# Boeing Alert Service Bulletin 747-53A2880: No revision named

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- Document: [Boeing Alert Service Bulletin 747-53A2880](https://openairdocs.org/service-documents/boeing/747-53a2880.md)
- Title as filed: FAA-2015-3630 SB-747-53A2880
- Pages: 38
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### Page 1

Commercial 
Airplanes
747
Service Bulletin
ALERT
Number: 747-53A2880
Original Issue: December 03, 2014
ATA System: 5311
SUBJECT: FUSELAGE - Nose Section - Nose Cargo Door Portal C-3 Frame Upper Closure Fitting
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 © 2014 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Unpublished Work.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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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 1
D. Description .............................................. 1 1
E. Compliance .............................................. 1 1
F. Approval ............................................... 1 3
G. Manpower .............................................. 1 4
H. Weight and Balance Changes .................................... 1 4
I. Electrical Load Data ......................................... 1 4
J. References .............................................. 1 4
1. Existing Data: ......................................... 1 4
2. Data Supplied with this Service Bulletin: ........................... 1 5
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 5
K. Publications Affected ........................................ 1 5
L. Interchangeability and Intermixability of Parts ........................... 1 5
M. Software Accomplishment Summary ................................ 1 5
2. MATERIAL INFORMATION ........................................ 1 7
A. Material - Price and Availability ................................... 1 7
B. Industry Support Information .................................... 1 7
C. Parts Necessary for Each Airplane ................................. 1 7
1. Kits/Parts ............................................ 1 7
2. Parts and Materials Supplied by the Operator ........................ 1 8
3. Parts Modified and Reidentified ................................ 1 8
4. Parts Removed and Not Replaced .............................. 1 8
D. Parts Necessary to Change Spares ................................. 1 8
E. Special Tooling - Price and Availability ............................... 1 8
F. Special Tooling Necessary to do this Service Bulletin ....................... 1 8
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 1 9
A. GENERAL INFORMATION ..................................... 1 9
B. WORK INSTRUCTIONS ....................................... 2 0
FIGURE 1: INSPECTION FOR CRACKS IN UPPER CLOSURE FITTING AND CONNECTED STRUCTURE
.................................................. 2 6
FIGURE 2: OVERSIZE FASTENER REPAIR ............................... 2 9
FIGURE 3: INSURANCE OVERSIZE ................................... 3 3
APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE : TABLE 1: C-3 FRAME UPPER
CLOSURE FITTING INSPECTION AND REPAIR ...................... 3 6
APPENDIX B: PART DEMAND INTENT ................................... 3 8
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Commercial 
Airplanes
747
Service Bulletin
ALERT
SummaryNumber: 747-53A2880Original Issue: December 03, 2014
ATA System: 5311
SUBJECT: FUSELAGE - Nose Section - Nose Cargo Door Portal C-3 Frame Upper Closure Fitting
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
This service bulletin gives instruction to inspect the upper closure fitting and connected structure at the nose
cargo door portal C-3 frame for cracks. Cracks in the upper closure fitting that are not found and repaired can
grow with continued use of the airplane and cause a sudden decompression and loss of structural integrity.
Boeing issued service bulletin 747-53A2495 in 2003 to give inspections for cracks in the C-3 frame upper closure
fittings of 747-200F and 747-200C airplanes. Service bulletin 747-53A2495 was issued in response to crack
reports which are described in that service bulletin. The upper closure fittings installed in the airplanes affected
by this service bulletin were shot peened during production to increase fatigue resistance; however, subsequent
analysis has shown that the increase in fatigue resistance may not be sufficient to ensure that upper closure
fitting cracks will be found soon enough with existing inspections per the 747-400 MPD. While there have been
no upper closure fitting cracks found on the airplanes affected by this service bulletin, the potential for cracks
to initiate and grow in the upper closure fitting makes the inspections given in this service bulletin necessary. It
is necessary to do these inspections to make sure that cracks in the upper closure fitting will be found and
repaired before they can affect flight safety.
Boeing Service Related Problem (SRP) 747-SRP-53-0460 is related to this service bulletin.
The table below 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
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ReferenceAffectedPlanning Data
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/PartsYesKits/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
A Detailed inspection and a Surface High Frequency Eddy Current (HFEC) inspection for cracks in the upper
closure fitting and connected structure at the nose cargo door portal C-3 frame are to be accomplished. If any
crack is found with these inspections, a repair is to be done in accordance with this service bulletin. The repair
alternatives given in this service bulletin are an oversize fastener repair, a time limited repair, and a part
replacement repair. Repeat inspections are to be done within a compliance time that can be extended by
zero-timing specified fastener holes common to the upper closure fitting.
EFFECTIVITY
All 747-400F airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.
COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service
bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin
mandatory.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the inspection and repair procedures 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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BOEING SERVICE BULLETIN 747-53A2880
ALERT  ALERT
DOUBLER
STA
287  STA
270
LEFT SIDE SHOWN,
RIGHT SIDE OPPOSITE
STRAP
DO A DETAILED AND A SURFACE HFEC
INSPECTION OF THE C3 FRAME UPPER
CLOSURE FITTING AND REPAIR OR
REPLACE THE UPPER CLOSURE
FITTING IF ANY CRACK IS FOUND
• TYPICA
CRACK
C-3 FRAME UPPER  CLOSURE FITTING  2365579
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Commercial 
Airplanes
747
Service Bulletin
ALERT
Number: 747-53A2880
Original Issue: December 03, 2014
ATA System: 5311
SUBJECT: FUSELAGE - Nose Section - Nose Cargo Door Portal C-3 Frame Upper Closure Fitting
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 D6-30300 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
This service bulletin is applicable to 747-400F airplanes in one group. The Variable Numbers and
Group Information for the applicable airplanes is given below.
DESCRIPTIONCONFIGURATIONGROUP
All 747-400F Airplanes-1
Airplane Models:
747-400F
GroupVariable Number
1RL401 - RL403
1RL411 - RL436
1RL451 - RL456
1RL461 - RL462
1RL471 - RL481
1RL491 - RL492
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GroupVariable Number
1RL501 - RL502
1RL511 - RL516
1RL521 - RL522
1RL531 - RL534
1RL551
1RL561 - RL568
1RL571 - RL572
1RL576 - RL577
1RL579
1RL581 - RL586
1RL651 - RL655
1RL671 - RL675
1RL681 - RL684
1RL751 - RL752
1RM851 - RM859
1RM861 - RM863
1RM871 - RM899
1RM901 - RM906
1RM911
1RR701
1RR721 - RR724
1RR746 - RR748
1RR851 - RR856
1RR861 - RR862
1RR951 - RR952
2. Spares Affected
None.
B. Concurrent Requirements
None.
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C. Reason
This service bulletin gives instruction to inspect the upper closure fitting and connected structure at the
nose cargo door portal C-3 frame for cracks. Cracks in the upper closure fitting that are not found and
repaired can grow with continued use of the airplane and cause a sudden decompression and loss of
structural integrity.
Boeing issued service bulletin 747-53A2495 in 2003 to give inspections for cracks in the C-3 frame
upper closure fittings of 747-200F and 747-200C airplanes. Service bulletin 747-53A2495 was issued
in response to crack reports which are described in that service bulletin. The upper closure fittings
installed in the airplanes affected by this service bulletin were shot peened during production to increase
fatigue resistance; however, subsequent analysis has shown that the increase in fatigue resistance
may not be sufficient to ensure that upper closure fitting cracks will be found soon enough with existing
inspections per the 747-400 MPD. While there have been no upper closure fitting cracks found on the
airplanes affected by this service bulletin, the potential for cracks to initiate and grow in the upper
closure fitting makes the inspections given in this service bulletin necessary. It is necessary to do these
inspections to make sure that cracks in the upper closure fitting will be found and repaired before they
can affect flight safety.
Boeing Service Related Problem (SRP) 747-SRP-53-0460 is related to this service bulletin.
D. Description
A Detailed inspection and a Surface High Frequency Eddy Current (HFEC) inspection for cracks in the
upper closure fitting and connected structure at the nose cargo door portal C-3 frame are to be
accomplished. If any crack is found with these inspections, a repair is to be done in accordance with
this service bulletin. The repair alternatives given in this service bulletin are an oversize fastener repair,
a time limited repair, and a part replacement repair. Repeat inspections are to be done within a
compliance time that can be extended by zero-timing specified fastener holes common to the upper
closure fitting.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
221, 222747-400F
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.
A logic diagram showing compliance tasks and compliance times is included as an aid in Appendix A.
Do the required actions on both sides of the airplane in accordance with Paragraph 3. Accomplishment
Instructions.
When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When
more than one ACTION is given for a CONDITION number or an OPTION number, do all of the ACTION
numbers for that CONDITION number or OPTION number.
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Table 1: C-3 Frame Upper Closure Fitting Inspection and Repair
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Before 28,000 total
flight cycles, or
2,000 flight cycles
after the original is-
sue date of this
service bulletin,
whichever occurs
later.
Do PART 1: INSPEC-
TION FOR CRACKS IN
UPPER CLOSURE FIT-
TING AND CONNECTED
STRUCTURE. (g)
All airplanes.
3,000 flight cycles.Within 3,000 flight
cycles after doing
the inspection.
OPTION 1: Repeat PART
1. (g)
CONDITION 1: NO
CRACK FOUND
-Before further
flight.
OPTION 2: Do PART 3:
INSURANCE OVERSIZE.
(b) (e) (f)
3,000 flight cycles.Within 20,000 flight
cycles after doing
PART 3.
Repeat PART 1. (g)CONDITION 1.1: NO
CRACK FOUND AND
PART 3 ACCOMPLISHED
-Before further
flight.
Do a repair in accordance
with applicable repair in-
struction given in this
service bulletin. (a) (b)
CONDITION 2: ANY
CRACK FOUND
-Before further
flight.
Do PART 8: SPECIAL
INSTRUCTION REPAIR.
(d)
CONDITION 2.1: REMAIN-
ING CRACK IN STRAP (c)
3,000 flight cycles.Within 3,000 flight
cycles after doing
PART 2 or PART
6.
Repeat PART 1. (g)CONDITION 2.2: ONLY
PART 2 AND/OR PART 6
ACCOMPLISHED
3,000 flight cycles.Within 20,000 flight
cycles after doing
PART 2 or PART 6
and doing PART 3.
Repeat PART 1. (g)CONDITION 2.3: PART 2
AND/OR PART 6 ACCOM-
PLISHED PLUS PART 3
ACCOMPLISHED
-Within 10,000 flight
cycles after doing
PART 4.
Do PART 5: REPLACE
UPPER CLOSURE FIT-
TING.
CONDITION 2.4: PART 4
ACCOMPLISHED
3,000 flight cycles.Within 20,000 flight
cycles after doing
PART 5.
Repeat PART 1. (g)CONDITION 2.5: PART 5
ACCOMPLISHED
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Table 1: C-3 Frame Upper Closure Fitting Inspection and Repair
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
(a) Instruction is given in this service bulletin for the following repairs:
– PART 2: OVERSIZE FASTENER REPAIR
– PART 3: INSURANCE OVERSIZE
– PART 4: TIME LIMITED REPAIR
– PART 5: REPLACE UPPER CLOSURE FITTING
– PART 6: REPLACE DOUBLER
– PART 8: SPECIAL INSTRUCTION REPAIR (applicable if a crack found in the strap
cannot be repaired in accordance with PART 2)
(b) PART 2 and PART 3 can be accomplished only if limits specified for maximum hole diam-
eter and minimum edge margin can be maintained.
The minimum edge margin that applies at the strap can be reduced by fabricating and in-
stalling a new doubler in accordance with PART 7: FABRICATE / REPLACE DOUBLER.
Thus, accomplishment of PART 2 or PART 3 can include accomplishment of PART 7 also.
(c) CONDITION 2.1 applies if a crack is found in the strap and the crack cannot be removed
in accordance with PART 2.
(d) After a repair is accomplished in accordance with PART 8: SPECIAL INSTRUCTION
REPAIR, the post-repair inspections are specified in the repair instructions.
(e) PART 3 includes an Open Hole HFEC inspection for cracks. If any crack is found with this
inspection, CONDITION 1 is no longer applicable and CONDITION 2: ANY CRACK FOUND
becomes applicable. If this occurs, it may not be possible to complete a repair with existing
parts due to hole size and/or edge margin limits.
(f) Successful accomplishment of PART 3 extends the compliance time for the next inspection;
however, a need to access the same area to accomplish other inspections including those
given in service bulletins 747-53A2500 and 747-53A2753 could make the extension of
the compliance time less advantageous.
(g) PART 1 includes instruction to do a Detailed inspection for cracks in the upper closure
fitting and connected strap and doubler, and a Surface HFEC inspection for cracks in the
upper closure fitting.
F. Approval
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified
in this service bulletin comply with the applicable regulations and are FAA approved, as well as European
Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved
airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on
the airplane in its original Boeing delivery configuration or as modified by other approved Boeing
changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
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G. Manpower
The table below shows an estimate of the task hours necessary to do the inspection given in this service
bulletin 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
2.04.02Open Access
1.01.01Inspect (FIGURE 1)
2.04.02Close Access
5.09.0TOTAL FOR EACH AIRPLANE
NOTE: More time will be necessary for repairs if cracks are found.
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Boeing Service Bulletin 747-53A2495, 747-53A2500, 747-53A2753
b. Boeing Service Related Problem (SRP) 747-SRP-53-0460
c. Service Bulletin Index D6-30300
d. Standard Overhaul Practices Manual (SOPM) 20-41-02, 20-43-03, 20-50-01
e. 747 Non-Destructive Testing (NDT) Manual Part 6, 51-00-00, Procedures 1, 4, 11, 16, 23
f. 747-400 Aircraft Maintenance Manual (AMM) 25-11-01, 25-15-00
g. 747-400 Maintenance Planning Data (MPD)
h. 747-400F Structural Repair Manual (SRM) 51-10-02, 51-20-07, 51-40
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2. Data Supplied with this Service Bulletin:
a. Drawings:
ADCNDCN/REVSheetTitleDrawing No
-A1Time Limited Repair C-3 Upper Closure
Fitting Freighter Nose Door
691U0144
-A2
-A3
--4
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
Frame Installation - Closure, Upper65B12887
Beam Instl - Body Cab WL 331.565B12886
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. DTI requirements for the structure affected
are contained in Paragraph 1.E., Compliance of this service bulletin.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
M. Software Accomplishment Summary
Not affected.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the parts shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators
are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin.
The parts are subject to the terms and conditions of the Boeing standard purchase order
acknowledgment. Prices are in United States Dollars. Terms: Net 30 days.
Reference this service bulletin and submit your purchase order by one of these methods:
1. Order on-line via ATA Spec 2000 or The Boeing PART Page
2. Fax to (206) 662-7145
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
$136.00199Doubler65B12886-503
$21,465.00199Fitting - Closure Frame, Upper (left side)65B12888-17
$21,465.00199Fitting - Closure Frame, Upper, (right side)65B12888-18
Operators are encouraged to complete the survey provided in APPENDIX B of this service bulletin to
help Boeing predict the quantity and timing of the Boeing Supplied Kits/Parts.
B. Industry Support Information
Boeing warranty remedies are not available for the inspection and/or repair procedures given in this
service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts
To get the parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
NOTE: A part shown below could be necessary to do a change given in this service bulletin. The
parts will be needed only as noted in the table.
NotesNameQTYPart Number /
Specification
(a)Doubler-65B12886-503
(b)Fitting - Closure Frame, Upper (left
side)
165B12888-17
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NotesNameQTYPart Number /
Specification
(b)Fitting - Closure Frame, Upper, (right
side)
165B12888-18
(a) The identified doubler will be needed only if a decision is made to accomplish Paragraph
3.B., Work Instructions, PART 6: REPLACE DOUBLER on either side of the airplane.
(b) The identified fitting will be needed only if a decision is made to accomplish Paragraph
3.B., Work Instructions, PART 5: REPLACE UPPER CLOSURE FITTING.
2. Parts and Materials Supplied by the Operator
The following parts could be necessary to do a change given 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
(b) (c)Bolts/Collars(a)(a)
(a) A fastener listed in FIGURE 2 will be needed if a crack is found and repaired in accordance
with Paragraph 3.B., Work Instructions, PART 2: OVERSIZE FASTENER REPAIR.
Fasteners identified in FIGURE 3 will be needed if Paragraph 3.B., Work Instructions,
PART 3: INSURANCE OVERSIZE is accomplished.
(b) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS)
for supplier data.
(c) Refer to 747 Structural Repair Manual Chapter 51 for alternate fasteners.
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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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 Values:
— Values for structural fasteners are given in 747 Structural Repair Manual,
Chapter 51.
— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
4. Use the approved fastener, process and material substitutions in accordance with
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. Refer to SOPM 20-50-01 for alternate
full threaded fasteners (screws) needed for installation in this service bulletin.
6. A Detailed Inspection 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. 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.
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8. 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.
9. Refer to Appendix A for a logic diagram. The Logic diagram is provided as an aid
only. Information contained in Paragraph 1.E., Compliance is the primary source for
compliance times. Information in Paragraph 3.B., Work Instructions is the primary
source for tasks required for compliance.
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.
12. If shading is used, shaded areas in Figures are to separate the non-critical and
non-authoritative information from the critical and authoritative information.
13. Use of colors in Figures is based on guidance from the ATA e-Business Program
(ATA) iSpec 2200.
14. When more than one OPTION is given for a CONDITION, do only one of the OPTION
numbers. When more than one ACTION is given for a CONDITION number or an
OPTION number, do all of the ACTION numbers for that CONDITION number or
OPTION number.
15. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
16. The CONDITIONS, ACTIONS and OPTIONS shown apply to each side of the airplane
independently.
17. Some steps in the Work Instructions are identified as Required for Compliance (RC).
If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps
identified as RC must be done to comply with the AD. Alternative procedures for
steps not identified with RC can be used if the RC steps can still be done as specified,
and the airplane can be put back in a serviceable condition. An Alternative Method
of Compliance (AMOC) is not necessary for deviations to steps that are not identified
as RC.
18. Edge margin (EM) is the distance from the center of the fastener hole to the edge
of the part. The specified minimum value is given as a constant times the hole
diameter D
B. WORK INSTRUCTIONS
1. Remove flight deck sidewall lining and insulation to get access to the C-3 Frame Upper Closure
Fitting where the C-3 frame intersects the body frame at STA 287. Refer to 747-400 AMM 25-15-00
as an accepted procedure for removal of the sidewall lining and insulation. To get easier access
to the inspection area, remove the pilot and copilot seats. Refer to 747-400 AMM 25-11-01 as an
accepted procedure for removal of the seats.
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2. RC - Do PART 1: INSPECTION FOR CRACKS IN UPPER CLOSURE FITTING AND CONNECTED
STRUCTURE.
3. RC - Do one of the OPTIONS given below that applies for the CONDITION found with the PART
1 inspection.
a. If CONDITION 1: NO CRACK FOUND applies:
(1) OPTION 1: Do steps 4-6 below.
CAUTION: IF OPTION 2 BELOW IS CHOSEN, REMOVE THE FASTENERS CAREFULLY
TO AVOID DAMAGING THE FASTENER HOLES WHEN ACCOMPLISHING
PART 3: INSURANCE OVERSIZE.
(2) OPTION 2: Do PART 3: INSURANCE OVERSIZE and then do steps 4-6 below.
NOTE: – Accomplishment of PART 3 is possible only if the insurance oversize can
be done within specified hole size and edge margin limits. Sufficient edge
margins should be verified before the fasteners are removed.
– PART 3 includes an Open Hole HFEC inspection. If any crack is found with
this inspection, CONDITION 1 is no longer applicable and CONDITION 2:
ANY CRACK FOUND becomes applicable. If this occurs, it may not be
possible to complete a repair with existing parts due to hole size and/or
edge margin limits.
– Successful accomplishment of PART 3 extends the compliance time for the
next inspection as shown in Paragraph 1.E., Compliance; however, a need
to access the same area to accomplish other inspections including those
given in service bulletins 747-53A2500 and 747-53A2753 could make the
extension of the compliance time less advantageous.
b. If CONDITION 2: ANY CRACK FOUND applies:
Accomplish a repair that removes the crack or replaces the cracked part in accordance with
one or more of the repairs listed in the table below and then do steps 4-6 below.
NOTE: Accomplishment of PART 2 is possible only if the crack indication can be
eliminated within specified hole size and edge margin limits.
–
– Accomplishment of PART 3 is possible only if the insurance oversize can be
done within specified hole size and edge margin limits. Accomplishment of PART
3 affects the compliance time for the repeat inspection.
– If accomplishment of PART 2 or PART 3 is prevented by a short edge margin
condition at the strap, a new doubler with increased edge margin can be
fabricated and installed in accordance with PART 7: FABRICATE / REPLACE
DOUBLER. Accomplishment of PART 7 will reduce the minimum edge margin
permitted for the strap; thus, accomplishment of PART 7 could allow for a PART
2, PART 3 repair that would otherwise be prevented.
DescriptionApplicable Instruction
OVERSIZE FASTENER REPAIRPART 2 (a)
OVERSIZE FASTENER REPAIR + INSURANCE OVERSIZEPART 2 plus PART 3 (a)
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DescriptionApplicable Instruction
TIME LIMITED REPAIRPART 4
REPLACE UPPER CLOSURE FITTINGPART 5
REPLACE DOUBLERPART 6
REPLACE DOUBLER + INSURANCE OVERSIZEPART 6 plus PART 3 (a)
(a) PART 2 and PART 3 are applicable only if limits specified for maximum hole diameter and minimum edge
margin can be maintained.
The minimum edge margin that applies at the strap can be reduced by fabricating and installing a new
doubler in accordance with PART 7: FABRICATE / REPLACE DOUBLER. Thus, accomplishment of PART
2 or PART 3 can include accomplishment of PART 7 also.
c. CONDITION 2.1: REMAINING CRACK IN STRAP
If a crack is found in the strap that cannot be repaired in accordance with PART 2, do PART
8: SPECIAL INSTRUCTION REPAIR.
4. Install removed flight deck sidewall lining and insulation. Refer to 747-400 AMM 25-15-00 as an
accepted procedure for installation of the sidewall lining and insulation. If removed, reinstall the
pilot and copilot seats. Refer to 747-400 AMM 25-11-01 as an accepted procedure for installation
of the seats.
5. Put the airplane back to a serviceable condition.
6. RC - Repeat PART 1: INSPECTION FOR CRACKS IN UPPER CLOSURE FITTING AND
CONNECTED STRUCTURE in accordance with Paragraph 1.E., Compliance. Use the compliance
data in Paragraph 1.E., Compliance that applies for the applicable post-change CONDITION
identified in the table below.
DescriptionCondition After Change
ONLY PART 2 AND/OR PART 6 ACCOMPLISHEDCONDITION 2.2:
PART 2 AND/OR PART 6 ACCOMPLISHED PLUS
PART 3 ACCOMPLISHED
CONDITION 2.3:
PART 4 ACCOMPLISHEDCONDITION 2.4:
PART 5 ACCOMPLISHEDCONDITION 2.5:
PART 8 ACCOMPLISHEDCONDITION 2.1.1:
PART 1: INSPECTION FOR CRACKS IN UPPER CLOSURE FITTING AND CONNECTED
STRUCTURE
1. Do a Detailed inspection and a Surface High Frequency Eddy Current (HFEC) inspection for cracks
in the upper closure fitting and connected structure at the nose cargo door portal C-3 frame in
accordance with FIGURE 1. Do these inspections on both sides of the airplane.
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PART 2: OVERSIZE FASTENER REPAIR
1. Oversize the fastener hole to remove material containing the crack and inspect to confirm that no
detectable crack remains in the upper closure fitting or the connected strap and doubler in
accordance with FIGURE 2.
2. Install a new fastener at the oversized hole in accordance with FIGURE 2.
PART 3: INSURANCE OVERSIZE
1. Do an Open Hole HFEC inspection at two fastener holes common to the upper closure fitting in
accordance with FIGURE 3 to confirm there is no detectable crack in the upper closure fitting or
the connected strap and doubler at these locations.
2. Oversize the two inspected fastener holes common to the upper closure fitting and strap and
doubler in accordance with FIGURE 3 to remove material that could contain an undetected crack.
3. Install new fasteners at the oversized holes in accordance with FIGURE 3.
PART 4: TIME LIMITED REPAIR
1. Do a time limited repair in accordance with drawing 691U0144 except where drawing 691U0144
specifies sections of the 747-100/200/300 Structural Repair Manual (SRM), the equivalent section
of the 747-400 SRM is to be used as shown in the table below.
NOTE: After accomplishment of PART 4: TIME LIMITED REPAIR, PART 5: REPLACE
UPPER CLOSURE FITTING must be accomplished within the time given in Paragraph
1.E., Compliance.
–
– Drawing 691U0144 shows a stop drill repair (or a freeze plug repair for a small crack)
and new CRES doublers which must be installed if a stop drill or freeze plug repair
is done.
747-400F SRM Section747-100/200/300 SRM Section
747-400F SRM 51-10-0251-10-01
747-400F SRM 51-20-0751-10-08
747-400F SRM 51-4051-30
PART 5: REPLACE UPPER CLOSURE FITTING
1. Remove the damaged upper closure fitting and install a new upper closure fitting. Install fitting
65B12888-17 as a left side replacement. Install fitting 65B12888-18 as a right side replacement.
If the minimum edge margin at the strap fastener holes common to the upper closure fitting is 1.0D
or more but less than 1.7D, fabricate and install a replacement doubler along with the new upper
closure fitting in accordance with PART 7: FABRICATE / REPLACE DOUBLER. The edge margin
at fastener holes in the new upper closure fitting is to be 1.7D or more. The edge margin at fastener
holes in the new doubler is to be 2.0D or more.
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NOTE: If there is a freeze plug installed in the strap, the edge margin calculation at the location
of the freeze plug is to be based on the diameter of the hole that holds the freeze plug,
not the fastener hole size.
If CONDITION 2.4: PART 4 ACCOMPLISHED is applicable and the minimum edge margin at the
strap fastener holes common to the upper closure fitting is 1.7D or more, install a new 65B12886-503
doubler along with the new upper closure fitting. The minimum permitted edge margin at fastener
holes in the new upper closure fitting and the new doubler is 1.7D.
For PART 5 the maximum permitted hole size for fasteners common to the new upper closure
fitting, new doubler and strap are as follows:
Maximum Hole Di-
ameter
Fastener Location
The maximum diame-
ter specified in FIG-
URE 2.
Bottom two fasteners common to the upper closure fitting / doubler / strap.
0.281 inch.Fasteners common to the upper closure fitting / doubler / strap other than the bottom
two fasteners.
Contact Boeing if additional instruction is needed to install a new upper closure fitting. If the new
fitting cannot be installed within the edge margin and fastener hole size limits given above, contact
Boeing to get special instruction and install the new fitting in accordance with the special instruction
from Boeing.
PART 6: REPLACE DOUBLER
1. Remove the damaged doubler and install a new 65B12886-503 doubler. The limits for fastener
hole size and edge margin given in this service bulletin apply for the installation of the new doubler.
PART 7: FABRICATE / REPLACE DOUBLER
1. Fabricate a new replacement doubler that is sized to give 2.0D or more edge margin at all fastener
locations. Make the doubler 0.090 inch thick from 7075-T6 Clad sheet per QQ-A-250/13.
NOTE: Accomplishment of PART 7 could allow for a PART 2 or PART 3 repair that would
otherwise be prevented by a short edge margin condition at the strap. If PART 7 is
accomplished, the minimum edge margin permitted for the strap changes from 1.7D to
1.0D.
2. Apply Chemical conversion coating to the surfaces of the doubler. Refer to SOPM 20-43-03 as an
accepted procedure.
3. Apply one layer of BMS 10-11, Type 1 primer. Refer to SOPM 20-41-02 as an accepted procedure.
4. Remove the existing doubler and install the replacement doubler with 2.0D or more edge margin
at all the fastener holes common to the doubler.
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PART 8: SPECIAL INSTRUCTION REPAIR
1. If a crack is found in the strap and the crack cannot be repaired in accordance with PART 2:
OVERSIZE FASTENER REPAIR, contact Boeing to get special repair and post-repair inspection
instruction and do the repair and post-repair inspections.
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BOEING SERVICE BULLETIN 747-53A2880
ALERT  ALERT
STA
270
LEFT SIDE SHOWN
RIGHT SIDE OPPOSITE
APPROXIMATELY
12 INCHES ABOVE  1 TYPICAL
THE FLIGHT DECK  CRACK
FLOOR.
CLOSURE
STA  FITTING  2365678
287
FIGURE 1: INSPECTION FOR CRACKS IN UPPER CLOSURE FITTING AND CONNECTED STRUCTURE
(SHEET 1 OF 3)
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### Page 27

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)--Upper Closure Fitting /
Strap / Doubler
Inspect1
(b)--Upper Closure FittingInspect2
(a) Do a Detailed inspection for cracks. Inspect all visible parts of the upper closure fitting, strap and doubler
in the area shown.
FIGURE 1: INSPECTION FOR CRACKS IN UPPER CLOSURE FITTING AND CONNECTED STRUCTURE
(SHEET 2 OF 3)
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More DataQtyIdentificationNameTaskStep
(b) Do a Surface HFEC inspection of the upper closure fitting for cracks in accordance with 747 NDT Manual
Part 6, 51-00-00, Procedure 4 or 23. Inspect the surface of the upper closure fitting around the heads of
the two fasteners shown in Detail C of this figure.
FIGURE 1: INSPECTION FOR CRACKS IN UPPER CLOSURE FITTING AND CONNECTED STRUCTURE
(SHEET 3 OF 3)
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BOEING SERVICE BULLETIN 747-53A2880
ALERT  ALERT
LEFT SIDE SHOWN,
RIGHT SIDE OPPOSITE
FITTING
STA  287  2365729
FIGURE 2: OVERSIZE FASTENER REPAIR
(SHEET 1 OF 4)
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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
(a)--Fastener HoleDrill / Ream1
(b)--Upper Closure Fitting /
Strap / Doubler
Inspect2
(c)--FastenerInstall (New)3
(a) The fastener hole is to be oversized to remove material containing the crack. There are two limitations
for this step as follows:
1. The oversized hole must not exceed the maximum diameter for the accomplishment of PART
2: OVERSIZE FASTENER REPAIR given in the table below. Note that accomplishment of PART
3: INSURANCE OVERSIZE will be possible only if the oversize is kept within the limit for accom-
plishment of PART 3 given in the table below.
2. The edge margin for the upper closure fitting, strap and doubler is not to be less than the value
specified in the table below.
(b) Do an Open Hole HFEC inspection for cracks in the upper closure fitting, strap and doubler in accordance
with 747 NDT Manual Part 6, 51-00-00, Figures 1, 11, or 16.
If the hole size is less than the maximum permitted size and a crack is indicated with this inspection, repeat
steps 1 and 2 as necessary/permitted.
(c) Install the fastener identified in the fastener table below that is applicable for the final hole size. This step
is not applicable if an additional oversize will be made to accomplish PART 3: INSURANCE OVERSIZE.
Maximum Hole Diame-
ter that Permits Ac-
complishment of
PART 3: INSURANCE
OVERSIZE
Maximum Hole Diame-
ter for Accomplish-
ment of PART 2:
OVERSIZE FASTEN-
ER REPAIR
Initial Hole Size
0.2190.2813/16
FIGURE 2: OVERSIZE FASTENER REPAIR
(SHEET 2 OF 4)
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Maximum Hole Diame-
ter that Permits Ac-
complishment of
PART 3: INSURANCE
OVERSIZE
Maximum Hole Diame-
ter for Accomplish-
ment of PART 2:
OVERSIZE FASTEN-
ER REPAIR
Initial Hole Size
0.2810.3441/4
Minimum Edge Margin (a)Part
1.7DUpper Closure Fitting
1.7DDoubler
1.7D if the doubler edge margin is not 2.0D or more at
all fastener holes common to the strap and doubler.
Strap
1.0D if the doubler edge margin is 2.0D or more at all
fastener holes common to the strap and doubler. (b)
(a) Edge margin is the distance from the center of the fastener hole to the edge of the part. The specified
minimum value is given as a constant times the final hole diameter D.
(b) PART 7: FABRICATE / REPLACE DOUBLER gives instruction to fabricate and install a replacement
doubler that has 2.0D or more edge margin at all fastener holes common to the strap and doubler.
The code shown below agrees with the letter shown in the upper left corner of the fastener symbols in the figure.
The applicable fastener is the fastener that applies for the diameter of the fastener hole.
More DataHole DiaQtyIdentificationNameCode
-0.200 - 0.203-BACB30NX6K6XBoltA
---BACC30BH6Collar
-0.216 - 0.219-BACB30NX6K6YBolt
---BACC30AC6Collar
-0.247 - 0.250-BACB30NX8K6Bolt
---BACC30BH8Collar
-0.263 - 0.266-BACB30NX8K6XBolt
---BACC30BH8Collar
-0.278 - 0.281-BACB30NX8K6YBolt
--BACC30AC8Collar
FIGURE 2: OVERSIZE FASTENER REPAIR
(SHEET 3 OF 4)
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More DataHole DiaQtyIdentificationNameCode
0.263 - 0.266-BACB30NX8K6XBoltB
--BACC30BH8Collar
0.278 - 0.281-BACB30NX8K6YBolt
--BACC30AC8Collar
-0.309 - 0.313-BACB30NX10K6Bolt
--BACC30BH10Collar
-0.325 - 0.328-BACB30NX10K6XBolt
---BACC30BH10Collar
-0.341 - 0.344-BACB30NX10K6YBolt
---BACC30AC10Collar
FIGURE 2: OVERSIZE FASTENER REPAIR
(SHEET 4 OF 4)
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BOEING SERVICE BULLETIN 747-53A2880
ALERT  ALERT
STA
270
LEFT SIDE SHOWN,
RIGHT SIDE OPPOSITE
3\4
FITTING
STA  287  2365751
FIGURE 3: INSURANCE OVERSIZE
(SHEET 1 OF 3)
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### Page 34

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
NOTE: If the work given in this figure is accomplished after a crack is removed in accordance with FIGURE 2,
the work given in step 1 and step 2 of this figure will already have been accomplished in accordance
with FIGURE 2 . The Open Hole HFEC inspection with no crack indication accomplished in accordance
with FIGURE 2 is a satisfactory inspection for step 2 of this figure.
More DataQtyIdentificationNameTaskStep
-2-FastenersRemove1
(a) (b)--Upper Closure Fitting /
Strap / Doubler
Inspect2
(c)--Fastener HoleDrill / Ream3
(d)2-FastenersInstall (New)4
(a) Do an Open Hole HFEC inspection for cracks in the upper closure fitting, strap and doubler in accordance
with 747 NDT Manual Part 6, 51-00-00, Figures 1, 11, or 16.
(b) If any crack is found with the inspection given in this step, the remainder of the work given in this figure
is not applicable.
(c) The diameter of the fastener hole that contains no detectable crack is to be increased by 1/16 inch to re-
move material that could contain an undetected crack. The hole size is not to exceed the maximum size
given in the table below and the edge margin is not to be less than the minimum value given in the table
below. The hole diameter is to be within the limits given in the fastener table for the fastener to be installed.
(d) Install the fastener identified in the fastener table below that is applicable for the final hole size.
Maximum Hole DiameterInitial Hole Size
0.2813/16
0.3441/4
Minimum Edge Margin (a)Part
1.7DUpper Closure Fitting
FIGURE 3: INSURANCE OVERSIZE
(SHEET 2 OF 3)
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Minimum Edge Margin (a)Part
1.7DDoubler
1.7D if the doubler edge margin is not 2.0D or more at
all fastener holes common to the strap and doubler.
Strap
1.0D if the doubler edge margin is 2.0D or more at all
fastener holes common to the strap and doubler. (b)
(a) Edge margin is the distance from the center of the fastener hole to the edge of the part. The specified
minimum value is given as a constant times the final hole diameter D.
(b) PART 7: FABRICATE / REPLACE DOUBLER gives instruction to fabricate and install a replacement
doubler that has 2.0D or more edge margin at all fastener holes common to the strap and doubler.
More DataHole DiaQtyIdentificationNameCode
-0.247 - 0.250-BACB30NX8K6BoltC
---BACC30BH8Collar
-0.263 - 0.266-BACB30NX8K6XBolt
---BACC30BH8Collar
-0.278 - 0.281-BACB30NX8K6YBolt
--BACC30AC8Collar
-0.309 - 0.313-BACB30NX10K6BoltD
--BACC30BH10Collar
-0.325 - 0.328-BACB30NX10K6XBolt
---BACC30BH10Collar
-0.341 - 0.344-BACB30NX10K6YBolt
---BACC30AC10Collar
FIGURE 3: INSURANCE OVERSIZE
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 03, 2014
747-53A2880
35 of 38
BOEING SERVICE BULLETIN 747-53A2880
ALERTALERT

### Page 36 (OCR)

BOEING SERVICE BULLETIN 747-53A2880
ALERT  ALERT
WHICHEVER OCCURS LATER:
2,000 FLIGHT CYCLES
28,000 TOTAL  AFTER THE ORIGINAL
FLIGHT CYCLES  ISSUE DATE OF THIS
SERVICE BULLETIN
REPEAT PART 1  DO PART 1
CONDITION 1: NO CRACK FOUND  CONDITION 2: ANY CRACK FOUND
OPTION 1:  OPTION 2:  BEFORE FURTHER  FLIGHT
REPEAT  PART 1  DO PART 3
DO A REPAIR IN ACCORDANCE WITH APPLICABLE
FLIGHT CYCLES  WITHIN 3,000  REPAIR INSTRUCTION GIVEN IN PARTS 2-8 OF THIS
SERVICE BULLETIN
CONDITION 2.1  CONDITION 2.3
CONDITION 1.1  CONDITION 2.2  CONDITION 2.4
WITHIN 20,000
WITHIN 20,000  DO PART 8  FLIGHT CYCLES
FLIGHT CYCLES
WITHIN 3,000
FLIGHT CYCLES
CONDITION  CONDITION 2.5
2.1.1  WITHIN 10,000
FLIGHT CYCLES
WITHIN 20,000
IN ACCORDANCE  FLIGHT CYCLES
WITH PART 8
SPECIAL  DO PART 5
INSTRUCTION
2365784
A description for each PART and CONDITION included in the logic diagram is given in the tables below. The
actions associated with each PART are to be done in accordance with Paragraph 3. Accomplishment Instructions.
APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 1: C-3 FRAME UPPER
CLOSURE FITTING INSPECTION AND REPAIR
(SHEET 1 OF 2)
Original Issue: December 03, 2014
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### Page 37

DescriptionPart
INSPECTION FOR CRACKS IN UPPER CLOSURE FITTING AND CONNECTED
STRUCTURE
PART 1:
OVERSIZE FASTENER REPAIR (a) (c)PART 2:
INSURANCE OVERSIZE (b) (c)PART 3:
TIME LIMITED REPAIRPART 4:
REPLACE UPPER CLOSURE FITTINGPART 5:
REPLACE DOUBLER (c)PART 6:
FABRICATE / REPLACE DOUBLER (c)PART 7:
SPECIAL INSTRUCTION REPAIR (d)PART 8:
(a) Accomplishment of PART 2 is possible only if the crack indication can be eliminated within specified hole
size and edge margin limits.
(b) Accomplishment of PART 3 is possible only if the insurance oversize can be done within specified hole
size and edge margin limits.
(c) If accomplishment of PART 2 or PART 3 is prevented by a short edge margin condition at the strap, a
new doubler with increased edge margin can be fabricated and installed in accordance with PART 7 to
reduce the minimum edge margin permitted for the strap. Accomplishment of PART 7 with PART 2 or
PART 3 allows the PART 2 or PART 3 repair to be done with edge margin = 1.0D (versus 1.7D) at the
strap.
(d) Special instruction will be provided by Boeing to repair a crack in the strap that cannot be repaired in ac-
cordance with PART 2. Special instruction will also be provided for post-repair inspections that will apply
after the special repair is accomplished.
DescriptionCondition
NO CRACK FOUNDCONDITION 1:
NO CRACK FOUND AND PART 3 ACCOMPLISHEDCONDITION 1.1
ANY CRACK FOUNDCONDITION 2:
REMAINING CRACK IN STRAP (a)CONDITION 2.1
PART 8 ACCOMPLISHEDCONDITION 2.1.1
ONLY PART 2 AND/OR PART 6 ACCOMPLISHEDCONDITION 2.2
PART 2 AND/OR PART 6 ACCOMPLISHED PLUS PART 3 ACCOMPLISHEDCONDITION 2.3
PART 4 ACCOMPLISHEDCONDITION 2.4
PART 5 ACCOMPLISHEDCONDITION 2.5
(a) CONDITION 2.1 applies if a crack found in the strap cannot be repaired in accordance with PART 2.
APPENDIX A:  LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE : TABLE 1: C-3 FRAME UPPER
CLOSURE FITTING INSPECTION AND REPAIR
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 03, 2014
747-53A2880
37 of 38
BOEING SERVICE BULLETIN 747-53A2880
ALERTALERT

### Page 38 (OCR)

BOEING SERVICE BULLETIN 747-53A2880
ALERT  ALERT
Boeing Part Demand Intent
After review of this service bulletin, Boeing asks that the primary engineer fill out this survey to help Boeing
predict the quantity and timing of the Boeing supplied kits.
Airline:
Contact Name:
Date:
Contact E-mail:
• Yes  • No Have/will you recommend to your airline to accomplish this service bulletin?
• Yes  • No Would issuance of an AD change this decision?
When would you likely be starting this SB incorporation? Month/ Year_
How many airplanes per month do you plan to accomplish? Airplane/Month
How many total airplanes do you plan to complete? Total Airplanes
For inspection Service Bulletins, are you planning to replace on condition, or a fleet campaign to replace on
all airplanes regardless of condition?
- On Condition  Campaign
If you are not incorporating this Service Bulletin at this time will you please help us understand the reason(s)
why? Your input will help us provide better customer support.
- Cost Prohibitive  - Continue Inspections  • Other
Operator Comments:
Within 45 days of the SB issue, or as soon after as possible, please scan this form and send to:
sbsolutions@boeing.com
Disclaimer: The data provided in this survey will be used for planning purposes only and does not  constitute a commitment on any part of the airlines to purchase the parts in question, nor does it constitute  2326214
a commitment on the part of Boeing to deliver the parts in question. This survey is a projection to help
Boeing forecast demand levels and timing to better support the customers schedule.
APPENDIX B: PART DEMAND INTENT
(SHEET 1 OF 1)
Original Issue: December 03, 2014
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  747-53A2880
Work - See page 1 for details.  38 of 38

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