Airworthiness Directives; The Boeing Company Airplanes, 73814-73817 [2014-28926]
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Federal Register / Vol. 79, No. 239 / Friday, December 12, 2014 / Rules and Regulations
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0057; Directorate
Identifier 2013–NM–210–AD; Amendment
39–18044; AD 2014–25–03]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 737–100,
–200, –200C, –300, –400, and –500
series airplanes. This AD was prompted
by reports from multiple operators that
have found fatigue cracking in the
corners of the forward galley service
doorway. This AD requires repetitive
inspections for any cracking of the skin
and bear strap doublers in the corners
of the forward galley service doorway,
and corrective action if necessary. This
AD also provides optional terminating
actions for certain repetitive
inspections. We are issuing this AD to
detect and correct fatigue cracking,
which could result in rapid loss of cabin
pressure.
DATES: This AD is effective January 16,
2015.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of January 16, 2015.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, WA 98124–2207;
telephone 206–544–5000, extension 1;
fax 206–766–5680; Internet https://
www.myboeingfleet.com. You may view
this referenced 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.
SUMMARY:
other information. The address for the
Docket Office (phone: 800–647–5527) is
Docket 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:
Nenita Odesa, Aerospace Engineer,
Airframe Branch, ANM–120L, FAA, Los
Angeles Aircraft Certification Office,
3960 Paramount Boulevard, Lakewood,
CA 90712–4137; phone: 562–627–5234;
fax: 562–627–5210; email:
nenita.odesa@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain The Boeing Company
Model 737–100, –200, –200C, –300,
–400, and –500 series airplanes. The
NPRM published in the Federal
Register on February 25, 2014 (79 FR
10429). The NPRM was prompted by
reports from multiple operators that
have found fatigue cracking of the skin
and bear strap in the corners of the
forward galley service doorway. Some of
the reported cracks were found outside
of areas of directed or recommended
inspections, or in areas modified as
specified in previous revisions of
Boeing Alert Service Bulletin 737–
53A1116. Some airplanes were found to
have multiple cracks in the corner areas.
The NPRM proposed to require
repetitive inspections for any cracking
of the skin and bear strap doublers in
the corners of the forward galley service
doorway, and corrective action if
necessary. The NPRM also proposed to
provide optional terminating actions for
certain repetitive inspections. We are
issuing this AD to detect and correct
fatigue cracking, which could result in
rapid loss of cabin pressure.
rljohnson on DSK3VPTVN1PROD with RULES
Examining the AD Docket
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM (79 FR 10429,
February 25, 2014) and the FAA’s
response to each comment.
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0057; 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
Request To Clarify Terminating Action
for Initial Inspection
Southwest Airlines (Southwest)
requested that the NPRM (79 FR 10429,
February 25, 2014) be revised to include
provisions in paragraph (i)(1) of the
proposed AD for terminating the
requirement proposed by paragraph (g)
of the proposed AD for initial
inspections in the areas of the upper aft
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corner that are covered by the repair.
Southwest noted that paragraph (i)(1) of
the proposed AD provides for
terminating the repetitive inspections
required by paragraph (g) of the AD.
Southwest also stated that it would like
clarification on whether
accomplishment of a repair also
terminates the initial inspection
requirements of paragraph (g) of the
proposed AD for the upper aft corner.
We agree to revise paragraph (i)(1) of
this AD. Notes in the tables of paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert
Service Bulletin 737–53A1116, Revision
4, dated September 30, 2013, state that
accomplishing certain repairs
terminates repetitive inspections in the
areas covered by the repair. We have
determined that accomplishing the
repair as required by paragraph (i)(1) of
this AD would also terminate the initial
inspection requirement for that repaired
corner. We have coordinated this issue
with Boeing and revised paragraph (i)(1)
of this AD to terminate the initial
inspection requirement as well. We
have also revised paragraphs (i)(2) and
(i)(3) of this AD accordingly.
Request To Add a Repair as a Method
of Compliance
Southwest requested that paragraph
(i) of the proposed AD (79 FR 10429,
February 25, 2014), be revised to
specifically provide for repairs
accomplished using information from
certain repair procedures specified in
Boeing Alert Service Bulletin 737–
53A1116, Revision 4, dated September
30, 2013, and to allow accomplishment
of those repairs as terminating action for
the inspection requirements of
paragraph (g) of the proposed AD.
Southwest also requested an additional
provision to allow Repair 2 of section
53–10–01 of the Boeing 737–300/–500
Structural Repair Manual as terminating
action for the initial and repetitive
inspections proposed in paragraph (g) of
the proposed AD.
We partially agree with the request.
Certain repair procedures are addressed
in Boeing Alert Service Bulletin 737–
53A1116, Revision 4, dated September
30, 2013, as possible methods of
corrective action or preventative
modification. Provisions for these repair
procedures are provided in paragraphs
(i)(2) and (i)(3) of this AD. However,
Repair 2 of section 53–10–01 of the
Boeing 737–300/–500 Structural Repair
Manual was not addressed in Boeing
Alert Service Bulletin 737–53A1116,
Revision 4, dated September 30, 2013,
or considered during development of
this AD. We do not consider that
delaying this action until the
manufacturer revises the service
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information to include the information
in Repair 2 is warranted. To delay this
action would be inappropriate since we
have determined that an unsafe
condition exists and that actions
required by this AD must be conducted
to ensure continued safety. Operators
may apply for an alternative method of
compliance (AMOC) under the
requirements of paragraph (m) of this
AD.
Request To Revise Credit Paragraph
Southwest noted that paragraph (k) of
the proposed AD (79 FR 10429,
February 25, 2014), gives credit for
inspections of the upper corners of the
forward galley doors, provided that the
preventative modification is also
inspected in accordance with the
requirements of paragraph (g) of the
proposed AD. Southwest also noted that
paragraph (k) of the proposed AD does
not specifically mention whether credit
is given for previous repairs that were
accomplished using the specified
service information or explain how
these repairs affect compliance with the
initial inspection requirements of
paragraph (g) of the AD.
We agree to clarify the intent of
paragraph (k) of this AD. If any
inspection of the upper corners of the
forward galley service door was
accomplished before the effective date
of this AD using any of the service
information identified in paragraphs
(k)(1), (k)(2), (k)(3), and (k)(4) of this AD
instead of Boeing Alert Service Bulletin
737–53A1116, Revision 4, dated
September 30, 2013, those inspections
are considered acceptable for
compliance with certain requirements of
paragraph (g) of this AD. Certain
modifications specified in those
previous service bulletins that were
previously determined to be terminating
action for inspections, have now been
determined to need further inspection
in accordance with paragraph (g) of this
AD and Boeing Alert Service Bulletin
737–53A1116, Revision 4, dated
September 30, 2013. Paragraphs (i)(1)
and (i)(2) of this AD address repairs of
the upper corners and clarify that
accomplishing the repairs terminates
the requirements of paragraph (g) of this
AD for the inspections of the repaired
area. Repetitive inspections specified in
paragraph (g) of this AD are required
and are only terminated if optional
terminating action specified in
paragraph (i) of this AD is done. We
have not changed the AD in this regard.
Request To Accommodate Certain
AMOCs
Southwest noted that Note 14 in the
Accomplishment Instructions of Boeing
Alert Service Bulletin 737–53A1116,
Revision 4, dated September 30, 2013,
specifies that inspections as given in
that service bulletin for the upper
forward corner are not necessary in the
repaired area if, among other conditions,
‘‘the repair has been approved as an
Alternative Method of Compliance
(AMOC) to AD 2008–11–04.’’ Southwest
pointed out that AD 2008–11–04,
Amendment 39–15526 (73 FR 29421,
May 21, 2008), has been superseded by
AD 2014–05–21, Amendment 39–17794
(79 FR 14992, March 18, 2014), and
requests that Note 14 of the
Accomplishment Instructions of Boeing
Alert Service Bulletin 737–53A1116,
Revision 4, dated September 30, 2013,
also apply to repairs approved as an
AMOC to AD 2014–05–21.
We partially agree with Southwest’s
request. We cannot revise Boeing’s
service information. However, we have
added paragraph (j)(3) to this AD to
provide an exception to Boeing Alert
Service Bulletin 737–53A1116, Revision
4, dated September 30, 2013, and allow
a Boeing-provided repair that has been
approved as an AMOC to AD 2014–05–
21, Amendment 39–17794 (79 FR
14992, March 18, 2014), for the repaired
area only, provided the approval was
made before the effective date of this AD
and the repair doubler covers the
doorway upper forward corner and the
upper hinge cutout.
Effect of Winglets on This AD
Aviation Partners Boeing stated that
accomplishing the supplemental type
73815
certificate (STC) ST01219SE (https://
rgl.faa.gov/Regulatory_and_Guidance_
Library/rgstc.nsf/0/
ebd1cec7b301293e86257cb30045557a/
$FILE/ST01219SE.pdf) does not affect
the actions specified in the NPRM (79
FR 10429, February 25, 2014).
We concur with the commenter. We
have redesignated paragraph (c) of the
NPRM (79 FR 10429, February 25, 2014)
as (c)(1) and added new paragraph (c)(2)
to this final rule to state that installation
of STC ST01219SE (https://rgl.faa.gov/
Regulatory_and_Guidance_Library/
rgstc.nsf/0/
ebd1cec7b301293e86257cb30045557a/
$FILE/ST01219SE.pdf) does not affect
the ability to accomplish the actions
required by this final rule. 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.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this AD
with the changes described previously
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM (79 FR
10429, February 25, 2014) for correcting
the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (79 FR 10429,
February 25, 2014).
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Costs of Compliance
We estimate that this AD affects 419
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Labor cost
Parts cost
Cost per product
Inspection ..........
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Action
19 work-hours × $85 per hour =
$1,615 per inspection cycle.
None ............
$1,615 per inspection cycle .........
We have received no definitive data
that would enable us to provide cost
estimates for any on-condition actions
specified in this AD. We have no way
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of determining the number of aircraft
that might need this repair.
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Cost on U.S. operators
$676,685 per inspection cycle.
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
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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
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
1. The authority citation for part 39
continues to read as follows:
■
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Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2014–25–03 The Boeing Company:
Amendment 39–18044 ; Docket No.
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FAA–2014–0057; Directorate Identifier
2013–NM–210–AD.
(a) Effective Date
This AD is effective January 16, 2015.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to The Boeing
Company Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes,
certificated in any category, as identified in
Boeing Alert Service Bulletin 737–53A1116,
Revision 4, dated September 30, 2013.
(2) Installation of Supplemental Type
Certificate (STC) ST01219SE (https://
rgl.faa.gov/Regulatory_and_Guidance_
Library/rgstc.nsf/0/
ebd1cec7b301293e86257cb30045557a/$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
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports from
multiple operators that have found fatigue
cracking in the corners of the forward galley
service doorway. We are issuing this AD to
detect and correct fatigue cracking, which
could result in rapid loss of cabin pressure.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspections and Corrective Actions for
Groups 1 Through 4 Airplanes
For Groups 1 through 4 airplanes identified
in Boeing Alert Service Bulletin 737–
53A1116, Revision 4, dated September 30,
2013: Within the applicable compliance
times specified in Tables 1 through 10 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1116,
Revision 4, dated September 30, 2013, except
as provided by paragraph (j)(1) and (j)(3) of
this AD, do the applicable detailed and low
frequency eddy current inspections for any
cracking of the skin and bear straps in the
corners of the forward galley service door,
and do all applicable corrective actions, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1116, Revision 4, dated September
30, 2013, except as required by paragraph
(j)(2) of this AD. Do all applicable corrective
actions before further flight. Repeat the
inspections at the applicable time specified
in Tables 1 through 10 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1116, Revision 4, dated
September 30, 2013.
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(h) Inspections and Corrective Actions for
Group 5 Airplanes
For Group 5 airplanes identified in Boeing
Alert Service Bulletin 737–53A1116,
Revision 4, dated September 30, 2013:
Within 120 days after the effective date of
this AD, do inspections of the skin and bear
straps and all applicable corrective actions
using a method approved in accordance with
the procedures specified in paragraph (m) of
this AD.
(i) Optional Terminating Actions
(1) For Groups 1 and 2 airplanes identified
in Boeing Alert Service Bulletin 737–
53A1116, Revision 4, dated September 30,
2013: Accomplishment of a repair before the
effective date of this AD in the upper aft
corner of the forward galley service doorway,
in accordance with the Accomplishment
Instructions of any service information
specified in paragraphs (i)(1)(i) through
(i)(1)(iv) of this AD, terminates the
inspections required by paragraph (g) of this
AD for that repaired doorway corner only.
(i) Boeing Service Bulletin 737–53–1116,
dated July 21, 1988.
(ii) Boeing Service Bulletin 737–53–1116,
Revision 1, dated September 7, 1989.
(iii) Boeing Service Bulletin 737–53–1116,
Revision 2, dated September 30, 1993.
(iv) Boeing Service Bulletin 737–53–1116,
Revision 3, dated July 27, 1995.
(2) For Group 2 airplanes identified in
Boeing Alert Service Bulletin 737–53A1116,
Revision 4, dated September 30, 2013, on
which no repair or modification was done
using any of the service information
identified in paragraphs (i)(2)(i) through
(i)(2)(iv) of this AD; and for Group 3
airplanes identified in Boeing Alert Service
Bulletin 737–53A1116, Revision 4, dated
September 30, 2013: Repairing or modifying
the upper aft corner of the forward galley
service doorway, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1116, Revision 4,
dated September 30, 2013, terminates the
inspections required by paragraph (g) of this
AD for that repaired or modified doorway
corner only.
(i) Boeing Service Bulletin 737–53–1116,
dated July 21, 1988.
(ii) Boeing Service Bulletin 737–53–1116,
Revision 1, dated September 7, 1989.
(iii) Boeing Service Bulletin 737–53–1116,
Revision 2, dated September 30, 1993.
(iv) Boeing Service Bulletin 737–53–1116,
Revision 3, dated July 27, 1995.
(3) For Groups 2 and 3 airplanes identified
in Boeing Alert Service Bulletin 737–
53A1116, Revision 4, dated September 30,
2013: Repairing or modifying the lower
forward or lower aft corner of the forward
galley service doorway, in accordance with
the Accomplishment Instructions of Boeing
Alert Service Bulletin 737–53A1116,
Revision 4, dated September 30, 2013,
terminates the inspections required by
paragraph (g) of this AD for that repaired or
modified doorway corner only.
(j) Exceptions to the Service Information
(1) Where Boeing Alert Service Bulletin
737–53A1116, Revision 4, dated September
30, 2013, specifies a compliance time ‘‘after
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the Revision 4 date of this service bulletin,’’
this AD requires compliance within the
specified compliance time ‘‘after the effective
date of this AD.’’
(2) Where Boeing Alert Service Bulletin
737–53A1116, Revision 4, dated September
30, 2013, specifies to contact Boeing for
repair instructions: Before further flight,
repair the cracking using a method approved
in accordance with the procedures specified
in paragraph (m) of this AD.
(3) Note 14 of paragraph 3.A., ‘‘General
Information’’ in the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1116, Revision 4, dated September
30, 2013, states that inspections as given in
that service bulletin are not required for the
upper forward corner if there is a Boeingprovided repair which has been approved as
an alternative method of compliance (AMOC)
to AD 2008–11–04, Amendment 39–15526
(73 FR 29421, May 21, 2008). This AD also
does not require inspections for the upper
forward corner given in Boeing Alert Service
Bulletin 737–53A1116, Revision 4, dated
September 30, 2013, if there is a Boeingprovided repair approved as an AMOC to the
corresponding requirements of AD 2014–05–
21, Amendment 39–17794 (79 FR 14992,
March 18, 2014), for the repaired area only,
provided the approval was made before the
effective date of this AD and the repair
doubler covers the doorway upper forward
corner and the upper hinge cutout.
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(k) Credit for Previous Actions
This paragraph provides credit for the
inspections of the upper corners of the
forward galley service doors specified in
paragraph (g) of this AD, if those actions were
performed before the effective date of this AD
using any of the service information
identified in paragraphs (k)(1) through (k)(4)
of this AD (which are not incorporated by
reference in this AD), provided that any
preventative modification installed using this
service information is inspected in
accordance with paragraph (g) of this AD.
(1) Boeing Service Bulletin 737–53–1116,
dated July 21, 1988.
(2) Boeing Service Bulletin 737–53–1116,
Revision 1, dated September 7, 1989.
(3) Boeing Service Bulletin 737–53–1116,
Revision 2, dated September 30, 1993.
(4) Boeing Service Bulletin 737–53–1116,
Revision 3, dated July 27, 1995.
(l) Post-Repair Inspections
The post-repair inspections specified in
Table 11 of paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 737–53A1116,
Revision 4, dated September 30, 2013, are not
required by this AD.
Note 1 to paragraph (l) of this AD: The
post-repair inspections specified in Table 11
of paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1116,
Revision 4, dated September 30, 2013, may
be used in support of compliance with
section 121.1109(c)(2) or 129.109(b)(2) of the
Federal Aviation Regulations (14 CFR
121.1109(c)(2) or 14 CFR 129.109(b)(2)).
(m) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Los Angeles Aircraft
Certification Office (ACO), FAA, has the
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14:38 Dec 11, 2014
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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
paragraph (n) of this AD. Information may be
emailed to: 9-ANM-LAACO-AMOCRequests@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 Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Los Angeles
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.
(n) Related Information
For more information about this AD,
contact Nenita Odesa, Aerospace Engineer,
Airframe Branch, ANM–120L, FAA, Los
Angeles Aircraft Certification Office, 3960
Paramount Boulevard, Lakewood, CA 90712–
4137; phone: 562–627–5234; fax: 562–627–
5210; email: nenita.odesa@faa.gov.
(o) 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) Boeing Service Bulletin 737–53–1116,
dated July 21, 1988.
(ii) Boeing Service Bulletin 737–53–1116,
Revision 1, dated September 7, 1989. Pages
20, 21, and 22 are dated July 21, 1988.
(iii) Boeing Service Bulletin 737–53–1116,
Revision 2, dated September 30, 1993.
(iv) Boeing Service Bulletin 737–53–1116,
Revision 3, dated July 27, 1995.
(v) Boeing Alert Service Bulletin 737–
53A1116, Revision 4, dated September 30,
2013.
(3) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P. O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; telephone 206–
544–5000, extension 1; fax 206–766–5680;
Internet https://www.myboeingfleet.com.
(4) You may view this service information
at 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.
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73817
Issued in Renton, Washington, on
November 28, 2014.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2014–28926 Filed 12–11–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF THE TREASURY
Internal Revenue Service
26 CFR Part 1
[TD 9706]
RIN 1545–BJ69
Reporting of Specified Foreign
Financial Assets
Internal Revenue Service (IRS),
Treasury.
ACTION: Final regulations and removal of
temporary regulations.
AGENCY:
This document contains final
regulations providing guidance relating
to the provisions of the Hiring
Incentives to Restore Employment
(HIRE) Act that require specified foreign
financial assets to be reported to the
Internal Revenue Service for taxable
years beginning after March 18, 2010. In
particular, the final regulations provide
guidance relating to the requirement
that individuals attach a statement to
their income tax return to provide
required information regarding specified
foreign financial assets in which they
have an interest. The final regulations
affect individuals required to file Form
1040, ‘‘U.S. Individual Income Tax
Return,’’ or Form 1040–EZ, ‘‘Income
Tax Return for Single and Joint Filers
With No Dependents,’’ and certain
individuals required to file Form 1040–
NR, ‘‘Nonresident Alien Income Tax
Return,’’ or Form 1040NR–EZ, ‘‘U.S.
Income Tax Return for Certain
Nonresident Aliens with No
Dependents.’’
SUMMARY:
Effective Date: These regulations
are effective on December 12, 2014.
Applicability Date: For dates of
applicability, see §§ 1.6038D–1(b),
1.6038D–2(g), 1.6038D–3(e), 1.6038D–
4(b), 1.6038D–5(g), 1.6038D–7(d), and
1.6038D–8(g).
FOR FURTHER INFORMATION CONTACT:
Joseph S. Henderson or Michael
Kaercher, (202) 317–6942 (not a toll-free
number).
SUPPLEMENTARY INFORMATION:
DATES:
Paperwork Reduction Act
An agency may not conduct or
sponsor, and a person is not required to
E:\FR\FM\12DER1.SGM
12DER1
Agencies
[Federal Register Volume 79, Number 239 (Friday, December 12, 2014)]
[Rules and Regulations]
[Pages 73814-73817]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-28926]
[[Page 73814]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0057; Directorate Identifier 2013-NM-210-AD;
Amendment 39-18044; AD 2014-25-03]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) for certain
The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500
series airplanes. This AD was prompted by reports from multiple
operators that have found fatigue cracking in the corners of the
forward galley service doorway. This AD requires repetitive inspections
for any cracking of the skin and bear strap doublers in the corners of
the forward galley service doorway, and corrective action if necessary.
This AD also provides optional terminating actions for certain
repetitive inspections. We are issuing this AD to detect and correct
fatigue cracking, which could result in rapid loss of cabin pressure.
DATES: This AD is effective January 16, 2015.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of January 16,
2015.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced 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.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0057; 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 Docket 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: Nenita Odesa, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-
627-5234; fax: 562-627-5210; email: nenita.odesa@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to certain The Boeing Company
Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. The
NPRM published in the Federal Register on February 25, 2014 (79 FR
10429). The NPRM was prompted by reports from multiple operators that
have found fatigue cracking of the skin and bear strap in the corners
of the forward galley service doorway. Some of the reported cracks were
found outside of areas of directed or recommended inspections, or in
areas modified as specified in previous revisions of Boeing Alert
Service Bulletin 737-53A1116. Some airplanes were found to have
multiple cracks in the corner areas. The NPRM proposed to require
repetitive inspections for any cracking of the skin and bear strap
doublers in the corners of the forward galley service doorway, and
corrective action if necessary. The NPRM also proposed to provide
optional terminating actions for certain repetitive inspections. We are
issuing this AD to detect and correct fatigue cracking, which could
result in rapid loss of cabin pressure.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM (79
FR 10429, February 25, 2014) and the FAA's response to each comment.
Request To Clarify Terminating Action for Initial Inspection
Southwest Airlines (Southwest) requested that the NPRM (79 FR
10429, February 25, 2014) be revised to include provisions in paragraph
(i)(1) of the proposed AD for terminating the requirement proposed by
paragraph (g) of the proposed AD for initial inspections in the areas
of the upper aft corner that are covered by the repair. Southwest noted
that paragraph (i)(1) of the proposed AD provides for terminating the
repetitive inspections required by paragraph (g) of the AD. Southwest
also stated that it would like clarification on whether accomplishment
of a repair also terminates the initial inspection requirements of
paragraph (g) of the proposed AD for the upper aft corner.
We agree to revise paragraph (i)(1) of this AD. Notes in the tables
of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-53A1116, Revision 4, dated September 30, 2013, state that
accomplishing certain repairs terminates repetitive inspections in the
areas covered by the repair. We have determined that accomplishing the
repair as required by paragraph (i)(1) of this AD would also terminate
the initial inspection requirement for that repaired corner. We have
coordinated this issue with Boeing and revised paragraph (i)(1) of this
AD to terminate the initial inspection requirement as well. We have
also revised paragraphs (i)(2) and (i)(3) of this AD accordingly.
Request To Add a Repair as a Method of Compliance
Southwest requested that paragraph (i) of the proposed AD (79 FR
10429, February 25, 2014), be revised to specifically provide for
repairs accomplished using information from certain repair procedures
specified in Boeing Alert Service Bulletin 737-53A1116, Revision 4,
dated September 30, 2013, and to allow accomplishment of those repairs
as terminating action for the inspection requirements of paragraph (g)
of the proposed AD. Southwest also requested an additional provision to
allow Repair 2 of section 53-10-01 of the Boeing 737-300/-500
Structural Repair Manual as terminating action for the initial and
repetitive inspections proposed in paragraph (g) of the proposed AD.
We partially agree with the request. Certain repair procedures are
addressed in Boeing Alert Service Bulletin 737-53A1116, Revision 4,
dated September 30, 2013, as possible methods of corrective action or
preventative modification. Provisions for these repair procedures are
provided in paragraphs (i)(2) and (i)(3) of this AD. However, Repair 2
of section 53-10-01 of the Boeing 737-300/-500 Structural Repair Manual
was not addressed in Boeing Alert Service Bulletin 737-53A1116,
Revision 4, dated September 30, 2013, or considered during development
of this AD. We do not consider that delaying this action until the
manufacturer revises the service
[[Page 73815]]
information to include the information in Repair 2 is warranted. To
delay this action would be inappropriate since we have determined that
an unsafe condition exists and that actions required by this AD must be
conducted to ensure continued safety. Operators may apply for an
alternative method of compliance (AMOC) under the requirements of
paragraph (m) of this AD.
Request To Revise Credit Paragraph
Southwest noted that paragraph (k) of the proposed AD (79 FR 10429,
February 25, 2014), gives credit for inspections of the upper corners
of the forward galley doors, provided that the preventative
modification is also inspected in accordance with the requirements of
paragraph (g) of the proposed AD. Southwest also noted that paragraph
(k) of the proposed AD does not specifically mention whether credit is
given for previous repairs that were accomplished using the specified
service information or explain how these repairs affect compliance with
the initial inspection requirements of paragraph (g) of the AD.
We agree to clarify the intent of paragraph (k) of this AD. If any
inspection of the upper corners of the forward galley service door was
accomplished before the effective date of this AD using any of the
service information identified in paragraphs (k)(1), (k)(2), (k)(3),
and (k)(4) of this AD instead of Boeing Alert Service Bulletin 737-
53A1116, Revision 4, dated September 30, 2013, those inspections are
considered acceptable for compliance with certain requirements of
paragraph (g) of this AD. Certain modifications specified in those
previous service bulletins that were previously determined to be
terminating action for inspections, have now been determined to need
further inspection in accordance with paragraph (g) of this AD and
Boeing Alert Service Bulletin 737-53A1116, Revision 4, dated September
30, 2013. Paragraphs (i)(1) and (i)(2) of this AD address repairs of
the upper corners and clarify that accomplishing the repairs terminates
the requirements of paragraph (g) of this AD for the inspections of the
repaired area. Repetitive inspections specified in paragraph (g) of
this AD are required and are only terminated if optional terminating
action specified in paragraph (i) of this AD is done. We have not
changed the AD in this regard.
Request To Accommodate Certain AMOCs
Southwest noted that Note 14 in the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-53A1116, Revision 4, dated September
30, 2013, specifies that inspections as given in that service bulletin
for the upper forward corner are not necessary in the repaired area if,
among other conditions, ``the repair has been approved as an
Alternative Method of Compliance (AMOC) to AD 2008-11-04.'' Southwest
pointed out that AD 2008-11-04, Amendment 39-15526 (73 FR 29421, May
21, 2008), has been superseded by AD 2014-05-21, Amendment 39-17794 (79
FR 14992, March 18, 2014), and requests that Note 14 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1116, Revision 4, dated September 30, 2013, also apply to repairs
approved as an AMOC to AD 2014-05-21.
We partially agree with Southwest's request. We cannot revise
Boeing's service information. However, we have added paragraph (j)(3)
to this AD to provide an exception to Boeing Alert Service Bulletin
737-53A1116, Revision 4, dated September 30, 2013, and allow a Boeing-
provided repair that has been approved as an AMOC to AD 2014-05-21,
Amendment 39-17794 (79 FR 14992, March 18, 2014), for the repaired area
only, provided the approval was made before the effective date of this
AD and the repair doubler covers the doorway upper forward corner and
the upper hinge cutout.
Effect of Winglets on This AD
Aviation Partners Boeing stated that accomplishing the supplemental
type certificate (STC) ST01219SE (https://rgl.faa.gov/
Regulatory_and_Guidance_Library/rgstc.nsf/0/
ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf) does not affect
the actions specified in the NPRM (79 FR 10429, February 25, 2014).
We concur with the commenter. We have redesignated paragraph (c) of
the NPRM (79 FR 10429, February 25, 2014) as (c)(1) and added new
paragraph (c)(2) to this final rule to state that installation of STC
ST01219SE (https://rgl.faa.gov/Regulatory_and_Guidance_Library/
rgstc.nsf/0/ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf) does
not affect the ability to accomplish the actions required by this final
rule. 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.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (79 FR 10429, February 25, 2014) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (79 FR 10429, February 25, 2014).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Costs of Compliance
We estimate that this AD affects 419 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection...................... 19 work-hours x $85 per None............... $1,615 per inspection $676,685 per inspection cycle.
hour = $1,615 per cycle.
inspection cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for any on-condition actions specified in this AD. We
have no way of determining the number of aircraft that might need this
repair.
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
[[Page 73816]]
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
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 adding the following new airworthiness
directive (AD):
2014-25-03 The Boeing Company: Amendment 39-18044 ; Docket No. FAA-
2014-0057; Directorate Identifier 2013-NM-210-AD.
(a) Effective Date
This AD is effective January 16, 2015.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes, certificated in any
category, as identified in Boeing Alert Service Bulletin 737-
53A1116, Revision 4, dated September 30, 2013.
(2) Installation of Supplemental Type Certificate (STC)
ST01219SE (https://rgl.faa.gov/Regulatory_and_Guidance_Library/
rgstc.nsf/0/ebd1cec7b301293e86257cb30045557a/$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
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports from multiple operators that
have found fatigue cracking in the corners of the forward galley
service doorway. We are issuing this AD to detect and correct
fatigue cracking, which could result in rapid loss of cabin
pressure.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspections and Corrective Actions for Groups 1 Through 4 Airplanes
For Groups 1 through 4 airplanes identified in Boeing Alert
Service Bulletin 737-53A1116, Revision 4, dated September 30, 2013:
Within the applicable compliance times specified in Tables 1 through
10 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 737-53A1116, Revision 4, dated September 30, 2013, except
as provided by paragraph (j)(1) and (j)(3) of this AD, do the
applicable detailed and low frequency eddy current inspections for
any cracking of the skin and bear straps in the corners of the
forward galley service door, and do all applicable corrective
actions, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-53A1116, Revision 4, dated
September 30, 2013, except as required by paragraph (j)(2) of this
AD. Do all applicable corrective actions before further flight.
Repeat the inspections at the applicable time specified in Tables 1
through 10 of paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-53A1116, Revision 4, dated September 30, 2013.
(h) Inspections and Corrective Actions for Group 5 Airplanes
For Group 5 airplanes identified in Boeing Alert Service
Bulletin 737-53A1116, Revision 4, dated September 30, 2013: Within
120 days after the effective date of this AD, do inspections of the
skin and bear straps and all applicable corrective actions using a
method approved in accordance with the procedures specified in
paragraph (m) of this AD.
(i) Optional Terminating Actions
(1) For Groups 1 and 2 airplanes identified in Boeing Alert
Service Bulletin 737-53A1116, Revision 4, dated September 30, 2013:
Accomplishment of a repair before the effective date of this AD in
the upper aft corner of the forward galley service doorway, in
accordance with the Accomplishment Instructions of any service
information specified in paragraphs (i)(1)(i) through (i)(1)(iv) of
this AD, terminates the inspections required by paragraph (g) of
this AD for that repaired doorway corner only.
(i) Boeing Service Bulletin 737-53-1116, dated July 21, 1988.
(ii) Boeing Service Bulletin 737-53-1116, Revision 1, dated
September 7, 1989.
(iii) Boeing Service Bulletin 737-53-1116, Revision 2, dated
September 30, 1993.
(iv) Boeing Service Bulletin 737-53-1116, Revision 3, dated July
27, 1995.
(2) For Group 2 airplanes identified in Boeing Alert Service
Bulletin 737-53A1116, Revision 4, dated September 30, 2013, on which
no repair or modification was done using any of the service
information identified in paragraphs (i)(2)(i) through (i)(2)(iv) of
this AD; and for Group 3 airplanes identified in Boeing Alert
Service Bulletin 737-53A1116, Revision 4, dated September 30, 2013:
Repairing or modifying the upper aft corner of the forward galley
service doorway, in accordance with the Accomplishment Instructions
of Boeing Alert Service Bulletin 737-53A1116, Revision 4, dated
September 30, 2013, terminates the inspections required by paragraph
(g) of this AD for that repaired or modified doorway corner only.
(i) Boeing Service Bulletin 737-53-1116, dated July 21, 1988.
(ii) Boeing Service Bulletin 737-53-1116, Revision 1, dated
September 7, 1989.
(iii) Boeing Service Bulletin 737-53-1116, Revision 2, dated
September 30, 1993.
(iv) Boeing Service Bulletin 737-53-1116, Revision 3, dated July
27, 1995.
(3) For Groups 2 and 3 airplanes identified in Boeing Alert
Service Bulletin 737-53A1116, Revision 4, dated September 30, 2013:
Repairing or modifying the lower forward or lower aft corner of the
forward galley service doorway, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1116, Revision 4, dated September 30, 2013, terminates the
inspections required by paragraph (g) of this AD for that repaired
or modified doorway corner only.
(j) Exceptions to the Service Information
(1) Where Boeing Alert Service Bulletin 737-53A1116, Revision 4,
dated September 30, 2013, specifies a compliance time ``after
[[Page 73817]]
the Revision 4 date of this service bulletin,'' this AD requires
compliance within the specified compliance time ``after the
effective date of this AD.''
(2) Where Boeing Alert Service Bulletin 737-53A1116, Revision 4,
dated September 30, 2013, specifies to contact Boeing for repair
instructions: Before further flight, repair the cracking using a
method approved in accordance with the procedures specified in
paragraph (m) of this AD.
(3) Note 14 of paragraph 3.A., ``General Information'' in the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1116, Revision 4, dated September 30, 2013, states that
inspections as given in that service bulletin are not required for
the upper forward corner if there is a Boeing-provided repair which
has been approved as an alternative method of compliance (AMOC) to
AD 2008-11-04, Amendment 39-15526 (73 FR 29421, May 21, 2008). This
AD also does not require inspections for the upper forward corner
given in Boeing Alert Service Bulletin 737-53A1116, Revision 4,
dated September 30, 2013, if there is a Boeing-provided repair
approved as an AMOC to the corresponding requirements of AD 2014-05-
21, Amendment 39-17794 (79 FR 14992, March 18, 2014), for the
repaired area only, provided the approval was made before the
effective date of this AD and the repair doubler covers the doorway
upper forward corner and the upper hinge cutout.
(k) Credit for Previous Actions
This paragraph provides credit for the inspections of the upper
corners of the forward galley service doors specified in paragraph
(g) of this AD, if those actions were performed before the effective
date of this AD using any of the service information identified in
paragraphs (k)(1) through (k)(4) of this AD (which are not
incorporated by reference in this AD), provided that any
preventative modification installed using this service information
is inspected in accordance with paragraph (g) of this AD.
(1) Boeing Service Bulletin 737-53-1116, dated July 21, 1988.
(2) Boeing Service Bulletin 737-53-1116, Revision 1, dated
September 7, 1989.
(3) Boeing Service Bulletin 737-53-1116, Revision 2, dated
September 30, 1993.
(4) Boeing Service Bulletin 737-53-1116, Revision 3, dated July
27, 1995.
(l) Post-Repair Inspections
The post-repair inspections specified in Table 11 of paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1116,
Revision 4, dated September 30, 2013, are not required by this AD.
Note 1 to paragraph (l) of this AD: The post-repair inspections
specified in Table 11 of paragraph 1.E., ``Compliance,'' of Boeing
Alert Service Bulletin 737-53A1116, Revision 4, dated September 30,
2013, may be used in support of compliance with section
121.1109(c)(2) or 129.109(b)(2) of the Federal Aviation Regulations
(14 CFR 121.1109(c)(2) or 14 CFR 129.109(b)(2)).
(m) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Los Angeles Aircraft Certification Office
(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 paragraph (n) of this AD.
Information may be emailed to: 9-ANM-LAACO-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 Organization Designation Authorization
(ODA) that has been authorized by the Manager, Los Angeles 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.
(n) Related Information
For more information about this AD, contact Nenita Odesa,
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles
Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood,
CA 90712-4137; phone: 562-627-5234; fax: 562-627-5210; email:
nenita.odesa@faa.gov.
(o) 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) Boeing Service Bulletin 737-53-1116, dated July 21, 1988.
(ii) Boeing Service Bulletin 737-53-1116, Revision 1, dated
September 7, 1989. Pages 20, 21, and 22 are dated July 21, 1988.
(iii) Boeing Service Bulletin 737-53-1116, Revision 2, dated
September 30, 1993.
(iv) Boeing Service Bulletin 737-53-1116, Revision 3, dated July
27, 1995.
(v) Boeing Alert Service Bulletin 737-53A1116, Revision 4, dated
September 30, 2013.
(3) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P. O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
(4) You may view this service information at 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/ibr-locations.html.
Issued in Renton, Washington, on November 28, 2014.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-28926 Filed 12-11-14; 8:45 am]
BILLING CODE 4910-13-P