT196 - YT199
3YT201
3YT206 - YT207
3YT211 - YT213
3YT251 - YT299
3YT301 - YT307
3YT311 - YT312
3YT321 - YT355
3YT371 - YT372
3YT381
3YT391 - YT396
3YT401 - YT403
3YT411 - YT417
3YT427
3YT461 - YT477
3YT491 - YT492
3YT501 - YT521
3YT551 - YT552
3YT556 - YT563
3YT565
3YT571 - YT578
3YT601 - YT606
3YT701 - YT708
3YT723 - YT726
3YT761 - YT781
3YT791 - YT794
3YT796 - YT797
3YT801 - YT804
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### Page 21

GroupVariable Number
3YT811 - YT813
3YT826 - YT827
3YT831 - YT832
3YT841 - YT852
3YT856 - YT863
3YT885 - YT887
3YT891 - YT895
3YT901 - YT998
3YU001 - YU060
3YU201 - YU218
3YU301 - YU329
3YU901 - YU931
3YV001 - YV012
3YV021 - YV023
3YV030 - YV034
3YV037 - YV042
3YV045 - YV047
3YV051 - YV059
3YV081
3YV083 - YV084
3YV097 - YV099
3YV101 - YV154
3YV201 - YV203
3YV251 - YV252
3YV256 - YV257
3YV301 - YV312
3YV351 - YV368
3YV381 - YV388
3YV391 - YV394
3YV401
3YV411 - YV413
3YV431 - YV433
GroupVariable Number
3YV441 - YV454
3YV461 - YV464
3YV467 - YV470
3YV501 - YV512
3YV521
3YV571 - YV586
3YV596
3YV601 - YV605
3YV651 - YV676
3YV695 - YV696
3YV701 - YV702
3YV711
3YV722 - YV731
3YV741 - YV794
3YV801 - YV820
3YV831 - YV848
3YV881 - YV883
3YV901 - YV915
3YV923 - YV926
3YV971 - YV983
3YW001
3YW011 - YW099
3YW101 - YW164
3YW201 - YW212
3YW226 - YW240
3YW245 - YW261
3YW263
3YW267 - YW281
3YW283 - YW285
3YW292 - YW299
3YW351
3YW356 - YW358
GroupVariable Number
3YW361 - YW366
3YW371 - YW399
3YW401 - YW430
3YW441 - YW445
3YW451 - YW452
3YW471 - YW472
3YW491 - YW498
3YW531 - YW536
3YW541 - YW545
3YW551 - YW580
3YW585 - YW591
3YW595 - YW596
3YW601
3YW610 - YW613
3YW616 - YW623
3YW666
3YW696 - YW699
3YW701 - YW715
3YW726 - YW731
3YW766 - YW775
3YW801 - YW803
3YW811 - YW813
3YW821
3YW831
3YW881
3YW891 - YW893
3YW906 - YW910
3YW916 - YW918
3YW921 - YW925
3YW971 - YW976
--
--
2. Spares Affected
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### Page 22

None.
B. Concurrent Requirements
None.
C. Reason
The Federal Aviation Administration (FAA) has issued an Airworthiness Directive (AD) which requires
incorporation of this service bulletin.
Several operators have reported significant corrosion to electrical connectors located in the main wheel
well.The airplanes in these operations land on runways that are treated with deicing fluids that contain
potassium formate or potassium acetate. These deicing fluids are used in multiple locations in the
world.
Corrosion is an indicator that the electrical connectors may have been exposed to potassium formate
and/or potassium acetate. Loss of cadmium-plating of the electrical connectors may allow a path for
moisture ingress which may lead to electrical shorting of the connector. Electrical shorting of the
electrical connectors in the wheel well can cause incorrect function of critical systems necessary for
safe flight.
Tests conducted at Boeing have demonstrated that corrosion inhibiting compounds (CICs) can be used
to form a shield against the contamination and corrosion caused by the potassium formate or potassium
acetate. Tests conducted at Boeing have also demonstrated that the recommended CICs do not affect
the electrical components or the systems.
The work given in this service bulletin will increase the corrosion resistance of the electrical connectors
located in the main wheel well. This will improve the reliability and maintainability of the electrical
components that are exposed to potassium formate or potassium acetate.
An evaluation of exposure to runway deicing fluids that contain potassium formate or potassium acetate
and repetitive inspections of connectors and application of CICs must be completed at the time intervals
given in Paragraph 1.E., Compliance.
Boeing Service Related Problem (SRP) 737NG-SRP-26-0056S is related to this service bulletin. Boeing
Service Bulletins 737-24-1149 and 737-26-1112 are related to this service bulletin. Boeing Service
Letter 737-SL-24-171 is related to this service bulletin.
Revision 1: sent to inform operators of changes to the runway deicing compounds shown in this service
bulletin. Boeing has determined that the corrosive effects of potassium acetate on electrical connectors
in the main wheel well of the airplane is similar to the corrosive effects of potassium formate. The
original release of the service bulletin described the corrosive effects of the potassium formate only.
Revision 2: sent to:
– Add the 737-900ER minor model in the model designation
– Changed resistance for connector D4850 to meet Airworthiness Limitation.
– Add Federal Aviation Administration (FAA) Airworthiness Directive AD 2005-18-23 and NPRM
2019-NM-165-AD
– Change the inspection interval and the connector and backshell replacement requirements
– Change approval statements
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– Remove requirement to disconnect the J-side of the connector from the disconnect bracket during
the repeat interval inspection.
– Changes the test titles to agree with the Aircraft Maintenance Manual (AMM),
The data given in Alternative Method of Compliance Notice 737-24A1148-AMOC-01 is included in this
revision.
D. Description
In Group 1 airplanes, remove the seven wire bundle connectors from the LRU components and the
disconnect brackets.
Examine the LRUs and replace if necessary. Apply the internal avionics CIC to the LRU connectors.
Examine the seven connectors and backshells and replace if necessary. Examine the contacts for
corrosion and replace if necessary. Apply the internal avionics CIC. Mate the connectors. Do an
operational test of the affected systems. Apply the external CIC to the connectors. Return the airplane
to service.
In Group 2 airplanes, apply the internal avionics CIC to the LRU connectors. Apply the internal avionics
CIC to the seven connectors. Apply the external CIC to the seven connectors. Mate the connectors.
Do an operational test of the affected systems. Apply the external CIC to the connectors. Return the
airplane to service.
In Group 1 through 3 airplanes, examine the connectors and backshells and replace if necessary.
Complete operational tests if the connector has been disconnected or replaced. Apply CICs at the time
intervals given in Paragraph 1.E., Compliance.
Revision 1: More work is necessary on airplanes changed as shown in the initial release of this service
bulletin to accomplish the repeat inspections at the time intervals given in Paragraph 1.E., Compliance.
Revision 2: Effects of this Revision on airplanes on which Revision 1 was previously done:
None.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1:
Affected Maintenance Zones
ZoneModel
131, 132, 133, 134737-600, 737-700, 737-700C,
737-800, 737-900
Group 2:
Affected Maintenance Zones
ZoneModel
131, 132, 133, 134737-600, 737-700, 737-800
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Group 3:
Affected Maintenance Zones
ZoneModel
131, 132, 133, 134737-600, 737-700, 737-700C,
737-800, 737-900, 737-900ER
E. Compliance
Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2019-NM-165-AD is
related to this service bulletin.
Federal Aviation Administration (FAA) Airworthiness Directive AD 2005-18-23 is related to this service
bulletin. The effective date of AD 2005-18-23 is October 19, 2005.
Group 1-2:
Boeing recommends that operators accomplish this service bulletin within 12 months of the release
date of Revision 1 of this service bulletin.
Group 3:
Boeing recommends that operators accomplish this service bulletin within 12 months of the release
date of Revision 1 of this service bulletin or 12 months after delivery date of the airplane whichever
occurs later.
Connector and backshell replacement is required immediately if the cumulative area of corrosion is
greater than 10% of the total backshell area. If the cumulative area of corrosion is less than 10% of
the total backshell surface area, the backshell may be cleaned only.
Boeing recommends that each operator request data about the components of the fluids used to deice
the runways that support their operations. Use this information to determine the applicability of the
changes and inspections given in this service bulletin.
For airplanes which are exposed to runway deicing fluids that contain potassium formate or potassium
acetate, within 90 days of making this determination Boeing recommends the examination of connectors
and application of CICs, with a repeat interval every 24 months. For airplanes which are not exposed
to runway deicing fluids that contain potassium formate or potassium acetate, no inspections are
required. A re-evaluation of exposure must be completed at 12 month intervals. If future exposure
occurs, complete this service bulletin.
F. Approval
NOTE: The approval statement that follows is valid for all affected airplanes, except 737-700C
airplanes.
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.
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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.
NOTE: The approval statement that follows is valid for all 737-700C airplanes.
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 for the 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.
NOTE: The AMOC statement that follows is valid for all affected airplanes, except 737-900ER.
In addition, the Manager of the FAA Seattle ACO Branch approves the inspection and change defined
in this service bulletin revision as an alternative method of compliance to the requirements of paragraph
(f) of AD 2005-18-23. All provisions of AD 2005-18-23 that are not specifically referenced in the above
statement remain fully applicable and must be complied with accordingly.
G. Manpower
The table below shows an estimate of the man-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
man-hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
— Time to adjust to the workplace
— Time to schedule the work
— Time to examine the work
— Time to cure the materials
— Time to make the parts
— Time to find the tools.
Elapsed HoursTask-HoursNumber of
Persons
Task
.51.02Open Access
3.06.02Examine and Change
.51.02Close Access
1.02.02Test
5.010.0TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
None
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I. Electrical Load Data
Not changed
J. References
1. Existing Data:
a. Engineering Change Memo PRR 38275-36S
b. Service Related Problem (SRP) 737NG-SRP-26-0056S
c. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2005-18-23
d. Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM)
2019-NM-165-AD
e. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-20-00, 20-24-12, 20-25-00,
20-25-12, 20-35-11, 20-35-22, 20-60-09, 20-61-11, 20-63-14
f. 737-600/700/800/900 Aircraft Maintenance Manual (AMM) 24-22-00, 27-09-31, 27-09-61,
27-51-00, 27-51-02, 27-61-12, 27-81-00, 28-41-00, 29-11-81, 29-22-31, 29-33-21, 31-51-00,
32-31-71
g. Boeing Service Bulletins 737-24-1149, "ELECTRICAL POWER - General - Corrosion Protection
of the Electrical Connectors in the Main Wheel Well", "ELECTRICAL POWER - General -
Corrosion Protection of the Electrical Connectors in the Main Wheel Well", and 737-26A1112,
"FIRE PROTECTION - Detection - Corrosion Protection of the Fenwal Connectors in the Main
Wheel Well".
h. Boeing Service Letter 737-SL-24-171
i. 737-600/700/700C/800/900/900ER Special Compliance Items/Airworthiness Limitations
(SCI/AWL) D626A0001-9-04.
j. 737-600/700/800/900 Airworthiness Limitations (AWL) 28-AWL-03, 28-AWL-04
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
None.
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K. Publications Affected
1. Publications:
Chapter-SectionPublication
D6-82560737 Corrosion Prevention Manual
27-51, 29-11, 53-21737 Illustrated Parts Catalog
24-00, 28-42737 Aircraft Maintenance Manual
28-41737 Fault Isolation 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
None.
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### Page 29

2.    MATERIAL INFORMATION
A. Material - Price and Availability
Group 1:
The operator can supply the parts and materials shown in the kits in Paragraph 2.C., Parts Necessary
For Each Airplane. As an alternative, operators can purchase the kit from Boeing Spares. The Boeing
price data shown below is given for planning purposes. Supply data can be given if requested.
Group 1:
Unit Price thruNameKit Number
July 31/03
$831.00Top Kit, Main Wheel Well
Connector Replacement
002A0006-39
Group 2-3:
The parts and materials shown in the kits in Paragraph 2.C., Parts Necessary For Each Airplane may
be necessary based on inspection results.
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:
To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by
the Operator, are necessary for each airplane.
Kit 002A0006 - Top Kit, Main Wheel Well Connector Replacement
NotesExisting Part NumberNameQTYNew Part Number
-39
BACC10KD14Backshell (D762)1BACC10KA14
BACC10KD22Backshell (D4850J/P)2BACC10KA22
BACC10KE14Backshell (D764)1BACC10KB14
BACC10KD14Backshell (D46020J/P)2BACC10KD14
BACC10KD20Backshell (D46038J/P)2BACC10KD20
BACC10KE10Backshell (D1582)1MS27559-2
BACC10KE14Backshell (D1014)1MS27559-4
(a) (c)BACC63BV14F7S8Connector (D46020J)1CN0967C14A07S8-000 or
R071114G07S8-000 (b)
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Kit 002A0006 - Top Kit, Main Wheel Well Connector Replacement
NotesExisting Part NumberNameQTYNew Part Number
-39
(a) (c)BACC63BV20F28S7Connector (D46038J)1CN0967C20A28S7Y000 or
R071120G28S7-000 or
CN0967C20A28S7-000
(b)
(a)
(a) (c)BACC63BP14C7P8Connector (D46020P)1CN0966A14A07P8-000 or
R071014E07P8-000 (b)
(a) (c)BACC63BP20C28P7Connector (D46038P)1CN0966A20A28P7Y000 or
R071020E28P7-000 or
CN0966A20A28P7-000
(b)
(a)
(c)BACC63CB10-20SNConnector (D1582)1BACC45FT10-20S
(c)BACC63CB14-7SNConnector (D1014)1BACC45FT14-7S
(c)BACC63BP22C55SNConnector (D4850P)1BACC63BP22D55SN
(c)BACC63BV22F55PNConnector (D4850J)1BACC63BV22B55PN
MS3459LS14S-5SConnector (D762, D764)2MS3459LS14S-5S
(a) Labinal Components and Systems Inc. (V13556) Cinch Military Aerospace Division 8821 Science
Center Drive Minneapolis, Minnesota 55428-3619
(b) RMS Co. (V41118) 8600 Evergreen Boulevard Minneapolis, Minnesota 55433-6036
(c) The new part number shown in the left column above is the preferred part number. If necessary, to
meet the compliance recommendations given in this service bulletin, a new replacement part of the existing
part number is optional to the preferred part only if the preferred part is unavailable.
2. Parts and Materials Supplied by the Operator:
NotesNameQTYPart Number / Specification
(a)Dinitrol AV25 (External CIC)1 CanAV25 - 13.5 Ounces
(b)Zip-Chem Corrosion Inhibiting Com-
pound (Internal CIC)
1 Can
-
D5026NS (D-5026NS) - 11
Ounces or ZC-026 - Bulk
Material
(a) This part can be obtained directly from the supplier: Aviall (Cage 22819) 2750 Regent
Boulevard, Dallas, Texas 75261 Telephone: 1-800-Aviall-1 Website:
http://www.aviall.com
(b) Zip-Chem ZC-026 is the same as D5026NS except it is in bulk form. It has no pro-
pellant so it must be applied with a pump-action sprayer.
3. Parts Modified and Reidentified:
None.
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4. Parts Removed and Not Replaced:
None.
D. Parts Necessary to Change Spares
None
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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### Page 33

3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
OBEY THE MANUFACTURER'S PROCEDURES WHEN YOU DO TASKS THAT
ARE RELATED TO AIRWORTHINESS LIMITATIONS (AWL). IF YOU DO NOT
OBEY THE PROCEDURES, IT CAN INCREASE THE RISK OF A SOURCE OF
IGNITION. INJURIES TO PERSONNEL, AND DAMAGE TO EQUIPMENT CAN
OCCUR IF THERE IS A FIRE OR EXPLOSION.
WARNING
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.
CAUTION
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, 20-10-12 for the wire installation procedures.
4. This service bulletin includes functional test procedures for the systems repaired by
this service bulletin. More functional tests can possibly be necessary in accordance
with standard maintenance practices because of interruption to other airplane systems.
5. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
6. Some Work Instructions task(s) are related to 737-600/700/700C/800/900/900ER
Special Compliance Items/Airworthiness Limitation (SCI/AWL) D626A0001-9-04.
Strict adherence to SCI/AWL D626A0001-9-04 is required.
7. The Work Instructions include electrical bonding resistance tasks that are related to
Critical Design Configuration Control Limitation (CDCCL) and Airworthiness Limitation
Instructions (ALI). Strict adherence to CDCCL and ALI are required. Refer to
28-AWL-03 and AWL 28-04.
B. WORK INSTRUCTIONS
The Accomplishment Instructions are divided into three Parts:
PART 1 - Electrical Connector Replacement and CIC Application - Group 1 Airplanes
1. Get access to the wheel well of the main landing gear.
2. In Group 1 airplanes, examine the electrical connectors and backshells and replace if necessary
as shown in Figure 1. Apply CIC in the wheel well of the main landing gear as shown in Figure 1.
3. Put the airplane back to a serviceable condition.
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4. Repeat the inspection of the connectors and backshells at the time intervals given in Paragraph
1.E., Compliance.
PART 2 - CIC Application - Group 2 Airplanes
1. Get access to the wheel well of the main landing gear.
2. In Group 2 airplanes, apply CIC in the wheel well of the main landing gear as shown in Figure 2.
3. Put the airplane back to a serviceable condition.
4. Repeat the inspection of the connectors and backshells at the time intervals given in Paragraph
1.E., Compliance.
PART 3 - Repeat Inspections - Electrical Connector Inspection and CIC Application - Group 1,
2, and 3 Airplanes
1. Remove the electrical power from the airplane. Refer to 737-600/700/800/900 AMM 24-22-00/201.
2. Get access to the wheel well of the main landing gear.
3. In Group 1, 2 and 3 airplanes, examine the connectors and backshells at the time intervals given
in Paragraph 1.E, Compliance.
a. Measure the resistance of the D4850J/P connectors as shown in Figure 3.
b. Examine the connectors and backshells for exterior corrosion as shown in Figure 4.
c. Change the electrical connectors, backshells and contacts, if necessary, and apply CIC in the
wheel well of the main landing gear as shown in Figure 5.
4. Restore the electrical power to the airplane. Refer to 737-600/700/800/900 AMM 24-22-00/201.
5. Put the airplane back to a serviceable condition.
6. Repeat the inspection of the connectors and backshells at the time intervals given in Paragraph
1.E., Compliance.
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BOEING SERVICE BULLETIN 737-24A1148
ALERT  ALERT
This Figure applies only to: Group 1.
SEE
1,22
D46038J/P
(10)  (POS 3)
M/W ALO675C
SEE
SEE  D4850J/P  11/12  MW V34  D764
TX8 (POS 2)  SEE
SEE
M/W AL0675B
6 D762  SEE D
MW V33
SEE
→ FWD  •FWD
V66730
FIGURE 1: MAIN WHEEL WELL ELECTRICAL CONNECTOR REPLACEMENT
(SHEET 1 OF 7)
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### Page 36 (OCR)

BOEING SERVICE BULLETIN 737-24A1148
ALERT  ALERT
D1014
115116 M/W V52
SEE O
D46020J/P
2 17 18) (POS 4)
M/W AL0720B
SEE •
FWD
LRU
(13)14  D1582  M/W V94  (19,20)
SEE •
CONNECTOR  V66685
TYPICAL
FIGURE 1: MAIN WHEEL WELL ELECTRICAL CONNECTOR REPLACEMENT
(SHEET 2 OF 7)
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### Page 37

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
NOTESQTYPART NUMBERNAMETASKSTEP
Remove the electrical power
from the airplane. Refer to 737-
600/700/800/900 AMM 24-22-
00/201.
--Electrical PowerRemove1
Disconnect the D762, D764,
D1014 and D1582 connectors
from the LRUs. Disconnect the
D4850P, D46020P and
D46038P connectors. It is not
necessary to remove recepta-
cles D4850J, D46020J and
D46038J from the disconnect
bracket.
7-ConnectorsDisconnect2
(a) (b)--LRU Connector and
Contacts
Examine /
Clean or
Replace
3
--
(c)-D-5026NS (D5026NS) or
ZC-026
Internal CICApply4
(j) (k) Refer to SWPM 20-24-12
and SWPM 20-25-12.
1MS3459LS14S-5SConnector D762Examine /
Clean or
Replace
5
1BACC10KD14Backshell
(d) (e) Refer to SWPM 20-63-14.5M39029/30-217Contacts (D762)
If necessary. Refer to SWPM
20-25-12 and SWPM 20-61-11.
1MS3459LS14S-5S BConnector D762Install6
1BACC10KA14Backshell
WARNING: THIS STEP IS RE-
LATED TO SCI/AWL REQUIRE-
MENTS.
1
1
BACC63BV22F55PN
BACC63BP22C55SN
Connector D4850J
Connector D4850P
Examine /
Clean or
Replace
7
2BACC10KD22Backshell (j) (k) Refer to SWPM 20-25-12,
SWPM 20-35-22 or SWPM 20-
61-11
(d) (e) (f) Refer to SWPM 20-61-
11.
55
55
BACC47CN1( )
BACC47CP1( )
Contacts (D4850J)
Contacts (D4850P)
WARNING: THIS STEP IS RE-
LATED TO SCI/AWL REQUIRE-
MENTS.
1
1
BACC63BV22B55PN
BACC63BP22D55SN
Connector D4850J
Connector D4850P
Install8
2BACC10KA22Backshell (g) If necessary. Refer to SWPM
20-25-12, SWPM 20-35-22 or
SWPM 20-61-11.
FIGURE 1: MAIN WHEEL WELL ELECTRICAL CONNECTOR REPLACEMENT
(SHEET 3 OF 7)
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(j) (k)1BACC63BV20F28S7Connector D46038J
Connector D46038P
Examine /
Clean or
Replace
9
Refer to SWPM 20-25-12, SW-
PM 20-35-11 or SWPM 20-61-
11.
1BACC63BP20C28P
2BACC10KD20Backshell
(d) (e) Refer to SWPM 20-61-11.24BACC47CP1( )Contacts (D46038J)
4BACC47CP3( )
24BACC47CN1( )Contacts (D46038P)
4BACC47CN3( )
(g) If necessary. Refer to SWPM
20-25-12 and SWPM 20-61-11.
1CN0967C20A28S7Y000
or R071120G28S7-000 or
CN0967C20A28S7-000
Connector D46038JInstall10
1CN0966A20A28P7Y000
or R071020E28P7-000 or
CN0966A20A28P7-000
Connector D46038P
2BACC10KD20Backshell
(j) (k) Refer to SWPM 20-24-12
and SWPM 20-25-12.
1MS3459LS14S-5SConnector D764Examine /
Clean or
Replace
11
1BACC10KE14Backshell
(d) (e) Refer to SWPM 20-63-14.5M39029/30-217Contacts (D764)
If necessary. Refer to SWPM
20-24-12 and SWPM 20-25-12.
1MS3459LS14S-5SConnector D764Install12
1BACC10KB14Backshell
(j) (k) Refer to SWPM 20-25-12
and SWPM 20-61-11.
1BACC63CB10-20SNConnector D1582Examine /
Clean or
Replace
13
1BACC10KE10Backshell
(d) (e) Refer to SWPM 20-61-11.-BACC47CP2( )Contacts (D1582)
(g) If necessary. Refer to SWPM
20-25-12 and SWPM 20-61-11..
1BACC45FT10-20SConnector D1582Install14
1MS27559-2Backshell
(j) (k) Refer to SWPM 20-25-12
and SWPM 20-61-11..
1BACC63CB14-7SNConnector D1014Examine /
Clean or
Replace
15
1BACC10KE14Backshell
(d) (e) Refer to SWPM 20-61-11.7BACC47CP2( )Contacts (D1014)
(g) If necessary. Refer to SWPM
20-25-12 and SWPM 20-61-11..
1BACC45FT14-7SConnector D1014Install16
1MS27559-4Backshell
(j) (k) Refer to SWPM 20-25-12
and SWPM 20-61-11.
1
1
BACC63BV14F7S8
BACC63BP14C7P8
Connector D46020J
Connector D46020P
Examine /
Clean or
Replace
17
2BACC10KD14Backshell
(d) (e) Refer to SWPM 20-61-11.7BACC47CP2( )Contacts (D46020J)
7BACC47CN1( )Contacts (D46020P)
FIGURE 1: MAIN WHEEL WELL ELECTRICAL CONNECTOR REPLACEMENT
(SHEET 4 OF 7)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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BOEING SERVICE BULLETIN 737-24A1148
ALERTALERT

### Page 39

(g) If necessary. Refer toSWPM
20-25-12 and SWPM 20-61-11.
1CN0967C14A07S8-000 or
R071114G07S8-000
Connector D46020JInstall18
1CN0966A14A07P8-000 or
R071014E07P8-000
Connector D46020P
2BACC10KD14Backshell
(h)7D-5026NS (D5026NS) or
ZC-026
Internal CICApply19
WARNING: THIS STEP IS RE-
LATED TO SCI/AWL REQUIRE-
MENTS.
7-ConnectorsMate20
Mate the D762, D764, D1014
and D1582 connectors to the
LRUs. Connect the D4850P,
D46020P and D46038P connec-
tors.
Restore the electrical power to
the airplane. Refer to 737-
600/700/800/900 AMM 24-22-
00/201.
--Electrical PowerRestore21
Do the operational tests of the
affected systems as shown in
Table I.
--Operational TestDo22
(i)-AV25External CICApply23
Examine the LRU connectors for signs of corrosion. Look for the presence of moisture, corrosion pits,
and / or white-colored material buildup. (Accumulation of white-colored material is an indication of
corrosion.) Examine the LRU connector contacts for signs of corrosion. Look for exposure of the copper
base metal or blue-green deposits that indicate the presence of copper corrosion. Look for a black or
reddish discoloration of the gold-plated contacts.
(a)
If there are no signs of corrosion, clean the LRU connector and contacts with a cotton swab moistened
with isopropyl alcohol. If there are signs of corrosion, replace the LRU with a new LRU of the same
part number. Replace the LRU as shown in the applicable AMM.
(b)
Apply the D5026NS CIC to the pin contacts of the LRU connector receptacle. Spray with a 2 - 4 second
burst 4 - 8 inches away from the connector.The operator may use the ZC-026 instead of the D-5026NS
(D5026NS). Apply the ZC-026 with a pump-action sprayer.
(c)
Examine the connector contacts for signs of corrosion. Look for exposure of the copper base metal or
blue-green deposits that indicate the presence of copper corrosion.
(d)
If there are no signs of corrosion, clean the connector contacts with a cotton swab moistened with
isopropyl alcohol. If there are signs of corrosion, replace all contacts in the connector with new contacts
of the same part number. Replace the contact as shown in the applicable SWPM.
(e)
FIGURE 1: MAIN WHEEL WELL ELECTRICAL CONNECTOR REPLACEMENT
(SHEET 5 OF 7)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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BOEING SERVICE BULLETIN 737-24A1148
ALERTALERT

### Page 40

Connector D4850J and D4850P have shield wire terminations. Look for the presence of moisture,
corrosion pits, and / or white-colored material buildups on the shield wire terminations. (Accumulation
of white-colored material is an indication of corrosion.) If there are no signs of corrosion on the terminal
lug or the exposed wire strands, clean the terminal lug and exposed wire strands with a cotton swab
moistened with isopropyl alcohol. If there are signs of corrosion, replace the terminal lug with a terminal
lug of the same part number. Replace the terminal lug as shown in the applicable SWPM.
(f)
The part number shown is the preferred part number. If necessary, to meet the compliance recommen-
dations given in this service bulletin, a new replacement part of the existing part number is optional to
the preferred part only if the preferred part is unavailable.
(g)
Apply the D-5026NS (D5026NS) CIC to the connectors. Spray with a 2 - 4 second burst 4 - 8 inches
away from the connector. The operator may use the ZC-026 instead of the D5026NS. Apply the ZC-
026 with a pump-action sprayer.
(h)
Apply the external CIC to the mated connector assembly, include the grommets and backshells, after
the operational tests are done. Spray the connector assembly completely until the AV25 drips from it.
Do not remove excess AV25.
(i)
Examine the connector for signs of corrosion. Look for the presence of moisture, corrosion pits and/or
white-colored material buildup. (Accumulation of white-colored material is an indication of corrosion.)
If there are no signs of corrosion, clean the connector with a cloth moistened with isopropyl alcohol. If
there are signs of corrosion, replace the connector as shown.
(j)
Examine the backshell for signs of corrosion. Look for the presence of corrosion pits, and/or white-
colored material buildup. (Accumulation of white-colored material is an indication of corrosion, and/or
loss of olive-drab color.) If there are signs of corrosion on the backshell, estimate the area of corrosion.
If the cumulative area of corrosion is less than 10% of the total backshell surface area, clean the
backshell with a cloth moistened with isopropyl alcohol. If the cumulative area of corrosion is greater
than 10% of the total backshell surface area, replace the connector and backshell as shown.
(k)
TABLE 1 - Operational Tests
NotesOperational TestConnector
737-600/700/800/900 AMM 29-11-81 Engine Driven Pump Supply Shutoff Valve
Operational Test.
D00762
737-600/700/800/900 AMM 29-11-81 Engine Driven Pump Supply Shutoff Valve
Operational Test.
D00764
737-600/700/800/900 AMM 27-51-02 Trailing Edge Flap Bypass Valve Functional
Test.
D01014
737-600/700/800/900 AMM 27-51-00 Trailing Edge Flap System Operational Test.D01582
737-600/700/800/900 AMM 28-41-00 Fuel Quantity BITE Test Procedure.D4850J/P
737-600/700/800/900 AMM 27-81-00 Leading Edge Cruise Depressurization Test.D46020J/P
(a)737-600/700/800/900 AMM 29-33-21 Standby Hydraulic System Reservoir Low
Quantity Switch Installation Test.
FIGURE 1: MAIN WHEEL WELL ELECTRICAL CONNECTOR REPLACEMENT
(SHEET 6 OF 7)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 06, 2001
737-24A1148Revision 2 September 14, 2020
40 of 61
BOEING SERVICE BULLETIN 737-24A1148
ALERTALERT

### Page 41

TABLE 1 - Operational Tests
NotesOperational TestConnector
737-600/700/800/900 AMM 27-09-31 Flight Controls Shutoff Valve Test.D46038J/P
737-600/700/800/900 AMM 27-09-61 Low Pressure Warning Switch Test.
737-600/700/800/900 AMM 27-61-12 Spoiler Shutoff Valve Test.
737-600/700/800/900 AMM 27-81-00 Leading Edge Uncommanded Motion Protection
Test.
737-600/700/800/900 AMM 29-22-31 Power Transfer Unit (PTU) Control Valve In-
stallation Test.
737-600/700/800/900 AMM 31-51-00 Takeoff Warning System Test.
737-600/700/800/900 AMM 32-31-71 Operational Test of the Transfer Valve.
(a) As an alternative to the 737 AMM 29-33-21/401, Paragraph 3, Standby Hydraulic System
Reservoir Low Quantity Switch Installation Test, Steps (1) through (12), the following steps may be
taken:
1. Remove plug D678 from the S49 Standby Hydraulic System Low Quantity Indication Switch.
2. Apply a ground to pin 2 of the D678 plug and make sure that the Standby Hydraulic System
Low Oil Quantity light on the Flight Control Panel P5-3 comes on.
3. Remove the ground from pin 2 of the D678 plug and reconnect the plug to the S49 Standby
Hydraulic System Low Quantity Indication Switch. Make sure that the Low Quantity light on
the Flight Control Panel P5-3 goes out.
This alternate test method would eliminate the requirement to drain and refill the Standby Hydraulic
System reservoir.
FIGURE 1: MAIN WHEEL WELL ELECTRICAL CONNECTOR REPLACEMENT
(SHEET 7 OF 7)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 06, 2001
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BOEING SERVICE BULLETIN 737-24A1148
ALERTALERT

### Page 42 (OCR)

BOEING SERVICE BULLETIN 737-24A1148
ALERT  ALERT
This Figure applies only to: Group 2.
SEE
1011
D46038J/P
) (POS 3)
M/W ALO675C
SEE •
SEE  D4850J/P  012 0764  MW V34
SEE  6) 12) (POS 2)  SEE
M/W AL0675B
12) D762  / MW V33  SEE OO
SEE
→FWD  SEWD
2564844
FIGURE 2: CIC APPLICATION
(SHEET 1 OF 7)
Original Issue: December 06, 2001
Revision 2 September 14, 2020  Export Controlled ECCN: 9E991 - BOEING  737-24A1148
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  42 of 61

### Page 43 (OCR)

BOEING SERVICE BULLETIN 737-24A1148
ALERT  ALERT
D1014
112  M/W V52
SEE O
D46020J/P
16 12 (POS 4)
M/W AL0720B
SEE D
DOD MN 294
SEE D
2564845
FIGURE 2: CIC APPLICATION
(SHEET 2 OF 7)
Original Issue: December 06, 2001
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### Page 44 (OCR)

BOEING SERVICE BULLETIN 737-24A1148
ALERT  ALERT
J-SIDE RECEPTACLE
V66706
FIGURE 2: CIC APPLICATION
(SHEET 3 OF 7)
Original Issue: December 06, 2001
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Work - See page 1 for details.  44 of 61

### Page 45

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
NOTESQTYPART NUMBERNAMETASKSTEP
Remove the electrical power
from the airplane. Refer to 737-
600/700/800/900 AMM 24-22-
00/201.
--Electrical PowerRemove-
Disconnect the D762, D764,
D1014 and D1582 connectors
from the LRUs. Disconnect the
D4850P, D46020P and
D46038P connectors. It is not
necessary to remove recepta-
cles D4850J, D46020J and
D46038J from the disconnect
bracket.
7-ConnectorsDisconnect1
(a) (b)--LRU Connector and
Contacts
Examine /
Clean or
Replace
2
-
(c)-D-5026NS (D5026NS) or
ZC-026
Internal CICApply3
(k)--ConnectorsExamine /
Clean or
Replace
4
(d) (e)--Contacts
(l)--Backshells
(f)7D-5026NS (D5026NS) or
ZC-026
Internal CICApply5
Mate the D762, D764, D1014
and D1582 connectors to the
LRUs. Connect the D4850P,
D46020P and D46038P connec-
tors.
7-ConnectorsMate6
WARNING: THIS STEP IS RE-
LATED TO SCI/AWL REQUIRE-
MENTS.
--DC ResistanceMeasure7
(g) D4850J/P
WARNING: THIS STEP IS RE-
LATED TO SCI/AWL REQUIRE-
MENTS.
--DC ResistanceMeasure8
(h) D4850J/P
WARNING: THIS STEP IS RE-
LATED TO SCI/AWL REQUIRE-
MENTS.
--DC ResistanceMeasure9
(i) D4850J/P
FIGURE 2: CIC APPLICATION
(SHEET 4 OF 7)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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BOEING SERVICE BULLETIN 737-24A1148
ALERTALERT

### Page 46

Restore the electrical power to
the airplane. Refer to 737-
600/700/800/900 AMM 24-22-
00/201.
--Electrical PowerRestore10
Do the operational tests of the
affected systems as shown in
Table I of Figure 1.
--Operational TestDo11
(j)-AV25External CICApply12
Examine the LRU connectors for signs of corrosion. Look for the presence of moisture, corrosion pits,
and / or white-colored material buildup. (Accumulation of white-colored material is an indication of
corrosion.) Examine the LRU connector contacts for signs of corrosion. Look for exposure of the
copper base metal or blue-green deposits that indicate the presence of copper corrosion. Look for a
black or reddish discoloration of the gold-plated contacts.
(a)
If there are no signs of corrosion, clean the LRU connector and contacts with a cotton swab moistened
with isopropyl alcohol. If there are signs of corrosion, replace the LRU with a new LRU of the same
part number. Replace the LRU as shown in the applicable AMM.
(b)
Apply the D-5026NS (D5026NS) CIC to the pin contacts of the LRU connector receptacle. Spray with
a 2 - 4 second burst 4 - 8 inches away from the connector. The operator may use the ZC-026 instead
of the D5026NS. Apply the ZC-026 with a pump-action sprayer.
(c)
Examine the connector contacts for signs of corrosion. Look for exposure of the copper base metal
or blue-green deposits that indicate the presence of copper corrosion.
(d)
If there are no signs of corrosion, clean the connector contacts with a cotton swab moistened with
isopropyl alcohol. If there are signs of corrosion, replace all contacts in the connector with new contacts
of the same part number. Replace the contact as shown in the applicable SWPM.
(e)
Apply the D-5026NS (D5026NS) CIC to the connectors. Spray with a 2 - 4 second burst 4 - 8 inches
away from the connector. The operator may use the ZC-026 instead of the D5026NS. Apply the ZC-
026 with a pump-action sprayer.
(f)
For D4850J/P only, measure the DC resistance between the connector receptacle backshell and the
airplane structure or bracket disconnect. Maximum resistance 3.0 milliohms. If the resistance mea-
surements are greater than the specified milliohms, refer to SWPM 20-20-00, SWPM 20-25-00,
SWPM 20-60-09 and SWPM 20-61-11 for repair instructions.
(g)
For D4850J/P only, measure the DC resistance between the connector plug backshell and the con-
nector receptacle. Maximum resistance 3.0 milliohms. If the resistance measurements are greater
than the specified milliohms, refer to SWPM 20-20-00, SWPM 20-25-00, SWPM 20-60-09 and SWPM
20-61-11 for repair instructions.
(h)
For D4850J/P only, measure the DC resistance between the connector plug backshell and the con-
nector plug. Maximum resistance 3.0 milliohms. If the resistance measurements are greater than the
specified milliohms, refer to SWPM 20-20-00, SWPM 20-25-00, SWPM 20-60-09 and SWPM 20-61-
11 for repair instructions.
(i)
Apply the external CIC to the mated connector assembly, include the grommets and backshells, after
the operational tests are done. Spray the connector assembly completely until the AV25 drips from
it. Do not remove excess AV25.
(j)
FIGURE 2: CIC APPLICATION
(SHEET 5 OF 7)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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ALERTALERT

### Page 47

Examine the connector for signs of corrosion. Look for the presence of moisture, corrosion pits and/or
white-colored material buildup. (Accumulation of white-colored material is an indication of corrosion.)
If there are no signs of corrosion, clean the connector with a cloth moistened with isopropyl alcohol.
If there are signs of corrosion, replace the connector as shown.
(k)
Examine backshell for signs of corrosion. Look for the presence of corrosion pits, and/or white-colored
material buildup. (Accumulation of white-colored material is an indication of corrosion, and/or loss of
olive-drab color.) If there are signs of corrosion on the backshell, estimate the area of corrosion. If
the cumulative area of corrosion is less than 10% of the total backshell surface area, clean the
backshell with a cloth moistened with isopropyl alcohol. If the cumulative area of corrosion is greater
than 10% of the total backshell surface area, replace the connector and backshell as shown.
(l)
TABLE 1 - Operational Tests
NotesOperational TestConnector
737-600/700/800/900 AMM 29-11-81 Engine Driven Pump Supply Shutoff Valve
Operational Test.
D00762
737-600/700/800/900 AMM 29-11-81 Engine Driven Pump Supply Shutoff Valve
Operational Test.
D00764
737-600/700/800/900 AMM 27-51-02 Trailing Edge Flap Bypass Valve Functional
Test.
D01014
737-600/700/800/900 AMM 27-51-00 Trailing Edge Flap System Operational Test.D01582
737-600/700/800/900 AMM 28-41-00 Fuel Quantity BITE Test Procedure.D4850J/P
737-600/700/800/900 AMM 27-81-00 Leading Edge Cruise Depressurization Test.D46020J/P
(a)737-600/700/800/900 AMM 29-33-21 Standby Hydraulic System Reservoir Low
Quantity Switch Installation Test.
737-600/700/800/900 AMM 27-09-31 Flight Controls Shutoff Valve Test.D46038J/P
737-600/700/800/900 AMM 27-09-61 Low Pressure Warning Switch Test.
737-600/700/800/900 AMM 27-61-12 Spoiler Shutoff Valve Test.
737-600/700/800/900 AMM 27-81-00 Leading Edge Uncommanded Motion Protection
Test.
737-600/700/800/900 AMM 29-22-31 Power Transfer Unit (PTU) Control Valve In-
stallation Test.
737-600/700/800/900 AMM 31-51-00 Takeoff Warning System Test.
737-600/700/800/900 AMM 32-31-71 Operational Test of the Transfer Valve.
FIGURE 2: CIC APPLICATION
(SHEET 6 OF 7)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 06, 2001
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BOEING SERVICE BULLETIN 737-24A1148
ALERTALERT

### Page 48

TABLE 1 - Operational Tests
NotesOperational TestConnector
(a) As an alternative to the 737 AMM 29-33-21/401, Paragraph 3, Standby Hydraulic System
Reservoir Low Quantity Switch Installation Test, Steps (1) through (12), the following steps may be
taken:
1. Remove plug D678 from the S49 Standby Hydraulic System Low Quantity Indication Switch.
2. Apply a ground to pin 2 of the D678 plug and make sure that the Standby Hydraulic System
Low Oil Quantity light on the Flight Control Panel P5-3 comes on.
3. Remove the ground from pin 2 of the D678 plug and reconnect the plug to the S49 Standby
Hydraulic System Low Quantity Indication Switch. Make sure that the Low Quantity light on
the Flight Control Panel P5-3 goes out.
This alternate test method would eliminate the requirement to drain and refill the Standby Hydraulic
System reservoir.
FIGURE 2: CIC APPLICATION
(SHEET 7 OF 7)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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BOEING SERVICE BULLETIN 737-24A1148
ALERTALERT

### Page 49 (OCR)

BOEING SERVICE BULLETIN 737-24A1148
ALERT  ALERT
D4850J/P
(POS 2)
M/W AL0675B
SEE (B
SEE
→ FWD
2564849
FIGURE 3: REPEAT INSPECTIONS - RESISTANCE MEASUREMENTS
(SHEET 1 OF 3)
Original Issue: December 06, 2001
Revision 2 September 14, 2020  PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  737-24A1148
Work - See page 1 for details.  49 of 61

### Page 50 (OCR)

BOEING SERVICE BULLETIN 737-24A1148
ALERT  ALERT
J-SIDE
RECEPTACLE
B
V66704
FIGURE 3: REPEAT INSPECTIONS - RESISTANCE MEASUREMENTS
(SHEET 2 OF 3)
Original Issue: December 06, 2001
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Work - See page 1 for details.  50 of 61

### Page 51

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
NOTESQTYPART NUMBERNAMETASKSTEP
(a) D4850J/P--ConnectorsMake Sure1
WARNING: THIS STEP IS RE-
LATED TO SCI/AWL REQUIRE-
MENTS.
--DC ResistanceMeasure2
(b) D4850J/P
WARNING: THIS STEP IS RE-
LATED TO SCI/AWL REQUIRE-
MENTS.
--DC ResistanceMeasure3
(c) D4850J/P
WARNING: THIS STEP IS RE-
LATED TO SCI/AWL REQUIRE-
MENTS.
--DC ResistanceMeasure4
(d) D4850J/P
Make sure the connectors are not loose or damaged. Make sure the backshells are not
loose or damaged. Make sure the strain relief is not loose. Make sure the terminal lugs of
the shield pigtails are tight.
(a)
For D4850J/P only, measure the DC resistance between the connector receptacle backshell
and the airplane structure or bracket disconnect.Maximum resistance 3.0 milliohms. If the
resistance measurements are greater than the specified milliohms, refer to SWPM 20-20-
00, SWPM 20-25-00, SWPM 20-60-09 and SWPM 20-61-11 for repair instructions.
(b)
For D4850J/P only, measure the DC resistance between the connector plug backshell and
the connector receptacle. Maximum resistance 3.0 milliohms. If the resistance measure-
ments are greater than the specified milliohms, refer to SWPM 20-20-00, SWPM 20-25-
00, SWPM 20-60-09 and SWPM 20-61-11 for repair instructions.
(c)
For D4850J/P only, measure the DC resistance between the connector plug backshell and
the connector plug. Maximum resistance 3.0 milliohms. If the resistance measurements
are greater than the specified milliohms, refer to SWPM 20-20-00, SWPM 20-25-00, SWPM
20-60-09 and SWPM 20-61-11 for repair instructions.
(d)
FIGURE 3: REPEAT INSPECTIONS - RESISTANCE MEASUREMENTS
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991 - BOEING
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BOEING SERVICE BULLETIN 737-24A1148
ALERTALERT

### Page 52 (OCR)

BOEING SERVICE BULLETIN 737-24A1148
ALERT  ALERT
SEE
D46038J/P
(POS 3)
M/W AL0675C
SEE
| D764
SEE  D4850J/P  MW V34
SEE  M/W AL0675B  (POS 2)  SEE
D762  • SEE
MW V33
SEE D
EWD  FWD
2564851
FIGURE 4: REPEAT INSPECTIONS - EXTERIOR CORROSION INSPECTION
(SHEET 1 OF 3)
Original Issue: December 06, 2001
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Work - See page 1 for details.  52 of 61

### Page 53 (OCR)

BOEING SERVICE BULLETIN 737-24A1148
ALERT  ALERT
D1014
M/W V52
SEE
D46020J/P
(POS 4)
M/W AL0720B
SEE O
FWD <
D1582
M/W V94
SEE D
2564853
FIGURE 4: REPEAT INSPECTIONS - EXTERIOR CORROSION INSPECTION
(SHEET 2 OF 3)
Original Issue: December 06, 2001
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Work - See page 1 for details.  53 of 61

### Page 54

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
NOTESQTYPART NUMBERNAMETASKSTEP
(a) D762, D4850J/P, D46038J/P,
D764, D1582, D1014, and
D46020J/P. It is not necessary to
remove receptacles D4850J,
D46020J and D46038J from the
disconnect bracket.
-
-
-
-
Connector
Backshell
Examine1
(b) D4850J/P It is not necessary
to remove receptacles D4850J,
D46020J and D46038J from the
disconnect bracket.
--BackshellExamine2
Examine the outer surface of the connectors and backshells for corrosion material de-
posits. If corrosion is visible, refer to SWPM 20-20-00, SWPM 20-25-00, SWPM 20-60-
09 and SWPM 20-61-11 for repair instructions.
(a)
Examine the backshell with shielded ground wires for signs of loss of the olive-drab
color conversion coating. If corrosion is visible, refer to SWPM 20-20-00, SWPM 20-25-
00, SWPM 20-60-09 and SWPM 20-61-11 for repair instructions.
(b)
FIGURE 4: REPEAT INSPECTIONS - EXTERIOR CORROSION INSPECTION
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 06, 2001
737-24A1148Revision 2 September 14, 2020
54 of 61
BOEING SERVICE BULLETIN 737-24A1148
ALERTALERT

### Page 55 (OCR)

BOEING SERVICE BULLETIN 737-24A1148
ALERT  ALERT
SEE C
10(11)
D46038J/P
6 12) (POS 3)
M/W ALO675C
SEE
SEE  D4850J/P  0017 V34
SEE  12) (POS 2)  M/W AL0675B  SEE
0O107 V33  SEE OO
SEE  (D)
→ FWD  → FWD
2564846
FIGURE 5: REPEAT INSPECTIONS - INTERIOR CORROSION OR FLUID CONTAMINATION INSPECTION
(SHEET 1 OF 7)
Original Issue: December 06, 2001
Revision 2 September 14, 2020  PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  737-24A1148
Work - See page 1 for details.  55 of 61

### Page 56 (OCR)

BOEING SERVICE BULLETIN 737-24A1148
ALERT  ALERT
\ D1014
12  / M/W V52
SEE
D46020J/P
6 12) (POS 4)
M/W AL0720B
SEE D
FWD
6 12)  M/W V94  D1582
SEE
2564847
FIGURE 5: REPEAT INSPECTIONS - INTERIOR CORROSION OR FLUID CONTAMINATION INSPECTION
(SHEET 2 OF 7)
Original Issue: December 06, 2001
Revision 2 September 14, 2020  Export Controlled ECCN: 9E991 - BOEING  737-24A1148
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  56 of 61

### Page 57 (OCR)

BOEING SERVICE BULLETIN 737-24A1148
ALERT  ALERT
TYPICAL
J-SIDE RECEPTACLE
TYPICAL  W03921
FIGURE 5: REPEAT INSPECTIONS - INTERIOR CORROSION OR FLUID CONTAMINATION INSPECTION
(SHEET 3 OF 7)
Original Issue: December 06, 2001
Revision 2 September 14, 2020  Export Controlled ECCN: 9E991 - BOEING  737-24A1148
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  57 of 61

### Page 58

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
NOTESQTYPART NUMBERNAMETASKSTEP
Disconnect the D762, D764,
D1014 and D1582 connectors
from the LRUs. Disconnect the
D4850P, D46020P and D46038P
connectors from the J side con-
nectors on the disconnect brack-
et. It is not necessary to remove
receptacles D4850J, D46020J
and D46038J from the discon-
nect bracket.
7-ConnectorsDisconnect1
(a) (b)--LRU Connector and
Contacts
Examine / Clean
or Replace
2
-
(c)-D-5026NS
(D5026NS) or ZC-
026
Internal CICApply3
(f)--ConnectorsExamine / Clean
or Replace
4
(d) (e)--Contacts
(g)--Backshells
(h)7D-5026NS
(D5026NS) or ZC-
026
Internal CICApply5
Mate the D762, D764, D1014
and D1582 connectors to the
LRUs. Connect the D4850P,
D46020P and D46038P connec-
tors to the J side connectors on
the disconnect bracket.
7-ConnectorsMate6
WARNING: THIS STEP IS RE-
LATED TO SCI/AWL REQUIRE-
MENTS.
--DC ResistanceMeasure7
(i) D4850P
WARNING: THIS STEP IS RE-
LATED TO SCI/AWL REQUIRE-
MENTS.
--DC ResistanceMeasure8
(j) D4850P
WARNING: THIS STEP IS RE-
LATED TO SCI/AWL REQUIRE-
MENTS.
--DC ResistanceMeasure9
(k) D4850P
FIGURE 5: REPEAT INSPECTIONS - INTERIOR CORROSION OR FLUID CONTAMINATION INSPECTION
(SHEET 4 OF 7)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 06, 2001
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BOEING SERVICE BULLETIN 737-24A1148
ALERTALERT

### Page 59

Restore the electrical power to
the airplane. Refer to 737-
600/700/800/900 AMM 24-22-
00/201.
--Electrical PowerRestore10
Do the operational tests of the
affected systems as shown in
Table I of Figure 1.
--Operational TestDo11
(l)-AV25External CICApply12
Examine the LRU connectors for signs of corrosion. Look for the presence of moisture, corrosion pits,
and / or white-colored material buildup. (Accumulation of white-colored material is an indication of
corrosion.) Examine the LRU connector contacts for signs of corrosion. Look for exposure of the copper
base metal or blue-green deposits that indicate the presence of copper corrosion. Look for a black or
reddish discoloration of the gold-plated contacts.
(a)
If there are no signs of corrosion, clean the LRU connector and contacts with a cotton swab moistened
with isopropyl alcohol. If there are signs of corrosion, replace the LRU with a new LRU of the same
part number. Replace the LRU as shown in the applicable AMM.
(b)
Apply the D-5026NS (D5026NS) CIC to the pin contacts of the LRU connector receptacle. Spray with
a 2 - 4 second burst 4 - 8 inches away from the connector. The operator may use the ZC-026 instead
of the D-5026NS (D5026NS). Apply the ZC-026 with a pump-action sprayer.
(c)
Examine the connector contacts for signs of corrosion. Look for exposure of the copper base metal or
blue-green deposits that indicate the presence of copper corrosion.
(d)
If there are no signs of corrosion, clean the connector contacts with a cotton swab moistened with
isopropyl alcohol. If there are signs of corrosion, replace all contacts in the connector with new contacts
of the same part number. Replace the contact as shown in the applicable BBSWPM.
(e)
Examine the connector for signs of corrosion. Look for the presence of moisture, corrosion pits and/or
white-colored material buildup. (Accumulation of white-colored material is an indication of corrosion.)
If there are no signs of corrosion, clean the connector with a cloth moistened with isopropyl alcohol. If
there are signs of corrosion, replace the connector as shown.
(f)
Examine the backshell for signs of corrosion. Look for the presence of corrosion pits, and/or white-
colored material buildup. (Accumulation of white-colored material is an indication of corrosion, and/or
loss of olive-drab color.) If there are signs of corrosion on the backshell, estimate the area of corrosion.
If the cumulative area of corrosion is less than 10% of the total backshell surface area, clean the
backshell with a cloth moistened with isopropyl alcohol. If the cumulative area of corrosion is greater
than 10% of the total backshell surface area, replace the connector and backshell as shown.
(g)
Apply the D-5026NS (D5026NS) CIC to the connectors. Spray with a 2 - 4 second burst 4 - 8 inches
away from the connector. The operator may use the ZC-026 instead of the D-5026NS (D5026NS).
Apply the ZC-026 with a pump-action sprayer.
(h)
For D4850J/P only, measure the DC resistance between the connector receptacle backshell and the
airplane structure or bracket disconnect.Maximum resistance 3.0 milliohms. If the resistance measure-
ments are greater than the specified milliohms, refer to SWPM 20-20-00, SWPM 20-25-00, SWPM 20-
60-09 and SWPM 20-61-11 for repair instructions.
(i)
FIGURE 5: REPEAT INSPECTIONS - INTERIOR CORROSION OR FLUID CONTAMINATION INSPECTION
(SHEET 5 OF 7)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 06, 2001
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BOEING SERVICE BULLETIN 737-24A1148
ALERTALERT

### Page 60

For D4850J/P only, measure the DC resistance between the connector plug backshell and the connector
receptacle. Maximum resistance 3.0 milliohms. If the resistance measurements are greater than the
specified milliohms, refer to SWPM 20-20-00, SWPM 20-25-00, SWPM 20-60-09 and SWPM 20-61-
11 for repair instructions.
(j)
For D4850J/P only, measure the DC resistance between the connector plug backshell and the connector
plug. Maximum resistance 3.0 milliohms. If the resistance measurements are greater than the specified
milliohms, refer to SWPM 20-20-00, SWPM 20-25-00, SWPM 20-60-09 and SWPM 20-61-11 for repair
instructions.
(k)
Apply the external CIC to the mated connector assembly, include the grommets and backshells, after
the operational tests are done. Spray the connector assembly completely until the AV25 drips from it.
Do not remove excess AV25.
(l)
TABLE 1 - Operational Tests
NotesOperational TestConnector
737-600/700/800/900 AMM 29-11-81 Engine Driven Pump Supply Shutoff Valve
Operational Test.
D00762
737-600/700/800/900 AMM 29-11-81 Engine Driven Pump Supply Shutoff Valve
Operational Test.
D00764
737-600/700/800/900 AMM 27-51-02 Trailing Edge Flap System Operational Test.D01014
737-600/700/800/900 AMM 27-51-00 Trailing Edge Flap System Operational Test.D01582
737-600/700/800/900 AMM 28-41-00 Fuel Quantity BITE Test Procedure.D4850J/P
737-600/700/800/900 AMM 27-81-00 Leading Edge Cruise Depressurization Test.D46020J/P
(a)737-600/700/800/900 AMM 29-33-21 Standby Hydraulic System Reservoir Low
Quantity Switch Installation Test.
737-600/700/800/900 AMM 27-09-31 Flight Controls Shutoff Valve Test.D46038J/P
737-600/700/800/900 AMM 27-09-61 Low Pressure Warning Switch Test.
737-600/700/800/900 AMM 27-61-12 Spoiler Shutoff Valve Test.
737-600/700/800/900 AMM 27-81-00 Leading Edge Uncommanded Motion Protection
Test.
737-600/700/800/900 AMM 29-22-31 Power Transfer Unit (PTU) Control Valve In-
stallation Test.
737-600/700/800/900 AMM 31-51-00 Takeoff Warning System Test.
737-600/700/800/900 AMM 32-31-71 Operational Test of the Transfer Valve.
FIGURE 5: REPEAT INSPECTIONS - INTERIOR CORROSION OR FLUID CONTAMINATION INSPECTION
(SHEET 6 OF 7)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 06, 2001
737-24A1148Revision 2 September 14, 2020
60 of 61
BOEING SERVICE BULLETIN 737-24A1148
ALERTALERT

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