# Boeing Alert Service Bulletin MD90-30A031: No revision named

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- Document: [Boeing Alert Service Bulletin MD90-30A031](https://openairdocs.org/service-documents/boeing/md90-30a031.md)
- Title as filed: SB-MD90-30A031
- Pages: 37
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## Text

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### Page 1

Commercial 
Airplanes
MD90
Service Bulletin
ALERT
Number: MD90-30A031
Original Issue: June 02, 2017
ATA System: 3030
SUBJECT: ICE AND RAIN PROTECTION - Pitot and Static - Air Data Sensor Heat System 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 © 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Unpublished Work.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: June 02, 2017
MD90-30A031
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2.0

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Table of Contents
Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11
B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11
C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11
D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12
E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12
F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12
G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12
H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14
1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14
2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 15
3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 15
K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15
L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 18
3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 19
3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
FIGURE 1: ELECTRICAL/ELECTRONICS (E/E) COMPARTMENT - AFT RIGHT RADIO RACK - RELAY
AND SOCKET INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26
FIGURE 2: ELECTRICAL/ELECTRONICS (E/E) COMPARTMENT - STA 110 RELAY PANEL AND AFT
RIGHT RADIO RACK - WIRE ROUTING . . . . . . . . . . . . . . . . . . . . . . . . . . . 28
FIGURE 3: ELECTRICAL/ELECTRONICS (E/E) COMPARTMENT - STA 110 RELAY PANEL AND AFT
RIGHT RADIO RACK - WIRING CHANGES . . . . . . . . . . . . . . . . . . . . . . . . . 33
APPENDIX A: PART DEMAND INTENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37
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Commercial 
Airplanes
MD90
Service Bulletin
ALERT
SummaryNumber: MD90-30A031Original Issue: June 02, 2017
ATA System: 3030
SUBJECT: ICE AND RAIN PROTECTION - Pitot and Static - Air Data Sensor Heat System 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
None.
BACKGROUND
This service bulletin gives instructions to change the Air Data Heat (ADH) System. The accomplishment of this
service bulletin will turn on the ADH system when the left and right fuel switches are set to the ON position. Air
data sensors directly affect flight computers and flight deck instrumentation. The air data sensors have heaters
to prevent blockage from ice formation in the sensor or from ice formation on the static plates. Incorrect airspeed
indications can be the direct result of pitot tubes icing. Unheated Air Data sensors, mainly the pitot and static
sensors, in icing conditions may result in irregular airspeed or altitude indications. If this service bulletin is not
done, then failure of the Captain or First Officer to activate the ADH System can result in unsafe flight conditions.
One 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.
Boeing Service Related Problem (SRP) MD90-SRP-30-0053 is related to this service bulletin.
Boeing Fleet Team Digest (FTD) MD-90 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 ChangesYesWeight and Balance Change
Paragraph 1.I., Electrical Load DataYesElectrical 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/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 (E/E) compartment, do the following:
– Install two new relays in the aft right radio rack.
– Install a terminal block, new wires and in-line junctions between the E/E compartment aft right radio rack
and the STA 110 relay panel.
– Do the Operational test of the static ports and pitot heaters and the Enhanced Air Data System test.
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
MD-90-30 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 after the original
issue date of this service bulletin.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the changes given in this service bulletin.
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MANPOWER
Elapsed HoursTotal Task HoursAirplanes
18.9036.80Group 1
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
MD90
Service Bulletin
ALERT
Number: MD90-30A031
Original Issue: June 02, 2017
ATA System: 3030
SUBJECT: ICE AND RAIN PROTECTION - Pitot and Static - Air Data Sensor Heat System 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 service bulletin is for the airplanes shown below.
The intent of this change was done on fuselage number 2224 prior to the Original Issue of this
service bulletin in accordance with SP90300001 Drawing, Revision C.
DESCRIPTIONCONFIGURATIONGROUP
MD-90-30 airplanes making changes to Air Data Sensor Heat System.-1
Airplane Models:
MD-90-30
GroupFuselage Num-
ber
12094 - 2099
12100
12115
12117
12120
12122 - 2123
12125 - 2126
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GroupFuselage Num-
ber
12131
12136
12138
12140 - 2143
12146 - 2147
12149 - 2150
12154
12156 - 2157
12159
12161
12163 - 2165
12169 - 2171
12173
12175
12177
12179
12184
12186
12190
12193 - 2195
12197 - 2198
12200
12202 - 2203
12207
12210 - 2212
12217
12220
12222
12224
12228
12233
12236
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GroupFuselage Num-
ber
12240
12245
12248
12253
12258 - 2259
12261
14001 - 4002
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
This service bulletin gives instructions to change the Air Data Heat (ADH) System. The accomplishment
of this service bulletin will turn on the ADH system when the left and right fuel switches are set to the
ON position. Air data sensors directly affect flight computers and flight deck instrumentation. The air
data sensors have heaters to prevent blockage from ice formation in the sensor or from ice formation
on the static plates. Incorrect airspeed indications can be the direct result of pitot tubes icing. Unheated
Air Data sensors, mainly the pitot and static sensors, in icing conditions may result in irregular airspeed
or altitude indications. If this service bulletin is not done, then failure of the Captain or First Officer to
activate the ADH System can result in unsafe flight conditions.
One 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.
Boeing Service Related Problem (SRP) MD90-SRP-30-0053 is related to this service bulletin.
Boeing Fleet Team Digest (FTD) MD-90 FTD 30-15001 is related to this service bulletin.
Export Controlled ECCN: 9E991 - BOEING
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D. Description
In the Electrical/Electronics (E/E) compartment, do the following:
– Install two new relays in the aft right radio rack.
– Install a terminal block, new wires and in-line junctions between the E/E compartment aft right
radio rack and the STA 110 relay panel.
– Do the Operational test of the static ports and pitot heaters and the Enhanced Air Data System
test.
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
114MD-90-30
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 after the
original issue date of this service bulletin.
F. Approval
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified
in this service bulletin comply with the applicable regulations and are FAA approved, as well as European
Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved
airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on
the airplane in its original Boeing delivery configuration or as modified by other approved Boeing
changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
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
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• Time to cure the materials
• Time to make the parts
• Time to find the tools
Elapsed HoursTask HoursNumber of PersonsTask
0.100.101Open Access
0.500.501FIGURE 1
16.4032.802FIGURE 2
1.503.002FIGURE 3
0.100.101Close Access
0.300.301Test
18.9036.80TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
Change in Mo-
ment (Pound-
Inches)
Change in
Weight
(Pounds)
Approximate Sta-
tion (Inches)Airplane
+165.0+1.0165All
I. Electrical Load Data
1. Direct Current (DC) Load Changes
UNITS/
%OPRE/NEVDCUNITLOADNOTESSUPPLIEREQUIPMENT NAMEPART NUMBERITEMCHAPBUS
1/100E280.11(B1-1098)Leach Inter-nationalRight Fuel SwitchRelay 5D0004-14502R2-15087401T
AVERAGE WATTS% TIME OPR
15/30 M2/5 M5 S15/30 M2/5 MCONDITION
011030LOADING
011030START
0550100TAXI
555100100TAKEOFF & CLIMB
555100100CRUISE COLD
555100100CRUISE HOT
555100100DESCENT & LAND
00000EMERGENCY
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UNITS/
%OPRE/NEVDCUNITLOADNOTESSUPPLIEREQUIPMENT NAMEPART NUMBERITEMCHAPBUS
1/100E280.11(B1-1098)Leach Inter-nationalRight Fuel SwitchRelay 5D0004-14502R2-15087401T
AVERAGE WATTS% TIME OPR
15/30 M2/5 M5 S15/30 M2/5 MCONDITION
00000GROUND SERVICE
UNITS/
%OPRE/NEVDCUNITLOADNOTESSUPPLIEREQUIPMENT NAMEPART NUMBERITEMCHAPBUS
1/100E280.11(B1-1099)Leach Inter-nationalRight Fuel SwitchRelay 5D0004-14503R2-15077401T
AVERAGE WATTS% TIME OPR
15/30 M2/5 M5 S15/30 M2/5 MCONDITION
011030LOADING
011030START
0550100TAXI
555100100TAKEOFF & CLIMB
555100100CRUISE COLD
555100100CRUISE HOT
555100100DESCENT & LAND
00000EMERGENCY
00000GROUND SERVICE
2. Alternating Current (AC) Load Changes
Not changed.
J. References
1. Existing Data:
a. Standard Overhaul Practices Manual (SOPM) 20-50-01
b. 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, 20-20-02, 20-20-03, 20-50-01
c. MD-90 Aircraft Maintenance Manual (AMM) 24-00-00, 30-30-00
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d. MD-90 Fleet Team Digest (FTD) 30-15001
e. MD-90 Structural Repair Manual (SRM) 51
f. MD-90 Wiring Diagram Manual (WDM) 30-31-01, 74-11-11, 74-11-12
g. Approved Equivalent Parts List (AEPL) Drawing 7595071
h. Boeing Service Related Problem (SRP) MD90-SRP-30-0053
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
ChangeTitleDocument Number
DENHANCED ACTUATION OF THE
AIR DATA HEAT (ADH) SYSTEM
SPECIAL PRODUCT DRAWING
SP90300001
The table above lists the applicable drawing used to prepare this service bulletin. The drawing is
not necessary to make the specified changes, and is not supplied with this service bulletin. The
drawing may not be applicable to all airplane configurations or operators.
K. Publications Affected
1. Publications:
Chapter-SectionPublication
Volume 3, Chapter Ice & Rain Protec-
tion
Flight Crew Operations Manual
24-23, 26-00, 30-30, 73-21, 74-00Fault Isolation Manual
30-31Illustrated Parts Catalog
23-31, 24-23, 26-11, 30-30, 71-01,
71-02, 74-00
Aircraft Maintenance Manual
30-31, 74-11Wiring Diagram Manual
30-30, 76-13System Schematic Manual
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary.
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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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### Page 17

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
4,395.00120SERVICE KIT - ENHANCED ACTUATION
OF THE AIR DATA HEAT (ADH) SYSTEM
SA90300031-3
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 change 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 SA90300031
NotesExisting Part
Number
NameQTYNew Part Number
-101-3
SERVICE KIT.-SA90300031-3
WIRE KIT-1SA90300031-101
(a)RELAY.25D0004-1
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### Page 18

Kit SA90300031
NotesExisting Part
Number
NameQTYNew Part Number
-101-3
(a)TERM BLOCK.15D0010-13
(a)SOCKET2.5D0020-8
(a)TERMINAL LUG
766
6.5D0086-26
(a)TERMINAL LUG
761
4.5D0086-5
(a)TERMINAL LUG
762
2.5D0086-6
(a)SEALING PLUG.65D0206-20
JUNCTION.6CTM-16-090
WIRE CODE 801280
FT
.D2426-1C-16NM
WIRE CODE 801187
FT
.D2426-1C-20NM
PIN, T/C 112610.DC38-20P
SKT T/C 112320.DC39-16S
(a)CONTACT TC
542/546
18.M39029/22-193
(a) Or approved equivalent. Refer to AEPL, Drawing 7595071.
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)STRING TIE-18XTZ, 23XTZ
(DMS 2089)
or Equivalent
(b)TAPE PRESSURE SENSITIVE
TAPE, ADHESIVE, WRAP ON
LABEL
-DMS 2359 Type 2 Class B
(a) For new wire installation. Use the quantity needed to do the changes given in this service
bulletin.
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NotesNameQTYPart Number / Specification
(b) For labeling new splices. 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.
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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### Page 20

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BLANK PAGE

### Page 21

3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
WARNING: 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.
CAUTION: 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.
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
MD-90 SRM 51.
4. If the length of any fastener specified in this service bulletin 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 MD-90 SRM 51.
– Torque Values:
— Values for structural fasteners are given in MD90 Structural Repair Manual,
Chapter 51.
— Values for airframe maintenance tasks are included in Chapter 20 of MD90
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 MD90
Aircraft Maintenance Manual (AMM).
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### Page 22

— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
6. Refer to SWPM 20-10-01 as accepted wire installation procedures.
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. Autoland system separated bundles are tied with yellow string and have run letters
starting with "S". These bundles must not touch other wires bundles unless explicitly
stated on wire installation, or are sleeved.
Yellow string ties must remain on them. If removed, the yellow string must be
reinstalled per SWPM 20-10-01.
Sleeving installed on wire assemblies must remain on them. If removed, the sleeving
must be reinstalled, with no bare (unsleeved) wire allowed to touch other runs in the
area.
Run letters on wire assemblies must remain on them. If removed, the run letters must
be reinstalled per SWPM 20-00-03.
Where parallel wire assemblies make contact or can be brought together and stay
together due to space limitations, spacer must be used to assure system separation.
8. Obey all of the warnings and cautions given in the specified manual sections.
9. 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.
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### Page 23

10. 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.
11. The modules on a terminal block are controlled by the wire data. Verify/Install terminal
block modules and end clamps to agree with the wire data, refer to SWPM 20-20-02
as an accepted procedure.
12. Install terminal block at noted position. If noted position is occupied with a spare
terminal block replace it with a specified terminal block. If specified terminal block is
the same type as existing spare terminal block it is not necessary to replace the
terminal block.
13. 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.
14. 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.
15. If shading is used, shaded areas in Figures are reference only. Shaded areas in
Figures may look different than your airplane.
16. Use of colors in Figures is based on guidance from the ATA e-Business Program
(ATA) iSpec 2200.
17. 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 MD-90 AMM 24-00-00 as an accepted
procedure.
2. Get access to the Electrical/Electronics (E/E) compartment using access door 110BL or 211ABF.
3. RC - Install new relays in the aft right radio rack in accordance with FIGURE 1.
4. RC - Install new wires between the aft right radio rack and the STA 110 relay panel in accordance
with FIGURE 2 and FIGURE 3.
5. Supply electrical power to the airplane. Refer to MD-90 AMM 24-00-00 as an accepted procedure.
6. RC - Do the tests that follow:
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### Page 24

CAUTION: IN ORDER TO AVOID ANY POTENTIAL HAZARD OR DAMAGE TO EQUIPMENT
IT IS RECOMMENDED THAT POWER AND GROUND CONNECTIONS, IF
AFFECTED AS PART OF THIS MODIFICATION, BE VERIFIED BY APPROPRIATE
SHOP TOOLS AND PROCEDURES, PRIOR TO APPLICATION OF POWER.
CAUTION: IN ORDER TO ASSURE THE INTEGRITY OF THE AIRCRAFT AFTER THE WORK
IS COMPLETED IT IS EXPECTED THAT ALL APPLICABLE RETURN TO SERVICE
TESTS WILL BE PERFORMED ON ALL THE SYSTEMS DIRECTLY OR
INDIRECTLY AFFECTED BY THIS MODIFICATION.
CAUTION: POTENTIAL ELECTRICAL POWER HAZARD EXISTS WHEN PERFORMING THIS
TEST. USE APPLICABLE SHOP PROCEDURES AS REQUIRED.
CAUTION: PRIMARY COMPONENTS INSTALLED DURING THIS MODIFICATION CONTAIN
ELECTROSTATIC DISCHARGE (ESD) SENSITIVE MICROELECTRONIC
SEMICONDUCTOR COMPONENTS. USE PROPER PERSONAL GROUNDING,
ENCLOSURE, AND SHIELDING PROCEDURES WHEN WORKING AROUND THIS
EQUIPMENT AND ASSOCIATED WIRING.
a. Do the Operational Test of the Static ports and Pitot heaters. Refer to MD-90 AMM 30-30-00
as an accepted procedure.
(1) If the test fails, do corrective actions, repeat the test, and do corrective actions until the
Operational test of the Static ports and Pitot heaters passes.
NOTE: Leave the airplane in the same configuration after the Operational test of the Static
ports and Pitot heaters has been completed.
b. Do the Enhanced Air Data System Test that follows:
(1) Make sure that the following circuit breakers are closed:
CIRCUIT BREAKER PANEL -LOWER EPC
NameNumberColumnRow
RIGHT ENGINE FUEL SWITCH (28 VDC-XFR)B1-109840B7-41
LEFT ENGINE FUEL SWITCH (28 VDC-XFR)B1-109942B7-39
(2) Make sure that the ICE PROTECTION METER SEL & HEAT switch is in the OFF position
and the PITOT/STALL HEAT OFF message is displayed on the Electronic Overhead
Annunciator Panel (EOAP)
(3) Set the R FUEL SHUTOFF SWITCH to the ON position.
(4) Make sure that the PITOT/STALL HEAT OFF message is still displayed on the EOAP.
(5) Set the R FUEL SHUTOFF SWITCH to the OFF position.
(6) Make sure that the PITOT/STALL HEAT OFF message is still displayed on the EOAP.
(7) Set the L FUEL SHUTOFF SWITCH to the ON position.
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### Page 25

(8) Make sure that the PITOT/STALL HEAT OFF message is still displayed on the EOAP.
(9) Set the L FUEL SHUTOFF SWITCH to the OFF position.
(10) Make sure that the PITOT/STALL HEAT OFF message is still displayed on the EOAP.
(11) Set the L FUEL SHUTOFF SWITCH and the R FUEL SHUTOFF SWITCH to the ON
position.
(12) Make sure that the PITOT/STALL HEAT OFF message is not displayed on the EOAP.
(13) Set the L FUEL SHUTOFF SWITCH and the R FUEL SHUTOFF SWITCH to the OFF
position.
(14) Make sure that the PITOT/STALL HEAT OFF message is displayed on the EOAP.
(15) If the Enhanced Air Data System Test fails, do corrective actions, repeat the test, and do
corrective actions until the Enhanced Air Data System Test passes.
7. Close access to the Electrical/Electronics (E/E) compartment.
8. Put the airplane back to a serviceable condition.
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### Page 26 (OCR)

BOEING SERVICE BULLETIN MD90-30A031
ALERT  ALERT
R2-1507
R5-1507
R2-1508
R5-1508
STA
200
ELECTRICAL/ELECTRONICS (E/E)  COMPARTMENT  WD
AFT RIGHT RADIO RACK
6 LOCATIONS 2
6 LOCATIONS (
6 LOCATIONS (2  2 2 LOCATIONS
1 2 LOCATIONS
AFT RIGHT
RADIO RACK
6 LOCATIONS (  (TYPICAL)
6 LOCATIONS  2547811
FIGURE 1: ELECTRICAL/ELECTRONICS (E/E) COMPARTMENT - AFT RIGHT RADIO RACK - RELAY AND
SOCKET INSTALLATION
(SHEET 1 OF 2)
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### Page 27

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
(e)25D0020-8SOCKETInstall (New)1
(a)6-WASHERInstall (New)
(a)6-NUTInstall (New)
(e)25D0004-1RELAYInstall (New)2
(a)12-WASHERInstall (New)
(a)6-NUTInstall (New)
(b)(d)2--Identify3
(c)(d)2--Identify4
(a) Relay mounting and relay socket mounting hardware, is vendor furnished.
(b) Ink stamp the relay number "R2-1507" and relay socket number "R5-1507" on the structure, adjacent to
the equipment. Refer to SWPM 20-00-09 as an accepted procedure. Use ink color black, text height 0.18
inches minimum. The marking must be visible after the relay and socket are installed.
(c) Ink stamp the relay number "R2-1508" and relay socket number "R5-1508" on the structure, adjacent to
the equipment. Refer to SWPM 20-00-09 as an accepted procedure. Use ink color black, text height 0.18
inches minimum. The marking must be visible after the relay and socket are installed.
(d) As an option to ink stamp marking install adhesive backed markers. Refer to SWPM 20-00-09 as an ac-
cepted procedure.
(e) Or approved equivalent. Refer to AEPL, Drawing 7595071.
FIGURE 1: ELECTRICAL/ELECTRONICS (E/E) COMPARTMENT - AFT RIGHT RADIO RACK - RELAY AND
SOCKET INSTALLATION
(SHEET 2 OF 2)
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### Page 28 (OCR)

BOEING SERVICE BULLETIN MD90-30A031
ALERT  ALERT
STA
GND 3544  GND 3545  218.00  STA 200  RELAY PANEL
GROUND
BRACKET,
S3-526
TERMINAL BLOCK  AFT RIGHT
- RADIO RACK
STA
110.00
STA
160.00
ELECTRICAL/ELECTRONICS
(E/E) COMPARTMENT
STA 110  R2-1507
RELAY PANEL  R5-1507
R2-1508
R5-1508
STA
200
*RAF
AAJ  X=-26.00
AFT RIGHT RADIO RACK  2547833
FIGURE 2: ELECTRICAL/ELECTRONICS (E/E) COMPARTMENT - STA 110 RELAY PANEL AND AFT RIGHT
RADIO RACK - WIRE ROUTING
(SHEET 1 OF 5)
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### Page 29 (OCR)

BOEING SERVICE BULLETIN MD90-30A031
ALERT  ALERT
TO:
GND 3544
GND 3545
AAJ
STA
200.00
RAF
SPLICE  AAJ
AREA  S3-526,
J2-401
00091/  J2-402  AAJ
avS
AAJ  90+-Zr
avs
AFT RIGHT RADIO RACK
2548121
FIGURE 2: ELECTRICAL/ELECTRONICS (E/E) COMPARTMENT - STA 110 RELAY PANEL AND AFT RIGHT
RADIO RACK - WIRE ROUTING
(SHEET 2 OF 5)
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### Page 30 (OCR)

BOEING SERVICE BULLETIN MD90-30A031
ALERT  ALERT
× 1000))
'AAC
AAC
AAJ
STA
160.000
AAJ
SAB
X= -40.00
2548159
FIGURE 2: ELECTRICAL/ELECTRONICS (E/E) COMPARTMENT - STA 110 RELAY PANEL AND AFT RIGHT
RADIO RACK - WIRE ROUTING
(SHEET 3 OF 5)
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### Page 31 (OCR)

BOEING SERVICE BULLETIN MD90-30A031
ALERT  ALERT
STA
160.00
STA
148.55
X = 30.00
X = 20.00
_ AAB
_AAJ
AAC
2548350
FIGURE 2: ELECTRICAL/ELECTRONICS (E/E) COMPARTMENT - STA 110 RELAY PANEL AND AFT RIGHT
RADIO RACK - WIRE ROUTING
(SHEET 4 OF 5)
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### Page 32 (OCR)

BOEING SERVICE BULLETIN MD90-30A031
ALERT  ALERT
R2-97
R2-99
X = -37.000
Х = 40 PANEL
STA 120.050
TEND
men
120
R2-98
R2-100
STA 110 RELAY PANEL
SIA
134
AA.
AAJ
LOWER NOSE  2548360
The wires are contained in Wire Kit SA90300031-101.
FIGURE 2: ELECTRICALELECTRONICS (E/E) COMPARTMENT - STA 110 RELAY PANEL AND AFT RIGHT
RADIO RACK - WIRE ROUTING
(SHEET 5 OF 5)
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### Page 33 (OCR)

BOEING SERVICE BULLETIN MD90-30A031
ALERT  ALERT
2 LOCATIONS (1123  - АЗ
FURN 2-20  A1
OFFA  (AAJ)
1EB300F20
ON T  - FURN 1-20  1126  100 IN.
: Оз  - FURN 3-20  1HH
LEFT FUEL SHUTOFF  S1-645  SH 1  P1-1411  R5-1411  S3-526  R5-150  LEFT ENG FUEL SW RELAY 5  R2-1507
SW
AFT RIGHT RADIO RACK SHELF 2
STA 200
FURN 2-20
OFFL  GND 3545
ON T  _ (AAJ)
30,05 FURN 320-  • FURN 1-20  1EB292B20N  100 IN.
(762
SH 1
S1-644  P1-1412  R5-1412
RIGHT FUEL SHUTOFF
SW
AFT PEDESTAL
2 LOCATIONS 1123  - АЗ
¡А2
- A1
(AAJ)
2EB301F20
1126  100 IN.
2HH
S3-526  R5-1508  R2-1508
RIGHT ENG FUEL SW RELAY 5
AFT RIGHT RADIO RACK SHELF
STA 200
GND 3544
(AAJ)
2EB292B20N
100 IN.
(762
• ADDED WIRE OR NEW ROUTING
HA DELETED WIRE OR FORMER ROUTING
O TERMINAL CODE  EXISTING WIRE  2548361
FIGURE 3: ELECTRICAL/ELECTRONICS (E/E) COMPARTMENT - STA 110 RELAY PANEL AND AFT RIGHT
RADIO RACK - WIRING CHANGES
(SHEET 1 OF 4)
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### Page 34 (OCR)

BOEING SERVICE BULLETIN MD90-30A031
ALERT  ALERT
4 LOCATIONS  4 LOCATIONS  1123  (1123
(RAF, AAC, AAJ)  (1126  (1126  D2-  D3
• 1F988D20 -  8JB
360 IN.
2 LOCATIONS (761  B1  C2  - C3
--- 30-31-02 •--  45-130-31-02  -C1  - B3
B2
•-- 30-31-02 •  —B1
- 30-31-02 •-  _(AAJ)  — АЗ
R2-99  1F988E20 •  A2
LEFT STALL WARN VANE AND  100 IN.  - A1
STATIC PORT HEATERS
30-31-02
I (RAF, AAC, AAJ)  8JA  ×1
1F965C20
360 IN.  X2
R5-1507  R5-1507
R2-1507
LEFT ENG FUEL SW RELAY 5
AFT RIGHT RADIO RACK SHELF 2
STA 200
(AAJ)
1F965D20
100 IN.
1123  1123
(RAF, AAC, AAJ)  D2
• 1F988D20 -  8JY  -D1
360 IN.
2 LOCATIONS (761  - C3
C2
-- 30-31-02 •-  -C1
--] 30-31-02  - ВЗ
B2
•-- 30-31-02 •  - B1
--- 30-31-02 •--X30  (AAJ)  - АЗ
R2-100  2F988E20 -  A2
RIGHT STALL WARN VANE AND  100 IN.  -А-
STATIC PORT HEATERS
30-31-02
• (RAF, AAC, AAJ)  8JХ
2F965C20
360 IN.  X2
S3-526
R5-1508  R5-1508
R2-1508
RIGHT ENG FUEL SW RELAY 5
AFT RIGHT RADIO RACK SHELF 2
STA 200
(AAJ)
• 2F965D20
100 IN.
2548367
FIGURE 3: ELECTRICAL/ELECTRONICS (E/E) COMPARTMENT - STA 110 RELAY PANEL AND AFT RIGHT
RADIO RACK - WIRING CHANGES
(SHEET 2 OF 4)
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### Page 35 (OCR)

BOEING SERVICE BULLETIN MD90-30A031
ALERT  ALERT
3 LOCATIONS  3 LOCATIONS
(1123  1123
-DЗ
F950E16  D2  (AAJ)
100 IN.  F1662C16
100 IN.
- СЗ
F952C16  (AAJ)
100 IN.  F1663C16
100 IN.
(AAJ)  - ВЗ
F951E16  B2  (AAJ)
100 IN.  -B1  F1664C16
100 IN.
R5-1507  R5-1507
R2-1507
LEFT ENG FUEL SW RELAY 5
3 LOCATIONS  3 LOCATIONS
(1123  1123
(AAJ)  -DЗ
F950F16
100 IN.  D1  F1662D16
100 IN
(AAJ)  -СЗ
F952D16  (AAJ)
100 IN.  F1663D16
100 IN
(AAJ)  - ВЗ
F951F16  (AAJ)
100 IN.  -В†  F1664D16
100 IN.
R5-1508  R5-1508
R2-1508
RIGHT ENG FUEL SW RELAY 5
AFT RIGHT RADIO RACK SHELF 2 STA 200
3 LOCATIONS  3 LOCATIONS
536  (RAF  766)  (RAF  536
AAC, AÁJ)  AAC, AAJ)
F950D16  F1662B16
J2-401  360 IN.  -- - SH 1  360 IN.  J2-402
R2-97
CAPTAIN'S PITOT HEATER
3 LOCATIONS  SH 1  3 LOCATIONS
536  (RAF  (766  766  (RAF  536)
AAC, AÁJ)  AAC, AAJ)
J2-403  F952B16  360 IN.  52-- SH1  F1663B16  360 IN.  J2-404
3 LOCATIONS  3 LOCATIONS
536  (RAF.  (766)  766  (RAF  536
AAC, AÁJ)  AAC, AAJ
F951D16  A2_- SH1  F1664B16
J2-405  360 IN.  360 IN.  J2-406
R2-98
FIRST OFFICER AND AUX PITOT HEATER
SH 1
STA 110 RELAY PANEL
+ DELETED WIRE OR FORMER ROUTING  ADDED WIRE OR NEW ROUTING  EXISTING WIRE  TERMINAL CODE  2548543
REFERENCE: MD-90 WDM 30-31-01, MD-90 WDM 74-11-11, MD-90 WDM 74-11-12
FIGURE 3: ELECTRICAL/ELECTRONICS (E/E) COMPARTMENT - STA 110 RELAY PANEL AND AFT RIGHT
RADIO RACK - WIRING CHANGES
(SHEET 3 OF 4)
Original Issue: June 02, 2017
Export Controlled ECCN: 9E991 - BOEING  MD90-30A031
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  35 of 37

### Page 36

MORE DATAQTYIDENTIFICATIONNAMETERM CODE
(a)(c)15D0010-13TERM BLOCK-
(c) For in-line junction.65D0206-20SEALING PLUG
(b)(c)-18XTZ, 23XTZ (DMS
2089) or Equivalent
STRING TIE
(e) Identification for in-line
junctions.
12DMS 2359 Type 2 Class
B
TAPE PRESSURE
SENSITIVE TAPE, AD-
HESIVE, WRAP ON
LABEL
(h)(i)(j) In-line junction.6CTM-16-090JUNCTION
20DC39-16SSKT T/C 11231123
10DC38-20PPIN T/C 11261126
(c)(d) Pins for in-line junctions.18M39029/22-193CONTACT T/C 542/546536
(c)(d)65D0086-26TERMINAL LUG 766766
(c)(d)45D0086-5TERMINAL LUG 761761
(c)(d)(f)(g)25D0086-6TERMINAL LUG 762762
(a) To be installed at position 8 on track assembly S3-526. Refer to SWPM 20-20-02 as an accepted procedure.
(b) String tie new wires to the existing wire bundle. Tie 1.25 +/- 0.25 inches from edge of clamp and every
2.75 +/- 0.25 inches between clamps. Refer to SWPM 20-10-01 as an accepted procedure.
(c) Or approved equivalent. Refer to AEPL, Drawing 7595071.
(d) Install terminals. Refer to SWPM 20-20-01 as an accepted procedure.
(e) Use DMS 2359 Type 2 Class B tape to identify each in-line junction. Refer to BAC 5153 as an accepted
procedure. Install 5.75-6.25 inches from both sides of the in-line junction. Refer to SWPM 20-00-03 as an
accepted procedure.
(f) Measure the electrical bond resistance between the terminal lug and the ground stud. Make sure the bond
resistance is not greater than 0.0025 ohms. Refer to SWPM 20-50-01 as an accepted procedure.
(g) Adjust NAS1096-3-* fastener length if/as required to ensure proper thread protrusion, and install referring
to SWPM 20-20-03 as an accepted procedure.
(h) Make sure to stagger in-line junctions to allow smooth transition of the bundle. Refer to SWPM 20-10-01
as an accepted procedure.
(i) Make sure not to terminate in-line junctions within a bend radius of the bundle. Refer to SWPM 20-10-01
as an accepted procedure.
(j) Make sure not to terminate in-line junctions in such a way, that a completed in-line junction will be positioned
inside a clamp. Refer to SWPM 20-10-01 as an accepted procedure.
FIGURE 3: ELECTRICAL/ELECTRONICS (E/E) COMPARTMENT - STA 110 RELAY PANEL AND AFT RIGHT
RADIO RACK - WIRING CHANGES
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 02, 2017
MD90-30A031
36 of 37
BOEING SERVICE BULLETIN MD90-30A031
ALERTALERT

### Page 37 (OCR)

BOEING SERVICE BULLETIN MD90-30A031
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 on
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)
Original Issue: June 02, 2017
Export Controlled ECCN: 9E991 - BOEING  MD90-30A031
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  37 of 37

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