# Boeing Alert Service Bulletin 717-30A0009: No revision named

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2020-0467; AD 2021-02-16 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Alert Service Bulletin 717-30A0009](https://openairdocs.org/service-documents/boeing/717-30a0009.md)
- Title as filed: SB 717-30A0009
- Pages: 29
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## Text

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### Page 1

Commercial
Airplanes
717
Service Bulletin
ALERT
Number: 717-30A0009
Original Issue: March 31, 2020
ATA System: 3030
SUBJECT: ICE AND RAIN PROTECTION - Air Data Sensor Heating - Air Data Heat System Wiring
Change
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 © 2020 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Unpublished Work.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.
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Table of Contents
S u m m a r y ...................................................... 5
1. PLANNING INFORMATION ........................................ 9
A . E f f e c t i v i t y ................................................ 9
1. Airplanes ............................................. 9
2 . S p a r e s  A f f e c t e d  ......................................... 9
B. Concurrent Requirements ...................................... 1 0
C. Reason ................................................ 1 0
D. Description .............................................. 1 0
E. Compliance .............................................. 1 1
F . A p p r o v a l............................................... 1 1
G. Manpower .............................................. 1 1
H. Weight and Balance Changes .................................... 1 1
I. Electrical Load Data ......................................... 1 2
J . R e f e r e n c e s .............................................. 1 2
1. Existing Data: ......................................... 1 2
2. Data Supplied with this Service Bulletin: ........................... 1 2
3. Installation Drawings Used in the Preparation of this Service  Bulletin: ........... 1 2
K. Publications Affected ........................................ 1 2
L. Interchangeability and Intermixability of Parts ........................... 1 3
M. Software Accomplishment Summary ................................ 1 3
2. MATERIAL INFORMATION ........................................ 1 5
A. Material - Price and Availability ................................... 1 5
B. Industry Support Information .................................... 1 5
C . P a r t s  N e c e s s a r y  f o r  E a c h  A i r p l a n e  ................................. 1 5
1 . K i t s / P a r t s............................................ 1 5
2. Parts and Materials Supplied by the Operator ........................ 1 6
3. Parts Modified and Reidentified ................................ 1 6
4. Parts Removed and Not Replaced .............................. 1 6
D. Parts Necessary to Change Spares ................................. 1 6
E. Special Tooling - Price and Availability ............................... 1 7
F. Special Tooling Necessary to do this Service Bulletin ....................... 1 7
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 1 9
A. GENERAL INFORMATION ..................................... 1 9
B. WORK INSTRUCTIONS ....................................... 2 1
FIGURE 1: ELECTRICAL/ELECTRONICS COMPARTMENT - STA 110 RELAY PAN EL AND AFT RIGHT
R A D I O  R A C K  -  W I R I N G  C H A N G E .............................. 2 7
APPENDIX A: PART DEMAND INTENT ................................... 2 9
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Commercial
Airplanes
717
Service Bulletin
ALERT
SummaryNumber: 717-30A0009Original Issue: March 31, 2020
ATA System: 3030
SUBJECT: ICE AND RAIN PROTECTION - Air Data Sensor Heating - Air Data Heat System Wiring
Change
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
An operator reported that during takeoff, both the captain's and first officer's airspeed indications froze at 80
knots. The captain made the decision to continue the takeoff which resulted in an overboost of both engines.
The flight was diverted to an alternate airport. A review of the weather at the departure airport indicated an
Outside Air Temperature (OAT) of 25 degrees Fahrenheit and wind at approximately 20 knots in light snow. The
airplane had been waiting in this weather condition for about two hours for de-icing before takeoff. A review of
the flight data recorder from this event indicated the airspeed became irregular and could not be read during
takeoff until the airplane reached 6000 feet Above Ground Level (AGL). The recorded data also indicated that
the pitot tube was possibly blocked with ice. If this service bulletin is not done, then the captain or first officer
may fail to activate the Air Data Heat (ADH) System which can result in unsafe flight conditions.
This service bulletin gives instructions to change the ADH system. The new certified ADH system will display
ADH Level 1 alerts with the master caution light. The alerts will be displayed when the left or right or both engine
fuel switches are in the ON position and the ADH system is not on. This method does not change the current
operation of the ADH system by the flight crew or crew's response to ADH system annunciations. The flight crew
must then manually activate the ADH system.
Boeing Service Related Problem (SRP) 717-SRP-30-0052 is related to this service bulletin.
Boeing Fleet Team Digest (FTD) 717 FTD 30-15001 is related to this service bulletin.
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
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ReferenceAffectedPlanning Data
Paragraph 1.E., Compliance and Paragraph
1.F., Approval
YesAD Related
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 AffectedNoAirplane Flight Operations Affected (Flight Crew
Operations Manual and/or FAA Approved Air-
plane Flight Manual)
Paragraph 2.C.1., Kits/PartsYesKits/Parts Required
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
YesOperator Supplied Parts/Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
ACTION
In the electrical/electronics compartment, install new wires between the STA 110 relay panel and the left radio
rack. Do tests.
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
717-200 Airplane(s). Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s).
COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service
bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin
mandatory.
Boeing recommends that the change given in this service bulletin be done within 27 months, or within 3944 flight
hours, after the original issue date of this service bulletin, whichever occurs first.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the changes given in this service bulletin.
MANPOWER
Elapsed HoursTotal Task HoursAirplanes
7.411.1Group 1
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MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Operator Supplied Parts/Materials.
Refer to Paragraph 2.A., Material - Price and Availability.
Operators are encouraged to complete the survey provided in APPENDIX A of this service bulletin to help Boeing
predict the quantity and timing of the Boeing Supplied Kits/Parts.
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Commercial
Airplanes
717
Service Bulletin
ALERT
Number: 717-30A0009
Original Issue: March 31, 2020
ATA System: 3030
SUBJECT: ICE AND RAIN PROTECTION - Air Data Sensor Heating - Air Data Heat System Wiring
Change
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 717-200 Airplane(s), line number(s) 5002-5156 in 2 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.
This service bulletin is for the airplanes shown below.
DESCRIPTIONCONFIGURATIONGROUP
Airplanes with concurrent requirement.-1
Airplanes with no concurrent requirement.-2
Airplane Models:
717-200
GroupFuselage Number
15002 - 5099
GroupFuselage Number
15100 - 5146
GroupFuselage Number
25147 - 5156
2. Spares Affected
None.
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B. Concurrent Requirements
Group 1:
The service bulletin(s) listed below must be done before or at the same time as this service bulletin:
Group 1:
DescriptionService BulletinCompany
Change the first officer's Pitot Heat System wiring.717-30A0003 Original Issue, Revision 1
or Revision 2
Boeing
Group 2:
None.
C. Reason
An operator reported that during takeoff, both the captain's and first officer's airspeed indications froze
at 80 knots. The captain made the decision to continue the takeoff which resulted in an overboost of
both engines. The flight was diverted to an alternate airport. A review of the weather at the departure
airport indicated an Outside Air Temperature (OAT) of 25 degrees Fahrenheit and wind at approximately
20 knots in light snow. The airplane had been waiting in this weather condition for about two hours for
de-icing before takeoff. A review of the flight data recorder from this event indicated the airspeed
became irregular and could not be read during takeoff until the airplane reached 6000 feet Above
Ground Level (AGL). The recorded data also indicated that the pitot tube was possibly blocked with
ice. If this service bulletin is not done, then the captain or first officer may fail to activate the Air Data
Heat (ADH) System which can result in unsafe flight conditions.
This service bulletin gives instructions to change the ADH system. The new certified ADH system will
display ADH Level 1 alerts with the master caution light. The alerts will be displayed when the left or
right or both engine fuel switches are in the ON position and the ADH system is not on. This method
does not change the current operation of the ADH system by the flight crew or crew's response to ADH
system annunciations. The flight crew must then manually activate the ADH system.
Boeing Service Related Problem (SRP) 717-SRP-30-0052 is related to this service bulletin.
Boeing Fleet Team Digest (FTD) 717 FTD 30-15001 is related to this service bulletin.
D. Description
In the electrical/electronics compartment, install new wires between the STA 110 relay panel and the
left radio rack. Do tests.
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.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
114, 211717-200
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E. Compliance
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to
this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this
service bulletin mandatory.
Boeing recommends that the change given in this service bulletin be done within 27 months, or within
3944 flight hours, after the original issue date of this service bulletin, whichever occurs first.
F. Approval
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified
in this service bulletin comply with the applicable regulations and are FAA approved, as well as European
Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved
airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on
the airplane in its original Boeing delivery configuration or as modified by other approved Boeing
changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
G. Manpower
The table below shows an estimate of the task hours necessary to do this change for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
• Time to adjust to the workplace
• Time to schedule the work
• Time to inspect the work
• Time to cure the materials
• Time to make the parts
• Time to find the tools
Elapsed HoursTask HoursNumber of PersonsTask
0.10.11Open Access
3.53.51FIGURE 1
3.77.42Test
0.10.11Close Access
7.411.1TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
None.
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I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Boeing Service Bulletin 717-30A0003
b. Standard Overhaul Practices Manual (SOPM) 20-50-01
c. Standard Wiring Practices Manual (SWPM) 20-00-03, 20-00-09, 20-00-13, 20-00-16, 20-10-01,
20-10-04, 20-20-01, 20-20-03, 20-50-01
d. Boeing Service Related Problem (SRP) 717-SRP-30-0052
e. 717 Aircraft Maintenance Manual (AMM) 24-00-00, 30-31-00
f. 717 Fleet Team Digest (FTD) 30-15001
g. 717 Structural Repair Manual (SRM) 51
h. 717 Wiring Diagram Manual (WDM) 30-31-01, 74-10-01, 74-10-02
2. Data Supplied with this Service Bulletin:
a. Drawings:
ADCNDCN/REVSheetTypeTitleDrawing No
-NEW-DWGENHANCED ACTUATION OF
THE AIR DATA HEAT (ADH)
SYSTEM SERVICE REWORK
DRAWING
SR95300005
3. Installation Drawings Used in the Preparation of this Service  Bulletin:
None
K. Publications Affected
1. Publications:
Chapter-SectionPublication
30-30, 76-13System Schematic Manual
30-31, 74-10Wiring Diagram Manual
2. Damage Tolerance Based Structural Inspections:
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Boeing has evaluated the repairs 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
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
M. Software Accomplishment Summary
Not affected.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators
are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin.
The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.
Prices are in United States Dollars. Terms: Net 30 days.
Reference this service bulletin and submit your purchase order by one of these methods:
1. Order on-line via ATA Spec 2000 or The Boeing PART Page
2. Fax to (206) 662-7145
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NameKit Number
4,863.00120ENHANCED ACTUATION OF THE AIR
DATA HEAT (ADH) SYSTEM
SA95300009-3
Operators are encouraged to complete the survey provided in APPENDIX A of this service bulletin to
help Boeing predict the quantity and timing of the Boeing Supplied Kits/Parts.
B. Industry Support Information
Boeing warranty remedies are not available for the changes given in this service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts
To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by
the Operator, are necessary for each airplane.
Kit SA95300009
NotesNameQTYNew Part Number
-7001-102-101-3
ENHANCED ACTUATION OF THE
AIR DATA HEAT (ADH) SYSTEM
1---SA95300009-3
WIRE KIT---1SA95300009-101
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Kit SA95300009
NotesNameQTYNew Part Number
-7001-102-101-3
WIRE KIT---1SA95300009-102
(a)TERMINAL LUG 878-2--5D0086-3
(a)SEALING PLUG---15D0206-20
(a)(b)STA-STRAP---1009D0254-1-1-9
IN-LINE JUNCTION---1CTM-20-090
(a)SKT T/C 1123-4--DC39-16S
(c)WIRE CODE 801--1-D2426-1C-20NM
(c)WIRE CODE 801-4--D2426-1C-22NM
(a)SOCKET T/C 524-21-M39029/22-192
(a)CONTACT TC 542/546--1-M39029/22-193
(a) Refer to AEPL, Drawing 7595071 for approved equivalent.
(b) There might be more parts than necessary.
(c) Refer to Service Rework Drawing SR95300005 for wire numbers and lengths.
2. Parts and Materials Supplied by the Operator
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.
NotesNameQTYPart Number / Specification
(a)TAPE PRESSURE SENSITIVE ADHESIVE,
WRAP ON LABEL
2DMS 2359, TYPE 2, CLASS B
(a) Use the quantity needed to do the changes given in this service bulletin.
3. Parts Modified and Reidentified
None.
4. Parts Removed and Not Replaced
None.
D. Parts Necessary to Change Spares
None.
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E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
IF ELECTRICAL POWER IS APPLIED TO THE AIRPLANE, MAKE SURE YOU
OBEY ALL PRECAUTIONS WHILE YOU DO WORK. IF YOU DO NOT OBEY THE
PRECAUTIONS, DEATH OR INJURY TO PERSONS, AND DAMAGE TO THE
AIRPLANE CAN OCCUR.WARNING
ELECTRICALLY GROUND THE AIRPLANE. THIS WILL HELP TO PREVENT
DAMAGE TO THE AIRPLANE OR EQUIPMENT.CAUTION
KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF
METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED
MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE
BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES
CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE.
CAUTION
NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph  1.J., References, for
definition of the acronyms.
2. Equivalent parts are listed in the AEPL, Drawing 7595071.
3. Use the approved fastener and process material substitutions,  in accordance with
717 SRM 51.
4. If the length of any fastener specified in this service bulle tin does not meet installation
standards given in Structural Repair Manual (SRM) Chapter 51, then a fastener of
the same specification, or an approved substitute, with a length which meets the
installation standards given in SRM Chapter 51 may be used. In addition, washers
may be installed for fastener grip length in accordance with SRM Chapter 51. Refer
to SOPM 20-50-01 for alternate full threaded fasteners (screws) needed for installation
in this service bulletin.
5. 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 are in 717 SRM 51
– Torque Values:
— Values for structural fasteners are given in 717 Structural Repair Manual,
Chapter 51.
— Values for airframe maintenance tasks are included in Chapter 20 of 717
Aircraft Maintenance Manual (AMM).
— Values for electrical maintenance tasks are included in Chapter 20 of
Standard Wiring Practices Manual (SWPM).
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— Values for engine maintenance tasks are included in Chapter 70 of 717
Aircraft Maintenance Manual (AMM).
— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
6. Refer to the SWPM 20-10-01 as accepted wire installation proc edures.
Refer to these SWPM chapters for applicable operations, as accepted procedures:
Identification of electrical wires, refer to SWPM 20-00-03 as an accepted procedure.
Electrical wire end terminal codes, refer to SWPM 20-00-16 as an accepted procedure.
Alternative wire type list, refer to SWPM 20-00-13 as an accepted procedure.
Wiring Installation, refer to SWPM 20-10-01 as an accepted procedure.
Coil and stow excess wire length, refer to SWPM 20-10-04 as an accepted procedure.
String tie wires, refer to SWPM 20-10-01 as an accepted procedure.
Electrical identification and shop practice, refer to SWPM 20-00-09 as an accepted
procedure.
Installation of STA strap to existing wire bundle, refer to SWPM 20-10-01 as an
accepted procedure.
Terminals - maintenance practices, refer to SWPM 20-20-01 as an accepted
procedure.
Rivnut grounds and hardware installation, refer to SWPM 20-20-03 as an accepted
procedure.
Electrical bonding, refer to SWPM 20-50-01 as an accepted procedure.
7. Obey all of the warnings and cautions given in the specified manual sections.
8. 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.
9. If it is necessary to remove more parts for access, you can r emove 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.
10. This service bulletin includes functional test procedures fo r 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.
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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.
B. WORK INSTRUCTIONS
1. Remove electrical power from the airplane. Refer to 717 AMM 24-00-00 as an accepted procedure.
2. Get access to the electrical/electronics compartment.
3. RC - Install new wires and in-line junction between the STA 110 relay panel and the left radio rack
as follows:
DocumentChange
In accordance with FIGURE 1.Wiring
In accordance with Service Rework Drawing
SR95300005, sheets 6.0 through 6.4.
Routing and Clipping
4. Supply electrical power to the airplane. Refer to 717 AMM 24- 00-00 as an accepted procedure.
5. RC - Do the test that follows:
a. RC - Exempt. Make sure that no covers are installed on any of  the air data sensors.
b. RC - Exempt. Get access to the flight compartment.
c. RC - Exempt. In the Electrical Power Center (EPC), lower pane l, open the circuit breakers
that follow, attach circuit breaker collars and DO-NOT-CLOSE tags, and make sure the system
is in a zero energy state:
NomenclatureRow/ColumnNumber
FIRE EXTINGUISHING CONTROL BOTTLE 1X/41B1-95
FIRE EXTINGUISHING CONTROL BOTTLE 2X/42B1-96
d. RC - Exempt. Pull the left and right fire control handles to prevent fuel flow to the engines.
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e. Air Data Heat (ADH) Followed by Left and Right Fuel Switches:
(1) Make sure that the AIR DATA HEAT switch, left FUEL switch and right FUEL switch are
in the OFF position.
(2) Make sure that no ADH related alerts other than AIR DATA HEAT OFF is shown on the
MISCELLANEOUS page of the Systems Display (SD).
(3) Set the AIR DATA HEAT switch to the ON position. Make sure that no ADH related alerts
are shown on the MISCELLANEOUS page of the SD.
(4) Set the left FUEL switch to the ON position. Make sure that no ADH related alerts are
shown on the MISCELLANEOUS page of the SD.
(5) Set the right FUEL switch to the ON position. Make sure that no ADH related alerts are
shown on the MISCELLANEOUS page of the SD.
(6) Set the left FUEL switch to the OFF position. Make sure that no ADH related alerts are
shown on the MISCELLANEOUS page of the SD.
(7) Set the right FUEL switch to the OFF position. Make sure that no ADH related alerts are
shown on the MISCELLANEOUS page of the SD.
(8) Set the AIR DATA HEAT switch to the OFF position. Make sure that no ADH related
alerts other than AIR DATA HEAT OFF is shown on the MISCELLANEOUS page of the
SD.
f. Left Fuel Switch Followed by ADH Switch:
(1) Make sure that the AIR DATA HEAT switch, left FUEL switch and right FUEL switch are
in the OFF position.
(2) Make sure that no ADH related alerts other than AIR DATA HEAT OFF is shown on the
MISCELLANEOUS page of the SD.
(3) Set the left FUEL switch to the ON position and do the following:
(a) Make sure that the ADH alerts listed below are shown on the Engine and Alert Display
(EAD):
– PITOT AUX FAIL
– PITOT CAPT FAIL
– AOA HEAT R FAIL
– AOA HEAT L FAIL
NOTE: These alerts may not show in the order listed above.
(b) Push the MISC switch on the Systems Control Panel (SCP).
(c) Make sure that the ADH alerts listed below are shown on the MISCELLANEOUS
page of the SD:
– PITOT AUX FAIL
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– PITOT CAPT FAIL
– AOA HEAT R FAIL
– AOA HEAT L FAIL
– RUD PITOT FAIL
NOTE: These alerts may not show in the order listed above.
(d) Make sure that the MASTER CAUTION light on the glareshield is on.
(e) Push the STATUS switch on the SCP.
(f) Make sure that the alerts listed below are shown on the STATUS page of the SD:
– STATIC R HEAT
– STATIC L HEAT
NOTE: These alerts may not show in the order listed above.
(4) Set the AIR DATA HEAT switch to the ON position. Make sure that no ADH related alerts
are shown on the MISCELLANEOUS page of the SD.
(5) Set the left FUEL switch to the OFF position. Make sure that no ADH related alerts are
shown on the MISCELLANEOUS page of the SD.
(6) Set the AIR DATA HEAT switch to the OFF position. Make sure that no ADH related
alerts other than AIR DATA HEAT OFF is shown on the MISCELLANEOUS page of the
SD.
g. Right Fuel Switch Followed by ADH Switch:
(1) Make sure that the AIR DATA HEAT switch, left FUEL switch and right FUEL switch are
in the OFF position.
(2) Make sure that no ADH related alerts other than AIR DATA HEAT OFF is shown on the
MISCELLANEOUS page of the SD.
(3) Set the right FUEL switch to the ON position and do the following:
(a) Make sure that the ADH alerts listed below are shown on the EAD:
– PITOT AUX FAIL
– PITOT CAPT FAIL
– AOA HEAT R FAIL
– AOA HEAT L FAIL
NOTE: These alerts may not show in the order listed above.
(b) Push the MISC switch on the SCP.
(c) Make sure that the ADH alerts listed below are shown on the MISCELLANEOUS
page of the SD:
– PITOT AUX FAIL
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– PITOT CAPT FAIL
– AOA HEAT R FAIL
– AOA HEAT L FAIL
– RUD PITOT FAIL
NOTE: These alerts may not show in the order listed above.
(d) Make sure that the MASTER CAUTION light on the glareshield is on.
(e) Push the STATUS switch on the SCP.
(f) Make sure that the alerts listed below are shown on the STATUS page of the SD:
– STATIC R HEAT
– STATIC L HEAT
NOTE: These alerts may not show in the order listed above.
(4) Set the AIR DATA HEAT switch to the ON position. Make sure that no ADH related alerts
are shown on the MISCELLANEOUS page of the SD.
(5) Set the right FUEL switch to the OFF position. Make sure that no ADH related alerts are
shown on the MISCELLANEOUS page of the SD.
(6) Set the AIR DATA HEAT switch to the OFF position. Make sure that no ADH related
alerts other than AIR DATA HEAT OFF is shown on the MISCELLANEOUS page of the
SD.
h. Left and Right Fuel Switches Followed by ADH Switch:
(1) Make sure that the AIR DATA HEAT switch, left FUEL switch and right FUEL switch are
in the OFF position.
(2) Make sure that no ADH related alerts other than AIR DATA HEAT OFF is shown on the
MISCELLANEOUS page of the SD.
(3) Set the left FUEL switch and right FUEL switch to the ON position and do the following:
(a) Make sure that the ADH alerts listed below are shown on the EAD:
– PITOT AUX FAIL
– PITOT CAPT FAIL
– AOA HEAT R FAIL
– AOA HEAT L FAIL
NOTE: These alerts may not show in the order listed above.
(b) Push the MISC switch on the SCP.
(c) Make sure that the ADH alerts listed below are shown on the MISCELLANEOUS
page of the SD:
– PITOT AUX FAIL
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– PITOT CAPT FAIL
– AOA HEAT R FAIL
– AOA HEAT L FAIL
– RUD PITOT FAIL
NOTE: These alerts may not show in the order listed above.
(d) Make sure that the MASTER CAUTION light on the glareshield is on.
(e) Push the STATUS switch on the SCP.
(f) Make sure that the alerts listed below are shown on the STATUS page of the SD:
– STATIC R HEAT
– STATIC L HEAT
NOTE: These alerts may not show in the order listed above.
(4) Set the AIR DATA HEAT switch to the ON position. Make sure that no ADH related alerts
are shown on the MISCELLANEOUS page of the SD.
(5) Set the left FUEL switch and right FUEL switch to the OFF position. Make sure that no
ADH related alerts are shown on the MISCELLANEOUS page of the SD.
(6) Set the AIR DATA HEAT switch to the OFF position. Make sure that no ADH related
alerts other than AIR DATA HEAT OFF is shown on the MISCELLANEOUS page of the
SD.
i. Put the left and right fire control handles back to the norma l position.
j. In the EPC, lower panel, close th e circuit breakers that follow and remove the circuit breaker
collars and DO-NOT-CLOSE tags:
NomenclatureRow/ColumnNumber
FIRE EXTINGUISHING CONTROL BOTTLE 1X/41B1-95
FIRE EXTINGUISHING CONTROL BOTTLE 2X/42B1-96
k. If a test fails, do corrective actions, repeat the test, and do corrective actions until the test
passes.
6. RC - Do the Operational Test of the Captain's Pitot Heater. R efer to 717 AMM 30-31-00 as an
accepted procedure.
a. If the test fails, do corrective actions, repeat the test, an d do corrective actions until the
operational test of the captain's pitot heater test passes.
7. RC - Do the Operational Test of the First Officer's Pitot Heater. Refer to 717 AMM 30-31-00 as an
accepted procedure.
a. If the test fails, do corrective actions, repeat the test, an d do corrective actions until the
operational test of the first officer's pitot heater test passes.
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### Page 26

8. RC - Do the Functional Test of the Left Static Port Plate Hea ter. Refer to 717 AMM 30-31-00 as
an accepted procedure.
a. If the test fails, do corrective actions, repeat the test, an d do corrective actions until the
functional test of the left static port plate heater test passes.
9. RC - Do the Functional Test of the Right Static Port Plate Heater. Refer to 717 AMM 30-31-00 as
an accepted procedure.
a. If the test fails, do corrective actions, repeat the test, an d do corrective actions until the
functional test of the right static port plate heater test passes.
10. Put the airplane back to a serviceable condition.
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### Page 27 (OCR)

BOEING SERVICE BULLETIN 717-30A0009
ALERT  ALERT
546N9221-1572-20-  J2-336
STA 110 RELAY PANEL
3 LOCATIONS
(524  1123฿  (1238  (878
J2-338  N5201-763-22-  - N5201-762-22N-||I•GND-3605D
R5-3087 R2-639 R5-3087
L ENG FUEL SW RELAY 3
1123B  1123B
• N5201-772-22-  A2  • N5201-770-22N-  ||I GND-3606D
R5-3086 R2-640 R5-3086
R ENG FUEL SW RELAY 3
AFT LEFT EQUIPMENT BAY
- ADDED WIRE OR NEW ROUTING
TERMINAL CODE
REFERENCE: 717 WDM 30-31-01, 717 WDM 74-10-01, 717 WDM 74-10-02
The Terminal Code numbers shown below agree with the number shown in the Terminal Code symbol in this
figure.
TERM CODE  NAME  IDENTIFICATION  QTY  MORE DATA
WIRE CODE 801  D2426-1C-20NM  1  (a)
WIRE CODE 801  D2426-1C-22NM  4  (a)
IN-LINE JUNCTION  CTM-20-090  1  (a)
SEALING PLUG  5D0206-20  1
STA-STRAP  9D0254-1-1-9  (a)
TAPE PRESSURE SENSITIVE  DMS 2359, TYPE 2,  2  (b)
ADHESIVE, WRAP ON LABEL  CLASS B
1123B  SKT T/C 1123  DC39-16S  4
FIGURE 1: ELECTRICAL/ELECTRONICS COMPARTMENT - STA 110 RELAY PANEL AND AFT RIGHT
RADIO RACK - WIRING CHANGE
(SHEET 1 OF 2)
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### Page 28

MORE DATAQTYIDENTIFICATIONNAMETERM CODE
(c)25D0086-3TERMINAL LUG 878878
1M39029/22-193CONTACT TC 542/546546
3M39029/22-192CONTACT T/C 524524
(a) Install new in-line junction and wires to existing wire bundles. Refer to SWPM 20-10-01 as an accepted
procedure.
(b) Use to identify new in-line junction. Install 6 inches from both sides of the in-line junction. Refer to
SWPM 20-00-03 as an accepted procedure.
(c) Measure the electrical bond resistance between the terminal lug and the ground stud. Make sure
that the bond resistance is not greater than 0.0025 ohms. Refer to SWPM 20-50-01 as an accepted
procedure.
FIGURE 1: ELECTRICAL/ELECTRONICS COMPARTMENT - STA 110 RELAY PANEL AND AFT RIGHT
RADIO RACK - WIRING CHANGE
(SHEET 2 OF 2)
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### Page 29 (OCR)

BOEING SERVICE BULLETIN 717-30A0009
ALERT  ALERT
Boeing Part Demand Intent
After review of this service bulletin (SB), Boeing asks that the primary engineer fill out this survey to
help Boeing predict the quantity and timing of the Boeing supplied kits.
Airline:
Contact Name:
Date:
Contact E-mail:
_ Yes  No Have/will you recommend to your airline to accomplish this SB?
_ Yes  • No Would issuance of an Airworthiness Directive change this decision?
When would you likely be starting this SB incorporation? Month/ Year
How many airplanes per month do you plan to accomplish? Airplane/Month
How many total airplanes do you plan to complete? Total Airplanes
For inspection related SBS, are you planning to replace on condition, or a fleet campaign to replace or
all airplanes regardless of condition?
On Condition  _ Campaign
If you are not incorporating this SB at this time will you please help us understand the reason(s) why?
Your input will help us provide better customer support.
• Cost Prohibitive  - Continue Inspections  • Other
Operator Comments:
Within 45 days of the SB issue, or as soon after as possible, please scan this form and send to:
KitsandMods@boeing.com
Disclaimer: The data provided in this survey will be used for planning purposes only and does not
constitute a commitment on any part of the airlines to purchase the parts in question, nor does it constitute
a commitment on the part of Boeing to deliver the parts in question. This survey is a projection to help
Boeing forecast demand levels and timing to better support the customers schedule.
2402568
APPENDIX A: PART DEMAND INTENT
(SHEET 1 OF 1)
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