# Boeing Alert Service Bulletin MD80-57A244: Revision 1

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- Title as filed: SB-MD80-57A244-01--BOEING
- Pages: 109
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## Text

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### Page 1

Commercial 
Airplanes
MD80
Service Bulletin
ALERT
Number: MD80-57A244
Original Issue: March 03, 2016
Revision 1: October 01, 2019
ATA System: 5732
SUBJECT: WINGS - Lower Wing Skin - Inspection of Left Side and Right Side Center Wing Lower
Skins and Stringers
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 300-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET
Copyright © 2016 Boeing.
Unpublished Work. All Rights Reserved.
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document
are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The
Boeing Company.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and
Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in
connection with this document unless provided in writing by Boeing.
Original Issue: March 03, 2016
MD80-57A244Revision 1: October 01, 2019
1 of 109
20.0

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Table of Contents
Revision Transmittal Sheet ............................................ 5
S u m m a r y  ...................................................... 7
1. PLANNING INFORMATION ........................................ 1 1
A . E f f e c t i v i t y  ............................................... 1 1
1. Airplanes ............................................ 1 1
2 . S p a r e s  A f f e c t e d  ........................................ 1 3
B. Concurrent Requirements ...................................... 1 3
C. Reason ................................................ 1 4
D. Description .............................................. 1 4
E. Compliance .............................................. 1 5
F . A p p r o v a l  ............................................... 3 2
G. Manpower .............................................. 3 3
H. Weight and Balance Changes .................................... 3 3
I. Electrical Load Data ......................................... 3 3
J . R e f e r e n c e s  .............................................. 3 4
1. Existing Data: ......................................... 3 4
2. Data Supplied with this Service Bulletin: ........................... 3 4
3. Installation Drawings Used in the Preparation of this Service  Bulletin: ........... 3 6
K. Publications Affected ........................................ 3 6
L. Interchangeability and Intermixability of Parts ........................... 3 6
M. Software Accomplishment Summary ................................ 3 6
2. MATERIAL INFORMATION ........................................ 3 7
A. Material - Price and Availability ................................... 3 7
B. Industry Support Information .................................... 3 7
C. Parts Necessary for Each Airplane ................................. 3 7
1 . K i t s / P a r t s  ............................................ 3 7
2. Parts and Materials Supplied by the Operator ........................ 3 7
3. Parts Modified and Reidentified ................................ 3 7
4. Parts Removed and Not Replaced .............................. 3 7
D. Parts Necessary to Change Spares ................................. 3 7
E. Special Tooling - Price and Availability ............................... 3 8
F. Special Tooling Necessary to do this Service Bulletin ....................... 3 8
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 9
A. GENERAL INFORMATION ..................................... 3 9
B. WORK INSTRUCTIONS ....................................... 4 1
FIGURE 1: OPEN ACCESS - LEFT SIDE ................................. 6 3
FIGURE 2: INSPECTION - LEFT SIDE .................................. 6 5
FIGURE 3: CLOSE ACCESS - LEFT SIDE ................................ 6 8
FIGURE 4: OPEN ACCESS - RIGHT SIDE ................................ 7 0
FIGURE 5: INSPECTION - RIGHT SIDE .................................. 7 2
FIGURE 6: CLOSE ACCESS - RIGHT SIDE ............................... 7 5
FIGURE 7: OPEN ACCESS - LEFT SIDE AND RIGHT SIDE ...................... 7 7
FIGURE 8: INSPECTION - LEFT SIDE AND RIGHT SIDE ........................ 7 9
FIGURE 9: CLOSE ACCESS - LEFT SIDE AND RIGHT SIDE ...................... 8 2
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### Page 4

APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE TABLE 1: EDDY CURRENT, LOW
FREQUENCY (ETLF) AND EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTIONS OF
THE LEFT SIDE AND RIGHT SIDE CENTER WING LOWER SKINS AND STRINGERS. [Group
1, Configuration 1] ....................................... 8 5
APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE TABLE 2: EDDY CURRENT, LOW
FREQUENCY (ETLF) AND EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTIONS OF
THE LEFT SIDE AND RIGHT SIDE CENTER WING LOWER SKINS AND STRINGERS. [Group
1, Configuration 1] ....................................... 8 9
APPENDIX C: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE TABLE 3: EDDY CURRENT, LOW
FREQUENCY (ETLF) AND EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTIONS OF
THE LEFT SIDE AND RIGHT SIDE CENTER WING LOWER SKINS AND STRINGERS. [Group
1, Configuration 2] ....................................... 9 5
APPENDIX D: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE TABLE 4: EDDY CURRENT, LOW
FREQUENCY (ETLF) AND EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTIONS OF
THE LEFT SIDE AND RIGHT SIDE CENTER WING LOWER SKINS AND STRINGERS. [Group
1, Configuration 2] ....................................... 9 9
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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ALERTALERT

### Page 5

Commercial 
Airplanes
MD80
Service Bulletin
ALERT
Revision Transmittal SheetNumber: MD80-57A244Original Issue: March 03, 2016
Revision 1: October 01, 2019
ATA System: 5732
SUBJECT: WINGS - Lower Wing Skin - Inspection of Left Side and Right Side Center Wing Lower
Skins and Stringers
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
Federal Aviation Administration (FAA) Airworthiness Directive AD 2016-07-28 is related to this service bulletin.
Effects of this Revision on airplanes on which Original Issue was previously done:
None.
Refer to Paragraph 1.E., Compliance for changes to Compliance actions and times.
REASON FOR REVISION
Revision 1 is sent to expand the inspection of the stringers by doing an external Eddy Current, Low Frequency
(ETLF) inspection of the left and right side wing fastener holes common to stringers 11 thru 22 and the forward
and aft skins and an Eddy Current, High Frequency (ETHF) inspection of the lower skin at stringers 18 thru 20
for any crack.
These sections were changed:
1. Summary, Background, added Revision information.
2. Summary, Action, added new inspection information.
3. Summary, Compliance, added Federal Aviation Authority (FAA) Airworthiness Directive (AD) reference.
4. Summary, Illustration, revised to include new inspections.
5. Paragraph 1.C., Reason, added Revision information.
6. Paragraph 1.D., Description, added new inspection information  and effects of this revision statement.
7. Paragraph 1.E., Compliance, added FAA AD reference, logic diagram reference, added new inspection
and revised compliance information.
8. Paragraph 1.F., Approval, added FAA AD Alternative Method of Compliance (AMOC) statement.
Export Controlled ECCN: 9E991 - BOEING
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9. Paragraph 1.J., References, added new references and new draw ing reference.
10. Paragraph 2.C., Parts and Materials Supplied by the Operator , added footnote.
11. Paragraph 3.A., General Information, added logic diagram inf ormation.
12. Paragraph 3.B., Work Instructions, added new inspection inst ructions.
13. Figure 7: Added information for new inspection.
14. Figure 8: Added instructions for new inspection.
15. Figure 9: Added close access information for new inspection criteria.
16. Appendix A: Added logic diagram.
17. Appendix B: Added logic diagram.
18. Appendix C: Added logic diagram.
19. Appendix D: Added logic diagram.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes,
to show the location of all content changes.
Pages with no vertical lines have no changes.
REVISION HISTORY
March 03, 2016Original Issue:
October 01, 2019Revision 1:
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: March 03, 2016
MD80-57A244Revision 1: October 01, 2019
6 of 109
BOEING SERVICE BULLETIN MD80-57A244
ALERTALERT

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Commercial 
Airplanes
MD80
Service Bulletin
ALERT
SummaryNumber: MD80-57A244Original Issue: March 03, 2016
Revision 1: October 01, 2019
ATA System: 5732
SUBJECT: WINGS - Lower Wing Skin - Inspection of Left Side and Right Side Center Wing Lower
Skins and Stringers
THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN
PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT
TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE
NEW OWNER.
CONCURRENT REQUIREMENTS
None.
BACKGROUND
This service bulletin gives instructions to do an Eddy Current, Low Frequency (ETLF) inspection of the left and
right side fastener holes common to stringers 11 thru 22 and the forward and aft skins and do an Eddy Current,
High Frequency (ETHF) inspection of the lower skin at stringers 18 thru 20 for any crack. If the inspection in this
service bulletin is not done, fatigue cracks could grow to a critical length before being found by routine maintenance
inspections which could cause structural failure of the wings.
There have been five reports of cracks at Stringers S-15, S-16, or S-17, associated end fittings and skins in the
center wing fuel tank where the stringers meet the end fittings near Xcw=13 and Xcw=15. The table below
shows, for each reported case of cracks, where the cracks occurred, and the flight cycles and hours of the
airplane at the time of the crack. In four of the five reports, the cracks were discovered while doing Maintenance
Planning Document (MPD) item 57-086-02 during scheduled maintenance. The cause of the cracks is determined
to be fatigue.
NotesFlight Cycles/
Flight Hours
Structure CrackedDateReport
Scheduled Maintenance42,247 / 78,873Stringer 17 RightJuly 20141
Found during fuel leak in-
vestigation
44,147 / 61,208Stringer 17 Left, Fwd Skin, Aft SkinApril 20152
Scheduled Maintenance56,908 / 74,240Stringer 17 Right, Fwd Skin, Aft
Skin
July 20153
Scheduled Maintenance43,756 / 60,690Stringer 15 and 16 Right, four end
fittings (two per stringer)
August 20154
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NotesFlight Cycles/
Flight Hours
Structure CrackedDateReport
Scheduled Maintenance45,421 / 63,168Stringer 17 Left and Stringer 17
Right
January 20165
After the release of the Original Issue of this service bulletin there have been 10 additional reports of cracks at
Stringers S-15, S-16, or S-17, three of these with forward and aft skin cracks at S-17. In addition, on one of
these aircraft a crack was reported at Stringer S-13 location. Boeing has determined the inspections given in
the Original Issue of this service bulletin requires an expansion of the inspection to adjacent stringers with similar
stress levels and requires an inspection with increased sensitivity for crack detection in the area. This revision
is sent to replace and expand the inspection of the stringers by doing an external Eddy Current, Low Frequency
(ETLF) inspection of the left and right side wing fastener holes common to stringers 11 thru 22 and the forward
and aft skins and an Eddy Current, High Frequency (ETHF) inspection of the lower skin at stringers 18 thru 20
for any crack.
This table is provided to operators for planning purposes only. Refer to the applicable sections for more
information.
ReferenceAffectedPlanning Data
Paragraph 1.A.2., Spares AffectedNoSpares Affected
Paragraph 1.E., Compliance and Paragraph
1.F., Approval
YesAD Related
Paragraph 1.H., Weight and Balance ChangesNoWeight and Balance Change
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
Paragraph 1.K., Publications AffectedNoPublications Affected
Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew
Operations Manual and/or FAA Approved Air-
plane Flight Manual)
Paragraph 2.C.1., Kits/PartsNoKits/Parts Required
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
YesOperator Supplied Parts/Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
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ALERTALERT

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ACTION
Get access to the left and right center wing lower skins, stringers S-11 thru S-22 between Xcw=0 and Xcw=20
under the wing/fuselage fillet panels. This service bulletin gives instructions to do an Eddy Current, Low Frequency
(ETLF) inspection of the left and right side fastener holes common to stringers 11 thru 22 and the forward and
aft skins and do an Eddy Current, High Frequency (ETHF) inspection of the lower skin at stringers 18 thru 20
for any crack. If any crack is found, contact The Boeing Company for repair instructions and do the repair; and
repeat the inspections for any crack in the unrepaired area. If no crack is found, repeat the inspections for any
crack.
EFFECTIVITY
All DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 airplanes. Refer to
Paragraph 1.A.1., Airplanes, for the list of affected airplane(s).
COMPLIANCE
Federal Aviation Administration (FAA) Airworthiness Directive AD 2016-07-28 is related to this service bulletin.
The effective date of AD 2016-07-28 is April 26, 2016.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the inspection given in this service bulletin.
MANPOWER
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
Operator Supplied Parts/Materials.
Refer to Paragraph 2.A., Material - Price and Availability.
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ALERTALERT

### Page 10 (OCR)

BOEING SERVICE BULLETIN MD80-57A244
ALERT  ALERT
DO AN EDDY CURRENT, LOW FREQUENCY (ETLF)
INSPECTION OF FASTENER HOLES COMMON TO
STRINGERS 11 THRU 22 AND THE FORWARD AND
AFT SKINS FOR ANY CRACK.
DO AN EDDY CURRENT, HIGH FREQUENC
ETHF) INSPECTION OF THE LOWER SKIN AT
STRINGERS 18 THRU 20 FOR ANY CRACK
Xcw=0.000
Xcw=20.000
INSPECTION AREA
STRINGERS 11-22
STRINGER 22
- STRINGER 21
- STRINGER 20
- STRINGER 19
STRINGER 18
• STRINGER 17
•STRINGER 16
STRINGER 15
STRINGER 14
• STRINGER 13
• STRINGER 12
STRINGER 11
- REAR SPAR
— SKIN
STRINGER
INSPECTION AREA
LEFT SIDE SHOWN, RIGHT SIDE OPPOSITE  LOWER WING SKINS AND STRINGERS  2481761
(VIEW LOOKING DOWN)
Original Issue: March 03, 2016
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Work - See page 1 for details.  10 of 109

### Page 11

Commercial 
Airplanes
MD80
Service Bulletin
ALERT
Number: MD80-57A244
Original Issue: March 03, 2016
Revision 1: October 01, 2019
ATA System: 5732
SUBJECT: WINGS - Lower Wing Skin - Inspection of Left Side and Right Side Center Wing Lower
Skins and Stringers
THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN
PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT
TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE
NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
This bulletin is applicable to DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87
(MD-87), MD-88 Airplane(s), line number(s) 909, 917, 924, 938, 941, 944, 946, 948, 950, 952-953,
955, 957-958, 960, 962-963, 965-967, 969-971, 973-975, 977-979, 981, 983, 985-986, 988-989,
991-992, 994-999, 1000-1013, 1015-1016, 1018-1020, 1022-1023, 1025-1026, 1028-1029,
1031-1032, 1034-1035, 1037-1038, 1040-1041, 1043, 1045, 1047, 1049, 1051, 1053, 1055, 1057,
1059-1080, 1082-1083, 1085-2007, 2009-2016, 2019-2034, 2036-2069, 2071-2093, 2101-2114,
2116, 2118-2119, 2121, 2124, 2127-2128, 2130, 2132, 2134-2135, 2137, 2139, 2145, 2148,
2151-2152, 2155, 2167, 2174, 2176, 2178, 2180, 2183, 2185, 2187, 2189, 2192, 2196, 2199,
2201, 2204, 2206, 2208, 2214, 2218, 2234, 2239, 2241, 2244, 2247, 2249, 2252, 2254, 2264-2287
in 1 Group(s). Where the effectivity is presented with hyphens between line numbers, the airplane
applicability means "through" and "inclusive", e.g. line numbers 1-9 means line numbers 1 through
9 inclusive.
The Variable Numbers and Group Information for the applicable airplanes is given below.
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### Page 12

DESCRIPTIONCONFIGURATIONGROUP
All DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87
(MD-87), and MD-88 airplanes.
-1
DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87
(MD-87), and MD-88 airplanes that have not done any inspection in
accordance with the Original Issue of this service bulletin.
1
DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87
(MD-87), and MD-88 airplanes that have done the inspection in
accordance with the Original Issue of this service bulletin.
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 Number
1909
1917
1924
1938
1941
1944
1946
1948
1950
1952 - 953
1955
1957 - 958
1960
1962 - 963
1965 - 967
1969 - 971
1973 - 975
1977 - 979
1981
1983
1985 - 986
GroupFuselage Number
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
11055
11057
11059 - 1080
GroupFuselage Number
11082 - 1083
11085 - 2007
12009 - 2016
12019 - 2034
12036 - 2069
12071 - 2093
12101 - 2114
12116
12118 - 2119
12121
12124
12127 - 2128
12130
12132
12134 - 2135
12137
12139
12145
12148
12151 - 2152
12155
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GroupFuselage Number
12167
12174
12176
12178
12180
12183
12185
12187
12189
GroupFuselage Number
12192
12196
12199
12201
12204
12206
12208
12214
12218
GroupFuselage Number
12234
12239
12241
12244
12247
12249
12252
12254
12264 - 2287
2. Spares Affected
None.
B. Concurrent Requirements
None.
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C. Reason
This service bulletin gives instructions to do an Eddy Current, Low Frequency (ETLF) inspection of the
left and right side fastener holes common to stringers 11 through 22 and the forward and aft skins and
do an Eddy Current, High Frequency (ETHF) inspection of the lower skin at stringers 18 through 20
for any crack. If the inspection in this service bulletin is not done, fatigue cracks could grow to a critical
length before being found by routine maintenance inspections which could cause structural failure of
the wings.
There have been five reports of cracks at Stringers S-15, S-16, or S-17, associated end fittings and
skins in the center wing fuel tank where the stringers meet the end fittings near Xcw=13 and Xcw=15.
The table below shows, for each reported case of cracks, where the cracks occurred, and the flight
cycles and hours of the airplane at the time of the crack. In four of the five reports, the cracks were
discovered while doing Maintenance Planning Document (MPD) item 57-086-02 during scheduled
maintenance. The cause of the cracks is determined to be fatigue.
NotesFlight Cycles/
Flight Hours
Structure CrackedDateReport
Scheduled Maintenance42,247 / 78,873Stringer 17 RightJuly 20141
Found during fuel leak in-
vestigation
44,147 / 61,208Stringer 17 Left, Fwd Skin, Aft SkinApril 20152
Scheduled Maintenance56,908 / 74,240Stringer 17 Right, Fwd Skin, Aft
Skin
July 20153
Scheduled Maintenance43,756 / 60,690Stringer 15 and 16 Right, four end
fittings (two per stringer)
August 20154
Scheduled Maintenance45,421 / 63,168Stringer 17 Left and Stringer 17
Right
January 20165
After the release of the Original Issue of this service bulletin there have been 10 additional reports of
cracks at Stringers S-15, S-16, or S-17, three of these with forward and aft skin cracks at S-17. In
addition, on one of these aircraft a crack was reported at Stringer S-13 location. Boeing has determined
the inspections given in the Original Issue of this service bulletin requires an expansion of the inspection
to adjacent stringers with similar stress levels and requires an inspection with increased sensitivity for
crack detection in the area. This revision is sent to replace and expand the inspection of the stringers
by doing an external Eddy Current, Low Frequency (ETLF) inspection of the left and right side wing
fastener holes common to stringers 11 thru 22 and the forward and aft skins and do an Eddy Current,
High Frequency (ETHF) inspection of the lower skin at stringers 18 thru 20 for any crack.
D. Description
Get access to the left and right center wing lower skins, stringers S-11 thru S-22 between Xcw=0 and
Xcw=20 under the wing/fuselage fillet panels. Do an Eddy Current, Low Frequency (ETLF) inspection
of the left and right side fastener holes common to stringers 11 thru 22 and the forward and aft skins
and do an Eddy Current, High Frequency (ETHF) inspection of the lower skin at stringers 18 thru 20
for any crack. If any crack is found, contact The Boeing Company for repair instructions and do the
repair; and repeat the inspections for any crack in the unrepaired area. If no crack is found, repeat the
inspections for any crack.
Effects of this Revision on airplanes on which Original Issue was previously done:
Export Controlled ECCN: 9E991 - BOEING
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ALERTALERT

### Page 15

None.
Refer to Paragraph 1.E., Compliance for changes to Compliance actions and times.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
21, 22DC-9-81 (MD-81), DC-9-82
(MD-82), DC-9-83 (MD-83), DC-
9-87 (MD-87), MD-88
E. Compliance
Federal Aviation Administration (FAA) Airworthiness Directive AD 2016-07-28 is related to this service
bulletin. The effective date of AD 2016-07-28 is April 26, 2016.
A logic diagram showing compliance tasks and compliance times is included as an aid in APPENDIX
A, APPENDIX B, APPENDIX C and APPENDIX D.
Do the required actions in accordance with Paragraph 3. Accomplishment Instructions.
All Group 1, Configuration 1 airplanes must do one of the following options:
– Option 1: Do Table 1 - Eddy Current, Low Frequency (ETLF) and Eddy Current, High Frequency
(ETHF) Inspections of stringers 11 thru 22 for initial inspection and repeat inspections.
– Option 2: Do Table 2 - High Frequency (ETHF) inspection of stringers 15 thru 17 for initial inspection
and Eddy Current, Low Frequency (ETLF) and Eddy Current, High Frequency (ETHF) Inspections
of stringers 11 thru 22 for repeat inspections.
All Group 1, Configuration 2 airplanes must do one of the following options:
– Option 1: Do Table 3 - Eddy Current, Low Frequency (ETLF) and Eddy Current, High Frequency
(ETHF) Inspections of stringers 11 thru 22 for initial inspection and repeat inspections.
– Option 2: Do Table 4 - High Frequency (ETHF) inspection of stringers 15 thru 17 for initial inspection
and Eddy Current, Low Frequency (ETLF) and Eddy Current, High Frequency (ETHF) Inspections
of stringers 11 thru 22 for repeat inspections.
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ALERTALERT

### Page 16

Group 1, Configuration 1, Option 1:
Table 1: Eddy Current, Low Frequency (ETLF) and Eddy Current, High Frequency (ETHF) Inspections
of stringers 11 thru 22 for initial inspection and repeat inspections.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 300 flight
cycles after the
effective date of
AD 2016-07-28
or within 5,400
flight cycles af-
ter the last de-
tailed inspection
done in accor-
dance with MPD
item 57-086-02,
whichever oc-
curs later.
Before 35,400
total flight cy-
cles.
Do a general visual in-
spection for existing exter-
nal lower skin repairs be-
tween Xcw=0.0 and
Xcw=20.0, stringers 11
thru 22.
Airplanes with less than
45,000 total flight cycles as
of the effective date of AD
2016-07-28.
--Within 150 flight
cycles after the
effective date of
AD 2016-07-28
or within 5,400
flight cycles af-
ter the last de-
tailed inspection
done in accor-
dance with MPD
item 57-086-02,
whichever oc-
curs later.
Do a general visual in-
spection for existing exter-
nal lower skin repairs be-
tween Xcw=0.0 and
Xcw=20.0, stringers 11
thru 22.
Airplanes with 45,000 or
more total flight cycles as
of the effective date of AD
2016-07-28.
-Before further flight.Do Part 2: Eddy Current,
Low Frequency (ETLF)
inspection of the left and
right side fastener holes
common to stringers 11
thru 22 and the forward
and aft skins and do an
Eddy Current, High Fre-
quency (ETHF) inspec-
tion of the lower skin at
stringers 18 thru 20 for
any crack.
CONDITION 1: NO RE-
PAIR FOUND.
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ALERTALERT

### Page 17

Group 1, Configuration 1, Option 1:
Table 1: Eddy Current, Low Frequency (ETLF) and Eddy Current, High Frequency (ETHF) Inspections
of stringers 11 thru 22 for initial inspection and repeat inspections.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 1.1 (AC-
TION 1): Contact The
Boeing Company for re-
pair instructions and do
the repair.
CONDITION 1.1: ANY
CRACK FOUND.
4,100 flight cycles.-CONDITION 1.1 (AC-
TION 2): Repeat Part 2:
Eddy Current, Low Fre-
quency (ETLF) inspection
of the left and right side
fastener holes common
to stringers 11 thru 22
and the forward and aft
skins and do an Eddy
Current, High Frequency
(ETHF) inspection of the
lower skin at stringers 18
thru 20 for any crack in
the unrepaired area.(a)
4,100 flight cycles.-Repeat Part 2: Eddy Cur-
rent, Low Frequency
(ETLF) inspection of the
left and right side fastener
holes common to
stringers 11 thru 22 and
the forward and aft skins
and do an Eddy Current,
High Frequency (ETHF)
inspection of the lower
skin at stringers 18 thru
20 for any crack.(a)
CONDITION 1.2: NO
CRACK FOUND.
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ALERTALERT

### Page 18

Group 1, Configuration 1, Option 1:
Table 1: Eddy Current, Low Frequency (ETLF) and Eddy Current, High Frequency (ETHF) Inspections
of stringers 11 thru 22 for initial inspection and repeat inspections.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 2 (ACTION
1): Contact The Boeing
Company for alternative
inspection(s), incorporate
the inspection(s) require-
ments into the mainte-
nance program and do
the inspection(s) at the
times specified by Boe-
ing.
CONDITION 2: ANY EXIST-
ING REPAIR FOUND.
-Before further flight.CONDITION 2 (ACTION
2): Do Part 2: Eddy Cur-
rent, Low Frequency
(ETLF) inspection of the
left and right side fastener
holes common to
stringers 11 thru 22 and
the forward and aft skins
and do an Eddy Current,
High Frequency (ETHF)
inspection of the lower
skin at stringers 18 thru
20 for any crack in the
unrepaired area.(a)
-Before further flight.CONDITION 2.1 (AC-
TION 1): Contact The
Boeing Company for re-
pair instructions and do
the repair.
CONDITION 2.1: ANY
CRACK FOUND.
4,100 flight cycles.-CONDITION 2.1 (AC-
TION 2): Repeat Part 2:
Eddy Current, Low Fre-
quency (ETLF) inspection
of the left and right side
fastener holes common
to stringers 11 thru 22
and the forward and aft
skins and do an Eddy
Current, High Frequency
(ETHF) inspection of the
lower skin at stringers 18
thru 20 for any crack in
the unrepaired area.(a)
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PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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ALERTALERT

### Page 19

Group 1, Configuration 1, Option 1:
Table 1: Eddy Current, Low Frequency (ETLF) and Eddy Current, High Frequency (ETHF) Inspections
of stringers 11 thru 22 for initial inspection and repeat inspections.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
4,100 flight cycles.-Repeat Part 2: Eddy Cur-
rent, Low Frequency
(ETLF) inspection of the
left and right side fastener
holes common to
stringers 11 thru 22 and
the forward and aft skins
and do an Eddy Current,
High Frequency (ETHF)
inspection of the lower
skin at stringers 18 thru
20 for any crack in the
unrepaired area.(a)
CONDITION 2.2: NO
CRACK FOUND.
(a) It is not required to do the Eddy Current, Low Frequency ins pection and Eddy Current, High Frequency
inspection in this service bulletin in the areas where a repair covers the affected inspection area and the
repair meets any of the conditions that follow:
1. The repair is the corrective action to the crack condition id entified in MD80-57A244 Original Issue
and this Service Bulletin and was approved by the Boeing Organization Designation Authorization
(ODA) via a FAA Form 8100-9.
2. The installed repair was due to cracking as described in this  Service Bulletin and was approved
by the Boeing Organization Designation Authorization (ODA) via a FAA Form 8100-9.
Group 1, Configuration 1, Option 2:
Table 2: High Frequency (ETHF) inspection of stringers 15 thru 17 for initial inspection and Eddy Current,
Low Frequency (ETLF) and Eddy Current, High Frequency (ETHF) Inspections of stringers 11 thru 22
for repeat inspections.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 300 flight
cycles after the
effective date of
AD 2016-07-28
or within 5,400
flight cycles af-
ter the last de-
tailed inspection
done in accor-
dance with MPD
item 57-086-02,
whichever oc-
curs later.
Before 35,400
total flight cy-
cles.
Do Part 1: ETHF inspec-
tion for any crack in the
left side and right side
center wing lower skin.
Airplanes with less than
45,000 total flight cycles as
of the effective date of AD
2016-07-28.
Export Controlled ECCN: 9E991 - BOEING
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ALERTALERT

### Page 20

Group 1, Configuration 1, Option 2:
Table 2: High Frequency (ETHF) inspection of stringers 15 thru 17 for initial inspection and Eddy Current,
Low Frequency (ETLF) and Eddy Current, High Frequency (ETHF) Inspections of stringers 11 thru 22
for repeat inspections.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
--Within 150 flight
cycles after the
effective date of
AD 2016-07-28
or within 5,400
flight cycles af-
ter the last de-
tailed inspection
done in accor-
dance with MPD
item 57-086-02,
whichever oc-
curs later.
Do Part 1: ETHF inspec-
tion for any crack in the
left side and right side
center wing lower skin.
Airplanes with 45,000 or
more total flight cycles as
of the effective date of AD
2016-07-28.
-Before further flight.CONDITION 1 (ACTION
1): Contact The Boeing
Company for repair in-
structions and do the re-
pair.
CONDITION 1: ANY
CRACK FOUND.
-Before further flight.CONDITION 1 (ACTION
2): Do an internal general
visual inspection for any
cracks in the stringers
between Xcw=0.0 and
Xcw=20.0, stringers 11
thru 22.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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ALERTALERT

### Page 21

Group 1, Configuration 1, Option 2:
Table 2: High Frequency (ETHF) inspection of stringers 15 thru 17 for initial inspection and Eddy Current,
Low Frequency (ETLF) and Eddy Current, High Frequency (ETHF) Inspections of stringers 11 thru 22
for repeat inspections.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 1.1 (AC-
TION 1): Contact The
Boeing Company for re-
pair instructions and do
the repair.
CONDITION 1.1: ANY
CRACK FOUND.
-Within 2,000 flight cycles after Part
1; ETHF inspection for any crack
in the left side and right side cen-
ter wing lower skin.
CONDITION 1.1 (AC-
TION 2): Do Part 2: Eddy
Current, Low Frequency
(ETLF) inspection of the
left and right side fastener
holes common to
stringers 11 thru 22 and
the forward and aft skins
and do an Eddy Current,
High Frequency (ETHF)
inspection of the lower
skin at stringers 18 thru
20 for any crack.(a)
-Before further flight.CONDITION 1.1.1 (AC-
TION 1): Contact The
Boeing Company for re-
pair instructions and do
the repair.
CONDITION 1.1.1: ANY
CRACK FOUND.
4,100 flight cycles.-CONDITION 1.1.1 (AC-
TION 2): Repeat Part 2:
Eddy Current, Low Fre-
quency (ETLF) inspection
of the left and right side
fastener holes common
to stringers 11 thru 22
and the forward and aft
skins and do an Eddy
Current, High Frequency
(ETHF) inspection of the
lower skin at stringers 18
thru 20 for any crack.(a)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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ALERTALERT

### Page 22

Group 1, Configuration 1, Option 2:
Table 2: High Frequency (ETHF) inspection of stringers 15 thru 17 for initial inspection and Eddy Current,
Low Frequency (ETLF) and Eddy Current, High Frequency (ETHF) Inspections of stringers 11 thru 22
for repeat inspections.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
4,100 flight cycles.-Repeat Part 2: Eddy Cur-
rent, Low Frequency
(ETLF) inspection of the
left and right side fastener
holes common to
stringers 11 thru 22 and
the forward and aft skins
and do an Eddy Current,
High Frequency (ETHF)
inspection of the lower
skin at stringers 18 thru
20 for any crack.(a)
CONDITION 1.1.2: NO
CRACK FOUND.
-Within 2,000 flight cycles after Part
1; ETHF inspection for any crack
in the left side and right side cen-
ter wing lower skin.
Do Part 2: Eddy Current,
Low Frequency (ETLF)
inspection of the left and
right side fastener holes
common to stringers 11
thru 22 and the forward
and aft skins and do an
Eddy Current, High Fre-
quency (ETHF) inspec-
tion of the lower skin at
stringers 18 thru 20 for
any crack.(a)
CONDITION 1.2: NO
CRACK FOUND.
-Before further flight.CONDITION 1.2.1 (AC-
TION 1): Contact The
Boeing Company for re-
pair instructions and do
the repair.
CONDITION 1.2.1: ANY
CRACK FOUND.
4,100 flight cycles.-CONDITION 1.2.1 (AC-
TION 2): Repeat Part 2:
Eddy Current, Low Fre-
quency (ETLF) inspection
of the left and right side
fastener holes common
to stringers 11 thru 22
and the forward and aft
skins and do an Eddy
Current, High Frequency
(ETHF) inspection of the
lower skin at stringers 18
thru 20 for any crack.(a)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: March 03, 2016
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22 of 109
BOEING SERVICE BULLETIN MD80-57A244
ALERTALERT

### Page 23

Group 1, Configuration 1, Option 2:
Table 2: High Frequency (ETHF) inspection of stringers 15 thru 17 for initial inspection and Eddy Current,
Low Frequency (ETLF) and Eddy Current, High Frequency (ETHF) Inspections of stringers 11 thru 22
for repeat inspections.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
4,100 flight cycles.-Repeat Part 2: Eddy Cur-
rent, Low Frequency
(ETLF) inspection of the
left and right side fastener
holes common to
stringers 11 thru 22 and
the forward and aft skins
and do an Eddy Current,
High Frequency (ETHF)
inspection of the lower
skin at stringers 18 thru
20 for any crack.(a)
CONDITION 1.2.2: NO
CRACK FOUND.
-Within 2,000 flight cycles after Part
1; ETHF inspection for any crack
in the left side and right side cen-
ter wing lower skin.
Do Part 2: Eddy Current,
Low Frequency (ETLF)
inspection of the left and
right side fastener holes
common to stringers 11
thru 22 and the forward
and aft skins and do an
Eddy Current, High Fre-
quency (ETHF) inspec-
tion of the lower skin at
stringers 18 thru 20 for
any crack.
CONDITION 2: NO
CRACK FOUND.
-Before further flight.CONDITION 2.1 (AC-
TION 1): Contact The
Boeing Company for re-
pair instructions and do
the repair.
CONDITION 2.1: ANY
CRACK FOUND.
4,100 flight cycles.-CONDITION 2.1 (AC-
TION 2): Repeat Part 2:
Eddy Current, Low Fre-
quency (ETLF) inspection
of the left and right side
fastener holes common
to stringers 11 thru 22
and the forward and aft
skins and do an Eddy
Current, High Frequency
(ETHF) inspection of the
lower skin at stringers 18
thru 20 for any crack.(a)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: March 03, 2016
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ALERTALERT

### Page 24

Group 1, Configuration 1, Option 2:
Table 2: High Frequency (ETHF) inspection of stringers 15 thru 17 for initial inspection and Eddy Current,
Low Frequency (ETLF) and Eddy Current, High Frequency (ETHF) Inspections of stringers 11 thru 22
for repeat inspections.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
4,100 flight cycles.-Repeat Part 2: Eddy Cur-
rent, Low Frequency
(ETLF) inspection of the
left and right side fastener
holes common to
stringers 11 thru 22 and
the forward and aft skins
and do an Eddy Current,
High Frequency (ETHF)
inspection of the lower
skin at stringers 18 thru
20 for any crack.(a)
CONDITION 2.2: NO
CRACK FOUND.
(a) It is not required to do the Eddy Current, Low Frequency ins pection and Eddy Current, High Frequency
inspection in this service bulletin in the areas where a repair covers the affected inspection area and the
repair meets any of the conditions that follow:
1. The repair is the corrective action to the crack condition id entified in MD80-57A244 Original Issue
and this Service Bulletin and was approved by the Boeing Organization Designation Authorization
(ODA) via a FAA Form 8100-9.
2. The installed repair was due to cracking as described in this  Service Bulletin and was approved
by the Boeing Organization Designation Authorization (ODA) via a FAA Form 8100-9.
Group 1, Configuration 2, Option 1:
Table 3: Eddy Current, Low Frequency (ETLF) and Eddy Current, High Frequency (ETHF) Inspections
of stringers 11 thru 22 for initial inspection and repeat inspections.
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Within 2,000 flight cycles
after the most recent in-
spection done in accor-
dance with the Original Is-
sue of this Service Bulletin.
Do a general visual inspection for exist-
ing external lower skin repairs between
Xcw=0.0 and Xcw=20.0, stringers 11
thru 22.
All Airplanes.
-Before further flight.Do Part 2: Eddy Current, Low Frequency
(ETLF) inspection of the left and right
side fastener holes common to stringers
11 thru 22 and the forward and aft skins
and do an Eddy Current, High Frequen-
cy (ETHF) inspection of the lower skin
at stringers 18 thru 20 for any crack.
CONDITION 1: NO
REPAIR FOUND.
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Work - See page 1 for details.
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ALERTALERT

### Page 25

Group 1, Configuration 2, Option 1:
Table 3: Eddy Current, Low Frequency (ETLF) and Eddy Current, High Frequency (ETHF) Inspections
of stringers 11 thru 22 for initial inspection and repeat inspections.
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Before further flight.CONDITION 1.1 (ACTION 1): Contact
The Boeing Company for repair instruc-
tions and do the repair.
CONDITION 1.1:
ANY CRACK
FOUND.
4,100 flight cycles.-CONDITION 1.1 (ACTION 2): Repeat
Part 2: Eddy Current, Low Frequency
(ETLF) inspection of the left and right
side fastener holes common to stringers
11 thru 22 and the forward and aft skins
and do an Eddy Current, High Frequen-
cy (ETHF) inspection of the lower skin
at stringers 18 thru 20 for any crack in
the unrepaired area.(a)
4,100 flight cycles.-Repeat Part 2: Eddy Current, Low Fre-
quency (ETLF) inspection of the left and
right side fastener holes common to
stringers 11 thru 22 and the forward and
aft skins and do an Eddy Current, High
Frequency (ETHF) inspection of the
lower skin at stringers 18 thru 20 for any
crack.(a)
CONDITION 1.2:
NO CRACK
FOUND.
-Before further flight.CONDITION 2 (ACTION 1): Contact The
Boeing Company for alternative inspec-
tion(s), incorporate the inspection(s) re-
quirements into the maintenance pro-
gram and do the inspection(s) at the
times specified by Boeing.
CONDITION 2: ANY
EXISTING REPAIR
FOUND.
-Before further flight.CONDITION 2 (ACTION 2): Do Part 2:
Eddy Current, Low Frequency (ETLF)
inspection of the left and right side fas-
tener holes common to stringers 11 thru
22 and the forward and aft skins and do
an Eddy Current, High Frequency
(ETHF) inspection of the lower skin at
stringers 18 thru 20 for any crack in the
unrepaired area.(a)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: March 03, 2016
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25 of 109
BOEING SERVICE BULLETIN MD80-57A244
ALERTALERT

### Page 26

Group 1, Configuration 2, Option 1:
Table 3: Eddy Current, Low Frequency (ETLF) and Eddy Current, High Frequency (ETHF) Inspections
of stringers 11 thru 22 for initial inspection and repeat inspections.
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Before further flight.CONDITION 2.1 (ACTION 1): Contact
The Boeing Company for repair instruc-
tions and do the repair.
CONDITION 2.1:
ANY CRACK
FOUND.
4,100 flight cycles.-CONDITION 2.1 (ACTION 2): Repeat
Part 2: Eddy Current, Low Frequency
(ETLF) inspection of the left and right
side fastener holes common to stringers
11 thru 22 and the forward and aft skins
and do an Eddy Current, High Frequen-
cy (ETHF) inspection of the lower skin
at stringers 18 thru 20 for any crack in
the unrepaired area.(a)
4,100 flight cycles.-Repeat Part 2: Eddy Current, Low Fre-
quency (ETLF) inspection of the left and
right side fastener holes common to
stringers 11 thru 22 and the forward and
aft skins and do an Eddy Current, High
Frequency (ETHF) inspection of the
lower skin at stringers 18 thru 20 for any
crack in the unrepaired area.(a)
CONDITION 2.2:
NO CRACK
FOUND.
(a) It is not required to do the Eddy Current, Low Frequency ins pection and Eddy Current, High Frequency
inspection in this service bulletin in the areas where a repair covers the affected inspection area and the
repair meets any of the conditions that follow:
1. The repair is the corrective action to the crack condition id entified in MD80-57A244 Original Issue
and this Service Bulletin and was approved by the Boeing Organization Designation Authorization
(ODA) via a FAA Form 8100-9.
2. The installed repair was due to cracking as described in this  Service Bulletin and was approved
by the Boeing Organization Designation Authorization (ODA) via a FAA Form 8100-9.
Group 1, Configuration 2, Option 2:
Table 4: High Frequency (ETHF) inspection of stringers 15 thru 17 for initial inspection and Eddy Current,
Low Frequency (ETLF) and Eddy Current, High Frequency (ETHF) Inspections of stringers 11 thru 22
for repeat inspections.
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Within 2,000 flight cycles
after the most recent in-
spection done in accor-
dance with the Original Is-
sue of this Service Bulletin.
Do a general visual inspection for exist-
ing external lower skin repairs between
Xcw=0.0 and Xcw=20.0, stringers 15
thru 17.
All Airplanes.
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ALERTALERT

### Page 27

Group 1, Configuration 2, Option 2:
Table 4: High Frequency (ETHF) inspection of stringers 15 thru 17 for initial inspection and Eddy Current,
Low Frequency (ETLF) and Eddy Current, High Frequency (ETHF) Inspections of stringers 11 thru 22
for repeat inspections.
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Within 2,000 flight cycles
after the most recent in-
spection done in accor-
dance with the Original Is-
sue of this Service Bulletin.
Do Part 1: ETHF inspection for any crack
in the left side and right side center wing
lower skin.
CONDITION 1: NO
REPAIR FOUND.
-Before further flight.CONDITION 1.1 (ACTION 1): Contact
The Boeing Company for repair instruc-
tions and do the repair.
CONDITION 1.1:
ANY CRACK
FOUND.
-Before further flight.CONDITION 1.1 (ACTION 2): Do an in-
ternal general visual inspection for any
cracks in the stringers between Xcw=0.0
and Xcw=20.0, stringers 11 thru 22.
-Before further flight.CONDITION 1.1.1 (ACTION 1): Contact
The Boeing Company for repair instruc-
tions and do the repair.
CONDITION 1.1.1:
ANY CRACK
FOUND.
-Within 2,000 flight cycles
after the repair.
CONDITION 1.1.1 (ACTION 2): Do Part
2: Eddy Current, Low Frequency (ETLF)
inspection of the left and right side fas-
tener holes common to stringers 11 thru
22 and the forward and aft skins and do
an Eddy Current, High Frequency
(ETHF) inspection of the lower skin at
stringers 18 thru 20 for any crack in the
unrepaired area.(a)
-Before further flight.CONDITION 1.1.1.1 (ACTION 1): Con-
tact The Boeing Company for repair in-
structions and do the repair.
CONDITION
1.1.1.1: ANY
CRACK FOUND.
4,100 flight cycles.-CONDITION 1.1.1.1 (ACTION 2): Re-
peat Part 2: Eddy Current, Low Frequen-
cy (ETLF) inspection of the left and right
side fastener holes common to stringers
11 thru 22 and the forward and aft skins
and do an Eddy Current, High Frequen-
cy (ETHF) inspection of the lower skin
at stringers 18 thru 20 for any crack in
the unrepaired area.(a)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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MD80-57A244Revision 1: October 01, 2019
27 of 109
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ALERTALERT

### Page 28

Group 1, Configuration 2, Option 2:
Table 4: High Frequency (ETHF) inspection of stringers 15 thru 17 for initial inspection and Eddy Current,
Low Frequency (ETLF) and Eddy Current, High Frequency (ETHF) Inspections of stringers 11 thru 22
for repeat inspections.
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
4,100 flight cycles.-Repeat Part 2: Eddy Current, Low Fre-
quency (ETLF) inspection of the left and
right side fastener holes common to
stringers 11 thru 22 and the forward and
aft skins and do an Eddy Current, High
Frequency (ETHF) inspection of the
lower skin at stringers 18 thru 20 for any
crack in the unrepaired area.(a)
CONDITION
1.1.1.2: NO CRACK
FOUND.
-Within 2,000 flight cycles
after Part 1: ETHF inspec-
tion for any crack in the left
side and right side center
wing lower skin.
Do Part 2: Eddy Current, Low Frequency
(ETLF) inspection of the left and right
side fastener holes common to stringers
11 thru 22 and the forward and aft skins
and do an Eddy Current, High Frequen-
cy (ETHF) inspection of the lower skin
at stringers 18 thru 20 for any crack in
the unrepaired area.(a)
CONDITION 1.1.2:
NO CRACK
FOUND.
-Before further flight.CONDITION 1.1.2.1 (ACTION 1): Con-
tact The Boeing Company for repair in-
structions and do the repair.
CONDITION
1.1.2.1: ANY
CRACK FOUND.
4,100 flight cycles.-CONDITION 1.1.2.1 (ACTION 2): Re-
peat Part 2: Eddy Current, Low Frequen-
cy (ETLF) inspection of the left and right
side fastener holes common to stringers
11 thru 22 and the forward and aft skins
and do an Eddy Current, High Frequen-
cy (ETHF) inspection of the lower skin
at stringers 18 thru 20 for any crack in
the unrepaired area.(a)
4,100 flight cycles.-Repeat Part 2: Eddy Current, Low Fre-
quency (ETLF) inspection of the left and
right side fastener holes common to
stringers 11 thru 22 and the forward and
aft skins and do an Eddy Current, High
Frequency (ETHF) inspection of the
lower skin at stringers 18 thru 20 for any
crack in the unrepaired area.(a)
CONDITION
1.1.2.2: NO CRACK
FOUND.
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Group 1, Configuration 2, Option 2:
Table 4: High Frequency (ETHF) inspection of stringers 15 thru 17 for initial inspection and Eddy Current,
Low Frequency (ETLF) and Eddy Current, High Frequency (ETHF) Inspections of stringers 11 thru 22
for repeat inspections.
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Within 2,000 flight cycles
after Part 1: ETHF inspec-
tion for any crack in the left
side and right side center
wing lower skin.
Do Part 2: Eddy Current, Low Frequency
(ETLF) inspection of the left and right
side fastener holes common to stringers
11 thru 22 and the forward and aft skins
and do an Eddy Current, High Frequen-
cy (ETHF) inspection of the lower skin
at stringers 18 thru 20 for any crack.
CONDITION 1.2:
NO CRACK
FOUND.
-Before further flight.CONDITION 1.2.1 (ACTION 1): Contact
The Boeing Company for repair instruc-
tions and do the repair.
CONDITION 1.2.1:
ANY CRACK
FOUND.
4,100 flight cycles.-CONDITION 1.2.1 (ACTION 2): Repeat
Part 2: Eddy Current, Low Frequency
(ETLF) inspection of the left and right
side fastener holes common to stringers
11 thru 22 and the forward and aft skins
and do an Eddy Current, High Frequen-
cy (ETHF) inspection of the lower skin
at stringers 18 thru 20 for any crack in
the unrepaired area.(a)
4,100 flight cycles.-Repeat Part 2: Eddy Current, Low Fre-
quency (ETLF) inspection of the left and
right side fastener holes common to
stringers 11 thru 22 and the forward and
aft skins and do an Eddy Current, High
Frequency (ETHF) inspection of the
lower skin at stringers 18 thru 20 for any
crack in the unrepaired area.(a)
CONDITION 1.2.2:
NO CRACK
FOUND.
-Before further flight.CONDITION 2 (ACTION 1): Contact The
Boeing Company for alternative inspec-
tion(s), incorporate the inspection(s) re-
quirements into the maintenance pro-
gram and do the inspection(s) at the
times specified by Boeing.
CONDITION 2: ANY
EXISTING REPAIR
FOUND.
-Within 2,000 flight cycles
after the most recent in-
spection done in accor-
dance with the Original Is-
sue of this Service Bulletin.
CONDITION 2 (ACTION 2): Do Part 1:
ETHF inspection for any crack in the left
side and right side center wing lower
skin in the unrepaired area.(a)
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### Page 30

Group 1, Configuration 2, Option 2:
Table 4: High Frequency (ETHF) inspection of stringers 15 thru 17 for initial inspection and Eddy Current,
Low Frequency (ETLF) and Eddy Current, High Frequency (ETHF) Inspections of stringers 11 thru 22
for repeat inspections.
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Before further flight.CONDITION 2.1 (ACTION 1): Contact
The Boeing Company for repair instruc-
tions and do the repair.
CONDITION 2.1:
ANY CRACK
FOUND.
-Before further flight.CONDITION 2.1 (ACTION 2): Do an in-
ternal general visual inspection for any
cracks in the stringers between Xcw=0.0
and Xcw=20.0, stringers 11 thru 22.
-Before further flight.CONDITION 2.1.1 (ACTION 1): Contact
The Boeing Company for repair instruc-
tions and do the repair
CONDITION 2.1.1:
ANY CRACK
FOUND.
-Within 2,000 flight cycles
after Part 1: ETHF inspec-
tion for any crack in the left
side and right side center
wing lower skin.
CONDITION 2.1.1 (ACTION 2): Do Part
2: Eddy Current, Low Frequency (ETLF)
inspection of the left and right side fas-
tener holes common to stringers 11 thru
22 and the forward and aft skins and do
an Eddy Current, High Frequency
(ETHF) inspection of the lower skin at
stringers 18 thru 20 for any crack in the
unrepaired area.(a)
-Before further flight.CONDITION 2.1.1.1 (ACTION 1): Con-
tact The Boeing Company for repair in-
structions and do the repair
CONDITION
2.1.1.1: ANY
CRACK FOUND.
4,100 flight cycles.-CONDITION 2.1.1.1 (ACTION 2): Re-
peat Part 2: Eddy Current, Low Frequen-
cy (ETLF) inspection of the left and right
side fastener holes common to stringers
11 thru 22 and the forward and aft skins
and do an Eddy Current, High Frequen-
cy (ETHF) inspection of the lower skin
at stringers 18 thru 20 for any crack in
the unrepaired area.(a)
4,100 flight cycles.-Repeat Part 2: Eddy Current, Low Fre-
quency (ETLF) inspection of the left and
right side fastener holes common to
stringers 11 thru 22 and the forward and
aft skins and do an Eddy Current, High
Frequency (ETHF) inspection of the
lower skin at stringers 18 thru 20 for any
crack in the unrepaired area.(a)
CONDITION
2.1.1.2: NO CRACK
FOUND.
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### Page 31

Group 1, Configuration 2, Option 2:
Table 4: High Frequency (ETHF) inspection of stringers 15 thru 17 for initial inspection and Eddy Current,
Low Frequency (ETLF) and Eddy Current, High Frequency (ETHF) Inspections of stringers 11 thru 22
for repeat inspections.
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Within 2,000 flight cycles
after Part 1: ETHF inspec-
tion for any crack in the left
side and right side center
wing lower skin.
Do Part 2: Eddy Current, Low Frequency
(ETLF) inspection of the left and right
side fastener holes common to stringers
11 thru 22 and the forward and aft skins
and do an Eddy Current, High Frequen-
cy (ETHF) inspection of the lower skin
at stringers 18 thru 20 for any crack in
the unrepaired area.(a)
CONDITION 2.1.2:
NO CRACK
FOUND.
-Before further flight.CONDITION 2.1.2.1 (ACTION 1): Con-
tact The Boeing Company for repair in-
structions and do the repair
CONDITION
2.1.2.1: ANY
CRACK FOUND.
4,100 flight cycles.-CONDITION 2.1.2.1 (ACTION 2): Re-
peat Part 2: Eddy Current, Low Frequen-
cy (ETLF) inspection of the left and right
side fastener holes common to stringers
11 thru 22 and the forward and aft skins
and do an Eddy Current, High Frequen-
cy (ETHF) inspection of the lower skin
at stringers 18 thru 20 for any crack in
the unrepaired area.(a)
4,100 flight cycles.-Repeat Part 2: Eddy Current, Low Fre-
quency (ETLF) inspection of the left and
right side fastener holes common to
stringers 11 thru 22 and the forward and
aft skins and do an Eddy Current, High
Frequency (ETHF) inspection of the
lower skin at stringers 18 thru 20 for any
crack in the unrepaired area.(a)
CONDITION
2.1.2.2: NO CRACK
FOUND.
-Within 2,000 flight cycles
after Part 1: ETHF inspec-
tion for any crack in the left
side and right side center
wing lower skin.
Do Part 2: Eddy Current, Low Frequency
(ETLF) inspection of the left and right
side fastener holes common to stringers
11 thru 22 and the forward and aft skins
and do an Eddy Current, High Frequen-
cy (ETHF) inspection of the lower skin
at stringers 18 thru 20 for any crack in
the unrepaired area.(a)
CONDITION 2.2:
NO CRACK
FOUND.
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### Page 32

Group 1, Configuration 2, Option 2:
Table 4: High Frequency (ETHF) inspection of stringers 15 thru 17 for initial inspection and Eddy Current,
Low Frequency (ETLF) and Eddy Current, High Frequency (ETHF) Inspections of stringers 11 thru 22
for repeat inspections.
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Before further flight.CONDITION 2.2.1 (ACTION 1): Contact
The Boeing Company for repair instruc-
tions and do the repair.
CONDITION 2.2.1:
ANY CRACK
FOUND.
4,100 flight cycles.-CONDITION 2.2.1 (ACTION 2): Repeat
Part 2: Eddy Current, Low Frequency
(ETLF) inspection of the left and right
side fastener holes common to stringers
11 thru 22 and the forward and aft skins
and do an Eddy Current, High Frequen-
cy (ETHF) inspection of the lower skin
at stringers 18 thru 20 for any crack in
the unrepaired area.(a)
4,100 flight cycles.-Repeat Part 2: Eddy Current, Low Fre-
quency (ETLF) inspection of the left and
right side fastener holes common to
stringers 11 thru 22 and the forward and
aft skins and do an Eddy Current, High
Frequency (ETHF) inspection of the
lower skin at stringers 18 thru 20 for any
crack in the unrepaired area.(a)
CONDITION 2.2.2:
NO CRACK
FOUND.
(a) It is not required to do the Eddy Current, Low Frequency ins pection and Eddy Current, High Frequency
inspection in this service bulletin in the areas where a repair covers the affected inspection area and the
repair meets any of the conditions that follow:
1. The repair is the corrective action to the crack condition id entified in MD80-57A244 Original Issue
and this Service Bulletin and was approved by the Boeing Organization Designation Authorization
(ODA) via a FAA Form 8100-9.
2. The installed repair was due to cracking as described in this  Service Bulletin and was approved
by the Boeing Organization Designation Authorization (ODA) via a FAA Form 8100-9.
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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In addition, the Manager of the FAA Los Angeles ACO Branch approves the inspection and repair
defined in this service bulletin revision as an alternative method of compliance to the requirements of
paragraph (g), (h)(1) and (h)(2) of AD 2016-07-28. All provisions of AD 2016-07-28 that are not
specifically referenced in the above statement remain fully applicable and must be complied with
accordingly.
G. Manpower
The table below shows an estimate of the task hours necessary to do this inspection for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
• Time to adjust to the workplace
• Time to schedule the work
• Time to inspect the work
• Time to cure the materials
• Time to make the parts
• Time to find the tools
Elapsed HoursTask HoursNumber of PersonsTask
2.04.02Figure 1
0.51.02Figure 2
1.02.02Figure 3
2.04.02Figure 4
0.51.02Figure 5
1.02.02Figure 6
8.016.02Figure 7
5.010.02Figure 8
4.08.02Figure 9
(a)(a)TOTAL FOR EACH AIRPLANE
(a) The total task hours and elapsed hours are not given as the work necessary
is variable.
H. Weight and Balance Changes
Weight and Balance changes affected by incorporation of this service bulletin are dependent on the
inspection, number of flight cycles, condition, type, number and location of repairs done on each
particular airplane. Weight and Balance are to be calculated by the operator by weighing parts installed
or removed. Operators should make necessary revisions to the appropriate weight and balance report.
I. Electrical Load Data
Not changed.
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### Page 34

J. References
1. Existing Data:
a. Non-Destructive Test Standard Practices Manual (NDTSPM) Part 06 Eddy Current:
06-10-01.001
b. Standard Overhaul Practices Manual (SOPM) 20-50-01
c. MD-80 Structural Repair Manual (SRM) 51-20-00, 51-30
d. MD-80 Maintenance Planning Document (MPD) item 57-086-02
e. Federal Aviation Administration (FAA) Airworthiness Directive  (AD) 2016-07-28
f. MD80 Aircraft Maintenance Manual (AMM) 06-22-00
2. Data Supplied with this Service Bulletin:
a. Drawings:
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### Page 35

ADCNDCN/REVSheetTypeTitleDrawing No
-B1.0DWGINSPECTION - LOWER WING
STRINGERS
SN09570007
--10.0DWG
--11.0DWG
--12.0DWG
--12.1DWG
-A13.0DWG
--13.1DWG
--14.0DWG
-B14.1DWG
--15.0DWG
--16.0DWG
--17.0DWG
--17.1DWG
-A18.0DWG
-A18.1DWG
--19.0DWG
-B2.0DWG
-B2.1DWG
--20.0DWG
-A21.0DWG
--22.0DWG
--23.0DWG
-A24.0DWG
--25.0DWG
--26.0DWG
--27.0DWG
--28.0DWG
--29.0DWG
--3.0DWG
--30.0DWG
-B31.0DWG
--32.0DWG
--33.0DWG
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ADCNDCN/REVSheetTypeTitleDrawing No
DWG - -34.0
--35.0DWG
--36.0DWG
--37.0DWG
--38.0DWG
-B4.0DWG
-B5.0DWG
--6.0DWG
-A6.1DWG
-B7.0DWG
--7.1DWG
--7.2DWG
--7.3DWG
--8.0DWG
-B9.0DWG
3. Installation Drawings Used in the Preparation of this Service  Bulletin:
None.
K. Publications Affected
1. Publications:
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 but no new DTIs are necessary.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
M. Software Accomplishment Summary
Not affected.
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### Page 37

2.    MATERIAL INFORMATION
A. Material - Price and Availability
The operator can supply the parts and materials shown in Paragraph 2.C., Parts Necessary for Each
Airplane. As an alternative, operators can purchase the parts from Boeing Spares. This service bulletin
does not show the Boeing price and supply data.
B. Industry Support Information
Boeing warranty remedies are not available for the inspection given in this service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts
None.
2. Parts and Materials Supplied by the Operator
The following parts or materials are necessary to do the change in this service bulletin. Parts and
materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine
operator part and material supply to make sure all necessary parts and materials are available.
NotesNameQTYPart Number / Specification
(a)(d)Sealant16 oz.PR-1828
(b)(c)(d)Sealant16 oz.DMS 1819
(a) This sealant has a dark color and a shorter curing time than  DMS 1819 sealant.
(b) This is an aluminized sealant with a longer curing time than PR-1828 sealant. It may be used as an alter-
native to PR-1828 sealant.
(c) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data.
(d) Sealant can be purchased from Aviall. Aviall (Cage 22819), 2 750 Regent Boulevard, Dallas, Texas
75261Contact Information: Email: Supplier_Services@Aviall.com, Attention: Product Line Manager,
Telephone:1-800-Aviall-1 or 972-586-1000, Website: http://www.aviall.com
3. Parts Modified and Reidentified
None.
4. Parts Removed and Not Replaced
None.
D. Parts Necessary to Change Spares
None.
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E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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### Page 39

3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
IF ELECTRICAL POWER IS APPLIED TO THE AIRPLANE, MAKE SURE YOU
OBEY ALL PRECAUTIONS WHILE YOU DO WORK. IF YOU DO NOT OBEY THE
PRECAUTIONS, DEATH OR INJURY TO PERSONS, AND DAMAGE TO THE
AIRPLANE CAN OCCUR.WARNING
ELECTRICALLY GROUND THE AIRPLANE. THIS WILL HELP TO PREVENT
DAMAGE TO THE AIRPLANE OR EQUIPMENT.CAUTION
KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF
METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED
MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE
BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES
CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE.
CAUTION
NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph  1.J., References, for
definition of the acronyms.
2. Equivalent parts are listed in the AEPL, Drawing 7595071.
3. Use the approved fastener and process material substitutions,  in accordance with
MD-80 SRM 51-30.
4. If the length of any fastener specified in this service bulle tin does not meet installation
standards given in Structural Repair Manual (SRM) Chapter 51, then a fastener of
the same specification, or an approved substitute, with a length which meets the
installation standards given in SRM Chapter 51 may be used. In addition, washers
may be installed for fastener grip length in accordance with SRM Chapter 51. Refer
to SOPM 20-50-01 for alternate full threaded fasteners (screws) needed for installation
in this service bulletin.
5. A 1/8-inch thick stack of the same type washers called for in  this service bulletin is
the maximum thickness which may be used under fastener head or nut to counteract
accumulation of tolerances.
EXCEPTION: When the available fastener length increments are greater than
1/16-inch, a 3/16-inch thick stack of the same type washers may be used.
6. Unless shown differently, these dimensions and tolerances are  used:
– Linear dimensions are in inches
– Tolerance on linear dimensions, other than rivet and bolt edge  margins, is plus
or minus 0.03 inch.
– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch
– Angular tolerance is plus or minus 2 degrees
– Hole dimensions for standard solid rivets are in MD-80 SRM 51- 30
– Torque Values:
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— Values for structural fasteners are given in MD-80 Structural Repair Manual,
Chapter 51.
— Values for airframe maintenance tasks are included in Chapter 20 of MD-80
Aircraft Maintenance Manual (AMM).
— Values for electrical maintenance tasks are included in Chapte r 20 of
Standard Wiring Practices Manual (SWPM).
— Values for engine maintenance tasks are included in Chapter 70  of MD-80
Aircraft Maintenance Manual (AMM).
— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
7. Obey all of the warnings and cautions given in the specified manual sections.
8. These work instructions refer to procedures included in other  Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "in
accordance with" are included in the instruction, the procedure in the Boeing document
must be used.
9. If it is necessary to remove more parts for access, you can r emove those parts. If
you can get access without removing identified parts, it is not necessary to remove
all of the identified parts. Jacking and shoring limitations must be observed.
10. Where the work instructions include installation of a kept p art, a new or serviceable
part with the same part number can be installed as an alternative to the kept part.
11. Use of colors in Figures is based on guidance from the ATA e -Business Program
(ATA) iSpec 2200.
12. The compliance times for the actions in Paragraph 3.B., WORK  INSTRUCTIONS
are in Paragraph 1.E., Compliance.
13. Some steps in the Work Instructions are labeled as Required for Compliance (RC).
If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps
labeled as RC, including sub-steps under an RC step and any figures identified in
an RC step, must be done to comply with the AD. An Alternative Method of
Compliance (AMOC) is required for any deviations to RC steps, including sub-steps
and identified figures. Steps not labeled as RC may be deviated from using accepted
methods in accordance with the operator's maintenance or inspection program without
obtaining approval of an AMOC. This is provided that the RC steps, including
sub-steps and identified figures, can still be done as specified, and the airplane can
be put back in an airworthy condition.
14. Refer to APPENDIX A, APPENDIX B, APPENDIX C and APPENDIX D f or logic
diagrams. Logic diagrams are provided as an aid only. Information contained in
Paragraph 1.E., Compliance is the primary source for compliance times. Information
in Paragraph 3.B., Work Instructions is the primary source for tasks required for
compliance.
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### Page 41

B. WORK INSTRUCTIONS
Group 1, Configuration 1:
Option 1:
1. Remove and keep left and right wing/fuselage fillet panels, r efer to FIGURE 7 to get access to the
inspection area.
2. RC - Do a general visual inspection for existing external low er skin repairs between Xcw=0.0 and
Xcw=20.0, stringers 11 thru 22.
PART 2: Eddy Current, Low Frequency (ETLF) inspection of the left and right side wing
fastener holes common to stringers 11 thru 22 and the forward and aft skins and do an
Eddy Current, High Frequency (ETHF) inspection of the lower skin at stringers 18 thru 20
for any crack.
a. CONDITION 1: NO REPAIR FOUND.
(1) Do Eddy Current, Low Frequency (ETLF) inspection of the left and right side wing fastener
holes common to stringers 11 thru 22 and the forward and aft skins and do an Eddy
Current, High Frequency (ETHF) inspection of the lower skin at stringers 18 thru 20 for
any crack in accordance with FIGURE 8.
(a) CONDITION 1.1: ANY CRACK FOUND.
1) CONDITION 1.1 (ACTION 1): Contact The Boeing Company for repa ir
instructions and do the repair.
2) CONDITION 1.1 (ACTION 2): Repeat Eddy Current, Low Frequency (ETLF)
inspection of the left and right side wing fastener holes common to stringers 11
thru 22 and the forward and aft skins and do an Eddy Current, High Frequency
(ETHF) inspection of the lower skin at stringers 18 thru 20 for any crack in the
unrepaired area in accordance with FIGURE 8.
NOTE: It is not required to do the Eddy Current, Low Frequency inspection
and Eddy Current, High Frequency inspection in this service bulletin
in the areas where a repair covers the affected inspection area and the
repair meets any of the conditions that follow:
1. The repair is the corrective action to the crack condition
identified in MD80-57A244 Original Issue and this Service
Bulletin and was approved by the Boeing Organization
Designation Authorization (ODA) via a FAA Form 8100-9.
2. The installed repair was due to cracking as described in this
Service Bulletin and was approved by the Boeing Organization
Designation Authorization (ODA) via a FAA Form 8100-9.
(b) CONDITION 1.2: NO CRACK FOUND.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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BOEING SERVICE BULLETIN MD80-57A244
ALERTALERT

### Page 42

1) Repeat Part 2: Eddy Current, Low Frequency (ETLF) inspection of the left and
right side wing fastener holes common to stringers 11 thru 22 and the forward
and aft skins and do an Eddy Current, High Frequency (ETHF) inspection of the
lower skin at stringers 18 thru 20 for any crack in accordance with FIGURE 8.
NOTE: It is not required to do the Eddy Current, Low Frequency inspection
and Eddy Current, High Frequency inspection in this service bulletin
in the areas where a repair covers the affected inspection area and the
repair meets any of the conditions that follow:
1. The repair is the corrective action to the crack condition
identified in MD80-57A244 Original Issue and this Service
Bulletin and was approved by the Boeing Organization
Designation Authorization (ODA) via a FAA Form 8100-9.
2. The installed repair was due to cracking as described in this
Service Bulletin and was approved by the Boeing Organization
Designation Authorization (ODA) via a FAA Form 8100-9.
b. CONDITION 2: ANY EXISTING REPAIR FOUND.
(1) CONDITION 2 (ACTION 1): Contact The Boeing Company for alter native inspection(s),
incorporate the inspection(s) requirements into the maintenance program and do the
inspection(s) at the times specified by Boeing.
(2) CONDITION 2 (ACTION 2): Do Eddy Current, Low Frequency (ETLF ) inspection of the
left and right side wing fastener holes common to stringers 11 thru 22 and the forward
and aft skins and do an Eddy Current, High Frequency (ETHF) inspection of the lower
skin at stringers 18 thru 20 for any crack in the unrepaired area in accordance with FIGURE
8.
NOTE: It is not required to do the Eddy Current, Low Frequency inspection and Eddy
Current, High Frequency inspection in this service bulletin in the areas where a
repair covers the affected inspection area and the repair meets any of the
conditions that follow:
1. The repair is the corrective action to the crack condition id entified in
MD80-57A244 Original Issue and this Service Bulletin and was
approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
2. The installed repair was due to cracking as described in this  Service
Bulletin and was approved by the Boeing Organization Designation
Authorization (ODA) via a FAA Form 8100-9.
(a) CONDITION 2.1: ANY CRACK FOUND.
1) CONDITION 2.1 (ACTION 1): Contact The Boeing Company for repa ir
instructions and do the repair.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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BOEING SERVICE BULLETIN MD80-57A244
ALERTALERT

### Page 43

2) CONDITION 2.1 (ACTION 2): Repeat Eddy Current, Low Frequency (ETLF)
inspection of the left and right side wing fastener holes common to stringers 11
thru 22 and the forward and aft skins and do an Eddy Current, High Frequency
(ETHF) inspection of the lower skin at stringers 18 thru 20 for any crack in the
unrepaired area in accordance with FIGURE 8.
NOTE: It is not required to do the Eddy Current, Low Frequency inspection
and Eddy Current, High Frequency inspection in this service bulletin
in the areas where a repair covers the affected inspection area and the
repair meets any of the conditions that follow:
1. The repair is the corrective action to the crack condition
identified in MD80-57A244 Original Issue and this Service
Bulletin and was approved by the Boeing Organization
Designation Authorization (ODA) via a FAA Form 8100-9.
2. The installed repair was due to cracking as described in this
Service Bulletin and was approved by the Boeing Organization
Designation Authorization (ODA) via a FAA Form 8100-9.
(b) CONDITION 2.2: NO CRACK FOUND.
1) Repeat Part 2: Eddy Current, Low Frequency (ETLF) inspection of the left and
right side wing fastener holes common to stringers 11 thru 22 and the forward
and aft skins and do an Eddy Current, High Frequency (ETHF) inspection of the
lower skin at stringers 18 thru 20 for any crack in the unrepaired area in
accordance with FIGURE 8.
NOTE: It is not required to do the Eddy Current, Low Frequency inspection
and Eddy Current, High Frequency inspection in this service bulletin
in the areas where a repair covers the affected inspection area and the
repair meets any of the conditions that follow:
1. The repair is the corrective action to the crack condition
identified in MD80-57A244 Original Issue and this Service
Bulletin and was approved by the Boeing Organization
Designation Authorization (ODA) via a FAA Form 8100-9.
2. The installed repair was due to cracking as described in this
Service Bulletin and was approved by the Boeing Organization
Designation Authorization (ODA) via a FAA Form 8100-9.
3. Install the kept wing/fuselage fillet panels, refer to FIGURE  9 to close access.
4. Put the airplane back to a serviceable condition.
Group 1, Configuration 1:
Option 2:
1. Remove left wing/fuselage fillet panel 2110C in accordance wi th FIGURE 1 to get access to the
inspection area on the left side of the airplane.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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BOEING SERVICE BULLETIN MD80-57A244
ALERTALERT

### Page 44

2. Remove the right wing/fuselage fillet panel 2210C in accordan ce with FIGURE 4 to get access to
the inspection area on the right side of the airplane.
PART 1: Eddy Current, High Frequency (ETHF) inspection for any crack in the left side and
right side center wing lower skin.
a. RC - Do an Eddy Current, High Frequency (ETHF) inspection for  any crack in the left side
and right side center wing lower skin in accordance with FIGURE 2 and FIGURE 5.
(1) CONDITION 1: ANY CRACK FOUND.
(a) CONDITION 1 (ACTION 1): Contact The Boeing Company for repai r instructions
and do the repair.
(b) CONDITION 1 (ACTION 2): Do an internal general visual inspec tion for any cracks
in the stringers between Xcw=0.0 and Xcw=20.0, stringers 11 thru 22.
1) CONDITION 1.1: ANY CRACK FOUND.
a) CONDITION 1.1 (ACTION 1): Contact The Boeing Company for repa ir
instructions and do the repair.
b) CONDITION 1.1 (ACTION 2): Do Part 2: Eddy Current, Low Freque ncy
(ETLF) inspection of the left and right side wing fastener holes common to
stringers 11 thru 22 and the forward and aft skins and do an Eddy Current,
High Frequency (ETHF) inspection of the lower skin at stringers 18 thru 20
for any crack in accordance with FIGURE 8.
NOTE: It is not required to do the Eddy Current, Low Frequency inspection
and Eddy Current, High Frequency inspection in this service bulletin
in the areas where a repair covers the affected inspection area
and the repair meets any of the conditions that follow:
1. The repair is the corrective action to the crack condition
identified in MD80-57A244 Original Issue and this Service
Bulletin and was approved by the Boeing Organization
Designation Authorization (ODA) via a FAA Form 8100-9.
2. The installed repair was due to cracking as described in
this Service Bulletin and was approved by the Boeing
Organization Designation Authorization (ODA) via a FAA
Form 8100-9.
{1} CONDITION 1.1.1: ANY CRACK FOUND.
– CONDITION 1.1.1 (ACTION 1): Contact The Boeing Company for
repair instructions and do the repair.
– CONDITION 1.1.1 (ACTION 2): Repeat Part 2: Eddy Current, Low
Frequency (ETLF) inspection of the left and right side wing fastener
holes common to stringers 11 thru 22 and the forward and aft skins
and do an Eddy Current, High Frequency (ETHF) inspection of
the lower skin at stringers 18 thru 20 for any crack in accordance
with FIGURE 8.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: March 03, 2016
MD80-57A244Revision 1: October 01, 2019
44 of 109
BOEING SERVICE BULLETIN MD80-57A244
ALERTALERT

### Page 45

NOTE: It is not required to do the Eddy Current, Low Frequency
inspection and Eddy Current, High Frequency inspection
in this service bulletin in the areas where a repair covers
the affected inspection area and the repair meets any of
the conditions that follow:
1. The repair is the corrective action to the crack
condition identified in MD80-57A244 Original
Issue and this Service Bulletin and was
approved by the Boeing Organization
Designation Authorization (ODA) via a FAA
Form 8100-9.
2. The installed repair was due to cracking as
described in this Service Bulletin and was
approved by the Boeing Organization
Designation Authorization (ODA) via a FAA
Form 8100-9.
{2} CONDITION 1.1.2: NO CRACK FOUND.
– Repeat Part 2: Eddy Current, Low Frequency (ETLF) inspection
of the left and right side wing fastener holes common to stringers
11 thru 22 and the forward and aft skins and do an Eddy Current,
High Frequency (ETHF) inspection of the lower skin at stringers
18 thru 20 for any crack in accordance with FIGURE 8.
NOTE: It is not required to do the Eddy Current, Low Frequency
inspection and Eddy Current, High Frequency inspection
in this service bulletin in the areas where a repair covers
the affected inspection area and the repair meets any of
the conditions that follow:
1. The repair is the corrective action to the crack
condition identified in MD80-57A244 Original
Issue and this Service Bulletin and was
approved by the Boeing Organization
Designation Authorization (ODA) via a FAA
Form 8100-9.
2. The installed repair was due to cracking as
described in this Service Bulletin and was
approved by the Boeing Organization
Designation Authorization (ODA) via a FAA
Form 8100-9.
2) CONDITION 1.2: NO CRACK FOUND.
Export Controlled ECCN: 9E991 - BOEING
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Work - See page 1 for details.
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45 of 109
BOEING SERVICE BULLETIN MD80-57A244
ALERTALERT

### Page 46

a) Do Part 2: Eddy Current, Low Frequency (ETLF) inspection of t he left and
right side wing fastener holes common to stringers 11 thru 22 and the
forward and aft skins and do an Eddy Current, High Frequency (ETHF)
inspection of the lower skin at stringers 18 thru 20 for any crack in
accordance with FIGURE 8.
NOTE: It is not required to do the Eddy Current, Low Frequency inspection
and Eddy Current, High Frequency inspection in this service bulletin
in the areas where a repair covers the affected inspection area
and the repair meets any of the conditions that follow:
1. The repair is the corrective action to the crack condition
identified in MD80-57A244 Original Issue and this Service
Bulletin and was approved by the Boeing Organization
Designation Authorization (ODA) via a FAA Form 8100-9.
2. The installed repair was due to cracking as described in
this Service Bulletin and was approved by the Boeing
Organization Designation Authorization (ODA) via a FAA
Form 8100-9.
{1} CONDITION 1.2.1: ANY CRACK FOUND.
– CONDITION 1.2.1 (ACTION 1): Contact The Boeing Company for
repair instructions and do the repair.
– CONDITION 1.2.1 (ACTION 2): Repeat Part 2: Eddy Current, Low
Frequency (ETLF) inspection of the left and right side wing fastener
holes common to stringers 11 thru 22 and the forward and aft skins
and do an Eddy Current, High Frequency (ETHF) inspection of
the lower skin at stringers 18 thru 20 for any crack in accordance
with FIGURE 8.
NOTE: It is not required to do the Eddy Current, Low Frequency
inspection and Eddy Current, High Frequency inspection
in this service bulletin in the areas where a repair covers
the affected inspection area and the repair meets any of
the conditions that follow:
1. The repair is the corrective action to the crack
condition identified in MD80-57A244 Original
Issue and this Service Bulletin and was
approved by the Boeing Organization
Designation Authorization (ODA) via a FAA
Form 8100-9.
2. The installed repair was due to cracking as
described in this Service Bulletin and was
approved by the Boeing Organization
Designation Authorization (ODA) via a FAA
Form 8100-9.
{2} CONDITION 1.2.2: NO CRACK FOUND.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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MD80-57A244Revision 1: October 01, 2019
46 of 109
BOEING SERVICE BULLETIN MD80-57A244
ALERTALERT

### Page 47

– Repeat Part 2: Eddy Current, Low Frequency (ETLF) inspection
of the left and right side wing fastener holes common to stringers
11 thru 22 and the forward and aft skins and do an Eddy Current,
High Frequency (ETHF) inspection of the lower skin at stringers
18 thru 20 for any crack in accordance with FIGURE 8.
NOTE: It is not required to do the Eddy Current, Low Frequency
inspection and Eddy Current, High Frequency inspection
in this service bulletin in the areas where a repair covers
the affected inspection area and the repair meets any of
the conditions that follow:
1. The repair is the corrective action to the crack
condition identified in MD80-57A244 Original
Issue and this Service Bulletin and was
approved by the Boeing Organization
Designation Authorization (ODA) via a FAA
Form 8100-9.
2. The installed repair was due to cracking as
described in this Service Bulletin and was
approved by the Boeing Organization
Designation Authorization (ODA) via a FAA
Form 8100-9.
(2) CONDITION 2: NO CRACK FOUND.
(a) Do Part 2: Eddy Current, Low Frequency (ETLF) inspection of the left and right side
fastener holes common to stringers 11 thru 22 and the forward and aft skins and do
an Eddy Current, High Frequency (ETHF) inspection of the lower skin at stringers
18 thru 20 for any crack in the unrepaired area in accordance with FIGURE 8.
1) CONDITION 2.1: ANY CRACK FOUND.
a) CONDITION 2.1 (ACTION 1): Contact The Boeing Company for repa ir
instructions and do the repair.
b) CONDITION 2.1 (ACTION 2): Repeat Part 2: Eddy Current, Low Frequency
(ETLF) inspection of the left and right side wing fastener holes common to
stringers 11 thru 22 and the forward and aft skins and do an Eddy Current,
High Frequency (ETHF) inspection of the lower skin at stringers 18 thru 20
for any crack in accordance with FIGURE 8.
NOTE: It is not required to do the Eddy Current, Low Frequency inspection
and Eddy Current, High Frequency inspection in this service bulletin
in the areas where a repair covers the affected inspection area
and the repair meets any of the conditions that follow:
1. The repair is the corrective action to the crack condition
identified in MD80-57A244 Original Issue and this Service
Bulletin and was approved by the Boeing Organization
Designation Authorization (ODA) via a FAA Form 8100-9.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: March 03, 2016
MD80-57A244Revision 1: October 01, 2019
47 of 109
BOEING SERVICE BULLETIN MD80-57A244
ALERTALERT

### Page 48

2. The installed repair was due to cracking as described in
this Service Bulletin and was approved by the Boeing
Organization Designation Authorization (ODA) via a FAA
Form 8100-9.
2) CONDITION 2.2: NO CRACK FOUND.
a) Repeat Eddy Current, Low Frequency (ETLF) inspection of the left and right
side fastener holes common to stringers 11 thru 22 and the forward and aft
skins and do an Eddy Current, High Frequency (ETHF) inspection of the
lower skin at stringers 18 thru 20 for any crack in the unrepaired area in
accordance with FIGURE 8.
NOTE: It is not required to do the Eddy Current, Low Frequency inspection
and Eddy Current, High Frequency inspection in this service bulletin
in the areas where a repair covers the affected inspection area
and the repair meets any of the conditions that follow:
1. The repair is the corrective action to the crack condition
identified in MD80-57A244 Original Issue and this Service
Bulletin and was approved by the Boeing Organization
Designation Authorization (ODA) via a FAA Form 8100-9.
2. The installed repair was due to cracking as described in
this Service Bulletin and was approved by the Boeing
Organization Designation Authorization (ODA) via a FAA
Form 8100-9.
3. Install the left wing/fuselage fillet panel 2110C in accordan ce with FIGURE 3.
4. Install the right wing/fuselage fillet panel 2210C in accorda nce with FIGURE 6.
5. Put the airplane back to a serviceable condition.
Group 1, Configuration 2:
Option 1:
1. Remove and keep left and right wing/fuselage fillet panels, r efer to FIGURE 7 to get access to the
inspection area.
2. RC - Do a general visual inspection for existing external low er skin repairs between Xcw=0.0 and
Xcw=20.0, stringers 11 thru 22.
PART 2: Eddy Current, Low Frequency (ETLF) inspection of the left and right side wing
fastener holes common to stringers 11 thru 22 and the forward and aft skins and do an
Eddy Current, High Frequency (ETHF) inspection of the lower skin at stringers 18 thru 20
for any crack.
a. CONDITION 1: NO REPAIR FOUND.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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48 of 109
BOEING SERVICE BULLETIN MD80-57A244
ALERTALERT

### Page 49

(1) Do Eddy Current, Low Frequency (ETLF) inspection of the left and right side wing fastener
holes common to stringers 11 thru 22 and the forward and aft skins and do an Eddy
Current, High Frequency (ETHF) inspection of the lower skin at stringers 18 thru 20 for
any crack in accordance with FIGURE 8.
(a) CONDITION 1.1: ANY CRACK FOUND.
1) CONDITION 1.1 (ACTION 1): Contact The Boeing Company for repa ir
instructions and do the repair.
2) CONDITION 1.1 (ACTION 2): Repeat Eddy Current, Low Frequency (ETLF)
inspection of the left and right side wing fastener holes common to stringers 11
thru 22 and the forward and aft skins and do an Eddy Current, High Frequency
(ETHF) inspection of the lower skin at stringers 18 thru 20 for any crack in the
unrepaired area in accordance with FIGURE 8.
NOTE: It is not required to do the Eddy Current, Low Frequency inspection
and Eddy Current, High Frequency inspection in this service bulletin
in the areas where a repair covers the affected inspection area and the
repair meets any of the conditions that follow:
1. The repair is the corrective action to the crack condition
identified in MD80-57A244 Original Issue and this Service
Bulletin and was approved by the Boeing Organization
Designation Authorization (ODA) via a FAA Form 8100-9.
2. The installed repair was due to cracking as described in this
Service Bulletin and was approved by the Boeing Organization
Designation Authorization (ODA) via a FAA Form 8100-9.
(b) CONDITION 1.2: NO CRACK FOUND.
1) Repeat Part 2: Eddy Current, Low Frequency (ETLF) inspection of the left and
right side wing fastener holes common to stringers 11 thru 22 and the forward
and aft skins and do an Eddy Current, High Frequency (ETHF) inspection of the
lower skin at stringers 18 thru 20 for any crack in accordance with FIGURE 8.
NOTE: It is not required to do the Eddy Current, Low Frequency inspection
and Eddy Current, High Frequency inspection in this service bulletin
in the areas where a repair covers the affected inspection area and the
repair meets any of the conditions that follow:
1. The repair is the corrective action to the crack condition
identified in MD80-57A244 Original Issue and this Service
Bulletin and was approved by the Boeing Organization
Designation Authorization (ODA) via a FAA Form 8100-9.
2. The installed repair was due to cracking as described in this
Service Bulletin and was approved by the Boeing Organization
Designation Authorization (ODA) via a FAA Form 8100-9.
b. CONDITION 2: ANY EXISTING REPAIR FOUND.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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49 of 109
BOEING SERVICE BULLETIN MD80-57A244
ALERTALERT

### Page 50

(1) CONDITION 2 (ACTION 1): Contact The Boeing Company for alter native inspection(s),
incorporate the inspection(s) requirements into the maintenance program and do the
inspection(s) at the times specified by Boeing.
(2) CONDITION 2 (ACTION 2): Do Eddy Current, Low Frequency (ETLF ) inspection of the
left and right side wing fastener holes common to stringers 11 thru 22 and the forward
and aft skins and do an Eddy Current, High Frequency (ETHF) inspection of the lower
skin at stringers 18 thru 20 for any crack in the unrepaired area in accordance with FIGURE
8.
NOTE: It is not required to do the Eddy Current, Low Frequency inspection and Eddy
Current, High Frequency inspection in this service bulletin in the areas where a
repair covers the affected inspection area and the repair meets any of the
conditions that follow:
1. The repair is the corrective action to the crack condition id entified in
MD80-57A244 Original Issue and this Service Bulletin and was
approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
2. The installed repair was due to cracking as described in this  Service
Bulletin and was approved by the Boeing Organization Designation
Authorization (ODA) via a FAA Form 8100-9.
(a) CONDITION 2.1: ANY CRACK FOUND.
1) CONDITION 2.1 (ACTION 1): Contact The Boeing Company for repa ir
instructions and do the repair.
2) CONDITION 2.1 (ACTION 2): Repeat Eddy Current, Low Frequency (ETLF)
inspection of the left and right side wing fastener holes common to stringers 11
thru 22 and the forward and aft skins and do an Eddy Current, High Frequency
(ETHF) inspection of the lower skin at stringers 18 thru 20 for any crack in the
unrepaired area in accordance with FIGURE 8.
NOTE: It is not required to do the Eddy Current, Low Frequency inspection
and Eddy Current, High Frequency inspection in this service bulletin
in the areas where a repair covers the affected inspection area and the
repair meets any of the conditions that follow:
1. The repair is the corrective action to the crack condition
identified in MD80-57A244 Original Issue and this Service
Bulletin and was approved by the Boeing Organization
Designation Authorization (ODA) via a FAA Form 8100-9.
2. The installed repair was due to cracking as described in this
Service Bulletin and was approved by the Boeing Organization
Designation Authorization (ODA) via a FAA Form 8100-9.
(b) CONDITION 2.2: NO CRACK FOUND.
Export Controlled ECCN: 9E991 - BOEING
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Work - See page 1 for details.
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MD80-57A244Revision 1: October 01, 2019
50 of 109
BOEING SERVICE BULLETIN MD80-57A244
ALERTALERT

### Page 51

1) Repeat Part 2: Eddy Current, Low Frequency (ETLF) inspection of the left and
right side wing fastener holes common to stringers 11 thru 22 and the forward
and aft skins and do an Eddy Current, High Frequency (ETHF) inspection of the
lower skin at stringers 18 thru 20 for any crack in the unrepaired area in
accordance with FIGURE 8.
NOTE: It is not required to do the Eddy Current, Low Frequency inspection
and Eddy Current, High Frequency inspection in this service bulletin
in the areas where a repair covers the affected inspection area and the
repair meets any of the conditions that follow:
1. The repair is the corrective action to the crack condition
identified in MD80-57A244 Original Issue and this Service
Bulletin and was approved by the Boeing Organization
Designation Authorization (ODA) via a FAA Form 8100-9.
2. The installed repair was due to cracking as described in this
Service Bulletin and was approved by the Boeing Organization
Designation Authorization (ODA) via a FAA Form 8100-9.
3. Install the kept wing/fuselage fillet panels, refer to FIGURE  9 to close access.
4. Put the airplane back to a serviceable condition.
Group 1, Configuration 2:
Option 2:
1. Remove left wing/fuselage fillet panel 2110C in accordance wi th FIGURE 1 to get access to the
inspection area on the left side of the airplane.
2. Remove the right wing/fuselage fillet panel 2210C in accordan ce with FIGURE 4 to get access to
the inspection area on the right side of the airplane.
3. RC - Do a general visual inspection for existing external low er skin repairs between Xcw=0.0 and
Xcw=20.0, stringers 15 thru 17.
PART 1: Eddy Current, High Frequency (ETHF) inspection for any crack in the left side and
right side center wing lower skin.
a. CONDITION 1: NO REPAIR FOUND.
(1) Do an Eddy Current, High Frequency (ETHF) inspection for any crack in the left side and
right side center wing lower skin in accordance with FIGURE 2 and FIGURE 5.
(a) CONDITION 1.1: ANY CRACK FOUND.
1) CONDITION 1.1 (ACTION 1): Contact The Boeing Company for repa ir
instructions and do the repair.
2) CONDITION 1.1 (ACTION 2): Do an internal general visual inspe ction for any
cracks in the stringers between Xcw=0.0 and Xcw=20.0, stringers 11 thru 22.
a) CONDITION 1.1.1: ANY CRACK FOUND.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: March 03, 2016
MD80-57A244Revision 1: October 01, 2019
51 of 109
BOEING SERVICE BULLETIN MD80-57A244
ALERTALERT

### Page 52

{1} CONDITION 1.1.1 (ACTION 1): Contact The Boeing Company for
repair instructions and do the repair.
{2} CONDITION 1.1.1 (ACTION 2): Do an Eddy Current, Low Frequenc y
(ETLF) inspection of the left and right side wing fastener holes common
to stringers 11 thru 22 and the forward and aft skins and do an Eddy
Current, High Frequency (ETHF) inspection of the lower skin at stringers
18 thru 20 for any crack in the unrepaired area in accordance with
FIGURE 8.
NOTE: It is not required to do the Eddy Current, Low Frequency
inspection and Eddy Current, High Frequency inspection in
this service bulletin in the areas where a repair covers the
affected inspection area and the repair meets any of the
conditions that follow:
1. The repair is the corrective action to the crack
condition identified in MD80-57A244 Original Issue
and this Service Bulletin and was approved by the
Boeing Organization Designation Authorization
(ODA) via a FAA Form 8100-9.
2. The installed repair was due to cracking as described
in this Service Bulletin and was approved by the
Boeing Organization Designation Authorization
(ODA) via a FAA Form 8100-9.
– CONDITION 1.1.1.1: ANY CRACK FOUND.
– CONDITION 1.1.1.1 (ACTION 1): Contact The Boeing
Company for repair instructions and do the repair.
– CONDITION 1.1.1.1 (ACTION 2): Repeat Eddy Current, Low
Frequency (ETLF) inspection of the left and right side wing
fastener holes common to stringers 11 thru 22 and the forward
and aft skins and do an Eddy Current, High Frequency (ETHF)
inspection of the lower skin at stringers 18 thru 20 for any
crack in the unrepaired area in accordance with FIGURE 8.
NOTE: It is not required to do the Eddy Current, Low
Frequency inspection and Eddy Current, High
Frequency inspection in this service bulletin in the
areas where a repair covers the affected inspection
area and the repair meets any of the conditions that
follow:
1. The repair is the corrective action to the
crack condition identified in MD80-57A244
Original Issue and this Service Bulletin and
was approved by the Boeing Organization
Designation Authorization (ODA) via a FAA
Form 8100-9.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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52 of 109
BOEING SERVICE BULLETIN MD80-57A244
ALERTALERT

### Page 53

2. The installed repair was due to cracking as
described in this Service Bulletin and was
approved by the Boeing Organization
Designation Authorization (ODA) via a FAA
Form 8100-9.
– CONDITION 1.1.1.2: NO CRACK FOUND.
– Repeat Eddy Current, Low Frequency (ETLF) inspection of
the left and right side wing fastener holes common to stringers
11 thru 22 and the forward and aft skins and do an Eddy
Current, High Frequency (ETHF) inspection of the lower skin
at stringers 18 thru 20 for any crack in the unrepaired area in
accordance with FIGURE 8.
NOTE: It is not required to do the Eddy Current, Low
Frequency inspection and Eddy Current, High
Frequency inspection in this service bulletin in the
areas where a repair covers the affected inspection
area and the repair meets any of the conditions that
follow:
1. The repair is the corrective action to the
crack condition identified in MD80-57A244
Original Issue and this Service Bulletin and
was approved by the Boeing Organization
Designation Authorization (ODA) via a FAA
Form 8100-9.
2. The installed repair was due to cracking as
described in this Service Bulletin and was
approved by the Boeing Organization
Designation Authorization (ODA) via a FAA
Form 8100-9.
b) CONDITION 1.1.2: NO CRACK FOUND.
{1} Do an Eddy Current, Low Frequency (ETLF) inspection of the left and
right side wing fastener holes common to stringers 11 thru 22 and the
forward and aft skins and do an Eddy Current, High Frequency (ETHF)
inspection of the lower skin at stringers 18 thru 20 for any crack in the
unrepaired area in accordance with FIGURE 8.
NOTE: It is not required to do the Eddy Current, Low Frequency
inspection and Eddy Current, High Frequency inspection in
this service bulletin in the areas where a repair covers the
affected inspection area and the repair meets any of the
conditions that follow:
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: March 03, 2016
MD80-57A244Revision 1: October 01, 2019
53 of 109
BOEING SERVICE BULLETIN MD80-57A244
ALERTALERT

### Page 54

1. The repair is the corrective action to the crack
condition identified in MD80-57A244 Original Issue
and this Service Bulletin and was approved by the
Boeing Organization Designation Authorization
(ODA) via a FAA Form 8100-9.
2. The installed repair was due to cracking as described
in this Service Bulletin and was approved by the
Boeing Organization Designation Authorization
(ODA) via a FAA Form 8100-9.
– CONDITION 1.1.2.1: ANY CRACK FOUND.
– CONDITION 1.1.2.1 (ACTION 1): Contact The Boeing
Company for repair instructions and do the repair.
– CONDITION 1.1.2.1 (ACTION 2): Repeat Eddy Current, Low
Frequency (ETLF) inspection of the left and right side wing
fastener holes common to stringers 11 thru 22 and the forward
and aft skins and do an Eddy Current, High Frequency (ETHF)
inspection of the lower skin at stringers 18 thru 20 for any
crack in the unrepaired area in accordance with FIGURE 8.
NOTE: It is not required to do the Eddy Current, Low
Frequency inspection and Eddy Current, High
Frequency inspection in this service bulletin in the
areas where a repair covers the affected inspection
area and the repair meets any of the conditions that
follow:
1. The repair is the corrective action to the
crack condition identified in MD80-57A244
Original Issue and this Service Bulletin and
was approved by the Boeing Organization
Designation Authorization (ODA) via a FAA
Form 8100-9.
2. The installed repair was due to cracking as
described in this Service Bulletin and was
approved by the Boeing Organization
Designation Authorization (ODA) via a FAA
Form 8100-9.
– CONDITION 1.1.2.2: NO CRACK FOUND.
– Repeat Eddy Current, Low Frequency (ETLF) inspection of
the left and right side wing fastener holes common to stringers
11 thru 22 and the forward and aft skins and do an Eddy
Current, High Frequency (ETHF) inspection of the lower skin
at stringers 18 thru 20 for any crack in the unrepaired area in
accordance with FIGURE 8.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: March 03, 2016
MD80-57A244Revision 1: October 01, 2019
54 of 109
BOEING SERVICE BULLETIN MD80-57A244
ALERTALERT

### Page 55

NOTE: It is not required to do the Eddy Current, Low
Frequency inspection and Eddy Current, High
Frequency inspection in this service bulletin in the
areas where a repair covers the affected inspection
area and the repair meets any of the conditions that
follow:
1. The repair is the corrective action to the
crack condition identified in MD80-57A244
Original Issue and this Service Bulletin and
was approved by the Boeing Organization
Designation Authorization (ODA) via a FAA
Form 8100-9.
2. The installed repair was due to cracking as
described in this Service Bulletin and was
approved by the Boeing Organization
Designation Authorization (ODA) via a FAA
Form 8100-9.
(b) CONDITION 1.2: NO CRACK FOUND.
1) Do Eddy Current, Low Frequency (ETLF) inspection of the left and right side
wing fastener holes common to stringers 11 thru 22 and the forward and aft
skins and do an Eddy Current, High Frequency (ETHF) inspection of the lower
skin at stringers 18 thru 20 for any crack in the unrepaired area in accordance
with FIGURE 8.
a) CONDITION 1.2.1: ANY CRACK FOUND.
{1} CONDITION 1.2.1 (ACTION 1): Contact The Boeing Company for
repair instructions and do the repair.
{2} CONDITION 1.2.1 (ACTION 2): Repeat Eddy Current, Low Frequency
(ETLF) inspection of the left and right side wing fastener holes common
to stringers 11 thru 22 and the forward and aft skins and do an Eddy
Current, High Frequency (ETHF) inspection of the lower skin at stringers
18 thru 20 for any crack in the unrepaired area in accordance with
FIGURE 8.
NOTE: It is not required to do the Eddy Current, Low Frequency
inspection and Eddy Current, High Frequency inspection in
this service bulletin in the areas where a repair covers the
affected inspection area and the repair meets any of the
conditions that follow:
1. The repair is the corrective action to the crack
condition identified in MD80-57A244 Original Issue
and this Service Bulletin and was approved by the
Boeing Organization Designation Authorization
(ODA) via a FAA Form 8100-9.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: March 03, 2016
MD80-57A244Revision 1: October 01, 2019
55 of 109
BOEING SERVICE BULLETIN MD80-57A244
ALERTALERT

### Page 56

2. The installed repair was due to cracking as described
in this Service Bulletin and was approved by the
Boeing Organization Designation Authorization
(ODA) via a FAA Form 8100-9.
b) CONDITION 1.2.2: NO CRACK FOUND.
{1} Repeat Eddy Current, Low Frequency (ETLF) inspection of the left and
right side wing fastener holes common to stringers 11 thru 22 and the
forward and aft skins and do an Eddy Current, High Frequency (ETHF)
inspection of the lower skin at stringers 18 thru 20 for any crack in the
unrepaired area in accordance with FIGURE 8.
NOTE: It is not required to do the Eddy Current, Low Frequency
inspection and Eddy Current, High Frequency inspection in
this service bulletin in the areas where a repair covers the
affected inspection area and the repair meets any of the
conditions that follow:
1. The repair is the corrective action to the crack
condition identified in MD80-57A244 Original Issue
and this Service Bulletin and was approved by the
Boeing Organization Designation Authorization
(ODA) via a FAA Form 8100-9.
2. The installed repair was due to cracking as described
in this Service Bulletin and was approved by the
Boeing Organization Designation Authorization
(ODA) via a FAA Form 8100-9.
b. CONDITION 2: ANY EXISTING REPAIR FOUND.
(1) CONDITION 2 (ACTION 1): Contact The Boeing Company for alter native inspection(s),
incorporate the inspection(s) requirements into the maintenance program and do the
inspection(s) at the times specified by Boeing.
(2) CONDITION 2 (ACTION 2): Do an Eddy Current, High Frequency (ETHF) inspection for
any crack in the left side and right side center wing lower skin in accordance with FIGURE
2 and FIGURE 5.
NOTE: It is not required to do the Eddy Current, Low Frequency inspection and Eddy
Current, High Frequency inspection in this service bulletin in the areas where a
repair covers the affected inspection area and the repair meets any of the
conditions that follow:
1. The repair is the corrective action to the crack condition id entified in
MD80-57A244 Original Issue and this Service Bulletin and was
approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
2. The installed repair was due to cracking as described in this  Service
Bulletin and was approved by the Boeing Organization Designation
Authorization (ODA) via a FAA Form 8100-9.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: March 03, 2016
MD80-57A244Revision 1: October 01, 2019
56 of 109
BOEING SERVICE BULLETIN MD80-57A244
ALERTALERT

### Page 57

(a) CONDITION 2.1: ANY CRACK FOUND.
1) CONDITION 2.1 (ACTION 1): Contact The Boeing Company for repa ir
instructions and do the repair.
2) CONDITION 2.1 (ACTION 2): Do an internal general visual inspe ction for any
cracks in the stringers between Xcw=0.0 and Xcw=20.0, stringers 11 thru 22.
a) CONDITION 2.1.1: ANY CRACK FOUND.
{1} CONDITION 2.1.1 (ACTION 1): Contact The Boeing Company for
repair instructions and do the repair.
{2} CONDITION 2.1.1 (ACTION 2): Do an Eddy Current, Low Frequenc y
(ETLF) inspection of the left and right side wing fastener holes common
to stringers 11 thru 22 and the forward and aft skins and do an Eddy
Current, High Frequency (ETHF) inspection of the lower skin at stringers
18 thru 20 for any crack in the unrepaired area in accordance with
FIGURE 8.
NOTE: It is not required to do the Eddy Current, Low Frequency
inspection and Eddy Current, High Frequency inspection in
this service bulletin in the areas where a repair covers the
affected inspection area and the repair meets any of the
conditions that follow:
1. The repair is the corrective action to the crack
condition identified in MD80-57A244 Original Issue
and this Service Bulletin and was approved by the
Boeing Organization Designation Authorization
(ODA) via a FAA Form 8100-9.
2. The installed repair was due to cracking as described
in this Service Bulletin and was approved by the
Boeing Organization Designation Authorization
(ODA) via a FAA Form 8100-9.
– CONDITION 2.1.1.1: ANY CRACK FOUND.
– CONDITION 2.1.1.1 (ACTION 1): Contact The Boeing
Company for repair instructions and do the repair.
– CONDITION 2.1.1.1 (ACTION 2): Repeat Eddy Current, Low
Frequency (ETLF) inspection of the left and right side wing
fastener holes common to stringers 11 thru 22 and the forward
and aft skins and do an Eddy Current, High Frequency (ETHF)
inspection of the lower skin at stringers 18 thru 20 for any
crack in the unrepaired area in accordance with FIGURE 8.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: March 03, 2016
MD80-57A244Revision 1: October 01, 2019
57 of 109
BOEING SERVICE BULLETIN MD80-57A244
ALERTALERT

### Page 58

NOTE: It is not required to do the Eddy Current, Low
Frequency inspection and Eddy Current, High
Frequency inspection in this service bulletin in the
areas where a repair covers the affected inspection
area and the repair meets any of the conditions that
follow:
1. The repair is the corrective action to the
crack condition identified in MD80-57A244
Original Issue and this Service Bulletin and
was approved by the Boeing Organization
Designation Authorization (ODA) via a FAA
Form 8100-9.
2. The installed repair was due to cracking as
described in this Service Bulletin and was
approved by the Boeing Organization
Designation Authorization (ODA) via a FAA
Form 8100-9.
– CONDITION 2.1.1.2: NO CRACK FOUND.
– Repeat Eddy Current, Low Frequency (ETLF) inspection of
the left and right side wing fastener holes common to stringers
11 thru 22 and the forward and aft skins and do an Eddy
Current, High Frequency (ETHF) inspection of the lower skin
at stringers 18 thru 20 for any crack in the unrepaired area in
accordance with FIGURE 8.
NOTE: It is not required to do the Eddy Current, Low
Frequency inspection and Eddy Current, High
Frequency inspection in this service bulletin in the
areas where a repair covers the affected inspection
area and the repair meets any of the conditions that
follow:
1. The repair is the corrective action to the
crack condition identified in MD80-57A244
Original Issue and this Service Bulletin and
was approved by the Boeing Organization
Designation Authorization (ODA) via a FAA
Form 8100-9.
2. The installed repair was due to cracking as
described in this Service Bulletin and was
approved by the Boeing Organization
Designation Authorization (ODA) via a FAA
Form 8100-9.
b) CONDITION 2.1.2: NO CRACK FOUND.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: March 03, 2016
MD80-57A244Revision 1: October 01, 2019
58 of 109
BOEING SERVICE BULLETIN MD80-57A244
ALERTALERT

### Page 59

{1} Do an Eddy Current, Low Frequency (ETLF) inspection of the left and
right side wing fastener holes common to stringers 11 thru 22 and the
forward and aft skins and do an Eddy Current, High Frequency (ETHF)
inspection of the lower skin at stringers 18 thru 20 for any crack in the
unrepaired area in accordance with FIGURE 8.
NOTE: It is not required to do the Eddy Current, Low Frequency
inspection and Eddy Current, High Frequency inspection in
this service bulletin in the areas where a repair covers the
affected inspection area and the repair meets any of the
conditions that follow:
1. The repair is the corrective action to the crack
condition identified in MD80-57A244 Original Issue
and this Service Bulletin and was approved by the
Boeing Organization Designation Authorization
(ODA) via a FAA Form 8100-9.
2. The installed repair was due to cracking as described
in this Service Bulletin and was approved by the
Boeing Organization Designation Authorization
(ODA) via a FAA Form 8100-9.
– CONDITION 2.1.2.1: ANY CRACK FOUND.
– CONDITION 2.1.2.1 (ACTION 1): Contact The Boeing
Company for repair instructions and do the repair.
– CONDITION 2.1.2.1 (ACTION 2): Repeat Eddy Current, Low
Frequency (ETLF) inspection of the left and right side wing
fastener holes common to stringers 11 thru 22 and the forward
and aft skins and do an Eddy Current, High Frequency (ETHF)
inspection of the lower skin at stringers 18 thru 20 for any
crack in the unrepaired area in accordance with FIGURE 8.
NOTE: It is not required to do the Eddy Current, Low
Frequency inspection and Eddy Current, High
Frequency inspection in this service bulletin in the
areas where a repair covers the affected inspection
area and the repair meets any of the conditions that
follow:
1. The repair is the corrective action to the
crack condition identified in MD80-57A244
Original Issue and this Service Bulletin and
was approved by the Boeing Organization
Designation Authorization (ODA) via a FAA
Form 8100-9.
2. The installed repair was due to cracking as
described in this Service Bulletin and was
approved by the Boeing Organization
Designation Authorization (ODA) via a FAA
Form 8100-9.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: March 03, 2016
MD80-57A244Revision 1: October 01, 2019
59 of 109
BOEING SERVICE BULLETIN MD80-57A244
ALERTALERT

### Page 60

– CONDITION 2.1.2.2: NO CRACK FOUND.
– Repeat Eddy Current, Low Frequency (ETLF) inspection of
the left and right side wing fastener holes common to stringers
11 thru 22 and the forward and aft skins and do an Eddy
Current, High Frequency (ETHF) inspection of the lower skin
at stringers 18 thru 20 for any crack in the unrepaired area in
accordance with FIGURE 8.
NOTE: It is not required to do the Eddy Current, Low
Frequency inspection and Eddy Current, High
Frequency inspection in this service bulletin in the
areas where a repair covers the affected inspection
area and the repair meets any of the conditions that
follow:
1. The repair is the corrective action to the
crack condition identified in MD80-57A244
Original Issue and this Service Bulletin and
was approved by the Boeing Organization
Designation Authorization (ODA) via a FAA
Form 8100-9.
2. The installed repair was due to cracking as
described in this Service Bulletin and was
approved by the Boeing Organization
Designation Authorization (ODA) via a FAA
Form 8100-9.
(b) CONDITION 2.2: NO CRACK FOUND.
1) Do an Eddy Current, Low Frequency (ETLF) inspection of the le ft and right side
wing fastener holes common to stringers 11 thru 22 and the forward and aft
skins and do an Eddy Current, High Frequency (ETHF) inspection of the lower
skin at stringers 18 thru 20 for any crack in the unrepaired area in accordance
with FIGURE 8.
NOTE: It is not required to do the Eddy Current, Low Frequency inspection
and Eddy Current, High Frequency inspection in this service bulletin
in the areas where a repair covers the affected inspection area and the
repair meets any of the conditions that follow:
1. The repair is the corrective action to the crack condition
identified in MD80-57A244 Original Issue and this Service
Bulletin and was approved by the Boeing Organization
Designation Authorization (ODA) via a FAA Form 8100-9.
2. The installed repair was due to cracking as described in this
Service Bulletin and was approved by the Boeing Organization
Designation Authorization (ODA) via a FAA Form 8100-9.
a) CONDITION 2.2.1: ANY CRACK FOUND.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: March 03, 2016
MD80-57A244Revision 1: October 01, 2019
60 of 109
BOEING SERVICE BULLETIN MD80-57A244
ALERTALERT

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