Airworthiness Directives; The Boeing Company Airplanes, 43921-43925 [2015-17977]
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Federal Register / Vol. 80, No. 142 / Friday, July 24, 2015 / Rules and Regulations
specific to a consumer, and
§ 1026.19(e)(2)(iii), which prohibits
creditors from requiring the submission
of documents verifying information
related to the consumer’s application.
Accordingly, the provisions under
§ 1026.19(e)(2) are effective on October
3, 2015, without respect to whether an
application has been received on that
date. In addition, the amendments to
§ 1026.28 and the commentary to
§ 1026.29 govern the preemption of
State laws and thus, the amendments to
those provisions and associated
commentary made by the TILA–RESPA
Final Rule are effective on October 3,
2015, without respect to whether an
application has been received on that
date. The following examples illustrate
the application of the effective date for
the TILA–RESPA Final Rule.
i. General. Assume a creditor receives
an application, as defined under
§ 1026.2(a)(3) of the TILA–RESPA Final
Rule, for a transaction subject to
§ 1026.19(e) and (f) on October 3, 2015,
and that consummation of the
transaction occurs on October 31, 2015.
The amendments of the TILA–RESPA
Final Rule, including the requirements
to provide the Loan Estimate and
Closing Disclosure under § 1026.19(e)
and (f), apply to the transaction. The
creditor would also be required to
provide the special information booklet
under § 1026.19(g) of the TILA–RESPA
Final Rule, as applicable. Assume a
creditor receives an application, as
defined under § 1026.2(a)(3) of the
TILA–RESPA Final Rule, for a
transaction subject to § 1026.19(e) and
(f) on September 30, 2015, and that
consummation of the transaction occurs
on October 30, 2015. The amendments
of the TILA–RESPA Final Rule,
including the requirements to provide
the Loan Estimate and Closing
Disclosure under § 1026.19(e) and (f), do
not apply to the transaction, except that
the provisions of § 1026.19(e)(2),
specifically § 1026.19(e)(2)(i), (e)(2)(ii),
and (e)(2)(iii), do apply to the
transaction beginning on October 3,
2015, because they become effective on
October 3, 2015, without respect to
whether an application, as defined
under § 1026.2(a)(3) of the TILA–RESPA
Final Rule, has been received by the
creditor or mortgage broker on that date.
The creditor does not provide the
Closing Disclosure so that it is received
by the consumer at least three business
days before consummation; instead, the
creditor and the settlement agent
provide the disclosures under
§ 1026.19(a)(2)(ii) and § 1024.8, as
applicable, under the Truth in Lending
Act and the Real Estate Settlement
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Procedures Act, respectively. The
requirement to provide the special
information booklet under § 1026.19(g)
of the TILA–RESPA Final Rule would
also not apply to the transaction. But the
creditor would provide the special
information booklet under § 1024.6, as
applicable.
ii. Predisclosure written estimates.
Assume a creditor receives a request
from a consumer for a written estimate
of terms or costs specific to the
consumer on October 3, 2015, before the
consumer submits an application to the
creditor, and thus before the consumer
has received the disclosures required
under § 1026.19(e)(1)(i). The creditor, if
it provides such written estimate to the
consumer, must comply with the
requirements of § 1026.19(e)(2)(ii) and
provide the required statement on the
written estimate, even though the
creditor has not received an application
for a transaction subject to § 1026.19(e)
and (f) on that date.
iii. Request for preemption
determination. Assume a creditor
submits a request to the Bureau under
§ 1026.28(a)(1) for a determination of
whether a State law is inconsistent with
the disclosure requirements of the
TILA–RESPA Final Rule on October 3,
2015. Because the amendments to
§ 1026.28(a)(1) are effective on that date
and do not depend on whether the
creditor has received an application as
defined under § 1026.2(a)(3) of the
TILA–RESPA Final Rule,
§ 1026.28(a)(1), as amended by the
TILA–RESPA Final Rule, is applicable
to the request on that date and the
Bureau would make a determination
based on the amendments of the TILA–
RESPA Final Rule, including, for
example, the requirements of § 1026.37.
Subpart C—Closed End Credit
*
*
*
*
*
Section 1026.19—Certain Mortgage and
Variable-Rate Transactions
*
*
*
*
*
19(g)(2) Permissible changes.
*
*
*
*
*
3. Permissible changes to title of
booklets in use before October 3, 2015.
Section 1026.19(g)(2)(iv) provides that
the title appearing on the cover of the
booklet shall not be changed. Comment
19(g)(1)–1 states that the Bureau may,
from time to time, issue revised or
alternative versions of the special
information booklet that address
transactions subject to § 1026.19(g) by
publishing a notice in the Federal
Register. Until the Bureau issues a
version of the special information
booklet relating to the Loan Estimate
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43921
and Closing Disclosure under
§§ 1026.37 and 1026.38, for applications
that are received on or after October 3,
2015, a creditor may change the title
appearing on the cover of the version of
the special information booklet in use
before October 3, 2015, provided the
words ‘‘settlement costs’’ are used in the
title. See comment 1(d)(5)–1 for
guidance regarding compliance with
§ 1026.19(g) for applications received on
or after October 3, 2015.
*
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*
*
Dated: July 20, 2015.
Richard Cordray,
Director, Bureau of Consumer Financial
Protection.
[FR Doc. 2015–18239 Filed 7–22–15; 11:15 am]
BILLING CODE 4810–AM–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0572; Directorate
Identifier 2014–NM–027–AD; Amendment
39–18214; AD 2015–15–05]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 98–22–10
for certain The Boeing Company Model
737–100, –200, –200C, and –300 series
airplanes. AD 98–22–10 required
repetitive inspections for cracking of the
aft frame and frame support structure of
the forward service doorway, and repair
if necessary. AD 98–22–10 also
provided an optional terminating action
for the repetitive inspection
requirements of that AD. This new AD
requires new inspections and adds
airplanes to the applicability; for certain
airplanes, this new AD provides an
optional preventive modification, which
terminates the repetitive inspections.
This AD was prompted by reports of
fatigue cracking of the aft frame and
frame support structure of the forward
service doorway around the six
doorstop fittings, and a determination
that inspections are needed in
additional locations and that additional
airplanes might be subject to the
identified unsafe condition. We are
issuing this AD to detect and correct
fatigue cracking of the aft frame and
frame support structure of the forward
service doorway around the six
SUMMARY:
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Federal Register / Vol. 80, No. 142 / Friday, July 24, 2015 / Rules and Regulations
doorstop fittings, which could result in
door deflection and loss of
pressurization.
DATES: This AD is effective August 28,
2015.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of August 28, 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;
phone: 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. It is also available
on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0572.
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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–
0572; 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
(ACO), 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 to supersede AD 98–22–10,
Amendment 39–10858 (63 FR 57240,
October 27, 1998). AD 98–22–10 applied
to certain The Boeing Company Model
737–100, –200, –200C, and –300 series
airplanes. The NPRM was published in
the Federal Register on August 26, 2014
(79 FR 50867). The NPRM was
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prompted by reports of cracking in the
surround structure of the forward galley
service doorway between body station
(STA) 332.1 and STA 344, which are
outside the inspection area of AD 98–
22–10, and by reports that cracking has
been discovered on airplanes outside
the applicability of AD 98–22–10. We
have determined that inspections are
needed in additional locations, and that
additional airplanes are subject to the
identified unsafe condition.
The NPRM (79 FR 50867, August 26,
2014) proposed to continue to require
repetitive inspections for cracking of the
aft frame and frame support structure of
the forward service doorway, and repair
if necessary. The NPRM also proposed
to add inspections, add airplanes to the
applicability, and for certain airplanes,
provide an optional preventive
modification, which would terminate
the repetitive inspections. We are
issuing this AD to detect and correct
fatigue cracking of the aft frame and
frame support structure of the forward
service doorway around the six
doorstop fittings, which could result in
door deflection and loss of
pressurization.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM (79 FR 50867,
August 26, 2014) and the FAA’s
response to each comment.
Request To Clarify Wording in NPRM
(79 FR 50867, August 6, 2014)
Boeing stated paragraph 1.E,
‘‘Compliance,’’ of Boeing Service
Bulletin 737–53A1108, Revision 7,
dated July 7, 2014, provides actions for
airplanes repaired or modified
previously where the preventive
modifications have been accomplished.
Boeing stated that paragraph (l)(4) of the
proposed AD reads: ‘‘AMOCs approved
for AD 98–22–10, Amendment 39–
10858 (63 FR 57240, October 27, 1998),
are approved as AMOCs for the
corresponding provisions of this AD.’’
Boeing interpreted the latter statement
to mean that AMOCs approved for AD
98–22–10 do not supersede (or negate)
the additional inspection requirements
provided in Boeing Service Bulletin
737–53A1108, Revision 7, dated July 7,
2014, and requested concurrence with
its interpretation of this language.
We agree with Boeing’s interpretation.
Paragraph (m)(4) of this AD (paragraph
(l)(4) of the proposed AD) establishes
that an AMOC issued for actions
performed in accordance with AD 98–
22–10, Amendment 39–10858 (63 FR
57240, October 27, 1998), satisfies the
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corresponding provisions, and only
those corresponding provisions, of the
this AD. All requirements of this AD
must be satisfied, whether by previous
AMOC, accomplishment of the specified
AD actions, or a new AMOC. We have
not changed this AD in this regard.
Request To Clarify Actions That Are
Not Required
Southwest Airlines (Southwest) noted
that paragraph (h) of the proposed AD
(79 FR 50867, August 26, 2014) would
provide terminating action for the
repetitive inspections required by
paragraph (g) of this AD. Southwest
requested that we revise the NPRM to
state that the post preventive
modification inspections specified in
tables 9, 10, 11, and 12 in paragraph 1.E,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1108, Revision 7,
dated July 7, 2014, would not be
required. Southwest also requested that
this provision apply to paragraph (k) of
the proposed AD (paragraph (l) of this
AD), which specifies credit for actions
done previously using Boeing Alert
Service Bulletin 737–53A1108, Revision
6, dated January 9, 2014.
We agree with the requests. While the
post-preventive modification
inspections specified by tables 9
through 12 in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1108, Revision 7,
dated July 7, 2014, 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)),
those actions are not required by this
AD. We have revised paragraph (g) of
this AD by specifying the required parts
of the service information: Parts 2 and
4. We have also added new paragraph
(j) in this final rule to specify that postpreventive modification inspections
(Part 6) are not required by this AD. We
have redesignated subsequent
paragraphs of this AD accordingly.
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
accomplishment of the actions specified
in the NPRM (79 FR 50867, August 26,
2014).
We concur with the commenter. We
have redesignated paragraph (c) of the
proposed AD (79 FR 50867, August 26,
2014) as (c)(1) and added new paragraph
(c)(2) to this AD to state that installation
of STC ST01219SE (https://rgl.faa.gov/
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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.
Explanation of Additional Changes
Made to This AD
We have updated the Costs of
Compliance section to add existing
inspection and repair costs from AD 98–
22–10, Amendment 39–10858 (63 FR
57240, October 27, 1998).
We have changed paragraph (b) of this
AD to add AD 90–06–02, Amendment
39–6489, (55 FR 8372, March 7, 1990),
as an affected AD since accomplishment
of the preventative modification
required by paragraph (h) of this AD is
an alternative method of compliance for
paragraph A. of AD 90–06–02.
In various locations, Boeing Alert
Service Bulletin 737–53A1108, Revision
7, dated July 7, 2014, cites Boeing Alert
Service Bulletin 737–53A1108, Revision
6, dated January 9, 2014, instead of
Revision 7 of the service information.
We have added a new paragraph (k)(3)
in this AD to clarify that, where
Revision 7 of the service information
specifies accomplishment of a
preventative modification be done using
Revision 6 of the service information,
this AD requires accomplishment of that
preventative modification with Revision
7 of this service information.
We also noted a discrepancy in table
4 of paragraph 1.E., ‘‘Compliance,’’ in
Boeing Alert Service Bulletin 737–
53A1108, Revision 7, dated July 7, 2014.
Although the fourth action is an
inspection of the intercostals ‘‘and
attaching stringers,’’ the corresponding
corrective action specified in table 4 is
for only a crack in ‘‘an intercostal.’’ We
have confirmed with Boeing that the
‘‘attaching stringers’’ were inadvertently
omitted from this condition in table 4.
Repair of a cracked attaching stringer,
however, is described in PART 4,
paragraph 7, of the Accomplishment
Instructions of Boeing Alert Service
Bulletin 737–53A1108, Revision 7,
dated July 7, 2014. We have added a
new paragraph (k)(4) in this AD to
specify that cracking in the attaching
stringers also requires repair.
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
43923
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM (79 FR
50867, August 26, 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 50867,
August 26, 2014).
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Alert Service
Bulletin 737–53A1108, Revision 7,
dated July 7, 2014. The service
information describes procedures for
inspections for cracking of the aft frame
and frame support structure of the
forward service doorway, and repair if
necessary. This service information is
reasonably available because the
interested parties have access to it
through their normal course of business
or by the means identified in the
ADDRESSES section 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
Cost per
product
Action
Labor cost
Parts cost
Cost on U.S. operators
Inspection [retained actions from AD
98–22–10, Amendment 39–10858
(63 FR 57240, October 27, 1998)].
Inspection [new AD action] ...................
7 work-hours × $85 per hour = $595
per inspection cycle.
$0 ...........
$595 per inspection
cycle.
$249,305 per inspection cycle.
28 work-hours × $85 per hour =
$2,380 per inspection cycle.
None ......
$2,380 per inspection
cycle.
$997,220 per inspection cycle.
ESTIMATED COSTS FOR ON-CONDITION ACTIONS
Action
Labor cost
Parts cost
Cost per
product
Repair [retained actions from AD 98–22–10, Amendment
39–10858 (63 FR 57240, October 27, 1998)].
42 work-hours × $85 per hour = $3,570 ..........................
$913
$4,483
ESTIMATED COSTS FOR OPTIONAL MODIFICATION
Labor cost
Parts cost
Repair/preventive modification [new AD action].
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Action
Between 12 and 17 work-hours × $85 per
hour = between $1,020 and $1,445.
Between $90 and $913 ..
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
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Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
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Cost per product
Between $1,110 and
$2,358.
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
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Federal Register / Vol. 80, No. 142 / Friday, July 24, 2015 / Rules and Regulations
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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
98–22–10, Amendment 39–10858 (63
FR 57240, October 27, 1998), and
adding the following new AD:
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■
2015–15–05 The Boeing Company:
Amendment 39–18214; Docket No. FAA–
2014–0572; Directorate Identifier 2014–
NM–027–AD.
(a) Effective Date
This AD is effective August 28, 2015.
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(b) Affected ADs
(1) This AD replaces AD 98–22–10,
Amendment 39–10858 (63 FR 57240, October
27, 1998).
(2) This AD affects AD 90–06–02,
Amendment 39–6489 (55 FR 8372, March 7,
1990).
Repeat the inspections at the applicable
times specified in tables 1 through 6 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1108,
Revision 7, dated July 7, 2014, until the
terminating action specified in paragraph (h)
of this AD is done.
(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 737–53A1108,
Revision 7, dated July 7, 2014.
(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.
(h) Optional Terminating Action
For Group 1, Configuration 1; Group 1,
Configuration 2; Group 2; Group 3; Group 4,
Configuration 1; and Group 4, Configuration
2 airplanes identified in Boeing Alert Service
Bulletin 737–53A1108, Revision 7, dated July
7, 2014: Accomplishment of a preventive
modification in accordance with Part 5 of
Boeing Alert Service Bulletin 737–53A1108,
Revision 7, dated July 7, 2014, terminates the
repetitive inspections required by paragraph
(g) of this AD.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of
fatigue cracking of the aft frame and frame
support structure of the forward service
doorway around the six doorstop fittings, and
a determination that inspections are needed
in additional locations and that additional
airplanes might be subject to the identified
unsafe condition. We are issuing this AD to
detect and correct fatigue cracking of the aft
frame and frame support structure of the
forward service doorway around the six
doorstop fittings, which could result in door
deflection and loss of pressurization.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspections and Corrective Actions
At the applicable times specified in tables
1 through 6 of paragraph 1.E., ‘‘Compliance,’’
of Boeing Alert Service Bulletin 737–
53A1108, Revision 7, dated July 7, 2014,
except as required by paragraph (k)(1) of this
AD: Do detailed inspections of the frame web
between body station (STA) 332.1 and STA
344, intercostal T-brackets, intercostal Tchords, intercostals, and stringers, as
applicable; do high frequency eddy current
(HFEC) inspections for cracking of door stop
intercostal T-brackets, intercostal web, door
stop intercostal T-chords, intercostals, and
stringers, as applicable; and do all applicable
related investigative and corrective actions;
in accordance with Parts 2 and 4 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1108, Revision 7,
dated July 7, 2014, except as required by
paragraphs (k)(2) through (k)(4) of this AD.
Do all applicable related investigative and
corrective actions before further flight.
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(i) Inspections and Corrective Actions for
Group 5 Airplanes
For Group 5 airplanes identified in Boeing
Alert Service Bulletin 737–53A1108,
Revision 7, dated July 7, 2014: Within 120
days after the effective date of this AD,
inspect and repair any cracking using a
method approved in accordance with the
procedures specified in paragraph (m) of this
AD. Repair any cracking, before further flight.
(j) Post Preventive Modification Inspections
Not Required
The post preventive modification
inspections specified in tables 9 through 12
in paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1108,
Revision 6, dated January 9, 2014; and
Boeing Alert Service Bulletin 737–53A1108,
Revision 7, dated July 7, 2014; are not
required by this AD.
Note 1 to paragraph (j) of this AD: Tables
9 through 12 in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1108, Revision 6, dated
January 9, 2014; and Boeing Alert Service
Bulletin 737–53A1108, Revision 7, dated July
7, 2014; specify that post preventive
modification inspections 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)). The corresponding
actions specified in the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1108, Revision 6, dated January 9,
2014; and Boeing Alert Service Bulletin 737–
53A1108, Revision 7, dated July 7, 2014; are
not required by this AD.
(k) Exceptions to the Service Information
(1) Where Boeing Alert Service Bulletin
737–53A1108, Revision 7, dated July 7, 2014,
specifies a compliance time ‘‘after the issue
date of Revision 6 of this service bulletin,’’
this AD requires compliance within the
specified time after the effective date of this
AD.
(2) Where Boeing Alert Service Bulletin
737–53A1108, Revision 7, dated July 7, 2014,
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.
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Federal Register / Vol. 80, No. 142 / Friday, July 24, 2015 / Rules and Regulations
(3) Where Boeing Alert Service Bulletin
737–53A1108, Revision 7, dated July 7, 2014,
specifies accomplishment of a preventative
modification in accordance with ‘‘Revision 6
of this service bulletin,’’ this AD requires
accomplishment of those actions to be done
in accordance with Boeing Alert Service
Bulletin 737–53A1108, Revision 7, dated July
7, 2014.
(4) Where table 4 in paragraph 1.E,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1108, Revision 7, dated July
7, 2014, specifies repairing a condition
identified as any crack found in ‘‘an
intercostal,’’ this AD requires repairing a
condition identified as any crack found in
‘‘an intercostal or attaching stringers.’’
(l) Credit for Previous Actions
This paragraph provides credit for the
actions required by paragraphs (g) and (h) of
this AD, if those actions were performed
before the effective date of this AD using
Boeing Alert Service Bulletin 737–53A1108,
Revision 6, dated January 9, 2014. This
service information is not incorporated by
reference in this AD.
rmajette on DSK2VPTVN1PROD with RULES
(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)(1) of this AD. Information may
be emailed to: 9-ANM-LAACO-ACO-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.
(4) AMOCs approved previously for AD
98–22–10, Amendment 39–10858 (63 FR
57240, October 27, 1998), are approved as
AMOCs for the corresponding provisions of
this AD.
(5) Accomplishment of the preventive
modification in accordance with Boeing Alert
Service Bulletin 737–53A1108, Revision 7,
dated July 7, 2014, as required by paragraph
(h) of this AD, is an AMOC for the structural
modification specified in Boeing Alert
Service Bulletin 737–53A1108 that is
required by paragraph A. of AD 90–06–02,
Amendment 39–6489, (55 FR 8372, March 7,
1990), for the airplanes identified in
paragraph (h) of this AD.
VerDate Sep<11>2014
14:07 Jul 23, 2015
Jkt 235001
(n) Related Information
(1) For more information about this AD,
contact Nenita Odesa, Aerospace Engineer,
Airframe Branch, ANM–120L, FAA, Los
Angeles ACO, 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; phone: 562–627–
5234; fax: 562–627–5210; email:
nenita.odesa@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraph (o)(3) of this AD.
(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 Alert Service Bulletin 737–
53A1108, Revision 7, dated July 7, 2014. (ii)
Reserved.
(3) For Boeing 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; phone:
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.
Issued in Renton, Washington, on July 10,
2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2015–17977 Filed 7–23–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–0679; Directorate
Identifier 2013–NM–182–AD; Amendment
39–18211; AD 2015–15–02]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
PO 00000
Frm 00015
Fmt 4700
Sfmt 4700
43925
We are superseding
Airworthiness Directive (AD) 2012–13–
06, for all Airbus Model A300 series
airplanes and all Model A300 B4–600,
B4–600R, and F4–600R series airplanes,
and Model A300 C4–605R Variant F
airplanes (collectively called Model
A300–600 series airplanes). AD 2012–
13–06 required a one-time detailed
inspection to determine the length of
the fire shut-off valve (FSOV) bonding
leads and for contact or chafing of the
wires, and corrective actions if
necessary. This new AD requires a new
one-time detailed inspection of the
FSOV bonding leads to ensure that the
correct bonding leads are inspected, and
corrective action if necessary. This AD
was prompted by a determination that
the description of the inspection area
specified in the service information was
misleading; therefore, some operators
might have inspected incorrect bonding
leads. We are issuing this AD to detect
and correct contact or chafing of wires
and the bonding leads, which, if not
detected, could be a source of sparks in
the wing trailing edge, and could lead
to an uncontrolled engine fire.
DATES: This AD becomes effective
August 28, 2015.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of August 28, 2015.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2015-0679; or in
person at the 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.
For service information identified in
this AD, contact Airbus SAS,
Airworthiness Office—EAW, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com;
Internet https://www.airbus.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. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
0679.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
SUMMARY:
E:\FR\FM\24JYR1.SGM
24JYR1
]]>Agencies
[Federal Register Volume 80, Number 142 (Friday, July 24, 2015)]
[Rules and Regulations]
[Pages 43921-43925]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-17977]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0572; Directorate Identifier 2014-NM-027-AD;
Amendment 39-18214; AD 2015-15-05]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 98-22-10 for
certain The Boeing Company Model 737-100, -200, -200C, and -300 series
airplanes. AD 98-22-10 required repetitive inspections for cracking of
the aft frame and frame support structure of the forward service
doorway, and repair if necessary. AD 98-22-10 also provided an optional
terminating action for the repetitive inspection requirements of that
AD. This new AD requires new inspections and adds airplanes to the
applicability; for certain airplanes, this new AD provides an optional
preventive modification, which terminates the repetitive inspections.
This AD was prompted by reports of fatigue cracking of the aft frame
and frame support structure of the forward service doorway around the
six doorstop fittings, and a determination that inspections are needed
in additional locations and that additional airplanes might be subject
to the identified unsafe condition. We are issuing this AD to detect
and correct fatigue cracking of the aft frame and frame support
structure of the forward service doorway around the six
[[Page 43922]]
doorstop fittings, which could result in door deflection and loss of
pressurization.
DATES: This AD is effective August 28, 2015.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of August 28,
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; phone: 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. It
is also available on the Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA-2014-0572.
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-
0572; 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 (ACO), 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 to supersede AD 98-22-10, Amendment 39-10858 (63 FR 57240,
October 27, 1998). AD 98-22-10 applied to certain The Boeing Company
Model 737-100, -200, -200C, and -300 series airplanes. The NPRM was
published in the Federal Register on August 26, 2014 (79 FR 50867). The
NPRM was prompted by reports of cracking in the surround structure of
the forward galley service doorway between body station (STA) 332.1 and
STA 344, which are outside the inspection area of AD 98-22-10, and by
reports that cracking has been discovered on airplanes outside the
applicability of AD 98-22-10. We have determined that inspections are
needed in additional locations, and that additional airplanes are
subject to the identified unsafe condition.
The NPRM (79 FR 50867, August 26, 2014) proposed to continue to
require repetitive inspections for cracking of the aft frame and frame
support structure of the forward service doorway, and repair if
necessary. The NPRM also proposed to add inspections, add airplanes to
the applicability, and for certain airplanes, provide an optional
preventive modification, which would terminate the repetitive
inspections. We are issuing this AD to detect and correct fatigue
cracking of the aft frame and frame support structure of the forward
service doorway around the six doorstop fittings, which could result in
door deflection and loss of pressurization.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM (79
FR 50867, August 26, 2014) and the FAA's response to each comment.
Request To Clarify Wording in NPRM (79 FR 50867, August 6, 2014)
Boeing stated paragraph 1.E, ``Compliance,'' of Boeing Service
Bulletin 737-53A1108, Revision 7, dated July 7, 2014, provides actions
for airplanes repaired or modified previously where the preventive
modifications have been accomplished. Boeing stated that paragraph
(l)(4) of the proposed AD reads: ``AMOCs approved for AD 98-22-10,
Amendment 39-10858 (63 FR 57240, October 27, 1998), are approved as
AMOCs for the corresponding provisions of this AD.'' Boeing interpreted
the latter statement to mean that AMOCs approved for AD 98-22-10 do not
supersede (or negate) the additional inspection requirements provided
in Boeing Service Bulletin 737-53A1108, Revision 7, dated July 7, 2014,
and requested concurrence with its interpretation of this language.
We agree with Boeing's interpretation. Paragraph (m)(4) of this AD
(paragraph (l)(4) of the proposed AD) establishes that an AMOC issued
for actions performed in accordance with AD 98-22-10, Amendment 39-
10858 (63 FR 57240, October 27, 1998), satisfies the corresponding
provisions, and only those corresponding provisions, of the this AD.
All requirements of this AD must be satisfied, whether by previous
AMOC, accomplishment of the specified AD actions, or a new AMOC. We
have not changed this AD in this regard.
Request To Clarify Actions That Are Not Required
Southwest Airlines (Southwest) noted that paragraph (h) of the
proposed AD (79 FR 50867, August 26, 2014) would provide terminating
action for the repetitive inspections required by paragraph (g) of this
AD. Southwest requested that we revise the NPRM to state that the post
preventive modification inspections specified in tables 9, 10, 11, and
12 in paragraph 1.E, ``Compliance,'' of Boeing Alert Service Bulletin
737-53A1108, Revision 7, dated July 7, 2014, would not be required.
Southwest also requested that this provision apply to paragraph (k) of
the proposed AD (paragraph (l) of this AD), which specifies credit for
actions done previously using Boeing Alert Service Bulletin 737-
53A1108, Revision 6, dated January 9, 2014.
We agree with the requests. While the post-preventive modification
inspections specified by tables 9 through 12 in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1108, Revision
7, dated July 7, 2014, 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)), those
actions are not required by this AD. We have revised paragraph (g) of
this AD by specifying the required parts of the service information:
Parts 2 and 4. We have also added new paragraph (j) in this final rule
to specify that post-preventive modification inspections (Part 6) are
not required by this AD. We have redesignated subsequent paragraphs of
this AD accordingly.
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/$FILE/ST01219SE.pdf) does not affect
accomplishment of the actions specified in the NPRM (79 FR 50867,
August 26, 2014).
We concur with the commenter. We have redesignated paragraph (c) of
the proposed AD (79 FR 50867, August 26, 2014) as (c)(1) and added new
paragraph (c)(2) to this AD to state that installation of STC ST01219SE
(https://rgl.faa.gov/
[[Page 43923]]
Regulatory_and_Guidance_Library/rgstc.nsf/0/
ebd1cec7b301293e86257cb30045557a/$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.
Explanation of Additional Changes Made to This AD
We have updated the Costs of Compliance section to add existing
inspection and repair costs from AD 98-22-10, Amendment 39-10858 (63 FR
57240, October 27, 1998).
We have changed paragraph (b) of this AD to add AD 90-06-02,
Amendment 39-6489, (55 FR 8372, March 7, 1990), as an affected AD since
accomplishment of the preventative modification required by paragraph
(h) of this AD is an alternative method of compliance for paragraph A.
of AD 90-06-02.
In various locations, Boeing Alert Service Bulletin 737-53A1108,
Revision 7, dated July 7, 2014, cites Boeing Alert Service Bulletin
737-53A1108, Revision 6, dated January 9, 2014, instead of Revision 7
of the service information. We have added a new paragraph (k)(3) in
this AD to clarify that, where Revision 7 of the service information
specifies accomplishment of a preventative modification be done using
Revision 6 of the service information, this AD requires accomplishment
of that preventative modification with Revision 7 of this service
information.
We also noted a discrepancy in table 4 of paragraph 1.E.,
``Compliance,'' in Boeing Alert Service Bulletin 737-53A1108, Revision
7, dated July 7, 2014. Although the fourth action is an inspection of
the intercostals ``and attaching stringers,'' the corresponding
corrective action specified in table 4 is for only a crack in ``an
intercostal.'' We have confirmed with Boeing that the ``attaching
stringers'' were inadvertently omitted from this condition in table 4.
Repair of a cracked attaching stringer, however, is described in PART
4, paragraph 7, of the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-53A1108, Revision 7, dated July 7, 2014. We have
added a new paragraph (k)(4) in this AD to specify that cracking in the
attaching stringers also requires repair.
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 50867, August 26, 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 50867, August 26, 2014).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Alert Service Bulletin 737-53A1108, Revision 7,
dated July 7, 2014. The service information describes procedures for
inspections for cracking of the aft frame and frame support structure
of the forward service doorway, and repair if necessary. This service
information is reasonably available because the interested parties have
access to it through their normal course of business or by the means
identified in the ADDRESSES section 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
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection [retained actions 7 work-hours x $85 $0................ $595 per $249,305 per
from AD 98-22-10, Amendment 39- per hour = $595 inspection cycle. inspection cycle.
10858 (63 FR 57240, October 27, per inspection
1998)]. cycle.
Inspection [new AD action]...... 28 work-hours x None.............. $2,380 per $997,220 per
$85 per hour = inspection cycle. inspection cycle.
$2,380 per
inspection cycle.
----------------------------------------------------------------------------------------------------------------
Estimated Costs for On-Condition Actions
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Repair [retained actions from AD 98-22-10, 42 work-hours x $85 per hour = $913 $4,483
Amendment 39-10858 (63 FR 57240, October 27, $3,570.
1998)].
----------------------------------------------------------------------------------------------------------------
Estimated Costs for Optional Modification
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Repair/preventive modification [new Between 12 and 17 work- Between $90 and $913... Between $1,110 and
AD action]. hours x $85 per hour = $2,358.
between $1,020 and
$1,445.
----------------------------------------------------------------------------------------------------------------
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
[[Page 43924]]
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)
98-22-10, Amendment 39-10858 (63 FR 57240, October 27, 1998), and
adding the following new AD:
2015-15-05 The Boeing Company: Amendment 39-18214; Docket No. FAA-
2014-0572; Directorate Identifier 2014-NM-027-AD.
(a) Effective Date
This AD is effective August 28, 2015.
(b) Affected ADs
(1) This AD replaces AD 98-22-10, Amendment 39-10858 (63 FR
57240, October 27, 1998).
(2) This AD affects AD 90-06-02, Amendment 39-6489 (55 FR 8372,
March 7, 1990).
(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-
53A1108, Revision 7, dated July 7, 2014.
(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 of fatigue cracking of the aft
frame and frame support structure of the forward service doorway
around the six doorstop fittings, and a determination that
inspections are needed in additional locations and that additional
airplanes might be subject to the identified unsafe condition. We
are issuing this AD to detect and correct fatigue cracking of the
aft frame and frame support structure of the forward service doorway
around the six doorstop fittings, which could result in door
deflection and loss of pressurization.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspections and Corrective Actions
At the applicable times specified in tables 1 through 6 of
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-53A1108, Revision 7, dated July 7, 2014, except as required by
paragraph (k)(1) of this AD: Do detailed inspections of the frame
web between body station (STA) 332.1 and STA 344, intercostal T-
brackets, intercostal T-chords, intercostals, and stringers, as
applicable; do high frequency eddy current (HFEC) inspections for
cracking of door stop intercostal T-brackets, intercostal web, door
stop intercostal T-chords, intercostals, and stringers, as
applicable; and do all applicable related investigative and
corrective actions; in accordance with Parts 2 and 4 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1108, Revision 7, dated July 7, 2014, except as required by
paragraphs (k)(2) through (k)(4) of this AD. Do all applicable
related investigative and corrective actions before further flight.
Repeat the inspections at the applicable times specified in tables 1
through 6 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 737-53A1108, Revision 7, dated July 7, 2014, until the
terminating action specified in paragraph (h) of this AD is done.
(h) Optional Terminating Action
For Group 1, Configuration 1; Group 1, Configuration 2; Group 2;
Group 3; Group 4, Configuration 1; and Group 4, Configuration 2
airplanes identified in Boeing Alert Service Bulletin 737-53A1108,
Revision 7, dated July 7, 2014: Accomplishment of a preventive
modification in accordance with Part 5 of Boeing Alert Service
Bulletin 737-53A1108, Revision 7, dated July 7, 2014, terminates the
repetitive inspections required by paragraph (g) of this AD.
(i) Inspections and Corrective Actions for Group 5 Airplanes
For Group 5 airplanes identified in Boeing Alert Service
Bulletin 737-53A1108, Revision 7, dated July 7, 2014: Within 120
days after the effective date of this AD, inspect and repair any
cracking using a method approved in accordance with the procedures
specified in paragraph (m) of this AD. Repair any cracking, before
further flight.
(j) Post Preventive Modification Inspections Not Required
The post preventive modification inspections specified in tables
9 through 12 in paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-53A1108, Revision 6, dated January 9, 2014; and
Boeing Alert Service Bulletin 737-53A1108, Revision 7, dated July 7,
2014; are not required by this AD.
Note 1 to paragraph (j) of this AD: Tables 9 through 12 in
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-53A1108, Revision 6, dated January 9, 2014; and Boeing Alert
Service Bulletin 737-53A1108, Revision 7, dated July 7, 2014;
specify that post preventive modification inspections 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)). The corresponding actions specified in the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1108, Revision 6, dated January 9, 2014; and Boeing Alert Service
Bulletin 737-53A1108, Revision 7, dated July 7, 2014; are not
required by this AD.
(k) Exceptions to the Service Information
(1) Where Boeing Alert Service Bulletin 737-53A1108, Revision 7,
dated July 7, 2014, specifies a compliance time ``after the issue
date of Revision 6 of this service bulletin,'' this AD requires
compliance within the specified time after the effective date of
this AD.
(2) Where Boeing Alert Service Bulletin 737-53A1108, Revision 7,
dated July 7, 2014, 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.
[[Page 43925]]
(3) Where Boeing Alert Service Bulletin 737-53A1108, Revision 7,
dated July 7, 2014, specifies accomplishment of a preventative
modification in accordance with ``Revision 6 of this service
bulletin,'' this AD requires accomplishment of those actions to be
done in accordance with Boeing Alert Service Bulletin 737-53A1108,
Revision 7, dated July 7, 2014.
(4) Where table 4 in paragraph 1.E, ``Compliance,'' of Boeing
Alert Service Bulletin 737-53A1108, Revision 7, dated July 7, 2014,
specifies repairing a condition identified as any crack found in
``an intercostal,'' this AD requires repairing a condition
identified as any crack found in ``an intercostal or attaching
stringers.''
(l) Credit for Previous Actions
This paragraph provides credit for the actions required by
paragraphs (g) and (h) of this AD, if those actions were performed
before the effective date of this AD using Boeing Alert Service
Bulletin 737-53A1108, Revision 6, dated January 9, 2014. This
service information is not incorporated by reference in this AD.
(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)(1) of this AD.
Information may be emailed to: 9-ANM-LAACO-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 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.
(4) AMOCs approved previously for AD 98-22-10, Amendment 39-
10858 (63 FR 57240, October 27, 1998), are approved as AMOCs for the
corresponding provisions of this AD.
(5) Accomplishment of the preventive modification in accordance
with Boeing Alert Service Bulletin 737-53A1108, Revision 7, dated
July 7, 2014, as required by paragraph (h) of this AD, is an AMOC
for the structural modification specified in Boeing Alert Service
Bulletin 737-53A1108 that is required by paragraph A. of AD 90-06-
02, Amendment 39-6489, (55 FR 8372, March 7, 1990), for the
airplanes identified in paragraph (h) of this AD.
(n) Related Information
(1) For more information about this AD, contact Nenita Odesa,
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO,
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5234; fax: 562-627-5210; email: nenita.odesa@faa.gov.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraph (o)(3) of this AD.
(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 Alert Service Bulletin 737-53A1108, Revision 7, dated
July 7, 2014. (ii) Reserved.
(3) For Boeing 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; phone:
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 July 10, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-17977 Filed 7-23-15; 8:45 am]
BILLING CODE 4910-13-P
