Airworthiness Directives; Airbus Airplanes, 18727-18730 [2018-08654]
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18727
Rules and Regulations
Federal Register
Vol. 83, No. 83
Monday, April 30, 2018
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents.
FEDERAL HOUSING FINANCE
AGENCY
12 CFR Part 1238
[No. 2018–N–04]
Orders: Reporting by Regulated
Entities of Stress Testing Results as of
December 31, 2017; Summary
Instructions and Guidance
Federal Housing Finance
Agency.
ACTION: Orders.
AGENCY:
In this document, the Federal
Housing Finance Agency (FHFA)
provides notice that it issued Orders,
dated March 1, 2018, with respect to
stress test reporting as of December 31,
2017, under section 165(i)(2) of the
Dodd-Frank Wall Street Reform and
Consumer Protection Act (Dodd-Frank
Act). Summary Instructions and
Guidance accompanied the Orders to
provide testing scenarios.
DATES: Effective April 30, 2018. Each
Order is applicable March 1, 2018.
FOR FURTHER INFORMATION CONTACT: John
Williams, Manager, Financial
Performance Reporting, Enterprise
Financial Reporting Section, (202) 649–
3159, John.Williams@fhfa.gov; Stefan
Szilagyi, Examination Manager, Office
of Risk Modeling, Division of Bank
Regulation (202) 649–3515,
Stefan.Szilagyi@fhfa.gov; Karen Heidel,
Assistant General Counsel, Office of
General Counsel, (202) 649–3073,
Karen.Heidel@fhfa.gov; or Mark D.
Laponsky, Deputy General Counsel,
Office of General Counsel, (202) 649–
3054, Mark.Laponsky@fhfa.gov. The
telephone number for the
Telecommunications Device for the
Hearing Impaired is (800) 877–8339.
SUPPLEMENTARY INFORMATION:
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SUMMARY:
I. Background
FHFA is responsible for ensuring that
the regulated entities operate in a safe
and sound manner, including the
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maintenance of adequate capital and
internal controls, that their operations
and activities foster liquid, efficient,
competitive, and resilient national
housing finance markets, and that they
carry out their public policy missions
through authorized activities. See 12
U.S.C. 4513. These Orders are being
issued under 12 U.S.C. 4516(a), which
authorizes the Director of FHFA to
require by Order that the regulated
entities submit regular or special reports
to FHFA and establishes remedies and
procedures for failing to make reports
required by Order. The Orders, through
the accompanying Summary
Instructions and Guidance, prescribe for
the regulated entities the scenarios to be
used for stress testing. The Summary
Instructions and Guidance also provides
to the regulated entities advice
concerning the content and format of
reports required by the Orders and the
rule.
II. Orders, Summary Instructions and
Guidance
For the convenience of the affected
parties and the public, the text of the
Orders follows below in its entirety. The
Orders and Summary Instructions and
Guidance are also available for public
inspection and copying at the Federal
Housing Finance Agency’s Freedom of
Information Act (FOIA) Reading Room
at https://www.fhfa.gov/AboutUs/
FOIAPrivacy/Pages/Reading-Room.aspx
by clicking on ‘‘Click here to view
Orders’’ under the Final Opinions and
Orders heading. You may also access
these documents at https://www.fhfa.gov/
SupervisionRegulation/
DoddFrankActStressTests.
The text of the Orders is as follows:
Federal Housing Finance Agency
Order Nos. 2018–OR–B–1, 2018–OR–
FNMA–1, and 2018–FHLMC–1
Reporting by Regulated Entities of Stress
Testing Results as of December 31, 2017
Whereas, section 165(i)(2) of the
Dodd-Frank Wall Street Reform and
Consumer Protection Act (‘‘Dodd-Frank
Act’’) requires certain financial
companies with total consolidated
assets of more than $10 billion, and
which are regulated by a primary
Federal financial regulatory agency, to
conduct annual stress tests to determine
whether the companies have the capital
necessary to absorb losses as a result of
adverse economic conditions;
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Whereas, FHFA’s rule implementing
section 165(i)(2) of the Dodd-Frank Act
is codified as 12 CFR 1238 and requires
that ‘‘[e]ach regulated entity must file a
report in the manner and form
established by FHFA.’’ 12 CFR
1238.5(b);
Whereas, The Board of Governors of
the Federal Reserve System issued stress
testing scenarios on February 1, 2018;
and
Whereas, section 1314 of the Safety
and Soundness Act, 12 U.S.C. 4514(a)
authorizes the Director of FHFA to
require regulated entities, by general or
specific order, to submit such reports on
their management, activities, and
operation as the Director considers
appropriate.
Now therefore, it is hereby Ordered as
follows:
Each regulated entity shall report to
FHFA and to the Board of Governors of
the Federal Reserve System the results
of the stress testing as required by 12
CFR 1238, in the form and with the
content described therein and in the
Summary Instructions and Guidance,
with Appendices 1 through 12 thereto,
accompanying this Order and dated
March 1, 2018.
It is so ordered, this the 1st day of
March, 2018.
This Order is effective immediately.
Signed at Washington, DC, this 1st day of
March, 2018.
Melvin L. Watt, Director,
Federal Housing Finance Agency.
Dated: April 23, 2018.
Melvin L. Watt,
Director, Federal Housing Finance Agency.
[FR Doc. 2018–09072 Filed 4–27–18; 8:45 am]
BILLING CODE 8070–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0305; Product
Identifier 2013–NM–226–AD; Amendment
39–19259; AD 2018–09–03]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
AGENCY:
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18728
Federal Register / Vol. 83, No. 83 / Monday, April 30, 2018 / Rules and Regulations
Final rule; request for
comments.
ACTION:
We are superseding
Airworthiness Directive (AD) 2009–11–
08, which applied to certain Airbus
Model A330–202, –223, –243, –301,
–322, and –342 airplanes. AD 2009–11–
08 required repetitive special detailed
(high frequency eddy current)
inspections to detect cracking of the
keel beam fitting horizontal flange edge
at a certain frame (FR) on the left- and
right-hand sides of the fuselage, and
repair if necessary. This AD was
prompted by a new fatigue and damage
tolerance evaluation that concluded the
current inspection thresholds and
intervals had to be modified. This AD
requires contacting the FAA to obtain
instructions for addressing the unsafe
condition on these products, and doing
the actions specified in those
instructions. We are issuing this AD to
address the unsafe condition on these
products.
DATES: This AD becomes effective May
15, 2018.
We must receive comments on this
AD by June 14, 2018.
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: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE, Washington, DC, between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays.
sradovich on DSK3GMQ082PROD with RULES
SUMMARY:
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–2018–
0305; or in person at the Docket
Operations office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone:
800–647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
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International Section, Transport
Standards Branch, FAA, 2200 South
216th Street, Des Moines, WA 98198;
telephone and fax: 206–231–3229.
SUPPLEMENTARY INFORMATION:
Discussion
We issued AD 2009–11–08,
Amendment 39–15918 (74 FR 25404,
May 28, 2009) (‘‘AD 2009–11–08’’),
which applied to certain Airbus Model
A330–202, –223, –243, –301, –322, and
–342 airplanes. AD 2009–11–08 was
prompted by reports of cracks on the
left- and right-hand sides between the
crossing area of the keel angle fitting
and the front spar of the center wing
box. AD 2009–11–08 required a special
detailed (high frequency eddy current)
inspection to detect cracking of the keel
beam fitting horizontal flange edge at
FR40 on the left- and right-hand sides
of the fuselage, and repair if necessary.
We issued AD 2009–11–08 to detect and
correct cracking on the left- and righthand sides, between the crossing area of
the keel angle fitting and the front spar
of the center wing box, which if not
corrected, could affect the structural
integrity of the airplane.
Since we issued AD 2009–11–08, a
new fatigue and damage tolerance
evaluation was conducted by the
manufacturer. It was concluded that,
due to airplane utilization, the current
inspection thresholds and intervals had
to be modified.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2013–0247,
dated October 10, 2013 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Airbus Model A330–202,
–223, –243, –301, –322, and –342
airplanes. The MCAI states:
During the A330 and A340 aeroplane
fatigue test, cracks appeared on the right and
left sides between the crossing area of the
keel angle fitting and the front spar of the
Centre Wing Box (CWB). Several
modifications were introduced in the fleet in
the area of frame (FR) 40 keel angle assembly
in order to prevent these cracks. However,
the new design caused interference between
one fastener and the keel angle which was
corrected by further local reprofiling of the
keel angle horizontal flange.
This condition, if not detected and
corrected, could result in reduced structural
integrity of the area.
Prompted by these findings, EASA issued
AD 2008–0213 [which corresponds to FAA
AD 2009–11–08] to require accomplishment
of repetitive special detailed inspection on
the horizontal flange of the keel beam in the
area of first fastener hole aft of FR40 and,
depending on findings, accomplishment of a
repair.
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Since that [EASA] AD was issued, a new
fatigue and damage tolerance evaluation was
conducted by Airbus. It was concluded that,
due to aeroplane utilisation, the current
inspection thresholds and intervals had to be
modified.
For the reason described above, this
[EASA] AD retains the requirements of EASA
AD 2008–0213, which is superseded, and
redefines the thresholds and intervals.
You may examine the MCAI on the
internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2018–0305.
FAA’s Determination and Requirements
of This AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI. We are issuing this AD because
we evaluated all pertinent information
and determined the unsafe condition
exists and is likely to exist or develop
on other products of the same type
design.
FAA’s Determination of the Effective
Date
Since there are currently no domestic
operators of this product, we find good
cause that notice and opportunity for
prior public comment are unnecessary.
In addition, for the reason(s) stated
above, we find that good cause exists for
making this amendment effective in less
than 30 days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not precede it by notice and
opportunity for public comment. We
invite you to send any written relevant
data, views, or arguments about this AD.
Send your comments to an address
listed under the ADDRESSES section.
Include ‘‘Docket No. FAA–2018–0305;
Product Identifier 2013–NM–226–AD’’
at the beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
this AD. We will consider all comments
received by the closing date and may
amend this AD based on 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 AD.
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Federal Register / Vol. 83, No. 83 / Monday, April 30, 2018 / Rules and Regulations
Costs of Compliance
Currently, there are no affected U.S.registered airplanes. This AD requires
contacting the FAA to obtain
instructions for addressing the unsafe
condition, and doing the actions
specified in those instructions. Based on
18729
the actions specified in the MCAI AD,
we are providing the following cost
estimates for an affected airplane that is
placed on the U.S. Register in the future:
ESTIMATED COSTS
Action
Labor cost
Inspection [new action] ...................................
9 work-hours × $85 per hour = $765 .............
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in the MCAI 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.
This AD is issued in accordance with
authority delegated by the Executive
Director, Aircraft Certification Service,
as authorized by FAA Order 8000.51C.
In accordance with that order, issuance
of ADs is normally a function of the
Compliance and Airworthiness
Division, but during this transition
period, the Executive Director has
delegated the authority to issue ADs
applicable to transport category
airplanes to the Director of the System
Oversight Division.
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Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
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17:01 Apr 27, 2018
Jkt 244001
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.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
[Amended]
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
2009–11–08, Amendment 39–15918 (74
FR 25404, May 28, 2009), and adding
the following new AD:
■
2018–09–03 Airbus: Amendment 39–19259;
Docket No. FAA–2018–0305; Product
Identifier 2013–NM–226–AD.
(a) Effective Date
This AD becomes effective May 15, 2018.
(b) Affected ADs
This AD replaces AD 2009–11–08,
Amendment 39–15918 (74 FR 25404, May 28,
2009) (‘‘AD 2009–11–08’’).
(c) Applicability
This AD applies to Airbus Model A330–
202, –223, –243, –301, –322, and –342
airplanes, certificated in any category,
manufacturer serial numbers: 0177, 0181,
0183, 0184, 0188, 0189, 0191, 0195, 0198,
0200, 0203, 0205, 0206, 0209, 0211, 0219,
0222, 0223, 0224, 0226, 0229, 0230, 0231,
0232, 0234, 0238, 0240, 0241, 0244, 0247,
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Fmt 4700
Sfmt 4700
$0
Cost on U.S.
operators
$765
$0
0248, 0249, 0250, 0251, 0253, 0254, and
0255.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by reports of cracks
on the left- and right-hand sides between the
crossing area of the keel angle fitting and the
front spar of the center wing box and by a
new fatigue and damage tolerance evaluation
that concluded the current inspection
thresholds and intervals had to be modified.
We are issuing this AD to detect and correct
cracking on the left- and right-hand sides
between the crossing area of the keel angle
fitting and the front spar of the center wing
box, which if not corrected, could affect the
structural integrity of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
■
§ 39.13
Cost per
product
Parts cost
Within 30 days after the effective date of
this AD, request instructions from the
Manager, International Section, Transport
Standards Branch, FAA, to address the
unsafe condition specified in paragraph (e) of
this AD; and accomplish the actions at the
times specified in, and in accordance with,
those instructions. Guidance can be found in
Mandatory Continuing Airworthiness
Information (MCAI) European Aviation
Safety Agency (EASA) AD 2013–0247, dated
October 10, 2013.
(h) Alternative Methods of Compliance
(AMOCs)
The Manager, International Section,
Transport Standards Branch, FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the International Section, send it to the
attention of the person identified in
paragraph (i)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. 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.
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Federal Register / Vol. 83, No. 83 / Monday, April 30, 2018 / Rules and Regulations
(i) Related Information
(1) Refer to MCAI EASA AD 2013–0247,
dated October 10, 2013, for related
information. You may examine the MCAI on
the internet at https://www.regulations.gov by
searching for and locating Docket No. FAA–
2018–0305.
(2) For more information about this AD,
contact Vladimir Ulyanov, Aerospace
Engineer, International Section, Transport
Standards Branch, FAA, 2200 South 216th
Street, Des Moines, WA 98198; telephone
and fax: 206–231–3229.
(j) Material Incorporated by Reference
None.
Issued in Des Moines, Washington, on
April 17, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–08654 Filed 4–27–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0302; Product
Identifier 2013–NM–228–AD; Amendment
39–19258; AD 2018–09–02]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are superseding
Airworthiness Directive (AD) 99–23–16,
which applied to certain Airbus Model
A330 and A340 series airplanes. AD 99–
23–16 required repetitive detailed visual
inspections to detect cracking of the
vertical flange of the inboard
Z-stiffeners of the centerline panel of
the fuselage belly fairing; and corrective
actions, if necessary. This AD was
prompted by a new fatigue and damage
tolerance evaluation that concluded that
the current inspection thresholds and
intervals had to be more restrictive. This
AD requires contacting the FAA to
obtain instructions for addressing the
unsafe condition on these products, and
doing the actions specified in those
instructions. We are issuing this AD to
address the unsafe condition on these
products.
DATES: This AD becomes effective May
15, 2018.
We must receive comments on this
AD by June 14, 2018.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
sradovich on DSK3GMQ082PROD with RULES
SUMMARY:
VerDate Sep<11>2014
17:01 Apr 27, 2018
Jkt 244001
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: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE, Washington, DC, between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays.
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–2018–
0302; or in person at the Docket
Operations office between 9 a.m. and
5 p.m., Monday through Friday, except
Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone:
800–647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 2200 South
216th Street, Des Moines, WA 98198;
telephone and fax: 206–231–3229.
SUPPLEMENTARY INFORMATION:
Discussion
We issued AD 99–23–16, Amendment
39–11412 (64 FR 61485, November 12,
1999) (‘‘AD 99–23–16’’), which applied
to certain Airbus Model A330 and A340
series airplanes. AD 99–23–16 was
prompted by issuance of mandatory
continuing airworthiness information by
a foreign civil aviation authority. AD
99–23–16 required repetitive detailed
visual inspections to detect cracking of
the vertical flange of the inboard
Z-stiffeners of the centerline panel of
the fuselage belly fairing; and corrective
actions, if necessary. We issued AD 99–
23–16 to detect and correct fatigue
cracking of the vertical flange of the
inboard Z-stiffeners of the centerline
panel of the fuselage belly fairing,
which could result in reduced structural
integrity of the belly fairing.
Since we issued AD 99–23–16, a new
fatigue and damage tolerance evaluation
was conducted by the manufacturer. It
was concluded that, due to airplane
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Sfmt 4700
utilization, the current inspection
thresholds and intervals had to be more
restrictive.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2013–0241,
dated October 1, 2013 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Airbus Model A330 and
A340 series airplanes. The MCAI states:
In order to prevent a damage in the inboard
Z profile at the Center Landing Gear (CLG)
door fitting location (Frame 49 to 53.2)
caused by cracks evidenced during fatigue
tests and which could lead to a reduced
structural integrity, DGAC France AD 96–
056–029(B) and DGAC France AD 96–057–
042(B) [which corresponds to FAA AD 99–
23–16] were issued to require a repetitive
inspection of the inboard Z profile on both
Left Hand (LH) and Right Hand (RH) sides.
An optional terminating action of the
repetitive inspection of this [EASA] AD
exists by modification of the aeroplane in
accordance with the instructions of Airbus
Service Bulletin (SB) A330–53–3019 or
Airbus SB A340–53–4028, as applicable.
Since those [EASA] ADs were issued, in
the frame of a new fatigue and damage
tolerance evaluation, taking into account the
aeroplane utilisation, the threshold and
intervals were reassessed. This resulted in
the conclusion that, in this specific case,
certain thresholds and intervals are more
restrictive.
For the reasons described above, this
[EASA] AD retains the requirements of both
DGAC France AD 96–056–029(B) and DGAC
France AD 96–057–042(B), which are
superseded, and requires accomplishment of
repetitive inspections of the inboard Z profile
(LH/RH) within the new thresholds and
intervals.
You may examine the MCAI on the
internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2018–0302.
FAA’s Determination and Requirements
of This AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI. We are issuing this AD because
we evaluated all pertinent information
and determined the unsafe condition
exists and is likely to exist or develop
on other products of these same type
designs.
FAA’s Determination of the Effective
Date
Since there are currently no domestic
operators of this product, we find good
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]]>Agencies
[Federal Register Volume 83, Number 83 (Monday, April 30, 2018)]
[Rules and Regulations]
[Pages 18727-18730]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-08654]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0305; Product Identifier 2013-NM-226-AD; Amendment
39-19259; AD 2018-09-03]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
[[Page 18728]]
ACTION: Final rule; request for comments.
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SUMMARY: We are superseding Airworthiness Directive (AD) 2009-11-08,
which applied to certain Airbus Model A330-202, -223, -243, -301, -322,
and -342 airplanes. AD 2009-11-08 required repetitive special detailed
(high frequency eddy current) inspections to detect cracking of the
keel beam fitting horizontal flange edge at a certain frame (FR) on the
left- and right-hand sides of the fuselage, and repair if necessary.
This AD was prompted by a new fatigue and damage tolerance evaluation
that concluded the current inspection thresholds and intervals had to
be modified. This AD requires contacting the FAA to obtain instructions
for addressing the unsafe condition on these products, and doing the
actions specified in those instructions. We are issuing this AD to
address the unsafe condition on these products.
DATES: This AD becomes effective May 15, 2018.
We must receive comments on this AD by June 14, 2018.
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: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
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-2018-
0305; or in person at the Docket Operations office between 9 a.m. and 5
p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the regulatory evaluation, any comments received, and
other information. The street address for the Docket Operations office
(telephone: 800-647-5527) is in the ADDRESSES section. Comments will be
available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 2200 South
216th Street, Des Moines, WA 98198; telephone and fax: 206-231-3229.
SUPPLEMENTARY INFORMATION:
Discussion
We issued AD 2009-11-08, Amendment 39-15918 (74 FR 25404, May 28,
2009) (``AD 2009-11-08''), which applied to certain Airbus Model A330-
202, -223, -243, -301, -322, and -342 airplanes. AD 2009-11-08 was
prompted by reports of cracks on the left- and right-hand sides between
the crossing area of the keel angle fitting and the front spar of the
center wing box. AD 2009-11-08 required a special detailed (high
frequency eddy current) inspection to detect cracking of the keel beam
fitting horizontal flange edge at FR40 on the left- and right-hand
sides of the fuselage, and repair if necessary. We issued AD 2009-11-08
to detect and correct cracking on the left- and right-hand sides,
between the crossing area of the keel angle fitting and the front spar
of the center wing box, which if not corrected, could affect the
structural integrity of the airplane.
Since we issued AD 2009-11-08, a new fatigue and damage tolerance
evaluation was conducted by the manufacturer. It was concluded that,
due to airplane utilization, the current inspection thresholds and
intervals had to be modified.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2013-0247, dated October 10, 2013 (referred to after this as the
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to
correct an unsafe condition for certain Airbus Model A330-202, -223, -
243, -301, -322, and -342 airplanes. The MCAI states:
During the A330 and A340 aeroplane fatigue test, cracks appeared
on the right and left sides between the crossing area of the keel
angle fitting and the front spar of the Centre Wing Box (CWB).
Several modifications were introduced in the fleet in the area of
frame (FR) 40 keel angle assembly in order to prevent these cracks.
However, the new design caused interference between one fastener and
the keel angle which was corrected by further local reprofiling of
the keel angle horizontal flange.
This condition, if not detected and corrected, could result in
reduced structural integrity of the area.
Prompted by these findings, EASA issued AD 2008-0213 [which
corresponds to FAA AD 2009-11-08] to require accomplishment of
repetitive special detailed inspection on the horizontal flange of
the keel beam in the area of first fastener hole aft of FR40 and,
depending on findings, accomplishment of a repair.
Since that [EASA] AD was issued, a new fatigue and damage
tolerance evaluation was conducted by Airbus. It was concluded that,
due to aeroplane utilisation, the current inspection thresholds and
intervals had to be modified.
For the reason described above, this [EASA] AD retains the
requirements of EASA AD 2008-0213, which is superseded, and
redefines the thresholds and intervals.
You may examine the MCAI on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0305.
FAA's Determination and Requirements of This AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI. We are
issuing this AD because we evaluated all pertinent information and
determined the unsafe condition exists and is likely to exist or
develop on other products of the same type design.
FAA's Determination of the Effective Date
Since there are currently no domestic operators of this product, we
find good cause that notice and opportunity for prior public comment
are unnecessary. In addition, for the reason(s) stated above, we find
that good cause exists for making this amendment effective in less than
30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not precede it by notice and opportunity for public
comment. We invite you to send any written relevant data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include ``Docket No. FAA-2018-0305; Product
Identifier 2013-NM-226-AD'' at the beginning of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this AD. We will consider all
comments received by the closing date and may amend this AD based on
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 AD.
[[Page 18729]]
Costs of Compliance
Currently, there are no affected U.S.-registered airplanes. This AD
requires contacting the FAA to obtain instructions for addressing the
unsafe condition, and doing the actions specified in those
instructions. Based on the actions specified in the MCAI AD, we are
providing the following cost estimates for an affected airplane that is
placed on the U.S. Register in the future:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Inspection [new action]............... 9 work-hours x $85 per $0 $765 $0
hour = $765.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in the MCAI 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.
This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to transport category airplanes to
the Director of the System Oversight Division.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under 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.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing airworthiness directive (AD)
2009-11-08, Amendment 39-15918 (74 FR 25404, May 28, 2009), and adding
the following new AD:
2018-09-03 Airbus: Amendment 39-19259; Docket No. FAA-2018-0305;
Product Identifier 2013-NM-226-AD.
(a) Effective Date
This AD becomes effective May 15, 2018.
(b) Affected ADs
This AD replaces AD 2009-11-08, Amendment 39-15918 (74 FR 25404,
May 28, 2009) (``AD 2009-11-08'').
(c) Applicability
This AD applies to Airbus Model A330-202, -223, -243, -301, -
322, and -342 airplanes, certificated in any category, manufacturer
serial numbers: 0177, 0181, 0183, 0184, 0188, 0189, 0191, 0195,
0198, 0200, 0203, 0205, 0206, 0209, 0211, 0219, 0222, 0223, 0224,
0226, 0229, 0230, 0231, 0232, 0234, 0238, 0240, 0241, 0244, 0247,
0248, 0249, 0250, 0251, 0253, 0254, and 0255.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by reports of cracks on the left- and
right-hand sides between the crossing area of the keel angle fitting
and the front spar of the center wing box and by a new fatigue and
damage tolerance evaluation that concluded the current inspection
thresholds and intervals had to be modified. We are issuing this AD
to detect and correct cracking on the left- and right-hand sides
between the crossing area of the keel angle fitting and the front
spar of the center wing box, which if not corrected, could affect
the structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
Within 30 days after the effective date of this AD, request
instructions from the Manager, International Section, Transport
Standards Branch, FAA, to address the unsafe condition specified in
paragraph (e) of this AD; and accomplish the actions at the times
specified in, and in accordance with, those instructions. Guidance
can be found in Mandatory Continuing Airworthiness Information
(MCAI) European Aviation Safety Agency (EASA) AD 2013-0247, dated
October 10, 2013.
(h) Alternative Methods of Compliance (AMOCs)
The Manager, International Section, Transport Standards Branch,
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. In accordance with 14
CFR 39.19, send your request to your principal inspector or local
Flight Standards District Office, as appropriate. If sending
information directly to the International Section, send it to the
attention of the person identified in paragraph (i)(2) of this AD.
Information may be emailed to: [email protected].
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.
[[Page 18730]]
(i) Related Information
(1) Refer to MCAI EASA AD 2013-0247, dated October 10, 2013, for
related information. You may examine the MCAI on the internet at
https://www.regulations.gov by searching for and locating Docket No.
FAA-2018-0305.
(2) For more information about this AD, contact Vladimir
Ulyanov, Aerospace Engineer, International Section, Transport
Standards Branch, FAA, 2200 South 216th Street, Des Moines, WA
98198; telephone and fax: 206-231-3229.
(j) Material Incorporated by Reference
None.
Issued in Des Moines, Washington, on April 17, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-08654 Filed 4-27-18; 8:45 am]
BILLING CODE 4910-13-P
