Airworthiness Directives; Airbus Airplanes, 11162-11164 [2017-03031]
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11162
Federal Register / Vol. 82, No. 33 / Tuesday, February 21, 2017 / Proposed Rules
ADAMS accession No./Web link/Federal
Register citation
Document
SECY–15–0065, ‘‘Proposed Rulemaking: Mitigation of Beyond-Design-Basis Events (RIN 3150–
AJ49),’’ April 30, 2015.
SECY–15–0137, ‘‘Proposed Plans for Resolving Open Fukushima Tier 2 and 3 Recommendations,’’
October 29, 2015.
SECY–16–0041, ‘‘Closure of Fukushima Tier 3 Recommendations Related to Containment Vents,
Hydrogen Control, and Enhanced Instrumentation,’’ March 31, 2016.
SRM–SECY–15–0065, ‘‘Proposed Rulemaking: Mitigation of Beyond-Design-Basis Events (RIN
3150–AJ49),’’ August 27, 2015.
SRM–SECY–15–0137, ‘‘Proposed Plans for Resolving Open Fukushima Tier 2 and 3 Recommendations,’’ February 8, 2016.
Dated at Rockville, Maryland, this 14th day
of February 2017.
For the Nuclear Regulatory Commission.
Annette L. Vietti-Cook,
Secretary of the Commission.
[FR Doc. 2017–03284 Filed 2–17–17; 8:45 am]
BILLING CODE 7590–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9571; Directorate
Identifier 2016–NM–139–AD]
Examining the AD Docket
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for all
Airbus Model A321 series airplanes.
This proposed AD was prompted by a
full scale fatigue test campaign on these
airplanes in the context of the extended
service goal. This proposed AD would
require inspections of the affected frame
locations, and repair if necessary. We
are proposing this AD to address the
unsafe condition on these products.
DATES: We must receive comments on
this proposed AD by April 7, 2017.
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
rmajette on DSK2TPTVN1PROD with PROPOSALS
SUMMARY:
VerDate Sep<11>2014
14:44 Feb 17, 2017
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Airbus,
Airworthiness Office—EIAS, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com;
Internet https://www.airbus.com. You
may view this referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221.
Jkt 241001
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
9571; 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 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:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1405;
fax 425–227–1149.
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–2016–9571; Directorate Identifier
2016–NM–139–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
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Sfmt 4702
ML15049A201.
ML15254A006, ML15254A034 (enc. 5).
ML16049A079.
ML15239A767.
ML16039A175.
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed 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 proposed AD.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2016–0146, dated July 20,
2016 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for all Airbus
Model A321 series airplanes. The MCAI
states:
Following the results of a new full scale
fatigue test campaign on the A321 airframe
in the context of the A321 extended service
goal, it was identified that cracks could
develop on the fastener holes of frame (FR)
35.1, FR 35.2, and FR 35.3 between stringers
(STR) 29 and STR 32 and at the FR 35.2 to
Slidebox junction (Triform fitting), both left
hand (LH) and right hand (RH) sides.
This condition, if not detected and
corrected, could reduce the structural
integrity of the fuselage. Prompted by these
findings, Airbus developed an inspection
programme, published in Service Bulletin
(SB) A320–53–1308, SB A320–53–1309, SB
A320–53–1310, SB A320–53–1311, SB A320–
53–1312 and SB A320–53–1313, each
containing instructions for a different
location. For the reasons described above,
this [EASA] AD requires repetitive special
detailed (rototest) inspections (SDI) of the
affected frame locations and, depending on
findings, accomplishment of a repair.
This [EASA] AD is considered an interim
action, pending the development of a
permanent solution.
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
9571.
E:\FR\FM\21FEP1.SGM
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Federal Register / Vol. 82, No. 33 / Tuesday, February 21, 2017 / Proposed Rules
Related Service Information Under 1
CFR Part 51
We reviewed the following Airbus
service information. This service
information describes procedures for
repetitive rototest inspections for
cracking of the affected frame locations,
and contacting Airbus for repair
instructions. These service bulletins are
distinct because they apply to different
frame locations.
• Airbus Service Bulletin A320–53–
1308, dated November 4, 2015.
• Airbus Service Bulletin A320–53–
1309, dated November 4, 2015.
• Airbus Service Bulletin A320–53–
1310, dated November 4, 2015.
11163
• Airbus Service Bulletin A320–53–
1311, dated November 4, 2015.
• Airbus Service Bulletin A320–53–
1312, dated November 4, 2015.
• Airbus Service Bulletin A320–53–
1313, dated November 4, 2015.
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.
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 and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
FAA’s Determination and Requirements
of This Proposed AD
Costs of Compliance
This product has been approved by
the aviation authority of another
country, and is approved for operation
We estimate that this proposed AD
affects 176 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
Action
Labor cost
Parts cost
Inspection ...................
54 work-hours × $85 per hour = $4,590 per
inspection cycle.
$1,070 per inspection
cycle.
$5,660 per inspection
cycle.
We have no way to estimate the costs
to do any necessary repairs that would
be required based on the results of the
proposed inspection. We have no way of
determining the number of airplanes
that might need these repairs.
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.
14:44 Feb 17, 2017
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
1. The authority citation for part 39
continues to read as follows:
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
VerDate Sep<11>2014
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.
■
Regulatory Findings
rmajette on DSK2TPTVN1PROD with PROPOSALS
Cost on U.S.
operators
Cost per product
Jkt 241001
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):
■
Airbus: Docket No. FAA–2016–9571;
Directorate Identifier 2016–NM–139–AD.
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$996,160 per inspection cycle.
(a) Comments Due Date
We must receive comments by April 7,
2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Airbus Model A321–
111, –112, –131, –211, –212, –213, –231, and
–232 airplanes, certificated in any category.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by a full scale
fatigue test campaign on Airbus Model A321
series airplanes in the context of the
extended service goal. It was determined that
cracks could develop on the fastener holes of
certain frames on the left-hand (LH) and
right-hand (RH) sides of the affected
airplanes. We are issuing this AD to detect
and correct cracking of the fastener holes at
certain frame locations, which could result in
reduced structural integrity of the fuselage.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Inspections of the Frames,
Stringers, and Slidebox Junctions
At the applicable time specified in table 1
to paragraph (g) of this AD, do a rototest
inspection for cracking at frame (FR) 35.1, FR
35.2, and FR 35.3 on the LH and RH sides,
in accordance with the Accomplishment
Instructions of the Airbus service information
specified in paragraphs (g)(1), (g)(2), (g)(3),
(g)(4), (g)(5), and (g)(6) of this AD. Repeat the
inspection thereafter at intervals not to
exceed 5,300 flight cycles.
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Federal Register / Vol. 82, No. 33 / Tuesday, February 21, 2017 / Proposed Rules
(1) Airbus Service Bulletin A320–53–1308,
dated November 4, 2015 (FR 35.1 LH side).
(2) Airbus Service Bulletin A320–53–1309,
dated November 4, 2015 (FR 35.1 RH side).
(3) Airbus Service Bulletin A320–53–1310,
dated November 4, 2015 (FR 35.2 LH side).
(4) Airbus Service Bulletin A320–53–1311,
dated November 4, 2015 (FR 35.2 RH side).
(5) Airbus Service Bulletin A320–53–1312,
dated November 4, 2015 (FR 35.3 LH side).
(6) Airbus Service Bulletin A320–53–1313,
dated November 4, 2015 (FR 35.3 RH side).
TABLE 1 TO PARAGRAPH (g) OF THIS AD—INSPECTION THRESHOLD
Airplane accumulated total flight cycles at the effective
date of this AD
Compliance time
For airplanes with 18,300 total flight cycles or less ..........
Before exceeding 18,300 total flight cycles, or within 5,300 flight cycles after the effective date of this AD, whichever occurs later.
Before exceeding 23,600 total flight cycles, or within 2,100 flight cycles after the effective date of this AD, whichever occurs later.
For airplanes with more than 18,300 total flight cycles .....
rmajette on DSK2TPTVN1PROD with PROPOSALS
(h) Corrective Action
If any crack is found during any inspection
required by paragraph (g) of this AD: Before
further flight, repair using a method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or the European Aviation
Safety Agency (EASA); or Airbus’s EASA
Design Organization Approval (DOA).
Although the service information specified in
paragraph (g) of this AD specifies to contact
Airbus for repair instructions, and specifies
that action as ‘‘RC’’ (Required for
Compliance), this AD requires repair as
specified in this paragraph. Repair of an
airplane as required by this paragraph does
not constitute terminating action for the
repetitive inspections required by paragraph
(g) of this AD for that airplane, unless
specified otherwise in the repair instructions
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or EASA; or Airbus’s EASA
DOA.
(i) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, 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 Branch, send it to ATTN:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1405; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@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.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the EASA; or Airbus’s EASA DOA. If
approved by the DOA, the approval must
include the DOA-authorized signature.
VerDate Sep<11>2014
14:44 Feb 17, 2017
Jkt 241001
(3) Required for Compliance (RC): Except
as required by paragraph (h) of this AD: If
any service information contains procedures
or tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(j) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2016–0146, dated
July 20, 2016, for related information. This
MCAI may be found in the AD docket on the
Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA–
2016–9571.
(2) For service information identified in
this AD, contact Airworthiness Office—EIAS,
1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone +33 5 61
93 36 96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com; Internet
https://www.airbus.com. You may view this
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 January
11, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–03031 Filed 2–17–17; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF HEALTH AND
HUMAN SERVICES
42 CFR Part 88
[NIOSH Docket 094]
World Trade Center Health Program;
Petition 014—Autoimmune Diseases;
Finding of Insufficient Evidence
Centers for Disease Control and
Prevention, HHS.
ACTION: Denial of petition for addition of
a health condition.
AGENCY:
On September 29, 2016, the
Administrator of the World Trade
Center (WTC) Health Program received
a petition to add autoimmune diseases,
including rheumatoid arthritis, to the
List of WTC-Related Health Conditions
(List). Upon reviewing the information
provided by the petitioner, the
Administrator has determined that
Petition 014 is not substantially
different from Petitions 007, 008, 009,
011, and 013, which also requested the
addition of autoimmune diseases,
including various subtypes. The
Administrator has published responses
to the five previous petitions in the
Federal Register and has determined
that Petition 014 does not provide
additional evidence of a causal
relationship between 9/11 exposures
and autoimmune diseases, including
rheumatoid arthritis. Accordingly, the
Administrator finds that insufficient
evidence exists to request a
recommendation of the WTC Health
Program Scientific/Technical Advisory
Committee (STAC), to publish a
proposed rule, or to publish a
determination not to publish a proposed
rule.
DATES: The Administrator of the WTC
Health Program is denying this petition
for the addition of a health condition as
of February 21, 2017.
FOR FURTHER INFORMATION CONTACT:
Rachel Weiss, Program Analyst, 1090
Tusculum Avenue, MS: C–46,
Cincinnati, OH 45226; telephone (855)
SUMMARY:
E:\FR\FM\21FEP1.SGM
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Agencies
[Federal Register Volume 82, Number 33 (Tuesday, February 21, 2017)]
[Proposed Rules]
[Pages 11162-11164]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-03031]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9571; Directorate Identifier 2016-NM-139-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
Airbus Model A321 series airplanes. This proposed AD was prompted by a
full scale fatigue test campaign on these airplanes in the context of
the extended service goal. This proposed AD would require inspections
of the affected frame locations, and repair if necessary. We are
proposing this AD to address the unsafe condition on these products.
DATES: We must receive comments on this proposed AD by April 7, 2017.
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 NPRM, contact Airbus,
Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44
51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com. You may view this referenced service information at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA, call
425-227-1221.
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-2016-
9571; 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
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: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405;
fax 425-227-1149.
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-2016-9571;
Directorate Identifier 2016-NM-139-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 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 proposed AD.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2016-0146, dated July 20, 2016 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Airbus Model A321
series airplanes. The MCAI states:
Following the results of a new full scale fatigue test campaign
on the A321 airframe in the context of the A321 extended service
goal, it was identified that cracks could develop on the fastener
holes of frame (FR) 35.1, FR 35.2, and FR 35.3 between stringers
(STR) 29 and STR 32 and at the FR 35.2 to Slidebox junction (Triform
fitting), both left hand (LH) and right hand (RH) sides.
This condition, if not detected and corrected, could reduce the
structural integrity of the fuselage. Prompted by these findings,
Airbus developed an inspection programme, published in Service
Bulletin (SB) A320-53-1308, SB A320-53-1309, SB A320-53-1310, SB
A320-53-1311, SB A320-53-1312 and SB A320-53-1313, each containing
instructions for a different location. For the reasons described
above, this [EASA] AD requires repetitive special detailed
(rototest) inspections (SDI) of the affected frame locations and,
depending on findings, accomplishment of a repair.
This [EASA] AD is considered an interim action, pending the
development of a permanent solution.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9571.
[[Page 11163]]
Related Service Information Under 1 CFR Part 51
We reviewed the following Airbus service information. This service
information describes procedures for repetitive rototest inspections
for cracking of the affected frame locations, and contacting Airbus for
repair instructions. These service bulletins are distinct because they
apply to different frame locations.
Airbus Service Bulletin A320-53-1308, dated November 4,
2015.
Airbus Service Bulletin A320-53-1309, dated November 4,
2015.
Airbus Service Bulletin A320-53-1310, dated November 4,
2015.
Airbus Service Bulletin A320-53-1311, dated November 4,
2015.
Airbus Service Bulletin A320-53-1312, dated November 4,
2015.
Airbus Service Bulletin A320-53-1313, dated November 4,
2015.
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.
FAA's Determination and Requirements of This Proposed 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 and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Costs of Compliance
We estimate that this proposed AD affects 176 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection..................... 54 work-hours x $85 $1,070 per $5,660 per $996,160 per
per hour = $4,590 per inspection cycle. inspection cycle. inspection
inspection cycle. cycle.
----------------------------------------------------------------------------------------------------------------
We have no way to estimate the costs to do any necessary repairs
that would be required based on the results of the proposed inspection.
We have no way of determining the number of airplanes that might need
these repairs.
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):
Airbus: Docket No. FAA-2016-9571; Directorate Identifier 2016-NM-
139-AD.
(a) Comments Due Date
We must receive comments by April 7, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Airbus Model A321-111, -112, -131, -211,
-212, -213, -231, and -232 airplanes, certificated in any category.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by a full scale fatigue test campaign on
Airbus Model A321 series airplanes in the context of the extended
service goal. It was determined that cracks could develop on the
fastener holes of certain frames on the left-hand (LH) and right-
hand (RH) sides of the affected airplanes. We are issuing this AD to
detect and correct cracking of the fastener holes at certain frame
locations, which could result in reduced structural integrity of the
fuselage.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections of the Frames, Stringers, and Slidebox
Junctions
At the applicable time specified in table 1 to paragraph (g) of
this AD, do a rototest inspection for cracking at frame (FR) 35.1,
FR 35.2, and FR 35.3 on the LH and RH sides, in accordance with the
Accomplishment Instructions of the Airbus service information
specified in paragraphs (g)(1), (g)(2), (g)(3), (g)(4), (g)(5), and
(g)(6) of this AD. Repeat the inspection thereafter at intervals not
to exceed 5,300 flight cycles.
[[Page 11164]]
(1) Airbus Service Bulletin A320-53-1308, dated November 4, 2015
(FR 35.1 LH side).
(2) Airbus Service Bulletin A320-53-1309, dated November 4, 2015
(FR 35.1 RH side).
(3) Airbus Service Bulletin A320-53-1310, dated November 4, 2015
(FR 35.2 LH side).
(4) Airbus Service Bulletin A320-53-1311, dated November 4, 2015
(FR 35.2 RH side).
(5) Airbus Service Bulletin A320-53-1312, dated November 4, 2015
(FR 35.3 LH side).
(6) Airbus Service Bulletin A320-53-1313, dated November 4, 2015
(FR 35.3 RH side).
Table 1 to Paragraph (g) of This AD--Inspection Threshold
------------------------------------------------------------------------
Airplane accumulated total flight
cycles at the effective date of Compliance time
this AD
------------------------------------------------------------------------
For airplanes with 18,300 total Before exceeding 18,300 total flight
flight cycles or less. cycles, or within 5,300 flight
cycles after the effective date of
this AD, whichever occurs later.
For airplanes with more than Before exceeding 23,600 total flight
18,300 total flight cycles. cycles, or within 2,100 flight
cycles after the effective date of
this AD, whichever occurs later.
------------------------------------------------------------------------
(h) Corrective Action
If any crack is found during any inspection required by
paragraph (g) of this AD: Before further flight, repair using a
method approved by the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; or the European Aviation Safety
Agency (EASA); or Airbus's EASA Design Organization Approval (DOA).
Although the service information specified in paragraph (g) of this
AD specifies to contact Airbus for repair instructions, and
specifies that action as ``RC'' (Required for Compliance), this AD
requires repair as specified in this paragraph. Repair of an
airplane as required by this paragraph does not constitute
terminating action for the repetitive inspections required by
paragraph (g) of this AD for that airplane, unless specified
otherwise in the repair instructions approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or EASA; or Airbus's EASA DOA.
(i) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, 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 Branch, send it to ATTN: Sanjay
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; fax 425-227-1149. Information may be
emailed to: 9-ANM-116-AMOC-REQUESTS@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.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA;
or Airbus's EASA DOA. If approved by the DOA, the approval must
include the DOA-authorized signature.
(3) Required for Compliance (RC): Except as required by
paragraph (h) of this AD: If any service information contains
procedures or tests that are identified as RC, those procedures and
tests must be done to comply with this AD; any procedures or tests
that are not identified as RC are recommended. Those procedures and
tests that are not identified as RC may be deviated from using
accepted methods in accordance with the operator's maintenance or
inspection program without obtaining approval of an AMOC, provided
the procedures and tests identified as RC can be done and the
airplane can be put back in an airworthy condition. Any
substitutions or changes to procedures or tests identified as RC
require approval of an AMOC.
(j) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2016-0146, dated July 20, 2016,
for related information. This MCAI may be found in the AD docket on
the Internet at https://www.regulations.gov by searching for and
locating Docket No. FAA-2016-9571.
(2) For service information identified in this AD, contact
Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93
44 51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com. You may view this 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 January 11, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-03031 Filed 2-17-17; 8:45 am]
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