Airworthiness Directives; The Boeing Company Airplanes, 27020-27025 [2013-09113]
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Federal Register / Vol. 78, No. 90 / Thursday, May 9, 2013 / Rules and Regulations
required by paragraphs (g), (h), and (i) and of
this AD.
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(r) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, Washington 98057–
3356; telephone (425) 227–1138; fax (425)
227–1149. Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office. The AMOC
approval letter must specifically reference
this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(s) Related Information
(1) Refer to MCAI European Aviation
Safety Agency Airworthiness Directive 2010–
0081, dated April 27, 2010, and the service
information specified in paragraphs (s)(1)(i)
through (s)(1)(xix) of this AD, for related
information.
(i) Airbus All Operators Telex (AOT)
A330–27A3129, Revision 01, dated July 16,
2004.
(ii) Airbus Mandatory Service Bulletin
A330–27–3136, Revision 01, dated July 19,
2006.
(iii) Airbus Mandatory Service Bulletin
A330–27–3146, Revision 01, dated
September 3, 2008.
(iv) Airbus Mandatory Service Bulletin
A330–27–3148, Revision 01, dated October 9,
2008.
(v) Airbus Mandatory Service Bulletin
A330–27–3176, Revision 02, dated April 24,
2012.
(vi) Airbus Mandatory Service Bulletin
A330–27–3177, dated December 21, 2011.
(vii) Airbus Mandatory Service Bulletin
A330–27A3131, Revision 01, dated March 3,
2005.
(viii) Airbus Mandatory Service Bulletin
A340–27–4144, dated October 19, 2009.
(ix) Airbus Mandatory Service Bulletin
A340–27–4146, dated June 1, 2007.
(x) Airbus Mandatory Service Bulletin
A340–27–4148, dated June 13, 2008.
(xi) Airbus Mandatory Service Bulletin
A340–27–4162, Revision 01, dated
September 17, 2012.
(xii) Airbus Mandatory Service Bulletin
A340–27–4174, dated November 21, 2011.
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15:51 May 08, 2013
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(xiii) Airbus Mandatory Service Bulletin
A340–27A4130, Revision 01, dated March 3,
2005.
(xiv) Airbus Service Bulletin A330–27–
3134, Revision 01, dated May 12, 2006.
(xv) Airbus Service Bulletin A330–27–
3144, Revision 01, dated July 16, 2009.
(xvi) Airbus Service Bulletin A330–27–
3145, dated December 16, 2008.
(xvii) Airbus Service Bulletin A340–27–
4145, dated December 16, 2008.
(xviii) Airbus Temporary Revision TR4,
Issue 1.0, ‘‘TR 4.02.00/25 Issue 2—
Undetected Elevator Control Loss in Case of
Dual Failure,’’ dated November 26, 2009, to
the Airbus A330/A340 Airplane Flight
Manual.
(xix) Airbus Temporary Revision TR22,
Issue 1.0, ‘‘TR 4.02.00/40 Issue 2—
Undetected Elevator Control Loss in Case of
Dual Failure,’’ dated November 26, 2009, to
the Airbus A330/A340 Airplane Flight
Manual.
(2) For service information identified in
this AD, contact Airbus SAS—Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 45 80; email
airworthiness.A330–A340@airbus.com;
Internet https://www.airbus.com. You may
review copies of the referenced service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221.
(t) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Airbus All Operators Telex (AOT)
A330–27A3129, Revision 01, dated July 16,
2004.
(ii) Airbus Mandatory Service Bulletin
A330–27–3136, Revision 01, dated July 19,
2006.
(iii) Airbus Mandatory Service Bulletin
A330–27–3146, Revision 01, dated
September 3, 2008.
(iv) Airbus Mandatory Service Bulletin
A330–27–3148, Revision 01, dated October 9,
2008.
(v) Airbus Mandatory Service Bulletin
A330–27–3176, Revision 02, dated April 24,
2012.
(vi) Airbus Mandatory Service Bulletin
A330–27–3177, dated December 21, 2011.
(vii) Airbus Mandatory Service Bulletin
A330–27A3131, Revision 01, dated March 3,
2005.
(viii) Airbus Mandatory Service Bulletin
A340–27–4144, dated October 19, 2009.
(ix) Airbus Mandatory Service Bulletin
A340–27–4146, dated June 1, 2007.
(x) Airbus Mandatory Service Bulletin
A340–27–4148, dated June 13, 2008.
(xi) Airbus Mandatory Service Bulletin
A340–27–4162, Revision 01, dated
September 17, 2012.
(xii) Airbus Mandatory Service Bulletin
A340–27–4174, dated November 21, 2011.
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(xiii) Airbus Mandatory Service Bulletin
A340–27A4130, Revision 01, dated March 3,
2005.
(xiv) Airbus Service Bulletin A330–27–
3134, Revision 01, dated May 12, 2006.
(xv) Airbus Service Bulletin A330–27–
3144, Revision 01, dated July 16, 2009.
(xvi) Airbus Service Bulletin A330–27–
3145, dated December 16, 2008.
(xvii) Airbus Service Bulletin A340–27–
4145, dated December 16, 2008.
(xviii) Airbus Temporary Revision TR4,
Issue 1.0, ‘‘TR 4.02.00/25 Issue 2—
Undetected Elevator Control Loss in Case of
Dual Failure,’’ dated November 26, 2009, to
the Airbus A330/A340 Airplane Flight
Manual.
(xix) Airbus Temporary Revision TR22,
Issue 1.0, ‘‘TR 4.02.00/40 Issue 2—
Undetected Elevator Control Loss in Case of
Dual Failure,’’ dated November 26, 2009, to
the Airbus A330/A340 Airplane Flight
Manual.
(3) For service information identified in
this AD, contact Airbus SAS—Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 45 80; email
airworthiness.A330–A340@airbus.com;
Internet https://www.airbus.com.
(4) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton,
WA. For information on the availability of
this material at the FAA, call 425–227–1221.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on February
28, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2013–10653 Filed 5–8–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–1316; Directorate
Identifier 2012–NM–186–AD; Amendment
39–17429; AD 2012–18–13 R1]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are revising an existing
airworthiness directive (AD) for all The
Boeing Company Model 737–100, –200,
–200C, –300, –400, and –500 series
SUMMARY:
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Federal Register / Vol. 78, No. 90 / Thursday, May 9, 2013 / Rules and Regulations
airplanes. That AD currently requires
repetitive inspections to detect cracking
in the web of the aft pressure bulkhead
at body station 1016 at the aft fastener
row attachment to the ‘‘Y’’ chord,
various inspections for discrepancies at
the aft pressure bulkhead, and related
investigative and corrective actions if
necessary. This new AD requires
clarifying certain actions specified in
the existing AD. This AD was prompted
by several reports of fatigue cracks in
the aft pressure bulkhead. We are
issuing this AD to detect and correct
such fatigue cracking, which could
result in rapid decompression of the
fuselage.
DATES: This AD is effective June 13,
2013.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of October 24, 2012 (77 FR 57990,
September 19, 2012).
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of May 10, 1999 (64 FR
19879, April 23, 1999).
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, Washington 98124–
2207; telephone 206–544–5000,
extension 1; fax 206–766–5680; Internet
https://www.myboeingfleet.com. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, Washington.
For information on the availability of
this material at the FAA, call 425–227–
1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton,
Washington 98057–3356; phone: (425)
917–6450; fax: (425) 917–6590; email:
alan.pohl@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to revise AD 2012–18–13,
Amendment 39–17190 (77 FR 57990,
September 19, 2012). That AD applies to
all The Boeing Company Model 737–
100, –200, –200C, –300, –400, and –500
series airplanes. (AD 2012–18–13
superseded AD 99–08–23, Amendment
39–11132 (64 FR 19879, April 23,
1999)). The NPRM published in the
Federal Register on January 9, 2013 (78
FR 1772). That NPRM proposed to
continue to require repetitive
inspections to detect cracking in the
web of the aft pressure bulkhead at body
station 1016 at the aft fastener row
attachment to the ‘‘Y’’ chord, various
inspections for discrepancies at the aft
pressure bulkhead, and related
investigative and corrective actions if
necessary. That NPRM also proposed to
clarify certain actions specified in the
existing AD.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the proposal (78 FR 1772,
January 9, 2013) and the FAA’s response
to each comment.
27021
Supportive Comment
The Boeing Company stated that it
supports the NPRM (78 FR 1772,
January 9, 2013).
Supplemental Type Certificate (STC)
Comment
Aviation Partners Boeing stated that
the installation of winglets per STC
ST01219SE (https://rgl.faa.gov/
Regulatory_and_Guidance_Library/
rgstc.nsf/0/2c6e3dbddd36f91c8625
76a4005d64e2/$FILE/ST01219SE.pdf)
does not affect the accomplishment of
the manufacturer’s service instructions.
We have added paragraph (c)(2) of
this AD to state that installation of STC
ST01219SE (https://rgl.faa.gov/
Regulatory_and_Guidance_Library/
rgstc.nsf/0/2c6e3dbddd36f91c862576a
4005d64e2/$FILE/ST01219SE.pdf) does
not affect the ability to accomplish the
actions required by this AD. Therefore,
for airplanes on which STC ST01219SE
is installed, a ‘‘change in product’’
AMOC approval request is not necessary
to comply with the requirements of 14
CFR 39.17.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting the AD
with the change described previously–
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM (78 FR 1772,
January 9, 2013) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (78 FR 1772,
January 9, 2013).
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of the AD.
Costs of Compliance
We estimate that this AD affects 566
airplanes of U.S. registry.
ESTIMATED COSTS
Parts
cost
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Action
Labor cost
Low frequency eddy current
(LFEC) inspection [retained action from AD 99–08–23, Amendment 39–11132 (64 FR 19879,
April 23, 1999)].
Detailed visual inspection [retained
action from AD 99-08–23,
Amendment 39–11132 (64 FR
19879, April 23, 1999)].
8 work-hours × $85 per hour = $680 ...............
$0
$680 ............................
$384,880.
2 work-hours × $85 per hour = $170 ...............
0
$170 ............................
$96,220.
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Cost per product
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Cost on U.S. operators
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Federal Register / Vol. 78, No. 90 / Thursday, May 9, 2013 / Rules and Regulations
ESTIMATED COSTS—Continued
Parts
cost
Action
Labor cost
Detailed, high frequency eddy current (HFEC), and LFEC inspections of the web at the ‘‘Y’’ chord
of the bulkhead, the web located
under the outer circumferential
tear strap, the ‘‘Z’’ stiffeners at
the dome cap, and existing repairs [retained actions from AD
2012–18–13, Amendment 39–
17190 (77 FR 57990, September
19, 2012)].
Up to 60 work-hours × $85 per hour = $5,100
per inspection cycle.
We estimate the following costs to do
any necessary on-condition inspections
that would be required based on the
0
results of the initial inspection. We have
no way of determining the number of
Cost per product
Up to $5,100 per inspection cycle.
Cost on U.S. operators
Up to $2,886,600 per
inspection cycle.
aircraft that might need these
inspections:
ON-CONDITION COSTS
Action
Labor cost
Detailed and HFEC inspections for oil-canning ................
LFEC or HFEC inspection for cracking ............................
1 work-hour × $85 per hour = $85 ..................................
2 work-hours × $85 per hour = $170 ...............................
We have received no definitive data
that would enable us to provide cost
estimates for the crack repairs specified
in this AD.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
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Regulatory Findings
15:51 May 08, 2013
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
VerDate Mar<15>2010
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation
in Alaska, and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
Jkt 229001
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
2012–18–13, Amendment 39–17190 (77
■
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Parts cost
Cost per
product
$0
0
$85
170
FR 57990, September 19, 2012), and
adding the following new AD:
2012–18–13 R1 The Boeing Company:
Amendment 39–17429; Docket No.
FAA–2012–1316; Directorate Identifier
2012–NM–186–AD.
(a) Effective Date
This AD is effective June 13, 2013.
(b) Affected ADs
This AD revises AD 2012–18–13,
Amendment 39–17190 (77 FR 57990,
September 19, 2012).
(c) Applicability
(1) This AD applies to all The Boeing
Company Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes,
certificated in any category.
(2) Installation of Supplemental Type
Certificate (STC) ST01219SE (https://
rgl.faa.gov/
Regulatory_and_Guidance_Library/rgstc.nsf/
0/2c6e3dbddd36f91c862576a4005d64e2/
$FILE/ST01219SE.pdf) does not affect the
ability to accomplish the actions required by
this AD. Therefore, for airplanes on which
STC ST01219SE is installed, a ‘‘change in
product’’ alternative method of compliance
(AMOC) approval request is not necessary to
comply with the requirements of 14 CFR
39.17.
(d) Subject
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by several reports
of fatigue cracks in the aft pressure bulkhead.
We are issuing this AD to detect and correct
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such fatigue cracking, which could result in
rapid decompression of the fuselage.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Initial Inspection
This paragraph restates the initial
inspection required by paragraph (g) of AD
2012–18–13, Amendment 39–17190 (77 FR
57990, September 19, 2012). Perform either
inspection specified by paragraph (g)(1) or
(g)(2) of this AD at the time specified in
paragraph (h) of this AD.
(1) Perform a low frequency eddy current
(LFEC) inspection from the aft side of the aft
pressure bulkhead to detect discrepancies
(including cracking, misdrilled fastener
holes, and corrosion) of the web of the upper
section of the aft pressure bulkhead at body
station 1016 at the aft fastener row
attachment to the ‘‘Y’’ chord, from stringer 15
left (S–15L) to stringer 15 right (S–15R), in
accordance with Boeing 737 Nondestructive
Test Manual D6–37239, Part 6, Section 53–
10–54, dated December 5, 1998.
(2) Perform a detailed visual inspection of
the aft fastener row attachment to the ‘‘Y’’
chord from the forward side of the aft
pressure bulkhead to detect discrepancies
(including cracking, misdrilled fastener
holes, and corrosion) of the entire web of the
aft pressure bulkhead at body station 1016.
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(h) Retained Compliance Times
This paragraph restates the compliance
times specified in paragraph (h) of AD 2012–
18–13, Amendment 39–17190 (77 FR 57990,
September 19, 2012). Perform the inspection
required by paragraph (g) of this AD at the
time specified in paragraph (h)(1), (h)(2), or
(h)(3) of this AD, as applicable.
(1) For airplanes that have accumulated
40,000 or more total flight cycles as of May
10, 1999 (the effective date of AD 99–08–23,
Amendment 39–11132 (64 FR 19879, April
23, 1999)): Inspect within 375 flight cycles or
60 days after May 10, 1999 (the effective date
of AD 99–08–23), whichever occurs later.
(2) For airplanes that have accumulated
25,000 or more total flight cycles and fewer
than 40,000 total flight cycles as of May 10,
1999 (the effective date of AD 99–08–23,
Amendment 39–11132 (64 FR 19879, April
23, 1999)): Inspect within 750 flight cycles or
90 days after May 10, 1999 (the effective date
of AD 99–08–23), whichever occurs later.
(3) For airplanes that have accumulated
fewer than 25,000 total flight cycles as of
May 10, 1999 (the effective date of AD 99–
08–23, Amendment 39–11132 (64 FR 19879,
April 23, 1999)): Inspect prior to the
accumulation of 25,750 total flight cycles.
(i) Retained Repetitive Inspections
This paragraph restates the repetitive
inspections required by paragraph (i) of AD
2012–18–13, Amendment 39–17190 (77 FR
57990, September 19, 2012). Within 1,200
flight cycles after performing the initial
inspection required by paragraph (g) of this
AD, and thereafter at intervals not to exceed
1,200 flight cycles: Perform either inspection
specified by paragraph (g)(1) or (g)(2) of this
AD.
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(j) Retained Corrective Actions
This paragraph restates the corrective
actions required by paragraph (j) of AD 2012–
18–13, Amendment 39–17190 (77 FR 57990,
September 19, 2012). If any discrepancy is
detected during any inspection required by
paragraph (g), (h), or (i) of this AD: Prior to
further flight, accomplish the actions
specified by paragraphs (j)(1) and (j)(3) of this
AD, and paragraph (j)(2) of this AD, if
applicable.
(1) Perform a high frequency eddy current
inspection from the forward side of the
bulkhead to detect cracking of the web at the
‘‘Y’’ chord attachment, around the entire
periphery of the ‘‘Y’’ chord, in accordance
with Boeing 737 Nondestructive Test Manual
D6–37239, Part 6, Section 51–00–00, Figure
23, dated November 5, 1995.
(2) If the most recent inspection performed
in accordance with paragraph (g) of this AD
was not a detailed visual inspection:
Accomplish the actions specified by
paragraph (g)(2) of this AD. If the inspection
was a detailed visual inspection, it is not
necessary to repeat that inspection prior to
further flight.
(3) Repair any discrepancy such as
cracking or corrosion or misdrilled fastener
holes using a method approved in
accordance with the procedures specified in
paragraph (u) of this AD.
(k) Retained Inspections of the Web at the
‘‘Y’’ Chord Upper Bulkhead From
S–15L to S–15R
This paragraph restates the inspections of
the web at the ‘‘Y’’ chord upper bulkhead
from S–15L to S–15R required by paragraph
(k) of AD 2012–18–13, Amendment 39–17190
(77 FR 57990, September 19, 2012). At the
later of the times specified in paragraphs
(k)(1) and (k)(2) of this AD: Do detailed and
LFEC inspections of the aft side of the
bulkhead web, or do detailed and high
frequency eddy current (HFEC) inspections
from the forward side of the bulkhead, and
do all applicable related investigative and
corrective actions; in accordance with Part 1
of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737–53A1214,
Revision 4, dated December 16, 2011, except
as required by paragraphs (r)(1) and (r)(3) of
this AD. Inspect for cracks, incorrectly
drilled fastener holes, and elongated fastener
holes. Do all applicable related investigative
and corrective actions before further flight.
Repeat the inspections at the applicable
times specified in table 1 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011.
(1) Prior to the accumulation of 25,000
total flight cycles.
(2) Except as required by paragraphs (r)(2)
and (r)(4) of this AD, at the later of the times
specified in the ‘‘Compliance Time’’ column
in table 1 of paragraph 1.E., ‘‘Compliance,’’
of Boeing Alert Service Bulletin 737–
53A1214, Revision 4, dated December 16,
2011.
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(l) Retained Inspections of the Web at the
‘‘Y’’ Chord in the Lower Bulkhead From S–
15L to S–15R With Revised Inspection and
Repair Conditions
This paragraph restates the inspections of
the web at the ‘‘Y’’ chord in the lower
bulkhead from S–15L to S–15R required by
paragraph (l) of AD 2012–18–13, Amendment
39–17190 (77 FR 57990, September 19, 2012),
with revised inspection and repair
conditions. Except as required by paragraphs
(r)(2) and (r)(5) of this AD, at the applicable
time specified in table 2 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011: Do detailed and eddy
current inspections of the web from the
forward or aft side of the bulkhead for cracks,
incorrectly drilled fastener holes, and
elongated fastener holes, in accordance with
Part III of the Accomplishment Instructions
of Boeing Alert Service Bulletin 737–
53A1214, Revision 4, dated December 16,
2011, except as required by paragraphs (r)(1)
and (r)(3) of this AD. If any crack, incorrectly
drilled fastener hole, elongated fastener hole,
or corrosion is found, before further flight,
repair using a method approved in
accordance with the procedures specified in
paragraph (u) of this AD. Repeat the
inspections at the applicable times specified
in table 2 of paragraph 1.E., ‘‘Compliance,’’
of Boeing Alert Service Bulletin 737–
53A1214, Revision 4, dated December 16,
2011.
(m) Retained One-Time Inspection Under the
Tear Strap
This paragraph restates the one-time
inspection under the tear strap required by
paragraph (m) of AD 2012–18–13,
Amendment 39–17190 (77 FR 57990,
September 19, 2012). Except as required by
paragraphs (r)(2) and (r)(5) of this AD, at the
applicable time specified in table 3 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1214,
Revision 4, dated December 16, 2011: Do a
one-time LFEC inspection for cracks on the
aft side of the bulkhead of the web located
under the outer circumferential tear strap, or
do a one-time HFEC inspection for cracks
from the forward side of the bulkhead of the
web located under the outer circumferential
tear strap, in accordance with Part II of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1214, Revision 4,
dated December 16, 2011, except as required
by paragraph (r)(1) of this AD. If any cracking
is found, before further flight, repair the
bulkhead using a method approved in
accordance with the procedures specified in
paragraph (u) of this AD.
(n) Retained Inspection for Oil-Canning
This paragraph restates the inspection for
oil-canning required by paragraph (n) of AD
2012–18–13, Amendment 39–17190 (77 FR
57990, September 19, 2012). Except as
required by paragraph (r)(2) of this AD, at the
applicable time specified in table 4 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1214,
Revision 4, dated December 16, 2011: Do a
detailed inspection from the aft side of the
bulkhead for oil-canning and do all
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applicable related investigative and
corrective actions, in accordance with Part II
of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737–53A1214,
Revision 4, dated December 16, 2011, except
as required by paragraph (r)(1) of this AD. Do
all related investigative and corrective
actions before further flight. Thereafter,
repeat the inspection at the applicable times
specified in table 4 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011. For oil-cans found
within the limits specified in Part II of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1214, Revision 4,
dated December 16, 2011: In lieu of installing
the repair before further flight, at the
applicable times specified in table 4 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1214,
Revision 4, dated December 16, 2011, do
initial and repetitive detailed and HFEC
inspections for cracks of the oil-canning and
install the repair, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1214, Revision 4,
dated December 16, 2011. If any crack is
found, before further flight, repair the
cracking using a method approved in
accordance with the procedures specified in
paragraph (u) of this AD. Installing the repair
terminates the repetitive inspections for
cracks.
tkelley on DSK3SPTVN1PROD with RULES
(o) Retained Inspection of the Dome Cap at
the Center of the Bulkhead
This paragraph restates the inspection of
the dome cap at the center of the bulkhead
required by paragraph (o) of AD 2012–18–13,
Amendment 39–17190 (77 FR 57990,
September 19, 2012). Except as required by
paragraphs (r)(2) and (r)(5) of this AD, at the
applicable time specified in table 5 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1214,
Revision 4, dated December 16, 2011: Do an
eddy current inspection to detect any
cracking of the dome cap at the center of the
bulkhead, and do all applicable corrective
actions, in accordance with Part IV of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1214, Revision 4,
dated December 16, 2011. Do all corrective
actions before further flight. Repeat the
inspection at the times specified in table 5 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1214,
Revision 4, dated December 16, 2011.
(p) Retained Inspection of the Forward
Flange of the ‘‘Z’’ Stiffeners at the Dome Cap
This paragraph restates the inspection of
the forward flange of the ‘‘Z’’ stiffeners at the
dome cap required by paragraph (p) of AD
2012–18–13, Amendment 39–17190 (77 FR
57990, September 19, 2012). Except as
required by paragraphs (r)(2) and (r)(5) of this
AD, at the applicable time specified in table
6 of paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1214,
Revision 4, dated December 16, 2011: Do an
HFEC inspection to detect any cracking of the
‘‘Z’’ stiffener flanges at the dome cap in the
center of the bulkhead, in accordance with
Part V of the Accomplishment Instructions of
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Boeing Alert Service Bulletin 737–53A1214,
Revision 4, dated December 16, 2011, except
as required by paragraph (r)(1) of this AD. If
any crack is found, before further flight,
repair the flanges using a method approved
in accordance with the procedures specified
in paragraph (u) of this AD. Repeat the
inspection at the applicable times specified
in table 6 of paragraph 1.E., ‘‘Compliance,’’
of Boeing Alert Service Bulletin 737–
53A1214, Revision 4, dated December 16,
2011.
(q) Retained Inspection for Existing Repairs
on the Bulkhead
This paragraph restates the inspection for
existing repairs on the bulkhead required by
paragraph (q) of AD 2012–18–13,
Amendment 39–17190 (77 FR 57990,
September 19, 2012). Except as required by
paragraph (r)(2) of this AD, at the applicable
time specified in table 7 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011: Do a detailed inspection
of the bulkhead web and stiffeners for
existing repairs, in accordance with Part VI
of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737–53A1214,
Revision 4, dated December 16, 2011, except
as required by paragraph (r)(1) of this AD.
(1) If any repair identified in the
‘‘Condition’’ column of table 8 of paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011, is found and the
‘‘Reference’’ column refers to Appendix A, B,
C, or D of that service bulletin: At the
applicable times specified in table 8 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1214,
Revision 4, dated December 16, 2011, except
as required by paragraph (r)(2) of this AD, do
an HFEC inspection or an LFEC inspection of
the web for cracking, in accordance with
Appendix A, B, C, or D, as applicable, of
Boeing Alert Service Bulletin 737–53A1214,
Revision 4, dated December 16, 2011. If any
cracking is found, before further flight, repair
using a method approved in accordance with
the procedures specified in paragraph (u) of
this AD. Repeat the inspections thereafter at
the applicable intervals specified in table 8
of paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1214,
Revision 4, dated December 16, 2011.
(2) If any repair identified in the
‘‘Condition’’ column of table 8 of paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011, is found and the
‘‘Reference’’ column refers to Appendix E of
that service bulletin: At the applicable times
specified in table 8 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011, except as required by
paragraph (r)(2) of this AD, remove the repair
and replace with a new repair, in accordance
with Appendix E of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011.
(3) If any non-SRM (structural repair
manual) repair is found and the repair does
not have FAA-approved damage tolerance
inspections: Except as required by paragraph
PO 00000
Frm 00024
Fmt 4700
Sfmt 4700
(r)(2) of this AD, at the applicable time
specified in table 7 of Paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011, contact the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
Aircraft Certification Office (ACO), for
damage tolerance inspections. Do those
damage tolerance inspections at the times
given using a method approved in
accordance with the procedures specified in
paragraph (u) of this AD.
(r) Retained Exceptions to the Service
Information
This paragraph restates the exceptions to
the service information required by
paragraph (r) of AD 2012–18–13, Amendment
39–17190 (77 FR 57990, September 19, 2012).
(1) Where Boeing Alert Service Bulletin
737–53A1214, Revision 4, dated December
16, 2011, specifies to contact Boeing for
repair instructions: Before further flight,
repair using a method approved in
accordance with the procedures specified in
paragraph (u) of this AD.
(2) Where Boeing Alert Service Bulletin
737–53A1214, Revision 4, dated December
16, 2011, specifies a compliance time ‘‘after
the date of Revision 1 to this service
bulletin,’’ ‘‘from the date of Revision 3 of this
service bulletin,’’ ‘‘after the date of Revision
3 to this service bulletin,’’ or ‘‘of the effective
date of AD 99–08–23,’’ this AD requires
compliance within the specified compliance
time after October 24, 2012 (the effective date
of AD 2012–18–13, Amendment 39–17190
(77 FR 57990, September 19, 2012)).
(3) Access and restoration procedures
specified in the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1214, Revision 4, dated December
16, 2011, are not required by this AD.
Operators may do those procedures following
their maintenance practices.
(4) Where table 1 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011, specifies a compliance
time relative to actions done ‘‘in accordance
with paragraph (a)(2) of AD 99–08–23,’’ this
AD requires compliance within the specified
compliance time relative to actions specified
in paragraph (g)(2) of this AD.
(5) Where the Condition columns in tables
2, 3, 5, and 6 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011, refer to total flight cycles,
this AD applies to the airplanes with the
specified total flight cycles as of October 24,
2012 (the effective date of AD 2012–18–13,
Amendment 39–17190 (77 FR 57990,
September 19, 2012)).
(s) Retained Terminating Action With
Revised Paragraph Reference
This paragraph restates the terminating
action specified in paragraph (s) of AD 2012–
18–13, Amendment 39–17190 (77 FR 57990,
September 19, 2012), with a revised
paragraph reference. Accomplishment of the
requirements in paragraph (k) of this AD
terminates the requirements of paragraphs (g)
through (j) of this AD.
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(t) Credit for Previous Actions
This paragraph restates the credit for
previous actions specified by paragraph (t) of
AD 2012–18–13, Amendment 39–17190 (77
FR 57990, September 19, 2012). This
paragraph provides credit for the actions
required by paragraphs (k) through (s) of this
AD, if the actions were performed before the
effective date of this AD using the service
bulletins specified in paragraphs (t)(1)
through (t)(4) of this AD.
(1) Boeing Alert Service Bulletin 737–
53A1214, dated June 17, 1999.
(2) Boeing Alert Service Bulletin 737–
53A1214, Revision 1, dated June 22, 2000.
(3) Boeing Alert Service Bulletin 737–
53A1214, Revision 2, dated May 24, 2001.
(4) Boeing Alert Service Bulletin 737–
53A1214, Revision 3, dated January 19, 2011.
tkelley on DSK3SPTVN1PROD with RULES
(u) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle ACO, FAA, has
the authority to approve AMOCs for this AD,
if requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in the
Related Information section of this AD.
Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests-faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD if it is approved by the
Boeing Commercial Airplanes ODA that has
been authorized by the Manager, Seattle
ACO, to make those findings. For a repair
method to be approved, the repair must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) AMOCs approved previously in
accordance with AD 99–08–23, Amendment
39–11132 (64 FR 19879, April 23, 1999), are
approved as AMOCs for the corresponding
provisions of this AD.
(5) AMOCs approved previously in
accordance with AD 2012–18–13,
Amendment 39–17190 (77 FR 57990,
September 19, 2012), are approved as
AMOCs for the corresponding provisions of
this AD.
(v) Related Information
(1) For more information about this AD,
contact Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue SW., Renton, Washington 98057–
3356; phone: (425) 917–6440; fax: (425) 917–
6590; email: alan.pohl@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P. O. Box 3707, MC 2H–65,
Seattle, Washington 98124–2207; telephone
206–544–5000, extension 1; fax 206–766–
5680; Internet https://
www.myboeingfleet.com. You may review
VerDate Mar<15>2010
15:51 May 08, 2013
Jkt 229001
27025
copies of the referenced service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, Washington.
For information on the availability of this
material at the FAA, call 425–227–1221.
DEPARTMENT OF TRANSPORTATION
(w) Material Incorporated by Reference
[Docket No. FAA–2012–0662; Airspace
Docket No. 08–AWA–2]
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(3) The following service information was
approved for IBR on October 24, 2012 (77 FR
57990, September 19, 2012).
(i) Boeing Alert Service Bulletin 737–
53A1214, Revision 4, dated December 16,
2011.
(ii) Reserved.
(4) The following service information was
approved for IBR on May 10, 1999 (64 FR
19879, April 23, 1999).
(i) Boeing 737 Nondestructive Test Manual
D6–37239, Part 6, Section 53–10–54, dated
December 5, 1998.
(ii) Boeing 737 Nondestructive Test
Manual D6–37239, Part 6, Section 51–00–00,
Figure 23, dated November 5, 1995.
(5) For Boeing service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data &
Services Management, P. O. Box 3707, MC
2H–65, Seattle, Washington 98124–2207;
telephone 206–544–5000, extension 1; fax
206–766–5680; Internet https://
www.myboeingfleet.com.
(6) You may review copies of the
referenced service information at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, Washington. For
information on the availability of this
material at the FAA, call 425–227–1221.
(7) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on April 5,
2013.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2013–09113 Filed 5–8–13; 8:45 am]
BILLING CODE 4910–13–P
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Federal Aviation Administration
14 CFR Part 71
RIN 2120–AA66
Modification of Class B Airspace;
Philadelphia, PA
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
This action modifies the
Philadelphia, PA, Class B airspace area
to ensure the containment of large
turbine-powered aircraft within Class B
airspace, reduce controller workload,
and reduce the potential for midair
collision in the Philadelphia terminal
area.
SUMMARY:
Effective Date: 0901 UTC, July
25, 2013. The Director of the Federal
Register approves this incorporation by
reference action under 1 CFR part 51,
subject to the annual revision of FAA
Order 7400.9 and publication of
conforming amendments.
FOR FURTHER INFORMATION CONTACT: Paul
Gallant, Airspace Policy and ATC
Procedures Group, Office of Airspace
Services, Federal Aviation
Administration, 800 Independence
Avenue SW., Washington, DC 20591;
telephone: (202) 267–8783.
SUPPLEMENTARY INFORMATION:
DATES:
History
The FAA published in the Federal
Register a notice of proposed
rulemaking (NPRM) to modify the
Philadelphia, PA, Class B airspace area
(77 FR 45290, July 31, 2012). Interested
parties were invited to participate in
this rulemaking effort by submitting
written comments on the proposal.
Three comments were received in
response to the NPRM. The FAA
considered all comments received
before making a determination on this
final rule.
Discussion of Comments
All three commenters expressed
concern over the effect of expanding the
PHL Class B to the east and southeast.
One commenter was concerned by the
possible effect on a busy VFR flyway,
and by the funnel effect of having only
1000 feet vertically between the
modified Class B and Alert Area A–220.
Another commenter was concerned that
more complicated airspace, combined
with a bad economy and the high cost
of flight training, would discourage
E:\FR\FM\09MYR1.SGM
09MYR1
]]>Agencies
[Federal Register Volume 78, Number 90 (Thursday, May 9, 2013)]
[Rules and Regulations]
[Pages 27020-27025]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-09113]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-1316; Directorate Identifier 2012-NM-186-AD;
Amendment 39-17429; AD 2012-18-13 R1]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are revising an existing airworthiness directive (AD) for
all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500
series
[[Page 27021]]
airplanes. That AD currently requires repetitive inspections to detect
cracking in the web of the aft pressure bulkhead at body station 1016
at the aft fastener row attachment to the ``Y'' chord, various
inspections for discrepancies at the aft pressure bulkhead, and related
investigative and corrective actions if necessary. This new AD requires
clarifying certain actions specified in the existing AD. This AD was
prompted by several reports of fatigue cracks in the aft pressure
bulkhead. We are issuing this AD to detect and correct such fatigue
cracking, which could result in rapid decompression of the fuselage.
DATES: This AD is effective June 13, 2013.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of October 24,
2012 (77 FR 57990, September 19, 2012).
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of May 10,
1999 (64 FR 19879, April 23, 1999).
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may review copies of the referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, Washington. For information on the availability of
this material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (phone: 800-647-5527) is Document Management Facility,
U.S. Department of Transportation, Docket Operations, M-30, West
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: (425) 917-
6450; fax: (425) 917-6590; email: alan.pohl@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to revise AD 2012-18-13, Amendment 39-17190 (77 FR 57990,
September 19, 2012). That AD applies to all The Boeing Company Model
737-100, -200, -200C, -300, -400, and -500 series airplanes. (AD 2012-
18-13 superseded AD 99-08-23, Amendment 39-11132 (64 FR 19879, April
23, 1999)). The NPRM published in the Federal Register on January 9,
2013 (78 FR 1772). That NPRM proposed to continue to require repetitive
inspections to detect cracking in the web of the aft pressure bulkhead
at body station 1016 at the aft fastener row attachment to the ``Y''
chord, various inspections for discrepancies at the aft pressure
bulkhead, and related investigative and corrective actions if
necessary. That NPRM also proposed to clarify certain actions specified
in the existing AD.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
(78 FR 1772, January 9, 2013) and the FAA's response to each comment.
Supportive Comment
The Boeing Company stated that it supports the NPRM (78 FR 1772,
January 9, 2013).
Supplemental Type Certificate (STC) Comment
Aviation Partners Boeing stated that the installation of winglets
per STC ST01219SE (https://rgl.faa.gov/Regulatory--and--Guidance--
Library/rgstc.nsf/0/2c6e3dbddd36f91c862576a4005d64e2/$FILE/
ST01219SE.pdf) does not affect the accomplishment of the manufacturer's
service instructions.
We have added paragraph (c)(2) of this AD to state that
installation of STC ST01219SE (https://rgl.faa.gov/Regulatory--and--
Guidance--Library/rgstc.nsf/0/2c6e3dbddd36f91c862576a4005d64e2/$FILE/
ST01219SE.pdf) does not affect the ability to accomplish the actions
required by this AD. Therefore, for airplanes on which STC ST01219SE is
installed, a ``change in product'' AMOC approval request is not
necessary to comply with the requirements of 14 CFR 39.17.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
the AD with the change described previously-and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (78 FR 1772, January 9, 2013) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (78 FR 1772, January 9, 2013).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of the AD.
Costs of Compliance
We estimate that this AD affects 566 airplanes of U.S. registry.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Parts Cost on U.S.
Action Labor cost cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Low frequency eddy current (LFEC) 8 work-hours x $85 per $0 $680................ $384,880.
inspection [retained action from hour = $680.
AD 99-08-23, Amendment 39-11132
(64 FR 19879, April 23, 1999)].
Detailed visual inspection 2 work-hours x $85 per 0 $170................ $96,220.
[retained action from AD hour = $170.
99[dash]08-23, Amendment 39-
11132 (64 FR 19879, April 23,
1999)].
[[Page 27022]]
Detailed, high frequency eddy Up to 60 work-hours x $85 0 Up to $5,100 per Up to $2,886,600
current (HFEC), and LFEC per hour = $5,100 per inspection cycle. per inspection
inspections of the web at the inspection cycle. cycle.
``Y'' chord of the bulkhead, the
web located under the outer
circumferential tear strap, the
``Z'' stiffeners at the dome
cap, and existing repairs
[retained actions from AD 2012-
18-13, Amendment 39-17190 (77 FR
57990, September 19, 2012)].
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary on-condition
inspections that would be required based on the results of the initial
inspection. We have no way of determining the number of aircraft that
might need these inspections:
On-condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Detailed and HFEC inspections for oil-canning. 1 work-hour x $85 per hour = $85...... $0 $85
LFEC or HFEC inspection for cracking.......... 2 work-hours x $85 per hour = $170.... 0 170
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the crack repairs specified in this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing airworthiness directive (AD)
2012-18-13, Amendment 39-17190 (77 FR 57990, September 19, 2012), and
adding the following new AD:
2012-18-13 R1 The Boeing Company: Amendment 39-17429; Docket No.
FAA-2012-1316; Directorate Identifier 2012-NM-186-AD.
(a) Effective Date
This AD is effective June 13, 2013.
(b) Affected ADs
This AD revises AD 2012-18-13, Amendment 39-17190 (77 FR 57990,
September 19, 2012).
(c) Applicability
(1) This AD applies to all The Boeing Company Model 737-100, -
200, -200C, -300, -400, and -500 series airplanes, certificated in
any category.
(2) Installation of Supplemental Type Certificate (STC)
ST01219SE (https://rgl.faa.gov/Regulatory--and--Guidance--Library/
rgstc.nsf/0/2c6e3dbddd36f91c862576a4005d64e2/$FILE/ST01219SE.pdf)
does not affect the ability to accomplish the actions required by
this AD. Therefore, for airplanes on which STC ST01219SE is
installed, a ``change in product'' alternative method of compliance
(AMOC) approval request is not necessary to comply with the
requirements of 14 CFR 39.17.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by several reports of fatigue cracks in the
aft pressure bulkhead. We are issuing this AD to detect and correct
[[Page 27023]]
such fatigue cracking, which could result in rapid decompression of
the fuselage.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Initial Inspection
This paragraph restates the initial inspection required by
paragraph (g) of AD 2012-18-13, Amendment 39-17190 (77 FR 57990,
September 19, 2012). Perform either inspection specified by
paragraph (g)(1) or (g)(2) of this AD at the time specified in
paragraph (h) of this AD.
(1) Perform a low frequency eddy current (LFEC) inspection from
the aft side of the aft pressure bulkhead to detect discrepancies
(including cracking, misdrilled fastener holes, and corrosion) of
the web of the upper section of the aft pressure bulkhead at body
station 1016 at the aft fastener row attachment to the ``Y'' chord,
from stringer 15 left (S-15L) to stringer 15 right (S-15R), in
accordance with Boeing 737 Nondestructive Test Manual D6-37239, Part
6, Section 53-10-54, dated December 5, 1998.
(2) Perform a detailed visual inspection of the aft fastener row
attachment to the ``Y'' chord from the forward side of the aft
pressure bulkhead to detect discrepancies (including cracking,
misdrilled fastener holes, and corrosion) of the entire web of the
aft pressure bulkhead at body station 1016.
(h) Retained Compliance Times
This paragraph restates the compliance times specified in
paragraph (h) of AD 2012-18-13, Amendment 39-17190 (77 FR 57990,
September 19, 2012). Perform the inspection required by paragraph
(g) of this AD at the time specified in paragraph (h)(1), (h)(2), or
(h)(3) of this AD, as applicable.
(1) For airplanes that have accumulated 40,000 or more total
flight cycles as of May 10, 1999 (the effective date of AD 99-08-23,
Amendment 39-11132 (64 FR 19879, April 23, 1999)): Inspect within
375 flight cycles or 60 days after May 10, 1999 (the effective date
of AD 99-08-23), whichever occurs later.
(2) For airplanes that have accumulated 25,000 or more total
flight cycles and fewer than 40,000 total flight cycles as of May
10, 1999 (the effective date of AD 99-08-23, Amendment 39-11132 (64
FR 19879, April 23, 1999)): Inspect within 750 flight cycles or 90
days after May 10, 1999 (the effective date of AD 99-08-23),
whichever occurs later.
(3) For airplanes that have accumulated fewer than 25,000 total
flight cycles as of May 10, 1999 (the effective date of AD 99-08-23,
Amendment 39-11132 (64 FR 19879, April 23, 1999)): Inspect prior to
the accumulation of 25,750 total flight cycles.
(i) Retained Repetitive Inspections
This paragraph restates the repetitive inspections required by
paragraph (i) of AD 2012-18-13, Amendment 39-17190 (77 FR 57990,
September 19, 2012). Within 1,200 flight cycles after performing the
initial inspection required by paragraph (g) of this AD, and
thereafter at intervals not to exceed 1,200 flight cycles: Perform
either inspection specified by paragraph (g)(1) or (g)(2) of this
AD.
(j) Retained Corrective Actions
This paragraph restates the corrective actions required by
paragraph (j) of AD 2012-18-13, Amendment 39-17190 (77 FR 57990,
September 19, 2012). If any discrepancy is detected during any
inspection required by paragraph (g), (h), or (i) of this AD: Prior
to further flight, accomplish the actions specified by paragraphs
(j)(1) and (j)(3) of this AD, and paragraph (j)(2) of this AD, if
applicable.
(1) Perform a high frequency eddy current inspection from the
forward side of the bulkhead to detect cracking of the web at the
``Y'' chord attachment, around the entire periphery of the ``Y''
chord, in accordance with Boeing 737 Nondestructive Test Manual D6-
37239, Part 6, Section 51-00-00, Figure 23, dated November 5, 1995.
(2) If the most recent inspection performed in accordance with
paragraph (g) of this AD was not a detailed visual inspection:
Accomplish the actions specified by paragraph (g)(2) of this AD. If
the inspection was a detailed visual inspection, it is not necessary
to repeat that inspection prior to further flight.
(3) Repair any discrepancy such as cracking or corrosion or
misdrilled fastener holes using a method approved in accordance with
the procedures specified in paragraph (u) of this AD.
(k) Retained Inspections of the Web at the ``Y'' Chord Upper Bulkhead
From S-15L to S-15R
This paragraph restates the inspections of the web at the ``Y''
chord upper bulkhead from S-15L to S-15R required by paragraph (k)
of AD 2012-18-13, Amendment 39-17190 (77 FR 57990, September 19,
2012). At the later of the times specified in paragraphs (k)(1) and
(k)(2) of this AD: Do detailed and LFEC inspections of the aft side
of the bulkhead web, or do detailed and high frequency eddy current
(HFEC) inspections from the forward side of the bulkhead, and do all
applicable related investigative and corrective actions; in
accordance with Part 1 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 737-53A1214, Revision 4, dated December 16,
2011, except as required by paragraphs (r)(1) and (r)(3) of this AD.
Inspect for cracks, incorrectly drilled fastener holes, and
elongated fastener holes. Do all applicable related investigative
and corrective actions before further flight. Repeat the inspections
at the applicable times specified in table 1 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1214,
Revision 4, dated December 16, 2011.
(1) Prior to the accumulation of 25,000 total flight cycles.
(2) Except as required by paragraphs (r)(2) and (r)(4) of this
AD, at the later of the times specified in the ``Compliance Time''
column in table 1 of paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-53A1214, Revision 4, dated December 16, 2011.
(l) Retained Inspections of the Web at the ``Y'' Chord in the Lower
Bulkhead From S-15L to S-15R With Revised Inspection and Repair
Conditions
This paragraph restates the inspections of the web at the ``Y''
chord in the lower bulkhead from S-15L to S-15R required by
paragraph (l) of AD 2012-18-13, Amendment 39-17190 (77 FR 57990,
September 19, 2012), with revised inspection and repair conditions.
Except as required by paragraphs (r)(2) and (r)(5) of this AD, at
the applicable time specified in table 2 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1214,
Revision 4, dated December 16, 2011: Do detailed and eddy current
inspections of the web from the forward or aft side of the bulkhead
for cracks, incorrectly drilled fastener holes, and elongated
fastener holes, in accordance with Part III of the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-53A1214, Revision
4, dated December 16, 2011, except as required by paragraphs (r)(1)
and (r)(3) of this AD. If any crack, incorrectly drilled fastener
hole, elongated fastener hole, or corrosion is found, before further
flight, repair using a method approved in accordance with the
procedures specified in paragraph (u) of this AD. Repeat the
inspections at the applicable times specified in table 2 of
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-53A1214, Revision 4, dated December 16, 2011.
(m) Retained One-Time Inspection Under the Tear Strap
This paragraph restates the one-time inspection under the tear
strap required by paragraph (m) of AD 2012-18-13, Amendment 39-17190
(77 FR 57990, September 19, 2012). Except as required by paragraphs
(r)(2) and (r)(5) of this AD, at the applicable time specified in
table 3 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 737-53A1214, Revision 4, dated December 16, 2011: Do a one-
time LFEC inspection for cracks on the aft side of the bulkhead of
the web located under the outer circumferential tear strap, or do a
one-time HFEC inspection for cracks from the forward side of the
bulkhead of the web located under the outer circumferential tear
strap, in accordance with Part II of the Accomplishment Instructions
of Boeing Alert Service Bulletin 737-53A1214, Revision 4, dated
December 16, 2011, except as required by paragraph (r)(1) of this
AD. If any cracking is found, before further flight, repair the
bulkhead using a method approved in accordance with the procedures
specified in paragraph (u) of this AD.
(n) Retained Inspection for Oil-Canning
This paragraph restates the inspection for oil-canning required
by paragraph (n) of AD 2012-18-13, Amendment 39-17190 (77 FR 57990,
September 19, 2012). Except as required by paragraph (r)(2) of this
AD, at the applicable time specified in table 4 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1214,
Revision 4, dated December 16, 2011: Do a detailed inspection from
the aft side of the bulkhead for oil-canning and do all
[[Page 27024]]
applicable related investigative and corrective actions, in
accordance with Part II of the Accomplishment Instructions of Boeing
Alert Service Bulletin 737-53A1214, Revision 4, dated December 16,
2011, except as required by paragraph (r)(1) of this AD. Do all
related investigative and corrective actions before further flight.
Thereafter, repeat the inspection at the applicable times specified
in table 4 of paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-53A1214, Revision 4, dated December 16, 2011.
For oil-cans found within the limits specified in Part II of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1214, Revision 4, dated December 16, 2011: In lieu of installing
the repair before further flight, at the applicable times specified
in table 4 of paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-53A1214, Revision 4, dated December 16, 2011,
do initial and repetitive detailed and HFEC inspections for cracks
of the oil-canning and install the repair, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1214, Revision 4, dated December 16, 2011. If any crack is found,
before further flight, repair the cracking using a method approved
in accordance with the procedures specified in paragraph (u) of this
AD. Installing the repair terminates the repetitive inspections for
cracks.
(o) Retained Inspection of the Dome Cap at the Center of the Bulkhead
This paragraph restates the inspection of the dome cap at the
center of the bulkhead required by paragraph (o) of AD 2012-18-13,
Amendment 39-17190 (77 FR 57990, September 19, 2012). Except as
required by paragraphs (r)(2) and (r)(5) of this AD, at the
applicable time specified in table 5 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1214,
Revision 4, dated December 16, 2011: Do an eddy current inspection
to detect any cracking of the dome cap at the center of the
bulkhead, and do all applicable corrective actions, in accordance
with Part IV of the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-53A1214, Revision 4, dated December 16, 2011.
Do all corrective actions before further flight. Repeat the
inspection at the times specified in table 5 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1214,
Revision 4, dated December 16, 2011.
(p) Retained Inspection of the Forward Flange of the ``Z'' Stiffeners
at the Dome Cap
This paragraph restates the inspection of the forward flange of
the ``Z'' stiffeners at the dome cap required by paragraph (p) of AD
2012-18-13, Amendment 39-17190 (77 FR 57990, September 19, 2012).
Except as required by paragraphs (r)(2) and (r)(5) of this AD, at
the applicable time specified in table 6 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1214,
Revision 4, dated December 16, 2011: Do an HFEC inspection to detect
any cracking of the ``Z'' stiffener flanges at the dome cap in the
center of the bulkhead, in accordance with Part V of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1214, Revision 4, dated December 16, 2011, except as required by
paragraph (r)(1) of this AD. If any crack is found, before further
flight, repair the flanges using a method approved in accordance
with the procedures specified in paragraph (u) of this AD. Repeat
the inspection at the applicable times specified in table 6 of
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-53A1214, Revision 4, dated December 16, 2011.
(q) Retained Inspection for Existing Repairs on the Bulkhead
This paragraph restates the inspection for existing repairs on
the bulkhead required by paragraph (q) of AD 2012-18-13, Amendment
39-17190 (77 FR 57990, September 19, 2012). Except as required by
paragraph (r)(2) of this AD, at the applicable time specified in
table 7 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 737-53A1214, Revision 4, dated December 16, 2011: Do a
detailed inspection of the bulkhead web and stiffeners for existing
repairs, in accordance with Part VI of the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-53A1214, Revision
4, dated December 16, 2011, except as required by paragraph (r)(1)
of this AD.
(1) If any repair identified in the ``Condition'' column of
table 8 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 737-53A1214, Revision 4, dated December 16, 2011, is found
and the ``Reference'' column refers to Appendix A, B, C, or D of
that service bulletin: At the applicable times specified in table 8
of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-53A1214, Revision 4, dated December 16, 2011, except as required
by paragraph (r)(2) of this AD, do an HFEC inspection or an LFEC
inspection of the web for cracking, in accordance with Appendix A,
B, C, or D, as applicable, of Boeing Alert Service Bulletin 737-
53A1214, Revision 4, dated December 16, 2011. If any cracking is
found, before further flight, repair using a method approved in
accordance with the procedures specified in paragraph (u) of this
AD. Repeat the inspections thereafter at the applicable intervals
specified in table 8 of paragraph 1.E., ``Compliance,'' of Boeing
Alert Service Bulletin 737-53A1214, Revision 4, dated December 16,
2011.
(2) If any repair identified in the ``Condition'' column of
table 8 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 737-53A1214, Revision 4, dated December 16, 2011, is found
and the ``Reference'' column refers to Appendix E of that service
bulletin: At the applicable times specified in table 8 of paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1214,
Revision 4, dated December 16, 2011, except as required by paragraph
(r)(2) of this AD, remove the repair and replace with a new repair,
in accordance with Appendix E of Boeing Alert Service Bulletin 737-
53A1214, Revision 4, dated December 16, 2011.
(3) If any non-SRM (structural repair manual) repair is found
and the repair does not have FAA-approved damage tolerance
inspections: Except as required by paragraph (r)(2) of this AD, at
the applicable time specified in table 7 of Paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1214,
Revision 4, dated December 16, 2011, contact the Boeing Commercial
Airplanes Organization Designation Authorization (ODA) that has been
authorized by the Manager, Seattle Aircraft Certification Office
(ACO), for damage tolerance inspections. Do those damage tolerance
inspections at the times given using a method approved in accordance
with the procedures specified in paragraph (u) of this AD.
(r) Retained Exceptions to the Service Information
This paragraph restates the exceptions to the service
information required by paragraph (r) of AD 2012-18-13, Amendment
39-17190 (77 FR 57990, September 19, 2012).
(1) Where Boeing Alert Service Bulletin 737-53A1214, Revision 4,
dated December 16, 2011, specifies to contact Boeing for repair
instructions: Before further flight, repair using a method approved
in accordance with the procedures specified in paragraph (u) of this
AD.
(2) Where Boeing Alert Service Bulletin 737-53A1214, Revision 4,
dated December 16, 2011, specifies a compliance time ``after the
date of Revision 1 to this service bulletin,'' ``from the date of
Revision 3 of this service bulletin,'' ``after the date of Revision
3 to this service bulletin,'' or ``of the effective date of AD 99-
08-23,'' this AD requires compliance within the specified compliance
time after October 24, 2012 (the effective date of AD 2012-18-13,
Amendment 39-17190 (77 FR 57990, September 19, 2012)).
(3) Access and restoration procedures specified in the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1214, Revision 4, dated December 16, 2011, are not required by
this AD. Operators may do those procedures following their
maintenance practices.
(4) Where table 1 of paragraph 1.E., ``Compliance,'' of Boeing
Alert Service Bulletin 737-53A1214, Revision 4, dated December 16,
2011, specifies a compliance time relative to actions done ``in
accordance with paragraph (a)(2) of AD 99-08-23,'' this AD requires
compliance within the specified compliance time relative to actions
specified in paragraph (g)(2) of this AD.
(5) Where the Condition columns in tables 2, 3, 5, and 6 of
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-53A1214, Revision 4, dated December 16, 2011, refer to total
flight cycles, this AD applies to the airplanes with the specified
total flight cycles as of October 24, 2012 (the effective date of AD
2012-18-13, Amendment 39-17190 (77 FR 57990, September 19, 2012)).
(s) Retained Terminating Action With Revised Paragraph Reference
This paragraph restates the terminating action specified in
paragraph (s) of AD 2012-18-13, Amendment 39-17190 (77 FR 57990,
September 19, 2012), with a revised paragraph reference.
Accomplishment of the requirements in paragraph (k) of this AD
terminates the requirements of paragraphs (g) through (j) of this
AD.
[[Page 27025]]
(t) Credit for Previous Actions
This paragraph restates the credit for previous actions
specified by paragraph (t) of AD 2012-18-13, Amendment 39-17190 (77
FR 57990, September 19, 2012). This paragraph provides credit for
the actions required by paragraphs (k) through (s) of this AD, if
the actions were performed before the effective date of this AD
using the service bulletins specified in paragraphs (t)(1) through
(t)(4) of this AD.
(1) Boeing Alert Service Bulletin 737-53A1214, dated June 17,
1999.
(2) Boeing Alert Service Bulletin 737-53A1214, Revision 1, dated
June 22, 2000.
(3) Boeing Alert Service Bulletin 737-53A1214, Revision 2, dated
May 24, 2001.
(4) Boeing Alert Service Bulletin 737-53A1214, Revision 3, dated
January 19, 2011.
(u) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle ACO, FAA, has the authority to approve
AMOCs for this AD, if requested using the procedures found in 14 CFR
39.19. In accordance with 14 CFR 39.19, send your request to your
principal inspector or local Flight Standards District Office, as
appropriate. If sending information directly to the manager of the
ACO, send it to the attention of the person identified in the
Related Information section of this AD. Information may be emailed
to: 9-ANM-Seattle-ACO-AMOC-Requests-faa.gov.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD if it is approved by the
Boeing Commercial Airplanes ODA that has been authorized by the
Manager, Seattle ACO, to make those findings. For a repair method to
be approved, the repair must meet the certification basis of the
airplane, and the approval must specifically refer to this AD.
(4) AMOCs approved previously in accordance with AD 99-08-23,
Amendment 39-11132 (64 FR 19879, April 23, 1999), are approved as
AMOCs for the corresponding provisions of this AD.
(5) AMOCs approved previously in accordance with AD 2012-18-13,
Amendment 39-17190 (77 FR 57990, September 19, 2012), are approved
as AMOCs for the corresponding provisions of this AD.
(v) Related Information
(1) For more information about this AD, contact Alan Pohl,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, Washington
98057-3356; phone: (425) 917-6440; fax: (425) 917-6590; email:
alan.pohl@faa.gov.
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P. O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone
206-544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may review copies of the referenced
service information at the FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, Washington. For information on the
availability of this material at the FAA, call 425-227-1221.
(w) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(3) The following service information was approved for IBR on
October 24, 2012 (77 FR 57990, September 19, 2012).
(i) Boeing Alert Service Bulletin 737-53A1214, Revision 4, dated
December 16, 2011.
(ii) Reserved.
(4) The following service information was approved for IBR on
May 10, 1999 (64 FR 19879, April 23, 1999).
(i) Boeing 737 Nondestructive Test Manual D6-37239, Part 6,
Section 53-10-54, dated December 5, 1998.
(ii) Boeing 737 Nondestructive Test Manual D6-37239, Part 6,
Section 51-00-00, Figure 23, dated November 5, 1995.
(5) For Boeing service information identified in this AD,
contact Boeing Commercial Airplanes, Attention: Data & Services
Management, P. O. Box 3707, MC 2H-65, Seattle, Washington 98124-
2207; telephone 206-544-5000, extension 1; fax 206-766-5680;
Internet https://www.myboeingfleet.com.
(6) You may review copies of the referenced service information
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW.,
Renton, Washington. For information on the availability of this
material at the FAA, call 425-227-1221.
(7) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on April 5, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-09113 Filed 5-8-13; 8:45 am]
BILLING CODE 4910-13-P
