# Boeing Alert Service Bulletin MD90-29A021: U.S. DOT/FAA - SB-MD90-29A021-02

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- Document: [Boeing Alert Service Bulletin MD90-29A021](https://openairdocs.org/service-documents/boeing/md90-29a021.md)
- Title as filed: U.S. DOT/FAA - SB-MD90-29A021-02
- Pages: 81
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## Text

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Commercial 
Airplanes
MD90
Service Bulletin
ALERT
Number: MD90-29A021
Original Issue: May 15, 2007
Revision 2: March 16, 2010
ATA System: 2920
SUBJECT: HYDRAULIC POWER - Auxiliary Hydraulic Power System - Replaces the Auxiliary
Hydraulic Pump Wire Harness and Changes Routing Installation
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 730-774). 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 © 2007 The Boeing Company
Unpublished Work - All Rights Reserved
Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable
subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.
This document includes proprietary information owned by The Boeing Company and/or one or more third parties.
Treatment of the document and the information it contains is governed by contract with Boeing. For more
information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.
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, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the
Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in
connection with this document unless provided in writing by Boeing.
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Table of Contents
Revision Transmittal Sheet ............................................ 5
Summary ...................................................... 7
1. PLANNING INFORMATION ........................................ 9
A. Effectivity ................................................ 9
1. Airplanes ............................................. 9
2. Spares Affected ........................................ 1 2
B. Concurrent Requirements ...................................... 1 2
C. Reason ................................................ 1 2
D. Description .............................................. 1 2
E. Compliance .............................................. 1 3
F. Approval ............................................... 1 3
G. Manpower .............................................. 1 3
H. Weight and Balance Changes .................................... 1 5
I. Electrical Load Data ......................................... 1 5
J. References .............................................. 1 6
1. Existing Data: ......................................... 1 6
2. Data supplied with this Service Bulletin: ........................... 1 6
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 7
2. MATERIAL INFORMATION ........................................ 1 9
A. Material - Price and Availability ................................... 1 9
B. Industry Support Information .................................... 2 0
C. Parts Necessary For Each Airplane ................................. 2 0
1. Kits/Parts: ........................................... 2 0
2. Parts and Materials Supplied by the Operator: ........................ 2 3
3. Parts Modified and Reidentified: ............................... 2 4
4. Parts Removed and Not Replaced: .............................. 2 4
D. Parts Necessary to Change Spares ................................. 2 4
E. Special Tooling - Price and Availability ............................... 2 4
F. Special Tooling Necessary to do this Service Bulletin ....................... 2 4
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 5
A. GENERAL INFORMATION ..................................... 2 5
B. WORK INSTRUCTIONS ....................................... 2 6
FIGURE 1: AUXILIARY HYDRAULIC PUMP WIRE HARNESS - REMOVAL [Group 1, Configuration 1-2;
Group 2, Configuration 1] ................................... 3 4
FIGURE 2: AUXILIARY HYDRAULIC PUMP WIRE HARNESS - SUPPORT BRACKETS - INSTALL [Group
1, Configuration 1-2; Group 2, Configuration 1] ........................ 3 7
FIGURE 3: AUXILIARY HYDRAULIC PUMP WIRE HARNESS - INSTALL [Group 1, Configuration 2; Group
2, Configuration 1] ....................................... 4 1
FIGURE 4: ELECTRICAL WIRING DIAGRAM - TERMINATE WIRE HARNESS [Group 1, Configuration 1-2;
Group 2, Configuration 1] ................................... 4 7
FIGURE 5: CLAMPS COMMON TO EXISTING WIRE HARNESSES - INSTALL [Group 1, Configuration
1-2; Group 2, Configuration 1] ................................. 4 8
FIGURE 6: AUXILIARY HYDRAULIC PUMP WIRE HARNESS - SUPPORT BRACKET AND CLAMP -
INSTALLATION [Group 1, Configuration 3] .......................... 5 1
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FIGURE 7: AUXILIARY HYDRAULIC PUMP WIRE HARNESS - SUPPORT BRACKET AND CLAMP -
INSTALLATION [Group 1, Configuration 3-4; Group 2, Configuration 2] .......... 5 7
FIGURE 8: AUXILIARY HYDRAULIC PUMP WIRE HARNESS - WIRE HARNESS - INSTALLATION [Group
1, Configuration 1] ....................................... 6 1
FIGURE 9: AUXILIARY HYDRAULIC PUMP WIRE HARNESS - SUPPORT CLAMP - INSTALLATION
[Group 1, Configuration 3-5; Group 2, Configuration 2-3] .................. 7 3
FIGURE 10: AUXILIARY HYDRAULIC PUMP WIRE HARNESS - CHECK ELECTRICAL RESISTANCE
[Group 1, Configuration 3-5; Group 2, Configuration 2-3] .................. 7 5
FIGURE 11: AUXILIARY HYDRAULIC PUMP WIRE HARNESS - SLEEVING - INSPECTION/INSTALLATION
[Group 1, Configuration 3-5; Group 2, Configuration 2-3] .................. 7 9
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Commercial 
Airplanes
MD90
Service Bulletin
ALERT
Revision Transmittal SheetNumber: MD90-29A021Original Issue: May 15, 2007
Revision 2: March 16, 2010
ATA System: 2920
SUBJECT: HYDRAULIC POWER - Auxiliary Hydraulic Power System - Replaces the Auxiliary
Hydraulic Pump Wire Harness and Changes Routing Installation
This Revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
More work is necessary on airplanes changed in accordance with the original issue or Revision 1 of this service
bulletin. The additional work involves checking electrical resistance, adding new clamps at two positions, adding
sleeving to the wire harness if its missing, and adding red tape to the connector end of the wire harness if its
missing. An additional 3.0 hours is required to complete the additional work described in this revision of this
service bulletin.
Federal Aviation Administration (FAA) Airworthiness Directive AD 2009-07-04 is related to this service bulletin.
REASON FOR REVISION
This revision is sent to incorporate engineering released subsequent to Revision 1 of this service bulletin, which
changes the wire harness clamp and sleeving installation. The data given in Information Notices MD90-29A021
IN 03 and MD90-29A021 IN 04 are included in this revision.
These sections were changed:
1. In Paragraph 1.A., Effectivity, changed group configuration table to reflect correct requirements.
2. In Paragraph 1.E., Compliance, added FAA Airworthiness Directive AD 2009-07-04 and changed compliance
time.
3. In Paragraph 1.F., Approval, changed approval statement.
4. In Paragraph 1.G., Manpower, changed manpower tables.
5. In Paragraph 1.J.1., Existing Data, added FAA Airworthiness Directive AD 2009-07-04 and Boeing Multiple
Operator Message (MOM) MOM-MOM-10-0034.
6. In Paragraph 1.J.3., Installation Drawings Used in the Preparation of this Service Bulletin, changed drawing
revision level.
7. In Paragraph 1.K., Publications, added Damage Tolerance Based Structural Inspections statement.
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8. In Paragraph 2.A., Material - Price and Availability, changed kit numbers, kit pricing and expiration date.
9. In Paragraph 2.C.1., Kits/Parts, changed kit applicability and parts lists to reflect correct requirements.
10. In Paragraph 2.C.2., Parts and Materials Supplied by the Operator, added new required materials.
11. In Paragraph 3., Accomplishment Instructions:
a. Added new General Information notes.
b. Changed Work Instructions to reflect correct requirements.
c. Changed Figures 1, 2, 3, 5, 6, 7, 8, 9 to reflect correct requirements.
d. Changed Figure 10.
e. Added Figure 11.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location
of important changes.
Pages with no vertical lines have no important changes.
REVISION HISTORY
May 15, 2007Original Issue:
August 29, 2008Revision 1:
March 16, 2010Revision 2:
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Commercial 
Airplanes
MD90
Service Bulletin
ALERT
SummaryNumber: MD90-29A021Original Issue: May 15, 2007
Revision 2: March 16, 2010
ATA System: 2920
SUBJECT: HYDRAULIC POWER - Auxiliary Hydraulic Power System - Replaces the Auxiliary
Hydraulic Pump Wire Harness and Changes Routing 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
On MD-80 airplanes three operators have reported three instances of electrically shorted wires in the right wheel
well and evidence of arcing on the auxiliary hydraulic pump power cables. One incident resulted in a fire in the
wheel well. Investigation revealed damage to the power cables was caused by structural chafing. In addition,
the Special Federal Aviation Regulation (SFAR) 88 analysis determined that extra protection is required on the
auxiliary hydraulic pump wire harness assembly where it comes in close proximity to the center fuel tank. MD-90
airplanes have a similar installation and Boeing analysis determined that the existing auxiliary hydraulic pump
wire harness assembly is routed within the tire burst area. A new and longer auxiliary hydraulic pump wire
harness assembly installed and routed outside the "tire burst" area will minimize the possibility of chaffing and
electrical wire arcing damage. If not corrected, electrical arcing and/or shorted wires could result in a wheel well
fire and/or hazard to the adjacent fuel tank.
This service bulletin is the result of the safety assessments conducted by Boeing under SFAR 88, "Fuel Tank
System Fault Tolerance Evaluation Requirements".
ACTION
This service bulletin provides instructions to install a new auxiliary hydraulic pump wire harness assembly and
route it outside of the "tire burst" area.
EFFECTIVITY
MD-90-30 Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.
COMPLIANCE
Federal Aviation Administration (FAA) Airworthiness Directive AD 2009-07-04 is related to this service bulletin.
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Boeing recommends that operators accomplish this service bulletin within 18 months after the date of Revision
2 on this service bulletin.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are available only for installation of the missing support bracket and installation of
an additional wire harness assembly support clamp for the affected airplanes (described in MD90-29A021
Revision 1) in warranty as of January 1, 2000. Please refer to Paragraph 2.B., Industry Support Information.
MANPOWER
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
Boeing supplied Parts/Materials.
Refer to Paragraph 2.A., Material - Price and Availability.
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Commercial 
Airplanes
MD90
Service Bulletin
ALERT
Number: MD90-29A021
Original Issue: May 15, 2007
Revision 2: March 16, 2010
ATA System: 2920
SUBJECT: HYDRAULIC POWER - Auxiliary Hydraulic Power System - Replaces the Auxiliary
Hydraulic Pump Wire Harness and Changes Routing 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.
NOTE: The intent of this service bulletin was accomplished on fuselage number 2094 prior to
the release of the original issue, at an operator's facility during a service bulletin validation.
The intent of this service bulletin was accomplished on fuselage number 2117 prior to
the release of Revision 2, at an operator's facility during a service bulletin validation.
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DESCRIPTIONCONFIGURATIONGROUP
MD-90 Airplanes with fuselage numbers 2018 through 2249.-1
Airplanes that have not accomplished the original issue or Revision
1 of this service bulletin and have not accomplished Service Bulletin
MD90-29-012.
1
Airplanes that have not accomplished the original issue or Revision
1 of this service bulletin and have accomplished Service Bulletin
MD90-29-012.
2
Airplanes that have accomplished the original issue of this service
bulletin and have not accomplished Service Bulletin MD90-29-012.
3
Airplanes that have accomplished the original issue of this service
bulletin and have accomplished Service Bulletin MD90-29-012.
4
Airplanes that have accomplished Revision 1 of this service bulletin.5
MD-90 Airplanes with fuselage numbers 2250 and higher.-2
Airplanes that have not accomplished the original issue or Revision
1 of this service bulletin.
1
Airplanes that have accomplished the original issue of this service
bulletin.
2
Airplanes that have accomplished Revision 1 of this service bulletin.3
Airplane Models:
MD-90-30
GroupFuselage Num-
ber
12094 - 2100
12115
12117
12120
12122 - 2123
12125 - 2126
12129
12131
12133
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GroupFuselage Num-
ber
12136
12138
12140 - 2144
12146 - 2147
12149 - 2150
12153 - 2154
12156 - 2159
12161 - 2166
12169 - 2171
12173
12175
12177
12179
12181
12184
12186
12190 - 2191
12193 - 2195
12197 - 2198
12200
12202 - 2203
12205
12207
12209 - 2213
12215 - 2217
12219 - 2233
12235 - 2237
12240
12243
12245
12248
22250 - 2251
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GroupFuselage Num-
ber
22253
22255 - 2263
22288 - 2290
24001 - 4002
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
On MD-80 airplanes three operators have reported three instances of electrically shorted wires in the
right wheel well and evidence of arcing on the auxiliary hydraulic pump power cables. One incident
resulted in a fire in the wheel well. Investigation revealed damage to the power cables was caused by
structural chafing. In addition, the Special Federal Aviation Regulation (SFAR) 88 analysis determined
that extra protection is required on the auxiliary hydraulic pump wire harness assembly where it comes
in close proximity to the center fuel tank. MD-90 airplanes have a similar installation and Boeing analysis
determined that the existing auxiliary hydraulic pump wire harness assembly is routed within the tire
burst area. A new and longer auxiliary hydraulic pump wire harness assembly installed and routed
outside the "tire burst" area will minimize the possibility of chaffing and electrical wire arcing damage.
If not corrected, electrical arcing and/or shorted wires could result in a wheel well fire and/or hazard to
the adjacent fuel tank.
This service bulletin is the result of the safety assessments conducted by Boeing under SFAR 88, "Fuel
Tank System Fault Tolerance Evaluation Requirements".
Revision 1 was sent to give instructions to install a wire harness assembly support bracket in the right
wheel well on all MD-90 airplanes if/when it is missing, install an additional wire harness assembly
support clamp, install a support and bracket for Group 1 airplanes that have not accomplished Service
Bulletin MD90-29-012, and to inspect wire harness assembly protective sleeving dimensions. The data
given in Information Notices MD90-29A021 IN 01 and MD90-29A021 IN 02 are included in this revision.
Revision 2 is sent to incorporate engineering released subsequent to Revision 1 of this service bulletin,
which changes the wire harness clamp and sleeving installation. The data given in Information Notices
MD90-29A021 IN 03 and MD90-29A021 IN 04 are included in this revision.
D. Description
This service bulletin provides instructions to install a new auxiliary hydraulic pump wire harness assembly
and route it outside of the "tire burst" area.
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Revision 2 - More work is necessary on airplanes changed in accordance with the original issue or
Revision 1 of this service bulletin. The additional work involves checking electrical resistance, adding
new clamps at two positions, adding sleeving to the wire harness if its missing, and adding red tape to
the connector end of the wire harness if its missing. An additional 3.0 hours is required to complete
the additional work described in this revision of this service bulletin.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
144MD-90-30
E. Compliance
Federal Aviation Administration (FAA) Airworthiness Directive AD 2009-07-04 is related to this service
bulletin.
Boeing recommends that operators accomplish this service bulletin within 18 months after the date of
Revision 2 on 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.
In addition, the Manager of the FAA Los Angeles Aircraft Certification Office approves the action (i.e.
inspection or modification) defined in this service bulletin as an alternative method of compliance to
the requirements of Paragraph (f) of AD 2009-07-04. All provisions of AD 2009-07-04 that are not
specifically referenced in the above statement remain fully applicable and must be complied with.
G. Manpower
The table below shows an estimate of the task hours necessary to do this modification for each airplane
without prior modifications. This estimate is for direct labor only, done by an experienced crew. Adjust
the estimate with the 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 examine the work
— Time to cure the materials
— Time to make the parts
— Time to find the tools.
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NOTE: Task hours and elapsed hours required for repair or replacement of damaged wires are
not included in this service bulletin.
Group 1, Configuration 1:
Elapsed HoursTask HoursNumber of PersonsTask
0.30.31Open Access
2.02.01Figure 1
1.01.01Figure 2
7.07.01Figures 8 and 4
1.01.01Figure 5
0.51.02Inspection/Check
0.20.21Connect/Lockwire
0.30.31Close Access
12.312.8TOTAL FOR EACH AIRPLANE
Group 1, Configuration 2; Group 2, Configuration 1:
Elapsed HoursTask HoursNumber of PersonsTask
0.30.31Open Access
2.02.01Figure 1
1.01.01Figure 2
6.56.51Figures 3 and 4
1.01.01Figure 5
0.51.02Inspection/Check
0.20.21Connect/Lockwire
0.30.31Close Access
11.812.3TOTAL FOR EACH AIRPLANE
Group 1, Configuration 3:
Elapsed HoursTask HoursNumber of PersonsTask
0.30.31Open Access
1.51.51Figure 6
0.50.51Figure 7
2.42.41Figure 9
0.50.51Figure 10
1.01.01Figure 11
0.30.31Close Access
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Group 1, Configuration 3:
Elapsed HoursTask HoursNumber of PersonsTask
6.56.5TOTAL FOR EACH AIRPLANE
NOTE: Task hours and elapsed hours required for replacement of wire harness assembly in
accordance with Figure 10 are not included in the table above.
Group 1, Configuration 4; Group 2, Configuration 2:
Elapsed HoursTask HoursNumber of PersonsTask
0.30.31Open Access
0.50.51Figure 7
2.42.41Figure 9
0.50.51Figure 10
1.01.01Figure 11
0.30.31Close Access
5.05.0TOTAL FOR EACH AIRPLANE
NOTE: Task hours and elapsed hours required for replacement of wire harness assembly in
accordance with Figure 10 are not included in the table above.
Group 1, Configuration 5; Group 2, Configuration 3:
Elapsed HoursTask HoursNumber of PersonsTask
0.30.31Open Access
2.42.41Figure 9
0.50.51Figure 10
1.01.01Figure 11
0.30.31Close Access
4.54.5TOTAL FOR EACH AIRPLANE
NOTE: Task hours and elapsed hours required for replacement of wire harness assembly in
accordance with Figure 10 are not included in the table above.
H. Weight and Balance Changes
Moment Change
(MEW) IN.-LBS
Mfr's Empty Weight
(MEW) LBS IN-
CREASE
Approximate Sta-
tion (Inches)
Airplane
+ 1495.5+ 1.5997.0MD-90-30
I. Electrical Load Data
Not changed.
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J. References
1. Existing Data:
a. FAA Airworthiness Directive AD 2009-07-04.
b. Boeing Service Bulletin MD90-29-012.
c. Federal Aviation Administration, Special Federal Aviation Regulation (SFAR) 88.
d. MD-90 Aircraft Maintenance Manual (AMM) 06-31-00, 29-21-01 and 32-00-00.
e. MD-90 Structural Repair Manual (SRM) 51, 53.
f. Standard Wiring Practices Manual (SWPM) 20-10-01, 20-31-00 and 20-50-01.
g. Boeing Multiple Operator Message (MOM) MOM-MOM-10-0034 dated January 18, 2010.
2. Data supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
ChangeTitleDrawing Number
K, L, MRe-route Auxiliary Hydraulic Pump Wire Har-
ness - Right Main Wheel Well
SR90290011
LHydraulic Installation - Forward Main Landing
Gear Wheel Well
5965225
BGSupport Installation - Fuselage Section Hy-
draulic Piping, Volume 3
7936937
These drawings were used to prepare this service bulletin. These drawings are not necessary to
make the specified changes, and are not supplied with this service bulletin. These drawings may
not be applicable to all airplane configurations or operators.
K. Publications Affected
1. Publications:
Chapter-SectionPublication
24-50, 27-67, 28-22, 29-12, 29-21,
29-31, 29-32, 29-34, 30-10, 30-11,
31-31, 32-44, 32-45, 32-48, 33-42
Illustrated Parts Catalog
29-21Wiring Diagram Manual Equipment List
2. Damage Tolerance Based Structural Inspections:
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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.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary For Each Airplane, as shown
below. Kits availability is shown in the Reorder Lead Time (ROLT). ROLT is calculated from the date
Boeing gets the purchase order.
Unit Price thru
June 30, 2011
ROLT
(Weeks)
NameKit Number
$4,870.0013SERVICE KITSA90290021-11
1,144.0013SERVICE KITSA90290021-13
105.0013SERVICE KITSA90290021-15
4,712.0013SERVICE KITSA90290021-17
SERVICE KIT REPLACEMENT INFORMATION (Refer to BOEING MULTIPLE OPERATOR MES-
SAGE (MOM) MOM-MOM-10-0034):
NotesReplacement
Kit Number
NameSuperseded Kit
Number
(a)SA90290021-
11
SERVICE KITSA90290021-3
SA90290021-
13
SERVICE KITSA90290021-5
SA90290021-
15
SERVICE KITSA90290021-7
(a)-SUPPLEMENTAL KITSA90290021-9
(b)SA90290021-
17
SERVICE KIT
(a) Supplemental kit SA90290021-9 is not replaced. This was a supplemental kit for
service kit SR90290011-7001, which was replaced by service kit SA90290021-11.
(b) Service kit SA90290021-17 is required only for the applicable group configuration if
the electrical resistance exceeds the maximum value allowed in accordance with
Figure 10.
The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.
After the Unit Price date, new price and ROLT data is applicable. Prices are in United States dollars.
Terms: Net 30 days.
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REFERENCE THIS SERVICE BULLETIN AND SUBMIT YOUR PURCHASE ORDER BY ONE OF
THE METHODS THAT FOLLOW:
1. Order on-line via ATA Spec 2000 or Boeing Part Page
2. Fax to (206) 662-7145
3. Spares Customer Support - MC 36-65
Boeing Spares Department
P.O. Box 3707
Seattle, Washington 98124-2207 USA
B. Industry Support Information
Boeing warranty remedies are available for only the condition of installation of the missing support
bracket and for installation of an additional wire harness support clamp for affected airplanes (described
in MD90-29A021 Revision 01) in warranty as of January 1, 2000. For man-hour and material
reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing Commercial
Airplanes Group - Warranties. Please refer to this service bulletin number and reference the airplane
identification number(s) in your claim.
Boeing Commercial Airplanes Group - Warranties
P.O. Box 3707 M/C 2L-46
Seattle, Washington 98124-2207 USA
(Service Bulletin MD90-29A021)
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.
QTYService Kit SA90290021
-17
(See
Note
b)
-15-13
(See
Note
a)
-11ConfigurationGroup
--1111
---121
111-31
11--41
11--51
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QTYService Kit SA90290021
-17
(See
Note
b)
-15-13
(See
Note
a)
-11ConfigurationGroup
---112
11--22
11--32
(a) Service kit SA90290021-13 is required only for the
applicable group configuration that have not previously
accomplished Service Bulletin MD90-29-012.
(b) Service kit SA90290021-17 is required only for the
applicable group configuration if the electrical resis-
tance exceeds the maximum value allowed in accor-
dance with Figure 10.
Group 1, Configuration 1-2; Group 2, Configuration 1:
Service Kit SA90290021-11
NotesNameQTYNew Part Number
NUT-CLIP153D0039-14
NUT-CLIP53D0039-16
BRACKET29D0062-3F08-08
BRACKET19D0062-3S10-12
NUT2AN315-3R
RIVET4MS20470AD3-5D
NUT6MS21042L3
CLAMP1MS21919WDG7
LOCKWASHER4MS35338-43
SCREW3NAS1096-3-10
SCREW1NAS1096-3-11
SCREW2NAS1096-3-12
SCREW1NAS1096-3-22
SCREW2NAS1096-3-42
SCREW15NAS1096-3-8
SCREW3NAS1096-3-9
WASHER2NAS1149D0316H
WASHER3NAS1149F0332P
WASHER36NAS1252-10L
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Group 1, Configuration 1-2; Group 2, Configuration 1:
Service Kit SA90290021-11
NotesNameQTYNew Part Number
WASHER10NAS1252-10H
SPACER2NAS43DD3-128FC
SPACER1NAS43DD3-48FC
SCREW1NAS623-3-3
CLAMP2S7913536-12
CLAMP3S7934111-10SA
CLAMP3S7934111-12SA
CLAMP3S7934111-14SA
CLAMP6S7934111-6SA
CLAMP7S7934111-8SA
WIRE HARNESS ASSEMBLY1SR90290011-7
(a)SLEEVING20 IN.SR90290011-3
BRACKET1TA4064G0612
(a) SR90290011-9 SLEEVING (DMS 2379 Type 4, Class 4) is an alternate for
SR90290011-3 SLEEVING (DMS 2109 Type 1).
Group 1, Configuration 1, 3:
Service Kit SA90290021-13
NotesNameQTYNew Part Number
PIN1HL328-5-4
RIVET2MS20470AD3-5D
RIVET2MS20470AD5-6D
RIVET1MS20470AD5-7D
RIVET2MS20470AD6-8D
NUT1MS21042L08
WASHER1NAS1252-8L
SUPPORT17936937-71
BRACKET19D0062-3-08-08
CLAMP1S7934111-12SA
NUT-CLIP13D0039-14
WASHER1NAS1252-10L
SCREW1NAS1096-3-8
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Group 1, Configuration 3-5; Group 2, Configuration 2-3:
Service Kit SA90290021-15
NotesNameQTYNew Part Number
NUT-CLIP43D0039-14
BRACKET19D0062-3F08-08
RIVET2MS20470AD3-5D
LOCKNUT1MS21042L3
SCREW4NAS1096-3-8
SCREW1NAS1096-3-9
WASHER6NAS1252-10L
WASHER1NAS1252-10H
CLAMP1MS21919WDG7
CLAMP1S7934111-6SA
CLAMP1S7934111-8SA
CLAMP1S7934111-10SA
CLAMP2S7934111-12SA
(a)SLEEVING20 IN.SR90290011-3
(a) SR90290011-9 SLEEVING (DMS 2379 Type 4, Class 4) is an alternate for
SR90290011-3 SLEEVING (DMS 2109 Type 1).
Group 1, Configuration 3-5; Group 2, Configuration 2-3:
Service Kit SA90290021-17
NotesNameQTYNew Part Number
NUT-CLIP23D0039-14
SCREW2NAS1096-3-8
WASHER2NAS1252-10L
CLAMP2S7934111-12SA
WIRE HARNESS ASSEMBLY1SR90290011-7
(a)SLEEVING20 IN.SR90290011-3
(a) SR90290011-9 SLEEVING (DMS 2379 Type 4, Class 4) is an alternate for
SR90290011-3 SLEEVING (DMS 2109 Type 1).
2. Parts and Materials Supplied by the Operator:
NOTE: The parts listed in the table below may be ordered as end item spares.
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NotesNameQTYPart Number /
Specification
(a)BRACKET19D0062-3F08-08
(b)TAPE, TYING, GLASS FIBERAs Re-
quired
18XTZ or 23XTZ
(DMS 2089)
or
Equivalent
(c)TAPE, ELECTRICAL INSULATION,
SELF-ADHERING HIGH TEMPERA-
TURE
As Re-
quired
T2/600T Series
(DMS 2186)
or
Equivalent
CAGE
81205
The Boeing Company
7755 East Marginal Way South
(a) Can be obtained from:
Seattle, Washington 98108
7F993Gudebrod, Incorporated(b) Can be obtained from:
262 King Street
Pottstown, Pennsylvania 19464
52869Arlon Silicone Technologies(c) Can be obtained from:
1100 Governor Lea Road
Bear, Delaware 19701
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 25

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.
CAUTION: POSITION CLAMPS PERPENDICULAR TO WIRE ASSEMBLY BUNDLE AND ASSURE
WIRE ASSEMBLY DOES NOT CONTACT ANY STRUCTURE OR HYDRAULIC PIPES.
NOTE: 1. The instructions identified in Paragraph 3.B., Work Instructions, and the Figure(s)
give the recommended sequence of steps. The sequence of steps to do this service
bulletin can be changed.
2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
3. Equivalent parts are listed in AEPL, Drawing 7595071.
4. Use the approved fastener and process material substitutions in accordance with
MD90 SRM 51.
5. If the length of any fastener specified in this service bulletin does not meet the
installation standards in MD90 SRM 51, then a fastener of the same specification,
or an approved substitute, with a length which meets the installation standards in
MD90 SRM 51 may be used.
6. 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.
7. 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
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— Angular tolerance is plus or minus 2 degrees
— Hole dimensions for standard solid rivets are given in MD-90 SRM, Chapter 51
— Torque limits to tighten nuts and bolts are given in MD-90 SRM, Chapter 51
8. The finish specification of all 2117 "AD" rivets used in this service bulletin shall be
per MIL-A-8625; anodize and dichromate seal per MIL-A-8625, Type 2, Class 1.
9. Refer to the Standard Wiring Practices Manual SWPM 20-10-01 for the wire
installation procedures and clearance requirements.
10. Obey all of the warnings and cautions given in the specified manual sections.
11. It is permissible to select smaller or larger sizes in that type of clamp to meet the
clamp installation requirements specified in SWPM 20-10-01.
12. Screw protrusion shall extend a minimum of 1-1/2 threads and shall not exceed 4
threads through the nut or nutplate. When the specified screw does not meet the
thread protrusion requirement, a screw with a different thread length (of the same
basic screw part number) shall be used to meet the protrusion requirement.
13. Corrosion resistant steel (CRES) lockwire may be used in place of inconel lockwire.
Refer to DPS 3.651 for lockwire selection.
14. Reference structure in Figures may not represent existing airplane configuration.
15. Adjust, locate, or position wire support clamps barrel up or down, forward or aft of
support bracket as required to clear structure and/or hydraulic line.
16. At operator's option, components around the area of modification may be removed
and reinstalled as required, for ease of installation of the new wire harness assembly.
17. A General Visual Inspection is defined as: A visual examination of an interior or
exterior area, installation or assembly to detect obvious damage, failure, or irregularity.
This level of inspection is made from within touching distance unless otherwise
specified. A mirror may be necessary to ensure visual access to all surfaces in the
inspection area. This level of inspection is made under normal available lighting
conditions such as daylight, hangar lighting, flashlight or drop-light and may require
removal or opening of access panels or doors. Stands, ladders or platforms may be
required to gain proximity to the area being checked.
18. 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.
B. WORK INSTRUCTIONS
Group 1, Configuration 1:
1. Open circuit breaker located on the lower Electrical Power Center (EPC), Miscellaneous - Right
DC Bus and install safety tag. Refer to MD-90 AMM 29-21-01.
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NameNumberColRow
Hydraulic Power Transfer Unit ControlB1-40327R
Open circuit breaker located on the upper EPC, Air Conditioning - Left A/C Bus and install safety
tag. Refer to MD-90 AMM 29-21-01.
NameNumberColRow
Right Auxiliary Hydraulic Pump ControlB1-66217H
Open circuit breaker located on the Cockpit Circuit Breaker Panel - Left Generator Bus and install
safety tag. Refer to MD-90 AMM 29-21-01.
NameNumberColRow
Right Auxiliary Hydraulic PumpB1-764--
2. Get access to area of modification by opening the right main landing gear wheel well inboard door
and install lockpin and doorkeeper. Refer to MD-90 AMM 32-00-00 as an accepted procedure.
3. Remove auxiliary hydraulic pump wire harness in accordance with Figure 1.
4. Install auxiliary hydraulic pump wire harness support brackets in accordance with Figure 2.
NOTE: Opening access door 160JR will ease access for bracket installation. Refer to MD-90
AMM 06-31-00.
5. Route/install auxiliary hydraulic pump wire harness in accordance with Figure 8. Terminate wire
harness in accordance with Figure 4.
6. Install clamps common to the existing wire harnesses in accordance with Figure 5.
7. Do an Inspection/Check of the auxiliary hydraulic pump. Refer to MD-90 AMM 29-21-01 as an
accepted procedure.
8. Remove safety tag and close circuit breaker located on the lower EPC, Miscellaneous - Right DC
Bus. Refer to MD-90 AMM 29-21-01.
NameNumberColRow
Hydraulic Power Transfer Unit ControlB1-40327R
Remove safety tag and close circuit breaker located on the upper EPC, Air Conditioning - Left A/C
Bus. Refer to MD-90 AMM 29-21-01.
NameNumberColRow
Right Auxiliary Hydraulic Pump ControlB1-66217H
Remove safety tag and close circuit breaker located on the Cockpit Circuit Breaker Panel - Left
Generator Bus. Refer to MD-90 AMM 29-21-01.
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Copyright © Unpublished Work - See page 1 for details.
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NameNumberColRow
Right Auxiliary Hydraulic PumpB1-764--
9. If opened, close access door 160JR. Refer to MD-90 AMM 06-31-00.
10. Remove lockpin and doorkeeper and close the right main landing gear wheel well inboard door.
Refer to MD-90 AMM 32-00-00 as an accepted procedure.
11. Put the airplane back to a serviceable condition.
Group 1, Configuration 2; Group 2, Configuration 1:
1. Open circuit breaker located on the lower Electrical Power Center (EPC), Miscellaneous - Right
DC Bus and install safety tag. Refer to MD-90 AMM 29-21-01.
NameNumberColRow
Hydraulic Power Transfer Unit ControlB1-40327R
Open circuit breaker located on the upper EPC, Air Conditioning - Left A/C Bus and install safety
tag. refer to MD-90 AMM 29-21-01.
NameNumberColRow
Right Auxiliary Hydraulic Pump ControlB1-66217H
Open circuit breaker located on the Cockpit Circuit Breaker Panel - Left Generator Bus and install
safety tag. Refer to MD-90 AMM 29-21-01.
NameNumberColRow
Right Auxiliary Hydraulic PumpB1-764--
2. Get access to area of modification by opening the right main landing gear wheel well inboard door
and install lockpin and doorkeeper. Refer to MD-90 AMM 32-00-00 as an accepted procedure.
3. Remove auxiliary hydraulic pump wire harness in accordance with Figure 1.
4. Install auxiliary hydraulic pump wire harness support brackets in accordance with Figure 2.
NOTE: Opening access door 160JR will ease access for bracket installation. Refer to MD-90
AMM 06-31-00.
5. Route/install auxiliary hydraulic pump wire harness in accordance with Figure 3. Terminate wire
harness in accordance with Figure 4.
6. Install clamps common to the existing wire harnesses in accordance with Figure 5.
7. Do an Inspection/Check of the auxiliary hydraulic pump. Refer to MD-90 AMM 29-21-01.
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8. Remove safety tag and close circuit breaker located on the lower EPC, Miscellaneous - Right DC
Bus. Refer to MD-90 AMM 29-21-01.
NameNumberColRow
Hydraulic Power Transfer Unit ControlB1-40327R
Remove safety tag and close circuit breaker located on the upper EPC, Air Conditioning - Left A/C
Bus. Refer to MD-90 AMM 29-21-01.
NameNumberColRow
Right Auxiliary Hydraulic Pump ControlB1-66217H
Remove safety tag and close circuit breaker located on the Cockpit Circuit Breaker Panel - Left
Generator Bus. Refer to MD-90 AMM 29-21-01.
NameNumberColRow
Right Auxiliary Hydraulic PumpB1-764--
9. If opened, close access door 160JR. Refer to MD-90 AMM 06-31-00.
10. Remove lockpin and doorkeeper and close the right main landing gear wheel well inboard door.
Refer to MD-90 AMM 32-00-00 as an accepted procedure.
11. Put the airplane back to a serviceable condition.
Group 1, Configuration 3:
1. Open circuit breaker located on the lower Electrical Power Center (EPC), Miscellaneous - Right
DC Bus and install safety tag. Refer to MD-90 AMM 29-21-01.
NameNumberColRow
Hydraulic Power Transfer Unit ControlB1-40327R
Open circuit breaker located on the upper EPC, Air Conditioning - Left A/C Bus and install safety
tag. Refer to MD-90 AMM 29-21-01.
NameNumberColRow
Right Auxiliary Hydraulic Pump ControlB1-66217H
Open circuit breaker located on the Cockpit Circuit Breaker Panel - Left Generator Bus and install
safety tag. Refer to MD-90 AMM 29-21-01.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
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NameNumberColRow
Right Auxiliary Hydraulic PumpB1-764--
2. Get access to area of modification by opening the right main landing gear wheel well inboard door
and install lockpin and doorkeeper. Refer to MD-90 AMM 32-00-00 as an accepted procedure.
NOTE: Opening access door 160JR will ease access bracket installation. Refer to MD-90 AMM
06-31-00.
3. Install new auxiliary hydraulic pump wire harness support bracket and clamp in accordance with
Figure 6.
4. Install auxiliary hydraulic pump wire harness support bracket and clamp in accordance with Figure
7.
5. Install wire harness support clamps and electrical insulation tape at connector backshell in
accordance with Figure 9.
6. Check electrical resistance value in accordance with Figure 10.
7. Do a general visual inspection of wire harness protective sleeving dimensions and change wire
harness sleeving as needed in accordance with Figure 11.
8. Remove safety tag and close circuit breaker located on the lower EPC, Miscellaneous - Right DC
Bus. Refer to MD-90 AMM 29-21-01.
NameNumberColRow
Hydraulic Power Transfer Unit ControlB1-40327R
Remove safety tag and close circuit breaker located on the upper EPC, Air Conditioning - Left A/C
Bus. Refer to MD-90 AMM 29-21-01.
NameNumberColRow
Right Auxiliary Hydraulic Pump ControlB1-66217H
Remove safety tag and close circuit breaker located on the Cockpit Circuit Breaker Panel - Left
Generator Bus. Refer to MD-90 AMM 29-21-01.
NameNumberColRow
Right Auxiliary Hydraulic PumpB1-764--
9. If opened, close access door 160JR. Refer to MD-90 AMM 06-31-00.
10. Remove lockpin and doorkeeper and close the right main landing gear wheel well inboard door.
Refer to MD-90 AMM 32-00-00 as an accepted procedure.
11. Put the airplane back to a serviceable condition.
Group 1, Configuration 4; Group 2, Configuration 2:
BOEING PROPRIETARY -
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### Page 31

1. Open circuit breaker located on the lower Electrical Power Center (EPC), Miscellaneous - Right
DC Bus and install safety tag. Refer to MD-90 AMM 29-21-01.
NameNumberColRow
Hydraulic Power Transfer Unit ControlB1-40327R
Open circuit breaker located on the upper EPC, Air Conditioning - Left A/C Bus and install safety
tag. Refer to MD-90 AMM 29-21-01.
NameNumberColRow
Right Auxiliary Hydraulic Pump ControlB1-66217H
Open circuit breaker located on the Cockpit Circuit Breaker Panel - Left Generator Bus and install
safety tag. Refer to MD-90 AMM 29-21-01.
NameNumberColRow
Right Auxiliary Hydraulic PumpB1-764--
2. Get access to area of modification by opening the right main landing gear wheel well inboard door
and install lockpin and doorkeeper. Refer to MD-90 AMM 32-00-00 as an accepted procedure.
NOTE: Opening access door 160JR will ease access for bracket installation. Refer to MD-90
AMM 06-31-00.
3. Install auxiliary hydraulic pump wire harness support bracket and clamp in accordance with Figure
7.
4. Install wire harness support clamps and electrical insulation tape at connector backshell in
accordance with Figure 9.
5. Check electrical resistance value in accordance with Figure 10.
6. Do a general visual inspection of wire harness protective sleeving dimensions and change wire
harness sleeving as needed in accordance with Figure 11.
7. Remove safety tag and close circuit breaker located on the lower EPC, Miscellaneous - Right DC
Bus. Refer to MD-90 AMM 29-21-01.
NameNumberColRow
Hydraulic Power Transfer Unit ControlB1-40327R
Remove safety tag and close circuit breaker located on the upper EPC, Air Conditioning - Left A/C
Bus. Refer to MD-90 AMM 29-21-01.
NameNumberColRow
Right Auxiliary Hydraulic Pump ControlB1-66217H
BOEING PROPRIETARY -
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### Page 32

Remove safety tag and close circuit breaker located on the Cockpit Circuit Breaker Panel - Left
Generator Bus. Refer to MD-90 AMM 29-21-01.
NameNumberColRow
Right Auxiliary Hydraulic PumpB1-764--
8. If opened, close access door 160JR. Refer to MD-90 AMM 06-31-00.
9. Remove lockpin and doorkeeper and close the right main landing gear wheel well inboard door.
Refer to MD-90 AMM 32-00-00 as an accepted procedure.
10. Put the airplane back to a serviceable condition.
Group 1, Configuration 5; Group 2, Configuration 3:
1. Open circuit breaker located on the lower Electrical Power Center (EPC), Miscellaneous - Right
DC Bus and install safety tag. Refer to MD-90 AMM 29-21-01.
NameNumberColRow
Hydraulic Power Transfer Unit ControlB1-40327R
Open circuit breaker located on the upper EPC, Air Conditioning - Left A/C Bus and install safety
tag. Refer to MD-90 AMM 29-21-01.
NameNumberColRow
Right Auxiliary Hydraulic Pump ControlB1-66217H
Open circuit breaker located on the Cockpit Circuit Breaker Panel - Left Generator Bus and install
safety tag. Refer to MD-90 AMM 29-21-01.
NameNumberColRow
Right Auxiliary Hydraulic PumpB1-764--
2. Get access to area of modification by opening the right main landing gear wheel well inboard door
and install lockpin and doorkeeper. Refer to MD-90 AMM 32-00-00 as an accepted procedure.
NOTE: Opening access door 160JR will ease access for bracket installation. Refer to MD-90
AMM 06-31-00.
3. Install wire harness support clamps and electrical insulation tape at connector backshell in
accordance with Figure 9.
4. Check electrical resistance value in accordance with Figure 10.
5. Do a general visual inspection of wire harness protective sleeving dimensions and change wire
harness sleeving as needed in accordance with Figure 11.
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### Page 33

6. Remove safety tag and close circuit breaker located on the lower EPC, Miscellaneous - Right DC
Bus. Refer to MD-90 AMM 29-21-01.
NameNumberColRow
Hydraulic Power Transfer Unit ControlB1-40327R
Remove safety tag and close circuit breaker located on the upper EPC, Air Conditioning - Left A/C
Bus. Refer to MD-90 AMM 29-21-01.
NameNumberColRow
Right Auxiliary Hydraulic Pump ControlB1-66217H
Remove safety tag and close circuit breaker located on the Cockpit Circuit Breaker Panel - Left
Generator Bus. Refer to MD-90 AMM 29-21-01.
NameNumberColRow
Right Auxiliary Hydraulic PumpB1-764--
7. If opened, close access door 160JR. Refer to MD-90 AMM 06-31-00.
8. Remove lockpin and doorkeeper and close the right main landing gear wheel well inboard door.
Refer to MD-90 AMM 32-00-00 as an accepted procedure.
9. Put the airplane back to a serviceable condition.
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ALERTALERT

### Page 34 (OCR)

BOEING SERVICE BULLETIN MD90-29A021
ALERT  ALERT
This Figure applies only to: Group 1, Configuration 1-2; Group 2, Configuration 1.
RIGHT SIDE WHEEL WELL
STA Y=997.000
1551117
FIGURE 1: AUXILIARY HYDRAULIC PUMP WIRE HARNESS - REMOVAL
(SHEET 1 OF 3)
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Revision 2 March 16, 2010  MD90-29A021
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### Page 35

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 each airplane.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
1P1-32PLUGDisconnect1
Wire terminations from terminal
strip (5 places).
5S3-13TERMINAL STRIPDisconnect2
From Ground 548.2AN315-3RNUTRemove3
2MS35338-43LOCKWASHERRemove
3NAS1149F0332PWASHERRemove
1NAS1096-3-10SCREWRemove
FIGURE 1: AUXILIARY HYDRAULIC PUMP WIRE HARNESS - REMOVAL
(SHEET 2 OF 3)
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BOEING SERVICE BULLETIN MD90-29A021
ALERTALERT

### Page 36

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
From Shield Ground Bracket1NAS1096-3-10SCREWRemove4
1MS35338-43LOCKWASHERRemove
1NAS1149F0332PWASHERRemove
Discard all clamp attaching
hardware.
5S7934111-10SACLAMPRemove5
4S7934111-12SACLAMPRemove
1S7934111-1SACLAMPRemove
Discard all clamp attaching
hardware.
2S7934111-12SACLAMPRemove/Keep6
1S7934111-3SACLAMP
Discard all clamp attaching
hardware.
3S7934111-14SACLAMPRemove7
1S7934111-6SACLAMPRemove
17907939619WIRE HARNESSRemove8
Discard all clamp attaching
hardware.
1S7934111-6SACLAMPRemove/Keep9
Discard all clamp attaching
hardware.
2TA520D08-18CLAMPRemove/Keep10
FIGURE 1: AUXILIARY HYDRAULIC PUMP WIRE HARNESS - REMOVAL
(SHEET 3 OF 3)
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BOEING SERVICE BULLETIN MD90-29A021
ALERTALERT

### Page 37 (OCR)

BOEING SERVICE BULLETIN MD90-29A021
ALERT  ALERT
This Figure applies only to: Group 1, Configuration 1-2; Group 2, Configuration 1.
RIGHT SIDE WHEEL WELL
STA Y=997.000
FIGURE 2: AUXILIARY HYDRAULIC PUMP WIRE HARNESS - SUPPORT BRACKETS - INSTALL
(SHEET 1 OF 4)
Original Issue: May 15, 2007
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Copyright © Unpublished Work - See page 1 for details.  18 10 LE

### Page 38 (OCR)

BOEING SERVICE BULLETIN MD90-29A021
ALERT  ALERT
FWD
BRACKET
OR  WITH
B-B  EXISTING  RIVNUT
LOOKING DOWN
- 3.75+0.13
FWD
A-A
LOOKING OUTBOARD
EXISTING BRACKET  0.50  BRACKET
WITHOUT
EXISTING
| 5.60 ‡ 0.10  RIVNUT
- D
D
INBD  - 0.50
C-C  FWD
LOOKING FORWARD  D-D
LOOKING OUTBOARD  1551131
FIGURE 2: AUXILIARY HYDRAULIC PUMP WIRE HARNESS - SUPPORT BRACKETS - INSTALL
(SHEET 2 OF 4)
Original Issue: May 15, 2007
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Copyright © Unpublished Work - See page 1 for details.  38 of 81

### Page 39 (OCR)

BOEING SERVICE BULLETIN MD90-29A021
ALERT  ALERT
X = -40.000
EXISTING
BRACKET
RING FRAME REF
PANEL REF
F O
Z = -50.000 -
- 1.00.25
E-E
O.
F-F
LOOKING DOWN
1577774
FIGURE 2: AUXILIARY HYDRAULIC PUMP WIRE HARNESS - SUPPORT BRACKETS - INSTALL
(SHEET 3 OF 4)
Original Issue: May 15, 2007
Revision 2 March 16, 2010  BOEING PROPRIETARY -  MD90-29A021
Copyright © Unpublished Work - See page 1 for details.  39 of 81

### Page 40

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 airplane.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
1-SCREWRemove1
1-WASHERRemove1
1-NUTRemove1
Locate to existing hole. Install
with head of screw on far side.
19D0062-3S10-12BRACKETInstall (New)1
1NAS623-3-3SCREWInstall (New)
2NAS1149D0316HWASHERInstall (New)
1MS21042L3NUTInstall (New)
Install long leg of bracket against
the support.
1TA4064G0612BRACKETInstall (New)2
Bracket with existing Rivnut. In-
stall screw in existing Rivnut. If
no Rivnut is installed, use alter-
nate attaching hardware below.
1NAS1096-3-12SCREWInstall (New)
1MS35338-43LOCKWASHERInstall (New)
1NAS1252-10LWASHERInstall (New)
OR
Bracket without existing Rivnut.
Drill a 0.218 - 0.229 diameter
hole in the support at noted loca-
tion and attach bracket.
1MS21042L3NUTInstall (New)
2NAS1252-10LWASHERInstall (New)
1NAS1096-3-8SCREWInstall (New)
Measure along surface to locate
where center of bracket is to be
installed. Drill 0.098 diameter
holes thru frame (2 places). Re-
fer to MD-90 SRM 51 as an ac-
cepted procedure.
19D0062-3F08-08BRACKETInstall (New)3
2MS20470AD3-5DRIVETInstall (New)
(a) Drill 0.098 diameter holes thru
frame (2 places). Refer to MD-90
SRM 51 as an accepted proce-
dure.
19D0062-3F08-08BRACKETInstall (New)4
2MS20470AD3-5DRIVETInstall (New)
(a) This bracket was installed on some production airplanes. Install this bracket at this location if it is missing.
FIGURE 2: AUXILIARY HYDRAULIC PUMP WIRE HARNESS - SUPPORT BRACKETS - INSTALL
(SHEET 4 OF 4)
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BOEING SERVICE BULLETIN MD90-29A021
ALERTALERT

### Page 41 (OCR)

BOEING SERVICE BULLETIN MD90-29A021
ALERT  ALERT
This Figure applies only to: Group 1, Configuration 2; Group 2, Configuration 1.
EXISTING CONTROL
CABLE CONDUIT
1.00 + 0.25
1.00 + 0.25
B  3.00 + 0.25
1.00 ‡ 0.25
OPTION 1
RIGHT SIDE WHEEL WELL
STA Y=997.000  OPTION 2: SLIT SLEEVING
INSTALLATION
FIGURE 3: AUXILIARY HYDRAULIC PUMP WIRE HARNESS - INSTALL
(SHEET 1 OF 6)
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### Page 42 (OCR)

BOEING SERVICE BULLETIN MD90-29A021
ALERT  ALERT
NUT
LOCKWASHER
WASHER
LUG
LUG
NUT
WASHER
STRUCTURE -
WASHER
LOCKWASHER
SCREW
‚SLEEVE
6.00 +/- 1.00
.50
WIRE ASSY  /STRING TIE (4 PLACES)
.375
TO P1-32  TO S3-13 TERM. STRIP
CONNECTOR
TO GROUND.
CUT HOLE
OPTION 1: UNSLIT SLEEVING  1551135
INSTALLATION
FIGURE 3: AUXILIARY HYDRAULIC PUMP WIRE HARNESS - INSTALL
(SHEET 2 OF 6)
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### Page 43

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 each airplane.
CAUTION: POSITION CLAMPS PERPENDICULAR TO WIRE ASSEMBLY BUNDLE AND ASSURE WIRE
ASSEMBLY DOES NOT CONTACT ANY STRUCTURE OR HYDRAULIC PIPES.
BEFORE ROUTING WIRES, VERIFY THAT THE MANUAL HYDRAULIC HANDLE IS IN THE
AFT POSITION.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
OPTION 1: (a) (b)20 IN.SR90290011-3SLEEVINGInstall (New)1
OPTION 2: (c)
Do not tighten clamps until
wire harness assembly can
be connected at both ends.
Refer to SWPM 20-10-01 as
an accepted procedure.
1SR90290011-7WIRE HARNESS
ASSEMBLY
Install (New)
Plug connector must be safety
wired to airplane structure.
Refer to SWPM 20-31-00 as
an accepted procedure.
1P1-32PLUGConnect
(d)3S7934111-12SACLAMPInstall (New)2
33D0039-14NUT-CLIPInstall (New)
3NAS1252-10LWASHERInstall (New)
3NAS1096-3-8SCREWInstall (New)
(d)1S7934111-10SACLAMPInstall (New)3
13D0039-14NUT-CLIPInstall (New)
1NAS1252-10LWASHERInstall (New)
1NAS1096-3-8SCREWInstall (New)
To hydraulic line.1S7913536-12CLAMPInstall (New)4
To new wire harness assem-
bly.
1S7934111-8SACLAMPInstall (New)
(d)1NAS1096-3-9SCREWInstall (New)
2NAS1252-10LWASHERInstall (New)
1MS21042L3NUTInstall (New)
FIGURE 3: AUXILIARY HYDRAULIC PUMP WIRE HARNESS - INSTALL
(SHEET 3 OF 6)
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BOEING SERVICE BULLETIN MD90-29A021
ALERTALERT

### Page 44

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
To new wire harness assem-
bly.
1S7934111-8SACLAMPInstall (New)5
To hydraulic line.1S7913536-12CLAMPInstall (New)
(d)1NAS1096-3-9SCREWInstall (New)
2NAS1252-10LWASHERInstall (New)
1MS21042L3NUTInstall (New)
Install washers at each end of
spacer and under screw head.
1S7934111-8SACLAMPInstall (New)6
13D0039-14NUT-CLIPInstall (New)
1NAS43DD3-128FCSPACERInstall (New)
3NAS1252-10LWASHERInstall (New)
1NAS1096-3-42SCREWInstall (New)
To new wire harness assem-
bly and existing wire assem-
bly.
1S7934111-10SACLAMPInstall (New)7
To existing wire assembly.1S7934111-3SACLAMPInstall (Kept)
13D0039-14NUT-CLIPInstall (New)
2NAS1252-10LWASHERInstall (New)
1NAS1096-3-10SCREWInstall (New)
To new wire harness assem-
bly.
1S7934111-8SACLAMPInstall (New)8
To existing wire assembly.1TA520D08-18CLAMPInstall (Kept)
Install washers at each end of
spacer and under screw head.
13D0039-14NUT-CLIPInstall (New)
1NAS43DD3-128FCSPACERInstall (New)
3NAS1252-10LWASHERInstall (New)
1NAS1096-3-42SCREWInstall (New)
To existing wire assembly.1S7934111-8SACLAMPInstall (New)9
To existing wire assembly.1TA520D08-18CLAMPInstall (Kept)
Install washers at each end of
spacer and under screw head.
1NAS43DD3-48FCSPACERInstall (New)
1NAS1096-3-22SCREWInstall (New)
3NAS1252-10LWASHERInstall (New)
13D0039-16NUT-CLIPInstall (New)
FIGURE 3: AUXILIARY HYDRAULIC PUMP WIRE HARNESS - INSTALL
(SHEET 4 OF 6)
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BOEING SERVICE BULLETIN MD90-29A021
ALERTALERT

### Page 45

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
1S7934111-8SACLAMPInstall (New)10
13D0039-14NUT-CLIPInstall (New)
1NAS1252-10LWASHERInstall (New)
1NAS1096-3-8SCREWInstall (New)
3S7934111-14SACLAMPInstall (New)11
33D0039-16NUT-CLIPInstall (New)
6NAS1252-10HWASHERInstall (New)
3NAS1096-3-8SCREWInstall (New)
1S7934111-6SACLAMPInstall (New)12
13D0039-16NUT-CLIPInstall (New)
2NAS1252-10HWASHERInstall (New)
1NAS1096-3-8SCREWInstall (New)
1MS21919WDG7CLAMPInstall (New)13
1S7934111-8SACLAMPInstall (New)
1MS21042L3LOCK-NUTInstall (New)
2NAS1252-10LWASHERInstall (New)
1NAS1096-3-9SCREWInstall (New)
Measure and trim sleeving to
dimensions shown. Secure
sleeving with tie tape in accor-
dance with SWPM 20-10-01.
1SR90290011-3SLEEVINGAlign/Trim/ Se-
cure
14
-DMS 2089TAPE, TIE
Use existing hole in bracket.
Verify Electrical Bond. Refer
to SWPM 20-50-01 as an ac-
cepted procedure.
1NAS1096-3-11SCREWInstall (New)15
1NAS1252-10LWASHERInstall (New)
1MS35338-43LOCKWASHERInstall (New)
For Ground 548. Verify Electri-
cal Bond. Refer to SWPM 20-
50-01 as an accepted proce-
dure.
1NAS1096-3-12SCREWInstall (New)16
2MS35338-43LOCKWASHERInstall (New)
3NAS1149F0332PWASHERInstall (New)
2AN315-3RNUTInstall (New)
Make sure wire clamps are
tightened following wire instal-
lation.
CLAMPSTighten17 (Not
Shown)
(a) Option 1: Measure 6.00 inches +/- 1.00 inch from the edge of the SR90290011-3 sleeving. Fold sleeving
and measure .50 inch horizontally and .375 inch vertically and cut sleeving in accordance with View C.
FIGURE 3: AUXILIARY HYDRAULIC PUMP WIRE HARNESS - INSTALL
(SHEET 5 OF 6)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 15, 2007
MD90-29A021Revision 2 March 16, 2010
45 of 81
BOEING SERVICE BULLETIN MD90-29A021
ALERTALERT

### Page 46

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(b) Option 1: Slide the reworked sleeving over wire assembly SR90290011-7 starting from the terminal strip
end and moving toward the connector end. Insert ground wires through cut hole. Do not trim sleeving until
clamps are installed.
(c) Option 2: Slit new sleeving. Align, measure, and trim to meet the dimensions shown. Overlap the slit
sleeving and secure with tie tape in accordance with SWPM 20-10-01. Run ground wires outside of the
sleeving.
(d) Adjust wire support clamps as required to clear structure and hydraulic lines.
FIGURE 3: AUXILIARY HYDRAULIC PUMP WIRE HARNESS - INSTALL
(SHEET 6 OF 6)
BOEING PROPRIETARY -
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BOEING SERVICE BULLETIN MD90-29A021
ALERTALERT

### Page 47

This Figure applies only to: Group 1, Configuration 1-2; Group 2, Configuration 1.
FIGURE 4: ELECTRICAL WIRING DIAGRAM - TERMINATE WIRE HARNESS
(SHEET 1 OF 1)
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47 of 81
BOEING SERVICE BULLETIN MD90-29A021
ALERTALERT

### Page 48 (OCR)

BOEING SERVICE BULLETIN MD90-29A021
ALERT  ALERT
This Figure applies only to: Group 1, Configuration 1-2; Group 2, Configuration 1.
RIGHT SIDE WHEEL WELL  STA Y=997.000  1551146
FIGURE 5: CLAMPS COMMON TO EXISTING WIRE HARNESSES - INSTALL
(SHEET 1 OF 3)
Original Issue: May 15, 2007
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### Page 49 (OCR)

BOEING SERVICE BULLETIN MD90-29A021
ALERT  ALERT
•NUT-CLIP
WASHER
‚CLAMP
/ WASHER
/SCREW
1907894
FIGURE 5: CLAMPS COMMON TO EXISTING WIRE HARNESSES - INSTALL
(SHEET 2 OF 3)
Original Issue: May 15, 2007
Revision 2 March 16, 2010  BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  18 10 6₺

### Page 50

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 each airplane.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
1S7934111-6SACLAMPInstall (New)1
13D0039-14NUT-CLIPInstall (New)
1NAS1252-10LWASHERInstall (New)
1NAS1096-3-8SCREWInstall (New)
Adjust/locate/po-
sition clamp as
required to clear
structure.
2S7934111-6SACLAMPInstall (New)2
23D0039-14NUT-CLIPInstall (New)
2NAS1252-10LWASHERInstall (New)
2NAS1252-10HWASHERInstall (New)
2NAS1096-3-8SCREWInstall (New)
1S7934111-6SACLAMPInstall (New)3
1S7934111-12SACLAMPInstall (Kept)
1NAS1096-3-10SCREWInstall (New)
3NAS1252-10LWASHERInstall (New)
1MS21042L3NUTInstall (New)
1S7934111-6SACLAMPInstall (New)4
13D0039-14NUT-CLIPInstall (New)
1NAS1252-10LWASHERInstall (New)
1NAS1096-3-8SCREWInstall (New)
1S7934111-12SACLAMPInstall (Kept)5
13D0039-14NUT-CLIPInstall (New)
1NAS1252-10LWASHERInstall (New)
1NAS1096-3-8SCREWInstall (New)
1S7934111-6SACLAMPInstall (Kept)6
1S7934111-10SACLAMPInstall (New)
13D0039-14NUT-CLIPInstall (New)
2NAS1252-10LWASHERInstall (New)
1NAS1096-3-10SCREWInstall (New)
FIGURE 5: CLAMPS COMMON TO EXISTING WIRE HARNESSES - INSTALL
(SHEET 3 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 15, 2007
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50 of 81
BOEING SERVICE BULLETIN MD90-29A021
ALERTALERT

### Page 51 (OCR)

BOEING SERVICE BULLETIN MD90-29A021
ALERT  ALERT
This Figure applies only to: Group 1, Configuration 3.
A C
STA
Y=997.437
LOOKING DOWN
CENTER LINE
AIRPLANE
MANIFOLD
ASSY (REF)
STA
X=24.524
LEFT SIDE MLG  RIGHT SIDE MLG
WHEEL WELL  WHEEL WELL
DOORJAMB  DOORJAMB
A-A
LOOKING FORWARD STATION Y=997.437
FIGURE 6: AUXILIARY HYDRAULIC PUMP WIRE HARNESS - SUPPORT BRACKET AND CLAMP -
INSTALLATION
(SHEET 1 OF 6)
Original Issue: May 15, 2007
Revision 2 March 16, 2010  MD90-29A021
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### Page 52 (OCR)

BOEING SERVICE BULLETIN MD90-29A021
ALERT  ALERT
STA
X=24.524
CHANNEL
c-
MANIFOLD
ASSY (REF)
BEFORE MODIFICATION
LOOKING FORWARD
RIGHT SIDE
C-C  1577740
FIGURE 6: AUXILIARY HYDRAULIC PUMP WIRE HARNESS - SUPPORT BRACKET AND CLAMP -
INSTALLATION
(SHEET 2 OF 6)
Original Issue: May 15, 2007
Revision 2 March 16, 2010  MD90-29A021
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### Page 53 (OCR)

BOEING SERVICE BULLETIN MD90-29A021
ALERT  ALERT
CENTERLINE
AIRCRAFT
G
D-D
STA
Y=997.437  RIGHT SIDE ONLY
MANIFOLD AND HYDRAULIC LINES
OMITTED FOR CLARITY
0.50
INBD
0.69-
RIVET
EXISTING HOLE  (2 PLACES)
ATTACHMENT FROM
REMOVED MANIFOLD
SUPPORT BRACKET  E-E
VIEW LOOKING DOWN  1577742
FIGURE 6: AUXILIARY HYDRAULIC PUMP WIRE HARNESS - SUPPORT BRACKET AND CLAMP -
INSTALLATION
(SHEET 3 OF 6)
Original Issue: May 15, 2007
Revision 2 March 16, 2010  MD90-29A021
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### Page 54 (OCR)

BOEING SERVICE BULLETIN MD90-29A021
ALERT  ALERT
STA
X=24.524
- ANGLE (REF)
1.44  MANIFOLD
ASSY (REF)
1.25
AFTER MODIFICATION
LOOKING FORWARD
RIGHT SIDE
G-G
LOOKING OUTBOARD
F-F
1577743
FIGURE 6: AUXILIARY HYDRAULIC PUMP WIRE HARNESS - SUPPORT BRACKET AND CLAMP -
INSTALLATION
(SHEET 4 OF 6)
Original Issue: May 15, 2007
Revision 2 March 16, 2010  MD90-29A021
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  54 of 81

### Page 55

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 each airplane.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
1S7934111-1SACLAMPRemove1
2MS21042L8NUTRemove/Keep2
2MAS1251-10LWASHER
2NAS1303-6BOLT
1MS21042L3NUTRemove/Keep3
1NAS1252-10LWASHER
13D0005-3-8SCREW
1S7913536-4CLAMP
Plug open holes in frame
with AD rivet material.
Refer to MD-90 SRM 53
as an accepted proce-
dure.
4MS20470AD4RIVETRemove4
17936937-57SUPPORT
1-PIN
19D0062-3F08-08BRACKETInstall (New)5
2MS20470AD3-5DRIVET
Use pilot holes in support
as guides.
17936937-71SUPPORTAlign6
As Re-
quired
-HOLESDrill
17936937-71SUPPORTInstall (New)7
2NAS1303-6BOLTInstall (Kept)8
2NAS1252-10LWASHER
2MS21042L8NUT
1S7913536-4CLAMPInstall (Kept)9
13D0005-3-8SCREW
1NAS1252-10LWASHER
1MS21042L3NUT
FIGURE 6: AUXILIARY HYDRAULIC PUMP WIRE HARNESS - SUPPORT BRACKET AND CLAMP -
INSTALLATION
(SHEET 5 OF 6)
BOEING PROPRIETARY -
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Original Issue: May 15, 2007
MD90-29A021Revision 2 March 16, 2010
55 of 81
BOEING SERVICE BULLETIN MD90-29A021
ALERTALERT

### Page 56

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Adjust/locate/position
clamp as required to
clear structure and hy-
draulic lines.
1S7934111-12SACLAMPInstall (New)10
13D0039-14NUT-CLIP
1NAS1252-10LWASHER
1NAS1096-3-8SCREW
The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure.
A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the
number of fasteners necessary for this figure.
MORE DATAHOLE DIAQTYIDENTIFICATIONNAMECODE
Use pilot holes in support
as guides.
No. 102MS20470AD6-8DRivetA
Pick up existing hole in
channel.
No. 201MS20470AD5-7DRivetB
Layout and drill through
support and channel.
No. 201MS20470AD5-6DRivetC
Pick up existing hole in
channel.
No. 201MS20470AD5-6DRivetD
Pick up existing hole in
channel.
0.1605/0.16251HL328-5-4PinE
1NAS1252-8LWasher
1MS21042L08Nut
FIGURE 6: AUXILIARY HYDRAULIC PUMP WIRE HARNESS - SUPPORT BRACKET AND CLAMP -
INSTALLATION
(SHEET 6 OF 6)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 15, 2007
MD90-29A021Revision 2 March 16, 2010
56 of 81
BOEING SERVICE BULLETIN MD90-29A021
ALERTALERT

### Page 57 (OCR)

BOEING SERVICE BULLETIN MD90-29A021
ALERT  ALERT
This Figure applies only to: Group 1, Configuration 3-4; Group 2, Configuration 2.
RIGHT SIDE WHEEL WELL
STA Y=997.000
1557764
FIGURE 7: AUXILIARY HYDRAULIC PUMP WIRE HARNESS - SUPPORT BRACKET AND CLAMP -
INSTALLATION
(SHEET 1 OF 4)
Original Issue: May 15, 2007
Revision 2 March 16, 2010  MD90-29A021
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  57 of 81

### Page 58 (OCR)

BOEING SERVICE BULLETIN MD90-29A021
ALERT  ALERT
X = -40.000
EXISTING
BRACKET
RING FRAME REF
PANEL REF
Z = -50.000 -
- 1.00.25
A-A
0.50
B-B
LOOKING DOWN
1557765
FIGURE 7: AUXILIARY HYDRAULIC PUMP WIRE HARNESS - SUPPORT BRACKET AND CLAMP -
INSTALLATION
(SHEET 2 OF 4)
Original Issue: May 15, 2007
Revision 2 March 16, 2010  MD90-29A021
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  58 of 81

### Page 59 (OCR)

BOEING SERVICE BULLETIN MD90-29A021
ALERT  ALERT
RIGHT SIDE WHEEL WELL
STA Y=997.000  1557767
FIGURE 7: AUXILIARY HYDRAULIC PUMP WIRE HARNESS - SUPPORT BRACKET AND CLAMP -
INSTALLATION
(SHEET 3 OF 4)
Original Issue: May 15, 2007
Revision 2 March 16, 2010  BOEING PROPRIETARY -  MD90-29A021
Copyright © Unpublished Work - See page 1 for details.  59 of 81

### Page 60

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 each airplane.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a) Drill 0.098 diameter holes
thru frame (2 places). Refer to
MD-90 SRM 51 as an accepted
procedure.
19D0062-3F08-08BRACKETInstall (New)1
2MS20470AD3-5DRIVET
(b)1S7934111-10SACLAMPInstall (New)2
13D0039-14NUT-CLIP
1NAS1252-10LWASHER
1NAS1096-3-8SCREW
(a) This bracket was installed on some production airplanes. Install this bracket at this location if it is missing.
(b) Adjust wire support clamp as required to clear structure and hydraulic lines.
FIGURE 7: AUXILIARY HYDRAULIC PUMP WIRE HARNESS - SUPPORT BRACKET AND CLAMP -
INSTALLATION
(SHEET 4 OF 4)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 15, 2007
MD90-29A021Revision 2 March 16, 2010
60 of 81
BOEING SERVICE BULLETIN MD90-29A021
ALERTALERT

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