Airworthiness Directives; The Boeing Company Airplanes, 25630-25633 [2015-10316]
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25630
Federal Register / Vol. 80, No. 86 / Tuesday, May 5, 2015 / Proposed Rules
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–1266; Directorate
Identifier 2014–NM–151–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
The Boeing Company Model 747–100,
747–100B, 747–100B SUD, 747–200B,
747–300, 747SR, and 747SP series
airplanes. This proposed AD was
prompted by an evaluation by the
design approval holder (DAH)
indicating that certain fuselage skin lap
joints are subject to widespread fatigue
damage (WFD). This proposed AD
would require repetitive postmodification inspections for cracking of
the skin or internal doubler along the
edge fastener rows of the modification,
and repair if necessary. We are
proposing this AD to detect and correct
fatigue cracking in certain fuselage skin
lap joints, which could result in rapid
depressurization of the airplane.
DATES: We must receive comments on
this proposed AD by June 19, 2015.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed 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
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SUMMARY:
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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–
1266.
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–2015–
1266; 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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Nathan Weigand, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton,
Washington 98057–3356; phone: 425–
917–6428; fax: 425–917–6590; email:
nathan.p.weigand@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2015–1266; Directorate Identifier 2014–
NM–151–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
Structural fatigue damage is
progressive. It begins as minute cracks,
and those cracks grow under the action
of repeated stresses. This can happen
because of normal operational
conditions and design attributes, or
because of isolated situations or
incidents such as material defects, poor
fabrication quality, or corrosion pits,
dings, or scratches. Fatigue damage can
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occur locally, in small areas or
structural design details, or globally.
Global fatigue damage is general
degradation of large areas of structure
with similar structural details and stress
levels. Multiple-site damage is global
damage that occurs in a large structural
element such as a single rivet line of a
lap splice joining two large skin panels.
Global damage can also occur in
multiple elements such as adjacent
frames or stringers. Multiple-sitedamage and multiple-element-damage
cracks are typically too small initially to
be reliably detected with normal
inspection methods. Without
intervention, these cracks will grow,
and eventually compromise the
structural integrity of the airplane, in a
condition known as WFD. As an
airplane ages, WFD will likely occur,
and will certainly occur if the airplane
is operated long enough without any
intervention.
The FAA’s WFD final rule (75 FR
69746, November 15, 2010) became
effective on January 14, 2011. The WFD
rule requires certain actions to prevent
structural failure due to WFD
throughout the operational life of
certain existing transport category
airplanes and all of these airplanes that
will be certificated in the future. For
existing and future airplanes subject to
the WFD rule, the rule requires that
DAHs establish a limit of validity (LOV)
of the engineering data that support the
structural maintenance program.
Operators affected by the WFD rule may
not fly an airplane beyond its LOV,
unless an extended LOV is approved.
The WFD rule (75 FR 69746,
November 15, 2010) does not require
identifying and developing maintenance
actions if the DAHs can show that such
actions are not necessary to prevent
WFD before the airplane reaches the
LOV. Many LOVs, however, do depend
on accomplishment of future
maintenance actions. As stated in the
WFD rule, any maintenance actions
necessary to reach the LOV will be
mandated by airworthiness directives
through separate rulemaking actions.
In the context of WFD, this action is
necessary to enable DAHs to propose
LOVs that allow operators the longest
operational lives for their airplanes, and
still ensure that WFD will not occur.
This approach allows for an
implementation strategy that provides
flexibility to DAHs in determining the
timing of service information
development (with FAA approval),
while providing operators with certainty
regarding the LOV applicable to their
airplanes.
This proposed AD was prompted by
an evaluation by the DAH indicating
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Federal Register / Vol. 80, No. 86 / Tuesday, May 5, 2015 / Proposed Rules
that certain fuselage skin lap joints are
subject to WFD. We are proposing this
AD to detect and correct fatigue
cracking in certain fuselage skin lap
joints, which could result in rapid
depressurization of the airplane.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Alert Service
Bulletin 747–53A2367, Revision 5,
dated July 8, 2014. This service
information describes procedures for
inspections for cracks in the skin and
doublers along the edge fastener rows of
modifications in the fuselage, and
repairs. Refer to this service information
for information on the procedures and
compliance times. This service
information is reasonably available at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2015–
1266. Or see ADDRESSES for other ways
to access this service information.
Related Rulemaking
AD 2010–10–05, Amendment 39–
16284 (75 FR 27424, May 17, 2010)
requires, among other things,
modification of certain lap joints in
fuselage sections 41 and 42. This
proposed AD would require repetitive
post-modification inspections for
cracking of the skin or internal doubler
along the edge fastener rows of the
modification, and repair if necessary.
FAA’s Determination
We are proposing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other products of these same
type designs.
Proposed AD Requirements
This proposed AD would require
accomplishing the actions specified in
the service information described
previously, except as discussed under
‘‘Difference Between this Proposed AD
and the Service Information.’’
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Difference Between This Proposed AD
and the Service Information
Boeing Alert Service Bulletin 747–
53A2367, Revision 5, dated July 8, 2014,
specifies to contact the manufacturer for
instructions on how to repair cracking,
but this proposed AD would require
repairing those conditions in one of the
following ways:
• In accordance with a method that
we approve; or
• Using data that meet the
certification basis of the airplane, and
that have been approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) whom
we have authorized to make those
findings.
Costs of Compliance
We estimate that this proposed AD
affects 50 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
Action
Post-modification inspection
Labor cost
124 work-hours × $85 per
hour = $10,540 per inspection cycle..
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this proposed AD.
According to the manufacturer, some
of the costs of this proposed AD may be
covered under warranty, thereby
reducing the cost impact on affected
individuals. We do not control warranty
coverage for affected individuals. As a
result, we have included all costs in our
cost estimate.
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Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701:
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
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Parts cost
Jkt 235001
Cost per product
Cost on U.S. operators
$0
$10,540 per inspection cycle
$527,000 per inspection cycle.
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.
List of Subjects in 14 CFR Part 39
Regulatory Findings
The Proposed Amendment
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would 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 this proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
the 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.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
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Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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 adding
the following new airworthiness
directive (AD):
■
The Boeing Company: Docket No. FAA–
2014–1266; Directorate Identifier 2014–
NM–151–AD.
(a) Comments Due Date
We must receive comments by June 19,
2015.
(b) Affected ADs
None.
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Federal Register / Vol. 80, No. 86 / Tuesday, May 5, 2015 / Proposed Rules
(c) Applicability
This AD applies to The Boeing Company
Model 747–100, 747–100B, 747–100B SUD,
747–200B, 747–300, 747SR, and 747SP series
airplanes, certificated in any category, as
identified in Boeing Alert Service Bulletin
747–53A2367, Revision 5, dated July 8, 2014.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by an evaluation by
the design approval holder (DAH) indicating
that certain fuselage skin lap joints are
subject to widespread fatigue damage (WFD).
We are issuing this AD to detect and correct
fatigue cracking in certain fuselage skin lap
joints, which could result in rapid
depressurization of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Post-Modification Inspections
for Airplane Groups 1 Through 3, 7, and 8
For airplanes identified as Groups 1
through 3, 7, and 8 in Boeing Alert Service
Bulletin 747–53A2367, Revision 5, dated July
8, 2014: Except as provided by paragraph (m)
of this AD, at the applicable time specified
in table 3 of paragraph 1.E., ‘‘Compliance,’’
of Boeing Alert Service Bulletin 747–
53A2367, Revision 5, dated July 8, 2014, do
internal detailed and surface high frequency
eddy current (HFEC) inspections for cracks in
the skin and internal doubler along the edge
fastener rows of the modification; in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–53A2367, Revision 5, dated July 8, 2014.
In unrepaired areas, repeat the internal
detailed and surface HFEC inspections for
cracks in the skin or internal doubler along
the edge fastener rows of the modification
thereafter at the applicable intervals specified
in paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 747–53A2367,
Revision 5, dated July 8, 2014.
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(h) Initial Post-Modification Inspections for
Airplane Groups 4 Through 6, and 9
Through 11
For airplanes identified as Groups 4
through 6, and 9 through 11 in Boeing Alert
Service Bulletin 747–53A2367, Revision 5,
dated July 8, 2014, with external doublers
installed as specified in Boeing Service
Bulletin 747–53–2272: Except as provided by
paragraph (m) of this AD, at the applicable
time specified in table 4 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 747–53A2367, Revision 5, dated July
8, 2014, do external detailed, low frequency
eddy current (LFEC), and HFEC inspections
for cracks in the skin and external doubler,
in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–53A2367, Revision 5, dated July 8, 2014.
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(i) Repetitive Post-Modification Inspections
for Airplane Groups 4 Through 6, and 9
through 11
For airplanes with no crack findings during
the inspections required by paragraph (h) of
this AD: Do the applicable actions required
by paragraphs (i)(1) and (i)(2) of this AD.
(1) For airplanes with less than 15,000
flight cycles since stringer 6 external
doublers were installed as specified in
Boeing Service Bulletin 747–53–2272: At the
applicable intervals specified in table 4 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 747–53A2367,
Revision 5, dated July 8, 2014, in unrepaired
areas, repeat the external detailed and LFEC
inspections for cracks in the skin, and the
external detailed and HFEC inspections for
cracks in the external doubler, in accordance
with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–53A2367,
Revision 5, dated July 8, 2014.
(2) For airplanes with 15,000 or more flight
cycles since the stringer 6 external doublers
were installed as specified in Boeing Service
Bulletin 747–53–2272: At the applicable
intervals specified in table 4 of paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert Service
Bulletin 747–53A2367, Revision 5, dated July
8, 2014, in unrepaired areas, do external
detailed and LFEC inspections for cracks in
the skin; and do internal and external
detailed and HFEC inspections for cracks in
the skin and external doubler; in accordance
with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–53A2367,
Revision 5, dated July 8, 2014.
(j) Repetitive Post-Modification Inspections
for Airplane Groups 4 Through 6, and 9
Through 11 With External Doublers
For airplanes identified as Groups 4
through 6, and 9 through 11 in Boeing Alert
Service Bulletin 747–53A2367, Revision 5,
dated July 8, 2014, with external doublers
installed as specified in Boeing Alert Service
Bulletin 747–53A2367: Except as provided
by paragraph (m) of this AD, at the applicable
time specified in table 5 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 747–53A2367, Revision 5, dated July
8, 2014, do internal detailed and surface
HFEC inspections for cracks in the skin and
internal doubler along the edge fastener rows
of the modification; and do internal detailed
and surface HFEC inspections for cracks in
the skin or internal doubler along the edge
fastener rows of the modification; in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–53A2367, Revision 5, dated July 8, 2014.
In unrepaired areas, repeat the internal
detailed and surface HFEC inspections for
cracks in the skin or internal doubler along
the edge fastener rows of the modification
thereafter at the applicable interval specified
in paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 747–53A2367,
Revision 5, dated July 8, 2014.
(k) Repetitive Post-Modification Inspections
for Airplane Groups 12 and 13
For airplanes identified as Groups 12 and
13 in Boeing Alert Service Bulletin 747–
53A2367, Revision 5, dated July 8, 2014:
Except as provided by paragraph (m) of this
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AD, at the applicable time specified in table
6 of paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 747–53A2367,
Revision 5, dated July 8, 2014, do internal
detailed and surface HFEC inspections for
cracks in the skin and internal doubler along
the edge fastener rows of the modification, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–53A2367, Revision 5, dated July 8, 2014.
In unrepaired areas, repeat the internal
detailed and surface HFEC inspections for
cracks in the skin or internal doubler along
the edge fastener rows of the modification
thereafter at the applicable interval specified
in paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 747–53A2367,
Revision 5, dated July 8, 2014.
(l) Corrective Actions
If any cracking is found during any
inspection required by this AD: Before
further flight, repair the cracking using a
method approved in accordance with the
procedures specified in paragraph (n) of this
AD.
(m) Exception to Boeing Alert Service
Bulletin 747–53A2367, Revision 5, Dated
July 8, 2014
Where paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 747–53A2367,
Revision 5, dated July 8, 2014, specifies a
compliance time ‘‘after the Revision 5 date of
this service bulletin,’’ this AD requires
compliance within the specified compliance
time ‘‘after the effective date of this AD.’’
(n) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle 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 (o)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-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 the
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make those findings. For a repair
method to be approved, the repair must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(o) Related Information
(1) For more information about this AD,
contact Nathan Weigand, Aerospace
Engineer, Airframe Branch, ANM–120S,
FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, Washington
98057–3356; phone: 425–917–6428; fax: 425–
917–6590; email: nathan.p.weigand@faa.gov.
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Federal Register / Vol. 80, No. 86 / Tuesday, May 5, 2015 / Proposed Rules
(2) 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.
Issued in Renton, Washington, on April 28,
2015.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2015–10316 Filed 5–4–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF ENERGY
Federal Energy Regulatory
Commission
18 CFR Part 352
[Docket No. AD12–6–001]
Retrospective Analysis of Existing
Rules
Federal Energy Regulatory
Commission, DOE.
ACTION: Notice of staff memorandum.
AGENCY:
In this document, the
Commission is seeking public comment
on whether the existing regulations
concerning the Uniform Systems of
Accounts prescribed for oil pipeline
companies and hydropower prefiling
requirements, and a requirement
imposed in 2001 that Western public
and non-public utilities offer available
real-time electric energy capacity into
the markets and post the availability on
their Web sites and the WSPP Web site,
warrant a formal public review.
DATES: Comments are due by May 26,
2015.
SUMMARY:
Comments, identified by
docket number, may be filed in the
following ways:
• Electronic Filing through https://
www.ferc.gov. Documents created
electronically using word processing
software should be filed in native
applications or print-to-PDF format and
not in a scanned format.
• Mail/Hand Delivery: Those unable
to file electronically may mail or handdeliver comments to: Federal Energy
Regulatory Commission, Secretary of the
Commission, 888 First Street NE.,
Washington, DC 20426.
Instructions: For detailed instructions
on submitting comments and additional
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ADDRESSES:
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25633
information on the rulemaking process,
see the Comment Procedures Section of
this document.
Issued: April 23, 2015.
Kimberly D. Bose,
Secretary.
FOR FURTHER INFORMATION CONTACT:
[FR Doc. 2015–10310 Filed 5–4–15; 8:45 am]
Christy Walsh, Office of the General
Counsel, Federal Energy Regulatory
Commission, 888 First Street NE.,
Washington, DC 20426, 202–502–6523,
Christy.Walsh@ferc.gov.
BILLING CODE 6717–01–P
Take
notice that the Commission staff is
issuing a memorandum seeking public
comment on whether the existing
regulations concerning the Uniform
Systems of Accounts prescribed for oil
pipeline companies and hydropower
prefiling requirements, and a
requirement imposed in 2001 that
Western public and non-public utilities
offer available real-time electric energy
capacity into the markets and post the
availability on their Web sites and the
WSPP Web site, warrant a formal public
review. The memorandum is being
issued pursuant to the November 8,
2011 Plan for Retrospective Analysis of
Existing Rules prepared in response to
Executive Order 13579, which requested
independent regulatory agencies issue
plans for periodic retrospective analysis
of their existing regulations.
The Staff Memorandum is being
placed in the record in the abovereferenced administrative docket. The
Staff Memorandum will also be
available on the Commission’s Web site
at https://www.ferc.gov.
Comments on the Staff Memorandum
should be filed within 30 days of the
issuance of this document. The
Commission encourages electronic
submission of comments in lieu of
paper using the ‘‘eFiling’’ link at https://
www.ferc.gov. Persons unable to file
electronically should submit an original
of the comment to the Federal Energy
Regulatory Commission, 888 First Street
NE., Washington, DC 20426.
All filings in this docket are
accessible on-line at https://
www.ferc.gov, using the ‘‘eLibrary’’ link.
There is an ‘‘eSubscription’’ link on the
Web site that enables subscribers to
receive email notification when a
document is added to a subscribed
docket. For assistance with any FERC
Online service, please email
FERCOnlineSupport@ferc.gov, or call
(866) 208–3676 (toll free). For TTY, call
(202) 502–8659.
Questions regarding this document
should be directed to: Christy Walsh,
Office of the General Counsel, Federal
Energy Regulatory Commission, 888
First Street NE., Washington, DC 20426,
202–502–6523, Christy.Walsh@ferc.gov.
SUPPLEMENTARY INFORMATION:
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DEPARTMENT OF LABOR
Employment and Training
Administration
20 CFR Part 655
RIN 1205–AB70
Temporary Agricultural Employment of
H–2A Foreign Workers in the Herding
or Production of Livestock on the
Open Range in the United States;
Extension of Comment Period
Employment and Training
Administration, Labor.
ACTION: Proposed rule; extension of
comment period.
AGENCY:
The Department of Labor
(Department) issued a proposed rule in
the Federal Register of April 15, 2015
[FR Doc. 2015–08505], concerning
proposed amendments to its regulations
governing certification of the
employment of nonimmigrant workers
in temporary or seasonal agricultural
employment under the H–2A program
to codify certain procedures for
employers seeking to hire foreign
temporary agricultural workers for job
opportunities in sheepherding, goat
herding and production of livestock on
the open range. This notice extends the
comment period for 15 days, from May
15 to June 1, 2015. Multiple commenters
requested additional time to develop
their comments concerning the
proposed rulemaking. The Department
is therefore extending the comment
period in order to give all interested
persons the opportunity to comment
fully.
SUMMARY:
The comment period for the
proposed rule published on April 15,
2015 (80 FR 20300) is extended.
Interested persons are invited to submit
written comments on the proposed rule,
identified by RIN 1205–AB70, on or
before June 1, 2015
ADDRESSES: You may submit comments,
identified by Regulatory Information
Number (RIN) 1205–AB70, by any one
of the following methods:
• Federal e-Rulemaking Portal
www.regulations.gov. Follow the Web
site instructions for submitting
comments.
• Mail or Hand Delivery/Courier:
Please submit all written comments
(including disk and CD–ROM
DATES:
E:\FR\FM\05MYP1.SGM
05MYP1
Agencies
[Federal Register Volume 80, Number 86 (Tuesday, May 5, 2015)]
[Proposed Rules]
[Pages 25630-25633]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-10316]
[[Page 25630]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-1266; Directorate Identifier 2014-NM-151-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-
200B, 747-300, 747SR, and 747SP series airplanes. This proposed AD was
prompted by an evaluation by the design approval holder (DAH)
indicating that certain fuselage skin lap joints are subject to
widespread fatigue damage (WFD). This proposed AD would require
repetitive post-modification inspections for cracking of the skin or
internal doubler along the edge fastener rows of the modification, and
repair if necessary. We are proposing this AD to detect and correct
fatigue cracking in certain fuselage skin lap joints, which could
result in rapid depressurization of the airplane.
DATES: We must receive comments on this proposed AD by June 19, 2015.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed 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. It
is also available on the Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA 2015-1266.
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-2015-
1266; 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 proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will
be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Nathan Weigand, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 425-917-
6428; fax: 425-917-6590; email: nathan.p.weigand@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2015-1266;
Directorate Identifier 2014-NM-151-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
Structural fatigue damage is progressive. It begins as minute
cracks, and those cracks grow under the action of repeated stresses.
This can happen because of normal operational conditions and design
attributes, or because of isolated situations or incidents such as
material defects, poor fabrication quality, or corrosion pits, dings,
or scratches. Fatigue damage can occur locally, in small areas or
structural design details, or globally. Global fatigue damage is
general degradation of large areas of structure with similar structural
details and stress levels. Multiple-site damage is global damage that
occurs in a large structural element such as a single rivet line of a
lap splice joining two large skin panels. Global damage can also occur
in multiple elements such as adjacent frames or stringers. Multiple-
site-damage and multiple-element-damage cracks are typically too small
initially to be reliably detected with normal inspection methods.
Without intervention, these cracks will grow, and eventually compromise
the structural integrity of the airplane, in a condition known as WFD.
As an airplane ages, WFD will likely occur, and will certainly occur if
the airplane is operated long enough without any intervention.
The FAA's WFD final rule (75 FR 69746, November 15, 2010) became
effective on January 14, 2011. The WFD rule requires certain actions to
prevent structural failure due to WFD throughout the operational life
of certain existing transport category airplanes and all of these
airplanes that will be certificated in the future. For existing and
future airplanes subject to the WFD rule, the rule requires that DAHs
establish a limit of validity (LOV) of the engineering data that
support the structural maintenance program. Operators affected by the
WFD rule may not fly an airplane beyond its LOV, unless an extended LOV
is approved.
The WFD rule (75 FR 69746, November 15, 2010) does not require
identifying and developing maintenance actions if the DAHs can show
that such actions are not necessary to prevent WFD before the airplane
reaches the LOV. Many LOVs, however, do depend on accomplishment of
future maintenance actions. As stated in the WFD rule, any maintenance
actions necessary to reach the LOV will be mandated by airworthiness
directives through separate rulemaking actions.
In the context of WFD, this action is necessary to enable DAHs to
propose LOVs that allow operators the longest operational lives for
their airplanes, and still ensure that WFD will not occur. This
approach allows for an implementation strategy that provides
flexibility to DAHs in determining the timing of service information
development (with FAA approval), while providing operators with
certainty regarding the LOV applicable to their airplanes.
This proposed AD was prompted by an evaluation by the DAH
indicating
[[Page 25631]]
that certain fuselage skin lap joints are subject to WFD. We are
proposing this AD to detect and correct fatigue cracking in certain
fuselage skin lap joints, which could result in rapid depressurization
of the airplane.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Alert Service Bulletin 747-53A2367, Revision 5,
dated July 8, 2014. This service information describes procedures for
inspections for cracks in the skin and doublers along the edge fastener
rows of modifications in the fuselage, and repairs. Refer to this
service information for information on the procedures and compliance
times. This service information is reasonably available at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
1266. Or see ADDRESSES for other ways to access this service
information.
Related Rulemaking
AD 2010-10-05, Amendment 39-16284 (75 FR 27424, May 17, 2010)
requires, among other things, modification of certain lap joints in
fuselage sections 41 and 42. This proposed AD would require repetitive
post-modification inspections for cracking of the skin or internal
doubler along the edge fastener rows of the modification, and repair if
necessary.
FAA's Determination
We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of these same type
designs.
Proposed AD Requirements
This proposed AD would require accomplishing the actions specified
in the service information described previously, except as discussed
under ``Difference Between this Proposed AD and the Service
Information.''
Difference Between This Proposed AD and the Service Information
Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July
8, 2014, specifies to contact the manufacturer for instructions on how
to repair cracking, but this proposed AD would require repairing those
conditions in one of the following ways:
In accordance with a method that we approve; or
Using data that meet the certification basis of the
airplane, and that have been approved by the Boeing Commercial
Airplanes Organization Designation Authorization (ODA) whom we have
authorized to make those findings.
Costs of Compliance
We estimate that this proposed AD affects 50 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Post[dash]modification inspection... 124 work-hours x $85 $0 $10,540 per inspection $527,000 per inspection cycle.
per hour = $10,540 per cycle.
inspection cycle..
--------------------------------------------------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD.
According to the manufacturer, some of the costs of this proposed
AD may be covered under warranty, thereby reducing the cost impact on
affected individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the 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.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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):
The Boeing Company: Docket No. FAA-2014-1266; Directorate Identifier
2014-NM-151-AD.
(a) Comments Due Date
We must receive comments by June 19, 2015.
(b) Affected ADs
None.
[[Page 25632]]
(c) Applicability
This AD applies to The Boeing Company Model 747-100, 747-100B,
747-100B SUD, 747-200B, 747-300, 747SR, and 747SP series airplanes,
certificated in any category, as identified in Boeing Alert Service
Bulletin 747-53A2367, Revision 5, dated July 8, 2014.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by an evaluation by the design approval
holder (DAH) indicating that certain fuselage skin lap joints are
subject to widespread fatigue damage (WFD). We are issuing this AD
to detect and correct fatigue cracking in certain fuselage skin lap
joints, which could result in rapid depressurization of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Post-Modification Inspections for Airplane Groups 1
Through 3, 7, and 8
For airplanes identified as Groups 1 through 3, 7, and 8 in
Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8,
2014: Except as provided by paragraph (m) of this AD, at the
applicable time specified in table 3 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2367,
Revision 5, dated July 8, 2014, do internal detailed and surface
high frequency eddy current (HFEC) inspections for cracks in the
skin and internal doubler along the edge fastener rows of the
modification; in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8,
2014. In unrepaired areas, repeat the internal detailed and surface
HFEC inspections for cracks in the skin or internal doubler along
the edge fastener rows of the modification thereafter at the
applicable intervals specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8,
2014.
(h) Initial Post-Modification Inspections for Airplane Groups 4 Through
6, and 9 Through 11
For airplanes identified as Groups 4 through 6, and 9 through 11
in Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July
8, 2014, with external doublers installed as specified in Boeing
Service Bulletin 747-53-2272: Except as provided by paragraph (m) of
this AD, at the applicable time specified in table 4 of paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2367,
Revision 5, dated July 8, 2014, do external detailed, low frequency
eddy current (LFEC), and HFEC inspections for cracks in the skin and
external doubler, in accordance with the Accomplishment Instructions
of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July
8, 2014.
(i) Repetitive Post-Modification Inspections for Airplane Groups 4
Through 6, and 9 through 11
For airplanes with no crack findings during the inspections
required by paragraph (h) of this AD: Do the applicable actions
required by paragraphs (i)(1) and (i)(2) of this AD.
(1) For airplanes with less than 15,000 flight cycles since
stringer 6 external doublers were installed as specified in Boeing
Service Bulletin 747-53-2272: At the applicable intervals specified
in table 4 of paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014, in
unrepaired areas, repeat the external detailed and LFEC inspections
for cracks in the skin, and the external detailed and HFEC
inspections for cracks in the external doubler, in accordance with
the Accomplishment Instructions of Boeing Alert Service Bulletin
747-53A2367, Revision 5, dated July 8, 2014.
(2) For airplanes with 15,000 or more flight cycles since the
stringer 6 external doublers were installed as specified in Boeing
Service Bulletin 747-53-2272: At the applicable intervals specified
in table 4 of paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014, in
unrepaired areas, do external detailed and LFEC inspections for
cracks in the skin; and do internal and external detailed and HFEC
inspections for cracks in the skin and external doubler; in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014.
(j) Repetitive Post-Modification Inspections for Airplane Groups 4
Through 6, and 9 Through 11 With External Doublers
For airplanes identified as Groups 4 through 6, and 9 through 11
in Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July
8, 2014, with external doublers installed as specified in Boeing
Alert Service Bulletin 747-53A2367: Except as provided by paragraph
(m) of this AD, at the applicable time specified in table 5 of
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
747-53A2367, Revision 5, dated July 8, 2014, do internal detailed
and surface HFEC inspections for cracks in the skin and internal
doubler along the edge fastener rows of the modification; and do
internal detailed and surface HFEC inspections for cracks in the
skin or internal doubler along the edge fastener rows of the
modification; in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8,
2014. In unrepaired areas, repeat the internal detailed and surface
HFEC inspections for cracks in the skin or internal doubler along
the edge fastener rows of the modification thereafter at the
applicable interval specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8,
2014.
(k) Repetitive Post-Modification Inspections for Airplane Groups 12 and
13
For airplanes identified as Groups 12 and 13 in Boeing Alert
Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014: Except
as provided by paragraph (m) of this AD, at the applicable time
specified in table 6 of paragraph 1.E., ``Compliance,'' of Boeing
Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014,
do internal detailed and surface HFEC inspections for cracks in the
skin and internal doubler along the edge fastener rows of the
modification, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8,
2014. In unrepaired areas, repeat the internal detailed and surface
HFEC inspections for cracks in the skin or internal doubler along
the edge fastener rows of the modification thereafter at the
applicable interval specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8,
2014.
(l) Corrective Actions
If any cracking is found during any inspection required by this
AD: Before further flight, repair the cracking using a method
approved in accordance with the procedures specified in paragraph
(n) of this AD.
(m) Exception to Boeing Alert Service Bulletin 747-53A2367, Revision 5,
Dated July 8, 2014
Where paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 747-53A2367, Revision 5, dated July 8, 2014, specifies a
compliance time ``after the Revision 5 date of this service
bulletin,'' this AD requires compliance within the specified
compliance time ``after the effective date of this AD.''
(n) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle 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 (o)(1) of this AD.
Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD if it is approved the Boeing
Commercial Airplanes Organization Designation Authorization (ODA)
that has been authorized by the Manager, Seattle ACO, to make those
findings. For a repair method to be approved, the repair must meet
the certification basis of the airplane, and the approval must
specifically refer to this AD.
(o) Related Information
(1) For more information about this AD, contact Nathan Weigand,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, Washington
98057-3356; phone: 425-917-6428; fax: 425-917-6590; email:
nathan.p.weigand@faa.gov.
[[Page 25633]]
(2) 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.
Issued in Renton, Washington, on April 28, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-10316 Filed 5-4-15; 8:45 am]
BILLING CODE 4910-13-P