# Boeing Alert Service Bulletin MD80-55A068: No revision named

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- Title as filed: U.S. DOT/FAA - Service Bulletin - SB-MD80-55A068-00
- Pages: 38
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### Page 1

Commercial 
Airplanes
MD80
Service Bulletin
ALERT
Number: MD80-55A068
Original Issue: July 16, 2010
ATA System: 5510
SUBJECT: STABILIZERS - Horizontal Stabilizer - Inspect/Replace Upper Center Skin Panels
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 © 2010 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Unpublished Work - All Rights Reserved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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2.0

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Table of Contents
Summary ...................................................... 5
1. PLANNING INFORMATION ........................................ 7
A. Effectivity ................................................ 7
1. Airplanes ............................................. 7
2. Spares Affected ........................................ 1 0
B. Concurrent Requirements ...................................... 1 0
C. Reason ................................................ 1 1
D. Description .............................................. 1 1
E. Compliance .............................................. 1 1
F. Approval ............................................... 1 5
G. Manpower .............................................. 1 6
H. Weight and Balance Changes .................................... 1 7
I. Electrical Load Data ......................................... 1 8
J. References .............................................. 1 9
1. Existing Data: ......................................... 1 9
2. Data supplied with this Service Bulletin: ........................... 1 9
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 9
K. Publications Affected ........................................ 1 9
L. Interchangeability and Intermixability of Parts ........................... 2 0
2. MATERIAL INFORMATION ........................................ 2 1
A. Material - Price and Availability ................................... 2 1
B. Industry Support Information .................................... 2 2
C. Parts Necessary For Each Airplane ................................. 2 2
1. Kits/Parts: ........................................... 2 2
2. Parts and Materials Supplied by the Operator: ........................ 2 6
3. Parts Modified and Reidentified: ............................... 2 6
4. Parts Removed and Not Replaced: .............................. 2 6
D. Parts Necessary to Change Spares ................................. 2 6
E. Special Tooling - Price and Availability ............................... 2 7
F. Special Tooling Necessary to do this Service Bulletin ....................... 2 7
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 9
A. GENERAL INFORMATION ..................................... 2 9
B. WORK INSTRUCTIONS ....................................... 3 0
FIGURE 1: HORIZONTAL STABILIZER LEFT AND RIGHT UPPER CENTER SKIN PANELS - EDDY
CURRENT INSPECTION ................................... 3 3
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Commercial 
Airplanes
MD80
Service Bulletin
ALERT
SummaryNumber: MD80-55A068Original Issue: July 16, 2010
ATA System: 5510
SUBJECT: STABILIZERS - Horizontal Stabilizer - Inspect/Replace Upper Center Skin Panels
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
During inspection of the horizontal stabilizer upper aft skin panel in accordance with Service Bulletin
MD80-55A065, one operator reported finding a crack in the right horizontal stabilizer upper center skin panel at
the aft inboard corner. The airplane had accumulated 47,146 flight-hours and 26,490 flight cycles when the
crack was found. The cause of the horizontal stabilizer upper center skin panel cracking is suspected to be
fatigue. If undetected, a crack in the upper center skin panel may transfer load to the upper aft skin panel. This
may result in the upper aft skin panel cracking faster than the existing inspection intervals, defined in Service
Bulletin MD80-55A065, will detect. Inspection of the affected areas will determine the condition of the horizontal
stabilizer upper center skin panels. If not corrected, undetected cracks may ultimately lead to the loss of overall
structural integrity of the horizontal stabilizer.
ACTION
Refer to Paragraph 1.D., Description.
EFFECTIVITY
DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), MD-88 Airplanes. Refer to Paragraph
1.A.1., Airplanes, for the list of affected airplanes.
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.
Refer to Paragraph 1.E., Compliance.
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INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the inspection and/or repair procedures given in this service
bulletin.
MANPOWER
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
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Commercial 
Airplanes
MD80
Service Bulletin
ALERT
Number: MD80-55A068
Original Issue: July 16, 2010
ATA System: 5510
SUBJECT: STABILIZERS - Horizontal Stabilizer - Inspect/Replace Upper Center Skin Panels
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.
DESCRIPTIONCONFIGURATIONGROUP
MD-80 Series Airplanes (Fuselage Numbers 909 Thru 1614)-1
MD-80 Series Airplanes (Fuselage Numbers 1615 Thru 2287)-2
Airplane Models:
DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), MD-88
GroupFuselage Num-
ber
1909
1917
1924
1938
1941
1944
1946
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GroupFuselage Num-
ber
1948
1950
1952 - 953
1955
1957 - 958
1960
1962 - 963
1965 - 967
1969 - 971
1973 - 975
1977 - 979
1981
1983
1985 - 986
1988 - 989
1991 - 992
1994 - 1013
11015 - 1016
11018 - 1020
11022 - 1023
11025 - 1026
11028 - 1029
11031 - 1032
11034 - 1035
11037 - 1038
11040 - 1041
11043
11045
11047
11049
11051
11053
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GroupFuselage Num-
ber
11055
11057
11059 - 1080
11082 - 1083
11085 - 1614
21615 - 2007
22009 - 2016
22019 - 2034
22036 - 2069
22071 - 2093
22101 - 2114
22116
22118 - 2119
22121
22124
22127 - 2128
22130
22132
22134 - 2135
22137
22139
22145
22148
22151 - 2152
22155
22167
22174
22176
22178
22180
22183
22185
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GroupFuselage Num-
ber
22187
22189
22192
22196
22199
22201
22204
22206
22208
22214
22218
22234
22239
22241
22244
22247
22249
22252
22254
22264 - 2287
2. Spares Affected
None.
B. Concurrent Requirements
None.
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C. Reason
During inspection of the horizontal stabilizer upper aft skin panel in accordance with Service Bulletin
MD80-55A065, one operator reported finding a crack in the right horizontal stabilizer upper center skin
panel at the aft inboard corner. The airplane had accumulated 47,146 flight-hours and 26,490 flight
cycles when the crack was found. The cause of the horizontal stabilizer upper center skin panel cracking
is suspected to be fatigue. If undetected, a crack in the upper center skin panel may transfer load to
the upper aft skin panel. This may result in the upper aft skin panel cracking faster than the existing
inspection intervals, defined in Service Bulletin MD80-55A065, will detect. Inspection of the affected
areas will determine the condition of the horizontal stabilizer upper center skin panels. If not corrected,
undetected cracks may ultimately lead to the loss of overall structural integrity of the horizontal stabilizer.
D. Description
This service bulletin provides instructions to do an eddy current inspection of the horizontal stabilizer
left and right upper center skin panels for cracks, and based on inspection results for each panel, does
as follows:
Condition 1 (No Crack Found)
1. Does repetitive eddy current inspections of the horizontal stabilizer upper center skin panel.
Condition 2 (Crack Found)
1. OPTION 1:
a. Replaces the cracked horizontal stabilizer upper center skin panel.
b. Does repetitive eddy current inspection of the replacement horizontal stabilizer upper center
skin panel.
2. OPTION 2:
a. Contacts Boeing for possible temporary repair of crack and does the repair in accordance
with Boeing's instructions.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
33, 34DC-9-81 (MD-81), DC-9-82
(MD-82), DC-9-83 (MD-83), DC-
9-87 (MD-87), MD-88
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.
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Table 1: Inspect Horizontal Stabilizer Left and Right Upper Center Skin Panels for Cracks
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 4,379
flight cycles af-
ter the original
issue date on
this service bul-
letin.
Before the accu-
mulation of
20,000 total
flight cycles.
Do initial eddy current in-
spection of the horizontal
stabilizer left and right
upper center skin panels
in accordance with Para-
graph 3.B., Work Instruc-
tions, using one of the
options as follows:
All Airplanes
OPTION 1:
Scan 1 - Eddy Current,
High Frequency (ETHF)
Scan 2 - Eddy Current,
High Frequency (ETHF)
Scan 3 - Eddy Current,
Low Frequency (ETLF)
OR
OPTION 2:
Scan 1 - Eddy Current,
High Frequency (ETHF)
Scan 2 - Eddy Current,
High Frequency (ETHF)
Scan 3 - Eddy Current,
High Frequency (ETHF)
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Table 1: Inspect Horizontal Stabilizer Left and Right Upper Center Skin Panels for Cracks
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
---Do repetitive eddy current
inspection of the horizon-
tal stabilizer left and right
upper center skin panels
in accordance with Para-
graph 3.B., Work Instruc-
tions, using one of the
options as follows:
Condition 1
(No Crack Found)
5,200 flight cycles-Within 5,200
flight cycles af-
ter doing the ini-
tial eddy current
inspection.
OPTION 1:
Scan 1 - Eddy Current,
High Frequency (ETHF)
Scan 2 - Eddy Current,
High Frequency (ETHF)
(a)
(a)Scan 3 - Eddy Current,
Low Frequency (ETLF)
OR
2,500 flight cycles-Within 2,500
flight cycles af-
ter doing the ini-
tial eddy current
inspection.
OPTION 2:
Scan 1 - Eddy Current,
High Frequency (ETHF)
Scan 2 - Eddy Current,
High Frequency (ETHF)
(a)
(a)Scan 3 - Eddy Current,
High Frequency (ETHF)
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Table 1: Inspect Horizontal Stabilizer Left and Right Upper Center Skin Panels for Cracks
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
---OPTION 1: Do items (1),
(2), and (3) as follows:
Condition 2
(Crack Found)
--Before further
flight
(1) Replace the cracked
horizontal stabilizer upper
center skin panel in accor-
dance with Paragraph
3.B., Work Instructions
AND
--Within 20,000
flight cycles af-
ter installation of
the replacement
horizontal stabi-
lizer upper cen-
ter skin panel.
(2) Do initial eddy current
inspection of the replace-
ment horizontal stabilizer
upper center skin panel
in accordance with Para-
graph 3.B., Work Instruc-
tions, using one of the
options as follows:
OPTION 1:
Scan 1 - Eddy Current,
High Frequency (ETHF)
Scan 2 - Eddy Current,
High Frequency (ETHF)
Scan 3 - Eddy Current,
Low Frequency (ETLF)
OR
OPTION 2:
Scan 1 - Eddy Current,
High Frequency (ETHF)
Scan 2 - Eddy Current,
High Frequency (ETHF)
Scan 3 - Eddy Current,
High Frequency (ETHF)
AND
---(3) Do repetitive eddy
current inspection of the
horizontal stabilizer left
and right upper center
skin panels in accordance
with Paragraph 3.B.,
Work Instructions, using
one of the options as fol-
lows:
5,200 flight cycles-OPTION 1:
(a)
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Table 1: Inspect Horizontal Stabilizer Left and Right Upper Center Skin Panels for Cracks
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
Scan 1 - Eddy Current,
High Frequency (ETHF)
Within 5,200
flight cycles af-
ter doing the ed-
dy current in-
spection.
Scan 2 - Eddy Current,
High Frequency (ETHF)
Scan 3 - Eddy Current,
Low Frequency (ETLF) (a)
OR
2,500 flight cycles-Within 2,500
flight cycles af-
ter doing the ed-
dy current in-
spection.
OPTION 2:
Scan 1 - Eddy Current,
High Frequency (ETHF)
Scan 2 - Eddy Current,
High Frequency (ETHF)
(a)
(a)Scan 3 - Eddy Current,
High Frequency (ETHF)
OR
--Before further
flight
OPTION 2:
Contact Boeing for possi-
ble temporary repair of
crack and do the repair in
accordance with Boeing's
instructions.
Condition 2
(Crack Found)
(a) It is acceptable to change inspection procedures from Option 1 to Option 2 or from Option 2 to Option 1
if you do as follows:
1. If the inspection procedure is being changed from Option 1 to Option 2, the first Option 2 inspection must
be done within 5,200 flight cycles after the Option 1 inspection. The Option 2 inspections that follows must
be done within 2,500 flight cycle repeat intervals
2. If the inspection procedure is being changed from Option 2 to Option 1, the first Option 1 inspection must
be done within 2,500 flight cycles after the Option 2 inspection. The Option 1 inspections that follows must
be done within 5,200 flight cycle repeat intervals
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
The table below shows an estimate of the task hours necessary to do the inspection and/or configuration
changes for each horizontal stabilizer upper center skin panel. This estimate is for direct labor only,
done by an experienced crew. Adjust the estimate with operator task hour data if necessary. The
estimate does not include lost time. These are some examples of lost time:
 Time to adjust to the workplace
 Time to schedule the work
 Time to inspect the work
 Time to cure the materials
 Time to make the parts
 Time to find the tools.
All Airplanes: Horizontal Stabilizer Upper Center Skin Panel Initial Inspection
Elapsed HoursTask HoursNumber of PersonsTask
2.04.02Figure 1 - Inspection
2.04.0TOTAL FOR EACH UPPER CENTER SKIN
PANEL
Condition 1: Horizontal Stabilizer Upper Center Skin Panel Repetitive Inspection
Elapsed HoursTask HoursNumber of PersonsTask
2.04.02Figure 1 - Inspection
2.04.0TOTAL FOR EACH UPPER CENTER SKIN
PANEL
Condition 2, Option 1: Horizontal Stabilizer Upper Center Skin Panel Replacement
Elapsed HoursTask HoursNumber of PersonsTask
8.048.06Remove Horizontal
Stabilizer
12.024.02Remove Leading
Edge and Upper For-
ward Skin Panel
168.0504.03Replace Horizontal
Stabilizer Upper
Center Skin Panel
12.024.02Install Leading Edge
and Upper Forward
Skin Panel
8.048.06Install Horizontal
Stabilizer
208.0648.0TOTAL FOR EACH UPPER CENTER SKIN
PANEL
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H. Weight and Balance Changes
Group 1:
Condition 1:
1. None
Group 1:
Condition 2, Option 1:
1. Replacement of 5922577-501 or 5922577-502 Upper Center Skin Panel
a. DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and MD-88 Airplanes
Moment Change
(MEW) IN.-LBS
Mfr's Empty
Weight (MEW)
LBS
Approximate Sta-
tion (Inches)
SR09550033 Con-
figuration
3117.0+ 1.9+ 1640.5SR09550033-7005
SR09550033-7006
3117.0+ 1.9+ 1640.5SR09550033-7007
SR09550033-7008
b. DC-9-87 (MD-87) Airplanes
Moment Change
(MEW) IN.-LBS
Mfr's Empty
Weight (MEW)
LBS
Approximate Sta-
tion (Inches)
SR09550033 Con-
figuration
2719.9+ 1.9+ 1431.5SR09550033-7005
SR09550033-7006
2719.9+ 1.9+ 1431.5SR09550033-7007
SR09550033-7008
2. Replacement of 5922577-507 or 5922577-508 Upper Center Skin Panel
a. DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and MD-88 Airplanes
Moment Change
(MEW) IN.-LBS
Mfr's Empty
Weight (MEW)
LBS
Approximate Sta-
tion (Inches)
SR09550033 Con-
figuration
1804.6+ 1.1+ 1640.5SR09550033-7005
SR09550033-7006
1804.6+ 1.1+ 1640.5SR09550033-7007
SR09550033-7008
b. DC-9-87 (MD-87) Airplanes
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Moment Change
(MEW) IN.-LBS
Mfr's Empty
Weight (MEW)
LBS
Approximate Sta-
tion (Inches)
SR09550033 Con-
figuration
1574.7+ 1.1+ 1431.5SR09550033-7005
SR09550033-7006
1574.7+ 1.1+ 1431.5SR09550033-7007
SR09550033-7008
Group 2:
Condition 1:
1. None
Group 2:
Condition 2, Option 1:
1. Replacement of 5922577-507 or 5922577-508 Upper Center Skin Panel
a. DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and MD-88 Airplanes
Moment Change
(MEW) IN.-LBS
Mfr's Empty
Weight (MEW)
LBS
Approximate Sta-
tion (Inches)
SR09550033 Con-
figuration
1804.6+ 1.1+ 1640.5SR09550033-7001
SR09550033-7002
1804.6+ 1.1+ 1640.5SR09550033-7003
SR09550033-7004
b. DC-9-87 (MD-87) Airplanes
Moment Change
(MEW) IN.-LBS
Mfr's Empty
Weight (MEW)
LBS
Approximate Sta-
tion (Inches)
SR09550033 Con-
figuration
1574.7+ 1.1+ 1431.5SR09550033-7001
SR09550033-7002
1574.7+ 1.1+ 1431.5SR09550033-7003
SR09550033-7004
I. Electrical Load Data
Not changed.
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J. References
1. Existing Data:
a. Non-Destructive Test Standard Practices Manual (NDTSPM) 06-00-07, 06-10-01.001,
06-10-02.005.
b. MD80 Aircraft Maintenance Manual (AMM) 55-10-00, 55-10-01.
2. Data supplied with this Service Bulletin:
No data is supplied with this service bulletin. To obtain the data necessary to support this service
bulletin submit a data request to:
Data and Services Management
MS D800-0019
3855 Lakewood Boulevard
Long Beach, California 90846
Phone: (562) 593-6996
Fax: (562) 593-2001
E-mail: dse.boecom@boeing.com
a. Drawings:
ADCNDCN/REVSheetTitleDrawing No
--DWGPANEL INSTL-UPPER & LOWER CTR
PANEL, HORIZONTAL STABILIZER
SR09550033
3. Installation Drawings Used in the Preparation of this Service Bulletin:
ChangeTitleDocument Number
TPANEL-SKIN AND STGR, HORIZ
STAB, CTR
5922577
DASTRUCT ASSEM-HORIZ STAB
OUTER PANEL FRONT TO REAR
SPAR
5922575
BFSTABILIZER ASSY-COMPLETE
HORIZONTAL
5930603
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:
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None.
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 affects FCS. DTI requirements for the structure affected
are contained in Paragraph 1.E., Compliance of this service bulletin.
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 below which contain the parts listed in Paragraph 2.C., Parts Necessary
for Each Airplane. Operators are encouraged to share schedule requirements with Boeing for
incorporation of the service bulletin. The kits are subject to the terms and conditions of the Boeing
standard purchase order acknowledgment. Prices are in United States Dollars. Terms: Net 30 days.
Reference this service bulletin and submit your purchase order by one of these methods:
1. Order on-line via ATA Spec 2000 or The Boeing PART Page
2. Fax to (206) 662-7145
Group 1:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RE-
SPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE
INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NameKit Number
$36,405.00120Service Kit - Upper CenterSA09550068-3
Skin Panel (Left)
$36,405.00120Service Kit - Upper CenterSA09550068-5
Skin Panel (Right)
Group 2:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RE-
SPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE
INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NameKit Number
$54,071.00120Service Kit - Upper CenterSA09550068-7
Skin Panel (Left)
$54,071.00120Service Kit - Upper CenterSA09550068-9
Skin Panel (Right)
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Boeing can supply the parts shown below as end item spares. Operators are encouraged to share
schedule requirements with Boeing for incorporation of the service bulletin. The parts are subject to
the terms and conditions of the Boeing standard purchase order acknowledgment. Prices are in United
States Dollars. Terms: Net 30 days.
Reference this service bulletin and submit your purchase order by one of these methods:
1. Order on-line via ATA Spec 2000 or The Boeing PART Page
2. Fax to (206) 662-7145
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
$23,995.00120Upper Center Skin Panel (Left)SE09550017-6 (a)
(5922577-508)
$23,995.00120Upper Center Skin Panel (Right)SE09550017-5 (a)
(5922577-507)
(a) A limited quantity of parts are available. Please contact spares for parts availability. Once the supply is
exhausted this part will no longer be available.
B. Industry Support Information
Boeing warranty remedies are not available for the inspection and/or repair procedures given in this
service bulletin.
C. Parts Necessary For Each Airplane
1. Kits/Parts:
To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
NOTE: One top kit per panel location (left or right) and the items shown in Paragraph 2.C.2.,
Parts and Materials Supplied by the Operator, are necessary for each airplane.
Group 1:
SERVICE KIT APPLICABILITY
SR Drawing ConfigurationNameSA Kit Number
SR09550033-7005Service Kit - Upper CenterSA09550068-3
Skin Panel (Left)
SR09550033-7007Service Kit - Upper CenterSA09550068-5
Skin Panel (Right)
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### Page 23

Group 2:
SERVICE KIT APPLICABILITY
SR Drawing ConfigurationNameSA Kit Number
SR09550033-7001Service Kit - Upper CenterSA09550068-7
Skin Panel (Left)
SR09550033-7003Service Kit - Upper CenterSA09550068-9
Skin Panel (Right)
Group 1:
Kit SA09550068
NotesExisting Part
Number
NameQTYNew Part Number
-5-3
(a).-SA09550068-3
(a)-.SA09550068-5
NUT BARREL77117LH7940T-054
(b)5930603-9FILLER14143964835-511
NUT ASSEMBLY113D0006-3
NUT ASSEMBLY113D0006-4
BOLT663D0031-5-22
BOLT113D0031-5-24
(c)5922577-501UPPER PANEL
(RIGHT)
1.5922577-511
or
5922577-507
(d)5922577-502UPPER PANEL
(LEFT)
.15922577-512
or
5922577-508
WASHER7773232-5-8.1
PIN1414HLT435-6-3
PIN2727HLT435-6-4
PIN77HLT435-6-5
PIN55HLT435-6-6
PIN22HLT435-6-8
PIN1515HLT435-8-3
PIN4343HLT435-8-4
PIN11HLT435-8-5
PIN5858HLT439-8-3
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### Page 24

Group 1:
Kit SA09550068
NotesExisting Part
Number
NameQTYNew Part Number
-5-3
RIVET1212MS20426AD5-6D
RIVET4444MS20426AD5-7D
RIVET66MS20426AD5-8D
RIVET88MS20426AD6-8D
RIVET77MS20426E8-12D
RIVET3737MS20426E8-9D
RIVET1616MS20470AD6-7D
RIVET2222MS20470AD6-8D
NUT5858MS21042L3
NUT116116MS21042L4
RIVET5454NAS1097KE8-10D
RIVET22NAS1097KE8-11D
RIVET1111NAS1097KE8-12D
RIVET110110NAS1097KE8-9D
WASHER5858NAS1252-10L
WASHER116116NAS1252-416L
PIN44S4931919-6-5
(a) If grip length shown is not available at Boeing, fasteners supplied in kits may
be one grip length longer than indicated. Also, if any fasteners part numbers
listed are not available or have been superseded, substitute fasteners may be
supplied in kits.
(b) 5930603-9 Filler may be used in lieu of 3964835-511 Filler.
(c) 5922577-507 Upper Center Skin Panel may be used in lieu of 5922577-511
Upper Center Skin Panel.
(d) 5922577-508 Upper Center Skin Panel may be used in lieu of 5922577-512
Upper Center Skin Panel.
Group 2:
Kit SA09550068
NotesExisting Part
Number
NameQTYNew Part Number
-9-7
(a).-SA09550068-7
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### Page 25

Group 2:
Kit SA09550068
NotesExisting Part
Number
NameQTYNew Part Number
-9-7
(a)-.SA09550068-9
NUT BARREL77117LH7940T-054
(b)5930603-9FILLER14143964835-511
NUT ASSEMBLY113D0006-3
BOLT663D0031-5-22
BOLT113D0031-5-24
(c)5922577-507UPPER PANEL
(RIGHT)
1.5922577-511
(d)5922577-508UPPER PANEL
(LEFT)
.15922577-512
WASHER7773232-5-8.1
PIN1414HLT435-6-3
PIN2727HLT435-6-4
PIN77HLT435-6-5
PIN55HLT435-6-6
PIN22HLT435-6-8
PIN7373HLT435-8-3
PIN4343HLT435-8-4
RIVET1212MS20426AD5-6D
RIVET4444MS20426AD5-7D
RIVET66MS20426AD5-8D
RIVET88MS20426AD6-8D
RIVET1616MS20470AD6-7D
RIVET2222MS20470AD6-8D
NUT5858MS21042L3
NUT116116MS21042L4
RIVET5454NAS1097KE8-10D
RIVET22NAS1097KE8-11D
RIVET1818NAS1097KE8-12D
RIVET147147NAS1097KE8-9D
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### Page 26

Group 2:
Kit SA09550068
NotesExisting Part
Number
NameQTYNew Part Number
-9-7
WASHER5858NAS1252-10L
WASHER116116NAS1252-416L
PIN44S4931919-6-5
(a) If grip length shown is not available at Boeing, fasteners supplied in kits may
be one grip length longer than indicated. Also, if any fasteners part numbers
listed are not available or have been superseded, substitute fasteners may be
supplied in kits.
(b) 5930603-9 Filler may be used in lieu of 3964835-511 Filler.
(c) 5922577-507 Upper Center Skin Panel may be used in lieu of 5922577-511
Upper Center Skin Panel.
(d) 5922577-508 Upper Center Skin Panel may be used in lieu of 5922577-512
Upper Center Skin Panel.
2. Parts and Materials Supplied by the Operator:
NotesQTYNamePart Number/Specification
(a)As RequiredSealantPR-1422 B-2
(DMS 2082)
or
Equivalent
CAGESupplier
83574PRC - DeSoto International, Incorporated(a) Can be purchased from:
24811 Avenue Rockefeller
Valencia, California 91355 -3468
3. Parts Modified and Reidentified:
None.
4. Parts Removed and Not Replaced:
None.
D. Parts Necessary to Change Spares
None.
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### Page 27

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 28

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BLANK PAGE

### Page 29

3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
WARNING: IF ELECTRICAL POWER IS APPLIED TO THE AIRPLANE, MAKE SURE YOU OBEY
ALL PRECAUTIONS WHILE YOU DO WORK. IF YOU DO NOT OBEY THE
PRECAUTIONS, DEATH OR INJURY TO PERSONS, AND DAMAGE TO THE AIRPLANE
CAN OCCUR.
CAUTION: ELECTRICALLY GROUND THE AIRPLANE. THIS WILL HELP TO PREVENT DAMAGE
TO THE AIRPLANE OR EQUIPMENT.
CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL
PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,
METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE
DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR
OTHER ELECTRICAL DAMAGE.
NOTE: 1. 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 the AEPL, Drawing 7595071.
4. Use the approved fastener substitutions and process material substitutions, in
accordance with MD-80 Structural Repair Manual (SRM) 51.
5. If the length of any fastener specified in this service bulletin does not meet the
installation standards in MD-80 SRM 51, then a fastener of the same specification,
or an approved substitute, with a length which meets the installation standards in
MD-80 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
– Angular tolerance is plus or minus 2 degrees
– Hole dimensions for standard solid rivets are in MD-80 SRM 51.
– Torque limits to tighten nuts and bolts are in MD-80 SRM 51.
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### Page 30

8. Obey all of the warnings and cautions given in the specified manual sections.
9. These work instructions refer to procedures included in other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "in
accordance with" are included in the instruction, the procedure in the Boeing document
must be used.
10. Some Boeing parts are supplied in a temporary configuration. Those parts are
identified with a 'U' or 'Y' in place of the '-' (dash) in the part number. It is permitted
to install parts identified with a 'U' or 'Y' as an alternative to the '-' (dash) number
part. Boeing Drawing SE10000000, Sheets 5.0 and 6.0 contain more data.
B. WORK INSTRUCTIONS
GROUP 1:
1. Do an eddy current inspection of the horizontal stabilizer left and right upper center skin panels in
accordance with FIGURE 1 and based on inspection results for each panel, do as follows:
Condition 1 (No Crack Found)
a. Do repetitive eddy current inspections of the horizontal stabilizer upper center skin panel in
accordance with FIGURE 1, at intervals specified in Paragraph 1.E., Compliance.
Condition 2 (Crack Found)
a. OPTION 1:
(1) Remove and keep horizontal stabilizer. Refer to MD80 AMM 55-10-00.
(2) Remove and keep horizontal stabilizer leading edge. Refer to MD80 AMM 55-10-01.
(3) Remove and keep horizontal stabilizer upper forward skin panel to gain access to the
cracked horizontal stabilizer upper center skin panel. Refer to drawing 5922575.
(4) Remove and replace the cracked horizontal stabilizer upper center skin panel in
accordance with the applicable configuration of Service Rework Drawing SR09550033
using the applicable kit as follows:
KIT
SA09550068
CENTER SKIN
PANEL LOCATION
DRAWING
SR09550033
-3UPPER LEFT-7005
-5UPPER RIGHT-7007
(5) Install kept horizontal stabilizer upper forward skin panel. Refer to drawing 5922575 and
MD80 SRM 51.
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### Page 31

(6) Install kept horizontal stabilizer leading edge. Refer to MD80 AMM 55-10-01.
(7) Install kept horizontal stabilizer. Refer to MD80 AMM 55-10-00.
(8) Do repeat eddy current inspection of the replacement horizontal stabilizer upper center
skin panel in accordance with FIGURE 1, at intervals specified in Paragraph 1.E.,
Compliance.
b. OPTION 2:
(1) Contact Boeing for possible temporary repair of crack and do the repair in accordance
with Boeing's instructions.
2. Put the airplane back to serviceable condition.
GROUP 2:
1. Do an eddy current inspection of the horizontal stabilizer left and right upper center skin panels in
accordance with FIGURE 1 and based on inspection results for each panel, do as follows:
Condition 1 (No Crack Found)
a. Do repeat eddy current inspections of the horizontal stabilizer upper center skin panel in
accordance with FIGURE 1, at intervals specified in Paragraph 1.E., Compliance.
Condition 2 (Crack Found)
a. OPTION 1:
(1) Remove and keep horizontal stabilizer. Refer to MD80 AMM 55-10-00.
(2) Remove and keep horizontal stabilizer leading edge. Refer to MD80 AMM 55-10-01.
(3) Remove and keep horizontal stabilizer upper forward skin panel to gain access to the
cracked horizontal stabilizer upper center skin panel. Refer to drawing 5922575.
(4) Remove and replace the cracked horizontal stabilizer upper center skin panel in
accordance with the applicable configuration of Service Rework Drawing SR09550033
using the applicable kit as follows:
KIT
SA09550068
CENTER SKIN
PANEL LOCATION
DRAWING
SR09550033
-7UPPER LEFT-7001
-9UPPER RIGHT-7003
(5) Install kept horizontal stabilizer upper forward skin panel. Refer to drawing 5922575 and
MD80 SRM 51.
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### Page 32

(6) Install kept horizontal stabilizer leading edge. Refer to MD80 AMM 55-10-01.
(7) Install kept horizontal stabilizer. Refer to MD80 AMM 55-10-00.
(8) Do repeat eddy current inspection of the replacement horizontal stabilizer upper center
skin panel in accordance with FIGURE 1, at intervals specified in Paragraph 1.E.,
Compliance.
b. OPTION 2:
(1) Contact Boeing for possible temporary repair of crack and do the repair in accordance
with Boeing's instructions.
2. Put the airplane back to serviceable condition.
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### Page 33 (OCR)

BOEING SERVICE BULLETIN MD80-55A068
ALERT  ALERT
.35 + .05
STGR.3
NBD
.25 + .10
XH=7.234
UPPER PANEL
LOOKING DOWN  _ LEFT SIDE  1956784
FIGURE 1: HORIZONTAL STABILIZER LEFT AND RIGHT UPPER CENTER SKIN PANELS - EDDY CURRENT
INSPECTION
(SHEET 1 OF 6)
Original Issue: July 16, 2010
MD80-55A068
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  33 of 38

### Page 34 (OCR)

BOEING SERVICE BULLETIN MD80-55A068
ALERT  ALERT
SCAN PARALLEL TO EDGE S
.35 + .05
(3)
NBD
STGR.3
25 + .10
XH=7.234
UPPER PANEL
LEFT SIDE
LOOKING DOWN
1957252
FIGURE 1: HORIZONTAL STABILIZER LEFT AND RIGHT UPPER CENTER SKIN PANELS - EDDY CURRENT
INSPECTION
(SHEET 2 OF 6)
Original Issue: July 16, 2010
BOEING PROPRIETARY -  MD80-55A068
Copyright © Unpublished Work - See page 1 for details.  34 of 38

### Page 35 (OCR)

BOEING SERVICE BULLETIN MD80-55A068
ALERT  ALERT
======
.35 + .05
INBD
STGR.3
.25 + .10
XH=7.234
UPPER PANEL
RIGHT SIDE
LOOKING DOWN  1957268
FIGURE 1: HORIZONTAL STABILIZER LEFT AND RIGHT UPPER CENTER SKIN PANELS - EDDY CURRENT
INSPECTION
(SHEET 3 OF 6)
Original Issue: July 16, 2010
MD80-55A068
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  35 of 38

### Page 36 (OCR)

BOEING SERVICE BULLETIN MD80-55A068
ALERT  ALERT
- SCAN PARALLEL TO EDGE
.35 + .05
INBD
.25 + .10
2.5 + .10
XH=7.234
UPPER PANEL
LOOKING DOWN  RIGHT SIDE  1957272
FIGURE 1: HORIZONTAL STABILIZER LEFT AND RIGHT UPPER CENTER SKIN PANELS - EDDY CURRENT
INSPECTION
(SHEET 4 OF 6)
Original Issue: July 16, 2010
MD80-55A068
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  36 of 38

### Page 37

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) (e)15922577-501Upper Center Skin
Panel - Right
Inspect - (Scan 1)
OPTION 1, 2:
1
or
Eddy Current, High
Frequency (ETHF)
5922577-507
or
5922577-511
or
SE09550017-5
5922577-502Upper Center Skin
Panel - Left or
5922577-508
or
5922577-512
or
SE09550017-6
(b) (e)15922577-501Upper Center Skin
Panel - Right
Inspect - (Scan 2)
OPTION 1, 2:
2
or
Eddy Current, High
Frequency (ETHF)
5922577-507
or
5922577-511
or
SE09550017-5
5922577-502Upper Center Skin
Panel - Left or
5922577-508
or
5922577-512
or
SE09550017-6
(c) (e)15922577-501Upper Center Skin
Panel - Right
Inspect - (Scan 3)
OPTION 1:
3
or
Eddy Current, Low
Frequency (ETLF)
5922577-507
or
5922577-511
or
SE09550017-5
5922577-502Upper Center Skin
Panel - Left or
5922577-508
or
5922577-512
or
SE09550017-6
FIGURE 1: HORIZONTAL STABILIZER LEFT AND RIGHT UPPER CENTER SKIN PANELS - EDDY CURRENT
INSPECTION
(SHEET 5 OF 6)
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### Page 38

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Inspect - (Scan 3) (d) (e) 15922577-501Upper Center Skin
Panel - Right orOPTION 2:
5922577-507Eddy Current, High
Frequency (ETHF) or
5922577-511
or
SE09550017-5
5922577-502Upper Center Skin
Panel - Left or
5922577-508
or
5922577-512
or
SE09550017-6
Do an Eddy Current, High Frequency surface inspection of the horizontal stabilizer upper center
skin panels around the fastener in the inspection area. Scan around the fastener using a nonconduc-
tive circle template looking for cracks propagating from the fastener hole. Refer to NDTSPM 06-10-
01.001 (ETHF - Procedure 1). Use Calibration Method "P" and Scan Method "47".
(a)
Do an Eddy Current, High Frequency surface inspection of the horizontal stabilizer upper center
skin panels along the inboard portion of the aft edge as shown in the inspection area. Scan the edges
looking for cracks propagating from the panel edge. Refer to NDTSPM 06-10-01.001 (ETHF - Pro-
cedure 1). Use Calibration Method "A" and Scan Method "79".
(b)
Do an Eddy Current, Low Frequency sub-surface inspection of the horizontal stabilizer upper center
skin panels at all other areas in the rectangular shaped inspection area not inspected by Scan 1 or
2. Scan the noted area of the upper surface of the upper panels. Refer to NDTSPM 06-10-02.005
(ETLF - Procedure 5).
(c)
NOTE:
Space each scan approximately 1/2 probe coil diameter apart.
Do an Eddy Current, High Frequency surface inspection of the horizontal stabilizer upper center
skin panels at all other areas in the rectangular shaped inspection area not inspected by Scan 1 or
2. Scan the noted area of the upper surface of the upper panels. Refer to NDTSPM 06-10-01.001
(ETHF - Procedure 1).Use Calibration Method "C" and Scan Method "61".
(d)
NOTE:
Space each scan approximately 1/2 probe coil diameter apart.
Evaluate and verify crack indications found during inspection. Refer to NDTSPM 06-00-07.(e)
FIGURE 1: HORIZONTAL STABILIZER LEFT AND RIGHT UPPER CENTER SKIN PANELS - EDDY CURRENT
INSPECTION
(SHEET 6 OF 6)
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