# Boeing Alert Service Bulletin 747-53A2844: Revision 1

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- Document: [Boeing Alert Service Bulletin 747-53A2844](https://openairdocs.org/service-documents/boeing/747-53a2844.md)
- Title as filed: U.S. DOT/FAA - Boeing Service Bulletin
- Pages: 41
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## Text

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### Page 1

Commercial 
Airplanes
747
Service Bulletin
ALERT
Number: 747-53A2844
Original Issue: September 15, 2011
Revision 1: July 30, 2012
ATA System: 5300
SUBJECT: FUSELAGE - Station 1920 Splice Clip Fasteners Inspection
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 © 2011 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Unpublished Work.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
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. BOEING is a trademark of Boeing Management
Company.
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1 of 41
3.0

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Table of Contents
Revision Transmittal Sheet ............................................ 5
Summary ...................................................... 7
1. PLANNING INFORMATION ........................................ 1 1
A. Effectivity ............................................... 1 1
1. Airplanes ............................................ 1 1
2. Spares Affected ........................................ 1 2
B. Concurrent Requirements ...................................... 1 2
C. Reason ................................................ 1 2
D. Description .............................................. 1 2
E. Compliance .............................................. 1 3
F. Approval ............................................... 1 6
G. Manpower .............................................. 1 6
H. Weight and Balance Changes .................................... 1 7
I. Electrical Load Data ......................................... 1 7
J. References .............................................. 1 7
1. Existing Data: ......................................... 1 7
2. Data Supplied with this Service Bulletin: ........................... 1 7
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 8
K. Publications Affected ........................................ 1 8
L. Interchangeability and Intermixability of Parts ........................... 1 8
M. Software Accomplishment Summary ................................ 1 8
2. MATERIAL INFORMATION ........................................ 1 9
A. Material - Price and Availability ................................... 1 9
B. Industry Support Information .................................... 1 9
C. Parts Necessary for Each Airplane ................................. 1 9
1. Kits/Parts ............................................ 1 9
2. Parts and Materials Supplied by the Operator ........................ 1 9
3. Parts Modified and Reidentified ................................ 1 9
4. Parts Removed and Not Replaced .............................. 1 9
D. Parts Necessary to Change Spares ................................. 1 9
E. Special Tooling - Price and Availability ............................... 1 9
F. Special Tooling Necessary to do this Service Bulletin ....................... 2 0
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 1
A. GENERAL INFORMATION ..................................... 2 1
B. WORK INSTRUCTIONS ....................................... 2 2
FIGURE 1: SPLICE CLIP 65B17957-3 FASTENER INSTALLATION - INSPECTION .......... 2 4
FIGURE 2: INSPECTIONS AT BODY STATION 1920 AND STRINGER 4L ............... 3 0
FIGURE 3: AUX SILL OUTER CHORD TEE - INSPECTION ....................... 3 4
FIGURE 4: SPLICE ANGLE FASTENER - INSTALLATION ....................... 3 7
FIGURE 5: TYPICAL CRACK REMOVAL ................................. 4 0
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Commercial 
Airplanes
747
Service Bulletin
ALERT
Revision Transmittal SheetNumber: 747-53A2844Original Issue: September 15, 2011
Revision 1: July 30, 2012
ATA System: 5300
SUBJECT: FUSELAGE - Station 1920 Splice Clip Fasteners Inspection
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
No more work is necessary on the airplane(s) changed in accordance with the original issue of this service
bulletin.
REASON FOR REVISION
This revision is sent to clarify the Work Instructions, Figures and Step Table to be consistent with the information
in the Compliance Paragraph.
Illustrations have been changed in the Summary Art and Figures to meet current standards and added view
callouts for clarity.
These sections were changed:
1. In Paragraph 1.D., Description, changed 3.d.
2. Added Paragraph 1.M., Software Accomplishment Summary.
3. In Paragraph 3.B., Work Instructions, changed 4.a.(4).
4. In Figure 2, changed as follows:
a. Changed sheet 2 to add bubble 5.
b. Changed Step Table to add step 5 and foot note (e).
5. In Figure 3, changed sheet 3, to remove bubble 3 to match Step Table.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location
of important changes.
Pages with no vertical lines have no important changes.
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REVISION HISTORY
September 15, 2011Original Issue:
July 30, 2012Revision 1:
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Commercial 
Airplanes
747
Service Bulletin
ALERT
SummaryNumber: 747-53A2844Original Issue: September 15, 2011
Revision 1: July 30, 2012
ATA System: 5300
SUBJECT: FUSELAGE - Station 1920 Splice Clip Fasteners Inspection
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
An airplane that was undergoing Boeing Converted Freighter conversion was missing fasteners on the Station
1920 Splice Clip as part of the new converted components. This discrepancy was found after 23 aircraft had
been delivered and the possibility of this discrepancy exists on already delivered airplanes. A one time inspection
of the station 1920 splice clip will determine if the fasteners are missing, and installation of fasteners is required.
Installation of the missing fasteners, if required will restore structural integrity and minimize the possibility of
crack growth. If not corrected, undetected missing fasteners at the station 1920 splice clip and possible crack
growth can potentially lead to a significant loss of load carrying capacity of the structural detail resulting in the
inability to sustain limit load or potentially result in a decompression event.
ACTION
This service bulletin provides instructions to do as follows:
1. Do General Visual Inspection (GVI) of the station 1920 Splice Clip for correct fastener installation and
do the work that follows based on conditions found:
2. Condition 1 - Correct Fasteners Installed:
a. No further work require.
3. Condition 2 - Incorrect Fasteners Found OR Condition 3 - No Fasteners Found:
a. Do a Detailed Inspection (DI) of Frame 1920 Inboard Chord Splice Angle and the parts attached
to the angle for any crack.
b. Do a DI of the cutout hole in the Sill Web and the attached parts for any crack.
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c. Do a General Visual Inspection (GVI) of the Shear Tie and its fasteners for any crack.
d. Do a DI of the Shear Clip, Aux Sill Outer Chord Tee and the Splice Angle and their fasteners for
any crack.
e. Do Surface High Frequency Eddy Current (HFEC) inspection of the Radii of the Tee along 5" either
side of Frame at station 1920 for cracks.
f. Do Surface HFEC inspection around fastener heads common to the Tee for cracks.
4. Condition 4 - No Crack Found:
a. Install fasteners of the Splice Angle.
5. Condition 5 - Any Crack Found:
a. Remove any crack found.
b. Repair in accordance with Structural Repair Manual (SRM).
c. Do open hole HFEC inspections of all fasteners common to the repair(s) for cracks. If any crack
found, repair in accordance with Structural Repair Manual (SRM).
d. Install fasteners of the Splice Angle.
EFFECTIVITY
747-400 Airplane(s). Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s).
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 available for airplanes in warranty as of 11/19/2007. Please refer to Paragraph
2.B., Industry Support Information.
MANPOWER
Elapsed HoursTotal Task HoursAirplanes
5.05.0747-400
MATERIAL INFORMATION
Operator Supplied Parts/Materials.
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BOEING SERVICE BULLETIN 747-53A2844
ALERT  ALERT
Refer to Paragraph 2.A., Material - Price and Availability
STA
1920
S-4L
STA
1920
STATION 1920 SPLICE CLIP FASTENERS INSPECTION  2062270
Original Issue: September 15, 2011
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Commercial 
Airplanes
747
Service Bulletin
ALERT
Number: 747-53A2844
Original Issue: September 15, 2011
Revision 1: July 30, 2012
ATA System: 5300
SUBJECT: FUSELAGE - Station 1920 Splice Clip Fasteners Inspection
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 Document D6-30300 Part 3 for Airplane Variable Number, Line
Number, and Serial Number data.
This service bulletin is for the airplane(s) shown below.
DESCRIPTIONCONFIGURATIONGROUP
747-400 airplanes that are Boeing Converted Freightters (BCF)-1
Airplane Models:
747-400
GroupVariable Number
1RT456
1RT501
1RT506 - RT510
1RT513
1RT516
1RT518
1RT520
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GroupVariable Number
1RT528
1RT572 - RT575
1RT655 - RT657
1RT751
1RT781 - RT782
1RT967
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
An airplane that was undergoing Boeing Converted Freighter conversion was missing fasteners on the
Station 1920 Splice Clip as part of the new converted components. This discrepancy was found after
23 aircraft had been delivered and the possibility of this discrepancy exists on already delivered airplanes.
A one time inspection of the station 1920 splice clip will determine if the fasteners are missing, and
installation of fasteners is required. Installation of the missing fasteners, if required will restore structural
integrity and minimize the possibility of crack growth. If not corrected, undetected missing fasteners at
the station 1920 splice clip and possible crack growth can potentially lead to a significant loss of load
carrying capacity of the structural detail resulting in the inability to sustain limit load or potentially result
in a decompression event.
Revision 1 is sent to clarify the Work Instructions, Figures and Step Table to be consistent with the
information in the Compliance Paragraph.
Illustrations have been changed in the Summary Art and Figures to meet current standards and added
view callouts for clarity.
D. Description
This service bulletin provides instructions to do as follows:
1. Do General Visual Inspection (GVI) of the station 1920 Splice Clip for correct fastener installation
and do the work that follows based on conditions found:
2. Condition 1 - Correct Fasteners Installed:
a. No further work require.
3. Condition 2 - Incorrect Fasteners Found OR Condition 3 - No Fasteners Found:
a. Do a Detailed Inspection (DI) of Frame 1920 Inboard Chord Splice Angle and the parts attached
to the angle for any crack.
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b. Do a DI of the cutout hole in the Sill Web and the attached parts for any crack.
c. Do a General Visual Inspection (GVI) of the Shear Tie and its fasteners for any crack.
d. Do a DI of the Shear Clip, Aux Sill Outer Chord Tee and the Splice Angle and their fasteners
for any crack.
e. Do Surface High Frequency Eddy Current (HFEC) inspection of the Radii of the Tee along 5"
either side of Frame at station 1920 for cracks.
f. Do Surface HFEC inspection around fastener heads common to the Tee for cracks.
4. Condition 4 - No Crack Found:
a. Install fasteners of the Splice Angle.
5. Condition 5 - Any Crack Found:
a. Remove any crack found.
b. Repair in accordance with Structural Repair Manual (SRM).
c. Do open hole HFEC inspections of all fasteners common to the repair(s) for cracks. If any
crack found, repair in accordance with Structural Repair Manual (SRM).
d. Install fasteners of the Splice Angle.
Revision 1 - No more work is necessary on the airplane(s) changed in accordance with the original
issue of this service bulletin.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
263747-400
E. Compliance
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to
this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this
service bulletin mandatory.
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Table No. 1 - Station 1920 Splice Clip Fastener Inspection
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever occurs later)
ActionCondition
-Within 8,000 flight cycles
after completion of freighter
modification.
Do a General Visual Inspection
(GVI) for correct fastener installa-
tion in accordance with Paragraph
3.B., Work Instructions, Step 2.
All Airplanes
Or
Within 250 flight cycles af-
ter the original issue date
of the service bulletin.
--No further work required in accor-
dance with Paragraph 3.B., Work
Instructions, Step 3.
Condition 1
(Correct fasteners
installed)
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Table No. 1 - Station 1920 Splice Clip Fastener Inspection
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever occurs later)
ActionCondition
-Before further flight.Do the 7 inspections for cracks as
follows in accordance with Para-
graph 3.B., Work Instructions,
Step 4.
Condition 2
(Incorrect Fasteners In-
stalled)
Or
AndCondition 3
Do the work of condition 4 if no
crack found or do the work of
condition 5 if any crack found.
(No fasteners installed)
1) Do a Detailed Inspection of
Frame 1920 Inboard Chord Splice
Angle and the parts attached to
the angle.
And
2) Do a Detailed Inspection of the
cutout hole in the Sill Web and
the attached parts.
And
3) Do a General Visual Inspection
of the Shear Tie and its fasteners.
And
4) Do a Detailed Inspection of the
Shear Clip and the Splice Angle
and their fasteners.
And
5) Do a Detailed Inspection of the
Aux Sill Outer Chord Tee and at-
tached parts.
And
6) Do Surface High Frequency
Eddy Current (HFEC) inspection
of the Radii of the Tee along 5"
either side of Frame at station
1920 using a transverse scan to
look for cracks.
And
7) Do Surface HFEC inspection
around fastener heads common
to the Tee for cracks.
Before further flight.Condition 4
(No crack found)
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Table No. 1 - Station 1920 Splice Clip Fastener Inspection
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever occurs later)
ActionCondition
Install fasteners of the Splice An-
gle in accordance with Paragraph
3.B., Work Instructions, Step 5.
-Before further flight.Do the work that follows in accor-
dance with Paragraph 3.B., Work
Instructions, Step 6.
Condition 5
(Any crack found)
1) Remove any crack found.
And
2) Repair as applicable.
And
3) Do open hole HFEC inspec-
tions of all fasteners common to
the repair(s) for cracks.
If any crack found, repair as appli-
cable.
And
4) Install fasteners of the Splice
Angle (65B17957-3).
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.
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
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 Time to make the parts
 Time to find the tools.
Elapsed HoursTask HoursNumber of PersonsTask
0.500.501Open Access
0.250.251FIGURE 1
0.750.751FIGURE 2
1.501.501FIGURE 3
1.501.501FIGURE 4
1.251.251FIGURE 5 (a)
0.500.501Close Access
5.005.00TOTAL FOR EACH AIRPLANE
(a) Estimate given in figure 5 is for a typical crack removal and is not included in
total shown. Times number of typical cracks to be removed by estimate given
to arrive at revised total.
H. Weight and Balance Changes
1. If no fastener changes are required:
None.
2. If maximum number of fastener are added:
Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)Airplane
+1304+ 0.7747-400
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. 747 Non-Destructive Testing (NDT) Manual Part 6, 51-00-00
b. 747-400 Aircraft Maintenance Manual (AMM) 25-59-00
c. 747-400SF Structural Repair Manual (SRM) 51-40-02, 51-70-12, 51-70-13, 53-00-01
2. Data Supplied with this Service Bulletin:
None.
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3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
Upper Panel Assembly - End Item, Freighter814B6801
This drawing were used to prepare this service bulletin. This drawing are not necessary to make
the specified changes, and are not supplied with this service bulletin. These drawings may not be
applicable to all airplane configurations or operators.
K. Publications Affected
1. Publications:
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 available for 747-400 airplanes in warranty as of 11/19/2007. For
inspection task hour reimbursement for airplanes in warranty as of that date, send a warranty claim to
Boeing Commercial Airplanes Group - Warranties. If the condition described in this service bulletin is
found during the inspection for airplanes in warranty as of that date and additional task hours and parts
are required, send a warranty claim to Boeing Commercial Airplanes Group - Warranties. Please refer
to this service bulletin number and reference the airplane variable numbers in your purchase order.
C. Parts Necessary for Each Airplane
1. Kits/Parts
None.
2. Parts and Materials Supplied by the Operator
NotesNameQTYPart Number /
Specification
(a)HI-LOK7BACB30NX8K9
(a)HI-LOK2BACB30NX10K9
(a)COLLAR7BACC30BH8
(a)COLLAR2BACC30BH10
(a) 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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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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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
– 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 and fasteners are in Structural Repair
Manual (SRM) Chapter 51
– Torque limits to tighten nuts and bolts are in SRM Chapter 51
4. Use the approved fastener and process material substitutions in accordance with
SRM Chapter 51. Alternate fasteners are listed in SRM Chapter 51.
5. If the length of any fastener specified in this service bulletin does not meet installation
standards given in 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.
6. A Detailed Inspection (DI) is defined as: An intensive examination of a specific item,
installation, or assembly to detect damage, failure, or irregularity. Available lighting
is normally supplemented with a direct source of good lighting at an intensity deemed
appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be
necessary. Surface cleaning and elaborate procedures may be required.
7. A General Visual Inspection (GVI) is defined as: A visual examination of an interior
or exterior area, installation or assembly to detect obvious damage, failure or
irregularity. This level of inspection is made from within touching distance unless
otherwise specified. A mirror may be necessary to enhance visual access to all
exposed surfaces in the inspection area. This level of inspection is made under
normally available lighting conditions such as daylight, hangar lighting, flashlight or
drop-light and may require removal or opening of access panels or doors. Stands,
ladders or platforms may be required to gain proximity to the area being checked.
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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. 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.
10. 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.
11. 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.
The removed part can be discarded if a new or serviceable part is installed.
B. WORK INSTRUCTIONS
Splice Clip 65B17957-3 Fastener Installation - Inspection
1. Remove and keep the cargo liner and insulation blanket on the Main Deck door surround to gain
access to the Auxiliary Sill at stringer 4L at STA 1920, WL 350, LBL 30. Refer to 747-400 AMM
25-59-00 as an accepted procedure.
2. Do a General Visual Inspection (GVI) of the 65B17957-3 Splice Clip common to the 65B17669-47
Aux Sill Web and the 65B17669-606 Tie Clip for correct fastener installation in accordance with
FIGURE 1 and do the work that follows based on conditions found:
3. Condition 1 - Correct Fasteners Installed:
a. No further work required. Go to step 7.
4. Condition 2 - Incorrect Fasteners Installed OR Condition 3 - No Fasteners Found:
a. Do the following inspections for cracks in accordance with FIGURE 2.
(1) Do a Detailed Inspection (DI) of Frame 1920 Inboard Chord Splice Angle (69B15483-2)
and the parts attached to the angle.
(2) Do a DI of the cutout hole in the Sill Web (65B17669-47) and the attached parts.
(3) Do a General Visual Inspection (GVI) of the Shear Tie (69B18157-1) and its fasteners.
(4) Do a DI of the Shear Clip (65B17665-69) and the Splice Angle (65B17665-62) and their
fasteners and do a DI of the Aux Sill Outer Chord Tee (65B17829-1) and attached parts.
b. Do the following inspections accordance with FIGURE 3.
(1) Do Surface High Frequency Eddy Current (HFEC) inspection of the Radii of the Tee along
5" either side of Frame at station 1920 using a transverse scan to look for cracks.
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### Page 23

(2) Do Surface HFEC inspection around fastener heads common to the Tee along 5" each
side of Frame at station 1920 to look for cracks.
c. Based on condition found from the inspections (steps 4.a and 4.b) do the work of step 5 or
step 6.
5. Condition 4 - No Crack Found:
a. Install fasteners of the Splice Angle (65B17957-3) accordance with FIGURE 4. Refer to
747-400SF SRM 51-40-02 as an accepted procedure.
b. Go to step 7.
6. Condition 5 - Any Crack Found:
a. Remove any crack found in accordance with 747-400SF SRM 53-00-01 Figure 201, Repair
16 and 747-400SF SRM 51-70-12, 747-400SF SRM 51-70-13 and FIGURE 5.
For any crack found at a fastener hole, remove crack in accordance with 747-400SF SRM
51-10-02 Paragraph 11.B.3.b and Paragraph 11.B.4.
b. Repair as applicable in accordance with 747-400SF SRM 53-00-01 Figure 201, Repair 16,
and 747-400SF SRM 51-70-12, 747-400SF SRM 51-70-13.
c. Do open hole HFEC inspections of all fasteners common to the repair(s) for cracks. Refer to
747 NDT Part 6, 51-00-00, Figure 1 as an acceptable procedure. If any crack found, do as
follows:
(1) Remove any crack found in accordance with 747-400SF SRM 53-00-01 Figure 201,
Repair 16 and 747-400SF SRM 51-70-12, 747-400SF SRM 51-70-13 and FIGURE 5.
For any crack found at a fastener hole, remove crack in accordance with 747-400SF SRM
51-10-02 Paragraph 11.B.3.b and Paragraph 11.B.4.
(2) Repair as applicable in accordance with 747-400SF SRM 53-00-01 Figure 201, Repair
16, and 747-400SF SRM 51-70-12, 747-400SF SRM 51-70-13.
d. Install fasteners of the Splice Angle (65B17957-3) accordance with FIGURE 4. Refer to
747-400SF SRM 51-40-02 as an accepted procedure.
7. Install kept cargo liner and insulation blanket on the Main Deck door surround, removed to gain
access to the Auxiliary Sill at stringer 4L at STA 1920, WL 350, LBL 30. Refer to 747-400 AMM
25-59-00 as an accepted procedure.
8. Put the airplane back to a serviceable condition.
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BOEING SERVICE BULLETIN 747-53A2844
ALERT  ALERT
STA
1920
S-4L
> A 1520  STA
B
B FASTENER PATTERN 1
C FASTENER PATTERN 2
D FASTENER PATTERN 3
2048452
FIGURE 1: SPLICE CLIP 65B17957-3 FASTENER INSTALLATION - INSPECTION
(SHEET 1 OF 6)
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### Page 25 (OCR)

BOEING SERVICE BULLETIN 747-53A2844
ALERT  ALERT
STA
1920
+
+
FWD
A-A  2048458
FIGURE 1: SPLICE CLIP 65B17957-3 FASTENER INSTALLATION - INSPECTION
(SHEET 2 OF 6)
Original Issue: September 15, 2011
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Work - See page 1 for details.  25 of 41

### Page 26 (OCR)

BOEING SERVICE BULLETIN 747-53A2844
ALERT  ALERT
STA
1920
FWD
FASTENER PATTERN 1
B-B  2050226
FIGURE 1: SPLICE CLIP 65B17957-3 FASTENER INSTALLATION - INSPECTION
(SHEET 3 OF 6)
Original Issue: September 15, 2011
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### Page 27 (OCR)

BOEING SERVICE BULLETIN 747-53A2844
ALERT  ALERT
STA
1920
#*#####
FWD
FASTENER PATTERN 2
C-C  2050227
FIGURE 1: SPLICE CLIP 65B17957-3 FASTENER INSTALLATION - INSPECTION
(SHEET 4 OF 6)
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PROPRIETARY - Copyright © Unpublished
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### Page 28 (OCR)

BOEING SERVICE BULLETIN 747-53A2844
ALERT  ALERT
STA
1920
FWD
FASTENER PATTERN 3
D-D
FIGURE 1: SPLICE CLIP 65B17957-3 FASTENER INSTALLATION - INSPECTION
(SHEET 5 OF 6)
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### Page 29

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for each airplane.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a) (b) (c) (d)--FASTENERSInspect1
(a) Do a General Visual Inspection to see if the fasteners shown have been installed and determined the
condition.
(b) Condition 1: Correct fasteners installed and the fasteners installed matches one of the three fastener
patterns shown (type of fastener and fastener pattern).
(c) Condition 2: Incorrect fasteners installed. The fasteners installed does not match any of the fastener
patten shown (type of fastener and fastener pattern).
(d) Condition 3: No fasteners installed.
The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure.
MORE DATAHOLE DIAQTYIDENTIFICATIONNAMECODE
--BACB30NX8K9HI-LOKA
(a)--BACC30BH8COLLAR
--BACB30NX10K9HI-LOKB
(a)--BACC30BH10COLLAR
(a) BACC30X* or BACC30M* collar in lieu of BACC30BH* is acceptable.
FIGURE 1: SPLICE CLIP 65B17957-3 FASTENER INSTALLATION - INSPECTION
(SHEET 6 OF 6)
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### Page 30 (OCR)

BOEING SERVICE BULLETIN 747-53A2844
ALERT  ALERT
STA
1920
S-4L
STA
1920
<≤^
2050245
FIGURE 2: INSPECTIONS AT BODY STATION 1920 AND STRINGER 4L
(SHEET 1 OF 4)
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### Page 31

FIGURE 2: INSPECTIONS AT BODY STATION 1920 AND STRINGER 4L
(SHEET 2 OF 4)
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### Page 32 (OCR)

BOEING SERVICE BULLETIN 747-53A2844
ALERT  ALERT
STA
1920
FWD
B-B  2050243
FIGURE 2: INSPECTIONS AT BODY STATION 1920 AND STRINGER 4L
(SHEET 3 OF 4)
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### Page 33

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for each airplane.
More DataQtyIdentificationNameTaskStep
(a)-69B15483-2SPLICE ANGLEInspect1
(b)-69B17669-47SILL WEBInspect2
(c)-69B18157-1SHEAR TIEInspect3
Aft (d)-65B17665-62SPLICE ANGLEInspect4
Fwd (d)-65B17665-69SHEAR CLIPInspect
(e) And attached
parts.
-65B17829-1TEE, AUX SILL OUTER
CHORD
Inspect5
(a) Do a Detailed Inspection of Frame 1920 Inboard Chord Splice Angle and the parts attached to the angle
for any crack.
(b) Do a Detailed Inspection of the cutout hole in the Sill Web and the attached parts for any crack.
(c) Do a General Visual Inspection of the Shear Tie and its fasteners for any crack.
(d) Do a Detailed Visual inspection of the Shear Clip and the Splice Angle and their fasteners for any crack.
(e) Do a Detailed Visual inspection of the Aux Sill Outer Chord Tee and attached parts for any crack.
FIGURE 2: INSPECTIONS AT BODY STATION 1920 AND STRINGER 4L
(SHEET 4 OF 4)
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### Page 34 (OCR)

BOEING SERVICE BULLETIN 747-53A2844
ALERT  ALERT
STA
1920
S-4L
STA
1920
2050223
FIGURE 3: AUX SILL OUTER CHORD TEE - INSPECTION
(SHEET 1 OF 3)
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### Page 35

FIGURE 3: AUX SILL OUTER CHORD TEE - INSPECTION
(SHEET 2 OF 3)
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### Page 36

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 .
More DataQtyIdentificationNameTaskStep
(a)-65B17829-1TEE, AUX SILL OUTER
CHORD
Inspect1
(b)-65B17829-1TEE, AUX SILL OUTER
CHORD
Inspect2
(a) Do a Surface High Frequency Eddy Current (HFEC) inspection of the Radii of the Aux Sill Outer Chord
Tee along 5" either side of Frame at station 1920 using a transverse scan to look for cracks in accordance
with 747 NDT Part 6, 51-00-00 Figure 4 or Figure 23.
(b) Do a Surface HFEC inspection for cracks of the internal surface of the Aux Sill Outer Chord Tee around
fastener heads along 5" each side of Frame at station 1920 to look for cracks in accordance with 747
NDT Part 6, 51-00-00 Figure 4 or Figure 23.
FIGURE 3: AUX SILL OUTER CHORD TEE - INSPECTION
(SHEET 3 OF 3)
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### Page 37 (OCR)

BOEING SERVICE BULLETIN 747-53A2844
ALERT  ALERT
SIA
1920
S-4L
2050233
FIGURE 4: SPLICE ANGLE FASTENER - INSTALLATION
(SHEET 1 OF 3)
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### Page 38 (OCR)

BOEING SERVICE BULLETIN 747-53A2844
ALERT  ALERT
STA
1920
FWD
A-A  2050234
FIGURE 4: SPLICE ANGLE FASTENER - INSTALLATION
(SHEET 2 OF 3)
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### Page 39

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for each airplane.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
2BACB30NX10K9HI-LOKInstall (New)1
2BACC30BH10COLLARInstall (New)
7BACB30NX8K9HI-LOKInstall (New)2
7BACC30BH8COLLARInstall (New)
(a) Use of BACC30X* or BACC30M* collar in lieu of BACC30BH* is acceptable.
The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure.
A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the
number of fasteners necessary for this figure.
MORE DATAHOLE DIAQTYIDENTIFICATIONNAMECODE
-7BACB30NX8K9HI-LOKA
-7BACC30BH8COLLAR
-2BACB30NX10K9HI-LOKB
-2BACC30BH10COLLAR
FIGURE 4: SPLICE ANGLE FASTENER - INSTALLATION
(SHEET 3 OF 3)
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### Page 40 (OCR)

BOEING SERVICE BULLETIN 747-53A2844
ALERT  ALERT
• INITIAL TRIM LINE
"INSURANCE CUT" O  TRIMLINE
0.03 MIN.
0.03 MIN.
TYPICAL CRACK
1) INITIAL TRIM LINE
TYPICAL CRACK LOCATION
FIGURE 5: TYPICAL CRACK REMOVAL
(SHEET 1 OF 2)
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### Page 41

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for each airplane.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a)--PARTTrim1
1. Maintain a minimum trim radius of 0.5 inch.
2. Break all sharp edges 0.015-0.030 inch.
3. Maintain a 125 microinch finish on all cut or
trimmed surfaces.
4. Finish all bare aluminum with chemical film
treatment and one coat of BMS 10-11, Type 1
Primer.
Do the steps that follow:(a)
1. Trim to remove the crack. Do a surface HFEC inspection along the edge of the trimmed surface
in accordance with 747 NDT Part 6, 51-00-00, Figure 4 or 23 to confirm that there is no crack.
2. Remove an additional 0.03 inch of material as an "insurance cut" to ensure crack removal.
Note: Do not trim beyond the tangent point of the radius of the horizontal flange. Ask Boeing for repair
data if crack removal requires trimming beyond the tangent point.
FIGURE 5: TYPICAL CRACK REMOVAL
(SHEET 2 OF 2)
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ALERTALERT

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