Airworthiness Directives; The Boeing Company Airplanes, 36255-36258 [2015-15400]
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Federal Register / Vol. 80, No. 121 / Wednesday, June 24, 2015 / Proposed Rules
Could we amend the scope of a rule to
clarify its applicability or to reduce the
burden, while remaining faithful to
statutory intent? If so, specify which
regulation(s) should be clarified.
• Burden on small insured
institutions. The Board has a particular
interest in minimizing burden on small
insured credit unions (those with less
than $50 million in assets). NCUA
solicits comment on whether any
regulations within these categories
should be continued without change,
amended or rescinded in order to
36255
minimize any significant economic
impact the regulations may have on a
substantial number of small federally
insured credit unions.
V.A.—REGULATIONS ABOUT WHICH BURDEN REDUCTION RECOMMENDATIONS ARE REQUESTED CURRENTLY
Corporate Credit Unions .................
Directors, Officers, and Employees
Money Laundering ..........................
Corporate credit unions .........................................................................
Loans and lines of credit to officials ......................................................
Reimbursement, insurance, and indemnification of officials and employees.
Retirement benefits for employees ........................................................
Management officials interlock ..............................................................
Fidelity bond and insurance coverage ..................................................
General authorities and duties of federal credit union directors ...........
Golden parachutes and indemnification payments ...............................
Report of crimes or suspected crimes ..................................................
Bank Secrecy Act ..................................................................................
12 CFR 704.
12 CFR 701.21(d).
12 CFR 701.33.
12
12
12
12
12
12
12
CFR
CFR
CFR
CFR
CFR
CFR
CFR
701.19.
711.
713.
701.4.
750.
748.1.
748.2.
V.B.—CATEGORIES AND REGULATIONS ABOUT WHICH NCUA WILL SEEK COMMENT LATER
Rules of Procedure .........................
Safety and Soundness ....................
Liquidation (involuntary and voluntary) ..................................................
Uniform rules of practice and procedure ...............................................
Local rules of practice and procedure ...................................................
Lending ..................................................................................................
Investments ............................................................................................
Supervisory committee audit .................................................................
Security programs ..................................................................................
Guidelines for safeguarding member information and responding to
unauthorized access to member information.
Records preservation program and record retention appendix ............
Appraisals ..............................................................................................
Examination ...........................................................................................
Liquidity and contingency funding plans ...............................................
Regulations codified elsewhere in NCUA’s regulations as applying to
federal credit unions that also apply to federally insured state-chartered credit unions.
By the National Credit Union
Administration Board on June 18, 2015.
Gerard Poliquin,
Secretary of the Board.
[FR Doc. 2015–15472 Filed 6–23–15; 8:45 am]
BILLING CODE 7535–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–1984; Directorate
Identifier 2015–NM–022–AD]
RIN 2120–AA64
tkelley on DSK3SPTVN1PROD with PROPOSALS
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2005–01–
09, which applies to certain The Boeing
SUMMARY:
VerDate Sep<11>2014
16:23 Jun 23, 2015
Jkt 235001
Company Model 747–100, 747–100B,
747–100B SUD, 747–200B, 747–200C,
747–200F, 747–300, 747–400, 747–
400D, 747–400F, and 747SR series
airplanes. AD 2005–01–09 requires a
one-time detailed inspection for
discrepancies of the frame web and
inner chords on the forward edge frame
of the number 5 main entry door cutout,
and corrective action if necessary. Since
we issued AD 2005–01–09, additional
cracking was found in the same area
after completion of the one-time
detailed inspection. This proposed AD
would add repetitive high frequency
eddy current inspections for cracking of
the frame inner chords (forward and
aft), and corrective action if necessary.
We are proposing this AD to detect and
correct discrepancies of the frame web
and inner chords, which could result in
cracking, subsequent severing of the
frame, and consequent rapid
depressurization of the airplane.
DATES: We must receive comments on
this proposed AD by August 10, 2015.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
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CFR
CFR
CFR
CFR
CFR
CFR
CFR
CFR
709 and 710.
747, subpart A.
747, subpart B.
701.21.
703.
715.
748.0.
748, Appendices A and B.
12
12
12
12
12
CFR
CFR
CFR
CFR
CFR
749.
722.
741.1.
741.12.
741, subpart B.
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,
E:\FR\FM\24JNP1.SGM
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36256
Federal Register / Vol. 80, No. 121 / Wednesday, June 24, 2015 / Proposed Rules
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–
1984.
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–
1984; 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, WA
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 proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2015–1984; Directorate Identifier
2015–NM–022–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.
tkelley on DSK3SPTVN1PROD with PROPOSALS
Discussion
On December 27, 2004, we issued AD
2005–01–09, Amendment 39–13933 (70
FR 1340, January 7, 2005), for certain
The Boeing Company Model 747–100,
747–100B, 747–100B SUD, 747–200B,
VerDate Sep<11>2014
16:23 Jun 23, 2015
Jkt 235001
747–200C, 747–200F, 747–300, 747–
400, 747–400D, 747–400F, and 747SR
series airplanes. AD 2005–01–09
requires a one-time inspection for
discrepancies of the frame web and
inner chords on the forward edge frame
of the number 5 main entry door cutout,
and corrective action if necessary. AD
2005–01–09 resulted from a report of
cracking of the frame web and inner
chords on the forward edge frame of the
number 5 main entry door. We issued
AD 2005–01–09 to find and fix
discrepancies of the frame web and
inner chords, which could result in
cracking, subsequent severing of the
frame, and consequent rapid
depressurization of the airplane.
multiple reports of cracking outside of
the previous inspection areas and a
report of a crack that initiated at the aft
edge of the inner chord rather than
initiating at a fastener location. We
issued AD 2013–17–08 to detect and
correct such cracks, which could cause
damage to the adjacent body structure
and could result in depressurization of
the airplane in flight.
Actions Since AD 2005–01–09,
Amendment 39–13933 (70 FR 1340,
January 7, 2005), Was Issued
Since we issued AD 2005–01–09,
Amendment 39–13933 (70 FR 1340,
January 7, 2005), additional cracking
was found in the same area after
completion of the one-time detailed
inspection required by AD 2005–01–09.
Proposed AD Requirements
Related Service Information Under 1
CFR Part 51
We reviewed and approved Boeing
Alert Service Bulletin 747–53A2494,
Revision 1, dated January 9, 2015. The
service information describes
procedures for a one-time detailed
inspection and repetitive surface high
frequency eddy current inspections of
the Station 2231 frame inner chords
(forward and aft), and repair of
discrepancies. 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 NPRM.
Related AD
On August 16, 2013, we issued AD
2013–17–08, Amendment 39–17572 (78
FR 57053, September 17, 2013), for
certain The Boeing Company Model
747–100, 747–100B, 747–100B SUD,
747–200B, 747–200C, 747–200F, 747–
300, 747–400, 747–400D, 747–400F, and
747SR series airplanes. AD 2013–17–08
requires repetitive inspections to find
cracking of the web, strap, inner chords,
inner chord angle of the forward edge
frame of the number 5 main entry door
cutouts; the frame segment between
stringers 16 and 31; repair if necessary;
and repetitive inspections for cracking
of repairs. AD 2013–17–08 resulted from
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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 the same
type design.
Although this proposed AD does not
explicitly restate the requirements of AD
2005–01–09, Amendment 39–13933 (70
FR 1340, January 7, 2005), this proposed
AD would retain all of the requirements.
Those requirements are referenced in
the service information identified
previously, which, in turn, is referenced
in paragraph (g) of this proposed AD.
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 Bulletin.’’ Refer to this
service information for information on
the procedures and compliance times.
Difference Between This Proposed AD
and the Service Bulletin
Although Boeing Alert Service
Bulletin 747–53A2494, Revision 1,
dated January 9, 2015, specifies that
operators may contact the manufacturer
for disposition of certain repair
conditions, 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 174 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
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Federal Register / Vol. 80, No. 121 / Wednesday, June 24, 2015 / Proposed Rules
36257
ESTIMATED COSTS
Action
Labor cost
Detailed inspection ........
HFEC inspections .........
2 work-hours × $85 per hour = $170 .................
4 work-hours × $85 per hour = $340 .................
We have received no definitive data
that would enable us to provide a cost
estimate for the on-condition actions
specified in this proposed AD.
Authority for This Rulemaking
Parts cost
Cost per product
$0
0
$170 .............................
$340 per inspection
cycle.
$29,580.
$59,160 per inspection
cycle.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
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.
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
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)
2005–01–09, Amendment 39–13933 (70
FR 1340, January 7, 2005), and adding
the following new AD:
■
The Boeing Company: Docket No. FAA–
2015–1984; Directorate Identifier 2015–
NM–022AD.
(a) Comments Due Date
Regulatory Findings
tkelley on DSK3SPTVN1PROD with PROPOSALS
Cost on U.S. operators
The FAA must receive comments on this
AD action by August 10, 2015.
We have 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 that the 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.
(b) Affected ADs
VerDate Sep<11>2014
16:23 Jun 23, 2015
Jkt 235001
This AD replaces AD 2005–01–09,
Amendment 39–13933 (70 FR 1340, January
7, 2005).
(c) Applicability
This AD applies to The Boeing Company
Model 747–100, –100B, 747–100B SUD, 747–
200B, 747–200C, 747–200F, 747–300, 747–
400, 747–400D, 747–400F, and 747SR series
airplanes; certificated in any category; as
identified in Boeing Alert Service Bulletin
747–53A2494, Revision 1, dated January 9,
2015.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of
additional cracking found in the same area
after completion of the one-time detailed
inspection. We are issuing this AD to detect
and correct discrepancies of the frame web
and inner chords, which could result in
cracking, subsequent severing of the frame,
and consequent rapid depressurization of the
airplane.
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Fmt 4702
Sfmt 4702
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspections
Do the applicable actions specified in
paragraphs (g)(1), (g)(2), (g)(3), and (g)(4) of
this AD, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–53A2494, Revision 1,
dated January 9, 2015, except as required by
paragraph (h)(2) of this AD.
(1) At the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 747–53A2494,
Revision 1, dated January 9, 2015, do a
detailed inspection for nicks, scratches, or
gouges of the Station 2231 frame inner
chords, forward and aft, at stringer 26 at the
edge and side of the inner chords.
(2) At the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 747–53A2494,
Revision 1, dated January 9, 2015, except as
required by paragraph (h)(1) of this AD: Do
a surface high frequency eddy current (HFEC)
inspection for cracks of the frame inner
chords, forward and aft.
(3) Based on the findings from the
inspections specified in paragraphs (g)(1) and
(g)(2) of this AD, do all applicable corrective
actions, before further flight.
(4) Repeat the HFEC inspection specified
in paragraph (g)(2) of this AD at the
applicable time specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 747–53A2494, Revision 1, dated
January 9, 2015.
(h) Exceptions to Service Bulletin
Specifications
(1) Where Boeing Alert Service Bulletin
747–53A2494, Revision 1, dated January 9,
2015, specifies a compliance time ‘‘after the
release of Revision 1 of this service bulletin,’’
this AD requires compliance within the
specified compliance time after the effective
date of this AD.
(2) Where Boeing Alert Service Bulletin
747–53A2494, Revision 1, dated January 9,
2015, specifies to contact Boeing for repair
instructions: Before further flight, repair
using a method approved in accordance with
the procedures specified in paragraph (j) of
this AD.
(i) Credit for Previous Actions
(1) This paragraph provides credit for
inspections required by paragraph (g)(1) of
this AD, if those inspections were performed
before the effective date of this AD using
Boeing Alert Service Bulletin 747–53A2494,
dated September 18, 2003, which was
incorporated by reference in AD 2005–01–09,
Amendment 39–13933 (70 FR 1340, January
7, 2005).
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Federal Register / Vol. 80, No. 121 / Wednesday, June 24, 2015 / Proposed Rules
(2) This paragraph provides credit for
inspections required by paragraphs (g)(1) and
(g)(2) of this AD, if those inspections were
performed before the effective date of this AD
using Boeing Alert Service Bulletin 747–
53A2450, Revision 7, dated November 2,
2011, which was incorporated by reference in
AD 2013–17–08, Amendment 39–17572 (78
FR 57053, September 17, 2013).
(j) 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 (k)(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 by 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.
(4) AMOCs approved for AD 2005–01–09,
Amendment 39–13933 (70 FR 1340, January
7, 2005), are approved as AMOCs for the
corresponding provisions of paragraph (g)(1)
of this AD.
tkelley on DSK3SPTVN1PROD with PROPOSALS
(k) 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, WA 98057–
3356; phone: 425–917–6428; fax: 425–917–
6590; email: nathan.p.weigand@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, 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, Washington.
For information on the availability of this
material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on June 12,
2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2015–15400 Filed 6–23–15; 8:45 am]
BILLING CODE 4910–13–P
VerDate Sep<11>2014
16:23 Jun 23, 2015
Jkt 235001
[Docket No. FAA–2015–1983; Directorate
Identifier 2015–NM–020–AD]
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–
1983.
RIN 2120–AA64
Examining the AD Docket
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
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 all The
Boeing Company Model 737–100, –200,
–200C, –300, –400, and –500 series
airplanes. This proposed AD was
prompted by a report of a crack of the
forward leg of the left front spar lower
chord and cracks on the lower wing skin
at three fastener holes common to the
nacelle outboard side load fitting. This
proposed AD would require repetitive
inspections for cracks on the front spar
lower chord, inspar skin, and wing skin,
and corrective action if necessary. We
are proposing this AD to detect and
correct fatigue cracking of the forward
leg of the front spar lower chord, inspar
skin, and wing skin common to the
nacelle outboard side load fitting, which
could adversely affect the structural
integrity of the wing.
DATES: We must receive comments on
this proposed AD by August 10, 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.,
SUMMARY:
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You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
1983; 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:
Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA
98057–3356; phone: 425–917–6450; fax:
425–917–6590; email: alan.pohl@
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–
2015–1983; Directorate Identifier 2015–
NM–020–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
We received a report of a crack on the
forward leg of the left front spar lower
chord at wing buttock line (WBL) 177.
The front spar lower chord was
removed, repaired, and reinstalled.
Upon additional inspection of the
repaired spar chord installation, cracks
were also discovered on the lower wing
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]]>Agencies
[Federal Register Volume 80, Number 121 (Wednesday, June 24, 2015)]
[Proposed Rules]
[Pages 36255-36258]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-15400]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-1984; Directorate Identifier 2015-NM-022-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 supersede Airworthiness Directive (AD) 2005-01-
09, which applies to certain The Boeing Company Model 747-100, 747-
100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400,
747-400D, 747-400F, and 747SR series airplanes. AD 2005-01-09 requires
a one-time detailed inspection for discrepancies of the frame web and
inner chords on the forward edge frame of the number 5 main entry door
cutout, and corrective action if necessary. Since we issued AD 2005-01-
09, additional cracking was found in the same area after completion of
the one-time detailed inspection. This proposed AD would add repetitive
high frequency eddy current inspections for cracking of the frame inner
chords (forward and aft), and corrective action if necessary. We are
proposing this AD to detect and correct discrepancies of the frame web
and inner chords, which could result in cracking, subsequent severing
of the frame, and consequent rapid depressurization of the airplane.
DATES: We must receive comments on this proposed AD by August 10, 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,
[[Page 36256]]
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-
1984.
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-
1984; 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, WA 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 proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-1984;
Directorate Identifier 2015-NM-022-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
On December 27, 2004, we issued AD 2005-01-09, Amendment 39-13933
(70 FR 1340, January 7, 2005), for certain The Boeing Company Model
747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300,
747-400, 747-400D, 747-400F, and 747SR series airplanes. AD 2005-01-09
requires a one-time inspection for discrepancies of the frame web and
inner chords on the forward edge frame of the number 5 main entry door
cutout, and corrective action if necessary. AD 2005-01-09 resulted from
a report of cracking of the frame web and inner chords on the forward
edge frame of the number 5 main entry door. We issued AD 2005-01-09 to
find and fix discrepancies of the frame web and inner chords, which
could result in cracking, subsequent severing of the frame, and
consequent rapid depressurization of the airplane.
Actions Since AD 2005-01-09, Amendment 39-13933 (70 FR 1340, January 7,
2005), Was Issued
Since we issued AD 2005-01-09, Amendment 39-13933 (70 FR 1340,
January 7, 2005), additional cracking was found in the same area after
completion of the one-time detailed inspection required by AD 2005-01-
09.
Related Service Information Under 1 CFR Part 51
We reviewed and approved Boeing Alert Service Bulletin 747-53A2494,
Revision 1, dated January 9, 2015. The service information describes
procedures for a one-time detailed inspection and repetitive surface
high frequency eddy current inspections of the Station 2231 frame inner
chords (forward and aft), and repair of discrepancies. 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 NPRM.
Related AD
On August 16, 2013, we issued AD 2013-17-08, Amendment 39-17572 (78
FR 57053, September 17, 2013), for certain The Boeing Company Model
747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300,
747-400, 747-400D, 747-400F, and 747SR series airplanes. AD 2013-17-08
requires repetitive inspections to find cracking of the web, strap,
inner chords, inner chord angle of the forward edge frame of the number
5 main entry door cutouts; the frame segment between stringers 16 and
31; repair if necessary; and repetitive inspections for cracking of
repairs. AD 2013-17-08 resulted from multiple reports of cracking
outside of the previous inspection areas and a report of a crack that
initiated at the aft edge of the inner chord rather than initiating at
a fastener location. We issued AD 2013-17-08 to detect and correct such
cracks, which could cause damage to the adjacent body structure and
could result in depressurization of the airplane in flight.
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 the same type design.
Proposed AD Requirements
Although this proposed AD does not explicitly restate the
requirements of AD 2005-01-09, Amendment 39-13933 (70 FR 1340, January
7, 2005), this proposed AD would retain all of the requirements. Those
requirements are referenced in the service information identified
previously, which, in turn, is referenced in paragraph (g) of this
proposed AD. 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
Bulletin.'' Refer to this service information for information on the
procedures and compliance times.
Difference Between This Proposed AD and the Service Bulletin
Although Boeing Alert Service Bulletin 747-53A2494, Revision 1,
dated January 9, 2015, specifies that operators may contact the
manufacturer for disposition of certain repair conditions, 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 174 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
[[Page 36257]]
Estimated Costs
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Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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Detailed inspection............ 2 work-hours x $85 per $0 $170.............. $29,580.
hour = $170.
HFEC inspections............... 4 work-hours x $85 per 0 $340 per $59,160 per
hour = $340. inspection cycle. inspection cycle.
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We have received no definitive data that would enable us to provide
a cost estimate for the on-condition actions specified in this proposed
AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this 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 that the 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 removing Airworthiness Directive (AD)
2005-01-09, Amendment 39-13933 (70 FR 1340, January 7, 2005), and
adding the following new AD:
The Boeing Company: Docket No. FAA-2015-1984; Directorate Identifier
2015-NM-022AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by August 10,
2015.
(b) Affected ADs
This AD replaces AD 2005-01-09, Amendment 39-13933 (70 FR 1340,
January 7, 2005).
(c) Applicability
This AD applies to The Boeing Company Model 747-100, -100B, 747-
100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D,
747-400F, and 747SR series airplanes; certificated in any category;
as identified in Boeing Alert Service Bulletin 747-53A2494, Revision
1, dated January 9, 2015.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of additional cracking found in
the same area after completion of the one-time detailed inspection.
We are issuing this AD to detect and correct discrepancies of the
frame web and inner chords, which could result in cracking,
subsequent severing of the frame, and consequent rapid
depressurization of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspections
Do the applicable actions specified in paragraphs (g)(1),
(g)(2), (g)(3), and (g)(4) of this AD, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2494, Revision 1, dated January 9, 2015, except as required by
paragraph (h)(2) of this AD.
(1) At the applicable time specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2494,
Revision 1, dated January 9, 2015, do a detailed inspection for
nicks, scratches, or gouges of the Station 2231 frame inner chords,
forward and aft, at stringer 26 at the edge and side of the inner
chords.
(2) At the applicable time specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2494,
Revision 1, dated January 9, 2015, except as required by paragraph
(h)(1) of this AD: Do a surface high frequency eddy current (HFEC)
inspection for cracks of the frame inner chords, forward and aft.
(3) Based on the findings from the inspections specified in
paragraphs (g)(1) and (g)(2) of this AD, do all applicable
corrective actions, before further flight.
(4) Repeat the HFEC inspection specified in paragraph (g)(2) of
this AD at the applicable time specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2494,
Revision 1, dated January 9, 2015.
(h) Exceptions to Service Bulletin Specifications
(1) Where Boeing Alert Service Bulletin 747-53A2494, Revision 1,
dated January 9, 2015, specifies a compliance time ``after the
release of Revision 1 of this service bulletin,'' this AD requires
compliance within the specified compliance time after the effective
date of this AD.
(2) Where Boeing Alert Service Bulletin 747-53A2494, Revision 1,
dated January 9, 2015, specifies to contact Boeing for repair
instructions: Before further flight, repair using a method approved
in accordance with the procedures specified in paragraph (j) of this
AD.
(i) Credit for Previous Actions
(1) This paragraph provides credit for inspections required by
paragraph (g)(1) of this AD, if those inspections were performed
before the effective date of this AD using Boeing Alert Service
Bulletin 747-53A2494, dated September 18, 2003, which was
incorporated by reference in AD 2005-01-09, Amendment 39-13933 (70
FR 1340, January 7, 2005).
[[Page 36258]]
(2) This paragraph provides credit for inspections required by
paragraphs (g)(1) and (g)(2) of this AD, if those inspections were
performed before the effective date of this AD using Boeing Alert
Service Bulletin 747-53A2450, Revision 7, dated November 2, 2011,
which was incorporated by reference in AD 2013-17-08, Amendment 39-
17572 (78 FR 57053, September 17, 2013).
(j) 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 (k)(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 by 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.
(4) AMOCs approved for AD 2005-01-09, Amendment 39-13933 (70 FR
1340, January 7, 2005), are approved as AMOCs for the corresponding
provisions of paragraph (g)(1) of this AD.
(k) 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, WA 98057-3356;
phone: 425-917-6428; fax: 425-917-6590; email:
nathan.p.weigand@faa.gov.
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, 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, Washington. For information on the availability
of this material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on June 12, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-15400 Filed 6-23-15; 8:45 am]
BILLING CODE 4910-13-P
