# Boeing Service Bulletin A3543: No revision named

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- Document: [Boeing Service Bulletin A3543](https://openairdocs.org/service-documents/boeing/a3543.md)
- Title as filed: SB-707-00A3543-R00--
- Pages: 52
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## Text

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### Page 1

Commercial 
Airplanes
707
Service Bulletin
ALERT
Number: A3543
Original Issue: September 15, 2016
ATA System: 5304
SUBJECT: FUSELAGE - Aft Fuselage Section - STA 1440 Aft Pressure Bulkhead Web Inspection
for Oil Canning
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 300-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET
Copyright © 2016 Boeing.
Unpublished Work. All Rights Reserved.
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document
are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The
Boeing Company.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and
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.
Original Issue: September 15, 2016
A3543
1 of 52
3.0

### Page 2

Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: September 15, 2016
A3543
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BOEING SERVICE BULLETIN A3543
ALERTALERT
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### Page 3

Table of Contents
Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14
E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14
F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18
G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18
H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18
I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18
J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 19
K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 21
3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 21
3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24
FIGURE 1: STA 1440 AFT PRESSURE BULKHEAD WEB - DETAILED INSPECTION . . . . . . . . 28
FIGURE 2: STA 1440 AFT PRESSURE BULKHEAD WEB - OIL CANNING ZONE DETERMINATION AND
DETAILED INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31
FIGURE 3: STA 1440 AFT PRESSURE BULKHEAD WEB - DETAILED INSPECTION AND EDDY CURRENT
INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38
FIGURE 4: STA 1440 AFT PRESSURE BULKHEAD WEB - Y-CHORD - DETAILED INSPECTION AND
EDDY CURRENT INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42
FIGURE 5: STA 1440 AFT PRESSURE BULKHEAD WEB - HIGH FREQUENCY EDDY CURRENT (HFEC)
INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 47
APPENDIX A: TABLE 1: STA 1440 AFT PRESSURE BULKHEAD WEB INSPECTION FOR OIL CANNING
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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A3543
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### Page 5

Commercial 
Airplanes
707
Service Bulletin
ALERT
SummaryNumber: A3543Original Issue: September 15, 2016
ATA System: 5304
SUBJECT: FUSELAGE - Aft Fuselage Section - STA 1440 Aft Pressure Bulkhead Web Inspection
for Oil Canning
THIS DOCUMENT 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 DOCUMENT
TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE
NEW OWNER.
CONCURRENT REQUIREMENTS
None.
BACKGROUND
This service bulletin gives instructions to inspect for any oil canning and any crack on the STA 1440 aft pressure
bulkhead web. If the work given in this service bulletin is not accomplished, a fatigue crack caused by oil canning
may go undetected. An undetected fatigue crack in the aft pressure bulkhead web could grow in length and may
result in reduced structural integrity of the web and lead to rapid decompression of the airplane.
Accomplishment of the inspections in this service bulletin will enable early detection of any web fatigue crack
at oil canning locations.
Oil canning is defined as a locally buckled forward area of the aft pressure bulkhead web between the radial
stiffeners and the circumferential tear straps which can pop outward when the fuselage is pressurized causing
a stress reversal cycle during each flight that may lead to fatigue cracking of the aft pressure bulkhead web.
Boeing Service Related Problem 707-SRP-53-0445 is related to this service bulletin.
Boeing Fleet Team Digest 707 FTD 53-16001 is related to this service bulletin.
This table is provided to operators for planning purposes only. Refer to the applicable sections for more
information.
ReferenceAffectedPlanning Data
Paragraph 1.A.2., Spares AffectedNoSpares Affected
Paragraph 1.E., Compliance and Paragraph
1.F., Approval
YesAD Related
Paragraph 1.H., Weight and Balance ChangesNoWeight and Balance Change
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### Page 6

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/PartsNoKits/Parts Required
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
NoOperator Supplied Parts/Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
ACTION
Get access to the aft side of the STA 1440 aft pressure bulkhead web and do a detailed inspection for any oil
canning. If no oil canning is found do repeat inspections for any oil canning. If any oil canning is found, determine
if the oil canning is within Zone 1 limits, do a detailed inspection for any damage or any irregularity and do an
eddy current inspection for any crack from the forward or aft side of the STA 1440 aft pressure bulkhead web.
If any oil canning is found within Zone 1 limits and no crack is found, then do one of the following options. Option
1 do repeat inspections and then contact The Boeing Company for repair instructions and do the repair. Option
2 contact The Boeing Company for repair instructions and do the repair.
If any oil canning is found with any damage or any irregularity, contact The Boeing Company for repair instructions
and do the repair.
If any oil canning is found within Zone 2 limits or if any crack is found, contact The Boeing Company for repair
instructions and do the repair.
EFFECTIVITY
707-100 LONG BODY, 707-100B LONG BODY, 707-100B SHORT BODY, 707-200, 707-300, 707-300B,
707-300C, 707-400, 720, 720B 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 for compliance information.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the inspection, and/or repair procedures given in this service
bulletin.
Export Controlled ECCN: 9E991 - BOEING
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MANPOWER
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
None.
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### Page 8 (OCR)

BOEING SERVICE BULLETIN A3543
ALERT  ALERT
, RADIAL STIFFENER
CIRCUMFERENTIAL
TEAR STRAPS
WEB LAP
SPLICES
Y CHORD
AFT PRESSURE
BULKHEAD WEB
VIEW LOOKING FORWARD
GET ACCESS TO THE AFT SIDE OF THE STA 1440 AFT PRESSURE BULKHEAD WEB AND DO A DETAILED
INSPECTION FOR ANY OIL CANNING. IF NO OIL CANNING IS FOUND DO REPEAT INSPECTIONS FOR ANY OIL
CANNING. IF ANY OIL CANNING IS FOUND, DETERMINE IF THE OIL CANNING IS WITHIN ZONE 1 LIMITS, DO A
DETAILED INSPECTION FOR ANY DAMAGE OR ANY IRREGULARITY AND DO AN EDDY CURRENT INSPECTION
FOR ANY CRACK FROM THE FORWARD OR AFT SIDE OF THE STA 1440 AFT PRESSURE BULKHEAD WEB.
IF ANY OIL CANNING IS FOUND WITHIN ZONE 1 LIMITS AND NO CRACK IS FOUND, THEN DO ONE OF THE
FOLLOWING OPTIONS. OPTION 1: DO REPEAT INSPECTIONS AND THEN CONTACT THE BOEING COMPANY
FOR REPAIR INSTRUCTIONS AND DO THE REPAIR. OPTION 2: CONTACT THE BOEING COMPANY FOR REPAIR
INSTRUCTIONS AND DO THE REPAIR.
IF ANY OIL CANNING IS FOUND WITH ANY DAMAGE OR ANY IRREGULARITY, CONTACT THE BOEING
COMPANY FOR REPAIR INSTRUCTIONS AND DO THE REPAIR.
IF ANY OIL CANNING IS FOUND WITHIN ZONE 2 LIMITS OR IF ANY CRACK IS FOUND, CONTACT THE BOEING
COMPANY FOR REPAIR INSTRUCTIONS AND DO THE REPAIR.
Original Issue: September 15, 2016
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  A3543
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### Page 9

Commercial 
Airplanes
707
Service Bulletin
ALERT
Number: A3543
Original Issue: September 15, 2016
ATA System: 5304
SUBJECT: FUSELAGE - Aft Fuselage Section - STA 1440 Aft Pressure Bulkhead Web Inspection
for Oil Canning
THIS DOCUMENT 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 DOCUMENT
TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE
NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
This service bulletin is applicable to 707/720 airplanes, line numbers 1 thru 941 in 1 Group. The
Variable Numbers and Group Information for the applicable airplanes is given below.
Refer to Service Bulletin Index D6-1647 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
DESCRIPTIONCONFIGURATIONGROUP
707-100 LONG BODY, 707-100B LONG BODY, 707-100B SHORT
BODY, 707-200, 707-300, 707-300B, 707-300C, 707-400, 720, 720B
airplanes.
-1
Airplane Models:
707-100 LONG BODY, 707-100B LONG BODY, 707-100B SHORT BODY, 707-200, 707-300,
707-300B, 707-300C, 707-400, 720, 720B
GroupVariable Number
1B0001 - B0029
1B0101 - B0125
1B0201 - B0203
1B0301 - B0306
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### Page 10

GroupVariable Number
1B0401 - B0402
1B0501 - B0515
1B2001 - B2008
1B2091 - B2092
1B2101 - B2116
1B2191 - B2194
1B2199
1B2201 - B2227
1B2401 - B2403
1B2501 - B2502
1B2551 - B2553
1B2601 - B2608
100001 - 00002
100004 - 00006
100101
100103 - 00113
100115 - 00153
100201 - 00205
100301 - 00305
100401 - 00449
100471 - 00475
100501 - 00513
100601
100701 - 00703
102001 - 02020
102101 - 02121
102201 - 02207
102301 - 02303
102401 - 02418
104001 - 04005
104020 - 04022
104101 - 04106
104201 - 04218
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GroupVariable Number
104271 - 04272
104301 - 04303
105001 - 05060
105101 - 05138
105201 - 05208
105301 - 05312
105401
105601 - 05605
105631 - 05635
105701 - 05703
105801 - 05802
105821 - 05827
105831 - 05833
105851 - 05854
105891 - 05892
105921 - 05923
105941 - 05942
105961 - 05970
106001 - 06002
106101
106401 - 06404
106451
106461
107001 - 07017
107041 - 07059
107071 - 07081
107101 - 07109
107181
107191
107201 - 07215
107251 - 07271
107401 - 07407
107451 - 07458
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GroupVariable Number
107501 - 07504
107601 - 07626
107661 - 07662
107681 - 07684
107701 - 07702
107801 - 07821
107901 - 07907
108001 - 08008
108021
108051 - 08056
108071 - 08077
108101 - 08104
108121 - 08129
108141 - 08144
108151 - 08153
108171 - 08173
108191 - 08192
108201 - 08210
108221 - 08224
108241 - 08244
108251
108261
108271
108301 - 08320
108324 - 08330
108333
108401 - 08410
108451 - 08452
108471 - 08475
108501 - 08502
108551 - 08553
108581 - 08582
109001 - 09006
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GroupVariable Number
109101 - 09107
109161 - 09167
109201 - 09204
109221 - 09223
109227
109231 - 09232
109251
109271
109281
109286 - 09290
109411
109421
109438
109441
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
This service bulletin gives instructions to inspect for any oil canning and any crack on the STA 1440
aft pressure bulkhead web. If the work given in this service bulletin is not accomplished, a fatigue crack
caused by oil canning may go undetected. An undetected fatigue crack in the aft pressure bulkhead
web could grow in length and may result in reduced structural integrity of the web and lead to rapid
decompression of the airplane.
Accomplishment of the inspections in this service bulletin will enable early detection of any web fatigue
crack at oil canning locations.
Oil canning is defined as a locally buckled forward area of the aft pressure bulkhead web between the
radial stiffeners and the circumferential tear straps which can pop outward when the fuselage is
pressurized causing a stress reversal cycle during each flight that may lead to fatigue cracking of the
aft pressure bulkhead web.
Boeing Service Related Problem 707-SRP-53-0445 is related to this service bulletin.
Boeing Fleet Team Digest 707 FTD 53-16001 is related to this service bulletin.
Export Controlled ECCN: 9E991 - BOEING
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### Page 14

D. Description
Get access to the aft side of the STA 1440 aft pressure bulkhead web and do a detailed inspection for
any oil canning. If no oil canning is found do repeat inspections for any oil canning. If any oil canning
is found, determine if the oil canning is within Zone 1 limits, do a detailed inspection for any damage
or any irregularity and do an eddy current inspection for any crack from the forward or aft side of the
STA 1440 aft pressure bulkhead web.
If any oil canning is found within Zone 1 limits and no crack is found, then do one of the following
options. Option 1 do repeat inspections and then contact The Boeing Company for repair instructions
and do the repair. Option 2 contact The Boeing Company for repair instructions and do the repair.
If any oil canning is found with any damage or any irregularity, contact The Boeing Company for repair
instructions and do the repair.
If any oil canning is found within Zone 2 limits or if any crack is found, contact The Boeing Company
for repair instructions and do the repair.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
1-37707-100 LONG BODY, 707-
100B LONG BODY, 707-100B
SHORT BODY, 707-200, 707-
300, 707-300B, 707-300C, 707-
400, 720, 720B
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.
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.
Accomplish the required action(s), based on the applicable conditions in Table 1, in accordance with
Paragraph 3. Accomplishment Instructions.
A logic diagram showing compliance tasks and compliance times is included as an aid in APPENDIX
A.
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### Page 15

Table 1: STA 1440 AFT PRESSURE BULKHEAD WEB INSPECTION FOR OIL CANNING:
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 1,200
flight cycles af-
ter the original
issue date of
this service bul-
letin.
Before 15,000
total flight cy-
cles.
Do PART 2: DETAILED
INSPECTION OF THE
STA 1440 AFT PRES-
SURE BULKHEAD WEB
for any oil canning.
All Airplanes.
6,000 flight cycles.--Repeat PART 2: DE-
TAILED INSPECTION
OF THE STA 1440 AFT
PRESSURE BULKHEAD
WEB for any oil canning.
CONDITION 1: NO OIL
CANNING FOUND.
--Before further
flight.
CONDITION 2 (ACTION
1): Do PART 3: OIL
CANNING ZONE DETER-
MINATION AND DE-
TAILED INSPECTION for
any damage or any irreg-
ularity. (a)
CONDITION 2: ANY OIL
CANNING FOUND.
--Before further
flight.
CONDITION 2 (ACTION
2): Do PART 4: DE-
TAILED INSPECTION
AND EDDY CURRENT
INSPECTION for any
crack.
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Table 1: STA 1440 AFT PRESSURE BULKHEAD WEB INSPECTION FOR OIL CANNING:
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
1,200 flight cycles.--OPTION 1 (ACTION 1):
Repeat PART 4: DE-
TAILED INSPECTION
AND EDDY CURRENT
INSPECTION for any
crack.
CONDITION 2.1: ANY OIL
CANNING FOUND WITH-
IN ZONE 1 LIMITS AND
NO CRACK FOUND.
--Within 12,000
flight cycles
from the time
the oil canning
condition was
initially found.
OPTION 1 (ACTION 2):
Contact The Boeing
Company for repair in-
structions and do the re-
pair.
6,000 flight cycles--OPTION 1 (ACTION 3):
Repeat PART 2: DE-
TAILED INSPECTION
OF THE STA 1440 AFT
PRESSURE BULKHEAD
WEB for any oil canning
at unrepaired areas.
--Before further
flight.
OPTION 2 (ACTION 1):
Contact The Boeing
Company for repair in-
structions and do the re-
pair.
6,000 flight cycles--OPTION 2 (ACTION 2):
Repeat PART 2: DE-
TAILED INSPECTION
OF THE STA 1440 AFT
PRESSURE BULKHEAD
WEB for any oil canning
at unrepaired areas.
--Before further
flight.
CONDITION 2.2 (AC-
TION 1): Contact The
Boeing Company for re-
pair instructions and do
the repair.
CONDITION 2.2: ANY OIL
CANNING FOUND WITH
ANY DAMAGE OR ANY
IRREGULARITY. (a)
6,000 flight cycles--CONDITION 2.2 (AC-
TION 2): Repeat PART 2:
DETAILED INSPECTION
OF THE STA 1440 AFT
PRESSURE BULKHEAD
WEB for any oil canning
at unrepaired areas.
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Table 1: STA 1440 AFT PRESSURE BULKHEAD WEB INSPECTION FOR OIL CANNING:
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
--Before further
flight.
CONDITION 2.3 (AC-
TION 1): Contact The
Boeing Company for re-
pair instructions and do
the repair.
CONDITION 2.3: ANY OIL
CANNING FOUND WITH-
IN ZONE 2 LIMITS AND
NO CRACK FOUND.
6,000 flight cycles--CONDITION 2.3 (AC-
TION 2): Repeat PART 2:
DETAILED INSPECTION
OF THE STA 1440 AFT
PRESSURE BULKHEAD
WEB for any oil canning
at unrepaired areas.
--Before further
flight.
CONDITION 2.4 (AC-
TION 1): Do PART 5:
HIGH FREQUENCY ED-
DY CURRENT (HFEC)
INSPECTION for crack
location, length, and orien-
tation.
CONDITION 2.4: ANY OIL
CANNING FOUND WITH
ANY CRACK FOUND.
--Before further
flight.
CONDITION 2.4 (AC-
TION 2): Contact The
Boeing Company for re-
pair instructions and do
the repair.
6,000 flight cycles--CONDITION 2.4 (AC-
TION 3): Repeat PART 2:
DETAILED INSPECTION
OF THE STA 1440 AFT
PRESSURE BULKHEAD
WEB for any oil canning
at unrepaired areas.
(a) Any damage can include, any sharp creases, any gouges, any crack, any deformation to a radial stiffener,
circumferential tear strap, Y-chord or terminal fitting splice plate, or any damaged holes.
Any irregularity can include, any loose or missing fasteners, any pressure leakage, any fasteners within
1.0 inch of any oil canning location or any oil canning location within 2.0 inch inches of any other oil
canning location.
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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
• Time to make the parts
• Time to find the tools
Elapsed HoursTask HoursNumber of PersonsTask
13.0026.002Open Access
6.006.001FIGURE 1
0.500.501FIGURE 2 (a)
4.004.001FIGURE 3 (a)
8.708.701FIGURE 4 (a)
1.251.251FIGURE 5 (a)
16.0032.002Close Access
35.0064.00TOTAL FOR EACH AIRPLANE
(a) Estimate given is per oil canning location and must be multiplied by the number
of oil canning locations found after inspection in FIGURE 1 and added to total
shown to arrive at a revised total required.
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not applicable.
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J. References
1. Existing Data:
a. Boeing Service Related Problem (SRP) 707-SRP-53-0445
b. Service Bulletin Index D6-1647
c. 707, 720 Non-Destructive Testing (NDT) Manual Part 6, 51-00-00, Figure 16, Part 6, 51-00-00,
Figure 4 or Figure 23, Part 6, 53-10-07, Figure 18
d. 707 Fleet Team Digest (FTD) 53-16001
e. 707 Airplane Maintenance Manual (AMM) Section 25-18-0, 12-02-0
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
BULKHEAD INSTALLATION - STATION 144005-86000
The table above lists applicable drawings used to prepare this service bulletin. The drawings are
not necessary to make the specified changes, and are not supplied with this service bulletin. The
drawings may not be applicable to all airplane configurations or operators.
K. Publications Affected
1. Publications:
None.
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin affects FCS but no new DTIs are necessary.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
M. Software Accomplishment Summary
Not affected.
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### Page 21

2.    MATERIAL INFORMATION
A. Material - Price and Availability
None.
B. Industry Support Information
Boeing warranty remedies are not available for the inspection given in this service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts
None.
2. Parts and Materials Supplied by the Operator
None.
3. Parts Modified and Reidentified
None.
4. Parts Removed and Not Replaced
None.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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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 707 Structural Repair Manual,
Chapter 51.
— Values for airframe maintenance tasks are included in Chapter 20 of 707
Aircraft Maintenance Manual (AMM).
— Values for electrical maintenance tasks are included in Chapter 20 of
Standard Wiring Practices Manual (SWPM).
— Values for engine maintenance tasks are included in Chapter 70 of 707
Aircraft Maintenance Manual (AMM).
— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
4. 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.
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.
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6. When requesting repair information, refer to Boeing Service Letter 707-SL-51-029,
Damage Reporting and Repair Plan/Design Guidelines, is an acceptable procedure
to request information from Boeing for structural repair instructions. The Service
Letter describes what information must be provided to Boeing before a structural
repair can be provided.
7. Refer to APPENDIX A for logic diagram(s). Logic diagrams are 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.
8. 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.
9. 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.
10. If shading is used, shaded areas in Figures are to separate the non-critical and
non-authoritative information from the critical and authoritative information.
11. Use of colors in Figures is based on guidance from the ATA e-Business Program
(ATA) iSpec 2200.
12. 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.
13. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
14. Some steps in the Work Instructions are labeled as Required for Compliance (RC).
If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps
labeled as RC, including sub-steps under an RC step and any figures identified in
an RC step, must be done to comply with the AD. If a step or sub-step is labeled
"RC Exempt," then the RC requirement is removed from that step or sub-step. An
Alternative Method of Compliance (AMOC) is required for any deviations to RC steps,
including sub-steps and identified figures. Steps not labeled as RC may be deviated
from using accepted methods in accordance with the operator's maintenance or
inspection program without obtaining approval of an AMOC. This is provided that
the RC steps, including sub-steps and identified figures, can still be done as specified,
and the airplane can be put back in an airworthy condition.
B. WORK INSTRUCTIONS
1. Do PART 1: OPEN ACCESS.
2. RC - Do PART 2: DETAILED INSPECTION OF THE STA 1440 AFT PRESSURE BULKHEAD
WEB for any oil canning.
a. CONDITION 1: NO OIL CANNING FOUND.
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(1) Repeat PART 2: DETAILED INSPECTION OF THE STA 1440 AFT PRESSURE
BULKHEAD WEB for any oil canning at the time given in Paragraph 1.E., Compliance.
b. CONDITION 2: ANY OIL CANNING FOUND.
(1) CONDITION 2 (ACTION 1): Do PART 3: OIL CANNING ZONE DETERMINATION AND
DETAILED INSPECTION for any damage or any irregularity.
NOTE: Any damage can include, any sharp creases, any gouges, any crack, any
deformation to a radial stiffener, circumferential tear strap, Y-chord or terminal
fitting splice plate, or any damaged holes.
Any irregularity can include, any loose or missing fasteners, any pressure
leakage, any fasteners within 1.0 inch of any oil canning location or any oil
canning location within 2.0 inch inches of any other oil canning location.
(2) CONDITION 2 (ACTION 2): Do PART 4: DETAILED INSPECTION AND EDDY CURRENT
INSPECTION for any crack.
(a) CONDITION 2.1: ANY OIL CANNING FOUND WITHIN ZONE 1 LIMITS AND NO
CRACK FOUND.
1) OPTION 1 (ACTION 1): Repeat PART 4: DETAILED INSPECTION AND EDDY
CURRENT INSPECTION for any crack at the time given in Paragraph 1.E.,
Compliance.
2) OPTION 1 (ACTION 2): Contact The Boeing Company for repair instructions
and do the repair.
3) OPTION 1 (ACTION 3): Repeat PART 2: DETAILED INSPECTION OF THE
STA 1440 AFT PRESSURE BULKHEAD WEB for any oil canning at unrepaired
areas at the time given in Paragraph 1.E., Compliance.
4) OPTION 2 (ACTION 1): Contact The Boeing Company for repair instructions
and do the repair.
5) OPTION 2 (ACTION 2): Repeat PART 2: DETAILED INSPECTION OF THE
STA 1440 AFT PRESSURE BULKHEAD WEB for any oil canning at unrepaired
areas at the time given in Paragraph 1.E., Compliance.
(b) CONDITION 2.2: ANY OIL CANNING FOUND WITH ANY DAMAGE OR ANY
IRREGULARITY.
NOTE: Any damage can include, any sharp creases, any gouges, any crack, any
deformation to a radial stiffener, circumferential tear strap, Y-chord or
terminal fitting splice plate, or any damaged holes.
Any irregularity can include, any loose or missing fasteners, any pressure
leakage, any fasteners within 1.0 inch of any oil canning location or any oil
canning location within 2.0 inch inches of any other oil canning location.
1) CONDITION 2.2 (ACTION 1): Contact The Boeing Company for repair
instructions and do the repair.
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2) CONDITION 2.2 (ACTION 2): Repeat PART 2: DETAILED INSPECTION OF
THE STA 1440 AFT PRESSURE BULKHEAD WEB for any oil canning at
unrepaired areas at the time given in Paragraph 1.E., Compliance.
(c) CONDITION 2.3: ANY OIL CANNING FOUND WITHIN ZONE 2 LIMITS AND NO
CRACK FOUND.
1) CONDITION 2.3 (ACTION 1): Contact The Boeing Company for repair
instructions and do the repair.
2) CONDITION 2.3 (ACTION 2): Repeat PART 2: DETAILED INSPECTION OF
THE STA 1440 AFT PRESSURE BULKHEAD WEB for any oil canning at
unrepaired areas at the time given in Paragraph 1.E., Compliance.
(d) CONDITION 2.4: ANY OIL CANNING FOUND WITH ANY CRACK FOUND.
1) CONDITION 2.4 (ACTION 1): Do PART 5: HIGH FREQUENCY EDDY CURRENT
(HFEC) INSPECTION for crack location, length, and orientation.
2) CONDITION 2.4 (ACTION 2): Contact The Boeing Company for repair
instructions and do the repair.
3) CONDITION 2.4 (ACTION 3): Repeat PART 2: DETAILED INSPECTION OF
THE STA 1440 AFT PRESSURE BULKHEAD WEB for any oil canning at
unrepaired areas at the time given in Paragraph 1.E., Compliance.
3. Do PART 6: CLOSE ACCESS.
4. Put airplane back to a serviceable condition.
PART 1: OPEN ACCESS
1. Get access to the aft side of the STA 1440 aft pressure bulkhead web. Remove and keep stabilizer
jackscrew access panel No. 1185. Refer to 707 Airplane Maintenance Manual (AMM) Section
12-02-0 as an accepted procedure.
PART 2: DETAILED INSPECTION OF THE STA 1440 AFT PRESSURE BULKHEAD WEB
1. Do a detailed inspection for any oil canning on the STA 1440 aft pressure bulkhead web in
accordance with FIGURE 1.
PART 3: OIL CANNING ZONE DETERMINATION AND DETAILED INSPECTION
1. Determine if oil canning is in Zone 1 or Zone 2 and do a detailed inspection for any damage or
any irregularity in accordance with FIGURE 2.
PART 4: DETAILED INSPECTION AND EDDY CURRENT INSPECTION
1. If the oil canning condition is in either the middle or inner bay web sections, do a detailed inspection,
surface High Frequency Eddy Current (HFEC) inspection and Low Frequency Eddy Current (LFEC)
inspection for any crack in accordance with FIGURE 3.
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2. If the oil canning condition is in the outer bay web section common to the Y-chord, do the steps
that follow:
a. RC Exempt - Get access to the forward side of the STA 1440 aft pressure bulkhead web.
Remove and keep floor panels and either one or both C and D lavatories. Refer to 707 AMM,
Section 25-18-0 as an accepted procedure.
b. Do a detailed inspection, surface HFEC inspection and LFEC inspection for any crack in
accordance with FIGURE 4.
PART 5: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION
1. Do an HFEC inspection from the forward side of the affected location and find the crack location,
length, and orientation in accordance with FIGURE 5.
PART 6: CLOSE ACCESS
1. Install kept floor panels and either one or both C and D lavatories that were previously removed
to gain access to the forward side. Refer to 707 AMM Section 25-18-0 as an accepted procedure.
2. Install kept stabilizer jackscrew access panel No. 1185. Refer to 707 AMM Section 12-02-0 as an
accepted procedure.
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### Page 28 (OCR)

BOEING SERVICE BULLETIN А3543
ALERT  ALERT
TYPICAL OIL
CANNING
CIRCUMFERENTIAL
TEAR STRAPS
WEB LAP SPLICE'
RADIAL
STIFFENERS
AFT PRESSURE
INSPECTION AREA  VIEW LOOKING FORWARD  BULKHEAD WEB  2506408
A-A
FIGURE 1: STA 1440 AFT PRESSURE BULKHEAD WEB - DETAILED INSPECTION
(SHEET 1 OF 3)
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### Page 29 (OCR)

BOEING SERVICE BULLETIN А3543
ALERT  ALERT
AFT PRESSURE
BULKHEAD WEB
ORIGINAL
CONTOUR
TYPICAL OIL
CANNING
OIL CANNING
(TYPICAL)
B-B
INSPECTION AREA  2508264
FIGURE 1: STA 1440 AFT PRESSURE BULKHEAD WEB - DETAILED INSPECTION
(SHEET 2 OF 3)
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### Page 30

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a) (b) (c) (d)1STA 1440Aft Pressure Bulkhead
Web
Inspect1
(a) Do a detailed inspection for any oil canning on the STA 1440 aft pressure bulkhead web.
(b) When inspecting for oil canning, make sure the airplane is not jacked, cradled, or supported at or aft of
the STA 1440 aft pressure bulkhead web.
(c) Use a flashlight held parallel to the STA 1440 aft pressure bulkhead web surface to highlight oil canning.
(d) An oil canning condition is an area on the STA 1440 aft pressure bulkhead web that is visibly displaced
forward from initial contour of the STA 1440 aft pressure bulkhead web. Refer to view B-B.
FIGURE 1: STA 1440 AFT PRESSURE BULKHEAD WEB - DETAILED INSPECTION
(SHEET 3 OF 3)
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BOEING SERVICE BULLETIN А3543
ALERT  ALERT
3) SPLICE PLATE
FIN TERMINAL
FITTING
CIRCUMFERENTIAL
TEAR STRAPS
WEB LAP SPLICE
RADIAL
STIFFENERS
TYPICAL OIL
CANNING
AFT PRESSURE
INSPECTION AREA  VIEW LOOKING FORWARD  BULKHEAD WEB  2506434
A-A
FIGURE 2: STA 1440 AFT PRESSURE BULKHEAD WEB - OIL CANNING ZONE DETERMINATION AND
DETAILED INSPECTION
(SHEET 1 OF 7)
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### Page 32 (OCR)

BOEING SERVICE BULLETIN А3543
ALERT  ALERT
AFT PRESSURE
BULKHEAD WEB
FLEXIBLE METAL
/ STRIP
OUTER EDGE OF
OIL CANNING
ORIGINAL
CONTOUR
D = DEPTH OF OIL CANNING
CONCAVE FORWARD
W = MEASURED ACROSS
MINIMUM WIDTH OF OIL
CANNING AT PERIMETER
WD
OIL CANNING
(TYPICAL)
B-B
2506753
FIGURE 2: STA 1440 AFT PRESSURE BULKHEAD WEB - OIL CANNING ZONE DETERMINATION AND
DETAILED INSPECTION
(SHEET 2 OF 7)
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### Page 33 (OCR)

BOEING SERVICE BULLETIN А3543
ALERT  ALERT
RADIAL STIFFENER
D  (2) OIL CANNING
CIRCUMFERENTIALS
TEAR STRAP
RADIAL STIFFENER
OIL CANNING (2
WEB LAP SPLICE -
TYPICAL OIL
CANNING CENTER
RADIAL STIFFENER
/ TYPICAL OIL CANNING
OUTER EDGE
ORIGINAL
CONTOUR  AFT PRESSURE
1.00-  BULKHEAD WEB
TYPICAL OIL
CANNING  ZA  RADIAL  STIFFENER
WEB LAP
SPLICE
C-C
INSPECTION AREA  2508560
FIGURE 2: STA 1440 AFT PRESSURE BULKHEAD WEB - OIL CANNING ZONE DETERMINATION AND
DETAILED INSPECTION
(SHEET 3 OF 7)
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### Page 34 (OCR)

BOEING SERVICE BULLETIN А3543
ALERT  ALERT
ORIGINAL  1.00
CONTOUR
CIRCUMFERENTIAL
TEAR STRAP
AFT PRESSURE  TYPICAL OIL
BULKHEAD WEB  CANNING
D-D
INSPECTION AREA
TYPICAL OIL
CANNING OUTER EDGE
ORIGINAL  ORIGINAL
CONTOUR  CONTOUR
CIRCUMFERENTIAL
2.00 MIN  TEAR STRAP
TYPICAL OIL CANNING
E-E  AFT PRESSURE
BULKHEAD WEB
INSPECTION AREA
FIGURE 2: STA 1440 AFT PRESSURE BULKHEAD WEB - OIL CANNING ZONE DETERMINATION AND
DETAILED INSPECTION
(SHEET 4 OF 7)
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### Page 35

FIGURE 2: STA 1440 AFT PRESSURE BULKHEAD WEB - OIL CANNING ZONE DETERMINATION AND
DETAILED INSPECTION
(SHEET 5 OF 7)
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BOEING SERVICE BULLETIN A3543
ALERT  ALERT
0.35
ZONE 2
0.3
D (MAXIMUM DEPTH OF OIL CANNING INCH)  ZONE 1
0.05
10  12  14
W (MINIMUM WIDTH OF OIL CANNING AT PERIMETER INCH)
ZONE 1 AND ZONE 2 LIMITS
TABLE 1
2506768
FIGURE 2: STA 1440 AFT PRESSURE BULKHEAD WEB - OIL CANNING ZONE DETERMINATION AND
DETAILED INSPECTION
(SHEET 6 OF 7)
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### Page 37

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a) (b)1STA 1440Aft Pressure Bulkhead
Web
Measure1
(c)1STA 1440Aft Pressure Bulkhead
Web
Inspect2
(c)1STA 1440Aft Pressure Bulkhead
Web
Inspect3
(c)1STA 1440Aft Pressure Bulkhead
Web
Inspect4
(c)1STA 1440Aft Pressure Bulkhead
Web
Inspect5
(c)1STA 1440Aft Pressure Bulkhead
Web
Inspect6
(a) Measure the depth and width of each oil canning area to determine if the oil canning is within Zone 1 or
Zone 2 limits. Refer to view B-B and Zone 1 and Zone 2 limits Table 1.
(b) Apply the flexible metal strip to make depth and width measurements, by pressing the ends of the strip
flush to the outside surface of the web only in areas outside the oil canning outer edge. Measure the
maximum depth of the oil canning condition between the dome surface and the metal strip.
(c) Do a detailed inspection for any damage or any irregularity. Any damage can include, any sharp creases,
any gouges, any crack, any deformation to a radial stiffener, circumferential tear strap, Y-chord or terminal
fitting splice plate, or any damaged holes. Any irregularity can include, any loose or missing fasteners,
any pressure leakage, any fasteners within 1.0 inch of any oil canning location or any oil canning location
within 2.0 inch inches of any other oil canning location.
FIGURE 2: STA 1440 AFT PRESSURE BULKHEAD WEB - OIL CANNING ZONE DETERMINATION AND
DETAILED INSPECTION
(SHEET 7 OF 7)
Export Controlled ECCN: 9E991 - BOEING
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BOEING SERVICE BULLETIN A3543
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### Page 38 (OCR)

BOEING SERVICE BULLETIN А3543
ALERT  ALERT
CIRCUMFERENTIAL
TEAR STRAPS
WEB LAP SPLICE
RADIAL
STIFFENERS
AFT PRESSURE
INSPECTION AREA  VIEW LOOKING FORWARD  BULKHEAD WEB  2506484
A-A
FIGURE 3: STA 1440 AFT PRESSURE BULKHEAD WEB - DETAILED INSPECTION AND EDDY CURRENT
INSPECTION
(SHEET 1 OF 4)
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Work - See page 1 for details.  38 of 52

### Page 39 (OCR)

BOEING SERVICE BULLETIN А3543
ALERT  ALERT
RADIAL STIFFENER  OIL CANNING
CIRCUMFERENTIAL
TEAR STRAP
RADIAL STIFFENER
TYPICAL OIL
CANNING
TYPICAL WEB BAY AREA (5
WEB LAP SPLICE
INSPECTION AREA  • RADIAL STIFFENER
TYPICAL OIL CANNING
OUTER EDGE
ORIGINAL
CONTOUR  AFT PRESSURE
BULKHEAD WEB
RADIAL
STIFFENER
TYPICAL OIL
CANNING
WEB LAP
SPLICE
INSPECTION AREA  B-B  2506490
FIGURE 3: STA 1440 AFT PRESSURE BULKHEAD WEB - DETAILED INSPECTION AND EDDY CURRENT
INSPECTION
(SHEET 2 OF 4)
Original Issue: September 15, 2016
Export Controlled ECCN: 9E991 - BOEING  A3543
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  39 of 52

### Page 40

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)1STA 1440Aft Pressure Bulkhead
Web
Inspect1
(b)1STA 1440Aft Pressure Bulkhead
Web
Inspect2
(c)1STA 1440Aft Pressure Bulkhead
Web
Inspect3
(d)1STA 1440Aft Pressure Bulkhead
Web
Inspect4
(e)1STA 1440Aft Pressure Bulkhead
Web
Inspect5
(f)1STA 1440Aft Pressure Bulkhead
Web
Inspect6
(a) Do a detailed inspection for any crack on the STA 1440 aft pressure bulkhead web.
(b) Do a surface HFEC inspection for any crack of the web, from the aft side along each oil canning outer
edge in accordance with 707, 720 NDT Manual Part 6, 51-00-00, Figure 4 or Figure 23.
(c) Do a LFEC inspection for any crack of the forward web lap splice hidden fastener rows, from the aft side
of the aft pressure bulkhead web at all fastener locations common to the outer edge of the web bay area
in which the oil canning was found in accordance with 707, 720 NDT Manual Part 6, 53-10-07, Figure 18.
FIGURE 3: STA 1440 AFT PRESSURE BULKHEAD WEB - DETAILED INSPECTION AND EDDY CURRENT
INSPECTION
(SHEET 3 OF 4)
Export Controlled ECCN: 9E991 - BOEING
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Work - See page 1 for details.
Original Issue: September 15, 2016
A3543
40 of 52
BOEING SERVICE BULLETIN A3543
ALERTALERT

### Page 41

More DataQtyIdentificationNameTaskStep
(d) Do a LFEC inspection for any crack of the web hidden underneath the circumferential tear straps, from
the aft side of the aft pressure bulkhead web at all fastener locations common to the perimeter of the web
bay area in which the oil canning was found in accordance with 707, 720 NDT Manual Part 6, 53-10-07,
Figure 18.
(e) Do a surface HFEC inspection for any crack of the web common to the radial stiffener, from the aft side
of the aft pressure bulkhead web at all fastener locations common to the outer edge of the web bay area
in which the oil canning was found in accordance with 707, 720 NDT Manual Part 6, 51-00-00, Figure 4
or Figure 23. Make sure to inspect 360 degrees around fasteners.
(f) Do a surface HFEC inspection for any crack of the web common to a web lap splice, from the aft side of
the aft pressure bulkhead web at all fastener locations common to the outer edge of the web bay area in
which the oil canning was found in accordance with 707, 720 NDT Manual Part 6, 51-00-00, Figure 4 or
Figure 23. Make sure to inspect 360 degrees around fasteners.
FIGURE 3: STA 1440 AFT PRESSURE BULKHEAD WEB - DETAILED INSPECTION AND EDDY CURRENT
INSPECTION
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: September 15, 2016
A3543
41 of 52
BOEING SERVICE BULLETIN A3543
ALERTALERT

### Page 42 (OCR)

BOEING SERVICE BULLETIN А3543
ALERT  ALERT
Y CHORD
CIRCUMFERENTIAL
TEAR STRAPS
WEB LAP SPLICE
RADIAL
STIFFENERS
AFT PRESSURE
VIEW LOOKING FORWARD  BULKHEAD WEB
INSPECTION AREA
A-A
FIGURE 4: STA 1440 AFT PRESSURE BULKHEAD WEB - Y-CHORD - DETAILED INSPECTION AND EDDY
CURRENT INSPECTION
(SHEET 1 OF 5)
Original Issue: September 15, 2016
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  A3543
Work - See page 1 for details.  42 of 52

### Page 43 (OCR)

BOEING SERVICE BULLETIN А3543
ALERT  ALERT
RADIAL STIFFENER
C
TYPICAL OIL
CIRCUMFERENTIAL  CANNING
TEAR STRAP
Y CHORD
6) TYPICAL WEB
RADIAL STIFFENER'  BAY AREA
WEB LAP SPLICE
INSPECTION AREA
RADIAL STIFFENER
STA
1440
SKIN
Y CHORD
AFT PRESSURE
BULKHEAD WEB
FWD
.00
/ INSPECTION AREA  B-B  2518712
FIGURE 4: STA 1440 AFT PRESSURE BULKHEAD WEB - Y-CHORD - DETAILED INSPECTION AND EDDY
CURRENT INSPECTION
(SHEET 2 OF 5)
Original Issue: September 15, 2016
Export Controlled ECCN: 9E991 - BOEING  A3543
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  43 of 52

### Page 44 (OCR)

BOEING SERVICE BULLETIN А3543
ALERT  ALERT
) TYPICAL OIL CANNING
OUTER EDGE
ORIGINAL
CONTOUR  AFT PRESSURE
BULKHEAD WEB
RADIAL
STIFFENER
TYPICAL OIL
CANNING
WEB LAP
SPLICE
C-C
INSPECTION AREA
3) TYPICAL OIL CANNING
OUTER EDGE
ORIGINAL
CONTOUR  CIRCUMFERENTIAL
TEAR STRAP
AFT PRESSURE  TYPICAL OIL
BULKHEAD WEB  CANNING
D-D
INSPECTION AREA  2508283
FIGURE 4: STA 1440 AFT PRESSURE BULKHEAD WEB - Y-CHORD - DETAILED INSPECTION AND EDDY
CURRENT INSPECTION
(SHEET 3 OF 5)
Original Issue: September 15, 2016
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Work - See page 1 for details.  44 of 52

### Page 45

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a) (b) (c)1STA 1440Aft Pressure Bulkhead
Web
Inspect1
(d)1STA 1440Aft Pressure Bulkhead
Web
Inspect2
(e)1STA 1440Aft Pressure Bulkhead
Web
Inspect3
(f)1STA 1440Aft Pressure Bulkhead
Web
Inspect4
(g)1STA 1440Aft Pressure Bulkhead
Web
Inspect5
(h)1STA 1440Aft Pressure Bulkhead
Web
Inspect6
(i)1STA 1440Aft Pressure Bulkhead
Web
Inspect7
(a) Do a surface High Frequency Eddy Current (HFEC) inspection for any crack at the aft fastener row from
the forward side of the bulkhead in accordance with 707, 720 NDT Manual Part 6, 51-00-00, Figure 4 or
23. Make sure to inspect 360 degrees around the fastener. Do this inspection except where a radial stiff-
ener overlaps the Y-chord at the perimeter of the web at the fastener locations or where production doublers
overlap the web.
(b) Where a radial stiffener overlaps the Y-chord at the perimeter of the web at the fastener location, do a
surface HFEC inspection for any crack of the web, along the edge of the radial stiffener adjacent to the
fastener locations in accordance with 707, 720 NDT Manual Part 6, 51-00-00, Figure 4 or 23. Make sure
to inspect the web up to 1.0 inch on each side of the fastener row.
(c) Where production doublers overlap the web, do a surface HFEC inspection for any crack of the web,
along the outer edge fastener row of the doubler in accordance with 707, 720 NDT Manual Part 6, 51-00-
00, Figure 4 or Figure 23.
(d) Do a detailed inspection for any crack of the web, from the aft side along each oil canning outer edge.
(e) Do a surface HFEC inspection for any crack of the web, from the aft side along each oil canning outer
edge in accordance with 707, 720 NDT Manual Part 6, 51-00-00, Figure 4 or Figure 23.
(f) Do a LFEC inspection for any crack of the forward web lap splice hidden fastener rows, from the aft side
of the aft pressure bulkhead web at all fastener locations common to the outer edge of the web bay area
in which the oil canning was found in accordance with 707, 720 NDT Manual Part 6, 53-10-07, Figure 18.
(g) Do a HFEC inspection for any crack of the web underneath the circumferential tear straps, from the forward
side of the aft pressure bulkhead web at all fastener locations common to the perimeter of the web bay
area in which the oil canning was found in accordance with 707, 720 NDT Manual Part 6, 51-00-00, Figure
4 or Figure 23.
FIGURE 4: STA 1440 AFT PRESSURE BULKHEAD WEB - Y-CHORD - DETAILED INSPECTION AND EDDY
CURRENT INSPECTION
(SHEET 4 OF 5)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: September 15, 2016
A3543
45 of 52
BOEING SERVICE BULLETIN A3543
ALERTALERT

### Page 46

More DataQtyIdentificationNameTaskStep
(h) Do a surface HFEC inspection for any crack of the web common to the radial stiffener, from the aft side
of the aft pressure bulkhead web at all fastener locations common to the outer edge of the web bay area
in which the oil canning was found in accordance with 707, 720 NDT Manual Part 6, 51-00-00, Figure 4
or Figure 23. Make sure to inspect 360 degrees around fasteners.
(i) Do a surface HFEC inspection for any crack of the web common to a web lap splice, from the aft side of
the aft pressure bulkhead web at all fastener locations common to the outer edge of the web bay area in
which the oil canning was found in accordance with 707, 720 NDT Manual Part 6, 51-00-00, Figure 4 or
Figure 23. Make sure to inspect 360 degrees around fasteners.
FIGURE 4: STA 1440 AFT PRESSURE BULKHEAD WEB - Y-CHORD - DETAILED INSPECTION AND EDDY
CURRENT INSPECTION
(SHEET 5 OF 5)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: September 15, 2016
A3543
46 of 52
BOEING SERVICE BULLETIN A3543
ALERTALERT

### Page 47 (OCR)

BOEING SERVICE BULLETIN A3543
ALERT  ALERT
1 TYPICAL OIL CANNING
RADIAL STIFFENER
(TYPICAL)
CIRCUMFERENTIAL
TEAR STRAPS
AFT PRESSURE
BULKHEAD WEB
INSPECTION AREA  TYPICAL AFT PRESSURE BULKHEAD  (VIEW LOOKING AFT)  2508598
A-A
FIGURE 5: STA 1440 AFT PRESSURE BULKHEAD WEB - HIGH FREQUENCY EDDY CURRENT (HFEC)
INSPECTION
(SHEET 1 OF 2)
Original Issue: September 15, 2016
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PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  47 of 52

### Page 48

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a) (b)1STA 1440Aft Pressure Bulkhead
Web
Inspect1
(a) Do a surface High Frequency Eddy Current (HFEC) inspection from the forward side of the affected location
for the crack location, length and orientation in accordance with 707, 720 NDT Manual Part 6, 51-00-00,
Figure 4 or Figure 23.
(b) If access is not available to do a surface HFEC inspection, then remove the fasteners at the affected lo-
cation and do an Open Hole Eddy Current inspection of the web at the affected location to find the crack
location and orientation in accordance with 707, 720 NDT Manual Part 6, 51-00-00, Figure 16.
FIGURE 5: STA 1440 AFT PRESSURE BULKHEAD WEB - HIGH FREQUENCY EDDY CURRENT (HFEC)
INSPECTION
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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Original Issue: September 15, 2016
A3543
48 of 52
BOEING SERVICE BULLETIN A3543
ALERTALERT

### Page 49

Logic diagrams are provided as an aid only. Information contained in Paragraph 1.E., Compliance is the primary
source for compliance times. Information contained in Paragraph 3.B., Work Instructions is the primary source
for tasks required for compliance.
1. The table below gives the description for the parts and conditions called out in the logic diagrams.
DescriptionTitle
DETAILED INSPECTION OF THE STA 1440 AFT PRESSURE BULKHEAD
WEB.
PART 2
OIL CANNING ZONE DETERMINATION AND DETAILED INSPECTION.PART 3
DETAILED INSPECTION AND EDDY CURRENT INSPECTION.PART 4
HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION.PART 5
NO OIL CANNING FOUND.CONDITION 1
ANY OIL CANNING FOUND.CONDITION 2
ANY OIL CANNING FOUND WITHIN ZONE 1 LIMITS AND NO CRACK
FOUND.
CONDITION 2.1
ANY OIL CANNING FOUND WITH ANY DAMAGE OR ANY IRREGULARITY.CONDITION 2.2
ANY OIL CANNING FOUND WITHIN ZONE 2 LIMITS AND NO CRACK
FOUND.
CONDITION 2.3
ANY OIL CANNING FOUND WITH ANY CRACK FOUND.CONDITION 2.4
2. The table below gives the description for the flag notes called out in the logic diagram.
DescriptionFlag Note Letter
Any damage can include, any sharp creases, any gouges, any crack, any
deformation to a radial stiffener, circumferential tear strap, Y-chord or terminal
fitting splice plate, or any damaged holes.
(a)
Any irregularity can include, any loose or missing fasteners, any pressure
leakage, any fasteners within 1.0 inch of any oil canning location or any oil
canning location within 2.0 inch inches of any other oil canning location.
APPENDIX A: TABLE 1: STA 1440 AFT PRESSURE BULKHEAD WEB INSPECTION FOR OIL CANNING
(SHEET 1 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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ALERTALERT

### Page 50 (OCR)

BOEING SERVICE BULLETIN A3543
ALERT  ALERT
CONDITION 2
(ACTION 2):
DO PART 4
WHICHEVER OCCURS LATER
WITHIN 1,200 FLIGHT
BEFORE 15,000 TOTAL  CYCLES AFTER THE  ORIGINAL ISSUE DATE
FLIGHT CYCLES  OF THIS SERVICE
BULLETIN
DO PART 2
CONDITION 1  CONDITION 2
NOT TO EXCEED 6,000  BEFORE FURTHER
FLIGHT CYCLES  FLIGHT
REPEAT  CONDITION 2
PART 2  (ACTION 1):
DO PART 3 (a)
C
2521696
APPENDIX A: TABLE 1: STA 1440 AFT PRESSURE BULKHEAD WEB INSPECTION FOR OIL CANNING
(SHEET 2 OF 4)
Original Issue: September 15, 2016
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### Page 51 (OCR)

BOEING SERVICE BULLETIN А3543
ALERT  ALERT
CONDITION 2
(ACTION2):
DO PART 4
CONDITION 2.1  CONDITION 2.2
(a)
NOT TO EXCEED 1,200  BEFORE FURTHER  BEFORE FURTHER
FLIGHT CYCLES  FLIGHT  FLIGHT
OPTION 1 (ACTION 1):  OPTION 2 (ACTION 1):  CONDITION 2.2 (ACTION 1)
REPEAT PART 4  CONTACT THE  CONTACT THE
BOEING COMPANY  BOEING COMPANY
FOR REPAIR  FOR REPAIR
INSTRUCTIONS  INSTRUCTIONS
AND DO THE  AND DO THE
WITHIN 12,000  REPAIR  REPAIR
FLIGHT CYCLES
AFTER THE
OIL CANNING
CONDITION WAS  NOT TO EXCEED 6,000  NOT TO EXCEED 6,000
FOUND  FLIGHT CYCLES  FLIGHT CYCLES
OPTION 1 (ACTION 2):  BOEING COMPANY  CONTACT THE  OPTION 2 (ACTION 2):  REPEAT PART 2  CONDITION 2.2  (ACTION 2):
REPEAT PART 2
FOR REPAIR
INSTRUCTIONS AND
DO THE REPAIR
NOT TO EXCEED 6,000
FLIGHT CYCLES
OPTION 1 (ACTION 3):
REPEAT PART 2
2521697
APPENDIX A: TABLE 1: STA 1440 AFT PRESSURE BULKHEAD WEB INSPECTION FOR OIL CANNING
(SHEET 3 OF 4)
Original Issue: September 15, 2016
Export Controlled ECCN: 9E991 - BOEING  A3543
PROPRIETARY - Copyright © Unpublished
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### Page 52 (OCR)

BOEING SERVICE BULLETIN А3543
ALERT  ALERT
C
CONDITION 2.3  CONDITION 2.4
BEFORE FURTHER  BEFORE FURTHER
FLIGHT  FLIGHT
CONDITION 2.3 (ACTION 1):  CONDITION 2.4
CONTACT THE  (ACTION 1):
BOEING COMPANY  DO PART 5
FOR REPAIR
INSTRUCTIONS
AND DO THE
REPAIR
CONDITION 2.4
NOT TO EXCEED 6,000  (ACTION 2):
FLIGHT CYCLES  CONTACT THE
BOEING COMPANY
FOR REPAIR
INSTRUCTIONS AND
CONDITION 2.3  DO THE REPAIR
(ACTION 2):
REPEAT PART 2
NOT TO EXCEED 6,000
FLIGHT CYCLES
CONDITION 2.4
(ACTION 3):
REPEAT PART 2
2521695
APPENDIX A: TABLE 1: STA 1440 AFT PRESSURE BULKHEAD WEB INSPECTION FOR OIL CANNING
(SHEET 4 OF 4)
Original Issue: September 15, 2016a
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright @ Unpublished  A3543
Work - See page 1 for details.  52 of 52

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