# Boeing Alert Service Bulletin 737-30A1064: Revision 2

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2021-0190; AD 2021-07-02 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Alert Service Bulletin 737-30A1064](https://openairdocs.org/service-documents/boeing/737-30a1064.md)
- Title as filed: SB 737-30A1064 R02
- Pages: 84
- PDF: https://openairdocs.org/files/sha256/8b/3d/8b3dcbff995f9e73f2029050e2d9a7bcc85af613dccd8f8ffb6f74321b20e8d2
- Page: https://openairdocs.org/service-documents/boeing/737-30a1064/file/8b3dcbff995f

## Text

Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-30A1064
Original Issue: May 04, 2017
Revision 2: June 26, 2020
ATA System: 3031
SUBJECT: ICE AND RAIN PROTECTION - Pitot Static Tubes, Temperature Probe, and Alpha
Vane Anti-Icing System - Change P5 and P18-3 Panels to Activate Automated Probe
Heat System
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 © 2017 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Unpublished Work.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: May 04, 2017
737-30A1064Revision 2: June 26, 2020
1 of 84
5.0

### Page 2

Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
2 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT
BLANK PAGE

### Page 3

Table of Contents
Revision Transmittal Sheet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
2. Spares Aff ected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20
B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20
C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20
D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24
G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24
H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
2. Data Supplied with this Ser vice Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
3. Installation Drawings Used in the Prepar ation of this Ser vice Bulletin: . . . . . . . . . . . 27
K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
L. Interchangeability and Inter mixability of P arts . . . . . . . . . . . . . . . . . . . . . . . . . . . 28
M. Software Accomplishment Summar y . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28
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 Mater ials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 29
3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29
4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29
D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30
E. Special Tooling - Pr ice and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30
F. Special Tooling Necessary to do this Ser vice Bulletin . . . . . . . . . . . . . . . . . . . . . . . 30
3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31
A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31
B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32
FIGURE 1: FLIGHT COMPARTMENT - P5-9 WINDOW AND PITOT HEAT MODULE - REPLACEMENT
[Group 1, 6] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 71
FIGURE 2: FLIGHT COMPARTMENT - P5-9 WINDOW AND PITOT HEAT MODULE - REPLACEMENT
[Group 2-4] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 73
FIGURE 3: FLIGHT COMPARTMENT - P18-3 CIRCUIT BREAKER PANEL - CHANGE [Group 1, 6] . 75
FIGURE 4: FLIGHT COMPARTMENT - P18-3 CIRCUIT BREAKER PANEL - CHANGE [Group 2] . . . 77
FIGURE 5: FLIGHT COMPARTMENT - P18-3 CIRCUIT BREAKER PANEL - CHANGE [Group 3] . . . 79
FIGURE 6: FLIGHT COMPARTMENT - P18-3 CIRCUIT BREAKER PANEL - CHANGE [Group 4] . . . 81
FIGURE 7: FLIGHT COMPARTMENT - P18-3 CIRCUIT BREAKER PANEL - CHANGE [Group 1-4, 6] . 83
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
3 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 4

Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
4 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT
BLANK PAGE

### Page 5

Commercial 
Airplanes
737
Service Bulletin
ALERT
Revision Transmittal SheetNumber: 737-30A1064Original Issue: May 04, 2017
Revision 2: June 26, 2020
ATA System: 3031
SUBJECT: ICE AND RAIN PROTECTION - Pitot Static Tubes, Temperature Probe, and Alpha
Vane Anti-Icing System - Change P5 and P18-3 Panels to Activate Automated Probe
Heat System
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2019-09-01 is related to this service bulletin.
Airplanes PK625-PK627 were added to new Group 6 of this service bulletin effectivity.
Effects of this revision on airplanes on which Revision 1 were previously done:
None.
REASON FOR REVISION
This revision is sent to add airplanes inadvertently omitted to the effectivity of this service bulletin, PK625-PK627.
These airplanes are in the effectivity of the concurrent requirement service bulletins.
The data given in Information Notice (IN) 737-30A1064 IN 01 is included in this revision.
The data given in Alternative Method of Compliance Notice (AMOC) 737-30A1064 AMOC 01 is included in this
revision.
These sections were changed:
1. Summary, ACTION, added Group 6 information.
2. Summary, COMPLIANCE, added FAA AD and changed to reference statements.
3. Paragraph 1.A.1., Airplanes, added airplanes to Group 6.
4. Paragraph 1.B., Concurrent Requirements, added Group 6 information.
5. Paragraph 1.C., Reason:
a. Added revision statement.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
5 of 84

### Page 6

b. Added Information Notice (IN) statement.
c. Added Alternative Method of Compliance (AMOC) statement.
6. Paragraph 1.D., Description:
a. Added Group 6 information.
b. Added effects of this Revision.
c. Added Group 6 Maintenance Zones information.
7. Paragraph 1.E., Compliance:
a. Added FAA AD and compliance statements.
b. Added Group 6 compliance table.
8. Paragraph 1.F. Approval, added AMOC statement.
9. Paragraph 1.G. Manpower, added Group 6 manpower.
10. Paragraph 1.J.1., Existing Data:
a. Added FAA AD reference.
b. Changed Aircraft Maintenance Manual (AMM) reference.
11. Paragraph 1.K., Publications Affected, added and removed references.
12. Paragraph 2.C.2, Parts and Materials Supplied by the Operator, added Group 6 information.
13. Paragraph 3.B., Work Instructions:
a. Added Group 6 work instructions.
b. Added notes for TAT test feature.
c. Added FIGURE 7 instructions.
14. FIGURE 1:
a. Added Group 6 applicability.
b. Step table, footnote (a), changed Aircraft Maintenance Manual (AMM) reference.
15. FIGURE 3, added Group 6 applicability.
16. Added FIGURE 7.
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.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
6 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 7

Pages with no vertical lines have no changes.
REVISION HISTORY
May 04, 2017Original Issue:
October 18, 2017Revision 1:
June 26, 2020Revision 2:
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
7 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 8

Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
8 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT
BLANK PAGE

### Page 9

Commercial 
Airplanes
737
Service Bulletin
ALERT
SummaryNumber: 737-30A1064Original Issue: May 04, 2017
Revision 2: June 26, 2020
ATA System: 3031
SUBJECT: ICE AND RAIN PROTECTION - Pitot Static Tubes, Temperature Probe, and Alpha
Vane Anti-Icing System - Change P5 and P18-3 Panels to Activate Automated Probe
Heat System
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
Refer to Paragraph 1.B., Concurrent Requirements.
BACKGROUND
Boeing has received reports from operators that the pitot heat switch is not always set to ON. The work given
in this service bulletin changes the anti-icing system to automatically supply power to heat the air data sensors.
The anti-icing system will come on (AUTO) automatically after engine start if the crew does not activate the
system. If this service bulletin is not done, the air data sensors could be unheated, which could let ice form on
the sensors, and cause erroneous air data. Unreliable air data can lead to loss of crew situational awareness
which could cause failure to maintain safe flight and landing of the airplane.
Boeing Fleet Team Digest (FTD) 737 FTD 30-8001 is related to this service bulletin.
Boeing Service Related Problem (SRP) 737-SRP-30-0050 (previously 737-SRP-30-0032) is related to this
service bulletin.
As a part of a service bulletin remote certification program, this change was completed on airplane PR009 by
Service Bulletin 737-30A1064 RC 1 before the Original Issue of this service bulletin. The change completed on
airplane PR009 by Service Bulletin 737-30A1064 RC 1 is equivalent to the Original Issue of this service bulletin.
Airplane PR009 has the configuration of a Group 3 airplane.
This table is provided to operators for planning purposes only. Refer to the applicable sections for more
information.
ReferenceAffectedPlanning Data
Paragraph 1.A.2., Spares AffectedNoSpares Affected
Paragraph 1.E., ComplianceYesAD Related
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
9 of 84

### Page 10

ReferenceAffectedPlanning Data
Paragraph 1.H., Weight and Balance ChangesNoWeight and Balance Change
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
Paragraph 1.K., Publications AffectedYesPublications Affected
Paragraph 1.K., Publications AffectedYesAirplane Flight Operations Affected (Flight Crew
Operations Manual and/or FAA Approved Air-
plane Flight Manual)
Paragraph 2.C.1., Kits/PartsNoKits/Parts Required
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
YesOperator Supplied Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
ACTION (PRR 35005-295RS)
Group 1, 6:
1. Access the flight compartment.
2. Replace the P5-9 Window and Pitot Heat Module.
3. Remove INOP markers and collars on the P18-3 circuit breaker panel.
4. Do Pitot Static and Temperature Probe Anti-Icing System Test.
5. Do Control Cabin Window Anti-Icing System Test.
6. Do repetitive Pitot Static and Temperature Probe Anti-Icing System Test at the times specified in
Paragraph 1.E., Compliance.
Group 2-4:
1. Access the flight compartment.
2. Replace the P5-9 Window and Pitot Heat Module.
3. Remove INOP markers and collars on the P18-3 circuit breaker panel.
4. Do Pitot-Static Tubes, Temperature Probe and Alpha Vane Anti-Icing System Test.
5. Do Operational Test - Control Cabin Window Anti-Icing System.
6. Do repetitive Pitot-Static Tubes, Temperature Probe and Alpha Vane Anti-Icing System Test at the
times specified in Paragraph 1.E., Compliance.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
10 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 11

Group 5:
Boeing endorses the Federal Aviation Administration (FAA) rules related to Limit of Validity (LOV) and recommends
immediate and permanent removal from service of any airplane upon reaching the LOV, whether or not it is
operated under FAA jurisdiction. As such, Boeing no longer provides maintenance instructions for airplanes that
have accumulated flight cycles beyond the LOV. Airplanes in Group 5 (line numbers 1-291) have accumulated
flight cycles beyond the LOV of the maintenance program. Title 14, Code of Federal Regulations (14 CFR)
121.1115 and 129.115 prohibit operation of an airplane beyond its LOV.
Accomplishment of this service bulletin changes the flight deck and/or operations of the airplane. Refer to
Paragraph 1.K., Publications Affected, for affected publications.
EFFECTIVITY
737-100/-200/-200C/-300/-400/-500 Airplane(s). Refer to Paragraph 1.A., Effectivity for the list of affected
airplane(s).
COMPLIANCE
Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2019-09-01 is related to this service bulletin.
The effective date of AD 2019-09-01 is June 26, 2019.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
MANPOWER
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
Operator Supplied Parts/Materials.
Refer to Paragraph 2.A., Material - Price and Availability
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
11 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 12

Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
12 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 13

Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-30A1064
Original Issue: May 04, 2017
Revision 2: June 26, 2020
ATA System: 3031
SUBJECT: ICE AND RAIN PROTECTION - Pitot Static Tubes, Temperature Probe, and Alpha
Vane Anti-Icing System - Change P5 and P18-3 Panels to Activate Automated Probe
Heat System
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 737-100, 737-200, 737-200C, 737-300, 737-400, 737-500 Airplane(s),
line number(s) 1-295, 298-299, 302-304, 307-311, 314, 319-321, 326, 334-340, 343-345, 348-351,
354-360, 362-363, 365-366, 368, 371-372, 378, 381, 384, 387, 389, 397, 399-402, 404-406, 408,
411, 414-415, 417-418, 421-422, 424, 427, 431, 433-438, 440-442, 445, 447, 453-455, 458-460,
462, 466-469, 472-475, 477, 479-483, 485-490, 494, 501-503, 505-507, 510-515, 517-518, 520-523,
525, 529-533, 535-537, 539-541, 546, 548, 551, 554-555, 557-558, 560, 562-565, 567-570,
572-577, 579-581, 583-590, 592, 594-603, 605, 607-608, 610-611, 613, 615-616, 618-623, 626-627,
629, 632-633, 635-636, 639-646, 648-651, 653-661, 663-666, 668-670, 672-674, 677, 679-683,
686-696, 698-699, 701-708, 710, 712-718, 720-721, 723-724, 726-727, 729-731, 734-737, 739-742,
744-754, 756-766, 768-774, 776-777, 781, 783-786, 788-801, 803, 805-816, 820-823, 825, 827-831,
833-840, 843-854, 856-857, 859-865, 867-868, 870-874, 876-881, 883, 886-887, 889-892, 896-897,
899-903, 905, 907, 909-912, 914-919, 921, 923-924, 927-930, 932-956, 958-961, 963-972, 975-978,
980-987, 989, 992-994, 996-998, 1000-1013, 1015-1024, 1026-1047, 1049-1051, 1053-1062,
1065-1068, 1070-1071, 1073-1086, 1089-1091, 1093, 1095-1119, 1122-1130, 1132, 1134-1142,
1146-1148, 1151-1156, 1158-1159, 1161-1166, 1168-1171, 1174-1178, 1180-1181, 1186-1189,
1191-1195, 1197-1209, 1211-1227, 1229, 1231-1237, 1239-1246, 1248-1251, 1255-1265,
1267-1274, 1277-1278, 1280-1282, 1284-1294, 1297, 1299-1302, 1304-1317, 1320-1327,
1329-1332, 1334-1337, 1339, 1341-1346, 1348-1350, 1352-1354, 1356-1376, 1378-1379,
1381-1395, 1397-1403, 1405-1411, 1413-1415, 1417-1428, 1430, 1432-1436, 1438-1441,
1443-1445, 1447-1449, 1454-1455, 1457-1463, 1465-1471, 1473-1477, 1479, 1481, 1484-1487,
1489-1501, 1504-1517, 1519-1521, 1523-1526, 1528-1529, 1531-1542, 1545-1550, 1552-1557,
1559, 1562, 1564-1568, 1570-1574, 1576-1578, 1581-1583, 1585-1591, 1593-1596, 1598-1602,
1604-1639, 1641-1642, 1644-1648, 1650-1654, 1656-1664, 1666-1668, 1671-1677, 1679-1680,
1682-1705, 1707-1718, 1720-1738, 1740-1760, 1762, 1764, 1766-1770, 1772, 1774-1794,
1796-1823, 1825-1827, 1829-1832, 1834-1837, 1839-1864, 1866-1877, 1879-1894, 1896-1922,
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
13 of 84

### Page 14

1924-1970, 1972-2003, 2005-2051, 2053-2086, 2088-2111, 2114-2134, 2136-2145, 2147-2199,
2201-2289, 2291-2310, 2312-2352, 2354-2375, 2377-2382, 2384-2392, 2394-2399, 2401-2576,
2578-2605, 2607-2731, 2734-2850, 2852-2932, 2934-2981, 2983-3132 in 6 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 Service Bulletin Index D6-19567 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
This service bulletin is for the airplane(s) shown below. Refer to PRR 35005-295RS for data about
this change.
Airplane PR009 was changed in accordance with Boeing Service Bulletin 737-30A1064 RC 1 and
Installation Deviation Record (IDR) Log number 737-30A1064-PR009.
DESCRIPTIONCONFIGURATIONGROUP
737-200/200C Airplanes-1
737-300/500 Airplanes with a different P18-3 circuit breaker panel
configuration
-2
737-300/400/500 Airplanes with a different P18-3 circuit breaker
panel configuration
-3
737-400 Airplanes with a different P18-3 circuit breaker panel
configuration
-4
737-100/100/200C Airplanes, Line Numbers 1-291-5
737-200 Airplanes-6
Airplane Models:
737-100, 737-200, 737-200C, 737-300, 737-400, 737-500
GroupVariable Number
5PA001 - PA022
5PA099
5PA231 - PA232
5PC001 - PC005
5PG001 - PG075
5PG199
5PG201 - PG230
5PG251 - PG255
5PG271 - PG279
GroupVariable Number
5PG301 - PG314
5PG331 - PG332
5PG351 - PG356
5PG375
5PG401 - PG403
5PG431 - PG442
5PG471 - PG475
5PG501 - PG505
5PG571 - PG583
GroupVariable Number
1PG584 - PG585
5PG621 - PG630
5PG651 - PG652
5PG701 - PG705
5PH701 - PH715
5PH731 - PH732
5PH741 - PH742
5PJ001 - PJ002
1PJ003 - PJ009
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
14 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 15

GroupVariable Number
5PJ031 - PJ032
5PJ071 - PJ072
5PJ101 - PJ104
1PJ107
1PJ110 - PJ112
1PJ114 - PJ115
1PJ117
1PJ202
1PJ205 - PJ211
1PJ213 - PJ219
3PJ301 - PJ302
3PJ551 - PJ561
3PJ601 - PJ615
3PJ811
3PJ816 - PJ817
1PK026
1PK029
1PK041
1PK044 - PK048
1PK050 - PK053
1PK068 - PK070
1PK094 - PK095
1PK102 - PK103
1PK111 - PK112
1PK114
1PK118 - PK120
1PK143 - PK145
1PK201 - PK203
1PK213
1PK215 - PK222
1PK231 - PK233
1PK235
1PK237 - PK240
GroupVariable Number
1PK253 - PK254
1PK257 - PK258
1PK274
1PK281 - PK284
1PK286
1PK303 - PK304
1PK307 - PK310
1PK312 - PK318
1PK351 - PK353
1PK357 - PK361
1PK391
1PK431
1PK451
1PK468
1PK495
1PK501
1PK503
1PK511
1PK514 - PK515
1PK519
1PK524 - PK528
1PK546
1PK548 - PK549
1PK551 - PK552
1PK557 - PK558
1PK560 - PK565
1PK581
1PK593 - PK596
1PK598 - PK599
1PK601 - PK602
1PK604 - PK606
1PK608 - PK617
1PK622 - PK624
GroupVariable Number
6PK625 - PK627
1PK629
1PK632 - PK635
1PK641 - PK642
1PK661
1PK664 - PK666
1PK671
1PK673
1PK675
1PK677
1PK681
1PK692
1PK696
1PK711 - PK716
1PK731 - PK732
1PK734 - PK745
1PK747 - PK755
1PK757 - PK761
1PK763 - PK765
1PK771 - PK773
1PK775
1PK777
1PK779
1PK801 - PK804
1PK819
1PK821 - PK827
1PK830
1PK861 - PK863
1PK871 - PK872
1PK874
1PK881
1PK884
1PK901 - PK938
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
15 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 16

GroupVariable Number
1PK971 - PK974
1PL001 - PL005
1PL007 - PL023
1PL025 - PL026
1PL028
1PL061
1PL081
1PL102 - PL113
1PL151
1PL171 - PL172
1PL201 - PL203
1PL221
1PL401 - PL417
1PL441
1PL451
1PL454 - PL456
1PL471
1PL501 - PL506
1PL551
1PL553 - PL556
1PL558
1PL560 - PL562
1PL581
1PL601 - PL603
1PL611
1PL621 - PL626
1PL631 - PL632
5PL711 - PL712
5PL716
1PL722 - PL725
1PL727 - PL733
1PL735 - PL737
1PL740 - PL743
GroupVariable Number
1PL745
1PL763
1PL768
1PL770
1PL793
5PL801 - PL803
1PM001 - PM006
1PM016 - PM017
1PM021 - PM022
1PM051 - PM052
1PM054
1PM056 - PM062
1PM064 - PM066
1PM101 - PM119
1PM141 - PM142
1PM181
1PM251 - PM254
1PM281 - PM283
3PM381 - PM385
3PM387 - PM399
3PM401 - PM402
3PM404 - PM405
3PM407 - PM417
3PM541 - PM549
3PM551 - PM557
3PM559 - PM564
1PN001
1PN021
1PN023
1PN025 - PN028
1PN030
1PN032 - PN033
1PN036 - PN037
GroupVariable Number
1PN039 - PN043
1PN082 - PN083
1PN085 - PN086
1PN101 - PN117
1PN132 - PN133
1PN135 - PN163
1PN401 - PN405
1PN407 - PN412
1PN414 - PN420
1PN431 - PN433
1PN451 - PN455
1PN472
1PN474
1PN481
1PN491 - PN493
1PN501
1PN512
1PN521
2PP001 - PP010
2PP013 - PP014
2PP017 - PP030
2PP034
2PP036
2PP039 - PP041
2PP043
2PP047 - PP054
2PP101
2PP104 - PP108
2PP110
2PP113 - PP119
2PP122 - PP160
2PP163 - PP164
2PP166 - PP167
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
16 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 17

GroupVariable Number
2PP169
2PP181 - PP199
3PP202 - PP203
2PP221
2PP232 - PP234
2PP237 - PP243
2PP281 - PP282
2PP284 - PP286
2PP301 - PP305
3PP351 - PP353
3PP376 - PP382
3PP384
2PP391 - PP393
2PP401 - PP415
2PP417
2PP419 - PP423
2PP425
2PP427 - PP430
2PP432 - PP436
2PP440
2PP471 - PP474
3PP501 - PP520
2PP521 - PP522
2PP631
2PP634
2PP651 - PP652
2PP671 - PP673
2PP676 - PP677
2PP679
2PP681 - PP688
2PP690 - PP694
2PP698
2PP702 - PP703
GroupVariable Number
2PP711 - PP716
2PP719 - PP723
2PP725
2PP727 - PP729
2PP731
2PP771 - PP779
2PP801 - PP804
3PP805 - PP808
2PP821 - PP827
3PP831 - PP835
3PP837 - PP841
3PP843
3PP845 - PP848
3PP852
3PP862
3PP865 - PP870
3PP872
3PP874 - PP877
3PP892 - PP899
3PP901 - PP904
3PP906 - PP911
3PP913 - PP915
3PP917 - PP919
3PP921
3PP923
3PP925 - PP936
3PP946 - PP948
3PP951 - PP952
3PP962 - PP967
3PP983 - PP991
3PQ001 - PQ012
3PQ014 - PQ015
3PQ026 - PQ028
GroupVariable Number
3PQ030 - PQ041
3PQ051 - PQ092
3PQ101 - PQ113
3PQ115 - PQ131
3PQ133 - PQ151
3PQ153 - PQ184
3PQ186 - PQ199
3PQ201 - PQ202
3PQ221 - PQ226
3PQ228
3PQ230 - PQ231
3PQ233 - PQ237
3PQ241 - PQ243
3PQ251 - PQ267
3PQ281
3PQ284 - PQ293
3PQ295 - PQ299
3PQ301 - PQ307
3PQ331 - PQ332
3PQ341 - PQ348
3PQ361 - PQ373
3PQ391 - PQ395
3PQ401 - PQ412
3PQ414 - PQ418
3PQ421
3PQ431 - PQ438
3PQ447 - PQ448
3PQ451
3PQ454
3PQ471 - PQ475
3PQ479 - PQ481
3PQ487
3PQ491 - PQ493
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
17 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 18

GroupVariable Number
3PQ771 - PQ772
3PQ791 - PQ793
3PQ801 - PQ805
3PQ931 - PQ935
3PQ951
3PQ971 - PQ972
3PQ974 - PQ997
3PR001 - PR017
3PR021 - PR026
3PR028 - PR034
3PR041 - PR045
3PR061 - PR072
3PR077 - PR082
3PR091 - PR092
3PR096
3PR101
3PR121 - PR122
3PR131 - PR132
3PR141 - PR143
3PR161 - PR172
3PR181
3PS601 - PS618
3PS620 - PS631
3PS636 - PS638
3PS641 - PS644
3PS652 - PS657
2PS666 - PS668
3PS691 - PS692
3PS701 - PS706
2PS751 - PS799
3PS811
3PS836 - PS837
3PS841 - PS846
GroupVariable Number
3PS851 - PS852
3PS856
3PS861 - PS863
3PS866 - PS868
3PS871 - PS874
3PS896 - PS897
2PS901 - PS909
3PS910 - PS941
3PS956 - PS957
3PS961 - PS963
3PS971 - PS978
3PT002 - PT015
3PT021 - PT025
3PT027 - PT031
3PT041 - PT064
3PT101 - PT105
3PT121
3PT123 - PT138
3PT146 - PT148
2PT161 - PT170
3PT181 - PT188
2PT211 - PT220
3PT295
2PT301 - PT309
3PT331 - PT360
3PT381 - PT395
3PT397 - PT399
3PT401 - PT438
3PT501 - PT517
3PT561
3PT563 - PT565
2PT581 - PT586
2PT611 - PT621
GroupVariable Number
3PT641 - PT644
3PT651 - PT656
2PT671 - PT672
3PT681 - PT685
2PT701 - PT703
2PT716 - PT717
3PT721 - PT725
3PT801 - PT834
3PT851 - PT854
3PT871 - PT886
3PT901 - PT905
3PT907 - PT930
3PT971 - PT973
3PT981 - PT985
3PT996
2PU001 - PU025
3PU301
3PU311 - PU313
3PV001 - PV003
3PV006 - PV010
3PV012 - PV023
3PV025 - PV055
3PV201 - PV209
3PV226 - PV229
3PV232 - PV237
3PV271
3PV281 - PV287
3PV296
3PV301 - PV302
3PV351
3PV356 - PV357
3PW001 - PW002
3PW004 - PW007
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
18 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 19

GroupVariable Number
3PW009 - PW011
3PW013 - PW026
3PW028 - PW031
3PW033 - PW054
3PW061
3PW063
3PW065 - PW068
3PW072
3PW086 - PW088
3PW091
3PW093 - PW094
3PW101 - PW102
3PW106
3PW111 - PW120
3PW156 - PW157
3PW161 - PW162
3PW164 - PW171
3PW201 - PW252
3PW261 - PW268
4PW271 - PW276
3PW278
3PW281 - PW291
3PW293
3PW296
3PW301 - PW327
3PW401 - PW408
3PW411 - PW418
3PW421 - PW424
3PW431 - PW435
3PW441 - PW450
3PW461 - PW467
3PW501 - PW504
GroupVariable Number
3PW511 - PW522
3PW524 - PW550
3PW556 - PW557
3PW561 - PW564
3PW571 - PW576
3PW591 - PW596
3PW611 - PW619
3PW621 - PW622
3PW631 - PW636
3PW661 - PW662
3PW681 - PW683
3PW701 - PW702
3PW711 - PW717
3PW741 - PW742
3PW761
3PW771
3PW831
3PW851 - PW856
5PX071
5PX701
5PY001 - PY008
5PY021
1PY022
5PY031
1PY036 - PY037
1PY046 - PY047
1PY051
1PY053
1PY056 - PY057
1PY101 - PY103
1PY113
1PY131
GroupVariable Number
1PY133 - PY135
1PY141 - PY142
1PY151 - PY154
1PY162
1PY166
1PY191
1PY201
1PY241 - PY244
1PY270
1PY272
1PY274 - PY275
1PY281
5PY301 - PY304
5PY321 - PY323
5PY341 - PY346
5PY361 - PY362
5PY381
1PY409 - PY411
1PY421 - PY422
1PY441
1PY451
1PY461
1PY463
1PY592 - PY595
1PY611 - PY612
1PY621
1PY631
1PY671 - PY672
1PY721
1PY741
--
--
2. Spares Affected
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
19 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 20

None.
B. Concurrent Requirements
Airplane PR009 was changed in accordance with Boeing Service Bulletin 737-30A1064 RC 1 and IDR
Log number 737-30A1064-PR009.
The service bulletin(s) listed below must be done before or at the same time as this service bulletin:
Group 1-4, 6:
DescriptionService BulletinCompany
ICE AND RAIN PROTECTION - Pitot Static Tubes, Temperature
Probe, and Alpha Vane Anti-Icing System - J18 Junction Box In-
stallation.
737-30-1067 Revision 1Boeing
ICE AND RAIN PROTECTION - Pitot Static Tubes, Temperature
Probe, and Alpha Vane Anti-Icing System - Air Data Probe Heat
Automation Wire Provisions Installation.
737-30-1068 Revision 1Boeing
Group 5:
Boeing endorses the Federal Aviation Administration (FAA) rules related to Limit of Validity (LOV) and
recommends immediate and permanent removal from service of any airplane upon reaching the LOV,
whether or not it is operated under FAA jurisdiction. As such, Boeing no longer provides maintenance
instructions for airplanes that have accumulated flight cycles beyond the LOV. Airplanes in Group 5
(line numbers 1-291) have accumulated flight cycles beyond the LOV of the maintenance program.
Title 14, Code of Federal Regulations (14 CFR) 121.1115 and 129.115 prohibit operation of an airplane
beyond its LOV.
C. Reason
Boeing has received reports from operators that the pitot heat switch is not always set to ON.The work
given in this service bulletin changes the anti-icing system to automatically supply power to heat the
air data sensors.The anti-icing system will come on (AUTO) automatically after engine start if the crew
does not activate the system. If this service bulletin is not done, the air data sensors could be unheated,
which could let ice form on the sensors, and cause erroneous air data. Unreliable air data can lead to
loss of crew situational awareness which could cause failure to maintain safe flight and landing of the
airplane.
Boeing Fleet Team Digest (FTD) 737 FTD 30-8001 is related to this service bulletin.
Boeing Service Related Problem (SRP) 737-SRP-30-0050 (previously 737-SRP-30-0032) is related to
this service bulletin.
As a part of a service bulletin remote certification program, this change was completed on airplane
PR009 by Service Bulletin 737-30A1064 RC 1 before the Original Issue of this service bulletin. The
change completed on airplane PR009 by Service Bulletin 737-30A1064 RC 1 is equivalent to the
Original Issue of this service bulletin. Airplane PR009 has the configuration of a Group 3 airplane.
Revision 1: Sent to add a repetitive test in the work instructions and give a repetitive test interval for
Groups 1 through 4.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
20 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 21

Revision 2: Sent to add airplanes inadvertently omitted to the effectivity of this service bulletin,
PK625-PK627. These airplanes are in the effectivity of the concurrent requirement service bulletins.
The data given in Information Notice 737-30A1064 IN 01 is included in Revision 2.
The data given in Alternative Method of Compliance Notice 737-30A1064 AMOC 01 is included in
Revision 2.
D. Description
Group 1, 6:
1. Access the flight compartment.
2. Replace the P5-9 Window and Pitot Heat Module.
3. Remove INOP markers and collars on the P18-3 circuit breaker panel.
4. Do Pitot Static and Temperature Probe Anti-Icing System Test.
5. Do Control Cabin Window Anti-Icing System Test.
6. Do repetitive Pitot Static and Temperature Probe Anti-Icing System Test at the times specified in
Paragraph 1.E., Compliance.
Group 2-4:
1. Access the flight compartment.
2. Replace the P5-9 Window and Pitot Heat Module.
3. Remove INOP markers and collars on the P18-3 circuit breaker panel.
4. Do Pitot-Static Tubes, Temperature Probe and Alpha Vane Anti-Icing System Test.
5. Do Operational Test - Control Cabin Window Anti-Icing System.
6. Do repetitive Pitot-Static Tubes, Temperature Probe and Alpha Vane Anti-Icing System Test at
the times specified in Paragraph 1.E., Compliance.
Group 5:
Boeing endorses the FAA rules related to LOV and recommends immediate and permanent removal
from service of any airplane upon reaching the LOV, whether or not it is operated under FAA jurisdiction.
As such, Boeing no longer provides maintenance instructions for airplanes that have accumulated flight
cycles beyond the LOV. Airplanes in Group 5 (line numbers 1-291) have accumulated flight cycles
beyond the LOV of the maintenance program.Title 14, Code of Federal Regulations (14 CFR) 121.1115
and 129.115 prohibit operation of an airplane beyond its LOV.
Accomplishment of this service bulletin changes the flight deck and/or operations of the airplane. Refer
to Paragraph 1.K., Publications Affected, for affected publications.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
21 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 22

Effects of this revision on airplanes on which Revision 1 were previously done:
None.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1:
Affected Maintenance Zones
ZoneModel
1-1, 1-2737-200, 737-200C
Group 2:
Affected Maintenance Zones
ZoneModel
101, 102737-300, 737-500
Group 3:
Affected Maintenance Zones
ZoneModel
101, 102737-300, 737-400, 737-500
Group 4:
Affected Maintenance Zones
ZoneModel
101, 102737-400
Group 5:
Affected Maintenance Zones
ZoneModel
1-1, 1-2737-100, 737-200, 737-200C
Group 6:
Affected Maintenance Zones
ZoneModel
1-1, 1-2737-200
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
22 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 23

E. Compliance
Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2019-09-01 is related to this service
bulletin. The effective date of AD 2019-09-01 is June 26, 2019.
Accomplish the required action(s), based on the applicable condition(s) in Table(s) 1 through 3, in
accordance with Paragraph 3. Accomplishment Instructions.
Group 1:
Table 1 - Replacement, Initial Tests and Repetitive Tests
Interval (Not to Ex-
ceed)
Compliance TimeActionCondition
-Within 24 months after the
original issue date of this
service bulletin
Replacement and initial
tests
All airplanes
11,000 flight hoursWithin 11,000 flight hours
after the replacement
Repetitive Pitot Static and
Temperature Probe Anti-
Icing System Test
Airplanes on which the re-
placement has been done
-Before further flightDo corrective action(s), re-
peat the test and do appli-
cable corrective action(s)
until the test passes
Any test fails
Group 2-4:
Table 2 - Replacement, Initial Tests and Repetitive Tests
Interval (Not to Ex-
ceed)
Compliance TimeActionCondition
-Within 24 months after the
original issue date of this
service bulletin
Replacement and initial
tests
All airplanes
11,000 flight hoursWithin 11,000 flight hours
after the replacement
Repetitive Pitot-Static
Tubes, Temperature Probe
and Alpha Vane Anti-Icing
System Test
Airplanes on which the re-
placement has been done
-Before further flightDo corrective action(s), re-
peat the test and do appli-
cable corrective action(s)
until the test passes
Any test fails
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
23 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 24

Group 6:
Table 3 - Replacement, Initial Tests and Repetitive Tests
Interval (Not to Ex-
ceed)
Compliance TimeActionCondition
-Within 24 months after the
Revision 2 date of this ser-
vice bulletin
Replacement and initial
tests
All airplanes
11,000 flight hoursWithin 11,000 flight hours
after the replacement
Repetitive Pitot-Static
Tubes, Temperature Probe
and Alpha Vane Anti-Icing
System Test
Airplanes on which the re-
placement has been done
-Before further flightDo corrective action(s), re-
peat the test and do appli-
cable corrective action(s)
until the test passes
Any test fails
Group 5:
Boeing endorses the FAA rules related to LOV and recommends immediate and permanent removal
from service of any airplane upon reaching the LOV, whether or not it is operated under FAA jurisdiction.
As such, Boeing no longer provides maintenance instructions for airplanes that have accumulated flight
cycles beyond the LOV. Airplanes in Group 5 (line numbers 1-291) have accumulated flight cycles
beyond the LOV of the maintenance program.Title 14, Code of Federal Regulations (14 CFR) 121.1115
and 129.115 prohibit operation of an airplane beyond its LOV.
F. Approval
This service bulletin was examined by the 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.
Group 1-4, 6:
In addition, the Manager of the Los Angeles ACO Branch approves accomplishment of the change
defined in this service bulletin revision as an alternative method of compliance to the requirements of
paragraph (h) of AD 2019-09-01. All provisions of AD 2019-09-01 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 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:
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
24 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 25

• Time to adjust to the workplace
• Time to schedule the work
• Time to inspect the work
• Time to cure the materials
• Time to make the parts
• Time to find the tools.
Group 1, 6:
Elapsed HoursTask HoursNumber of PersonsTask
0.250.251Open Access
0.300.301FIGURE 1
0.300.301FIGURE 3
0.250.251Close Access
1.004.004Test
2.105.10TOTAL FOR EACH AIRPLANE
Group 2:
Elapsed HoursTask HoursNumber of PersonsTask
0.250.251Open Access
0.300.301FIGURE 2
0.300.301FIGURE 4
0.250.251Close Access
1.004.004Test
2.105.10TOTAL FOR EACH AIRPLANE
Group 3:
Elapsed HoursTask HoursNumber of PersonsTask
0.250.251Open Access
0.300.301FIGURE 2
0.300.301FIGURE 5
0.250.251Close Access
1.004.004Test
2.105.10TOTAL FOR EACH AIRPLANE
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
25 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 26

Group 4:
Elapsed HoursTask HoursNumber of PersonsTask
0.250.251Open Access
0.300.301FIGURE 2
0.300.301FIGURE 6
0.250.251Close Access
1.004.004Test
2.105.10TOTAL FOR EACH AIRPLANE
Group 1, 6:
Repetitive Pitot Static and Temperature Probe Anti-Icing System Test
Elapsed HoursTask HoursNumber of PersonsTask
0.250.251Open Access
1.004.004Test
0.250.251Close Access
1.504.50TOTAL FOR EACH AIRPLANE
Group 2-4:
Repetitive Pitot-Static Tubes,Temperature Probe and Alpha Vane Anti-Icing System Test
Elapsed HoursTask HoursNumber of PersonsTask
0.250.251Open Access
1.004.004Test
0.250.251Close Access
1.504.50TOTAL FOR EACH AIRPLANE
Group 1-4, 6:
1. This estimate does not include the task hour data given in the service bulletin(s) in Paragraph 1.B.,
Concurrent Requirements.
2. The time to make the change to the P5-9 Window and Pitot Heat Module in accordance with BAE
Systems SB 69-37346-30-04 Service Bulletin is not included.
Group 5:
Boeing endorses the FAA rules related to LOV and recommends immediate and permanent removal
from service of any airplane upon reaching the LOV, whether or not it is operated under FAA jurisdiction.
As such, Boeing no longer provides maintenance instructions for airplanes that have accumulated flight
cycles beyond the LOV. Airplanes in Group 5 (line numbers 1-291) have accumulated flight cycles
beyond the LOV of the maintenance program.Title 14, Code of Federal Regulations (14 CFR) 121.1115
and 129.115 prohibit operation of an airplane beyond its LOV.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
26 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 27

H. Weight and Balance Changes
None.
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Engineering Change Memo PRR 35005-295RS
b. Boeing Service Bulletin 737-30-1067, 737-30-1068
c. Boeing Service Related Problem (SRP) 737-SRP-30-0032, 737-SRP-30-0050
d. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2019-09-01
e. Service Bulletin Index D6-19567
f. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19
g. 737 Fleet Team Digest (FTD) 30-8001
h. 737-100/200 Aircraft Maintenance Manual (AMM) 24-22-00, 30-09-11, 30-41-00, 71-00-00
i. 737-100/200 Wiring Diagram Manual (WDM) 79-34-01
j. 737-300/400/500 Aircraft Maintenance Manual (AMM) 24-22-00, 30-09-11, 30-41-00, 71-00-00
k. 737-300/400/500 Wiring Diagram Manual (WDM) 79-34-11
l. BAE Systems Service Bulletin 69-37346-30-04
m. Installation Deviation Record (IDR) Log number 737-30A1064-PR009
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:
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
27 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 28

Chapter-SectionPublication
Chapters 1.20 and 3.20737 Flight Crew Operations Manual
30-31737-100/-200 Aircraft Maintenance Manual
30-09, 30-31, 31-24, 34-12737-300/-400/-500 Aircraft Maintenance Manual
11-17, 30-30, 31-10737-100/-200 Illustrated Parts Catalog
11-30, 24-50, 30-09, 30-31,31-11,
33-11, 56-11, 56-12
737-300/-400/-500 Illustrated Parts Catalog
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program.This service bulletin does not affect FCS, therefore DTIs are not necessary.
L. Interchangeability and Intermixability of Parts
Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for interchangeability and intermixability
information.
M. Software Accomplishment Summary
Not affected.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
28 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 29

2.    MATERIAL INFORMATION
A. Material - Price and Availability
The operator can supply the parts and materials shown in Paragraph 2.C., Parts Necessary for Each
Airplane. As an alternative, operators can purchase the parts from Boeing Spares.This service bulletin
does not show the Boeing price and supply data.
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
None.
2. Parts and Materials Supplied by the Operator
Group 1-4, 6:
The following parts or materials are necessary to do the change in this service bulletin. Parts and
materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine
operator part and material supply to make sure all necessary parts and materials are available.
Group 1-4, 6:
NotesExisting Part NumberNameQTYPart Number /
Specification
(a)69-37346-( )P5-9 WINDOW AND PITOT HEAT MODULE169-37346-( )
(a) Replace or make the change in accordance with BAE Systems SB 69-37346-30-04, Original Issue, dated
Aug 02/2012. The existing part cannot replace the new or changed part.
Group 5:
Boeing endorses the Federal Aviation Administration (FAA) rules related to Limit of Validity (LOV)
and recommends immediate and permanent removal from service of any airplane upon reaching
the LOV, whether or not it is operated under FAA jurisdiction. As such, Boeing no longer provides
maintenance instructions for airplanes that have accumulated flight cycles beyond the LOV.
Airplanes in Group 5 (line numbers 1-291) have accumulated flight cycles beyond the LOV of the
maintenance program. Title 14, Code of Federal Regulations (14 CFR) 121.1115 and 129.115
prohibit operation of an airplane beyond its LOV.
3. Parts Modified and Reidentified
None.
4. Parts Removed and Not Replaced
None.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
29 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 30

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.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
30 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 31

3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
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. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches
– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch
– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch
– Angular tolerance is plus or minus 2 degrees
– Hole dimensions for standard solid rivets and fasteners are in Structural Repair
Manual (SRM) Chapter 51
– Torque Values:
— Values for structural fasteners are given in 737 Structural Repair Manual,
Chapter 51.
— Values for airframe maintenance tasks are included in Chapter 20 of 737
Aircraft Maintenance Manual (AMM).
— Values for electrical maintenance tasks are included in Chapter 20 of
Standard Wiring Practices Manual (SWPM).
— Values for engine maintenance tasks are included in Chapter 70 of 737
Aircraft Maintenance Manual (AMM).
— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
4. Use the approved fastener, process and material substitutions in accordance with
SRM Chapter 51.
5. 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.
6. 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.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
31 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 32

7. 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.
8. If it is necessary to remove more parts for access, you can remove those parts. If
you can get access without removing identified parts, it is not necessary to remove
all of the identified parts. Jacking and shoring limitations must be observed.
9. Where the work instructions include installation of a kept part, a new or serviceable
part with the same part number can be installed as an alternative to the kept part.
10. 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.
11. Use of colors in Figures is based on guidance from the ATA e-Business Program
(ATA) iSpec 2200.
12. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
13. Some steps in the Work Instructions are labeled as Required for Compliance (RC).
If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps
labeled as RC, including sub-steps under an RC step and any figures identified in
an RC step, must be done to comply with the AD. If a step or sub-step is labeled
"RC Exempt," then the RC requirement is removed from that step or sub-step. An
Alternative Method of Compliance (AMOC) is required for any deviations to RC steps,
including sub-steps and identified figures. Steps not labeled as RC may be deviated
from using accepted methods in accordance with the operator's maintenance or
inspection program without obtaining approval of an AMOC. This is provided that
the RC steps, including sub-steps and identified figures, can still be done as specified,
and the airplane can be put back in an airworthy condition.
14. Airplane PR009 was changed in accordance with Boeing Service Bulletin
737-30A1064 RC 1 and Installation Deviation Record (IDR) Log number
737-30A1064-PR009.
15. When more than one OPTION is given, do only one of the OPTION numbers.
B. WORK INSTRUCTIONS
Group 5:
Boeing endorses the Federal Aviation Administration (FAA) rules related to Limit of Validity (LOV) and
recommends immediate and permanent removal from service of any airplane upon reaching the LOV,
whether or not it is operated under FAA jurisdiction. As such, Boeing no longer provides maintenance
instructions for airplanes that have accumulated flight cycles beyond the LOV. Airplanes in Group 5
(line numbers 1-291) have accumulated flight cycles beyond the LOV of the maintenance program.
Title 14, Code of Federal Regulations (14 CFR) 121.1115 and 129.115 prohibit operation of an airplane
beyond its LOV.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
32 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 33

Group 1, 6:
1. Remove electrical power from the airplane. Refer to 737-100/200 AMM 24-22-00 as an accepted
procedure.
2. Open the following circuit breakers and install circuit breaker locks and DO-NOT-CLOSE tags.
PanelCircuit Breaker NomenclatureCircuit Breaker Number
P6 PANELL4 & L5C229
P6 PANELR SIDEC393
P6 PANELL FRONTC228
P6 PANELR4 & R5C395
P6 PANELR FRONTC394
P6 PANELL SIDEC392
P6 PANELCAPT PITOT STATIC INDICATIONC569
P6 PANELF/O PITOT STATIC INDICATIONC570
P6 PANELMASTER CAUTION ANTI-ICEC573
P18 PANELCAPT UPPER LC523
P18 PANELCAPT LWR RC524
P18 PANELF/O UPPER RC525
P18 PANELF/O LWR LC522
P18 PANELELEVATOR PITOT RC237
P18 PANELELEVATOR PITOT LC236
P18 PANELRIGHT TEMP PROBC708
P18 PANELRIGHT FWD ACC226
P18 PANELRIGHT FWD DCC222
P18 PANELRIGHT SIDE ACC227
P18 PANELRIGHT SIDE DCC223
P18 PANELLEFT FWD ACC224
P18 PANELLEFT FWD DCC220
P18 PANELLEFT SIDE ACC225
P18 PANELLEFT SIDE DCC221
P18 PANELLEFT TEMP PROB / TEMP PROBC238
3. Access the P5 overhead panel in the flight compartment.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
33 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 34

DO NOT TOUCH ELECTRICAL CONNECTOR UNTIL INSTRUCTED BY THE
PROCEDURE. THE MODULE IS SENSITIVE TO THE ELECTROSTATIC
DISCHARGE. ELECTROSTATIC DISCHARGE CAN CAUSE DAMAGE TO THE
MODULE. INJURY TO PERSONNEL OR DAMAGE TO EQUIPMENT CAN OCCUR.
CAUTION
4. RC - Replace the P5-9 Window and Pitot Heat Module in accordance with FIGURE 1.
5. Remove INOP markers and collars on the P18-3 circuit breaker panel in accordance with FIGURE
3 or FIGURE 7.
NotesPanelCircuit Breaker NomenclatureCircuit Breaker Number
(a)P18-3 CIRCUIT BREAKER
PANEL
PROBE HEAT CAPTC1946
(a)P18-3 CIRCUIT BREAKER
PANEL
PROBE HEAT F/OC1947
(a) An option is provided to allow operators to use available circuit breaker positions.
6. Close the following circuit breakers and remove circuit breaker locks and DO-NOT-CLOSE tags.
PanelCircuit Breaker NomenclatureCircuit Breaker Number
P6 PANELL4 & L5C229
P6 PANELR SIDEC393
P6 PANELL FRONTC228
P6 PANELR4 & R5C395
P6 PANELR FRONTC394
P6 PANELL SIDEC392
P6 PANELCAPT PITOT STATIC INDICATIONC569
P6 PANELF/O PITOT STATIC INDICATIONC570
P6 PANELMASTER CAUTION ANTI-ICEC573
P18 PANELCAPT UPPER LC523
P18 PANELCAPT LWR RC524
P18 PANELF/O UPPER RC525
P18 PANELF/O LWR LC522
P18 PANELELEVATOR PITOT RC237
P18 PANELELEVATOR PITOT LC236
P18 PANELRIGHT TEMP PROBC708
P18 PANELRIGHT FWD ACC226
P18 PANELRIGHT FWD DCC222
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
34 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 35

PanelCircuit Breaker NomenclatureCircuit Breaker Number
P18 PANELRIGHT SIDE ACC227
P18 PANELRIGHT SIDE DCC223
P18 PANELLEFT FWD ACC224
P18 PANELLEFT FWD DCC220
P18 PANELLEFT SIDE ACC225
P18 PANELLEFT SIDE DCC221
P18 PANELLEFT TEMP PROB / TEMP PROBC238
ALL PROTECTIVE CAPS AND COVERS MUST BE REMOVED FROM ALL AIR
DATA PROBES. AIR DATA PROBES AND COVERS COULD BE DAMAGED IF
THERE ARE COVERS INSTALLED ON THE AIR DATA PROBES WHEN THEY
ARE HEATED.
CAUTION
7. Remove any installed protective caps or covers on pitot probes, outside air temperature probe,
and alpha vanes.
8. Make sure the following circuit breakers are closed.
More DataPanelCircuit Breaker NomenclatureCircuit Breaker Number
(a)P6 PANELENG 1 THRUST REVERSER DCC276
(a)P6 PANELENG 2 THRUST REVERSER DCC277
(a)P6 PANELENG 2 T/R CONT ALTNC175
(a)P6 PANELENG 1 T/R IND SYSC1003
(a)P6 PANELENG 2 T/R IND SYSC1004
(a) If installed.
9. Make sure the battery switch on the P5-13 Electrical Meter Battery and Galley Power Panel is set
ON.
10. Make sure Engine 1 Fire Switch and Engine 2 Fire Switch on the P8-1 Engine and Fire Control
Panel are pushed in.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
35 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 36

DO NOT TOUCH THE AIR DATA PROBES WHILE THE HEATERS ARE ON. FEEL
FOR HEAT RADIATION FROM THE AIR DATA PROBES IN THE VICINITY OF
THE AIR DATA PROBES. HOT AIR DATA PROBES CAN CAUSE BURN INJURIES.
WARNING
DO NOT OPERATE ANY HEATER FOR MORE THAN 5 MINUTES. THE LIFE OF
THE HEATER WOULD DECREASE IF IT STAYS ON FOR MORE THAN 5
MINUTES.
CAUTION
11. Supply electrical power to the airplane. Refer to 737-100/200 AMM 24-22-00 as an accepted
procedure.
12. RC - Do Pitot Static and Temperature Probe Anti-Icing System Test as follows: if the test fails, do
corrective action(s), repeat the test, and do applicable corrective action(s) until the operational
test passes.
NOTE: The master caution indicators might turn on for the test below. Cancel master caution,
as necessary, throughout the test.
a. Make sure the engines are turned off. Refer to 737-100/200 AMM 71-00-00 as an accepted
procedure.
b. Set Switch A and B on the P5-9 Window and Pitot Heat Module to ON position and make sure
all probe heat indicators on the P5-9 Window and Pitot Heat Module turn OFF.
c. Set Switch A and B on the P5-9 Window and Pitot Heat Module to AUTO position and make
sure all probe heat indicators on the P5-9 Window and Pitot Heat Module turn ON.
d. Do one of the following options to test probe heat indicators:
ALL AIR DATA PROBES WILL BE HOT WHEN RUNNING TESTS WITH
PROBE HEAT SWITCHES A AND B IN THE AUTO POSITION AND
EITHER ENGINE RUNNING.
WARNING
(1) OPTION 1: ENGINE CYCLE METHOD
(a) Start Engine 1. Refer to 737-100/200 AMM 71-00-00 as an accepted procedure.
(b) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module turn
OFF.
NOTE: If TAT Test switch is installed do as follows:
(1) Press and hold the TAT Test switch.
(2) Make sure the TEMP Probe Indicator(s) remain off.
(3) Make sure the TAT Probe heater is on, the TAT Probe will get hot.
(4) Limit the test time to 20 seconds (holding the TAT Test switch).
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
36 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 37

(c) Stop Engine 1. Refer to 737-100/200 AMM 71-00-00 as an accepted procedure.
(d) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module turn
ON.
(e) Start Engine 2. Refer to 737-100/200 AMM 71-00-00 as an accepted procedure.
(f) Make sure all the probe heat indicators on the P5-9 Window and Pitot Heat Module
turn OFF.
NOTE: If TAT Test switch is installed do as follows:
(1) Press and hold the TAT Test switch.
(2) Make sure the TEMP Probe Indicator(s) remain off.
(3) Make sure the TAT Probe heater is on, the TAT Probe will get hot.
(4) Limit the test time to 20 seconds (holding the TAT Test switch).
(g) Stop Engine 2. Refer to 737-100/200 AMM 71-00-00 as an accepted procedure.
(h) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module turn
ON.
ALL AIR DATA PROBES WILL BE HOT WHEN RUNNING TESTS WITH
PROBE HEAT SWITCHES A AND B IN THE AUTO POSITION AND
CONNECTOR D752 FROM EITHER SWITCH S124 WITH PINS 1 AND
2 CONNECTED.
WARNING
(2) OPTION 2: CONNECTOR METHOD
(a) Disconnect connector D752 from S124 Engine-1 Low Oil Pressure Switch. Refer to
737-100/200 WDM 79-34-01.
(b) Connect jumper wires between Pins 1 and 2 of Connector D752. Refer to 737-100/200
WDM 79-34-01.
(c) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module turn
OFF.
NOTE: If TAT Test switch is installed do as follows:
(1) Press and hold the TAT Test switch.
(2) Make sure the TEMP Probe Indicator(s) remain off.
(3) Make sure the TAT Probe heater is on, the TAT Probe will get hot.
(4) Limit the test time to 20 seconds (holding the TAT Test switch).
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
37 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 38

(d) Remove jumper wire between Pins 1 and 2 of Connector D752. Refer to 737-100/200
WDM 79-34-01.
(e) Connect connector D752 to S124 Engine-1 Low Oil Pressure Switch. Refer to
737-100/200 WDM 79-34-01.
(f) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module turn
ON.
(g) Disconnect connector D752 from S124 Engine-2 Low Oil Pressure Switch. Refer to
737-100/200 WDM 79-34-01.
(h) Connect jumper wires between Pins 1 and 2 of Connector D752. Refer to 737-100/200
WDM 79-34-01.
(i) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module turn
OFF.
NOTE: If TAT Test switch is installed do as follows:
(1) Press and hold the TAT Test switch.
(2) Make sure the TEMP Probe Indicator(s) remain off.
(3) Make sure the TAT Probe heater is on, the TAT Probe will get hot.
(4) Limit the test time to 20 seconds (holding the TAT Test switch).
(j) Remove jumper wire between Pins 1 and 2 of Connector D752. Refer to 737-100/200
WDM 79-34-01.
(k) Connect connector D752 to S124 Engine-2 Low Oil Pressure Switch. Refer to
737-100/200 WDM 79-34-01.
(l) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module turn
ON.
13. Do Control Cabin Window Anti-Icing System Test. Refer to 737-100/200 AMM 30-41-00 as an
accepted procedure.
14. Put the airplane back to a serviceable condition.
15. Do repetitive Pitot Static and Temperature Probe Anti-Icing System Test, as follows, at the times
specified in Paragraph 1.E., Compliance.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
38 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 39

ALL PROTECTIVE CAPS AND COVERS MUST BE REMOVED FROM ALL
AIR DATA PROBES. AIR DATA PROBES AND COVERS COULD BE
DAMAGED IF THERE ARE COVERS INSTALLED ON THE AIR DATA
PROBES WHEN THEY ARE HEATED.
CAUTION
a. Remove any installed protective caps or covers on pitot probes, outside air temperature probe,
and alpha vanes.
b. Make sure the following circuit breakers are closed.
More DataPanelCircuit Breaker NomenclatureCircuit Breaker Number
(a)P6 PANELENG 1 THRUST REVERSER DCC276
(a)P6 PANELENG 2 THRUST REVERSER DCC277
(a)P6 PANELENG 2 T/R CONT ALTNC175
(a)P6 PANELENG 1 T/R IND SYSC1003
(a)P6 PANELENG 2 T/R IND SYSC1004
(a) If installed.
c. Make sure the battery switch on the P5-13 Electrical Meter Battery and Galley Power Panel
is set ON.
d. Make sure Engine 1 Fire Switch and Engine 2 Fire Switch on the P8-1 Engine and Fire Control
Panel are pushed in.
DO NOT TOUCH THE AIR DATA PROBES WHILE THE HEATERS ARE ON.
FEEL FOR HEAT RADIATION FROM THE AIR DATA PROBES IN THE
VICINITY OF THE AIR DATA PROBES. HOT AIR DATA PROBES CAN CAUSE
BURN INJURIES.
WARNING
DO NOT OPERATE ANY HEATER FOR MORE THAN 5 MINUTES.THE LIFE
OF THE HEATER WOULD DECREASE IF IT STAYS ON FOR MORE THAN
5 MINUTES.
CAUTION
e. Supply electrical power to the airplane. Refer to 737-100/200 AMM 24-22-00 as an accepted
procedure.
f. RC - Do Pitot Static and Temperature Probe Anti-Icing System Test as follows: if the test fails,
do corrective action(s), repeat the test, and do applicable corrective action(s) until the
operational test passes.
NOTE: The master caution indicators might turn on for the test below. Cancel master caution,
as necessary, throughout the test.
(1) Make sure the engines are turned off. Refer to 737-100/200 AMM 71-00-00 as an accepted
procedure.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
39 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 40

(2) Set Switch A and B on the P5-9 Window and Pitot Heat Module to ON position and make
sure all probe heat indicators on the P5-9 Window and Pitot Heat Module turn OFF.
(3) Set Switch A and B on the P5-9 Window and Pitot Heat Module to AUTO position and
make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module turn ON.
(4) Do one of the following options to test probe heat indicators:
ALL AIR DATA PROBES WILL BE HOT WHEN RUNNING TESTS
WITH PROBE HEAT SWITCHES A AND B IN THE AUTO POSITION
AND EITHER ENGINE RUNNING.
WARNING
(a) OPTION 9: ENGINE CYCLE METHOD
1) Start Engine 1. Refer to 737-100/200 AMM 71-00-00 as an accepted procedure.
2) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module
turn OFF.
NOTE: If TAT Test switch is installed do as follows:
(1) Press and hold the TAT Test switch.
(2) Make sure the TEMP Probe Indicator(s) remain off.
(3) Make sure the TAT Probe heater is on, the TAT Probe will get hot.
(4) Limit the test time to 20 seconds (holding the TAT Test switch).
3) Stop Engine 1. Refer to 737-100/200 AMM 71-00-00 as an accepted procedure.
4) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module
turn ON.
5) Start Engine 2. Refer to 737-100/200 AMM 71-00-00 as an accepted procedure.
6) Make sure all the probe heat indicators on the P5-9 Window and Pitot Heat
Module turn OFF.
NOTE: If TAT Test switch is installed do as follows:
(1) Press and hold the TAT Test switch.
(2) Make sure the TEMP Probe Indicator(s) remain off.
(3) Make sure the TAT Probe heater is on, the TAT Probe will get hot.
(4) Limit the test time to 20 seconds (holding the TAT Test switch).
7) Stop Engine 2. Refer to 737-100/200 AMM 71-00-00 as an accepted procedure.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
40 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 41

8) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module
turn ON.
ALL AIR DATA PROBES WILL BE HOT WHEN RUNNING TESTS
WITH PROBE HEAT SWITCHES A AND B IN THE AUTO POSITION
AND CONNECTOR D752 FROM EITHER SWITCH S124 WITH
PINS 1 AND 2 CONNECTED.
WARNING
(b) OPTION 10: CONNECTOR METHOD
1) Disconnect connector D752 from S124 Engine-1 Low Oil Pressure Switch. Refer
to 737-100/200 WDM 79-34-01.
2) Connect jumper wires between Pins 1 and 2 of Connector D752. Refer to
737-100/200 WDM 79-34-01.
3) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module
turn OFF.
NOTE: If TAT Test switch is installed do as follows:
(1) Press and hold the TAT Test switch.
(2) Make sure the TEMP Probe Indicator(s) remain off.
(3) Make sure the TAT Probe heater is on, the TAT Probe will get hot.
(4) Limit the test time to 20 seconds (holding the TAT Test switch).
4) Remove jumper wire between Pins 1 and 2 of Connector D752. Refer to
737-100/200 WDM 79-34-01.
5) Connect connector D752 to S124 Engine-1 Low Oil Pressure Switch. Refer to
737-100/200 WDM 79-34-01.
6) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module
turn ON.
7) Disconnect connector D752 from S124 Engine-2 Low Oil Pressure Switch. Refer
to 737-100/200 WDM 79-34-01.
8) Connect jumper wires between Pins 1 and 2 of Connector D752. Refer to
737-100/200 WDM 79-34-01.
9) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module
turn OFF.
NOTE: If TAT Test switch is installed do as follows:
(1) Press and hold the TAT Test switch.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
41 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 42

(2) Make sure the TEMP Probe Indicator(s) remain off.
(3) Make sure the TAT Probe heater is on, the TAT Probe will get hot.
(4) Limit the test time to 20 seconds (holding the TAT Test switch).
10) Remove jumper wire between Pins 1 and 2 of Connector D752. Refer to
737-100/200 WDM 79-34-01.
11) Connect connector D752 to S124 Engine-2 Low Oil Pressure Switch. Refer to
737-100/200 WDM 79-34-01.
12) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module
turn ON.
g. Put the airplane back to a serviceable condition.
Group 2:
1. Remove electrical power from the airplane. Refer to 737-300/400/500 AMM 24-22-00 as an
accepted procedure.
2. Open the following circuit breakers and install circuit breaker locks and DO-NOT-CLOSE tags.
PanelCircuit Breaker NomenclatureCircuit Breaker Number
P6 PANELMSTR CAUTION - ANTI-ICEC00573
P6 PANELPITOT STATIC INDICATION - F/OC00570
P6 PANELPITOT STATIC INDICATION - CAPTC00569
P6 PANELR FRONT WINDOW ANTI-ICEC00394
P6 PANELL FRONT WINDOW ANTI-ICEC00228
P6 PANELR SIDE WINDOW ANTI-ICEC00393
P6 PANELL SIDE WINDOW ANTI-ICEC00392
P6 PANELRIGHT NO. 4 AND NO. 5 WINDOW ANTI-ICEC00395
P6 PANELLEFT NO. 4 AND NO. 5 WINDOW ANTI-ICEC00229
P18 PANELCAPT - UPPER LC00523
P18 PANELCAPT - LWR RC00524
P18 PANELF/O UPPER RC00525
P18 PANELF/O LWR LC00522
P18 PANELELEVATOR PITOT - RC00237
P18 PANELELEVATOR PITOT - LC00236
P18 PANELTEMP PROBEC00238
P18 PANELALPHA VANE HTR - RC01071
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
42 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 43

PanelCircuit Breaker NomenclatureCircuit Breaker Number
P18 PANELALPHA VANE HTR - LC01072
P18 PANELRIGHT FRONT ACC00226
P18 PANELRIGHT FRONT DCC00222
P18 PANELRIGHT SIDE ACC00227
P18 PANELRIGHT SIDE DCC00223
P18 PANELLEFT FRONT ACC00224
P18 PANELLEFT FRONT DCC00220
P18 PANELLEFT SIDE ACC00225
P18 PANELLEFT SIDE DCC00221
3. Access the P5 overhead panel in the flight compartment.
DO NOT TOUCH ELECTRICAL CONNECTOR UNTIL INSTRUCTED BY THE
PROCEDURE. THE MODULE IS SENSITIVE TO THE ELECTROSTATIC
DISCHARGE. ELECTROSTATIC DISCHARGE CAN CAUSE DAMAGE TO THE
MODULE. INJURY TO PERSONNEL OR DAMAGE TO EQUIPMENT CAN OCCUR.
CAUTION
4. RC - Replace the P5-9 Window and Pitot Heat Module in accordance with FIGURE 2.
5. Remove INOP markers and collars on the P18-3 circuit breaker panel in accordance with FIGURE
4 or FIGURE 7.
NotesPanelCircuit Breaker NomenclatureCircuit Breaker Number
(a)P18-3 CIRCUIT BREAKER
PANEL
PROBE HEAT CAPTC1946
(a)P18-3 CIRCUIT BREAKER
PANEL
PROBE HEAT F/OC1947
(a) An option is provided to allow operators to use available circuit breaker positions.
6. Close the following circuit breakers and remove circuit breaker locks and DO-NOT-CLOSE tags.
PanelCircuit Breaker NomenclatureCircuit Breaker Number
P6 PANELMSTR CAUTION - ANTI-ICEC00573
P6 PANELPITOT STATIC INDICATION - F/OC00570
P6 PANELPITOT STATIC INDICATION - CAPTC00569
P6 PANELR FRONT WINDOW ANTI-ICEC00394
P6 PANELL FRONT WINDOW ANTI-ICEC00228
P6 PANELR SIDE WINDOW ANTI-ICEC00393
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
43 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 44

PanelCircuit Breaker NomenclatureCircuit Breaker Number
P6 PANELL SIDE WINDOW ANTI-ICEC00392
P6 PANELRIGHT NO. 4 AND NO. 5 WINDOW ANTI-ICEC00395
P6 PANELLEFT NO. 4 AND NO. 5 WINDOW ANTI-ICEC00229
P18 PANELCAPT - UPPER LC00523
P18 PANELCAPT - LWR RC00524
P18 PANELF/O UPPER RC00525
P18 PANELF/O LWR LC00522
P18 PANELELEVATOR PITOT - RC00237
P18 PANELELEVATOR PITOT - LC00236
P18 PANELTEMP PROBEC00238
P18 PANELALPHA VANE HTR - RC01071
P18 PANELALPHA VANE HTR - LC01072
P18 PANELRIGHT FRONT ACC00226
P18 PANELRIGHT FRONT DCC00222
P18 PANELRIGHT SIDE ACC00227
P18 PANELRIGHT SIDE DCC00223
P18 PANELLEFT FRONT ACC00224
P18 PANELLEFT FRONT DCC00220
P18 PANELLEFT SIDE ACC00225
P18 PANELLEFT SIDE DCC00221
ALL PROTECTIVE CAPS AND COVERS MUST BE REMOVED FROM ALL AIR
DATA PROBES. AIR DATA PROBES AND COVERS COULD BE DAMAGED IF
THERE ARE COVERS INSTALLED ON THE AIR DATA PROBES WHEN THEY
ARE HEATED.
CAUTION
7. Remove any installed protective caps or covers on pitot probes, outside air temperature probe,
and alpha vanes.
8. Make sure the following circuit breakers are closed.
More DataPanelCircuit Breaker NomenclatureCircuit Breaker Number
(a)P6 PANELENG 1 T/R CONT SYSC00276
(a)P6 PANELENG 2 T/R CONT SYSC00277
(a)P6 PANELENG 2 T/R CONT ALTNC00175
(a)P6 PANELENG 1 T/R IND SYSC01003
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
44 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 45

More DataPanelCircuit Breaker NomenclatureCircuit Breaker Number
(a)P6 PANELENG 2 T/R IND SYSC01004
(a) If installed.
9. Make sure the battery switch on the P5-13 Electrical Meter Battery and Galley Power Panel is set
ON.
10. Make sure Engine 1 Fire Switch and Engine 2 Fire Switch on the P8-1 Engine and Fire Control
Panel are pushed in.
DO NOT TOUCH THE AIR DATA PROBES WHILE THE HEATERS ARE ON. FEEL
FOR HEAT RADIATION FROM THE AIR DATA PROBES IN THE VICINITY OF
THE AIR DATA PROBES. HOT AIR DATA PROBES CAN CAUSE BURN INJURIES.
WARNING
DO NOT OPERATE ANY HEATER FOR MORE THAN 5 MINUTES. THE LIFE OF
THE HEATER WOULD DECREASE IF IT STAYS ON FOR MORE THAN 5
MINUTES.
CAUTION
11. Supply electrical power to the airplane. Refer to 737-300/400/500 AMM 24-22-00 as an accepted
procedure.
12. RC - Do Pitot-Static Tubes, Temperature Probe and Alpha Vane Anti-Icing System Test as follows:
if the test fails, do corrective action(s), repeat the test, and do applicable corrective action(s) until
the operational test passes.
NOTE: The master caution indicators might turn on for the test below. Cancel master caution,
as necessary, throughout the test.
a. Make sure the engines are turned off. Refer to 737-300/400/500 AMM 71-00-00 as an accepted
procedure.
b. Set Switch A and B on the P5-9 Window and Pitot Heat Module to ON position and make sure
all probe heat indicators on the P5-9 Window and Pitot Heat Module turn OFF.
c. Set Switch A and B on the P5-9 Window and Pitot Heat Module to AUTO position and make
sure all probe heat indicators on the P5-9 Window and Pitot Heat Module turn ON.
d. Do one of the following options to test probe heat indicators:
ALL AIR DATA PROBES WILL BE HOT WHEN RUNNING TESTS WITH
PROBE HEAT SWITCHES A AND B IN THE AUTO POSITION AND
EITHER ENGINE RUNNING.
WARNING
(1) OPTION 3: ENGINE CYCLE METHOD
(a) Start Engine 1. Refer to 737-300/400/500 AMM 71-00-00 as an accepted procedure.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
45 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 46

(b) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module turn
OFF.
NOTE: If TAT Test switch is installed do as follows:
(1) Press and hold the TAT Test switch.
(2) Make sure the TEMP Probe Indicator(s) remain off.
(3) Make sure the TAT Probe heater is on, the TAT Probe will get hot.
(4) Limit the test time to 20 seconds (holding the TAT Test switch).
(c) Stop Engine 1. Refer to 737-300/400/500 AMM 71-00-00 as an accepted procedure.
(d) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module turn
ON.
(e) Start Engine 2. Refer to 737-300/400/500 AMM 71-00-00 as an accepted procedure.
(f) Make sure all the probe heat indicators on the P5-9 Window and Pitot Heat Module
turn OFF.
NOTE: If TAT Test switch is installed do as follows:
(1) Press and hold the TAT Test switch.
(2) Make sure the TEMP Probe Indicator(s) remain off.
(3) Make sure the TAT Probe heater is on, the TAT Probe will get hot.
(4) Limit the test time to 20 seconds (holding the TAT Test switch).
(g) Stop Engine 2. Refer to 737-300/400/500 AMM 71-00-00 as an accepted procedure.
(h) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module turn
ON.
ALL AIR DATA PROBES WILL BE HOT WHEN RUNNING TESTS WITH
PROBE HEAT SWITCHES A AND B IN THE AUTO POSITION AND
CONNECTOR D752 FROM EITHER SWITCH S124 WITH PINS 1 AND
2 CONNECTED.
WARNING
(2) OPTION 4: CONNECTOR METHOD
(a) Disconnect connector D752 from S124 Engine-1 Low Oil Pressure Switch. Refer to
737-300/400/500 WDM 79-34-11.
(b) Connect jumper wires between Pins 1 and 2 of Connector D752. Refer to
737-300/400/500 WDM 79-34-11.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
46 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 47

(c) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module turn
OFF.
NOTE: If TAT Test switch is installed do as follows:
(1) Press and hold the TAT Test switch.
(2) Make sure the TEMP Probe Indicator(s) remain off.
(3) Make sure the TAT Probe heater is on, the TAT Probe will get hot.
(4) Limit the test time to 20 seconds (holding the TAT Test switch).
(d) Remove jumper wire between Pins 1 and 2 of Connector D752. Refer to
737-300/400/500 WDM 79-34-11.
(e) Connect connector D752 to S124 Engine-1 Low Oil Pressure Switch. Refer to
737-300/400/500 WDM 79-34-11.
(f) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module turn
ON.
(g) Disconnect connector D752 from S124 Engine-2 Low Oil Pressure Switch. Refer to
737-300/400/500 WDM 79-34-11.
(h) Connect jumper wires between Pins 1 and 2 of Connector D752. Refer to
737-300/400/500 WDM 79-34-11.
(i) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module turn
OFF.
NOTE: If TAT Test switch is installed do as follows:
(1) Press and hold the TAT Test switch.
(2) Make sure the TEMP Probe Indicator(s) remain off.
(3) Make sure the TAT Probe heater is on, the TAT Probe will get hot.
(4) Limit the test time to 20 seconds (holding the TAT Test switch).
(j) Remove jumper wire between Pins 1 and 2 of Connector D752. Refer to
737-300/400/500 WDM 79-34-11.
(k) Connect connector D752 to S124 Engine-2 Low Oil Pressure Switch. Refer to
737-300/400/500 WDM 79-34-11.
(l) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module turn
ON.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
47 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 48

13. Do Operational Test - Control Cabin Window Anti-Icing System. Refer to 737-300/400/500 AMM
30-41-00 as an accepted procedure.
14. Put the airplane back to a serviceable condition.
15. Do repetitive Pitot-Static Tubes, Temperature Probe and Alpha Vane Anti-Icing System Test, as
follows, at the times specified in Paragraph 1.E., Compliance.
ALL PROTECTIVE CAPS AND COVERS MUST BE REMOVED FROM ALL
AIR DATA PROBES. AIR DATA PROBES AND COVERS COULD BE
DAMAGED IF THERE ARE COVERS INSTALLED ON THE AIR DATA
PROBES WHEN THEY ARE HEATED.
CAUTION
a. Remove any installed protective caps or covers on pitot probes, outside air temperature probe,
and alpha vanes.
b. Make sure the following circuit breakers are closed.
More DataPanelCircuit Breaker NomenclatureCircuit Breaker Number
(a)P6 PANELENG 1 T/R CONT SYSC00276
(a)P6 PANELENG 2 T/R CONT SYSC00277
(a)P6 PANELENG 2 T/R CONT ALTNC00175
(a)P6 PANELENG 1 T/R IND SYSC01003
(a)P6 PANELENG 2 T/R IND SYSC01004
(a) If installed.
c. Make sure the battery switch on the P5-13 Electrical Meter Battery and Galley Power Panel
is set ON.
d. Make sure Engine 1 Fire Switch and Engine 2 Fire Switch on the P8-1 Engine and Fire Control
Panel are pushed in.
DO NOT TOUCH THE AIR DATA PROBES WHILE THE HEATERS ARE ON.
FEEL FOR HEAT RADIATION FROM THE AIR DATA PROBES IN THE
VICINITY OF THE AIR DATA PROBES. HOT AIR DATA PROBES CAN CAUSE
BURN INJURIES.
WARNING
DO NOT OPERATE ANY HEATER FOR MORE THAN 5 MINUTES.THE LIFE
OF THE HEATER WOULD DECREASE IF IT STAYS ON FOR MORE THAN
5 MINUTES.
CAUTION
e. Supply electrical power to the airplane. Refer to 737-300/400/500 AMM 24-22-00 as an
accepted procedure.
f. RC - Do Pitot-Static Tubes, Temperature Probe and Alpha Vane Anti-Icing System Test as
follows: if the test fails, do corrective action(s), repeat the test, and do applicable corrective
action(s) until the operational test passes.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
48 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 49

NOTE: The master caution indicators might turn on for the test below. Cancel master caution,
as necessary, throughout the test.
(1) Make sure the engines are turned off. Refer to 737-300/400/500 AMM 71-00-00 as an
accepted procedure.
(2) Set Switch A and B on the P5-9 Window and Pitot Heat Module to ON position and make
sure all probe heat indicators on the P5-9 Window and Pitot Heat Module turn OFF.
(3) Set Switch A and B on the P5-9 Window and Pitot Heat Module to AUTO position and
make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module turn ON.
(4) Do one of the following options to test probe heat indicators:
ALL AIR DATA PROBES WILL BE HOT WHEN RUNNING TESTS
WITH PROBE HEAT SWITCHES A AND B IN THE AUTO POSITION
AND EITHER ENGINE RUNNING.
WARNING
(a) OPTION 11: ENGINE CYCLE METHOD
1) Start Engine 1. Refer to 737-300/400/500 AMM 71-00-00 as an accepted
procedure.
2) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module
turn OFF.
NOTE: If TAT Test switch is installed do as follows:
(1) Press and hold the TAT Test switch.
(2) Make sure the TEMP Probe Indicator(s) remain off.
(3) Make sure the TAT Probe heater is on, the TAT Probe will get hot.
(4) Limit the test time to 20 seconds (holding the TAT Test switch).
3) Stop Engine 1. Refer to 737-300/400/500 AMM 71-00-00 as an accepted
procedure.
4) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module
turn ON.
5) Start Engine 2. Refer to 737-300/400/500 AMM 71-00-00 as an accepted
procedure.
6) Make sure all the probe heat indicators on the P5-9 Window and Pitot Heat
Module turn OFF.
NOTE: If TAT Test switch is installed do as follows:
(1) Press and hold the TAT Test switch.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
49 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 50

(2) Make sure the TEMP Probe Indicator(s) remain off.
(3) Make sure the TAT Probe heater is on, the TAT Probe will get hot.
(4) Limit the test time to 20 seconds (holding the TAT Test switch).
7) Stop Engine 2. Refer to 737-300/400/500 AMM 71-00-00 as an accepted
procedure.
8) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module
turn ON.
ALL AIR DATA PROBES WILL BE HOT WHEN RUNNING TESTS
WITH PROBE HEAT SWITCHES A AND B IN THE AUTO POSITION
AND CONNECTOR D752 FROM EITHER SWITCH S124 WITH
PINS 1 AND 2 CONNECTED.
WARNING
(b) OPTION 12: CONNECTOR METHOD
1) Disconnect connector D752 from S124 Engine-1 Low Oil Pressure Switch. Refer
to 737-300/400/500 WDM 79-34-11.
2) Connect jumper wires between Pins 1 and 2 of Connector D752. Refer to
737-300/400/500 WDM 79-34-11.
3) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module
turn OFF.
NOTE: If TAT Test switch is installed do as follows:
(1) Press and hold the TAT Test switch.
(2) Make sure the TEMP Probe Indicator(s) remain off.
(3) Make sure the TAT Probe heater is on, the TAT Probe will get hot.
(4) Limit the test time to 20 seconds (holding the TAT Test switch).
4) Remove jumper wire between Pins 1 and 2 of Connector D752. Refer to
737-300/400/500 WDM 79-34-11.
5) Connect connector D752 to S124 Engine-1 Low Oil Pressure Switch. Refer to
737-300/400/500 WDM 79-34-11.
6) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module
turn ON.
7) Disconnect connector D752 from S124 Engine-2 Low Oil Pressure Switch. Refer
to 737-300/400/500 WDM 79-34-11.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
50 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 51

8) Connect jumper wires between Pins 1 and 2 of Connector D752. Refer to
737-300/400/500 WDM 79-34-11.
9) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module
turn OFF.
NOTE: If TAT Test switch is installed do as follows:
(1) Press and hold the TAT Test switch.
(2) Make sure the TEMP Probe Indicator(s) remain off.
(3) Make sure the TAT Probe heater is on, the TAT Probe will get hot.
(4) Limit the test time to 20 seconds (holding the TAT Test switch).
10) Remove jumper wire between Pins 1 and 2 of Connector D752. Refer to
737-300/400/500 WDM 79-34-11.
11) Connect connector D752 to S124 Engine-2 Low Oil Pressure Switch. Refer to
737-300/400/500 WDM 79-34-11.
12) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module
turn ON.
g. Put the airplane back to a serviceable condition.
Group 3:
1. Remove electrical power from the airplane. Refer to 737-300/400/500 AMM 24-22-00 as an
accepted procedure.
2. Open the following circuit breakers and install circuit breaker locks and DO-NOT-CLOSE tags.
PanelCircuit Breaker NomenclatureCircuit Breaker Number
P6 PANELMSTR CAUTION - ANTI-ICEC00573
P6 PANELPITOT STATIC INDICATION - F/OC00570
P6 PANELPITOT STATIC INDICATION - CAPTC00569
P6 PANELR FRONT WINDOW ANTI-ICEC00394
P6 PANELL FRONT WINDOW ANTI-ICEC00228
P6 PANELR SIDE WINDOW ANTI-ICEC00393
P6 PANELL SIDE WINDOW ANTI-ICEC00392
P6 PANELRIGHT NO. 4 AND NO. 5 WINDOW ANTI-ICEC00395
P6 PANELLEFT NO. 4 AND NO. 5 WINDOW ANTI-ICEC00229
P18 PANELCAPT - UPPER LC00523
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
51 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 52

PanelCircuit Breaker NomenclatureCircuit Breaker Number
P18 PANELCAPT - LWR RC00524
P18 PANELF/O UPPER RC00525
P18 PANELF/O LWR LC00522
P18 PANELELEVATOR PITOT - RC00237
P18 PANELELEVATOR PITOT - LC00236
P18 PANELTEMP PROBEC00238
P18 PANELALPHA VANE HTR - RC01071
P18 PANELALPHA VANE HTR - LC01072
P18 PANELRIGHT FRONT ACC00226
P18 PANELRIGHT FRONT DCC00222
P18 PANELRIGHT SIDE ACC00227
P18 PANELRIGHT SIDE DCC00223
P18 PANELLEFT FRONT ACC00224
P18 PANELLEFT FRONT DCC00220
P18 PANELLEFT SIDE ACC00225
P18 PANELLEFT SIDE DCC00221
3. Access the P5 overhead panel in the flight compartment.
DO NOT TOUCH ELECTRICAL CONNECTOR UNTIL INSTRUCTED BY THE
PROCEDURE. THE MODULE IS SENSITIVE TO THE ELECTROSTATIC
DISCHARGE. ELECTROSTATIC DISCHARGE CAN CAUSE DAMAGE TO THE
MODULE. INJURY TO PERSONNEL OR DAMAGE TO EQUIPMENT CAN OCCUR.
CAUTION
4. RC - Replace the P5-9 window and pitot heat module in accordance with FIGURE 2.
5. Remove INOP markers and collars on the P18-3 circuit breaker panel in accordance with FIGURE
5 or FIGURE 7.
NotesPanelCircuit Breaker NomenclatureCircuit Breaker Number
(a)P18-3 CIRCUIT BREAKER
PANEL
PROBE HEAT CAPTC1946
(a)P18-3 CIRCUIT BREAKER
PANEL
PROBE HEAT F/OC1947
(a) An option is provided to allow operators to use available circuit breaker positions.
6. Close the following circuit breakers and remove circuit breaker locks and DO-NOT-CLOSE tags.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
52 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 53

PanelCircuit Breaker NomenclatureCircuit Breaker Number
P6 PANELMSTR CAUTION - ANTI-ICEC00573
P6 PANELPITOT STATIC INDICATION - F/OC00570
P6 PANELPITOT STATIC INDICATION - CAPTC00569
P6 PANELR FRONT WINDOW ANTI-ICEC00394
P6 PANELL FRONT WINDOW ANTI-ICEC00228
P6 PANELR SIDE WINDOW ANTI-ICEC00393
P6 PANELL SIDE WINDOW ANTI-ICEC00392
P6 PANELRIGHT NO. 4 AND NO. 5 WINDOW ANTI-
ICE
C00395
P6 PANELLEFT NO. 4 AND NO. 5 WINDOW ANTI-
ICE
C00229
P18 PANELCAPT - UPPER LC00523
P18 PANELCAPT - LWR RC00524
P18 PANELF/O UPPER RC00525
P18 PANELF/O LWR LC00522
P18 PANELELEVATOR PITOT - RC00237
P18 PANELELEVATOR PITOT - LC00236
P18 PANELTEMP PROBEC00238
P18 PANELALPHA VANE HTR - RC01071
P18 PANELALPHA VANE HTR - LC01072
P18 PANELRIGHT FRONT ACC00226
P18 PANELRIGHT FRONT DCC00222
P18 PANELRIGHT SIDE ACC00227
P18 PANELRIGHT SIDE DCC00223
P18 PANELLEFT FRONT ACC00224
P18 PANELLEFT FRONT DCC00220
P18 PANELLEFT SIDE ACC00225
P18 PANELLEFT SIDE DCC00221
ALL PROTECTIVE CAPS AND COVERS MUST BE REMOVED FROM ALL AIR
DATA PROBES. AIR DATA PROBES AND COVERS COULD BE DAMAGED IF
THERE ARE COVERS INSTALLED ON THE AIR DATA PROBES WHEN THEY
ARE HEATED.
CAUTION
7. Remove any installed protective caps or covers on pitot probes, outside air temperature probe,
and alpha vanes.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
53 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 54

8. Make sure the following circuit breakers are closed.
More DataPanelCircuit Breaker NomenclatureCircuit Breaker Number
(a)P6 PANELENG 1 T/R CONT SYSC00276
(a)P6 PANELENG 2 T/R CONT SYSC00277
(a)P6 PANELENG 2 T/R CONT ALTNC00175
(a)P6 PANELENG 1 T/R IND SYSC01003
(a)P6 PANELENG 2 T/R IND SYSC01004
(a) If installed.
9. Make sure the battery switch on the P5-13 Electrical Meter Battery and Galley Power Panel is set
ON.
10. Make sure Engine 1 Fire Switch and Engine 2 Fire Switch on the P8-1 Engine and Fire Control
Panel are pushed in.
DO NOT TOUCH THE AIR DATA PROBES WHILE THE HEATERS ARE ON. FEEL
FOR HEAT RADIATION FROM THE AIR DATA PROBES IN THE VICINITY OF
THE AIR DATA PROBES. HOT AIR DATA PROBES CAN CAUSE BURN INJURIES.
WARNING
DO NOT OPERATE ANY HEATER FOR MORE THAN 5 MINUTES. THE LIFE OF
THE HEATER WOULD DECREASE IF IT STAYS ON FOR MORE THAN 5
MINUTES.
CAUTION
11. Supply electrical power to the airplane. Refer to 737-300/400/500 AMM 24-22-00 as an accepted
procedure.
12. RC - Do Pitot-Static Tubes, Temperature Probe and Alpha Vane Anti-Icing System Test as follows:
if the test fails, do corrective action(s), repeat the test, and do applicable corrective action(s) until
the operational test passes.
NOTE: The master caution indicators might turn on for the test below. Cancel master caution,
as necessary, throughout the test.
a. Make sure the engines are turned off. Refer to 737-300/400/500 AMM 71-00-00 as an accepted
procedure.
b. Set Switch A and B on the P5-9 Window and Pitot Heat Module to ON position and make sure
all probe heat indicators on the P5-9 Window and Pitot Heat Module turn OFF.
c. Set Switch A and B on the P5-9 Window and Pitot Heat Module to AUTO position and make
sure all probe heat indicators on the P5-9 Window and Pitot Heat Module turn ON.
d. Do one of the following options to test probe heat indicators:
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
54 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 55

ALL AIR DATA PROBES WILL BE HOT WHEN RUNNING TESTS WITH
PROBE HEAT SWITCHES A AND B IN THE AUTO POSITION AND
EITHER ENGINE RUNNING.
WARNING
(1) OPTION 5: ENGINE CYCLE METHOD
(a) Start Engine 1. Refer to 737-300/400/500 AMM 71-00-00 as an accepted procedure.
(b) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module turn
OFF.
NOTE: If TAT Test switch is installed do as follows:
(1) Press and hold the TAT Test switch.
(2) Make sure the TEMP Probe Indicator(s) remain off.
(3) Make sure the TAT Probe heater is on, the TAT Probe will get hot.
(4) Limit the test time to 20 seconds (holding the TAT Test switch).
(c) Stop Engine 1. Refer to 737-300/400/500 AMM 71-00-00 as an accepted procedure.
(d) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module turn
ON.
(e) Start Engine 2. Refer to 737-300/400/500 AMM 71-00-00 as an accepted procedure.
(f) Make sure all the probe heat indicators on the P5-9 Window and Pitot Heat Module
turn OFF.
NOTE: If TAT Test switch is installed do as follows:
(1) Press and hold the TAT Test switch.
(2) Make sure the TEMP Probe Indicator(s) remain off.
(3) Make sure the TAT Probe heater is on, the TAT Probe will get hot.
(4) Limit the test time to 20 seconds (holding the TAT Test switch).
(g) Stop Engine 2. Refer to 737-300/400/500 AMM 71-00-00 as an accepted procedure.
(h) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module turn
ON.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
55 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 56

ALL AIR DATA PROBES WILL BE HOT WHEN RUNNING TESTS WITH
PROBE HEAT SWITCHES A AND B IN THE AUTO POSITION AND
CONNECTOR D752 FROM EITHER SWITCH S124 WITH PINS 1 AND
2 CONNECTED.
WARNING
(2) OPTION 6: CONNECTOR METHOD
(a) Disconnect connector D752 from S124 Engine-1 Low Oil Pressure Switch. Refer to
737-300/400/500 WDM 79-34-11.
(b) Connect jumper wires between Pins 1 and 2 of Connector D752. Refer to
737-300/400/500 WDM 79-34-11.
(c) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module turn
OFF.
NOTE: If TAT Test switch is installed do as follows:
(1) Press and hold the TAT Test switch.
(2) Make sure the TEMP Probe Indicator(s) remain off.
(3) Make sure the TAT Probe heater is on, the TAT Probe will get hot.
(4) Limit the test time to 20 seconds (holding the TAT Test switch).
(d) Remove jumper wire between Pins 1 and 2 of Connector D752. Refer to
737-300/400/500 WDM 79-34-11.
(e) Connect connector D752 to S124 Engine-1 Low Oil Pressure Switch. Refer to
737-300/400/500 WDM 79-34-11.
(f) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module turn
ON.
(g) Disconnect connector D752 from S124 Engine-2 Low Oil Pressure Switch. Refer to
737-300/400/500 WDM 79-34-11.
(h) Connect jumper wires between Pins 1 and 2 of Connector D752. Refer to
737-300/400/500 WDM 79-34-11.
(i) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module turn
OFF.
NOTE: If TAT Test switch is installed do as follows:
(1) Press and hold the TAT Test switch.
(2) Make sure the TEMP Probe Indicator(s) remain off.
(3) Make sure the TAT Probe heater is on, the TAT Probe will get hot.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
56 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 57

(4) Limit the test time to 20 seconds (holding the TAT Test switch).
(j) Remove jumper wire between Pins 1 and 2 of Connector D752. Refer to
737-300/400/500 WDM 79-34-11.
(k) Connect connector D752 to S124 Engine-2 Low Oil Pressure Switch. Refer to
737-300/400/500 WDM 79-34-11.
(l) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module turn
ON.
13. Do Operational Test - Control Cabin Window Anti-Icing System. Refer to 737-300/400/500 AMM
30-41-00 as an accepted procedure.
14. Put the airplane back to a serviceable condition.
15. Do repetitive Pitot-Static Tubes, Temperature Probe and Alpha Vane Anti-Icing System Test, as
follows, at the times specified in Paragraph 1.E., Compliance.
ALL PROTECTIVE CAPS AND COVERS MUST BE REMOVED FROM ALL
AIR DATA PROBES. AIR DATA PROBES AND COVERS COULD BE
DAMAGED IF THERE ARE COVERS INSTALLED ON THE AIR DATA
PROBES WHEN THEY ARE HEATED.
CAUTION
a. Remove any installed protective caps or covers on pitot probes, outside air temperature probe,
and alpha vanes.
b. Make sure the following circuit breakers are closed.
More DataPanelCircuit Breaker NomenclatureCircuit Breaker Number
(a)P6 PANELENG 1 T/R CONT SYSC00276
(a)P6 PANELENG 2 T/R CONT SYSC00277
(a)P6 PANELENG 2 T/R CONT ALTNC00175
(a)P6 PANELENG 1 T/R IND SYSC01003
(a)P6 PANELENG 2 T/R IND SYSC01004
(a) If installed.
c. Make sure the battery switch on the P5-13 Electrical Meter Battery and Galley Power Panel
is set ON.
d. Make sure Engine 1 Fire Switch and Engine 2 Fire Switch on the P8-1 Engine and Fire Control
Panel are pushed in.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
57 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 58

DO NOT TOUCH THE AIR DATA PROBES WHILE THE HEATERS ARE ON.
FEEL FOR HEAT RADIATION FROM THE AIR DATA PROBES IN THE
VICINITY OF THE AIR DATA PROBES. HOT AIR DATA PROBES CAN CAUSE
BURN INJURIES.
WARNING
DO NOT OPERATE ANY HEATER FOR MORE THAN 5 MINUTES.THE LIFE
OF THE HEATER WOULD DECREASE IF IT STAYS ON FOR MORE THAN
5 MINUTES.
CAUTION
e. Supply electrical power to the airplane. Refer to 737-300/400/500 AMM 24-22-00 as an
accepted procedure.
f. RC - Do Pitot-Static Tubes, Temperature Probe and Alpha Vane Anti-Icing System Test as
follows: if the test fails, do corrective action(s), repeat the test, and do applicable corrective
action(s) until the operational test passes.
NOTE: The master caution indicators might turn on for the test below. Cancel master caution,
as necessary, throughout the test.
(1) Make sure the engines are turned off. Refer to 737-300/400/500 AMM 71-00-00 as an
accepted procedure.
(2) Set Switch A and B on the P5-9 Window and Pitot Heat Module to ON position and make
sure all probe heat indicators on the P5-9 Window and Pitot Heat Module turn OFF.
(3) Set Switch A and B on the P5-9 Window and Pitot Heat Module to AUTO position and
make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module turn ON.
(4) Do one of the following options to test probe heat indicators:
ALL AIR DATA PROBES WILL BE HOT WHEN RUNNING TESTS
WITH PROBE HEAT SWITCHES A AND B IN THE AUTO POSITION
AND EITHER ENGINE RUNNING.
WARNING
(a) OPTION 13: ENGINE CYCLE METHOD
1) Start Engine 1. Refer to 737-300/400/500 AMM 71-00-00 as an accepted
procedure.
2) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module
turn OFF.
NOTE: If TAT Test switch is installed do as follows:
(1) Press and hold the TAT Test switch.
(2) Make sure the TEMP Probe Indicator(s) remain off.
(3) Make sure the TAT Probe heater is on, the TAT Probe will get hot.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
58 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 59

(4) Limit the test time to 20 seconds (holding the TAT Test switch).
3) Stop Engine 1. Refer to 737-300/400/500 AMM 71-00-00 as an accepted
procedure.
4) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module
turn ON.
5) Start Engine 2. Refer to 737-300/400/500 AMM 71-00-00 as an accepted
procedure.
6) Make sure all the probe heat indicators on the P5-9 Window and Pitot Heat
Module turn OFF.
NOTE: If TAT Test switch is installed do as follows:
(1) Press and hold the TAT Test switch.
(2) Make sure the TEMP Probe Indicator(s) remain off.
(3) Make sure the TAT Probe heater is on, the TAT Probe will get hot.
(4) Limit the test time to 20 seconds (holding the TAT Test switch).
7) Stop Engine 2. Refer to 737-300/400/500 AMM 71-00-00 as an accepted
procedure.
8) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module
turn ON.
ALL AIR DATA PROBES WILL BE HOT WHEN RUNNING TESTS
WITH PROBE HEAT SWITCHES A AND B IN THE AUTO POSITION
AND CONNECTOR D752 FROM EITHER SWITCH S124 WITH
PINS 1 AND 2 CONNECTED.
WARNING
(b) OPTION 14: CONNECTOR METHOD
1) Disconnect connector D752 from S124 Engine-1 Low Oil Pressure Switch. Refer
to 737-300/400/500 WDM 79-34-11.
2) Connect jumper wires between Pins 1 and 2 of Connector D752. Refer to
737-300/400/500 WDM 79-34-11.
3) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module
turn OFF.
NOTE: If TAT Test switch is installed do as follows:
(1) Press and hold the TAT Test switch.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
59 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

### Page 60

(2) Make sure the TEMP Probe Indicator(s) remain off.
(3) Make sure the TAT Probe heater is on, the TAT Probe will get hot.
(4) Limit the test time to 20 seconds (holding the TAT Test switch).
4) Remove jumper wire between Pins 1 and 2 of Connector D752. Refer to
737-300/400/500 WDM 79-34-11.
5) Connect connector D752 to S124 Engine-1 Low Oil Pressure Switch. Refer to
737-300/400/500 WDM 79-34-11.
6) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module
turn ON.
7) Disconnect connector D752 from S124 Engine-2 Low Oil Pressure Switch. Refer
to 737-300/400/500 WDM 79-34-11.
8) Connect jumper wires between Pins 1 and 2 of Connector D752. Refer to
737-300/400/500 WDM 79-34-11.
9) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module
turn OFF.
NOTE: If TAT Test switch is installed do as follows:
(1) Press and hold the TAT Test switch.
(2) Make sure the TEMP Probe Indicator(s) remain off.
(3) Make sure the TAT Probe heater is on, the TAT Probe will get hot.
(4) Limit the test time to 20 seconds (holding the TAT Test switch).
10) Remove jumper wire between Pins 1 and 2 of Connector D752. Refer to
737-300/400/500 WDM 79-34-11.
11) Connect connector D752 to S124 Engine-2 Low Oil Pressure Switch. Refer to
737-300/400/500 WDM 79-34-11.
12) Make sure all probe heat indicators on the P5-9 Window and Pitot Heat Module
turn ON.
g. Put the airplane back to a serviceable condition.
Group 4:
1. Remove electrical power from the airplane. Refer to 737-300/400/500 AMM 24-22-00 as an
accepted procedure.
2. Open the following circuit breakers and install circuit breaker locks and DO-NOT-CLOSE tags.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 04, 2017
737-30A1064Revision 2: June 26, 2020
60 of 84
BOEING SERVICE BULLETIN 737-30A1064
ALERTALERT

The text continues at https://openairdocs.org/service-documents/boeing/737-30a1064/file/8b3dcbff995f.md?from=61

---
OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.