# Boeing Alert Service Bulletin MD90-30A029: No revision named

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- Document: [Boeing Alert Service Bulletin MD90-30A029](https://openairdocs.org/service-documents/boeing/md90-30a029.md)
- Title as filed: U.S. DOT/FAA - BOEING SB-MD90-30A029-00
- Pages: 61
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### Page 1

Commercial 
Airplanes
MD90
Service Bulletin
ALERT
Number: MD90-30A029
Original Issue: November 25, 2015
ATA System: 3031
SUBJECT: NAVIGATION - Angle of Attack Sensor - External Case Heater Installation
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 © 2015 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Unpublished Work.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: November 25, 2015
MD90-30A029
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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  ........................................ 1 1
B. Concurrent Requirements ...................................... 1 1
C. Reason ................................................ 1 1
D. Description .............................................. 1 2
E. Compliance .............................................. 1 2
F . A p p r o v a l  ............................................... 1 2
G. Manpower .............................................. 1 3
H. Weight and Balance Changes .................................... 1 3
I. Electrical Load Data ......................................... 1 4
J . R e f e r e n c e s  .............................................. 1 5
1. Existing Data: ......................................... 1 5
2. Data Supplied with this Service Bulletin: ........................... 1 5
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 6
K. Publications Affected ........................................ 1 6
L. Interchangeability and Intermixability of Parts ........................... 1 6
M. Software Accomplishment Summary ................................ 1 6
2. MATERIAL INFORMATION ........................................ 1 7
A. Material - Price and Availability ................................... 1 7
B. Industry Support Information .................................... 1 7
C. Parts Necessary for Each Airplane ................................. 1 7
1 . K i t s / P a r t s  ............................................ 1 7
2. Parts and Materials Supplied by the Operator ........................ 2 0
3. Parts Modified and Reidentified ................................ 2 0
4. Parts Removed and Not Replaced .............................. 2 0
D. Parts Necessary to Change Spares ................................. 2 1
E. Special Tooling - Price and Availability ............................... 2 1
F. Special Tooling Necessary to do this Service Bulletin ....................... 2 1
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 3
A. GENERAL INFORMATION ..................................... 2 3
B. WORK INSTRUCTIONS ....................................... 2 5
FIGURE 1: FLIGHT COMPARTMENT, LEFT AND RIGHT SIDE - AOA SENSOR ENCLOSURE - DRILL
[Group 1] ............................................ 2 7
FIGURE 2: FLIGHT COMPARTMENT, LEFT AND RIGHT SIDE - CLIP ASSEMBLIES - INSTALL [Group
1 ]  ................................................ 3 0
FIGURE 3: FLIGHT COMPARTMENT TO STATION 110 RELAY PANEL - WIRES - WIRE ROUTING [Group
1 ]  ................................................ 3 3
FIGURE 4: FLIGHT COMPARTMENT, LEFT AND RIGHT SIDE - AOA SENSOR ENCLOSURE - APPLY
SEALANT [Group 1] ...................................... 4 2
FIGURE 5: AIRCRAFT EXTERIOR, LEFT AND RIGHT SIDE - AOA SENSOR EXTERNAL CASE HEATERS
AND AOA SENSORS - INSTALL [Group 1] .......................... 4 5
FIGURE 6: FLIGHT COMPARTMENT TO STATION 110 RELAY PANEL - WIRES - WIRE CHANGES
[Group 1] ............................................ 5 0
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FIGURE 7: STATION 110 RELAY PANEL - WIRES - WIRE ROUTING [Group 2] ........... 5 2
FIGURE 8: AIRCRAFT EXTERIOR, LEFT AND RIGHT SIDE - AOA SENSOR EXTERNAL CASE HEATERS
AND AOA SENSORS - INSTALL [Group 2] .......................... 5 4
FIGURE 9: FLIGHT COMPARTMENT TO STATION 110 RELAY PANEL - WIRES - WIRE CHANGES
[Group 2] ............................................ 5 9
APPENDIX A: PART DEMAND INTENT ................................... 6 1
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### Page 5

Commercial 
Airplanes
MD90
Service Bulletin
ALERT
SummaryNumber: MD90-30A029Original Issue: November 25, 2015
ATA System: 3031
SUBJECT: NAVIGATION - Angle of Attack Sensor - External Case Heater Installation
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
CONCURRENT REQUIREMENTS
None.
BACKGROUND
Stall Protection System anomalies have been reported on the 717-200 related to the Angle of Attack (AOA)
Sensor becoming immobilized and reporting incorrect angle of attack alpha values. Boeing investigation found
potential water intrusion and subsequent ice formation between the AOA sensor vane and face plate could
cause the vane to become immobilized until the airplane is operated at temperatures above freezing. The MD-90
uses the same AOA sensors as the 717 and the same potential for AOA vane immobilization exists. If this
condition occurs the Stall Protection System may become unreliable or non-functional which can result in unsafe
flight conditions or loss of controllability of the airplane.
Eight (8) reports from four (4) 717-200 operators identified stick shaker activation at airspeeds that were above
the stall protection system's stick shaker schedule. Review of the flight data and operator reports indicate the
AOA sensor vanes were exposed to moisture/water intrusion prior to and during takeoff/climb. As a result, the
AOA sensor vanes may become immobilized when the Total Air Temperature (TAT) is below 0 degrees Celsius
during the climb and cruise portion of flight. The consequence of this immobilization renders the Stall Protection
System non-functional until the airplane operates in above 0 degree Celsius conditions. Additionally, the MD-90
Stall Protection System does not incorporate the same 717 Mach compensated stall warning system or stick
shaker warning system features which under some conditions could alert the crew an AOA sensor is immobilized.
Performing this service bulletin installs AOA Sensor External Case Heaters on the Left and Right Side AOA
Sensor assemblies. External Case Heaters will increase the temperature of the AOA sensor assemblies to
mitigate the possibility of ice formation and subsequent system anomalies caused by AOA vane immobilization.
Boeing Fleet Team Digest (FTD) MD-90 FTD 34-09003 is related to this service bulletin.
This table is provided to operators for planning purposes only. Refer to the applicable sections for more
information.
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ReferenceAffectedPlanning Data
Paragraph 1.A.2., Spares AffectedNoSpares Affected
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
Group 1:
Get access to Flight compartment and Electronic Equipment compartment then do the following:
– Install clip assemblies and wires.
– Install Left and Right Side AOA Sensor External Case Heaters.
– Connect wires to Left and Right Side AOA Sensor External Case Heaters.
– Do the Functional Test of the Left and Right Side AOA Sensor External Case Heaters.
Group 2:
Get access to the Electronic Equipment compartment and do the following:
– Install Left and Right Side AOA Sensor External Case Heaters.
– Connect wires to Left and Right Side AOA Sensor External Case Heaters.
– Do the Functional Test of the Left and Right Side AOA Sensor External Case Heaters.
EFFECTIVITY
All 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 six years after the original
issue date of this service bulletin.
Export Controlled ECCN: 9E991 - BOEING
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INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
At the time of release of this service bulletin, warranty remedies have not been determined. A subsequent
revision or Information Notice will address the warranty remedies available, if any.
MANPOWER
Refer to Paragraph 1.G., Manpower
MATERIAL INFORMATION
Negotiated Kits/Parts.
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.
Export Controlled ECCN: 9E991 - BOEING
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BOEING SERVICE BULLETIN MD90-30A029
ALERT  ALERT
GROUP 1: INSTALL AOA SENSOR EXTERNAL CASE HEATERS AND WIRING.
GROUP 2: INSTALL AOA SENSOR EXTERNAL CASE HEATERS.
2350427
Original Issue: November 25, 2015
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Work - See page 1 for details.  8 of 61

### Page 9

Commercial 
Airplanes
MD90
Service Bulletin
ALERT
Number: MD90-30A029
Original Issue: November 25, 2015
ATA System: 3031
SUBJECT: NAVIGATION - Angle of Attack Sensor - External Case Heater Installation
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
This service bulletin is for the airplanes shown below.
All MD-90-30 aircraft.
DESCRIPTIONCONFIGURATIONGROUP
MD-90 airplanes applicable for kit SA90300029-3.-1
MD-90 airplanes applicable for kit SA90300029-5.-2
Airplane Models:
MD-90-30
GroupFuselage Num-
ber
12018
12094 - 2099
12100
12115
12117
12120
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### Page 10

GroupFuselage Num-
ber
12122 - 2123
12125 - 2126
12129
12131
12133
12136
12138
12140 - 2144
12146 - 2147
22149
12150
12153 - 2154
12156 - 2166
12168 - 2173
12175
12177
12179
12181 - 2182
12184
12186
12190 - 2191
12193 - 2195
12197 - 2198
12200
12202 - 2203
12205
12207
12209 - 2213
12215 - 2217
12219 - 2233
12235 - 2238
12240
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GroupFuselage Num-
ber
12242 - 2243
12245 - 2246
12248
12250 - 2251
12253
12255 - 2263
12288 - 2290
14001 - 4002
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
Stall Protection System anomalies have been reported on the 717-200 related to the Angle of Attack
(AOA) Sensor becoming immobilized and reporting incorrect angle of attack alpha values. Boeing
investigation found potential water intrusion and subsequent ice formation between the AOA sensor
vane and face plate could cause the vane to become immobilized until the airplane is operated at
temperatures above freezing. The MD-90 uses the same AOA sensors as the 717 and the same
potential for AOA vane immobilization exists. If this condition occurs the Stall Protection System may
become unreliable or non-functional which can result in unsafe flight conditions or loss of controllability
of the airplane.
Eight (8) reports from four (4) 717-200 operators identified stick shaker activation at airspeeds that
were above the stall protection system's stick shaker schedule. Review of the flight data and operator
reports indicate the AOA sensor vanes were exposed to moisture/water intrusion prior to and during
takeoff/climb. As a result, the AOA sensor vanes may become immobilized when the Total Air
Temperature (TAT) is below 0 degrees Celsius during the climb and cruise portion of flight. The
consequence of this immobilization renders the Stall Protection System non-functional until the airplane
operates in above 0 degree Celsius conditions. Additionally, the MD-90 Stall Protection System does
not incorporate the same 717 Mach compensated stall warning system or stick shaker warning system
features which under some conditions could alert the crew an AOA sensor is immobilized.
Performing this service bulletin installs AOA Sensor External Case Heaters on the Left and Right Side
AOA Sensor assemblies. External Case Heaters will increase the temperature of the AOA sensor
assemblies to mitigate the possibility of ice formation and subsequent system anomalies caused by
AOA vane immobilization.
Boeing Fleet Team Digest (FTD) MD-90 FTD 34-09003 is related to this service bulletin.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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### Page 12

D. Description
Group 1:
Get access to Flight compartment and Electronic Equipment compartment then do the following:
– Install clip assemblies and wires.
– Install Left and Right Side AOA Sensor External Case Heaters.
– Connect wires to Left and Right Side AOA Sensor External Case Heaters.
– Do the Functional Test of the Left and Right Side AOA Sensor External Case Heaters.
Group 2:
Get access to the Electronic Equipment compartment and do the following:
– Install Left and Right Side AOA Sensor External Case Heaters.
– Connect wires to Left and Right Side AOA Sensor External Case Heaters.
– Do the Functional Test of the Left and Right Side AOA Sensor External Case Heaters.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
114, 211MD-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 six years 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.
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G. Manpower
Group 1:
Elapsed HoursTask HoursNumber of PersonsTask
15.015.01Open Access
0.20.21Remove AOA Sen-
sors
0.40.41FIGURE 1
0.30.31FIGURE 2
9.39.31FIGURE 3
0.10.11FIGURE 4
2.02.01FIGURE 5 and FIG-
URE 6
15.015.01Close Access
0.51.02Test
42.843.3TOTAL FOR EACH AIRPLANE
Group 2:
Elapsed HoursTask HoursNumber of PersonsTask
1.01.01Open Access
0.20.21Remove AOA Sen-
sors
0.70.71FIGURE 7
2.02.01FIGURE 8 and FIG-
URE 9
1.01.01Close Access
0.51.02Test
5.45.9TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
Moment Change
(MEW) IN.-LBS
Mfr's Empty
Weight (MEW)
LBS
Approximate Sta-
tion (Inches)Airplane
+211.2+2.4+88.0MD-90
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I. Electrical Load Data
1. Alternating Current (AC) Load Changes.
UNITSE/NE/MVACUNITEQUIPMENT NAMEITEMCHAPCIRCUIT
BREAKER
BUS
%OPR
1
100
Phase
E
C
PF
115
1
Load
(W)
125
L-AOA Sensor External
Case Heater
201150 (WSP1377-1)
Hartzell
20xxx
H1-
151
300B1-251L
Average Watts% Time OperationCondition
15/30 M2/5 M5S15/30 M2/5 M
00000Loading
012500100Start
012500100Taxi
125125125100100Takeoff &
Climb
125125125100100Cruise Cold
125125125100100Cruise Hot
125125125100100Descent &
Land
00000Emergency
00000Ground
Service
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### Page 15

UNITSE/NE/MVACUNITEQUIPMENT NAMEITEMCHAPCIRCUIT
BREAKER
BUS
%OPR
1
100
Phase
E
C
PF
115
1
Load
(W)
125
R-AOA Sensor External
Case Heater
201150 (WSP1377-1)
Hartzell
20xxx
H1-
152
300B1-3412R
Average Watts% Time OperationCondition
15/30 M2/5 M5S15/30 M2/5 M
00000Loading
012500100Start
012500100Taxi
125125125100100Takeoff &
Climb
125125125100100Cruise Cold
125125125100100Cruise Hot
125125125100100Descent &
Land
00000Emergency
00000Ground
Service
J. References
1. Existing Data:
a. Standard Overhaul Practices Manual (SOPM) 20-10-01
b. Standard Wiring Practices Manual (SWPM) 20-00-03, 20-00-09, 20-00-16, 20-10-01
c. MD-90 Aircraft Maintenance Manual (AMM) 20-20-03, 24-00-00, 30-32-00, 34-19-02
d. MD-90 Fleet Team Digest (FTD) 34-09003
e. MD-90 Structural Repair Manual (SRM) 51
2. Data Supplied with this Service Bulletin:
None.
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### Page 16

3. Installation Drawings Used in the Preparation of this Service Bulletin:
ChangeTitleDocument Number
Installation of AOA
Sensor External
Case Heaters
ANGLE OF ATTACK SENSOR IMMO-
BILIZATION - SENSOR ENHANCE-
MENT
SR90300009 Revision
E
The table above lists applicable drawings used to prepare this service bulletin. The drawings are
not necessary to make the specified changes, and are not supplied with this service bulletin. The
drawings may not be applicable to all airplane configurations or operators.
K. Publications Affected
1. Publications:
Chapter-SectionPublication
30-30Fault Isolation Manual
34-19Illustrated Parts Catalog
30-31Aircraft Maintenance Manual
30-13, 30-30System Schematic Manual
30-1Special Compliance Items / Airworthiness
Limitations
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
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 parts 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 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 Service Bul-
letin (US Dollars)
ROLT as of the
Original Issue date
of this Service Bul-
letin (Calendar
Days)
QTYNameKit Number
$1,220.00901Service KitSA90300029-3
$120.00901Service KitSA90300029-5
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 configuration changes given in this service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts
To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
NOTE: There may be more kit parts than necessary to complete this service bulletin.
Group 1:
SA90300029-3 Service Kit
NotesExisting Part
Number
NameQtyNew Part Number
(a)WIRE KIT1SA90300029-101
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### Page 18

Group 1:
SA90300029-3 Service Kit
NotesExisting Part
Number
NameQtyNew Part Number
CLIP ASSY2230012-8R
TIE MOUNT25D0061-4
(b)STA-STRAP1009D0254-1-1-9
RIVET10MS20470AD3-5D
GROMMET10
in.
MS21266-2N
GROMMET2MS35489-1
SCREW2NAS1096-3-8
WASHER2NAS620-10L
CLIP ASSY5S2887245B6-10
SLEEVING1300
in.
SA90300029-7
JUNCTION4CTL-20-090
SOCKET T/C 5244MS39029/22-192
(a) Refer to SA90300029-101 Wire Kit table for Wire Kit contents.
(b) There may be more parts than necessary.
Group 1:
SA90300029-101 Wire Kit
NotesNameQtyNew Part Number
WIRE CODE 801960 in.D2426-1C-20NM
SOCKET T/C 5244MS39029/22-192
TERMINAL LUG 76225D0086-6
TERMINAL LUG 76125D0086-5
Group 2:
SA90300029-5 Service Kit
NotesExisting Part
Number
NameQtyNew Part Number
(a)STA-STRAP209D0254-1-1-9
JUNCTION4CTL-20-090
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### Page 19

Group 2:
SA90300029-5 Service Kit
NotesExisting Part
Number
NameQtyNew Part Number
SOCKET T/C 5248M39029/22-192
TERMINAL LUG
761
25D0086-5
(a) There may be more parts than necessary.
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### Page 20

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)SEALANTAS REQUIREDDMS 2082, CLASS
B2
OR
DMS 2427, CLASS
B2
(b)EXTERNAL CASE HEATER2WSP1377-1
(a) Refer to the Qualified Products List at the end of the Boeing Material Specification
(BMS) for supplier data.
(b) Order WSP1377-1 hardware from:
Roehl Jacob
Inside Sales Manager
ITT Aerospace / Electrofilm
Phone: 661-257-2242
Email: Roehl.jacob@itt.com
OR
Sharon Haack
Sales Administrator
ITT Aerospace / Electrofilm
Phone: 661-257-2242
Email: Sharon.haack@itt.com
3. Parts Modified and Reidentified
None.
4. Parts Removed and Not Replaced
None.
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### Page 21

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 22

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BLANK PAGE

### Page 23

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: 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: ELECTRICALLY GROUND THE AIRPLANE. THIS WILL HELP TO PREVENT DAMAGE
TO THE AIRPLANE OR EQUIPMENT.
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 20-10-01 for alternate full threaded fasteners (screws) needed for installation
in this service bulletin.
5. A 1/8-inch thick stack of the same type washers called for in this service bulletin is
the maximum thickness which may be used under fastener head or nut to counteract
accumulation of tolerances.
EXCEPTION: When the available fastener length increments are greater than
1/16-inch, a 3/16-inch thick stack of the same type washers may be used.
6. 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 MD-90 Structural Repair Manual,
Chapter 51.
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### Page 24

— Values for airframe maintenance tasks are included in Chapter 20 of MD-90
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 MD-90
Aircraft Maintenance Manual (AMM).
— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
7. Refer to the SWPM 20-10-01 as accepted wire installation procedures.
8. Obey all of the warnings and cautions given in the specified manual sections.
9. Refer to APPENDIX A for part demand intent survey.
10. 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.
11. 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.
12. 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.
13. 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.
14. If shading is used, shaded areas in Figures are reference only. Shaded areas in
Figures may look different than your airplane.
15. Use of colors in Figures is based on guidance from the ATA e-Business Program
(ATA) iSpec 2200.
16. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
17. Some steps in the Work Instructions are identified as Required for Compliance (RC).
If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps
identified as RC must be done to comply with the AD. Alternative procedures for
steps not identified with RC can be used if the RC steps can still be done as specified,
and the airplane can be put back in a serviceable condition. An Alternative Method
of Compliance (AMOC) is not necessary for deviations to steps that are not identified
as RC.
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### Page 25

B. WORK INSTRUCTIONS
Group 1:
1. Remove electrical power from the airplane. Refer to MD-90 AMM 24-00-00 as an accepted
procedure. Attach DO-NOT-CLOSE identifiers to opened circuit breakers and DO-NOT-OPERATE
identifiers to applicable switches. Use an independent power source for lighting.
2. The following items may require removal to accomplish this Service Bulletin.
– 3A071-0003-21-3, Seat Assembly, Left Side
– 9957803-1, Panel Assembly, Left Side
– 3646212-501, Panel Assembly, Left Side
– 3926386-501, Wedge Assembly, Left Side
– 9957802-49, Panel Assembly, Left Side
– 5916181-35, Footrest Assembly, Left Side
– 5916169-1, Footrest Assembly, Left Side
– 9966419-3, Panel, Left Side (Sidewall Panel / Speaker)
– 9957848-507, Floor Assembly, Left Side (Briefcase Console / Lift Up Panel)
– 9957820-21, Door, Left Side
– 5939725-105, Duct Assembly, Left Side
– MC10-08-127, Oxygen Mask, Captain Oxygen
– MXP402-2, Mask Stowage Box, Captain Oxygen
– 9966528-11, Bracket Assembly, Captain Oxygen
– 9955779-61, Panel Assembly, Pedestal / Step Panel
– 5957233-413, Cavity Assembly, Pedestal
– 50470-100, Seat Assembly-Observer, Cockpit Entrance Door
– MXP147-2, Mask Stowage Box, Observer Console
– 3A071-0004-21-3, Seat Assembly, Right Side
– 9955779-39, Door Assembly, Right Side
– 9957848-509, Floor Assembly, Right Side (Briefcase Console / Lift Up Panel)
– 9957802-50, Panel Assembly, Right Side
– 9957803-2, Panel Assembly, Right Side
– 3646212-502, Panel Assembly, Right Side
– 3926386-502, Wedge Assembly, Right Side
– 5916169-2, Footrest Assembly, Right Side
– 3914880-501, Panel Assembly, Right Side
– 9966528-12, Bracket Assembly, First Officer Oxygen
– MXP402-2, Mask Stowage Box, First Officer Oxygen
– 5916324-23, Wire Guard, E&E Compartment Left Side
– X=40.00 PANEL, Electrical Panel, E&E Compartment Left Side
3. Remove and keep the Left and Right Side Angle of Attack (AOA) Sensors. Refer to MD-90 AMM
34-19-02.
4. Change AOA Sensor Enclosures in accordance with FIGURE 1.
5. Install clip assemblies in accordance with FIGURE 2.
6. Route and clip wires in accordance with FIGURE 3.
7. Seal Left and Right Side AOA Sensor Enclosures in accordance with FIGURE 4.
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### Page 26

8. RC - Install the Left and Right Side AOA Sensor External Case Heaters, Left and Right Side AOA
Sensors and change wires in accordance with FIGURE 5 and FIGURE 6.
9. RC - Do the Functional Test of the Left and Right Side AOA Sensor External Case Heaters in
accordance with MD-90 AMM 30-32-00. If the Left and/or Right Side AOA Sensor External Case
Heaters fail the Functional Test, do corrective actions, repeat the Functional Test, and do applicable
corrective actions until the Left and Right Side AOA Sensor External Case Heaters pass the
Functional Test.
10. Put the airplane back to a serviceable condition.
Group 2:
1. Remove electrical power from the airplane. Refer to MD-90 AMM 24-00-00 as an accepted
procedure. Attach DO-NOT-CLOSE identifiers to opened circuit breakers and DO-NOT-OPERATE
identifiers to applicable switches. Use an independent power source for lighting.
2. Remove and keep the Left and Right Side Angle of Attack (AOA) Sensors. Refer to MD-90 AMM
34-19-02.
3. Route and clip wires in accordance with FIGURE 7.
4. RC - Install the Left and Right Side AOA Sensor External Case Heaters, Left and Right Side AOA
Sensors and change wires in accordance with FIGURE 8 and FIGURE 9.
5. RC - Do the Functional Test of the Left and Right Side AOA Sensor External Case Heaters in
accordance with MD-90 AMM 30-32-00. If the Left and/or Right Side AOA Sensor External Case
Heaters fail the Functional Test, do corrective actions, repeat the Functional Test, and do applicable
corrective actions until the Left and Right Side AOA Sensor External Case Heaters pass the
Functional Test.
6. Put the airplane back to a serviceable condition.
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### Page 27 (OCR)

BOEING SERVICE BULLETIN MD90-30A029
ALERT  ALERT
This Figure applies only to: Group 1.
STA
69.55
STA
83.55
0.26 DIA  0.25
2.50
2.00
1.00
0.50  A-A
FIGURE 1: FLIGHT COMPARTMENT, LEFT AND RIGHT SIDE - AOA SENSOR ENCLOSURE - DRILL
(SHEET 1 OF 3)
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### Page 28 (OCR)

BOEING SERVICE BULLETIN MD90-30A029
ALERT  ALERT
120.05
STA
101.55
STA
83.55
2.50
2.00
0.25  1.00
0.50
B-B  2350443
FIGURE 1: FLIGHT COMPARTMENT, LEFT AND RIGHT SIDE - AOA SENSOR ENCLOSURE - DRILL
(SHEET 2 OF 3)
Original Issue: November 25, 2015
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### Page 29

More DataQtyIdentificationNameTaskStep
(a)1-ANGLE OF ATTACK
SENSOR ENCLO-
SURE
Drill1
1MS35489-1GROMMETInstall (New)2
(a)1-ANGLE OF ATTACK
SENSOR ENCLO-
SURE
Drill3
1MS35489-1GROMMETInstall (New)4
(b)1MS21266-2NGROMMETInstall (New)5
(a) Drill and deburr a hole through the AOA Sensor Enclosure in the location specified. Refer to MD-90 SRM
51.
(b) Install MS21266-2N Caterpillar Grommet by cutting to fit on installation, refer to SWPM 20-00-09, cement
in place, refer to SWPM 20-00-09.
FIGURE 1: FLIGHT COMPARTMENT, LEFT AND RIGHT SIDE - AOA SENSOR ENCLOSURE - DRILL
(SHEET 3 OF 3)
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ALERTALERT

### Page 30 (OCR)

BOEING SERVICE BULLETIN MD90-30A029
ALERT  ALERT
This Figure applies only to: Group 1.
STA
69.55
STA
83.55
STA
69.55
3) 3 LOCATIONS
STA
12.00  83.55
- 11.00
12.00
11.00
2350447
FIGURE 2: FLIGHT COMPARTMENT, LEFT AND RIGHT SIDE - CLIP ASSEMBLIES - INSTALL
(SHEET 1 OF 3)
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### Page 31 (OCR)

BOEING SERVICE BULLETIN MD90-30A029
ALERT  ALERT
STA
120.05
13.50  ® 2 LOCATIONS
12.50
STA
101.55
2.50
1.50
STA
83.55
2350448
FIGURE 2: FLIGHT COMPARTMENT, LEFT AND RIGHT SIDE - CLIP ASSEMBLIES - INSTALL
(SHEET 2 OF 3)
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### Page 32

More DataQtyIdentificationNameTaskStep
1230012-8RCLIP ASSYInstall (New)1
15D0061-4TIE MOUNTInstall (New)
1NAS620-10LWASHERInstall (New)
1NAS1096-3-8SCREWInstall (New)
1230012-8RCLIP ASSYInstall (New)2
15D0061-4TIE MOUNTInstall (New)
1NAS620-10LWASHERInstall (New)
1NAS1096-3-8SCREWInstall (New)
5S2887245B6-10CLIP ASSYInstall (New)3
(a)10MS20470AD3-5DRIVETInstall (New)
(a) Refer to MD-90 SRM 51.
FIGURE 2: FLIGHT COMPARTMENT, LEFT AND RIGHT SIDE - CLIP ASSEMBLIES - INSTALL
(SHEET 3 OF 3)
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### Page 33 (OCR)

BOEING SERVICE BULLETIN MD90-30A029
ALERT  ALERT
This Figure applies only to: Group 1.
STA
69.55
STA
83.55
STA
69.55
TO: GND4114
STA
83.55
2350453
FIGURE 3: FLIGHT COMPARTMENT TO STATION 110 RELAY PANEL - WIRES - WIRE ROUTING
(SHEET 1 OF 9)
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### Page 34 (OCR)

BOEING SERVICE BULLETIN MD90-30A029
ALERT  ALERT
STA
120.05
STA
101.55
STA
83.55
TO: GND4113
2351214
FIGURE 3: FLIGHT COMPARTMENT TO STATION 110 RELAY PANEL - WIRES - WIRE ROUTING
(SHEET 2 OF 9)
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### Page 35 (OCR)

BOEING SERVICE BULLETIN MD90-30A029
ALERT  ALERT
STA
120.05
2350454
FIGURE 3: FLIGHT COMPARTMENT TO STATION 110 RELAY PANEL - WIRES - WIRE ROUTING
(SHEET 3 OF 9)
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### Page 36 (OCR)

BOEING SERVICE BULLETIN MD90-30A029
ALERT  ALERT
STA
101  .55
STA
120.05
2350464
FIGURE 3: FLIGHT COMPARTMENT TO STATION 110 RELAY PANEL - WIRES - WIRE ROUTING
(SHEET 4 OF 9)
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### Page 37

FIGURE 3: FLIGHT COMPARTMENT TO STATION 110 RELAY PANEL - WIRES - WIRE ROUTING
(SHEET 5 OF 9)
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### Page 38 (OCR)

BOEING SERVICE BULLETIN MD90-30A029
ALERT  ALERT
S-19L
S-20L-
S-23L
S-24L
S-25L
S-26L
S-27L
S-30L
STA
148
2350479
FIGURE 3: FLIGHT COMPARTMENT TO STATION 110 RELAY PANEL - WIRES - WIRE ROUTING
(SHEET 6 OF 9)
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### Page 39 (OCR)

BOEING SERVICE BULLETIN MD90-30A029
ALERT  ALERT
STA
160
STA
148
2351197
FIGURE 3: FLIGHT COMPARTMENT TO STATION 110 RELAY PANEL - WIRES - WIRE ROUTING
(SHEET 7 OF 9)
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### Page 40 (OCR)

BOEING SERVICE BULLETIN MD90-30A029
ALERT  ALERT
STA
120
STA
134
R2-100
2350481
FIGURE 3: FLIGHT COMPARTMENT TO STATION 110 RELAY PANEL - WIRES - WIRE ROUTING
(SHEET 8 OF 9)
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### Page 41

More DataQtyIdentificationNameTaskStep
(a) (b) (c) (d) (e) (f)-1F1652B20WIREInstall (New)1
-SA90300029-7SLEEVINGInstall (New)
-9D0254-1-1-9STA-STRAPInstall (New)
(a) (b) (c) (d) (e) (f)-2F1652B20WIREInstall (New)2
-SA90300029-7SLEEVINGInstall (New)
-9D0254-1-1-9STA-STRAPInstall (New)
(a) (b) (d) (e) (f)-1F1653A20NWIREInstall (New)3
-SA90300029-7SLEEVINGInstall (New)
-9D0254-1-1-9STA-STRAPInstall (New)
(a) (b) (d) (e) (f)-2F1653A20NWIREInstall (New)4
-SA90300029-7SLEEVINGInstall (New)
-9D0254-1-1-9STA-STRAPInstall (New)
(a) Slide on SA90300029-7 SLEEVING to wire.
(b) Insert wire through the center hole of its respective rubber grommet leaving 18 to 24 inches of wire length
on the inside of the AOA Sensor Enclosure.
(c) Before cutting of new sleeved wires make sure to leave extra length at relay panel end for 2 reterminations.
(d) After cutting of new sleeved wires string tie sleeve at both ends.
(e) Attach wire identification tag at both ends of sleeves, refer to SWPM 20-00-03.
(f) Attach new sleeved wires to existing wire bundle using 9D0254-1-1-9 STA-STRAP, refer to SWPM 20-
10-01.
FIGURE 3: FLIGHT COMPARTMENT TO STATION 110 RELAY PANEL - WIRES - WIRE ROUTING
(SHEET 9 OF 9)
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ALERTALERT

### Page 42 (OCR)

BOEING SERVICE BULLETIN MD90-30A029
ALERT  ALERT
This Figure applies only to: Group 1.
STA
69.55
STA
83.55
STA
69.55
STA
83.55
LO1-Z0
201-Z0
2350457
FIGURE 4: FLIGHT COMPARTMENT, LEFT AND RIGHT SIDE - AOA SENSOR ENCLOSURE - APPLY
SEALANT
(SHEET 1 OF 3)
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### Page 43 (OCR)

BOEING SERVICE BULLETIN MD90-30A029
ALERT  ALERT
STA
83.55
2-10.
2-10.
GROMMET
ANGLE OF ATTACK
ENCLOSURE  ANGLE OF ATTACK
• ENCLOSURE
A-A
FIGURE 4: FLIGHT COMPARTMENT, LEFT AND RIGHT SIDE - AOA SENSOR ENCLOSURE - APPLY
SEALANT
(SHEET 2 OF 3)
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### Page 44

More DataQtyIdentificationNameTaskStep
(a)-DMS 2082, CLASS 2
(DMS 2427, CLASS 2
optional)
SEALANTApply1
(a) A fillet of sealant shall be applied from the enclosure to the rubber grommet and from the slot of the rubber
grommet to the wires as given in MD-90 AMM 20-20-03. Perform this sealing process on both sides of
the AOA Sensor Enclosure.
FIGURE 4: FLIGHT COMPARTMENT, LEFT AND RIGHT SIDE - AOA SENSOR ENCLOSURE - APPLY
SEALANT
(SHEET 3 OF 3)
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ALERTALERT

### Page 45 (OCR)

BOEING SERVICE BULLETIN MD90-30A029
ALERT  ALERT
This Figure applies only to: Group 1.
H1-151
• FUSELAGE SKIN
A-A
FIGURE 5: AIRCRAFT EXTERIOR, LEFT AND RIGHT SIDE - AOA SENSOR EXTERNAL CASE HEATERS
AND AOA SENSORS - INSTALL
(SHEET 1 OF 5)
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### Page 46 (OCR)

BOEING SERVICE BULLETIN MD90-30A029
ALERT  ALERT
• H1-152
FUSELAGE SKIN
B-B  2350716
FIGURE 5: AIRCRAFT EXTERIOR, LEFT AND RIGHT SIDE - AOA SENSOR EXTERNAL CASE HEATERS
AND AOA SENSORS - INSTALL
(SHEET 2 OF 5)
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### Page 47 (OCR)

BOEING SERVICE BULLETIN MD90-30A029
ALERT  ALERT
EXTERNAL
CASE HEATER
H1-151
-FACE PLATE
ANGLE OF ATTACK
SENSOR CASE ~
-VANE
EXTERNAL
CASE HEATER
C-C  2350806
FIGURE 5: AIRCRAFT EXTERIOR, LEFT AND RIGHT SIDE - AOA SENSOR EXTERNAL CASE HEATERS
AND AOA SENSORS - INSTALL
(SHEET 3 OF 5)
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### Page 48 (OCR)

BOEING SERVICE BULLETIN MD90-30A029
ALERT  ALERT
EXTERNAL
CASE HEATER
H1-152
FACE PLATE-  ANGLE OF ATTACK
SENSOR CASE
CASE HEATER 5  EXTERNAL
D-D  2443011
FIGURE 5: AIRCRAFT EXTERIOR, LEFT AND RIGHT SIDE - AOA SENSOR EXTERNAL CASE HEATERS
AND AOA SENSORS - INSTALL
(SHEET 4 OF 5)
Original Issue: November 25, 2015
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  MD90-30A029
Work - See page 1 for details.  48 of 61

### Page 49

More DataQtyIdentificationNameTaskStep
(a) (b) (c)1WSP1377-1EXTERNAL CASE
HEATER
Install (New)1
(d) (e)1NAS1801-06-12SCREWInstall (New)2
(e)1NAS620-06WASHERInstall (New)
(e) (f)1MS21042L06NUTInstall (New)
(g)1081EW1ANGLE OF ATTACK
SENSOR
Install (Kept)3
(a) (c) (h)1WSP1377-1EXTERNAL CASE
HEATER
Install (New)4
(d) (e)1NAS1801-06-12SCREWInstall (New)5
(e)1NAS620-6WASHERInstall (New)
(e) (f)1MS21042L06NUTInstall (New)
(g)1081EW1ANGLE OF ATTACK
SENSOR
Install (Kept)6
(a) Ensure that the External Case Heater seats firmly against the aft face of the transducer's faceplate and
radially around the transducer case.
(b) Item Number H1-151 is to be ink stamped on structure adjacent to part. Apply marking per SWPM 20-00-
09. Markings should be visible after equipment is installed. Marking to be black .19 high. Adhesive-backed
markers installed per SWPM 20-00-09 may be substituted for ink stamping.
(c) Cut the vendor furnished External Case Heater wires to 5.0 in +/- 1.0 inch length.
(d) Apply anaerobic locking/sealing compound A60079 on the screw threads before installation.
(e) This part is supplier furnished with WSP1377-1.
(f) Torque the nut to 10 in-lb (1.1 N-m) - 12 in-lb (1.4 N-m).
(g) Install in accordance with MD-90 AMM 34-19-02.
(h) Item Number H1-152 is to be ink stamped on structure adjacent to part. Apply marking per SWPM 20-00-
09. Markings should be visible after equipment is installed. Marking to be black .19 high. Adhesive-backed
markers installed per SWPM 20-00-09 may be substituted for ink stamping.
FIGURE 5: AIRCRAFT EXTERIOR, LEFT AND RIGHT SIDE - AOA SENSOR EXTERNAL CASE HEATERS
AND AOA SENSORS - INSTALL
(SHEET 5 OF 5)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 25, 2015
MD90-30A029
49 of 61
BOEING SERVICE BULLETIN MD90-30A029
ALERTALERT

### Page 50 (OCR)

BOEING SERVICE BULLETIN MD90-30A029
ALERT  ALERT
This Figure applies only to: Group 1.
EXTERNAL CASE  HEATER  - -  H1-152  R ANGLE OF ATTACK ENCLOSURE  EXTERNAL CASE  HEATER  H1-151  LANGLE OF ATTACK ENCLOSURE
J2-104  P30-ZZE  STA 80  J2-101  FURNI  J2-102  FURNH115120WHBK  P3-XZG  STA 80  ADDED WIRE OR NEW ROUTING  + DELETED WIRE OR FORMER ROUTING  EXISTING WIRE  ~ COILED AND STOWED
• 2F1653A20N  1F1652B20  1F1652A22 -  - 1F1653A20N
R2-100  R STALL WARN  VANE AND  STATIC PORT  HEATER  R2-99  L STALL WARN  VANE AND  STATIC PORT  HEATER  STA 110  RELAY PANEL
• 2F1668A22  1F1668A22
115VAC-OC-R  B1-341  R STALL WARN  AND VANE HEATER  115VAC-OC-L  B1-25  L STALL WARN  AND VANE HEATER  LOWER EPC  CIRCUIT BREAKER PANEL
2350815
FIGURE 6: FLIGHT COMPARTMENT TO STATION 110 RELAY PANEL - WIRES - WIRE CHANGES
(SHEET 1 OF 2)
Original Issue: November 25, 2015
Export Controlled ECCN: 9E991 - BOEING  MD90-30A029
PROPRIETARY - Copyright © Unpublished  Work - See page 1 for details.  50 of 61

### Page 51

MORE DATAQTYPART NUMBERNAMETERM
CODE
(a)25D0086-6TERMINAL LUG 762762
8MS39029/22-192SOCKET T/C 524524
25D0086-5TERMINAL LUG 761761
(a) Refer to SWPM 20-00-16.
FIGURE 6: FLIGHT COMPARTMENT TO STATION 110 RELAY PANEL - WIRES - WIRE CHANGES
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 25, 2015
MD90-30A029
51 of 61
BOEING SERVICE BULLETIN MD90-30A029
ALERTALERT

### Page 52 (OCR)

BOEING SERVICE BULLETIN MD90-30A029
ALERT  ALERT
This Figure applies only to: Group 2.
STA
69.55
R2-100
LEFT SIDE LOOKING FWD AND OUTBD
2351276
FIGURE 7: STATION 110 RELAY PANEL - WIRES - WIRE ROUTING
(SHEET 1 OF 2)
Original Issue: November 25, 2015
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  MD90-30A029
Work - See page 1 for details.  52 of 61

### Page 53

More DataQtyIdentificationNameTaskStep
-1F1652B20WIREChange1
-9D0254-1-1-9STA-STRAPInstall (New)
-2F1652B20WIREChange2
-9D0254-1-1-9STA-STRAPInstall (New)
(a) Attach sleeved wires to existing wire bundle using 9D0254-1-1-9 STA-STRAP, refer to SWPM 20-10-01.
FIGURE 7: STATION 110 RELAY PANEL - WIRES - WIRE ROUTING
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 25, 2015
MD90-30A029
53 of 61
BOEING SERVICE BULLETIN MD90-30A029
ALERTALERT

### Page 54 (OCR)

BOEING SERVICE BULLETIN MD90-30A029
ALERT  ALERT
This Figure applies only to: Group 2.
B
H1-151
• FUSELAGE SKIN
A-A  2350953
FIGURE 8: AIRCRAFT EXTERIOR, LEFT AND RIGHT SIDE - AOA SENSOR EXTERNAL CASE HEATERS
AND AOA SENSORS - INSTALL
(SHEET 1 OF 5)
Original Issue: November 25, 2015
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  MD90-30A029
Work - See page 1 for details.  54 of 61

### Page 55 (OCR)

BOEING SERVICE BULLETIN MD90-30A029
ALERT  ALERT
H1-152
FUSELAGE SKIN -
B-B  2350955
FIGURE 8: AIRCRAFT EXTERIOR, LEFT AND RIGHT SIDE - AOA SENSOR EXTERNAL CASE HEATERS
AND AOA SENSORS - INSTALL
(SHEET 2 OF 5)
Original Issue: November 25, 2015
Export Controlled ECCN: 9E991 - BOEING  MD90-30A029
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  55 of 61

### Page 56 (OCR)

BOEING SERVICE BULLETIN MD90-30A029
ALERT  ALERT
EXTERNAL
CASE HEATER
H1-151
- FACE PLATE
ANGLE OF ATTACK
SENSOR CASE ~
VANE
EXTERNAL
CASE HEATER
C-C  2350954
FIGURE 8: AIRCRAFT EXTERIOR, LEFT AND RIGHT SIDE - AOA SENSOR EXTERNAL CASE HEATERS
AND AOA SENSORS - INSTALL
(SHEET 3 OF 5)
Original Issue: November 25, 2015
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  MD90-30A029
Work - See page 1 for details.  56 of 61

### Page 57 (OCR)

BOEING SERVICE BULLETIN MD90-30A029
ALERT  ALERT
EXTERNAL
• CASE HEATER
H1-152
FACE PLATE  ANGLE OF ATTACK
SENSOR CASE
EXTERNAL
CASE HEATER
D-D  2443009
FIGURE 8: AIRCRAFT EXTERIOR, LEFT AND RIGHT SIDE - AOA SENSOR EXTERNAL CASE HEATERS
AND AOA SENSORS - INSTALL
(SHEET 4 OF 5)
Original Issue: November 25, 2015
Export Controlled ECCN: 9E991 - BOEING  MD90-30A029
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  57 of 61

### Page 58

More DataQtyIdentificationNameTaskStep
(a) (b) (c)1WSP1377-1EXTERNAL CASE
HEATER
Install (New)1
(d) (e)1NAS1801-06-12SCREWInstall (New)2
(e)1NAS620-6WASHERInstall (New)
(e) (f)1MS21042L06NUTInstall (New)
(g)-081EW1ANGLE OF ATTACK
SENSOR
Install (Kept)3
(a) (c) (h)1WSP1377-1EXTERNAL CASE
HEATER
Install (New)4
(d) (e)1NAS1801-06-12SCREWInstall (New)5
(e)1NAS620-6WASHERInstall (New)
(e) (f)1MS21042L06NUTInstall (New)
(g)-081EW1ANGLE OF ATTACK
SENSOR
Install (Kept)6
(a) Ensure that the External Case Heater seats firmly against the aft face of the transducer's faceplate and
radially around the transducer case.
(b) Item Number H1-151 is to be ink stamped on structure adjacent to part. Apply marking per SWPM 20-00-
09. Markings should be visible after equipment is installed. Marking to be black .19 high. Adhesive-backed
markers installed per SWPM 20-00-09 may be substituted for ink stamping.
(c) Cut the vendor furnished External Case Heater wires to 5.0 inch +/- 1.0 inch length.
(d) Apply anaerobic locking/sealing compound A60079 on the screw threads before installation.
(e) This part is supplier furnished with WSP1377-1.
(f) Torque the nut to 10 in-lb (1.1 N-m) - 12 in-lb (1.4 N-m).
(g) Install in accordance with MD-90 AMM 34-19-02.
(h) Item Number H1-152 is to be ink stamped on structure adjacent to part. Apply marking per SWPM 20-00-
09. Markings should be visible after equipment is installed. Marking to be black .19 high. Adhesive-backed
markers installed per SWPM 20-00-09 may be substituted for ink stamping.
FIGURE 8: AIRCRAFT EXTERIOR, LEFT AND RIGHT SIDE - AOA SENSOR EXTERNAL CASE HEATERS
AND AOA SENSORS - INSTALL
(SHEET 5 OF 5)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 25, 2015
MD90-30A029
58 of 61
BOEING SERVICE BULLETIN MD90-30A029
ALERTALERT

### Page 59 (OCR)

BOEING SERVICE BULLETIN MD90-30A029
ALERT  ALERT
This Figure applies only to: Group 2.
EXTERNAL CASE  HEATER  H1-152  R ANGLE OF ATTACK ENCLOSURE  EXTERNAL CASE  HEATER  H1-151  LANGLE OF ATTACK ENCLOSURE
20WHBK
FURNI  P30-ZZE  STA Pr  J2-101  FURNI  ~ J2-102  FURNH1  P3-XZG  STA 80  ADDED WIRE OR NEW ROUTING  + DELETED WIRE OR FORMER ROUTING  EXISTING WIRE  ~ COILED AND STOWED
2F1653A20N  1F1652B20  1F1652A22  4112- 1F1653A20N
R2-100  R SANE ANDRIN  STATIC PORT  HEATER  761)  R2-99  L STALL WARN  VANE AND  STATIC PORT  HEATER  STA 110  RELAY PANEL
• 1F1668A22
15VAC-OC-R  B1-341  R STALL WARN  AND VANE HEATER  115VAC-0C-L  L STALL WARN  AND VANE HEATER  LOWER EPC  CIRCUIT BREAKER PANEL
2350956
FIGURE 9: FLIGHT COMPARTMENT TO STATION 110 RELAY PANEL - WIRES - WIRE CHANGES
(SHEET 1 OF 2)
Original Issue: November 25, 2015
Export Controlled ECCN: 9E991 - BOEING  MD90-30A029
PROPRIETARY - Copyright © Unpublishec  Work - See page 1 for details.  59 of 61

### Page 60

MORE DATAQTYPART NUMBERNAMETERM
CODE
(a)8MS39029/22-192SOCKET T/C 524524
25D0086-5TERMINAL LUG 761761
(a) Refer to SWPM 20-00-16.
FIGURE 9: FLIGHT COMPARTMENT TO STATION 110 RELAY PANEL - WIRES - WIRE CHANGES
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 25, 2015
MD90-30A029
60 of 61
BOEING SERVICE BULLETIN MD90-30A029
ALERTALERT

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