# Boeing Alert Service Bulletin MD80-57A244: U.S. DOT/FAA - SB-MD80-57A244-00

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- Document: [Boeing Alert Service Bulletin MD80-57A244](https://openairdocs.org/service-documents/boeing/md80-57a244.md)
- Title as filed: U.S. DOT/FAA - SB-MD80-57A244-00
- Pages: 37
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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
ATA System: 5732
SUBJECT: WINGS - Lower Wing Skin - Inspection of Left Side and Right Side Center Wing Lower
Skin
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Unpublished Work.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
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connection with this document unless provided in writing by Boeing.
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### Page 3

Table of Contents
Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14
E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14
F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15
G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 17
K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 19
3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 20
3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
FIGURE 1: OPEN ACCESS - LEFT SIDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24
FIGURE 2: INSPECTION - LEFT SIDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26
FIGURE 3: CLOSE ACCESS - LEFT SIDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29
FIGURE 4: OPEN ACCESS - RIGHT SIDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31
FIGURE 5: INSPECTION - RIGHT SIDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33
FIGURE 6: CLOSE ACCESS - RIGHT SIDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36
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Commercial 
Airplanes
MD80
Service Bulletin
ALERT
SummaryNumber: MD80-57A244Original Issue: March 03, 2016
ATA System: 5732
SUBJECT: WINGS - Lower Wing Skin - Inspection of Left Side and Right Side Center Wing Lower
Skin
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
CONCURRENT REQUIREMENTS
None.
BACKGROUND
This service bulletin does an external Eddy Current, High Frequency (ETHF) inspection for any crack around
fastener heads or nuts on the left side and right side center wing lower skin. The ETHF inspection is done at
the area of the left side and right side center wing lower skin common to Stringers S-15, S-16, and S-17 under
the wing/fuselage fillet panel. If Stringer S-15, S-16, or S-17 is cracked in this area and there is a crack in the
skin adjacent to the stringer crack, then the skin crack could grow to a critical length before it can be found by
routine maintenance inspections. If the inspection in this service bulletin is not done, a crack in the center wing
lower skin 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 Mainte-
nance
42,247 / 78,873Stringer 17 RightJuly 20141
Found during fuel
leak investigation
44,147 / 61,208Stringer 17 Left, Fwd
Skin, Aft Skin
April 20152
Scheduled Mainte-
nance
56,908 / 74,240Stringer 17 Right,
Fwd Skin, Aft Skin
July 20153
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NotesFlight Cycles/ Flight
Hours
Structure CrackedDateReport
Scheduled Mainte-
nance
43,756 / 60,690Stringer 15 and 16
Right, four end fit-
tings (two per
stringer)
August 20154
Scheduled Mainte-
nance
45,421 / 63,168Stringer 17 Left and
Stringer 17 Right
January 20165
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
ACTION
Get access to the left side and right side lower surface of the center wing lower skin at stringers S-15, S-16, and
S-17 at approximately Xcw=15 and do an ETHF inspection for any crack at 12 fastener locations at Stringer
S-15, 12 fastener locations at stringer S-16, and 14 fastener locations at stringer S-17. At each fastener location,
do the ETHF inspection around the fastener heads or nuts for any crack in the adjacent skin.
If any crack is found, contact The Boeing Company for inspection and repair instructions and do the inspection
and repair. If no crack is found, repeat ETHF inspections for any crack in the left side and right side center wing
lower skin.
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).
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COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service
bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin
mandatory.
Refer to Paragraph 1.E., Compliance.
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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### Page 8 (OCR)

BOEING SERVICE BULLETIN MD80-57A244
ALERT  ALERT
~
S-17
S-16
BUTT
SPLICE
S-15
CENTER WING
LOWER SKIN
EXTERNAL
DOUBLER
FWD
DO AN ETHF INSPECTION AROUND
THE FASTENER HEADS OR COLLARS
FOR ANY CRACK IN THE CENTER
WING LOWER SKIN
(VIEW LOOKING UP)  2481761
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### Page 9

Commercial 
Airplanes
MD80
Service Bulletin
ALERT
Number: MD80-57A244
Original Issue: March 03, 2016
ATA System: 5732
SUBJECT: WINGS - Lower Wing Skin - Inspection of Left Side and Right Side Center Wing Lower
Skin
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
This service bulletin is for the airplanes shown below.
DESCRIPTIONCONFIGURATIONGROUP
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
Airplane Models:
DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), MD-88
GroupFuselage Num-
ber
1909
1917
1924
1938
1941
1944
1946
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GroupFuselage Num-
ber
1948
1950
1952 - 953
1955
1957 - 958
1960
1962 - 963
1965 - 967
1969
1970 - 971
1973 - 975
1977 - 979
1981
1983
1985 - 986
1988 - 989
1991 - 992
1994 - 999
11000 - 1013
11015 - 1016
11018 - 1020
11022 - 1023
11025 - 1026
11028 - 1029
11031 - 1032
11034 - 1035
11037 - 1038
11040 - 1041
11043
11045
11047
11049
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GroupFuselage Num-
ber
11051
11053
11055
11057
11059 - 1080
11082 - 1083
11085 - 1099
11100 - 1199
11200 - 1299
11300 - 1399
11400 - 1499
11500 - 1599
11600 - 1699
11700 - 1799
11800 - 1899
11900 - 1999
12000 - 2007
12009 - 2016
12019 - 2034
12036 - 2069
12071 - 2093
12101 - 2114
12116
12118 - 2119
12121
12124
12127 - 2128
12130
12132
12134 - 2135
12137
12139
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GroupFuselage Num-
ber
12145
12148
12151 - 2152
12155
12167
12174
12176
12178
12180
12183
12185
12187
12189
12192
12196
12199
12201
12204
12206
12208
12214
12218
12234
12239
12241
12244
12247
12249
12252
12254
12264 - 2287
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### Page 13

2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
This service bulletin does an external Eddy Current, High Frequency (ETHF) inspection for any crack
around fastener heads or nuts on the left side and right side center wing lower skin. The ETHF inspection
is done at the area of the left side and right side center wing lower skin common to Stringers S-15,
S-16, and S-17 under the wing/fuselage fillet panel. If Stringer S-15, S-16, or S-17 is cracked in this
area and there is a crack in the skin adjacent to the stringer crack, then the skin crack could grow to a
critical length before it can be found by routine maintenance inspections. If the inspection in this service
bulletin is not done, a crack in the center wing lower skin 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 Mainte-
nance
42,247 / 78,873Stringer 17 RightJuly 20141
Found during fuel
leak investigation
44,147 / 61,208Stringer 17 Left, Fwd
Skin, Aft Skin
April 20152
Scheduled Mainte-
nance
56,908 / 74,240Stringer 17 Right,
Fwd Skin, Aft Skin
July 20153
Scheduled Mainte-
nance
43,756 / 60,690Stringer 15 and 16
Right, four end fit-
tings (two per
stringer)
August 20154
Scheduled Mainte-
nance
45,421 / 63,168Stringer 17 Left and
Stringer 17 Right
January 20165
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D. Description
Get access to the left side and right side lower surface of the center wing lower skin at stringers S-15,
S-16, and S-17 at approximately Xcw=15 and do an ETHF inspection for any crack at 12 fastener
locations at Stringer S-15, 12 fastener locations at stringer S-16, and 14 fastener locations at stringer
S-17. At each fastener location, do the ETHF inspection around the fastener heads or nuts for any
crack in the adjacent skin.
If any crack is found, contact The Boeing Company for inspection and repair instructions and do the
inspection and repair. If no crack is found, repeat ETHF inspections for any crack in the left side and
right side center wing lower skin.
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
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to
this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this
service bulletin mandatory.
Do the required actions in accordance with Paragraph 3. Accomplishment Instructions.
Table 1: ETHF Inspection of the Left Side and Right Side Center Wing Lower Skin
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Within 300 flight cycles af-
ter the Original Issue date
of this Service Bulletin or
within 5,400 flight cycles
after the last detailed in-
spection done in accor-
dance with MPD item 57-
086-02, or before 35,400
total flight cycles, whichev-
er occurs latest.
Do an ETHF inspection
for any crack in the left
side and right side cen-
ter wing lower skin.
Airplanes with less
than 45,000 total
flight cycles as of
the Original Issue
date of this Service
Bulletin.
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Table 1: ETHF Inspection of the Left Side and Right Side Center Wing Lower Skin
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Within 150 flight cycles af-
ter the Original Issue date
of this Service Bulletin or
within 5,400 flight cycles
after the last detailed in-
spection done in accor-
dance with MPD item 57-
086-02, whichever occurs
latest.
Do an ETHF inspection
for any crack in the left
side and right side cen-
ter wing lower skin.
Airplanes with
45,000 or more total
flight cycles as of
the Original Issue
date of this Service
Bulletin.
-Before further flight.ACTION 1: Contact The
Boeing Company for
inspection and repair
instructions and do the
inspection and repair.
Any crack found in
the left side or right
side center wing
lower skin.
2,000 flight cycles.-ACTION 2: Repeat
ETHF inspection in the
unrepaired areas.
2,000 flight cycles.-Repeat ETHF inspec-
tion in the left side and
right side center wing
lower skin.
No crack found in
either the left side or
right side center
wing lower skin.
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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### Page 16

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
7.014.0TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Non-Destructive Test Standard Practices Manual (NDTSPM) 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
2. Data Supplied with this Service Bulletin:
None.
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### Page 17

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 18

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BLANK PAGE

### Page 19

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)Sealant16 oz.PR-1828
(b) (c)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 alternative to PR-1828 sealant.
(c) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS)
for supplier data.
3. Parts Modified and Reidentified
None.
4. Parts Removed and Not Replaced
None.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
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### Page 20

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 21

3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
WARNING: IF ELECTRICAL POWER IS APPLIED TO THE AIRPLANE, MAKE SURE YOU OBEY
ALL PRECAUTIONS WHILE YOU DO WORK. IF YOU DO NOT OBEY THE
PRECAUTIONS, DEATH OR INJURY TO PERSONS, AND DAMAGE TO THE AIRPLANE
CAN OCCUR.
CAUTION: ELECTRICALLY GROUND THE AIRPLANE. THIS WILL HELP TO PREVENT DAMAGE
TO THE AIRPLANE OR EQUIPMENT.
CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL
PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,
METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE
DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR
OTHER ELECTRICAL DAMAGE.
NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
2. Equivalent parts are listed in the AEPL, Drawing 7595071.
3. Use the approved fastener and process material substitutions, in accordance with
MD-80 SRM 51-30.
4. If the length of any fastener specified in this service bulletin does not meet installation
standards given in Structural Repair Manual (SRM) Chapter 51, then a fastener of
the same specification, or an approved substitute, with a length which meets the
installation standards given in SRM Chapter 51 may be used. In addition, washers
may be installed for fastener grip length in accordance with SRM Chapter 51. Refer
to SOPM 20-50-01 for alternate full threaded fasteners (screws) needed for installation
in this service bulletin.
5. 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:
— Values for structural fasteners are given in MD-80 Structural Repair Manual,
Chapter 51.
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### Page 22

— 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 Chapter 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 remove those parts. If
you can get access without removing identified parts, it is not necessary to remove
all of the identified parts. Jacking and shoring limitations must be observed.
10. Where the work instructions include installation of a kept part, a new or serviceable
part with the same part number can be installed as an alternative to the kept part.
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.
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### Page 23

B. WORK INSTRUCTIONS
1. Remove left wing/fuselage fillet panel 2110C in accordance with FIGURE 1 to get access to the
inspection area on the left side of the airplane.
2. RC - Do an Eddy Current, High Frequency (ETHF) inspection for any crack in the left side center
wing lower skin in accordance with FIGURE 2.
a. If any crack is found, contact The Boeing Company for inspection and repair instructions and
do the inspection and repair.
b. If no crack is found, repeat the ETHF inspections for any crack in the left side center wing
lower skin in accordance with FIGURE 2.
3. Install the left wing/fuselage fillet panel 2110C in accordance with FIGURE 3.
4. Remove the right wing/fuselage fillet panel 2210C in accordance with FIGURE 4 to get access to
the inspection area on the right side of the airplane.
5. RC - Do an Eddy Current, High Frequency (ETHF) inspection for any crack in the right side center
wing lower skin in accordance with FIGURE 5.
a. If any crack is found, contact The Boeing Company for inspection and repair instructions and
do the inspection and repair.
b. If no crack is found, repeat ETHF inspections for any crack in the right side center wing lower
skin in accordance with FIGURE 5.
6. Install the right wing/fuselage fillet panel 2210C in accordance with FIGURE 6.
7. Put the airplane back to a serviceable condition.
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### Page 24 (OCR)

BOEING SERVICE BULLETIN MD80-57A244
ALERT  ALERT
STA
883
TYPICAL
2481768
FIGURE 1: OPEN ACCESS - LEFT SIDE
(SHEET 1 OF 2)
Original Issue: March 03, 2016
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### Page 25

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one side of the airplane.
More DataQtyIdentificationNameTaskStep
Keep all of the fas-
teners.
1-PANELRemove / Keep1
FIGURE 1: OPEN ACCESS - LEFT SIDE
(SHEET 2 OF 2)
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### Page 26 (OCR)

BOEING SERVICE BULLETIN MD80-57A244
ALERT  ALERT
STA
883
TYPICAL
LA  2481875
FIGURE 2: INSPECTION - LEFT SIDE
(SHEET 1 OF 3)
Original Issue: March 03, 2016
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### Page 27 (OCR)

BOEING SERVICE BULLETIN MD80-57A244
ALERT  ALERT
S-17
S-16
BUTT
SPLICE
S-15
CENTER WING
LOWER SKIN
EXTERNAL
DOUBLER
FWD
VIEW LOOKING UP
2481884
FIGURE 2: INSPECTION - LEFT SIDE
(SHEET 2 OF 3)
Original Issue: March 03, 2016
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### Page 28

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one side of the airplane.
More DataQtyIdentificationNameTaskStep
(a)--LOWER WING SKINInspect1
(a) Do an ETHF inspection for any crack around each fastener head or nut in accordance with NDTSPM Part
06 Eddy Current: 06-10-01.001 (Procedure 1 - Surface Defect Detection).
Select DAC GSET AL.01 (Part 06-20-0, Figure 1, Sheets 1-3) and place a protruding head fastener (or
nonconductive facsimile) in either of the holes containing notches N3 or N4 so that 0.100-0.125 inches
of the notch extends out beyond the fastener head. Using calibration scan Method "K", place probe on
the reference standard surface and scan around the fastener head.
Using inspection scan Method "44", place probe on the lower wing skin surface adjacent to one of the
fasteners in the affected area and renull/balance the instrument. Scan around each affected fastener hole
using the head of the fastener as a guide to the probe.
FIGURE 2: INSPECTION - LEFT SIDE
(SHEET 3 OF 3)
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### Page 29 (OCR)

BOEING SERVICE BULLETIN MD80-57A244
ALERT  ALERT
STA
883
12
TYPICAL
2481886
FIGURE 3: CLOSE ACCESS - LEFT SIDE
(SHEET 1 OF 2)
Original Issue: March 03, 2016
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### Page 30

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one side of the airplane.
More DataQtyIdentificationNameTaskStep
Install with kept fas-
teners.
1-PANELInstall (Kept)1
(a)-PR-1828 or DMS 1819SEALANTApply2
(a) Apply sealant to the gap on three sides and smooth flush to the surrounding surfaces. Refer to MD-80
SRM 51-20-00 as an accepted procedure.
FIGURE 3: CLOSE ACCESS - LEFT SIDE
(SHEET 2 OF 2)
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### Page 31 (OCR)

BOEING SERVICE BULLETIN MD80-57A244
ALERT  ALERT
STA
883
TYPICAL
2481905
FIGURE 4: OPEN ACCESS - RIGHT SIDE
(SHEET 1 OF 2)
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### Page 32

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one side of the airplane.
More DataQtyIdentificationNameTaskStep
Keep all of the fas-
teners.
1-PANELRemove / Keep1
FIGURE 4: OPEN ACCESS - RIGHT SIDE
(SHEET 2 OF 2)
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### Page 33 (OCR)

BOEING SERVICE BULLETIN MD80-57A244
ALERT  ALERT
STA
883
TYPICAL
2481908
FIGURE 5: INSPECTION - RIGHT SIDE
(SHEET 1 OF 3)
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### Page 34 (OCR)

BOEING SERVICE BULLETIN MD80-57A244
ALERT  ALERT
S-17
S-16
BUTT
SPLICE
S-15
CENTER WING
LOWER SKIN
EXTERNAL
DOUBLER
VIEW LOOKING UP
B  2481909
FIGURE 5: INSPECTION - RIGHT SIDE
(SHEET 2 OF 3)
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### Page 35

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one side of the airplane.
More DataQtyIdentificationNameTaskStep
(a)--LOWER WING SKINInspect1
(a) Do an ETHF inspection for any crack around each fastener head or nut in accordance with NDTSPM Part
06 Eddy Current: 06-10-01.001 (Procedure 1 - Surface Defect Detection).
Select DAC GSET AL.01 (Part 06-20-0, Figure 1, Sheets 1-3) and place a protruding head fastener (or
nonconductive facsimile) in either of the holes containing notches N3 or N4 so that 0.100-0.125 inches
of the notch extends out beyond the fastener head. Using calibration scan Method "K", place probe on
the reference standard surface and scan around the fastener head.
Using inspection scan Method "44", place probe on the lower wing skin surface adjacent to one of the
fasteners in the affected area and renull/balance the instrument. Scan around each affected fastener hole
using the head of the fastener as a guide to the probe.
FIGURE 5: INSPECTION - RIGHT SIDE
(SHEET 3 OF 3)
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### Page 36 (OCR)

BOEING SERVICE BULLETIN MD80-57A244
ALERT  ALERT
TYPICAL
2481907
FIGURE 6: CLOSE ACCESS - RIGHT SIDE
(SHEET 1 OF 2)
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### Page 37

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one side of the airplane.
More DataQtyIdentificationNameTaskStep
Install with kept fas-
teners.
1-PANELInstall (Kept)1
(a)-PR-1828 or DMS 1819SEALANTApply2
(a) Apply sealant to the gap on three sides and smooth flush to the surrounding surfaces. Refer to MD-80
SRM 51-20-00 as an accepted procedure.
FIGURE 6: CLOSE ACCESS - RIGHT SIDE
(SHEET 2 OF 2)
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---
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