Airworthiness Directives; Airbus Airplanes, 33002-33004 [2017-14588]
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33002
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Federal Register / Vol. 82, No. 137 / Wednesday, July 19, 2017 / Rules and Regulations
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Dated at Rockville, Maryland, this 10th day
of July 2017.
For the Nuclear Regulatory Commission.
Cindy Bladey,
Chief, Rules, Announcements and Directives
Branch, Division of Administrative Services,
Office of Administration.
[FR Doc. 2017–14717 Filed 7–18–17; 8:45 am]
BILLING CODE 7590–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9498; Directorate
Identifier 2016–NM–105–AD; Amendment
39–18958; AD 2017–14–14]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
Airbus Model A321 series airplanes.
This AD was prompted by a
determination from fatigue testing that
cracks could develop in the cabin floor
beam junction at certain fuselage frame
locations. This AD requires repetitive
inspections for cracking in the cabin
floor beam junction at certain fuselage
frame locations, and repair if necessary.
We are issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective August 23,
2017.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of August 23, 2017.
ADDRESSES: For service information
identified in this final rule, 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. It is also available on the Internet
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2016–9498.
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SUMMARY:
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Jkt 241001
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–
9498; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Office (telephone: 800–647–
5527) is Docket Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
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:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all Airbus Model A321 series
airplanes. The NPRM published in the
Federal Register on December 16, 2016
(81 FR 91060). The NPRM was
prompted by a determination from
fatigue testing on the Model A321
airframe that cracks could develop in
the cabin floor beam junction at certain
fuselage frame locations. The NPRM
proposed to require repetitive
inspections for cracking in the cabin
floor beam junction at certain fuselage
frame locations, and repair if necessary.
We are issuing this AD to detect and
correct cracking in the cabin floor beam
junction at certain fuselage frame
locations, which could result in reduced
structural integrity of the airplane.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2016–0105,
dated June 6, 2016 (referred to after this
as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
on 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 in the cabin floor beam junctions at
fuselage frame (FR) 35.1 and FR 35.2, on both
left hand (LH) and right hand (RH) sides, also
on aeroplanes operated in the context of
design service goal.
PO 00000
Frm 00016
Fmt 4700
Sfmt 4700
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–
1317, SB A320–53–1318, SB A320–53–1319,
and SB A320–53–1320, each containing
instructions for a different location.
For the reasons described above, this
[EASA] AD requires repetitive detailed
inspections (DET) of the affected cabin floor
beam junctions [for cracking] and, depending
on findings, accomplishment of a repair.
This [EASA] AD is considered an interim
action, pending development of a permanent
solution.
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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–
9498.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comment
received on the NPRM and the FAA’s
response.
Request To Use Later Approved Service
Information Revisions
Delta Airlines (DAL) requested that
we revise the proposed AD to permit
use of later approved revisions of
service information as we have done in
previous alternative methods of
compliance (AMOCs). DAL stated that
Airbus service bulletins are EASA
approved, and through the bi-lateral
agreement with the European Union,
these subsequent service bulletin
revisions should be allowed to be used
by U.S. operators without seeking an
AMOC. DAL also explained that having
the ability to utilize future service
bulletin revisions without seeking an
AMOC is more efficient and preserves
the required level of safety. DAL added
that they operate airplanes that are not
listed in the service bulletin
applicability, but are included in the
proposed AD. DAL claimed that without
a provision allowing later approved
revisions, they might have to apply for
multiple AMOCs as the service
information is updated.
We do not agree with DAL’s request.
We may not refer to any document that
does not yet exist in an AD. In general
terms, we are required by Office of the
Federal Register (OFR) regulations to
either publish the service document
contents as part of the actual AD
language; or submit the service
document to the OFR for approval as
‘‘referenced’’ material, in which case we
may only refer to such material in the
text of an AD. The AD may refer to the
E:\FR\FM\19JYR1.SGM
19JYR1
Federal Register / Vol. 82, No. 137 / Wednesday, July 19, 2017 / Rules and Regulations
service document only if the OFR
approved it for ‘‘incorporation by
reference.’’ See 1 CFR part 51.
To allow operators to use later
revisions of the referenced document
(issued after publication of the AD),
either we must revise the AD to
reference specific later revisions, or
operators must request approval to use
later revisions as an AMOC under the
provisions of paragraph (i)(1) of this AD.
In addition, in accordance with 14
CFR part 39.27, if there is a conflict
between an AD and service information,
operators must follow the requirements
of the AD. We have not changed this AD
in this regard.
Conclusion
We reviewed the relevant data,
considered the comment received, and
determined that air safety and the
public interest require adopting this AD
33003
• Airbus Service Bulletin A320–53–
1317, dated December 15, 2015 (FR 35.1
on the right-hand side).
• Airbus Service Bulletin A320–53–
1318, dated October 9, 2015 (FR 35.1 on
the left-hand side).
• Airbus Service Bulletin A320–53–
1319, dated October 9, 2015 (FR 35.2 on
the right-hand side).
• Airbus Service Bulletin A320–53–
1320, dated October 9, 2015 (FR 35.2 on
the left-hand side).
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.
as proposed except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Related Service Information Under 1
CFR Part 51
We reviewed the following service
information, which describes
procedures for inspections for cracking
on the frame to cabin floor beam
junction at certain fuselage frame
locations, and repairs. This service
information is distinct because it
applies to different locations on the
airplanes.
Costs of Compliance
We estimate that this AD affects 175
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Inspection .........
6 work-hours × $85 per hour = $510 per inspection
cycle.
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this AD.
Authority for This Rulemaking
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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 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,
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16:17 Jul 18, 2017
Jkt 241001
Parts cost
Cost per product
$0
$510 per inspection cycle
Cost on U.S. operators
$89,250 per inspection
cycle.
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.
§ 39.13
List of Subjects in 14 CFR Part 39
(d) Subject
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Air Transport Association (ATA) of
America Code 53, Fuselage.
Adoption of the Amendment
This AD was prompted by a determination
from fatigue testing on the Model A321
airframe that cracks could develop in the
cabin floor beam junction at certain fuselage
frame locations. We are issuing this AD to
detect and correct cracking in the cabin floor
beam junction at certain fuselage frame
locations, which could result in reduced
structural integrity of the airplane.
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:
■
PO 00000
Authority: 49 U.S.C. 106(g), 40113, 44701.
Frm 00017
Fmt 4700
Sfmt 4700
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2017–14–14 Airbus: Amendment 39–18958;
Docket No. FAA–2016–9498; Directorate
Identifier 2016–NM–105–AD.
(a) Effective Date
This AD is effective August 23, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A321–
111, –112, –131, –211, –212, –213, –231, and
–232 airplanes, certificated in any category,
all manufacturer serial numbers.
(e) Reason
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
E:\FR\FM\19JYR1.SGM
19JYR1
33004
Federal Register / Vol. 82, No. 137 / Wednesday, July 19, 2017 / Rules and Regulations
(g) Repetitive Inspections
Before exceeding 36,900 total flight cycles
since first flight of the airplane, or within
2,100 flight cycles after the effective date of
this AD, whichever occurs later: Do a
detailed inspection for cracking of the frame
to cabin floor beam junction on the aft and
forward sides at frame (FR) 35.1 and FR 35.2
on the left-hand and right-hand sides, in
accordance with the Accomplishment
Instructions of the Airbus service information
specified in paragraphs (g)(1), (g)(2), (g)(3),
and (g)(4) of this AD. Repeat the inspection
of the frame to cabin floor beam junction on
the aft and forward sides at FR 35.1 and FR
35.2 on the left-hand and right-hand sides
thereafter at intervals not to exceed 15,300
flight cycles.
(1) Airbus Service Bulletin A320–53–1317,
dated December 15, 2015 (FR 35.1 right-hand
side).
(2) Airbus Service Bulletin A320–53–1318,
dated October 9, 2015 (FR 35.1 left-hand
side).
(3) Airbus Service Bulletin A320–53–1319,
dated October 9, 2015 (FR 35.2 right-hand
side).
(4) Airbus Service Bulletin A320–53–1320,
dated October 9, 2015 (FR 35.2 left-hand
side).
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(h) Repair
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 actions required by paragraph (g) of
this AD, unless otherwise specified in the
instructions provided 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 the
attention of the person identified in
paragraph (j)(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
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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
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 AD
2016–0105, dated June 6, 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–2016–9498.
(2) For more information about this AD,
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. Information may be emailed to: 9ANM-116-AMOC-REQUESTS@faa.gov.
(3) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (k)(3) and (k)(4) of this AD.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A320–53–1317,
dated December 15, 2015.
(ii) Airbus Service Bulletin A320–53–1318,
dated October 9, 2015.
(iii) Airbus Service Bulletin A320–53–
1319, dated October 9, 2015.
(iv) Airbus Service Bulletin A320–53–
1320, dated October 9, 2015.
(3) For service information identified in
this AD, 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.airwortheas@airbus.com; Internet: https://
www.airbus.com.
(4) You may view this service information
at the FAA, Transport Airplane Directorate,
PO 00000
Frm 00018
Fmt 4700
Sfmt 4700
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on June 29,
2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–14588 Filed 7–18–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9389; Directorate
Identifier 2014–NM–153–AD; Amendment
39–18953; AD 2017–14–09]
RIN 2120–AA64
Airworthiness Directives; Fokker
Services B.V. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
Fokker Services B.V. Model F28 Mark
0100 airplanes. This AD was prompted
by an evaluation by the design approval
holder (DAH) indicating that certain
wing fuel tank access panels are subject
to widespread fatigue damage (WFD).
This AD requires replacement of
affected access panels and modification
of the coamings of the associated access
holes. We are issuing this AD to address
the unsafe condition on these products.
DATES: This AD is effective August 23,
2017.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of August 23, 2017.
ADDRESSES: For service information
identified in this final rule, contact
Fokker Services B.V., Technical
Services Dept., P.O. Box 1357, 2130 EL
Hoofddorp, the Netherlands; telephone:
+31 (0)88–6280–350; fax: +31 (0)88–
6280–111; email: technicalservices@
fokker.com; Internet: https://
www.myfokkerfleet.com. You may view
this referenced service information at
the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW.,
SUMMARY:
E:\FR\FM\19JYR1.SGM
19JYR1
Agencies
[Federal Register Volume 82, Number 137 (Wednesday, July 19, 2017)]
[Rules and Regulations]
[Pages 33002-33004]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-14588]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9498; Directorate Identifier 2016-NM-105-AD;
Amendment 39-18958; AD 2017-14-14]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all
Airbus Model A321 series airplanes. This AD was prompted by a
determination from fatigue testing that cracks could develop in the
cabin floor beam junction at certain fuselage frame locations. This AD
requires repetitive inspections for cracking in the cabin floor beam
junction at certain fuselage frame locations, and repair if necessary.
We are issuing this AD to address the unsafe condition on these
products.
DATES: This AD is effective August 23, 2017.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of August 23,
2017.
ADDRESSES: For service information identified in this final rule,
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. It is also available on the
Internet at https://www.regulations.gov by searching for and locating
Docket No. FAA-2016-9498.
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-
9498; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the regulatory evaluation, any comments received, and
other information. The street address for the Docket Office (telephone:
800-647-5527) is Docket Management Facility, U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: 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:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to all Airbus Model A321
series airplanes. The NPRM published in the Federal Register on
December 16, 2016 (81 FR 91060). The NPRM was prompted by a
determination from fatigue testing on the Model A321 airframe that
cracks could develop in the cabin floor beam junction at certain
fuselage frame locations. The NPRM proposed to require repetitive
inspections for cracking in the cabin floor beam junction at certain
fuselage frame locations, and repair if necessary. We are issuing this
AD to detect and correct cracking in the cabin floor beam junction at
certain fuselage frame locations, which could result in reduced
structural integrity of the airplane.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2016-0105, dated June 6, 2016 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ``the MCAI''), to correct an
unsafe condition on 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 in the cabin floor
beam junctions at fuselage frame (FR) 35.1 and FR 35.2, on both left
hand (LH) and right hand (RH) sides, also on aeroplanes operated in
the context of design service goal.
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) A320-53-1317, SB A320-
53-1318, SB A320-53-1319, and SB A320-53-1320, each containing
instructions for a different location.
For the reasons described above, this [EASA] AD requires
repetitive detailed inspections (DET) of the affected cabin floor
beam junctions [for cracking] and, depending on findings,
accomplishment of a repair.
This [EASA] AD is considered an interim action, pending
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-
9498.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comment received on the NPRM and
the FAA's response.
Request To Use Later Approved Service Information Revisions
Delta Airlines (DAL) requested that we revise the proposed AD to
permit use of later approved revisions of service information as we
have done in previous alternative methods of compliance (AMOCs). DAL
stated that Airbus service bulletins are EASA approved, and through the
bi-lateral agreement with the European Union, these subsequent service
bulletin revisions should be allowed to be used by U.S. operators
without seeking an AMOC. DAL also explained that having the ability to
utilize future service bulletin revisions without seeking an AMOC is
more efficient and preserves the required level of safety. DAL added
that they operate airplanes that are not listed in the service bulletin
applicability, but are included in the proposed AD. DAL claimed that
without a provision allowing later approved revisions, they might have
to apply for multiple AMOCs as the service information is updated.
We do not agree with DAL's request. We may not refer to any
document that does not yet exist in an AD. In general terms, we are
required by Office of the Federal Register (OFR) regulations to either
publish the service document contents as part of the actual AD
language; or submit the service document to the OFR for approval as
``referenced'' material, in which case we may only refer to such
material in the text of an AD. The AD may refer to the
[[Page 33003]]
service document only if the OFR approved it for ``incorporation by
reference.'' See 1 CFR part 51.
To allow operators to use later revisions of the referenced
document (issued after publication of the AD), either we must revise
the AD to reference specific later revisions, or operators must request
approval to use later revisions as an AMOC under the provisions of
paragraph (i)(1) of this AD.
In addition, in accordance with 14 CFR part 39.27, if there is a
conflict between an AD and service information, operators must follow
the requirements of the AD. We have not changed this AD in this regard.
Conclusion
We reviewed the relevant data, considered the comment received, and
determined that air safety and the public interest require adopting
this AD as proposed except for minor editorial changes. We have
determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Related Service Information Under 1 CFR Part 51
We reviewed the following service information, which describes
procedures for inspections for cracking on the frame to cabin floor
beam junction at certain fuselage frame locations, and repairs. This
service information is distinct because it applies to different
locations on the airplanes.
Airbus Service Bulletin A320-53-1317, dated December 15,
2015 (FR 35.1 on the right-hand side).
Airbus Service Bulletin A320-53-1318, dated October 9,
2015 (FR 35.1 on the left-hand side).
Airbus Service Bulletin A320-53-1319, dated October 9,
2015 (FR 35.2 on the right-hand side).
Airbus Service Bulletin A320-53-1320, dated October 9,
2015 (FR 35.2 on the left-hand side).
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.
Costs of Compliance
We estimate that this AD affects 175 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection............... 6 work-hours x $85 per $0 $510 per inspection $89,250 per
hour = $510 per cycle. inspection cycle.
inspection cycle.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this 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 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 adding the following new airworthiness
directive (AD):
2017-14-14 Airbus: Amendment 39-18958; Docket No. FAA-2016-9498;
Directorate Identifier 2016-NM-105-AD.
(a) Effective Date
This AD is effective August 23, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A321-111, -112, -131, -211, -
212, -213, -231, and -232 airplanes, certificated in any category,
all manufacturer serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by a determination from fatigue testing on
the Model A321 airframe that cracks could develop in the cabin floor
beam junction at certain fuselage frame locations. We are issuing
this AD to detect and correct cracking in the cabin floor beam
junction at certain fuselage frame locations, which could result in
reduced structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
[[Page 33004]]
(g) Repetitive Inspections
Before exceeding 36,900 total flight cycles since first flight
of the airplane, or within 2,100 flight cycles after the effective
date of this AD, whichever occurs later: Do a detailed inspection
for cracking of the frame to cabin floor beam junction on the aft
and forward sides at frame (FR) 35.1 and FR 35.2 on the left-hand
and right-hand sides, in accordance with the Accomplishment
Instructions of the Airbus service information specified in
paragraphs (g)(1), (g)(2), (g)(3), and (g)(4) of this AD. Repeat the
inspection of the frame to cabin floor beam junction on the aft and
forward sides at FR 35.1 and FR 35.2 on the left-hand and right-hand
sides thereafter at intervals not to exceed 15,300 flight cycles.
(1) Airbus Service Bulletin A320-53-1317, dated December 15,
2015 (FR 35.1 right-hand side).
(2) Airbus Service Bulletin A320-53-1318, dated October 9, 2015
(FR 35.1 left-hand side).
(3) Airbus Service Bulletin A320-53-1319, dated October 9, 2015
(FR 35.2 right-hand side).
(4) Airbus Service Bulletin A320-53-1320, dated October 9, 2015
(FR 35.2 left-hand side).
(h) Repair
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 actions required by paragraph
(g) of this AD, unless otherwise specified in the instructions
provided 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 the attention of
the person identified in paragraph (j)(2) of this AD. 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 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 AD 2016-0105, dated June 6, 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-2016-9498.
(2) For more information about this AD, 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. Information may be
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.
(3) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (k)(3) and (k)(4) of this AD.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A320-53-1317, dated December 15,
2015.
(ii) Airbus Service Bulletin A320-53-1318, dated October 9,
2015.
(iii) Airbus Service Bulletin A320-53-1319, dated October 9,
2015.
(iv) Airbus Service Bulletin A320-53-1320, dated October 9,
2015.
(3) For service information identified in this AD, 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.
(4) 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.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on June 29, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-14588 Filed 7-18-17; 8:45 am]
BILLING CODE 4910-13-P