# Boeing Alert Service Bulletin 747-53A2854: No revision named

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### Page 1

Commercial 
Airplanes
747
Service Bulletin
ALERT
Number: 747-53A2854
Original Issue: September 17, 2012
ATA System: 5331
SUBJECT: FUSELAGE - Skin - Skin Panel Chem-Milled Pocket Inspection and Repair at Locations
Adjacent to Lap Splices
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 © 2012 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Unpublished Work.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, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and Boeing
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with this document unless provided in writing by Boeing. BOEING is a trademark of Boeing Management
Company.
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3.0

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Table of Contents
Summary ...................................................... 5
1. PLANNING INFORMATION ........................................ 9
A. Effectivity ................................................ 9
1. Airplanes ............................................. 9
2. Spares Affected ........................................ 1 0
B. Concurrent Requirements ...................................... 1 0
C. Reason ................................................ 1 0
D. Description .............................................. 1 1
E. Compliance .............................................. 1 1
F. Approval ............................................... 1 2
G. Manpower .............................................. 1 3
H. Weight and Balance Changes .................................... 1 3
I. Electrical Load Data ......................................... 1 3
J. References .............................................. 1 3
1. Existing Data: ......................................... 1 3
2. Data Supplied with this Service Bulletin: ........................... 1 4
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 4
K. Publications Affected ........................................ 1 4
L. Interchangeability and Intermixability of Parts ........................... 1 4
M. Software Accomplishment Summary ................................ 1 4
2. MATERIAL INFORMATION ........................................ 1 5
A. Material - Price and Availability ................................... 1 5
B. Industry Support Information .................................... 1 5
C. Parts Necessary for Each Airplane ................................. 1 5
1. Kits/Parts ............................................ 1 5
2. Parts and Materials Supplied by the Operator ........................ 1 5
3. Parts Modified and Reidentified ................................ 1 5
4. Parts Removed and Not Replaced .............................. 1 5
D. Parts Necessary to Change Spares ................................. 1 5
E. Special Tooling - Price and Availability ............................... 1 5
F. Special Tooling Necessary to do this Service Bulletin ....................... 1 5
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 1 7
A. GENERAL INFORMATION ..................................... 1 7
B. WORK INSTRUCTIONS ....................................... 1 7
FIGURE 1: SKIN INSPECTION IN SECTION 42, 44 AND 46 [Group 1] ................. 1 9
FIGURE 2: SKIN INSPECTION IN SECTION 42 [Group 2] ........................ 3 0
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Commercial 
Airplanes
747
Service Bulletin
ALERT
SummaryNumber: 747-53A2854Original Issue: September 17, 2012
ATA System: 5331
SUBJECT: FUSELAGE - Skin - Skin Panel Chem-Milled Pocket Inspection and Repair at Locations
Adjacent to Lap Splices
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 gives instructions to do inspections of the fuselage skin for cracks just above certain lap
splice locations. Skin cracks that are not found and repaired can become large and cause sudden loss of cabin
pressure and loss of structural integrity..
Two operators of Boeing 757 airplanes have reported cracking, on two airplanes, that initiated at multiple locations
on the inboard surface of the skin, along the edge of the chem-milled step just above the skin lap splice. No
cracking of this kind has been reported on 747 airplanes, but analysis by Boeing indicates that the 747 fuselage
skin in the areas shown in this service bulletin may be susceptible to similar cracking.
The related Boeing 757 service bulletin is 757-53-0097, "FUSELAGE - Skin - Crown Skin Panel - Station 297
to Station 439, Chem-Milled Step Above Stringer 4 Left and Stringer 4 Right Lap Joint - Inspection".
Accomplishment of the inspections in this service bulletin and installation of a repair will help prevent in-flight
depressurization of the airplane and ensure the structural integrity of the fuselage skin at certain chem-milled
skin locations.
The skin at the edge of chem-milled steps above certain skin lap splices has been determined to be structure
that is susceptible to Widespread Fatigue Damage (WFD). For more information about WFD, refer to
747-SL-53-088A.
Boeing Service Related Problem (SRP) 747-SRP-53-0396 is related to this service bulletin.
This table is provided to operators for planning purposes only. Refer to the applicable sections for more
information.
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ReferenceAffectedPlanning Data
Paragraph 1.A.2., Spares AffectedNoSpares Affected
Paragraph 1.E., ComplianceNoAD 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
NoOperator Supplied Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
ACTION
Get external access to the fuselage skin just above certain lap splice locations. Do external sliding probe eddy
current inspections at the affected locations for cracks. If no crack indications are found, put the airplane back
to a serviceable condition, and do the inspection again at the times given in this service bulletin. If crack indications
are found, contact Boeing for repair data and do the repair. After repair, put the airplane back to a serviceable
condition, and do the inspection again at the times given in this service bulletin.
EFFECTIVITY
747-100B SUD, 747-300 and 747SP Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected
airplanes.
COMPLIANCE
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the inspection and repair procedures given in this service bulletin.
MANPOWER
Elapsed HoursTotal Task HoursAirplanes
28.5056.50Group 1
5.2510.00Group 2
Refer to Paragraph 1.G., Manpower.
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### Page 7 (OCR)

BOEING SERVICE BULLETIN 747-53A2854
ALERT  ALERT
MATERIAL INFORMATION
None.
EDGE OF INTERNAL
CHEM-MILLED STEP
IN OVERLAPPING
SKIN
- STRINGER
A —
OVERLAPPING
SKIN
FWD  OVERLAPPED
SKIN
LAP SPLICE
(TYPICAL)
CHEM-MILLED
STEP
TYPICAL
CRACK
DO EXTERNAL SLIDING PROBE EDDY
CURRENT INSPECTIONS FOR CRACKS
AT THE CHEM-MILLED STEP. IF CRACK
INDICATIONS ARE FOUND, INSTALL A
REPAIR.
OVERLAPPED
/ SKIN
SKERLAPPING-
A-A  2148046
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Commercial 
Airplanes
747
Service Bulletin
ALERT
Number: 747-53A2854
Original Issue: September 17, 2012
ATA System: 5331
SUBJECT: FUSELAGE - Skin - Skin Panel Chem-Milled Pocket Inspection and Repair at Locations
Adjacent to Lap Splices
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
Refer to Service Bulletin Index D6-30300 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
This service bulletin is for the airplanes shown below.
DESCRIPTIONCONFIGURATIONGROUP
All 747SP airplanes.-1
747-100B SUD airplanes line number 636 and 655, and 747-300
airplanes line number 692 through 695.
-2
Airplane Models:
747-100B SUD, 747-300, 747SP
GroupVariable Number
1RG001 - RG009
1RG091
1RG095
1RG101 - RG104
1RG121 - RG126
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GroupVariable Number
1RG141 - RG142
1RG161 - RG164
1RG171 - RG174
1RG191 - RG193
1RG211 - RG213
1RG221 - RG222
1RH101 - RH102
1RH111 - RH112
1RH121 - RH122
2RS001 - RS002
2RS265 - RS268
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
This service bulletin gives instructions to do inspections of the fuselage skin for cracks just above
certain lap splice locations. Skin cracks that are not found and repaired can become large and cause
sudden loss of cabin pressure and loss of structural integrity..
Two operators of Boeing 757 airplanes have reported cracking, on two airplanes, that initiated at multiple
locations on the inboard surface of the skin, along the edge of the chem-milled step just above the skin
lap splice. No cracking of this kind has been reported on 747 airplanes, but analysis by Boeing indicates
that the 747 fuselage skin in the areas shown in this service bulletin may be susceptible to similar
cracking.
The related Boeing 757 service bulletin is 757-53-0097, "FUSELAGE - Skin - Crown Skin Panel - Station
297 to Station 439, Chem-Milled Step Above Stringer 4 Left and Stringer 4 Right Lap Joint - Inspection".
Accomplishment of the inspections in this service bulletin and installation of a repair will help prevent
in-flight depressurization of the airplane and ensure the structural integrity of the fuselage skin at certain
chem-milled skin locations.
The skin at the edge of chem-milled steps above certain skin lap splices has been determined to be
structure that is susceptible to Widespread Fatigue Damage (WFD). For more information about WFD,
refer to 747-SL-53-088A.
Boeing Service Related Problem (SRP) 747-SRP-53-0396 is related to this service bulletin.
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D. Description
Get external access to the fuselage skin just above certain lap splice locations. Do external sliding
probe eddy current inspections at the affected locations for cracks. If no crack indications are found,
put the airplane back to a serviceable condition, and do the inspection again at the times given in this
service bulletin. If crack indications are found, contact Boeing for repair data and do the repair. After
repair, put the airplane back to a serviceable condition, and do the inspection again at the times given
in this service bulletin.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1:
Affected Maintenance Zones
ZoneModel
122, 147, 148, 241, 242747SP
Group 2:
Affected Maintenance Zones
ZoneModel
225, 226747-100B SUD, 747-300
E. Compliance
Accomplish the required actions, based on the applicable conditions in Table 1, in accordance with
Paragraph 3. Accomplishment Instructions.
Group 1:
Table 1: Skin Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 500
flight-cycles or
one year after
the original is-
sue date of this
service bulletin,
whichever oc-
curs later.
Before 18,500
total flight-cy-
cles
Do an external sliding
probe eddy current in-
spections for cracking in
accordance with Para-
graph 3.B., Work Instruc-
tions.
All airplanes
-Before further flightContact Boeing for repair
data and do the repair.
Any cracking found
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Group 1:
Table 1: Skin Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
500 flight-cyclesWithin 500 flight-cycles after the
previous inspection.
Do external sliding probe
eddy current inspections
for cracking in unrepaired
areas in accordance with
Paragraph 3.B., Work In-
structions.
No cracking found
Group 2:
Table 2: Skin Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 800
flight-cycles or
one year after
the original is-
sue date of this
service bulletin,
whichever oc-
curs later.
Before 18,500
total flight-cy-
cles
Do an external sliding
probe eddy current in-
spections for cracking in
accordance with Para-
graph 3.B., Work Instruc-
tions.
All airplanes
-Before further flightContact Boeing for repair
data and do the repair.
Any cracking found
800 flight-cyclesWithin 800 flight-cycles after the
previous inspection.
Do external sliding probe
eddy current inspections
for cracking in unrepaired
areas in accordance with
Paragraph 3.B., Work In-
structions.
No cracking found
F. Approval
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified
in this service bulletin comply with the applicable regulations and are FAA approved, as well as European
Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved
airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on
the airplane in its original Boeing delivery configuration or as modified by other approved Boeing
changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
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G. Manpower
The table below shows an estimate of the task hours necessary to do 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.
Group 1:
Table 1 - Skin Inspection in Section 42, 44 and 46
Elapsed HoursTask HoursNumber of PersonsTask
0.500.501Prepare
28.0056.002Inspect (Figure 1)
28.5056.50TOTAL FOR EACH AIRPLANE
Group 2:
Table 2 - Skin Inspection in Section 42
Elapsed HoursTask HoursNumber of PersonsTask
0.500.501Prepare
4.759.502Inspect (Figure 2)
5.2510.00TOTAL FOR EACH AIRPLANE
NOTE: More time will be required for repairs if cracks are found.
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not applicable.
J. References
1. Existing Data:
a. Boeing Service Bulletin 757-53-0097
b. Boeing Service Letter 747-SL-51-048, 747-SL-53-088A
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c. Boeing Service Related Problem (SRP) 747-SRP-53-0396
d. Service Bulletin Index D6-30300
e. 747 Non-Destructive Testing (NDT) Manual Part 6, 53-30-25
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
Skin Panel Instl - STA 741.1 to STA 1000.0 Stgr 6 to Stgr 1265B04112
Skin Panel Instl - STA 520 to STA 1000 S-23R to S-34R65B18625
Skin Panel Instl - STA 1000 to STA 1200.0, Stgr 6 to Stgr 1265B18631
The table above lists applicable drawings used to prepare this service bulletin. The drawings are
not necessary to make the specified changes, and are not supplied with this service bulletin. The
drawings may not be applicable to all airplane configurations or operators.
K. Publications Affected
1. Publications:
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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2.    MATERIAL INFORMATION
A. Material - Price and Availability
None.
B. Industry Support Information
Boeing warranty remedies are not available for the inspection and repair procedures given in this
service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts
None.
2. Parts and Materials Supplied by the Operator
None.
3. Parts Modified and Reidentified
None.
4. Parts Removed and Not Replaced
None.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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### Page 17

3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
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. Obey all of the warnings and cautions given in the specified manual sections.
3. 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
4. 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.
5. Boeing Service Letter 747-SL-51-048, Damage Reporting and Repair Plan/Design
Guidelines, is an acceptable procedure to request information from Boeing for
additional structural repair instructions. The Service Letter describes what information
must be provided to Boeing before a structural repair can be provided.
6. The instructions in Paragraph 3.B., Work Instructions and the figures can include
operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated
Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing
Index contain data on versions of the tools or test equipment that you can use. It is
permitted to use replaced tools. It is not permitted to use superseded tools.
7. 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.
B. WORK INSTRUCTIONS
Group 1:
SKIN INSPECTION
1. Get external access and do external sliding probe eddy current inspections for cracking in
accordance with FIGURE 1.
NOTE: If any part of the inspection area is covered by an external doubler, contact Boeing for
inspection instructions.
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### Page 18

2. If any cracking is found, contact Boeing for repair data and do the repair.
3. Put the airplane back in a serviceable condition. Do the external sliding probe eddy current
inspections again in all affected unrepaired areas at the time given in Paragraph 1.E., Compliance,
Table 1.
Group 2:
SKIN INSPECTION
1. Get external access and do external sliding probe eddy current inspections for cracking in
accordance with FIGURE 2.
NOTE: If any part of the inspection area is covered by an external doubler, contact Boeing for
inspection instructions.
2. If any cracking is found, contact Boeing for repair data and do the repair.
3. Put the airplane back in a serviceable condition. Do the external sliding probe eddy current
inspections again in all affected unrepaired areas at the time given in Paragraph 1.E., Compliance,
Table 2.
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### Page 19 (OCR)

BOEING SERVICE BULLETIN 747-53A2854
ALERT  ALERT
This Figure applies only to: Group 1.
STA
1000
STA  STA  STA  1200  STA  STA
135  520  800  1350
STA
1240
- S-4L
S-12L
STA
2140
STA  STA  STA  SIA  STA
1350  1740  1961  2084  2360
• S-4L
- S-12L
- S-46L
S-40L -
S-46L -
2147405
FIGURE 1: SKIN INSPECTION IN SECTION 42, 44 AND 46
(SHEET 1 OF 11)
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### Page 20 (OCR)

BOEING SERVICE BULLETIN 747-53A2854
ALERT  ALERT
STA
1000
STA
STA  1200  STA  STA  STA
1350  800  520  135
STA
1240
S-4R -
S-12R -
S-34R -
S-39R -
S-44R
STA  780  C
D
STA
2140  E
2360  STA  2084  STA  1961  STA  1740  STA  1350  STA
S-4R
S-12R
S-46R
- S-40R
- S-46R
2147412
FIGURE 1: SKIN INSPECTION IN SECTION 42, 44 AND 46
(SHEET 2 OF 11)
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Work - See page 1 for details.  20 of 33

### Page 21 (OCR)

BOEING SERVICE BULLETIN 747-53A2854
ALERT  ALERT
STA
1000
STA  STA  STA  STA  STA  STA
800  1020  1040  1060  1080  1100
STA  STA  STA  STA  STA  STA
1100  1120  1140  1160  1180  1199.0
S-12-
FWD
LEFT SIDE SHOWN
RIGHT SIDE OPPOSITE
2177132
FIGURE 1: SKIN INSPECTION IN SECTION 42, 44 AND 46
(SHEET 3 OF 11)
Original Issue: September 17, 2012
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  747-53A2854
Work - See page 1 for details.  21 of 33

### Page 22 (OCR)

BOEING SERVICE BULLETIN 747-53A2854
ALERT  ALERT
STA  STA  STA  STA  STA  STA
1961.10  1980  2000  2020  2040  2062
- S-46
STA
STA  STA  2360
STA  2104
2062  2084
- S-46
FWD  LEFT SIDE SHOWN
RIGHT SIDE OPPOSITE
2177853
FIGURE 1: SKIN INSPECTION IN SECTION 42, 44 AND 46
(SHEET 4 OF 11)
Original Issue: September 17, 2012
Export Controlled ECCN: 9E991 - BOEING  747-53A2854
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  22 of 33

### Page 23 (OCR)

BOEING SERVICE BULLETIN 747-53A2854
ALERT  ALERT
STA  VIS  STA
560  540  520
— S-34
RIGHT SIDE ONLY
FWD
STA  SIA  SIA  STA  STA
780  760  740  700  680
S-34
RIGHT SIDE ONLY
2177987
FIGURE 1: SKIN INSPECTION IN SECTION 42, 44 AND 46
(SHEET 5 OF 11)
Original Issue: September 17, 2012
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  747-53A2854
Work - See page 1 for details.  23 of 33

### Page 24

FIGURE 1: SKIN INSPECTION IN SECTION 42, 44 AND 46
(SHEET 6 OF 11)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: September 17, 2012
747-53A2854
24 of 33
BOEING SERVICE BULLETIN 747-53A2854
ALERTALERT

### Page 25 (OCR)

BOEING SERVICE BULLETIN 747-53A2854
ALERT  ALERT
EDGE OF INTERNAL
1 CHEM-MILLED STEP
IN OVERLAPPING SKIN
3.01  - S-12L
OVERLAPPING
SKIN
OVERLAPPED
TYPICAL  SKIN
EDGE OF INTERNAL
CHEM-MILLED STEP
IN OVERLAPPING SKIN
2.90
2.78  - S-46L
OVERLAPPING
SKIN
FWD  OVERLAPPED
TYPICAL  SKIN
G  2148076
FIGURE 1: SKIN INSPECTION IN SECTION 42, 44 AND 46
(SHEET 7 OF 11)
Original Issue: September 17, 2012
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  747-53A2854
Work - See page 1 for details.  25 of 33

### Page 26 (OCR)

BOEING SERVICE BULLETIN 747-53A2854
ALERT  ALERT
EDGE OF INTERNAL
1) CHEM-MILLED STEP
IN OVERLAPPING SKIN
3.20
3.10  - S-34R
• 0
OVERLAPPING
SKIN
OVERLAPPED
SKIN
TYPICAL
CHEM-MILLED
' STEP
OVERLAPPED
SKIN
OVERLAPPING
SKIN
A-A  2148142
FIGURE 1: SKIN INSPECTION IN SECTION 42, 44 AND 46
(SHEET 8 OF 11)
Original Issue: September 17, 2012
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  747-53A2854
Work - See page 1 for details.  26 of 33

### Page 27 (OCR)

BOEING SERVICE BULLETIN 747-53A2854
ALERT  ALERT
EDGE OF  FORWARD  CARGO DOOR  CUTOUT  S-33R  OVERLAPPED  OVERLAPPED
SKIN  CHEM-MILLED  SKIN
STEP
EDGE OF INTERNAL  CHEM-MILLED STEP IN  OVERLAPPING  OVERLAPPING  SKIN  OVERLAPPING -  SKIN
2.96  2.86  RIGHT SIDE ONLY
OVERLAPPING SKIN  VIS  08L
6.15  7.15  FWD
2147505
FIGURE 1: SKIN INSPECTION IN SECTION 42, 44 AND 46
(SHEET 9 OF 11)
Original Issue: September 17, 2012
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  747-53A2854
Work - See page 1 for details.  27 of 33

### Page 28 (OCR)

BOEING SERVICE BULLETIN 747-53A2854
ALERT  ALERT
EDGE OF INTERNAL
1) CHEM-MILLED STEP
IN OVERLAPPING SKIN
2.90
2.80  - S-12L
OVERLAPPING
SKIN
OVERLAPPED
SKIN
TYPICAL
CHEM-MILLED
' STEP
OVERLAPPED
SKIN
OVERLAPPING
SKIN
C-C
FIGURE 1: SKIN INSPECTION IN SECTION 42, 44 AND 46
(SHEET 10 OF 11)
Original Issue: September 17, 2012
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  747-53A2854
Work - See page 1 for details.  28 of 33

### Page 29

The step number shown below agrees with the number shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
Do external sliding
probe eddy current
inspections of the
skin for cracks just
above the upper row
of fasteners in the
affected lap joint in
accordance with 747
NDT Part 6, 53-30-
25.
--SkinInspect1
FIGURE 1: SKIN INSPECTION IN SECTION 42, 44 AND 46
(SHEET 11 OF 11)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: September 17, 2012
747-53A2854
29 of 33
BOEING SERVICE BULLETIN 747-53A2854
ALERTALERT

### Page 30 (OCR)

BOEING SERVICE BULLETIN 747-53A2854
ALERT  ALERT
This Figure applies only to: Group 2.
STA  STA  STA  STA
135  520  740  880  1000  STA  1220  STA  1350  STA
- S-4L
- S-12L
0000000
LEFT SIDE
STA  STA  STA  STA  STA
STA  STA  1000  880  740  520  135
1350  1220
S-4R -
S-12R •
0000000  0 0
RIGHT SIDE
2148160
FIGURE 2: SKIN INSPECTION IN SECTION 42
(SHEET 1 OF 4)
Original Issue: September 17, 2012
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright @ Unpublished
Work - See page 1 for details.  30 of 33

### Page 31

FIGURE 2: SKIN INSPECTION IN SECTION 42
(SHEET 2 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: September 17, 2012
747-53A2854
31 of 33
BOEING SERVICE BULLETIN 747-53A2854
ALERTALERT

### Page 32 (OCR)

BOEING SERVICE BULLETIN 747-53A2854
ALERT  ALERT
EDGE OF INTERNAL
1 CHEM-MILLED STEP
IN OVERLAPPING SKIN
3.27
3.17  - S-12L
OVERLAPPING
SKIN
FWD
OVERLAPPED
TYPICAL  SKIN
B
CHEM-MILLED
STEP
- OVERLAPPED
SKIN
OVERLAPPING •
SKIN
A-A
FIGURE 2: SKIN INSPECTION IN SECTION 42
(SHEET 3 OF 4)
Original Issue: September 17, 2012
Export Controlled ECCN: 9E991 - BOEING  747-53A2854
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  32 of 33

### Page 33

The step number shown below agrees with the number shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
Do external sliding
probe eddy current
inspections of the
skin for cracks just
above the upper row
of fasteners in the
affected lap joint in
accordance with 747
NDT Part 6, 53-30-
25.
--SkinInspect1
FIGURE 2: SKIN INSPECTION IN SECTION 42
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: September 17, 2012
747-53A2854
33 of 33
BOEING SERVICE BULLETIN 747-53A2854
ALERTALERT

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