# Boeing Special Attention Service Bulletin 767-53-0207: No revision named

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- Pages: 27
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### Page 1

Commercial 
Airplanes
767
Service Bulletin
SPECIAL ATTENTION
Number: 767-53-0207
Original Issue: December 17, 2009
ATA System: 5365 2312
SUBJECT: FUSELAGE - Section 46 Skin - Fuselage Skin and Backup Structure Inspection and
Repair at the Lower VHF Antenna Cutout at Station 1197 + 99, Between Stringers 39L
and 39R
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9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET
Copyright © 2009 The Boeing Company
Unpublished Work - All Rights Reserved
Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable
subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.
This document includes proprietary information owned by The Boeing Company and/or one or more third parties.
Treatment of the document and the information it contains is governed by contract with Boeing. For more
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Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
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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 3
G. Manpower .............................................. 1 3
H. Weight and Balance Changes .................................... 1 5
I. Electrical Load Data ......................................... 1 5
J. References .............................................. 1 5
1. Existing Data .......................................... 1 5
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 6
L. Interchangeability and Intermixability of Parts ........................... 1 6
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 7
3. Parts Modified and Reidentified ................................ 1 7
4. Parts Removed and Not Replaced .............................. 1 7
D. Parts Necessary to Change Spares ................................. 1 7
E. Special Tooling - Price and Availability ............................... 1 7
F. Special Tooling Necessary to do this Service Bulletin ....................... 1 7
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 1 9
A. GENERAL INFORMATION ..................................... 1 9
B. WORK INSTRUCTIONS ....................................... 1 9
FIGURE 1: FUSELAGE SKIN WITH THE ANTENNA REMOVED - INSPECTION ........... 2 2
FIGURE 2: BACKUP STRUCTURE - INSPECTION ........................... 2 4
FIGURE 3: FUSELAGE SKIN WITHOUT ANTENNA REMOVED - INSPECTION ............ 2 6
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Commercial 
Airplanes
767
Service Bulletin
SPECIAL ATTENTION
SummaryNumber: 767-53-0207Original Issue: December 17, 2009
ATA System: 5365 2312
SUBJECT: FUSELAGE - Section 46 Skin - Fuselage Skin and Backup Structure Inspection and
Repair at the Lower VHF Antenna Cutout at Station 1197 + 99, Between Stringers 39L
and 39R
BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.
CONCURRENT REQUIREMENTS
None.
BACKGROUND
Accomplishment of the inspections in this service bulletin will make sure that cracks in fuselage skin around the
VHF antenna and internal backup structure at station 1197+ 99 are found and repaired. If not repaired, cracks
in the fuselage skin and/or internal backup structure could result in unscheduled repairs.
Two operators have reported cracks in the section 46 fuselage lower skin around the periphery of the VHF
antenna baseplate at station 1197+99. One operator reported 5 cracks with a maximum length of 11 inches,
found on an airplane with 38,804 total flight-hours/34,929 total flight-cycles. Another operator reported a maximum
crack length of 9.5 inches, found on an airplane with 60,467 total flight-hours/29,185 total fight-cycles. Boeing
investigation has revealed that the fuselage skin and/or internal backup structure cracks are attributed to fatigue.
This fatigue is the result of bending loads in the skin, which are caused by vibration of the antenna in flight. No
operator reported crack findings for the backup structure.
This service bulletin gives instructions to do detail inspections for cracks, and repair if necessary, of the fuselage
skin and internal backup structure at the VHF antenna at station 1197+ 99.
Boeing Service Related Problem (SRP) 767-SRP-53-0323 is related to this service bulletin.
ACTION
Part 1 - Fuselage Skin and Backup Structure Inspection ( Initial Inspection )
Do an external Detail Inspection ( DI ) of the fuselage skin at the lower aft VHF antenna cutout and internal DI
of the backup structure for crack at station 1197+99 and do as follows:
Condition 1 ( No fuselage skin and backup structure crack found )
Do an external DI of the fuselage skin in accordance with Part 2 at the times given in Paragraph 1.E.Table 2
Compliance.
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Condition 2 ( Fuselage skin crack found )
Repair fuselage skin crack in accordance with 767-300 SRM.
Condition 3 ( Backup structure crack found )
Repair or replace cracked part(s).
Part 2 - Fuselage Skin Inspection ( Repeat Inspection )
Do an external DI of the fuselage skin for crack at the periphery of the antenna baseplate and do as follows:
Condition 4 ( No fuselage skin crack found )
Repeat Part 2 Paragraph 1 inspection at the times given in Paragraph 1.E. Table 2 Compliance.
Condition 5 ( Fuselage skin crack found )
Repair fuselage skin crack in accordance with 767-300 SRM.
Airplanes after line number 350 incorporate an improved VHF antenna backup structure that makes skin cracks
around the antenna cutout less likely.
EFFECTIVITY
767-300 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 configuration changes, inspection and/or repair procedures
given in this service bulletin.
MANPOWER
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
None.
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Commercial 
Airplanes
767
Service Bulletin
SPECIAL ATTENTION
Number: 767-53-0207
Original Issue: December 17, 2009
ATA System: 5365 2312
SUBJECT: FUSELAGE - Section 46 Skin - Fuselage Skin and Backup Structure Inspection and
Repair at the Lower VHF Antenna Cutout at Station 1197 + 99, Between Stringers 39L
and 39R
BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
Refer to Service Bulletin Index Document D624T001 Part 3 for Airplane Variable Number, Line
Number, and Serial Number data.
This service bulletin is for the airplanes shown below.
DESCRIPTIONCONFIGURATIONGROUP
767-300 airplanes. Line numbers 132-350 except 310, 323, 328,
331,and 332.
-1
Airplane Models:
767-300
GroupVariable Number
1VK001 - VK011
1VK021 - VK022
1VK031 - VK048
1VK081 - VK097
1VL001 - VL006
1VL011
1VN001 - VN015
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GroupVariable Number
1VN051 - VN060
1VN081 - VN088
1VN111 - VN119
1VN151 - VN156
1VN163 - VN166
1VN171 - VN173
1VN191 - VN192
1VN211 - VN212
1VN221 - VN222
1VN231 - VN234
1VN241
1VN251 - VN259
1VN291
1VN301 - VN303
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
Accomplishment of the inspections in this service bulletin will make sure that cracks in fuselage skin
around the VHF antenna and internal backup structure at station 1197+ 99 are found and repaired. If
not repaired, cracks in the fuselage skin and/or internal backup structure could result in unscheduled
repairs.
Two operators have reported cracks in the section 46 fuselage lower skin around the periphery of the
VHF antenna baseplate at station 1197+99. One operator reported 5 cracks with a maximum length
of 11 inches, found on an airplane with 38,804 total flight-hours/34,929 total flight-cycles. Another
operator reported a maximum crack length of 9.5 inches, found on an airplane with 60,467 total
flight-hours/29,185 total fight-cycles. Boeing investigation has revealed that the fuselage skin and/or
internal backup structure cracks are attributed to fatigue. This fatigue is the result of bending loads in
the skin, which are caused by vibration of the antenna in flight. No operator reported crack findings for
the backup structure.
This service bulletin gives instructions to do detail inspections for cracks, and repair if necessary, of
the fuselage skin and internal backup structure at the VHF antenna at station 1197+ 99.
Boeing Service Related Problem (SRP) 767-SRP-53-0323 is related to this service bulletin.
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D. Description
Part 1 - Fuselage Skin and Backup Structure Inspection. ( Initial Inspection )
Do an external Detail Inspection ( DI ) of the fuselage skin at the lower aft VHF antenna cutout and
internal DI of the backup structure for crack at station 1197+ 99 and do as follows:
Condition 1 ( No fuselage skin and backup structure crack found )
Do an external DI of the fuselage skin in accordance with Part 2 at the times given in Paragraph 1.E.
Table 2 Compliance.
Condition 2 ( Fuselage skin crack found )
Repair fuselage skin crack in accordance with 767-300 SRM.
Condition 3 ( Backup structure crack found )
Repair or replace cracked part(s).
Part 2 - Fuselage Skin Inspection ( Repeat Inspection )
Do an external DI of the fuselage skin for crack at the periphery of the antenna baseplate and do as
follows:
Condition 4 ( No fuselage skin crack found )
Repeat Part 2 Paragraph 1 inspection at the times given in Paragraph 1.E. Table 2 Compliance
Condition 5 ( Fuselage skin crack found )
Repair fuselage skin crack in accordance with 767-300 SRM
Airplanes after line number 350 incorporate an improved VHF antenna backup structure that makes
skin cracks around the antenna cutout less likely.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
155, 156767-300
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 1 - Initial Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later )
ActionCondition
-Within 3000
flight cycles af-
ter the date on
this service bul-
letin.
Within 25,000
total flight cy-
cles.
( 1 ) Do an external Detail
Inspection ( DI ) of the
fuselage skin with the an-
tenna removed, in accor-
dance with Accomplish-
ment Instructions Para-
graph 3.B. Part 1.
All airplanes
(a)
-Within 3,000
flight cycles af-
ter the date on
this service bul-
letin
Within 25,000
total flight cy-
cles.
( 2 ) Do an internal DI of
the antenna backup
structure in accordance
with Accomplishment In-
structions Paragraph 3.B.
Part 1. or
Within 6,000
flight cycles if no
fuselage skin
cracks are
found per exter-
nal detailed in-
spection. ( 1 )
---Go to Accomplishment
Instructions Paragraph
3.B. Part 2.
Condition 1 - No fuselage
skin and backup structure
crack found.
(b)-Before further
flight.
Repair fuselage skin
crack in accordance with
Accomplishment Instruc-
tions Paragraph 3.B. Part
1.
Condition 2 - Fuselage skin
crack found.
--Before further
flight.
Repair or replace cracked
part(s) in accordance with
Accomplishment Instruc-
tions Paragraph 3.B. Part
1.
Condition 3 - Backup
structure crack found.
(a) Airplanes with FAA approved repairs for skin cracking at this subject location prior to the release of this
service bulletin, do not require this service bulletin action.
(b) Do the repair in accordance with Accomplishment Instructions 3.B. Part 1 to terminate the inspections
in this service bulletin.
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Table 2 - Repeat Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
3,000 flight cycles.-Within 3,000
flight cycles
from last exter-
nal detailed in-
spection.
Do an external DI of the
fuselage skin without an-
tenna removal, in accor-
dance with Accomplish-
ment Instructions Para-
graph 3.B., Part 2.
Condition 4 - No fuselage
skin crack found.
(a)-Before further
flight.
Repair fuselage skin
crack in accordance with
Accomplishment Instruc-
tions Paragraph 3.B. Part
2.
Condition 5 - Fuselage skin
crack found.
(a) Do the repair in accordance with Accomplishment Instructions 3.B. Part 2 to terminate the inspections
in this service bulletin.
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.
No new DTI are required by this service bulletin.
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 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
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 Time to cure the materials
 Time to make the parts
 Time to find the tools.
Part 1 - Fuselage Skin and Backup Structure Inspection. ( Initial Inspection )
Condition 1 - No fuselage skin and backup structure crack found
Elapsed HoursTask HoursNumber of Per-
sons
Task
2.502.501Open Access
0.150.151Figure 1
2.002.001Figure 2
2.502.501Close Access
7.157.15TOTAL FOR EACH AIRPLANE
Condition 2 - Fuselage skin crack found
Elapsed HoursTask HoursNumber of Per-
sons
Task
2.502.501Open Access
0.150.151Figure 1
15.50(a)31.00(a)2Repair
2.502.501Close Access
20.6536.15TOTAL FOR EACH AIRPLANE
(a) Does not include time to make parts.
Condition 3 - Backup structure crack found
Elapsed HoursTask HoursNumber of Per-
sons
Task
2.502.501Open Access
2.002.001Figure 2
2.502.501Close Access
7.00(a)7.00(a)TOTAL FOR EACH AIRPLANE
(a) More time will be necessary for repair or replace cracked part(s).
Part 2 - Fuselage Skin Inspection. ( Repeat Inspection )
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Condition 4 - No fuselage skin crack found
Elapsed HoursTask HoursNumber of Per-
sons
Task
0.150.151Figure 3
0.150.15TOTAL FOR EACH AIRPLANE
Condition 5 - Fuselage skin crack found
Elapsed HoursTask HoursNumber of Per-
sons
Task
2.502.501Open Access
15.50(a)31.00(a)2Repair
2.502.501Close Access
20.5036.00TOTAL FOR EACH AIRPLANE
(a) Does not include time to make parts.
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not changed.
J. References
1. Existing Data
a. 767 Aircraft Maintenance Manual (AMM) 23-12-03, 25-52-03, and 53-01-05.
b. 767-300 Structural Repair Manual (SRM) 53-60-01.
c. Service Related Problem (SRP) 767-SRP-53-0323.
2. Data supplied with this Service Bulletin
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin
TitleDrawing Number
Panel Integration - Antenna Provisions146T0012
This drawing is used to prepare this service bulletin. This drawing is not necessary to make the
specified changes, and is not supplied with this service bulletin. This drawing may not be applicable
to all airplane configurations or operators.
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K. Publications Affected
Chapter-SectionPublication
53-60767 Structural Repair Manual
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
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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 configuration changes, inspection, and/or 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.
NOTE: No parts or materials are required for inspection. However, if repairs are necessary, the
materials shown in the applicable Structural Repair Manual sections will be necessary.
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. The instructions identified in Paragraph 3.B., Work Instructions and the Figure(s)
give the recommended sequence of steps. The sequence of steps to do this service
bulletin can be changed.
2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
3. Obey all of the warnings and cautions given in the specified manual sections.
4. 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.
5. 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.
B. WORK INSTRUCTIONS
Part 1 - Fuselage Skin and Backup Structure Inspection ( Initial Inspection )
1. Remove/keep lower VHF antenna at station 1197 + 99. Refer to 767 AMM 23-12-03 as an
acceptable procedure.
2. Do an external Detailed Inspection ( DI ) of the fuselage skin with the antenna removed at the
lower aft VHF antenna cutout in accordance with Figure 1 and at the time given in Paragraph 1.E.
Table 1 Compliance.
NOTE: If no fuselage skin cracks are found, the following internal DI of the backup structure for
crack inspection can be deferred in accordance with Paragraph 1.E. Table 1 Compliance.
3. Remove/keep cargo floor panel at station 1197+ 99, S-39L to S-39R approximately. Refer to 767
AMM 53-01-05 as an acceptable procedure.
4. Remove/keep insulation blankets at station 1197+ 99, S-39L to S-39R approximately. Refer to
767 AMM 25-52-03 as an acceptable procedure.
5. Do an internal DI of the backup structure for crack in accordance with Figure 2 and at the times
given in Paragraph 1.E. Table 1 Compliance and do as follows:
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Condition 1 - ( No fuselage skin and backup structure crack found )
a. Install/kept insulation blankets. Refer to 767 AMM 25-52-03 as an acceptable procedure.
b. Install/kept cargo floor panel. Refer to 767 AMM 53-01-05 as an acceptable procedure.
c. Install/kept lower VHF antenna at station 1197+ 99. Refer to 767 AMM 23-12-03 as an
acceptable procedure.
d. Go to Part 2.
Condition 2 - ( Fuselage skin crack found )
a. Repair fuselage skin crack in accordance with 767-300 SRM 53-60-01, Repair 2 before further
flight.
NOTE: Accomplishment of this repair terminates the Part 2 repeat inspection in this service
bulletin.
b. Install/kept insulation blankets. Refer to 767 AMM 25-52-03 as an acceptable procedure.
c. Install/kept cargo floor panel. Refer to 767 AMM 53-01-05 as an acceptable procedure.
d. Install/kept lower VHF antenna at station 1197+ 99. Refer to 767 AMM 23-12-03 as an
acceptable procedure.
Condition 3 - ( Backup structure crack found )
a. Repair or replace cracked part(s) before further flight.
b. Install/kept insulation blankets. Refer to 767 AMM 25-52-03 as an acceptable procedure.
c. Install/kept cargo floor panel. Refer to 767 AMM 53-01-05 as an acceptable procedure.
d. Install/kept lower VHF antenna at station 1197+ 99. Refer to 767 AMM 23-12-03 as an
acceptable procedure.
6. Put the airplane back to a serviceable condition.
Part 2 - Fuselage Skin Inspection ( Repeat Inspection )
1. Do an external DI of the fuselage skin without antenna removal for crack at the periphery of the
antenna baseplate in accordance with Figure 3 and at the times given in Paragraph 1.E. Table 2
Compliance and do as follows:
Condition 4 - ( No fuselage skin crack found )
a. Repeat Part 2 Paragraph 1 inspection at the times given in Paragraph 1.E. Table 2 Compliance.
Condition 5 - ( Fuselage skin crack found )
a. Repair fuselage skin crack in accordance with 767-300 SRM 53-60-01, Repair 2 before further
flight.
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### Page 21

NOTE: Accomplishment of this repair terminates the Part 2 repeat inspection in this service
bulletin.
2. Put the airplane back to a serviceable condition.
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### Page 22 (OCR)

BOEING SERVICE BULLETIN 767-53-0207
BS
1197+99
TYPICAL CRACK
BL O
1573542
FIGURE 1: FUSELAGE SKIN WITH THE ANTENNA REMOVED - INSPECTION
(SHEET 1 OF 2)
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Copyright © Unpublished Work - See page 1 for details.  22 of 27

### Page 23

The step number shown below agree with the number shown in the circle symbol in the figure.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a)--Fuselage SkinInspect1
(a) Detail inspection for cracks in the fuselage skin under the VHF antenna and a 2 inch periphery around
the antenna footprint.
FIGURE 1: FUSELAGE SKIN WITH THE ANTENNA REMOVED - INSPECTION
(SHEET 2 OF 2)
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### Page 24 (OCR)

BOEING SERVICE BULLETIN 767-53-0207
I S-39L
S-39R
(INTERNAL VIEW OF BACKUP STRUCTURE)  1573434
TYPICAL VIEW
FIGURE 2: BACKUP STRUCTURE - INSPECTION
(SHEET 1 OF 2)
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### Page 25

The step number shown below agree with the number shown in the circle symbol in the figure.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a) (b)--Backup StructureInspect1
(a) Detail inspection for cracks of the backup structure between stringer 39L and 39R including stringers and
between station 1197+ 88 and 1197+110.
(b) Backup structure consist of nut plate assemblies, channels, clips, and support bracket.
FIGURE 2: BACKUP STRUCTURE - INSPECTION
(SHEET 2 OF 2)
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BOEING SERVICE BULLETIN 767-53-0207

### Page 26 (OCR)

BOEING SERVICE BULLETIN 767-53-0207
BS
1197+99
TYPICAL CRACK
BLO
1573543
FIGURE 3: FUSELAGE SKIN WITHOUT ANTENNA REMOVED - INSPECTION
(SHEET 1 OF 2)
Original Issue: December 17, 2009
BOEING PROPRIETARY -  767-53-0207
Copyright © Unpublished Work - See page 1 for details.  26 of 27

### Page 27

The step number shown below agree with the number shown in the circle symbol in the figure.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a)--Fuselage SkinInspect1
(a) Detail inspection for cracks in the fuselage skin around 2 inch periphery around the antenna baseplate.
FIGURE 3: FUSELAGE SKIN WITHOUT ANTENNA REMOVED - INSPECTION
(SHEET 2 OF 2)
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Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 17, 2009
767-53-0207
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BOEING SERVICE BULLETIN 767-53-0207

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